04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
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<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031637 1263343 ALBERTA INC DBA ENERJET TCCA STC C-LSA10-077/D ISSUE 1 B737-700 Bucher LH Windscreen /Closet Modification Limited to B737-700 aircraft S/N<br />
Prior to installation of this modification it <strong>01</strong>.09.2<strong>01</strong>0<br />
33920Maintenance of the Bucher Closet is to must be determined thatthe<br />
be performed by Boeing AircraftMaintenance interrelationship between this modification<br />
Manual D633A1<strong>01</strong>-CQT, and Bucher and any other previouslyinstalled<br />
Component MaintenanceManual 25-30-65 modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031638 1263343 ALBERTA INC DBA ENERJET TCCA STC C-LSA08-311/D ISSUE B737-700 131, 137 & 145 Passenger Seating<br />
Reconfiguration<br />
10031639 1263343 ALBERTA INC DBA ENERJET TCCA STC C-LSA08-310/D ISSUE B737-700 Artex C406-2 ELT Installation Limited to B737-700 aircraft S/N 33920 and<br />
34480<br />
10031640 1263343 ALBERTA INC DBA ENERJET TCCA STC C-LSA10-078/D ISSUE B737-700 TIA Model 1545 oven Installation in forward LH<br />
monument.<br />
10<strong>01</strong>4424 A&M AVIONICS, SL <strong>EASA</strong>.A.S.02469 PIPER PA-31-350 Verification of the B-RNAV<br />
Capability.Installation of GPS Modes Panel<br />
Annunciator.Installation of new XPDR Mode S<br />
Garmin GTX-330 and Encoder AK-350.<br />
10<strong>01</strong>4434 A&M AVIONICS, SL <strong>EASA</strong>.A.S.02483 CESSNA 4<strong>04</strong> Remove Weather Radar Bendix King RDS81.<br />
Install Weather Radar Bendix King DRD 2000<br />
with MFD Avidyne EX 500. Reinvestigation of<br />
DualGNS530 Installation according to A&M<br />
10<strong>01</strong>4788 A&M AVIONICS, SL <strong>EASA</strong>.A.S.02988 FAIRCHILD SWEARINGEN SA<br />
226-TC<br />
Avionics BI Nº <strong>01</strong>7/2006 for B-RNAV Approval,<br />
Model: Cessna 4<strong>04</strong>, S/N 4<strong>04</strong> 0614<br />
Installation of New Avionics<br />
Equipment.Transponders Mode S Filser<br />
Electronics TRT800H.<br />
Limited to B737-700 aircraft S/N<br />
Prior to installation of this modification it <strong>01</strong>.09.2<strong>01</strong>0<br />
33920Maintenance of the Recaro seats are to must be determined thatthe<br />
be performed per Recaro<br />
interrelationship between this modification<br />
ComponentMaintenance Manual 25-22-11, 25- and any other previouslyinstalled<br />
25-81 and 25-24-79<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Limited to B737-700 aircraft S/N<br />
33920Maintenance of the TIA Model 1545<br />
Oven is to be performed per TIAComponent<br />
Maintenance Manual 25-30-61<br />
In accordance with Supplement No. SMV<br />
02/06 R0, to the original Flight Manual<br />
approved by FAA.SN 31-7952088<br />
1. The design changes to be approved are<br />
only applicable to Cessna 4<strong>04</strong> airplanes with<br />
Dual GNS530 Installation according to A&M<br />
Avionics BI Nº <strong>01</strong>7/2006, and EHSI SANDEL<br />
SN 3500 previously installed and approved as<br />
Primary Navigation Display.2. Prior<br />
Prior to installation of this modification it 02.09.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it <strong>01</strong>.09.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4877 A&M AVIONICS, SL <strong>EASA</strong>.A.S.031<strong>04</strong> CESSNA 500 Installation of New Avionics<br />
Equipement.Transponder Mode S GARMIN<br />
GTX-330D.<br />
05.02.2008<br />
10032066 A.I.M.S. INTERNATIONAL Corp. FAA ST02675AT BD-700-1A10 Sound Reduction Kit None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.10.2<strong>01</strong>0<br />
10<strong>01</strong>5780 AAE LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>826 REV. 1 FAA STC ST<strong>01</strong>114WI BOEING 737 CLASSIC SERIES Installation of Smoke Detection and Fire<br />
Suppression System<br />
10<strong>01</strong>5840 AAE LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>934 FAA STC ST030<strong>01</strong>AT FOKKER F.28 MARK <strong>01</strong>00 Smoke detection and Fire Suppression System<br />
for lower Deck Class C Cargo Compartments<br />
of Fokker F100 Series Aircraft<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. AAE, Ltd. Document TFA09-0087, Revision<br />
IR, dated January 14, 2005 "FAA approved<br />
Airplane Flight Manual Supplement for the<br />
Class"C" Cargo Compartment Smoke<br />
Detection and Fire Suppression System on the<br />
Fokker F.28 Mark <strong>01</strong>00 Series Aircraft"<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 1/<strong>462</strong><br />
21.12.2007<br />
30.<strong>01</strong>.2009<br />
08.10.2007<br />
26.11.2002<br />
25.09.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong><strong>04</strong>11 AAR AIRCRAFT SERVICES FAA STC ST03119CH B717-200 Interior Reconfiguration None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.07.2<strong>01</strong>2<br />
10<strong>01</strong>5931 AAR AIRCRAFT SERVICES INC.-<br />
INDIANAP<br />
<strong>EASA</strong>.IM.A.S.02068 SA7467SW FOKKER F.27 Installation of dual freon air conditioning<br />
systems in accordance with AAR Oklahoma,<br />
Inc., Drawing List 19L002, Revision F, dated<br />
July 19, 1988, or later FAA approved revision.<br />
10<strong>01</strong>5627 AAR CARGO SYSTEMS <strong>EASA</strong>.IM.A.S.<strong>01</strong>579 REV. 1 FAA STC ST02021CH MD-11 Installation of a Main Deck Cargo Handling<br />
System (FAA STC ST02021CH)<br />
10028433 AAR CARGO SYSTEMS P-<br />
<strong>EASA</strong>.IM.A.S.03180<br />
10<strong>04</strong>0510 AAR CARGO SYSTEMS REV. 1 FAA STC ST02665CH A300B4-6<strong>01</strong>, A300B4-603<br />
A300B4-605 R, A300B4-620<br />
A300B4-622, A300B4-622 R<br />
1. FAA approved flight manual supplement<br />
dated August 10, 1988, is required.2.<br />
Compatibility of this modification with<br />
previously installed equipment must be<br />
FAA STC ST02767CH B767-300 Install Main Deck Cargo Loading System To be installed on a/c converted by IAI<br />
Freighter Conversion (<strong>EASA</strong> STC10028430)<br />
Validation of FAA Supplemental Type<br />
Certificate (STC) ST02665CHInstall a Main<br />
Deck Cargo Loading System (AAR Part<br />
Number 58535-1<strong>01</strong>) onAirbus A300-600 series<br />
aeroplanes in accordance with AAR Master<br />
DrawingList Report Number 2149 Revision B,<br />
dated 15 Decemb<br />
10<strong>01</strong>6873 AAR COMPOSITES, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>249 FAA STC SR<strong>01</strong>934LA SIKORSKY S-92A Installation of Partial Search and Rescue<br />
Interior Configuration.<br />
13.10.2006<br />
determined by installer.<br />
None Compatibility of this design change will<br />
previously approvedmodifications must<br />
be determined by the installer.An <strong>EASA</strong><br />
approved cargo interior, compatible with<br />
this modification mustbe installed on this<br />
aircraft.Prior to installation of this<br />
modification it<br />
10.12.2<strong>01</strong>0<br />
Prior to installation of this modification it 08.<strong>01</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none An <strong>EASA</strong> approved cargo interior,<br />
compatible with this modification, mustbe<br />
installed on this aircraft. Aircraft must be<br />
loaded,with this cargoloading system<br />
installed, in accordance with the<br />
previously approvedweight and balance<br />
and cargo loading instruct<br />
13.07.2<strong>01</strong>2<br />
No passengers permitted in the main cabin<br />
until the complete interior arrangement has<br />
been <strong>EASA</strong> or cognizant National<br />
AirworthinessAuthority approved.<br />
10<strong>01</strong>6932 AAR COMPOSITES, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>318 FAA STC SR03370AT SIKORSKY S-92A Structural provisions for a composite ramp floor MDL items under this STC meet Part 29.853.<br />
panel.<br />
The installer is responsible for panel sealant<br />
and all fasteners as well as for structural<br />
provisions to the aircraft ramp door. User must<br />
not exceed the maximum load per surface area<br />
of the ramp panel as specifie<br />
10<strong>01</strong>7082 AAR COMPOSITES, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>540 FAA STC NO. SR03077 AT SIKORSKY S-92A S-92A Structural Provisions for a Composite<br />
Passenger Cabin VIP Interior.<br />
1. The installer is responsible for the addition<br />
of decorative finish to continue to comply with<br />
JAR 29.853.AAR bulkheads are for interior<br />
partitions only and are not intended means of<br />
compliance for cargo or smoke retention that<br />
the installer must ensu<br />
10<strong>01</strong>5303 AB LUFTFAHRTTECHNIK BERLIN GMBH <strong>EASA</strong>.A.S.03868 AIRBUS A319-112 Change of the Cabin Configuration (150 1. Prior to installation of this modification the<br />
Pax)/The cabin configuration will be changed to installer must determine that the<br />
increase the certified 145pax configuration to a interrelationship between this modificationand<br />
150 pax configuration with minimum<br />
any other previously installed modification<br />
CabinCrew of 3 Flight Attendants<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>3958 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.A.S.00516 REV. 1 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation of an Artex ELT C406-1 This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
19.<strong>01</strong>.2005<br />
10<strong>01</strong>4138 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.A.S.<strong>01</strong>249 LEARJET 35<br />
Installation of Honeywell MST-67A dual Mode<br />
28.<strong>04</strong>.2005<br />
LEARJET 35A<br />
S XPDR/CAS-67A TCAS II System.<br />
10<strong>01</strong>4160 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.A.S.<strong>01</strong>292 FOKKER F.27 MARK 500 Installation of an ARTEX ELT C406-1/-2 26.07.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 2/<strong>462</strong><br />
07.05.2007<br />
07.05.2007<br />
23.<strong>04</strong>.2009<br />
05.05.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4764 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.A.S.02954 LEARJET 35<br />
Installation of Honeywell EGPWS Mk. VIII(in None 02.03.2007<br />
LEARJET 35A<br />
combination with an existing Weather Redar<br />
LEARJET 36<br />
LEARJET 36A<br />
display)<br />
10<strong>01</strong>7178 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.R.S.<strong>01</strong>296 EUROCOPTER DEUTSCHLAND Installation of a HeliMap.MIDI.P0252 Moving<br />
19.09.2006<br />
EC-135-<br />
Map System<br />
10<strong>01</strong>7179 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.R.S.<strong>01</strong>297 EUROCOPTER DEUTSCHLAND Installation of a HeliMap MIDI.P0252 Moving<br />
19.09.2006<br />
MBB-BK<br />
Map System<br />
10<strong>01</strong>7213 ACC COLUMBIA JET SERVICE GMBH <strong>EASA</strong>.R.S.<strong>01</strong>369 EUROCOPTER DEUTSCHLAND Installation of an EAE Heli.Map.MDI.P0252<br />
14.06.2007<br />
MBB-BK<br />
system with extension box (for advisory<br />
only).Installation of a moving map system into<br />
BK117B-2 and BK117C-1 models.<br />
10034112 ACC COLUMBIA JET SERVICE GMBH CL-600-2B16, CL-600-2B19 Installation of a combined IRIDIUM-GPS None Prior to installation of this modification it 08.03.2<strong>01</strong>1<br />
Antenna as provision of anoptional Sky<br />
must be determined thatthe<br />
Tracking System.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4653 ACI SYSTEMES <strong>EASA</strong>.A.S.02810 BEECH 200 ATC replacement and Mode S installation. AFMS must be on board when modified 07.05.2007<br />
10<strong>01</strong>4737 ACI SYSTEMES <strong>EASA</strong>.A.S.02920 CESSNA 550 Single pilot operation and associated<br />
modifications<br />
06.06.2007<br />
10<strong>01</strong>4902 ACI SYSTEMES <strong>EASA</strong>.A.S.03137 REIMS AVIATION CESSNA F 406 ACI-024 - Universal UNS-1L Installation - B- F406 equipped with KCP220 Allied Signal<br />
10.10.2007<br />
RNAV and P-RNAV Capability.<br />
AutoPilot.<br />
10<strong>01</strong>4905 ACI SYSTEMES <strong>EASA</strong>.A.S.03140 REIMS AVIATION CESSNA F 406 ACI-030 - Installation of an NAT NTX138 - FM<br />
Communication device.<br />
08.10.2007<br />
10<strong>01</strong>4996 ACI SYSTEMES <strong>EASA</strong>.A.S.03293 BEECH 90 GNS 430 and B-RNAV capability on Beech 90 N/A 18.02.2008<br />
10<strong>01</strong>5003 ACI SYSTEMES <strong>EASA</strong>.A.S.03303 FALCON 50<br />
FALCON 900<br />
Falcon 50 and F900 EHS Mode S Capability Applicability for Falcon 50 and F900 which are<br />
already Mode A, C and ELS Mode S certified,<br />
ACAS certified and equipped with a dual<br />
transponder system.<br />
10<strong>01</strong>50<strong>04</strong> ACI SYSTEMES <strong>EASA</strong>.A.S.033<strong>04</strong> FALCON 10 Falcon 10 EHS Mode S Capability. Applicabilty for Falcon 10 that are already<br />
Mode A. C and ELS Mode S certified and<br />
equipped with a dual transponder system.<br />
10<strong>01</strong>5<strong>01</strong>6 ACI SYSTEMES <strong>EASA</strong>.A.S.03320 CESSNA 550 ACI-<strong>04</strong>5 - DFDR Upgrade. This STC is only applicable to aircraft equipped<br />
with Fairchild F800 FDR.<br />
10<strong>01</strong>5075 ACI SYSTEMES <strong>EASA</strong>.A.S.03406 BEECH 200<br />
Installation of a Garmin 400 Series with B-<br />
BEECH 300<br />
RNAV capability on Beech 200.<br />
10<strong>01</strong>5099 ACI SYSTEMES <strong>EASA</strong>.A.S.03441 BEECH 90 Installation of Garmin 500 Series GPS with B-<br />
RNAV capability on Beech 90.<br />
10<strong>01</strong>6968 ACROHELIPRO GLOBAL SERVICES,<br />
INC<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>369 FAA STC SR02292AK BELL 206<br />
BELL 206A<br />
BELL 206B<br />
BELL 206L<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
Sagem ICDS and Crossbow AHRS Installation.<br />
Consists of two 8 inch integrated cockpit<br />
display units (one PFD and one MFD) including<br />
engine instruments and an attitude and heading<br />
reference system. This STC is classified as<br />
"BASIC" by the FAA and is approved<br />
10031149 ACS-NAI Ltd. TCCA STC SA10-26 CL-600-2B19 Installation, CMC Electronics Pilot view Class II<br />
Electronics Flight Bag<br />
The supplemental Airplane Flight Manual ACI-<br />
09-AFM-M-070, revision 0, dated 15 January<br />
2008 must be on board when the modification<br />
is installed.<br />
Maximum ambient operating temperature of 40<br />
degrees Celsius (103 degrees Fahrenheit)<br />
29.10.2007<br />
29.10.2007<br />
16.05.2008<br />
05.02.2008<br />
<strong>04</strong>.<strong>04</strong>.2008<br />
31.10.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.07.2<strong>01</strong>0<br />
10031944 ACS-NAI Ltd. TCCA STC #C-LSA10-034/D ISS 1 BD-700-1A10 Installation of Two 16G Side Facing Divans Restricted to ASN 9347 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.09.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 3/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032295 ACS-NAI Ltd. <strong>EASA</strong>.IM.A.S.03152 REV. 1 TCCA STC NO. C-LSA09-021/D CL-600-2B19 Installation, Complete Custom Aircraft Interior - Restricted to ASN 8080 Prior to installation of this modification it 25.10.2<strong>01</strong>0<br />
ASN 8080<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032519 ACS-NAI Ltd. TCCA STC NO. SA10-25 DHC-8-4<strong>01</strong>, DHC-8-402 Installation of LED Lavatory Light System none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.11.2<strong>01</strong>0<br />
10032736 ACS-NAI Ltd. <strong>EASA</strong>.IM.A.S.03130 REV. 1 TCCA STC C-LSA09-024/D CL-600-2B19 Installation, Complete Custom Aircraft Interior -<br />
ASN 8077<br />
Restricted to ASN 8077 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.11.2<strong>01</strong>0<br />
10033800 ACS-NAI Ltd. TCCA STC NO.C-LSA11-<strong>04</strong>0/D BD700-1A11 Cabin Modifications for Wheelchair Access Restricted to ASN 9373. Previous embodiment Prior to installation of this modification it 09.02.2<strong>01</strong>1<br />
of <strong>EASA</strong> STC No. 10031088 (TCCA STC must be determined thatthe<br />
SA05-60).<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034703 ACS-NAI Ltd. REV. 1 TCCA STC SA07-40 PC-12/45, PC-12/47, PC-12/47E Installation Utility DoorExisting Cargo door<br />
modified to incorporate a utility door (990 mm<br />
highby 635 mm wide)<br />
10034865 ACS-NAI Ltd. TCCA STC SA98-60 ISSUE 2 DHC-8-102,-103,-106<br />
DHC-8-2<strong>01</strong>,-202<br />
DHC-8-3<strong>01</strong>,-311,-314,-315<br />
DHC-8-4<strong>01</strong>,-402<br />
Flight Deck Manual Stowage BoxTCCA STC<br />
SA98-60, Issue 2, dated 12.02.20<strong>01</strong>.<br />
10035310 ACS-NAI Ltd. REV. 1 TCCA STC C-LSA11-075/D ISS1 BD-700-1A10 Installation, Complete Custom Aircraft Interior. Restricted to ASN 9403.This system is<br />
intended to provide internet connectivity and<br />
emailservices to the airplane's cabin using<br />
portable electronic devices(PEDs). Any other<br />
intended function of this equipment will require<br />
are-examination of the certificati<br />
100361<strong>01</strong> ACS-NAI Ltd. TCCA STC C-LSA11-134/D BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9412<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.11.2<strong>01</strong>2<br />
None. None. 06.05.2<strong>01</strong>1<br />
Restricted to ASN 9412.The Wireless Local<br />
Area Network (WLAN) system is intended to<br />
provideinternet connectivity and email services<br />
to the airplane's cabin usingportable electronic<br />
devices (PEDs). Any other intended function of<br />
thisequipment will require a<br />
Prior to installation of this modification it 15.06.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 11.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036345 ACS-NAI Ltd. TCCA STC C-LSA11-058/D BD-700-1A10 Installation of Tailwind 500 System None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.09.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 4/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037710 ACS-NAI Ltd. TCCA STC C-LSA10-169/D CL-600-2B19 Installation, Complete Custom Aircraft Interior. Restricted to ASN 81<strong>01</strong>. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.12.2<strong>01</strong>1<br />
10037711 ACS-NAI Ltd. TCCA STC C-LSA11-165/D CL-600-2B19 Installation, Complete Custom Aircraft Interior. Restricted to ASN 8107. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.12.2<strong>01</strong>1<br />
10038022 ACS-NAI Ltd. TCCA STC NO. C-LSA11-009/D CL-600-2B19 Installation, Complete Custom Aircraft Interior. Restricted to ASN 81051.The Wireless Local Prior to installation of this modification it 12.<strong>01</strong>.2<strong>01</strong>2<br />
Area Network (WLAN) system installed as part must be determined thatthe<br />
of theinterior completion is intended to provide interrelationship between this modification<br />
cached internet content andemail services to and any other previouslyinstalled<br />
Portable Electronic Devices. Any other use of modification and/ or repair will introduce<br />
thisequipment will require a<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038149 ACS-NAI Ltd. TCCA STC NO. C-LSA11-179/D BD-700-1A10 Modifications to Existing Interior Completions -<br />
ASN 9393.<br />
10039631 ACS-NAI Ltd. TCCA STC C-LSA05-318/D CL-600-2B16 Aircraft Completion ASN 5618, 12 Passenger<br />
Interior Configuration.<br />
10039703 ACS-NAI Ltd. TCCA STC NO. C-<br />
LSA12-038/D<br />
10<strong>04</strong>0686 ACS-NAI Ltd. JAA STC<br />
ACG.21NE2.084<br />
TCCA SA<strong>01</strong>-77/JAA ACG.21NE2.084 DHC-8-102,-103,-106<br />
DHC-8-2<strong>01</strong>,-202,<br />
DHC-8-3<strong>01</strong>,-311,-314,-315<br />
10<strong>04</strong>1474 ACS-NAI Ltd. REV. 1 TCCA STC SA12-17 PC-6/B2-H2<br />
PC-6/B2-H4<br />
10<strong>04</strong>2346 ACS-NAI Ltd. ACG.21NE2.108 TCCA SA02-127 / ACG.21NE2.108 DHC-8-102,-103,-106<br />
DHC-8-2<strong>01</strong>,-202<br />
DHC-8-3<strong>01</strong>,-311,-314,-315<br />
Restricted to ASN 9393 andThe Installation of Prior to installation of this modification it 24.<strong>01</strong>.2<strong>01</strong>2<br />
<strong>EASA</strong> STC No. 10036060 is a prerequisite for must be determined thatthe<br />
theapproval of this STC.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 5618 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.05.2<strong>01</strong>2<br />
BD-700-1A10 Installation of Complete Custom Aircraft Interior Restricted to ASN 9434.The Wireless Local Prior to installation of this modification it 18.05.2<strong>01</strong>2<br />
- ASN 9434<br />
Area Network (WLAN) system is intended to must be determined thatthe<br />
provideinternet connectivity and email services interrelationship between this modification<br />
to the airplane's cabin usingportable devices and any other previouslyinstalled<br />
(PEDs). Any other intended function of this modification and/ or repair will introduce<br />
equipmentwill require a re-examina<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of an improved Aft Jet Pipe Support None. Prior to installation of this modification it 19.07.2<strong>01</strong>2<br />
TCCA STC N° SA<strong>01</strong>-77, Issue 3<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Vapour Cycle Air Conditioner<br />
System.<br />
Installation of an Improved Gound Power<br />
Current Limiter(ACS-NAI Ltd. Modification<br />
Data Summary D 11900) TCCA STC SA02-<br />
127, Issue 1<br />
Refer to the Airworthiness Limitations Prior to installation of this modification it <strong>04</strong>.10.2<strong>01</strong>2<br />
contained in Airplane FlightManual Supplement must be determined thatthe<br />
H4<strong>04</strong>091 Revision N/C.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.11.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 5/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5375 ACSS, AVIATION COMMUNICATION <strong>EASA</strong>.IM.A.S.<strong>01</strong><strong>04</strong>5 FAA STC ST<strong>01</strong>583LA BOEING 737-300<br />
Installation of ACSS T2CAS System according 1. According to limitations section in FAA STC<br />
17.08.2005<br />
AND<br />
BOEING 737-400<br />
to FAA STC ST<strong>01</strong>583LA dated 20th January ST<strong>01</strong>583LA dated 20th January 20<strong>04</strong>.2. This<br />
20<strong>04</strong>.- ACSS Index of Master Data Lists, STC is approved only for the product<br />
Document No. 8900034, Revision "A" dated configuration as defined in the approved design<br />
3rd September 20<strong>04</strong>, or later FAA approved data referred to in the paragraph "Description".<br />
revision- ACSS Airplane Flight Manual<br />
Supplement,<br />
Compatibility with other aircraft<br />
10<strong>01</strong>5406 ACSS, AVIATION COMMUNICATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>117 FAA STC ST<strong>01</strong>702LA BOEING 747-200<br />
Installation of ACSS T2CAS 1. in accordance with Approval Report<br />
<strong>01</strong>.08.2005<br />
AND<br />
BOEING 747-300<br />
DL/LVT/05.5325422. T2CAS Airplane Flight<br />
Manual Supplement (AFMS), ACSS document<br />
number 8003638-0<strong>01</strong> revision A, approved by<br />
the FAA on May 25, 20053. This STC is<br />
approved only for the product configuration as<br />
defined i<br />
10<strong>01</strong>5573 ACSS, AVIATION COMMUNICATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>480 FAA STC SA4839NM BOEING 757-200 Installation and activation of TCAS and the XS-<br />
07.11.2005<br />
AND<br />
950 Mode S Transponder (including<br />
ELS/EHS).<br />
10<strong>01</strong>5650 ACSS, AVIATION COMMUNICATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>625 FAA STC SA5061NM DC-9-81 (MD-81)<br />
Installation of Honeywell Traffic Alert &<br />
30.<strong>01</strong>.2006<br />
AND<br />
DC-9-82 (MD-82)<br />
DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
MD-88<br />
Collision Avoidance System (TCAS II)<br />
10<strong>01</strong>5651 ACSS, AVIATION COMMUNICATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>626 FAA STC SA5541NM BOEING 767-200<br />
Installation of Honeywell Traffic Alert & 1. TCAS Airplane Flight Manual Supplement<br />
12.12.2005<br />
AND<br />
BOEING 767-300<br />
Collision Avoidance System (TCAS)<br />
(Change 7) TCAS-APPS-0294, Rev A.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engin<br />
10<strong>01</strong>5731 ACSS, AVIATION COMMUNICATION<br />
AND<br />
10<strong>01</strong>5838 ACSS, AVIATION COMMUNICATION<br />
AND<br />
10031364 ACSS, AVIATION COMMUNICATION<br />
AND<br />
10032094 ACSS, AVIATION COMMUNICATION<br />
AND<br />
10<strong>04</strong>2297 ACSS, AVIATION COMMUNICATION<br />
AND<br />
10<strong>04</strong>2553 ACSS, AVIATION COMMUNICATION<br />
AND<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>753 - AIRBUS A320-200 Installation of Honeywell TCAS II system This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>932 FAA STC SA4882NM BOEING 747-100<br />
BOEING 747-100B SUD<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
BOEING 747-400<br />
BOEING 747-SP<br />
BOEING 747-SR<br />
Installation of a Honeywell Traffic Alert and<br />
Collision Avoidance System (TCAS II) in<br />
accordance with FAA approved Honywell<br />
Master Data List number ML4071598<br />
FAA approved Flight Manual Supplement<br />
required for this configuration is listed on the<br />
appropriate approved Honeywell and ACSS<br />
Master Index List.<br />
FAA STC ST<strong>01</strong>911LA B747-400 Installation of ACSS Mode S Transponder with See Limitation Section of FAA approved ACSS None 11.08.2<strong>01</strong>0<br />
ELS/EHS capability toreplace Mode S<br />
Transponder in existing ACSS Traffic Alert and<br />
CollisionAvoidance system TCAS II in<br />
accordance with FAA approval ACSS<br />
MasterData List Document No. 8900<strong>01</strong>9-0<strong>01</strong>,<br />
Revision B, dat<br />
Master Data List No. 8900<strong>01</strong>9<br />
FAA STC NO. ST0<strong>04</strong>11LA B747-400 Installation of Honeywell Traffic Alert and<br />
Collision Avoidance System(TCASII)<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>059 FAA ST<strong>01</strong>646LA ATR 42/72 ALL MODELS Installation of ACSS T2CAS in accordance with<br />
FAA Approved ACSS Index ofMaster Data List<br />
for installation of TCAS II and TAWS,<br />
Document No8900038, rev. B, dd. August<br />
20<strong>04</strong>, or later FAA approved revision and<br />
inaccordance with ACSS Summary of Data<br />
Submittals<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong><strong>04</strong>4 REV. 1 FAA STC SA5530NM B737-100/200/300/400/500 FAA STC SA5530NM validation - Installation of<br />
the ACSS TCAS II Systemwith Change 7.1<br />
software<br />
25.11.2005<br />
31.07.2006<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.10.2<strong>01</strong>0<br />
1- This STC is approved only for the<br />
product configuration as defined inthe<br />
approved design data referred to in the<br />
paragraph "Description".Compatibility<br />
with other aircraft/engine configurations<br />
shall bedetermined by the installer. This<br />
certificate shall<br />
None. Prior to installation of this STC it must be<br />
determined that theinterrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and / or<br />
repair will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 6/<strong>462</strong><br />
21.06.2005<br />
14.12.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2711 ACSS, AVIATION COMMUNICATION<br />
FAA STC ST02406LA SEE <strong>EASA</strong> APPROVED MODEL Installation of Traffic Alert and Collision none Section 1.2.2.3 of Installation Instruction, 14.12.2<strong>01</strong>2<br />
AND<br />
LIST<br />
Avoidance Systems (TCAS II)version 7.1<br />
ref. doc. 8008571-0<strong>01</strong>, Rev.G, is not<br />
applicable to this <strong>EASA</strong> STC. It is<br />
replaced by:Confirm the existing ACSS<br />
TCAS Change 7.0 system was approved<br />
by <strong>EASA</strong>Prior to installation of this<br />
modification it must be dete<br />
10033485 ADAC LUFTFAHRT TECHNIK GmbH EC135P2 (CPDS), EC135 P2+,<br />
EC135T2 (CPDS), EC135 T2+<br />
10035671 ADAC LUFTFAHRT TECHNIK GmbH EC135 T1(CDS)<br />
EC135 T1(CPDS)<br />
EC135 T2(CPDS)<br />
EC135 T2+<br />
EC135 P1(CDS)<br />
EC135 P1(CPDS)<br />
EC135 P2(CPDS)<br />
EC135 P2+<br />
10036349 ADAC LUFTFAHRT TECHNIK GmbH EC135 P2(CPDS), EC135 P2+<br />
EC135 T2(CPDS), EC135 T2+<br />
Installation of Dual Garmin GNS 430W into EC<br />
135 with MEGHAS cockpitInstallation of two<br />
GNS430W linked with indication on the<br />
FCDSas definedin the Master Drawing List<br />
EC135-<strong>01</strong> 066-005-LIN and based on ALT<br />
MajorChange EC135-<strong>01</strong>066.<br />
Installation of fixed Landing Lights on the<br />
forward crosstube. Installation of a second<br />
fixed landing light on the forward cross tubeas<br />
defined in the MDL EC135-<strong>01</strong>072-0<strong>01</strong>-LMD<br />
and based on ALT changeproject EC135-<br />
<strong>01</strong>072.<br />
10039230 ADAC LUFTFAHRT TECHNIK GmbH BK117 C-2 NVIS Certification of mission equipment on an<br />
Eurocopter BK117 C2<br />
10028594 ADVANCED AVIONICS TECHNOLOGIES P-<br />
<strong>EASA</strong>.IM.A.S.03223<br />
10028595 ADVANCED AVIONICS TECHNOLOGIES P-<br />
<strong>EASA</strong>.IM.A.S.03220<br />
10028911 ADVANCED AVIONICS TECHNOLOGIES P-<br />
<strong>EASA</strong>.IM.A.S.03222<br />
10029263 ADVANCED AVIONICS TECHNOLOGIES P-<br />
<strong>EASA</strong>.IM.A.S.03221<br />
REV. 1 FAA STC ST09365SC DHC-8-2<strong>01</strong>, DHC-8-202 Installation of dual Collins Mode S<br />
TranspondersFAA STC ST09365SC, IR,<br />
August 14, 1997<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
25.<strong>01</strong>.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.07.2<strong>01</strong>1<br />
Installation of a NVIS lighting system into an None. -,,The first installation of this kit must be<br />
Eurocopter EC135(MEGHAS).Installation of a<br />
supervised by the STCholder. -,,This<br />
NVIS lighting system into an Eurocopter EC135<br />
rotorcraft employs Night Vision Imaging<br />
withMEGHAS cockpit as defined in the MDL<br />
System lighting,commonly named NVIS<br />
EC135-<strong>01</strong>065-0<strong>01</strong>-LMD, based on ALTchange<br />
lighting, that has been certified to ensure<br />
project EC135-<strong>01</strong>065.<br />
theaircraft is compatible with night vision<br />
goggles (<br />
Required pre-modification <strong>EASA</strong> approval<br />
10038241 (ECD major change 2237)<br />
The first installation of this kit must be<br />
supervised by the STC holder. This<br />
rotorcraft employs Night Vision Imaging<br />
System lighting, commonlynamed NVIS<br />
lighting, that has been certified to ensure<br />
the aircraft iscompatible with night vision<br />
goggles (NVG).<br />
02.09.2<strong>01</strong>1<br />
19.<strong>04</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.07.2<strong>01</strong>1<br />
REV. 2 FAA STC ST09326SC DHC-8-2<strong>01</strong>, DHC-8-202 Installation of Dual Universal Navigation UNS- None Prior to installation of this modification it 20.07.2<strong>01</strong>1<br />
1C Flight ManagementSystemFAA STC<br />
must be determined thatthe<br />
ST09326SC, Rev. 1, dated 14 November 2000<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
REV. 2 FAA STC ST09347SC DHC-8-2<strong>01</strong>, DHC-8-202<br />
DHC-8-4<strong>01</strong>, DHC-8-402<br />
Installation of Coltech ATSCALL SystemFAA<br />
STC ST09347SC, Rev. 1, dated May 08,<br />
20<strong>01</strong>.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.07.2<strong>01</strong>1<br />
REV. 2 FAA STC ST09346SC DHC-8-2<strong>01</strong>, DHC-8-202 Installation of Honeywell Traffic Alert and none Prior to installation of this modification it 20.07.2<strong>01</strong>1<br />
Collision Avoidance System,TCAS IIFAA STC<br />
must be determined thatthe<br />
ST09326SC, Rev.1, dated 14 November 2000.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 7/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7156 AERAZUR - ZODIAC AEROSPACE <strong>EASA</strong>.R.S.<strong>01</strong>263 REV. 4 S-92A Installation of AERAZUR Internal Auxiliary Fuel The IAFS Completion Kit can be installed only Prior to installation of this modification it 10.03.2<strong>01</strong>1<br />
GROUP<br />
System (lAFS) completionkit pin 508617 or on S-92A helicoptersequipped with: - must be determined thatthe<br />
508617-1 or 508617-2 or 508617-3.Revision 4 AERAZUR IAFS Provision Kit p/n 509429-02 interrelationship between thismodification<br />
of STC introducing new kit pin 508617-3 and or 509429-03, approved underSTC 10<strong>01</strong>7259 and any other previously installed<br />
reviseddocumentations<br />
Revision 3 or later-S-92A Avionics<br />
modification and/ orrepair will introduce<br />
Management System (AMS) version n° 091- no adverseeffect upon the airworthiness<br />
2527-007 or latera<br />
of the product.IAFS com<br />
10<strong>01</strong>7259 AERAZUR - ZODIAC AEROSPACE<br />
GROUP<br />
<strong>EASA</strong>.R.S.<strong>01</strong>466 REV. 6 S-92A Installation of Provision Kit p/n 509429-03 of<br />
Internal Auxiliary FuelSystem (IAFS).STC<br />
Revision 5 introduces minor design<br />
modifications, reviseddocumentation and<br />
revised limitations for compatibility with S-92A<br />
cabininterior panels.<br />
10<strong>01</strong>4306 AERLYPER S.A. <strong>EASA</strong>.A.S.<strong>01</strong>550 BEECH 200 Installation of MST67A Transponder Mode S<br />
Equipment.<br />
10<strong>01</strong>4317 AERLYPER S.A. <strong>EASA</strong>.A.S.<strong>01</strong>567 BEECH 200, SUPER KING AIR Tactical console installation on B-200 aircraft In accordance with Doc. No. 100528 "Aircraft<br />
with ARGOS system, tactical communications Flight Manual Supplement", Issue <strong>01</strong>, 27<br />
system and fixed provisions for ASTRA<br />
system.<br />
November 2006.<br />
10<strong>01</strong>4318 AERLYPER S.A. <strong>EASA</strong>.A.S.<strong>01</strong>568 BEECH 200 Inmarsat SATCOM installation on board In accordance with Doc. No. 10<strong>04</strong>29 AFM<br />
B200.The modification is optional and fixed. It<br />
consists of an Inmarsat SATCOM terminal to<br />
be installed in the passenger cabin. A<br />
SATCOMantenna is installed on the upper part<br />
of the fuselage.<br />
Supplement ED.03.<br />
10<strong>01</strong>4319 AERLYPER S.A. <strong>EASA</strong>.A.S.<strong>01</strong>569 BEECH 200 Installation of New Avionics Equipment to<br />
comply with COM/NAV regulations for IFR and<br />
B-RNAV Operation.<br />
10<strong>01</strong>4420 AERLYPER S.A. <strong>EASA</strong>.A.S.<strong>01</strong>741 FAIRCHILD SWEARINGEN SA Garmin GPS 155XL with antenna GA-56, Mid- The aircraft is approved for dual pilot B-RNAV<br />
227-BC<br />
Continent MD41-448 Annunciation control Unit operation, subject to the conditions, limitations<br />
and copilot CDI Mid-Continent MD 40-09L and procedures contained in Doc NoAI03-081installation<br />
for B-RNAV operation<br />
03 "Flight Manual Supplement", Rev 03<br />
10<strong>01</strong>7103 AERLYPER S.A. <strong>EASA</strong>.R.S.<strong>01</strong>073 EC 135 P2 Microwave Transmission System on EC-135<br />
Helicopters<br />
10<strong>01</strong>71<strong>04</strong> AERLYPER S.A. <strong>EASA</strong>.R.S.<strong>01</strong>075 BO105 C, BO105 S ASTRA System installation on BO-105 C/S<br />
Helicopters<br />
10<strong>01</strong>7105 AERLYPER S.A. <strong>EASA</strong>.R.S.<strong>01</strong>076 EC 135 P2 Installation of Image Recorder System UM III<br />
and Options System<br />
10<strong>01</strong>7137 AERLYPER S.A. <strong>EASA</strong>.R.S.<strong>01</strong>231 BO 105 C, BO 105 S Digital microwave transmission system<br />
installation on board BO-105 C/S.<br />
10<strong>01</strong>7197 AERLYPER S.A. <strong>EASA</strong>.R.S.<strong>01</strong>338 REV. 1 EC-135-P2 (CPDS)<br />
EC-135-P2+<br />
UM-III HD Camera System & Microwave<br />
Transmission System Installation Onboard<br />
EC135.<br />
10033659 AERLYPER S.A. P-<strong>EASA</strong>.R.S.<strong>01</strong>507 REV. 1 EC135 P2 & EC135 P2+ Installation of STAR SAFIRE HD Camera<br />
System & Digital TransmissionSystem<br />
10<strong>01</strong>5649 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>624 REV 1 TCCA STC C-LSA05-303/D ISSUE 2 BOMBARDIER CL-600-2B16 Aircraft Completion 12 Passenger Interior<br />
Configuration<br />
10<strong>01</strong>5653 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>628 REV 1 TRANSPORT CANADA STC C-LSA05- BOMBARDIER CL-600-2B16 Aircraft Completion 12 Passenger Interior<br />
2<br />
Configuration<br />
Refer to attached table. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.07.2<strong>01</strong>2<br />
06.12.2007<br />
31.05.2007<br />
31.05.2007<br />
06.12.2007<br />
17.<strong>01</strong>.2006<br />
In accordance with Doc No 10<strong>01</strong>98: RFM<br />
14.02.2006<br />
Supplemt Ed. 3<br />
In accordance with Doc No 10<strong>01</strong>37: RFM<br />
30.<strong>01</strong>.2006<br />
Supplement Ed.4<br />
Doc No 100059: RFM Supplement Ed. 3 08.02.2006<br />
In accordance with Doc. No. 100589 "Aircraft<br />
Flight Manual Supplement", issue 1, April<br />
2008.Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed mod<br />
1. Master Data List and RFM Supplement<br />
mentioned above.<br />
<strong>01</strong>.07.2008<br />
13.05.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
02.03.2<strong>01</strong>1<br />
Restricted to Aircraft Serial Number 5610 25.07.2006<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.2. Restricted t<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 8/<strong>462</strong><br />
25.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5670 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>647 REV 1 TCCA STC C-LSA05-317/D ISSUE BOMBARDIER CL-600-2B16 Aircraft Completion 12 Passenger Interior 1. Restricted to ASN 5620 only.2. This STC is<br />
10.08.2006<br />
Configuration<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the<br />
10<strong>01</strong>5671 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>649 REV 1 TCCA C-LSA05-315/D ISSUE 2 BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>04</strong><br />
Aircraft Completion 12 Passenger Interior<br />
Configuration<br />
10<strong>01</strong>5678 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>659 REV 1 TCCA STC C-LSA05-328/D BOMBARDIER CL-600-2B16 Aircraft Completion 12 Passenger Interior<br />
Configuration<br />
1. Restricted to ASN 5612 only2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the i<br />
1. Limited to S/N 56172. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the ins<br />
10<strong>01</strong>5859 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>967 TCCA STC SA03-43 BOMBARDIER CL-600-2B19 Installation of Safe Flight Autopower<br />
(Autothrottle) System<br />
-- 14.09.2006<br />
10<strong>01</strong>6132 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02326 TCCA STC SA95-67 BOMBARDIER DHC-8-100 Installation of Aero Consulting Services Ltd.<br />
<strong>01</strong>.03.2007<br />
SERIES<br />
"Improved Exhaust Outlet Shroud Assembly"<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
according to Transport Canada STC SA 95-67<br />
10<strong>01</strong>6192 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02429 TCCA SA<strong>01</strong>-65, ISSUE 4 BOMBARDIER DHC-8-100 Addition of filtration to Cabin Recirculation 1. Applicable to DHC-8-100 series with 1990<br />
06.07.2007<br />
SERIES<br />
Air.Addition of recirculation air filter reduces (Post-Mod 8/1127*) cabin interior, all DHC-8-<br />
BOMBARDIER DHC-8-200 potential blockage of the condenser mixer and 200 series and DHC-8-300 series with 1990<br />
SERIES<br />
promotes peak performance of the ECS (Post-Mod 8/1128*) cabin interior.*Including<br />
BOMBARDIER DHC-8-300 system. TCCA STC SA<strong>01</strong>-65, Issue 4, dated Hunting and CD interior.2. Prior to installation<br />
SERIES<br />
24 June 2005.<br />
of this modification the<br />
10<strong>01</strong>6270 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02554 TCCA STC C-LSA07-190/D ISSUE 2 Upgrade to Honeywell Mark V EGPWS. 02.11.2007<br />
10<strong>01</strong>6376 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02699 REV. 1 TCCA LSTC C-LSA07-342/D BOMBARDIER BD-700-1A11 Installation, Side Facing Divan, S/N 9229<br />
Configuration.<br />
Restricted to ASN 9229. 05.03.2008<br />
10<strong>01</strong>6429 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02768 TCCA STC C-LSA08-<strong>01</strong>7/D ISSUE 2 BOMBARDIER BD-700-1A10 Cabin Electronics Upgrade. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
09.07.2008<br />
10<strong>01</strong>6470 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02816 TCCA STC C-LSA08-143/D GULFSTREAM IV Installation of Interior Modifications. Aircraft Serial Number 1109 Only.Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no<br />
adverse effect upon the<br />
02.06.2008<br />
10<strong>01</strong>6471 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.02817 TCCA STC C-LSA08-151/D GULFSTREAM IV Installation of Rockwell Collins Radio Tuning Application to Aircraft Serial Number 1109<br />
11.06.2008<br />
Units RTU-4210 and Rockwell Collins TDR- only,The operator is responsible for th<br />
94D (ELS/EHS) Transponder.<br />
einclusion of a 24 month check in their<br />
maintenance schedule of the Mode S<br />
transponder system toensure correct operation<br />
of the 24BIT address and the required DAPs<br />
IAW ACS M<br />
10<strong>01</strong>6605 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03022 TCCA STC SA00-109, ISSUE 4 BOMBARDIER DHC-8-102 Installation of Enviromental Control System, Prior to installation of this modification the<br />
19.12.2008<br />
BOMBARDIER DHC-8-103 Low Temperature Limit System (Cold installer must determine that the<br />
BOMBARDIER DHC-8-200 Clamp)Ref. TCCA STC SA00-109, Issue 4, interrelationship between this modification and<br />
SERIES<br />
dated 19. October 2000<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6606 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03023 TCCA STC SA02-4, ISSUE 1 Installation of NAI part C93602 Solid State Prior to installation of this modification the<br />
14.10.2008<br />
Logo Light<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 9/<strong>462</strong><br />
11.08.2006<br />
27.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6612 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03033 TCCA STC C-LSA08-268/D BOMBARDIER BD-700-1A10 Installation, Side Facing Divan, S/N 9260 Prior to installation of this modification the<br />
13.03.2009<br />
Configuration<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6629 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03064 TCCA STC C-LSA09-087/D GULFSTREAM IV Refurbishment and Installation of Cabin Interior<br />
Modifications.<br />
10<strong>01</strong>6630 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03065 TCCA STC C-LSA09-086/D GULFSTREAM IV Installation of Rockwell Collins Radio Tuning<br />
Units RTU-4210 and Rockwell Collins TDR-<br />
94D (ELS/EHS) Transponder.<br />
10<strong>01</strong>6647 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03091 TCCA C-LSA09-088/D Installation of L3 Communications MicroQAR<br />
Quick Access Recorder.<br />
Aircraft Serial Number 1202 OnlyPrior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no<br />
adverse effect upon the a<br />
Aircraft Serial Number 1202 OnlyThe operator<br />
is responsible for the inclusion of a 24 month<br />
check in their maintenance schedule of the<br />
Mode S transponder system toensure correct<br />
operation of the 24BIT address and the<br />
required DAPs IAW ACS MM 34 53 00.<br />
Aircraft Serial Number 1202 OnlyPrior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworthi<br />
10<strong>01</strong>6662 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03125 TCCA LSTC # C-LSA08-317/D ISSU BOMBARDIER CL-600-2B16 Installation, Complete Custom Aircraft Interior Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6664 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03129 TCCA STC NO. C-LSA09-022/D ISS BOMBARDIER CL-600-2B16 Installation, Complete Custom Aircraft Interior. 1. Restricted to ASN 5734.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the airwor<br />
10<strong>01</strong>6665 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03135 PENDING TCCA LSTC # C-LSA09-03 BOMBARDIER CL-600-2B19 Installation, Complete Custom Aircraft Interior 1) Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2) The ins<br />
10<strong>01</strong>6669 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03151 TCCA STC C-LSA09-009/D ISSUE 1 BOMBARDIER CL-600-2B19 Installation, Complete Custom Aircraft Interior Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6674 AERO CONSULTING SERVICES LTD. <strong>EASA</strong>.IM.A.S.03177 REV. 1 TCCA STC SA91-97 BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-103<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
10026769 AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03137<br />
Safety Catch Mechanism on the Rear Baggage 1. Prior to installation of this modification the<br />
DoorRef. TCCA STC SA91-97, Issue 3, dated installer must determine that the<br />
18.11.2003Note: This STC supersedes interrelationship between this modification and<br />
<strong>EASA</strong>.IM.A.S.03177.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
TCCA LSTC C-LSA09-026 CL-600-2B19 Installation, Complete Custom Aircraft Interior Restricted to ASN 8079.The applicant must<br />
submit the final EWIS ICA, if applicable, to<br />
theAgency by 7 June, 2<strong>01</strong>0.<br />
08.<strong>04</strong>.2009<br />
08.<strong>04</strong>.2009<br />
08.<strong>04</strong>.2009<br />
19.02.2009<br />
14.<strong>04</strong>.2009<br />
10.06.2009<br />
13.03.2009<br />
14.05.2009<br />
1) Prior to installation of this modification 07.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 10/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10026840 AERO CONSULTING SERVICES LTD. TCCA LSTC C-LSA09-028/D CL-600 2B19 Installation, Complete Custom Aircraft Restricted to ASN 8070The applicant must 1) Prior to installation of this modification 14.08.2009<br />
submit the final EWIS ICA, if applicable, to the installer mustdetermine that the<br />
theAgency by 07 June 2<strong>01</strong>0.<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
100269<strong>04</strong> AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03136<br />
10027086 AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03165<br />
10027216 AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03160<br />
TCCA LSTC C-LSA09-032/D CL-600-2B19 Installation, Complete Custom Aircraft Interior Restricted to ASN 8089 The applicant must submit the final EWIS<br />
ICA, if applicable, to theAgency by 07<br />
June 2<strong>01</strong>0. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification a<br />
REV. 1 TCCA STC C-LSA09-33/D CL-600-2B19 Installation, Complete Custom Aircraft Interior -<br />
ASN 8085<br />
21.08.2009<br />
Restricted to ASN 8085 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.10.2<strong>01</strong>0<br />
TCCA STC C-LSA09-079/D BD-700-1A11 Installation 16G Side Facing Divan Restricted to: ASN 9289 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.09.2009<br />
10027715 AERO CONSULTING SERVICES LTD. TCCA LSTC C-LSA09-099/D BD-700-1A10 Installation, 16 G Side Facing Divan. None. Prior to installation of this modification the 26.10.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10028465 AERO CONSULTING SERVICES LTD. TCCA LSTC C-LSA08-007/D LEARJET 60 Installation of Chelton HSD Satcom System. Approval is valid for s/n 60-328 only. None. 13.<strong>01</strong>.2<strong>01</strong>0<br />
10028761 AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03154<br />
10028762 AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03131<br />
10028763 AERO CONSULTING SERVICES LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03134<br />
10028799 AERO CONSULTING SERVICES LTD. TCCA STC C-LSA10-006/D 900XP Installation of Dual Lifeport Patient Loading and<br />
Utility System (PLUS)<br />
10029239 AERO CONSULTING SERVICES LTD. TCCA LSTC C-LSA10-<strong>01</strong>0/D PC-12/47E Installation, Lifeport PLUS Units in Tandem<br />
Configuration<br />
10029773 AERO CONSULTING SERVICES LTD. REV. 1 TCCA PROJECT # C-09-784 PC-12/47E Main battery No. 2 relocation.Validation of the<br />
TCCA STC SA10-4 Issue 1: Relocation of the<br />
mainbattery No 2 from the tail section to the<br />
engine compartment.<br />
10029833 AERO CONSULTING SERVICES LTD. TCCA STC SA10-9 CL600-1A11, CL600-2A12,<br />
CL600-2B16<br />
BOMBARDIER CL-600-2B19 31.07.2009<br />
BOMBARDIER CL-600-2B19 16.07.2009<br />
BOMBARDIER CL-600-2B19 27.07.2009<br />
Transport Canada STC No. SA10-9 Issue 1<br />
dated 08 February 2<strong>01</strong>0.ACS-NAI Ltd.<br />
Modification Data Summary Number G373000<br />
Revision N/C orlater approved<br />
revision.Instructions for Continued<br />
Airworthiness G373071 Revision A and<br />
G373072Revision N/C, or later approv<br />
Aircraft Serial Number HA-<strong>01</strong>14 Only - Prior to installation of this modification<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product- The installa<br />
10.02.2<strong>01</strong>0<br />
The applicability of the present STC is limited<br />
to Aircraft S/N: 1165Refer to the Limitations<br />
section in the TCCA-approved Airplane<br />
FlightManual Supplement listed in associated<br />
technical documentation<br />
Prior to installation of this modification it 15.03.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. None. 02.11.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.<strong>04</strong>.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 11/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
1003<strong>01</strong>00 AERO CONSULTING SERVICES LTD. TCCA STC NO. C-LSA10-<strong>04</strong>8/D BD-700-1A10 Installation, Complete Custom Aircraft Interior Restricted to ASN 9319 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.05.2<strong>01</strong>0<br />
1003<strong>01</strong>39 AERO CONSULTING SERVICES LTD. TCCA STC NO. C-LSA10-<strong>04</strong>1/D BD-700-1A11 Installation, Complete Custom Aircraft Interior Restricted to ASN 9324 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.05.2<strong>01</strong>0<br />
10<strong>01</strong>6126 AERO DESIGN LTD. <strong>EASA</strong>.IM.A.S.02320 TCCA STC C-LSA05-2<strong>04</strong>/D PIPER PA-31 (NAVAJO) Installation of Heater Exhaust Extension. / The<br />
purpose is to route exhaust from the<br />
combustion heater in the aircraft nose to the aft<br />
of the wing to prevent fouling of the camera<br />
port.Ref.: Trasnport Canada Limited<br />
Supplemental Type Certificate C-LSA05-20<br />
10<strong>01</strong>6782 AERO DESIGN LTD. <strong>EASA</strong>.IM.R.S.<strong>01</strong>123 TCCA STC SH02-26, ISSUE 2 EUROCOPTER FRANCE AS 350<br />
B<br />
10028376 AERO DYNAMIX, INC. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>543<br />
FAA STC SR09480RC MD900 Installation of Night Image Vision System<br />
(NVIS) / Night Vision Goggles(NVG) Cockpit<br />
lighting.Validation of FAA STC SR09480RC.<br />
10031298 AERO DYNAMIX, INC. FAA STC SR09519RC AW119MKII Installation of Night Image Vision System<br />
(NVIS) / Night Vision Goggles(NVG) Cockpit<br />
lighting.<br />
Limited to aircraft serial numbers 31-457 and<br />
31-7912028.<br />
Installation of DynaNav Seisbag System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Refer to applicable RFMS for list of equipment<br />
mandatory for NightVision Image System<br />
certification<br />
Refer to applicable RFMS for list of equipment<br />
mandatory for NightVision Image System<br />
certification The Finish Board Guard<br />
Configuration as defined in Appendix B<br />
ofdocument 'Instructions for Continued<br />
Airworthiness (ICA)', Aero Dynamix,Inc. No.<br />
ICA A119-<strong>01</strong><br />
10034881 AERO DYNAMIX, INC. FAA STC SR09543RC S-76C Installation of Night Vision Imaging System Refer to applicable Rotorcraft Flight Manual<br />
(NVIS) / Night Vision Goggle(NVG) compatible Supplement (RFMS) for listof equipment<br />
lighting system.<br />
mandatory for Night Vision Imaging System<br />
(NVIS)certification.<br />
10<strong>04</strong>28<strong>04</strong> AERO DYNAMIX, INC. FAA STC SR09566RC 429 Installation of Night Vision Imaging System Refer to applicable Rotorcraft Flight Manual<br />
(NVIS) / Night Vision Goggle(NVG) compatible Supplement (RFMS) for listof equipment<br />
lighting system.<br />
mandatory for Night Vision Imaging System<br />
(NVIS)certification.<br />
28.08.2007<br />
25.<strong>01</strong>.2008<br />
Prior to installation of this modification it 23.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product -Instal<br />
Prior to installation of this modification it 13.08.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. Instal<br />
Prior to installation of this modification it 10.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. Instal<br />
Prior to installation of this modification it 19.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. -Insta<br />
10<strong>01</strong>4080 AERO ENGINEERING DESIGN LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>172 BOEING 737-300-400-500 Aero Engineering Design Modification 34-1-<br />
226.SSR Mode S Enhanced Surveillance<br />
21.06.2005<br />
10<strong>01</strong>4081 AERO ENGINEERING DESIGN LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>173 BAE HS 748 Installation of a Honeywell MK VI EGPWS 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
02.03.2005<br />
10<strong>01</strong>4130 AERO ENGINEERING DESIGN LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>240 BOEING 727-200 Installation of Honeywell MK VII EGPWS. 22.<strong>04</strong>.2005<br />
10<strong>01</strong>4186 AERO ENGINEERING DESIGN Ltd <strong>EASA</strong>.A.S.<strong>01</strong>324 BAE 125 800B Introduction of Rockwell Collins TCAS 4000 19.09.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 12/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4187 AERO ENGINEERING DESIGN Ltd <strong>EASA</strong>.A.S.<strong>01</strong>325 MD-80 Aero Engineering Design Modification 34-77-<br />
211. Introduction of Honeywell MK VII EGPWS<br />
25.07.2005<br />
10<strong>01</strong>4188 AERO ENGINEERING DESIGN Ltd <strong>EASA</strong>.A.S.<strong>01</strong>328 MD-80 Aero Engineering Design Modification 34-77-<br />
210.Introductiom of Honeywell RDR-4B<br />
Weather Radar<br />
10<strong>01</strong>6210 AERO MEDICAL PRODUCTS MFG INC. <strong>EASA</strong>.IM.A.S.02456 FAA STC SA1035GL PIPER PA-31<br />
PIPER PA-31-300<br />
PIPER PA-31-325<br />
PIPER PA-31-350<br />
FAA STC SA 1035GL "Aircraft Stretcher 1. Prior to the first flight of each modified<br />
System - Installation of Air Ambulance aircraft, and after each exchange to any of the<br />
Stretcher P/N 125 Kit P/N 800, Medical Communication, Navigational or MedPack<br />
Oxygen System Kit P/N 807 (FAA approved Equipment, a ground EMI test must be<br />
option), Inverter/ Pump Kit P/N 812 in conducted in accordance with EA form 173<br />
accordance with Drawing List Report 0<strong>01</strong> Rev. dated 15-11-1993. A copy of the EA form 17<br />
C or later appro<br />
10029339 AERO MEDICAL PRODUCTS MFG INC. FAA STC ST<strong>01</strong>188CH CESSNA 5<strong>01</strong>, 551 Installation of Air Ambulance Conversion iaw. As referred in limitations section of the AFM-S The installation of this modification by 19.03.2<strong>01</strong>0<br />
Aero Medical Products MfgInstallation Drawing Prior to the first flight of each modified aircraft, third persons is subject towritten<br />
List Report 006-1 or later FAA approved and after eachchange to any of the<br />
permission of the approval holder and<br />
revisions<br />
communication, Navigational, or Med Pack holding and disposal ofthe approved<br />
equipment,a ground EMI test must be appropriate documentation. Prior to<br />
conducted iaw. EA Form 173. A copy of EA Fo installation of this modification it must be<br />
determined thatthe interr<br />
10034128 AERO MEDICAL PRODUCTS MFG INC. FAA STC ST02863CH FALCON 50 Aircraft Medical stretcher for MF 50<br />
This STC does not constitute an approval for Prior to installation of this modification it 09.03.2<strong>01</strong>1<br />
aircraftFAA STC ST02863CH<br />
installation.Compliance with minimum following must be determined thatthe<br />
requirements below need to bedemonstrated interrelationship between this modification<br />
through a design approval for installation in and any other previouslyinstalled<br />
each aircraftmodel to be equipped with this modification and/ or repair will introduce<br />
medical stretcher assembly part:<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7055 AERO PACIFIC <strong>EASA</strong>.IM.R.S.<strong>01</strong>486 REV. 1 FAA STC STC SR<strong>01</strong>521LA EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
10039781 AERO PACIFIC FAA STC SR<strong>01</strong>688LA<br />
D<br />
206, 206A, 206B, 206B-1, 206L<br />
206L-1, 206L-3, 206L-4, 407<br />
Installation of a Belly Utility Mount.Note: This<br />
STC supersedes <strong>EASA</strong>.IM.R.S.<strong>01</strong>486.<br />
Installation of Aero Pacific Belly Utility Mount<br />
AP206UM02(Validation of FAA STC<br />
SR<strong>01</strong>688LA)<br />
1. This STC provides approval for structural<br />
provisions for installation of other equipment.<br />
This other equipment for which these<br />
provisions are intended has not been certified.<br />
A separate <strong>EASA</strong> approval is required for the<br />
installation of this equipment<br />
- This Belly utility Mount Installation is approved<br />
for a maximum weightof not more than 150<br />
pounds and a frontal area of 2.5 square feet.-<br />
This STC only addresses structural,<br />
performance and handling<br />
qualitiesrequirements. No system or electrical<br />
requirem<br />
25.07.2005<br />
<strong>01</strong>.02.2008<br />
<strong>04</strong>.03.2009<br />
Prior to installation of this modification it 23.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6841 AERO SEATS AND SYSTEMS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>214 SR09455RC SIKORSKY S-76A Installation of External Liferaft Deployment Approval limited to Sikorsky S-76A registration<br />
11.05.2006<br />
System<br />
G-BVCX Serial number 76<strong>01</strong>83<br />
10<strong>01</strong>6842 AERO SEATS AND SYSTEMS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>218 SR09355RC SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
Installation of Passenger Seats None 10.05.2006<br />
10<strong>01</strong>6844 AERO SEATS AND SYSTEMS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>220 FAA STC SR09<strong>01</strong>1RC SIKORSKY S-76A<br />
Installation of Emergency Exit Window in Configurations with forward facing seats only 27.07.2006<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
Passenger Door<br />
10<strong>01</strong>6912 AERO SEATS AND SYSTEMS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>293 FAA STC SR09211RC SIKORSKY S-76A<br />
Installation of External Mounted Life Raft Installation of external mounted life raft<br />
15.<strong>01</strong>.2007<br />
SIKORSKY S-76B<br />
Deployment System[Identified as “Basic STC” deployment system, with optional deployment<br />
SIKORSKY S-76C<br />
by the FAA and approved using the<br />
handles in passenger compartment, in<br />
FAA/JAA/<strong>EASA</strong> type validation principles accordance with Aero Seats and Systems Inc.<br />
(TVP)]<br />
Installation manual ASI-500-100-<strong>01</strong>/02, revision<br />
H, dated December 5, 2005 or later appro<br />
10<strong>01</strong>6924 AERO SEATS AND SYSTEMS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>309 FAA STC SR09453RC BELL 412<br />
BELL 412 EP<br />
Installation of Cabin Seats 15.03.2007<br />
10<strong>01</strong>4192 AERO TECHNICS DESIGN LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>334 1. BOEING 747-100<br />
Introduction of Horsebox Containers BAC1136-<br />
26.07.2005<br />
1. BOEING 747-200<br />
1. BOEING 747-400<br />
2. BOEING MD-11 SERIES<br />
3. DC-10 SERIES<br />
3<strong>01</strong> and BAC1136-4<strong>01</strong><br />
10<strong>01</strong>4600 AERO TECHNICS DESIGN LIMITED <strong>EASA</strong>.A.S.02722 REV 1 BOEING MD-83 Cabin Reconfiguration from 167Y to 52C/22Y<br />
Seating<br />
28.09.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 13/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029250 AERO TECHNICS DESIGN LIMITED A300, A310<br />
Introduction of Instone Airservices Airstable This STC is approved only for the product None. 26.03.2<strong>01</strong>0<br />
B747-400, DC-8, DC-10.MD-11, Horse/Freight ContainerP/N 73-90-343. configuration as defined inthe approved design<br />
B767, L100/L1<strong>01</strong>1, B777<br />
data referred to in the paragraph ’Description’.<br />
Compatibility with all aircraft configurations<br />
shall be determined bythe installer.<br />
10031612 AERO TECHNICS DESIGN LIMITED B737-500 Cabin Seating Reconfiguration from 120Y to<br />
16C/28C layout (44C)<br />
10031614 AERO TWIN, Inc. FAA STC SA<strong>462</strong>5NM CESSNA 208, 208B Fabrication and Installation of Aero Twin, Inc<br />
EB8-200 extended baggagekit in accordance<br />
to FAA STC SA<strong>462</strong>5NM<br />
10033295 AERO TWIN, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02690<br />
FAA STC SA02291AK CESSNA 208, 208B Installation of Honeywell TPE331-12JR turbine<br />
engine and HartzellHC-B4TN-<br />
5QL/LT10890N(K) propeller and associated<br />
structure and equipmentin accordance with<br />
FAA STC SA02291AK.<br />
100370<strong>01</strong> AERO TWIN, Inc. FAA STC SA<strong>462</strong>6NM CESSNA 208, 208B Fabrication and Installation of Auxiliary dry air<br />
pump kit AP8-100 inaccordance to FAA STC<br />
SA<strong>462</strong>6NM.<br />
10038365 AERO TWIN, Inc. FAA STC SA02080AK-D 208, 208B Fabrication and Installation of Aero Twin, Inc.<br />
Exhaust Deflector P/NED8-100 in accordance<br />
with FAA STC SA02080AK-D<br />
10027700 AERO VODOCHODY A.S. P-<strong>EASA</strong>.A.S.03909 REV. 1 EMB-135BJ EFB class2 navAero- t.BagC2² Electronic Bag<br />
System implementation<br />
10037255 AERO VODOCHODY A.S. REV. 1 A330-2<strong>01</strong>, -202, -203<br />
A330-223, -223F<br />
A330-243, -243F<br />
A330-3<strong>01</strong>, -302, -303<br />
A330-321, -322, -323<br />
A330-341, -342, -343<br />
Implementation of Electronic Flight Bag Class<br />
2This STC installs provisions for Class 2 EFB<br />
(navAero T.Bag C²).<br />
10<strong>04</strong>0961 AERO VODOCHODY A.S. REV. 1 A300 SERIES, A310 SERIES Implementation of provisions for EFB Class2,<br />
NavAero T.Bag C2 inaccordance with Aero<br />
Vodochody MDL AM003-MDL Rev 4. Rev 1 of<br />
this STC addresses the installation of power<br />
switches to the28V DC bus for safe power off<br />
for the EFB-system.<br />
Limited to B737-500 S/N 24645, 24648 and<br />
24649<br />
Prior to installation of this modification it 31.08.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.08.2<strong>01</strong>0<br />
a) This modification is not compatible withi.<br />
Cessna 208 serial numbers 208000<strong>01</strong> through<br />
20800<strong>01</strong>3, 2080<strong>04</strong>16,20800500 and greaterii.<br />
Cessna 208B serial numbers 208B1190,<br />
208B1216, 208B2000 and greateriii. FAA STC<br />
SA<strong>01</strong>478WIb) This modification has been verif<br />
1. The following modifications are 12.<strong>01</strong>.2<strong>01</strong>1<br />
required for Cessna 208 (208A) aspart of<br />
this modification:a) Wipaire Inc.;<br />
Installation of Vortex Generator in<br />
combination withGross Weight Increase,<br />
FAA STC SA270CHb) Aero Twin, Inc.,<br />
Auxiliary Vacuum Pump, FAA STC SA46<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.10.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.02.2<strong>01</strong>2<br />
-Application of Electronic Checklist/ECL and<br />
WLAN need a separateapproval-No external<br />
devises are approved to be connected to the<br />
display duringmovement/flight of the aircraft.<br />
EMB-135 model BJ not affected by<br />
EWIS requirements Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
20.07.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
29.11.2<strong>01</strong>1<br />
FOR MSN 0554, 0560; 0614 AND 0667,<br />
REVISION 1 OF THIS RAPPROVAL IS<br />
VALIDONLY UNDER THE FOLLOWING<br />
CONDITION: ACCOMPLISHMENT OF<br />
INSTALLATION OFSWITCHES ACCORDING<br />
TO AERO VODOCHODY MINOR CHANGE,<br />
A-STC-Z 0058 FOR MSN0554, A-STC-Z 0059<br />
FOR MSN 0560, A-STC-Z 006<br />
Prior to installation of this modification it 31.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 14/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029795 AEROACOUSTICS AIRCRAFT<br />
FAA STC SA02<strong>04</strong>2SE CESSNA 208 Aircraft Payload Extender (APE) STOL System Note 1: This modification is also applicable to Prior to installation of this modification it 21.<strong>04</strong>.2<strong>01</strong>0<br />
SYSTEMS, INC<br />
for Cessna 208 and 208A inacc. to FAA STC the following aircraft that have been modified must be determined thatthe<br />
SA02<strong>04</strong>2SE<br />
with Wipaire, Inc. STC No. SA149CH (675 interrelationship between this modification<br />
SHP PT6A-114A Engine Installation). and any other previouslyinstalled<br />
Model,,Serial Number,,,,,,Note 208,,,,20800<strong>01</strong> modification and/ or repair will introduce<br />
through 20800060,,Eligible only if mo no adverse effectupon the airworthiness<br />
of the product.<br />
10029821 AEROACOUSTICS AIRCRAFT<br />
SYSTEMS, INC<br />
10033826 AEROACOUSTICS AIRCRAFT<br />
SYSTEMS, INC<br />
10033827 AEROACOUSTICS AIRCRAFT<br />
SYSTEMS, INC<br />
10<strong>01</strong>6152 AEROCET, INC. <strong>EASA</strong>.IM.A.S.02354 FAA STC SA0<strong>01</strong>37SE CESSNA 180A<br />
CESSNA 180H<br />
CESSNA 180J<br />
CESSNA 180K<br />
FAA STC SA<strong>01</strong>805SE 208B Aircraft Payload Extender (APE) STOL System The installation must be maintained in<br />
in acc. to FAA STC SA<strong>01</strong>805SE<br />
accordance with Section 3.0 ofDocument No.<br />
AA1976<br />
FAA STC SA<strong>01</strong>239SE 208 Fabrication and installation of AeroAcoustics<br />
Aircraft Systems (AAIS)Aircraft Payload<br />
Extender III (APE III) system in acc. with FAA<br />
STCSA<strong>01</strong>239SE.<br />
FAA STC SA<strong>01</strong>180SE 208 Fabrication and installation of AeroAcoustics<br />
Aircraft Systems (AAIS)Aircraft Payload<br />
Extender II (APE II) system in acc. with FAA<br />
STCSA<strong>01</strong>180SE.<br />
10<strong>01</strong>6153 AEROCET, INC. <strong>EASA</strong>.IM.A.S.02355 FAA STC SA5908NM CESSNA 185A<br />
CESSNA 185B<br />
CESSNA 185C<br />
CESSNA 185D<br />
CESSNA 185E<br />
CESSNA A185E<br />
CESSNA A185F<br />
10<strong>01</strong>6154 AEROCET, INC. <strong>EASA</strong>.IM.A.S.02356 FAA STC SA00003SE CESSNA P206<br />
CESSNA P206A<br />
CESSNA TP206A<br />
CESSNA TU206A<br />
CESSNA TU206B<br />
CESSNA TU206C<br />
CESSNA TU206D<br />
CESSNA TU206E<br />
CESSNA TU206F<br />
CESSNA TU206G<br />
CESSNA U206A<br />
CESSNA U206B<br />
CESSNA U206C<br />
CESSNA U206D<br />
CESSNA U206E<br />
CESSNA U206F<br />
CESSNA U206G<br />
10<strong>01</strong>5746 AEROCON ENGINEERING COMPANY <strong>EASA</strong>.IM.A.S.<strong>01</strong>778 FAA STC ST<strong>01</strong>086LA JETSREAM 4100 Installation of Smoke Detection & Fire<br />
Suppression Systems for Conversion of Class<br />
D Cargo Compartments to Class C<br />
10<strong>01</strong>4554 AEROCONDOR TRANSPORTES<br />
AEREOS SGPS<br />
10<strong>01</strong>4754 AEROCONDOR TRANSPORTES<br />
AEREOS SGPS<br />
Prior to installation of this modification it 22.<strong>04</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
This modification is limited to the following If the STC holder agrees to permit 10.02.2<strong>01</strong>1<br />
landplanes (serialnumbers) only: 208000<strong>01</strong> another person to use thiscertificate to<br />
through 20800060 (eligible only if modified with alter the product, the STC holder shall<br />
Cessna KitSK-208-12) 20800061 and up give the otherperson written evidence on<br />
Speed limits: Maneuvering Speed @ 8.362 lbs: that permission.Prior to installation of this<br />
143 KIASCG Range: Takeoff and Flight modification it must be determined<br />
thatthe interrelat<br />
Additional limitation: Refer to original FAA STC If the STC holder agrees to permit<br />
SA<strong>01</strong>180SESerial Number:208000<strong>01</strong> through another person to use thiscertificate to<br />
20800060 (eligible only if modified with Cessna alter the product, the STC holder shall<br />
10.02.2<strong>01</strong>1<br />
KitSK-208-12)20800061 and upThis<br />
give the otherperson written evidence on<br />
modification is also applicable to the following that permission.Prior to installation of this<br />
aircraft equippedwith Wipline Model 8 modification it must be determined<br />
thatthe interrelat<br />
Installation of Aerocet Model 3500 or 3500L Those Cessna Model 180G, 180H, 180J and<br />
09.08.2007<br />
seaplane floats on Cessna 180 Aircraft. 180Kairplanes equipped with the structural<br />
modifications defined in Kenmore Air Harbour<br />
STCNo. SA649NW, Amendment dated 14<br />
July 1984, may be operated on Aerocet Model<br />
3500 or 3500L floats at gross weight up to<br />
3190lb<br />
Installation of Aerocet Model 3500 or 3500L The airplane must incorporate the Cessna<br />
09.08.2007<br />
seaplane floats on Cessna 185 Aircraft. approved seaplane kit referred to Section 7 of<br />
the Aerocet AFM. The airplane must be<br />
equipped with the Cessna rudder centering<br />
device/non-linear rudder centering spring<br />
system defined on Aerocet Drawing No. 35-<br />
10000<br />
Installation of Aerocet Model 3500 or 3500L<br />
seaplane floats<br />
03.07.2007<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
<strong>EASA</strong>.A.S.02652 DORNIER DO 228-202K Installation of Honeywell TCAS system CAS-<br />
67A with Diversity Mode S Transponder MST-<br />
67A, Control Unit PS-550 and two E-VSI IVA-<br />
81A<br />
21.11.2006<br />
<strong>EASA</strong>.A.S.02940 Installation of TAWS As per AFM 26.03.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 15/<strong>462</strong><br />
17.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4780 AEROCONDOR TRANSPORTES <strong>EASA</strong>.A.S.02978 Installation of Honeywell TAWS Mark VI<br />
08.08.2007<br />
AEREOS SGPS<br />
System with GPS Antenna Honeywell KA-92<br />
and OAT Probe.<br />
10<strong>01</strong>4525 AEROCONSEIL <strong>EASA</strong>.A.S.02610 BOEING 757 Mode S Elementary & Enhanced Surveillance<br />
System Installation<br />
<strong>01</strong>.06.2006<br />
10<strong>01</strong>4698 AEROCONSEIL <strong>EASA</strong>.A.S.02865 AIRBUS A340 Installation of Aeromobile (ARINC/Telenor Joint 1. The applicability of this STC is limited to<br />
05.03.2008<br />
Venture) GSM Connectivity System.<br />
the Airbus A340-313 and A340-541 and any<br />
other A340 shown to the identical A340-313<br />
MSN 139 or A340-541 MSN 457, through the<br />
DOA's process as defined within the Document<br />
00<strong>01</strong>-<strong>01</strong>-B-0914 (Classification of Mo<br />
10<strong>01</strong>4699 AEROCONSEIL <strong>EASA</strong>.A.S.02866 REV. 3 A330 Installation of Aeromobile GSM Connectivity<br />
System onboard Airbus A330AircraftRevision<br />
of the <strong>EASA</strong> STC 10<strong>01</strong>4699 Rev. 2 to remove<br />
EWIS limitation<br />
10<strong>01</strong>4898 AEROCONSEIL <strong>EASA</strong>.A.S.03128 BOEING 777-200<br />
BOEING 777-300<br />
Installation of Aeomobile GSM connectivity<br />
system.<br />
10<strong>01</strong>5<strong>04</strong>6 AEROCONSEIL <strong>EASA</strong>.A.S.03362 AIRBUS A319-133 Finish Material Change in Private Area on<br />
A319CJ MSN 1468 /This modification<br />
concerns the change of fabric on part of the<br />
existing panels (including seals) in the private<br />
office, washroom and conference room in the<br />
10<strong>01</strong>5184 AEROCONSEIL <strong>EASA</strong>.A.S.03564 REV. 1 ATR 42-300/-320/-500<br />
ATR 72-202/-212/-212A<br />
A319CJ MSN 1468.<br />
Floor To Floor Nets installation on "Quick<br />
Change" ATR42 & 72 This STC consists in<br />
installing the floor to floor nets instead<br />
ofcontainer cargo system. Those nets are<br />
installed in the container zonedefined by ATR<br />
through their Class E Quick change configur<br />
10<strong>01</strong>5238 AEROCONSEIL <strong>EASA</strong>.A.S.03665 AEROSPATIALE CORVETTE Finish Material Change on Aerospatiale SN<br />
6<strong>01</strong> ‘Corvette’This STC concerns the change<br />
of finish materials in the cabin such as interior<br />
linings, seat foam and cover and floor.<br />
10028688 AEROCONSEIL P-<strong>EASA</strong>.A.S.03382 A318/A319/A320/A321 Approval of Installation Provisions for the use of<br />
EFB Class 2 on AirbusA318/A319/A320/A321<br />
10031972 AEROCONSEIL P-<strong>EASA</strong>.A.S.03959 A330-200/-300 Humidification System Installation on A330<br />
aircraft<br />
10032763 AEROCONSEIL 777-300ER Onboard Mobile Phone system installation on<br />
Boeing 777-300ER aircraftprovisioned by<br />
Boeing<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.09.2<strong>01</strong>0<br />
The applicability of this STC is limited to any<br />
Boeing 777-200 or B777-300 shown to be<br />
identical to Boeing 777-200 MSN27247 or<br />
Boeing 777-300 MSN 29063, through the<br />
DOA's process as defined within document<br />
00<strong>01</strong>-<strong>01</strong>-B-0914 (Classification of Modification<br />
Cha<br />
This STC is limited to aircraft Airbus A319-133<br />
MSN 1468.<br />
Limited to those ATR aeroplane models having<br />
embodied the following ATRmodifications: For<br />
the ATR42-300 / -320: Option 1: -ATR Mod<br />
1769 - Modify a/c for Cargo Container Loading, in addition to the original applicableATR<br />
and-ATR Mod 1393 - Reinforce all floor panels Weight and Balance Manuals. Prior to<br />
to 400 Kg/m2, and-ATR Mod 2080 -<br />
installation of this modification it must be<br />
determined thatthe interrelati<br />
This STC is limited to the SN 6<strong>01</strong> ’Corvette’<br />
MSNs : 11, 13, 30, 31, and 32.Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will int<br />
26.05.2008<br />
30.11.2007<br />
Information contained through the 22.07.2<strong>01</strong>1<br />
Aéroconseil Weight and Balance<br />
ManualSupplements must be considered<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.08.2008<br />
03.02.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
28.09.2<strong>01</strong>0<br />
The applicability of this STC is limited to<br />
Boeing 777-31HER aircraftMSN38983,<br />
MSN38984 and MSN35595<br />
Prior to installation of this modification it 30.11.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 16/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034165 AEROCONSEIL F2000 FALCON 2000 S/N 226 INTERIOR<br />
Restricted to S/N 226 Prior to installation of this modification it 14.03.2<strong>01</strong>1<br />
MATERIAL CHANGESChange consists in<br />
must be determined thatthe<br />
refurbishing certain panels- Windows Panels &<br />
interrelationship between this modification<br />
Valance Panels (lower and upper)- Glass<br />
and any other previouslyinstalled<br />
Carbon 250/56%/G874 panels.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10034950 AEROCONSEIL AS 365N3 Installation of structural provisions (floor fittings)<br />
for cabin layoutModification in accordance with<br />
AEROCONSEIL Installation ServiceBulletin<br />
2<strong>01</strong>8-<strong>01</strong>-A-31<strong>01</strong>.<br />
10035182 AEROCONSEIL A300 B4-6<strong>01</strong>, A300 B4-603,<br />
A300 B4-620, A300 B4-622,<br />
A300 B4-622 R, A300 B4-605 R,<br />
A300 C4-605 R VARIANT F,<br />
A300 C4-620,<br />
A300 F4-605 R, A300 F4-622 R<br />
10035880 AEROCONSEIL B777-200, B777-200LR<br />
B777-300, B777-300ER<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.05.2<strong>01</strong>1<br />
Aeroconseil STC <strong>04</strong>90-1 Aircell ST3100 None. Prior to installation of this modification it <strong>01</strong>.06.2<strong>01</strong>1<br />
SATCOM Installation on A300-600s.This STC<br />
must be determined thatthe<br />
covers the installation of a Satellite Telephone<br />
interrelationship between this modification<br />
SystemTransceiver, a Telephone adapter with<br />
and any other previouslyinstalled<br />
Display, a Base cradle for theCordless Handset<br />
modification and/ or repair will introduce<br />
and a Satellite antenna in accordanc<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
0555-<strong>01</strong>: Provisions of OnAir GSM/Internet<br />
System on B777<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.07.2<strong>01</strong>1<br />
10036272 AEROCONSEIL REV. 1 A340-311/-312/-313 A340 Cabin Reconfiguration & Zodiac SiT In- 1. Aeroconseil Modification, ref: MOD 7<strong>04</strong>9-<strong>01</strong>, Prior to installation of this modification it 09.08.2<strong>01</strong>2<br />
Flight EntertainmentInstallation The<br />
must be installed,being a pre-requisite to must be determined thatthe<br />
modification consists in reconfiguring the A340 this STC.2. This STC is limited to the A340- interrelationship between this modification<br />
cabin compartment byreplacing the economy 300 MSNs 197 and 378<br />
and any other previouslyinstalled<br />
class seats, from 218 Y/C seats to 215 Y/C<br />
modification and/ or repair will introduce<br />
seatswith Sicma 3537 series seats, and inst<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037524 AEROCONSEIL A330-3<strong>01</strong>/-302/-303<br />
A330-321/-322/-323<br />
A330-341/-342/-343<br />
Panasonic eXPhone System activation on<br />
A330-300 with eX2 IFEThis STC installs a<br />
Panasonic eXphone System allowing, in<br />
conjunctionwith other devices, the use of<br />
cellphones during flight.<br />
10037893 AEROCONSEIL 747-100, -200, -200F Installation of a CAS-81 TCAS II system and<br />
Dual TRA-67 "Mode S"transponders in<br />
accordance with Aeroconseil Master Drawing<br />
List0520-<strong>01</strong>-A-2103-R00 or later approved<br />
revisions.<br />
10038574 AEROCONSEIL A330-200, -300 A330 Tape Video Reproducer Unit Installation<br />
The change consist in areplacement of each<br />
MAS Video Tape Player (VTP) by new digital<br />
videoreproducer units manufactured by<br />
Goodrich installed in the aircraftexisting Video<br />
10038663 AEROCONSEIL REV. 1 777-200, 777-200LR<br />
777-300, 777-300ER<br />
Contro Center.<br />
<strong>04</strong>11-<strong>01</strong>: Installation/activation of OnAir<br />
GSM/Internet System on B777<br />
The following modifications are prerequisites to Prior to installation of this modification it 02.12.2<strong>01</strong>1<br />
the installation ofthis STC:-Airbus Minor must be determined thatthe<br />
Change ref: 20<strong>01</strong>90 - Approved under Airbus interrelationship between this modification<br />
DOA<strong>EASA</strong>.21J.031, on 22 February 2<strong>01</strong>1- and any other previouslyinstalled<br />
Delta Engineering STC ref: ODA-2234-<strong>01</strong> - modification and/ or repair will introduce<br />
<strong>EASA</strong> Approval 10036548 Rev 1or later revisio no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>.<strong>01</strong>.2<strong>01</strong>2<br />
this change is limited to A330-200 and A330-<br />
300, providing that the VCCP/N RDAA902251<br />
isinstalled, and still in the configuration<br />
approved by the aircraftmanufacturer (no other<br />
STCs modifying the VCC before this change).<br />
None 27.02.2<strong>01</strong>2<br />
Per AFM Supplement <strong>04</strong>11-<strong>01</strong>-AThis<br />
modification is limited as stated below except<br />
similaritydemonstrated per Document 00<strong>01</strong>-<strong>01</strong>-<br />
B-0914 (Classification of ModificationChange<br />
Procedure for Connectivity System).STC<br />
effectivity: Boeing 777-300ER MSN 33377,<br />
34568,<br />
To be installed concurrent with <strong>EASA</strong><br />
STC 10035880 (Provisions)Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 17/<strong>462</strong><br />
08.03.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038678 AEROCONSEIL B777-200 0527-<strong>01</strong>: eXPhone System Installation on B777-Per<br />
AFM Supplement 0527-<strong>01</strong>-A-23<strong>01</strong>.This Prior to installation of this modification it 07.03.2<strong>01</strong>2<br />
200 aircraft.<br />
modification is limited to Boeing 777-200 must be determined thatthe<br />
MSN29953, exceptsimilarity demonstrated per interrelationship between this modification<br />
Document 00<strong>01</strong>-<strong>01</strong>-B-0914 (Classification and any other previouslyinstalled<br />
ofModification Change Procedure for GSM modification and/ or repair will introduce<br />
connectivity System).<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038812 AEROCONSEIL REV. 1 A330-3<strong>01</strong> / -302 / -303<br />
A330-321 / -322 / -323<br />
A330-341/ - 342 / -343<br />
10038876 AEROCONSEIL B777-200 0542-<strong>01</strong>: WiFi internet access system<br />
installation on B777-200<br />
10039705 AEROCONSEIL A330-2<strong>01</strong> / -202 / -203<br />
A330-223 / -243<br />
10<strong>04</strong>0592 AEROCONSEIL A330-2<strong>01</strong> / -202 / -203<br />
A330-223 / -243<br />
Panasonic eXPhone System activation on none The following modifications are<br />
21.08.2<strong>01</strong>2<br />
A330-300 with eXconnectThis STC installs a<br />
prerequisites to the installation ofthis STC<br />
Panasonic eXphone System allowing, in<br />
:- Delta Engineering STC ref : ODA-2224conjunctionwith<br />
other devices, the use of<br />
<strong>01</strong> - <strong>EASA</strong> Approval 10037166 Rev 1or<br />
cellphones during flight.This revision <strong>01</strong> extends<br />
later revisions of the above listed<br />
the STC applicability to a second aircraftco<br />
documents approved by <strong>EASA</strong>Prior to<br />
installation of this modificatio<br />
Panasonic eXPhone System activation on<br />
A330 with eXConnect and Rack P/NRD-<br />
AA903023This STC installs a Panasonic<br />
eXphone System allowing, in conjunctionwith<br />
other devices, the use of cellphones during<br />
flight.<br />
Panasonic eXPhone System Activation on<br />
A330 with eX2 IFE and eXconnect.This STC<br />
installs a Panasonic eXphone System allowing,<br />
in conjunctionwith other devices, the use of<br />
cellphones during flight.<br />
10<strong>04</strong>1655 AEROCONSEIL 777-200LR & 777-300ER <strong>04</strong>65-<strong>01</strong>: eXPhone System Activation on B777-<br />
200LR/300ER<br />
10<strong>04</strong>2771 AEROCONSEIL A320-111,-211,-212,-214,-215<br />
A320-216,-231,-232,-233<br />
10038123 AEROCONTROLEX GROUP, INC. FAA STC ST02798CH 1. B767-200/-300/-400ER<br />
2. B777-200/-300/-300ER/-200LR<br />
- per AFMS 0542-<strong>01</strong>-A-23<strong>01</strong>- Airworthiness Prior to installation of this modification it 21.03.2<strong>01</strong>2<br />
Limitations per ICA Document 0542-<strong>01</strong>-A-2211 must be determined thatthe<br />
aremandatory- This modification is limited to interrelationship between this modification<br />
Boeing 777-200 MSN29953, exceptsimilarity and any other previouslyinstalled<br />
demonstrated per Document 00<strong>01</strong>-<strong>01</strong>-B-0914 modification and/ or repair will introduce<br />
(Classification ofModification Change Proc no adverse effectupon the airworthiness<br />
of the product.<br />
None. The following modification is prerequisite 18.05.2<strong>01</strong>2<br />
to the installation of thisSTC : -,,Delta<br />
Engineering STC "installation of<br />
Panasonic GCS" - <strong>EASA</strong><br />
Approval10038944 Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between<br />
None. The following modifications are<br />
prerequisites to the installation ofthis STC<br />
: -,,Airbus Minor Change ref : 48818 -<br />
Approved under Airbus<br />
DOA<strong>EASA</strong>.21J.031, on 03 December<br />
2002-,,Delta Engineering STC ref : ODA-<br />
2269-<strong>01</strong> - <strong>EASA</strong> Approval 10038944or<br />
later revisi<br />
per AFMS <strong>04</strong>65-<strong>01</strong>-A-23<strong>01</strong> Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.07.2<strong>01</strong>2<br />
<strong>04</strong>.10.2<strong>01</strong>2<br />
Installation of SICMA Dragonfly seats for Indigo none Prior to installation of this modification it 18.12.2<strong>01</strong>2<br />
on A320<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of an AeroControlex Potable Water<br />
Level Sensor Assembly P/N8430-000000<br />
10<strong>01</strong>3930 AERODATA AG <strong>EASA</strong>.A.S.00277 REV. 2 B300 Installation of Aerodata Automatic Flight<br />
Inspection System AD-AFIS-112.<br />
10<strong>01</strong>3931 AERODATA AG <strong>EASA</strong>.A.S.00278 REV. 2 BEECH 300 Flight Data Recorder (FDR) integration into<br />
Hawker Beechcraft King Air B300<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.<strong>01</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.05.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 18/<strong>462</strong><br />
19.10.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>3988 AERODATA AG <strong>EASA</strong>.A.S.<strong>01</strong>020 BEECH B200<br />
Installation of TCAS 2000 with RCZ 852 Mode 1. This STC is approved only for the product<br />
11.02.2005<br />
BEECH B200T<br />
S Transponders<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>3989 AERODATA AG <strong>EASA</strong>.A.S.<strong>01</strong>021 BEECH B200<br />
Installation of UNS 1-F Flight Management<br />
11.02.2005<br />
BEECH B200T<br />
BEECH B300<br />
System<br />
10<strong>01</strong>3991 AERODATA AG <strong>EASA</strong>.A.S.<strong>01</strong>023 DORNIER D328-100<br />
DORNIER D328-300<br />
AeroPhone IRIDIUM SATCOM Installation 14.09.2005<br />
10<strong>01</strong>3993 AERODATA AG <strong>EASA</strong>.A.S.<strong>01</strong>024 REV. 9 DORNIER 328-100 Installation of Maritime Surveillance System on None Prior to installation of this modification the 30.<strong>01</strong>.2<strong>01</strong>2<br />
Dornier 328-100including SAR Radar, FLIR,<br />
installer must determinethat the<br />
and optional IR/UV Scanner Revision 4:<br />
interrelationship between this modification<br />
Functional/optional upgrade to the radar<br />
and any otherpreviously installed<br />
system and mission software tooptimize search<br />
modification will introduce no adverse<br />
and rescue operation. Hardware upgrade t<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>4244 AERODATA AG <strong>EASA</strong>.A.S.<strong>01</strong>454 BEECH B200 SUPER KING AIR Installation of Aerodata Flight Inspection<br />
System AD-FIS-9<br />
25.<strong>01</strong>.2006<br />
10<strong>01</strong>4515 AERODATA AG <strong>EASA</strong>.A.S.02591 Installation of Aerodata Flight Inspection<br />
System AD-AFIS-0220.<br />
31.10.2006<br />
10<strong>01</strong>4516 AERODATA AG <strong>EASA</strong>.A.S.02592 LBA STC SA 1320 BEECH B200 Installation of Normarc Flight Inspection<br />
System NM3625B.NOTE: this STC<br />
supersedes existing LBA STC SA 1320<br />
None 07.09.2006<br />
10<strong>01</strong>4785 AERODATA AG <strong>EASA</strong>.A.S.02985 BEECH B300 Installation of EGPWS Mark VI Upgrade in Compatibility of this modification with other<br />
16.<strong>04</strong>.2007<br />
B300.<br />
previously approved modifications must be<br />
determined by the installer.<br />
10<strong>01</strong>4930 AERODATA AG <strong>EASA</strong>.A.S.03184 REV. 1 KING AIR 300 Installation of an Aerodata Flight Inspection Airplane must be equipped with Collins ProLine<br />
26.10.2007<br />
System AD-AFIS-230<br />
II to be eligible for this STC.<br />
10<strong>01</strong>5136 AERODATA AG <strong>EASA</strong>.A.S.03489 REV. 3 B200, B200C, B200GT Installation of Aerodata Flight Inspection For AD-AFIS-120, Mod. No. B200-11.<strong>01</strong>:Only The installation of this modification by 08.06.2<strong>01</strong>1<br />
System- AD-AFIS-120, Mod. No. B200-11.<strong>01</strong>, applicable for aircraft model B200 and third persons is subject towritten<br />
or- AD-AFIS-250, Mod. No. B200-12.<strong>01</strong>, or- B200GT, and when equippedwith Collins permission of the approval holder and<br />
AD-AFIS-250, Mod. No. B200-12.02, or- AD- Proline 21, and preconditions as defined disposal of the approvedappropriate<br />
AFIS-250, Mod. No. B200-14.<strong>01</strong><br />
in DesignDescription, Installation of Aerodata documentation. Prior to installation of this<br />
10<strong>01</strong>5166 AERODATA AG <strong>EASA</strong>.A.S.03536 REV. 1 CESSNA 550 CITATION II Additional Cockpit Information DisplayThe<br />
FIS, Doc. No. DES-A/C-836, Rev. 2,dated 27- modification it must be determined<br />
thatthe interrelationship<br />
Prior to installation of this modification the<br />
26.<strong>01</strong>.2009<br />
current STC <strong>EASA</strong>.A.S.03536 covers the installer must determine that the<br />
installation of an Aerodata Flight Inspection interrelationship between this modification and<br />
System (FIS). To further reduce the required any other previously installed modification<br />
verbal communication and therefore the will introduce no adverse effect upon the<br />
workload of the cockpit crew and the FIS opera airworthiness of the product.<br />
10<strong>01</strong>5182 AERODATA AG <strong>EASA</strong>.A.S.03561 PILATUS PC-12 Modification as surveillance aircraft 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>5235 AERODATA AG <strong>EASA</strong>.A.S.03660 LEARJET 31A Installation of Aerodata Flight Inspection<br />
System (FIS)<br />
10<strong>01</strong>5270 AERODATA AG <strong>EASA</strong>.A.S.03745 BEECH 300 Installation of an Aerodata Flight Inspection<br />
System AD-AFIS-111<br />
10<strong>01</strong>7098 AERODATA AG <strong>EASA</strong>.R.S.<strong>01</strong>022 REV. 1 EUROCOPTER DEUTSCHLAND<br />
BK117 B<br />
EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
- Cockpit Arrangement for ADAC BK 117<br />
Fleet for IFR operation- Re-arrangement of<br />
Cockpit Instruments for a harmonized Cockpit<br />
Layout of several BK 117 Helicopters.<br />
Furthermore integration of a dual Garmin<br />
GNS430 equipment and GTX330 Mode S<br />
Transponde<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
1. Airplane must be equipped as stated in<br />
Chapter 1.3.1 of <strong>EASA</strong> approved Aerodata<br />
Certification Program, Doc. No. CP-B300-<br />
13.<strong>01</strong>,Revision 0, dated 12-Jan-2009, or later<br />
approved revision2. Prior to installation of this<br />
modification the installer must<br />
1 Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the pro<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 19/<strong>462</strong><br />
11.11.2008<br />
16.10.2008<br />
13.03.2009<br />
10.02.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7120 AERODATA AG <strong>EASA</strong>.R.S.<strong>01</strong>205 EUROCOPTER DEUTSCHLAND Installation of AeroPhone IRIDIUM<br />
This STC is approved only for the product<br />
31.08.2005<br />
MBB-BK<br />
SATCOMInstallation of satellite telephone configuration as defined in the approved design<br />
system AeroPhone on helicopter<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
10<strong>01</strong>7257 AERODATA AG <strong>EASA</strong>.R.S.<strong>01</strong>464 EUROCOPTER DEUTSCHLAND Airborne observation Platform (AOP) None. 29.08.2008<br />
EC-135-<br />
Integration in EC135. Installation of a Star<br />
Safire HD FLIR on the right skid and an<br />
operator station in the passenger compartment<br />
based on Aerodata change no. EC135-3.02<br />
iaw MDL-A/C-132 Rev. 1 or later approved<br />
revision<br />
10<strong>01</strong>7258 AERODATA AG <strong>EASA</strong>.R.S.<strong>01</strong>465 EUROCOPTER FRANCE EC 155 Airborne observation platform (AOP)<br />
1. Prior to installation of this modification the<br />
18.03.2009<br />
B1<br />
Integration in EC155.Optional Installation of a installer must determine that the<br />
EUROCOPTER FRANCE EC operator station and a external FLIR camera interrelationship between this modification and<br />
155B<br />
system as replacement for an existing any other previously installed modification will<br />
equipment. The installation is in accordance introduce no adverse effect upon the<br />
with Aerodata Major change EC155-3.<strong>01</strong>, with airworthiness of the product.2.<br />
d<br />
10<strong>01</strong>7277 AERODATA AG <strong>EASA</strong>.R.S.<strong>01</strong>523 EUROCOPTER DEUTSCHLAND 1. Title: Installation of AeroPhone IRIDIUM 1. Prior to installation of this modification the<br />
13.11.2008<br />
EC-135-<br />
SATCOM in EC135.2. Description:<br />
installer must determine that the<br />
Installation of an AeroPhone IRIDIUM interrelationship between this modification and<br />
SATCOM system in EC135 based on any other previously installed modification will<br />
AERODATA change no. AD-IRI-3.02 i.a.w. the introduce no adverse effect upon the<br />
MDL MDL-A/C-093 Rev.3 or later approved<br />
revision.<br />
airworthiness of the product. The i<br />
10027409 AERODATA AG P-<strong>EASA</strong>.A.S.03795 BEECH B300 Installation of Aerodata Flight Inspection Only applicable for aircraft / preconditions as The installation of this modification by 29.09.2009<br />
System AD-AFIS-150<br />
defined in DesignDescription, Doc. No. DES- third persons is subject towritten<br />
A/C-884, Rev. 1, dated 03-Aug-2009, or permission of the approval holder and<br />
laterapproved revision<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe ,,interrelationshi<br />
10027987 AERODATA AG P-<strong>EASA</strong>.A.S.03960 B300 Installation of Aerodata Flight Inspection Only applicable for aircraft / preconditions as The installation of this modification by 23.11.2009<br />
System AD-AFIS-260<br />
defined in DesignDescription, Integration of AD- third persons is subject towritten<br />
AFIS-260, Doc. No. DES-A/C-887, Rev. permission of the approval holder and<br />
2,dated 19-Oct-2009, or later approved disposal of the approvedappropriate<br />
revision<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe ,,interrelationshi<br />
10029093 AERODATA AG P-<strong>EASA</strong>.A.S.03846 1329-25 (JETSTAR II) Avionics Upgrade for RVSM<br />
Limited to: S/N 5226 Prior to installation of this modification it 03.03.2<strong>01</strong>0<br />
CompatibilityDesign definition: Aerodata's<br />
must be determined thatthe<br />
documents reference MDL-A/C-075 Rev.<br />
interrelationship between this modification<br />
3,23/02/2<strong>01</strong>0, Master Document List<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030547 AERODATA AG P-<strong>EASA</strong>.A.S.03903 L-410UVP-E15 Installation of Aerodata Flight Inspection<br />
System AD-AFIS-130<br />
10033638 AERODATA AG REV. 1 BAE.125 SERIES 800A<br />
HAWKER 800 (U125)<br />
Installation of Aerodata FIS (Flight Inspection<br />
System).The FIS installation consists of nonessential<br />
sensor systems in thecabin and a<br />
camera system in the tail cone to enable<br />
calibrationmissions for navigation equipment.<br />
10034248 AERODATA AG REV. 1 B200 Modification for Maritime Patrol MissionThe<br />
modification consist of the installation of a belly<br />
mounted radomewith integrated camera<br />
elevator, a drop hatch and bubble<br />
windowsdesigned by Hawker Beechcraft and<br />
the integration of non-essentialsystems and<br />
sens<br />
Limited to serial no. 892318 and 892329 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.06.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.02.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.09.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 20/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036103 AERODATA AG REV. 1 B300 Installation of Aerodata Automatic Flight None. Prior to installation of this modification it 16.08.2<strong>01</strong>1<br />
Inspection System AD-AFIS-112.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036478 AERODATA AG LBA EMZ NR. TA0607 FALCON 10 Change to LBA STC approval "EMZ Nr.<br />
TA0607 and AFM approval DTM-721A"dated<br />
26 June 2002.Change of procedures<br />
"Instructions for Continued Airworthiness"<br />
inrelation with RVSM qualification and update<br />
of the aircraftconfiguration.<br />
10036479 AERODATA AG LBA EMZ NR. TA0600 FALCON 10 Change to LBA STC approval "EMZ Nr.<br />
TA0600 and AFM approval DTM-721A"dated<br />
06 June 2002.Change of procedures<br />
"Instructions for Continued Airworthiness"<br />
inrelation with RVSM qualification and update<br />
of the aircraftconfiguration.<br />
10039634 AERODATA AG B300 Installation of Aerodata Automatic Flight<br />
Inspection System AD-AFIS-0270<br />
10<strong>04</strong>0364 AERODATA AG B300 Installation of Aerodata Automatic Flight<br />
Inspection System AD-AFIS-0280<br />
10<strong>01</strong>4029 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>095 LEARJET 60 Installation of a Cabin Entertainment System<br />
with Airshow 4X0.<br />
10<strong>01</strong>41<strong>01</strong> AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>203 LEARJET 60 Installlation of an Iridium Satelitte ICS-200<br />
System.<br />
Restricted to S/N 183 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.09.2<strong>01</strong>1<br />
Restricted to S/N 216. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.09.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.05.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.06.2<strong>01</strong>2<br />
For certification basis refer to FAA TCDS<br />
A10CE plus FAR 25.1309 at Amdt. 25-41 and<br />
FAR 25.1529 at Amdt. 25-54 and plus JAA<br />
TGL No.17, IFE Systems.<br />
For certification basis refer to FAA TCDS<br />
A10CE plus FAR 25.1309 at Amdt. 25-41 and<br />
FAR 25.1529 at Amdt. 25-54.<br />
10<strong>01</strong>4132 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>242 HAWKER HS 125-700B Installation of Traffic Alert Collision and<br />
Avoidance System Collins TCAS 4000<br />
30.05.2005<br />
10<strong>01</strong>4221 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>383 BAE 125 SERIES 800A<br />
BAE 125 SERIES 800B<br />
Installation of a L-3 F1000 SSFDR 10.11.2005<br />
10<strong>01</strong>4222 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>384 BAE 125 SERIES 800A<br />
Installation of a Rockwell Collins TCAS 4000<br />
10.11.2005<br />
BAE 125 SERIES 800B<br />
with Dual TDR-94D and Dual RTU-4210<br />
System<br />
10<strong>01</strong>4223 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>385 BAE 125 SERIES 800A<br />
Installation of an Universal Avionics System<br />
10.11.2005<br />
BAE 125 SERIES 800B<br />
Corporation Flight Management System UNS-<br />
1L<br />
10<strong>01</strong>4224 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>386 BAE 125 SERIES 800A<br />
BAE 125 SERIES 800B<br />
Installation of an UASC CVR-30B 10.11.2005<br />
10<strong>01</strong>4382 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>666 LEARJET 25C Collins TCAS-4000 with Dual TDR-94D Certification Basis of Change: FAR 25 as<br />
03.03.2006<br />
System Installation<br />
defined in TCDS A10CE issue 55, additionaly<br />
JAA Leaflet No. 8, Rev. 2 (ACAS II), JAA<br />
Leaflet No. 13, Rev. 1 (Modes S ELS)<br />
10<strong>01</strong>4385 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>671 HAWKER HS 125-700B Installation of Honeywell EGPWS Mark VIII<br />
System and interface to Honeywell KMD-850<br />
MFD via a KAC-502 EGPWS Module.<br />
10<strong>01</strong>4386 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.<strong>01</strong>672 HAWKER HS 125-700B Installation of Honeywell ART 2000 Weather<br />
Radar System and a Honeywell KMD-850<br />
MFD.<br />
10<strong>01</strong>4547 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02637 LEARJET 55 Cockpit Voice Recorder CVR-30B Installation<br />
(Universal Avionics System Corp.)<br />
28.<strong>04</strong>.2005<br />
28.<strong>04</strong>.2005<br />
None. 19.<strong>04</strong>.2006<br />
None. 19.<strong>04</strong>.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 21/<strong>462</strong><br />
24.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4548 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02638 LEARJET 55 Solide State Flight Data Recorder F1000<br />
Installation (L3-AR)<br />
24.07.2006<br />
10<strong>01</strong>4560 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02659 LEARJET 55 FMS UNS-1L Installation (Universal Avionics<br />
System Corp.)<br />
24.07.2006<br />
10<strong>01</strong>4634 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02777 LEARJET L-55 Installation of TAWS / RMI ST3400 (Sandel) This STC is approved only for the product<br />
23.<strong>01</strong>.2007<br />
System<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4662 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02819 LEARJET 31A Enhanced Surveillance Mode S Transponder<br />
Upgrade (Honeywell)<br />
28.03.2007<br />
10<strong>01</strong>4669 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02828 REV. 1 HAWKER HS 125-700B FMS UNS-1L System Installation (UASC) 07.<strong>01</strong>.2008<br />
10<strong>01</strong>4700 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02869 LEARJET 31 TCAS-4000 / Dual TDR-94D Mode S<br />
Transponder Systems Installation (Collins)<br />
26.03.2007<br />
10<strong>01</strong>4706 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02878 LEARJET 31 FMS UNS-1L System Installation (UASC) Certification basis of the change FAR 25,<br />
additionally JAA Leaflet No. 10, Precision<br />
(RNAV), AMC 20-4 (Basic RNAV), AMC 20-5<br />
(GPS).<br />
21.03.2007<br />
10<strong>01</strong>4755 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.02942 BAE 125 SERIES 800B TAWS ST3400 System Installation (Sandel) 13.<strong>04</strong>.2007<br />
10<strong>01</strong>4955 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03223 LEARJET 35A MFD-640 with WX Controller RP-1008<br />
Installation (UASC)<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>4956 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03224 LEARJET 35A Cockpit Voice Recorder CVR-120 Installation<br />
(UASC).<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>4962 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03233 LEARJET 35A Dual VHF NAV VIR-30/DME-40 replacement<br />
by VIR-32/DME-42 with Dual CTL-32<br />
installation (Collins).<br />
N/A <strong>04</strong>.12.2007<br />
10<strong>01</strong>4968 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03247 LEARJET 35A Enhanced Surveiilance Mode S Transponder<br />
modification (Collins).<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>4969 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03248 LEARJET 35A Centre Pedestal Enlargement / Nose<br />
Compartment Rearrangement.<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>5051 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03370 LEARJET 60 GPWS to EGPWS System Upgrade<br />
(Honeywell)<br />
21.02.2008<br />
10<strong>01</strong>5150 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03511 LEARJET 35A Flight Crew Intercom System (NAT) Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10.07.2008<br />
10<strong>01</strong>5233 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03658 LEARJET 35A Solid State Flight Data Recorder SSFDR<br />
Installation (L-3)<br />
10<strong>01</strong>5234 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03659 LEARJET 35A Cockpit Voice Recorder CVR-30B Installation<br />
(UASC).<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
nterrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product. The insta<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5272 AERO-DIENST GMBH & CO. KG <strong>EASA</strong>.A.S.03754 LEARJET 55 FMS Upgrade to PRNAV Compliance (UASC). 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10036586 AERO-DIENST GMBH & CO. KG LEARJET 35A Installation of Honeywell (Allied Signal)<br />
Enhanced Ground ProximityWarning MK VIII<br />
System<br />
<strong>04</strong>.11.2008<br />
<strong>04</strong>.11.2008<br />
02.02.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.09.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 22/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4006 AERODISA S.L. <strong>EASA</strong>.A.S.<strong>01</strong><strong>04</strong>3 EMBRAER EMB-120 Installation TCAS IIHoneywell TCAS II TPU Subject th the conditions, limitations and<br />
31.07.2006<br />
67A Processor and Configuration Module with procedures contained in Doc No.<br />
lower and upper ANT 67A Antennas, dual IVA- AED20<strong>04</strong>_<strong>01</strong>M_D03_OP1 "Flight Manual<br />
81D TA/RA/VSI System Displays, one Supplement for 1 transponder installation", Rev<br />
MST67A Mode S Transponder (OPTION 1) or 0 or AED20<strong>04</strong>_<strong>01</strong>M_D03_OP2 " Flight Manual<br />
two MST67A Mode S Transponder (OPTION Suppplement for 2 transponders installation",<br />
2) with lower<br />
Rev. 0<br />
10<strong>01</strong>4051 AERODISA S.L. <strong>EASA</strong>.A.S.<strong>01</strong>133 FAIRCHILD SWEARINGEN SA TCAS II installation on Fairchild SA<br />
Subjected to the conditions, limitations and<br />
<strong>04</strong>.09.2006<br />
227 SE<br />
227Honeywell TCAS II TPU 67A Processor pocedures contained in Doc N°<br />
FAIRCHILD SWEARINGEN SA and Configuration Module with lower and upper AED20<strong>04</strong>_02M_D03 "Flight Manual<br />
227-BC<br />
ANT 67A Antennas, dual IVA-81D TA/RA/VSI Supplement", Rev 0<br />
System Displays, two MST67A Mode S<br />
Transponders with lower and uppar KA60<br />
Omnidirectional Ant<br />
10<strong>01</strong>4286 AERODISA S.L. <strong>EASA</strong>.A.S.<strong>01</strong>523 DC-8-62 SERIES Revision to the cargo modification on DC-8-62. Limited to DC-8-62 series airplanes which have<br />
18.<strong>04</strong>.2007<br />
Compliance with FAA AD 20<strong>01</strong>-26-<strong>04</strong> & AD been converted from a passenger to a cargo-<br />
20<strong>01</strong>-26-<strong>01</strong>.<br />
carrying ("freighter") configuration by FAA STC<br />
No. SA1802SO, but with a deviation in the<br />
main deck cargo 9g crash barrier that was<br />
installed following FAA STC No. SA<br />
10<strong>01</strong>4368 AERODISA S.L. <strong>EASA</strong>.A.S.<strong>01</strong>638 EMBRAER EMB-120 Structural Permanent element for a Winch<br />
installation.<br />
10<strong>01</strong>4475 AERODISA S.L. <strong>EASA</strong>.A.S.02537 FALCON 20 AED2006-<strong>01</strong>M: TCAS II Installation for Falcon<br />
20.<br />
10<strong>01</strong>4608 AERODISA S.L. <strong>EASA</strong>.A.S.02734 EMBRAER EMB-120 AED2006-03M: TAWS Installation on<br />
EMBRAER 120.<br />
10<strong>01</strong>4609 AERODISA S.L. <strong>EASA</strong>.A.S.02735 FAIRCHILD SWEARINGEN SA<br />
226 SE<br />
FAIRCHILD SWEARINGEN SA<br />
227 SE<br />
AED2006-<strong>04</strong>M: TAWS installation on Fairchild<br />
SA 226/227<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
1. See FM Supplement AED2006-<strong>01</strong>M_D03<br />
Section I: LIMITATIONS.2. Certification basis<br />
CS 25 Orig issue.3. TGL 8 Rev.2 "ACAS II"<br />
complied with.4. TGL 13 Rev.1 "Elementary<br />
Surveillance" complied with.5. Prior to<br />
installation of this modification<br />
1. See FM Supplement AED2006-<br />
<strong>01</strong>M_MDL_D03 Section II: LIMITATIONS.2.<br />
Certification basis per ANAC TCDS EA-8505:<br />
RBHA 25 corresponding to FAR 25 Amdt 54.3.<br />
TGL 12 complied with.4. SANDEL<br />
mandatory SB 3400-09 to be incorporated.5.<br />
Prior to ins<br />
See FM Supplement AED2006-<strong>04</strong>M_D03<br />
Section II: Limitations.Certification basis per<br />
FAA TCDS A8SW: FAR 23 Amdt 6.TGL 12<br />
10<strong>01</strong>4735 AERODISA S.L. <strong>EASA</strong>.A.S.02918 MYSTERE FALCON 20 AED2006-14M: TAWS installation for Falcon<br />
complied with.<br />
See FM Supplement AED2006-14M_D03<br />
26.07.2007<br />
20.<br />
Section II "Limitations".Certification basis:<br />
CS25 initial issue.TGL 12 complied<br />
with.SANDEL mandatory SB 3400-09 to be<br />
incorporated.<br />
10<strong>01</strong>4748 AERODISA S.L. <strong>EASA</strong>.A.S.02933 MD80 SERIES LOPA for MD80 Series 168 Pax/ Layout The installation should not be incorporated in<br />
31.05.2007<br />
passenger arrangement to allow 168<br />
any other aircraft unless it is determined that<br />
passengers capacity.<br />
the interrelationship between this installation<br />
and any previously approved configuration will<br />
not introduce any adverse effect upon the<br />
airworthiness of the air<br />
10<strong>01</strong>4776 AERODISA S.L. <strong>EASA</strong>.A.S.02974 PIPER PA-23-250 Upgrade of NAV/COM Equipment for IFR<br />
navigation.<br />
S/N: 27-7754134. 18.07.2007<br />
10<strong>01</strong>5273 AERODISA S.L. <strong>EASA</strong>.A.S.03756 FALCON 900 Upgrade of dual Mode S SSR Transponder 1. Prior to installation of this modification the<br />
27.03.2009<br />
installation to provide both Elementary Mode S installer must determine that the<br />
Surveillance Flight ID and Enhanced Mode S interrelationship between this modification and<br />
Surveillance capability (EHS Capable). any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10028207 AERODISA S.L. P-<strong>EASA</strong>.A.S.03152 REV. 1 FALCON 2000 Pocket Door Installation for Falcon 2000In Design Change limited to Falcon 2000 aircraft Prior to installation of this modification it 21.12.2009<br />
accordance with Aerodisa Master Data List serial number 55<br />
must be determined thatthe<br />
AED2007-09M_MDL Revision 3,dated <strong>04</strong>th<br />
interrelationship between this modification<br />
December 2009 or later revisions approved by<br />
and any other previouslyinstalled<br />
<strong>EASA</strong><br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 23/<strong>462</strong><br />
<strong>04</strong>.11.2008<br />
18.07.2007<br />
05.07.2007<br />
31.05.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030750 AERODISA S.L. P-<strong>EASA</strong>.A.S.03802 A310 EHS upgrade on Honeywell TRA-67A066- None. Prior to installation of this modification the 03.07.2009<br />
<strong>01</strong>127-1402This STC upgrades existing<br />
installer must determinethat the<br />
transponder sysytem by installing Mode<br />
interrelationship between this modification<br />
SEnhance surveillance (EHS).<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10031538 AERODISA S.L. DC9-80 (MD80) Aeronautical Capsat Transceiver None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.08.2<strong>01</strong>0<br />
10<strong>04</strong>0651 AERODISA S.L. B300 FMS Upgrade for King Air B300. S/N Limitation:AIRPLANE MODEL HAWKER<br />
BEECHCRAFT B300 S/N FL-255<br />
10<strong>04</strong>1087 AERODISA S.L. DC 9-87, MD88<br />
DC9-81, DC9-82, DC9-83,<br />
Equipment update for MD80 series SatCom<br />
System - Update for MD80 SeriesSatCom<br />
System approved under <strong>EASA</strong> STC<br />
This STC is applicable only to aeroplanes that<br />
have already incorporatedAerodisa STC<br />
certified as <strong>EASA</strong> STC 10031538 dated 24<br />
August 2<strong>01</strong>0<br />
The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21A.109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/or<br />
repair<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation Prior to<br />
installation of this modification it must be<br />
determined thatthe interre<br />
10<strong>01</strong>6341 AERODYME CORPORATION <strong>EASA</strong>.IM.A.S.02654 FAA STC SA00246BO COMMANDER AIRCRAFT 114<br />
COMMANDER AIRCRAFT 114A<br />
Installation of Lycoming IO-540-T4B5 engine. 27.11.2007<br />
10<strong>01</strong>67<strong>01</strong> AERODYME CORPORATION <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>6 FAA STC SE00242BO LYCOMING ENGINES IO-320-B Installation of induction intake pipes in 1. This STC must be installed concurrently<br />
<strong>04</strong>.03.2008<br />
accordance with Aerodyme 114/A/B/TC 320 with STC <strong>EASA</strong>.IM.A.S.02653.2. If the<br />
HP Engine Conversion Installation Instructions, holder agrees to permit another person to use<br />
dated July 20th 2006,or later revisions of the this certificate to alter a product, the holder<br />
above listed document approved by <strong>EASA</strong> in must give the other person written evidence of<br />
accordance with ED decision 20<strong>04</strong>/<strong>04</strong>/C that permission.<br />
10034211 AERO-DYNE REPAIR SERVICES LTD. REV. 1 TCCA STC SH08-41 BELL 407 External MGT and Torque Indicating System<br />
Installation<br />
10038920 AEROFDC WA LP REV. 1 FAA STC SR02059SE EC135 P2+, EC135 P2 Installation of an engine IBF system in<br />
accordance with theFDC/aerofilter Master<br />
Document List 1135-SERIES-MDL-5 and<br />
FDC/aerofilter Installation Instructions 1135-<br />
Series-INS-5.<br />
10<strong>04</strong>0685 AEROFDC WA LP <strong>EASA</strong>.IM.R.S.00273 REV. 1 FAA STC SR00811SE AS 350 B, AS 350 B1, AS 350 B2<br />
AS 350 B3, AS 350 BA<br />
10<strong>01</strong>6764 AEROLITE GmbH <strong>EASA</strong>.IM.R.S.<strong>01</strong>095 - EUROCOPTER DEUTSCHLAND<br />
MBB-BK<br />
10<strong>01</strong>7183 AEROLITE GmbH <strong>EASA</strong>.R.S.<strong>01</strong>316 EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
Installation of engine inlet air filtration system<br />
iaw Master DrawingList No 1350-10<strong>01</strong> revision<br />
D and Installation Instructions 1350-INST-<br />
1,revision IR Notes: 1. STC<br />
<strong>EASA</strong>.IM.R.S.00273 issued on 28 October<br />
20<strong>04</strong> was the validation ofFAA STC<br />
SR00811SE first i<br />
Installation of EC 145 EMS Equipment P/N<br />
145121-5<strong>01</strong><br />
16.07.2<strong>01</strong>2<br />
20.08.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.08.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.08.2<strong>01</strong>2<br />
This STC is not applicable to AS350B3 model<br />
helicopters incorporatingmodification OP-3369<br />
(2370kg weight extension)This STC is not<br />
applicable to AS350B2 model helicopters<br />
equipped withVEMD major modificationThis<br />
STC is not applicable to AS350B3 model helic<br />
1. No Smoking when Medical Oxygen Cabinet<br />
is installed.2. The LOX System can only be<br />
operated during flight when appropriately<br />
trained medical crew are on board.3. This STC<br />
is approved only for the product configuration<br />
as defined in the approved design da<br />
Installation of NATO Stretcher Retainer. The NATO Stretcher (NSN 6530-<strong>01</strong>-380-<br />
7309) referred to in this installation is not part<br />
of this STC.<br />
Prior to installation of this modification it 19.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 24/<strong>462</strong><br />
05.09.2005<br />
03.11.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7241 AEROLITE GmbH <strong>EASA</strong>.R.S.<strong>01</strong>429 REV. 2 AB139, AW139 EMS Kit Light Lateral Stretcher P/N139127- None The approval holder shall fulfill the 30.08.2<strong>01</strong>1<br />
5<strong>01</strong> Note: this STC is issued for the purpose of<br />
obligations of Part 21,<br />
transferring STC No.10<strong>01</strong>7241 Rev. 1 and<br />
Paragraph21A.118A. Prior to installation<br />
AFM approval 10029997 of Aerolite AG to the<br />
of this modification it must be determined<br />
aboveidentified new holder.<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
rep<br />
10<strong>01</strong>7280 AEROLITE GmbH <strong>EASA</strong>.R.S.<strong>01</strong>528 REV. 4 MBB-BK 117 C-2 Stylence Package (VIP Kit) Aerolite P/N When the Cargo Separation Wall is installed Prior to installation of this modification it 02.03.2<strong>01</strong>2<br />
145305-5<strong>01</strong>/-502 (Revision<br />
the original BK117 C-2 smokedetector kit must must be determined thatthe<br />
to<strong>EASA</strong>.R.S.<strong>01</strong>528)Passenger Seat<br />
be installed in the cargo compartment.When interrelationship between this modification<br />
Modification P/N 021376-502, Curtain Inst. P/N operating the rotorcraft with the doors open or and any other previouslyinstalled<br />
145319-502and Finishing P/N 145302-506/- removed, thelimitations given in Flight Manual modification and/ or repair will introduce<br />
507<br />
Supplement No. FMS 9.1-2 mus<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10033323 AEROLITE GmbH REV. 1 429 EMS Equipment P/N 429020-5<strong>01</strong>/-502This<br />
STC revision introduces the new EMS<br />
Equipment P/N 429020-502.In addition the<br />
following modifications to the existing EMS<br />
EquipmentP/N 429020-5<strong>01</strong> are covered by this<br />
change:- Introduction of Cargo Platform P/N<br />
429022-50<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
24.05.2<strong>01</strong>1<br />
10036324 AEROLITE GmbH AB 139, AW 139 EMS Equipment P/N 139250-5<strong>01</strong> none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.08.2<strong>01</strong>1<br />
10037576 AEROLITE GmbH REV. 1 AW109SP EMS Equipment with Floor Modification, EMS<br />
Gas, PAX/Med Seats,Stretcher, and Cabinet<br />
Installations in accordance with<br />
AeroliteConfiguration Matrix Drawing No. 109-<br />
0002060<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.05.2<strong>01</strong>2<br />
10039929 AEROLITE GmbH AW109SP EMS Equipment P/N 109-0008662-5<strong>01</strong> None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.06.2<strong>01</strong>2<br />
10<strong>04</strong>2079 AEROLITE GmbH AW139 "EMS Equipment P/N 139-00<strong>04</strong>728-5<strong>01</strong>". None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.11.2<strong>01</strong>2<br />
10<strong>01</strong>4816 AEROLITE MAX BUCHER AG <strong>EASA</strong>.A.S.03024 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) 3rd Stretcher and Cargo Platform. P/N 6<strong>04</strong>489- S/N: 5529/5530/5540<br />
5<strong>01</strong><br />
20.06.2007<br />
10<strong>01</strong>4983 AEROLITE MAX BUCHER AG <strong>EASA</strong>.A.S.03275 MD-11 Modification of two SICMA Mono F/C Seat It is the responsibility of the installer to make<br />
16.11.2007<br />
Type 17<strong>01</strong>1(X)1-(XX) as detailed in Lufthansa sure that this installation is certified for the use<br />
Supplemental Type Definition Document STDD in effective aircraft.Compliance with the<br />
25-05/32 R02 and in accordance with Aerolite following Cabin Safety requirements is not<br />
Bucher Master Document List MDL-06-<strong>01</strong>5 covered by this approval:1. FAR/JAR 25.791<br />
Rev. B for installation in MD-11 MSN48533. Passenger information<br />
10<strong>01</strong>5764 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.A.S.<strong>01</strong>800 REV. 2 L35A EMS Equipment InstallationIntroduction of Limited to: S/N: 628, 663 The approval holder shall fulfil the<br />
stretcher configuration P/N Aerolite 250071-<br />
obligations of Part 21,<br />
506 andpower box installation P/N Aerolite<br />
Paragraph21.A109. Prior to installation of<br />
250080-503 into existing EMSconfiguration P/N<br />
this modification it must be determined<br />
Aerolite 250070-5<strong>01</strong><br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 25/<strong>462</strong><br />
06.<strong>01</strong>.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6720 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>4 - AGUSTA A-109 E Installation of Medical Oxygen Cabinet P/N 1. No Smoking when Medical Oxygen Cabinet<br />
18.05.2005<br />
109111-5<strong>01</strong><br />
is installed2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shal<br />
10<strong>01</strong>6722 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>9 - MD HELICOPTERS MD900 External Hoist Mirror Installation P/N 9005024- 1. Only for VFR operations.2. Only approved<br />
5<strong>01</strong>, P/N 9005024-502, P/N 9005024-503, P/N configurations to be installed.3. This STC is<br />
9005024-5<strong>04</strong>.Flight Manual Supplement FMS- approved only for the product configuration as<br />
4<strong>04</strong>.<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engin<br />
10<strong>01</strong>6742 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong>068<br />
REVISION<br />
AGUSTA AB-139 Installation of Aerolite EMS equipment P/N<br />
1390<strong>01</strong>-5<strong>01</strong>, 1390<strong>01</strong>-502<br />
10<strong>01</strong>6765 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong>096 REV. 1 MBB-BK 117 C-2 EMS Equipment P/N 145146-5<strong>01</strong>Revision 1<br />
introduces a new stretcher and various<br />
provisions forinstallation of medical<br />
equipments.<br />
10<strong>01</strong>6793 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong>143 REV. 1 EUROCOPTER DEUTSCHLAND<br />
MBB-BK<br />
1. No smoking permitted when the Oxygen<br />
system is installed.2. The occupant of the LH<br />
forward Aft facing seat must wear a helmet.3.<br />
For the installation of the EMS equipment the<br />
following Agusta equipment must be installed:the<br />
EMS Electrical Syst<br />
EMS Equipment P/N 145181-5<strong>01</strong>Introduction 1. This STC is approved only for the product<br />
of a second configuration with a secondary RH configuration as defined in the approved design<br />
stretcher installation on EMS integral floor data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.2. No smoking i<br />
08.07.2005<br />
19.06.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.<strong>04</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>6794 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong>144 REV. 1 AGUSTA A109S A109S EMS equipment P/N 109115-50X. This The Agusta provision for EMS kits (Aerolite) Prior to installation of this modification the 18.<strong>01</strong>.2<strong>01</strong>0<br />
revision 1 of <strong>EASA</strong> STC<strong>EASA</strong>.IM.R.S.<strong>01</strong>144 is P/N 109-0814-22-5<strong>01</strong> has tobe installed. installer must determinethat the<br />
related to the introduction of<br />
interrelationship between this modification<br />
stretcherconfiguration Aerolite P/N 109<strong>01</strong>17-<br />
and any otherpreviously installed<br />
503.<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The approval ho<br />
10<strong>01</strong>6817 AEROLITE MAX BUCHER AG P-<br />
REV. 1 MBB-BK117 C-2 Master Document List MDL-06-002 includes 2 No smoking in the rotorcraft. When the co- The approval holder shall fulfil the 09.08.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>182<br />
EMS configurations:Both configurations include pilots seat has been removed and the medical obligations of Part 21,<br />
1 integral floor, 2 medical seats, 1<br />
cockpit seat isinstalled in the fwd or aft facing Paragraph21.A109. Prior to installation of<br />
primarystretcher, 1 medical stowage cabinet, 1 direction the cyclic and collectivestick must be this modification it must be determined<br />
medical supply unit, one bottlerack and removed. Compatibility with NVIS has not been thatthe interrelationship between this<br />
retainers for medical equipment. In the ri demonstrated. Compatibil<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10<strong>01</strong>6820 AEROLITE MAX BUCHER AG <strong>EASA</strong>.IM.R.S.<strong>01</strong>185 - EUROCOPTER DEUTSCHLAND "EMS Equipment P/N 135138-502This major 1. Limited to S/N <strong>01</strong>052. No Smoking when<br />
22.03.2006<br />
EC-135<br />
modification covers an EMS equipment Medical Oxygen cabinet is installed3. This STC<br />
inculding medical seats, stretcher, oxygen is approved only for the product configuration<br />
cylinder rack, stowage cabinet and Oxylog and as defined in the approved design data<br />
Propaq retainersSome components, indentified referred to in the paragraph "Description".<br />
in the equipment list EQL-06-003 and already Compatibility with other aircraft/engi<br />
10<strong>01</strong>7085 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.00397 REV. 2 EC135 SERIES EMS Equipment DRF - P/N 135405-5<strong>01</strong>/-502.<br />
Revision 1 to extend approval from P1/P2,<br />
T1/T2 to all EC135 models. Revision 2 to<br />
introduce reversible C/P seat installation<br />
configurationP/N 135331-503 into EMS<br />
equipment configuration P/N 135405-5<strong>01</strong> and<br />
tointrodu<br />
10<strong>01</strong>7088 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.0057 REV. 3 EC 135 EMS Equipment P/N 135375-5<strong>01</strong> / 135375-<br />
502STC revision 3 relates to:- EMS<br />
Integralfloor Inst. P/N 1353<strong>01</strong>-503 incl. EO-10-<br />
<strong>01</strong>7 (Aeration CoverKit P/N 0071664-5<strong>01</strong>,<br />
applicable to EMS Equipment P/N 135375-502<br />
only)- Med. Equipment Rails Inst. P/N 135552-<br />
5<strong>01</strong>/-502<br />
22.06.2006<br />
P/N 1353<strong>01</strong>-503 and P/N 135543-503 are only Prior to installation of this modification it 05.02.2<strong>01</strong>0<br />
valid for the rotorcraft S/N870 and subsequent. must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.08.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 26/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7157 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>265 EUROCOPTER DEUTSCHLAND APC-06-006 EMS equipment installation fro<br />
24.07.2006<br />
MBB-BK<br />
BK-117-C2 (EC145), part number 145221-5<strong>01</strong><br />
10<strong>01</strong>7164 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>272 EUROCOPTER DEUTSCHLAND Installation of EMS equipment Aerolite P/N Only S/N 0<strong>04</strong>1 15.06.2006<br />
EC-135<br />
135570-5<strong>01</strong><br />
10<strong>01</strong>7172 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>286 REV. 1 EUROCOPTER DEUTSCHLAND Installation of EMS Equipment P/N 135500- Prior to installation of this modification the<br />
29.05.2008<br />
EC-135-<br />
5<strong>01</strong> or P/N 135500-502. This revision extends installer must determine that the<br />
the applicability to \ec135P2+ and EC135T2+. interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7187 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>324 REV. 1 EC135 P2(CPDS), P2+<br />
EMS Equipment P/N 135572-5<strong>01</strong>Change This STC is limited to aircraft with S/N 0337 The approval holder shall fulfill the 22.06.2<strong>01</strong>0<br />
EC135 T2(CPDS), T2+<br />
covered by Rev. 1 to<br />
and subsequent onlyThis STC is approved only obligations of Part 21,Paragraph<br />
<strong>EASA</strong>.R.S.<strong>01</strong>324:Installation of EMS Retainer for the product configuration as defined inthe 21.A109Prior to installation of this<br />
Set P/N 135742-5<strong>01</strong> into Aerolite<br />
approved design data referred to in the modification it must be determined<br />
EMSEquipment P/N 135572-5<strong>01</strong><br />
paragraphs "Description" and"Associated thatthe interrelationship between this<br />
Technical Documentation". Compatibilit modification and any other<br />
previouslyinstalled modification and/ or<br />
10<strong>01</strong>7194 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>331 AGUSTA AB-139<br />
AGUSTA AW-139<br />
10<strong>01</strong>7209 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>361 AGUSTA AB-139<br />
AGUSTA AW-139<br />
10<strong>01</strong>7214 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>371 EUROCOPTER AS365 SERIES<br />
EUROCOPTER DEUTSCHLAND<br />
EC-135<br />
EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
EUROCOPTER DEUTSCHLAND<br />
10<strong>01</strong>7215 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>372 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
EUROCOPTER DEUTSCHLAND<br />
EC-635<br />
EUROCOPTER DEUTSCHLAND<br />
EC-635-<br />
10<strong>01</strong>7216 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>373 EUROCOPTER DEUTSCHLAND<br />
EC-135<br />
EUROCOPTER DEUTSCHLAND<br />
EC-635<br />
10<strong>01</strong>7217 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>374 REV. 1 SEE ATTACHED <strong>EASA</strong><br />
APPROVED TYP<br />
EC-635<br />
EMS Medical Rack Installation p/n 139099-5<strong>01</strong> EMS (Medevac) electrical provisions<br />
3G2564A<strong>01</strong>441 must be installed with<br />
modifications according to 3G2564W002<strong>01</strong><br />
(page 1 only).<br />
P/N 139086-5<strong>01</strong>.The equipment contains a<br />
specific cabin floor layer, 2 medical seats<br />
installed in the aft part of the cabin, one or 2<br />
stretchers, amedical supply cabinet and various<br />
stowage compartments.<br />
Armasuisse1 LH Stretcher Installation. P/N<br />
135586-5<strong>01</strong>.<br />
Armasuisse 2 RH Stretcher Installation P/N<br />
135587-5<strong>01</strong>.<br />
Life Support Module installation:P/N 135588-<br />
5<strong>01</strong>. The installation consists of a stowage<br />
provision for up to three oxygen bottles. The is<br />
module installed in the forward part of the<br />
passenger cabine.<br />
EMS Stretcher InstallationInstallation P/N<br />
135525-5<strong>01</strong>, -502 for R/H side and -503, -5<strong>04</strong><br />
for the L/H side.Note: This change to<br />
<strong>EASA</strong>.R.S.<strong>01</strong>374 introduces a new stretcher<br />
installation on the left hand side of the<br />
1. When oxygen is installed No smoking<br />
permitted.2. The occupant of the LH FWD<br />
Aft facing seat must wear a helmet.3. When<br />
the secondary stretcher is occupied the head<br />
protection pad must be installed between the<br />
stretchers.4. Following equipmen<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. P/N 135525-5<strong>01</strong> and -503 are eligible for<br />
installation in S/N up to 03362. P/N 135525-<br />
502 and -5<strong>04</strong> are eligible for installation in S/N<br />
0337 and up3. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelations<br />
10<strong>01</strong>7229 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>400<br />
rotorcraft.<br />
EUROCOPTER DEUTSCHLAND EMS Stretcher Installation Police Thüringen<br />
12.11.2008<br />
BK117 C<br />
(Aerolite P/N 145285-5<strong>01</strong>).<br />
10<strong>01</strong>7231 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>403 REV. 1 AGUSTA AB-139<br />
Installation P/N 139084-5<strong>01</strong> for 3 stretcher 1. Agusta EMS (Medevac) electrical<br />
28.11.2007<br />
AGUSTA AW-139<br />
units with relevant cabin floor rails and featuring provisions 3G2564A<strong>01</strong>411 must be installed<br />
each, dedicated oxygen and electrical with modifications according<br />
distribution systems and oxygen bottles 3G2564W002<strong>01</strong>.2. When oxygen is installed<br />
stowage provisions.<br />
No smoking permitted.3. Required minimum<br />
crew is defined in FMS-07-008.4. The<br />
dimensional limitat<br />
10<strong>01</strong>7232 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>406 REV. 1 EC 135 T2, EC 135 P2,<br />
EMS Stretcher Installation P/N 135591- To ensure patient head protection from injuries Prior to installation of this modification it 20.<strong>04</strong>.2<strong>01</strong>0<br />
EC 135 T2+, EC 135 P2+ 5<strong>01</strong>.Introduction of the Cirrus Stretcher Model during crash, there mustbe at least 200mm of must be determined thatthe<br />
EC 135, EC 135 T1, EC 135 P1, CI-1 <strong>01</strong> 0-123-<strong>01</strong> into thealready certified space between the forward end of each interrelationship between this modification<br />
EC635 P2+<br />
Cirrus 1<strong>01</strong>0 Stretcher Installation P/N135574- installedstretchers and any equipment installed and any other previouslyinstalled<br />
EC635 T1 (CDPS), EC635 T2+ 5<strong>01</strong>/-502/-503/-5<strong>04</strong> (STC <strong>EASA</strong>.R.S.<strong>01</strong>406) forward of the stretchers.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 27/<strong>462</strong><br />
08.03.2007<br />
21.11.2007<br />
03.07.2007<br />
03.07.2007<br />
31.10.2007<br />
24.02.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7249 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>448 AGUSTA AB-139<br />
EMS Multi-Mission KitInstallation of the EMS Rotorcraft Operational Limitations: (ref.<br />
<strong>04</strong>.<strong>04</strong>.2008<br />
AGUSTA AW-139<br />
Multimission Kit Aerolite-P/N 139124-5<strong>01</strong> into (R)FMS-08-003 Rev N/C)-When oxygen is<br />
cabin of AgustaWestland rotorcraft model installed no smoking permitted-When<br />
AB/AW 139.The Kit covers EMS equipment equipment rack is installed occupant of LH<br />
(ref. Aerolite-P/N 139086-5<strong>01</strong>) certified per FWD aft-facing seat must wear a helmet-<br />
<strong>EASA</strong>.R.S.<strong>01</strong>361 adding a new so-called Mu When secondary stretcher is occupied head<br />
protection pad m<br />
10<strong>01</strong>7252 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>454 REV. 2 EC135 P1(CDS), EC135 Change to Installation of EMS Equipment This STC is limited to S/N 337 and above. Prior to installation of this modification it 15.10.2<strong>01</strong>2<br />
P1(CPDS)<br />
Aerolite P/N 135602-502Change comprises of:-<br />
must be determined thatthe<br />
EC135 P2(CPDS), EC135 P2+ Introduction of Support Panel Assy P/N 0<strong>04</strong>191-<br />
interrelationship between this modification<br />
EC135 T1(CDS), EC135<br />
5<strong>01</strong> into DC Power SystemInst. P/N 135615-<br />
and any other previouslyinstalled<br />
T1(CPDS)<br />
5<strong>01</strong>- Introduction of EMS Integralfloor Inst. P/N<br />
modification and/ or repair will introduce<br />
EC135 T2(CPDS), EC135 T2+ 1353<strong>01</strong>-503- Introduction of Reversi<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7263 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>474 REV. 1 AGUSTA AB-139<br />
AGUSTA AW-139<br />
EMS Provisions Kit. Revision of STC for<br />
incorporation of PAX seat configurations<br />
Aerolite P/N 139117-505; 139117-506 and<br />
139117-507of 12, 14 and 15 PAX seats<br />
10<strong>01</strong>7265 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>479 REV. 2 AW139 AW 139 EMS Kit P/N 139097-5<strong>01</strong> Revision 1<br />
related changes:- Stretcher Inst. P/N 139190-<br />
5<strong>01</strong>/-503/-505/-507/-511/-513/-515/-517/-6<strong>01</strong>/-<br />
603/-605/-607/-611/-613/-615/-617- Cargo<br />
Platform Inst. P/N 139191-5<strong>01</strong>- Toughbook<br />
Retainer Inst. P/N 139192-5<strong>01</strong>- Toughbook Re<br />
10<strong>01</strong>7266 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>481 EUROCOPTER DEUTSCHLAND<br />
EC-135<br />
10<strong>01</strong>7274 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>506 EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
EC135 EMS Equipment.Update of (R)FMS-<br />
4<strong>01</strong> for EMS equipment P/N 135545-5<strong>01</strong> with<br />
validation for all EC135 models up to S/N<br />
0337.Introduction of new EMS equipment<br />
variant P/N 135545-502 with new (R)FMS-08-<br />
006 and OPM-08-006 valid for all EC135<br />
models from S/N<br />
Installation of EMS equipment P/N 145268-5<strong>01</strong><br />
including: 3 medical seats, a primary patient<br />
system, medical supply unit, bottle rack,<br />
medical stowage cabinet, EMS electrical<br />
installation, medical equipment retainers, tie<br />
down web and stretcher stowage provi<br />
10<strong>01</strong>7278 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>524 REV. 2 AB139, AW139 EMS Kit P/N 139172-5<strong>01</strong>/139172-502<br />
Revision 1 of STC to incorporate PAX seat<br />
configurations Aerolite P/N139117-505,<br />
139117-506 and 139117-507 of 12, 14 and 15<br />
PAX seats (as perSTC <strong>EASA</strong>.R.S.<strong>01</strong>524<br />
Revision 1) Revision 2 of STC to introduce<br />
Ceiling Unit Assy c<br />
10<strong>01</strong>7286 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>535 REV. 1 FOCA STC 25-20-91; <strong>EASA</strong>.R.S.<strong>01</strong> EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
10<strong>01</strong>7292 AEROLITE MAX BUCHER AG <strong>EASA</strong>.R.S.<strong>01</strong>554 FOCA STC 25-20-65 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
30.03.2009<br />
None As prerequisite for installation of Aerolite 08.11.2<strong>01</strong>1<br />
AW 139 EMS Kit P/N139097-5<strong>01</strong>, the<br />
Aerolite EMS Provisions Kit P/N 139125-<br />
5<strong>01</strong> must bepreviously installed.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this mo<br />
Helicopter shall be operated as per limititations<br />
section of FMS.Placards as per limitations<br />
section of FMS shall be installed.No smoking<br />
permitted when Oxygen is installed.Prior to<br />
installation of this modification the installer must<br />
determine that the in<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of EMS equipment P/N 145030- 1. Prior to installation of this modification the<br />
5<strong>01</strong>Note:This STC is based on the FOCA STC installer must determine that the<br />
25-20-91 and consists of a stretcher platform, 3 interrelationship between this modification and<br />
medical seats, 2 medical cabinets and a any other previously installed modification will<br />
medical supply unit.This revision 1 of the STC introduce no adverse effect upon the<br />
supersedes original issue of <strong>EASA</strong>.R. airworthiness of the product.2.<br />
Clamshell Door Lock installation P/N 135065-<br />
5<strong>01</strong>/-502.Note: This STC is based on the<br />
FOCA STC Z 25-20-65. Its applicability is<br />
extended to P2+ and T2+ models.<br />
10026923 AEROLITE MAX BUCHER AG P-<strong>EASA</strong>.R.S.<strong>01</strong>571 REV. 3 EC135 EMS P/N 135652-502Design changes<br />
covered:- Cargo Platform Installation P/N<br />
135746-5<strong>01</strong>- Stowage Compartment<br />
Installation P/N 135663-5<strong>04</strong>- Spineboard<br />
Retainer Installation P/N 135730-502- Propaq<br />
Encore Retainer Installation P/N 135747-5<strong>01</strong>-<br />
Snorkel Kit P/N 007<br />
24.06.2008<br />
14.10.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.02.2<strong>01</strong>0<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
08.<strong>04</strong>.2009<br />
23.02.2009<br />
S/N: 337 and onwards only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.12.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 28/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
100291<strong>01</strong> AEROLITE MAX BUCHER AG P-<strong>EASA</strong>.A.S.03979 REV. 1 BEECH 200 SUPER KING AIR Change to B200 Medical Interior KitP/N Applicable to Beechcraft model B200 S/N BB- Prior to installation of this modification it 25.02.2<strong>01</strong>1<br />
2300<strong>01</strong>-5<strong>01</strong> Change compromises of:- Cargo 20<strong>01</strong> and subsequent<br />
must be determined thatthe<br />
Platform Inst. P/N 230006-502- Stretcher Seat<br />
interrelationship between this modification<br />
Inst. P/N 230<strong>01</strong>5-502- AC Power Kit P/N<br />
and any other previouslyinstalled<br />
0071605-5<strong>01</strong>- Engineering Orders EO-10-<strong>01</strong>0/-<br />
modification and/ or repair will introduce<br />
<strong>01</strong>1/-037 In addition this Major Change covers<br />
no adverse effectupon the airworthiness<br />
mi<br />
of the product.<br />
10029681 AEROLITE MAX BUCHER AG REV. 2 EC135P1(CDS),<br />
EC135P1(CPDS),<br />
EC135P2(CPDS), EC135P2+<br />
EC135T1(CDS), EC135T1(CPDS),<br />
EC135T2(CPDS), EC135T2+<br />
Utility Missions Interior P/N 135736-502 This<br />
major change to <strong>EASA</strong> STC No. 10029681<br />
dated 12.<strong>04</strong>.2<strong>01</strong>0 covers theintroduction/<br />
modification of the following components into<br />
the UtilityMissions Interior P/N 135736-502:-<br />
Introduction of the Seat FWD LH, RH and<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.08.2<strong>01</strong>2<br />
10029915 AEROLITE MAX BUCHER AG EC135 P1(CDS), EC135 EMS Equipment P/N 135710-502 Limited to: S/N 870 and subsequent The approval holder shall fulfil the 03.05.2<strong>01</strong>0<br />
P1(CPDS),<br />
obligations of Part 21,<br />
EC135 P2(CPDS), EC135 P2+,<br />
Paragraph21A.118A. Prior to installation<br />
EC135 T1(CDS), EC135<br />
of this modification it must be determined<br />
T1(CPDS),<br />
thatthe interrelationship between this<br />
EC135 T2(CPDS), EC135 T2+<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
10030822 AEROLITE MAX BUCHER AG P-<strong>EASA</strong>.R.S.<strong>01</strong>551 REV. 2 A109 SP EMS Kit AW109SP REGAAerolite P/N None Prior to installation of this modification it 15.06.2<strong>01</strong>1<br />
109<strong>01</strong>50-5<strong>01</strong> Changes related to Rev.1 to STC<br />
must be determined thatthe<br />
10030822:- Introduction of the Propaq MD<br />
interrelationship between this modification<br />
Retainer Inst. P/N 109<strong>01</strong>70-503 and<br />
and any other previouslyinstalled<br />
anadditional 'Training Configuration 2' into the<br />
modification and/ or repair will introduce<br />
already certified EMSEquipment P/N 109<strong>01</strong>50-<br />
no adverse effectupon the airworthiness<br />
5<strong>01</strong> (STC EA<br />
of the product.<br />
10030992 AEROLITE MAX BUCHER AG REV. 2 MBB-BK 117 C-2 EMS Equipment P/N 145341-5<strong>01</strong>Change for<br />
Rev. 1 of STC comprises of:Addition of<br />
Configuration 145341-502,and the<br />
following changes compared to the version -<br />
5<strong>01</strong> of the equipment:- Relocation of a Seat<br />
and changes of the Seating configuration.-<br />
Relocatio<br />
Compatibility with NVIS has not been Prior to installation of this modification it <strong>01</strong>.08.2<strong>01</strong>1<br />
demonstrated.Compatibility with TC-holders 3- must be determined thatthe<br />
seat bench has not been demonstrated interrelationship between this modification<br />
forconfiguration P/N 145341-5<strong>01</strong>.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032080 AEROLITE MAX BUCHER AG AW139 EMS Equipment P/N 139200-5<strong>01</strong> Limited to: S/N 41226 onwards Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.10.2<strong>01</strong>0<br />
10033098 AEROLITE MAX BUCHER AG EC135 VIP Equipment P/N 135748-5<strong>01</strong> Reg.: \-\ ,,S/N: Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
17.12.2<strong>01</strong>0<br />
10036912 AEROLITE MAX BUCHER AG AW139/AB139 EMS Equipment P/N 139-0003670-5<strong>01</strong>This<br />
STC covers 4 EMS cabin configurations and 3<br />
PAX configurations asdescribed in the FMS-<br />
139-0003670-5<strong>01</strong> and according to the<br />
Masterdocument list MDL-11-<strong>01</strong>6 rev N/C.<br />
10038985 AEROLITE MAX BUCHER AG EC135 EMS Equip. P/N 135-00<strong>04</strong>171-5<strong>01</strong>The<br />
equipment includes up to two stretchers, two<br />
seats installed in theforward part of the cabin<br />
and stowage between the two seats.<br />
None The following item are required for the<br />
installation of the STC:-Helicopter must<br />
be in standard configuration AW P/N<br />
3G0000X00231-Cockpit Bulkhead MAG<br />
P/N 6AB1KT002-431 (or equivalent)<br />
must beinstalled for EMS operations.-<br />
Rear Panel Closure Inst. AW P/N 3G<br />
17.10.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.03.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 29/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039944 AEROLITE MAX BUCHER AG LBA STC RC 1240 REV. 1 MBB-BK117 C-2 Change to LBA STC No.RC 1240 on EMS Not applicable Prior to installation of this modification it <strong>04</strong>.06.2<strong>01</strong>2<br />
Equipment P/N 145170-5<strong>01</strong>:Addition of variant<br />
must be determined thatthe<br />
P/N 145169-5<strong>01</strong>This change introduces:EMS<br />
interrelationship between this modification<br />
variant P/N 145169-5<strong>01</strong> composed by:-<br />
and any other previouslyinstalled<br />
Introduction of the new Cargo Platform Inst.<br />
modification and/ or repair will introduce<br />
P/N 145-0000835-5<strong>01</strong>- Introduction of the new<br />
no adverse effectupon the airworthiness<br />
Cover I<br />
of the product.<br />
10<strong>04</strong>0646 AEROLITE MAX BUCHER AG REV. 1 EC 135 P1<br />
EC 135 P2<br />
EC 135 P2+<br />
EC 135 T1<br />
EC 135 T2<br />
EC 135 T2+<br />
EC 635 P2+<br />
EC 635 T1<br />
EC 635 T2+<br />
10<strong>01</strong>5544 AEROMECH INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>429 FAA STC SA5800NM BEECH 200<br />
BEECH 200C<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>5820 AEROMECH INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>892 ST<strong>01</strong>413SE HAWKER HS 125-700A<br />
HAWKER HS 125-700B<br />
10<strong>01</strong>6064 AEROMECH INC. <strong>EASA</strong>.IM.A.S.02243 REV. 3 FAA STC ST<strong>01</strong>526SE 500 (CITATION I)<br />
550 (CITATION II)<br />
560 (CITATION V)<br />
S550 (CITATION S/II)<br />
10<strong>01</strong>6065 AEROMECH INC. <strong>EASA</strong>.IM.A.S.02244 FAA STC #ST<strong>01</strong>522SE CESSNA 500<br />
CESSNA 551<br />
10026757 AEROMECH INC. P-<br />
<strong>EASA</strong>.IM.A.S.03086<br />
Ballast Platform Installation P/N 135-0<strong>01</strong>2762-<br />
5<strong>01</strong>.<br />
Group approval for reduced vertical separation<br />
minimum.<br />
Approval of Reduced Vertical Separation<br />
Minimum (RVSM).<br />
Group Aircraft Approval for Reduced Vertical<br />
Separation Minimum (RVSM)for Cessna Model<br />
500/550/S550/560.This STC is an update of<br />
STC <strong>EASA</strong>.IM.A.S.02243 Rev 1, and<br />
incorporatesan added class of avionics as<br />
applicable to the RVSM Group approval<br />
inaccordancewi<br />
Validation of FAA STC ST<strong>01</strong>522SE:Group<br />
aircraft approval for RVSM capability.<br />
FAA STC SA<strong>01</strong>602SE CESSNA 441 SERIES Group Approval for Reduced Vertical<br />
Separation Minimum (RVSM)<br />
10<strong>01</strong>6739 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>064 FAA STC SH3756NM MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HS<br />
10<strong>01</strong>6740 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>065 FAA STC SH5055NM MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
10<strong>01</strong>6931 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>317 FAA STC SR<strong>01</strong>524SE MD HELICOPTERS 369A<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
Installation of Aerometals tailboom P/N<br />
369X3500-505 or Yehnert tailboom P/N YH-<br />
203.The present STC is the validation of the<br />
FAA STC SH3756NM amended on 30/11/99,<br />
limited to MDHI 369H, HS and HE models.<br />
Installation of- Aerometals tailboom:- P/N<br />
369X23500-505 as replacement of MDHI<br />
tailboom P/N 369D23500-505, or-P/N<br />
369X23500-507 as replacement of MDHI<br />
tailboom P/N 369D2300-507, or- Yehnert<br />
tailboom :- P/N YH-228-1 as replacement of<br />
MDHI tailboom P/N 369D<br />
Horizontal stabilizer, P/N AM369A3600-<br />
603Validation of FAA STC SRSR<strong>01</strong>524SE<br />
reissued June 28, 2006<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.07.2<strong>01</strong>2<br />
1. AFMS No. AMI-AFMS-KAIR-<strong>04</strong>29A Rev<br />
"Original", dated 30 September 20<strong>04</strong> is<br />
required on-board for operation with Beech<br />
200, 200C,B200, B200C, 300 and 300LW<br />
series.2. AFMS No. AMI-AFMS-KAIR-<strong>04</strong>29B<br />
Rev "Original", dated 30 September 20<strong>04</strong> is<br />
required on-b<br />
1. Only applicable to Aircraft Serial 257037.2.<br />
This STC must be installed after Avionics<br />
Mobile STC ref AM/1518. The installation is to<br />
be completed by the embodiment of Avionics<br />
Mobile Minor change AM/1532 installation of<br />
RVSM ADM’s.<br />
24.11.2005<br />
17.10.2006<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.08.2<strong>01</strong>1<br />
The installer muste determine if this design is<br />
compatible with previously approved<br />
modifications. If the holder agrees to permit<br />
another person to use this certification or alter<br />
a product, the holder must give the other<br />
person written evidence of that pe<br />
This approval is issued based on the FAA STC<br />
SA<strong>01</strong>602SE, issued on 26October 2005 and<br />
later amended on 17 November 2006.<br />
1. Service life of the Aerometals and Yehnert<br />
referenced tailbooms is established according<br />
to FAR 27.571 (e) at 10000 flight hours, with<br />
periodic inspections required at 2450 flight<br />
hours and each 2450 flight hours thereafter.2.<br />
Inspections of the Aeromet<br />
1.Service life of the Aerometals and Yehnert<br />
referenced tailbooms is established according<br />
to FAR 27.571 (e) at 10300 flight hours,with<br />
periodic inspections required at 7300 flight<br />
hours and each 1000 flight hours hereafter.2.<br />
Inspections of- the Aerometal<br />
Limited to MDHI (Hughes) models 369HM,<br />
369HS, 369HEall other limitation and<br />
conditions listed in FAA STC SRSR<strong>01</strong>524SE<br />
reissued June 28, 2006 apply<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 30/<strong>462</strong><br />
product.<br />
26.<strong>04</strong>.2007<br />
06.08.2009<br />
30.05.2005<br />
17.05.2005<br />
31.05.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7<strong>01</strong>3 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>430 FAA STC SR00981LA MD HELICOPTERS 369D Strut Assy - Landing Gear, p/n 369XH60<strong>01</strong>,<br />
29.<strong>04</strong>.2008<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
<strong>EASA</strong> validation of FAA approved PMA part.<br />
10<strong>01</strong>7<strong>01</strong>4 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>431 FAA STC SR00766LA MD HELICOPTERS 369D Skid Tube Position Light Assys., p/n<br />
29.<strong>04</strong>.2008<br />
MD HELICOPTERS 369E 369XH92<strong>04</strong>1, <strong>EASA</strong> validation of FAA<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
approved PMA part.<br />
10<strong>01</strong>7<strong>01</strong>5 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>432 FAA STC SR<strong>01</strong>062LA MD HELICOPTERS 369A Exhaust Tailpipe Outlet hangar Assys., p/n<br />
29.<strong>04</strong>.2008<br />
MD HELICOPTERS 369D 369X8236, <strong>EASA</strong> validation of FAA approved<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
PMA part.<br />
10<strong>01</strong>7<strong>01</strong>6 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>433 FAA STC ST<strong>01</strong>550SE MD HELICOPTERS 369D Scavenge Air Elbow Assy., p/n<br />
29.<strong>04</strong>.2008<br />
MD HELICOPTERS 369E AM369D29<strong>01</strong>35, <strong>EASA</strong> validation of FAA<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 500N<br />
approved PMA part.<br />
10<strong>01</strong>7<strong>01</strong>9 AEROMETALS <strong>EASA</strong>.IM.R.S.<strong>01</strong>437 FAA STC SR<strong>01</strong>136SE MD HELICOPTERS 369D Landing Gear Fillet Fairings p/n AM369A6200-<br />
29.<strong>04</strong>.2008<br />
MD HELICOPTERS 369E 45, -46, -57, -58; and Landing Gear Fairing<br />
MD HELICOPTERS 369HM Guides p/n AM369H6200-73, -74. <strong>EASA</strong><br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
validation of FAA approved PMA part.<br />
10<strong>01</strong>6708 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.00548 FAA STC SR02381AT BELL 427 Manufacture and Installation of Passenger 1. Rotorcraft Flight Manual Supplement<br />
26.<strong>01</strong>.2005<br />
Sliding Door for Bell 427 Model Helicopters dated 7/09/20<strong>01</strong>, is a required part of this<br />
(FAA STC SR02381AT dated 19/09/2002). STC.2. 'Instruction for Continued<br />
Airworthiness', AAI Report No. AA-99<strong>04</strong>3,<br />
Revision A dated 6/10/2000 is also a required<br />
part of this STC.3. This STC is approve<br />
10<strong>01</strong>6762 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>091 FAA STC SR09324RC-D BELL 407 Installaton of Passenger photo Window for Bell 1. The compatibility of this design change<br />
407 Model Helicopters in accordance with:-the with other previously approved modifications<br />
FAA STC SR09324RC-D dated 22/9/2003-AAI must be determined by the installer.2. This<br />
22.08.2005<br />
Master Drawing List Report AA-<strong>01</strong>095, STC is approved only for the product<br />
Revision B, dated 19/3/2003.<br />
configuration as defined in the approved design<br />
data referred to in the paragraph<br />
10<strong>01</strong>6767 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>098 FAA STC SR<strong>01</strong>450LA BELL 407 Installation of Apical Industries, Inc. Emergency 1. The compatibility of this design change<br />
Float Assemply, Part number 6<strong>04</strong>.95<strong>01</strong> for Bell with other previously approved modifications<br />
22.08.2005<br />
407 Model Helicopters in accordancewith:-the must be determined by the installer.2. This<br />
FAA STC SR<strong>01</strong>450LA dated 27/5/2003.- STC is approved only for the product<br />
Master document List MD407-11 Revision C, configuration as defined in the approved design<br />
dated 28/4/2003.<br />
data referred to in the paragraph<br />
10<strong>01</strong>6770 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>102 FAA STC SR09239RC BELL 407 Installation of a Steerable Landing Light. None 10.05.2007<br />
10<strong>01</strong>6771 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>105 FAA STC SR<strong>01</strong>849AT BELL 212, 412, 412 EP Light weight nitrogen reservoir kit/Replacement<br />
of nitrogen cylinder for emergency flotation<br />
system kit.<br />
20.12.2007<br />
10<strong>01</strong>6777 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>116 FAA STC SR02074AT BELL 427 Manufacture of Automatic Door Opener for Bell 1. The compatibility of this design change with<br />
15.07.2005<br />
427 Model Helicopters in accordance with the other previously approved modifications must<br />
FAA STC SR02074AT. AAI Master Drawing be determined by the installer.2. This STC is<br />
List Report AA-98109 dated 30/10/1998. FAA approved only for the product configuration as<br />
STC SR 02<strong>04</strong>7AT dated 14/02/2000 (Atlanta defined in the approved design data referred to<br />
Aircraft Certification Office).<br />
in the paragraph "Desc<br />
10<strong>01</strong>6791 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>139 FAA STC SR<strong>01</strong>411AI BELL 407 Manufacture and Installation of console<br />
assembly<br />
26.<strong>01</strong>.2006<br />
10<strong>01</strong>6840 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>211 FAA STC SR<strong>01</strong>844AT A109, A109A, A109A II, A109C Installation of Tail Rotor Lockout Kit for Agusta Compatibilty of this design change with<br />
06.<strong>04</strong>.2006<br />
A109E, A109K2, A119<br />
A109, A109A, A109AII, A109C, A109E, previously approved modifications must be<br />
A109K2, A119 Model Helicopter<br />
determined by the installer. If the holder<br />
agreesto permit another person to use this<br />
certificate to alter the product, the holder shall<br />
give the other person written evidenc<br />
10<strong>01</strong>6860 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>236 FAA STC SR00235AT 206A, 206B, 206L, 206L-1,<br />
206L-2, 206L-3, 206L-4, 407<br />
Installation of Headset Retention Brackets None 29.08.2006<br />
10<strong>01</strong>6872 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>248 FAA STC SR02070AT BELL 427 Installation of Baggage Floor Protector 25.10.2006<br />
10<strong>01</strong>6902 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>279 FAA STC SR<strong>01</strong>687AT BELL 407 Manufacture of crew and passenger<br />
emergency push out windows<br />
16.11.2006<br />
10<strong>01</strong>6920 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>305 FAA STC SR09373RC-D BELL 412, 412EP Bell Helicopter Vibration monitor (BHVM)<br />
System<br />
31.05.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 31/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6921 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>306 FAA STC SR09347RC-D 212, 412, 412 EP Helicopter Emergency Egress Lighting (Heel)<br />
System. This STC is classified as "Basic" by<br />
the FAA and is approved under the Post Type<br />
Validation Principles (PTVP).<br />
25.<strong>04</strong>.2007<br />
10<strong>01</strong>6922 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>307 FAA STC SR<strong>01</strong>278NY-D 412 EP L-3 Communications FA2300 Series Combined No credit is given for operational requirements<br />
<strong>04</strong>.05.2007<br />
Cockpit Voice Recorder and Flight Data<br />
Recorder Kit. This STC is classified as “BASIC”<br />
bythe FAA and is approved under the Post<br />
Type Validation Principles (PTVP).<br />
that require both a CVR and FDR.<br />
10<strong>01</strong>6925 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>311 FAA STC SR<strong>01</strong>474NY BELL 412 EP Installation of Honeywell Mark XXII EGPWS for<br />
Bell Helicopter Textron 412EP<br />
helicopters.Validation of FAA STC<br />
SR<strong>01</strong>474NY dated January 9, 2007<br />
10<strong>01</strong>6930 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>316 FAA STC SR00790NY BELL 407 Installation of a SFIM Automatic Flight Control This approval is for VFR operations only.If the<br />
System (AFCS) on Bell 407 helicopters.<strong>EASA</strong> holder agrees to permit another person to use<br />
validation of FAA STC SR00760NY dated July this certificate to alter the product, the holder<br />
27, 2007This STC is classified ‘Basic’ by the shall give the other person written evidence of<br />
FAA and is approved under the post type that permission.Installation of SFIM Force trim<br />
Validation Principles (PTVP)<br />
system in accord<br />
10<strong>01</strong>6967 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>368 FAA STC SR00778AT BELL 206A/B/L/L-1/L-3/L-4 Expanded Instrument Panel. This STC is<br />
classified as “BASIC” by the FAA and is<br />
approved under the Post Type Validation<br />
Principles (PTVP).<br />
16.11.2007<br />
10<strong>01</strong>6969 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>370 FAA STC SH2616SO BELL 206A/B/L/L-1/L-3/L-4 Lower Console Assembly. This STC is<br />
classified as "BASIC" by the FAA and is<br />
approved under the Post Type Validation<br />
Principles (PTVP).<br />
09.10.2007<br />
10<strong>01</strong>6970 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>371 FAA STC SR<strong>01</strong>075AT BELL 407 Crew and Passenger Wedge Windows. 09.10.2007<br />
10<strong>01</strong>6985 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>390 FAA STC SR00760NY BELL 407 Installation of SFIM Force Trim System on Bell<br />
407 helicopters.This STC is classified ‘Basic’<br />
by the FAA and is approved under the post<br />
type Validation Principles (PTVP)<br />
07.<strong>04</strong>.2008<br />
10<strong>01</strong>6986 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>391 FAA STC SR<strong>01</strong>285AT-D BELL 407 Rubber mounted replacement chin window.<br />
This STC is classified as "BASIC" by the FAA<br />
and is approved under the Post Type<br />
ValidationPrinciples (PTVP).<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>7<strong>04</strong>3 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>467 FAA STC SH8421SW BELL 206B, 206L-3, 206L-4 Steerable Nose Landing Light. This STC is<br />
classified as “BASIC” by the FAA and is<br />
approved under the Post Type Validation<br />
Principles (PTVP).<br />
09.07.2008<br />
10<strong>01</strong>7<strong>04</strong>7 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>471 FAA STC SH3316SO BELL 212, 412, 412EP Pushout Window Assembly Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
18.06.2008<br />
10<strong>01</strong>7051 AERONAUTICAL ACCESSORIES, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>475 FAA STC SR09379RC-D BELL 412 EP Pilot heater failure monitor kit (412-081-<br />
0<strong>01</strong>/002), Stand by attitude battery monitor kit<br />
(412-080-0<strong>01</strong>), Crew flashlight holder kit(412-<br />
086-0<strong>01</strong>).<br />
1. Applicable to Registration Marks I-OTEL.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effec<br />
10027902 AERONAUTICAL ACCESSORIES, INC REV. 1 FAA STC SR<strong>01</strong>515AT BELL 407 Expanded Area Instrument Panel None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.12.2009<br />
10027913 AERONAUTICAL ACCESSORIES, INC REV. 1 FAA STC SR09533RC-D BELL 407 Vertical Fin Cap with LED Light Kit None The Vertical Fin Cap with LED Light Kit is <strong>01</strong>.12.2009<br />
applicable for installationas a<br />
replacement for the factory installed<br />
Vertical Fin FairingAssembly. The kit also<br />
relocates the vertical fin quartz anticollisionlight<br />
to the belly of the aircraft and<br />
installs a re<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 32/<strong>462</strong><br />
20.06.2007<br />
07.<strong>04</strong>.2008<br />
05.03.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028641 AERONAUTICAL ACCESSORIES, INC BELL 206 A & B Installation of Aft Passenger Seat Shoulder None Prior to installation of this modification it 29.<strong>01</strong>.2<strong>01</strong>0<br />
Harness/Lap Belt Assemblyfor Bell Helicopter<br />
must be determined thatthe<br />
Textron 206 A / B Models<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028796 AERONAUTICAL ACCESSORIES, INC FAA STC SR02162LA BELL 407 Installation of Mounting Provisions for a Tail<br />
Boom Radar Altimeter inaccordance with<br />
Meeker Aviation Drawing List for Radar<br />
Altimeter MountKit, AA-TBA-16-<strong>01</strong>0, and<br />
Document List of Radar Altimeter Mount<br />
Kit, AA-TBA-16-<strong>01</strong>1.<br />
This STC provides mounting provisions only; it<br />
does not allow the holderto install an altimeter<br />
or any wiring to power an altimeter.<br />
Prior to installation of this modification it 10.02.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028797 AERONAUTICAL ACCESSORIES, INC FAA STC ST02121LA BELL 407 Installation of a Tail Boom Antenna Mount Kit in This STC provides mounting provisions only; it Prior to installation of this modification it 10.02.2<strong>01</strong>0<br />
accordance with MeekerAviation MDL for VHF does not allow theholder to install an antenna must be determined thatthe<br />
Communication Antenna Mount Kit, AA-TBA- or any wiring to power an antenna.<br />
interrelationship between this modification<br />
<strong>01</strong>0.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028872 AERONAUTICAL ACCESSORIES, INC FAA STC SR09325RC BELL 407 Installation of Bulged Skylight in accordance<br />
with AeronauticalAccessories, Inc. Drawing<br />
List, Report No AA-<strong>01</strong>070<br />
10028891 AERONAUTICAL ACCESSORIES, INC FAA STC SR09326RC BELL 407 Development and Installation of High Visibility<br />
Crew Door in accordancewith Aeronautical<br />
Accessories, Inc. Drawing List, Report No AA-<br />
<strong>01</strong>073<br />
10028893 AERONAUTICAL ACCESSORIES, INC FAA STC SR09376RC-D BELL 407 High Visibility Door Kits in accordance with<br />
Aeronautical Accessories,Inc. Drawing List<br />
Report No AA-05155<br />
10031747 AERONAUTICAL ACCESSORIES, INC FAA STC SR00646AT AB412, AB412EP Replacement Low Skid Landing Gear<br />
Crosstubes<br />
10033707 AERONAUTICAL ACCESSORIES, INC FAA STC SH1281SO 206A, 206B, 206L, 206L-1<br />
206L-3, 206L-4, 407<br />
10034699 AERONAUTICAL ACCESSORIES, INC FAA STC SR09536RC-D 429 Installation of Health and Usage Monitoring<br />
System (HUMS)<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.02.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.02.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.02.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.09.2<strong>01</strong>0<br />
Maintenance Step. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.02.2<strong>01</strong>1<br />
The HUMS kit is installed on a non-<br />
Prior to installation of this modification it 20.<strong>04</strong>.2<strong>01</strong>1<br />
required/non-hazardous basis. Theutilization of must be determined thatthe<br />
the HUMS kit for maintenance credit is limited interrelationship between this modification<br />
to: 1)main rotor track and balance; 2) tail rotor and any other previouslyinstalled<br />
dynamic balance; and 3)frahm vibration modification and/ or repair will introduce<br />
absorber tuning. HUMS data may not be no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 33/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5732 AERONAUTICAL ENGINEERS INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>754 REV. 4 FAA STC ST<strong>01</strong>827LA B737-300 / B737-400 BOEING 737-300/-400 FREIGHTER WITH Limited to B737-300/400 modified with <strong>EASA</strong> Prior to installation of this modification it 24.09.2<strong>01</strong>0<br />
OPTIONAL CARGO<br />
STC IM.A.S.<strong>01</strong>754 Rev 3 (FAAST<strong>01</strong>827LA) must be determined thatthe<br />
CONTAINERCONFIGURATION.Modification<br />
interrelationship between this modification<br />
of notch frames to accommodate 88x125"<br />
and any other previouslyinstalled<br />
container indisposition 10 (rear)<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>5836 AERONCA, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>928 ST09456SC BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
10<strong>01</strong>7069 AEROQUEST INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>505 TCCA STC SH97-63; EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
350B<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
10<strong>01</strong>7073 AEROQUEST INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>513 TCCA STC SH08-52 ISSUE 1<br />
355F2<br />
EUROCOPTER FRANCE SA<br />
315B<br />
Manufacture and Installation of Engine Fan<br />
Cowl Doors<br />
Compliance with Aronca Engineering Report<br />
Number ER 19<strong>04</strong> "Instructions for Continued<br />
Airworthiness and Structural Repair Manual"<br />
Revision B, dated January 29, 1998, or later<br />
approved revision required.<br />
AS350/AS355 Aeroquest Survey Installation Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Installation of Aeroquest Survey Modification -<br />
Validation of Transport Canada (TCCA) STC<br />
No. SH08-52.<br />
10<strong>01</strong>4614 Aeroservis s.r.o. <strong>EASA</strong>.A.S.02741 CESSNA T210 SERIES Upgrade of NAV/COM equipment for IFR<br />
navigation.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
1. S/N: 210638072. This STC is approved<br />
only for the product configuration as defined in<br />
the approved design data referred to in the<br />
paragraphs "Description" and “Associated<br />
Technical Documentation”. Compatibility with<br />
other aircraft/engine configura<br />
10<strong>01</strong>5076 Aeroservis s.r.o. <strong>EASA</strong>.A.S.03407 L 200 A Installation of NAV/COM/GPS device GNS 430 25.03.2008<br />
10027356 AEROSERVIS, S.R.O. P-<strong>EASA</strong>.A.S.039<strong>04</strong> CESSNA F172-N Installation of NAV/COM Equipment:GNS 430<br />
(NAV/COM/GPS), KX155 (NAV/COM), KR87<br />
(ADF),KMA 24 (AUDIO/MKR)<br />
10027739 AEROSERVIS, S.R.O. P-<strong>EASA</strong>.A.S.03929 L 410 UVP-E, L 410 UVP-E9 The set of the safety modifications in order to<br />
prepare the alternativemean of the compliance<br />
to <strong>EASA</strong> AD 2008-<strong>01</strong><strong>04</strong> and <strong>EASA</strong> AD 2008-<br />
<strong>01</strong>05.<br />
10030622 AEROSERVIS, S.R.O. L 410 UVP The set of the safety modifications in order to<br />
prepare the alternativemean of the compliance<br />
to the <strong>EASA</strong> AD 2008-<strong>01</strong>03.<br />
28.07.2006<br />
28.05.2009<br />
06.02.2009<br />
30.<strong>04</strong>.2007<br />
none Prior to installation of this modification the 24.09.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
Prior to installation of this modification the 26.10.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 34/<strong>462</strong><br />
28.06.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030755 AEROSERVIS, S.R.O. P-<strong>EASA</strong>.A.S.03873 SF340A Installation of Universal UNS-1Msp Flight Valid for Saab SF340A/s/n 340.026 and 1.,,Prior to installation of this modification 03.07.2009<br />
management System<br />
340.038 only.<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2.,,The ins<br />
10<strong>01</strong>5200 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10<strong>01</strong>5246 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10030093 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10031738 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10032496 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10032541 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10034447 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10037643 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10038646 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10039615 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
10<strong>04</strong><strong>01</strong>89 AEROSPACE DESIGN AND<br />
CERTIFICATION<br />
<strong>EASA</strong>.A.S.03592 AIRBUS A320-232 A320 In Flight Entertainment – IFE – Upgrade Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
29.10.2008<br />
<strong>EASA</strong>.A.S.03683 DIAMOND DA-42 Banbury Modification 0<strong>01</strong> - FLIR Installation. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
07.11.2008<br />
BAE 146-200 New Cabin Configuration None None 21.05.2<strong>01</strong>0<br />
P-<strong>EASA</strong>.R.S.<strong>01</strong>593 AS 350 B, D, B1, B2, BA, BB<br />
AS 350 B3<br />
B300 Review of modifications installed prior to import Aircraft Serial Number FL-327 Only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.09.2<strong>01</strong>0<br />
Installation of Indraero Siren IS10-100 Cargo<br />
Hook<br />
P-<strong>EASA</strong>.A.S.03947 BOEING 767-341 Review of modifications installed prior to import Limitations as per associated technical<br />
(B767-341 Installationof SELL Galley, Crew documentation:- Flight Manual Supplement,<br />
Rest, 221 LOPA & ELT)<br />
doc. JN189 ADC29 Issue 1 dated 16/11/09-<br />
Instructions for Continued Airworthiness, doc.<br />
JN189 ADC54-25 Issue 5dated<br />
14/10/2<strong>01</strong>0.Restricted to S/N 24753<br />
REV. 1 B737-700 Cabin certification for aircraft use in<br />
Commercial operations<br />
A330-243 Installation of new Business Class Avio EBIZ<br />
Seats and IMS Rave IFESystem. The FWD<br />
cabin is currently configured with BC and EY<br />
seats which are tobe removed and replaced<br />
with new Avio BC seats. The MAS 200E IFE<br />
systemwill be removed from the FWD Cabin<br />
and<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
11.11.2<strong>01</strong>0<br />
Refer to AFM supplement JN314-002 ADC29<br />
Issue 1<br />
MBB-BK 117 B-2 Installation of LTS1<strong>01</strong>-850B-2 Engines into<br />
MBB-BK117 B-2 Helicopter<br />
B200 KING AIR Installation of polyurethane reticulated foam This STC grants no credit for any fuel tank<br />
into fuel tanks, asdefined by:JN323 ADC17 (1) flammability reduction.<br />
Master Data List<br />
Prior to installation of this modification it 15.11.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it 12.<strong>04</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.12.2<strong>01</strong>1<br />
None None 05.03.2<strong>01</strong>2<br />
Prior to installation of this modification it 14.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
B757-200 Installation of VIP Bedroom and Bathroom None None 15.06.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 35/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2466 AEROSPACE DESIGN AND<br />
A340-300 Installation of new Business Class Avio EBIZ None Prior to installation of this modification it 03.12.2<strong>01</strong>2<br />
CERTIFICATION<br />
Seats and IMS Rave IFESystem.The FWD<br />
must be determined thatthe<br />
cabin is currently configured with BC and EY<br />
interrelationship between this modification<br />
seats which will beremoved and replaced with<br />
and any other previouslyinstalled<br />
new Avio BC seats. The Rockwell Collins<br />
modification and/ or repair will introduce<br />
IFEsystem will be removed from the FWD<br />
no adverse effectupon theairworthiness<br />
Cabin<br />
of the product.<br />
10<strong>01</strong>4369 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4371 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4397 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4405 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4459 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4460 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4855 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4882 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4946 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>4948 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>5157 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>5242 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>01</strong>5279 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
<strong>EASA</strong>.A.S.<strong>01</strong>640 BOEING 737-3M8 Introduction of G2 Stowage Galley -- 06.<strong>04</strong>.2006<br />
<strong>EASA</strong>.A.S.<strong>01</strong>645 Installation of an Enhanced Surveillance Mose<br />
S Transponder<br />
08.06.2006<br />
<strong>EASA</strong>.A.S.<strong>01</strong>691 BOEING 737 Introduction of Three Overhead Liferaft<br />
Stowages<br />
none 06.<strong>04</strong>.2006<br />
<strong>EASA</strong>.A.S.<strong>01</strong>700 BOEING 737-200<br />
Installation of a Dual High Frequency (HF) As referred in Paragraph 4.1 of MOD-00<strong>01</strong><br />
31.05.2007<br />
BOEING 737-300<br />
Communication System.<br />
Revision B,Compatibility of this design change<br />
BOEING 737-400<br />
with other previously approved modifications<br />
BOEING 737-500<br />
BOEING 737-600<br />
must be determined by the installer.<br />
<strong>EASA</strong>.A.S.02517 BOEING 737-4Y0 Introduction of 8/150 Passenger Configuration Compatibility of this design change with other<br />
20.10.2006<br />
and Associated Customisation<br />
previously approved modifications must be<br />
determined by the installer.<br />
<strong>EASA</strong>.A.S.02518 REV. 1 BOEING 737-300<br />
Introduction of Enhanced Surveillance Mode S 1. Compatibility of this design change with<br />
07.09.2006<br />
BOEING 737-400<br />
ATC System / Installation of new Mode S other previously approved modifications must<br />
BOEING 737-500<br />
Transponders, components and data link wiring be determined by the installer.<br />
which will provide the ATC System with<br />
additional parameters necessary to comply<br />
with TGL N 18 revision 1, dated August 3 200<br />
<strong>EASA</strong>.A.S.03079 BOEING 767-300 Introduction of 25XF/188Y passenger<br />
configuration and associated customisation.<br />
<strong>EASA</strong>.A.S.03110 BOEING B737-300 Introduction of 138 Passenger Configuration<br />
and Associated Customizations<br />
Serial Number 24952 only. 14.06.2007<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.03206 REV. 1 BOEING 747-300 Installation of an Elementary Surveillance Mode-FMA-234-031<br />
Rev. 1 Flight Manual<br />
S System in a Boeing 747-30.<br />
Supplement MCN 23410FMA 0234-032 Ref.<br />
Flight Manual Supplement MCN 23751This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data. Compatibility with other aircraft/engine<br />
configuration<br />
<strong>EASA</strong>.A.S.03209 DC-9-81 (MD-81)<br />
Elementary/ Enhanced Surveillance Mode S<br />
DC-9-81 (MD-82)<br />
DC-9-81 (MD-83)<br />
DC-9-81 (MD-87)<br />
ATC System.<br />
<strong>EASA</strong>.A.S.03524 BOEING 737-700 Introduction of Seat-track mounted 40 Inch Prior to installation of this modification the<br />
Closet-Boeing 737-700.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.03676 BOEING 767-200 Introduction of 12C/241Y Passenger Cabin<br />
Configuration and Associated Floor Structure<br />
Changes.<br />
<strong>EASA</strong>.A.S.038<strong>04</strong> AIRBUS A320-200 Introduction of 16J/126Y Class Cabin<br />
Configuration<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 36/<strong>462</strong><br />
20.09.2007<br />
02.11.2007<br />
11.<strong>01</strong>.2008<br />
28.11.2008<br />
11.12.2008<br />
11.05.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5297 AEROSPACE DESIGN AND<br />
<strong>EASA</strong>.A.S.03847 REV. 1 A320-232 Installation of an Enhanced Surveillance Mode None Prior to installation of this modification it 09.08.2<strong>01</strong>0<br />
ENGINEERING<br />
S ATC SystemRevision of the <strong>EASA</strong> STC P-<br />
must be determined thatthe<br />
<strong>EASA</strong>.A.S.03847 to remove EWIS Limitation.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027558 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10027628 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10029548 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10030206 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10032318 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10033237 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10039894 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
10<strong>04</strong>2785 AEROSPACE DESIGN AND<br />
ENGINEERING<br />
P-<strong>EASA</strong>.A.S.03680 DHC-8-102 Traffic Alert and Collision Avoidance System<br />
(TCAS II) Installation.<br />
P-<strong>EASA</strong>.A.S.03677 REV. 1 A330-223 Introduction of a change from a 48C/182Y dual<br />
class seatingconfiguration to a 24C/242Y<br />
passenger seating configuration.<br />
REV. 1 B737-600, -700, -800, -900 Change to STC "Introduction of a Dual Battery<br />
System, MOD-0702"The change consists in<br />
removing the EWIS limitation.<br />
P-<strong>EASA</strong>.A.S.03549 B747-400 Reconfiguration of compartment zone A in<br />
accordance with AerodecModification<br />
summary MOD-0386 Rev. B dated 29 March<br />
2<strong>01</strong>0 or laterapproved revision.This STC<br />
validates FAA STC ST<strong>01</strong>829SE.<br />
Prior to installation of this modification the 09.10.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.12.2009<br />
The STC holder shall monitor all documentary<br />
changes of the basic AFMand related<br />
operational documentation issued by the TCholder<br />
to assurethat those documents remain<br />
suitable to be used operationally for<br />
theinstallation of dual batteries under this STC.<br />
Prior to installation of this modification it 03.11.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Jamco America Inc. Instructions for<br />
Continued Airworthiness,<br />
documentnumber JD-09AC03 Rev. New,<br />
dated March 06, 2008 or later<br />
approvedrevisions must be made<br />
available to the operator at the time<br />
ofinstallation. <strong>EASA</strong> STC<br />
<strong>EASA</strong>.IM.A.02858 must be incorporated<br />
02.06.2<strong>01</strong>0<br />
DHC-8-4<strong>01</strong>, DHC-8-402 Installation of Ground Recognition Lights none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.10.2<strong>01</strong>0<br />
B767-300 Installation of First Class Seating None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
05.<strong>01</strong>.2<strong>01</strong>1<br />
REV. 1 A330-243 Revise the passenger seat place cabin<br />
configuration from8FC/24JCL/183YCL (215<br />
pax) to 8FC/247YCL (255 pax) passenger<br />
placestogether with associated changes to the<br />
complete aircraft interior.Installation of 64<br />
passenger places of newly manufactured<br />
Sicma Ae<br />
747-400 Certification of drainmast p/n 24E507589G02<br />
against 25.1455 on Boeing747-467ERF MSN<br />
37299 in order to nullify Hong Kong Civil<br />
AviationDepartment Variation No<br />
VAR/2<strong>01</strong>2/133.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.05.2<strong>01</strong>2<br />
STC is only valid for B747-467F MSN37299 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.12.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 37/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7117 AEROSPACE DESIGN FACILITIES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>099 EUROCOPTER FRANCE AS 355 Installation of Wescam nose mount This STC is approved only for the product<br />
18.08.2005<br />
SERIE<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>7147 AEROSPACE DESIGN FACILITIES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>250 EUROCOPTER FRANCE AS 350 |nstallation of Wescam combined nose and Approval limited to nose mount only <strong>01</strong>.03.2006<br />
SERIE<br />
side mount<br />
10<strong>01</strong>7276 AEROSPACE DESIGN FACILITIES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>512 EUROCOPTER FRANCE AS ADF2003-0<strong>01</strong> Utility Pole Mount.This STC None. 21.08.2008<br />
355F<br />
supersedes <strong>EASA</strong> approval 20<strong>04</strong>-1997, dated<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
5 March 20<strong>04</strong>.<br />
10028585 AEROSPACE DESIGN FACILITIES Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>444 REV. 2 1. AS350 B, B1, B2, BA, BB, B3 Cowling - Secondary Latching None Prior to installation of this modification it 14.09.2<strong>01</strong>0<br />
1. AS350 D, EC130B4<br />
must be determined thatthe<br />
2. AS355E,<br />
interrelationship between this modification<br />
2. AS355F, AS355F1, AS355F2,<br />
and any other previouslyinstalled<br />
2. AS355N, AS355NP<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>3963 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>01</strong>4122 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>01</strong>4123 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>01</strong>4557 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>01</strong>4854 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>01</strong>4949 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>01</strong>5236 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10034052 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
100377<strong>04</strong> AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
10<strong>04</strong>0625 AEROSPACE ENGINEERING<br />
SOLUTIONS<br />
<strong>EASA</strong>.A.S.00652 REV 2 BOEING 767-300 Introduction of Matsushita In-Flight<br />
Entertainment System<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.A.S.<strong>01</strong>232 BOEING 767-300 Introduction of 258 Passenger Configuration &<br />
Associated Cabin Changes<br />
<strong>EASA</strong>.A.S.<strong>01</strong>233 BOEING 767-300 Introduction of Matsushita in-Flight<br />
Entertainment System<br />
<strong>EASA</strong>.A.S.02655 BOEING 767-300 Introduction of Main/APU Battery Paralleling for Restricted to Aircraft G-DBLA ASN 26063 & G-<br />
Extended Standby Power Time Capability. PJLO ASN 26064.<br />
<strong>EASA</strong>.A.S.03078 B767 Introduction of 290 Pac Place Interior<br />
Configuration<br />
S/N 23765 ONLY. 31.05.2007<br />
<strong>EASA</strong>.A.S.03212 BOEING 757-200 Introduction of alternative EGPWS Mode 6 FAA STC ST00381SE must be installed prior<br />
21.08.2007<br />
Callout Menu.<br />
to the installation of this STC<br />
<strong>EASA</strong>.A.S.03662 BOEING 757-200 Introduction of Flight Control Computer (FCC) • Prior to installation of this modification the<br />
13.08.2008<br />
Interlock2.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.• Th<br />
P-<strong>EASA</strong>.A.S.03621 REV. 1 B757-200 Introduction of IFE System Circuit Breaker, None The embodiment of this STC also 02.03.2<strong>01</strong>1<br />
Relays and Wiring.<br />
constitutes an Alternative Means<br />
ofCompliance (AMOC) to the<br />
requirements of FAA AD 2007-16-12,<br />
which hasbeen adopted by <strong>EASA</strong>. This<br />
AMOC is issued in respect of the<br />
installationof this STC in lieu of the<br />
mandated Boeing SB 75<br />
A319-132 Introduction of Panasonic dMPES In Flight None Prior to installation of this modification it 16.12.2<strong>01</strong>1<br />
Entertainment - IFE System<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
321-231 Introduction of Panasonic MPES IFE system The approval is limited to MSN 2730 and MSN<br />
2793<br />
02.11.2005<br />
30.05.2005<br />
30.05.2005<br />
10.10.2006<br />
Prior to installation of this modification it 16.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 38/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027883 AEROSPACE ENGINEERING<br />
REV. 1 A320-214 Introduction of Rockwell Collins dPAVES IFE Not applicable Prior to installation of this modification it 22.03.2<strong>01</strong>1<br />
SOLUTIONS LIM<br />
SystemRevision of the <strong>EASA</strong> STC 10027883<br />
must be determined thatthe<br />
to remove EWIS limitation<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031517 AEROSPACE ENGINEERING<br />
SOLUTIONS LIM<br />
10036814 AEROSPACE ENGINEERING<br />
SOLUTIONS LIM<br />
10<strong>04</strong>07<strong>04</strong> AEROSPACE ENGINEERING<br />
SOLUTIONS LIM<br />
10<strong>01</strong>4059 AEROSPACE ENGINEERING<br />
SOLUTIONS Ltd<br />
10<strong>01</strong>4208 AEROSPACE ENGINEERING<br />
SOLUTIONS Ltd<br />
10<strong>01</strong>4495 AEROSPACE ENGINEERING<br />
SOLUTIONS Ltd<br />
10<strong>01</strong>6714 AEROSPACE FILTRATION SYSTEMS,<br />
Inc.<br />
10<strong>01</strong>6715 AEROSPACE FILTRATION SYSTEMS,<br />
Inc.<br />
10<strong>01</strong>6741 AEROSPACE FILTRATION SYSTEMS,<br />
Inc.<br />
10<strong>01</strong>6929 AEROSPACE FILTRATION SYSTEMS,<br />
Inc.<br />
CAA UK<br />
CAA.21NE2.00057<br />
B757-220, MSN 27973 Introduction of Driessen G1A and G4B Galleys Restricted to ASN 27973 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.08.2<strong>01</strong>0<br />
REV. 3 CAA UK CAA.21NE2.00057 REV. 2 B757-2<strong>04</strong>/-236 FAR Part 26 Validation for <strong>EASA</strong> STC<br />
CAA.21NE2.00057<br />
A321 Introduction of Twin Class Cabin Interior<br />
Configuration.<br />
<strong>EASA</strong>.A.S.<strong>01</strong>143 B757-200 Introduction of Pegasus Flight Management<br />
Computers & Multi Mode Receivers (MMRs)<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.10.2<strong>01</strong>1<br />
The <strong>EASA</strong> STC 10038683 is a prerequisite for<br />
the installation of thisSTC.<br />
The approval holder shall fulfill the 20.07.2<strong>01</strong>2<br />
obligations of Part 21,<br />
Paragraph21A.109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
<strong>EASA</strong>.A.S.<strong>01</strong>360 B767-300 Introduction of 279 passenger configuration <strong>01</strong>.07.2005<br />
<strong>EASA</strong>.A.S.02557 B767-300 Introduction of 290 passenger place interior<br />
configuration<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>008 REV. 1 FAA STC SR09421RC BELL 206L-3<br />
Installation of Aerospace Filtration System This STC is approved only for the product<br />
BELL 206L-4<br />
(AFS) Engine Inlet Barrier Filter (IBF) system in configuration as defined in the approved design<br />
accordance with the FAA STC SR09421 RC. data referred to in the paragraph "Description".<br />
AFS Drawing Number 10600, Revision B dated Compatibility with other aircraft/engine<br />
17/6/20<strong>04</strong>FAA STC SR09421RC dated configurations shall be determined by the<br />
25/08/20<strong>04</strong> (Rotorcraft Certification Offiice S installer.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>009 FAA STC SR09368RC BELL 407 Installation of Aerospace Filtration System<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>067 FAA STC SR<strong>01</strong>394LA MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369H<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>315 FAA STC SR09451RC BELL 206B Installation of Aerospace Filtration Systems<br />
(AFS) Engine Inlet Barrier Filter (IBF) on Bell<br />
206B helicopters.Validation of FAA STC<br />
SR09451RC dated December 14, 2005. This<br />
STC is classified as ‘BASIC’ by the FAA and is<br />
approved under the post type Validati<br />
1. Rotorcraft Flight Manual Supplement dated<br />
(AFS) Engine Inlet Barrier Filter (IBF) system in 10/12/2003 is a required part of this STC2.<br />
accordance with the FAA STC<br />
"Instructions for continued airworthiness" AFS-<br />
SR09368RC.AFS Drawing Number 10600, BH407-IBF-KIT-ICA is also required part of this<br />
Revision A dated 8/4/2003 FAA STC STC.3. This STC is approved only for the<br />
SR09421RC dated 25/08/20<strong>04</strong> (Rotorcraft<br />
Certification Office So<br />
product configuration as define<br />
Installation of Aerospace Filtration Systems This STC is approved only for the product<br />
Inlet Barrier Filter System instead of Engine Air configuration as defined in the approved design<br />
Separator (with or without Mist Eliminator) or data referred to in the paragraph "Description".<br />
FOD Screen. According to FAA STC Compatibility with other aircraft/engine<br />
SR<strong>01</strong>394LA. Master Data List: MD500-IBF-KIT- configurations shall be determined by the<br />
MDL, Rev. D, dated 30.09.20<strong>04</strong> or later installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 39/<strong>462</strong><br />
23.03.2005<br />
22.05.2006<br />
27.<strong>01</strong>.2005<br />
27.<strong>01</strong>.2005<br />
16.08.2005<br />
05.12.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7072 AEROSPACE FILTRATION SYSTEMS, <strong>EASA</strong>.IM.R.S.<strong>01</strong>509 FAA STC SR02393CH EUROCOPTER FRANCE AS 350 Installation of Inlet Barrier Filter system in Prior to installation of this modification the<br />
13.<strong>01</strong>.2009<br />
Inc.<br />
B<br />
accordance with AFS, Inc. Master Data installer must determine that the<br />
EUROCOPTER FRANCE AS 350 ListThis STC is the validation of FAA STC interrelationship between this modification and<br />
B1<br />
SR02393CH (issued on March 20, 2007) any other previously installed modification<br />
EUROCOPTER FRANCE AS 350<br />
will introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
airworthiness of the product.<br />
10026895 AEROSPACE FILTRATION SYSTEMS, P-<br />
FAA STC SR02526CH MD900 Installation of engine inlet barrier filter (IBF) None 1) Prior to installation of this modification 20.08.2009<br />
Inc.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>495<br />
system<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10036331 AEROSPACE FILTRATION SYSTEMS,<br />
Inc.<br />
10034213 AEROSPACE TECHNOLOGIES GROUP,<br />
INC.<br />
P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>331<br />
FAA STC SR02338CH A119 & AW119MKII <strong>EASA</strong> Validation of FAA STC SR02338CH<br />
"Installation of a foreign objectdamage (FOD)<br />
screen or an inlet barrier filter (IBF) system"<br />
FAA STC ST03910AT A320-111, -211, -212, -214<br />
A320-215, -216<br />
A320-231, -232, -233<br />
Installation of Passenger Cabin electrically<br />
powered Window Shades<br />
10<strong>01</strong>5550 AEROSYS Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>444 FAA STC ST<strong>01</strong>843LA BOEING MD 11F Installation of the main deck cargo<br />
compartment one minute smoke detector in<br />
accordance with FAA STC ST<strong>01</strong>843LA or later<br />
<strong>EASA</strong>-approved revision.<br />
1003<strong>462</strong>8 AEROTEC - T. UHL GMBH & CO. KG P-<strong>EASA</strong>.A.S.03924 REV. 2 CESSNA 206H, T206H Sky Diving Kit for Cessna 206HInstallation of<br />
components to release sky divers.<br />
10<strong>01</strong>3984 AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>6 BEECH C90 A Installation of Garmin GNS 430 (VHF NAV ILS 1. Modification limited to s/n LJ 10982. <strong>EASA</strong><br />
GPS/BRNAV), Allied Signal ART 2000 Supplemental Airplane Flight Manual GNS 430<br />
(weather radar), Allied Signal KMD 850 (MFD), must be used with this modification. 3. <strong>EASA</strong><br />
MD 41 (panel annunciator) and GMA 340 Supplemental Airplane Flight Manual KMD 850<br />
(markers)<br />
must be used with this modification.<br />
10<strong>01</strong>4<strong>01</strong>4 AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong>057 PIPER PA-28RT-2<strong>01</strong>T Installation of GARMIN GNS 430<br />
(VJF/NAV/ILS/GPS) and MD 41 (panel<br />
annunciator)Removal of VHF KY 97A, GPS<br />
150XL, NAV VIR 351 and Glide GLS 350.<br />
Installation of GNS 430 and MD 41 panel<br />
annunciator, auto-pilot coupled.<br />
10<strong>01</strong>4061 AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong>147 PIPER PA-31T Installation of radio navigation and<br />
communication systems in accordance with<br />
Document Reference 53<strong>04</strong> - Revision 2 dated<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>01</strong>.09.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.03.2<strong>01</strong>1<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph 'Description.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
16.02.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.08.2<strong>01</strong>2<br />
The approval is limited to MSN 28R7931294 F-<br />
GJRR<br />
This STC is limited to Piper PA-31T SN<br />
8020037<br />
10<strong>01</strong>4106 AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong>211 BEECH 95-B55<br />
April 15, 2005<br />
Radio and navigation change with BRNAV Modification limited to s/n TC1143AFMS No<br />
capacity and STEC 55X automatic pilot<br />
steered<br />
modification 0505 must be on board<br />
10<strong>01</strong>4278 AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong>514 PIPER PA-31 Installation of Radio Navigation and<br />
The approval is limited to MSN 31-367 F-<br />
Communication Systems- KX 175B, KY 196,<br />
KN 53, KN 75, KMA 24 and KN 65 removal-<br />
GNS 430, KX 155A, MD 41, RDR 2000, GMA<br />
340, KN 62A, KI 229, GI 106A installation<br />
GDPU<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 40/<strong>462</strong><br />
19.<strong>01</strong>.2005<br />
25.10.2005<br />
11.10.2005<br />
26.09.2006<br />
20.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>43<strong>01</strong> AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong>545 BEECH C90 Installation of radio communication<br />
1. This STC is limited to Beechcraft C90 SN LJ<br />
12.09.2005<br />
systemsModel: Beechcraft C90 SN LJ 710 710.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft configurations shall be deter<br />
10<strong>01</strong>4391 AEROTEC CONCEPT <strong>EASA</strong>.A.S.<strong>01</strong>677 MOONEY M20E BRNAV capacity with AP Steering Modification limited to s/n 28R7931294The<br />
AFMS BRNAV Garmin 430 must be used with<br />
this modification<br />
<strong>04</strong>.05.2006<br />
10<strong>01</strong>4756 AEROTEC CONCEPT <strong>EASA</strong>.A.S.02944 CESSNA 208<br />
CESSNA 208A<br />
CESSNA 208B<br />
Video Mast Installation under Cessna 208. 28.08.2007<br />
10<strong>01</strong>4794 AEROTEC CONCEPT <strong>EASA</strong>.A.S.02996 PIPER PA-31T Installation ATC mode S. 1. This STC is limited to the S/N: 7720036<br />
and 8020037.2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed modification<br />
will introduce no a<br />
10.09.2007<br />
10<strong>01</strong>4799 AEROTEC CONCEPT <strong>EASA</strong>.A.S.03002 PIPER PA-31T Modification radio installation. 1. This STC is limited to the S/N 7720036.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect<br />
10<strong>01</strong>4985 AEROTEC CONCEPT <strong>EASA</strong>.A.S.03277 BRITTEN NORMAN BN-2T<br />
ISLANDER<br />
10<strong>01</strong>5093 AEROTEC CONCEPT <strong>EASA</strong>.A.S.03430 REV. 1 C-212-DD Navigation / Communication (NAV/COM) set<br />
replacement and HFCommunication set<br />
(provisions) installationThis STC replaces a<br />
previous NAV/COM system by an up-to-date<br />
one, andinstalls a new HF communication set<br />
(provision).This revision restores the aircraft I<br />
Survey Capacity on BN-2T Supplemental Airplane Flight Manual, revision<br />
00, dated 17 January 2008, or later approved<br />
revision must be on board when modification is<br />
installed.Instruction for Continued<br />
Airworthiness, revision 00, dated 26 January<br />
2008 and Supplemental Airplane Mainte<br />
1. This STC is limited to the MSN 3872. HF<br />
communication set (subpart of this STC) is not<br />
approved (notinstalled / not operational – wiring<br />
provisions are accepted)<br />
10.09.2007<br />
08.<strong>04</strong>.2008<br />
Prior to installation of this modification it <strong>01</strong>.06.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7145 AEROTEC CONCEPT <strong>EASA</strong>.R.S.<strong>01</strong>248 EUROCOPTER FRANCE EC 120 Modification des sources d’attitude, d’écart de Limited to aircraft EC120B s/n1327, F-GJIR<br />
19.<strong>01</strong>.2007<br />
B<br />
cap et GPS du système pilote automatique only, when equipped with <strong>EASA</strong>.IM.R.S.1056<br />
PA85 SAGEM(change of sensors sources for Rev.1 and <strong>EASA</strong>.R.C.<strong>01</strong>912 and<br />
attitudes retention, heading error select and<br />
GPS steerings of Sagem PA85 Automatic Pilot<br />
system)<br />
<strong>EASA</strong>.R.C.<strong>01</strong>913 changes<br />
10<strong>01</strong>7169 AEROTEC CONCEPT <strong>EASA</strong>.R.S.<strong>01</strong>277 EUROCOPTER FRANCE EC 120 Improvement of "VG Fail" alarm for<br />
Limited to aircraft EC120B S/N 1<strong>04</strong>9, G-VIPR<br />
<strong>04</strong>.08.2006<br />
B<br />
<strong>EASA</strong>.R.S.<strong>01</strong><strong>01</strong>7 and <strong>EASA</strong>.IM.R.S.<strong>01</strong>056 only, when equipped with <strong>EASA</strong>.R.S.<strong>01</strong><strong>01</strong>7<br />
installations<br />
and <strong>EASA</strong>.IM.R.S.<strong>01</strong>056<br />
10<strong>01</strong>7193 AEROTEC CONCEPT <strong>EASA</strong>.R.S.<strong>01</strong>330 EUROCOPTER FRANCE SA AEROTEC avionics modification n° 6306: This STC is limited to SA 365 N s/n 6218 and<br />
12.02.2007<br />
365N<br />
installation of:two NAV/COM/GPS GARMIN can be installed only by AERTOTEC technical<br />
GNS 430 for IFR B-RNAV "En route" staff in accordance with AEROTEC STC<br />
operations, with their associated GARMIN GA Implementation File n°6306, revision 1 dated<br />
56 GPS antenna,two MID CONTINENT MD 41 26/10/06, or later revision.AEROTEC minor<br />
Annunciation Control Units,an ALLIED SIGNAL modification n°6206, approved under <strong>EASA</strong>.R.<br />
KA 33 cooling blo<br />
10034668 AEROTEC CONCEPT C-212-DD ( C212-300) Mod 0921: EGPWS Installation This STC is limited to the MSN 387 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>04</strong>.2<strong>01</strong>1<br />
10034675 AEROTEC CONCEPT C90A Installation d'une antenne SATCOM iridium -<br />
dossier aerotec 1082rev1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>04</strong>.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 41/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034876 AEROTEC CONCEPT P-<strong>EASA</strong>.A.S.03826 C-212-300 INSTALLATION OF HONEYWELL CAS 67A The Airworthiness Approval is limited to the The approval holder shall fulfil the 09.05.2<strong>01</strong>1<br />
TCAS II SYSTEM AND ATC<br />
Airplane CASA C-212 S/N 387<br />
obligations of Part 21,<br />
TRANSPONDERMODE S HONEYWELL<br />
Paragraph21A.109Prior to installation of<br />
MST 67A IN THE AIRPLANE CASA C-212-<br />
this modification it must be determined<br />
300 S/N 387<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/or<br />
repair w<br />
10034891 AEROTEC CONCEPT A340-313 Installation of EFB class IIThis STC installs the None Prior to installation of this modification it 10.05.2<strong>01</strong>1<br />
Rosemount Aerospace 8700C2-3 Laptop<br />
must be determined thatthe<br />
DockingStation (System provision)<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036025 AEROTEC CONCEPT PA 30 PFD ASPEN EFD 1000 PRO INSTALLATION<br />
on Piper PA 30.<br />
10036974 AEROTEC CONCEPT C90A Installation of Honeywell TCAS II ATC and<br />
GPWS MK VI according toAerotec<br />
modification n° MOD 1085.<br />
10037027 AEROTEC CONCEPT C90A Installation of Garmin G600 EFIS and Garmin<br />
GNS 430 W COM/NAV/GPSsystem.<br />
10037808 AEROTEC CONCEPT REV. 1 A319-115, -133<br />
A320-214, -216<br />
Advanced Mission Display System - phase B<br />
(AMDS/B) Activation<br />
10038070 AEROTEC CONCEPT REV. 1 A330-243/-3<strong>01</strong>/-341/-343 This modification intends to:- Install the<br />
Ball‐Mount support on the cockpit sliding<br />
windows- Install the two Pilot Terminal Units<br />
(PTU/B) in the cockpit on theirBall‐Mount<br />
support- Install OWCU thin mounting tray-<br />
Install AMDP 3MCU fixed mounting tray in<br />
10038946 AEROTEC CONCEPT PA-23-250 Installation of Aspen EFD 1000 Pro electronic<br />
flight instrument system.<br />
10039917 AEROTEC CONCEPT 210N Installation of a Garmin G500 EFIS, two<br />
Garmin GNS 430 W systems andassociated<br />
GA 35 GPS antennas, a Garmin GTX 330<br />
mode S transponder, aGarmin GMA 340<br />
audiopanel, a Honeywell KN62A DME receiver,<br />
a HoneywellKR 87 ADF receiver and<br />
associated KA 44B antenna.<br />
In case of malfunction of the Aspen EFD 1000<br />
Pro PFD or divergence ofindications, use<br />
Prior to installation of this modification it 05.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
standard instruments for reference.AHRS reset interrelationship between this modification<br />
prohibited in flight.LPV Approaches are not and any other previouslyinstalled<br />
authorized.RSM GPS to be used only in case modification and/ or repair will introduce<br />
of emergency.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This change is applicable to aircraft s/n<br />
LJ1066.<br />
Prior to installation of this modification it 21.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between thismodification<br />
and any other previously installed<br />
modification and/orrepair will introduce no<br />
adverse effect upon the airworthiness of<br />
theproduct.<br />
1- This change is applicable to aircraft s/n LJ Prior to installation of this modification it 26.10.2<strong>01</strong>1<br />
1066 and it is approvedfor BRNAV<br />
must be determined thatthe<br />
operations.2- The airplane must be equipped interrelationship between this modification<br />
with: - an altitude indicator, an airspeed and any other previouslyinstalled<br />
indicator and an altimeterindependent from the modification and/or repair will introduce<br />
G600 EFIS. - a third radio-communicat no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
22.12.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.06.2<strong>01</strong>2<br />
Initial installation of this design change must be Prior to Installation of this modification it 30.03.2<strong>01</strong>2<br />
performed by AEROTECtechnical<br />
must be determined thatthe<br />
personnel.This installation is approved for interrelationship between this modification<br />
BRNAV operations with coupling toS-TEC 55X end any other previouslyinstalled<br />
autopilot.The modified airplane must be modification and/or repair will introduce<br />
equipped with an attitude indicator, anairspeed no adverse effectupon the airworthiness<br />
of the product.<br />
This STC is limited to aircraft s/n 62969. This<br />
avionics installation is approved for BRNAV<br />
operations withcoupling to S-TEC 55X<br />
autopilot. The aircraft must be equipped with:-<br />
back-up airspeed, altitude, attitude, magnetic<br />
heading and navigationindicators<br />
Prior to installation of this modification it <strong>01</strong>.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 42/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong><strong>04</strong>56 AEROTEC CONCEPT EC225LP SYSTEME ANTI-GIRATOIRESling load S/N 2797 and 2824VFR onlyRequired pre- None <strong>04</strong>.07.2<strong>01</strong>2<br />
stabilization system<br />
modification: Aerotec minor modification<br />
AE11142MAS(Logging EC255 LP) and use of<br />
the dedicated RFM 'SELECTEUR DE<br />
MISSION:UPPER/LOWER (Transport de<br />
charge externe à l’élingue)', <strong>EASA</strong><br />
approval10037964<br />
10<strong>01</strong>7251 AEROTEC SARL <strong>EASA</strong>.R.S.<strong>01</strong>452 REV. 1 SA365N AEROTEC modification IRB (installation radio This STC is limited to SA 365N S/N 6080 This STC is approved only for the product <strong>01</strong>.03.2<strong>01</strong>0<br />
de bord) n° 0928. (Note for internal record: & S/N 6147 and can beinstalled only by configuration as defined inthe approved<br />
This application is to amend an existing AEROTEC technical staff in accordance with: - design data referred to in the paragraphs<br />
<strong>EASA</strong>STC (Ref P-<strong>EASA</strong>.R.S.<strong>01</strong>452) to add AEROTEC STC file Mod n° 0809. for S/N "Description" and"Associated Technical<br />
the S/N 6147)<br />
6080-AEROTEC STC file Mod n° 0928. for Documentation" Prior to installation of this<br />
S/N 6147<br />
modification it must be determined<br />
thatthe inter<br />
10<strong>01</strong>4631 AEROTECHNIC GMBH <strong>EASA</strong>.A.S.02773 DORNIER DO 228-212 Installation of mission equipment for maritime<br />
surveillance.<br />
10<strong>01</strong>6766 AGUSTAWESTLAND PHILADELPHIA <strong>EASA</strong>.IM.R.S.<strong>01</strong>097 TCCA STC SH284NE AGUSTA A-109<br />
AGUSTA A-109 AII<br />
Restricted to S/N 8181, 8183.RUAG changes<br />
<strong>EASA</strong>.A.C.<strong>04</strong>131 and <strong>EASA</strong>.A.C.<strong>04</strong>132 must<br />
be installed concurrently.<br />
Installation of Alternate Static Pressure Source 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.Configuration A is el<br />
10031050 AGUSTAWESTLAND PHILADELPHIA FAA STC SR02767NY AW119MKII Installation of an Artex ME406P ELT none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.- If th<br />
23.07.2<strong>01</strong>0<br />
10031114 AGUSTAWESTLAND PHILADELPHIA FAA STC SR02777NY AW119MKII Installation of a SX-5 Searchlight and cargo<br />
Hook Heated rearview mirror<br />
10031274 AGUSTAWESTLAND PHILADELPHIA FAA STC SR02265NY A119/AW119MKII Installation of pedal extensions on A119,<br />
AW119MKII helicopters<br />
26.07.2007<br />
<strong>04</strong>.07.2005<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
28.07.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product- If the<br />
06.08.2<strong>01</strong>0<br />
10031277 AGUSTAWESTLAND PHILADELPHIA FAA STC SR02789NY AW119MKII Installation of a Border Guard Configuration none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
06.08.2<strong>01</strong>0<br />
10031316 AGUSTAWESTLAND PHILADELPHIA FAA STC SR02428NY A119 / AW119MKII <strong>EASA</strong> Validation FAA STC SR02428NY for<br />
A119 / AW119MKII - High VisibilityCrew Doors<br />
10039055 AGUSTAWESTLAND PHILADELPHIA FAA STC SR02444NY A119<br />
AW119 MKII<br />
<strong>EASA</strong> Validation of FAA STC SR02444NY<br />
"Installation of the OffshoreConfiguration in<br />
accordance with Agusta Aerospace Master<br />
Data ListAAC-ENG-06-051 Rev.C"<br />
None The modified crew doors of this STC may<br />
be used to replace either one ofthe<br />
existing doors or both. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
09.08.2<strong>01</strong>0<br />
None.<br />
previouslyinstalled modif<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.<strong>04</strong>.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 43/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4165 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.<strong>01</strong>297 AIRBUS A300-600 Installation of a Galley bulkhead. 1. Viewing of all Placards and signage to be in<br />
compliance with CS/FAR 25.791 Weight,<br />
Centre Gravity and Weight Distribution to be in<br />
Compliance with CS/FAR 25.1519.2.<br />
Compliance with CS/FAR 25.785 (d) (3), the<br />
elimination of any injurious abject within st<br />
08.06.2005<br />
10<strong>01</strong>4166 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.<strong>01</strong>299 BOEING 767-300 Installation of Stowage C2. 1. Viewing of all Placards and signage to be in<br />
compliance with CS/FAR 25.791 Weight,<br />
Centre Gravity and Weight Distribution to be in<br />
Compliance with CS/FAR 25.1519.2.<br />
Compliance with CS/FAR 25.785 (d) (3), the<br />
elimination of any injurious abject within st<br />
10<strong>01</strong>4167 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.<strong>01</strong>300 BOEING 737-500 Installation of Galley 3. 1. Viewing of all Placards and signage to be in<br />
compliance with CS/FAR 25.791 Weight,<br />
Centre Gravity and Weight Distribution to be in<br />
Compliance with CS/FAR 25.1519.2.<br />
Compliance with CS/FAR 25.785 (d) (3), the<br />
elimination of any injurious abject within st<br />
10<strong>01</strong>4168 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.<strong>01</strong>3<strong>01</strong> BOEING 737-500 Installation of Wardrobe W1. 1. Viewing of all Placards and signage to be in<br />
compliance with CS/FAR 25.791 Weight,<br />
Centre Gravity and Weight Distribution to be in<br />
Compliance with CS/FAR 25.1519.2.<br />
Compliance with CS/FAR 25.785 (d) (3), the<br />
elimination of any injurious abject within st<br />
10<strong>01</strong>4356 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.<strong>01</strong>621 BOEING 737-400 Installation of Galley 1 & Galley 2 for Futura<br />
International Airways<br />
10<strong>01</strong>4453 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.02507 BOEING 747-428 Installation of Upper Deck Galley partnr<br />
747AFA<strong>01</strong>GA00 into a B747-428 passenger to<br />
cargo conversion (747-400BCF) as defined in<br />
STC Definition Document DD 1022 d.d. <strong>01</strong>-06-<br />
2006 or later <strong>EASA</strong> approved revisions.<br />
10<strong>01</strong>4479 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.02542 BOEING 767-300 Installation of Galley F4 Part Number<br />
7673FCF4GA00<br />
10<strong>01</strong>5007 AIM AVIATION (HENSHALLS) LTD <strong>EASA</strong>.A.S.03307 BOEING 757-200 Installation of Crew Galley in B757-200<br />
Freighter Conversion.<br />
10034166 AIM AVIATION (HENSHALLS) LTD B757-200 Installation of a Crew Galley in the G1A<br />
Position on a FreighterConversion a/c<br />
10036493 AIM AVIATION (HENSHALLS) LTD A319 Installation of a Galley 13 and Closet C1into an<br />
Airbus A319-100 to beoperated by BMI<br />
10038683 AIM AVIATION (HENSHALLS) LTD A321 Installation of Galley 2A Part No.<br />
321BMI2AGA00 and Galley 3A Part<br />
No321BMI3AGA00 into an A321-200 to be<br />
operated by BMI.<br />
Restricted to Aircraft Serial Number 26063 &<br />
26064<br />
08.06.2005<br />
14.06.2005<br />
08.06.2005<br />
06.<strong>01</strong>.2006<br />
03.05.2007<br />
29.09.2006<br />
05.02.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
14.03.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.09.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.03.2<strong>01</strong>2<br />
10<strong>04</strong><strong>04</strong>27 AIM AVIATION (HENSHALLS) LTD B747-400 Installation of Galley 2A, 2B, 4B, 4C and 4D<br />
and ceilings in the G4complex in a Boeing 747-<br />
400 to be operated by Virgin Atlantic Airways<br />
inaccordance with AIM Henshalls STC<br />
Definition Document DD 1198,dated 3<br />
January 2<strong>01</strong>2<br />
None None 02.07.2<strong>01</strong>2<br />
10<strong>01</strong><strong>462</strong>9 AIM AVIATION (JECCO) LIMITED <strong>EASA</strong>.A.S.02768 AIRBUS A330-200<br />
Introduction of flight crew rest facility into A330- MM-358-07 must be installed. 31.05.2007<br />
AIRBUS A330-300<br />
200 and -300 aircraft.<br />
10<strong>01</strong>4649 AIM AVIATION (JECCO) LIMITED <strong>EASA</strong>.A.S.028<strong>04</strong> AIRBUS A330-200<br />
AIRBUS A330-300<br />
Aer Lingus Flight Crew Rest Facility 05.02.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 44/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4919 AIM AVIATION (JECCO) LIMITED <strong>EASA</strong>.A.S.03165 JAA/25/03/028 ISSUE 1 BOEING 747-400 Virgin Atlantic Airways B747-400 CoCo The following <strong>EASA</strong> approved STC's must be<br />
09.10.2007<br />
Reconfiguration.<br />
installed concurrently with this design<br />
change:<strong>EASA</strong>.A.S.02860<strong>EASA</strong>.IM.A.S.02572<br />
10<strong>01</strong>5102 AIM AVIATION (JECCO) LIMITED <strong>EASA</strong>.A.S.03445 Premium Cabins UpgradeAppearance, comfort Prior to installation of this modification the<br />
and maintenance improvement changes to the installer must determine that the<br />
seats and the window reveals and shades in interrelationship between this modification and<br />
the First and Business Class cabins.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5103 AIM AVIATION (JECCO) LIMITED <strong>EASA</strong>.A.S.03446 REV. 1 AIRBUS A330-243 Major Change to STC <strong>EASA</strong>.A.S.03446 (AIM<br />
Major Change MM384-07)date of issue 14<br />
November 2008.Introduce decorative finish<br />
change to Contour 0995 series BusinessClass<br />
Seats.<br />
10<strong>04</strong><strong>04</strong>31 AIM AVIATION (JECCO) LIMITED 747-400 Installation of a single isolation switch in<br />
accordance with AIMAviation Service Bulletin<br />
B747-24-<strong>01</strong>1 dated April 23, 2<strong>01</strong>2<br />
asreplacement for AIM Aviation Service<br />
Bulletin B747-24-<strong>04</strong> or B747-24-05in order to<br />
comply to FAA AD 2009-15-12.<br />
<strong>EASA</strong> Supplemental Type Certificate<br />
<strong>EASA</strong>.A.S.03446 (AIM Major ChangeMM384-<br />
07) must be embodied prior to the installation<br />
of this MajorChange.As per indications stated<br />
in AIM MAJOR Change ref. Doc. MM481-10<br />
IssueC.<br />
05.08.2008<br />
Prior to installation of this modification it 22.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Flight Manual Supplement AIM Aviation<br />
Document Nr 11184 Issue A, dated28<br />
May, 2<strong>01</strong>2 shall be on board the modified<br />
aircraft.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other pr<br />
03.07.2<strong>01</strong>2<br />
10<strong>01</strong>5599 AIM AVIATION INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>535 ST<strong>01</strong>5<strong>04</strong>SE BOEING 757-200 Installation of a Flight Deck Galley 03.<strong>04</strong>.2006<br />
10<strong>01</strong>5600 AIM AVIATION INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>536 FAA STC ST<strong>01</strong>490SE BOEING 757-200 SERIES Installation of a Flight Deck Lavatory This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
31.03.2006<br />
10<strong>01</strong>4775 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.02973 SOCATA TBM 700 Installation of Garmin GTX330D Transponder Prior to installation of this modification the<br />
15.08.2007<br />
with Top Antenna.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4857 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03081 REV. 3 CESSNA 208<br />
CESSNA 208A<br />
CESSNA 208B<br />
Conversion of airplane for parachute<br />
operations.Installation of PARAKIT NAY0<strong>01</strong> or<br />
ParaKit C208-83 00 00 "System Gomolzig".<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4947 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03207 PIPER PA-42 Installation of TCAS 9900 BX. 06.12.2007<br />
10<strong>01</strong>4988 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03281 PIPER PA-31T1 Installation of Avionic Upgrade according MDL<br />
2007_<strong>01</strong>9_2029 AA Form 1 Rev. 0.<br />
10.<strong>01</strong>.2008<br />
10<strong>01</strong>5178 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03556 REV. 1 BEECH 300 Installation of L3 FDR1000; Collins EGPWS Prior to installation of this modification the<br />
20.06.2008<br />
Mark VI; Honeywell CAS 67 & Dual MST 67A installer must determine that the<br />
Mode S Diversity Transponder; Artex 406-2 interrelationship between this modification and<br />
ELT<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>5205 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03606 CESSNA 525<br />
CESSNA 525A<br />
Exchange of GPS Navigation System KING<br />
KLN 900 against Flight Management System<br />
Universal UNS 1Lw<br />
10<strong>01</strong>5226 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03643 REV. 1 CESSNA 525 Installation of Dual GTX 330D as Replacement<br />
of Dual KT 70 or KT 71<br />
1. This STC is only eligible for aeroplanes<br />
equipped with GPS Receiver System KLN<br />
900 and Collins Pro Line 21 Avionic<br />
System2.Prior to installation of this modification<br />
the installer must determine that the<br />
interrelationship between this modific<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 45/<strong>462</strong><br />
29.<strong>01</strong>.2009<br />
12.08.2008<br />
05.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5263 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03721 DORNIER DO 228-1<strong>01</strong><br />
Installation of FMS Universal UNS-1Lw. 1. Restricted to aircrafts which have already<br />
23.<strong>01</strong>.2009<br />
DORNIER DO 228-2<strong>01</strong><br />
installed a LH HSI Honeywell KPI552B and two<br />
DORNIER DO 228-202<br />
Shadin ADC’s ADC2000.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any ot<br />
10<strong>01</strong>5271 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03753 PIPER PA-31T<br />
PIPER PA-31T1<br />
PIPER PA-31T2<br />
10<strong>01</strong>5298 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03851 BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>5299 AIR ALLIANCE GmbH <strong>EASA</strong>.A.S.03852 PIPER PA-31T<br />
PIPER PA-31T1<br />
PIPER PA-31T2<br />
Camera Installation Floor Cut Out 1 Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the pro<br />
Installation of Honeywell Mark VI EGPWS. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
Installation/ Exchange of Avionics acc.<br />
AirAlliance MDL 2008_059_A8EA in latest<br />
approved Revision<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6091 AIR ALLIANCE GmbH <strong>EASA</strong>.IM.A.S.02278 REV. 3 PA-42-720 Extension of pressurized fuselage life limit to This STC is limited only to airplane S/N 42- The installation of this modification by 19.07.2<strong>01</strong>1<br />
account for the changein operational usage 55<strong>01</strong><strong>04</strong>6 and 42-55<strong>01</strong><strong>04</strong>7operated by any third persons is subject towritten<br />
from Alitalia Airlines Training to Normal Usage operator.Operation in normal usage up to a life- permission of the approval holder and<br />
byany operator.Note: This STC supersedes limit of 21.452 hours for S/N42-55<strong>01</strong><strong>04</strong>6 and holding and disposal ofthe approved<br />
STC <strong>EASA</strong>.IM.A.S.02278 Rev 2 and indicates 21.561 hours for S/N 42-55<strong>01</strong><strong>04</strong>7.Air Alliance appropriate documentation. Prior to<br />
thetransfer of an applicable S/N t<br />
GmbH Report No AARD-2 Rev B dated 28 installation of this modification it must be<br />
determined thatthe interr<br />
10027217 AIR ALLIANCE GmbH P-<strong>EASA</strong>.A.S.03905 REV. 1 TB9, TB10, TB 20, TB21, TB200 Installation of Aspen EFD 1000 PRO None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>0<br />
10027714 AIR ALLIANCE GmbH P-<strong>EASA</strong>.A.S.03957 TBM 700 Installation of GPS Antenna for Situational<br />
Awareness Tool.<br />
10029583 AIR ALLIANCE GmbH P-<strong>EASA</strong>.A.S.03461 LEARJET 35A Installation of new avionics (FDR, TAWS, FMS,<br />
RDR/KMD)<br />
10033818 AIR ALLIANCE GmbH PA-42-1000 Installation of SAT antenna (Data-Link) into<br />
pressurized fuselage.<br />
10035779 AIR ALLIANCE GmbH PA-42-720 Extension of pressurized fuselage life limit to<br />
account for the changein operational usage<br />
from Alitalia Airlines Training to Normal Usage<br />
byany operatorNote: This STC indicates the<br />
transfer of an applicable S/N from<br />
STC<strong>EASA</strong>.IM.A.S.02278 Rev 2 to this STC<br />
10035987 AIR ALLIANCE GmbH LEARJET 35A Installation of Honeywell GNS-XLS second<br />
FMS system.<br />
21.<strong>01</strong>.2009<br />
<strong>01</strong>.<strong>04</strong>.2009<br />
<strong>01</strong>.<strong>04</strong>.2009<br />
None. Prior to installation of this modification the 26.10.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
Approval valid for s/n 35A-616 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.<br />
This STC is limited only to airplane S/N 42-<br />
55<strong>01</strong><strong>04</strong>5 operated by anyoperator. Operation<br />
in normal usage up to a life-limit of 21.563<br />
hours for S/N42-55<strong>01</strong><strong>04</strong>5. Air Alliance GmbH<br />
Report No AARD-2 Rev B dated 28 Dec 2006<br />
"Air AlliancePA-42-720 Aircraft - Pressu<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
02.<strong>04</strong>.2<strong>01</strong>0<br />
10.02.2<strong>01</strong>1<br />
19.07.2<strong>01</strong>1<br />
Limited to 35A-421 and 35A-616.<br />
determined thatthe interr<br />
None. 03.08.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 46/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037809 AIR ALLIANCE GmbH 337, A, B, C, D, E, F, G, H Replacement of installed Slaved Gyro system None Prior to installation of this modification it 22.12.2<strong>01</strong>1<br />
M337B, P337H<br />
by ASPEN EFD 1000 PROPrimary Flight<br />
must be determined thatthe<br />
T337B, C, D, E, F, G, H, H-SP Display<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038951 AIR ALLIANCE GmbH 208, 208B Installation of Honeywell KFD840 Primary<br />
Flight Display.<br />
10<strong>04</strong>2509 AIR ALLIANCE GmbH PA-44-180<br />
PA-44-180T<br />
Replacement of installed Gyro system by<br />
ASPEN EFD 1000 Pro PrimaryFlight Display.<br />
10<strong>01</strong>4268 AIR ALPHA A/S <strong>EASA</strong>.A.S.<strong>01</strong>497 REV 1 BAE HS 748 2A & 2B Installation of a Honeywell EGPWS MK6<br />
system.<br />
10028446 AIR ALPHA A/S P-<strong>EASA</strong>.A.S.03971 BEECH 200, BEECH B200 Installation of Blue Sky Network (BSN)<br />
BEECH B200C, BEECH<br />
D1000(A) Iridium SatelliteCommunication and<br />
B200CGT<br />
BEECH B200GT<br />
Tracking<br />
1003<strong>04</strong>56 AIR ALPHA A/S B200, B200GT Air Alpha STC Definition Document EO-B200-<br />
25-145. Flight InspectionSystem Interface<br />
Installation King Air 200 Series.<br />
1003<strong>04</strong>70 AIR ALPHA A/S P-<strong>EASA</strong>.A.S.03969 200, B200 AND B200GT Provision for Flight Inspection use of MLS<br />
navigation input<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.03.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.12.2<strong>01</strong>2<br />
1. Existing GPS antenna shall be used with<br />
15.08.2005<br />
coach splitter.<br />
None 1. Prior to installation of this modification 12.<strong>01</strong>.2<strong>01</strong>0<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.06.2<strong>01</strong>0<br />
MINIMUM FLIGHT CREW: FIS MLS<br />
Navigation may only be used with two (2)flight<br />
crew members seated in the cockpitMLS/FIS<br />
NOT FOR PRIMARY NAVIGATION. FLIGHT<br />
INSPECTION GUIDANCE ONLY<br />
STC Holder approval required prior to<br />
application by any other partyPrior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
1003<strong>04</strong>71 AIR ALPHA A/S P-<strong>EASA</strong>.A.S.03942 B200 AND B200GT MD-124F Direction Finder Antenna Installation None<br />
repair will intr<br />
STC Holder approval required prior to<br />
application by any other partyPrior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will intr<br />
17.06.2<strong>01</strong>0<br />
10<strong>01</strong>4578 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.02683 BEECH B200 Installation of Trane & Trane Aero-I satcom<br />
equipment in accordance with danish STC<br />
03/9Note: This STC superseads SLV STC No.<br />
3/99<br />
13.07.2006<br />
10<strong>01</strong>4579 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.02684 BEECH B200 Installation of Trane & Trane Aero-M satcom<br />
equipment in accordance with danish STC<br />
<strong>04</strong>/99Note: This STC superseads SLV STC<br />
No. <strong>04</strong>/99<br />
13.07.2006<br />
10<strong>01</strong>4580 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.02685 BEECH B200 Installation of Trane & Trane Aero-C satcom<br />
equipment in accordance with danish STC<br />
05/99.Note: This STC superseads SLV STC<br />
No. 05/99<br />
13.07.2006<br />
10<strong>01</strong>4581 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.02686 BEECH B200 Installation of Trane & Trane Aero-I, Aero-M<br />
and Aero-C satcom equipment in accordance<br />
with danish STC 29/99.Note: This STC<br />
superseads SLV STC No. 29/99.<br />
13.07.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 47/<strong>462</strong><br />
17.06.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4598 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.02718 KING AIR 200 Installation of a Navaids Flight Inspection Installed unit, UNIFIS 3000 must comply with<br />
11.10.2006<br />
System UNIFIS 3000. Installation in aircraft requirements in JAA TGL No. 17.Antenna<br />
includes: Two static inverters installations and pilot aids as a CDI with<br />
for power supply.A vertical gyro VG400 annunciator and intercom must be approved<br />
separately.<br />
10<strong>01</strong>4618 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.02750 Antennas - Relocation and Installation in<br />
accordance with EO-B200-25-106 and DWG.<br />
No. EN-B200-25-106-<strong>01</strong> to support UNIFIS<br />
3000 Flight Inspection System.<br />
MSN BB1221 only. 20.09.2006<br />
10<strong>01</strong>4798 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.030<strong>01</strong> BEECH B200 Installation of Unifis 3000 Flight Inspection<br />
System including antennas in Beech B200.The<br />
system is used to check and calibrate ground<br />
based navigation aids.<br />
Limited to B200 S/N: BB-829. <strong>04</strong>.12.2007<br />
10<strong>01</strong>4844 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03062 PILATUS PC-12<br />
Installation of an L3 Communications Solid Only for PC12/45 and PC 12/47 without the<br />
23.07.2007<br />
PILATUS PC-12/45<br />
State Flight Data Recorder Model F-1000, P/N Oxygen System Installation, Rear Fuselage.<br />
PILATUS PC-12/47<br />
S703-1000-00The recorder meets the<br />
requirement of FAA TSO-C124a<br />
10<strong>01</strong>4884 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03112 CESSNA 560 XL Installation of UNIFIS 3000 Flight Inspection<br />
System:Console, cockpit indication system,<br />
antennae<br />
12.12.2007<br />
10<strong>01</strong>4894 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03124 BEECH 200, SUPER KING AIR Replacement of ATC transponders with<br />
Rockwell Collins TDR-94 or TDR-94D Mode S<br />
systems for ELS and EHS. Installation of top<br />
Antenna(s) CI110-660 or DMN 150-6.<br />
23.07.2007<br />
10<strong>01</strong>4975 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03262 BEECH B200 Garmin GWX-68 Radar, Garmin GMX-200<br />
Multi-Function Display, and Avidyne TAS620<br />
Traffic Adivsory System.<br />
Aircraft S/N BB829 20.12.2007<br />
10<strong>01</strong>4976 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03264 BEECH B200 Installation of two Sandel SN3500 EHSI 1. Aircraft S/N BB829.2. Prior to installation<br />
29.11.2007<br />
(Electronic Horisontal Situation Indicator) of this modification the installer must determine<br />
replacing existing HSI Displays.<br />
that the interrelationship between this<br />
modification and any other previously installed<br />
modification will introduce no adverse effect<br />
upon the airworthin<br />
10<strong>01</strong>5164 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03535 CESSNA 560 XL Printer Stand Installation 28.<strong>04</strong>.2008<br />
10<strong>01</strong>5217 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.A.S.03632 BEECH B200 Flight Inspection System antenna and 1. The applicability of this STC is limited to<br />
17.<strong>04</strong>.2009<br />
equipment interface installation.<br />
B200 S/N: BB-1399.2. Prior to installation of<br />
this modification the installer must determine<br />
that the interrelationship between this<br />
modification and any other previously installed<br />
modification will intr<br />
10<strong>01</strong>7124 AIR ALPHA MAINTENANCE A/S <strong>EASA</strong>.R.S.<strong>01</strong>211 DANISH STC NO.51/2002 EUROCOPTER FRANCE EC 120 Installation of Flying Pictures Model BSS 400 1. This STC does not include the Videolink<br />
<strong>04</strong>.<strong>01</strong>.2006<br />
B<br />
Camera System in accordance with Danish System with its Antenna, Antenna Actuator,<br />
STC No. 51/2002<br />
Power Supply, Remote Control, and<br />
Amplifier.Concerning the transfer:CAA-<br />
Denmark confirms that the new STC holder,<br />
Air Alpha Maintenance A/S, has received all<br />
necessary da<br />
10028645 AIR ALPHA MAINTENANCE A/S B200, B200C, B200GT, B200CGT Air Alpha STC Definition Document EO-B200- None Prior to installation of this modification it <strong>01</strong>.02.2<strong>01</strong>0<br />
23-138 for Intercominstallation and<br />
must be determined thatthe<br />
modification. Intercom installation in cabin<br />
interrelationship between this modification<br />
forspecial mission aircraft. The cabin intercom<br />
and any other previouslyinstalled<br />
interfaces to the cockpitintercom.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4960 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10<strong>01</strong>5192 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10<strong>01</strong>7086 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
<strong>EASA</strong>.A.S.03231 BEECH 65-A90<br />
BEECH C90<br />
Installation of Air Medical Interior "Quick<br />
Conversion" Beech 65-A90, Beech C90, P/N<br />
65-A90-25-20-15.000.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.03576 BEECH 100<br />
BEECH 200<br />
Installation of Air Medical Interior. 17.06.2008<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>61 REV. 3 AS 332 C, AS 332 C1, AS332 L1, Cabin Interior "Quick Conversion" kits, installing None The approval holder shall fulfil the 03.08.2<strong>01</strong>0<br />
AS 332 L2<br />
either AAT AirAmbulance Equipment or AAT<br />
obligations of Part 21,<br />
SA 330 J, EC225 LP<br />
Mission Equipment cabin layout configurations<br />
Paragraph21.A118. Prior to installation of<br />
Note: This STC is a superseding revision of<br />
this modification it must be determined<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>61 Rev. 2,underlining<br />
thatthe interrelationship between this<br />
Associated Technical Documentation updat<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 48/<strong>462</strong><br />
19.12.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7087 AIR AMBULANCE TECHNOLOGY <strong>EASA</strong>.R.S.0<strong>04</strong>62 REV. 3 EC 135 Installation of Air Ambulance Equipment, 1. Subject to compliance with the provisions<br />
08.10.2008<br />
GES.m.b.H.<br />
Mission Equipment, Airborne Radiation of EC 1702/2003 PART 21 Subpart E, this<br />
Measuring Equipment, Revision2 addsVIP Certificate and associated data shall remain<br />
Interior P/N 135-25-20-5000-900 incl. flooring, valid until surrendered, withdrawn or other<br />
seats, fairing and cabinets.<br />
terminated.2. This STC is approved only for<br />
the product configuration as d<br />
10<strong>01</strong>7112 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10<strong>01</strong>7225 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10<strong>01</strong>7254 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10<strong>01</strong>7291 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10031521 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10032292 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10034706 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
100372<strong>01</strong> AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10037231 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
10038064 AIR AMBULANCE TECHNOLOGY<br />
GES.m.b.H.<br />
<strong>EASA</strong>.R.S.<strong>01</strong>089 BELL 407 Mission Equipment Bell 407 – Several racks to<br />
install a camera equipment for TV productions<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
<strong>EASA</strong>.R.S.<strong>01</strong>393 AS 332 L2 VIP interior, quick conversion P/N 332-25-24installer.<br />
1. STC applicable only on individual<br />
3000-9<strong>01</strong>.<br />
AS332L2 aircraft equipped with approved VIP<br />
salon consisting of Eurocopter<br />
furniture:Forward Lounge: 4 face-to-face VIP<br />
seats with 2 VIP tables in the middle based on<br />
Eurocopter Dwg 332V851329.Rear Lounge: 8<br />
comfort<br />
<strong>EASA</strong>.R.S.<strong>01</strong>457 W-3AS Installation of Air Ambulance Equipment "quick<br />
conversion P/N W-3A-25-20-33.000.<br />
<strong>EASA</strong>.R.S.<strong>01</strong>548 AB 139, AW 139 Installation of Air Ambulance Equipment, 1) Prior to installation of this modification the<br />
Mission Equipment "Quick - Conversion", P/N installer must determine that the<br />
AW139-25-20-37.000-60x model<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2) The ins<br />
REV. 1 ASTRA SPX Installation of Air Ambulance Equipment In<br />
Astra SPX<br />
A330-200/ -300 Air Ambulance Equipment "quick<br />
conversion"P/N A330-25-20-10.000 515 -<br />
Intensive Care Module P/NA330-25-20-10.300-<br />
603<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>70 REV.1 AS 350 B, AS 350 B1, AS 350 B2 Installation of Air Ambulance Equipment<br />
AS 350 B3, AS 350 BA,EC 130 B4 (removable stretcher)<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>64 REV. 3 1. BHT 212/412/412 EP<br />
2. AB 212/AB 412/412 EP<br />
Installation of Air Ambulance<br />
EquipmentExtension of existing<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>64 Rev. 2 with Helicopter Model<br />
412EP<br />
02.11.2005<br />
17.08.2007<br />
17.<strong>04</strong>.2008<br />
09.06.2009<br />
For S/N 133: Limited to Astra SPX, S/N 133 Prior to installation of this modification it 13.02.2<strong>01</strong>2<br />
with Duncan Interior STC ST00808 WIinstalled. must be determined thatthe<br />
and modified according this <strong>EASA</strong> STCThis interrelationship between this modification<br />
STC requires implementation of Two (2) Minor and any other previouslyinstalled<br />
changes:Avionics Integration & Engineering modification and/ or repair will introduce<br />
Corporation AG, CH : Removal ofpart no adverse effectupon the airworthiness<br />
of the product.<br />
This STC does not constitute an approval for<br />
installation. Compliancewith the following<br />
requirements will be demonstrated and<br />
covered by theDOA responsible for the<br />
medical stretcher installation on the<br />
aircraftA330 through a design approval: §<br />
25.561(d) §<br />
Prior to installation of this modification it 25.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
none none 20.<strong>04</strong>.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.11.2<strong>01</strong>1<br />
MYSTERE FALCON 50 Installation of Air Ambulance Equipment "quick None. Prior to installation of this modification it 11.11.2<strong>01</strong>1<br />
conversion" in MF50 inthe RH Cabin Section of<br />
must be determined thatthe<br />
Aircraft.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
LEARJET 45 Installation of Air Ambulance Equipment Minor Change LR45-19<strong>01</strong>0-050-LP, Installation Prior to installation of this modification it 16.<strong>01</strong>.2<strong>01</strong>2<br />
of EMS power source must beinstalled prior must be determined thatthe<br />
this modification<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 49/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4296 AIR CARAIBES INDUSTRIES <strong>EASA</strong>.A.S.<strong>01</strong>540 DORNIER DO 228-202K Flight Data Recorder installation. Installation of 1. This STC is limited to MSN 8139, F-OGOL<br />
SSFDR type flight data recorder following OPS<br />
1.725 implementation.<br />
12.09.2005<br />
10<strong>01</strong>6784 AIR COMM CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>125 SR0<strong>04</strong>91DE EUROCOPTER FRANCE EC 120<br />
B<br />
Installation of Cabin Air Conditioning<br />
system.The present STC is the validation of the<br />
10<strong>01</strong>6787 AIR COMM CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>132 SR0<strong>04</strong>63DE AGUSTA A-119<br />
FAA STC n°SR0<strong>04</strong>91DE.<br />
Air Conditioning System for Agusta A 119FAA This approval should not be extended to<br />
STC SR0<strong>04</strong>63DE issued on 11th January 2002 rotorcraft of this model on which other<br />
and amended on 24th January 2006<br />
previously approved modifications are<br />
incorporated unless it is determinded that the<br />
interrelationship between this change and any<br />
of those other previously approved modificati<br />
10<strong>01</strong>6812 AIR COMM CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>173 FAA STC SR00222DE BELL 407 Installation of a vapour cycle air conditioning<br />
system<br />
None 30.06.2006<br />
10<strong>01</strong>6939 AIR COMM CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>327 FAA STC SH4057NM SIKORSKY S-76A<br />
Installation of bleed air cabin heater and This STC is approved only for the product<br />
08.05.2007<br />
SIKORSKY S-76B<br />
windshield defrost system.Note: STC configuration as defined in the approved design<br />
SIKORSKY S-76C<br />
SH4057NM was originally approved by the UK data referred to in the paragraphs "Description"<br />
CAA under Airworthiness Approval note NO. and “Associated Technical Documentation”.<br />
25242. This approval adds models S76A and Compatibility with other aircraft/engine<br />
S76B to the approval. This STC supersedes<br />
UK CAA A<br />
configurations shall be determined<br />
10<strong>01</strong>6959 AIR COMM CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>356 FAA STC SR006<strong>01</strong>DE EUROCOPTER EC 135 Installation of Cabin Air Conditioning System<br />
i.a.w. FAA STC SR00565DE, dated<br />
22/06/2005.<br />
09.10.2007<br />
10<strong>01</strong>7<strong>04</strong>4 AIR COMM CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>468 FAA STC SH5226NM BELL 230 Installation of a bleed air cabin heating system. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
02.09.2008<br />
10026907 AIR COMM CORPORATION P-<br />
FAA STC SR00230DE BELL 407 Bell Helicopter Model 407 Cabin Ventilation None 1) Prior to installation of this modification 21.08.2009<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>559<br />
System.<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10028717 AIR COMM CORPORATION FAA STC SR00693DE BELL HELICOPTER 429 Installation of Cabin Air Conditioning System<br />
Provisions<br />
24.<strong>01</strong>.2006<br />
02.03.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.02.2<strong>01</strong>0<br />
10029555 AIR COMM CORPORATION FAA STC SR00543DE EC 130 B4 Installation of Cabin Air Conditioning System None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>0<br />
1003<strong>01</strong>66 AIR COMM CORPORATION FAA STC SR0<strong>04</strong>63DE A119, AW119 MKII FAA STC No. SR0<strong>04</strong>63DE Installation of Air<br />
Conditioning System<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.05.2<strong>01</strong>0<br />
10038232 AIR COMM CORPORATION FAA STC SR00692DE 429 Installation of Bleed Air Heater None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
30.<strong>01</strong>.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 50/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029849 AIR CRUISERS COMPANY FAA STC SR02538NY BELL 407 Bell 407 Emergency Float Kit P/N 67432- For installation only on Bell 407 models Prior to installation of this modification it 26.<strong>04</strong>.2<strong>01</strong>0<br />
1<strong>01</strong>Note: This STC is for the installation of the previously equipped with theBell Emergency must be determined thatthe<br />
Pneumatic ActivationSystem only.<br />
Float Gear Skid tubes BHT P/N 206-053-184- interrelationship between this modification<br />
121 and206-053-184-122 or approved and any other previouslyinstalled<br />
equivalents. The ACC Bell 407 Emergency modification and/ or repair will introduce<br />
Float Installation Kit is used in conjunctionwith no adverse effectupon the airworthiness<br />
the f<br />
of the product.<br />
10029956 AIR CRUISERS COMPANY FAA STC SR02633NY BELL 206 L-4 Bell 206L-4 Emergency Float Kit P/N 67585-<br />
1<strong>01</strong><br />
10<strong>01</strong>3926 AIR FRANCE <strong>EASA</strong>.A.S.0<strong>01</strong>98 REV. 1 BOEING 747-400 Air France B747-400 "ULYSSE" cabin 1.The approval of this modification is limited to<br />
reconfiguration. This is a revision to STC Ref the Boeing B747-400 MAS 24969, 24990,<br />
<strong>EASA</strong>.A.S.0<strong>01</strong>98, to extend the applicability to 25344, 25600, 256<strong>01</strong>, 25602, 32868, 32869,<br />
the aircraft B747-400 F-GITH MSN 32868, F- 32871, 25238, 25302, 25559, 25628, 25630,<br />
GITI MSN 32869 and F-GEXA MSN 24154. 24154, 24155. The limitations and conditions<br />
The general description is included in the Air F defined in the <strong>EASA</strong> Datasheet are appli<br />
10<strong>01</strong>3927 AIR FRANCE <strong>EASA</strong>.A.S.00225 REV. 2 BOEING 747-400 ISPSS Installation on B747-400 in accordance<br />
with MA.PM 263/03 rev 5 dated 22/09/2005<br />
The ACC Bell 206L-4 Emergency Float Prior to installation of this modification it 06.05.2<strong>01</strong>0<br />
Installation Kit is for theinstallation of the must be determined thatthe<br />
Pneumatic Activation System only, and is used interrelationship between this modification<br />
inconjunction with the float bags Type Certified and any other previouslyinstalled<br />
per TCCA TC H-92 (BellP/Ns 206-706-210- modification and/ or repair will introduce<br />
113).<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph “Description”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by installer.<br />
10<strong>01</strong>3939 AIR FRANCE <strong>EASA</strong>.A.S.00375 REV. 1 AIRBUS A319-115 A319 CJ CASTA II Cabin Reconfiguration 1. This STC is limited to the A319-115 CJ<br />
MSN's 1485 and 15562. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine config<br />
10<strong>01</strong>3947 AIR FRANCE <strong>EASA</strong>.A.S.0<strong>04</strong>05 REV 1 BOEING 777-200-228-300 RAAS (Runway Awareness and Advisory 1. See AFM limitations for options to be<br />
13.07.2006<br />
System) activation. Air France AEO 77-34- used.2. Applicable to a/c serial numbers<br />
0051 rev. 2 dated November 24, 20<strong>04</strong>CAS- listed in Air France CAS-B777-05-<strong>01</strong>92. This<br />
B777-05-19 rev 0 dated 29 June 2006 (or later STC is approved only for the product<br />
approved issue)RAAS Activation on B777-200/- configuration as defined in the approved design<br />
300 Air France aircraftNote: This modification<br />
ext<br />
data referred to in the paragraph "D<br />
10<strong>01</strong>3996 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>030 REV 1 AIRBUS A321-211 Cabin reconfigurationChange Approval Sheet<br />
ref. CAS-A320-<strong>04</strong>-<strong>01</strong>5 revision 2, dated<br />
October 21, 2005<br />
This STC is limited to the A321 MSN 1<strong>01</strong>7 08.09.2006<br />
10<strong>01</strong>4054 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>137 BOEING 767-200-300 Installation of Elementary Surveillance Dual<br />
ATC Mode S on B767-300The ATC Mode S<br />
computers TPR 720 are replaced by a TPR<br />
9<strong>01</strong> which is compliant with ATC Mode S<br />
Elementary surveillance requirements.ATC<br />
Mode S Elementary surveillance<br />
implementation is descr<br />
22.08.2005<br />
10<strong>01</strong>4055 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>138 BOEING 767-200-300 Installation of Elementary Surveillance Dual<br />
ATC Mode S on B767-300The ATC Mode S<br />
computers TPR 720 are replaced by a TPR<br />
9<strong>01</strong> which is compliant with ATC Mode S<br />
Elementary surveillance requirements.ATC<br />
Mode S Elementary surveillance<br />
implementation is descr<br />
07.<strong>04</strong>.2005<br />
10<strong>01</strong>4056 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>139 BOEING 747-200-300 Installation of EGPWS.This STC supersedes<br />
and cancels DGAC STC IM29-SF-0282.<br />
18.05.2005<br />
10<strong>01</strong>4057 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>140 BOEING 747-300 Elementary surveillance dual ATC Mode S<br />
installation.<br />
This STC is limited to the B747 MSN 24106. 15.03.2007<br />
10<strong>01</strong>4065 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>151 AIRBUS A320 Cabin passenger seats relocation and floor<br />
proximity emergency escape path marking<br />
change<br />
07.<strong>04</strong>.2005<br />
10<strong>01</strong>4264 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>494 B767 Rockwell Collins Aero I SATCOM installation 19.12.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 51/<strong>462</strong><br />
19.10.2005<br />
20.02.2006<br />
18.10.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4337 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>594 AIRBUS A330-203<br />
Air France A330 "Ulysse" cabin reconfiguration The approval of this STC is limited to Airbus<br />
12.10.2005<br />
MSN 422, 443, 448, 458, 465, in accordance with Change Approval Sheet A330-203 Serial Numbers 422, 443, 448, 458,<br />
MSN 498, 500, 502, 503, 516, No. CAS-A330-<strong>04</strong>-0<strong>01</strong> dated 16/09/2005 (or 465, 481, 498, 500, 502, 503, 516, 519. The<br />
later <strong>EASA</strong> approved revision)<br />
Limitations and conditions defined in the <strong>EASA</strong><br />
Datasheet are applicable.A copy of this STC<br />
and the CAS must be enclosed in<br />
10<strong>01</strong>4338 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>596 BOEING 747-400 Air France B747-400 Big Bins modification. 1. The approval of this modification is limited to<br />
This is a revision to the <strong>EASA</strong> STC Ref 20<strong>04</strong>- the Boeing B747-400 MSN 24969, 24990,<br />
4528, to extend the applicability to Boeing747- 25344, 25600, 256<strong>01</strong>, 25602, 32868, 32869,<br />
400 , F-GEXA, MSN 24154.The general 32871, 25238, 25302, 25559, 25628, 25630,<br />
description is included in the Air France Letter 24154, 24155.The limitations and conditions<br />
BL.NI 10 003/EB and in the AEO 47-25 defined in the <strong>EASA</strong> Datasheet are appli<br />
10<strong>01</strong>4361 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>627 FAA STC ST02348NY BOEING 767-300 Cabin Reconfiguration with an increased<br />
seating configuration for LOT Polish Airlines.<br />
10<strong>01</strong>4375 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>650 BOEING 747-200<br />
BOEING 747-300<br />
Suppression of climb inhibition above flight<br />
level 300 on TCAS computer in accordance<br />
with AEO 47-34-0714 Revision 1 dated<br />
17/10/2005<br />
10<strong>01</strong>4380 AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>658 BOEING 767 Emergency Escape Path Marking System 08.02.2006<br />
10<strong>01</strong>4451 AIR FRANCE <strong>EASA</strong>.A.S.025<strong>04</strong> BOEING 737-800<br />
KLM 737-800, -900 Recaro Seats Installation - Compatibility of this design change with other<br />
11.05.2006<br />
BOEING 737-900<br />
previously approved modifications must be<br />
determined by the installer.- The installation is<br />
limited to the B 737-800, -900 listed in the CP-<br />
B737-06-0<strong>01</strong> Rev2, March 28th 2006.- As<br />
indicated in the doc. CP-B73<br />
10<strong>01</strong>4454 AIR FRANCE <strong>EASA</strong>.A.S.02508 BOEING 767-300 Cabin Reconfiguration -- 26.06.2006<br />
10<strong>01</strong>4456 AIR FRANCE <strong>EASA</strong>.A.S.02510 AIRBUS A330-343 Cabin Reconfiguration with the Installation of<br />
new B/C Seating Configuration as per Air<br />
France Change Approval Sheet n° CAS A330-<br />
05-<strong>01</strong>2<br />
30.<strong>04</strong>.2007<br />
10<strong>01</strong>4570 AIR FRANCE <strong>EASA</strong>.A.S.02674 BOEING 767 B767 Cabin Reconfiguration from KLM to<br />
Aeroflot.<br />
20.07.2007<br />
10<strong>01</strong>46<strong>01</strong> AIR FRANCE <strong>EASA</strong>.A.S.02724 BOEING 767-300 Enhanced Surveillance Dual ATC Mode S<br />
Installation<br />
23.02.2007<br />
10<strong>01</strong>4719 AIR FRANCE <strong>EASA</strong>.A.S.02896 BOEING 757-200 Installation of ATC Mode S Elementary and Certification basis as FAA TCDS<br />
28.03.2007<br />
Enhanced Surveillance<br />
A2NMIncluding:TGL 13 Rev 1,<br />
<strong>01</strong>/06/2003<strong>EASA</strong> AMC-20.13, 02/12/2005JAA<br />
TGM 21/07, <strong>01</strong>/10/2003.<br />
10<strong>01</strong>4822 AIR FRANCE <strong>EASA</strong>.A.S.03034 BOEING 767-300 Installation of Elementary Surveillance Dual This STC is approved only for the product<br />
26.02.2007<br />
ATS Mode S.<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4865 AIR FRANCE <strong>EASA</strong>.A.S.03089 AIRBUS A340-300 A340 FINNAIR Cabin and IFE Upgrade Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5195 AIR FRANCE <strong>EASA</strong>.A.S.03581 REV 1 BOEING 777-200<br />
BOEING 777-300<br />
ADS-B Out Activation. None. 05.09.2008<br />
10<strong>01</strong>5245 AIR FRANCE <strong>EASA</strong>.A.S.03681 BOEING 747-400 ADS-B Out Installation and Activation as per 1. Prior to installation of this modification the<br />
10.12.2008<br />
Air France Service Bulletin B747-08-0<strong>04</strong>-34- installer must determine that the<br />
0<strong>01</strong> rev. 0 or later approved revisions. interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7148 AIR GRISCHA HELIKOPTER AG <strong>EASA</strong>.R.S.<strong>01</strong>251 REV. 1 FOCA STC 56-30-<strong>01</strong> AS 350 B3 Bubble Window RH Installation P/N<br />
1. When the bubble window is used for vertical Prior to installation of this modification the 21.03.2<strong>01</strong>1<br />
030603/350BW according FOCA Data reference, the followingapplies: If the pilot installer must determinethat the<br />
Sheet56-30-<strong>01</strong>.Installation of P/N<br />
cannot firmly hold the collective pitch lever interrelationship between this modification<br />
030603/350BW according to FOCA data sheet whenin the position intended for vertical and any otherpreviously installed<br />
56-30-<strong>01</strong>at issue 3.Revision 1: This is a change reference through the bubblewindow, an modification will introduce no adverse<br />
to <strong>EASA</strong>.R.S.<strong>01</strong>251 issued 23/03/2006 approved collective pitch lever exte<br />
effect uponthe airworthiness of the<br />
whichwas based on STC FOCA 56<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 52/<strong>462</strong><br />
19.10.2005<br />
24.<strong>04</strong>.2006<br />
23.11.2005<br />
18.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7167 AIR MACH S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>275 EUROCOPTER FRANCE AS 350 Kit Air Mach ELIRAI TV-99-Internal Rack/ This installation should not be incorporated in<br />
10.05.2006<br />
B2<br />
Installation of electronic equipment for radio any aircraft unless it is determined that the<br />
bridge<br />
interrelationship between this installation and<br />
any previously approved configuration will not<br />
introduce any adverse effefct upon the<br />
airworthiness of the aircraf<br />
10<strong>01</strong>7168 AIR MACH S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>276 EUROCOPTER FRANCE AS Kit Air Mach ELIRAI TV-99-Internal Rack/ This installation should not be incorporated in<br />
10.05.2006<br />
355F1<br />
Installation of electronic equipment for radio any aircraft unless it is determined that the<br />
EUROCOPTER FRANCE AS bridge<br />
interrelationship between this installation and<br />
355F2<br />
any previously approved configuration will not<br />
introduce any adverse effefct upon the<br />
airworthiness of the aircraf<br />
10<strong>01</strong>6871 AIR METHODS CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>247 FAA STC SR00032DE-D AGUSTA BELL 412<br />
Installation of Air Methods Corporation 1. Single and dual patient configurations are<br />
11.<strong>01</strong>.2007<br />
BELL 412<br />
Emergency Medical System interior that to be installed in strict accordance with Air<br />
provides 3 patient locations to be configured Methods Corporation Maintenance Manual<br />
one oftwo ways using an Intensive Care AMMS 050-<strong>01</strong>10 rev N/C dated 156 April 1993<br />
Transport Litter (ICTL) and Ferno stretchers. or later approved revision and FAA approved<br />
Rotorcraft Flight Manual Supplemen<br />
10029569 AIR METHODS CORPORATION REV. 1 FAA STC SR00705DE-D S-76A, S-76B, S-76C Installation of Articulated Patient Loading<br />
System (APLS).Note: The STC amendment<br />
adds an ALLFA litter as an option.<br />
10030372 AIR METHODS CORPORATION FAA STC SR00250DE-D MD900 Installation of an EMS Interior in a MD902<br />
Helicopter<br />
Required pre-modification Sikorsky cabin Prior to installation of this modification it 19.08.2<strong>01</strong>1<br />
medical interior GA dwg. no.09076B10E0<strong>01</strong>-1 must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
If damage or excess wear warrants structural<br />
repair or alteration to thefloor system, preapproval<br />
authorized by the holder of this STC<br />
isrequired in accordance with AMMS 050-<br />
<strong>01</strong>67, Rev. (-), dated June 13, 1996or later<br />
FAA accepted revision.The multi-purpo<br />
Prior to installation of this modification it 11.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031942 AIR METHODS CORPORATION FAA STC SR00702DE-D BELL 429 Installation of Supplemental Strobe Lights None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.09.2<strong>01</strong>0<br />
10032603 AIR METHODS CORPORATION FAA STC SR007<strong>01</strong>DE-D 429 Installation of a controllable Searchlight none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.11.2<strong>01</strong>0<br />
10032617 AIR METHODS CORPORATION FAA STC SR007<strong>04</strong>DE-D BELL 429 Installation of Emergency Medical Services<br />
Interior and Systems<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.11.2<strong>01</strong>0<br />
10032620 AIR METHODS CORPORATION FAA STC SR00710DE-D BELL 429 Installation of Scene and Patient Loading Lights None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.11.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 53/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032621 AIR METHODS CORPORATION FAA STC SR00698DE-D BELL 429 Installation of Patient Loading System None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.11.2<strong>01</strong>0<br />
10<strong>04</strong>0541 AIR METHODS CORPORATION FAA STC SR00523DE SA365N, SA365N1, AS365N2 Installation of Emergency Medical Interior None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.07.2<strong>01</strong>2<br />
10<strong>04</strong>0543 AIR METHODS CORPORATION FAA STC SR00525DE SA365N, SA365N1, AS365N2 Installation of two (2) aft jump seats None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.07.2<strong>01</strong>2<br />
10<strong>04</strong>0545 AIR METHODS CORPORATION FAA STC SR00524DE SA365N, SA365N1, AS365N2 Installation of Articulating Patient Loading<br />
System<br />
10<strong>01</strong>7134 AIR SERVICE CENTER S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>228 A119 ASC 119-<strong>01</strong>-00 “Helibasket Kit” /Installation of<br />
External Basket<br />
10<strong>01</strong>7154 AIR SERVICE CENTER S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>260 A119 ASC 119-02-00 External self moving mirror<br />
kit/installation of external mirror in accordance<br />
with "Certification Report" Edition 0 dated 5<br />
February 2007 Rev. 1 dated 19 March 2007.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.07.2<strong>01</strong>2<br />
Report Helibasket ASC 119-<strong>01</strong>-00 Part.3<br />
Chapter 4 RFM Supplement Ed.2 dated 21<br />
August 2006<br />
This installation should not be incorporated in<br />
any aircraft unless it is determined that the<br />
interrelationship between this installation and<br />
any previously approved configuration will not<br />
introduce any adverse effect upon the<br />
10034544 AIR SERVICE CENTER S.R.L. REV. 1 182 SERIES Installation of Vaccine Dispersal Kit.<br />
airworthiness of the aircraft<br />
None. None. 11.05.2<strong>01</strong>1<br />
10034547 AIR SERVICE CENTER S.R.L. REV. 1 AS 350 B3 Installation of Vaccine Dispersal Kit. None. None. 11.05.2<strong>01</strong>1<br />
10<strong>01</strong>4992 AIR SUPPORT INTERNATIONAL S.r.l. <strong>EASA</strong>.A.S.03288 PIPER PA-31T1 ASI BMA <strong>04</strong>/B/06 “Installation of Garmin GNS 1. Prior to installation of this modification the<br />
22.10.2008<br />
430 & GNS 530, Goodrich WX 500, Garmin installer must determine that the<br />
MX 20 and Accessories”<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product. The insta<br />
10<strong>01</strong>5293 AIR SUPPORT INTERNATIONAL S.r.l. <strong>EASA</strong>.A.S.03835 MOONEY M20K ASI BMA <strong>01</strong>/B/09 “ Installation of Garmin GNS<br />
430W for B-RNAV Operation”<br />
1) The approval holder shall fulfil the<br />
obligations of Part 21, Paragraph 21.A1092)<br />
10030246 AIR SUPPORT INTERNATIONAL S.r.l. PA -30<br />
Limited to S/N 25-0862<br />
ASI BMA <strong>01</strong>/B/10 "Installation of Garmin GNS None.<br />
430W approved for B-RNAV andother avionic<br />
equipment".<br />
None. 07.06.2<strong>01</strong>0<br />
10030248 AIR SUPPORT INTERNATIONAL S.r.l. PA-30 None. None. 07.06.2<strong>01</strong>0<br />
10<strong>01</strong>4142 AIRBERLIN TECHNIK GmbH <strong>EASA</strong>.A.S.<strong>01</strong>256 REV. 1 A330-322 Cabin reconfiguration from a 18 B/C + 331 Y/C none Prior to installation of this modification it 22.05.2<strong>01</strong>2<br />
layout to a 18 B/C + 343Y/C layout.This STC<br />
must be determined thatthe<br />
installs a new cabin arrangement.The Revision<br />
interrelationship between this modification<br />
1 retains the certificated design of the<br />
and any other previouslyinstalled<br />
<strong>EASA</strong>.A.S.<strong>01</strong>256 andcapture the transfer of<br />
modification and/ or repair will introduce<br />
STC ownership from LTU (owned by Air<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4924 AIRBERLIN TECHNIK GmbH <strong>EASA</strong>.A.S.03172 REV. 1 A330-322 Business Class extension to a 30 B/C + 295<br />
Y/C layout.This STC modifies cabin<br />
arrangementfrom a 18 B/C +343 Y/C layout to<br />
a 30B/C +295 Y/C layout with new B/C seat<br />
and stowage compartmentinstallations.The<br />
Revision 1 retains the certificated design of the<br />
E<br />
24.10.2006<br />
30.<strong>04</strong>.2007<br />
10.06.2009<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 54/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037159 AIRBERLIN TECHNIK GmbH A320-214 A320 Cabin Reconfiguration for AZAL - This design change (STC) is applicable to the This STC does not require a revision or 07.11.2<strong>01</strong>1<br />
following AirbusA320-214 serial number supplement to the original TCHolder's<br />
aircraft (MSNs):2685; 2846; 2853; 2865; 2991 EWIS Instructions for Continued<br />
and 3006.<br />
Airworthiness.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other p<br />
10039755 AIRBERLIN TECHNIK GmbH <strong>EASA</strong>.A.S.005<strong>04</strong> REV. 1 A330-322 Cabin reconfiguration from a 387 Y/C layout to None Prior to installation of this modification it 22.05.2<strong>01</strong>2<br />
a 18 B/C + 331 Y/Clayout.This STC installs a<br />
must be determined thatthe<br />
new cabin arrangement with in-seat video<br />
interrelationship between this modification<br />
andadditional galley installations.The Revision 1<br />
and any other previouslyinstalled<br />
retains the certificated design of the<br />
modification and/ or repair will introduce<br />
<strong>EASA</strong>.A.S.005<strong>04</strong> andcapture the tran<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1988 AIRBORNE MAINTENANCE AND FAA STC ST<strong>01</strong>096CH 767-200/ -300 Upgrade of Teledyne Digital Flight Data<br />
Acquisition Unit<br />
10<strong>04</strong>1989 AIRBORNE MAINTENANCE AND REV. 1 FAA STC ST02325CH 767-200/ -300 Installation of Electronic Standby Instrument<br />
System (ESIS)<br />
10033764 AIRBORNE TECHNOLOGIES GmbH REV. 1 P.68TC "OBSERVER" Change of cabin layout /For the installation of<br />
different mission equipment in a<br />
VulcanairP.68TC aircraft, the aircraft cabin has<br />
to be modified and provisions toaccommodate<br />
Mission Equipment have to be installed. This<br />
modificationincludes the removal of t<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.10.2<strong>01</strong>2<br />
Only to be installed on a/c with <strong>EASA</strong> STC<br />
10036223 installed.<br />
Prior to installation of this modification it 05.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Limited to S/N 454, 456 and 459 Prerequisites:Vulcanair Service Bulletin<br />
No. 163 must be installed prior or<br />
concurrentthis modificationVulcanair<br />
Mod.P68/129 must not installed prior or<br />
concurrent thismodificatonThe approval<br />
holder shall fulfill the obligations of Part<br />
21,Paragraph<br />
10033844 AIRBORNE TECHNOLOGIES GmbH REV. 2 T182T Camera Hatch Installation none The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair<br />
24.05.2<strong>01</strong>2<br />
10034631 AIRBORNE TECHNOLOGIES GmbH REV. 1 P2006T Provisions for surveillance configurationFor Step 1 and 3 can be installed without Prior to installation of this modification it 26.10.2<strong>01</strong>1<br />
standard analogue instruments equipped prerequisite, step 2 and step 4requires step 1 must be determined thatthe<br />
aircraft:Step 1: installation of a camera hatch, and step 3The installation of this STC must be interrelationship between this modification<br />
electric doors, and a 28Vmission power carried out while production of theaircraft at the and any other previouslyinstalled<br />
systemStep 2: installation of an electric camera facilities of the airplane manufacturer. modification and/ or repair will introduce<br />
lift For Garmin G950 equipped aircr<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036443 AIRBORNE TECHNOLOGIES GmbH P.68 "OBSERVER 2"<br />
P.68 "OBSERVER"<br />
P.68TC "OBSERVER"<br />
10038317 AIRBORNE TECHNOLOGIES GmbH P.68 "OBSERVER 2"<br />
P.68 "OBSERVER"<br />
P.68TC "OBSERVER"<br />
Mission cabin configuration /For the installation<br />
of different mission equipment in a Vulcanair<br />
P.68aircraft, the aircraft cabin has to be<br />
modified and provisions toaccommodate<br />
Mission Equipment have to be installed. The<br />
installation ofmission equipment it<br />
None Prerequisite:Vulcanair Service Bulletin<br />
No. 163 must be installed prior or<br />
concurrentthis modificationThe approval<br />
holder shall fulfill the obligations of Part<br />
21,Paragraph 21.A109. Prior to<br />
installation of this modification it must be<br />
determined tha<br />
Electric Camera Lift installation/Installation of Airborne Technologies STC-AT-036 must be<br />
an electric camera lift, an operator console and installed prior or concurrentwith this<br />
acamera lift control panel.<br />
modification<br />
<strong>04</strong>.<strong>01</strong>.2<strong>01</strong>2<br />
08.09.2<strong>01</strong>1<br />
The approval holder shall fulfill the 06.02.2<strong>01</strong>2<br />
obligations of Part 21,<br />
Paragraph21.A109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 55/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038324 AIRBORNE TECHNOLOGIES GmbH P2006T Hatch Cover. STC-AT-003 must be installed prior this The approval holder shall fulfill the 07.02.2<strong>01</strong>2<br />
modification.<br />
obligations of Part 21,<br />
Paragraph21.A109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10039513 AIRBORNE TECHNOLOGIES GmbH P2006T Police cabin configuration/Installation of a Airborne Technologies STC no. "STC-AT-003", Prior to installation of this modification it 08.05.2<strong>01</strong>2<br />
camera lift for 10" gimbals, operator console step 1 (analogueinstruments) or step 3 (Garmin must be determined thatthe<br />
andreplacement of hatch doors by fixed G950 version) of latest approved revisionmust interrelationship between this modification<br />
coversFor standard analogue instruments be installed prior this modification.<br />
and any other previouslyinstalled<br />
equipped aircraft step 1 of this STCis<br />
modification and/ or repair will introduce<br />
applicable, for Garmin G950 equipped aircraft<br />
no adverse effectupon the airworthiness<br />
s<br />
of the product.<br />
10<strong>04</strong><strong>01</strong>98 AIRBORNE TECHNOLOGIES GmbH P2006T Title: Provisions for radar operationDescription: STC-AT-003 step 1 or step 3 and EO-AT-<strong>04</strong>7<br />
Installation of a radome below the<br />
photogrammetric hatch,activation of the rear<br />
hatch (installed with EO-AT-<strong>04</strong>7), installation<br />
ofa ventral fin, upgraded mission power supply<br />
system and removal of hatchdoors<br />
must be installed prior thismodification.<br />
Prior to installation of this modification it 18.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0955 AIRBORNE TECHNOLOGIES GmbH P.68 C, P.68 C-TC Title: Mission cabin configuration P.68 C / Vulcanair SB-163 must be carried out prior this Prior to installation of this modification it 07.08.2<strong>01</strong>2<br />
Description: This STC consists of 3 steps: Step STC.<br />
must be determined thatthe<br />
1: To install different mission equipment in a<br />
interrelationship between this modification<br />
Vulcanair P.68aircraft, step 1 modifies the<br />
and any other previouslyinstalled<br />
aircraft cabin and installs provisions<br />
modification and/ or repair will introduce<br />
toaccommodate Mission Equipment. S<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>2009 AIRBORNE TECHNOLOGIES GmbH EC135 P2+ Title: Provisions for surveillance operations<br />
Description: Installation of provisions for<br />
surveillance operations,consisting of the<br />
following parts:Step 1 : Provisions for<br />
surveillance operationsStep 2 : Cabin<br />
provisionsStep 3 : Trim mass installation<br />
10<strong>01</strong>3925 AIRBUS S.A.S. <strong>EASA</strong>.A.S.0<strong>01</strong>96 REV. 1 AIRBUS A319-112 Cabin reconfiguration into an executive 44 pax, The Document Ref.: DIT/N/20<strong>04</strong>/1726/OS<br />
in accordance with the Modification Approval Revision B must be incorporated as a<br />
Sheet (MAS) Ref. SOG-00-830, issue 4, dated supplement to the Airplane Flight Manual<br />
September 20, 20<strong>04</strong><br />
(AFM)<br />
10<strong>01</strong>3936 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00347 REV. 1 AIRBUS A330-203 VIP Cabin Installation 1. The approval of this modification is limited<br />
to the Airbus A330-203 MSN 487 which is<br />
used as a private aircraft. The limitations and<br />
conditions defined in the <strong>EASA</strong> Datasheet are<br />
applicable. A copy of this STC and of the MDL,<br />
AFM must be enclosed in t<br />
10<strong>01</strong>3937 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00348 REV. 1 AIRBUS A330-203 Installation of a SATCOM Live TV system. 1. The approval of this modification is limited<br />
to the AIRBUS A330-203 MSN 487. The<br />
limitations and conditions defined in the <strong>EASA</strong><br />
Datasheet are applicable. A copy of this STC<br />
and of the MDL, AFM must be enclosed in the<br />
file of the modified aircraft. An<br />
10<strong>01</strong>3945 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00387 REV. 5 LBA STC TA<strong>04</strong>41 ISSUE 4 A300B4-6<strong>01</strong>, -603, -605R<br />
A300B4-620, -622, -622R<br />
<strong>EASA</strong> STC <strong>EASA</strong>.A.S.00387 revision 4 (ref. to<br />
former Luftfahrt BundesamtSTC TA<strong>04</strong>41 Issue<br />
4) The STC <strong>EASA</strong>.A.S.00387 has covered the<br />
transfer of the STC TA<strong>04</strong>41 Issue4 (original<br />
Aviation Authority reference) from the original<br />
AviationAuthority (LBA) to the <strong>EASA</strong><br />
10<strong>01</strong>3946 AIRBUS S.A.S. <strong>EASA</strong>.A.S.0<strong>04</strong>03 REV. 1 A310-3<strong>04</strong> - <strong>EASA</strong> STC <strong>EASA</strong>.A.S.0<strong>04</strong>03 revision 1(Ref.<br />
to former DGAC-F STC S1-72-<strong>01</strong>)- The STC<br />
<strong>EASA</strong>.A.S.0<strong>04</strong>03 has covered the transfer of<br />
the STC S1-72-<strong>01</strong>(Original Aviation Authority<br />
reference) from the original AviationAuthority<br />
(DGAC-F) to the <strong>EASA</strong> allowing the conve<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.10.2<strong>01</strong>2<br />
02.07.2008<br />
<strong>04</strong>.07.2008<br />
<strong>04</strong>.07.2008<br />
N/A Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
05.03.2<strong>01</strong>2<br />
N/A Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
26.02.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 56/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>3957 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00514 REV. 3 A310-3<strong>04</strong> - <strong>EASA</strong> STC <strong>EASA</strong>.A.S.00514 revision 3- The N/A - The STC <strong>EASA</strong>.A.S.0<strong>04</strong>03 is a pre- 19.02.2<strong>01</strong>0<br />
STC <strong>EASA</strong>.A.S.00514 allowed the installation<br />
requisite for the embodiment of theSTC<br />
of the Air to AirRefuelling kit provision, on the<br />
<strong>EASA</strong>.A.S.00514 (original and<br />
A310-3<strong>04</strong> aircraft model converted in aMulti<br />
subsequent issues) - Prior to installation<br />
Role Transport version, called ‘Polaris’<br />
of this modification it must be determined<br />
configuration.- Revision 1 introduc<br />
thatthe interrelationship between this<br />
modification and any other pr<br />
10<strong>01</strong>3960 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00634 REV. 6 A310-203/-221/-222<br />
A310-3<strong>04</strong>/-308/-324/-325<br />
<strong>EASA</strong> STC 10<strong>01</strong>3960 Revision 6 (A310-200<br />
series and -300 seriesaeroplanes, Passenger<br />
to Freighter conversion)(Ref. to former<br />
Luftfahrt Bundesamt STC TA0383 Issue 9)-<br />
The STC <strong>EASA</strong>.A.S.00634 has covered the<br />
transfer of the STC TA0383Issue 9 (original<br />
Aviation<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.06.2<strong>01</strong>2<br />
10<strong>01</strong>3966 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00685 REV. 1 AIRBUS A321-231 VIP cabin modification in accordance with<br />
Modification Approval Sheet (MAS) ref. SOG-<br />
792 issue 1, dated March 31st, 2005<br />
This STC is limited to A321-231 MSN 1202 <strong>04</strong>.06.2008<br />
10<strong>01</strong>3972 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00767 REV. 1 AIRBUS A320-214 LIVE TV Installation This STC is limited to A320-213 MSN 2165 <strong>04</strong>.07.2008<br />
10<strong>01</strong>3973 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00769 REV. 1 AIRBUS A320-214 Avionic Rack 9100 VU Installation This STC is limited to A320-214 MSN 2165 <strong>04</strong>.07.2008<br />
10<strong>01</strong>3974 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00772 REV. 1 AIRBUS A320-214 NAS VIP Cabin Modification This STC is limited to A320-214 MSN 2165 <strong>04</strong>.07.2008<br />
10<strong>01</strong>4023 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>078 REV. 1 AIRBUS A319-133 AL SALAM Master Modification This STC is limited to A319-133 CJ MSN 2421 02.07.2008<br />
10<strong>01</strong>4127 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>237 REV. 1 AIRBUS A321-231 Satcom in accordance with Morification<br />
Approval Sheet (MAS) ref. : SOG-00-794 issue<br />
3, dated March 18, 2005.<br />
This STC is limited to A321-231 MSN 1202 <strong>04</strong>.07.2008<br />
10<strong>01</strong>4140 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>253 REV. 1 AIRBUS A340-541 DA WLAT Qatar Airways Modifications in The applicability of this STC is limited to MSN<br />
<strong>04</strong>.07.2008<br />
accordance with Modification Approval Sheet 495No more than 10 Laptops equipped with<br />
Ref. SOG-<strong>01</strong>-0648<br />
WiFi system are allowed in the cabin<br />
10<strong>01</strong>4164 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>296 REV. 1 AIRBUS A340-541 DA WLAT Qatar Airways Live TV Modifications The applicability of this STC is limited to MSN<br />
in accordance with Modification Approval Sheet 495<br />
Ref. SOG-23-690<br />
10<strong>01</strong>4197 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>340 REV. 1 AIRBUS A330-200 Installation of a more powerful air heater (3kg<br />
W) inside the private cabin washroom<br />
10<strong>01</strong>4231 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>394 REV. 1 AIRBUS A340-212 VIP Cabin and systems upgrade in accordance<br />
with Sogerma Modification Approval Sheet<br />
(MAS) SOG-00-0977 issue 3 dated 03/02/06<br />
1.This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.2. The limitations and<br />
The approval of this modification is limited to<br />
the Airbus A340-212 MSN 061<br />
10<strong>01</strong>4233 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>396 REV. 1 AIRBUS A319-133 Avionics Rack 9100 VU installation 1. This STC is limited to A319-133 CJ MSN<br />
2421<br />
<strong>04</strong>.07.2008<br />
10<strong>01</strong>4234 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>397 REV. 1 AIRBUS A319-133 Live TV system provision This STC is limited to A319-133 CJ MSN 2421 <strong>04</strong>.07.2008<br />
10<strong>01</strong>4408 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>703 AIRBUS A300-600ST MODEL F4-<br />
608<br />
Installation of ISIS on A300-600STInstallation<br />
of two Integrated Stand-by Instrument System<br />
(ISIS) in replacement of the stand by speed,<br />
attitude and altitude.<br />
10<strong>01</strong>4419 AIRBUS S.A.S. <strong>EASA</strong>.A.S.<strong>01</strong>740 REV. 1 AIRBUS A320 SAT TV Tailwind 550 antenna installation in<br />
accordance with MAS SOG-53-1252 issue 2<br />
dated 27/07/06<br />
10<strong>01</strong>4686 AIRBUS S.A.S. <strong>EASA</strong>.A.S.02849 REV. 1 AIRBUS A319 Modification MOD SOG-53-1296 " A319-SAT<br />
TV Tailwind 550 Antenna Installation"<br />
10<strong>01</strong>4779 AIRBUS S.A.S. <strong>EASA</strong>.A.S.02977 REV. 1 LBA STC TA0<strong>01</strong>5 ISSUE 4 A300B2-1A/ -1C/ K-3C/ -203 - <strong>EASA</strong> STC <strong>EASA</strong>.A.S.02977 revision 1-<br />
A300B4-2C/ -103/ -203<br />
(Ref. to former Luftfahrt Bundesamt STC<br />
TA0<strong>01</strong>5 Issue 4)- The STC <strong>EASA</strong>.A.S.02977<br />
has covered the transfer of the STC<br />
TA0<strong>01</strong>5Issue 4 (original Aviation Authority<br />
reference) from the originalAviation Authority<br />
(LBA) to the<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in paragraph ‘Description’.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. The installation is compatible with the<br />
installation of a VH3 antenna between Fr 51<br />
and Fr 52, and a Canadian Marconi Aero-H+<br />
antenna betweeen Fr 58 and Fr 61 (separately<br />
or simultaneously).2. The installation requires<br />
both ACT 1 and 2 be installed on A<br />
<strong>04</strong>.07.2008<br />
<strong>04</strong>.07.2008<br />
<strong>04</strong>.07.2008<br />
26.10.2006<br />
30.06.2008<br />
30.06.2008<br />
N/A Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
26.02.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 57/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4911 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03155 AIRBUS A320-214 Airbus Corporate Jet Centre Modification<br />
CJ<strong>01</strong>03 –VIP Interior - Shining Star No. 2<br />
03.03.2008<br />
10<strong>01</strong>5025 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03332 AIRBUS A320-214 Airbus Corporate Jet Centre Modification Prior to installation of this modification the<br />
12.12.2008<br />
CJ<strong>01</strong>45 Issue 1 -VIP Interior - Shining Star No. installer must determine that the<br />
1<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5053 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03374 AIRBUS A319-115 Airbus Corporate Jet Centre Modification 1. Prior to installation of this modification the<br />
22.06.2009<br />
CJ0222 Issue 1VIP Interior - Residence installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>5198 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03589 AIRBUS A320-214 Airbus Corporate Jet Centre Modification<br />
CJ0356 Issue 1 –AFM Supplement - VIP<br />
Interior: Shining Star No. 2<br />
10<strong>01</strong>5210 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03625 DGAC STC 180-SF-0227 AIRBUS A320 SERIES Installation of a cabin VIP (Aeroservices) in<br />
accordance with the Service Bulletin SOG-WD-<br />
00-00-<strong>01</strong> (or later approved revision)<br />
10<strong>01</strong>5211 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03626 DGAC FRANCE 180-SF-<strong>01</strong>87 AIRBUS A320 SERIES Cabin Conversion of one A319 corporate jet<br />
(A319 CJ)<br />
10<strong>01</strong>5212 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03627 DGAC FRANCE STC 180-SF-0212 AIRBUS A320 SERIES Cabin Conversion of one A319 Corporate Jet<br />
(A319 CJ)<br />
10<strong>01</strong>5281 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03813 LBA STC NO.2830/0009 ISSUE 1 A300C4-203 - Ref. to former Luftfarhrt Bundesamt STC<br />
2830/0009 Issue 1- This <strong>EASA</strong> STC keeps the<br />
certificated design of the LBA STC<br />
2830/0009Issue 1, which consisted in the<br />
installation of structure and systemprovisions to<br />
change the loading system to an integrated si<br />
10<strong>01</strong>5282 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03814 LBA STC NO.TA<strong>04</strong>66 A300F4-605R - Ref. to former Luftfahrt Bundesamt STC<br />
TA<strong>04</strong>66- This <strong>EASA</strong> STC keeps the<br />
certificated design of the LBA STC<br />
TA<strong>04</strong>66,which consisted in theretrofit of the<br />
Lower Deck Cargo Compartment (LDCC) -<br />
Cargo LoadingSystem (CLS), andreflects the<br />
changes induced by the<br />
06.06.2008<br />
<strong>04</strong>.07.2008<br />
07.07.2008<br />
07.07.2008<br />
Limited to MSN 212 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.02.2<strong>01</strong>0<br />
Limited to the aircraft model operated by<br />
Federal Express (FedEX)<br />
Prior to installation of this modification it 26.02.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
10<strong>01</strong>5283 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03816 LBA STC NO. TA0217 AIRBUS A319-132 Equipment / Furnishing - Passenger<br />
Limited to MSN 913. Prior to installation of this modification it 12.05.2<strong>01</strong>0<br />
Compartment - VIP-Kit for A319Kharafi Group<br />
must be determined thatthe<br />
KuwaitRevision to Luftfahrt Bundesamt STC<br />
interrelationship between this modification<br />
TA0217 Issue 2.This <strong>EASA</strong> STC keeps the<br />
and any other previouslyinstalled<br />
certificated design of the LBA STC TA0217<br />
modification and/ or repair will introduce<br />
issue2, which consisted in the aircraft VIP cabin<br />
no adverse effectupon the airworthiness<br />
reco<br />
of the product.<br />
10<strong>01</strong>5284 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03817 LBA STC NO. TA0265 AIRBUS A319-133 Equipment / Furnishings - Passenger<br />
Compartment - Install cabinfurnishing for<br />
Daimler Chrysler AviationRevision to Luftfahrt<br />
Bundesamt STC TA0265This <strong>EASA</strong> STC<br />
keeps the certificated design of the LBA STC<br />
TA0231 whichconsisted in the aircraft cabin<br />
reconfig<br />
10<strong>01</strong>5285 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03818 LBA STC NO. TA0269 AIRBUS A319-133 Equipment / Furnishing - Passenger<br />
Compartment - Install baggagecontainer for<br />
Daimlerchrysler Aviation.Revision to Luftfahrt<br />
Bundesamt STC TA0269 Issue 2.This <strong>EASA</strong><br />
STC keeps the certificated design of the LBA<br />
STC TA0269 Issue2 which consisted in the<br />
instal<br />
10<strong>01</strong>5286 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03819 LBA STC NO. TA0231 AIRBUS A320-232 Equipment/ Furnishings - Passenger<br />
Compartment - VIP-kit for A320 Syria.Revision<br />
to Luftfahrt Bundesamt STC TA0231.This<br />
<strong>EASA</strong> STC keeps the certificated design of the<br />
LBA STC TA0231 whichconsisted in the<br />
aircraft cabin VIP reconfiguration, and reflects<br />
thec<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.05.2<strong>01</strong>0<br />
Limited to MSN 1053 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.05.2<strong>01</strong>0<br />
Limited to MSN 886, 918, 1032, and 1075 Private used only (non-commercial<br />
transportationPrior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse eff<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 58/<strong>462</strong><br />
12.05.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5287 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03820 LBA STC NO. TA0228 A330-223 (Ref. to former Luftfarhrt Bundesamt STC Limited to MSN 240, 249, 253, 255, 262, 275, Prior to installation of this modification it 31.08.2<strong>01</strong>0<br />
TA0228)This <strong>EASA</strong> STC keeps the certificated 288, 291, and 366<br />
must be determined thatthe<br />
design of the LBA STC TA0228<br />
interrelationship between this modification<br />
whichconsisted in the aircraft cabin<br />
and any other previouslyinstalled<br />
reconfiguration, and reflects thechanges<br />
modification and/ or repair will introduce<br />
induced by the transfer of LBA STC TA0228<br />
no adverse effectupon the airworthiness<br />
from DaimlerChryslerA<br />
of the product.<br />
10<strong>01</strong>5288 AIRBUS S.A.S. <strong>EASA</strong>.A.S.03821 LBA STC TA0261 AIRBUS A310-3<strong>04</strong> GLARE demonstrator panel<br />
installationRevision to Luftfahrt Bundesamt<br />
STC TA0261.This <strong>EASA</strong> STC keeps the<br />
certificated design of the LBA STC TA0261,<br />
whichconsisted in the installation of the Glare<br />
demonstrator panel fortesting purpose, and<br />
reflects the chang<br />
10028319 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03500 REV. 1 A319-115, MSN 3243 ACJ Centre Modification CJ0300 Issue 1 (VIP<br />
Cabin Interior - ALF) -ACJ Centre Modification<br />
CJ0392 Issue 1 (Private to Public Conversion)<br />
10028791 AIRBUS S.A.S. <strong>EASA</strong>.A.S.00351 REV. 2 A310-3<strong>04</strong> - <strong>EASA</strong> STC <strong>EASA</strong>.A.S.00351 revision 2(Ref.<br />
to former Luftfahrt Bundesamt STC TA<strong>01</strong>75<br />
Issue 3)- The STC <strong>EASA</strong>.A.S.00351 has<br />
covered the transfer of the STC TA <strong>01</strong>75issue<br />
3 (Original Aviation Authority reference) from<br />
the originalAviation Authority (LBA) to the<br />
10028999 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03735 REV. 1 A319-115 ACJ Centre Modification CJ<strong>04</strong>00 Issue 1 (VIP<br />
Cabin Interior - ACROPOLIS)<br />
1003<strong>01</strong>47 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03949 A320-200 Airbus Corporate Jet Centre Modification<br />
CJ0531 Issue 1 - VIP KIT - RAFOProject<br />
10031829 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03426 REV. 1 A310-3<strong>04</strong> Replacement of Cockpit Communication Unit<br />
(CCU) and Radio Control Unit(RCU) by<br />
Centralized Radio Control (CRC).This STC will<br />
modify the communication system by changing<br />
equipments,mating connectors, and wiring.<br />
10031840 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03950 A320-232 Airbus Corporate Jet Centre Modification<br />
CJ0540 Issue 1 -VIP Interior - "QATAR"<br />
10033449 AIRBUS S.A.S. A319-133 Airbus Corporate Jet Centre Modification<br />
CJ0615 Issue 1 - VIP Interior -"HNA"<br />
Limited to MSN 484. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.05.2<strong>01</strong>0<br />
This STC is limited to Airbus A319 MSN 3243 Operations under EU-OPS possible by<br />
application of ConversionInstruction<br />
(Aircraft in Public Configuration) Ref: CI<br />
00CJ002 Issue B Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
1- Transmissions (transmission operation) in<br />
tactical/close air supportband [frequency range<br />
30-89 MHz] are prohibited on the military<br />
radiosV/UHF Cockpit and V/UHF FOS during<br />
flight.2- Aircraft Flight Manual Supplement for<br />
Airbus A310-3<strong>04</strong>, TemporaryRevisi<br />
modification and any<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.12.2009<br />
19.02.2<strong>01</strong>0<br />
This STC is limited to Airbus A319 MSN 3826 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.02.2<strong>01</strong>0<br />
This STC is limited to Airbus A320-200 MSN<br />
3723 & MSN 4117<br />
The current STC needs specific aircraft<br />
configuration as a prerequisite:To install this<br />
STC on A310-3<strong>04</strong> aircraft models,<br />
embodiment of <strong>EASA</strong> STCref: 10<strong>01</strong>3946, Rev<br />
1 - previously referenced as <strong>EASA</strong> STC<br />
<strong>EASA</strong>.A.S.0<strong>04</strong>03-(or any further <strong>EASA</strong><br />
approved revision) i<br />
The VIP KIT shall be installed in<br />
accordance with the<br />
"ConversionInstruction" documentref. CI<br />
00CJ003 at the latest revision approved<br />
under DOA No.<strong>EASA</strong>.21J.031Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
betwee<br />
28.05.2<strong>01</strong>0<br />
Prior to installation of this modification it 09.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC is limited to A320-232 MSN 4170 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.09.2<strong>01</strong>0<br />
This STC is limited to A319-133 MSN 4<strong>04</strong>2 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
21.<strong>01</strong>.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 59/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034553 AIRBUS S.A.S. P-<strong>EASA</strong>.A.S.03845 A319-115 Airbus Corporate Jet Centre Modification This STC is limited to A319-115 MSN 3994 Operations under EU-OPS is possible by 12.<strong>04</strong>.2<strong>01</strong>1<br />
CJ0500 Issue 1 - VIP Interior -"ORION"<br />
application of ConversionInstruction<br />
(Aircraft in Public Configuration) Ref: CI<br />
00CJ0<strong>04</strong> RevisionC Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification an<br />
10036239 AIRBUS S.A.S. A320-200 Airbus Corporate Jet Centre Modification This STC is limited to A320-214 MSN 4795. Prior to installation of this modification it 24.08.2<strong>01</strong>1<br />
CJ1000 Issue 1 -VIP Interior - "RAFO 3".<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037<strong>01</strong>5 AIRBUS S.A.S. A319-133 Airbus Corporate Jet Centre Modification<br />
CJ0700 Issue 1 - VIP Interior -"OPTIMA<br />
PROJECT"<br />
10037612 AIRBUS S.A.S. A320-214 Airbus Corporate Jet Centre Modification<br />
CJ1118 Issue 1 - Cabin SystemUpgrade<br />
10037703 AIRBUS S.A.S. A319-115 Airbus Corporate Jet Centre Modification<br />
CJ0800 Issue 1 - Project "2A"<br />
10038826 AIRBUS S.A.S. A319-115 Airbus Corporate Jet Centre Modification<br />
CJ0950 Issue 1 -VIP Interior - "Metropole".<br />
10039051 AIRBUS S.A.S. A321-200 Airbus Corporate Jet Centre Modification<br />
CJ1094 Issue 1 -Installation of Business Class<br />
Seating Area - "Gulf Air (Type C)"<br />
10039666 AIRBUS S.A.S. A320-214 Airbus Corporate Jet Centre Modification<br />
CJ1100 Issue 1 -Installation of Business Class<br />
Seating Area - "Gulf Air - Type A"<br />
10<strong>04</strong>0777 AIRBUS S.A.S. A320-214 Airbus Corporate Jet Centre Modification<br />
CJ1108 Issue 1 -Installation of Business Class<br />
Seating Area - "Gulf Air - Type B"<br />
This STC is limited to A319-133 MSN 4319 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
25.10.2<strong>01</strong>1<br />
This STC is limited to A320-214 MSN 2165 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.12.2<strong>01</strong>1<br />
This STC is limited to A319-115 MSN 4470 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
16.12.2<strong>01</strong>1<br />
This STC is limited to A319-115 MSN 4024<br />
and MSN 4679.<br />
Prior to installation of this modification it 19.03.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.<strong>04</strong>.2<strong>01</strong>2<br />
This STC is limited to MSN 4827, MSN 4860,<br />
MSN 4865<br />
Prior to installation of this modification it 16.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC is limited to MSN 5171, MSN 5175 The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21A.109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
26.07.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 60/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4094 AIRBUS TRANSPORT INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>192 AIRBUS A300-600ST MODEL F4- STC ST46MOD0<strong>01</strong> Issue <strong>01</strong>: A300-600ST / This STC is approved only for A300F4-608ST. 12.<strong>04</strong>.2005<br />
SNC<br />
608<br />
Data Link System. This controller data link<br />
communication based on VDL mode 2 project<br />
is led by Eurocontrol. The crew will be able to<br />
exchange data and messages with a groundbased<br />
station airline operation centre and<br />
10<strong>01</strong>4202 AIRBUS TRANSPORT INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>352 AIRBUS A300-600ST MODEL F4- ST34MOD027 " Enhanced Surveillance on<br />
07.<strong>04</strong>.2006<br />
SNC<br />
608<br />
A300-600ST"<br />
10<strong>01</strong>4921 AIRBUS TRANSPORT INTERNATIONAL <strong>EASA</strong>.A.S.03168 AIRBUS A300-600ST MODEL F4- Implementation of Automatic Dependant Prior to installation of this modification the<br />
22.12.2008<br />
SNC<br />
608<br />
Surveillance – Broadcast in Non Radar installer must determine that the<br />
Airspace capability (ADS-B NRA) on A300- interrelationship between this modification and<br />
600ST.This STC provide surveillance services any other previously installed modification will<br />
in non-radar airspaces using ADS-B Out.ADS- introduce no adverse effect upon the<br />
B NRA is part of the Eurocontrol ‘Cascade’<br />
project.<br />
airworthiness of the product.<br />
10<strong>01</strong>5056 AIRBUS TRANSPORT INTERNATIONAL <strong>EASA</strong>.A.S.03378 AIRBUS A300-600ST MODEL F4- FMS SwitchingThe modification installs the 1. The MMEL Supplement associated with this<br />
12.03.2008<br />
SNC<br />
608<br />
coupling of each FMC to both FMS CDU and STC is only quoted for information. The STC<br />
EFIS displays, in order to comply with the B- approval <strong>EASA</strong>.A.S.03378 does not<br />
RNAV requirements in case of one FMC constituteits approval. The MMEL Supplement<br />
source failure. This modification allows approval will be granted separately.2. Prior to<br />
10027571 AIRBUS TRANSPORT INTERNATIONAL P-<strong>EASA</strong>.A.S.03848 AIRBUS A300F4-608ST<br />
dispatching the serviceable FMC signal on the installation of this modification the insta<br />
CDU<br />
Special Transports / Transports Speciaux. (This<br />
Prior to installation of this modification it 12.10.2009<br />
SNC<br />
STC, ref. ST25MOD020ed.<strong>01</strong> (Applicant<br />
must be determined thatthe<br />
reference), has been developed, reviewed,<br />
interrelationship between this modification<br />
tested andfound compliant with the Certification<br />
and any other previouslyinstalled<br />
Basis to deal with non-Airbussub-assemblies<br />
modification and/ or repair will introduce<br />
transport. On case by case basis, th<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028350 AIRBUS TRANSPORT INTERNATIONAL<br />
SNC<br />
10032203 AIRBUS TRANSPORT INTERNATIONAL<br />
SNC<br />
10037753 AIRBUS TRANSPORT INTERNATIONAL<br />
SNC<br />
10<strong>04</strong>0583 AIRBUS TRANSPORT INTERNATIONAL<br />
SNC<br />
A300F4-608ST Special Transports / Transports SpeciauxThis<br />
STC, ref. ST25MOD020 ed.<strong>01</strong> (Applicant<br />
reference), has beendeveloped, reviewed,<br />
tested and found compliant with the<br />
CertificationBasis to deal with non-Airbus subassemblies<br />
transport. On case by casebasis,<br />
this<br />
A300F4-608ST Special Transports / Transports SpeciauxThis<br />
STC, ref. ST25MOD020 ed.<strong>01</strong> (Applicant<br />
reference), has beendeveloped, reviewed,<br />
tested and found compliant with the<br />
CertificationBasis to deal with non-Airbus subassemblies<br />
transport. On case by casebasis,<br />
this<br />
A300F4-608ST Special Transports / Transports SpeciauxIssue<br />
1 of ATI STC ref. ST25MOD020 (Applicant<br />
reference),was developed, reviewed,<br />
tested and found compliant with the<br />
CertificationBasis to deal with non-Airbus subassemblies<br />
transport. On case by casebasis,<br />
A300F4-608ST Special Transport - Instrumented Airbus<br />
SectionsIssue 1 of ATI modification<br />
ST25MOD020 (applicant’s<br />
reference),was developed, reviewed,<br />
tested and found compliant with the<br />
Certification Basis to deal with non-Airbussubassemblies<br />
transport. On case<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.12.2009<br />
None This STC approved the transport<br />
configuration only. The dangerous<br />
goodsincluded within the payload have to<br />
be compliant with the IATA<br />
dangerousgoods requirements (or any<br />
relevant National Aviation<br />
Authorityregulation).Prior to installation of<br />
this modifica<br />
15.10.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
20.12.2<strong>01</strong>1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.07.2<strong>01</strong>2<br />
10<strong>04</strong>0859 AIRBUS TRANSPORT INTERNATIONAL<br />
A300F4-608ST Installation of an Iridium Satcom for voice and None None 31.07.2<strong>01</strong>2<br />
SNC<br />
ACARS on A300-600ST<br />
10<strong>01</strong>5032 AIRCAD AIRCRAFT CABIN DESIGN <strong>EASA</strong>.A.S.03344 EMBRAER EMB-120 EMB-120 VIP Cabin Modification is a major<br />
change designed by AIRCAD that converts half<br />
part of the airliner cabin to a VIP cabin with six<br />
VIP seats and two tables on pallets and a<br />
curtain dividing the airline and VIP areas. One<br />
of the three emergency exits<br />
None. 11.07.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 61/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0380 AIRCAD AIRCRAFT CABIN DESIGN F900EX Partial Cabin Entertainment and Galley Falcon 900EX S/N 054 Prior to installation of this modification it 28.06.2<strong>01</strong>2<br />
equipment upgrade<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0624 AIRCAD AIRCRAFT CABIN DESIGN REV. 1 F2000 Installation of a sliding door, main entryway<br />
door removableworkshelves, installation or<br />
replacement of galleys equipment and<br />
IFEequipment, RH and annex RH galleys<br />
shelves rearrangement.<br />
10038356 AIRCRAFT CABIN MAINTENANCE GmbH A318, A319, A320, A321 Installation of refurbished Passenger Seat Belt<br />
P/N EPA20511-2-<strong>01</strong>-33 on16g seats<br />
10039575 AIRCRAFT CABIN MAINTENANCE GmbH REV. 1 1. A330<br />
2. B737<br />
3. B767<br />
10<strong>04</strong>2194 AIRCRAFT CABIN MAINTENANCE GmbH SEE APPROVED MODEL LIST Installation of refurbished Passenger Seat Belt<br />
P/N EPA 6488-2-<strong>01</strong>-40 on16g seats<br />
10033896 AIRCRAFT DESIGN & CERTIFICATION<br />
Ltd<br />
10035295 AIRCRAFT DESIGN & CERTIFICATION<br />
Ltd<br />
100365<strong>01</strong> AIRCRAFT DESIGN & CERTIFICATION<br />
Ltd<br />
Falcon 2000 S/N 111. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.07.2<strong>01</strong>2<br />
As per Service Bulletin No. 62-146169 SEB 06<br />
00, latest revision.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation.Prior to<br />
installation of this modification it must be<br />
Installation of refurbished Passenger Seat Belt As per Service Bulletin No. 82-1000845 SEB<br />
determined thatthe interre<br />
The installation of this modification by 21.05.2<strong>01</strong>2<br />
P/N EPA20511-2-<strong>01</strong>-20 on16g seats 06 00, latest revision<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe interr<br />
As per Service Bulletin No. 1<strong>04</strong>-10<strong>01</strong>541 SEB The installation of this modification by 14.11.2<strong>01</strong>2<br />
06 00, latest revision<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation.Prior to<br />
installation of this modification it must be<br />
determined thatthe interre<br />
VENTUS CM Steerable Tail Wheel Ventus cM with Schempp-Hirth technical Note None.<br />
825-6.<br />
17.02.2<strong>01</strong>1<br />
REV. 1 L-13 "BLANÍK" Modification and inspection program for According to the applicable AFM Supplement. Prior to installation of this modification it 28.02.2<strong>01</strong>2<br />
compliance with <strong>EASA</strong>AD-2<strong>01</strong>0-<strong>01</strong>85-E.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
EA 300, EA 300/S<br />
EA 300/L, EA 300/LC<br />
Multi glider towing capacity up to 1000kg total<br />
tow mass<br />
10<strong>01</strong>6510 AIRCRAFT ENGINEERING & <strong>EASA</strong>.IM.A.S.02877 FAA STC ST02974AT BOEING 767 Installation of the KANNAD 406 ATP<br />
Emergency Locator Transmitter<br />
10<strong>01</strong>4852 AIRCRAFT INDUSTRIES, A.S. <strong>EASA</strong>.A.S.03076 CAA CZ STC--<strong>01</strong>0 LETECKE ZAVODY L 410 UVP-<br />
E20<br />
Completion recorded parameters FDR BUR 1-<br />
2G for compliance with Brazilian regulation<br />
RBHA 135.152.<br />
10<strong>01</strong>4896 AIRCRAFT INDUSTRIES, A.S. <strong>EASA</strong>.A.S.03126 Implementation of VFR-NIGHT kind of<br />
operation - installation of additionalm<br />
equipment ensuring the extension of currently<br />
approved kinds of operation to VFR-NIGHT<br />
kind of operation.<br />
08.02.2<strong>01</strong>2<br />
Aircraft conforming to <strong>EASA</strong> TCDS.A.362 and Prior to installation of this modification it 14.09.2<strong>01</strong>1<br />
being equipped accordingUA-300-4-95 Air-tow- must be determined thatthe<br />
release.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
03.06.2008<br />
22.03.2007<br />
Applicable for s/n 23-08 only. 23.07.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 62/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027121 AIRCRAFT PERFORMANCE<br />
P-<br />
REV. 1 FAA STC SA<strong>01</strong>935LA 4<strong>01</strong>, 4<strong>01</strong>A, 4<strong>01</strong>B, 402, 402A, Installation of external aft body strakes None 1) Prior to installation of this modification 22.02.2<strong>01</strong>0<br />
MODIFICATIONS,<br />
<strong>EASA</strong>.IM.A.S.03144<br />
402B, 402C, 411, 411A, 414,<br />
the installer mustdetermine that the<br />
414A, 421, 421A, 421B, 421C,<br />
interrelationship between this modification<br />
425, 441<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2) The insta<br />
10<strong>01</strong>5803 AIRCRAFT SAFETY EQUIPMENT <strong>EASA</strong>.IM.A.S.<strong>01</strong>868 SA3278SO BOEING DC-10<br />
BOEING MD 11 SERIES<br />
10<strong>04</strong>0586 AIRCRAFT STRUCTURES<br />
INTERNATIONAL<br />
10<strong>04</strong>1470 AIRCRAFT STRUCTURES<br />
INTERNATIONAL<br />
10<strong>01</strong>5313 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>5341 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>5342 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>5350 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>5772 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>5950 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>5964 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
10<strong>01</strong>6137 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
Smoke Barrier Cargo Copmartment McDonnell- 1. The Aircraft Flight Manual should be<br />
Douglas (Boeing) MD-11F, aircraft serial no. amended in order to make sure that before<br />
48445.Installation of a modified berrier in the each flight:(a) the integrity of the smoke barrier<br />
Class "E" cargo compartment in accordance is checked:(1) the smoke barrier should be<br />
with FAA STC SA3278SO, reissued on without any tears(2) the OEM crown area<br />
September 24, 20<strong>04</strong><br />
smoke barrier should be without any tear<br />
FAA STC SA10840SC CESSNA 208, CESSNA 208B Installation of Jack Pads on Cessna 208 Series None Prior to installation of this modification it 11.07.2<strong>01</strong>2<br />
aircraft in accordancewith FAA STC<br />
must be determined thatthe<br />
SA10840SC<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC NO. SA<strong>01</strong>1054SC 208, 208B Installation of an internal Cargo Pod lighting<br />
system.<br />
<strong>EASA</strong>.IM.A.S.0<strong>01</strong>66 FAA STC ST09887 SC BOEING 727 Installation of RVSM compliant equipment<br />
(dual DADS).FAA STC N° ST09887 SC<br />
<strong>EASA</strong>.IM.A.S.0<strong>04</strong>15 FAA STC ST09988SC DC-9-81 (MD-81)<br />
DC-9-81 (MD-82)<br />
DC-9-81 (MD-83)<br />
DC-9-81 (MD-87)<br />
<strong>EASA</strong>.IM.A.S.0<strong>04</strong>16 ST09989SC DC-9-81 (MD-81)<br />
DC-9-81 (MD-82)<br />
DC-9-81 (MD-83)<br />
DC-9-81 (MD-87)<br />
<strong>EASA</strong>.IM.A.S.00522 FAA STC ST09586SC REV 1 DC-9-81 (MD-81)<br />
DC-9-81 (MD-82)<br />
DC-9-81 (MD-83)<br />
DC-9-81 (MD-87)<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>811 FAA STC ST09580SC BOEING 767-200<br />
BOEING 767-300<br />
<strong>EASA</strong>.IM.A.S.02092 ST10084SC BOEING 737-100<br />
BOEING 737-200<br />
BOEING 737-300<br />
Installation of Universal Avionics Terrain<br />
Awareness & Warning System.<br />
Installation of Universal Avionics Multi Function<br />
Display Model 640.<br />
If the holder agrees to permit another person to<br />
use this certificate toalter the product, the<br />
holder shall give the other person<br />
writtenevidence of that permission.<br />
1. This STC is approved only for the<br />
installation of an RVSM compliant Air Data<br />
System and does not constitute an approval of<br />
RVSM operation.2. This STC is approved<br />
only for the product configuration as defined in<br />
the approved design data referred to<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of Universal UNS Flight<br />
1. This STC is approved only for the product<br />
Management System with UL-6<strong>01</strong> Unilink Data configuration as defined in the approved design<br />
Link System<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of Digital Flight Data Recorder<br />
(RFDR) Expanded ParameterUpgrade for<br />
Teledyne ARINC 717 DFDAU.<br />
Installation of an Innovative Solutions &<br />
Support (IS&S) digital air data system<br />
consisting of an electric altimeter, Digital Air<br />
Data Computer (DADC), Air Data Display Unit<br />
(ADDU), and an altitude alerter in accordance<br />
with ASM Master Data List 5572-00<strong>01</strong>-<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
<strong>EASA</strong>.IM.A.S.02113 ST09744SC BAE 146/AVRO 146 SERIES Installation of a Digital Flight Data Recorder<br />
(DFDR) Expanded Parameter Sensor Upgrade<br />
on a British Aerospace Avro 146-RJ85A<br />
Aircraft<br />
None 19.07.2006<br />
<strong>EASA</strong>.IM.A.S.02333 FAA STC NO. ST10606SC BOEING 767-200<br />
Installation of Mode S Upgrade, Elementary<br />
07.03.2008<br />
BOEING 767-300<br />
BOEING 767-400<br />
and Enhanced Surveillance Parameters<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 63/<strong>462</strong><br />
14.11.2006<br />
19.09.2<strong>01</strong>2<br />
07.10.20<strong>04</strong><br />
14.12.20<strong>04</strong><br />
14.12.20<strong>04</strong><br />
19.<strong>01</strong>.2005<br />
20.03.2006<br />
15.03.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6276 AIRCRAFT SYSTEMS AND<br />
<strong>EASA</strong>.IM.A.S.02565 FAA STC ST10268SC DC-9-80 (MD-80) SERIES FAA STC ST10268SC "installation of Universal 1. TGL 12 complied with.2. Prior to<br />
10.10.2007<br />
MANUFACTURING,<br />
Avionics Terrain Awareness Warning Ststem installation of this modification the installer must<br />
(TAWS)".<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworth<br />
10031221 AIRCRAFT SYSTEMS AND<br />
MANUFACTURING,<br />
FAA STC ST09<strong>04</strong>0SC B737-300, -400, -500 Installation of Digital Flight Data Recorder<br />
System (DFDR) using aTeledyne Digital Flight<br />
Data Acquisition Unit (DFDAU)<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
03.08.2<strong>01</strong>0<br />
10<strong>01</strong>6366 AIRCRAFT TECHNICAL DEVELOPMENT <strong>EASA</strong>.IM.A.S.02688 FAA STC ST02122LA AIRBUS A320 SERIES Installation of Aerocon Engineering Company<br />
14.03.2008<br />
Inc.<br />
(AEC) On-Board Airstair<br />
10<strong>01</strong>6409 AIRCRAFT TECHNICAL DEVELOPMENT <strong>EASA</strong>.IM.A.S.02741 REV. 3 FAA STC ST02112LA A318-111, -112, -121, -122 Installation of Cabin Interior Noise Reduction None. Prior to installation of this modification the 31.03.2<strong>01</strong>0<br />
Inc.<br />
A319-111, -112, -113, -114 Kit/Installation of new Thermal Insulation<br />
installer must determinethat the<br />
A319-115, -131, -132, -133 blankets in the cabinRevision of the <strong>EASA</strong> STC<br />
interrelationship between this modification<br />
<strong>EASA</strong>.IM.A.S.02741 to include A318-111/112/-<br />
and any otherpreviously installed<br />
121/-122 Models<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
10<strong>01</strong>6636 AIRCRAFT TECHNICAL DEVELOPMENT <strong>EASA</strong>.IM.A.S.03076 FAA STC ST<strong>01</strong>635 LA BOEING 737-700<br />
- Installation of Cabin Interior Noise 1. Prior to installation of this modification the<br />
20.<strong>01</strong>.2009<br />
Inc.<br />
BOEING 737-800<br />
Reduction Kit.- Validation of FAA<br />
installer must determine that the<br />
ST<strong>01</strong>635LA.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6645 AIRCRAFT TECHNICAL DEVELOPMENT <strong>EASA</strong>.IM.A.S.03088 FAA STC ST<strong>01</strong>568LA BOEING 737-700 - Installation of Cabin Interior Noise 1. Prior to installation of this modification the<br />
20.<strong>01</strong>.2009<br />
Inc.<br />
Reduction Kit.- Validation of FAA<br />
installer must determine that the<br />
ST<strong>01</strong>568LA.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10032264 AIRCRAFT TECHNICAL DEVELOPMENT<br />
FAA STC ST02317LA A330-200 Installation of Cabin Interior Noise Reduction Not applicable Prior to installation of this modification it 21.10.2<strong>01</strong>0<br />
Inc.<br />
Kit<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034009 AIRCRAFT TECHNICAL DEVELOPMENT<br />
Inc.<br />
10038108 AIRCRAFT TECHNICAL DEVELOPMENT<br />
Inc.<br />
10039327 AIRCRAFT TECHNICAL DEVELOPMENT<br />
Inc.<br />
FAA STC ST02112LA A320 Installation of Cabin Interior Noise Reduction<br />
Kit/Installation of new Thermal Insulation<br />
blankets in the cabin.<br />
FAA STC ST02382LA CL-600-2C10 Cabin Interior Noise Reduction Systems<br />
installation Kit in BombardierCL-600-2C10<br />
(Regional Jet Series 700, 7<strong>01</strong> & 702) Series<br />
Aircraft<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
25.02.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>01</strong>.2<strong>01</strong>2<br />
REV. 1 FAA STC ST02361LA A340-311/-312/-313 Installation of On-Board Airstair Interaction of this STC with cabin arrangement Prior to installation of this modification it 24.07.2<strong>01</strong>2<br />
features has not beenevaluated.Should this must be determined thatthe<br />
STC be part of a cabin arrangement, the interrelationship between this modification<br />
interactions betweenthis STC and any cabin or and any other previouslyinstalled<br />
seating arrangements must be evaluated modification and/ or repair will introduce<br />
forcompliance with applicable certificati no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 64/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6159 AIRCRAFT TECHNICAL SERVICE, Inc. <strong>EASA</strong>.IM.A.S.02381 FAA STC SA02123LA BEECH 200 Installation of a nose mounting truss, bulkhead, This approval is limited to Aircraft Serial<br />
28.<strong>04</strong>.2008<br />
camera, electronic backplane and missile Number BB-777 Only.This STC cannot be<br />
seeker head.<br />
removed from the subject aircraft (BB-777)<br />
without an <strong>EASA</strong> approved modification that reestablishes<br />
it’s conformity to the Type design<br />
standard detailed in <strong>EASA</strong> TCDS ref IM.<br />
10<strong>01</strong>6800 AIRFILM CAMERA SYSTEMS, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>158 FAA STC SR<strong>01</strong>784LA EUROCOPTER FRANCE AS 350<br />
SERIE<br />
EUROCOPTER FRANCE AS 355<br />
SERIE<br />
10<strong>01</strong>68<strong>01</strong> AIRFILM CAMERA SYSTEMS, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>160 FAA STC SR<strong>01</strong>785LA EUROCOPTER FRANCE AS 350<br />
SERIE<br />
EUROCOPTER FRANCE AS 355<br />
SERIE<br />
10<strong>01</strong>6802 AIRFILM CAMERA SYSTEMS, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>162 SR<strong>01</strong>654LA BELL 206<br />
BELL 407<br />
Installation of Down Post Utility Bracket AFDP-<br />
1 that attaches to the aircraft for attachment of<br />
a payload device<br />
Installation of Single Pole Utility Bracket AFSP-<br />
1 that attaches to the aircraft for attachment of<br />
a payload device.<br />
Installation of Model G1 Utility Bracket that<br />
attaches to the aircraft for attachment of a<br />
payload device.<br />
10<strong>01</strong>6857 AIRFILM CAMERA SYSTEMS, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>233 FAA STC SR<strong>01</strong>058LA EUROCOPTER FRANCE AS 350<br />
SERIE<br />
EUROCOPTER FRANCE AS 355<br />
SERIE<br />
10<strong>01</strong>7057 AIRFILM CAMERA SYSTEMS, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>489 FAA STC SR02137LA EUROCOPTER DEUTSCHLAND Side step bracket with Payload Capability, in<br />
MBB-BK<br />
accordance with FAA STC SR02137LA.<br />
10<strong>01</strong>7058 AIRFILM CAMERA SYSTEMS, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>490 FAA STCSR02138LA EUROCOPTER EC 135 Side step bracket with Payload Capability, in<br />
accordance with FAA STC SR02138LA.<br />
10033617 AIRFILM CAMERA SYSTEMS, LLC FAA STC SR02297LA 1. BELL 212, 412 AND 412EP<br />
2. AB412 AND AB412EP<br />
This STC approves the installation of the Down<br />
Post Utility Bracket AFDP-1 and physical<br />
installation of payloads that meet the RFM<br />
restrictions. Any electrical installations must<br />
receive further <strong>EASA</strong> approval.<br />
This STC approves the installation of the Single<br />
Pole Utility Bracket AFSP-1 and physical<br />
installation of payloads that meet the RFM<br />
restrictions. Any electrical installations must<br />
receive further <strong>EASA</strong> approval.<br />
This STC approves the installation of the Model<br />
G1 Utility Bracket and physical installation of<br />
payloads that meet the RFM restrictions. Any<br />
electrical installations must receive further<br />
<strong>EASA</strong> approval.<br />
13.07.2006<br />
13.07.2006<br />
13.07.2006<br />
Utility Mount 18.<strong>04</strong>.2007<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10.11.2008<br />
10.11.2008<br />
Nose Mount Utility Bracket None This approval is for the installation of the 31.<strong>01</strong>.2<strong>01</strong>1<br />
AirFilm mount only.Additional approval is<br />
required prior to installing additional<br />
equipmentto this mount.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this mo<br />
10039428 AIRFILM CAMERA SYSTEMS, LLC FAA STC SR02377LA 429 Airfilm Nose Utility Mount None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2<strong>01</strong>2<br />
10039429 AIRFILM CAMERA SYSTEMS, LLC FAA STC SR02376LA 429 Airfilm Tail Utility Mount None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 65/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5632 AIRGLAS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>586 FAA STC SA02244AK CESSNA 180<br />
Fabrication and Installation of Airglas Inc Model 1. This STC is only applicable to aircraft fitted<br />
28.07.2006<br />
CESSNA 180A<br />
CESSNA 180B<br />
CESSNA 180C<br />
CESSNA 180D<br />
CESSNA 180E<br />
CESSNA 180F<br />
CESSNA 180G<br />
CESSNA 180H<br />
CESSNA 180J<br />
CESSNA 180K<br />
CESSNA 185<br />
CESSNA 185A<br />
CESSNA 185B<br />
CESSNA 185C<br />
CESSNA 185D<br />
CESSNA 185E<br />
CESSNA A185E<br />
CESSNA A185F<br />
LH4000 hydraulically retractable wheel skis. with a Tyre size of 8.50-6, Type III.<br />
10<strong>01</strong>6958 AIRGLAS, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>355 FAA STC SH709AL EUROCOPTER FRANCE AS 350 Installation of Airglas, Inc. P/N L2700-AS350 1. Installation of Airglas, Inc. P/N L2700-AS350<br />
21.09.2007<br />
B<br />
skis on Eurocopter AS350 series<br />
ski kit is approved on AS350B, AS350B1,<br />
EUROCOPTER FRANCE AS 350 helicopters.This STC is a validation of FAA AS350B2, AS350B3, AS350BA, and AS350D<br />
B1<br />
STC SH709AL issued on January 29, 1981 helicopters which are equipped with<br />
EUROCOPTER FRANCE AS 350 and last amended on November 13, 2000 Eurocopter standard or high skid landing<br />
B2<br />
gear.2. Installation and operation of the kit on<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
AS3<br />
10<strong>01</strong>5169 AIRLEC AIR ESPACE <strong>EASA</strong>.A.S.03539 SA226-TB Stretcher Installation: New stretchers<br />
installation put in the aircraft with storage place<br />
and O2 botle space.<br />
06.02.2009<br />
10<strong>01</strong>7102 AIRLIFT A/S <strong>EASA</strong>.R.S.<strong>01</strong>072 REV. 1 AS 365 N2,AS 365 N3<br />
EMS-Installation/Installation of Medical none The approval holder shall fulfill the 23.08.2<strong>01</strong>2<br />
SA 365 C,SA 365 C1,SA 365 C2 Equipment and associatedattachment and<br />
obligations of Part 21, Paragraph<br />
SA 365 C3,SA 365 N,SA 365 N1 supports.Note: this STC is issued for the<br />
21A.118A.Prior to installation of this<br />
purpose of transferring STC<br />
modification it must be determined<br />
No.<strong>EASA</strong>.R.S.<strong>01</strong>072 of Lufttransport AS to<br />
thatthe interrelationship between this<br />
the above identified newholder.<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
rep<br />
10<strong>01</strong>7289 AIRLIFT A/S <strong>EASA</strong>.R.S.<strong>01</strong>539 EUROCOPTER FRANCE AS EMS kit installation 1) Prior to installation of this modification the<br />
27.05.2009<br />
365N3<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2) The ins<br />
10028603 AIRLIFT A/S AS365, EC 155 Installation of Latitude Skynode Satcom and<br />
Tracking System<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.<strong>01</strong>.2<strong>01</strong>0<br />
10029680 AIRLIFT A/S AS365N SERIES EMS Cabin Layout Kit DO-365-25-105 None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>0<br />
10030710 AIRLIFT A/S P-<strong>EASA</strong>.R.S.<strong>01</strong>574 EC 225, AS 332, SA 330 SERIES Installation of Latitude SkyNode Satcom and<br />
Tracking System<br />
The SkyNode Satcom and Tracking System Prior to installation of this modification the 08.07.2009<br />
installed on the helicopter hasto be operated in installer must determinethat the<br />
accordance with the Flight manual<br />
,,interrelationship between this<br />
SupplementFMS-332-23-106 Revision 1. modification and any otherpreviously<br />
installed ,,modification will introduce no<br />
adverse effectupon the airworthiness of<br />
the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 66/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032471 AIRLIFT A/S AS 350 B, AS 350 BA, AS 350 B1 Installation of Geophysical Equipments in A cargo mirror allowing in-flight observation of Prior to installation of this modification it 11.11.2<strong>01</strong>0<br />
AS 350 B2, AS 350 B3<br />
accordance with MasterDocument List DO-350- the spectrometer and EM/ magnetometer must be determined thatthe<br />
25-107, revision 0, dated 09.11.2<strong>01</strong>0 sensors must be installed<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10035077 AIRLIFT A/S REV. 1 AS365N3 Installation of NVIS Lighting System in<br />
accordance with Airlift MOD.DO-365-33-1<strong>04</strong>.<br />
Note: Revision 1 introduces new helicopter<br />
configurations.<br />
10035080 AIRLIFT A/S P-<strong>EASA</strong>.R.S.<strong>01</strong>514 AS 365N2 Installation of NVIS Lighting System in<br />
accordance with Airlift MOD.DO-365-33-1<strong>01</strong>.<br />
10036162 AIRLIFT A/S AS350B1<br />
AS350B2<br />
AS350B3<br />
EC130B4<br />
10<strong>04</strong>1311 AIRLIFT A/S MBB-BK 117 C-2 NVIS certification in order to enable Night<br />
Vision Goggles operation.<br />
10031253 AIRMOTIVE ENGINEERING<br />
CORPORATION<br />
REV. 1 FAA STC SE1<strong>01</strong>29SC SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10<strong>01</strong>4<strong>01</strong>1 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.<strong>01</strong>054 PIPER PA-23-250 Installation of1. COM/VOR/ILS/GPS-System<br />
Garmin GNS 4302. ELT Kannad 406AF<br />
10<strong>01</strong>4427 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.02472 CESSNA 208 Installation of a FLIR System, Inc. Ultramedia<br />
III/HD television camera. New Pilot Operating<br />
Handbook Supplement PO-0023-250000.<br />
Refer to applicable Flight Manual Supplement The installation of this modification by<br />
(FMS) for list of equipmentmandatory for Night third persons is subject towritten<br />
Vision Imaging System (NVIS) certification. permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Installation of<br />
NVIS/NVG compatible lighting does not<br />
include or implyapproval<br />
Refer to applicable Flight Manual Supplement<br />
(FMS) for list of equipmentmandatory for Night<br />
Vision Imaging System (NVIS) certification.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Installation of<br />
NVIS/NVG compatible lighting does not<br />
20.<strong>04</strong>.2<strong>01</strong>2<br />
24.05.2<strong>01</strong>1<br />
Installation of Bendix/King KRA 405B Radar AS350B3 - only aircraft with Arriel 2B and<br />
include or implyapproval<br />
The approval holder shall fulfil the 17.08.2<strong>01</strong>1<br />
Altimeter.<br />
Arriel 2B1 engines installed.<br />
obligations of Part 21,<br />
Paragraph21A.118A. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
Refer to applicable Flight Manual Supplement - The installation of this modification by<br />
(FMS) for list of equipmentmandatory for Night third persons is subject towritten<br />
12.09.2<strong>01</strong>2<br />
Vision Imaging System (NVIS) certification. permission of the approval holder and<br />
This Major Change is applicable only to holding and disposal ofthe approved<br />
helicopters deliveredNVIS-friendly from appropriate documentation. - Installation<br />
Eurocopter Deutschland GmbH, as defined of NVIS/NVG compatible lighting does<br />
not include or implyappro<br />
Installation of rotocoil, valve springs, ni-resist none Prior to installation of this modification it <strong>04</strong>.11.2<strong>01</strong>0<br />
valve guide, exhaustvalve with chrome flash on<br />
must be determined thatthe<br />
stem, and rocker shaft with thrust buttons<br />
interrelationship between this modification<br />
inaccordance with ECi Drawing Number<br />
and any other previouslyinstalled<br />
AEC65314, Rev E, dated February 6,2003, or<br />
modification and/ or repair will introduce<br />
later FAA approved revision - <strong>EASA</strong><br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
VFR; no AP, Max speed (camera operationg)<br />
115 KIAS, 2 pilots and max 4 passengers (see<br />
POH Supplement for full Limitations text).<br />
10<strong>01</strong>4848 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03070 BEECH B200 SUPER KING AIR TDR-94D-007 Mode S Transponder Dual<br />
Installation.<br />
10<strong>01</strong>4849 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03071 CESSNA T303 Installation of GNS480 COM/NAV/GPS,<br />
TAWS8000, Sky 497 Skywatch, KCS55A<br />
Compass System, SL30 COM/NAV,<br />
KN63DME, GWX68 Radar, MX200 MFD and<br />
GMA 347 Audio System. This installation<br />
includes also one Digiflow and Engine<br />
monitoring system.<br />
10<strong>01</strong>4851 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03073 REV. 1 TWIN COMMANDER AIRCRAFT Installation of Garmin GTX 330 Mode S<br />
690<br />
Transponder<br />
10<strong>01</strong>4952 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03216 CESSNA S550 (CITATION II) Installation of Bendix/King KLN 900, Shadin Prior to installation of this modification the<br />
ADC-200 and Garmin GNS 530A.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5062 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03388 COMMANDER AIRCRAFT 690A GPS Antenna Installation. 25.03.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 67/<strong>462</strong><br />
26.07.2006<br />
06.02.2006<br />
05.07.2007<br />
17.09.2007<br />
05.03.2008<br />
19.09.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5096 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03433 BEECH B200 Installation of SKY899 Transmitter Receiver<br />
Computer and Directional Antenna NY164<br />
Installation.<br />
14.02.2008<br />
10<strong>01</strong>5219 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03634 PIPER PA-42 Installation of the Garmin GNS530, Junction Prior to installation of this modification the<br />
<strong>04</strong>.05.2009<br />
Boxes, GMA 340, EX-500 and GTX330D in installer must determine that the<br />
Piper PA-42 Series.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>5240 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong>.A.S.03667 KING AIR 200 Installation of Dual Garmin COMM/NAV/GPS<br />
GNS430AW or GNS430Wand/or<br />
Avidyne EX500 MFD interfaced with existing<br />
WX Radarand/or L3-Com A100S<br />
1. Restricted to aircraft which have already<br />
approved antenna locations for thenew<br />
equipment.GNS430(A)W installations<br />
restricted to aircraft which have already the<br />
Cockpit Voice Recorderand/or Single followingequipment installed, completely<br />
Counter Pointer Drum Altimeter<br />
independend from the Garmin GNS430(A)W<br />
units:VHF tr<br />
10028933 AIRPLUS MAINTENANCE GmbH P-<strong>EASA</strong>.A.S.03609 PA-46-310P Installation of Garmin GNS530W, GNS430W None Prior to installation of this modification the 19.02.2<strong>01</strong>0<br />
and GMA347.<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
100290<strong>04</strong> AIRPLUS MAINTENANCE GmbH CESSNA 5<strong>01</strong>, 551 Installation of Avidyne TAS 620 and Honeywell None Prior to installation of this modification it 25.02.2<strong>01</strong>0<br />
KGP 860<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029265 AIRPLUS MAINTENANCE GmbH P-<strong>EASA</strong>.A.S.03811 REV. 1 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Enabeling of SVT Functionalities on Garmin<br />
G5/600 System (Revision of<strong>EASA</strong> STC<br />
10029265)<br />
10029716 AIRPLUS MAINTENANCE GmbH P-<strong>EASA</strong>.A.S.03907 REV. 1 SEE APPROVED MODEL LIST Enabling of SVT Functionalities on Garmin<br />
G5/600 Avionics System(Revision of <strong>EASA</strong><br />
STC 10029716)<br />
The aircraft must have been already equipped<br />
with Garmin G5/600System(s) according to<br />
<strong>EASA</strong> STC 10029265.<br />
The aircraft must have been already equipped<br />
with Garmin G5/600System(s) according to<br />
<strong>EASA</strong> STC 10029716<br />
11.03.2009<br />
Prior to installation of this modification it 19.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
10032902 AIRPLUS MAINTENANCE GmbH SC <strong>01</strong>, SC <strong>01</strong>B Inspection Program to increase operating None<br />
product.<br />
Prior to installation of this modification it 07.12.2<strong>01</strong>0<br />
hoursMM Modification of chapter IV<br />
must be determined thatthe<br />
Airworthiness Limitations - Implementationof<br />
interrelationship between this modification<br />
Inspection Program to increase operating hours<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034024 AIRPLUS MAINTENANCE GmbH <strong>EASA</strong> APPROVED MODEL LIST Dual Installation of Garmin GNS 430<br />
(A)W/GNS 530 (A)W (TAWS).<br />
10034382 AIRPLUS MAINTENANCE GmbH 1.BEECH 58, 58A, G58<br />
2.BEECH 58P, 58PA, 58TC,<br />
58TCA<br />
Dual Installation of Garmin GNS430(A)W /<br />
GNS530(A)W(TAWS)<br />
03.12.2<strong>01</strong>2<br />
None The antenna installation is not covered by 28.02.2<strong>01</strong>1<br />
this STC. The aircraft musthave been<br />
already equipped with suitable antennas.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other prev<br />
None The antenna installation is not covered by 30.03.2<strong>01</strong>1<br />
this STC.The aircraft must have been<br />
already equipped with suitable antennas.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other prev<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 68/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
1003<strong>462</strong>3 AIRPLUS MAINTENANCE GmbH 112, 112B, 112TC, 112TCA Dual installation of Garmin<br />
None The antenna installation is not covered by 15.<strong>04</strong>.2<strong>01</strong>1<br />
114, 114A, 114B, 114TC GNS430(A)W/GNS530(A)W(TAWS)<br />
this STC. The aircraft musthave been<br />
already equipped with suitable antennas.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other prev<br />
10035120 AIRPLUS MAINTENANCE GmbH P-<strong>EASA</strong>.A.S.03596 DHC-8-315 VIP Cabin Interior Modification as detailed in Installation is limited to DHC-8-315, S/N 0348 V-Plane engineering GmbH, DOA <strong>EASA</strong> 26.05.2<strong>01</strong>1<br />
AIRplus DescriptionDocument DE-0348-<br />
21J.323 shall fulfil the obligationsof Part<br />
2500<strong>01</strong>, Revision 3, dated 03.05.2<strong>01</strong>1<br />
21, Paragraph 21A.3. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modif<br />
10036129 AIRPLUS MAINTENANCE GmbH SEE <strong>EASA</strong> APPROVEL MODEL<br />
LIST<br />
10037559 AIRPLUS MAINTENANCE GmbH SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of Honeywell EGPWS MK VI<br />
System<br />
10038318 AIRPLUS MAINTENANCE GmbH 500 Installation of Garmin Transponder GTX 330D<br />
on Cessna 500 Series./ Installation of Garmin<br />
Mode A/C/S Transponder GTX 330D with<br />
additionaldiversity antenna.<br />
The aircraft must have been already equipped<br />
with a suitable display andsuitable sensors.<br />
Prior to installation of this modification it 12.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Garmin G600 Avionics System None The Aircraft must have been already<br />
equipped with a suitable GPSReceiver.<br />
Autopilot Coupling is not covered by this<br />
STC. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other prev<br />
06.12.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.02.2<strong>01</strong>2<br />
10<strong>01</strong>4468 AIRTOURING LTD <strong>EASA</strong>.A.S.02529 CESSNA 441 SERIES Installation of Dual GTX330D, RDR2000,<br />
MX20, KN63 & KGP-560 TAWS<br />
-- 11.08.2006<br />
10<strong>01</strong>4591 AIRTOURING LTD <strong>EASA</strong>.A.S.02702 PIPER PA-31-350 Installation of Avionics Upgrade -- 28.07.2006<br />
10<strong>01</strong>4717 AIRTOURING LTD <strong>EASA</strong>.A.S.02893 SOCATA TB 10<br />
Installation of Honeywell KGP560 Class B This STC is approved only for the product<br />
12.12.2006<br />
SOCATA TB 20<br />
TAWS<br />
configuration as defined in the approved design<br />
SOCATA TB 200<br />
data referred to in the paragraph "Description".<br />
SOCATA TB 21<br />
Compatibility with other aircraft/engine<br />
SOCATA TB 9<br />
configurations shall be determined by the<br />
SOCATA TB.20GT<br />
installer.<br />
10<strong>01</strong>4740 AIRTOURING LTD <strong>EASA</strong>.A.S.02923 BEECH B200 Installation of KGP560 TAWS and Dual This STC is approved only for the product<br />
05.03.2007<br />
GTX330D Mode S<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4874 AIRTOURING LTD <strong>EASA</strong>.A.S.03099 CESSNA CITATION CS 551 Installation of Avionic Upgrade Requires prior embodiment of Gamma<br />
Support Services Minor Change GSSL-MIN-<br />
CJ551-202.<br />
10<strong>01</strong>7125 AIRTOURING LTD <strong>EASA</strong>.R.S.<strong>01</strong>212 AGUSTA A-109 C Installation of Dual GNS430, GTX330 and<br />
PMA700B<br />
10030747 AIRWELD, INC. P-<br />
<strong>EASA</strong>.IM.A.S.03228<br />
10<strong>01</strong>6989 AIRWOLF AEROSPACE L.L.C. <strong>EASA</strong>.IM.R.S.<strong>01</strong>395 FAA STC SR02491CH ROBINSON R22<br />
ROBINSON R44<br />
707-300C SERIES Vapor Cycle Air Conditioning System<br />
Installation (Validation of FAA STCSA5008NM)<br />
Airwolf Rotor Blade Protective Tape.Installation<br />
of a leading edge protective tape for Robinson<br />
R22 and R44 helicopter models according to<br />
FAA STC SR02491CHNote: The<br />
recommendation for approval is given based<br />
on a review performed in accordance with the<br />
Ty<br />
27.11.2007<br />
02.11.2005<br />
The limitations of FAA STC SA5008NM apply Prior to installation of this modification the 14.07.2009<br />
installer must determinethat the<br />
,,interrelationship between this<br />
modification and any otherpreviously<br />
installed ,,modification will introduce no<br />
adverse effectupon the airworthiness of<br />
the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 69/<strong>462</strong><br />
07.02.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036114 AIRWOLF AEROSPACE L.L.C. FAA STC SR02964CH 206,206A,206B,206L,206L-1 Tension-Torsion strap - Replacement of life none Prior to installation of this modification it 11.08.2<strong>01</strong>1<br />
206L-3,206L-4<br />
limited part<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6590 AIRWOLF FILTER CORPORATION <strong>EASA</strong>.IM.A.S.03000 FAA STC SA02268CH SEE ATTACHED <strong>EASA</strong><br />
APPROVED TYP<br />
10<strong>01</strong>7141 AIRWORK FRANCE <strong>EASA</strong>.R.S.<strong>01</strong>243 AS 355 F, AS 355 F1, AS 355 F2<br />
AS 355 N<br />
10<strong>01</strong>7142 AIRWORK FRANCE <strong>EASA</strong>.R.S.<strong>01</strong>244 AS 350 B, AS 350 BA<br />
AS 350 B1, AS 350 B2<br />
AS 350 B3<br />
10<strong>01</strong>7190 AIRWORK FRANCE <strong>EASA</strong>.R.S.<strong>01</strong>327 AS 350 B, AS 350 B1<br />
AS 350 B2, AS 350 BA<br />
AS 350 B3<br />
10<strong>01</strong>7191 AIRWORK FRANCE <strong>EASA</strong>.R.S.<strong>01</strong>328 AS 355 E, AS 355 F, AS 355 F1<br />
AS 355 F2, AS 255 N, AS 355 NP<br />
10<strong>01</strong>5355 AIRWORTHINESS RESOURCES<br />
CORPORATION<br />
Installation of Airwolf Filter Corp Air Oil<br />
Seperator<br />
Installation of Thales AGILE 2 external camera<br />
and associated cabin electronic control unit.<br />
Installation of Thales AGILE 2 external camera<br />
and associated cabin electronic control unit, in<br />
accordance with AIRWORK STC file<br />
n°AWF.0<strong>01</strong>.05 revision A, dated January 2007,<br />
or later <strong>EASA</strong> approved revision.<br />
Nouveau système de prises de vues frontales<br />
(Front Mounted Camera Installation).<br />
Nouveau System de Prises de Vues<br />
Frontales(Front Mounted Camera Installation)<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
This STC is not approved for Category A<br />
operations.<br />
<strong>EASA</strong>.IM.A.S.00640 REV. 1 TCCA STC SA00-148 BOMBARDIER CL-415 Installation of an Integrated Liquid Spray 1. Operation in accordance with AFM<br />
System (ILSS)Relocation of the cockpit control Supplement C53790 Rev. B or later approved<br />
panel for the Integrated Liquid Spray System revision. AMM Supplement A65-10, or later<br />
(ILSS)<br />
approved revision.2. Prior to installation of<br />
this modification the installer must determine<br />
that the interrelationship betwee<br />
10<strong>01</strong>7050 AKV Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>474 FAA STC SR<strong>01</strong>958LA EUROCOPTER FRANCE AS 350<br />
B2<br />
Installation of AKV, Inc. Ng/Np Cycle Counter<br />
P/N 350NGLTSB2<br />
AS350B2 modification iaw STC<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>222 issued on 20 March 2008<br />
is required prior to the installation of the Ng/Np<br />
Cycle Counter. The Ng/Np Cycle Counter can<br />
only be installed on day/night VFR aircraft with<br />
non-FADEC equipped engine.The Ng/Np<br />
Cycle<br />
10028164 AKV Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>555 FAA SR00631DE-D 31.07.2009<br />
10<strong>01</strong>7181 ALIDAUNIA S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>3<strong>04</strong> A109 E Installation of a Ginevri Incubator Type "Baby Agusta A109E equipped with Agusta Kit EMS<br />
14.08.2006<br />
10<strong>01</strong>7242 ALIDAUNIA S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>436 MBB-BK 117 C-1<br />
Shuttle Intensive Care" P/N 7634B complete of P/N 109-0326-69-103.<br />
the attachment fittings<br />
MB <strong>01</strong>8/ALI/2008 "Installation of GPS/Satellite Prior to installation of this modification the<br />
System usable to locate the helicopter position. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
18.07.2008<br />
10028026 ALIDAUNIA S.R.L. P-<strong>EASA</strong>.R.S.<strong>01</strong>508 A109S BM No. 020/AL/2008 Installation of a "Ginevri"<br />
Incubator Type "BabyShuttle Intensive Care"<br />
10035253 ALIDAUNIA S.R.L. A109A II MB 022/ALI/2<strong>01</strong>0 "Installation of Alternate<br />
Static Pressure Source forthe Indicator:<br />
Altimeter, Airspeed & Vertical Speed"<br />
19.02.2009<br />
27.11.2008<br />
27.02.2007<br />
16.06.2008<br />
16.06.2008<br />
22.10.2007<br />
29.07.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.11.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.07.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 70/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038498 ALPINE AVIATION, L.L.C. FAA STC SA0<strong>04</strong>69NY 1- G36<br />
Installation of Main Landing Gear Auxiliary None. Prior to installation of this modification it 21.02.2<strong>01</strong>2<br />
2- 33, 35, 36<br />
Landing Lights in accordancewith FAA STC<br />
must be determined thatthe<br />
SA0<strong>04</strong>69NYInstallation of Main landing Fear<br />
interrelationship between this modification<br />
Auxiliary Landing Lights in accordancewith<br />
and any other previouslyinstalled<br />
Alpine Aviation, Inc. Installation Manual, Report<br />
modification and/ or repair will introduce<br />
No. <strong>01</strong>4, datedJune 14, 1996.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6940 ALTAIR AVIONICS CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>332 FAA STC SR0<strong>01</strong>70BO AGUSTA AB-412<br />
BELL 212<br />
BELL 222<br />
BELL 222B<br />
BELL 222U<br />
BELL 412<br />
BELL 412 EP<br />
EUROCOPTER DEUTSCHLAND<br />
BK117 A<br />
EUROCOPTER DEUTSCHLAND<br />
BK117 B<br />
EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
10038718 ALTITUDE AEROSPACE Inc. TCCA STC SA11-43 DHC-8-2<strong>01</strong>/-202 Installation of an Oven and a Coffee Brewer in<br />
the GalleyTCCA STC SA11-43, Issue 1<br />
Monitoring System "Altair Avionics SmartCycle" This STC supersedes <strong>EASA</strong> STC 20<strong>04</strong>-1554<br />
by adding model Bell 412 EP to the<br />
applicability list.<br />
10032055 ALTITUDE AEROSPACE INTERIORS Ltd. REV. 1 B747-400 Installation of Honeywell / Racal MSC6000<br />
SatCom System per AltitudeAerospace<br />
Interiors Master Data List MDL 220<strong>01</strong>052 Rev.<br />
B<br />
10032069 ALTITUDE AEROSPACE INTERIORS Ltd. B747-400 Refurbishment of the B747-400 Upper and<br />
Main deck interior installationand seating<br />
configuration in accordance with Altitude<br />
AerospaceInteriors Master Data List MDL<br />
220<strong>01</strong>038 Rev. A or later EAWSA<br />
approvedrevision.<br />
10028359 AMAC AEROSPACE SWITZERLAND AG P-<strong>EASA</strong>.A.S.03791 REV. 1 A320 Humidification and Zonal Dryer System<br />
Installation(see project description document<br />
PD-AA32<strong>01</strong>-2100)<br />
10028365 AMAC AEROSPACE SWITZERLAND AG P-<strong>EASA</strong>.A.S.03792 REV. 1 A320-232 Interior Outfitting(see project description<br />
document PD-AA<strong>01</strong>-2500-1) The limitation for<br />
use of Supplemental Water Tanks has been<br />
removed atRev. 1 of <strong>EASA</strong> STC 10028365.<br />
10032<strong>04</strong>3 AMAC AEROSPACE SWITZERLAND AG A319-133CJ MSN4114 Interior Outfitting.The change<br />
consists in a complete cabin interior outfitting<br />
with a 28passenger VIP interior including two<br />
medical stretcher units.<br />
18.05.2007<br />
Galley PN H82530009 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.03.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.11.2<strong>01</strong>0<br />
This STC is applicable to A/C Serial Numbers Prior to installation of this modification it 06.10.2<strong>01</strong>0<br />
24855, 24896, 24957, 25605,26910, 27602 must be determined thatthe<br />
and 29375. Several parts installed with this interrelationship between this modification<br />
STC deviate from Part 21A.8<strong>04</strong>regarding EPA and any other previouslyinstalled<br />
marking. The responsible NAA grant a 14.4 modification and/ or repair will introduce<br />
exemptions toaccept the aircraft on its r no adverse effectupon the airworthiness<br />
of the product.<br />
According to doc. No ICA-A32<strong>01</strong>-2100 as Prior to installation of this modification it <strong>04</strong>.03.2<strong>01</strong>0<br />
listed under associated technicaldocumentation must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to MSN 3379 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.<strong>01</strong>.2<strong>01</strong>0<br />
MSN 4114 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
05.10.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 71/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035437 AMAC AEROSPACE SWITZERLAND AG A319-133 Satcom and LAN / WLAN System Installation Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
22.06.2<strong>01</strong>1<br />
10036061 AMAC AEROSPACE SWITZERLAND AG B737-700IGW VIP seat change / Replacement of single seat<br />
by one with massagefeature.<br />
10037123 AMAC AEROSPACE SWITZERLAND AG A319-133 Monitor Replacement / Exchange of Plasma-<br />
TV with LCD-TV screens in VIPcabin.<br />
10039943 AMAC AEROSPACE SWITZERLAND AG A319-133 Interior RefurbishmentBy: - Carpet and Curtain<br />
replacement- Seat re-upholstery- Replacement<br />
of 4 double seats by 2 L-Shape Divans- VCC<br />
(IFE) Cabinet relocation- IFE upgrade-<br />
Additional Power Outlets installation-<br />
Emergency Equipment replacement<br />
10<strong>04</strong>1797 AMAC AEROSPACE SWITZERLAND AG B777-200LR Interior Outfitting project BA<strong>01</strong>-2500 (S/N<br />
40753) The change consists in a complete<br />
cabin interior outfitting of B777-200LR S/N<br />
40753 aircraft with a 125 passengers, plus 16<br />
crew seatingarrangement in a new "VVIP"<br />
Cabin Interior suitable for"Private/Smokin<br />
10<strong>01</strong>6760 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10<strong>01</strong>6761 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10<strong>01</strong>6769 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10<strong>01</strong>6778 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10<strong>01</strong>6779 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10<strong>01</strong>6834 AMERICAN EUROCOPTER<br />
CORPORATION<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>089 FAA STC SR09281RC-D EUROCOPTER FRANCE EC 155<br />
B1<br />
American Eurocopter LLC Modification FAA<br />
STC SR09281RC-D.Installation of a Garmin<br />
Global Positioning System (GPS) - GPS 500.<br />
This approval is limited to Aircraft B737-<br />
700IGW, Serial Number 36027.<br />
Prior to installation of this modification it 09.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
S/N: 2421 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.11.2<strong>01</strong>1<br />
S/N: 1335 ,,A7-HHJ Approval valid only for MSN 1335. The<br />
aircraft is certified for private use only. It<br />
is prohibited tooperate the aircraft for hire<br />
or offered for common carriage. The<br />
aircraft is a "No Smoking" aircraft. A<br />
Minimum of 1 Cabin Crew is required.<br />
<strong>04</strong>.06.2<strong>01</strong>2<br />
S/N 40753<br />
For other Lim<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.10.2<strong>01</strong>2<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>090 FAA STC SR09290RC-D EUROCOPTER FRANCE EC 155 Installation of horizontal tip position/anti-<br />
installer.<br />
This STC is approved only for the product<br />
B1<br />
collision strobe lights<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>100 FAA STC SR09282RC-D EUROCOPTER FRANCE EC 155 American Eurocopter LLC Modification FAA This STC is approved only for the product<br />
B1<br />
STC SR09282RC-D. Installation of a configuration as defined in the approved design<br />
Honeywell Enhanced Ground Proximity data referred to in the paragraph "Description".<br />
Warning System.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>117 FAA STC SH88<strong>04</strong>SW-D EUROCOPTER FRANCE EC 155 Installation of a Universal Navigation UNS- 1F<br />
B1<br />
Flight Management System for IFR enroute &<br />
non-precision approaches.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>118 FAA STC SR09295RC-D EUROCOPTER FRANCE EC 155 Installation of navigation, communications & This STC is approved only for the product<br />
B1<br />
various electrical equipment<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>205 FAA STC SH7339SW-D EUROCOPTER FRANCE AS Installation of an extended radome and FLIR<br />
365N2<br />
2000 infrared imaging system, in accordance<br />
EUROCOPTER FRANCE AS with AEC Drawing List n° 365A73-9037,<br />
365N3<br />
revision H dated 09 October 2000, or later FAA<br />
EUROCOPTER FRANCE SA<br />
365N<br />
EUROCOPTER FRANCE SA<br />
365N1<br />
approved revision.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 72/<strong>462</strong><br />
15.08.2005<br />
20.07.2005<br />
11.08.2005<br />
10.10.2005<br />
10.10.2005<br />
28.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6835 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>206 FAA STC SH7338SW-D EUROCOPTER FRANCE AS Installation of an AFT mounted retractable<br />
28.08.2006<br />
CORPORATION<br />
365N2<br />
Nightsun Searchlight System, in accordance<br />
EUROCOPTER FRANCE AS with AEC Drawing List n° 365A73-9036,<br />
365N3<br />
revision F dated 19 March 1999, or later FAA<br />
EUROCOPTER FRANCE SA<br />
365N1<br />
approved revision.<br />
10<strong>01</strong>6836 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>207 FAA STC SH7022SW-D EUROCOPTER FRANCE AS Installation of Radio Master switch, in Compatibility of this modification with<br />
20.07.2006<br />
CORPORATION<br />
365N2<br />
accordance with AEC Drawing List No. previously approved modifications must be<br />
EUROCOPTER FRANCE AS 365A73-9034, revision B dated 25 April 2002, determined by the installer.<br />
365N3<br />
EUROCOPTER FRANCE SA<br />
365N1<br />
or later <strong>EASA</strong> approved revision<br />
10<strong>01</strong>6837 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>208 SH7<strong>01</strong>4SW-D EUROCOPTER FRANCE AS Installation ofvertical fin anti-collision light, in Compatibility of this modification with<br />
20.07.2006<br />
CORPORATION<br />
365N2<br />
accordance with AEC Drawing List No. previously approved modifications must be<br />
EUROCOPTER FRANCE AS 365A73-9027, revision E dated 09 June 2003, determined by the installer.<br />
365N3<br />
EUROCOPTER FRANCE SA<br />
365N1<br />
or later <strong>EASA</strong> approved revision<br />
10<strong>01</strong>6838 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>209 SH5499SW-D EUROCOPTER FRANCE AS Installation of supplement strobe light, in Compatibility of this modification with<br />
20.07.2006<br />
CORPORATION<br />
365N2<br />
accordance with AEC Drawing List No. H365- previously approved modifications must be<br />
EUROCOPTER FRANCE AS 64-2D-1<strong>01</strong>, revision L dated 06 June 2003, or determined by the installer.<br />
365N3<br />
EUROCOPTER FRANCE SA<br />
365N1<br />
later <strong>EASA</strong> approved revision<br />
10<strong>01</strong>6839 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>210 SH8790SW-D EUROCOPTER FRANCE AS Installatino of a Bendix/King GPS KLN 90B or<br />
07.12.2006<br />
CORPORATION<br />
365N2<br />
KLN 900 for IFR en route operations in<br />
EUROCOPTER FRANCE SA accordance with AEC Drawing List 365A73-<br />
365N1<br />
9060, revision C, dated 02/03/2005, or later<br />
<strong>EASA</strong> approved revision.<br />
10<strong>01</strong>6943 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>337 FAA STC SH8803SW-D EUROCOPTER FRANCE AS Installation of combination position lights and Compatibility of this modification with<br />
13.06.2007<br />
CORPORATION<br />
365N2<br />
strobe lights with supplemental anti-collision previously approved modifications must be<br />
EUROCOPTER FRANCE SA lights replacing the red, green and white determined by the installer.<br />
365N1<br />
position lights..<br />
10<strong>01</strong>6944 AMERICAN EUROCOPTER<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>338 FAA STC SH7<strong>01</strong>8SW-D EUROCOPTER FRANCE AS Installation of 4.0 inch Footwell in the<br />
Compatibility of this modification with<br />
13.06.2007<br />
CORPORATION<br />
365N2<br />
passenger cabin of the Model SA365A73- previously approved modifications must be<br />
EUROCOPTER FRANCE SA<br />
365N1<br />
9022.<br />
determined by the installer.<br />
10033895 AMERICAN EUROCOPTER<br />
FAA STC SR09094RC-D EC 135 P1 (CDS)<br />
Installation of a collective activated tenth None. Prior to installation of this modification it 17.02.2<strong>01</strong>1<br />
CORPORATION<br />
EC 135 P1 (CPDS)<br />
hourmeter in accordancewith AEC Drawing List<br />
must be determined thatthe<br />
EC 135 P2 (CPDS)<br />
135A82-8006.This <strong>EASA</strong> STC is based on<br />
interrelationship between this modification<br />
EC 135 P2+<br />
FAA STC SR9094RC-D.<br />
and any other previouslyinstalled<br />
EC 135 T1 (CDS)<br />
modification and/ or repair will introduce<br />
EC 135 T1 (CPDS)<br />
no adverse effectupon the airworthiness<br />
EC 135 T2 (CPDS)<br />
EC 135 T2+<br />
of the product.<br />
10035<strong>01</strong>5 AMERICAN EUROCOPTER<br />
REV. 1 FAA STC NO. SR09262RC-D EC135 P1(CDS), EC135 Installation of a Belly and Fin Strobe lights in None. Prior to installation of this modification it 23.05.2<strong>01</strong>1<br />
CORPORATION<br />
P1(CPDS),<br />
accordance with AECDrawing List 135A82-<br />
must be determined thatthe<br />
EC135 P2(CPDS), EC135 P2+, 8<strong>01</strong>8.<br />
interrelationship between this modification<br />
EC135 T1(CDS), EC135<br />
and any other previouslyinstalled<br />
T1(CPDS),<br />
modification and/ or repair will introduce<br />
EC135 T2(CPDS), EC135 T2+<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035617 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10035996 AMERICAN EUROCOPTER<br />
CORPORATION<br />
FAA STC SH8171SW-D SA 365 N1,AS 365 N2 Installation of Bendix /King EFIS 40 Electronic none If the holder agrees to permit another<br />
Flight InstrumentationSystem in accordance<br />
person to use this certificate toalter the<br />
with AEC Drawing List 365A73-9051Revision B<br />
product, the holder shall give the other<br />
dated10/1/93 or Bendix /King EFIS 50<br />
person writtenevidence of that<br />
Electronic Flight InstrumentationSystem in<br />
permission.Prior to installation of this<br />
accordance with AEC Drawing List 365A73-<br />
modification it must be determined<br />
thatthe interrelationship<br />
FAA STC SR09306RC-D MBB-BK 117-C2 Installation of tailboom mounted aft ballast in<br />
accordance with AmericanEurocopter Drawing<br />
List 145A82-8006.<br />
None Compatibility of this modification when<br />
more than 4.5 kg of additionalequipment<br />
is installed on the tailboom has to be<br />
determined prior toinstallation.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this m<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 73/<strong>462</strong><br />
05.07.2<strong>01</strong>1<br />
03.08.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039855 AMERICAN EUROCOPTER<br />
FAA STC SR09137RC-D EC 135 P2, EC 135 P2+<br />
Installation of an Extended Right Hand side none Prior to installation of this modification it 30.05.2<strong>01</strong>2<br />
CORPORATION<br />
EC 135 T1, EC 135 T2<br />
Instrument Panel inaccordance with AEC<br />
must be determined thatthe<br />
EC 135 T2+, EC 135 P1<br />
Drawing List 135A82-8020.This <strong>EASA</strong> STC is<br />
interrelationship between this modification<br />
based on validation of FAA STC SR09137RC-<br />
and any other previouslyinstalled<br />
D (Amdt.10-May-2<strong>01</strong>2) iaw the TIP.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1261 AMERICAN EUROCOPTER<br />
CORPORATION<br />
10<strong>01</strong>6415 AMERICAN PROPELLER SERVICE <strong>EASA</strong>.IM.A.S.02747 FAA STC SA5896NM CESSNA 210F<br />
CESSNA 210G<br />
CESSNA 210H<br />
CESSNA 210J<br />
CESSNA 210K<br />
CESSNA 210L<br />
CESSNA 210M<br />
10<strong>01</strong>4425 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10<strong>01</strong>4680 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10<strong>01</strong>4681 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10<strong>01</strong>4818 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10<strong>01</strong>5009 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10<strong>01</strong>53<strong>01</strong> AMES - AEROSPACE AND<br />
MECHANICAL<br />
10027678 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10035593 AMES - AEROSPACE AND<br />
MECHANICAL<br />
10036300 AMES - AEROSPACE AND<br />
MECHANICAL<br />
FAA STC SR091<strong>04</strong>RC-D EC135 P1, P2, P2+, T1, T2, T2+ Installation of a pulsed engine and gearbox chip None Prior to installation of this modification it 03.09.2<strong>01</strong>2<br />
detector system inaccordance with AEC<br />
must be determined thatthe<br />
Drawing List 135A82-8009.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>EASA</strong>.A.S.02470 CESSNA 208<br />
CESSNA 208A<br />
CESSNA 208B<br />
Installation of a McCauley D3A34C4<strong>04</strong>/80VA-0 As defined in FAA STC SA5896NM1 Prior to<br />
Propeller.<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no<br />
adverse effect upon th<br />
Mount assembly for external side loads for<br />
Cessna 208 models<br />
<strong>EASA</strong>.A.S.02841 CESSNA 550 Supplemental Type Certificate for Cargo Net CRI A-02; Registration: OE-GAD; S/N C550-<br />
Installation on C550 MSN 00<strong>01</strong>-0626 0071<br />
<strong>EASA</strong>.A.S.02842 CESSNA 551 Supplemental Type Certificate for Cargo Net CRI A-02Registration (if applicable): OE-<br />
Installation on C551 MSN 00<strong>01</strong>-0549 FADSerial number (if applicable): C551-<strong>04</strong>96<br />
<strong>EASA</strong>.A.S.03026 REV. 2 A320 Installation of an In-Flight Entertainment<br />
System (Live TV) on AirbusA320 Aircraft<br />
02.10.2008<br />
07.06.2006<br />
12.02.2007<br />
13.<strong>04</strong>.2007<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
05.11.2<strong>01</strong>0<br />
<strong>EASA</strong>.A.S.03311 BEECH 400A Activation of Garmin MX-20 Multifunction<br />
Display.<br />
None. 13.08.2008<br />
<strong>EASA</strong>.A.S.03862 FALCON 2000 Falcon 2000 MSN209 Interior Refurbishment. 1. Limited to A/C Falcon 2000, MSN 209.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect up<br />
11.05.2009<br />
P-<strong>EASA</strong>.A.S.03803 REV. 1 A330-223 Airbus A330 - 200 B/C ISPSS Installation This STC is limited to the following Serial<br />
Numbers:MSN 403, 432, 444, 454, 469, 476,<br />
493<br />
REV. 1 737-700 AND 737-800 B737-800/-700 Live TV System Removal / This STC is only applicable for aircraft which<br />
Major Change to <strong>EASA</strong> STC 10035593to have been previouslymodified with FAA<br />
implement B737-700 as effective aircraftAMES Supplemental Type Certificate ST02887AT.<br />
will use FAA approved Live TV documentation<br />
such as but not limitedto: Drawings, Structural<br />
substantiation reports, ELA and W&B fo<br />
767-300 B767-300 Astronics EMPower 110VAC<br />
activation.<br />
Prior to installation of this modification it 25.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 09.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>EASA</strong> STC <strong>EASA</strong>.IM.A.S.<strong>01</strong>257 must be Prior to installation of this modification it 29.08.2<strong>01</strong>1<br />
installed prior to the accomplishmentof the must be determined thatthe<br />
changes of this approval, andThe installation of interrelationship between this modification<br />
the In-Seat components is not covered with and any other previouslyinstalled<br />
thisapproval and must be approved prior to the modification and/ or repair will introduce<br />
accomplishment of the changesdetailed no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 74/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037822 AMES - AEROSPACE AND<br />
A330-2<strong>01</strong>, -202, -203<br />
A330-200 Cabin reconfigurationThis STC The following modifications, in accordance with Prior to installation of this modification it 22.12.2<strong>01</strong>1<br />
MECHANICAL<br />
A330-223, -243<br />
installs mainly new B/C and Y/C seats and new their aircraftapplicability, are<br />
must be determined thatthe<br />
In-FlightEntertainment system, according to prerequisites to the installation of this STC :- interrelationship between this modification<br />
various cabin configurations.<br />
AMES Minor Change ref :<br />
and any other previouslyinstalled<br />
M1480<strong>01</strong>10.11082<strong>01</strong>1 (Approved under modification and/ or repair will introduce<br />
AMES DOA<strong>EASA</strong>.21J.299)- AMES Minor no adverse effectupon the airworthiness<br />
Change ref : M1480<strong>01</strong>11.1108<br />
of the product<br />
1003<strong>01</strong>18 AMICALE DE VOLTIGE AERIENNE (AVA) REV. 1 CAP 232 Evolution of of CAP 232 to CAP 332<br />
SC.Revision 1: Modifications majeures<br />
applicables aux CAP23X et 332 SC<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.07.2<strong>01</strong>1<br />
10<strong>01</strong>5819 AM-SAFE INCORPORATED <strong>EASA</strong>.IM.A.S.<strong>01</strong>891 FAA STC ST<strong>01</strong>866LA JETSTREAM 4100 SERIES Installation of AMSAFE Aviation Inflatable<br />
Restraint (AAIR) System on Front Row<br />
Passenger Seats of the Jetstream 4100 Series<br />
Not valid for Jetstream Model 4124 17.05.2006<br />
10<strong>01</strong>5412 AMSAFE, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>128 FAA STC SA<strong>01</strong>700LA. CESSNA 172R<br />
CESSNA 172S<br />
CESSNA 177<br />
CESSNA 206H<br />
10<strong>01</strong>5687 AMSAFE, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>672 SA<strong>01</strong>7<strong>01</strong>LA AVIAT HUSKY A-1<br />
AVIAT HUSKY A-1A<br />
AVIATION AIRCRAFT A-1B<br />
10031<strong>01</strong>0 AMSAFE, Inc. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10031808 AMSAFE, Inc. REV. 1 FAA STC ST02152LA SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of AMSAFE Aviation Infatable<br />
Restraint (AAIR) System.<br />
Installation of Am-Safe Aviation Inflatable<br />
Restraint System on pilot and copilot<br />
seatsValidation of FAA STC SA<strong>01</strong>7<strong>01</strong>LA<br />
Isuued December 06, 20<strong>04</strong><br />
Installation of AmSafe Aviation Inflatable<br />
Restraints in Non 23.562certified Airplanes in<br />
accordance with Model Specific Master Data<br />
Listidentified on AML SA02276AK , Rev J ,<br />
dated 10 Dec. 2009<br />
AmSafe Aviation Inflatable Restraint (AAIR)<br />
System on various transportcategory airplanes.<br />
This revision <strong>01</strong> extends the applicability of<br />
AAIR to Reynard Reverbseat fitted on A330-<br />
300 airplanes, operated by Virgin Atlantic<br />
Airways.<br />
10<strong>01</strong>5973 AMTECH AERONAUTICAL LIMITED <strong>EASA</strong>.IM.A.S.02124 SA02-132, ISSUE NO.3 LOCKHEED 382G Oil Dispersant Spraying System Installation on<br />
Lockheed 328G aircraft.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
The Electronic Module P/N 508358-409 and<br />
the Inflator Assembly P/N 508794-4<strong>01</strong> must be<br />
replaced every seven (7) years<br />
If Installation of the Shoulder Harness is not to<br />
approved Data definedin the STC a separate<br />
approval has to be obtained<br />
1-,,For the installation of approved seats<br />
modified by installation ofthe AmSafe Inflatable<br />
Restraint System in a specific cabin<br />
layout,compliance to 25.561 must be<br />
demonstrated for the individual seat at<br />
itsspecific location within the approval project<br />
fo<br />
Operation in accordance with Airplane Flight<br />
Manual Supplement FMS2439<strong>01</strong> Rev. 4 dated<br />
November 4, 2005 or later TCCA approved<br />
revision in conjunction with AFI Operating<br />
Manual OP2439 Rev. 3 dated August 2005 or<br />
later TCCA approved revision.Instructions for<br />
10<strong>01</strong>6638 AMTECH AERONAUTICAL LIMITED <strong>EASA</strong>.IM.A.S.03078 TCCA STC C-LSA06-378/D LEARJET 45 AirCell Axxess II Iridium SatcomTCCA LSTC C- 1 Prior to installation of this modification the<br />
LSA06-378/D<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2 Th<br />
10034839 AMTECH AERONAUTICAL LIMITED TCCA STC SA09-51, ISSUE NO. 1 CL-600-2C10<br />
CL-600-2D15<br />
CL-600-2D24<br />
Installation of a Rosemount Aerospace Angle<br />
of Attack Sensor.<br />
Model additions to the FAA Approved<br />
Model List Rev J , dated 10 Dec<br />
2009have to be applied to <strong>EASA</strong>Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modific<br />
22.<strong>04</strong>.2005<br />
30.11.2005<br />
21.07.2<strong>01</strong>0<br />
Prior to installation of this modification it 14.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>01</strong>.02.2007<br />
06.<strong>01</strong>.2009<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.05.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 75/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039313 AMTECH AERONAUTICAL LIMITED REV. 1 TCCA STC C-LSA06-188/D MF900 Artex C406-N ELT and Flight Displays FD600 Limited to S/N 141 Prior to installation of this modification it 27.<strong>04</strong>.2<strong>01</strong>2<br />
Video Camera Installations.<strong>EASA</strong> validation of<br />
must be determined thatthe<br />
TCCA Limited STC No C-LSA06-188/D Issue<br />
interrelationship between this modification<br />
1 dated 23May 2006.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5619 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>571 ST<strong>01</strong>748LA BOEING 757-200 Installation of a Main Deck Cargo Handling<br />
System<br />
10<strong>01</strong>5736 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>760 ST116<strong>04</strong>LA-T BOEING 747-400 SERIES Installation of Main Deck Cargo Loading<br />
System<br />
<strong>EASA</strong> STC <strong>EASA</strong>.IM.A.S.02<strong>04</strong>0 must be<br />
installed in conjunction with this installation.<br />
10<strong>01</strong>5739 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>763 ST<strong>01</strong>644LA AIRBUS A300-600 <strong>EASA</strong> validation of FAA STC<br />
This STC is only applicable on Airbus A300-<br />
ST<strong>01</strong>644LA:revision C to Ancra Controlled 600 aircraft converted to freighter in<br />
Drawing List DL83690STC ST<strong>01</strong>644LA, cargo accordanace with <strong>EASA</strong>.A.S.00387/FAA STC<br />
Loading Sytem,Project Number SA11805LA-T ST<strong>01</strong>431NYThe aircraft must be compliant<br />
with the instructions for continued airworthiness<br />
(see ANCRA reports 8967 revision A and 8284<br />
10<strong>01</strong>5953 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.02095 REV. 1 FAA STC ST<strong>01</strong>926LA BOEING 747-400 Installation of Main Deck Cargo Loading<br />
System<br />
10<strong>01</strong>6063 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.02242 FAA STC ST<strong>01</strong>551LA AEROSPATIALE ATR 42-300 Installation of Ancra mechanical main deck<br />
AEROSPATIALE ATR 42-320 cargo landing system<br />
10<strong>01</strong>6114 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.023<strong>04</strong> FAA STC ST<strong>01</strong>890LA BOEING B737-400 Installation of cargo loading system in<br />
accordance with FAA approved Ancra<br />
International LLC Controlled Drawing List<br />
DL84670-10, Revision B, dated March 22,<br />
2006, or later FAA approved revision.<br />
10<strong>01</strong>6408 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.02739 FAA STC ST<strong>01</strong>388LA BOEING 747-200<br />
BOEING 747-300<br />
BOEING 747-400<br />
BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
BOEING 767-400<br />
BOEING 767-400ER<br />
BOEING 777-200<br />
BOEING 777-300<br />
Installation of Power Drive Unit (Cargo<br />
System).<br />
10<strong>01</strong>6473 ANCRA INTERNATIONAL LLC <strong>EASA</strong>.IM.A.S.02819 FAA STC ST00680DE BOEING B737-400 Installation of mechanical cargo loading system<br />
Part Number84980-10 & -20 on B737-400<br />
aircraft<br />
<strong>EASA</strong> STC <strong>EASA</strong>.IM.A.S.02039 must be<br />
installed in conjunction with this installation.This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Document<br />
1. STC SA 2968SO (<strong>EASA</strong>.IM.A.S.02423),<br />
SA2969SO (<strong>EASA</strong>.IM.A.S.02424), and<br />
SA2970SO (<strong>EASA</strong>.IM.A.S.02425) must be<br />
installed in conjunction with this installation.2.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
10028464 ANCRA INTERNATIONAL LLC FAA STC ST02279LA B767-300 Install Main Deck Cargo Loading System<br />
airworthiness of the product.2.<br />
To be installed on a/c converted by IAI<br />
Freighter Conversion (<strong>EASA</strong> STC10028430)<br />
23.12.2005<br />
27.06.2006<br />
07.<strong>04</strong>.2006<br />
12.<strong>01</strong>.2007<br />
08.12.2006<br />
18.<strong>04</strong>.2007<br />
31.03.2008<br />
02.03.2009<br />
Prior to installation of this modification it 13.<strong>01</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030694 ANCRA INTERNATIONAL LLC FAA STC ST023<strong>04</strong>LA B737-300 Installation of main deck cargo loading system. None This modification does not effect<br />
Electrical Wiring InterconnectionSystems<br />
This modification does not effect or<br />
create Fatigue Critical StructuresThe<br />
STC <strong>EASA</strong>.IM.A.S.<strong>01</strong>754 (FAA<br />
ST<strong>01</strong>827LA) must be installed<br />
inconjunction with this installation.Prior to<br />
inst<br />
<strong>01</strong>.07.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 76/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10033161 ANCRA INTERNATIONAL LLC FAA STC ST02319LA B737-400 Installation of main deck cargo loading system <strong>EASA</strong> validated equivalent to FAA STC This modification does not affect 21.12.2<strong>01</strong>0<br />
ST<strong>01</strong>827LA must be installed inconjunction Electrical Wiring InterconnectionSystems.<br />
with this STC<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair w<br />
10038884 ANCRA INTERNATIONAL LLC FAA STC ST02414LA B757-200 Installation of Main Deck Cargo Loading<br />
System.<br />
10<strong>01</strong>4603 APA AVIONES PIEZAS Y ACCESORIOS <strong>EASA</strong>.A.S.02726 CESSNA 421C Installation GNS-430 and DME KN62AGarmin<br />
GNS-430 GPS/NAV/COMM system, Mid-<br />
Continent MD41D Annunciation Control Unit<br />
and Bendix King KN62 DME installed on<br />
Cessna 421CS/N 0272 (GPS approved for IFR<br />
and B-RNAV operations).<br />
10<strong>01</strong>6710 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.00619 FAA STC SR0<strong>04</strong>70LA AS 350 B/D/BA/B1/B2/B3 Emergency Flotation Kit installation according<br />
to FAA STC No. SR0<strong>04</strong>70LA issued on<br />
November 17, 1997 and reissued December<br />
22, 1998.<br />
10<strong>01</strong>6719 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>3 FAA STC SR00780LA EC 120 B Installation of Apical Emergency Float Kit, p/n<br />
10<strong>01</strong>6772 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>107 REV. 1 FAA STC SR<strong>01</strong>779LA AB412, AB412EP<br />
BELL 212, 412, 412EP/CF<br />
BELL 412 EP<br />
10<strong>01</strong>6775 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>114 FAA STC SR00831LA AS 350 D/B/B1/B2/B3/BA,<br />
AS 355 E/F/F1/F2/N<br />
2<strong>04</strong>98.The present STC is the validation of the<br />
FAA STC n° SR00780LA issued on<br />
19/03/1999.<br />
STC <strong>EASA</strong>.IM.R.S.<strong>01</strong>107 applicability<br />
extended to B212, 412 CF, AB412 and<br />
AB412EP.<br />
10<strong>01</strong>6776 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>115 FAA STC SR<strong>01</strong>687LA EC 130 B4 Installation of Apical Emergency Float kit p/n<br />
6<strong>04</strong>-0<strong>01</strong>8-100 or Emergency Float kit with<br />
Liferaft p/n 6<strong>04</strong>-0<strong>01</strong>8-300.<br />
10<strong>01</strong>6788 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>135 FAA STC SR<strong>01</strong>535LA BELL 206A, 206B, 206L, 206L-1<br />
BELL 206L-3, 206L-4, BELL 407<br />
To be installed on a/c converted to a<br />
Combination Passenger/ Freighterby ST<br />
Aerospace Inc, <strong>EASA</strong> STC 10038822.<br />
1. Restricted to aircraft CESSNA 421C S/N<br />
0272.2. The aircraft is approved for dual pilot B-<br />
RNAV operation, subjected to the conditions,<br />
limitations and procedures contained in Doc N°<br />
APA <strong>01</strong>8/03 "Supplement Flight Manual", Ed 2<br />
Rev 0<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Instruction for Continued Airworthiness ICA<br />
412-41 Rev. B dated 12th July 2005 or later<br />
approved revision.2. Bell Helicopter Textron,<br />
Inc. High Skid Landing Gear with Lightweight<br />
Flotation Skid Tubes, Part Number 412-050-<br />
<strong>01</strong>5-111/-112 or Aeronautic<br />
Installation of Apical Emergency Float kit, Part 1. This approval requires the inspection and<br />
Number 2<strong>04</strong>16, in accordance with the overhaul schedules to be performed as<br />
following FAA approved Apical Industries, Inc., mandated by the Apical Instructions for<br />
Master Document List and Rotorcraft Flight Continued Airworthiness n° ICA 355-1, rev. G,<br />
Manual Supplement :- For AS 350 series : dated December 3rd, 20<strong>04</strong> or later FAA<br />
MDL n° MD350(4) rev. I, dated Decemb approved revision.2. This installation should not<br />
Installation of Apical Industries Inc. Emergency<br />
Float Kits.<br />
10<strong>01</strong>6795 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>148 FAA STC SR00627LA AS 350 B, AS 350 B1, AS 350 B2 Installation of Utility floats in accordance with<br />
AS 350 B3, AS 350 BA, AS 350 D FAA STC SR00627LA issued May 08, 1998,<br />
reissued December 22, 1998 and amended<br />
September 14, 1998.<br />
10<strong>01</strong>6829 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>199 REV. 1 FAA STC SR<strong>01</strong>855LA EC 135 P1 (CDS)<br />
EC 135 P1 (CPDS)<br />
EC 135 P2 (CPDS), EC 135 P2+<br />
EC 135 T1 (CDS)<br />
EC 135 T1 (CPDS)<br />
EC 135 T2 (CPDS), EC 135 T2+<br />
Emergency Floats KitsInstallation of Apical<br />
Industries, Inc. Emergency Floats Kits i.a.w.<br />
FAASTC SR<strong>01</strong>855LA Apical MDL MD 135-1<br />
provides for different installationseither with<br />
liferats or without. Amendment of the STC in<br />
order to add the EC135 Mid Height La<br />
This StC is the <strong>EASA</strong> validation of FAA STC<br />
n0 SR<strong>01</strong>687LA, dated March 22nd, 2005.<br />
1. This installation of Apical Industries Inc.<br />
Emergency Float Kit requires prior installation<br />
of high landing gear with provision for float<br />
installation as defined in Apical Industries Inc.<br />
Approved Landing Gears for Apical<br />
Emergency Float Kit, AIPHI-8<br />
This approval requires the inspections and<br />
overhaul schedules to be performed as<br />
mandated by the Instruction for Continued<br />
Airworthiness, ICA350-2 dated 2, 1997 or later<br />
FAA approved revision.<br />
1. The installation is not approved for<br />
helicopters equipped with highskid landing<br />
gear.2. Metro Aviation, Inc., Landing Gear Skid<br />
Extensions, Part Number135M-110, must be<br />
installed i.a.w. STC <strong>EASA</strong>.IM.R.S.<strong>01</strong>377 (FAA<br />
STCSR09230RC) prior to the installation<br />
Prior to installation of this modification it 21.03.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 77/<strong>462</strong><br />
29.06.2006<br />
14.<strong>04</strong>.2005<br />
11.<strong>04</strong>.2005<br />
14.05.2007<br />
15.11.2005<br />
25.<strong>04</strong>.2008<br />
16.<strong>01</strong>.2007<br />
20.06.2006<br />
<strong>01</strong>.06.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6831 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>202 FAA STC SR<strong>01</strong>459LA BELL 412, 412EP Installation of Emergency Mid-Float with 10- Bell Helicopter Textron, Inc. Emergency Float<br />
<strong>04</strong>.09.2006<br />
man Liferaft KitsInstallation of Apical<br />
Kit Part Number 412-706-0<strong>04</strong>-137, or 412-706-<br />
EMERGENDY Mid-Float with 10-man Liferaft 0<strong>04</strong>-143, or 412-706-0<strong>04</strong>-149 or Apical<br />
Kits<br />
Industries, Inc. Emergency Float Kit, Part<br />
Number 6<strong>04</strong>.96<strong>01</strong> per FAA STCSR<strong>01</strong>648LA,<br />
when approved by <strong>EASA</strong> must be installed<br />
prior t<br />
10<strong>01</strong>6849 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>225 FAA STC SR00856LA BO105 A/C/S Installation of Apical Emergency Float Kits, The installation is not approved for helicopters<br />
07.03.2008<br />
Part Number 2<strong>04</strong>30Description: Installation of<br />
Emergency Float Kit in accordance with FAA<br />
STC SR00856LA. Apical MDL MD105-2<br />
provies for two differentinstallations either with<br />
liferafts or without.Note: the recomm<br />
equipped with high skid landing gear.<br />
10<strong>01</strong>6850 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>226 FAA STC SR00932LA MD 369 HS, HM, HE,<br />
Installation of Apical Emergency Roat kit p/n This STC is the <strong>EASA</strong> validation of FAA STC<br />
25.<strong>04</strong>.2008<br />
D,E,FF,500N<br />
2<strong>04</strong>91 -1.<br />
ne SR00932LA dated February 23rd, 2006.<br />
10<strong>01</strong>6851 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>227 FAA STC SR<strong>01</strong>420LA AS 332 C/L/L1 Installation of Apical Industries, Inc. Emergency<br />
float assemblies, P/N 20729-100, 207300-100<br />
and 2073, and inflation cylinders, P/N 20330-2<br />
1 Aerazur's emergency float assemblies P/N<br />
158820, 158565 and 158566, and inflation<br />
cylinders P/N 158562 (i.e. parts of original<br />
emergency floatation kit approved on<br />
Eurocopter AS332C, L and L1 models) must<br />
be installed prior to applying this STC.The inter<br />
10<strong>01</strong>6865 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>241<br />
REV 1<br />
REV. 1 FAA STC SR<strong>01</strong>902LA S-76 A, B, C Installation of Apical Industries Inc. Liferaft Kit. 16.05.2007<br />
10<strong>01</strong>6923 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>308 FAA STC SR<strong>01</strong>949LA AGUSTA AB-139, AW139 Installation of Apical Industries, Inc. Liferaft Kit. 1. This approval requires the inspections and<br />
overhaul schedules to be performed as<br />
mandated by the Instruction for Continued<br />
Airworthiness, ICA139-1, Revision N/C, dated<br />
July 27, 2006, or later approved revision.<br />
19.10.2007<br />
10<strong>01</strong>6941 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>334 FAA STC SR02<strong>04</strong>9LA ROBINSON R44, R44 II Pop Out Floats Kit: Installation of Apical<br />
Industries, Inc. Pop Out Floats Kit (also titled as<br />
"Emergency Floats Kit") in accordance with<br />
approved Apical Industries, Inc. Master<br />
Document List MD44-1, rev. D, dated 12-<strong>04</strong>-<br />
2007, or later approved revision bas<br />
N/A 27.11.2007<br />
10<strong>01</strong>6947 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>341 FAA STC SH7685SW BO-105 C/S Replacement of the MBB Oil Cooler Fairing,<br />
MBB P/N 105-61802<br />
10<strong>01</strong>6971 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>372 FAA STC SR02065LA AS 350 B/B1/B2/B3/BA/D<br />
AS 355 E/F/F1/F2/N<br />
10<strong>01</strong>7<strong>01</strong>7 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>435 FAA STC SR02108LA AB139, AW139 Nose Landing Gear Doors Kit on Agusta<br />
AB139, AW139.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
350-31 Lower Front Fairing Assembly. 1. This approval requires the inspections and<br />
overhaul schedules to be performed as defined<br />
by Apical Industries Inc’s Instructions for<br />
Continued Airworthiness, ICA350-31, Revision<br />
B, dated 3rd January 2007, or later approved<br />
revision.2. Prior to ins<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7022 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>440 FAA STC SR<strong>01</strong>439LA BELL 407 Emergency Float Assemblies. Bell Helicopter Textron Canada Limited<br />
Emergency Float Kit P/N 407-350-300-1<strong>01</strong><br />
and/or 407-350-3<strong>01</strong>-1<strong>01</strong> and/or 407-350-302-<br />
1<strong>01</strong> must be installed prior to the installation of<br />
this STC;The intermixed installation<br />
configuration between the following Apical Indu<br />
10<strong>01</strong>7023 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>441 FAA STC SR<strong>01</strong>392LA A, AW119 MKII119 Emergency Float Kits FAA STC SR<strong>01</strong>392LA<br />
dated 21 December 2007.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 78/<strong>462</strong><br />
13.05.2008<br />
15.08.2007<br />
23.<strong>01</strong>.2009<br />
29.<strong>01</strong>.2009<br />
13.03.2008<br />
12.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7081 APICAL INDUSTRIES, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>534 FAA STC SR02180LA AS 350 B, AS 350 B1, AS 350 B2 Installation of a Cable Cutter Kit. 1. Prior to installation of this modification the<br />
23.03.2009<br />
AS 350 B3, AS 350 BA, AS 350 D<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10028171 APICAL INDUSTRIES, Inc. FAA STC SR02244LA BK117 C-2 Title: Emergency Float KitsDescription:<br />
Installation of Apical Industries, Inc. Emergency<br />
FloatKits. This STC is based on the validation<br />
of FAA STC SR02244LA issued21.07.2009.<br />
None None 07.12.2009<br />
10028493 APICAL INDUSTRIES, Inc. FAA STC SR00645LA AS355E, AS355F, AS355F1<br />
AS355F2, AS355N, AS355NP<br />
10029348 APICAL INDUSTRIES, Inc. FAA STC SR02271LA 206A, 206B, 206L, 206L-1,<br />
206L-3, 206L-4<br />
10030503 APICAL INDUSTRIES, Inc. FAA STC SR02289LA BELL 2<strong>04</strong>B<br />
BELL 212, BELL 214B<br />
BELL 214B-1, BELL 205A-1<br />
BELL 412, BELL 412EP<br />
10031793 APICAL INDUSTRIES, Inc. FAA STC SR02307LA EC135 P1(CDS), EC135<br />
P1(CPDS)<br />
EC135 P2(CPDS), EC135 P2+<br />
EC135 T1(CDS), EC135<br />
T1(CPDS)<br />
EC135 T2(CPDS), EC135 T2+<br />
Emergency Float Kit Not Applicable Prior to installation of this modification the 16.03.2<strong>01</strong>1<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
Bell 206 Cable Cutter Kit None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.03.2<strong>01</strong>0<br />
Installation of Cable Cutters Kit in accordance<br />
with Master DocumentList MD412-1<strong>01</strong>,<br />
Revision B, dated May 12, 2<strong>01</strong>0 or later FAA<br />
approvedrevision.<br />
Cable Cutters KitInstallation of Cable Cutters<br />
Kit with deflectors on skids and wiper<br />
inaccordance with Master Document List<br />
MD135-2, based on FAA STCSR02307LA.<br />
10032468 APICAL INDUSTRIES, Inc. REV. 1 FAA STC SR02290LA MBB-BK 117 C-2 Cable Cutters KitInstallation of Cable Cutters<br />
Kit with deflectors on skids and wiper<br />
inaccordance with Master Document List<br />
MD145-2, based on FAA STCSR02290LA.<br />
10034031 APICAL INDUSTRIES, Inc. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>426<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.06.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.09.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
19.11.2<strong>01</strong>0<br />
FAA STC SR0<strong>04</strong>71LA MD600N Emergency Floats None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>01</strong>.03.2<strong>01</strong>1<br />
10034100 APICAL INDUSTRIES, Inc. REV. 1 FAA STC SR02291LA BELL 407 Cable Cutters KitThe Bell 407 Cable Cutter kit<br />
provides a means of protecting thehelicopter<br />
during a wire strike by providing the capability<br />
to cut acable or wire before catastrophic<br />
damage occurs.<br />
10039222 APICAL INDUSTRIES, Inc. AW139 <strong>EASA</strong> Validation of FAA STC No. SR02379LA<br />
"Installation of ApicalIndustries, Inc. Cable<br />
Cutter Kit"<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.03.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.<strong>04</strong>.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 79/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1959 APICAL INDUSTRIES, Inc. FAA STC NO. SR02425LA A119, A119 MK II <strong>EASA</strong> Validation of FAA STC No. SR02425LA None. Prior to installation of this modification it 26.10.2<strong>01</strong>2<br />
"Installation of ApicalIndustries, Inc. Cable<br />
must be determined thatthe<br />
Cutter Kit".<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>2766 APICAL INDUSTRIES, Inc. FAA STC SR02373LA EC130B4 Installation of Fresh Air Vents in accordance<br />
with Apical Industries,Inc. Master Document<br />
List MD130-3. This STC is the validation of<br />
FAA STC SR02373LA (date of<br />
issuanceSeptember 12, 2<strong>01</strong>2).<br />
10<strong>01</strong>6824 APOLLO SPRAY SYSTEMS <strong>EASA</strong>.IM.R.S.<strong>01</strong>194 SR<strong>01</strong>215CH ROBINSON R44 Installation of Apollo Spray system DTM-4<br />
agricultural sprayer onto Robinson R44<br />
helicopter. <strong>EASA</strong> validation of FAA STC<br />
SR<strong>01</strong>215CH<br />
10<strong>04</strong>2428 APPAREO SYSTEMS, L.L.C. FAA STC SR02797CH AS350B1, AS350B2,<br />
AS350B3, AS350BA.<br />
10<strong>01</strong>5635 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.<strong>01</strong>591 FAA STC ST02959AT BOEING 737-300 SERIES<br />
BOEING 737-400 SERIES<br />
BOEING 737-500 SERIES<br />
10<strong>01</strong>5665 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.<strong>01</strong>641 FAA STC SA2890AT FAIRCHILD SWEARINGEN SA<br />
226<br />
FAIRCHILD SWEARINGEN SA<br />
227<br />
10<strong>01</strong>6083 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.02267 FAA STC03354AT BOEING 737-200<br />
BOEING 737-300<br />
10<strong>01</strong>6084 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.02269 FAA ST03356AT BOEING 737-200<br />
BOEING 737-300<br />
10<strong>01</strong>6085 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.02270 REV. 2 FAA ST03362AT BOEING 737-200<br />
BOEING 737-300<br />
10<strong>01</strong>6086 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.02271 FAA STC ST03363AT BOEING 737-200<br />
BOEING 737-300<br />
10<strong>01</strong>6298 ARC AVIONICS CORP. <strong>EASA</strong>.IM.A.S.02595 FAA STC ST03458AT BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Installation of Vision 1000 System in<br />
accordance with Vision 1000 MasterDocument<br />
List 606586-000<strong>01</strong>1This STC is the validation<br />
of FAA STC SR02797CH (date of<br />
issuanceDecember 28, 2009)<br />
Installation of Collins Model 700 High<br />
Frequency (HF) Communication System and<br />
HF Antenna<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.12.2<strong>01</strong>2<br />
Certified in restricted category.All limitations of<br />
RFM supplement apply.<br />
None If the holder agrees to permit another<br />
person to use this certificate tomodify the<br />
product, the holder shall give to the other<br />
person writtenevidence of that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
Installation of a Honeywell Model CAS 67A Prior to installation of this modification the<br />
Traffic Alert and Collision Avoidance System II installer must determine that the<br />
(TCAS II) with Single Mode-S Transponder interrelationship between this modification and<br />
MST 67A iaw FAA STC SA02890AT. any other previously installed modification will<br />
FAIRCHILD SWEARINGEN SA 26<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of a single Universal Avionics Class<br />
“A” TAWS system on 737-300 series aircraft.<br />
12.02.2007<br />
30.11.2<strong>01</strong>2<br />
thatthe interrelations<br />
According to FAA STC ST02959AT 17.11.2005<br />
The aircraft has to be equipped with a<br />
Universal EFIS to display the TAWS terrain.<br />
<strong>EASA</strong> Approved Flight Manual Supplement<br />
ARC Avionics document 730-061505 Rev A<br />
for Boeing 737-300 series aircraft, dated Feb 8<br />
2007 is a part of this STC.<br />
Installation of a dual Universal Avionics UNS- The aircraft have to be equipped with a<br />
1F FMS sys on Boeing 737-300 aircraft Universal Avionics EFIS as it provides the<br />
Installation includes 2 Nav Control Units Navigation Displays and Data Concentrator<br />
(NCU)in the EE bay and 2 GPS antennas. Units M integrate the aircraft sensors and<br />
Center pedestal pilot and co-pilot Control communications. FAA Approved Flight Manual<br />
Display Units (CDU). Nav data can be selected Supplement, ARC Avionics document 730an<br />
120605<br />
Installation of a dual Universal Avionics UNS-<br />
1F Flight ManagementSystem (FMS) or UNS-<br />
1Fw WAAS capabe FMS, on- Boeing 737-200<br />
and 737-300 aircraft without EFIS<br />
(Configuration I)- Boeing 737-300 aircraft with<br />
original Honeywell or Collins<br />
EFIS(Configuration<br />
Installation of a single Universal Avionics Class<br />
“A” TAWS system on 737-200 series aircraft.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
The aircraft has to be equipped with a<br />
Universal EFIS to display in the center pedestal<br />
in order to display the TAWS terrain. This MFD<br />
can be part of this installation, or pre-existing<br />
as the 737-200 series Aircraft. <strong>EASA</strong><br />
Approved Flight manual Supplement<br />
Installation upgrade to replace the existing - AFM Document, ARC Avionics Document<br />
system with either Honeywell or Collins Dual 730-030806, for Boeing 737-300, -400, -500<br />
Enhanced Mode S Transponder system. The series aircraft, dated 2 July 2007, or later<br />
existing Omni directional antenna is compatible <strong>EASA</strong> approved revision.<br />
with the new system and will not be replaced.<br />
The two Honeywell TRA-67A or Col<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 80/<strong>462</strong><br />
05.09.2008<br />
03.07.2007<br />
31.05.2007<br />
28.<strong>04</strong>.2<strong>01</strong>1<br />
27.06.2007<br />
10.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034376 ARCHEION HOLDINGS L.L.C. FAA STC ST03529AT 1. B757-200<br />
Installation of an Avionica satLINK<br />
None Prior to installation of this modification it 30.03.2<strong>01</strong>1<br />
2. B757-300<br />
Communication Management System<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>5815 ARINC INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>886 FAA STC SA00558DE-D BEECH 200, 200C, B200, B200C,<br />
BEECH 300, 300LW, B300,<br />
B300C<br />
10<strong>01</strong>5823 ARMSTRONG AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>895 FAA STC ST<strong>01</strong>872CH B737-200, 737-300, 737-400,<br />
B737-500, 737-600, 737-700,<br />
B737-800, 737-900<br />
Installation of a Pilot and Co-Pilot Digital Air<br />
Data Unit<br />
Installation of a Honeywell RESCU 406AF<br />
Emergency Locator Transmitter (ELT) System<br />
on Boeing 737 Series aircraft<br />
10<strong>04</strong>2075 ARMSTRONG AEROSPACE <strong>EASA</strong>.IM.A.S.00252 MD-90-30 stc-easa.i.m.a.s.00252-aerospace engineering<br />
solutions Installation of a Honeywell RESCU<br />
406AF Emergency Locator<br />
Transmitter.ST<strong>01</strong>997CH in accordance with<br />
Armstrong Aerospace Master Data<br />
ListDocument No. DC1<strong>04</strong>-3063-00, Revision<br />
A, dated 21 June 20<strong>04</strong> or late<br />
10<strong>01</strong>5590 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>5<strong>01</strong> FAA STC ST<strong>01</strong>742CH BOEING 747-400 SERIES<br />
BOEING 747-400D<br />
BOEING 747-400F<br />
10<strong>01</strong>5662 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>639 FAA STC ST<strong>01</strong>773CH BOEING 777-200<br />
BOEING 777-300<br />
Installation of Honeywell RESCU 406AF<br />
Emergency Locator Transmitter (ELT) system<br />
Installation of Honeywell RESCU 406AF<br />
Emergency Locator Transmitter (ELT)<br />
10<strong>01</strong>5664 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>640 FAA STC ST02108CH BOEING 767-300 Installation of Honeywell RESCU 406AF<br />
Emergency Locator Transmitter (ELT)<br />
10<strong>01</strong>5725 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>737 ST02202CH BOEING 757-200 Installation of Honeywell RESCU 406AF<br />
Emergency Locator Transmitter (ELT)<br />
10<strong>01</strong>5789 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>845 ST<strong>01</strong>797CH AIRBUS A320<br />
Installation of a Honeywell RESCU 406 AF<br />
AIRBUS A321<br />
Emergency Locator Transmitter (ELT)<br />
10<strong>01</strong>6211 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02458 FAA ST024<strong>04</strong>CH AIRBUS A318<br />
AIRBUS A319<br />
AIRBUS A320<br />
AIRBUS A321<br />
10<strong>01</strong>6363 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02685 FAA STC ST025<strong>01</strong>CH AIRBUS B4-603<br />
AIRBUS B4-605R<br />
10<strong>01</strong>6553 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02935 FAA STC ST<strong>01</strong>837CH BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
Activation of Honeywell Runway Awareness<br />
and Advisory System (RAAS).<br />
1. Airplane Flight Manual Supplement:AFMS<br />
Document 34-07-0002-00, Revision IR, dated<br />
19 August 20<strong>04</strong> or Document 34-07-0026-00,<br />
Revision IR or later approved revision<br />
isrequired on board for the IS&S ADDU<br />
installation,or, AFMS Document 34-07-0002-<br />
<strong>01</strong>, Revisi<br />
Compatibility of this design change with other<br />
previously approved modifications must be<br />
determined by the installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Instructions for Continued Airworthiness (ICA),<br />
ref. DC113-1020-00, Section 2, revision D,<br />
dated June 17, 2005 or later <strong>EASA</strong> approved<br />
revision<br />
Activation of Honeywell Runway Awareness This STC is only applicable on Honeywell<br />
and Advisory System (RAAS)(Validation of the EGPWS P/N identified through the 'Associated<br />
FAA STC n° ST025<strong>01</strong>CH)This STC consists in Technical Documentation' fitted with the<br />
activating the RAAS function on EGPWS Hardware/Software configuration up to ref :<br />
226/226<br />
Installation of Honeywell RESCU 406AF/AFN Airplane Flight Manual Supplements Armstrong<br />
Emergency Locator Transmitter (ELT) System. Aerospace Doc. No. DC303-1003-00, Rev.C,<br />
approved 4 February 2008 or later approved<br />
revision is required on board of the modified<br />
aircraft.Instruction for Continued Airworthiness,<br />
Armstron Aerospace Doc. No. DC1<br />
02.<strong>01</strong>.2006<br />
25.<strong>04</strong>.2006<br />
1- Subject to compliance with the 15.10.20<strong>04</strong><br />
provisions of Par 21 Subpart E, thisSTC<br />
and associated data shall remain valid<br />
until surrendered, withdrawnor otherwise<br />
terminated 2- If transfer of this Certificate<br />
is requested under Part 21A.116, theSTC<br />
will be reissued<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 81/<strong>462</strong><br />
25.10.2005<br />
25.10.2005<br />
25.11.2005<br />
26.<strong>01</strong>.2006<br />
17.05.2006<br />
31.10.2007<br />
13.05.2008<br />
12.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6554 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02936 FAA STC ST02536CH AIRBUS A330-3<strong>01</strong><br />
Activation of Honeywell Runway Awareness Prior to installation of this modification the<br />
03.09.2008<br />
AIRBUS A330-302<br />
and Advisory System (RAAS).<br />
installer must determine that the<br />
AIRBUS A330-303<br />
interrelationship between this modification and<br />
AIRBUS A330-321<br />
any other previously installed modification<br />
AIRBUS A330-322<br />
will introduce no adverse effect upon the<br />
AIRBUS A330-323<br />
AIRBUS A330-341<br />
AIRBUS A330-342<br />
AIRBUS A330-343<br />
airworthiness of the product.<br />
10<strong>01</strong>6555 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02937 FAA STC ST02537CH AIRBUS A340-311<br />
Activation of Honeywell Runway Awareness Prior to installation of this modification the<br />
08.<strong>01</strong>.2009<br />
AIRBUS A340-312<br />
and Advisory System(RAAS)<br />
installer must determine that the<br />
AIRBUS A340-313<br />
interrelationship between this modification and<br />
AIRBUS A340-642<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10029877 ARMSTRONG AEROSPACE Inc. FAA STC ST02776CH B737-300, B737-500 Activation of Honeywell Runway Awareness None Prior to installation of this modification it 28.<strong>04</strong>.2<strong>01</strong>0<br />
and Advisory System (RAAS)<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031966 ARMSTRONG AEROSPACE Inc. FAA STC ST02778CH 747-400, 747-400 (BCF)<br />
747-400F<br />
10031995 ARMSTRONG AEROSPACE Inc. FAA STC ST02376CH ATR72-2<strong>01</strong>,ATR72-202,ATR72-<br />
212<br />
Activation of Honeywell Runway Awareness &<br />
Advisory System (RAAS) inaccordance with<br />
Armstrong Aerospace Master Data List DOC<br />
No.DC1<strong>04</strong>-7007-00 Revision D,dated<br />
November 9,2009 or later FAA aproved<br />
revision.Validation of FAA STC ST02778CH<br />
<strong>EASA</strong> Validation of FAA STC ST02376CH (as<br />
amended by FAA on 24th June2<strong>01</strong>0)<br />
regarding: Installation of a Rockwell Collins HF-<br />
9000 HF Radio System in accordancewith<br />
Armstrong Aerospace Master Data List, Doc.<br />
Number DC1<strong>04</strong>-4033-00,Revision E, dated<br />
27th May 2<strong>01</strong><br />
10034747 ARMSTRONG AEROSPACE Inc. FAA STC ST02939CH-D B737-800 Validation of FAA STC ST02939CH-<br />
DPANASONIC DMPES - In flight<br />
Entertainment System installation<br />
None Armstrong Aerospace Airplane Flight<br />
Manual Supplement for B747-400series<br />
aircraftDoc. No. DC303-7007-00 Rev.- is<br />
required on board the aircraft.<br />
27.09.2<strong>01</strong>0<br />
None After the analysis performed by<br />
Armstrong Aerospace in accordance<br />
withSpecial Condition <strong>EASA</strong> CRI H-0<strong>01</strong><br />
no additional specific EWIS ICAS<br />
taskshave been identified for this <strong>EASA</strong><br />
STC validation with regards thosealready<br />
identified and approved to the original<br />
30.09.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.<strong>04</strong>.2<strong>01</strong>1<br />
10038436 ARMSTRONG AEROSPACE Inc. FAA STC ST02947CH B737-800 Validation of FAA STC ST02947CH:<br />
1) Modification in accordance with this STC It must be determined that the activation 02.03.2<strong>01</strong>2<br />
Installation and activation of aPanasonic Global requires prior or concurrentmodification in of the Panasonic GlobalCommunications<br />
Communications Suite (GCS) system in accordance with <strong>EASA</strong> STC 10038435.2 )The Suite (GCS) System Provisions (<strong>EASA</strong><br />
accordance withArmstrong Aerospace Master activation of the Panasonic Global<br />
STC 10038435) inaccordance with this<br />
Data List DC1<strong>04</strong>-9<strong>04</strong>3-00, Revision A, dated Communications Suite (GCS)System STC and their interrelationships between<br />
22December 2<strong>01</strong>1.<br />
Provisions (<strong>EASA</strong> STC 10038435) in and anyother previously installed STC,<br />
accordance with this STC<br />
modification and / or r<br />
10<strong>04</strong>0305 ARMSTRONG AEROSPACE Inc. FAA STC ST03085CH B747-400 Installation of provisions for Panasonic Global<br />
Communications Suite(GCS) System in<br />
accordance with Armstrong Aerospace Inc.<br />
Master DataList DC1<strong>04</strong>-9027-00 Rev. D dated<br />
April 25, 2<strong>01</strong>2, or later<br />
approvedrevision.Validation of FAA STC<br />
ST03085CH<br />
10<strong>04</strong><strong>04</strong>70 ARMSTRONG AEROSPACE Inc. FAA STC ST02948CH 767-300 Installation of Board Connect In-Flight<br />
Entertainment System<br />
None -These provisions are for a Panasonic<br />
Global Communications Suite<br />
(GCS)System. The installation and<br />
activation of the GCS system is to be<br />
inaccordance with a separate approval.<br />
Additional approval is required forthe<br />
installation of additional GCS system eq<br />
This system is intended to provide internet<br />
connection and e-mailservices using portable<br />
electronic devices (PEDs). Any other<br />
intendedfunction of this equipment will require<br />
further certification approval.<br />
22.06.2<strong>01</strong>2<br />
Prior to installation of this modification it 05.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 82/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0513 ARMSTRONG AEROSPACE Inc. FAA STC ST03<strong>04</strong>7CH B747-400 Certification of Compatibility with Cellular and This STC may only be applied to an aircraft Prior to installation of this modification it 06.07.2<strong>01</strong>2<br />
Wireless DataTechnologies in accordance with when an airplane installedbase station using must be determined thatthe<br />
Armstrong Aerospace Master Data List,Doc. the cellular technologies is concurrently interrelationship between this modification<br />
No. DC1<strong>04</strong>-9026-00 Revision C, dated June installedin accordance <strong>EASA</strong> Form 96 Post-TC and any other previouslyinstalled<br />
28, 2<strong>01</strong>2 or later approvedrevision.Validation of Technical Visa <strong>Page</strong> 4/5 Issue 4,<strong>01</strong>/05/2<strong>01</strong>0 modification and/ or repair will introduce<br />
FAA STC ST03<strong>04</strong>7CH<br />
with a separate approval.This STC does no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1316 ARMSTRONG AEROSPACE Inc. FAA STC ST03086CH B747-400 Installation and activation of a Panasonic None Modification of the aircraft in accordance 06.09.2<strong>01</strong>2<br />
Global Communication Suite(GCS) System in<br />
with this STC requires prioror concurrent<br />
accordance with Armstrong Aerospace Master<br />
modifications in accordance with FAA<br />
Data ListDoc. No. DC 1<strong>04</strong>-9034-00 Revision D,<br />
STC’s ST03<strong>04</strong>7CH andST03085CH. The<br />
dated May 14, 2<strong>01</strong>2 or later FAAapproved<br />
Panasonic eXPhone system equipment<br />
revisionValidation of FAA STC ST03086CH<br />
for which certain provisions inthis<br />
modification are intended has<br />
10<strong>04</strong>2211 ARMSTRONG AEROSPACE Inc. FAA STC ST02314CH A319-131, A319-133<br />
A320-232, A321-232<br />
10<strong>04</strong>2212 ARMSTRONG AEROSPACE Inc. FAA STC ST02314CH A319-111,-112,-113,-114,-115<br />
A319-131,-132,-133<br />
A320-111,-211,-212,-214,-231<br />
A320-232,-233<br />
A321-231,-232<br />
10<strong>01</strong>6057 AS&T AEROSPACE SYSTEM &<br />
TECHNOLOGIE<br />
10<strong>01</strong>6058 AS&T AEROSPACE SYSTEM &<br />
TECHNOLOGIE<br />
10<strong>01</strong>6257 AS&T AEROSPACE SYSTEM &<br />
TECHNOLOGIE<br />
<strong>EASA</strong>.IM.A.S.02234 FAA STC SA755GL CESSNA 206H<br />
CESSNA T206H<br />
CESSNA TU206G<br />
CESSNA U206F<br />
CESSNA U206G<br />
<strong>EASA</strong>.IM.A.S.02235 FAA STC SA<strong>01</strong>338WI CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA 182S<br />
CESSNA 182T<br />
CESSNA R182<br />
CESSNA T182<br />
CESSNA TR182<br />
<strong>EASA</strong>.IM.A.S.02535 FAA STC SA<strong>01</strong>328WI PIPER PA-32-3<strong>01</strong>FT (PIPER 6X)<br />
PIPER PA-32-3<strong>01</strong>XTC (PIPER<br />
6XT)<br />
PIPER PA-32R-3<strong>01</strong><br />
PIPER PA-32R-3<strong>01</strong>T<br />
<strong>EASA</strong> validation of FAA STC ST02377CH<br />
"Installation of a Rockwell CollinsTailwind 560<br />
Satellite System and modification of a Thales<br />
Top Seriesi3000/i4000 In flight Entertainment<br />
(IFE) System"<br />
<strong>EASA</strong> validation of FAA STC ST02314CH<br />
"Installation of an Aft Cargo BayEquipment<br />
Rack"<br />
Installation of TKS Ice Protection Systems<br />
Components on a no-hazard / no credit basis.<br />
Installation of TKS Ice Protection Systems<br />
Components on a no-hazard / no credit basis<br />
Installation of TKS Ice Protection Systems<br />
Components on no-hazard / no credit basis.<br />
10031933 ASI INNOVATION T206H ASI-fam-0009-<strong>01</strong> Installation of FLIR MX10<br />
mechanical provision on T206Haircraft<br />
100329<strong>04</strong> ASI INNOVATION F406 ASI-FAM-0<strong>01</strong>5-02 Provision installation of<br />
console PMR/DMR and UHFantenna<br />
- The FAA STC ST02314CH validated through<br />
<strong>EASA</strong> STC Approval 10<strong>04</strong>2211 forAft Cargo<br />
Bay Equipment Rack Installation must be<br />
installed on aircraftprior or in conjunction with<br />
this STC design change.<br />
Prior to installation of this modification it 15.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.11.2<strong>01</strong>2<br />
1. This installation is not approved for flight into<br />
known icing conditions.2. A placard must be<br />
fitted on the upper control panel in front of the<br />
pilot, stating “FLIGHT INTO KNOWN ICING<br />
CONDITIONS IS PROHIBITED”. 3. This<br />
installation is approved on a no-h<br />
1. This installation is not approved for flight into<br />
known icing conditions.2. A placard must be<br />
fitted on the upper control panel in front of the<br />
pilot, stating "FLIGHTINTO KNOWN ICING<br />
CONDITIONS IS PROHIBITED".3. Applicable<br />
serial numbers: 182P: S/N 1826<br />
1. This installation is not approved for flight into<br />
known icing conditions.2. A placard must be<br />
fitted on the upper control panel in front of the<br />
pilot, stating “FLIGHT INTO KNOWN ICING<br />
CONDITIONS IS PROHIBITED”.3. This<br />
installation is approved on a no-ha<br />
Limitation to Cessna T206H serial number 445<br />
and 446<br />
Limited to: F406 S/N 006-<strong>01</strong>7-025-039-<strong>04</strong>2-<br />
070-074-075-077-086<br />
<strong>04</strong>.<strong>01</strong>.2007<br />
08.12.2006<br />
27.08.2007<br />
Prior to installation of this modification it 23.09.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 07.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 83/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035229 ASI INNOVATION T206H ASI-FAM-0002-<strong>01</strong> Installation of Flir MX10 on Limitation to Cessna T206H serial numbers Prior to installation of this modification it 07.06.2<strong>01</strong>1<br />
Cessna T206H.<br />
445 and 446.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039405 ASI INNOVATION CESSNA F150L, FA150L ASI-FAM-082-<strong>04</strong> - Installation of EFIS Aspen<br />
EFD 1000 on Cessna 150<br />
10<strong>04</strong>0616 ASI INNOVATION 1. C90, C90A, C90GT, C90GTI<br />
2. B90, E90<br />
10<strong>04</strong>0891 ASI INNOVATION P2006T ASI-0084-03 dated 30 July 2<strong>01</strong>2 - Installation<br />
of removable missionconsole (without<br />
equipments) in the aircraft cabin in place of<br />
passengerseat.<br />
10<strong>04</strong>0999 ASI INNOVATION EMB-135LR Oven installationDescription as per:ASI SDL,<br />
STC Data List ref. ASI-SDL-0087-03, dated<br />
<strong>01</strong>/08/2<strong>01</strong>2.ASI MDL, Master Drawing List ref.<br />
ASI-MDL-0087-<strong>01</strong>, dated <strong>01</strong>/08/2<strong>01</strong>2.ASI<br />
Technical Dossier ref. ASI-TD-0087-02, dated<br />
<strong>01</strong>/08/2<strong>01</strong>2.<br />
10<strong>04</strong>1603 ASI INNOVATION EMB-120ER "P-RNAV Certification"Description as per<br />
documents in "Associated Technical<br />
Documentation".<br />
10<strong>04</strong>1778 ASI INNOVATION EMB-135LR Cabin interior modification.Description as per<br />
Associated Technical Documentation.<br />
The EFD 1000 must not be used as primary Prior to installation of this modification it 02.05.2<strong>01</strong>2<br />
flight and navigation source.Independent and must be determined thatthe<br />
dissimilar instruments must be installed for interrelationship between this modification<br />
primaryindication of attitude, altitude, airspeed, and any other previouslyinstalled<br />
vertical speed, magneticheading and modification and/ or repair will introduce<br />
navigation data, as required for day a no adverse effectupon the airworthiness<br />
of the product.<br />
VHF, UHF and GPS antennas installation This change is applicable to aircraft:-B90 S/N Prior to installation of this modification it 13.07.2<strong>01</strong>2<br />
provisions according to ASImodification no ASI- LJ-318 to LJ-5<strong>01</strong>-C90 S/N LJ-502 to LJ-1062- must be determined thatthe<br />
FAM-0096-00<br />
C90A S/N LJ-1062 to LJ-1726, LJ-1727 to LJ- interrelationship between this modification<br />
1753 and LJ-1755-C90GT S/N LJ-1727, LJ- and any other previouslyinstalled<br />
1754, LJ-1756 and after-C90GTi S/N LJ-1847, modification and/ or repair will introduce<br />
LJ-1853 and after-E90 S/N LW-1 and after no adverse effectupon the airworthiness<br />
of the product.<br />
This STC shall be used only by ASI Innovation. Prior to installation of this modification it <strong>01</strong>.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Applicability limited to EMB-135LR S/N 886 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.08.2<strong>01</strong>2<br />
Applicability restricted to the following S/Ns:<br />
<strong>01</strong>2, <strong>01</strong>3, 027, 158.<br />
None. <strong>01</strong>.10.2<strong>01</strong>2<br />
Applicability limited to EMB-135LR S/N 886. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.10.2<strong>01</strong>2<br />
10<strong>04</strong>2<strong>04</strong>5 ASI INNOVATION E90 Mast with relay antenna installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.11.2<strong>01</strong>2<br />
10<strong>04</strong>2513 ASI INNOVATION ATR 42-300 Radio Honeywell HF 950 Installation This<br />
modification consists in installing the<br />
Bendix/King KHF950 HF/SSBCommunication<br />
System. This includes mainly the embodiment<br />
of HF antenna,control unit, receiver, amplifier<br />
coupler and electrical protection.<br />
10<strong>01</strong>6994 ASI SERVICES <strong>EASA</strong>.IM.R.S.<strong>01</strong>403 FAA STC SH296NM BELL 206L-1 Installation of a Rolls Royce model 250-C30P Prior to installation of this modification the<br />
engine and associated airframe and tail rotor installer must determine that the<br />
control modifications similar to the Model 206L- interrelationship between this modification and<br />
3. This STC has been classified as “BASIC” by any other previously installed modification<br />
the FAA and has been approved under the will introduce no adverse effect upon the<br />
PTVP.<br />
airworthiness of the product.<br />
This Modification is limited to MSN 148. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.12.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 84/<strong>462</strong><br />
06.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5758 ASSOCIATED AIR CENTER <strong>EASA</strong>.IM.A.S.<strong>01</strong>793 FAA STC ST10546SC AIRBUS A319-115 VIP Cabin modification This STC is limited to the A319 CJ MSN<br />
2592.Instructions for Continued Airworthiness<br />
(ICAW), Chapter 3 "Airworthiness Limitations"<br />
ref. 2350050090, revision A dated June 8,<br />
2006 or later <strong>EASA</strong> approved revision.<br />
13.06.2006<br />
10<strong>01</strong>5490 ASSOCIATED AIR CENTER, L.P. <strong>EASA</strong>.IM.A.S.<strong>01</strong>252 FAA STC ST1<strong>04</strong>74SC AIRBUS A319-133 Installation of an Executive Style Interioracc.:<br />
MDL 2300000091 Rev. D<br />
10<strong>01</strong>5924 ASSOCIATED AIR CENTER, L.P. <strong>EASA</strong>.IM.A.S.02059 REV. 2 FAA STC ST10593SC AIRBUS A319-115 Revision to <strong>EASA</strong> STC reference<br />
<strong>EASA</strong>.IM.A.S.02059 - Introduction of revised<br />
Instructions for Continued Airworthiness.STC<br />
<strong>EASA</strong>.IM.A.S.02059 - Installation of an<br />
Executive Style Interior (reference FAA STC<br />
ST10593SC dated 6 February 2007).First<br />
10<strong>01</strong>5975 ASSOCIATED AIR CENTER, L.P. <strong>EASA</strong>.IM.A.S.02126 FAA STC ST10613SC AIRBUS A319-115<br />
installation i<br />
Executive style interior (validation of FAA STC<br />
ST10613SC)<br />
10<strong>01</strong>6150 ASSOCIATED AIR CENTER, L.P. <strong>EASA</strong>.IM.A.S.02352 FAA STC ST10536SC AIRBUS A319-115 Installation of an Executive Style Interior in<br />
accordance with Master Document List,<br />
Document Number 2459000000, Revision IR,<br />
dated25 October 2007, or later <strong>EASA</strong><br />
approved revision.First installation is on MSN<br />
2837<br />
10027816 ASSOCIATED AIR CENTER, L.P. P-<br />
<strong>EASA</strong>.IM.A.S.03147<br />
REV. 1 FAA STC ST10895SC-D A319-115 Major Change to the <strong>EASA</strong> STC 10027816<br />
(FAA STC ST10895SC-D) to introducethe<br />
Decrane's side facing divan (FAA STC<br />
ST<strong>01</strong>450CH) within the"Executive Style<br />
Interior" configuration.<br />
1) Ref.: 2300021090 Rev. IR2) Limited to S/N<br />
2192Note: The airplane is limited to private use<br />
only unless the cabin door is rendered<br />
inoperable.<br />
1. The aircraft is limited to Private use only (not<br />
to be operated for hire, reward or common<br />
carriage).2. This STC is approved only for the<br />
product configuration as defined in the above<br />
Master Document List.3. Limitations and<br />
Conditions specified in FAA S<br />
Instruction for Continued Airworthiness,<br />
Chapter 3 "Airworthiness Limitation", ref.<br />
2393050090, dated March 8, 2007 or later<br />
approved revision<br />
The aircraft is limited to Private use only (not to<br />
be operated for hire, reward or common<br />
carriage).This STC is approved only for the<br />
product configuration as defined in the above<br />
Master Document List.Limitations and<br />
Conditions specified in FAA STC ST1053<br />
This approval is limited only to the installation<br />
made in Airbus ModelNumber A319-115,<br />
Serial Number 3133<br />
10030326 ASSOCIATED AIR CENTER, L.P. FAA STC ST10900SC-D A319-115 Installation of an Executive Interior This approval is limited to only the installation<br />
made in Airbus ModelNumber A319-115,<br />
Serial Number 3957Airworthiness Limitation<br />
10035731 ASSOCIATED AIR CENTER, L.P. REV. 1 FAA STC ST10906SC-D A319-115 Installation of an Executive Style Interior<strong>EASA</strong><br />
validation of FAA STC ST10906SC-D<br />
10035915 ASSOCIATED AIR CENTER, L.P. FAA STC ST10903SC-D A319-133 Modification of an Executive Interior<strong>EASA</strong><br />
Validation of FAA STC ST10903SC-D<br />
10036081 ASSOCIATED AIR CENTER, L.P. REV. 2 FAA STC ST10897SC-D B737-700 Change to <strong>EASA</strong> STC 0<strong>01</strong>0036081<br />
(Installation of an Executive Interior<br />
onB737700IGW aircraft : Project No.AAC-08-<br />
06-DAS): Installation of theERDA Model 4402<br />
Single occupant Side facing divan.<br />
inspection to be performed in all the locationsof<br />
the Cabin Interior Primary Structure Elements<br />
attachments for every3000 FC u<br />
21.11.2005<br />
14.05.2009<br />
19.03.2007<br />
30.10.2007<br />
Prior to installation of this modification it 11.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 10.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
restricted to MSN 3542 As per FAA STC ST10906SC-DPrior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
effectupon the airworthin<br />
Restricted to MSN 910 As per FAA STC ST10903SC-DPrior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
effectupon the airworthin<br />
1) This approval is limited to Aircraft B737-700,<br />
Serial number 36027.2) The aircraft operator<br />
must perform the instructions for<br />
continuedairworthiness and comply with the<br />
Airworthiness Limitation Items as perthe<br />
Instruction Continued Airworthiness, Refere<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 85/<strong>462</strong><br />
19.07.2<strong>01</strong>1<br />
27.07.2<strong>01</strong>1<br />
29.06.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2309 ASSOCIATED AIR CENTER, L.P. FAA STC ST10913SC A319-133 Validation of FAA STC ST10913SC - This modification is applicable to MSN 4992. Prior to installation of this modification it 22.11.2<strong>01</strong>2<br />
Installation of an Executive interior.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6730 ASTEC HELICOPTER SERVICES AS <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>04</strong>8 - S-61N Installation of Honeywell MST 67A Mode S<br />
Transponder<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>7091 ASTEC HELICOPTER SERVICES AS <strong>EASA</strong>.R.S.<strong>01</strong>002 REV. 1 AS 332L, AS 332L1, AS 332L2 Skywatch SKY-497 Traffic Advisory System 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>7092 ASTEC HELICOPTER SERVICES AS <strong>EASA</strong>.R.S.<strong>01</strong>003 REV. 1 Techtest CPI-503 ELT 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6500 ASTRONICS ADVANCED ELECTRONIC <strong>EASA</strong>.IM.A.S.02862 FAA STC ST02535AT BOEING 747-400 Installation of a General Dynamics EmPower Prior to installation of this modification the<br />
AC In-Seat powerSupply System on a Boeing installer must determine that the<br />
747-400 type aircraft in accordance with interrelationship between this modification and<br />
Master Drawing list MDL1091-3, Rev. C, dated any other previously installed modification will<br />
August 6, 2002, or later FAA approved revision introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4147 ATELIER CHABORD <strong>EASA</strong>.A.S.<strong>01</strong>266 APEX DR 400/100<br />
APEX DR 400/120<br />
APEX DR 400/120A<br />
APEX DR 400/120D<br />
APEX DR 400/125<br />
APEX DR 400/2+2<br />
10037356 ATELIER CHABORD F150F, F150G, F150H, F150J<br />
F150K, F150L, F150M<br />
FA150K, FA150L, FA150M<br />
10039166 ATELIER CHABORD REV. 1 CESSNA 172R, 172S Exhaust system and silencer for general<br />
aviation aeroplanes<br />
10<strong>01</strong>6626 ATLANTIC AERO INC <strong>EASA</strong>.IM.A.S.03061 FAA STC ST00026AT CESSNA 208 Installation of Passenger Interior And Cargo<br />
Door Modification inCessna Caravan (Cargo<br />
Conversion)<br />
10<strong>01</strong>6627 ATLANTIC AERO INC <strong>EASA</strong>.IM.A.S.03062 FAA STC SA00<strong>01</strong>54AT CESSNA 208<br />
CESSNA 208A<br />
CESSNA 208B<br />
22.11.2005<br />
18.11.2005<br />
15.11.2005<br />
23.07.2008<br />
nstallation of exhaust system and silencer 02.12.2005<br />
STC CESSNA150-11-<strong>01</strong> Rev E - Dispositif de Tout Reims Aviation Cessna F150F a M. Prior to installation of this modification it 22.11.2<strong>01</strong>1<br />
boite de réchauffagecarburateur additionnel sur FA150K a M modifié selon le STC38-SF-00<strong>01</strong> must be determined thatthe<br />
ensemble collecteur d'échappement et ou toute révision ultérieure.<br />
interrelationship between this modification<br />
silencieux.<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Cabin Windows in the Cargo<br />
versions of Cessna 208 series<br />
10028652 ATLANTIC AERO, Inc. FAA STC ST02635AT LEARJET 35, 35A, 36, 36A Deactivation of Aeronca (Learjet) Thrust<br />
Reversers<br />
10029557 ATLANTIC AERO, Inc. FAA STC SA<strong>01</strong>539AT-D 206, P206, P206A, P206B, P206D Installation of a Remote Mounted Oil Cooler in<br />
P206E, TP206A, TP206C, accordance with AtlanticAero Inc. Master<br />
TP206D<br />
Drawing List 166930<strong>01</strong>, Rev. Basic, dated<br />
TU206C, TU206D, TU206E, December 5,1997 or later FAA approved<br />
TU206F<br />
revision in accordance with FAA<br />
TU206G<br />
U206, U206A, U206B, U206C,<br />
U206D, U206E, U206F, U206G,<br />
STCSA<strong>01</strong>539AT-D<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.<strong>04</strong>.2<strong>01</strong>2<br />
- 16.12.2008<br />
15.12.2008<br />
Not Applicable Not Applicable <strong>01</strong>.02.2<strong>01</strong>0<br />
None None <strong>01</strong>.<strong>04</strong>.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 86/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1533 ATLANTIC AERO, Inc. FAA STC SA03931AT-D TBM 700 A/B/C1/C2/N Installation of modified battery heat shield None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The EA<br />
25.09.2<strong>01</strong>2<br />
10<strong>01</strong>4073 ATLANTIC AEROENGINEERING <strong>EASA</strong>.A.S.<strong>01</strong>165 BAE JETSTREAM 3100 Installation of a Honeywell MK-VI GPWS &<br />
LIMITED<br />
Honeywell RT 300 Radio Altimeter<br />
10<strong>01</strong>3952 ATS INTERNATIONAL <strong>EASA</strong>.A.S.0<strong>04</strong>51 REV 1 DC-9-80 (MD-80) SERIES Mk VII EGPWS System Installation This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>3979 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>0<strong>04</strong> BOEING 737-200-200C installation of a Class A Terrain Awareness AFMS : 0200-<strong>01</strong>-A-23<strong>01</strong>-R00.ADSS<br />
Warning System (TAWS), based on an (Airworthiness Data Sheet Supplement)<br />
Honeywell EGPWS MK VII System, aboard including ICA (Instructions for Continued<br />
Boeing 737-200aircraft equipped with external Airworthiness): 0200-<strong>01</strong>-A-2203-R00.This STC<br />
GPS source.<br />
is limited to Terrain display configuration 1 :<br />
Honeywell PPI-4B or Collins WXI 7<strong>01</strong>/711.<br />
10<strong>01</strong>4033 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>103 BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Installation of an Artex Emergency Locator<br />
Transmitter<br />
10<strong>01</strong>4053 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>135 42-320-300<br />
121.5/243/406 MHz Emergency Locator<br />
AEROSPATIALE ATR 42-300<br />
AEROSPATIALE ATR 72-2<strong>01</strong><br />
AEROSPATIALE ATR 72-202<br />
AEROSPATIALE ATR 72-211<br />
AEROSPATIALE ATR 72-212<br />
ATR 72-1<strong>01</strong>-102-2<strong>01</strong>-202-211-212<br />
Transmitter Installation.<br />
10<strong>01</strong>4120 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>230 REV 2 AIRBUS A318-319-320-321 MK V EGPWS System Installation <strong>01</strong>.03.2006<br />
10<strong>01</strong>4125 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>235 AIRBUS A319-320-321 ELT antenna installation on A320 family 30.05.2005<br />
10<strong>01</strong>4182 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>319 BOEING 767-200<br />
BOEING 767-300<br />
Installation of Enhanced Mode S Surveillance 25.<strong>01</strong>.2006<br />
10<strong>01</strong>4183 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>320 B757 Installation of emergency Locator Transmitter -- 16.10.2006<br />
10<strong>01</strong>4235 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>398 BOEING 737-300 ATLAS Standard Galleys Installation. 18.10.2005<br />
10<strong>01</strong>4363 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>631 REV 1 DC-10 SERIES Installation of a Honeywell Enhanced Ground 1) Approval of this change in type design<br />
20.12.2006<br />
Proximity Warning System MK VII.The FAA applies to the above model aircraft equipped<br />
has processed a similar application for an STC with either a Flight Management System<br />
for a similar installation under project n°: (FMS), which meets AC90-45A, a Global<br />
ST00536E.<br />
Positioning System (GPS) navigational based<br />
system or an EGPWS equipped with an<br />
internal GPS<br />
10<strong>01</strong>4402 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>697 BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
TCAS II Change 7 System Installation 22.05.2006<br />
10<strong>01</strong>4410 ATS INTERNATIONAL <strong>EASA</strong>.A.S.<strong>01</strong>706 REV 1 DC-9-82<br />
Elementary and Enhanced Surveillance<br />
27.02.2007<br />
DC-9-83 (MD-83)<br />
Installation<br />
10<strong>01</strong>4<strong>462</strong> ATS INTERNATIONAL <strong>EASA</strong>.A.S.02522 REV 1 Mode S Elementary and Enhanced surveillance 30.06.2006<br />
10<strong>01</strong>4503 ATS INTERNATIONAL <strong>EASA</strong>.A.S.02573 AIRBUS A300 MODEL B2<br />
AIRBUS A300 MODEL B4<br />
MK7 EGPWS Installation on A300 B2- Instructions for Continued Airworthiness are<br />
B4Config 1: EGPWS with Dual FPI-910Config described in the Airworthiness Data Sheet<br />
2: EGPWS with Dual PPI-4BConfig 3: Supplement ADSS <strong>01</strong>21-<strong>01</strong> - A-2203-R05 or<br />
EGPWS with Dual PPI-4B and reactive later <strong>EASA</strong> approved revision.<br />
Windshear<br />
10<strong>01</strong>4762 ATS INTERNATIONAL <strong>EASA</strong>.A.S.02952 A310 Elementary and Enhanced Surveillance This STC is approved only for the product<br />
installation on A310 aircraft.This STC has been configuration as defined in the approved design<br />
developed for the Mode S<br />
data referred to in paragraph ‘Description’.<br />
elementary/enhanced surveillance installation Compatibility with other aircraft/engine<br />
on A310 aircraft.<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5553 AVCON DIVISION/BUTLER NATIONAL <strong>EASA</strong>.IM.A.S.<strong>01</strong>449 FAA STC SA2479CE LEARJET 35, 35A, 36, 36A Installation of dual openable hatches on the<br />
CORP<br />
belly of the fuselage.<br />
10<strong>01</strong>5672 AVCON INDUSTRIES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>650 ST<strong>01</strong>195WI LEARJET 24<br />
LEARJET 35<br />
LEARJET 36<br />
Learjet 20 Series RVSMLearjet 35/36 Series<br />
RVSM<br />
06.<strong>04</strong>.2005<br />
21.03.2006<br />
26.07.2005<br />
18.03.2005<br />
24.03.2005<br />
03.<strong>01</strong>.2006<br />
02.<strong>04</strong>.2007<br />
20.02.2006<br />
As detailed in the AFM 08.03.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 87/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036439 AVCON INDUSTRIES, Inc. FAA STC SA0<strong>04</strong>15WI 100, A100, A100A, A100C, B100 Installation of Baggage Door. None Prior to installation of this modification it 08.09.2<strong>01</strong>1<br />
200, 200T, A200, B200, B200T<br />
must be determined thatthe<br />
300, 300LW, B300<br />
interrelationship between this modification<br />
B90, C90, C90A, E90, H90<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>6623 AVIATION CONSULTING &<br />
ENGINEERING<br />
<strong>EASA</strong>.IM.A.S.03054 FAA STC SA<strong>01</strong>282WI CESSNA 525 Installation of Replacement of Seat Cushions. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>4067 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.<strong>01</strong>154 REV. 2 BEECH 200<br />
BEECH B200<br />
10<strong>01</strong>4068 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.<strong>01</strong>155 BEECH 200<br />
BEECH B200<br />
Installation of an Emergency Locator ELT 96 -<br />
406 MhZ.<br />
Installation of 2 Mode S transponders MST<br />
67A.<br />
This STC is limited to Beechcraft 200 MSN BB<br />
199, Beechcraft B200 MSN BB920 and<br />
Beechcraft 200 s/n BB439.<br />
1. This STC requires a pre-modification: 2<br />
bottom transponder antennas.2. This STC is<br />
limited to Beech s/n BB199 and Beech 200 s/n<br />
BB439.<br />
This STC is limited to Beechcraft C90 s/n<br />
LJ860 and Beechcraft E90 s/n LW251.<br />
10<strong>01</strong>4069 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.<strong>01</strong>157 BEECH C90<br />
Installation of an Emergency Locator ELT 96-<br />
BEECH E90<br />
406 MhZ.<br />
10<strong>01</strong>4070 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.<strong>01</strong>158 BEECH C90 Installation of Mode S Transponder MST 67A. 1. This STC requires a pre-modification: 2<br />
bottom transponders antennas.2. This<br />
Modification is limited to Beechcraft C90 s/n<br />
LJ860.<br />
10<strong>01</strong>4146 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.<strong>01</strong>265 BEECH C90 Replacement of Primus 40 weather radar by a This STC is limited to Beechcraft C90 s/n<br />
Primus weather Radar.<br />
LJ860.<br />
10<strong>01</strong>4212 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.<strong>01</strong>370 BEECH 58 Installation of emergency locator transmitter Modification limited to s/n TH-647The AFMS<br />
ELT 96-406 MHz in accordance with<br />
No. 1 / AvDef Beech 58 must be used with this<br />
modification file AVD-MB58-23-<strong>04</strong>4A. modification.<br />
10<strong>01</strong>4584 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02691 REV. 1 FALCON 20<br />
AVD-MDA20-95-054B: Installation of new age 1. Limitations iaw SAFM FALC20 apply for<br />
FAN JET<br />
Alkan Pylon6075(76)C006<br />
operation with AVDMDA20-95-054B2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previously<br />
installed modification will intr<br />
10<strong>01</strong>4585 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02692 MYSTERE FALCON 20 AVD-MDA20-95-055A: Installation of underwing<br />
stores<br />
10<strong>01</strong>4586 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02693 MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
STRUCTURAL INSTALLATION OF A FUGRO<br />
GPS ANTENNA ON THE FUSELAGE<br />
1. Limitations iaw AFM Supplement SAFM-<br />
FALC20 to DTM 918 apply for operation with<br />
POD installation iaw AVD-MDA20-95-055A2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany o<br />
Compatibility with previous approved<br />
modifications shall be determined by the<br />
installer.<br />
10<strong>01</strong>4587 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02694 MYSTERE FALCON 20 AVD-MDA20-25-050A: Installation of consoles<br />
in cabin.<br />
10<strong>01</strong>4639 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02785 MYSTERE FALCON 20 AVD-MDA20-49-053A: Additional Power Bus Limitations iaw AFM supplement to DTM 918 -<br />
using APU generation, installation of 2 AFMS FA20 apply for operation with additional<br />
additional inverters.<br />
inverters installed iaw AVD-MDA20-49-053A.<br />
10<strong>01</strong>4724 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.029<strong>01</strong> FALCON 10 AVD-MDA10-34-060A: installation of EGPWS<br />
Mark VIII<br />
10<strong>01</strong>4730 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02909 REV. 1 FALCON 20 AVD-MDA20-95-057A: Activation of the SETHI<br />
2 missionAVD-MDA20-95-054B: RAMHY<br />
Project - VHF/UHF Atenna<br />
Limitations iaw AFM Supplement Supavd1 to<br />
DTM 721 apply for operation with EGPWS<br />
installation iaw AVD-MDA10-34-060A.TGL 12<br />
complied with.Cert basis FAR 25 Amdt 20.<br />
1. This STC ensures proper isolation of<br />
Payload (SETHI Mission Equipment) from /<br />
return to - civil configuration in case of<br />
inadvertent activation.2. Activated SETHI<br />
Mission Equipment is not approved by<br />
<strong>EASA</strong>.3. Limitations iaw AFM Supplement<br />
10<strong>01</strong>4760 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02950 BEECH 200 Installation of two 8.33 kHz VHF<br />
SAFM-FALC20 to<br />
This STC is limited to the S/N BB199 and<br />
BB920<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 88/<strong>462</strong><br />
03.12.2008<br />
15.03.2005<br />
28.07.2005<br />
28.07.2005<br />
22.07.2005<br />
28.07.2005<br />
21.<strong>04</strong>.2006<br />
24.11.2008<br />
24.11.2008<br />
23.<strong>04</strong>.2007<br />
15.11.2007<br />
10.<strong>01</strong>.2008<br />
26.11.2007<br />
18.12.2008<br />
<strong>04</strong>.<strong>04</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4783 AVIATION DEFENSE SERVICE (AVdef) <strong>EASA</strong>.A.S.02981 FALCON 20 Enhanced Surveillance Mode S Transponder Major change applicaable to aircraft Fan Jet<br />
16.<strong>01</strong>.2008<br />
installation.<br />
Falcon and Falcon 20 serial numbers 076, 103<br />
and 280 equipped with:- Integrated Collins<br />
Proline IV avionics suite.- DFS Elementary<br />
Mode S Transponder as per <strong>EASA</strong>.A.S.00203<br />
STC.- AvDef Minor change <strong>EASA</strong>.A.C.05646<br />
10037677 AVIATION DEFENSE SERVICE (AVdef) FAN JET FALCON BASIC Carriage of ARPEGE pylons onlyThe purpose<br />
of this approval is to clear the carriage of the<br />
ARPEGEpylons only configuration on Falcon<br />
20 S/N 076.<br />
Restricted to Falcon 20 S/N 076 aircraft.As per Prior to installation of this modification it 14.12.2<strong>01</strong>1<br />
AFM Supplement N° SAFM-FALC20 Rev. 17. must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0822 AVIATION DEFENSE SERVICE (AVdef) FAN JET FALCON BASIC Carriage of PIRATE pylons only.The purpose is Restricted to Falcon 20 S/N 076 aircraft.As per Prior to installation of this modification it 27.07.2<strong>01</strong>2<br />
to clear the carriage of a new configuration of AFM Supplement N° SAFM-FALC20 Rev. 18. must be determined thatthe<br />
underwingstores, dedicated for ferry<br />
interrelationship between this modification<br />
flights without the PIRATE pods.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034408 AVIATION ENGINEERING AS AS 350 B2 & AS 350 B3 Installation of Electromagnetic Ground Ice<br />
Thickness Sensor<br />
AS350B2 and AS350B3 post mod Eurocopter<br />
SBT 25.00.62<br />
Prior to installation of this modification it <strong>01</strong>.<strong>04</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>04</strong>2854 AVIATION ENGINEERING AS AS365 N1, N2, N3 Modification of Helidyne DPL Litter P/N HD365- STC <strong>EASA</strong>.R.S.<strong>01</strong>072 to be installed The approval holder shall fulfil the 20.12.2<strong>01</strong>2<br />
15-1036 Approved under STCLFVS 21E2.003<br />
obligations of Part 21,<br />
(Sweden). Rebuilding of the Helidyne DPL<br />
Paragraph21.A.118. Prior to installation<br />
Litter tofacilitate Aerolite Platform P/N 007-<br />
of this modification it must be determined<br />
0002633-5<strong>01</strong> (EMS Patient Platform).<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
10<strong>01</strong>5339 AVIATION FABRICATORS / CENTRAL <strong>EASA</strong>.IM.A.S.00389 REV. 2 SEE ATTACHED <strong>EASA</strong><br />
Installation of aft Jump Seat Kits. 1. Installation per the STC Drawing Lists<br />
17.<strong>04</strong>.2008<br />
APPROVED TYP<br />
defined in the AML is limited to aircraft with<br />
Beech factory installed oxygen system for the<br />
jump seat locations. Aircraft configured for<br />
more than 14 total occupants must be<br />
equipped with a 49 cubic foot or gre<br />
10<strong>01</strong>5427 AVIATION FABRICATORS / CENTRAL <strong>EASA</strong>.IM.A.S.<strong>01</strong>160 FAA STC ST00716WI CESSNA 500<br />
CESSNA 5<strong>01</strong><br />
CESSNA 550<br />
CESSNA 551<br />
CESSNA 560<br />
CESSNA 650<br />
CESSNA S550<br />
Installation of Shoulder Harness Kit 22.07.2005<br />
10<strong>01</strong>5577 AVIATION FABRICATORS / CENTRAL <strong>EASA</strong>.IM.A.S.<strong>01</strong>488 REV. 1 FAA STC SA00622WI SEE <strong>EASA</strong> APPROVED MODEL Installation of shoulder harness kit None Prior to installation of this modification it 11.12.2009<br />
LIST<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5888 AVIATION FABRICATORS / CENTRAL <strong>EASA</strong>.IM.A.S.02007 FAA STC ST<strong>01</strong>262WI CESSNA 650 Installation of a 1, 2 or 3 place side facing<br />
Divan<br />
10<strong>01</strong>5991 AVIATION FABRICATORS / CENTRAL <strong>EASA</strong>.IM.A.S.02145 FAA STC SA4147SW HAWKER 1000<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER HS 125<br />
Installation of one, two, three & four-place side<br />
facing seat.<br />
Applicable to aircraft serials 650-0023 and<br />
subsequent.This STC approves only the<br />
installation of the parts contained in the<br />
installation documents referenced above. The<br />
requirements foraisle width, passenger oxygen<br />
systems, seats and safety belts, and uph<br />
This STC grants no operational approval to this<br />
installation, that will need to be obtained from<br />
the State of registry for the particular aircraft<br />
involved as defined in JAR OPS1.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 89/<strong>462</strong><br />
09.<strong>01</strong>.2007<br />
30.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6005 AVIATION FABRICATORS / CENTRAL <strong>EASA</strong>.IM.A.S.02168 FAA STC ST<strong>01</strong>139WI CESSNA 560 Installation of a 39-inch or a 45-inch two-place The STC covers only installation of parts<br />
divan or a 24-inch one-place divan per Aviation contained in the Description sectionUpholstery,<br />
13.09.2006<br />
Fabricators STC Data Package, AF-342, Rev covers, aisle width, oxygen, seat belts are not<br />
A, dated 12, June, 2003 and stamped "FAA<br />
Approved" with an approval date of October<br />
22, 2003 or later approved revisi<br />
covered<br />
10<strong>01</strong>5576 AVIATION FABRICATORS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>487 REV. 1 FAA STC SA2629CE 200, 200C, 200CT, 200T, 300<br />
300LW, B200, B200C, B200CT<br />
B200GT, B200CGT<br />
B200T, B300, B300C<br />
Installation of two place side-facing divan. 1) Prior to installation of this modification the<br />
installer mustdetermine that the<br />
interrelationship between this modification and<br />
anyother previously installed modification will<br />
introduce no adverse effectupon the<br />
airworthiness of the product. 2) The inst<br />
1. This STC must be installed per 08.10.2009<br />
Aviation Fabricators drawing D-10265,no<br />
revision or later approved revision on<br />
airplanes manufactured after12<br />
December 1986, with nine or fewer<br />
passenger seats, including thedivan. 2.<br />
For other divan installation, Aviatio<br />
10029817 AVIATION FABRICATORS, Inc. FAA STC ST<strong>01</strong>572WI 400 Beechjet 400 Cabin Configuration. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.<strong>04</strong>.2<strong>01</strong>0<br />
10029869 AVIATION FABRICATORS, Inc. FAA STC NO. SA00961WI PA-31-325, PA-31-350<br />
PA-31P, PA-31T, PA-31T1<br />
PA-31T2, PA-31T3, PA-31<br />
PA-42, PA-42-720, PA-42-1000<br />
Stretcher Installation per Aviation Fabricators,<br />
Inc. STC Drawing List,Doc. No. AF-2<strong>04</strong><br />
10031917 AVIATION FABRICATORS, Inc. FAA STC SA2818SW 441 Installation of 1, 2 or 3 place side seating<br />
divans in accordance withFAA STC<br />
SA2818SW<br />
10032446 AVIATION FABRICATORS, Inc. FAA STC SA2774CE 1. 200, 200C, 200CT, 200T<br />
1. A200, A200C, A200CT, B200<br />
1. B200CT, B200T, 300, 300LW<br />
2. B200C, B200CGT, B200GT<br />
2. B300, B300C<br />
10032903 AVIATION FABRICATORS, Inc. FAA STC REF SA4157SW SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of Passenger Seats with Hinged<br />
Backrest.<br />
Installation of one, two, or three place side<br />
facing seat (frame only).<br />
The installer is responsible for ensuring that the<br />
installation complieswith any supplemental<br />
oxygen requirements as required for operation<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
27.<strong>04</strong>.2<strong>01</strong>0<br />
none<br />
thatthe interrelationship b<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.09.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.11.2<strong>01</strong>0<br />
None This STC only approves the installation of 07.12.2<strong>01</strong>0<br />
the parts contained in theabove section<br />
"associated technical documentation".<br />
The requirements forthe aisle width,<br />
passenger oxygen system, seats and<br />
safety belts, andupholstery coverings will<br />
require a separate a<br />
10<strong>01</strong>5323 AVIATION PARTNERS BOEING <strong>EASA</strong>.IM.A.S.00279 REV. 3 FAA STC ST00830SE BOEING 737-700<br />
Installation of Aviation Partners Boeing 1. Subject to compliance with the provisions<br />
30.06.2008<br />
BOEING 737-800<br />
Winglets in accordance with the following of Part 21 Subpart E, this STC and associated<br />
BOEING 737-900<br />
documents:- APB Document List AP37.7- data shall remain valid until surrendered,<br />
E620 Rev. A (737-700)- APB Document List withdrawn or otherwise terminated.2. If<br />
AP37.1- E620 Rev. A (737-700IGW)- APB transfer of this Certificate is requested under<br />
10<strong>01</strong>5659 AVIATION PARTNERS BOEING <strong>EASA</strong>.IM.A.S.<strong>01</strong>636 REV. 5 FAA STC ST<strong>01</strong>518SE B757-200, -300<br />
Document List AP37.8- E620 Rev. A (737-800)- Part 21A.116 the STC will be<br />
APB Documen<br />
Install of Aviation Partners Boeing Winglets on The Partial Wing Retrofit Installation (300-1 Kit) Prior to installation of this modification it 11.<strong>04</strong>.2<strong>01</strong>1<br />
B757-200 and B757-300Aeroplanes<br />
is approved for RollsRoyce RB211-535 must be determined thatthe<br />
powered a/c.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 90/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6394 AVIATION PARTNERS BOEING <strong>EASA</strong>.IM.A.S.02723 REV. 3 FAA STC ST<strong>01</strong>920SE BOEING 767-300, -300F Installation of Aviation Partners Boeing Operational/ Performance limitations are Prior to installation of this modification it 07.<strong>01</strong>.2<strong>01</strong>1<br />
Winglets on Boeing B767-300 and-300F a/c. defined within the AFMsupplement. This STC must be determined thatthe<br />
is approved for a/c equipped with General interrelationship between this modification<br />
Electric CF6-80C2series engines or Pratt and and any other previouslyinstalled<br />
Whitney PW 4000 series engines with modification and/ or repair will introduce<br />
noengine strut vibration isolators installed only no adverse effectupon the airworthiness<br />
of the product.<br />
10029056 AVIATION PARTNERS BOEING <strong>EASA</strong>.IM.A.S.02838 FAA STC ST<strong>01</strong>219SE BOEING 737-500 15.07.2009<br />
10<strong>01</strong>5403 AVIATION PARTNERS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>113 FAA STC ST<strong>01</strong>411SE BAE 125 SERIES 800A<br />
Installation of Winglets, associated changes in Installation of this STC on Model Hawker<br />
26.10.2005<br />
BAE 125 SERIES 800B<br />
wing and Aileron structures and related 800XP is limited to Aircraft equipped with the<br />
HAWKER 800 XP<br />
systems changes on Raytheon Aircraft Honeywell DFZ-800 (SPZ-800 avionics)<br />
Company Model Bae 125 Series 800A, 800B autopilot, the Collins 85/86 (FCC-86E avionics)<br />
and Hawker 800XP Aircraft, in accordance auto pilot and Collins Pro line 21 (FGC-300<br />
with FAA STC ST<strong>01</strong>411SE<br />
avionics) autopilot, for Category I app<br />
10028844 AVIATION PARTNERS, INC. <strong>EASA</strong>.IM.A.S.02<strong>04</strong>3 FAA STC ST<strong>01</strong>987SE DASSAULT FALCON 2000<br />
DASSAULT FALCON 2000EX<br />
SERIES<br />
10038665 AVIATION PARTNERS, INC. REV. 1 FAA STC ST02188SE MF900, F900EX FAA STC ST02188SE: Installation of blended Applicable to MF900 aircraft orApplicable to<br />
winglet on Dassault Falcon900 Series airplanes MF900 aircraft fitted with modification M1975<br />
orApplicable to Falcon 900EX aircraft<br />
orApplicable to Falcon 900EX fitted with<br />
modifications M3083 or M4000<br />
10<strong>01</strong>5248 AVIATION SERVICE A.S. <strong>EASA</strong>.A.S.03687 LETECKE ZAVODY L 410 UVP-E Installation of EGPWS Mark VI. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10029324 AVIATION SERVICE A.S. P-<strong>EASA</strong>.A.S.03854 L 200 A, L 200 D Installation of Aspen EDF-1000 "PRO" and<br />
EFD-1000 "PILOT", GNS 430W, GTX330, KR<br />
87, KN 62A and ELT ME406 systems.<br />
10030602 AVIATION SERVICE A.S. L410 UVP-E, L410 UVP-E9,<br />
L410 UVP-E20<br />
TCAS II CAS67A, Mode S transponder<br />
MST67A, and Air Data Display UnitAD32<br />
installation to comply with regulation<br />
requirements.<br />
10031903 AVIATION SERVICE A.S. 407 Installation of alternate static port for VFR night<br />
operation<br />
10033022 AVIATION SERVICE A.S. AN-26B An-26 Aircraft Upgrade; TCASII CAS-67A,<br />
Mode S Transpon. MST-67A andKT73,<br />
EGPWS Mk-VI, NAV/COMM KX165A,<br />
GPS155XL, Audio panel KMA28, WxRadar<br />
ART2000, MFD KMD540, ADF KR87, DME<br />
KN63, Air Data Display AD32,RAlt KRA405B,<br />
Airspeed Ind. LUN110, ELT C406-2;<br />
Steep approach Operation with Winglets<br />
installed is not approvedHUD/CATIII<br />
Operation with Winglets installed is not<br />
approvedPrior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other p<br />
None. Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
08.05.2009<br />
08.08.2<strong>01</strong>2<br />
24.11.2008<br />
18.03.2<strong>01</strong>0<br />
None<br />
product.The installatio<br />
None 24.06.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
21.09.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
15.12.2<strong>01</strong>0<br />
10<strong>01</strong>7094 AVIATION SUPPORT GmbH <strong>EASA</strong>.R.S.<strong>01</strong>006 EUROCOPTER DEUTSCHLAND Installation of a Gas Detection System CHARM<br />
13.02.2007<br />
BO-105<br />
with a laser scanner<br />
10<strong>01</strong>7159 AVIATION SUPPORT GmbH <strong>EASA</strong>.R.S.<strong>01</strong>267 SCHWEIZER AIRCRAFT 269A<br />
SCHWEIZER AIRCRAFT 269B<br />
SCHWEIZER AIRCRAFT 269C<br />
SCHWEIZER AIRCRAFT 269C-1<br />
SCHWEIZER AIRCRAFT 269D<br />
Installation of Clipboard/Tablet-PC rack -- 30.<strong>01</strong>.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 91/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027152 AVIATION SUPPORT GmbH P-<strong>EASA</strong>.R.S.<strong>01</strong>558 MD 600N Installation of HD Camera System and right Approval limited to S/N RN073 Prior to installation of this modification it 10.09.2009<br />
side dual utility mount MD600N, as per Master<br />
must be determined thatthe<br />
Document List Ref MDL-ASE-90819, dated<br />
interrelationship between this modification<br />
08.09.2009<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027605 AVIATION SUPPORT GmbH P-<strong>EASA</strong>.R.S.<strong>01</strong>336 AS350 B, D, B1, B2, BA, BB, B3 Installation of a 3D laser measurement system<br />
in an external cargo pod.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.10.2009<br />
10030519 AVIATION SUPPORT GmbH AS350B, D, B1, B2, BA, BB, B3 Cargo Mirror Set Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
22.06.2<strong>01</strong>0<br />
10032031 AVIATION SUPPORT GmbH REV. 1 MD900 Installation of an O2 Rack This change is restricted to Serial number 900-<br />
0<strong>01</strong>05 only.<br />
Prior to installation of this modification it 08.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10033427 AVIATION SUPPORT GmbH P-<strong>EASA</strong>.R.S.<strong>01</strong>335 MD900 Installation of swiveling speaker system MD900 none Prior to installation of this modification it 23.06.2009<br />
(ALS-ausfahrbaresLautsprecher-System MD<br />
must be determined thatthe<br />
900)<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
10033443 AVIATION SUPPORT GmbH P-<strong>EASA</strong>.R.S.<strong>01</strong>513 EC135 Installation of High Definition (HD)<br />
Broadcasting System<br />
With HDBS camera system installed: VMC Prior to installation of this modification it 06.07.2009<br />
DAY ONLY; Category "A" operationprohibited. must be determined thatthe<br />
Antenna Actuator: Minimum height to deploy interrelationship between this modification<br />
antenna: 50ft AGL Maximumflight speed to and any other previouslyinstalled<br />
deploy antenna is 75 KIAS until antenna is modification and/ or repair will introduce<br />
fullydeployed.<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
10033667 AVIATION SUPPORT GmbH MD900 Installation of an Equipment Rack None The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21.A109Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair<br />
10033670 AVIATION SUPPORT GmbH 1. AB 206 A & AB 206 B<br />
2. 206A & 206B<br />
Installation of ALMA (Airborne Laser Methane<br />
Assessment) - Gas DetectionSystem.<br />
10034980 AVIATION SUPPORT GmbH REV. 1 SA 365 N Title: SA 365 EMS Equipment.Description:<br />
Installation of an EMS Equipment fixed at the<br />
seat andcargo attachment points of the<br />
passenger compartment.The System is<br />
installed at the location of the first and second<br />
seatrow. The aft seat row remains for the he<br />
02.02.2<strong>01</strong>1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.02.2<strong>01</strong>1<br />
This STC is applicable for the Serial Number<br />
6100.The use of the electrical components of<br />
the medical equipment is limitedto VFR<br />
Operations.The use of a hoist is not possible if<br />
the EMS Equipment is installed.<br />
Prior to installation of this modification it 24.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 92/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039242 AVIATION SUPPORT GmbH 0<strong>01</strong>0<strong>01</strong>2<strong>01</strong>0-0<strong>01</strong> FOCA STC 25-70-<strong>01</strong>2 EC135 T2 Installation of an external Ski Basket<br />
None Prior to installation of this modification it 19.<strong>04</strong>.2<strong>01</strong>2<br />
Equipment P/N AV 115.00<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5418 AVIATION TECHNICAL SERVICES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>141 FAA STC ST00988SE-D BOEING 757-200 Installation of an Interior Arrangement, Avionics 1. This STC is approved only for the product<br />
& Ozone Converters.<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5543 AVIATION TECHNICAL SERVICES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>428 ST00299SE-D BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Modification of an 87MCU FMC Tray to accept<br />
a 4MCU FMC LRU according to FAA STC<br />
ST00299SE-D<br />
10<strong>01</strong>6147 AVIATION TECHNICAL SERVICES, Inc. <strong>EASA</strong>.IM.A.S.02348 FAA STC SA7030NM-D BOEING 737-300 Installation of Allied Signal p/n 967-<strong>01</strong>02-0<strong>01</strong><br />
Digital Flight Data Acquisition Unit (DFDAU)<br />
and necessary sensors and wiring to record<br />
Twenty Two (22) Parameters of data per<br />
Tramco Incorporated Master Drawing List 95-<br />
180 Sheet 1 Revision A dated January 12<br />
10<strong>01</strong>6176 AVIATION TECHNICAL SERVICES, Inc. <strong>EASA</strong>.IM.A.S.02405 FAA STC SA5115NM BOEING 737-300 Installation of a Collins Traffic Alert and<br />
Collision Avoidance System (TCAS II)<br />
Transmitter/Receiver with Honeywell<br />
TA/RA/IVSI´s.<br />
10<strong>01</strong>6177 AVIATION TECHNICAL SERVICES, Inc. <strong>EASA</strong>.IM.A.S.02406 US FAA STC SA4978NM BOEING 737-300 Installation of Traffic Alert and Collision<br />
Avoidance System (TCAS) provisions<br />
10029541 AVIATION TECHNICAL SERVICES, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02553<br />
10029850 AVIATION TECHNICAL SERVICES, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02613<br />
FAA STC ST00051SE BOEING 737-400 Installation of a Collins Traffic Alert and<br />
Collision Avoidance System(TCAS II)<br />
Transmitter/Receiver per Goodrich ATS, Inc<br />
Top Drawing 93<strong>04</strong>6Revision F dated 05<br />
January 20<strong>01</strong>.<br />
FAA STC ST00631SE-D B737-800 Interior Reconfiguration - Installation of an<br />
Interior Arrangement,Entertainment System<br />
Components and Avionics Components.<br />
11.<strong>04</strong>.2005<br />
According to FAA STC ST00299SE-D 29.09.2005<br />
1. Approval of this change in Type Design<br />
applies to the above model aircraft only. This<br />
approval should not be extended to other<br />
aircraft of this model on which other previously<br />
approved modifications are incorporated<br />
unless it is determined that the<br />
27.02.2007<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
22.<strong>04</strong>.2009<br />
This approval is applicable only to the electrical<br />
provisions for TCAS and does not approve the<br />
actual TCAS installation or any TCAS<br />
equipment.<br />
12.07.2007<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.03.2<strong>01</strong>0<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>04</strong>.2<strong>01</strong>0<br />
10<strong>01</strong>40<strong>01</strong> AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>038 BOEING 757-200 Installation of Enhanced Mode S Transponders 17.03.2005<br />
10<strong>01</strong>4002 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>039 BOEING 737-700 Installation of Enhanced Mode S Transponders 17.03.2005<br />
10<strong>01</strong>4003 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong><strong>04</strong>0 BOEING 737-300 Installation of Enhanced Mode S Transponders 17.03.2005<br />
10<strong>01</strong>4163 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>295 Installation of Teledyne Flight Data Acquisition<br />
Unit P/N 2233000-811 to provide parameters<br />
to the FDR<br />
22.11.2005<br />
10<strong>01</strong>4175 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>310 COMMANDER AIRCRAFT 114B Wing auxiliary Spar Repair 13.10.2005<br />
10<strong>01</strong>4254 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>479 BOEING 707-300 Avionics Upgrade Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
15.10.2008<br />
10<strong>01</strong>4322 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>575 REV. 1 AIRBUS A300 B4 Introduction of Enhanced Mode S Transponder This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 93/<strong>462</strong><br />
14.09.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4323 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>576 BOEING 727 SERIES Introduction of Terrain Awareness & Warning<br />
System (TAWS)<br />
25.<strong>01</strong>.2006<br />
10<strong>01</strong>4358 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>623 BOEING 757-200 Introduction of Enhanced Mode S Transponder 18.<strong>01</strong>.2006<br />
10<strong>01</strong>4372 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.<strong>01</strong>646 BOEING 747-200 Introduction of a Litton 72R INS in a Boeing<br />
747-200 series aircraft<br />
A copy of this Certificate and the <strong>EASA</strong><br />
Approved Flight Manual Supplement (AFMS)<br />
must be maintained as part of the permanent<br />
records for the modified aircraft.<br />
10<strong>01</strong>4499 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02564 REV. 1 PARTENAVIA P68C Camera Port Installation -- 13.12.2006<br />
10<strong>01</strong>4594 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02706 BAE 146 Noneywell TCAS II 05.07.2006<br />
10<strong>01</strong>4595 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02712 Installation of Honeywell MKVII EGPWS. Compatibility of this design with previously<br />
approved modifications must be determined by<br />
the installer.<br />
31.05.2007<br />
10<strong>01</strong>4633 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02775 BAE 146 Installation of dual AlliedSignal GNS-XLS Flight Restricted to VH-JJY ASN E2113.<br />
Management System<br />
10.05.2007<br />
10<strong>01</strong>4660 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02817 BOEING 737-300<br />
Mode 'S' Transponder System for Elementary In accordance with Paragraphs 3, 9, 10, 13 & Prior to installation of this modification the 20.07.2009<br />
BOEING 737-400<br />
and EnhancedSurveillanceRevison to 16 of the ModificationSummary ATL/737/M556 installer must determinethat the<br />
BOEING 737-500<br />
<strong>EASA</strong>.A.S.02617 (B737-400 added to existing Issue 1, dated 9th October 2006Compatibility interrelationship between this modification<br />
STC)<br />
of this design change with other previously and any other previouslyinstalled<br />
approvedmodifications must be determined by modification will introduce no adverse<br />
the installer.<br />
effect upon the airworthiness ofthe<br />
product. The installati<br />
10<strong>01</strong>4707 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02879 BOEING 747-400 SERIES Installation of a Bendix / King CAS-81 TCAS II Prior to installation of the STC Boeing SB 747-<br />
System in B747-400 in accordance with Master 34-2309 must be installed.<br />
Drawing List Drawing No. 699-50021, initial<br />
release and Dual Bendix / King TRA-67 Mode<br />
S Transponder in accordance with Master<br />
Drawing List, Drawing 699-50020, init<br />
10<strong>01</strong>4708 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02880 BOEING 747-400 SERIES RTA-44D VHF Data Radio System. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph 4:<br />
Specification Aircraft/Modification.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
10<strong>01</strong>4709 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02881 BOEING 747-400 Certification of Collins Data Link ACARS<br />
Installation in the B747-400<br />
MDL 94-24<strong>Page</strong> Avjet Master Drawing List for<br />
installation of Collins ACARS Part No 622-<br />
9717-00X on B747-400 series aircraft.<br />
10<strong>01</strong>4734 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02917 BOEING 757-200 238 PAX LOPA Installation 21.03.2007<br />
10<strong>01</strong>4757 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.02945 BOEING 757 2<strong>01</strong>PAX LOPA Installation 03.<strong>04</strong>.2007<br />
10<strong>01</strong>4887 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03116 BAE 146/AVRO 146 SERIES 95 Passenger LOPA Installation. 05.09.2007<br />
10<strong>01</strong>4940 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03198 148 Pax LOPA Installation Compatibility of this design change with other<br />
previously approved modifications must be<br />
determined by the installer.<br />
05.09.2008<br />
10<strong>01</strong>4942 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.032<strong>01</strong> BOEING 757-2Q8 219 PAX LOPA Installation. This STC is limited to aircraft s/n 26270. 21.08.2007<br />
10<strong>01</strong>4963 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03234 BOMBARDIER CL-600-2B16 Introduction of Honeywell Mark V EGPWS. Aviation Traders Ltd Modification ATL/600/003<br />
(<strong>EASA</strong>.A.S.03244) must be embodied prior to,<br />
or concurrently with, Modification<br />
ATL/600/002.Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modific<br />
18.07.2008<br />
10<strong>01</strong>4967 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03244 BOMBARDIER CL-600-2B16 EFIS, GPS approach scaling and EGPWS<br />
display<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4994 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03291 REV. 2 B757-200 Passenger/ Cargo Combi Configuration This STC is limited to a/c serial number 25621 Prior to installation of this modification it<br />
onlyATL Minor Modification MOD/11630/00003 must be determined thatthe<br />
07.02.2<strong>01</strong>1<br />
must be installed concurrentlywith this STC. interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 94/<strong>462</strong><br />
19.06.2006<br />
22.03.2007<br />
<strong>01</strong>.02.2007<br />
31.<strong>01</strong>.2007<br />
18.07.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5097 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03436 REV. 1 A310-203<br />
Bluesky D1000 Satcom installation The None The BlueSky Satcom System, installed 21.03.2<strong>01</strong>1<br />
A310-203C<br />
Supplemental Type Certificate<br />
by this STC, has not been certifiedas a<br />
A310-2<strong>04</strong><br />
<strong>EASA</strong>.A.S.03436 embodied provisions fora<br />
means of voice or data communications<br />
A310-221<br />
further configuration installing BlueSky Network<br />
with Air Traffic Control andshould<br />
A310-222<br />
Satcom System D1000with an Intercom<br />
therefore not be relied upon when<br />
A310-3<strong>04</strong><br />
Integration option.This revision <strong>01</strong> approves the<br />
planning operations outside<br />
A310-308<br />
A310-322<br />
A310-324<br />
A310-325<br />
activation of<br />
VHFcoverage.<br />
10<strong>01</strong>5253 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.A.S.03698 BOEING 747-100<br />
Installation of a Solid State Cockpit Voice 1. Prior to installation of this modification the<br />
21.03.2009<br />
BOEING 747-200<br />
Recorder and Control Unit in Boeing 747-100 installer must determine that the<br />
and –200 series aircraft per ATL Master interrelationship between this modification and<br />
Document List MDL-11053-000<strong>01</strong> at Issue 1 or any other previously installed modification will<br />
later approved revisions.<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7153 AVIATION TRADERS LIMITED - ATL <strong>EASA</strong>.R.S.<strong>01</strong>256 SCHWEIZER AIRCRAFT 269D Introduction of EAC-333-000 Airborne Camera Restricted to: G-TAMA ASN 051A, G-TAMB<br />
03.10.2006<br />
System<br />
ASN 052A, G-TAMC ASN 054A, G-TAMD<br />
ASN 056A & G-TAME ASN 035A<br />
10027284 AVIATION TRADERS LIMITED - ATL P-<strong>EASA</strong>.A.S.03927 A320-232 Airbus A320 12C/8J/36Y LOPA The STC holder shall provide by 7th June 2<strong>01</strong>0 Prior to installation of this modification the 18.09.2009<br />
Instructions for ContinuedAirworthiness on installer must determinethat the<br />
Electrical Wiring Interconnection System - interrelationship between this modification<br />
EWIS ICA -in accordance with Special and any otherpreviously installed<br />
Condition H-<strong>01</strong> "Enhanced<br />
modification will introduce no adverse<br />
AirworthinessProgramme for Aeroplane effect uponthe airworthiness of the<br />
Systems - ICA on EWIS".<br />
product.The installatio<br />
10027820 AVIATION TRADERS LIMITED - ATL P-<strong>EASA</strong>.A.S.03974 757-200 205 Passenger LOPA The STC holder shall submit to the agency Prior to installation of this modification the 09.11.2009<br />
before 7th June 2<strong>01</strong>0 finalinstructions of installer must determinethat the<br />
instructions for continued airworthiness on interrelationship between this modification<br />
ElectricalWiring Interconnection System and any otherpreviously installed<br />
(EWIS) in accordance with the specialcondition modification will introduce no adverse<br />
(H-<strong>01</strong>).<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10027954 AVIATION TRADERS LIMITED - ATL P-<strong>EASA</strong>.A.S.03798 REV. 1 BAE 146-200 VIP Cabin Interior. Approval of Alternative Serial Number E2079 only Prior to installation of this modification it 09.07.2<strong>01</strong>0<br />
Limitation on <strong>EASA</strong> STC10027954. <strong>EASA</strong><br />
must be determined thatthe<br />
STC 10027954 contains the following<br />
interrelationship between this modification<br />
Limitation: The STC holdershall submit to the<br />
and any other previouslyinstalled<br />
agency before 7th June 2<strong>01</strong>0 final instructions<br />
modification and/ or repair will introduce<br />
forcontinued airworthiness on Electrical Wirin<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028747 AVIATION TRADERS LIMITED - ATL REV. 1 737 ALL MODELS Blue Sky Network Satcom installation.This<br />
STC installs Satcom communications at the<br />
captain and F/O station.<br />
10029091 AVIATION TRADERS LIMITED - ATL P-<strong>EASA</strong>.A.S.03891 B747-400 Introduction of changes to the cabin layout in<br />
accordance with ATLModification Summary<br />
MOD-11427-000<strong>01</strong>Part A: introduces a seating<br />
configuration of 22 business class and<br />
440economy classPart B: introduces all<br />
emergency equipment necessary to comply<br />
with th<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.03.2<strong>01</strong>0<br />
None The EU-OPS 1 subparts K & L<br />
compliance has not been investigated<br />
byCAA-NL (this is up to the local<br />
authority) This STC is limited to A/C S/N<br />
24920<br />
10029662 AVIATION TRADERS LIMITED - ATL P-<strong>EASA</strong>.A.S.03876 B737-300 Business Interior - 48 PAX LOPA The STC holder shall provide by 7th June 2<strong>01</strong>0<br />
Instructions for ContinuedAirworthiness on<br />
Electrical Wiring Interconnection System -<br />
EWIS ICA -in accordance with Special<br />
Condition H-<strong>01</strong> "Enhanced<br />
AirworthinessProgramme for Aeroplane<br />
Systems - ICA on EWIS".Li<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029965 AVIATION TRADERS LIMITED - ATL B757-200 Boeing 757-200 229Y Passenger Configuration As per associated Technical documentation for Prior to installation of this modification it<br />
weight and balance(maximum allowable limit in must be determined thatthe<br />
07.05.2<strong>01</strong>0<br />
the forward and aft cargo area is to<br />
interrelationship between this modification<br />
beamended as per indicated in doc. N° MOD- and any other previouslyinstalled<br />
11682-000<strong>01</strong>, Issue 3).Limited to: MSN 27973 modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 95/<strong>462</strong><br />
03.03.2<strong>01</strong>0<br />
09.<strong>04</strong>.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6672 AVIDYNE CORPORATION <strong>EASA</strong>.IM.A.S.03174 FAA STC SA02<strong>01</strong>3CH CIRRUS SR20<br />
Installation of Avidyne Model 9900BX/ TAS 1) Prior to installation of this modification the<br />
27.05.2009<br />
CIRRUS SR22<br />
600 Series Traffic Advisory System (TAS) installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2) The ins<br />
10030294 AVIDYNE CORPORATION REV. 1 FAA STC SA00269BO 1. SR20, SR22<br />
2.SR22T<br />
Installation of Avidyne 700-00033-() Tactical<br />
Weather Detection System<br />
10033140 AVIDYNE CORPORATION FAA STC SA00296BO SR20, SR22 Installation of Avidyne Model DFC90 Autopilot<br />
P/N 700-0<strong>01</strong>70-000 System<br />
As indicated in FAA STC SA00269BO AML limited to Cirrus Design Corporation<br />
SR20, SR22, SR22T only. Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introdu<br />
as indicated in FAA STC SA00296BOAvidyne<br />
software P/N 530-00214-() Rev 02 or later<br />
FAA approved revisionwith underspeed<br />
protection functionality must be installed on<br />
PFD P/N700-00006-()<br />
10038669 AVIDYNE CORPORATION FAA STC SA00310BO PA46-350P, PA-46R-350T Autopilot Series / DFC 90 Autopilot P/N 700- Aircraft must be configured with an existing S-<br />
0<strong>01</strong>70-002 DFC100 AutopilotP/N 700-0<strong>01</strong>70- TEC 55X (or 55SR)Autopilot and with an<br />
003 as replacement for the S-Tec System 55X existing Avidyne Flight Display System as<br />
Autopilot P/N1192-()-() in accordance with followsin order to accomplish this STC:For<br />
Avidyne Corporation Master Document DFC90: Avidyne Primary Flight Display, p/n<br />
ListAVDFC-077<br />
700-00006-( ), loadedwith Release 8.0.4 so<br />
10039607 AVIDYNE CORPORATION REV. 1 FAA STC SA0282BO PA-46R-350T Integrated Flight Display Enhanced Vision System (EVS) is not included<br />
in the scope of thisapprovalCompatibility with<br />
Mode 5 alerts must be shown when a TAWS<br />
Class A isinstalled.<br />
10<strong>04</strong>1185 AVIDYNE CORPORATION FAA STC SA00282BO SR20, SR22 Installation of Avidyne Corporation 700-00083-<br />
XXX Entegra IntegratedFlight Display System<br />
on Cirrus SR20 and SR22 according Avidyne<br />
Doc. NoAVIFD-006 in latest FAA approved<br />
Revision<br />
As indicated in FAA STC<br />
SA00282BOEnhanced Vision System (EVS) is<br />
not included in the scope of<br />
thisapprovalCompatibility with Mode 5 alerts<br />
must be shown when a TAWS Class A<br />
isinstalled.<br />
21.12.2<strong>01</strong>0<br />
Prior to installation of this modification it 20.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
The approval holder shall fulfill the<br />
obligations of Part 21,Paragraph<br />
21.A109.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
06.03.2<strong>01</strong>2<br />
Prior to installation of this modification it 11.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 28.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
10<strong>04</strong>2507 AVIDYNE CORPORATION FAA STC SA00323BO 182E, 182F, 182G, 182H, 182J, Installation of Avidyne Corporation Autopilot; Operation must be in accordance with Avidyne The installation of this modification by 05.12.2<strong>01</strong>2<br />
182K, 182L, 182M, 182N, 182P, model DFC90, p/n700-0<strong>01</strong>70-022 (28-Volt Corporation AFMS documentNo. 600-00293- third persons is subject towritten<br />
182R, 182S, 182T, R182. Electrical system) or p/n 700-0<strong>01</strong>70-024 (14- 000, rev.00 dated <strong>01</strong>-October-2<strong>01</strong>2.The AFMS permission of the approval holder and<br />
VoltElectrical system), loaded with Release 0 must be carried in the Aircraft during all disposal of the approvedappropriate<br />
Software, as a replacement forthe S-Tec flights.Maintenance must be in accordance with documentation.Prior to installation of this<br />
Autopilot.<br />
ICA document AVDFC-125, rev.00dated 09- modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>04</strong>2851 AVION RESEARCH, Inc. REV. 1 FAA STC SA170CH 1. 172<br />
Installation of a Control Yoke and Instrument None 1. A copy of this certificate or later FAA 21.12.2<strong>01</strong>2<br />
1. 172A/B/C/D/E/F/G/H/I/K/L/M Panel in accordance withFAA STC SA170CH<br />
approved revision must bemaintained as<br />
2. 175, 175A/B/C<br />
part of the permanent records for the<br />
modified aircraft.2. If the holder agrees to<br />
permit another person to use this<br />
certificateto alter the product, the holder<br />
shall give th<br />
10<strong>01</strong>4692 AVIONES, PIEZAS Y ACCESORIOS, S.L. <strong>EASA</strong>.A.S.02857 PIPER PA-31 Installation Dual integrated NAV/COMM/GPS<br />
GARMIN 480 and Transponder GARMIN GTX<br />
33 (APA OT 50<strong>01</strong> Rev.1).<br />
05.02.2008<br />
10<strong>01</strong>47<strong>04</strong> AVIONES, PIEZAS Y ACCESORIOS, S.L. <strong>EASA</strong>.A.S.02875 MITSUBISHI MU-2B-35 Installation of New Avionics Equipment to<br />
comply with COM/NAV regulations for IFR and<br />
B-RNAV Operation.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 96/<strong>462</strong><br />
10.12.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7246 AVIONES, PIEZAS Y ACCESORIOS, S.L. <strong>EASA</strong>.R.S.<strong>01</strong>443 EUROCOPTER FRANCE AS 355 HD I. Ponti Radio Digital video, audio & data Prior to installation of this modification the<br />
08.09.2008<br />
SERIE<br />
Transmission System.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5426 AVIONICS GROUP INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>159 REV. 1 FAA STC ST02198AT B757-200, -200CB, -200PF Installation of a Teledyne Digital Flight Data<br />
Acquisition Unit, PartNumber 2233000-811<br />
10<strong>01</strong>6034 AVIONICS GROUP INC. <strong>EASA</strong>.IM.A.S.02203 ST02997AT BOEING 737-100<br />
BOEING 737-200<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Installation of a Sandal Avionics ST3400 Class<br />
A Terrain Awareness and Warning System<br />
10038339 AVIONICS GROUP INC. FAA STC ST03559AT 767-200, -300, -300F, -400ER Installation of Honeywell (TRA-67A) or Collins<br />
(TPR9<strong>01</strong>) Mode S EnhancedSurveillance<br />
System<br />
10<strong>01</strong>4572 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>47<strong>01</strong> AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4739 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4793 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4815 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4912 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4913 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4917 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4925 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4932 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>4959 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>5026 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
08.02.2<strong>01</strong>1<br />
FAA approved Airplane Flight Manual<br />
Supplement for Avionics Group, Inc. Sandel<br />
Avionics ST3400 Class A Terrain Awareness<br />
and Warning System dated December 8, 20<strong>04</strong><br />
is a required part of this STC.<br />
31.10.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
08.02.2<strong>01</strong>2<br />
<strong>EASA</strong>.A.S.02676 BAE 125 -800<br />
Replacement of Dual FMS UNS-1D by Dual -- 21.09.2006<br />
HAWKER 800 SERIES<br />
UNS-1F, to allow the aircraft to comply with PR-<br />
NAV requirements.<br />
<strong>EASA</strong>.A.S.02870 BEECH B200 SUPER KING AIR Installation of a UASC Flight Management<br />
System (FMS) UNS-1L<br />
24.<strong>01</strong>.2007<br />
<strong>EASA</strong>.A.S.02922 BEECH B300 Standby Instruments InstallationIn: 2" Revue<br />
Thommen Standby Altimeter & 2" Revue<br />
Thommen Airspeed Indicator & L3<br />
Communications Standby Attitude Indicator AI-<br />
8<strong>04</strong>with Goodrich JET Emergency Power<br />
Supply Battery Pack PS-835<br />
11.05.2007<br />
<strong>EASA</strong>.A.S.02995 REV 1 BEECH 400A Upgrade of existing FID capable dual TDR-94D 1. This change is limited to the configuration<br />
<strong>04</strong>.<strong>04</strong>.2007<br />
Mode S transponder system to enhanced of aircraft / equipment type as listed under Item<br />
surveillance capability by incorporation of 1.2 in Engineering Order, Doc. No. CV649-<br />
Collins SB 502 and SB 507.<br />
062, Revision A, dated 23 March 2007, or later<br />
approved issue.2. This STC is approved only<br />
for the product confi<br />
<strong>EASA</strong>.A.S.03023 BOMBARDIER CL-600-2B16 Enhanced Surveillance Mode S Transponder<br />
Upgrade (Collins)<br />
N/A 15.03.2007<br />
<strong>EASA</strong>.A.S.03156 REV 1 CESSNA 550 CITATION II Honeywell ART 2000 Weather Radar<br />
transceiver/antenna installation interfacing with<br />
KMD 850 MFD to replace the existing RCA P-<br />
400 radar, to improve reliability and to add<br />
display of terrain and traffic graphics.<br />
22.<strong>01</strong>.2008<br />
<strong>EASA</strong>.A.S.03157 REV 1 CESSNA 550 CITATION II Honeywell EGPWS Mark VIII Sysem<br />
Installation,interfacing with KMD 850 MFD, as a<br />
replacement of the existing GPWS MK VI.<br />
22.<strong>01</strong>.2008<br />
<strong>EASA</strong>.A.S.03163 BEECH 200 Upgrade of dual Mode S transponder system<br />
TDR-94 to TDR-94D with ELS capability and<br />
diversity<br />
This change is limited to the configuration of<br />
aircraft / equipment type as listed under “1.2.<br />
Prerequisite Conditions”, in Engineering Order,<br />
Doc. No. 677-062, Initial Revision, dated 12-<br />
Jun-2007<br />
<strong>EASA</strong>.A.S.03173 BOMBARDIER CL-600-2B16 Replacement of 3 FMS GPS Antennas<br />
(UASC)<br />
<strong>04</strong>.09.2007<br />
<strong>EASA</strong>.A.S.03187 BAE 125 -800A SERIES<br />
Upgrade of EGPWS MK V to RAAS capability. This STC is limited to the configuration of<br />
10.<strong>01</strong>.2008<br />
BAE 125-800B SERIES<br />
aircraft / equipment type as listed under Item<br />
2.1 Limitation, in Engineering Order, Doc. No.<br />
687- 062, Revision B, dated 18-Dec-2007, or<br />
later approved revision.<br />
<strong>EASA</strong>.A.S.03230 BAE 125 -800 SERIES Modification of Collins Transponders to achieve None.<br />
Enhanced Surveillance Capability.<br />
10.09.2007<br />
<strong>EASA</strong>.A.S.03333 BOMBARDIER CL-600-2B19 Dual Electronic Flight Bag Installation<br />
(Maxware).<br />
Aircraft Flight Manual Supplement 667-071. 11.<strong>04</strong>.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 97/<strong>462</strong><br />
14.08.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5030 AVIONICS INTEGRATION &<br />
<strong>EASA</strong>.A.S.03342 FOCA STC 34-45-0<strong>04</strong> CESSNA 525, CITIATION JET TCAS-400 & dual TDR-94D<br />
10.10.2007<br />
ENGINEERING<br />
CESSNA 525A<br />
installation.Change to the FOCA STC 34-45-<br />
0<strong>04</strong> "TCAS-4000, Dual TDR-94D, GNS-430<br />
Installation.By: Incorporation of an Gables<br />
IST.G7614-() as an alternative ATC/TCAS<br />
controller.<br />
10<strong>01</strong>5114 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
<strong>EASA</strong>.A.S.03<strong>462</strong> LEARJET 60 UNS-1B or 1C upgrade to UNS 1C+ 25.<strong>04</strong>.2008<br />
10<strong>01</strong>5143 AVIONICS INTEGRATION &<br />
<strong>EASA</strong>.A.S.03503 1329-25 Upgraded Avionics systems:- UNS-1D to UNS- Reg.: HB-JGK S/N: 5233Valid for this S/N<br />
14.07.2008<br />
ENGINEERING<br />
1D+ FMS- Dual VHF-20A system to VHF-22C only.<br />
incl CTL-22C Control Head- Dual DME-42<br />
system with 2 CTL-32C Control Head- Dual<br />
VIR-30 NAV system with 2 CAD-31 Control<br />
Adapter- Altimetry system with a IS&S Air Data<br />
System<br />
10<strong>01</strong>5155 AVIONICS INTEGRATION &<br />
<strong>EASA</strong>.A.S.03520 LEARJET 60 Installation of Iridium SAT/COM Antenna Installation of the Iridium SAT/COM antenna<br />
22.<strong>04</strong>.2008<br />
ENGINEERING<br />
(Sensor Systems)<br />
and the antenna coax outlet as covered by this<br />
STC does not constitute an approval of the<br />
utility system installation or operation.<br />
10<strong>01</strong>5213 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>5252 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>5260 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>5280 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>5292 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>7244 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10<strong>01</strong>7268 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10028083 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10028084 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10028085 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10028086 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
<strong>EASA</strong>.A.S.03628 LEARJET 31 P-RNAV Compliance Demonstration Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.03697 BOMBARDIER CL-600-2B16 P-RNAV Compliance Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.03718 REV 1 BEECH 390 Iridium SATCOM System Installation (Sky<br />
Connect)<br />
<strong>EASA</strong>.A.S.03806 REV. 2 CESSNA 206, 210 Installation of Aspen Avionics EFD 1000<br />
system (STC to cover now CessnaC-206 &<br />
newly added Cessna C-210 series)<br />
This change is limited to the configuration of<br />
aircraft / equipment type as listed under 3.1<br />
Mechanical Installations”, in Engineering<br />
Order, Doc. No. 788-062, Revision A, dated 13-<br />
Jan-2009, or later approved revision.1 Prior<br />
to installation of<br />
Not valid if the Garmin 1000 ICS option is<br />
installed.<br />
25.08.2008<br />
13.10.2008<br />
09.02.2009<br />
The approval holder shall fulfil the 25.06.2<strong>01</strong>0<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
20.<strong>04</strong>.2009<br />
<strong>EASA</strong>.A.S.03834 CESSNA 206 SERIES Dual GNS 430w with TAS 600 SystemsBy Aspen EFD-1000 Primary Flight Display must<br />
installing two GARMIN GNS430W with external be installed in the aircraft.<br />
121.5MHz Frequency selection and an Avidyne<br />
TAS 600 system<br />
<strong>EASA</strong>.R.S.<strong>01</strong>441 A 109 K2 Replacement Euronav III by Euronav V Prerequisite conditions:- Dual GNS-530A<br />
28.<strong>04</strong>.2008<br />
(Euroavionics)By removing- the existing RN 5 installation- RN 5 Euronav III Map Generator<br />
Euronav III Map Generatorand installing- a new installed with interface to the GNS-530A #2-<br />
RN 6 Euronav V Digital Map Generator CLN.14-3.0 Control Unit installed- DYNT64-2.0<br />
Display installed<br />
<strong>EASA</strong>.R.S.<strong>01</strong>488 EC-135-T2 COM/NAV/ATC Avionics System Installation. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
<strong>04</strong>.02.2009<br />
P-<strong>EASA</strong>.A.S.03930 LEARJET 35A Installation of Artex ELT C406-02 (Cobham). None. None. <strong>01</strong>.12.2009<br />
P-<strong>EASA</strong>.A.S.03936 LEARJET 35A Installation of ART 2000 Weather Radar with<br />
KMD 850 MFD (Honeywell).<br />
None. None. <strong>01</strong>.12.2009<br />
P-<strong>EASA</strong>.A.S.03933 LEARJET 35A Installation of SSFDR F1000 (L-3<br />
Communications).<br />
None. None. <strong>01</strong>.12.2009<br />
P-<strong>EASA</strong>.A.S.03932 LEARJET 35A Installation of EGPWS Mk VIII (Honeywell). None. None. <strong>01</strong>.12.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 98/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030099 AVIONICS INTEGRATION &<br />
MBB-BK 117 C-1 Cabin Interior RetrofitInstallation of a cabin S/N 7541 Prior to installation of this modification it 21.05.2<strong>01</strong>0<br />
ENGINEERING<br />
interior retrofit based on AIEC engineeringorder<br />
must be determined thatthe<br />
854-062.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10030961 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10032056 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10033418 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10035543 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10037002 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10038857 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10038859 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10038860 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
10039495 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
BEECH 200 Installation of HySpex Camera System (NEO) Only aeroplanes in compliance with the<br />
preconditions as listed inChapter C of<br />
Engineering Order, Doc. No. CV877-062,<br />
Revision A, dated14-Jul-2<strong>01</strong>0, or later<br />
approved revision, are eligible for this change.<br />
35A / 36A COMJAM System Installation This COMJAM system installation approval is<br />
only applicable to thefollowing aircraft<br />
equipped with certain special mission<br />
provisions(including electrical power supply,<br />
harnesses and wiring, workstationand<br />
antennas): s/n's 35A-139, 35A-179, 35A-268,<br />
35A-33<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
P-<strong>EASA</strong>.A.S.03870 PA-31T TAS 620 System Installation by installing an<br />
Avidyne TAS 620 TrafficAdvisory System<br />
None None 03.07.2009<br />
EC135 P2+ GNS-530 & GNS-430A InstallationOut: Garmin This <strong>EASA</strong> STC is only valid after <strong>EASA</strong> The approval holder shall fulfil the 29.06.2<strong>01</strong>1<br />
GNS-530W & GNS-430WIn: Garmin GNS-530 Validation of FAA STC SR09137RC- obligations of Part 21,<br />
& GNS-430AComplete retrofit done by D(Extended R/H Side Instrument Panel).S/N: Paragraph21.A109. Prior to installation of<br />
American Eurocopter under FAA Form 337 0684<br />
this modification it must be determined<br />
dated11.12.2009 and FAA Form 8110-3 dated<br />
thatthe interrelationship between this<br />
11.12.2009<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
HAWKER 900XP Cabin Interior Removal and Modification. None. None. 24.10.2<strong>01</strong>1<br />
16.07.2<strong>01</strong>0<br />
05.10.2<strong>01</strong>0<br />
CL-600-2B16 Iridium Satcom Installation (ICG) None The e-phone, base station and docking<br />
station units not installed, thesame will be<br />
performed under DOA minor change<br />
separately.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any othe<br />
20.03.2<strong>01</strong>2<br />
CL-600-2B16 Terrain Awareness and Warning System<br />
(TAWS) Upgrade to SCN 12.0 (UASC)<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.03.2<strong>01</strong>2<br />
CL-600-2B16 CVR-120 replacement by CVR-120R (UASC) None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.03.2<strong>01</strong>2<br />
REV. 1 35A/36A Enhanced Surveillance Upgrade to MST 67A<br />
Transponder (Honeywell)<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 99/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039496 AVIONICS INTEGRATION &<br />
35A/36A Replacement of UNS-1M by UNS-1Fw MMMS None Prior to installation of this modification it 08.05.2<strong>01</strong>2<br />
ENGINEERING<br />
(UASC)<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1282 AVIONICS INTEGRATION &<br />
ENGINEERING<br />
CL-600-2B16 CPDLC System Capability CPDLC system not compliant with<br />
Commission Regulation (EC) 29/2009<br />
10<strong>01</strong>4074 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>166 BAE JETSTREAM 31<br />
Installation of Airborne Collision Avoidance<br />
BAE JETSTREAM 32<br />
System (ACASII)<br />
10<strong>01</strong>4139 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>252 CESSNA 550<br />
Installation of an Airborne Collision Avoidance<br />
CESSNA 650<br />
System (ACAS II)<br />
10<strong>01</strong>4184 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>322 CN 235M-100 Installation of a Ground Proximity Warning Aircraft Registration A40-CU and A40-<br />
10<strong>01</strong>4198 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>341 BAE 125-800<br />
system (GPWS) & Terrain Awareness Warning CVSerial numbers C062 and C063<br />
System (TAWS)<br />
Installation of an Airborne Collision Avoidance<br />
System (ACAS II)<br />
10<strong>01</strong>4215 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>376 CESSNA 550 SERIES<br />
Avionics Mobile Services Modification<br />
CESSNA 560 SERIES<br />
AM/1478. Installation of an Airborne Collision<br />
Avoidance System (ACAS II)<br />
10<strong>01</strong>4303 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>547 PIPER PA-31T2 Certification of FAA Approved field modificains<br />
for the issue of an <strong>EASA</strong> C of A.Avionics<br />
Mobile Services AFM supplement Part 21-008<br />
<strong>01</strong>4 GNS-530,Avionics Mobile Services AFM<br />
supplement Part 21-008 <strong>01</strong>5 KMH-<br />
880Avionics Mobile Services AFM supplement<br />
Part 21-<br />
Applicable to s/n 5<strong>04</strong>2 onlyPrior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
effectupon the airworthi<br />
10<strong>01</strong>4431 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.02479 1124A WESTWIND II Installation of Airborne Collision Avoidance<br />
System (ACAS II)<br />
13.03.2006<br />
10<strong>01</strong>4480 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.02543 REV 2 HAWKER HS 125-700 SERIES Installation of an Airborne Collision Avoidance This STC is approved only for the product<br />
09.10.2006<br />
REV 2<br />
System (ACASII)Amendment of the above to configuration as defined in the approved design<br />
include installation variations for alternate data referred to in the paragraph "Description".<br />
aircraft with regard to the Downlink Aircraft Compatibility with other aircraft/engine<br />
Parameters (DAP's) for Mode-S Enhanced configurations shall be determined by the<br />
Surveillance (EHS)<br />
installer.<br />
10<strong>01</strong>4481 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.A.S.02544 HS 125-700 SERIES Installation of a Digital Air Data Display System -- 06.<strong>04</strong>.2006<br />
10<strong>01</strong>5654 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>63<br />
REVISION 1<br />
10<strong>01</strong>5663 AVIONICS MOBILE DESIGN SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>64<br />
REVISION 1<br />
10036511 AVIONICS MOBILE DESIGN SERVICES<br />
(AM<br />
REV 1 HS 125-700 SERIES Installation of a Rockwell Collins TCAS-4000<br />
Traffic Alert and Collision Avoidance System<br />
(TCAS-II)<br />
REV 1 - HS 125-700 SERIES Installation of a Ground Proximity Warning<br />
System (GPWS) and Terrain Awareness<br />
Warning System (TAWS)<br />
10<strong>01</strong>5345 AVIONICS SUPPORT GROUP, INC. <strong>EASA</strong>.IM.A.S.0<strong>04</strong>46 FAA STC ST02900AT BOEING 747-200<br />
BOEING 747-300<br />
HAWKER 800XP Installation of a Flight Data Recorder (FDR)<br />
System.<br />
T2CAS provisions on Boeing 747-200 & -300<br />
Series Aircraft.<br />
<strong>04</strong>.09.2<strong>01</strong>2<br />
17.03.2005<br />
08.<strong>04</strong>.2005<br />
29.11.2005<br />
06.10.2005<br />
26.07.2005<br />
18.11.2005<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
09.06.2006<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
09.06.2006<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.09.2<strong>01</strong>1<br />
1. Subject to compliance with the provisions of<br />
Part 21 Subpart E, this STC and associated<br />
shall remain valid until surrendered, withdrawn<br />
or otherwise terminated.2. If transfer of this<br />
STC is requested under Part 21A.116, the<br />
STC will be reissued.3. This<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 100/<strong>462</strong><br />
21.12.20<strong>04</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5447 AVIONICS SUPPORT GROUP, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>188 FAA STC ST02976AT BOEING 737-300 SERIES Installation of ACCS Elementary and Enhanced 1. According to FAA STC No ST02976AT2.<br />
25.10.2005<br />
BOEING 737-400 SERIES Surveillance capable Mode S Transponders This STC is approved only for the product<br />
BOEING 737-500 SERIES and Flight ID capable Transponder Control configuration as defined in the approved design<br />
Panel<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by<br />
10<strong>01</strong>5660 AVIONICS SUPPORT GROUP, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>637 FAA STC ST02763AT BOEING 757-200<br />
BOEING 757-300<br />
Installation of an In-Flight Cabin Video<br />
Surveillance System<br />
10<strong>01</strong>6116 AVIONICS SUPPORT GROUP, INC. <strong>EASA</strong>.IM.A.S.02307 FAA STC ST03071AT BOEING 727-200 Installation of Avionics System for Reduced<br />
Vertical Separation Minimum (RVSM)<br />
Provisions into a Boeing 727-200 aircraft.<br />
10026764 AVIONICS SUPPORT GROUP, INC. P-<br />
<strong>EASA</strong>.IM.A.S.03249<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
FAA STC ST03700AT 747-400, 747-400F Installation of an International communications After Installation of this STC the operator is<br />
Group ICS-220A IridiumSATCOM System in a required to incorporatein the Airworthiness<br />
B747-400/-400F series aircraft in accordance Limitations Section of the Instructions<br />
withAvionics Support Group, Inc. Master Data forContinued Airworthiness applicable to the<br />
List 28546-MDL, Revision A,dated March 16, existing Maintenance Program adetailed<br />
2009, or later FAA approved revisi<br />
inspection item at a threshold of 8400 Fl<br />
16.03.2006<br />
<strong>04</strong>.06.2007<br />
1) Prior to installation of this modification 10.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10<strong>01</strong>3962 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.00646<br />
GmbH<br />
REV. 1 Installation of single/dual Garmin GTX330D. 17.06.2008<br />
10<strong>01</strong>4031 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>097 PIPER PA-31 Installations of Avidyne FM850, 2x Garmin This STC is approved only for the product<br />
26.10.2005<br />
GmbH<br />
GTX330D Mode S Transponder and Garmin configuration as defined in the approved design<br />
GMA340 Marker/Audio<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4032 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>098 BEECH 300LW Installation of Mode S Transponder TDR94D<br />
22.06.2005<br />
GmbH<br />
with new Top Antenna.<br />
10<strong>01</strong>4089 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>185 CESSNA 5<strong>01</strong><br />
Installation of Artex ELT C406-1. 28.<strong>04</strong>.2005<br />
GmbH<br />
CESSNA 551<br />
10<strong>01</strong>4174 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>309 BEECH 65-90<br />
Installation of Skywatch L3 SKY899, Radar<br />
07.10.2005<br />
GmbH<br />
BEECH 65-A90<br />
BEECH 90<br />
BEECH B90<br />
BEECH C90<br />
BEECH C90 A<br />
BEECH E90<br />
RDR 2000 and EGPWS KGP 560<br />
10<strong>01</strong>4213 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>372 CESSNA 5<strong>01</strong><br />
Installation of Dual Garmin GNS 430A <strong>01</strong>.09.2005<br />
GmbH<br />
CESSNA 551<br />
10<strong>01</strong>4273 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>507<br />
GmbH<br />
BEECH 90 Installation of Avidyne FM850 18.08.2005<br />
10<strong>01</strong>4311 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.<strong>01</strong>556 CESSNA 525 Installation of SKY497 and TAWS 8000The<br />
21.06.2006<br />
GmbH<br />
SKY497 is wired to the new Antenna, existing<br />
AM-250 Copilot Altimeter, i-linc MFD and Audio<br />
CTL. The TAWS 8000 is wired to theexisting<br />
MFD, KLN90B and ADC 200<br />
10<strong>01</strong>4340 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
<strong>EASA</strong>.A.S.<strong>01</strong>598 CESSNA 550 Installation of CAS67A (incl. MST67A), Mark<br />
VIII, Kannad 406AF and Garmin GPS400<br />
10<strong>01</strong>4448 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.025<strong>01</strong> PIPER PA-46-310P Installation of GNS530, with GDC31 Roll<br />
GmbH<br />
Steering Converter<br />
10<strong>01</strong>4546 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.02634 PIPER PA-31P Installation of COM/NAV/GS/GPS Garmin<br />
GmbH<br />
GNS530/GNS430 (dual installation)<br />
10<strong>01</strong>4566 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.02667 PIPER PA34-200<br />
Installation of dual Garmin GNS430 and Dittel<br />
GmbH<br />
PIPER PA34-200T<br />
PIPER PA34-220T<br />
FSG 2T in a Piper PA34.<br />
Certification Basis of the Change: CS 25,<br />
additionally AMC 20-4 (Basic R-Nav), AMC 20-<br />
5 (GPS), JAA Leaflet No. 8, Rev. 2 (ACAS<br />
II),JAA Leaflet No. 12 (TAWS), JAA Leaflet<br />
No. 13 Rev. 1 (Mode-S ELS), JAA Leaflet No.<br />
18 (Mode-S EHS)<br />
1. Maximum operating altitude 18.000 ft2.<br />
GPS is not approved for TERM and APPR<br />
NAV3. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with oth<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 1<strong>01</strong>/<strong>462</strong><br />
11.<strong>04</strong>.2006<br />
05.<strong>04</strong>.2006<br />
11.09.2006<br />
22.05.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4615 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.02744 PIPER PA-46-310P<br />
Installation of COM/NAV/GS/GPS GNS430, This STC is approved only for the product<br />
07.05.2007<br />
GmbH<br />
PIPER PA-46-350P<br />
with GDC31 Roll Steering<br />
configuration as defined in the approved design<br />
Converter.Installation of Diversity Mode S data referred to in the paragraphs "Description"<br />
XPDR Garmin GTX330D.Installation of TCAS and “Associated Technical Documentation”.<br />
Avidyne TAS610.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4705 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10<strong>01</strong>4772 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10<strong>01</strong>4773 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10<strong>01</strong>4802 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10<strong>01</strong>4811 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10<strong>01</strong>5159 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10<strong>01</strong>5229 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
<strong>EASA</strong>.A.S.02876 BEECH 65-90<br />
BEECH 65-A90<br />
BEECH B90<br />
BEECH C90<br />
BEECH C90A<br />
BEECH E90<br />
<strong>EASA</strong>.A.S.02964 FAIRCHILD SWEARINGEN SA<br />
226-AT<br />
FAIRCHILD SWEARINGEN SA<br />
226-T<br />
FAIRCHILD SWEARINGEN SA<br />
226-T(<br />
FAIRCHILD SWEARINGEN SA<br />
227-AT<br />
Dual Installation of COM/NAV/GS/GPS Prior to installation of this modification the<br />
GNS430, with GDC31 Roll Steering Converter; installer must determine that the<br />
Installation of Stormscope WX500 and TCAS interrelationship between this modification and<br />
Avidyne TAS610.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of Mode S XPDR Diversity Garmin<br />
GTX 330D with now top Antenna.<br />
Prior to installation of this modification the<br />
installer msut determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>EASA</strong>.A.S.02965 CESSNA 525 Installation of one Garmin GNS530 in a Cessna Prior to installation of this modification the<br />
525.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
<strong>EASA</strong>.A.S.03005 CESSNA 525<br />
CESSNA 525A<br />
<strong>EASA</strong>.A.S.03<strong>01</strong>6 CESSNA 525A Installation of single/ dual Garmin GTX<br />
330DModel: Cessna 525A, S/N 00<strong>01</strong> and on<br />
<strong>EASA</strong>.A.S.03528 FAIRCHILD SWEARINGEN SA<br />
226-AT<br />
FAIRCHILD SWEARINGEN SA<br />
226-T<br />
FAIRCHILD SWEARINGEN SA<br />
226-T(<br />
FAIRCHILD SWEARINGEN SA<br />
226-TC<br />
FAIRCHILD SWEARINGEN SA<br />
227-AC<br />
FAIRCHILD SWEARINGEN SA<br />
227-BC<br />
FAIRCHILD SWEARINGEN SA<br />
227-DC<br />
<strong>EASA</strong>.A.S.03647 CESSNA 5<strong>01</strong><br />
CESSNA 551<br />
Installation of Garmin GTX330D single/dual. Limited to Cessna 525, SN 00<strong>01</strong>-<br />
0359.Compatibility of this modification with<br />
other previously approved modifications must<br />
be determined by the installer.<br />
Installation of honeywell Mark VI EGPWS -<br />
Optional installation of Comant CI4<strong>01</strong>-220 GPS<br />
Antenna.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of COM/NAV/GS/GPS Garmin 1. Prior to installation of this modification the<br />
GNS430W (AW) or COM/NAV/GS/GNS530W installer must determine that the<br />
(AW).<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 102/<strong>462</strong><br />
12.07.2007<br />
16.10.2007<br />
19.09.2008<br />
08.02.2007<br />
21.06.2007<br />
06.05.2008<br />
18.11.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5244 AVIONIK STRAUBING ENTWICKLUNGS <strong>EASA</strong>.A.S.03679 CESSNA 4<strong>01</strong><br />
Installation of Single or Dual Garmin G600 1) Prior to installation of this modification the<br />
15.06.2009<br />
GmbH<br />
CESSNA 4<strong>01</strong>A<br />
Avionics System and dual Garmin<br />
installer must determine that the<br />
CESSNA 4<strong>01</strong>B<br />
GNS4/530(A)W GPS/COMM/NAV<br />
interrelationship between this modification<br />
CESSNA 402<br />
andany other previously installed modification<br />
CESSNA 402A<br />
will introduce no adverse effect upon the<br />
CESSNA 402B<br />
CESSNA 402C<br />
CESSNA 4<strong>04</strong><br />
CESSNA 406<br />
CESSNA 411<br />
CESSNA 411A<br />
CESSNA 414<br />
CESSNA 414A<br />
CESSNA 421<br />
CESSNA 421A<br />
CESSNA 421B<br />
CESSNA 421C<br />
CESSNA 425<br />
CESSNA 441 SERIES<br />
CESSNA F406<br />
airworthiness of the product.2) The ins<br />
10026784 AVIONIK STRAUBING ENTWICKLUNGS P-<strong>EASA</strong>.A.S.03917 REV. 1 PIPER PA-46-310P<br />
Installation of Single or Dual Garmin G500 / This STC is limited to the configuration of Prior to installation of this modification the 23.<strong>04</strong>.2<strong>01</strong>0<br />
GmbH<br />
PIPER PA-46-350P<br />
G600 Avionics System(including SVS) and aircraft, equipment type,and functions as listed installer must determinethat the<br />
PIPER PA-46-500TP<br />
Dual Garmin GNS4/530(A)W<br />
in <strong>EASA</strong> approved Instructions for<br />
interrelationship between this modification<br />
PIPER PA-46R-350T<br />
GPS/COMM/NAV.<br />
Installation,Doc. No. ASR-2009-075-IFI-10-00, and any otherpreviously installed<br />
Amdt. Level 00, dated 18-Jun-2009,especially modification will introduce no adverse<br />
as mentioned in Item 2. of this docume effect uponthe airworthiness of the<br />
product. The installati<br />
10026941 AVIONIK STRAUBING ENTWICKLUNGS P-<strong>EASA</strong>.A.S.03675 BEECH 60, A60, B60 Installation of Garmin GNS430W /<br />
None 1) Prior to installation of this modification 25.08.2009<br />
GmbH<br />
GNS430AW / GNS430 / GNS530W /<br />
the installer mustdetermine that the<br />
GNS530AW/ GNS530, with Installation of<br />
interrelationship between this modification<br />
Garmin GA35/GA56 GPS Antenna.<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10028197 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10028486 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10028816 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10029814 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10029856 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
P-<strong>EASA</strong>.A.S.03875 B90, C90, C90A, C90GT, C90GTI,<br />
E90, F90<br />
P-<strong>EASA</strong>.A.S.03916 MOONEY M20 C, E, F, G, J, K<br />
MOONEY M20 L, M, R, S<br />
Installation of an FMS System Universal UNS-<br />
1Lw and an EGPWS KGP 560<br />
None The installation of an LP/LPV Monitor is<br />
optional<br />
08.12.2009<br />
SEE ATTACHED MODEL LIST Installation of an Aspen EFD-1000 ProSystem. None. Prior to installation of this modification the 15.<strong>01</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
PA-46-310P, -350P,<br />
PA-46-500TP, PA-46R-350T<br />
1) M20C, M20E, M20F, M20G,<br />
1) M20J, M20K, M20L,<br />
2) M20M, M20R, M20S<br />
Installation of Aspen EFD1000 PRO System. None. Prior to installation of this modification the 11.02.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
Installation of a Stormscope Avidyne TWX670 None This STC is also applicable to Turbine<br />
Converted Aircraft (PA46-310-DLX,PA46-<br />
350DLX) according to FAA STC<br />
ST00541SE. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other previous<br />
22.<strong>04</strong>.2<strong>01</strong>0<br />
Installation of a Garmin G500 System None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>04</strong>.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 103/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029947 AVIONIK STRAUBING ENTWICKLUNGS<br />
CESSNA 340, 340A Installation of Thommen AD32 Air Data None Prior to installation of this modification it 05.05.2<strong>01</strong>0<br />
GmbH<br />
Display/Altimeter and AvionikStraubing Altitude<br />
must be determined thatthe<br />
Preselect System APS4A<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030025 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
1003<strong>04</strong><strong>04</strong> AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10031180 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10032176 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10033937 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
100346<strong>01</strong> AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10034991 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
10035162 AVIONIK STRAUBING ENTWICKLUNGS<br />
GmbH<br />
PA-31-325, PA31-350<br />
PA-31P, PA-31T, PA-31T1,<br />
PA-31T2, PA-31T3, PA-31,<br />
REV. 1 1. PA-31, PA-31-325, PA-31-350<br />
2. PA-31P, PA-31T, PA-31T1<br />
2. PA-31T2<br />
REV. 1 1. PA-32-260, PA-32-300<br />
1. PA-32R-300, PA-32RT-300<br />
1. PA-32R-3<strong>01</strong>T, PA-32-3<strong>01</strong><br />
1. PA-32RT-300T, PA-32R-3<strong>01</strong><br />
2. PA-32-3<strong>01</strong>XTC, PA-32-3<strong>01</strong>FT<br />
REV. 1 31<strong>01</strong>,3102,3103,3107,3108<br />
3109,3110,3112,3116,32<strong>01</strong><br />
3202,3206,3207,3212,3216,3217<br />
Installation of Avidyne TAS 610/620/9900BX,<br />
Transponder Couplers andBottom/Top TAS<br />
Antennas<br />
EC 120 B Panel Modification including position change of<br />
ApolloMX20(GarminGMX200),HSI Indicator KI<br />
525 and installation of new Attitude Indicator<br />
and Moving Terrain MT-Vision MFD.<br />
210, 210-5, -5A<br />
210A, B, C, D, E, F, G, H, J<br />
210K, L, M, N, R<br />
P210N, R<br />
T210F, G, H, J, K, L, M, N, R<br />
SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
PA-28-150, -160, -235, -2<strong>01</strong>T<br />
PA-28-180, -181, -161, -140<br />
PA-28-236, -151<br />
PA-28R-180, -200, -2<strong>01</strong>, -2<strong>01</strong>T<br />
PA-28RT-2<strong>01</strong>, -2<strong>01</strong>T<br />
Dual/Single installation of Garmin<br />
GNS430(A)W/530(A)W with GPS<br />
AntennaGarmin GA35 and Roll Steering<br />
Converter DAC GDC31.<br />
Dual/Single Installation of Garmin<br />
GNS430(A)W / GNS530(A)W<br />
Dual/Single Installation of Garmin<br />
GNS430(A)W I GNS530(A)W and<br />
optionalInstallation of Marker Receiver<br />
Honeywell (Bendix/King) KMR675<br />
Dual/Single Installation of Garmin<br />
GNS430(A)W / GNS530(A)W.<br />
Restricted to aircraft which have Avidyne<br />
EX500/600 MFD, Garmin GDU620PFD,<br />
Garmin GNS430(A)W or Garmin<br />
GNS530(A)W system installed in orderto<br />
display the information.<br />
Prior to installation of this modification it 12.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.06.2<strong>01</strong>0<br />
none Prior to installation of this modification the 13.09.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.10.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
24.02.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.<strong>04</strong>.2<strong>01</strong>1<br />
Installation of PFD Aspen EFD1000 PRO. None. The Installation of the Avionik Straubing<br />
Altitude Preselect SystemAPS4A is<br />
optional.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
Installation of dual GPS/NAV/COMM Garmin<br />
GNS430/530(A)W.<br />
None. Dual installation of Garmin GNS<br />
430/530(A)W requires a third<br />
independentCOMM device or an<br />
independent NAV/DME or ADF/DME<br />
combination.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and an<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 1<strong>04</strong>/<strong>462</strong><br />
18.05.2<strong>01</strong>1<br />
31.05.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035456 AVIONIK STRAUBING ENTWICKLUNGS<br />
F406 Cockpit Upgrade basing on dual Garmin G600 Only applicable for Aircraft S/N 097 and up A third, fully independent COMM device 24.06.2<strong>01</strong>1<br />
GmbH<br />
and GNS430W<br />
must have been already installed.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will<br />
10036102 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036149 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036230 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036231 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036587 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036677 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036784 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10036858 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
REV. 1 DA 40, 40D, 40F Installation of PFD Aspen EFD1000 PRO. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.08.2<strong>01</strong>1<br />
REV. 1 1. PA-31-325, PA-31-350,<br />
1. PA-31, PA-31-300,<br />
2. PA-31P, PA-31P-350,<br />
2. PA-31T, PA-31T1,<br />
2. PA-31T2, PA-31T3<br />
SR20, SR22 Installation of a Primary Function Display<br />
Avidyne EXP5000<br />
The aircraft must have been already equipped<br />
with suitable GPS system.<br />
Prior to installation of this modification it 16.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
5<strong>01</strong>, 551 Installation of a TAS SystemL3 Communication The aircraft must have been already equipped Prior to installation of this modification it 23.08.2<strong>01</strong>1<br />
SKY899<br />
with a suitableMultifunction Display.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
208, 208B Installation of a Satellite Antenna Chelton HGA- none Prior to installation of this modification it 23.08.2<strong>01</strong>1<br />
7000<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of one or more Avionik Straubing<br />
Heater Control Unit(s)HCU200.<br />
60, A60, B60 Installation of a Traffic Advisory System<br />
Avidyne TAS 605/615/620,Ryan<br />
9900BX<br />
BEECH 60, A60, AND B60 Installation of Garmin G600 System with<br />
Synthetic Vision Technology(SVT).<br />
60, A60, B60 Installation of a Satellite Data Link System<br />
Garmin GSR56.<br />
None. The HCU200 as approved together with<br />
this STC must be produced andqualified<br />
in accordance with Avionik Straubing<br />
Declaration of Design andPerformance<br />
(DDP) ASR-1038-HCU200-002-DDP-<br />
02.Prior to installation of this modification<br />
it must be determined thatthe<br />
<strong>04</strong>.10.2<strong>01</strong>1<br />
None The aircraft must already have been<br />
equipped with a suitableMultifunction<br />
Display.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or re<br />
28.09.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.10.2<strong>01</strong>1<br />
None. The aircraft must already have been<br />
equipped with a suitableMultifunction<br />
Display.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or re<br />
12.10.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 105/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037583 AVIONIK STRAUBING ENTWICKLUNGS<br />
1. PA-31-350<br />
Installation of Garmin G600 System with None A suitable Garmin GPS System must 08.12.2<strong>01</strong>1<br />
GMBH<br />
1. PA-31, PA-31-300, PA-31-325 Synthetic Vision (SVT)<br />
have been already installed. This STC<br />
2. PA-31P, PA-31P-350<br />
includes the optional installation of<br />
2. PA-31T, PA-31T1, PA-31T2<br />
Avionik StraubingEmergency Power Unit<br />
2. PA-31T3<br />
EPU6A5 and/or Standby Attitude Gyro<br />
AIM 505 and/orAvionik Straubing Altitude<br />
Preselector APS4A. Prior to ins<br />
10037817 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10038943 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10<strong>04</strong><strong>04</strong>68 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10<strong>04</strong>1<strong>04</strong>9 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10<strong>04</strong>1441 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10<strong>04</strong>2720 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10<strong>04</strong>2753 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
10<strong>04</strong>2880 AVIONIK STRAUBING ENTWICKLUNGS<br />
GMBH<br />
1. M20, M20A, M20B, M20C,<br />
M20D<br />
1. M20E, M20F, M20G, M20J<br />
1. M20K, M20L, M20S<br />
2. M20M, M20R<br />
SR20<br />
SR22<br />
Dual/Single Installation of Garmin<br />
GPS/COMM/NAV<br />
GNS430(A)W/GNS530(A)W<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.12.2<strong>01</strong>1<br />
Installation of PFD Aspen EFD1000 PRO. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.03.2<strong>01</strong>2<br />
PA-42, PA-42-720, PA-42-1000 Installation of Garmin G600 System with<br />
Synthetic Vision (SVT)<br />
DA40, DA40D, DA40F Dual/Single Installation of Garmin<br />
GPS/COMM/NAV GNS430W / GNS530W.<br />
REV. 1 650 Dual Installation of Flight management System<br />
Universal UNS-1Lw<br />
none A suitable Garmin GPS System must<br />
have been already installed.This STC<br />
includes the optional installation of<br />
Avionik StraubingAltitude Preselector<br />
APS4A and/or Standby Altitude Indicator<br />
Sigmatec5000B-40 and/or Standby<br />
Altitude Indicator United Instruments<br />
05.07.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.08.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.09.2<strong>01</strong>2<br />
SC7 SERIES 3 Installation of PFD ASPEN EFD1000 C3 None. This STC includes the optional installation 14.12.2<strong>01</strong>2<br />
of a multifunction displayASPEN<br />
EFD1000 MFD. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and<br />
525, 525A Single Installation of GPS/COMM/NAV System<br />
Garmin GTN725/750.<br />
B200, B200C, B200GT, B200CGT Installation of Flight Management System<br />
Universal UNS-1Lw<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.12.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.12.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 106/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4810 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03<strong>01</strong>5 CESSNA 5<strong>01</strong> Replacement of XPDR to GARMIN GTX 330D<br />
Diversity Mode S and change of GPS interface<br />
29.<strong>01</strong>.2008<br />
10<strong>01</strong>4846 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03067 PIPER PA-31T1 Replacing of existing avionics by newer<br />
generation of avionics in accordance with Unit<br />
change overview Nr. 063247-050.<br />
Limited to S/N 31T-79<strong>04</strong><strong>01</strong>4 17.<strong>01</strong>.2008<br />
10<strong>01</strong>4858 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03082 PIPER PA-60-6<strong>01</strong>P Avionics retrofitOut. Radar system Bendix RDR-Reg.:<br />
HB-LIN S/N: 571-7963248/<br />
150; VHF-COM King KY-196; VHF-NAV King<br />
KN-53, Indicators KI-252A, KI-2<strong>04</strong>, and KI-226;<br />
ADF system King KR-87 incl. Antenna KA-44B,<br />
obsolete ADF antenna Collins ANT-650A and<br />
adapter ADA-650, Moving map Eventide A<br />
08.10.2007<br />
10<strong>01</strong>4864 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03088 MOONEY M20J Installation of replaced Avionics according CP<br />
No. 073372<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>4916 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03162 PIPER PA-28R-2<strong>01</strong>T Replacing of existing avionics by newer<br />
generation of avionics in accordance with Unit<br />
change overview Nr. 073528-050, Rev 0,<br />
dated11.06.07.<br />
Limited to S/N T21059922. 08.05.2008<br />
10<strong>01</strong>4986 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03278 REV. 1 Avionics TetrofitOut: King Mode A/C<br />
Transponder KT-76A, king Audio Panel KMA-<br />
24, Autopilot Badin Crouzet.In: Garmin Mode S<br />
Transponder GTX-330, Garmin Audio Panel<br />
GMA-340, Autopilot S-Tec System 55X.<br />
Reg.: HB-DCE, S/N 420. 06.09.2007<br />
10<strong>01</strong>5064 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03390 CESSNA T210L Replacing of existing avionics by newer<br />
generation of avionics in accordance with Unit<br />
change overview Nr. 073775-050, Rev 0,<br />
dated05.12.07.<br />
10<strong>01</strong>51<strong>04</strong> AVIONITEC Ltd. <strong>EASA</strong>.A.S.03447 BEECH F90 Avionics replacing: Garmin GTX330D XPDR<br />
and Weather Radar System RDR 2000.<br />
10<strong>01</strong>5163 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03534 PIPER PA-46-350P Avionics upgrade to GNS 430, Removed<br />
Equipment:- KX-165 NAV/COM 2- KI-206 NAV<br />
2 IndicatorInstalled Equipment- GNS-430<br />
NAV/COM/GPS 2- GI-106A NAV/GPS<br />
Indicator 2- GA-56 GPS 2 Antenna<br />
21.11.2008<br />
Limited to S/N T21059922. 27.02.2008<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.Reg.: HB-PPH<br />
10<strong>01</strong>5191 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03575 COMMANDER AIRCRAFT RC114 Avionics Retrofit Removed Equipment: - KMA 1. Prior to installation of this modification the<br />
23.12.2008<br />
20 Audio Panel- Isocom Intercom - Dual KX installer must determine that the<br />
155 COM/NAV- KI 203 NAV #2 Indicator- GPS interrelationship between this modification and<br />
#1, Garmin GPS 100 incl. Antenna- OEM any other previously installed modification will<br />
vacuum Directional Gyro- KT 76A Transponder- introduce no adverse effect upon the<br />
Narco ELT 10 New installed Equipment:- GMA airworthiness of the product. The i<br />
340<br />
10<strong>01</strong>5278 AVIONITEC Ltd. <strong>EASA</strong>.A.S.03794 PIPER PA-46-350P (MALIBU Installation Weather avoidance systems and Reg.: HB-POY, SN: <strong>462</strong>2090 10.03.2009<br />
MIRAG<br />
TAS and ME406 ELT by installation of:-<br />
Avidyne MFD EX 500- Avidyne Traffic Advisory<br />
system TAS 610- Avidyne Tactical Weather<br />
detection System TWX 670- Avidyne Iridium<br />
Data Link Transceiver MLX 770- Artex ME406<br />
ELT<br />
10033155 AVIONITEC Ltd. T303 Avionics RetrofitRemoved: -Garmin GNS 430 Limited to: HB-LUV, S/N T30300058 The approval holder shall fulfil the 21.12.2<strong>01</strong>0<br />
NAV/COM/GPS-King KX 165 NAV/COM with<br />
obligations of Part 21,<br />
King KI 206 Indicator-ARC RTA 476A DME-<br />
Paragraph21.A109. Prior to installation of<br />
ARC R-446A ADF with ARC IN 346A<br />
this modification it must be determined<br />
IndicatorInstalled:-Garmin GNS 530W<br />
thatthe interrelationship between this<br />
NAV/COM/GPS (upgrade from a Garmin GNS<br />
modification and any other<br />
430)-Garmin GNS 430W NAV/COM/GP<br />
previouslyinstalled modification and/ or<br />
repai<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 107/<strong>462</strong><br />
23.09.2008<br />
30.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034285 AVIONITEC Ltd. REV. 1 PA-46-310P Avionics Retrofit Removed Equipment: -,,Dual S/N: HB-PJW<br />
KX 165 NAV/COM System-,,WX 1000<br />
Stormscope System-,,Argus 5000 Moving Map-<br />
,,KMA 24 Audio Panel -,,PM 2000 Intercom<br />
New installed Equipment:-,,GNS 530W<br />
NAV/COM/GPS System #1-,,GNS 430W<br />
NAV/COM/GPS System #2-,,<br />
Not Applicable 25.03.2<strong>01</strong>1<br />
10034590 AVIONITEC Ltd. M20K Avionics RetrofitRemoved: ,,- King KX 165 S/N: 25-1170 HB-DHG The approval holder shall fulfill the 13.<strong>04</strong>.2<strong>01</strong>1<br />
NAV/COM with King KI 206 CDI,- King<br />
obligations of Part 21,<br />
KR 87 ADF with King KI 229 Indicator- Garmin<br />
Paragraph21.A109.Prior to installation of<br />
GNS530 NAV/COM/GPSInstalled: ,,- Garmin<br />
this modification it must be determined<br />
530W NAV/COM/GPS- Garmin 430W<br />
thatthe interrelationship between this<br />
NAV/COM/GPS with GI 106A<br />
modification and any other<br />
IndicatorVertically guided RNAV<br />
previouslyinstalled modification and/ or<br />
repai<br />
10037582 AVIONITEC Ltd. PA-28-236 IFR Avionics upgradeRemoved: - King KY S/N: 28-8<strong>01</strong>1<strong>01</strong>1 HB-PEN The approval holder shall fulfill the 08.12.2<strong>01</strong>1<br />
197A COM- King KMA 20Audio Panel- King<br />
obligations of Part 21,<br />
KN 53 NAV Receiver- King KI 203 NAV<br />
Paragraph21A.118A.Prior to installation<br />
Indicator- David Clark Isocom Intercom<br />
of this modification it must be determined<br />
Installed: - Garmin GNS530W GPS/COM/NAV<br />
thatthe interrelationship between this<br />
with GA35 antenna- Garmin GMA 347 Audio<br />
modification and any other<br />
Panel- King KR 87 ADF S<br />
previouslyinstalled modification and/ or<br />
repa<br />
10038996 AVIONITEC Ltd. REV. 1 BEECH 35-C33A Upgrade Garmin GNS430, repl.<br />
S/N CE-39, F-BNOI The approval holder shall fulfil the 05.<strong>04</strong>.2<strong>01</strong>2<br />
NAV/COMRemoved:-Garmin GNS430 System-<br />
obligations of Part 21,<br />
King KX 155 NAV/COM system-King KR 85<br />
Paragraph21.A118. Prior to installation of<br />
ADF SystemInstalled:-Dual Garmin GNS430W<br />
this modification it must be determined<br />
System-King KR 87 ADF System<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10037702 AZRA LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>16 REV. 2 737-200, 737-200C, 737-300 Modification of Wing Inboard & Outboard Aft Scheduled inspections and repairs are required Prior to installation of this modification it 22.12.2<strong>01</strong>1<br />
737-400, 737-500<br />
Trailing Edge Flaps Revision 2 of the STC with in accordance with thefollowing documents: 1. must be determined thatthe<br />
reference <strong>EASA</strong>.IM.A.S.<strong>01</strong>16 has been issued Chapter 05 of the "737-200, -200C Aircraft interrelationship between this modification<br />
asa result of its transfer from AeroTech Maintenance ManualSupplement”,Report No. and any other previouslyinstalled<br />
Services Inc (ATS) to AZRA LLCDBA ATS 52-0008, Issue 4, dated 6/30/05, for 737- modification and/or repair will introduce<br />
AeroTech Services.<br />
200and -200C, with this STC modi<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4133 AZUR AERO ASSISTANCE <strong>EASA</strong>.A.S.<strong>01</strong>244 CESSNA 500, CITATION Installation of Radar RDR 2000 Bendix/King<br />
with radar screen KMD 540/850 Bndix/King in<br />
accordance with MDL AAA 08/20<strong>04</strong> ed 1 Rev<br />
1 dated 10/10/05<br />
10<strong>01</strong>4134 AZUR AERO ASSISTANCE <strong>EASA</strong>.A.S.<strong>01</strong>245 CESSNA 500, CITATION Installation of Mode S Transponder GTX 330<br />
Garmin in accordance with MDL AAA 07/20<strong>04</strong><br />
Ed 1 Rev. 1 dated 10/10/2005<br />
10<strong>01</strong>4135 AZUR AERO ASSISTANCE <strong>EASA</strong>.A.S.<strong>01</strong>246 CESSNA 500, CITATION Installation of GPS GNS 430 GARMIN in<br />
accordance with MDL AAA 06/20<strong>04</strong> Ed 1 Rev<br />
1 dated 10/10/2005<br />
10<strong>01</strong>4136 AZUR AERO ASSISTANCE <strong>EASA</strong>.A.S.<strong>01</strong>247 CESSNA 500, CITATION Installation of GPS GNS 530 BRNAV<br />
GARMIN in accordance with MDL AAA<br />
05/20<strong>04</strong> Ed 1 Rev 1 dated 10/10/2005<br />
10<strong>01</strong>6328 B&B PARTNERS <strong>EASA</strong>.IM.A.S.02637 FAA STC ST03483AT Installation of a portable beverage dispensing<br />
system,P/N B43-FA 0<strong>01</strong><br />
10<strong>01</strong>6351 B&C SPECIALITY PRODUCTS <strong>EASA</strong>.IM.A.S.02671 FAA STC SA00846WI CESSNA 210L<br />
CESSNA 210M<br />
CESSNA 210N<br />
CESSNA P210N<br />
CESSNA T210L<br />
CESSNA T210M<br />
CESSNA T210N<br />
Addition of Vacuum Pump drive alternator and<br />
regulator with associated controls.<br />
10033488 B/E AEROSPACE, INC. FAA STC ST14379LA-T 777-300, 777-300ER Installation of B/E Aerospace Pantry Air Chiller<br />
P/N 470-1<br />
This STC is limited to MSN 308. 10.11.2005<br />
This STC is limited to MSN 308. 10.11.2005<br />
This STC is limited to MSN 308. 10.11.2005<br />
This STC is limited to MSN 308 10.11.2005<br />
1. This STC is applicable to the aircraft types<br />
as listed in the Approved Model List for FAA<br />
STC ST03483AT2. This STC is to be<br />
installed in accordance with the Galley<br />
Interface Criteria defined in Drawing No.<br />
1178.3. The limitations as defined in<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
06.02.2008<br />
28.11.2007<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.<strong>01</strong>.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 108/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036542 B/E AEROSPACE, Inc. FAA STC ST02876CH B777-200, B777-200LR<br />
Installation of B/E Aerospace, Inc., Vacuum None Prior to installation of this modification it 19.09.2<strong>01</strong>1<br />
B777-300, B777-300ER<br />
Toilet Assembly Retrofit Kit<br />
must be determined thatthe<br />
B777F<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036558 B/E AEROSPACE, Inc. FAA STC ST02876CH B737-600/700/800/900 Installation of Vacuum Toilet Assembly Retrofit<br />
Kit P/N 4100390-003.<br />
10036659 B/E AEROSPACE, Inc. FAA STC ST02876CH B747-400<br />
B747-400F<br />
Installation of Vacuum Toilet Assembly Retrofit<br />
Kit P/N 4100390-003Validation FAA STC<br />
ST02876CH. ,,<br />
10<strong>04</strong>0968 B/E AEROSPACE, Inc. FAA STC ST02876CH B767-200/-300/-300F/-400ER Installation of BE Aerospace Inc. Vacuum<br />
Toilet Assembly Retrofit Kit<br />
10<strong>01</strong>6917 BAE SYSTEMS AEROSPACE &<br />
DEFENSE<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>302 REV. 1 FAA STC SR<strong>01</strong>906LA BK117 C-2 Installation of the Folding Utility Seat in Multiple-<br />
Place SeatArrangements. The Utility Seating<br />
System, as installed in the MBB BK117 C-2<br />
helicopteris multiple-place utility seating system<br />
consiting of energy-absorbingUtility Installation<br />
of the Folding U<br />
10<strong>01</strong>5952 BARBARA AND ROBERT WILLIAMS <strong>EASA</strong>.IM.A.S.02094 SA572CE CESSNA 150<br />
CESSNA 150A<br />
CESSNA 150B<br />
CESSNA 150C<br />
CESSNA 150D<br />
CESSNA 150E<br />
CESSNA 150F<br />
CESSNA 150G<br />
CESSNA 150H<br />
CESSNA 150J<br />
CESSNA 150K<br />
CESSNA 150L<br />
CESSNA 150M<br />
CESSNA A150K<br />
CESSNA A150L<br />
Replacement of Continental O-200A with<br />
Lycoming 150 or 160hp Model O-320 engines<br />
10<strong>01</strong>6380 BASIC AIRCRAFT PRODUCTS, INC. <strong>EASA</strong>.IM.A.S.027<strong>04</strong> FAA STC ST00702AT CESSNA 210 Installation of Basic Type mBAE-14/28 Model<br />
2025 Deployable Air Driven Alternator System<br />
10<strong>01</strong>6497 BASIC AIRCRAFT PRODUCTS, INC. <strong>EASA</strong>.IM.A.S.02859 FAA STC SA02747AT CESSNA 182 Stand-by Alternator – Installation of Basic Type<br />
BAE-14/28 Deployable Air Driven Alternator<br />
System.<br />
10<strong>01</strong>4838 BAYO S.A.S. <strong>EASA</strong>.A.S.03055 MOONEY M20K Modification of radio electric installation for B-<br />
RNAV capacity with AP/FD coupling.<br />
10<strong>01</strong>4903 BAYO S.A.S. <strong>EASA</strong>.A.S.03138 CESSNA P210N 53/2006 - IFR B-RNAV certification extension<br />
of the GNS530 already installed.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.09.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.09.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.08.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.12.2009<br />
As defined in FAA STC SA572CEModified<br />
engine mounting structure and relocated<br />
battery installation must be inspected every<br />
500 flight hours or annually, whichever occurs<br />
earlier for any cracking or corrosion and if<br />
found rectified with an <strong>EASA</strong> approved re<br />
This approval should not be extended to other<br />
aircraft of this moel on which other previously<br />
approved modifcations will produce noadverse<br />
effect upon the airworthiness of that aircrat.<br />
<strong>EASA</strong> approved Supplemental Airplane Flight<br />
Manual or <strong>EASA</strong> approved Air<br />
20.09.2006<br />
18.<strong>01</strong>.2008<br />
As per FAA STC SA02747AT limitations. 29.08.2008<br />
Modification limited to serial number<br />
250508AFMS must be on board for any flight.<br />
STC Bayo 36/2006 must be already<br />
installed.The aricraft must be equipped with<br />
HSI KI525A and S-TEC 55X autopilot.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 109/<strong>462</strong><br />
31.05.2007<br />
21.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4920 BAYO S.A.S. <strong>EASA</strong>.A.S.03167 CESSNA 177RG STC 42/2007 - Modification of radio electric 1. Aircraft must be equipped with HSI<br />
08.02.2008<br />
installation for B-RNAV certification with AP KI525A and S-TEC 60-2 autopilot;2. Prior to<br />
coupling.<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will<br />
10<strong>01</strong>5<strong>01</strong>0 BAYO S.A.S. <strong>EASA</strong>.A.S.03312 CESSNA 182J 54/2006 - IFR BRNAV certification extension of STC Bayo 27/2006 must be already<br />
the GNS430 without Autopilot coupling. installed.The Aircraft must be equipped with<br />
HSI KI525A.<br />
10<strong>01</strong>5098 BAYO S.A.S. <strong>EASA</strong>.A.S.03439 REV. 1 FAIRCHILD SWEARINGEN SA<br />
226-T<br />
10<strong>01</strong>5138 BAYO S.A.S. <strong>EASA</strong>.A.S.03491 FAIRCHILD SWEARINGEN SA<br />
226-T<br />
Modification of radio electrical Installation2 VHF The approvam is limited to MSN T-276 F-<br />
21A, 2VOR/ILS/MKR VIR 30A, 2 ATC TDR GLLOGPS use is forbidden for<br />
90, 1 RMI 30 removal2GNS 430 W, 2 MD 41, SID/STAR/ApproachesGPS/Auto Pilot<br />
2 A-30 ACK, 2GTX 330D, 1 KA-33, 1 ST3400 coupling is forbidden below 2000 ft.<br />
Installation<br />
Modification of radio electrical installation:<br />
replacement radar indicator by MFD Garmin<br />
GMX200 and/or Concord Batteries.<br />
1. The approval is limited to MSN T-276 F-<br />
GLLO;2. Use of GMX 200 limited to radar<br />
weather display function;3. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any othe<br />
10<strong>01</strong>5179 BAYO S.A.S. <strong>EASA</strong>.A.S.03557 PIPER PA-25-235 Modification of radio electrical<br />
Limited to S/N 25-74-05726, 25-3109, 25- Prior to installation of this modification the 21.<strong>01</strong>.2009<br />
installation.Installation of AG-NAV2 GPS 37<strong>04</strong>, 25-3984, 25-4382, 25-3292,25-2400, 25- installer must determinethat the<br />
spreading guidance system not to be used for 4445.<br />
interrelationship between this modification<br />
navigation, in accordance with "Fiche<br />
and any otherpreviously installed<br />
d'approbation de conception d'une évolution<br />
modification will introduce no adverse<br />
No. 53/2007, rev.3 dated 12/12/08".<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>5220 BAYO S.A.S. <strong>EASA</strong>.A.S.03635 BEECH 58 Modification of radio electrical installation for B- The applicability of this STC is limited to the<br />
14.11.2008<br />
RNAV certification with AP coupling<br />
Beech 58 S/N TH-488Navigation on SID and<br />
STARs prohibited in Terminal AreaUtilisation of<br />
GPS prohibited for approachesPrior to<br />
installation of this modification the installer must<br />
determine that the interrela<br />
10<strong>01</strong>7122 BAYO S.A.S. <strong>EASA</strong>.R.S.<strong>01</strong>209 EUROCOPTER FRANCE AS<br />
365N SERI<br />
10032968 BAYO S.A.S. STC 2<strong>01</strong>0-006 HR 100/200, HR100/200 B<br />
HR 100/210, HR 100/210 D<br />
HR 100/285 TIARA<br />
HR100/250 TR, HR 100/285 C<br />
10<strong>01</strong>5726 BAYSYS TECHNOLOGIES, LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>741 FAA STC ST<strong>01</strong>939LA AIRBUS A319-115<br />
AIRBUS A319-133<br />
BAYO avionics modification no. 16/2005: This STC can be installed only by BAYO<br />
installation of- two NAV/COM/GPS GNS 430 technical personal in accordance with BAYO<br />
for IFR B-RNAV operations, with their STC definition file n°16/2005-DEF, revision 0,<br />
associated MD 41 annunciators, A-30 ACK dated December 19th 2005 or later <strong>EASA</strong><br />
altitude encoders and KA 33cooling system,- a approved revision<br />
Garmin GTX 330 mode S transponder,- two<br />
Bendix-King<br />
Installation of single EFIS Aspen EFD1000 Pro<br />
for VFR navigation.<br />
Direct TV - Installation of a tailwind 55 Satellite<br />
direct TV receive system<br />
Approved software version for ACU and PFD<br />
units is 1.1.Navigation coupling to automatic<br />
pilot is limited to heading mode.<br />
1. Maximum Tekeoff Weight and Maximum<br />
Landing Weight shall be reduced as<br />
follows:Takeoff 350 lbs (159 Kg)Landing 410<br />
lbs (186 Kg)2. For airplane(s) modified by this<br />
STC, prior to the accumulation of 9,200 total<br />
flight cycles from the STC modification, the<br />
10<strong>01</strong>3982 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>4 AIRBUS A320-200 Reconfiguration of Passenger Cabin to 180<br />
Economy Class Passengers<br />
10<strong>01</strong>3985 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>7 REV. 1 BOEING 737-700<br />
Installation of 44 Passenger Seats, seats<br />
BOEING 737-800<br />
power supply and in seat power supply system<br />
on Boeing-BBJ128 Reynard J2000 double<br />
seats,safety equipment, carpet and new<br />
wardrobes. Installation of General Dynamics In<br />
Seat Power System.<br />
10<strong>01</strong>3986 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>8 Floor Structure rework. 1. This STC is restricted to Boeing 767-3Z9<br />
Registration G-VKNG, Serial Number 23765.2.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other airc<br />
24.<strong>01</strong>.2008<br />
05.03.2008<br />
08.<strong>04</strong>.2008<br />
19.<strong>01</strong>.2006<br />
Prior to installation of this modification it 10.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.Install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 110/<strong>462</strong><br />
23.11.2006<br />
17.<strong>01</strong>.2005<br />
24.10.2005<br />
08.06.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>3987 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>9 Replacement of a Lufthansa Technik IFE 1. This STC is approved only for the product<br />
17.03.2005<br />
System with an ITAN IFE System<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4<strong>04</strong>7 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>129 BOEING 757-200 Enhanced Mode S Surveillance System<br />
completion and activation<br />
<strong>01</strong>.<strong>04</strong>.2005<br />
10<strong>01</strong>4<strong>04</strong>8 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>130 BOEING 767-300 Enhanced Mode S Surveillance System<br />
completion and activation<br />
<strong>01</strong>.<strong>04</strong>.2005<br />
10<strong>01</strong>4232 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>395 AIRBUS A321 Installation of Koito 24B/C and 148Y seats for<br />
Dragonair<br />
11.11.2005<br />
10<strong>01</strong>4321 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>573 AIRBUS A330 Installation of In Seat Power Supply Korean Air<br />
Airbus A330<br />
25.<strong>01</strong>.2006<br />
10<strong>01</strong>4388 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>674 Replacement of Aft G4B Galley. 27.06.2006<br />
10<strong>01</strong>4520 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.026<strong>01</strong> REV. 1 BOEING 767-300ER Installation of a MAS2000E in Flight<br />
Entertainment System on Austrian Airlines<br />
B767-300ER aircraft<br />
-- 02.02.2007<br />
10<strong>01</strong>4567 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.02668 BD-700-1A11 Installation of an Electronic Flight Bag (EFB) on This approval of thie installation does not<br />
03.11.2006<br />
A/C S/N 9089Modification Summary List: include any approval of the suitability, integrity,<br />
BBJ745 issue 1CCL: BBJCCL205 issue or accuracy of the EFB hardware, software,<br />
1ADoC: Mod. Sum. Sh. & Certificate of Design data base, display, controls or lighting.The<br />
iss. 25/10/2006<br />
capability of the system to "perform its<br />
intended function" has not been<br />
10<strong>01</strong>4658 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.02815 BOEING 747-400 Interior changes required on Cathay Pacific<br />
Boeing 747-400 aircraft MSN 27132 for BE<br />
Aerospace Flight Structures.<br />
10.05.2007<br />
10<strong>01</strong>4665 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.02822 REV. 1 BOEING 757-200 SERIES Cabin Reconfiguration on Boeing 757-230<br />
aircraft<br />
-- 02.03.2007<br />
10<strong>01</strong>4770 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.02962 BOEING 747-400 Interior Changes required on Cathay Pacific Prior to installation of this modification the<br />
02.07.2007<br />
Boeing 747-400 for BE Aerospace Flight installer must determine that the<br />
Structures.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4774 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.02966 BOEING 767-300 Installation of an in-seat power supply system<br />
and reconfiguration of business class seating.<br />
10<strong>01</strong>4784 BBJ DESIGN SERVICES LIMITED <strong>EASA</strong>.A.S.02984 BOEING 757-200 Installation of fixed Emergency Locator<br />
Transmitter<br />
10<strong>01</strong>4250 BEECHCRAFT BERLIN AVIATION GmbH <strong>EASA</strong>.A.S.<strong>01</strong>472 REV. 2 B200 Installation of Cloud Research and Seeding<br />
System This <strong>EASA</strong> STC 10<strong>01</strong>4250,<br />
REV. 2 reflects the transfer of<br />
STC<strong>EASA</strong>.A.S.<strong>01</strong>472 Revision 1 from<br />
Scandinavian Avionics Design GmbH<br />
toBeechcraft Berlin Aviation GmbH<br />
10<strong>04</strong>2830 BEECHCRAFT BERLIN AVIATION GmbH C90GTI Laser Scanner and Weather Research<br />
Application.<br />
10<strong>01</strong>7062 BELL HELICOPTER TEXTRON CANADA, <strong>EASA</strong>.IM.R.S.<strong>01</strong>497 TCCA STC NO. SH05-2 BELL 212<br />
Ltd<br />
BELL 412<br />
BELL 412 EP<br />
10<strong>01</strong>6755 BELL HELICOPTER TEXTRON, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>084 SR09397RC BELL 206A<br />
BELL 206B<br />
TCCA SH05-2 “Cold Weather Use of<br />
Kerosene Fuels”.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
30.05.2007<br />
N/A 13.<strong>04</strong>.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
27.09.2<strong>01</strong>0<br />
For mission equipment installed under the<br />
wingSpeeds are limited to vNO = 150 KIAS,<br />
and vNE = 169 KIASFlights into areas with<br />
known icing conditions is not permitted. For<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
further limitation see AFMS, Doc. No. D18-B11- documentation. Prior to installation of this<br />
<strong>01</strong>, Section II<br />
modification it must be determined<br />
thatthe interrelationship<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
STC ST09397RCIncrease in takeoff weight Aircraft effectivity is as follows: • This STC is<br />
from 1.451 Kg (3200 lbs) to 1.520 Kg (3350 lbs limited to 206A or 206B aircraft that are<br />
when modified in accordance with Bell Model qualified for and configured with the 65 inch<br />
206 Series Service Instructions BHT-206-SI- diameter tail rotor. • 206A S/N 4 thru 660,<br />
129 dated July 12, 20<strong>04</strong>, or later FAA and 672 thru 715 if modified to a Model 206B<br />
approved revision.<br />
by incorporation of Ser<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 111/<strong>462</strong><br />
19.12.2<strong>01</strong>2<br />
24.11.2008<br />
<strong>01</strong>.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7021 BELL HELICOPTER TEXTRON, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>439 FAA STC SH8713SW BELL 230 Replacement of the cabin door with right hand<br />
sliding door. This STC has been classified as<br />
“BASIC” by the FAA and has been approved<br />
under the PTVP.<br />
08.05.2008<br />
10037652 BELL HELICOPTER TEXTRON, Inc. FAA STC SR03923AT BELL 407 Installation of Aeronautical Accessories Lighting None Prior to installation of this modification it 13.12.2<strong>01</strong>1<br />
and Vision Accessoriesfor Bell Helicopter<br />
must be determined thatthe<br />
Textron 407 Model Helicopters Any of the<br />
interrelationship between this modification<br />
following kits can be installed individually or in<br />
and any other previouslyinstalled<br />
anycombination: - Preflight Lighting Kit per<br />
modification and/ or repair will introduce<br />
installation instructions A<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038134 BELL HELICOPTER TEXTRON, Inc. LBA STC RC1132 /<br />
98/5476/MAE<br />
REV. 1 FAA STC SH3311SO BELL 212, 412, 412EP Replacement Windows None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>01</strong>.2<strong>01</strong>2<br />
10038194 BELL HELICOPTER TEXTRON, Inc. FAA STC SR02808NY 429 Installation of wedge Windows with Sliders into<br />
L/H and R/H PassengerDoors in accordance<br />
with Aeronautical Accessories Inc.<br />
InstallationInstructions Report Number AA-<br />
09064, Revision A, 09. (FAA STC<br />
SR02808NY)<br />
10038231 BELL HELICOPTER TEXTRON, Inc. FAA STC SR00707DE 429 Automatic Door Openers for Crew and<br />
Passenger Doors and Pilot andCo-Pilot Floor<br />
Protectors<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
26.<strong>01</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.<strong>01</strong>.2<strong>01</strong>2<br />
10038305 BELL HELICOPTER TEXTRON, Inc. FAA STC SR09534RC-D BELL 429 Installation of Cargo Mirror None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.02.2<strong>01</strong>2<br />
10039466 BELL HELICOPTER TEXTRON, Inc. FAA SR02810NY 429 Installation of Hardpoint and Spotter Fixtures in<br />
accordance withAeronautical Accessories Inc.<br />
Installation Drawing List for HardpointFixture<br />
Kit, Ceiling Spotter Fixture Kit, Floor Spotter<br />
Fixture Kit,Report Number AA-09<strong>04</strong>3, Rev C,<br />
dated June 29, 2<strong>01</strong>0.<br />
10<strong>04</strong>1096 BELL HELICOPTER TEXTRON, Inc. FAA STC SR09537RC-D 429 Installation of High Frequency (HF) Antenna Kit<br />
(P/N 429-007-0<strong>01</strong>) forBell Helicopter Textron<br />
Model 429 Helicopters.<br />
10<strong>04</strong>1097 BELL HELICOPTER TEXTRON, Inc. FAA STC SR00739DE 429 Installation of Sliding Door Push-Out<br />
WindowsKit (P/N 429-563-<br />
0<strong>01</strong>/2/3/4/5/6/7/8/9)for Bell Helicopter Textron<br />
Model 429 Helicopters.<br />
10<strong>04</strong>1124 BELL HELICOPTER TEXTRON, Inc. FAA SR00740DE BELL 429 Installation of Aft Cabin Floor Protectors Kit<br />
(P/N 429-457-0<strong>01</strong>) forBell Helicopter Textron<br />
Model 429 Helicopters.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.05.2<strong>01</strong>2<br />
Only the installation of the HF Antenna Kit is<br />
included in this STC. Theantenna is capable of<br />
interfacing with many different types of<br />
HFradios; therefore, the compatibility of an HF<br />
radio installation withthe HF Antenna Kit is the<br />
responsibility of the in<br />
If the holder agrees to permit another<br />
person to use this certificate toalter the<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission. Prior to installation of this<br />
modification it must be determined<br />
22.08.2<strong>01</strong>2<br />
None.<br />
thatthe interrelationship<br />
If the holder agrees to permit another<br />
person to use this certificate toalter the<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
22.08.2<strong>01</strong>2<br />
None If the holder agrees to permit another<br />
person to use this certificate toalter the<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
22.08.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 112/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1125 BELL HELICOPTER TEXTRON, Inc. FAA SR00741DE BELL 429 Removable Crew Door Installation Kit (P/N 429- None If the holder agrees to permit another 22.08.2<strong>01</strong>2<br />
650-0<strong>01</strong>/3/4) for BellHelicopter Textron Model<br />
person to use this certificate toalter the<br />
429 Helicopters.<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
10<strong>04</strong>1215 BELL HELICOPTER TEXTRON, Inc. FAA STC SR09541RC 407 Passenger Sliding Doors Kit P/N 407-270-003 1. The Passenger Sliding Doors Kit P/N 407- If the holder agrees to permit another 30.08.2<strong>01</strong>2<br />
for Bell Helicopter TextronModel 407<br />
270-003 modifies the hingedpassenger doors person to use this certificate toalter the<br />
Helicopters.Reference FAA STC SR0941RC. for the Bell Helicopter Textron Canada Limited product, the holder shall give the other<br />
(BHTCL)Model 407 Helicopters. A Personnel person writtenevidence of that<br />
attachment Fixture mounted in thepassenger permission.Prior to installation of this<br />
compartment is not intended to secure modification it must be determined<br />
thatthe interrelationship<br />
10<strong>04</strong>1217 BELL HELICOPTER TEXTRON, Inc. FAA STC SR09540RC 407 Crew Area Hardpoints Kit BHTI P/N 407-240- 1. High skid landing gear is required for BHTI - The Kits approved in this STC can be 30.08.2<strong>01</strong>2<br />
0<strong>01</strong>Internal Hardpoint Kit BHTI P/N 407-638- P/N 407-638-0<strong>01</strong> ExternalHardpoint Kit installed individually or in anycombination-<br />
0<strong>01</strong>External Hardpoint Kit BHTI P/N 407-230- installation.2. Installation of BHTI P/N 407-270- If the holder agrees to permit another<br />
0<strong>01</strong> and P/N 407-230-100Pylon Hardpoint Kit 003 Passenger Sliding Doors Kit(separate person to use this certificateto alter the<br />
BHTI P/N 407-854-0<strong>01</strong>/2/3Reference FAA STC) is a co-requisite for BHTI P/N 407-854- product, the holder shall give the other<br />
STC SR09540RC<br />
0<strong>01</strong>/2/3 PylonHardpoints Kit installat<br />
person writtenevidence of that<br />
permission.Prior t<br />
10<strong>04</strong>1283 BELL HELICOPTER TEXTRON, Inc. FAA STC SR02405LA 407 Survivor Window Raft Kit P/N 407-567-002 for None If the holder agrees to permit another<br />
Bell Helicopter TextronModel 407<br />
person to use this certificate toalter the<br />
Helicopters.Reference FAA STC SR02405LA.<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
10<strong>01</strong>5578 BENZ AIRBORNE SYSTEMS <strong>EASA</strong>.IM.A.S.<strong>01</strong>489 FAA STC SA10365SC PIPER PA-31T<br />
PIPER PA-31T1<br />
FAA STC SA10365SC: Installation of a Benz<br />
Airborn System Model 800-0021 torque<br />
pressure system.<br />
1003<strong>04</strong>05 BENZ AIRBORNE SYSTEMS FAA STC SA<strong>01</strong>969CH DHC-6-100, -200, -300 Installation of Torque Pressure System on<br />
DHC-6 in acc. to FAA STCSA<strong>01</strong>969CH<br />
1003<strong>04</strong>08 BENZ AIRBORNE SYSTEMS FAA STC SA<strong>01</strong>970CH DHC-6-100, -200, -300 Installation of Engine Oil Pressure System on<br />
DHC-6 in acc. to FAA STCSA<strong>01</strong>970CH<br />
10029629 BERINGER AERO PC-6/A2-H2, PC-6/B1-H2<br />
PC-6/B2-H2, PC-6/B2-H4<br />
BRGAP-STC-002 - New wheels and brake<br />
system.<br />
<strong>04</strong>.09.2<strong>01</strong>2<br />
N/A 19.03.2007<br />
For models DHC-6-100 and DHC-6-200, this<br />
installation is only applicablewhen the airplane<br />
has been modified with PT6A-27 engines.<br />
For models DHC-6-100 and DHC-6-200, this<br />
installation is only applicablewhen the airplane<br />
has been modified with PT6A-27 engines.<br />
Prior to installation of this modification it 15.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it 15.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
None. Prior to installation of this modification the 08.<strong>04</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
None None 10.10.2<strong>01</strong>2<br />
10<strong>04</strong>1707 BERINGER AERO DISCUS-2A, DISCUS A,<br />
BRGAP-STC-007(0) - Replacement of wheel<br />
VENTUS-2A, VENTUS A. and brake system<br />
10<strong>04</strong>2599 BERINGER AERO 1- DHC-6 SERIES 1<br />
Replacement of nose wheel BF Goodrich 8.90- None. Prior to installation of this modification it 10.12.2<strong>01</strong>2<br />
1- DHC-6 SERIES 100<br />
12.5 P/N 3-1197 by Beringerwheel assembly<br />
must be determined thatthe<br />
1- DHC-6 SERIES 110<br />
P/N: RA-008.<br />
interrelationship between this modification<br />
1- DHC-6 SERIES 200<br />
and any other previouslyinstalled<br />
1- DHC-6 SERIES 210<br />
modification and/ or repair will introduce<br />
1- DHC-6 SERIES 300<br />
no adverse effectupon the airworthiness<br />
1- DHC-6 SERIES 310<br />
1- DHC-6 SERIES 320<br />
2- DHC-6 SERIES 400<br />
of the product.<br />
10036735 BHE & ASSOCIATES, LTD. B200, B200C, B200CGT, B200GT Installation of upgraded hardware to the This Installation is limited to aircraft serials Prior to installation of this modification it 05.10.2<strong>01</strong>1<br />
B300, B300C<br />
Rockwell Collins Pro Line 21FMS-3000 to listed in BHE andAssociates document 324-00- must be determined thatthe<br />
provide Localiser Performance with Vertical 0002, Rev IR, dated November 24, 2009, interrelationship between this modification<br />
Guidance (LPV).<br />
orlater approved revisions.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 113/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4464 BINDER MOTORENBAU GmbH <strong>EASA</strong>.A.S.02525 ALEXANDER SCHLEICHER ASH Modification of outer wing panel with winglets<br />
02.03.2006<br />
25 E<br />
and 27 m wingspan<br />
10<strong>01</strong>4471 BINDER MOTORENBAU GmbH <strong>EASA</strong>.A.S.02532 ALEXANDER SCHLEICHER ASW Binder Motorenbau Technische Mitteilung ASW This STC is approved only for the product<br />
12.<strong>04</strong>.2006<br />
22 BL<br />
22 BLE B2Changes in engine installation:- configuration as defined in the approved design<br />
Different type of spindle drive- Installation of a data referred to in the paragraph "Description".<br />
primer ball- CFRP gear mount<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4490 BINDER MOTORENBAU GmbH <strong>EASA</strong>.A.S.02552 ALEXANDER SCHLEICHER ASH Modification of outer wing panel with winglets<br />
03.02.2006<br />
25<br />
and 27 m wingspan<br />
10029418 BINDER MOTORENBAU GmbH P-<strong>EASA</strong>.A.S.03569 NIMBUS-3DM Nimbus-3DM - Umbau von Rotax535C auf None. Prior to installation of this modification the 24.03.2<strong>01</strong>0<br />
Solo 2625/2<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The approval ho<br />
10034252 BINDER MOTORENBAU GmbH ASH 25 E Conversion from hand starter to electric<br />
starter.Umbau Handstarter auf Elektrostarter.<br />
None. None. 21.03.2<strong>01</strong>1<br />
10036110 BINDER MOTORENBAU GmbH ETA None. None. 11.08.2<strong>01</strong>1<br />
10<strong>04</strong>2442 BINDER MOTORENBAU GmbH DG-500 M DG500M - Umbau von Rotax535C auf Solo<br />
2625/2<br />
None. None. 30.11.2<strong>01</strong>2<br />
10028420 BIZJET INTERNATIONAL REV. 1 FAA STC ST10964SC A318-112 Installation of provisions for an Executive Not applicable Prior to installation of this modification it 14.10.2<strong>01</strong>0<br />
Power System<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028421 BIZJET INTERNATIONAL REV. 1 FAA STC ST10963SC A318-112 Installation of a Miltope Wireless Access Point Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.10.2<strong>01</strong>0<br />
10028425 BIZJET INTERNATIONAL REV. 8 FAA STC ST10958SC A318-112, A319-133 Installation of a Cabin VIP InteriorMajor<br />
Change to the <strong>EASA</strong> STC 10028425 REV 7<br />
introducing changes in theCabin VIP Interior<br />
Installation (add the -007 configuration)<br />
10<strong>04</strong>2292 BIZJET INTERNATIONAL SALES AND<br />
SUPP<br />
10<strong>01</strong>6472 BJAC BUSINESS JET AIRCRAFT <strong>EASA</strong>.IM.A.S.02818 TC STC SA07-129 ISSUE 1 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
10<strong>01</strong>5400 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>110 FAA STC SA10341SC BEECH C90<br />
BEECH C90A<br />
BEECH E90<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.07.2<strong>01</strong>2<br />
FAA STC ST09033SC MYSTERE FALCON 50 Installation of a quick drain kit on Environmental None Prior to installation of this modification it 21.11.2<strong>01</strong>2<br />
Control UnitValidation of FAA STC<br />
must be determined thatthe<br />
ST09033SC<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Goodrich Class III Electronic Flight Bag. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of Pratt & Whitney Canada PT6A- 1. AFMS No 19005, Rev IR 24 November<br />
135A (de-rated to 550 HP) engines and 20<strong>04</strong> oe later approved revision is required for<br />
McCauley 4HFR34C762/94LMA-4 or the Raytheon C90, C90A or E90 airplane with<br />
4HFR34C768/94LMA-4propellers in<br />
Pratt& Whitney Canada PT6A-135A engines.<br />
accordance with Blackhawk Modifications Inc Note that the Horsepower is limited to 550 at<br />
Drawing No 19005-<strong>01</strong> Rev IR, dated 15 March 1900 RPM.2. Each engine mount must be re<br />
20<strong>04</strong>, "Installation Inst<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 114/<strong>462</strong><br />
14.10.2008<br />
29.03.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5414 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>134 REV. 1 FAA STC SA10341SC BEECH C90<br />
Installation of Pratt & Whitney PT6A-135A AFMS No 19003-00, Rev a, dated 7th october<br />
20.<strong>04</strong>.2006<br />
BEECH C90A<br />
engine with:1. Hartzell propellers HC-D4N- 20<strong>04</strong> or later approved revision is required for<br />
BEECH E90<br />
3C/D9290(S,K) with a diameter of 93 inches (4 the Raytheon C90, C90A or E90 airplane with<br />
blades) in accordance with Blackhawk Pratt & Whitney Canada PT6A-135A engines.<br />
Modification, Inc.Drawing No 19003-<strong>01</strong>, Rev B, Note that the shaft horspower is limited to 550<br />
dated 1st April 20<strong>04</strong>, "Installation Instruc at 1900 RPMEach engine mount mu<br />
10<strong>01</strong>6078 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02262 FAA STC SA10567SC Installation of Pratt and Whitney PT6A-135A<br />
engines in place of PT6A-135 engines.<br />
10<strong>01</strong>6079 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02263 REV. 1 FAA STC SA0<strong>04</strong>33AT BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
10<strong>01</strong>6156 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02359 REV. 2 FAA STC SA<strong>01</strong>946LA BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH A200<br />
BEECH A200C<br />
BEECH A200CT<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
BEECH C90<br />
BEECH C90A<br />
BEECH E90<br />
BEECH F90<br />
1. Installation limited to Serial Number LA-2<br />
thru LA-2<strong>04</strong>, except for LA-202.2.<br />
Compatibility of this modification with other<br />
previously approved modifications must be<br />
determined by the installer.3. This STC is<br />
approved only for the product config<br />
Installation of Pratt and Whitney PT6A-42<br />
engines in place of PT6A-41 engines. This<br />
project is to amend <strong>EASA</strong> TSC No.<br />
<strong>EASA</strong>.IM.A.S. 02263 using the data from the<br />
amended FAA-STC SA0<strong>04</strong>33AT dated 22.<br />
August 2007 to include Beechcraft Super King<br />
Air 200C, 200T<br />
Installation of Ultra Electronics Engine 1. Blackhawk Modifications, Inc. STC<br />
Instruments.Revision 1: Installation of SA10341SC or SA10364SC is a prerequisite<br />
powerplant indication system. This project is to for this modification.2. Prior to installation of<br />
amend <strong>EASA</strong> of <strong>EASA</strong> STC No.<br />
this modification the installer must determine<br />
<strong>EASA</strong>.IM.A.S.02359.<br />
that the interrelationship between this<br />
modification and any other previous<br />
10<strong>01</strong>6381 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02705 REV. 1 FAA STC SA10560SC KING AIR C90GTI Installation of Wing Mounted Auxiliary Fuel<br />
Transfer Tank in BeechC90GTi. This project is<br />
to amend <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.02705.<br />
10<strong>01</strong>6403 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02732 REV. 1 FAA STC SA10737SC BEECH 200, 200C<br />
BEECH 200T, 200CT, A200,<br />
A200C<br />
BEECH A200CT, B200, B200C,<br />
BEECH B200CT, B200T<br />
10<strong>01</strong>6484 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02839 FAA STC SA10824SC ; RICK RITZ BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
Installation of Pratt and Whitney PT6A-61<br />
engines in Beech 200 Series.This project is to<br />
amend <strong>EASA</strong> STC No. <strong>EASA</strong>.IM.A.S. 02732.<br />
Upgrade Super King Air 200, A200 and B200<br />
Series King Airs to Pratt and Whitney Canada<br />
PT6A-52 engines.<br />
None Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
23.<strong>01</strong>.2007<br />
<strong>01</strong>.<strong>04</strong>.2008<br />
27.05.2009<br />
16.09.2<strong>01</strong>1<br />
product. The installati<br />
None Prior to installation of this modification the 05.07.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
Prior to installation of this modification the<br />
25.08.2008<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>6559 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.02944 FAA STC SA5786SW CESSNA 425 Installation of Pratt and Whitney Canada PT6A - None.<br />
135A engines on Cessna Conquest 425<br />
airplanes.<br />
16.02.2009<br />
10031080 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.03186 FAA STC SA4705SW BEECH 65-A90, B90, C90 Upgrade King Air 65-A90, B90 and C90 Engines can be either type certified Pratt and Prior to installation of this modification it 26.07.2<strong>01</strong>0<br />
airplanes with PT6A-28 engines<br />
Whitney PT6A-27 orPT6A-28 engines, or must be determined thatthe<br />
converted PT6A-27 or PT6A-28 engines from interrelationship between this modification<br />
PT6A-21engines in accordance with Atlantic and any other previouslyinstalled<br />
Turbines International Inc STCSE02290NY, or modification and/ or repair will introduce<br />
converted PT6A-27 or PT6A-28 engines from no adverse effectupon the airworthiness<br />
of the product.The ins<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 115/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031460 BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.03209 FAA STC SA<strong>01</strong>248SE PA-31T<br />
<strong>EASA</strong> Validation of FAA STC SA<strong>01</strong>248SE - none Prior to installation of this modification it 17.08.2<strong>01</strong>0<br />
PA-31T1<br />
Installation of two HartzellHC-E4N-<br />
must be determined thatthe<br />
3N/D8990SB propellers<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031<strong>462</strong> BLACKHAWK MODIFICATIONS Inc. <strong>EASA</strong>.IM.A.S.03208 FAA STC SA00863SE PIPER PA-31T<br />
PIPER PA-31T1<br />
PIPER PA-31T2<br />
10031945 BLACKHAWK MODIFICATIONS Inc. FAA STC SA10816SC 425 Installation of Ultra Electronics engine torque<br />
indicators in Cessna 425in accordance with<br />
FAA STC SA10816SC<br />
<strong>EASA</strong> Validation of FAA STC SA00863SE- none Prior to installation of this modification it 17.08.2<strong>01</strong>0<br />
Installation of two Pratt &Whitney PT6A-135 or<br />
must be determined thatthe<br />
PT6A-135A engines and two HartzellHC-B3TN-<br />
interrelationship between this modification<br />
3B/T1<strong>01</strong>78B-8R or HC-E4N-3N/D8990SB<br />
and any other previouslyinstalled<br />
propellers<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.09.2<strong>01</strong>0<br />
10036326 BLACKHAWK MODIFICATIONS Inc. FAA STC SA<strong>01</strong>946LA PA-31T, PA-31T1, PA31T2 Installation of Powerplant Indication System. None. Blackhawk Modifications Inc, FAA STC’s <strong>01</strong>.09.2<strong>01</strong>1<br />
ref SA00863SE (PT6A-<br />
135(A)Installation) or SA10956SC (PT6A-<br />
28 Installation) are prerequisite forthis<br />
modification. It is the installer’s<br />
responsibility to ensure thesereferenced<br />
STC’s are <strong>EASA</strong> approved prior to instal<br />
10036469 BLACKHAWK MODIFICATIONS Inc. FAA SA02357LA CESSNA 208B Replacement of the original P&W PT6A- 1. AeroAcoustics Aircraft Systems, Inc.,<br />
114(A) engine and propellerwith P&W<br />
PT6A-42A and 4-blade Hartzell PropellerHC-<br />
E4N-3P/D9900(K) and associated equipment<br />
in accordance with FAA STCSA02357LA.<br />
"Aircraft Payload Extender STOLSystem",<br />
10<strong>01</strong>4731 BLOM COMPAGNIA GENERALE<br />
RIPRESE AER<br />
10028772 BLOM COMPAGNIA GENERALE<br />
RIPRESE AER<br />
10029675 BLOM COMPAGNIA GENERALE<br />
RIPRESE AER<br />
<strong>EASA</strong>.A.S.02913 CESSNA 172P<br />
CGR P0<strong>01</strong>-00 "Structure & Exhaust System<br />
REIMS AVIATION CESSNA F-172 Modification for Camera Installation".<br />
If the STC holder agrees to permit other<br />
person to use this certificateto alter the<br />
STC SA<strong>01</strong>805SE (<strong>EASA</strong> STC No. 10029821) product, the holder shall give the other<br />
12.09.2<strong>01</strong>1<br />
is required as part ofthis alteration.2. This person writtenevidence of that<br />
modification is not compatible with Cessna permission.Prior to installation of this<br />
Model 208B SerialNumber 208B1190, modification it must be determined<br />
208B1216, and<br />
thatthe interrelationshi<br />
Applicable to S/N 172-7631 only. <strong>04</strong>.06.2008<br />
<strong>EASA</strong>.A.S.03636 PARTENAVIA P68<br />
PARTENAVIA P68C<br />
17.07.2009<br />
PA 31-350 GPS Garmin 430 for IFR The installation of <strong>EASA</strong> approved modification Prior to installation of this modification it 12.<strong>04</strong>.2<strong>01</strong>0<br />
<strong>EASA</strong>.A.C.07903 isrequired.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5918 BLR AEROSPACE, L.L.C. <strong>EASA</strong>.IM.A.S.02051 REV.2 FAA STC SA<strong>01</strong>615SE BEECH 200, 200C<br />
BEECH 300, 300LW<br />
BEECH B200, 200C<br />
BEECH B200GT, B200CGT<br />
Installation of winglets and associated changes<br />
in wing and aileronstructures and related<br />
system changes on Raytheon Model 200<br />
200C, B200,B200C, 300 and 300LW<br />
airplanes.Revision 1 adds models B200GT,<br />
B200CGT.<br />
10029451 BLR AEROSPACE, L.L.C. REV. 1 FAA STC SA02054SE C90A, C90GT, C90GTI Installation of winglets and associated changes Eligible Serial Numbers are defined in BLR<br />
in wing and aileronstructures and related<br />
system changes on Hawker Beechcraft Model<br />
C90A.C90GT and C90GTi.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.<strong>01</strong>.2<strong>01</strong>1<br />
Master Drawing List, DocumentReference BLR<br />
KA90W-002, rev. J, dated March 02, 2<strong>01</strong>0, or<br />
later approvedrevisions.Structural life limit of<br />
the wing structure as expressed in flight<br />
hoursare reduced to, 15,590 hours b<br />
Prior to installation of this modification the 18.05.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 116/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038758 BLR AEROSPACE, L.L.C. FAA STC SA02131SE KING AIR B200GT AND<br />
Installation of a BLR Aerospace Ultimate Approval of this change in type design applies Performance Enhancement Package 22.03.2<strong>01</strong>2<br />
B200CGT<br />
Performance Package (UPP).<br />
to the above listedaircraft models only. This requires the installation of thefollowing<br />
approval should not be extended to<br />
Supplemental Type Certificates<br />
otheraircraft of this model series unless the (STC):STC Number<br />
installer determines that therelationship ,,DescriptionSA<strong>01</strong>615SE,,BLR<br />
between this change and any other previ Aerospace Winglet Installation (STC<br />
ref<strong>EASA</strong>.IM.A.S.02051)SA3366NM,,Rais<br />
beck Ram Air Recovery System (RARS)<br />
10039059 BLR AEROSPACE, L.L.C. REV. 2 FAA STC SR<strong>01</strong>865SE 1- BELL 212<br />
2- BELL 2<strong>04</strong>B, BELL 205A1<br />
10<strong>04</strong>0783 BLR AEROSPACE, L.L.C. FAA SR00798SE / LBA RC 1163 1- 2<strong>04</strong>B, 205A-1<br />
2- 212, 412, 412EP<br />
10<strong>01</strong>7218 BOGGI S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>375 EUROCOPTER FRANCE AS<br />
365N3<br />
Installation of Dual Tailboom Strakes and Day/Night VFR only, flight into known icing<br />
FastFin.Revision 1 adds Model 2<strong>04</strong>B and conditions prohibited.<br />
changes the reference to LBA STC RC 1163to<br />
<strong>EASA</strong> STC 10<strong>04</strong>0783.Revision 2 adds<br />
additional Bell 212 and 412 FMSs.<br />
Installation of Dual Tailboom Strakes. This STC Day/Night VFR only, flight into known icing<br />
revises and supersedesLBA STC RC 1163 to conditions prohibited.<br />
add the Bell Helicopter Textron Inc. Model<br />
2<strong>04</strong>B, 412and 412EP. The AB 212 is removed<br />
as it is not included in the FAA STC.<br />
KIT MDS365-P0<strong>01</strong>-00, Additional seat fitting<br />
for Eurocopter AS365N3 Helicopter in Hems<br />
configuration.<br />
10033945 BOGGI S.R.L. AS 365 N3 Kit P/N MDS365-P002-00 ,External rear view<br />
mirror.<br />
Limited to AS 365N3 S/N 6609 and 6356,<br />
previously modified by the kit Bucher P/N ARA-<br />
AS365N2-AC50.<br />
- as defined in -Boggi s.r.l. Rotorcraft Flight<br />
Manual Supplement,Owner Manual,section 4,<br />
Edition 2,Rev. 0 dtd 12/<strong>01</strong>/2<strong>01</strong>1<br />
10035798 BOGGI S.R.L. AS365N3 Installation of Draeger TI 500 "Globetrotter" Limited to:-Incubator model Draeger TI 500<br />
incubator on AS 365N3(ref. Change 365-M003- P/N TI 500, S/N 002-Helicopter model<br />
00).<br />
AS365N3 S/N 6609 & 6356<br />
10<strong>01</strong>5497 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>260 REV. 1 TCCA STC C-LSA05-294/D CHALLENGER CL-600-2B16 Aircraft Completion 9 Passenger Interior<br />
Configuration. (ASN 5595)<br />
10<strong>01</strong>5564 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>463 C-LSA05-181/D, ISSUE 2 BOMBARDIER BD-100-1A10 Installation of Equipment Ladder (Aft<br />
(CHALLE<br />
Equipment Bay) in accordance with<br />
MDL3808<strong>01</strong>, rev. 1 dated 11 June 2005 and<br />
compliance report BAS683800<strong>04</strong><br />
10<strong>01</strong>5565 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>464 C-LSA05-212/D, ISSUE 1 BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
Installation of a Satellite Telephone System<br />
Interfaced to an existing Flight Telephone<br />
System in accordance with MDL<br />
BAS68<strong>01</strong>0<strong>01</strong>0 Revision A dated 30 May 2005<br />
and Compliance Report BAS68380005 dated<br />
Must be installed in conjunction with FAA 19.11.2<strong>01</strong>2<br />
STC SR00798SE (<strong>EASA</strong><br />
STC10<strong>04</strong>0783).Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair wi<br />
Prior to installation of this modification it 26.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21A.118A. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
<strong>04</strong>.12.2007<br />
21.02.2<strong>01</strong>1<br />
repa<br />
Prior to installation of this modification it 19.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to Aircraft Serial Number 5595 <strong>04</strong>.<strong>04</strong>.2006<br />
1. Limited to: S/N 20<strong>01</strong>32. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the install<br />
1. This STC is limited to BD-100-1A10<br />
(Challenger 300) SN 20<strong>01</strong>3<br />
10<strong>01</strong>5567 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>474 REV 1 TCCA STC C-LSA06-<strong>01</strong>5/D ISSUE 2 BOMBARDIER CL-600-2B16<br />
10/09/2005<br />
Aircraft Completion Restricted to ASN 5605 27.09.2006<br />
10<strong>01</strong>5603 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>539 TCCA STC C-LSA05-314/D BOMBARDIER CL-600-2B16 Aircraft Completion 11 PassengerInterior 1. Restricted to Aircraft Serial Number<br />
28.11.2005<br />
Configuration<br />
5599.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall b<br />
10<strong>01</strong>5674 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>654 REV 1 TCCA STC C-LSA06-025/D BOMBARDIER CL-600-2B16 Aircraft Completion, 10 Passenger Interior. 1. Restricted to ASN 5613.2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the insta<br />
26.10.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 117/<strong>462</strong><br />
23.09.2005<br />
05.10.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5676 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>657 REV 1 TCCA STC C-LSA06-023/D ISSUE 3 BOMBARDIER CL-600-2B16 Aircraft Completion, 10 Passenger Interior<br />
Configuration<br />
1. Restricted to ASN 5608 08.09.2006<br />
10<strong>01</strong>5677 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>658 REV 1 TCCA STC C-LSA06-024/D ISSUE 2 BOMBARDIER CL-600-2B16 Aircraft Completion, 10 Passenger Interior 1. Restricted to Aircraft Serial Number<br />
08.09.2006<br />
Configuration<br />
5611.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall b<br />
10<strong>01</strong>5782 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>828 TCCA STC C-LSA06-032/D BD-700-1A11 Aircraft Completion 12 Passenger Interior WLAN system is compatible only to IEEE 802<br />
28.<strong>04</strong>.2006<br />
ConfigurationValidation of TCCA Limited STC 11(b)Use of IEEE 802 11(b) compatible<br />
C-LSA06-032/D to S/N 9174MDL: E764000 TPEDS for interaction with WLAN is subject to<br />
Rev NC or later TCCA approved revisions operational rules<br />
10<strong>01</strong>5812 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>881 TCCA STC SA06-2 BD-700-1A10 Main Entry Door Handrail<br />
ModificationValidation of TCCA STC SA06-<br />
2MDL: BAS67<strong>01</strong>0036 REV NC or later TCCA<br />
approved revisionsTCCA SoC: C-05-1053<br />
SA06-2 dated January 23, 2006<br />
-- 23.<strong>01</strong>.2007<br />
10<strong>01</strong>5816 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>887 TCCA STC C-LSA06-178/D BOMBARDIER CL-600-2B16 (CL- Aircraft Completion<br />
6<strong>04</strong><br />
-- 27.06.2006<br />
10<strong>01</strong>5843 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>938 REV. 2 TCCA STC SA06-14 ISSUE 2 BD100-1A10 (CHALLENGER 300) INSTALLATION OF AN Artex ELT c-406-n<br />
WITH A NAVIGATION INTERFACE.Revision<br />
of the <strong>EASA</strong> STC IM.A.S.<strong>01</strong>938 REV 1 in<br />
order to delete thestructural provisions<br />
approved under STC TCCA SA-05-28 as a<br />
prerequesite to TCCA STC SA 06-14 for future<br />
a/c deliveries<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.03.2<strong>01</strong>1<br />
10<strong>01</strong>5885 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02003 TCCA STC SA03-113 CL-600-2B16 (6<strong>04</strong>) Installation of Complete Custom Aircraft Interior Limited to ASN 5591 only 17.08.2006<br />
10<strong>01</strong>5932 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02070 TCCA STC C-LSA06-3<strong>04</strong>/D CL-600-2B16 Aircraft Completion Restricted to ASN 5648 16.11.2006<br />
10<strong>01</strong>5933 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02071 TCCA STC C-LSA06-243-D ISSUE 1 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Aircraft Completion 1. Restricted to ASN 5644.2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the insta<br />
19.09.2006<br />
10<strong>01</strong>5967 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02118 TCCA STC C-LSA06-317/D BOMBARDIER BD-700-1A10 Aircraft Completion, 14 Passenger Interior<br />
ConfigurationValidation of TCCA Limited<br />
STC C-LSA06-317/D to S/N 9197MDL:<br />
F<strong>01</strong>7000 Rev NC or later TCCA approved<br />
revisions<br />
10<strong>01</strong>5999 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02157 TCCA STC SA06-88 CL-600-2B16 Activation of Runway Awareness Advisory<br />
System (RAAS) Functionality.<br />
Refer to the Limitations sections of the required<br />
FM SupplementWLAN system is compatible<br />
only to IEEE 802.11(b).The use of WLAN is<br />
subject to operational rules.<br />
10<strong>01</strong>6<strong>04</strong>7 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02218 REV. 1 TCCA STC SA03-113 CL-600-2B16 Complete Custom Interior Restricted to ASN 5636. 17.<strong>01</strong>.2007<br />
10<strong>01</strong>6062 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02240 TCCA LSTC C-LSA07-<strong>04</strong>4/D BOMBARDIER CL-600-2B16 Costumised Interior Completion Restricted to ASN 5659. 11.<strong>04</strong>.2007<br />
10<strong>01</strong>6068 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02247 TCCA LIMITED STC C-LSA06-281/D BOMBARDIER BD-700-1A11 Aircraft Completion, 13 Passenger Interior Refer to the Limitations Sections of the<br />
23.<strong>01</strong>.2007<br />
ConfigurationValidation of TCCA Limited STC required FM SupplementWLAN system is<br />
C-LSA06-281/D to S/N 9186MDL: E915000 compatible only to IEEE 802.11(b)The use of<br />
Rev A or later approvad revisions<br />
WLAN is subject to operational rules<br />
10<strong>01</strong>6075 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02258 TCCA LIMITED STC C-LSA07-<strong>04</strong>5D BOMBARDIER CL-600-2B16 Customized Interior completion - Aircraft 5664. Restricted to Aircraft Serial No. 5664. 18.07.2007<br />
10<strong>01</strong>6081 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02265 TCCA STC C-LSA07-111/D BD-100-1A10 (CHALLENGER<br />
300)<br />
AIRCRAFT COMPLETION, 9 PASSENGER Prior to installation of this modification the<br />
INTERIOR CONFIGURATION<strong>EASA</strong> Validation installer must determine that the<br />
of:Transport Canada Limited Supplemental interrelationship between this modification and<br />
Type Certificate C-LSA07-111/D Issue 1 dated any other previously installed modification will<br />
11th May 2007, in accordance with Aero introduce no adverse effect upon the<br />
Consulting Services Ltd. Modification Data airworthiness of the product.The use of a<br />
Summary F111000 R<br />
10<strong>01</strong>6119 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02311 TCCA STC SA03-113 CL-600-2B16 Complete Custom Aircraft Interior. Restricted to Serial no. 5655 26.03.2007<br />
10<strong>01</strong>6172 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02399 TCCA STC C-LSA07-2<strong>04</strong>/D BD-100-1A10 (CHALLENGER AIRCRAFT COMPLETION, 9 PASSENGERS 1. This STC is limited to aircraft Bombardier<br />
24.09.2007<br />
300)<br />
INTERIOR CONFIGURATION /<strong>EASA</strong> BD100-1A10 Serial Number 2<strong>01</strong>49.2. Prior<br />
Validation of:Transport Canada Limited to installation of this modification the installer<br />
Supplemental Type Certificate C-LSA07- must determine that the interrelationship<br />
2<strong>04</strong>/DIssue 1 dated 7th September 2007, in between this modification and any other<br />
accordance with Aero ConsultingServices Ltd. previously installed modificati<br />
Modification Data Summary F38<br />
10<strong>01</strong>6208 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02454 TCCA STC SA03-113 CL-600-2B16 Complete Custom Aircraft Interior. Restricted to ASN 5628. 06.09.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 118/<strong>462</strong><br />
31.<strong>01</strong>.2007<br />
06.09.2007<br />
15.05.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6237 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.025<strong>01</strong> TCCA STC C-LSA07-366/D BD-100-1A10 (CHALLENGER AIRCRAFT COMPLETION, 10<br />
This STC is limited to aircraft Bombardier<br />
10.<strong>01</strong>.2008<br />
300)<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>69.<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA07-<br />
366/DIssue 1 dated 20th December 2007, in<br />
accordance with Aero ConsultingServices Ltd.<br />
Modification Data Summary F<br />
10<strong>01</strong>6238 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02502 TCCA STC C-LSA07-320/D BD-100-1A10 (CHALLENGER<br />
300)<br />
10<strong>01</strong>6362 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02684 TCCA STC C-LSA08-<strong>01</strong>4/D BD-100-1A10 (CHALLENGER<br />
300)<br />
AIRCRAFT COMPLETION, 10<br />
This STC is limited to aircraft Bombardier<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>59.<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA07-<br />
320/DIssue 1 dated 20th November 2007, in<br />
accordance with Aero ConsultingServices Ltd.<br />
Modification Data Summary F5<br />
AIRCRAFT COMPLETION, 10<br />
This STC is limited to aircraft Bombardier<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>79.<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA08-<br />
<strong>01</strong>4/DIssue 1 dated 20th February 2008, in<br />
accordance with Aero ConsultingServices Ltd.<br />
Modification Data Summary F<br />
10<strong>01</strong>6423 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02761 REV. 35 TCCA STC SA<strong>04</strong>-112 BD100-1A10 (CHALLENGER 300) Customized Interior CompletionNote: Major The revised STC is limited to aircraft<br />
Change to <strong>EASA</strong> STC 10<strong>01</strong>6423 rev 34 which Bombardier BD100-1A10 SerialNumber<br />
has been updated toinclude S/N 20357 20096, 20200, 20206, 20214, 20218, 20221,<br />
20222, 20226, 20227,<br />
20232,20236,20237, 20241, 20243,<br />
20251, 20252, 20256, 20261, 20271, 20272,<br />
20274,20275,20276, 20277, 20284,<br />
10<strong>01</strong>6476 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02826 REV. 2 TCCA STC SA08-35 ISSUE 3 BD100-1A10 (CHALLENGER 300) Observer Seat Installation, Model 409-00<strong>01</strong><br />
/Installation of an observer seat between the<br />
avionics racks, forward ofthe main passenger<br />
cabin.Revision of <strong>EASA</strong> STC 10<strong>01</strong>6476, Rev.<br />
1 due to revised technical data(Modification<br />
Data Summary F797000 Rev. D).<br />
26.11.2007<br />
25.02.2008<br />
Prior to installation of this modification it 16.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Observer Seat for crew use only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
21.<strong>01</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>6477 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02828 TCCA STC SA08-58 ISSUE 1 CL-600-2B16 (6<strong>04</strong>) Installation, AVS-470 Tail Camera System 1. For Configuration -2, the modification<br />
defined by <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>946 (TCCA STC No. SA97-<br />
71) must be embodied as aprerequisite.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between<br />
<strong>01</strong>.10.2008<br />
10<strong>01</strong>6493 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02855 TCCA C-LSA08-097/D ISSUE 1 CL-600-2B16 Installation of Club Seating 05.05.2008<br />
10<strong>01</strong>6494 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02856 TCCA C-LSA07-418/D ISSUE 1 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation of EMS High Speed Data System 1. Restricted to ASN 54642. Limitation: This<br />
approval is limited to 1,500 flight cycles or 12<br />
months from the approval date, whichever<br />
comes first until theAirworthiness Limitations<br />
subdocument BAS63<strong>01</strong><strong>01</strong>16-AWL-1 of<br />
Bombardier IFCA BAS63<strong>01</strong><strong>01</strong>16-IFCA-1 is<br />
app<br />
28.07.2008<br />
10<strong>01</strong>6502 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.02865 TCCA STC C-LSA08-237/D BD-100-1A10 (CHALLENGER<br />
300)<br />
10<strong>01</strong>6631 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.03068 TCCA STC C-LSA08-275/D ISS1 BD-100-1A10 (CHALLENGER<br />
300)<br />
CUSTOMIZED INTERIOR COMPLETION – 1 Prior to installation of this modification the<br />
AIRCRAFT 2021210 passenger seats interior installer must determine that the<br />
configuration<strong>EASA</strong> Validation of:Transport interrelationship between this modification and<br />
Canada Limited Supplemental Type Certificate any other previously installed modification will<br />
C-LSA08-237/DIssue 1 dated 24th September introduce no adverse effect upon the<br />
2008, in accordance with Aero<br />
ConsultingServices Ltd<br />
airworthiness of the product.1 Th<br />
Customized Interior Completion - Aircraft Prior to installation of this modification the<br />
200659 passenger seats interior<br />
installer must determine that the<br />
configuration.<strong>EASA</strong> Validation of:Transport interrelationship between this modification and<br />
Canada Limited Supplemental Type Certificate any other previously installed modification<br />
C-LSA08-275/DIssue 1 dated 21st October will introduce no adverse effect upon the<br />
2008, in accordance with Aero<br />
ConsultingServices Ltd.<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 119/<strong>462</strong><br />
09.10.2008<br />
06.11.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6657 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.03117 TCCA C-LSA09-0002/D ISSUE 1 BOMBARDIER CL-600-2B16 Main & Nose Wheel Storage Modifications. 1. Restricted to ASN 5426.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the airwor<br />
20.<strong>01</strong>.2009<br />
10<strong>01</strong>6671 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.03161 TCCA STC SA09-16 BD-100-1A10 (CHALLENGER Installation of KGS Electronic SS200 Static Prior to installation of this modification the<br />
06.<strong>04</strong>.2009<br />
300)<br />
Inverter<strong>EASA</strong> Validation of:Transport Canada installer must determine that the<br />
Supplemental Type Certificate SA09-16, Issue interrelationship between this modification and<br />
2 dated19th March 2009 in accordance with any other previously installed modification<br />
Aero Consulting Services Ltd. Modification will introduce no adverse effect upon the<br />
Data Summary G072000 Revision B. airworthiness of the product.<br />
10<strong>01</strong>6673 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.03176 TCCA STC SA<strong>04</strong>-69 ISSUE 1 BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6676 BOMBARDIER AEROSPACE <strong>EASA</strong>.IM.A.S.03189 FAA STC ST02683CH BOEING 747-400 SERIES Installation of EZMount (TM) mechanical<br />
mounting assembly on lower frame of cockpit<br />
sliding windows in accordance with Electronic<br />
Cable Specialists Master Data List ECS-<br />
206728 Rev. E, dated April 8, 2009, or later<br />
FAA approved revisions.Validation of FAA S<br />
10027267 BOMBARDIER AEROSPACE P-<br />
<strong>EASA</strong>.IM.A.S.03252<br />
TCCA STC SA09-43 BD-100-1A10 (CHALLENGER<br />
300)<br />
Installation of 115 VAC TIA Wavejet<br />
1. Prior to installation of this modification the<br />
Microwave Oven in Forward RH Galley.<strong>EASA</strong> installer must determine that the<br />
Validation of:Transport Canada Supplemental interrelationship between this modification and<br />
Type Certificate SA<strong>04</strong>-69, Issue 1 dated 4th any other previously installed modification will<br />
June 20<strong>04</strong> in accordance with Aero Consulting introduce no adverse effect upon the<br />
Services Ltd. Modification Data Summary airworthiness of the product.2.<br />
E02700<br />
VHF COMM 3 Power Source Relocation<strong>EASA</strong><br />
Validation of:Transport Canada Supplemental<br />
Type Certificate SA09-43, Issue 1 dated20th<br />
May 2009 in accordance with Aero Consulting<br />
Services Ltd.Modification Data Summary<br />
F912000 Revision N/C.<br />
1. AFM Supplement as listed in Appendix A of<br />
Electronic Cable Specialists Master Data List<br />
ECS-206728, Rev. E, dated April 8, 2009 or<br />
later FAA approved revision, is required on<br />
board the modified aircraft.2. The equipment<br />
for which these provisions are in<br />
<strong>04</strong>.05.2009<br />
18.06.2009<br />
None 1) Prior to installation of this modification 17.09.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10027876 BOMBARDIER AEROSPACE TCCA STC SA09-53 ISSUE 1 CL-600-2B16 Optional Fuel Quantity Display in Kilograms Not Applicable. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.11.2009<br />
10028730 BOMBARDIER AEROSPACE TCCA LSTC C-LSA08-338/D CL-600-2B16 Installation, Complete Custom Aircraft Interior -<br />
ASN 5506<br />
10029282 BOMBARDIER AEROSPACE TCCA STC SA10-21 CL-600-2B16 Installation, Un-Upholstered Headliner,<br />
Rockwell Collins HUD.<br />
Restricted to ASN 5506.Aircraft must be fitted<br />
with an approved means to disconnect the<br />
cabinAC and DC utility buses as a prerequisite<br />
to this modification.<br />
Prior to installation of this modification it 05.02.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.03.2<strong>01</strong>0<br />
10029957 BOMBARDIER AEROSPACE TCCA STC SA10-36 CL-600-2B16 Installation, Quick Access Recorder (QAR) None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.05.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 120/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030620 BOMBARDIER AEROSPACE BD-100-1A10 (CHALLENGER Installation of Miniature Quick Access Recorder None Prior to installation of this modification it 28.06.2<strong>01</strong>0<br />
300)<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030934 BOMBARDIER AEROSPACE REV. 1 TCCA STC SA10-50 BD100-1A10 Activation of Wireless Local Area Network<br />
Access Point on BombardierBD-100-<br />
1A10Revision of the <strong>EASA</strong> STC 10030934,<br />
<strong>EASA</strong> Validation of TCAA<br />
approvedSupplemental Type Certificate SA10-<br />
50<br />
10030938 BOMBARDIER AEROSPACE REV. 1 TCCA STC SA10-44 BD100-1A10 CHALLENGER 300 Installation of Mechanical Provisions and LRU<br />
Installation, AircellAir-to-Ground<br />
Communication System and Immarsat Satcom<br />
System.Revision of the <strong>EASA</strong> STC<br />
10030938, validation of TCAA<br />
approvedSupplemental Type Certificate SA10-<br />
44<br />
10033558 BOMBARDIER AEROSPACE REV. 1 TCCA STC SA10-109 CL-600-2B16 Dual Power for Electronic Flight Bag (EFB) -<br />
Challenger 6<strong>04</strong>/605<br />
10033889 BOMBARDIER AEROSPACE TCCA STC NO. SA11-1 ISSUE 1 CL-600-2B16 Activation of Wireless Local Area Network<br />
Acces Point ICG NXT MailServer System<br />
10034212 BOMBARDIER AEROSPACE TCCA STC SA10-93 CL-600-2B16 WLAN Activation & Incorporation of Aircell<br />
Components<br />
10036<strong>04</strong>2 BOMBARDIER AEROSPACE P-<br />
<strong>EASA</strong>.IM.A.S.03247<br />
TCCA STC SA07-110 BOMBARDIER BD-100-1A10<br />
CHALLENGER 300<br />
10037113 BOMBARDIER AEROSPACE REV. 1 TCCA STC SA11-41 BD-100-1A10 (CHALLENGER<br />
300)<br />
Installation of AVS-470 Tail Camera System.<br />
<strong>EASA</strong> Validation of:Transport Canada<br />
Supplemental Type Certificate SA07-110,<br />
Issue 1 dated3rd August 2007 in accordance<br />
with Aero Consulting Services Ltd.Modification<br />
Data Summary F1610<strong>01</strong>.<br />
Activation of Wireless Local Area Network<br />
Access Point, ICG NxtMailServer System<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.09.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.09.2<strong>01</strong>0<br />
The complete custom aircraft interior defined Prior to installation of this modification it 11.08.2<strong>01</strong>1<br />
by <strong>EASA</strong> STC No. 10<strong>01</strong>6<strong>01</strong>9must be installed must be determined thatthe<br />
concurrently or as a pre-requisite.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Structural and electrical provisions must be<br />
installed in accordancewith <strong>EASA</strong> STC No.<br />
10<strong>01</strong>6<strong>01</strong>9 (TCCA STC No. SA06-90)<br />
Structural and electrical provisions must be<br />
installed in accordancewith <strong>EASA</strong> STC No.<br />
10<strong>01</strong>6<strong>01</strong>9 (TCCA STC No. SA06-90)<br />
concurrently or as apre-requisite.<br />
10037705 BOMBARDIER AEROSPACE TCCA STC NO. SA11-89 ISSUE 1 CL-600-2B16 Modification to Potable Water Tank Air Supply Previous installation of a specific potable water<br />
system is required.Drawings listed in<br />
Modification Data Summary H311000 identify<br />
theprerequisite installations.<br />
Prior to installation of this modification it 16.02.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 16.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification the 23.07.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
This system is intended to provide cached Structural and electrical provisions must 07.11.2<strong>01</strong>1<br />
internet content and e-mailservices to Portable be installed in accordancewith TCCA<br />
Electronic Devises. Any other use of this STC SA<strong>04</strong>-112 (<strong>EASA</strong> STC 10<strong>01</strong>6423)<br />
equipmentwill require a re-examination of the concurrently or as apre-requisite. Prior to<br />
certificate basis.this STC is a design<br />
installation of this modification it must be<br />
certification approval for the activati<br />
determined thatthe interrelationship<br />
between this modifi<br />
Prior to installation of this modification it 16.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 121/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038288 BOMBARDIER AEROSPACE TCCA STC SA11-88 CL-600-2B16 Electronic Flight Bag Class II (PED)<br />
None Prior to installation of this modification it 03.02.2<strong>01</strong>2<br />
(Provisions)<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038597 BOMBARDIER AEROSPACE TCCA STC NO. SA12-12 ISSUE 1 CL-600-2B16 Galley Modification for Microwave Overheat As a prerequisite aircraft must be fitted with<br />
<strong>EASA</strong> STC No. 10<strong>01</strong>6<strong>01</strong>9,Installation of<br />
Complete Custom Aircraft Interior.<br />
10<strong>01</strong>5690 BOMBARDIER AEROSPACE/LEARJET<br />
INC<br />
10<strong>01</strong>5592 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>5955 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>5957 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>5958 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>5959 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>5960 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>5961 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6<strong>01</strong>1 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6055 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6136 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6214 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>677 FAA STC ST03023AT BD-700-1A10 Installation of a Lower Fuselage Canted Drain<br />
Mast Validation of FAA STC ST03023AT as<br />
Basic STC MDL: BAS67<strong>01</strong>7009<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>5<strong>04</strong> REV. 1 TCCA STC C-LSA05-272/D BOMBARDIER BD-700-1A10 1. Installation, Aircraft Interior Completion for 1. Ref G-FM2500<strong>01</strong>32 Rev N/C Limited to<br />
BD700-1A10 Global Express acc MDS S/N 9159.2. This STC is approved only for<br />
E553000 Rev N/C.2. Revision 1: Modification the product configuration as defined in the<br />
to Interior Completion.<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shal<br />
<strong>EASA</strong>.IM.A.S.02098 C-LSA06-256/D BOMBARDIER BD-700-1A11 Aircraft Completion, 13 Passenger Interior Refer to the Limitations sections of the required<br />
ConfigurationValidation of TCCA Limited STC FM Supplement WLAN system os compatible<br />
C-LSA06-256/D to S/N 9188MDL: E786000<br />
Rev NC or later TCCA approved revisions<br />
only to IEEE 802.11(b).<br />
<strong>EASA</strong>.IM.A.S.02100 TCCA STC C-LSA06-291/D BOMBARDIER BD-700-1A10 Aircraft Completion, 12 Passeger Interior<br />
ConfigurationValidation of TCCA Limited STC<br />
C-LSA06-291/D to S/N 9189MDL: F<strong>01</strong>5000<br />
Rev NC or later approved revisions<br />
<strong>EASA</strong>.IM.A.S.021<strong>01</strong> TCCA STC C-LSA06-336/D BOMBARDIER BD-700-1A11 Aircraft Completion, 13 Passenger Interior<br />
ConfigurationValidation of TCCA Limited STC<br />
C-LSA06-336/D to S/N 92<strong>04</strong>MDL: F082000<br />
Rev NC or later approved revisions<br />
<strong>EASA</strong>.IM.A.S.02102 C-LSA06-321/D BOMBARDIER BD-700-1A10 Aircraft Completion, 14 Passenger Interior<br />
CompletionValidation of TCCA Limited STC<br />
C-LSA06-321/D to S/N 9200MDL: F099000<br />
Rev NC or later TCCA approved revisions<br />
<strong>EASA</strong>.IM.A.S.02103 TCCA STC C-LSA07-<strong>01</strong>5/D BOMBARDIER BD-700-1A10 Customized Interior Completion - SN<br />
9196.Validation of TCCA STC C-LSA07-<br />
<strong>01</strong>5/D.<br />
<strong>EASA</strong>.IM.A.S.02106 TCCA STC C-LSA07-<strong>01</strong>3/D BOMBARDIER BD-700-1A10 Aircraft Completion, 13 Passenger Interior<br />
ConfigurationValidation of TCCA Limited<br />
STC C-LSA07-<strong>01</strong>3/D to S/N 9202MDL:<br />
F<strong>01</strong>8000 Rev NC or later TCCA approved<br />
revisions<br />
<strong>EASA</strong>.IM.A.S.02176 BOMBARDIER BD-700-1A11 Aircraft Completion, 13 Passenger Interior<br />
ConfigurationValidation of TCCA Limited STC<br />
C-LSA06-335/D to S/N 9198MDL: F069000<br />
<strong>EASA</strong>.IM.A.S.02227 TCCA STC C-LSA07-086/D REV NC BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
Rev NC or later approved revisions<br />
Customized Interior Completion - SN<br />
9208Validation of TCCA STC C-LSA07-<br />
086/D Rev NC<br />
Refer to the Limitations sections of the required<br />
FM SupplementWLAN system is compatible<br />
only to IEEE 802.11(b)The use of WLAN is<br />
subject to operational rules.<br />
Refer to Limitation sections of the required FM<br />
Supplement<br />
Refer to the Limitations sections of the required<br />
FM SupplementWLAN system is compatible<br />
only to IEEE 802.11(b).The use of WLAN is<br />
subject to operational rules.<br />
Refer to the Limitations sections of the required<br />
AFM Supplement.WLAN system is compatible<br />
only to IEEE 802.11(b).The use of WLAN is<br />
subject to operational rules.<br />
Refer to the Limitations sections of the required<br />
FM SupplementWLAN system is compatible<br />
only to IEEE 802.11(b).The use of WLAN is<br />
subject to operational rules.<br />
Refer to Limitation sections of the required FM<br />
SupplementWLAN system is compatible only<br />
to IEEE 802.11(b)The use of WLAN is subject<br />
to operational rules.<br />
1. Refer to the Limitations sections of the<br />
required FM Supplement2. WLAN system is<br />
compatible only to IEEE 802.11(b).3. The<br />
use of WLAN is subject to operational rules.<br />
<strong>EASA</strong>.IM.A.S.02332 TCCA STC C-LSA07-087/D ISSUE 1 BOMBARDIER BD-700-1A10 Customized Interior Completion - SN Refer to the Limitations sections of the required<br />
9213Validation of TCCA STC C-LSA07-087/D FM Supplement,WLAN system is compatible<br />
issue 1<br />
to IEEE 802.11(b),The use of WLAN is subject<br />
to operational rules,Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship b<br />
<strong>EASA</strong>.IM.A.S.02<strong>462</strong> TCCA STC C-LSA02-251/D BOMBARDIER BD-700-1A10 Customized Interior Completion - SN<br />
9084Validation of TCCA STC C-LSA02-<br />
251/D issue 2<br />
Refer to the Limitations sections of the required<br />
AFM Supplemen<br />
Prior to installation of this modification it 29.02.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 122/<strong>462</strong><br />
06.<strong>04</strong>.2006<br />
26.11.2008<br />
<strong>04</strong>.10.2006<br />
30.11.2006<br />
05.12.2006<br />
20.12.2006<br />
29.11.2007<br />
21.03.2007<br />
05.12.2006<br />
21.06.2007<br />
09.07.2007<br />
05.10.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6242 BOMBARDIER COMPLETION CENTRE <strong>EASA</strong>.IM.A.S.02515 TCCA STC SA05-60 BOMBARDIER BD-700-1A11 Customized Interior Completion - SN Refer to the Limitations sections of the required<br />
24.10.2007<br />
INC<br />
9182.Validation of TCCA STC SA05-60.via<br />
SoC limited to SN 9182.Configuration acc:<br />
CDL E25000 Rev N<br />
AFM Supplement<br />
10<strong>01</strong>6259 BOMBARDIER COMPLETION CENTRE <strong>EASA</strong>.IM.A.S.02538 REV. 1 TCCA SA<strong>04</strong>-113 ISSUE 1 (CDL REV BD-700-1A10 Cabin Interior Door Modifications - ASN 9167. Restricted to ASN 9167. Prior to installation of this modification the 20.12.2007<br />
INC<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
10<strong>01</strong>63<strong>01</strong> BOMBARDIER COMPLETION CENTRE <strong>EASA</strong>.IM.A.S.02598 TCCA STC C-LSA08-<strong>01</strong>9/D BOMBARDIER BD-700-1A11 Customized interior Completion - ACSN 9257 1. Restricted to ASN 9257;2. WLAN<br />
20.03.2008<br />
INC<br />
System in only compatible to IEEE802.11(b);3.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modific<br />
10<strong>01</strong>6302 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6303 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6305 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6306 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6311 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6330 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6355 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6377 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6382 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6416 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6436 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6438 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
<strong>EASA</strong>.IM.A.S.02599 TCCA LIMITED STC C-LSA07-284/D BOMBARDIER BD-700-1A10 Customized Interior Completion - ACSN 9235 Refer to the limitations section of the required<br />
AFM Supplement and to the referenced<br />
FCOMS.WLAN system is compatible only to<br />
IEEE 802.11 (B).<br />
21.12.2007<br />
<strong>EASA</strong>.IM.A.S.02600 TCCA STC C-LSA07-286/D FOR CAB BOMBARDIER BD-700-1A10 Customised Interior Completion -ACSN 9238. Restricted to ASN 9238 and Refer to the<br />
limitations sections of the required AFM<br />
supplement and to the referenced<br />
FCOMS.WLAN System is compatible only to<br />
IEEE 802.11(b).<br />
21.<strong>01</strong>.2008<br />
<strong>EASA</strong>.IM.A.S.02602 TCCA STC (SA05-60) FOR CABIN BOMBARDIER BD-700-1A11 Customised Interior Completion - ACSN 9241 Restricted to ASN 9241 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement.<br />
07.05.2008<br />
<strong>EASA</strong>.IM.A.S.02603 TCCA LIMITED STC C-LSA07-278/D BOMBARDIER BD-700-1A11 Customized Interior Completion - ACSN 9243. Refer to the limitations section of the required<br />
AFM Supplement and to the referenced<br />
FCOMS.WLAN system is compatible only to<br />
IEEE 802.11 (B).<br />
21.12.2007<br />
<strong>EASA</strong>.IM.A.S.02614 TCCA STC SA 03-113 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation, complete Custom Interior Restricted to ASN 5623. 02.11.2007<br />
<strong>EASA</strong>.IM.A.S.02639 TCCA 0-LSA<strong>01</strong>-007 ISSUE 6 BOMBARDIER BD-700-1A10 Interior and Avionics Installation. 1. Limited to AS N90<strong>04</strong>2. Compliance with<br />
Bombardier Aerospace Airworthiness<br />
Limitations GC-90<strong>04</strong>5000-AWL, dated July 15,<br />
2002, is mandatory.3. Occupancy•<br />
Maximum number of passengers Twelve<br />
(12)• Maximum number of occupants<br />
including fligh<br />
<strong>EASA</strong>.IM.A.S.02676 TCCA O-LSA07-261/D ISSUE 1 07/ BOMBARDIER BD-700-1A10 Cabine Floor Structure Modification &<br />
Decompression Panel Relocation.<br />
<strong>EASA</strong>.IM.A.S.027<strong>01</strong> TCCA STC SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Customized interior Completion - ACSN 9254. Restricted to ASN 9254 and1. Refer to<br />
limitations sections of the required AFM<br />
Supplement and to the reference<br />
FCOMS.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
<strong>EASA</strong>.IM.A.S.02706 TCCA STC SA<strong>01</strong>-156 BOMBARDIER BD-700-1A10 Multi-Function Ladder Installation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.02749 TCCA STC C-LSA08-089/D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
AIRCRAFT COMPLETION, 10<br />
This STC is limited to aircraft Bombardier<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>89.<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA08-<br />
089/DIssue 1 dated 21st April 2008, in<br />
accordance with Aero ConsultingServices Ltd.<br />
Modification Data Summary F791<br />
<strong>EASA</strong>.IM.A.S.02777 TCCA C-LSA08-062/D ISSUE 1 BOMBARDIER BD-700-1A10 Customized Interior Completion - ACSN 9250. Restricted to ASN 9250 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and to the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).3. Prior to installation of this<br />
modification the installer must determine that th<br />
<strong>EASA</strong>.IM.A.S.02779 C-LSA08-065/D ISSUE 1 BOMBARDIER BD-700-1A11 Customized Interior Completion - ACSN 9269 Restricted to ASN 9269.WLAN System is only<br />
compatible to 1EEE802.11 (b).<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 123/<strong>462</strong><br />
22.05.2008<br />
05.05.2008<br />
08.05.2008<br />
16.07.2008<br />
23.<strong>04</strong>.2008<br />
17.07.2008<br />
22.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6448 BOMBARDIER COMPLETION CENTRE <strong>EASA</strong>.IM.A.S.02794 TCCA STC SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Customized Interior Completion - ACSN 9262 Restricted to ASN 9262 and1.Refer to the<br />
09.06.2008<br />
INC<br />
Limitations sections of the required AFM<br />
Supplement and to the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer must determine that<br />
the i<br />
10<strong>01</strong>6449 BOMBARDIER COMPLETION CENTRE <strong>EASA</strong>.IM.A.S.02795 BOMBARDIER BD-700-1A11 Customized Interior Completion - ACSN 9273. Prior to installation of this modification the<br />
10.09.2008<br />
INC<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6457 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6458 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6459 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6542 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6543 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6565 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6566 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6567 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
<strong>EASA</strong>.IM.A.S.02803 TCCA C-LSA08-081/D BOMBARDIER BD-700-1A10 Interior Completion, BD-700-1A10 serial<br />
number 9252<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
<strong>EASA</strong>.IM.A.S.028<strong>04</strong> REV. 3 TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Customized Interior Completion - ACSN 9272. 1. Restricted to ACSN 9272.2. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.3.<br />
WLAN systems are compatible only to IEEE<br />
802.11(b).<br />
<strong>EASA</strong>.IM.A.S.02805 TCCA STC C-LSA08-082/D BOMBARDIER BD-700-1A10 Interior Completion, BD-700-1A10 serial<br />
number 9256.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product. The insta<br />
<strong>EASA</strong>.IM.A.S.02920 TCCA STC SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Interior Completion - ACSN 9234 Restricted to ASN 9234 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and to the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).3. Prior to installation of this<br />
modification the installer must determine that th<br />
<strong>EASA</strong>.IM.A.S.02921 TCCA STC SA06-43 ISSUE 2 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
<strong>EASA</strong>.IM.A.S.02956 TCCA STC C-LSA03-458/D BOMBARDIER BD-700-1A10 Installation of Thales Integrated Standby<br />
Instrument.<br />
<strong>EASA</strong>.IM.A.S.02957 TCCA STC C-LSA03-372/D BOMBARDIER BD-700-1A10 Aircraft Completion, 13 Passenger Interior<br />
Configuration<br />
Installation of XM Satellite Radio Antenna. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
1. Restricted to ASN 9120.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworthiness<br />
<strong>EASA</strong>.IM.A.S.02958 TCCA STC C-LSA<strong>01</strong>-417/D BOMBARDIER BD-700-1A10 Approval of Side Facing Divan Limitations. Restricted to ASN 9<strong>01</strong>6.Required<br />
Equipment:Previous installation of<br />
corresponding <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>252 (FAA STC SA8164NM-<br />
D).Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificatio<br />
07.11.2008<br />
Prior to installation of this modification it 18.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 124/<strong>462</strong><br />
28.10.2008<br />
28.07.2008<br />
22.08.2008<br />
23.12.2008<br />
15.12.2008<br />
19.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6572 BOMBARDIER COMPLETION CENTRE <strong>EASA</strong>.IM.A.S.02970 TCCA STC C-LSA03-334/D BOMBARDIER BD-700-1A10 Installation of interior furnishings and cabin 1. Prior to installation of this modification the<br />
02.10.2008<br />
INC<br />
systems, applicable to BD-700-1A10 serial installer must determine that the<br />
number 9112 only.<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product. The insta<br />
10<strong>01</strong>6573 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6591 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6593 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6635 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6652 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6653 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6656 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6667 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10<strong>01</strong>6668 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
<strong>EASA</strong>.IM.A.S.02971 TCCA STC C-LSA05-100/D BOMBARDIER BD-700-1A10 Relocation of Aft Toilet Compressor. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.030<strong>01</strong> TCCA STC SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Customized Interior Completion - ACSN 9270. Restricted to ASN 9270 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and to the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer must determine that<br />
the<br />
<strong>EASA</strong>.IM.A.S.030<strong>04</strong> REV. 1 TCCA STC SA07-<strong>01</strong>9 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
Waterproofing and Spill Management, Interior<br />
Modifications<br />
<strong>EASA</strong>.IM.A.S.03074 TCCA STC SA<strong>04</strong>-113 ISSUE 1 BOMBARDIER BD-700-1A10 Installation, Complete Custom Aircraft Interior /<br />
Installation of cabin systems and custom<br />
furnishings - ACSN 9291<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. Restricted to ASN 9291.2. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and to the referenced FCOMS.3.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).4. Prior to installation of this<br />
modification the installer must deter<br />
<strong>EASA</strong>.IM.A.S.03100 TCCA STC SA05-60 BOMBARDIER BD-700-1A11 Customized Interior Completion - ACSN 9293 Restricted to ASN 9293 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and to the referenced<br />
FCOMS.2.2. WLAN system is compatible only<br />
to IEEE 802.11 (b).3. Prior to installation of this<br />
modification the installer must determine that<br />
<strong>EASA</strong>.IM.A.S.03102 BOMBARDIER BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9286<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.03105 SA05-60 BOMBARDIER BD-700-1A11 Installation, Complete Custom Aircraft Interior Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.03140 TCCA STC SA06-34 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
Installation of CMS-400 Digital Voice Checklist<br />
System.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.03141 TCCA STC SA<strong>04</strong>-113 ISSUE 1 BOMBARDIER BD-700-1A10 Interior Completion, BD-700-1A10 - ASN 9281 Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 125/<strong>462</strong><br />
19.09.2008<br />
21.11.2008<br />
16.03.2009<br />
20.<strong>01</strong>.2009<br />
14.<strong>01</strong>.2009<br />
26.<strong>01</strong>.2009<br />
02.<strong>04</strong>.2009<br />
27.<strong>04</strong>.2009<br />
10.03.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027058 BOMBARDIER COMPLETION CENTRE P-<br />
TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, complete Custom Aircraft Interior Restricted to ASN 9306. 1. Refer to the Prior to installation of this modification it 02.09.2009<br />
INC<br />
<strong>EASA</strong>.IM.A.S.03192<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced FCOMS. 2. interrelationship between this modification<br />
WLAN system is compatible only to IEEE and any other previouslyinstalled<br />
802.11(b). 3. Prior to installation of this modification and/ or repair will introduce<br />
modification the installer mustdetermine that no adverse effectupon the airworthiness<br />
the<br />
of the product.<br />
10028361 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10028491 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
10028492 BOMBARDIER COMPLETION CENTRE<br />
INC<br />
TCCA STC SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9353<br />
Restricted to ASN 9353 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.12.2009<br />
TCCA STC C-LSA09-091/D BD-700-1A10 Bandit Mask Paint Scheme - ASN 9332. Restricted to ASN 9332. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.<strong>01</strong>.2<strong>01</strong>0<br />
TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9332.<br />
10<strong>01</strong>5334 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.00358 TCCA LTD STC C-LSA<strong>04</strong>-212/D CL-600-2B16 Installation of Securaplane Camera System<br />
Transport Canada Limited STC C-LSA<strong>04</strong>-<br />
212/D in accordance with Aero Consulting<br />
Services Modification Data Summary Notice<br />
E091000 Revision n/c or later Transport<br />
Canada Approved Revision.<br />
10<strong>01</strong>5477 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>231 C-LSA05-024/D BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
Installation of Thales Integrated Electronic<br />
Standby Instruments for BD700-1A10 Global<br />
Express and BD700-1A11 Global<br />
5000Validation of imported TCC STC: SA<strong>04</strong>-<br />
118<br />
10<strong>01</strong>5498 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>261 C-LSA05-298/D BOMBARDIER CL-600-2B16 (CL- Aircraft Completion 11 Passenger Interior<br />
6<strong>04</strong><br />
Configuration<br />
10<strong>01</strong>5499 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>262 TCCA STC C-LSA05-321/D BOMBARDIER CL-600-2B16 (CL- Aircraft Completion 9 Passenger Interior<br />
6<strong>04</strong><br />
Configuration<br />
10<strong>01</strong>5500 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>263 C-LSA06-022/D BOMBARDIER CL-600-2B16 (CL- Aircraft Completion, 12 Passenger Interior<br />
6<strong>04</strong><br />
Configuration<br />
10<strong>01</strong>55<strong>01</strong> BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>264 BOMBARDIER BD-100-1A10 Installation of an Executive interior on aircraft<br />
(CHALLE<br />
20<strong>04</strong>7 in accordance with MDL E449000<br />
10<strong>01</strong>5502 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>265 REV 1 TCCA C-LSA06-051/D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
Aircraft completion, 9 passengers interior<br />
configuration in accordance with Aero<br />
Consulting Services Ltd. Modification Data<br />
SummaryE840000 Revision N/C<br />
Restricted to ASN 9332.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and tothe referenced<br />
FCOMS.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
1. Subject to compliance with the provisions<br />
of Part 21 Subpart E, this STC and associated<br />
data shall remain valid until surrendered,<br />
withdrawn or otherwise terminated.2. If<br />
transfer of this Certificate is requested under<br />
Part 21A.116, the STC will b<br />
1. ref. G-FM340<strong>04</strong>0<strong>01</strong> Rev B2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the<br />
Prior to installation of this modification it 15.<strong>01</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.12.20<strong>04</strong><br />
08.08.2005<br />
Valid only for ASN 5596 Registration OY-SGM 07.09.2005<br />
This STC is approved only for the product<br />
15.11.2005<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Restricted to ASN 5602 20.<strong>01</strong>.2006<br />
1. This STC is limited to SN 20<strong>04</strong>7.2.<br />
Certification Basis: an equivalent Safety<br />
Finding has been granted in CRI D-8 for<br />
Emergency exit Marker and Locator Signes.A<br />
deviation form paragraph 25.785(B) has been<br />
granted for personal injury criteria of dynamic t<br />
1. This STC is limited to SN 200942. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determine<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 126/<strong>462</strong><br />
07.11.2005<br />
02.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5563 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>461 TCCA STC Q-LSA05-030/D BD-700-1A10 Installation of Replacement Cockpit Printer 1. Installation is limited to S/N 9086Note: All<br />
Portable Electronic Equipment/Devices PED,<br />
must be unplugge, turned-off and stowed prior<br />
taxi, take-off and landing2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design<br />
12.12.2005<br />
10<strong>01</strong>5591 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>502 TCCA LIMITED STC C-LSA05-347/D BOMBARDIER BD-700-1A10 Installation, Aircraft Interior Completion for<br />
BD700-1A10 Global Expressacc.: MDS<br />
E583000 Rev. N/CValidation of imported<br />
TCCA Limited STC: C-LSA05-347/D<br />
ref. G-FM2500<strong>01</strong>33 Rev. N/C; Limited to S/N<br />
9163Note: 1. The airplane is limited to privat<br />
use only unless the mid cabin door is rendered<br />
inoperable.2. Approval of EFB installation does<br />
not constituete operational approval to use<br />
EFB function.3. This STC<br />
10<strong>01</strong>5594 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>507 FAA STC SA556NE CL-600-2B16 Installation of a Forward Overboard Servicing Limited to Airplane Serial Number 5055 25.10.2005<br />
10<strong>01</strong>5630 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>582 REV. 1 TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Completion of custom Aircraft<br />
Interior for BD700-1A10 Global Expressacc.:<br />
CDL D954000 Rev. KValidation of imported<br />
TCC STC: SA<strong>04</strong>-113<br />
1. Ref. G-FM250<strong>04</strong>0<strong>01</strong> Rev. N/C: Limited to<br />
S/N 91452. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations sh<br />
10<strong>01</strong>5641 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>605 TCCA STC C-LSA06-<strong>01</strong>4/D BOMBARDIER BD-700-1A11 Installation 13 Passenger interior completion for 1. Installation of limited to S/N 91682. This<br />
BD700-1A11<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>5642 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>606 REV. 1 TCCA STC C-LSA05-391/D BD-700-1A10 Aircraft Completion, 13 Passenger Interior<br />
Configuration<br />
17.11.2005<br />
12.09.2005<br />
30.<strong>01</strong>.2006<br />
1. This STC is approved only for the product Prior to installation of this modification it 07.07.2<strong>01</strong>0<br />
configuration as defined inthe approved design must be determined thatthe<br />
data referred to in the paragraph<br />
interrelationship between this modification<br />
"Description".Compatibility with other and any other previouslyinstalled<br />
aircraft/engine configurations shall<br />
modification and/ or repair will introduce<br />
bedetermined by the installer.2. The installation no adverse effectupon the airworthiness<br />
is l<br />
of the product.<br />
10<strong>01</strong>5643 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>607 TCCA STC NO C-LSA05-382/D BOMBARDIER BD-700-1A11 Aircraft Completion 13 Passenger Interior<br />
Configurationalidation of TCCA Limited STC C-<br />
LSA05-382/D to S/N 9170MDL: E810000 Rev<br />
A or later approved revisions<br />
07.<strong>04</strong>.2006<br />
10<strong>01</strong>5675 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>656 FAA STC ST03065AT LEARJET 31A Installation of a Single Universal UNS-1C+ or<br />
UNS-1E Flight Management System<br />
<strong>04</strong>.<strong>01</strong>.2006<br />
10<strong>01</strong>5737 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>761 BOMBARDIER BD-700-1A10 Customised Interior Completion Aircraft 20071, 1. S/N 20071<br />
in accordance with Aero Consulting Services<br />
Ltd. Modification Data Summary E725000 rev<br />
N/C or later approved revision<br />
30.<strong>01</strong>.2006<br />
10<strong>01</strong>5743 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>767 FAA STC ST00393DE-D LEARJET 31A Installation of a Honeywell 440, 660 or 880<br />
Radar System<br />
None 20.<strong>01</strong>.2006<br />
10<strong>01</strong>5781 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>827 TCCA LTD STC C-LSA06-132/D BOMBARDIER BD-700-1A10 Customized Interior Completion ACSN Aerworthiness Limitations - Camera Sysem<br />
17.07.2006<br />
9173Validation of TCCA Limited STC C- Electrical Receptacle Installation - FS806: G-<br />
LSA06-132/D to S/N 9173MDL: E776000 Rev. TM05100073 Rev. NC or later TCCA<br />
NC or later TCCA approved revisionsTCCA<br />
SoC: C-06-316 dated June 30, 2006<br />
approved revisions<br />
10<strong>01</strong>5841 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>936 - BOMBARDIER BD-100-1A10 Aircraft completion, interior configuration in Limited to S/N 20097 17.08.2006<br />
(CHALLE<br />
accordance with Aero Consultung Services Ltd.<br />
Modification Data Summary E843000 revision<br />
N/C<br />
10<strong>01</strong>5858 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>962 TCCA STC C-LSA06-020/D BOMBARDIER BD-100-1A10 Aircraft completion, 10 Passenger interior<br />
configuration, in accordance with MDS<br />
E790000<br />
S/N 20079 24.<strong>04</strong>.2006<br />
10<strong>01</strong>5903 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02029 TCCA STC Q-LSA06-25/D BOMBARDIER BD-700-1A10 Installation Acoustic Insulation ACSN<br />
This STC is approved only for the product<br />
25.07.2006<br />
9163Validation of TCCA Limited STC Q- configuration as defined in the approved design<br />
LSA06-25/D to S/N 9163MDL: 26118002 Rev data referred to in the paragraph "Description".<br />
NC or later TCCA approved revisionsTCCA Compatibility with other aircraft/engine<br />
SoC: NAI5<strong>01</strong>2-06-00062 dated June 20, 2006 configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5912 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02<strong>04</strong>1 C-LSA06-270/D BOMBARDIER BD-100-1A10 Aircraft completion, 10 passenger interior Limited to S/N 2<strong>01</strong>06 18.10.2006<br />
(CHALLE<br />
configuration, in accordance with MDS<br />
F029000 (Original STC numer: Transport<br />
Canada STC C-LSA06-270/D)<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 127/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5956 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02099 REV. 1 TCCA STC SA06-37 BD-700-1A10, BD-700-1A11 Installation, Provisions for D&M PN 444- None. Prior to installation of this modification it 17.03.2<strong>01</strong>0<br />
DMC57-1 SecuraplaneAntenna.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5997 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02154 TCCA STC C-LSA07-003/D BOMBARDIER BD-100-1A10 Aircraft completion, 10 passenger interior Limited to S/N 2<strong>01</strong>11. 12.<strong>01</strong>.2007<br />
(CHALLE<br />
configuration, in accordance with MDS f070000<br />
(Original STC number: Transport Canada<br />
STCC-LSA07-003/D)<br />
10<strong>01</strong>6<strong>01</strong>9 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02186 REV. 61 TCCA STC SA06-90 CL-600-2B16 Customized Interior Completion ASN 57<strong>04</strong>, Restricted to 57<strong>04</strong>, 5707, 5709, 5710, 5712, Prior to installation of this modification it 14.12.2<strong>01</strong>2<br />
5707, 5709, 5710, 5712, 5715,5718, 5725, 5715, 5718, 5725, 5728,5731, 5732, 5733, must be determined thatthe<br />
5728, 5731, 5732, 5733, 5735, 5736, 5743, 5735, 5736, 5743, 5745, 5746, 5748, 5749, interrelationship between this modification<br />
5745, 5746, 5748,5749, 5753, 5754, 5756, 5753, 5754,5756, 5757, 5758, 5760, 5762, and any other previouslyinstalled<br />
5757, 5758, 5760, 5762, 5764, 5765, 5768, 5764, 5765, 5768, 5772, 5774, 5779, modification and/ or repair will introduce<br />
5772,5774, 5779, 5780, 5782, 5785, 5787, 5780,5782, 5785, 5787, 5791, 5797, 5799, no adverse effectupon the airworthiness<br />
5791, 57<br />
5806, 5808,<br />
of the product.<br />
10<strong>01</strong>6102 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02292 TCCA C-LSA07-<strong>04</strong>9/D ISSUE 1 BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6120 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02312 TCCA STC NO. C-LSA07-154/D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6197 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02437 TCCA STC C-LSA07-288/D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6239 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02508 REV. 4 TCCA STC SA07-117 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
10<strong>01</strong>6251 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02528 TCCA STC C-LSA08-<strong>01</strong>2/D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6293 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02589 TCCA STC SA06-84 BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
AIRCRAFT COMPLETION, 10 PASSENGER 1. Compatibility with previous approved<br />
INTERIOR CONFIGURATION<strong>EASA</strong> Validation modifications shall be determined by the<br />
of:Transport Canada Limited Supplemental installer.2. This STC is limited to aircraft<br />
Type Certificate C-LSA07-<strong>04</strong>9/D Issue 1 dated Bombardier BD100-1A10 Serial Number<br />
19th February 2007, in accordance with Aero 2<strong>01</strong>16.<br />
Consulting Services Ltd. Modification Data<br />
Summary F07<br />
AIRCRAFT COMPLETION, 10 PASSENGER<br />
INTERIOR CONFIGURATION /<strong>EASA</strong><br />
Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA07-<br />
154/DIssue 1dated 15th June 2007, in<br />
accordance with Aero Consulting ServicesLtd.<br />
Modification Data Summary F311000<br />
1. This STC is limited to aircraft Bombardier<br />
BD100-1A10 Serial Number 2<strong>01</strong>45.2. Prior<br />
to installation of this modification the installer<br />
must determine that the interrelationship<br />
between this modification and any other<br />
previously installed modificati<br />
Aircraft Completion, 10 passengers interior This STC is limited to aircraft Bombardier<br />
configuration:<strong>EASA</strong> Validation of:Transport BD100-1A10 Serial Number 2<strong>01</strong>55.<br />
Canada Limited Supplemental Type Certificate<br />
C-LSA07-288/D, issue 1dated 22nd October<br />
2007, in accordance with Aeoro Consulting<br />
Services Ltd. Modification Data Summary F<br />
Installation of Class 2 Electronic Flight Bag<br />
(EFB).<br />
10<strong>01</strong>63<strong>04</strong> BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.026<strong>01</strong> REV. 1 TCCA STC C-LSA07-285/D BD-700-1A10 Aircraft Completion, 14 Passenger Interior<br />
Configuration.<br />
This installation approval does not constitute<br />
operational approval forany use of the EFB.<br />
This approval is for the EFB system<br />
structuralmounting and interconnect wiring<br />
only.<br />
AIRCRAFT COMPLETION, 10<br />
1. This STC is limited to aircraft Bombardier<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>72;2. Prior<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited to installation of this modification the installer<br />
Supplemental Type Certificate C-LSA08- must determine that the interrelationship<br />
<strong>01</strong>2/DIssue 1 dated 11th January 2008, in between this modification and any other<br />
accordance with Aero ConsultingServices Ltd. previously installed modificati<br />
Modification Data Summary F5<br />
Improved Hinge Design, Toilet Seat and Lid / -Decrane Aircraft Service Bulletin "Bombardier<br />
Modification of existing toilet seat installation C300 Lavatory Seat Lid/Hinge Assembly", ref.<br />
which allows both toilet seat and lid to remain in SB06008, Revision G, dated 23rd July 2007.<br />
the up position without falling.<strong>EASA</strong> Validation<br />
of Transport Canada Supplemental Type<br />
Certificate SA06-84, Iss<br />
Restricted to ASN 9237.This does not<br />
constitute an operational approval of the<br />
Wireless LocalArea Network (WLAN) system.<br />
It is the operator's responsibility toobtain<br />
operational approval for the airborne use of<br />
transmittingportable electronic devices in ac<br />
28.02.2007<br />
03.07.2007<br />
31.10.2007<br />
Prior to installation of this modification it 17.02.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.<strong>01</strong>.2008<br />
05.11.2007<br />
Prior to installation of this modification it 07.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 128/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6332 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02641 REV. 1 TCCA STC C-LSA07-229/D BD-700-1A11 Installation, Interior Completions In-Service Restricted to ASN 9249 Prior to installation of this modification it 20.<strong>04</strong>.2<strong>01</strong>1<br />
Improvement Modificationsfor ASN 9249.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6333 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02642 TCCA STC NO. SA<strong>04</strong>-112 ISSUE 3. BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6427 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02766 TCCA STC C-LSA08-145/D ISSUE 1 BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6446 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02792 STC C-LSA08-107/D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>6478 BOMBARDIER INC. P-<br />
<strong>EASA</strong>.IM.A.S.02830<br />
REV. 4 TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Aircraft Completion, 13 Passenger Interior<br />
Configuration<br />
10<strong>01</strong>6544 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.02923 REV. 5 TCCA STC SA08-48 BD-700-1A10, BD-700-1A11 Installation, Interior Completions In-Service<br />
Improvement Modifications<br />
AIRCRAFT COMPLETION, 10<br />
This STC is limited to aircraft Bombardier<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>41.<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA07-<br />
411/DIssue 1 dated 5th December 2007, in<br />
accordance with Aero ConsultingServices Ltd.<br />
Modification Data Summary F63<br />
10<strong>01</strong>6660 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.03121 REV. 1 TCCA STC SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior<br />
(S/N 9311).<br />
CUSTOMIZED INTERIOR COMPLETION – Prior to installation of this modification the<br />
AIRCRAFT 2020310 passenger seats interior installer must determine that the<br />
configuration<strong>EASA</strong> Validation of:Transport interrelationship between this modification and<br />
Canada Limited Supplemental Type Certificate any other previously installed modification will<br />
C-LSA08-145/DIssue 1 dated 18th August introduce no adverse effect upon the<br />
2008, in accordance with Aero<br />
airworthiness of the product.1 The ins<br />
ConsultingServices Ltd. M<br />
AIRCRAFT COMPLETION, 10<br />
This STC is limited to aircraft Bombardier<br />
PASSENGERS INTERIOR CONFIGURATION BD100-1A10 Serial Number 2<strong>01</strong>23.<br />
/<strong>EASA</strong> Validation of:Transport Canada Limited<br />
Supplemental Type Certificate C-LSA08-<br />
107/DIssue 1 dated 19th March 2008, in<br />
accordance with Aero ConsultingServices Ltd.<br />
Modification Data Summary F786<br />
Restricted to ASN 9274 and1) Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2)<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
10027337 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Installation, Complete Custom Aircraft Interior Restricted to ASN 9309.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and tothe referenced<br />
FCOMS.WLAN system is compatible only to<br />
IEEE 802.11(b)<br />
10027762 BOMBARDIER INC. REV. 1 TCCA STC SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9343<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
18.12.2007<br />
20.08.2008<br />
28.03.2008<br />
12.<strong>04</strong>.2<strong>01</strong>1<br />
None<br />
product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.05.2<strong>01</strong>1<br />
Restricted to ASN 9311. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.06.2<strong>01</strong>0<br />
Prior to installation of this modification it 22.09.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification will introduce no adverse<br />
effect upon theairworthiness of the<br />
product.<br />
Restricted to ASN 9343. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.06.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 129/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028181 BOMBARDIER INC. TCCA STC SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior - Restricted to ASN 9231 Prior to installation of this modification it 07.12.2009<br />
ASN 9231<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028344 BOMBARDIER INC. BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9320<br />
10028416 BOMBARDIER INC. REV. 2 TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Modification to install the Fwd Pocket door and<br />
Mid Pocket door on aseparate<br />
circuitInstallation, Complete Custom Aircraft<br />
Interior - Revision to <strong>EASA</strong>Supplemental Type<br />
Certificate 10028416 to incorporate missing<br />
drawingson the MDL - ASN 9329<br />
10028519 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9333<br />
10028553 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9115<br />
10028579 BOMBARDIER INC. REV. 2 TCCA STC SA05-60 BD-700-1A11 Installation, Interior Completions In-Service<br />
Improvement Modifications- ASN 9334<br />
10029275 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9323.<br />
10029589 BOMBARDIER INC. TCCA STC SA10-19 BD-700-1A10 Installation, Upgrade from Swift 63 to Swift<br />
Broadband<br />
10029628 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9336<br />
Restricted to ASN 9320 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).3. Prior to installation of this<br />
modification the installer mustdetermine that<br />
the<br />
Restricted to ASN 9329 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Restricted to ASN 9333 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
Restricted to ASN 9115 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
Prior to installation of this modification it 18.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 19.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 21.<strong>01</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 21.<strong>01</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9334 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.08.2<strong>01</strong>1<br />
Restricted to ASN 9323.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement and tothe referenced<br />
FCOMS.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
Prior to installation of this modification it 17.03.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.<strong>04</strong>.2<strong>01</strong>0<br />
Restricted to ASN 9336 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 08.<strong>04</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 130/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029774 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior - Restricted to ASN 9341 and1. Refer to the Prior to installation of this modification it 20.<strong>04</strong>.2<strong>01</strong>0<br />
ASN 9341<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced FCOMS.2. interrelationship between this modification<br />
WLAN system is compatible only to IEEE and any other previouslyinstalled<br />
802.11(b).<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
100300<strong>01</strong> BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9339<br />
Restricted to ASN 9339 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 10.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030<strong>04</strong>0 BOMBARDIER INC. TCCA STC NO. SA10-15 BD-700-1A10/-1A11 Modification, External Airstair Door Switch None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.05.2<strong>01</strong>0<br />
10030078 BOMBARDIER INC. TCCA STC C-LSA02-396/D BD-700-1A10 Modification, 13 Passenger Interior<br />
Configuration<br />
10030079 BOMBARDIER INC. TCCA STC C-LSA02-330/D BD-700-1A10 Aircraft Completion, 10 Passenger Interior<br />
Configuration<br />
10030080 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9331<br />
Restricted to ASN 9102.1. Previous<br />
Embodiment of <strong>EASA</strong> STC No. 10030079<br />
"Aircraft Completion, 10Passenger Interior<br />
Configuration" is required.2. Bombardier<br />
Service Bulletin 700-31-<strong>01</strong>8 Modification -<br />
IntegratedAvionics Computers - Avionics 20<strong>01</strong><br />
Batch 1 IAC U<br />
Prior to installation of this modification it 19.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9102 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.05.2<strong>01</strong>0<br />
Restricted to ASN 9331 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
10030239 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.03164 REV. 1 TCCA STC SA05-60 BD-700-1A11 Installation, Interior Completions. Restricted to ASN 9318.<br />
product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.06.2<strong>01</strong>0<br />
10030240 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.03162 TCCA STC SA05-60 BD-700-1A11 Installation, Interior Completions. Restricted to ASN 9315. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.06.2<strong>01</strong>0<br />
10030781 BOMBARDIER INC. REV. 1 TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Interior Completions In-Service<br />
Improvements Modifications- ASN 9348<br />
Restricted to ASN 9348 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
19.05.2<strong>01</strong>0<br />
Prior to installation of this modification it 25.02.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 131/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030900 BOMBARDIER INC. REV. 3 TCCA STC SA05-60 BD-700-1A11 Installation, Interior Completions In-Service Restricted to ASN 9359 Prior to installation of this modification it 02.03.2<strong>01</strong>1<br />
Improvements Modifications- ASN 9359<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031088 BOMBARDIER INC. REV. 1 TCCA STC SA05-60 BD-700-1A11 Installation, Interior Completions In-Service<br />
Improvements Modifications- ASN 9373<br />
Restricted to ASN 9373 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.02.2<strong>01</strong>1<br />
10031105 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.03036 REV. 1 TCCA STC SA 08-65 BD700-1A10 Water Tank Modification None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.07.2<strong>01</strong>0<br />
10031184 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 Installation, Complete Custom Aircraft Interior -<br />
ASN 9351<br />
10031510 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9349<br />
10031663 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9364<br />
10031900 BOMBARDIER INC. TCCA STC SA05-60 ISSUE 1 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9379<br />
10032248 BOMBARDIER INC. REV. 1 TCCA STC NO. SA05-60 BD-700-1A11 Modification to incorporate changes to the<br />
installation of CustomAircraft Interior - ASN<br />
9370. Revision to <strong>EASA</strong> STC 10032248<br />
10032327 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9360<br />
Restricted to ASN 9351 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer mustdetermine that<br />
the int<br />
Restricted to ASN 93491.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11 (b).<br />
Restricted to ASN 9364 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer mustdetermine that<br />
the int<br />
Prior to installation of this modification it 30.07.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 20.08.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 02.09.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9379 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.09.2<strong>01</strong>0<br />
Restricted to ASN 9370 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.11.2<strong>01</strong>0<br />
Restricted to ASN 9360 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer mustdetermine that<br />
the int<br />
Prior to installation of this modification it 27.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 132/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032532 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior - Restricted to ASN 9377 and1.Refer to the Prior to installation of this modification it 12.11.2<strong>01</strong>0<br />
ASN 9377<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced<br />
interrelationship between this modification<br />
FCOMS.2.WLAN system is compatible only to and any other previouslyinstalled<br />
IEEE 802.11(b).<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032907 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9367<br />
10032919 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9371<br />
10033177 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9369<br />
10033710 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 ISSUE 1 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9385<br />
10033779 BOMBARDIER INC. P-<br />
<strong>EASA</strong>.IM.A.S.03145<br />
TCCA STC SA08-86 BD-700-1A10 Ground Service Mode DC Cabin Power<br />
Distribution Modification<br />
10033995 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113, ISSUE 1 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9380.<br />
10033998 BOMBARDIER INC. REV. 1 TCCA STC SA05-60 BD-700-1A11 Aft Lavatory Backsplash<br />
replacementInstallation, Complete Custom<br />
Aircraft Interior - ASN 9405<br />
10034082 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9394<br />
Restricted to ASN 9367 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer mustdetermine that<br />
the int<br />
Restricted to ASN 9371 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).3.Prior to installation of this<br />
modification the installer mustdetermine that<br />
the int<br />
Restricted to ASN 9369 and1.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
Restricted to ASN 9385 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 07.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 08.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 21.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it <strong>04</strong>.02.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
23.07.2009<br />
Restricted to ASN 9380 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 24.02.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any otherpreviouslyinstalled<br />
modification and/ or repair will introduce<br />
noadverse effect upon the airworthiness<br />
of the product.<br />
Restricted to ASN 9405. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.06.2<strong>01</strong>1<br />
Restricted to ASN 9394 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it <strong>04</strong>.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 133/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034192 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior - Restricted to ASN 9391 and1. Refer to the Prior to installation of this modification it 15.03.2<strong>01</strong>1<br />
ASN 9391<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced FCOMS.2. interrelationship between this modification<br />
WLAN system is compatible only to IEEE and any other previouslyinstalled<br />
802.11(b).<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034584 BOMBARDIER INC. TCCA STC NO. SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9408<br />
Restricted to ASN 9408. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.<strong>04</strong>.2<strong>01</strong>1<br />
10034902 BOMBARDIER INC. TCCA STC C-LSA11-024/D BD-700-1A11 Installation, Antenna Provisions None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.05.2<strong>01</strong>1<br />
10035585 BOMBARDIER INC. REV. 1 TCCA STC NO. C-LSA02-261/D BD-700-1A10 Approval of Side Facing Divan Seating<br />
Limitations<br />
100357<strong>01</strong> BOMBARDIER INC. REV. 1 TCCA STC NO. SA11-30 BD-700-1A10<br />
BD-700-1A11<br />
Restricted to ASN 9054.Previous embodiment<br />
of <strong>EASA</strong> STC No. 10<strong>01</strong>6140 (FAA STC No<br />
SA8164NM-D)<br />
Prior to installation of this modification it 06.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation, Portable Water System UV Filter Prior to the installation of this modification it Prior to installation of this modification it 14.07.2<strong>01</strong>1<br />
must be determinedthat the aircraft interior has must be determined thatthe<br />
been approved by the issuance of an interrelationship between this modification<br />
<strong>EASA</strong>STC that corresponds to one of the and any other previouslyinstalled<br />
Transport Canada STCs listed onTransport modification and/ or repair will introduce<br />
Canada STC No. SA11-30.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
100357<strong>04</strong> BOMBARDIER INC. TCCA STC NO. C-LSA11-025/D BD-700-1A11 Installation, Avionics Systems 1. Restricted to ASNs 9395, 94<strong>04</strong>, 9411,<br />
94172. Embodiment of <strong>EASA</strong> STC No.<br />
10034902 (Transport Canada STC No.C-<br />
LSA11-024/D)<br />
10035711 BOMBARDIER INC. TCCA STC NO. C-LSA11-022/D BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASNs 9395, 94<strong>04</strong>, 9411,9417<br />
10035712 BOMBARDIER INC. TCCA STC NO. C-LSA11-023/D BD-700-1A11 Installation, Medical Evacuation Configuration<br />
Provisions<br />
10035777 BOMBARDIER INC. TCCA STC NO. SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9418<br />
1. Restricted to ASNs 9395, 94<strong>04</strong>, 9411,<br />
9417.2. Embodiment of <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.02172<br />
1. Restricted to ASNs 9395, 94<strong>04</strong>, 9411,<br />
9417.2. Embodiment of <strong>EASA</strong> STC No.<br />
10035711 (refers to PN<br />
0<strong>01</strong>0007349)(Transport Canada STC No. C-<br />
LSA11-022/D)<br />
Prior to installation of this modification it 13.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 13.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 13.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9418 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.07.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 134/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036054 BOMBARDIER INC. REV. 1 TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior - Restricted to ASN 94061. Refer to the Prior to installation of this modification it 08.08.2<strong>01</strong>1<br />
ASN 9406<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced FCOMS2. interrelationship between this modification<br />
WLAN system is compatible only to IEEE and any other previouslyinstalled<br />
802.11(b)<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036058 BOMBARDIER INC. TCCA STC SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9421<br />
10036060 BOMBARDIER INC. REV. 1 TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation of cabin systems and custom<br />
furnishings applicable toBD-700-1A10 serial<br />
number 9393<br />
10036095 BOMBARDIER INC. TCCA STC C-LSA<strong>01</strong>-452/D BD-700-1A10 Interior Modification - ASN 9020 - Installation,<br />
Modifications to APUBay Light, Galley Oven,<br />
Smoke Detector Wiring and Equipment<br />
BayProvisions<br />
Restricted to ASN 9421 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.08.2<strong>01</strong>1<br />
Restricted to ASN 93931. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
Restricted to ASN 9020.Previous embodiment<br />
of <strong>EASA</strong> STC No. 10<strong>01</strong>6140 (refers to PN<br />
0<strong>01</strong>0<strong>01</strong>1877)(Installation of a Complete<br />
Custom Aircraft Interior in accordance withFAA<br />
STC SA8164NM-D) is mandatory.<br />
10036096 BOMBARDIER INC. TCCA STC Q-LSA02-065/D BD-700-1A10 Miscellaneous Cabin Modifications Restricted to ASN 9020.Previous embodiment<br />
of <strong>EASA</strong> STC No. 10<strong>01</strong>6140 (refers to PN<br />
0<strong>01</strong>0<strong>01</strong>1877)(Installation of a Complete<br />
10036344 BOMBARDIER INC. TCCA STC NO. SA11-69 BD-700-1A10, -1A11 Installation, Structural Provisions for Shower<br />
Drain Feedthrough<br />
10036603 BOMBARDIER INC. TCCA STC SA05-60 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9427<br />
10037<strong>04</strong>0 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 ISSUE 1 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9413<br />
10037055 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 ISSUE 1 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9238<br />
Custom Aircraft Interior in accordance withFAA<br />
STC SA8164NM-D) is mandatory.<br />
Prior to installation of this modification it 09.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>1<br />
10.08.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.09.2<strong>01</strong>1<br />
Restricted to ASN 9427 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.09.2<strong>01</strong>1<br />
Restricted to ASN 9413 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN System is compatible only to IEEE<br />
802.11(b).<br />
Restricted to ASN 9238 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN System is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 26.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 27.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 135/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037096 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Installation, Complete Custom Aircraft Interior - Restricted to ASN 9420 and1. Refer to the Prior to installation of this modification it 02.11.2<strong>01</strong>1<br />
ASN 9420.<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced FCOMS.2. interrelationship between this modification<br />
WLAN System is compatible only to IEEE and any other previouslyinstalled<br />
802.11(b).<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037122 BOMBARDIER INC. TCCA STC NO. C-LSA05-030/D BD-700-1A11 Aircraft Completion, 13 Passenger Interior<br />
Configuration.<br />
10037223 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BOMBARDIER BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9419.<br />
Restricted to ASN 9130.Drawing<br />
Prior to installation of this modification it <strong>04</strong>.11.2<strong>01</strong>1<br />
B170<strong>04</strong>4250<strong>04</strong>5 Rev N/C "WD-MOD. TO must be determined thatthe<br />
WIRELESS CABIN NETWORK<br />
interrelationship between this modification<br />
WIRINGPROVISION" disables the Wireless and any other previouslyinstalled<br />
LAN system by disconnecting, cappingStowing modification and/ or repair will introduce<br />
the WLU electrical connector. In lieu of no adverse effectupon the airworthiness<br />
conformity to drawingB170<strong>04</strong>420<strong>04</strong>5 Rev N/C, of the product.<br />
t<br />
Restricted to ASN 9419 and1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN System is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 11.11.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037297 BOMBARDIER INC. TCCA STC SA05-60 BD-700-1A11 Installation of Complete Custom Aircraft Interior Restricted to ASN 9430 Prior to installation of this modification it 17.11.2<strong>01</strong>1<br />
- ASN 9430.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037640 BOMBARDIER INC. TCCA STC NO. SA<strong>04</strong>-113 BD-700-1A10 Installation of Complete Custom Aircraft Interior Restricted to ASN 9423 and1. Refer to the<br />
- ASN 9423.<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN System is compatible only to IEEE<br />
802.11(b).<br />
10037644 BOMBARDIER INC. TCCA STC SA<strong>04</strong>-113 BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9429.<br />
10037675 BOMBARDIER INC. TCCA STC NO. SA05-60 ISSUE 1 BD-700-1A11 Installation, Complete Custom Aircraft Interior -<br />
ASN 9226<br />
10038659 BOMBARDIER INC. REV. 2 TCCA STC SA12-24 BD-700-1A10, BD-700-1A11 Installation of Class II Electronic Flight Bag<br />
(EFB) System for Global6000 and / or Global<br />
5000 aircraft.<br />
Restricted to ASN 9429 and1. Refer to the<br />
Limitations section of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN System is compatible only to IEEE<br />
802.11(b).<br />
Prior to installation of this modification it 12.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 13.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9226 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.12.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.11.2<strong>01</strong>2<br />
10038764 BOMBARDIER INC. TCCA STC C-LSA12-009/D BD-700-1A11 Installation of Complete Custom Aircraft Interior Restricted to ASN 94<strong>01</strong> Prior to installation of this modification it 12.03.2<strong>01</strong>2<br />
- ASN 94<strong>01</strong><br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 136/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038864 BOMBARDIER INC. TCCA STC SA11-96 BD-700-1A10 Installation of a Frequency Converter Fuse None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.03.2<strong>01</strong>2<br />
10039764 BOMBARDIER INC. TCCA STC SA12-16, ISSUE 2 BD-700-1A10 Installation, Aircraft Completion Modifications -<br />
ASN 9440.<br />
10039790 BOMBARDIER INC. TCCA STC Q-LSA00-009/D ISSUE 1 BD-700-1A10 Transport Canada STC No. Q-LSA00-009/D -<br />
Installation of Interior andAvionics.<br />
Restricted to ASN 9440.The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs). Any other intended function of<br />
this equipmentwill require a re-ex<br />
Restricted to ASN 9028.Installation of <strong>EASA</strong><br />
STC No. 10039791 is a pre-requisite.<br />
10039791 BOMBARDIER INC. TCCA STC C-LSA12-<strong>04</strong>0/D ISSUE 1 BD-700-1A10 Installation, Modifications to Interior Completion Restricted to ASN 9028. Installation of <strong>EASA</strong><br />
- ASN 9028.<br />
STC No. 10039790 is apre-requisite.<br />
10039792 BOMBARDIER INC. TCCA STC LSA<strong>01</strong>-329 ISSUE 2 BD-700-1A10 Approval of Seating Limitations for Center &<br />
Aft Positions of Aft RHSDivan (FS 663).<br />
10039808 BOMBARDIER INC. TCCA STC SA12-16, ISSUE 2 BD-700-1A11 Installation, Aircraft Completion Modifications -<br />
ASN 9453<br />
10<strong>04</strong><strong>01</strong>71 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A10 Installation, Aircraft Completion Modifications -<br />
ASN 9450<br />
10<strong>04</strong><strong>01</strong>72 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A10 Installation, Aircraft Completion Modification -<br />
ASN 9441<br />
10<strong>04</strong>0256 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A10 Installation, Aircraft Completion Modifications -<br />
ASN 9455.<br />
Prior to installation of this modification it 22.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 23.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 23.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9028.Previous installation of Prior to installation of this modification it<br />
<strong>EASA</strong> STC No. 10039790 and <strong>EASA</strong> STC No. must be determined thatthe<br />
23.05.2<strong>01</strong>2<br />
10039791are pre-requisites.The aircraft is interrelationship between this modification<br />
limited to private use only, unless the<br />
and any other previouslyinstalled<br />
conditionsspecified in Flight Manual<br />
modification and/ or repair will introduce<br />
Supplement D00691 Revision N/C are no adverse effectupon the airworthiness<br />
satisfied.<br />
of the product.<br />
Restricted to ASN 9453.The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs). Any other intended function of<br />
this equipmentwill require a re-exa<br />
Restricted to ASN 9450The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs). Any other intended function of<br />
this equipmentwill require a re-exam<br />
Prior to installation of this modification it 24.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 15.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9441.The Wireless Local Prior to installation of this modification it 15.06.2<strong>01</strong>2<br />
Area Network (WLAN) is intended to provide must be determined thatthe<br />
internetconnectivity and email services to the interrelationship between this modification<br />
airplane's cabin using portableelectronic and any other previouslyinstalled<br />
devices (PEDs). Any other intended function of modification and/ or repair will introduce<br />
this equipmentwill require a re-exa<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9455.The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs). Any other intended function of<br />
this equipmentwill require a re-exa<br />
Prior to installation of this modification it 21.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 137/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0296 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A10 Installation of Aircraft Completion Modifications Restricted to ASN 9437.The Wireless Local Prior to installation of this modification it 22.06.2<strong>01</strong>2<br />
- ASN 9437.<br />
Area Network (WLAN) is intended to provide must be determined thatthe<br />
internetconnectivity and email services to the interrelationship between this modification<br />
airplane's cabin using portableelectronic and any other previouslyinstalled<br />
devices (PEDs). Any other intended function of modification and/ or repair will introduce<br />
this equipmentwill require a re-exa<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong><strong>04</strong>78 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A11 Installation, Aircraft Completion Modifications -<br />
ASN 9457<br />
10<strong>04</strong>06<strong>01</strong> BOMBARDIER INC. TCCA STC SA12-16 ISSUE 2 BD-700-1A11 Installation, Aircraft Completion Modifications -<br />
ASN 9461<br />
10<strong>04</strong>0720 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A10 Installation, Aircraft Completion Modifications -<br />
ASN 9443.<br />
Restricted to ASN 9457.The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs).Any other intended function of<br />
this equipment will require are-exam<br />
Restricted to ASN 9461The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin portableelectronic devices<br />
(PEDs).Any other intended function of this<br />
equipment will require are-examination<br />
Restricted to ASN 9443.The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs). Any other intended function of<br />
this equipmentwill require a re-exa<br />
Prior to installation of this modification it 05.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 12.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 24.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0722 BOMBARDIER INC. TCCA STC NO. SA12-31 BD-700-1A10/-1A11 Modification, Electronic Wiring Heater Current / None. Prior to installation of this modification it 24.07.2<strong>01</strong>2<br />
Brake TemperatureMonitor Unit (HBMU).<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1031 BOMBARDIER INC. TCCA STC NO. O-LSA02-400 BD-700-1A10 Chairman Interior Installation Restricted to ASN 9003Previous embodiment<br />
of JAA (<strong>EASA</strong>) Accepted Bombardier Service<br />
Bulletin700-23-0<strong>01</strong>, Satellite Communications<br />
System - Installation is aprequisite.The Public<br />
Address System does not comply with<br />
requirements of JAR25.1423. It is not usabl<br />
Prior to installation of this modification it 16.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1238 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>208 REV. 1 TCCA STC C-LSA05-1<strong>04</strong>/D BD700-1A10 Cabin Interior Completion / Furnishings Restricted to ASN 9147 None 17.09.2<strong>01</strong>2<br />
10<strong>04</strong>1239 BOMBARDIER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>230 REV. 1 TCCA STC C-LSA05-169/D BD700-1A10 Passenger Occupancy of the Crew Rest Area Restricted to ASN 9147 Provided Installation of Complete Custom 17.09.2<strong>01</strong>2<br />
Aircraft Interior approvedunder Limited<br />
TCCA STC C-LSA05-1<strong>04</strong>/D and<br />
approved under <strong>EASA</strong> STCNo.10<strong>04</strong>1238<br />
is a prerequisite.<br />
10<strong>04</strong>1267 BOMBARDIER INC. REV. 1 TCCA STC SA03-113 CL-600-2B16 Installation of Complete Customized Aircraft This STC is limited to aircraft Bombardier CL- This certificate also covers the following 14.12.2<strong>01</strong>2<br />
Interior.<br />
600-2B16 (6<strong>04</strong> variant),Serial Number 5580, <strong>EASA</strong><br />
5589, 5591, 5628, 5636 and 5655.<br />
STC:<strong>EASA</strong>.IM.A.S.02003,<strong>EASA</strong>.I<br />
M.A.S.02218,<strong>EASA</strong>.IM.A.S.02311<br />
and,<strong>EASA</strong>.IM.A.S.02454. Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modif<br />
10<strong>04</strong>1344 BOMBARDIER INC. TCCA STC SA12-16 BD-700-1A10 Installation, Aircraft Completion Modifications -<br />
ASN 9456.<br />
Restricted to ASN 9456.The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDS). Any other intended function of<br />
this equipmentwill require a re-exa<br />
Prior to installation of this modification it 10.09.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 138/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1500 BOMBARDIER INC. REV. 1 TCCA STC SA-12-16 ISSUE 2 BD-700-1A10 Installation, Aircraft Completion Modifications - Restricted to ASN 9464 Prior to installation of this modification it 24.09.2<strong>01</strong>2<br />
ASN 9464<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1512 BOMBARDIER INC. TCCA STC SA-12-16 ISSUE 2 BD-700-1A11 Installation, Aircraft Completion Modifications -<br />
ASN 9<strong>462</strong><br />
10<strong>04</strong>1975 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A11 Installation, Aircraft Completion Modifications -<br />
ASN 9458.<br />
10<strong>04</strong>2314 BOMBARDIER INC. TCCA STC NO. SA12-16 BD-700-1A10<br />
BD-700-1A11<br />
10<strong>04</strong>2835 BOMBARDIER INC. STC NO C-LSA03-348/D BD-700-1A10 Aircraft Completion, 13 Passenger Interior<br />
Configuration<br />
10<strong>01</strong>6316 BOMBARDIER INC. - COMPLETION<br />
CENTRE<br />
10029547 BOMBARDIER SHORTS BROTHERS,<br />
PLC<br />
<strong>EASA</strong>.IM.A.S.02622 REV. 7 TCCA STC SA07-119 BD100 CHALLENGER 300 Installation, In-Service Improvement<br />
Restricted to ASN 9<strong>462</strong>. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.09.2<strong>01</strong>2<br />
Restricted to ASN 9458. The Wireless Local<br />
Area Network (WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane's cabin using portableelectronic<br />
devices (PEDs).Any other intended function of<br />
this equipment will require are-exa<br />
Installation, Aircraft Completion Modifications. <strong>EASA</strong> approved configurations are identified in<br />
Configuration DefinitionRecord RAZ-BM700-<br />
0<strong>01</strong>. The Wireless Local Area Network<br />
(WLAN) is intended to provide<br />
internetconnectivity and email services to the<br />
airplane’s cabin using portableelectronic<br />
devices (PED<br />
ModificationsIn-service design improvements to<br />
cabin interior featuresRevision of the <strong>EASA</strong><br />
STC 10<strong>01</strong>6316, Rev. 6 due to revised<br />
technicaldata (Modification Data Summary<br />
F344000 Rev. H )<br />
P-<strong>EASA</strong>.A.S.03579 A319, A320, A321SERIES V2500 NACELLE - RTI MONOLITHIC FAN<br />
COWL DOOR<br />
1003<strong>04</strong>74 BOND HELICOPTERS EUROPE Ltd. EC135 T2(CPDS), EC135 T2+ Engine Usage Monitoring SystemInstallation of<br />
an Engine Usage Monitoring System in<br />
accordance withchange number<br />
BOND/MOD/<strong>01</strong>0 as defined in DL/<strong>01</strong>0-099 to<br />
monitor certainengine parameters, further<br />
described in Design Report DR/<strong>01</strong>0-0<strong>01</strong>.<br />
10031949 BOND HELICOPTERS EUROPE Ltd. REV. 1 AS 332 L2 Installation of TCAS II system in accordance<br />
with BOND/MOD/<strong>01</strong>8.<br />
Restricted to ASN 9093.Bombardier Service<br />
Bulletin 700-31-<strong>01</strong>8 Modification -<br />
IntegratedAvionics Computers - Avionics 20<strong>01</strong><br />
Batch 1 IAC Upgrade must be embodied.<br />
Prior to installation of this modification it 29.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 23.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 20.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.10.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.03.2<strong>01</strong>0<br />
None It is the operator's responsibility to obtain 17.06.2<strong>01</strong>0<br />
operational approval forthe use of the<br />
system in accordance with the operating<br />
rules of theapplicable civil aviation<br />
authority.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelat<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.07.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 139/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039850 BOND HELICOPTERS EUROPE Ltd. EC 135 P1<br />
BOND/MOD/060 "Martin- Baker Rotating Seat None. Prior to installation of this modification it 29.05.2<strong>01</strong>2<br />
EC 135 P2<br />
Installation, EC 135"<br />
must be determined thatthe<br />
EC 135 P2+<br />
interrelationship between this modification<br />
EC 135 T1<br />
and any other previouslyinstalled<br />
EC 135 T2<br />
modification and/ or repair will introduce<br />
EC 135 T2+<br />
no adverse effectupon the airworthiness<br />
EC 635 P2+<br />
EC 635 T1<br />
EC 635 T2+<br />
of the product.<br />
10<strong>04</strong>2728 BOND HELICOPTERS EUROPE Ltd. EC135 T1,-T2,-T2+,-P1,-P2,-P2+ "East Anglia Air Ambulance Role Equipment, Limited to Aircraft with CPDS and FCDS Prior to installation of this modification it 14.12.2<strong>01</strong>2<br />
EC 135" for installation ofNVIS equipment installed.- This STC applies only to the models must be determined thatthe<br />
based on modification BOND/MOD/063 as listed above. This rotorcraftemploys Night interrelationship between this modification<br />
defined inDL/063-099.<br />
Vision Imaging System lighting, commonly and any other previouslyinstalled<br />
named NVISlighting, that has been certified to modification and/ or repair will introduce<br />
ensure the aircraft is compatiblewith<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4082 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4083 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4277 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4310 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4331 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4352 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4437 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4438 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4467 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4473 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4478 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4532 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4533 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4534 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4535 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4536 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4588 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4596 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>4636 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
<strong>EASA</strong>.A.S.<strong>01</strong>174 BOEING 737-200 Revised Seating Layout of 124 Seats and 130<br />
Seats using BAC 1288 Series Seats<br />
17.03.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>175 BOEING 737-200 Deactivation of Type III Exits & Installation of a<br />
60 Seat VIP Passenger configuration.<br />
03.03.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>513 REV 2 BAE 146<br />
Installation of PRNAV Compliant UNS-1E FMS This STC is approved only for the product<br />
08.12.2006<br />
BAE 146/AVRO 146 SERIES<br />
configuration as defined in the approved design<br />
BAE 146/RJ SERIES<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.A.S.<strong>01</strong>555 BAE 146 Change EGPWS Altitude Callouts 16.03.2006<br />
<strong>EASA</strong>.A.S.<strong>01</strong>585 BOEING 737-200 Installation of Cargo Hold Smoke Detection &<br />
Fire Suppression System<br />
<strong>01</strong>.12.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>617 BAE 146/AVRO 146 SERIES Installation of BRNAV Compliant GPS 12.12.2005<br />
<strong>EASA</strong>.A.S.02487 BAE 146-200 Layout of Passenger Accomodation (LOPA) for<br />
84, 93, 95 & 96<br />
19.<strong>04</strong>.2006<br />
<strong>EASA</strong>.A.S.02488 BOEING 737-400 Installation of 136 (16/120) PAX LOPA 07.<strong>04</strong>.2006<br />
<strong>EASA</strong>.A.S.02528 B757-200 Layout of Passenger Accommodation, C2C<br />
Seats with new audio IFE & Seat Covers.<br />
20.03.2006<br />
<strong>EASA</strong>.A.S.02534 BOEING 757-200 Layout of Passenger Accommodation - 92<br />
Business & 8 Economy/Crew<br />
20.03.2006<br />
<strong>EASA</strong>.A.S.02540 CESSNA 441 SERIES Installation of Two L Band Antennae Installation of Aircraft Registered within <strong>EASA</strong><br />
Member State only<br />
17.05.2006<br />
<strong>EASA</strong>.A.S.02618 BOMBARDIER DHC-8-100 ACS Change 7 Upgrade & Elementary -- <strong>04</strong>.08.2006<br />
SERIES<br />
Surveillance Upgrade<br />
<strong>EASA</strong>.A.S.02620 BOMBARDIER DHC-8-100<br />
SERIES<br />
Installation of HF System -- <strong>04</strong>.08.2006<br />
<strong>EASA</strong>.A.S.02621 REV 1 BOMBARDIER DHC-8-102 Installation of Dual UNS-1E Flight Management 1. This STC is approved only for the product<br />
26.<strong>01</strong>.2009<br />
BOMBARDIER DHC-8-103 System.Note: Rev.1 to STC <strong>EASA</strong>.A.S.02621 configuration as defined in the approved design<br />
adds RNP Approach Capability.<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.2. Prior to ins<br />
<strong>EASA</strong>.A.S.02622 BOMBARDIER DHC-8-100 Installation of Aircell ST3100 Satellite -- <strong>04</strong>.08.2006<br />
SERIES<br />
Telephone System (SATCOM)<br />
<strong>EASA</strong>.A.S.02623 BOMBARDIER DHC-8-100 Installation of Universal Terrain Awareness -- <strong>04</strong>.08.2006<br />
SERIES<br />
Warning System (TAWS)<br />
<strong>EASA</strong>.A.S.02695 BOEING 737-200 Installation of 106 Seat LOPA 31.07.2006<br />
<strong>EASA</strong>.A.S.02713 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Omnibus Modification to Support Aircraft<br />
Importation.<br />
Restricted to ASN 5383. 28.11.2006<br />
<strong>EASA</strong>.A.S.02782 AIRBUS A330 Installation of Quick Access Recorder. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description<br />
& Associated Technical Documentation".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by t<br />
02.<strong>01</strong>.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 140/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4640 BOURNEMOUTH AVIATION<br />
<strong>EASA</strong>.A.S.02789 AEROSPATIALE ATR 42 Indraero Siren Cargo Container System This STC is applicable on the following<br />
29.<strong>01</strong>.2008<br />
(CONSULTANTS)<br />
AEROSPATIALE ATR 72 installation on ATR42-320 and ATR72-202 aircraft:Those ATR42-320 previously converted<br />
aircraft previously converted to Class E Cargo to Class E Cargo Compartment Freighter by<br />
Compartment Freighter.<br />
the embodiment of the following ATR GIE<br />
Service Bulletins: • ATR42-25-0070<br />
Reinforce all floor panels, and• ATR42-25-<br />
0063<br />
10<strong>01</strong>4697 BOURNEMOUTH AVIATION<br />
<strong>EASA</strong>.A.S.02864 BOEING 757-200 Installation of B/C LOPA with standing bar<br />
08.03.2007<br />
(CONSULTANTS)<br />
tables<br />
10<strong>01</strong>4863 BOURNEMOUTH AVIATION<br />
<strong>EASA</strong>.A.S.03087 REV. 4 B747-100, -200B/C/F, -300, STC <strong>EASA</strong>.A.S.03087: This modification None. Airplane Flight Manual Supplement, FMS- 21.05.2<strong>01</strong>2<br />
(CONSULTANTS)<br />
B747-400, -400F<br />
introduces a Universal CockpitDisplay System<br />
468-38 Rev. 5 or later approvedrevision,<br />
(Electronic Flight Bag) into the aircraft<br />
is required on board the aircraft Prior to<br />
consisting of 2Flight Deck Displays, an<br />
installation of this modification it must be<br />
Application Server Unit, an Accessible<br />
determined thatthe interrelationship<br />
DataUnit, an external video camera and<br />
between this modification and any other<br />
associated wi<br />
previouslyi<br />
10<strong>01</strong>4928 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
<strong>EASA</strong>.A.S.03181 BAE 146-200 SSR Mode S Enhanced Surveillance 16.08.2007<br />
10<strong>01</strong>4999 BOURNEMOUTH AVIATION<br />
<strong>EASA</strong>.A.S.03299 AIRBUS 1-11 TAWS Installation. Prior to installation of this modification the<br />
30.09.2008<br />
(CONSULTANTS)<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>50<strong>01</strong> BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>5020 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>5023 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>5<strong>04</strong>8 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>5117 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>5122 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>5290 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>01</strong>71<strong>01</strong> BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
<strong>EASA</strong>.A.S.033<strong>01</strong> BAE 146 Installation of VIP LOPA (Inc. Club 4 Layout). Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.03326 BOEING 737-500 Layout of Passenger Accommodation. 19.05.2008<br />
<strong>EASA</strong>.A.S.03329 BOEING 767-300 Layout Passenger Accomodation 17.<strong>04</strong>.2008<br />
<strong>EASA</strong>.A.S.03364 BOEING 757 - 200 Installation of revised Passenger<br />
Accommodation<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
<strong>EASA</strong>.A.S.03466 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation of Electronic Flight Bag Restricted to ASN 5383 06.06.2008<br />
<strong>EASA</strong>.A.S.03471 REV. 1 BOEING 737-300 Installation of B1/B2 Power Connector (Engine<br />
Thrust Change).<br />
Prior to embodying this modification the aircraft<br />
must be modified inaccordance with the<br />
applicable Boeing Service Bulletins for the<br />
22000lbs thrust setting with two CFM-56-3B-2<br />
engines installed as listed inBAC/737/091.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>EASA</strong>.A.S.03825 REV. 1 A320 Installation of 148 PAX Layout of Passenger none Prior to installation of this modification it 12.11.2<strong>01</strong>2<br />
Accommodation (LOPA)This STC is revised in<br />
must be determined thatthe<br />
order to remove the EWIS Limitation<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>EASA</strong>.R.S.<strong>01</strong>071 MD900 Upgrading of existing Single Cargo Hook to<br />
Dual Hook System<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 141/<strong>462</strong><br />
14.07.2008<br />
23.<strong>01</strong>.2009<br />
27.06.2008<br />
07.09.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029836 BOURNEMOUTH AVIATION<br />
BOEING 737-800 164 Passenger Layout. None. Prior to installation of this modification it 23.<strong>04</strong>.2<strong>01</strong>0<br />
(CONSULTANTS)<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038818 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
100389<strong>04</strong> BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10038905 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10038906 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10038907 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10038986 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>04</strong>1170 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
10<strong>04</strong>1983 BOURNEMOUTH AVIATION<br />
(CONSULTANTS)<br />
REV. 1 AS332 L2 Installation of Seat Rail Mounted Fuel Tank. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.03.2<strong>01</strong>2<br />
0<strong>01</strong>0<strong>01</strong>2414-0<strong>01</strong> CAA UK STC AAN 27329 A109E OBSERVER MOVING MAP SYSTEM The approval holder shall fulfill the obligations<br />
INSTALLATIONThe system is manufactured of Part 21, Paragraph 21A.118A.Prior to<br />
by Skyforce and consists of a 5"Display/Control installation of this modification it must be<br />
Head, a Processor Unit, and a Control Panel. determined thatthe interrelationship between<br />
Theequipment is CAA approved under this modification and any other<br />
miscellaneous approvals No. MIS0<strong>01</strong>83.The<br />
installation is ident<br />
previouslyinstalled modification and/ or rep<br />
0<strong>01</strong>0<strong>01</strong>2415-0<strong>01</strong> CAA UK STC AAN 27645 A109E OXYGEN SYSTEM MODIFICATIONReplace<br />
(before) P/N 127<strong>01</strong>52-3 Oxygen cylinder with<br />
(now) "BritishOxygen Company" (BOC),<br />
Medical Gases AF size cylinder.The installation<br />
is identified and defined by the "Sloane<br />
HelicoptersLtd. Modification document No.<br />
P023/109/M<br />
0<strong>01</strong>0<strong>01</strong>2416-0<strong>01</strong> CAA UK STC AAN 27764 A109E Installation of Bendix/King RDR 2000 Weather<br />
Radar System(Bendix/King RDR 200 is CAA<br />
approved Ref. VC <strong>01</strong><strong>04</strong>8).The installation<br />
consists of an antenna-receiver-transmitter<br />
(ART) unit,the Configuration Module, and the<br />
Control Panel. The (ART) radar unit isfi<br />
0<strong>01</strong>0<strong>01</strong>2417-0<strong>01</strong> CAA UK STC AAN 27763 A109E Trimble 21<strong>01</strong> (IO) Approach Plus GPS(CAA<br />
approved Ref. VC<strong>01</strong><strong>04</strong>8)The installation<br />
consists of a Jeppesen data base slot card,<br />
aReceiver/Display Unit (RDU) interfaced to the<br />
EFIS via ARINC 429 andfitted on the top<br />
centre of the instrument panel. A GPS antenna<br />
BOEING 757-200 Installation of 21 Horse Stalls and a 10<br />
Passenger Pallet.<br />
CAA-UK AAN28344 REV. 1 A109A II AVIONICS UPGRADE FOR A109A<br />
IIInstallation of 2 x Garmin GNS430<br />
Nav/Com/GPS, 1 x Garmin<br />
GTX327Transponder, 1 x Garmin GMA340<br />
Audio Panel, Skymap KMD150 and Kannad<br />
406AF-H ELT. Also King KNI 582-<strong>01</strong>. Removal<br />
of 2 x Collins Comms, 2 xCollins Navs, Collins<br />
None The approval holder shall fulfill the<br />
obligations of Part 21,Paragraph<br />
21.A109.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
None The approval holder shall fulfill the<br />
obligations of Part 21, Paragraph<br />
21A.118A.interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
effectupon the airworthiness of the<br />
product<br />
A Placard is placed in clear view of the pilot<br />
and reads:GPS SYSTEM. USE ONLY<br />
DURING VFR OPERATIONAs specified in the<br />
Sloane Flight Manual Supplement No 8:1. The<br />
GPS systems to be used in VFR conditions<br />
only, for use as asupplemental navigation<br />
system.2. T<br />
The approval holder shall fulfill the<br />
obligations of Part 21, Paragraph<br />
21A.118A.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
22.03.2<strong>01</strong>2<br />
22.03.2<strong>01</strong>2<br />
22.03.2<strong>01</strong>2<br />
22.03.2<strong>01</strong>2<br />
This <strong>EASA</strong> STC does not approve the<br />
rep<br />
Prior to installation of this modification it 28.03.2<strong>01</strong>2<br />
installation of Horse Boxes. The following BAC must be determined thatthe<br />
Minor Modifications must be installed as interrelationship between this modification<br />
aprerequisite for this approval:- Mod BAC- and any other previouslyinstalled<br />
820MOD<strong>01</strong>- Mod BAC-820MOD02- Mod BAC- modification and/ or repair will introduce<br />
820MOD03- Mod BAC-820MOD<strong>04</strong>- Mod BAC- no adverse effectupon the airworthiness<br />
820MOD06<br />
of the product.<br />
ONE PLACARD WITH THE WORDS "GPS<br />
LIMITED TO VFR ONLY" POSITIONED ON<br />
THEINSTRUMENT PANEL NEAR THE KMD<br />
150<br />
Prior to installation of this modification it 03.09.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
767-300<br />
Tran<br />
Installation y 276 PAX LOPA on B767-300. The following BAC minor modifications are Prior to installation of this modification it 29.10.2<strong>01</strong>2<br />
prerequisites for thismodification:(1) Mod BAC- must be determined thatthe<br />
784MOD12 Revision of Emergency safety interrelationship between this modification<br />
Equipment Layout;(2) Mod BAC-784MOD06 and any other previouslyinstalled<br />
Revision of Emergency Floor Path Lighting;(3) modification and/ or repair will introduce<br />
Mod BAC-784MOD18 Revision of the PSU no adverse effectupon the airworthiness<br />
(overhea<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 142/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2007 BOURNEMOUTH AVIATION<br />
767-300 In Flight Entertainment and In Seat Power The following BAC STC is a prerequisite for Prior to installation of this modification it 30.10.2<strong>01</strong>2<br />
(CONSULTANTS)<br />
Supply Revision<br />
this modification: ModBAC-784MOD02 must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6987 BRISTOL AEROSPACE LTD. <strong>EASA</strong>.IM.R.S.<strong>01</strong>393 TCCA STC SH91-15; FAA STC SH26 BELL 222<br />
BELL 222B<br />
BELL 222U<br />
BELL 230<br />
BELL 430<br />
Installation of Wire Strike Protection System. 10.03.2008<br />
10033724 BRISTOL AEROSPACE LTD. TCCA STC SH10-4 429 Installation of Wire Strike Protection System. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.02.2<strong>01</strong>1<br />
10<strong>01</strong>7097 BRISTOW HELICOPTERS Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>020 AS 332 L2 Installation of FLIR Ultraforce II system Restricted to Aircraft Serial Number 2616 G-<br />
REDN only<br />
10<strong>01</strong>7131 BRISTOW HELICOPTERS Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>224 AS 332 L, AS 332 L1 AS 332L & L1 Introduction of Rockwell Collins AS332L SeriesAFM Supplements AS332L<br />
TCAS II System.<br />
Flight Manual Supplement No. 36<br />
10<strong>01</strong>7206 BRISTOW HELICOPTERS Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>358 S-92A Installation of Additional Cargo Compartment Prior to installation of this modification the<br />
Baggage Shelf.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10027446 BRISTOW HELICOPTERS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>370 REV. 1 AS 332 L1 ECT Night Vision Imaging System<br />
InstallationMaster Drawing NOR-<strong>04</strong>50 Rev.<br />
ENote: STC revised due to new ownership<br />
Bristow Helicopters<br />
10030289 BRISTOW HELICOPTERS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>472 REV. 1 AS350B2 System Configuration Modification No.<br />
MOD/350/00.5696 includinginstallation of<br />
several avionics and electrical equipment items<br />
andmiscellaneous equipment as specified in<br />
the Modification<br />
SheetMOD/350/00.5696Revision 1 to this STC<br />
introduces AS350B2 Series<br />
None - The first installation of this kit must be<br />
supervised by the STCholder. - This<br />
rotorcraft employs Night Vision Imaging<br />
System lighting, commonlynamed NVIS<br />
lighting, that has been certified to ensure<br />
the aircraft iscompatible with night vision<br />
goggles (<br />
27.07.2006<br />
30.10.2008<br />
20.07.2007<br />
27.10.2<strong>01</strong>1<br />
Limited to S/Nos 1902 and 2312 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
06.09.2<strong>01</strong>0<br />
10034638 BRISTOW HELICOPTERS Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>356 REV. 1 S-76C Qualification of the Garmin GNS-530 Series None. Prior to installation of this modification it 29.03.2<strong>01</strong>2<br />
GPS for En-route Navigationand Non-precision<br />
must be determined thatthe<br />
approaches.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035156 BRISTOW HELICOPTERS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>356 SIKORSKY S-76C Qualification of the Garmin 400 Series GPS for None. Prior to installation of this modification it 30.05.2<strong>01</strong>1<br />
enroute navigation andnon-precision approach.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035471 BRISTOW HELICOPTERS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>467 REV. 1 S-92A Installation of Rockwell Collins TCAS II<br />
systemRev. 1 covers modification of Rockwell<br />
Collins TCAS-4000 TCAS II updateto version<br />
7.1 software - Modification S92/34.5702<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
18.07.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 143/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038558 BRISTOW HELICOPTERS Ltd. REV. 1 S-76C Modification of Rockwell Collins TCAS-4000 Applicable only to the S76C with Turbomeca Prior to installation of this modification it 17.07.2<strong>01</strong>2<br />
TCAS II update to version 7.1software. Arriel 2S2 engines.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0678 BRISTOW HELICOPTERS Ltd. S-61N Activation of ADS-B Function using Mode S<br />
Extended Squitter<br />
10035883 BRISTOW U.S. L.L.C. FAA STC SR09577RC S-76A, S-76C Installation of an Automatic Deployable<br />
Emergency Transmitter (ADELT)<br />
10<strong>01</strong>4176 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.<strong>01</strong>312 BOEING 747-400 Omnibus Modification for B747 Mid J Project<br />
Stretch Embodiment<br />
10<strong>01</strong>4177 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.<strong>01</strong>314 BOEING 747-400 Omnibus Modification for Boeing 747-436 Hi J<br />
Project Stretch Embodiment<br />
10<strong>01</strong>4178 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.<strong>01</strong>315 BOEING 777-200 Omnibus Modification for B777 4 Class Project Prior to installation of this modification the<br />
Stretch Embodiment.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.07.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.07.2<strong>01</strong>1<br />
10<strong>01</strong>4376 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.<strong>01</strong>651 BOEING 737-400 Installation of Enhanced Mode S None 25.11.2005<br />
10<strong>01</strong>5033 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.03345 BOEING 757-200 Reconfiguration of Passenger Cabin 13.06.2008<br />
10<strong>01</strong>5055 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.03376 BOEING 757-200 B757 GPS upgrade to EGPWS. BA B757 AFM Change Sheet No. 10, <strong>Page</strong> 1<br />
and 3 (issue 2).<br />
28.03.2008<br />
10028294 BRITISH AIRWAYS PLC <strong>EASA</strong>.A.S.<strong>01</strong>313 BOEING 777-236 07.05.2009<br />
10030714 BRITISH AIRWAYS PLC B737-400 Fuselage skin GPS antenna structural<br />
provisions<br />
None None 02.07.2<strong>01</strong>0<br />
10031240 BRITISH AIRWAYS PLC B737-400 B737 GPS UPGRADE OF EGPWS None As a prerequisite to this modification the<br />
antenna installation inaccordance with BA<br />
Service Bulletin BA-757-53-00<strong>01</strong> under<br />
<strong>EASA</strong> approval10030714 must be<br />
performed. Successful completion of the<br />
of the test i.a.w. ESA-5<strong>01</strong>-DS-4<strong>01</strong>8<br />
isrequired upon the first in<br />
05.08.2<strong>01</strong>0<br />
10039421 BRITISH AIRWAYS PLC A318/A319/A320/A321 Airbus TCAS change 7.1 update. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2<strong>01</strong>2<br />
10<strong>04</strong>0257 BRITISH AIRWAYS PLC 777-200 B777 TCAS Change 7.1 update none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.06.2<strong>01</strong>2<br />
10<strong>04</strong>0970 BRITISH AIRWAYS PLC B737-400 B737 TCAS Change 7.1 Update. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.08.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 144/<strong>462</strong><br />
28.02.2007<br />
17.11.2006<br />
09.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1273 BRITISH AIRWAYS PLC 747-400 B747-400 TCAS change 7.1 update none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.09.2<strong>01</strong>2<br />
10<strong>01</strong>6535 BRUCE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02912 REV. 1 FAA STC ST00941LA BD-700-1A10 Installation of Floor Proximity Emergency<br />
Escape Path Marking System.<br />
10035636 BRUCE AEROSPACE Inc. 2003-1912 FAA STC SA6<strong>01</strong>1NM CL-600-2B16 Installation of Floor Proximity Emergency<br />
Escape Path Marking System<br />
Seat Mounted Proximity Lighting System:-Exit<br />
identifiers and flood lights (e.g. part number<br />
BR9279-series): aminimum of two out of five<br />
lamps in each part must be operative.-All light<br />
modules (e.g. part number BR9644-series): a<br />
minimum of oneout of two lam<br />
This system has been determined to comply<br />
with the applicableairworthiness requirements<br />
with the following operative lightassemblies: -<br />
Floor Mounted Proximity Lighting SystemExit<br />
identifiers and/or flood lights - 2 bulbs<br />
operative, light trackred modules<br />
10<strong>01</strong>5035 BUCHER LEICHTBAU AG <strong>EASA</strong>.A.S.03348 MD-11 Modification of New Generation Stretcher This approval is only valid for the modified<br />
(NGS) pn. 1120000-2<strong>01</strong> for installation in a MD- installation in the MD-11 on the right hand side<br />
11 on the right hand side of the fuselage, in of the fuselage.All other installations of the<br />
accordance with Bucher General Arrangement New Generation Stretcher are covered by<br />
Drawing 1120000-2<strong>01</strong>.<br />
FOCA STC No. Z25-20-60It is the<br />
responsibility of the installer to make sur<br />
10<strong>01</strong>5074 BUCHER LEICHTBAU AG <strong>EASA</strong>.A.S.034<strong>04</strong> FOCA STC: Z 25-20-53 PILATUS PC-12<br />
PILATUS PC-12/45<br />
PILATUS PC-12/47<br />
EMS installation P/N 1270<strong>01</strong>-300This <strong>EASA</strong><br />
STC extens the validity of FOCA STC Z25-<br />
2053 for PC-12 S/N up to 888.<br />
Prior to installation of this modification it 30.06.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 06.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.11.2007<br />
S/N 861-888 19.12.2007<br />
10<strong>01</strong>5092 BUCHER LEICHTBAU AG <strong>EASA</strong>.A.S.03429 PILATUS PC-12 Heavy Duty Floor Panel 19.05.2008<br />
10<strong>01</strong>5227 BUCHER LEICHTBAU AG <strong>EASA</strong>.A.S.03644 REV. 3 PILATUS PC-12/47E Bucher EMS Equipment PC-12/47E.P/N Applicable to PC12/47E series only.Smoking is The approval holder shall fulfil the 07.07.2<strong>01</strong>0<br />
<strong>01</strong>270<strong>01</strong>-400: Addition of equipment<br />
not permitted in the aircraft cabin when the obligations of Part 21,<br />
configuration P/N <strong>01</strong>270<strong>01</strong>-450<br />
oxygen bottle isinstalled.<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10<strong>01</strong>6797 BUCHER LEICHTBAU AG <strong>EASA</strong>.IM.R.S.<strong>01</strong>150 EUROCOPTER DEUTSCHLAND Ambulance Rescue SystemThe FOCA STC Z This STC is approved only for the product<br />
11.11.2005<br />
BO-105<br />
25-20-49 (ambulance rescue system) was configuration as defined in the approved design<br />
validated by the LBA under the number data referred to in the paragraph "Description".<br />
0589/3025 dated 24 February 1995, approving Compatibility with other aircraft/engine<br />
installation onto the BO105SThis STC is re- configurations shall be determined by the<br />
issued as <strong>EASA</strong> STC to extend applicability to installer.<br />
BO105LS.<br />
10<strong>01</strong>7089 BUCHER LEICHTBAU AG <strong>EASA</strong>.R.S.00697 REV. 2 EUROCOPTER DEUTSCHLAND Ambulance and rescue equipment P/N ARA- 1. No smoking is allowed in the rotorcraft<br />
12.<strong>01</strong>.2007<br />
EC-135-<br />
EC135-AC65 in accordance with master cabin.2. This STC is approved only for the<br />
document list MDOC-AC65 rev D or later product configuration as defined in the<br />
approved revision. Revision 1: Change of approved design data referred to in the<br />
Converter from ARA-EC135-AC65.Revision 2: paragraphs "Description" and “Associated<br />
Inclusion of models P2+ and T2+<br />
Technical Documentation”. Compatibility wit<br />
10<strong>01</strong>7192 BUCHER LEICHTBAU AG <strong>EASA</strong>.R.S.<strong>01</strong>329 REV. 1 EC135 P1, T1, P2, T2, P2+, T2+ EMS-Equipment ARA-EC135-AC66Minor<br />
change to STC <strong>EASA</strong>.R.S.<strong>01</strong>329 to<br />
incorporate:- new mattress for the stretcher-<br />
dead end stop for the stretcher installation-<br />
additionnal stud to the center cabinet- medical<br />
equipment retainers.<br />
10<strong>01</strong>7211 BUCHER LEICHTBAU AG <strong>EASA</strong>.R.S.<strong>01</strong>367 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
EMS Instalaltion ARA-EC135-AC61This<br />
change introduces the following new items not<br />
included in FOCA STC FOCA 25-20-<br />
108:alternative side cabinet LH (p/n<br />
1359270)new center cabinet (p/n<br />
13597<strong>01</strong>)alternative seat installation (p/n<br />
1353<strong>04</strong>0).<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
24.07.2009<br />
Smoking is not permitted in the rotorcraft<br />
cabin.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 145/<strong>462</strong><br />
29.05.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7240 BUCHER LEICHTBAU AG <strong>EASA</strong>.R.S.<strong>01</strong>428 FOCA STC 25-20-62 EUROCOPTER DEUTSCHLAND 1. Installation of ambulance and rescue<br />
22.11.2007<br />
EC-135-<br />
equipment.2. Extension of Validity of former<br />
FOCA STC Z - 25-2062 to the new model<br />
versions T2+/P2+ of EC 135.<br />
10<strong>01</strong>7275 BUCHER LEICHTBAU AG <strong>EASA</strong>.R.S.<strong>01</strong>509 FOCA STC 25-20-64 EC-135-P1, EC-135-P2,<br />
Installation of VIP-EC135-AC63 Bucher VIP Not applicable The approval holder shall fulfil the 14.11.2008<br />
EC-135-P2+, EC-135-T1 Equipment(Revision of FOCA STC FOCA Z 25-<br />
obligations of Part 21,<br />
EC-135-T2, EC-135-T2+<br />
20-64 Issue 3)<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10027691 BUCHER LEICHTBAU AG FOCA 25-20-102 REV. 4 SEE AIRCRAFT ALLOCATION 16G New Generation Stretcher P/N 1120030 S/N: as per Aircraft Allocation Table E<strong>04</strong>3-<strong>01</strong>- This STC revision replaces <strong>EASA</strong> STC 21.08.2<strong>01</strong>2<br />
REV 3<br />
TABLE<br />
SeriesMinor change to <strong>EASA</strong> STC 10027691- 12 Rev. E of 31/07/2<strong>01</strong>2This installation 10027691 Rev. 3Prior to installation of<br />
E<strong>04</strong>3-<strong>01</strong>-12 REV. E OF 31/07/12 Stretcher integration P/N 1120030-Series on constitutes an approval for installation only this modification it must be determined<br />
Airbus A321-211<br />
foraircraft serial numbers as stated in the thatthe interrelationship between this<br />
Master Document List. For anyadditional modification and any other<br />
configurations as per Aircraft Allocati previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
10027884 BUCHER LEICHTBAU AG P-<strong>EASA</strong>.A.S.03796 REV. 2 SEE <strong>EASA</strong> APPROVED AML P/N 1120030-300 - 16g New Generation This STC does not constitute an approval for Prior to installation of this modification it <strong>01</strong>.07.2<strong>01</strong>0<br />
Stretcher XLRevision of the <strong>EASA</strong> STC installation. Compliancewith following must be determined thatthe<br />
10027884 to include A380 a/c type in requirements below need to be demonstrated interrelationship between this modification<br />
theapplicability<br />
through adesign approval for Stretcher and any other previouslyinstalled<br />
installation in aircraft per approvedModel list: § modification and/or repair will introduce<br />
25.561(d) § 25.785(a) § 25.785(h) § 25. no adverse effectupon the airworthiness<br />
of the product.<br />
10029211 BUCHER LEICHTBAU AG REV. 5 EC135 ARA-EC135-AC67 BUCHER Ambulance and<br />
Rescue System (ARA):Rev. 5 to <strong>EASA</strong> STC<br />
10029211: - Installation of a hot compartment<br />
10030689 BUCHER LEICHTBAU AG P-<strong>EASA</strong>.A.S.03797 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
intocenter cabinet Record of revisions: Rev 4: -<br />
editorial change to <strong>EASA</strong> approval certificate<br />
(correction by <strong>EASA</strong>)Rev 3: (Minor Chang<br />
16g New Generation Stretcher P/N 1120020-<br />
300 - (NGS)<br />
10030758 BUCHER LEICHTBAU AG P-<strong>EASA</strong>.A.S.03712 ERJ-170() E006-14-08 - P/N 1120050 9G NGS XL<br />
Stretcher: Installation of aremovable 9g New<br />
Generation Stretcher (NGS)<br />
10030810 BUCHER LEICHTBAU AG FOCA Z25-20-57 REV. 1 EC135 P1(CDS), EC135<br />
P1(CPDS)<br />
EC135 P2(CPDS), EC135 P2+<br />
EC135 T1, EC135 T2, EC135 T2+<br />
10031757 BUCHER LEICHTBAU AG P-<strong>EASA</strong>.A.S.03984 REV. 6 SEE AIRCRAFT ALLOCATION<br />
TABLE E-<strong>04</strong>3-02-12 REV. A<br />
DATED 10/12/2<strong>01</strong>2<br />
10038839 BUCHER LEICHTBAU AG <strong>EASA</strong>.A.S.03919 REV. 1 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of ARA-EC135-AC60 Ambulance<br />
and Rescue SystemNew revision covers:STC<br />
issuance under <strong>EASA</strong> format at revision 0,<br />
Exchange of Suction Unitwith new P/N<br />
1355185,adding P2+ and T2+ at the list<br />
of EC135 models. This STC revokes the STC<br />
1003<strong>04</strong>89<br />
ATS 16g Stretcher P/N: 1123000-000 / -100 / -<br />
200 / -300 / -390 / -400 /-500 / -590Major<br />
Change to STC 10031757 Rev. 4-Installation<br />
envelope expansion for Boeing B787-<br />
Reduction of installation limitations-Introduction<br />
of the Aircraft Allocation Table<br />
Small person restraint system P/N 1120<strong>04</strong>0 for<br />
use on 16G New GenerationStretcher P/N<br />
1120020-XXX.<br />
Compliance with NVIS compatible flight decks Prior to installation of this modification it 21.05.2<strong>01</strong>2<br />
must be demonstrated by theinstaller when must be determined thatthe<br />
ARA-EC135-AC67 with NVIS compatible cabin interrelationship between this modification<br />
lighting shallbe installed into NVIS equipped and any other previouslyinstalled<br />
rotorcraft.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC does not constitute an approval for Prior to installation of this modification it <strong>01</strong>.07.2<strong>01</strong>0<br />
installation. Compliancewith following must be determined thatthe<br />
requirements below need to be demonstrated interrelationship between this modification<br />
through adesign approval for Stretcher and any other previouslyinstalled<br />
installation in aircraft per approvedModel list: § modification and/ or repair will introduce<br />
25.561(d) § 25.785(a) § 25.785(h) § 25. no adverse effectupon the airworthiness<br />
of the product.<br />
-Limitations iaw. User Manual E<strong>01</strong>7-<strong>01</strong>-08-<br />
TGM 25/12 addressed per CRI D-1 A.S.3712<br />
None. 13.07.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.11.2<strong>01</strong>1<br />
This STC constitutes an approval for<br />
installation only for aircraftserial numbers as<br />
stated in the Master Document List. For any<br />
additionalconfiguration as per Aircraft<br />
Allocation Table, the requirements asstated in<br />
the Master Document List have to be demo<br />
Small person restraint to be used only on<br />
stretcher P/N 1120020-XXX.Occupant<br />
limitations as per General Arrangement<br />
drawing 1120<strong>04</strong>0 and UserManual E<strong>01</strong>7-<strong>04</strong>-<br />
08.<br />
This <strong>EASA</strong> STC amends STC 10031757<br />
Rev. 5Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
14.12.2<strong>01</strong>2<br />
effectupon<br />
The installation of this modification by 20.03.2<strong>01</strong>2<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation.Prior to<br />
installation of this modification it must be<br />
determined thatthe interre<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 146/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1271 BUCHER LEICHTBAU AG FOCA STC 25.20.42<br />
SEE APPROVED MODEL LIST ATL Airtransport Litter System P/N 123000 - 1. This STC does not constitute an approval for This <strong>EASA</strong> STC replaces STC-FOCA 25- 03.09.2<strong>01</strong>2<br />
(ISSUE 5)<br />
Seriesincluding customers options:P/N 123000- installation. Compliancewith following 20-42 This Supplemental Type Certificate<br />
000 (Demo ATL)P/N 123000-110<br />
requirements below need to be demonstrated is approved only for the<br />
(Lufthansa)P/N 123000-241 (AUA-2)P/N by a designapproval for Stretcher installation in productconfiguration as defined in the<br />
123000-27 (Emirates-2)<br />
aircraft per applicable approvedmodel list: JAR approved design data referred to<br />
25.561(d) JAR 25.785(a), JAR<br />
inparagraph "Description". The approval<br />
holder shall fulfill the obligations of Par<br />
10<strong>01</strong>4<strong>01</strong>9 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>073 CESSNA 550 CITATION II Installation of TCAS II system in accordance<br />
with MDL BCA 70-00 rev. 3 dated 18/03/05<br />
10<strong>01</strong>4024 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>079 BEECH 1900D Emergency Transmitter Kannad 406 MHz<br />
installation on Beechcraft 1900 D.<br />
10<strong>01</strong>4<strong>04</strong>9 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>131 REV. 1 BEECH 300<br />
BEECH B300<br />
Installation of KLN 900 GPS with EFIS-85<br />
according to STC<strong>EASA</strong>.A.S.<strong>01</strong>131.<br />
This STC is applicable to s/n 550-0622 <strong>04</strong>.<strong>04</strong>.2005<br />
1. This STC is limited to Beechcraft 1900 s/n<br />
UE-1 and up.2. Required Pre-Modification:<br />
any existing <strong>EASA</strong> approved ELT doubler<br />
Airplane Flight Manual Supplement No.<br />
BCA/61 must be used with this modification.<br />
10<strong>01</strong>4088 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>182 BEECH C90<br />
Installation of Weather Radar RDR-2000 Modification limited to Beech C90 S/N LJ-684<br />
BEECH C90 A<br />
and Becch C90A S/N LJ-1526<br />
10<strong>01</strong>4121 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>231 BEECH C90 A Skywatch SKY497 TCAS I installation on 1. AFMS No 68/BCA rev 0 of April 2005 must<br />
Beech C90A<br />
be used when modification is installed2.<br />
Modification is limited to Beech C90A S/N LJ-<br />
1526<br />
10<strong>01</strong>4190 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>332 REV. 1 CESSNA 500, CITATION Dual GARMIN GPS installation: GNS-430A + 1. S/N 550-0324 and 500-03612. This STC<br />
CESSNA 550 CITATION II GNS-530A in accordance with MDL BCA 74- is approved only for the product configuration<br />
00 rev 6 dated 19/07/05<br />
as defined in the approved design data<br />
referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by t<br />
20.<strong>01</strong>.2005<br />
BEECH 300 /B300 - F-GPRH - SN FA 226. The approval holder shall fulfil the<br />
obligations of Part<br />
21,Paragraph21.A109.Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this and<br />
any other previously installedand/ or<br />
repair will introduce no adverse<br />
06.02.2<strong>01</strong>2<br />
10<strong>01</strong>4220 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>381 BEECH 1900D Installation of ACSS TCAS 2000 System. 08.07.2005<br />
10<strong>01</strong>4335 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>590 BEECH 1900C, AIRLINER Installation of ACSS TACS 2000 System on This STC is limited to Beech 1900 C SN UC-<br />
11.10.2005<br />
Beech 1900C.<br />
115<br />
10<strong>01</strong>4387 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.<strong>01</strong>673 BEECH 1900D Installation of a TCAS II System This STC is applicable to Beechcraft 1900<br />
model D, all Serial Numbers<br />
05.12.2005<br />
10<strong>01</strong>4616 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.02745 BEECH 1900D Installation of VIP configuration in aft ward This modification limits 14 passengers<br />
09.11.2006<br />
cabin and passive noise reduction kit<br />
maximum.<br />
10<strong>01</strong>4831 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03<strong>04</strong>6 BEECH C90<br />
Installation of dual Mode S transponder system<br />
22.05.2007<br />
BEECH E90<br />
BEECH F90<br />
(GARMIN GTX-330 or GTX-330D).<br />
10<strong>01</strong>4835 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03051 <strong>EASA</strong> STC 20<strong>04</strong>-2474 CESSNA 500 Major Modification: change of a pilot HSI 1. See original STC : DGAC-F nr. F-CIM81-<br />
02.03.2007<br />
against EHSI ; re-wiring of existing equipment SF-00<strong>01</strong>02. This STC is approved only for<br />
power supply to the emergency bus.Note: This the product configuration as defined in the<br />
<strong>EASA</strong> STC supersedes <strong>EASA</strong> STC 20<strong>04</strong>- approved design data referred to in the<br />
2474.<br />
paragraphs "Description" and “Associated<br />
Technical Documentation”. Compatibility wi<br />
10<strong>01</strong>5029 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03338 BEECH 1900C, AIRLINER Installation of a toilet cargo aera. Modification limited to Beech 1900C s/n UC-<br />
168.<br />
10<strong>01</strong>5038 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03351 BEECH 1900 28-230 volts inverter installation on Beech 1900 Airplane flight manual supplement BCA 102,<br />
series according to modification file BCA102, rev. 0, dated 30-10-2007 or later approved<br />
rev. 0, dated 30-10-2007 or later approved revisions must be used when modiifcation is<br />
revisions.<br />
applied.<br />
10<strong>01</strong>5058 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03380 BEECH 1900C, AIRLINER Installation of a galley in the FWD right area of 1. Must be installed on Beech 1900C (S/N<br />
the A/C.<br />
UC-1 and after);2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed modification<br />
will introduce no<br />
10<strong>01</strong>5059 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03381 REV. 1 BEECH 1900C, AIRLINER Installation of a galley in the FWD right area of<br />
the A/C.<br />
Must be installed on Beech 1900C (S/N UC-1<br />
and after).<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 147/<strong>462</strong><br />
17.03.2005<br />
30.05.2005<br />
31.<strong>01</strong>.2007<br />
10.<strong>01</strong>.2008<br />
19.11.2007<br />
29.<strong>01</strong>.2008<br />
29.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5111 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03454 REV. 1 BEECH BARON 58 Dual Garmin Installation : GNS-530 (GPS Airplane Flight Manual Supplement ref. BCA<br />
08.05.2008<br />
approaches and PRNAV approved) + GNS 107-06, revision 2, dated 23 April 2008 or later<br />
430 on Baron 58 (EFS 40/50 equipped). approved revision must be used when<br />
modification is applied in the<br />
Aircraft.Modification limited to s/n TH-1510, TH-<br />
1515, TH-1537, TH-17<strong>01</strong> to TH-1706, TH-<br />
1734 and T<br />
10<strong>01</strong>5140 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03496 DGAC AAC NO. 751 BEECH 1900C, AIRLINER Installation of a King/ Bendix KLN-90B GPS 1. The supplemental AFM No. TF524PA<br />
28.02.2008<br />
with B-RNAV capacity.Note: This STC revises must be used when the modification is<br />
DGAC approval AAC No. 751.<br />
installed.2. Limited to S/N UC-168, F-GVLC<br />
and UC-153, F-GNPM.<br />
10<strong>01</strong>5232 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03655 BEECH 200<br />
Be ‘Mode S / Flight ID’ capable Collins TDR- Prior to installation of this modification the<br />
27.<strong>04</strong>.2009<br />
BEECH 300<br />
94(D) transponders.<br />
installer must determine that the<br />
BEECH B200<br />
interrelationship between this modification and<br />
BEECH B300<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5239 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03666 BEECH C90<br />
BCA 110 Rev. 3 - Garmin GNS-x30WA (GNS- Prior to installation of this modification the<br />
09.<strong>01</strong>.2009<br />
BEECH C90A<br />
530WA or GNS-430WA) and Sandel SN4500 installer must determine that the<br />
BEECH E90<br />
installation for B-RNAV, P-RNAV and GNSS interrelationship between this modification and<br />
BEECH F90<br />
approaches.<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5291 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03830 REV. 1 200C BCA112 revision 2, dated 15 July 2<strong>01</strong>2 : Limitation to sn BB-1473 Prior to installation of this modification it 25.07.2<strong>01</strong>2<br />
underwings, rooftop and PODantennas<br />
must be determined thatthe<br />
installation and belly antennas relocation.Major<br />
interrelationship between this modification<br />
Change of STC <strong>EASA</strong>.A.S.03830.<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The app<br />
10<strong>01</strong>5307 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03899 BEECH B90<br />
BEECH C90<br />
BEECH E90<br />
Be ‘Mode S / Flight ID’ capable Collins TDR-<br />
94(D) transponders.<br />
10<strong>01</strong>5308 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.03900 BEECH F90 Be ‘Mode S / Flight ID’ capable Collins TDR-<br />
94(D) transponders.<br />
10027323 BUSINESS & COMMUTER AIRCRAFT B300 HF-9000 installation on Beech B300 Series<br />
PROLINE 21 Equipped<br />
10029562 BUSINESS & COMMUTER AIRCRAFT BEECH C90A BCA117 rev 0 - GPS replacement and aircraft<br />
capacity validation forB-RNAV, P-RNAV and<br />
GNSS approaches prodecures<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Modification applicable to B300 equipped with<br />
Proline 21, serial numberFL-1 and after and<br />
FM-1 and after<br />
27.<strong>04</strong>.2009<br />
27.<strong>04</strong>.2009<br />
1) The approval holder shall fulfil the 21.09.2009<br />
obligations of Part 21,Paragraph<br />
21.A1092) Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/or re<br />
Limited to: S/N LJ-1660 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.<strong>04</strong>.2<strong>01</strong>0<br />
10032469 BUSINESS & COMMUTER AIRCRAFT C90 BCA118-00 - ADF system upgrade on beech<br />
S/N LJ - 894<br />
Limitation to beech C90 SN LJ-894 09.11.2<strong>01</strong>0<br />
10034237 BUSINESS & COMMUTER AIRCRAFT REV. 1 1900D Double GARMIN GPS400W Installation for B- Installation limited to Beech 1900D equipped Prior to installation of this modification it 15.06.2<strong>01</strong>2<br />
RNAV and P-RNAV and RNPApproach LNAV with Rockwell CollinsAPC-65H autopilot or must be determined thatthe<br />
procedures, according to modification No BCA FYD-65 H flight director and EFIS Rockwell interrelationship between this modification<br />
121.Revision 1 adding the coupling to Rockwell CollinsDPU 84, upgraded for GPS approach and any other previouslyinstalled<br />
Collins FYD-65 H flightdirector.<br />
through Rockwell Collins SB 77(523-0805196) modification and/ or repair will introduce<br />
and SB 81 (523-0805<strong>04</strong>6).<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 148/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034238 BUSINESS & COMMUTER AIRCRAFT 1900C, 1900D BCA 120 revision 0 - 28-230 volts inverter(s) Not applicable Prior to installation of this modification it 17.03.2<strong>01</strong>1<br />
Installation on Beech 1900Series.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1003<strong>462</strong>2 BUSINESS & COMMUTER AIRCRAFT BEECH 1900D BCA 85 rev 3 - Full VIP Cabin Installation<br />
Beech 1900D<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.<strong>04</strong>.2<strong>01</strong>1<br />
10035661 BUSINESS & COMMUTER AIRCRAFT B200 Installation of a ADF60 on a Beech 200 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.07.2<strong>01</strong>1<br />
10035662 BUSINESS & COMMUTER AIRCRAFT B200 Installation of a ALT4000 on a Beech 200 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.07.2<strong>01</strong>1<br />
10035665 BUSINESS & COMMUTER AIRCRAFT B200 Installation of a DME4000 on a Beech 200 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.07.2<strong>01</strong>1<br />
10038717 BUSINESS & COMMUTER AIRCRAFT <strong>EASA</strong>.A.S.00327 REV. 1 B1900D Installation of Two Transponders mode S RCZ- BEECH 1900 D S/N UE 70 The approval holder shall fulfil the 09.03.2<strong>01</strong>2<br />
852<br />
obligations of Part<br />
21,Paragraph21.A109.Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this and<br />
any other previously installedand/ or<br />
repair will introduce no adverse<br />
10<strong>01</strong>6240 BUTLER NATIONAL CORPORATION <strong>EASA</strong>.IM.A.S.02512 FAA STC NO. ST00846SE BOEING 747-100<br />
BOEING 747-200<br />
BOEING 747-300<br />
10<strong>01</strong>6460 BUTTERFIELD INDUSTRIES, INC. <strong>EASA</strong>.IM.A.S.02806 FAA STC SA4362NM BEECH 200<br />
BEECH B200 SERIES<br />
Installation of Model 840037-108, 840037-112, This STC is approved only for the product<br />
and 840037-113 transient Suppression Device configuration as defined in the approved design<br />
on Boeing 747-100, 747-200, 747-300 SP and data. Compatibility with other aicraft/engine<br />
SR series airplanes fitted with Honeywell configuraitons shall be determined by the<br />
Analog Fuel quantity Indication System in installer.<br />
accordance with Butler National Corpora<br />
Installation of Butterfield Industries Oil Residue<br />
Collection System Kit P/N BI 1<strong>01</strong>1-1<br />
10<strong>01</strong>6461 BUTTERFIELD INDUSTRIES, INC. <strong>EASA</strong>.IM.A.S.02807 FAA STC SA00829CH BEECH B200 SERIES Installation of Butterfield Industries Air/Oil<br />
Separator System Kit P/N BI 60<strong>01</strong>-1<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the prod<br />
Aircraft which are not modified by STC<br />
SA4362NM, will also require installation of an<br />
oil collection tank1 Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this<br />
modification and any other pre<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 149/<strong>462</strong><br />
15.10.2007<br />
08.08.2008<br />
08.08.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039322 BUTTERFIELD INDUSTRIES, INC. FAA STC SA02215SE 1. F90<br />
Inspection Panel Kit BI 95<strong>01</strong>-0<strong>01</strong>.Fabrication of None Prior to installation of this modification it 25.<strong>04</strong>.2<strong>01</strong>2<br />
2. 200, 200C, 200CT, 200T Inspection Panel Kit BI 95<strong>01</strong>-0<strong>01</strong>, in<br />
must be determined thatthe<br />
2. A200, A200C, A200CT, B200CT accordance withDrawing List BI 9025, Revision<br />
interrelationship between this modification<br />
2. B200T, 300<br />
A, dated February 17, 2<strong>01</strong>2, or laterFAA-<br />
and any other previouslyinstalled<br />
3. B200, B200C, B300<br />
approved revision; and installation in<br />
modification and/ or repair will introduce<br />
accordance with InstallationInstructions BI 90<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5347 C & D INTERIORS <strong>EASA</strong>.IM.A.S.0<strong>04</strong>75 REV. 1 BOEING 737-600 C&D Interiors Stowage S1, Galley S1, Galley<br />
G2B, Galley G3B, Stowage S2, Forward<br />
lavatory, Passenger Seat Installation,<br />
Overhead Stowage Bin Installation, Sidewall<br />
Installation, PSU Installation, Passenger Seat<br />
Proximity Light installation.<br />
10<strong>01</strong>5324 C & D ZODIAC, Inc. <strong>EASA</strong>.IM.A.S.0028 REV. 3 FAA STC ST<strong>01</strong>415LA CL-600-2C10<br />
CL-600-2D24<br />
CL-600-2E25<br />
1. Subject to compliance with the provisions of<br />
Part21 Subpart E, this STC and associated<br />
data shall remain valid until surrendered,<br />
revoked or otherwise terminated.2. If transfer<br />
of this STC Certificate is requested under Part<br />
21A.116, the STC will be rei<br />
17.05.2006<br />
Flight Deck Access System (FDAS) Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.<strong>01</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>5346 C & D ZODIAC, Inc. <strong>EASA</strong>.IM.A.S.0<strong>04</strong>71 REV 1 FAA STC ST<strong>01</strong>056LA DC-9-81 (MD-81)<br />
Installation of Galleys, Closets, Stowages, 1. This STC is approved only for the product<br />
10.<strong>01</strong>.2007<br />
DC-9-82 (MD-82)<br />
Lavatories, Bins, Class Divider, (Movable), configuration as defined in the approved design<br />
DC-9-83 (MD-83)<br />
Sidewall Panels, Ceiling Panels,<br />
data referred to in the paragraph "Description".<br />
DC-9-87 (MD-87) MD 90-30 Coatrooms,and Passenger Service Unites Compatibility with other aircraft/engine<br />
(PSUs) Installation in accordance with C & D configurations shall be determined by the<br />
Interiors Index List No. A<strong>04</strong>, Revision A, dated installer.<br />
Ju<br />
10<strong>01</strong>5837 C & D ZODIAC, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>931 FAA STC ST<strong>01</strong>880LA BOEING 747-400 Installation of pantry -- 19.12.2006<br />
10<strong>01</strong>6190 C & D ZODIAC, Inc. <strong>EASA</strong>.IM.A.S.02421 REV. 1 FAA STC ST02144LA B777-200 Pantry installation P/N C8<strong>01</strong>0<strong>01</strong>-1<strong>01</strong>,P/N 1. Prior to installation of this modification the<br />
08.<strong>01</strong>.2009<br />
C8<strong>01</strong>0<strong>01</strong>-103 and P/N C8020<strong>01</strong>-1<strong>01</strong>.Revision installer must determine that the<br />
1: addition of P/N C8020<strong>01</strong>-1<strong>01</strong><br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
1003<strong>01</strong>54 C & D ZODIAC, Inc. FAA STC ST<strong>01</strong>989LA-D SEE <strong>EASA</strong> APPROVED MODEL Validation of FAA STC ST<strong>01</strong>989LA-D: None Prior to installation of this modification it 31.05.2<strong>01</strong>0<br />
LIST<br />
Adjustable Cargo Net Installation<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038766 C & D ZODIAC, Inc. FAA STC NO. ST02415LA B767-300 Interior Installation and Modification to include<br />
Center Bin, CabinCeilings and Outboard<br />
Stowage Bins.<br />
10<strong>04</strong>0831 C & D ZODIAC, Inc. FAA STC ST00869SE B757-200 Validation of FAA STC ST00869SE<br />
(Modification to Overhead Stowage<br />
Binslocated in the passenger cabin in order to<br />
extend the bins inboard).<br />
10032537 C&D ASSOCIATES, INC. FAA STC SA02816CH G58 Installation of C&D Associates<br />
Combustion Heater Part<br />
NumberCD50000K33.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.03.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.07.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.11.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 150/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034098 C.A. FLOR FLORDELIS FAA STC ST<strong>01</strong>786LA B737-100, -200, -200C SERIES Upgrade Flight Data Recorder System Not Applicable Prior to installation of this modification it 08.03.2<strong>01</strong>1<br />
B737-300, -400, -500 SERIES Parameters<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>7158 CALEDONIAN AIRBORNE SYSTEMS<br />
LTD<br />
10<strong>01</strong>7222 CALEDONIAN AIRBORNE SYSTEMS<br />
LTD<br />
10<strong>01</strong>7223 CALEDONIAN AIRBORNE SYSTEMS<br />
LTD<br />
10035678 CALEDONIAN AIRBORNE SYSTEMS<br />
LTD<br />
10034473 CALIFORNIA SHOCK TRAUMA AIR<br />
RESCUE<br />
<strong>EASA</strong>.R.S.<strong>01</strong>266 SIKORSKY S-76 AF-ADELT improved installation on S-76 STC requires minor change F<strong>01</strong>2/208/0<strong>01</strong> to<br />
be incorporated.<br />
25.<strong>01</strong>.2007<br />
<strong>EASA</strong>.R.S.<strong>01</strong>386 REV. 2 AGUSTA-BELL 212 & 412 Installation of CAS CPT 900 ELT. None Prior to installation of this modification the 21.<strong>04</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
<strong>EASA</strong>.R.S.<strong>01</strong>388 REV. 2 BELL 212, BELL 412 Installation of CAS CPT 900 ELT None Prior to installation of this modification the 21.<strong>04</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
JETSTREAM 4100 Installation of Role Equipment for Maritime Serial numbers 41022 and 41025 only. Prior to installation of this modification it 11.07.2<strong>01</strong>1<br />
Patrol Training<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC SR02160LA BO 105 LS A-3 Engine Upgrade:Removal of two (2) Rolls-<br />
Royce engine models 250-C28C and installing<br />
two(2) Rolls-Royce engine models 250-C30P<br />
in accordance with FAA STCSR02160LA,<br />
dated March 11, 2<strong>01</strong>1.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and! or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.<strong>04</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>5309 CAMERON BALLOONS LIMITED <strong>EASA</strong>.BA.S.<strong>01</strong>0<strong>01</strong> GEFA AS 105 GD (HOT AIR<br />
AIRSHI<br />
Introduction of Liquid Pilot Lights. None. 30.<strong>04</strong>.2007<br />
10<strong>01</strong>6193 CANARD AEROSPACE CORPORATION <strong>EASA</strong>.IM.A.S.02430 FAA STC ST<strong>01</strong>106CH BOEING 747-100<br />
Installation of Digital Flight Data Recorder This STC is approved only for the product<br />
29.10.2007<br />
BOEING 747-100B SUD<br />
Expanded Parameters in accordance with configuration as defined in the approved design<br />
BOEING 747-200B<br />
Canard Aerospace Corporation Document data. Compatibility with other aircraft/engine<br />
BOEING 747-200C<br />
Control Drawing No. 30<strong>01</strong>0, Rev. G. dated 6 configurations shall be determined by the<br />
BOEING 747-200F<br />
October 2003, or later FAA approved revisions, installer.<br />
BOEING 747-300<br />
BOEING 747-SP<br />
BOEING 747-SR<br />
FAA STC number ST<strong>01</strong>106CH.<br />
10<strong>01</strong>6546 CANARD AEROSPACE CORPORATION <strong>EASA</strong>.IM.A.S.02925 FAA STC ST<strong>01</strong>117CH BOEING 747-100<br />
Option 1: Installation of Honeywell Classic 1. Prior to installation of this modification the<br />
12.11.2008<br />
BOEING 747-100B SUD<br />
Navigator system in accordance with Canard installer must determine that the<br />
BOEING 747-200<br />
Aerospace Corporation Control Drawing Nr. interrelationship between this modification and<br />
BOEING 747-200C<br />
30<strong>01</strong>1, Rev. NC, dated November 25, 2002, any other previously installed modification will<br />
BOEING 747-200F<br />
Appendix A, or later FAA approved<br />
introduce no adverse effect upon the<br />
BOEING 747-300<br />
revision.Option 2: Installation of a CMA-900 airworthiness of the product. The i<br />
BOEING 747-SP<br />
BOEING 747-SR<br />
Flight<br />
10028374 CANARD AEROSPACE CORPORATION P-<br />
FAA STC ST<strong>01</strong>331CH DHC-8-2<strong>01</strong>, -202 Installation of Honeywell Mark VII Enhanced Electronic Flight Information Systems (EFIS) The STC holder shall provide by 7th June 23.12.2009<br />
<strong>EASA</strong>.IM.A.S.03246<br />
Ground Proximity WarningSystem to replace symbol generator upgradedto Part Number 2<strong>01</strong>0 Instructions for<br />
existing Mark II Ground Proximity Warning (PIN) 70<strong>04</strong>544.314 in accordance with ContinuedAirworthiness on Electrical<br />
SystemFAA STC No ST<strong>01</strong>331CH, reissued 21 Honeywell ServiceBulletin (SB) 70<strong>04</strong>544.34-48 Wiring Interconnection System - EWIS<br />
May 2009<br />
(modification BC) is required prior to, ICA -in accordance with Special<br />
orconcurrent with, accomplishment of this Condition H-<strong>01</strong> "Enhanced<br />
modific<br />
AirworthinessProgramme for Aeroplane<br />
System - ICA on EWIS" Pri<br />
10<strong>01</strong>4684 CARGOLUX AIRLINES INTERNATIONAL <strong>EASA</strong>.A.S.02847 BOEING 747-400 SERIES Installation of an Artex B406-4 Automatic Fixed<br />
Emergency Locator Transmitter on B747-400F<br />
in accordance with Cargolux Service Bulletin<br />
CLX-SB-747-23-0<strong>01</strong> and Master Drawing list<br />
CLX-STC-06-<strong>01</strong>.<br />
14.03.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 151/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5<strong>04</strong>9 CARGOLUX AIRLINES INTERNATIONAL <strong>EASA</strong>.A.S.03366 BOEING 747-400F ICS-220A Iridium sitcom installation on B747- The Data on Airworthiness Limitations,<br />
22.<strong>04</strong>.2008<br />
400F airplanes in accordance with Master revisions required of the Maintenance<br />
Drawing List CLX-STC-07-<strong>01</strong>, dated 22 publications etc. arising from the changes<br />
November2007 or later <strong>EASA</strong> approved associated with the STC is provided in DWG<br />
revisions.<br />
CLX-STC-07-<strong>01</strong>: ICS-220A Iridium Satcom<br />
Installation on B747-400F Airplanes - ICA and<br />
miscella<br />
10028509 CARSON HELICOPTERS, INC. P-<br />
FAA STC SR02487NY SIKORSKY S61N AND S61NM Increased Category A Performance. As specified in the approved RFMS. Carson Helicopters Inc. composite main 18.<strong>01</strong>.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>532<br />
rotor blades (STC<strong>EASA</strong>.IM.R.S.<strong>01</strong>129)<br />
must be installed.<br />
10032448 CARSON HELICOPTERS, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>138 FAA STC SH639NE S61 N Installation of 11,000 pound capacity Cargo<br />
Sling in accordance withCarson Services, Inc.,<br />
Drawing List Report No S61N-1A Revision D<br />
datedJanuary 10, 2005<br />
10<strong>01</strong>5717 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>714 SA00-69 BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
Environmental Control System Performance<br />
Improvement Modification as per TCCA STC<br />
#SA00-69, Issue 2, Issue Date: 15 June 2000<br />
10<strong>01</strong>5908 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02035<br />
TCCA STC SA06-58 BOEING 747-400 Design Elementary & Enhanced<br />
REVISON 1<br />
Surveillance.Validation of a STC SA06-58.<br />
10<strong>01</strong>5925 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02060 SA<strong>01</strong>-98 BOMBARDIER DHC-8-102 APU Oil Cooler Door Deletionas per TCCA<br />
BOMBARDIER DHC-8-103 STC # SA<strong>01</strong>-98, Issue 1, Issue Date: 23.<br />
BOMBARDIER DHC-8-311<br />
BOMBARDIER DHC-8-315<br />
August 20<strong>01</strong><br />
10<strong>01</strong>5926 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02061 SA<strong>01</strong>-67 BOMBARDIER DHC-8-102<br />
BOMBARDIER DHC-8-103<br />
BOMBARDIER DHC-8-311<br />
BOMBARDIER DHC-8-315<br />
Screen Door and Ram Air Vent Modificationas<br />
per TCCA STC # SA<strong>01</strong>-67, Issue 1, Issue<br />
Date: 7. June 20<strong>01</strong><br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
06.07.2009<br />
Configuration 1:a) Fwd Exhaust per Conair<br />
Aerospace Drawing 2302D21003 Rev Nil,<br />
dated May 19, 2000*.b) Aft Exhaust per<br />
Conair Aerospace Drawing 2302D21005 Rev<br />
Nil, dated May 19, 2000*. This element<br />
applicable to -300 Series only.c) Fwd Intake<br />
per<br />
Configuration 1:DHC-8 Series 100/200/300<br />
aircraft modified in accordance withSTC<br />
<strong>EASA</strong>.IM. A.S. <strong>01</strong>714Configuration 2:DHC-8<br />
Series 100/200/300 aircraft in accordance with<br />
STC <strong>EASA</strong>.IM.A.S 02061 (equivalent to<br />
Bombardier Mod 8/2328 and<br />
8/3330.Conditions: This<br />
Configuration 1:DHC-8 Series 100/200/300<br />
aircraft with or without Bombardier Standard<br />
option Order 8155 APUConfiguration 2:DHC-8<br />
Series 100/200/300 aircraft with or without<br />
Bombardier ACM Exhaust Mod.<br />
8/1815Configuration 3:DHC-8 Series<br />
100/200/300 aircraft<br />
10<strong>01</strong>6096 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02285 TCCA STC SA07-44 BOMBARDIER CL-600-2B19 Conversion of full cabin class E Cargo<br />
Compartment.<br />
11.<strong>04</strong>.2007<br />
10<strong>01</strong>6357 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02679 TCCA STC SA 08-08 ISSUE 1, MAR BOMBARDIER DHC-8-400<br />
SERIES<br />
Forward Baggage Compartment Installation. 12.03.2008<br />
10<strong>01</strong>6358 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02680 TCCA STC SA08-9, ISSUE 1, 4 FE BOMBARDIER DHC-8-400<br />
SERIES<br />
G4 Galley Installation. 08.02.2008<br />
10<strong>01</strong>6359 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02681 TCCA STC SA08-10, ISSUE 1, 4 F BOMBARDIER DHC-8-400 Right AFT Draft Bulkhead InstallationTCCA<br />
08.02.2008<br />
SERIES<br />
STC Number: SA08-10, Issue 1, <strong>04</strong> February<br />
2008<br />
10<strong>01</strong>6360 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02682 TCCA STC SA 08-11 ISSUE 1 4 FE BOMBARDIER DHC-8-400<br />
SERIES<br />
72 Passenger Seat Reconfiguration 08.02.2008<br />
10<strong>01</strong>6361 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02683 TCCA STC SA 08-12 ISSUE 1 4 FE BOMBARDIER DHC-8-400<br />
SERIES<br />
G3 Galley Modification. 08.02.2008<br />
10<strong>01</strong>6563 CASCADE AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02954 TCCA STC NUMBER SA08-91 BOMBARDIER DHC-8-400 DHC-8-400 Conversion to Bulk FreighterTCCA 1 Prior to installation of this modification the<br />
29.<strong>01</strong>.2009<br />
SERIES<br />
STC Number SA08-91, Issue 1, dated 31 installer must determine that the<br />
December 2008<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the pro<br />
10029545 CASCADE AEROSPACE Inc. TCCA STC SA<strong>01</strong>-40 DHC-8-102, -103, -106<br />
Ground Air Connection ModificationTCCA STC Placards have to be installed in accordance Note: SC EWIS is not applicable. 31.03.2<strong>01</strong>0<br />
DHC-8-2<strong>01</strong>, -202<br />
SA<strong>01</strong>-40, Is.1, dated 14 March 20<strong>01</strong><br />
with Conair AerospaceEngineering drawing<br />
DHC-8-3-1, -302<br />
2854D215<strong>01</strong>, Rev. D.<br />
10<strong>01</strong>5469 CASCADE AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>222 SA<strong>01</strong>513SE BAE JETSTREAM 32<strong>01</strong> SERIES Installation of Sandel Terrain Awareness<br />
Warning System (TAWS)<br />
Limitations as per Flight Manual 09.02.2007<br />
10<strong>01</strong>5711 CASCADE AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>706 REV 1 FAA STC ST<strong>01</strong>630SE BOEING 737 Installation of Eybrow Window Deletion Kit.FAA Compatibility of this design change with other<br />
14.03.2006<br />
STCST<strong>01</strong>630SE<br />
previously approved modifications must be<br />
determined by the installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 152/<strong>462</strong><br />
22.02.2006<br />
20.11.2006<br />
07.08.2006<br />
07.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6109 CASCADE AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.02299 STC ST<strong>01</strong>181SE DORNIER 328-100<br />
Installation of increased security cockpit door A copy of this Certificate and Cascade Aviation<br />
19.<strong>01</strong>.2007<br />
DORNIER 328-300<br />
Services Master Drawing List (MDL)<br />
02CAS096-MDL, Revision D, dated July 14,<br />
2003 orlater approved revision must be<br />
maintained as part of the permanent records<br />
for the modified aircraft<br />
10027057 CASCADE AVIATION SERVICES INC. P-<br />
FAA STC ST<strong>01</strong>133SE DHC-8-102, -103, -106<br />
Installation of an increased security cockpit None 1) Prior to installation of this modification 02.09.2009<br />
<strong>EASA</strong>.IM.A.S.03259<br />
DHC-8-2<strong>01</strong><br />
doorFAA STC # ST<strong>01</strong>133SE<br />
the installer mustdetermine that the<br />
DHC-8-3<strong>01</strong>, -311, 314, 315<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10039180 CEAPR REV. 2 HR 200/100, HR200/100S<br />
HR200/120, HR200/120B<br />
HR200/160<br />
R2100, R2100A, R2112, R2120U<br />
R2160, R2160D, R2160I<br />
DET 1203<strong>01</strong> Rev. 0 - Oil pressure tranducer<br />
line R2000-HR2000 dated 7March 2<strong>01</strong>2<br />
10032548 CENTURY FLIGHT SYSTEMS, INC AK 847 STC SA 3389SW-D PA-31, PA-31-325, PA-31-350 AK 847 Validation / Century 41 Installation in<br />
Piper, Type CertificateNumber A20SO models<br />
PA-31, PA-31-325, PA-31-350<br />
Limitation to serial numbers 0<strong>01</strong> up to 378<br />
included.<br />
1. This STC is limited to aircraft Models PA-31,<br />
PA-31-325 and PA-31-350,2. Piper<br />
Model PA-31 is limited to S/N 712 and<br />
Up,3. Placard 13A990-1 stating<br />
"conduct trim check prior to first flight ofday<br />
(see POH)" is required<br />
Prior to installation of this modification it 26.<strong>04</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
The approval holder shall fulfill the 15.11.2<strong>01</strong>0<br />
obligations of Part 21, Pragraph21A.3<br />
The approval holder shall fulfill the<br />
obligations of Part 21, Paragraph21.A109<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between<br />
10<strong>01</strong>5954 CERTIFICATION DOCUMENTS AND <strong>EASA</strong>.IM.A.S.02097 FAA STC ST10674SC CESSNA 750 CITATION X Installation of an Aerodata AG Automatic Flight Limited to Aircraft Serial Number 262 only.<br />
Inspection System (AFIS).<br />
15.10.2007<br />
10<strong>01</strong>4339 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.<strong>01</strong>597 MITSUBISHI MU-2B-36A Avionics Upgrade in accordance with doc No<br />
CLS-05-MU-AC128, Revision 1.3., dated<br />
27/<strong>01</strong>/2006.<br />
Limited to S/N MU2B-36A-718SA. 08.02.2006<br />
10<strong>01</strong>4486 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.02548 LETECKE ZAVODY L 200 D Avionics upgrade in accordance with the<br />
document no;CLS-06-L200-AC 129, dated<br />
23/06/2006<br />
S/N 171206 28.07.2006<br />
10<strong>01</strong>4761 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.02951 CESSNA 421C Avionics Upgrade, Proj. No.: CLS-07-C421-<br />
AC147Replacement of existing obsolete<br />
transponder, altimeters, ELT and COM/NAV<br />
with new that meets the current technical and<br />
operating requirements.<br />
15.10.2007<br />
10<strong>01</strong>49<strong>01</strong> CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.03135 CESSNA 172S Installation of the DME KN 62A, ADF KR-87<br />
and XPDR KT-73<br />
10.10.2007<br />
10<strong>01</strong>4989 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.03284 LETECKE ZAVODY L-410-UVP- Installation of ACAS II system with XPDR This STC is valid only for L410-UVP-E13<br />
05.11.2007<br />
E13<br />
(MST-67A) and ELT defined in document CLS- aircraft type, registration OK-UDS, S/N 892321<br />
05-L410-AC125, revision 02 dated <strong>04</strong>.11.2005<br />
10<strong>01</strong>4990 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.03285 LETECKE ZAVODY L-410-UVP Installation of NAV/COM/GPS as defined in<br />
document CLS-06-6410-AC140, issue 0,<br />
revision 2 dated 13.09.2006<br />
1. This STC is valid only for L410-UVP aircraft<br />
type.<br />
10<strong>01</strong>4991 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.03286 LETECKE ZAVODY L 410 UVP-E Installation of- ACAS II (CAS-67) system with 1. This is valid only for L-410-UVP-E aircraft<br />
one XPDR (MST-67)- EGPWS Mk. VI system- type.<br />
KLN-94 GPS receiver, FA 2100 CVR, C 406-1<br />
ELT- KMA-24H-70, LUN1120 and SAE-5-35as<br />
defined in document CLS-06-L410-AC138,<br />
issue 0, revision 1 dated 14.<strong>04</strong>.2006<br />
10<strong>01</strong>5069 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.03395 LETECKE ZAVODY L 200 A<br />
LETECKE ZAVODY L 200 D<br />
10<strong>01</strong>5193 CESKA LETECKA SERVISNI A.S. <strong>EASA</strong>.A.S.03577 CESSNA 414<br />
CESSNA 414A<br />
10029112 CESKA LETECKA SERVISNI A.S. L-410 UVP-E-LW, L-410 UVP- Dual Mode-S Transponder upgrade for EHS<br />
E20,<br />
L-410 UVP-E9, L-410 UVP-LW,<br />
L-410M, L-410 UVP, L-410 UVP-E<br />
L-420<br />
capability<br />
05.11.2007<br />
05.11.2007<br />
Installation of new COM, NAV, GPS, XPDR +<br />
<strong>04</strong>.07.2008<br />
Encoder, DME, ADF and flight instruments to<br />
meet the current technical and operating<br />
requirements of IFR category.<br />
Avionics upgrade 16.12.2008<br />
None None 05.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 153/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
100297<strong>01</strong> CESKA LETECKA SERVISNI A.S. P-<strong>EASA</strong>.A.S.03951 SUKHOI SU-31 Avionics upgrade. None. Prior to installation of this modification the 14.<strong>04</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10<strong>01</strong>6<strong>01</strong>2 CESSNA AIRCRAFT COMPANY <strong>EASA</strong>.IM.A.S.02178 ST<strong>01</strong>399WI CESSNA 560<br />
Cessna STC ST<strong>01</strong>399WI, of 21 August<br />
05.02.2007<br />
CESSNA 650 CITATION III 2006.Installation of a Honeywell DL-950 Data<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
CESSNA 750 CITATION X<br />
Loaderto replace the existing DL-800.<br />
10<strong>01</strong>6637 CESSNA AIRCRAFT COMPANY <strong>EASA</strong>.IM.A.S.03077 FAA STC SA<strong>01</strong>519WI CESSNA 525 Installation of an observer seat/3rd audio 1. Prior to installation of this modification the<br />
28.11.2008<br />
station/Extended Range Comm.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>3934 CESSNA CITATION EUROPEAN <strong>EASA</strong>.A.S.00334 REV. 1 CESSNA 525 Installation of a Skywatch HP SKY899A TCAS 1. Applicability: Cessna 525 MSN 525-0<strong>01</strong> to<br />
30.08.2007<br />
SERVICE<br />
I coupled to a Honeywell KMD-850 MFD, in 359 included equipped with Honeywell WX RSaccordance<br />
with Cessna Citation European<br />
Service Center FAM Ref.: 111, Rev NC. Dated<br />
14 August 2007 and FAM ref 82, Rev <strong>01</strong>,<br />
dated 22 October 20<strong>04</strong> or later approved<br />
revision<br />
811A and FMS GNS-XLS.<br />
10<strong>01</strong>6805 CHELTON FLIGHT SYSTEMS <strong>EASA</strong>.IM.R.S.<strong>01</strong>165 REV. 1 FAA STC SR02209AK BELL 206A<br />
Installation of FlightLogic Synthetic Vision EFIS/AIU integration with the autopilot is Prior to installation of this modification it 23.11.2<strong>01</strong>1<br />
BELL 206B<br />
Electronic FlightInformation System (EFIS-SV). approved only when configuredwith the 902- must be determined thatthe<br />
BELL 206L<br />
00028-<strong>01</strong> Control Panel;Activation of Fuel Flow interrelationship between this modification<br />
BELL 206L-1<br />
functions requires installation of<br />
and any other previouslyinstalled<br />
BELL 206L-3<br />
separatelyapproved fuel flow<br />
modification and/ or repair will introduce<br />
BELL 206L-4<br />
transducers;Installation is not permitted on no adverse effectupon the airworthiness<br />
BELL 407<br />
Instrument Flig<br />
of the product.<br />
10<strong>01</strong>6223 CHEYENNE TECH <strong>EASA</strong>.IM.A.S.02471 FAA STC SA<strong>01</strong>379WI PIPER PA-42-1000<br />
PIPER PA-42-720<br />
Dual Digital Air Data System Installation<br />
Qualified for Operation in RVSM Airspace.<br />
10<strong>01</strong>5771 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>810 ST03064AT BAE JETSTREAM 41<strong>01</strong> Installation of Honeywell MK VI Enhanced<br />
Ground Proximity Warning System (EGPWS)<br />
Additional operational limitatiosn may apply for<br />
dual operation due to RVSM Altimeter location.<br />
10<strong>01</strong>6183 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02412 FAA STC ST 03080 AT Installation of a Honeywell AAK VI EGPWS. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6184 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02413 FAA STC ST 02898 AT BOMBARDIER CL-600-2B19 Installation of a Honeywell MK V EGPWS.<br />
BOMBARDIER CL-600-2C10 (FAA STC ST 02898 AT).<br />
10<strong>01</strong>6185 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02414 FAA STC ST 03336 AT BOMBARDIER CL-600-2B19 Installation of Protective Covers for K4XD<br />
Relay. Traffic Alert and Collision Avoidance<br />
Systems (TCAS) Processor and Horizontal<br />
Stabilizer Control Unit (HSTCU).<br />
10<strong>01</strong>6186 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02415 FAA STC ST 03099 AT BOMBARDIER CL-600-2B19 Installation of a replacement landing gear<br />
wiring harness.<br />
10<strong>01</strong>6345 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02662 FAA STC ST2685AT SAAB 340B<br />
Installation of FA2100CVF Cockpit Voice<br />
SAAB SF340A<br />
Recorder in Saab 340 series.<br />
10<strong>01</strong>6437 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02778 FAA STC ST03336AT BOMBARDIER CL-600-2B19 Installs of Protective Covers for the 1K4XD,<br />
BOMBARDIER CL-600-2C10<br />
BOMBARDIER CL-600-2D15<br />
BOMBARDIER CL-600-2D24<br />
TCAS and HSTU Processor.<br />
10<strong>01</strong>6506 CHIPPEWA AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02870 FAA STC ST03573AT BOMBARDIER CL-600-2B19 Installs the electrical provisions for Goodrich<br />
BOMBARDIER CL-600-2C10<br />
BOMBARDIER CL-600-2D15<br />
BOMBARDIER CL-600-2D24<br />
8730A2 Class 2 Elect. Flt. Bag.<br />
06.09.2007<br />
31.05.2006<br />
03.07.2007<br />
07.<strong>04</strong>.2008<br />
N/A 29.05.2007<br />
N/A 29.05.2007<br />
N/A 22.02.2008<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.This modific<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 154/<strong>462</strong><br />
09.<strong>04</strong>.2008<br />
24.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10026871 CHIPPEWA AEROSPACE, Inc. P-<br />
FAA STC ST03280AT BAE 125-700<br />
Installation of a Honeywell Flitelink Engine None. 1. Prior to installation of this modification 19.08.2009<br />
<strong>EASA</strong>.IM.A.S.03213<br />
BAE 125-800<br />
Condition Trend Monitoring- Data Downloader<br />
the installer mustdetermine that the<br />
BAE 125-800A<br />
(ECTM-DD)<br />
interrelationship between this modification<br />
BAE 125-800B<br />
and anyother previously installed<br />
HAWKER 750<br />
modification will introduce no adverse<br />
HAWKER 800<br />
effectupon the airworthiness of the<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
product.2. The insta<br />
10026882 CHIPPEWA AEROSPACE, Inc. P-<br />
FAA STC ST03573AT CL-600-2B19, CL-600-2C10, Installation of a Goodrich Class 2 Electronic Restricted to Configuration 2 as defined in 1) Prior to installation of this modification 19.08.2009<br />
<strong>EASA</strong>.IM.A.S.03218<br />
CL-600-2D15, CL-600-2D24 Flight Bag<br />
Chippewa AerospaceCertification Plan No 6<strong>01</strong>- the installer mustdetermine that the<br />
<strong>462</strong>0-CP Rev D, dated 24 March 2009. The interrelationship between this modification<br />
applicant must submit the final EWIS ICA, if and anyother previously installed<br />
applicable, to theAgency by7 June 2<strong>01</strong>0 modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10031668 CHIPPEWA AEROSPACE, Inc. REV. 1 FAA STC SA03859AT LIBERTY XL-2 Garmin GTX 330 None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.11.2<strong>01</strong>0<br />
10032241 CHIPPEWA AEROSPACE, Inc. FAA STC SA03860AT LIBERTY XL-2 Honeywell KN-62A DME none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.11.2<strong>01</strong>0<br />
10<strong>04</strong>21<strong>01</strong> CHIPPEWA AEROSPACE, Inc. FAA STC ST026<strong>04</strong>AT DHC-8-102,-103,-106<br />
DHC-8-2<strong>01</strong>,-202<br />
DHC-8-3<strong>01</strong>,-311,-314,-315<br />
10<strong>04</strong>2660 CHIPPEWA AEROSPACE, Inc. FAA STC ST02<strong>04</strong>6AT DHC-8-102, DHC-8-103,<br />
DHC-8-106, DHC-8-2<strong>01</strong>,<br />
DHC-8-202, DHC-8-3<strong>01</strong>,<br />
DHC-8-311, DHC-8-314,<br />
DHC-8-315.<br />
Installation of a Honeywell MK VIII Enhanced<br />
Ground Proximity WarningSystem (EGPWS).<br />
Installation of a ground service busFAA STC<br />
ST02<strong>04</strong>6AT<br />
The aircraft must be equipped with the factory<br />
installed HoneywellGround Proximity Warning<br />
System (GPWS).<br />
Prior to installation of this modification it 08.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.12.2<strong>01</strong>2<br />
10<strong>01</strong>4984 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03276 CESSNA P210N Avionics RetrofitOut: King KMA-24; Sigtronics<br />
SPA-400; Dual King KY-196; Dual King KN-53;<br />
King KI-525A; trimble TNL-2000; King KT-76A;<br />
ARGUS-5000; BF Goodrich WX-1000In:<br />
Garmin GMA-347; Dual Garmin GNS-430;<br />
Garmin GTX-330; Garmin GMX-200; L-3 WX-<br />
500; Sande<br />
Reg: HB-CZK S/N: P21-00860 24.<strong>01</strong>.2008<br />
10<strong>01</strong>4987 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03280 CESSNA P210N Avionics Upgradeby removing:1. GPS-155 1. Reg.: HB-CHJ S/N: P210-0522. Valid for<br />
06.11.2007<br />
GPS2. KX-165 COM/NAV 13. KX-155 this S/N Only.2. Prior to installation of this<br />
COM/NAV 24. WX-8 Stormscope5. KMA- modification the installer must determine that<br />
24 Audio Paneland installing:1. GNS-530 the interrelationship between this modification<br />
COM/NAV/GPS 12. GNS-430<br />
and any other previously installed modification<br />
COM/NAV/GPS 23. WX-500 Stormscope4. will introduce n<br />
GMA-347 Audio Panel<br />
10<strong>01</strong>5066 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03392 BEECH C90KING AIR GNS 530A, GNS 430A, GAD 42<br />
installation:Removed equipment:- 2 KTR 905<br />
COM 1 & COM 2- 2 KNR 630 NAV 1 & NAV 2-<br />
1 KLN 90B GPS with AK-950 GPS<br />
Annunciator- 1 KDM 705A DME with KDI 570<br />
DME IndicatorNew installed equipment:- 1<br />
GNS 530AW COM/NAV/GPS 1 with GAD 4<br />
F-GBLU, SN: LJ-822. 10.09.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 155/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5129 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03480 CESSNA P210N Avionics upgradeBy removing:-NSD 360<br />
HISSA-832B Slaving BoxACK A-30 mod 8<br />
Altitude EncoderGMA-340 Audio PanelAnd<br />
installingSN-3500 E-HISSAC 7-35 Airdada<br />
ComputerKG-102A Remote GyroGMA-347<br />
Audio Panel<br />
Reg.: HB-CZB S/N: P-210-0780 05.03.2008<br />
10<strong>01</strong>5262 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03720 CESSNA 210 Avionics UpgradeBy removing the existing:- Prior to installation of this modification the<br />
11.12.2008<br />
COM/NAV 1 + 2- DME - Mode A/C<br />
installer must determine that the<br />
Transponder- Audio Panel And install the new interrelationship between this modification and<br />
Avionics Systems:- GNS 530W<br />
any other previously installed modification will<br />
COM/NAV/GPS 1- GNS 430W<br />
introduce no adverse effect upon the<br />
COM/NAV/GPS 2 with GI106A GPS/NAV<br />
Indicator- KN 62A DME - GTX 330 Mode S<br />
Transponderairworthiness<br />
of the product. The install<br />
10031914 CHRISTEN-AIRTECH AG TBM 700 A Avionics Upgrade Out: Dual COM-NAV Bendix- Reg.: D-FIRE,,S/N: 137 The approval holder shall fulfil the 21.09.2<strong>01</strong>0<br />
King KX-165A, GPS Apollo MNS21<strong>01</strong>, MFD<br />
obligations of Part 21,<br />
ApolloMX20, Encoder Shadin 8800-T In: COM-<br />
Paragraph21.A109. Prior to installation of<br />
NAV-GPS Garmin GNS-530W & 430W, MFD<br />
this modification it must be determined<br />
Garmin GMX-200, Encoder ACKA-30 Mod. 8<br />
thatthe interrelationship between this<br />
serial<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10036867 CHRISTEN-AIRTECH AG 414A Inst.Traffic alerting<br />
S/N: 414A-0233,,,,D-IMUB The approval holder shall fulfill the 13.10.2<strong>01</strong>1<br />
system/StormscopeRemoved:- NIL Installed:-<br />
obligations of Part 21, §21.A118A.Prior<br />
Garmin GTS800 Traffic Alerting System- L-3<br />
to installation of this modification it must<br />
WX500 Stormscope System<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will<br />
10<strong>01</strong>5968 CIRRUS DESIGN CORPORATION <strong>EASA</strong>.IM.A.S.02119 SA<strong>01</strong>355WI-D CIRRUS SR20 Validation of FAA STC SA<strong>01</strong>355WI-D –<br />
“Installation of Bendix/King KR87 ADF and/ or<br />
KN 62A DME”<br />
10<strong>01</strong>6118 CITATION TECH <strong>EASA</strong>.IM.A.S.02310 FAA STC ST<strong>01</strong>395WI CESSNA 500<br />
Installation of Dual Honeywell AM-250 Digital<br />
CESSNA 5<strong>01</strong><br />
Altimeter and Skylight Avionics Air Data<br />
CESSNA 550<br />
Interface Adapter ADC-602 AIU and<br />
CESSNA 551<br />
associatedequipment to obtain RVSM<br />
REIMS AVIATION CESSNA F 177 approval.<br />
RG<br />
10<strong>01</strong>6006 CLIPPER AVIATION, Inc. <strong>EASA</strong>.IM.A.S.02170 FAA STC ST02318NY BOEING 747-400 FREIGHTER Upper Deck seating arrangement for B747-<br />
400BCF as defined in Weber Aircraft<br />
installation drawing No. 860<strong>01</strong>4 and Clipper<br />
Aviation CLI-2006-003 Rev. A, Master Data<br />
List B747-400BCF<br />
10036123 CLIPPER AVIATION, Inc. FAA STC ST02318NY B747-400 Installation of seating configuration on Upper<br />
Deck of B747-400 Boeingconverted Special<br />
Freighter<br />
10<strong>01</strong>5822 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.<strong>01</strong>894 ST<strong>01</strong>128 BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200CT<br />
BEECH B200T<br />
BEECH B300<br />
BEECH B300C<br />
Installation of Honeywell MK-VIII Enhanced<br />
Ground Proximity Warning System (with or<br />
without optional EFIS-85B/14 Display).<br />
1. The installer must determine, if this design<br />
is compatible with previously approved<br />
modifications. If the holder agrees to permit<br />
another person to use this certification or alter<br />
a product, the holder must give the other<br />
person written evidence of t<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
15.05.2007<br />
<strong>04</strong>.07.2007<br />
<strong>04</strong>.<strong>04</strong>.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.08.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 156/<strong>462</strong><br />
28.09.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5860 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.<strong>01</strong>973 FAA STC SA<strong>01</strong>156WI CESSNA 5<strong>01</strong><br />
Installation of dual RVSM compliant IS&S or J2 1. Prior to installation of this modification the<br />
12.02.2009<br />
CESSNA 551<br />
(Kollsman) air data system.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6271 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.02555 FAA STC ST<strong>01</strong>149WI CESSNA 500<br />
Installation of IS&S or J2 (Kollsman) Air Data<br />
27.08.2007<br />
CESSNA 550<br />
Systemwith Reduced Vertical Separation<br />
CESSNA 560<br />
CESSNA S550<br />
Minimum (RVSM)<br />
10<strong>01</strong>6272 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.02557 FAA STC ST<strong>01</strong>252WI CESSNA 560<br />
Vertical Separation Minimum (RVSM) group 1. Prior to installation of this modification the<br />
27.08.2007<br />
CESSNA S550<br />
airworthiness approval of Cessna Modell S550 installer must determine that the<br />
and 560 Citation Aircraft<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
10<strong>01</strong>6320 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.02629 REV. 1 FAA STC ST<strong>01</strong>162WI CESSNA 500<br />
Vertical Separation Minimum (RVSM) group 1. Prior to installation of this modification the<br />
19.03.2009<br />
CESSNA 5<strong>01</strong><br />
airworthiness approval of Cessna Models 500, installer must determine that the<br />
CESSNA 550<br />
5<strong>01</strong>, 550 and 551 Citation Aircraft<br />
interrelationship between this modification and<br />
CESSNA 551<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6321 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.02630 FAA STC ST<strong>01</strong>084WI Installation of Collins TCAS-4000 TCAS II<br />
System (with or without optional Avidyne Flight<br />
Max 800 MFD.<br />
03.06.2008<br />
10<strong>01</strong>5895 COMMUTER AIR TECHNOLOGY <strong>EASA</strong>.IM.A.S.02<strong>01</strong>5 REV. 1 FAA STC SA0<strong>01</strong>84LA BEECH 200<br />
Installation of Alternate Main Landing Gear Prior to installation of this modification the<br />
10.02.2009<br />
BEECH 200C<br />
Tires, Michelin P/N 026-335-0.Revision 1 installer must determine that the<br />
BEECH 200CT<br />
issued to add models B200GT and B200CGT. interrelationship between this modification and<br />
BEECH 200T<br />
any other previously installed modification will<br />
BEECH A200<br />
introduce no adverse effect upon the<br />
BEECH A200C<br />
BEECH A200CT<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
airworthiness of the product.<br />
10<strong>01</strong>62<strong>04</strong> COMMUTER AIR TECHNOLOGY <strong>EASA</strong>.IM.A.S.02446 FAA STC SA10370SC RAYTHEON A36 Installation of exhaust gas extractors on Pratt & Note that the airspeed and shaft horsepower<br />
Whitney Canada PT6A-21, -27, -28, -29, -34, - limits listed in the original Airplane Flight<br />
21.05.2007<br />
34B, -135, or 135A turboprop engines. Manuals are still applicable (see TC DataSheet<br />
No. 3A20). Compatibility of this design change<br />
with previously approved modifications must be<br />
determined by the install<br />
10029892 COMPAGNIE FRANCE AVIATION P-<strong>EASA</strong>.A.S.03869 GARDAN GY80-160 Installation of Aspen Avionics EFD1000 PRO,<br />
1 Garmin GMA340, 1 GarminGNS 430 and 1<br />
Kannad 406MHZ AF Compact in the GARDAN<br />
GY-80 series.<br />
10033572 COMPAGNIE FRANCE AVIATION P-<strong>EASA</strong>.A.S.03031 R2160 FA 07/2007 Edition 1 - Installation malonnier<br />
sur R2160<br />
10<strong>01</strong>5540 COMTEK ADVANCED STRUCTURES<br />
Ltd.<br />
10034405 COMTRAN INTERNATIONAL, INC. P-<br />
<strong>EASA</strong>.IM.A.S.02963<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this and any<br />
other previously installedand/ or repair will<br />
introduce no adverse upon the<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>424 - DORNIER D328-100 Replacement of trolley stowage unit panels 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
FAA STC SA00664DE DORNIER 328-300 Cabin Interior Re-Configuration Domier 328-<br />
300<br />
10<strong>01</strong>5738 CONCORDE BATTERY CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>762 FAA STC ST00640LA HAWKER 1000 Installation of Cocorde Battery Model No RG-<br />
380E/60K sealed lead acid batteries<br />
10<strong>01</strong>6315 CONCORDE BATTERY CORPORATION <strong>EASA</strong>.IM.A.S.02620 FAA STC NO. ST<strong>01</strong>173WI LEARJET 45 Installation of Concorde RG-443 Lead Acid<br />
Battery.<br />
30.<strong>04</strong>.2<strong>01</strong>0<br />
Limited to S/N 154<br />
airworthiness of theproduct.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.07.2009<br />
18.07.2005<br />
None Prior to installation of this modification the 29.07.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
-- 06.<strong>04</strong>.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 157/<strong>462</strong><br />
05.02.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038867 CONCORDE BATTERY CORPORATION FAA STC 03930AT ATR 42-200 /-300 /-320 /-500 Installation of a Lead Acid BatteryThis STC None. Prior to installation of this modification it 20.03.2<strong>01</strong>2<br />
ATR 72-1<strong>01</strong> / -102<br />
installs a Lead Acid battery in replacement of<br />
must be determined thatthe<br />
ATR 72-2<strong>01</strong> / -202 / -211 the existingNickel-Cadmium battery.<br />
interrelationship between this modification<br />
ATR 72-212 / -212A<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0738 CONCORDE BATTERY CORPORATION FAA STC NO. SA<strong>01</strong>633WI EMB 500 Installation of Concorde RG-390E VRSLA<br />
Batteries in the Embraer 500 inaccordance<br />
with Concorde Battery Corporation Master<br />
Drawing List, DWGNo. 5-0359, Revision NC,<br />
dated August 25, 2<strong>01</strong>0 or later FAA<br />
approvedrevisions.<br />
10<strong>04</strong>0781 CONCORDE BATTERY CORPORATION FAA STC ST<strong>01</strong>643WI DHC-8-102, -103, -106<br />
DHC-8-2<strong>01</strong>, -202<br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
10<strong>04</strong>2099 CONCORDE BATTERY CORPORATION FAA STC SA<strong>01</strong>118WI SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of Concorde RG-380E/44 (42AH)<br />
or RG-380E/60L (48AH) SeriesValve<br />
Regulated Sealed Lead-Acid (VRSLA)<br />
batteries as replacement of OEMbatteries.FAA<br />
STC ST<strong>01</strong>643WI<br />
Installation of the Concorde FLA or VRSLA RG<br />
series batteries in CessnaSingle Engine<br />
Airplanes listed on the attached Approved<br />
Model List (AML)in accordance with Concorde<br />
Battery Corporation, Master Drawing ListDwg.<br />
No. 5-<strong>01</strong>48, Revision A, dated August 16,<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.07.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.07.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.11.2<strong>01</strong>2<br />
10<strong>01</strong>4097 CONTOUR AEROSPACE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>195 REV 1 BOEING 767-300 SERIES Introduction G3 Wardrobe to British Airways<br />
aircraft as defined in the modification definition<br />
document and Declaration of Design and<br />
Performance (DDP)<br />
As defined in the DDP. 20.05.2005<br />
10<strong>01</strong>6274 CORPORATION LOGIC AIR Inc. <strong>EASA</strong>.IM.A.S.02560 REV 1 TC STC C-LSA07-205/D ISSUE 2 BOEING 767-300 Installation of In-Flight Entertainment System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6283 CORPORATION LOGIC AIR Inc. <strong>EASA</strong>.IM.A.S.02578 TCCA SA07-210/D ISSUE 1 BOEING 767-300 Installation of 270 Pax Interior Configuration. 02.11.2007<br />
10<strong>01</strong>6284 CORPORATION LOGIC AIR Inc. <strong>EASA</strong>.IM.A.S.02579 REV 1 TCCA STC SA07-12 ISSUE 2 BOEING 767 Tire pressure Indication System De-activation,<br />
Boeing 767-300.<br />
10<strong>01</strong>6285 CORPORATION LOGIC AIR Inc. <strong>EASA</strong>.IM.A.S.02580 TCCA STC C-LSA07-091/D BOEING 767-300 installation of Mode S ATC Transponder with<br />
Elementary and Enhanced Surveillance Modes.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6290 CORPORATION LOGIC AIR Inc. <strong>EASA</strong>.IM.A.S.02585 C-LSA03-498/D BOEING 767-300 Changes to Altitude Callout Configuration,<br />
Honeywell Mark V EGPWS.<br />
02.11.2007<br />
10033973 CRANE AEROSPACE & ELECTRONICS FAA STC ST02316LA LEARJET 60 Installation of Tire Pressure Sensor FAA STC None Prior to installation of this modification it 23.02.2<strong>01</strong>1<br />
ST02316LA (Date of issuance: September 28,<br />
must be determined thatthe<br />
2<strong>01</strong>0)<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4384 CRANFIELD AEROSPACE LTD <strong>EASA</strong>.A.S.<strong>01</strong>669 Installation of a Honeywell Global GNS-XLS This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
20.02.2006<br />
10027822 CRANFIELD AEROSPACE LTD P-<strong>EASA</strong>.A.S.03734 BAE JETSTREAM 3100 Installation of Satcom System None None 09.11.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 158/<strong>462</strong><br />
10.<strong>04</strong>.2008<br />
07.08.2008<br />
02.11.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037359 CRANFIELD AEROSPACE LTD CESSNA 421C Installation of Initial Role Change Equipment in S/N 421C-0218. This STC requires installation of System 22.11.2<strong>01</strong>1<br />
a Civil ContingencyAircraft - Cessna 421C as<br />
and Structural provisions asdefined in<br />
defined in Cranfield Aerospace<br />
Cranfield Aerospace document<br />
documentCAeM/Cessna/1327.<br />
CAeM/Cessna/1326.<br />
10037360 CRANFIELD AEROSPACE LTD CESSNA 421C System and Structural Provisions for a Civil<br />
Contingency Aircraft -Cessna 421C as defined<br />
in Cranfield Aerospace document<br />
CAeM/Cessna/1326.<br />
S/N 421C-0218. None. 22.11.2<strong>01</strong>1<br />
10<strong>01</strong>4485 CTT SYSTEMS AB <strong>EASA</strong>.A.S.02547 REV. 2 CAA NL STC SA0009NL BOEING 767-300 Replacement of Zonal Dryer related to <strong>EASA</strong> Instruction for the installationInstallation<br />
14.<strong>04</strong>.2009<br />
AD 2006-<strong>01</strong>40-E.The above reference <strong>EASA</strong> instructions II767-2 and II767B-2, latest<br />
AD required the de-activation of Zonal Drying issue.KLM MO 21-<strong>04</strong>76 and Martinair MO<br />
Systems installed via CAA NL STC SA 0009 76730MP-003.Instructions for operationNo<br />
NL due to the potential for combustion of specific Airplane Flight Manual Supplement is<br />
contaminants in the dryer unit. A new dryer neededPrior to installation of this modifica<br />
10<strong>01</strong>5267 CTT SYSTEMS AB <strong>EASA</strong>.A.S.03738 CAA NL STC SA 0003 NL BOEING MD 11 Replacement of Zonal Dryer related to <strong>EASA</strong><br />
AD 2006-<strong>01</strong>40-E.The above reference <strong>EASA</strong><br />
AD required the de-activation of Zonal Drying<br />
Systems installed via CAA NL STC SA 0003<br />
NL due to the potential for combustion of<br />
contaminants in the dryer unit. A new dryer<br />
Instruction for the installation:Installation<br />
instruction IIMD11, latest revision, Swissair<br />
Engineering Order 51<strong>04</strong>40.Instructions for<br />
operation:Airplane Flight Manual Supplement,<br />
AFM-98-02, Rev. 0, dated 3-11-98 or<br />
latestrevision. Instructions for continue<br />
10<strong>01</strong>6071 CUB CRAFTERS INC. <strong>EASA</strong>.IM.A.S.02252 REV. 1 FAA STC SA00522SE PA-18-125, PA-18A, PA-18-135, Installation of Lycoming O-320-A2B, O-320- The compatibility of this modification with other<br />
11.12.2006<br />
PA-18A-135, PA-18-150, A2C, O-320-A2D, O-320-B2B, O-320-B2C, O- approved modifications has to be ensured by<br />
PA-18A-150<br />
320-D2A, O-320-D2B and O-320-D3G engines the company installing the modification.<br />
with Sensenich M74DM-52 through -56 or<br />
74DM6-0-52 through -56 propellers and<br />
assocaited hardware, i.a with FAA STC<br />
SA00522SE.<br />
Approved MTOM up to 794 kg.<br />
10<strong>04</strong>2813 CUSTOM FIBERGLASS MOLDING INC. FAA STC SA02391CH BEE DEE M-4, M-4<br />
Installation of Custom Fiberglass Molding Skis, Installer must check availability of <strong>EASA</strong>- The installation of this modification by 19.12.2<strong>01</strong>2<br />
M-4-210, M-4-210C<br />
Model 3000, according toMaster Drawing List approval for one or morereferenced STC when third persons is subject towritten<br />
M-4-220, M-4-220C<br />
CFMI 3000-9, Rev D dated <strong>04</strong>th April 2<strong>01</strong>1 or airplane is modified per that / those STC(s). permission of the approval holder and<br />
M-4-220S, M-4-180V<br />
laterFAA approved revision.Installation of<br />
disposal of the approvedappropriate<br />
M-4C, M-4S, M-4T<br />
Custom Fiberglass Molding Skis, Model 3000-<br />
documentation. Prior to installation of this<br />
M-5-235C, M-5-180C, M-6-235 <strong>01</strong>(A/B),according to Master Drawin<br />
modification it must be determined<br />
M-7-235, M-7-235B<br />
MX-7-160, MX-7-180<br />
MX-7-180A, MX-7-235<br />
MX-7-180B, MX-7-180C<br />
thatthe interrelationship<br />
10<strong>01</strong>4718 CZECH AIRLINES TECHNICS A.S. <strong>EASA</strong>.A.S.02895 AIRBUS A320-214 Cabin layout modification from 156 pax to 162<br />
pax with seat type change /Removal of the<br />
existing seats for 156 passengers and<br />
doghouses, installation of new seats for 162<br />
passengers, new doghouses, relocation and<br />
addition of PSU’s as required, installation<br />
19.03.2007<br />
10037313 DAHER SOCATA A/S REV. 1 AS 355 F2 Modification STC.34.0<strong>01</strong>.11Version A for VFR - Version A limited to VFR onlyVersion B: for<br />
Installation of GNS 430W for<br />
IFR-operation refer also to AS355 F2 RFM<br />
VHF1/NAV1/ILS1/GPS1,AN/ARC 210 for<br />
VHF2, BXP64<strong>01</strong> for XPDR Mode S, Sky<br />
Connect for IridiumSat Phone, Motorola<br />
DM3600 for UHF FMVersion B for IFR -<br />
Installation of GNS 430W for VHF1/N<br />
Supplement 11.4"IFR Flight".<br />
10026805 DANSK FLY ELEKTRONIK ApS P-<strong>EASA</strong>.A.S.03944 BEECH 1900D Installation of Skytrac ISAT-100 GPS/Iridium<br />
communicator system<br />
10027379 DANSK FLY ELEKTRONIK ApS P-<strong>EASA</strong>.A.S.03915 PIPER PA-28-140<br />
PIPER PA-28-150<br />
PIPER PA-28-151<br />
PIPER PA-28-160<br />
PIPER PA-28-161<br />
PIPER PA-28-180<br />
PIPER PA-28-181<br />
PIPER PA-28-235<br />
PIPER PA-28-236<br />
PIPER PA-28R-180<br />
PIPER PA-28R-200<br />
PIPER PA-28R-2<strong>01</strong><br />
PIPER PA-28R-2<strong>01</strong>T<br />
PIPER PA-28RT-2<strong>01</strong><br />
PIPER PA-28RT-2<strong>01</strong>T<br />
PIPER PA-28S-160<br />
PIPER PA-28S-180<br />
Installation of ASPEN EFD1000 PRO Flight<br />
display<br />
Serial numbers 5026, 5299, 5298 and<br />
5156 only. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse effe<br />
15.12.2008<br />
21.09.2<strong>01</strong>2<br />
None None 11.08.2009<br />
None - Prior to installation of this modification<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.- The install<br />
25.09.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 159/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027985 DANSK FLY ELEKTRONIK ApS F172D, F172E, F172F, F172H, ASPEN EFD1000 Installation Not Applicable Prior to installation of this modification it 23.11.2009<br />
F172K, F172L, F172M, F172N,<br />
must be determined thatthe<br />
F172P<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031092 DANSK FLY ELEKTRONIK ApS PA-42, PA-42-720, PA-42-1000 Installation of Avidyne EX500 MFD None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.07.2<strong>01</strong>0<br />
10031093 DANSK FLY ELEKTRONIK ApS PA-42, PA-42-720, PA-42-1000 Installation of one or two Garmin GTX 330D<br />
Mode-S transponder<br />
10031129 DANSK FLY ELEKTRONIK ApS P-<strong>EASA</strong>.A.S.03981 PA-42, PA-42-1000, PA-42-720 Installation of dual Garmin GNS 430AW, dual<br />
Garmin GNS 530AW or GarminGNS 430AW<br />
and GNS 530AW<br />
100314<strong>04</strong> DANSK FLY ELEKTRONIK ApS B200, B200C Installation of L-3 Skywatch HP Traffic Alert &<br />
Collision AvoidanceSystem, Model SKY899A.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.07.2<strong>01</strong>0<br />
For PA-42 with Bendix King EFIS only Prior to installation of this modification the 28.07.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
Garmin G1000 retrofit STC must be installed in<br />
aircraft prior toinstalling this STC.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034209 DANSK FLY ELEKTRONIK ApS B200 KING AIR Installation of Garmin DUAL GPS 400. GPS# 1 None Prior to installation of this modification it 16.03.2<strong>01</strong>1<br />
is linked to the autopilotsystem. Ref. DFE-DO-<br />
must be determined thatthe<br />
<strong>04</strong><strong>01</strong>-PS-00 Product Specification.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034210 DANSK FLY ELEKTRONIK ApS B200 KING AIR Installation of Bendix/Kings KGP 560 EGPWS None Prior to installation of this modification it 16.03.2<strong>01</strong>1<br />
system with Avidyne EX500display. Ref. DFE-<br />
must be determined thatthe<br />
DO-<strong>04</strong>00-PS-00 Product Specification.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035243 DANSK FLY ELEKTRONIK ApS CESSNA 414, 414A Installation of Garmin GTX330D Transponder None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.06.2<strong>01</strong>1<br />
10<strong>01</strong>4207 DAO AVIATION A/S <strong>EASA</strong>.A.S.<strong>01</strong>358 PIPER PA-24<br />
PIPER PA-24-250<br />
PIPER PA-24-260<br />
PIPER PA-24-400<br />
Installation of Garmin GNS 430<br />
COM/NAV/GPS. Approval for B-RNAV, en<br />
route IFR and Terminal flights<br />
10<strong>01</strong>4324 DAO AVIATION A/S <strong>EASA</strong>.A.S.<strong>01</strong>577 BEECH 200, SUPER KING AIR Installation of Honeywell ACAS II system<br />
comprising CAS 67A processor, 2 IVA-81D<br />
VSIs and 2 ANT-67A antennas.<br />
13.08.2<strong>01</strong>0<br />
29.06.2005<br />
MSN BB-309 only. 27.10.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 160/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4518 DAO AVIATION A/S <strong>EASA</strong>.A.S.02596 Avionics upgrade with following equipment<br />
(DFE-DO-0075-EPL-<strong>01</strong> Equipment and Parts<br />
List.(Rev. 1)1 GMA 347 Audiopanel<br />
Garmin 1 GNS<br />
13.07.2006<br />
10<strong>01</strong>6712 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.00710 REV. 1 TCCA STC SH<strong>04</strong>-7 BELL 205A<br />
530 COM/ NAV/ GPS Garmin<br />
1 GNS<br />
Installation of D412-702 Shoulder Harness Kits. Prior to installation of this modification the<br />
09.08.2007<br />
BELL 205A-1<br />
Transport Canada STC No SH<strong>04</strong>-7 issue 1 installer must determine that the<br />
BELL 205B<br />
dated 6th February 20<strong>04</strong>. The purpose of these interrelationship between this modification and<br />
BELL 212<br />
kits is to add shoulder harnesses to existing any other previously installed modification will<br />
BELL 214B<br />
seats that are only equipped with lap belts. introduce no adverse effect upon the<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 EP<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6723 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>021 SH<strong>04</strong>-31 BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
Installation of Replacement Window Kits 02.<strong>01</strong>.2006<br />
10<strong>01</strong>6748 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>074 TCCA STC SH<strong>04</strong>-30, ISSUE 2 ROBINSON R22 ALPHA Validation of TCCA STC SH<strong>04</strong>-30 for the 1. Installation and Maintenance in accordance<br />
14.06.2005<br />
ROBINSON R22 BETA<br />
installation of Cabin Floor Protectors. with the above referenced Technical<br />
Documentation.2. This STC is approved only<br />
for the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
10<strong>01</strong>6749 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>075 TCCA STC SH<strong>04</strong>-40, ISSUE 1 ROBINSON R44<br />
ROBINSON R44 II<br />
10<strong>01</strong>6750 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>076 TCCA STC SH05-7, ISSUE 1 ROBINSON R44<br />
ROBINSON R44 II<br />
10<strong>01</strong>6756 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>085 SH05-10, ISSUE 1 BELL 205B<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
10<strong>01</strong>6757 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>086 SH94-38, ISSUE 2 SIKORSKY S-76A<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6758 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>087 TCCA STC SH05-14 ROBINSON R22 ALPHA<br />
ROBINSON R22 BETA<br />
10<strong>01</strong>6759 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>088 TCCA STC SH05-13 ROBINSON R44<br />
ROBINSON R44 II<br />
10<strong>01</strong>6814 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>179 TCCA STC SH<strong>01</strong>-5 ISSUE 2 BELL 206A<br />
BELL 206L<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
BELL 407<br />
Validation of TCCA STC SH<strong>04</strong>-40 for the<br />
installation of Cabin Floor Protectors.<br />
Validation of TCCA STC SH05-7 for the<br />
Installation of a Cold Weather Baffle Kit for<br />
Cold Weather operation of Robinson R44 and<br />
R44II.<br />
1. Installation must be performed in<br />
accordance with Installation Instructions IIN-<br />
D<strong>04</strong>4-719.2. Maintenance in accordance with<br />
Instructions for Continued Airworthiness ICA-<br />
D<strong>04</strong>4-719.3. This STC is approved only for the<br />
product configuration as defined in the<br />
1. Installation must be performed in<br />
accordance with Installation Instructions IIN-<br />
D<strong>04</strong>4-717.2. Maintenance in accordance with<br />
Instructions for Continued Airworthiness ICA-<br />
D<strong>04</strong>4-717.3. This STC is approved only for the<br />
product configuration as defined in the<br />
14.06.2005<br />
14.06.2005<br />
Spacedoor Installation 02.<strong>01</strong>.2006<br />
Installation of Cargo Mirrors 25.<strong>01</strong>.2006<br />
Installation of Replacement Window Kits in<br />
accordance with TCCA STC SH05-14.<br />
Installation of Replacement Window Kit in<br />
accordance with TCCA STC SH05-13.<br />
1. Installation, Operation and Maintenance<br />
must be held in accordance with the above<br />
referenced Technical Documentation. 2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Descrip<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Landing Gear Crosstubes This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 161/<strong>462</strong><br />
14.06.2005<br />
13.06.2005<br />
03.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6815 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>180 SH<strong>04</strong>-54 ISSUE1 BELL 2<strong>04</strong>B<br />
BELL 205A<br />
BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
Installation of Fuel Purge Canister 26.<strong>04</strong>.2007<br />
10<strong>01</strong>6816 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>181 SH05-11 BELL 2<strong>04</strong>B<br />
BELL 205A<br />
BELL 205A-1<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 EP<br />
D212-722 Avionics Console None 30.06.2006<br />
10<strong>01</strong>6822 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>187 SH05-44 BELL 206A<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
BELL 407<br />
D206/407-728 Skid tube wear plates. 09.10.2007<br />
10<strong>01</strong>6828 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>198 SH03-6 BELL 2<strong>04</strong>B<br />
D205-594 Extended height landing GearTCCA Maintenance of the Extended Height Landing<br />
03.10.2006<br />
BELL 205A<br />
STC SH03-6<br />
Gear must be in accordance with Dart<br />
BELL 205A-1<br />
Aerospace Ltd. ICA-D205-594, Revision 2,<br />
BELL 212<br />
dated 18 July 2005, or later approved<br />
BELL 214B<br />
revisions.Operation of the Bell 214B and 214B-<br />
BELL 214B-1<br />
1 model types with the Extended Height<br />
Landing Gear<br />
10<strong>01</strong>6833 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>2<strong>04</strong> SH96-69 BELL 205A<br />
Installation of Heli Access Steps i.a.w.<br />
02.06.2006<br />
BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 EP<br />
Transport Canada STC SH96-69, issue 7<br />
10<strong>01</strong>6866 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>242 TCCA STC SH96-120 BELL 2<strong>04</strong><br />
D205-541 Heli-Utility Basket in accordance 1. VFR Only;2. Doors to be closed at all<br />
29.09.2006<br />
BELL 205A<br />
with Transport Canada STC SH96-120, Issue times during flight;3. Maximum Load 136 kg<br />
BELL 205A-1<br />
3, dated May 16, 2006<br />
(300 lb) or 100kg (220lb) if middle support is<br />
BELL 205B<br />
not installed;4. This STC is approved only for<br />
BELL 212<br />
the product configuration as defined in the<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
approved design data r<br />
10<strong>01</strong>6876 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>253 TCCA STC SH<strong>04</strong>-17 ROBINSON R44 Installation of D<strong>04</strong>4-715 Cargo Mirrors i.a: with None<br />
TCCA STC SH<strong>04</strong>-17<br />
11.12.2006<br />
10<strong>01</strong>6877 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>254 TCCA STC SH<strong>04</strong>-12 ROBINSON R22 ALPHA Installation of D022-716 Cargo Mirrors i.a. with<br />
12.12.2006<br />
ROBINSON R22 BETA<br />
TCCA STC SH<strong>04</strong>-12<br />
10<strong>01</strong>69<strong>01</strong> DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>278 REV. 1 EUROCOPTER DEUTSCHLAND D135-751 Skidtube and Skidtube Extension<br />
10.12.2008<br />
EC-135-<br />
Installation iaw FAA STC SR<strong>01</strong>709SE.<br />
10<strong>01</strong>6903 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>280 REV. 2 TCCA STC SH06-27 AS350B, AS350B1, AS350B2 Cross Tube Installation in accordance with None Prior to installation of this modification it 03.09.2<strong>01</strong>0<br />
AS350B3, AS350BA, AS350D Transport Canada STC SH06-27,Issue 1,<br />
must be determined thatthe<br />
AS355E, AS355N, AS355NP dated 16 August 2006.<br />
interrelationship between this modification<br />
AS355F, AS355F1, AS355F2<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6908 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>289 REV. 1 TCCA STC SH06-39 ISSUE 2 AGUSTA A119, AW119 MKII TCA STC No. SH06-39 Issue 2 - "Heli-Utility<br />
Basket Installation" - Thisinstallation consists in<br />
a box, fixed to the landing gear, for<br />
goodstransportation.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.02.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 162/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6909 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>290 TCCA STC SH93-97 EUROCOPTER FRANCE AS 350 D350-602 Helicopter Utility Pod – Validation of Prior to installation of this modification the<br />
02.06.2008<br />
B<br />
Transport Canada STC SH93-97.<br />
installer must determine that the<br />
EUROCOPTER FRANCE AS 350<br />
interrelationship between this modification and<br />
B1<br />
any other previously installed modification will<br />
EUROCOPTER FRANCE AS 350<br />
introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
airworthiness of the product.AS355 helico<br />
10<strong>01</strong>6911 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>292 REV. 1 TCCA STC SH93-88 EUROCOPTER FRANCE AS 350 Spacepod Installations(Validation of Canadian<br />
09.<strong>04</strong>.2008<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
STC Number SH93-88)<br />
10<strong>01</strong>6918 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>303 TCCA STC SH96-88 BELL 2<strong>04</strong>B<br />
Skidtube Installation 1. Operation of the Bell 214B and 214B-1<br />
27.06.2007<br />
BELL 205A<br />
model types with Dart D205-634-<strong>01</strong>1 skidtubes<br />
BELL 205A-1<br />
and the required Dart D212-664-1<strong>01</strong>/2<strong>01</strong><br />
BELL 205B<br />
Crosstube installation as incorporated by<br />
BELL 212<br />
<strong>EASA</strong> STC No. IM.R.S.<strong>01</strong>3<strong>04</strong> (Canadian STC<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 EP<br />
SH<strong>01</strong>-9) is limited to a maximum take off and l<br />
10<strong>01</strong>6919 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>3<strong>04</strong> TCCA STC SH<strong>01</strong>-9 BELL 2<strong>04</strong>B<br />
Cross Tube Installation in accordance with Bell 214B and 214B-1 models onlyOperation of<br />
06.03.2007<br />
BELL 205A<br />
Transport Canada STC SH<strong>01</strong>-9, Issue 3, dated the Bell 214B and 214B-1 model types with the<br />
BELL 205A-1<br />
8 June 2005. Revision to LBA STC RC 1181 cross tube installation is limited to a maximum<br />
BELL 205B<br />
dated 15 January 2002<br />
take off and landing weight of 5403 kg (11,900<br />
BELL 212<br />
lbs). Longitudinal centre of gravity limits have<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
changed accordingly a<br />
10<strong>01</strong>6942 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>335 TCCA STC SH02-8; ROBINSON R44<br />
D<strong>04</strong>4-662 Bearpaws.Revision to DGAC STC This STC is approved only for the product<br />
31.05.2007<br />
ROBINSON R44 II<br />
IM225-SI-0026, DGAC approved 30/<strong>04</strong>/2003, configuration as defined in the approved design<br />
with addition of R44II aircraft model and larger data referred to in the paragraphs "Description"<br />
Bearpaw Kits.<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>6962 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>361 TCCA STC SH07-37 BELL 205A<br />
BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
D412-760 Cabin Floor Protectors. 06.09.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 163/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6984 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>389 REV. 1 TCCA STC SH93-4 SEE <strong>EASA</strong> APPROVED MODEL Bearpaw Installation none Prior to installation of this modification it 22.09.2<strong>01</strong>0<br />
LIST<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6991 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>398 TCCA STC SH92-20, ISSUE 2; FAA BELL 2<strong>04</strong>B<br />
BELL 205A<br />
BELL 205A-1<br />
10<strong>01</strong>6996 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>405 REV. 2 TCCA STC SH94-14 1. AS350B/B1/B2/B3/BA/D/D1<br />
1. EC130B4<br />
2. AS355E/F/F1/F2/N/NP<br />
D2<strong>04</strong>-575/D205-576 Cabin Heating Systems,<br />
Transport Canada STC SH92-20 Issue 2 dated<br />
14 May 1992<br />
D350-607, D130-7<strong>01</strong> Basket InstallationsThis<br />
revision adds the models AS355N and NP.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
03.09.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.<strong>01</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>7030 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>449 REV. 1 TC STC SH05-45 BELL 206A<br />
BELL 206B<br />
D206-746 Shroud Air Flow Heater System. 16.<strong>04</strong>.2008<br />
10<strong>01</strong>7031 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>451 TCCA STC SH99-221 ISSUE 1 EUROCOPTER FRANCE EC 120 D120 -638 Bearpaw Installation. 1. Prior to installation of this modification the<br />
13.08.2008<br />
B<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7032 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>452 TCCA STC SH<strong>01</strong>-25 ISSUE 1 EUROCOPTER FRANCE EC 120 D120 -639 Wearplate Installation. 1. Prior to installation of this modification the<br />
13.08.2008<br />
B<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7033 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>456 TCCA STC SH08-5 EUROCOPTER FRANCE AS 350 D350-766 interior Trim Kit Installations<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
EUROCOPTER FRANCE AS<br />
355NP<br />
30.<strong>04</strong>.2008<br />
10<strong>01</strong>7059 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>492 REV. 1 TCCA STC SH08-40 BELL 212<br />
Replacement Glareshield Installation. Prior to installation of this modification the<br />
<strong>04</strong>.05.2009<br />
BELL 412<br />
installer must determine that the<br />
BELL 412 EP<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2. The in<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 164/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7074 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>516 REV. 1 TCCA STC SH91-20 AS350 AS350B1, AS350B2 D350-561 Cargo Mirror installations. none Prior to installation of this modification the 03.09.2<strong>01</strong>0<br />
AS350B3, AS350BA , AS350C<br />
installer must determinethat the<br />
AS350D, AS350D1<br />
interrelationship between this modification<br />
AS355E, AS355F, AS355F1<br />
and any otherpreviously installed<br />
AS355F2, AS355N, AS355NP<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>7075 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>518 TC STC SH08-37 ISSUE 1 BELL 205A-1<br />
D205-778 Comfort Seat Installation Prior to installation of this modification the<br />
09.<strong>01</strong>.2009<br />
BELL 205B<br />
installer must determine that the<br />
BELL 212<br />
interrelationship between this modification and<br />
BELL 214B<br />
any other previously installed modification<br />
BELL 214B-1<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.The<br />
10<strong>01</strong>7077 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>526 REV. 2 TCCA STC SH92-16 1. 2<strong>04</strong>B, 205A-1<br />
D212-580 Cargo Mirror/LED Pulse Light None Prior to installation of this modification the 26.11.2<strong>01</strong>0<br />
2. 212, 412, 412EP<br />
InstallationThis revision adds the LED Pulse<br />
installer must determinethat the<br />
3. 214B, 214B-1<br />
light installation to the CargoMirrors.<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10<strong>01</strong>7078 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>528 TCCA STC SH08-08 BELL 205A<br />
Replacement Engine Mount Installation (kit Prior to installation of this modification the<br />
26.02.2009<br />
BELL 205A-1<br />
205-770)<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7079 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>529 TCCA STC SH08-53 AGUSTA AB-412<br />
Procedure Trim Installations (kit D412-775). Prior to installation of this modification the<br />
25.02.2009<br />
AGUSTA AB-412EP<br />
installer must determine that the<br />
BELL 2<strong>04</strong>B<br />
interrelationship between this modification and<br />
BELL 205A-1<br />
any other previously installed modification<br />
BELL 205B<br />
will introduce no adverse effect upon the<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 EP<br />
airworthiness of the product.<br />
10027063 DART AEROSPACE Ltd. P-<br />
REV. 1 TCCA STC SH08-38 205A-1, 205B, 212,<br />
SH08-38 Issue 1 "D412-769 Aft Facing Seat For Instructions for Continued Airworthiness Prior to installation of this modification the 05.11.2009<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>493<br />
412, 412EP<br />
Installation"<br />
see Report ICA-D412-769Rev. 0 dated 24 installer must determinethat the<br />
June 2008.<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10028823 DART AEROSPACE Ltd. P-<br />
TCCA STC SH09-16 EC130B4 Traffic Advisory System Installation. None. Prior to installation of this modification it 12.02.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>554<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028917 DART AEROSPACE Ltd. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>556<br />
10029207 DART AEROSPACE Ltd. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>485<br />
TCCA STC SH09-<strong>04</strong> BELL 2<strong>04</strong>B, 205A-1,<br />
BELL 212, 214B, 214B-1,<br />
BELL 412, 412EP<br />
"Full Vertical Reference Door for Left Hand<br />
Vertical ReferenceOperations"<br />
Full compliance has not been demonstrated for<br />
airworthiness standards29.1303(g)(h)(i)(j),<br />
29.1321(b) and 29.1523(b) for single<br />
pilotoperation from the Left Seat resulting in a<br />
Restricted Categoryclassification. When<br />
conducting vertical reference work from<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
TCCA STC SH99-11 ISSUE 5 2<strong>04</strong>B, 205A-1 "Adjustable Engine Mount Kit" None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 165/<strong>462</strong><br />
10.03.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029712 DART AEROSPACE Ltd. P-<br />
TCCA STC SH07-36 A119 & AW119 MKII TCA STC SH07-36 Issue 2 "Replacement Not Applicable Prior to installation of this modification it 15.<strong>04</strong>.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>380<br />
Windows Kit" - D119-755-<strong>01</strong>1/-14 -This STC<br />
must be determined thatthe<br />
involves removing of the existing window and<br />
interrelationship between this modification<br />
installing a flatwindow (-<strong>01</strong>1) in LH or RH crew<br />
and any other previouslyinstalled<br />
door or installing a bubble window (-14)in the<br />
modification and/or repair will introduce<br />
RH crew door)<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031514 DART AEROSPACE Ltd. TCCA STC SH05-4 AS350 B, B1, B2, B3, BA, D Installation of an Auxiliary Side Locker Fuel<br />
Tank.<br />
10032253 DART AEROSPACE Ltd. TCCA STC SH09-37 ISSUE 1 1. 214B, 214B-1<br />
2. 212, 412, 412 EP<br />
3. 2<strong>04</strong>B, 205A-1<br />
10033253 DART AEROSPACE Ltd. TCCA STC SH10-44 206, A, A1, B, B1<br />
L, L1, L3, L4, 407<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
20.08.2<strong>01</strong>0<br />
D412-791 Safety Enhancement kits None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.11.2<strong>01</strong>0<br />
Automatic Door Opener Kits (Cabin and<br />
Baggage Doors).<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
07.<strong>01</strong>.2<strong>01</strong>1<br />
10034340 DART AEROSPACE Ltd. TCCA STC SH10-49 429 Installation of UltraPaws. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.03.2<strong>01</strong>1<br />
10034634 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>560 TCCA STC SH92-18 AS350B, BA, B1, B2, B3, D, D1 D350-567 Vertical Reference Window<br />
Installations. Addition of AS350Dl tolist of<br />
models.This STC revises and supersedes<br />
DGAC France STC 84-5[1103, dated<br />
27September 2002.<br />
None Prior to installation of this modification the 17.07.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10034636 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>561 TCCA STC SH92-18 AS355E, F, F1, F2, N, NP D350-567 Vertical Reference Window None Prior to installation of this modification the 31.07.2009<br />
Installations.This STC is a revision of and<br />
installer must determinethat the<br />
supersedes DGAC-F STC 168-5111<strong>04</strong> dated<br />
interrelationship between this modification<br />
27September 2002 for addition of AS355N and<br />
and any otherpreviously installed<br />
NP to list of models.<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10034637 DART AEROSPACE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>453 TCCA STC SH02-33 1. AS350 D, B, B1, B2, BA, B3<br />
1. (OP-3369 OPTION<br />
EXCLUDED)<br />
2. AS355 E, F, F1, F2, N<br />
10035429 DART AEROSPACE Ltd. REV. 2 TCCA STC SH11-1 206L, 206L-1, 206L-3, 206L-4<br />
407<br />
Installation of Dual High Back Seat, Left<br />
Forward Position (Modificationapproved by<br />
TCCA under STC SH02-33 issue 1)<br />
D407-797 Heli Utility Basket and Heli Access<br />
Step Installation, Revisionto STC 10035429 to<br />
add D407-797-311 Heli Access Step.<br />
None Prior to installation of this modification the 03.06.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.11.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 166/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039<strong>04</strong>2 DART AEROSPACE Ltd. REV. 1 206 A/B/L/L1/L3/L4 Screw In Windshield Modification. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.<strong>04</strong>.2<strong>01</strong>2<br />
10<strong>04</strong>2362 DART AEROSPACE Ltd. DGAC STC 168-<br />
SI0994<br />
REV. 1 TCCA SH 90-4 ISSUE 4 AS355E, AS355F, AS355F1,<br />
AS355F2, AS355N, AS355NP.<br />
10<strong>01</strong>6785 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>126 FAA STC SR<strong>01</strong>583SE AGUSTA AB-412<br />
AGUSTA AB-412EP<br />
BELL 205A<br />
BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
10<strong>01</strong>6934 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>320 REV. 1 FAA STC SA0<strong>04</strong>75SE BELL 206<br />
BELL 206A<br />
BELL 206B<br />
BELL 206L<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
BELL 407<br />
10<strong>01</strong>6945 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>339 TCCA STC SH98-14 BELL 206A<br />
BELL 206B<br />
BELL 206L<br />
BELL 407<br />
10<strong>01</strong>70<strong>01</strong> DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>412 FAA STC SR00211SE EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
350B<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
Installation of rear locker extender as defined in<br />
Dart Aerospace LtdMaster Document List No.<br />
MDL-D350-6<strong>04</strong> Rev. C.Note 1.This approval<br />
amends DGAC STC 168-SI0994 to add the<br />
AS355N and AS355NPaircraft models.Note<br />
2.This STC is the validation of TCCA STC SH9<br />
Installation of DART D412-742 Float Skidtubes<br />
(FAA STC SR<strong>01</strong>583SE issued on 29 July<br />
2005)<br />
Replacement of the original landing gear skid<br />
tubes and saddles with DART Aerospace<br />
Model D206-642 skid tubes and saddles. This<br />
TV modifies STC <strong>EASA</strong>.IM.R.S.<strong>01</strong>320<br />
D206-628 Heli Access Steps. This STC has<br />
been classified as “BASIC” by the FAA and is<br />
approved under the Type Validation Principles.<br />
D350-764 Shoulder Harness Kits. This STC<br />
has been classified as "BASIC" by the FAA and<br />
has been approved under the PTVP.<br />
10<strong>01</strong>7034 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>458 FAA STC SR00948SE<br />
355N<br />
AGUSTA A-119<br />
FAA STC SR00948SE “D119-675 Heli-Access-<br />
AGUSTA AW-119 MKII<br />
Step”.<br />
10<strong>01</strong>7<strong>04</strong>5 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>469 REV. 1 FAA STC SR00910SE EUROCOPTER CANADA BO-105 D105-674 Skidtube Installation i.a. with FAA<br />
LS A-<br />
EUROCOPTER DEUTSCHLAND<br />
BO-105<br />
STC SR00910SE<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.11.2<strong>01</strong>2<br />
Installation Insttruction IIN-D412-742 Rev. B<br />
dated 3 October 2005 or later approved<br />
document.This approval should not be<br />
extended to other rotorcraft of this model on<br />
which other previously approved modifications<br />
are incorporated unless it is determined b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 167/<strong>462</strong><br />
12.05.2006<br />
10.09.2007<br />
26.07.2007<br />
05.03.2008<br />
18.<strong>04</strong>.2008<br />
07.<strong>01</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7052 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>477 FAA STC SR00914SE EUROCOPTER FRANCE SA Installation of DART Bearpaws P/N D315-670- 1. Prior to installation of this modification the<br />
06.02.2009<br />
315B<br />
<strong>01</strong>1 - Validation of FAA STC SR00914SE. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7053 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>478 FAA STC SR00848SE EUROCOPTER FRANCE SA Installation of Dart Aerospace Skidtube P/N 1. Prior to installation of this modification the<br />
06.02.2009<br />
315B<br />
D315-668-<strong>01</strong>1 (LH) and -<strong>01</strong>2 (RH). Validation installer must determine that the<br />
of FAA STC SR00848SE.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7063 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>499 FAA STC SR<strong>01</strong>853SE EUROCOPTER DEUTSCHLAND 117-762 Skitube Installation in accordance with Prior to installation of this modification the<br />
10.11.2008<br />
MBB-BK<br />
FAA STC SR<strong>01</strong>853SE.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7084 DART AEROSPACE USA, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>551 FAA STC SR<strong>01</strong><strong>04</strong>3SE AGUSTA A119 Cargo Mirror Installation.Note: This STC<br />
supersedes ENAC STC N-CS-<strong>01</strong>4 being the<br />
validation of FAA STC SR<strong>01</strong><strong>04</strong>3SE dated 25<br />
January 2002.<br />
10029107 DART AEROSPACE USA, Inc. N-CS-022 FAA STC SR00949SE A119, AW119MKII FAA STC SR00949SE dated 21 August 2008<br />
"Bearpaw Installation"<br />
10033942 DART AEROSPACE USA, Inc. CAA UK 28081 AND<br />
28082<br />
FAA STC SR00646SE 1. AS350 B, AS350 B1, AS350 B2 D350-636 Skidtube Installations Note: This<br />
1. AS350 B3, AS350 BA, AS350 D STC supersedes CAA Approval Notes 28081<br />
2. AS355 E, AS355 F, AS355 F1 and 28082 and addsmodels AS355N and NP<br />
2. AS355 F2, AS355 N, AS355 NP to applicability.<br />
10038103 DART AEROSPACE USA, Inc. REV. 1 FAA STC SR<strong>01</strong><strong>04</strong>2SE EC135 P1(CDS)<br />
EC135 P1(CPDS)<br />
EC135 P2(CPDS), EC135 P2+<br />
EC135 T1(CDS), EC135<br />
T1(CPDS)<br />
EC135 T2(CPDS), EC135 T2+<br />
Dart D135-692-<strong>01</strong>1 Bearpaws in accordance<br />
with Dart Aerospace DrawingList No. MDL-<br />
D135-692, and installation of this system.This<br />
<strong>EASA</strong> STC is based on validation of FAA STC<br />
SR<strong>01</strong><strong>04</strong>2SE iaw the PTVP.<br />
10038656 DART AEROSPACE USA, Inc. REV. 1 FAA STC SR02138SE AW139 <strong>EASA</strong> Validation of FAA STC SR02138SE<br />
"Installation of Dart D139-799Maintenance<br />
Kits".<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
11.05.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.03.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.02.2<strong>01</strong>1<br />
Approval of this change in type design applies<br />
only to Eurocopter EC135rotorcraft, which are<br />
equipped with standard skidtubes, high<br />
gearskidtubes, or float skidtubes as defined in<br />
the installationinstructions.<br />
Prior to installation of this modification it 27.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.03.2<strong>01</strong>2<br />
10<strong>04</strong>0294 DART AEROSPACE USA, Inc. REV. 1 FAA STC SR02024SE A119, AW119MKII Validation of FAA STC SR02024SE: D119-646 None Prior to installation of this modification it 06.07.2<strong>01</strong>2<br />
Replacement Sikdtube Ins.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1447 DASSAULT AIRCRAFT SERVICES (DAS) FAA STC ST02964NY-D MF50 Installation of Crane Eldec "SmartStem" Tire<br />
Pressure Sensor (TPS)System.Validation of<br />
FAA STC N° ST02964NY-D.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.09.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 168/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1722 DASSAULT AIRCRAFT SERVICES (DAS) FAA STC ST02962NY-D FALCON 2000, FALCON 2000EX Validation of FAA STC Number ST02962NY- None - <strong>EASA</strong> STC ref. <strong>EASA</strong>.IM.A.S.02889 is 11.10.2<strong>01</strong>2<br />
D. Installation of RockwellCollins, Inc. ADS-B<br />
a pre requisite for thisinstallation.-<br />
Out System.Description as per Associated<br />
Airplane Flight Manual Supplement ref.<br />
Technical Documentation<br />
F2XW-D0006-150 IR, dated10/10/2<strong>01</strong>1<br />
is required for this installation.-<br />
Instructions for Continued Airworthiness<br />
ref. F2XW-D0006-155 RevisionB<br />
10<strong>04</strong>1723 DASSAULT AIRCRAFT SERVICES (DAS) FAA STC ST02963NY-D MYSTERE-FALCON 50 Validation of FAA STC Number ST02963NY-<br />
D. Installation of RockwellCollins, Inc. ADS-B<br />
Out System.Description as per Associated<br />
Technical Documentation.<br />
None - <strong>EASA</strong> STC ref. <strong>EASA</strong>.IM.A.S.02889 is<br />
a pre requisite for thisinstallation.-<br />
Airplane Flight Manual Supplement ref.<br />
F5XW-D0008-150 IR, dated02/12/2<strong>01</strong>1<br />
is required for this installation.-<br />
Instructions for Continued Airworthiness<br />
ref. F5XW-D0008-155 IR, dated<br />
10<strong>01</strong>5765 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.<strong>01</strong>803 SA8279SW-D FALCON 900EX Installation of the Auxiliary Battery System 08.02.2006<br />
10<strong>01</strong>5766 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.<strong>01</strong>805 FAA STC SA8303SW-D FALCON 900EX Installation of the Water System Modifications This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
08.02.2006<br />
10<strong>01</strong>5767 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.<strong>01</strong>806 FAA STC SA8270SW-D FALCON 900EX Installation of the Miscellaneous Structures This STC is approved only for the product<br />
08.02.2006<br />
(General / Mechanical)<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5768 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.<strong>01</strong>807 FAA STC SA8287SW-D FALCON 900EX Installation of the Equipment Rack This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
08.02.2006<br />
10<strong>01</strong>5778 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.<strong>01</strong>823 SA5611SW MYSTERE FALCON 200 Installation of the Collins Dual EFIS-85EFIS-85 1. <strong>EASA</strong> Approved Airplane Flight Manual<br />
02.08.2006<br />
(Standard II) Instrument & Flight Director Supplement for Collins Dual EFIS-85<br />
System of Collins Dual EFIS-86 Instrument & (Standard II) Instrument and Flight Director<br />
Flight Director System<br />
System, Falcon Jet Report 35402-1, Rev. B, or<br />
later <strong>EASA</strong> approved revision is a required part<br />
of this STC2. <strong>EASA</strong> Approved Airplane Flig<br />
10<strong>01</strong>6<strong>01</strong>6 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02182 ST1<strong>04</strong>61SC-D FALCON 900 Mid Cabin Door Installation, Enflite This STC is Limited to F9EX-<strong>01</strong>056-5<strong>01</strong><br />
Installations in Model Falcon 900EX.<br />
27.10.2006<br />
10<strong>01</strong>6<strong>01</strong>7 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02183 ST10510SC-D FALCON 900 Aircraft Compliance for Falcon 900EX S/N Limited to S/N 165. No duplicate Installation<br />
27.10.2006<br />
165.<br />
permitted.<br />
10<strong>01</strong>6<strong>01</strong>8 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02184 ST10253SC-D FALCON 900EX Oxygen System Installation. 27.10.2006<br />
10<strong>01</strong>6025 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02193 ST09296SC-D FALCON 2000 FAA STC ST09296SC-D: "Service and Indirect<br />
Lighting System"<br />
18.12.2006<br />
10<strong>01</strong>6026 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02194 SA8267SW-D FALCON 2000 FAA STC SA8267SW-D: "Auxiliary Battery<br />
System"<br />
20.12.2006<br />
10<strong>01</strong>6027 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02195 SA8227SW-D FALCON 2000 FAA STC SA8227SW-D: Automatic Electrical -Systems or components connected to the<br />
18.12.2006<br />
Load Shed System<br />
shed system must have a separate approval<br />
different from STC SA8227SW-D -Shedded<br />
componentsare non essential equipment<br />
10<strong>01</strong>6468 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02814 FAA STC ST09733SC-D FALCON 2000 Installation of Cabin Master Switch. Validation<br />
of FAA STC ST09733SC-D.<br />
See those of original FAA STC ST09733SC-D<br />
Revision 2 dated <strong>04</strong>th October 2002,AFM<br />
Supplement Report No. 37023-1, Revision A<br />
dated 25th July 2002 for F2M-<strong>01</strong>055-5<strong>01</strong> and -<br />
503 installations.AFM Supplement Report No.<br />
37023-2, Revision NC dated <strong>04</strong>th October<br />
2002<br />
10<strong>01</strong>6469 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02815 FAA STC SA8228W-D FALCON 2000 Installation of the Airborne Flight Information See those of original FAA STC SA8228SW-D<br />
System.Validation of FAA STC SA8228SW-D. Revision 2 dated 21st May 1999 or later<br />
revisions approved by <strong>EASA</strong> in accordance<br />
with <strong>EASA</strong>ED Decision 20<strong>04</strong>/<strong>04</strong>/CF (or<br />
subsequent revisions of this decision).<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 169/<strong>462</strong><br />
11.10.2<strong>01</strong>2<br />
20.05.2008<br />
20.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6586 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02991 FAA STC ST09313SC-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC ST09313SC-D 1. Prior to installation of this modification the<br />
02.<strong>04</strong>.2009<br />
Revision 1, <strong>01</strong>st October 2002Installation of installer must determine that the<br />
Standby Horizon System Modifications in interrelationship between this modification and<br />
accordance with Drawing List Report No. F9EX-any<br />
other previously installed modification will<br />
<strong>01</strong>035 Revision B dated 25 September 2002 or introduce no adverse effect upon the<br />
later revisions approved by <strong>EASA</strong> i.a.w. EAS airworthiness of the product.2.<br />
10<strong>01</strong>6587 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02992 FAA STC ST09311SC-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC ST09311SC-<br />
DInstallation of the Inertial Reference System<br />
Modification in accordance with Drawing List<br />
Report No. F9EX-<strong>01</strong>033 Revision NC dated<br />
<strong>04</strong>th May 2000 or later revisions approved by<br />
<strong>EASA</strong> i.a.w. <strong>EASA</strong> ED Decisions 2007/0<strong>01</strong>/C<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6588 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.02994 FAA STC SA8291SW-D FALCON 900EX<br />
a<br />
<strong>EASA</strong> Validation of FAA STC SA8291SW- 1. The F9EX-<strong>01</strong>003-503 and F9EX-<strong>01</strong>003-507<br />
DInstallation of the Battery Installations i.a.w. installations are limited to aircraft serial number<br />
Drawing List Report No. F9EX-<strong>01</strong>0003 <strong>04</strong>9.2. Prior to installation of this modification<br />
Revision F dated 14 September 2000 or later the installer must determine that the<br />
revisions approved by <strong>EASA</strong> i.a.w. <strong>EASA</strong> ED interrelationship between this modificationand<br />
Decisions 2007/0<strong>01</strong>/C and 20<strong>04</strong>/<strong>04</strong>/CF (or<br />
subseque<br />
any other previously ins<br />
10<strong>01</strong>6640 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.03080 FAA STC ST09293SC-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC ST09293SC-D 1. Prior to installation of this modification the<br />
Revision 10, 22nd December 20<strong>04</strong>Installation installer must determine that the<br />
of the FMZ-2000 Flight Management System in interrelationship between this modification<br />
accordance with Data List Report No. F9EX- andany other previously installed modification<br />
<strong>01</strong>026 Revision G dated 20 December 20<strong>04</strong> or will introduce no adverse effect upon the<br />
later revisions approved by <strong>EASA</strong> i.a.w. <strong>EASA</strong> airworthiness of the product.2. The ins<br />
10<strong>01</strong>6643 DASSAULT FALCON JET <strong>EASA</strong>.IM.A.S.03084 FAA STC ST09715SC-D FALCON 900EX - <strong>EASA</strong> Validation of FAA STC ST09715SC-<br />
D- Installation of the Control Wheel<br />
Modifications in accordance with Drawing List<br />
Report No. F9EX-<strong>01</strong>032<br />
10035<strong>01</strong>7 DASSAULT FALCON JET FAA STC ST10657SC-D 1. FALCON 2000EX<br />
2. FALCON 900EX<br />
10028268 DASSAULT FALCON JET - WILMINGTON P-<br />
<strong>EASA</strong>.IM.A.S.03109<br />
Assist Handle Installation:Configuration -5<strong>01</strong>:<br />
Main entry door assist handle<br />
installationConfiguration -503: Aft lavatory<br />
assist handle installationValidation of FAA STC<br />
N°ST10657SC-D<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2. The ins<br />
20.03.2009<br />
18.03.2009<br />
07.<strong>04</strong>.2009<br />
11.05.2009<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.05.2<strong>01</strong>1<br />
FAA STC ST<strong>01</strong>795NY-D F900EX <strong>EASA</strong> Validation of FAA STC ST<strong>01</strong>795NY- This design change is applicable to Dassault Prior to installation of this modification it 14.12.2009<br />
DInstallation of Decrane Aircraft Seating Aviation Mystere Falcon 900aircraft which have must be determined thatthe<br />
Company, Inc, Model 80A42S2three place previously been equipped with Dassault interrelationship between this modification<br />
partial berthing divan installation in accordance AviationModification M3000 (Falcon 900EX and any other previouslyinstalled<br />
withDassault Falcon Jet-Wilmington Master definition)<br />
modification and/ or repair will introduce<br />
Drawing List, 1979009<strong>04</strong> RevisionB, dated<br />
no adverse effectupon the airworthiness<br />
29th<br />
of the product.<br />
10<strong>01</strong>5465 DASSAULT FALCON JET - WILMINGTON <strong>EASA</strong>.IM.A.S.<strong>01</strong>217 FAA STC ST<strong>01</strong>156NY-D MYSTERE FALCON 900 Validation of FAA STC ST<strong>01</strong>156NY-D:<br />
CO<br />
Installation of a Honeywell Mark V Enhanced<br />
Ground Proximity Warning System (EGPWS)<br />
upgrade iaw Master Drawing List 027670321,<br />
Rev. - dtd Jan 26, 20<strong>01</strong>.<br />
10<strong>01</strong>5466 DASSAULT FALCON JET - WILMINGTON <strong>EASA</strong>.IM.A.S.<strong>01</strong>218 FAA STC ST<strong>01</strong>157NY-D MYSTERE FALCON 900 Validation of FAA STC No ST<strong>01</strong>157NY-D:<br />
CO<br />
Installation of a Honeywell Electronic Flight<br />
Instrument System (EFIS) EDZ-820 Software<br />
Upgrade iaw Master Drawing List 027670320,<br />
Rev. - dtd. Jan. 26, 20<strong>01</strong>.<br />
10<strong>01</strong>5467 DASSAULT FALCON JET - WILMINGTON <strong>EASA</strong>.IM.A.S.<strong>01</strong>219 FAA STC ST<strong>01</strong>775NY-D MYSTERE FALCON 900 Validation of FAA STC No ST<strong>01</strong>775-NY-D:<br />
CO<br />
Update of Dual Rockwell Collins TCR-94<br />
Transponder for Elementary Surveillance iaw<br />
Master Drawing List 126980303, Rev.- dtd.<br />
Oct. 15, 20<strong>04</strong>.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 170/<strong>462</strong><br />
31.05.2005<br />
31.05.2005<br />
31.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027110 DASSAULT FALCON JET CORP P-<br />
FAA STC SA8300SW-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC SA8300SW- See those of original FAA STC SA8300SW-D Prior to installation of this modification it 07.09.2009<br />
<strong>EASA</strong>.IM.A.S.02993<br />
D:Installation of the Automatic Cabin Electrical<br />
must be determined thatthe<br />
Load Shed System inaccordance with Drawing<br />
interrelationship between this modification<br />
List Report No. F9EX-<strong>01</strong>023, Revision E<br />
and any other previouslyinstalled<br />
dated28th September 2000 or later revisions<br />
modification and/ or repair will introduce<br />
approved by <strong>EASA</strong> in accordancewith <strong>EASA</strong><br />
no adverse effectupon the airworthiness<br />
ED De<br />
of the product<br />
10027112 DASSAULT FALCON JET CORP P-<br />
<strong>EASA</strong>.IM.A.S.02997<br />
FAA STC SA8283SW-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC SA8283SW-<br />
D:Installation of the Auxiliary Light Modifications<br />
in accordance withDrawing List Report No.<br />
F9EX-1<strong>01</strong>1, dated 16th October 1996 or<br />
laterrevisions approved by <strong>EASA</strong> in<br />
accordance with <strong>EASA</strong> ED<br />
Decision20<strong>04</strong>/<strong>04</strong>/CF (or subseq<br />
10<strong>01</strong>6<strong>04</strong>4 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02215 ST09737SC-D FALCON 900EX Bracket Installation for Mid Cabin Door i.a.w.<br />
Drawing List Report " F90-<strong>01</strong>093<br />
10<strong>01</strong>6216 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02464 FAA STC SA8312SW-D FALCON 50 Installation of the Automatic Cabin Electrical 1. As per FAA STC No. SA8312SW-D2.<br />
Load Shed System in accordance with Drawing Prior to installation of this modification the<br />
List Report No. F50-<strong>01</strong>182 Revision A, dated installer must determine that the<br />
27th September 1999 or later approved interrelationship between this modification and<br />
revisions.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
10<strong>01</strong>6217 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02465 FAA STC SA8299SW-D FALCON 50 Installation of Auxiliary Battery System in<br />
accordance with Drawing List Report No. F50-<br />
<strong>01</strong>173, Revision E dated 19th September<br />
20<strong>01</strong>or later approved revisions.<br />
10<strong>01</strong>6218 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02466 FAA STC SA8222SW-D FALCON 50 Installation of the GWS Satellite Data<br />
Communication System in accordance with<br />
Drawing List Report No. F50-<strong>01</strong>159, Revision<br />
NC, dated 21st July 1993 or later approved<br />
revisions.<br />
See those of original FAA STC SA8283SW-D Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
07.09.2009<br />
1. As per FAA STC No. SA8299SW-D.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
1. As per FAA STC No. SA8222SW-D.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
10<strong>01</strong>6219 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02467 FAA STC SA7300SW-D FALCON 50 Installation of the Service and Indirect Lighting 1. As per FAA STC No. SA7300SW-D.2.<br />
System in accordance with Drawing List Report Prior to installation of this modification the<br />
No. F50-<strong>01</strong>145, Revision L, dated 25October installer must determine that the<br />
2000 or later approved revisions.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
10<strong>01</strong>6220 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02468 FAA STC ST09316SC-D FALCON 50 Installation of the Standby Instrument Systemn<br />
in accordance with Drawing List Report No.<br />
F50-<strong>01</strong>172, Revision B, dated 12th<br />
October2000 or later approved revisions.<br />
10<strong>01</strong>6221 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02469 FAA STC SA7260SW-D FALCON 50 Installation of the Auxiliary Equipment Rack in<br />
accordance with Drawing List Report No. F50-<br />
<strong>01</strong>116, Revision N, dated 2nd June 1993 or<br />
later approved revisions.<br />
10<strong>01</strong>6222 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02470 FAA STC SA7069SW-D FALCON 50 Installation of the Centralized Water System in<br />
accordance with Drawing List Report No. F50-<br />
<strong>01</strong>095-2, Revision A, dated 6th September<br />
1999 or later approved revisions.<br />
10<strong>01</strong>6524 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02897 FAA STC SA7<strong>04</strong>9SW-D MYSTERE FALCON 900 Installation of Electrical FeedThru in Pressure<br />
Vessel.<br />
1. FAA STC No. ST09316SC-D2. Limited<br />
to Falcon 50EX version aircraft.3. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification wi<br />
1. As per FAA STC No. SA7260SW-D2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
1. As per FAA STC No. SA7069SW-D.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 171/<strong>462</strong><br />
19.12.2006<br />
19.07.2007<br />
09.07.2007<br />
19.07.2007<br />
17.07.2007<br />
19.07.2007<br />
19.07.2007<br />
19.07.2007<br />
23.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6525 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02898 FAA STC SA7056SW-D MYSTERE FALCON 900 Installation of Automatic Cabin Electrical Load Prior to installation of this modification the<br />
23.06.2008<br />
Shed System.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6526 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02899 REV 1 FAA STC SA7060SW-D MYSTERE FALCON 900 Installation of Basic Interior Furnishings. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
23.06.2008<br />
10<strong>01</strong>6527 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02900 REV 1 FAA STC SA7062SW-D MYSTERE FALCON 900 Installation of Basic Oxygen System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
23.06.2008<br />
10<strong>01</strong>6528 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.029<strong>01</strong> REV 1 FAA STC SA7085SW-D MYSTERE FALCON 900 Installation of Avionics Rack. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
23.06.2008<br />
10<strong>01</strong>6529 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02902 REV 1 FAA STC SA7123SW-D MYSTERE FALCON 900 Installation of APU Fault Panel Installation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
23.06.2008<br />
10<strong>01</strong>6530 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02903 REV 1 FAA STC SA7239SW-D MYSTERE FALCON 900 Installation of Emergency Power Supply Prior to installation of this modification the<br />
23.06.2008<br />
System.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6531 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.029<strong>04</strong> REV 1 FAA STC SA7227SW-D MYSTERE FALCON 900 Installation of Air Distribution System<br />
Prior to installation of this modification the<br />
23.06.2008<br />
Modification.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6532 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02905 REV 1 FAA STC ST09308SC-D MYSTERE FALCON 900 Installation of FMZ-2000 Flight Management<br />
System.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6533 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02906 REV 1 FAA STC ST09309SC-D MYSTERE FALCON 900 Installation of Universal Bracket Attachments. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6585 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02990 FAA STC SA8271SW-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC SA8271SW- Prior to installation of this modification the<br />
DInstallation of the APU Fault Panel Installation installer must determine that the<br />
i.a.w. Drawing List Report No. F9EX-<strong>01</strong>007 interrelationship between this modification and<br />
dated 08th October 1996 or later revisions any other previously installed modification will<br />
approved by <strong>EASA</strong> i.a.w. <strong>EASA</strong> ED Decisions introduce no adverse effect upon the<br />
2007/0<strong>01</strong>/C and 20<strong>04</strong>/<strong>04</strong>/CF (or subsequent re airworthiness of the product.¿ The<br />
10<strong>01</strong>6589 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.02995 FAA STC ST09312SC-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC ST09312SC-<br />
DInstallation of the Engine Instrument Display<br />
System Modification in accordance with<br />
Drawing List Report No. F9EX-1034 Revision<br />
NC dated <strong>04</strong>th May 2000 or later revisions<br />
approved by <strong>EASA</strong> i.a.w. <strong>EASA</strong> ED Decisions<br />
2007/0<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 172/<strong>462</strong><br />
23.06.2008<br />
23.06.2008<br />
27.03.2009<br />
24.03.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6641 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.03082 FAA STC ST093<strong>01</strong>SC-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC ST093<strong>01</strong>SC- Prior to installation of this modification the<br />
31.03.2009<br />
DInstallation of the Service and Indirect Lighting installer must determine that the<br />
System in accordance with Drawing List report interrelationship between this modification and<br />
No. F9EX-<strong>01</strong>027, Revision B dated<br />
any other previously installed modification<br />
28September 2000 or later revisions approved will introduce no adverse effect upon the<br />
by <strong>EASA</strong> i.a.w. <strong>EASA</strong> ED Decisions<br />
2007/0<strong>01</strong>/C<br />
airworthiness of the product.<br />
10<strong>01</strong>6642 DASSAULT FALCON JET CORP. <strong>EASA</strong>.IM.A.S.03083 FAA STC ST09738SC-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC ST09738SC- Prior to installation of this modification the<br />
31.03.2009<br />
DInstallation of the HF Radio Master System in installer must determine that the<br />
accordance with Drawing List Report No. F9EX-interrelationship<br />
between this modification and<br />
<strong>01</strong><strong>04</strong>4 Revision NC dated 16 September 2002 any other previously installed modification<br />
or later revisions approved by <strong>EASA</strong> i.a.w. will introduce no adverse effect upon the<br />
<strong>EASA</strong> ED Decisions 2007/0<strong>01</strong>/C and<br />
20<strong>04</strong>/<strong>04</strong>/C<br />
airworthiness of the product.<br />
10<strong>01</strong>6215 DASSAULT FALCON JET<br />
<strong>EASA</strong>.IM.A.S.02463 REV. 1 FAA STC ST093<strong>04</strong>SC-D MYSTERE FALCON 50 (MF50) Installation of the Inertial Reference System As per FAA STC ST093<strong>04</strong>SC-D Prior to installation of this modification the <strong>04</strong>.05.2<strong>01</strong>2<br />
CORPORATION<br />
Modifications(installation of Securaplane XL-<br />
installer must determinethat the<br />
245 batteries in lieu of Saft batteriesto provide<br />
interrelationship between this modification<br />
backup power) in accordance with Drawing List<br />
and any otherpreviously installed<br />
report No.F50-<strong>01</strong>188 Revision NC dated 23rd<br />
modification will introduce no adverse<br />
July 1999 or later approve<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>6224 DASSAULT FALCON JET<br />
<strong>EASA</strong>.IM.A.S.02472 FAA STC ST1<strong>04</strong>23SC-D FALCON 900EX Installation of the Service and Indirect Lighting 1. As per FAA STC ST1<strong>04</strong>23SC-D.2.<br />
26.09.2007<br />
CORPORATION<br />
System (EMTEQ) in accordance with Data List Applicable to Falcon 900EX EASy aircraft<br />
Report No. F9EX-<strong>01</strong><strong>04</strong>8 Revision A dated 07th version.3. F900EX EASy designation does<br />
October 2005 or later revisions of the above not correspond to a new MF900 model<br />
listed documents approved by <strong>EASA</strong> in designation but is a commercial designation for<br />
accordance with <strong>EASA</strong> ED Decision 200 airplanes onwhich the specific Dassault<br />
modificat<br />
10027395 DASSAULT FALCON JET<br />
P-<br />
FAA STC SA8279SW-D MF900, F900EX <strong>EASA</strong> Validation of FAA STC SA8279SW- This design change is also applicable on the Prior to installation of this modification it 28.09.2009<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.03264<br />
D:Installation of the Auxiliary Battery System in Falcon 900C designation asdefined on <strong>EASA</strong> must be determined thatthe<br />
accordance with DrawingList Report No. F9EX- TCDS.A.062<br />
interrelationship between this modification<br />
<strong>01</strong>008, Revision K dated 26th September 2002<br />
and any other previouslyinstalled<br />
orlater revisions approved by <strong>EASA</strong> in<br />
modification and/ or repair will introduce<br />
accordance with <strong>EASA</strong> ED<br />
no adverse effectupon the airworthiness<br />
Decision20<strong>04</strong>/<strong>04</strong>/CF (<br />
of the product.<br />
10028777 DASSAULT FALCON JET<br />
CORPORATION<br />
10029434 DASSAULT FALCON JET<br />
CORPORATION<br />
10035<strong>01</strong>6 DASSAULT FALCON JET<br />
CORPORATION<br />
10035<strong>01</strong>8 DASSAULT FALCON JET<br />
CORPORATION<br />
10035461 DASSAULT FALCON JET<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.02998 FAA STC SA8275SW-D FALCON 900EX 16.07.2009<br />
P-<br />
<strong>EASA</strong>.IM.A.S.02996<br />
FAA STC SA8285SW-D FALCON 900EX <strong>EASA</strong> Validation of FAA STC SA8285SW-D None. Prior to installation of this modification it 24.03.2<strong>01</strong>0<br />
Revision1:Installation of the Security System<br />
must be determined thatthe<br />
(Structural Provisions) inaccordance with<br />
interrelationship between this modification<br />
Drawing List Report No. F9EX-<strong>01</strong>021, Revision<br />
and any other previouslyinstalled<br />
B dated13th June 1997 or later revisions<br />
modification and/ or repair will introduce<br />
approved by <strong>EASA</strong> in accordance with<strong>EASA</strong><br />
no adverse effectupon the airworthiness<br />
ED D<br />
of the product.<br />
FAA STC N° ST10262SC-D F2000EX Oxygen system installation.Installation of added As per FAA STC N° ST10262SC-D, Revision<br />
portion of the continuous flow, dropout<br />
typeoxygen system for the cabin and lavatory.<br />
This system connects to theexisting TC aircraft<br />
oxygen system.Validation of FAA STC N°<br />
ST10262SC-D, Revision 2 Issue date<br />
2 Issue date April 14, 2<strong>01</strong>1.<br />
FAA STC N° ST10584SC-D F2000EX & F900EX Console table installation.Installation of a<br />
Console Table in the main cabin area of the<br />
aircraftside ledge. This table design will<br />
typically be located between twosingle seats<br />
and is not designed to be installed in front of<br />
theemergency escape hatch.Valid<br />
FAA STC N° ST10583SC-D 1. F2000EX<br />
2. F900EX<br />
Galley pocket door installationValidation of<br />
FAA STC N°ST10583SC-D<br />
Prior to installation of this modification it 19.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
19.05.2<strong>01</strong>1<br />
Approval is limited to the "-5<strong>01</strong>" configuration. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
24.06.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 173/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037659 DASSAULT FALCON JET<br />
FAA STC ST10890SC-D F2000EX Aft RH Divan installationValidation of FAA STC As per FAA STC N°ST10890SC-D Prior to installation of this modification it 14.12.2<strong>01</strong>1<br />
CORPORATION<br />
N°ST10890SC-D<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037660 DASSAULT FALCON JET<br />
CORPORATION<br />
FAA STC ST10891SC-D F2000EX Avionics and interiors installationValidation of<br />
FAA STC N°ST10891SC-D<br />
10<strong>01</strong>3990 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>022 MYSTERE FALCON 20-5 Installation of Collins TCAS-4000 and of 2 ATC<br />
TDR 94D capable of elementary surveillance.<br />
10<strong>01</strong>4<strong>01</strong>8 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>065 MYSTERE FALCON 50 Installation of a Honeywell Mark V EGPWS<br />
soft 217-217 with terrain display in the Collins<br />
EFIS 86-C14<br />
10<strong>01</strong>4030 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>096 MYSTERE FALCON 50 Installation of a Honeywell Mark VII EGPWS<br />
soft 217-217 with terrain display in the MFD<br />
10<strong>01</strong>4052 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>134 FALCON 10 DFS 1261 dtd 13.Oct 2005: Installation of a<br />
TAWS Honeywell Mark VIII EGPWS soft <strong>01</strong>1<br />
10<strong>01</strong>4071 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>161 FALCON 10 DFS 1255 dtd. 29.3.06: Installation of two FMS<br />
UNS-1L Soft 802.X / B-RNAV & P-RNAV<br />
10<strong>01</strong>4072 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>163 REV. 1 FALCON 10 DFS 1252 dtd. 9.6.05: EFIS Universal EFI<br />
550/600<br />
10<strong>01</strong>4099 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>200 FALCON 10 Installation of Collins ATC with flight ID and<br />
Gables Control Panel<br />
10<strong>01</strong>4117 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>224 FALCON 10 DFS 1251 dtd. 2.6.05: Installation of a Multi<br />
functional display MFD 640<br />
As per FAA STC N°ST10891SC-DRestricted<br />
to F2000EX S/N 216<br />
1. Applicable to Mystère Falcon 50 equipped<br />
with Collins EFIS 86-C14 only2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine<br />
This STC is only valid for Falcon 50 equipped<br />
with a Universal FMS UNS-1B with GPS-1000,<br />
or UNS-1C/1C+/1D/1E/1F/1K/1K+/1L and with<br />
Collins EFIS-86C(x)/weather radar WXR-350<br />
1. This STC is approved only for the<br />
configuration as defined in Mod Sheet DFS<br />
1261.2. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
1. This STC is approved only for the<br />
configuration as defined in Mod Sheet DFS<br />
1255. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
STC applicable only to Falcon 10 aircraft<br />
equipped with:- 2 Collins ATC TDR-94D p/n<br />
622-9210-0<strong>01</strong>/002/003 or 0<strong>04</strong>.- and ATC<br />
control box Gables G7 130-XX.<br />
1. This STC is approved only for the<br />
configuration as defined in Mod Sheet DFS<br />
1251. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
10<strong>01</strong>4118 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>225 MYSTERE FALCON 900 EGPWS Software Evolution (222-222) Applicable to MF900 equipped with EGPWS<br />
Mark V soft 212-212 installed with DFS 9259<br />
STC<br />
10<strong>01</strong>4119 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>226 MYSTERE FALCON 900 Incorporation of RAAS function on EGPWS<br />
soft 222-222<br />
Applicable to MF900 equipped with EGPWS<br />
Mark V soft 222-222 installed with DFS 9472<br />
STC<br />
10<strong>01</strong>4137 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>248 FALCON 10 DFS 1250 dtd. 22.3.06: Weather Radar Primus 1. This STC is approved only for the<br />
660<br />
configuration as defined in Mod Sheet DFS<br />
1250. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
10<strong>01</strong>4141 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>254 MYSTERE FALCON 20-5 Installation of one FMS Universal UNS-1L<br />
SOFT 802.X in accordance with the Change<br />
Approval Sheet -Original- or later <strong>EASA</strong><br />
approved revisions.<br />
Operation of the Flight Management System in<br />
the Approach Mode is not allowed<br />
Prior to installation of this modification it 14.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 174/<strong>462</strong><br />
28.<strong>04</strong>.2005<br />
03.02.2005<br />
15.02.2005<br />
02.05.2006<br />
02.05.2006<br />
11.<strong>01</strong>.2007<br />
11.<strong>04</strong>.2005<br />
02.05.2006<br />
12.12.2005<br />
06.10.2006<br />
02.05.2006<br />
19.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4152 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>273 FALCON 2000 DFSD066 dtd. 19. October 05: Airview 1. This STC is limited to Falcon 2000 S/N<br />
08.11.2005<br />
Communication and Security System 0<strong>01</strong>2. This STC is approved only for the<br />
configuration as defined in Mod Sheet<br />
DFSD066<br />
10<strong>01</strong>4156 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>280 MYSTERE FALCON 200 AFM supplement associated to Dassault Subject AFM supplement is associated to<br />
21.06.2005<br />
Aviation Mod M1632 "Installation d'un hublot Dassault Aviation Mod M1632: "Installation<br />
inférieur avec volet de protection".<br />
d'un hublot inférieur avec volet de<br />
protection",applicable to F20 GF SN 397 only<br />
10<strong>01</strong>4170 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>303 FALCON 10 Antenna installation 1. This STC is approved only for the<br />
configuration as defined in Mod Sheet DFS<br />
1263.2. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4172 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>305 MYSTERE FALCON 50 Introduction of Pressure Seals for wire runs This STC is approved only for the configuration<br />
as defined in Mod Sheet DFS<br />
5610.Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4217 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>378 MYSTERE FALCON 900 Call out evolution with EGPWS Honeywell Applicable to all MF900 aircraft with<br />
Mark V 212-212.This STC supersedes the STC modification DFS 9259<br />
F-C163-SF-2107 <strong>EASA</strong> approved on March 9,<br />
20<strong>04</strong> with the reference 20<strong>04</strong>-2073.<br />
10<strong>01</strong>4243 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>452 MYSTERE FALCON 20 Deviation to M GE 2 - Pressure seals FR17-18 1. This STC is applicable to Falcon 20S/N 103<br />
only2. This STC is to be applied simultaneously<br />
with Dassault Aviation Mod M GE23.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determines by the<br />
installer<br />
10<strong>01</strong>4255 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>481 FAN JET<br />
DFS 2545 dtd. 12. October 05: Camera and This STC approves the installation only, system<br />
MYSTERE FALCON 20<br />
Video Recorder installation<br />
activation is not considered.<br />
10<strong>01</strong>4263 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>493 Installation of two V/UHF AN/ARC210 1. This STC is applicable to Falcon 20 SN 076<br />
only2. System activation is not considered3.<br />
This STC is approved only for the configuration<br />
as defined in Mod Sheet DFS 25434.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4267 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>496 MYSTERE FALCON 20 Antenna relocations, skin repairs 1. This STC is only approved for the<br />
configuration as defined in Mod Sheet DFS<br />
2558 Issue Original<br />
14.09.2005<br />
10<strong>01</strong>4270 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>500 FALCON 10 GPS Antenna installation 1. Applicable to Falcon 20 S/N 103 only. 16.08.2005<br />
10<strong>01</strong>4274 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>510 FALCON 20 Time Base Installation. 1. This STC is applicable to Falcon 20 SN 076<br />
only 2. System activation is not considered 3.<br />
This STC is approved only for the configuration<br />
as defined in Mod Sheet DFS 2548 4.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined b<br />
18.08.2005<br />
10<strong>01</strong>4276 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>512 FALCON 10 Frame 0 Pressure Seal through-fitting<br />
modification (enlarge pressure seals)<br />
This STC is approved only for the configuration<br />
as defined in Mod Sheet DFS 1272 Issue<br />
Original. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4284 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>521 MYSTERE FALCON 20 Power Utility System activation is not considered 28.09.2005<br />
10<strong>01</strong>4294 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>536 MYSTERE FALCON 20 DFS 2562 dtd 21.Dec 05: Master Mission 1. This STC is approved only for the<br />
25.<strong>01</strong>.2006<br />
Function<br />
configuration as defined in Mod Sheet DFS<br />
25622. Compatibility with other aircraft/engine<br />
configurations shall be determinded by the<br />
installer<br />
10<strong>01</strong>4332 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>586 FALCON 10 Update ATC Transponder for elementary This STC is approved only for the configuration<br />
10.10.2005<br />
surveillance DFS 1253 issue A<br />
as defined in Mod Sheet DFS 1253.<br />
10<strong>01</strong>4334 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>589 FALCON 10 DFS1226 Revision D dated 9 June 2005:<br />
Installation of Collins TCAS 4000with one or<br />
two TDR-94D<br />
10<strong>01</strong>4383 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.<strong>01</strong>667 MYSTERE FALCON 2000<br />
MYSTERE FALCON 2000EX<br />
DFS D078 dtd. 5.4.2006: EGPWS Software<br />
222-222<br />
This STC is approved only for the configuration<br />
as defined in Mod Sheet DFS 1226.<br />
1. Activation of Runway Awareness Advisory<br />
System (RAAS) is not approved through this<br />
STC2. This STC is approved only for the<br />
configuration as defined in Mod Sheet DFS<br />
D0782. Compatibility with other aircraft/engine<br />
configurations shall be determined by th<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 175/<strong>462</strong><br />
10.08.2005<br />
22.09.2005<br />
<strong>04</strong>.07.2005<br />
22.09.2005<br />
08.11.2005<br />
09.08.2005<br />
24.08.2005<br />
10.10.2005<br />
07.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4436 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02485 DFS 2568 dtd. 21.Dec 05: DFS AFM 1. This STC is approved only for the<br />
26.<strong>01</strong>.2006<br />
Supplement F20 # 51 to DTM<br />
configuration as defined in Mod Sheet DFS<br />
589/DTM590/DTM591<br />
2568.2. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.3. This STC is approved only for the<br />
product configuration as defined in the<br />
10<strong>01</strong>4505 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02575 REV. 1 MF900 & F900EX 220 VAC ELECTRICAL DISTRIBUTION ON None Prior to installation of this modification it 13.10.2<strong>01</strong>0<br />
AIRCRAFTSTC <strong>EASA</strong>.A.S 02575 revision for<br />
must be determined thatthe<br />
applicability extension and addition ofversion 2.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>4517 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02593 MYSTERE FALCON 50 DFS 5625A dtd. 4.Mai 2006: Equipment<br />
installation with 220V inverter<br />
05.05.2006<br />
10<strong>01</strong>4529 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02614 FALCON 10 DFS 1274 dtd 5.5.06: Mode S Transponder Applicable to Falcon 10 with DFS 1269B<br />
05.05.2006<br />
Enhanced Surveillance<br />
applied previously or simultaneously<br />
10<strong>01</strong>4617 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02747 FAN JET<br />
DFS536 Issue A dtd. 29.Sep 06: Honeywell Leaflet TGL 12 "Certification Considerations<br />
02.10.2006<br />
MYSTERE FALCON 20<br />
EGPWS Mark Vinstallation with Terrain display for the TerrainAwareness Warning System:<br />
MYSTERE FALCON 20-5<br />
MYSTERE FALCON 200<br />
in Collins EFIS 86-C14<br />
TAWS" applies<br />
10<strong>01</strong>4619 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02751 FAN JET<br />
MYSTERE FALCON 200<br />
DFS2574: Limitation Removal Applicable to Fan Jet Falcon S/N 328 only 05.09.2006<br />
10<strong>01</strong>4666 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02823 FALCON 10 MODE S TRANSPONDER WITH<br />
1. This STC is approved only for those Falcon<br />
05.12.2006<br />
ENHANCED SURVEILLANCE CAPACITY 10 aircraft equipped with two Collins TDR-94D(-<br />
007) Mode “S” ATC Transponders and “Flight<br />
Ident” source.2. Compatibility with previous<br />
approved modifications shall be determined by<br />
the installer.3. JAA Leaflet<br />
10<strong>01</strong>4678 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02839 MYSTERE FALCON 900 MODE S TRANSPONDER WITH<br />
ENHANCED SURVEILLANCE CAPACITY<br />
10<strong>01</strong>4682 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02843 FALCON 10 Extended Function (P-RNAV / RNP 1<br />
Compliance) on Flight Management System<br />
(FMS) UNS-1K+ installation<br />
10<strong>01</strong>4685 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02848 MYSTERE FALCON 50 MODE S TRANSPONDER WITH<br />
ENHANCED SURVEILLANCE CAPACITY<br />
10<strong>01</strong>4687 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02850 FAN JET FALCON SERIES C<br />
MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
MYSTERE FALCON 20-F5<br />
Mode S Transponder with enhanced<br />
surveillance capacity.<br />
This STC is approved only for those Mystere<br />
Falcon 900B aircraft equipped with two Collins<br />
TDR-94D(-007) Mode “S” ATC Transponders<br />
and “Flight Ident” source.Compatibility with<br />
previous approved modifications shall be<br />
determined by the installer.JAA Leaflet<br />
his STC is applicable to Falcon 10 aircraft<br />
equipped with:• Collins Autopilot and Flight<br />
Director APS80,• Collins EFIS 85C-14.• 1<br />
FMS Universal UNS-1K+ with software version<br />
802.2 or laterFMS Universal UNS-1K+<br />
installation has to be embodied throu<br />
This STC is approved only for those Mystere<br />
Falcon 50 aircraft equipped with:- Two<br />
Collins TDR-94D(-007) Mode “S” ATC<br />
Transponders and “Flight Ident” source, and-<br />
Two Inertial Reference Systems.Compatibility<br />
with previous approved modifications shall<br />
1. This STC is approved only for those Fan<br />
Jet Falcon and Mystere Falcon 20-()5 aircraft<br />
equipped with two Collins TDR-94D(-<br />
007)Mode “S” ATC Transponders and “Flight<br />
Ident” source.2. JAA Leaflet TGL 13<br />
“Certification of Mode S Transponder Systems<br />
for<br />
10<strong>01</strong>4688 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02851 MYSTERE FALCON 900 CABIN REFURBISHMENT This STC is approved only for Mystere Falcon<br />
900 Serial Number Aircraft 054.Compatibility<br />
with previous approved modifications shall be<br />
determined by the installer.<br />
10<strong>01</strong>4714 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02887 FAN JET FALCON SERIES C<br />
FAN JET FALCON SERIES D<br />
FAN JET FALCON SERIES E<br />
FAN JET FALCON SERIES F<br />
FAN JET FALCON SERIES G<br />
Incorporation of Runway Awareness and This STC is approved for all Fan Jet Falcon all<br />
Advisory System (RAAS) Function on EGPWS series and all Mystere Falcon 20-()5 aircraft<br />
Honeywell Mark V or Mark VII.<br />
with EGPWS Mark V or Mark VII software 224-<br />
224 and Terrain Database or later.Aircraft<br />
avionics required pre-installation as per DFS<br />
Change Approval Sheet DFS2576-<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 176/<strong>462</strong><br />
30.11.2006<br />
29.07.2008<br />
29.11.2006<br />
18.<strong>01</strong>.2007<br />
21.12.2006<br />
18.07.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4733 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.02915 MYSTERE FALCON 50 Mode S Transponder with enhanced<br />
This STC is approved only for those Mystere<br />
08.02.2007<br />
surveillance capacity.<br />
Falcon 50 aircraft equipped with two Collins<br />
TDR-94D(-007) Mode “S” ATC Transponders,<br />
“Flight Ident” source and without IRS and with<br />
one or two FMS’s.Compatibility with previous<br />
approved modifications shall be de<br />
10<strong>01</strong>4820 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03030 Elementary and enhanced mode S<br />
transponder capabilities on existing dual MST-<br />
67A mode S transponder installation.<br />
10<strong>01</strong>4847 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03069 MYSTERE FALCON 50 Incorporation of Runway Awareness and<br />
Advisory System (RAAS) function on EGPWS<br />
Honeywell MK V.<br />
10<strong>01</strong>5006 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03306 FALCON 2000<br />
FALCON 2000EX<br />
F2000 / F2000EX Incorporation of Runway<br />
Awareness and Advisory System (RAAS)<br />
Function on EGPWS Honeywell Mk V.<br />
10<strong>01</strong>5071 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03397 MYSTERE FALCON 50 Air Data Sensor Installation for non essential<br />
systems<br />
This STC is limited to all Mystere Falcon 200<br />
aircraft equipped with two Mode S<br />
Transponders Honeywell MST–67A with<br />
antenna diversity as part of the original<br />
transponder installation plus two FMS Universal<br />
UNS-1() and two ADC 80 installed.See:<br />
Mystere Falc<br />
1. This STC is approved only for those<br />
Mystere Falcon 50 aircraft equipped with a<br />
Honeywell EGPWS Mk V with Software<br />
version 212-212 or later and with Proline<br />
Avionic Suite V6 with Terrain Display available;<br />
Terrain Database 435 or later is required (as<br />
1. As per applicability defined on DFS<br />
Change Approval Sheet DFS-D100-CAS Issue<br />
A1 or later approved revisions this STC is<br />
limited to those Falcon 2000 and Falcon<br />
2000EX previously equipped with:-<br />
Honeywell EGPWS Mk V Soft. 212-212 or<br />
later with terr<br />
This STC is limited to all Mystere Falcon 50<br />
aircraft without ARINC 429 air data parameters<br />
available.In case the aircraft is RVSM<br />
compliant this DFS modification will be<br />
applicable only on those aircraft on which<br />
Dassault Aviation SB F50-246 have been imp<br />
10<strong>01</strong>5108 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03451 REV. 1 MYSTERE FALCON 50 IFE / Galley Electrical Load Shedding. 1. This STC is applicable to:- All Mystere<br />
Falcon MF50 aircraft and;- Falcon 50EX<br />
aircraft variant up to serial number aircraft 333<br />
included, on which Dassault Aviation Mod.<br />
M2849 “IFE Load Shedding: electrical<br />
capability” has not been embodied.2.<br />
10<strong>01</strong>5110 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03453 MYSTERE FALCON 50 Installation of AC Electrical Generation /<br />
Distribution compliant with JAA TGM/25/10<br />
requisites<br />
10<strong>01</strong>5181 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03560 FALCON 900EX Falcon 900C and F900EX: Incorporation of<br />
Runway Awareness and Advisory System<br />
(RAAS) Function software version 224-224 on<br />
EGPWS Honeywell Mk V<br />
10<strong>01</strong>5266 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03736 FALCON 900EX<br />
MYSTERE FALCON 900<br />
One or two three-places Sofa installation in the<br />
aft part of the Cabin.<br />
STC applicable on those Mystere Falcon 50<br />
aircraft on which STC <strong>EASA</strong>.A.S.03451 (Mod.<br />
DFS 5653) “IFE / Galley Electrical Load<br />
Shedding” has been implemented previously or<br />
simultaneously.<br />
As per applicability defined on DFS Change<br />
Approval Sheet DFS9541-CAS Issue A1 or<br />
later approved revisions this STC is limited to<br />
those Falcon 900C and Falcon 900EX aircraft<br />
previously equipped with:• Honeywell<br />
EGPWS Mk V Soft. 212-212 with terrain disp<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2. The in<br />
10027351 DASSAULT FALCON SERVICE P-<strong>EASA</strong>.A.S.03939 MYSTERE FALCON 50 P-RNAV Capability This <strong>EASA</strong> approval is applicable on those<br />
Mystere Falcon 50 aircraftwhich have<br />
previously incorporated the Mod DFS 5598<br />
(approved under<strong>EASA</strong>.A.S.00615)<br />
with:·,,Collins Autopilot APS 85·,,EFIS 86 C14<br />
and·,,Version 802.X for the FMS UNS-1L<br />
Software This desig<br />
22.<strong>04</strong>.2008<br />
30.05.2007<br />
21.11.2007<br />
28.03.2008<br />
26.06.2008<br />
28.03.2008<br />
10.06.2008<br />
09.<strong>01</strong>.2009<br />
Prior to installation of this modification it 24.09.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 177/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028563 DASSAULT FALCON SERVICE P-<strong>EASA</strong>.A.S.03652 MYSTERE FALCON 900 Mode S dual transponder installation with This <strong>EASA</strong> approval is applicable on those Prior to installation of this modification it 22.<strong>01</strong>.2<strong>01</strong>0<br />
elementary and enhancedsurveillance Basic Mystere Falcon 900aircraft previously must be determined thatthe<br />
capabilities<br />
equipped with:- Dual ATC Transponders interrelationship between this modification<br />
Honeywell MST-67A P/N 066-<strong>01</strong>143-06<strong>01</strong> and any other previouslyinstalled<br />
withantenna diversity installation- 2 IRS and 2 modification and/ or repair will introduce<br />
ADC AZ 810As per DFS Change Approval no adverse effectupon the airworthiness<br />
Sheet DFS<br />
of the product.<br />
10028776 DASSAULT FALCON SERVICE <strong>EASA</strong>.A.S.03729 FALCON 900 20.07.2009<br />
10029669 DASSAULT FALCON SERVICE P-<strong>EASA</strong>.A.S.03764 FALCON 900EX F900EX Serial Number 111 aircraft completion This <strong>EASA</strong> design change airworthiness Prior to installation of this modification it 12.<strong>04</strong>.2<strong>01</strong>0<br />
definition<br />
approval is applicable on Falcon900EX serial must be determined thatthe<br />
number aircraft 111<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032131 DASSAULT FALCON SERVICE MF50 AND FALCON 50EX Stretchers installation.Provide the ability to<br />
install in the aircraft one or two stretchers forair<br />
ambulance according to two configurations:-<br />
One stretcher is installed in the LH side instead<br />
of the two LH fwdseats. - Two stretchers are<br />
installed in the<br />
10032163 DASSAULT FALCON SERVICE MF900 & F900EX 230VAC electrical distribution for galley.An<br />
inverter and a GFI are installed to provide<br />
230AC power on one outletin the galley.<br />
100322<strong>04</strong> DASSAULT FALCON SERVICE F900EX F900EX S/N 086 Cabin Layout<br />
Modification.New interior cabin configuration<br />
features a 12-passenger and 3crewaccommodation.<br />
10033835 DASSAULT FALCON SERVICE P-<strong>EASA</strong>.A.S.03935 FALCON 900EX Falcon 900EX aircraft serial numbers 065 and<br />
073 - CompletionDefinition.<br />
10034125 DASSAULT FALCON SERVICE FAA STC ST02863CH MF50, FALCON 50EX Stretchers installation for medical<br />
evacuation.Provide the ability to install in the<br />
aircraft one or two stretchers forair ambulance<br />
operations.<br />
10034893 DASSAULT FALCON SERVICE F2000, F2000EX 115VAC electrical distribution for<br />
galley.DFSD144 A consists in installing a<br />
28VDC/115VAC inverter, the<br />
associatedprotections and an outlet in the<br />
galley area.<br />
10035568 DASSAULT FALCON SERVICE REV. 1 F900EX, F900C, MF900 B WiFi activation on Falcon 900 non Easy<br />
aircraftThis Major Change to <strong>EASA</strong> STC<br />
10035568 approves the extension<br />
ofapplicability to MF900B aircraft.<br />
This modification is applicable on Mystère<br />
Falcon 50 and Falcon 50EXaircraft equipped<br />
with four seats installed in the LH side and two<br />
seatsand a sofa installed in the RH side as<br />
defined in the Modification SheetDFS5691.This<br />
installation does not cover any<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.10.2<strong>01</strong>0<br />
Modification applicable to MF900, F900EX Prior to installation of this modification it 13.10.2<strong>01</strong>0<br />
aircraft with :- 1400W available on A4 bus, and- must be determined thatthe<br />
Master switch in cockpit to switch off<br />
interrelationship between this modification<br />
components electricallysupplied in Galley area, and any other previouslyinstalled<br />
and- Master switch in cockpit to switch off all modification and/ or repair will introduce<br />
115/230VAC distributioncircuit<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Modification applicable to F900EX S/N 086<br />
with a pre mod configurationas described in<br />
DFS Modification Sheet DFS9613, Issue A.<br />
Prior to installation of this modification it 15.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
This <strong>EASA</strong> design change airworthiness Prior to installation of this modification it<br />
approval is applicable only onFalcon 900EX must be determined thatthe<br />
aircraft serial numbers 065 and 073.Associated interrelationship between this modification<br />
limitation: Non commercial air transportation and any other previouslyinstalled<br />
use.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC does not cover the qualification of<br />
the installed stretcher. Itis to be used in<br />
conjunction with <strong>EASA</strong> STC covering the<br />
validation ofFAA STC ST02863CH.This<br />
modification does not cover the use of any<br />
auxiliary medicalequipment to be used in<br />
conjunct<br />
11.02.2<strong>01</strong>1<br />
Prior to installation of this modification it 09.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Modification applicable to F2000 & F2000 EX Prior to installation of this modification it 11.05.2<strong>01</strong>1<br />
aircraft with:- 1400W available on A4 bus must be determined thatthe<br />
(version 1) or 1280W (version 2), and- Master interrelationship between this modification<br />
switch in cockpit to switch off components and any other previouslyinstalled<br />
electricallysupplied in Galley area, and- Master modification and/ or repair will introduce<br />
switch in cockpit to switch off<br />
no adverse effectupon the airworthiness<br />
of the product<br />
F900EX and 900C aircraft equipped with WiFi<br />
equipments installationcompliant with<br />
prerequisite note DT-003-10.MF900B aircraft<br />
equipped with WiFi equipments installation<br />
compliantwith prerequisite note DT-0<strong>01</strong>-11.<br />
Prior to installation of this modification it 22.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 178/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037056 DASSAULT FALCON SERVICE F900B, F900C & F900EX Cabin Master installation.A Cabin Master Not applicable Prior to installation of this modification it 27.10.2<strong>01</strong>1<br />
Switch is installed on Co-pilot console.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10037415 DASSAULT FALCON SERVICE F900B, F900C, F900EX<br />
F900EX EASY<br />
FR14 CABIN PARTITION WITH<br />
MECHANICAL POCKET SLIDING DOOR.<br />
As per DFS Change Approval Sheet DFS9654- Prior to installation of this modification it 25.11.2<strong>01</strong>1<br />
CAS Issue A dated 06.08.2<strong>01</strong>1.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10037417 DASSAULT FALCON SERVICE F900EX F900EX S/N 038 Cabin Layout Modification. Restricted to F900EX S/N 038 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
25.11.2<strong>01</strong>1<br />
10038490 DASSAULT FALCON SERVICE REV. 2 F900EX EASY TCAS 2000 upgrade to TCAS change 7.1 on<br />
F900EX EASyMajor Change to <strong>EASA</strong> STC<br />
10038490This Major Change consists in<br />
removing the former limitation (onlyVersion 1<br />
(F900EX EASy Step 3+) was approved)<br />
10039335 DASSAULT FALCON SERVICE F2000EX EASY TCAS 2000 upgrade to TCAS change 7.1 on<br />
F2000EX EASy<br />
10<strong>04</strong>1183 DASSAULT FALCON SERVICE MYSTERE-FALCON 50 Mode S transponder upgrade to comply with<br />
Elementary and<br />
EnhancedSurveillance.Honeywell transponder<br />
MST-67A version is upgraded and ATC/TCAS<br />
ControlBox is replaced by new Honeywell PS-<br />
578A unit.<br />
10<strong>04</strong>1623 DASSAULT FALCON SERVICE F2000, F2000EX WiFi activation on Falcon 2000, F2000EX<br />
aircraft.<br />
10<strong>01</strong>5747 DAYTON-GRANGER Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>779 REV. 4 FAA STC NO. ST02241NY CL-600-2B19<br />
CL-600-2C10<br />
CL-600-2D15<br />
CL-600-2D24<br />
CL-600-2E25<br />
10<strong>01</strong>6<strong>04</strong>3 DC AEROSPACE <strong>EASA</strong>.IM.A.S.02214 REV. 1 ST03<strong>01</strong>1AT BOEING 727-100 SERIES<br />
BOEING 727-200 SERIES<br />
Installation of Winglet and Horizontal Stabilizer<br />
End Cap LightningProtection Kits<br />
Installation of Sandel ST3400 Terrain<br />
Awareness and Warning System (TAWS) in<br />
Boeing 727 Series Aircraft according to FAA<br />
STC ST03<strong>01</strong>1AT dated 22 December 20<strong>04</strong><br />
As per DFS Change Approval Sheet DFS9664- Prior to installation of this modification it 08.05.2<strong>01</strong>2<br />
CAS Issue B dated 05.<strong>04</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
As per DFS Change Approval Sheet DFSD149-Prior<br />
to installation of this modification it 26.<strong>04</strong>.2<strong>01</strong>2<br />
CAS Issue A dated 07 March 2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.08.2<strong>01</strong>2<br />
F2000 and F2000EX aircraft equipped with<br />
WiFi equipments installationcompliant with<br />
prerequisite note DT-0<strong>01</strong>-12.<br />
Prior to installation of this modification it 02.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.06.2<strong>01</strong>1<br />
SANDEL mandatory SB 3400-09 to be<br />
incorporatedThe limitations as listed in FAA<br />
STC ST03<strong>01</strong>1AT apply.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 179/<strong>462</strong><br />
23.07.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5830 DECA AVIATION ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>919 REV 2 TCCA LSTC O-LSA06-056/D ISS1 DHC-6-300 Installation of an ASIRAS Radar System in a 1. DECA Aviation Flight Manual Supplement<br />
18.07.2007<br />
LIMITED<br />
DHC-6-300 aircraft in accordance with<br />
Modification Summary for ASIRIS Radar<br />
System Installation, DECA Aviation<br />
Engineering Limited document DCP 05259,<br />
Revision 2, dated 14/12/05 or later <strong>EASA</strong><br />
approved revision<br />
FMS05259, Revision 1, is required<br />
10<strong>01</strong>6112 DECA AVIATION ENGINEERING <strong>EASA</strong>.IM.A.S.02302 TCCA STC O-LSA02-397/D ISS 2 A320-214 Installation Of 180 Passenger - All Economy 1. As per Transport Canada STC O-LSA02-<br />
10.05.2007<br />
LIMITED<br />
Class Seating Arrangement, in accordance 397/D Issue 2.2. This STC is approved only<br />
with Transport Canada STC O LSA02-397/D for the product configuration as defined in the<br />
Issue 2<br />
approved design data referred to in the<br />
paragraphs "Description" and “Associated<br />
Technical Documentation”. Compatibility<br />
10<strong>01</strong>6342 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10<strong>01</strong>6431 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10<strong>01</strong>6482 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10027141 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10029659 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10029922 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10030614 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10032064 DECA AVIATION ENGINEERING<br />
LIMITED<br />
<strong>EASA</strong>.IM.A.S.02656 REV. 1 TCCA SA00-98 ISSUE 4 BD-700-1A10 Baggage Door Locking System Modification. 23.<strong>04</strong>.2008<br />
<strong>EASA</strong>.IM.A.S.02771 REV 1 TCCA STC O-LSA07-260/D ISSUE 2 BOMBARDIER BD-700-1A10 Cabin Interior Reconfiguration. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.02836 TC STC O-LSA08-069/D BOMBARDIER DHC-6-300 Radar System Installation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
REV. 1 TCCA SA00-126; CAA NL SA0<strong>01</strong>4NL DHC-8-102, -103, -106<br />
DHC-8-2<strong>01</strong>, -202<br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
QAR/ASAP Monitoring SystemTCCA SA00-<br />
126, Is. 4<br />
TCCA LSTC O-LSA09-37/D B737-800 Interior Reconfiguration & miscelaneous Cabin<br />
Alterations /Modification and relocation of the<br />
passenger seats along<br />
withrelocation/installation of emergency<br />
equipments.<br />
TCCA LSTC O-LSA09-<strong>04</strong>0/D B737-800 Sliding Carpet Loading System Removal/<br />
Deactivation<br />
TCCA STC O-LSA06-007/D B737-800 Passenger Seating Arrangement - Installation /<br />
Relocation of passengerSeats in 186-189 Pax<br />
Configuration and installation of<br />
EmergencyEquipments<br />
TCCA STC O-LSA10-43 DHC-6-300 Radar Antenna Installation - Structural<br />
Provisions i.a.w. TCCA STCO-LSA10-<strong>04</strong>3/D<br />
The QAR system configurations are<br />
compatible with each of the<br />
followingFDR/FDAU combinations: For Model<br />
DHC -8- 102, -103, -106, -2<strong>01</strong>, -202L3 FDR<br />
No: 2100-4<strong>04</strong>3-00 with Plessey FDAU No:<br />
612/1/49780/102 (ModelPA3810Bl/Post Mod<br />
8/1876). For Model DHC -8 -3<strong>01</strong>,<br />
12.11.2008<br />
12.11.2008<br />
1. Prior to installation of this modification <strong>04</strong>.<strong>01</strong>.2<strong>01</strong>0<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
Valid for MSN 30292 only None 09.<strong>04</strong>.2<strong>01</strong>0<br />
Valid for MSN30292 and 33029 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2<strong>01</strong>0<br />
Only valid for MSN 28373, 28375, 29351,<br />
29642, 29883, 30637, 30671,33003, 33029,<br />
33699, 347<strong>04</strong>, 35093<br />
a) For serial number 235 only.b) Flight in kwon<br />
icing conditions are not approved.<br />
Prior to installation of this modification it 25.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 06.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 180/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10033224 DECA AVIATION ENGINEERING<br />
O-LSA07-225/D,ISSUE 1 P-180 AVANTI II TCA STC No. O-LSA07-225/D Issue 1 "Import None Prior to installation of this modification it <strong>04</strong>.<strong>01</strong>.2<strong>01</strong>1<br />
LIMITED<br />
Configuration - InteriorCompletion (including<br />
must be determined thatthe<br />
various cabin installations)"<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038463 DECA AVIATION ENGINEERING<br />
LIMITED<br />
10<strong>04</strong>0912 DECA AVIATION ENGINEERING<br />
LIMITED<br />
TCCA STC NO. O-LSA09-344/D CL-600-2B19 Iridium Antenna Installation. Restricted to ASN 8092. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.02.2<strong>01</strong>2<br />
REV. 1 TCCA STC NO. O-LSA00-829/D BD-700-1A10 Baggage Door Locking System Modification Restricted to ASN 9003 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.08.2<strong>01</strong>2<br />
10<strong>01</strong>5489 DECA AVIATION ENGINEERING LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>251 - A321-211, SN 675 Interior reconfiguration 20J/152 Y seating<br />
arrangement<br />
10<strong>01</strong>5492 DECA AVIATION ENGINEERING LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>254 TCCA STC O-LSA<strong>04</strong>-008/D A320-232 Passenger Seat Cushion Assembly<br />
Replacement on B/E Aerospace, seat typ:<br />
D3111F11xx-<strong>01</strong> series<br />
10<strong>01</strong>5493 DECA AVIATION ENGINEERING LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>255 TCCA STC O-LSA05-<strong>01</strong>8/D A320-232 Reconfiguration of existing 180 passenger all<br />
economy seating arrangement<br />
10<strong>01</strong>5494 DECA AVIATION ENGINEERING LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>256 TCCA STC O-LSA02-327/D A319-112, A320-211, A320-212,<br />
A320-214, A320-231, A320-232<br />
Flight Warning Computer Altitude Callout<br />
Reconfiguration<br />
1. This STC is limited to A321 MSN 675.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
18.07.2005<br />
1. This STC is limited to the A320 MSN 496. 18.10.2005<br />
1. This STC is limited to the A320 MSN<br />
496.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall be<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5587 DECA AVIATION ENGINEERING LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>498 TCCA STC O-LSA<strong>01</strong>-428/D ISS3 A320-232 Emergency exit sign Relocation 1) Limited to the A320 MSN 4962) This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the i<br />
10<strong>01</strong>5791 DECA AVIATION ENGINEERING LTD <strong>EASA</strong>.IM.A.S.<strong>01</strong>849 TCCA LSTC O-LSA02-653/D ISS 3 A318-112, A320-214 Passenger seat leather dress cover<br />
replacement<br />
10<strong>01</strong>6241 DECRANE AEROSPACE PATS<br />
<strong>EASA</strong>.IM.A.S.02513 REV. 1 FAA STC ST00741LA-D BOEING 737-700 Installation of Canadian Marconi CMA-21<strong>01</strong><br />
AIRCRAFT,<br />
High Gain SATCOM Antenna. This STC<br />
revises and supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.IM.A.S.02513. The revisionwas issued<br />
to reflect the transfer from Hollingshead<br />
International toDecrane Aerospace PATS<br />
Aircraft.<br />
10<strong>01</strong>6649 DECRANE AEROSPACE PATS<br />
AIRCRAFT,<br />
<strong>EASA</strong>.IM.A.S.03093 REV. 1 FAA STC ST02057LA BOEING 737-700 SERIES<br />
BOEING 737-800 SERIES<br />
Installation of Electronic Equipment Rack in Aft<br />
Bulk Cargo Compartment. This STC revises<br />
and supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.IM.A.S.03093. The revisionwas issued<br />
to reflect the transfer from Hollingshead<br />
International toDecrane Aerospace PATS<br />
Aircraft.<br />
18.10.2005<br />
18.10.2005<br />
25.10.2005<br />
This STC is limited to: A319 MSN 1846, A319<br />
MSN 1598 and A320 MSN 1686<br />
12.05.2006<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.The ins<br />
18.11.2009<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.The ins<br />
18.11.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 181/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10026943 DECRANE AEROSPACE PATS<br />
P-<br />
B737-800 Installation of Auxiliary Fuel System in the None. - Prior to installation of this modification 26.08.2009<br />
AIRCRAFT,<br />
<strong>EASA</strong>.IM.A.S.03257<br />
forward and aft cargocompartments.Validation<br />
the installer mustdetermine that the<br />
of STC ST<strong>01</strong>713NY-D as amended June 29,<br />
interrelationship between this modification<br />
2009<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.- The install<br />
10027297 DECRANE AEROSPACE PATS<br />
AIRCRAFT,<br />
10027298 DECRANE AEROSPACE PATS<br />
AIRCRAFT,<br />
10027299 DECRANE AEROSPACE PATS<br />
AIRCRAFT,<br />
10028092 DECRANE AEROSPACE PATS<br />
AIRCRAFT,<br />
10028093 DECRANE AEROSPACE PATS<br />
AIRCRAFT,<br />
<strong>EASA</strong>.IM.A.S.03026 REV. 3 FAA STC ST<strong>01</strong>727NY-D ERJ 190-100ECJ Major Change to FAA STC ST<strong>01</strong>727NY-D:<br />
Project DAS-GED-P072 / ODA-GED-0<strong>01</strong>-<br />
Installation of Executive Interior (A/C #4)<br />
<strong>EASA</strong>.IM.A.S.03027 REV. 1 FAA STC ST<strong>01</strong>728NY-D ERJ 190-100ECJ Major Change to FAA STC ST<strong>01</strong>728NY-D:<br />
DAS-GED-P067 - Modification of theClass C<br />
Forward Cargo Compartment<br />
<strong>EASA</strong>.IM.A.S.03028 REV. 1 FAA STC ST<strong>01</strong>729NY-D ERJ 190-100ECJ ST<strong>01</strong>729NY-D: Installation of a Passenger<br />
Gaseous Oxygen Supply System<br />
10<strong>01</strong>5980 DEL-AIR <strong>EASA</strong>.IM.A.S.02132 FAA STC SA5733SW CESSNA 150<br />
CESSNA 150A<br />
CESSNA 150B<br />
CESSNA 150C<br />
CESSNA 150D<br />
CESSNA 150E<br />
CESSNA 150F<br />
CESSNA 150G<br />
CESSNA 150H<br />
CESSNA 150L<br />
CESSNA 150M<br />
CESSNA 152<br />
CESSNA A152<br />
FAA STC ST0<strong>04</strong>05LA-D 737-700 IGW Alteration of Fire Protection Systems, Lower<br />
Cargo Compartments. This STC revises and<br />
supersedes LBA STC LBA.21NE1.TA0682.<br />
The revisionwas issued to reflect the transfer<br />
from Hollingshead International toDecrane<br />
Aerospace PATS Aircraft.<br />
FAA STC ST<strong>01</strong>184LA B737-800 Alteration of Fire Protection Systems, Lower<br />
Cargo Compartments. This STC revises and<br />
supersedes LBA STC LBA.21NE1.TA0511.<br />
The revisionwas issued to reflect the transfer<br />
from Hollingshead International toDecrane<br />
Aerospace PATS Aircraft.<br />
Configuration 1: - Concurrent installation of<br />
STC ST<strong>01</strong>728NY-D (Class "C"<br />
CargoCompartment) iaw. Master Drawing List<br />
6071-0000-MDL Rev. IR dtd.7.October 2008 is<br />
required. -Commercial operation under <strong>EASA</strong><br />
rules requires installation of PATS<br />
SBST<strong>01</strong>72NY-D-25-S<br />
Configuration 1: - Concurrent installation of<br />
STC ST<strong>01</strong>727NY-D (Installation of<br />
anExecutive Interior) iaw. Master Drawing List<br />
5950-0000-MDL revision Gdtd. 16.April 2009 is<br />
required Configuration 2: - Concurrent<br />
installation of STC ST<strong>01</strong>727NY-D (Installation<br />
Not Applicable 26.03.2<strong>01</strong>0<br />
Not Applicable 18.09.2009<br />
- Concurrent installation of STC's ST<strong>01</strong>727NY- Not Applicable<br />
D (Installation of anExecutive Interior) and<br />
ST<strong>01</strong>728NY-D (Class "C" Cargo<br />
Compartment) isrequired - For aircraft under<br />
FAA jurisdiction this modification may not<br />
beinstalled after 30.August 2<strong>01</strong>0 unless:(1)<br />
previ<br />
18.09.2009<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.The ins<br />
18.11.2009<br />
Installation of Longe Range Wing Fuel Tanks 1. If the holder agrees to permit another<br />
person to use this certificate to alter the<br />
product, the holder shall give the other person<br />
written evidence of that permission.2. This<br />
STC is approved only for the product<br />
configuration as defined in the app<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.The ins<br />
18.11.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 182/<strong>462</strong><br />
14.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5984 DEL-AIR <strong>EASA</strong>.IM.A.S.02136 FAA STC SA<strong>01</strong>388SE CESSNA 170A<br />
Installation of a 7 Gallon extended range tank in This STC is approved only for the product<br />
18.09.2006<br />
CESSNA 170B<br />
each wing.<br />
configuration as defined in the approved design<br />
CESSNA 172<br />
data referred to in the paragraph "Description".<br />
CESSNA 172A<br />
Compatibility with other aircraft/engine<br />
CESSNA 172B<br />
configurations shall be determined by the<br />
CESSNA 172C<br />
CESSNA 172D<br />
CESSNA 172E<br />
CESSNA 172F<br />
CESSNA 172G<br />
CESSNA 172H<br />
CESSNA 172I<br />
CESSNA 172J<br />
CESSNA 172K<br />
CESSNA 172L<br />
CESSNA 172M<br />
CESSNA 172N<br />
CESSNA 172P<br />
installer.<br />
10<strong>01</strong>5503 DELASTEK AERONAUTIQUE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>266 TCCA STC SA<strong>04</strong>-116 ISSUE 1 BOMBARDIER CL-600-2B19 Installation of Delastek Bleed Lead Monitoring For s/n 7003 through 7212 Bombardier Service<br />
23.07.2007<br />
(SERIES<br />
System p/n DK-329-0<strong>01</strong>.<br />
Bulletin 6<strong>01</strong>R-30-022 Part C must be<br />
integrated prior to the installation.<br />
10<strong>01</strong>5800 DELTA AIR LINES, INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>864 SA3305SO BOEING 767-200 Installation of a Delta modified forward trunnion<br />
bearing housing & a Delta manufactured<br />
bearing retainer bolt to allow forced lubrication<br />
of the respective joints.<br />
<strong>01</strong>.06.2006<br />
10<strong>01</strong>5363 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.00677 REV. 1 FAA STC ST<strong>01</strong>523SE BOEING 747-400 1. Configuration 1:Installation of Interior 1. The approval holder shall fulfill the<br />
09.09.2008<br />
Components in accordance with Delta obligations of Part 21, Paragraph 21 .Al 09;2.<br />
Engineering Master Data List <strong>01</strong>07-05983- Configuration 1:- This STC must be installed<br />
2128, Revision A, dated March 26, 2007 or concurrent with Jamco America ST<strong>01</strong>455SE,<br />
later DAS approved;2. Configuration EJM Aerospace Services ST03078AT, STG<br />
2:Installation of Interior Components in<br />
accordance<br />
Aerospace ST02993AT and Boeing Serv<br />
10<strong>01</strong>5393 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>094 REV. 2 FAA STC ST<strong>01</strong>507SE BOEING 747-400 Description of Design Change:Installation of 1.This STC is approved only for the product<br />
<strong>01</strong>.11.2007<br />
Interior Equipment:1.ConfigurationInstallation of configuration as defined in the approved design<br />
interior components in accordance with Health data referred to in the paragraph "Description".<br />
Tecna, Inc. Drawing List HPD-DL-55, Rev. BF, Compatibility with other aircraft/engine<br />
dated February 11, 2005 or later approved configurations shall be determined by the<br />
revision.2.ConfigurationMod<br />
installer.2.Configuration 1:TThi<br />
10<strong>01</strong>5421 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>151 FAA STC ST<strong>01</strong>895NY DC-9-87 (MD-87)<br />
MD-88<br />
10<strong>01</strong>5443 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>183 FAA STC ST<strong>01</strong>310NY AEROSPATIALE ATR 42-200<br />
AEROSPATIALE ATR 42-300<br />
AEROSPATIALE ATR 42-320<br />
AEROSPATIALE ATR 42-500<br />
AEROSPATIALE ATR 72-1<strong>01</strong><br />
AEROSPATIALE ATR 72-102<br />
AEROSPATIALE ATR 72-2<strong>01</strong><br />
AEROSPATIALE ATR 72-202<br />
AEROSPATIALE ATR 72-211<br />
AEROSPATIALE ATR 72-212<br />
AEROSPATIALE ATR 72-212A<br />
Validation of FAA STC No<br />
ST<strong>01</strong>895NY.Replacement of Dual<br />
Transponders with ACSS 7517800-10005<br />
ATDL Transponders with ELS and Gobles<br />
G7490-58 Control Head.<br />
Configuration 1: Installation of Delta<br />
Engineering sensors, brackets and wiring<br />
harnesses in accordance with Delta<br />
Engineering Master Drawing List <strong>01</strong><strong>01</strong>-<strong>04</strong>808-<br />
2030 revision F dated August 5,<br />
20<strong>04</strong>Configuration 2: Installation of the SFIM<br />
Inc. Auxiliary Fligh<br />
1. This installation does not include EHS or<br />
ADS-B functionality.The Delta Engineering<br />
MMS No 0758-05312-2076 dated 19 April<br />
20<strong>04</strong> is required.<br />
1. Configuration 1; this approval is for structural<br />
provisions only2. Configuration1 is required for<br />
Configuration 23.This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description".<br />
10<strong>01</strong>6039 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02208 REV. 1 FAA STC ST02223NY-D BOEING 767-200 Heath Tecna NuLook Interior 17.09.2007<br />
10<strong>01</strong>6094 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02283 FAA STC ST02227NY-D AIRBUS A340-300 Panasonic Aviation Corporation System 3000i ¿ Delta Engineering Instructions for<br />
05.07.2007<br />
IFE Installation /Installation of a Panasonic Continued Airworthiness, Ref. No. 0752-05945-<br />
Avionics Corporation System 3000i In- 2135 Revision A, dated March 8th 2007.¿<br />
FlightPassenger Entertainment System with Delta Engineering Airplane Flight Manual<br />
Astronics Empower ® In-Seat PowerSupply Supplement, Ref. No. 0652-06023-2135,<br />
System in accordance with Delta Engineering dated June 21st 2007.¿ Cabin configuration<br />
Mas<br />
mus<br />
10<strong>01</strong>6134 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02330 FAA ST<strong>01</strong>767NY BOEING 747-200 Update of seat components for System 2000E This STC is approved only for the product<br />
per DAS project DAS-2056-03 on a B747-400. configuration as defined in the approved design<br />
data. Compatibilitty with other aircraft/engine<br />
configuraitons shall be determined by the<br />
installer.<br />
25.03.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 183/<strong>462</strong><br />
22.07.2005<br />
30.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6280 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02572 FAA STC ST02393NY-D BOEING 747-400 Installation of Heath Tecna Cabin Interior 1. TGL 12 complied with.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworth<br />
09.10.2007<br />
10<strong>01</strong>6318 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02624 REV. 1 FAA STC ST024<strong>04</strong>NY-D B767-300 Installation of Panasonic Avionics Overhead In-<br />
Flight EntertainmentSystem<br />
10<strong>01</strong>6329 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02638 FAA STC ST02630NY BOEING 777-200 Heath Tecnica Interior Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6496 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02858 FAA STC ST02403NY-D BOEING 747-400 Installation of Seat In-Flight Entertainment<br />
Components and Software update in<br />
accordance with Delta Engineering Master<br />
Data List <strong>01</strong>07-06195-2172 Revision A, dated<br />
4 April 2008. Validation of FAA STC<br />
ST02403NY-D.<br />
10<strong>01</strong>6540 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.02917 FAA STC ST02402NY-D AIRBUS A320 Panasonic IFE a eFXInstallation of Panasonic<br />
eFX system<strong>EASA</strong> validation of FAA STC No.<br />
ST02402NY-D from 28. March 2008.<br />
Limited to installation on aircraft already fitted Prior to installation of this modification it 11.02.2<strong>01</strong>1<br />
with HeathTechnaNuLook interior<br />
must be determined thatthe<br />
(Configuration 4) ref <strong>EASA</strong> STC IM.A.S.02474 interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.1 The ins<br />
10<strong>01</strong>6675 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.03182 FAA STC ST02215NY-D BOEING 747-400 SERIES Installation of Panasonic Avionics Corporation 1. Delta Engineering Instructions for Continued<br />
System 3000i In-Flight Entertainment System Airworthiness 0707-05814-2121 Rev. A dated<br />
in accordance with Delta Engineering Master Aug 31, 2006 are required with this installation.<br />
Data List <strong>01</strong>07-05809-2121 Rev. A dated Nov. 2. The cabin configuration of the seats installed<br />
15, 2006 or later approved revisionsValidation in accordance with KLM LOPA KLM3H112780<br />
of FAA STC ST02215NY-D<br />
Revision ORG is required<br />
10027744 DELTA ENGINEERING CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03198<br />
10027745 DELTA ENGINEERING CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03199<br />
10027746 DELTA ENGINEERING CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03200<br />
REV. 1 FAA STC ST02643NY-D A340-300 Update of a Panasonic System 2000E In-Flight<br />
PassengerEntertainment System to a System<br />
2000E HybridMajor Change to the <strong>EASA</strong> STC<br />
10027744 to remove EWIS limitation<br />
REV. 1 FAA STC ST02642NY-D A330-200 Update of a Panasonic System 2000E In-Flight<br />
PassengerEntertainment System to a System<br />
2000E HybridMajor Change to the <strong>EASA</strong> STC<br />
10027746 to remove EWIS limitation<br />
REV. 1 FAA STC ST02642NY-D A330-200 Update of a Panasonic System 2000E In-Flight<br />
PassengerEntertainment System to a System<br />
2000E HybridMajor Change to the <strong>EASA</strong> STC<br />
10027746 to remove EWIS limitation<br />
15.12.2008<br />
14.08.2008<br />
16.07.2008<br />
18.06.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.<strong>04</strong>.2<strong>01</strong>2<br />
The STC holder shall provide by 7th June 2<strong>01</strong>0 Prior to installation of this modification the <strong>04</strong>.<strong>04</strong>.2<strong>01</strong>2<br />
Instructions for ContinuedAirworthiness on installer must determinethat the<br />
Electrical Wiring Interconnection System - interrelationship between this modification<br />
EWIS ICA -in accordance with Special and any otherpreviously installed<br />
Condition H-<strong>01</strong> "Enhanced<br />
modification will introduce no adverse<br />
AirworthinessProgramme for Aeroplane effect uponthe airworthiness of the<br />
Systems - ICA on EWIS".<br />
product.The installatio<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.<strong>04</strong>.2<strong>01</strong>2<br />
10029<strong>01</strong>1 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.03196 FAA STC ST<strong>01</strong>483NY BOEING 747-400 SERIES 23.07.2009<br />
10029<strong>01</strong>2 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.03197 FAA STC ST<strong>01</strong>519NY BOEING 747-400 SERIES 23.07.2009<br />
10029<strong>01</strong>3 DELTA ENGINEERING CORPORATION <strong>EASA</strong>.IM.A.S.03195 FAA STC ST<strong>01</strong>482NY BOEING 747-400 SERIES 21.07.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 184/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030<strong>01</strong>1 DELTA ENGINEERING CORPORATION REV. 1 FAA STC ST02654NY-D B757-300 Installation of Panasonic Avionics Corporation Finnair Minor Modifications (<strong>EASA</strong>.21J.263) Prior to installation of this modification it 25.<strong>01</strong>.2<strong>01</strong>1<br />
System Digital MPES IIPassenger<br />
EO 15330FR 1 and EO 15383 Fmust be must be determined thatthe<br />
Entertainment System.<br />
installed prior to or concurrent with the interrelationship between this modification<br />
installation of thisSTC.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10031836 DELTA ENGINEERING CORPORATION FAA STC ST02755NY A330-300 Update of a Panasonic System eX2 In-Flight<br />
Passenger EntertainmentSystem<br />
10033290 DELTA ENGINEERING CORPORATION FAA STC ST<strong>01</strong>662NY B747-400 Modification of existing Mode S Transponders This approval is for the replacement of the<br />
& TCAS by installation ofHoneywell/ACSS P/N Transponder Units and TCAS.This approval<br />
7517800-100<strong>04</strong> ATDL Transponders & does not include the transponder and TCAS<br />
4066<strong>01</strong>0-910 TCAS inaccordance with Delta system, wiring,trays, antennas, structural<br />
Engineering Master Drawing List <strong>01</strong>07-05185-<br />
2059,Rev A, dated April 18,2003.Validation of<br />
FAA<br />
provisions, etc.<br />
10033430 DELTA ENGINEERING CORPORATION FAA STC ST02647NY-D ATR 42-200, ATR 42-300,<br />
ATR 42-320, ATR 42-400,<br />
ATR 42-500, ATR 72-1<strong>01</strong>,<br />
ATR 72-102, ATR 72-2<strong>01</strong>,<br />
ATR 72-202, ATR 72-211,<br />
ATR 72-212, ATR 72-212 A<br />
<strong>EASA</strong> validation of FAA STC ST02647NY-D<br />
(as amended by FAA on August31st, 2<strong>01</strong>0)<br />
regarding:Installation of Delta Engineering<br />
Synchro’s in accordance with DeltaEngineering<br />
Master Data List <strong>01</strong><strong>01</strong>-06413-2166 Revision A<br />
dated January13th, 2<strong>01</strong>0 or later approved r<br />
Not applicable The Panasonic System eX2 must<br />
interface with the following listedrequired<br />
existing components/systems that are not<br />
approved by this STCand approved<br />
under the <strong>EASA</strong> STC "10031815" of<br />
Flight Structures Inc.:1. Cabin<br />
Configuration2. Structural Provisions for<br />
V<br />
17.09.2<strong>01</strong>0<br />
Delta Engineering Maintenance Manual<br />
Supplement Doc. No.0707-05223-2059,<br />
dated February 12, 2003 is required for<br />
thismodification<br />
11.<strong>01</strong>.2<strong>01</strong>1<br />
See those of original FAA STC ST02647NY-D. Prior to installation of this modification it 19.<strong>01</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10033596 DELTA ENGINEERING CORPORATION P-<br />
FAA STC ST00988NY-D BOEING 747-400 Installation of Matsushita Avionics Systems Maintenance Manual Supplement for 747-400 Prior to installation of this modification the 30.07.2009<br />
<strong>EASA</strong>.IM.A.S.03098<br />
Corporation 2000E with AVOD1.5 Cabin with Matsushita AvionicsSystems Corporation installer must determinethat the<br />
Entertainment System in accordance with 2000E Cabin Entertainment System, Delta interrelationship between this modification<br />
Delta Engineering,L.P. Master Drawing List EngineeringDoc. No. 707-<strong>04</strong>403-250, must be and any otherpreviously installed<br />
107-<strong>04</strong>323-250, Revision C, dated Sept. 24, incorporated into the operator’smaintenance modification will introduce no adverse<br />
1999or later FAA approved revisions.Validation instructions.<br />
effect uponthe airworthiness of the<br />
of<br />
product.The installatio<br />
10036548 DELTA ENGINEERING CORPORATION REV. 1 FAA STC ST02668NY-D A330-3<strong>01</strong>, -302, -303<br />
Provision of a Panasonic Ex Phone<br />
This STC approval only certifies the provisions Prior to installation of this modification it 10.11.2<strong>01</strong>1<br />
A330-321, -322, -323<br />
System(Validation of FAA STC ST02668NY- for the PanasoniceXPhone. This device must be determined thatthe<br />
A330-341, -342, -343<br />
D)This STC installs provisions (antenna and activation, for which these provisions<br />
interrelationship between this modification<br />
wiring) for Panasonic eX phoneSystem. The areintended, will be certified separately. and any other previouslyinstalled<br />
Revision 1 of this STC corrects the applicability<br />
modification and/ or repair will introduce<br />
by adding twoaircraft models, omitted at the in<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037166 DELTA ENGINEERING CORPORATION A330-3<strong>01</strong>, A330-302, A330-303<br />
A330-321, A330-322, A330-323<br />
A330-341, A330-342, A330-343<br />
10037167 DELTA ENGINEERING CORPORATION REV. 1 FAA STC ST02884NY-D A330-2<strong>01</strong> / -202 / -203<br />
A330-223 / -243<br />
A330-3<strong>01</strong> / -302 / -303<br />
A330-321 / -322 / -323<br />
A330-341 / -342 / -343<br />
Panasonic Global Communication System -<br />
System installationThis STC covers the<br />
installation of Panasonic Global<br />
CommunicationSystem (GCS) and activates<br />
the wireless portion.<br />
Panasonic Global Communication System -<br />
Antenna installation This STC installs a large<br />
antenna for the future use of Panasonic<br />
GlobalCommunication System (GCS), on A330-<br />
300 aircraft models.Revision 1 of this STC<br />
extends the applicability to the A330-200air<br />
10037970 DELTA ENGINEERING CORPORATION FAA STC ST02888NY-D 777-300ER STC ST02888NY-D: Activation of Panasonic<br />
nMAP's (Wi-Fi)<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
07.11.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.03.2<strong>01</strong>2<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.<strong>01</strong>.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 185/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038251 DELTA ENGINEERING CORPORATION FAA STC ST02890NY-D A319 Installation of Panasonic Global<br />
None Prior to installation of this modification it <strong>01</strong>.02.2<strong>01</strong>2<br />
Communication System Antenna<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10038944 DELTA ENGINEERING CORPORATION FAA STC ST02889NY-D A330-2<strong>01</strong>, -202, -203<br />
A330-223, -243<br />
Panasonic Global Communication System -<br />
System installation This STC installs of<br />
Panasonic Global Communication System<br />
(GCS) andactivate the wireless portion.<br />
10<strong>04</strong><strong>01</strong>02 DELTA ENGINEERING CORPORATION REV. 1 FAA STC ST02903NY-D B747-400 Installation of Panasonic eX2 In-Flight<br />
Entertainment system witheXPhone in<br />
accordance with Delta Engineering Master<br />
Data list<strong>01</strong>07-07608-2280 Rev. E, dated<br />
September 13, 2<strong>01</strong>2 or later FAA<br />
approvedrevisions.Validation of FAA STC<br />
ST02903NY-D.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.03.2<strong>01</strong>2<br />
The Panasonic eXPhone system must The Instructions for Continued<br />
30.10.2<strong>01</strong>2<br />
interface with the following<br />
Airworthiness, Electrical<br />
existingsystems/components which must be WiringInterconnect System Instructions<br />
installed in a manner acceptable to<br />
for Continued Airworthiness andAirplane<br />
theauthorities. The below listed required Flight Manual Supplement as listed on<br />
existing systems are not approvedby this STC. the Master Data List arerequired with this<br />
Required Supplemental Type C<br />
installation. Prior to installation of<br />
10<strong>04</strong>0214 DELTA ENGINEERING CORPORATION FAA STC ST029<strong>01</strong>NY-D B747-400 Installation of a Panasonic eX2 In-Flight None The Instructions for Continued<br />
18.06.2<strong>01</strong>2<br />
Entertainment System inaccordance with Delta<br />
Airworthiness and Electrical<br />
Engineering Master Data List <strong>01</strong>07-07459-<br />
WiringInterconnect System Instructions<br />
2283Revision B, dated May 9, 2<strong>01</strong>2 or later<br />
for Continued Airworthiness as listedon<br />
FAA approved revisionsValidation of FAA STC<br />
the Master Data List are required with this<br />
ST029<strong>01</strong>NY-D<br />
installation.FAA STC ST02227SE, <strong>EASA</strong><br />
approval 10039535, must be installed<br />
10<strong>04</strong>1776 DELTA ENGINEERING CORPORATION FAA STC ST02714NY-D 737-600, 737-700, 737-700C,<br />
737-800, 737-900, 737-900ER<br />
Installation of provisions for dual NavAero<br />
Electronic Flight Bags withNavaero Mount.<br />
10<strong>04</strong>2191 DELTA ENGINEERING CORPORATION FAA STC ST02<strong>04</strong>9NY B747-400 Installation of Panasonic Avionics Corporation<br />
System 3000i PassengerEntertainment System<br />
in accordance with Delta Engineering Master<br />
DrawingList <strong>01</strong>07-05381-2073, Revision D,<br />
dated June 08, 2005 or later approvedrevision.<br />
Validation of FAA STC ST02<strong>04</strong>9NY.<br />
10<strong>04</strong>2528 DELTA ENGINEERING CORPORATION FAA STC ST003056CH 737-800 Validation of FAA STC ST003056CH:<br />
Installation of Panasonic<br />
GlobalCommunications suite (GCS) System<br />
Provisions in accordance withArmstrong<br />
Aerospace Master Data List DC1<strong>04</strong>-9<strong>04</strong>1-00,<br />
Revision B, dated 22September 2<strong>01</strong>1.Revision<br />
1: Transfer of STC from Armstro<br />
10<strong>04</strong>2791 DELTA ENGINEERING CORPORATION FAA ST02926NY-D A330-2<strong>01</strong>, A330-202<br />
A330-203, A330-223<br />
A330-243<br />
10<strong>01</strong>5483 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.A.S.<strong>01</strong>243 FAA STC ST09191AC BOEING 737-200<br />
BOEING 737-200C<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Provisions for Panasonic Global<br />
Communication System: This project covers<br />
the installation and deactivation of a<br />
PanasonicGlobal Communication Suite (GCS)<br />
and Cell Modem on Airbus A330-200.<br />
Theactivation of the equipment installed is not<br />
cover by this proj<br />
InInstallation of DeVore Wing Forward Position<br />
Light Assembly according to FAA STC<br />
ST09191AC<br />
Only for Installation of NavAero Mount<br />
("Configuration 2").The installation of ECS<br />
Mount ("Configuration 1") is not certified.<br />
Prior to installation of this modification it 15.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon theairworthiness<br />
of the product.<br />
None. STC ST<strong>01</strong>492SE is required to be<br />
installed as a prerequisite<br />
foraccomplishing this STC. The<br />
Instructions for Continued Airworthiness<br />
as listed on the MasterData List are<br />
required with this installation. Prior to<br />
installation of this modification it must be<br />
1) The Panasonic Global Communication Suite<br />
System for which theseprovisions are installed<br />
and these provisions activated in<br />
accordancewith a separate STC, <strong>EASA</strong> STC<br />
10038436.2) The aircraft operator must<br />
perform the instructions for<br />
continuedairworthiness<br />
This approval does not cover the activation of<br />
the components installed.The wiring related to<br />
this modification must not be connected and<br />
mustbe properly stowed in order to assure that<br />
the equipment installed isnot energized.<br />
1. According to Limitations Section of FAA<br />
STC ST09191AC2. This STC is approved only<br />
for the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations sh<br />
14.11.2<strong>01</strong>2<br />
Prior to installation of this STC it must be 07.12.2<strong>01</strong>2<br />
determined that theinterrelationship<br />
between this STC and any other<br />
previously installedSTC, modification and<br />
/ or repair will introduce no adverse effect<br />
uponthe airworthiness of the product.<br />
Prior to installation of this modification it 18.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 186/<strong>462</strong><br />
25.10.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5937 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.A.S.02078 REV 1 FAA STC SA7473SW BOEING 757 Installation of tail floodlights in accordance with<br />
DeVore Drawing No. 757000<strong>01</strong>, Rev B, dated<br />
September 14, 1988, or later FAA approved<br />
revision.<br />
02.<strong>04</strong>.2007<br />
10<strong>01</strong>5947 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.A.S.02089 SA998EA BOMBARDIER DHC-6 SERIES Installation of Engine Fuel Drain Recirculation<br />
18.10.2006<br />
100<br />
BOMBARDIER DHC-6 SERIES<br />
200<br />
BOMBARDIER DHC-6 SERIES<br />
300<br />
System<br />
10<strong>01</strong>6743 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.R.S.<strong>01</strong>069 FAA STC SH4694SW S-76A/B/C Installation of Under Fuselage forward facing This STC is approved only for the product<br />
31.05.2006<br />
recognitionn lights and rotor disc lights configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6744 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.R.S.<strong>01</strong>070 FAA STC SH5867SW AS 365N/N1/N2, EC 155B/B1 Installation of Tail Floodlights and Associated 1. This STC is approved only for the product<br />
21.06.2005<br />
Technical Documentation Devore Drawing List configuration as defined in the approved design<br />
365000<strong>01</strong> Revision J dated March 16 data referred to in the paragraph "Description".<br />
1999DCN F-1 dated February 8 1989 & DCN L-Compatibility<br />
with other aircraft/engine<br />
1 dated October 22 20<strong>01</strong> or later approved configurations shall be determined by the<br />
revision<br />
installer.<br />
10<strong>01</strong>6745 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.R.S.<strong>01</strong>071 FAA STC SH5866SW AS 365N/N1/N2, EC 155B/B1 Installation of Forward Facing Recognition 1. This STC is approved only for the product<br />
21.06.2005<br />
Lights<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6746 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.R.S.<strong>01</strong>072 FAA STC SH7579SW AS 365N1/N2/N3, EC 155B/B1 Installation of a rotor disc light and associated 1. This STC is approved only for the product<br />
22.06.2005<br />
DeVore Aviation Corporation Top Drawing- configuration as defined in the approved design<br />
Rotor Disc Light Inspection;<br />
data referred to in the paragraph "Description".<br />
AerospatialeDauphin Drawing 36500003 Compatibility with other aircraft/engine<br />
revision E dated August 21 20<strong>01</strong> or later configurations shall be determined by the<br />
approved revision DeVore Aviation<br />
Corporation RFM Supplem<br />
installer.<br />
10<strong>01</strong>7026 DEVORE AVIATION CORPORATION OF <strong>EASA</strong>.IM.R.S.<strong>01</strong>445 FAA STC SH3754SW Installation of DeVore forward facing<br />
recognitions lights<br />
<strong>01</strong>.07.2008<br />
10028007 DEVORE AVIATION CORPORATION OF FAA STC SR09557RC R44II Installation of Tail/Rotor, Forward Facing None Prior to installation of this modification it 24.11.2009<br />
Recognition and FuselageFloodlights in<br />
must be determined thatthe<br />
accordance with DeVore Aviation Corporation<br />
interrelationship between this modification<br />
DrawingNumber 440000<strong>01</strong>. This installation is<br />
and any other previouslyinstalled<br />
based on FAA STC SR09557RC.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6995 DIAMOND J, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>4<strong>04</strong> FAA STC NO. SR00031LB DATED MA BELL 206B<br />
BELL 206L<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
Installation of Analog/Digital Turbine Outlet<br />
Temperature (TOT) Indicator with Exceedance<br />
logging Capability. This STC has been<br />
classified as "Basic" by FAA and has been<br />
approved under the PTVP.<br />
10<strong>01</strong>5149 DIEHL SERVICE MODULES GmbH <strong>EASA</strong>.A.S.03509 REV 1 BOEING 777-200 Installation of Galleys and Closets on BAW<br />
B777-236, Kit P/N 190331-51<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any otherpreviously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The installa<br />
10<strong>01</strong>4433 DINAN AVIATION SIBA AVIONIQUE <strong>EASA</strong>.A.S.02481 PIPER PA-31T Modification SIBA MD<strong>01</strong>_2006Replacement of This STC is limited to: S/N 31T-7920094 F-<br />
one ATC mode C by Mode S and replacement GPBF<br />
of an old DME with adding an ATC antenna on<br />
the top of frame<br />
31.08.2006<br />
10030311 DINAN AVIATION SIBA AVIONIQUE PA28 R 2<strong>01</strong> T M05-2009 Rev. 0 modernisation du système<br />
de communication.<br />
None. None. 10.06.2<strong>01</strong>0<br />
10039614 DONICA INTERNATIONAL LIMITED REV. 1 MD-90-30 AE-DMR300 Digital Media Reproducer in lieu<br />
of existing Rockwell Collinsor Panasonic<br />
analogue Hi 8 video tape reproducer.<br />
05.03.2008<br />
24.11.2008<br />
None Amendment to the STC is required in<br />
order to extend applicability tothose types<br />
listed in the attached AML list. The<br />
amendment to the STCshall provide the<br />
installation instructions and ICA to<br />
supplement thecommon data package<br />
that is defined within Modific<br />
16.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 187/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7285 DRF STIFTUNG LUFTRETTUNG <strong>EASA</strong>.R.S.<strong>01</strong>533 EUROCOPTER DEUTSCHLAND Title: Installation of a L-3 SSCVR Cockpit 1. Prior to installation of this modification the<br />
<strong>04</strong>.05.2009<br />
BK117 B<br />
Voice RecorderDescription: Optional<br />
installer must determine that the<br />
Installation of a Cockpit Voice Recorder. The interrelationship between this modification and<br />
installation is in accordance with DRF change any other previously installed modification will<br />
no. 135, MDL MD-117-31-32-000<strong>01</strong>.<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10029942 DRF STIFTUNG LUFTRETTUNG MBB-BK 117 B-2, MBB-BK 117 C- Installation of Garmin GNS 530 FMS<br />
Not Applicable The approval holder shall fulfil the <strong>04</strong>.05.2<strong>01</strong>0<br />
1<br />
COM/NAV System and TCAS-1 Sky 899TCAS<br />
obligations of Part 21,<br />
Paragraph21A.118A. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
10031819 DRF STIFTUNG LUFTRETTUNG MBB-BK117B-2, MBB-BK117 C-1 Installation of second directional gyro None Prior to installation of this modification it 16.09.2<strong>01</strong>0<br />
systemInstallation of a second directional gyro<br />
must be determined thatthe<br />
system for IFR operation basedon DRF Major<br />
interrelationship between this modification<br />
Change Project 240 and defined in MD-117-34-<br />
and any other previouslyinstalled<br />
20-000<strong>01</strong>.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10033429 DRF STIFTUNG LUFTRETTUNG P-<strong>EASA</strong>.R.S.<strong>01</strong>563 BK117 C-1 Title: Installation of Modular Airborne Data<br />
Recording/AcquisitionSystem<br />
(MADRAS)Description: Optional Installation of<br />
a Cockpit Voice and Flight DataRecorder<br />
System. The installation is in accordance with<br />
DRF change no.111, MOL MD-117-31-<br />
32-00003 Re<br />
10<strong>04</strong>1970 DRF STIFTUNG LUFTRETTUNG MB BK 117 C-2 Installation of a TETRA Digital Radio System<br />
into a NVIS certifiedCockpit.<br />
10<strong>01</strong>6181 DRIESSEN AIRCRAFT INTERIOR<br />
SYSTEMS<br />
10<strong>01</strong>6292 DRIESSEN AIRCRAFT INTERIOR<br />
SYSTEMS<br />
10<strong>01</strong>6552 DRIESSEN AIRCRAFT INTERIOR<br />
SYSTEMS<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
23.06.2009<br />
Required premodification: <strong>EASA</strong> approval<br />
<strong>EASA</strong> 10034057 (ECD major changeE-1807).<br />
This rotorcraft employs Night Vision Imaging<br />
System lighting, commonlynamed NVIS<br />
lighting, that has been certified to ensure the<br />
aircraft iscompatible with night vision goggl<br />
<strong>EASA</strong>.IM.A.S.02410 FAA STC ST00826LA AIRBUS A340-300 Installation of Lower Deck Mobile Crewrest. 1. The limitations and conditions as<br />
referenced in FAA STC ST00826LA apply.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
The change has undergone NVIS 29.10.2<strong>01</strong>2<br />
compatibility engineering evaluation. Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will intr<br />
<strong>EASA</strong>.IM.A.S.02588 REV. 1 FAA STC ST00843LA BOEING 757-200 SERIES Galley installation. None. Prior to installation of this modification the 18.02.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
<strong>EASA</strong>.IM.A.S.02932 BOEING 747-200B<br />
BOEING 747-200C<br />
Installation of a TBO Container. The installation should not be incorporated in<br />
any aircraft unless it is determined that the<br />
relationship between this installationand any<br />
previously approved configuration will not<br />
introduce any adverse effect upon the<br />
Airworthiness of the Aircraft. The a<br />
10037862 DUGAN KINETICS, L.L.C. FAA STC ST02127SE DC-9-81/-82/-83/-87, MD-88 Thrust Reverser/Installation of ejector thrust<br />
reverser on Pratt &Whitney Turbofan JT8D-<br />
217, -217A, 217C or -219 Engines as per FAA<br />
STCST02127SE dated 08 Apr. 2<strong>01</strong>1.<br />
Refer to FAA STC ST02127SE. Refer to FAA STC ST02127SE. 03.<strong>01</strong>.2<strong>01</strong>2<br />
10<strong>01</strong>5358 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.00657 FAA STC ST00515WI LEARJET 35<br />
Installation of an Allied Signal CAS 67A Traffic 1. This STC is approved only for the product<br />
<strong>04</strong>.<strong>04</strong>.2005<br />
LEARJET 35A<br />
Alert & Collision Avoidance (TCAS II). (STC configuration as defined in the approved design<br />
LEARJET 36<br />
ST00515WI)<br />
data referred to in the paragraph "Description".<br />
LEARJET 36A<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5417 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>139 FAA STC ST00546WI LEARJET 60 Installation of a Universal Avionics Inc. UNS-1B 1. For certification basis refer to FAA TCDS<br />
11.<strong>04</strong>.2005<br />
FMS (Dual).<br />
A10CE.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 188/<strong>462</strong><br />
22.08.2007<br />
<strong>04</strong>.07.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5488 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>249 FAA STC ST0<strong>04</strong>52WI CESSNA 650 CITATION III Installation of the AlliedSignal CAS 67A TCAS This STC is approved only for the product<br />
13.03.2006<br />
CESSNA 650 CITATION IV II System<br />
configuration as defined in the approved design<br />
CESSNA 650 CITATION VII<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5505 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>268 ST00315WI LEARJET 60 Installation of Collins TCAS-94 i.a.w. Dok List<br />
10<strong>04</strong>5000<br />
07.02.2007<br />
10<strong>01</strong>5640 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>603 FAA STC ST0069WI BOMBARDIER CL-600-1A11 (CL- Installation of Honeywell TCZ-910 TCAS II & This STC is approved only for the product<br />
25.10.2005<br />
600<br />
XS-852 Mode S Transponder System configuration as defined in the approved design<br />
BOMBARDIER CL-600-2A12 (CL-<br />
data referred to in the paragraph "Description".<br />
6<strong>01</strong><br />
Compatibility with other aircraft/engine<br />
BOMBARDIER CL-600-2B16<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5742 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>766 FAA STC SA00894WI CESSNA 525 Installation of Honeywell CAS 67A TCAS II The call outs and their priority are to be<br />
26.<strong>01</strong>.2006<br />
System on Cessna 525. FAA Approval of STC confirmed as part of each installation.<br />
Nr. SA00894WI: 08 September 2000.<br />
10<strong>01</strong>5826 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>9<strong>04</strong> ST00932WI LEARJET 31<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
Installation of Universal Avionics TAWS None 11.05.2006<br />
10<strong>01</strong>5844 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>941 FAA STC SA2405CE-D GULFSTREAM 1125 WESATRD Installation of Garret Model GTCP36-150(W) This STC is approved only for the product<br />
25.10.2006<br />
ASTRA<br />
Auxiliary Power Unit used as nonessential configuration as defined in the approved design<br />
GULFSTREAM ASTRA/SPX Bleed Air source for on board electrical and data referred to in the paragraph "Description".<br />
enviromental systems.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5917 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02<strong>04</strong>9 FAA STC ST00865CH-D BAE 125 -800 SERIES<br />
Installation of Honeywell MK VII Enhanced 1. Only Software standard -226-226 or later<br />
10.09.2007<br />
HAWKER 800<br />
Ground Proximity Warning System (EGPWS) is approved for installation.2. Prior to<br />
HAWKER 800 XP<br />
to software version -226-226 and Optional installation of this modification the installer must<br />
RAAS<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification w<br />
10<strong>01</strong>5938 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02079 ST<strong>01</strong>157WI-D LEARJET 35A<br />
Installation of L-3 Communications F1000,<br />
30.10.2006<br />
LEARJET 36A<br />
SSFDRFAA STC ST<strong>01</strong>157WI-D<br />
10<strong>01</strong>5972 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02123 FAA STC ST<strong>01</strong>159WI-D LEARJET 31<br />
Installation of Honeywell Mk-VIII EGPWS.FAA None. 17.<strong>01</strong>.2007<br />
LEARJET 35A<br />
LEARJET 36A<br />
STC ST<strong>01</strong>159WI-D<br />
10<strong>01</strong>5987 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02141 ST02092CH-D HAWKER 800 XP Installation of a forward cabin entry door and Applicable to Aircraft Serial Number 258645<br />
20.09.2006<br />
aft cabin reconfiguration<br />
only<br />
10<strong>01</strong>61<strong>04</strong> DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02294 FAA STC NO. ST2359CH-D BAE 125 SERIES 800A Modification of the existing Collins TDR-94D 1. This STC is only approved where ARINC<br />
20.08.2007<br />
Transponders and Collins RTU-870 Radio 429 databus or similar standard is used as an<br />
Tuning Units to Enhanced Surveillance capable input to the transponders, it does not approve<br />
equipment and aircraft interface requirements. the use of Gilham or Grey code as the input to<br />
the Mode S transponders. As the applicant has<br />
not demonstrated that this<br />
10<strong>01</strong>6105 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02295 FAA STC NO. ST02370CH-D BAE 125 SERIES 800A<br />
HAWKER 800<br />
HAWKER 800XP<br />
10<strong>01</strong>6110 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02300 US STC NO. ST02371CH-D HAWKER 800 XP<br />
HAWKER 800, 800A<br />
10<strong>01</strong>6149 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02351 FAA STC NO. ST02091 CH-D BAE 125 SERIES 800A<br />
HAWKER 800<br />
HAWKER 800 XP<br />
10<strong>01</strong>6235 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02499 FAA STC ST00858WI LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
Upgrade of the existing dual Universal Avionics<br />
Systems Corporation UNS-1D Flight<br />
Management System to UNS-1D+ Flight<br />
Management System.<br />
<strong>EASA</strong> approved Airplane Flight Manual<br />
Supplement, 0611080<strong>04</strong>, Revision 0, dated<br />
November 10, 2006, <strong>EASA</strong> approved Jabuary<br />
10, 2007 or later <strong>EASA</strong> approved revision is<br />
required.Compatibility of this design change<br />
with previously approved modifications must be<br />
d<br />
Installation of Aircell Iridium ST-3100 single Compatibility of this design change with<br />
channel SATCOM system.<br />
previously approved modifications must be<br />
determined by the installer.If the holder agrees<br />
to permit another person to use this certificate<br />
to alter the product , the holder shall give the<br />
other personwritten eviden<br />
Replacement of Existing #3, #4 and #5 1. If the holder agrees to permit another person<br />
auxiliary batteries with Securaplane XL245 lead to use this certificate to alter the product, the<br />
acid batteries<br />
holder shall give the other person written<br />
evidence of that permission.<br />
Installation of Collins TCAS-94 TCAS II This installation is not to be used in airspace<br />
System.<br />
where Elementary Surveillance (ELS) or<br />
enhanced surveillance (EHS) is required.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 189/<strong>462</strong><br />
31.05.2007<br />
31.05.2007<br />
30.<strong>04</strong>.2007<br />
19.12.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6392 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02721 FAA STC ST00914WI-D LOCKHEED 1<strong>01</strong>1-385-1 Installation of Dual IS&S Air Data/ Altimeter approval may be extended to aircraft models<br />
26.05.2008<br />
System along with two inch standby pneumatic Lockheed 1329-23, previously modified iaw<br />
altimeter (FAA STC ST00914WI-D).<br />
FAA STC SA2326SW, when this STC has<br />
been <strong>EASA</strong>validated.Lockheed 1329-25 Group<br />
Approval for RVSM requirements can be<br />
shown in conjunction with FAA STC<br />
ST<strong>01</strong>082SE (AeroMech<br />
10<strong>01</strong>6393 DUNCAN AVIATION, Inc. <strong>EASA</strong>.IM.A.S.02722 FAA STC ST<strong>01</strong>059WI LOCKHEED 1<strong>01</strong>1-385-1 Installation of Honeywell MK VII Enhanced This Design Approval may be extended to<br />
Ground Proximity Warning System (EGPWS). Airplanes Model Lockheed 13-29-23,<br />
FAA STC ST<strong>01</strong>059WI.<br />
previously modified iaw FAA STC SA2326SW,<br />
when validatedby <strong>EASA</strong>.Prior to installation of<br />
this modification the installer must determine<br />
that the interrelationship between this modif<br />
10026867 DUNCAN AVIATION, INC. P-<br />
<strong>EASA</strong>.IM.A.S.03211<br />
10028927 DUNCAN AVIATION, INC. P-<br />
<strong>EASA</strong>.IM.A.S.03<strong>04</strong>6<br />
FAA STC ST00703WI CESSNA 650 Installation of an AlliedSignal Enhanced Ground According to associated technical<br />
Proximity Warning System(EGPWS) documentation, FAA STC, AFMS and ICA<br />
FAA STC ST<strong>01</strong>409WI-D MYSTERE FALCON MF900 <strong>EASA</strong> Validation of FAA STC ST<strong>01</strong>409WI- Validation limited to Basic Mystere Falcon<br />
DInstallation of an L3 Communications, GH-<br />
3100 Electronic StandbyInstrument System<br />
(ESIS) in accordance with Duncan Aviation Inc<br />
MasterDocument List No 06062208, Revision<br />
C, dated February 19th, 2008or later revisions<br />
a<br />
MF900 aircraft model<br />
10<strong>04</strong>0935 DUNCAN AVIATION, INC. FAA STC ST00600CH-D MF 900 & F900EX <strong>EASA</strong> validation of FAA STC ST00600CH-D As per FAA STC ST00600CH-D issue dated<br />
issue dated 12 Sept 2008Installation of<br />
Honeywell Enhanced Ground Proximity<br />
Warning System withWindshear Detection and<br />
optional Terrain Display (S/W level -218-<br />
218)and optional Runway Advisory Awareness<br />
System (RAAS)<br />
12 Sept 2008<br />
10028837 DUNLOP AIRCRAFT TYRES LIMITED P-<strong>EASA</strong>.A.S.03864 REV. 1 EMBRAER ERJ 190-100 ECJ<br />
EMBRAER ERJ 190-100IGW<br />
EMBRAER ERJ 190-100LR<br />
EMBRAER ERJ 190-100STD<br />
EMBRAER ERJ 190-200IGW<br />
EMBRAER ERJ 190-200LR<br />
EMBRAER ERJ 190-200STD<br />
10038094 DUNLOP AIRCRAFT TYRES LIMITED 0<strong>01</strong>0<strong>01</strong>4209-0<strong>01</strong> TCCA STC SA02-29 CL-600-2B19 Installation, Dunlop Aircraft Tyres Ltd P/N<br />
DR27921T Main and DR15112TNose Gear<br />
Tyres This STC is issued in order to reflect the<br />
transfer of ownership fromACS-NAI Ltd to<br />
Dunlop Aircraft Tyres Ltd. This STC has<br />
previously been validated in the following Eur<br />
10039387 DUNLOP AIRCRAFT TYRES LIMITED ATR 42-200/-300/-320/-400/-500 Installation of Dunlop Aircraft Tyres on ATR 42<br />
seriesThe STC installs Dunlop Aircraft Tyres<br />
Ltd P/N DZ33<strong>01</strong>2T (Main LandingGear) and<br />
P/N DR15520T (Nose Landing Gear).<br />
10<strong>04</strong>1486 DUNLOP AIRCRAFT TYRES LIMITED ERJ 170-100 LR,<br />
ERJ 170-100 STD,<br />
ERJ 170-200 LR,<br />
ERJ 170-200 STD.<br />
Dunlop Aircraft Tyres Limited P/N DZ32816T<br />
Radial Nose Landing Gearinstallation on ERJ<br />
170.<br />
Different nose landing gear part number tires<br />
may not be intermixed onthe same axle.<br />
13.10.2008<br />
Prior to installation of this modification it 18.08.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 19.02.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 06.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.06.2009<br />
Prior to installation of this modification it 18.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.05.2<strong>01</strong>2<br />
It is not allowable to mix different tyre types<br />
(radial and bias) in thenose landing gear leg.<br />
Prior to installation of this modification it 20.09.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 190/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030818 DYN'AVIATION DR300/108, DR300/180R, MD09F00<strong>01</strong> 050210 - New flaps and control None None 08.07.2<strong>01</strong>0<br />
DR300/120, DR400/120,<br />
DR300/140, DR300/125,<br />
DR340, DR315, DR360, DR380,<br />
DR400/100, DR400RP,<br />
DR400NGL,<br />
DR400/120A, DR400/160D,<br />
DR400/120D, DR400/180S,<br />
DR400/125, DR400/140,<br />
DR400/125I, DR400/140B,<br />
DR400/160, DR400/180,<br />
DR400/180R, DR400/2+2,<br />
DR400/200R, DR400/500<br />
system<br />
10031522 E & B HELICOPTERS LTD. TCCA STC SH07-38 407 Audio Alert System None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.08.2<strong>01</strong>0<br />
10<strong>01</strong>3998 E A D AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>035 BEECH 1900C, AIRLINER<br />
BEECH 1900D<br />
ELS/EHS mode S installation on B1900 series. The Airplane Flight Manual Supplement DC107-<br />
0886-00B or later approved revisions must be<br />
used with this modification.<br />
10<strong>01</strong>3999 E A D AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>036 BOEING 737 Installation of a Honeywell EGPWS Mark V. 14.06.2005<br />
10<strong>01</strong>4000 E A D AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>037 BEECH 1900 Installation of a Traffic Alert and Collision<br />
Avoidance System, model Hoenywell CAS-<br />
67A TCASII installation on B1900 Series.<br />
10<strong>01</strong>4124 E A D AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>234 AIRBUS A300-600<br />
Modification of ELT ADT406 AF on<br />
AIRBUS A310<br />
A300/A310Installation of ELT ADT 406 AF<br />
10<strong>01</strong>4314 E A D AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>562 REV. 1 FAIRCHILD SWEARINGEN SA<br />
227 SE<br />
10<strong>01</strong>4315 E A D AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>563 AEROSPATIALE ATR 42-300<br />
SERIES<br />
10<strong>01</strong>4749 E.I.S. AIRCRAFT GMBH <strong>EASA</strong>.A.S.02934 CESSNA 525<br />
CESSNA 525A<br />
10<strong>01</strong>4931 E.I.S. AIRCRAFT GMBH <strong>EASA</strong>.A.S.03185 BEECH C90 A<br />
BEECH C90KING AIR<br />
All wiring required for TCAS II activation must<br />
be installed.ATC Mode S Transponders must<br />
be installed.<br />
Installation of TCAS II on SA 227 series This STC is approved only for the product<br />
aircraftTCAS II installation in accordance with configuration as defined in the approved design<br />
EAD Supplemental Type Design Definition data referred to in the paragraph "Description".<br />
Document <strong>01</strong><strong>04</strong>3-EAS-A-STD-<strong>01</strong> rev. A :• Compatibility with other aircraft/engine<br />
Removal of existing TCAS and associated tray configurations shall be determined by the<br />
in forward avionics• Installation of TCAS II installer.<br />
Installation of a calibration antenna in<br />
accordance with <strong>01</strong>050-EAS-A-MDL.<br />
Avionic Upgrade TO DUAL GTX 330D and<br />
installation of SAT-COM Antenna.<br />
Avionics Upgrade to Garmin GTX330D<br />
diversity Mode S Transponder.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>5148 E.I.S. AIRCRAFT GMBH <strong>EASA</strong>.A.S.03508 BOEING 737-700 Cabin reconfiguration. Applicable for B737-700 MSN 28609. 15.<strong>04</strong>.2008<br />
10<strong>01</strong>5187 E.I.S. AIRCRAFT GMBH <strong>EASA</strong>.A.S.03571 SOCATA TBM 700 Avionics Upgrade to Garmin GTX330D Prior to installation of this modification the<br />
14.08.2008<br />
diversity Mode S Transponder.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>5188 E.I.S. AIRCRAFT GMBH <strong>EASA</strong>.A.S.03572 BEECH C90 A<br />
BEECH C90KING AIR<br />
Installation of dual Rockwell/Collins TDR 94D<br />
diversity mode-s transponder.<br />
10<strong>01</strong>3951 E.I.S.A. <strong>EASA</strong>.A.S.0<strong>04</strong>39 REV 1 CESSNA 551 Installation of two Rockwell / Collins TDR 94D<br />
instead of two TDR 90 according to FDM EISA<br />
05FDM F055 rev. 4 dated November 20<strong>04</strong> and<br />
associated documents.New transponder<br />
location<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
1. Compatibility of this modification with other<br />
previously approved modifications must be<br />
determined by the installer.2. Applicability<br />
Cessna 551 S/N 551-<strong>01</strong>33 and S/N CE551-<br />
<strong>01</strong>74.3. <strong>EASA</strong> approved Airplane Flight<br />
Manual Supplement, dated 23 November 20<strong>04</strong><br />
is<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 191/<strong>462</strong><br />
12.<strong>04</strong>.2005<br />
18.07.2005<br />
28.07.2005<br />
03.<strong>04</strong>.2006<br />
21.<strong>04</strong>.2006<br />
23.<strong>01</strong>.2007<br />
21.08.2007<br />
19.12.2008<br />
30.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>3970 E.I.S.A. <strong>EASA</strong>.A.S.00741 REV. 2 BEECH 200 Photo Conversion / based on existing STC No. 1 The application of this STC is limited to the<br />
27.02.2009<br />
<strong>EASA</strong>.A.S.00741r1<br />
S/N BB221 and BB16072 Utilisation of<br />
Intercom prohibited in dense traffic areas3<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modifi<br />
10<strong>01</strong>4075 E.I.S.A. <strong>EASA</strong>.A.S.<strong>01</strong>167 REV 1 FALCON 10 Installation of a TCAS 4000 unit from<br />
Rockwell/CollinsInstallation of a TCAS 4000<br />
unit from Rockwell/Collins<br />
30.06.2006<br />
10<strong>01</strong>4530 E.I.S.A. <strong>EASA</strong>.A.S.02615 CESSNA 4<strong>04</strong> Installation of a video under Cessna 4<strong>04</strong> Applicable to Cessna 4<strong>04</strong> <strong>04</strong>.10.2006<br />
10<strong>01</strong>4643 E.I.S.A. <strong>EASA</strong>.A.S.02795 MYSTERE FALCON 20 Addition of Enhanced Surveillance Capacity on<br />
existing TDR 94 Mode S Transponder<br />
installation.<br />
Major Design Change applicable to aircraft Fan<br />
Jet Falcon and Falcon 20 equipped with:•<br />
Rockwell Collins Proline IV avionics suite.•<br />
Mode S Elementary Transponder TDR-94D-<br />
008.• FMS-6000.• Air Data Computer ADC-<br />
850C.• An Input/Output Concentr<br />
10<strong>01</strong>4736 E.I.S.A. <strong>EASA</strong>.A.S.02919 REV 1 CESSNA 525A Installation of SAT-COM Antenna 24.<strong>01</strong>.2007<br />
10<strong>01</strong>4786 E.I.S.A. <strong>EASA</strong>.A.S.02986 FALCON 50 ADDITION OF ENHANCED SURVEILLANCE This STC is approved only for those Mystere<br />
29.05.2007<br />
CAPACITY ON EXISTING ELEMENTARY Falcon 50 aircraft previously equipped to this<br />
MODE S TRANSPONDER INSTALLATION modification with:• Option 1: Rockwell Collins<br />
Proline IV, FMS FMC-6000 and Mode S<br />
Elementary Surveillance Installation with<br />
Transponder Rockwell Collins TDR 94D<br />
10<strong>01</strong>4908 E.I.S.A. <strong>EASA</strong>.A.S.03151 FALCON 10 MODE S TRANSPONDER WITH<br />
ENHANCED SURVEILLANCE CAPACITY<br />
31.05.2007<br />
10<strong>01</strong>5021 E.I.S.A. <strong>EASA</strong>.A.S.03327 CESSNA 525B S134 - Maximum Takeoff/Landing Weight<br />
reduction.<br />
None 05.02.2008<br />
10<strong>01</strong>5364 E.J. MLYNARCZYK & CO. INC. <strong>EASA</strong>.IM.A.S.00679 REV. 1 FAA STC ST03078AT BOEING 747-400 Installation of a Panasonic Avionics<br />
1. STC No ST<strong>01</strong>523SE must be<br />
12.10.2005<br />
Corporation System 3000 In-Flight<br />
accomplished concurrently with MAS1<strong>04</strong>13-<strong>01</strong><br />
Entertainment System in accordance with and MAS1<strong>04</strong>13-02 installations.2. This STC<br />
Master Drawing List MDL 1<strong>04</strong>13, Rev. F dated is approved only for the product configuration<br />
14 September 2005. Validation of FAA STC as defined in the approved designdata referred<br />
ST03078AT amended 22 September 2005. to in the paragraph "Description". Compatib<br />
10<strong>01</strong>5656 E.J. MLYNARCZYK & CO. INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>632 ST<strong>01</strong>519AT BOEING DC-9-82 (MD-82)<br />
BOEING DC-9-83 (MD-83)<br />
FAA STC ST<strong>01</strong>519ATInstallation of Dual<br />
Canadian Marconi Company CMA-900 Flight<br />
Management System<br />
10039<strong>04</strong>0 E4C AEROSPACE, Inc. REV. 1 FAA STC ST02110LA B767-300 Seat power, Seat Modifications and Seat track<br />
Installation<br />
10<strong>01</strong>3929 EAD AEROSPACE <strong>EASA</strong>.A.S.00265 REV. 1 BOEING 737-300, 737-400,<br />
BOEING 737-500<br />
Compatibility of this design with previously<br />
approved modifications must be determined by<br />
<strong>01</strong>.02.2008<br />
31.07.2006<br />
the installer.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.05.2<strong>01</strong>2<br />
Installation of Honeywell EGPWS Mark V Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
This STC is approved only for the product<br />
10<strong>01</strong>42<strong>01</strong> EAD AEROSPACE <strong>EASA</strong>.A.S.<strong>01</strong>351 REV 1 SA 227 SERIES ELS/EHS installation on SA 227 series aircraft -<br />
Removal of existing two ATC transponders and configuration as defined in the approved design<br />
associated trays in forward avionics- Removal data referred to in the paragraph "Description".<br />
of existing ATC Mode S Control Panel from Compatibility with other aircraft/engine<br />
Instrument Panel- Disconnection of ATC 2 configurations shall be determined by the<br />
Mode S bottom antenna- Installati<br />
installer.<br />
10<strong>01</strong>4450 EAD AEROSPACE <strong>EASA</strong>.A.S.02503 B757 ELT antenna installation as provision only Maintenance Planning Document Supplement<br />
<strong>01</strong>060-EAS-C-MPD-02, Revision A<br />
10<strong>01</strong>4637 EAD AEROSPACE <strong>EASA</strong>.A.S.02783 REV 1 BOEING 767 Installation of Panasonic "EFX" Passenger in<br />
Flight Entertainment System (IFE).<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 192/<strong>462</strong><br />
02.02.2009<br />
27.06.2006<br />
10.03.2006<br />
<strong>04</strong>.<strong>04</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4638 EAD AEROSPACE <strong>EASA</strong>.A.S.02784 BOEING 737-600<br />
Implementation of Honeywell “Link 2000” Compatibility of this design change with other<br />
09.03.2007<br />
BOEING 737-700<br />
Controller-Pilot Data Link Communications previously approved modifications must be<br />
BOEING 737-800<br />
BOEING 737-900<br />
(CPDLC) on B 737<br />
determined by the installer.<br />
10<strong>01</strong>4664 EAD AEROSPACE <strong>EASA</strong>.A.S.02821 BOEING 757-200 SERIES Installation of Thales Integrated Standby Flight<br />
System<br />
11.05.2007<br />
10<strong>01</strong>4679 EAD AEROSPACE <strong>EASA</strong>.A.S.02840 B767-300 Installation of Thales Integrated Standby Flight<br />
Display (ISFD)<br />
05.03.2007<br />
10<strong>01</strong>5106 EAD AEROSPACE <strong>EASA</strong>.A.S.03449 A319 Installation of AMT-3800 High Gain Antenna on 1. Prior to installation of this modification the<br />
17.11.2008<br />
A319 Series Aircraft<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10039303 EAD AEROSPACE REV. 1 B747-400 Installation of Cobham SATCOM antenna type<br />
HGA-70<strong>01</strong> in accordance withAerotec Master<br />
Data List AE11110MDL Rev.1, dated 4 April<br />
2<strong>01</strong>2.<br />
10<strong>04</strong>0<strong>04</strong>3 EAD AEROSPACE REV. 1 B747-400 Swift broadband Satcom installation in S/N: 30885, 32337, 32338, 32339, 32340,<br />
accordance with Aerotec ConceptMaster Data 28757, 29406<br />
List AE11111MDL Rev 2, dated April 3, 2<strong>01</strong>2<br />
10<strong>01</strong>5302 EAD AEROSPACE AIRWORTHINESS <strong>EASA</strong>.A.S.03866 REV. 3 A340 Installation of Advanced Mission Display<br />
System Phase A- AMDS/ARevision of the<br />
<strong>EASA</strong> STC <strong>EASA</strong>.A.S.03866 Revision 2 to<br />
remove EWISlimitation<br />
10027343 EAD AEROSPACE AIRWORTHINESS P-<strong>EASA</strong>.A.S.03706 A330 Installation of Advanced Mission Display<br />
System - Phase A (AMDS/A)<br />
10031354 EAD AEROSPACE AIRWORTHINESS REV. 1 A320 Installation of Advanced Mission Display<br />
System Phase A- AMDS/A on A320Series<br />
Aircraft Revision of the <strong>EASA</strong> STC 10031354<br />
to remove EWIS limitation<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.07.2<strong>01</strong>2<br />
None 06.07.2<strong>01</strong>2<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
02.12.2<strong>01</strong>0<br />
None 1. Prior to installation of this modification 23.09.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
29.11.2<strong>01</strong>0<br />
10036787 EAD AEROSPACE AIRWORTHINESS A320 SERIES Cabin Modification 174 to 168 PAX on A320 None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
06.10.2<strong>01</strong>1<br />
10<strong>01</strong>6076 EAD INC. <strong>EASA</strong>.IM.A.S.02260 FAA STC ST02267CH BOEING 747-400 EAD installed Honeywell Weight and Balance<br />
System (WBS) on B747-400 in accordance<br />
with EAD Master Data List <strong>01</strong>021-FAA-A-MDL,<br />
rev. E, or later <strong>EASA</strong>-approved revision.This<br />
STC is a validation of FAA STC ST02267CH<br />
10<strong>01</strong>6545 EAD INC. <strong>EASA</strong>.IM.A.S.02924 FAA STC ST<strong>01</strong>481CH BOEING 737-400 SERIES TCAS/Mode-S Activation on Boeing 737-400<br />
Series as approved under the STC FAA<br />
ST<strong>01</strong>481CH.<br />
1. This on board weight and balance system is<br />
considered an advisory systeem and is not<br />
certified as the primary means of calculating<br />
the aircraft's weight and balance.2. <strong>EASA</strong><br />
approved Airplane Flight Manual Supplement,<br />
EAD document <strong>01</strong>021-FAA-A-AFM-<strong>01</strong>, Rev<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 193/<strong>462</strong><br />
27.<strong>04</strong>.2007<br />
02.10.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034640 EAD INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>715 REV. 1 FAA STC ST03205AT BOEING DC-9-82 (MD-82) Installation of Rockwell Collins CMU-900 None Prior to installation of this modification the 31.07.2009<br />
Communications Management Unit,VHF-920<br />
installer must determinethat the<br />
VDL Mode 2 Radio, Gables Mode 2 VDR<br />
interrelationship between this modification<br />
Control Panel and ACARS TP4429 Printer to<br />
and any otherpreviously installed<br />
provide Controller Pilot Data Link<br />
modification will introduce no adverse<br />
Communications(CPCDL) Baseline 1 service in<br />
effect uponthe airworthiness of the<br />
accordance with EAD<br />
product. The installati<br />
10029272 EADS CASA P-<strong>EASA</strong>.A.S.02790 REV. 3 A330-203 WEIGHT VARIANT 052 Conversion of A330-200 Series A/C to A330 Approval of this STC is limited to compliance to This STC can only be installed in 21.12.2<strong>01</strong>1<br />
FOR CONFIGURATION 1 Multi Role Transport Tanker(MRTT) RAAF selected CertificationStandards as defined in conjunction with the modificationsdefined<br />
A330-202 WEIGHT VARIANT 052 (Royal Australian Air Force), RSAF (Royal CRI A-<strong>01</strong>. CRI G-<strong>01</strong> defines in<br />
by: - Airbus Change G-MRTT-<strong>01</strong> certified<br />
FOR CONFIGURATION 2 Saudi Arabian AirForce) and UAE (United particularrestrictions relating to Maintenance under <strong>EASA</strong> ref. 10029273 and- Airbus<br />
A330-243 (WEIGHT VARIANT Arabic Emirates Force)Rev. 1 of this STC has Tasks and AirworthinessLimitations, ref JAR Change G-MRTT-02 certified under<br />
052)<br />
been issued in order to add Configuration 25.571a(3) and 25.1529.Therefore, the fo <strong>EASA</strong> ref. 10029276- Airbus Change G-<br />
FOR CONFIGURATION 3 2.Rev.<br />
MRTT-<strong>04</strong> certified under <strong>EASA</strong> ref.<br />
10034690 EADS CASA P-<strong>EASA</strong>.A.S.03608 REV. 2 A330-243 A330 MRTT FSTA Modification STC1With the<br />
Revision 1 of this STC a previous limitation on<br />
the occupationof medical stretchers has been<br />
deleted.With the revision 2 of this STC the role<br />
change capability isintroduced. Therefore, it is<br />
possible for an aircraft<br />
None This approval includes the possibility for<br />
aircraft and aircraft parttransfer from<br />
military operation (INTA Technical<br />
Certificateconfiguration) to civil operation<br />
(this STC's configuration). For aircraft<br />
transfer from military to civil operation:-<br />
10035945 EADS CASA P-<strong>EASA</strong>.A.S.03607 REV. 2 A330-243 A330 MRTT FSTA Modification STC2 Revision Based on the conditions established in CRI G-<br />
The condi<br />
1. This STC can only be installed in 02.08.2<strong>01</strong>2<br />
1Remark: This revision 1 of the STC introduces <strong>01</strong> with respect to thedefinition of the conjunction with the modificationsdefined<br />
the following changes:- Deletion of previous Airworthiness Limitation Section of the by: - Airbus Change G-MRTT-<strong>01</strong> certified<br />
limitation no. 4 on Autoland / CAT III function- Instructionsfor Continued Airworthiness the under <strong>EASA</strong> ref. 10029273*- Airbus<br />
Replacement of temporary conservative Noise following limitations apply:1. As the<br />
Change G-MRTT-02 certified under<br />
levels by final values- Parti<br />
modifications of this STC are intended for <strong>EASA</strong> ref. 10029276*and - Airbus<br />
milita<br />
Change G-MRTT-03 certified under<br />
<strong>EASA</strong><br />
10<strong>04</strong>2436 EADS CASA A330-243 Installation of a Cockpit Door Surveillance None Prior to installation of this modification it 30.11.2<strong>01</strong>2<br />
System in the A330<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4980 EADS ELBE FLUGZEUGWERKE GmbH <strong>EASA</strong>.A.S.03272 AIRBUS A310-3<strong>04</strong> A310-3<strong>04</strong> Cabin ReconfigurationTransfer of<br />
the STC holder, from ASL Aircraft Services<br />
Lemwerder GmbH to EADS Elbe<br />
Flugzeugwerke GmbH.Former LBA STC ref<br />
TA0721Cabin Reconfiguration from 265 seats<br />
to 225 seats (18 Business Class + 207<br />
1. This STC is limited to A310-3<strong>04</strong> aircraft<br />
model MSN 448.2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adver<br />
10<strong>01</strong>4981 EADS ELBE FLUGZEUGWERKE GmbH <strong>EASA</strong>.A.S.03273 AIRBUS A310-3<strong>04</strong><br />
Economy Class).<br />
A310-3<strong>04</strong> Floor Path Marking System 1. This STC is limited to A310-3<strong>04</strong> aircraft<br />
08.10.2007<br />
installationTransfer of the STC holder, from model MSN 448.2. Prior to installation of this<br />
ASL Aircraft Services Lemwerder GmbH to modification the installer must determine that<br />
EADS Elbe Flugzeugwerke GmbH.Former the interrelationship between this modification<br />
LBA STC ref TA0719The modification related andany other previously installed modification<br />
to this supplement concerns the installation of a will introduce no adver<br />
photolu<br />
10<strong>01</strong>4982 EADS ELBE FLUGZEUGWERKE GmbH <strong>EASA</strong>.A.S.03274 AIRBUS A320-214 A320-214 Cabin ReconfigurationTransfer of 1. This STC is limited to A320-214 aircraft<br />
08.10.2007<br />
the STC holder, from ASL Aircraft Services model MSN 1081 and MSN 1370.2. Prior to<br />
Lemwerder GmbH to EADS Elbe<br />
installation of this modification the installer must<br />
Flugzeugwerke GmbH.Former LBA STC ref determine that the interrelationship between<br />
TA0717 Issue 2Cabin Reconfiguration from this modification andany other previously<br />
156 seats (90 Business Class + 66 Economic<br />
Class) to 180 seats (<br />
installed modification will intr<br />
10031745 EADS ELBE FLUGZEUGWERKE GmbH P-<strong>EASA</strong>.A.S.03661 A300B4-6<strong>01</strong>/ -603/ -620/ -622 Courier Stowage installationThis STC consists The current STC needs specific aircraft Prior to installation of this modification it 09.09.2<strong>01</strong>0<br />
A300B4-605R/ -622R<br />
in modifying the Courier Area of aircraft configuration as aprerequisite:- To install this must be determined thatthe<br />
A310-3<strong>04</strong>/ -308/ -324/ -325 converted byAirbus Pax to Freighter STCs by STC on A310 aircraft models, embodiment of interrelationship between this modification<br />
installing a Courier Stowage<br />
<strong>EASA</strong> STCref: 10<strong>01</strong>3945, Rev 4 (or any and any other previouslyinstalled<br />
further <strong>EASA</strong> approved revision) isrequired.- modification and/ or repair will introduce<br />
To install this STC on A300-600 aircraft m no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 194/<strong>462</strong><br />
02.08.2<strong>01</strong>2<br />
08.10.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>3940 EADS SOGERMA <strong>EASA</strong>.A.S.00376 REV 1 AIRBUS A310-3<strong>04</strong> Royal Jordanian ATC Mode S Enhanced 1. The Aircraft Flight Manual Supplement No<br />
07.<strong>01</strong>.2008<br />
Surveillance installation according to EADS AFM-34-974 issue B dated 29 November<br />
Sogerma Modification Approval Sheet SOG-34- 20<strong>04</strong>, or later <strong>EASA</strong>-approved revision, is a<br />
974 issue 3 dated 29 November 20<strong>04</strong>.Note: required part of this STC.2. Prior to<br />
This revision reflects the transfer of this STC installation of this modification the installer must<br />
from EADS Sogerma Services to Sogerma<br />
Servic<br />
determine that the interrelationsh<br />
10<strong>01</strong>3941 EADS SOGERMA <strong>EASA</strong>.A.S.00377 REV 1 AIRBUS 310-325 Cabin Modification from 18F/C-180Y/C to Prior to installation of this modification the<br />
07.<strong>01</strong>.2008<br />
18B/C-188Y/C according to the modification installer must determine that the<br />
approval sheet MAS No SOG-25-957 issue 1 interrelationship between this modification and<br />
dated 6October 20<strong>04</strong> or later <strong>EASA</strong>-approved any other previously installed modification will<br />
revision.Note: This revision reflects the transfer introduce no adverse effect upon the<br />
of this STC from EADS Sogerma Services airworthiness of the product. The install<br />
10<strong>01</strong>3950 EADS SOGERMA <strong>EASA</strong>.A.S.0<strong>04</strong>32 REV 1 AIRBUS 310-325 Modification of ATLAS/KSSU galleys into full Prior to installation of this modification the<br />
ATLAS standard in accordance with<br />
installer must determine that the<br />
Modification Approval Sheet reference SOG-25-interrelationship<br />
between this modification and<br />
958 Issue <strong>01</strong> dated 14 October 20<strong>04</strong>. All any other previously installed modification will<br />
documents related to this STC are listed in the introduce no adverse effect upon the<br />
Master Drawing List reference MDL-25-958 Iss airworthiness of the product. The install<br />
10<strong>01</strong>4005 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong><strong>04</strong>2 REV 1 AIRBUS A340-300 Installation of an upper class with side facing<br />
Britax Malcom seats with inflatable restraints,<br />
monument, bar and chandelier, and<br />
modification of the premium and economy<br />
class by repitching.Note: This revision reflects<br />
the transfer of this STC from EADS So<br />
1. This STC is limited to Airbus A340-300<br />
MSN 214, 002, 003, 164 and 225.2. A copy<br />
of this STC and of the MAS/MDL must be<br />
enclosed in the files of each modified aircraft.<br />
10<strong>01</strong>4022 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>077 REV 1 AIRBUS A330-203 Qatar Airways - Cabin Modification.<br />
1. The approval of this modification is limited<br />
Modification number: SOG-25-886 issue to the identified aircraft. The limitations and<br />
1Note: This revision reflects the transfer of this conditions defined in the <strong>EASA</strong> Datasheet are<br />
STC from EADS Sogerma Services to also applicable. A copy of the STC approval<br />
Sogerma Services.Model: Airbus A330-203 and the MDL must be enclosed in the files of<br />
MSN 463 and 5<strong>04</strong><br />
each modified aircraft.<br />
10<strong>01</strong>4076 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>168 REV 1 AIRBUS A330-243 Cabin configuration for Gulf Air. All documents Prior to installation of this modification the<br />
related to this STC are listed in the Modification installer must determine that the<br />
SOG-25-1075 iss. <strong>01</strong> (or later <strong>EASA</strong>-aproved interrelationship between this modification and<br />
revision).Note: This revision reflects the transfer any other previously installed modification will<br />
of this STC from EADS Sogerma Services to introduce no adverse effect upon the<br />
Sogerma Services.Mod<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4077 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>169 REV 1 AIRBUS A310 Installation of an ATC Mode S EHS. ATC<br />
mode S modification for compliance with<br />
Enhance Surveillance. Replacement of the<br />
Rockwell Collins TRP-720 ATC by TRP-9<strong>01</strong><br />
ATC.Note: This revision reflects the transfer of<br />
this STC from EADS Sogerma Services to<br />
Sogerma<br />
07.<strong>01</strong>.2008<br />
10<strong>01</strong>4087 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>179 REV 1 DC-9-21 ELT Kannad 406 AF modification (SOG-25-<br />
1106)Note: This revision reflects the transfer of<br />
this STC from EADS Sogerma Services to<br />
Sogerma Services.<br />
1. This STC is limited to the DC-9 MSN 4708 <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>4113 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>219 REV 1 ATR 42-320 SERIES Pseudo-Lisse configuration; RESSAC 1. In RALI configuration:-the mass of under<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
configuration and RALI configuration.Note: This wing POD is limited to 72kg (POD equipped);-<br />
revision reflects the transfer of this STC from the new design for the titanium pin on POD<br />
EADS Sogerma Services to Sogerma rear attachment must be applied according to<br />
Services.Model: Aerospatiale ATR 42-320 the EADS Sogerma Services waiver No.<br />
MSN 078<br />
A3002.2. The lighting issues are cert<br />
10<strong>01</strong>4114 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>220 REV 1 AEROSPATIALE ATR 42-320 ELT Kannad 406 AF ModificationNote: This<br />
revision reflects the transfer of this STC from<br />
EADS Sogerma Services to Sogerma<br />
Services. Model: Aerospatiale ATR 42-320<br />
MSN 078<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4169 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>302 REV 1 AIRBUS A321-200 A321 Livingston - Cabin Modification from 196 Prior to installation of this modification the<br />
Y/C to 210 Y/C with relocation of two attendant installer must determine that the<br />
seats.Note: This revision reflects the transfer of interrelationship between this modification and<br />
this STC from EADS Sogerma Services to any other previously installed modification will<br />
Sogerma Services.Model: Airbus A321-200 introduce no adverse effect upon the<br />
MSN 1950 & 1970<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 195/<strong>462</strong><br />
07.<strong>01</strong>.2008<br />
07.<strong>01</strong>.2008<br />
07.<strong>01</strong>.2008<br />
07.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4171 EADS SOGERMA <strong>EASA</strong>.A.S.<strong>01</strong>3<strong>04</strong> REV 1 AIRBUS A330-200 Installation of a Cabin modification from 24B/C -<br />
248Y/C to 18B/C - 271Y/C with removal of<br />
galley G2 and installation of new partitions for<br />
LAUDA AIR fleet. The associated modification<br />
Approval sheet is referenced SOG-25-1122<br />
issue1 dated 10/06/05. All doc<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>4675 EADS SOGERMA <strong>EASA</strong>.A.S.02835 REV 1 AIRBUS A320-211<br />
AIRBUS A320-212<br />
10<strong>01</strong>6905 EAGLE COPTERS MAINTENANCE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>284 TCCA STC SH92-28 BELL 2<strong>04</strong>B<br />
BELL 205A<br />
BELL 205A-1<br />
Emergency locator transmitter Thales/Serpe<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
Kannad 406 ATP installation.Note: This<br />
revision reflects the transfer of this STC from<br />
EADS Sogerma Services to Sogerma<br />
Services.<br />
Dual Cargo Hook Mechanical release Kit. 09.10.2007<br />
10<strong>01</strong>6906 EAGLE COPTERS MAINTENANCE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>285 TCCA STC SH92-30 BELL 2<strong>04</strong>B Vertical Reference Door. Day VFR Only;Minimum Flight Crew - 1 in left<br />
crew seat;Crew restricted to:- Flight Crew-<br />
Flight Crew under Training- Persons essential<br />
for the type of operationDual controls must be<br />
installed per Bell Helicopter Service Instruction<br />
206-6 for Model 2<strong>04</strong>B;App<br />
10<strong>01</strong>6977 EAGLE COPTERS MAINTENANCE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>379 TCCA STC SH00-37 BELL 2<strong>04</strong>B DCL 361 Tailboom Vertical Fin Spar<br />
Reinforcement.New STC for modification of<br />
tailboom vertical fin spar to comply with<br />
requirements of FAA AD 99-17-03.<br />
10<strong>01</strong>6980 EAGLE COPTERS MAINTENANCE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>383 REV. 1 TCCA STC SH03-14 BELL 2<strong>04</strong>B<br />
BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 214B<br />
BELL 214B-1<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
10<strong>01</strong>7024 EAGLE COPTERS MAINTENANCE Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>442 FAA STC SR00600NY EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
This approval supports an Alternative Means of<br />
Compliance (AMOC) for satisfying FAA AD99-<br />
17-03. An <strong>EASA</strong> AMOC authority is required in<br />
addition to this STC.<br />
D412-758 GPS receiver Gimbal Mount 1) Eligible GPS receivers are listed in<br />
Installation Instructions IIN-D412-758 Revision<br />
B dated 8 April 20082) GPS operation is<br />
limited to VFR use only<br />
D350-721 Lightweight Heli Utility Basket<br />
Installations.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 196/<strong>462</strong><br />
09.10.2007<br />
15.11.2007<br />
21.<strong>04</strong>.2008<br />
05.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7099 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>023 EUROCOPTER FRANCE AS 350 Installation of External Load Box ELB<strong>01</strong> This STC is approved only for the product<br />
30.<strong>01</strong>.2006<br />
B<br />
configuration as defined in the approved design<br />
EUROCOPTER FRANCE AS 350<br />
data referred to in the paragraph "Description".<br />
B1<br />
Compatibility with other aircraft/engine<br />
EUROCOPTER FRANCE AS 350<br />
configurations shall be determined by the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
BB<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
installer.<br />
10<strong>01</strong>7173 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>288 EUROCOPTER DEUTSCHLAND Balance Weighing System BWS02. The Balnce Weighing System BWS02 is<br />
20.07.2007<br />
EC-135<br />
compatible with the following EC135 cargo<br />
hook installations:Dual External Cargo Hook<br />
(Eurocopter FMS 9.2-47) orExternal Cargo<br />
Hook (Eurocopter FMS 9.2-19).Fixed<br />
provisions including internal wiring harness are<br />
required<br />
10<strong>01</strong>7200 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>349 REV. 2 EUROCOPTER DEUTSCHLAND "Load Attachment Device EAD<strong>01</strong>"Provides Prior to installation of this modification the<br />
11.12.2008<br />
EC-135-<br />
attachment provisions on rotorcraft for fast installer must determine that the<br />
EUROCOPTER DEUTSCHLAND roping / rappelling and Human External Cargo interrelationship between this modification and<br />
EC-635<br />
operations.Revision 1 to the STC is a revision any other previously installed modification will<br />
EUROCOPTER DEUTSCHLAND of the previous LBA STC No. 1025, dated introduce no adverse effect upon the<br />
EC-635-<br />
24.11.2003. Revision 1 adds applicable m airworthiness of the product. The install<br />
10<strong>01</strong>72<strong>01</strong> ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>350 REV. 1 <strong>EASA</strong> STC 1025 EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
10<strong>01</strong>7250 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>451 EUROCOPTER FRANCE AS<br />
365N3<br />
EUROCOPTER FRANCE EC 155<br />
B1<br />
EUROCOPTER FRANCE EC<br />
155B<br />
EUROCOPTER FRANCE SA<br />
10<strong>01</strong>7273 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>503 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
EUROCOPTER DEUTSCHLAND<br />
EC-635<br />
EUROCOPTER DEUTSCHLAND<br />
EC-635-<br />
365C2<br />
“External Abseil Device EAD<strong>01</strong>”Provides<br />
attachment provisions on rotorcraft for fast<br />
roping / rappelling and Human External Cargo<br />
operations.This STC is a revision of the<br />
previous <strong>EASA</strong> STC No. 1025, dated<br />
24.11.2003The Technical Changes are as<br />
follows:-<br />
1. The scope of this STC is limited to<br />
attachment provisions for rappelling / fast<br />
roping and HEC operations. It does not include<br />
all the necessary equipment like ropes and<br />
personal carrying device. It does not establish<br />
all the procedures necessary for<br />
External Load Attachment Device EDX02. The scope of this STC is limited to technical<br />
provisions to the helicopter. It does not include<br />
ropes and personal equipment, training<br />
aspects and operation procedures necessary<br />
for the fast roping operation. These procedures<br />
must be established by the ope<br />
Installation of HEC Rope System HRS<strong>01</strong>, P/N<br />
HRS<strong>01</strong>-<strong>01</strong>-00.00<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7282 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>530 EUROCOPTER DEUTSCHLAND Installation of HEC Rope System HRS<strong>01</strong>, P/N<br />
MBB-BK<br />
HRS<strong>01</strong>-<strong>01</strong>-00.00<br />
10<strong>01</strong>7283 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>531 EUROCOPTER FRANCE AS 350 External Antenna for Transceiver System 1. This STC provides approval for structural<br />
B1<br />
ATS<strong>01</strong> installation on the ldg gear crosstube. and electrical provisions only. Installation and<br />
EUROCOPTER FRANCE AS 350<br />
operation of any equipment to be connected to<br />
B2<br />
the external antenna shall be covered by<br />
EUROCOPTER FRANCE AS 350<br />
separate approval.2. Prior to installation of<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
BB<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS<br />
350B<br />
this modification the i<br />
10<strong>01</strong>7293 ECMS AVIATION SYSTEMS GMBH <strong>EASA</strong>.R.S.<strong>01</strong>566 BELL 206A<br />
Installation of Bifilar Cargo System 1) Prior to installation of this modification the<br />
BELL 206A-1<br />
installer must determine that the<br />
BELL 206B<br />
interrelationship between this modification<br />
BELL 206B-1<br />
andany other previously installed modification<br />
BELL 206L<br />
will introduce no adverse effect upon the<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
airworthiness of the product.2) The ins<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 197/<strong>462</strong><br />
30.<strong>01</strong>.2007<br />
18.07.2008<br />
11.12.2008<br />
19.12.2008<br />
03.03.2009<br />
08.06.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028706 ECMS AVIATION SYSTEMS GMBH BELL 212, 412 Load Attachment Device BRD<strong>01</strong> None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.02.2<strong>01</strong>0<br />
10<strong>01</strong>7166 ECT INDUSTRIES <strong>EASA</strong>.R.S.<strong>01</strong>274 AS 350 B3 Installation of ECT Industries DMS ARINC data<br />
recorder p/n REC-AR0-TT-OO<br />
<strong>04</strong>.<strong>04</strong>.2007<br />
10<strong>01</strong>7228 ECT INDUSTRIES <strong>EASA</strong>.R.S.<strong>01</strong>399 REV. 4 AS355F1, AS355F2<br />
Installation of BRITE SAVER 2 Data Monitoring None The installation of this modification by 15.05.2<strong>01</strong>2<br />
AS355N, AS355NP<br />
SystemRevision 1 - covered a documentary<br />
third persons is subject towritten<br />
change to STCRevision 2 - covered torque and<br />
permission of the approval holder and<br />
memory management minor changeRevision 3<br />
holding and disposal ofthe approved<br />
- covered installation of ultrasonic air/ground<br />
appropriate documentation.Prior to<br />
switch,second possible location of<br />
installation of this modification it must be<br />
determined thatthe interre<br />
10<strong>01</strong>7230 ECT INDUSTRIES <strong>EASA</strong>.R.S.<strong>01</strong>4<strong>01</strong> REV. 4 AS350B, AS350B1, AS350B2 Installation of BRITE SAVER 2 Usage None This STC is approved only for the product 20.08.2<strong>01</strong>2<br />
AS350BA, AS350BB, AS350D Monitoring System Revision 1 - includes torque<br />
configuration as defined inthe approved<br />
and memory management minor change<br />
design data referred to in the<br />
Revision 2 - includes addition of the possibility<br />
paragraphs"Title/Description" and<br />
to install theultrasonic air/ground switch and<br />
"Associated Technical<br />
second source for the SUBD connectorsand<br />
Documentation".Compatibility with other<br />
aircraft/engine configurations shall<br />
bedetermin<br />
10<strong>01</strong>7248 ECT INDUSTRIES <strong>EASA</strong>.R.S.<strong>01</strong>446 REV. 2 AS350 B3, EC 130 B4 Installation of BRITE SAVER 2 Data Monitoring None Prior to installation of this modification it 19.10.2009<br />
System (DMS)This STC is a Revision to an<br />
must be determined thatthe<br />
already <strong>EASA</strong> approved STC ref.<br />
interrelationship between this modification<br />
10<strong>01</strong>7248,rev 1 dated 31/08/2009 to include<br />
and any other previouslyinstalled<br />
Software Evolution and upgrade of CPUand<br />
modification and/ or repair will introduce<br />
analogical card of the data Monitoring System<br />
no adverse effectupon the airworthiness<br />
BRITE SA<br />
of the product.<br />
10<strong>01</strong>7272 ECT INDUSTRIES <strong>EASA</strong>.R.S.<strong>01</strong>494 ROBINSON R22<br />
ROBINSON R22 ALPHA<br />
ROBINSON R22 BETA<br />
ROBINSON R44<br />
ROBINSON R44 II<br />
DMS R22 & R44 - Brite Saver PE Usage<br />
Monitoring System for Robinson R22 and R44<br />
Series Helicopters<br />
10027406 ECT INDUSTRIES P-<strong>EASA</strong>.R.S.<strong>01</strong>417 REV. 3 EC 120B Installation of ECT Industries DMS P/N REC-<br />
ARAO-TT-00 Rev. 1 adds a software change<br />
in the Data Monitoring System "Brite Saver2<br />
and an RFM SupplementRev. 2 adds a Usage<br />
Monitoring System for EC120 - "Brite Saver 2<br />
amdt 4"<br />
• Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.• Th<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027594 ECT INDUSTRIES P-<strong>EASA</strong>.R.S.<strong>01</strong>487 REV. 6 EC120B Installation of Night Image Vision System kit, Refer to applicable RFM for list of equipment<br />
allowing night VFR flightwith Night Vision mandatory for Night VisionImage System<br />
GogglesRev. 2 changes temperature limitation certificationEC120B equipped with STC<br />
in Rotorcraft Flight ManualRev. 3 incorporates 10027594 Revision 4<br />
minor changes to NVIS Shunt and LACURev. 4<br />
displays administrative changes<br />
10028220 ECT INDUSTRIES REV. 1 206H, P206, P206A, P206B,<br />
P206C, P206D, P206E, T206H,<br />
TP206A, TP206B, TP206C,<br />
PT206D<br />
TP206E, TU206A, TU206B,<br />
TU206C<br />
TU206D, TU206E, TU206F,<br />
TU206G<br />
U206A, U206B, U206C, U206D<br />
U206E, U206F, U206G<br />
10029479 ECT INDUSTRIES P-<strong>EASA</strong>.R.S.<strong>01</strong>541 AS355E, AS355F, AS355F1<br />
AS355F2, AS355N, AS355NP<br />
STC DTS and DTS V2 Cessna 206 -<br />
Installation Tracking System<br />
STC DTS AS 355 - Installation of a Tracking<br />
system.<br />
13.<strong>01</strong>.2009<br />
19.09.2<strong>01</strong>1<br />
Prior to installation of this modification it 19.09.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The fi<br />
Limitation to Cessna 206 VFR only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.03.2<strong>01</strong>0<br />
None. Prior to installation of this modification the 26.03.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 198/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029936 ECT INDUSTRIES REV. 1 AS350B, AS350B1, AS350B2 Installation of DTSV2 Data Transmission Modification not approved for aircraft equipped The approval holder shall fulfil the 30.07.2<strong>01</strong>2<br />
AS350BA, AS350BB, AS350B3 System.Revision 1 introduces corrections of with weather radar orAFCS (Automatic Flight obligations of Part 21,<br />
the tracking system installation.<br />
Control System).Modification not approved for Paragraph21.A118A. Prior to installation<br />
AS350B3 model helicopters withmodification of this modification it must be determined<br />
OP-4305 (Arriel 2D engine installation) thatthe interrelationship between this<br />
incorporated.<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
1003<strong>01</strong>43 ECT INDUSTRIES AS355E, AS355F, AS355F1,<br />
AS355F2, AS355N, AS355NP<br />
Installation of DTSV2 Tracking System None None 27.05.2<strong>01</strong>0<br />
10030338 ECT INDUSTRIES P-<strong>EASA</strong>.R.S.<strong>01</strong>510 AS350B, AS350B1, AS350B2, Installation of a tracking system (DTS - Data Modification not approved for aircraft equipped Prior to installation of this modification it 11.06.2<strong>01</strong>0<br />
AS350BA, AS350BB, AS350B3 Transmission System)<br />
with weather radar orAFCS (Automatic Flight must be determined thatthe<br />
Control System)<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10033164 ECT INDUSTRIES P-<strong>EASA</strong>.R.S.<strong>01</strong>505 REV. 3 EC135 P1(CPDS)<br />
EC135 P2(CPDS), EC135 P2+<br />
EC135 T1(CPDS)<br />
EC135 T2(CPDS), EC135 T2+<br />
EC135 NVIS Lighting SystemInstallation of a<br />
Night Vision Imaging Lighting system, to<br />
enableoperation with Night Vision Goggles.-<br />
Avionic type 1- P/N: 60D-1000-000, into<br />
helicopters with CPDS andconventional<br />
flight/navigation instruments-Avionic type 2-<br />
P/N:<br />
None The first installation of this kit must be<br />
supervised by the STC holder.This<br />
rotorcraft employs Night Vision Imaging<br />
System lighting, commonlynamed NVIS<br />
lighting, that has been certified to ensure<br />
the aircraft iscompatible with night vision<br />
goggles (NVG).<br />
10037841 ECT INDUSTRIES EC135 P1, EC135 P2, EC135 P2+ Installation of Brite Saver Usage Monitoring Only for EC135/EC635 variants with CPDS-<br />
EC135 T1, EC135 T2, EC135 T2+ SystemInstallation of a Brite Saver Usage Cockpit<br />
EC635 P2+<br />
Monitoring System. This modificationis defined<br />
EC635 T1(CPDS), EC635 T2+ in CONFAD-<strong>01</strong>15-92-EN.<br />
10<strong>04</strong>2<strong>01</strong>2 ECT INDUSTRIES AS 350 B,AS 350 B1,AS 350 B2<br />
AS 350 B3,AS 350 BA,AS 350 BB<br />
Installation of Data Tracking System DTS-<br />
Alpha.Modification as defined in STC Data List,<br />
doc. SDL-DTSALPHA-AS350 Rev.<strong>04</strong><br />
10032345 EICHELSDOERFER GmbH RF5 STC "Installation engine Rotax 912 and<br />
propeller HO-V352F-S1/S170FQ inthe<br />
powered sailplane Fournier RF 5"<br />
10<strong>04</strong>0934 EIRTECH AVIATION SERVICES LIMITED REV. 1 737-600,-700,-800,-900,-900ER Cabin Altitude and Take-off Configuration<br />
warnings and indications -Activation.<br />
27.<strong>01</strong>.2<strong>01</strong>2<br />
Prior to installation of this modification it 03.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Modification not approved for rotorcraft Prior to installation of this modification it 31.10.2<strong>01</strong>2<br />
equipped with AFCS (AutomaticFlight Control must be determined thatthe<br />
System) or Weather Radar.Modification not interrelationship between this modification<br />
approved for AS350B3 model helicopters and any other previouslyinstalled<br />
withmodification OP-4305 (Arriel 2D engine modification and/ or repair will introduce<br />
installation) incorporated.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Limited to Fournier RF 5, S/N 5<strong>01</strong>2 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.10.2<strong>01</strong>0<br />
This change is not applicable to an aircraft with<br />
High Altitude LandingCapability.<br />
10<strong>01</strong>6491 EJM AEROSPACE SERVICES <strong>EASA</strong>.IM.A.S.02853 FAA STC ST02534AT BOEING 747-400 Installation of a Matsushita Avionics Systems This STC is approved only for the product<br />
Corporation System 3000 In-Flight<br />
configuration as defined in the approved design<br />
Entertainement System on a Singapore Airlines data. Compatibilty with other aircraft/engine<br />
Boeing 747-400 in accordance with Master configurations shall be determined by the<br />
Drawing List MDL 10321, Rev. H. dated<br />
29/<strong>04</strong>/2003, or later FAA approved revision.<br />
installer.<br />
10028392 EJM AEROSPACE SERVICES FAA STC ST02531AT B747-400 Installation of a Matsushita Avionics Systems<br />
Corporation System 3000In-Flight<br />
Entertainment system on a Singapore Airlines<br />
Boeing 747-400type aircraft in accordance with<br />
Master Drawing List MDL10270, Rev. G,dated<br />
06 June 2003 or later FAA approved revisio<br />
Prior to installation of this modification it 26.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.08.2008<br />
Not Applicable Airplane Flight Manual Supplement, Doc. <strong>04</strong>.<strong>01</strong>.2<strong>01</strong>0<br />
Nr. 14526003 dated June 4, 2002or later<br />
approved revision is required as part of<br />
this STC<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 199/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5335 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.00360 FAA STC ST<strong>01</strong>449CH BOEING 757-200 Dual GPS Antenna and Coax Cable (FAA STC 1. Subject to compliance with the provisions<br />
07.12.20<strong>04</strong><br />
ST<strong>01</strong>449CH) as per Master Data List ECS- of Part 21 Subpart E, this STC and associated<br />
200555 revision B dated June 11, 2003 or later data shall remain valid until surrendered,<br />
FAA-approved revision.<br />
withdrawn or otherwise terminated.2. If<br />
transfer of this Certificate is requested under<br />
Part 21A.116, the STC will b<br />
10<strong>01</strong>5336 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.00361 FAA STC ST<strong>01</strong>839CH BOEING 757-200 Honeywell MK V Enhanced Ground Proximity<br />
Warning System (FAA STC ST<strong>01</strong>839CH) as<br />
per Master Data List ECS-2<strong>01</strong>736 revision H<br />
dated 25 May 20<strong>04</strong> or later FAA-approved<br />
revision.<br />
1. Subject to compliance with the provisions<br />
of Part 21 Subpart E, this STC and associated<br />
data shall remain valid until surrendered,<br />
withdrawn or otherwise terminated.2. If<br />
transfer of this Certificate is requested under<br />
Part 21A.116, the STC will b<br />
10<strong>01</strong>5398 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>1<strong>01</strong> ST02126CH BOEING 757 Installation of elementary & enhanced Mode S<br />
Transponders<br />
26.07.2005<br />
10<strong>01</strong>55<strong>04</strong> ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>267 ST<strong>01</strong>818CH DC-9-21<br />
Installation of a Honeywell Enhanced Ground None 21.<strong>04</strong>.2006<br />
DC-9-32, -33F, -34, -34F, -41<br />
DC-9-51<br />
DC-9-81 (MD-81)<br />
DC-9-82 (MD-82)<br />
DC-9-83,<br />
DC-9-87 (MD-87), -88, MD90-30<br />
Proximity System<br />
10<strong>01</strong>5561 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>459 ST<strong>01</strong>4<strong>04</strong>CH DC-9-10 SERIES<br />
Installation of Universal Avionics system<br />
17.02.2006<br />
DC-9-20 SERIES<br />
Corporation Multi-Function Display in<br />
DC-9-30 SERIES<br />
accordance with Electronic Cable Specialists<br />
DC-9-40 SERIES<br />
MasterData List ECS-200<strong>04</strong>16 rev. E dated<br />
DC-9-50 SERIES<br />
DC-9-81 (MD-81)<br />
DC-9-82 (CF6)<br />
DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
17.3.2003<br />
10<strong>01</strong>5679 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>660 ST<strong>01</strong>841CH BOEING 747-100<br />
Installation of GPS Antenna Provisions B747 1. This STC is approved only for the product<br />
31.07.2006<br />
BOEING 747-200C<br />
Series in accordance with ST<strong>01</strong>841CH configuration as defined in the approved design<br />
BOEING 747-200F<br />
data referred to in the paragraph<br />
BOEING 747-300<br />
5Documentation. Compatibility with other<br />
aircraft/engine configurations shall be<br />
determined by the installer.2. The Boeing<br />
10<strong>01</strong>5680 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>661 ST<strong>01</strong>877CH BOEING 747-100<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
10<strong>01</strong>5682 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>666 ST<strong>01</strong>923CH LOCKHEED 1<strong>01</strong>1-385-1<br />
LOCKHEED 1<strong>01</strong>1-385-1-15<br />
10<strong>01</strong>5684 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>668 ST<strong>01</strong>887CH DC-9-32<br />
DC-9-51<br />
DC-9-81 (MD-81)<br />
DC-9-82 (CF6)<br />
DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
MD-88<br />
10<strong>01</strong>5692 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>680 REV 2 FAA STC ST02162CH BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-800<br />
10<strong>01</strong>57<strong>01</strong> ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>689 REV 1 FAA STC ST02184CH DC 10-30 SERIES<br />
DC-10-10 SERIES<br />
MD-11<br />
Installation of a Honeywell Ground proximity<br />
Warning System in accordance with FAA STC<br />
ST<strong>01</strong>877CH<br />
Installation of a Honeywell Enhanced Ground<br />
Proximity Warning System in accordance with<br />
ST<strong>01</strong>923CH<br />
Installation of GPS antenna provisions in<br />
accordance with FAA STC ST<strong>01</strong>887CH<br />
Installation of elementary or Enhanced<br />
surveillance Mode S transponders.<br />
1. Airplane Flight Manual Supplement,<br />
Electronic Cable Specialists Doc. No. ECS-<br />
202314, Revision A, approved September 23,<br />
2005, orlater FAA approved revisions, are<br />
required on board the aircraft.2. Airplane Flight<br />
Manual Supplement, Electronic Cable Speci<br />
The equipment for which these provisions are<br />
intended has not been certified. Additional<br />
<strong>EASA</strong> approval is required for the installation of<br />
this equipment<br />
1. Only configurations 1, 2, 4, 5, 7, 8 and 9<br />
as listed in the Master Data List ECS-203150,<br />
Revision P, are deemed to be approved; 2.<br />
The AFM Supplement as listed in Appendix A<br />
of Electronic Cable Specialists Master Data<br />
List ECS-203150, Revision P,<br />
Installation of elementary and enhanced 1. ECS-203482 Rev. N/C AFM Supplement<br />
surveillance Mode S transponders In MD-11; for McDonnell Douglas MD11 Series with<br />
MD-11F; DC-10-10; DC-10-15; DC10-30; DC Enhanced Mode-S Transponder Upgrade with<br />
10-40; DC-10-10F; DC–10-30F; DC-10-40F in Flight ID from Transponder Control Panel.2.<br />
accordance with “Electronic Cables Specialists ECS 2<strong>04</strong>353 Rev N/C AFM Supplement for<br />
Master Data List ECS-203475”.<br />
Douglas DC-10 Series Airplane with Mode-S<br />
Transpon<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 200/<strong>462</strong><br />
07.12.20<strong>04</strong><br />
19.05.2006<br />
02.08.2006<br />
13.03.2006<br />
30.07.2008<br />
27.11.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5799 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>863 REV 1 FAA STC ST1193LA-T BOEING 767-300 SERIES Installation of Honeywell MCS-6000 SATCOM This installation must be installed in conjunction<br />
08.03.2007<br />
System<br />
with Honeywell STC <strong>EASA</strong>.IM.A.S.02276 for<br />
the installation of the SATCOM High-Gain<br />
Antenna and Diplexer / Low Noise Amplifier<br />
(D/LNA).<br />
10<strong>01</strong>5889 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02008 FAA STC STC02075CH AIRBUS A300 MODEL B2-1A Installation of Universal Avionics Systems Aircraft Flight Manual Supplement ECS<br />
20.09.2006<br />
AIRBUS A300 MODEL B2-1C Corporation Terrain Awareness and warning 2026<strong>04</strong>, revision B, dated 11 October 2005 or<br />
AIRBUS A300 MODEL B2-203 System (TAWS)<br />
later approved revisionInstruction for continued<br />
AIRBUS A300 MODEL B2K-3C<br />
airworthiness ECS 2026<strong>04</strong>, revision B, dated 5<br />
AIRBUS A300 MODEL B4-103<br />
December 2005If the holder agrees to permit<br />
AIRBUS A300 MODEL B4-203<br />
AIRBUS A300 MODEL B4-2C<br />
another person to use this certifi<br />
10<strong>01</strong>5992 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02146 ST00694CH DC-9-81 (MD-81)<br />
Installation of Dual Honeywell HT9100 GNSS 1. Limited to configuration III and IV.2.<br />
21.05.2007<br />
DC-9-82 (MD-82)<br />
GPS Navigation System.<br />
Compatibility of this design change with<br />
DC-9-83 (MD-83)<br />
previously approved modifications must be<br />
DC-9-87 (MD-87)<br />
determined by the installer.3. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design d<br />
10<strong>01</strong>6069 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02249 FAA STC ST02316CH DC-9-80 SERIES FAA STC ST02316CH - Elementary and Limited to configuration 3 of ECS MDL ECS-<br />
28.02.2007<br />
Enhanced Mode S.<br />
203350 Rev. G dated July 7, 2006.This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraphs "Description" and<br />
“Associated Technical Documentation”.<br />
10<strong>01</strong>6124 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02317 FAA STC ST02303CH BOEING 767-200, -300 SERIES Installation of Enhanced Mode-S Transponder. The Airplane Flight Manual Supplement as<br />
listed in Appendix A of Electronic Cable<br />
Specialists Master Data List, Document No.<br />
ECS-202463, Revision F, dated June 27,<br />
2006, or later approved revision is required on<br />
board the modified aircraft.<br />
10<strong>01</strong>6386 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02714 FAA STC SA<strong>01</strong>527CH PILATUS PC-12<br />
PILATUS PC-12/45<br />
PILATUS PC-12/47<br />
Installation of a Honeywell KMH 880 Multi-<br />
Hazard Awareness System or a Honeywell<br />
KTA 870 Traffic Advisory System.<br />
10<strong>01</strong>6388 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02716 FAA STC ST<strong>01</strong>479CH BOEING 737-300-900 SERIES Installation of a Smiths Industries Flight<br />
Management System Data Bus Portable<br />
Computing Device Recorder.<br />
10<strong>01</strong>6507 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.02873 FAA STC ST02182CH BOEING 747-100<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
BOEING 747-400<br />
BOEING 747-400D<br />
BOEING 747-400F<br />
BOEING 747-SR<br />
Installation of Elementary or Enhanced<br />
Surveillance Mode S Transponder iaw<br />
Electronic Cable Specialists Master Data List<br />
ECS-202128, rev. AB, 7 January 2008 or later<br />
approved revision.<br />
Limitations as per Master Data List PC-12, PC-<br />
12/45, PC-12/47, Installation of IHAS, ECS-<br />
200836 Revision L, dated August 29, 2006, or<br />
later FAA approved revision, Part III.<br />
Limitations<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 2<strong>01</strong>/<strong>462</strong><br />
14.06.2007<br />
10.03.2008<br />
17.07.2008<br />
20.10.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6659 ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.03120 FAA STC ST02612CH AIRBUS A318-111<br />
Installation of AD Aerospace Cockpit Door 1. Prior to installation of this modification the<br />
29.<strong>04</strong>.2009<br />
AIRBUS A318-112<br />
Monitoring System<br />
installer must determine that the<br />
AIRBUS A318-121<br />
interrelationship between this modificationand<br />
AIRBUS A318-122<br />
any other previously installed modification<br />
AIRBUS A319-111<br />
will introduce no adverse effect upon the<br />
AIRBUS A319-112<br />
AIRBUS A319-113<br />
AIRBUS A319-114<br />
AIRBUS A319-115<br />
AIRBUS A319-131<br />
AIRBUS A319-132<br />
AIRBUS A319-133<br />
AIRBUS A320-111<br />
AIRBUS A320-211<br />
AIRBUS A320-212<br />
AIRBUS A320-214<br />
AIRBUS A320-231<br />
AIRBUS A320-232<br />
AIRBUS A320-233<br />
AIRBUS A321-111<br />
AIRBUS A321-112<br />
AIRBUS A321-131<br />
AIRBUS A321-211<br />
AIRBUS A321-212<br />
AIRBUS A321-213<br />
AIRBUS A321-231<br />
AIRBUS A321-232<br />
airworthiness of the produc<br />
10027156 ELECTRONIC CABLE SPECIALISTS, Inc. P-<br />
FAA STC ST00646CH L1<strong>01</strong>1-385-1-15, L1<strong>01</strong>1-385-3 Installation of a single or dual<br />
None - Airplane Flight Manual Supplement, 10.09.2009<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>665<br />
L1<strong>01</strong>1-385-1, L1<strong>01</strong>1-385-1-14 Honeywell/Trimble HT900 GlobalNavigation<br />
document ECS-96<strong>01</strong>50 shall be<br />
System, configurations 1, 2 or 3 in accordance<br />
usedonboard the modified aircraftwithElectronic<br />
Cable Speciatlists Master Data<br />
Aircraft Maintenance Manual<br />
List, ECS-96<strong>01</strong>51, Rev. H datedJanuary 8,<br />
Supplement, document ECS-96<strong>01</strong>69<br />
1999 or later FAA approved revisions<br />
shall bepart of the Instructions for<br />
Validation<br />
Continued Airworthiness of the aircraft<br />
Prior to installat<br />
10027270 ELECTRONIC CABLE SPECIALISTS, Inc. P-<br />
FAA STC ST02637CH 737-100, 737-200, 737-200C, Installation of ECS EZMount (TM) mechanical see limitations and conditions on STC FAA Prior to installation of this modification it 17.09.2009<br />
<strong>EASA</strong>.IM.A.S.03122<br />
737-300, 737-400, 737-500, mounting assemblies<br />
ST02637CH<br />
must be determined thatthe<br />
737-600, 737-700, 737-800,<br />
interrelationship between this modification<br />
737-900, 737-900ER<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028835 ELECTRONIC CABLE SPECIALISTS, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.031<strong>01</strong><br />
FAA STC ST02626CH A318111/-112/-121/-122<br />
A319-111/-112/-113/-114/-115<br />
A319-131/-132/-133<br />
A320-111/-211/-212/-214/<br />
A320-214/-231/-232/<br />
A321-111/-112/-131/-211/-212<br />
A321-213/-231/-232<br />
100335<strong>01</strong> ELECTRONIC CABLE SPECIALISTS, Inc. <strong>EASA</strong>.IM.A.S.031<strong>01</strong> REV. 1 FAA STC ST02626CH A318-111, -112, -121, -122<br />
A319-111, -112, -113, -114<br />
A319-115, -131, -132, -133<br />
A320-111, -211, -212, -214<br />
A320-231, -232, -233<br />
A321-111, -112, -131, -211<br />
A321-212, -213, -231, -232<br />
10033754 ELECTRONIC CABLE SPECIALISTS, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03248<br />
·,,Electronic Cable Specialists Master Data<br />
List, ref. doc. ECS-206919,Revision E, dated<br />
9th September 2008 (*)·,,Airplane Flight<br />
Manual Supplement, ref. doc. ECS-206922,<br />
RevisionN/C, dated 29th September 2008<br />
(*)·,,Instructions for Continued Airworthiness<br />
FAA STC ST02708CH MD-11 Installation of EZMount (TM) Tilt mechanical<br />
mounting assembly onsidewalls of cockpit in<br />
accordance with Electronic Cable<br />
SpecialistsMaster Data List ECS-207476 Rev.<br />
A, dated March 4, 2009, or later FAAapproved<br />
revisions.Validation of FAA STC ST02708CH<br />
10039706 ELECTRONIC CABLE SPECIALISTS, Inc. FAA STC ST02923CH 737-600/-700/-800/-900/-900ER Validation of FAA STC ST02923CH: EFB<br />
Installation of ECS EZMountTMMechanical<br />
Mounting Assemblies<br />
None 1.,,Prior to installation of this modification 02.06.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2.,,The ins<br />
Installation of an EZMount Tilt Mechanical Not Applicable Prior to installation of this modification it 26.<strong>01</strong>.2<strong>01</strong>1<br />
Mounting AssemblyRevision of the <strong>EASA</strong> STC<br />
must be determined thatthe<br />
<strong>EASA</strong>.IM.A.S.031<strong>01</strong> to add Configuration 2<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
AFM Supplement as listed in Appendix A of<br />
Electronic Cable SpecialistsMaster Data List<br />
ECS-207476, Rev. A, dated March 4, 2009 or<br />
later FAAapproved revision, is required on<br />
board the modified aircraftThe equipment for<br />
which these provisions are intended is<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
1) This approval constitutes approval for the<br />
product.The installatio<br />
Prior to installation of this STC it must be<br />
EZMountTM MechanicalMounting Assemblies determined that theinterrelationship<br />
only. The capability of any system attached to between this modification and any other<br />
theEZMountTM Mechanical Mounting previouslyinstalled modification and / or<br />
Assembly requires additional <strong>EASA</strong>approval. repair will introduce no adverse<br />
2) The maximum allowed weight of any device effectupon the airworthiness of the<br />
to<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 202/<strong>462</strong><br />
23.06.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>09<strong>01</strong> ELECTRONIC CABLE SPECIALISTS, Inc. FAA STC ST02907CH B747-400<br />
Installation of ECS EZMount mechanical The equipment for which these provisions are AFM Supplement ECS 208936 for 02.08.2<strong>01</strong>2<br />
B747-400F<br />
mounting assemblies in accordancewith installed has not beencertified. Additional Boeing 747-400 series Aircraft<br />
Electronic Cable Specialists, Inc. Master Data approval is required for the installation of equippedwith ECS EZMount tilt is<br />
List ECS 209135,Revision H, dated November thisequipment and must be evaluated to assure required on board of the modified<br />
29, 2<strong>01</strong>1 or later approved revisionValidation of satisfactory compliance withapplicable aircraft.Prior to installation of this<br />
FAA STC ST02907CH<br />
airworthiness standards.<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification an<br />
10<strong>04</strong>1328 ELECTRONIC CABLE SPECIALISTS, Inc. FAA STC ST02961CH B737-600/-700/-800/-900/-900ER Validation of FAA STC ST02961CH - None 1) Prior to installation of this STC it must 07.09.2<strong>01</strong>2<br />
Approved configurations are thefollowing:-<br />
be determined that theinterrelationship<br />
Configuration 1: Replacement of Honeywell<br />
between this STC and any other<br />
Weather Radar System RDR-4Bwith<br />
previously installedmodification and / or<br />
Honeywell Honeywell Weather Radar RDR-<br />
repair will introduce no adverse effect<br />
4000,-Configuration 2: Software<br />
upon theairworthiness of the product. 2)<br />
upgrade to Honeywell WRS RDR-4<br />
This STC is <strong>EASA</strong><br />
10<strong>04</strong>2532 ELECTRONIC CABLE SPECIALISTS, Inc. FAA STC ST02992CH B737-600/-700/-800/-900/-900ER Validation of FAA STC ST02992CH -<br />
Installation of dual Electronic FlightBag (EFB)<br />
System Provisions.<br />
10<strong>01</strong>3942 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
10<strong>01</strong>3968 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
10<strong>01</strong>4112 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
10<strong>01</strong>4251 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
10<strong>01</strong>4341 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
10<strong>01</strong>4747 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
10<strong>01</strong>4812 ELECTRONIQUE MAINTENANCE<br />
AVIATION<br />
<strong>EASA</strong>.A.S.00378 REV. 1 FAIRCHILD SWEARINGEN SA<br />
226-T(<br />
- Installation of VHF 8.33<br />
KHz/VOR/ILS/GPS/STORMSCOPE/VHF 150<br />
MHz/UHF/ICS Passengers according to<br />
E.M.A. Modification Approval Sheet (FAM) No<br />
EMA/03/002/SA226Serie/VHF.GPSBRNAV.S<br />
TORM.UHF dated 22 December 2003.-<br />
Installation of GARMIN GNS 530A, STORM<br />
1) The aircraft operator must perform the<br />
instructions for continuedairworthiness and<br />
comply with the Airworthiness Limitation Items<br />
as perthe Instructions for Continued<br />
Airworthiness (ICA), ReferenceECS-209337,<br />
Revision G, dated 22 August 2<strong>01</strong>2. 2) Additio<br />
1. This modification is applicable only to SA<br />
226 T(B) s/n T298 F-GLPT.2. <strong>EASA</strong><br />
Approved Airplane Flight Manual Supplements<br />
"Supplément au manuel de vol GPS BRNAV"<br />
are required.3. This STC is approved only for<br />
the product configuration as defined i<br />
1) Prior to installation of this STC it must<br />
be determined that theinterrelationship<br />
between this STC and any other<br />
previously installedmodification and / or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product. 2)<br />
This STC is <strong>EASA</strong><br />
<strong>EASA</strong>.A.S.00738 REV. 1 FAIRCHILD SWEARINGEN SA Installation of GPS BRNAV, EGPWS, TAS, 1. This STC is limited to MSN T312 F-GRNT2.<br />
20.02.2006<br />
226-T(<br />
Stormscope, Radar, MFD- Garmin GNS 530 This STC is approved only for the product<br />
VHF.NAV.GPS, Honeywell RDR 2000 Radar, configuration as defined in the approved design<br />
BF Goodrich WX 500 Stormscope and Avidyne data referred to in the paragraph "Description".<br />
EX 500 MDF installation- BF Goodrich Sky 899 Compatibility with other aircraft/engine<br />
TAS and Honeywell KGP 560 EGPWS<br />
provision<br />
configurations shall be determin<br />
<strong>EASA</strong>.A.S.<strong>01</strong>217 BEECH C90<br />
Allied Signal KT73 ATC Mode S, Kannad This STC is limited to Beech C90 MSN LJ667<br />
13.06.2005<br />
BEECH E90<br />
406AF ELT 406 and 2 IDC 570 altimeters<br />
installation.<br />
& Beech E90 MSN LW 278.<br />
<strong>EASA</strong>.A.S.<strong>01</strong>473 BEECH 200 406 MHz ELT installation Modification applicable on s/n BB616 and<br />
BB202 only.<br />
05.08.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>6<strong>01</strong> FAIRCHILD SWEARINGEN SA ATC Mode S, ELT 406 MHz, Altimeter, Turn<br />
30.<strong>01</strong>.2006<br />
226-T(<br />
and Bank annunciator installation<br />
<strong>EASA</strong>.A.S.02930 FAIRCHILD SWEARINGEN SA Garmin GNS 530A VHF 8.33KHZ, Honeywell This STC is limited to the SA226 S/N T312 26.02.2007<br />
226<br />
KY 196B VHF 8.33 KHZ, BF Goodrich TAS<br />
SKY 899 Installation<br />
<strong>EASA</strong>.A.S.03<strong>01</strong>9 Installation of Avionic Upgrade according<br />
EMA/07/0<strong>01</strong>/SA226/VHF8.33-ATC-MFD-RDR<br />
30.<strong>04</strong>.2007<br />
10<strong>01</strong>4834 ELECTRONIQUE MAINTENANCE <strong>EASA</strong>.A.S.03050 BEECH 200 Installation of Garmin GTX330D Mode S<br />
21.<strong>04</strong>.2008<br />
AVIATION<br />
Transponder.<br />
10<strong>01</strong>5<strong>04</strong>5 ELECTRONIQUE MAINTENANCE <strong>EASA</strong>.A.S.03361 BEECH 200 Installation of new COM-NAV-GPS with AFM Supplement must be used when the<br />
<strong>04</strong>.08.2008<br />
AVIATION<br />
BRNAV capacity and coupled to AP.<br />
application is applied.Modification limited to sn<br />
BB616.<br />
10<strong>01</strong>7146 ELECTRONIQUE MAINTENANCE <strong>EASA</strong>.R.S.<strong>01</strong>249 EUROCOPTER FRANCE AS Installation of SAFE FLIGHT Power Line<br />
27.02.2007<br />
AVIATION<br />
355E<br />
Detector p/n 71<strong>01</strong>-5, in accordance with EMA<br />
EUROCOPTER FRANCE AS STC file n° 06/0<strong>01</strong>/AS355Serie/PLD revision 0,<br />
355F<br />
dated January 2006, or later <strong>EASA</strong> approved<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
revision.<br />
10<strong>01</strong>6097 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02286 TCCA STC SA07-9 BOMBARDIER CL-600-2B19 Iridium Antenna Installation 31.05.2007<br />
10<strong>01</strong>6098 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02287 TCCA STC SA07-3 BOMBARDIER CL-600-2B19 Aft Equipment Bay Steps 31.05.2007<br />
10<strong>01</strong>6099 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02288 TCCA STC SA07-4 BOMBARDIER CL-600-2B19 Ladder Stowage 31.05.2007<br />
10<strong>01</strong>6100 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02289 TCCA STC SA07-5 BOMBARDIER CL-600-2B19 Towbar Head Stowage 31.05.2007<br />
10<strong>01</strong>61<strong>01</strong> ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02290 TCCA STC SA07-6 BOMBARDIER CL-600-2B19 Main wheel stowage 31.05.2007<br />
10<strong>01</strong>6168 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02395 TCCA STC SA07-20 BOMBARDIER CL-600-2B19 Miscellaneous Storage Box, Project No. 29R2-<br />
707<br />
03.07.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 203/<strong>462</strong><br />
06.12.2<strong>01</strong>2<br />
05.02.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6169 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02396 TCCA STC SA07-21 BOMBARDIER CL-600-2B19 Towbar Stowage, Project No. 29R2-708. 03.07.2007<br />
10<strong>01</strong>6170 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02397 TCCA STC SA07-22 BOMBARDIER CL-600-2B19 Equipment Bay Forward Catwalk, Project No.<br />
29R2-709.<br />
03.07.2007<br />
10<strong>01</strong>6171 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02398 TCCA STC SA07-23 BOMBARDIER CL-600-2B19 Equipment Bay Stowage Box, Project No. Prior to installation of this modification the<br />
<strong>04</strong>.07.2007<br />
29R2-710.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6310 ELISEN TECHNOLOGIES <strong>EASA</strong>.IM.A.S.02612 TRANSPORT CANADA STC NO.<br />
SA07-<br />
BOMBARDIER CL-600-2B19 Lockable Fuels Caps. 21.11.2007<br />
10<strong>01</strong>5349 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.00503 REV. 1 FAA STC SA<strong>01</strong>352CH BEECH 200<br />
Installation of Dual TDR-94D Transponders 1. Limited to Aircraft equipped with Raytheon<br />
06.03.2006<br />
BEECH 200C<br />
with Flight ID in B200/B200C/B300/B300C Aircraft Company "Collins Pro Line 21 Avionics<br />
BEECH 200CT<br />
Aircraft with Pro Line 21 Avionics, in<br />
Suite" major change2. Limited to<br />
BEECH 200T<br />
accordancewith Configuration 3 of Elliott Configuration 3 of Elliott Aviation FAA STC<br />
BEECH 300<br />
Aviation Master Data List, No 2026-576DL, SA<strong>01</strong>352CH3. This STC is approved only for<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
BEECH B300<br />
BEECH B300C<br />
Revision 2 or later approved revision. the product configuration as define<br />
10<strong>01</strong>5683 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>667 FAA STC ST02007CH BEECH 400<br />
Certification for Reduced Vertical Separation 1. This STC is approved only for the product<br />
24.<strong>01</strong>.2006<br />
BEECH MU-300<br />
Minimum (RVSM) operational capability and configuration as defined in the approved design<br />
BEECH MU-300-10<br />
installation of Honeywell AZ-252 Air Data data referred to in the paragraph "Description".<br />
Computer and AM-250 Altimeter with optional Compatibility with other aircraft/engine<br />
BA-250 Altitude Indicator and AL-800 Altitude configurations shall be determined by the<br />
Preselector<br />
installer.2. Certification basi<br />
10<strong>01</strong>5693 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>681 FAA STC ST<strong>01</strong>486CH BEECH 400<br />
BEECH MU-300<br />
BEECH MU-300-10<br />
Installation of a Honeywell Mark VI/VIII<br />
EGPWS<br />
Validation Basis of the Change: FAR 25,<br />
additionally JAA Leaflet No. 12 (TAWS)<br />
10<strong>01</strong>5716 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>713 ST02194CH FALCON 10 ST02194CH: Installation of UNS EFI-890R<br />
EFIS<br />
Certification basis iaw CRI A1 IM.A.S.<strong>01</strong>713 13.02.2007<br />
10<strong>01</strong>5721 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>720 FAA STC ST<strong>01</strong>666CH FALCON 10 ST<strong>01</strong>666CH: Installation of a Rockwell Collins 1. Certification basis iaw CRI A1 IM.A.S.<strong>01</strong>720<br />
13.02.2007<br />
TCAS 4000Traffic Alert and Collission<br />
Avoidance System (TCAS II)<br />
and TGL Nr. 8<br />
10<strong>01</strong>5757 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>791 FAA STC SA02206CH BEECH 200<br />
Installation of Honeywell Digital Flight Data Limited to the aircraft types listed above with<br />
03.03.2006<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH 300<br />
BEECH 300C<br />
Recorder System (DFDR)<br />
Proline 21 Avionics Suite installed.<br />
10<strong>01</strong>5894 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02<strong>01</strong>4 FAA STC SA02264CH BEECH 300<br />
Airworthiness certification of Reduced Vaertical None 09.11.2006<br />
BEECH 300LW<br />
seperation Minimum (RVSM) and installation of<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B300<br />
BEECH B300C<br />
Air Data Systems<br />
10<strong>01</strong>5976 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02128 FAA ST5990CH-T FALCON 10 ST02333CH: Installation of a Universal<br />
Avionics SystemsCorporation(UASC) UNS-<br />
1K+/L FLIGHT MANAGEMENTSYSTEM<br />
(FMS), Dual Universal Avionics Radio<br />
ControlUnits (RCU), and/or dual Rockwell<br />
Collins VIR-32Navigation Receiver<br />
1. Certification basis FAR 25 Amdt 117 13.02.2007<br />
10<strong>01</strong>5978 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02130 SA<strong>01</strong>216CH BEECH 200<br />
Installation of Honeywell (Allied Signal) MK-VI 1. Compatibility of this design change with<br />
24.08.2006<br />
BEECH 200C<br />
Enhanced Ground Proximity Warning System, previously approved modifications must be<br />
BEECH 200CT<br />
Universal Avionics Systems Corporation determined by the installer.2. Airplane Flight<br />
BEECH 300<br />
Terrain Awareness Warning System and Manual Supplement, Elliott Aviation Report No.<br />
BEECH 300LW<br />
Universal Avionics Systems Multifunction EGPWS-FMS Rev 1, FAA approved August<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
BEECH B300<br />
BEECH B300C<br />
Display<br />
23, 2000, or later FAA approved revisio<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 2<strong>04</strong>/<strong>462</strong><br />
19.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6252 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02529 FAA STC SA02447CH BEECH 200<br />
Installation of a Rockwell Collins IFIS-5000<br />
27.02.2008<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH 300<br />
BEECH 300C<br />
Integrated Flight Information system.<br />
10<strong>01</strong>6254 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02532 FAA STC ST02431CH FALCON 10 <strong>EASA</strong> Validation of FAA STC<br />
The aircraft must be equipped with Universal<br />
13.05.2008<br />
ST02431CH<strong>EASA</strong> Validation is limited to Avionics EFI-890R Electronic Flight Instrument<br />
Provisions for Installation of a Universal System (EFIS) as installed by Elliott Aviation’s<br />
Avionics Application Server Unit (ASU) on STC <strong>EASA</strong>.IM.A.S.<strong>01</strong>713.This <strong>EASA</strong> Approval<br />
Falcon 10<br />
is limited to provisions for installation only with<br />
the ASU System deactiv<br />
10<strong>01</strong>6474 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02822 FAA STC ST02548CH FALCON 10 <strong>EASA</strong> Validation of FAA STC<br />
ST02548CHInstallation of an International<br />
Communications Group ICS-120 Iridium<br />
Satellite Telephone System<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6475 ELLIOTT AVIATION <strong>EASA</strong>.IM.A.S.02823 FAA STC ST02547CH FALCON 10 <strong>EASA</strong> Validation of FAA STC<br />
Prior to installation of this modification the<br />
ST02547CHInstallation of a Universal Avionics installer must determine that the<br />
Systems Corporation UL-7<strong>01</strong> UniLink System interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10029872 ELLIOTT AVIATION FAA STC STC02784CH BEECHJET 400/400A Installation of Honeywell Digital Flight Data None Prior to installation of this modification it 28.<strong>04</strong>.2<strong>01</strong>0<br />
RecorderValidation of FAA STC STC02784CH<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029873 ELLIOTT AVIATION FAA STC STC02783CH BEECHJET 400 Installation of an Artex C406-2 Emergency<br />
Locator Transmitter (ELT)Validation of FAA<br />
STC STC02783CH<br />
10<strong>01</strong>5890 EMBRAER - EMPRESA BRASILEIRA <strong>EASA</strong>.IM.A.S.02009 CTA STC2006S02-09 EMBRAER EMB-135BJ CTA STC2006S02-09 "Installation of a 30' 1. Limited to EMB-135BJ SN 145000802.<br />
LCD monitor and Playstation Entertainment Instructions for Continued Airworthiness Report<br />
System iaw Avionic Services master drawing No. 135-23-0008 Rev. 0 dtd. 9. Sep. 05 or<br />
list 135-23-0<strong>01</strong> Rev. D dtd. 28. Nov. 05 or later later accepted revision.2. This STC is<br />
approved revision<br />
approved only for the product configuration as<br />
defined in the approved design data<br />
10027373 EMBRAER - EMPRESA BRASILEIRA P-<br />
<strong>EASA</strong>.IM.A.S.03273<br />
ANAC STC 2009S05-14 EMB-500 Installation of a Honeywell HF Communications<br />
System, Model KHF-1050 andoptionally the<br />
Avtech Corporation SELCAL decoder, Model<br />
CSD-714.<br />
10038234 EMBRAER GPX Ltda. (PC 722) REV. 1 EMB-135BJ/LR/ER<br />
<strong>EASA</strong> Validation of ANAC STC 2<strong>01</strong>0S10-18.<br />
EMB-145<br />
Electronic Flight Bag<br />
EMB-145ER/EU/EP/MP/LR/LU/MK (EFB)Installation.Description as<br />
per:ESCMSC002-Rev A, dated 17th January<br />
2<strong>01</strong>2.Master Documents List ESCCCD003-<br />
Rev B, dated 17th January 2<strong>01</strong>2.<br />
10038291 EMBRAER GPX Ltda. (PC 722) EMB-135BJ <strong>EASA</strong> validation of ANAC STC N°2<strong>01</strong>1S09-<br />
02Installation of a cabinet and a 17'' video<br />
monitor on EMB-135BJ aircraft<br />
26.05.2008<br />
26.05.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.<strong>04</strong>.2<strong>01</strong>0<br />
Required Markings and Placards:-.In close<br />
proximity to the 5A breaker in panel LH circuit<br />
breaker "HFPWR". In close proximity to the<br />
30A breaker in circuit breaker of LPDU<br />
"HFAMPL". (If applicable) In close proximity to<br />
the 5A breaker in panel LH circuitbr<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
23.<strong>01</strong>.2007<br />
25.09.2009<br />
None<br />
product.The installatio<br />
None <strong>01</strong>.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.02.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 205/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039722 EMBRAER GPX Ltda. (PC 722) ANAC STC NO. 2009S10-20 EMB-135BJ The Certification Basis for the original product<br />
remains applicable tothis certificate/<br />
approval.The requirements for environmental<br />
protection and the associatedcertificated noise<br />
and/or emissions levels of the original product<br />
areunchanged and remain appl<br />
none none 18.05.2<strong>01</strong>2<br />
10031622 EMBRAER S.A. EMB-500 <strong>01</strong>.09.2009<br />
10032105 EMS AVIATION, Inc. REV. 1 FAA STC SR03333AT S-76A, S-76B, S-76C Installation of the Sky Connect Satellite Phone None Prior to installation of this modification it 21.09.2<strong>01</strong>1<br />
and Tracking System.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10038432 EMS AVIATION, Inc. FAA STC SR09583RC EC135 P1/P2/P2+/T1/T2/T2+ Installation of the Sky Connect Forte Iridium<br />
Satellite Phone and /orautomated reporting<br />
system (FAA STC SR09583RC)<br />
10<strong>04</strong>1<strong>01</strong>7 EMS AVIATION, Inc. FAA STC NO SR02569NY AS 350 B,AS 350 B1,AS 350 B2<br />
AS 350 B3,AS 350 BA,AS 350 D<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.02.2<strong>01</strong>2<br />
Installation of Sky Connect Tracking System This STC is not applicable to AS350B3 model If the holder agrees to permit another<br />
iaw Master Drawing ListMDL07094This STC is helicopters withmodification OP4305 (Arriel 2D person to use this certificate tomodify a<br />
the validation of FAA STC SR02569NY (last engine installation) incorporated.<br />
product, the holder must give to the other<br />
reissued April 15,2009)<br />
person writtenevidence of that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
10<strong>01</strong>6107 EMS TECHNOLOGIES CANADA LTD <strong>EASA</strong>.IM.A.S.02297 TCCA STC SA05-12, ISSUE 3, DAT Installation of EMS HSD-64/-128/-X/-400/-400i/- This STC is approved only for the product<br />
HD-710 High Speed Data Transceiver configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>5314 EMTEQ <strong>EASA</strong>.IM.A.S.0<strong>01</strong>84 FAA STC ST00221AT B727-100, B727-200 Installation of a Digital Flight Data Recorder<br />
Upgrade from 6 to 11 channels in accordance<br />
with Avitas Engineering Report No 92AMJT.<br />
003 R-1, Revision B, dated May 4, 1993 or<br />
later<br />
1. This approval should not be extended to<br />
other aircraft of this modelon which other<br />
previously approved modifications are<br />
incorporated, unless it is determined by the<br />
installer that the interrelationship between this<br />
10<strong>01</strong>5315 EMTEQ <strong>EASA</strong>.IM.A.S.0<strong>01</strong>85 FAA STC ST02006AT 727-100, 727-200<br />
change and any other previously ap<br />
Installation of an Allied Signal 18 Channel Flight 1. This approval should not be extended to<br />
Data Recorder (Upgrade) for Aircraft not other aircraft of this model on which other<br />
containing a Flight Data Acquisition Unit in previously approved modifications are<br />
accordance with Avitas Engineering Report No incorporated, unless it is determined by the<br />
99AMJT.<strong>04</strong>0R-1, No Revision, dated march installer that the interrelationship between this<br />
15, 1999, Appendix A, master Drawi<br />
change and any other previously a<br />
10<strong>01</strong>5645 EMTEQ <strong>EASA</strong>.IM.A.S.<strong>01</strong>609 REV 1 FAA STC ST02<strong>01</strong>9AT B767-300 Installation of Passenger Cabin Interior<br />
Arrangement<br />
10<strong>01</strong>5316 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.0<strong>01</strong>88 FAA STC ST02869AT BOEING 767-300 Installation of a passenger cabin interior<br />
arrangement in accordance with Master<br />
Drawing List ANST-<strong>04</strong>8-MDL, Revision C<br />
dated 27/05/20<strong>04</strong> or later <strong>EASA</strong> approved<br />
revision<br />
10<strong>01</strong>54<strong>04</strong> EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>115 FAA STC ST02780AT BOEING 757-200 Installation of Honeywell Mark V Enhanced<br />
Ground Proximity Warning System (EGPWS)<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the prod<br />
1. Subject to compliance with the provisions<br />
of Part 21 Subpart E, this STC and associated<br />
data shall remain valid until surrendered,<br />
withdrawn or otherwise terminated2. If<br />
transfer of this Certificate is requested under<br />
Part 21A.116 the STC will be<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 206/<strong>462</strong><br />
15.08.2<strong>01</strong>2<br />
27.06.2007<br />
07.10.20<strong>04</strong><br />
07.10.20<strong>04</strong><br />
02.02.2009<br />
<strong>01</strong>.10.20<strong>04</strong><br />
<strong>04</strong>.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5405 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>116 FAA STC ST02761AT BOEING 757<br />
Installation of Honeywell RESCU 406AF This STC is approved only for the product<br />
05.06.2005<br />
BOEING 767<br />
Emergency Locator Transmitter (ELT) configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5407 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>118 FAA STC ST02896AT AIRBUS A319 SERIES<br />
Installation of a Kannad Model 406-AF 1. This STC is approved only for the product<br />
26.10.2005<br />
AIRBUS A320 SERIES<br />
Emergency Locator Transmitter (ELT) configuration as defined in the approved design<br />
AIRBUS A321 SERIES<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5408 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>122 FAA STC ST02896AT FOKKER F.28 MARK <strong>01</strong>00 Installation of a Kannad Model 406-AF<br />
Emergency Locator Transmitter (ELT) in<br />
accordance with FAA STC ST02896AT dated<br />
22/07/05 or later <strong>EASA</strong>-approved revision.<br />
10.03.2006<br />
10<strong>01</strong>5566 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>470 FAA STC SA03020AT BAE JETSTREAM 31<strong>01</strong><br />
Installation of Sandel Model ST3400 Terrain<br />
BAE JETSTREAM 32<strong>01</strong> SERIES Awareness and Warning System (TAWS)<br />
10<strong>01</strong>5568 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>475 FAA STC ST02793AT BEECH 1900D Installation of Honeywell Mk VI Enhanced 1. AFMS is required on-board for operation<br />
Ground Proximity Warning System (EGPWS). with Beechcraft 1900 D series.<br />
10<strong>01</strong>5569 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>476 FAA STC ST03022AT EMBRAER EMB-120 Installation of Sandel Model ST3400 Terrain<br />
Awareness and Warning System<br />
10<strong>01</strong>5570 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>477 FAA STC SA02821AT BEECH 1900D<br />
Installation of Sandel Model ST3400 Terrain<br />
RAYTHEON 1900C<br />
Awareness and Warning System<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.2. AFMS is required o<br />
10<strong>01</strong>5571 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>478 FAA STC ST03003AT BOEING 767-200<br />
Honeywell Mk V Enhanced Ground Proximity<br />
<strong>01</strong>.12.2005<br />
BOEING 767-300<br />
Warning System Installation<br />
10<strong>01</strong>5638 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>595 REV 1 FAA STC ST02929AT 1. BAE JETSTREAM 31<strong>01</strong> Installation of an ARTEX Model C406-1 ELT 1. This STC is approved only for the product<br />
12.09.2006<br />
2. BOEING 727-100<br />
Emergency Locator Transmitter (ELT) in configuration as defined in the approved design<br />
3. BOEING 737-100<br />
accordance with EMTEQ Master Drawing data referred to in the paragraph "Description".<br />
4. BOEING 747-100<br />
List(s) (MDL)as contained in EMTEQ Approved Compatibility with other aircraft/engine<br />
5. BOEING 757-200 SERIES Model List (AML), Document No.2-22566-002, configurations shall be determined by the<br />
6. BOEING 767-200<br />
Revision G, dated 09 June 2006, or later installer.2. This approval shou<br />
7. BOEING 777-200 SERIES<br />
8. DC-9-10 SERIES<br />
BOEING 727-200<br />
BOEING 737-200<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-800<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
BOEING 747-400 SERIES<br />
BOEING 747-SP<br />
BOEING 767-300<br />
DC-9-20 SERIES<br />
DC-9-30 SERIES<br />
DC-9-40 SERIES<br />
DC-9-50 SERIES<br />
approved r<br />
10<strong>01</strong>5828 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>917 FAA STC ST03212AT BOEING 737-300 SERIES Installation of an Active Noise Reduction (ANR)<br />
23.05.2006<br />
BOEING 737-400 SERIES<br />
BOEING 737-500 SERIES<br />
Headset<br />
10<strong>01</strong>5951 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.02093 FAA STC ST03269AT BAE JETSTREAM 31<strong>01</strong><br />
Installation of a Honeywell CAS 67A Traffic<br />
<strong>01</strong>.08.2006<br />
BAE JETSTREAM 32<strong>01</strong> SERIES Alert & Collision Avoidanc System II (TCAS II)<br />
& Dual Mode S Transponder<br />
10<strong>01</strong>6111 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.023<strong>01</strong> FAA STC ST03345AT BOEING 767-200<br />
Installation of an Enhanced Surveillance None 26.02.2007<br />
BOEING 767-300<br />
System (EHS) to expand Transponder Mode-S<br />
functionality<br />
10<strong>01</strong>6113 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.02303 FAA STC ST02297AT AIRBUS A300 MODEL B2-203 This installation added three additional<br />
21.06.2007<br />
AIRBUS A300 MODEL B4-103 parameters to be recorded bby the existing<br />
AIRBUS A300 MODEL B4-203 Flight Data Recorder.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 207/<strong>462</strong><br />
10.<strong>01</strong>.2006<br />
<strong>01</strong>.12.2005<br />
19.12.2005<br />
28.11.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6180 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.02409 FAA STC ST03394AT BAE JETSTREAM 41<strong>01</strong> Installation of an Avionics Innovations DMP- Prior to installation of this modification the<br />
30.<strong>01</strong>.2009<br />
100/-200 Digital Media Player (DMP) for installer must determine that the<br />
reproduction of Boarding Music and Cabin interrelationship between this modification and<br />
Briefings<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6433 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.02773 FAA STC ST03<strong>462</strong>AT BOEING 767-200<br />
BOEING 767-300<br />
BOEING 767-400<br />
10<strong>01</strong>6434 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.02774 FAA STC ST03461AT BOEING 757-200<br />
BOEING 757-300<br />
Install the RAAS software in the Runway<br />
Awareness & Advisory System (RAAS)<br />
Installation of the Honeywell Runway<br />
Awareness & Advisory System (RAAS).<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.This STC is<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6658 EMTEQ ENGINEERING <strong>EASA</strong>.IM.A.S.03119 FAA STC ST03660AT PILATUS PC-12 LED Position Lights InstallationRemoved 1. Prior to installation of this modification the<br />
Equipment:- Existing Left and Right Wing Tip, installer must determine that the<br />
and Tail Position LightsNew Installed<br />
interrelationship between this modification and<br />
Equipment:- Red LED Position Light Assy, P/N any other previously installed modification will<br />
03-9000-1103- Green LED Position Light Assy, introduce no adverse effect upon the<br />
P/N 03-9000-21<strong>04</strong>- White LED Position Light airworthiness of the product.2.<br />
10033802 EMTEQ ENGINEERING FAA STC ST03282AT B737-600, B737-700<br />
B737-800, B737-900<br />
Installation of Dual Collins HFS-900 High<br />
Frequency (HF) communicationsystem.<br />
10035812 EMTEQ ENGINEERING FAA STC ST03906AT CL-600-2B19 Installation of EMTEQ LED Anticollision/Position<br />
(Navigation) Light inthe<br />
Bombardier Regional Jet Series 100/200/440<br />
Aircraft<br />
10036838 EMTEQ ENGINEERING REV. 1 FAA STC ST03918AT 777-200, 777-200LR<br />
777-300, 777-300ER<br />
10037<strong>01</strong>8 EMTEQ ENGINEERING FAA STC ST03253AT 757-200, 757-200CB<br />
757-200PF, 757-300<br />
FAA STC ST03918AT: Installation of the<br />
Honeywell MCS-7200 SATCOM System<br />
Installation of the Honeywell MK II Aircraft<br />
Communication Addressingand Reporting<br />
System (ACARS).<br />
10037514 EMTEQ ENGINEERING FAA STC ST03606AT B757-200/-200CB/-200PF/-300 Installation of the Iridium Communication<br />
System (ICS)<br />
05.06.2008<br />
05.06.2008<br />
21.<strong>01</strong>.2009<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.02.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.07.2<strong>01</strong>1<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.10.2<strong>01</strong>1<br />
Compliance with <strong>EASA</strong> AMC 20-9 and AMC<br />
20-10 has not been shown.<br />
Prior to installation of this modification it 25.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.12.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 208/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038431 EMTEQ ENGINEERING REV. 1 FAA STC ST03345AT B737-300/-400/-500 Validation of FAA STC No. ST03345AT issued None Prior to installation of this modification it 16.02.2<strong>01</strong>2<br />
27 October 2006. Installationof Elementary<br />
must be determined thatthe<br />
Surveillance System / Enhanced Surveillance<br />
interrelationship between this modification<br />
System(ELS/EHS) in the Boeing 737-300/-400/-<br />
and any other previouslyinstalled<br />
500 series aircraft. Installationof EHS capable<br />
modification and/ or repair will introduce<br />
Mode S transponders and ELS capabl<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong><strong>01</strong>85 EMTEQ ENGINEERING FAA STC ST03846AT ATR 42-200/-300/-320<br />
ATR 42-500<br />
ATR 72-1<strong>01</strong>/-102/-2<strong>01</strong>/-202<br />
ATR 72-211/-212/-212A<br />
Installation of the IMS Flight Deck Ressources<br />
SkyTab 32<strong>01</strong> ElectronicFlight Bag (EFB)<br />
SystemThis STC is installing the SkyTab 32<strong>01</strong><br />
EFB mount arm/device andelectrical supply, as<br />
well as a Satellite Weather Receiver together<br />
withits antenna.<br />
10<strong>01</strong>6117 ENGINE TECHNOLOGIES, INC. <strong>EASA</strong>.IM.A.S.02309 FAA STC SA10588SC CIRRUS SR22 Validation of FAA STC SA10588SC<br />
"Installation of modified Teledyne Continental<br />
Motors IO-550-N engine equipped with<br />
turbonormalizing system"<br />
10<strong>01</strong>6699 ENGINE TECHNOLOGIES, INC. <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>3 SE10589SC TELEDYNE IO-550-G Installation of turbonormalizing system in<br />
accordance with Engine Technologies, Inc.<br />
Master Drawing List Number ETI-G2-1, Rev.<br />
NC, dated November 1, 2006, or later FAA<br />
approved revision.<br />
10029711 ERWIN AERO INTERNATIONAL LTD. REV. 1 TCCA LSTC C-LSA09-321/D DHC-6-300 Avionics to installed in acc. with PAA Design<br />
Group Modification DataSummary: R0910773,<br />
Issue A, approved 31 December 2009 with<br />
TransportCanada approved Flight Manual<br />
Supplements in acc. to TCCA STCC-LSA09-<br />
321/D<br />
10029999 ESG ELEKTRONIKSYSTEM- P-<strong>EASA</strong>.R.S.<strong>01</strong>419 BK 117 C-2 FLIR Mission Work Station PTA-THInstallation<br />
of a FLIR Star Safire HD System and an<br />
Operator Console inaccordance with ESG<br />
GmbH MDL 0005-MDL-006 based on ESG<br />
change no. 0005.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.06.2<strong>01</strong>2<br />
Installation of STC SE10589SC<br />
(<strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>3) is requiredAn oxygen<br />
system meeting requirements of CS23.1441<br />
through 23.1449 must be installed in<br />
conjunction with this STCThe installer must<br />
determine, if this design is compatible with<br />
previously approve<br />
1. Approval of this change in type design<br />
applies to the above model engine only. This<br />
approval should not be extended to enginesof<br />
this model on which other previously approved<br />
modifications are incorporated unless it is<br />
determined that the interrelatio<br />
11.05.2007<br />
02.<strong>04</strong>.2007<br />
Limited to: S/N 840 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
19.<strong>04</strong>.2<strong>01</strong>0<br />
-ESG GmbH Minor Change 0003 and STC<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>489 have to beinstalled as<br />
prerequisite for the installation of this<br />
modification.-This approval does not include<br />
the operation of laser pointer or laserilluminator<br />
devices.<br />
Prior to installation of this modification it 10.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10030259 ESG ELEKTRONIKSYSTEM- MBB-BK 117 B-2 Star SAFIRE and Mission Console<br />
This approval does not include the operation of Prior to installation of this modification it 07.06.2<strong>01</strong>0<br />
BK117Installation of FLIR Star Safire HD laser pointer or laserilluminator devices. must be determined thatthe<br />
System on a bolster step on the RHside,<br />
interrelationship between this modification<br />
mission console, equipment rack, operator and<br />
and any other previouslyinstalled<br />
observer seats onadapter plates in the cabin, in<br />
modification and/ or repair will introduce<br />
accordance with ESG GmbH MDL0<strong>01</strong>2-MDL-<br />
no adverse effectupon the airworthiness<br />
006 based o<br />
of the product.<br />
10<strong>04</strong>2409 ESG ELEKTRONIKSYSTEM- <strong>EASA</strong>.R.S.<strong>01</strong>577 EC135 P1, EC135 P2,<br />
EC135 P2+, EC135 T1,<br />
EC135 T2, EC135 T2+.<br />
Trakka A800 Searchlight InstallationGimbal<br />
installation of a 800W searchlight and related<br />
electrical andmechanical provisions.<br />
10<strong>01</strong>6724 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>022 REV. 1 TCCA STC SH96-39 AS 350 BA/B2/B3 Two place forward passenger seat (RH) 1. Refer to Flight manual supplement<br />
attached to STC SH96-39 issue 5 approved 12<br />
April 1996 or later approved revision.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Des<br />
- Activation and/or use of IR-Filter is not Prior to installation of this modification it 29.11.2<strong>01</strong>2<br />
approved- Activation and/or use of Laser is not must be determined thatthe<br />
approved<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 209/<strong>462</strong><br />
19.12.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6725 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>023 REV. 1 TCCA STC SH 96-32 AS350BA, AS350B2, AS350B3 Left-side pilot configuration Note: Revision of None Prior to installation of this modification it 13.12.2<strong>01</strong>0<br />
<strong>EASA</strong> STC ref. <strong>EASA</strong>.IM.R.S.<strong>01</strong>023 being a<br />
must be determined thatthe<br />
validation ofTCCA STC SH 96-32 at issue 7.<br />
interrelationship between this modification<br />
This STC revision is validation of TCCASTC<br />
and any other previouslyinstalled<br />
SH 96-32 at issue 11 and includes the left-side<br />
modification and/ or repair will introduce<br />
pilot configurationchange made to<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6728 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>031 TCCA STC SH 97-15 AS 350 B/BA/B1/B2/B3/D Installation of LH and/or RH Cargo pods 1. This STC is approved only for the product<br />
(Squirrel Cheeks")Master Drawing List MDL-94- configuration as defined in the approved design<br />
0<strong>04</strong> and associated maintenance<br />
data referred to in the paragraph "Description".<br />
instructionsFlight manual supplement FMS- Compatibility with other aircraft/engine<br />
ECL-9, revision 2 or later TCCA approved configurations shall be determined by the<br />
revisions<br />
installer.<br />
10<strong>01</strong>6747 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>073 TCCA STC SH 96-31 AS 350 B/BA/BB/D/B1/B2/B3<br />
AS 355 E/F/F1/F2<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
Relocation of higher capacity battery to tail<br />
boomMaster Drawing List MDL-<strong>04</strong>-003 and<br />
MDL-96-0<strong>01</strong> associated installation procedure<br />
and maintenance instructions.Flight Manual<br />
Supplement attached to STC SH96-31 issue 6,<br />
approved 25 March 1996 or later TCCA ap<br />
10<strong>01</strong>6825 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>195 TCCA STC SH00-1 ISSUE 3 AS 350 B, AS 350 B1, AS 350 B2 Installation of high visibility main and aft cabin<br />
AS 350 B3, AS 350 BA, AS 350 D doorsrefer to TCCA STC SH00-1 issue N°3,<br />
July 25, 2003<br />
10<strong>01</strong>6845 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>221 TCCA STC SH05-18 AS 350 B/B1/B2/B3/BA/D/D1 Installation of Forward Short High-visibility<br />
Doors (350-202414).<br />
10<strong>01</strong>6935 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>321 TCCA STC SH97-34 ISSUE 3 AS 350 B/B1/B2/B3/BA/D<br />
AS 355 E/F/F1/F2/N<br />
Installation of Forward Opening Rear Cargo<br />
Doors.(Modification approved by TCCA under<br />
STC SH97-34 Issue 3).<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Refer to TCCA STC SH00-1 issue N°3, July<br />
25, 2003<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1; This STC is approved only for the production<br />
configuration as defined in the approved design<br />
data referred to in the paragraph “Description”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.Installation of th<br />
10<strong>01</strong>7000 EUROCOPTER CANADA Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>410 TCCA STC SH03-33 EC 130 B4 Cargo Pods Installation 12.06.2008<br />
10038250 EUROCOPTER CANADA Ltd. TCCA STC SH94-29 1- AS350B, BA, B1, B2, B3, D Title: Left-Hand Litter KitDescription: Installation Configuration must be in accordance with Prior to installation of this modification it 31.<strong>01</strong>.2<strong>01</strong>2<br />
2- AS355E, F, F1, F2, N, NP of Left-Hand Litter Kit P/N 350-200034 or Eurocopter Canada MasterDrawing List No. must be determined thatthe<br />
P/N350-20<strong>01</strong>94 in accordance with Eurocopter MDL-99-0<strong>01</strong>, Issue F, or later approved interrelationship between this modification<br />
Canada Master Drawing List No.MDL-99-0<strong>01</strong>. revisions.Approved configurations are listed in and any other previouslyinstalled<br />
The Left-Hand Litter Kit provides med-evac the attached table.<br />
modification and/ or repair will introduce<br />
capabilities fornon-EMS dedicate<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1637 EUROCOPTER CANADA Ltd. TCCA STC SH12-10 EC130B4 Door handle installation (P/N 120-200<strong>01</strong>4)This<br />
STC is the validation of TCCA STC SH12-10<br />
(issue date -February 10,2<strong>01</strong>2)<br />
10<strong>04</strong>1736 EUROCOPTER CANADA Ltd. TCCA STC SH11-35 EC130B4 Glare Shield Modification P/N 130-885114This<br />
STC is the validation of TCCA STC SH11-35<br />
(issue No. 1 dtdSeptember 20, 2<strong>01</strong>1)<br />
10033870 EUROCOPTER DEUTSCHLAND GmbH P-<strong>EASA</strong>.R.S.<strong>01</strong>568 EC120B Installation on an EC120B helicopter of a<br />
ETSO-certified (ETSO C113)Moving Map<br />
system (MT VisionAir EPIII)<br />
12.10.2005<br />
12.10.2005<br />
12.05.2006<br />
05.07.2007<br />
18.10.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.10.2<strong>01</strong>2<br />
None The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21.A.118A. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or re<br />
11.10.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.02.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 210/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039633 EUROCOPTER DEUTSCHLAND GmbH LBA STC EMZ NR. 0654/3058 BO105 LS A-3 Title: Superlifter Conversion Kit 105-<br />
None The implementation of the modified 24.05.2<strong>01</strong>2<br />
8003331Description:Original STC: The model<br />
cargo hook 105-8031<strong>01</strong> is onlyapproved<br />
BO105 LS A-3 is changed in accordance<br />
after conversion of the helicopter in<br />
withdrawing No. 105-800331. The changed<br />
accordance with drawingNo. 105model<br />
is called "Superlifter".Revision 1: The<br />
800331.This STC is valid in conjunction<br />
Airworthiness Limitations related to EMZ Nr.<br />
with the <strong>EASA</strong> TCDS R.<strong>01</strong>1 in<br />
0654/3<br />
theapplicable version. This Supplemental<br />
Type<br />
10<strong>04</strong>1899 EUROCOPTER DEUTSCHLAND GmbH EC 120 B Installation of GTN 650 Unit on EC 120B none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.10.2<strong>01</strong>2<br />
10<strong>01</strong>7128 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>216 EUROCOPTER FRANCE AS<br />
355N<br />
10<strong>01</strong>7136 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>230 REV. 1 EC135-P1+, EC135-P2+ Change to existing <strong>EASA</strong> STC<br />
EC135-T1, EC135-T2, EC135-T2+ <strong>EASA</strong>.R.S.<strong>01</strong>230 - NVG Compatible<br />
LightingSystem - to extend the approved Night<br />
Vision Goggle types to allowsingle pilot<br />
operations and to include the latest EC135<br />
types.<br />
Integration of minor and major changes to 1. Limited to AS355N, S/N 5708 OE-XDM2.<br />
Storm Light, 406MHz ELT, STBY Altimeter, This STC is approved only for the product<br />
Exhaust heat shield, Autopilot, ADI, COM/NAV, configuration as defined in the approved design<br />
Transponder, Audiopanel, GNS 530, Compass data referred to in the paragraph "Description".<br />
System and Instrument Panel<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined b<br />
13.10.2005<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The fi<br />
20.11.2009<br />
10<strong>01</strong>7177 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>295 EUROCOPTER DEUTSCHLAND Variable External Playload Configuration<br />
MBB-BK<br />
Refer to above RFM Supplements 16.03.2007<br />
10<strong>01</strong>7199 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>348 EUROCOPTER DEUTSCHLAND Installation of Honeywell Avionics MKXXII As defined in the AFM Supplement No. 34 03.<strong>04</strong>.2007<br />
EC-135-<br />
EGPWS<br />
10<strong>01</strong>7219 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>376 EUROCOPTER FRANCE AS Re-Instatement of approval for Category A<br />
13.<strong>04</strong>.2007<br />
365N3<br />
Operations reference FAR 29 Amendment 16<br />
10<strong>01</strong>7253 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>456 EUROCOPTER FRANCE AS Installation of NAT 611-<strong>01</strong>4 Voice Warning<br />
365N3<br />
Generator (AVAD).<br />
10<strong>01</strong>7256 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>463 REV. 1 EUROCOPTER DEUTSCHLAND Installation of FreeFlight 21<strong>01</strong> I/O Approach Prior to installation of this modification the<br />
EC-135-<br />
Plus GPS with navigation information installer must determine that the<br />
interfaced to the aircraft FCDS and the aircraft interrelationship between this modification and<br />
AFCS for coupled autopilot operations, iaw any other previously installed modification will<br />
Drawing No. A3/1351114-100.<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7260 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>469 EUROCOPTER DEUTSCHLAND<br />
EC-135<br />
10<strong>01</strong>7264 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>475 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
10<strong>01</strong>7269 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>489 EUROCOPTER FRANCE AS<br />
355NP<br />
10<strong>01</strong>7270 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>490 EUROCOPTER FRANCE AS<br />
355NP<br />
Installation of honeywell EGPWS Mk XXII.<br />
Installation of Honeywell EGPWS XXII iaw<br />
drwg. no. A3/1351134-100 with aural and<br />
display based on ECUK modification<br />
MHL/135/1134.<br />
Installation of STAR SAFIRE HD FLIR (based<br />
on EC UK modification MHL/135/1116)..<br />
ECUK modifcation MCH/A/135/1075 must be<br />
installed as prerequisite.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
Installation of a Leo II FLIR System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Installation of SFIM 85T31 3 Axis Autopilot 0 Prior to installation of this modification the<br />
System<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the pro<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 211/<strong>462</strong><br />
22.<strong>04</strong>.2008<br />
11.12.2008<br />
<strong>01</strong>.09.2008<br />
14.11.2008<br />
13.<strong>01</strong>.2009<br />
14.<strong>01</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7271 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>491 EUROCOPTER FRANCE AS Installation of an alternate Pitot System Prior to installation of this modification the<br />
11.12.2008<br />
355NP<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7281 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>529 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
FSI STAR SAFIRE FLIR SKID<br />
MOUNTEDOptional installation of an external<br />
FLIR camera FSI Star Safire on the right hand<br />
1) Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
multifunction carrier. The installation is basedon andany other previously installed modification<br />
EC UK change MHL/135/1155 and in will introduce no adverse effect upon the<br />
accordance with drawing number A4/1351155- airworthiness of the product.2) The ins<br />
100-1 Issue A<br />
10<strong>01</strong>7284 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>532 REV. 1 EC 135 T2+, EC 135 P2+ Installation of Spectrolab Nightsun XP Skid<br />
Mounted System. Equipmentinspection and recertification<br />
to close the requirement for AD<br />
No.2<strong>01</strong>0-<strong>01</strong>83R1.<br />
10<strong>01</strong>7288 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>537 EUROCOPTER DEUTSCHLAND<br />
BK117 C<br />
10<strong>01</strong>7294 EUROCOPTER UK Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>578 EUROCOPTER DEUTSCHLAND<br />
EC-135-<br />
- Installation of a MX 15 FLIR, Skid Mounted 1. The EC UK change ¿¿¿/¿/145/10<strong>01</strong> must<br />
(Meeker Mount)- Installation of a MX 15 FLIR be installed prior to the installation of<br />
in combination with the installation of<br />
MHL/145/1157.2. Prior to installation of this<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>489. The installation is based modification the installer must determine that<br />
on EC UK MHL/145/1157 i.a.w. Drw. No. the interrelationship between this modification<br />
A2/1451157-100.<br />
and any other previously in<br />
Bucher 16g Stretcher InstallationInstallation of<br />
Bucher Leichtbau 16g Stretchers and<br />
Associated Equipment in the Rear Cabin. The<br />
installation is based on EC UK Major Change<br />
MCH/A/98/480H, in accordance with Master<br />
Drawing No. A0/98480-100 Issue B.This STC<br />
09.06.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.11.2<strong>01</strong>0<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10027764 EUROCOPTER UK Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>588 EC135 T2+, EC135 P2+ Title: Installation of an External Camera and<br />
related ENG equipment Description: Installation<br />
of an Axsys Technologies Cineflex V14<br />
Camerabased on EC UK change<br />
MHL/135/1200 as defined in Drw.<br />
No.A3/1351200-100-1 Issue A and installation<br />
of the related ENG<br />
None None 30.10.2009<br />
10028856 EUROCOPTER UK Ltd. BK117 C-2 Cabin ConfigurationDefinition of permissible None Prior to installation of this modification it 16.02.2<strong>01</strong>0<br />
configurations and combinations ofindividually<br />
must be determined thatthe<br />
approved changes based on EC UK Major<br />
interrelationship between this modification<br />
Change MHL/145/1229Iss. A into the BK117 C-<br />
and any other previouslyinstalled<br />
2.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028925 EUROCOPTER UK Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>590 BK117 C-2 Bucher 16G stretcher None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.02.2<strong>01</strong>0<br />
10029165 EUROCOPTER UK Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>591 MBB-BK117-C2 Martin Baker Swivelling Passenger Seats None The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
09.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 212/<strong>462</strong><br />
31.03.2009<br />
15.06.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029931 EUROCOPTER UK Ltd. REV. 1 MBB-BK117 C-2 Cabin Configuration - Installation of Police or None Prior to installation of this modification it 11.06.2<strong>01</strong>0<br />
Emergency Medical SystemRole Equipment<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030287 EUROCOPTER UK Ltd. MBB-BK 117 C-2 Wescam HDi FLIR camera system.Installation<br />
of Wescam HDi FLIR camera system with<br />
build standards foralternate installation of MX-<br />
15 Analogue system in accordance with EC<br />
UKchange no. MHL/145/1211, Master<br />
Drawings A3/1451211-100-1&-2.<br />
Theinstallation is inc<br />
1. Following items must be installed on the<br />
aircraft prior toincorporation of this<br />
change:ACS/MEEKER Utility step on the right<br />
hand side, p/n AFM/SM117A-11 andrelated<br />
Arm p/n AF-SM117-C10 installed i.a.w. STC<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>489 2. This approval does not<br />
inc<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030343 EUROCOPTER UK Ltd. BK117 C-2 (EC145) Dual Martin Baker Swivelling Passenger Seats As identified in RFMS 19 None 11.06.2<strong>01</strong>0<br />
10031371 EUROCOPTER UK Ltd. AS350B3 Coupling of the existing Sagem/SFIM Autopilot<br />
installation with theGarmin GNS530<br />
10031633 EUROCOPTER UK Ltd. MBB-BK 117C2 Skyshout SystemInstallation of a Skyshout<br />
System. With internal cabin control andexternal<br />
loudspeaker array, installed on aircraft RHS<br />
and configuredwith low skid landing gear<br />
10032268 EUROCOPTER UK Ltd. REV. 1 EC135 T2+ NVIS Certification for EC135 T2+REV. 1 is<br />
implementing administrative changes<br />
10033580 EUROCOPTER UK Ltd. EC 135 T1(CDS)<br />
EC 135 T1(CPDS)<br />
EC 135 T2(CPDS)<br />
EC 135 T2+<br />
Installation of Spectrolab Nightsun XP on<br />
EC135 equipped with ECUKequipment pod.<br />
Equipment inspection and re-certification to<br />
close therequirement for AD No. 2<strong>01</strong>0-<br />
<strong>01</strong>83R1. Note: Identical to STC with ref.<br />
10032575, re-issued for<br />
administrativepurposes.<br />
10034086 EUROCOPTER UK Ltd. REV. 1 EC 130 B4 Installation of Sagem Cockpit Display System<br />
MHL/130/1245 and revisionto Eurocopter UK<br />
EC130B4 Supplement No. 1<br />
10039454 EUROCOPTER UK Ltd. EC135 P1 Installation of Kelvin 275 Camera per Drawing<br />
List DL/1352<strong>04</strong>4-0<strong>01</strong>, IssueA<br />
100397<strong>04</strong> EUROCOPTER UK Ltd. EC 135 P1 Cabin ConfigurationInstallation of equipment<br />
rack and pedestal mounted LCD monitor in<br />
theforward cabin, as per ECD design change<br />
EC UK/135/2<strong>04</strong>3<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.08.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.09.2<strong>01</strong>0<br />
None The first installation of this STC must be<br />
performed with the assistanceof the STC<br />
holder.This rotorcraft employs Night<br />
Vision Imaging System lighting,<br />
commonlynamed NVIS lighting, that has<br />
been certified to ensure the aircraft<br />
iscompatible with night visi<br />
11.02.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.11.2<strong>01</strong>0<br />
Prerequisite<br />
Prior to installation of this modification it <strong>04</strong>.03.2<strong>01</strong>1<br />
changes:MHL/130/1246,,,,,,TWX670 Weather must be determined thatthe<br />
detection systemMHL/130/1070,,,,,,KRA405B interrelationship between this modification<br />
Radio AltimeterMHL/130//1069,,,,,,Avidyne and any other previouslyinstalled<br />
TAS620 Traffic Advisory<br />
modification and/ or repair will introduce<br />
SystemMHL/130/952,,,,,,Replacement of no adverse effectupon the airworthiness<br />
GNS430 with GNS530WSTC<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>061,,Installation o<br />
of the product<br />
-Day/Night VFR operation only-Operation of<br />
the Kelvin 275 camera approved under this<br />
STC (EC UKmodification EC UK/135/2<strong>04</strong>4)<br />
has to be done, in conjunction with EC<br />
UKmodifications EC UK/135/2<strong>04</strong>5 and EC<br />
UK/135/2<strong>04</strong>3<br />
Prior to installation of this modification it <strong>04</strong>.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 213/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0937 F&M ENTERPRISES INC. FAA STC SE7559SW 1. C-75 SERIES, C-85 SERIES Install adapter to permit use of a spin-on oil Engines modified in accordance with this STC In order to install this modified engine in 06.08.2<strong>01</strong>2<br />
2. C090 SERIES, O-200 SERIES filter in accordance withF. & M. Enterprises' will not differ inperformance or operating an aeroplane, or to installthe modification<br />
Installation Instructions for Model TAF-Long limitations for unmodified engines.Only the on an engine in an aeroplane it will be<br />
OilFilter, dated October 26, 1998, or later FAA following filters are eligible for this<br />
necessary toapply for approval of a minor<br />
approved revision.<strong>EASA</strong> Validation of FAA installation:Champion No. CH48108A.C No. modification to the aeroplane.<br />
STC SE7559SW<br />
OF-53A<br />
Theinstaller must determine whether this<br />
design change<br />
10<strong>04</strong>0938 F&M ENTERPRISES INC. FAA STC SE09356SC 1. O-470 SERIES<br />
Install F. & M. Enterprises' Model C6LC, C6LC- None In order to install this modified engine in 06.08.2<strong>01</strong>2<br />
2. IO-470 SERIES<br />
S, or C6LC-L oil filteradapter for a spin-on oil<br />
an aeroplane, or to installthe modification<br />
3. IO-520 SERIES<br />
filter in accordance with F. & M.<br />
on an engine in an aeroplane it will be<br />
Enterprises'Installation Instructions dated<br />
necessary toapply for approval of a minor<br />
October 26, 1998, or later FAA<br />
modification to the aeroplane.<br />
approvedrevision.<strong>EASA</strong> Validation of FAA STC<br />
Theinstaller must determine whether this<br />
SE09356S<br />
design change<br />
10<strong>04</strong>0939 F&M ENTERPRISES INC. FAA STC SE08409SW 1. C-125 SERIES<br />
Installation of F. & M. Enterprises Model CO- Engines modified in accordance with this STC In order to install this modified engine in 06.08.2<strong>01</strong>2<br />
2. C-145 SERIES, O-300 SERIES 300 or C6SC spin-on oilfilter adapter, in will not differ inperformance or operating an aeroplane, or to installthe modification<br />
3. GO-300 SERIES<br />
accordance with F. & M. Enterprises<br />
limitations for unmodified engines.<br />
on an engine in an aeroplane it will be<br />
4. IO-360 SERIES<br />
installationinstructions for Model CO-300 dated<br />
necessary toapply for approval of a minor<br />
5. TSIO-360 SERIES<br />
October 26, 1998, or ModelC6SC dated<br />
modification to the aeroplane.<br />
October 5, 2005, or later FAA approved rev<br />
Theinstaller must determine whether this<br />
design change<br />
10<strong>01</strong>5468 F. ATLEE DODGE AIRCRAFT SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>221 FAA STC SA02115AK PIPER PA-12<br />
Fabrication and installation of F.Atlee Dodge 1. Any Piper aircraft incorporating this change<br />
09.06.2005<br />
PIPER PA-12S<br />
30.5 gallon wing fuel tank sight gages must be equipped with F. Atlee Dodge 30.5<br />
PIPER PA-14<br />
gallon wing fuel tanks in accordance withFAA<br />
PIPER PA-18-150<br />
STC SA649AL, SA00092SE, or<br />
PIPER PA-18A-150<br />
SA5781NM.2.This STC is approved only for<br />
PIPER PA-18AS-150<br />
the product configuration as defined in the<br />
PIPER PA-18S-150<br />
approved<br />
10<strong>01</strong>6731 FARGO MANUFACTURING <strong>EASA</strong>.IM.R.S.<strong>01</strong>055 FAA STC SR<strong>01</strong>926CH MD HELICOPTERS MD900 Install 61.8 gallon crashworthy auxiliary fuel This STC is approved only for the product<br />
30.03.2005<br />
tank on the aft cabin baggage bay floor configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>7067 FARGO MANUFACTURING <strong>EASA</strong>.IM.R.S.<strong>01</strong>503 FAA STC SR<strong>01</strong>813CH MD HELICOPTERS MD900 Installation of Auxiliary Fuel System Kit in This STC is limited to the installation of Fargo<br />
15.12.2008<br />
accordance with FAA STC SR<strong>01</strong>813CH Manufacturing Co. 52.5-gallon, crashworthy<br />
auxiliary fuel tank pursuant to FAA<br />
STCSR<strong>01</strong>238CH as referred in FAA STC<br />
SR<strong>01</strong>813CH. The 55-gallon installation and the<br />
28-gallon installation are not included in thi<br />
10<strong>01</strong>5060 FEDERATION FRANCAISE DE VOL A<br />
VOILE<br />
10030091 FEDERATION FRANCAISE DE VOL A<br />
VOILE<br />
10032277 FIBERGLAS-TECHNIK RUDOLF<br />
LINDNER<br />
<strong>EASA</strong>.A.S.03383 Winglet Retrofitting. 2.2 Supplemental Flight Manual <strong>01</strong>.02.2008<br />
ASW20F STC M-<strong>01</strong>/09-A<strong>01</strong> Winglet Installation on<br />
ASW20F<br />
None None 20.05.2<strong>01</strong>0<br />
GROB G 103 "TWIN II" STC "Reparatur Twin ll" Even if parts from a "Twin ll "Acro" are used, - Further conditions according to the 22.10.2<strong>01</strong>0<br />
the combined sailplanewill be always a "Twin ll" conditions of the STC "ReparaturTwin ll"-<br />
(without Acro). / Auch wenn Teile eines Twinll Weitere Festlegungen entsprechend den<br />
"Acro" verwendet werden, das neu<br />
Bedingungen des STC "ReparaturTwin<br />
entstandene Segelflugzeug ist immerein "Twin ll"Prior to installation of this modification it<br />
ll" (ohne Acro).<br />
must be determined thatthe<br />
interrelationship between t<br />
10<strong>01</strong>5983 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02135 SA93-81 BOMBARDIER DHC-6<br />
BOMBARDIER DHC-6 SERIES<br />
200<br />
BOMBARDIER DHC-6 SERIES<br />
300<br />
Roof Access Steps Installation -- 13.11.2006<br />
10<strong>01</strong>6003 FIELD AVIATION COMPANY Inc. <strong>EASA</strong>.IM.A.S.02164 O-LSA06-179/D ISSUE 1 (TCCA LI BEECH B200 SUPER KING AIR Installation of a single Universal UNS-1F Flight Aircraft Serial BB-1547 onlyThe UNS-1F Flight<br />
05.02.2007<br />
Management System complete with dual Management System is approved for En-route,<br />
Universal GLS-1250 DGPS Receivers (SCAT- Terminal and Non Precision Approach<br />
1).Transport Canada LSTC O-LSA06-179/D<br />
Issue 2.<br />
Operations only.<br />
10<strong>01</strong>6129 FIELD AVIATION COMPANY Inc. <strong>EASA</strong>.IM.A.S.02323 REV. 1 TCCA STC SA07-80 BOMBARDIER DHC-8-311 Retrofit of Swedish Coastguard Maritime Patrol Limitations UNS-1F Flight Management<br />
<strong>01</strong>.07.2008<br />
Modification.TCCA STC Number: SA07-80, Systems approved for En-route, Terminal and<br />
Issue 2 dated 26 February 2008<br />
Non Precision approach operations<br />
oniy.External Mission LAN System not<br />
approved for airborne operations.External<br />
Nokia Cellular Telephone System not approved<br />
for airborne use.<br />
10<strong>01</strong>6225 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02476 TCCA C-LSA07-021/D BOMBARDIER CL-600-2B19 Installation of Corporate Shuttle Interior. Limited to serial no. 8<strong>04</strong>9 09.10.2007<br />
10<strong>01</strong>6299 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02596 TCCA STC C-LSA07-322/D BOMBARDIER CL-600-2B19 Installation of Life Rafts. Aircraft Serial No. 8<strong>04</strong>9 only 12.10.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 214/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6417 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02750 TCCA STC SA05-73 BOMBARDIER DHC-8-311 Intallation of a Artex C406-2 or C406-N Three<br />
Frequency Emergency Locator Transmitter<br />
(ELT).<br />
11.06.2008<br />
10<strong>01</strong>6418 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02751 TCCA STC SA00-2 BOMBARDIER DHC-8-200 Ultra Electronics ANVC-Active Noise and Prior to installation of this modification the<br />
25.08.2008<br />
SERIES<br />
Vibration Control System and PBMS – installer must determine that the<br />
BOMBARDIER DHC-8-300 Propeller Balancing and Monitoring SystemRef. interrelationship between this modification and<br />
SERIES<br />
TCCA STC SA00-2, Issue 4, dated 24 October any other previously installed modification<br />
BOMBARDIER DHC-8-311 20<strong>04</strong><br />
will introduce no adverse effect upon the<br />
BOMBARDIER DHC-8-315<br />
airworthiness of the product.<br />
10<strong>01</strong>6419 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02752 TCCA LSTC C-LSA06-1<strong>01</strong>/D BOMBARDIER DHC-8-311 Installation of a 320cuft baggage compartment<br />
and installation of PBE's and O2 bottle into the<br />
cabin (Ref. TCCA LSTC C-LSA06-<strong>01</strong>0/D)<br />
06.10.2008<br />
10<strong>01</strong>6430 FIELD AVIATION COMPANY Inc. <strong>EASA</strong>.IM.A.S.02769 REV. 1 TCCA STC C-LSA08-056/D DHC-8-202, DHC-8-311 Honeywell AHRS to SFIM APIRS Conversion<br />
Provisions TCCA STC C-LSA08-056/D, Issue<br />
2<br />
10<strong>01</strong>6432 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.02772 TCCA STC O-LSA08-023/D BOMBARDIER DHC-8-311 VHF Comm Replacement for 8.33 kHz<br />
Spacing, ref. TCCA LST C-LSA08-023/D.<br />
10<strong>01</strong>6603 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.03<strong>01</strong>7 TCCA STC SA<strong>01</strong>-55 BOMBARDIER DHC-8-400<br />
SERIES<br />
BOMBARDIER DHC-8-4<strong>01</strong><br />
BOMBARDIER DHC-8-402<br />
Installation of Variable Position Cabin Class<br />
Divider.<br />
10<strong>01</strong>6648 FIELD AVIATION COMPANY INC. <strong>EASA</strong>.IM.A.S.03092 REV. 1 TCCA (LSTC) C-LSA08-<strong>01</strong>8/D BOMBARDIER DHC-8-4<strong>01</strong>, -402 G3 Water System Modification: TCCA LSTC C-<br />
LSA08-<strong>01</strong>8/D, Issue 3, dated 14September<br />
2009.<br />
10027252 FIELD AVIATION COMPANY Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02934<br />
TCCA STC SA09-15 DHC-8-314 Icelandic Coast Guard Maritime Patrol<br />
ModificationTCCA STC Number: SA09-15,<br />
Issue 1 dated 29. April 2009<br />
10029315 FIELD AVIATION COMPANY INC. TCCA STC SA02-86 DHC-8-102, -103, -106, -2<strong>01</strong><br />
DHC-8-202, -3<strong>01</strong>, -311, -314<br />
DHC-8-315<br />
10030757 FIELD AVIATION COMPANY Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03226<br />
TCCA STC SA92-93 ISSUE 4 DHC-8-102, -103, -106, -2<strong>01</strong><br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
Installation of a HF Antenna into the Vertical<br />
Stabilizer Leading Edgefor an Allied Signal<br />
KHF-950 HF Transceiver.TCCA STC SA02-<br />
86, Issue 2<br />
Installation is limited to Serial Numbers 435,<br />
440, 441 and 407<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product;2.<br />
Prior to installation of this modification it 23.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification the<br />
UNS-1F(w) Flight Management Systems<br />
approved for En-route, Terminal andNon<br />
Precision approach operations only. External<br />
LAN System not approved for airborne<br />
operations. External Nokia Cellular Telephone<br />
System not approved for airborne use. The<br />
authorizati<br />
Prior to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or repair<br />
will introduce no adverse effectupon the<br />
airworthiness of the product.<br />
installer must determinethat the<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe interr<br />
De-Icer Boot Installation None. 1. Prior to installation of this modification<br />
the installer mustdetermine that the<br />
,,interrelationship between this<br />
modification and anyother previously<br />
installed ,,modification will introduce no<br />
adverseeffect upon the airworthiness of<br />
the product.2. The i<br />
10031816 FIELD AVIATION COMPANY Inc. CAA STC 20<strong>04</strong>-5141 TCCA STC SH88-1 AS 332 L, AS 332 L1 Installation of 4 Place Auxiliary Seat TankThis None Prior to installation of this modification it 22.12.2<strong>01</strong>0<br />
<strong>EASA</strong> STC revises CAA STC 20<strong>04</strong>-5141<br />
must be determined thatthe<br />
dated 14 may 20<strong>04</strong> and adds modelAS332L1.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 215/<strong>462</strong><br />
15.08.2008<br />
28.08.2008<br />
21.09.2009<br />
16.09.2009<br />
18.03.2<strong>01</strong>0<br />
03.07.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032965 FIELD AVIATION COMPANY INC. TCCA LSTC C-LSA09-212/D DHC-8-311 Installation of Aft Baggage Bay Divider The modification is applicable only when the Prior to installation of this modification it 10.12.2<strong>01</strong>0<br />
NetsTCCA LSTC C-LSA09-212/D<br />
necessary structuralprovisions are pre-existing. must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035887 FIELD AVIATION COMPANY Inc. REV. 1 DHC-8--2<strong>01</strong>/-202<br />
DHC-8-102/-103/-106<br />
DHC-8-3<strong>01</strong>/-302<br />
Auxilliary Power Unit (APU) RemovalTCCA<br />
STC SA98-30, Issue 3<br />
10035939 FIELD AVIATION COMPANY Inc. DHC-8-102/-103/-106 Installation of Right Hand Ground Air<br />
ConnectionTCCA STC C-LSA11-<strong>04</strong>3/D, Issue<br />
1<br />
10036488 FIELD AVIATION COMPANY Inc. TCCA STC NO. SA11-37 DHC-8-4<strong>01</strong>, -402 Temporary Removal of Auxilliary Power Unit<br />
(APU)TCCA STC SA11-37, Issue 1<br />
10038098 FIELD AVIATION COMPANY Inc. REV. 1 TCCA STC O-LSA06-139/D DHC-8-106<br />
DHC-8-202<br />
TCCA STC O-LSA06-139/D, Issue 2Retrofit<br />
installation of a Honeywell KHF-950 HF Radio<br />
System.<br />
100381<strong>04</strong> FIELD AVIATION COMPANY Inc. TCCA STC O-LSA06-111/D DHC-8-202 TCCA STC O-LSA06-111/D, Issue 2Retrofit of<br />
AirCell ST3100 Satellite Telephone and<br />
Tracking System.<br />
The modification is applicable only when the<br />
necessary structuralprovisions are pre-existing<br />
OEM installed APU must be removed in<br />
accordance with <strong>EASA</strong> STC 10035887or<br />
TCCA STC SA98-30, Issue 3.<br />
The modification is applicable only when the<br />
necessary structuralprovisions are pre-existing<br />
The modification is limited to Serial numbers<br />
335, 337, 445, 446.<br />
The modification is limited to Serial numbers<br />
445, 446.<br />
10038661 FIELD AVIATION COMPANY Inc. TCCA STC O-LSA11-232/D DHC-8-103 Honeywell Mark VII EGPWS Annunciator This modification is limited to Serial number<br />
Relocation and UpgradeTCCA STC O-LSA11- 310 with <strong>EASA</strong> STC No.MOT.21NE2.138<br />
232/D, Issue 1<br />
installed.<br />
10038932 FIELD AVIATION COMPANY Inc. DHC-8-102/-103/-106/-2<strong>01</strong>/-202<br />
DHC-8-3<strong>01</strong>/-311/-314/315<br />
10038999 FIELD AVIATION COMPANY Inc. JAA STC<br />
ACG.21.NE.050<br />
TCCA STC SA<strong>01</strong>-50 DHC-8-102/-103/-106<br />
DHC-8-2<strong>01</strong>/-202<br />
DHC-8-3<strong>01</strong>/-311/-314/-315<br />
Prior to installation of this modification it 28.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 29.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 13.09.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it 19.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 19.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 06.03.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Auxiliary Wing Fuel Tank InstallationTCCA STC None Prior to installation of this modification it 23.03.2<strong>01</strong>2<br />
SA11-64, Issue 2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Variable Position Cabin Class<br />
DividerTCCA STC SA<strong>01</strong>-50, Issue 2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.03.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 216/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039339 FIELD AVIATION COMPANY Inc. REV. 1 TCCA STC SA11-27 DHC-8-102, -103, -106,<br />
Universal EFI-890R EFIS Cockpit<br />
The Installation of the DHC-8-314 MPA Prior to installation of this modification it 03.05.2<strong>01</strong>2<br />
DHC-8-2<strong>01</strong>, -202<br />
UpgradeTCCA STC SA11-27, Issue 3 configuration is limited to Serialnumber must be determined thatthe<br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
0660.The installation of dual, Universal UNS- interrelationship between this modification<br />
1E, or UNS-1E(w) or UNS-1F orUNS-1F(w) and any other previouslyinstalled<br />
Flight Management Systems are a prerequisite modification and/ or repair will introduce<br />
to theinstallation of the EFI 890R Electronic Fl no adverse effectupon the airworthiness<br />
of the product.<br />
10039340 FIELD AVIATION COMPANY Inc. REV. 1 TCCA STC C-LSA12-<strong>01</strong>4/D DHC-8-202 Installation of upgraded Cabin Floor<br />
PanelsTCCA STC C-LSA12-<strong>01</strong>4/D, Issue 1<br />
10039731 FIELD AVIATION COMPANY Inc. TCCA STC C-LSA12-<strong>01</strong>7/D DHC-8-202 Fleet Standardization ModificationTCCA STC<br />
C-LSA12-<strong>01</strong>7/D, Issue 1<br />
10039983 FIELD AVIATION COMPANY Inc. TCCA STC C-LSA12-006/D DHC-8-202 RH Rear Facing Seat Installation.TCCA STC<br />
C-LSA12-006/D, Issue 1.<br />
The modification is limited to Serial numbers<br />
445, 446 with post-1990Hunting interiors<br />
only.Floor loads of 75 lbs/ft(s) only in<br />
conjunction with underfloor supportstructure<br />
modified per Bombardier CR 853CH2003 or<br />
equivalent.<br />
The modification is limited to Serial numbers<br />
435, 440 and 441.<br />
The modification is limited to Serial numbers<br />
435, 440 and 441 withpost-1990 Hunting or<br />
C&D interiors only.,,<br />
10<strong>04</strong>1560 FIELD AVIATION COMPANY Inc. TCCA STC C-LSA12-128/D DHC-8-202 Auxiliary Ground Heater System TCCA STC C- Installation is limited to Serial Numbers 435,<br />
LSA12-128/D, Issue 1<br />
440, 441, 445 and 446<br />
10<strong>04</strong>1590 FIELD AVIATION COMPANY Inc. REV. 1 TCCA STC SA-12-57 DHC-8-102, DHC-8-103,<br />
DHC-8-106.<br />
10<strong>01</strong>5754 FIELD AVIATION EAST, LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>787 REV 2 SA<strong>04</strong>-125 ISSUE 1 BOMBARDIER DHC-8-102<br />
BOMBARDIER DHC-8-103<br />
BOMBARDIER DHC-8-311<br />
BOMBARDIER DHC-8-315<br />
10<strong>01</strong>5755 FIELD AVIATION EAST, LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>788 REV 1 SA05-67 ISSUE 1 BOMBARDIER DHC-8-102<br />
BOMBARDIER DHC-8-103<br />
BOMBARDIER DHC-8-311<br />
BOMBARDIER DHC-8-315<br />
10<strong>01</strong>5849 FIELD AVIATION EAST, LTD. <strong>EASA</strong>.IM.A.S.<strong>01</strong>949 REV. 2 TCCA STC SA05-42 DHC-8-102, -103, -106<br />
DHC-8-2<strong>01</strong>/-202<br />
10027122 FIELD AVIATION EAST, LTD. P-<br />
<strong>EASA</strong>.IM.A.S.03183<br />
REV. 2 TCCA STC SA02-48 DHC-8-102, -103, -106<br />
DHC-8-2<strong>01</strong>/-202<br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
Installation of Protective Breathing Equipment<br />
(PBE)TCCA STC SA 12-57, Issue 1<br />
Collins CTL-94E Controller for Elementary<br />
Surveillance<br />
Installation of ICARUS Sky Connect Tracker<br />
SOP and Satellite Communication System<br />
Installation of Dual Universal GLS-1250 DGPS<br />
Receivers (SCAT-1)TCCA STC SA05-42,<br />
Issue 3<br />
Retrofit Installation of Universal Avionics<br />
Systems Corp. UNS-1F FMS forSoftware<br />
versions SCN 8<strong>01</strong>/802 and 803Ref. TCCA<br />
SA02-48, Issue 5<br />
Prior to installation of this modification it 03.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 21.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 05.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 26.09.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.10.2<strong>01</strong>2<br />
Thi sapproval is only applicable to the<br />
type/model of aeronautical product specified<br />
therein. Prior to incorporating thi smodification,<br />
the installer shall establish that the<br />
interrelationship between this change and any<br />
other modification(s) incorporated<br />
FAEL (Dual UNS-1F FMS for Software<br />
versions 8<strong>01</strong>/802 and 803)<br />
STC<strong>EASA</strong>.IM.AS.3183, Issue1 or later <strong>EASA</strong><br />
approved revision must beinstalled as a<br />
prerequisite to the installation of the Dual GLS-<br />
1250DGPS (SCAT-1) modification.<br />
Configuration B Single UNS-1F with Software<br />
Version SCN 8<strong>01</strong>, EFISEquipped AircraftdeHavilland<br />
factory installed single UNS-1B or<br />
UNS-1B+ FlightManagement System Electrical<br />
and Structural provisions are aprerequisite to<br />
the Universal UNS-1F Flight Manageme<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 217/<strong>462</strong><br />
26.02.2007<br />
<strong>04</strong>.08.2006<br />
20.<strong>01</strong>.2<strong>01</strong>2<br />
31.<strong>01</strong>.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038517 FIELD AVIATION EAST, LTD. TCCA STC SA05-8 DHC-8-202 Max. Gross Takeoff Weight Increase to 37.300 None Prior to installation of this modification it 22.02.2<strong>01</strong>2<br />
lbsTCCA STC SA05-08, Issue 1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038533 FIELD AVIATION EAST, LTD. TCCA STC O-LSA11-177/D DHC-8-202 Cabin Drop Down Oxygen System Removal<br />
and Cabin Interior RefurbishmentTCCA STC<br />
O-LSA11-177/D, Issue 1<br />
10039284 FIELD AVIATION EAST, LTD. REV. 1 TCCA STC O-LSA11-147/D DHC-8-202 Air Iceland Avionics UpgradeTCCA STC O-<br />
LSA11-147/D, Issue 1<br />
10<strong>01</strong>7035 FILTRATION DEVELOPMENT<br />
CORPORATION<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>459 FAA STC SR<strong>01</strong>616SE SIKORSKY S-76A<br />
SIKORSKY S-76A++<br />
SIKORSKY S-76C<br />
SIKORSKY S-76C+<br />
Installation of an Engine Air Filter System for<br />
Sikorsky S-76 models, A+, A++ and C & C+<br />
The modification is limited to Serial numbers<br />
445, 446.<br />
Prior to installation of this modification it 23.02.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
The modification is limited to Serial numbers Prior to installation of this modification it 03.05.2<strong>01</strong>2<br />
445, 446.Universal UNS-1E(w) Flight must be determined thatthe<br />
Management Systems are approved for IFREn- interrelationship between this modification<br />
route, Terminal and Non Precisions approach and any other previouslyinstalled<br />
operations.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>4229 FINNAIR OYJ <strong>EASA</strong>.A.S.<strong>01</strong>392 BOEING MD 11 MD11 Cabin Crew Rest Area Emergency evacuation procedures, including<br />
the emergency evacuation of an incapacitated<br />
occupant from the Crew Rest Area, must be<br />
established. All of these procedures must be<br />
transmitted to the operator for incorporation<br />
into their training programs and ap<br />
10<strong>01</strong>6090 FIREWALL FORWARD TECHNOLOGIES<br />
LLC<br />
10<strong>01</strong>6691 FIREWALL FORWARD TECHNOLOGIES<br />
LLC<br />
10<strong>01</strong>6696 FIREWALL FORWARD TECHNOLOGIES<br />
LLC<br />
10<strong>01</strong>6697 FIREWALL FORWARD TECHNOLOGIES<br />
LLC<br />
<strong>EASA</strong>.IM.A.S.02277 FAA STC SA<strong>01</strong>435LA Installation of engines, modified with a Firewall<br />
Forward Technologies, LLC modified<br />
camshaft, into aircraft listed on the <strong>EASA</strong><br />
approved ATL<br />
<strong>EASA</strong>.IM.E.S.<strong>01</strong>005 FAA STC SE00584DE Installation of modified Oil Fitter Adapter, an<br />
increased opening pressure spring for filter<br />
bypass, and modified filter stud in accordance<br />
with Firewall Forward Technologies. Inc.<br />
Master Document List No. FFT-MDOCLST-<br />
OILSTUD-0<strong>01</strong>, Rev. B, dated August 8, 2<br />
<strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>0 FAA STC SE<strong>01</strong>436LA Installation of Firewall Forward Technologies,<br />
LLC modified camshaft in accordance with<br />
Master Drawing List FWF-MDL-ST9721 LA-E,<br />
revision G, dated 2/14/03 or later FAA<br />
approved revision.<br />
1. This installation must be done concurrently<br />
with <strong>EASA</strong> STC No. <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>0,<br />
which modifies the engine.2. Regardless of<br />
the <strong>EASA</strong> Approved Type List (ATL),<br />
installation is only approved if the Airplane<br />
Type / Variant itself is <strong>EASA</strong> approved.3.<br />
Compatibility of this design change with<br />
previously approved modifications must be<br />
determined by the installer.If the holder agrees<br />
to permit another person to use this certificate<br />
to alter the product, the holder shall give the<br />
other person written eviden<br />
This installation must be done concurrently with<br />
<strong>EASA</strong> STC No. <strong>EASA</strong>.IM.A.S.02277, which<br />
modifies the airplane installation.Compatibility<br />
of this design change with previously approved<br />
modifications must he determined by the<br />
installer. The installation shoul<br />
<strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>1 REV. 1 FAA STC SE00590DE Installation of a Lubricated Camshaft in 1. All engine installation criteria and limitations<br />
accordance with Master Drawing List FFT-MDL- are unchanged and remain in effect.<br />
ST3370DE-E, Revision IR dated September 9, Installation of engines modified by this STC<br />
2005, FAA approved September 26, 2005, or must be in accordance with the original aircraft<br />
later FAA approved revision.<br />
installation criteria.2. Instructions for Continued<br />
Airworthiness, Firewal<br />
10<strong>01</strong>5970 FIRST AIR MAINTENANCE SERVICES <strong>EASA</strong>.IM.A.S.02121 SA06-39 AEROSPATIALE ATR 42-300<br />
AEROSPATIALE ATR 42-320<br />
AEROSPATIALE ATR 72-1<strong>01</strong><br />
AEROSPATIALE ATR 72-102<br />
AEROSPATIALE ATR 72-2<strong>01</strong><br />
AEROSPATIALE ATR 72-202<br />
Installation of Dual SAGEM F227 APIRS<br />
Attitude and Heading Reference System<br />
This STC is approved only for the aircraft<br />
modelsATR 42-200 / 300 / 320 / 400 / 500ATR<br />
72-1<strong>01</strong> / 102 / 2<strong>01</strong> / 202 / 211 / 212 / 212 Afor<br />
those serial numbers fitted with the Honeywell<br />
AH600 AHRS as per originally manufactured<br />
and delivered by ATR (Type Desig<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 218/<strong>462</strong><br />
05.02.2009<br />
15.08.2006<br />
12.02.2007<br />
18.<strong>01</strong>.2007<br />
06.02.2007<br />
05.02.2007<br />
16.<strong>01</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7203 FISCHER + ENTWICKLUNGEN <strong>EASA</strong>.R.S.<strong>01</strong>352 BELL 427 Installation of floor mounted F+E Medical Seats<br />
230/305 into Bell 427 cabin by use of<br />
installation racks attached to forward and aft<br />
cabin bulkhead fittings<br />
20.07.2007<br />
10<strong>01</strong>5484 FLIGHT ENVIRONMENTS INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>244 FAA STC SA<strong>01</strong>318LA BEECH 390 Installation of thermal/accoustic insulation kit This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
26.07.2005<br />
10<strong>01</strong>5709 FLIGHT STRUCTURES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>702 FAA STC ST02944AT B777-200, B777-300 Installation of Cabin Wireless Local Area Airworthines Limitations Section of the<br />
20.07.2006<br />
Network (CWLAN) Distribution System Instruction for Continuous Airworthiness,<br />
document numbers F44-0246, revision A,<br />
dated 20thOctober 20<strong>04</strong> or R44-<strong>04</strong>06, revision<br />
IR, dated 23rd June 2005 or later FAA<br />
approved revisions<br />
10<strong>01</strong>5719 FLIGHT STRUCTURES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>717 FAA STC ST<strong>01</strong>729SE B747-400 Business Class Seat Installation Boeing Service Bulletin 747-25-3420 dated<br />
June 13 2006 must be installed concurrently<br />
with this STC.<br />
17.<strong>01</strong>.2007<br />
10<strong>01</strong>5720 FLIGHT STRUCTURES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>719 REV. 3 FAA STC NO. ST<strong>01</strong>849SE 777-200 Business Class Seat Installation Boeing Structural Compliance summary Prior to installation of this modification it 02.02.2<strong>01</strong>2<br />
Report Document DLR-36718 revisionNew must be determined thatthe<br />
dated 17 March 2008 must be accomplished interrelationship between this modification<br />
concurrently with this STCBoeing Structural and any other previouslyinstalled<br />
Compliance Summary Report Document DLR- modification and/ or repair will introduce<br />
36718 RevisionNew dated 17 March 2008 no adverse effectupon the airworthiness<br />
must be accomplishe<br />
of the product.<br />
10<strong>01</strong>6319 FLIGHT STRUCTURES, Inc. <strong>EASA</strong>.IM.A.S.02627 REV. 3 FAA STC ST<strong>01</strong>950SE B777-200 Remove EWIS limitation for <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.02627 Rev 1 - Door 1Overhead<br />
Flight Crew Rest Installation<br />
The Boeing Service Bulletin 777-25-<strong>04</strong>29<br />
dated 15 October 2008 must beaccomplished<br />
concurrently with this STC for the serial<br />
numbers listed onthe FSI top Collector<br />
A700000-0<strong>01</strong> revision C dated 8 December<br />
2008The Main deck seat arrangement must be<br />
installed<br />
10<strong>01</strong>6564 FLIGHT STRUCTURES, Inc. <strong>EASA</strong>.IM.A.S.02955 FAA STC ST00386SE BOEING 747-200 This design change relocates the E/E Bay This STC can only be installed in aircraft with<br />
Acces Hatch on the main deck floor and FAA STC SA2725CE-D or STC ST00255WI-D<br />
Installs Gari o Handling System Provisions for a or STC ST00252WI-D or STC ST00214SE<br />
30pallet main deck cargo configuration per<br />
Flight Structures, Inc.<br />
installed.<br />
10<strong>01</strong>6610 FLIGHT STRUCTURES, Inc. <strong>EASA</strong>.IM.A.S.03030 REV. 2 FAA STC ST020<strong>04</strong>SE B777-200 Remove EWIS limitation for <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>. IM.A.S.03030 - Door 3Overhead<br />
Attendant Rest Installation<br />
10029094 FLIGHT STRUCTURES, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02978<br />
10029964 FLIGHT STRUCTURES, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03<strong>04</strong>5<br />
10031815 FLIGHT STRUCTURES, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03215<br />
REV. 1 FAA STC ST02051SE B777-200 Remove EWIS limitation for <strong>EASA</strong> STC No.<br />
10029094 - First Class SeatInstallation<br />
REV. 1 FAA STC ST02060SE B747-400 Amendment of STC 10029964 in order to<br />
remove EWIS Limitations and updatethe MDL<br />
reference<br />
FAA STC ST02038SE A330-300 Installation of an Interior Reconfiguration in<br />
A330-300 Series aircraft<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
07.10.2<strong>01</strong>0<br />
18.09.2008<br />
The Main deck seating arrangement must be Prior to installation of this modification it 07.10.2<strong>01</strong>0<br />
installed in accordance withBritish Airways must be determined thatthe<br />
drawing 3-302-342 revision 10 dated 12 interrelationship between this modification<br />
February 2009FSI STC 10<strong>01</strong>6319 rev. 2 (FAA and any other previouslyinstalled<br />
STC number ST<strong>01</strong>950SE) for the FSI Door modification and/ or repair will introduce<br />
1Overhead Flight Crew Rest Installation no adverse effectupon the airworthiness<br />
(OFCR) mus<br />
of the product<br />
Concurrent installation of <strong>EASA</strong> STC No.<br />
10029095 (<strong>EASA</strong> Project No.P-<br />
<strong>EASA</strong>.IM.A.S.03<strong>04</strong>3) is requiredConcurrent<br />
installation of <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>797 is required<br />
Concurrent Installation of <strong>EASA</strong> STC No.<br />
10029975 is requiredConcurrent installation of<br />
FAA STC ST00720LA (<strong>EASA</strong> approved<br />
undergrandfather rights by CAA Airworthiness<br />
Approval Note No. 26656 dated 8March 1999)<br />
is required<br />
Prior to installation of this modification it <strong>04</strong>.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it <strong>04</strong>.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Not applicable Concurrent installation of Delta<br />
Engineering Supplemental<br />
TypeCertificate <strong>EASA</strong> STC 10031836 is<br />
required Concurrent installation of<br />
AmSafe, Inc. Supplemental Type<br />
Certificate<strong>EASA</strong> STC 10031808 is<br />
required Prior to installation of this<br />
modification it must be<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 219/<strong>462</strong><br />
17.09.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032896 FLIGHT STRUCTURES, Inc. FAA STC ST02160SE-D B737-500 Interior Reconfiguration in accordance with Not Applicable Prior to installation of this modification it 07.12.2<strong>01</strong>0<br />
Flight structures, Inc.(FSI) Master Drawing List<br />
must be determined thatthe<br />
B0FS003-D<strong>01</strong> Installation of new windscreen,<br />
interrelationship between this modification<br />
stowage bin, stowage bin extension<br />
and any other previouslyinstalled<br />
kits,moveable under-bin class divider, sidewall<br />
modification and / or repair will introduce<br />
panel, lowered ceiling paneland asso<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10033035 FLIGHT STRUCTURES, Inc. FAA STC ST02161SE-D B737-300 Interior Reconfiguration in accordance with<br />
Flight Structure, Inc. (FSI)Master Drawing List<br />
B0FS003-D02Installation of new windscreen,<br />
stowage bin, stowage bin extension<br />
kits,moveable under-bin class divider, sidewall<br />
panel, lowered ceiling paneland associ<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.12.2<strong>01</strong>0<br />
10036059 FLIGHT STRUCTURES, Inc. FAA STC SA5738NM B747-400 Installation of an extended upper deck crew<br />
rest in accordance withFlight Structures Inc.<br />
Master Drawing List 90SF0<strong>04</strong>-D<strong>01</strong>, Revision<br />
E,dated July 13, 1992, or later FAA approved<br />
revisions.Validation of FAA STC SA5738NM. ,,<br />
None. None. 09.08.2<strong>01</strong>1<br />
10036590 FLIGHT STRUCTURES, Inc. FAA STC ST00695AT-D B747-400 Modification of Upper Deck Crew Rest<br />
Compartment in accordance withTimco Master<br />
Data List, MDL-<strong>01</strong>090, Revision E, dated July<br />
22, 1996, orlater FAA approved<br />
RevisionValidation of FAA STC ST00695AT-D<br />
10037<strong>04</strong>9 FLIGHT STRUCTURES, Inc. FAA STC ST00840SE B747-400 Reconfiguration of the Main Deck of the B747-<br />
400 series airplane inaccordance with Flight<br />
Structures, Inc. Master Drawing List 99FS908-<br />
D<strong>01</strong>Rev. E, dated 10 November 2009 or a<br />
later FAA approved revision.Validation of FAA<br />
STC ST00840SE ,,<br />
10037365 FLIGHT STRUCTURES, Inc. FAA STC ST00756SE B747-400 Reconfiguration of the Main and Upper Deck of<br />
B747-400 series airplanes,in accordance with<br />
Flight Structures, Inc. Master Drawing<br />
List98FS818-D<strong>01</strong> Rev. J, dated November 10,<br />
2009 or a later FAA<br />
approvedrevision.Validation of FAA STC<br />
ST00756SE.<br />
10039031 FLIGHT STRUCTURES, Inc. FAA STC ST02164SE A330-3<strong>01</strong>/-302/-303<br />
A330-321/-322/-323<br />
A330-341/-342/-343<br />
10<strong>04</strong>1241 FLIGHT STRUCTURES, Inc. FAA STC ST<strong>01</strong>941SE A300 B4-6<strong>01</strong>/-603/-605R<br />
A300 B4-620/-622/-622R<br />
A330-300 Cabin reconfiguration.This STC<br />
installs new economy class and business class<br />
seats togetherwith the replacement of the IFE<br />
system.<br />
10<strong>04</strong>2096 FLIGHT STRUCTURES, Inc. FAA STC ST02166SE 747-400 Installation of additional Crew Rest Bunks in<br />
the Door 5 Overhead CrewRest.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.09.2<strong>01</strong>1<br />
None. Heath Tecna. STC ST0<strong>04</strong>84SE must be 27.10.2<strong>01</strong>1<br />
installed concurrently with this STC.,,<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair wi<br />
None. Heath Tecna. STC ST0<strong>04</strong>84SE and<br />
Rockwell Collins STC 00720LA must<br />
beinstalled concurrently with this<br />
STC.The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21.A109.Prior to installation of<br />
this modification it must be determined<br />
thatthe<br />
None Modification MCA 19<strong>04</strong>41, supporting<br />
installation of Front Row ServiceModules<br />
(Muhlenberg ottomans), in accordance<br />
with Diehl Services ModulesMaster<br />
Drawing List Ref: MDL19<strong>04</strong>41, dated 15<br />
March 2<strong>01</strong>2, is requiredwith this STC<br />
embodiment.Prior to installation<br />
Validation of FAA Supplemental Type The STC is limited to three A300B4-600 series A copy of this certificate and Flight<br />
Certificate (STC) ST<strong>01</strong>941SEConversion of an model aeroplanes,Manufacturer Serial Number Structures MDL A5FS524-D<strong>01</strong> must<br />
Airbus A300B4-600 series aeroplanes from a (MSN) 734, 739 and 756.Per the Temporary bemaintained as part of the permanent<br />
passengerconfiguration to a freighter<br />
Deviation, aeroplanes converted under this records for the modifiedaeroplane(s).<br />
configuration (including main deck cargodoor, STC:- are limited to 1,500 flight cycles or 3,300 This STC acts as an AMOC to several<br />
interior, and associated systems), in<br />
flight hours, whicheveroccurs fi<br />
<strong>EASA</strong> ADs, the list of which can befound<br />
accordance<br />
in the appendix to this approval c<br />
Maximum number of occupants of the Door 5<br />
overhead crew rest is eightpersons.<br />
22.11.2<strong>01</strong>1<br />
30.03.2<strong>01</strong>2<br />
31.08.2<strong>01</strong>2<br />
Prior to installation of this modification it 08.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 220/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5410 FLIGHT TEST ASSOCIATES, INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>124 FAA STC ST<strong>01</strong>524LA LEARJET 31<br />
Installation of Rosemount Pitot Static Probe 1. This STC is approved only for the product<br />
05.07.2005<br />
LEARJET 35<br />
Part Numbers 856NA1 & 856NA2<br />
configuration as defined in the approved design<br />
LEARJET 35A<br />
data referred to in the paragraph "Description".<br />
LEARJET 36<br />
Compatibility with other aircraft/engine<br />
LEARJET 36A<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5411 FLIGHT TEST ASSOCIATES, INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>125 FAA STC ST<strong>01</strong>525LA LEARJET 31<br />
Installation of Honeywell AZ-252 air data 1. This STC is approved only for the product<br />
06.07.2005<br />
LEARJET 35<br />
computer, Ba-250 barometric altitude display, configuration as defined in the approved design<br />
LEARJET 35A<br />
AM-250 barometric altimeter, AL-800 altitude data referred to in the paragraph "Description".<br />
LEARJET 36<br />
alert controller, and Aerosonic standby Compatibility with other aircraft/engine<br />
LEARJET 36A<br />
altimeter.<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5560 FLINT AERO, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>457 FAA STC SA3232NM CESSNA 206H<br />
Installation of 14.9 gallon usable fuel containing 1. Prior to installation of this modification the<br />
23.02.2009<br />
CESSNA T206H<br />
lightning resistant wing tips<br />
installer must determine that the<br />
CESSNA TU206G<br />
interrelationship between this modification<br />
CESSNA U206G<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2. The ins<br />
10<strong>01</strong>6592 FLINT AERO, INC. <strong>EASA</strong>.IM.A.S.03003 CESSNA 182<br />
CESSNA 182A<br />
CESSNA 182B<br />
CESSNA 182C<br />
CESSNA 182D<br />
CESSNA 182E<br />
CESSNA 182F<br />
CESSNA 182G<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA 182S<br />
CESSNA 182T<br />
CESSNA R182<br />
CESSNA T182, T182T<br />
CESSNA TR182<br />
10031241 FLINT AERO, INC. P-<br />
<strong>EASA</strong>.IM.A.S.02712<br />
FAA STC SA3226NM 210G, 210H, 210J, 210K, 210L<br />
210M, 210N<br />
T210G, T210H, T210J, T210K<br />
T210L, T210M, T210N, P210N<br />
10034927 FLINT AERO, INC. FAA STC SA2529WE 185, 185A, 185B, 185C, 185D<br />
185E, A185E, A185F<br />
10035079 FLINT AERO, INC. FAA STC SA1614WE SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Auxiliary Internal Wing Fuel Tanks.This STC is<br />
a revision of LBA STC SA 1305, dated 14<br />
January 2003.<br />
Installation of 16,25 US Gallon usable fuel<br />
lightning resistant wing tipfuel tanks<br />
Installation of twelve (12) gallon auxiliary fuel<br />
tank in each wing inacc. with FAA STC<br />
SA2529WE.<br />
Installation of one twelve (12) gallon auxiliary<br />
fuel tank in eachoutboard wing panel in acc.<br />
with FAA STC SA1614WE.<br />
None. 15.08.2008<br />
According limitation section of AFM-SFor<br />
P210N and T210N following limitation<br />
additionally apply:-Wing Tip Aux/ Aux Tank<br />
either is less than 7 gals MTOW 3730lbs,<br />
MLW3530lbs-Wing Tip Aux/ Aux Tank both are<br />
7 gals or more MTOW 4000lbs, MLW3800lbs<br />
Prior to installation of this modification it 03.08.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
The limitations and conditions of FAA TCDS Prior to installation of this modification it 13.05.2<strong>01</strong>1<br />
3A24 apply, except asoutlined below: a) Model must be determined thatthe<br />
185 through A185F S/N 18502262 - 89 gal. interrelationship between this modification<br />
(85 gal. useable); two32.5 gal. main tanks in and any other previouslyinstalled<br />
wings at (+48) and two 12 gal. (11.5<br />
modification and/ or repair will introduce<br />
gal.usable) aux. tanks in wings at (+50).b) no adverse effectupon the airworthiness<br />
of the product.<br />
The limitations and conditions of FAA Aircraft<br />
Specification A-799, FAAData Sheets 3A12,<br />
3A17, or FAA Data Sheets A4EU and A18EU<br />
or <strong>EASA</strong> TCDSIM.A.051 apply, except as<br />
outlined below of this STC: 1. Fuel Capacity<br />
Add "24 gal. (23 gal. useable); two 12 gal.<br />
Prior to installation of this modification it 24.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>4390 FLYBE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>676 BAE ATP Cargo Layout for class "E" compartment (LFD) 30.<strong>01</strong>.2006<br />
10<strong>01</strong>4413 FLYBE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>712 BAE ATP Introduction of Class E Compartment Cargo<br />
Layout<br />
10<strong>04</strong>2037 FLYBE LIMITED REV. 1 ERJ 190-100<br />
Embraer ERJ 190 - Installation of Tropospheric<br />
STD/LR/IGW/ECJ/SR<br />
Airborne Data ReportingSystemThis <strong>EASA</strong><br />
ERJ 190-200 STD/LR/IGW approval is an update of the <strong>EASA</strong> approval<br />
ref. 10<strong>04</strong>2037Description as per Associated<br />
Technical Documentation<br />
Restricted to Aircraft Serial Number 2<strong>04</strong>2 &<br />
2052<br />
ALS update as stated in ICA Supplement<br />
RE2088-17 Issue 3, dated<strong>01</strong>/10/2<strong>01</strong>2.<br />
17.<strong>01</strong>.2006<br />
Prior to installation of this modification it 08.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthinessof the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 221/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6123 FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.02316 TCCA STC SA06-33 AIRBUS A319<br />
AFIRS 220 Automated Flight Information ¿ AMS Instructions for Continued<br />
20.07.2007<br />
AIRBUS A320<br />
Reportiing System Installationwith optional Airworthiness, Ref. 153-0029, Rev. A.<br />
AIRBUS A321<br />
Global Voice and Global Text Satellite Compliance with the approved Airworthiness<br />
10<strong>01</strong>6213 FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.02461 TCCA STC SA07-47 BOEING 757-200<br />
Communication/<strong>EASA</strong> Validation of Transport Limitations contained therein is mandatory.<br />
Canada approved Supplemental<br />
TypeCertificate SA06-33.<br />
AFIRS 220 Automated Flight Information<br />
Reporting System Installation with Optional<br />
Gobal Voice and Global Text Satellite<br />
Communication.<br />
13.09.2007<br />
10<strong>01</strong>6343 FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.02659 TCCA STC SA07-7 BOMBARDIER DHC-8-100 Aeromechanical Services AFIRS (Automated<br />
21.<strong>01</strong>.2008<br />
SERIES<br />
Flight Information Reporting System) 220<br />
BOMBARDIER DHC-8-200 installation with optional Global Voice and<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
Global Text Satellite Communication.<br />
10<strong>01</strong>6344 FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.02660 REV. 2 TCCA STC SA07-8 BOEING 737-200 SERIES AFIRS 220 Automated Flight Information Prior to installation of this modification the<br />
22.05.2008<br />
BOEING 737-300 SERIES Reporting System installation with Optional installer must determine that the<br />
BOEING 737-400 SERIES Global Voice and Global Text Satellite interrelationship between this modification and<br />
BOEING 737-500 SERIES Communication.<br />
any other previously installed modification will<br />
BOEING 737-600 SERIES<br />
introduce no adverse effect upon the<br />
BOEING 737-700 SERIES<br />
BOEING 737-800 SERIES<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6385 FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.02711 TCCA STC SA07-84 BOMBARDIER CL-600-2B19 AFIRS 220 Automated Flight Information AMS Instructions for Continued Airworthiness,<br />
03.07.2008<br />
(SERIES<br />
Reporting System installation with Optional Ref. 153-0036 Rev. A or later approved<br />
Global Voice and Global Text Satellite revision. Compliance with the approved<br />
Communication<br />
Airworthiness Limitations contained therein is<br />
mandatory.<br />
10<strong>01</strong>6522 FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.02895 TCCA STC SA07-124 BOEING 767-200<br />
AFIRS 220 Automated Flight Information Prior to installation of this modification the<br />
19.08.2008<br />
BOEING 767-300<br />
Reporting System installation with Optional installer must determine that the<br />
Global Voice and Global Satellite<br />
interrelationship between this modification and<br />
Communication<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
100279<strong>04</strong> FLYHT AEROSPACE SOLUTIONS Ltd. <strong>EASA</strong>.IM.A.S.03184 REV. 4 TCCA STC SA08-7 HAWKER 750<br />
HAWKER 800XP<br />
HAWKER 850XP<br />
HAWKER 900XP<br />
AFIRS 220 / AFIRS 228 Automated Flight<br />
Information Reporting SystemInstallation With<br />
Optional Global Voice and Global Text<br />
SatelliteCommunications.<br />
None. TCCA approved Airworthiness<br />
Limitations in Part I of<br />
AeroMechanicalServices Ltd ("FLYHT"),<br />
Instructions for Continued<br />
Airworthiness153-0<strong>04</strong>0, Rev. D, dated 30<br />
March 2<strong>01</strong>1, or later TCCA accepted<br />
revisions,are mandatory for both the<br />
AFIRS 220 system and AFIRS<br />
29.08.2<strong>01</strong>2<br />
10028338 FLYING COLOURS CORP. REV. 2 TCCA LSTC C-LSA09-326/D CL-600-2B19 Installation, Complete Custom Aircraft Interior Restricted to ASN 8092 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.12.2<strong>01</strong>1<br />
10032278 FLYING COLOURS CORP. REV. 1 TCCA STC NO. SA10-66 CL-600-2B19 Installation, Equipment Bay Catwalk none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.10.2<strong>01</strong>0<br />
10032279 FLYING COLOURS CORP. REV. 1 TCCA STC NO. SA10-67 CL-600-2B19 Installation, Equipment Bay Ladder Prior embodiment of <strong>EASA</strong> STC No. Prior to installation of this modification it 28.10.2<strong>01</strong>0<br />
10032278 'Installation, Equipment BayCatwalk' must be determined thatthe<br />
is required.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 222/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032280 FLYING COLOURS CORP. REV. 1 TCCA STC NO. SA10-65 CL-600-2B19 Installation, Equipment Bay Access Door Steps none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.10.2<strong>01</strong>0<br />
10039852 FLYING COLOURS CORP. TCCA STC NO. SA12-33 CL-600-2B19 Installation, Aft Equipment Bay Tow Bar<br />
Stowage Provisions<br />
10<strong>01</strong>6455 FLYING INVESTMENTS, LLC <strong>EASA</strong>.IM.A.S.028<strong>01</strong> FAA STC ST<strong>01</strong>349WI FAN JET<br />
FAN JET FALCON SERIES C<br />
FAN JET FALCON SERIES D<br />
FAN JET FALCON SERIES E<br />
FAN JET FALCON SERIES F<br />
FAN JET FALCON SERIES G<br />
MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
MYSTERE FALCON 20-F5<br />
10<strong>01</strong>6456 FLYING INVESTMENTS, LLC <strong>EASA</strong>.IM.A.S.02802 FAA STC ST00571DE FAN JET<br />
FAN JET FALCON SERIES C<br />
FAN JET FALCON SERIES D<br />
FAN JET FALCON SERIES E<br />
FAN JET FALCON SERIES F<br />
FAN JET FALCON SERIES G<br />
MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
MYSTERE FALCON 20-F5<br />
10<strong>04</strong>1003 FMD FLUGPLATZ MAGDEBURG <strong>EASA</strong>.A.S.03983 1. 172E,172F,172H,172K,172L<br />
1. 172M,172N,172P,172R,<br />
2. FR172E<br />
10<strong>01</strong>4607 FOKKER SERVICES B.V. <strong>EASA</strong>.A.S.02732 REV. 2 CL-600-2C10 (CRJ-700) VIP conversion of Bombardier CL600-2C10<br />
(CRJ-700) for ConsolidatedContractors<br />
Company, as detailed in Fokker Services<br />
Reduced Vertical Separation Minimum (RVSM) Prior to installation of this modification the<br />
group airworthiness approval of specific installer must determine that the<br />
Dassault Aviation Fan Jet Falcon and Mystere- interrelationship between this modification and<br />
Falcon 20 aircraft in accordance with Flying any other previously installed modification will<br />
Investments LLC Master Drawing List introduce no adverse effect upon the<br />
MDL1<strong>01</strong>7, Revision G, dated 19th February airworthiness of the product. The install<br />
2008<br />
Installation of an Innovative Solutions & Prior to installation of this modification the<br />
Supports (IS&S) Dual Air Data Display Units installer must determine that the<br />
(ADDU), an Analog Interface Unit or Air Data interrelationship between this modification and<br />
Sensor and Goodrich Dual Pitot-Static Probes, any other previously installed modification will<br />
in accordance with Flying Investments Master introduce no adverse effect upon the<br />
Data List GEN-031217-0<strong>01</strong>, Revision airworthiness of the product. The install<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.05.2<strong>01</strong>2<br />
The certificate shall remain valid unless<br />
otherwise surrendered orrevoked.<br />
If the utilisation of the VIP converted aircraft<br />
deviates from theassumed utilisation (e.g. flight<br />
hours or flight profile) supporting thescheduled<br />
Engineering ReportFS-N594. Description of the maintenance requirements as defined by<br />
modification.Revision 2: Wireless handsets in Bombardier, theoperator of the aircraft will<br />
the Aircell telephone installation in aCRJ-700 have to review the adequ<br />
10<strong>01</strong>4752 FOKKER SERVICES B.V. <strong>EASA</strong>.A.S.02937 REV. 2 A319CJ Changes to Airbus A319CJ in addition to the The activation of the Zonal<br />
VIP Conversion introduced by<strong>EASA</strong> STC Dryer/Humidification System is not part ofthis<br />
A.S.02937 as described in Fokker Services Major Change. The installation of the Zonal<br />
B.V. EngineeringReport A319-SAG-CRR-0002 Dryer/HumidificationSystem is certified,<br />
Issue 1. This STC has been revised to clarify however the correct use and functioning is<br />
the text in the Limitations andConditions. notcertified. Therefore the Zonal<br />
Dryer/Humidificatio<br />
10031332 FOKKER SERVICES B.V. <strong>EASA</strong>.A.S.03317 A318-112 A318-112 VIP conversion, for description see 1. Refer to Chapter 2, Limitations of the AFM<br />
Chapter 1.1 of. ComplianceRecord Report A18- Supplement Airbus A318Model A318-112<br />
MAK-CRR-00<strong>01</strong> issue 5 d.d. 29-5-2009 Aircraft for the VIP Conversion As installed in<br />
Serialnumber 3238 issue 5 d.d. 29-5-20092.<br />
The STC is approved only for the product<br />
configuration as defined inthe approved d<br />
10034242 FOKKER SERVICES B.V. P-<strong>EASA</strong>.A.S.03722 AIRBUS A320-232 Airbus A320-232 VIP Conversion. Refer to Limitations section of the approved<br />
AFM Supplement:A320-CAI-AFM-S-<br />
APPROVAL issue 1, dated 15th March<br />
2<strong>01</strong>1.Remarks: The aircraft type, model and<br />
manufacturer serial number forwhich this<br />
change is applicable is: Airbus A320-232 with<br />
ManufacturerSeri<br />
22.07.2008<br />
22.07.2008<br />
This STC is a revision of and supersedes 29.07.2009<br />
LBA STC SA1303, dated 15 April2003.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
21.<strong>01</strong>.2<strong>01</strong>0<br />
product.<br />
Prior to installation of this modification it <strong>01</strong>.07.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 223/<strong>462</strong><br />
29.05.2009<br />
18.03.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038053 FOKKER SERVICES B.V. F28 MARK 0070 Activation of WLAN functionality of an already -Installation of <strong>EASA</strong> STC 10027637 is a Prior to installation of this modification it 16.<strong>01</strong>.2<strong>01</strong>2<br />
installed andcertificated router (ref <strong>EASA</strong> STC prerequisite for this STC-Limitation of Wireless must be determined thatthe<br />
10027637)The Fokker 70 aircraft contains a Local Area Network as documented in AFM interrelationship between this modification<br />
router that has been certificatedunder STAC changeAFMJET2<strong>01</strong>1-007<br />
and any other previouslyinstalled<br />
10027637. Fokker Services will activate and<br />
modification and/ or repair will introduce<br />
certificate theWLAN functionali<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>2160 FOKKER SERVICES B.V. B737-600/-700/-800/-900/-900ER Introduction of LED light assembles in the<br />
Boeing B737 NG aircraft<br />
10<strong>01</strong>5713 FOKKER50FREIGHTER STC CORP. <strong>EASA</strong>.IM.A.S.<strong>01</strong>710 REV 1 FAA STC ST<strong>01</strong>916LA FOKKER F.27 MARK 050 Installation of Large Cargo door.Installation of<br />
Large Cargo door.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.11.2<strong>01</strong>2<br />
1. To allow the carriage of cargo STC<br />
IM.A.S.<strong>01</strong>711 shall be incorporated;2. The<br />
maximum number of occupants in the aircraft<br />
including crew members is 3;3. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design da<br />
10<strong>01</strong>5714 FOKKER50FREIGHTER STC CORP. <strong>EASA</strong>.IM.A.S.<strong>01</strong>710 REV 1 FAA STC STO1916LA - <strong>EASA</strong>.IM.A. FOKKER F.27 MARK 050 21.05.2008<br />
10<strong>01</strong>5715 FOKKER50FREIGHTER STC CORP. <strong>EASA</strong>.IM.A.S.<strong>01</strong>711 REV 1 FAA STC ST00260DE FOKKER F.27 MARK 050 Installation of Class E Cargo Interior,<br />
1. Cargo Loading Manual WB-2052 Rev. C or<br />
02.11.2007<br />
configuration 24B3<strong>01</strong>-211 in accordance with later approved revisions shall be used when<br />
Branson Aircraft Corporation Drawing List loading the aircraft.2. This STC is approved<br />
24A300, revision B dated November 5, 1996, only for the product configuration as defined in<br />
FAA approved November 7, 1996 or later the approved design data referred to in the<br />
revision approved in accordance with ED<br />
Decision<br />
paragraphs "Description" and “As<br />
10028703 FORCED AEROMOTIVE<br />
FAA STC SE10926SC IO-550-N Installation of BAR Air, LLC supercharger The supercharged IO-550-N engine is limited Prior to installation of this modification it 03.02.2<strong>01</strong>0<br />
TECHNOLOGIES<br />
system on Teledyne ContinentalMotors IO-550- to 29.6 in Hg (2<strong>04</strong> kPa) MAPand 2700 RPM or must be determined thatthe<br />
N Engines in accordance with Master Drawing 310 HP (231 kW).<br />
interrelationship between this modification<br />
ListMDL-SR22-1-E, Revision A, dated April 4,<br />
and any other previouslyinstalled<br />
2008 or later FAA approvedrevision - <strong>EASA</strong><br />
modification and/ or repair will introduce<br />
Validation of FAA STC SE10926SC.<br />
no adverse effectupon the airworthiness<br />
of the product If the<br />
10029290 FORCED AEROMOTIVE<br />
TECHNOLOGIES<br />
10029878 FORCED AEROMOTIVE<br />
TECHNOLOGIES<br />
10030005 FORCED AEROMOTIVE<br />
TECHNOLOGIES<br />
FAA STC SA10925SC SR22 Installation of BAR Air, LLC modified Teledyne As referred in limitations section of the AFM-S<br />
Continental MotorsIO-550-N iaw. MDL-SR22-1- 22006Engine must be modified acc. <strong>EASA</strong><br />
A, Rev. E or later FAA approved<br />
revisions.Installation requires <strong>EASA</strong> STC<br />
10028703 to be installed.<br />
STC 10028703<br />
FAA STC SE10233SC O-470-L, -R, -S, -U Installation of a Belt-Driven Vortech V-1S<br />
supercharger assembly on theTeledyne<br />
Continental Motors (TCM) O-470-L, O-470-R,<br />
O-470-S, and O-470-Uengines in accordance<br />
with Type Inspection Data contained in<br />
MasterDrawing List No. MDL-182-1-E, Rev. D,<br />
dated Ja<br />
FAA-STC SE10233SC 182E, 182F, 182G, 182H, 182J,<br />
182K, 182L, 182M, 182N, 182P,<br />
182Q, 182R<br />
The supercharged O-470-L, -R, -S, and -U<br />
engines are limited to 28 inHg(193 kPa) MAP<br />
and 2600 RPM or 230 HP (171.5 kW) with<br />
minimum fuel gradeAvgas 100LL.<br />
Installation of Rod Sage Supercharged This Supplemental Type Certificate requires<br />
Teledyne Continental Motors (TCM)O-470-L, O- installation of <strong>EASA</strong> STC10029878 (see also<br />
470-R, O-470-S and O-470-U Engines in acc. FAA-STC SE10233SC)<br />
with FAA STCSA10232SC<br />
10033805 FR AVIATION LIMITED B300 Observer Training Platform Mod.-B300. The approval is limited to the Aircraft Serial<br />
Numbers: FL-597,FL-618, FL-629 and<br />
FL-633.<br />
21.05.2008<br />
Prior to installation of this modification the 17.03.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
28.<strong>04</strong>.2<strong>01</strong>0<br />
Prior to installation of this modification it 10.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification the 09.02.2<strong>01</strong>1<br />
installer must determinethat the<br />
,,interrelationship between this<br />
modification and any otherpreviously<br />
installed ,,modification will introduce no<br />
adverse effectupon the airworthiness of<br />
the product. The instal<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 224/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035091 FR AVIATION LIMITED TYPE: FAN JET FALCON Extended underwing stores carriage (flutter This approval only addresses the clearance of The responsible design organization must 30.05.2<strong>01</strong>1<br />
BASIC, D AND E SERIES clearance)The goal is to approve the flutter the pod configurationswith respect to flutter, all ensure that the intendedconfiguration is<br />
clearance of underwing storeconfigurations other aspects of the certification process,such within the scope of the approved design<br />
installed onto Fan Jet Falcon aircraft with as structural strength, effects on aircraft definition forthe flutter analysis.<br />
existingunderwing hard points. This design handling andperformance, system safety and<br />
definition establishes an envelope of<br />
environmental prot<br />
10<strong>04</strong>2074 FRAKES AVIATION <strong>EASA</strong>.IM.A.S.00228 1900<br />
Installation of engine exhaust stub in<br />
1. Compability of this modification with 28.10.20<strong>04</strong><br />
1900C<br />
accordance with Frakes AviationInstallation<br />
previously installed equipmentmust be<br />
1900D<br />
drawing number FA5726, dated September 6,<br />
determined by installer 2. This SIC is<br />
200<br />
1985, for the 200series, and drawing FA56<strong>01</strong><br />
issued as result of the validation of the<br />
200C<br />
dated June 19, 1995 for the 300 and<br />
Frakes AviationSIC N° SA8703SW<br />
300<br />
1900series, or later <strong>EASA</strong>-approved revision<br />
approved by the FAA on October 27,<br />
300LW<br />
B200<br />
B200C<br />
B300<br />
B300C<br />
1993 and amended onJune 21, 19<br />
10<strong>01</strong>4725 FRANCE AVIATION <strong>EASA</strong>.A.S.02902 BEECH F33 Installation and BRNAV approval of Garmin<br />
GNS-480.<br />
05.12.2006<br />
10<strong>01</strong>4839 FRANCE AVIATION <strong>EASA</strong>.A.S.03056 BEECH B200 Installation of Honeywell MST-67A Mode S Prior to installation of this modification the<br />
18.06.2007<br />
Transponder.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4914 FRANCE AVIATION <strong>EASA</strong>.A.S.03159 PIPER PA-32 Rudder Hand Control installation for lower<br />
Limbs.The "SD1" system consists in a control<br />
for rudder that is handled by the pilot while<br />
seated in the LH (Left Hand) station. This<br />
"SD1" RHC system is mountained on existing<br />
manufacturing rudder system. The sy<br />
10<strong>01</strong>5002 FRANCE AVIATION <strong>EASA</strong>.A.S.03302 BEECH F90 Installation of 2 Collins 8.33 KHz COMM<br />
System and GTX330D mode S diversity<br />
transponder.<br />
10<strong>01</strong>5<strong>01</strong>4 FRANCE AVIATION <strong>EASA</strong>.A.S.03316 BEECH F90 IFR/RNAV classification of the GNS530AW<br />
AFMS No. AFM-35-2007-0<strong>01</strong>, dated<br />
26/09/2007 or later approved revision must be<br />
used with the modification.<br />
The following AFMS must be used when<br />
coupled to the autopilot; basic IFR classification modification is applied:Aircraft Flight Manual<br />
of the GNS430AW and Mode S transponder Supplement for GTX330/330D, # AFM-38-<br />
GTX330 installation.<br />
2007-0<strong>01</strong> revision 1, dated 10/<strong>04</strong>/2008, or later<br />
approved revisions.Aircraft Flight Manual<br />
Supplement for GMX200, # AFM-38-2007-002<br />
revi<br />
10<strong>01</strong>5028 FRANCE AVIATION <strong>EASA</strong>.A.S.03335 PIPER PA-28 Rudder hand control and brake system Prior to installation of this modification the<br />
forlower limbs disabled pilot. The "LPS" rudder installer must determine that the<br />
hand control and brake system installation is to interrelationship between this modification and<br />
permit LLD pilot to operate the aircraft without any other previously installed modification will<br />
safety pilot or flight instructor in the right hand introduce no adverse effect upon the<br />
pilot station. The "L<br />
airworthiness of the product.<br />
10<strong>01</strong>7205 FRANCE AVIATION <strong>EASA</strong>.R.S.<strong>01</strong>357 EUROCOPTER DEUTSCHLAND Installation of Avidyne Adivsory System TAS- Installation limited to EC 135 T2 s/n 274. 30.11.2007<br />
EC-135<br />
620.<br />
10033540 FRANCE AVIATION P-<strong>EASA</strong>.A.S.03527 BEECH A36 FA 06/2008 Rev. 2 - Avionic change with B- None Prior to installation of this modification it 06.07.2009<br />
RNAV/SID/STAR/GNSS andconventional non-<br />
must be determined thatthe<br />
precision approaches privileges with AP<br />
interrelationship between this modification<br />
coupling.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 225/<strong>462</strong><br />
23.11.2007<br />
10.12.2007<br />
23.05.2008<br />
24.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6792 FUGRO AIRBORNE SURVEYS <strong>EASA</strong>.IM.R.S.<strong>01</strong>140 TCCA STC SH 98-37 EUROCOPTER FRANCE AS 350 Installation of Fugro Airborne Surveys Electro- 1. STC SH 98-37 Supplemental Flight Manual<br />
11.10.2005<br />
B<br />
Magnetometer Boom & Geosurvey Equipment 4537-<strong>01</strong> Revision <strong>01</strong> approved 18 July 2000<br />
EUROCOPTER FRANCE AS 350 installation<br />
or later approved revisions.2. DECA Aviation<br />
B1<br />
Flight Manual Supplement No. 453707<br />
EUROCOPTER FRANCE AS 350<br />
Revision 1, dated 18 July 2000 or later<br />
B2<br />
approved revision3. This STC is approved only<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
for<br />
10<strong>01</strong>6428 G&D AERO PRODUCTS INC. <strong>EASA</strong>.IM.A.S.02767 FAA STC SA7063NM BEECH 200<br />
BEECH 300<br />
Installation of Acrylic window liners None 05.03.2008<br />
10<strong>01</strong>4342 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>602 BEECH 200 Major Avionic Upgrade 06.<strong>04</strong>.2006<br />
10<strong>01</strong>4355 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>620 BEECH 200, SUPER KING AIR Major Avionic System Upgrade 19.12.2005<br />
10<strong>01</strong>4357 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>622 REV. 1 BEECH B200C, SUPER KING AIR Ground Use Battery None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.03.2<strong>01</strong>1<br />
10<strong>01</strong>4389 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>675 REV. 1 BAE.125 SERIES 800 Title: Upgrade of the dual Flight Management<br />
System (FMS).Description of change: The<br />
original dual Honeywell FMZ-900 FMS<br />
isupgraded to a dual Honeywell FMZ-2000<br />
FMS.<br />
The installer must determine whether this<br />
design change is compatiblewith previously<br />
approved modifications.<br />
Prior to installation of this modification it 05.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4502 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02570 BEECH 200 Mode S Transponder Installation. Beech 200 Series. As per AFMS7060<strong>01</strong> Issue<br />
1<br />
06.02.2008<br />
10<strong>01</strong>4542 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02629 REV. 1 A340-311, A340-312, A340-313. Child Restraint System - CRS - Installation in Limitations in accordance with § 4 - Limitations Prior to installation of this modification it 10.12.2<strong>01</strong>2<br />
A340-300<br />
of the above mentionedDDP, ref. No. DDP- must be determined thatthe<br />
1785-026.All cabin interiors must be evaluated interrelationship between this modification<br />
for compatibility of the ChildRestraint System and any other previouslyinstalled<br />
(CRS). The CRS is not approved for<br />
modification and/ or repair will introduce<br />
aeroplanes that arenot defined by § 4 no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4543 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02630 REV. 1 A340-643 Child Restraint System - CRS - Installation in<br />
A340-600<br />
Limitations in accordance with § 4 - Limitations Prior to installation of this modification it 10.12.2<strong>01</strong>2<br />
of the above mentionedDDP, ref. No. DDP- must be determined thatthe<br />
1785-026.All cabin interiors must be evaluated interrelationship between this modification<br />
for compatibility of the ChildRestraint System and any other previouslyinstalled<br />
(CRS). The CRS is not approved for<br />
modification and/ or repair will introduce<br />
aeroplanes that arenot defined by § 4 no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4544 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02631 REV. 1 B747-400 Installation of MAGE Child Restraint System as 1. This STC only covers the installation of the Prior to installation of this modification it 20.06.2<strong>01</strong>2<br />
detailed in ModificationLeaflet for Modification MAGE Child RestraintSystem on Virgin Atlantic must be determined thatthe<br />
no. B744-1795.<br />
Airways Boeing 747-400 Aircraft, as defined interrelationship between this modification<br />
inMAGE DDP1785-026 and in accordance with and any other previouslyinstalled<br />
the instructions and limitationsdefined in MAGE modification and/ or repair will introduce<br />
Crew Manual Supplement TN 17<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong><strong>462</strong>6 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02764 HAWKER 800 XP Installation of a L-3 Avionics F1000 Flight Data<br />
Recorder.<br />
This Installation is intended for compliance with<br />
JAR-OPS 1.715. This STC however grants no<br />
operational approval to this installation, that will<br />
need to be obtained from the State of registry<br />
for the particular aircraft involved as defined in<br />
JAR OPS 1.715<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 226/<strong>462</strong><br />
17.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong><strong>462</strong>7 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02765 BEECH 200 Enhanced Mode S Upgrade. Beech 200/300 SeriesAFM Supplements<br />
AFMS7300<strong>01</strong> and AFMS730002.<br />
12.03.2008<br />
10<strong>01</strong>4768 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02960 CESSNA 425 Installation of Traffic Advisory System As defined in the AFM supplement 08.03.2007<br />
10<strong>01</strong>4769 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.02961 CESSNA 425 Installation of Garmin GNS 530 & GTX330 As per AFM Supplements. 08.03.2007<br />
10<strong>01</strong>5050 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.03369 CESSNA 500, CITATION Upgrade of Mode S Transponder for Enhanced<br />
Surveillance<br />
05.03.2008<br />
10<strong>01</strong>5153 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.03516 HAWKER HS 125-700 SERIES Dual FMS Upgrade. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
14.08.2008<br />
10<strong>01</strong>5186 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.03570 CESSNA 525 Upgrade of Mode S transponders for enhanced<br />
surveillance.<br />
13.06.2008<br />
10<strong>01</strong>5247 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.03684 HAWKER 700 Introduction of a Sandel ST3400 Class A Prior to installation of this modification the<br />
15.12.2008<br />
terrain awareness warning system.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7226 GAMA ENGINEERING Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>395 REV. 1 BO 105 S (CBS-4) The Pyrotechnic Display System:Carriage and none Prior to installation of this modification it 24.02.2<strong>01</strong>1<br />
deployment of static flares and roman candle<br />
must be determined thatthe<br />
typepyrotechnics, installed each side on<br />
interrelationship between this modification<br />
external dispenser mounts attachedto landing<br />
and any other previouslyinstalled<br />
gear skids and interfaced with cabin control box<br />
modification and/ or repair will introduce<br />
to sequenceignition. Note: this<br />
no adverse effectupon the airworthiness<br />
of the product.The app<br />
10<strong>01</strong>7247 GAMA ENGINEERING Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>445 BELL 412 Installation of a dual electronic horizontal<br />
situation indicator (EHSI) system.<br />
1. The EHSI system must have a minimum<br />
software level of Eight (8) installed in the<br />
symbol generators.2. The YELLOW symbol<br />
generator “SG” flag or display unit “DU” flag<br />
must not be visible prior to departure.3.<br />
Autopilot coupled ADF tracking is no<br />
10027113 GAMA ENGINEERING Ltd. P-<strong>EASA</strong>.A.S.03842 PA-28 Aspen EFD1000 System None None 07.09.2009<br />
10027314 GAMA ENGINEERING Ltd. PIPER PA32 ALL SERIES Installation of Aspen EFD1000 PFD Prior to installation of this modification the 21.09.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
10027637 GAMA ENGINEERING Ltd. <strong>EASA</strong>.A.S.03763 REV. 2 F28 MARK 0070 Interior Refurbishment and System Upgrade None. None. 26.11.2<strong>01</strong>2<br />
10027657 GAMA ENGINEERING Ltd. REV. 1 PA-23-235, PA-23-250<br />
Installation of Garmin G500/G600 EFIS None Prior to installation of this modification it 21.10.2<strong>01</strong>0<br />
PA-E23-25<br />
PFD/ND<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027818 GAMA ENGINEERING Ltd. REV. 2 PA32 ALL SERIES Installation of Garmin G500/G600 PFD/ND This change is limited to the configuration<br />
defined in Change StatementCS1100-02 Issue<br />
2 or later approved revision.<br />
None <strong>01</strong>.<strong>04</strong>.2<strong>01</strong>0<br />
10028029 GAMA ENGINEERING Ltd. PA-34-200, PA-34-200T, Installation of Aspen EFD1000 PFD as add on Only applicable for airplanes/preconditions as The installation of this modification by 26.11.2009<br />
PA-34-220T<br />
defined Section 1.1,"Installation planning" of third persons is subject towritten<br />
Doc. No. CS1106-<strong>01</strong>, "Change Statement", permission of the approval holder and<br />
Issue2, or later approved issue For approved holding and disposal ofthe approved<br />
Software Level of Aspen EFD1000 refer to appropriate documentation. Prior to<br />
"Limitations,Conditions, Exemptions"<br />
installation of this modification it must be<br />
determined thatthe interr<br />
10028069 GAMA ENGINEERING Ltd. 182 SERIES Installation of Aspen EFD1000 PFD None None 30.11.2009<br />
10029002 GAMA ENGINEERING Ltd. PA-31 Installation of defence aid antennas and None Applicable to Piper PA 31 s/n 31-815 25.02.2<strong>01</strong>0<br />
systems<br />
only.<br />
10029092 GAMA ENGINEERING Ltd. PA-31 ATC transponder upgrade for Mode S<br />
enhanced surveillance<br />
Not Applicable Not Applicable 03.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 227/<strong>462</strong><br />
22.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029406 GAMA ENGINEERING Ltd. REV. 1 1. 35-33, 35-A33, 35-B33 Amendment to existing STC 10029406 to add None Prior to installation of this modification it 03.<strong>01</strong>.2<strong>01</strong>1<br />
2. 35-C33, 35-C33A, E33, E33A TAWS-B functionality andinclude optional<br />
must be determined thatthe<br />
3. E33C, F33, F33A, F33C, H35 GAD43 autopilot interface unit.<br />
interrelationship between this modification<br />
4. J35, K35, M35, N35, P35<br />
and any other previouslyinstalled<br />
5. S35, V35, V35A, V35B<br />
modification and/ or repair will introduce<br />
6. 36, A36, A36TC, B36TC<br />
no adverse effectupon the airworthiness<br />
7. 95-55, 95-A55, 95-B55<br />
8. 95-C55, D55, E55, 58, 58P<br />
9. 58TC<br />
of the product.<br />
10029499 GAMA ENGINEERING Ltd. BEECH 90 Navigation/ communications systems upgrade. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.03.2<strong>01</strong>0<br />
10029724 GAMA ENGINEERING Ltd. P-<strong>EASA</strong>.A.S.03861 REV. 1 PA-28 Installation of Garmin G500/G600 EFIS<br />
PFD/ND.<br />
This change is limited to the configuration Prior to installation of this modification the 15.<strong>04</strong>.2<strong>01</strong>0<br />
defined in Change StatementCS1050-02 Issue installer must determinethat the<br />
1 or later approved revision.<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10029726 GAMA ENGINEERING Ltd. REV. 1 PIPER PA-28 16.<strong>04</strong>.2<strong>01</strong>0<br />
1003<strong>04</strong>65 GAMA ENGINEERING Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>596 BO105 Mounting boom for camera<br />
CAT-A-operation is prohibited (CAT-A- The approval holder shall fulfill the 16.06.2<strong>01</strong>0<br />
installation.Certification of the installation of a operation is excluded<br />
obligations of Part 21,<br />
mounting boom which can be usedfor fromcertification).Maximum weight for cameras Paragraph21.A109.Prior to installation of<br />
installation of a camera. The camera<br />
used is 43.1 kg and maximum frontal area this modification it must be determined<br />
installation provisions and themaximum weight is1470 sqcm.The used camera has to be thatthe interrelationship between this<br />
and frontal area of cameras which can be used certified separately.<br />
modification and any other<br />
with themountin<br />
previouslyinstalled modification and/ or<br />
repai<br />
10030863 GAMA ENGINEERING Ltd. P-<strong>EASA</strong>.A.S.03823 EXTRA EA-300 / L External camera installation None None 09.07.2<strong>01</strong>0<br />
10031729 GAMA ENGINEERING Ltd. PIPER PA-34 ALL SERIES Installation of Garmin G500/G600 PFD/ND This change is limited to the configuration Prior to installation of this modification it 08.09.2<strong>01</strong>0<br />
defined in Change StatementCS11<strong>01</strong>-<strong>01</strong> Issue must be determined thatthe<br />
1 or later approved revision.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031769 GAMA ENGINEERING Ltd. REV. 1 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10032795 GAMA ENGINEERING Ltd. REV. 1 112, 112TC, 112B, 112TCA,<br />
114, 114A, 114B, 114TC<br />
Child Restraint System - CRS - Installation in<br />
Various Aircraft<br />
Aspen EFD1000 Software Version 2.3.1<br />
upgrade<br />
Limitations in accordance with § 4 - Limitations<br />
of the above mentionedDDP, ref. No. DDP-<br />
1898-<strong>01</strong>2All cabin interiors must be evaluated<br />
for compatibility of the ChildRestraint System<br />
(CRS). The CRS is not approved for<br />
aeroplanes that arenot defined by § 4 o<br />
Procedures for extending the listing of<br />
approved aeroplane installationsin § 4 of<br />
the above referenced DDP are defined in<br />
Certification Plan No.TN 1898-005.Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
06.07.2<strong>01</strong>2<br />
None<br />
between t<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2<strong>01</strong>2<br />
10033225 GAMA ENGINEERING Ltd. PA-44-180 & PA-44-180T Installation of Garmin G500/G600 PFD/ND None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.<strong>01</strong>.2<strong>01</strong>1<br />
10033770 GAMA ENGINEERING Ltd. P-<strong>EASA</strong>.A.S.03723 CESSNA 310 Introduction of EXP5000 electronic primary<br />
flying display and dualGNS430W GPS<br />
navigation/communication units.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
27.07.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 228/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10033778 GAMA ENGINEERING Ltd. P-<strong>EASA</strong>.A.S.03724 CESSNA 310 Introduction of a GDC31 autopilot roll steering None Prior to installation of this modification it 27.07.2009<br />
converter<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
10034337 GAMA ENGINEERING Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10034531 GAMA ENGINEERING Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10034814 GAMA ENGINEERING Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
100377<strong>01</strong> GAMA ENGINEERING Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10037800 GAMA ENGINEERING Ltd. A) BN2A-8, BN2A-9, BN2A-20<br />
A) BN2A-21, BN2A-26<br />
A) BN2A-27, BN2B-20, BN2B-21<br />
A) BN2B-26, BN2B-27, BN2T<br />
A) BN2T-4R, BN2T-4S<br />
B) BN2A MARK III-3<br />
B) BN2A MARK III, III-1, III-2<br />
10039502 GAMA ENGINEERING Ltd. BN.2A MARK III TRISLANDER,<br />
BN.2A MARK III-1 TRISLANDER,<br />
BN.2A MARK III-2 TRISLANDER,<br />
BN.2A MARK III-3 TRISLANDER.<br />
Navigation/Communications Upgrade. None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.03.2<strong>01</strong>1<br />
Installation of Garmin G500 EFIS PFD/ND. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.<strong>04</strong>.2<strong>01</strong>1<br />
Navigation/ communications upgrade None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2<strong>01</strong>1<br />
GNS-W Navigation System Qualification None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.12.2<strong>01</strong>1<br />
GNS-W Navigation System Qualification in<br />
accordance with MDL-1275, Issue2.<br />
Installation of Aspen EFD1000 Electronic<br />
Primary Flight Display<br />
None None 22.12.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.05.2<strong>01</strong>2<br />
10<strong>04</strong>1163 GAMA ENGINEERING Ltd. P2006T Wingtip pyrotechnics & LED lights. As per: Flight manual supplement AFMS -1306 As per: Flight manual supplement AFMS - 24.08.2<strong>01</strong>2<br />
& Instructions for ContinuedAirworthiness ICA- 1306 & Instructions for<br />
1306.<br />
ContinuedAirworthiness ICA-1306. Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modifica<br />
10<strong>01</strong>5372 GARMIN INTERNATIONAL, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>023 SA<strong>01</strong>254WI DIAMOND DA-40 Installation of Garmin G1000 in the DA40 and<br />
DA40F airplane<br />
1. Hartzell Propeller STC <strong>EASA</strong>.IM.A.S.<strong>01</strong>644<br />
must be installed2. Diamond Aircraft Inductries<br />
Modifications listed in Garmin Drawing 005-<br />
003<strong>04</strong>-00 Rev 10 or later approved revision<br />
must be installed<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 229/<strong>462</strong><br />
11.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10033158 GARMIN INTERNATIONAL, Inc. P-<br />
REV. 2 FAA STC SA<strong>01</strong>535WI-D BEECH 200, 200C, B200, B200C Installation of the Garmin G1000 Integrated None Additional airframe, engine and propeller 05.10.2<strong>01</strong>1<br />
<strong>EASA</strong>.IM.A.S.03191<br />
Avionics System and GFC 700Automatic Flight<br />
configuration requirements aredefined in<br />
Control System and optional Electronic Stability<br />
the data shown on the Garmin Master<br />
andProtection system (ESP).<br />
Drawing List (MDL)identified<br />
above.Aircraft modified by this STC must<br />
be maintained in accordance with<br />
theInstructions for Continued Airw<br />
10034918 GARMIN INTERNATIONAL, Inc. FAA STC SA<strong>01</strong>595WI-D G36 G1000 Integrated Avionics System update with<br />
options including SyntheticVision and Pathways<br />
and GTS 820 Traffic Advisory System<strong>EASA</strong><br />
Approval of SBAS based LNAV/VNAV and<br />
LPV Functionality.<br />
10034986 GARMIN INTERNATIONAL, Inc. FAA STC SA<strong>01</strong>584WI-D G58 G1000 Integrated Avionics System update with<br />
10037574 GARMIN INTERNATIONAL, Inc. FAA STC SA02<strong>01</strong>9SE-D SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
options including SyntheticVision and Pathways<br />
and GTS 820 Traffic Advisory System<strong>EASA</strong><br />
Approval of SBAS based LNAV/VNAV and<br />
LPV Functionality.<br />
Installation of Garmin GTN 6XX/7XX<br />
Navigation System.<br />
10<strong>04</strong>0630 GCT DESIGN ORGANISATION GmbH 319-100 General Fin Camera Installation on Airbus<br />
A319<br />
10<strong>04</strong>0680 GCT DESIGN ORGANISATION GmbH REV. 1 B747-8 Structural provisions for 747-8i belly camera<br />
installation between theNLG bay and the belly<br />
fairing at the lowest point of the fuselage.<br />
Itcontains:- Attachment to the aircraft structure<br />
through brackets- Outside fairing- Installation of<br />
a wiring feed-thro<br />
10<strong>01</strong>5409 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>123 FAA STC ST02902AT BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
10<strong>01</strong>5450 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>194 REV. 1 FAA STC ST03<strong>04</strong>2AT BOEING 767-200<br />
BOEING 767-300<br />
10<strong>01</strong>5451 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>195 FAA STC ST03<strong>04</strong>1AT BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
10<strong>01</strong>5470 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>223 FAA STC ST03002AT BOEING 767-200<br />
BOEING 767-300<br />
10<strong>01</strong>5475 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>228 FAA STC ST0<strong>01</strong>15AT BOEING 767-200<br />
BOEING 767-300<br />
None Aircraft modified with this STC must be<br />
maintained in accordance withthe<br />
instructions for continued airworthiness<br />
(ICA) listed in the GarminMDL identified<br />
above.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship betw<br />
None Aircraft modified with this STC must be<br />
maintained in accordance withthe<br />
instructions for continued airworthiness<br />
(ICA) listed in the GarminMDL identified<br />
above.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship betw<br />
In order to approve adaptations for each<br />
specific installation a MinorChange must be<br />
raised for each installation as defined in the<br />
<strong>EASA</strong>Checklist ref 190-<strong>01</strong>007-E1.<br />
This design change approval is applicable on<br />
Aircraft model AirbusA319-100, aircraft serial<br />
number 4428.<br />
If the holder agrees to permit another<br />
person to use this Certificate tomake an<br />
installation the holder shall give that<br />
person written evidenceof that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship bet<br />
The GCT’s Instructions for continued<br />
airworthiness A319A-ICA-A, Revision0<br />
does not require additional EWIS ICAs<br />
tasks on top of those alreadydefined by<br />
original TC Holder Airbus. The GCT ICAs<br />
identify the specificoriginal Airbus EWIS<br />
ICAs applicable to thi<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of a honeywell RESCU 406 AF ELT 1. This STC is approved only for the product<br />
system<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of Honeywell Aircraft Comunication<br />
Addressing & Reporting System (ACARS).<br />
Installation of a Honeywell ARINC Data<br />
Acquisition Management System<br />
Installation of a Honeywell Enhanced Ground<br />
Proximity Warning System.<br />
Installation of Dual Mode S Transponders &<br />
Honeywell Traffic Alert & Collision Avoidance<br />
System II - FAA STC ST0<strong>01</strong>15AT<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 230/<strong>462</strong><br />
13.05.2<strong>01</strong>1<br />
18.05.2<strong>01</strong>1<br />
07.12.2<strong>01</strong>1<br />
16.07.2<strong>01</strong>2<br />
24.07.2<strong>01</strong>2<br />
30.05.2005<br />
12.06.2008<br />
30.05.2005<br />
14.06.2005<br />
14.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5620 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>572 FAA STC ST03138AT BOEING 737-200<br />
Installation of Honeywell Enhanced Ground According to FAA STC ST03138AT 03.03.2006<br />
BOEING 737-300<br />
Proximity Warning System according to FAA<br />
BOEING 737-400<br />
BOEING 737-500<br />
STC ST03138AT<br />
10<strong>01</strong>5639 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>602 FAA STC ST03126AT BOEING 737-100<br />
Installation of a honeywell RESCU 406AF According to FAA STC ST03126AT 29.11.2005<br />
BOEING 737-200<br />
Emergency locator transmitter (ELT) System<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
according to FAA STC STO3126AT<br />
10<strong>01</strong>6072 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.02253 FAA STC ST<strong>01</strong>792AT BOEING 757-200 TCAS and Duel Mode-S Transponders<br />
Installation.<br />
17.10.2007<br />
10<strong>01</strong>6466 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.02812 FAA STC ST03486AT BOEING 737-200<br />
Installation of a Haneywell ARINC 717 Flight<br />
19.03.2008<br />
BOEING 737-300<br />
Data Acquisition Management System<br />
BOEING 737-400<br />
BOEING 737-500<br />
(FDAMS).<br />
10035023 GENERAL AEROSPACE INC <strong>EASA</strong>.IM.A.S.02759 FAA STC SA3169SO B737-200, B737-300<br />
Installation of a Collins Traffic Alert an Collision A copy of this STC must be included in the Prior to installation of this modification the 30.07.2009<br />
B737-400, B737-500<br />
Avoidance Systemand Dual Mode-S<br />
permanent record of theaircraft.<br />
installer must determinethat the<br />
Transponders.<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>6948 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>343 REV. 1 FAA STC SH4747NM EUROCOPTER FRANCE AS 350 Installation of consoles, toggle switches, circuit 1. Prior to installation of this modification the<br />
25.11.2008<br />
B<br />
breakers, and replacement wiring harnesses in installer must determine that the<br />
EUROCOPTER FRANCE AS 350 accordance with MDL GA107.This STC is the interrelationship between this modification and<br />
B1<br />
validation of FAA STC SH4747NM (issued on any other previously installed modification will<br />
EUROCOPTER FRANCE AS 350 July 26, 1989 and last amended August 8, introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
2008).<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6960 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>357 FAA STC SR0<strong>04</strong>74SE EUROCOPTER FRANCE AS 350 Modular Equipment Rack installation per MDL This STC provides approval for structural<br />
03.<strong>04</strong>.2008<br />
B<br />
GA179.<br />
provisions only. A separate approval is required<br />
EUROCOPTER FRANCE AS 350<br />
for the installation of any equipment inthe<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
modular equipment rack.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 231/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6961 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>359 FAA STC SR00326SE EUROCOPTER FRANCE AS 350 Microwave Pod installation per MDL GA170 Prior to installation of this modification the<br />
15.07.2008<br />
B<br />
installer must determine that the<br />
EUROCOPTER FRANCE AS 350<br />
interrelationship between this modification and<br />
B1<br />
any other previously installed modification<br />
EUROCOPTER FRANCE AS 350<br />
will introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
airworthiness of the product.<br />
10<strong>01</strong>6972 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>373 FAA STC SH4748NM EUROCOPTER FRANCE AS 350 Installation of a replacement instrument panel 1. Prior to installation of this modification the<br />
11.12.2008<br />
B<br />
visor in accordance with MDL GA127. installer must determine that the<br />
EUROCOPTER FRANCE AS 350<br />
interrelationship between this modification and<br />
B1<br />
any other previously installed modification will<br />
EUROCOPTER FRANCE AS 350<br />
introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
airworthiness of the product. The i<br />
10<strong>01</strong>6973 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>374 FAA STC SR00222SE EUROCOPTER FRANCE AS 350 Installation of a supplemental avionics console This STC provides approval for structural<br />
07.03.2008<br />
B<br />
per MDL GA158.<br />
provisions only. A separate approval is required<br />
EUROCOPTER FRANCE AS 350<br />
for the installation of any equipment inthe<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
supplemental avionics console.<br />
10<strong>01</strong>6974 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>375 FAA STC SR00242SE EUROCOPTER FRANCE AS 350 Installation of a new instrument panel and 1. Prior to installation of this modification the<br />
11.12.2008<br />
B<br />
pedestal per MDL GA162.<br />
installer must determine that the<br />
EUROCOPTER FRANCE AS 350<br />
interrelationship between this modification and<br />
B1<br />
any other previously installed modification will<br />
EUROCOPTER FRANCE AS 350<br />
introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
airworthiness of the product. The i<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 232/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6975 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>376 FAA STC SH5119 NM EUROCOPTER FRANCE AS 350 Rear Bench Seat Modification per MDL GA141<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
03.<strong>04</strong>.2008<br />
10<strong>01</strong>6992 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>4<strong>01</strong> FAA STC SR00388SE EUROCOPTER FRANCE AS 350 Installation of a rear communications console This STC provides approval for structural<br />
06.03.2008<br />
B<br />
per MDL GA178This STC is the validation of provisions only. A separate approval is required<br />
EUROCOPTER FRANCE AS 350 FAA STC SR00388SE (last amended January for the installation of any equipment inthe<br />
B1<br />
18, 2000)<br />
communication console.The rear<br />
EUROCOPTER FRANCE AS 350<br />
communications console installation is not<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
approved for the cabin configuration with the t<br />
10<strong>01</strong>7002 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>413 FAA STC SR00361SE EUROCOPTER FRANCE AS 350 Utility Rack installation per MDL GA164. This STC provides approval for Utility Rack<br />
16.07.2008<br />
B<br />
installation only. A separate approval is<br />
EUROCOPTER FRANCE AS 350<br />
required for the installation of any equipment in<br />
B1<br />
the utility rack.Prior to installation of this<br />
EUROCOPTER FRANCE AS 350<br />
modification the installer must determine that<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
the interrelationship<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 233/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7003 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>414 FAA STC SH4785NM EUROCOPTER FRANCE AS 350 Installation of Dome Light / Air Vent<br />
27.02.2008<br />
B<br />
AssemblyThis STC is the validation of FAA<br />
EUROCOPTER FRANCE AS 350 STC SH4785NM issued on 06 November,<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
1989<br />
10<strong>01</strong>70<strong>04</strong> GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>415 FAA STC SH5120NM EUROCOPTER FRANCE AS 350 Installation of a two place front seat. Copilot dual controls may not be installed with<br />
20.03.2008<br />
B<br />
this STC;Number of occupants increased to 7<br />
EUROCOPTER FRANCE AS 350<br />
(1 pilot and 6 passengers) with this STC<br />
B1<br />
installed.The following placard to be installed<br />
EUROCOPTER FRANCE AS 350<br />
on the instrument panel in front of the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
pilot:AIRCRAFT IS BALLASTED TO ALLO<br />
10<strong>01</strong>7054 GENEVA AVIATION, INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>483 FAA STC SR0<strong>01</strong>91SE EUROCOPTER FRANCE AS 350 Installation of a single place pilot/copilot seat in Prior to installation of this modification the<br />
27.08.2008<br />
B<br />
accordance with MDL GA156<br />
installer must determine that the<br />
EUROCOPTER FRANCE AS 350<br />
interrelationship between this modification and<br />
B1<br />
any other previously installed modification<br />
EUROCOPTER FRANCE AS 350<br />
will introduce no adverse effect upon the<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
airworthiness of the product.<br />
10030234 GENEVA AVIATION, INC. P-<br />
FAA STC SH4776NM AS 350 B, AS 350 B1, AS 350 B2 Installation of replacement transmission None 1.,,Prior to installation of this modification 17.02.2009<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>482<br />
AS 350 B3, AS 350 BA, AS 350 D cowling panels i.a.w. MasterDrawing List<br />
the installer mustdetermine that the<br />
GA119.This STC is the validation of FAA STC<br />
interrelationship between this modification<br />
SH4776NM (issued on October 06,1989).<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2.,,The ins<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 234/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
1003<strong>04</strong>79 GENEVA AVIATION, INC. P-<br />
FAA STC SR00219SE 1. AS350B, AS350B1, AS350B2 Horizontal Stabilizer Color Camera MountThis None Prior to installation of this modification it 17.06.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>510<br />
1. AS350BA, AS350D<br />
STC is the validation of FAA STC SR00219SE<br />
must be determined thatthe<br />
2. AS355E, AS355F, AS355F1, (last amended August 11,1995)<br />
interrelationship between this modification<br />
2. AS355F2, AS355N<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036806 GENEVA AVIATION, INC. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>362<br />
10036868 GENEVA AVIATION, INC. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>400<br />
FAA STC SR00521SE 1. AS350B, AS350BA, AS350B1<br />
1. AS350B2, AS350B3, AS350D<br />
2. AS355E, AS355F, AS355F1<br />
2. AS355F2<br />
3. BELL 407<br />
FAA STC SR00643SE 1. AS350 D/-B/-B1/-B2/-BA<br />
2. AS355 E/-F/-F1/-F2<br />
3. BO-105 A/-C/-S/-LS A-1<br />
3. BO-105 LS A-3<br />
4. BELL 206 L-3/-L-4<br />
4. BELL 206A/-A-1/-B/-L/-L-1<br />
4. BELL 407<br />
10<strong>01</strong>5647 GKN AEROSPACE CHEM-TRONICS Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>620 - AIRBUS A318<br />
AIRBUS A319<br />
AIRBUS A320<br />
AIRBUS A321<br />
10<strong>01</strong>6008 GKN AEROSPACE CHEM-TRONICS Inc. <strong>EASA</strong>.IM.A.S.02173 FAA STC ST<strong>01</strong>189LA BOEING DC-9-81/82<br />
BOEING DC-9-83 (MD-83)<br />
BOEING DC-9-87 (MD-87)<br />
BOEING MD-88<br />
Installation of Geneva Aviation Audio System<br />
per Geneva Aviation MasterDrawing List<br />
GA182This STC is the validation of FAA STC<br />
SR00521SE (last amended April 09,2009)<br />
Installation of Geneva Aviation Video System<br />
per Geneva Aviation MasterDrawing List<br />
GA183This STC is the validation of FAA STC<br />
SR00643SE (last amended April 17,2009)<br />
Replacement CFM56-5B Inlet Barrel Lower<br />
Panel Assembly (Part Number 030-130<strong>01</strong>-<br />
1)Replacement CFM56-5B Inlet Barrel Lower<br />
Panel Assembly (Part Number 030-130<strong>01</strong>-1)<br />
Installation of ASTECH Manufacturing, Inc.<br />
inlet assembly<br />
10<strong>01</strong>6312 GKN AEROSPACE CHEM-TRONICS Inc. <strong>EASA</strong>.IM.A.S.02616 FAA STC SA5818NM MD-88 FAA STC SA5818NM “Installation of<br />
Astech/MCI tailpipe assembly.<br />
10<strong>01</strong>6441 GKN AEROSPACE CHEM-TRONICS Inc. <strong>EASA</strong>.IM.A.S.02786 FAA STC ST<strong>01</strong>898LA; WILLIAM BON AIRBUS A319<br />
AIRBUS A320<br />
AIRBUS A321<br />
10<strong>01</strong>6571 GKN AEROSPACE CHEM-TRONICS Inc. <strong>EASA</strong>.IM.A.S.02969 FAA STC ST<strong>01</strong>578LA;BOND TEL.<strong>01</strong>1 AIRBUS A319-113<br />
AIRBUS A319-114<br />
AIRBUS A320-111<br />
AIRBUS A320-211<br />
AIRBUS A320-212<br />
Installation of ASTECH Engineered Products<br />
fan cowl door in accordance with ASTECH’s<br />
Master Drawing List V2500 Cowl Door<br />
Assembly No. MDL030-16103, Revision “A”.<br />
Installation of ASTECH Engineered Products,<br />
Inc. Inlet Inner BarrelAssembly in accordance<br />
with Master Drawing List, A320/CFM56-<br />
5ASeries Engine Inlet, Drawing List Number<br />
MDL030-11030 Revision C.<br />
Any optional Geneva Aviation modifications<br />
listed in InstallationInstructions, to be installed<br />
in conjunction with this STC, shall be<strong>EASA</strong><br />
approved. The STC applicability does not<br />
cover the model AS350B3<br />
incorporatingmodification OP-4305 (Arriel2D<br />
engine in<br />
Any optional Geneva Aviation modifications<br />
listed in InstallationInstructions, to be installed<br />
in conjunction with this STC, shallbe<br />
<strong>EASA</strong> approved.This STC covers installation of<br />
the complete set of equipment as definedby<br />
this STC or a subset of thos<br />
This approval should not be extended to other<br />
specified airplanes of this model series on<br />
which other previously approved modifications<br />
are incorporated, unless it is determined that<br />
the interrelationship between this change and<br />
any those other previously<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.1 The ins<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>4305 GKN AEROSPACE SERVICES LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>549 REV. 1 BOEING 737 Number 1 Cockpit Windshields. Addition of This approval provides for the installation of the<br />
layers of polyurethane interlayer to the existing referenced windows individually or in any<br />
qualified designs to improve in-servicereliability combination.<br />
10<strong>01</strong>4677 GKN AEROSPACE SERVICES LIMITED <strong>EASA</strong>.A.S.02838 BOEING 747 Introduction of cockpit windows with improved<br />
design for Boeing 747 series aircraft. GKN p/n<br />
06314 and 06315 as replacement for Boeing<br />
p/n 65B27<strong>04</strong>2 and 65B27<strong>04</strong>6 and GKN p/n<br />
06316 and 06317 as replacement for Boeing<br />
p/n 065B27<strong>04</strong>3 and 65B27<strong>04</strong>7.<br />
This approval provides for the installation of the<br />
referenced windows indivdually or in any<br />
combination.<br />
Prior to installation of this modification it 07.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 235/<strong>462</strong><br />
13.10.2<strong>01</strong>1<br />
30.<strong>01</strong>.2006<br />
31.10.2006<br />
19.03.2008<br />
10.10.2008<br />
12.12.2008<br />
12.<strong>01</strong>.2007<br />
10.<strong>04</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4782 GKN AEROSPACE SERVICES LIMITED <strong>EASA</strong>.A.S.02980 BOEING 737-100<br />
Number 2 Cockpit Windshields Addition of This approval provides for the installation of the<br />
19.12.2007<br />
BOEING 737-200<br />
Layers of Polyrethane Interlayer to the Existing referenced windows individually or in any<br />
BOEING 737-200C<br />
Qualified Design to improve In-Service combination.<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-700C<br />
BOEING 737-800<br />
BOEING 737-900<br />
Reliability.<br />
10036545 GKN AEROSPACE SERVICES LIMITED P-<strong>EASA</strong>.A.S.03492 REV. 1 B777-200, B777-200LR<br />
Installation of a GKN Aerospace designed None Replacement of a Flight Compartment 02.11.2<strong>01</strong>1<br />
B777-300, B777-300ER<br />
Boeing 777 No 1 Windshield PartNo. 10702<br />
Window Number 1 per this STC withGKN<br />
B777F<br />
(LH) / 10703 (RH); or Part No. 10712 (LH) /<br />
ATS part no. 10712 (LH) / 10713 (RH)<br />
10713 (RH)<br />
together with the relevantwiring loom<br />
modification constitutes an Alternative<br />
Method of Compliance(AMOC) to the<br />
terminating action requirements of<br />
10<strong>01</strong>5318 GLOBAL AIRWORKS, Inc. <strong>EASA</strong>.IM.A.S.00254 REV. 1 FAA STC ST<strong>01</strong>626LA; <strong>EASA</strong>.IM.A.S BOMBARDIER CL-600-2B19<br />
BOMBARDIER CL-600-2C10<br />
BOMBARDIER CL-600-2D24<br />
10<strong>01</strong>6684 GLOBAL AIRWORKS, Inc. <strong>EASA</strong>.IM.A.S.C.<strong>01</strong>05<br />
9<br />
REV. 1 FAA STC ST<strong>01</strong>585LA A330-2<strong>01</strong>, A330-202, A330-203<br />
A330-223, A330-243, A330-3<strong>01</strong><br />
A330-321, A330-322, A330-323<br />
A330-341, A330-342, A330-343<br />
10<strong>04</strong>1546 GLOBAL AIRWORKS, Inc. FAA STC ST3<strong>04</strong>2CH ATR 42-200, ATR 42-300,<br />
ATR 42-320, ATR 42-500<br />
ATR 72-1<strong>01</strong>, ATR 72-102,<br />
ATR 72-2<strong>01</strong>, ATR 72-202,<br />
ATR 72-211, ATR 72-212,<br />
ATR 72-212A.<br />
Installation of Airworks Cockpit Door<br />
Prior to installation of this modification the<br />
Surveillance SystemRevision 1: Amended FAA installer must determine that the<br />
STC ST<strong>01</strong>626LA<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of AirWorks Cockpit Door Prior to the installation of this modification it<br />
Surveillance Systems (Validationof the FAA must be determinedthat the interrelationship<br />
STC ST<strong>01</strong>585LA). This STC installs a CDSS. between this modification and any<br />
The Revision 1 has been issued to correct the otherpreviously installed modification and/or<br />
references of AssociatedTechnical Documents. repair will introduce noadverse effect upon the<br />
airworthiness of the product.<br />
05.<strong>01</strong>.2009<br />
30.11.2<strong>01</strong>1<br />
Installation of a Global AirWorks Cockpit Door None<br />
Surveillance SystemThis STC installs a cockpit<br />
door surveillance system (CDSS) allowingcrew<br />
to view video images of the area outside the<br />
cockpit door.<br />
None 26.09.2<strong>01</strong>2<br />
10<strong>01</strong>57<strong>04</strong> GODERICH AIRCRAFT Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>691 - BEECH B300 Artex ELT C406-N Installation. Modification limited to s/n FL-175.Maintenance<br />
must be in accordance with above Continued<br />
Airworthiness document<br />
10<strong>01</strong>5705 GODERICH AIRCRAFT Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>692 BEECH B300 Universal UNS 1E Flight Management System<br />
Installation.<br />
Modification limited to s/n FL-175.Operation<br />
must bein accordance with Goderich Aircraft<br />
Inc. Flight Mnaual Supplement FMS05097-1<br />
Revision N/C approved 20 September 2005 or<br />
later approved revision. Maintenance must be<br />
in accordance with above Continued Air<br />
10<strong>01</strong>5886 GODERICH AIRCRAFT Inc. <strong>EASA</strong>.IM.A.S.020<strong>04</strong> O-LSA06-081/D (LSTC) BEECH 400A (HAWKER 400 XP) Cabin Entertainment Equipment Installation. This Installation is limited to the Serial No. RK-<br />
37 (Registration SE-DRS).This approval is for<br />
electrical/avionics aspects only. Structural<br />
aspects of this installation are not included and<br />
require separate approval.<br />
10<strong>01</strong>5887 GODERICH AIRCRAFT Inc. <strong>EASA</strong>.IM.A.S.02005 O-LSA06-117/D (LSTC) BEECH 400A (HAWKER 400 XP) Change in interior seating arrangement, 1. This Installation is limited to the Serial No.<br />
addition of sink to existing rear lavatory, RK-37 (Registration SE-DRS).2. Compatibility<br />
fabrication and installation of RH fwd<br />
of this modification with other previously<br />
cabinet,revision of existing LH fwd cabinet, approved modifications must be determined by<br />
revision to interior finishing details, and addition the installer.<br />
of new fuselage antenna.<br />
10<strong>01</strong>6452 GODERICH AIRCRAFT Inc. <strong>EASA</strong>.IM.A.S.02798 TCCA STC O-LSA08-056/D ISSUE 3 FALCON 10 <strong>EASA</strong> Validation of Transport Canada Limited<br />
STC O-LSA08-056/D Issue 3:Cabin<br />
Entertainment Equipment Upgrade for Falcon<br />
10 serial number 161 aircraft in accordance<br />
with Avionics Design Services Ltd. Master<br />
Drawing List MDL08009 Revision B, dated 31st<br />
March<br />
<strong>EASA</strong> STC limited to Falcon 10 serial number<br />
161 aircraftSee original Transport Canada<br />
Limited STC O-LSA08-056/D Issue 3See:<br />
Avionics Design Services Ltd. Master Drawing<br />
List MDL08009 Revision B, Issue 1, dated 31st<br />
March 2008.Goderich Aircraft Inc. Mainten<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 236/<strong>462</strong><br />
17.<strong>01</strong>.2006<br />
17.<strong>01</strong>.2006<br />
09.11.2006<br />
19.12.2006<br />
21.<strong>04</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4214 GOMOLZIG FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.<strong>01</strong>374 REV 1 CESSNA 182E<br />
Installation of Noise Reduction Kit C182- 1. The approval is valid only in combination<br />
<strong>04</strong>.08.2006<br />
MASCHINENBAU<br />
CESSNA 182F<br />
606650<br />
with the installation of FAA STC SA009133SC<br />
CESSNA 182G<br />
(Texas Skyways Inc) or STC SA0<strong>01</strong>52WI (Air<br />
CESSNA 182H<br />
Plains Services Corp.) Both with own <strong>EASA</strong><br />
CESSNA 182J<br />
approval.2. The approval for the models<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA F182-P<br />
CESSNA F182-Q<br />
Cessna 182 E, F and G is not valid fo<br />
10<strong>01</strong>4302 GOMOLZIG FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.<strong>01</strong>546 DR300/108, DR300/125<br />
Operation on unleaded automotive gasoline in<br />
14.09.2005<br />
MASCHINENBAU<br />
DR300/180R, DR315<br />
DR400/120(D), DR400/125<br />
DR400/140B, DR400/180R<br />
DR400/2+2, DR400/140<br />
accordance with Norm EN 228<br />
10<strong>01</strong>4483 GOMOLZIG FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.02546 PIPER PA-23-250 Modification 13452Alteration of Piper PA-23-<br />
13.03.2006<br />
MASCHINENBAU<br />
250 aircraft to aerial work with a Leica ADS 40<br />
digital camera installation in addition to the<br />
installation of Zeiss RMK 15 Top Cameras<br />
based on <strong>EASA</strong> approval No. 20<strong>04</strong>-9428<br />
10<strong>01</strong>4590 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>4635 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>4670 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>4832 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>4836 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>4907 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
<strong>EASA</strong>.A.S.02699 DIAMOND HK-36 SUPER<br />
DIMONA<br />
Modification of the Dimona HK 36 R "Super<br />
Dimona" equipped with the engine Rotax 912<br />
A3 with the alternative Propeller MTV-21-A-<br />
CF/C175-05.<br />
<strong>EASA</strong>.A.S.02779 CESSNA 172S Installation of Noise Reduction Kit C172S-<br />
606560<br />
<strong>EASA</strong>.A.S.02829 REV. 2 CESSNA 172RG Modification 14839Installation of Low Noise<br />
Silencer Kit "System Gomolzig"<br />
C172RG_606520<br />
All S/N of the variant: HK 36 R "Super<br />
Dimona"<br />
11.06.2008<br />
None 26.09.2006<br />
As referred in AFM-S Must be maintained iaw. Original Cessna 22.02.2<strong>01</strong>2<br />
MM and in addition iawMaintenance<br />
Instructions given in the above mentioned<br />
InstallationInstructions or later approved<br />
revisions. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelatio<br />
<strong>EASA</strong>.A.S.03<strong>04</strong>7 REV. 1 1. PA-34-200T (SENECA II) System PA-34-812000Installation of Penta As referred in AFM-S Must be maintained iaw. Original Piper 21.12.2<strong>01</strong>1<br />
1. PA-34-220T (SENECA III) Camera SystemSystem PA-34-813000<br />
MM and in addition iawMaintenance<br />
1. PA-34-220T (SENECA IV) Version 2024425Camera Hatch and<br />
Instructions given in the above mentioned<br />
2. PA-34-220T (SENECA V) Equipment Installation<br />
InstallationInstructions or later approved<br />
revisions.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelations<br />
<strong>EASA</strong>.A.S.03052 CESSNA 182 Towing Kit Cessna 182 "System Gomolzig" Cessna 182M, N,P,Q,R, equipped with SMA<br />
12.10.2007<br />
C182-820000".The Cessna 182 and its series SR 305-23-MA<strong>01</strong> Diesel engine according to<br />
equipped with the SMA Diesel engine shall be<br />
equipped with a towing system for banning<br />
towing and sailplanes up to 850 kg MTOW.<br />
STC <strong>EASA</strong>.A.S.00774.<br />
<strong>EASA</strong>.A.S.03145 REV. 1 TP206C-E, TU206B,<br />
TU206E-G, T206H.<br />
Cessna Exhaust System with Extension1. as referred in limitations section of the AFM-S<br />
TP206C-E; TU206B, E-G Exhaust System with xxx<br />
Extension c()206()-6065802. T206H Low Noise<br />
Silencer Kit CT206H-606570<br />
Prior to installation of this modification it 30.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 237/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5022 GOMOLZIG FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.03328 CESSNA 4<strong>01</strong><br />
Alternative Supplemental Inspection Document 1. Alteration to A-SID is subject to written<br />
05.12.2008<br />
MASCHINENBAU<br />
CESSNA 4<strong>01</strong>A<br />
(A-SID).<br />
permission of approval holder.2. This<br />
CESSNA 4<strong>01</strong>B<br />
modification is only limited to S/N listed in<br />
CESSNA 402<br />
<strong>EASA</strong> approved Gomolzig Document No.<br />
CESSNA 402A<br />
17070_Master Aircraft Application Control<br />
CESSNA 402B<br />
CESSNA 402C<br />
CESSNA 411<br />
CESSNA 411A<br />
CESSNA 414<br />
CESSNA 414A<br />
CESSNA 421<br />
CESSNA 421A<br />
CESSNA 421B<br />
CESSNA 421C<br />
CESSNA 425<br />
List_<strong>01</strong>122008_ rev0, or later <strong>EASA</strong> approved<br />
10<strong>01</strong>5027 GOMOLZIG FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.03334 CESSNA 208B Installation of Camera Kit Cessna 208B<br />
19.12.2007<br />
MASCHINENBAU<br />
"System Gomolzig" C208B-812000 as defined<br />
by Equipmentlist<br />
AEL_17000_Rev0_11112007.XLS, dated<br />
11.11.2007<br />
10<strong>01</strong>5031 GOMOLZIG FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.03343 REV. 1 DO 28 D-2 Turbine Conversion of Do 28 D-2 (model according limitation section of <strong>EASA</strong> STCDS Prior to installation of this modification it 06.12.2<strong>01</strong>0<br />
MASCHINENBAU<br />
marketing name: Do 28-G92 and Do28-G92- 10<strong>01</strong>5031<br />
must be determined thatthe<br />
EF) including new Propeller variantsMaster<br />
interrelationship between this modification<br />
Drawing List G92 for STC-Version G92-A-<br />
and any other previouslyinstalled<br />
1900; G92-EF-A-1900;G92-A-1950 and G92-<br />
modification and/ or repair will introduce<br />
EF-A-1950Master Document List<br />
no adverse effectupon the airworthiness<br />
MDOCL_2023625_rev0_2<strong>01</strong><strong>01</strong>0<strong>01</strong><br />
of the productIf the h<br />
10<strong>01</strong>5034 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>5<strong>04</strong>0 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>5121 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>5261 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>01</strong>7100 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10027347 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
<strong>EASA</strong>.A.S.03347 REV 1 BEECH 99<br />
BEECH B99<br />
<strong>EASA</strong>.A.S.03353 LEARJET 35A<br />
LEARJET 36A<br />
<strong>EASA</strong>.A.S.03470 <strong>EASA</strong> STC 20<strong>04</strong>-1522 CESSNA 402<br />
CESSNA 402A<br />
CESSNA 402B<br />
CESSNA 402C<br />
<strong>EASA</strong>.A.S.03719 LBA STC 0279/2038 BRITTEN NORMAN BN-2A-21<br />
ISLAND<br />
BRITTEN NORMAN BN-2A-26<br />
ISLAND<br />
BRITTEN NORMAN BN-2A-27<br />
ISLAND<br />
BRITTEN NORMAN BN-2B-20<br />
ISLAND<br />
BRITTEN NORMAN BN-2B-26<br />
ISLAND<br />
Installation of P&W PT6A-34 Engine This STC is limited to Beech 99 / B99 models<br />
equiped with Propeller McCauley<br />
4HFR34C769/94LMA-4 i.a.w. FAA STC<br />
SA1351GL.<br />
Installation of Laser Reflector Dekagon Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Use of Aerial Survey Camera Kit C402-812000<br />
for installation of Zeiss RMK Top 15 and Top<br />
30 cameras.Note: Change to the existing<br />
<strong>EASA</strong> STC 20<strong>04</strong>-1522 to enable optional<br />
operation of digital camera systems or laser<br />
scanners in accordance with MDL<br />
MDRWL_14631_<br />
Installation of Exhaust System Gomolzig BN2-<br />
606500.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
<strong>EASA</strong>.R.S.<strong>01</strong>056 HUGHES 369D, HUGHES 369E Installation of Isolator Washing Platform Helicopter must be eqipped with- High Skid<br />
Landing Gear and- McDonnel Douglas<br />
Helicopter Cargo Hook Kit P/N 369H90072-<br />
505<br />
P-<strong>EASA</strong>.A.S.03887 SA 226T Installation of Wescam MX20 Camera Turret<br />
with ManualExtension/Retraction Mechanism<br />
and Operator Console<br />
Aircraft must be previously modified with<br />
camera hatches i.a.w.Swearingen Camera<br />
Plane Modification<br />
19.12.2008<br />
05.08.2008<br />
08.02.2008<br />
<strong>04</strong>.12.2008<br />
06.12.2006<br />
- The installation of this modification by 24.09.2009<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation- Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationshi<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 238/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029335 GOMOLZIG FLUGZEUG- UND<br />
310, 310A, 310B, 310C, 310D, Alternative Supplemenal Inspection Document As referred in limitations section of the 3A10_A- The installation of this modification by 19.03.2<strong>01</strong>0<br />
MASCHINENBAU<br />
310E, 310F, 310G, 310H, 310I, (A-SID)<br />
SID_Maintenance ManualSupplement_21530 third persons is subject towritten<br />
310J, 310J-1, 310K, 310L, 310N<br />
Alteration to A-SID is subject to written permission of the approval holder and<br />
310P, 310Q, 310R<br />
permission of approval holder This modification holding and disposal ofthe approved<br />
E310H, E310J<br />
is only limited to S/N listed in <strong>EASA</strong><br />
appropriate documentation. Prior to<br />
T310P, T310Q, T310R<br />
approvedGomolzig Document No.<br />
installation of this modification it must be<br />
21530_Mast<br />
determined thatthe interr<br />
10029380 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10029570 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10029736 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10030084 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10030085 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10031342 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10038775 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
10<strong>04</strong>0526 GOMOLZIG FLUGZEUG- UND<br />
MASCHINENBAU<br />
CESSNA 182, -A, -B, -C, -D, -E Camera Modification Kit As referred in limitations section of the AFM- The installation of this modification by 19.03.2<strong>01</strong>0<br />
CESSNA 182F, -G, -H, -J, -K,<br />
S:Airplane Flight Manual Supplement third persons is subject towritten<br />
CESSNA 182L, -M, -N, -P, -Q,<br />
SPOH_2022177_rev0_<strong>01</strong>022<strong>01</strong>0 for permission of the approval holder and<br />
CESSNA 182R, -S, T, T182<br />
Cessna182S, T and T182T Anhang zum holding and disposal ofthe approved<br />
CESSNA T182T<br />
Flughandbuch Kameraumrüstsatz C182- appropriate documentation Prior to<br />
812000 Ausgabe 21.03.97for Cessna 182, -A, - installation of this modification it must be<br />
B, -C, -D, -E, -F, -G, -H, -J<br />
determined thatthe interre<br />
HUSKY A-1, A-1A, A-1B, A-1C Husky A1 Silencer STC Ext. To Variant A, B As referred in limitations section of the AFM- The installation of this modification by <strong>01</strong>.<strong>04</strong>.2<strong>01</strong>0<br />
and C<br />
S:Airplane Flight Manual Supplement third persons is subject towritten<br />
SPOH_21750_rev0_2<strong>01</strong>003<strong>01</strong><br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe interr<br />
P-<strong>EASA</strong>.A.S.03144 CESSNA 421B Installation of Silver Jodide Generators on Not Applicable Prior to installation of this modification it 16.<strong>04</strong>.2<strong>01</strong>0<br />
Cessna 421B<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
LBA STC 0060/549B REV. 1 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
LBA STC 0059/549B REV. 1 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Upwards Opening Door for Parachutist<br />
Dropping.This STC revises and supersedes<br />
LBA STC 0060/549b.<br />
Dropping of max 4 Parachutists with Manual or<br />
Automatic Release. This STC revises and<br />
supersedes LBA STC 0059/549B.<br />
As referred in limitations section of the AFM-<br />
SSPOH_2022824_rev0_15<strong>04</strong>2<strong>01</strong>0For<br />
parachutist dropping<br />
As referred in limitations section of the AFM-<br />
SSPOH_2022926_rev0_15<strong>04</strong>2<strong>01</strong>0Max 4<br />
parachutists<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation.Prior to<br />
installation of this modification it must be<br />
determined thatthe interre<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation.Prior to<br />
installation of this modification it must be<br />
determined thatthe interre<br />
08.10.2<strong>01</strong>0<br />
08.10.2<strong>01</strong>0<br />
208B C208B Ferry Fuel Tank Installation in none The installation of this modification by 11.08.2<strong>01</strong>0<br />
accordance with Gomolzig Flugzeug-und<br />
third persons is subject towritten<br />
Maschinenbau GmbH MDOCL_2023163, Rev.<br />
permission of the approval holder.Prior to<br />
0, dated <strong>01</strong>/08/2<strong>01</strong>0<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinsta<br />
M6/91 PA-25-235, PA-25-260 Modification 2027423Low Noise Silencer Kit<br />
"System Gomolzig" PA-25-606500<br />
PA-31T PA-31T Camera Hole ModificationChange<br />
Note CN_2025593_rev0_2<strong>01</strong>202<strong>01</strong><br />
As referred in AFM-S Must be maintained iaw. Original MM and 13.03.2<strong>01</strong>2<br />
in addition iaw MaintenanceInstructions<br />
given in the above mentioned Installation<br />
Instructions orlater approved<br />
revisions.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship be<br />
as referred in AFM-S Must be maintained iaw. Original Piper<br />
MM and in addition<br />
iawII_2025593_rev0_2<strong>01</strong>202<strong>01</strong> or later<br />
approved revisions.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other previouslyi<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 239/<strong>462</strong><br />
09.07.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0826 GOMOLZIG FLUGZEUG- UND<br />
0<strong>01</strong>0<strong>01</strong>6836-0<strong>01</strong> LBA STC EMZ SA <strong>01</strong>00/2025 CESSNA 340A 1. Camera Modification Kit System C340- As referred in AFM Must be maintained iaw. Original Cessna 27.07.2<strong>01</strong>2<br />
MASCHINENBAU<br />
8120002. C340 Camera Hatch Installation<br />
MM and in addition<br />
System C340-812500Change Note<br />
iawII_2027313_rev0_2<strong>01</strong>2<strong>04</strong>02or later<br />
CN_2027313_rev0_2<strong>01</strong>2<strong>04</strong>02<br />
approved revisions.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other previouslyi<br />
10<strong>01</strong>6207 GOODRICH CORPORATION <strong>EASA</strong>.IM.A.S.02452 FAA STC ST02551CH BOEING 747-400F Installation of Centerline Restraint System on<br />
the main cargo deck of a B747-400F in<br />
accordance with Master Data List MDL<br />
10026859 GOODRICH CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03106<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
7M39300. Validation of FAA STC ST02551CH. any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
02.07.2008<br />
FAA STC ST00989SE-D B767-300F Installation of the CHS (Cargo Handling The operation of the STC is only approved The applicant has to show and maintain 18.08.2009<br />
System) on the B767-300FMD:<br />
when installed on theprovisions of the Boeing the compliance to JAR 25.1309 atchange<br />
MDL7N10000FAA STC: ST00989SE-D A/C B767-300F.<br />
13.Remarks: The STC is part of the<br />
equipment for the Boeing A/C<br />
modelB767-300F. The provisions for the<br />
Cargo Handling System must beinstalled<br />
prior to the installation of the STC<br />
10031947 GOODRICH CORPORATION REV. 1 TCCA STC SA10-3 DHC-8-4<strong>01</strong>, DHC-8-402 Installation of Goodrich De-Icer boots on the<br />
Aircraft Wings, HorizontalStabilizer and Vertical<br />
StabilizerFAA STC ST02834NY, reissued<br />
September 20, 2<strong>01</strong>0(identical with TCCA STC<br />
SA10-3, Issue 2)<br />
10<strong>01</strong>60<strong>01</strong> GOODRICH INTERIORS <strong>EASA</strong>.IM.A.S.02161 REV. 2 FAA STC ST<strong>01</strong>691LA B767-200/-300 Installation of "Sentry One" Flight Deck Door<br />
Camera Surveillance System<br />
10<strong>01</strong>6<strong>462</strong> GOODRICH INTERIORS <strong>EASA</strong>.IM.A.S.02808 REV. 1 FAA STC ST<strong>01</strong>788LA DC-9-81 (MD-81),<br />
DC-9-82 (MD-82),<br />
DC-9-83 (MD-83),<br />
DC-9-87 (MD-87),<br />
MD-88, MD-90-30.<br />
Installation of Sentry One Flight Deck Door<br />
Surveillance Camera System.<br />
10<strong>01</strong>6505 GOODRICH INTERIORS <strong>EASA</strong>.IM.A.S.02869 REV. 1 FAA STC ST<strong>01</strong>007LA-D 737-800 Installation of Hollingsead Sentry One Cabin<br />
Video Camera System.<br />
10<strong>01</strong>6523 GOODRICH INTERIORS <strong>EASA</strong>.IM.A.S.02896 REV. 1 FAA STC ST<strong>01</strong>638LA 737-300, 737-400, 737-500 Installation of Hollinsead Sentry One Cabin<br />
mounted Video Camera System.<br />
100299<strong>01</strong> GOODRICH INTERIORS REV. 1 FAA STC ST<strong>01</strong>472LA-D 747-100, 747-100B,<br />
747-100B SUD, 747-200B,<br />
747-300, 747-400, 747-SP<br />
Installation of Hollingsead International Sentry<br />
One Cockpit Entry DoorSurveillance Camera<br />
System.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.06.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.08.2<strong>01</strong>2<br />
None Prior to installation of this modification the 08.11.2<strong>01</strong>2<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.11.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.11.2<strong>01</strong>2<br />
None FAA approved Flight Manual<br />
Supplement, document No. 2763-<br />
AFM,revision NC, dated May 25,<br />
20<strong>04</strong> is required for the B747-400 series.<br />
FAA approved Flight Manual<br />
Supplement, document No. 2763-AFM-<br />
1,revision NC, dated July 21, 20<strong>04</strong><br />
is required for th<br />
08.11.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 240/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037327 GPI AS 332 C, C1, L, L1, L2 Installation of Cargo Net in Cabin. No Passengers allowedWeight Limitation - 294 Prior to installation of this modification it 18.11.2<strong>01</strong>1<br />
kg;Maximum deformation - 257mm<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>3948 GRAFAIR AB <strong>EASA</strong>.A.S.0<strong>04</strong>21 REV. 1 CESSNA 550<br />
CESSNA S550<br />
10<strong>01</strong>5541 GRIMES AEROSPACE COMPANY <strong>EASA</strong>.IM.A.S.<strong>01</strong>425 ST500CH BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Installation of an Allied Signal Corporation CAS- 1. Pro Star Aviation Aircraft Flight Manual<br />
67A Traffic Alert and Collision Avoidance Supplement No <strong>01</strong>00-FMS-02 for the Cessna<br />
System (TCAS II). Technical Documentation Aircraft Company, Models 550, S550 and 560,<br />
Associated: - FAA STC ST0<strong>01</strong>16BO. - Pro Revision A, FAA-approved March 8, 20<strong>01</strong>, or<br />
Star Aviation, Master Document List No <strong>01</strong>00- later FAA-approved revision, is required with<br />
MDL-02, Revision A, dated February 1, 20 this modification.2. This approval is<br />
Installation of Grimes Aerospace Overwing<br />
Emergency/ IceDetection Light Assemblies<br />
10<strong>01</strong>5936 GROVE AIRCRAFT LANDING GEAR <strong>EASA</strong>.IM.A.S.02077 SA<strong>01</strong>7<strong>04</strong>LA SEE APPROVED MODEL LIST Installation of the Grove Disk Brake System in The installation applies only to aircraft that have<br />
SYSTEMS<br />
accordance with FAA approved Master hydraulic brake systems installed. The<br />
Drawing List Number MDL2337-000<strong>01</strong>, installation should not be incorporated in any<br />
Revision B, dated December 8, 20<strong>04</strong>, or later aircraft unless it is determined that the<br />
FAA approved revision are required as part of interrelationship between this installation any<br />
this installation<br />
ant previous<br />
10<strong>01</strong>5449 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>192 FAA STC ST02883AT-D GULFSTREAM 200 Installation of Transponder Flight ID This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5456 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>202 FAA STC ST10299SC-D GULFSTREAM 200 Installation of ICG-200 SATCOM System 1. Instructions for continued Airworthiness<br />
GA24103A000 Revision N/C dated 31 January<br />
2005 or later FAA approved revision is required<br />
2. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the parag<br />
10<strong>01</strong>5457 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>203 FAA STC ST10297SC-D GULFSTREAM 200 Installation of Executive Cabin Interior 1. This STC is limited to the installation made in<br />
Gulfstream Aerospace LP(Istrael Aircraft<br />
Industries, LTD) model Gulfstream 200 serial<br />
number 103 only.2. This STC does not permit<br />
manufacturing of part for multiple installation3.<br />
This STC is approved only<br />
10<strong>01</strong>5459 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>205 FAA STC ST10050SC-D GULFSTREAM 200 Installation of Honeywell Laseref V IRS 1. Compliance with FAA Special Condition 25-<br />
263-SC and ACG/<strong>EASA</strong> CRI F-06 for HIRF<br />
has been demonstrated.2. The aircraft must be<br />
equipped with Rockwell Collins FMS-6100<br />
Flight Management Systems installed in<br />
accordance with IAI MOD Nos.7219 and<br />
100233. This<br />
10<strong>01</strong>5460 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>206 FAA STC ST10020SC-D GULFSTREAM 200 Installation of DeCrane/ERDA Cabin Double<br />
Seats<br />
10<strong>01</strong>5579 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>490 FAA STC ST09625SC GULFSTREAM 200 Installation of a Universal Unilink UL-6<strong>01</strong><br />
Datalink Data Communication System<br />
10<strong>01</strong>5580 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>491 FAA STC ST09628SC GULFSTREAM 200 Installation of Hard Point Attachments and<br />
associated floor structure<br />
03.11.2005<br />
According to FAA STC ST500CH 08.11.2005<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 241/<strong>462</strong><br />
<strong>04</strong>.07.2006<br />
28.06.2005<br />
28.06.2005<br />
28.06.2005<br />
28.06.2005<br />
28.06.2005<br />
06.10.2005<br />
06.10.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5581 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>492 FAA STC ST09629SC GULFSTREAM 200 Installation of an Artex ELT (110-406 NAV) 1. For aircraft imported into the European<br />
06.10.2005<br />
Emergency Locator Transmitter Sytem with Union, changes per Gulfstream Aerospace<br />
NAV interface<br />
drawing CEB442310<strong>01</strong>, Rev A are required to<br />
be incorporated until Revision L os the<br />
Engineering document 30-110005 has been<br />
released.2. This STC is approved only for the<br />
prod<br />
10<strong>01</strong>5582 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>493 FAA STC ST09747SC GULFSTREAM 200 Installation of a N°2 Allied Signal KHF-950 HF This STC is approved only for the product<br />
06.10.2005<br />
Communication System<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5583 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>494 FAA STC ST09748SC GULFSTREAM 200 Installation of a second 77 cubic-foot oxygen This STC is approved only for the product<br />
06.10.2005<br />
bottle in nose radome area, above existing configuration as defined in the approved design<br />
bottle<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5584 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>495 FAA STC ST09851SC GULFSTREAM 200 Installation of interior shell, forward cabinets, This STC is approved only for the product<br />
06.10.2005<br />
10<strong>01</strong>5585 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>496 FAA STC ST09953SC GULFSTREAM 200<br />
card tables, lavatory partitions and door, curtain configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of B/E Aerospace, Aircraft Modular This STC is approved only for the product<br />
06.10.2005<br />
Products Forward/Rearward Facing Single configuration as defined in the approved design<br />
Seat, model 2524.546.<strong>01</strong> ( )<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5586 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>497 FAA STC ST09954SC GULFSTREAM 200 Installation of an Oxygen Filler Panel with This STC is approved only for the product<br />
06.10.2005<br />
Pressure Gauge<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5749 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>782 REV 2 FAA STC ST103<strong>01</strong>SC-D GULFSTREAM 200 Installation of Executive Cabin Interior in Compatibility of this design change with<br />
03.03.2008<br />
accordance with Index List GA222<strong>04</strong>80<strong>01</strong>, Rev previously approved modifications must be<br />
A, dated 3-23-2005 or later revisions of the<br />
above listed documents approved by <strong>EASA</strong> in<br />
accordance with <strong>EASA</strong> ED Decision<br />
20<strong>04</strong>/<strong>04</strong>/CF (or subsequent revisions of this<br />
dec<br />
determined by the installer.<br />
10<strong>01</strong>5750 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>783 FAA STC ST103<strong>04</strong>SC-D GULFSTREAM 200 Installation of Forward R/H Galley Compatibility of this design change with<br />
previously approved modifications must be<br />
determined by the installer.<br />
14.03.2006<br />
10<strong>01</strong>5751 GULFSTREAM AEROSPACE Corp. <strong>EASA</strong>.IM.A.S.<strong>01</strong>784 FAA STC ST02847AT-D GULFSTREAM 200 Installation of Safe Flight Instrument Corp Auto Compatibility of this design change with<br />
14.03.2006<br />
Power Automatic Throttle Control System previously approved modifications must be<br />
determined by the installer<br />
10<strong>01</strong>5382 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>069 FAA STC ST<strong>01</strong>220LA-D GULFSTREAM GV S/N 641 Aircraft Serial No. 641 completion and cabin 1. GV Serial No. 641 only 17.07.2007<br />
CORPORATION<br />
interior installation.<br />
10<strong>01</strong>5388 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>085 FAA STC ST<strong>01</strong>671LA-D GULFSTREAM GV-SP Cabin Interior Installation 1. This STC is approved only for the product<br />
25.<strong>01</strong>.2005<br />
CORPORATION<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5389 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>086 FAA STC ST<strong>01</strong>376LA-D GULFSTREAM GV-SP Installation of Aerospace Technologies Group 1. This STC is approved only for the product<br />
25.<strong>01</strong>.2005<br />
CORPORATION<br />
(ATG) Cabin Window<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5390 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>087 FAA STC ST<strong>01</strong>373LA-D GULFSTREAM GV-SP Installation of Securaplane External Camera 1. This STC is approved only for the product<br />
25.<strong>01</strong>.2005<br />
CORPORATION<br />
System<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 242/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5391 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>089 FAA STC ST<strong>01</strong>375LA-D GULFSTREAM GV-SP Installation of Airshow CMS Two System 1. This STC is approved only for the product<br />
25.<strong>01</strong>.2005<br />
CORPORATION<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5420 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>150 FAA STC ST<strong>01</strong>752LA-D GULFSTREAM GV-SP Gulfstream Aerospace Corporation<br />
1. Serial 5068 only2. This STC is approved<br />
08.08.2005<br />
CORPORATION<br />
Modification FAA STC ST <strong>01</strong>752 LA-D. Aircraft only for the product configuration as defined in<br />
Completion & Custom Cabin Installation. the approved design data referred to in the<br />
Gulfstream DAS Report Number<br />
paragraph "Description". Compatibility with<br />
GC52000K329 Dated 03/08/05 Flight Manual other aircraft/engine configurations shall be<br />
Supplement ref GC 52000M<strong>01</strong>2 Dated<br />
02/08/05 or later approved revisio<br />
determined by the installer.<br />
10<strong>01</strong>5452 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5487 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5609 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5610 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5612 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5613 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5617 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5618 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5628 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5629 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5673 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5694 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>196 ST<strong>01</strong>753LA-D GULFSTREAM GV-SP Aircraft completion and cabin interior<br />
installationGulfstream DAS report No.<br />
GC52000K341 dated 13 SEP 2005 or later<br />
approved revisions.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>248 FAA STC ST03<strong>04</strong>8AT-D GULFSTREAM GV-SP Aircraft completion and installation of a custom<br />
cabin interior<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>545 ST02952AT-D GULFSTREAM GV-SP Installation of a Satellite communications<br />
system to be used for passenger<br />
communications.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>546 ST<strong>01</strong>824CH-D GULFSTREAM 100<br />
GULFSTREAM ASTRA/SPX<br />
MD-88<br />
Installation of the Honeywell MK-V EGPWS,<br />
with windshear warning and terrain display on<br />
the Collins Pro Line 4 EFIS<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>550 FAA STC ST<strong>01</strong>495LA- GULFSTREAM GV-SP installation of a Honeywell Satellite TV antenna<br />
to provide television reception to passenger<br />
cabin TV monitors<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>551 FAA STC ST<strong>01</strong>378LA-D GULFSTREAM GV-SP Installation of a Conduit in the vertical stabiliser<br />
to accommodate wiring for the STACOM and<br />
SAT TV antennas<br />
This STC is limited to Gulfstream GV-SP Serial<br />
Number 5070 only.<br />
GV-SP Aircraft Serial Number 5057 Only.1.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>569 FAA STC ST02915AT-D GULFSTREAM GV-SP Lightning Sensor System Installation<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
06.12.2005<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>570 FAA STC ST03134AT-D GULFSTREAM GV-SP Aircraft Completion STC Limited to S/N 5080 06.12.2005<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>580 FAA STC ST<strong>01</strong>758LA-D GULFSTREAM G550 Installation of Executive Cabin Interior and<br />
other Completion Related Modifications<br />
G550 S/N 5078 only 30.<strong>01</strong>.2006<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>581 ST<strong>01</strong>503LA-D GULFSTREAM G550 Installation of an Motorola Satellite Telephone<br />
(Iridium) Antenna<br />
GV-SP (550) 30.<strong>01</strong>.2006<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>651 FAA STC ST03142AT-D GULFSTREAM GV-SP Aircraft Completion STC 1. Limited to S/N 50812. This STC is approved<br />
only for the product configuration as defined in<br />
the approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall be<br />
determined by the installer<br />
06.12.2005<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>682 FAA STC ST03<strong>04</strong>7AT-D GULFSTREAM GIV-X Installation of Airshow 4000 (Moving Map and<br />
In-Flight Information)<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 243/<strong>462</strong><br />
21.09.2005<br />
<strong>01</strong>.07.2005<br />
26.09.2005<br />
12.10.2005<br />
06.10.2005<br />
06.10.2005<br />
08.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5695 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>683 REV 1 FAA STC ST03027AT-D GULFSTREAM GIV-X Installation of Broad Band Multi-Link System This STC is approved only for the product<br />
19.<strong>01</strong>.2007<br />
CORPORATION<br />
(BBML).<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>5696 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5697 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5698 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5699 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5773 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5821 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5839 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5914 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5923 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5929 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5930 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5939 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5940 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5941 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5969 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5988 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5989 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5990 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>684 FAA STC ST02987AT-D GULFSTREAM GIV-X Installation of Interior Emergency Lights This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>685 FAA STC ST02980AT-D GULFSTREAM GIV-X Installation of External Camera System<br />
(Securaplane)<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>686 FAA STC ST02979AT-D GULFSTREAM GIV-X Installation of Passenger Oxygen System This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
08.02.2006<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>687 FAA STC ST02948AT-D GULFSTREAM GIV-X Installation of Cabin Window Shades This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
08.02.2006<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>817 FAA STC ST03196AT-D GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial 5094<br />
Aircraft Serial 5094 Only 21.<strong>04</strong>.2006<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>893 FAA STC ST<strong>01</strong>519LA-D GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial No 5<strong>04</strong>0<br />
Aircraft Serial 5<strong>04</strong>0 Only 24.08.2006<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>933 FAA STC ST03224AT-D GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial 5099.<br />
Aircraft Serial 5099 Only. 06.06.2006<br />
<strong>EASA</strong>.IM.A.S.02<strong>04</strong>4 FAA STC ST02920AT-D GULFSTREAM GV-SP Installation of Honeywell MCS-7000 SATCOM None<br />
system<br />
21.08.2006<br />
<strong>EASA</strong>.IM.A.S.02058 FAA STC ST02905AT-D GULFSTREAM 100<br />
GULFSTREAM ASTRA/SPX<br />
Installation of Collins Transponder with Flight ID<br />
for Elementary Surveillance (-5<strong>01</strong><br />
configuration) or Enhanced Surveillance (-503<br />
configuration).<br />
<strong>EASA</strong>.IM.A.S.02065 FAA STC ST03254AT-D GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial 5071<br />
Aircraft Serial 5071 only 21.08.2006<br />
<strong>EASA</strong>.IM.A.S.02066 FAA STC ST03264AT-D GULFSTREAM GIV-X Completion and installation of the custom<br />
interior on Aircraft Serial Number 4<strong>04</strong>5.<br />
Aircraft Serial Number 4<strong>04</strong>5 Only. 27.10.2006<br />
<strong>EASA</strong>.IM.A.S.02081 FAA STC ST<strong>01</strong>673AT-D GULFSTREAM GV-SP Installation of a Honeywell P-880 Radar<br />
System<br />
N/A 15.03.2007<br />
<strong>EASA</strong>.IM.A.S.02082 FAA STC ST<strong>01</strong>673AT-D GULFSTREAM GV-SP Installation of a Transponder Flight<br />
Identification<br />
N/A 15.03.2007<br />
<strong>EASA</strong>.IM.A.S.02083 FAA STC ST<strong>01</strong>388AT-D GULFSTREAM GV-SP Installation of a Vacuum Toilet System N/A 15.03.2007<br />
<strong>EASA</strong>.IM.A.S.02120 FAA STC ST03295AT-D GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial 5116<br />
Aircraft Serial 5116 OnlyThe following STC's<br />
are required to be installed as part of this STC:-<br />
FAA STC ST02915AT-D, <strong>EASA</strong> Approved ref:<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>569,FAA STC ST02796AT-D,<br />
<strong>EASA</strong> Approved ref: <strong>EASA</strong>.IM.A.S.<strong>01</strong>259,FAA<br />
STC ST02696AT-D, <strong>EASA</strong> Approved ref:<br />
<strong>EASA</strong>.<br />
<strong>EASA</strong>.IM.A.S.02142 ST02<strong>04</strong>8CH-D GULFSTREAM GV-SP Installation of the Airshow 4000 -- 14.12.2006<br />
<strong>EASA</strong>.IM.A.S.02143 REV. 1 FAA STC ST02<strong>04</strong>9CH-D GIV-X, GV-SP Installation of Securaplane Security System in<br />
Gulfstream models GIV-Xand GV-SP<br />
<strong>EASA</strong>.IM.A.S.02144 ST02<strong>04</strong>7CH-D GULFSTREAM GV-SP Installation of Magnastar Radio Telephone<br />
System<br />
08.02.2006<br />
08.02.2006<br />
24.07.2006<br />
09.11.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.02.2<strong>01</strong>1<br />
-- 14.12.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 244/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5993 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02147 FAA STC ST02696AT-D GULFSTREAM GV-SP Installation of Passenger Oxygen System This STC is approved only for the product<br />
28.08.2006<br />
CORPORATION<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5995 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02151 FAA STC ST02290CH-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and Aircraft Serial No 5114 Only. 14.12.2006<br />
CORPORATION<br />
Aircraft Completion Aircraft Serial 5114.<br />
10<strong>01</strong>60<strong>04</strong> GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02167 REV. 1 FAA STC ST02796AT-D GV-SP Installation of Board Band Multi-Link System None Prior to installation of this modification it 20.08.2<strong>01</strong>2<br />
CORPORATION<br />
(BBML)Revision of the <strong>EASA</strong> STC<br />
must be determined thatthe<br />
<strong>EASA</strong>.IM.A.S.02167<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
10<strong>01</strong>6009 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6021 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6067 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6073 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6074 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6087 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6122 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6141 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6142 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6143 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6144 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6145 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6162 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.02174 FAA STC ST03238AT-D GULFSTREAM GI-X<br />
Installation of SATCOM (High Speed Data HD-<br />
GULFSTREAM GV-SP<br />
128).<br />
<strong>EASA</strong>.IM.A.S.02187 FAA STC ST03256AT-D GULFSTREAM GIV-X Installation of an Enhanced Surveillance Flight This STC is approved only for the product<br />
Identification System with Collins Radio Tuning configuration as defined in the approved design<br />
Units<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
<strong>EASA</strong>.IM.A.S.02246 FAA STC ST03324AT-D GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial 5127.<br />
Aircraft Serial 5127 Only.The following STC’s<br />
are required to be installed as part of this STC:-<br />
FAA STC ST02696AT-D, <strong>EASA</strong> Approved ref<br />
<strong>EASA</strong>.IM.A.S.02147.FAA STC ST03290AT-D,<br />
<strong>EASA</strong> Approved ref <strong>EASA</strong>.IM.A.S.02255FAA<br />
ST02697AT-D was approved prior to <strong>EASA</strong><br />
unde<br />
<strong>EASA</strong>.IM.A.S.02255 FAA STC ST03290AT-D GULFSTREAM GIV-X<br />
GULFSTREAM GV-SP<br />
Installation of Cabin Window Shades (ATG) None. 23.<strong>01</strong>.2007<br />
<strong>EASA</strong>.IM.A.S.02256 FAA STC ST03351AT-D GULFSTREAM GIV-X Airplane Completion on Aircraft Serial Number Aircraft Serial Number 4060 Only.The following<br />
23.<strong>01</strong>.2007<br />
4060<br />
STC's are a required part of this STC:-<br />
ST02978AT-D, ST02987AT-D, ST03290AT-D,<br />
ST03<strong>04</strong>7AT-D, ST02980AT-D and<br />
ST03027AT-D. It is the Installer's responsibility<br />
to ensure these STC's are all <strong>EASA</strong> approved.<br />
<strong>EASA</strong>.IM.A.S.02274 FAA STC ST64<strong>04</strong>9CH-T GULFSTREAM GV-SP Completion and installation of the custom<br />
interior on Aircraft Serial 5124<br />
<strong>EASA</strong>.IM.A.S.02315 GULFSTREAM GIV-X Airplane Completion on Aircraft Serial Number<br />
4066.<br />
Aircraft Serial 5124 only.The following STCs<br />
are required to be installed as part of this<br />
STC:FAA STC ST02696AT-D, <strong>EASA</strong><br />
approved <strong>EASA</strong>.IM.A.S.02147FAA STC<br />
ST02796AT-D, <strong>EASA</strong> approved<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>259FAA STC ST02<strong>04</strong>7CH-D,<br />
<strong>EASA</strong> approved <strong>EASA</strong>.IM.A.S.02144FAA ST<br />
Aircraft Serial Number 4066 Only.The following<br />
STC’s are a required part of this STC:-<br />
ST02979AT-D, ST02987AT-D, ST03290AT-D,<br />
ST03<strong>04</strong>7AT-D, ST02980AT-D and<br />
ST03027AT-D. It is the installers responsibility<br />
to ensure these STC’s are all <strong>EASA</strong> approved.<br />
<strong>EASA</strong>.IM.A.S.02337 FAA STC ST02883AT-D GULFSTREAM 200 Installation of Transponder Flight ID i.a.w. Index<br />
List CEB1 1268000, Rev. NC or later FAA<br />
approved version,<br />
20.08.2007<br />
<strong>EASA</strong>.IM.A.S.02338 FAA STC ST03358AT-D GULFSTREAM 200 Installation of Universal UNS 1C+ Dual FMS<br />
Software upgrade i.a.w. Index list CEB1<br />
1188000 Rev. B or later approved version.<br />
20.08.2007<br />
<strong>EASA</strong>.IM.A.S.02339 FAA STC ST02872AT-D GULFSTREAM IV Installation of Gables Flight Identification. Compatibility of this design change with<br />
previously approved modifications must be<br />
determined by the installer. If the holder<br />
agrees to permit another person to use this<br />
certificate to alter the product, the holder shall<br />
give the other person written evid<br />
19.10.2007<br />
<strong>EASA</strong>.IM.A.S.02345 REV 1 FAA STC ST02228CH-D GULFSTREAM GIV-X<br />
Installation of the Heads Up Technologies CMS-<br />
10.<strong>01</strong>.2008<br />
GULFSTREAM GV-SP<br />
400 Checklist Management System.<br />
<strong>EASA</strong>.IM.A.S.02346 FAA STC ST<strong>01</strong>931LA-D GULFSTREAM GV-SP Aircraft Serial No. 5139 completion and cabin<br />
interior installation.<br />
GV-SP Serial No. 5139 Only. 14.06.2007<br />
<strong>EASA</strong>.IM.A.S.02385 FAA STC ST02348CH-D GULFSTREAM IV Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 1331.<br />
Aircraft S/N 1331 Only. 31.05.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 245/<strong>462</strong><br />
15.05.2007<br />
15.03.2007<br />
05.02.2007<br />
19.02.2007<br />
28.03.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6187 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02416 US FAA STC NO. ST<strong>01</strong>775LA-D GULFSTREAM GV-SP Installation of an Avionica Inc Miniature Quick<br />
21.06.2007<br />
CORPORATION<br />
Access Data Recorder (Mini QAR)<br />
10<strong>01</strong>6188 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02417 FAA STC ST03409AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and Aircraft Serial Number 40<strong>04</strong> only.The following<br />
09.10.2007<br />
CORPORATION<br />
Aircraft Completion for Aircraft Serial 40<strong>04</strong>. STCs are a required part of this STC:-<br />
ST02979AT-DST02987AT-DST02948AT-DIt is<br />
the installers responsibility to ensure these<br />
STCs are all <strong>EASA</strong> approved.<br />
10<strong>01</strong>62<strong>01</strong> GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6205 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6232 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6233 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6234 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6236 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6245 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6282 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6289 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6322 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6323 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6324 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6325 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6368 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6369 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.02443 FAA STC ST<strong>01</strong>508LA-D GULFSTREAM GV-SP Aircraft S/N 5142 completion and cabin interior GV-SP S/N 5142 only.<br />
installation.<br />
26.07.2007<br />
<strong>EASA</strong>.IM.A.S.02447 FAA STC ST<strong>01</strong>508LA-D GULFSTREAM GV-SP Aircraft S/N 5022 completion and cabin interior GV-SP S/N 5022 only.<br />
installation.<br />
26.07.2007<br />
<strong>EASA</strong>.IM.A.S.02496 FAA STC SA8223SW-D GIV, GV Installation of the Runway Awareness and 1. Applies to models G-IV and GV aircraft<br />
19.07.2007<br />
Advisory System (RAAS) Software for the equipped with Honeywell EGPWS with version -<br />
Honeywell MK V Enhanced Ground Proximity 210-210 or later approved software.2. Prior<br />
Warning System (EGPWS).Installation of the to installation of this modification the installer<br />
Runway Awareness and Advisory System must determine that the interrelationship<br />
(RAAS) Software for the Honeywell MK V<br />
Enhanced Ground<br />
between this modification a<br />
<strong>EASA</strong>.IM.A.S.02497 FAA STC ST03428AT-D GULFSTREAM GV-SP Cabin Interior and Aircraft Completion STC on<br />
Aircraft Serial Number 5150.<br />
<strong>EASA</strong>.IM.A.S.02498 STC ST03414AT-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5153.<br />
<strong>EASA</strong>.IM.A.S.02500 FAA STC ST<strong>01</strong>937LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5151.<br />
<strong>EASA</strong>.IM.A.S.02520 GULFSTREAM GIV-X Aircraft Serial No 4092 completion and cabin<br />
interior installation.<br />
<strong>EASA</strong>.IM.A.S.02577 FAA STC ST03476AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4093.<br />
1. Aircraft Serial Number 5150 only.2. The<br />
following STC's are a required part of this STC:<br />
ST02696AT-D, ST02697AT-D and<br />
ST03290AT-D. It is the installer’s responsibility<br />
to ensure these STC's are all <strong>EASA</strong><br />
approved.3. Prior to installation of this<br />
Aircraft Serial Number 5153 only.The following<br />
STCs are a required part of this STC:-<br />
ST02696AT-DST02697AT-DST03290AT-<br />
DST02715AT-DST02796AT-Dand<br />
ST00892LA.It is the installer responsability to<br />
ensure these STCs are all <strong>EASA</strong> approved.<br />
10.09.2007<br />
09.10.2007<br />
Aircraft Serial Number 5151 only. 09.10.2007<br />
GIV-X Serial No. 4092 Only. 10.<strong>01</strong>.2008<br />
Aircraft Serial Number 4093 only.The following<br />
STCs are a required part of this<br />
STC:ST03027AT-DST03<strong>04</strong>7AT-DST02980AT-<br />
DST02979AT-DST02987AT-DST03290AT-D<br />
<strong>EASA</strong>.IM.A.S.02584 FAA STC ST<strong>01</strong>94LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5162.<br />
Aircraft Serial Number 5162 only. 18.12.2007<br />
<strong>EASA</strong>.IM.A.S.02631 FAA STC ST03533AT-D GULFSTREAM GV-SP Installation of AirCell Axxess II Iridium Satellite Aircraft Serial 5180 and subsequent.<br />
Telephone.<br />
26.05.2008<br />
<strong>EASA</strong>.IM.A.S.02632 FAA STC ST03522AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and 1. Aircraft Serial number 41<strong>04</strong> only;2. The<br />
26.03.2008<br />
Aircraft Completion for Aircraft Serial 41<strong>04</strong>. following STCs are a required part of this STC:-<br />
ST03027AT-D- ST03<strong>04</strong>7AT-D-<br />
ST02980AT-D- ST02979AT-D-<br />
ST02987AT-D- ST03290AT-D-<br />
ST03238AT-D3. It is the installers<br />
responsibility to ens<br />
<strong>EASA</strong>.IM.A.S.02633 FAA STC ST03532AT-D GULFSTREAM GIV-X Installation of AirCell Axxess II Iridium Satellite<br />
Telephone.<br />
05.05.2008<br />
<strong>EASA</strong>.IM.A.S.02634 FAA STC ST02519CH-D GULFSTREAM GV-SP Aircraft Serial No 5176 completion and cabin<br />
interior installation<br />
GV-SP Serial No. 5176 Only 13.05.2008<br />
<strong>EASA</strong>.IM.A.S.02691 FAA STC ST03531AT-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and Prior to installation of this modification the<br />
26.05.2008<br />
Aircraft Completion for Aircraft Serial 5178. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.02692 FAA STC ST03523AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4103.<br />
Aircraft Serial Number 4103 only.The following<br />
STCs are a required part of this<br />
STC:ST03027AT-D,ST02987AT-<br />
D,ST03<strong>04</strong>7AT-D,ST02980AT-D,ST03290AT-<br />
Dand ST02979AT-D.It is the installers<br />
responsibility to ensure these STCs are all<br />
<strong>EASA</strong> approved.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 246/<strong>462</strong><br />
18.12.2007<br />
05.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6370 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02693 FAA STC ST03524AT-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and Aircraft Serial Number 5174 only.The following<br />
07.<strong>04</strong>.2008<br />
CORPORATION<br />
Aircraft Completion for Aircraft Serial 5174. STCs are a required part of this<br />
STC:ST02697AT-D, ST-03290-AT-D,<br />
ST02696AT-D.It is the installers responsibility<br />
to ensure that these STCs are all <strong>EASA</strong><br />
approved.<br />
10<strong>01</strong>6371 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02694 FAA STC ST03525AT-D GULFSTREAM GV-SP Airplane Completion STC on Aricraft Serial Aircraft Serial Number 5167 only.The following<br />
21.<strong>01</strong>.2008<br />
CORPORATION<br />
Number 5167.<br />
STC's are a required part of this STC:<br />
ST02696AT-D<br />
10<strong>01</strong>6372 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02695 FAA STC ST03526AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and Aircraft Serial Number 4099 only.The following<br />
10.<strong>01</strong>.2008<br />
CORPORATION<br />
Aircraft Completion for Aircraft Serial 4099. STCs are a required part of this STC:-<br />
ST03027AT-DST03<strong>04</strong>7AT-DST02980AT-<br />
DST02979AT-DST02987AT-DST03290AT-<br />
D.It is the installers responsibility to ensure<br />
these STCs are all <strong>EASA</strong> approved.<br />
10<strong>01</strong>6373 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6374 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6383 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6391 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6420 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6421 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6439 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6440 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6444 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6498 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>65<strong>04</strong> GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.02696 FAA STC ST03479AT-D GULFSTREAM GV-SP Airplane Completion STC on Aircraft Serial<br />
Number 5166.<br />
<strong>EASA</strong>.IM.A.S.02697 FAA STC NO. ST<strong>01</strong>945LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5172.<br />
<strong>EASA</strong>.IM.A.S.02707 ST02084LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5175.<br />
<strong>EASA</strong>.IM.A.S.02720 FAA STC ST03530AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4106.<br />
<strong>EASA</strong>.IM.A.S.02756 FAA STC ST03543AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4113.<br />
Aircraft Serial Number 5166 only.The following<br />
24.<strong>01</strong>.2008<br />
STC’s are a required part of this<br />
STC:ST02696AT-D,ST02697AT-<br />
D,ST03290AT-D.It is the installers<br />
responsibility to ensure these STC’s are all<br />
<strong>EASA</strong> approved.<br />
Aircraft Serial Number 5172 only. 17.03.2008<br />
Aircraft Serial Number 5175 only. 13.05.2008<br />
Applicable to Aircraft Serial Number 4106<br />
only.The following STCs are required as part of<br />
this STC: FAA STC ST03027AT-D,<br />
ST03<strong>04</strong>7AT-D, ST02980AT-D, ST02979AT-D,<br />
ST02987AT-D, ST03290AT-D, ST03238AT-D.<br />
Aircraft Serial Number 4113 only.The following<br />
STCs are required part of this<br />
STC:ST03027AT-D ST02987AT-D<br />
ST03<strong>04</strong>7AT-D ST02980AT-D ST03290AT-D<br />
ST03532AT-D ST02979AT-D It is the installers<br />
responsibility to ensure these STCs are all<br />
<strong>EASA</strong> approved.Prior to in<br />
<strong>EASA</strong>.IM.A.S.02757 FAA STC ST03410AT-D GULFSTREAM GIV-X Installation of a Aft Lavatory Multiple STC 1. This Aft Lavatory Multiple STC, (FAA ref<br />
ST03410AT-D), does not approve the entire<br />
airplane completion and interior installationand<br />
has the following limitations as defined in<br />
document GC41468<strong>01</strong>45, “Guidance for<br />
Follow on Installation, Aft Lavatory Mult<br />
<strong>EASA</strong>.IM.A.S.02780 FAA STC ST03546AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4115.<br />
<strong>EASA</strong>.IM.A.S.02781 REV. 1 FAA STC ST03535AT-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5177.<br />
<strong>EASA</strong>.IM.A.S.02790 FAA STC ST02085LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5179.<br />
<strong>EASA</strong>.IM.A.S.02860 FAA STC ST02523CH-D GULFSTREAM GV-SP Aircraft Serial No 5186 completion and cabin<br />
interior installation.<br />
<strong>EASA</strong>.IM.A.S.02868 FAA STC ST02092LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5191.<br />
07.<strong>04</strong>.2008<br />
23.05.2008<br />
08.06.2009<br />
Aircraft Serial Number 4115 only.The following<br />
29.05.2008<br />
STC's are a required part of this<br />
STC:ST03027AT-DST02987AT-DST03<strong>04</strong>7AT-<br />
DST02980AT-DST03290AT-DST03532AT-<br />
DST02228CH-DST02979AT-D<br />
Aircraft Serial Number 5177 only.The following<br />
06.10.2<strong>01</strong>0<br />
STC’s are a required part of this<br />
STC:ST02796AT-T,ST02697AT-<br />
D,ST02715AT-D,ST03290AT-D,ST03238AT-<br />
Dand ST02696AT-D.It is the installers’<br />
responsibility to ensure these STC’s are all<br />
<strong>EASA</strong> approved.<br />
Aircraft Serial Number 5179 only. 30.05.2008<br />
1. GV-SP Serial No. 5186 Only2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the air<br />
1. Aircraft Serial Number 5191 only.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previously<br />
installed modification will introduce no adverse<br />
effect upon the air<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 247/<strong>462</strong><br />
29.07.2008<br />
11.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6512 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02879 FAA STC ST02524CH-D GULFSTREAM GIV-X Aircraft completion and cabin interior<br />
1. GIV-X Serial No. 4119 Only;2. Prior to<br />
07.08.2008<br />
CORPORATION<br />
installation Serial No 4119.<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the ai<br />
10<strong>01</strong>6513 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6514 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6515 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6520 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6521 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6534 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6539 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6547 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6548 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6560 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6561 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.02882 FAA STC ST02583CH-D GULFSTREAM GV-SP Aircraft Serial No 5197 completion and cabin<br />
interior installation.<br />
<strong>EASA</strong>.IM.A.S.02884 FAA STC ST03570AT GULFSTREAM 200 Installation of an Auxiliary Power Unit (APU)<br />
Surge Control Valve Modification.<br />
<strong>EASA</strong>.IM.A.S.02886 FAA STC ST02578CH-D GULFSTREAM GV-SP Aircraft Serial No 5189 completion and cabin<br />
interior installation.<br />
<strong>EASA</strong>.IM.A.S.02892 FAA STC ST03565AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4122.<br />
<strong>EASA</strong>.IM.A.S.02893 FAA STC ST03449AT-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5155.<br />
<strong>EASA</strong>.IM.A.S.02911 FAA STC ST03579AT-D GULFSTREAM GIV-X Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 4123.<br />
<strong>EASA</strong>.IM.A.S.02916 FAA STC ST02089LA-D GULFSTREAM GV-SP Installation of Cabin Interior Modification for<br />
Aircraft Serial 5155.<br />
<strong>EASA</strong>.IM.A.S.02926 FAA STC ST02091LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5193.<br />
<strong>EASA</strong>.IM.A.S.02927 FAA STC ST02093LA-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 5198.<br />
<strong>EASA</strong>.IM.A.S.02945 FAA STC ST03587AT-D GULFSTREAM GIV-X Installation of an Airplane Interior for Aircraft<br />
Serial 4130.<br />
<strong>EASA</strong>.IM.A.S.02946 FAA STC ST03592AT-D GULFSTREAM GV-SP Installation of Custom Cabin Interior and<br />
Aircraft Completion for Aircraft Serial 52<strong>01</strong>.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product. The insta<br />
1. GV-SP Serial No. 5189 Only2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworthin<br />
27.10.2008<br />
02.07.2008<br />
17.09.2008<br />
Aircraft Serial Number 4122 only.The following<br />
06.08.2008<br />
STC's are a required part of this<br />
STC:ST03027AT-DST02987AT-DST03<strong>04</strong>7AT-<br />
DST02980AT-DST03290AT-DST03532AT-<br />
DST03238AT-DST02979AT-DIt is the<br />
installer's responsability to ensure these STC's<br />
are all <strong>EASA</strong> approved.<br />
Aircraft Serial Number 5155 only:the following<br />
05.08.2008<br />
STC's are a required part of this<br />
STC:ST02796AT-DST02697AT-DST02715AT-<br />
DST03290AT-DST<strong>01</strong>775LA-DST02696AT-<br />
DST00892LA In addition, this STC must be<br />
installed in conjunction with Cabin Modification<br />
STC ST02089LA-D<br />
1. Aircraft Serial Number 4123 only:2. The<br />
07.08.2008<br />
following STCs are a required part of this STC:-<br />
ST03027AT-D- ST02987AT-D-<br />
ST03<strong>04</strong>7AT-D- ST02980AT-D-<br />
ST03290AT-D- ST03532AT-D-<br />
ST03238AT-D- ST02979AT-DIt is the<br />
installer’s responsibi<br />
Aircraft Serial Number 5155 only. <strong>04</strong>.08.2008<br />
Aircraft Serial Number 5193 only.Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworth<br />
1. Aircraft Serial Number 5198 only.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previously<br />
installed modification will introduce no adverse<br />
effect upon the air<br />
Aircraft Serial Number 4130 only.The following<br />
STCs are a required part of this<br />
STC:ST03027AT-D ST02987AT-D<br />
ST03<strong>04</strong>7AT-D ST02980AT-D ST03290AT-D<br />
ST03532AT-D ST02979AT-D It is the installers<br />
responsibility to ensure these STCs are all<br />
<strong>EASA</strong> approved.Prior to<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 248/<strong>462</strong><br />
02.09.2008<br />
30.09.2008<br />
16.10.2008<br />
<strong>04</strong>.11.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6568 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02959 FAA STC ST03007AT-D GV Installation of Honeywell Integrate Avionics Prior to installation of this modification the<br />
02.10.2008<br />
CORPORATION<br />
Computers (IAC) with Software Version NZ installer must determine that the<br />
6.0.<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6569 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02960 FAA STC ST03074AT-D GV Installation of Honeywell NZ-2000 Third FMS Prior to installation of this modification the<br />
02.10.2008<br />
CORPORATION<br />
Computer with Software Version NZ 6.0. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6596 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.03007 FAA STC ST03610AT-D GULFSTREAM G550<br />
Installation of Custom Cabin Interior and Prior to installation of this modification the<br />
24.11.2008<br />
CORPORATION<br />
GULFSTREAM GV-SP<br />
Aircraft Completion for Aircraft Serial 52<strong>04</strong>. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6597 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6602 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6607 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6608 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6613 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6621 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6639 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6650 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.03009 FAA STC ST03511AT-D GULFSTREAM G150 Installation of Concorde Valve Regulated Lead None.<br />
Acid Main Batteries.<br />
18.02.2009<br />
<strong>EASA</strong>.IM.A.S.03<strong>01</strong>6 FAA STC ST02097LA-D GULFSTREAM G550 Installation of Custom Cabin Interior and 1. Aircraft Serial Number 5203 only.2. Prior<br />
02.12.2008<br />
Aircraft Completion for Aircraft Serial 5203. to installation of this modification the installer<br />
must determine that the interrelationship<br />
between this modification and any other<br />
previously installed modification will introduce<br />
no adverse effect upon<br />
<strong>EASA</strong>.IM.A.S.03024 FAA STC ST03617AT-D GULFSTREAM GIV-X Installation of Export Modifications for Aircraft<br />
Serial 4091.<br />
<strong>EASA</strong>.IM.A.S.03025 FAA STC ST03477AT-D GULFSTREAM GIV-X Airplane Completion and Custom Cabin<br />
Installation for Aircraft Serial 4091.<br />
<strong>EASA</strong>.IM.A.S.03038 FAA STC ST03643AT-D GULFSTREAM GV-SP Aircraft completion and Installation of Airplane<br />
Interior for Aircraft Serial 5210.<br />
<strong>EASA</strong>.IM.A.S.03052 FAA STC ST02632CH-D GULFSTREAM GV-SP Aircraft completion and cabin interior<br />
installation for Serial No 5212.<br />
<strong>EASA</strong>.IM.A.S.03079 FAA FAA STC ST6870CH-T GULFSTREAM GV-SP Aircraft Serial No 5220 completion and cabin<br />
interior installation.<br />
<strong>EASA</strong>.IM.A.S.03095 FAA STC ST03542AT-D GULFSTREAM GIV-X Installation of an Aft Galley/Galley Annex<br />
Multiple STC.<br />
1. Aircraft Serial Number 4091 only.2. This<br />
STC must be installed in conjunction with<br />
Airplane Completion STC ST03477AT-D<br />
(<strong>EASA</strong>.IM.A.S.03025) to fully meet <strong>EASA</strong><br />
requirements. 3. It is the installers’<br />
responsibility to ensure these STC’s are all<br />
<strong>EASA</strong> approv<br />
Aircraft Serial Number 4091 only.The following<br />
STCs are a required part of this<br />
STC:ST03027AT-D ST02987AT-D<br />
ST03<strong>04</strong>7AT-D ST02980AT-D ST03290AT-D<br />
ST02979AT-D ST00892LA Additionally, this<br />
STC must be installed in conjunction with<br />
Export Modification STC ST036<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. Serial No. 5212 Only2. Prior to installation of<br />
this modification the installer must determine<br />
that the interrelationship between this<br />
modification andany other previously installed<br />
modification will introduce no adverse effect<br />
upon the airworthiness of<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. This Aft Galley/Galley Annex Multiple STC,<br />
(FAA ref ST03542AT-D), does not approve the<br />
entire airplane interior installation andhas the<br />
following limitations as defined in document<br />
GC415400266.“Guidance for Follow on<br />
Installation, Aft Galley/Galley Anne<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 249/<strong>462</strong><br />
15.10.2008<br />
15.10.2008<br />
08.<strong>01</strong>.2009<br />
02.03.2009<br />
08.<strong>04</strong>.2009<br />
10.06.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6666 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.03139 FAA STC ST03668AT-D GULFSTREAM GIV-X Installation of an Airplane Interior and Prior to installation of this modification the<br />
07.<strong>04</strong>.2009<br />
CORPORATION<br />
completion for Aircraft Serial 4148.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6678 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6679 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6680 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>6681 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10027065 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10027320 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10027731 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10028267 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10028488 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10028505 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10028642 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.032<strong>01</strong> REV. 1 FAA STC ST03646AT-D GIV-X Installation of Cabin/Baggage Compartment This Cabin/Baggage Compartment Multiple<br />
STC, (FAA ref ST03646AT-D), doesnot<br />
approve the entire airplane interior installation<br />
and has thefollowing limitations as defined in<br />
<strong>EASA</strong>.IM.A.S.03202 REV. 1 FAA STC ST03648AT-D GIV-X Installation of Cabin/Baggage Compartment<br />
(AG)<br />
document GC422<strong>04</strong>02<strong>04</strong>, "Guidance forFollow<br />
on Installation, Cabin/Baggage Compartmen<br />
This Cabin/Baggage Compartment Multiple<br />
STC, (FAA ref ST03648AT-D), doesnot<br />
approve the entire airplane interior installation<br />
and has thefollowing limitations as defined in<br />
document GC422<strong>04</strong>0205, "Guidance forFollow<br />
on Installation, Cabin/Baggage Compartmen<br />
<strong>EASA</strong>.IM.A.S.03203 FAA STC ST03647AT-D GIV-X Installation of a Forward Galley-Vestibule Area- 1. The Forward Galley-Vestibule Area-Forward<br />
Forward Lavatory-Flight Deck Multiple STC Lavatory-Flight Deck Multiple STC, (FAA ref<br />
ST03647AT-D), does not approve the entire<br />
airplane completion and interior installation and<br />
has the following limitations as defined in<br />
document GC421<strong>04</strong>0<strong>01</strong>9, “Guidance<br />
<strong>EASA</strong>.IM.A.S.032<strong>04</strong> FAA STC ST03649AT-D GULFSTREAM GIV-X Installation of a Flight Deck-Forward Vestibule-<br />
Forward Lavatory Multiple STC<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03148<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03251<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03254<br />
P-<br />
<strong>EASA</strong>.IM.A.S.02713<br />
GV-SP (G550) Installation of Custom Cabin Interior and<br />
Aircraft Completion forAircraft Serial 5224.<br />
FAA STC ST03710AT-D GULFSTREAM GIV-X Installation of an Airplane Interior and<br />
completion for Aircraft SerialNumber 4161.<br />
1. This Flight Deck-Forward Vestibule-Forward<br />
Lavatory Multiple STC, (FAA ref ST03649AT-<br />
D), does not approve the entire airplane<br />
completion and interior installation and has the<br />
following limitations as defined in document<br />
GC421<strong>04</strong>0020“Guidance for Follow o<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.02.2<strong>01</strong>2<br />
08.02.2<strong>01</strong>2<br />
08.06.2009<br />
10.06.2009<br />
Aircraft Serial Number 5224 only. Prior to installation of this modification the 03.09.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
Aircraft Serial Number 4161 only. The following The installer must determine whether this 21.09.2009<br />
STCs are a required partof this STC: design change is compatiblewith<br />
ST02987AT-D, ST03290AT-D, ST02979AT-D,<br />
ST03410AT-D andST03647AT-D.It is the<br />
installer's responsibility to check these STC’s<br />
are <strong>EASA</strong>Approved.<br />
previously approved modifications. If the<br />
holder agrees to permitanother person to<br />
use this certificate to alter the product,<br />
the holdershall give the other person<br />
FAA STC ST02705CH-D GV-SP Aircraft Serial No 5240 completion and cabin<br />
interior installation.<br />
GV-SP Serial No. 5240 Only.<br />
written evidence o<br />
None. 26.10.2009<br />
FAA STC ST03740AT-D GV-SP Aircraft Serial No 5246 completion and cabin<br />
interior installation.<br />
GV-SP Serial No. 5246 Only. None 14.12.2009<br />
REV. 1 FAA STC ST03699AT GULFSTREAM 150 G150 Steep Approach Landing None None 27.<strong>01</strong>.2<strong>01</strong>0<br />
FAA STC NO. ST03746AT-D GV-SP Completion and Installation of an Airplane<br />
Interior for Aircraft Serial5242.<br />
REV. 1 FAA STC ST03739AT-D G150 Installation of an International Communications<br />
Group (ICG). Inc.NxtMail Server<br />
Aircraft Serial Number 5242 only. The following STCs are a required part of<br />
this STC: ST02696AT-D ST02697AT-D<br />
ST02715AT-D ST02796AT-D<br />
ST03290AT-D ST03533AT-D<br />
ST03737AT-D ST00892LA It is the<br />
installers responsibility to ensure these<br />
STCs are all <strong>EASA</strong>approved. Prior to<br />
installation of this<br />
Installation of Cabin Interior STC<br />
<strong>EASA</strong>.IM.A.S.02543 (FAA STCST10316SC-<br />
D) is required prior to installation of this NxtMail<br />
Serverarrangement.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 250/<strong>462</strong><br />
18.<strong>01</strong>.2<strong>01</strong>0<br />
<strong>01</strong>.02.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029061 GULFSTREAM AEROSPACE<br />
REV. 1 FAA STC ST03752AT-D GIV-X Aircraft completion and installation of an This approval is limited to S/N 4180 only.The Not applicable 11.06.2<strong>01</strong>0<br />
CORPORATION<br />
Airplane Interior, S/N 4180<br />
following STC's are required part of this<br />
STC:ST02979AT-D, ST02980AT-D,<br />
ST02987AT-D, ST03027AT-D, ST03<strong>04</strong>7AT-<br />
D,ST03290AT-D, ST03410AT-D, ST03532AT-<br />
D, and ST03647AT-D.It is he installers<br />
responsibility to ensure<br />
10029212 GULFSTREAM AEROSPACE<br />
REV. 1 FAA STC ST03738AT-D GIV-X, GV-SP Installation of Fwd & Aft Lavatory Smoke None Prior to installation of this modification it 10.05.2<strong>01</strong>2<br />
CORPORATION<br />
Detectors.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
10029213 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10030647 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10030690 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10030691 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10031140 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10031982 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10031983 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10031985 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032074 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
FAA STC ST03667AT-D GULFSTREAM GV-SP, GIV-X Installation of a Generation 3, Broad Band Multi- The installer must determine whether this None. 12.03.2<strong>01</strong>0<br />
Link (BBML) System.<br />
design change is compatiblewith previously<br />
approved modifications. If the holder agrees to<br />
permitanother person to use this certificate to<br />
alter the product, the holdershall give the other<br />
person written evidence o<br />
FAA STC ST03731AT-D GIV-X Installation of an Audio Video Distribution None. The installer must determine whether this 29.06.2<strong>01</strong>0<br />
System<br />
design change is compatiblewith<br />
previously approved modifications. If the<br />
holder agrees to permitanother person to<br />
use this certificate to alter the product,<br />
the holdershall give the other person<br />
written evidence o<br />
FAA STC REF ST03737AT-D GIV-X AND GV-SP Installation of a Honeywell/EMS HD-710 Not Applicable The installer must determine whether this 02.07.2<strong>01</strong>0<br />
combined SATCOM Swift BroadbandHigh<br />
design change is compatiblewith<br />
Speed Data System.<br />
previously approved modifications.<br />
P-<br />
FAA STC REF ST03685AT-D GV-SP (G550) Installation of Flight Crew Sleeping Facilities. Not Applicable The installer must determine whether this 02.07.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.A.S.03225<br />
design change is compatiblewith<br />
previously approved modifications.<br />
<strong>EASA</strong>.IM.A.S.02821 FAA STC ST03713-AT G150 Installation of Enhanced Vision System (EVS) II This approval does not constitute any operation none<br />
credit<br />
28.07.2<strong>01</strong>0<br />
FAA STC ST02525CH-D GULFSTREAM GV-SP (G 550) Installation of an Aft Lavatory Compartment. none The following STC is a required part of<br />
the -505 or -507<br />
Configuration:ST02696AT-D (Passenger<br />
Oxygen), it is the installers responsibility<br />
toensure this STC is <strong>EASA</strong><br />
Approved.Subsequent Installations of the -<br />
505 or -507 Configurations require<br />
themodifier to<br />
29.09.2<strong>01</strong>0<br />
REV. 1 FAA STC ST03743AT-D GV-SP Installation of an 18 Passenger Aircraft Cabin None The installer must follow the instructions 23.02.2<strong>01</strong>2<br />
Compartment.<br />
contained in the Guidance forFollow-On<br />
Installation, Aircraft Cabin Compartment<br />
GC52200F003 Rev - ,dated November<br />
19, 2009, or later approved<br />
revisions.Prior to installation of this<br />
modification it must be determi<br />
FAA STC ST02190LA-D GULFSTREAM GV-SP (G 550) Installation of the Forward Vestibule<br />
Compartment.<br />
REV. 1 FAA STC ST<strong>04</strong>2<strong>04</strong>AT-D GV-SP Installation of the Aircraft Cabin Compartment<br />
for Gulfstream GV-SPSerial Number 5284.<br />
none Subsequent Installations must follow the<br />
instructions contained in theGuidance for<br />
Follow-On Installations, Fwd Vestibule<br />
Compartment RefGC52200F000, Rev -<br />
dated July 2, 2009.Prior to installation of<br />
this modification it must be determined<br />
thatthe interre<br />
29.09.2<strong>01</strong>0<br />
Aircraft Serial Number 5284 Only. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 251/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032075 GULFSTREAM AEROSPACE<br />
REV. 1 FAA STC NO. ST03793AT-D GULFSTREAM GV-SP Installation of an Airplane Interior for aircraft This approval is limited to only the installation Prior to installation of this modification it 06.10.2<strong>01</strong>0<br />
CORPORATION<br />
S/N 5277<br />
made in Gulfstream,GV-SP, A/C 5277The must be determined thatthe<br />
following STC’s are a required part of this interrelationship between this modification<br />
STC:ST02696AT-D, ST02697AT-D,<br />
and any other previouslyinstalled<br />
ST03533AT-D, ST02796AT-D, ST02715AT-D, modification and/ or repair will introduce<br />
andST03290AT-DIt is the installers<br />
no adverse effectupon the airworthiness<br />
responsibility to en<br />
of the product.<br />
10032076 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032077 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032086 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032609 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032631 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032651 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10032980 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10033988 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
REV. 1 FAA STC ST02292CH-D GV-SP Installation of the 115V AC/60Hz Outlets<br />
Multiple STC for GulfstreamGV-SP model<br />
aircraft.<br />
REV. 1 FAA STC ST03794AT-D GV-SP Installation of the Aircraft Cabin Compartment<br />
for Gulfstream GV-SPmodel aircraft.<br />
REV. 1 FAA STC ST03759AT-D GV-SP Installation of the Audio Video Distribution<br />
System (AVDS) Multiple STCfor Gulfstream<br />
GV-SP model aircraft.<br />
FAA STC ST<strong>04</strong>209AT-D GIV-X Aircraft Completion and Installation of an<br />
Airplane Interior<br />
FAA STC ST<strong>04</strong>213AT-D GIV-X Aircraft Completion and Installation of Airplane<br />
Interior.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.02.2<strong>01</strong>2<br />
You may not use descriptive data about this The following STCs are a required part of<br />
design change to duplicateto other<br />
this STC: ST02979AT-D,ST02980AT-D,<br />
products.This approval is limited to aircraft ST02987AT-D, ST03027AT-D,<br />
Serial 4200.This STC does not permit ST03<strong>04</strong>7AT-D, ST03290ATmanufacturing<br />
of parts for multipleinstallations. D,ST03410AT-D, ST03532AT-D,<br />
ST03742AT-D and ST03647AT-D.Prior<br />
to installation of this modification it must<br />
be determined thatthe i<br />
You cannot use descriptive data about this<br />
design change to duplicate toother<br />
,,products.This approval is limited to<br />
Gulfstream GIV-X, Serial 4202.This STC does<br />
not permit manufacturing of parts for<br />
multipleinstallations.<br />
The following STC's are a required part<br />
of this STC: ST02979AT-D,<br />
,,ST02980AT-D, ST02987AT-D,<br />
ST03027AT-D, ST03<strong>04</strong>7AT-D,<br />
ST03290AT-D, ST03410AT-D,<br />
ST03532AT-D, ST03646AT-D,<br />
ST03647AT-D, andST03737AT-D.It is<br />
the installers responsibility to ensure the<br />
FAA STC ST03742AT-D GIV-X Installation of a Cabin/Baggage Compartment. None<br />
above<br />
Follow-On Installation Guide<br />
GC422<strong>04</strong>0214, Revision A, dated<br />
November <strong>01</strong>,2<strong>01</strong>0, or later FAA<br />
approved revision is to be used for<br />
subsequentinstallations. Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this<br />
19.11.2<strong>01</strong>0<br />
FAA STC ST<strong>04</strong>215AT-D GIV-X Aircraft Completion and Installation of an You cannot use descriptive data about this The following STCs are a required part of 13.12.2<strong>01</strong>0<br />
Airplane Interior on AircraftSerial 4203. design change to duplicateother products. This this STC: ST03542AT-D,ST02<strong>04</strong>9CH-D,<br />
approval is limited to only the installation ST02979AT-D, ST02980AT-D,<br />
madein Gulfstream GIV-X, A/C 4203. This ST02987AT-D, ST03027AT-<br />
STC does not permit manufacturing ofparts for D,ST03<strong>04</strong>7AT-D, ST03290AT-D,<br />
multiple installations.<br />
ST03410AT-D, ST03532AT-D,<br />
ST03648AT-D andST03649AT-D.It is the<br />
installers responsibility to ensure the<br />
FAA STC ST<strong>04</strong>225AT-D GV-SP Aircraft Serial No 5302 completion and cabin<br />
interior installation<br />
17.11.2<strong>01</strong>0<br />
18.11.2<strong>01</strong>0<br />
GV-SP Serial No. 5302 Only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.02.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 252/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10033989 GULFSTREAM AEROSPACE<br />
REV. 1 FAA STC ST<strong>04</strong>221AT-D GV-SP Aircraft Serial No 5294 completion and cabin GV-SP Serial No. 5294 Only Prior to installation of this modification it <strong>04</strong>.03.2<strong>01</strong>1<br />
CORPORATION<br />
interior installation<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035124 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10035125 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10035279 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10035421 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10037106 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10038524 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10038629 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10038724 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
FAA STC ST03070AT GIV-X Installation of a Honeywell LSZ-860 Lightning<br />
Sensor System.<br />
FAA STC ST03566AT-D GIV-X Installation of a Custom Cabin Interior and<br />
completion of AircraftSerial Number 4121.<br />
FAA STC ST03795AT-D GV-SP Aircraft Completion and Installation of an<br />
Airplane Interior<br />
FAA STC NO. ST<strong>04</strong>238AT-D GV-SP (G550) Installation of Cabin Interior and Aircraft<br />
Completion for GulfstreamGV-SP model<br />
Aircraft<br />
This approval should not be extended to other<br />
aircraft of this model onwhich other previously<br />
approved modifications are incorporated,<br />
unlessit is determined by the installer that the<br />
interrelationship betweenthis change and any<br />
other previously approved m<br />
Prior to installation of this modification it 27.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
You cannot use descriptive data about this The following STCs are a required part of<br />
design change to duplicateother products. This this STC: ST02979AT-D,ST02987AT-D<br />
approval is limited to only the installation and ST03290AT-D. It is the installers<br />
madein Gulfstream GIV-X, A/C 4121. This responsibility toensure these STC's are<br />
STC does not permit manufacturing ofparts for <strong>EASA</strong> approved prior to installation.Prior<br />
multiple installations.<br />
to installation of this modification it must<br />
be determined t<br />
The installer must determine whether this<br />
design change is compatiblewith previously<br />
approved modifications.If the holder agrees to<br />
permit another person to use this certificate<br />
toalter the product, the holder shall give the<br />
other person writtenevidence of<br />
Guidance for Follow on Installation,<br />
GC522<strong>04</strong>0598, Revision -,<br />
dated09/16/10, or later approved<br />
revision, is to be used for<br />
subsequentinstallations.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
27.05.2<strong>01</strong>1<br />
10.06.2<strong>01</strong>1<br />
between this modif<br />
None The following STC's are required as part 21.06.2<strong>01</strong>1<br />
of this STC: ST02696AT-D,ST02697AT-<br />
D, ST03290AT-d and ST02292CH-D, it<br />
is the installersresponsibility to ensure<br />
these STC's are <strong>EASA</strong> approved.Prior to<br />
installation of this modification it must be<br />
determined thatthe<br />
FAA STC ST<strong>04</strong>244AT-D GULFSTREAM GV-SP Executive Aircraft Completion, Multiple STC. None 1. The following STCs are a required part<br />
of this STC:--ST02696AT-D (Passenger<br />
Oxygen)-ST02697AT-D (Interior<br />
Emergency Lights)-ST03290AT-D<br />
(Electric Window Shades)-It is the<br />
installer’s responsibility to ensure the<br />
above referencedSTC’s are <strong>EASA</strong><br />
approved p<br />
FAA STC ST03784AT-D GV-SP Installation of an Audio Video Distribution<br />
System<br />
REV. 2 FAA STC ST<strong>04</strong>251AT-D GULFSTREAM GV-SP Installation of an Executive Completion -<br />
Multiple STC<br />
1. The installer must determine whether this<br />
design change Is compatiblewith previously<br />
approved modifications.2. If the holder agrees<br />
to permit another person to alter the<br />
product,the holder must give the other person<br />
written evidence of thatpermission.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
03.11.2<strong>01</strong>1<br />
23.02.2<strong>01</strong>2<br />
This Executive Completion, Multiple STC, (FAA Prior to installation of this modification it<br />
ref ST<strong>04</strong>251AT-D), does notapprove the entire must be determined thatthe<br />
23.03.2<strong>01</strong>2<br />
airplane interior installation and has the interrelationship between this modification<br />
followinglimitations as defined in document and any other previouslyinstalled<br />
GC522<strong>04</strong>3<strong>04</strong>6, "Guidance for Follow- modification and/ or repair will introduce<br />
OnInstallation, Executive Completion Multipl no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC ST03686AT-D GV-SP Installation of an Airplane Cabin Interior. 1. The approved <strong>EASA</strong> Configurations and the Prior to installation of this modification it 09.03.2<strong>01</strong>2<br />
compatible <strong>EASA</strong> exportoption are defined in must be determined thatthe<br />
GC522<strong>04</strong>0616, "<strong>EASA</strong> Validated Configuration interrelationship between this modification<br />
Lists", Revision "-", dated 03/02/12 or and any other previouslyinstalled<br />
later approved revisions.2. Follow-On modification and/ or repair will introduce<br />
Installation Guide GC522<strong>04</strong>0565, Revision no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 253/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0608 GULFSTREAM AEROSPACE<br />
FAA STC ST03779AT-D GIV-X Installation of an AirCell High Speed Internet <strong>EASA</strong> STC number <strong>EASA</strong>.IM.A.S.02633 is Prior to installation of this modification it 13.07.2<strong>01</strong>2<br />
CORPORATION<br />
System<br />
required for installation of thisSTC<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0627 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>1062 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>1063 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>11<strong>01</strong> GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>1234 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>1649 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>1900 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>2374 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
FAA STC ST00803LA-D GV Installation of Satcom Antenna (Racal). None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
16.07.2<strong>01</strong>2<br />
FAA STC ST03771AT-D GV-SP Installation of an Airplane Interior Limitations are defined in document<br />
Prior to installation of this modification it 20.08.2<strong>01</strong>2<br />
GC522<strong>04</strong>0593, "Follow-On InstallationGuide", must be determined thatthe<br />
Revision NC, dated May 5, 2<strong>01</strong><strong>01</strong>. The installer interrelationship between this modification<br />
must determine whether this design change is and any other previouslyinstalled<br />
compatiblewith previously approved<br />
modification and/ or repair will introduce<br />
modifications.2. If the holder agrees to permit a no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC ST02884AT-D GV Installation of a Transponder Flight<br />
Identification<br />
FAA STC ST<strong>04</strong>263AT-D GV-SP Executive Completion, Multiple STC. Limitations are defined in document<br />
GC522<strong>04</strong>3055, "Follow-On InstallationGuide",<br />
Revision NC, dated August 7, 2<strong>01</strong>2 1.,,The<br />
installer must determine whether this design<br />
change iscompatible with previously approved<br />
modifications.2.,,If the holder agrees to pe<br />
FAA STC ST<strong>01</strong>105LA-D GV Installation of a 13 Passenger Cabin Interior The approval of this modification applied only<br />
to Model GV S/N 622<br />
FAA STC ST<strong>01</strong>822AT-D GV AND GV-SP Installation of APU Fire Bottle 1- The installer must determine whether this<br />
design change is compatiblewith previously<br />
approved modifications2- If the holder agrees<br />
to permit another person to alter the<br />
product,the holder must give the other person<br />
written evidence of thatpermission.<br />
REV. 1 FAA STC ST00673LA-D GV Installation of Honeywell TCAS 2000 TCAS II<br />
System<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
20.08.2<strong>01</strong>2<br />
Prior to installation of this modification it 21.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 31.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
Prior to installation of this modification it <strong>04</strong>.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
23.10.2<strong>01</strong>2<br />
FAA STC ST<strong>01</strong>751LA-D GV-SP Installation of EROS Convertible MLD20 Series None Prior to installation of this modification it 28.11.2<strong>01</strong>2<br />
Crew Oxygen Mask -Regulator with<br />
must be determined thatthe<br />
Detachable Smoke Goggles<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 254/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2377 GULFSTREAM AEROSPACE<br />
FAA STC ST<strong>01</strong>957CH-D GV, GV-SP Installation of an Airshow RF/IF Remote None If the holder agrees to permit another 28.11.2<strong>01</strong>2<br />
CORPORATION<br />
Controller<br />
person to alter the product, theholder<br />
must give the other person written<br />
evidence of that permission.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modificatio<br />
10<strong>04</strong>2407 GULFSTREAM AEROSPACE<br />
FAA STC ST02518CH-D GV-SP Installation of a 16 Passenger Corporate This STC approval is limited to the installation JAR 25 Modifications: To meet <strong>EASA</strong> 29.11.2<strong>01</strong>2<br />
CORPORATION<br />
Aircraft Interior<br />
in GV-SP Serial NumberSN 5171<br />
Type Certificate DataSheet requirements,<br />
the following design changes are<br />
required:.Ashtrays to be installed in the<br />
interior of the lavatories, in additionto the<br />
ashtrays on the entry side of lavatories.<br />
(JAR §25.853(e))-<br />
10<strong>04</strong>2618 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>04</strong>2689 GULFSTREAM AEROSPACE<br />
CORPORATION<br />
10<strong>01</strong>5351 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5593 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5595 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5596 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5597 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5598 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5965 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5966 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>5994 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
FAA STC ST<strong>04</strong>280AT-D GV-SP Installation of an Executive Completion 1. The installer must determine whether this<br />
design change is compatiblewith previously<br />
approved modifications.2. If the holder agrees<br />
to permit another person to use this<br />
certificateto alter the product, the holder shall<br />
give the other person writtenevide<br />
FAA STC ST<strong>04</strong>249AT-D G350 AND G450 Installation of a Cabin Interior and Airplane<br />
Completion.<br />
<strong>EASA</strong>.IM.A.S.00567 REV. 1 FAA STC ST10<strong>01</strong>6SC-D GULFSTREAM 200 Installation of BE Single (light weight) Seats<br />
Arrangement.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>506 FAA STC ST399CH BOMBARDIER CL-600-2B16 Installation of a Honeywell FMZ-2000 Flight<br />
Management System<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>508 FAA STC SA589GL BOMBARDIER CL-600-2B16 Installation of Passenger Oxygen System and<br />
Modification of Crew Oxygen System<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>509 FAA STC SA3716SW BOMBARDIER CL-600-2B16 Installation of a baggage compartment smoke<br />
detector system<br />
1. The installer must determine whether this<br />
design change is compatiblewith previously<br />
approved modifications.2. The instructions<br />
contained in the Guidance for Follow-On<br />
Installation, GC422<strong>04</strong>0227, Revision A,<br />
dated January 19, 2<strong>01</strong>2 or later FAA appr<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Canadair Part Numbers 600-34<strong>01</strong>2-73,<br />
located at B.L.6 06, and 600-34<strong>01</strong>2-71,<br />
located at B.L.13, 73, must be replaced if any<br />
cracksare detected during the inspections<br />
required at intervals of 1000 take-off/landing<br />
cycles with this modification installed2.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>510 FAA STC SA4372SW BOMBARDIER CL-600-2B16 Installation of an emergency lighting system This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>511 FAA STC SA8353SW BOMBARDIER CL-600-2B16 Installation of a Loral F-1000 Flight Data<br />
Recorder<br />
<strong>EASA</strong>.IM.A.S.02114 FAA STC ST09639SC GULFSTREAM 200 Installation of an Allied Signal DFDR i.a.w.<br />
MDL30-11000007<br />
<strong>EASA</strong>.IM.A.S.02115 FAA STC ST09945SC GULFSTREAM 200 Installation of Lead Acid Batteries i.a.w. MDL30-<br />
1100<strong>01</strong>4<br />
<strong>EASA</strong>.IM.A.S.02148 FAA STC ST03270AT-D GULFSTREAM 200 Installation of a proective shroud around the<br />
60Hz inverter<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
For subsequent installations of this STC, 11.12.2<strong>01</strong>2<br />
the instructions contained indocument<br />
GC522<strong>04</strong>3062, Rev. -, dated 12th<br />
November 2<strong>01</strong>2, "Guidance forFollow-On<br />
Installation, Executive Completion" must<br />
be followed.<br />
The approved <strong>EASA</strong> Configurations and 13.12.2<strong>01</strong>2<br />
the compatible <strong>EASA</strong> export optionare<br />
defined in GC422<strong>04</strong>0234, "<strong>EASA</strong><br />
Validated Configuration ListsST<strong>04</strong>249AT-<br />
D", Revision "-", dated December 03,<br />
2<strong>01</strong>2 or later approvedrevision.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 255/<strong>462</strong><br />
<strong>04</strong>.12.2008<br />
12.09.2005<br />
12.09.2005<br />
12.09.2005<br />
12.09.2005<br />
12.09.2005<br />
16.10.2006<br />
16.10.2006<br />
21.11.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6138 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02334 REV. 1 FAA STC ST02873AT-D GULFSTREAM 200 Installation of a Runway Awareness and 1. Prior to installation of this modification the<br />
<strong>04</strong>.03.2009<br />
CORPORATION.<br />
Advisory System i.a.w. Index List CEB1 installer must determine that the<br />
3498000.Note: This Revision corrects a typo in interrelationship between this modification and<br />
the Original Product Type Certificate Number. any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6182 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02411 FAA STC ST10021SC GULFSTREAM 200 Installation of an executive cabin interior on This approval is limited to Gulfstream G200<br />
15.08.2007<br />
CORPORATION.<br />
Gulfstream 200 S/N 065 including<br />
miscellaneous mechanical and electrical<br />
modifications to S/N 065.<br />
S/N 065 only.<br />
10<strong>01</strong>6229 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
<strong>EASA</strong>.IM.A.S.02485 FAA STC ST10314SC-D GULFSTREAM G500 Installation of a Satcom Antenna. 09.10.2007<br />
10<strong>01</strong>6263 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02543 FAA STC ST10316SC-D GULFSTREAM G150 Installation of an Executive cabin interior in Installation of this STC requires incorporation<br />
10.12.2007<br />
CORPORATION.<br />
accordance with Gulfstream Index List of1) STC ST10314SC-D Installatio of<br />
GA322<strong>04</strong>8000, Rev "-" dated 14 August 2006 ICG/Iridium Stacom Antenna,2) When optional<br />
or later FAA approved revision.<br />
XM radiosystem is installed, XM Antenna<br />
installation is required per STC ST 10313SC-D<br />
(both have to be <strong>EASA</strong> validated). The comp<br />
10<strong>01</strong>6264 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6265 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6266 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6267 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6268 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6308 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6309 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6334 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6336 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6346 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6364 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6365 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6406 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6486 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6487 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
<strong>EASA</strong>.IM.A.S.02544 FAA STC ST10317SC-D GULFSTREAM G150 Installation of a Collins IFIS 5000 EFB System. 10.10.2007<br />
<strong>EASA</strong>.IM.A.S.02545 FAA STC ST10321SC-D GULFSTREAM G150 Installation of a WX-1000 Stormscope 09.10.2007<br />
<strong>EASA</strong>.IM.A.S.02547 FAA STC ST10327SC-D GULFSTREAM G150 Installation of a Collins DBU 5000 System. 09.10.2007<br />
<strong>EASA</strong>.IM.A.S.02548 FAA STC ST10324SC-D GULFSTREAM G150 Installation of a second ADF. 05.12.2007<br />
<strong>EASA</strong>.IM.A.S.02549 FAA STC ST10326SC-D GULFSTREAM G150 Installation of a Honeywell FDR. 09.10.2007<br />
<strong>EASA</strong>.IM.A.S.02610 FAA STC ST10312SC-D Installation of a VHF COM Antenna. 22.11.2007<br />
<strong>EASA</strong>.IM.A.S.02611 FAA STC ST10315SC-D GULFSTREAM G150 Installation of a 3rd VHF COM with Data link. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.02643 FAA STC ST09823SC-D GULFSTREAM 200 Installation of Dual UNS 1C + upgraded FMS<br />
i.a.w. Index List CEB111880<strong>01</strong><br />
<strong>EASA</strong>.IM.A.S.02645 FAA STC ST10329SC-D GULFSTREAM 200 Installation of a forward RH Galley with a<br />
convertible high Temp Oven/Microwave Oven<br />
Configuration.<br />
1. For A/C S/N0<strong>04</strong> through 051 only.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon t<br />
A prerequisite to the convertible Oven<br />
confirguration is the installation of the Galley<br />
Multiple STC ST103<strong>04</strong>SC-D; installation limited<br />
to Gulfstream G200, S/N 163 only.<br />
<strong>EASA</strong>.IM.A.S.02663 FAA STC ST10313SC-D Installation of an XM Antenna. 05.02.2008<br />
<strong>EASA</strong>.IM.A.S.02686 FAA STC ST10319SC-D Installation of Laserref V IRS. 25.03.2008<br />
<strong>EASA</strong>.IM.A.S.02687 FAA STC ST10320SC-D Installation of 115 cubic foot oxygen cylinder in<br />
accordance with Index list GA327088000, Rev<br />
B, dated 15.09.2006 or later revisions of the<br />
above listed documents approved by <strong>EASA</strong> in<br />
accordance with <strong>EASA</strong> ED Decision<br />
2007/<strong>04</strong>/CF (or subsequent revisions of t<br />
<strong>EASA</strong>.IM.A.S.02735 FAA STC ST10334SC-D Installation of a Lavatory Smoke Detection<br />
system.<br />
<strong>EASA</strong>.IM.A.S.02842 FAA STC ST10296SC-D GULFSTREAM 200 Installation of a Cabin interior G-200, S/N 102, The compatibility of this<br />
design change with previously approved<br />
modifications must be determined by the<br />
installer .<br />
<strong>EASA</strong>.IM.A.S.02843 FAA STC ST10295SC-D GULFSTREAM 200 Installation of a 3rd FMS 6100 Flight<br />
Prior to installation of this modification the<br />
Management System i.a.w.Index List installer must determine that the<br />
GA213188000, Rev C or later revisions of the interrelationship between this modification and<br />
above listed documents approved by <strong>EASA</strong> in any other previously installed modification will<br />
accordance with <strong>EASA</strong> ED Decision<br />
introduce no adverse effect upon the<br />
20<strong>04</strong>/<strong>04</strong>/CF (or subsequent revisions of this<br />
decision).<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 256/<strong>462</strong><br />
22.11.2007<br />
18.12.2007<br />
17.<strong>04</strong>.2008<br />
07.<strong>04</strong>.2008<br />
18.03.2008<br />
08.07.2008<br />
28.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6488 GULFSTREAM AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.02844 FAA STC ST10294SC-D GULFSTREAM 200 Installation of a Pedestal Extension in a Prior to installation of this modification the<br />
08.07.2008<br />
CORPORATION.<br />
Gulfstream G200.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>6556 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6557 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6584 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6632 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6633 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
10<strong>01</strong>6634 GULFSTREAM AEROSPACE<br />
CORPORATION.<br />
<strong>EASA</strong>.IM.A.S.02940 FAA STC ST10338SC-D GULFSTREAM G150 Installation of an Emergency<br />
Power/Annunciator System i.a.w. Gulfstream<br />
Index List GA313318000, Rev. B or later<br />
revisions of the above listed documents<br />
approved by <strong>EASA</strong> in accordance with <strong>EASA</strong><br />
ED Decision 20<strong>04</strong>/<strong>04</strong>/CF (or subsequent<br />
revisions of this decisio<br />
<strong>EASA</strong>.IM.A.S.02941 FAA STC ST10303SC-D GULFSTREAM 200 Installation of an XM Satellite Radio System<br />
i.a.w. Index list GA216078000, Rev. A. or later<br />
approved revisions of the aforementioned<br />
document approved by <strong>EASA</strong> in accordance<br />
with <strong>EASA</strong> ED Decision 20<strong>04</strong>/<strong>04</strong>/CF (or<br />
subsequent revisions of this decision).<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.IM.A.S.02989 FAA STC ST10035SC-D GULFSTREAM 200 Installation of Executive Cabin Interior i.a.w.<br />
Gulfstream Index List GA220008063, Rev. A or<br />
later revisions of this document approved by<br />
<strong>EASA</strong> in accordance with <strong>EASA</strong> ED Decision<br />
20<strong>04</strong>/<strong>04</strong>/CF (or subsequent revisions of this<br />
decision).<br />
Limited to S/N 063 20.08.2008<br />
<strong>EASA</strong>.IM.A.S.03069 FAA STC ST10291SC-D GULFSTREAM 200 Installation of Satcom High Speed Data 1 Prior to installation of this modification the<br />
21.<strong>01</strong>.2009<br />
Antenna i.a.w. Index List GA243038000 Rev. D installer must determine that the<br />
or later revisions of the above listed documents interrelationship between this modification and<br />
approved by <strong>EASA</strong> in accordance with <strong>EASA</strong> any other previously installed modification will<br />
ED Decision 20<strong>04</strong>/<strong>04</strong>/CF (or subsequent introduce no adverse effect upon the<br />
revisions of this decision).<br />
airworthiness of the product1 The<br />
<strong>EASA</strong>.IM.A.S.03070 FAA STC ST10290SC-D GULFSTREAM 200 Relocation of AFIS/VHF Comm No. 1 Antenna<br />
i.a.w. Index List GA243068000 Rev. C or later<br />
revisions of the above listed documents<br />
approved by <strong>EASA</strong> in accordance with <strong>EASA</strong><br />
ED Decision 20<strong>04</strong>/<strong>04</strong>/CF (or subsequent<br />
revisions of this decision).<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the productThe Installat<br />
<strong>EASA</strong>.IM.A.S.03071 FAA STC ST10292SC-D GULFSTREAM 200 Installation of Thrane & Thrane Aero HSD+ 1 Prior to installation of this modification the<br />
Satcom System i.a.w. Index List GA213038000 installer must determine that the<br />
Rev. D or later revisions of the above interrelationship between this modification and<br />
listeddocuments approved by <strong>EASA</strong> in any other previously installed modification will<br />
accordance with <strong>EASA</strong> ED Decision<br />
introduce no adverse effect upon the<br />
20<strong>04</strong>/<strong>04</strong>/CF (or subsequent revisions of this<br />
decision).<br />
airworthiness of the product1 The<br />
10<strong>01</strong>4<strong>04</strong>2 GULFSTREAM AEROSPACE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>120 GULFSTREAM IV Installation of Artex C406N Emergency Locator<br />
Transmitter<br />
15.02.2005<br />
10<strong>01</strong>4828 GULFSTREAM AEROSPACE LIMITED <strong>EASA</strong>.A.S.03<strong>04</strong>1 GULFSTREAM GIV-X <strong>EASA</strong> Certification of a number of FAA Major<br />
Alterations installed at original delivery.<br />
Aircraft GIV-X Serial No. 40<strong>04</strong> only. 09.10.2007<br />
10<strong>01</strong>5024 GULFSTREAM AEROSPACE LIMITED <strong>EASA</strong>.A.S.03330 GULFSTREAM GV-SP Repositioning of Cabin Seat to meet the<br />
requirements of JAR 25.562(c)(8).<br />
Aircraft Serial No 5032 Only. 29.10.2007<br />
10<strong>01</strong>5276 GULFSTREAM AEROSPACE LIMITED <strong>EASA</strong>.A.S.03787 GULFSTREAM GV-SP Re-placard aft seats “Not for use during Taxi 1. Aircraft Serials:- GV Serials 572 and<br />
18.02.2009<br />
Takeoff & Landing”.<br />
582;- GVSP Serial 5078.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will<br />
10<strong>01</strong>5413 GULFSTREAM AEROSPACE SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>132 FAA STC ST2137CH-T GULFSTREAM GV-SP Custom 14 Passenger Interior & Aircraft Limited to Gulfstream GV-SP Registration G-<br />
21.02.2007<br />
Completion.<br />
JCBC Serial Number 5060.<br />
10<strong>01</strong>5533 GULFSTREAM AEROSPACE SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>413 FAA STC ST00640CH BOMBARDIER CL-600-1A11 (CL- Installation of the Honeywell Enhanced Ground<br />
26.07.2005<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Proximity Warning System<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 257/<strong>462</strong><br />
29.07.2008<br />
29.07.2008<br />
22.<strong>01</strong>.2009<br />
22.<strong>01</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5688 GULFSTREAM AEROSPACE SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>673 FAA STC ST02229CH-D GULFSTREAM GIV-X Installation of Corporate Aircraft Completion 1. Aircraft Serial Number 4027 only2. This STC<br />
13.03.2006<br />
STC<br />
is approved only for the product configuration<br />
as defined in the approved design data<br />
referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by<br />
10<strong>01</strong>5848 GULFSTREAM AEROSPACE SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>948 ST10308SC-D GULFSTREAM 100<br />
GULFSTREAM 1125 WESATRD<br />
ASTRA<br />
10<strong>01</strong>5856 GULFSTREAM AEROSPACE SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>960 FAA STC NO ST02237CH-D<br />
GULFSTREAM ASTRA/SPX<br />
GULFSTREAM 100<br />
GULFSTREAM ASTRA/SPX<br />
Installation of Dual Universal Avioniks UNS-<br />
1C+ Flight Management Systems. FAA STC<br />
<strong>01</strong>0308SC-D<br />
10<strong>01</strong>4830 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03<strong>04</strong>5 BOEING B737-800 Installation of a Satcom Antenna for a GSM<br />
system on B737-800<br />
This STC is only applicable to A/C with<br />
previous installed dual Universal Avionik UNS-<br />
1C FMS.<br />
13.07.2006<br />
Installation of a Corporate Aircraft Completion Limited to S/N 158 11.08.2006<br />
in accordance with Gulfstream Master Drawing<br />
List GA122<strong>04</strong>6000, Rev B dated July 19,2006<br />
or later approved revision<br />
As in Instrucions for Continued Airworthiness<br />
H4ADR259 Issue 1 or later <strong>EASA</strong> approved<br />
revision.<br />
10<strong>01</strong>4843 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03060 Interior Changes for the B/E Aerospace First 1. Instructions for Continued Airworthiness,<br />
Class Seat Integration in the Forward Ref. No. H4ADR238.2. This approval is<br />
Passenger Cabin.This modification removes limited to only the installation made in the<br />
the existing 16 off Weber Business class seats Boeing Model B767-306, Serial Number 30393<br />
and installs 12 B/E Aerospace First Class aircraft.3. Prior to installation of this<br />
Passenger Seats with Ottomans and Sideledg modification the installer must de<br />
10<strong>01</strong>4867 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03091 BOEING B737-800 Installation of GSM Phone / SATCOM system<br />
on B737-800 aircraft.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>4876 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03103 BOEING 767-300 The cabin reconfiguration of B767-300 Aircraft Continued Airworthiness Manual, Ref. No.<br />
with Brice B1000S seats for TUI<br />
ML3263, Rev. A.This approval is limited to only<br />
ARKEFLY/This modification removes the the installation made in the Boeing Models<br />
existing 260 economy class seats and installs B767-300, S/N 24477, S/N 24847, S/N 24848<br />
260 new Brice B1000s economy class seats in aircraft.<br />
an identical passenger layout.<br />
10<strong>01</strong>4883 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03111 BOEING 737-500 Implementation of Interior Changes associated<br />
with the cabinreconfiguration from 124YC to<br />
126YC.<br />
Prior to installation of this modification the<br />
installer must determine that<br />
theinterrelationship between this modification<br />
and any other previously installedmodification<br />
will introduce no adverse effect upon the<br />
airworthiness of theproduct.The installatio<br />
10<strong>01</strong>5300 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03859 AIRBUS A320-232 GUEST/STAFF SEATING AREA<br />
Approval valid only for MSN 2403.The use of<br />
<strong>04</strong>.05.2009<br />
RECONFIGURATION & MISC CABIN ITEMS the aircraft is limited to non-commercial<br />
FOR A320-232 AIRCRAFT as defined in operation only. For other Limitations refer to<br />
H4ACP057.Model: Airbus A320-232 MSN<br />
2403, A6-DLM<br />
Flight Manual Supplement H4AFMS<strong>01</strong>9.<br />
10026811 H4 AEROSPACE (UK) Ltd. P-<strong>EASA</strong>.A.S.03841 BOEING 767-300 Installation of Lifeport Stretcher. None. Prior to installation of this modification the 12.08.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
10027495 H4 AEROSPACE (UK) Ltd. REV. 1 B737-800 Introduction of Recaro Economy Passenger None The STC is based upon cabin<br />
09.03.2<strong>01</strong>1<br />
Seats on Boeing 737-800, inaccordance with<br />
installations as approved under<br />
project H4A1239(Revision of STC 10027495<br />
STC<strong>EASA</strong>.A.S.03836. Applicable<br />
to remove EWIS Limitation)<br />
documents must be considered.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previo<br />
10029103 H4 AEROSPACE (UK) Ltd. REV. 2 A319, A320, A321 Installation of Runway Turnoff and Logo Lights. Restricted to the aircraft listed in doc. N° Prior to installation of this modification it 20.10.2<strong>01</strong>0<br />
Minor Change to <strong>EASA</strong> STC10029103, Rev.1 H4ADR530 - MasterEffectivity List for must be determined thatthe<br />
issue date 31.03.2<strong>01</strong>0 granted to H4<br />
Goodrich RTO and Logo Light Installation. interrelationship between this modification<br />
Aerospace (UK) Ltd.Minor change approval is<br />
and any other previouslyinstalled<br />
sought to reflect the up issue wording of<br />
modification and/ or repair will introduce<br />
theinstructions of continued airworthiness inc<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 258/<strong>462</strong><br />
16.<strong>01</strong>.2008<br />
19.06.2007<br />
12.12.2008<br />
14.06.2007<br />
10.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032786 H4 AEROSPACE (UK) Ltd. 737-700 Interior Reconfiguration from 18 to 22 None Prior to installation of this modification it 03.12.2<strong>01</strong>0<br />
Passenger Capacity on Boeing737-700 Aircraft<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10032969 H4 AEROSPACE (UK) Ltd. REV. 1 BD-700-1A10 Activation of Nicemate WLAN System Restricted to ASN 9<strong>01</strong>1 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.06.2<strong>01</strong>1<br />
10033551 H4 AEROSPACE (UK) Ltd. REV. 1 737-300, -400, -500, -800 Introduction of Cockpit Door Surveillance and<br />
Cabin Witness System<br />
10034127 H4 AEROSPACE (UK) Ltd. <strong>EASA</strong>.A.S.03836 REV. 1 B737-800 Introduction of Interior with 56 Recaro Business - The STC is limited to MSN 33<strong>01</strong>6 (YJ935)<br />
class seats andassociated systems(Revison of and MSN 33021 (YJ936).- Changes to MMEL<br />
STC <strong>EASA</strong>.A.S.03836 to remove EWIS or MEL are not covered under the STC<br />
Limitation)<br />
approval andrequire an additional approval, if<br />
deemed necessary.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.02.2<strong>01</strong>2<br />
Prior to installation of this modification it 09.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.The in<br />
10034368 H4 AEROSPACE (UK) Ltd. B737-400 Installation of a two-class seating arrangement Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.03.2<strong>01</strong>1<br />
10034588 H4 AEROSPACE (UK) Ltd. 747-200, -300 Installation of a CabinVu-123 Cockpit Door<br />
Monitoring System and aFlightVu Witness<br />
Cabin Surveillance System in accordance with<br />
H4Aerospace Modification Summary<br />
document nr. H4A1333 Rev. 1, dated 18<br />
052<strong>01</strong>0 or later approved revision.<br />
10035914 H4 AEROSPACE (UK) Ltd. 777-200 Introduction of an Aerospace Cockpit Door and<br />
Cabin Surveillance onBoeing 777-200.<br />
None H4AFMS022 Flight Manual Supplement<br />
shall be included in the AircraftFlight<br />
ManualH4ADR548 Instructions for<br />
Continued Airworthiness shall be included<br />
inthe aircraft maintenance<br />
instructionsPrior to installation of this<br />
modification it must be determined tha<br />
13.<strong>04</strong>.2<strong>01</strong>1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.07.2<strong>01</strong>1<br />
10037544 H4 AEROSPACE (UK) Ltd. B757-300 Installation of Geven Piuma Seats as defined in None Prior to installation of this modification it 05.12.2<strong>01</strong>1<br />
H4ACP076<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038071 H4 AEROSPACE (UK) Ltd. 767-31K ER Installation of Geven 'Nova' & 'Puma' Series<br />
Passenger Seats 326Yconfiguration.<br />
10038630 H4 AEROSPACE (UK) Ltd. REV. 1 B777-200 Installation of new cabin interior as defined in<br />
H4ACP075<br />
Limited to installation on B767-31K Serial<br />
Numbers 27205, 27206 and28865.<br />
None. 16.<strong>01</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.07.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 259/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0254 H4 AEROSPACE (UK) Ltd. B757-200 Passenger cabin reconfiguration on Openskies None<br />
B757<br />
None 20.06.2<strong>01</strong>2<br />
10<strong>04</strong>0531 H4 AEROSPACE (UK) Ltd. 767-200, -300 Introduction of an AD Aerospace Cockpit Door none Prior to installation of this modification it 09.07.2<strong>01</strong>2<br />
and Cabin SurveillanceSystem on Boeing B767-<br />
must be determined thatthe<br />
200/300.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1036 H4 AEROSPACE (UK) Ltd. B757-200 Cabin Re-configuration and Airvod IFE System<br />
Installation<br />
10<strong>01</strong>5668 HARTZELL PROPELLER INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>644 FAA STC SA<strong>01</strong>850CH DIAMOND DA-40 Installation of Hartzell Two blade propeller HC-<br />
C2YR-1BF/F7495S with STC SA<strong>01</strong>850CH in<br />
the Diamond DA40 aeroplane<br />
1003<strong>01</strong>56 HARTZELL PROPELLER INC. P-<br />
<strong>EASA</strong>.IM.A.S.03250<br />
FAA STC SA02677CH-D PA-46-350P, PA-46R-350T <strong>EASA</strong> validation of FAA STC SA02677CH-<br />
DInstallation of Hartzell Propellers HCI3YR-<br />
1N/N7605(K)+2,HCI3Y1R-1N/N7605(K)+2<br />
10034394 HARTZELL PROPELLER INC. FAA STC SA10551SC 58, 58A, G58 Installation of Hartzell PHC-J3YF-<br />
2UF/FFC7391D(B, K) propellers<br />
10038909 HARTZELL PROPELLER INC. FAA STC SA02130SE KING AIR B200GT AND B200CGT Installation of BLR Hartzell Composite<br />
Propeller HC-E4N-3A/NC9208K.<br />
10039256 HARTZELL PROPELLER INC. FAA STC SA0<strong>04</strong>70AT A188, A188A, A188B Installation of either a Hartzell model PHC-<br />
C3YF-1RF/F8468A()-6Rpropeller and<br />
associated spinner assembly C-3535-1(P) in<br />
accordance withFAA STC SA0<strong>04</strong>70AT<br />
10<strong>01</strong>5394 HARTZELL SERVICE CENTER <strong>EASA</strong>.IM.A.S.<strong>01</strong>095 SA1105CH PIPER PA-32-260 Installation of Hartzell HC-C3YR-1RF/F7693F<br />
three bladed propeller on the Piper-PA32-260<br />
per FAA STC SA1105CH<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.08.2<strong>01</strong>2<br />
Diamond Modifications as detailed in the<br />
Installation instructions<br />
For further limitations see applicable<br />
associated technicaldocumentation<br />
30.09.2005<br />
1. Prior to installation of this modification 31.05.2<strong>01</strong>0<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2. The inst<br />
Only aircraft equipped with a Teledyne Prior to installation of this modification it 31.03.2<strong>01</strong>1<br />
Continental IO-550-C engine areeligible for this must be determined thatthe<br />
STC.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Requires the installation of a BLR Aerospace Eligible Serial Numbers are listed in FAA 22.03.2<strong>01</strong>2<br />
Ultimate PerformancePackage (UPP) ref FAA Approved MDL BLR-KA250CP-<br />
STC SA02131SE and <strong>EASA</strong> STC 10038758. 002,Revision B dated May 3, 2<strong>01</strong>1. Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modi<br />
None If the holder agrees to permit another<br />
person to use this certificate toalter the<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
1. <strong>EASA</strong> does not consider this modification to<br />
increase the noise level and it was not<br />
considered an acoustical change from the HC-<br />
C2YK-1F/F8477-2 Propeller.2. If the holder<br />
agrees to permit another person to use this<br />
certificate to alter the product, the<br />
10<strong>01</strong>5485 HARTZELL SERVICE CENTER <strong>EASA</strong>.IM.A.S.<strong>01</strong>245 FAA STC SA02181AK CESSNA 208, CESSNA 208B Installation of a Hartzell HC-B3TN-<br />
3AF(Y)/T10890CN(K)-2 three bladed propeller<br />
and D-4897(P) assembly on the type Cessna<br />
208, 208A and 208B in accordance with the<br />
application dated 22 April 2005.FAA STC:<br />
SA02181AK<br />
-- 07.08.2006<br />
10<strong>01</strong>5907 HARTZELL SERVICE CENTER <strong>EASA</strong>.IM.A.S.02033 SA02092AK CESSNA 208<br />
Installation of Hartzell HC-D4N-3R/D9511F(K) This approval is limited to Model 208<br />
13.<strong>04</strong>.2007<br />
CESSNA 208A<br />
CESSNA 208B<br />
Four Bladed Propeller and D-630-3(P) Spinner landplanes only.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 260/<strong>462</strong><br />
20.<strong>04</strong>.2<strong>01</strong>2<br />
30.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5985 HARTZELL SERVICE CENTER <strong>EASA</strong>.IM.A.S.02138 FAA STC SA<strong>01</strong>024CH PIPER PA-28R-2<strong>01</strong>T<br />
Installation of a Hartzell PHC-C3YF-<br />
The aircraft complies with annex 16, volume I,<br />
09.11.2006<br />
PIPER PA-28RT-2<strong>01</strong>T<br />
1RF/F7663-4T propeller and C-3570(P) third edition, amendment 7, chapter 6. The<br />
spinner in accordance with Hartzell installation certified noise level is 75.1 dB(A) at 2575<br />
instructions HP2834 dated February 3, 1999 or rpmThis STC is approved only for the product<br />
later approved revision (validation of FAA STC configuration as defined in the approved design<br />
SA<strong>01</strong>024CH)<br />
data referred to in the parag<br />
10<strong>01</strong>6516 HARTZELL SERVICE CENTER <strong>EASA</strong>.IM.A.S.02887 FAA STC SA2078CH CESSNA R172K Installation of a Hartzell Propeller Inc. 75” This STC is compatible with STC SA1437CE<br />
Diameter 3-Blade Propellermodel (P)HC-C3YF- that installs the TCM IO-360-K, or –KB, engine<br />
1RF/F7392 with A-2295-1(P) spinneror model as modified by STC SE1436CE. The re-rated<br />
(P)HC-G3YF-1RF/F7392 with C-4582-(P) engine is designated IO-360-KC, or –KBC,<br />
spinneron a Cessna R172K (Hawk XP) which increases the power rating to<br />
Landplane aircraft.<br />
210hp@2800 rpm for five minutes at takeoff<br />
and 1<br />
10<strong>01</strong>5337 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5472 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5473 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5644 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5861 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5862 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5863 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5864 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5865 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5866 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5867 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5868 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5869 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5870 HAWKER BEECHCRAFT<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.00364 REV. 2 FAA STC SA2824SW-D BAE 125 SERIES 800A<br />
HAWKER 800, 800XP, 850XP<br />
HAWKER HS 125-700<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>224 REV. 3 FAA STC ST10385SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>225 REV. 3 FAA STC ST10369SC-D HAWKER 750<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
05.08.2008<br />
Installation of a Long Range Oxygen System This STC is approved only for the product Prior to installation of this modification the 18.02.2<strong>01</strong>0<br />
configuration as defined inthe approved design installer must determinethat the<br />
data referred to in the paragraph<br />
interrelationship between this modification<br />
"Description".Compatibility with other and any otherpreviously installed<br />
aircraft/engine configurations shall<br />
modification will introduce no adverse<br />
bedetermined by the installer.<br />
effect uponthe airworthiness of the<br />
product.<br />
Installation of a Rockwell Collins CMS-1 Cabin<br />
Management System.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>608 FAA STC ST<strong>01</strong>342WI-D HAWKER 800 XP Installation of Collins Integrated Flight<br />
Information System (IFIS 5000) and Pro Line<br />
21 Radios<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>974 REV. 2 FAA STC ST10066SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>975 REV. 1 HAWKER 800 XP<br />
HAWKER 850 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>976 REV. 2 FAA STC ST1<strong>01</strong>08SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>977 REV. 2 FAA STC ST1<strong>01</strong>09SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>978 REV. 2 FAA STC ST1<strong>01</strong>28SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>979 ST1<strong>01</strong>89SC HAWKER 800 XP<br />
HAWKER 850 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>980 REV. 2 FAA STC ST1<strong>01</strong>87SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>982 ST1<strong>01</strong>90SC HAWKER 800 XP<br />
HAWKER 850 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>984 REV. 3 FAA STC ST09262SC-D HAWKER 750, 800XP, 850XP,<br />
HAWKER 900XP<br />
1. This modification requires installation of<br />
STC ST10369SC-D, Installation of an<br />
Emergency Light System;<br />
Installation of an Emergency Light System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of B.F. Goodrich WX-1000E<br />
Stormscope.<br />
1. Prior to installation and approval of<br />
Raytheon Aircraft Company Kit 149-3419-00<strong>01</strong><br />
is prerequisite to this STC.2. Prior to<br />
installation and approval of Rautheon Aircraft<br />
Company Kit 149-3420-00<strong>01</strong> is prerequisite to<br />
this STC.3. This STC is approv<br />
21.05.2008<br />
21.05.2008<br />
19.10.2005<br />
20.05.2008<br />
Installation of a Davtron Clock 23.06.2008<br />
Installation of a Cockpit Speaker Volume<br />
Recalibration.<br />
20.05.2008<br />
Installation of a Cockpit Speaker Inhibit Switch. 21.05.2008<br />
Installation of a Precise Flight Pulselight<br />
System Activated by (existing) TCAS.<br />
Installation of Digital Passenger Briefing<br />
System<br />
Installation of a Satellite Communications<br />
System.<br />
21.05.2008<br />
-- 18.09.2006<br />
Installation of CMS 400 Checklist Management --<br />
System<br />
19.09.2006<br />
Installation of a Third and Fourth 750 Liter -1<strong>01</strong> and -103 installation: Model Hawker 750; Prior to installation of this modification the 18.02.2<strong>01</strong>0<br />
Oxygen Bottle in AftEquipment Bay.<br />
Hawker 800XP; Hawker 850XP-105<br />
installer must determinethat the<br />
installation: Model Hawker 900XP<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>985 REV. 4 FAA STC ST09651SC HAWKER 750 Installation of Cabin Interior and Avionics 1. Hawker 750 with 238M530760-0<strong>01</strong>7 and -<br />
15.12.2008<br />
Systems<br />
0<strong>01</strong>9 installations only, are limited to a<br />
maximum of 10 passengers.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previous<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 261/<strong>462</strong><br />
21.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5871 HAWKER BEECHCRAFT<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>986 REV. 2 FAA STC SA8063SW BAE 125 SERIES 800A<br />
Installation of Cabin Headliner/Window Panel<br />
20.05.2008<br />
CORPORATION<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
Brackets.<br />
10<strong>01</strong>5872 HAWKER BEECHCRAFT<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>987 REV. 2 FAA STC SA8062SW BAE 125 SERIES 800A<br />
Installation of a Therapeutic Oxygen System. 20.05.2008<br />
CORPORATION<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
10<strong>01</strong>5873 HAWKER BEECHCRAFT<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>988 REV. 2 FAA STC SA7972SW-D HAWKER 800 XP<br />
Installation of Airborne Flight Information<br />
20.05.2008<br />
CORPORATION<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
System (AFIS).<br />
10<strong>01</strong>5874 HAWKER BEECHCRAFT<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>989 REV. 2 FAA STC SA7944SW BAE 125 SERIES 800A<br />
Installation of a Cabin Oxygen System. 20.05.2008<br />
CORPORATION<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
10<strong>01</strong>5875 HAWKER BEECHCRAFT<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>990 REV. 1 FAA STC SA3810SW-D BAE 125 SERIES 800A<br />
Installation of Precise Pulselite Control Unit 1. 103 Installation is for Models Hawker<br />
19.11.2007<br />
CORPORATION<br />
HAWKER 800<br />
800XP, Hawker 850XP and Hawker 900XP.2.<br />
HAWKER 800 XP<br />
All installations except -103 is for Models BAe.<br />
HAWKER 850 XP<br />
125 Series 800A, Hawker 800; Hawker 800XP<br />
10<strong>01</strong>5876 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5877 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5878 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5879 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5880 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5881 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>6024 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>6179 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>65<strong>01</strong> HAWKER BEECHCRAFT<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>992 REV. 2 FAA STC SA2710SW BAE 125 SERIES 800A<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
HAWKER HS 125<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>993 REV. 2 FAA STC ST<strong>01</strong>342WI-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>994 REV. 2 FAA STC ST09772SC-D BAE 125 SERIES 800A<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>995 ST0998SC HAWKER 800 XP<br />
HAWKER 850 XP<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>996 REV. 2 FAA STC ST09986SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
Installation of Observer’s Jump Seat. 20.05.2008<br />
Installation of Collins Integral Flight Information<br />
System (IFIS 5000) and Proline 21 Radios.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>997 REV. 3 FAA STC ST100<strong>01</strong>SC-D 750, 800XP, 850XP, 900XP Installation of a Honeywell Solid State Flight<br />
Data Recorder withInterface to Collins Proline<br />
21.<br />
<strong>EASA</strong>.IM.A.S.02192 REV. 2 FAA STC ST1<strong>04</strong>32SC-D HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.02408 REV. 2 FAA STC ST09955SC-D BAE 125 SERIES 800A<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
<strong>EASA</strong>.IM.A.S.02863 REV. 3 FAA STC SA10747SC C90, C90A, C90GT, C90GTI, E90 Increase Operating Gross Weight Approval(as<br />
defined in the attached table)<br />
1. Prior installation and approval of Kit 149-<br />
3419-00<strong>01</strong> is a prerequisite;2. Prior<br />
installation and approval of Kit 149-3420-00<strong>01</strong><br />
20.05.2008<br />
is a prerequisite;<br />
Installation of a Smoke Detector System. 20.05.2008<br />
Installation of the Magnastar C-2000 Airborne<br />
Telephone System<br />
-- 19.09.2006<br />
Installation of an Airshow System. 20.05.2008<br />
For Hawker 800XP model, installation is limited Prior to installation of this modification it 19.09.2<strong>01</strong>1<br />
to aircraft equippedwith Collins Proline 21 must be determined thatthe<br />
Avionics<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Mark V Enhance Ground 1. The Flight Manual Supplement is not<br />
Proximity Warning System (EGPWS) with and needed for the -1<strong>01</strong> installation because the<br />
without Runway Awareness Advisory System. aircraft's basic AFM is still applicable.2.<br />
When fitted to Hawker 800XP and 850XP this<br />
STC is limited to the following aircraft 258541,<br />
258556, 258567 through 258609,<br />
Installation of a Divan Cargo Net Assembly. 1. In accordance with Master Drawing List<br />
800-197, Revision D, or later approved<br />
revision.2. Maintenance Manual Addenda 25-<br />
50-05,<br />
This modification is only applicable to aircraft<br />
equipped with theCollins Proline 21 avionics<br />
package.Refer to aircraft defined in<br />
HawkerBeechcraft major change SC0353A.<br />
21.05.2008<br />
20.05.2008<br />
Prior to installation of this modification it 23.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 262/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6598 HAWKER BEECHCRAFT<br />
<strong>EASA</strong>.IM.A.S.03<strong>01</strong>1 REV. 4 FAA STC ST 10596SC-D 800,750, 800XP, 850XP, 900XP Installation of an Aircell Axxess Voice/Data This modification is only applicable to aircraft Prior to installation of this modification it 30.10.2<strong>01</strong>2<br />
CORPORATION<br />
Communications System.<br />
equipped with theCollins Proline 21 or must be determined thatthe<br />
Honeywell SPZ-8000 avionics packages.RDL interrelationship between this modification<br />
230-20<strong>01</strong>-103 and-107 Installation requires the and any other previouslyinstalled<br />
aircraft be equippedwith Collins Proline 21 modification and/ or repair will introduce<br />
radios with the IFIS STC ST<strong>01</strong>342WI-D no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6625 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10027658 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10029215 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10029220 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10029784 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10029917 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10030002 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10030003 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10031606 HAWKER BEECHCRAFT<br />
CORPORATION<br />
<strong>EASA</strong>.IM.A.S.03058 REV. 1 FAA STC SA03622AT BEECH B300, BEECH B300C Installation of an Air Conditioning Evaporator<br />
Blower Motor RF NoiseFilter into a Hawker<br />
Beechcraft Model B300 / B300C aircraft .<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03021<br />
This modification is only applicable to aircraft<br />
equipped with theCollins Proline 21 avionics<br />
package. Refer to aircraft defined in<br />
HawkerBeechcraft major change SC0353A.<br />
Prior to installation of this modification it 23.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
REV. 1 FAA STC SA02253LA B300/B300C Installation of Belly Radome. none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.10.2<strong>01</strong>1<br />
FAA STC SA<strong>01</strong>502WI-D B300 SERIES STC SA<strong>01</strong>502WI-D issued to allow<br />
modification of the FGC-3000 units as asolution<br />
to eliminate nuisance pitch trim wheel<br />
movement.<br />
None. None. 12.03.2<strong>01</strong>0<br />
FAA STC ST03749AT-D GIV-X Installation of cabin interior and Airplane This approval is limited to only the installation None. 12.03.2<strong>01</strong>0<br />
Completion for Serial 4175.<br />
made in GulfstreamGIV-X, Serial No 4175.The<br />
following STC’s are a required part of this<br />
STC: ST02228CH-D, ,,ST02979AT-D,<br />
ST02980AT-D, ST02987AT-D, ST03<strong>04</strong>7AT-D,<br />
ST03290AT-D, ST03410AT-D, ST03532AT-D,<br />
ST0354<br />
FAA STC REF SA02277LA B300 KING AIR Installation of High Definition Audio Video Only applicable to King Air Model B300 aircraft Prior to installation of this modification it 20.<strong>04</strong>.2<strong>01</strong>0<br />
(HDAV-3002) LRU Unit as aninterface with the equipped with theRockwell Collins Venue must be determined thatthe<br />
Rockwell Collins Venue Cabin Management Cabin Management System.<br />
interrelationship between this modification<br />
System.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC ST10599SC-D 800XP, 850XP, 900XP Installation of an Espresso Maker This modification requires the installation of<br />
FAA STC ST10385SC-D,Installation of a<br />
Rockwell Collins CMS-1 Cabin Management<br />
System.<br />
FAA STC SA10969SC KING AIR C90GTI Installation of an upgraded Flight Management<br />
System (Version 4.0). This upgrade will offer a<br />
standard Flight Management Computer and<br />
willinclude an option for Search and Rescue<br />
Mission Profiles.<br />
Prior to installation of this modification the 03.05.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
None. None. 10.05.2<strong>01</strong>0<br />
FAA STC SA10970SC KING AIR B200 AND B300 Installation of an upgraded Flight Management None.<br />
System (Version 4.0) . This upgrade will offer a<br />
standard Flight Management Computer and<br />
willinclude an option for Search and Rescue<br />
Mission Profiles.<br />
None. 10.05.2<strong>01</strong>0<br />
REV. 2 FAA STC ST10922SC-D MODEL 4000 Installation of Cabin Interior Furnishings and<br />
Systems.<br />
Only configuration 3, 6, 8 and 9 installations <strong>EASA</strong> accepts the use of FAA (Means of 16.10.2<strong>01</strong>2<br />
are <strong>EASA</strong> approved. Airworthiness Limitations Compliance) Issue Papers S-1(Stage 4,<br />
inspections are contained in Chapter 4 of Closed <strong>04</strong>/05/2<strong>01</strong>0), S-1 (signed June<br />
theCompletions Manual. Airworthiness 21, 2<strong>01</strong>1) and S-2 (signedJune 21, 2<strong>01</strong>1)<br />
Limitations:for configurations 6 and 8 per 240- as being applicable to this project. Future<br />
590<strong>01</strong>1-0003C approved August 2<strong>01</strong>0;for changes tothis STC that impact on the<br />
agreed means of comp<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 263/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032246 HAWKER BEECHCRAFT<br />
FAA STC ST10598SC-D 4000 Installation of Flight Camera System None Prior to installation of this modification it 19.10.2<strong>01</strong>0<br />
CORPORATION<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10035154 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10036742 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>04</strong>2768 HAWKER BEECHCRAFT<br />
CORPORATION<br />
10<strong>01</strong>5370 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>5373 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>5909 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>5982 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>6127 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>6230 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>6231 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>6367 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
10<strong>01</strong>6577 HAWKER BEECHCRAFT<br />
CORPORATION (HBC)<br />
REV. 1 FAA STC SA00526DE 390 (PREMIER I)<br />
390 (PREMIER IA)<br />
FAA STC SA02331LA B300 & B300C Installation and maintenance of Switches and<br />
wiring for anElectro-Optical/Infra-Red Lift and<br />
Turret System.<br />
Installation of an AirCell telephone system. Serial Number RB-73 OnlyHawker Beechcraft<br />
Ltd. Minor Modification SC0392A must be<br />
embodied.<br />
FAA STC SA00782WI-D <strong>EASA</strong> APPROVED MODEL LIST Modification of Collins VHF-22A/VHF-22B VHF<br />
COMM Receiver Transmitterwith CTL-22<br />
Control Pro Line II System Installation to a<br />
CollinsVHF-22C/VHF-22D VHF COMM<br />
Receiver Transmitter with CTL-22C Control<br />
8.33kHz Pro Line II System Installation.<br />
Prior to installation of this modification it 15.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none This STC is part of an existing belly<br />
mounted Radar installation and mayonly<br />
be installed on aircraft previously installed<br />
with STC SA02253LA(<strong>EASA</strong> approval ref<br />
10027658)Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelations<br />
05.10.2<strong>01</strong>1<br />
A VHF-22C unit can be installed to replace<br />
either an existing VHF-22A orVHF-22B unit. A<br />
VHF-22D unit can only be installed to replace<br />
anexisting VHF-22B unit.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>009 FAA STC SA8356SW HAWKER 1000 Installation of Air Distribution System 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>026 SA8348SW HAWKER 1000 Installation of Honeywell SRZ-8000 Digital<br />
Integrated Flight Control System with low<br />
speed awareness cue in accordance with<br />
Arkansas Aerospace Inc. Drawing List 1000-<br />
008<br />
<strong>EASA</strong>.IM.A.S.02036 ST09250AC HAWKER 1000<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
<strong>EASA</strong>.IM.A.S.02134 REV. 3 FAA STC ST0<strong>04</strong>59NY HAWKER 750<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
Installation of a Logo Light on the lower surface<br />
of the Horizontal Stabiliser<br />
Installation of an Allied Signal (Garrett) GTCP<br />
36-150W gas turbine Auxiliary Power Unit<br />
(APU).<br />
<strong>EASA</strong>.IM.A.S.02321 FAA STC SA<strong>01</strong>417WI RAYTHEON A36 Replace pilot's altimeter with IS&S encoding<br />
altimeter.<br />
<strong>EASA</strong>.IM.A.S.02492 FAA STC SA0859WI BEECH 1900D Installation of EROS MAGIC (Mask and<br />
Goggles Integrated Concept) Quick Donning<br />
Masks.<br />
<strong>EASA</strong>.IM.A.S.02494 FAA STC SA0876WI BEECH 1900D Installation of an Allied Signal CAS 67A Traffic<br />
Alert and Collision Avoidance System (TCAS<br />
II)<br />
<strong>EASA</strong>.IM.A.S.02689 FAA STC SA<strong>01</strong>798SE BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 300<br />
BEECH 300C<br />
Reduced Vertical Separation Minimum<br />
Qualification Document Group Aircraft<br />
Classification Hawker Beechcraft Models<br />
B200/B200C/B200GT/B200CGT/ B300/B300C<br />
(Super King Air)<br />
<strong>EASA</strong>.IM.A.S.02975 FAA STC ST02113LA BEECH 400A Rockwell Collins dual Attitude Heading<br />
Reference system (AHRS).<br />
This STC does not give:PRNAV<br />
approvalRVSM approvalCAT II approval<br />
Compliance with the following requirements, in<br />
addition to the requirements shown on the<br />
Type Certificate Data Sheet 3A20, has<br />
beenshown: 23.303, 23.305, 23.307, 23.321,<br />
23.341, 23.365, 23.6<strong>01</strong>, 23.609, 23.627<br />
effective February 1, 196523.611 as amended<br />
thr<br />
Cutter aviation Master Data List Document No.<br />
02A-2406-2<strong>01</strong>, Revision “B” dated December<br />
5, 2007 or later approved revisions.<br />
Prior to installation of this modification it 18.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 264/<strong>462</strong><br />
11.02.2005<br />
<strong>01</strong>.02.2007<br />
21.09.2006<br />
16.06.2008<br />
26.02.2007<br />
17.07.2007<br />
17.07.2007<br />
18.<strong>04</strong>.2008<br />
12.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030074 HAWKER BEECHCRAFT<br />
FAA STC SA<strong>01</strong>566WI-D KING AIR B200 SERIES Installation of modified Rockwell Collins Flight Prior approved installation of a Rockwell Prior to installation of this modification it 19.05.2<strong>01</strong>0<br />
CORPORATION (HBC)<br />
Guidance Computers(FGC-3000 units) as a Collins Inc FGC-3000 FlightGuidance must be determined thatthe<br />
solution to eliminate nuisance pitch trim Computer Module (CPN 822-1108-031) is a interrelationship between this modification<br />
wheelmovement.<br />
prerequisite to thisSTC.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4008 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>051 REV. 1 HAWKER HS 125-700B Increase Maximum Zero Fuel Weight 22.02.2005<br />
10<strong>01</strong>4102 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>206 BEECH 400A (HAWKER 400 XP) Certification for Steep Approaches 26.07.2005<br />
10<strong>01</strong>4103 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>207 BAE 125 SERIES 800B Raytheon Aircraft Services Modification<br />
SC<strong>01</strong>35R. Runway Awareness & Advisory<br />
System (RAAS) to the MK VII EGPWS<br />
Computer<br />
10<strong>01</strong>41<strong>04</strong> HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>208 HAWKER HS 125-700B Installation of a Collins AHS-3000A Attitude<br />
Heading Reference System.<br />
10<strong>01</strong>4105 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>209 HAWKER HS 125-700B Installation of Traffic Alert & Collision<br />
Avoidance System (TCAS-4000), Mode S<br />
Elementary Surveillance (Flight ID) and<br />
Emergency Locator Transmitter (Artex C406-2)<br />
10<strong>01</strong>4157 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>283 BAE 125 SERIES 800B Special Interior Refurbishement 28.<strong>04</strong>.2005<br />
10<strong>01</strong>4350 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>615 BAE 125 -800 SERIES Steep Approch Capability 25.10.2005<br />
10<strong>01</strong>4466 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.02527 BAE 125 SERIES 800B To indroduce completion of the upgrade to the Applicable to Aircraft Serial 258208 only<br />
existing Terrain Awareness Warning System<br />
(TAWS) installation to include terrain display.<br />
02.05.2006<br />
10<strong>01</strong>4803 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03006 REV. 1 HAWKER 850 XP Introduction of Steep Approach Capability. 03.07.2007<br />
10<strong>01</strong>5118 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03467 HAWKER 800 XP To upgrade Dual Honeywell NZ-2000 FMS<br />
Computers from 5.2 to 6.0 software and<br />
provide P-RNAV approval.<br />
None. 06.10.2008<br />
10<strong>01</strong>5119 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03468 HAWKER 1000 To introduce Dual Honeywell NZ-2000 FMS 1. As per AFM Supplement for Hawker<br />
25.09.2008<br />
Computers in lieu of NZ-920 FMS Computers 1000B (HS1.18) Supplement 3 issue 1;2.<br />
and add a second GPS GNSSU. The existing Prior to installation of this modification the<br />
Data Loader is replaced with Model DL-950. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification wi<br />
10<strong>01</strong>5126 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03476 REV. 1 HAWKER 750 Installation of Steep Approach Capability None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.05.2<strong>01</strong>1<br />
10<strong>01</strong>5127 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03477 REV. 1 HAWKER 900 XP Installation of Steep Approach Capability None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.05.2<strong>01</strong>1<br />
10<strong>01</strong>5133 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03486 HAWKER HS 125-700A To upgrade Dual UNS-1K FMS to Dual UASC<br />
UNS-1Lw in preparation for P-RNAV<br />
compliance.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
10<strong>01</strong>5322 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.IM.A.S.00275 FAA STC ST00983CH BEECH 400A Installation of a Honeywell Enhanced Ground<br />
airworthiness of the product. The i<br />
1. AFM Supplement Elliott Aviation<br />
Proximity Warning System (EGPWS) Mark VIII Document No. FS2<strong>01</strong>8-571 rev.0 or later<br />
in accordance with Elliot Aviation Master Data <strong>EASA</strong> approved revisions.2. Instructions for<br />
List 2<strong>01</strong>8-571DL, Revision 4, dated 6 Continued Airworthiness Document No.<br />
November 2003 or later <strong>EASA</strong> approved CA2<strong>01</strong>8-571.3. This STC is approved only<br />
revisions.This STC is issued as result of the va for the product configuration as defined in the<br />
app<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 265/<strong>462</strong><br />
21.06.2005<br />
13.06.2005<br />
23.03.2005<br />
10.11.2008<br />
20.10.20<strong>04</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5332 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.IM.A.S.00350 FAA STC SA0<strong>04</strong>21WI BEECH 1900C, AIRLINER Defines an all cargo interior using web nets. 1. The Airplane Flight Manual Supplement<br />
03.12.20<strong>04</strong><br />
The all cargo interior is defined by the top No RAS 114-590021 is required equipment<br />
drawing of Raytheon Aircraft Services No114- when this STC is installed.2. Compatibility of<br />
<strong>01</strong>00, no change, dated April 17, 1996, with an this design change with previously approved<br />
"FAA Approved" stamp of April 17, 1996 or modifications must be determined by the<br />
later FAA-approved revision.<br />
installer.3. This STC is issued as<br />
10032984 HAWKER BEECHCRAFT Ltd. B200, B300 Installation of Thrane & Thrane Aviator 200/300<br />
Inmarsat Satcom withWi-Fi capability on<br />
Beechcraft King Air B200/B300<br />
10037296 HAWKER BEECHCRAFT Ltd. HAWKER 750, 800XP<br />
HAWKER 850XP, 900XP<br />
10038135 HAWKER BEECHCRAFT Ltd. HAWKER 750, 800XP, 850XP<br />
HAWKER 900XP<br />
10038252 HAWKER BEECHCRAFT Ltd. <strong>EASA</strong>.A.S.03559 HAWKER 750<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
To introduce interior and electrical provisions<br />
for Medevac stretcherrole change<br />
capability.This Change instructs the interior and<br />
electrical changes to theaircraft. Stretcher and<br />
medical equipment installation will be<br />
certifiedby the appropriate vendor.<br />
To introduce Dual L3 Electronic Flight Bags<br />
(EFB) units in the cockpitwith power supplies.<br />
To introduce a new forward cabin door with<br />
associated placards.<br />
10038800 HAWKER BEECHCRAFT Ltd. KING AIR B300CER To introduce increased maximum landing<br />
weight to 16,500lbs for the KingAir B300CER.<br />
This modification is only applicable to aircraft<br />
equipped with theCollins Proline 21 avionics<br />
package. Refer to aircraft defined in<br />
HawkerBeechcraft major change SC0353A.<br />
Prior to installation of this modification it 13.12.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.11.2<strong>01</strong>1<br />
All EFB functionality and software approval will<br />
be the responsibilityof the aircraft operator.<br />
Unless approved otherwise by all<br />
RequiredManuals (Hard Copy) must still be<br />
carried in the aircraft.<br />
Prior to installation of this modification it 23.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.02.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.03.2<strong>01</strong>2<br />
10<strong>04</strong>0927 HAWKER BEECHCRAFT Ltd. C90GTI To introduce L3 Electronic Standby Instrument None<br />
System (ESIS) in lieu ofexisting Meggitt Mk II<br />
Secondary Flight Display (SFD) System.The<br />
existing Meggitt Mk II SFD (part number 39221-<br />
<strong>01</strong>-<strong>01</strong>) is removed andreplaced with L3 GH-<br />
3900.2 ESIS (Part number 9200-3450<br />
None 03.08.2<strong>01</strong>2<br />
10<strong>04</strong>1476 HAWKER BEECHCRAFT Ltd. REV. 1 B200<br />
B200GT<br />
10<strong>01</strong>6247 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02524 FAA STC ST02619AT BEECH 400<br />
BEECH 400A<br />
Introduce Rockwell Collins TCAS 4000, Traffic<br />
Collision Avoidance System(TCAS) II System.<br />
Installation of a Battery Low Voltage Warning /<br />
Shutoff System on Raytheon Aircraft 400 and<br />
400A.<br />
10<strong>01</strong>6248 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02525 FAA STC SA03292AT BEECH 390 Modification to install an Auxiliary Gound<br />
Heating System.<br />
STC does not provide compliance with<br />
Commission Regulation (EC)1332/2<strong>01</strong>1 as<br />
regards to ACAS II equipment.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
Prior to installation of this modification it 05.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 266/<strong>462</strong><br />
28.08.2007<br />
18.10.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6250 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02527 FAA STC NUMBER ST<strong>01</strong>441WI HAWKER 800<br />
Hawker Beechcraft Corporation Installation of<br />
10.10.2007<br />
HAWKER 800 XP<br />
upper and lower LED beacons, wingtip LED<br />
navigation lights and wingtip strobe lights.<br />
10<strong>01</strong>6269 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02552 FAA STC ST03405AT BEECH 400<br />
BEECH 400A<br />
Replacement of a Standby Altimeter<br />
installation in the Raytheon (Beech) models<br />
400, 400A aircraft.This STC is a duplicate of<br />
STC ST03379AT, <strong>EASA</strong>.IM.A.S.02353<br />
10<strong>01</strong>6281 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02574 REV. 1 FAA STC ST<strong>01</strong>369AT BEECH 300 Installation of a 70% Ground Idle Stop Dropout<br />
System.Installs cams and switches on the<br />
existing aircraft’s power lever system to allow<br />
the propeller system to transition from Ground<br />
Idle to Flight Idle when both Power levers are<br />
advances above 70 %. This<br />
10<strong>01</strong>6352 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02672 FAA STC SA<strong>01</strong>414WI HAWKER BEECHCRAFT G58 Modification to install a Honeywell KR 87 None 27.05.2009<br />
(BARON)<br />
Automatic Direction Finder (ADF) System and<br />
the Honeywell KA-44B Antenna interfaced with<br />
the previously installed Garmin 1000 Avionics<br />
System.<br />
10<strong>01</strong>6353 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02673 FAA STC SA<strong>01</strong>455WI HAWKER BEECHCRAFT G36 Modification to install a Honeywell KR 87 None 27.05.2009<br />
(BONANZA<br />
Automatic Direction Finder (ADF) System and<br />
the Honeywell KA-44B Antenna interfaced with<br />
the previously installed Garmin 1000 Avionics<br />
System.<br />
10<strong>01</strong>6550 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02930 FAA STC ST<strong>01</strong>191WI BEECH 1900D Installation of Cargo Conversion Modifications. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
03.09.2008<br />
10<strong>01</strong>6551 HAWKER BEECHCRAFT SERVICES <strong>EASA</strong>.IM.A.S.02931 REV. 1 FAA STC ST00589LA HAWKER 1000 Installation of AlliedSignal Enhanced Gound The installation should not be incorporated in<br />
<strong>04</strong>.07.2008<br />
Proximity Warning System (EGPWS). any aircraft unless it is determined that the<br />
relationship between this installationand any<br />
previously approved configuration will not<br />
introduce any adverse effect upon the<br />
Airworthiness of the Aircraft. The a<br />
10026878 HAWKER BEECHCRAFT SERVICES P-<br />
FAA STC SA<strong>01</strong>525WI BEECH 200, 200C, 200CT, 200T Installation of AirLock Secure Entry Door Lock None 1) Prior to installation of this modification 13.08.2009<br />
<strong>EASA</strong>.IM.A.S.03243<br />
BEECH 300, 300LW, B200, System in place oforiginal equipment locks for<br />
the installer mustdetermine that the<br />
B200C,<br />
the main cabin door, nose avionics doors,and<br />
interrelationship between this modification<br />
BEECH B200CT, B200T, B300, aft equipment door.<br />
and anyother previously installed<br />
BEECH B300C,<br />
modification will introduce no adverse<br />
HAWKER BEECHCRAFT<br />
effectupon the airworthiness of the<br />
B200GT, B200<br />
product. 2) The inst<br />
10036781 HAWKER BEECHCRAFT SERVICES FAA STC SA00857WI BEECH 1900D Installation of Universal Avionics System Corp<br />
UNS-1K Flight ManagementSystem.<br />
10036782 HAWKER BEECHCRAFT SERVICES FAA STC SA00878WI BEECH 1900D Installation of a forward double or triple club<br />
executive style interiorconfiguration.<br />
10<strong>01</strong>6<strong>04</strong>6 HAWKER BEECHCRAFT SERVICES, Inc. <strong>EASA</strong>.IM.A.S.02217 REV. 2 FAA STC SA1<strong>04</strong>78SC BEECH B200, B200C<br />
BEECH B200GT, B200CGT<br />
BEECH B300, B300C<br />
Installation of Digital Flight Data Recorder<br />
System<br />
<strong>04</strong>.09.2007<br />
19.10.2007<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.10.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.10.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.06.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 267/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6686 HEAD BALLOONS, INC. <strong>EASA</strong>.IM.BA.S.<strong>01</strong>000 SL2263SO HEAD BALLOONS AX7-77 Installatiopn of Aerostar (Raven) Models CW The following Aerostar burners are approved<br />
13.<strong>04</strong>.2007<br />
HEAD BALLOONS AX7-77B and RW baskets.<br />
for usewith the above Head envelope /<br />
HEAD BALLOONS AX8-105<br />
Aerostar basket configuration:Rally HP burner<br />
HEAD BALLOONS AX8-88<br />
PN 13180HP II Dual burner PN 17395HP II<br />
HEAD BALLOONS AX8-88B<br />
Single burner PN 17398Rally HP II burner PN<br />
HEAD BALLOONS AX9-118<br />
17399HP III Dual burner part number 52350HP<br />
10<strong>01</strong>6687 HEAD BALLOONS, INC. <strong>EASA</strong>.IM.BA.S.<strong>01</strong>0<strong>01</strong> FAA STC SB0<strong>04</strong>63AT HEAD BALLOONS AX7-77<br />
HEAD BALLOONS AX7-77B<br />
HEAD BALLOONS AX8-105<br />
HEAD BALLOONS AX8-88<br />
HEAD BALLOONS AX8-88B<br />
HEAD BALLOONS AX9-118<br />
10<strong>01</strong>5546 HEADS UP TECHNOLOGIES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>437 FAA STC SA00558DE-D DORNIER 328-100<br />
DORNIER D328-100<br />
MSN 3061<br />
Installation of Cameron Balloons Ltd. baskets<br />
and burners underneath Head Balloons, Inc.<br />
envelopes<br />
Installation of a Pilot and Co-Pilot Digital Air<br />
Data Unit<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
1. Airplane Flight Manual Supplement:AFMS<br />
Document 34-07-0002-00, Revision IR, dated<br />
19 August 20<strong>04</strong> or Document 34-07-0026-00,<br />
Revision IR or later approved revision<br />
isrequired on board for the IS&S ADDU<br />
installation,or AFMS Document 34-07-0002-<strong>01</strong>,<br />
Revisio<br />
10<strong>01</strong>5476 HEATH TECNA, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>229 FAA STC ST<strong>01</strong>532SE B747-400 Cabin Interior Reconfiguration 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5574 HEATH TECNA, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>484 FAA STC ST00636SE BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Installation of ATIX Interior retrofit Kit according<br />
to FAA STC ST00636SE<br />
10<strong>01</strong>6255 HEATH TECNA, INC. <strong>EASA</strong>.IM.A.S.02533 FAA STC ST<strong>01</strong>780SE B747-400 Installation of interior components in<br />
accordance with Heath Tecna Inc. Drawing List<br />
HPD-DL-105<br />
10<strong>01</strong>6256 HEATH TECNA, INC. <strong>EASA</strong>.IM.A.S.02534 FAA STC ST008700SE B737-330 Installation of galley supports structure and<br />
jumper wire provisions in accordance with<br />
Health Tecna Drawing List HPD-DL-76,<br />
Revision B, dated 16, January 20<strong>04</strong> or later<br />
approved revision.<br />
10<strong>01</strong>66<strong>01</strong> HEATH TECNA, INC. <strong>EASA</strong>.IM.A.S.03<strong>01</strong>5 FAA STC ST<strong>01</strong>154SE B747-200B Installation of interior components in<br />
accordance with Britax Heath Tecna Inc. (BHT)<br />
Drawing List HPD-DL-81 Revision B, dated<br />
December 12, 2002 or later FAA approved<br />
revisions<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Modification of the aircraft per Boeing Service<br />
Bulletin 747-00-20<strong>04</strong>, conversion from<br />
passenger to freighter configuration must be<br />
performed concurrently with this STC.<br />
Approval of this change in type design applies<br />
to the above model aircraft only. This approval<br />
should not be extended to aircraft on which<br />
other previously approved modifications are<br />
incorporated unless it is determined that the<br />
relationship between this c<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10028538 HEATH TECNA, INC. <strong>EASA</strong>.IM.A.S.03263 FAA STC ST<strong>01</strong>061SE 27.07.2009<br />
10030956 HEATH TECNA, INC. FAA STC ST02067SE B747-400 LCD Monitor installation on Boeing Model 747- None The Supplemental Instructions for 16.07.2<strong>01</strong>0<br />
400 series aircraft inaccordance with Heath<br />
Continued Airworthiness, Heath<br />
Tecna, Inc. Master Drawing List HPD-DL-<br />
TecnaDocument HTM957, Revision A,<br />
136,Revision E, dated May 5, 2<strong>01</strong>0, or later<br />
dated March 1, 2<strong>01</strong>0, or later FAA-<br />
FAA approved revisions.Validation of FAA STC<br />
acceptedrevision must be incorporated<br />
ST02067SE<br />
into the operator's maintenance program.<br />
10030973 HEATH TECNA, INC. FAA STC ST02066SE B747-400 Seat Installation and interior reconfiguration on<br />
Boeing Model 747-400series aircraft in<br />
accordance with Heath Tecna, Inc. Master<br />
Drawing ListHPD-DL-137, Revision B dated<br />
May 11, 2<strong>01</strong>0, or later FAA approvedrevisions.<br />
Validation of FAA STC ST02066SE<br />
None The Supplemental Instructions for<br />
Continued Airworthiness, Heath<br />
TecnaDocument HTM960, Revision E,<br />
dated May 20, 2<strong>01</strong>0, or later <strong>EASA</strong><br />
approvedrevision must be incorporated<br />
into the operator's maintenance<br />
program.Concurrent installation of<br />
Rockwell Collins S<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 268/<strong>462</strong><br />
19.11.2008<br />
15.08.2005<br />
30.05.2005<br />
<strong>01</strong>.09.2005<br />
29.08.2007<br />
24.10.2007<br />
16.03.2009<br />
19.07.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035106 HEATH TECNA, INC. FAA STC ST02072SE A330-2<strong>01</strong>, A330-202, A330-203 Installation of New J Class Crew Rest for none Prior to installation of this modification it 26.05.2<strong>01</strong>1<br />
A330-223, A330-243<br />
Qantas Airlines A330-200seriesThis STC<br />
must be determined thatthe<br />
installs a removable crew rest curtain and<br />
interrelationship between this modification<br />
curtain header<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039535 HEATH TECNA, INC. FAA ST02227SE 747-400 Installation of 2 new avionics racks in the EE Approval of this change applies to Boeing 747- Instructions for Continued Airworthiness<br />
bay of a Boeing 747-400series aircraft in 400 aircraft listed inHPD-DL-162 Rev.A, dated Heath Tecna Inc. Doc HTM<br />
accordance with Heath Tecna Inc. Master Data April 12, 2<strong>01</strong>2 or later approved revisions only 10<strong>04</strong>,Revision B, dated April 4, 2<strong>01</strong>2<br />
ListHPD-DL-162 Rev. A, dated April 12, 2<strong>01</strong>2<br />
must be incorporated into the<br />
or later approved revision.<br />
operatorsmaintenance program. Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship be<br />
10<strong>01</strong>4<strong>04</strong>0 HEATHTECNA <strong>EASA</strong>.A.S.<strong>01</strong>114 B767-300 SERIES Introduction of Stowage 4B and infill panel to<br />
British Airways aircraft as defined in the<br />
modification definition document and<br />
Declaration of Design and Performance (DDP)<br />
10<strong>01</strong>4078 HEATHTECNA <strong>EASA</strong>.A.S.<strong>01</strong>170 B747-400 Reconfiguration of Cabin Interior from current<br />
387SIA passenger cabin configuration<br />
(16F+58B+313Y for RT 514) to a 383<br />
(12F+47B+324Y), Cathy Pacific Boing 747-400<br />
fleet standard passenger cabin configuration.<br />
10<strong>01</strong>4143 HEATHTECNA <strong>EASA</strong>.A.S.<strong>01</strong>261 B747-400 SN 25127 & 25128 Heath Techna Modification C943 - Cathay<br />
Interiors Modification.<br />
10<strong>01</strong>4298 HEATHTECNA <strong>EASA</strong>.A.S.<strong>01</strong>542 B767-300 Business Class Footstool Assemblies on British<br />
Airways Boeing 767-300<br />
As defined in DDP, Aircraft Serial MSN 26548.<br />
Zero Occupancy. For this modification to be<br />
accepted on an EU registered aircraft, requires<br />
the operator to confirm that all the associate<br />
FAA and Hong Kong CDA modifications have<br />
been <strong>EASA</strong> approved.<br />
1. As defined in DDP Aircraft Serial Numbers<br />
25172 & 25128.2. Zero Occupancy.3. For this<br />
modification to be accepted on an EU<br />
registered aircraft requires the operator to<br />
confirm that all the associated FAA &Hong<br />
King CAD modifications have been <strong>EASA</strong><br />
appro<br />
This STC is limited to S/N 24340, 24341,<br />
252<strong>04</strong>, 25444, 25442, 25732, 25826, 25828,<br />
25829, 27140, 24335, 24336, 25831 and<br />
10<strong>01</strong>4519 HEATHTECNA <strong>EASA</strong>.A.S.02600 REV 1 B747-400 Cathay Pacific B747 Cabin Re-Configuration<br />
25834.<br />
1. Restricted to MSN 27132, MSN 27069 &<br />
07.<strong>04</strong>.2008<br />
REV 1<br />
MSN 265522. Zero occupancy3. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraphs "Description" and<br />
"Associated Technical Documentation".<br />
Compat<br />
10<strong>01</strong>4998 HEATHTECNA <strong>EASA</strong>.A.S.03298 DC-9 SERIES Meridiana DC-9 Series Stow Bin Extension. Restricted to ASN 49247,49248, 49531,<br />
49669, 49740, 499<strong>01</strong>, 49902, 49903, 53064,<br />
49808, 53182, 49785, 49792, 49935, 49951,<br />
49854, 53<strong>01</strong>3.<br />
20.11.2007<br />
10<strong>01</strong>6868 HELICOPTER TECHNOLOGY COMPANY <strong>EASA</strong>.IM.R.S.<strong>01</strong>244 FAA STC SR<strong>01</strong>282LA MD HELICOPTERS 369A Installation of a Tail Rotor Blade Assembly. N/A 15.03.2007<br />
MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369H<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
(STC Classified as Basic by the FAA).<br />
10<strong>01</strong>5311 HELICOPTERES GUIMBAL <strong>EASA</strong>.E.S.<strong>01</strong>0<strong>01</strong> REV. 1 O-360-J2A Low Temperature Extension - STC<br />
None Prior to installation of this modification it 22.11.2<strong>01</strong>0<br />
<strong>EASA</strong>.E.S.<strong>01</strong>0<strong>01</strong><br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10039707 HELICOPTERS ITALIA S.R.L.<br />
UNIPERSON<br />
AS 365N2 Installation of Audio Voice Warning on Radar<br />
Altimeter Thales AHV-8(ref. Change HI-365-34-<br />
<strong>01</strong>).<br />
10.05.2<strong>01</strong>2<br />
11.02.2005<br />
26.07.2005<br />
24.08.2005<br />
11.10.2005<br />
Limited to S/N 6414 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 269/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7144 HELIKOPTER AIR TRANSPORT GmbH <strong>EASA</strong>.R.S.<strong>01</strong>247 EC 135 Installation of Laser Scannig Equipment Limited to SN 025, 050, 053, 072, 097, 127,<br />
128, 160, 168, 181, 182, 187, 196, 199, 205,<br />
210, 220, 221, 305, 308, 325, 359, 368<br />
and387.<br />
<strong>01</strong>.06.2006<br />
10027677 HELIKOPTER AIR TRANSPORT GMBH P-<strong>EASA</strong>.R.S.<strong>01</strong>499 EC 135 T1 (CDS)<br />
Engineering Order EO 85-002, dated 21 Installation does not constitute operational Prior to installation of this modification the 20.10.2009<br />
EC 135 T2 (CPDS)<br />
September 2009 "Replacement ofSiren Hooks approval.Approval of PCDS (Personal Carrying installer must determinethat the<br />
EC 135 T2+<br />
with Onboard Talon Systems".<br />
Device System) for external loadoperation interrelationship between this modification<br />
must be granted by the competent authority. and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10033490 HELIKOPTER AIR TRANSPORT GmbH EC 135 T1(CDS)<br />
Replacement of Onboard Talon System with Installation does not constitute operational Prior to installation of this modification it 25.<strong>01</strong>.2<strong>01</strong>1<br />
EC 135 T2(CPDS), EC 135 T2+ improved IAOSI hook AS 21-17<br />
approval. Approval of PCDS(Personal Carrying must be determined thatthe<br />
Device System) for external load operation interrelationship between this modification<br />
must begranted by the competent authority. and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034657 HELIKOPTER AIR TRANSPORT GmbH EC135 T2 Dual GNS430W Installation in Autopilot<br />
helicopter<br />
10<strong>01</strong>6751 HELI-LYNX <strong>EASA</strong>.IM.R.S.<strong>01</strong>078 TCCA STC SH05-8, ISSUE 1 EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
10<strong>01</strong>6752 HELI-LYNX <strong>EASA</strong>.IM.R.S.<strong>01</strong>079 SH<strong>04</strong>-27 EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
10<strong>01</strong>6818 HELI-LYNX <strong>EASA</strong>.IM.R.S.<strong>01</strong>183 SH05-41 EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
10<strong>01</strong>6819 HELI-LYNX <strong>EASA</strong>.IM.R.S.<strong>01</strong>184 SH05-40 EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
Installation of Anticipator of Govenor<br />
CablesAss.Refer to installation manual IM, PA<br />
<strong>04</strong> <strong>01</strong>5 91 <strong>01</strong> issue 1 or later approved<br />
Heli-Lynx AS 355 FX System modifications, as<br />
per Transport Canada STC n° SH<strong>04</strong>-27<br />
Installation of One or Two Concorde RG 355<br />
Laed-Acid Batteries accorging to TCCA STC<br />
SH05-41 issue N°2 approved September 09,<br />
2005<br />
Installation of Purolator De-icing Fuel Filter p/n<br />
1743640-<strong>01</strong><br />
The installation is limited to Aircraft Serial<br />
Numbers 0220 and 0221<br />
1. Refer to instructions for continued<br />
airworthiness ICA PA <strong>04</strong> <strong>01</strong>5 05 <strong>01</strong> issue 1 or<br />
later approved and associated maintenance<br />
instructions.2. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to i<br />
Refer to STC SH05-41 and Flight Manual<br />
Supplement<br />
This STC is the <strong>EASA</strong> validation of Transport<br />
Canada STC n0 SH05-40, issue 1, dated<br />
September 9*, 2005,<br />
The approval holder shall fulfill the<br />
obligations of Part 21,Paragraph<br />
21.A109.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 270/<strong>462</strong><br />
18.<strong>04</strong>.2<strong>01</strong>1<br />
10.10.2005<br />
<strong>04</strong>.<strong>04</strong>.2007<br />
16.03.2006<br />
25.<strong>04</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6938 HELI-LYNX <strong>EASA</strong>.IM.R.S.<strong>01</strong>326 TCCA STC SH05-20 ISSUE 2 EUROCOPTER FRANCE AS 350 AS350/AS355 Rear Shoulder Harness Installation of a Rear Shoulder Harness on<br />
<strong>04</strong>.09.2007<br />
EUROCOPTER FRANCE AS 350 Installation.(Modiciation approved by TCCA AS350B3 with the modification OP-3369<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE AS<br />
350B<br />
EUROCOPTER FRANCE AS 355<br />
SERIE<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
under STC SH05-20 Issue 2.)<br />
incorporated is not approved.<br />
10035276 HELI-ONE TCCA STC SH05-46 S-61N Sealed Lead Acid Battery Installation none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.06.2<strong>01</strong>1<br />
10027687 HELI-ONE (NORWAY) AS P-<strong>EASA</strong>.R.S.<strong>01</strong>307 AS332C<br />
AS332C1<br />
AS332L<br />
AS332L1<br />
10036393 HELI-ONE (NORWAY) AS AS332 L1/L2 Installation of STAR SAFIRE FLIR system<br />
consisting of external mount,internal and<br />
external cabling and installation of mission<br />
console inCabin.<br />
EFIS 520 Installation. None. Prior to installation of this modification the 21.10.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
Flight into known Icing Conditions prohibited. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.09.2<strong>01</strong>1<br />
10<strong>04</strong>0394 HELI-ONE (NORWAY) AS AS 332 L, AS 332 L1 Goodrich Dual Hoist Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.06.2<strong>01</strong>2<br />
10037034 HELI-ONE CANADA INC. S-61L & N Lower Housing Weld Repair Applicable only to Sikorsky S-61N Lower<br />
Housing Assembly Part No'sS6135-20670-9,<br />
S6135-20670-42, S6135-20670-43, S6135-<br />
20629-102,S6135-20629-1<strong>04</strong>.<br />
10<strong>01</strong>6796 HELI-ONE NORWAY AS <strong>EASA</strong>.IM.R.S.<strong>01</strong>149 - AS 332 L1 BPOL 332L1 Police equipment Installation Helicopter modified in accordance with this<br />
STC are not approved for NVG operations<br />
Prior to installation of this modification it 26.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 271/<strong>462</strong><br />
12.06.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0<strong>01</strong>0 HELI-ONE NORWAY AS REV. 2 EC225 LP Installation of LH or RH or both Vertical Day VFR Only; Flight into known icing None 29.10.2<strong>01</strong>2<br />
Reference Door.<br />
conditions prohibited;Category A operations<br />
prohibited;Operations requiring certification for<br />
Ditching prohibited;Power On VNE: 150 kts or<br />
lower as limited by PMV;Power Off VNE: 150<br />
kts or lower as limited by PMVMax ai<br />
10<strong>01</strong>7036 HELI-ONE USA <strong>EASA</strong>.IM.R.S.<strong>01</strong>460 FAA STC SH86<strong>01</strong>SW BELL 230 Installation of EDZ-705 EFIS four tube flight<br />
instrument System. (This STC was classified<br />
as Basic by the FAA and is approved usingthe<br />
Post Type Validation Principles.)<br />
10<strong>01</strong>7<strong>04</strong>2 HELI-ONE USA <strong>EASA</strong>.IM.R.S.<strong>01</strong>466 FAA STC SH5880SW REV2 BELL 230 Installation of SPZ-7000 DAFCS System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6843 HELI-TRADE CORPORATION <strong>EASA</strong>.IM.R.S.<strong>01</strong>219 SR<strong>01</strong>592SE BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 214ST<br />
BELL 412<br />
Installation and Maintenance of Goodrich<br />
Internal HoistFAA STC SR<strong>01</strong>592SE<br />
10<strong>01</strong>7279 HELI-UNION <strong>EASA</strong>.R.S.<strong>01</strong>525 AS 365 N GPS Stand alone BRNAV FREEFLIGHT TNL<br />
20<strong>01</strong>. Approach plus I/O Installation<br />
In order to operate the internal hoist in the<br />
referenced airframes, the following provision<br />
kits must be installed:HOIST P/N BELL<br />
PROVISION KIT # BELL SERVICE<br />
INSTRUCTION # HELICOPTER S/N<br />
EFFECTIVITYHTC-42305A 205-706-091-1<br />
BHT-205-SI-44<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>6727 HERITAGE AVIATION LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>028 FAA STC SR09407RC EUROCOPTER FRANCE EC 155 Installation of Forward and Aft Facing<br />
B1<br />
Passenger Couch<br />
10<strong>01</strong>6768 HERITAGE AVIATION LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>099 FAA STC SR00530NY EUROCOPTER FRANCE EC 155 Installation of a Cocoon wall panel system 1. This STC is approved only for the product<br />
B1<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>7029 HERITAGE AVIATION LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>448 FAA STC SH7733SW MD HELICOPTERS 369E Installation of enlarged instrument paqnel and Not compatible with the MDHI optional centre<br />
MD HELICOPTERS 369FF slant console. This STC has been classified as seat installation.<br />
MD HELICOPTERS 500N “BASIC” by the FAA and has been approved<br />
MD HELICOPTERS 600N under the PTVP.<br />
10<strong>01</strong>7<strong>04</strong>8 HERITAGE AVIATION LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>472 FAA STC SR09483RC MD HELICOPTERS 369E Heritage Aviation, Ltd. STC SR09483RC; 1. Applicable to MDHI 369E, 369FF, 500N<br />
MD HELICOPTERS 369FF Replacement Instrument Panel (including and 600N helicopters.2. Prior to installation<br />
MD HELICOPTERS 500N pedestal, shrouds and glare shield) on of this modification the installer must determine<br />
MD HELICOPTERS 600N applicable MDHI 369E, 369FF, 500N & 600N that the interrelationship between this<br />
helicopters.<br />
modification and any other previously installed<br />
modification will introduc<br />
10<strong>01</strong>7<strong>04</strong>9 HERITAGE AVIATION LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>473 FAA STC SR09484RC MD HELICOPTERS 369E<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 500N<br />
10<strong>01</strong>7068 HERITAGE AVIATION LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>5<strong>04</strong> FAA STC SR09481RC MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 500N<br />
MD HELICOPTERS 600N<br />
Heritage Aviation, Ltd. STC SR09484RC;<br />
Chelton EFIS installation on applicable MDHI<br />
369E, 369FF & 500N helicopters.<br />
10<strong>01</strong>6082 HOLLINGSEAD INTERNATIONAL <strong>EASA</strong>.IM.A.S.02266 FAA STC ST<strong>01</strong>879LA BOEING 747-400 SERIES Installation of B/E Aerospace Air Chiller P/N<br />
470-1<br />
1. Applicable to MDHI 369E, 369FF, 500N.2.<br />
Operation with the Chelton EFIS is limited to<br />
VFR only.3. (See limitations specified in RFM<br />
Supplement)4. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelations<br />
Heritage Aviation, Ltd. STC SR09481RC; 1. Applicable to MDHI 369E, 369F, 369FF,<br />
Installation of nose shelf on applicable MDHI 500N and 600N.2. Prior to installation of this<br />
369E, 369F, 369FF, 500N & 600N helicopters. modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed modification<br />
will introduce no a<br />
10<strong>01</strong>6189 HOLLINGSEAD INTERNATIONAL <strong>EASA</strong>.IM.A.S.02418 FAA STC ST00740LA-D BOEING 737-300 Installation of Smoke Detection and Fire<br />
Suppression Systems Provisions, Lower Cargo<br />
Compartments.<br />
10<strong>01</strong>6262 HOLLINGSEAD INTERNATIONAL <strong>EASA</strong>.IM.A.S.02541 FAA STC ST0<strong>04</strong><strong>04</strong>LA-D BOEING 737-400 Installation of Smoke Detection and Fire<br />
Suppression Systems Provisions, Lower Cargo<br />
Compartments.<br />
This approval is limited to airplanes on which<br />
C&D Zodiac Pantry P/N C4810<strong>01</strong>-1<strong>01</strong> has<br />
been installed in accordance with STC<br />
ST<strong>01</strong>880LA<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 272/<strong>462</strong><br />
13.05.2008<br />
05.06.2008<br />
03.10.2006<br />
16.03.2009<br />
20.07.2005<br />
18.07.2005<br />
<strong>01</strong>.<strong>04</strong>.2008<br />
19.03.2009<br />
19.03.2009<br />
19.03.2009<br />
23.<strong>01</strong>.2007<br />
09.10.2007<br />
14.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6300 HOLLINGSEAD INTERNATIONAL <strong>EASA</strong>.IM.A.S.02597 FAA STC ST02147LA BOEING 777-200 SERIES Installation of B/E Aerospace air Chiller P/N Applicable only to A/C with C&D Zodiac pantry<br />
18.06.2008<br />
470-1<br />
installation P/N C8<strong>01</strong>0<strong>01</strong>-1<strong>01</strong> and C8<strong>01</strong>0<strong>01</strong>-<br />
103 covered by FAA STC ST02144LA and<br />
<strong>EASA</strong> STC P-<strong>EASA</strong>.A.S.02421.<br />
10<strong>01</strong>6499 HOLLINGSEAD INTERNATIONAL <strong>EASA</strong>.IM.A.S.02861 FAA STC <strong>01</strong>835LA BOEING 767-200<br />
BOEING 767-300<br />
10<strong>01</strong>5343 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.0<strong>04</strong>42 REV 3 FAA STC ST00705SE BOEING 747-400, 747-200 Installation of the Enhanced Ground Proximity<br />
Warning System on a Boeing 747-200/-400<br />
aircraft.<br />
10<strong>01</strong>5348 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.0<strong>04</strong>98 FAA STC ST<strong>01</strong>124SE BOEING 747-400 SERIES Installation of the Flight Data Acquisition<br />
Management System<br />
10<strong>01</strong>5371 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong><strong>01</strong>4 REV 1 SEE STC LIST Installation of Honeywell TFE731-3D-1H or<br />
TFE731-3DR-1H Turbofan Engines.<br />
10<strong>01</strong>5377 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>051 REV 1 FAA STC NO ST02005CH-D LEARJET 55 Installation of Honeywell N1 Digital Electronic<br />
Engine Control (DEEC)Note: This revision<br />
reflects the transfer of STC<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>051 from Garrett Aviation<br />
Services to Honeywell International Inc.<br />
10<strong>01</strong>5<strong>462</strong> HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>209 FAA STC ST<strong>01</strong>298AT BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
Installation of mounting provisions and electrical Prior to installation of this modification the<br />
provisions for electronic flight bags.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Installation of Flight Data Aquistion &<br />
Management System (FDAMS) with Mark II<br />
Aircraft Communication & Reporting System<br />
1This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph ' Description'.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.For Boeing B747-20<strong>01</strong>.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Pitch & Roll Attitude is sampled one per<br />
second.2. Pneumatic power is sampled once<br />
every 4 seconds.<br />
10<strong>01</strong>5491 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>253 FAA STC ST00961AT BOEING 757-200 SERIES<br />
(ACARS)<br />
Installation of Flight Data Acquisition and<br />
Management System (FDAMS), FAA STC<br />
ST00961AT.<br />
10<strong>01</strong>5547 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>438 FAA STC SA3122SO BOEING 747 Honeywell International Inc. of Redmond, 1. Refer to Approval Report IVW/LTB/TCP-<br />
Washington, USA has applied for an STC to 05.5330542. This STC is approved only for<br />
cover the installation of a CAS81 Traffic the product configuration as defined in the<br />
Collision Avoidance System (TCAS) II with dual approved design data referred to in the<br />
TRA-67 Mode S transponders on Boeing 747- paragraph "Description". Compatibility with<br />
100/200/SP Series aircraft. The FAA has iss other aircraft/engine configurations sha<br />
10<strong>01</strong>5572 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>479 FAA STC SA00842WI-D BEECH 1900D Installation of the Honeywell Mark VI Enhanced AFMS 006-00875-0000 is required on-board<br />
Grounfd Proximity Warning System<br />
for operation with Beech 1900 D series<br />
10<strong>01</strong>5575 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>485 FAA STC SA2726SO DC-9-80 (MD-80) SERIES Installation of CAS-81 TCAS II SystemFAA<br />
STC SA2726SO<br />
10<strong>01</strong>5685 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>670 FAA STC SA<strong>01</strong>116WI-D PILATUS PC-12/45 Single or Dual Altimeters (FAA STC<br />
SA<strong>01</strong>116WI-D)<br />
10<strong>01</strong>5686 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>671 FAA STC SA<strong>01</strong>253WI-D PILATUS PC-12/45 RVSM (FAA STC SA<strong>01</strong>253WI-D issue dated PC-12/45: MSN 1<strong>01</strong> to 835 (except MSN<br />
20/02/2007)<br />
545)PC-12/47: MSN 684 to 835<br />
10<strong>01</strong>5745 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>776 FAA STC ST0<strong>04</strong>91SE BOEING DC-9-81 (MD-81) FAA STC ST0<strong>04</strong>91SE "Installation of the<br />
BOEING DC-9-82 (MD-82)<br />
BOEING DC-9-83 (MD-83)<br />
BOEING DC-9-87 (MD-87)<br />
BOEING MD-90-30<br />
Enhanced Ground Proximity Warning System"<br />
10<strong>01</strong>5756 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>790 ST<strong>01</strong>619SE BOEING 747-400 Introduction of Honeywell International Inc.<br />
Main/Nose Wheel pn. 26159<strong>01</strong>-1 and Carbon<br />
Brake pn. 2615902-1 in accordance with<br />
Honeywell Service Bulletin 26159<strong>01</strong>-32-<br />
0<strong>01</strong>_2615902-32-0<strong>01</strong> Revision New or later<br />
FAA-approved revision as replacement for<br />
Goodrich Br<br />
10<strong>01</strong>5805 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>870 FAA STC ST00705SE BOEING 747-100<br />
Installation of Honeywell Enhanced Ground<br />
BOEING 747-100F<br />
BOEING 747-300<br />
BOEING 747-SP<br />
Proximity Warning System (EGPWS).<br />
10<strong>01</strong>5806 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>871 FAA STC ST0<strong>01</strong>40AT AIRBUS A310-200<br />
Installation of MUA-45 Data Link System in<br />
AIRBUS A310-300<br />
Airbus A310-200 / -300 series aircraft.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 273/<strong>462</strong><br />
02.06.2008<br />
29.<strong>01</strong>.2007<br />
10.<strong>01</strong>.2005<br />
31.03.2008<br />
02.<strong>04</strong>.2009<br />
30.06.2006<br />
29.06.2005<br />
17.08.2005<br />
28.11.2005<br />
02.05.2006<br />
15.05.2007<br />
15.05.2007<br />
05.03.2007<br />
22.03.2006<br />
06.09.2007<br />
12.<strong>04</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5847 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>947 FAA STC ST0<strong>04</strong>17SE BOEING 767-200<br />
Installation of Enhanced Ground Proximity Honeywell International Inc. Airplane Flight<br />
07.<strong>04</strong>.2006<br />
BOEING 767-300<br />
Warning System (EGPWS)<br />
Manual Supplements 060-4189-003 Revision<br />
BOEING 767-300F<br />
B, 060-4189-<strong>01</strong>4 Revision A, 060-4189-008<br />
Revision A, 060-4189-037 Initial Revision, 060-<br />
4189-052 Revision A, 060-4189-<strong>01</strong>3 Initial<br />
Revision, 060-4189-068 Revision A, 060-4<br />
10<strong>01</strong>5893 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02<strong>01</strong>3 FAA STC ST0<strong>04</strong>46SE DC-9-80 (MD-80) SERIES Installation of the Honeywell Solid State Flight<br />
Data Recorder<br />
-- 11.09.2006<br />
10<strong>01</strong>5921 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02054 FAA STC ST00389SE BOEING 737-200<br />
Installation of the Honeywell Enhanced Ground - Approval of this change in type design applies<br />
28.02.2007<br />
BOEING 737-300<br />
proximity Warning System (EGPWS) and to the BOEING 737-200/ -300/ -400/ -500/ -<br />
BOEING 737-400<br />
Runway Awareness & Advisory System 700/ -800/-900 aircraft equipped with either a<br />
BOEING 737-500<br />
(RAAS).<br />
flight management system (FMS) or a global<br />
BOEING 737-700<br />
positioning system (GPS) based navigation<br />
BOEING 737-800<br />
BOEING 737-900<br />
system or an EGPWS equipped with<br />
10<strong>01</strong>5934 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02072 FAA STC ST00255DE-D BAE 146/AVRO 146 SERIES Installation of Allied Siganl VHF AFIS -- 26.09.2006<br />
10<strong>01</strong>5946 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02088 FAA STC ST<strong>01</strong>000SE BOEING 737-600<br />
Installation of the Mark II Aircraft<br />
1. Compatibility of this design change with<br />
09.10.2006<br />
BOEING 737-700<br />
Communications Addressing and Reporting other previously approved modifications must<br />
BOEING 737-800<br />
System (ACARS) in the Boeing 737-600, -700, be determined by the installer.<br />
BOEING 737-900<br />
-800, -900Series Aircraft.<br />
10<strong>01</strong>5949 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02091 FAA STC ST<strong>01</strong>424CH-D HAWKER 125 -800 SERIES Installation of Honeywell N1 Digital Electronic<br />
<strong>04</strong>.10.2006<br />
HAWKER 125 -850XP SERIES Engine Control (DEEC)<br />
10<strong>01</strong>5962 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02110 FAA STC ST00844SE BAE 146/AVRO 146 SERIES Installation of the Flight Data Acquisition This change is not JAR-OPS-1.715<br />
13.12.2006<br />
Management System (FDAMS)<br />
(EUROCAE ED55) compliant in the following<br />
parameters:Parameter 6, Pitch Attitude is only<br />
sampled once per second.Parameter 7, Roll<br />
Attitude is only sampled once per<br />
second.Parameter 23, Ground Spoiler position,<br />
Brake Select<br />
10<strong>01</strong>6<strong>04</strong>2 HONEYWELL INTERNATIONAL Inc. <strong>EASA</strong>.IM.A.S.02213 FAA STC ST<strong>01</strong>003CH-D 600A, 600B, 700A, 700B Installation of Honeywell N1 Digital Electronic 1. Compatibility of this modification with other<br />
12.12.2006<br />
DH. 125 SERIES 1A, 3A, 3A/RA, Engine Control (DEEC).<br />
previously approved modifications must be<br />
F3B, F3B/RA, 400A, 400B, 403B,<br />
determined by the installer2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Desc<br />
10<strong>01</strong>6089 HONEYWELL INTERNATIONAL Inc. <strong>EASA</strong>.IM.A.S.02276 FAA STC SA6086NM BOEING 767-300 Installation of Honeywell/Racal Aeronautical<br />
SATCOM<br />
10<strong>01</strong>6115 HONEYWELL INTERNATIONAL Inc. <strong>EASA</strong>.IM.A.S.02306 FAA STC SA5473NM BOEING 747-100-400 Installation of Honeywell/Racal Aeronautical<br />
Satelite Communication system<br />
10<strong>01</strong>6173 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02400 FAA STC ST00717WI BOEING 737-200 SERIES<br />
BOEING 737-500<br />
BOEING B737-300<br />
BOEING B737-400<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Approval of this type design applies only to<br />
Boeing 747 series aircraft when:1. Provisions<br />
for this SATCOM installation have been<br />
installed and approved in accordance with this<br />
STC, or2. Provisions for this SATCOM<br />
installation have been installed and<br />
Installation of the Honeywell Mark II ACARS Compatibility of this design change with<br />
previously approved modifications must be<br />
determined by the installer.If the holder agrees<br />
to permit another person to use this certificate<br />
to alter the product, the holder shall give the<br />
other person written eviden<br />
10<strong>01</strong>6195 HONEYWELL INTERNATIONAL Inc. <strong>EASA</strong>.IM.A.S.02433 FAA STC ST00361LA GULFSTREAM IV Installation of the Honeywell HUD-2020 Head Prior to installation of this modification the<br />
up Display System on Gulfstream G-IV aircraft installer must determine that the<br />
for Category II approach criteria.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6402 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02731 FAA STC ST00381SE BOEING 757 Installation of Enhanced Ground Proximity 1. Approval of this change in type design<br />
Warning System in B-757 Series<br />
applies to the above model aircraft equipped<br />
Aircraft.Approval applies to aircraft equipped with either a flight management system (FMS),<br />
with a flight management system, which meets which meets AC90-45A, or an EGPWS with a<br />
AC90-45A, or an EGPWS with a GPS based global positioning system (GPS) based<br />
navigation system or an EGPWS equipped<br />
with an inter<br />
navigation system or an EGPWS equipped wi<br />
10028540 HONEYWELL INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.03210 BOEING 747-400<br />
BOEING 747-400F<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 274/<strong>462</strong><br />
21.12.2006<br />
10.<strong>04</strong>.2007<br />
21.05.2007<br />
18.02.2009<br />
11.<strong>04</strong>.2008<br />
16.07.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031536 HONEYWELL INTERNATIONAL INC. P-<br />
FAA STC ST<strong>01</strong>280SE B737-600/-700/-800/-900 Installation of the XK516 HF Transceiver None Prior to installation of this modification it 24.08.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>131<br />
System in accordance withMaster Drawing List<br />
must be determined thatthe<br />
756-<strong>01</strong>73-0<strong>01</strong> (and FAA STC ST<strong>01</strong>280SE<br />
interrelationship between this modification<br />
dated 15 October2003)<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034246 HONEYWELL INTERNATIONAL INC. FAA STC SR02114NY-D EC135 P2(CPDS), EC135 P2+<br />
EC135 T2(CPDS), EC135 T2+<br />
Installation of a Honeywell Model 15175 VXP<br />
SystemThe Honeywell Model 15175 VXP<br />
System is a Health and Usage<br />
MonitoringSystem that monitors vibration<br />
characteristics of the aircraft toprovide data to<br />
aid aircraft maintenance. The information<br />
provided bythe<br />
10038956 HONEYWELL INTERNATIONAL INC. FAA STC ST00806AT B767-200/ -300 Installation of Aircraft Communications<br />
Addressing and Reporting System(ACARS)<br />
Mark II.<br />
10<strong>01</strong>5981 HORTON STOL-CRAFT INC. <strong>EASA</strong>.IM.A.S.02133 FAA STC SA989CE CESSNA 170A<br />
CESSNA 170B<br />
Installation of STOL Kit(Wing leading edge<br />
cuffs, drooped tips, stall fences and aileron gap<br />
seals)<br />
10<strong>01</strong>6763 HOWARD J. FULLER, JR. <strong>EASA</strong>.IM.R.S.<strong>01</strong>092 FAA STC SR00081BO SCHWEIZER 269 C-1 Operation of rotorcraft on unleaded and leaded<br />
automotive gasoline, 93 minimum antiknock<br />
index (RON+MON)/2 per ASTM Specification<br />
D-439 or D-4814 as noted on placard to be<br />
installed in accordance with H.J.Fuller Jr.<br />
Installation Instructions No. HFJ97269,<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.03.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.03.2<strong>01</strong>2<br />
1. Aircraft to be placarded "Intentional Spins<br />
Prohibited".2. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configur<br />
1. This STC is limited to those model<br />
helicopters equipped with Lycoming HO-360-<br />
C1A engines, modified in accordance with FAA<br />
STC No. SE2563CE.2. Howard J. Fuller, Jr.<br />
Rotorcraft Flight Manual Supplement No. 269-<br />
1, Rev 2 dated July 2, 20<strong>04</strong>, or later approve<br />
10<strong>04</strong>1028 HOWARD J. FULLER, JR. REV. 1 FAA STC SR00086BO R44 Operation of rotorcraft on unleaded automotive 1. This approval is limited to those model<br />
gasoline, 91 minimumantiknock index (RON + helicopters equipped withLycoming O-540-<br />
MON)/2 per ASTM Specification D-439 or D- F1B5 engines modified IAW STC<br />
4814 inaccordance with Howard. J. Fuller SE00663WI(<strong>EASA</strong>.IM.E.S.<strong>01</strong>002). This<br />
Installation Instructions No HJF97<strong>04</strong>4.(This approval is applicable only with the<br />
STC is based on FAA STC SR00086BO dated followingengine power ratings:-,,Maximum<br />
Continuous Power 205 HP (24.7<br />
10<strong>01</strong>5608 HYDRO-AIRE, INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>544 FAA STC SA3339WE BEECH 200, SUPER KING AIR<br />
KING AIR 200<br />
Installation of Power Brake / Skid Control<br />
System<br />
1. Models 200: Hydro-Aire Airplane Falight<br />
Manual Supplement dated on 17 MAY 1977 or<br />
later approved revision.2. Models B200: Hydro-<br />
Aire Airplane Flight Manual Supplement No.<br />
R13-0<strong>01</strong>-100-05 dated 12 MAY 2005 or later<br />
approved revision.3. This STC is approve<br />
<strong>04</strong>.09.2006<br />
23.11.2005<br />
Prior to installation of this modification it 17.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4561 IBERIA LINEAS AEREAS DE ESPANA <strong>EASA</strong>.A.S.02661 AIRBUS A321-212 Passenger Cabin Lay-Out Modification for -- 05.09.2006<br />
SOCI<br />
Special Flight<br />
10029481 ICELANDAIR B757-200 Navigation - Dependant Position Determining - None. Prior to installation of this modification it 26.03.2<strong>01</strong>0<br />
Activation of the ADS-Bout function of the<br />
must be determined thatthe<br />
Transponder system.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030954 ICELANDAIR GA8 AIRVAN Installation of TopScan Camera System Only applicable for aircraft / preconditions as<br />
defined in EngineeringOrder, Doc. No. EO-<br />
GTA-2520-03, Rev. IR, dated 28-Jun-2<strong>01</strong>0, or<br />
laterapproved revision.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentationPrior to installation of this<br />
modification it must be determined<br />
thatthe ,,interrelationship<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 275/<strong>462</strong><br />
02.09.2005<br />
15.07.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038270 ICELANDAIR B757-200 Installation of Satcom and Flight Tracking None. Prior to installation of this modification it 02.02.2<strong>01</strong>2<br />
System.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5254 ICELANDAIR TECHNICAL SERVICES <strong>EASA</strong>.A.S.03700 BOEING 757-200 Reconfigure seating layout to 52/10 Pax<br />
arrangement (VIP & Lounge)<br />
10038368 IMAGIK INTERNATIONAL<br />
CORPORATION<br />
FAA STC NO. ST03400AT BOEING 767-200/-300 Installation of IMAGIK LCD Entertainment<br />
Monitors.<br />
10<strong>01</strong>5207 INAER AVIATION ITALIA S.p.A. <strong>EASA</strong>.A.S.03620 REV. 1 CESSNA 500 STC <strong>EASA</strong>.A.S.03620 dated 2 June 2009<br />
"Satellite Telephone System"<br />
10032602 INAER AVIATION ITALIA S.p.A. REV. 1 CESSNA 650 (CITATION VI) Enhanced Ground Proximity Warning System<br />
(EGPWS) Honeywell MK<br />
VIIIinstallation.Honeywell EGPWS MK VIII<br />
installation in replacement of Honeywell GPWS<br />
MKVI.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
15.12.2008<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.02.2<strong>01</strong>2<br />
None 1. Prior to installation of this modification 23.02.2<strong>01</strong>2<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
STC is applicable to S/N 650-0216 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.09.2<strong>01</strong>1<br />
10038266 INAER AVIATION ITALIA S.p.A. CL-215-6B11 (CL415 VARIANT) Elementary Surveillance Mode S Diversity<br />
TranspondersUpgrade/Replacement and<br />
Installation of new transponders with<br />
Elementary Surveillance and Diversity<br />
capabilities.<br />
None. None. <strong>01</strong>.02.2<strong>01</strong>2<br />
10<strong>01</strong>7095 INAER MAINTENANCE S.A.U. <strong>EASA</strong>.R.S.<strong>01</strong><strong>01</strong>0 212, 412, 412EP, AB212, AB412 Installation of external Cargo basket for "Bambi In accordance with RFM CMA005AFMS E1<br />
23.05.2006<br />
Bucket"<br />
R0 Supplement<br />
1003<strong>01</strong>30 INAER MAINTENANCE S.A.U. BELL 412EP Installation of Weather Radar Bendix-King None. Prior to installation of this modification the 26.05.2<strong>01</strong>0<br />
model RDR1400C in Bell 412EPhelicopters.<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
10034643 INAER MAINTENANCE S.A.U. <strong>EASA</strong>.R.S.<strong>01</strong><strong>01</strong>9 AS 365N3 Adaption of a FLIR ULTRA 4000 system FLIR ULTRA 4000 must be previously fitted Prior to installation of this modification the 20.05.2009<br />
installation provisions for a FLIRULTRA according to the STC FUR ULTRA4000 - installer must determinethat the<br />
FORCE II. This modification is a minor change 365N3 REF. AHSE-50300 of ASTEC interrelationship between this modification<br />
of the STC FLIRULTRA 4000 - 365N3 REF. HELICOPTER SERVICES AS<br />
and any otherpreviously installed<br />
AHSE-50300 of ASTEC HELICOPTER<br />
modification will introduce no adverse<br />
SERVICES AS,keeping the supporting<br />
effect uponthe airworthiness of the<br />
structure and the electrical<br />
product. The installati<br />
10035000 INAER MAINTENANCE S.A.U. SA330J Modification of transponder wiring installation to None Prior to installation of this modification it 18.05.2<strong>01</strong>1<br />
comply with <strong>EASA</strong> ADNo 2<strong>01</strong>0-0067<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 276/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038296 INAER MAINTENANCE S.A.U. DGAC-E NO 138 1. BELL 206B, 206L<br />
Transfer of STC "DGAC-E No. 138"<br />
None Prior to installation of this modification it 08.03.2<strong>01</strong>2<br />
2. AB206B<br />
(Certificado de componente aeronáuticoNo.<br />
must be determined thatthe<br />
138 de 09-08-1996), Power lines cleaning<br />
interrelationship between this modification<br />
system with high pressurewater with "DGAC-E<br />
and any other previouslyinstalled<br />
Certificate Data Sheet No. 138" from<br />
modification and/ or repair will introduce<br />
Heliservicio toInaer Maintenance S.A.U. (DOA<br />
no adverse effectupon the airworthiness<br />
No. <strong>EASA</strong>.21J.1<br />
of the product.<br />
10<strong>04</strong>0333 INAER MAINTENANCE S.A.U. P.68 C<br />
P.68 OBSERVER<br />
P.68 OBSERVER 2<br />
"External load mount". Installation of a mount to<br />
hold external loads inthe existing<br />
photogrammetric hatch, according to<br />
Certification Plan"INAER.M11/037/25-PdC",<br />
Revision 0, Date: 21/06/2<strong>01</strong>2.<br />
10<strong>04</strong>0926 INAER MAINTENANCE S.A.U. REV. 1 B200GT "Stretcher kit Avfab 32-<strong>01</strong>17". Installation of a<br />
stretcher kit replacingLH seats (rows 2 and 3),<br />
according to Certification Plan<br />
"INAER.M12/<strong>04</strong>4/25-PdC", Revision 0, Date:<br />
27/07/2<strong>01</strong>2.<br />
10029799 INDIGOSAT 208 / 208B Installation of IndigoOne Satellite Tracking and<br />
Communication System(Kit Part No.<br />
IGO1_MA1236_<strong>01</strong>R1-1) in accordance with<br />
CASA (Australia)STC SVA 513<br />
10<strong>01</strong>6562 INFINION CERTIFICATION<br />
ENGINEERING<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.06.2<strong>01</strong>2<br />
None The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe interr<br />
Effected S/N see in Installation Manual IS-IM-<br />
2007-0<strong>01</strong>, Issue C<br />
<strong>EASA</strong>.IM.A.S.02948 REV. 1 TCCA STC SA06-30 BAE JETSTREAM 3100 Concorde RG-380 Battery Installation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5538 INFLIGHT CANADA Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>422 REV. 1 TCCA STC C-LSA95-037/D AIRBUS A320-232 SONY TRANS COM Passenger Entertainment<br />
System installationNote: This STC had to be<br />
revised due to a correction to the holder of the<br />
original STC.<br />
10<strong>01</strong>6609 INFLIGHT CANADA Inc. <strong>EASA</strong>.IM.A.S.03029 TCCA STC O-LSA03-127/D BOMBARDIER CL-600-2B19 Honeywell SCS-1000 Mini-M Aero SATCOM<br />
System and Securaplane Camera Installation.<br />
10027294 INFLIGHT CANADA Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03187<br />
REV. 4 TCCA STC SA09-28 737-800 Rockwell Collins dPAVES Overhead<br />
Passenger Entertainment System, TCCASTC<br />
Number: SA09-28 Issue 3 dated Nov 16, 2009.<br />
This revision consistsin removing the limitation<br />
on EWIS ICA<br />
10030534 INFLIGHT CANADA Inc. REV. 1 TCCA STC O-LSA08-<strong>04</strong>5/D 767-300 Audio Video on Demand (AVOD) and In-Seat<br />
Power Supply (ISPS) SystemInstallation<br />
1. This STC is limited to the A320 MSN's 496<br />
and 5252. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations<br />
1. DECA Aviation / Inflight Canada<br />
Modification Summary MS03055, Revision 4,<br />
dated 16 October 20<strong>04</strong>, or later approved<br />
revision.2. DECA Aviation / Inflight Canada<br />
Instructions for Continued Airworthiness<br />
ICA03055, Revision 2, dated 12 October 20<strong>04</strong>,<br />
or<br />
08.08.2<strong>01</strong>2<br />
Prior to installation of this modification it 21.<strong>04</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.09.2008<br />
27.11.2006<br />
<strong>04</strong>.12.2008<br />
<strong>04</strong>.06.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.09.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 277/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>1380 INFLIGHT WARNING SYSTEMS, Inc. FAA STC ST02300LA B777-200, 200LR, 300, 300ER Validation of FAA STC ST02300LA related to None. Prior to installation of this modification it 12.09.2<strong>01</strong>2<br />
Installation of Fan VibrationMonitor Unit.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1522 INFLIGHT WARNING SYSTEMS, Inc. A318-111/-112/-121/-122<br />
A319-111/-112/-113/-114/-115<br />
A319-131/-132/-133<br />
A320-111/-211/-212/-214<br />
A320-231/-232/-233<br />
A321-111/-112/-131/-211/-212<br />
A321-213/-231/-232<br />
10<strong>01</strong>7143 ING. MIROSLAV RUSINAK S.R.O. <strong>EASA</strong>.R.S.<strong>01</strong>246 BELL 427 Installation of the articulated patient loading<br />
system into Bell 427 rotorcraft.<br />
Installation of Inflight Warning System Fan None Prior to installation of this modification it 25.09.2<strong>01</strong>2<br />
Vibration Monitor Unit (VMU)model n. 2160<strong>01</strong>-<br />
must be determined thatthe<br />
400<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
427-706-020-1<strong>01</strong> – Bell Helicopter Textron<br />
Cabin Hardpoints Provision Kit must be<br />
installed (BHT-427-II-27 rev 0 dated 16<br />
September 20<strong>04</strong>) prior to installation of this<br />
STC.STC <strong>EASA</strong>.IM.R.S.00548 or<br />
<strong>EASA</strong>.IM.R.S.00577 (FAA STC SR02381AT)<br />
– Installation of Pass<br />
10038518 ING. MIROSLAV RUSINAK S.R.O. P-<strong>EASA</strong>.R.S.<strong>01</strong>416 BELL 427 Support unit for medical devices None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.02.2<strong>01</strong>2<br />
10027603 INGENIEURBUERO FUER LUFTFAHRT P-<strong>EASA</strong>.R.S.<strong>01</strong>447 AS350 B1, B2, B3<br />
AS355 E, F, F1, F2, N, NP<br />
Installation of airborne laser scanning<br />
equipment in AS350/355 serieshelicopter<br />
10<strong>01</strong>5589 INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>500 TCCA/LSTC Q-LSA05-029/D BOMBARDIER BD-700-1A10 Miscellaneous modifications to cabin interior 1. Limited to S/N 9<strong>01</strong>72. Regarding the<br />
and installation of Electronic Flight Bag System installation of the Electronic Flight Bag System<br />
provisions for BD700-1A10 Global Express the design covers only the mounting device<br />
Acc.: MDL-05103002 Rev. B or later TCCA and its connection to the aircraft. The<br />
approved rev.Validation of imported<br />
suitability, integrity or accuracy of the EFB<br />
TCCA/LSTC: Q-LSA05-029/D<br />
hardware, software, database, dis<br />
10<strong>01</strong>59<strong>04</strong> INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.02030 TCCA LSTC Q-LSA06-026/D ISS 1 BD-700-1A10 Modification of EGPWS Radar Altimeter<br />
Callouts and installationof the IPOD on ACSN<br />
9163Valdiation of TCCA Limited STC Q-<br />
LSA06-26/D to S/N 9163MDL: 26126002 Rev<br />
NC or later approved revisionsTCCA SoC:<br />
NAI5<strong>01</strong>2-06-0063 dated June 20, 2006<br />
10<strong>01</strong>6130 INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.02324 TCCA STC Q-LSA06-<strong>01</strong>8D BOMBARDIER BD-700-1A10 Re-Locate Electronic Flight Bag and<br />
Miscellaneous Cabin Modifications in Cockpit<br />
of SN 9145Validation of TCCA Limited STC<br />
Q-LSA06-<strong>01</strong>8/D to S/N 9145MDL: 26115002<br />
Rev A or later TCCA approved<br />
revisionsCompliance Plan: CP26115-0<strong>01</strong><br />
10<strong>01</strong>6228 INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.02480 TCCA STC Q-LSA07-029/D BD-700-1A11 Installation of Photosmart printer and<br />
installation of additional handset for in the aft<br />
lhs of SN 92<strong>04</strong>Validation of TCCA Limited STC<br />
Q-LSA07-029/D to S/N 92<strong>04</strong><br />
10<strong>01</strong>6277 INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.02566 Q-LSA07-035/D BD-700-1A11 Miscellaneous Cabin Modifications on SN<br />
9188Validation of TCCA Limited STC Q-<br />
LSA07-035/D to S/N 9188MDL:<br />
MDL27124002Compliance Plan: CP27124-0<strong>01</strong><br />
Rev. A<br />
10<strong>01</strong>6407 INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.02737 TCCA STC Q-LSA08-0<strong>01</strong>/D BOMBARDIER BD-700-1A10 Replacement of conference table in aircraft<br />
S/N 9197, aft cabin.<br />
19.02.2007<br />
Service Bulletin No. 25.00.62 is a prerequisite Prior to installation of this modification it 13.10.2009<br />
and must be installedprior this modification Any must be determined thatthe<br />
alteration of installed equipment leads to interrelationship between this modification<br />
noncompliance ofcommitted and approved and any other previouslyinstalled<br />
design and therefore requires reinvestigation modification and/ or repair will introduce<br />
undchange approval prior use.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9197With this modification<br />
incorporated Aft LSH forward facing double<br />
seats must not be occuped durint taxi take off<br />
and landing.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 278/<strong>462</strong><br />
18.11.2005<br />
28.07.2006<br />
22.03.2007<br />
21.<strong>01</strong>.2008<br />
12.10.2007<br />
19.03.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6508 INNOTECH AVIATION <strong>EASA</strong>.IM.A.S.02875 TCCA Q-LSA08-021/D BOMBARDIER CL-600-2B16 (CL- Cabin Finishing Refurbish on aircraft S/N 5442. 1. Restricted to ASN 5442.2. Prior to<br />
06.10.2008<br />
6<strong>04</strong><br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification andany other previously<br />
installed modification will introduce no adverse<br />
effect upon the airworthiness<br />
10031405 INNOTECH AVIATION REV. 1 TCCA STC O-LSA10-185/D BD-700-1A10, ASN 9287 HB-JGE I-Ku System Installation with Viasat VMT 1500<br />
Ku Band System andHoneywell MHC Cabin<br />
Management.<br />
10031686 INNOTECH AVIATION TCCA STC SA10-18 BD-700-1A10 I-CAIR System Installation with JetAir Bio-<br />
Protection (BPS) System<br />
10031791 INNOTECH AVIATION REV. 2 TCCA STC N° C-LSA10-022/D BD-700-1A10 Installation, Complete Custom Aircraft Interior Restricted to ASN 9352.1. Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced FCOMS.2.<br />
WLAN system is compatible only to IEEE<br />
802.11(b).<br />
10032531 INNOTECH AVIATION REV.1 TCCA STC NO. C-LSA10-207/D BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9374<br />
10035813 INNOTECH AVIATION TCCA STC Q-LSA06-059/D BD-700-1A10 Cabin Management System Upgrade - ASN<br />
9020<br />
Restricted to ASN 9287 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.05.2<strong>01</strong>1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.09.2<strong>01</strong>0<br />
Restricted to ASN 93741.Refer to the<br />
Limitations sections of the required AFM<br />
Supplement andto the referenced<br />
FCOMS.2.WLAN system is compatible only to<br />
IEEE 802.11(b).<br />
Prior to installation of this modification it 31.<strong>01</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 17.<strong>01</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9020 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.07.2<strong>01</strong>1<br />
10036090 INNOTECH AVIATION TCCA STC O-LSA07-336/D BD-700-1A10 ICG BD700 Satcom Upgrade. Restricted to ASN 9028. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>1<br />
10036091 INNOTECH AVIATION TCCA STC O-LSA08-197/D BD-700-1A10 Software and DLNA Upgrade to Existing HSD-<br />
400 Satcom Installation.<br />
10036347 INNOTECH AVIATION TCCA STC C-LSA11-079/D BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9399<br />
Restricted to ASN 9028. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>1<br />
Restricted to ASN 9399The wireless Local<br />
Area Network (WLAN) System is intended to<br />
provideinternet connectivity and email services<br />
to the airplane’s cabin usingportable electronic<br />
devices (PEDS). Any other intended function of<br />
thisequipment will require a<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 279/<strong>462</strong><br />
02.09.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036823 INNOTECH AVIATION TCCA STC NO. SA10-8 BD-700-1A10 I-KU System Installation with VIASAT VMT None Prior to installation of this modification it 10.10.2<strong>01</strong>1<br />
1500 KU Band System<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037477 INNOTECH AVIATION BD-700-1A10 Installation, Complete Custom Aircraft Interior -<br />
ASN 9416<br />
10<strong>04</strong>0515 INNOTECH AVIATION TCCA STC NO. Q-LSA07-<strong>04</strong>0/D BD-700-1A10 Installation of Iridium Phone System and<br />
interior modification - ASN9028<br />
10<strong>04</strong>0920 INNOTECH AVIATION REV. 1 TCCA STC C-LSA12-105 BD-700-A110 Installation, Complete Custom Aircraft Interior -<br />
ASN 9433<br />
10033170 INNOVATIVE SOLUTIONS AND<br />
SUPPORT, I<br />
10036223 INNOVATIVE SOLUTIONS AND<br />
SUPPORT, I<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03020<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03107<br />
FAA STC ST02372CH B757-200/-300 Installation of Integrated Flat Panel Display<br />
10<strong>01</strong>6867 INTEGRATED FLIGHT SYSTEMS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>243 FAA STC SH3509SW EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
C<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
D1<br />
EUROCOPTER FRANCE EC 130<br />
10029611 INTEGRATED FLIGHT SYSTEMS, INC P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>407<br />
System (IFPDS) and L-3Avionics Systems GH-<br />
3100 Electronic Standby Instrument System<br />
(ESIS)<br />
Restricted to ASN 9416.Refer to the<br />
Airworthiness Limitations contained in the<br />
requiredAirplane Flight Manual<br />
Supplements.The Wireless LAN System is<br />
intended to provide internet connectivity<br />
andemail services to the airplane’s cabin using<br />
portable electron<br />
Prior to installation of this modification it 29.11.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9028.Previous installation of Prior to installation of this modification it 06.07.2<strong>01</strong>2<br />
<strong>EASA</strong> STC No. 10039790 and <strong>EASA</strong> STC No. must be determined thatthe<br />
10039791are pre-requisites.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9433.The Wireless LAN<br />
System is intended to provide internet<br />
connectivity andemail services to the airplane's<br />
cabin using portable electronic devices(PEDs).<br />
Any other intended function of this equipment<br />
will require are-examination of the<br />
FAA STC ST02165NY B767-200/-300/-300F Installation of Flat Panel Display System Installation Configuration #6 approved only.The<br />
Smiths Aerospace Limited Integrated Standby<br />
Instrument System (ISIS)is not approved for<br />
installation under this STC.No earlier revisions<br />
of the listed documents are approved under<br />
thisSTC.<br />
Installation of a Belt Driven Freon Air<br />
Conditioning System (FAA STC SH3509SW).<br />
REV. 1 STC SR09178RC<br />
B4<br />
600N Integrated Flight Systems Vapor Cycle Air<br />
Conditioning System<br />
Prior to installation of this modification it 09.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Approved Installation Configuration #9 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.12.2<strong>01</strong>0<br />
1. VFR Operations only2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraphs "Description" and<br />
“Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine con<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.08.2<strong>01</strong>1<br />
26.<strong>04</strong>.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.06.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 280/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong><strong>01</strong>83 INTERNATIONAL ENGINEERING<br />
F177RG IEA/STC/ERHC/<strong>01</strong>/2<strong>01</strong>0 revision 00 - Electric Limitation to F177RG serial number 0<strong>01</strong>6. Prior to installation of this modification it 15.06.2<strong>01</strong>2<br />
ASSISTANC<br />
Rudder Hand Control.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027431 ISEI P-<strong>EASA</strong>.R.S.<strong>01</strong>543 AS350 B3, EC130 B4 -Installation of Safetyplane Equipment-<br />
Installation of a system for tracking a set of<br />
flight and systemparameters during operation<br />
of the rotorcraft. The modification is basedon<br />
ISEI change N-EC130 AS350B3 as defined in<br />
Dossier de Définition de laModificat<br />
10027889 ISEI REV. 1 EC 120 B Installation of HELICOM V1 or HELICOMV2<br />
data recording system.Revision 1 of STC<br />
10027889 introducing change in system<br />
name(Safetyplane becomes HELICOM<br />
V1), new V2 version and<br />
Associateddocumentation.<br />
10028200 ISEI R44, R44 II Title: Installation of Safetyplane<br />
EquipmentDescription: Installation of a system<br />
for tracking a set of flight andsystem<br />
parameters during operation of the rotorcraft.<br />
The modificationis based on ISEI change N-<br />
R44 as defined in the Master Document ListN1-<br />
R<br />
10028789 ISEI AS350 B, BA, BB, B1, B2 Installation of Safetyplane<br />
EquipmentInstallation of a system for tracking a<br />
set of flight and systemparameters during<br />
operation of the rotorcraft as defined in the<br />
ApprovalChange Document N2-AS350 B BA<br />
BB B1 B2 E-A-02.<br />
10033288 ISEI P-<strong>EASA</strong>.R.S.<strong>01</strong>542 REV. 1 AS 355 NP Installation of HELICOMV2 NUMInstallation of<br />
a system for tracking a set of flight and<br />
systemparameters during operation of the<br />
rotorcraft. The modification is basedon ISEI<br />
change N-AS355_NP as defined in N1-AS355<br />
NP-HV2 NUM-APPROVALCHANGE FILE-E-<br />
A.<br />
10033974 ISEI REV. 1 A109E Installation of HELICOM V1 or HELICOM V2<br />
data monitoring system.Revision 1 of STC<br />
10033974 introducing change in system<br />
name(Safetyplane becomes HELICOM V1),<br />
new V2 version and associateddocumentation.<br />
10034914 ISEI EC135 P1(CPDS),<br />
EC135 P2(CPDS),<br />
EC135 P2+,<br />
EC135 T1(CPDS),<br />
EC135 T2(CPDS),<br />
EC135 T2+<br />
Installation of HELICOMV2 NUMInstallation of<br />
a system for tracking a set of flight and<br />
systemparameters during operation of the<br />
rotorcraft. The modification is basedon ISEI<br />
change "Installation of HELICOMV2 NUM" as<br />
defined in ApprovalChange File N1- EC135<br />
10035287 ISEI REV. 2 AS350B2, AS350B3, EC130B4 Installation of HELICOM V2 NUMRevision 1<br />
introducing alternate positions for<br />
antennas.Revision 2 correcting minor<br />
discrepancies in associated documentation.<br />
None The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
30.09.2009<br />
None. None. 03.06.2<strong>01</strong>1<br />
None The approval holder shall fulfil the<br />
08.12.2009<br />
obligations of Part 21, Paragraph21.A109<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.02.2<strong>01</strong>0<br />
None The system does not replace standard<br />
maintenance records and<br />
pilotreporting.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair w<br />
None The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21A.118A. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
31.<strong>01</strong>.2<strong>01</strong>1<br />
05.05.2<strong>01</strong>1<br />
None.<br />
repa<br />
The system does not replace standard<br />
maintenance records and<br />
pilotreporting.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair w<br />
16.05.2<strong>01</strong>1<br />
For AS350B2 model this STC is applicable The system does not replace standard 27.11.2<strong>01</strong>2<br />
only to aircraft equipped withVEMD system maintenance records and pilotreporting.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 281/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038671 ISEI EC 225 LP Installation of the Helicom V2 NUM embedded None Prior to installation of this modification it 07.03.2<strong>01</strong>2<br />
Equipment<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10039479 ISEI AS 355 F, AS 355 F1, AS 355 F2<br />
AS 355 N<br />
Installation of: HELICOM V2 ANA ON<br />
PANELInstallation of a recorder and transmitter<br />
of flight-and-systemsparameters.The<br />
modification is defined in Document ISEI<br />
change N3-AS355 ANA-HV2 ANAON PANEL-<br />
DESIGN CHANGE-E-A-<strong>04</strong>.<br />
10<strong>01</strong>6951 ISOLAIR Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>346 FAA STC SH4796NM BELL 206B Installation of Isolair 3900-206 Spray System<br />
consisting of a fibreglass 130 gallon belly tank<br />
and spray booms for agricultural applications.<br />
10039386 ISOLAIR Inc. FAA STC SR02813CH ENSTROM 480<br />
ENSTROM 480B<br />
Title: Installation of 3900-480 Spray<br />
SystemDescription: The installation of the 3900-<br />
480 Spray System pertains tothe installation of<br />
an agricultural spray system onto the Enstrom<br />
480and 480B rotorcraft.<br />
10<strong>04</strong>1184 ISOLAIR Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>8 Data not found Installation of Isolair spray system model 3900-<br />
350B2.<br />
10<strong>01</strong>5542 ISRAEL AEROSPACE INDUSTRIES,<br />
LTD.<br />
10<strong>01</strong>6227 ISRAEL AEROSPACE INDUSTRIES,<br />
LTD.<br />
10<strong>01</strong>4423 ISRAEL AEROSPACE INDUSTRIES,<br />
LTD. I<br />
10<strong>01</strong>5354 ISRAEL AEROSPACE INDUSTRIES,<br />
LTD. I<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>426 REV. 5 B737-300 Conversion from Passenger configuration to<br />
Special Freighter (SF),Special Freighter with<br />
Rigid Barrier and to Quick Change<br />
(QC)configuration and approval of increased<br />
weight limitations Summary of <strong>EASA</strong> STC<br />
Revisions: Original <strong>EASA</strong> approval: CAA UK<br />
STC No C<br />
<strong>EASA</strong>.IM.A.S.02479 REV. 5 CAA ISRAEL STC SA160 B737-400 Major Change to STC 10<strong>01</strong>6227 Revision 4 for<br />
the IAI 737-400 conversionto freighter aircraft.<br />
Update of the MDL TR 365-00-00-B4200 from<br />
issue Nto Issue T.All design changes being of<br />
level 2 and approved by the CAAI, theworking<br />
arrangement (<strong>EASA</strong>/CAAI 22Nov20<br />
None The system does not replace standard<br />
maintenance records and pilotreporting.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair<br />
08.05.2<strong>01</strong>2<br />
Bell 206B High Skid Landing Gear must be<br />
installed.An aircraft with this STC installed will<br />
be operating in the Restricted<br />
Category.Essential crew required for the<br />
mission only;Vne is 90 KIAS;Spaying at<br />
airspeeds below 17 KIAS is prohibited;<br />
andSpraying pr<br />
Restricted to agricultural use. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1. The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation.2. Prior to<br />
installation of this modification it must be<br />
determined thatthe i<br />
06.03.2008<br />
02.05.2<strong>01</strong>2<br />
16.06.2009<br />
This STC is approved only for the product Prior to installation of this modification it 23.<strong>04</strong>.2<strong>01</strong>2<br />
configuration as defined inthe approved design must be determined thatthe<br />
data referred to in the paragraph<br />
interrelationship between this modification<br />
"Description".Compatibility with other and any other previouslyinstalled<br />
aircraft/engine configurations shall<br />
modification and/ or repair will introduce<br />
bedetermined by the installer.If the holder no adverse effectupon the airworthiness<br />
agrees to per<br />
of the product<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.03.2<strong>01</strong>2<br />
<strong>EASA</strong>.IM.A.S.02039 REV. 2 CAA ISRAEL STC NO SA152 747-400 Revision 1: Boeing 747-400SF conversion from none<br />
PAX to Freighter CAAI STCSA152/<strong>EASA</strong> STC<br />
IM.A.S.02039Revision 2: Increase of Max. Taxi<br />
Weight and Max. Take Off Weight<br />
from873.000 / 870.000 to 878.000 / 875.000<br />
Lbs<br />
none 11.07.2<strong>01</strong>1<br />
<strong>EASA</strong>.IM.A.S.00632 REV. 2 BOEING 767-200 Conversion from Boeing 767-200 passenger 1. Supplementary Data Sheet<br />
aircraft to Boeing 767-200SF (Special TCDS.IM.A.S.006322. This STC is approved<br />
Freighter) configuration, to enable for Carriage only for the product configuration as defined in<br />
of palletised cargo.Revision 1 to approved the approved design data referred to in the<br />
increased weight limitations<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 282/<strong>462</strong><br />
27.06.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5911 ISRAEL AEROSPACE INDUSTRIES, <strong>EASA</strong>.IM.A.S.02<strong>04</strong>0 REV. 1 BOEING 747-400 Conversion of Boeing 747-400 Aircraft from 1. Supplementary Data Sheet<br />
27.06.2007<br />
LTD. I<br />
Combi to Special Freighter Configuration TCDS.IM.A.A.02<strong>04</strong>0 applies,2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configuration<br />
10028430 ISRAEL AEROSPACE INDUSTRIES,<br />
LTD. I<br />
P-<br />
<strong>EASA</strong>.IM.A.S.02477<br />
REV. 3 CAAI STC SA218 B767-300 Conversion of Boeing B767-300 from<br />
Passenger Configuration to SpecialFreighter<br />
(BDSF) with Main Deck Class E Cargo<br />
Compartment.<br />
An approved Cargo Loading System must be<br />
installed.<br />
10<strong>01</strong>5652 ITOCHU AIRLEASE, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>627 ST1<strong>04</strong>36SC BOEING 767-300 Reconfiguration of an existing three seating<br />
class interior with 199 passengers to a two<br />
seating class interior (enconomy & business<br />
seats) with 232 passengers.<br />
10<strong>01</strong>4840 J & C ENGINEERING SERVICES LTD <strong>EASA</strong>.A.S.03057 BOEING B737-300 TCAS II Installation Limited to installation on Boeing 737-300 MSN<br />
28740.Compatibility of this design change with<br />
other previously approved modifications must<br />
be determined by the installer.<br />
10<strong>01</strong>4841 J & C ENGINEERING SERVICES LTD <strong>EASA</strong>.A.S.03058 BOEING B737-300 Installation of Driessen Galley No 1 Limited to installation on Boeing 737-300 MSN<br />
28740.Compatibility of this design change with<br />
other previously approved modifications must<br />
be determined by the installer.<br />
10<strong>01</strong>5174 J & C ENGINEERING SERVICES LTD <strong>EASA</strong>.A.S.03547 REV 1 R2160, R2160D, R2160I, R2120U Removal of VFR Limitation from AFM<br />
Approved Operation Section.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Incorporation of this STC constitutes an 20.11.2<strong>01</strong>2<br />
AMOC for the list of affectedADs as<br />
published in the TCDS Supplement. Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinst<br />
10<strong>01</strong>5175 J & C ENGINEERING SERVICES LTD <strong>EASA</strong>.A.S.03550 BOEING 767-200 Approval of Galley and Crew Rest Installation. 12.06.2008<br />
10<strong>01</strong>5356 JAMCO AMERICA INC <strong>EASA</strong>.IM.A.S.00647 FAA STC ST<strong>01</strong>372SE BOEING 767-300 New Seats and Interior Reconfiguration 1. Limitation on FAA STC in respect of<br />
concurrent installation of Thales IFE STC<br />
ST<strong>01</strong>62LA is not applicable2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compati<br />
10<strong>01</strong>5496 JAMCO AMERICA INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>258 FAA STC ST<strong>01</strong>121SE BOEING 767-200<br />
BOEING 767-300<br />
BOEING 767-400ER<br />
10<strong>01</strong>6<strong>04</strong>0 JAMCO AMERICA INC <strong>EASA</strong>.IM.A.S.02209 REV. 1 FAA STC ST<strong>01</strong>700SE BOEING 747-400 Removal of the strengthened flight deck door<br />
and modification and reinstallation of luggage<br />
bins on the upper deck in accordance with<br />
Jamco Aero Design & Engineering Master<br />
Drawing List JD-03AC02 Rev. F or later<br />
revisions of the above listed documents appr<br />
Installation of a new security flight deck door 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is limited to the following aircraft<br />
after incorporation of Boeing SB 747-00-20<strong>04</strong><br />
Passenger to Freighter conversion:a. RT5<strong>01</strong><br />
Sn. 24061b. RT506 Sn. 24066c. RT507<br />
Sn. 24226d. RT509 Sn. 249752. This<br />
STC is<br />
10<strong>01</strong>6307 JAMCO AMERICA INC <strong>EASA</strong>.IM.A.S.026<strong>04</strong> FAA STC ST<strong>01</strong>459SE BOEING 767-300 Oxygen Module Installation. Reconfiguration of Passenger seats as per<br />
FAA STC SA7032NM-D must be installed<br />
concurrently. This FAA STC must be<br />
approved by <strong>EASA</strong>directly or by Grandfather<br />
Rights before installation on a <strong>EASA</strong> member<br />
state aircraft.<br />
10<strong>01</strong>6541 JAMCO AMERICA INC <strong>EASA</strong>.IM.A.S.02919 FAA STC ST00240SE ; P. GILLESP BOEING 747-200 Installation of Jamco Galley in accordance with Prior to installation of this modification the<br />
Jamco America Inc. Master Drawing List IA- installer must determine that the<br />
036, Rev. A dated September 1, 1995, or later interrelationship between this modification and<br />
approved revisions.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The interior<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 283/<strong>462</strong><br />
02.11.2005<br />
29.05.2007<br />
31.05.2007<br />
07.11.2008<br />
17.03.2005<br />
21.06.2005<br />
02.<strong>04</strong>.2007<br />
10.<strong>01</strong>.2008<br />
16.<strong>01</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
100321<strong>04</strong> JAMCO AMERICA INC FAA STC ST<strong>01</strong>094SE 747-400 Installation of an interior reconfiguration of the None STC ST<strong>01</strong>482NY, <strong>EASA</strong>.A.S.03195, 07.10.2<strong>01</strong>0<br />
main and upper decksin 747-400 airplanes in<br />
(IFE system, purser work station,<br />
accordance with Jamco America, Inc.<br />
videomonitors and projectors) and STC<br />
MasterDrawing List no. IA-072MDL, Revision<br />
ST<strong>01</strong>519NY,<br />
AD dated 19 September 2008 or laterapproved<br />
<strong>EASA</strong>.IM.A.S.03197,(Installation of Inrevision<br />
Validation of FAA STC ST<strong>01</strong>094<br />
Seat Power Supply) must be installed<br />
concurrentlywith this STC.Prior to<br />
installation of this modificatio<br />
10<strong>04</strong>1373 JAMCO AMERICA INC FAA STC ST02107SE-D B777-300 Validation of FAA STC ST02107SE-D related Approval of this change in type design is STC ST03928AT-D, Installation of an IFE 11.09.2<strong>01</strong>2<br />
to Interior Reconfiguration.<br />
applicable to the above modelaircraft only. system and components, must<br />
beinstalled concurrently with this<br />
modification. STC ST03684AT,<br />
Installation of a photo luminescent floor<br />
proximitylighting system, as amended for<br />
the Boeing Model 777-300 seriesaircraft,<br />
10<strong>04</strong>1806 JAMCO AMERICA INC FAA STC ST<strong>01</strong>884SE-D 747-400 Installation of a galley modification on Boeing<br />
747-400 series aircraftin accordance with<br />
Jamco America, Inc. Master Drawing List<br />
(MDL) 1419-1,Rev.E, dated May 25, 2<strong>01</strong>2, or<br />
later FAA approved revision.Validation of FAA<br />
STC ST<strong>01</strong>884SE-D<br />
10<strong>04</strong>2094 JAMCO AMERICA INC FAA STC ST<strong>01</strong>514SE B747-400 Lavatory and galley modification of 747-400<br />
series airplanes inaccordance with Jamco<br />
America, Inc. Master Data List IA-102MDL,<br />
Rev. D,dated March 15,2005, or later FAA<br />
approved revision. Validation of FAA STC<br />
ST<strong>01</strong>514SE.<br />
10<strong>01</strong>6454 JAZZ AVIATION LP <strong>EASA</strong>.IM.A.S.02800 TC STC SA03-70 BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
10033847 JCB AERO SA A320 Installation of Hi-Low Table for VIP cabin<br />
interior<br />
10<strong>01</strong>6<strong>01</strong>0 JCM AERODESIGN LIMITED <strong>EASA</strong>.IM.A.S.02175 O-LSA06-268/D ISSUE 1 BOMBARDIER DHC-8-311 EMS Installation as per TCCA Limited<br />
Supplemental Type Certificate # O-LSA06<br />
268/D, Issue 1, dated 13 September 2006<br />
10<strong>01</strong>6783 JCM AERODESIGN LIMITED <strong>EASA</strong>.IM.R.S.<strong>01</strong>124 REV. 2 TCCA STC SH02-2 EUROCOPTER FRANCE AS 350<br />
B3<br />
S/N 29262 None 17.10.2<strong>01</strong>2<br />
FAA STC ST<strong>01</strong>492SE, interior reconfiguration<br />
of passenger seating, mustbe installed<br />
concurrently with this STC.<br />
Cockpit Door Electronic Strike System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.This AFM Sup<br />
Installation of Optech Inc. Airborne Laser<br />
Terrain Mapper ALTM 1225 or ALTM 3033 in<br />
Eurocopter AS 350B1 and AS 350B2 rotorcraft<br />
(approved under <strong>EASA</strong>.IM.R.S.<strong>01</strong>124 – initial<br />
issue).Installation of Optech Inc. Airborne Laser<br />
Terrain Mapper ALTM 3100 in Euroco<br />
10<strong>01</strong>5264 JET AVIATION AG <strong>EASA</strong>.A.S.03726 REV. 1 GULFSTREAM V Iridium Antenna InstallationA dual Iridium<br />
antenna has been installed on top of the<br />
fuselage located between Sta. 539.5 & Sta.<br />
554.5.<br />
10<strong>01</strong>5626 JET AVIATION AG <strong>EASA</strong>.IM.A.S.<strong>01</strong>578 REV. 2 BOMBARDIER CL-600-1A11 (CL-<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Prior to installation of this modification it 07.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.06.2008<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.02.2<strong>01</strong>1<br />
DHC-8-311, S/N. 216 20.12.2006<br />
1. This STC is not approved for AS350 B3<br />
aircraft when equipped with Eurocopter Mod<br />
OP-3369 (2370 kg certified weight<br />
extension).2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modifi<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
22.05.2008<br />
19.12.2008<br />
Activation of RAAS 13.<strong>01</strong>.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 284/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028110 JET AVIATION AG GULFSTREAM GV Mid Cabin Door None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.12.2009<br />
10034437 JET AVIATION AG A319-100 GSM Securaplane Antenna Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
05.<strong>04</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>4577 JET AVIATION AG BASEL <strong>EASA</strong>.A.S.02682 B727-200 Stretcher & Medical Equipment<br />
installation:According to the description in the<br />
Certification Plan, Doc. No. BACBA008-3<br />
Reg.; A9C-BA, S/N: 21824Approval limited to<br />
S/N 21824 only.<br />
10<strong>01</strong>4691 JET AVIATION AG BASEL <strong>EASA</strong>.A.S.02855 REV. 1 A319 Cabin interior outfitting Limited to Reg. P4-VNL, S/N 2921 Prior to installation of this modification the 02.11.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>4821 JET AVIATION AG BASEL <strong>EASA</strong>.A.S.03032 REV. 1 A330-202 Cabin Interior Outfitting None Prior to installation of this modification the 02.11.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>5445 JET AVIATION AG BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>186 - A320-232 Cabin Modification (Final Completion of VIP<br />
Configuration)<br />
1) Modification limited to Aircraft S/N 25662)<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be deter<br />
10029053 JET AVIATION AG BASEL <strong>EASA</strong>.A.S.03258 BOEING 737-700 IGW 15.07.2009<br />
10029540 JET AVIATION AG BASEL MYSTERE FALCON 50 (MF50) Runway Awareness and Advisory System ·,,This Jet Aviation Supplemental Type Prior to installation of this modification it 30.03.2<strong>01</strong>0<br />
(RAAS). Smart Runway Activation.i.a.w. Jet Certificate is applicable onMystere Falcon 50 must be determined thatthe<br />
Aviation Master Data List BF5EX34461-0<strong>01</strong> EX (F50EX) version airplanes with an existing interrelationship between this modification<br />
Revision B or later<strong>EASA</strong> Approved revisions. anddesign approved Honeywell EGPWS Mark and any other previouslyinstalled<br />
V installation.·,,Caution alerts, terrain display modification and/ or repair will introduce<br />
text messages, take-off flapsconfig<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029553 JET AVIATION AG BASEL P-<strong>EASA</strong>.A.S.03788 REV. 1 B737-800 EMS SATCOM AMT-3800 Installation Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.07.2<strong>01</strong>0<br />
10029554 JET AVIATION AG BASEL P-<strong>EASA</strong>.A.S.03517 REV. 1 AIRBUS A319-115 Airbus A319-115 "BCJ03513" VIP Cabin Not Applicable This certificate is granted under the <strong>04</strong>.08.2<strong>01</strong>0<br />
Interior CompletionRevision 1: Update of the<br />
commitment from the applicant tocomply<br />
Instructions for Continued Airworthiness<br />
with the post STC actions as referred to<br />
in Jet Aviation's letterref. "Commitments<br />
to Post STC actions" dated 16 July<br />
2<strong>01</strong>0Prior to installation of this<br />
modification it must be det<br />
10029953 JET AVIATION AG BASEL P-<strong>EASA</strong>.A.S.03531 REV. 1 B737-800 VIP Cabin Interior Outfitting Limited to: S/N 37545 This STC has been assessed for<br />
compatibility for installation on thesubject<br />
aircraft, which is equipped for lower cabin<br />
altitude under FAASTC ST<strong>01</strong>697SE.<br />
However, <strong>EASA</strong> has not yet approved<br />
the lower cabinaltitude STC. Therefore, if<br />
this aircraft is to be en<br />
12.07.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 285/<strong>462</strong><br />
22.03.2007<br />
21.12.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030964 JET AVIATION AG BASEL P-<strong>EASA</strong>.A.S.03518 REV. 1 A319-115 Airbus A319-115 "BCJ03632" VIP Cabin None This certificate is granted under the <strong>04</strong>.08.2<strong>01</strong>0<br />
Interior CompletionRevision 1: Update of the<br />
commitment from the applicant tocomply<br />
Instructions for Continued Airworthiness<br />
with the post STC actions as referred to<br />
in Jet Aviation's letterref. "Commitments<br />
to Post STC actions" dated 16 July<br />
2<strong>01</strong>0.Prior to installation of this<br />
modification it must be de<br />
10032331 JET AVIATION AG BASEL B747-400 Replacement of a dual Allied Signal High none Prior to installation of this modification it 27.10.2<strong>01</strong>0<br />
Frequency (HF) Radio by dualRockwell Collins<br />
must be determined thatthe<br />
Air Transport (RCAT) HFS-900D HF Radio<br />
interrelationship between this modification<br />
equipment (ARINC753) with HF Data Link<br />
and any other previouslyinstalled<br />
activation in accordance with Jet Aviation<br />
modification and/ or repair will introduce<br />
MasterData List Doc. No. B7428343-006 Rev<br />
no adverse effectupon the airworthiness<br />
D, date<br />
of the product.<br />
10037000 JET AVIATION AG BASEL P-<strong>EASA</strong>.A.S.03714 B747-400 Installation of Cabin Interior Doors in<br />
accordance with Jet AviationMaster Data List<br />
BHHM10<strong>01</strong>-0<strong>01</strong> Rev. B, dated 19th October,<br />
2<strong>01</strong>1 forB747-400 S/N 28343<br />
10037425 JET AVIATION AG BASEL FALCON 2000EX Change consists in activating WLAN WiFi<br />
function of existing Satcom/LANrouter<br />
equipment.<br />
100375<strong>04</strong> JET AVIATION AG BASEL <strong>EASA</strong>.A.S.03322 REV. 2 B737-700 EMS SATCOM AMT-3800<br />
Installation:Installation option between<br />
STA.727E to STA.787 and STA.727B to<br />
STA.727E(Major change to <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.A.S.03322 Rev.1)<br />
10038393 JET AVIATION AG BASEL A319-133 VIP Cabin Interior CompletionSee Master Data<br />
List BCJ<strong>04</strong>151-0<strong>01</strong><br />
10039269 JET AVIATION AG BASEL P-<strong>EASA</strong>.A.S.03779 REV. 1 A340-600 Airbus A340-600 "Eminence" VIP Cabin<br />
Interior CompletionRevision 1 to remove<br />
limitations<br />
10039356 JET AVIATION AG BASEL A340-211, A340-212, A340-213<br />
A340-311, A340-312, A340-313<br />
10039357 JET AVIATION AG BASEL A340-211, A340-212, A340-213<br />
A340-311, A340-312, A340-313<br />
Camera Unit and Structural provision<br />
installationThis STC installs one camera on the<br />
tail of the aircraft, watchingforward. This covers<br />
the mechanical installation of the camera unit<br />
andthe penetration of the pressure.<br />
This aircraft is not eligible for registration in a<br />
European country,because it does not comply<br />
with the JAA Special Conditions 1 and 2.<br />
Aircraft must be fitted with Dassault Aviation<br />
M3196 that installscomplete Aircell Axxes II<br />
system, including WiFi antennas.<br />
Prior to installation of this modification it 24.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to the installation of this modification 25.11.2<strong>01</strong>1<br />
it must be determinedthat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification and/or repair will introduce<br />
noadverse effect upon the airworthiness<br />
of the product.<br />
None. None. 02.12.2<strong>01</strong>1<br />
Approval valid only for MSN 4151.The aircraft<br />
is certified for private use only, not to be<br />
operated forcommercial air transport.The<br />
aircraft is a No Smoking aircraft.For other<br />
Limitations refer to Airplane Flight Manual<br />
SupplementBCJ<strong>04</strong>151-2<strong>01</strong>-<strong>01</strong> Rev. B or<br />
Prior to installation of this modification it 15.02.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
11.05.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.<strong>04</strong>.2<strong>01</strong>2<br />
Tailwind 550/560 antenna installationThis STC None. Prior to installation of this modification it 30.<strong>04</strong>.2<strong>01</strong>2<br />
installs a tailwind SAT TV antenna and radome<br />
must be determined thatthe<br />
on top of thefuselage.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 286/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039715 JET AVIATION AG BASEL FALCON 2000 WLAN activationFor WLAN working in the 2.4<br />
Prior to installation of this modification it 24.05.2<strong>01</strong>2<br />
GHz frequency band<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong><strong>01</strong>66 JET AVIATION AG BASEL 737-800 Iridium Antenna Structural Provisionsbetween<br />
fuselage station BS 727C & 727D<br />
10<strong>04</strong>0780 JET AVIATION AG BASEL B737-800 Forward VIP Lavatory reconfiguration- new<br />
shower system- relocation of handspray<br />
system- new vanity light system- new shower<br />
light system- new pax sign inside shower-<br />
adaptation of existing systems<br />
10<strong>04</strong>0974 JET AVIATION AG BASEL A330-2<strong>01</strong>, - 202, - 203<br />
A330-223, -243<br />
EMS Satcom AMT-3800 antenna<br />
installation.This modification installs EMS<br />
Satcom AMT-3800 high gain antenna,Diplexer<br />
Low Noise Amplifier, and associated structural<br />
provision.<br />
10<strong>04</strong>1576 JET AVIATION AG BASEL FALCON 10 Exchange to Universal Avionics FMS UNS-<br />
1LwOut: Universal Avionics FMS UNS-1Msp<br />
systemIn: Universal Avionics FMS UNS-1Lw<br />
system<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.06.2<strong>01</strong>2<br />
S/N: 33473 (A6-AUH) Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.07.2<strong>01</strong>2<br />
This STC approval has been granted for 100 Prior to installation of this modification it 10.08.2<strong>01</strong>2<br />
Flight Cycle (FC) or 6months, counted from the must be determined thatthe<br />
STC approval date, whichever occurred first. interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
S/N: 216 The approval holder shall fulfill the<br />
obligations of Part 21,Paragraph<br />
21.A109.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
10<strong>04</strong>1595 JET AVIATION AG BASEL B737-900ER EMS SATCOM AMT-3800 Installation. Approval valid only for S/N: 37560 This STC has been assessed for<br />
compatibility for installation on thesubject<br />
aircraft, which is equipped for lower cabin<br />
altitude under FAASTC ST<strong>01</strong>697SE.<br />
However, <strong>EASA</strong> has not yet approved<br />
the lower cabinaltitude STC. Therefore, if<br />
this aircraft is to be en<br />
<strong>01</strong>.10.2<strong>01</strong>2<br />
10<strong>04</strong>16<strong>04</strong> JET AVIATION AG BASEL REV. 1 B737-900ER VIP Cabin interior installation.Installation of<br />
table leaf adjacent to RH over-wing exit.See<br />
Master Data List BBJ37560-0<strong>01</strong> Rev. C (or<br />
later approved revision).<br />
28.09.2<strong>01</strong>2<br />
S/N: 37560 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.11.2<strong>01</strong>2<br />
10<strong>04</strong>2850 JET AVIATION AG BASEL REV. 1 GV-SP MDL BDBMW002-0<strong>01</strong> Rev. IR S/N: 5336 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.12.2<strong>01</strong>2<br />
10<strong>01</strong>4526 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02611 B727-200 ADI/ HIS & FMS upgrade by:removing both<br />
existing 329B-8x ADI 329Bremoving both<br />
existing 331A-9G HISremoving both LTN-92<br />
CDUremoving both ALI 55B Radio Altimeter<br />
Indicatorsinstalling two new 5ATI E-ADI, p/n<br />
195000-21installing two new ATI E-HIS, p/n<br />
195000-<br />
Reg.: A9C-BA, S/N 21824. Valid for this serial<br />
number only.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 287/<strong>462</strong><br />
<strong>04</strong>.09.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4555 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02653 BAE 146/AVRO 146 SERIES Cabin Interior Outfitting:Introducing a custom 1. Reg.: A6-RJK S/N: E1267.2. For<br />
12.<strong>04</strong>.2007<br />
passenger cabin with individual interior and limitations refer to Flight Manual Supplement<br />
seating, VIP lavatory, In-flight Entertainment /<br />
Cabin ManagementSystem w/ tail and cockpit<br />
camera, Iridium Satcom system, cabin poweroutlet<br />
system and oxygen ove<br />
BRJE1267-2<strong>01</strong>-<strong>01</strong>.<br />
10<strong>01</strong>4576 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02681 BOEING 727-200 Cabin interior modification:According to the<br />
description in the Certification Plan, Doc. No.<br />
BACBA008-1.<br />
Reg.: A9C-BA, S/N: 218424Approval limited to<br />
S/N 21824 only.<br />
10<strong>01</strong>4613 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02740 BOEING 737-100 SERIES Cabin ModificationGalley installation in the LH 1. Approval valid only for s/n 32774 with FAA-<br />
FWD Entrance AreaHigh Cabinet installation in STC No. ST09981SC installed;2. This STC<br />
the FWD RH Cabin<br />
is approved only for the product configuration<br />
as defined in the approved design data<br />
referred to in the paragraph "Description".<br />
Compatibility with other aircraft/<br />
10<strong>01</strong>4630 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02770 AIRBUS A319-115 Cabin interior outfittingsee Master Data List<br />
BA3192949-0<strong>01</strong><br />
Limited to S/N 2949. 19.07.2007<br />
10<strong>01</strong>4644 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02796 AIRBUS A319-100 Installation Of Additional Water Tank 24.<strong>04</strong>.2007<br />
10<strong>01</strong>4652 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02807 MYSTERE FALCON 900 Wireless Access Service Point (WASP) 1. Applicable for S/N 109 only;2. This STC<br />
is approved only for the product configuration<br />
as defined in the approved design data<br />
referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined b<br />
29.09.2006<br />
10<strong>01</strong>4659 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02816 BOEING 737-700 IGW Wireless LAN (WLAN) Activation This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4738 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02921 MYSTERE FALCON 50 MK-V EGPWS upgrade. 1. Required Avionics Configuration:• Collins<br />
ProLine II• Collins EFIS 84/85/86• Collins<br />
WXP 8502. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compati<br />
10<strong>01</strong>4750 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.02935 BOEING 727-200 Activation of RAAS on MK-V or MK-VII<br />
EGPWS with Softwareversion -218-218 or<br />
higher up to -226-226<br />
10<strong>01</strong>4859 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03083 BOMBARDIER BD-700-1A10 W-LAN Activation.By installing:A swivel dipole<br />
antenna in the cabin, a WLAN ON/OFF switch<br />
and new wiring between the router, antenna<br />
and the HD-710.<br />
10<strong>01</strong>4868 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03092 AIRBUS A319-115 Wireless Local Area Network (WLAN)<br />
Activation.The modification includes the<br />
following:The antenna will be connected and<br />
the WLAN will be activated.A "WLAN OFF"<br />
switch will be installed to switch the Wireless<br />
LAN functionality 'on' and 'off'.<br />
S/N 21824 as initial installationSTC Valid for<br />
B727-200 Series with EGPWS MK-V or MK-<br />
VII with Softwareversion -218-218 or higher up<br />
to -226-226<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4888 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03117 AIRBUS A319-115 Water Tanks Installation/The modification Prior to installation of this modification the<br />
includes the following:Installation of two installer must determine that the<br />
additional water tanks in the AFT lower lobe interrelationship between this modification and<br />
area between frame FR62 and frame FR65 on any other previously installed modification will<br />
the LH and RH side.<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>49<strong>04</strong> JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03139 GULFSTREAM III Super FMS Installation by:Removing the<br />
existing dual UNS-1Msp Flight Management<br />
System (FMS)and Install a new dual UNS-1L<br />
Super Flight Management System (FMS)a<br />
DTU-100 Data Transfer Unit.<br />
22.03.2007<br />
16.11.2006<br />
15.11.2006<br />
<strong>04</strong>.<strong>01</strong>.2007<br />
14.03.2007<br />
06.11.2007<br />
13.08.2007<br />
14.09.2007<br />
Reg.: TJ-AAW S/N 486Valid for this S/N only. 05.03.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 288/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4915 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03160 GV Installation of bulkheads and door in the mid 1. S/N: 669.2. Prior to installation of this<br />
19.10.2007<br />
cabin.<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the<br />
10<strong>01</strong>4977 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03265 MYSTERE FALCON 50 Triple FMS Upgrade to UNS-1F 1. Mystere Falcon MF 50 Serial Number<br />
222See: • Airplane Flight Manual (AFM)<br />
Supplement BOHIT039-2<strong>01</strong>-13, Rev. IR, dated<br />
14th November 2007.• Instructions for<br />
Continued Airworthiness BOHIT039-150-13,<br />
Revision B, dated 09th October 2007,Or later<br />
app<br />
17.12.2007<br />
10<strong>01</strong>4978 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03267 FALCON MF 50 MYSTERE Interior Modifications. Mystère Falcon MF 50 Serial Number<br />
2222See Operations Instructions BOHIT039-<br />
202-11 Rev. IRInstructions for Continued<br />
Airworthiness BOHIT039-150-11 Revision A<br />
17.10.2007<br />
10<strong>01</strong>5000 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03300 BOEING 767 Activation of RAAS. 14.09.2007<br />
10<strong>01</strong>5<strong>01</strong>9 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03325 AIRBUS A330 Tailwind 550/560 Antenna and Rack<br />
Applicable A330-220/-300 MSN’s are listed in<br />
03.07.2008<br />
InstallationThe modification includes the ref. doc. No. BA3305320-123, “Effectivity<br />
following:- Installation of a radome with Substantiation Report”, Rev. IR, dated<br />
10<strong>01</strong>5<strong>04</strong>2 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03358 GULFSTREAM GV-SP G550<br />
mechanical antenna located top of the fuselage- 23.<strong>04</strong>.08<br />
Installation of a system rack inside the cabin,<br />
above the headliner<br />
Wireless LAN (WLAN) Activation 11.03.2008<br />
10<strong>01</strong>5077 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03408 GULFSTREAM III Iridium SATCOM Installation consisting of-1<br />
ICS-200 Iridium Transceiver- 1ICS Iridium<br />
Antenna- 1 Sigma 7 handset- 2 Cordless<br />
Handset<br />
Reg. TJ-AAW S/N 486Valid for this S/N only. 05.03.2008<br />
10<strong>01</strong>5090 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03427 BOMBARDIER CL-600-2B16 Iridium Antenna Installation Aircell ST2100. Reg.: ZS-SGC S/N: 5070 28.03.2008<br />
10<strong>01</strong>5167 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03537 MYSTERE FALCON 20 Installation of a Honeywell MK VIII Enhanced Prior to installation of this modification the<br />
24.06.2008<br />
Ground Proximity Warning System (EGPWS). installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.This STC is<br />
10<strong>01</strong>52<strong>01</strong> JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03598 GULFSTREAM IV Wireless LAN (WLAN) Activation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5206 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03619 AIRBUS A319-133 Wireless Local Area Network (WLAN)<br />
Activation<br />
10<strong>01</strong>5228 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03645 BOMBARDIER CL-600-2B16 Aircell Iridium Antenna P/N.<strong>01</strong>5-10306-0<strong>01</strong><br />
Installation<br />
28.08.2008<br />
None 13.08.2008<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5289 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03824 GULFSTREAM III Activation of the Runway Awareness and<br />
Advisory System (RAAS)EGPWC upgrade to<br />
software level 228-228 and activation of the<br />
RAAS<br />
None 11.05.2009<br />
10<strong>01</strong>5296 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03844 REV 2 FOCA STC Z25-20-77 BOEING 737-700 IGW CTT Zonal dryer activationReplacement of<br />
Zonal Dryer related to <strong>EASA</strong> AD 2006-<strong>01</strong>40-<br />
E.The above reference <strong>EASA</strong> AD required the<br />
de-activation of Zonal Drying Systems installed<br />
via Swiss FOCA STC Z 25-20-77 due to the<br />
potential for combustion of contaminants i<br />
S/N 32627 21.<strong>04</strong>.2009<br />
10<strong>01</strong>53<strong>04</strong> JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03886 FALCON 900 Activation of the Runway Awareness and<br />
Advisory System (RAAS) i.a.w. Jet Aviation<br />
Master Data List BF90034461-0<strong>01</strong><br />
1) Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2) The ins<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 289/<strong>462</strong><br />
13.08.2008<br />
22.05.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5444 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>185 - AIRBUS A319-115 Cabin interior outfitting Approval valid for S/N 2507 onlyThe aircraft is<br />
certified for private use only. It is prohibited to<br />
operate the aircraft for hire or offered for<br />
common carriage. The aircraft is a NO<br />
SMOKING aircraft. For other limitations, see<br />
flight manual supplement BCJ<br />
20.12.2005<br />
10<strong>01</strong>5446 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>187 - LEARJET 31<br />
LEARJET 31A<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
LEARJET 55<br />
LEARJET 55B<br />
LEARJET 55C<br />
LEARJET 60<br />
10<strong>01</strong>5463 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>210 - BOMBARDIER CL-600-1A11 (CL-<br />
600<br />
Activation of the Runway Awareness and<br />
Advisory System (RAAS).<br />
Flight Management System (FMS) Upgrade &<br />
Terrain Awareness Warning System (TAWS)<br />
Installation<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5548 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>439 - MYSTERE FALCON 50 Installation of a Honeywell MK VII EGPWS none 15.11.2005<br />
10<strong>01</strong>5607 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>543 - MYSTERE FALCON 50 GPWS upgrade to EGPWS This STC is limited to Falcon 50 S/N 2<strong>04</strong>. 17.08.2005<br />
10<strong>01</strong>5661 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>638 REV 1 FALCON 900 1. FMZ-2000 Software Upgrade;2.<br />
Prior to installation of this modification the<br />
22.08.2008<br />
Application of Honeywell Service Bulletin No. installer must determine that the<br />
7<strong>01</strong>8879-34-A6060.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5689 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>674 - GULFSTREAM IV Installation of a L3 F2100 Solid State Flight<br />
Data Record (FDR) and Teledyne Mini Flight<br />
Data Acquisition Unit<br />
10<strong>01</strong>5722 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>724 - AIRBUS A320-232 Cabin Interior OutfittingSee Master Data List<br />
B3202403-0<strong>01</strong><br />
1. Limited to Gulfstream IV (S/N. 1<strong>01</strong>1 - A6-<br />
HHH)<br />
1. Approval valid only for MSN 2403.2. The<br />
aircraft is certified for private use only, not to<br />
be operated for commercial air transport.3.<br />
The aircaft is a No Smoking aircraft.4. The<br />
W-LAN System is limited to Cabin W-LAN,<br />
10<strong>01</strong>5729 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>748 BOEING 737-700 IGW Cabin Modification - Aft Lounge Modification -<br />
wich is not interfaced<br />
Approval valid only for MSN 28976 with FAA<br />
Replacement of IFE/CMS and Installation of<br />
Airshow 4000<br />
STC No. ST09106AC-D installed<br />
10<strong>01</strong>5752 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>785 - BOEING 737-800 Installation of modified customized seats 1. Modification limited to Aircraft S/N 334732.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be dete<br />
10<strong>01</strong>5769 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>808 - FALCON 2000 Cabin Reconfiguration Modification limited to Aircraft S/N 076 09.02.2006<br />
10<strong>01</strong>5774 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>818 - AIRBUS A320-111<br />
CAIR TM System Installation The aircraft maximum number of passengers is<br />
30.08.2006<br />
AIRBUS A320-211<br />
AIRBUS A320-212<br />
AIRBUS A320-214<br />
AIRBUS A320-231<br />
AIRBUS A320-232<br />
AIRBUS A320-233<br />
reduced by 7 (seven) passengers.<br />
10<strong>01</strong>5775 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>819 REV 1 AIRBUS A319-111<br />
Cameras InstallationSee Master Data List Prior to installation of this modification the<br />
10.09.2007<br />
AIRBUS A319-112<br />
BA32023391-0<strong>01</strong><br />
installer must determine that the<br />
AIRBUS A319-113<br />
interrelationship between this modification and<br />
AIRBUS A319-114<br />
any other previously installed modification will<br />
AIRBUS A319-115<br />
introduce no adverse effect upon the<br />
AIRBUS A319-131<br />
AIRBUS A319-132<br />
AIRBUS A319-133<br />
AIRBUS A320-111<br />
AIRBUS A320-211<br />
AIRBUS A320-212<br />
AIRBUS A320-214<br />
AIRBUS A320-231<br />
AIRBUS A320-232<br />
AIRBUS A320-233<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 290/<strong>462</strong><br />
30.05.2005<br />
25.07.2005<br />
15.11.2005<br />
06.09.2006<br />
15.11.2006<br />
30.<strong>01</strong>.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5779 JET AVIATION AG, BASEL <strong>EASA</strong>.IM.A.S.<strong>01</strong>825 - GULFSTREAM 1159 (G-II) Weather Radar Installation -- 05.05.2006<br />
10034649 JET AVIATION AG, BASEL MF900 (EXCEPTED F900C) NZ2000 6.1 upgrade with CD820 CDU As per AFMS Doc. No. BF9003<strong>462</strong>3-2<strong>01</strong>-<strong>01</strong> Prior to installation of this modification it 18.<strong>04</strong>.2<strong>01</strong>1<br />
replacement.Existing dual or triple Honeywell Rev. IR dated 17.03.2<strong>01</strong>1.<br />
must be determined thatthe<br />
NZ2000 Flight Management System<br />
interrelationship between this modification<br />
isupgraded as follows:- NCU NZ2000 FMS<br />
and any other previouslyinstalled<br />
1&2 version NZ5.2 or later is replaced with<br />
modification and/ or repair will introduce<br />
versionNZ6.1 - CD800/CD810 1&2 CDU<br />
no adverse effectupon the airworthiness<br />
replaced with CD820.No cha<br />
of the product.<br />
10035212 JET AVIATION AG, BASEL <strong>EASA</strong>.A.S.03807 FALCON 900EX Activation of the Runway Awareness and<br />
Advisory System (RAAS) i.a.w. JetAviation<br />
Master Data List BF9EX34461-0<strong>01</strong><br />
10035406 JET AVIATION AG, BASEL FALCON 2000 Iridium antenna installation.Structural<br />
justification of the installation of an Aircell low<br />
profiledual patch antenna on top of the<br />
fuselage between frames 17 and 18.<br />
10039436 JET AVIATION AG, BASEL P-<strong>EASA</strong>.A.S.03778 REV. 1 A340-300 Airbus A340-300 "Olbia" VIP Cabin Interior<br />
Completion STC10039436Revision 1 to<br />
remove limitation<br />
10<strong>04</strong>0716 JET AVIATION AG, BASEL A319-115 VIP Cabin Interior Completion. See Master<br />
Data List BCJ03856-0<strong>01</strong>.<br />
10<strong>04</strong>2418 JET AVIATION AG, BASEL A319-115 Cabin Interior OutfittingSee Master Data List<br />
BCJ<strong>04</strong>353-0<strong>01</strong> Rev. C<br />
10<strong>01</strong>4941 JET AVIATION AG, ZURICH AIRPORT<br />
BRA<br />
10026896 JET AVIATION AG, ZURICH AIRPORT<br />
BRA<br />
10027723 JET AVIATION AG, ZURICH AIRPORT<br />
BRA<br />
10036985 JET AVIATION AG, ZURICH AIRPORT<br />
BRA<br />
<strong>EASA</strong>.A.S.03200 CESSNA 560 EHS integration into Aircraft.By upgrading both<br />
existing RCZ-833E to RCZ-833K and<br />
integrated Mode S Transponder Module XS-<br />
852A to XS-852F, with the Honeywell Service<br />
Bulletin No. 7510700-23-6<strong>04</strong>6.<br />
P-<strong>EASA</strong>.A.S.03967 HS 125 SERIES 700B Cockpit Voice Recorder InstallationBy installing<br />
a new L3 FA2100 Cockpit Voice Recorder<br />
(CVR)<br />
525 / 525A / 525B MINIQAR installation; By installing an Avionica<br />
miniQAR MK II and the MKIII according to the<br />
Installation Instructions OPM-009.<br />
CESSNA 525 Removed Equipment:-Aerosonic VSI #1 & #2-<br />
Skywatch 497 TCAS I SystemNew installed<br />
equipment:-Honeywell TA/VSI Indicator #1 &<br />
#2-PS-578A XPDR/TCAS Control HeadCAS-<br />
67A TCAS II System<br />
1.,,Prior to installation of this modification the<br />
installer mustdetermine that the<br />
interrelationship between this modification and<br />
anyother previously installed modification will<br />
introduce no adverse effectupon the<br />
airworthiness of the product.2.,,The ins<br />
Restricted to S/N 173This approval only covers<br />
the structural installation of the<br />
antenna.Installation and activation of any<br />
related Satcom system must bejustified and<br />
covered by another suitable approval.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Airstairs installation is not part of the<br />
approved configuration.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introdu<br />
Approval valid only for MSN 3856. The aircraft<br />
is certified for private use only, not to be<br />
operated forcommercial air transport. The<br />
aircraft is a No Smoking aircraft. For other<br />
Limitations refer to Airplane Flight Manual<br />
SupplementBCJ03856-2<strong>01</strong>-<strong>01</strong> Rev. C<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.07.2009<br />
21.06.2<strong>01</strong>1<br />
21.06.2<strong>01</strong>2<br />
23.07.2<strong>01</strong>2<br />
S/N: 4353 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.11.2<strong>01</strong>2<br />
Ref.: \-\ S/N:\Prerequisit equipment:- IC-600<br />
CDG, P/N 7<strong>01</strong>7000-8<strong>01</strong>62- IC-600 CDG, P/N<br />
7<strong>01</strong>7000-81162- RCZ-833E ICU, P/N<br />
7510700-866- RM-850 RMU, P/N 7<strong>01</strong>2100-<br />
825- GNS-XL FMS, P/N 18355-<strong>01</strong><strong>01</strong>-<strong>01</strong><strong>01</strong>For<br />
aircrafts equipped with a CAS-67A TCAS II-<br />
08.10.2007<br />
TPU 67-A, P/N 066-<br />
None 1) Prior to installation of this modification 20.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The in<br />
S/N 525-0600 & ON, 525A-00<strong>01</strong> & ON, 525B-<br />
<strong>01</strong>35 & ON.<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
26.10.2009<br />
S/N: 525-0322 F-HCPB<br />
product.<br />
none 24.10.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 291/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0249 JET AVIATION AG, ZURICH AIRPORT<br />
REV. 1 B200, B200C, B200GT, B200CGT ADS-B-OUT ComplianceOut: Dual Collins TDR-none<br />
Collins Pro Line 21 system & dual FMS- 11.09.2<strong>01</strong>2<br />
BRA<br />
B300, B300C<br />
94D Transponder Mode S P/N 822-9210-<br />
3000 & dual GPS-4000<br />
008In: Dual Collins TDR-94D Transponder<br />
(EGNOScapable) are prerequisiteThe<br />
Mode S P/N 622-9210-409 & 1<br />
approval holder shall fulfil the obligations<br />
dualannunciator/switch ADS-B 1/ADS-B 2<br />
of Part 21, Paragraph21.A109.Prior to<br />
inhibit<br />
installation of this modification it must be<br />
determined thatthe interrelationsh<br />
10<strong>04</strong>0290 JET AVIATION AG, ZURICH AIRPORT<br />
BRA<br />
10<strong>04</strong>2873 JET AVIATION AG, ZURICH AIRPORT<br />
BRA<br />
10<strong>01</strong>3961 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>3983 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4009 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4<strong>01</strong>0 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4<strong>04</strong>1 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4108 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4109 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4110 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4144 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4145 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4153 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4271 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4272 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4288 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4289 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
B200, B200C, B200GT, B200CGT Mini Quick Access Recorder<br />
None The approval holder shall fulfil the 22.06.2<strong>01</strong>2<br />
B300, B300C<br />
(QAR)InstallationIn: Single or Dual Avionica<br />
obligations of Part 21,<br />
P/N 8<strong>04</strong>-1205 miniQAR Mk III<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
B200, B200C, B200GT, B200CGT BARO-VNAV Temp. Comp. Activation & RF S/N: same as <strong>EASA</strong> TCDS with Rockwell Prior to the installation of this modification 21.12.2<strong>01</strong>2<br />
B300, B300C<br />
Legs Authorization Activation of Temperature Collins Proline 21 Avionics<br />
it must be determinedthat the<br />
Compensation on already approved APV<br />
interrelationship between this modification<br />
BARO-VNAVsystem and RF Legs<br />
and any otherpreviously installed<br />
Authorization (This functionality can be used in<br />
modification and/or repair will introduce<br />
the initial andintermediate approach segments,<br />
noadverse effect upon the airworthiness<br />
the final ph<br />
of the product.<br />
<strong>EASA</strong>.A.S.00645 LEARJET 55 Installation of Honeywell ACAS II CAS 67A and 1. FAA TCDS A10CE plus JAA TGL No 8 and<br />
17.05.2005<br />
Mode S XPDR MST 67A<br />
JAA TGL No 13 apply2. This STC is approved<br />
only for the product configuration as defined in<br />
the approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations<br />
<strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>5 CESSNA 5<strong>01</strong>-551 Installation of a Honeywell KTA 870 and<br />
ART2000<br />
15.06.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>052 CESSNA 525- 525A Installation of a Dual MST 67A Mode S This STC is approved only for the product<br />
13.06.2005<br />
Transponder System.<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>EASA</strong>.A.S.<strong>01</strong>053 525<br />
Installation of Dual Garmin GTX 330D Mode<br />
17.11.2005<br />
CESSNA 525A<br />
SAFM Supplement 20<strong>04</strong>-16-8 Revision A or<br />
later <strong>EASA</strong> approved RevisionMM Supplement<br />
2005-16-10 Revision A or later <strong>EASA</strong><br />
approved Revision<br />
<strong>EASA</strong>.A.S.<strong>01</strong>116 PA-42 SERIES Installation of Artex ELT 406. 23.06.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>213 CESSNA 650 Installation of SATCOM Universal TT-3000 16.11.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>214 CESSNA 650 Installation of Airshow Entertainer System Part 25 of the Federal Aviation Regulations<br />
effective February 1, 1965 as amended by<br />
Amendments 25-1 through 25-39; TGM JAA<br />
leafletNo. 17Weight and Balance Analysis,<br />
Report 2005-17-9, Rev. A<br />
13.03.2006<br />
<strong>EASA</strong>.A.S.<strong>01</strong>215 CESSNA 550-560-S550 Installation of ACAS II CAS 67A and Dual<br />
Mode - S Transponder RCZ-833<br />
23.09.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>262 LEARJET 55 Installation of Secondary UNS 1F 23.06.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>263 LEARJET 55 Installation of ELT 406 29.06.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>274 GULFSTREAM ASTRA/SPX Upgrade of Universal UNS-1C to 1C+ 21.09.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>5<strong>01</strong> REV. 1 525, 525A Installation of Honeywell KMH 880 or KMH-980 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.06.2<strong>01</strong>1<br />
<strong>EASA</strong>.A.S.<strong>01</strong>502 CESSNA 5<strong>01</strong><br />
CESSNA 551<br />
Installation of Honeywell RDS 84 WX System. 16.08.2005<br />
<strong>EASA</strong>.A.S.<strong>01</strong>529 BEECH 1900 Installation of Universal Flight Manager System<br />
UNS-1L<br />
25.<strong>01</strong>.2006<br />
<strong>EASA</strong>.A.S.<strong>01</strong>531 BEECH 200<br />
Installation of Universal Flight Management<br />
24.10.2006<br />
BEECH 200C<br />
System UNS-1L<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 292/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4290 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
<strong>EASA</strong>.A.S.<strong>01</strong>532 IAI ASTRA SPX Installation of Universal Cockpit Display System n/a 14.12.2005<br />
10<strong>01</strong>4297 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.<strong>01</strong>541 BEECH 200<br />
Installation of Universal Multifunction Display<br />
31.08.2006<br />
GmbH<br />
BEECH 200C<br />
BEECH B200<br />
BEECH B200C<br />
MFD-640<br />
10<strong>01</strong>4299 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.<strong>01</strong>543 ASTRA 1125<br />
Installation of Collins TCAS 4000 Certification basis of the change: FAR Part 25,<br />
28.08.2006<br />
GmbH<br />
GULFSTREAM 100<br />
additionally JAA Leaflet No. 8 Rev. 2 (ACAS<br />
II), JAA Leaflet No. 13 Rev. 1 (Mode S ELS),<br />
JAA Leaflet No. 18 (Mode S EHS)<br />
10<strong>01</strong>4300 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.<strong>01</strong>544 WESTWIND ASTRA 1125 Installation of Garmin GNC 300XL Certification basis of the change: FAR Part 25,<br />
28.08.2006<br />
GmbH<br />
additionally <strong>EASA</strong> AMC 20-5 (GPS)<br />
10<strong>01</strong>4329 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.<strong>01</strong>582 CESSNA 560 (CITATION V) Installation, Completion of custom Aircraft Ref. G-FM250<strong>04</strong>0<strong>01</strong> Rev. N/C: Limited to S/N<br />
13.03.2006<br />
GmbH<br />
Interior for BD700-1A10 Global Expressacc.:<br />
CDL D954000 Rev. KValidation of imported<br />
TCC STC: SA<strong>04</strong>-113<br />
9145<br />
10<strong>01</strong>4345 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4346 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4351 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4366 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4370 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4374 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4457 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4458 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4541 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4553 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4647 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4726 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4741 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4742 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>4922 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
<strong>EASA</strong>.A.S.<strong>01</strong>608 BEECH 200<br />
BEECH 200C<br />
BEECH B200<br />
BEECH B200C<br />
<strong>EASA</strong>.A.S.<strong>01</strong>609 BEECH 200<br />
BEECH 200C<br />
BEECH B200<br />
BEECH B200C<br />
<strong>EASA</strong>.A.S.<strong>01</strong>616 LEARJET 35<br />
LEARJET 35A<br />
<strong>EASA</strong>.A.S.<strong>01</strong>636 CESSNA 550<br />
CESSNA 560<br />
CESSNA S550<br />
Installation of Blue Sky C-1000 SATCOM 31.08.2006<br />
Installation of Universal TAWS 31.08.2006<br />
Installation of Flight Data Recorder F1000 26.10.2005<br />
Installation of Honeywell CAS 81 ACAS and<br />
MST 67A Mode-S XPDR<br />
<strong>EASA</strong>.A.S.<strong>01</strong>641 CONSTRUCCIONES C-212 Installation of CAS 67A ACAS II and dual MST<br />
67A Mode-S XPDR<br />
<strong>EASA</strong>.A.S.<strong>01</strong>649 BEECH 300<br />
BEECH 300LW<br />
BEECH B300<br />
<strong>EASA</strong>.A.S.02511 CESSNA 525<br />
CESSNA 525A<br />
<strong>EASA</strong>.A.S.02515 CESSNA 525<br />
CESSNA 525A<br />
<strong>EASA</strong>.A.S.02628 LEARJET 35<br />
LEARJET 35A<br />
Installation of Universal UNS-1L Softeware<br />
802.XX<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Instructions for Continued Airworthiness, Doc.<br />
No. 2005-33-10 Rev. B<br />
Installation of EGPWS MARK VIII Maintenance Manual Supplement 2005-9-10-<br />
Rev. B<br />
Installation of Skywatch HP Maintenance Manual Supplement 2005-10-10<br />
Rev B<br />
Installation of Universal UNS 1L/K+ Certification Basis of the change: FAR Part 25,<br />
additionally <strong>EASA</strong> AMC 20-4 (B-RNAV), <strong>EASA</strong><br />
AMC 20-5 (GPS), JAA TGL No. 10 Rev. 1 (P-<br />
RNAV)<br />
<strong>EASA</strong>.A.S.02651 PIPER PA-46-310P<br />
Installation of Garmin GTX 330 or Garmin GTX<br />
PIPER PA-46-350P<br />
330D Transponder<br />
<strong>EASA</strong>.A.S.02802 LEARJET 35<br />
Installation of Honeywell RDR 2000 and KMD<br />
LEARJET 35A<br />
850.<br />
<strong>EASA</strong>.A.S.02903 CESSNA C650 Installation of Solid State Flight Data Recorder<br />
(SSFDR) F1000<br />
<strong>EASA</strong>.A.S.02924 BEECH 1900<br />
Installation of an Executive Power System Prior to installation of this modification the<br />
BEECH 1900C WET WING, (EPS) with Inverter and Power Outlet. installer must determine that the<br />
AIRLINER<br />
interrelationship between this modification and<br />
BEECH 1900D<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>EASA</strong>.A.S.02925 BEECH 1900<br />
BEECH 1900C, AIRLINER<br />
BEECH 1900D<br />
Installation of a Satcom System for Passenger<br />
Communication.<br />
<strong>EASA</strong>.A.S.03169 CESSNA 650 CITATION III,VI,VII Installation of Honeywell CAS-67A and RCZ-<br />
833 Mode S transponders.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 293/<strong>462</strong><br />
14.11.2005<br />
23.02.2006<br />
13.07.2006<br />
31.07.2006<br />
28.07.2006<br />
11.09.2006<br />
27.<strong>04</strong>.2006<br />
25.06.2007<br />
<strong>04</strong>.05.2007<br />
07.09.2007<br />
07.09.2007<br />
<strong>01</strong>.02.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5151 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.03512 PILATUS PC-12<br />
Replacement of existing KX 165 COM / NAV, Limited to single GNS 480 installation per<br />
17.10.2008<br />
GmbH<br />
PILATUS PC-12/45<br />
KLN 90B GPS, and GTX 330D Mode S cockpit only.Prior to installation of this<br />
PILATUS PC-12/47<br />
Transponder installation by GNS480 COM / modification the installer must determine that<br />
NAV / GPS and GTX 33D Mode S<br />
the interrelationship between this<br />
Transponder installation.<br />
modification and any other previously installed<br />
modification will introduce no a<br />
10<strong>01</strong>5152 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.03513 PILATUS PC-12<br />
Installation of AIRCELL SATCOM ST3100 1. Prior to installation of this modification the<br />
14.10.2008<br />
GmbH<br />
PILATUS PC-12/45<br />
installer must determine that the<br />
PILATUS PC-12/47<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>5161 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5171 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5190 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5221 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5222 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5223 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5224 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5225 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10<strong>01</strong>5231 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
<strong>EASA</strong>.A.S.03530 CESSNA 525<br />
CESSNA 525A<br />
<strong>EASA</strong>.A.S.03545 PILATUS PC-12<br />
PILATUS PC-12/45<br />
PILATUS PC-12/47<br />
<strong>EASA</strong>.A.S.03574 CESSNA 525<br />
CESSNA 525A<br />
Upgrade of existing Dual Honeywell MST 67A For variant 525 this change is limited to serial<br />
Mode-S XPDR Installation to EHS Capabilities numbers 525 0360 and subsequent<br />
Installation of Honeywell EGPWS MK VI by<br />
installing a Honeywell EGPWS MK-VI.<br />
Installation of GARMIN GPS 400 (w) or 500<br />
(w)<br />
1. For approved Software Versions refer to<br />
Airplane Flight Manual, Section II -<br />
Limitations2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously instal<br />
<strong>EASA</strong>.A.S.03638 REV. 1 650 (CITATION III) Primus 880 WX & MFRD installationRemoved None Prior to installation of this modification it 23.02.2<strong>01</strong>2<br />
existing Weather Radar Equipment:- i.a.w<br />
must be determined thatthe<br />
Installation Instructions, Doc. No. OPM-<br />
interrelationship between this modification<br />
003New Installed Weather Radar Equipment:-<br />
and any other previouslyinstalled<br />
Primus 880 Weather Radar System-<br />
modification and/ or repair will introduce<br />
Honeywell Multi Function Display, P/N 80-52<strong>04</strong>-<br />
no adverse effectupon the airworthiness<br />
XX-Xi.a.w In<br />
of the product.<br />
<strong>EASA</strong>.A.S.03639 REV. 2 650 (CITATION III) MK VII EGPWS Installation.Removed existing<br />
Equipment:i.a.w. Installation Instructions, Doc.<br />
No. OPM-0<strong>04</strong>New installed EGPWS<br />
Equipment:- Honeywell MK-VII EGPWSi.a.w.<br />
Installation Instructions, Doc. No. OPM-<br />
0<strong>04</strong>Revision 1: By revising the interface<br />
between the<br />
<strong>EASA</strong>.A.S.03640 REV. 1 650 (CITATION III) RAAS activation on the Honeywell MK-VII<br />
EGPWSi.a.w. Installation Instructions, Doc. No.<br />
OPM-005 Revision 1 has been issued to reflect<br />
the transfer of STC.<br />
<strong>EASA</strong>.A.S.03641 REV. 1 650 (CITATION III) P-RNAV Compliance on the installed GNS-<br />
XLS FMS, i.a.w. InstallationInstructions, Doc.<br />
No. OPM-006 Revision 1 has been issued to<br />
reflect the transfer of STC.<br />
<strong>EASA</strong>.A.S.03642 REV. 1 650 (CITATION III) FA2100 CVR installationRemoved Equipment:-<br />
i.a.w. Installation Instructions, Doc. No. OPM-<br />
007New Installed Equipment:- FA2100 Cockpit<br />
Voice Recorder Systemi.a.w. Installation<br />
Instructions, Doc. No. OPM-007 Revision 1 has<br />
been issued to reflect the transfer<br />
<strong>EASA</strong>.A.S.03653 CESSNA CITATION C525 Installation of AIRCELL Iridium Dual Patch<br />
Satcom Antenna.<br />
07.07.2008<br />
13.10.2008<br />
28.<strong>04</strong>.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.02.2<strong>01</strong>2<br />
1. Antenna Installation only.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will introduce no adverse<br />
effect upon the air<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 294/<strong>462</strong><br />
12.05.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5295 JET AVIATION FLUGZEUGWARTUNG <strong>EASA</strong>.A.S.03840 CESSNA 650 Installation of dual Honeywell GNS-XLS 1) Prior to installation of this modification the<br />
27.05.2009<br />
GmbH<br />
PRNAV FMS<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2) The ins<br />
10027115 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10027116 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10027199 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10027391 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10027933 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10028549 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10028945 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10035941 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
10038721 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
P-<strong>EASA</strong>.A.S.03705 500, 550, S550, 560 Installation of a TAWS System Honeywell Mark Restricted to aircraft which already have<br />
VIII EGPWS<br />
installed a suitablemultifunction display.<br />
P-<strong>EASA</strong>.A.S.03730 500, 550, S550, 560 Installation of an FMS System Universal UNS-<br />
1M<br />
P-<strong>EASA</strong>.A.S.03743 P.180 AVANTI II Installation of Garmin GPS-400 / 400W<br />
System<br />
1) Prior to installation of this modification 08.09.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
None The installation of Air Data Computer<br />
B&D ADC900<strong>04</strong> is optional. Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will in<br />
08.09.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
14.09.2009<br />
P-<strong>EASA</strong>.A.S.03654 500, 550, 560 Installation of Honeywell KLN-94-GPS The installation is limited to Cessna models Prior to installation of this modification it 28.09.2009<br />
500, 550 and 560 equippedwith Honeywell must be determined thatthe<br />
SPZ 500 Auto Pilot /Flight Director system and interrelationship between this modification<br />
RD600 /RD44 Horizontal Situation Indicator and any other previouslyinstalled<br />
525A Upgrade of existing Dual Garmin GTX 330D<br />
Transponder System for EHS<br />
system Limitations according to AFMS 2008-8-<br />
8<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
,,interrelationship between this<br />
modification and any otherpreviously<br />
installed modification and/ or repair will<br />
introduce noadverse effect upon the<br />
airworthiness of the product. The<br />
<strong>EASA</strong>.A.S.03911 BEECH 1900 15.07.2009<br />
P.180 AVANTI, AVANTI II Installation of In-Flight Entertainment System in<br />
accordance withEngineering Order, Doc. No.<br />
2009-9<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
,,interrelationship between this<br />
modification and any otherpreviously<br />
installed modification and/ or repair will<br />
introduce noadverse effect upon the<br />
airworthiness of the product. The<br />
17.11.2009<br />
22.02.2<strong>01</strong>0<br />
BD-700-1A11 Cabin Reconfiguration Restricted to ASN 9166A prerequisite for this Prior to installation of this modification it 29.07.2<strong>01</strong>1<br />
approval is Transport Canada STC No. SA05- must be determined thatthe<br />
60(FAA STC No ST02140NY) as applicable to interrelationship between this modification<br />
ASN 9166. However <strong>EASA</strong> has notapproved and any other previouslyinstalled<br />
this STC for ASN9166 and if this aircraft is to modification and/ or repair will introduce<br />
be entered onan EU register then the ST no adverse effectupon the airworthiness<br />
of the product.<br />
EMB-135BJ Installation of 4 Place Ambulance Stretcher<br />
System/ VIP interior.Description as per:Master<br />
Data List reference 2<strong>01</strong>1-8-16, Revision A,<br />
dated 26th February2<strong>01</strong>2. Engineer Order<br />
reference 2<strong>01</strong>1-8, Revision A, dated 26th<br />
February 2<strong>01</strong>2.AFM Supplement, reference 2<br />
None. None. 09.03.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 295/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0869 JET AVIATION FLUGZEUGWARTUNG<br />
CESSNA 560XL Installation of a Moving Map System. None. Prior to installation of this modification it 31.07.2<strong>01</strong>2<br />
GmbH<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>2792 JET AVIATION FLUGZEUGWARTUNG<br />
GmbH<br />
525<br />
525A<br />
WX-950 Stormscope installation. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.12.2<strong>01</strong>2<br />
10<strong>01</strong>4249 JET AVIATION GMBH <strong>EASA</strong>.A.S.<strong>01</strong>471 LEARJET 55<br />
LEARJET 55C<br />
Installation of Flight Data Recorder F1000 <strong>01</strong>.08.2005<br />
10<strong>01</strong>4291 JET AVIATION GMBH <strong>EASA</strong>.A.S.<strong>01</strong>533 IAI ASTRA SPX Installation of Universal Unilink UL-6<strong>01</strong> Certification Basis:FAR Part 25, TGL Leaflet<br />
No. 15 and 16<br />
19.<strong>04</strong>.2006<br />
10<strong>01</strong>4353 JET AVIATION GMBH <strong>EASA</strong>.A.S.<strong>01</strong>618 CESSNA 560 (CITATION V) Installation of Honeywell EGPWS Mark VIII 02.11.2005<br />
10<strong>01</strong>4393 JET AVIATION GMBH <strong>EASA</strong>.A.S.<strong>01</strong>683 BEECH 1900<br />
Installation of Universal UNS-1K+ Instructions for Continued Airworthiness, Doc.<br />
31.08.2006<br />
BEECH 1900C, AIRLINER<br />
BEECH 1900D<br />
No. 2005-35-10 Rev. B<br />
10<strong>01</strong>4394 JET AVIATION GMBH <strong>EASA</strong>.A.S.<strong>01</strong>684 BEECH 1900<br />
BEECH 1900D<br />
Installation of Universal TAWS and MFD 640 28.08.2006<br />
10<strong>01</strong>44<strong>01</strong> JET AVIATION GMBH <strong>EASA</strong>.A.S.<strong>01</strong>696 LEARJET 31 Installation of Bluesky C-1000 SATCOM -- 03.08.2006<br />
10039198 JET AVIATION ST. LOUIS, INC. FAA STC ST<strong>01</strong>065WI-D BD-700-1A10/11 Installation of a Supplemental Crew Oxygen None The supplemental crew oxygen masks 17.<strong>04</strong>.2<strong>01</strong>2<br />
System<br />
are not intended to be used in<br />
anemergency situation as a direct<br />
replacement for the type-certificatedcrew<br />
oxygen mask with integral smoke<br />
goggles.Prior to installation of this<br />
modification it must be determined<br />
thatthe i<br />
10039199 JET AVIATION ST. LOUIS, INC. FAA STC ST02658CH-D BD-700-1A10 Installation of a Passenger Address System None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.<strong>04</strong>.2<strong>01</strong>2<br />
10<strong>04</strong>0607 JET AVIATION ST. LOUIS, INC. FAA STC ST<strong>01</strong>376WI-D BD-700-1A10 Installation of a Cabin Interior Arrangement,<br />
Passenger Oxygen Systemand Emergency<br />
Lighting<br />
Restricted to ASN 9267 (Configuration 13) Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.07.2<strong>01</strong>2<br />
10<strong>04</strong>1674 JET AVIATION ST. LOUIS, INC. FAA STC ST02868CH-D CL-600-2B16 (CL-6<strong>04</strong> VARIANT) Installation of Drain Mast None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.10.2<strong>01</strong>2<br />
10<strong>01</strong>5882 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02000 FAA STC ST<strong>01</strong>319WI-D BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>04</strong><br />
Addition of Runway Awareness & Advisory<br />
System-RAAS to Honeywell MK-V & MK-VII<br />
Enhanced Ground Proximity Warning System-<br />
EGPWS<br />
10<strong>01</strong>5883 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.020<strong>01</strong> FAA STC ST<strong>01</strong>318WI-D BOMBARDIER CL-600-2B16 Software upgrade to 218-218 of the Honeywell<br />
MK-V Enhanced Ground Proximity Warning<br />
System to support Runway Awareness &<br />
Advisory System (RAAS).<br />
10<strong>01</strong>6260 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02539 FAA STC ST02543CH-D BOMBARDIER CL-600-2B16 Installation of a Cabin Interior Arrangement,<br />
Passenger Oxygen System, and Emergency<br />
Lighting.<br />
1. Prerequisite: MK V or MK VII EGPWS<br />
must be installed at Software Level - 218-218<br />
or greater.2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously in<br />
Prerequisite: MK V EGPWS must be installed<br />
per Bombardier Service Bulletin 6<strong>04</strong>-34-020<br />
or 6<strong>04</strong>-34-025.<br />
06.09.2007<br />
06.09.2007<br />
Restricted to ASN 57<strong>01</strong>. 03.06.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 296/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6261 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02540 FAA STC ST4837WI-T BOMBARDIER CL-600-2B16 Installation of an Audio International Articulated Prior to installation of this modification the<br />
03.10.2008<br />
Mounting Arm and Data Connectivity for an installer must determine that the<br />
Electronic Flight Bag<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6411 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02743 FAA STC ST00754WI BOMBARDIER CL-600-1A11 (CL-<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Installation of Emergency Lighting System. This STC must be installed with Cabin interior<br />
arrangement per <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.02745 and an oxygen system<br />
per <strong>EASA</strong> STC <strong>EASA</strong>.IM.A.S.02744 or other<br />
approved interior arrangement and oxugen<br />
10<strong>01</strong>6412 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02744 FAA STC ST00755WI BOMBARDIER CL-600-2B16 Installation of Passenger Oxygen System.<br />
system.<br />
This STC must be installed with Cabin interior<br />
arrangement per <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.02745 and an emergency<br />
lighting per <strong>EASA</strong> STC. No. IM.A.S.02743 or<br />
other approved interior arrangement and<br />
emergency lighting system.<br />
10<strong>01</strong>6413 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02745 FAA STC ST00756WI BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Cabin Interior Arrangement. This STC must be installed concurrent with an<br />
3A<br />
emergency lighting system per <strong>EASA</strong> STC No.<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
<strong>EASA</strong>.IM.A.S.02743 and an oxygen system<br />
3R<br />
per<strong>EASA</strong>.IM.A.S.02744 or other approved<br />
BOMBARDIER CL-600-2B16 (6<strong>04</strong>)<br />
emergency lighting and oxygen system.<br />
10<strong>01</strong>6414 JET AVIATON ST. LOUIS, Inc. <strong>EASA</strong>.IM.A.S.02746 FAA STC ST00812WI BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Installation of the Allied Signal MK-V Enhanced Gama Support Services Modification No.<br />
03.06.2008<br />
3A<br />
Ground Proximity Warning System (EGPWS). GSSL-MIN-CL6<strong>04</strong>-226 (Including Gama<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
Support Services Flight Manual Change Sheet<br />
3R<br />
No. GSS-FMS-CL6<strong>04</strong>-226 <strong>EASA</strong> approval<br />
BOMBARDIER CL-600-2B16 (6<strong>04</strong>)<br />
number <strong>EASA</strong>.A.A.<strong>01</strong>831), or equivalent<br />
<strong>EASA</strong> approved modification, is a prerequisite<br />
for the <strong>EASA</strong> appro<br />
10<strong>04</strong>0724 JET AVIATON ST. LOUIS, Inc. FAA STC NO. ST02744CH-D BD-700-1A10 Installation of a Rockwell Collins Wireless Local None. Prior to installation of this modification it 24.07.2<strong>01</strong>2<br />
Area Network (WLAN).<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>2519 JET AVIATON ST. LOUIS, Inc. FAA STC SA02789CE MYSTERE FALCON MF 50 <strong>EASA</strong> validation of FAA originally approved<br />
STC SA02789CE "Installationof a Bendix/King<br />
CAS-81 TCAS System".<br />
Aeroplanes modified in accordance with this<br />
STC must be maintained inaccordance with<br />
Approved Instructions for Continued<br />
Airworthiness, JetAviation Report No. 13-<br />
027E054, Section O - Airworthiness<br />
Limitations,Revision NC dated June 03rd 2<strong>01</strong>1<br />
or later revi<br />
10<strong>01</strong>4336 JET AVIONICS AVIATION & MARINE <strong>EASA</strong>.A.S.<strong>01</strong>591 CESSNA 650 CITATION III BDI 0<strong>04</strong>-05 Updating to TCAS II & ELT system Applicable only if the STC No ST502CH of 16<br />
and installation SSFDR<br />
may 1996 was previously installed<br />
10<strong>01</strong>4349 JET AVIONICS AVIATION & MARINE <strong>EASA</strong>.A.S.<strong>01</strong>614 BEECH 58, BARON Imrpoving of avionics systems for updating FM FM Supplement Sandel SN-3400, dated<br />
immunity 8.33 kHz channelling, B-RNAV, Mode 09/07/2007.FM Supplement Sandel ST-3400,<br />
S Transponder, TAWS, Weather Radar, Traffic dated 09/07/2007.FM Supplement Garmin<br />
Advisory System, ELT and entertainment GTX 330, dated 09/07/2007.FM Supplement<br />
system.<br />
Garmin GNS 430, dated 09/07/2007.FM<br />
Supplement Garmin MX-20, dated<br />
09/07/2007.FM Supplement L3 Sky-49<br />
20.03.2008<br />
20.03.2008<br />
20.03.2008<br />
Prior to installation of this modification it 06.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4674 JET AVIONICS AVIATION & MARINE <strong>EASA</strong>.A.S.02834 BOMBARDIER CL-215-6B11 Installation of Radar Altimeter AA-300 System N/A <strong>01</strong>.03.2007<br />
10<strong>01</strong>5<strong>04</strong>4 JET AVIONICS AVIATION & MARINE <strong>EASA</strong>.A.S.03360 CESSNA 500, CITATION BDI 0<strong>04</strong>-07 Installation of Mode S Transponder<br />
- Elementary Surveillance.<br />
10<strong>01</strong>5237 JET AVIONICS AVIATION & MARINE <strong>EASA</strong>.A.S.03664 CESSNA CITATION 5<strong>01</strong> Installation of Mode S Transponder. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 297/<strong>462</strong><br />
11.10.2005<br />
08.08.2007<br />
05.03.2008<br />
23.12.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0231 JET AVIONICS AVIATION & MARINE PA-31T CHEYENNE II General avionic improvement/installation - None. Prior to installation of this modification it 19.06.2<strong>01</strong>2<br />
Replacement of GPS, MovingMap,<br />
must be determined that<br />
Stormscope, Weather Radar system, TCAI I.<br />
heinterrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.<br />
10<strong>01</strong>6135 JET ENGINEERING LLC <strong>EASA</strong>.IM.A.S.02331 FAA STC ST<strong>01</strong>943LA DC-9-81 (MD-81)<br />
Installation of a JET Engineering, Ltd. This installation is done concurrently with STC<br />
14.06.2007<br />
DC-9-81 (MD-82)<br />
Advanced Jet Nozzles on the above airplane <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>2, installation of Jet<br />
DC-9-81 (MD-83)<br />
model(s) when powered by Pratt & Whitney Engineeirng, Ldt. Turbine Exhaust Cone<br />
DC-9-81 (MD-87)<br />
JT8D-21JT8D-217, 7A, -217C, 219 engines Mixer(TECM), which modifies the Pratt &<br />
Whitney JT8D-217, JT8D-217A, -217C, -219<br />
engines.<br />
10<strong>01</strong>6698 JET ENGINEERING LLC <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>2 FAA STC ST<strong>01</strong>944LA PRATT & WHITNEY JT8D-217 Installation of a JET Engineering, Ltd. Turbine This installation must be done concurrently with<br />
05.03.2007<br />
PRATT & WHITNEY JT8D-217A Exhaust Cone Mixer (TECM)<br />
STC <strong>EASA</strong>.IM.A.S.02331, installation of Jet<br />
PRATT & WHITNEY JT8D-217C<br />
Engineering, Ltd. Advanced Jet Nozzles which<br />
PRATT & WHITNEY JT8D-219<br />
modifies the airplane engine<br />
installation.Approval of this change in type<br />
design applies to the above engine model(s) o<br />
10<strong>01</strong>5249 JET ENGINEERING TECHNICAL<br />
SUPPORT<br />
10031570 JET ENGINEERING TECHNICAL<br />
SUPPORT<br />
<strong>EASA</strong>.A.S.03688 BAE JETSTREAM 41 Mode-S Enhanced Surveillance (EHS)<br />
Upgrade<br />
P-<strong>EASA</strong>.A.S.03968 DORNIER 328-100, 328-300 Installation of Emergency Lighting Power<br />
Supply System<br />
10<strong>01</strong>6549 JETAIRE AEROSPACE, LLC <strong>EASA</strong>.IM.A.S.02929 REV. 2 FAA STC ST<strong>01</strong>466LA-D B737-300/-400 Installation of fire protection systems, lower<br />
cargo compartment Class Dto Class C<br />
conversion. Original FAA STC ST<strong>01</strong>466LA-D<br />
for B737-300;this revision is implementing the<br />
validation of FAA STC ST00749LA-D forB737-<br />
400.<br />
10<strong>01</strong>5707 JETPROP, LLC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>698 LBA STC SA1189 PIPER PA-46-310P<br />
PIPER PA-46-350P<br />
10<strong>01</strong>6000 JETPROP, LLC. <strong>EASA</strong>.IM.A.S.02158 ST00541SE PIPER PA-46-310P<br />
PIPER PA-46-350P<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of the following engines, propellers 1. This STC is valid only in connection with<br />
and associated hardware:Pratt & whitney PT6A-FAA<br />
STC SA00859AT (EMZ 0721/1076)2.<br />
34 engine limited to 560 SHP at 2200 This airplane/engine/propeller combination is<br />
RPMPratt & Whitney PT6A-35 engine limited life limited. The life limit for the modified<br />
to 560 SHP at 2190 RPMPratt & Whitney airplane shall be detrmined by usingthe<br />
PT6A-21 engine limited to 550 SHP at 2200 minimum value calculated by the following f<br />
RP<br />
Installation of PWC PT6A-34/-35/-21 turboprop PT6A-34, rated at 560 HP, 2200 RPMPT6Aengines<br />
in any combination withHartzell 35, rated at 560 HP, 2190 RPMPT6A-21,<br />
Propellers:HC-E4N-3I/E85<strong>01</strong>B-3.5HC-E4N- rated at 550 HP, 2200 RPMThis<br />
3M/E8190KHC-E4N-3N/D8292HC-E4N- airplane/engine/propeller combination is life<br />
3N/D8292(B,K)-2and MT-Propeller:MTV-16-1- limited. The life limit for the modified airplane<br />
E-C-F-R(P)/CFR206-58aon Piper PA-46-310P shall be determined by using the minimum<br />
and PA-46-350P airp<br />
value calcul<br />
10<strong>01</strong>5892 JOE'S AIRCRAFT MODS LLC <strong>EASA</strong>.IM.A.S.02<strong>01</strong>2 FAA STC SA564NE CESSNA F172-N Installation of a Textron Lycoming Model O-360-<br />
A4A, -A4M or -A4N engine and a Sensinech<br />
Model 76EM8S14-0-60 fixed Pitch metal<br />
propeller.<br />
10034129 KAWAK AVIATION TECHNOLOGIES,<br />
INC.<br />
REV. 1 FAA STC SR<strong>01</strong>561SE KAMAN K-1200 Title: Auxiliary Hydraulic System, K-Max K1200<br />
Helicopter Model 36300,DWG 36300, REV B,<br />
25th June 2005Description: Auxiliary hydraulic<br />
power source provides hydraulic powerfor<br />
external implements used in fire fighting,<br />
logging, and agriculturaloperation.<br />
10<strong>01</strong>5824 KELOWNA FLIGHTCRAFT Ltd. <strong>EASA</strong>.IM.A.S.<strong>01</strong>896 SA<strong>04</strong>-32 BOMBARDIER CL-215-6B11 TCCA STC SA<strong>04</strong>-32 issue 3SPZ-4500<br />
Honeywell AFCS and Universal UNS 1K/1L<br />
FMS<br />
16.12.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.08.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.08.2<strong>01</strong>2<br />
26.10.2005<br />
24.<strong>04</strong>.2008<br />
08.11.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.03.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 298/<strong>462</strong><br />
17.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028498 KEYSTONE HELICOPTER<br />
P-<br />
REV. 1 FAA STC SR<strong>01</strong>127NY-D S-76A, S-76B, S-76C Installation of a Keystone Medical Interior - See As specified in the approved RFMS. RFMS N° 00549 is required for this 03.02.2<strong>01</strong>0<br />
CORPORATION<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>562<br />
Conditions<br />
installation with configurations 1,2,3,4,5<br />
and 6 The following configurations are<br />
approved for this installation:<br />
Configuration No. 1 -P/N 02076-10E000-<br />
1 Lifeport litter base installedwith one or<br />
two litters, control cab<br />
100285<strong>01</strong> KEYSTONE HELICOPTER<br />
CORPORATION<br />
10028503 KEYSTONE HELICOPTER<br />
CORPORATION<br />
10029641 KEYSTONE HELICOPTER<br />
CORPORATION<br />
10030668 KEYSTONE HELICOPTER<br />
CORPORATION<br />
P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>563<br />
P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>564<br />
FAA STC SR00910NY S-76A, S-76B, S-76C Structural provisions for the installation of a<br />
Spectrolab SX5Searchlight to the left or right<br />
side of the S76.<br />
FAA STC SR00642NY S-76A, S-76B, S-76C Installation of a Liquid Oxygen System for<br />
Medevac use<br />
As specified in the approved RFMS. This STC covers the structural provisions 18.<strong>01</strong>.2<strong>01</strong>0<br />
for the installation of an SX5searchlight.<br />
Wiring and associated control of the SX5<br />
and assessment ofthe effects on aircraft<br />
performance and handling must be the<br />
subject ofseparate modification action.<br />
Prior to ins<br />
- This approval should not be incorporated in<br />
any aircraft of thisspecific model on which<br />
other approved modifications are<br />
incorporated,unless it is determined that the<br />
interrelationship between this changeand any<br />
other previously incorporated approved mod<br />
Not Applicable 18.<strong>01</strong>.2<strong>01</strong>0<br />
FAA STC SR02588NY-D S-76C Installation of Goodrich Auxiliary Utility Hoist As specified in the approved RFMS Installation of the Auxiliary Hoist requires:<br />
1. Pre-installation of the Goodrich<br />
Primary Hoist p/n 42325-18-1<br />
inaccordance with Sikosrsky TC Option<br />
33776-061154.and 2. On aircraft with<br />
Turbomeca Arriel 1S1 or 2S1<br />
engines,pre-installation of FAA STC<br />
SR<strong>01</strong>61<br />
FAA STC SR02597NY-D S92A Installation of a tail mounted, forward facing<br />
camera.<br />
08.<strong>04</strong>.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.06.2<strong>01</strong>0<br />
10<strong>04</strong>1473 KMLEX AVIATION INC. TCCA STC Q-LSA10-<strong>04</strong>7/D FALCON 50EX Relocation of Radio Altimeter<br />
Restricted to S/N 278 Prior to installation of this modification it 19.09.2<strong>01</strong>2<br />
ConverterValidation of TCCA STC N° Q-<br />
must be determined thatthe<br />
LSA10-<strong>04</strong>7/D issue dated November <strong>04</strong>, 2<strong>01</strong>0.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1475 KMLEX AVIATION INC. TCCA STC Q-LSA10-<strong>04</strong>8/D FALCON 50EX Replacement of Aft lavatory faucet adapter -<br />
Dassault Falcon 50EXaircraft MSN<br />
278Validation of TCCA STC N° Q-LSA10-<br />
<strong>04</strong>8/D issue dated November <strong>04</strong>, 2<strong>01</strong>0.<br />
10<strong>01</strong>5415 KNH AVIATION SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>136 FAA STC ST09993SC FAIRCHILD DORNIER DO 328-<br />
300<br />
FAA STC ST09993SC; 12 Seats configuration 1. This STC may be installed only in<br />
(extended to 14 seats throught minor change, combination with Change Notice CN-F0535, -<br />
part of Avcraft CN-F 0535)Installation of F0<strong>04</strong>0,-F<strong>01</strong>25 owned by Avcraft Germany<br />
interior shell, cabinetry ,seats, card tables, and RUAG minor Changes “In Seat Power<br />
monitors, entertainment system, system wiring, Supply and FI Switch” and “Installation of<br />
and lavatory in accordance with<br />
Double Latches on drawers” .2. The water<br />
pumping syste<br />
10<strong>01</strong>5482 KNH AVIATION SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>242 FAA STC ST09468AC DORNIER D328-100 installation of a corporate/executive interior 1. According to the application as forwarded by<br />
FAA letter dated 27 April 2005 and FAA STC<br />
ST09468AC, the approval is limited to the<br />
aircraft S/N 30952. Furthermore this installation<br />
has to be performed in combination with the<br />
installation of FAA STC ST094<br />
Restricted to S/N 278 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.09.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 299/<strong>462</strong><br />
20.06.2006<br />
15.08.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
100283<strong>04</strong> KNOTS 2U, LTD. P-<br />
PA-28-151, PA-28-161,<br />
Piper Wing Tips with Landing / Recognition None Prior to installation of this modification it 16.12.2009<br />
<strong>EASA</strong>.IM.A.S.03267<br />
PA-28-181, PA-28-2<strong>01</strong>T, Lights<br />
must be determined thatthe<br />
PA-28-236, PA-28R-2<strong>01</strong><br />
interrelationship between this modification<br />
PA-28-RT-2<strong>01</strong>T, PA-32-3<strong>01</strong><br />
and any other previouslyinstalled<br />
PA-28R-2<strong>01</strong>T, PA-28RT-2<strong>01</strong>,<br />
modification and/ or repair will introduce<br />
PA-32-3<strong>01</strong> T, PA-32R-3<strong>01</strong>,<br />
no adverse effectupon the airworthiness<br />
PA-32R-3<strong>01</strong>T<br />
of the product.<br />
10031230 KNOTS 2U, LTD. LBA EMZ SA1221 FAA SA1217GL 1. PA-32-3<strong>01</strong>FT, PA-32-3<strong>01</strong>XTC<br />
1. PA-32R-3<strong>01</strong>(HP)<br />
1. PA-32R-3<strong>01</strong>T(TC)<br />
2. PA-32-3<strong>01</strong>, PA-32-3<strong>01</strong>T<br />
2. PA-32R-3<strong>01</strong>, PA-32R-3<strong>01</strong>(SP)<br />
10031235 KNOTS 2U, LTD. FAA STC SA1521GL 1. PA-32-3<strong>01</strong>FT, PA-32-3<strong>01</strong>XTC<br />
1. PA-32R-3<strong>01</strong>(HP)<br />
1. PA-32R-3<strong>01</strong>T(TC)<br />
2. PA-32-3<strong>01</strong>, PA-32-3<strong>01</strong>T<br />
2. PA-32R-3<strong>01</strong>, PA-32R-3<strong>01</strong>(SP)<br />
Installation of wing root fairings in accordance<br />
with FAA STC SA1217GL(Revision of LBA<br />
EMZ 1221, issue 1, dated July 20, 20<strong>01</strong>).<br />
Installation of flaps, aileron, flap/fuselage and<br />
stabilator gap sealsin accordance with FAA<br />
STC SA1521GL.<br />
10031236 KNOTS 2U, LTD. LBA EMZ SA1222 FAA SA1195GL 1. PA-32-3<strong>01</strong>FT, PA-32-3<strong>01</strong>XTC Installation of Flap Hinge Fairing seals in<br />
1. PA-32R-3<strong>01</strong>(HP)<br />
accordance with FAA STCSA1195GL<br />
1. PA-32R-3<strong>01</strong>T(TC)<br />
(Revision of LBA EMZ 1222, issue 1, dated<br />
2. PA-32-260, PA-32-300<br />
2. PA-32-3<strong>01</strong>, PA-32-3<strong>01</strong>T<br />
2. PA-32R-300, PA-32RT-300<br />
2. PA-32R-3<strong>01</strong>(SP), PA-32S-300<br />
2. PA-32R-3<strong>01</strong>T(SP), PA-32R-300<br />
2. PA-32RT-300T<br />
July 20, 20<strong>01</strong>).<br />
10<strong>01</strong>4885 KORFF LUFTFAHRT <strong>EASA</strong>.A.S.03113 GROB G 109<br />
GROB G 109 B<br />
10<strong>01</strong>4470 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.02531 LEARJET 60 Installation of SSFDR and MFDAUInstallation<br />
of a Honeywell Solide State Flight Data<br />
Recorder and Teledyne Mini Data Acquisition<br />
Unit in Learjet Model 60<br />
Changes:- at the luggage compartment to be 1. Limted to S/N: 62192. This STC is<br />
used as basis for instruments,- additional cable approved only for the product configuration as<br />
routing in the wings- reinforced attachment defined in the approved design data referred to<br />
points at the lower side of both wings for under in the paragraphs "Description" and<br />
wing pots- reinforcements of the root tips- “Associated Technical Documentation”.<br />
operation with external loa<br />
Compatibility with other aircraft/engine con<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.08.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.08.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.08.2<strong>01</strong>0<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
10<strong>01</strong>4482 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.02545 CESSNA 340A Avionic Retrofit<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
25.<strong>04</strong>.2006<br />
10<strong>01</strong>4569 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.02673 BOMBARDIER DHC-6 SERIES<br />
300<br />
Installation of KMH-880, GPS-400 & KMD-850. Limited to S/N 0841. 13.<strong>04</strong>.2007<br />
10<strong>01</strong>4716 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.02892 PILATUS PC-12/45 Honeywell GNS-XLS FMS InstallationBy<br />
installing a single GNS-XLS Flight<br />
Management System with GPS and DME<br />
sensor.<br />
HB-FPI S/N 551. Valid for this S/N only. 23.<strong>04</strong>.2007<br />
10<strong>01</strong>4806 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03<strong>01</strong>0 PILATUS PC-12/47 HF 1050 & AFFS Installation by installing a new S/N 795 for initial installation.Approval valid for<br />
22.03.2007<br />
HF-1050 HF COM System with a PS440 HF<br />
Control Panel and a new F5K AFFS<br />
(Automated Flight Following System).<br />
S/N 795 and any other PC-12/47.<br />
10<strong>01</strong>4878 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03105 PIPER PA-31T Installation of Dual Mode-S XPDR &<br />
TASInstallation of- Dual Mode S Transponder<br />
GTX-330D with diversity antenna.- Traffic<br />
10<strong>01</strong>4945 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03205 CESSNA 340A<br />
Advisory System SKY497<br />
Installation of a Traffic Advisory System:By<br />
installing a SKY497 Skywatch Traffic Advisory<br />
System with appropriate antenna. Traffic<br />
information will be displayed on<br />
existingsystems.<br />
Reg. HB-LNLS/N: 31T-8020083Valid for this<br />
S/N only<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 300/<strong>462</strong><br />
30.<strong>04</strong>.2007<br />
11.12.2006<br />
11.05.2007<br />
28.08.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4974 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03260 PILATUS PC-12/47 FMS and DME installation:By installinga new<br />
GNS-XLS FMSa new DM-441B DME<br />
26.11.2007<br />
10<strong>01</strong>5230 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03648 PILATUS PC-12/47E FDR and CVR Installation. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
31.10.2008<br />
10<strong>01</strong>5275 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03770 PILATUS PC-12/45 GPS 400W and GMA 347 InstallationRemoved Prior to installation of this modification the<br />
02.03.2009<br />
Equipment:- KLM 90B GPS- Existing GPS installer must determine that the<br />
Antenna- KMA 24H Audio PanelNew Installed interrelationship between this modification and<br />
Equipment- GPS 400W GPS- GA 35 any other previously installed modification will<br />
GPS/WAAS Antenna- GMA 347 Audio Panel introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5277 KUERZI AVIONICS AG <strong>EASA</strong>.A.S.03789 PIPER PA-23-250 Dual GNS430W, GMA340, KN 63<br />
1. Prior to installation of this modification the<br />
InstallationOut: Dual KX-155 COM/NAV installer must determine that the<br />
systems, Trimble-2000 approach GPS system, interrelationship between this modification and<br />
KMA-24H Audio system, MKR-1<strong>01</strong> marker any other previously installed modification will<br />
system, KN-65 DME systemIn: Dual GNS- introduce no adverse effect upon the<br />
430W system, GMA-340 Audio/MKR system,<br />
KN-63 DME system.<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7221 KUERZI AVIONICS AG <strong>EASA</strong>.R.S.<strong>01</strong>382 BELL 206B Hellas installation:As a convertible EADS Reg.: D-HEDB S/N: 4197Valid for this S/N<br />
HELLAS (Helicopter Laser Radar) System that only<br />
provides the following functions:-Raw data<br />
acquisition-System development-System<br />
demonstrationThe rotorcraft can be operated<br />
either in a "Normal" or a "HELLAS" configurat<br />
10<strong>01</strong>7239 KUERZI AVIONICS AG <strong>EASA</strong>.R.S.<strong>01</strong>425 EUROCOPTER FRANCE SA<br />
315B<br />
NVIS Conversion.Includes Rad. Altimeter and<br />
Mode S ELS Transponder installation.<br />
10<strong>01</strong>7262 KUERZI AVIONICS AG <strong>EASA</strong>.R.S.<strong>01</strong>471 BELL 206B Radar altimeter installation including adapter<br />
plate.<br />
10027877 KUERZI AVIONICS AG P-<strong>EASA</strong>.A.S.03965 LEARJET 55 Installation of Satellite Tracking System SAT-<br />
111<br />
10033212 KUERZI AVIONICS AG 500N MD520N Gyro camera & equipment<br />
inst.(Gyrocam "Turret Assy" for filming or live<br />
broadcasting)<br />
08.<strong>04</strong>.2009<br />
25.10.2007<br />
Reg.: HB-XII S/N: 2551Mode S Transponder<br />
system alleviation of flight status according<br />
JAA TGL-13 note 10 granted.<br />
06.08.2008<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
18.12.2008<br />
None None 11.11.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.<strong>01</strong>.2<strong>01</strong>1<br />
10033622 KUERZI AVIONICS AG AS 350 B2, AS 350 B3 G500H Avionic Retrofit (Option 1 & 2)Option 1 None Prior to installation of this modification it 31.<strong>01</strong>.2<strong>01</strong>1<br />
Out: Original OEM installed -Airspeed Indicator -<br />
must be determined thatthe<br />
Gyro Horizon -Altimeter -Turn & Bank Indicator -<br />
interrelationship between this modification<br />
Directional Gyro -Vertical Speed Indicator In: -<br />
and any other previouslyinstalled<br />
Garmin G500H system including PFD/MFD<br />
modification and/ or repair will introduce<br />
GDU 620-Attitude heading Re<br />
no adverse effectupon the airworthiness<br />
of the product. As a m<br />
10034392 KUERZI AVIONICS AG MYSTÈRE-FALCON 50 FMS upgradeUpdate of the existing UNS-1k to<br />
UNS-1LW. Installation of a second<br />
FMS.Upgrade of the existing Collins VIR-31<br />
#1/2 and DME-41 #1/2 to VIR-32and DME-42<br />
so that ARINC429 can be used to interface<br />
with the dual FMS.<br />
10035249 KUERZI AVIONICS AG PC-6-B2-H4 Cold weather operation package (230VAC or<br />
110VAC)By installation of:- One TANIS<br />
TAS200 Battery Heater system- One TANIS<br />
TAS300 Turbine Preheat system- One Power<br />
receptacle in the cabin front right<br />
Restricted to MF50 S/N 183. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.03.2<strong>01</strong>1<br />
S/N: all The approval holder shall fulfill the<br />
obligations of Part 21,<br />
§21.A109.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 3<strong>01</strong>/<strong>462</strong><br />
08.06.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035488 KUERZI AVIONICS AG DHC-6-300 Installation of two Aspen Electronic Flight None Prior to installation of this modification it 27.06.2<strong>01</strong>1<br />
Display (EFD1000 Pro, oneGarmin GNS530W<br />
must be determined thatthe<br />
(GPS, COM, NAV), one Garmin GNS430W<br />
interrelationship between this modification<br />
(GPS, COM, NAV), oneGarmin GTX330<br />
and any other previouslyinstalled<br />
(XPDR) and one Garmin GTS800 (TAS)<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10036481 KUERZI AVIONICS AG MF50 P-RNAV and RNP10 certificationCertification <strong>EASA</strong> STC 10034392 is a required pre-<br />
of P-RNAV and RNP10 for a Falcon 50 based requisite.<br />
on existing <strong>EASA</strong>STC 10034392.<br />
10036940 KUERZI AVIONICS AG EC 130 B4 G500H Avionic RetrofitOut: Original OEM S/N: all; minimum one G500H compatible<br />
installed Horizon and Directional Gyro system( GPS/WAAS navigator is aprerequisite.<br />
option1 and 2) Original OEM installed Airspeed<br />
Indicator (only option 1) andAltimeter (only<br />
option 1),In: Garmin G500H system including<br />
PFD/MFD GDU 620, Attitude Heading<br />
10039239 KUERZI AVIONICS AG MF900 SATCOM Upgrade to WiFiActivation of the<br />
WLAN option of the existing AVIATOR 300<br />
SATCOM systemon MF900 S/N 118<br />
10<strong>04</strong><strong>01</strong>76 KUERZI AVIONICS AG B737-300 GSM mail tracker installation:a small GSM<br />
device integrated into the aircraft and able to<br />
report itscurrent position by means of GSM cell<br />
information.<br />
Prior to installation of this modification it 12.09.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. 03.11.2<strong>01</strong>1<br />
Limited to MF 900 S/N 118 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>04</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.06.2<strong>01</strong>2<br />
10<strong>04</strong>1972 KUERZI AVIONICS AG R 90-230RG Avionic upgrade Removed: - Original flight None. The approval holder shall fulfill the<br />
instrument including KCS55 pictorial<br />
obligations of Part 21 §21.A118. Prior to<br />
navigationsystem, attitude indication (with flight<br />
installation of this modification it must be<br />
director), electrical attitudeindication, encoding<br />
determined thatthe interrelationship<br />
Altimeter 2x, mechanical AS, VS and turn and<br />
between this modification and any other<br />
bank.- Original vacuum system<br />
previouslyinstalled modification and/ or<br />
repair will i<br />
10<strong>04</strong>2467 KUERZI AVIONICS AG PC-12/45 Replacement of obsolete systemsReplacement<br />
of: - Bendix/King EFIS40/50 Systems with<br />
Universal EFI890R 3-Display.Configuration<br />
(PFD/ND/CPFD) incl. required controls.-<br />
Universal UNS-1K FMS with UNS-1Lw FMS<br />
incl. LPV Monitor as primary NAVSource.<br />
Installation<br />
10<strong>01</strong>7171 KUERZI AVIONICS DEUTSCHLAND<br />
GMBH<br />
10028707 KUERZI AVIONICS DEUTSCHLAND<br />
GMBH<br />
<strong>EASA</strong>.R.S.<strong>01</strong>282 REV. 2 EUROCOPTER FRANCE SA<br />
330J<br />
S/N: 134 ; HB-FOG The approval holder shall fulfill the<br />
obligations of Part 21 §21.A118.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will in<br />
Avionics UpgradeGPS, Monitor, Cabin Prior to installation of this modification the<br />
Intercom, EMS, SAT111 Tracking System, HF installer must determine that the<br />
Radio, WX Radar, Power Connector, FM interrelationship between this modification and<br />
Radio<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
P-<strong>EASA</strong>.A.S.03752 REV.2 PC-6-B2-H4 Transfer of STC 10028707 Garmin G950<br />
Installation.Integration of a new Garmin G950<br />
Integrated Flight Deck and legacysystems on<br />
the Pilatus PC-6/B2-H4 model.The G950<br />
system (a derivate of the G1000 system)<br />
combines primary flightinstrumentation, aircraft<br />
s<br />
Required pre-modifications:- Pilatus PC-6 pitch<br />
trim warning system according SB-180-<br />
Electrical stall warning system, type Safe Flight<br />
1-02-0005 No. 164(Transmitter) and C-73113<br />
(Buzzer)- Electrical power distribution system<br />
(MCA 06/24/130)- Electrical fl<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 302/<strong>462</strong><br />
29.10.2<strong>01</strong>2<br />
03.12.2<strong>01</strong>2<br />
06.<strong>01</strong>.2009<br />
30.03.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038677 L D AVIATION PRAGUE, s.r.o. F172M<br />
Avionics upgrade - installation of:GMA 340 None. Prior to installation of this modification it 07.03.2<strong>01</strong>2<br />
F172N<br />
(audio), SL 40 (VHF COMM), SL 30 (VHF<br />
must be determined thatthe<br />
F172P<br />
NAV/COMM),MD 200-306 (CDI indicator),<br />
interrelationship between this modification<br />
GTX 328 (Mode S XPNDR), CI 102<br />
and any other previouslyinstalled<br />
(MKRantenna), Kannad 406 AF Compact<br />
modification and/ or repair will introduce<br />
(ELT), AV 200 (ELT antenna), CI 105(XPNDR<br />
no adverse effectupon the airworthiness<br />
antenna).<br />
of the product.<br />
10<strong>01</strong>6133 L-3 COMMUNICATIONS INTEGRATED <strong>EASA</strong>.IM.A.S.02329 FAA STC ST9765SC-D BOEING 767 Installation of a First-Class Interior/The project<br />
installs an all first-class interior in a Swiss<br />
registered Boeing 767 aircraft. This interior<br />
consists of installing 54seats, a bar and dining<br />
area, and upgrades to entertainment system<br />
1. Instruction for Continued Airworthiness<br />
(ICA) dated May 1, 2007.2. This approval is<br />
limited to only the installation made in the<br />
Boeing Model B767-306, Serial Number 30393<br />
aircraft.<br />
10<strong>01</strong>6313 L-3 COMMUNICATIONS INTEGRATED <strong>EASA</strong>.IM.A.S.02617 FAA STC ST091<strong>01</strong>AC-D BOEING 737-700 IGW<br />
electronics.<br />
Modification of aircraft environmental control Raytheon Systems Company "Type Design<br />
system.<br />
Data List" Report no. 98<strong>01</strong>03<strong>04</strong>-000.<br />
10<strong>01</strong>6314 L-3 COMMUNICATIONS INTEGRATED <strong>EASA</strong>.IM.A.S.02618 FAA STC ST09102AC-D BOEING 737-700 IGW Installation of passenger gaseous oxygen Raytheon Systems Company "Type Design<br />
equipment.<br />
Data List" Report no. 98<strong>01</strong>02<strong>04</strong>-000.<br />
10<strong>01</strong>6854 L-3 WESCAM INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>230 REV. 1 TCCA STC SH<strong>04</strong>-29 EUROCOPTER FRANCE AS 350 MX-15 camera installation (structural provisions<br />
B<br />
only).Note: The revision extends the<br />
EUROCOPTER FRANCE AS 350 applicability of STC <strong>EASA</strong>.IM.R.S.<strong>01</strong>230 to<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS<br />
355N<br />
AS355N.<br />
10<strong>01</strong>7071 L-3 WESCAM INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>507 REV. 1 TCCA STC SH<strong>04</strong>-29 SEE <strong>EASA</strong> APPROVED MODEL MX-Series Camera Installation (Structural This STC is for structural provisions only. Placard containing the following<br />
LIST<br />
Provisions Only)Note: This revision to the STC Functional and electricalaspects will require limitations to be installed in clearview of<br />
adds a second Downlink antenna<br />
separate airworthiness approval.VNE limited to the pilot:AS350: VNE Limited to 126<br />
(OMNIAntenna) and a MX-10 Camera 126ktsVFR OnlyCategory A operations KIAS, VFR Operations OnlyAS355:<br />
applicability.<br />
prohibited<br />
Category A operations prohibited. VNE<br />
Limited to 126 KIAS, VFROperations<br />
OnlyPrior to installation of this modi<br />
10027823 L-3 WESCAM INC. P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>517<br />
REV. 1 TCCA STC SH97-31 1. AS350 B, B1, B2, B3, BA, D<br />
2. AS355 E, F, F1, F2, N, NP<br />
MX-Series Camera Installation (Structural<br />
Provisions Only)<br />
This STC is for structural provisions only.<br />
Functional and electricalaspects will require<br />
separate airworthiness approval.VNE limited to<br />
126ktsVFR OnlyCategory A operations<br />
prohibited<br />
10<strong>01</strong>5833 LAKE & AIR INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>924 FAA STC SA39CH SEE ATTACHED <strong>EASA</strong><br />
Installation of an Amphibian Landing Gear<br />
APPROVED TYP<br />
Position Advisory System<br />
10<strong>01</strong>5759 LAKE CENTRAL AIR SERVICES <strong>EASA</strong>.IM.A.S.<strong>01</strong>795 TCCA STC SA-05-71 LAKE LA 4/200 Horizontal Stabilizer Attachment Fitting P/N LC- - Parts must be manufactured in accordance<br />
2200-21 TCCA STC SA-05-71 issued on 8th with Lake Central Air Services Drawing LC-<br />
July 2005<br />
2200-21, Rev. 0, dated July 06, 2005, and<br />
LakeCentral Air Services Manufacturing<br />
Procedures MP-LC-2200-21, Rev. B, dated<br />
July 06, 2005, or later approved revisions.- Inst<br />
10<strong>01</strong>54<strong>01</strong> LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>111 FAA STC ST451CH-D CESSNA 650 Installation of an AlliedSignal Avionics MK-VII,<br />
Enhanced Ground Proximity Warning System<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
10<strong>01</strong>5402 LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>112 FAA STC ST451CH-D CESSNA 650<br />
installer.<br />
Installation of a Bendix/King CAS 67A TCAS II 1. This STC is approved only for the product<br />
System with Dual Bendix/King MST-67A Mode configuration as defined in the approved design<br />
S Transponders<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Placard containing the following<br />
limitations to be installed in clearview of<br />
the pilot:AS350: VNE Limited to 126<br />
KIAS, VFR Operations Only AS355:<br />
Category A operations prohibited. VNE<br />
Limited to 126 KIAS, VFROperations<br />
Only Prior to installation of this mo<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 303/<strong>462</strong><br />
15.05.2007<br />
11.02.2008<br />
11.02.2008<br />
21.<strong>01</strong>.2008<br />
14.<strong>01</strong>.2<strong>01</strong>1<br />
<strong>04</strong>.<strong>01</strong>.2<strong>01</strong>1<br />
21.06.2006<br />
18.<strong>04</strong>.2006<br />
24.03.2005<br />
24.03.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5814 LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>884 SA00987CH CESSNA 525 Installation of an Allied Signal two tube EFIS-50 1. Compatibility of this design change with<br />
on Co-pilot's panel with Honeywell FZ500 Flight previously approved modifications must be<br />
05.10.2006<br />
Director in accordance with ElectroSonics determined by the installer.2. The aircraft must<br />
Drawing No. ES525-720250-<strong>01</strong>, Revision 1, be maintained in accordance wit FAA<br />
dated February 2, 1999 or later FAA approved Approved Maintenance Manual Supplement,<br />
revision.<br />
document number ES525-720250-200, Initial<br />
Rel<br />
10<strong>01</strong>6028 LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.02197 ST00939CH-D FALCON 10 Validation of FAA STC ST00939CH-D: Compatibility with previous approved<br />
06.02.2007<br />
Installation of a Honeywell Enhanced Ground modifications shall be determined by the<br />
Proximity Warning System (EGPWS) in installer.JAA Leaflet TGL 12 Certification<br />
accordance with Garrett Aviation Drawing List Considerations for the Terrain Awareness<br />
DL939 Revision F, dated 20th January 2005. Warning System: TAWS requisittes have been<br />
applied.Configurations 2 and 3 (without Terrain<br />
Dis<br />
10<strong>01</strong>6032 LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.022<strong>01</strong> FAA STC ST<strong>01</strong>579CH-D MYSTERE FALCON 20-C5 Installation of a Honeywell MK-VIII Enhanced This STC is approved only for the product<br />
16.10.2006<br />
MYSTERE FALCON 20-D5 Ground Proximity Warning System (EGPWS) configuration as defined in the approved design<br />
MYSTERE FALCON 20-E5<br />
data referred to in the paragraph "Description".<br />
MYSTERE FALCON 20-F5<br />
Compatibility with other aircraft/engine<br />
MYSTERE FALCON 200<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6037 LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.02206 FAA STC ST<strong>01</strong>579CH-D MYSTERE FALCON 20-5 Installation of a Honeywell MK-VIII Enhanced 1. JAA Leaflet TGL 12 Certification<br />
03.07.2007<br />
MYSTERE FALCON 20-C5 Ground Proximity Warning System (EGPWS) Considerations for the Terrain Awareness<br />
MYSTERE FALCON 20-E5 in accordance with Garrett Aviation Services Warning System: TAWS requisites have been<br />
MYSTERE FALCON 20-F5 Drawing List 70-0739-0<strong>01</strong> revision G dated applied.2. Prior to installation of this<br />
MYSTERE FALCON 200 05th October 2005 or later approved<br />
modification the installer must determine that<br />
revisions.<strong>EASA</strong> Validation of:Federal Aviation<br />
Ad<br />
the interrelationship between this modifica<br />
10<strong>01</strong>6209 LANDMARK AVIATION <strong>EASA</strong>.IM.A.S.02455 FAA STC ST<strong>01</strong>136CH-D Installation of a Senior Flexonics Inc. Signal Compatibility of this design change with<br />
31.05.2007<br />
Conditioner Unit<br />
previously approved modifications must be<br />
determined by the installer.If the holder agrees<br />
to permit another person to use this certifcate<br />
to alter the product, the holder shall give the<br />
other person evidence of tha<br />
10028<strong>01</strong>4 LAST REFUGE LTD P-<strong>EASA</strong>.A.S.03964 REV. 1 FR172J, R172K, 182, 206, 208 Approval of Flight Manual Supplements for None The approval holder shall fulfil the 25.11.2009<br />
Last Refuge Ltd Wing Strutmounted camera<br />
obligations of Part 21,<br />
installation.<br />
Paragraph21.A109This STC is a revision<br />
of and supersedes <strong>EASA</strong> Approval No<br />
67, dated 10October 2003.<br />
10028910 LATITUDE TECHNOLOGIES<br />
CORPORATION<br />
10030640 LATITUDE TECHNOLOGIES<br />
CORPORATION<br />
10030644 LATITUDE TECHNOLOGIES<br />
CORPORATION<br />
10030765 LATITUDE TECHNOLOGIES<br />
CORPORATION<br />
TCCA STC SH10-16 AS355E, AS355F, AS355F1,<br />
AS355F2, AS355N, AS355NP<br />
REV. 1 TCCA STC SH10-16 206, 206A, 206A-1, 206B<br />
206B-1, 206L, 206L-1<br />
206L-3, 206L-4, 407<br />
TCCA STC SH10-16 AS350B, AS350B1, AS350B2,<br />
AS350B3, AS350BA, AS350D,<br />
AS350D1<br />
212, 412 Skynode S200-xxx SATPHONE/TRACKER<br />
system product design in accordancewith<br />
Latitude Technologies Corporation Skynode<br />
S200-xxx Master DocumentList No S200-000-<br />
0<strong>01</strong> Revision 1.09, dated Aug 10, 2009.<br />
Installation of Latitude Technologies S100<br />
Tracking System<br />
Installation of Latitude Technologies S100<br />
Tracking System<br />
Installation of Latitude Technologies S100<br />
Tracking System<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.02.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
29.06.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.07.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.07.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 3<strong>04</strong>/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038140 LAZ-TEC, L.L.C. FAA STC SR00716DE BELL 429 Crew Door Assist Handle None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.<strong>01</strong>.2<strong>01</strong>2<br />
10<strong>01</strong>4950 LD AVIATION PRAGUE S.R.O. <strong>EASA</strong>.A.S.03213 CESSNA T303 COMM/NAV/GPS GNS 530, GNS 430,<br />
Navigation Indicator GI 106, S-mode GTX 330<br />
Transponder, GMA 340 ICS, and ELT Kannad<br />
406AF installation into Cessna T303.<br />
S/N: T303 00205. 15.11.2007<br />
10<strong>01</strong>4958 LD AVIATION PRAGUE S.R.O. <strong>EASA</strong>.A.S.03228 CESSNA T206H Installation of Leica RC30 with IPAS 10 and<br />
FCMS options.<br />
S/N T20608636. 19.10.2007<br />
10026761 LD AVIATION PRAGUE S.R.O. P-<strong>EASA</strong>.A.S.03837 CESSNA 172 RG Avionics Upgrade - GNS430W, KX165A, None. 1.,,Prior to installation of this modification 07.08.2009<br />
GMA340, GI106A, KN62A,<br />
the installer mustdetermine that the<br />
GTX330,KANNAD406AF Compact Installation<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2.,,The ins<br />
10036826 LD AVIATION PRAGUE S.R.O. L 200A, L 200 D Avionics Upgrade , GNS 430W, GMA 347, WX None Prior to installation of this modification it 10.10.2<strong>01</strong>1<br />
500, KCS 55A , ELT 406, MID4200-10<br />
must be determined thatthe<br />
Installation<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029813 LE BOZEC FILTRATION & SYSTEMS<br />
SAS<br />
REV. 2 FAA STC ST09864SC 737-100, -200, -200C, -300<br />
737-400, -500<br />
Rain Repellent System Modification -<br />
Modification of Rain RepellentSystem in<br />
accordance with "Le Bozec, Inc.” documents.<br />
Only applicable to Rain repellent systems that Prior to installation of this modification it 06.08.2<strong>01</strong>2<br />
were installed at time ofairplane production must be determined thatthe<br />
under TC <strong>EASA</strong> IM.A.120 or FAA TC A16WE. interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031318 LEARJET INC FAA STC SA8119NM-D CL-600-2B16 Installation of the Bulkhead F.S.353 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>0<br />
10031319 LEARJET INC FAA STC SA8120NM-D CL-600-2B16 Interior Installation - Main Cabin none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>0<br />
10031320 LEARJET INC FAA STC SA8122NM-D CL-600-2B16 Installation of the Armledge / Dado none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>0<br />
10<strong>01</strong>5312 LEARJET INC. <strong>EASA</strong>.IM.A.S.0<strong>01</strong>62 FAA STC ST<strong>01</strong>606LA-D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
The modification consists in the installation of 1. The Maintenance Instructions for<br />
an Executive Interior in accordance with Master Continued Airworthiness are contained in<br />
Drawing List HC20<strong>01</strong>350<strong>01</strong>, Rev. E dated July Documents Number HC20<strong>01</strong>35000-IFCA-1.<br />
10, 20<strong>04</strong> (or later FAA approved<br />
Modification of an aircraft by this STC obligates<br />
revision).Validation of FAA STC ST<strong>01</strong>606LA- the aircraft operator to include the maintenance<br />
D.<br />
information provided by this document in<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 305/<strong>462</strong><br />
07.10.20<strong>04</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5329 LEARJET INC. <strong>EASA</strong>.IM.A.S.00322 FAA STC ST0<strong>01</strong>51BO LEARJET 55 Installation of Honeywell CAS-67A TCAS II 1. FAA STC ST0<strong>01</strong>51BO.2. This STC is<br />
09.11.20<strong>04</strong><br />
Software Change 7,0.<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the ins<br />
10<strong>01</strong>5330 LEARJET INC. <strong>EASA</strong>.IM.A.S.00323 REV. 5 FAA STC SA8168NM-D CL-600-2B16 (CL-6<strong>04</strong>) Installation of a Complete Custom Aircraft<br />
Interior<br />
10<strong>01</strong>5357 LEARJET INC. <strong>EASA</strong>.IM.A.S.0065 FAA STC ST<strong>01</strong>595LA-D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>5359 LEARJET INC. <strong>EASA</strong>.IM.A.S.0066 FAA STC ST<strong>01</strong>603LA-D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>5360 LEARJET INC. <strong>EASA</strong>.IM.A.S.0067 FAA STC ST<strong>01</strong>253LA-D BD-100-1A10 (CHALLENGER<br />
300)<br />
10<strong>01</strong>5365 LEARJET INC. <strong>EASA</strong>.IM.A.S.0068 FAA STC ST<strong>01</strong>254LA-D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>5392 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>091 FAA STC ST<strong>01</strong>619LA-D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>5486 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>247 FAA STC ST<strong>01</strong>720LA-D LEARJET 31<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
Restricted to MSN 5449, 5510, 5523, 5539,<br />
5572, 5577, 5585<br />
The modification consists in the installation of 1. Modification of an aircraft by this<br />
Control Wheel Lighted Chart Holders, in supplemental Type Certificate obligates the<br />
accordance with Master Drawing List aircraft operator to include the maintenance<br />
HC33105000, Revision B, dated April 23, 20<strong>04</strong> information provided by Document Number<br />
or later FAA approved revision.This STC is the HC33105000-IFCA-1 in the operator's Aircraft<br />
validation of the FAA approved STC No. Maintenance Manual and the operator's Ai<br />
The modification consists in the installation of a 1. Modification of an aircraft by this<br />
Service Panel Lighting System, in accordance Supplemental Type Certificate under -1<br />
with Master Drawing List HC33315000, Configuration/installation, obligates the<br />
Revision A, dated june 03, 20<strong>04</strong> or later FAA aircraftoperator to include the maintenance<br />
approved revision.This STC is the validation of information provided by Document Number<br />
the FAA approved STC No. ST<strong>01</strong>6<br />
HC33315000-IFCA-1 in the operator's Aircraft<br />
Main<br />
The modification consists in the installation of 1. Modification of an aircraft by this<br />
Cockpit Writing Tables, in accordance with Supplemental Type Certificate obligates the<br />
Master Drawing List HC31515000, Revision D, aircraft operator to include the maintenance<br />
dated December 18, 2003 or later FAA- information provided by Document Number<br />
approved revision.This STC is the validation of HC31515000-IFCA in the operator's Aircraft<br />
the FAA approved STC No. ST<strong>01</strong>253LA- Maintenance Manual and the operator's Airc<br />
The modification consists in the installation of 1. The Maintenance Instructions for<br />
an Artex ELT with Nav Interface in accordance Continued Airworthiness are contained in<br />
with Master Drawing List HC25615000,Rev. D Documents Number HC25615000-IFCA.<br />
dated December 19, 2003 (or later FAA Modification of an aircraft by this STC obligates<br />
approved revision).This STC is the validation of the aircraft operator to include the maintenance<br />
the FAA approved STC No. ST<strong>01</strong>25<br />
information provided by this document in th<br />
Installation of an Executive Interior in<br />
accordance with Master Drawing List<br />
HC200335000 Revision D or later FAA<br />
approved revision<br />
Dual Honeywell MST-67A Diversity<br />
Transponders for Elementary & Enhanced<br />
Surveillance<br />
10<strong>01</strong>5532 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>412 FAA STC ST0<strong>01</strong>90DE-D CL-600-2B16 Installation of Honeywell FMZ-2000 Flight<br />
Management System (FMS) with a Honeywell<br />
GNSSU 12 Channel GPS Sensor<br />
1. The Maintenance Instructions for Continued<br />
Airworthiness are contained in Document<br />
Number HC200335000-IFCA-1. Modification<br />
of anaircraft by this STC obligates the aircraft<br />
operator to include the maintenance<br />
information provided by this document in the<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
10<strong>01</strong>5534 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>418 FAA STC ST<strong>01</strong>235LA-D BOMBARDIER CL-600-2B16 Universal Avionics TT-3000 AERO-M Satcom<br />
installer.<br />
This STC is approved only for the product<br />
System.Master Drawing List No. DC 23155002 configuration as defined in the approved design<br />
Revision E or later FAA approved revision data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5535 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>419 FAA STC SA8195NM-D BOMBARDIER CL-600-2B16 Observer Audio Panel Installation.Master This STC is approved only for the product<br />
Drawing List No. DC23515000 Revision F or configuration as defined in the approved design<br />
later FAA approved revision.<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Prior to installation of this modification it <strong>04</strong>.03.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 306/<strong>462</strong><br />
28.07.20<strong>04</strong><br />
28.07.20<strong>04</strong><br />
28.07.20<strong>04</strong><br />
28.07.20<strong>04</strong><br />
24.<strong>01</strong>.2005<br />
26.07.2005<br />
26.07.2005<br />
09.08.2005<br />
09.08.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5536 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>420 FAA STC ST<strong>01</strong>258LA-D LEARJET 45 Installation of a Universal UMS-1C+ Flight 1. Universal UNS-1C FMS System must be<br />
18.08.2005<br />
Management System Upgrade from Software installed prior to installation of this STC.2.<br />
Control Number (SCN) 602.X to (SCN) 80X.X This STC is approved only for the product<br />
with Data Transfer Unit<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other<br />
10<strong>01</strong>5537 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>421 FAA STC ST0<strong>04</strong>12DE-D LEARJET 45 Installation of UNS-1C Flight Management<br />
System (Software Version 6<strong>04</strong>.X)<br />
10<strong>01</strong>5549 LEARJET Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>443 FAA STC ST<strong>01</strong>463SE LEARJET 31 Group Aircraft Approval for Reduced Vertical<br />
Separation Minimum (RVSM)<br />
10<strong>01</strong>5616 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>555 FAA STC SA8171NM-D BOMBARDIER BD-700-1A10 Pilot and Co-Pilot Footrests for BF700-1A10<br />
Global Expressacc.: MDL GC25005<strong>01</strong> Rev. B<br />
or later FAA approved rev.Validation of<br />
imported FAA STC: SA8171NM-D<br />
10<strong>01</strong>5710 LEARJET Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>703 FAA STC ST<strong>01</strong>181WI-D LEARJET 31<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
Installation of Honeywell IHAS-800 Multi-<br />
Hazard Awareness System<br />
10<strong>01</strong>5730 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>749 FAA STC ST00342DE-D LEARJET 31A Installation of Single Universal Avionics<br />
Corporation UNS-1C FMS<br />
10<strong>01</strong>5788 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>844 FAA STC ST00508DE-D BOMBARDIER CL-600-2B16 Installation of Collins PCD-3000 Data Loader<br />
Interface System<br />
10<strong>01</strong>5790 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>848 FAA STC ST8139NM-D BOMBARDIER CL-600-2B16 Installation of a Collins VHF-22C Comm<br />
System with CTL-22C.<br />
10<strong>01</strong>5796 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>855 FAA STC ST<strong>01</strong>717LA-D BOMBARDIER BD-100-1A10<br />
(CHALLE<br />
10<strong>01</strong>5817 LEARJET INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>888 REV. 1 SA06-10 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
10<strong>01</strong>5852 LEARJET Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>955 FAA STC ST<strong>01</strong>186WI-D LEARJET 31<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
1. Instructions for Continued Airworthiness<br />
BAS-45<strong>01</strong>0006-IFCA or BAS-45<strong>01</strong>0006-IFC-2<br />
dated March 28 2000 or later approved<br />
revision required for this installation.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved de<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Learjet Master Document List BAS35<strong>01</strong>5037<br />
Revision l or later approved revision -<br />
configurations -2, -4 and -5 only<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
installation of a lavatory Seat Modification - Belt Certification basis: a deviation from 25.789(b)<br />
replacement,in accordance with Master has been granted for personal injury criteria<br />
Drawing List BAS68<strong>01</strong>0002, rev C<br />
testing of side singlw occupancy seats (Learjet<br />
CRI D-3)<br />
EGPWS Software Upgrade Installation of<br />
Cockpit Speaker Mute<br />
Installation of Universal UNS-1L Flight<br />
Management System.<br />
1.The approval for the Master Document List -<br />
1 configuration, EGPWS Software Upgrade (-<br />
218-218 Software), is contingent on the aircraft<br />
being equipped with a previously <strong>EASA</strong><br />
approved installation of a MK V Honeywell<br />
EGPWS with Version -206-206 Software or<br />
Not JAA TGL10 Compliant with present<br />
software load.<br />
10<strong>01</strong>5884 LEARJET INC. <strong>EASA</strong>.IM.A.S.02002 FAA STC SA8197NM-D BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation of Oxygen System-Passenger &<br />
crew (14500ft)<br />
-- 20.06.2006<br />
10<strong>01</strong>5919 LEARJET INC. <strong>EASA</strong>.IM.A.S.02052 ST<strong>01</strong>237LA-D BOMBARDIER CL-600-2B16 (CL- Installation of a Complete Custom Interior Modification of an aircraft by this STC obligates<br />
03.11.2006<br />
6<strong>04</strong><br />
the aircraft operator to include the maintenance<br />
information TE-55325000-IFCA in the<br />
operators Maintenance Manual & the<br />
Operators Scheduled Maintenance<br />
ProgramThe equipment for which provisions<br />
were provide<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 307/<strong>462</strong><br />
18.08.2005<br />
08.12.2005<br />
16.11.2005<br />
22.03.2006<br />
02.<strong>01</strong>.2006<br />
20.<strong>01</strong>.2006<br />
07.05.2007<br />
07.<strong>04</strong>.2006<br />
03.06.2008<br />
13.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5920 LEARJET INC. <strong>EASA</strong>.IM.A.S.02053 FAA STC SA8109NM-D BOMBARDIER CL-600-2B16 Installation of Honeywell Enhanced Ground<br />
Proximity Warning System with Runway<br />
Awareness & Advisory System (RAAS)<br />
05.07.2007<br />
10<strong>01</strong>5948 LEARJET INC. <strong>EASA</strong>.IM.A.S.02090 REV. 1 FAA STC SA8129NM-D BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation of Ultra Electronics Active Noise &<br />
Vibration Control system<br />
-- 14.09.2007<br />
10<strong>01</strong>6066 LEARJET INC. <strong>EASA</strong>.IM.A.S.02245 FAA STC ST<strong>01</strong>731LA-D LEARJET 45 Installation of Honeywell Integrated<br />
1. Incorporation of ECR 7598 and Honeywell<br />
14.03.2007<br />
Communication Unit / Enhanced Surveillance Service Bulletins 7517400-23-6008, 7510700-<br />
Upgrade (-1 Configuration).<br />
23-6<strong>04</strong>4 and 7510700-23-6<strong>04</strong>6 is a prior or<br />
concurrent requirement to this installation.2.<br />
This STC is approved only for the product<br />
configuration as defined in the approve<br />
10<strong>01</strong>6070 LEARJET INC. <strong>EASA</strong>.IM.A.S.02251 FAA STC SA8178NM-D BOMBARDIER BD-700-1A10 Installation of an Artex ELT/NAV Interface<br />
SystemValidation of the FAA STC SA8178NM-<br />
D<br />
10<strong>01</strong>6106 LEARJET INC. <strong>EASA</strong>.IM.A.S.02296 FAA ST00222BO BOMBARDIER CL-600-2B16 Installation of enhanced surveillance<br />
modification to Dual Collins TDR-94/94D<br />
transponder system.<br />
10<strong>01</strong>6108 LEARJET INC. <strong>EASA</strong>.IM.A.S.02298 REV. 1 FAA STC ST<strong>01</strong>732LA-D BOMBARDIER BD-700-1A10 Installation of a Rockwell Collins Integrated<br />
Flight Information System (IFIS-5000).<br />
10<strong>01</strong>6140 LEARJET INC. <strong>EASA</strong>.IM.A.S.02336 REV. 3 FAA STC SA8164NM-D BD-700-1A10 Installation of a Complete Custom Aircraft<br />
Interior - ASN 9<strong>01</strong>6, 9020,9054, 9098, 9106<br />
10<strong>01</strong>6148 LEARJET INC. <strong>EASA</strong>.IM.A.S.02349 FAA STC SA8133NM-D BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>04</strong><br />
Replacement of a Collins TCAS II bottom<br />
OMNI-Directional Antenna (Sensor Systems)<br />
10<strong>01</strong>6160 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02382 FAA STC ST<strong>01</strong>082WI-D LEARJET 60 Universal UNS-1E/C+ Flight Management<br />
SystemFAA STC ST<strong>01</strong>082WI-D<br />
10<strong>01</strong>6163 LEARJET INC. <strong>EASA</strong>.IM.A.S.02390 FAA STC SA8100NM-D BOMBARDIER CL-600-2B16 Installation of an Axle Jack Storage Box<br />
Installation<br />
10<strong>01</strong>6164 LEARJET INC. <strong>EASA</strong>.IM.A.S.02391 FAA STC SA8097NM-D BOMBARDIER CL-600-2B16 Installation of an Engine Cover Storage - Aft<br />
Equipment<br />
10<strong>01</strong>6165 LEARJET INC. <strong>EASA</strong>.IM.A.S.02392 FAA STC SA6003NM-D BOMBARDIER CL-600-2A12 (CL- Interior Installation/Modification in accordance<br />
6<strong>01</strong><br />
with DAS approved Learjet Master document<br />
BOMBARDIER CL-600-2B16 list No. CA-1000TUC, Rev "N" dated January<br />
12, 1995 or later approved revision<br />
10<strong>01</strong>6226 LEARJET INC. <strong>EASA</strong>.IM.A.S.02478 FAA STC SA81<strong>01</strong>NM-D BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>04</strong><br />
FAA STC SA81<strong>01</strong>NM-D, NAV Lights<br />
RelocationThis STC supersedes LBA TA<strong>01</strong>36.<br />
Installation of emhanced surveillance<br />
modificationper this STC requires that a<br />
previously <strong>EASA</strong> approved dual installation of<br />
Collins p/n 622-9352-007 (TDR-94) or 622-<br />
9210-007 (TDR-94D) or later version has been<br />
installed in the aircraft.<br />
Restricted to ASN 9<strong>01</strong>6, 9020, 9054, 9098,<br />
9106.The following STC's are a concurrent<br />
requirement with this STC:-<strong>EASA</strong> STC<br />
10<strong>01</strong>6535 (FAA STC ST00941LA) - Floor<br />
Proximity EmergencyEscape Path Marking<br />
System is applicable to all aircraft serial<br />
numbersapproved<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
1. This approval only applies to the -0<strong>04</strong>, -<br />
005, -006, and -<strong>01</strong>0 configurations of the<br />
Universal UNS-1C+ Flight Management<br />
System2. See also FAA STC ST<strong>01</strong>082WI-<br />
D3. Prior to installation of this modification<br />
the installer must determine that the inte<br />
The proper interrelationship between this<br />
installation and any previously approved<br />
configuration has to be assured.<br />
10<strong>01</strong>6356 LEARJET INC. <strong>EASA</strong>.IM.A.S.02678 FAA SA8191NM-D BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Installation of a Safe Flight Enhanced The -3 configuration requires the installation of<br />
Autopower System.<br />
FAA STC SA8191NM-D -2 configuration.<br />
10<strong>01</strong>6387 LEARJET INC. <strong>EASA</strong>.IM.A.S.02715 FAA STC ST<strong>01</strong>737LA-D BOMBARDIER BD-700-1A10 Installation of Honeywell / EMS HD-710 High- The installation of an <strong>EASA</strong> approved Router/<br />
BOMBARDIER BD-700-1A11 Speed Data Satcom System.<br />
LAN System is a prerequisite/ concurrent<br />
requirement to the installation of the -1<br />
Configuration.<br />
10<strong>01</strong>64<strong>01</strong> LEARJET INC. <strong>EASA</strong>.IM.A.S.02730 FAA ST0<strong>01</strong>63BO BOMBARDIER BD-700-1A10 Installation of a main entry door rain deflector<br />
BOMBARDIER BD-700-1A11 channel.<br />
10<strong>01</strong>6445 LEARJET INC. <strong>EASA</strong>.IM.A.S.02791 FAA STC ST02023 LA-D BOMBARDIER CL-600-2B16 Installation of a Mid-Cabin Interior Modification. A prior or concurrent requirement for the<br />
installation of the -1 Configuration is the<br />
incorporation of <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.02392 for the<br />
interior/Modification Installation.<br />
21.02.2007<br />
31.05.2007<br />
<strong>04</strong>.12.2007<br />
Prior to installation of this modification it 10.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 308/<strong>462</strong><br />
07.05.2007<br />
08.08.2007<br />
31.05.2007<br />
31.05.2007<br />
03.08.2007<br />
31.05.2007<br />
21.08.2007<br />
07.<strong>04</strong>.2008<br />
08.05.2008<br />
07.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6481 LEARJET INC. <strong>EASA</strong>.IM.A.S.02834 FAA STC ST<strong>01</strong>730LA-D BOMBARDIER CL-600-2B16 (6<strong>04</strong>) FAA STC ST<strong>01</strong>730LA-D, Installation of an Prior to installation of this modification the<br />
24.06.2008<br />
Aircell Axxess II Iridium Satcom System. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6570 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02967 FAA STC ST00994WI-D LEARJET 60 Cockpit Speaker Mute FunctionFAA STC Prior to installation of this modification the<br />
06.10.2008<br />
ST00994WI-D<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6574 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02972 FAA STC ST<strong>01</strong>421WI-D LEARJET 60 Airshow 410 System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
16.09.2008<br />
10<strong>01</strong>6575 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02973 FAA STC ST<strong>01</strong>424WI-D LEARJET 60 Emergency power supply #1 Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>6600 LEARJET INC. <strong>EASA</strong>.IM.A.S.03<strong>01</strong>3 FAA STC ST10380SC BOMBARDIER BD-700-1A10 Replacement of Low Back Seats with High<br />
Back Seats.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
10<strong>01</strong>6611 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03031 FAA STC ST<strong>01</strong>370WI-D LEARJET 60 Honeywell HF Communication System. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>6618 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03<strong>04</strong>9 FAA STC ST<strong>01</strong>402WI-D LEARJET 60 Collins Pro Line 21 Avionics InstallationFAA<br />
STC ST<strong>01</strong>402WI-D<br />
10<strong>01</strong>6619 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03050 FAA STC ST<strong>01</strong>422WI-D LEARJET 60 Interior Upgrade (Floor Plans A, B, C & D)FAA<br />
STC ST<strong>01</strong>422WI-D<br />
10<strong>01</strong>6651 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03099 REV. 2 FAA STC SA8199NM-D BD-700-1A10 FAA STC SA8199NM-D, Installation of a Full<br />
Authority Cabin Temp Control.<br />
10<strong>01</strong>6682 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03205 FAA STC ST006<strong>04</strong>WI LEARJET 31A Installation of stand-alone Garmin GPS-165<br />
Global Positioning System (VFR Navigation<br />
Only).<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The inst<br />
16.09.2008<br />
23.12.2008<br />
27.10.2008<br />
13.11.2008<br />
13.11.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.12.2<strong>01</strong>0<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 309/<strong>462</strong><br />
28.<strong>04</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027108 LEARJET INC. P-<br />
FAA STC ST<strong>01</strong>716LA-D BD-100-1A10 (CHALLEGER 300) - Installation of a Passenger Seat Upgrade- None - Prior to installation of this modification 07.09.2009<br />
<strong>EASA</strong>.IM.A.S.03188<br />
Validation of FAA STC ST<strong>01</strong>716LA-D<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product- The installa<br />
10028342 LEARJET INC. P-<br />
<strong>EASA</strong>.IM.A.S.03206<br />
REV. 1 FAA STC ST<strong>01</strong>255LA-D BD-100-1A10 (CHALLENGER<br />
300)<br />
Installation of a Baseline Executive<br />
Interior.Validation of FAA STC ST<strong>01</strong>255LA-D (-<br />
2 Configuration)Revision of the <strong>EASA</strong> STC<br />
10028342 to include -2 Configuration<br />
Not Applicable Prerequisite for the installation of this<br />
STC as per FAA STCST<strong>01</strong>255LA-D:<br />
Bruce Industries Inc. STC ST<strong>01</strong>569LA -<br />
Installation of FloorProximity Emergency<br />
Escape Path Marking System Prior to<br />
installation of this modification it must be<br />
determined thatthe inte<br />
10031271 LEARJET Inc. FAA STC SA8117NM-D CL-600-2B16 Installation of the RH Forward Lavatory none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.08.2<strong>01</strong>0<br />
10031299 LEARJET Inc. FAA STC SA8118NM-D CL-600-2B16 Installation of the RH Forward Galley none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.08.2<strong>01</strong>0<br />
10035643 LEARJET INC. P-<br />
<strong>EASA</strong>.IM.A.S.02343<br />
10036055 LEARJET INC. P.<strong>EASA</strong>.IM.A.S.0325<br />
3<br />
FAA STC ST<strong>01</strong>239LA-D CL-600-2B16 FAA STC ST<strong>01</strong>239LA-D, Complete Custom<br />
Aircraft Interior<br />
BOMBARDIER CL-600-1A11<br />
BOMBARDIER CL-600-2A12<br />
BOMBARDIER CL-600-2B16<br />
FAA STC ST<strong>01</strong>735LA-D, Installation of a<br />
Kidde Aerospace Smoke Detector inthe Aft<br />
Baggage Compartment, as a replacement for<br />
Walter Kidde PIN473052.<br />
10037572 LEARJET INC. REV. 1 FAA STC ST00288BO BD100-1A10 (CHALLENGER 300) Installation of Honeywell EGPWS with<br />
windshear and Terrain Display (MDL-1<br />
configuration), Runway Awareness and<br />
Advisory System (RAAS) (MDL -<br />
2configuration) or Runway Awareness and<br />
Advisory System (RAAS) inhibit(MDL -3<br />
configuration) in accordance with Bomb<br />
10038287 LEARJET INC. FAA STC ST00299BO BD-700-1A10, BD-700-1A11 Installation of Honeywell Cockpit Displays<br />
Upgrade<br />
10<strong>04</strong><strong>04</strong>05 LEARJET INC. FAA STC SA8192NM-D BD-700-1A10 Installation of a Sextant Integrated Electronic<br />
Standby InstrumentSystem<br />
Restricted to ASN 5541.A concurrent<br />
requirement to this STC is the installation of<br />
BruceAerospace <strong>EASA</strong> STC No. 10035636<br />
(FAA STC SA6<strong>01</strong>1NM) (ref. <strong>EASA</strong><br />
PN0<strong>01</strong>0<strong>01</strong>1393) Floor Proximity Emergency<br />
Escape Path Marking System.<br />
An <strong>EASA</strong> approved Walter Kidde Smoke<br />
Detector System for PIN 473052 is<br />
aprerequisite I concurrent requirement for the<br />
installation of this STC.<br />
15.03.2<strong>01</strong>0<br />
Prior to installation of this modification it 06.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
02.07.2009<br />
- Instructions for Continued Airworthiness ref.<br />
product. The installati<br />
Prior to installation of this modification it 19.03.2<strong>01</strong>2<br />
BAS68<strong>01</strong>70<strong>01</strong>-ICA-1 rev Adated January 14, must be determined thatthe<br />
2<strong>01</strong>1 must be made available to the operator interrelationship between this modification<br />
at thetime of installation for MDL-1<br />
and any other previouslyinstalled<br />
configuration, EGPWS with Windshear modification and/ or repair will introduce<br />
andTerrain Display. - Instructions for Continued no adverse effectupon the airworthiness<br />
A<br />
of the product.<br />
The Honeywell DU-875 Multifunction Display<br />
(MFD) Expansion Applicationsinclude 'MFD<br />
charts' (date sensitive charts with ownship<br />
position) and'MFD Uplink Graphical Weather<br />
Map' (XM Weather). Any other<br />
intendedfunction of this equipment will require<br />
a re-exa<br />
Prior to installation of this modification it 03.02.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.07.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 310/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0951 LEARJET Inc. <strong>EASA</strong> STC NO. 1426 REV. 1 FAA STC ST<strong>01</strong>122SE-D LEARJET 35/35A/36/36A Group Aircraft Approval for RVSM. Validation The following items listed in the Limitations and Prior to installation of this modification it 07.08.2<strong>01</strong>2<br />
of FAA STC ST<strong>01</strong>122SE-D dated 14 April Conditions section ofthe FAA STC<br />
must be determined thatthe<br />
2<strong>01</strong>0. Note: This approval constitutes an ST<strong>01</strong>122SE-D, dated April 14 2<strong>01</strong>0, are interrelationship between this modification<br />
update to <strong>EASA</strong> STC ref. N° 1426 dated2 excluded from <strong>EASA</strong>approval of this STC, and any other previouslyinstalled<br />
December 2003 (LBA STC TA0751, dated 27 because they are related to a configuration(C- modification and/ or repair will introduce<br />
November 2003) in order toreflect the 21A) that has not been validated by <strong>EASA</strong>:§ 4 no adverse effectupon the airworthiness<br />
compatibility o<br />
Grou<br />
of the product.<br />
10031894 LEARJET, INC REV. 1 FAA STC ST02025LA-D 31A Installation of Northrop Grumman Dual LITEF<br />
LCR-100 AHRSFAA STC ST02025LA-D<br />
(issued March 10, 2<strong>01</strong>0)<br />
Previous or concurrent requirement for this<br />
installation is an approvedinstallation of the<br />
LCR-93 AHRS in accordance with Learjet<br />
ECR 4467.<br />
10035128 LEARJET, INC FAA STC SA8182NM-D BD-700-1A10 Modification of the Forward Water Fill Panel This installation modifies the existing water fill<br />
panel installationinstalled by Bombardier Inc.<br />
Engineering Drawing MDC9000-<strong>01</strong>42-1<br />
only(Previously approved under <strong>EASA</strong> STC<br />
No. <strong>EASA</strong>.IM.A.S.02336)<br />
Prior to installation of this modification it 20.09.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 27.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029566 LEES AVIONICS Ltd. COMMANDER 112, 114 Installation of Garmin G500/G600 PFD/ND This change is limited to the configuration<br />
defined in Change StatementCS1097-<strong>01</strong> Issue<br />
2 or later approved revision.<br />
None <strong>01</strong>.<strong>04</strong>.2<strong>01</strong>0<br />
10033384 LEES AVIONICS Ltd. LEARJET 35, LEARJET 35A Installation of single or dual Universal Avionics Refer to Flight Manual Change Sheet FCMS- Prior to installation of this modification it 17.12.2<strong>01</strong>0<br />
UNS-1Lor UNS-1LW FMS (Flight Management 1159, issue 1<br />
must be determined thatthe<br />
System)<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10036361 LEES AVIONICS Ltd. P-<strong>EASA</strong>.A.S.02912 1900, 1900C, 1900D<br />
200, 200C, 200CT, 200T, A200<br />
A200C, A200CT, B200, B200C<br />
B200CGT, B200CT, B200GT,<br />
B200T<br />
TAWS-B Installation. None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.09.2<strong>01</strong>1<br />
10036482 LEES AVIONICS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>567 BELL 412 Installation of the Spectrolab search light SX16. None. None. 16.09.2<strong>01</strong>1<br />
10036506 LEES AVIONICS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>570 BELL 412 Installation of the UNS-1E FMS. This kit/STC can be installed on helicopter that<br />
has installed the kitDualBendix/King ED551A<br />
EHSI, <strong>EASA</strong> approved <strong>EASA</strong>.R.S.<strong>01</strong>445.<br />
10036591 LEES AVIONICS Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10039936 LEES AVIONICS Ltd. BN2A-20, BN2A-21, BN2A-26,<br />
BN2A-27, BN2A-8,<br />
BN2A-9, BN2B-20,<br />
BN2B-21, BN2B-26, BN2B-27<br />
None. 14.09.2<strong>01</strong>1<br />
GNS430W/GNS530W Installation for BRNAV None The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
30.09.2<strong>01</strong>1<br />
Garmin G600 PFD/ND. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.06.2<strong>01</strong>2<br />
10034642 LETH & ASSOCIATES, LLC FAA STC ST<strong>01</strong>857SE 757-200 Max Zero Fuel Weight Increase Only applicable to a/c converted to Freighter by Prior to installation of this modification it 18.<strong>04</strong>.2<strong>01</strong>1<br />
Precision ConversionsSTC (ref:<br />
must be determined thatthe<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>423)<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 311/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035929 LIBERTY AEROSPACE INC. FAA STC SA03488AT XL-2 S-TEC system 30 autopilot installation on Option 1: Chippewa Aerospace Inc Document Prior to installation of this modification it 28.07.2<strong>01</strong>1<br />
Liberty XL-2 series inaccordance with the XL2-2210-<strong>01</strong>-0002 Rev IR, datedJune 18, must be determined thatthe<br />
following:Option 1 (for use with S-Tec Model 2007, or later FAA approved revision - interrelationship between this modification<br />
ST-9<strong>01</strong> GPS Steering Converter<br />
Instructions forContinued Airworthiness and any other previouslyinstalled<br />
Unit):Chippewa Aerospace Master Data List (ICA).Option 2: Liberty Aerospace Document modification and/or repair will introduce<br />
(MDL) n° XL2-2210-<strong>01</strong>-00<strong>01</strong>, revision4, dated 135A-970-110, rev D. dated July 19,2<strong>01</strong>0, or no adverse effectupon the airworthiness<br />
November 20<br />
lat<br />
of the product.Option 2<br />
10<strong>01</strong>5453 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>198 FAA STC SA<strong>01</strong>093SE CESSNA 525<br />
CESSNA 525A<br />
Installation and inspection of emergency<br />
medical stretcher and base, oxygen system in<br />
accordance with FAA STC SA<strong>01</strong>093SE or<br />
later <strong>EASA</strong> approved revision.<br />
10<strong>01</strong>5454 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>199 FAA STC ST00909SE LEARJET 45 Installation of emergency medical stretchers<br />
and bases, oxygen and electrical systems and<br />
associated Lifeport Inc. Report No. EGR-644-<br />
12 Revision IR dated November 6 2000 &<br />
Master Drawing List EGR-644-00 revision R<br />
dated 25 April 20<strong>01</strong> or later approved rev<br />
10<strong>01</strong>5551 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>445 FAA STC SA00273WI BEECH 100<br />
BEECH 200<br />
BEECH 300<br />
BEECH 65-90<br />
BEECH 65-A90<br />
BEECH B90<br />
BEECH C90<br />
BEECH C90 A<br />
BEECH E90<br />
BEECH F90<br />
Installation of a Patient Loading and Utility<br />
System (PLUS)<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Modification must be used with AFMS 35 for<br />
Lifeport PLUS<br />
10<strong>01</strong>5614 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>553 REV. 1 FAA STC ST<strong>01</strong>780LA CESSNA 560 XL Installation of a Patient Loading and Utility Ref. AFM Supplement EGR-777-11, Revision<br />
System (PLUS) inaccordance with FAA STC A, dated June 24, 2005, or later FAA approved<br />
ST<strong>01</strong>780LA or later <strong>EASA</strong> approved revision<br />
Note: Revision 1 issued to correct a type in the<br />
Original STC number.<br />
revision<br />
10<strong>01</strong>5646 LIFEPORT, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>619 FAA STC SA00635SE 208 208A 208B Installation of a Patient Loading and Utility<br />
System (PLUS) in accordance with FAA STC<br />
SA00635SE or later <strong>EASA</strong> approved revision.<br />
1. Airplane Flight Manual supplement EGR-571-<br />
11, Revision A, dated January 11, 2002, or<br />
later FAA approved revision.<br />
10<strong>01</strong>6288 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.02583 FAA STC SA02060LA BEECH 1900D Emergency Medical System The installer of this STC must ensure that, if<br />
the life vests have been removed with the<br />
seats, a life vest for the occupant of thelitter<br />
system is installed and available to the<br />
occupant.<br />
10<strong>01</strong>6483 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.02837 FAA STC ST02119LA CESSNA 750 CITATION X Emergency Medical System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6489 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.02845 FAA STC SA00096LA BAE 125 SERIES 1000A<br />
BAE 125 SERIES 1000B<br />
BAE 125 SERIES 800A<br />
BAE 125 SERIES 800B<br />
HAWKER 1000<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER HS 125-700A<br />
10<strong>01</strong>6492 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.02854 FAA STC ST0<strong>01</strong>54SE CESSNA 500<br />
CESSNA 550<br />
CESSNA 560<br />
CESSNA S550<br />
10<strong>01</strong>6578 LIFEPORT, Inc. <strong>EASA</strong>.IM.A.S.02977 REV. 1 FAA STC SA00528SE PA-31, PA-31-300, PA-31-350,<br />
PA-31P, PA-31T, PA-31T1,<br />
PA-31T2, PA-31T3, PA-31P-350,<br />
PA-42, PA-42-1000<br />
Installation of a Patient Loading and Utility<br />
System.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Emergency Medical System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Emergency Medical System (The Emergency<br />
Medical System attaches only to the existing<br />
aircraft seat tracks. The system will be a free<br />
standing unit that can be rapidly installed and<br />
removed from the cabin).<br />
13.02.2007<br />
21.06.2005<br />
19.09.2005<br />
24.07.2009<br />
16.02.2006<br />
<strong>04</strong>.10.2007<br />
30.07.2008<br />
30.07.2008<br />
27.08.2008<br />
None. None. 30.<strong>04</strong>.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 312/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6933 LIFEPORT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>319 FAA STC SR<strong>01</strong>948LA SIKORSKY S-92A Installation of a triple litter stacking system The installation should not be incorporated in<br />
any aircraft unless it is determined that the<br />
interrelationship between this installation and<br />
any previously approved configurations will not<br />
introduce any adverse effect upon the<br />
airworthiness of the aircraft<br />
02.05.2007<br />
10<strong>01</strong>6963 LIFEPORT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>363 FAA STC SR02054LA AGUSTA AB-139<br />
AGUSTA AW-139<br />
10<strong>01</strong>6978 LIFEPORT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>381 FAA STC SR09082RC BELL 222<br />
BELL 230<br />
10<strong>01</strong>6979 LIFEPORT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>382 FAA STC SR00360DE BELL 222<br />
BELL 222B<br />
BELL 222U<br />
BELL 230<br />
10030942 LIFEPORT, Inc. FAA STC ST<strong>01</strong>891LA-D SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10032771 LIFEPORT, Inc. FAA STC ST02286LA CESSNA 680 Installation of a Medical Patient Loading and<br />
Utility System (PLUS)<br />
10<strong>01</strong>5384 LITEAIR AVIATION PRODUCTS INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>078 FAA STC ST<strong>01</strong>091SE BOEING 737-100<br />
BOEING 737-200<br />
BOEING 737-200C<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-700C<br />
BOEING 737-800<br />
BOEING 737-900<br />
10<strong>01</strong>5385 LITEAIR AVIATION PRODUCTS INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>079 REV 1 FAA STC ST00758SE BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
10<strong>01</strong>5386 LITEAIR AVIATION PRODUCTS INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>080 FAA STC ST00638SE BOEING 747-100<br />
BOEING 747-100B SUD<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-300<br />
BOEING 747-400<br />
BOEING 747-400D<br />
BOEING 747-SR<br />
10<strong>01</strong>5387 LITEAIR AVIATION PRODUCTS INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>081 FAA STC ST00353SE BOEING 747-100<br />
BOEING 747-100B SUD<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-300<br />
BOEING 747-400<br />
BOEING 747-400D<br />
BOEING 747-SR<br />
Installation of an Emergency Medical System 1. The installer of this STC must be ensure<br />
that, if the life vests have been removed with<br />
the seats, a life vest for the occupant of the<br />
litter system is installed and available to the<br />
occupant.<br />
Air medical System. This STC has been<br />
classified as "BASIC' by the FAA and has been<br />
approved under the PTVP.<br />
Medical System. This STC has been classified<br />
as "BASIC" by the FAA and has been<br />
approved under the PTVP.<br />
Multi Models Commercial Medical<br />
This STC does not constitute an approval for<br />
StretcherValidation of FAA STC ST<strong>01</strong>891LA-D installation. Compliancewith following<br />
requirements below need to be demonstrated<br />
through adesign approval for commercial<br />
medical stretcher installation in eachaircraft<br />
model per approved Model list:§ 25.561(d)<br />
Installation of Lightweight Window Plugs. 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of Lightweight Window Plugs Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Installation of upper deck lightweight window<br />
plugs<br />
Installation of Main Deck Lightweight Window<br />
Plugs.<br />
19.09.2007<br />
05.03.2008<br />
05.03.2008<br />
Prior to installation of this modification it 15.07.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.11.2<strong>01</strong>0<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6139 LITEAIR AVIATION PRODUCTS INC. <strong>EASA</strong>.IM.A.S.02335 FAA STC ST<strong>01</strong>732SE BOMBARDIER CL-600-2B19 Installation of light weight window plug. N/A 15.03.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 313/<strong>462</strong><br />
22.<strong>04</strong>.2005<br />
26.03.2009<br />
18.11.2005<br />
22.<strong>04</strong>.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6622 LITEAIR AVIATION PRODUCTS INC. <strong>EASA</strong>.IM.A.S.03053 FAA STC ST<strong>01</strong>872SE BOMBARDIER DHC-8-400 Installation of lightweight window plug.Ref. FAA 1. Prior to installation of this modification the<br />
26.11.2008<br />
SERIES<br />
STC ST<strong>01</strong>872SE, dated 09 September 2008. installer must determine that the<br />
BOMBARDIER DHC-8-4<strong>01</strong><br />
interrelationship between this modification and<br />
BOMBARDIER DHC-8-402<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10032950 LITEAIR AVIATION PRODUCTS INC. FAA STC ST02073SE 777-200, -300, -200LR, -300ER Lightweight window plug Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.12.2<strong>01</strong>0<br />
10<strong>01</strong>6<strong>04</strong>8 LIVETV <strong>EASA</strong>.IM.A.S.02220 FAA STC ST10056SC AIRBUS A320-232 Installation Of Electronic Equipment Rack As per FAA STC ST10065SC the following<br />
STC’s must be installed concurrently with this<br />
STC:ST00788SE, ST02483AT and<br />
ST<strong>01</strong>447NY.<br />
10<strong>01</strong>6<strong>04</strong>9 LIVETV <strong>EASA</strong>.IM.A.S.02221 FAA STC ST02483AT AIRBUS A320 SERIES Installation Of a Cabin Mounted Video Camera<br />
System<br />
As per FAA STC ST10065SC the following<br />
STC’s must be installed concurrently with this<br />
STC:ST10065SC, ST00788SE, and<br />
10<strong>01</strong>6050 LIVETV <strong>EASA</strong>.IM.A.S.02222 FAA STC ST00788SE AIRBUS A320-200 Installation of a Live TV Satellite Television<br />
ST<strong>01</strong>447NY.<br />
As per FAA STC ST10065SC the following<br />
29.05.2007<br />
System<br />
STC’s must be installed concurrently with this<br />
STC:ST10065SC, ST02483AT and<br />
ST<strong>01</strong>447NY.<br />
10<strong>01</strong>6051 LIVETV <strong>EASA</strong>.IM.A.S.02223 FAA STC ST<strong>01</strong>447NY AIRBUS A320-200 Installation Of Harris Ground Wireless Aircraft As per FAA STC ST10065SC the following<br />
29.05.2007<br />
Data Link & Partial Power Provisions for STC’s must be installed concurrently with this<br />
Installation of a Cabin Surveillance System STC:ST10065SC, ST02483AT and<br />
ST00788SE.<br />
10<strong>01</strong>6503 LIVETV <strong>EASA</strong>.IM.A.S.02867 FAA STC ST03177AT EMBRAER ERJ 190-100 ECJ FAA STC ST03177AT: Installation of LiveTV<br />
LTV 2000 In-Flight Entertainment System<br />
Installation based on EMBRAER provisions 05.09.2008<br />
10<strong>04</strong>1796 LLOPIS BALLOONS 1. BASKET: THUNDER & COLT Modifications "Diners a bord"2-guests kit Modification to Thunder & Colt baskets limited Prior to installation of this modification it 22.10.2<strong>01</strong>2<br />
40+B<br />
applicable on Ultramagic C5, C5L, C7, C8, to S/N 943 and 1834 When any guests kits are must be determined thatthe<br />
2. BASKETS: C5, C5L, C7, C8, C8L, C9 and C11baskets and Cameron in place, the supplemental flight<br />
interrelationship between this modification<br />
2. BASKETS: C8L, C9, C11 & C12 CB8202 "Thunder & Colt 40+B" baskets16- manual"supplément au manuel de vol Llopis and any other previouslyinstalled<br />
guests kit applicable on Ultramagic C12 basket Balloons pour modification enconfiguration modification and/ or repair will introduce<br />
diners a bord" must be used.<br />
no adverse effectupon the airworthiness<br />
of the product. One or<br />
10<strong>01</strong>6038 LOPRESTI SPEED MERCHANTS Inc. <strong>EASA</strong>.IM.A.S.02207 REV. 2 ST02893AT BAE 125 SERIES 1000A<br />
BAE 125 SERIES 800A<br />
HAWKER 750<br />
HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
10<strong>01</strong>6161 LP AERO PLASTICS, INC. <strong>EASA</strong>.IM.A.S.02383 FAA STC SA002<strong>04</strong>NY BEECH 35<br />
BEECH 35-33<br />
BEECH 35-A33<br />
BEECH 35-B33<br />
BEECH 35-C33<br />
BEECH 95<br />
BEECH 95-55<br />
BEECH 95-A55<br />
BEECH 95-B55<br />
BEECH A35<br />
BEECH B95<br />
BEECH B95A<br />
BEECH C35<br />
BEECH E35<br />
BEECH F35<br />
BEECH G35<br />
BEECH H35<br />
BEECH J35<br />
BEECH K35<br />
BEECH M35<br />
BEECH N35<br />
BEECH P35<br />
BEECH S35<br />
Installation of a Boom Beam Taxi/Landing Light<br />
System.HID Wing Taxi/Landing Light<br />
System,HID Nose Taxi Light System<br />
Installation of 250”, 312” or 375” thick one 1. This approval should not be incorporated<br />
piece windshields (two piece windshield to one in any aircraft models listed in this STC on<br />
piece wind shield conversion).<br />
which other approved modifcations are<br />
incorporated , unless it is determined that the<br />
interrelationship between this change and any<br />
of those previously incorporated<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 314/<strong>462</strong><br />
29.05.2007<br />
29.05.2007<br />
16.11.2007<br />
20.<strong>04</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5134 LTB SAMMET GmbH <strong>EASA</strong>.A.S.03487 <strong>EASA</strong> STC <strong>EASA</strong>.A.S.C.<strong>01</strong>008 AND CESSNA 150D<br />
Installation of engine Rotax 912 F3 and 1. Spin is prohibited to all models.2. Aerobatic<br />
25.02.2008<br />
CESSNA 150E<br />
installation of Propeller Hoffmann HO- including Spin is prohibited to Cessna A150K,<br />
CESSNA 150F<br />
V352F/170FQ on Cessna Models 150H, FA150K, A150L and FA150L.3. Prior to<br />
CESSNA 150G<br />
F150H, A150K, FA150K, A150L, FA150L, installation of this modification the installer must<br />
CESSNA 150H<br />
150K, F150K, 150L and F150L only.Installation determine that the interrelationship between<br />
CESSNA 150J<br />
of engine Rotax 912 S3 (100PS) and this modification andany o<br />
CESSNA 150L<br />
CESSNA 150M<br />
CESSNA A150L<br />
CESSNA F150-G<br />
CESSNA F150-H<br />
CESSNA F150-J<br />
CESSNA F150-K<br />
CESSNA F150-L<br />
CESSNA F150-M<br />
CESSNA FA-150-K<br />
installation of Propeller<br />
10<strong>01</strong>3924 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02836 REV. 4 AIRBUS A318-112 Structural Floor Panel ReconfigurationThe 1. Side facing divans may not be used for taxi,<br />
18.12.2008<br />
limitation for divans that they must not be take off and landing after1315 FH or 14<br />
occupied for taxi, take off and landing has been months whatever occurs first, starting at June<br />
suspended for 1315 FH or 14 monthswhatever 26th, 2008.2. Prior to installation of this<br />
occurs first, starting at June 26th, 2008.The modification the installer must determine that<br />
modification is described in the<br />
the interrelationship betw<br />
10<strong>01</strong>3943 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.00382 REV 1 AIRBUS A340-300 Installation of Antenna and Receiver Transmit 1. "The IEEE 802.11 a, b, g (as customized)<br />
System and Network Services(acc.: STDD 00- Wireless Local Area Network (WLAN)<br />
03/11M issue 02)<br />
introduced by this modification, may be<br />
activated onboard Airbus A340-600 Aircraft for<br />
operation with commercial IEEE 802.11a, b, g<br />
& h compliant WLAN enabled portable<br />
electroni<br />
10<strong>01</strong>3964 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.00654 REV. 2 A340 Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
10<strong>01</strong>3967 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.007<strong>01</strong> REV 1 BOEING 747-300-400 Radome Installation for Live TV Antenna<br />
Installation<br />
10<strong>01</strong>3977 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>000 BOEING 767-300 Installation of an Optical Quick Access<br />
Recorder (OQAR) according to LHT<br />
Engineering Bulletin No. 767-EB31-0203,<br />
dated 09.09.<strong>04</strong> or later approved Revision for<br />
FOQA Purpose<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Maintenance requirements, Doc. No. C-<br />
AAL900-MR shall be incorporated in the<br />
aircraft maintenance documentation.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data. Compatibility with other aircraft/eng<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other Aircraft configurations<br />
shall be determined by the installer.<br />
10<strong>01</strong>3978 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>0<strong>01</strong> BOEING 737-300 Installation of an Optial Quick Access Recorder This STC is approved only for the product<br />
(OQAR) according to LHT Engineering Bulletin configuration as defined in the approved design<br />
No.737-EB31- 0202, dated 29.09.<strong>04</strong> or later data referred to in the paragraph "Description".<br />
approved Revision for FOQA Purpose. Compatibility with other Aircraft configurations<br />
shall be determined by the installer.<br />
10<strong>01</strong>4<strong>01</strong>3 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>056 REV. 1 A318/A319/A320/A321 Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
10<strong>01</strong>4<strong>04</strong>3 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>121 AIRBUS A330-200 A330-200 Air Algerie Quick Change VIP Kit<br />
OnePlus.<br />
10<strong>01</strong>4079 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>171 BOEING 777-300 Installation of PC Power and PC Data Outlets<br />
on the existing B/C Seats and installation of<br />
new ECO Class Seats with new P/N and PC-<br />
Power/PC-Data Outlets on Boeing 777-300<br />
A/C of Cathay Pacific Airways.<br />
10<strong>01</strong>4126 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>236 BOEING 747-2B4B<br />
BOEING 747-SP<br />
Flight Management System (FMS), Activation<br />
of Advisory VNAV Modeaccording to Lufthansa<br />
Technik Supplemental Type Definition<br />
Document STDD34-05/02M, Issue <strong>01</strong>, Rev 00,<br />
dated April 20, 2005 or laterapproved revision<br />
10<strong>01</strong>4158 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>286 BOEING 767-300 B-767- Cabin Layout Change - Air Europe 21.06.2005<br />
10<strong>01</strong>4191 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>333 REV 1 BOEING 767 SERIES Installation of Guideline-Self Illuminating Floor<br />
Path Marking System.<br />
14.12.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 315/<strong>462</strong><br />
15.11.2005<br />
14.09.2<strong>01</strong>2<br />
23.<strong>04</strong>.2009<br />
17.08.2005<br />
17.08.2005<br />
14.09.2<strong>01</strong>2<br />
31.03.2005<br />
<strong>01</strong>.03.2005<br />
30.05.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4193 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>335 BOEING MD 11<br />
Navigation - ATC system, Installation of<br />
29.06.2005<br />
BOEING MD 11F<br />
Upgrade for Enhanced Surveillance and<br />
associated Airplane Flight Manual Supplement.<br />
10<strong>01</strong>4196 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>338 BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Navigation - Introduction of ATC Mode S<br />
Enhanced Surveillance<br />
10<strong>01</strong>4216 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>377 BOEING 737-300 "Avionics Upgrade by- Installation of TCAS-<br />
Installation of Dual Mode S Transponder-<br />
Installation of Add. Parameters for Digital FDR-<br />
Digital Flight Data Acquisition Unit, Software<br />
Upgrade- Installation of Enhanced Ground<br />
Proximity Warning System"<br />
10<strong>01</strong>4218 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>379 AIRBUS A340-600 "Installation of Antenna and Receiver Transmit "The IEEE 802.11 a,b,g (as customized)<br />
System and Network Services". Acc.: STDD Wireless Local Area Network (WLAN)<br />
00-<strong>04</strong>/10M. Ref. to former LBA STCs: TA0810 introduced by this midification, may be<br />
and TA0811. AFM Suppllement: A-34-05/260- activated on board Airbus A340-600 Aircraft<br />
AFM. ICA: R-00-<strong>04</strong>/120<br />
for operation with commercial IEEE 802.11a,<br />
b, g & h compliant WLAN enabled portable<br />
electronic de<br />
10<strong>01</strong>4225 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>388 AIRBUS A320<br />
AIRBUS A321<br />
ATC, System Upgrade for Enhanced<br />
Surveillance, acc.: STDD 34-05/06M<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4227 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>390 AIRBUS A330-300 Integration of Lower Deck Mobile Crew Rest 14.07.2005<br />
10<strong>01</strong>4228 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>391 AIRBUS A340-300 Integration of Lower Deck Mobile Crew Rest 14.07.2005<br />
10<strong>01</strong>4246 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>456 BOEING 767-300 ATC, System Upgrade for EHS Certification Basis of the Change: CS 25<br />
Change 0, additionally JAA Leaflet No 18<br />
(Mode-S EHS)<br />
10.<strong>04</strong>.2006<br />
10<strong>01</strong>4256 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>483 REV. 1 FOKKER F.28 MARK 0070 Installation of non-electrical Floor Path Marking<br />
14.09.2<strong>01</strong>2<br />
FOKKER F.28 MARK <strong>01</strong>00 System Guideline®<br />
10<strong>01</strong>4257 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>486 REV 1 AIRBUS A330-200<br />
Structural mounting provision for large antenna 1. <strong>EASA</strong> CS25, without Amendment,<br />
08.12.2006<br />
AIRBUS A330-300<br />
and random for Live TV Tailwind 560 Certification Specifications for Large<br />
Aeroplanes plus FAA Generic Issue Paper A-X<br />
"Structural Certification Criteria for Large<br />
Antenna Installations".2. This STC is approved<br />
only for the product configuration as defined in<br />
10<strong>01</strong>4258 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>487 AIRBUS A330-200<br />
AIRBUS A330-300<br />
Communication - Modification/Upgrade of the<br />
In-Flight Entertainment System, Installation of<br />
Tailwing 560 Live TV Equipment.<br />
<strong>EASA</strong> CS25, without Amendment,<br />
Certifications Specifications for Large<br />
Aeroplanes plus JAA INT/POL/25/3 Issue 2,<br />
JAA INT/POL/25/4 Issue 3, JAA Leaflet No.<br />
10<strong>01</strong>4260 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>488 REV 1 BOEING 777-200<br />
17.<br />
Rearrangement of VIP cabin interior (Majlis) & 1.This modification is limited to a/c serial<br />
systems and modification of pax entertainment number MSN29271.2. Occupancy of this zone<br />
system (IFE) including installation oftailwind is limited to Zero Passengers for Taxi, Take-off<br />
560 Live TV system.<br />
and Landing, pending substantiation of<br />
evacuation through the adjacent compartments<br />
10<strong>01</strong>4261 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>489 BOEING 777-200 Introduction of Tailwind 550 Antenna and Live This modification is limited to a/c serial number<br />
TV for VIP B777-200.<br />
MSN29271.<br />
10<strong>01</strong>4262 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>490 AIRBUS A300 ATC, System Upgrade for EHS Certification Basis of the Change: CS 25,<br />
additionaly JAA Leaflet No. 18 (Mod-S EHS)<br />
10<strong>01</strong>4269 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>498 BOEING 737-700 IGW Cabin and IFE Modification as defined in<br />
Supplemental Type Definition<br />
DocumentSTDD00 - 05/05 M, Issue <strong>01</strong>,<br />
Rev.00<br />
10<strong>01</strong>4281 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>518 BOEING 737-600 SERIES<br />
BOEING 737-700 SERIES<br />
BOEING 737-800 SERIES<br />
BOEING 737-900 SERIES<br />
Installation of Guideline-non-electrical Floor<br />
Path Marking System.<br />
10<strong>01</strong>4282 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>519 BOEING 747-400 VVIP Cabin InstallationSTDD 25-05 / 06M<br />
issue 1, STDD 25-05 / 19 issue1<br />
-- 19.10.2006<br />
10<strong>01</strong>4283 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>520 BOEING 757-300 Installation of Zonal Drying System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
06.11.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 316/<strong>462</strong><br />
26.07.2005<br />
<strong>01</strong>.09.2005<br />
12.08.2005<br />
22.07.2005<br />
07.<strong>04</strong>.2006<br />
12.06.2008<br />
29.06.2006<br />
13.03.2006<br />
25.10.2005<br />
25.10.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4292 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>534 REV. 1 B737-700 IGW Revision of <strong>EASA</strong>.A.S.<strong>01</strong>534 IR per Major Once LCA is activated (installation of FAA STC Prior to installation of this modification it 03.12.2<strong>01</strong>2<br />
Change 0<strong>01</strong>0002739-0<strong>01</strong>:Operationat 8.99 psi ST<strong>01</strong>697SE as validatedper <strong>EASA</strong> STC must be determined thatthe<br />
maximum cabin differential pressure (Lower 10<strong>04</strong>2295) on an individual aircraft, the interrelationship between this modification<br />
Cabin Altitude,LCA)Original STC Title: B737- maintenancerequirements defined in Doc A-00- and any other previouslyinstalled<br />
700 IGW VIP Cabin 19 Pax.<br />
06/100-ICA will apply for the life ofthis aircraft. modification and / or repair will introduce<br />
This limitation remains valid also in<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4293 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>535 REV 1 BOEING 747-SP ATC System, Upgrade to Enhanced<br />
SurveillanceNote: This Revision expands the<br />
application range of the existing STC.<br />
10<strong>01</strong>4308 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>553 AIRBUS A319 Installation of new B/E Aerospace convertible<br />
and standard seats and cabin refurbishment to<br />
PG-design on Lufthansa's A319 aircrafts<br />
1. Certification Basis of the change: CS 25<br />
Change O, additionaly JAA Leaflet No. 18<br />
(Mode-S EHS)2. This STC is approved only<br />
for the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibili<br />
10<strong>01</strong>4309 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>554 BOEING 747-400 B747-400 Guggenheim Seat Arrangement<br />
Modification from 384 passengers (main<br />
deck16 FC, 28 BC, 310 Y) to 398 passengers<br />
(main deck 12 FC, 0 BC, 46 Y + 310 Y)<br />
according to STD00-05/10M<br />
24.10.2005<br />
10<strong>01</strong>4316 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>564 AIRBUS A300-600 "Installation of Communication System IFE<br />
Update"acc.: STDD 23-05/07M<br />
Limited to s/n 354 10.11.2005<br />
10<strong>01</strong>4325 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>578 REV. 2 B747-400, B747-400F Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
14.09.2<strong>01</strong>2<br />
10<strong>01</strong>4326 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>579 B737-800 Business Class Installation with Sicma Seats 13.<strong>01</strong>.2006<br />
10<strong>01</strong>4347 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>611 AIRBUS A321 Installation of new B/E Aerospace convertible This STC is approved only for the product<br />
and standard seats and cabin refurbishment to configuration as defined in the approved design<br />
PG-design on Lufthansa's A321 aircrafts data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4354 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>619 REV 4 BOMBARDIER CL-600-2B19 CL-600-2B19 - Cabin Completion - 15 PAX –<br />
Configuration D.<br />
1. Certification Basis of Change: JAR-25<br />
Change 13, additionally:Configuration A and<br />
B*:CRI D-<strong>01</strong>, Side facing Divan (Deviation)CRI<br />
F-<strong>01</strong>, Executive Power Systems (Guidance<br />
Material)JAA TGL No. 17, Passenger service<br />
and In-Flight Entertainment (IFE) syste<br />
10<strong>01</strong>4359 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>624 BOEING 737-300 SERIES Installation of new Recaro Seating convertible Certification Basis of the change: FAR25 as<br />
and standard seats and cabin refurbishment to defined in FAA TCDS A16WE. The applicant<br />
PG-design on Lufthansa's Boeing B737-300 showed compliance to CS 25.0785(h)(2), CS<br />
aircraft<br />
25.811(d), (g), CS 25.812€, CS 25.0853(a),<br />
(c), (d), (f).<br />
10<strong>01</strong>4367 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>637 AIRBUS A319 A319 CJ VIP Cabin 34 Pax 1. JAR-25 Change 112. FAR 25.981 (a) (b)<br />
Amdt. 102 'Fuel Tank [ignition prevention]'3.<br />
'CRI D-03 'Type III Emergency Exit Access'<br />
dated 31. March 20064. CRI F-<strong>01</strong> 'Dimestic<br />
Power' dated 18 May 20065. TGL No. 17<br />
'Passenger Service and In-Flight Entertainment<br />
10<strong>01</strong>4373 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>647 REV. 1 B717-200<br />
Installation of non-electrical Floor Path Marking<br />
DC-9, MD-30, MD-88, MD-90 System Guideline®<br />
10<strong>01</strong>4395 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>689 AIRBUS A319<br />
Introduction of Link 2000+ Certification Basis of the Change: CS 25 Amdt<br />
AIRBUS A320<br />
AIRBUS A321<br />
02<br />
10<strong>01</strong>4398 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>692 BOEING 747-400 B747-400 Bahrain Royal Flight, VIP Cabin<br />
Installation<br />
10<strong>01</strong>44<strong>04</strong> LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>699 BOEING 737-500 Installation of new Recaro Aircraft Seating Certification Basis of the change: FAR25 as<br />
convertible and standard seats and cabin<br />
refurbishment to PG-design on Lufthansa's<br />
Boeing B737-500 aircraft.<br />
defined in FAA TCDS A16WE.<br />
10<strong>01</strong>4415 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.<strong>01</strong>715 AIRBUS A320 Installation of new B/E Aerospace convertible<br />
and standard seats and cabin refurbishment to<br />
PG-design on Lufthansa's A320 aircrafts<br />
10<strong>01</strong>4449 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02502 A320-200 A320 Pax Capacity Increase from 156 to 168<br />
Pax<br />
29.05.2006<br />
10<strong>01</strong>4472 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02533 REV 1 AIRBUS A340-300 Installation of CAIR System in A340-300 18.08.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 317/<strong>462</strong><br />
15.<strong>01</strong>.2007<br />
16.02.2006<br />
03.03.2006<br />
20.11.2007<br />
13.03.2006<br />
21.07.2006<br />
14.09.2<strong>01</strong>2<br />
26.02.2007<br />
16.12.2005<br />
23.05.2006<br />
17.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4494 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02556 BOMBARDIER CL-600-2B19 CL-600-2B19 - Cabin Completion - 16 PAX 1. Certification Basis of the Change: JAR-25<br />
Change 13, addtionally: CRI F-<strong>01</strong>, Executive<br />
Power System (Guidance Material)CRI D-<strong>01</strong>,<br />
Side Faching Divans (Deviation)CRI D-<strong>04</strong>,<br />
Door between passenger compartments with<br />
integrated blocking functionality (Deviatio<br />
29.03.2007<br />
10<strong>01</strong>45<strong>04</strong> LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02574 BOEING 747 Installation of an ATC Mode S - Enhanced<br />
Surveillance Upgrade in Boeing 747 series<br />
aircraft<br />
<strong>EASA</strong> approved Airplane Flight Manual<br />
Supplement, Lufthansa Technik Document A-<br />
34-06/135-AFM, Rev IR or later <strong>EASA</strong><br />
approved revisionis required part of this STC<br />
10<strong>01</strong>4507 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02580 REV. 1 A330 SERIES Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
10<strong>01</strong>4509 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02583 AIRBUS A300-600<br />
Installation of a new Stretcher for Kuwait<br />
AIRBUS A310-300<br />
Airways.<br />
10<strong>01</strong>4510 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02585 AIRBUS A320 Installation of a new Stretcher for Kuwait<br />
Airways<br />
10<strong>01</strong>4511 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02586 BOEING 777-200 SERIES Installation of a stretcher in the passenger Prior to installation of this modification the<br />
compartment for Kuwait Airways<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4512 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02587 BOEING 747-400 Installation of a new stretcher for Kuwait<br />
Airlines B747-400 in accordance with<br />
Supplemental Type Definition Document<br />
STDD25-06 09MIss. <strong>01</strong>, Rev. <strong>01</strong> or later <strong>EASA</strong><br />
approved revision.<br />
10<strong>01</strong>4513 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02588 AIRBUS A340-300 Installation of a new Stretcher for Kuwait<br />
Airways<br />
10<strong>01</strong>4521 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02603 REV 1 AIRBUS A300-600 A300-600 Cabin Reconfiguration from Current<br />
Continental Version to Intercontinental Layout<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4552 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02648 AIRBUS A310-300 A310-300 Siberia Airlines Cabin<br />
Reconfiguration from 248 to 255 pax<br />
10<strong>01</strong>4563 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02663 REV. 1 A300 SERIES, A310 SERIES Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
10<strong>01</strong>4574 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02678 AIRBUS A319-115 Interior and systems installation incl. convertible Instruction for Continued Airworthiness,<br />
cabin configuration<br />
Airworthiness Limitations, Section 4.3, ref. C-<br />
AAA000-ICA, issue 2, dated January 12,<br />
2007or later approved revision<br />
10<strong>01</strong>4593 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02705 BOEING 737-700<br />
Upgrade Package of existing VIP Cabin As indicated in the applicable AFM<br />
BOEING 737-700 IGW<br />
Configuration from private Operation to Supplement:- A_00_<strong>01</strong>_311_AFM<br />
Commercial Operation<br />
Supplement Cabin TT&L for Private Operation-<br />
A_25_06_17M_ AFM Supplement Cabin TT&L<br />
for Commercial Operation.And as indicated in<br />
the LBA STC LBA.21E2.TA0307Compatibility<br />
of this design c<br />
10<strong>01</strong>4602 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02725 BOEING 747-100<br />
BOEING 747-200<br />
BOEING 747-300<br />
Installation of Pneumatic Metric Altimeter Certification Baisis of the Change: CS-25<br />
Amdt. 1<br />
10<strong>01</strong>4606 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02730 BOEING MD 11 Installation of a Rockwell Collins Tailwind 550<br />
Live TV system in Boeing MD-11 as detailed in<br />
STDD53-06/19M Supplemental Type Definition<br />
Document for Tailwind 550 Live TV installation<br />
MD-11<br />
09.11.2007<br />
10<strong>01</strong><strong>462</strong>0 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02752 REV. 5 B737-700 IGW Revision of <strong>EASA</strong>.A.S.02752 Rev.4 per Major Once LCA is activated (installation of FAA STC Prior to installation of this modification it 03.12.2<strong>01</strong>2<br />
Change 0<strong>01</strong>0002741-0<strong>01</strong>:Operation at 8.99 psi ST<strong>01</strong>697SE as validatedper <strong>EASA</strong> STC must be determined thatthe<br />
maximum cabin differential pressure (Lower 10<strong>04</strong>2295) on an individual aircraft, the interrelationship between this modification<br />
CabinAltitude, LCA)Original STC Title: Design maintenancerequirements defined in Doc A-00- and any other previouslyinstalled<br />
and Implementation of VIP interior<br />
07/784-ICA will apply for the life ofthis aircraft. modification and / or repair will introduce<br />
andmiscellaneous aircraft systems.<br />
This limitation remains valid also in<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 318/<strong>462</strong><br />
<strong>04</strong>.08.2006<br />
14.09.2<strong>01</strong>2<br />
15.11.2007<br />
28.02.2008<br />
06.11.2007<br />
09.11.2007<br />
10.10.2007<br />
22.06.2006<br />
23.06.2006<br />
14.09.2<strong>01</strong>2<br />
26.<strong>01</strong>.2007<br />
18.08.2006<br />
25.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4651 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02806 AIRBUS A300 A300F4-605R Multi Mode Receiver (MMR) and<br />
Global Positioning System (GPS) installation<br />
22.03.2007<br />
10<strong>01</strong>4712 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02885 AIRBUS A300 MODEL B4-603 A300B4-603 Cabin Reconfiguration from This STC is approved only for the product<br />
25.<strong>01</strong>.2007<br />
current versions to Intercontinental LayoutCabin configuration as defined in the approved design<br />
Reconfiguration from current versions (total data referred to in paragraph ‘Description’.<br />
280 and 232 Passengers) to Intercontinental Compatibility with other aircraft/engine<br />
Layout (total 217 Passengers).<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4713 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02886 REV. 1 B757-200, B757-300 Installation of non-electrical Floor Path Marking Lufthansa Technik AG AFM Supplement A-33-<br />
14.09.2<strong>01</strong>2<br />
System Guideline®<br />
06/472-AFM<br />
10<strong>01</strong>4715 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02890 BOEING 767-300 Zonal Drying System Installation 11.02.2008<br />
10<strong>01</strong>4720 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02897 A330-300 Removal of Antenna and Receiver Transmit<br />
System and Network Services<br />
10<strong>01</strong>4721 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02898 AIRBUS A340-300 Removal of Antenna and Receiver Transmit<br />
System and Network Services<br />
10<strong>01</strong>4722 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02899 AIRBUS A340-600 Removal of Antenna and Receiver Transmit<br />
System and Network Services.<br />
10<strong>01</strong>4727 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02905 REV. 1 ATR 42-200- 300- 320 400- 500<br />
ATR 72-1<strong>01</strong>- 102- 2<strong>01</strong>- 202- 211<br />
ATR 72-212-212A<br />
Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
The AFM Supplement Doc. No. A-00-<strong>04</strong>/5856<br />
can be removed with the installation of this<br />
STC.<br />
The AFM Supplement Doc. No. A-00-<strong>04</strong>/072<br />
can be removed with the installation of this<br />
STC.<br />
The AFM Supplement Doc. No. A-00-<strong>04</strong>/133<br />
can be removed with the installation of this<br />
STC.<br />
ATR42/72 except those aircraft with<br />
convertible seats which do not have a fixed<br />
lateral position.See Airplane Flight Manual<br />
Supplement AFMS A-33-06/497-AFM Initial<br />
Revision or later approved<br />
revisions.Instructions for Continued<br />
10<strong>01</strong>4743 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02926 BOMBARDIER CL-600-2B19 CL-600-2B19 Cabin Completion - 13 PAX<br />
Airworthiness ICA33-06/<strong>04</strong>M I<br />
1. Certification Basis of Change: JAR-25<br />
Change 13, additionally:CRI D-<strong>01</strong>, Side-Facing<br />
DivanCRI D-<strong>04</strong>, Door between passenger<br />
compartment with integrated blocking<br />
functionalityCRI D-05, Isolated<br />
compartmentCRI F-<strong>01</strong>, Executive Power<br />
SystemJAA TGM Leaflet No.<br />
10<strong>01</strong>4744 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.02927 AIRBUS A300 MODEL B4-600 Zonal Drying System Installation Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>48<strong>01</strong> LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.030<strong>04</strong> BOEING 737-700<br />
BOEING 737-800<br />
BOEING 737-900<br />
ATC Mode S – Enhanced Surveillance<br />
Upgrade<br />
Compatibility of this design change with other<br />
previously approved modifications must be<br />
determined by the installer.<br />
10<strong>01</strong>4808 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03<strong>01</strong>2 REV. 1 CL-600-2B19/-2D24/-2D15 Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
14.09.2<strong>01</strong>2<br />
10<strong>01</strong>4833 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03<strong>04</strong>8 LEARJET 31A Navigation – Retrofit of Dual FMC None 02.<strong>04</strong>.2007<br />
10<strong>01</strong>4869 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03094 BOMBARDIER CL-600-2B19 Cabin Completion - 15 Passengers 1. Installation of "CL-600-2B19-Installation of<br />
Structural Provisions for Cabin Completion"<br />
approved with <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.A.S.03097, is required prior to<br />
installation of this STC.2. The Limitation<br />
"Installation of Ferry-Kit M/S TC 6<strong>01</strong>R16990"<br />
given<br />
11.03.2008<br />
10<strong>01</strong>4870 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03095 BOMBARDIER CL-600-2B19 Cabin Completion 1. Installation of "CL-600-2B19 - Installation<br />
of structural provisions for cabin completion",<br />
approved with <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.A.S.03097 is required prior to the<br />
installation of this STC.2. The limitation<br />
"Installation of Ferry-Kit M/S TC 6<strong>01</strong>R16990"<br />
27.02.2008<br />
10<strong>01</strong>4871 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03096 BOMBARDIER CL-600-2B19 Installation of Structural Provisions for AeroH<br />
Antenna system<br />
1. For all flights with "Green Aircraft" and<br />
"Structural Provisions for AeroH Antenna<br />
System" (2,5 [kg]) installed the installationof<br />
Ferry-Kit M/S TC 6<strong>01</strong>R16990 (867 [kg]) is<br />
necessary.2. With the installation of Ferry-Kit<br />
M/S TC 6<strong>01</strong>R16990 (867 [kg]) the a<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 319/<strong>462</strong><br />
31.05.2007<br />
19.06.2007<br />
19.06.2007<br />
14.09.2<strong>01</strong>2<br />
19.09.2007<br />
02.07.2007<br />
02.03.2007<br />
05.02.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4872 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03097 BOMBARDIER CL-600-2B19 Installation of Structural Provisions for Cabin 11. For all flights with "Green Aircraft" and<br />
05.02.2008<br />
Completion<br />
"Structural Provisions for cabin completion"<br />
(293,7 [kg]) installed the installation of Ferry-Kit<br />
M/S TC 6<strong>01</strong>R16990 (867 [kg]) is necessary.2.<br />
With the installation of Ferry-Kit M/S TC<br />
6<strong>01</strong>R16990 (867 [kg])<br />
10<strong>01</strong>4873 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03098 AIRBUS A330-200 A330 - Installation of Zonal Drying System /The<br />
system is installed to get rid of the humidity<br />
between the cabin lining and the fuselage<br />
10<strong>01</strong>4893 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03123 REV 1 AIRBUS A319-100 PTU and/or Stretcher Installation on A319-100<br />
/Optional replacement of seats by up to 2<br />
Passenger Transport Units (PTU) and/or up to<br />
4 stretchers.<br />
• Detailed visual inspection of the Oxygen<br />
Discharge Plug at an interval of 750 FC ( C<br />
check ), as reported in the document<br />
Instruction for Continued Airworthiness, ref.<br />
Doc. A-00-07/641-ICA Issue 03, dated<br />
19.09.07<br />
10<strong>01</strong>4897 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03127 REV. 1 B777-200, B777-300 Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
14.09.2<strong>01</strong>2<br />
10<strong>01</strong>4906 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03142 REV. 6 A318-112 Structural Floor Panel Reconfiguration None - Prior to installation of this modification<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.- The install<br />
07.10.2009<br />
10<strong>01</strong>4934 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03189 REV 5 AIRBUS A318-112 A318 ELITE – RAK – Structural Floor Panel –<br />
SFP - Retrofit<br />
10<strong>01</strong>4972 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03253 AIRBUS A340-212 WLAN InstallationDesign and implementation<br />
of Wireless Local Area Network System<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2. The ins<br />
10<strong>01</strong>5<strong>01</strong>1 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03313 REV. 1 EMB-135/-145 SERIES Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
10<strong>01</strong>5<strong>04</strong>3 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03359 A300B4-603 / -605R A300B4-603 / -605R Cabin<br />
The installation of this STC has a prerequisite<br />
ReconfigurationCabin Reconfiguration from aircraft configuration.2. This STC is only<br />
current version (280 MC) to two possible applicable on aircraft in association with the<br />
versions (58 CC / 188 MC or 40 CC / 220 MC). <strong>EASA</strong> STC ref: <strong>EASA</strong>.A.S.02663.3. The<br />
Certification Review Item A-<strong>01</strong> has to be<br />
considered, in addition to the<br />
10<strong>01</strong>5<strong>04</strong>7 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03363 BOEING 767-300 Condor B767 Interior Modification • Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.• Th<br />
10<strong>01</strong>5072 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03402 AIRBUS A318-112 A318 ELITE - Project BAA; VIP Cabin<br />
completion.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>5091 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03428 A3118 A318 – Ballast Weight Installation Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5107 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03450 A300 F4-600R Structure modification for GPS antennae<br />
installationThis STC defines the structural<br />
modification for the installation of a dual GPS<br />
antennae, in place of the existing Gatelink<br />
antenna<br />
10<strong>01</strong>5120 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03469 REV. 1 D328 SERIES Installation of non-electrical Floor Path Marking<br />
System Guideline®<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 320/<strong>462</strong><br />
25.05.2007<br />
<strong>01</strong>.10.2007<br />
08.<strong>04</strong>.2009<br />
11.10.2007<br />
14.09.2<strong>01</strong>2<br />
<strong>04</strong>.03.2008<br />
29.08.2008<br />
07.11.2008<br />
12.08.2008<br />
08.05.2008<br />
14.09.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5142 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03502 REV 1 LBA STC LBA.21E2.TA0270 BOMBARDIER CL-600-2B19 Replacement of Zonal Dryer related to <strong>EASA</strong><br />
AD 2006-<strong>01</strong>40-E.The above reference <strong>EASA</strong><br />
AD required the de-activation of Zonal Drying<br />
Systems installed via LBA STC<br />
LBA.21E2.TA0270 due to the potential for<br />
combustion of contaminants in the dryer unit. A<br />
new drye<br />
See related STC LBA.21E2.TA0270 05.08.2008<br />
10<strong>01</strong>5144 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.035<strong>04</strong> REV 1 LBA STC LBA.21E2.0307 BOEING 737-700 Replacement of Zonal Dryer related to <strong>EASA</strong><br />
AD 2006-<strong>01</strong>40-EThe above reference <strong>EASA</strong><br />
AD required the de-activation of Zonal Drying<br />
Systems installed via LBA STC<br />
LBA.21E2.0307 due to the potential for<br />
combustion of contaminants in the dryer unit. A<br />
new dryer u<br />
See related STC LBA.21E2.0307 05.08.2008<br />
10<strong>01</strong>5145 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03505 REV 1 LBA STC LBA.21E2.TA0636 BOEING 737-800 Replacement of Zonal Dryer related to <strong>EASA</strong><br />
AD 2006-<strong>01</strong>40-E.The above reference <strong>EASA</strong><br />
AD required the de-activation of Zonal Drying<br />
Systems installed via LBA STC<br />
LBA.21E2.TA0636 due to the potential for<br />
combustion of contaminants in the dryer unit. A<br />
new drye<br />
See related STC LBA.21E2.TA0636 05.08.2008<br />
10<strong>01</strong>5146 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03506 REV 1 LBA STC TA0733 BOEING 747-400 Replacement of Zonal Dryer related to <strong>EASA</strong><br />
AD 2006-<strong>01</strong>40-E.The above reference <strong>EASA</strong><br />
AD required the de-activation of Zonal Drying<br />
Systems installed via LBA STC TA0733 due to<br />
the potential for combustion of contaminants in<br />
the dryer unit. A new dryer unit ha<br />
See related STC TA0733 05.08.2008<br />
10<strong>01</strong>5147 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03507 REV 1 LBA STC LBA.21E2.TA0609 AIRBUS A330-200 Replacement of Zonal Dryer related to <strong>EASA</strong><br />
AD 2006-<strong>01</strong>40-E.The above reference <strong>EASA</strong><br />
AD required the de-activation of Zonal Drying<br />
Systems installed via LBA STC<br />
LBA.21E2.TA0609 due to the potential for<br />
combustion of contaminants in the dryer unit. A<br />
new drye<br />
See related STC LBA.21E2.TA0609 05.08.2008<br />
10<strong>01</strong>5158 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03526 AIRBUS A318-112 A318 ELITE - Project Comlux 2; VIP Cabin Prior to installation of this modification the<br />
12.12.2008<br />
completion<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5177 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03554 AIRBUS A318-112 A318-112 - ELITE - Project HKInstallation of a Prior to installation of this modification the<br />
VIP cabin for a maximum of 19 passengers for installer must determine that the<br />
28.<strong>01</strong>.2009<br />
commercial and non-commercial operation. interrelationship between this modification and<br />
The design details are described in General any other previously installed modification<br />
Description S-00-08/731.<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5215 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03630 AIRBUS A318-112 A318-112 - ELITE - Project Tanker<br />
1. Prior to installation of this modification the<br />
20.02.2009<br />
1Installation of a VIP cabin for a maximum of installer must determine that the<br />
16 passengers for non-commercial operation interrelationship between this modification and<br />
only. The design details are described in any other previously installed modification will<br />
General Description C-AAA024-SPA. introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10027345 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03346 CL-600-2D24 Introduction of Datalink 2000+ Not Applicable Not Applicable 23.09.2009<br />
10027505 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03912 FOKKER F27 MARK 050 Installation of self-illuminating Floor Path Fokker F50 (F27 Mark 050) aircraft series in Prior to installation of this modification it 06.10.2009<br />
Marking System.<br />
standard airline cabinconfiguration described must be determined thatthe<br />
as typical cabin layout in Engineering interrelationship between this modification<br />
BulletinF50-EB33-0343, Rev. <strong>01</strong>, CH. 4.2. and any other previouslyinstalled<br />
Cabin layout with convertible seats(non fixed modification and/ or repair will introduce<br />
lateral position may result in covering no adverse effectupon the airworthiness<br />
of the product.<br />
10028128 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03435 A330-243 A330-200 - VIP Cabin Interior Completion as per AFMS A-00-09/009-AFM issue 5 as as per AFMS A-00-09/009-AFM issue 5 03.12.2009<br />
listed in the associatedtechnical documentation as listed in the associatedtechnical<br />
documentation Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 321/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028238 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03774 REV. 1 A318-112 A318-112 - Elite 11 - VIP Cabin Completion Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>04</strong>.2<strong>01</strong>0<br />
10028693 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03921 REV. 1 B737-300 Zonal Dryer System Installation in accordance<br />
with 737-EB21-0212<br />
10028830 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03761 REV. 2 A319-133 A319-133 "GAF" VIP Cabin Completion,<br />
Revision 2To incorporate additional CMR in the<br />
ICA and MPD SupplementClosure of post<br />
certification action item D-08-<strong>01</strong>.<br />
10029134 LUFTHANSA TECHNIK AG A340-600 A340-600 Cabin Retrofit Etihad ETD06 The STC holder shall provide by 7th June 2<strong>01</strong>0<br />
Instructions for ContinuedAirworthiness on<br />
Electrical Wiring Interconnection System -<br />
EWIS ICA -in accordance with CS-25,<br />
Appendix H "Electrical Wiring<br />
InterconnectionSystem".<br />
10029677 LUFTHANSA TECHNIK AG A310-3<strong>04</strong> Fuselage - Structural provisions and Satcom<br />
antenna installation, Satcomequipment rack<br />
installation and VHF antenna installation.This<br />
STC installs Satcom and VHF antennae, as<br />
well as the provision forthe future support of a<br />
Satcom system installation.<br />
10030208 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03776 REV. 2 A318-112 Installation of a VIP cabin for a maximum of 19<br />
passengers. The designdetails are described in<br />
General Description C-AAA057-SPA.Deletion<br />
of the Airworthiness Limitation Item reference<br />
530000-<strong>01</strong>-S forA318-112 Elite 14 MSN 4169<br />
10030228 LUFTHANSA TECHNIK AG A380-841/ -842 Installation of Class 2 EFB Laptop Cradle This STC is only intended for the defined Class<br />
2 EFB with Type A andType B software<br />
applications, in accordance with JAA<br />
Temporary GuidanceLeaflet TGL-36 and FAA<br />
Advisory Circular AC120-76A.Operation of<br />
type C software applications in accordance<br />
with FAAA<br />
10030374 LUFTHANSA TECHNIK AG A340-500 A340-500 Cabin retrofit ETD03This STC<br />
modifies the cabin layout by replacing First<br />
Class seats andall associated seat<br />
monuments.<br />
100312<strong>01</strong> LUFTHANSA TECHNIK AG A340-213 A340-200 - Installation of provisions for Live<br />
TV, Satcom, and W-LANThis STC installs<br />
several structural provisions for Live TV,<br />
Satcom, andW-LAN systems, relocates the<br />
existing upper Anti-Collision Light (ACL)and<br />
installs a additional upper ACL.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.10.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.08.2<strong>01</strong>0<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.03.2<strong>01</strong>0<br />
Limited to: MSN 484 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
19.07.2<strong>01</strong>1<br />
Prior to installation of this modification it 03.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.06.2<strong>01</strong>0<br />
Limited to MSN 151 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.07.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 322/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031674 LUFTHANSA TECHNIK AG B747-400 Trial installation of 2 rows of the BE/Aerospace This STC is limited to Lufthansa B747-400 Prior to installation of this modification it 03.09.2<strong>01</strong>0<br />
V-seats model BE 15.0PN series 1<strong>01</strong>2121 as aircraft sn 629493, reg D-ABVWThe approval must be determined thatthe<br />
replacement for 3 rows of Recaro EC seat for this trial is valid until November 30, interrelationship between this modification<br />
model 3410in Section B of the Lufthansa B747- 2<strong>01</strong>0Compliance with CS 25.853 (heat and any other previouslyinstalled<br />
400 reg D-ABVW, in accordance withLHT release/smoke density) has not beenshown, in modification and/ or repair will introduce<br />
document STDD00-10/16M Issue <strong>01</strong> accordance with the certification basisThe seat no adverse effectupon the airworthiness<br />
of the product<br />
10032054 LUFTHANSA TECHNIK AG REV. 1 MD-11 Activation of ADS-B Out capability via<br />
1090MHz Extended Squitter inaccordance with<br />
Lufthansa Supplement Type Definition<br />
DocumentSTDD34-10/<strong>01</strong>M Iss. 2, dated Sep.<br />
20, 2<strong>01</strong>0 or later approved revision<br />
none Doc. No. A-00-10/153 Rev IR Airplane<br />
Flight Manual Supplement shall<br />
beavailable on board of the modified<br />
airplaneDoc. No. A-00-10/153-ICA IR<br />
Instructions for Continued<br />
Airworthinessshall be incorporated in the<br />
maintenance documentation of the<br />
10032628 LUFTHANSA TECHNIK AG A319, A320, A321 New European Cabin Modification Not applicable<br />
aircraft. Pri<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
18.11.2<strong>01</strong>0<br />
10032691 LUFTHANSA TECHNIK AG A340-600 A340-600 Cabin Retrofit - ETD05 Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.11.2<strong>01</strong>0<br />
10032887 LUFTHANSA TECHNIK AG B737-500 DLH New European Cabin for 737-500<br />
Aircraft.Modification of the Aircraft seat layout<br />
to increase the seat capacityfrom currently 111<br />
seats to 120 new seats, produced by<br />
RecaroAircraftseating, Germany.<br />
10033112 LUFTHANSA TECHNIK AG P-<strong>EASA</strong>.A.S.03762 A340-300 A340-300 - "GAF" VIP Cabin Interior<br />
Completion<br />
10033691 LUFTHANSA TECHNIK AG REV. 1 DHC-8-102, -103, -106<br />
DHC-8-2<strong>01</strong>, -202<br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
DHC-8-4<strong>01</strong>, -402<br />
Installation of Photoluminescent Emergency<br />
Floor Path Marking SystemGuideline®<br />
10033738 LUFTHANSA TECHNIK AG REV. 2 B747-400 Activation of ADS-B Out capability via<br />
1090MHz Extended Squitter inaccordance with<br />
Lufthansa Supplemental Type Definition<br />
DocumentSTDD34-10/02M Issue <strong>01</strong>, Rev 02,<br />
dated Feb. 10, 2<strong>01</strong>1 or later approvedrevision.<br />
10034322 LUFTHANSA TECHNIK AG A330-343 Thai Airways A330-300 - Seat exchange and<br />
electrical adaptionThis STC installs 263 Y class<br />
seats, with associated electricaladaptations.<br />
12.10.2<strong>01</strong>0<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.12.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.12.2<strong>01</strong>0<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.02.2<strong>01</strong>1<br />
none Doc. No. A-00-10/225 Rev IR Airplane<br />
Flight Manual Supplement shall<br />
beavailable on board of the modified<br />
airplaneDoc. No. A-00-10/225-ICA Issue<br />
1, Rev. IR Instructions for<br />
ContinuedAirworthiness shall be<br />
incorporated in the maintenance<br />
documentation ofthe<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 323/<strong>462</strong><br />
17.02.2<strong>01</strong>1<br />
24.03.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034796 LUFTHANSA TECHNIK AG A380-841, A380-842 DLH Stretcher Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.<strong>04</strong>.2<strong>01</strong>1<br />
10034892 LUFTHANSA TECHNIK AG A330-200 A330-200 Cabin retrofit ETD<strong>01</strong> None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10.05.2<strong>01</strong>1<br />
10034913 LUFTHANSA TECHNIK AG 747-400 Upgrade of first class cabin replacing 16 first<br />
class seats by 8modified first class seats and<br />
installation of 8 single beds and halfsize<br />
partitions in accordance with STDD25-10/13M<br />
Issue <strong>01</strong>, rev 00,d.d. 11-05-2<strong>01</strong>1<br />
10035638 LUFTHANSA TECHNIK AG A318-112 A318-112 - ELITE 16 MSN 4503Installation of<br />
a VIP Cabin Interior Completion.<br />
10036121 LUFTHANSA TECHNIK AG B747-400 SERIES Replacement of Global Positioning System<br />
Sensor Unit and GPS Antenna.<br />
10037721 LUFTHANSA TECHNIK AG A330-3<strong>01</strong> / -302 / -303<br />
Thai Airways A330-300 - Seat exchange and<br />
A330-321 / -322 / -323<br />
electrical adaption.This STC installs 263 Y<br />
A330-341 / -342 / -343<br />
class seats, with associated<br />
electricaladaptations.<br />
10038488 LUFTHANSA TECHNIK AG A340-311 / -312 / -313 A340-300 GPSSU ReplacementThis STC<br />
consists in replacing the current Global<br />
Positioning SystemSensor Unit (GPSSU) by a<br />
new standard able to transmit GPS<br />
qualityinformation.<br />
10038568 LUFTHANSA TECHNIK AG REV. 1 777-200 Introduction of Tailwind 550 Antenna This modification is limited to MSN 29953.This<br />
modification has a temporary life limit of 500<br />
Flight Cycles.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.05.2<strong>01</strong>1<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
06.07.2<strong>01</strong>1<br />
None. None. 19.08.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.12.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.02.2<strong>01</strong>2<br />
Prior to installation of this modification it 11.09.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039182 LUFTHANSA TECHNIK AG REV. 1 B737-700 Cabin Completion "Tiger" Refer to AFM limitations on the use of Portable Lufthansa Technik AG has shown within 24.<strong>04</strong>.2<strong>01</strong>2<br />
Electronic devices<br />
the substantiation data packagethat the<br />
installations covered by this Supplemental<br />
Type Certificate iscompatible with FAA<br />
approved FAA STC ST<strong>01</strong>697SE<br />
(identified thereafter asLow Cabin<br />
Altitude - LCA) for aircraft opera<br />
100393<strong>04</strong> LUFTHANSA TECHNIK AG A340-311/-312/-313 Navigation - ADS-B Out (Automatic Dependent<br />
Surveillance Broadcast)Capability on A340-<br />
300This STC consists in installing AOS-B Out<br />
capability.This surveillance function is based on<br />
the aircraft capability tobroadcast, without any<br />
ground request, aircraft p<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.<strong>04</strong>.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 324/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039353 LUFTHANSA TECHNIK AG REV. 1 A319-111/-112/-113/-114/-115 Replacement of Litton MK-1 Global Positioning None Prior to installation of this modification it 08.08.2<strong>01</strong>2<br />
A319-131/-132/-133<br />
System Sensor Unit (GPSSU)by CMC<br />
must be determined thatthe<br />
A320-111/-211/-212/-214/-215 Electronics GPSSU CMA-5024(STC revised<br />
interrelationship between this modification<br />
A320-216/-231/-232/-233 for validity extension to A319 and A321<br />
and any other previouslyinstalled<br />
A321-111/-112/-131/-211 models)<br />
modification and/ or repair will introduce<br />
A321-212/-213/-231/-232<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039798 LUFTHANSA TECHNIK AG REV. 1 B747-8 Installation of class 2 EFB docking station with<br />
display, cockpit doorsurveillance cameras an<br />
taxi aid cameras at vertical stabilizer and<br />
atfuselage belly.<br />
10039911 LUFTHANSA TECHNIK AG <strong>EASA</strong>.A.S.03922 777-200 AS PER 777-EB-21-0228 STDD 21-09/02M: B-777-200 - Zonal Drying<br />
System Installation<br />
10<strong>04</strong>0589 LUFTHANSA TECHNIK AG B747-8 Camera installation in the vertical stabilizer for<br />
ground manoeuvringservice.<br />
Only for EFB installation. No installation of the<br />
belly and tail fincamera in the frame of this<br />
STC.<br />
10<strong>04</strong>0628 LUFTHANSA TECHNIK AG 319-133 A319-133 ANJI VIP Cabin Completion - This design change approval is applicable on<br />
Aircraft model AirbusA319-133 CJ, aircraft<br />
serial number 4428.<br />
10<strong>04</strong>1<strong>04</strong>4 LUFTHANSA TECHNIK AG 737-800 VIP Cabin Interior Completion BBJ2 1) As per AFM limitations A-00-11/006-AFM,<br />
Issue05, Rev 00 :- The aircraft is certified for<br />
non-commercial use.- Required Crew: in case<br />
passengers are on board one (1) cabin<br />
attendantis required and has to be seated at<br />
door #1, left hand side.- Cabin WLAN:<br />
10<strong>04</strong>1482 LUFTHANSA TECHNIK AG A318-112 A318-100 - ELITE - Project Comlux3. Green<br />
aircraft completion to a VIPcabin configuration.<br />
10<strong>04</strong>2417 LUFTHANSA TECHNIK AG A320-211 Integration of the W-IFE (Wireless In-Flight<br />
Entertainment) system onA320.<br />
10<strong>01</strong>6808 LUFTTRANSPORT AS <strong>EASA</strong>.IM.R.S.<strong>01</strong>168 - EUROCOPTER FRANCE AS<br />
365N SERI<br />
Mast Measurement System / System for<br />
Measurement of ground stations fixed radio<br />
antenna for correct frequencies as signal<br />
effects<br />
10029513 M&D FLUGZEUGBAU GmbH & CO. KG P-<strong>EASA</strong>.A.S.029<strong>04</strong> GLASFLUEGEL 3<strong>04</strong>B Modification of Glasfluegel 3<strong>04</strong>B, S/N 324:<br />
retrofitting with winglets -modified wing tips:<br />
winglets.<br />
Prior to installation of this modification it 17.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
<strong>01</strong>.06.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
12.07.2<strong>01</strong>2<br />
The Lufthansa Technik's Instructions for<br />
continued airworthinessA-00-11/172-ICA<br />
Issue 2, Revision 00 dated 13th July 2<strong>01</strong>2<br />
approved aspart of this <strong>EASA</strong> STC<br />
contains:- A Section 4 with additional<br />
Airworthiness Limitation Items (ALI) that<br />
supplement those fr<br />
1) LCA compatibility necessary:<br />
Lufthansa Technik AG has shown<br />
withinthe substantiation data package<br />
that the installations covered by<br />
thisSupplemental Type Certificate is<br />
compatible with FAA approved FAA<br />
STCST<strong>01</strong>697SE (identified as Low Cabin<br />
16.07.2<strong>01</strong>2<br />
17.08.2<strong>01</strong>2<br />
Altitude - LC<br />
Prior to installation of this modification it 07.07.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.The ins<br />
This approval is limited to MSN <strong>01</strong>10. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.11.2<strong>01</strong>2<br />
None 12.06.2006<br />
Limited to Glasfluegel 3<strong>04</strong>B, S/N 324. None. 29.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 325/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4066 MACCARTHY AVIATION HOLDINGS Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>153 BOEING 747-400 Modification of Cabin to Install Zone B Cabin 1. Compliance with the following Requirements<br />
22.<strong>04</strong>.2005<br />
Class Dividers, Zone B Stowage & Dogbox, has not been established.:1.1. Viewing of all<br />
Door 2 Port & Starboard Dividers & Upper apllicable placards & signage to in compliance<br />
Deck Dogbox.<br />
with FAR/JAR 25.791.1.2. Weight, centre of<br />
Gravity & Weight Distribution, to be in<br />
compliance with JAR25.1519.1.3. Co<br />
10<strong>01</strong>4966 MACCARTHY AVIATION HOLDINGS Ltd. <strong>EASA</strong>.A.S.03241 BOEING 757 Installation of Galley 1B and Forward RH<br />
Wardrobe.<br />
10032<strong>01</strong>6 MACCARTHY AVIATION HOLDINGS Ltd. REV. 1 A319-133 CJ Revision of <strong>EASA</strong> STC 10032<strong>01</strong>6.Removal of<br />
the G1, G2 & G5 galleys’ loads established on<br />
initial issueof <strong>EASA</strong> STC 10032<strong>01</strong>6 date of<br />
issue <strong>01</strong>.10.2<strong>01</strong>0 granted to<br />
MacCarthyInteriors Ltd .<br />
10039505 MACH TECHNICAL DESIGN S.L. BELL 412 Surveillance Camera Installation according to<br />
MDL-FAA-<strong>01</strong>10 Rev. B(The modification<br />
consists in the installation of a camera to<br />
captureimages and the associated equipment<br />
to process and send them to a groundstation.)<br />
10<strong>01</strong>3933 MADELEC AERO - F9503 <strong>EASA</strong>.A.S.00318 REV 2 FOKKER F.28 MARK 0070 Installation of photoluminescent Floor Proximity<br />
Emergency Escape Path Marking system<br />
10<strong>01</strong>3949 MADELEC AERO - F9503 <strong>EASA</strong>.A.S.0<strong>04</strong>26 REV 3 AIRBUS A319-320-321 Replacement of the powered floor proximity<br />
emergency escape path marking system by a<br />
FPEEPM photoluminescent system<br />
<strong>04</strong>.12.2007<br />
Approval limited to MSN4114. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
25.10.2<strong>01</strong>0<br />
The installation of this STC is compatible with<br />
the installation of theTCCA STC SH96-57<br />
(LBA STC RC.1182): Installation of Heli-<br />
Access StepsP/N D205-0633-<strong>01</strong>1 in<br />
accordance with Dart Aerospace Ltd.<br />
DrawingIIN-D205-633, Rev A.Prior to<br />
installation of this m<br />
1. Photoluminescent system charge time: 10<br />
minutes.2. Photoluminescent Tape life time: 8<br />
years.3. MSN 11290-11296-11323-113294.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "De<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
10<strong>01</strong>5268 MAP AIRCRAFT PART 21 AS <strong>EASA</strong>.A.S.03739 REV 1 BOEING 737-400 Auxiliary Fuel Tank Removal, B737-400.<br />
installer.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7123 MAP AIRCRAFT PART 21 AS <strong>EASA</strong>.R.S.<strong>01</strong>210 EUROCOPTER FRANCE AS Installation of Polycon wireless communication Service Bulletin Polycon SB-03 Issue B shall<br />
332L2<br />
system in AS332L2 helicopter<br />
be implemented before installing this STC<br />
10<strong>01</strong>4154 MARSHALL OF CAMBRIDGE<br />
AEROSPACE<br />
10031215 MARSHALL OF CAMBRIDGE<br />
AEROSPACE<br />
10031227 MARSHALL OF CAMBRIDGE<br />
AEROSPACE<br />
10035677 MARSHALL OF CAMBRIDGE<br />
AEROSPACE<br />
<strong>EASA</strong>.A.S.<strong>01</strong>275 SOCATA MS 894A Marshall Aerospace Modification MA 1665.<br />
Radio Equipment Upgrade.<br />
26.07.2005<br />
A340-300 Structural Installation of 2 IFF Antennae none This STC only approves the antenna<br />
installation from a structural pointof view.<br />
Flight dynamic, electrical and functional<br />
aspects have not beenconsidered.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between thi<br />
02.08.2<strong>01</strong>0<br />
08.05.2<strong>01</strong>2<br />
08.03.2006<br />
31.03.2006<br />
16.02.2009<br />
<strong>04</strong>.12.2006<br />
A340-300 Structural Installation of a V/UHF Antenna none This STC only approves the antenna<br />
installation from a structural pointof view.<br />
Flight dynamic, electrical and functional<br />
aspects have not beenconsidered.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between thi<br />
03.08.2<strong>01</strong>0<br />
REV. 1 A318 CFM Major Change to <strong>EASA</strong> STC10035677<br />
"Installation of an Auxiliary FuelCentre Tank<br />
system on A318 Elite aircraft"This Major<br />
Change consists in removing the limitation<br />
concerning manualtransfer without<br />
pressurization above FL100.<br />
Restricted to A318 ELITE CFM aircraft<br />
only.This modification is not approved for<br />
installation on aircraft fittedwith a Flammability<br />
Reduction System<br />
Prior to installation of this modification it 08.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 326/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035729 MARSHALL OF CAMBRIDGE<br />
REV. 2 A340-313 Iberia Airways Interior Reconfiguration 1. This STC must be installed in conjunction Prior to installation of this modification it 16.07.2<strong>01</strong>2<br />
AEROSPACE<br />
with <strong>EASA</strong> STC No.<strong>EASA</strong>.A.S.00654. 2. This must be determined thatthe<br />
STC is limited to the aircraft MSN 125, 134, interrelationship between this modification<br />
145, 146, 217, 221,and 329<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036381 MARSHALL OF CAMBRIDGE<br />
AEROSPACE<br />
10<strong>04</strong><strong>04</strong>50 MARSHALL OF CAMBRIDGE<br />
AEROSPACE<br />
B737-700 737 Medevac Role Change None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.09.2<strong>01</strong>1<br />
REV. 1 A340-312 This modification intends to:This modification<br />
will install Seat Electronics Boxes (SEB)<br />
(PanasoniceX2) on to modified existing Avio<br />
business class seats and will removeexisting<br />
Zone Terminators (ZT) (installed under<br />
Marshall ModificationMA1951).Modificati<br />
10<strong>01</strong>5787 MASS SYSTEMS, <strong>EASA</strong>.IM.A.S.<strong>01</strong>843 FAA STC ST<strong>01</strong>708LA SD3-30 SD3-60 SD3-SHERPA<br />
SD3-60 SHERPA<br />
10<strong>01</strong>5793 MASS SYSTEMS, <strong>EASA</strong>.IM.A.S.<strong>01</strong>852 FAA STC ST00952LA 1.AEROSPATIALE ATR 72-1<strong>01</strong><br />
10.BOEING 757-200 SERIES<br />
11.BOEING 767-200 SERIES<br />
12.BOEING 777-200<br />
13.BOEING DC-10-10<br />
14.BOEING DC-9-81/82<br />
15.LOCKHEED 1<strong>01</strong>1-385-1<br />
2.AIRBUS A300 MODEL B2-1A<br />
3.AIRBUS A310-200<br />
4.AIRBUS A310-300<br />
5.AIRBUS A340-211<br />
6.AIRBUS A340-212<br />
7.BOEING 717-200<br />
8.BOEING 737-200 SERIES<br />
9.BOEING 747-400 SERIES<br />
AEROSPATIALE ATR 72-102<br />
AEROSPATIALE ATR 72-2<strong>01</strong><br />
AEROSPATIALE ATR 72-202<br />
AEROSPATIALE ATR 72-212<br />
AEROSPATIALE ATR 72-212A<br />
AIRBUS A300 MODEL B2-1C<br />
AIRBUS A300 MODEL B2-203<br />
AIRBUS A300 MODEL B2K-3C<br />
AIRBUS A300 MODEL B4-600<br />
AIRBUS A330-3<strong>01</strong><br />
AIRBUS A340-311<br />
AIRBUS A340-312<br />
BOEING 767-300 SERIES<br />
BOEING 777-300 SERIES<br />
BOEING DC-9-83 (MD-83)<br />
BOEING DC-9-87 (MD-87)<br />
BOEING MD-88<br />
BOEING MD-90<br />
Installation of MASS Systems’ fire extinguisher, The approval of this change in type design<br />
P/N M57331-009, as a replacement for the applies to the above-noted airplane model.<br />
Graviner fire extinguisher, P/N 57331-009in the This approval should not be extended to<br />
above-noted airplane model. This fire otherspecific airplanes of these model series<br />
extinguisher is in accordance with MASS on which other than noted previously approved<br />
Systems’ Drawing No. M57331-009, “Fire E modifications are incorporated, unless<br />
Installation of MASS Systems fire extinguisher<br />
cartridges as replacement for Walter Kidde<br />
Aerospace fire extinguisher cartridge in fire<br />
extinguisher bottles<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.10.2<strong>01</strong>2<br />
The approval of this change in type design<br />
applies to the airplane models noted on the<br />
FAA Approved Model ListA copy of thie STC<br />
must be included in the permanent records of<br />
the modified aircraft<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 327/<strong>462</strong><br />
16.<strong>04</strong>.2007<br />
<strong>04</strong>.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5794 MASS SYSTEMS, <strong>EASA</strong>.IM.A.S.<strong>01</strong>853 FAA STC ST00961LA 1.AEROSPATIALE ATR 42-200 Installation of MASS Systems Fire Extinguisher<br />
08.<strong>04</strong>.2008<br />
2.BELL 2<strong>04</strong>B<br />
Cartridge as replacement for Walter Kidde<br />
3.BOEING DC-8-71<br />
Aerospace fire extinguisher cartridges in fire<br />
4.BOEING DC-9-14<br />
extinguisher bottles installed in the airplane<br />
5.CESSNA 4<strong>01</strong><br />
models noted on the <strong>EASA</strong> approved model<br />
6.CESSNA 500<br />
7.EMBRAER EMB-120<br />
8.SAAB SF340A<br />
9.SIKORSKY S-76A<br />
AEROSPATIALE ATR 42-300<br />
AEROSPATIALE ATR 42-320<br />
AEROSPATIALE ATR 42-500<br />
AEROSPATIALE ATR 72-1<strong>01</strong><br />
AEROSPATIALE ATR 72-102<br />
AEROSPATIALE ATR 72-2<strong>01</strong><br />
AEROSPATIALE ATR 72-202<br />
AEROSPATIALE ATR 72-211<br />
AEROSPATIALE ATR 72-212<br />
AEROSPATIALE ATR 72-212A<br />
BELL 205A<br />
BELL 205A-1<br />
BELL 205B<br />
BELL 212<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
BOEING DC-8-61<br />
BOEING DC-8-61F<br />
BOEING DC-8-63<br />
BOEING DC-8-63F<br />
BOEING DC-8-71F<br />
BOEING DC-8-72<br />
list dtd 02 April 2008 (which exc<br />
10<strong>01</strong>5795 MASS SYSTEMS, <strong>EASA</strong>.IM.A.S.<strong>01</strong>854 FAA STC ST00885LA BOEING 1. AIRBUS DC-8-73 A300 SEE LIST Installation of Mass Systems, Inc. fire This STC is approved only for the product<br />
24.<strong>01</strong>.2007<br />
10. BOEING 737 SERIES extinguisher cartridges as replacements for configuration as defined in the approved design<br />
11. BOEING DC-9 SERIES SEE Pacific Scientific fire extinguisher cartridgesin data referred to in the paragraphs "Description"<br />
LIS<br />
fire extinguisher bottles installed in the airplane and “Associated Technical Documentation”.<br />
12. BOEING MD11 SEE LIST models noted on the <strong>EASA</strong> Approved Model Compatibility with other aircraft/engine<br />
13. BOEING 747SP SEE LIST<br />
14. BOEING 757 SEE LIST<br />
15. BOEING 767 SEE LIST<br />
16. BOMBARDIER CL-600 SEE<br />
LIST<br />
17. EMBRAER MB120 MB145<br />
18. JETSTREAM 41<strong>01</strong><br />
18. SAAB 340A 340B<br />
2.A319 A310 SEE LIST<br />
3. A330 SEE LIST<br />
4. A340 SEE LIST<br />
5. BOEING 747 SEE LIST<br />
6. FOKKER F.27 MARK 100 SEE<br />
LI<br />
7. F.47 MARK 1000 SEE LIST<br />
8. RAYTHEON HB. 125 SERIES<br />
9. BOEING 707 SEE LIST<br />
List dated 24th January.<br />
configurations shall be determined<br />
10027602 MAX-VIZ Inc. P-<br />
FAA STC ST<strong>01</strong>523LA F900EX, MF50, MF900 <strong>EASA</strong> Validation of FAA STC<br />
This design change is also applicable on the Prior to installation of this modification it 13.10.2009<br />
<strong>EASA</strong>.IM.A.S.02776<br />
ST<strong>01</strong>523LA:Installation of Max-Viz Enhanced Mystere Falcon 50EXdesignation as defined on must be determined thatthe<br />
Vision System (EVS) 1000 in accordancewith <strong>EASA</strong> TCDS.A.062 but limited to the interrelationship between this modification<br />
Master Drawing List Document number 3038- serialnumber aircraft MSN 286. For this MSN and any other previouslyinstalled<br />
00025 Revision 5, dated14th October 2008 or 286 aircraft the applicable <strong>EASA</strong>Flight Manual modification and/ or repair will introduce<br />
later revisions approved by <strong>EASA</strong> in<br />
Supplement is the initial release of Docu no adverse effectupon the airworthiness<br />
accordance with<strong>EASA</strong> ED<br />
of the product.<br />
10<strong>01</strong>7126 MBH TECHNIC'S <strong>EASA</strong>.R.S.<strong>01</strong>214 SA 365 N S/N 6100 Installation of EMS cabin configuration, in This STC is limited to SA 365 N s/n 6100 and<br />
accordance with MBH Technic's STC file n° <strong>01</strong> can be installed only by MBH Technic's<br />
MBHT-05, original issue dated 29/03/2005, or technical staff in accordance with MBH<br />
later <strong>EASA</strong> approved revision.<br />
Technic's STC file n° <strong>01</strong> MBHT-05, original<br />
issue dated 29/03/2005, or later <strong>EASA</strong><br />
approved revision.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 328/<strong>462</strong><br />
27.02.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5807 MCCAULEY PROPELLER SYSTEMS <strong>EASA</strong>.IM.A.S.<strong>01</strong>875 FAA STC SA00798CH CESSNA FR-182 Installation of a McCauley Propeller Model FAA Approved Flight Manual Supplement,<br />
08.06.2006<br />
B3D36C431/80VSA-1 or B3D36C433/80VSA- Technical Report Number 874, dated August<br />
1, and spinner assembly.<br />
4, 1997, or later approved revision<br />
required.Lycoming engine model O-540-<br />
J3C5D is eligible with the McCauley Propeller<br />
Model B3D36C433/80VSA-1 (S/N<br />
FR182000<strong>01</strong> through FR182000<br />
10<strong>01</strong>6128 MCCAULEY PROPELLER SYSTEMS <strong>EASA</strong>.IM.A.S.02322 FAA STC SA496CH BEECH 23 Installation of McCauley Propeller Model 1. Aircraft Specifications are the same as listed<br />
22.05.2007<br />
B3D36C429/82NPR-6<br />
on Type Certification Data Sheet A1CE, except<br />
as follows:Propeller and Propeller<br />
Limits:Propeller: McCauley Constant Speed<br />
B3D36C429/82NPA-6Number of blades: 3<br />
Blade Angels: At 30" station: Low 10.<br />
10029619 MCCAULEY PROPELLER SYSTEMS P-<br />
<strong>EASA</strong>.IM.A.S.03127<br />
FAA STC SA<strong>01</strong>511WI C400 (LC41-550FG) Installation of McCauley C447 As referred in limitations section of the AFM-S The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe interr<br />
10<strong>01</strong>7129 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>219 REV. 1 AB139/ AW139 AB139 VIP 28 P/N 6AB1KT003-0<strong>01</strong> Interior<br />
Configuration. This STC supersedes <strong>EASA</strong><br />
STC <strong>EASA</strong>.R.S.<strong>01</strong>219.<br />
Approval of this change in type design applies<br />
only to those AB139rotorcraft previously<br />
equipped with <strong>EASA</strong> approved Installation of<br />
AgustaKit VIP PROVISION P/N<br />
4G2520F00511.<br />
06.<strong>04</strong>.2<strong>01</strong>0<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7130 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>220 REV. 2 AW139 VIP 29 Interiors 10 seats P/N 6AB1KT0<strong>04</strong>-0<strong>01</strong>. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.07.2<strong>01</strong>2<br />
10<strong>01</strong>7140 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>242 REV. 1 AB139/ AW139 VIP 37 Interiors P/N 6AB1KT005-0<strong>01</strong>: Cabin<br />
interiors modification. This STC supersedes<br />
<strong>EASA</strong> STC <strong>EASA</strong>.R.S.<strong>01</strong>242.<br />
10<strong>01</strong>7149 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>252 REV. 2 A109S, AW109SP Cabinet Installation P/N 6A10AD0<strong>01</strong>-0<strong>01</strong>.<br />
Extension of the STC 10<strong>01</strong>7149 to the<br />
AW109SP model that is part of thesame TC<br />
Number <strong>EASA</strong>.R.005<br />
The change in type design applies only to those Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
AB139/AW139 Rotorcraftpreviously equipped must be determined thatthe<br />
with Agusta "Kit VIP Cabin Passenger interrelationship between this modification<br />
Provision P/N4G2520F00711".<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification the <strong>01</strong>.03.2<strong>01</strong>1<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10<strong>01</strong>7150 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>253 REV. 1 AB139/ AW139 CD Player Installation P/N 6AB1EL<strong>01</strong>7-0<strong>01</strong> the The change in type design applies only to those Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
change consists in theinstallation of a CD AB139 Rotorcraft previously equipped with must be determined thatthe<br />
Player into passenger cabin. This STC Agusta provision P/N 3G2520A00311 interrelationship between this modification<br />
supersedes <strong>EASA</strong> STC <strong>EASA</strong>.R.S.<strong>01</strong>253.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7151 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>254 REV. 1 AB139/ AW139 SAT-COM Installation P/N 6AB1EL<strong>01</strong>8-<br />
0<strong>01</strong>The change consists in the installation of a<br />
Satellite Telephone Systemon passenger<br />
cabin. This STC supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.R.S.<strong>01</strong>254.<br />
The change in type design applies only to those<br />
AB139 Rotorcraft previously equipped with<br />
Agusta SAT-COM provision P/N<br />
3G2310F0<strong>04</strong>11<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 329/<strong>462</strong><br />
19.06.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7161 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>269 REV. 1 AB139/ AW139 Cabinet Utility Installation P/N 6AB1AD0<strong>04</strong>- Cabinet Utility Installation P/N 6AB1AD0<strong>04</strong>- Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
0<strong>01</strong>. This STC supersedes <strong>EASA</strong> STC 0<strong>01</strong> is compatible with AgustaS.p.A. cabin must be determined thatthe<br />
<strong>EASA</strong>.R.S.<strong>01</strong>269.<br />
arrangements n. 3G2520F0<strong>01</strong>11 and interrelationship between this modification<br />
3G2520F00211.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7162 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>270 REV. 1 AB139/ AW139 115V AC Power Installation.Electrical power<br />
connectors installation in the passenger<br />
compartment. This STC supersedes <strong>EASA</strong><br />
STC <strong>EASA</strong>.R.S.<strong>01</strong>270.<br />
10<strong>01</strong>7163 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>271 REV. 1 AB139/ AW139 ICS Installation. Intercommunication System in<br />
the passengercompartment. This STC<br />
supersedes <strong>EASA</strong> STC <strong>EASA</strong>.R.S.<strong>01</strong>271.<br />
10<strong>01</strong>7170 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>278 REV. 2 AB139/ AW139 AB139 VIP 43 Interiors P/N 6AB1AD006-<br />
0<strong>01</strong>The change consists in customizing<br />
passenger cabin interiors(upholstering,<br />
installing a decorative bulkhead, entertainment<br />
devices,a small cabinet and other minor items).<br />
This STC supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.R.S.<strong>01</strong>278 R<br />
10<strong>01</strong>7176 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>294 REV. 1 AB139/ AW139 VIP 55 Interiors P/N 6AB1AD007-0<strong>01</strong>The<br />
change consists in customizing passenger<br />
cabin interiors(personalized seat layout, carpet<br />
and liners, devices, adding a smallcabinet and<br />
others minor items). This STC supersedes<br />
<strong>EASA</strong> STC <strong>EASA</strong>.R.S.<strong>01</strong>294.<br />
10<strong>01</strong>7198 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>341 REV. 1 AB139/ AW139 VIP 87 Interiors P/N 6AB1AD008-0<strong>01</strong>. This<br />
STC supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.R.S.<strong>01</strong>341.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.06.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.06.2<strong>01</strong>0<br />
This change in type design applies only to<br />
those AB139 rotorcrafts previously equipped<br />
with <strong>EASA</strong> approved installation of Agusta kit<br />
VIP PROVISION P/N 4G2520F00811.<br />
The change in type design applies only to those<br />
AB139/AW139 Rotorcrafts previously<br />
equipped with <strong>EASA</strong> "Kit VIP Provision P/N<br />
4G2520F<strong>01</strong>311".<br />
This STC is only applicable to the AB139 and<br />
AW139 helicopters equippedwith the Agusta<br />
provision for VIP Cabin Interiors P/N<br />
4G2520F<strong>01</strong>511.<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.06.2<strong>01</strong>0<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7255 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>461 REV. 1 AB139/ AW139 Interiors Configuration Vip 131 P/N<br />
Agusta provision P/N 4G2520F03311 must be Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
6AB1AD009-0<strong>01</strong>. This STC supersedes <strong>EASA</strong> installed.<br />
must be determined thatthe<br />
STC <strong>EASA</strong>.R.S.<strong>01</strong>461.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>7261 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>470 REV. 1 AB139/ AW139 AB/AW139 Seat Armrests Installation P/N This STC can only be installed on the<br />
6AB1AD<strong>01</strong>1-0<strong>01</strong>. This STC supersedes <strong>EASA</strong> AB/AW139 12-seat configuration<br />
STC <strong>EASA</strong>.R.S.<strong>01</strong>470.<br />
P/N3G2520F0<strong>01</strong>11 that embodies seats P/N<br />
3G2520V0<strong>01</strong>31.<br />
10<strong>01</strong>7267 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>486 REV. 2 AB139/ AW139 VIP 37 Plus Interiors P/N 6AB1AD<strong>01</strong>2-0<strong>01</strong>, 7<br />
and 9 seats configurations. This STC<br />
supersedes <strong>EASA</strong> STC <strong>EASA</strong>.R.S.<strong>01</strong>486<br />
Revision 1.<br />
The VIP 37 Plus Interiors Installation P/N<br />
6AB1AD<strong>01</strong>2-0<strong>01</strong> can only beinstalled on AB/<br />
AW 139 helicopters equipped with Agusta<br />
provision P/N4G2520F03911.<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 330/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7290 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>545 REV. 1 AB139/ AW139 AW139 VIP 221 Interiors, P/N 6AB1AD<strong>01</strong>3- The VIP 221 interiors can only be installed on Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
0<strong>01</strong>. This STC supersedes <strong>EASA</strong> STC AB/AW 139 helicoptersequipped with Agusta must be determined thatthe<br />
<strong>EASA</strong>.R.S.<strong>01</strong>545.<br />
provision P/N 4G2520F0<strong>04</strong>11.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030095 MECAER AVIATION GROUP S.P.A. AB139 / AW139 AW139 VIP 305 INTERIORSP/N 6AB1AD<strong>01</strong>5- As per the approved Rotorcraft Flight Manual<br />
0<strong>01</strong><br />
Supplement quoted above<br />
10030280 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.0<strong>04</strong>84 REV. 1 AB139/ AW139 Cabin Configuration VIP-4 P/N 6-A02<strong>01</strong>KI<strong>01</strong><strong>01</strong>- Approval of this change in type design applies<br />
003. This STC supersedes <strong>EASA</strong> STC only to those AB 139rotorcraft previously<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>84.<br />
equipped with <strong>EASA</strong> approved installation of<br />
AgustaKit Vip Cabin interior (Namibia) P/N<br />
3G2520F0<strong>04</strong>11.<br />
Prior to installation of this modification it 21.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
10030281 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.0<strong>04</strong>85 REV. 1 AB139/ AW139<br />
product.<br />
Cabin Configuration VIP-3 P/N 6-A02<strong>01</strong>KI<strong>01</strong><strong>01</strong>- Approval of this change in type design applies Prior to installation of this modification the 09.06.2<strong>01</strong>0<br />
0<strong>01</strong>. This STC supersedes <strong>EASA</strong> STC only to those AB 139rotorcraft previously installer must determinethat the<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>85.<br />
equipped with <strong>EASA</strong> approved installation of interrelationship between this modification<br />
AgustaKit Vip Cabin interior (Namibia) P/N and any otherpreviously installed<br />
3G2520F0<strong>04</strong>11.<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10030339 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.0<strong>04</strong>86 REV. 1 AB139/ AW139 Cabin Configuration VIP-2 P/N 6-A03<strong>01</strong>KI<strong>01</strong><strong>01</strong>- Approval of this change in type design applies Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
003. This STC supersedes <strong>EASA</strong> STC only to those AB 139rotorcraft previously must be determined thatthe<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>86.<br />
equipped with <strong>EASA</strong> approved installation of interrelationship between this modification<br />
AgustaKit Vip Cabin interior (UAE) P/N and any other previouslyinstalled<br />
3G2520F00511.<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10030340 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.0<strong>04</strong>87 REV. 1 AB139/ AW139 Cabin Configuration VIP-1 P/N 6-A03<strong>01</strong>KI<strong>01</strong><strong>01</strong>- Approval of this change in type design applies<br />
0<strong>01</strong>. This STC supersedes <strong>EASA</strong> STC only to those AB 139rotorcraft previously<br />
<strong>EASA</strong>.R.S.0<strong>04</strong>87.<br />
equipped with <strong>EASA</strong> approved installation of<br />
AgustaKit Vip Cabin interior (UAE) P/N<br />
3G2520F00511.<br />
10030342 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>226 REV. 2 AB139/ AW139 FWD Bulkhead P/N 6AB1AD005-0<strong>01</strong><br />
Installation. This STC supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.R.S.<strong>01</strong>226.<br />
10030371 MECAER AVIATION GROUP S.P.A. <strong>EASA</strong>.R.S.<strong>01</strong>534 REV. 1 AB139/ AW139 AW139 "Liners" Silens P/N 6AB1AD<strong>01</strong>0-0<strong>01</strong>.<br />
This STC supersedes <strong>EASA</strong> STC<br />
<strong>EASA</strong>.R.S.<strong>01</strong>534.<br />
10031938 MECAER AVIATION GROUP S.P.A. AW139 / AB139 IFEEL Entertainment System Installation P/N<br />
6AB1AD<strong>01</strong>6-0<strong>01</strong><br />
09.06.2<strong>01</strong>0<br />
Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.06.2<strong>01</strong>0<br />
This STC requires the installation of the Kit Prior to installation of this modification it 09.06.2<strong>01</strong>0<br />
Hinged Passengers DoorsP/N 4G5212F0<strong>01</strong>11. must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.09.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 331/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038915 MECAER AVIATION GROUP S.P.A. MBB-BK117 C-2 EC145 VIP MB Interiors Drawing No. None Prior to installation of this modification it 23.03.2<strong>01</strong>2<br />
6EC10000X0<strong>01</strong>-0<strong>01</strong><br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039438 MECAER AVIATION GROUP S.P.A. REV. 1 AW109SP Installation of Cabinet Five Star P/N<br />
6A10AD002-0<strong>01</strong> in AW109SP.Modification in<br />
accordance with MECAER Notice of Design<br />
Change NDC6A10AD-003 issue A dated<br />
24/<strong>04</strong>/2<strong>01</strong>2.<br />
This STC approval does not include the<br />
installation of the in-flightentertainment<br />
equipment inside the Cabinet Five Star.<br />
10<strong>04</strong>2023 MECAER AVIATION GROUP S.P.A. AW139 Ballast Installation P/N 6AB1AD<strong>01</strong>8-0<strong>01</strong> This STC is only installable on AW139<br />
Helicopters equipped withAgustaWestland<br />
Active Vibration Control System P/N<br />
4G1830F0<strong>01</strong>11 or4G1830F00211.<br />
10<strong>01</strong>5810 MEGGITT (ADDISON), Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>879 FAA STC NO ST09494SC CESSNA 182S<br />
CESSNA 182T<br />
CESSNA T182T<br />
10<strong>01</strong>6754 METRO AVIATION, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>083 FAA STC SH3880SW EUROCOPTER DEUTSCHLAND<br />
MBB-BK<br />
Installation of an R134a vapour cycle airconditioning<br />
system<br />
Installation of a Vapor Cycle Air Conditioner in<br />
accordance with FA STC SH3880SW<br />
10<strong>01</strong>6780 METRO AVIATION, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>120 FAA STC SR<strong>01</strong>606NY-D EUROCOPTER DEUTSCHLAND Installation of Spectrolab SX-5 Starbust<br />
MBB-BK<br />
searchlight according to FAA STC SR<strong>01</strong>606NY-<br />
D<br />
10<strong>01</strong>6823 METRO AVIATION, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>188 REV. 1 FAA STC SR09163RC EUROCOPTER EC 135 Installation of mechanically driven vapor cycle Prior to installation of this modification the<br />
air condition system i.a.w. FAA STC<br />
installer must determine that the<br />
SR09163RC as amended by 18-06-<br />
interrelationship between this modification and<br />
2007.Major change to <strong>EASA</strong> STC<br />
any other previously installed modification will<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>188, addition of models and introduce no adverse effect upon the<br />
incorporation of technical modifications. airworthiness of the product. The install<br />
10<strong>01</strong>6976 METRO AVIATION, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>377 FAA STC SR09230RC EUROCOPTER DEUTSCHLAND<br />
EC-135<br />
10035563 MICHELIN NORTH AMERICA, INC. FAA STC ST03642AT CL-600-2C10, CL-600-2D15<br />
CL-600-2D24<br />
10<strong>01</strong>5379 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>058 FAA STC SA00763SE PIPER PA-30<br />
PIPER PA-39<br />
Prior to installation of this modification it 16.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 05.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC is approved only for the product<br />
10.<strong>04</strong>.2006<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. This STC is approved only for the product<br />
31.05.2005<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
None 13.09.2006<br />
Installation of landing gear skid extensions Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of Michelin's tire(s) P/N 029-9<strong>01</strong>-0<br />
on the main gear and/orP/N 036-897-0 on the<br />
nose landing gear of Bombardier CL-600-<br />
2C10,CL-600-2D15, CL-600-2D24 aircraft<br />
wheel assembly.<br />
Installation of Vortex Generators on the Wing 1. This STC is approved only for the product<br />
leading edge, and vertical fin surfaces.Drawing configuration as defined in the approved design<br />
Package MA2122 Rev. IR dated 25 October data referred to in the paragraph "Description".<br />
1999, or later approved revision.AFM Compatibility with other aircraft/engine<br />
Supplement for PA-30 & PA-39 dated 13 July configurations shall be determined by the<br />
2005.Installation Manual MA2123 Rev. IR da installer.<br />
14.<strong>04</strong>.2008<br />
26.11.2007<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.06.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 332/<strong>462</strong><br />
08.08.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5979 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.02131 FAA STC SA00887SE CESSNA 206<br />
Installation of vortex generators on the wings, 1. If more than Five vortex generators are<br />
20.09.2006<br />
CESSNA 206H<br />
tail surfaces and vertical fin<br />
damaged or missing, the aircraft is not<br />
CESSNA 207<br />
airworthy2. This STC is approved only for the<br />
CESSNA 207A<br />
product configuration as defined in the<br />
CESSNA P206<br />
approved design data referred to in the<br />
CESSNA P206A<br />
CESSNA P206B<br />
CESSNA P206C<br />
CESSNA P206D<br />
CESSNA P206E<br />
CESSNA T206H<br />
CESSNA T207<br />
CESSNA T207A<br />
CESSNA TP206A<br />
CESSNA TP206B<br />
CESSNA TP206C<br />
CESSNA TP206D<br />
CESSNA TP206E<br />
CESSNA TU206A<br />
CESSNA TU206B<br />
CESSNA TU206C<br />
CESSNA TU206D<br />
CESSNA TU206E<br />
CESSNA TU206F<br />
CESSNA U206<br />
CESSNA U206A<br />
CESSNA U206B<br />
CESSNA U206C<br />
CESSNA U206D<br />
CESSNA U206E<br />
CESSNA U206F<br />
CESSNA U206G<br />
paragraph "Description". Compatibility with oth<br />
10<strong>01</strong>6088 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.02275 FAA STC SA00831SE CESSNA 172A-S<br />
Installation of vortex generators on the wings Approval of this change in type design applies<br />
13.<strong>04</strong>.2007<br />
CESSNA 172RG<br />
and tail surfaces in accordance with the to the aircraft listed on AML SA00831SE only.<br />
CESSNA 175A-C<br />
provisions of AML SA00831SE.<br />
This approval should not be extended to other<br />
CESSNA P172D<br />
aircraft on which other previously approved<br />
modification are incorporated unless it is<br />
determined that the relationsh<br />
10<strong>01</strong>6354 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.02675 FAA STC SA00941SE CESSNA 210G,H,J,K,L,M,N,<br />
CESSNA P210N<br />
CESSNA T210G<br />
CESSNA T210J, T210H<br />
CESSNA T210K<br />
CESSNA T210L<br />
CESSNA T210M<br />
CESSNA T210N<br />
Installation of vortex generators on the wing<br />
and tail surfaces.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 333/<strong>462</strong><br />
27.02.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6558 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.02942 REV 1 FAA STC SA00834SE CESSNA 182C<br />
Installation of vortex generators on the wings 1. Prior to installation of this modification the<br />
27.10.2008<br />
CESSNA 182D<br />
and tail surfaces in accordance with the installer must determine that the<br />
CESSNA 182E<br />
provisions of AML SA00834SE.<br />
interrelationship between this modificationand<br />
CESSNA 182F<br />
any other previously installed modification<br />
CESSNA 182G<br />
will introduce no adverse effect upon the<br />
CESSNA 182H<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA 182S<br />
CESSNA 182T<br />
CESSNA F182-P<br />
CESSNA F182-Q<br />
CESSNA FR-172-E<br />
CESSNA FR-172-F<br />
CESSNA FR-172-G<br />
CESSNA FR-172-H<br />
CESSNA FR-172-J<br />
CESSNA FR-172-K<br />
CESSNA FR-182<br />
CESSNA R172E/F/G/H/J/K<br />
CESSNA R182<br />
CESSNA T182T<br />
CESSNA TR182<br />
airworthiness of the produc<br />
10<strong>01</strong>6576 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.02974 REV. 1 FAA STC SA<strong>01</strong>266SE PA-32-3<strong>01</strong>, PA-32-3<strong>01</strong>T<br />
Installation of vortex generators on the wings If more than five vortex generators are Prior to installation of this modification the 10.02.2<strong>01</strong>0<br />
PA-32-3<strong>01</strong>FT, PA-32-3<strong>01</strong>XTC and tail surfaces inaccordance with the damaged or missing, the Aircraftis not installer must determinethat the<br />
PA-32R-3<strong>01</strong>(HP), PA-32R-3<strong>01</strong>T provisions of AML SA<strong>01</strong>266SE.<br />
airworthy.<br />
interrelationship between this modification<br />
PIPER PA-32R-3<strong>01</strong>(SP)<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>6663 MICRO AERODYNAMICS, INC. <strong>EASA</strong>.IM.A.S.03126 REV 1 FAA STC SA<strong>01</strong>646SE CESSNA 172<br />
Installation of vortex generators on the wings Prior to installation of this modification the<br />
17.03.2009<br />
CESSNA 175<br />
and tail surfaces in accordance with the installer must determine that the<br />
CESSNA 180<br />
provisions of AML SA<strong>01</strong>646SE.<br />
interrelationship between this modification and<br />
CESSNA 180A<br />
any other previously installed modification will<br />
CESSNA 180B<br />
introduce no adverse effect upon the<br />
CESSNA 180C<br />
CESSNA 180D<br />
CESSNA 180E<br />
CESSNA 180F<br />
CESSNA 180G<br />
CESSNA 180H<br />
CESSNA 180J<br />
CESSNA 180K<br />
CESSNA 182<br />
CESSNA 182A<br />
CESSNA 182B<br />
CESSNA 185<br />
CESSNA 185A<br />
CESSNA 185B<br />
CESSNA 185C<br />
CESSNA 185D<br />
CESSNA 185E<br />
CESSNA A185E<br />
CESSNA A185F<br />
airworthiness of the product.The installa<br />
10031549 MICRO AERODYNAMICS, INC. FAA STC SA00834SE 1. 150F, 150G, 150H, 150J Installation of vortex generators on the wings Approval of this change in type design applies Prior to installation of this modification the 25.08.2<strong>01</strong>0<br />
1. 150K, 150L, 150M, A150K and vertical tailsurfaces on Cessna 150/152 to the aircraft listed onAML SA<strong>01</strong>065SE only. installer must determinethat the<br />
1. A150L, A150M, 152, A152 (see applicabel Model list).<br />
This approval should not be extended to interrelationship between this modification<br />
2. F150G, F150H, F150J<br />
otheraircraft on which other previously and any otherpreviously installed<br />
2. F150K, F150L, F150M,<br />
approved modification areincorporated unless modification will introduce no adverse<br />
2. FA150K, FA150L, F152, FA152<br />
it is determined that the relationship<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 334/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034885 MICRO AERODYNAMICS, INC. FAA STC SA02098SE 65-90, 65-A90, 65-A90-1 Installation of Vortex Generators on the wings If more than five vortex generators, or either This STC has been found compatible 10.05.2<strong>01</strong>1<br />
65-A90-2, 65-A90-3, 65-A90-4 and tail surfaces, andstrakes on the engine nacelle stake are damagedor missing, the with FAA STC SA10747SC dated<br />
B90, C90, C90A, C90GT nacelles.<br />
aircraft is no longer airworthy.<br />
October06, 2006 (<strong>EASA</strong> STC ref<br />
C90GTI, E90, H90<br />
<strong>EASA</strong>.IM.A.S.02863 Rev 1)Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previou<br />
10038573 MICRO AERODYNAMICS, INC. FAA STC#SA<strong>01</strong>681SE 1. PA-34-200, PA-34-200T, Installation of vortex generators on the wings, If more than five vortex generators are The installation of this modification by 27.02.2<strong>01</strong>2<br />
1. PA-34-220T (SENECA III) horizontal and verticaltail surfaces (all models), damaged or missing, the aircraftis no longer third persons is subject towritten<br />
1. PA-34-220T (SENECA IV) and an increase in maximum zero fuel airworthy.<br />
permission of the approval holder and<br />
2. PA-34-220T (SENECA V) weight(PA-34-200T and M20 03 only).<br />
disposal of the approvedappropriate<br />
3. PZL M20 03 "MEWA"<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>04</strong>0949 MICRO AERODYNAMICS, INC. REV. 2 FAA STC SA<strong>01</strong>161SE PA-32-260, PA-32-300<br />
Installation of Vortex Generators on the wing If the holder agrees to permit another person to The installation of this modification by 11.09.2<strong>01</strong>2<br />
PA-32S-300, PA-32R-300 and tail surface accordingto drawing package use this certificate toalter the product, the third persons is subject towritten<br />
MA2174, revision IR dated 06-Sep-2002 holder shall give the other person<br />
permission of the approval holder and<br />
andinstallation manual MA2175 revision A writtenevidence of that permission.If more than disposal of the approvedappropriate<br />
dated 27-Aug-2003 or later FAAapproved 5 vortex generators are damaged or missing, documentation.Prior to installation of this<br />
revision to either of these documents. the A/C is notairworthy.<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>04</strong>1846 MICRO AERODYNAMICS, INC. FAA STC SA02226SE DA 42, DA 42NG, DA 42M-NG Installation of vortex generators on the wings None Prior to installation of this modification it 19.10.2<strong>01</strong>2<br />
and tail surfaces.FAA STC SA02226SE<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5935 MID-CANADA MOD CENTER <strong>EASA</strong>.IM.A.S.02075 SA03-92 Cockpit voice recorder replacement with<br />
Universal CVR 30 or CVR 120<br />
-- 14.12.2006<br />
10036039 MID-CANADA MOD CENTER CESSNA 550, S550 Installation of Rockwell Collins Proline 21 None Prior to installation of this modification it 08.08.2<strong>01</strong>1<br />
Integrated Display Systemwith new VHF<br />
must be determined thatthe<br />
communication transceivers, Navigation<br />
interrelationship between this modification<br />
Receivers withintegral ADF, Distance<br />
and any other previouslyinstalled<br />
Measuring Equipment Transceivers and Mode<br />
modification and/ or repair will introduce<br />
STransponders with Elementary Surveillance<br />
no adverse effectupon the airworthiness<br />
capability, R<br />
of the product.<br />
10038891 MID-CANADA MOD CENTER TCCA STC SA10-16 CL-600-2B19 CMC Electronics CMA-1100, Class II<br />
Electronic Flight Bag (EFB) SystemInstallation<br />
10<strong>04</strong>1743 MID-CANADA MOD CENTER TCCA STC O-LSA09-348/D CL-600-2B19 TrueNorth Satphone Installation Restricted to ASN 8092.<strong>EASA</strong> STC<br />
Nos.10038463 and 10028338 Rev. 2<br />
(Transport Canada STC Nos.O-LSA09-344/D<br />
and C-LSA09-326/D) are pre-requisites to this<br />
approval.<br />
10<strong>01</strong>5913 MILLENNIUM CONCEPTS, INC. <strong>EASA</strong>.IM.A.S.02<strong>04</strong>2 REV. 1 FAA STC SA<strong>01</strong>160WI CESSNA 208<br />
CESSNA 208B<br />
10<strong>04</strong>1159 MILLENNIUM CONCEPTS, INC. REV. 1 FAA STC SA<strong>01</strong>671WI - D 1- G36 - BONANZA<br />
2- G58 - BARON<br />
10<strong>01</strong>6595 MITSUBISHI HEAVY INDUSTRIES<br />
AMERICA<br />
Installation of Executive Interior in Cessna<br />
Models 208, 208B Caravan<br />
Installation of interior configuration per Master<br />
Drawing List2033-MDL<strong>04</strong>0, rev. P, dated 8<br />
February 2<strong>01</strong>2.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.03.2<strong>01</strong>2<br />
If the holder agrees to permit another person to<br />
use this certificate toalter the product, the<br />
holder shall give the other person<br />
writtenevidence of that permission.<br />
<strong>EASA</strong>.IM.A.S.03006 FAA STC SA1751SW Flight Crew Restraint System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
Prior to installation of this modification it 12.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 335/<strong>462</strong><br />
08.02.2008<br />
27.08.2<strong>01</strong>2<br />
22.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038450 MITSUBISHI HEAVY INDUSTRIES<br />
FAA STC SA<strong>01</strong>594SE 1- MU-2B-20, -25, -26<br />
Fabrication and Installation of Stretched Acrylic None. The installer must determine whether this 17.02.2<strong>01</strong>2<br />
AMERICA<br />
2- MU-2B-30, -35, -36<br />
Cabin Windows inaccordance with FAA STC<br />
design change is compatiblewith<br />
3- MU-2B-20, -25, -26<br />
SA<strong>01</strong>594SE.<br />
previously approved modifications.If the<br />
3- MU-2B-30, -35, -36<br />
holder agrees to permit another person to<br />
4- MU-2B-25, -26, -26A<br />
use this certificate toalter a product, the<br />
4- MU-2B-35, -36, -36A,<br />
holder must give the other person written<br />
4- MU-2B-40, -60<br />
evidenceof th<br />
10<strong>01</strong>4115 MONARCH AIRCRAFT ENGINEERING<br />
LTD<br />
<strong>EASA</strong>.A.S.<strong>01</strong>221 BOEING 737-522 Installation of Honeywell EGPWS 06.<strong>04</strong>.2005<br />
10<strong>01</strong>4116 MONARCH AIRCRAFT ENGINEERING<br />
LTD<br />
<strong>EASA</strong>.A.S.<strong>01</strong>222 BOEING 737-522 Introduction of 131 Passenger Configuration <strong>01</strong>.<strong>04</strong>.2005<br />
10<strong>01</strong>4155 MONARCH AIRCRAFT ENGINEERING <strong>EASA</strong>.A.S.<strong>01</strong>277 BOEING 767-300 Monarch Aircraft Engineering Modification Subject AFM supplement is associated to<br />
29.06.2005<br />
LTD<br />
MON/767/258/2995 Installation of a 38 Dassault Aviation Mod M1632: "Installation<br />
Premium Class Cabin<br />
d'un hublot inférieur avec volet de<br />
protection",applicable to F20 GF SN 397 only<br />
10<strong>01</strong>3959 MOTORFLUG BADEN-BADEN GmbH <strong>EASA</strong>.A.S.00610 SOCATA TB 20 Installation of Transponder Garmin GTX 330 -<br />
Mode S<br />
10028137 MOTORFLUG BADEN-BADEN GmbH P-<strong>EASA</strong>.A.S.03954 REV. 2 P.180 AVANTI II Additional installation of Collins BCU-4000 and<br />
CMU-4000 to flightinspection system.<br />
10028394 MOTORFLUG BADEN-BADEN GmbH PIAGGIO P.180 AVANTI II Installation of TCAS top & bottom antennas.<br />
Installation of TCASprocessor in nose section.<br />
Interface to existing transponder and<br />
avionicsystem.<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>01</strong>.03.2005<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.10.2<strong>01</strong>2<br />
None Prior to installation of this modification the <strong>04</strong>.<strong>01</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
10033883 MOTORFLUG BADEN-BADEN GmbH 407 Installation of Antenna Mount on Tailboom none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.02.2<strong>01</strong>1<br />
100366<strong>04</strong> MOTORFLUG BADEN-BADEN GmbH REV. 1 228-212 Installation of Mission Equipment for Maritime<br />
Surveillance.<br />
10<strong>04</strong>1143 MOTORFLUG BADEN-BADEN GmbH 2<strong>04</strong>B Exchange of engine torque and temperature<br />
indicator.<br />
10<strong>01</strong>6537 MPM INC. <strong>EASA</strong>.IM.A.S.02914 FAA STC SA<strong>01</strong>033WI Replacement of original main landing gear 1. The attached AML is applicable only on<br />
doors with one piece monolithic machined gear aircraft serial numbers called out in MPM Inc<br />
doors.<br />
Drawing No AML-LG-DR002-1, -2, -3 and -4for<br />
installation and applicability.2. Prior to<br />
installation of this modification the installer must<br />
determine that the int<br />
10<strong>01</strong>6538 MPM INC. <strong>EASA</strong>.IM.A.S.02915 FAA STC SA00902WI Replacement of original main landing gear<br />
doors with monolithic machined gear doors.<br />
None. This installation is only applicable to<br />
Dornier 228-212 with flight deckupgrade<br />
according to RUAG CN-228-247.The<br />
following RUAG Changes/Options must<br />
have been already installed:- Mechanical<br />
mounting provisions for SLAR Antenna<br />
according,CN-228-214m. - Mech<br />
11.10.2<strong>01</strong>1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.08.2<strong>01</strong>2<br />
1. The attached AML is applicable only on<br />
aircraft serial numbers called out in MPM Inc<br />
Drawing No. AML-LG-DR0<strong>01</strong>1. The attached<br />
AML is applicable only on aircraft serial<br />
numbers called out in MPM Inc Drawing No.<br />
AML-LG-DR0<strong>01</strong>.2. Prior to installation<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 336/<strong>462</strong><br />
05.06.2008<br />
10.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4<strong>04</strong>5 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>126 REV 1 REVO LAKE 250 Installation of propeller- MTV-9-B/LD193-109<br />
or- MTV-9-B-C-R(M)/CRLD193-109<br />
02.12.2005<br />
10<strong>01</strong>4<strong>04</strong>6 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>128 REV. 1 CESSNA 208, 208B 1. Installation of the MTV-16-1-E-C-F- None Prior to installation of this modification it 12.<strong>04</strong>.2<strong>01</strong>1<br />
R(P)/CFR250-55 full feathering andreversible 4-<br />
must be determined thatthe<br />
blade constant speed propeller2. Extension of<br />
interrelationship between this modification<br />
Installation 1 on MTV-16-1-E-C-F-<br />
and any other previouslyinstalled<br />
R(P)/CFR250-55propellers equipped with fluid<br />
modification and/ or repair will introduce<br />
deice system.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4100 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>202 SOCATA TB 21 Installation of MTV-9-B/198-52 hydraulically<br />
controlled 3-blade constant speed propeller<br />
<strong>01</strong>.08.2005<br />
10<strong>01</strong>4107 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>212 MOONEY M20M Installation of propeller MTV-14-B/185-59b 02.11.2005<br />
10<strong>01</strong>4194 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>336 PITTS S-2C S-2B Installation of propeller MTV-9-B-C/C203-46 16.08.2006<br />
10<strong>01</strong>4203 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>354 AVIATION AIRCRAFT A-1<br />
AVIATION AIRCRAFT A-1A<br />
AVIATION AIRCRAFT A-1B<br />
Installation of propeller MTV-14-B/183-<br />
3<strong>01</strong>aTake-off- and max. Continuous-power:<br />
126 kw by 2500 min<br />
10<strong>01</strong>4238 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>402 REV. 2 1. DV20 & 2. DA20-A1 Extension of <strong>EASA</strong> STC<br />
<strong>EASA</strong>.A.S.<strong>01</strong>402Installation of the 2-blade<br />
MTV-21-A/170-05<br />
10<strong>01</strong>4239 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>403 CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA F182-Q<br />
Installation of propeller MTV-9-D/203-52 This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>.11.2005<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.11.2<strong>01</strong>0<br />
10<strong>01</strong>4240 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>4<strong>04</strong> DIAMOND DA-20-C1 Installation of Propeller MT 175 R 150-2Ca 14.03.2006<br />
10<strong>01</strong>4241 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.<strong>01</strong>406 1. CESSNA 182<br />
CESSNA 182A<br />
CESSNA 182B<br />
CESSNA 182C<br />
CESSNA 182D<br />
CESSNA 182E<br />
CESSNA 182F<br />
CESSNA 182G<br />
CESSNA 182H<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA F182-P<br />
Installation of propeller MTV-9D/203-52 08.06.2006<br />
10<strong>01</strong>4432 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02480 PIPER PA-42-1000 Installation of propeller MTV-27-1-E-C-F-<br />
R(G)/CFRL250-103 (right),MTV-27-1-E-C-F-<br />
R(G)/CFR250-103 (left)<br />
-- 20.12.2006<br />
10<strong>01</strong>4441 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02491 CIRRUS SR22 Installation of 3-blade MTV-9-D/198-52<br />
constant speed Propeller<br />
10<strong>01</strong>4445 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02498 VULCANAIR P68<br />
VULCANAIR P68 B<br />
VULCANAIR P68 C<br />
VULCANAIR P68 C-TC<br />
VULCANAIR P68 OBSERVER<br />
VULCANAIR P68 OBSERVER 2<br />
VULCANAIR P68TC OBSERVER<br />
10<strong>01</strong>4491 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02553 PIPER PA-34-200T<br />
PIPER PA-34-220T<br />
P.68 "Victor", P.68B "Victor", P.68C, P.68<br />
"Observer", P.68 "Observer 2":Installation of<br />
propeller MTV-12-B-C-F/CF183-59bP.68C-TC,<br />
P.68TC "Observer":Installation of propeller<br />
MTV-12-B-C-F/CF188-53<br />
Installation of Propeller MTV-12-D-C-<br />
F/CF(L)/188-53<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
18.11.2005<br />
10.07.2006<br />
-- 07.11.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 337/<strong>462</strong><br />
13.03.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4492 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02554 BEECH 60<br />
Installation of 4-blade MTV-14-B-C-F/CF188- Applicable toDuke 60 and A60 S/N P-3 thru P-<br />
10.07.2006<br />
BEECH A60<br />
53a full fathering constant speed Propellers 597 with Lycoming TIO-541-E1C4 engineDuke<br />
BEECH B60<br />
B60 S/N P-247 and upDuke B60 S/N P-247<br />
thru P-597 with LBA STC 0662/2<strong>04</strong>0 and<br />
0666/2<strong>04</strong>0all equipped with “System<br />
Gomolzig” Silencer B60-606500<br />
10<strong>01</strong>4493 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02555 DIAMOND H-36 DIMONA Installation of 2-blade MTV-1-A/L 160-03<br />
constant speed propeller<br />
For all serial numbers. 12.12.2006<br />
10<strong>01</strong><strong>462</strong>1 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.02755 REV 3 DORNIER DO 228-100<br />
- Installation of 5-blade MTV-27-1-E-C-F- Prior to installation of this modification the<br />
<strong>04</strong>.02.2009<br />
DORNIER DO 228-1<strong>01</strong><br />
R(G) / CFRL250-55b Full Feathering and installer must determine that the<br />
DORNIER DO 228-200<br />
Reversing Propellers.Revision 1: Extension of interrelationship between this modification and<br />
DORNIER DO 228-2<strong>01</strong><br />
STC <strong>EASA</strong>.A.S.02755 to airplane model Do any other previously installed modification will<br />
DORNIER DO 228-202<br />
228-212.Revision 2 and 3 issued to correct introduce no adverse effect upon the<br />
DORNIER DO 228-202K<br />
DORNIER DO 228-212<br />
some typos.<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4837 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03054 MOONEY M20E<br />
Installation of propeller MTV-12-B/180-59b. This STC is approved only for the product<br />
06.03.2007<br />
MOONEY M20F<br />
configuration as defined in the approved design<br />
MOONEY M20J<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4886 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03114 CESSNA 421 Installation of 4-blade MT-Propeller Model MTV- Compliance has also been shown for all<br />
16-1-E-C- F/CF225-37a propellers on Cessna combinations (and/or) of following FAA STCs:<br />
421 C.<br />
SA438NW, SA5193NM, SA8352SW,<br />
SA00<strong>01</strong>5SE, SA5811SW<br />
10<strong>01</strong>4953 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03217 PILATUS PC-12 5-blade MTV-27-1-N-C-F-R(P)/CFR260-65a<br />
Propeller on Pilatus PC-12.<br />
10<strong>01</strong>4993 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03290 CESSNA 340<br />
CESSNA 340A<br />
10<strong>01</strong>5073 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03403 AVIAT HUSKY A-1A<br />
AVIAT HUSKY A-1B<br />
¿ Installation Instruction Document E-1530¿<br />
MT-Propeller AFM-S Doc. No E-1529, Original<br />
issue from 09. July 2007, or later <strong>EASA</strong><br />
approved Revision¿ MT-Propeller<br />
Instructions for ContAW. Doc. No. E-1360,<br />
Original issue from 09. July 2007, or later a<br />
Installation of Constant Speed 2 Blade<br />
propeller MTV-15-B/210-58.This STC is based<br />
on LBA STC SA 1314, issued 19.03.2003.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
18.12.2007<br />
16.03.2009<br />
1. FAA STC SA09574SC must be installed 06.09.2007<br />
10<strong>01</strong>5130 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03481 PAC 750XL Installation Propeller MTV-16-1-E-C-F-<br />
R(P)(CFR250-55a on PAC 750XL)<br />
22.07.2008<br />
10<strong>01</strong>5203 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03603 M7 AEROSPACE SA26-AT Installation of 5-blade MT-Propeller Model MTV- Prior to installation of this modification the<br />
02.10.2008<br />
27-1-E-C-F-R(G)/CFR210-58a propellers. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>52<strong>04</strong> MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.036<strong>04</strong> PIPER PA-42<br />
Installation of 4-blade MT-Propeller Model MTV- Prior to installation of this modification the<br />
02.10.2008<br />
PIPER PA-42-720<br />
16-1-E-C-F-R(P)/CFR230-37b propellers. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5216 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.03631 REV. 3 1. SA227-AT<br />
Installation of 5-blade MT-Propellers<br />
Model SA227-TT and SA226-T(B) limited to Prior to installation of this modification it 09.12.2<strong>01</strong>1<br />
1. SA227-TT, SA226-T(B) ModelMTV-27-1-E-C-F-R(G)/CFRL250-103 "Normal Category" with MTOW12500 must be determined thatthe<br />
2. SA227-AC, SA227-BC<br />
lbsAccording limitation section of AFM-S interrelationship between this modification<br />
3. SA227-CC, SA227-DC<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
10026785 MT-PROPELLER ENTWICKLUNG GmbH P-<strong>EASA</strong>.A.S.03902 95-C55, D55, E55, 58, G58 Installation of 4-blade MTV-14-D-C-F-/CF 188-<br />
30g propellers on HawkerBeechcraft Model 95-<br />
C55, D55, E55, 58, G58.<br />
19.12.2007<br />
None. Prior to installation of this modification the 10.08.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 338/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027008 MT-PROPELLER ENTWICKLUNG GmbH P-<strong>EASA</strong>.A.S.02941 PA-46-310P (MALIBU)<br />
Installation of 4 blade MTV-16-1-E-C-F- Prerequisite for the installation of this STC is None. 28.08.2009<br />
PA-46-350P (MALIBU MIRAGE) R(P)/CFR206-58a on airplanePA-46-310P and the installation of aPratt & Whitney PT6A-21, -<br />
PA-46-350P modified with Pratt & Whitney<br />
PT6A-21, -34 or-35 engine per FAA STC<br />
ST00541SE.<br />
34 or -35 engine per FAA STC ST00541SE.<br />
10027439 MT-PROPELLER ENTWICKLUNG GmbH P-<strong>EASA</strong>.A.S.03889 BAE JETSTREAM 3100, 3200 Installation of 5-blade MTV-27-1-E-C-F- None The installation of this modification by 30.09.2009<br />
R(G)/CFRL250-103() propellers<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe interr<br />
10028096 MT-PROPELLER ENTWICKLUNG GmbH P-<strong>EASA</strong>.A.S.039<strong>01</strong> MX-7-180 B, MX-7-180 C, Installation of a 2-blade MTV-15-B/203-58 None None <strong>01</strong>.12.2009<br />
MX-7-180, MX-7-180 A,<br />
propeller on Maule M-4 ModelsMX-7-180, MX-<br />
MXT-7-180, MXT-7-180A 7-180A, MX-7-180B, MX-7-180C, MXT-7-180,<br />
and MX-7-180A<br />
10029676 MT-PROPELLER ENTWICKLUNG GmbH 206H, T206H Installation of 5-blade MTV-5-1-D-C-F- Prior to installation of this STC modification None 12.<strong>04</strong>.2<strong>01</strong>0<br />
R(A)/CFR210-56 propeller on CessnaModel i.a.w. <strong>EASA</strong> STC 10027209(Soloy Mark II<br />
206H, T206H equipped with Rolls-Royce 250-<br />
B17F/2 series engine perFAA STC No.<br />
SA<strong>01</strong>878SE<br />
Turbine Conversion) is required<br />
10030966 MT-PROPELLER ENTWICKLUNG GmbH <strong>EASA</strong>.A.S.00749 REV. 1 CESSNA U 206G, TU 206G Installation of Propeller MTV-5-1-E-C-F- 1. This STC is applicable to Cessna U 206G, None 19.07.2<strong>01</strong>0<br />
R(M)/CFR220-54 orMTV-5-1-E-C-F/CF220-54 TU 206G both equipped withR/R Allison 250-<br />
C20S (Soloy Turbine PAC) in accordance with<br />
LBA EMZ(STC) 0082/673a only. 2.This STC is<br />
approved only for the product configuration as<br />
defined inthe approved design data r<br />
10031167 MT-PROPELLER ENTWICKLUNG GmbH PC-6/B1-H2, PC-6/B2-H2<br />
PC-6/B2-H4<br />
Installation of 4-blade MTV-16-1-E-C-F-<br />
R(P)/CFR240-55() propeller onPilatus PC-6/B1-<br />
H2, PC-6/B2-H2, PC-6/B2-H4<br />
10032680 MT-PROPELLER ENTWICKLUNG GmbH REV. 1 PA-31P Installation of two 4-blade MTV-16-1-E-C-<br />
F/CFL225-37a propellers onPiper PA-<br />
31PChange of Certification Basis.<br />
10033038 MT-PROPELLER ENTWICKLUNG GmbH TBM 700 A, TBM 700 B,<br />
TBM 700 C1, TBM 700 C2,<br />
TBM 700 N<br />
10034434 MT-PROPELLER ENTWICKLUNG GmbH LBA STC (EMZ)<br />
SA0786 ISSUE 3<br />
10034435 MT-PROPELLER ENTWICKLUNG GmbH LBA STC (EMZ)<br />
SA0626 ISSUE 4<br />
Installation of 5-blade MTV-27-1-E-C-F-<br />
R(P)/CFR225-55f propeller<br />
REV. 2 PA-46-310P 1) Installation of MTV-14-D/190-17 on PA-46-<br />
310P2) Installation of MTV-14-D/195-30a on<br />
PA-46-310P3) Installation of MTV-14-D/195-<br />
30a on PA-46-310P equipped with TCMTSIO-<br />
550-C i.a.w. FAA STC SA00380AT4)<br />
Installation of MTV-14-D/195-30b on PA-46-<br />
310P5) Insta<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.07.2<strong>01</strong>0<br />
According limitation section of AFM-S and<br />
POH-S.<br />
Prior to installation of this modification it 10.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
according limitation section of AFM-S Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
15.12.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.05.2<strong>01</strong>1<br />
REV. 1 PA-46-350P, PA-46R-350T 1) Installation of MTV-14-B/190-172)<br />
None Prior to installation of this modification it 07.<strong>04</strong>.2<strong>01</strong>1<br />
Installation of MTV-14-B/195-30a3) Installation<br />
must be determined thatthe<br />
of MTV-14-B/195-30b For installation 3 optional<br />
interrelationship between this modification<br />
reduction of take-off propeller speed to2400<br />
and any other previouslyinstalled<br />
rpm is included<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 339/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036196 MT-PROPELLER ENTWICKLUNG GmbH 200,200C,200CT,200T,A200 (12A) Installation of 5 blade MTV-27-1-E-C-F- none Prior to installation of this modification it 19.08.2<strong>01</strong>1<br />
A200 (C-12C),A200CT (C-12D) R(P)/CFR225-55f propellers<br />
must be determined thatthe<br />
A200CT (C-12F),A200CT (RC-<br />
interrelationship between this modification<br />
12D)<br />
and any other previouslyinstalled<br />
A200CT (FWC-12D)<br />
modification and/ or repair will introduce<br />
A200CT (RC-12G)<br />
no adverse effectupon the airworthiness<br />
A200CT (RC-12H),B200,B200C<br />
B200CGT,B200CT,B200GT,B200<br />
T<br />
of the product.<br />
10038174 MT-PROPELLER ENTWICKLUNG GmbH REV. 1 PA-31T, PA-31T1, PA-31T2 Installation of 5-blade MTV-27-1-E-C-F-<br />
PA-31T*, PA-31T1*, PA-31T2*<br />
-135A ENGINES PER FAA STC<br />
(*)MODIFIED WITH PT6A-135 OR<br />
SA00863SE<br />
R(P)/CFR210-58d propellers<br />
10038512 MT-PROPELLER ENTWICKLUNG GmbH REV. 1 CESSNA 425 Installation of 5-blade MTV-27-1-E-C-F-<br />
R(P)/CFR210-58d propellers.Cessna 425<br />
aircraft and models modified by <strong>EASA</strong> STC<br />
<strong>EASA</strong>.IM.A.02944 (FAASA5786SW) to install<br />
PT6A-135 (A) engine(s).<br />
10038566 MT-PROPELLER ENTWICKLUNG GmbH REV. 1 SR22, SR22T Installation of 4-blade MTV-14-D/195-30b<br />
propellers.<br />
10038720 MT-PROPELLER ENTWICKLUNG GmbH REV. 1 LBA STC SA 1063 P210N, P210R<br />
T210M, T210N, T210R<br />
This <strong>EASA</strong> STC is a revision of LBA SSTC<br />
(EMZ) SA1063, dated 21.09.1999.Installation<br />
of Propeller MTV-14-D/195-30b is included in<br />
the scope ofthe STC in addition to the already<br />
approved -30a blades.<br />
10039107 MT-PROPELLER ENTWICKLUNG GmbH TAIFUN 17 E & E II Installation of a 2-blade MTV-1-A/L165-06<br />
propeller on powered sailpnaeTaifun 17 E and<br />
Taifun E II with Limbach L2400 EB1.AB or<br />
L2400 EF1/DF1engine<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.02.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.03.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.03.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.03.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.<strong>04</strong>.2<strong>01</strong>2<br />
10039667 MT-PROPELLER ENTWICKLUNG GmbH CESSNA 208, 208B Installation of 5-blade MT-Propeller ModelMTV- According limitation section of AFM-S Prior to installation of this modification it 16.05.2<strong>01</strong>2<br />
27-1-E-C-F-R(P)/CFR245-55a<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
10<strong>04</strong>2832 MT-PROPELLER ENTWICKLUNG GmbH M-6-235, M-7-235, M-7-235B<br />
MX-7-235, MT-7-235<br />
Installation of 3-blade MT-Propeller Model MTV- according limitation section of AFM-S Prior to installation of this modification it 20.12.2<strong>01</strong>2<br />
9-B/198-52<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
10<strong>04</strong>2833 MT-PROPELLER ENTWICKLUNG GmbH M20R, M20S Installation of 4-blade MT-Propeller Model MTV- according limitation section of AFM-S Prior to installation of this modification it 20.12.2<strong>01</strong>2<br />
14-D/188-30b<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 340/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2834 MT-PROPELLER ENTWICKLUNG GmbH LC41-550FG Installation of 4-blade MT-Propeller Model MTV-<br />
14-D/195-30b<br />
20.12.2<strong>01</strong>2<br />
10<strong>01</strong>5760 NASCO AIRCRAFT BRAKE, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>796 FAA STC ST<strong>01</strong>833LA BOEING 737-200<br />
Installation of brake components listed on Limited to installation on BOEING 737-200,<br />
31.05.2006<br />
BOEING 737-200C<br />
Nasco Aircraft Brake, Inc drawing 7371<strong>01</strong>, 200C, -300, -400, -500For use only in Goodrich<br />
BOEING 737-300<br />
Revision , dated August 11, 2005 for use in brake assemblies 2-1474-3, -4, -5 and -<br />
BOEING 737-400<br />
Goodrich brake assemblies 2-1474-3, -4, -5 7Continued Airworthiness Requirements<br />
BOEING 737-500<br />
and -7 in accordance with Nasco Configuration included in the Goodrich Brake Overhaul<br />
Control Dawing NCC007, Revision B, dat Manual 32-40-30Compatibility of this design<br />
chang<br />
10<strong>01</strong>6628 NASCO AIRCRAFT BRAKE, INC. <strong>EASA</strong>.IM.A.S.03063 FAA STC ST02159LA BOEING 767-200 SERIES STC Validation - FAA STC ST02159LA Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
13.11.2008<br />
10029105 NASCO AIRCRAFT BRAKE, INC. FAA STC ST02664LA 747-100 SERIES,<br />
Installation and Replacement of Steel Brake None None 05.03.2<strong>01</strong>0<br />
747-200B SERIES,<br />
Components in accordancewith NASCO's<br />
747-200C SERIES,<br />
Configuration Control Drawing, Report Number<br />
747-200F SERIES,<br />
NCC 009,Revision A, dated December 2,<br />
747-300 SERIES<br />
2009, or later FAA approved revision.<br />
10033397 NASCO AIRCRAFT BRAKE, INC. FAA STC ST02321LA DC-9-81 (MD-81)<br />
DC-9-82 (MD-82)<br />
DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
MD-88<br />
10<strong>01</strong>5748 NATIONAL AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>781 FAA STC ST<strong>01</strong>883CH AIRBUS A300 MODEL B2-1A<br />
AIRBUS A300 MODEL B2-1C<br />
AIRBUS A300 MODEL B2-203<br />
AIRBUS A300 MODEL B2K-3C<br />
AIRBUS A300 MODEL B4-103<br />
AIRBUS A300 MODEL B4-2C<br />
AIRBUS A310<br />
AIRBUS A310-222<br />
AIRBUS A310-3<strong>04</strong><br />
B4-603 B4-620 B4-605R B4-622R<br />
F4-605R F4-622R C4-605 VAR.F<br />
10036680 NAYAK AIRCRAFT SERVICE GMBH PA-46-310P, -350P, -500TP,<br />
PA-46R-350T<br />
FAA STC No. ST02321LA Validation<br />
"Installation and replacement of<br />
brakeComponents"<br />
<strong>EASA</strong> validation of FAA STC<br />
#ST<strong>01</strong>883CHReinforced Flightdeck Door and<br />
Venting SystemInstallation of reinforced<br />
flightdeck door and venting system defined in<br />
Drawing List FDS-DL16, Revision M, dated<br />
August 26, 2003, or later FAA approved<br />
revisions, in accorda<br />
Installation of Tactical Weather Detection<br />
System (Stormscope) AvidyneTWX670.<br />
Refer to FAA STC ST02321LA Refer to FAA STC ST02321LAPrior to<br />
installation of this modification it must be<br />
determined theinterrelationship between<br />
this modification and any other<br />
previouslyinstalled modification and/or<br />
repair will introduce no adverse<br />
effectupon the airworthiness of<br />
1. This flightdeck door modification has not<br />
been shown to provide smoke penetration and<br />
evacuation protection as required by 14 CFR<br />
25.831. An <strong>EASA</strong> approved smoke<br />
barrier/curtain, installed behind the flightdeck<br />
bulkhead and in front of the cargo compartm<br />
18.<strong>01</strong>.2<strong>01</strong>1<br />
10.<strong>04</strong>.2006<br />
None. This STC is also applicable to Turbine<br />
Converted Aircraft (PA46-310-DLX,PA46-<br />
350DLX) according to FAA STC<br />
ST00541SE.The aircraft must have been<br />
already equipped with a<br />
suitableMultifunction Display (MFD).Prior<br />
to installation of this modification it must b<br />
28.09.2<strong>01</strong>1<br />
10036936 NAYAK AIRCRAFT SERVICE GMBH F27 MARK 050 Cabin divider for installation in Fokker 50. None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
18.10.2<strong>01</strong>1<br />
10038427 NAYAK AIRCRAFT SERVICE GMBH PA-46-310P, PA-46-350P,<br />
PA-46-500TP, PA-46R350T<br />
10<strong>01</strong>4090 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4426 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
<strong>EASA</strong>.A.S.<strong>01</strong>187 FAIRCHILD SWEARINGEN SA<br />
226 SE<br />
FAIRCHILD SWEARINGEN SA<br />
227 SE<br />
Installation of HID Xenon LDG/TAXI and LED<br />
NAV Light according NAYAKPA46-NY-09199<br />
Installation of Thommen Air Data Display and<br />
Altimeter.<br />
<strong>EASA</strong>.A.S.02471 CESSNA 441 SERIES Installation of Dual Mode S Transponder GTX<br />
330D<br />
as referred in AFM-S Must be maintained iaw. Original Piper<br />
MM and in addition iaw.Maintenance<br />
Instructions given in the above mentioned<br />
RepairInstructions or later approved<br />
revisions.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
15.02.2<strong>01</strong>2<br />
07.<strong>04</strong>.2005<br />
1. Limitation according AFM-S C441-NY-<strong>01</strong>24-<br />
082. Compatibility of this modification with<br />
other previously approved modifications must<br />
be determined by the installer<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 341/<strong>462</strong><br />
15.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4439 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02489 REV. 1 BAE 125 -800<br />
Installation of wing mounted Xenon<br />
This STC is approved only for the product<br />
05.09.2006<br />
CO. K<br />
BAE 125 SERIES 800A<br />
Taxi/Landing Light and/or Radom mounted configuration as defined in the approved design<br />
BAE 125 SERIES 800B<br />
Taxi Light<br />
data referred to in the paragraph "Description".<br />
HAWKER 800<br />
Compatibility with other aircraft/engine<br />
HAWKER 800 XP<br />
configurations shall be determined by the<br />
HAWKER 850 XP<br />
installer.<br />
10<strong>01</strong>4440 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02490 BAE 125 -800<br />
Installation of Iridium Satcom C1000 <strong>01</strong>.06.2006<br />
CO. K<br />
HAWKER 800<br />
HAWKER 800 XP<br />
10<strong>01</strong>4527 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02612 BOMBARDIER CL-600-2B19 Installation of RAAS compatible EPGWS Certification Basis of the Change: CS 25 Amdt<br />
28.02.2007<br />
CO. K<br />
BOMBARDIER CL-600-2C10 Computer in CL-600-2B19/-2C10/-2D24 Series 2<br />
BOMBARDIER CL-600-2D24 Aircraft<br />
10<strong>01</strong>4528 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02613 Activation of RAAS function of EGPWS As listed in the AFM 23.02.2007<br />
CO. K<br />
computer in AVRO RJ85/100 Series Aircraft<br />
10<strong>01</strong>4537 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02624 Installation of RAAS compatible EGPWS As listed in the AFM 23.02.2007<br />
CO. K<br />
Computer in ARO RJ85/100 Series Aircraft<br />
10<strong>01</strong>4538 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02625 BOMBARDIER CL-600-2B19 Activation of RAAS function of EGPWS Certification Basis of the Change: CS 25 Amdt<br />
23.02.2007<br />
CO. K<br />
BOMBARDIER CL-600-2C10 Computer in CL-600-2B19/-2C10/-2D24 Series 2, additionally CRI F-<strong>01</strong> at Issue 2<br />
BOMBARDIER CL-600-2D24 Aircraft<br />
"HONEYWELL RAAS Airworthiness Approval"<br />
10<strong>01</strong>46<strong>04</strong> NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4612 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4676 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4753 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>48<strong>04</strong> NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4881 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4971 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>5256 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>5257 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10028781 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
<strong>EASA</strong>.A.S.02727 DC-3C-S1C3G Installation of emergency exit signs and floor 1. The system must be maintained in<br />
05.02.2007<br />
escape path markings at DC3C series accordance with Maintenance Procedures DC3aircraftInstallation<br />
of emergency exit signs light NY-0532-07 Rev. 0 dated 20 Nov 2006 or later<br />
with power source and installation of<br />
approved revision.2. The system must be<br />
fluorescent floor path markings<br />
operated in accordance with AFM supplement<br />
DC3-NY-0532-08 Rev. 0 dated 20 Nov 2006<br />
or later<br />
<strong>EASA</strong>.A.S.02739 BEECH 1900<br />
BEECH 200<br />
BEECH 300<br />
Installation of HID Nose Gear Lights -- 12.02.2007<br />
<strong>EASA</strong>.A.S.02837 BOEING 737-300 Installation of Galley G2 Varig p/n 25-30-3154<br />
inside aircraft between STA 333.25 and STA<br />
350.50<br />
Elect to comply CS-25 ARNDT. 2 <strong>01</strong>.02.2007<br />
<strong>EASA</strong>.A.S.02939 DC-9-80 (MD-80) SERIES Installation of flight ID capable XPDR and<br />
CTRL<br />
13.<strong>04</strong>.2007<br />
<strong>EASA</strong>.A.S.03007 CESSNA 425 Installation of GTX 330D Mode S Transponder 20.03.2007<br />
<strong>EASA</strong>.A.S.03109 MITSUBISHI MU-2B-40<br />
MITSUBISHI MU-2B-60<br />
<strong>EASA</strong>.A.S.03251 FAIRCHILD SWEARINGEN SA<br />
226<br />
FAIRCHILD SWEARINGEN SA<br />
227<br />
<strong>EASA</strong>.A.S.03709 FAIRCHILD SWEARINGEN SA<br />
226-T(<br />
<strong>EASA</strong>.A.S.03710 PIPER PA-34-200<br />
PIPER PA-34-200T<br />
PIPER PA-34-220T<br />
Installation of XPDR Mode-S System with<br />
Diversity, Garmin GTX 330 D (single or<br />
optional dual installation possible)<br />
Installation of Honeywell MK IV EGPWS,<br />
together with MFD and Thommen Air Data<br />
Computer<br />
Installation of SLAR Surveillance System quick<br />
change roll<br />
Replacement of existing Garmin COM/NAV<br />
and existing Garmin GPS system by Garmin<br />
GNS 530w COM/NAV/GPS system.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. Limited to Serial Number T2942. With<br />
SLAR equipment installed, maximum cabin<br />
seating is 4 + 1. Operator Seat must not be<br />
occupied during take-off and landing3. Prior<br />
to installation of this modification the installer<br />
must determine that the int<br />
1. Limited to “Single GNS” – Installation<br />
only2. Prior to installation of this modification<br />
the installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse ef<br />
27.08.2007<br />
14.11.2007<br />
19.02.2009<br />
29.<strong>01</strong>.2009<br />
CESSNA 210 Post Installation Approval and conformity check Limited to S.N 57339 Prior to installation of this modification it 09.02.2<strong>01</strong>0<br />
of avionic system<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 342/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030066 NAYAK AIRCRAFT SERVICE GMBH &<br />
ATR 72-1<strong>01</strong>/-2<strong>01</strong>/-102/-202 Installation of single HF-9000 Communication This STC may only be embodied into ATR72- After application of CRI H-0<strong>01</strong> Issue <strong>01</strong>, 18.05.2<strong>01</strong>0<br />
CO. K<br />
ATR 72-211/-212/-212A<br />
Transceiver System inATR72's as per Nayak's 1<strong>01</strong>/102/2<strong>01</strong>/202/211/212/212Aaircraft additional specific EWIS ICAStasks to<br />
Master Document List ATR72-NY-02155 previously modified for the installation of ATR- those for the original aircraft configuration<br />
Revision 4 dated 18thMay 2<strong>01</strong>0 or later <strong>EASA</strong> GIE Mod 02028"Fuselage-Provide basic has been definedfor this Nayak STC and<br />
approved revisions<br />
provisions for HF antenna strap insulator" they are detailed on Nayak's<br />
andMod 03138 "Communications-HF system MaintenanceProcedures ATR72-NYinstallatio<br />
02155-07 Revision 2, dated 18th<br />
10031264 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10033154 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10033946 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10033970 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10034483 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10034925 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10037575 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
1. C90A,C90GT,C90GTI<br />
2. C90<br />
Installation of an Avidyne Traffic Advisory<br />
System TAS 600/610/620<br />
SA226-AT, SA226-T(B), SA226- Dual Installation of GNS 430 WAAS in<br />
TC<br />
SA226/227 Series<br />
SA227-AT<br />
SA227-TT, SA227-AC, SA227-DC<br />
SA26-T, SA26-AT, SA226-T,<br />
4<strong>01</strong>, 4<strong>01</strong>A, 4<strong>01</strong>B,<br />
402, 402A, 402B, 402C,<br />
411, 411A, 414, 414A,<br />
421, 421A, 421B, 421C, 425.<br />
REV. 2 4<strong>01</strong>, 4<strong>01</strong>A, 4<strong>01</strong>B,<br />
402, 402A, 402B, 402C,<br />
411, 411A, 414, 414A,<br />
421, 421A, 421B, 421C, 425<br />
Installation of a Traffic Advisory System<br />
Avidyne TAS610/620.<br />
Single installation of Garmin GNS 430<br />
(A)W/GNS 530 (A)W and optionalinstallation<br />
of Roll Steering Converter GDC31.<br />
560XL Installation of HID/LED LDG/REC/TAXI<br />
lightReplacement of existing conventional<br />
LDG/REC/TAXI lights by low powerHID/LED<br />
lights<br />
REV. 1 T303 Installation of1. Dual GPS/NAV/COMM Garmin<br />
GNS430/530(A)W2. E-HSI Sandel SN3308<br />
with Directional Gyro Century NSD360A3.<br />
Various other NAV/COMM related Avionic<br />
Components<br />
REV. 1 EMB-135BJ<br />
EMB-135ER, EMB-135LR<br />
EMB-145EP, EMB-145MP<br />
EMB-145ER, EMB-145LR<br />
EMB-145LU<br />
EMB-145MK, EMB-145EU<br />
Installation of HID Taxi/Landing light, inspection<br />
light on EMB-145aircraft.<br />
10<strong>01</strong>6258 NEW FLIGHT COOPERATION <strong>EASA</strong>.IM.A.S.02537 FAA STC SA4954NM CITATION 550-00<strong>01</strong> TO -0800 Gross Weight Increases based on Banson<br />
Aircraft Corp. STC.LBA STC Nr. 2<strong>04</strong>8, 05<br />
June1996;Spanish STC No. S325-I, 06 Febr.<br />
2003.<br />
10<strong>01</strong>5648 NEW SYSTEMS ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>622 FAA STC ST09384SC SAAB 340<br />
SAAB 340B<br />
Installation of a single Universal Avionics Flight<br />
Management System in SAAB SF340A and<br />
SAAB 340BFAA STC ST09384SC, Rev. 2<br />
none The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
None Installation of 3rd dissimilar and<br />
independent COM system required<br />
froIFR operation Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
06.08.2<strong>01</strong>0<br />
21.12.2<strong>01</strong>0<br />
None A compatible Multi Function Display<br />
(MFD) must have been alreadyinstalled.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair wi<br />
21.02.2<strong>01</strong>1<br />
None An independent COMM or NAV/DME or 14.03.2<strong>01</strong>1<br />
ADF/DME must have been<br />
alreadyinstalled. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair wi<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
07.<strong>04</strong>.2<strong>01</strong>1<br />
None This STC consists of three blocks (see<br />
title) which may be installedindependently<br />
from each other. The components of the<br />
third block (seeEquipment List) may also<br />
be installed independently. The third<br />
block of this STC includes the installation<br />
of:Honeywell<br />
16.05.2<strong>01</strong>1<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.12.2<strong>01</strong>1<br />
19.11.2007<br />
None 19.<strong>04</strong>.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 343/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039579 NEW SYSTEMS ENGINEERING REV. 1 FAA STC ST10977SC DHC-8-102/-103/-106<br />
Installation of Dual Universal Avionics Flight Installation is limited to serial numbers listed in Prior to installation of this modification it 21.05.2<strong>01</strong>2<br />
DHC-8-2<strong>01</strong>/-202<br />
Management Systems (FMS)with Global the latest approvedversion of FMS Instruction must be determined thatthe<br />
DHC-8-3<strong>01</strong>/-311/-314/-315 Positioning System (GPS)FAA STC<br />
Top Drawing 379-02-00<strong>01</strong>.<br />
interrelationship between this modification<br />
ST10977SC<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0905 NEXTANT AEROSPACE L.L.C. FAA STC ST03960AT 400A Installation of Rockwell Collins Venue In-Flight<br />
Entertainment (IFE),Aircell Axxess Cabin II<br />
Iridium Phone and High Speed Internet<br />
Systemwith Wireless Local Area Network<br />
(WLAN) Astronics 115V AC 60 Hz<br />
CabinInverter, and Emteq LED Cabin Lighting<br />
System.<br />
10<strong>04</strong>0906 NEXTANT AEROSPACE L.L.C. FAA STC ST03110CH 400A Installation of L3 Communications Digital Flight<br />
Data Recorder.<br />
10<strong>04</strong>2091 NEXTANT AEROSPACE L.L.C. FAA STC ST10959SC BEECHJET 400A Installation of Rockwell Collins Pro Line 21<br />
Electronic FlightInstrument System (EFIS) with<br />
Rockwell Collins FMS-6100,<br />
Localiserperformance with Vertical Guidance<br />
(LPV) approach capability andUniversal<br />
Systems Company (UASC) Terrain awareness<br />
warning Syste<br />
10<strong>04</strong>2353 NEXTANT AEROSPACE L.L.C. FAA STC ST02371LA 400A Installation of Williams International FJ44-3AP<br />
engines as replacementfor the original Pratt &<br />
Whitney Canada JT15D-5 units.<br />
10<strong>04</strong>0787 NORTH FLIGHT DATA SYSTEMS, L.L.C. FAA STC SR09468RC EC135 P1, EC135 P2,<br />
EC135 P2+, EC135 T1,<br />
EC135 T2, EC135 T2+<br />
10<strong>01</strong>6294 NORTHEAST ENGINEERING &<br />
DEVELOPMENT<br />
10<strong>01</strong>7039 NORTHEAST ENGINEERING &<br />
DEVELOPMENT<br />
This STC is intended to provide internet<br />
connection and E-Mail servicesto the aircraft<br />
cabin using portable electronic devices<br />
(PED's). Anyother intended function of this<br />
equipment will require a re-examinationof the<br />
certification basis.<br />
Prior to installation of this modification it 02.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.08.2<strong>01</strong>2<br />
None. For aircraft equipped with Williams FJ44- 07.11.2<strong>01</strong>2<br />
3AP Engines, those engines mustbe<br />
installed under FAA STA ST02371LA.<br />
Aircraft must have previously qualified for<br />
Operations in ReducedVertical Airspace<br />
via: - RK-1 through RK-117 and RK-119<br />
through RK-139, Hawker B<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.11.2<strong>01</strong>2<br />
Installation of the Outerlink Corporation CP-3 or none Use of Electronic Flight Bag (EFB) with<br />
CP-3i Automatic FlightFollowing System,<br />
optional N0<strong>04</strong>-4000 OCP shall bein<br />
Optional Electronic Flight Bag Provisions, and<br />
accordance with Advisory Circular AC<br />
FlightData System in accordance with North<br />
120-76A and may requireoperational<br />
Flight Data System, LLC MasterInstallation List,<br />
approval.Prior to installation of this<br />
Document N° NL<strong>462</strong>073006, Re<br />
modification it must be determined<br />
thatthe interrelationship between th<br />
<strong>EASA</strong>.IM.A.S.02591 TCCA LSTC NO. O-LSA05-321/D IS PILATUS PC-12/45 Installation of GNS 430 (COMM/NAV/GPS), This STC is limited to Pilatus PC-12/45, Serial<br />
GNS 530 (COM/NAV/GPS), KDR 510 (Data number 659Prior to the installation of this<br />
link Weather Receiver), KGS SS50 (Static modification the installer must determine that<br />
Inverter), XMRadio Receiver with XM Radio the interrelationship between this modification<br />
Display & Control Head (Cabin), and necessary and any over previously installed modifications<br />
antennas.<br />
will introduce no adv<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>463 TCCA STC SH97-59 ROBINSON R44<br />
Bear Paw Installation. Prior to installation of this modification the<br />
ROBINSON R44 II<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4817 NORTHERN AVIONICS S.R.L. <strong>EASA</strong>.A.S.03025 PIPER PA-31T Installation of Mode S Diversity XPDR<br />
Honeywell MST-67A (Elementary<br />
Surveillance).<br />
10<strong>01</strong>7108 NORTHERN AVIONICS S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>084 AGUSTA A-109 A<br />
AGUSTA A-109 AII<br />
AGUSTA A-109 C<br />
NAV 277 "Installation of an alternate static<br />
system on board to rotorcraft A 109 A/AII/C"<br />
10<strong>01</strong>7115 NORTHERN AVIONICS S.R.L. <strong>EASA</strong>.R.S.<strong>01</strong>097 AGUSTA AB-412EP Installation of an EGPWS Honeywell MK XXI. 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 344/<strong>462</strong><br />
26.07.2<strong>01</strong>2<br />
16.10.2007<br />
18.07.2008<br />
13.07.2007<br />
19.<strong>01</strong>.2006<br />
08.08.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027831 NORTHERN AVIONICS S.R.L. A109S NAV-396 "Installation of Helicopter Egress None. Prior to installation of this modification it 09.11.2009<br />
Light System (HEEL)"<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035325 NORTHERN AVIONICS S.R.L. REV. 1 AW109SP Installation of a Relay box and Control Panel<br />
for ICS VIP application.<br />
10035500 NORTHERN AVIONICS S.R.L. AB206B NAV 427 "Installation of Alternate Static This STC is applicable only to the helicopters<br />
System" - This kits consistsin the installation of S/Ns from 8590 to 8758.<br />
an additional line to the original static lineand a<br />
3-way valve/switch (with the air inlet port) to<br />
pick up the staticpressure in the cabin when the<br />
external ports<br />
10035741 NORTHERN AVIONICS S.R.L. REV. 1 AW109SP Installation of In-flight Entertainment System<br />
(IES) (composed by kitP/N KNAV-419 and<br />
KNAV-420) Certificate rev. 1 issued due to<br />
change of Modification BulletinRevision level.<br />
10036508 NORTHERN AVIONICS S.R.L. AW109SP NAV 434 "Installation of Helicopter Emergency<br />
Egress Light (HEEL)"<br />
10036765 NORTHERN AVIONICS S.R.L. P-<strong>EASA</strong>.R.S.<strong>01</strong>575 A109 AII Installation of a retractable swivelling landing<br />
light (searchlight).<br />
10039669 NORTHERN AVIONICS S.R.L. AW109SP Installation of In-flight Entertainment System<br />
(IES) (composed by KitPIN KNAV-419 and<br />
KNAV-442).<br />
10<strong>01</strong>5366 NORTHROP GRUMMAN GUIDANCE<br />
AND<br />
10<strong>01</strong>5825 NORTHROP GRUMMAN GUIDANCE<br />
AND<br />
<strong>EASA</strong>.IM.A.S.00759 REV 2 FAA STC ST<strong>01</strong>149LA AIRBUS A300 MODEL B2-203<br />
AIRBUS A300 MODEL B4-103<br />
AIRBUS A300 MODEL B4-203<br />
Installation of Litton Heading and Attitude<br />
System (LHAS) LTR-97.This STC is the result<br />
of the FAA STC No. ST<strong>01</strong>149LA validation.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>897 REV 1 FAA STC SA8027NM Replacement of old inertial navigation<br />
equipment with newer technology<br />
Required pre-modification: Agusta<br />
Prior to installation of this modification it 05.08.2<strong>01</strong>1<br />
electrical/mechanical provision nº109-B810-30- must be determined thatthe<br />
( )<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Must be installed in conjunction with Northern<br />
Avionics kit P/N KNAV-418<br />
Prior to installation of this modification it 27.06.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 21.10.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.09.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.10.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.05.2<strong>01</strong>2<br />
1. This STC is limited to the installation of three<br />
LHAS LTR-97 (triple configuration).2.The<br />
Airplane Flight Manual Supplement, Document<br />
No. 434593-<strong>EASA</strong> dated 25 May 2005 is<br />
required as part of this installation.3. This STC<br />
is approved only for the product<br />
Litton Airplane Flight Manual Supplement, Doc<br />
No 464427, N/C, FAA approved on August 8,<br />
1994, or later approved revisions, is required<br />
as part of this modificationThis STC is<br />
approved only for the Boeing 747-287 model<br />
airplanes, and it applies only when th<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 345/<strong>462</strong><br />
31.07.2006<br />
28.11.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5395 NORTHWEST AEROSPACE<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>096 BOEING 757-200 Installation of ELS/EHS S system Upgrade This STC is approved only for the product<br />
15.08.2005<br />
TECHNOLOGIES In<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10028415 NORTHWEST AEROSPACE<br />
P-<strong>EASA</strong>.A.S.03966 REV. 1 A320-232 Interior Reconfiguration and In Flight<br />
None Prior to installation of this modification it 05.08.2<strong>01</strong>0<br />
TECHNOLOGIES In<br />
Entertainment (IFE) Installationon Etihad<br />
must be determined thatthe<br />
Airways A320-232 Aircraft Revision of the<br />
interrelationship between this modification<br />
<strong>EASA</strong> 10028415 to remove EWIS limitation<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10029095 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10029975 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
1003<strong>04</strong>95 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10031457 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10032214 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10038268 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10038505 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03<strong>04</strong>3<br />
P-<br />
<strong>EASA</strong>.IM.A.S.03214<br />
FAA STC ST02052SE B777-200 First Class Cabin Upgrade - BA 777-200<br />
Aircraft<br />
Concurrent installation of <strong>EASA</strong> STC No.<br />
10029094 (<strong>EASA</strong> Project NoP-<br />
<strong>EASA</strong>.IM.A.S.02978) is required.Concurrent<br />
installation of <strong>EASA</strong> STC No.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>797 is required.This<br />
modification may not be installed after 30<br />
August 2<strong>01</strong>0 unless (1)previously approve<br />
FAA STC ST10594SE-T B747-400 First Class Cabin Upgrade BA 747-400 aircraft Concurrent installation of <strong>EASA</strong> STC<br />
10029964 is required.This modification may<br />
not be installed after 30 August 2<strong>01</strong>0 unless<br />
(1)previously approved electrical wiring<br />
interconnect system (EWIS)instructions for<br />
continued airworthiness (ICA) have been<br />
evaluate<br />
P-<strong>EASA</strong>.A.S.03958 A319-132 Interior Reconfiguration and In Flight<br />
Entertainment (IFE) Installationon Etihad<br />
Airways A319-132 Aircraft<br />
FAA STC ST02079SE B777-300 First and Business Class Cabin Interior - BA<br />
777-300 aircraft<br />
A320-232 Cabin Interior Reconfiguration and In Flight<br />
Entertainment (IFE)Modifications on Etihad<br />
Airways A320-232 Aircraft<br />
FAA STC NO. ST02412LA 777-200 First and Economy Class Cabin Interior - BA<br />
777-200 Aircraft<br />
Prior to installation of this modification it 03.03.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 07.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.06.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.08.2<strong>01</strong>0<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
18.10.2<strong>01</strong>0<br />
Concurrent installation of the following STCs<br />
are required for theinstallation of this STC:1)<br />
Flight Structures, Inc. <strong>EASA</strong> STC 10<strong>01</strong>5720,<br />
Business Class SeatInstallation.2) Thales<br />
Avionics, Inc. <strong>EASA</strong> STC No. 10038267<br />
(<strong>EASA</strong> Project No.0<strong>01</strong>0<strong>01</strong>1945), Passenger<br />
Prior to installation of this modification it 02.02.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC ST02195SE B747-400 Installation of a IMS RAVE In-flight<br />
Entertainment System into theeconomy class<br />
passenger seats of a Boeing 747-400 aircraft<br />
in accordancewith Northwest Aerospace<br />
Technologies Inc. Master Drawing ListN0374-<br />
D10, Rev. J dated December 27, 2<strong>01</strong>1 or later<br />
appro<br />
None. None. 22.02.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 346/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039202 NORTHWEST AEROSPACE<br />
REV. 1 B747-400 B747-400 Cabin re-configuration in accordance The use of the baby basinet is not permitted None 07.05.2<strong>01</strong>2<br />
TECHNOLOGIES In<br />
with Northwest AerospaceTechnologies Inc. unless a "Remove beforeTaxi, Take-off and<br />
Master Drawing List N0375-D10 Rev. A dated Landing" placard is installed either on the<br />
April 12,2<strong>01</strong>2<br />
babybassinet or on the surface on which the<br />
baby bassinet is mounted. Theuse of cabin<br />
crew procedures to show compliance with<br />
10<strong>04</strong>0082 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10<strong>04</strong>0295 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10<strong>04</strong>1628 NORTHWEST AEROSPACE<br />
TECHNOLOGIES In<br />
10<strong>01</strong>5367 NORTHWEST COMPOSITES <strong>EASA</strong>.IM.A.S.00763 FAA STC ST<strong>01</strong>565SE BOEING 737-300<br />
BOEING 737-400<br />
10<strong>01</strong>5740 NORTHWEST COMPOSITES <strong>EASA</strong>.IM.A.S.<strong>01</strong>764 FAA STC ST00867SE DC-9-82<br />
DC-9-83<br />
10<strong>01</strong>5741 NORTHWEST COMPOSITES <strong>EASA</strong>.IM.A.S.<strong>01</strong>765 FAA STC ST00868SE DC-9-82 (CF6)<br />
DC-9-83 (MD-83)<br />
10<strong>01</strong>7243 NSE INDUSTRIES S.A. <strong>EASA</strong>.R.S.<strong>01</strong>440 AS365N2, AS365N3<br />
SA365N, SA365N1<br />
B747-400 Interior Reconfiguration of VAA 747-400 A/C serial numbers: 30885, 32337, 32338,<br />
Aircraft: Cabin Configurationand Passenger<br />
Amenities Upgrade and Standardization in<br />
accordance withNAT Master Data List N0377-<br />
D10 Rev. B , dated May 22, 2<strong>01</strong>2<br />
32339, 32340, 28757 and 29406.<br />
B777-300ER N<strong>04</strong><strong>01</strong>: Certification of Deployment of In-Seat<br />
Video Monitors DuringTaxi, Take-Off and<br />
Landing - Business Class Seats on Cathay<br />
PacificB777-300(ER) Aircraft<br />
777-300ER N<strong>04</strong>19 Cabin Interior Modifications on Jet<br />
Airways Boeing 777-300ERAircraft<br />
Maintenance Manual Supplement, 12.06.2<strong>01</strong>2<br />
Northwest Aerospace Doc. N0377-<br />
D71Revision -, 20 February, 2<strong>01</strong>2 or later<br />
approved revision is requiredwith this<br />
installation. The Instructions for Continued<br />
Airworthiness, Electrical<br />
WiringInterconnect System Instructions<br />
for<br />
Limited to 777-300ER as per EO 20N00968 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.06.2<strong>01</strong>2<br />
Stowage bin Extension. 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Stowage Bin ExtensionModification to 1. Aircraft listed on Master Drawing List<br />
overhead stowage bin located in the passenger A075000 rev. F dated 20th January or later<br />
cabin in order to extend the bins for aircraft approved revision.2. This approval of this<br />
originally equipped with Heath-Techna Interiors change in type design applies to the above<br />
stowage bins.<br />
model aircraft only.3. This approval should<br />
not be extended to other aircraf<br />
Stowage Bin ExtensionModification to 1. Aircraft listed on Master Drawing List<br />
overhead stowage bin located in the passenger A074000 rev. J dated 3rd November 2005 or<br />
cabin in order to extend the bins for aircraft later approved revision.This approval of this<br />
originally equipped with C&D Interiors stowage change in type design applies to the above<br />
bins.FAA STC ST00868SE issue on 21st June model aircraft only.This approval should not be<br />
20<strong>01</strong><br />
extended to other aircaft of thi<br />
Installation of BRITE SAVER 2 Usage<br />
Monitoring System This STC is a revision of<br />
<strong>EASA</strong>.R.S.<strong>01</strong>440 and covers software<br />
upgrade andapplicability modification.<br />
10036630 NSE INTEGRATIONS ATR 42-300 Modification in ATR42-300 MSN <strong>04</strong>9's<br />
calibration test bench<br />
10<strong>01</strong>5792 O&N AIRCRAFT MODIFICATIONS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>851 FAA STC SA615NE CESSNA 172F<br />
CESSNA 172G<br />
CESSNA 172H<br />
CESSNA 172I<br />
CESSNA 172L<br />
CESSNA 172M<br />
CESSNA 172N<br />
CESSNA 172P<br />
Installation of an 18 gallon fuel tank in the aft<br />
baggage compartment, and fuel transfer<br />
system.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.10.2<strong>01</strong>2<br />
17.06.2005<br />
28.03.2006<br />
16.02.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification will introduce no adverse<br />
effect upon theairworthiness of the<br />
product. The approval holder s<br />
21.12.2<strong>01</strong>2<br />
This STC is limited to ATR42-300 serial<br />
number aircraft MSN <strong>04</strong>9<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Prior to installation of this modification it 28.09.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 347/<strong>462</strong><br />
29.08.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5986 O&N AIRCRAFT MODIFICATIONS, INC. <strong>EASA</strong>.IM.A.S.02139 FAA STC SA1035NE CESSNA 150F<br />
Installation of a 14.6 gallon aft fuselage tank in 1. FAA Approved Supplement to Pilot’s<br />
13.10.2006<br />
CESSNA 150G<br />
baggage compartment.<br />
Operating Handbook and / or FAA Approved<br />
CESSNA 150H<br />
Airplane Flight Manual, Nr. 19, 20 and 21,<br />
CESSNA 150J<br />
dated Jan. 13-93, or later approved revision, is<br />
CESSNA 150K<br />
required Cessna 150F, G, H, J, K ,L & M and<br />
CESSNA 150L<br />
CESSNA 150M<br />
CESSNA 152<br />
152.2. This installation is not eligible<br />
10<strong>01</strong>5797 OFEK HOLDING CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>858 FAA STC SA<strong>01</strong>415CH PIPER PA-31T Installation of camera provisions in fuselage This STC is approved only for the product<br />
30.<strong>01</strong>.2006<br />
floor cut-out<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5798 OFEK HOLDING CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>859 FAA STC SA<strong>01</strong>961CH PIPER PA-31T Installation OFEK Holding Company camera<br />
provisions installed pursuant to STC<br />
SA<strong>01</strong>962CH<br />
30.<strong>01</strong>.2006<br />
10034682 OGMA, INDUSTRIA AERONAUTICA DE EMB-135BJ Change Number 1086.07 - "Installation of none Prior to installation of this modification it 19.<strong>04</strong>.2<strong>01</strong>1<br />
coffee maker & associated watertank"<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10037579 OGMA, INDUSTRIA AERONAUTICA DE EMB-145EP, EMB-145LR<br />
EMB-145LU<br />
10039843 OGMA, INDUSTRIA AERONAUTICA DE EMB-145EP<br />
EMB-145EU<br />
EMB-145LR<br />
EMB-145LU<br />
10<strong>04</strong>2497 OGMA, INDUSTRIA AERONAUTICA DE EMB-145EP,EMB-145LR,EMB-<br />
145LU<br />
Installation of a VIP meeting room on EMB-145 Aircraft S/N 145076, 145084, 145129, 145135, Prior to installation of this modification it 08.12.2<strong>01</strong>1<br />
and 145147.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Nespresso Coffe Maker InstallationDescription<br />
as per Change Dossier, ref. 11P05CD000<strong>01</strong><br />
initial issue, dated 23th May 2<strong>01</strong>2.<br />
VIP room extension and Iridium Satphone<br />
system installation on EMB-145<br />
10031182 OHS AVIATION SERVICES GmbH <strong>EASA</strong>.A.S.03940 328-100, 328-300 Change seat cushions bottom and backrest,<br />
JB6series and AMP 1300 series for DO 328-<br />
100 and -300<br />
10<strong>01</strong>5480 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.A.S.<strong>01</strong>238 FAA STC ST10395SC MD-11 <strong>EASA</strong> Validation of FAA STC ST10395SC on<br />
“Installation of two non-taxi, take-off and<br />
landing (TT7L) courier seats" and associated<br />
Airplane Flight Manual Supplement<br />
10<strong>01</strong>6706 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.0<strong>04</strong>57 REV. 1 FAA STC NO SR<strong>01</strong>424SE AS355 E, AS355 F, AS355 F1,<br />
AS355 F2, AS355 N, AS355 NP<br />
Applicability for the following S/N: 145076,<br />
145084, 145129, 145135,145147,<br />
145242, 145258.<br />
The change is applicable to the following<br />
aircraft having OGMA STC10037579<br />
incorporated, and that do not have flux valve<br />
sensors: A/C SN145076, 145084, 145129,<br />
145135, and 145147<br />
Prior to installation of this modification it 29.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 05.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
30.07.2<strong>01</strong>0<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
31.05.2005<br />
Cargo Hook Kit model 200-292-<strong>01</strong> None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.07.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 348/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6709 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.00553 REV. 1 FAA STC SR00699SE BELL 2<strong>04</strong>B<br />
To amemd <strong>EASA</strong> STC <strong>EASA</strong>.IM.R.S.00553 to Approval of this change in type design applies<br />
19.10.2005<br />
BELL 205A<br />
list the correct document number for the only to Bell 2<strong>04</strong>B, 205A, 205A-1, 212, 412 and<br />
BELL 205A-1<br />
Rotorcraft Flight Manual Supplement<br />
412EP rotorcraft which where prevsiously<br />
BELL 212<br />
(RFMS)Ass.:Section 4 of Onboard Systems equipped with an approved installation of the<br />
BELL 412<br />
Service Manual No. 122-0<strong>04</strong>-00.Rotorcraft following cargo hook: Bell P/N 2<strong>04</strong>-072-924-1<br />
BELL 412 EP<br />
Flight Manual Supplement No. 121-020-00<br />
dated 24 September<br />
or Breeze Eastern P/n SP7109-1,<br />
10<strong>01</strong>6711 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.00623 FAA STC SR<strong>01</strong>166SE EUROCOPTER FRANCE AS 350 Cargo Hook Kit installation, in accordance with 1. This STC is approved only for the product<br />
15.03.2005<br />
B3<br />
FAA STC No. SR1166SE issued January 22, configuration as defined in the approved design<br />
2003.<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6726 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>027 REV. 2 FAA STC SR00886SE AS350B, AS350BA, AS350B1 Installation of Cargo Hook Kit Model 200-261- The cargo hook kits approved under this STC Prior to installation of this modification it 13.<strong>01</strong>.2<strong>01</strong>0<br />
AS350B2, AS350B3, AS350D 00, 200-261-<strong>01</strong>, and200-353-00This STC is a can be installed on AS 350B, BA, B1, B2, and must be determined thatthe<br />
EC130B4<br />
revision to <strong>EASA</strong> STC <strong>EASA</strong>.IM.R.S.<strong>01</strong>027 D helicopters equipped with Eurocopter swing interrelationship between this modification<br />
Revision 1 throughthe validation of amendment or slingtype systems, or on AS350B3 equipped and any other previouslyinstalled<br />
dated 11 August, 2009 to FAA STC<br />
with Eurocopter sling type systemonly, or on modification and/ or repair will introduce<br />
SR00886SE.<br />
EC 130B4 equipped with Eurocopte<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6781 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>122 FAA STC SH1262NW EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS 350<br />
10<strong>01</strong>6789 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>136 FAA STC SH4908NM<br />
D1<br />
MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
10<strong>01</strong>68<strong>04</strong> ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>164 FAA STC SR<strong>01</strong>588SE EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
10<strong>01</strong>6806 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>166 FAA STC SR00369SE<br />
D<br />
BELL 206L<br />
BELL 206L-1<br />
BELL 206L-3<br />
BELL 206L-4<br />
BELL 407<br />
10<strong>01</strong>6807 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>167 FAA STC SR00892SE MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
10<strong>01</strong>6809 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>169 FAA STC SR00557SE ROBINSON R22<br />
ROBINSON R22 ALPHA<br />
ROBINSON R22 BETA<br />
ROBINSON R22 MARINER<br />
Electronic Model E-69 Cargo Hook Load Cell<br />
System p/n 200-295-00, in accordance with<br />
Onboard Systems Master Drawing List n° 155-<br />
<strong>01</strong>0-00, revision 10 dated 15/06/<strong>04</strong> approved<br />
by FAA, or later FAA approved revision.<br />
Installation of Model E-51 Cargo Hook Load<br />
Cell System PN 200-034-00. This STC is the<br />
validation of the FAA STC SH4908NM<br />
amended on05/11/1990 and limited to MDHI<br />
369 D and E models<br />
1 - The present STC is the validation of the<br />
FAA STC SH1262NW last amended on<br />
15/03/05, limited to Eurocopter AS 350 B, BA,<br />
B1, B2,and D models.2 – The system covered<br />
by this STC can be installed on AS 350<br />
helicopters equipped with Eurocopter sling<br />
systems<br />
1. This STC is to be installed on aircraft models<br />
specified in "applicability" section above,<br />
equipped with MDHI Cargo Hook Kit<br />
No.369H90072, using MDHI cargo hook<br />
manual release PN 14323-2 only.2. Installation,<br />
Inspection and Operation must be done in acc<br />
ONBOARD SYSTEMS fuel drain guard kit for Refer to FAA STC SR<strong>01</strong>588SE reissued<br />
Eurocopter AS 350 series helicopter.Validation September 29, 2005<br />
of FAA STC SR<strong>01</strong>588SE<br />
Cargo hook installation n. 200-215-00 Approval of this change in type design applies<br />
to only those Bell model rotorcraft listed above,<br />
which were previously equipped with an FAA<br />
approved installation of Bell cargo hook<br />
suspension systems 206-706-341-5, 206-706-<br />
341-1<strong>01</strong>; 206-706-341-109 and eith<br />
Installation of Onboard Systems Model 200- This cargo hook is not approved for human<br />
264-00 Cargo Hook kit.<strong>EASA</strong> validation of FAA external load.Approval of this installation<br />
STC n0 SR00892SE, amended January 13th, applies to the above listed model rotorcraft<br />
2003, or later approved revision.This STC is only, which were previously equipped with an<br />
classified 'Basic' by the FAA and is approved approved installation of McDonnell Douglas<br />
under the post type Validation Princip cargo hook suspension systems and car<br />
10.<strong>01</strong>.2007<br />
12.10.2005<br />
06.03.2006<br />
27.09.2006<br />
08.07.2008<br />
Cargo Hook Suspension System 02.<strong>01</strong>.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 349/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6811 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>171 REV. 1 FAA STC SR<strong>01</strong>064SE ROBINSON R44<br />
Cargo hook suspension system i.a.w. US STC This STC is approved only for the product<br />
29.<strong>04</strong>.2009<br />
ROBINSON R44 II<br />
SR0<strong>01</strong>064SE.Note: Revision 1 of this STC is configuration as defined in the approved design<br />
made for correction of FAA original STC data referred to in the paragraph "Description".<br />
reference. This supersedes previous issuance Compatibility with other aircraft/engine<br />
of the STC.<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6862 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>238 FAA STC SR<strong>01</strong>164SE EUROCOPTER FRANCE AS 350 Fabrication and Installation of Onboard 1. Approval of this change in Type Design<br />
26.07.2006<br />
B<br />
Systems Model 200-280-<strong>01</strong> Cargo Hook Swing applies only fo those Eurocopter AS350 model<br />
EUROCOPTER FRANCE AS 350 Suspension System<br />
rotorcraft listed above;2. This approval<br />
B1<br />
should not be extended to other rotorcraft of<br />
EUROCOPTER FRANCE AS 350<br />
these models on which other previously<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
approved modifications areincorporate<br />
10<strong>01</strong>6869 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>245 FAA STC SR00649SE BELL 206A<br />
Cargo Hook Suspension Kit for Bell 206A and None 21.12.2006<br />
BELL 206B<br />
206B<br />
10<strong>01</strong>6870 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>246 REV. 1 FAA STC SR<strong>01</strong>393SE AS350B, AS350BA, AS350B1 Onboard Systems cargo hook kits P/N 200-286-None<br />
This STC is approved only for the product <strong>04</strong>.02.2<strong>01</strong>1<br />
AS350B2, AS350B3, AS350D <strong>01</strong> (with cargo hook P/N528-023-<strong>01</strong>) and P/N<br />
configuration as defined inthe approved<br />
200-286-02 (with cargo hook P/N 528-029-<br />
design data referred to in the paragraphs<br />
00)Revision 1 - introduces cargo hook kit P/N<br />
"Title/Description" and "Associated<br />
200-286-02This STC is the validation of FAA<br />
Technical Documentation". Compatibility<br />
STC SR<strong>01</strong>393SE (issued on April 05,20<strong>04</strong><br />
with other aircraft/engine configurations<br />
shall bedeterm<br />
10<strong>01</strong>6874 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>250 FAA STC SR00920SE ROBINSON R22<br />
ROBINSON R22 ALPHA<br />
ROBINSON R22 BETA<br />
ROBINSON R22 MARINER<br />
Cargo Hook Suspension Kit i.a. with FAA STC<br />
SR00920SE<br />
10<strong>01</strong>6907 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>287 FAA STC SR00711SE SCHWEIZER 269 SERIES Validation of FAA STCSR00711SE , amended<br />
January 13, 2003, or later approved versions.<br />
10<strong>01</strong>6937 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>324 REV. 2 FAA STC SR<strong>01</strong>164SE AS 350 B, AS 350 B1<br />
AS 350 B2, AS 350 B3<br />
AS 350 BA, AS 350 D<br />
10<strong>01</strong>6990 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>396 REV. 1 FAA STC SR0<strong>04</strong>07SE MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
10<strong>01</strong>6993 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>402 FAA STC SR<strong>01</strong>795SE EUROCOPTER FRANCE EC 120<br />
B<br />
10<strong>01</strong>6999 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>409 FAA STC SR<strong>01</strong>778SE MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
-- 20.12.2006<br />
Approval of this STC apply only to those<br />
Schweizer 269C which were previously<br />
equipped with FAA approved installation of<br />
Schweizer cargo hook kit P/N 269A4971-<br />
27.Modified rotorcraft must be operated i.a.w.<br />
FAA approved Rotorcraft Flight manual<br />
09.07.2007<br />
External Load Swing Suspension System<br />
Supplement (<br />
1. <strong>EASA</strong>-approved AS350 Flight Manual Prior to installation of this modification it 21.06.2<strong>01</strong>0<br />
models 200-280-<strong>01</strong> and -<strong>04</strong> (withKeeperless and must be determined thatthe<br />
Cargo Hooks) and model 200-280-02 and -03 FM supplement are required.2. This STC is interrelationship between this modification<br />
(with HydraulicCargo Hooks) Revision 1 - approved only for the product configuration as and any other previouslyinstalled<br />
introduced cargo hook kit 200-280-03 with a defined inthe approved design data referred to modification and/ or repair will introduce<br />
collectivefriction knob and a new release lever t in the paragraph "Description".Compatibil no adverse effectupon the airworthiness<br />
of the product.<br />
Onboard Systems Model 200-187-00 cargo Approval of this change in type design applies<br />
hook on helicopters 369D, 369E, 369FF. to only those McDonnell Douglas model<br />
369HE, 369HM, 369HS, 500N<strong>EASA</strong> validation rotorcraft listed above, which were<br />
of FAA STC SR0<strong>04</strong>07SE , amended 2 previouslyequipped with an FAA approved<br />
October 2007, or later approved 07This STC is installation of McDonnell Douglas cargo hook<br />
classified ‘Basic’ by the FAA and is approved suspension systems and Breeze-Eastern cargo<br />
under the po<br />
hooks<br />
Installation of Cargo Hook Suspension Kit P/N<br />
200 - 308 – 00.<br />
1. All limitations of RFM supplement apply;2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effec<br />
Onboard Systems Model 200-300-00 talon LC This cargo hook is not approved for human<br />
Hydraulic Cargo Hook Kit without load weight, external loadApproval of this change in type<br />
Model 200-3<strong>01</strong>-00 talon LC Hydraulic Cargo design applies to only those McDonnell<br />
Hook Kit with load weight on helicopters 369D, Douglas model rotorcraft listed above, which<br />
369E, 369FF. 369HE, 369HM, 369HS, 500N were previouslyequipped with • Onboard<br />
system model 200-187-00 cargo hook<br />
(approva<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 350/<strong>462</strong><br />
18.03.2008<br />
22.<strong>01</strong>.2008<br />
08.07.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7020 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>438 REV. 1 FAA STC SR<strong>01</strong>808SE R44, R44 II Cargo Hook System KitsThe installation as Approval of this change in type design applies Prior to installation of this modification it 17.12.2009<br />
defined in MDL 155-124-00 provides for only to those Robinsonrotorcraft models listed must be determined thatthe<br />
differentoptional Cargo Hook System kits above which are equipped with Robinson interrelationship between this modification<br />
depending on aircraft voltage system,with and hardpoint/tie down block P/N D134-1. and any other previouslyinstalled<br />
without load weighing system and the<br />
modification and/ or repair will introduce<br />
respective cargo hook inaccordance with FAA<br />
no adverse effectupon the airworthiness<br />
STC SR0<br />
of the product.<br />
10<strong>01</strong>7025 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>444 FAA STC SR<strong>01</strong>815SE EUROCOPTER FRANCE EC 130<br />
B4<br />
10<strong>01</strong>7027 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>446 FAA STC SR<strong>01</strong>812SE EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
10<strong>01</strong>7037 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>461 FAA STC SR<strong>01</strong>394SE EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
D<br />
Installation of Model 200-321-00 Cargo Hook<br />
Swing Suspension Kit and Model 200-322-00<br />
Cargo Hook Sling Suspension Kit.<br />
Installation of Cargo Hook Kit P/N 200-297-00<br />
and installation of Cargo Hook Kit P/N 200-298-<br />
00This STC is the validation of FAA STC<br />
SR<strong>01</strong>812SE<br />
Installation of Cargo Hook Sling Suspension Kit<br />
P/N 200-287-00This STC is the validation of<br />
FAA STC SR<strong>01</strong>394SE<br />
10<strong>01</strong>7080 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.<strong>01</strong>531 REV. 1 FAA STC SR<strong>01</strong>943SE BELL 407 200-328-00 Cargo Hook Fixed Provisions<br />
Kit;200-329-00 Cargo Hook Suspension Kit<br />
with Pillow Blocks200-330-00 Cargo Hook<br />
Suspension Kit without Pillow Blocks200-331-<br />
00 Pin Load Weigh Kit<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
1. For P/N 200-329-00 (Cargo Hook<br />
Suspension Kit with Pillow Blocks) – P/N 200-<br />
328-00 (Fixed Provisions Kit) or Bell Helicopter<br />
P/N 206-706-341-111, -117 or -123 (Auxiliary<br />
Equipment Kit – Cargo Hook Provisions) must<br />
be installed;For P/N 200-330-00 (Car<br />
10028873 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR02028SE EC 120 B Cargo hook kit Model 200-351-00 <strong>EASA</strong>-approved EC 120 B Flight Manual<br />
External Load Transport "CargoSling" FM<br />
Supplement is required.<br />
100305<strong>04</strong> ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.00542 REV. 1 FAA STC SR<strong>01</strong>165SE AS 350 B, AS 350 B1, AS 350 B2 Revision of STC <strong>EASA</strong>.IM.R.S.00542<br />
AS 350 B3, AS 350 BA, AS 350 D introducing additional cargo hook kit200-282-<br />
03.<br />
10030532 ONBOARD SYSTEMS INTERNATIONAL P-<br />
<strong>EASA</strong>.IM.R.S.00593<br />
27.03.2009<br />
21.11.2008<br />
06.11.2008<br />
10.03.2009<br />
Prior to installation of this modification it 16.02.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>EASA</strong>-approved AS 350 Flight Manual Prior to installation of this modification it 21.06.2<strong>01</strong>0<br />
and must be determined thatthe<br />
FM supplement are required.This STC is interrelationship between this modification<br />
approved only for the product configuration as and any other previouslyinstalled<br />
defined inthe approved design data referred to modification and/ or repair will introduce<br />
in the paragraph "Description".Compatibility w no adverse effectupon the airworthiness<br />
of the product.<br />
REV. 1 FAA STC SR000896SE BELL 206 A, 206 B Cargo Hook Kit None Approval of this change in type design<br />
applies only to those Bell modelrotorcraft,<br />
listed above, which were previously<br />
equipped with anapproved installation of<br />
Bell cargo hook suspension system<br />
P/N206-072-900-1, -1<strong>01</strong>, or -103; Bell<br />
cargo hook provisions ki<br />
23.06.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 351/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030772 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR02035SE AS355E, AS355F, AS355F1, Cargo Hook Kit model 200-352-00 None Applies only to Eurocopter model 07.07.2<strong>01</strong>0<br />
AS355F2, AS355N, AS355NP<br />
rotorcraft listed above which areequipped<br />
with a cargo swing type suspension<br />
system. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other previou<br />
10032737 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.00592 REV. 1 FAA STC SR00850SE 206L, 206L-1, 206L-3, 206L-4<br />
407<br />
10<strong>04</strong>0250 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR02217SE EC135 P1(CDS), EC135<br />
P1(CPDS)<br />
EC135 P2 (CPDS), EC135 P2+<br />
EC135 T1(CDS), EC135<br />
T1(CPDS)<br />
EC135 T2(CPDS), EC135 T2+<br />
EC635 T1 (CPDS), EC635 P2+<br />
EC635 T2+<br />
Cargo Hook Kit model 200-260-00 and 200-<br />
260-<strong>01</strong>This change adds an additional cargo<br />
hook<br />
10<strong>04</strong><strong>04</strong>40 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR<strong>01</strong>694SE BO 105 S, BO 105 LS A-3 Validation of FAA STC SR<strong>01</strong>694SE - Cargo<br />
Hook Kits<br />
10038238 ONE SKY AVIATION FAA STC SA02387AK 1- 58, 58A, G58, 95-B55, E55<br />
2- A36, G36, A36TC, B36TC,<br />
2- F33A, F33C<br />
10038364 ONE SKY AVIATION FAA STC SA02372AK 1. B200, B200C, B200CT, B200T<br />
1. B200GT, B200CGT<br />
1. B300, B300C<br />
2. C90GT, C90GTI<br />
Applies only to those Bell Helicopter models<br />
listed above previouslyequipped with Bell<br />
Helicopter Cargo Hook Suspension<br />
System206-706-341-5, 206-706-341-1<strong>01</strong> or<br />
206-706-341-109 and eitherBreeze-Eastern<br />
cargo hooks 17149-2, 17149-6 or Onboard<br />
Systems Cargoho<br />
Cargo Hook Kit. Limited to helicopters equipped with cargo<br />
hook assembly P/N AS22-44.<br />
Fabrication and Installation of Exterior LED<br />
Lighting Suite inaccordance with FAA STC<br />
SA02387AK.Fabrication and Installation of<br />
Exterior LED Lighting Suite on theBeechcraft<br />
Baron and Bonanza series aircraft in<br />
accordance to MasterData List No. 20 16 00,<br />
Re<br />
Installation of the Max-Viz® Enhanced Vision<br />
System (EVS) Model-1500 onHawker<br />
Beechcraft Corporation B200/B300/C90 Series<br />
aircraft equippedwith a Rockwell Collins<br />
ProLine 21 Adaptive Flight Display (AFD)<br />
havingthe video capability upgrade Part No 822-<br />
1753-<br />
10<strong>04</strong>0870 ORCON CORPORATION B737-200/-200C/-300/-400/-500 Thermal/acoustic insulation system for Boeing<br />
737 series aircraft:insulation blankets<br />
installation.<br />
10<strong>04</strong>1532 ORCON CORPORATION FAA STC ST<strong>01</strong>834LA B757-200/-200PF Validation of FAA STC ST<strong>01</strong>834LA related to<br />
Installation of InsulationBlanket<br />
10<strong>04</strong>2039 ORCON CORPORATION FAA STC ST02350LA CL600-2B19 Orcon Thermal/Acoustic Insulation System for<br />
Bombardier Challenger 850Series Aircraft<br />
This STC is restricted to installation of cargo<br />
hook kits model200-387-00 and model 200-<br />
388-00. Not included are cargo hook kits<br />
model200-302-00 and model 200-303-00.<br />
Prior to installation of this modification it 26.11.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 20.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 03.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.<strong>01</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
10027300 OREGON AERO, INC. FAA STC SA<strong>01</strong>597SE LC41-550FG (C400) Installation of replacement seats -as indicated in Engineering Manual Instruction<br />
for ContAW EM-<strong>01</strong>-<strong>01</strong>, RevB, or later FAA<br />
approved revisions-only for LC41-550FG S/N<br />
41002 through 41108, 415<strong>01</strong> through 41800<br />
and4110<strong>01</strong> and onwards<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.02.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.07.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.09.2<strong>01</strong>2<br />
None None 05.11.2<strong>01</strong>2<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe i<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 352/<strong>462</strong><br />
18.09.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6451 PANASONIC AVIONICS CORPORATION <strong>EASA</strong>.IM.A.S.02797 - BOEING 757-200 SERIES Installation of a Matsuhita Avionics Audio Prior to installation of this modification the<br />
18.07.2008<br />
System on a Boeing 757-200 Aircraft. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6826 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>196 FAA STC SR00338DE BELL 407 Installation of Anti-Torque Extention Adjustment None<br />
System<br />
30.06.2006<br />
10<strong>01</strong>6875 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>252 FAA STC SR00375DE BELL 206A/B/L/L-1/L-3/L-4 Laser Mapping Installation This STC is approved only for the product<br />
15.09.2006<br />
BELL 206L-4<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6949 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>344 FAA STC SR0<strong>04</strong>89SE BELL 407 Installation of Cabin Air Conditioner System. 21.08.2007<br />
10<strong>01</strong>6950 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>345 FAA STC SR00280DE BELL 407 Installation of Bleed Air Cabin Heater System. 21.08.2007<br />
10<strong>01</strong>6952 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>348 FAA STC SR00025DE BELL 206A/B/L/L-1/L-3/L-4, 407 Installation of an Equipment Tray. This approval is for a shelf only. The shelf is<br />
rated for a 15 pound load and must be<br />
placarded as shown in drawing 206ET-1000,<br />
Revision B dated 9 February 1993 or later<br />
approved revision.On 206A and B models, this<br />
approval is for serial numbers 154 and su<br />
10<strong>01</strong>6953 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>349 FAA STC SR00335DE BELL 407 Snow Pads Installation. 21.08.2007<br />
10<strong>01</strong>6954 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>350 FAA STC SR00344DE BELL 407 Installation of External Mirror. (This STC has<br />
been classified as “BASIC” by the FAA in<br />
accordance with FAA Order 8110.52 and has<br />
been approved using the PTVP Procedures.)<br />
06.09.2007<br />
10<strong>01</strong>6955 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>351 FAA STC SR00<strong>01</strong>1DE BELL 206B/L/L-1/L-3/L-4, 407 Provision for Mount of a Video Monitor Placed<br />
on Left or Right Instrument Panel Console.<br />
10<strong>01</strong>6956 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>352 FAA STC SR0<strong>04</strong>86DE BELL 407 Installation of mounting hardware and approval<br />
for the aircraft to be operated by a single pilot<br />
from the left crew seat.<br />
This approval is for the Mount Assembly only.<br />
The monitor installed must meet the<br />
requirements shown in drawings approved<br />
under theMaster Drawing List No. DL-<br />
206/407MM-110 revision N/C dated 27 July<br />
1999 or later approved revision.On Bell 206B<br />
models, this<br />
For left seat operation of equipment originally<br />
intended to be operated by the pilot from the<br />
right crew seat, provisions must be made to<br />
ensure that such equipment can be equally<br />
operable from the left crew seat with similar<br />
controls.<br />
10<strong>01</strong>6957 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>353 FAA STC SR0<strong>04</strong>11DE BELL 407 Installation of Mounting Hardware to Support<br />
Blade Folding Kit.<br />
10.09.2007<br />
10<strong>01</strong>6964 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>365 FAA STC SR00574DE BELL 407 Installation of 407FL-100 FADEC/Check<br />
instrument auxiliary annunciation system. (This<br />
STC has been classified as “BASIC” by the<br />
FAAin accordance with FAA Order 8110.52<br />
and has been approved using the PTVP<br />
Procedures.)<br />
06.09.2007<br />
10<strong>01</strong>6965 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>366 REV. 1 FAA STC SR00349DE BELL 407 Installation of a Searchlight. This STC has been<br />
classified as “BASIC” by the FAA and has been<br />
approved under the PTVP.<br />
19.03.2008<br />
10<strong>01</strong>6966 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>367 FAA STC SR00348DE BELL 407 Infrared Imaging System Installation. This STC None.<br />
has been classified as “BASIC” by the FAA and<br />
has been approved under the PTVP.<br />
22.05.2008<br />
10<strong>01</strong>6998 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>408 FAA STC SH2726NM 269A, 269B, 269C Cabin Heater Installation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7038 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>462</strong> FAA STC SR0<strong>04</strong><strong>01</strong>DE BELL 206L/L1/L3/L4 AND 407 Snow deflector Installation. 18.07.2008<br />
10<strong>01</strong>7<strong>04</strong>1 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>465 FAA STC SR00334DE BELL 407 Pneumatic Door Opener (PDO). This STC has<br />
been classified as “BASIC” by the FAA and has<br />
been approved under the PTVP.<br />
09.06.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 353/<strong>462</strong><br />
21.08.2007<br />
21.08.2007<br />
21.08.2007<br />
24.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7056 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>487 BELL 206, BELL 407 Vent Control Certification. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
11.08.2008<br />
10<strong>01</strong>7061 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>496 FAA STC SR00654DE 206L-3, 206L-4, BELL 407 Rotary Latch Belts Installation. Prior to installation of this modification the<br />
03.09.2008<br />
BELL 206A, 206B, 206L, 206L-1,<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7064 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>500 FAA STC SR00532DE BELL 212, ,412, 412EP ENHANCED VISION INSTALLATION (This Prior to installation of this modification the<br />
23.09.2008<br />
STC has been classified as “BASIC” by the installer must determine that the<br />
FAA in accordance with FAA Order 8110.52 interrelationship between this modification and<br />
and has been approved using the PTVP any other previously installed modification<br />
Procedures.)<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7065 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>5<strong>01</strong> FAA STC SR00603DE BELL 206, BELL 407 Enhanced Vision Installation. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
23.09.2008<br />
10033806 PARAVION TECHNOLOGY INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>558 FAA STC SH2735NM MD 369D, 369E, 369H, 369HE Pneumatic Door Opener (PDO) This <strong>EASA</strong> None Prior to installation of this modification it 23.06.2009<br />
MD 369HS, 500N, 600N<br />
STC supersedes and is a revision of LBA STC<br />
must be determined thatthe<br />
<strong>04</strong>26/3036.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
10039<strong>01</strong>1 PARAVION TECHNOLOGY INC. FAA STC SR00743DE BELL 429 Installation of structural provisions for a blade<br />
fold kit in accordancewith Paravion Technology<br />
Master Drawing List, Report No DL-429BF-<br />
100,Revision A, dated December 30, 2<strong>01</strong>1.<br />
10<strong>04</strong>1121 PARKER HANNIFIN FAA STC SH363NE AS 365N2, AS 365N3<br />
SA 365N, SA 365N1<br />
10<strong>04</strong>1145 PARKER HANNIFIN FAA STC SH362NE AS355E, AS355F, AS355F1,<br />
AS355F2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
29.03.2<strong>01</strong>2<br />
Installation of Parker 1C44-2 fuel pump in None. If the holder agrees to permit another 22.08.2<strong>01</strong>2<br />
accordance with Installation Manual SP1C44-2.<br />
person to use this certificate toalter the<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
Installation of Parker 1C44-2 Fuel Pump None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.08.2<strong>01</strong>2<br />
10<strong>04</strong>1148 PARKER HANNIFIN FAA STC SR153CH AS 332 L, AS 332 L1 Installation of Parker 1C64-15 Fuel Pump None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.08.2<strong>01</strong>2<br />
10027890 PARKER HANNIFIN CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03272<br />
REV. 1 FAA STC SA<strong>01</strong>376CH PC-12, PC-12/45,<br />
PC-12/47, PC-12/47E<br />
<strong>EASA</strong> Validation of STC SA<strong>01</strong>376CH None 1) Prior to installation of this modification <strong>04</strong>.12.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 354/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039114 PARKER HANNIFIN CORPORATION FAA STC SA619GL 1. C90A, C90GT, C90GTI <strong>EASA</strong> Validation of FAA STC<br />
None Prior to installation of this modification it 10.<strong>04</strong>.2<strong>01</strong>2<br />
2. 65-90, 65-A90<br />
SA619GLInstallation of Parker Hannifin Main<br />
must be determined thatthe<br />
2. 65-A90-1 (JU-21A)<br />
Wheel and Brake Conversion Kit PartNumbers<br />
interrelationship between this modification<br />
2. 65-A90-4 (RU-21E, RU-21H) 199-90 in accordance with Parker Hannifin<br />
and any other previouslyinstalled<br />
2. B90, C90, E90, H90 (T-44A) Conversion KitInstallation Manual IM 199-90,<br />
modification and/ or repair will introduce<br />
Revision J, dated January 7, 2009, orlater FAA<br />
no adverse effectupon the airworthiness<br />
approved<br />
of the product.<br />
10033420 PARMA-TECHNIK, S.R.O. 1. M 137A, M 137AZ<br />
2. M 332, M 332A, M 332AK<br />
3. M 337, M 337A, M 337AK<br />
Prolongation of TBO for the M137, M332 and<br />
M337 engines in serviceaccording to the<br />
procedure No. WMS - OS/09/<strong>04</strong> (Definition<br />
document)under the AP DOA Parma Technik<br />
organization No. M332, 137, 337/0<strong>01</strong><br />
10037491 PATS AIRCRAFT L.L.C. FAA STC ST<strong>01</strong>725NY-D B737-900ER Installation of ten auxiliary fuel tank system<br />
configurationsValidation of STC ST<strong>01</strong>725NY-D<br />
Approved configurations are the following:<br />
Configuration 1: ,,Installation of a Five-Cell<br />
Auxiliary Fuel System inthe forward and aft<br />
cargo compartments in accorda<br />
10027222 PATS AIRCRAFT LLC P-<br />
<strong>EASA</strong>.IM.A.S.03142<br />
10027223 PATS AIRCRAFT LLC P-<br />
<strong>EASA</strong>.IM.A.S.03235<br />
REV. 1 FAA STC ST00365NY-D CL-600-2B19 Revisions to Auxiliary Fuel System Structural<br />
Provisions<br />
none none 19.<strong>01</strong>.2<strong>01</strong>1<br />
Configurations 1 & 5:,,PATS Aircraft, LLC.<br />
Airplane Flight ManualSupplement No. 221 for<br />
a Five-Cell (1 Fwd/4 Aft) Auxiliary Fuel<br />
System,revision IR dated January 30, 2009 is<br />
required. Approved for aircraftwith NGS.<br />
Configurations 2 & 6:,,PATS Aircraft, L<br />
PATS Aircraft, LLC. Airplane Flight Manual<br />
Supplement No. 200, RevisionB, FAA<br />
approved 11 June 2009, is required with<br />
configurations 5 and 6.<br />
REV. 2 FAA STC ST<strong>01</strong>730NY-D CL-600-2B19 Installation of an Executive Interior In this installation the maximum passenger<br />
seating capacity is limitedto 15.<br />
10<strong>01</strong>6198 PEMCO WORLD AIR SERVICES <strong>EASA</strong>.IM.A.S.02438 REV. 2 FAA STC SA2968SO BOEING 737-400 Modification of floor in accordance with Pemco<br />
World Air Services, Inc. Master Data list,<br />
Report No. 2316, revision “K”, dated June15,<br />
2006, or later <strong>EASA</strong> approved revision.<br />
10<strong>01</strong>6199 PEMCO WORLD AIR SERVICES <strong>EASA</strong>.IM.A.S.02439 REV. 2 FAA STC SA2969SO BOEING 737-400 Installation of a cargo door in accordance with<br />
Pemco World Air Services, Inc. Master Data<br />
list, Report No. 2373, revision “T”, dated June<br />
15, 2006, or later <strong>EASA</strong> approved revision.<br />
10<strong>01</strong>6200 PEMCO WORLD AIR SERVICES <strong>EASA</strong>.IM.A.S.02440 FAA STC SA2970SO BOEING 737-400 Installation of a Class “E” Cargo Compartment<br />
and passenger interior configuration in<br />
accordance with with Pemco World Air<br />
Services, Inc. Master Data list, Report No.<br />
2374, revision “S”, dated June 15, 2006, or<br />
later <strong>EASA</strong> approved revision.<br />
10035332 PEMCO WORLD AIR SERVICES <strong>EASA</strong> STC 20<strong>04</strong>-<br />
3750<br />
REV. 1 FAA STC SA2971SO B737-300 Installation of a Cargo Loading System in acc<br />
with MDL 2337 rev X<br />
dated12/07/2<strong>01</strong>0Modification of the STC FAA<br />
SA2971SO to increase from 121 pax to 148<br />
paxaccording to drawing 90945-507/607<br />
10<strong>01</strong>6480 PENTASTAR AVIATION, L.L.C. <strong>EASA</strong>.IM.A.S.02832 FAA STC ST<strong>01</strong>759CH FALCON 50<br />
FALCON 900<br />
FALCON 900EX<br />
Instructions for Continued Airworthiness (ICA),<br />
Pemco Report No 2917, Revision C, dated<br />
January 18, 2006, or later <strong>EASA</strong> approved<br />
revision, is a required part of this STC, and<br />
must be incorporated into the operator’s<br />
maintenance program.<br />
- Airplane Flight manual Supplement<br />
(AFMS), Report P03-003FM Rev 7, or later<br />
<strong>EASA</strong> approved revision.- Instructions for<br />
Continued Airworthiness (ICA), Pemco Report<br />
No 2917, Revision C, dated January 18, 2006,<br />
or later <strong>EASA</strong> approved revision, is also a<br />
- Airplane Flight manual Supplement<br />
(AFMS), Report P03-003FM Rev 7, dated April<br />
27th 2007 or later <strong>EASA</strong> approved revision.-<br />
Instructions for Continued Airworthiness (ICA),<br />
Pemco Report No 2917, Revision C, dated<br />
January 18, 2006, or later <strong>EASA</strong> approv<br />
<strong>EASA</strong> Validation of FAA approved STC 1. See those of original FAA STC<br />
ST<strong>01</strong>759CHUpgrade of a Rockwell Collins ST<strong>01</strong>759CH.2. Prior to installation of this<br />
SAT-906 SATCOM system by modification of modification the installer must determine that<br />
Rockwell Collins SDU-906 Satellite Data Unit the interrelationship between this modification<br />
and HPA-9<strong>01</strong>A High Power Amplifier and the and any other previously installed modification<br />
installation of a Rockwell Collins HST-900 High will introduce no adverse effec<br />
Speed<br />
Prior to installation of this modification it 12.12.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 12.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 12.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.06.2008<br />
24.06.2008<br />
07.05.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.06.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 355/<strong>462</strong><br />
<strong>01</strong>.<strong>04</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5853 PETERSEN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>956 FAA STC SA00328WI REIMS AVIATION CESSNA F- Operation of airplane on leaded and unleaded Limited to those airplanes equipped with<br />
24.<strong>04</strong>.2006<br />
172N<br />
automotive gasoline, 91 minimum antiknock gravity fuel feed to the carburetor and STC<br />
index (RON + MON) / 2 per ASTM<br />
certificated or approved engine installation. All<br />
SpecificationD-439. Intermixing with aviation engines must have separate approval for<br />
gasoline also approved.<br />
operation on automotive gasoline in the form of<br />
Supplemental or Type Certificte a<br />
10<strong>01</strong>5854 PETERSEN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>957 FAA STC SA2600CE CESSNA 172D<br />
Operation of airplane on leaded and unleaded Limited to those airplanes equipped with<br />
20.<strong>04</strong>.2006<br />
CESSNA 172E<br />
automotive gasoline, 91 minimum antiknock gravity fuel feed wing fuel tanks as the main<br />
CESSNA 172F<br />
index (RON + MON) / 2 per ASTM<br />
fuel supply to the carburetor and certificated<br />
CESSNA 172G<br />
SpecificationD-439. Intermixing with aviation (original or STC) or approved engine<br />
CESSNA 172H<br />
gasoline also approved.<br />
installations. All engines must have separate<br />
CESSNA 172I<br />
CESSNA 172K<br />
CESSNA 172L<br />
CESSNA 172M<br />
CESSNA 172N<br />
CESSNA 172P<br />
approval for operation on automative ga<br />
10<strong>01</strong>6291 PETERSEN AVIATION, INC. <strong>EASA</strong>.IM.A.S.02586 FAA STC SA2660CE PA-28-160, PA-28-161,<br />
Operation of Piper airplanes with automotive 1. Limitations as established in FAA STC<br />
10.09.2007<br />
PA-28-180, PA-28-181<br />
gasoline in accordance with FAA STC SA2660CE, dated April 29, 2005 are<br />
SA2660CE, dated April 29, 2005.<br />
applicable.2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed<br />
10<strong>01</strong>6690 PETERSEN AVIATION, INC. <strong>EASA</strong>.IM.E.S.<strong>01</strong>002 FAA STC SE00663WI LYCOMING ENGINES O-540-<br />
F1B5<br />
1003<strong>04</strong>24 PETERSEN AVIATION, INC. P-<br />
<strong>EASA</strong>.IM.A.S.03224<br />
10033096 PETERSEN AVIATION, INC. FAA STC SA2670CE 1. A-1, A-1A, A-1B<br />
2. A-1C-180<br />
FAA STC SA00214WI CESSNA F182P Operation of airplane on unleaded automotive<br />
gasoline, 87 minimumantiknock index and<br />
leaded automotive gasoline, 88 minimum<br />
antiknockindex (RON + MON) /2 per ASTM<br />
Specification D-439 in acc. to FAA<br />
STCSA00214WI.<br />
Air Conditioning System for Agusta A 119FAA This approval should not be extended to<br />
STC SR0<strong>04</strong>63DE issued on 11th January 2002 rotorcraft of this model on which other<br />
and amended on 24th January 2006- Flight previously approved modifications are<br />
Manual Supplement Doc. N° A119-1 rev. 3 incorporated unless it is determinded that the<br />
dated 14th July 2005 or later approved interrelationship between this change and any<br />
revision.- Instruction for Continued<br />
of those other previously approved modificati<br />
Airworthiness<br />
Operation of airplanes using automotive<br />
gasoline according US STCSA2670CE<br />
1. Limited to those airplanes equipped with<br />
gravity fuel feed to thecarburettor and<br />
certificated (original or STC) <strong>EASA</strong> approved<br />
engineinstallations. All engines must have<br />
separate approval for operation onautomotive<br />
gasoline in the form of Supplemental or<br />
-According limitation section of AFM-S-Limited<br />
to those airplanes equipped with gravity fuel<br />
feed tocarburetor only-Not approved for 82UL<br />
23.02.2006<br />
Prior to installation of this modification it 15.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Conditions as indicated in FAA STC<br />
SA2670CE also apply. Prior to<br />
installation of this modification it must be<br />
or mixtures with 82UL-Limitation as indicated in determined thatthe interrelationship<br />
FAA STC SA2670CE also apply<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adv<br />
10<strong>01</strong>4378 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>653 Installation of Dual GNS530 with Dual GI-106A This STC is approved only for the product<br />
10.02.2006<br />
& Dual KNI-582 RMI<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4430 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.02478 BEECH A36 Installation of Skywatch Traffic Avoidance 07.06.2006<br />
10<strong>01</strong>4589 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.02696 REV. 1 BN2B-26 ISLANDER Installation of GNS530, GNS430 & GMA340. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
24.<strong>04</strong>.2007<br />
10<strong>01</strong>4732 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.02914 CESSNA 560 Installation of Honeywell EGPWSCessna 560 1. Restricted to G-PPLC ASN 560-00592.<br />
24.<strong>01</strong>.2007<br />
G-PPLC ASN 560-0059<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircr<br />
10<strong>01</strong>4979 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03269 Installation of new Avionics. 30.<strong>01</strong>.2008<br />
10<strong>01</strong>5100 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03443 PIPER PA-31 Installation of new Avionics Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
30.09.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 356/<strong>462</strong><br />
17.12.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>51<strong>01</strong> PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03444 PIPER PA-39 Validation of Foreign Installed Avionics 05.05.2008<br />
10<strong>01</strong>5141 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03499 CESSNA 208 Installation of Garmin GNS430 and GTX330<br />
Mode "S" Transponder.<br />
19.03.2008<br />
10<strong>01</strong>5189 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03573 Installation of Garmin GNS430 13.06.2008<br />
10<strong>01</strong>7139 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>240 EUROCOPTER DEUTSCHLAND Installation of Skywatch Traffic Avoidance<br />
MBB-BK<br />
22.05.2006<br />
10<strong>01</strong>7180 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>303 EUROCOPTER FRANCE AS Installation for KLN90B GPS, UNS-1K Flight AS365 NI, S/N 6309. 27.08.2007<br />
365N1<br />
Management System, Devore Recognition<br />
Light System and Whelen Strobe.<br />
10<strong>01</strong>7189 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>326 EUROCOPTER DEUTSCHLAND Installation of Honeywell AR30 Cockpit Voice -- 11.<strong>01</strong>.2007<br />
BK117 C<br />
Recorder<br />
10<strong>01</strong>7245 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>442 Installation of Power Line Detector System. Eurocopter Deutschland BK117 Series.RFM<br />
Supplement PADS/FMS/BK117/003<br />
05.03.2008<br />
10029133 PHOENIX AEROSPACE LIMITED P-<strong>EASA</strong>.R.S.<strong>01</strong>515 AS355E, AS355F, AS355F1, Installation of Skywatch L3 Traffic avoidance Not Applicable Not Applicable 08.03.2<strong>01</strong>0<br />
AS355F2, AS355N, AS355NP and Honeywell's KMD250 MFD<br />
10<strong>04</strong>1858 PHOENIX AEROSPACE LIMITED A139 Introduction of SX16 Searchlight System none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.12.2<strong>01</strong>2<br />
10<strong>04</strong>1863 PHOENIX AEROSPACE LIMITED AW 139 Introduction of an electronic message sign. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.12.2<strong>01</strong>2<br />
10030088 PIAGGIO AMERICA, Inc. FAA STC SA10955SC P.180 AVANTI & AVANTI II FAA STC SA10955SC "Installation of a<br />
passenger seating system to replacefive<br />
existing Decrane single seats with Model<br />
FS11<strong>01</strong> single seats"<br />
10<strong>01</strong>6399 PLANE POWER, LTD. <strong>EASA</strong>.IM.A.S.02728 FAA STC SA10682SC Replacement of generator and mechanical<br />
voltage regulator with alternator and electronic<br />
voltage regulator<br />
10<strong>04</strong>0602 PMV ENGINEERING REV. 1 A330-200, A330-300 Installation of provisions for the use of EFB<br />
Class 2 on Airbus A330.This modification deals<br />
with the installation of a dual Class 2Electronic<br />
Flight Bag (EFB) CMC Esterline 'Pilot View'<br />
system on AirbusA330-200/300. The<br />
modification is defined as follows:<br />
10<strong>04</strong>2279 PMV ENGINEERING B747-400 Installation of provisions for the use of EFB<br />
Class 2.<br />
10<strong>01</strong>7116 POLICE AVIATION SERVICES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>098 BELL 412 EP Installation of an L-3 Modular Airborne Data<br />
Recording/Acquisition System (MADRAS)<br />
combined CVR & FDR<br />
10<strong>01</strong>72<strong>04</strong> POLICE AVIATION SERVICES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>353 MD HELICOPTERS MD902 MTWA Increase with PAS External Stores and<br />
Surveillance Equipment<br />
10033979 POLICE AVIATION SERVICES Ltd. <strong>EASA</strong> STC 20<strong>04</strong>-<br />
3846<br />
REV. 1 EC 135 P1 (CDS)<br />
EC 135 P1 (CPDS)<br />
EC 135 P2 (CPDS)<br />
EC 135 P2+<br />
EC 135 T1 (CDS)<br />
EC 135 T1 (CPDS)<br />
EC 135 T2 (CPDS)<br />
EC 135 T2+<br />
EC 635 P2+<br />
EC 635 T1 (CPDS)<br />
EC 635 T2+<br />
Incubator Installation EC 135Transfer of <strong>EASA</strong><br />
STC No 20<strong>04</strong> 3846 (dated 16/<strong>04</strong>/20<strong>04</strong>) from<br />
PAS Ltd toBond Aviation Group Ltd<br />
None None 20.05.2<strong>01</strong>0<br />
The approval holder shall fulfil the obligations<br />
of Part 21, Paragraph 21.A109<br />
This certificate does not cover the installation<br />
of EDUs which will becover by the operational<br />
evaluation.<br />
<strong>EASA</strong> STC 10<strong>04</strong>09<strong>01</strong> is a prerequisite for this<br />
modification.<br />
13.05.2008<br />
Prior to installation of this modification it 13.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 20.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.05.2006<br />
Only those in the above F/M Supplement. 03.<strong>04</strong>.2007<br />
Prior to installation of this modification it 28.02.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 357/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034324 POLICE AVIATION SERVICES Ltd. MD902 CONFIG. P&W 206&207 Aircraft Role Configuration none The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21.A109Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair<br />
25.03.2<strong>01</strong>1<br />
10036834 POLICE AVIATION SERVICES Ltd. REV. 1 VULCANAIR P.68.TC<br />
Airborne Surveillance System Installation None Prior to installation of this modification it 24.11.2<strong>01</strong>1<br />
'OBSERVER'<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5338 PRATT & WHITNEY <strong>EASA</strong>.IM.A.S.00373 REV. 2 AIR TRACTOR AT-402 A<br />
AIR TRACTOR AT-5<strong>01</strong><br />
AIR TRACTOR AT-502 B<br />
AIR TRACTOR AT-503<br />
AIR TRACTOR AT-802<br />
AIR TRACTOR AT-802 A<br />
BEECH 1900<br />
BEECH 200<br />
BEECH 300<br />
BEECH C90<br />
CESSNA 208<br />
CESSNA 208A<br />
CESSNA 208B<br />
PILATUS PC-6/B-H2<br />
PILATUS PC-6/B1-H2<br />
PILATUS PC-6/B2-H2<br />
PILATUS PC-6/B2-H4<br />
10<strong>01</strong>5554 PRATT & WHITNEY <strong>EASA</strong>.IM.A.S.<strong>01</strong>451 REV. 1 FAA STC SA0<strong>01</strong>96BO BEECH 1900<br />
BEECH 200<br />
BEECH 300<br />
BEECH C90<br />
CESSNA 208<br />
CESSNA 208A<br />
CESSNA 208B<br />
10<strong>01</strong>5834 PRATT & WHITNEY <strong>EASA</strong>.IM.A.S.<strong>01</strong>925 REV 1 FAA STC ST00228BO DC-9-81 (MD-81)<br />
DC-9-82 (MD-82)<br />
DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
MD-88<br />
10<strong>01</strong>6426 PRATT & WHITNEY <strong>EASA</strong>.IM.A.S.02765 FAA STC SA00095BO, LBA SA 1346 BEECH 1900<br />
BEECH 1900C, AIRLINER<br />
BEECH 1900D<br />
BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH A200<br />
BEECH A200C<br />
BEECH A200CT<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
BEECH B300<br />
BEECH B300C<br />
Installation of Pratt & Whitney Data Acquisition<br />
System ADAS+, p/n ADAS-K-<strong>01</strong>0.<br />
1. Compatibility of this modification with other<br />
previously approved modifications must be<br />
determined by the installer.2. This Major<br />
Change to STC <strong>EASA</strong>.IM.A.S.00373 is issued<br />
as a result of the validation of the Altair<br />
Avionics Corporation STC No SA0<br />
Installation of Altair Avionics Corporation Data This STC is approved only for the product<br />
Transmission Unit in accordance with configuration as defined in the approved design<br />
instructions listed in Approved Model List (AML) data referred to in the paragraph "Description".<br />
DTU-T-225-1, Rev - or later approved Compatibility with other aircraft/engine<br />
revisions. FAA STC SA0<strong>01</strong>96BO refers configurations shall be determined by the<br />
installer.<br />
Installation of P&W JT8D-200 Series Engines<br />
incorporating the improved forward Fan Case<br />
as described in the P&W SB JT8D 6478,<br />
Rev.1, dated 1 August 2007.<br />
10<strong>01</strong>6692 PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong>006 FAA STC SE00033EN CFM56-3B1 Installation of Pratt & Whitney (P&W) Global<br />
Material Solutions (GMS) CFM56-3 High<br />
Pressure Compressor Module in accordance<br />
with P&W GMS Drawing List 880500-<strong>01</strong>C<br />
dated May 06, 2008 or later <strong>EASA</strong>-approved<br />
revision<strong>EASA</strong> Certification Basis:1.<br />
Airworthiness<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
datareferred to in the paragraph "Description".<br />
Prior to installation of this modification the<br />
installermust determine that the<br />
interrelationship between this modific<br />
Installation of Pratt & Whitney Engine Services, 1. Pratt & Whitney Engine Services,Inc.<br />
Inc. Twin Engine Aircraft Data Acquisition Aircraft Flight Manual Supplement for<br />
System ADAS/ADAS+ Upgrade, P/N TWIN-K- Raytheon Aircraft Company Models 200,<br />
<strong>01</strong>0<br />
200C, 200CT, 200T, A200, A200C, A200CT,<br />
B200, B200C, B200CT, B200T, 300, 300LW,<br />
B300C, 1900, 1900C, 1900D, Document No.<br />
TWIN-T-250-1, Revisi<br />
Limitations:1. The limitations of the <strong>EASA</strong><br />
Engine Type Certificate Data Sheet E.066<br />
issue 1, dated November 28, 2008 apply to this<br />
Supplemental Type Certificate.2. Life limits<br />
for the parts approved by this Supplemental<br />
Type Certificate are published<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 358/<strong>462</strong><br />
07.03.2008<br />
11.<strong>04</strong>.2008<br />
<strong>04</strong>.10.2007<br />
07.03.2008<br />
22.12.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6693 PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong>007 FAA STC SE00034EN CFM56-3B1 Installation of Pratt & Whitney (P&W) Global Limitations:1. The limitations of the <strong>EASA</strong><br />
22.12.2008<br />
Material Solutions (GMS) CFM56-3 High Engine Type Certificate Data Sheet E.066<br />
Pressure Turbine Module in accordance with issue 1, dated November 28, 2008 apply to this<br />
P&W GMS Drawing List 880500-<strong>01</strong>D dated Supplemental Type Certificate.2. Life limits<br />
May 06, 2008 or later <strong>EASA</strong>-approved for the parts approved by this Supplemental<br />
revision<strong>EASA</strong> Certification Basis:1.<br />
Airworthiness Sta<br />
Type Certificate are published<br />
10<strong>01</strong>6694 PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong>008 FAA STC SE00035EN CFM56-3B1 Installation of Pratt & Whitney (P&W) Global Limitations:1. The limitations of the <strong>EASA</strong><br />
22.12.2008<br />
Material Solutions (GMS) CFM56-3 Low Engine Type Certificate Data Sheet E.066<br />
Pressure Turbine Module in accordance with issue 1, dated November 28, 2008 apply to this<br />
P&W GMS Drawing List 880500-<strong>01</strong>E dated Supplemental Type Certificate.2. Life limits<br />
May 06, 2008 or later <strong>EASA</strong>-approved for the parts approved by this Supplemental<br />
revision<strong>EASA</strong> Certification Basis:1.<br />
Airworthiness Stan<br />
Type Certificate are published<br />
10<strong>01</strong>6695 PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong>009 FAA STC SE00032EN CFM56-3B1 Installation of Pratt & Whitney (P&W) Global Limitations:1. The limitations of the <strong>EASA</strong><br />
22.12.2008<br />
Material Solutions (GMS) CFM56-3 Fan and Engine Type Certificate Data Sheet E.066<br />
Booster Module in accordance with P&W GMS issue 1, dated November 28, 2008 apply to this<br />
Drawing List 880500-<strong>01</strong>B dated March 14, Supplemental Type Certificate.2. Life limits<br />
2008 or later <strong>EASA</strong>-approved revision<strong>EASA</strong> for the parts approved by this Supplemental<br />
Certification Basis:1. Airworthiness Standar Type Certificate are published<br />
10<strong>01</strong>6702 PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>7 FAA STC SE00026EN ROLLS-ROYCE 250-C18<br />
ROLLS-ROYCE 250-C18A<br />
ROLLS-ROYCE 250-C20<br />
ROLLS-ROYCE 250-C20B<br />
ROLLS-ROYCE 250-C20F<br />
ROLLS-ROYCE 250-C20J<br />
ROLLS-ROYCE 250-C20R/1<br />
ROLLS-ROYCE 250-C20R/2<br />
ROLLS-ROYCE 250-C20S<br />
10<strong>01</strong>6703 PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>8 FAA STC SE00029EN, LBA EN0034 HONEYWELL INT. T5313B<br />
HONEYWELL INT. T5317<br />
Installation of Pratt & Whitney Engine Services, 1. The IntelliStart Plus +TM ECU is desinged to<br />
Inc. IntelliStart Plus +TM Electronic Control Unit limit start temperatures and to provide an<br />
(ECU), P/N DPU-K-<strong>01</strong>0 on the specified 250 electronic aid for recording engine trend and<br />
engine models.<br />
cycle data.2. The IntelliStart Plus +TM ECU is<br />
designed as non-essential, ground use only<br />
equipment and cannot be used<br />
Installation of Pratt & Whitney Engine Services,<br />
Inc. SmartCycle Plus Engine Monitoring<br />
System, P/N EMU-K-<strong>01</strong>0-1 on the specified<br />
T53 engine models<br />
1. SmartCycle Plus Engine MonitoringSystem<br />
is designed as an electronic aid for recording<br />
engine trend and cycle data.This system does<br />
not eliminate any scheduled maintenance or<br />
parts replacement based on time or any engine<br />
Instructions for Continued Airwo<br />
10<strong>01</strong>67<strong>04</strong> PRATT & WHITNEY <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>9 FAA STC SE00027EN ROLLS RROYCE 250-C Installation of Pratt & Whitney Engine Services, 1. The IntelStart Plus +TM ECU is desinged to<br />
Inc. IntelliStart Plus +TM Electronic Control Unit limit start temperatures and to provide an<br />
(ECU), P/N DPU-K-<strong>01</strong>0 on the specified electronic aid for recording engine trend and<br />
engine models<br />
cycle data.2. The IntelliSTart Plus +TM ECU is<br />
designed as non-essential, ground use only<br />
equipment and cannot be used to<br />
10<strong>01</strong>6707 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.0<strong>04</strong>8 REV. 1 N 20<strong>04</strong>-6170 AGUSTA AB-412<br />
AGUSTA AB-412EP<br />
BELL 212<br />
BELL 222<br />
BELL 222B<br />
BELL 222U<br />
BELL 412<br />
BELL 412 EP<br />
10<strong>01</strong>6799 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>157 REV. 1 AGUSTA AB-412<br />
AGUSTA AB-412EP<br />
BELL 212<br />
BELL 412<br />
BELL 412 EP<br />
Installation of Pratt & Whitney Engine Services,<br />
Inc. SmartCycle monitoring and recording<br />
system<br />
Installation of Pratt & Whitney Engine Services<br />
, Inc. Data Transmission Unit<br />
1. Required maintenance, as prescribed in the<br />
applicable airframe or engine Instructions for<br />
Continued Airworthiness, shall not be predicted<br />
on the data obtained from Pratt & Whitney<br />
Engine Services, Inc., monitoring/recording<br />
system.2. This system shall<br />
10<strong>01</strong>6803 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>163 REV. 1 SCHWEIZER AIRCRAFT 269D Installation of Pratt & Whitney Engine Services, 1. Engine must be modified in accordance with<br />
Inc. IntelliStart+ Electronic Control System and STC SE00027EN, which must be <strong>EASA</strong><br />
Gine Trend Monitor P/N DPU-K-<strong>01</strong>0-14 approved or accepted prior to installation.2.<br />
Reference STC SE0027EN for any additional<br />
limitations applicable to the engine installation3.<br />
This system is designed as an electr<br />
10<strong>01</strong>6827 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>197 REV. 1 AGUSTA A-109 E Installation of a Pratt & Whitney Engine<br />
Services, Inc. Digital Aircraft Data Acquisition<br />
System ADASd<br />
10<strong>01</strong>6848 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>224 REV. 1 AGUSTA A-109 E Installation of a Pratt & Whitney Engine<br />
Services, Inc. Dta Transmission Unit Data<br />
Transmission UnitDTU-K-<strong>01</strong>0-7<br />
14.03.2008<br />
<strong>04</strong>.03.2008<br />
14.03.2008<br />
25.03.2008<br />
07.03.2008<br />
14.03.2008<br />
1. Required maintenance, as prescribed in the<br />
11.03.2008<br />
applicable airframe or engine Instructions for<br />
Continued Airworthiness, shall not be<br />
predicated on the data obtained from the Pratt<br />
& Whitney Engine Services, Inc.<br />
monioring/recording system.2. This system<br />
shal<br />
1. 109E with Pr & W: 206C Engine; 07.03.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 359/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7005 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>417 FAA STC SR0<strong>01</strong>25BO MD HELICOPTERS 369A Installation of a Pratt & Whitney Engine 1. Aircraft must have Engine modified in<br />
14.03.2008<br />
MD HELICOPTERS 369D Services. Inc.-Honeywell IntelliStart Plus+TM accordance with <strong>EASA</strong> STC<br />
MD HELICOPTERS 369E Electronic Control System P/N DPU-K- <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>9, FAA STC<br />
MD HELICOPTERS 369F <strong>01</strong>0Note: This STC reflects the transfer from SE00027EN.2. Pratt & Whitney Engine<br />
MD HELICOPTERS 369FF Altair Avionics Corporation to Pratt & Whitney Services, Inc. Rotorcraft Flight Manual DPPU-<br />
MD HELICOPTERS 369H Engine Services, Inc.<br />
T-250-2 dated July 27, 2000 or later approved<br />
MD HELICOPTERS 369HE<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
revision, is required.3. Th<br />
10<strong>01</strong>7006 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>418 FAA STC SR0<strong>01</strong>13BO BELL 206A<br />
Installation of a Pratt & Whitney Engine 1. Aircraft must have engine modified in<br />
14.03.2008<br />
BELL 206B<br />
Services, Inc. - AlliedSignal Aerospace accordance with <strong>EASA</strong> STC<br />
BELL 206L<br />
IntelliStart Plus + TM Electronic Control <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>7, FAA STC<br />
BELL 206L-1<br />
System P/N DPU-K-<strong>01</strong>0Note: This STC SE00026EN.2. Compatibility of this design<br />
BELL 206L-3<br />
reflects the transfer from Altair Avionics change with previously approved modifications<br />
BELL 206L-4<br />
Corporation to Pratt & Whitney Engine must be determined by the installer.3. Pratt &<br />
Services, Inc.<br />
Whitney Engine Serv<br />
10<strong>01</strong>7007 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>419 REV. 1 FAA STC SR0<strong>01</strong>69BO, LBA RC1237 EUROCOPTER DEUTSCHLAND Installation of Pratt & Whitney Engine Services, 1. Required maintenance, as prescribed in the<br />
25.03.2008<br />
BO-105<br />
Inc. SmartCycle+ monitoring and recording applicable airframe or engine Instructions for<br />
EUROCOPTER DEUTSCHLAND system<br />
Continued Airworthiness, shall not be predicted<br />
BO-105D<br />
on the data obtained from the Pratt & Whitney<br />
EUROCOPTER FRANCE AS 350<br />
Engine Services, Inc. monitoring/recording<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
EUROCOPTER FRANCE AS 350<br />
D<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
system.2. This system sha<br />
10<strong>01</strong>7008 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>420 FAA STC SR0<strong>01</strong>26BO AND LBA RC 1 BELL 205A-1 Installation of a Pratt & Whitney Engine 1. Pratt & Whitney Engine Services, Inc.<br />
03.03.2008<br />
Services, Inc. SmartCycle Plus System P/N Rotorcraft Flight Manual EMU-T-250-1 dated<br />
EMU-K-<strong>01</strong>0-2<br />
August 31, 2000 or later approved revision, is<br />
required.2. This system is designed as an<br />
electronic aid for recording engine trend and<br />
cycle data. This system does not elim<br />
10<strong>01</strong>7009 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>421 FAA STC SR0<strong>01</strong>18BO, LBA STC RC EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
10<strong>01</strong>7<strong>01</strong>0 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>423 FAA STC SR0<strong>01</strong>36BO, LBA RC1176<br />
BA<br />
EUROCOPTER FRANCE AS<br />
355E<br />
EUROCOPTER FRANCE AS<br />
355F<br />
EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
EUROCOPTER FRANCE AS<br />
355N<br />
Installation of Pratt & Whitney Engine Services,<br />
Inc. SmartCycle Engine Monitoring<br />
System,Part no. CYCLE-K-<strong>01</strong>0<br />
Installation of a Pratt & Whitney Engine<br />
Services, Inc. SmartCycle Twin Engine<br />
Monitoring System Part No. CYCLE-K-<strong>01</strong>0-4<br />
for AS355N and -5 for AS355E, AS355-F,<br />
AS355F1, AS355F2<br />
1. Pratt & Whitney Engine Services, Inc.<br />
Aircraft Flight Manual Supplement for<br />
Eurocopter France, Models, AS-350B, AS-<br />
350B1, AS-350B2, AS-350BA, and AS-<br />
350B3, Doc. No. Cycle-T-250-1, Revision-,<br />
approved April 11, 2000, or later approved<br />
revision, is requ<br />
1. Pratt & Whitney Engine Services, Inc.,<br />
Aircraft Flight Manual Supplement for<br />
Eurocopter France, Models AS355E, AS355-<br />
F, AS355-F1, AS355F2, and AS355N, Doc.<br />
No. CYCLE-T-250-2, Revision-, approved May<br />
22, 20<strong>01</strong>, or later approved revision, is required<br />
with<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 360/<strong>462</strong><br />
<strong>04</strong>.03.2008<br />
<strong>04</strong>.03.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7<strong>01</strong>1 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>424 FAA STC ST00<strong>04</strong>9BO, LBA RC 1<strong>04</strong>8 ROBINSON R22<br />
Installation of a Pratt & Whitney Engine 1. Federal Aviation Administration approval of<br />
<strong>04</strong>.03.2008<br />
ROBINSON R22 ALPHA Services, Inc. Health Usage Monitoring System the HUMS installation was determined on a<br />
ROBINSON R22 BETA<br />
(HUMS) Model 1022, P/N HUMS-A-030-1 non-interference basis. Operation of<br />
maintenance must not be predicated on the<br />
HUMS.<br />
10<strong>01</strong>7<strong>01</strong>2 PRATT & WHITNEY <strong>EASA</strong>.IM.R.S.<strong>01</strong>425 FAA STC SR00067BO, LBA STC RC EUROCOPTER FRANCE AS 350 Installation of a Pratt & Whitney Engine 1. Federal Aviation Administration approval of<br />
<strong>04</strong>.03.2008<br />
B<br />
Services, Inc. Health Usage Monitoring System the HUMS installation was determined on a<br />
EUROCOPTER FRANCE AS 350 (HUMS) Model 1122, P/N HUMS-A-070-I, non-interference basis. Operation of<br />
B1<br />
Revision B<br />
maintenance must not be predicated on the<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
BA<br />
HUMS.<br />
10026953 PRATT & WHITNEY P-<br />
FAA STC ST00261BO FALCON 2000EX <strong>EASA</strong> Validation of FAA STC<br />
Instructions for Continued Airworthiness (ICA) Prior to installation of this modification it 26.08.2009<br />
<strong>EASA</strong>.IM.A.S.03229<br />
ST00261BO:Installation of Pratt & DTU-G-260-7, Revision Cdated 26th May must be determined thatthe<br />
Whitney Engine Services, Inc<br />
2009 or later revisions shall be made available interrelationship between this modification<br />
DataTransmission Unit (DTU) in accordance to theoperator at the time of installation and any other previouslyinstalled<br />
with Pratt & Whitney EngineServices,<br />
modification and/ or repair will introduce<br />
Inc, Master Document List DTU-T-100-6,<br />
no adverse effectupon the airworthiness<br />
Revision F dated 23rdJuly 2009, or l<br />
of the product.<br />
10028632 PRATT & WHITNEY <strong>EASA</strong>.IM.A.S.03230 GULFSTREAM 200 17.07.2009<br />
10039147 PRATT & WHITNEY ENGINE SERVICES,<br />
FAA STC SA00303BO C90GT, C90GTI ADAS for Hawker Beechcraft Model C90GT, None Prior to installation of this modification it 12.<strong>04</strong>.2<strong>01</strong>2<br />
IN<br />
C90GTiInstallation of the Pratt & Whitney<br />
must be determined thatthe<br />
Engine Services ADAS in accordancewith Pratt<br />
interrelationship between this modification<br />
& Whitney Engine Services’ Installation Manual<br />
and any other previouslyinstalled<br />
DAAS-G-<strong>01</strong>0-6,Revision B, dated April 7,<br />
modification and/ or repair will introduce<br />
2<strong>01</strong>0, or later FAA approved revision.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039150 PRATT & WHITNEY ENGINE SERVICES,<br />
IN<br />
FAA STC SA00295BO 1. B200, B200C, B300, B300C<br />
2. 300<br />
ADAS for Hawker Beechcraft Model B200,<br />
B200C, 300, B300, B300CInstallation of the<br />
Pratt & Whitney Engine Services’ Master<br />
DocumentList No. DAAS-T-100-3, Revision D,<br />
dated May 13, 2<strong>01</strong>0, or laterFAA-approved<br />
revision.<br />
10<strong>01</strong>6093 PRECISE FLIGHT, Inc. <strong>EASA</strong>.IM.A.S.02280 REV. 2 FAA STC SA<strong>01</strong>708SE SR22, SR22T Installation of Cirrus Fixed Oxygen System - according limitation section of AFM-S- max<br />
altitude extension up to 25.000 ft, if operated<br />
acc. Limitationsection of AFM-S<br />
10<strong>01</strong>6858 PRECISE FLIGHT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>234 REV. 1 FAA STC SH3319NM SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Precise Flight PulseLite Control System.<br />
Adding MDHI 369 and 500Nmodels.<br />
10<strong>01</strong>6859 PRECISE FLIGHT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>235 FAA STC SA007<strong>01</strong>SE ROBINSON R22 & R44 Installation of Precise Flight Pulslite System in<br />
accordance with Precise Flight, Inc.<br />
Engineering drawings 590P00<strong>01</strong>, Rev. -,<br />
dated26 January, 1999 and 590P0002, Rev. -,<br />
dated 26 January 1999 or later approved<br />
revision in Robinson R22 model or R44 model<br />
he<br />
10<strong>01</strong>7060 PRECISE FLIGHT, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>494 FAA STC SR<strong>01</strong>821SE R22 MARINER<br />
R22, R22 ALPHA, R22 BETA<br />
Installation of a Precise Light HID Aviation<br />
Lighting System according to FAA STC<br />
SR<strong>01</strong>821SE.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>2<br />
Prior to installation of this modification it 03.08.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the productIf the h<br />
Approval for the physical installation of the Prior to installation of this modification it 08.<strong>04</strong>.2<strong>01</strong>1<br />
PulseLite Control Unitwill be required if there is must be determined thatthe<br />
no specific reference provided inEngineering interrelationship between this modification<br />
Drawing List 0<strong>01</strong>P00<strong>01</strong>, revision B, dated May and any other previouslyinstalled<br />
1, 2002, orlater FAA approved revision. modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 361/<strong>462</strong><br />
20.07.2007<br />
14.11.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035215 PRECISE FLIGHT, Inc. FAA STC SA2622NM FALCON 50 Installation of Precise Flight Pulse Light Control This approval is restricted to the following Prior to installation of this modification it 06.06.2<strong>01</strong>1<br />
system in Falcon 50aircraft.<strong>EASA</strong> validation of Pulselite units:2400-25-4-4 / 2400-25-4-4-1 / must be determined thatthe<br />
FAA STC SA2622NM for Falcon 50 aircraft. 2400-25-4-4-2 / 24<strong>01</strong>S / 24<strong>01</strong>.This approval interrelationship between this modification<br />
does not cover the physical installation of the and any other previouslyinstalled<br />
system.Physical installation of the system in the modification and/ or repair will introduce<br />
aircraft should be dulys<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5539 PRECISION CONVERSIONS LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>423 ST1529SE BOEING 757-200 SERIES Conversion from Passenger to Freighter<br />
Configuration (including Main Deck Cargo<br />
Door, Crew Entry Door, Interior & Associated<br />
Systems.<br />
27.10.2006<br />
10<strong>01</strong>4487 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.A.S.02549 BEECH 390 Satellite Telephone Installation 11.05.2006<br />
10<strong>01</strong>7110 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>087 AS 365N2 Premiair Aircraft Engineering Modification 05-<br />
<strong>01</strong>0.KLN 900 GPS Receiver Installation.<br />
10<strong>01</strong>7111 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>088 AS 365N2 Premiair Aircraft Engineering Modifications 05-<br />
007 & 05-009. Modifications embodied, since<br />
manufacture, in Brazil & South Africa. Also<br />
modifications embodied to meet <strong>EASA</strong> & JAR<br />
OPS-3 requirements.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Aircraft Serial No. 6393 Only2. This STC<br />
is approved only for the product configuration<br />
as defined in the approved design data<br />
referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>7121 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>208 AS 355N IFR Upgrade with EFIS 40 Installation 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>7155 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>261 REV. 2 AS365N2, AS365N3, SA365N1 Installation of Honeywell MK XXI EGPWSNote:<br />
This revision is to amend an existing <strong>EASA</strong><br />
STC (RefP-<strong>EASA</strong>.R.S.<strong>01</strong>261 rev. 1) to add the<br />
AS 365N3 model<br />
None This STC is approved only for the product<br />
configuration as defined inthe approved<br />
design data referred to in the paragraphs<br />
"Description" and"Associated Technical<br />
Documentation" Prior to installation of this<br />
modification it must be determined<br />
thatthe inter<br />
10<strong>01</strong>7160 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>268 AS 355 F1 Install a Honeywell KLN90B GPS -- 07.07.2006<br />
10<strong>01</strong>7174 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>289 REV. 2 AS365N2, AS365N3, SA365N1 Installation of Honeywell KTA 870 Traffic None This STC is approved only for the product <strong>01</strong>.02.2<strong>01</strong>0<br />
Advisory SystemNote: This revision is to<br />
configuration as defined inthe approved<br />
amend an existing <strong>EASA</strong> STC (RefP-<br />
design data referred to in the paragraphs<br />
<strong>EASA</strong>.R.S.<strong>01</strong>289 rev. 1) to add the AS365N3<br />
"Description" and"Associated Technical<br />
model<br />
Documentation" Prior to installation of this<br />
modification it must be determined<br />
thatthe inter<br />
10<strong>01</strong>7175 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>290 REV. 2 AS365N2, AS365N3, SA365N1 Installation of Honeywell KMD 850 Multi<br />
Function DisplayNote: This revision is to amend<br />
an existing <strong>EASA</strong> STC (RefP-<br />
<strong>EASA</strong>.R.S.<strong>01</strong>290 rev. 1) to add the AS 365N3<br />
model<br />
10.08.2005<br />
11.08.2005<br />
16.11.2005<br />
<strong>01</strong>.02.2<strong>01</strong>0<br />
None This STC is approved only for the product <strong>01</strong>.02.2<strong>01</strong>0<br />
configuration as defined inthe approved<br />
design data referred to in the paragraphs<br />
"Description" and"Associated Technical<br />
Documentation" Prior to installation of this<br />
modification it must be determined<br />
thatthe inter<br />
10<strong>01</strong>7227 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>397 S-76B Traffic Advisory System Installation. 26.05.2008<br />
10<strong>01</strong>7233 PREMIAIR AIRCRAFT ENGINEERING <strong>EASA</strong>.R.S.<strong>01</strong>411 AS 355 N Installation of a Honeywell KMD850<br />
Prior to installation of this modification the<br />
05.11.2007<br />
Multifunction Display replacing the existing installer must determine that the<br />
IN812A Radar Indicator plus GC360 Radar interrelationship between this modification and<br />
Graphics Computer and Interfacing with an any other previously installed modification will<br />
existing Honeywell RDR2000.<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10027205 PREMIAIR AIRCRAFT ENGINEERING P-<strong>EASA</strong>.A.S.03982 BEECH 390 (PREMIER 1) Cabin configuration change None Prior to installation of this modification the 14.09.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 362/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039783 PREMIAIR AIRCRAFT ENGINEERING A-60+ Installation of Cabin Safety Equipment None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.05.2<strong>01</strong>2<br />
10<strong>01</strong>5562 PREMIER AIR CENTER, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>460 ST<strong>01</strong>884CH FAN JET FALCON SERIES D<br />
FAN JET FALCON SERIES E<br />
FAN JET FALCON SERIES F<br />
MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
MYSTERE FALCON 20-F5<br />
MYSTERE FALCON 200<br />
10027600 PREMIER AIRCRAFT, LLC P-<br />
<strong>EASA</strong>.IM.A.S.02677<br />
10029073 PROTOPLANE SPECIAL MISSION<br />
AIRCRAFT<br />
10034751 PROTOPLANE SPECIAL MISSION<br />
AIRCRAFT<br />
10038293 PROTOPLANE SPECIAL MISSION<br />
AIRCRAFT<br />
10038491 PROTOPLANE SPECIAL MISSION<br />
AIRCRAFT<br />
10039039 PROTOPLANE SPECIAL MISSION<br />
AIRCRAFT<br />
10039373 PROTOPLANE SPECIAL MISSION<br />
AIRCRAFT<br />
FAA STC ST<strong>01</strong>951LA MF50 BASIC CONFIGURATION <strong>EASA</strong> Validation of FAA STC<br />
ST<strong>01</strong>951LA:Installation of TFE731-4-1C<br />
engine part number 3075900-1, per<br />
HoneywellService Bulletin TFE731-72-3703,<br />
dated January 19, 2007 on the MF50basic<br />
aircraft configuration in accordance with Flight<br />
Test Associates,Inc. Maste<br />
Installation of a Honeywell Mark VIII Enhanced 1. <strong>EASA</strong> approved Flight Manual Supplement,<br />
Ground Proximity Warning System with Terrain Premier Air Center Document 11-327B0<strong>01</strong>,<br />
Display<br />
Revision I/R, or later <strong>EASA</strong> approved revision<br />
isa required part of this STC (Configuration-<br />
<strong>01</strong>)2. <strong>EASA</strong> approved Flight Manual<br />
Supplement, Premier Air Center Document 11-<br />
327B0<br />
Not Applicable Flight Manual Supplement FTA-PA-<br />
0<strong>01</strong><strong>01</strong>9, Revision IR dated 22nd<br />
January2007 was found to contain<br />
incorrect data and has been replaced<br />
withFlight Manual Supplement FTA-PA-<br />
0<strong>01</strong><strong>01</strong>9, Revision C dated 30th<br />
September2009. All Revision IR Flight<br />
Manuals have been r<br />
<strong>EASA</strong>.A.S.03952 BEECH 200 Video transmission mast under a Beech 200. All associated Audio/Video Relay electronic<br />
systems and antennas must beturned off<br />
during VOR navigation and before beginning<br />
the approach.<br />
AS 350 B, -D, -B1, -B2<br />
AS 350 BA, -BB, -B3<br />
BN-2 BEZU installation on a BN-2 rev2 du<br />
27/<strong>01</strong>/2<strong>01</strong>2.<br />
AS355E, AS355F, AS355F1<br />
AS355F2, AS355N, AS355NP<br />
29.06.2006<br />
13.10.2009<br />
Prior to installation of this modification it <strong>01</strong>.03.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of video transmission equipment. None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
28.<strong>04</strong>.2<strong>01</strong>1<br />
Video transmission equipment When antenna holder PP-10-A6<strong>01</strong> is installed<br />
VNE is limited to 120 kts;When rack PP-10-<br />
A421 is installed, carriage of passengers in<br />
front seatsis prohibited;When racks PP-10-<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.02.2<strong>01</strong>2<br />
Prior to installation of this modification it 21.02.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
A4<strong>01</strong>c or PP-A461 are installed, a maximum of modification and/ or repair will introduce<br />
2passengers in rear seats is permitted no adverse effectupon the airworthiness<br />
of the product. The ap<br />
EC135 T1, T2, T2+, P1, P2, P2+ Installation of a Max-Viz EVS 1500 vision Limited to EC135 equipped with CPDS and<br />
enhancement system.Installation of EVS 1500 FCDS.<br />
system for Protoplane change project PP-<strong>01</strong>5<br />
asdefined in PP-<strong>01</strong>5-MDL-<strong>01</strong>.<br />
Prior to installation of this modification it 02.<strong>04</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
MF50 Attachment provisions on Falcon 50 S/N <strong>01</strong>1. Limited to S/N <strong>01</strong>1. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.<strong>04</strong>.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 363/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0578 PROTOPLANE SPECIAL MISSION<br />
208B Installation of Video Transmission Unit in Installer must check availability of <strong>EASA</strong>- The installation of this modification by 11.07.2<strong>01</strong>2<br />
AIRCRAFT<br />
accordance with Master DataList PP-008-MDL- approval for one or morereferenced STC when third persons is subject towritten<br />
<strong>04</strong>, Issue 4, dated 11. July 2<strong>01</strong>2 or later airplane is modified per that / those STC(s). permission of the approval holder and<br />
approvedrevision.<br />
disposal of the approvedappropriate<br />
,,documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
10<strong>04</strong>0714 PROTOPLANE SPECIAL MISSION<br />
B200C Removing of the metal parts of a cargo pod Limited to serial numbers BL 49 and BB 1473It This STC is applicable to aircraft B200C 23.07.2<strong>01</strong>2<br />
AIRCRAFT<br />
and provisions for theinstallation of signal is forbidden to use the modified pod to carry modified with an externalbaggage/cargo<br />
transmission antennas inside the pod. baggage or cargo.This modification does not carrier "Super 60 pod" as per FAA STC<br />
include power to the antennas installed onthe SA24551CE, <strong>EASA</strong>grandfathered<br />
pod. The operation of the antennas is not through LBA STC 321/2/92.Prior to<br />
include in this approvaland must<br />
installation of this modification it must be<br />
determined thatthe interrelati<br />
10<strong>01</strong>5666 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.<strong>01</strong>642 REV 3 ST<strong>01</strong>468SE LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
10<strong>01</strong>6131 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02325 STC ST<strong>01</strong>724SE DATED JANUARY<br />
5T<br />
10<strong>01</strong>6246 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02521 REV. 2 FAA STC SA3593NM KING AIR 65-A90, B90, C90<br />
KING AIR 65-C90A, C90GT,<br />
C90GT<br />
KING AIR 65-C90GTI, E90<br />
10<strong>01</strong>6579 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02983 FAA STC SA2939NM BEECH 65-90<br />
BEECH 65-A90<br />
BEECH B90<br />
BEECH C90<br />
BEECH C90A<br />
10<strong>01</strong>6580 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02984 FAA STC ST3857NM BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH A200<br />
BEECH A200C<br />
BEECH A200CT<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
10<strong>01</strong>6581 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02985 FAA STC SA3831NM BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH A200<br />
BEECH A200C<br />
BEECH A200CT<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
10<strong>01</strong>6582 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02987 REV. 2 FAA STC SA4<strong>01</strong>0NM 1. 65-90, 65-A90, B90, E90<br />
2. C90A, C90GT, C90GTI<br />
10<strong>01</strong>6583 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02988 FAA STC SA3366NM BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH A200<br />
BEECH A200C<br />
BEECH A200CT<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200CT<br />
BEECH B200T<br />
Installation of drag reduction system (including<br />
outboard trailing edge extension, leading edge<br />
vortilons & contoured flap).<br />
21.08.2006<br />
LEARJET 31 Installation of a drag reduction system<br />
(contoured flap).<br />
22.11.2007<br />
Installation of propeller system. 1. See attached Propellers and Propeller Prior to installation of this modification it 06.09.2<strong>01</strong>0<br />
Limitations 2. Hartzell HC-D4N-3C hubs with must be determined thatthe<br />
Hartzell D9290K blades in pairs.Diameter 93.0 interrelationship between this modification<br />
in. (maximum); minimum allowable for repair: and any other previouslyinstalled<br />
92.0 in. Nofurther reduction in diameter modification and/ or repair will introduce<br />
permitted. Pitch Settings: Low Pitch: 2 no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of nacelle overwing storage lockers<br />
and lower flap fairing.<br />
Installation of nacelle overwing storage lockers<br />
and lower flap fairing.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of improved leading edge consisting Prior to installation of this modification the<br />
of inboard leading edges, deice boots, leading installer must determine that the<br />
edge ducts, leading edge to nacellefairing, and interrelationship between this modification and<br />
associated hardware.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of dual aft body strakes on the 90<br />
series King Air aircraftper Raisbeck<br />
Engineering Inc. STC SA4<strong>01</strong>0 NM.<br />
05.08.2008<br />
05.08.2008<br />
05.08.2008<br />
none Prior to installation of this modification the 26.<strong>04</strong>.2<strong>01</strong>1<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
Installation of Ram Air Recovery System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 364/<strong>462</strong><br />
05.08.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6599 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.03<strong>01</strong>2 REV. 1 FAA STC ST3591NM 200, 200C, 200T, 200CT, A200, Installation of lower aft fuselage strakes. None Prior to installation of this modification the <strong>01</strong>.07.2<strong>01</strong>1<br />
A200C, A200CT, B200, B200C,<br />
installer must determinethat the<br />
B200GT, B200CGT<br />
interrelationship between this modification<br />
B200T, B200T, B200CT,<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>6620 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.03051 FAA STC ST00752SE BEECH 200<br />
This change applies only to the above listed Requires the prior incorporation of Raisbeck<br />
15.12.2008<br />
SEE ATTACHED <strong>EASA</strong><br />
model aircraft in accordance with Raisbeck STC’s ref:-SA4175NM (when equipped with<br />
APPROVED TYP<br />
Engineering Master Drawing List 99-1500, High Floatation<br />
Revision D, dated May 13, 2008 or later gear)SA3366NMSA3831NMSA3519NMIt is<br />
approved revisions.<br />
the installers responsibility to ensure all these<br />
referenced STC’s are <strong>EASA</strong> approved.<br />
1003<strong>01</strong>24 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.02986 REV. 3 FAA STC SA4175NM 200, 200C, 200T, 200CT, A200<br />
A200C, A200CT, B200, B200C<br />
B200T, B200CT, B200GT,<br />
B200CGT<br />
B300, B300C<br />
Installation of fully enclosed main landing gear<br />
door system forhigh-flotation gear equipped<br />
aircraft.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>1<br />
10031275 RAISBECK ENGINEERING <strong>EASA</strong>.IM.A.S.00765 REV. 1 FAA STC SA2698NM-S BEECH 200, A200, B200 Installation of Hartzell/Raisbeck Quiet Turbofan Data is suitable for reproduction and installation Prior to installation of this modification it 09.08.2<strong>01</strong>0<br />
Propeller. Thisinstallation consists of Hartzell 4- on all Beech SuperKing Model 200 series must be determined thatthe<br />
bladed propellers and aluminum hubswith aircraft. Approval of this change in type interrelationship between this modification<br />
spinners, and a propeller de-icing system designapplies to the above model aircraft only and any other previouslyinstalled<br />
This approval should not be extended to other modification and/ or repair will introduce<br />
aircraft on which otherpreviou<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031307 RAISBECK ENGINEERING FAA STC ST<strong>01</strong>182LA A320-232 A320 bin extension systemInstallation of a bin<br />
extension system in accordance with<br />
FAASupplemental Type Certificate<br />
ST<strong>01</strong>182LA issued 10 July 20<strong>01</strong>.<br />
10027805 RAM AIRCRAFT, LIMITED<br />
PARTNERSHIP<br />
10031425 RAM AIRCRAFT, LIMITED<br />
PARTNERSHIP<br />
10031513 RAM AIRCRAFT, LIMITED<br />
PARTNERSHIP<br />
10032348 RAM AIRCRAFT, LIMITED<br />
PARTNERSHIP<br />
- Refer to paragraph "Limitations & Conditions"<br />
listed in the FAA STCST<strong>01</strong>182LA;The<br />
Maintenance Instructions for Continued<br />
Airworthiness are containedin the RCAG<br />
Component Maintenance Manual 200A-2560.<br />
These maintenanceinstructions must be<br />
included in the o<br />
Prior to installation of this modification it 09.08.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
FAA STC SE10746SC-D IO-520-B -, -BB, -C, -CB Conversion of Teledyne Continental Motors The RAM model IO-550-B-RA engine is This approval should not be extended to 17.11.2009<br />
(TCM) models IO-520-B, -BB toRAM model IO- identical to and has the sameratings,<br />
other engines of these models onwhich<br />
550-B-RA engine, or conversion of TCM limitations, and installation interfaces as TCM other previously approved modifications<br />
models IO-520-C, -CBto RAM model IO-550-C- model IO-550-Bengine. The RAM model IO- are incorporated unless itis determined by<br />
RA engine in accordance with RAM Master 550-C-RA is identical to and has the<br />
the installer that the interrelationship<br />
DrawingList 2691, Revision I.R. dated sameratings, limitations, and installation between thischange and any other<br />
November 7, 20<br />
interfaces as T<br />
previously approved m<br />
REV. 2 FAA STC SA8125SW-D CESSNA 414A Installation of vortex generators in acc. with None See under "Description" Prior to 12.11.2<strong>01</strong>0<br />
FAA STC SA8125SW-D, lastissue, dated May<br />
installation of this modification it must be<br />
12, 2008:Option 1: Modification in acc. with<br />
determined thatthe interrelationship<br />
RAM Master Drawing No. 1507,Revision C,<br />
between this modification and any other<br />
dated 11/03/1992.Option 2: Modification in acc.<br />
previouslyinstalled modification and/ or<br />
with RAM Master Drawing No. 1507,Re<br />
repair will introduce no adverse<br />
effectupon the airworthines<br />
REV. 1 FAA STC SA09105SC-D CESSNA 414A Modification in acc. with FAA STC SA09105SC-This<br />
approval is limited to Hartzell PHC-C3YF- Prior to installation of this modification it 12.11.2<strong>01</strong>0<br />
D: Aircraft modified inaccordance with RAM 2UF/FC7663D(B)-2Q or PHC-C3YF- must be determined thatthe<br />
Master Drawing No. 1765, Revision B, 2UF/FC7693DF(B) propellers.<br />
interrelationship between this modification<br />
dated20/09/1995 and Installation of modified<br />
and any other previouslyinstalled<br />
TCM engine model TSIO-520-NB:Option 1:<br />
modification and/ or repair will introduce<br />
Cessna 414A modified by FAA STC<br />
no adverse effectupon the airworthiness<br />
SE091<strong>04</strong>SC-D or S<br />
of the product.<br />
REV. 1 FAA STC SA09971SC-D 1. CESSNA 340, 340A<br />
2. CESSNA 414, 414A, 402C<br />
Installation of Hartzell propeller PHC-C3YF-<br />
2UF/FC7693DF(B) inaccordance with FAA<br />
STC SA09971SC-D<br />
1. Hartzell Modell PHC-C3YF-2UF/FC7693DF Prior to installation of this modification it<br />
or PHC-C3YF-2UF/FC7693DFBpropellers are must be determined thatthe<br />
02.11.2<strong>01</strong>0<br />
limited to aircraft that are previously FAA interrelationship between this modification<br />
approved toinstall 78-inch (198 cm) diameter and any other previouslyinstalled<br />
propellers and have TCM model TSIO- modification and/ or repair will introduce<br />
520series engines with maximum rated power no adverse effectupon the airworthiness<br />
from 285<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 365/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10038286 RAM AIRCRAFT, LIMITED<br />
CESSNA 414 Modification of Cessna 414 in acc. with FAA This approval is limited to Hartzell<br />
None 03.02.2<strong>01</strong>2<br />
PARTNERSHIP<br />
STC SA09469SC-D: Aircraftmodified in<br />
accordance with RAM Master Drawing No.<br />
1982, Revision K, FAAapproved September<br />
23, 2009 and Installation of modified TCM<br />
enginemodel TSIO-520-NB in accordance with<br />
FAA STC SE0<br />
propellers:PHC-C3YF-2UF/FC7663D(B)-2Q<br />
10<strong>01</strong>5448 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>191 FAA STC SA<strong>01</strong>129AT-D RAYTHEON 1900C Installation and peration of a Lockheed 1.FAA approved Airplane Flight Manual<br />
31.08.2005<br />
Martin/Fairchild FDR F1000, solid State flight Supplement AFMS96060, dated 18 APR 1997<br />
data Recorder installed.Master Drawing List or later approved revision, is a required part of<br />
MDL9606 Initial Revision, dated January 10, this STC.2. This STC is approved only for the<br />
1997 or later FAA approved revision.<br />
product configuration as defined in the<br />
approved design data referred to in the pa<br />
10<strong>01</strong>5506 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>384 FAA STC SA4899SW BOMBARDIER CL-600-2B16 Installation of Wulfsberg Flitefone IV/VI<br />
Communication System<br />
10<strong>01</strong>5507 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>385 SA5953SW BOMBARDIER CL-600-1A11 (CL- FAA STC SA5953SW. Installation of a nose<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
gear door ground release mechanism<br />
10<strong>01</strong>5508 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>386 SA7457SW BOMBARDIER CL-600-2B16 FAA STC SA7457SW. Installation of Sperry<br />
LSZ-850 Lightning Sensor System<br />
10<strong>01</strong>5509 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>387 FAA STC SA7583SW BOMBARDIER CL-600-2B16 Installation of Sperry Primus 870 Weather<br />
Radar System<br />
10<strong>01</strong>5510 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>388 FAA STC SA7871SW BOMBARDIER CL-600-2B16 FAA STC SA7871SW. Installation of air driven<br />
generator inspection window<br />
10<strong>01</strong>5511 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>389 FAA STC SA7878SW BOMBARDIER CL-600-2B16 Installation of a DPI Labs 1800 Membrane<br />
Switch Control System<br />
10<strong>01</strong>5512 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>390 FAA STC SA7881SW BOMBARDIER CL-600-2B16 FAA STC SA7881SW. Installation of Sensor<br />
S67-1572 Global Positioning Antenna<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5513 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>391 FAA STC SA7880SW BOMBARDIER CL-600-2B16 Installation of an alternate location for the refuel<br />
panel<br />
25.07.2005<br />
10<strong>01</strong>5514 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>392 FAA STC SA7873SW BOMBARDIER CL-600-2B16 FAA STC SA7873SW. Installation of a cockpit<br />
Overhead Panel Extension<br />
25.07.2005<br />
10<strong>01</strong>5515 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>393 FAA STC SA7872SW BOMBARDIER CL-600-2B16 FAA STC SA7872SW. Installation of a cockpit<br />
Center Pedestal Extension<br />
25.07.2005<br />
10<strong>01</strong>5516 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>394 FAA STC SA7869SW BOMBARDIER CL-600-2B16 FAA STC SA7869SW. Installation of access<br />
door<br />
25.07.2005<br />
10<strong>01</strong>5517 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>395 FAA STC SA7870SW BOMBARDIER CL-600-2B16 FAA STC SA7870SW. Installation of a Rosen<br />
Sun Visor System<br />
25.07.2005<br />
10<strong>01</strong>5518 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>396 FAA STC SA7879SW BOMBARDIER CL-600-2B16 Installation of a cabin emergency lighting<br />
system<br />
25.07.2005<br />
10<strong>01</strong>5519 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>397 FAA STC SA7886SW BOMBARDIER CL-600-2B16 Installation of a cabin oxygen system 11.08.2005<br />
10<strong>01</strong>5520 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>398 FAA STC SA7887SW BOMBARDIER CL-600-2B16 Installation of a Cabin Water System 25.07.2005<br />
10<strong>01</strong>5521 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>399 SA3703SW BOMBARDIER CL-600-2B16 FAA STC SA3703 SW. Installation of Thrust<br />
Reverser Access Panel in the Lower Nacelle<br />
10<strong>01</strong>5522 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>400 FAA STC SA4900SW BOMBARDIER CL-600-2B16 FAA STC SA4900SW.Installation of Dual<br />
Baker M1<strong>04</strong>5 Cockpit Audio Systems with a<br />
Baker M1050 Cabin Paging/Chime Amplifier<br />
10<strong>01</strong>5523 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>4<strong>01</strong> FAA STC SA7460SW BOMBARDIER CL-600-2B16 Installation of Honeywell CG1230AC10<br />
Lasertrack Navigation System<br />
10<strong>01</strong>5524 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>402 FAA STC SA5718SW BOMBARDIER CL-600-1A11 (CL- Installation of Airshow 100/200 Cabin Video<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
System<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 366/<strong>462</strong><br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005<br />
25.07.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5525 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>403 SA5830SW BOMBARDIER CL-600-1A11 (CL- FAA STC SA5830SW. Installation of Radio<br />
25.07.2005<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Master Switch System<br />
10<strong>01</strong>5526 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>4<strong>04</strong> SA7451SW BOMBARDIER CL-600-2B16 Installation of a Dual EFIS Master Switch<br />
System<br />
25.07.2005<br />
10<strong>01</strong>5527 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>405 FAA STC SA7454SW BOMBARDIER CL-600-2B16 Installation of Shepherd Security System 25.07.2005<br />
10<strong>01</strong>5528 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>406 FAA STC SA7459SW BOMBARDIER CL-600-2B16 Installation of a Dual FMS Master Switch<br />
System<br />
10<strong>01</strong>5915 RCM NORMALIZING <strong>EASA</strong>.IM.A.S.02<strong>04</strong>5 SA5202NM COMMANDER AIRCRAFT 112 Validation of FAA STC SA5202NM: Installation<br />
of Lycoming engine model IO-360-C1D6<br />
modified in accordance with STC SE5203NM<br />
& Propeller Hartzell HC-E3YR-1RF/F7392.<br />
10<strong>01</strong>6700 RCM NORMALIZING <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>4 FAA STC SE5203NM LYCOMING ENGINES IO-360-<br />
C1D6<br />
Installation of turbocharger and induction air<br />
intercooler in accordance with “Drawing List<br />
Report No. 1” dated August 20, 1990, orlater<br />
FAA approved revision.<br />
10<strong>01</strong>4230 RECTIMO AVIATION <strong>EASA</strong>.A.S.<strong>01</strong>393 PIPER PA-28-181, ARCHER III GNS 430 installation with MD 41-1488 (HSI<br />
and AP coupled)Installation of GNS 430 and<br />
MD 41-1488 coupled with KI 525A<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
25.07.2005<br />
See AFM Supplement No. 1. 25.06.2007<br />
Compatibility of this design change with<br />
previously approved modifications must he<br />
determined by the installer. The installation<br />
should not be incorporated in any engine<br />
unless it is determined that the interrelationship<br />
between this installation and any p<br />
Limited to S/N 2843066 F-GSMDGPS use is<br />
forbidden for BRNAV and approachAuto Pilot<br />
coupling is forbidden under 2000 ft AGL<br />
10<strong>01</strong>5<strong>01</strong>5 RECTIMO AVIATION <strong>EASA</strong>.A.S.03319 PARTENAVIA P68C Installation of a COM/NAV/GPS GARMIN GNS This STC is limited to the S/N 279.<br />
430 (BRNAV without coupling to the auto-pilot)<br />
a COM/NAV GARMIN SL 30, a stormscope L3<br />
WX 500 and an ELT ARTEX ME 406.<br />
22.<strong>01</strong>.2008<br />
10<strong>01</strong>5112 RECTIMO AVIATION <strong>EASA</strong>.A.S.03459 PIPER PA-28R-2<strong>01</strong>T Replacement of : King KX155, KI209 and Applicable to S/N 7803232 F-GHYY.GPS use<br />
Garmin GPS 155 by Garmin GNS430 coupled is limited to Day VFR flights in sight of ground<br />
to HSI and autopilot. Installation of a RMI KI<br />
229.Removal of King KX155, KI209 and<br />
Garmin GPS 155 Installation of King RMI KI<br />
229, Garmin GNS 430 with MD 41 coupled to<br />
HSI KI5<br />
or water.<br />
10034509 REGENT AEROSPACE CORPORATION FAA STC ST02274LA B777-222 Interior modifications in accordance with<br />
Regent Aerospace CorporationMaster Data<br />
List MDL-4100, Revision E, dated November<br />
25, 2009. FAA STCST02274LA refers.<br />
Limited to B777-222 aircraft serial number<br />
30214 only<br />
31.05.2007<br />
20.07.2007<br />
22.09.2008<br />
Prior to installation of this modification it 08.<strong>04</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6335 REVUE THOMMEN AG <strong>EASA</strong>.IM.A.S.02644 FAA STC ST10685SC LEARJET 60 Installation of Revue Thommen 3A43 Standby<br />
Altimeter.<br />
12.03.2008<br />
10<strong>01</strong>6337 REVUE THOMMEN AG <strong>EASA</strong>.IM.A.S.02646 FAA STC ST10684SC LEARJET 45 Installation of Revue Thommen 3A43 Standby<br />
Altimeter.<br />
12.03.2008<br />
10<strong>01</strong>5602 ROCKWELL COLLINS AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>538 ST<strong>01</strong>205NY BOMBARDIER CL-600-2B16 Installation of Head Up Guidance System<br />
(HGS) Model 2100 (Phase 2)<br />
15.08.2005<br />
10<strong>01</strong>6646 ROCKWELL COLLINS AEROSPACE <strong>EASA</strong>.IM.A.S.03089 REV. 2 FAA STC ST<strong>01</strong>100SE DHC-8-4<strong>01</strong> & DHC-8-402 Updates for Flight Management System (FMS) None<br />
HGS 4100.FAA acceptance letter 130S-09-<br />
387, dated 21.09.2009.<br />
None 12.<strong>04</strong>.2<strong>01</strong>0<br />
10<strong>01</strong>5727 ROCKWELL COLLINS AEROSPACE & <strong>EASA</strong>.IM.A.S.<strong>01</strong>743 REV. 3 FAA STC ST<strong>01</strong>390LA CL-600-2C10, CL-600-2D15 Installation of Head-Up Guidance System None Prior to installation of this modification it 21.<strong>04</strong>.2<strong>01</strong>1<br />
CL-600-2D24, CL-600-2E25 (HGS) Model 4200.Addition of CL-600-2E25<br />
must be determined thatthe<br />
(CRJ 1000) to HGS 4200 STC<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6677 ROCKWELL COLLINS AEROSPACE & <strong>EASA</strong>.IM.A.S.03193 FAA STC ST0<strong>01</strong>29SE BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
Validation of the FAA STC ST0<strong>01</strong>29SE for the<br />
HGS 2800 on the Dash 8-100/200/300 Series<br />
Aircraft (editorial change).<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 367/<strong>462</strong><br />
27.<strong>04</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5761 ROCKWELL COLLINS Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>797 FAA STC ST<strong>01</strong>903LA BOEING 777-200 Total Entertainment System.Index List Limited to B777-200 models operated by<br />
19.<strong>01</strong>.2007<br />
13<strong>04</strong>641 rev new dated 2 August<br />
2006.Modification comprises a software<br />
upgrade to the VMOD, re-identification of the<br />
VMOD and re-installation in the Video Control<br />
Centre.<br />
British Airways plc.<br />
10<strong>01</strong>6243 ROCKWELL COLLINS Inc. <strong>EASA</strong>.IM.A.S.02517 FAA STC ST02055LA AIRBUS A330-203 IFE VMOD upgrade per System List 1310929-<br />
0<strong>01</strong>/IFE VMOD Upgrade consists of removing<br />
the existing VMOD and re-installing an<br />
upgraded VMOD in the Video Control Center<br />
(VCC).<br />
20.11.2007<br />
10<strong>01</strong>6244 ROCKWELL COLLINS Inc. <strong>EASA</strong>.IM.A.S.02518 FAA STC ST02056LA AIRBUS A340-311<br />
IFE VMOD upgrade per System List 1310930- Prior to installation of this modification the<br />
<strong>04</strong>.10.2007<br />
AIRBUS A340-313<br />
0<strong>01</strong>/IFE VMOD Upgrade consists of removing installer must determine that the<br />
the existing VMOD and re-installing an interrelationship between this modification and<br />
upgraded VMOD in the Video Control Center any other previously installed modification will<br />
(VCC).<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6670 ROCKWELL COLLINS Inc. <strong>EASA</strong>.IM.A.S.03156 FAA STC NO. SA5098NM AIRBUS A320-232 Installation of Sony Trans Com Inc. Video<br />
Entertainment System<br />
10030815 ROCKWELL COLLINS INC. FAA STC NO. ST<strong>01</strong>838LA B747-400 SERIES Installation of Rockwell Collins enhanced Total<br />
Entertainment System inaccordance with<br />
System List 1309713-002/-0<strong>04</strong>, Revision Y,<br />
datedSeptember 8, 2005 or later FAA<br />
approved revisions.Validation of FAA STC<br />
ST<strong>01</strong>838LA<br />
10031359 ROCKWELL COLLINS INC. FAA STC ST<strong>01</strong>829LA B747-400 Installation of Rockwell Collins enhanced Total<br />
Entertainment System inaccordance with<br />
System List 13<strong>04</strong>631, Revision N/C, dated<br />
August16, 2005or later FAA approved<br />
revisions.Validation of FAA STC ST<strong>01</strong>829LA<br />
10<strong>01</strong>5340 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.00392 FAA STC ST<strong>01</strong>202WI-D,STC <strong>EASA</strong>.I SEE ATTACHED <strong>EASA</strong><br />
APPROVED TYP<br />
Modification of an existing FAA-approved<br />
Collins TPR-720, TPR-900 or TPR-9<strong>01</strong> Mode<br />
S transponder installation in Part 25 aircraft.<br />
10<strong>01</strong>5344 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.0<strong>04</strong>44 FAA STC ST00587WI-D BOEING 747-400 Modification of Collins ACARS DLM-700B<br />
Management Unit (MU) System Installation to<br />
Collins ACARS DLM-900 MU System<br />
Installation.<br />
10<strong>01</strong>5368 ROCKWELL COLLINS, INC. <strong>EASA</strong>.IM.A.S.0090 FAA STC SA5859NM A320 Installation of Video Entertainment System in<br />
accordance with FAA approved Hugues-<br />
Avicom Index list 607278, Revision "A", dated<br />
September 24, 1992, or later FAA approved<br />
revisions.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
None FAA STC ST<strong>01</strong>603SE must be installed<br />
in conjunction with thisinstallation<br />
none FAA STC ST<strong>01</strong>603SE must be installed<br />
in conjunction with thisinstallationPrior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will<br />
1. Prior installation and approval of a Collins<br />
TPR-720, TPR-900 or TPR-9<strong>01</strong> Mode S<br />
transponder is a prerequisite to this STC.2.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Des<br />
1. Collins ACARS DLM-700B Management<br />
Unit System Installation, <strong>EASA</strong> STC<br />
<strong>EASA</strong>.IM.A.S.0<strong>04</strong>43, is required to be installed<br />
prior to or concurrent with using this STC.2.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
d<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft configurations<br />
shall be determined by the installer.<br />
10<strong>01</strong>5380 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>062 FAA STC ST<strong>01</strong>713LA BOEING 747-400 Installation of Rockwell Collins enhanced Total 1. FAA STC ST<strong>01</strong>507SE must be installed in<br />
Entertainment System in accordance with FAA conjunction with this installation2. This STC is<br />
STC No ST<strong>01</strong>713LA issued February 12, 2005 approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engi<br />
10<strong>01</strong>5464 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>214 SA1930CE-D BEECH B300<br />
BEECH B300C<br />
Installation of Collins TCAS-94 TCAS II<br />
System.<br />
1. Installation of STC SA1929CE-D, mode S<br />
transponder (single or dual) is a prerequisite to<br />
this STC. 2.This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 368/<strong>462</strong><br />
29.<strong>04</strong>.2009<br />
08.07.2<strong>01</strong>0<br />
11.08.2<strong>01</strong>0<br />
29.03.2005<br />
21.12.20<strong>04</strong><br />
09.08.20<strong>04</strong><br />
<strong>01</strong>.03.2005<br />
20.08.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5530 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>409 ST00673WI-D BOMBARDIER CL-600-1A11 (CL- Modification of Collins VHF-22A/VHF-22B VHF<br />
26.07.2005<br />
600<br />
COMM Receiver Transmitter with CTL-22<br />
BOMBARDIER CL-600-2A12 (CL- Control Pro Line II System Installation to a<br />
6<strong>01</strong><br />
Collins VHF-22/VHF-22D VHF COMM<br />
BOMBARDIER CL-600-2B16 Receiver Transmitter with CTL-22C 8.33 khz<br />
Pro Line II System Installation<br />
10<strong>01</strong>5531 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>410 ST<strong>01</strong>142WI-D BOMBARDIER CL-600-1A11 (CL- Modification of a single or dual Collins TDR-94<br />
26.07.2005<br />
600<br />
or TDR-94D Mode S Transponder System<br />
BOMBARDIER CL-600-2A12 (CL- installation with CTL-92 control head to a Flight<br />
6<strong>01</strong><br />
ID capable Collins TDR-94 or TDR-94D Mode<br />
BOMBARDIER CL-600-2B16 S Transponder installation with CTL-92E<br />
control head<br />
10<strong>01</strong>5615 ROCKWELL COLLINS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>554 FAA STC SA3979NM B757-200 Installation of Trans Com Video Projection<br />
System<br />
20.06.2006<br />
10<strong>01</strong>5631 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>584 ST<strong>01</strong>745CH HAWKER HS 125-700A Installation of Rockwell Collins Traffic Alert and<br />
Collision Avoidance System (TCAS II) in<br />
Raytheon HS 125 Series 700A Aircraft<br />
06.12.2005<br />
10<strong>01</strong>5691 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>679 REV. 1 ST02837AT BOEING 737-600<br />
Installation of a Rockwell Collins CMU-900 In accordance with the 2755-AFM Rev A,<br />
31.07.2009<br />
BOEING 737-700<br />
Communications Management Unit, VHF-920 dated December 12, 2005, or later <strong>EASA</strong><br />
BOEING 737-800<br />
VDL Mode 2 Radio and the APM-900 Airplane approved Revisions.<br />
BOEING 737-900<br />
Personality Module to provide Controller Pilot<br />
Data Link Communications (CPDLC) Baseline<br />
1 services<br />
10<strong>01</strong>5735 ROCKWELL COLLINS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>758 FAA STC SA5135NM B737-800 Installation of Audio Video Entertainment The limitations according to FAA STC<br />
17.08.2006<br />
System with Rockwell Collins System No.<br />
1309667-100 and 1310244-0<strong>01</strong> according to<br />
FAA STC SA5135NMRemark: Only 1 <strong>EASA</strong><br />
STC to be issued by Programmes Department<br />
to cover both applications (working hours<br />
information f<br />
SA5135NM apply.<br />
10<strong>01</strong>5906 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02032 ST00525WI-D Modification of Collins 618M-3/618m-4 VHF<br />
COMM Receiver Transmitter Installation to a<br />
618M-5 VHF COMM Receiver Transmitter<br />
Installation with either a Gables G7406-02 or<br />
Avtech 7522-1-2-VHF COMM Receiver<br />
Transmitter.<br />
31.07.2006<br />
10<strong>01</strong>5943 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02085 SA2656CE BOEING 747-100<br />
Collins traffic alert and collision avoidance 1. Installation of Collins Mode S Transponder ,<br />
<strong>01</strong>.02.2007<br />
BOEING 747-100B SUD<br />
system (TCAS II)<br />
per STC SA2636CE (P-<strong>EASA</strong>. IM.A.S.02087)<br />
BOEING 747-200B<br />
is a prerequisite to this modification.2. ACC-90-<br />
BOEING 747-200C<br />
113, Airplane Flight Manual Supplement3. 992-<br />
BOEING 747-200F<br />
BOEING 747-300<br />
BOEING 747-SP<br />
BOEING 747-SR<br />
1944-0<strong>01</strong>, Drawing Index<br />
10<strong>01</strong>5944 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02086 SA2676CE BOEING 747-100<br />
Collins traffic alert and collision avoidance Installation of Collins Mode S Transponder, per<br />
<strong>01</strong>.02.2007<br />
BOEING 747-100B SUD<br />
system (TCAS II)<br />
STC SA2636CE (P-<strong>EASA</strong>.IM.A.S.02087) is a<br />
BOEING 747-200B<br />
prerequisite to this modification.Aircraft Flight<br />
BOEING 747-200C<br />
Manual Supplement ACC-99-<strong>04</strong>2/-43/-44/-<br />
BOEING 747-200F<br />
45.Drawing Indexes 992-1978-0<strong>01</strong>, 992-1989-<br />
BOEING 747-300<br />
BOEING 747-SP<br />
BOEING 747-SR<br />
0<strong>01</strong>, and 992-2696-0<strong>01</strong>.<br />
10<strong>01</strong>5945 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02087 SA2636CE BOEING 747-100<br />
Dual Collins TPR-720 Mode S Transponder<br />
<strong>01</strong>.02.2007<br />
BOEING 747-100B SUD<br />
BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
BOEING 747-SP<br />
BOEING 747-SR<br />
System.<br />
10<strong>01</strong>6<strong>01</strong>3 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02179 FAA STC SA2685CE BOEING DC-9-81 (MD-81) Installation of Collins Traffic Alert and Collision Installation of Mode S Transponder System<br />
<strong>04</strong>.<strong>01</strong>.2007<br />
BOEING DC-9-82 (MD-82) Avoidance System (TCAS II)<br />
STC <strong>EASA</strong>.IM.A.S.02180 (SA2684CE) or<br />
BOEING DC-9-83 (MD-83)<br />
<strong>EASA</strong>. IM.A.S.02181 (SA3082SO) is a<br />
BOEING DC-9-87 (MD-87)<br />
BOEING MD-88<br />
prerequisite to this modification.<br />
10<strong>01</strong>6<strong>01</strong>4 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02180 FAA STC SA3082SO BOEING DC-9-81 (MD-81) Installation of Dual Collins TPR-720 Mode S None.Registration (if applicable):-Serialnumber<br />
<strong>04</strong>.<strong>01</strong>.2007<br />
BOEING DC-9-82 (MD-82)<br />
BOEING DC-9-83 (MD-83)<br />
BOEING MD-88<br />
Transponders<br />
(if applicable):-<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 369/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6<strong>01</strong>5 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02181 FAA STC SA2684CE BOEING DC-9-81 (MD-81) Installation of Dual Collins Mode S<br />
None.Registration (if applicable):-Serialnumber<br />
<strong>04</strong>.<strong>01</strong>.2007<br />
BOEING DC-9-82 (MD-82)<br />
BOEING DC-9-83 (MD-83)<br />
BOEING DC-9-87 (MD-87)<br />
BOEING MD-88<br />
DC-9-81 (MD-81)<br />
Transponders.<br />
(if applicable):-<br />
10<strong>01</strong>6059 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02236 ST<strong>01</strong>580AT-D BOEING 747-400 Installation of radio panels and Collins VHF ¿ Data package containing the following<br />
08.08.2007<br />
transceivers with 8.33 khz spacing in<br />
documents, and additional supporting data:¿<br />
accordance with Collins Master Data List MDL- MDL <strong>01</strong>237, rev. M: MDL Collins VHF700V/ -<br />
<strong>01</strong>237, revision M, dated August 9, 2005, or 900B in B747-400.¿ CFG-<strong>01</strong>296: installation<br />
later FAA approved revisions.<br />
of Collins VHF-700B communications system<br />
on B747-400 for Air France.¿ ENG-0<br />
10<strong>01</strong>6060 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02237 REV. 1 FAA STC ST02410CH-D BAE 125 SERIES 800A Installation of Rockwell Collins Pro Line 21 IDS<br />
(Integrated Display System) with IFIS-5000<br />
(Integrated Flight Information System) and<br />
Engine Instrument Display.<br />
10<strong>01</strong>6077 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02261 REV. 1 FAA STC ST<strong>01</strong>9<strong>01</strong>LA BOEING 767-200<br />
BOEING 767-300<br />
10<strong>01</strong>6202 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02444 FAA STC SA<strong>01</strong>267WI-D BEECH 300<br />
BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>6212 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02460 FAA STC ST<strong>01</strong>119WI-D CESSNA 750<br />
FALCON 10<br />
FALCON 900<br />
FALCON 900EX<br />
GULFSTREAM IV<br />
GULFSTREAM 1159 (G-II)<br />
GULFSTREAM 1159 A( G-II)<br />
GULFSTREAM 1159 B( G-II)<br />
HAWKER HS 125-700A<br />
HAWKER HS 125-700B<br />
MYSTERE FALCON 50<br />
10<strong>01</strong>6249 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02526 FAA STC ST00<strong>04</strong>0WI-D AIRBUS A320-111<br />
AIRBUS A320-211<br />
AIRBUS A320-212<br />
AIRBUS A320-231<br />
AIRBUS A320-232<br />
10<strong>01</strong>6273 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02558 FAA ST00392AT BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
10<strong>01</strong>6275 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02562 REV. 1 FAA STC ST<strong>01</strong>470LA-D 737-600, 737-700<br />
737-800, 737-900<br />
10<strong>01</strong>6287 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02582 REV. 1 FAA STC ST<strong>01</strong>927LA BOEING 757-200<br />
BOEING 757-300<br />
10<strong>01</strong>6378 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02702 FAA STC ST<strong>01</strong>454WI-D BOMBARDIER CL-600-2B19<br />
BOMBARDIER CL-600-2C10<br />
BOMBARDIER CL-600-2D15<br />
BOMBARDIER CL-600-2D24<br />
Installation of ARINC 718A MODE S<br />
Transponder Activation of Elementary and<br />
Enhanced Surveillance Capabilities.<br />
Installation of Collins Pro Line 21 Avionics<br />
System.<br />
Modification of Collins TDR-94 or TDR-94D<br />
Mode S Transponder System installation with<br />
stand-alone Collins TRU-4210 or RTU-4220<br />
Radio Tuning Unit(s) to a Flight ID capable<br />
Collins TDR-94 or TDR-94D Mode S<br />
Transponder System installation with standalone<br />
Col<br />
Installation of Collins Traffic Alert and Collision<br />
Avoidance System (TCAS II).<br />
Installation of Collins Duel TPR-720 Mode S<br />
Transponders.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
(1) Approval of this change in type design<br />
applies to the above model aircraft only.(2)<br />
Compatibility of this design change with<br />
previously approved modifications must be<br />
determined by the installer.(3) A copy of this<br />
Certificate and FAA Approved Model Lis<br />
Installation of a Collins TPR-720, TPR 900 or<br />
TPR-9<strong>01</strong> Mode S Transponder is a<br />
prerequisite to this modification.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
28.02.2008<br />
30.06.2008<br />
02.10.2008<br />
26.10.2007<br />
15.10.2007<br />
02.11.2007<br />
Installation of Rockwell Collins WXR-2100 Multi- None. Prior to installation of this modification the 08.07.2008<br />
scan (TM) Weather RadarSystem(Revision to<br />
installer must determinethat the<br />
the existing STC <strong>EASA</strong>.IM.A.S.02562 to<br />
interrelationship between this modification<br />
change the STC holdername and to add more<br />
and any otherpreviously installed<br />
models and correct the equipment reference<br />
modification will introduce no adverse<br />
name)<br />
effect uponthe airworthiness of the<br />
product.The installatio<br />
Installation of ARINC Characteristics 718A for Prior to installation of this modification the<br />
15.10.2007<br />
Mode S Transponder Activation of Elementary installer must determine that the<br />
and Enhanced Surveillance Capabilities. interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Modification of a Collins Control Display Unit,<br />
Installation, Type CDU-4100<br />
1. Prior installation and approval of a Collins<br />
Control Display Unit, type CDU-4100, is a<br />
prerequisite to this STC.2. Prior to installation<br />
of this modification the installer must determine<br />
that the interrelationship between this<br />
modification andany other<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 370/<strong>462</strong><br />
28.07.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6379 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02703 FAA STC ST<strong>01</strong>431WI-D SEE ATTACHED <strong>EASA</strong><br />
Modification of a Collins DBU-4000 or DBU- Prior to installation of this modification the<br />
15.10.2008<br />
APPROVED TYP<br />
4100 Data Base Unit installation to a Collins installer must determine that the<br />
DBU-5000 installation<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6395 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02724 FAA STC ST<strong>01</strong>452WI-D Modification of Collins FMS-5000 or FMS 6000 A prior installation and approval of a Collins<br />
and installation in Part 25 Airplanes i.a.w. FMS type FMS-5000 or FMS 6000 is a<br />
Drawing index as listed in AML Nr. ST<strong>01</strong>452WI- prerequisite to this STC. Refer to Collins<br />
D Rev- pr mater approved revisions approved Installation Instructions RCA-2447 in its latest<br />
by <strong>EASA</strong> i.a.w. <strong>EASA</strong> ED decision 20<strong>04</strong>/<strong>04</strong>/CF revision for approved FMC substitues.<br />
(or subsequent revision of this de<br />
10<strong>01</strong>6396 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02725 FAA STC ST00643WI-D BOEING 747-200B<br />
BOEING 747-200C<br />
BOEING 747-200F<br />
BOEING 747-300<br />
10<strong>01</strong>6397 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02726 FAA STC SA<strong>01</strong>430WI-D BEECH 390<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B300<br />
BEECH B300C<br />
PIAGGIO P 180<br />
SEE ATTACHED <strong>EASA</strong><br />
APPROVED TYP<br />
10<strong>01</strong>6398 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02727 FAA STC SA<strong>01</strong>453WI-D BEECH 300<br />
BEECH 390<br />
BEECH B200<br />
BEECH B300<br />
BEECH B300C<br />
CESSNA 525<br />
CESSNA 525A<br />
CESSNA 525B<br />
PIAGGIO P 180<br />
10<strong>01</strong>6517 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02888 FAA STC SA<strong>01</strong>434WI-D BEECH 390<br />
BEECH B200<br />
BEECH B200C<br />
CESSNA 525<br />
CESSNA 525A<br />
CESSNA 525B<br />
PIAGGIO P 180<br />
Modification of Collins 618M-3A VHF COMM<br />
R/T System Installation to Collins VHF-900B<br />
VHF COMM R/T System.<br />
Modification of a Collins DBU-4000 or DBU-<br />
4100 Data Base Unit installation to a Collins<br />
DBU-5000 Installation.<br />
Modification of a Collins Flight Management<br />
System type FMS-3000 Installed in Part 23<br />
Aircraft.<br />
Modification of Collins GPS-4000 or GPS-<br />
4000A Global Positioning Sensor (GPS)<br />
system installation to a Collins GPS-4000S<br />
Global Positioning Sensor (GPS) system<br />
installation<br />
10<strong>01</strong>6518 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.02889 FAA STC ST<strong>01</strong>433WI-D BEECH 400<br />
Modification of Collins GPS-4000 or GPS-<br />
BOMBARDIER BD-100-1A10 4000A Global PositioningSensor installation to<br />
(CHALLE<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>04</strong><br />
BOMBARDIER CL-600-2C10<br />
BOMBARDIER CL-600-2D24<br />
(SERIES<br />
CESSNA 560<br />
FALCON 2000<br />
FAN JET<br />
FAN JET FALCON SERIES C<br />
FAN JET FALCON SERIES D<br />
FAN JET FALCON SERIES E<br />
FAN JET FALCON SERIES F<br />
FAN JET FALCON SERIES G<br />
GULFSTREAM 200<br />
GULFSTREAM G150<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
LEARJET 60<br />
MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
MYSTERE FALCON 20-F5<br />
MYSTERE FALCON 50<br />
a Collins GPS-4000S installation<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data. Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Prior installation of Collins DBU-4000 part<br />
numbers 622-9865-0<strong>01</strong>/-002 or DBU-4100 part<br />
numbers 822-0<strong>01</strong>4-1<strong>01</strong>/-102/-103/-1<strong>04</strong> is a<br />
prerequisite to this STC.2. Prior to installation<br />
of this modification the installer must determine<br />
that the interrelationshi<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
This STC does not approve WAAS LPVPrior<br />
FAA approved installation of Collins GPS-4000<br />
part numbers 822-0931-0<strong>01</strong>/-002/-003 or GPS-<br />
4000A part number 822-1377-0<strong>01</strong> is a<br />
prerequisite to this STCPrior to installation of<br />
this modification the installer must deter<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 371/<strong>462</strong><br />
25.03.2008<br />
20.03.2008<br />
15.10.2008<br />
06.11.2008<br />
<strong>04</strong>.02.2009<br />
24.07.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6654 ROCKWELL COLLINS, Inc. <strong>EASA</strong>.IM.A.S.03103 SEE ATTACHED <strong>EASA</strong><br />
Collins CMU-900 ACARS Core Software Prior to installation of this modification the<br />
27.02.2009<br />
APPROVED TYP<br />
UpgradeThis modification removes the existing installer must determine that the<br />
CMU-900 and installs the same part number interrelationship between this modification and<br />
CMU-900 with updated core software. any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10035296 ROCKWELL COLLINS, Inc. FAA STC ST<strong>01</strong>886LA B767-300 Installation of Rockwell Collins CMU-900<br />
Communications ManagementSystem, APM-<br />
900 Airplane Personality Module, IDC-900<br />
Integrated DatalinkController & Teledyne TP-<br />
4499 Printer.<br />
10037095 ROCKWELL COLLINS, Inc. REV. 1 FAA STC ST<strong>01</strong>957AT-D B747-400 Installation of Collins SAT-906 Satcom<br />
Systems provisions in accordancewith Timco<br />
Master Data List MDL 99T<strong>04</strong>5L0<strong>01</strong>, Rev. C,<br />
dated October 21,1999 or later approved FAA<br />
revisions.<br />
10037522 ROCKWELL COLLINS, Inc. FAA STC NO. ST02177LA CL-600-2B16 HUD/EVS Model 6605 Validation of HUD/EVS<br />
in a Deactivated State<br />
10<strong>04</strong>1711 ROCKWELL COLLINS, Inc. REV. 1 FAA STC NO. ST<strong>01</strong>514WI-D CL600-2B19 REGIONAL JET<br />
A21EA<br />
Installation of Rockwell Collins FMS-4200 to<br />
provide WAAS/LPAcapability.<br />
10<strong>04</strong>1712 ROCKWELL COLLINS, Inc. FAA STC NO. ST<strong>01</strong>505WI-D CL-600-2B16 (CL-6<strong>04</strong> VARIANT) Installation of Rockwell Collins FMS-6000 to<br />
provide SBAS LPVcapability.<br />
10<strong>01</strong>5977 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02129 REV. 1 TCCA STC SA02-128 DHC 6-100, 6-200, 6-300 Installation of Single or Dual Sandel ST3400<br />
Terrain Awareness WarningSystem<br />
(TAWS)/RMI System<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.06.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
13.<strong>04</strong>.2<strong>01</strong>2<br />
Restricted to ASN 5872.This approval is for the<br />
installation and deactivation of the HUD<br />
andEVS in accordance with section 9 of the<br />
Rockwell Collins Master DrawingList 97<strong>01</strong>-<br />
1267 Revision D-1.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.12.2<strong>01</strong>1<br />
Installation and approval of WAAS compatible Prior to installation of this modification it<br />
GPS antennas is requiredprior to or concurrent must be determined thatthe<br />
12.10.2<strong>01</strong>2<br />
with this modification. This STC approves the interrelationship between this modification<br />
installation of DBU-5000 Part Number 822- and any other previouslyinstalled<br />
2215-602(Flip Door/Gray/No AFIS/Ethernet). modification and/ or repair will introduce<br />
Installation and approval of a Roc<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to Serial Numbers 53<strong>01</strong>-5699, 57<strong>01</strong><br />
and subsequent. Installation and approval of<br />
WAAS compatible GPS receivers/antennas<br />
arerequired prior to or concurrent with this<br />
modification. DBU-4000 and DBU-4100 Data<br />
Base Units are incompatible with the FMC-<br />
The audio for dual TAWS configuration must<br />
be from a single source inaccordance with<br />
drawings 1873419, 1873420 and 1873421<br />
incorporatingDCN’s RMA1873419/1,<br />
RMA18173420/2 and RMA18173422/1<br />
respectively.<br />
10<strong>01</strong>6029 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02198 TCCA STC SA<strong>01</strong>-30 Removal of Auxiliary Battery 1. An approved Main Battery Installation with<br />
a minimum capacity of 34 Ampere-Hours must<br />
be embodied as a pre-requisite.2. This STC<br />
is approved only for the product configuration<br />
as defined in the approved design data<br />
referred to in the paragraph "De<br />
10<strong>01</strong>6030 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02199 TCCA STC SA<strong>01</strong>-17 BOMBARDIER DHC-6 SERIES<br />
300<br />
10<strong>01</strong>6033 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02202 FAA STC SA02297NY BOMBARDIER DHC-6 SERIES<br />
200<br />
BOMBARDIER DHC-6-100<br />
DE HAVILLAND CANADA DHC6-<br />
300<br />
Cabin Evacuation Lighting Control System<br />
Change.<br />
(1) Installation of a Universal Avionics CVR-<br />
30B Cockpit Voice Recorder.(2) Installation of<br />
a Fairchild A100S, Honeywell SSCVR, or L3<br />
FA2100 Cockpit Voice Recorder.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
The installation applies only to aircraft not<br />
equipped with separate P.A.<br />
microphone.Maintenance must be in<br />
accordance with Field Aviation Company<br />
Maintenance Manual Supplement Report No<br />
199031, Original Issue, datedDecember 11,<br />
2006, or later approved rev<br />
Prior to installation of this modification it 09.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. 17.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 372/<strong>462</strong><br />
22.12.2006<br />
10.10.2008<br />
22.10.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6286 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02581<br />
TCCA STC SA02-119; <strong>EASA</strong> STC.IM VIKING AIR LIMITED (DCH) DHC- Dual or Single Garmin GNS530 or GNS430 Prior to installation of this modification the<br />
21.11.2008<br />
REVISION 1<br />
6<br />
installation.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6400 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02729 REV. 1 TCCA STC SA07-131 DHC-6-100, DHC-6-200,DHC-6-<br />
300<br />
10<strong>01</strong>6511 ROCKY MOUNTAIN AIRCRAFT <strong>EASA</strong>.IM.A.S.02878 REV. 1 TCCA STC SA08-38 BOMBARDIER DHC-6 SERIES<br />
200<br />
BOMBARDIER DHC-6-100<br />
BOMBARDIER DHC-6-300<br />
Installation of single or dual Sandel SN4500<br />
primary navigationdisplay(s) (EHSI) with<br />
optional SA4550 primary attitude<br />
display(s)(EADI)<br />
10037908 ROCKY MOUNTAIN AIRCRAFT TCCA STC SA11-72 DHC-6 SERIES 100, 200, 300 Installation of chip detectors on both left hand<br />
and right hand enginewith caution indication in<br />
DHC-6 series 100, 200, and 300 Twin<br />
Otteraircraft based on Engineering Data<br />
Summary E1<strong>04</strong>600 in accordance<br />
withTransport Canada STC SA11-72, Issue 1<br />
Installation of Pitot Heat Indication system. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The instal<br />
None 1) Prior to installation of this modification 03.08.2<strong>01</strong>0<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
11.11.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.<strong>01</strong>.2<strong>01</strong>2<br />
10038966 ROCKY MOUNTAIN AIRCRAFT DHC-6-100/-200/-300 Installation of Dual or Single Garmin GTN 650 None<br />
or GTN 750 in DHC-6 series100, 200, and 300<br />
Twin Otter aircraft based on Engineering Data<br />
SummaryE102910 & E102911 in accordance<br />
with Transport Canada STC SA11-79, Issue1<br />
None 27.03.2<strong>01</strong>2<br />
10<strong>04</strong>0247 ROCKY MOUNTAIN AIRCRAFT TCCA STC NO. SA11-80 DHC-6 SERIES 100<br />
DHC-6 SERIES 200<br />
DHC-6 SERIES 300<br />
10<strong>04</strong>2836 ROCKY MOUNTAIN AIRCRAFT TCCA STC SA05-54 DHC-6 SERIES 100<br />
DHC-6 SERIES 200<br />
DHC-6 SERIES 300<br />
10<strong>01</strong>5218 ROEDER PRAEZISION GMBH <strong>EASA</strong>.A.S.03633 CIRRUS SR20<br />
CIRRUS SR22<br />
Installation of either Universal Avionics CVR-<br />
120A or CVR-120R inaccordance with<br />
Transport Canada STC SA11-80, Issue 1<br />
Installation of a L-3 Skywatch HP TCAS 1<br />
System in accordance with TCCASTC SA05-<br />
54<br />
Installation of Avidyne Iridium MLX770 Two<br />
Way Datalink.<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.06.2<strong>01</strong>2<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.12.2<strong>01</strong>2<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
100292<strong>01</strong> ROEDER PRAEZISION GMBH CESSNA P210N Ferry Tank Provisioning Limited to Aircraft S/N P210 00629 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.03.2<strong>01</strong>0<br />
10030847 ROEDER PRAEZISION GMBH REV. 1 206H, T206H Provisioning for implementation and operation<br />
with a "Turtle Pac160-ferry tank"<br />
Installation of the ferry tank is not subject of<br />
this STC.<br />
03.12.2008<br />
Prior to installation of this modification it 14.07.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 373/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034119 ROEDER PRAEZISION GMBH PIPER PA-31-350 Provision for Camera Installation. None. This STC includes only the structural<br />
changes and the electrical powerbox. It<br />
does not include any installation of<br />
Equipment (e.g.Laserscanner, Computer,<br />
Cameras).Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship be<br />
08.03.2<strong>01</strong>1<br />
10039546 ROEDER PRAEZISION GMBH TU206F Installation of an additional Alternator with<br />
Battery for MissionPurposes<br />
10039554 ROEDER PRAEZISION GMBH 172S Installation of provision for the installation of a<br />
camera in the lowerfuselage as described in<br />
description document 14576DE 5300 10 00D.<br />
10<strong>01</strong>5845 ROSE UPHOLSTERY, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>945 SA1<strong>01</strong>88SC BAE JETSTREAM 32<strong>01</strong> Cabin Reconfiguration - 12 Passenger<br />
Executive Interior<br />
10<strong>01</strong>5376 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong><strong>04</strong>9 FAA STC ST02175CH BOEING 747-400 Installation of Rosemount Aerospace 8400M<br />
Series Cockpit Door Surveillance System<br />
10<strong>01</strong>5857 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>961 FAA STC ST00971SE-D BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
10<strong>01</strong>5899 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02020 FAA STC ST02368CH BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-800<br />
BOEING 737-900<br />
10<strong>01</strong>6410 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02742 REV. 3 FAA STC ST02649CH A319-111/-112/-113/-114/-115<br />
A319-131/-132/-133<br />
A320-111/-211/-212/-214<br />
A320-231/-232/-233<br />
A321-111/-112/-131<br />
A321-211/-212/-213/-231/-232<br />
Installation of the Rosemount Aerospace<br />
Coockpit Door Surveillance system (CDSS).<br />
Installation of Rosemount Aerospace Cockpit<br />
Door Surveillance System (CDSS) in<br />
accordance with Rosemount Aerospace MDL,<br />
Doc No. D06400594, Revision B, dated<br />
December 29, 2006, or later <strong>EASA</strong> approved<br />
revision.<br />
Installation of Rosemount Aerospace 8700C2-<br />
4 Laptop Docking Station -Electronic Flight Bag<br />
(EFB) System Provisions.A319/ A320 / A321<br />
Series 8700C2-4 Laptop Docking Station<br />
(LDS) -Electronic Flight Bag (EFB) System<br />
Provisions. Revision of the <strong>EASA</strong> STC 10<strong>01</strong>6<br />
10<strong>01</strong>6424 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.02762 FAA STC ST02712CH BOEING 747-400 Installation of Rosemount Aerospace 8700C2-<br />
6 Series Laptop Docking Station (LDS) -<br />
Electronic Flight Bag (EFB) Systems<br />
Provisions in accordance with Rosemount<br />
Aerospace Master Data List, Doc. No.<br />
D06402649 Revision C, dated April 3, 2009 or<br />
10<strong>01</strong>6617 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.03<strong>04</strong>4 REV. 2 FAA STC ST02675CH A340-211, -212, -213<br />
A340-311, -312, -313<br />
A340-541, -642<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.05.2<strong>01</strong>2<br />
Installer must check availability of <strong>EASA</strong>-<br />
approval for one or morereferenced STC when<br />
airplane is modified per that / those<br />
STC(s).This STC is limited to S/N<br />
172S8186.This STC provides instructions only<br />
for the installation of theprovision for a camera.<br />
Fu<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
- Compatibility of this design change with other<br />
previously approved modifications must be<br />
determined by the installer.- In accordance with<br />
Flight Manual Supplement, Rosemount<br />
Aerospace Doc No D0640<strong>01</strong>84, Rev A, FAA<br />
approved January 4th, 2007, or later ap<br />
The installation of this modification by 10.05.2<strong>01</strong>2<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
11.<strong>04</strong>.2006<br />
06.10.2005<br />
20.<strong>04</strong>.2006<br />
06.02.2007<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
18.11.2<strong>01</strong>0<br />
1. FAA approved Airplane Flight Manual<br />
Supplement, Rosemount Aerospace Doc. No.<br />
D06402687, Revision A, approved April 2,<br />
2009 orlater FAA approved revision, is required<br />
on board of the modified aircraft.2. This<br />
installation approval does not include<br />
23.<strong>04</strong>.2009<br />
later FAA appro<br />
Installation of Rosemount Aerospace 8700C2- This installation approval does not cover the Prior to installation of this modification it 26.08.2<strong>01</strong>0<br />
3 Laptop Docking Station -Electronic Flight Bag Electronic Flight Bagcomputers, only the must be determined thatthe<br />
(EFB) System Provisions Revision of the <strong>EASA</strong> Electronic Flight Bag mounting and wiring. interrelationship between this modification<br />
STC 10<strong>01</strong>6617, Rev. 1 to remove EWIS Theoperational approval of the Electronic Flight and any other previouslyinstalled<br />
Limitation<br />
Bag computers shouldfollow the guidance in modification and/ or repair will introduce<br />
the Temporary Guidance Leaflet TGL no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>6655 ROSEMOUNT AEROSPACE, Inc. <strong>EASA</strong>.IM.A.S.031<strong>04</strong> BOEING MD 11F Installation of Rosemount Aerospace 8700C2- 1) Prior to installation of this modification the<br />
8 Series Laptop Docking Station (LDS) - installer must determine that the<br />
Electronic Flight Bag (EFB) System Provisions interrelationship between this modification<br />
inaccordance with Rosemount Aerospace andany other previously installed modification<br />
Master Data List, Doc. No. D06403165, will introduce no adverse effect upon the<br />
Revision D, dated April 3, 2009 or later FAA<br />
approv<br />
airworthiness of the product.2) FAA app<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 374/<strong>462</strong><br />
10.06.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10026912 ROSEMOUNT AEROSPACE, Inc. P-<br />
REV. 1 FAA STC ST02743CH B737-600, -700, -800, -900 Validation of major change to FAA STC Not Applicable Prior to installation of this modification it <strong>01</strong>.07.2<strong>01</strong>1<br />
<strong>EASA</strong>.IM.A.S.03087<br />
concerning EFB 'Installation of8700A1-3<br />
must be determined thatthe<br />
Electronic Flight Bag'The change to EFB STC<br />
interrelationship between this modification<br />
adds the following features:- implementation of<br />
and any other previouslyinstalled<br />
Display Module (DM) ON/OFF backlight-<br />
modification and / or repair will introduce<br />
connections to WOW and Door Open discretes<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027535 ROSEMOUNT AEROSPACE, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03159<br />
10033819 ROSEMOUNT AEROSPACE, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02736<br />
FAA STC ST02761CH 737-300, 400, 500 Installation of Rosemount 8700C2-7 Series Refer to limitations and conditions on FAA<br />
Laptop Docking Station (LDS) -Electronic Flight ST02761CH.<br />
Bag (EFB) System. Validation of FAA STC<br />
ST02761CH<br />
REV. 1 FAA STC ST02668CH 777-200, 777-200LR, 777-300<br />
777-300ER, 777F<br />
10<strong>04</strong>1824 ROSEMOUNT AEROSPACE, Inc. FAA STC ST02944CH 777-200, 777-200LR, 777-300<br />
777-300ER, 777F<br />
Prior to installation of this modification it 08.10.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Rosemount Aerospace 8700C2- This installation approval does not include the Prior to installation of this modification it 18.10.2<strong>01</strong>2<br />
1 Laptop Docking Station- Electronic Flight Bag Electronic Flight Bagcomputers. The<br />
must be determined thatthe<br />
(EFB) System Provisions<br />
operational approval of the Electronic Flight interrelationship between this modification<br />
Bagcomputers should follow the <strong>EASA</strong> and any other previouslyinstalled<br />
Operational Approval process; Any equipment modification and/ or repair will introduce<br />
that is connected to the aircraft electrical p no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of an AC-DC Converter. Aircraft modification iaw Rosemount<br />
Aerospace Master Data List, Doc.<br />
No.D06408653 Configuration A requires<br />
concurrent installation of a systemor of<br />
equipment utilizing the DC power provided by<br />
the AC-DC powerconverter; Aircraft<br />
modification iaw Rosemount<br />
Prior to installation of this modification it 18.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6035 ROSEN SUNVISOR SYSTEMS LLC <strong>EASA</strong>.IM.A.S.022<strong>04</strong> REV. 2 FAA STC SA4147NM BAE 125 SERIES 1000A<br />
BAE 125 SERIES 800A<br />
HAWKER 1000<br />
HAWKER 800 XP<br />
HAWKER 850 XP<br />
HAWKER 900 XP<br />
Installation of Cockpit Sun Visors. 21.05.2008<br />
10<strong>01</strong>6661 ROSEN SUNVISOR SYSTEMS LLC <strong>EASA</strong>.IM.A.S.03124 FAA STC SA<strong>01</strong>838SE Installation of Sunvisor. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
23.<strong>04</strong>.2009<br />
10026892 ROSEN SUNVISOR SYSTEMS LLC P-<br />
<strong>EASA</strong>.IM.A.S.03271<br />
10027193 ROSEN SUNVISOR SYSTEMS LLC P-<br />
<strong>EASA</strong>.IM.A.S.03219<br />
10031251 ROSEN SUNVISOR SYSTEMS LLC P-<br />
<strong>EASA</strong>.IM.A.S.03270<br />
FAA STC SA2614NM 1. MYSTERE FALCON 200<br />
2. MYSTERE FALCON 50<br />
FAA STC SA00871SE SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
FAN JET FALCON C, D, E, F, G <strong>EASA</strong> Validation of FAA STC<br />
SA2652NMCockpit Sun Visor Installation i.a.w.<br />
Rosen Drawing List No. RF 20-00DL, Revision<br />
D dated 14th November 2008 or later revisions<br />
approved by<strong>EASA</strong> i.a.w. <strong>EASA</strong> ED Decisions<br />
2007/0<strong>01</strong>/C and 20<strong>04</strong>/<strong>04</strong>/CF (or<br />
subsequentrevisions to<br />
<strong>EASA</strong> Validation of FAA STC<br />
SA2614NM:Cockpit Sun Visor Installation in<br />
accordance with Rosen Drawing List No.RF<br />
50/200-00DL, Revision C dated 26th August<br />
2009 or later revisionsapproved by <strong>EASA</strong> in<br />
accordance with <strong>EASA</strong> ED Decision<br />
20<strong>04</strong>/<strong>04</strong>/CF (orsubsequent re<br />
10033410 ROSEN SUNVISOR SYSTEMS LLC FAA STC SA3529NM DHC-6-100, -200, -300 Cockpit Sun Visor installation in accordance<br />
with FAA STC SA3529NM<br />
None 1) Prior to installation of this modification<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
This <strong>EASA</strong> approval is also applicable to the<br />
Falcon 50EX version of theMF50 aircraft<br />
model as per this aircraft version definition<br />
described on<strong>EASA</strong> TCDS.A.062<br />
19.08.2009<br />
Prior to installation of this modification it 15.09.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of Sunvisor None Prior to installation of this modification the <strong>04</strong>.08.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
none If the holder agrees to permit another<br />
person to use this certificate toalter the<br />
product, the holder shall give the person<br />
written evidence ofthat permission.Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
betwee<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 375/<strong>462</strong><br />
19.<strong>01</strong>.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039248 ROSEN SUNVISOR SYSTEMS LLC FAA STC SA2367NM CL-600-1A11/-2A12/-2B16/-2B19 Cockpit Sunvisor Installation None Prior to installation of this modification it 20.<strong>04</strong>.2<strong>01</strong>2<br />
CL-600-2C10/-2D24<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028673 ROSS FRESNO LLB <strong>EASA</strong>.IM.A.S.03153 CESSNA 441 SERIES 15.07.2009<br />
10032879 ROTORCRAFT SUPPORT, Inc. FAA STC SR<strong>01</strong>456LA 407 Installation of Concorde RG407 Battery None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
06.12.2<strong>01</strong>0<br />
10<strong>01</strong>7109 ROTORTECH LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>085 EUROCOPTER FRANCE EC 155<br />
B1<br />
Compendium Modification. Compilation of 22<br />
individual modifications associated with the<br />
installation of equipment and systems enabling<br />
the transfer of EC 155B1 S/N 6642 from FAA<br />
register (N84AZ) to the UK register (G-NIVA).<br />
10033185 ROW 44, Inc. REV. 1 FAA STC ST02829CH B737-700/-800/-900 Installation of Row 44 Broadband Antenna<br />
System Provisions<br />
10033186 ROW 44, Inc. REV. 2 FAA STC ST02836CH-D B737-700, -800, -900 Installation and activation of a Row 44<br />
Broadband System<br />
1. This STC is applicable to EC155B1 S/N<br />
6642 only2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
22.09.2005<br />
other aircraft/engine configurations shall be<br />
The equipment for which these provisions are Prior to installation of this modification it 22.10.2<strong>01</strong>2<br />
intended has not beencertified. Additional must be determined thatthe<br />
approval is required for the installation of interrelationship between this modification<br />
thisequipment and must be evaluated to assure and any other previouslyinstalled<br />
satisfactory compliance withthe applicable modification and/ or repair will introduce<br />
airworthiness standards.<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
- The Row 44 Wireless Broadband System is<br />
intended to provide internetconnection and<br />
email services to the airplane's cabin using<br />
portableelectronic devices (PEDs). Any other<br />
use of this equipment will require a reexamination<br />
of thecertification basis. -<br />
10<strong>01</strong>6327 ROYAL ATLANTIC AVIATION, INC. <strong>EASA</strong>.IM.A.S.02636 FAA STC SA02636AT CESSNA 441 SERIES Ground Recognition Strobe Light System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7127 RTE - STH <strong>EASA</strong>.R.S.<strong>01</strong>215 REV. 1 AS 355N New pilot/co-pilot manual quick release 1. Limited to the following AS 355 N aircrafts:pyrotechnic<br />
sub-system, P/N JD3448AB0<strong>01</strong>00- S/N 5649, F-GSTH equipped with DGAC-F<br />
A0, for approved HEC devices ref: <strong>01</strong>-STH- approved design changes ref. <strong>01</strong>-STH-0<strong>01</strong> or<br />
0<strong>01</strong> and <strong>01</strong>-STH-002 and AAN 24527 <strong>01</strong>-STH-002-S/N 5543, F-GJAX equipped with<br />
DGAC-F approved design change ref. <strong>01</strong>-STH-<br />
0<strong>01</strong>-S/N 5566, G-LINE equipped with CAA-UK<br />
a<br />
10<strong>01</strong>7135 RTE - STH <strong>EASA</strong>.R.S.<strong>01</strong>229 AS 332 C1 Installation for Human External Cargo (HEC)<br />
applications<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is also applicable on AS355N when<br />
equipped with <strong>EASA</strong>.R.S.<strong>01</strong>366.<br />
10<strong>01</strong>7165 RTE - STH <strong>EASA</strong>.R.S.<strong>01</strong>273 DGAC-F TC N° 168 AS 355 N Personnel transport aboard hooked baskets as<br />
rotorcraft-load combinations for human external<br />
cargo (HEC).<br />
10<strong>01</strong>7210 RTE - STH <strong>EASA</strong>.R.S.<strong>01</strong>366 DGAC FRANCE STC FAM<br />
AS 355 N Helicopter equipped with ARRIUS 1A modified • Engine operating limitations as defined in<br />
98STH0595<br />
namedARRIUS 1E.DGAC-F approved design the “Installation Manual” reference X319 HS<br />
change 98STH0595 relates toinstallation of two 0<strong>01</strong>1.• Engine maintenance requirements<br />
modified ARRIUS 1A engines on the AS355N defined in Manuel d’entretien Turbomoteur<br />
helicopter. This installation allows increased<br />
engine performance required to perform<br />
GBF 124.<br />
Prior to installation of this modification it 08.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 376/<strong>462</strong><br />
22.09.2008<br />
08.08.2006<br />
21.12.2005<br />
18.10.2007<br />
23.03.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039175 RUAG AEROSPACE <strong>EASA</strong>.A.S.00200 REV. 2 DHC-6-300 Minor change to STC <strong>EASA</strong>.A.S.00200 by None The approval holder shall fulfil the 16.<strong>04</strong>.2<strong>01</strong>2<br />
adding the option to install aThommen AD32<br />
obligations of Part 21,<br />
instead of the Shadin ADC 2000 Installation of<br />
Paragraph21.A109. Prior to installation of<br />
TAWS class A Honeywell MK VI incl. KMD-850<br />
this modification it must be determined<br />
indicator inaccordance with Certification<br />
thatthe interrelationship between this<br />
Program Doc. T6-100<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10<strong>01</strong>3955 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.00505 BOMBARDIER CL-600-1A11 (CL- Upgrade Dual Honeywell FMS NZ-2000- 1. This STC is approved only for the product<br />
12.<strong>01</strong>.2005<br />
600<br />
PRNAV.<br />
configuration as defined in the approved design<br />
BOMBARDIER CL-600-2A12 (CL-<br />
data referred to in the paragraph "Description".<br />
6<strong>01</strong><br />
Compatibility with other aircraft/engine<br />
BOMBARDIER CL-600-2B16 (CL-<br />
configurations shall be determined by the<br />
6<strong>01</strong><br />
installer.<br />
10<strong>01</strong>3956 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.00506 BOMBARDIER CL-600-1A11 (CL- Mode-S Transmitter Collins TDR 94D upgrade - 1. This STC is approved only for the product<br />
12.<strong>01</strong>.2005<br />
600<br />
ELS/EHS; Associated Technical<br />
configuration as defined in the approved design<br />
BOMBARDIER CL-600-2A12 (CL- Documentation: Master Document List 100C- data referred to in the paragraph "Description".<br />
6<strong>01</strong><br />
MDL, Airplane Flight Manual Supplement 100C- Compatibility with other aircraft/engine<br />
BOMBARDIER CL-600-2B16 (CL- AFMS, Continued Airworthiness Plan 100C- configurations shall be determined by the<br />
6<strong>01</strong><br />
CAWP<br />
installer.<br />
10<strong>01</strong>3980 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>008 CESSNA 525<br />
Installation of Honeywell EGPWS MK V with<br />
10.<strong>04</strong>.2007<br />
CESSNA 525A<br />
RAAS<br />
10<strong>01</strong>3981 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong><strong>01</strong>2 BOMBARDIER CL-600-2B16 Installation of Honeywell EGPWS MK V. 1. This STC is approved only for the product<br />
12.<strong>04</strong>.2005<br />
BOMBARDIER CL-600-2B16 (CL-<br />
configuration as defined in the approved design<br />
6<strong>01</strong><br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4020 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>075 CESSNA 560 Installation of an ACAS II (TCAS 2000, CH 7) 1. This STC is approved only for the product<br />
27.<strong>01</strong>.2005<br />
with Dual Mode S Transponders ACSS RCZ- configuration as defined in the approved design<br />
852-ELS/EHS.<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4021 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>076 CESSNA 5<strong>01</strong> Installation of Dual Mode S Transponders<br />
ACSS RCZ-852-EHS<br />
<strong>01</strong>.03.2005<br />
10<strong>01</strong>4034 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>107 CESSNA 550 Installation of TCAS 2000, CH 7 with Dual<br />
Mode S transponders ACSS RCZ-852-EHS-<br />
Master Document List, Doc No 147A-MDL<br />
31.<strong>01</strong>.2005<br />
10<strong>01</strong>4035 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>108 CESSNA 550 BRAVO Upgrade of GPWS to EGPWS 10.02.2005<br />
10<strong>01</strong>4<strong>04</strong>4 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>122 CESSNA 560 Installation of ACAS II CAS 67A with Dual<br />
Mode S Transponder RCZ-833 J-ELS<br />
17.03.2005<br />
10<strong>01</strong>4060 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>144 CESSNA 560 (CITATION V) Installation of ACAS II (ACSS TCAS 2000,<br />
CH7) with Dual Mode S Transponders RCZ-<br />
833J ELS<br />
10.03.2005<br />
10<strong>01</strong>4085 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>176 REV. 1 BOMBARDIER CL-600-1A11 (CL- Upgrade of the two existing Mode-S<br />
29.02.2008<br />
600<br />
Transponders ACSS RCZ-852 by ACSS<br />
BOMBARDIER CL-600-2A12 (CL- Service Bulletin 8002246-0<strong>01</strong> for<br />
6<strong>01</strong><br />
ELS/EHS.Replacement of the Controller,<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Collins CTL-92 by Mode S Controller, Collins<br />
3A<br />
CTL-92E.ACSS Mode-S transponder RCZ-852<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>- ELS/EHS with Collins CTL-92E.<br />
3R<br />
10<strong>01</strong>4161 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>293 BOEING DC-9-82 (MD-82) Installation of Mode S Transponder ACSS XS-<br />
28.06.2005<br />
BOEING DC-9-83 (MD-83) 950 ELS/EHS with Control Gables G7490-66<br />
including associated Airplane Flight Manual<br />
Supplement<br />
10<strong>01</strong>4189 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>331 CESSNA 525 Installation of ACAS II System with Dual Mode<br />
S Transponder. ELS compliant and EHS<br />
capable<br />
18.07.2005<br />
10<strong>01</strong>4195 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>337 BOMBARDIER BD-700-1A10 Installation of MicroQAR acc.<strong>04</strong>6A-SD 21.06.2005<br />
10<strong>01</strong>42<strong>04</strong> RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>355 BOMBARDIER DHC-8-400 Installation of VDL 4000/A VHF Data Link<br />
Mode 4 (CNS Systems) and installation of a<br />
combined VHF/GPS Antenna<br />
18.07.2005<br />
10<strong>01</strong>4205 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>356 CESSNA 500, CITATION Installation of a TWS/RMI Sandel ST 3400<br />
(TAWS Class B)<br />
24.08.2005<br />
10<strong>01</strong>4206 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>357 CESSNA 500, CITATION Installation of Dual Mode - S Transponder<br />
System Garmin GTX-330D - Elementary<br />
Surveillance. (Removel of the exising Rockwell<br />
Collins TDR-90 transponder). Installation of two<br />
additional L-Band Antennas on top of the<br />
fuselage.<br />
24.08.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 377/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4377 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>652 CESSNA 560 Installation of a Honeywell Solid-State Flight<br />
Data Recorder (SSFDR) with Teledyne<br />
Controls Mini Flight Data Acquisition Unit<br />
(MFDAU)<br />
20.<strong>01</strong>.2006<br />
10<strong>01</strong>4407 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>702 CESSNA 550 CITATION II Honeywell EGPWS Mk VIII Certification Basis of the Change: FAR 25 as<br />
defined in TCDS A22CE;Rev. 58, additionally<br />
JAA Leaflet No. 12 (TAWS)<br />
24.<strong>04</strong>.2006<br />
10<strong>01</strong>4409 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>705 REV. 1 CESSNA 650 Upgrade of two existing Mode S transponders, Aircraft Serial Numbers 650-70<strong>01</strong> through 650- Prior to installation of this modification it 29.10.2<strong>01</strong>0<br />
Rockwell CollinsTDR-94D byRockwell Collins 7119<br />
must be determined thatthe<br />
SB 5<strong>01</strong>.Replacement of Mode S Controller<br />
interrelationship between this modification<br />
CTL-92 by CTL-92E along withinstallation of<br />
and any other previouslyinstalled<br />
new wiring for Enhances SurveillanceRevision<br />
modification and/ or repair will introduce<br />
1 to include <strong>EASA</strong> AD 2009-<strong>01</strong>73, Rockwel<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4429 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02475 CESSNA 550 CITATION II ACAS II 5CAS67A) with Dual Mode S XPDR<br />
MST-67A-EHS<br />
Certification Basis of the Change: FAR 25 as<br />
defined in TCDS A22CE; Rev. 58, additionally<br />
JAA Leaflet No. 8, Rev. 2 (ACAS II), JAA<br />
Leaflet No. 13, Rev. 1 (Mode-S ELS) and JAA<br />
NPA 20-12a (Mode-S EHS)<br />
10<strong>01</strong>4571 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02675 Installation of Honeywell Solid-State Flight Data --<br />
Recorder (SSFDR) with Teledyne Controls Mini<br />
Flight Data Acquisition Unit (MFDAU)<br />
26.06.2006<br />
10<strong>01</strong>4599 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02720 BOMBARDIER CL-600-1A11 (CL- Enhanced Ground Proximity Waning System-<br />
600<br />
EGPWS-MK VII or MKV enhancement with<br />
BOMBARDIER CL-600-2A12 (CL- RAAS<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3A<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3R<br />
BOMBARDIER CL-600-2B16 (6<strong>04</strong>)<br />
10<strong>01</strong>4610 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02737 CESSNA 525 Installation of KLN-90BModel: 525 S/N 00<strong>01</strong><br />
up to 0359<br />
10<strong>01</strong><strong>462</strong>3 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02757 BOMBARDIER CL-600-1A11 (CL- Honeywell Primus II RCZ-833 () Integrated<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>01</strong><br />
Radio System – EHS.<br />
10<strong>01</strong><strong>462</strong>4 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02758 BOMBARDIER CL-600-1A11 (CL- Upgrade Dual Honeywell FMS NZ-2000 /<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>01</strong><br />
PRNAV.<br />
S/N 525-00<strong>01</strong> up to 525-0359This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Description". Compatibility<br />
with other aircraft/engine configurations shall<br />
be determined by the install<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong><strong>462</strong>5 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02759 BOMBARDIER CL-600-1A11 (CL- Iridium Satcom ST3100. This STC is approved only for the product<br />
600<br />
configuration as defined in the approved design<br />
BOMBARDIER CL-600-2A12 (CL-<br />
data referred to in the paragraphs "Description"<br />
6<strong>01</strong><br />
and “Associated Technical Documentation”.<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
Compatibility with other aircraft/engine<br />
3A<br />
configurations shall be determined<br />
10<strong>01</strong>4645 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02799 BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>01</strong><br />
40Ah Battery with Charger. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 378/<strong>462</strong><br />
19.<strong>04</strong>.2006<br />
07.02.2007<br />
10.07.2006<br />
12.<strong>01</strong>.2007<br />
12.<strong>01</strong>.2007<br />
12.<strong>01</strong>.2007<br />
12.<strong>01</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4646 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02800 BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Interior, Aircell Antenna & Miscellaneous This STC is approved only for the product<br />
12.<strong>01</strong>.2007<br />
3A<br />
Equipment.<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>4648 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02803 CESSNA 560 (CITATION V) Transpoder Mode S Honeywell Primus II – This STC is approved only for the product<br />
ELS/EHS, Upgrade of the two existing Mode S configuration as defined in the approved design<br />
Transponder RCZ-833K by Honeywell Service data referred to in the paragraph "Description".<br />
Bulletin to implement ELS/EHS transponder Compatibility with other aircraft/engine<br />
capability. Installation of new wires from the configurations shall be determined by the<br />
FMS and the two Display/Guidance Compute installer.<br />
10<strong>01</strong>4654 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02811 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4655 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02812 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4656 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02813 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4657 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02814 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4661 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02818 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
Installation of Flight Information System Sirius<br />
FD200<br />
15.09.2006<br />
None 11.12.2006<br />
Installation of Honeywell EGPWS Mk VIII. None 11.12.2006<br />
Installation of Honeywell MST-67A Mode S<br />
Transponders.<br />
None 11.12.2006<br />
Installation of Aircell Iridium Satcom Axxess II None 11.12.2006<br />
Installation of modified and refurbished cabin<br />
interior<br />
10<strong>01</strong>4766 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02958 CESSNA CITATION 5<strong>01</strong> Installation of Honeywell Integrated Hazard<br />
Avoidance System (IHAS)<br />
10<strong>01</strong>4790 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02991 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
This installation does not comply to JAR OPS 1<br />
operational requirements (Class B equipment),<br />
thus it is up to installer to comply with national<br />
commercial operational rules and<br />
requirements.<br />
Upgrade of two Mode-S transponders According to EUROCONTROL definition this<br />
Honeywell MST-67A by Honeywell SB to equipment with approval <strong>EASA</strong>.A.S.02991 is<br />
implement ELS/EHS transponder<br />
non-EHS compliant.<br />
capability.ATC Controller KFS-578A is<br />
exchanged by Mode S ControllerPS-578A.New<br />
wires from the transponders to the FMS.<br />
10<strong>01</strong>4791 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02992 BOMBARDIER CL-600-1A11 (CL- Honeywell MST-67A Transponder Mode-S<br />
<strong>04</strong>.<strong>04</strong>.2007<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3A<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3R<br />
ELS/EHS<br />
10<strong>01</strong>4792 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.02994 BOMBARDIER CL-600-2A12 (CL- Inflight Entertainment System (IFE) Sirius<br />
6<strong>01</strong><br />
29.05.2007<br />
10<strong>01</strong>4819 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03029 BOMBARDIER CL-600-2B16 (CL- <strong>EASA</strong> Recertification of Cabin Modifications.<br />
6<strong>04</strong><br />
18.10.2007<br />
10<strong>01</strong>4860 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03084 BOMBARDIER CL-600-1A11 (CL- Honeywell EGPWS MK VII<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (CL-<br />
6<strong>01</strong><br />
11.05.2007<br />
10<strong>01</strong>4861 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03085 BOMBARDIER CL-600-1A11 (CL- ACSS Mode-S Transponder RCZ-852 - With this modification now embodied the<br />
11.05.2007<br />
600<br />
ELS/EHS<br />
aircraft is non EHS compliant.<br />
10<strong>01</strong>4866 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03090 BOMBARDIER CL-600-1A11 (CL- Dual TAWS Sandel ST3400 - Class A<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
29.02.2008<br />
10<strong>01</strong>4880 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03108 CESSNA CITATION 5<strong>01</strong><br />
CESSNA CITATION CS 551<br />
Installation of Dual Mode S XPDR MST-<br />
67A.Model: 5<strong>01</strong> S/N 00<strong>01</strong> and on (Citation I-<br />
SP)551 S/N 00<strong>01</strong> and on (Citation II-SP)<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 379/<strong>462</strong><br />
12.12.2006<br />
25.06.2007<br />
05.<strong>04</strong>.2007<br />
21.06.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4889 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03119 DORNIER 328-300 Modification of rear-facing seat for use during<br />
T/O and Landing.Backrest support of the<br />
already certified VIP seats AMP 2524..xxx is<br />
modified. The seats are now certified for T/O<br />
and landing in aft facing condition with a<br />
backrest support; ref. TSO-C127 dy<br />
19.11.2007<br />
10<strong>01</strong>4890 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03120 DORNIER 328-300 <strong>EASA</strong> Certification of Installed of Galley and<br />
Lavatory Water System.Certified earlier by<br />
AvCraft USA.Ref. FAA STC nr. 9993.<br />
13.11.2007<br />
10<strong>01</strong>4891 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03121 BOMBARDIER CL-600-2A12 (CL- <strong>EASA</strong> recertification of Cabin Modifications<br />
6<strong>01</strong><br />
29.02.2008<br />
10<strong>01</strong>4892 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03122 BOMBARDIER CL-600-2A12 (CL- <strong>EASA</strong> recertification of Avionics Modification<br />
6<strong>01</strong><br />
29.02.2008<br />
10<strong>01</strong>4895 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03125 DORNIER 228-212 Adjustment of Special Fatigue Life.Model:<br />
Dornier 228-212, S/N 8181 and 8183<br />
10<strong>01</strong>4935 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03190 BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Installation of a Honeywell Bendix/King Radio<br />
3A<br />
KTR 909 System.<br />
10<strong>01</strong>4938 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03195 BOMBARDIER CL-600-1A11 (CL- Aircell Iridium Satcom, Axxcess EZ (Magnaster<br />
600<br />
BOMBARDIER CL-6<strong>01</strong>-3A<br />
C-2000 replacement).<br />
10<strong>01</strong>4954 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03219 CESSNA 650 CITATION III Honeywell EGPWS Mk VIIDescription:<br />
CESSNA 650 CITATION VI replacement of the existing GPWS Mk VII with<br />
CESSNA 650 CITATION VII a Honeywell EGPWS Mk VII. Terrain<br />
presentation on the EFIS MFD.Installation of<br />
indicators/switches in the instremental Panel.<br />
1. This STC is only applicable to aircraft S/N:<br />
08.10.2007<br />
8181, 8183.2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed modification<br />
will introduce<br />
Restricted to ASN 5105. 10.10.2007<br />
10<strong>01</strong>4964 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03236 BEECH F90 Avionics Installation, consisting of- Dual<br />
GNS430A VHF Com/GPS and NAV- Dual<br />
GAD42 Adapter for GNS430/RMI- Dual<br />
KMR675 Marker Beacon Receiver- EHS<br />
GTX330D Diversity Transponder and<br />
Transponder Top Antenna- GMX200<br />
Traffic/Radar and Jeppview MFD Display- TAS<br />
None. 12.12.2007<br />
10<strong>01</strong>4995 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03292 Installation of dual Garmin GBS530AW Vertical approach navigation basing on<br />
NAV/COMM/GPS and dual sandel SN4500 E- GPS/WAAS is o nly approved in<br />
HS.<br />
VMC.Restricted to aircraft equipeed with<br />
Honeywell King Silver Crown Series.<br />
10<strong>01</strong>5005 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03305 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>5<strong>04</strong>1 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03357 CESSNA 525<br />
CESSNA 525A<br />
FMS Upgrade to Dual Honeywell NZ-<br />
2000/PRNAV<br />
Iridium Satcom AirCell ST3100,Description:<br />
Replacement to the previously installed AirCell<br />
AT.<strong>01</strong> Air Telephone System by AirCell ST<br />
3100 satellite Communication System<br />
(SATCOM).<br />
21.08.2007<br />
08.10.2007<br />
17.03.2008<br />
none 16.<strong>01</strong>.2008<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5054 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03375 DORNIER DO 228-202K Increase of Fatigue Life Limit. This STC is only applicable to Aircraft S/N:<br />
8<strong>04</strong>6.<br />
19.12.2007<br />
10<strong>01</strong>5094 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03431 BEECH B200 Dual Collins TDR-94() Upgrade-ELS/EHS and None<br />
Antenna Diversity.Upgrade of existing Dual<br />
Collins TDR-94() Transponders by TDR-94D<br />
and Replacement of Control CTL-92 by CTL-<br />
92E.Installation of two additional top-mounted<br />
L-Band Antennas for antenna diversity.Inst<br />
08.02.2008<br />
10<strong>01</strong>5124 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03474 REV. 1 FALCON 20 Dual Universal UNS-1L FMS Installation. This STC is limited to Mystere-Falcon 20-C5<br />
aircraft Serial Number 141.See: Airplane Flight<br />
Manual Supplement 236A-F20-34.60.02AFMS<br />
Revision N/CMaintenance Manual Supplement<br />
236A-F20-34.60.02MMS Revision N/COr later<br />
approved revisions.<br />
10<strong>01</strong>5125 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03475 REV. 1 FALCON 20 Dual Collins TDR-94D Enhanced Mode S<br />
Transponder Upgrade.<br />
This STC is limited to Mystere-Falcon 20-C5<br />
aircraft Serial Number 141.See:Airplane Flight<br />
Manual Supplement 236B-F20-34.80.05AFMS<br />
Revision OriginalOr later approved revisions.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 380/<strong>462</strong><br />
08.02.2008<br />
<strong>01</strong>.<strong>04</strong>.2008<br />
31.03.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5259 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03713 REV. 1 DC-9-87 (MD-87) Cabin Layout ChangeModification of existing 1. Prior to installation of this modification the<br />
02.12.2008<br />
Iberia 109 passenger economy seat layout to- installer must determine that the<br />
20 B/C + 79 E/C seat layout for S/N 49832; interrelationship between this modification and<br />
49834;49837; 49838; 49840; 49841 and- 12 any other previously installed modification will<br />
B/C + 89 E/C seat layout for S/N 49833; introduce no adverse effect upon the<br />
49839; 49842<br />
airworthiness of the product.2.<br />
10<strong>01</strong>5306 RUAG AEROSPACE SERVICES GmbH <strong>EASA</strong>.A.S.03897 EMBRAER EMB-135BJ Stone Flooring / Replacement of existing floor <strong>EASA</strong> EWIS Generic Special Condition not<br />
26.05.2009<br />
covering by a stone floor covering in the<br />
forward entrance area and in the rear lavatory.<br />
This modification will not affect the structural<br />
flooring, the stone floor covering is only a<br />
decorative component.<br />
applicable for this STC<br />
10027158 RUAG AEROSPACE SERVICES GmbH P-<strong>EASA</strong>.A.S.03970 CESSNA 525 P-RNAV Upgrade for the Honeywell GNS-XLS Restricted to aircraft with S/N 00<strong>01</strong> to 0359 1) Prior to installation of this modification 10.09.2009<br />
Flight Management System<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10027192 RUAG AEROSPACE SERVICES GmbH P-<strong>EASA</strong>.A.S.03963 BD-700-1A10, -1A11 EGPWS MK V Enhancement with RAAS - BD-700-1A10: S/N 9002 and subsequent- BD-Prior<br />
to installation of this modification it 14.09.2009<br />
Upgrade of the existing Honeywell Enhanced 700-1A11: S/N 9127 and subsequent must be determined thatthe<br />
Ground Proximity WarningSystem (EGPWS)<br />
interrelationship between this modification<br />
MK V with the Honeywell Runway Awareness<br />
and any other previouslyinstalled<br />
and AdvisorySystem (RAAS). Installation of an<br />
modification and/ or repair will introduce<br />
optional RAAS Advisory Mute switchinto the<br />
no adverse effectupon the airworthiness<br />
center pede<br />
of the product.<br />
10027824 RUAG AEROSPACE SERVICES GmbH CL-600-2B16 Installation of Honeywell Aircraft Flight<br />
Information System (AFIS)<br />
10028151 RUAG AEROSPACE SERVICES GmbH REV. 1 EMB-135BJ AXE4-869/2009-mk (297A-RFC): Electronic<br />
Flight Bag<br />
10030<strong>04</strong>5 RUAG AEROSPACE SERVICES GmbH CL-600-1A11 / -2A12 / -2B16 <strong>EASA</strong> AD 2009-0097 and AD 2009-<strong>01</strong>73 for<br />
Transponder TDR-94D<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.11.2009<br />
None. EMB-135 model BJ not affected by<br />
EWIS requirements.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse<br />
30.06.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.05.2<strong>01</strong>0<br />
1003<strong>04</strong>78 RUAG AEROSPACE SERVICES GmbH BD-700-1A11 Stone Flooring None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.06.2<strong>01</strong>0<br />
10031258 RUAG AEROSPACE SERVICES GmbH DC-9-83 (MD 83) Cabin Layout/Interior Change -DC-9-83 none Refer to RUAG Doc. No. 293B-<br />
AMMSPrior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/or<br />
repair will introduce no adverse<br />
effectupon the airwo<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 381/<strong>462</strong><br />
05.08.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032060 RUAG AEROSPACE SERVICES GmbH CL-600-1A11<br />
Installation of Satcom Iridium System none Prior to installation of this modification it 06.10.2<strong>01</strong>0<br />
CL600-2B16, CL-600-2A12 Simphone DUO<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032061 RUAG AEROSPACE SERVICES GmbH CL-600-1A11<br />
CL600-2B16, CL-600-2A12<br />
Electronic Flight Bag NavAero tBagC2 (EFB) -<br />
Class II<br />
10033641 RUAG AEROSPACE SERVICES GmbH P-<strong>EASA</strong>.A.S.03896 EMB-135BJ Modification 289A: Thrane & Thrane Aero SB<br />
Lite Satcom Installation<br />
10034074 RUAG AEROSPACE SERVICES GmbH 525<br />
525A<br />
10036250 RUAG AEROSPACE SERVICES GmbH BD 100-1A10 (CHALLENGER<br />
300)<br />
10036633 RUAG AEROSPACE SERVICES GmbH REV. 1 BD-700-1A10<br />
BD-700-1A11<br />
Installation of High Speed SATCOM system<br />
with on-board WLAN Interface.<br />
Installation of EGPWS MK-V with Runway<br />
Awareness and Advisory System(RAAS).<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.10.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.02.2<strong>01</strong>1<br />
STC limited to S/N 525-0516The WLAN clients Prior to installation of this modification it <strong>04</strong>.03.2<strong>01</strong>1<br />
(Handsets, Laptops, etc) are not covered by must be determined thatthe<br />
this STC.The usage of these components is interrelationship between this modification<br />
requiring operational approval.<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.08.2<strong>01</strong>1<br />
Dual Electronic Flight Bag (EFB) Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.09.2<strong>01</strong>1<br />
10039078 RUAG AEROSPACE SERVICES GmbH BELL 205A-1 Title: Load Attachment Device BRD<strong>01</strong> on Bell None<br />
205A-1Description: The BRD<strong>01</strong> is a cabin<br />
mounted device for attaching loads onBell<br />
helicopters. It is used with opened sliding doors<br />
and can bemounted left- and righthand<br />
simultaneously.<br />
None <strong>04</strong>.<strong>04</strong>.2<strong>01</strong>2<br />
10<strong>04</strong>2290 RUAG AEROSPACE SERVICES GmbH REV. 1 CL-600-1A11, CL-600-2A12<br />
CL-600-2B16<br />
10<strong>04</strong>2291 RUAG AEROSPACE SERVICES GmbH CL-600-1A11, CL-600-2A12<br />
CL-600-2B16<br />
Flight Management System NZ-2000 -<br />
Upgrade to SW 6.1<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.11.2<strong>01</strong>2<br />
ACSS TCAS II / 2000 Change 7.1 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.11.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 382/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5<strong>01</strong>2 RUAG SCHWEIZ AG <strong>EASA</strong>.A.S.03314 BOMBARDIER DHC-6 SERIES Avionics system upgrade- In: Weather Radar 1. Reg.:T-741 S/N: 4662. Prior to<br />
20.<strong>04</strong>.2009<br />
300<br />
System incl. ART-2000, AA-2<strong>01</strong>2V, CM-2000; installation of this modification the installer must<br />
Garmin GMX-200 Multi Function Display determine that the interrelationship between<br />
system; Avidyne TAS-620 system incl. Heading this modification and any other previously<br />
Adapter AHRS-500; Garmin GTX-330 Mode S installed modification will introduce no adverse<br />
Transponder system; Collins DME IND-42<br />
system<br />
effect upon the airworth<br />
10<strong>01</strong>7236 RUAG SCHWEIZ AG <strong>EASA</strong>.R.S.<strong>01</strong>415 EUROCOPTER FRANCE SA Enhanced navigation systemRemoved T-771 S/N: 6146Valid for this S/N. <strong>04</strong>.08.2008<br />
365N<br />
Equipment:- Pilot & Copilot HSI 651- Trimble<br />
21<strong>01</strong> GPS with MD41 Annunciator Control Unit<br />
and MD40 CDI- KTR 908 VHF COM System<br />
with KSF 598 Control Unit- KEA 346 Encoding<br />
Altimeter- Badin Crouzet Encoding Altimeter-<br />
KAS 297<br />
10026920 RUAG SCHWEIZ AG <strong>EASA</strong>.R.S.<strong>01</strong>550 <strong>01</strong>.07.2009<br />
10027200 RUAG SCHWEIZ AG P-<strong>EASA</strong>.R.S.<strong>01</strong>582 MD900 TV Broadcasting Equipment Installation The Installation TV Broadcasting Equipment is 1) Prior to installation of this modification 14.09.2009<br />
(camera adaptation on existingmount and limited to: S/N 900-0<strong>01</strong>31<br />
the installer mustdetermine that the<br />
certification of the operators rack)<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10030985 RUAG SCHWEIZ AG P 180 AVANTI II In-Flight Entert. System Installation by installing<br />
a ROSEN"RosenViewVX" moving Map and<br />
DVD System, an IR-Eye, One FLIGHT<br />
DISPLAYSYSTEM 10.2 inch LCD and two 7<br />
inch LCD's and a FLIGHT DISPLAY<br />
SYSTEMwireless audio transmitter for audio<br />
distribution to SENNH<br />
10031322 RUAG SCHWEIZ AG <strong>EASA</strong>.R.S.<strong>01</strong>547 500 N IRIS Camera Installation.Installed: L3 Avionics<br />
System Type A100 IRIS Camera System.<br />
10034921 RUAG SCHWEIZ AG PC-6 ALL SERIES Avionics upgrade with Aspen EFD1000<br />
Removed: - Various Equipment (if installed)<br />
i.a.w. DIC 1898256-1<strong>01</strong> Installed:- Aspen<br />
EFD1000 Electronic Flight Instrument System-<br />
Dual Garmin GNS430W COM/NAV/GPS-<br />
Garmin GMA 340 Audio Panel<br />
10037<strong>01</strong>1 RUAG SCHWEIZ AG EC 130 B4 Avionics RetrofitOut: Garmin GTX·330 Mode S<br />
Transponder & GMA·340 Audio/Marker<br />
system;Honeywell KX·165A VHF·COM/NAV<br />
systemIn: Aspen EFD 1000H EFIS system;<br />
Garmin GNS 430W VHF COM/NAV &<br />
GPSsystem; Garmin GSR 56 Iridium system;<br />
PS Engineering PMA 8000BAudio/<br />
10<strong>01</strong>4929 RUECKER AEROSPACE GMBH <strong>EASA</strong>.A.S.03182 AIRBUS A340-300 A340-300 new First Class Seats Test Aircraft<br />
/Installation of four newly developed First Class<br />
Seats in an Airbus A340-300 aircraft for<br />
testing.<br />
10<strong>01</strong>4961 RUECKER AEROSPACE GMBH <strong>EASA</strong>.A.S.03232 DORNIER 328-100 Installation of s 230VAC Euro standard power<br />
socketat both cockpit sidewalls.<br />
10027449 RUECKER AEROSPACE GMBH DORNIER 228-1<strong>01</strong> Installation of UHF Research Mission<br />
Equipment<br />
None The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
20.07.2<strong>01</strong>0<br />
Serial number: LN088. Prior to installation of this modification the 02.06.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
S/N: All- One independent Communication or<br />
Navigation System needs to beinstalled in<br />
addition to the two GNS430W.- RNAV (GPS)<br />
Approaches to LNAV, LNAV/VNAV or LPV<br />
minima are notapproved.<br />
The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
13.05.2<strong>01</strong>1<br />
S/N 7214<br />
repair<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.11.2<strong>01</strong>1<br />
25.03.2008<br />
22.08.2007<br />
Limited to serial number 7083 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.10.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 383/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027451 RUECKER AEROSPACE GMBH 208B Installation of UHF Research Mission Limited to serial number 708 Prior to installation of this modification it <strong>01</strong>.10.2009<br />
Equipment<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10027825 RUECKER AEROSPACE GMBH P-<strong>EASA</strong>.A.S.03855 B777-200 Installation of 2 single B/E Aerospace DS9000<br />
steam ovens and 2 OCM9000Oven Control<br />
Modules per B/E Aerospace Engineering<br />
OrderEO-253-000<strong>04</strong>-0<strong>01</strong> Rev. D. or later<br />
approved revision.<br />
10029687 RUECKER AEROSPACE GMBH P-<strong>EASA</strong>.A.S.03810 B747-400 Installation of 2 single B/E Aerospace DS9000<br />
steam ovens and 2 OCM9000Oven Control<br />
Modules per B/E Aerospace Engineering<br />
OrderEO-253-00002-0<strong>01</strong> Rev. A. or later<br />
approved revision<br />
10030032 RUECKER AEROSPACE GMBH SEE ATTACHED AML Fullsize/ Halfsize ATLAS trolley installation<br />
approval.<br />
None Jamco America Service Bulletin Nr.<br />
BA77-25-2393 must be<br />
installedconcurrently.<br />
None. Jamco America Service Bulletins Nr.<br />
BA74-25-2485 and BAW740-25-2392<br />
mustbe installed concurrently<br />
See Interface Control Drawing AIS-09-03,<br />
Issue C.<br />
None. 13.05.2<strong>01</strong>0<br />
10034669 RUECKER AEROSPACE GMBH 328-300 Modification to certificated LOPA none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>04</strong>.2<strong>01</strong>1<br />
10038569 RUECKER AEROSPACE GMBH REV. 1 777-200 Rücker Aerospace Nr.: 102100<strong>04</strong>0: Installation<br />
of CAIR (TM) system<br />
10<strong>01</strong>7195 S.A.M. - S.R.L - <strong>EASA</strong>.R.S.<strong>01</strong>333 EUROCOPTER FRANCE AS<br />
355F1<br />
EUROCOPTER FRANCE AS<br />
355F2<br />
10<strong>01</strong>7196 S.A.M. - S.R.L - <strong>EASA</strong>.R.S.<strong>01</strong>334 EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
SAM/002/2005: Archimede System "Digital<br />
acquisition and transmission of visible and<br />
infrared images"<br />
SAM/002/2005: Archimede System "Digital<br />
acquisition and transmission of visible and<br />
infrared images"<br />
09.11.2009<br />
13.<strong>04</strong>.2<strong>01</strong>0<br />
This modification is limited to MSN 29953. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.11.2<strong>01</strong>2<br />
10<strong>01</strong>43<strong>04</strong> S.E.A.M. <strong>EASA</strong>.A.S.<strong>01</strong>548<br />
BA<br />
BEECH S35 Installation of following equipments:<br />
This STC is applicable only for the Beechraft<br />
16.09.2005<br />
KN63+KDI572+KX165+KI203+KMD150+AR4<br />
4<strong>01</strong>+WX500+ANT NY163<br />
S35 - S/N D7498<br />
10<strong>01</strong>4650 S.E.A.M. <strong>EASA</strong>.A.S.02805 MOONEY M20M BRNAV capacity modification - Installation of<br />
annunciator MD 41, technical description in<br />
FAM No. 1147/06/SEAM<br />
Modification limited to s/n 27-<strong>01</strong>35 16.03.2007<br />
10<strong>01</strong>4745 S.E.A.M. <strong>EASA</strong>.A.S.02928 BEECH V35B Modification d'installation BRNAV. AFM Supplement n°1, revision 0, dated 8<br />
December 2006 or any later approved revision<br />
must be on board.<br />
14.07.2008<br />
10<strong>01</strong>4787 S.E.A.M. <strong>EASA</strong>.A.S.02987 PIPER PA-24-260 Installation modification B-RNAV Mid Continent Limited to S/N 24-4847 F-GKDA.<br />
MD41-1464A.<br />
07.11.2007<br />
10<strong>01</strong>4795 S.E.A.M. <strong>EASA</strong>.A.S.02997 BEECH 100 Installation of 2 GNS430A, 2 GTX330D XPDR, Installation Limited to Beech B100, S/N. B-199<br />
20.07.2007<br />
1KMR 675 and 1 GAD42.<br />
(F-GEXV).<br />
10<strong>01</strong>4796 S.E.A.M. <strong>EASA</strong>.A.S.02998 KING AIR 200 Installation of 2 GNS430A, 2 GTX330D XPDR Installation Limited to Beech B200, S/N. BL-11<br />
10.07.2007<br />
and 1 GAD42.<br />
(F-GRSO).<br />
10<strong>01</strong>4797 S.E.A.M. <strong>EASA</strong>.A.S.02999 BEECH 200 Installation of 2 GNS430A, 2GTX330D XPDR, Installation limited to Beech B200, S/N BB-622<br />
26.07.2007<br />
Akmr, 1KMR 675 and 1 GAD42.<br />
(F-GHSV).<br />
10<strong>01</strong>4842 S.E.A.M. <strong>EASA</strong>.A.S.03059 BEECH B200 Installation of one GTX330D and one TDR94. Limited to Beechcraft B200 SN BB-1116, F-<br />
GDJS.Prior to installation of this modification<br />
the installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon<br />
31.05.2007<br />
10<strong>01</strong>4845 S.E.A.M. <strong>EASA</strong>.A.S.03066 F500 Installation of a mode S GTX 330D Garmin<br />
Transponder.<br />
09.11.2006<br />
09.11.2006<br />
Limitation to s/n 500-0319. 10.<strong>04</strong>.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 384/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4939 S.E.A.M. <strong>EASA</strong>.A.S.03196 PIPER PA-23-250 Modification d'installation Radio/Couplage B-<br />
RNAV.Dépose: 2KX 175B+1 B.A. KMA 20+1<br />
ADF KR85 + 1DLE KN65 + 1GPS 155XL +<br />
1ATC KT 76 A.Pose: 1GNS 430 + 1KX 155 +<br />
1B.Q. GMA 340 +1 ADF KR 87 + 1 DME KN<br />
62A + 1 ATC GTX 330 + 1 MD41.<br />
Limited to S/N 27-4727 F-GOPR. 07.11.2007<br />
10<strong>01</strong>4944 S.E.A.M. <strong>EASA</strong>.A.S.03202 REV. 1 PIPER PA-28R-2<strong>01</strong>T Installation modification B-RNAV.Installation of<br />
annunciation unit Mid Continent MD 41-1484.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4970 S.E.A.M. <strong>EASA</strong>.A.S.03250 BEECH F90 Transponder ATC GTX330D, Radio/GPS GNS Modification limited to SN LA-19.AFMS 1609-<br />
530 and Radio/GPS GNS 430 installation. 07-<strong>01</strong>, 1609-07-02 and 1609-07-03 must be on<br />
board.<br />
10<strong>01</strong>5070 S.E.A.M. <strong>EASA</strong>.A.S.03396 PIPER PA-28R-200 Modification d'installation Radio / B-RNAV sans 1. Prior to installation of this modification the<br />
couplage PADépose: 1 boite audio KA 134+1 installer must determine that the<br />
GPS 150XL+1 VHF/VOR KX 155 + IND KI interrelationship between this modification<br />
208 + 1MKRKR21 + 1 ATC KT 76APose: 1 andany other previously installed modification<br />
boite audio/MKR GMA 340 + 1<br />
will introduce no adverse effect upon the<br />
VHF/VOR/GLD/GPS GNS 430 + IND GI airworthiness of the product.2. The ins<br />
10<strong>01</strong>5095 S.E.A.M. <strong>EASA</strong>.A.S.03432 CESSNA 210E STC 1862-08 - Avionic modification for<br />
BRNAV navigation and autopilot coupling.<br />
10<strong>01</strong>5105 S.E.A.M. <strong>EASA</strong>.A.S.03448 SOCATA TB 20 Installation of a GNS 430 W for IFR B-RNAV<br />
"en route" operations, without coupling to<br />
automatic pilot.<br />
07.10.2008<br />
21.09.2007<br />
02.03.2009<br />
Limited to S/N 58625. 29.<strong>04</strong>.2008<br />
1. This installation is limited to TB 20 s/n<br />
791.2. Prior to installation of this modification<br />
the installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse<br />
10<strong>01</strong>5135 S.E.A.M. <strong>EASA</strong>.A.S.03488 BEECH 58 STC 1940-08- Avionic modification for BRNAV Limitation to s/n TH 14<strong>01</strong><br />
navigation and autopilot coupling.<br />
06.05.2008<br />
10<strong>01</strong>5196 S.E.A.M. <strong>EASA</strong>.A.S.03582 PIPER PA-44-180 Modification d'installation B-RNAV : pose L’installation de ce STC est limitée au PA44-<br />
30.09.2008<br />
Annonciateur DWA 1000<br />
180 S/N 4479953081 L'utilisation du GPS en<br />
approche et sur SID's et STAR est interdite1<br />
Pré-requis: FAM 20<strong>04</strong>/08 “Pose GNS 430”<br />
suivant la modification approuvée<br />
<strong>EASA</strong>.A.C.096471 Avant installation de ce<br />
10<strong>01</strong>5214 S.E.A.M. <strong>EASA</strong>.A.S.03629 BEECH 200 Modification d'installation transpondeur Mode<br />
S: dépose 2 transpondeurs KXP 755 + Boite<br />
de commande + 2 antennes ATC / Pose 2<br />
transpondeurs GTX 330D + 4 antennes ATC<br />
1. This modification is valid only for aircraft<br />
Beech 200, S/N BB 406.2.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification wi<br />
10<strong>01</strong>5243 S.E.A.M. <strong>EASA</strong>.A.S.03678 CESSNA 182R MODIFICATION D'INSTALLATION B-RNAV<br />
avec couplage au pilote automatique<br />
Limitation to Cessna 182R S/N 182-68316 30.03.2009<br />
10029007 S.E.A.M. BEECH 58P STC 2589/09 - Radio B-RNAV avec couplage Limited to: S/N TJ-74 Prior to installation of this modification it 25.02.2<strong>01</strong>0<br />
PA<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032905 S.E.A.M. PA-28RT, PA-2<strong>01</strong>T, Avionic modification: dual installation of Garmin<br />
GNS 430W (with GA 35antennas) for B-RNAV<br />
operation with coupling to autopilot,<br />
installationof GMA 340 audio Intercom, KN 62A<br />
DME receiver and WX 500 stormsocpewith<br />
NY163 antenna<br />
17.<strong>04</strong>.2009<br />
05.08.2008<br />
The installation is limited to aircraft PA- Prior to installation of this modification it 07.12.2<strong>01</strong>0<br />
28RT/PA-28T S/N 28R813143.The aircraft must be determined thatthe<br />
must be equipped with a third radionavigation interrelationship between this modification<br />
orradiocommunicator mean independent from and any other previouslyinstalled<br />
the two GNS 430 units.The GNS 430W modification and/ or repair will introduce<br />
software version must be No 3.3. Installation of no adverse effectupon the airworthiness<br />
a<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 385/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10033951 S.E.A.M. FR182 STC 3005/10 rev 0 - Modification d'installation Limitation to Cessna FR182 equipped with Prior to installation of this modification it 22.02.2<strong>01</strong>1<br />
des équipements radio etBRNAV avec ASPEN EFD 1000 and NAVOMATIC300A. must be determined thatthe<br />
couplage au pilote automatique.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035923 S.E.A.M. C90 Installation of a passenger information display,<br />
a Sigma-Tek 5000B-36attitude indicator, a<br />
Garmin GMA 340 audio panel, a Collins ADF-<br />
60Anavigation system, a Garmin GTX 330<br />
transponder, a Garmin G600 primaryand<br />
navigation system with coupling to automatic p<br />
10036296 S.E.A.M. P-<strong>EASA</strong>.A.S.03809 F90 STC 2465/08 Rev 5GNS530W TAWS -<br />
GNS530W - Radar GWX 68 - TAS KTA 870<br />
Installation.<br />
10036367 S.E.A.M. P-<strong>EASA</strong>.A.S.03923 F90 STC 2589/09 Rev 4Dual EFIS G600<br />
installation<br />
100373<strong>04</strong> S.E.A.M. P-<strong>EASA</strong>.A.S.03890 PA-44-180 Avionics upgrade including Aspen Electronic<br />
Flight Display (EFD) 1000Pro system and<br />
Garmin GNS 430 W with coupling to S-TEC<br />
55X automaticpilot<br />
100378<strong>04</strong> S.E.A.M. 1900, 1900C, 1900D, 200, 200C Installation of Garmin 500 Series system with<br />
coupling to autopilotRockwell-Collins FCS 80,<br />
according to SEAM modification file n.<br />
3541/11.<br />
10038255 S.E.A.M. F177RG Installation of a Garmin GNS 400 series<br />
system, a Garmin GA 35 or GA 56GPS<br />
antenna, a Mid Continent MD41 annunciator<br />
and a Garmin GTX 330transponder.<br />
10038454 S.E.A.M. BN-2 Installation of Garmin GNS 400 series system,<br />
GA 35 GPS antenna, GMX 200multifunction<br />
display, GMA 347 audio box, SL30 NAV/COM<br />
system, GTX 330transponder, Mld Continent<br />
MD 41 annunciator, Collins ALT<br />
50radioaltimeter and Indigo One Tracking<br />
system, accordi<br />
10038702 S.E.A.M. DR 400/180 STC 3725/11 rev. 0 dated <strong>04</strong>/<strong>01</strong>/2<strong>01</strong>2 -<br />
Amélioration équipements radionavB-RNAV<br />
This STC is limited to airplane s/n LJ-972.RNP<br />
APCH-VNAV and LPV Approach operations<br />
are not authorised.A third radionavigation or<br />
radiocommunication system independent<br />
fromGNS 430 W units must be<br />
installed.Mechanical instruments must be<br />
installed to back-<br />
Prior to installation of this modification it 27.07.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Limitation to Beech F90 equipped with SPZ200 Prior to installation of this modification it 29.08.2<strong>01</strong>1<br />
autopilot and modifiedaccording SEAM STC must be determined thatthe<br />
2589/09 Dual G600 Installation.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Limitation to Beech F90 equipped with SPZ200 Prior to installation of this modification it 02.09.2<strong>01</strong>1<br />
autopilot and modifiedaccording SEAM STC must be determined thatthe<br />
2465/08 avionics installation.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1) This avionics installation if limited to aircraft Prior to installation of this modification it 17.11.2<strong>01</strong>1<br />
S/N 44-8095025 andit is approved for BRNAV, must be determined thatthe<br />
PRNAV and RNP Approach LNAV<br />
interrelationship between this modification<br />
operations.2) The only authorized mode for and any other previouslyinstalled<br />
GPS coupling to the S-TEC 55X automaticpilot modification and/ or repair will introduce<br />
(AP) is the NAV GPSS mode of the AP (activa no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of this design change must be<br />
performed by SEAM technicalpersonnel. If the<br />
GNS 500 Series system is installed whereas<br />
another Garmin GNSsystem is already<br />
installed on the airplane, a third<br />
independentradiocommunication or<br />
radionavigation syst<br />
Installation of this design change must be<br />
performed by authorised SEAMtechnical<br />
personnel.The aircraft must be equipped with<br />
at least one radionavigation<br />
orradiocommunication mean not similar to the<br />
GNS 400 series unit.This installation is<br />
approved for us<br />
This design change must be installed by SEAM<br />
technical personnel.This installation as<br />
approved for use in BRNAV<br />
operations.Coupling of GNS system to<br />
autopilot is authorised only for CENTURY<br />
2000autopilot.Installation of software updates<br />
must be approved.In<br />
Prior to the installation of this modification<br />
it must be determinedthat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification and/or repair will introduce<br />
noadverse effect upon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.12.2<strong>01</strong>1<br />
<strong>01</strong>.02.2<strong>01</strong>2<br />
17.02.2<strong>01</strong>2<br />
S/N 2105 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.Install<br />
09.03.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 386/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039279 S.E.A.M. DA40D Installation of two Garmin GNS 430 W Installation of this design change is limited to Prior to installation of this modification it 23.<strong>04</strong>.2<strong>01</strong>2<br />
systems, two GA 35 GPS antennas, aGMA airplane S/N D4-002 andit must be performed must be determined thatthe<br />
340 audiopanel, a GTX 330 Mode S<br />
by authorised SEAM technical personnel.This interrelationship between this modification<br />
transponder, a King KN-62A DME andCobham design change is approved for B-RNAV and any other previouslyinstalled<br />
antennas CI 292-2 (VHF), CI 105 (DME), CI operation without coupling ofthe GNS 430 W modification and/ or repair will introduce<br />
102 (MKR)<br />
systems to an autopilot.The airplane mu no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0057 S.E.A.M. REV. 1 P.68 C, P.68 TC (OBSERVER) Installation of Aspen EFD 1000 Pro EFIS and<br />
Mid Continent MD41annunciator according to<br />
SEAM modification n° 2622/11.<br />
10<strong>04</strong><strong>01</strong>61 S.E.A.M. B90, C90, E90 Installation of a Garmin GTS 8xx series Traffic<br />
Advisory System<br />
Initial installation of this design change must be Prior to installation of this modification it 15.06.2<strong>01</strong>2<br />
performed byauthorised SEAM technical must be determined thatthe<br />
personal.This installation is approved for interrelationship between this modification<br />
BRNAV operations with coupling toGarmin and any other previouslyinstalled<br />
GNS 430 or GNS 430 W system and to modification and/ or repair will introduce<br />
Century III autopilot.The modified airplane must no adverse effectupon the airworthiness<br />
of the product.<br />
Initial Installation of this design change must be<br />
performed byauthorized SEAM technical<br />
personnel. The modified aircraft must be<br />
equipped with:-TAS antennas installed<br />
according to SEAM modification No.<br />
2465/11approved under <strong>EASA</strong>.10<strong>01</strong>4783-A<br />
Garmin G600 EFI<br />
10<strong>04</strong>1160 S.E.A.M. 56TC, A56TC, 58, 58A, G58, 95, Installation of Garmin GNS 430 W system, GA Installation of this design change must be<br />
95-55, 95-A55, 95-B55,<br />
35 GPS antenna, GMA 340audiopanel and Mid performed by authorised SEAMtechnical<br />
95-B55A, 95-B55B, 95-C55, Continent MD 41 annunciator according to personnel.This installation is approved for<br />
95-C55A, D55, D55A, E55, E55A, SEAMmodification n°3823/12.<br />
BRNAV operations without coupling toan<br />
B95, B95A, D95A, E95<br />
autopilot.Used of GPS for SID/STAR and<br />
approach procedures is not<br />
authorised.Software upgrad<br />
10029549 S.E.I. SERVIZI ELICOTTERISTICI ITAL P-<strong>EASA</strong>.R.S.<strong>01</strong>549 MD HELICOPTERS 369HS Installation of Emergency Locator Transmitter<br />
(ELT), Artex C406-2HM, P/N369-25543-1<strong>01</strong><br />
10<strong>01</strong>6296 S.I.P. TECHNICAL SERVICES <strong>EASA</strong>.IM.A.S.02593 REV. 1 FAA STC ST09367SC DC-9-81 (MD-81)<br />
DC-9-82<br />
DC-9-83<br />
10<strong>01</strong>6297 S.I.P. TECHNICAL SERVICES <strong>EASA</strong>.IM.A.S.02594 FAA STC ST09389SC DC-9-82<br />
DC-9-83<br />
10<strong>01</strong>6331 S.I.P. TECHNICAL SERVICES <strong>EASA</strong>.IM.A.S.02640 FAA STC NO. ST9949SC BOEING DC-9-81 (MD-81)<br />
BOEING DC-9-82 (MD-82)<br />
BOEING DC-9-83 (MD-83)<br />
Installation of dual Canadian Marconi CMA 900 Prior to installation of this modification the<br />
FMS with GPS sensor (This is a revision of the installer must determine that the<br />
STC ST09367SC already validated by ENAC interrelationship between this modification and<br />
on 2 December 1997 and amended on 5 May any other previously installed modification will<br />
1998 to implement the PRNAV capability.) introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of Single Canadian Marconi CMA<br />
900 FMS with GPS Sensor.<br />
Installation of required sensor and interface for<br />
existing DFDR and FDAU to meet FAR<br />
121.344.<br />
10030551 S4A SOLUTIONS FOR AVIATION, S.L. EC135 P2+ Installation of an Iridium Satellite Telephone on<br />
board<br />
10<strong>04</strong>2171 S4A SOLUTIONS FOR AVIATION, S.L. C-212-200 "Installation of Iridium satellite phone". A<br />
satellite phone is added tothe airplane. This<br />
satellite phone is not located in the cockpit and<br />
itis used only by an operator located at the rear<br />
of the passenger cabin,according to "Plan de<br />
Certification A1203-<br />
Prior to installation of this modification it 14.06.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 24.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Not Applicable Not Applicable 31.03.2<strong>01</strong>0<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
20.12.2007<br />
05.03.2008<br />
10.06.2008<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.06.2<strong>01</strong>0<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.11.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 387/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039<strong>01</strong>7 SA BERINGER 1<strong>01</strong><br />
BRGAP-STC-003(0) dated 30 Jan 2<strong>01</strong>2 - None. Prior to installation of this modification it 30.03.2<strong>01</strong>2<br />
1<strong>01</strong>A<br />
Replacement of wheel and brakesystem.<br />
must be determined thatthe<br />
1<strong>01</strong>AP<br />
interrelationship between this modification<br />
1<strong>01</strong>B<br />
and any other previouslyinstalled<br />
1<strong>01</strong>BC<br />
modification and/or repair will introduce<br />
1<strong>01</strong>D<br />
no adverse effectupon the airworthiness<br />
1<strong>01</strong>P<br />
of the product.<br />
10<strong>04</strong>1414 SA BERINGER REV. 1 ASW 20 BL,ASW 20 C,ASW 20 BRGAP-STC-005(0) - Replacement of wheel<br />
CL<br />
ASW 20 F,ASW 20 FL,ASW 20 B<br />
ASW 20,ASW 20 L<br />
and brake system<br />
10<strong>04</strong>1955 SA BERINGER DR400-100/-120/-120A/-120D/125<br />
DR400-125I/-140/-140B/-160/<br />
DR400-160D/-180/-180R/-180S<br />
DR400-200R/-2+2/-500/-NGL/-RP<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.09.2<strong>01</strong>2<br />
BRGAP-STC-006 - Replacement of brake unit. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airwOr1hiness<br />
of the product.<br />
26.10.2<strong>01</strong>2<br />
10<strong>01</strong>4488 SAAB AB <strong>EASA</strong>.A.S.02550 BEECH A100 Installation of avionics in accordance with Saab This STC is limited to Beech A100, s/n B-217<br />
Aerotech AB, TDM06-<strong>04</strong><br />
19.<strong>04</strong>.2006<br />
10<strong>01</strong>4508 SAAB AB <strong>EASA</strong>.A.S.02582 LEARJET 35A Mission Power -- 20.06.2006<br />
10<strong>01</strong>4936 SAAB AB <strong>EASA</strong>.A.S.03192 CESSNA 560 Replacement of SSR Mode S Transponders<br />
for compliance with Enhanced Surveillance.<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>4937 SAAB AB <strong>EASA</strong>.A.S.03193 CESSNA 650 Replacement of SSR Mode S Transponders<br />
for compliance with Enhanced Surveillance.<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>5123 SAAB AB <strong>EASA</strong>.A.S.03472 MITSUBISHI MU-2B Garmin GTX 330/330D (SSR Mode S<br />
Transponder) upgrades for compliance with<br />
Enhanced Surveillance (EHS) requirements.<br />
27.03.2008<br />
10<strong>01</strong>5162 SAAB AB <strong>EASA</strong>.A.S.03532 LEARJET 35A Mode S Enhanced Surveillance (EHS)<br />
Upgrade.<br />
EHS Non Capable. <strong>01</strong>.07.2008<br />
10029935 SAAB AB MU-2B Installation Provisions/Video Signal in Mitsubishi Target Towing provisions according to Swedish Prior to installation of this modification it <strong>04</strong>.05.2<strong>01</strong>0<br />
MU-2B rear pressurebulkhead<br />
CAA approval C6A/71 mustbe installed. must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031209 SAAB AB P-<strong>EASA</strong>.A.S.03618 REV. 2 382 Installation of Saab Missile Protection System.<br />
The installationconsists of a forward sensor<br />
fairing on both sides of the nose and arear<br />
sensor installation in the tail. The dispensers<br />
are installed onboth sides under the rear edge<br />
of the wing.Inside the a<br />
Aircraft Serial 4954 Only The STC grants no operational approval,<br />
the aircraft operator will needto obtain<br />
operational approval from the Agency or<br />
Authority responsiblefrom the State of<br />
registry and the State in whose airspace<br />
it is to beoperated.Prior to installation of<br />
this modif<br />
10033697 SAAB AB AS 355 E, AS 355 F, AS 355 F1 Installation of New TopEye Mission Box none Prior to installation of this modification it 03.02.2<strong>01</strong>1<br />
AS 355 F2, AS 355 N, AS 355 NP<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038972 SAAB AB C-212-EE TDM10-05 Rev. G titled "Cabin Layout", dated<br />
2<strong>01</strong>2-03-20."New Cabin Layout for Maritime<br />
Surveillance System in CASA<br />
C212".Installation and Mounting of Maritime<br />
Surveillance System and change ofCabin<br />
Layout to accommodate a maximum of 5 crew<br />
members and nopa<br />
All equipment necessary for Maritime<br />
Surveillance Missions shall beinstalled or<br />
added with <strong>EASA</strong> DOA 21J.108 Minor Change<br />
Approvals<br />
21.12.2<strong>01</strong>0<br />
Prior to installation of this modification it 27.03.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 388/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5116 SAAB AB, AERONAUTICS <strong>EASA</strong>.A.S.03465 REV. 1 LEARJET 35A Installation of Honeywell MK VIII EGPWS and Prior to installation of this modification the<br />
25.08.2008<br />
Mission Inhibit System.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>04</strong><strong>04</strong>13 SAAB AB, NYKÖPING MU-2B-20, MU-2B-26 Installation of Aft Pressure Bulkhead and Cabin Mitsubishi MU-2B, S/N: 283, 287, 289, 293,<br />
Pressure Skin Feed Thruprovisions for Antenna 299, 320, 337 and 345<br />
/ Electrical Connectors<br />
Prior to installation of this modification it 02.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4330 SAAB NYGE AERO AB <strong>EASA</strong>.A.S.<strong>01</strong>583 LEARJET 35A Installation of Target Mission Operators<br />
Console<br />
17.11.2005<br />
10028070 SABENA TECHNICS BOD P-<strong>EASA</strong>.A.S.03815 REV. 4 A340-311, A340-312, A340-313 IAGOS ModificationThis STC installs the The modification is applicable to the following Prior to installation of this modification it 30.10.2<strong>01</strong>2<br />
Integration of routine Aircraft measurements aircraft Serial Numbers:MSN 3<strong>04</strong>, 327, 335, must be determined thatthe<br />
intoa Global Observing System.The Initial 347, 352, 354, 355, 377, 379, 390, 433, 434, interrelationship between this modification<br />
Release of the STC was approvingthe and 447On MSN 377, the partial installation of and any other previouslyinstalled<br />
technical provisions installing the IAGOS IAGOS system, according documentref : modification and/ or repair will introduce<br />
system.This Revision 1 approved the activation ECM_F4030_SNT_CNRS_ 12_008_R Issue no adverse effectupon the airworthiness<br />
of t<br />
of the product.<br />
10032216 SABENA TECHNICS BOD F28 MK<strong>01</strong>00 Modification wireless telephones installation. PER AFM Supplement FK100-25-LAIKA-<strong>01</strong>-<br />
FM Issue K dated 29 March 2<strong>01</strong>0Applicable<br />
only to MSN 11368, 11403 and 11406<br />
10032391 SABENA TECHNICS BOD <strong>EASA</strong>.A.S.03671 REV. 2 A330-223 A330-223 "P710" VIP Cabin CompletionThis<br />
STC installs a VIP cabin configuration.Revision<br />
1 was issued to update the Limitation<br />
Section.Revision 2 is issued to capture a<br />
design evolution (9000 VU change)<br />
andassociated documentation update.<br />
10033032 SABENA TECHNICS BOD A318 ALL MODELS<br />
A319 ALL MODELS<br />
A320 ALL MODELS<br />
A321 ALL MODELS<br />
Full provision for EFB Class 2 on Single Aisle<br />
Aircraft<br />
10033281 SABENA TECHNICS BOD <strong>EASA</strong>.A.S.03943 F28 MK <strong>01</strong>00 Fokker 100 CABIN VIP (premod <strong>EASA</strong> STC<br />
A.S.02677)<br />
10037593 SABENA TECHNICS BOD REV. 1 A340-542 VIP Tunisair upgrading projectThis STC installs<br />
a new cabin configuration, with presidential<br />
area.This revision1 updates the Associated<br />
Technical Documentation, in linewith the design<br />
evolution.<br />
10<strong>04</strong>0867 SABENA TECHNICS BOD A320-214 Structural provisions for the installation of<br />
SATCOM antenna<br />
Prior to installation of this modification it 18.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>04</strong>.2<strong>01</strong>2<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
15.12.2<strong>01</strong>0<br />
This Change to STC A.S.02677 does not Aircraft must be in post STC A.S.02677 11.<strong>01</strong>.2<strong>01</strong>1<br />
require a technical change to theaircraft.Private configuration<br />
use only, max 30 passengers<br />
This STC is applicable to MSN 902 MMEL Supplement associated with this<br />
STC / Approval of this MMELsupplement<br />
is not covered by this STC approvalPrior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinsta<br />
22.12.2<strong>01</strong>1<br />
This approval is limited only to MSN 3164.The<br />
approval is limited to 675 Flight Cycles.<br />
Additional analysis shall be done on PSE<br />
to extend life cycle ofaircraft.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 389/<strong>462</strong><br />
31.07.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0868 SABENA TECHNICS BOD A320-214 Installation of SATCOM system This modification can be installed only Prior to installation of this modification it 31.07.2<strong>01</strong>2<br />
concurrently with themodifications approved must be determined thatthe<br />
under <strong>EASA</strong> STC 10<strong>04</strong>0867 (<strong>EASA</strong><br />
interrelationship between this modification<br />
project0<strong>01</strong>0<strong>01</strong>6700).This approval is limited and any other previouslyinstalled<br />
only to MSN 3164.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4573 SABENA TECHNICS DNR <strong>EASA</strong>.A.S.02677 FOKKER F.28 MARK <strong>01</strong>00 Fokker 100 VIP Cabin Maximum approved passenger capacity:<br />
19Limited to serial numbers 11368, 11403,<br />
11406.Refer to AFM Supplement.<br />
10<strong>01</strong>6732 SAGEM AVIONICS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>056 REV. 4 FAA STC SR09263RC-D EC120B SFIM two-axis VFR Autopilot System (SAGEM<br />
PA85)Nota:,,- Original STC: FAA STC<br />
SR09263RC-D, amended 9 February, 2<strong>01</strong>1-<br />
Existing <strong>EASA</strong> STC: 10<strong>01</strong>6732 rev 3- Revision<br />
4 incorporates 2 new configurations related to<br />
minor changeto the FAA STC.<br />
10<strong>01</strong>6737 SAGEM AVIONICS, INC <strong>EASA</strong>.IM.R.S.<strong>01</strong>061 SR09291RC-D EUROCOPTER FRANCE EC 130<br />
B4<br />
10027509 SAGEM AVIONICS, INC P-<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>527<br />
10029542 SANDEL AVIONICS, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.02918<br />
Original STC nbr: FAA STC SR09291RC-D,<br />
amended 06-Oct-2006Installation of a two-axis<br />
REV. 2 FAA STC SR09450RC EC120B<br />
VFR auto-pilot<br />
Original STC: FAA STC SR09450RC,<br />
amended 11-May-2009SAGEM Integrated<br />
Cockpit Display System (ICDS)<br />
FAA STC ST<strong>01</strong>930LA S550 Installation of Sandel Avionics SA4550 Primary<br />
Attitude Display andSandel Avionics SN4500<br />
Primary Navigation Display.<br />
10<strong>01</strong>7096 SAS MAT AVIATION <strong>EASA</strong>.R.S.<strong>01</strong><strong>01</strong>7 EUROCOPTER FRANCE EC 120<br />
B<br />
10<strong>01</strong>64<strong>04</strong> SAVANNAH AIR CENTER, L.L.C. <strong>EASA</strong>.IM.A.S.02733 FAA STC ST03528AT BOMBARDIER BD-700-1A11 Installation, Complete Custom Interior, s/n<br />
10<strong>01</strong>6536 SAVANNAH AIR CENTER, L.L.C. <strong>EASA</strong>.IM.A.S.02913 FAA STC SA02683AT, CAA UK AAN GULFSTREAM IV Installation of L3 Communications Digital Flight<br />
Data Recorder With Teledyne Digital Flight<br />
Installation of FAA STC SR09450RC<br />
(<strong>EASA</strong>.IM.R.S.<strong>01</strong>527) is mandatory<br />
forconfigurations -<strong>01</strong>, -02of SAGEM<br />
Installation Drawing 120-1002Installation of<br />
FAA STC SR09450RC (<strong>EASA</strong>.IM.R.S.<strong>01</strong>527)<br />
is mandatory forconfigurations -03, -<strong>04</strong> of<br />
SAGEM Installation Dra<br />
For night VFR operations, the helicopter must<br />
be fitted with a backupinstrument permitting<br />
attitude control, such as a standby<br />
attitudeindicator or a slip/skid indicator<br />
03.07.2007<br />
Prior to installation of this modification it 14.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.12.2006<br />
Prior to installation of this modification it 24.11.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.03.2<strong>01</strong>0<br />
Upgraded Avionics configuration 1. Limited to aircraft EC120B s/n 1<strong>04</strong>9, F-<br />
GRAE only2. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations s<br />
22.08.2005<br />
9229 Configuration.<br />
Restricted to ASN 9229. <strong>01</strong>.<strong>04</strong>.2008<br />
Only approved for Aircraft manufactured<br />
before 18 August 2000<br />
10028136 SAVANNAH AIR CENTER, L.L.C. FAA STC ST03818AT BOMBARDIER BD-700-1A10<br />
Data Acquisition Unit.<br />
Complete Custom Aircraft Interior - ASN 9287. Restricted to ASN 9287 for a total of 15<br />
passengers.<br />
10031798 SAVANNAH AIR CENTER, L.L.C. FAA STC ST12210AT-T BD-700-1A10 Installation, Complete Custom Interior, ASN<br />
9347 Configuration.<br />
10032322 SAVANNAH AIR CENTER, L.L.C. REV. 1 FAA STC ST03881AT BD-700-1A10 Installation, Complete Custom Interior, S/N<br />
9345 Configuration<br />
03.06.2008<br />
Prior to installation of this modification it <strong>04</strong>.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 93471.Refer to the Prior to installation of this modification it 14.09.2<strong>01</strong>0<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced<br />
interrelationship between this modification<br />
FCOMS.2.WLAN system is compatible only to and any other previouslyinstalled<br />
IEEE 802.11(b).<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Restricted to ASN 9345 and1. Refer to the Prior to installation of this modification it 29.03.2<strong>01</strong>1<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the following<br />
interrelationship between this modification<br />
FCOMS:G862081 Rev NC - FCOMS - WLAN and any other previouslyinstalled<br />
SystemG862092 Rev A - FCOMS - Mid-Cabin modification and/ or repair will introduce<br />
Door2. WLAN system is compatible only to no adverse effectupon the airworthiness<br />
IEEE 802.11(b)<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 390/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032416 SAVANNAH AIR CENTER, L.L.C. FAA STC ST03628AT BD700-1A10 Installation, Complete Custom Interior, S/N Restricted to ASN 9260 and1. Refer to the Prior to installation of this modification it <strong>04</strong>.11.2<strong>01</strong>0<br />
9260 Configuration<br />
Limitations sections of the required AFM must be determined thatthe<br />
Supplement andto the referenced FCOMS.2. interrelationship between this modification<br />
WLAN system is compatible only to IEEE and any other previouslyinstalled<br />
802.11(b).<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4558 SCAI TECH <strong>EASA</strong>.A.S.02657 REV. 3 DR 300/108, DR 300/120<br />
DR 300/125, DR 300/140<br />
DR 300/180 R, DR 315, DR 340<br />
DR 360, DR 380, DR 400/100<br />
DR 400/120 D, DR 400/125<br />
DR 400/120, DR 400/120 A<br />
DR 400/140, DR 400/140 B<br />
DR 400/160, DR 400/160 D<br />
DR 400/180 S, DR 400/NGL<br />
DR 400/180, DR 400/180 R<br />
SCAI-DR315_DR300-108, 120, 125,<br />
140_DR340_DR360-FM-A,SCAI-<br />
DR380_DR300-180R-FM-A, SCAI-DR412-FM-<br />
B, SCAI-DR416-414-FM-B,SCAI-DR418-FM-<br />
B, SCAI-DR221_DR221B-FM-A.Extension of<br />
<strong>EASA</strong>.A.S.02657 to DR221 aircraft.<br />
10034639 SCAI-TECH <strong>EASA</strong>.A.S.02943 F150L, F150M, FA150L, FA150M SCAI-CE150-FM-A Echappement accorde<br />
avec silencieux double flux.<br />
10<strong>01</strong>3928 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.00239 REV. 1 BEECH 400A Installation of a EGPWS Mk. VIII system in<br />
accordance with the Engineering Order Doc.:<br />
2<strong>01</strong>7<strong>01</strong>6-EO-02 Issue 2 or later <strong>EASA</strong><br />
approvedrevision.<br />
None. Prior to installation of this modification the 23.10.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
Limitation to aircraft equipped with engine TCM Prior to installation of this modification it 02.06.2009<br />
0-200-A and propellerMcCauley<br />
must be determined thatthe<br />
1A102/0CM6948.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1. AFM Supplement Document No.<br />
2<strong>01</strong>7<strong>01</strong>6-AM-02 Issue 2 or later <strong>EASA</strong><br />
approved revisions.2. Maintenance<br />
Requirements and Instruction for Continuous<br />
Airworthiness Doc. 2<strong>01</strong>7<strong>01</strong>6-CA-02.<br />
10<strong>01</strong>3944 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.00384 BAE 125 SERIES 800B Installation of an Universal CVR-30B Cockpit 1. This STC is approved only for the product<br />
Voice Recorder in accordance with the configuration as defined in the approved design<br />
Engineering Order Doc: 2022468-EO-<strong>01</strong>, Issue data referred to in the paragraph "Description".<br />
1 orlater <strong>EASA</strong>-approved Revisions. AFM Compatibility with other aircraft/engine<br />
Supplement Document No 2022468-AM-<strong>01</strong> configurations shall be determined by the<br />
Issue 1 or later <strong>EASA</strong>-approved Revisions.<br />
Maintenance<br />
installer.<br />
10<strong>01</strong>3971 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.00766 SAAB SF340A Installation of an ADF 2 Bendix King KDF 806 1. This STC is approved only for the product<br />
System.<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>3994 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>028 LEARJET 55 Installation of a Rockwell Collins ACAS 1. Certification Basis for this STC is CS 25 plus<br />
(TCASII) 4000 with dual Mode S Transponders JAA TGL No 8 and JAA TGL No 13<br />
10<strong>01</strong>3995 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>029 LEARJET 55 Installation of a L3 Digital Flight Data Recorder Certification Basis for this STC is CS 25 31.<strong>01</strong>.2005<br />
10<strong>01</strong>3997 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>032 LEARJET 55 Installation of a Honeywell EGPWS mark VIII Certification Basis for this STC is CS 25 plus<br />
(TAWS)<br />
JAA TGL No 12 "TAWS"<br />
10<strong>01</strong>4<strong>01</strong>5 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>058 REV. 1 AMD/BA FALCON 10 Installation of Rockwell Collins TCAS-4000 incl.<br />
Dual Mode S Transponder TDR-94D in<br />
accordance with the Engineering Order Doc<br />
2022256-EO-<strong>01</strong> Issue 2 or later <strong>EASA</strong><br />
approved revisions<br />
10<strong>01</strong>4<strong>01</strong>6 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>059 REV. 1 AMD/BA FALCON 10 Installation of a Kannad 406 ELT in accordance<br />
with Engineering Order Doc 2022256-EO-03,<br />
Issue 1 or later <strong>EASA</strong> approved revisions<br />
10<strong>01</strong>4<strong>01</strong>7 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>060 REV. 2 AMD/BA FALCON 10 Installation of a Multi Function Radar Display<br />
(MFRD) and EGPWS MK VIII in accordance<br />
with the Engineering Order Doc 2022874-EO-<br />
<strong>01</strong>,Issue 2 or later <strong>EASA</strong> approved revisions<br />
10<strong>01</strong>4025 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>091 BEECH 200<br />
BEECH 200C<br />
BEECH B200<br />
BEECH B200C<br />
10<strong>01</strong>4026 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>092 BEECH 200<br />
BEECH B200<br />
Installation of a Universal TAWS system and<br />
related components.<br />
15.02.2008<br />
07.12.20<strong>04</strong><br />
08.06.2005<br />
31.<strong>01</strong>.2005<br />
31.<strong>01</strong>.2005<br />
30.05.2005<br />
14.05.2005<br />
09.08.2007<br />
<strong>04</strong>.<strong>01</strong>.2007<br />
Installation of GPS TNL-21<strong>01</strong> I/O APPR+ 11.02.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 391/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4027 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>093 REV. 1 BEECH 1900<br />
1. Installation of Dual Mode S Transponder For installations on or after 31-Jan-2007, this<br />
05.02.2007<br />
BEECH 200C<br />
MST-67A System with ELS capabilities change is limited to the configuration of aircraft<br />
BEECH 300<br />
(installation prior to 31-Jan-2007)2.<br />
/ equipment type as listed underItem 4. in<br />
BEECH 300LW<br />
Installation of Dual Mode S Transponder MST- Engineering Order, Doc. No. 2021128-EO-03,<br />
BEECH B200C<br />
67A System with ELS and EHS capabilities Issue 5, or later approved issue:<br />
BEECH B300<br />
BEECH B300C<br />
(installation on or after 31-Jan-2007)<br />
10<strong>01</strong>4028 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>094 BEECH 200<br />
Installation of Multifunction Display MFD-640 &<br />
11.02.2005<br />
BEECH B200<br />
RP 1008<br />
10<strong>01</strong>4036 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>109 CESSNA 525 Installation of Honeywell KMH 980 Multi-<br />
Hazard Awareness System including TCAS I<br />
and EGPWS (Class B).<br />
11.<strong>04</strong>.2005<br />
10<strong>01</strong>4037 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>110 CESSNA 525 Installation of WX-500 Stormscope System 11.<strong>04</strong>.2005<br />
10<strong>01</strong>4038 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>111 CESSNA 525 Installation of Bendix/King KLN 94 GPS<br />
System.<br />
11.<strong>04</strong>.2005<br />
10<strong>01</strong>4050 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>132 LEARJET 35<br />
Installation of Honywell CAS 67A ACAS/TCAS Certification Basis: applicable requirements of<br />
31.05.2005<br />
LEARJET 35A<br />
II with dual MST-67A Mode S Transponder CS25 plus JAA TGLs No 8 and 13 1.<br />
10<strong>01</strong>4091 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>189 REV. 1 CESSNA 500<br />
CESSNA 550<br />
CESSNA 560<br />
CESSNA S550<br />
10<strong>01</strong>4092 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>190 CESSNA 650 Installation of FreeFlight 21<strong>01</strong> I/O APPROACH<br />
PLUS GPS Navigation System<br />
10<strong>01</strong>4093 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>191 CESSNA 650 Installation of Honeywell CAS 67A TCAS II<br />
System, including Dual MST 67A Mode S<br />
Transponders<br />
10<strong>01</strong>4095 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>193 BAE ATP Installation of Universal Terrain Awareness<br />
Warning System (TAWS)<br />
10<strong>01</strong>4096 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>194 Installation of Universal UNS-1L Flight<br />
Management System<br />
10<strong>01</strong>4111 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>216 BEECH 300<br />
BEECH B300<br />
10<strong>01</strong>4150 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>270 BEECH 200<br />
BEECH 300<br />
BEECH B200<br />
BEECH B300<br />
10<strong>01</strong>4151 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>271 BEECH 200<br />
BEECH 300<br />
BEECH B200<br />
BEECH B300<br />
Installation of Kannad 406 AF ELT 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
07.<strong>04</strong>.2005<br />
- 25.08.2005<br />
- 25.08.2005<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of Honeywell CAS 67A<br />
ACAS/TCAS II with Dual MST-67A Mode S<br />
Transponder<br />
EGPWS Installation on Airbus A300/A310 Refer to AFM Supplement Ref. Dc113-0846<br />
Rev B and to Maintenance Planning Document<br />
Supplement DC114-0846-00 rev A.<br />
Installation of Dual GTX 330D Mode S<br />
Transponder System.<br />
10<strong>01</strong>4162 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>294 BAE 125 -800 SERIES Installation of a Rockwell Collins TCAS 4000<br />
with dual TDR-94D Mode S Transponder<br />
10<strong>01</strong>4199 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>349 REV. 1 BEECH 200<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B300<br />
Installation of TAWS ST3400 system.Revision<br />
of the AFM Supplement related to a Minor<br />
Change to <strong>EASA</strong>.A.S.<strong>01</strong>349.Installation of<br />
TAWS ST3400 system.Revision of the AFM<br />
Supplement related to a Minor Change to<br />
<strong>EASA</strong>.A.S.<strong>01</strong>349.<br />
10<strong>01</strong>4200 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>350 CESSNA 500 Installation of Honeywell KMH 880 Multi-<br />
Hazard Awareness System<br />
10<strong>01</strong>4226 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>389 CESSNA 300 SERIES<br />
CESSNA 400 SERIES<br />
10<strong>01</strong>4242 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>451 CESSNA 500<br />
CESSNA 550<br />
CESSNA S550<br />
10<strong>01</strong>4245 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>455 CESSNA 300 SERIES<br />
CESSNA 400 SERIES<br />
Installation of GNS 430A/530A<br />
COMM/NAV/GPS Systems<br />
Installation of GPS400 in center panel with<br />
GAD 42 adapter for roll steering<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.This STC is approved onl<br />
26.07.2005<br />
26.07.2005<br />
30.05.2005<br />
28.<strong>04</strong>.2005<br />
29.06.2005<br />
26.07.2005<br />
26.02.2007<br />
This STC is approved only for the product<br />
02.<strong>01</strong>.2006<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
none 20.09.2005<br />
24.<strong>01</strong>.2006<br />
Installation of GTX 330 Mode S Tansponder 20.09.2005<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 392/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4295 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>537 BEECH 400A (HAWKER 400 XP) IInstallation of a Rockwell Collins TCAS 4000<br />
with dual TDR-94D Transponder<br />
15.11.2005<br />
10<strong>01</strong>4313 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>561 BEECH 400A (HAWKER 400 XP) Installation of a L3 Digital FDR and Teledyne<br />
FDAU<br />
22.11.2005<br />
10<strong>01</strong>4333 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>587 LETECKE ZAVODY L 410 UVP- Installation of Honeywell CAS 67A TCAS II<br />
22.02.2006<br />
E20<br />
including dual MST 67A Mode S Transponder<br />
10<strong>01</strong>4343 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>603 PIPER PA-34-200<br />
PIPER PA-34-200T<br />
PIPER PA-34-220T<br />
Installation of KMD 850 Multi Function Display 03.<strong>04</strong>.2006<br />
10<strong>01</strong>4360 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>625 BEECH A36 Replacement of existing KI-525A HSI system<br />
with new KI-825 EHSI system<br />
20.02.2006<br />
10<strong>01</strong>4406 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.<strong>01</strong>7<strong>01</strong> BEECH A36 Title: GARMIN GNS 430/530 upgrade for GPS<br />
approachDescription: Upgrade of existing GNS<br />
430/530 for GPS approach and installation of<br />
annunciator panel<br />
13.02.2006<br />
10<strong>01</strong>4435 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02484 REV. 1 CESSNA 500, CITATION<br />
CESSNA 550 CITATION II<br />
CESSNA 560 (CITATION V)<br />
CESSNA S550, (CITIATION S/II)<br />
10<strong>01</strong>4455 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02509 BOMBARDIER SD-3-60-SHERPA<br />
BOMBARDIER SD-3-SHERPA<br />
10<strong>01</strong>4469 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02530 CESSNA 500, CITATION<br />
CESSNA 550 CITATION II<br />
CESSNA 560 (CITATION V)<br />
CESSNA S550, (CITIATION S/II)<br />
10<strong>01</strong>4489 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02551 LEARJET 35<br />
LEARJET 35A<br />
10<strong>01</strong>4496 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02559 DORNIER DO 228-100<br />
DORNIER DO 228-1<strong>01</strong><br />
DORNIER DO 228-200<br />
DORNIER DO 228-2<strong>01</strong><br />
DORNIER DO 228-212<br />
10<strong>01</strong>4497 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02560 DORNIER DO 228-100<br />
DORNIER DO 228-1<strong>01</strong><br />
DORNIER DO 228-200<br />
DORNIER DO 228-2<strong>01</strong><br />
DORNIER DO 228-212<br />
Sandel ST3400 TAWS Installation left hand<br />
and right hand<br />
Collins TCAS 4000 with dual TDR-94D<br />
Transponder Installation<br />
Certifications Basis of the Change: CS 25,<br />
additionally JAA Leaflet No. 12 (TAWS)<br />
Certification Basis of the Change: CS-25,<br />
additionally JAA leaflet No. 8 Rev. 2 (ACASII),<br />
JAA Leaflet No. 13 Rev. 1 (Mode S ELS)<br />
02.<strong>04</strong>.2006<br />
<strong>01</strong>.08.2006<br />
Installation of a Garmin GNS 530A and a<br />
Honeywell Marker Beacon KR21, for EU basic<br />
RNAV operations<br />
None 13.06.2006<br />
Installation of Dual Universal UNS-1E FMS in Certification Basis of the change: CS 25,<br />
06.<strong>04</strong>.2006<br />
Learjet 35/35A<br />
Amdt. <strong>01</strong><br />
Sandel ST3400 TAWS installationInstallation of --<br />
Class A TAWS/RMI Indicator in the right hand<br />
instrument panel with a remote Annunciator<br />
and Switching unit on the left hand instrument<br />
panel. Single 3" indicator is used to show<br />
compliance<br />
22.06.2006<br />
Installation of Honeywell CAS 67A ACAS II<br />
System incl. Dual Mode S XPDR<br />
10<strong>01</strong>4539 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02626 Universal TAWS Installation incl. MFD-640 Certification Basis of the Change: CS 25<br />
Amendment 1, additionally JAA Leaflet No. 12<br />
(TAWS)<br />
10<strong>01</strong>4540 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02627 Installation of Universal UNS-1L(-1K+) FMS Certification Basis of the Change: CS 25<br />
Amendment 1, additionally JAA Leaflet No. 10<br />
(Precision RNAV), AMC 20-4 (Basic RNAV),<br />
AMC 20-5 (GPS)<br />
10<strong>01</strong>4550 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02643 CESSNA 5<strong>01</strong>, CITIATION<br />
CESSNA 551, CITIATIONII<br />
10<strong>01</strong>4551 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02644 CESSNA 500, CITATION<br />
CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION II)<br />
Installation of Dual Garmin GNS 430A/530A 1. Certification basis of the Change CS-23,<br />
and 3rd COMM in Cessna Citation I model 5<strong>01</strong> additionally:2. AMC 20-4 (Basic RNAV),<br />
and Citation II model 551.<br />
AMC 20-5 (GPS), AMC 25-11 (Electronic<br />
Display Systems) and JAA TGL 7, rev.1 (VHF<br />
Com 8.33 KHz).3. Prior to installation of this<br />
modification the installer must dete<br />
Installation of Dual Garmin GNS 430A/530A 1. Certification Basis of the Change CS-25<br />
and 3rd COMM in Cessna Citation I model 500 Amdt. 2, additionally:2. AMC 20-4 (Basic<br />
and Citation II model 550, S550.<br />
RNAV), AMC 20-5 (GPS), AMC 25-11<br />
(Electronic Display Systems) and JAA TGL 7,<br />
rev.1 (VHF Com 8.33 KHz)3. Prior to<br />
installation of this modification the installer mu<br />
10<strong>01</strong>4556 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02654 Honeywell EGPWS MK VI Installation Certification Basis of the Change CS 25,<br />
additionally JAA TGL 12 (TAWS)<br />
10<strong>01</strong>4559 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02658 Trimble TNL-21<strong>01</strong> I/O Aproach + GPS System Certification Basis of the Change CS 25,<br />
Installation<br />
additionally <strong>EASA</strong> AMC 20-4 (BRNAV) and<br />
AMC 20-5 (GPS)<br />
10<strong>01</strong>4582 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02688 BAE 125 -800 SERIES<br />
Installation of an In-flight Entertainment System This change is limited to airplanes equipped<br />
HAWKER 800<br />
HAWKER 800 XP<br />
with ARINC 429 Interface to GPS / FMS<br />
10<strong>01</strong>4592 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02703 BAE JETSTREAM 3100<br />
Sandel ST3400 TAWS installation Certification Basis of the Change CS 25,<br />
BAE JETSTREAM 3200<br />
additionally JAA TGL No. 12 (TAWS)<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 393/<strong>462</strong><br />
12.06.2006<br />
27.06.2006<br />
27.06.2006<br />
20.06.2007<br />
20.06.2007<br />
06.06.2006<br />
06.06.2006<br />
22.03.2007<br />
21.07.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4605 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02728 CESSNA 650 CITATION III Installation of Honeywell Multi-Function Radar This STC is only applicable to Aircraft without<br />
11.09.2006<br />
CESSNA 650 CITATION VI Display (MFRD) and as an option a Honeywell EFIS system and integrated MFD.<br />
Primus 400 Radar system.<br />
10<strong>01</strong><strong>462</strong>2 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02756 CESSNA 500, CITATION Installation of a “Flight Display Systems” The IFE sound shall be overrided by the PA<br />
31.08.2006<br />
CESSNA 550 CITATION II Entertainment System: DVD player, Map system<br />
CESSNA 560 (CITATION V)<br />
CESSNA S550 (CITATION II)<br />
computer and 2 LCD displays<br />
10<strong>01</strong>4632 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02774 BEECH 60<br />
Installation of Mode S Transponder Garmin<br />
11.10.2007<br />
BEECH A60<br />
BEECH B60<br />
GTX 330D<br />
10<strong>01</strong>4641 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02791 CESSNA 550 BRAVO<br />
Honeywell EGPWS MK VIII Installation Certification Basis of the Change: CS 25<br />
03.11.2006<br />
CESSNA 560<br />
Amanedment 1m, aditionally JAA Leaflet No.<br />
12 (TAWS)<br />
10<strong>01</strong>4668 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02826 Honeywell EGPWS MK VI<br />
1. This STC is only applicable for aircraft<br />
30.<strong>01</strong>.2007<br />
Installation.Installation of Honeywell Enhanced which have all the following equipment already<br />
Ground Proximity Warning System<br />
installed:Honeywell (Bendix-King) IN-182<br />
EGPWS/TAWS.<br />
or KMD-850 Radar DisplayKN-53 NAV<br />
SystemKRA-405 Radar AltimeterKCS-55A<br />
Compass SystemComputer Instruments Corp.<br />
10<strong>01</strong>4672 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02832 BAE 125 -800 SERIES<br />
HAWKER 800<br />
HAWKER HS 125-600 SERIES<br />
HAWKER HS 125-700 SERIES<br />
10<strong>01</strong>4673 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02833 BAE 125 -800 SERIES<br />
HAWKER 800<br />
HAWKER HS 125-600 SERIES<br />
HAWKER HS 125-700 SERIES<br />
10<strong>01</strong>4689 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02852 BOEING 707-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
Installation of a Universal Terrain Awareness<br />
Warning System (TAWS).<br />
Installation of a Universal UNS-1F and / or<br />
UNS-1L Flight Management System for Basic<br />
RNAV, Precision RNAV Operations and Nonprecision<br />
Approaches and also as a primary<br />
means of navigation for oceanic/remote<br />
operations.<br />
Transponder S Mode Elementary and<br />
Enhanced Surveillance / Upgrade of existing<br />
dual diversity Transponder Mode S Installation<br />
1. This change is limited to following<br />
configuration of the aircraft / equipment type:all<br />
airplanes equipped with* ARINC 429 Air<br />
Data Computers with temperature<br />
compensation, and * Rockwell Collins<br />
Proline 2 or 4 RADALT, VOR/ILS, and*<br />
Display S<br />
1. This change is limited to following<br />
configuration of the aircraft / equipment type:all<br />
airplanes equipped with* Rockwell Collins<br />
Proline 1 (only NAV receiver), Proline 2 or 4<br />
Navigation Equipment,and * Rockwell Collins<br />
analog HSI’s or EFIS 85/8<br />
Certification Basis of the change: CS 25 Amdt.<br />
2, additionally JAA TGL 13 Rev. 1 (Mode S<br />
ELS), JAA TGL 18 (Mode S EHS, compliance<br />
to JAA NPA 20-12a shown voluntarily.This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
10<strong>01</strong>4690 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02853 CESSNA 650 Honeywell EGPWS MK VIII Installation Certification Basis of the Change: CS 25<br />
Amendment 2, additionally JAA Leaflet No. 12<br />
(TAWS).<br />
10<strong>01</strong>4695 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02861 BAE 125 -800 SERIES<br />
HAWKER 800<br />
10<strong>01</strong>4702 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02872 REV. 2 HAWKER 800<br />
HAWKER 800 XP<br />
HAWKER HS 125-700 SERIES<br />
10<strong>01</strong>4703 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02874 FAIRCHILD SWEARINGEN SA<br />
226-TC<br />
FAIRCHILD SWEARINGEN SA<br />
227<br />
FAIRCHILD SWEARINGEN SA<br />
227-AC<br />
FAIRCHILD SWEARINGEN SA<br />
227-BC<br />
10<strong>01</strong>4729 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02907 REV. 1 CESSNA 500, CITATION<br />
CESSNA 550 BRAVO<br />
CESSNA 550 CITATION II<br />
CESSNA 560 (CITATION V)<br />
10<strong>01</strong>4759 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02948 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
Installation of a Honeywell Class A Enhanced<br />
Ground Proximity Warning System<br />
EGPWS/TWAS for aircrafts equipped with a<br />
compatible MFD or weather radar display.<br />
Mode S Transponder Upgrade for existing<br />
Collins transponder system.<br />
1. This change is limited to following<br />
configuration of the aircraft / equipment type:*<br />
Rockwell Collins EFIS 85/86 with ARINC 453<br />
interface, and* Airdata system with ARINC<br />
429 interface (TSO-C10b or C106), and*<br />
Rockwell Collins VIR-432 with ARINC<br />
1. This STC approves only the installation of<br />
the parts contained in the above section<br />
“Description of Type Design Change”. This<br />
STC grants no operational approval to this<br />
installation, that will need to be obtained from<br />
the State of registry for the parti<br />
Installation of a Garmin GPS 400 System with This change is limited to following configuration<br />
Remote Annunciator Switch Panel in Fairchild of the aircraft / equipment type:-Airdata system<br />
Swearingen SA226-TC, SA227-AC, SA227 BC must be either ARINC 429, RS232 or Grey<br />
code as defined in the GPS 400 installation<br />
manual, and- any model of Rockwell Collins<br />
VIR-30/31/32 VOR/ILS<br />
Mode-S upgrade for existing Honeywell MST<br />
67A transponder system.<br />
Upgrade of existing MST-67A Transponder<br />
System<br />
10.<strong>01</strong>.2007<br />
10.<strong>01</strong>.2007<br />
03.<strong>01</strong>.2007<br />
13.02.2007<br />
03.<strong>01</strong>.2007<br />
06.03.2007<br />
14.12.2006<br />
N/A 03.<strong>04</strong>.2007<br />
As defined in Scandinavian Avionics<br />
Modification ref 2036080.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 394/<strong>462</strong><br />
12.02.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4763 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02953 CESSNA 425 Replacement of one existing Transponder This change is limited to the configuration of<br />
11.05.2007<br />
System by a Garmin GTX 330D Mode-S aircraft / equipment type as listed under Item 4.<br />
Transponder System<br />
in Engineering Order, Doc. No. 2037527-EO,<br />
Issue 3, dated <strong>04</strong>-May-2007 or later approved<br />
issuePrior to installation of this modification the<br />
installer must dete<br />
10<strong>01</strong>4767 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02959 CESSNA 500, CITATION Installation of Honeywell Multi-Function Radar 1. Prior to installation of this modification the<br />
16.02.2009<br />
CESSNA 550 CITATION II (MFRD) and an optional Honeywell Primus installer must determine that the<br />
CESSNA S550, (CITIATION S/II) Radar System, if the existing radar is interrelationship between this modification and<br />
incompatible with the MFRD.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>4777 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02975 CESSNA 650 CITATION III Installation of Honeywell TRA-45A Terrain Aircraft Serial No. 650-0037 with FOCA STC<br />
29.05.2007<br />
CESSNA 650 CITATION VI Display/ Radio Altimeter Indicator.<br />
Z34-44-05 installed as defined in Scandinavian<br />
CESSNA 650 CITATION VII<br />
Avionics Modification Reference 2037690.<br />
10<strong>01</strong>4778 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02976 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4800 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03003 SAAB 340B<br />
SAAB SF340A<br />
10<strong>01</strong>4807 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03<strong>01</strong>1 CESSNA 5<strong>01</strong>, CITIATION<br />
CESSNA 551, CITIATIONII<br />
10<strong>01</strong>4809 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03<strong>01</strong>3 BEECH 200<br />
BEECH 200C<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>4823 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03036 CESSNA 500, CITATION Installation of a single diversity Mode-S<br />
transponderGarmin GTX 330D and a new top<br />
antenna.<br />
10<strong>01</strong>4879 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03107 REV. 1 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4910 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03154 LEARJET 31<br />
LEARJET 31A<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
10<strong>01</strong>4957 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03227 REV. 1 DC-9-10 SERIES<br />
DC-9-20 SERIES<br />
DC-9-30 SERIES<br />
DC-9-40 SERIES<br />
DC-9-50 SERIES<br />
DC-9-81 (MD-81)<br />
DC-9-82<br />
DC-9-83<br />
DC-9-87 (MD-87)<br />
MD-88<br />
MD-90<br />
10<strong>01</strong>4965 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03238 CESSNA 5<strong>01</strong><br />
CESSNA 551<br />
10<strong>01</strong>5008 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03308 CESSNA 500, CITATION<br />
CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION II)<br />
Installation of Sandel ST3400 TAWS System. <strong>04</strong>.<strong>04</strong>.2007<br />
Installation of Universal UNS-1L/K+, FMSsystem.<br />
N/A 13.<strong>04</strong>.2007<br />
Installation of a Honeywell CAS 67A ACAS II This change is limited to the configuration of<br />
03.<strong>04</strong>.2007<br />
System and a Dual MST 67A Mode S aircraft / equipment type as listed under Item 4.<br />
Transponder System<br />
in Engineering Order, Doc. No. 2038224-EO,<br />
Issue 2, dated 21-Mar-2007 or later approved<br />
issue.<br />
Installation of Universal UNS-1L (-1K+) FMS This change is limited to the configuration of<br />
aircraft / equipment type as listed under Item 4.<br />
in Engineering Order, Doc. No. 2037417-EO,<br />
Issue 2, dated 09-Feb-2007 or later approved<br />
issue.<br />
13.02.2007<br />
Mode S Upgrade of existing Honeywell<br />
Transponder System RCZ-833 to comply with<br />
ICAO requirements for Mode S ELS and<br />
EHS.Minor change to <strong>EASA</strong>.A.S.03107:AFM<br />
Supplements for different Downlinked Aircraft<br />
Parameters.Mode S Upgrade of existing<br />
Honeywell Transpo<br />
Installation of a SANDEL ST3400 TAWS<br />
System (Class A)<br />
Mode S elementary and enhanced Upgrade of<br />
existing dual transponder system.<br />
Dual installation of Transponder Mode S<br />
System, MST 67A with PS 550 or PS 578A<br />
Mode S Control Panel, with ELS and EHS<br />
capability.<br />
Installation of Honeywell GNS-XLS FMS and<br />
L3 Standby horizon Reference System.<br />
According to EUROCONTROL definition this<br />
equipment with approval <strong>EASA</strong>.A.S.03036 is<br />
non-EHS compliant.Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously insta<br />
As defined in Scandinavian Avionics<br />
Modification ref 2037689.As defined in<br />
Scandinavian Avionics Modification ref<br />
2037689.<br />
Previous required aircraft configuration:All<br />
models equipped with:• Compatible Air Data<br />
Computers with ARINC 429 interface, and•<br />
Analogue Radio Altimeter interface (except<br />
ARINC 552) such asRockwell Collins ALT-<br />
50/50A , ALT-55 or Honeywell RT-200/300,<br />
and\<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
This change is limited to the configuration of<br />
aircraft / equipment type as listed under Item 4.<br />
in <strong>EASA</strong> approved Engineering Order, Doc.<br />
No. 2<strong>04</strong>1564-EO, Issue 2, dated 13-Aug-2007<br />
or later approved issue<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 395/<strong>462</strong><br />
06.06.2007<br />
20.11.2007<br />
22.02.2008<br />
24.07.2008<br />
26.09.2007<br />
28.11.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5052 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03373 DE HAVILLAND CANADA DHC6- Dual Directional Gyro, Dual EHSI/RMI and As detailed in the AFM 2<strong>04</strong>3963-AM 05.03.2008<br />
300<br />
DE HAVILLAND DHC6-310<br />
audio System.<br />
10<strong>01</strong>5057 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03379 BEECH 200<br />
Installation of Garmin GWX 68 / Garmin GMX This change is limited to the configuration of<br />
30.<strong>01</strong>.2008<br />
BEECH 200C<br />
200 Weather Radar System.<br />
aircraft / equipment type as listed under Item<br />
BEECH 300<br />
4. of <strong>EASA</strong> approved Engineering Order, Doc.<br />
BEECH 300LW<br />
No. 2038539-EO, Issue 3, dated 24-Jan-2008<br />
BEECH B200<br />
or later approved issue. The system is not<br />
BEECH B200C<br />
BEECH B300<br />
BEECH B300C<br />
approved for operati<br />
10<strong>01</strong>5061 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03384 BEECH 200<br />
Installation of Garmin GPS 500 System This change is limited to the configuration of<br />
30.<strong>01</strong>.2008<br />
BEECH 200C<br />
(including compliance with AMC 20-4, AMC 20- aircraft / equipment type as listed under Item<br />
BEECH 300<br />
5 and FAA AC20-138A)<br />
4. of <strong>EASA</strong> approved Engineering Order, Doc.<br />
BEECH 300LW<br />
No. 2038540-EO, Issue 2, dated 22-Jan-2008<br />
BEECH B200<br />
or later approved issue. The system is not<br />
BEECH B200C<br />
BEECH B300<br />
BEECH B300C<br />
approved for operati<br />
10<strong>01</strong>5063 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03389 Sandel ST3400 TAWS Installation. 30.05.2008<br />
10<strong>01</strong>5067 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03393 CESSNA 500, CITATION Installation of Honeywell ART2100/KMD850 1. This STC is exclusively applicable for<br />
12.03.2008<br />
CESSNA 550 CITATION II Weather Radar System.<br />
aircraft which have the equipment listed in<br />
CESSNA S550, (CITIATION S/II)<br />
chapter 4 of the Scandinavian Avionics<br />
Engineering Order 2<strong>04</strong>4352-EO Issue 2<br />
already installed;2. Prior to installation of this<br />
modification the installer must deter<br />
10<strong>01</strong>5089 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03424 FALCON 10 Dual TDR-94D Transponder Upgrade to Previous required aircraft configuration:•<br />
22.02.2008<br />
provide limited Enhanced Surveillance Aircraft equipped with Dual TDR-94D (-007/-<br />
Transponder Mode S capability (Non EHS 008) and installation compliant with Elementary<br />
Capable).<br />
Mode S requisites.• Mode S Transponder<br />
Antenna Diversity• Collins TCAS II System•<br />
Dual ADC’s installation with<br />
10<strong>01</strong>5113 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03460 FAN JET FALCON SERIES C<br />
FAN JET FALCON SERIES D<br />
FAN JET FALCON SERIES E<br />
FAN JET FALCON SERIES F<br />
FAN JET FALCON SERIES G<br />
MYSTERE FALCON 20-C5<br />
MYSTERE FALCON 20-D5<br />
MYSTERE FALCON 20-E5<br />
MYSTERE FALCON 20-F5<br />
MYSTERE FALCON 200<br />
10<strong>01</strong>5128 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03479 BOMBARDIER DHC-6 SERIES<br />
300<br />
10<strong>01</strong>5131 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03482 BEECH 300<br />
BEECH 300LW<br />
BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>5132 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03483 BEECH 200<br />
BEECH 200C<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B300<br />
BEECH B300C<br />
Dual TDR-94D Transponder Installation<br />
Upgrade to provide both Elementary and<br />
Enhanced Surveillance Transponder Mode S<br />
Capabilities.<br />
Honeywell EGPWS MK VI, TRA-45 Display<br />
installation.<br />
Installation of an L3 F-1000 Digital Flight Data<br />
Recorder System<br />
Installation of a Universal CVR-30B or CVR-<br />
120 Cockpit Voice Recorder<br />
10<strong>01</strong>5137 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03490 CESSNA 650 CITATION VII UPGRADE of existing FMS Universal UNS-<br />
1Csp to UNS-1Csp+ to comply with P-RNAV<br />
requirements.<br />
10<strong>01</strong>5170 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03544 BEECH 400<br />
BEECH 400A<br />
Mode S ELS/EHS Upgrade of existing<br />
transponder system.<br />
Previous required aircraft configuration:•<br />
Aircraft equipped with Dual TDR-94D<br />
installation with Mode S Diversity Antenna<br />
installation and Radio Tuning Unit RTU-4220•<br />
ADC’s with ARINC 429 Interface.• Collins<br />
TCAS II System• Collins Proline 4 Av<br />
This change is limited to the configuration of<br />
aircraft / equipment type as listed under Item<br />
4. of <strong>EASA</strong> approved Engineering Order, Doc.<br />
No. 2<strong>04</strong>5502-EO, Issue 2, dated 24-Apr-2008<br />
or later approved issue.<br />
This change is limited to the configuration of<br />
aircraft / equipment type as listed under Item<br />
4. of <strong>EASA</strong> approved Engineering Order, Doc.<br />
No. 2<strong>04</strong>5503-EO, Issue 2, dated 23-Apr-2008<br />
or later approved issue.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 396/<strong>462</strong><br />
09.06.2008<br />
28.03.2008<br />
05.05.2008<br />
05.05.2008<br />
25.08.2008<br />
10.06.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5183 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03563 Replacement of existing COM 1 / 2 and NAV 1 This change is limited to the configuration of<br />
/ 2 systems by Garmin GNS 530 (GNS #1) and aircraft / equipment type as listed under Item<br />
17.06.2008<br />
Garmin GNS 430 (GNS #2)<br />
4. of <strong>EASA</strong> approved Engineering Order, Doc.<br />
No. 2<strong>04</strong>6711-EO, Issue 1, dated 21-Apr-2008<br />
or later approved issue.<br />
10<strong>01</strong>5194 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03580 BAE 125 -800 SERIES<br />
HAWKER HS 125-600 SERIES<br />
HAWKER HS 125-700 SERIES<br />
Installation of a Digital Flight Data Recorder. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>5274 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03769 LEARJET 55 Dual Universal UNS-1F FMS Installation. • Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.• Th<br />
10<strong>01</strong>7138 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>237 EUROCOPTER DEUTSCHLAND Installation of Bendix/King Radar Altimeter<br />
BO-105<br />
System KRA 405/405B<br />
10<strong>01</strong>7188 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>325 EUROCOPTER FRANCE EC 120<br />
B<br />
10<strong>01</strong>7234 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>412 EUROCOPTER FRANCE EC 120<br />
B<br />
10<strong>01</strong>7235 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>413 EUROCOPTER FRANCE EC 120<br />
B<br />
VHF COMM, XPDR, ICS, Directional Gyro and<br />
Attitude Indicator.<br />
Installation of Avionics System Garmin GNS<br />
480 / Honeywell KY-96A / Garmin GTX 33 as<br />
defined in Engineering Order 2<strong>04</strong>2580-EO .<br />
Installation of several avionics system as<br />
definened into Engineering.Order No. 2<strong>04</strong>2316<br />
10028447 SCANDINAVIAN AVIONICS A/S P-<strong>EASA</strong>.A.S.03759 REV. 1 A318, A319, A320, A321<br />
– EO issue 2<br />
Installation of provisions for the use of Dual<br />
navAero Electronic FlightBag Class 2 (EFB)<br />
System<br />
10033960 SCANDINAVIAN AVIONICS A/S B200 Provisions for and installation of a SLAR and a<br />
Homer antenna.<br />
10<strong>01</strong>3976 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>01</strong>4039 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>01</strong>4148 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>01</strong>4696 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
<strong>EASA</strong>.A.S.0097 REV. 2 550 (CITATION BRAVO)<br />
550 (CITATION II)<br />
560 (CITATION ULTRA)<br />
560 (CITATION V)<br />
S550 (CITATION S/II)<br />
<strong>EASA</strong>.A.S.<strong>01</strong>112 REV. 2 CESSNA 525<br />
CESSNA 525A<br />
<strong>EASA</strong>.A.S.<strong>01</strong>268 REV. 1 1. SA226-TC, SA227-AC<br />
1. SA227-BC<br />
2. A226-T, SA226-AT<br />
2. SA226-T(B), SA227-AT<br />
2. SA227-TT<br />
<strong>EASA</strong>.A.S.02863 REV. 1 1. A226-T, SA226-AT<br />
1. SA226-T(B), SA227-AT<br />
1. SA227-TT<br />
2. SA226-TC, SA227-AC<br />
2. SA227-BC<br />
1. The installation of this STC is not approved<br />
for Night VFR approved aircraft.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modific<br />
This change is limited to Rotorcraft equipped<br />
with Garmin GNS 480 Installation.<br />
15.06.2009<br />
17.<strong>04</strong>.2009<br />
21.<strong>04</strong>.2006<br />
09.10.2007<br />
19.03.2008<br />
<strong>04</strong>.<strong>04</strong>.2008<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>01</strong>.2<strong>01</strong>0<br />
Applicable for serial number BB-1936 only. The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
Installation of an L3 Digital Flight Data Limited to:S/N 550-00<strong>01</strong> through 550-0733<br />
Recorder Revision 2 was raised due to missing (Citation II)S/N 550-08<strong>01</strong> through 550-1136<br />
technical document references inRevision 1 (Citation Bravo)S/N 560-00<strong>01</strong> through 560-<br />
0259 (Citation V)S/N 560-0260 through 560-<br />
0538 (Citation Ultra)S/N S550-00<strong>01</strong> through<br />
S550-<strong>01</strong>60 (Citation S/II)<br />
Installation of dual GTX 330D Mode S<br />
Transponder systems.Installation of dual GTX<br />
330D Mode S Transponder systems.<br />
Installation of Honeywell CAS 67A ACAS II<br />
System with dual Mode STransponder<br />
1. According to Engineering Order 2<strong>01</strong>9974-<br />
EO-05, Issue 41. According to Engineering<br />
Order 2<strong>01</strong>9974-EO-05, Issue 4<br />
This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2027<strong>04</strong>6-EO, Issue 2, dated<br />
25-Oct-2<strong>01</strong>0, or later approved issue.<br />
Installation of Sandel ST3400 TAWS System This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2035640-EO, issue 4, dated<br />
25-Oct-2<strong>01</strong>0, or later approved issue.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 397/<strong>462</strong><br />
22.02.2<strong>01</strong>1<br />
05.10.2<strong>01</strong>0<br />
25.02.2008<br />
08.11.2<strong>01</strong>0<br />
08.11.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4973 SCANDINAVIAN AVIONICS DESIGN <strong>EASA</strong>.A.S.03259 REV. 5 737-300, -400, -500, -600 Installation of a Dual navAero Electronic and Not Applicable Prior to installation of this modification it 14.11.2<strong>01</strong>1<br />
GMBH<br />
737-700, -800, -900<br />
logging display system.Change consisting in<br />
must be determined thatthe<br />
installing a dual portable Class 2 EFB's<br />
interrelationship between this modification<br />
t.BagC2system<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5305 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10026864 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10027<strong>01</strong>4 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10028068 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10028206 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10028452 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10031128 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10031822 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
<strong>EASA</strong>.A.S.03894 REV. 1 1. 200, 200C, 300, 300LW<br />
2. B200, B200C, B300, B300C<br />
P-<strong>EASA</strong>.A.S.03938 REV. 1 CESSNA 500, 550 GARMIN GPS 400W/500W installation<br />
Revision 1 supersedes the previous issue of<br />
this STC to delete the modelS550 from the<br />
applicability list for correction.<br />
P-<strong>EASA</strong>.A.S.03849 500 (CITATION AND CITATION I) Installation of Honeywell MST 67A Dual Mode<br />
S XPDR transponder.<br />
Dual TDR-94D Mode S ELS/EHS Transponder This change is limited to the configuration of<br />
System Upgrade, and optional forADS-B aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2073065-EO, Issue 1, dated<br />
22-Mar-2<strong>01</strong>2, or later approved issue<br />
forinstallations without ADS-B, or Issue 2,<br />
dated<br />
P-<strong>EASA</strong>.A.S.03732 650 (CITATION VII) Software upgrade of installed Honeywell GNS-<br />
XL or GNX-XLS FMS system forP-RNAV<br />
operation<br />
P-<strong>EASA</strong>.R.S.<strong>01</strong>586 R22 BETA Title: Camera with supportDescription: Optional<br />
Installation of a camera turret, related<br />
recorderand data link transmitter system in<br />
accordance with Master Document<br />
List2053852 DOC issue 2, dated <strong>04</strong>.12.2009.<br />
The installation is based onScandinavian<br />
Avionic<br />
P-<strong>EASA</strong>.R.S.<strong>01</strong>580 REV. 1 EC 120 B Replacement of existing SAFT Ni-Cad. battery<br />
with Concorde lead acidbattery RG-350.Note:<br />
this STC is issued for the purpose of<br />
transfering STC No. 10028452from Airalpha<br />
A/S (DOA 21J.268) to new STC holder<br />
Scandinavian AvionicsDesign GmbH (DOA<br />
21J.<strong>01</strong>4)<br />
<strong>EASA</strong>.R.S.<strong>01</strong>449 EUROCOPTER FRANCE AS<br />
365N<br />
EUROCOPTER FRANCE AS<br />
365N1<br />
EUROCOPTER FRANCE AS<br />
365N2<br />
EUROCOPTER FRANCE AS<br />
365N3<br />
ATR 42-200/300/320 Installation of Rockwell Collins TCAS-94<br />
System with Single TDR-94DSystem, as per<br />
Scandinavian Avionics Engineering Order<br />
2056096-EO issue1 dated 27th September<br />
2<strong>01</strong>0 or later <strong>EASA</strong> approved revisions.<br />
The limitations according to Aircraft Flight<br />
Manual Supplement205<strong>462</strong>8-AM are<br />
applicable.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
30.03.2<strong>01</strong>2<br />
1) Prior to installation of this modification 18.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
None 1. Prior to installation of this modification 31.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
Limited to: S/N 650-70<strong>01</strong> thru 650-7119 This Prior to installation of this modification it 30.11.2009<br />
STC applies only for Single or Dual FMS GNS- must be determined thatthe<br />
XL or GNS-XLSconfiguration, approved for B- interrelationship between this modification<br />
RNAV operation. Intermixing with other FMSis and any other previouslyinstalled<br />
not approved within this STC.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
- S/N 05<strong>01</strong> and subsequent,,- Pitot heat and<br />
Search Light must not be installed,,<br />
Not Applicable 10.12.2009<br />
None The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21A.118A.The installation of<br />
this modification by third persons is<br />
subject towritten permission of the<br />
approval holder.Prior to installation of this<br />
modification the installer must be<br />
12.12.2<strong>01</strong>2<br />
None No additional EWIS ICAS tasks over<br />
those already identified by theoriginal TC<br />
Holder for the applicable aircraft models<br />
are needed asconsequence of the<br />
implementation of this STC.Prior to<br />
installation of this modification it must be<br />
determined thatthe inte<br />
11.10.2<strong>01</strong>0<br />
25.06.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 398/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031899 SCANDINAVIAN AVIONICS DESIGN<br />
HAWKER 800XP Installation of an International Communications Model Hawker 800XP, S/N: 258358 Prior to installation of this modification it 20.09.2<strong>01</strong>0<br />
GMBH<br />
Group Inc, ICS-100Iridium Satellite Telephone.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032285 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10032445 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10033395 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10033781 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10033782 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10034415 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10036450 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10036673 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
REV.1 CESSNA 500<br />
CESSNA 550<br />
CESSNA S550<br />
P-<strong>EASA</strong>.A.S.03767 BEECH 1900C, AIRLINER<br />
BEECH 200<br />
BEECH 200C<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B300<br />
BEECH B300C<br />
P-<strong>EASA</strong>.A.S.03768 200, 200C, B200<br />
B200C, 300, 300LW, B300<br />
B300C, 1900C<br />
SF340A AND 340B Installation of Collins TCAS-94 system with<br />
dual Collins TDR-94Dtransponders.<br />
SA226-T(B), SA227-AT, SA227-TT Installation of Garmin GNS 530AW / GNS<br />
SA26-AT, SA226-T, SA226-AT 430AW as dual installationtogether with a<br />
Honeywell KMR 675 Marker Beacon Receiver<br />
GPS / Navigation / Communication, Dual<br />
Garmin GNS 430/530 AWinstallationThe<br />
installation includes GPS antenna and single<br />
marker beacon receiver(KMR 675 or 51Z6)<br />
installation<br />
Installation of Sandel SA4550 EADI and<br />
Sandel SA4500 EHSI CollinsAHS-1000<br />
Installation of Garmin GNS 430AW/GNS<br />
530AW<br />
<strong>EASA</strong>.A.S.03858 BEECH 400, 400A Installation of various Entertainment Systems<br />
acc.: Engineering OrderDoc.: 2051195-EO<br />
Compliance Record Doc.: 2051195-COR<br />
P-<strong>EASA</strong>.A.S.03703 SD3-30, SD3-60<br />
SD3-SHERPA, SD3-60 SHERPA<br />
GULFSTREAM 200 / GALAXY UPGRADE OF ROCKWELL COLLINS TDR-<br />
94D MODE S TRANSPONDER SYSTEM<br />
FORENHANCED (EHS) SURVEILLANCE<br />
CAPABILITY.<br />
Transponder system NOT approved for ELS or Prior to installation of this modification it 22.10.2<strong>01</strong>0<br />
EHS.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2061255-EO, issue 1, dated<br />
26-Oct-2<strong>01</strong>0, or later approved issue.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
08.11.2<strong>01</strong>0<br />
None - Directional Gyro or AHRS with synchro 21.<strong>01</strong>.2<strong>01</strong>1<br />
output (XYZ)- Analog HIS<br />
(RD<strong>04</strong>4/RD650)/ADI (AD650) and RMI<br />
(332C)- Honeywell SPZ 500 AP/FD- One<br />
Receiver/Transmitter VHF-20B or VHF-<br />
22x with CTL-22/20 or 313N-5A Control<br />
Panel- DME with 2*5 parallel DME tuning-<br />
Air<br />
This change is limited to the configuration of The installation of this modification by <strong>01</strong>.07.2009<br />
aircraft / equipment typeas listed under Item 4. third persons is subject towritten<br />
in <strong>EASA</strong> approved Engineering Order, Doc. permission of the approval holder, and<br />
No.2050691-EO, issue 1, dated 25-May-2009, having the appropriateapproved<br />
or later approved issue.<br />
documentation at one's disposal. Prior to<br />
installation of this modification it must be<br />
determined thatthe inte<br />
This change is limited to the configuration of The installation of this modification by <strong>01</strong>.07.2009<br />
aircraft / equipment typeas listed under Item 4. third persons is subject towritten<br />
in <strong>EASA</strong> approved Engineering Order, Doc. permission of the approval holder, and<br />
No.20S1374-EO, issue 1, dated 10-Jun-2009, having the appropriateapproved<br />
or later approved issue.<br />
documentation at one's disposal. Prior to<br />
installation of this modification it must be<br />
determined thatthe inte<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.07.2009<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.09.2<strong>01</strong>1<br />
Installation of GARMIN GPS-400 None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.09.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 399/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036958 SCANDINAVIAN AVIONICS DESIGN<br />
BAE 146, AVRO 146-RJ Provision for a Dual NAVAERO t.BagC2 Class None This STC for the provision for a dual 19.10.2<strong>01</strong>1<br />
GMBH<br />
2 Electronic Flight BagSystem<br />
Class 2 Electronic Flight Bag hasbeen<br />
assessed using the guidance in JAA<br />
Temporary Guidance Leaflet (TGL)No.<br />
36. As part of that airworthiness<br />
assessment a limited evaluationwas<br />
made of the proposed EFB installation o<br />
10037345 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10038456 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10039000 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>04</strong>0003 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>04</strong><strong>04</strong>72 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>04</strong>0973 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>04</strong>2855 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
CESSNA 525B Installation of L3 FA2100 Digital FDR S/N 525B-135 and onAccording limitation<br />
section of AFM-S<br />
ATP Installation of a Five Panel Universal EFI-890R<br />
EFIS.<br />
1. 200, 200C, 300, 300LW<br />
2. B200, B200C, B300, B300C<br />
REV. 1 MU-300 (DIAMOND I)<br />
MU-300 (DIAMOND IA)<br />
Installation of Universal UNS FMS System This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2073065-EO, Issue 1, dated<br />
22-Mar-2<strong>01</strong>2, or later approved issue.<br />
B300, B300C Installation of Mission Antennas and a Drop<br />
Tube<br />
10<strong>01</strong>4565 SCHERDEL ENGINEERING Ltd. <strong>EASA</strong>.A.S.02665 Change of Empty Mass and Ballast<br />
Requirements for the Glider LS1-f<br />
10<strong>01</strong>5154 SCHERDEL ENGINEERING Ltd. <strong>EASA</strong>.A.S.03519 DG 400<br />
DG 500 M<br />
DG 600M<br />
DG 800A<br />
SCHEMPP JANUS CM<br />
SCHEMPP NIMBUS 4M<br />
Prior to installation of this modification it 18.11.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.02.2<strong>01</strong>2<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
none This STC must be installed in<br />
concurrence with the Scandinavian<br />
AvionicsMinor Changes as referenced in<br />
their Document 2069196-EO.This STC<br />
does not cover Changes in Cabin<br />
Layout.Prior to installation of this<br />
modification it must be determined<br />
thatthe interr<br />
Digital FDR Installation This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2076242-EO, Issue 1, dated<br />
26-June-2<strong>01</strong>2, or later approved issue.<br />
29.03.2<strong>01</strong>2<br />
08.06.2<strong>01</strong>2<br />
The installation of this modification by 09.07.2<strong>01</strong>2<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
,,documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
ATP FMS Upgrade for P-RNAV none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>2<br />
228-200/-2<strong>01</strong>/-202/-212 Installation of GARMIN GTN750 / GTN650 and - This change is limited to the configuration of The installation of this modification by 20.12.2<strong>01</strong>2<br />
Sandel SN4500 EHSI<br />
aircraft and equipmentas defined in the third persons is subject towritten<br />
Engineering Order, Doc. No. 2077918-EO, permission of the approval holder and<br />
Section 4- LNAV/VNAV or LPV is not disposal of the approvedappropriate<br />
permittedIf the holder agrees to permit another documentation.Prior to installation of this<br />
person to use this certificate toalter the p modification it must be determined<br />
thatthe interrelationship b<br />
Alternate fuel lines for Rotax engine powered<br />
glider.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
19.02.2007<br />
For all serial numbers. 11.06.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 400/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5202 SCHERDEL ENGINEERING Ltd. <strong>EASA</strong>.A.S.03599 SCHEMPP CIRRUS Standard Cirrus: Weight of nonlifting parts Prior to installation of this modification the<br />
02.10.2008<br />
increase with winglets.Doc. No. 07-278-005, installer must determine that the<br />
rev. 2.Doc. No. 07-278-006, rev. 3<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1003<strong>04</strong>20 SCHERDEL ENGINEERING Ltd. ASK 21, ASK 21 MI ASK 21 Front Instrument Panel Modification -<br />
Modification of the ASK 21front seat instrument<br />
panel to allow more leg space for the pilot<br />
None None 15.06.2<strong>01</strong>0<br />
10038786 SCHERDEL ENGINEERING Ltd. 1. DUO DISCUS, 2. DISCUS A<br />
3. DISCUS BT, 4. DUO DISCUS T<br />
5. NIMBUS 4M, 6. VENTUS A<br />
7. STANDARD CIRRUS<br />
8. VENTUS BT, 9. CIRRUS<br />
10<strong>01</strong>5763 SEAPLANES WEST INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>799 TCCA STC SA<strong>04</strong>-63 CESSNA 182E<br />
CESSNA 182F<br />
CESSNA 182G<br />
CESSNA 182H<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
10027470 SECURAPLANE TECHNOLOGIES, Inc. P-<br />
<strong>EASA</strong>.IM.A.S.03268<br />
FAA STC ST<strong>01</strong>809LA SEE APPROVED MODEL LIST<br />
(AML)<br />
10038222 SECURAPLANE TECHNOLOGIES, INC. FAA STC SA<strong>01</strong>696LA SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Cockpit Ventilation Modification None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
14.03.2<strong>01</strong>2<br />
Installation of Aerocet 3400 Amphibious Float<br />
Conversion.<br />
Installation of Hawker 975W0640 Sealed Lead<br />
Acid Battery<br />
1. This STC confers no Operational<br />
Approval, that must be sought from the<br />
National Airworthiness Authority of the country<br />
of registration.2. This STC is approved only<br />
for the product configuration as defined in the<br />
approved design data referred to in<br />
17.07.2006<br />
This approval is limited to those aircraft listed in 1) Prior to installation of this modification 05.10.2009<br />
the AML andequipped with lead acid battery. the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
Installation of Hawker Part Number<br />
None Prior to installation of this modification it 30.<strong>01</strong>.2<strong>01</strong>2<br />
9750W0370 or 9750W0370-8 Series24Volt 43<br />
must be determined thatthe<br />
Ah Sealed Lead Acid Battery.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>3938 SEFA <strong>EASA</strong>.A.S.00352 REV. 1 BEECH B200 - Installation of calibration workbench ref. 1. Applicable only for F-GJFA s/n BB-1270, F-<br />
STNA "Margouillat1" according to the 02-11<strong>04</strong>- GJFC s/n BB-1347 and F-GJFE s/n BB1399<br />
DIR document.- Installation of calibration aircraft.2. Prior to installation of this<br />
workbench ref. STNA "Margouillat1".Revision modification the installer must determine that<br />
1: Extension of STC <strong>EASA</strong>.A.S.00352 with a the interrelationship between this modification<br />
minor change to another aircraf<br />
and any other previously inst<br />
10<strong>01</strong>4362 SEGELFLUGGRUPPE SIEMENS<br />
MUENCHEN<br />
<strong>EASA</strong>.A.S.<strong>01</strong>629 DIAMOND HK 36 TC Optional operation with skis instead of wheels<br />
in winterOne piece for serial-number 36730<br />
10039286 SEGINUS Inc. FAA STC ST02954CH BN2A-8/-9/-20/-21/-26/-27<br />
BN2B-20/-21/-26/-27<br />
BN2T/-4R/-4S<br />
Installation of a replacement pitot static probe<br />
P/N DU130-24 inaccordance with FAA STC<br />
ST02954CH.<br />
10<strong>01</strong>4058 SELL GmbH <strong>EASA</strong>.A.S.<strong>01</strong>142 BOEING 767-300 Replacement of galley G3A P/N1<strong>01</strong>60F23-<br />
00000with a new galley P/N 1<strong>01</strong>60F23A00000<br />
designed by Sell GmbHaccording to Sell<br />
Engineering Order Doc. No. EO WA 151<strong>04</strong>3,<br />
Issue May 7 20<strong>04</strong><br />
10<strong>01</strong>4575 SELL GmbH <strong>EASA</strong>.A.S.02679 BOEING 777-200<br />
BOEING 777-300<br />
Interior Re-configuration of Forward Galley<br />
Complex for Emirates airline.<br />
16.02.2009<br />
31.07.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.<strong>04</strong>.2<strong>01</strong>2<br />
Limited to B777-200/300 models serial<br />
numbers 29324 and 29325.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 4<strong>01</strong>/<strong>462</strong><br />
11.02.2005<br />
18.<strong>01</strong>.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4856 SELL GmbH <strong>EASA</strong>.A.S.03080 REV. 1 BOEING 777-300 Galley Reconfiguration and Replacement for Limited to B777-300 serial numbers: 28680,<br />
31.10.2007<br />
Emirates Airlines<br />
28687, 29062, 29063, 29064, 29067, 29395,<br />
29396, 32697, 32699, 32700, 32702<br />
10<strong>01</strong>4275 SERAM SARL <strong>EASA</strong>.A.S.<strong>01</strong>511 CESSNA 337D Installation of one KX 155A Immunity FM, one 1. This STC is limited to Cessna 337D SN 337-<br />
23.08.2005<br />
GNS430 and GI106A with BRNAV capability 1<strong>04</strong>8. 2. Autopilot coupled with GNS 430<br />
forbidden. 3. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
10<strong>04</strong>2367 SERAM SARL SEE <strong>EASA</strong> APPROVED MODEL Installation of a Garmin GNS 430/A/W/AW Initial installation of this design change must be Prior to installation of this modification it 27.11.2<strong>01</strong>2<br />
LIST<br />
system, a GA 35/56 GPS antenna,a GI 106A performed byauthorised SERAM technical must be determined thatthe<br />
CDI indicator, a Bendix/King KX 155<br />
personnel. This installation is approved for interrelationship between this modification<br />
NAV/COM system, aKI-203/4/8/9 VOR/ILS VFR, IFR, RNAV and RNP<br />
and any other previouslyinstalled<br />
indicator, a KN 62A DME receiver, GPS Approachoperations without coupling of modification and/or repair will introduce<br />
annunciationlights and AV22, KA60, CI 105 navigation systems to an autopilot or aflight no adverse effectupon the airworthiness<br />
antennas.<br />
director. LPV<br />
of the product.<br />
10<strong>01</strong>6022 SHADIN AVIONICS <strong>EASA</strong>.IM.A.S.02188 ST02115CH CESSNA 500<br />
CESSNA 550<br />
CESSNA 560<br />
CESSNA S550<br />
Validation of FAA STC ST02115CHInstallation<br />
of a dual Shadin "ADC 6000 System RVSM<br />
Capable": hardware provisions for RVSM<br />
cpability.<br />
This STC does not provide RVSM capability to<br />
the aircraft (compliance to RVSM airworthiness<br />
requirements are not part of this STC):a<br />
separate STC has to be applied.Airplane Flight<br />
Manual Supplement, Shadin Document No.<br />
DN2807A-006, Revision B, dated 23 Sep<br />
10<strong>01</strong>6036 SHADIN AVIONICS <strong>EASA</strong>.IM.A.S.02205 FAA STC SA02098CH CESSNA 5<strong>01</strong> Validation of FAA STC SA02098CH – The installer must determine, if this design is<br />
“Installation of dual Shadin ADC 6000 Air Data compatible with previously approved<br />
Computer System” for RVSM capability modifications. If the holder agrees to permit<br />
another person to use this certification or alter<br />
a product, the holder must give the other<br />
person written evidence of that pe<br />
10034421 SHADIN AVIONICS FAA STC SE578GL SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10034457 SHADIN AVIONICS FAA STC SH582GL BELL 206B, B-1, L, L-1, L-3<br />
BELL 407<br />
Fuel Flow Transducer Installation / Installation<br />
of Shadin fuel flowtransducer in the fuel line<br />
between the fuel control unit (FCU) and thefuel<br />
injector.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.12.2006<br />
10.<strong>04</strong>.2007<br />
<strong>04</strong>.<strong>04</strong>.2<strong>01</strong>1<br />
Installation of Digital Fuel Flow Meter. None. Rotorcraft modified in accordance with<br />
Shadin Report 4119 must have theengine<br />
modified in accordance with <strong>EASA</strong> STC<br />
10034421(FAA STC SE578GL).Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modificatio<br />
08.<strong>04</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>5809 SHOWA AIRCRAFT USA INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>878 ST<strong>01</strong>621SE BOEING 747-400 Installation of an Upper Deck Galley on Boeing 18.12.2006<br />
10<strong>01</strong>5846 SIDDHIS AERONAUTICAL DESIGN<br />
CORP.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>946 REV 3 TCCA STC SA97-71, ISSUE 6 BOMBARDIER CL-600-1A11 (CL- Installation of Fin Mounted Radome/ Antenna<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3A<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3R<br />
BOMBARDIER CL-600-2B16 (6<strong>04</strong>)<br />
BOMBARDIER CL-600-2B19<br />
(SERIES<br />
System (Structural Provisions only).<br />
1. The installation shall be visually inspected<br />
for external damage every 1200 hours and for<br />
lightning damage every flight in severe<br />
weather.2. The total weight of the antenna<br />
and the installed equipment shall not exceed<br />
18.1 kg.3. The additional<br />
10<strong>01</strong>5842 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.<strong>01</strong>937 FAA STC ST09559AC CESSNA C5<strong>01</strong> Installation of Williams/ Rolls FJ44-2Aengines The installer must determine, if this design is<br />
in accordance with FAA STC ST09559AC and compatible with previously approved<br />
Sierra Ind. Drawing SI360-000, dated modifications. If the holder agrees to permit<br />
27.02.2002. or later FAA approved Revision. another person to use this certification to alter<br />
a product, the holder must give the other<br />
person written evidence of that pe<br />
10<strong>01</strong>5851 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.<strong>01</strong>951 ST09630AC CESSNA 5<strong>01</strong> Installation of Meggitt Engine Instrument<br />
Display System according to FAA STC<br />
ST09630AC.<br />
The installer must determine, if this design is<br />
compatible with previously approved<br />
modifications. If the holder agrees to permit<br />
another person to use this certification to alter<br />
a product, the holder must give the other<br />
person written evidence of that pe<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 402/<strong>462</strong><br />
29.05.2007<br />
08.03.2007<br />
15.03.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6178 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02407 FAA STC SA29NW CESSNA 4<strong>01</strong><br />
Robertson STOL ModificationInstallation of As referred in FAA STC SA29NW:Max. Flap<br />
19.03.2008<br />
CESSNA 402<br />
fowler flaps, flap actuated droop ailerons, flap Extension Speed VFE : 10° Flap 195 mph<br />
actuated trim and anti-servo rudder trim tab in (CAS) 30°<br />
accordance with Drawing List No. 24<br />
Flap 145 mph (CAS)Min. Single Engine<br />
Control Speed VMC : 10° Flap 83 mph<br />
(CAS)<br />
10<strong>01</strong>6339 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02649 FAA STC SA80RM CESSNA 550 Installation of Extended Range Fuel Tank and Cessna Service Bulletin 34-15 or 34-23 (ref.<br />
11.06.2008<br />
relocation of Aft Pressure Bulkhead.<br />
Note 7 in TCDS A22CE, latest rev.) must be<br />
incorporated unless modified aircraft with full<br />
cabin tank fuel, minimum crew and required<br />
ballast is within maximum zero fuel weight and<br />
C.G. limits.<br />
10<strong>01</strong>6340 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02650 FAA STC SA174RM CESSNA 550 Installation of an extended width cabin door. 03.07.2008<br />
10<strong>01</strong>6443 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02788 FAA STC SA1689WE CESSNA 172P Installation of drooped ailerons in flaps down 1. Floatplane Models 172A thru 172H are<br />
13.05.2008<br />
mode, contoured wing leading edges, except only eligible with Franklin Engines 6A-350-C1<br />
for 172M, 172N, and 172P), and wing per STC SA340NW (215HP) or 6A-350-C2<br />
stallfences.<br />
per STC SA1334WE (180 HP). 2. Fixed tabs<br />
as shown on R/STOL Systems, Inc. Drawing<br />
10-100 required on Floatplane Model 172E.<br />
Th<br />
10<strong>01</strong>6447 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02793 REV. 1 FAA STC SA8829SW CESSNA 500<br />
Installation of Inertial Reel Assy.´s on Pilot and None. Prior to installation of this modification it 06.12.2<strong>01</strong>2<br />
CESSNA 550 CITATION II Co-Pilot ShoulderHarnessIn accordance with<br />
must be determined thatthe<br />
Sierra Master Drawing List, SI220-000, rev. A,<br />
interrelationship between this modification<br />
date28 March 1994.Validation of FAA approval<br />
and any other previouslyinstalled<br />
STC SA8829SW.This is an amendment to<br />
modification and/ or repair will introduce<br />
<strong>EASA</strong>.IM.A.S.02793 to include Cess<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6463 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02809 FAA STC SA8437SW CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION II)<br />
10<strong>01</strong>6464 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02810 FAA STC SA09<strong>01</strong>1SC CESSNA 550 CITATION II<br />
CESSNA S550<br />
10<strong>01</strong>6465 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02811 REV. 1 FAA STC SA09229SC CESSNA 500<br />
CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION S/II)<br />
10030649 SIERRA INDUSTRIES Ltd. REV. 1 FAA STC SA3634SW 206H, T206H LANDPLANES<br />
P206 A, D, E LANDPLANES<br />
U206 LANDPLANES A, B, D<br />
U206 LANDPLANES E, F, G<br />
Installation of radome quick release<br />
mechanism.FAA STC SA8437SW.<br />
Gear Horn Silence Switch,FAA STC<br />
SA09<strong>01</strong>1SC<br />
Installation of Gas Cylinder Nose baggage<br />
Door OpenersIn accordance with Sierra Master<br />
Drawing List, SI380-000, rev. C, date24 Sept<br />
1996.Validation of FAA approval STC<br />
SA09229SC.This is an amendment to<br />
<strong>EASA</strong>.IM.A.S.02811 to include Cessna Model<br />
500 asan app<br />
Auxiliary Fuel System: Installation of three<br />
auxiliary bladder type fueltanks in each wing in<br />
accordance with FAA STC SA3634SW,<br />
revision 4,dated 30.03.2<strong>01</strong>0. This <strong>EASA</strong> STC<br />
is a revision of LBA STC (EMZ) 0393/673,<br />
673a, dated05.05.1993.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
28.03.2008<br />
27.03.2008<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.12.2<strong>01</strong>2<br />
- Cessna P206 A, D and E model landplanes<br />
(S/N P206-<strong>01</strong>61 throughP206-00647) -<br />
Cessna U206 model landplanes A, B,<br />
D, E, F, G (S/N U206-<strong>04</strong>38through<br />
U206-<strong>04</strong>649) - Cessna 206H and T206H<br />
model landplanes (S/N 206-080<strong>01</strong> to present<br />
andS/N T206-080<strong>01</strong> to pre<br />
10036302 SIERRA INDUSTRIES Ltd. FAA STC ST02363LA HAWKER 800XP Installation of Honeywell TFE731-50R Engines. Limited to Hawker 800XP aircraft fitted with<br />
Honeywell SPZ-8000 AvionicsSystem,<br />
and:Winglets installed under Hawker<br />
Beechcraft (HBC) Mod Kit 140-1703 -Service<br />
Bulletin 57-3810, <strong>EASA</strong> approval ref<br />
<strong>EASA</strong>.IM.A.C.<strong>01</strong>451.<br />
10037473 SIERRA INDUSTRIES Ltd. FAA STC SA1435WE 180H Installation of drooped ailerons in flap down<br />
mode, re-contoured wingleading edge in<br />
accordance with FAA STC SA1435WE.<br />
Prior to installation of this modification it 17.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 30.08.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
S/N 18051446 through 18052284<br />
Prior to installation of this modification it 29.11.2<strong>01</strong>1<br />
onlyInstallation of SC-100 Stall Warning must be determined thatthe<br />
system is not included.CG range: straight line interrelationship between this modification<br />
between points- Amphibian with (+42.2 ) to and any other previouslyinstalled<br />
(+43.9) @ 2950 lb.- EDO 597-2790 (+36.0) to modification and/ or repair will introduce<br />
(+43.9) @ 2258 lb. or lessControl Surface no adverse effectupon the airworthiness<br />
Movement<br />
of the product<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 403/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6389 SIERRACIN/SYLMAR <strong>EASA</strong>.IM.A.S.02718 FAA STC ST<strong>01</strong>840NY BOMBARDIER DHC-8-100 Installation of Sierracin/Sylmar Windshield Prior to installation of this modification the<br />
14.08.2008<br />
SERIES<br />
Assembly P/N 802600-11/-12, Ref.: FAA STC installer must determine that the<br />
BOMBARDIER DHC-8-200 ST<strong>01</strong>840NY.<br />
interrelationship between this modification and<br />
SERIES<br />
any other previously installed modification will<br />
BOMBARDIER DHC-8-300<br />
introduce no adverse effect upon the<br />
SERIES<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6390 SIERRACIN/SYLMAR <strong>EASA</strong>.IM.A.S.02719 REV. 1 FAA STC ST<strong>01</strong>839NY BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
BOMBARDIER DHC-8-400<br />
SERIES<br />
10<strong>01</strong>6716 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>0 FAA STC SR00836NY SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6717 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>1 FAA STC SR<strong>01</strong>131NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6718 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong><strong>01</strong>2 FAA STC SR<strong>01</strong>593NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6733 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>057 FAA STC SR00033NY SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6734 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>058 SR<strong>01</strong>596NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6735 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>059 FAA STC SR<strong>01</strong>132NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6736 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>060 FAA STC SR<strong>01</strong>608NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
Installation of Sierracin/Sylmar Windshield<br />
Assembly P/N 802600-09/-10, Ref. FAA STC<br />
ST<strong>01</strong>839NY<br />
Installation of Cargo Compartment Baggage<br />
Liner.<br />
Installation of Luminescent Systems Helicopter<br />
Emergency Egress System (HEELS)<br />
Installation of Keystone Helicopter Utility<br />
Interior Panels<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. Keystone Helicopter Corp. Maintenance<br />
Manual S-76A, B&C Baggage Liner, Report<br />
No MM00081 dated February 17, 1997, as<br />
required.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Keystone Helicopter Instructions for<br />
Continued Airworthiness Report No IC00735<br />
Rev_dated June 11, 20<strong>04</strong> or later approved<br />
revision. 2. It is a prerequisite to have<br />
previously approved brackets installed for each<br />
individual panel installation as denoted i<br />
Installation of Grease Fittings. 1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Universal Avionics Systems Corporation UNS-<br />
1 Multi-Mission Management Systems (MMMS)<br />
with SCN 9<strong>01</strong>.X Software<br />
Honeywell KTA870 Traffic Advisory (TAS)<br />
displayes on a Honeywell KD550<br />
Multifunctional Display (MFD)Ass.:Report<br />
ER00566 Certification PlanRFM Supplement<br />
FM00566<br />
Installation of Aircell ST 3100 Satellite<br />
Telephone System<br />
10<strong>01</strong>6753 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>082 SR00688NY SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6773 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>108 FAA STC SR<strong>01</strong>958NY-D SIKORSKY S-76C Installation of Rockwell Collins TDR-94D<br />
Transponder with Elementary Surveillance<br />
10<strong>01</strong>6774 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>109 FAA STC SR<strong>01</strong>960NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
15.08.2008<br />
11.<strong>04</strong>.2005<br />
19.<strong>04</strong>.2005<br />
22.<strong>04</strong>.2005<br />
22.<strong>04</strong>.2006<br />
06.03.2006<br />
18.11.2005<br />
23.02.2006<br />
Installation of Medical Interior 12.05.2006<br />
Installation of baggage access panel (ground<br />
use only), forward facing seat, seat pan and<br />
wet floor.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 4<strong>04</strong>/<strong>462</strong><br />
13.03.2006<br />
13.03.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6821 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>186 SR<strong>01</strong>134NY-D SIKORSKY S-76C Installation of Bristow Helicopter’s Ltd This STC is valid only for S76C Sikorsky<br />
29.03.2006<br />
Automatic floating Deployement System helicopter model from S/N 760511 and<br />
(AFDS) in accordance with Keytech Installation subsequentThis STC should not be<br />
drawing list IDL006<strong>01</strong> Rev. dated 11/27/02 incorporated in any aircraft of this specific<br />
model on which other approved modifications<br />
are incorporated, unless is determined that the<br />
interr<br />
10<strong>01</strong>6855 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>231 FAA STC SR<strong>01</strong>140NY-D SIKORSKY S-76C Installation of a Cyclic Control Stick Guard 21.11.2006<br />
10<strong>01</strong>6863 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>239 FAA STC SR<strong>01</strong>135NY-D SIKORSKY S-76C Installation of a Chadwick-Helmuth Vibration<br />
Monitoring System<br />
10<strong>01</strong>6864 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>240 FAA STC SR02110NY-D SIKORSKY S-76A<br />
Installation of a Honeywell Chadwick Model<br />
SIKORSKY S-76C<br />
15175 VXP System<br />
10<strong>01</strong>6879 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>256 REV. 1 FAA STC SR02408NY-D S-92A Installation of Spectrolab Nightsun II XP<br />
SearchlightNote: This certificate revises and<br />
supersedes STC no.<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>256,aiming to update the<br />
Associated Technical Documentation as listed<br />
below<br />
26.09.2006<br />
26.09.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
22.11.2<strong>01</strong>0<br />
10<strong>01</strong>6880 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>257 FAA STC SR02411NY-D SIKORSKY S-92A WESCAM MX-15i FLIR Installation on a<br />
Sikorsky S-92 Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6881 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>258 FAA STC SR02412NY-D SIKORSKY S-92A Saab airborne Transponder System Installation<br />
in a Sikorsky S-92 Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6882 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>259 FAA STC SR02403NY-D SIKORSKY S-92A Chelton Tetra Tranceiver Provision Installation<br />
in a Sikorsky S92 Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6883 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>260 FAA STC SR02400NY-D SIKORSKY S-92A Helicopter Emergency Egress Lighting System<br />
(HEELS) Installation in a Sikorsky S-92<br />
Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6884 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>261 FAA STC SR024<strong>04</strong>NY-D SIKORSKY S-92A Scene Lights Installation in a Sikorsky S-92<br />
Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6885 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>262 FAA STC SR02133NY-D SIKORSKY S-92A Side Facing Utility Seat Installation in a<br />
Sikorsky S-92 Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6886 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>263 FAA STC SR02414NY-D SIKORSKY S-92A GKN Sliding Entry Door Installation in a<br />
Sikorsky S-92 Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6887 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>264 FAA STC SR02405NY-D SIKORSKY S-92A Logo Light Installation in a Sikorsky S-92<br />
Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6888 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>265 FAA STC SR02407NY-D SIKORSKY S-92A Auxiliary DC Power System Installation in a<br />
Sikorsky S-92 Helicopter.<br />
02.05.2007<br />
10<strong>01</strong>6889 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>266 FAA STC SR02121NY-D SIKORSKY S-92A Shelf Installation in Sikorsky S-92 Helicopter. 02.05.2007<br />
10<strong>01</strong>6890 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>267 FAA STC SR02132NY-D SIKORSKY S-92A Ramp Gap Bridge Installation in a Sikorsky S-<br />
92 Helicopter.<br />
10<strong>01</strong>6891 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>268 FAA STC SR02124NY-D SIKORSKY S-92A Jettisonable Cabin Window Installation on a<br />
Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6892 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>269 FAA STC SR024<strong>01</strong>NY-D SIKORSKY S-92A SAR Operators Seat Installation on a Sikorsky<br />
S-92 Helicopter.<br />
10<strong>01</strong>6893 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>270 FAA STC SR02413NY-D SIKORSKY S-92A Wulfsberg Flexcomm II Communications<br />
Management System Installation on a Sikorsky<br />
S-92 Helicopter.<br />
10<strong>01</strong>6894 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>271 REV. 1 FAA STC SR02433NY-D SIKORSKY S-92A NAT Loudhailer System Installation on a<br />
Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6895 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>272 FAA STC SR02406NY-D SIKORSKY S-92A Honeywell Primus 7<strong>01</strong>A Weather Radar<br />
Installation on a Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6896 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>273 FAA STC SR02410NY-D SIKORSKY S-92A SAR Audio System Installation on a Sikorsky S-<br />
92 Helicopter.<br />
10<strong>01</strong>6897 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>274 FAA STC SR02126NY-D SIKORSKY S-92A Skytrac System ISAT-100 Installation on a<br />
Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6898 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>275 FAA STC SR02409NY-D SIKORSKY S-92A Polycon Wireless Intercom System Installation<br />
on a Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6899 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>276 FAA STC SR02415NY-D SIKORSKY S-92A Chelton 935-2 VHF Direction Finder Installation<br />
on a Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6900 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>277 FAA STC SR02402NY-D SIKORSKY S-92A Search and Rescue (SAR) Interior Installation<br />
on a Sikorsky S-92 Helicopter.<br />
10<strong>01</strong>6910 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>291 FAA STC SR02129NY-D SIKORSKY S-76A<br />
Installation of Keystone Helicopter Corporation Compliance with FAR 29.812 has not been<br />
SIKORSKY S-76B<br />
“Silencer” Wall panel System. Classified as established for the installation of this system.<br />
SIKORSKY S-76C<br />
Basic STC by FAA.<br />
An approved emergency lighting system is<br />
required.Compliance with FAR 29.783(c)(e),<br />
29.803(a)(b), 29.807(a)(b), 29.809(c), 29.811,<br />
29.813(a), 29.13<strong>01</strong>(a)(d) and 29.1557<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 405/<strong>462</strong><br />
02.05.2007<br />
02.05.2007<br />
02.05.2007<br />
02.05.2007<br />
29.10.2007<br />
02.05.2007<br />
02.05.2007<br />
02.05.2007<br />
02.05.2007<br />
02.05.2007<br />
02.05.2007<br />
15.03.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6913 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>294 FAA STC SR02131NY-D SIKORSKY S-76A<br />
Installation of Keystone Helicopter Corporation Prior to installation of this modification the<br />
26.07.2007<br />
SIKORSKY S-76B<br />
Deluxe VIP Interior.<br />
installer must determine that the<br />
SIKORSKY S-76C<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6914 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>295 FAA STC SR02130NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6915 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>296 FAA STC SR02123NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6916 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>297 FAA STC SR02122NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
Installation of Garmin GMX 200 Multi Function<br />
Display. This STC has been classified as<br />
"BASIC" by the FAA and has been approved<br />
under the PTVP. The flight manual has been<br />
reviewed and is acceptable.<br />
Installation of Provisions for a EuroAvionics<br />
EuroNav IV System. STC SR02123NY-D<br />
classified as Basic by the FAA through FAA<br />
Order 8110.52.<br />
Installation of High Intensity Strobe Lights. STC<br />
Classified as Basic by FAA.<br />
10<strong>01</strong>6946 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>340 FAA STC SR<strong>01</strong>976NY-D SIKORSKY S-92A Installation of Keystone Helicopter Auxiliary<br />
Gauges and Relocation of Fill Ports for the Low<br />
Float Pressure Warning System.<br />
10<strong>01</strong>6981 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>384 FAA STC SR02417NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6982 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>386<br />
REVISION 1<br />
10<strong>01</strong>6983 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>387 FAA STC SR02426NY-D SIKORSKY S-76A<br />
SIKORSKY S-76B<br />
SIKORSKY S-76C<br />
Installation of Honeywell KHF 1050 HF<br />
Communication System.<br />
FAA STC SR02152NY-D SIKORSKY S-92A Installation of a Cockpit Pressure Refuelling<br />
Control in a Sikorsky S-92A. This STC has<br />
been classified as "BASIC" by the FAA and has<br />
been approved under the PTVP.<br />
Installation of a Replacement Concorde Lead<br />
Acid Battery.<br />
10<strong>01</strong>6997 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>406 REV. 1 FAA STC02436NY-D SIKORSKY S-92A Installation of a High Intensity Strobe Lights.<br />
This STC has been classified as BASIC by the<br />
FAA and has been approved under the PTVP.<br />
10<strong>01</strong>7<strong>01</strong>8 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>436 REV. 1 FAA STC SR<strong>01</strong>949NY-D EUROCOPTER FRANCE AS<br />
365N1<br />
EUROCOPTER FRANCE AS<br />
365N2<br />
EUROCOPTER FRANCE AS<br />
365N3<br />
Installation of a Honeywell Chadwick Model<br />
15175 VXP System.<br />
10<strong>01</strong>7<strong>04</strong>0 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>464 FAA STC SR02435NY-D SIKORSKY S-92A Installation of a Rockwell Collins SAR-126<br />
Direction Finder System. This STC has been<br />
classified as “BASIC” by the FAA and has<br />
beenapproved under the PTVP.<br />
The FAA has not certified, and <strong>EASA</strong> has not<br />
validated, the equipment for which these<br />
provisions are intended. Additional approvals<br />
are required to install this equipment. The<br />
equipment installation must be evaluated to<br />
ensure that it complies with the appl<br />
03.07.2007<br />
19.03.2007<br />
15.03.2007<br />
29.06.2007<br />
Refer to FAA STC SR02417NY-D. <strong>04</strong>.12.2007<br />
none 1. Prior to installation of this<br />
modification the installer mustdetermine<br />
that the interrelationship between this<br />
modification and anyother previously<br />
installed modification will introduce no<br />
adverse effectupon the airworthiness of<br />
the product;2. The<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>7070 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>506 FAA STC SR02577NY-D SIKORSKY S-76C Keystone Helicopters STC SR02577NY-D; 1. Prior to installation of this modification the<br />
Introduction of a cockpit digital video recorder installer must determine that the<br />
system to meet JAR-OPS 3 flight data interrelationship between this modification and<br />
recorder requirements on applicable Sikorsky S-any<br />
other previously installed modification will<br />
76C series aircraft.<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
10<strong>01</strong>7076 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>519 FAA STC SR02573NY-D SIKORSKY S-92A Installation of Main Rotor Blade Recognition 1. Prior to installation of this modification the<br />
Lights.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7083 SIKORSKY GLOBAL HELICOPTERS Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>550 FAA STC SR02208NY-D SIKORSKY S-92A Installation of lavatory. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 406/<strong>462</strong><br />
09.11.2007<br />
05.02.2008<br />
19.03.2008<br />
29.06.2<strong>01</strong>1<br />
10.07.2008<br />
19.02.2009<br />
02.12.2008<br />
30.<strong>04</strong>.2009
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029325 SILVERHAWK CONVERSIONS P-<br />
FAA STC SA10741SC BEECHCRAFT KING AIR Installation of Pratt and Whitney Canada PT6A - None Prior to installation of this modification the 18.03.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.A.S.02962<br />
C90, E90, C90A AIRCRAFT 135A Engines.<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
10<strong>01</strong>5331 SIMMONDS PRECISION PRODUCTS, <strong>EASA</strong>.IM.A.S.00345 FAA STC ST00089BO BOEING 727-200 SERIES Installation of either the Goodrich Corporation 1. The suppression feature of Fire Detection<br />
30.11.20<strong>04</strong><br />
INC<br />
Fire Detection and Suppression system, or the and Suppression system has been certified for<br />
Fire Detection only system in accordance with a maximum of 60 minutes from the activation<br />
Goodrich Corporation Master Drawing List of the suppression agent. Aircraft diversion<br />
T3008-MDL-<strong>01</strong><strong>01</strong>, Revision A, dated October time, including landing, should not exceed 60<br />
31, 2003 or later FAA-approved re<br />
minutes.2. This STC is<br />
10<strong>01</strong>5770 SIMMONDS PRECISION PRODUCTS,<br />
INC<br />
10<strong>01</strong>6158 SIMMONDS PRECISION PRODUCTS,<br />
INC<br />
10<strong>01</strong>6338 SIMMONDS PRECISION PRODUCTS,<br />
INC<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>809 FAA STC ST00<strong>04</strong>3BO BOEING 737-100<br />
BOEING 737-200<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
<strong>EASA</strong>.IM.A.S.02377 FAA STC ST00235BO BOEING 737-400 Installation of the Goodrich Corporation Fire<br />
Detection (Class “E”)<br />
<strong>EASA</strong>.IM.A.S.02647 FAA STC ST00092BO AIRBUS A300 In-Tank Fuel Quantity Indicating System (FAA<br />
10<strong>01</strong>6713 SIMPLEX MANUFACTURING CO. <strong>EASA</strong>.IM.R.S.0078 FAA STC SR00684SE, DGAC SPAIN EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
B3<br />
EUROCOPTER FRANCE AS 350<br />
10<strong>01</strong>7066 SIMPLEX MANUFACTURING CO. <strong>EASA</strong>.IM.R.S.<strong>01</strong>502 FAA STC SR00889SE EUROCOPTER FRANCE AS 355<br />
SERIE<br />
BA<br />
Installation of a Simmonds Precission 50203 Compatibility of this design change with other<br />
series Fuel Quantity Harness in accordance previously approved modifications must be<br />
with Simmonds Precision Installation Document determined by the installer.<br />
N0 E-3203, dated May 24, 1995, or later<br />
approved revision<br />
STC ST00092BO validation). This STC installs,<br />
within the aircraft fuel tanks, a new FQIS<br />
sensors and the associated wire harnesses.<br />
Installation of Simplex anti-fire system Model<br />
310-900, 310-1100 and 310-1200<br />
Installation of an agricultural spray system.<br />
(This STC has been classified as “BASIC” by<br />
the FAA in accordance with FAA Order<br />
8110.52 and has been approved using the<br />
PTVP Procedures.)<br />
1. The installation of this equipment is only<br />
applicable on 737-400 aircraft modified to full<br />
freighter configuration per Pemco<br />
STCnumbers SA2968SO, SA2969SO,<br />
SA2970SO and SA2971SO inclusively.2.<br />
Goodrich Corporation Airplane Flight Manual<br />
Supplement T3078<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph “Description”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Rotorcraft to be equipped with an <strong>EASA</strong><br />
approved high skid landing gear; Essential<br />
Crew only; Day/Night VFR only; and<br />
Airspeed Limitations per Flight Manual<br />
Supplement.Prior to installation of this<br />
modification the installer must determine that<br />
the<br />
10029552 SINGAPORE TECHNOLOGIES A320 Passenger Compartment Reconfiguration None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
31.03.2<strong>01</strong>0<br />
10033242 SINGAPORE TECHNOLOGIES A321 Passenger Compartment Reconfiguration Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
06.<strong>01</strong>.2<strong>01</strong>1<br />
10036609 SINGAPORE TECHNOLOGIES A320-200 SERIES Ural Airlines' A320 Cabin Reconfiguration -,,This design change on Aircraft model Airbus<br />
A320-200 is applicable tothe following aircraft<br />
serial numbers (MSNs): 203; 220; 735; 1152;<br />
1484;1777; 2175; 2187 and 2327.<br />
This STC does not require a revision or<br />
supplement to the original TCHolder’s<br />
EWIS Instructions for Continued<br />
Airworthiness.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other p<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 407/<strong>462</strong><br />
22.<strong>01</strong>.2007<br />
07.05.2007<br />
02.10.2008<br />
06.10.20<strong>04</strong><br />
26.09.2008<br />
22.09.2<strong>01</strong>1
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035668 SKY IMD Inc. REV. 1 SEE APPROVED MODEL LIST Installation of Sensor Pod and wiring for This STC is for installation of the sensor pod The installation of this modification by 08.07.2<strong>01</strong>1<br />
passenger operated monitoringsystem and wiring from thesensor pod into fuselage. third persons is subject towritten<br />
This STC does not include power to the permission of the approval holder and<br />
sensorpod or the sensor control unit.Limitations disposal of the approvedappropriate<br />
as defined in the applicable Aircraft Flight documentation. Prior to installation of this<br />
ManualSupplements.<br />
modification it must be determined<br />
thatthe interrelationship<br />
10<strong>01</strong>5785 SKY INTERNATIONAL Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>841 REV 1 SA1<strong>04</strong>63SC AVIAT HUSKY A-1B Installation of a Lycoming model IO-360-A1D6 The engine must be de-rated to 196 HP (see<br />
23.08.2006<br />
engine (derated to 196 HP) and MT Propeller Installation Instructions for details).The Airplane<br />
model MTV-15-B/205-58 propeller in<br />
Flight Manual Supplement No 55009-18,<br />
accordance with Installation Instructions No Revision IR or later <strong>EASA</strong> approved revision,<br />
11<strong>01</strong>, Revision C dated 8 May 2006, or later must be used with this modification.The<br />
approved revision<br />
approved Noise Level is 81.6 dB(A).<br />
10035483 SKYE AVIONICS Ltd. TCCA STC SH11-14 BELL 407 Installation of "Check Engine Instruments"<br />
Audio Alert System.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
27.06.2<strong>01</strong>1<br />
10<strong>04</strong>2298 SKYTECH, INC. <strong>EASA</strong>.IM.A.S.006<strong>04</strong> FAA STC ST<strong>01</strong>851NY PA46-310P 1- Skytech Inc. Airplane Flight Manual<br />
Supplement, HTW-494-782-100<br />
FAAApproved December 31, 2003, is<br />
required for this modification.2- This STC<br />
is approved only for the product<br />
configuration as defined inthe approved<br />
design data referred to in the paragrap<br />
02.03.2005<br />
10<strong>01</strong>6790 SKYTRAC SYSTEMS Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>137 REV. 2 TCCA STC SH05-42 BELL 407<br />
SkyTrac ISAT-100 Airborne Position/Data 1. Equipment configuration: ISAT-100 (no<br />
13.02.2006<br />
EUROCOPTER DEUTSCHLAND Communicator System Installation.TCCA STC mod.)/mod A, or later TCCA approved major<br />
BO-105<br />
SH05-42 Issue no 1 dated 12 September 2005 mod.2. This STC references specified<br />
interfacing equipment that is approved via this<br />
data. The ISAT-100 equipempment is capable<br />
of being interfaced to additional aircr<br />
10<strong>01</strong>6798 SKYTRAC SYSTEMS Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>151 REV. 2 TCCA STC SH03-30 ISSUE 4 BELL 212<br />
BELL 412<br />
BELL 412 CF<br />
BELL 412 EP<br />
EUROCOPTER FRANCE SA<br />
365C<br />
EUROCOPTER FRANCE SA<br />
365C1<br />
EUROCOPTER FRANCE SA<br />
365N<br />
SIKORSKY S-61N<br />
SIKORSKY S-76A<br />
SIKORSKY S-76C<br />
10<strong>01</strong>6927 SKYTRAC SYSTEMS Ltd. <strong>EASA</strong>.IM.R.S.<strong>01</strong>313 TCAA STC SH03-30 ISSUE 5 EUROCOPTER FRANCE AS<br />
365C<br />
EUROCOPTER FRANCE AS<br />
365C1<br />
EUROCOPTER FRANCE AS<br />
365N<br />
EUROCOPTER FRANCE EC<br />
155B<br />
Installation of SkyTrac ISAT-100 Airborne 1. This STC references specific interfacing<br />
Position/Data Communicator SystemRevison 1 equipment that is approved via this data.<br />
to add: BK-117 A-1, A-3, A-4, B-1 and B-2 The ISAT-100 equipment is capable of being<br />
modelsRevision 2 to add: Eurocopter SA 365 interfaced to additional aircraft systems for<br />
C, C1, N, EC 155B<br />
wich approval is beyond the scope of this STC.<br />
Such interfaces may<br />
Installation of SkyTrac ISAT-100 Airborne This STC references specific interfacing<br />
Position/ Data Communication System Note: equipment that is approved via this data. The<br />
This application is to amend an existing <strong>EASA</strong> ISAT 100 equipment is capable of being<br />
STC (Ref P-<strong>EASA</strong>.IM.R.S.0<strong>01</strong>151 Rev. 1) to interfaced to additional aircraft systems for<br />
add the SA 365 C,C1,N, EC 155B helicopter which approval is beyond the scope of this<br />
models<br />
STC. Such interfaces may need further ap<br />
10030917 SKYTRAC SYSTEMS Ltd. TCCA STC SA09-93 SkyTrac Flight Following / SATCOM Installation<br />
in acc. with TCCA STCSA09-93:ISAT-100<br />
transceiver installed in aft zone of aircraft, Dual<br />
elementGPS/Iridium antenna installed on upper<br />
fuselage, optional DVI-250 andCDP-250<br />
control panels installed at centre<br />
21.03.2007<br />
21.03.2007<br />
None None 12.07.2<strong>01</strong>0<br />
10030918 SKYTRAC SYSTEMS Ltd. TCCA STC SA09-80 CESSNA 208, 208B SkyTrac Flight Following / SATCOM Installation None<br />
in acc. with TCCA STCSA09-80, Issue 1:ISAT-<br />
100 transceiver installed in aft zone of aircraft,<br />
Dual elementGPS/Iridium antenna installed on<br />
upper fuselage, optional DVI-250 andCDP-250<br />
control panels installed a<br />
None 12.07.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 408/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031247 SKYTRAC SYSTEMS Ltd. REV. 2 TCCA STC SH10-24 ISSUE 2 206A, 206A-1, 206B, 206B-1, SkyTrac ISAT Airborne Position/Data STC <strong>EASA</strong>.IM.R.S.<strong>01</strong>137 is a prerequisite to Prior to installation of this modification it 22.12.2<strong>01</strong>0<br />
206L, 206L-1, 206L-3, 206L-4, Communicator<br />
this installation.<br />
must be determined thatthe<br />
407<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
100318<strong>04</strong> SKYTRAC SYSTEMS Ltd. TCCA STC SA06-85 200/200C/200T/200CT/A200/A200 SkyTrac ISAT Position Data Communicator<br />
C<br />
300/300LW/B300/B300C/1900D<br />
A200CT/B200/B200C/B200T/B200<br />
CT<br />
System Installation.<br />
10033276 SKYTRAC SYSTEMS Ltd. TCCA STC SH10-24 ISSUE 2 EC 120 B Sky Track ISAT AIRBORNE POSITION /<br />
COMMUNICATION UPGRADEThe<br />
modification upgrades an existing ISAT-100<br />
Airborne Position / DataCommunicator system<br />
installation to an ISAT-200 system(This <strong>EASA</strong><br />
approval validates the TCCA STC SH10-24,<br />
10033865 SKYTRAC SYSTEMS Ltd. TCCA STC NO. SH10-24 EC 135 P1(CDS),EC 135<br />
P1(CPDS)<br />
EC 135 P2(CPDS),EC 135 P2+<br />
EC 135 T1(CDS),EC 135<br />
T1(CPDS)<br />
EC 135 T2(CPDS),EC 135 T2+<br />
10036485 SKYTRAC SYSTEMS Ltd. TCCA STC SH10-24 AS 355 E, AS 355 F, AS 355 F1<br />
AS 355 F2, AS 355 N<br />
Issue 2)<br />
Sky Track ISAT AIRBORNE POSITION /<br />
COMMUNICATION UPGRADEThe<br />
modification upgrades an existing ISAT-100<br />
Airborne Position / DataCommunicator system<br />
installation to an ISAT-200 system(This <strong>EASA</strong><br />
approval validates the TCCA STC SH10-24,<br />
Issue 2)<br />
Sky Track ISAT AIRBORNE POSITION /<br />
COMMUNICATION UPGRADEThe<br />
modification upgrades an existing ISAT-100<br />
Airborne Position / DataCommunicator system<br />
installation to an ISAT-200 system(This <strong>EASA</strong><br />
approval validates the TCCA STC SH10-24,<br />
Issue 3 on thetype/mode<br />
10036492 SKYTRAC SYSTEMS Ltd. TCCA STC SH10-24 AS 350 B, AS 350 B1, AS 350 B2 Sky Track ISAT AIRBORNE POSITION /<br />
AS 350 B3, AS 350 BA, AS 350 D COMMUNICATION UPGRADEThe<br />
modification upgrades an existing ISAT-100<br />
Airborne Position / DataCommunicator system<br />
installation to an ISAT-200 system(This <strong>EASA</strong><br />
approval validates the TCCA STC SH10-24,<br />
Issue 3 on thetype/mode<br />
10<strong>04</strong>1706 SKYTRAC SYSTEMS Ltd. TCCA STC SH10-51 AW139 Installation of a SkyTrac ISAT-100/ISAT-200<br />
Position Data Communicator(Canadian STC<br />
SH10-51 issue 2)<br />
10<strong>01</strong>4444 SLINGSBY ADVANCED COMPOSITES<br />
LTD.<br />
<strong>EASA</strong>.A.S.02495 REV. 1 BEECH 76 Introduction of Bendix/King KCS 55A<br />
Compass, KX165 NAV/COM, KR87 ADF, King<br />
KN62A DME & KI229 Systems<br />
10<strong>01</strong>3975 SMA - SOCIETE DE MOTORISATIONS <strong>EASA</strong>.A.S.00774 REV. 7 1. 182M, 182N, 182P, 182Q,182R<br />
2. F182-P, F182-Q<br />
10<strong>01</strong>6495 SMA ENGINES INC. <strong>EASA</strong>.IM.A.S.02857 FAA STC SA03302AT CESSNA 182Q<br />
CESSNA 182R<br />
-DET C-09-503 Air Supply circuit modification-<br />
DET C-08-508 Introduction of new powerplant<br />
limitations-DET C-07-521 Kelly Aerospace<br />
alternator ES7024-16 Installation-DET C-08-<br />
510 Modification of the intercooler inlet and<br />
outlet nozzlesgeometry.-DJC-STC-C182<br />
Installation of Societe de Motorisations<br />
Aeronautiques (SMA) Aircraft Diesel Engine<br />
(ADE) model SR305-230-1 (or SR305-230<br />
convertedto model SR305-230-1 by<br />
incorperation of SMA Service Bulletin SB-<strong>01</strong>-<br />
76-002), MT propeller model MTV-9-BS/198-<br />
58B peopeller an<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.09.2<strong>01</strong>0<br />
None <strong>EASA</strong>.IM.R.S.<strong>01</strong>137 is a pre-requisite to<br />
this approval.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adver<br />
none <strong>EASA</strong>.IM.R.S.<strong>01</strong>137 is a pre-requisite to<br />
this approval.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adver<br />
None This STC references specified interfacing<br />
equipment that is approved viathis data.<br />
The ISAT -200 is capable of being<br />
interfaced to additionalaircraft systems<br />
for which approval is beyond the scope of<br />
this STC.Such interfaces may need<br />
further approval.<strong>EASA</strong>.<br />
11.<strong>01</strong>.2<strong>01</strong>1<br />
15.02.2<strong>01</strong>1<br />
12.09.2<strong>01</strong>1<br />
None This STC references specified interfacing 13.09.2<strong>01</strong>1<br />
equipment that is approved viathis data.<br />
The ISAT -200 is capable of being<br />
interfaced to additionalaircraft systems<br />
for which approval is beyond the scope of<br />
this STC.Such interfaces may need<br />
further approval. <strong>EASA</strong><br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.10.2<strong>01</strong>2<br />
Applicable to Cessna 182R, Q, P, N, M and<br />
Reims Aviation F182Q and Pmodified in<br />
accordance with STC SMA <strong>EASA</strong>.A.S.00774<br />
and later approvedrevisions.<br />
20.06.2006<br />
Prior to installation of this modification it <strong>04</strong>.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None. 06.11.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 409/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5728 SNAKY CREEK ENTERPRISES, LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>745 REV 1 FAA STC SA02177CH BAE JETSTREAM 32<strong>01</strong> SERIES Removal of passenger seats and installation of<br />
Spectrum Aeromed medical systemsNote:This<br />
revision reflects the transfer of this STC from<br />
Spectrum Aeromed, Inc to Snaky Creek<br />
Enterprises, LLC.<br />
07.<strong>01</strong>.2008<br />
10<strong>01</strong>6347 SNAKY CREEK ENTERPRISES, LLC <strong>EASA</strong>.IM.A.S.02664 FAA STC ST<strong>01</strong>248CH; LBA STC TA0 BAE 125 SERIES 1000A<br />
BAE 125 SERIES 1000B<br />
HAWKER 1000<br />
10<strong>01</strong>6348 SNAKY CREEK ENTERPRISES, LLC <strong>EASA</strong>.IM.A.S.02666 FAA STC ST<strong>01</strong>607CH; LBA STC TA0 LEARJET 31<br />
LEARJET 31A<br />
LEARJET 35<br />
LEARJET 35A<br />
10<strong>01</strong>6349 SNAKY CREEK ENTERPRISES, LLC <strong>EASA</strong>.IM.A.S.02668 FAA STC SA00882CH; LBA STC SA BEECH 200<br />
BEECH 200C<br />
BEECH B200<br />
BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>6350 SNAKY CREEK ENTERPRISES, LLC <strong>EASA</strong>.IM.A.S.02669 FAA STC SA00972CH; LBA STC SA PIPER PA-42<br />
PIPER PA-42-1000<br />
PIPER PA-42-720<br />
10<strong>01</strong>6988 SNAKY CREEK ENTERPRISES, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>394 FAA STC SR176CH; DGAC FRANCE<br />
S<br />
BELL 212<br />
BELL 412<br />
Installation of an air ambulance<br />
AFM Supplement dated August 4, 2007 or<br />
conversionNote:1. This STC reflects the later approved revision is required<br />
transfer of LBA STC TA0328 from Spectrum<br />
Aeromed, Inc to Snaky Creek Enterprises,<br />
LLC.2. This STC supersede LBA STC TA0328.<br />
Installation of an air ambulance<br />
1. AFM Supplement dated December 7, 20<strong>01</strong><br />
conversionNote:1. This STC reflects the or later approved revision is required.2.<br />
transfer of LBA STC TA0565 from Spectrum Installation requires previous or concurrent<br />
Aeromed, Inc to Snaky Creek Enterprises, installation per LBA STC TA0512 (STC<br />
LLC.2. This STC supersede LBA STC TA0565. ST<strong>01</strong>026WI).<br />
Installation of Spectrum Aeromed medical<br />
systems.<br />
07.<strong>01</strong>.2008<br />
07.<strong>01</strong>.2008<br />
07.<strong>01</strong>.2008<br />
Installation of an aor ambulance conversion 07.<strong>01</strong>.2008<br />
Installation of an air ambulance unitNote:1. This<br />
STC reflects the transfer of DGAC France STC<br />
SR176CH from Spectrum Aeromed, Inc to<br />
Snaky Creek Enterprises, LLC.2. This STC<br />
supersedes DGAC France STC SR176CH.<br />
10035259 SNAKY CREEK ENTERPRISES, LLC FAA STC SA02935CH CESSNA 441 Air Ambulance Conversion in accordance with<br />
Spectrum Aeromed DrawingList<br />
10035308 SNAKY CREEK ENTERPRISES, LLC FAA STC SA02897CH 510 Air Ambulance Conversion according FAA STC<br />
SA02897CH.<br />
10035962 SNAKY CREEK ENTERPRISES, LLC FAA STC SA02930CH CESSNA 208, 208B Air Ambulance Conversion in accordance with<br />
Spectrum Aeromed DrawingList<br />
10036411 SNAKY CREEK ENTERPRISES, LLC FAA STCSA<strong>01</strong>213CH;CAA ES S374-I SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10036412 SNAKY CREEK ENTERPRISES, LLC FAA STCSA<strong>01</strong>213CH;CAA ES S374-I SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
None The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
According limitation section of AFM-S. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
07.<strong>01</strong>.2008<br />
09.06.2<strong>01</strong>1<br />
14.06.2<strong>01</strong>1<br />
None The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
<strong>01</strong>.08.2<strong>01</strong>1<br />
Install air ambulance Note: 1. This STC reflects None Prior to installation of this modification it 26.07.2<strong>01</strong>2<br />
the transfer of STC CAA ES S374-1 from<br />
must be determined thatthe<br />
SpectrumAeromed, Inc to Snaky Creek<br />
interrelationship between this modification<br />
Enterprises, LLC2. This STC supersedes STC<br />
and any other previouslyinstalled<br />
CAA ES S374-1, <strong>EASA</strong> STC<br />
modification and/or repair will introduce<br />
<strong>EASA</strong>.IM.A.S.C.<strong>01</strong><strong>01</strong>63. This STC, together<br />
no adverse effectupon the airworthiness<br />
with <strong>EASA</strong> STCs 10036412<br />
of the product.<br />
Install air ambulance Note: 1. This STC reflects<br />
the transfer of STC CAA ES S374-1 from<br />
SpectrumAeromed, Inc to Snaky Creek<br />
Enterprises, LLC2. This STC supersedes STC<br />
CAA ES S374-1, <strong>EASA</strong> STC<br />
<strong>EASA</strong>.IM.A.S.C.<strong>01</strong><strong>01</strong>63. This STC, together<br />
with <strong>EASA</strong> STCs 10036411<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.07.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 410/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036413 SNAKY CREEK ENTERPRISES, LLC FAA STCSA<strong>01</strong>213CH;CAA ES S374-I SEE <strong>EASA</strong> APPROVED MODEL Install air ambulance Note: 1. This STC reflects None Prior to installation of this modification it 26.07.2<strong>01</strong>2<br />
LIST<br />
the transfer of STC CAA ES S374-1 from<br />
must be determined thatthe<br />
SpectrumAeromed, Inc to Snaky Creek<br />
interrelationship between this modification<br />
Enterprises, LLC2. This STC supersedes STC<br />
and any other previouslyinstalled<br />
CAA ES S374-1, <strong>EASA</strong> STC<br />
modification and/or repair will introduce<br />
<strong>EASA</strong>.IM.A.S.C.<strong>01</strong><strong>01</strong>63. This STC, together<br />
no adverse effectupon the airworthiness<br />
with <strong>EASA</strong> STCs 10036411<br />
of the product.<br />
10039407 SNAKY CREEK ENTERPRISES, LLC FAA STC ST02068CH BAE.125 SERIES 1000A<br />
BAE.125 SERIES 1000B<br />
BAE.125 SERIES 800A<br />
BAE.125 SERIES 800B<br />
BH.125 SERIES 400A<br />
BH.125 SERIES 600A<br />
DH.125 SERIES 400A<br />
HAWKER 1000<br />
HAWKER 800<br />
HAWKER 800XP<br />
HAWKER 850XP<br />
HAWKER 900XP<br />
HS.125 SERIES 400B<br />
HS.125 SERIES 400B/1<br />
HS.125 SERIES 4<strong>01</strong>B<br />
HS.125 SERIES 403A(C)<br />
HS.125 SERIES 403B<br />
HS.125 SERIES 600A<br />
HS.125 SERIES 600B<br />
HS.125 SERIES 600B/1<br />
HS.125 SERIES 600B/2<br />
HS.125 SERIES 600B/3<br />
HS.125 SERIES 700A<br />
HS.125 SERIES 700B<br />
HS.125 SERIES F400B<br />
HS.125 SERIES F403B<br />
HS.125 SERIES F600B<br />
To Install an Air Ambulance Conversion. This<br />
Change instructs the interior and electrical<br />
changes to theaircraft. Stretcher and medical<br />
equipment installation will be certifiedby the<br />
appropriate vendor.<br />
10039716 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02982CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02982CH<br />
"Installation of equipment railsand mounts in<br />
accordance with RSG AeroDesign Master<br />
Document List00A02160002, No Revision,<br />
dated February 23, 2<strong>01</strong>1, or later FAA<br />
approvedrevisions"<br />
10039717 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02981CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02981CH<br />
"Installation of a medical seat,fire extinguisher,<br />
utility track and cylinder mount in accordance<br />
withRSG AeroDesign Master Document List<br />
00A023900<strong>01</strong>, No Revision, datedFebruary 23,<br />
2<strong>01</strong>1, or later FAA approved revisions<br />
10039718 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02974CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02974CH "Air<br />
Ambulance Conversion inaccordance with<br />
Spectrum Aeromed Master Document List<br />
7<strong>01</strong>1DL, Revision1, dated May 18, 2<strong>01</strong>1, or<br />
later FAA approved revisions"<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.05.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.05.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.05.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.05.2<strong>01</strong>2<br />
10039719 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02978CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02978CH None Prior to installation of this modification it 18.05.2<strong>01</strong>2<br />
"Installation of shore powermechanical<br />
must be determined thatthe<br />
provisions in accordance with RSG AeroDesign<br />
interrelationship between this modification<br />
Master DocumentList 00A022400<strong>01</strong>, No<br />
and any other previouslyinstalled<br />
Revision, dated February 23, 2<strong>01</strong>1, or later<br />
modification and/ or repair will introduce<br />
FAAapproved revisions"<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 411/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039720 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02977CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02977CH None Prior to installation of this modification it <strong>04</strong>.06.2<strong>01</strong>2<br />
"Installation of a medical floorliner in<br />
must be determined thatthe<br />
accordance with RSG AeroDesign Master<br />
interrelationship between this modification<br />
Document List00A02160003, No Revision,<br />
and any other previouslyinstalled<br />
dated February 23, 2<strong>01</strong>1, or later FAA<br />
modification and/ or repair will introduce<br />
approvedrevisions"<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039721 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02980CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02980CH<br />
"Installation of an interior panelsystem in<br />
accordance with RSG AeroDesign Master<br />
Document List00A021600<strong>01</strong>, No Revision,<br />
dated February 23, 2<strong>01</strong>1, or later FAA<br />
approvedrevisions"<br />
10<strong>04</strong>1098 SNAKY CREEK ENTERPRISES, LLC FAA STC SA02488CH PC-12<br />
PC-12/45<br />
PC-12/47<br />
Air Ambulance Conversion Install air<br />
ambulance conversion in accordance with<br />
Spectrum AeromedInc. Master Drawing List<br />
6<strong>04</strong>5DL, dated July 23, 2007 or later<br />
FAAapproved revisions.<br />
10<strong>01</strong>4506 SOCATA <strong>EASA</strong>.A.S.02576 TBM 700 STC 34.0<strong>01</strong>.06/Gamin GNS530 TAWS. TBM 700 equipped Garmin GNS 530 only s/n<br />
to 433 excepted 269.<br />
10<strong>01</strong>4524 SOCATA <strong>EASA</strong>.A.S.02607 TB 200 Validation of definition specificities of TB200 STC 53.0<strong>01</strong>.06 applicable to TB200 s/n 1633<br />
S/N 1633 aircraft, compared to TB200 GT<br />
certified aircraft definition<br />
only<br />
10<strong>01</strong>5065 SOCATA <strong>EASA</strong>.A.S.03391 SOCATA TBM 700 Installation of a multi-functions display Garmin This revision can be installed on TBM 700 s/n<br />
GMX 200 connected to already installed to 433 when equipped with EADS SOCATA<br />
equipments (weather radar, COM/NAV/GPS, optional Modifications n° OPT 70-23-<strong>01</strong>9, OPT<br />
Traffic Advisory System).<br />
70-23-<strong>01</strong>8, OPT 70-34-<strong>04</strong>7 and OPT 70-34-<br />
<strong>04</strong>0.The installation can be performed only by<br />
EADS SOCATA technical staff according to t<br />
10029243 SOCATA P-<strong>EASA</strong>.A.S.03962 REV. 4 TB 20<br />
TB 21<br />
Installation of Garmin G500 EFIS Interfaced<br />
with a dual Garmin GNS430W/530W<br />
communication and navigation system, for IFR<br />
B-RNAV/P-RNAVoperations with coupling to<br />
autopilot.Revision 3 of the STC including the<br />
extent to RNP LNAV and LPV<br />
approachoperations.Re<br />
10<strong>04</strong>0655 SOCATA DHC-6 SERIES 300 Avionics upgrade based on Garmin G600 EFIS<br />
and GNS 430 W system,according to<br />
SOCATA modification file n° STC.00.0<strong>01</strong>.11<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.05.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.08.2<strong>01</strong>2<br />
The modified airplane must be equipped with:-<br />
an attitude indicator, an airspeed indicator, an<br />
altitude indicator, amagnetic heading indicator<br />
and a radionavigation indicator<br />
independentfrom the G500 EFIS,- a<br />
third radionavigation or radiocommunciati<br />
This design change is limited to airplanes s/n<br />
292, 298, 300, 730 and745. Initial installation<br />
must be performed by authorised Socata<br />
technicalpersonel. This avionics installation is<br />
approved for IFR operations in<br />
BRNAV,PRNAV, RNP approach LNAV and<br />
LPV app<br />
10<strong>04</strong>2727 SOCATA TB20, TB21 Installation of TAS Garmin GTS800 This STC is not applicable to airplanes<br />
equipped with a 14 V electricalsystem.Initial<br />
Installation of this design change must be<br />
performed byauthorized SOCATA<br />
personal.Modified airplanes must be equipped<br />
with Socata modification No.34-0<strong>01</strong>-009<br />
approved unde<br />
10028245 SOCATA SAS P-<strong>EASA</strong>.A.S.03961 REV. 2 TBM 700 N Installation of a Honeywell HF KHF 1050<br />
communication system on aircraftTBM 700 N<br />
equipped with Garmin 1000 Glass Cockpit<br />
System - Update forICA inclusion<br />
30.<strong>01</strong>.2008<br />
20.07.2006<br />
06.02.2008<br />
Prior to installation of this modification it 23.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 17.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 14.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.08.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 412/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036696 SOCATA SAS AS 355 F2 Installation of Provisions for WESCAM MX-10 Serial Numbers 5026, 5299, 5298, 5156 only Configuration is limited to the installation 30.09.2<strong>01</strong>1<br />
Camera installation<br />
of the following defined asprovisions:-<br />
UHF FM antenna for DR 3000 UHF<br />
relay;- GPS antenna for WESCAM<br />
camera MX-10;- The remote screen<br />
display is removed but its mounting<br />
bracket isinstalled;- Footswitch - is re<br />
10<strong>01</strong>4399 SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.<strong>01</strong>693 REV. 1 BOEING 767 Cabin Reconfiguration from Eva Air to Aeroflot FAA STC SA5950NM (Door 2 Aft Galley<br />
Standard<br />
Installation) is not included in this approval.<br />
10<strong>01</strong>4463 SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.02524 BOEING 777-200 Air France B777-200 "Ulysse" cabin<br />
Limited to Aircraft serial numbers as defined in<br />
modification with Contour (CAS B777-<strong>04</strong>-003) Air France document CAS B777-<strong>04</strong>-003 and<br />
or BEA business class seats (CAS B777-05-<br />
<strong>01</strong>5).<br />
CAS B777-05-<strong>01</strong>5<br />
10<strong>01</strong>4465 SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.02526 AIRBUS A320-211 Photo-luminescent EEPM system installation This STC is limited to the A320 MSN's 211,<br />
215 and 270<br />
10<strong>01</strong>45<strong>01</strong> SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.02568 A320 Cabin Reconfiguration in bi-classes on LAN 1. Limited to installation on MSN 13<strong>04</strong>, 1332,<br />
A320<br />
1351 and 1355.2. Compatibility of this design<br />
change with other previously approved<br />
modifications must be determined by the<br />
installer.<br />
10<strong>01</strong>4531 SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.02617 BOEING 737-300<br />
ATC Mode S-Enhanced Surveillance-Provision 1. Limited to installation on Boeing 737-300/-<br />
BOEING 737-500<br />
and Activation on Boeing 737-300/-50 in 500.2. Compatibility of this design change with<br />
accordance with the Modification File MF-B737- other previously approved modifications must<br />
06-0<strong>04</strong>, Rev 00, dated 11 October 2006. be determined by the installer.<br />
10<strong>01</strong>4611 SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.02738 AIRBUS A340-300 THY A340 Cabin Retrofit Modification 16.05.2007<br />
10<strong>01</strong>4663 SOCIETE AIR FRANCE <strong>EASA</strong>.A.S.02820 REV 1 BOEING 737-300<br />
Installation of elementary surveillance Dual 1. Limited to installation on Boeing 737-300/-<br />
23.10.2006<br />
BOEING 737-500<br />
ATC Mode S on B737-300/-500 in accordance 500.2. Compatibility of this design change with<br />
with the Modification File MDF-B737-<strong>04</strong>-0<strong>04</strong>, other previously approved modifications must<br />
Rev <strong>01</strong>, dated 11 October 2006.<br />
be determined by the installer.<br />
10027295 SOCIETE AIR FRANCE P-<strong>EASA</strong>.A.S.03975 REV. 2 A320 Cabin Reconfiguration from Dragon Aviation<br />
Leasing to Juneyao Standard(DKH) Revision of<br />
the <strong>EASA</strong> STC 10027295 to remove EWIS<br />
limitation<br />
10032363 SOCIETE AIR FRANCE A340-211, A340-212 A340 Royal Jordanian - New IFE and Cabin<br />
reconfigurationThis STC consists in a cabin<br />
reconfiguration by installing newecoconomic<br />
class seat and a new In-Flight Entertainment<br />
(IFE) system(Sicma Aero IFE SiT).<br />
17.07.2006<br />
03.11.2006<br />
06.06.2006<br />
30.10.2006<br />
23.10.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.11.2<strong>01</strong>0<br />
This STC is applicable to the following aircraft<br />
MSNs :,,- MSN 14,,- MSN 22,,- MSN 38,,-<br />
MSN 43<br />
10038157 SOCIETE AIR FRANCE 777-200 Alitalia Cabin Reconfiguration 777-200 MSN as defined in Change approval<br />
sheet CAS-B777-11-003<br />
10<strong>04</strong>2281 SOCIETE AIR FRANCE 747-400 CorsairFly cabin reconfiguration and SiT IFE<br />
installation.Cabin refurbishment and new IFE<br />
system installation.<br />
10<strong>04</strong>2639 SOCIETE AIR FRANCE A319-111, A319-113,<br />
A320-211, A320-212,<br />
A321-111, A321-212.<br />
Installation of the ACARS (Aircraft<br />
Communication Addressing andReporting<br />
System) CMU-900 to replace the Teledyne<br />
MUA45B<br />
Prior to installation of this modification it 29.10.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it 24.<strong>01</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
none Before installation of this STC, <strong>EASA</strong><br />
STC No. <strong>EASA</strong>.IM.A.S.00677 must<br />
beincorporated.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
21.11.2<strong>01</strong>2<br />
This approval is applicable to the following Prior to installation of this modification it 12.12.2<strong>01</strong>2<br />
MSN:61 ; 63 ; 102 ; 115 ; 144 ; 145 ; 155 ; 186 must be determined thatthe<br />
; 187 ; 214 ; 227 ; 236 ;237 ; 239 ; 270 ; 278 ; interrelationship between this modification<br />
285 ; 286 ; 287 ; 337 ; 352 ; 377 ; 491 ; 498 and any other previouslyinstalled<br />
;509 ; 521 ; 529 ; 544 ; 598 ; 600 ; 608; 618 ; modification and/ or repair will introduce<br />
625 ; 637 ; 777 ; 7<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4926 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.A.S.03176 BEECH 200 Installation of a support base for a stretcher. 08.10.2007<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 413/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4927 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.A.S.03177 BEECH 90 Installation of a support base for a stretcher. 08.10.2007<br />
10<strong>01</strong>5255 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.A.S.03707 BEECH 1900 Installation of a galley. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5294 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.A.S.03838 PIPER PA-34 Pneumatic deicer removal. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7182 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.R.S.<strong>01</strong>315 EUROCOPTER FRANCE AS<br />
355F1<br />
Installation of rack and sending/reception<br />
antennae.<br />
10<strong>01</strong>7237 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.R.S.<strong>01</strong>423 EUROCOPTER FRANCE AS 350 Modification H-25-<strong>04</strong>-07-SFP - installation of<br />
deployable antenna mounted on landing gear.<br />
10<strong>01</strong>7238 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.R.S.<strong>01</strong>424 EUROCOPTER FRANCE AS 355<br />
SERIE<br />
10027064 SOCIETE D'ETUDE ET DE GESTION P-<strong>EASA</strong>.A.S.03925 REV. 1 MS893 A, B, E, E-D<br />
MS894 A, C, E<br />
RALLYE 235 A, C, E, E-D, F<br />
Modification H-25-<strong>04</strong>-07-SFP - installation of<br />
deployable antenna mounted on landing gear.<br />
Reduction of maximum take off and landing<br />
weights to 1000 kg.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
This STC provides approval for the installation<br />
and deployment of the antenna. A separate<br />
approval is required for the installationand<br />
operation of any equipment transmitting<br />
through the antenna.The installation of this<br />
modification by third persons is sub<br />
This STC provides approval for the installation<br />
and deployment of the antenna. A separate<br />
approval is required for the installationand<br />
operation of any equipment transmitting<br />
through the antenna.Prior to installation of this<br />
modification the installer must<br />
MS894 models: seating capacity limited to 3<br />
persons, pilot included.Rallye 235 models:<br />
seating capacity limited to 3 persons,<br />
pilotincluded. Fuel tanks capacity limited to 240<br />
l (2*120l).The airplane configurations listed in<br />
attachment 1 are excluded from<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
16.<strong>01</strong>.2009<br />
21.<strong>04</strong>.2009<br />
12.06.2008<br />
25.09.2008<br />
25.09.2008<br />
Prior to installation of this modification the 08.<strong>01</strong>.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
10027989 SOCIETE D'ETUDE ET DE GESTION P-<strong>EASA</strong>.A.S.03973 DHC-8-100, -200, -300 Installation of ELT KANNAD 406 AF- None<br />
product.The installatio<br />
Upon completion of the change the 24.11.2009<br />
COMPACT or ARTEX ME406<br />
aircraft maintenance program must<br />
beupdated to reflect the recurrent<br />
inspections as defined by<br />
KANNADDOC08038C or ARTEX<br />
Document 570-1600 Rev. G or later<br />
revision of thedocuments approved by<br />
<strong>EASA</strong> The approval holder shall<br />
10028678 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.R.S.<strong>01</strong>561 EUROCOPTER FRANCE AS 350<br />
SERIE<br />
31.07.2009<br />
10028679 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.R.S.<strong>01</strong>560 EUROCOPTER FRANCE AS 355<br />
SERIE<br />
31.07.2009<br />
10028814 SOCIETE D'ETUDE ET DE GESTION P-<strong>EASA</strong>.R.S.<strong>01</strong>492 REV. 3 1. AS350 B, AS350 B1, AS350 B2 Modifications H-25-05-06-SFP and H-25-05-06- This STC is not applicable to AS350B3 model Prior to installation of this modification the 26.07.2<strong>01</strong>2<br />
1. AS350 B3, AS350 BA<br />
SFPAnt - Installation of arack and<br />
helicopters withmodification OP-4305 (Arriel installer must determinethat the<br />
1. AS350 D, AS350 BB<br />
transmitting/receiving antennaeNotes: Initial 2D engine installation) incorporated.<br />
interrelationship between this modification<br />
2. AS355 E, AS355 F, AS355 F1 issue of this STC covered installation of a rack -<br />
and any otherpreviously installed<br />
2. AS355 F2, AS355 N, AS355 NP modificationH-25-05-06-SFPRevision 1 to this<br />
modification will introduce no adverse<br />
STC added installation of transmitt<br />
effect uponthe airworthiness of the<br />
product.<br />
10029480 SOCIETE D'ETUDE ET DE GESTION AS350 B2 Installation system for "EC120 type" seats on<br />
Eurocopter AS350B2 -modification H-08-09-<br />
Siège<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.03.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 414/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032781 SOCIETE D'ETUDE ET DE GESTION DR300/108, DR300/120,<br />
A-07-09-Filtre Ed. 0 - Installation of remote oil None Prior to installation of this modification it <strong>01</strong>.12.2<strong>01</strong>0<br />
DR300/125, DR300/140<br />
filter kit<br />
must be determined thatthe<br />
DR300/180 R, DR315, DR340,<br />
interrelationship between this modification<br />
DR360, DR380, DR400/100,<br />
and any other previouslyinstalled<br />
DR400/120 D, DR400/125,<br />
modification and/ or repair will introduce<br />
DR400/120, DR400/120 A,<br />
no adverse effectupon the airworthiness<br />
DR400/140, DR400/140 B,<br />
DR400/160, DR400/160 D,<br />
DR400/180 S, DR400/200 R,<br />
DR400/180, DR400/180 R,<br />
DR400/2+2, DR400/500,<br />
DR400/NGL<br />
of the product.<br />
10036788 SOCIETE D'ETUDE ET DE GESTION REV. 1 1900 SERIES Installation of a partition in the rear cabin area. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.<strong>01</strong>.2<strong>01</strong>2<br />
10038783 SOCIETE D'ETUDE ET DE GESTION 1. AS350B/BB/BA/D/B1/B2 Front Lower Cowling Modification (Reference None AS350B3 change is also applicable to 14.03.2<strong>01</strong>2<br />
2. AS350B3 (SEE CONDITIONS) H-<strong>01</strong>-11-Capot)Separation of cowling in two<br />
helicopters incorporatingmodifications OP-<br />
3. AS355E/F/F1/F2/N/NP halves reassembled by fasteners.Note: This<br />
3369 and OP-4305. Prior to installation of<br />
STC is also applicable to front lower cowlings<br />
this modification it must be determined<br />
modified asper STC <strong>EASA</strong>.R.S.<strong>01</strong>359).<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modifica<br />
10039483 SOCIETE D'ETUDE ET DE GESTION <strong>EASA</strong>.R.S.<strong>01</strong>391 REV. 1 1- AS350B, AS350BA<br />
Installation of an Outside Aerial Picture This STC does not approve Installation of an The installation of this modification by 07.05.2<strong>01</strong>2<br />
1- AS350B3, AS350D<br />
System.Revision 1 adds installation of Outside Aerial PictureSystem on AS350B3 third persons is subject towritten<br />
1- AS350BB, AS350B1, AS350B2 AILIMOUNT III camera system.<br />
helicopters incorporating modification OP- permission of the approval holder and<br />
2- AS355E, AS355F, AS355F1<br />
4305(Arriel2D engine installation). Compliance holding and disposal ofthe approved<br />
2- AS355F2, AS355N, AS355NP<br />
against the requirements ofapplicable appropriate documentation.Prior to<br />
certification basis for AS350B3 helicopters installation of this modification it must be<br />
determined thatthe interre<br />
10039562 SOCIETE D'ETUDE ET DE GESTION REV. 1 1900 Installation of a galley in accordance with<br />
SOCIETE D'ETUDE ET DEGESTION<br />
AERONAUTIQUE (SEGA) Master Document<br />
ListA-11-03-TwinJet-GalleyII_MDoL Edition 1<br />
April 2<strong>01</strong>2<br />
None None 05.06.2<strong>01</strong>2<br />
10038292 SOFINARE R182<br />
Installation of integrated Flight System Garmin None. None. 03.02.2<strong>01</strong>2<br />
TR182<br />
G-500 and DoubleNav/Com/GPS systems<br />
GNS-430W.<br />
10039948 SOFINARE 1900D INSTALLATION OF TERRAIN AWARENESS None (Applicable to All Models Beechcraft The approval holder shall fulfil the <strong>04</strong>.06.2<strong>01</strong>2<br />
AND WARNING SYSTEM (TAWS).<br />
1900D Airplanes)<br />
obligations of Part 21,<br />
Paragraph21A.109.Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/or<br />
repair<br />
10<strong>01</strong>3935 SOGERMA SERVICES <strong>EASA</strong>.A.S.0034 REV. 1 AIRBUS A310-3<strong>04</strong> Aircraft modification for 8.33 kHz spacing on<br />
VHF system in accordance with Modification<br />
Approval Sheet SOG 23-878 Issue 1 dated<br />
<strong>01</strong>July 20<strong>04</strong> or later <strong>EASA</strong>-approved<br />
revision.Note: This revision reflects the transfer<br />
of this STC from EADS Sogerma Services to<br />
07.<strong>01</strong>.2008<br />
10<strong>01</strong>4149 SOGERMA SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>27 REV 1 AIRBUS A320-211 Cabin layout change from 144 pax to 155 pax<br />
configuration in accordance with the Master<br />
Drawing List ref. MDL-25-861, issue B, dated<br />
August 6, 20<strong>04</strong> or later <strong>EASA</strong> approved<br />
revision.Note: This revision reflects the transfer<br />
of this STC from EADS Sogerma Serv<br />
10<strong>01</strong>4307 SOGERMA SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>551 REV 1 ATR 42-320 Additional probes in RALI configuration in<br />
accordance with MAS SOG-<strong>01</strong>-459 issue 1<br />
dated 30/11/05Note: This revision reflects the<br />
transfer of this STC from EADS Sogerma<br />
Services to Sogerma Services.<br />
1. MSN 078 Associated STC<br />
No.<strong>EASA</strong>.A.S.<strong>01</strong>219 Revision 1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 415/<strong>462</strong><br />
07.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4348 SOGERMA SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>612 REV 1 AIRBUS A340-642 This STC deals with the installation of 4 new 1. This STC is approved only to allow airline<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
double seats in Y class (Kyoto<br />
customer to install on a trial basis a few seats<br />
manufacturer)Note: This revision reflects the on one aircraft (MSN 706).2. The limitations<br />
transfer of this STC from EADS Sogerma and conditions defined in the <strong>EASA</strong> Datasheet<br />
Services to Sogerma Services.<br />
are applicable.A copy of this STC and of the<br />
MAS/MDL must be encl<br />
10<strong>01</strong>4365 SOGERMA SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>635 REV 1 A340-642 This STC deals with the installation of a 2 new<br />
triple seats in W class (Contour design<br />
seats).Note: This revision reflects the transfer<br />
of this STC from EADS Sogerma Services to<br />
Sogerma Services.<br />
10<strong>01</strong>4416 SOGERMA SERVICES <strong>EASA</strong>.A.S.<strong>01</strong>73 REFV 1 AIRBUS A340-642 Installation in upper class side facing Britax<br />
Malcom seats equipped with the inflatable<br />
restraints, monuments, a bar and a chandelier<br />
according to MAS SOG-25-597 issue 4 (dated<br />
02/07/<strong>04</strong>) and reference documents : Airplane<br />
Flight Manual A340-600 1.02.00 P<br />
1. This STC is approved only to allow airline<br />
customer to install on a trial basis a few seats<br />
on one aircraft (MSN 706).2. The limitations<br />
and conditions defined in the <strong>EASA</strong> Datasheet<br />
are applicable.A copy of this STC and of the<br />
MAS/MDL must be encl<br />
10<strong>01</strong>4428 SOGERMA SERVICES <strong>EASA</strong>.A.S.02474 REV 1 DC-9-21 Modification Janus Phase I: Cancellation of the 1. This STC is limited to the MSN 47308.<br />
restriction of flights in icing conditionsNote: This<br />
revision reflects the transfer of this STC from<br />
EADS Sogerma Services to Sogerma<br />
Services.<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>4476 SOGERMA SERVICES <strong>EASA</strong>.A.S.02538 REV 1 AIRBUS A320-211 Cabin modification from 155 to 167 Y/CNote:<br />
This revision reflects the transfer of this STC<br />
from EADS Sogerma Services to Sogerma<br />
Services.<br />
1. This STC is limited to the A320 MSN 615. <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>4862 SOGERMA SERVICES <strong>EASA</strong>.A.S.03086 AIRBUS A300 MODEL B2-1C Replacement of the obsolete RCA weather 1. This STC is limited to the MSN 0032.<br />
29.05.2007<br />
radar by a Honeywell RDR-4B colour display This STC is approved only for the product<br />
radar system with predictive windshear configuration as defined in the approved design<br />
function.<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other airc<br />
10<strong>01</strong>4899 SOGERMA SERVICES <strong>EASA</strong>.A.S.03129 A310-325 Installation of ATC mode S Enhanced<br />
Surveillance (EHS)This Supplement Type<br />
Certificate consists in the installation of new<br />
1. This STC is limited to A310-325 aircraft<br />
model:- MSN 636- MSN 6442. Prior to<br />
installation of this modification the installer must<br />
ATC EHS in order to be compliant with the new determine that the interrelationship between<br />
ATC mode S ‘Enhanced Surveillance’ this modification and any other previously<br />
regulation.<br />
installed modification will i<br />
10<strong>01</strong>5<strong>01</strong>3 SOGERMA SERVICES <strong>EASA</strong>.A.S.03315 AIRBUS A340-313 Virgin Atlantic A340 Cabin Modification. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>5078 SOGERMA SERVICES <strong>EASA</strong>.A.S.03412 AIRBUS A320 SERIES Installation of passenger entertainment cabin<br />
audio system on seatsNote: This STC<br />
supersede DGAC France STC 180-SF-<strong>01</strong>75.<br />
10<strong>01</strong>5079 SOGERMA SERVICES <strong>EASA</strong>.A.S.03413 DGAC FRANCE STC 180-SF-<strong>01</strong>74 AIRBUS A320 SERIES Sony Video System InstallationNote: This STC<br />
supersede DGAC France STC 180-SF-<strong>01</strong>74.<br />
10<strong>01</strong>5080 SOGERMA SERVICES <strong>EASA</strong>.A.S.03414 DGAC FRANCE STC 072-MJ-0857 AIRBUS A300 MODEL B2-1A Installation of a GPS/HIS adapterNote: This<br />
STC supersede DGAC France STC 072-MJ-<br />
0857.<br />
10<strong>01</strong>5081 SOGERMA SERVICES <strong>EASA</strong>.A.S.03415 DGAC STC F-C180-SF-0242; <strong>EASA</strong> AIRBUS A320 SERIES Cabin conversion modificatiom "20 B/C - 148<br />
Y/C"Note: This STC supersede DGAC France<br />
STC F-C180-SF-0242 and <strong>EASA</strong> 20<strong>04</strong>-9168.<br />
10<strong>01</strong>5082 SOGERMA SERVICES <strong>EASA</strong>.A.S.03416 DGAC FRANCE STC F-C072MJ0864; AIRBUS A300-600 Installation of an ELT 96 emergency locator<br />
transmitterNote: This STC supersede DGAC<br />
France STC F-C072MJ0864 and <strong>EASA</strong> 20<strong>04</strong>-<br />
4595.<br />
10<strong>01</strong>5083 SOGERMA SERVICES <strong>EASA</strong>.A.S.03417 DGAC FRANCE STC 180-SF-0229; E AIRBUS A320 SERIES Cabin conversion from 180 Y/C to 16 B/C +<br />
169 Y/CNote: This STC supersede DGAC<br />
France 180-SF-0229 and <strong>EASA</strong> 20<strong>04</strong>-3515.<br />
10<strong>01</strong>5084 SOGERMA SERVICES <strong>EASA</strong>.A.S.03418 DGAC FRANCE STC 180-SF-0221; E AIRBUS A320 SERIES Installation of BENNET seat containerNote:<br />
This STC supersede DGAC France 180-SF-<br />
0221 and <strong>EASA</strong> 20<strong>04</strong>-2036.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 416/<strong>462</strong><br />
<strong>04</strong>.<strong>01</strong>.2008<br />
07.<strong>01</strong>.2008<br />
19.07.2007<br />
12.06.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008<br />
<strong>04</strong>.<strong>01</strong>.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5085 SOGERMA SERVICES <strong>EASA</strong>.A.S.03419 DGAC FRANCE STC 072-MJ-0862; E AIRBUS A300 MODEL B2 SPC antenna modificationNote: This STC<br />
supersede DGAC France STC 072-MJ-0862<br />
and <strong>EASA</strong> 2003-3<strong>04</strong>.<br />
1. Valid only for Airbus B2 MSN 003 <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>5086 SOGERMA SERVICES <strong>EASA</strong>.A.S.03420 DGAC FRANCE STC 072-MJ-0861; E AIRBUS A300 MODEL B2 Cargo door modification for use of SPC<br />
antennaNote: This STC supersede DGAC<br />
France STC 072-MJ-0861 and <strong>EASA</strong> 2003-<br />
303.<br />
1. Valid only for MSN 003. <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>5087 SOGERMA SERVICES <strong>EASA</strong>.A.S.03421 <strong>EASA</strong> 20<strong>04</strong>-2363 AIRBUS A300 MODEL B2 Installation of a ground proximity warning<br />
systemNote: This STC supersedes <strong>EASA</strong> STC<br />
20<strong>04</strong>-2363.<br />
1. Only valid for MSN 003. <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>5208 SOGERMA SERVICES <strong>EASA</strong>.A.S.03623 DHC-6-300 S-53-2039 Structural Provision for Insrument Prior to installation of this modification the<br />
27.08.2008<br />
Panel.<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6846 SOLOY, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>222 FAA STC SR<strong>01</strong>647SE EUROCOPTER FRANCE AS 350 Installation of Honeywell LTS1<strong>01</strong>-700D-2<br />
B2<br />
engine.<br />
10027209 SOLOY, LLC P-<br />
CESSNA 206H, CESSNA T206H Installation of Rolls-Royce 250-B17F/2 series<br />
<strong>EASA</strong>.IM.A.S.03096<br />
engine in a Cessna206H/T206H.<br />
10028355 SOLOY, LLC FAA STC SA<strong>01</strong>985SE 206H, T206H Installation of New Rear Observation Seat in<br />
Cessna 206<br />
10028448 SOLOY, LLC P-<br />
<strong>EASA</strong>.IM.A.S.03237<br />
10028449 SOLOY, LLC P-<br />
<strong>EASA</strong>.IM.A.S.03236<br />
FAA STC SA<strong>01</strong>688SE 206H, T206H Installation of a revised shoulder harness<br />
restraint system and new rearcabin headliner in<br />
a Cessna 206H/T206H<br />
FAA STC SA00858SE 206, U206B, U206C, U206D Installation of Observation Window in Cessna<br />
TU206A, U206E, TU206B<br />
TU206D, TU206E, U206, TU206F<br />
U206A, TU206G, 206H, T206H<br />
U206F, TU206C, U206G<br />
206<br />
See attached Annex. 20.03.2008<br />
None None 14.09.2009<br />
Weight and Balance: Equipment Removed<br />
Item,,Weight (lb),,Station(in)Seat, 2nd Row (2<br />
Seats),,57,,78.0Seat, 3rd Row<br />
(Bench),,36,,105.2 Equipment Installed<br />
Item,,Weight (lb),,Station (in)Seat Assembly<br />
with Armrests,,34.0,,81.7Base Plate<br />
Assembly,,23.2,,81.9<br />
Prior to installation of this modification it 21.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
N/A Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>01</strong>.2<strong>01</strong>0<br />
As per FAA STC SA00858SE, "This<br />
modification has been determined to<br />
becompatible with Soloy STC SA2353NM and<br />
airplanes in landplane,floatplane, and skiplane<br />
configuration when modified in accordance<br />
withFAA approved data."Installer must check<br />
availability<br />
Prior to installation of this modification it 12.<strong>01</strong>.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028758 SOLOY, LLC P-<br />
FAA STC SR00805SE AS350BA Installation of Honeywell LTS1<strong>01</strong>-600A-3A See attached Data Sheet See attached Data Sheet 14.06.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>457<br />
engine on Eurocopter AS350BAhelicopter.<br />
10<strong>01</strong>5900 SOUTHEAST JET GROUP, INC. <strong>EASA</strong>.IM.A.S.02021 ST00589WI CESSNA 5<strong>01</strong>, CITIATION Installation of Honeywell EDZ-605 Two-Tube<br />
24.08.2006<br />
CESSNA 550 CITATION II Electronic Flight Instrumentation System<br />
CESSNA 551, CITIATIONII<br />
CESSNA S550, (CITIATION S/II)<br />
(EFIS).<br />
10<strong>01</strong>6786 SPACECAM SYSTEMS INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>128 REV. 1 TCCA STC SH02-6 AS 350 B<br />
Spacecam RAMS Installation Eurocopter (Aerospatiale) Service Bulletin N° Prior to installation of this modification the 25.08.2009<br />
AS 350 B1<br />
53-05 and 53-06 (for Tail Boom Balast) are installer must determinethat the<br />
AS 350 B2<br />
required as part of this installation.This STC is interrelationship between this modification<br />
AS 350 B3<br />
the <strong>EASA</strong> Validation of Transport Canada STC and any otherpreviously installed<br />
AS 350 BA<br />
n° SH02-6 Issue 2, dated June 28, 2005 modification will introduce no adverse<br />
AS 350 D<br />
effect uponthe airworthiness of the<br />
AS 355 E<br />
AS 355 F<br />
AS 355 F1<br />
AS 355 F2<br />
AS 355 N<br />
product. The installati<br />
10<strong>01</strong>4403 SR TECHNICS AIRCRAFT DESIGN <strong>EASA</strong>.A.S.<strong>01</strong>698 BOEING 737-33V Reconfiguration of six Boeing 737-33V from B737-33V Serial Numbers 29337 to 29342<br />
16.03.2006<br />
SERVICE<br />
149TC to 16BC/100TC including installation of inclusive<br />
G2, G7 and LAV E<br />
10<strong>01</strong>4694 SR TECHNICS AIRCRAFT DESIGN <strong>EASA</strong>.A.S.02860 BOEING 747-400 SERIES Reconfiguration of five Boeing B747-400 1) Limited to the following registration<br />
08.10.2007<br />
SERVICE<br />
aircraft to 54J/62W/228Y.<br />
Mark/Serial Number aircraft: G-VFAB/24958,<br />
G-VHOT/26326, G-VBIG/26255,G-<br />
VWOW/32745, G-VROC/32746.2) The<br />
following <strong>EASA</strong> approved STC's must be<br />
installed concurrently with this design<br />
change:<strong>EASA</strong>.A.S.03165<strong>EASA</strong>.IM.A.S.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 417/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4007 SR TECHNICS SWITZERLAND Ltd. <strong>EASA</strong>.A.S.<strong>01</strong><strong>04</strong>7 REV. 1 B747-400 Reconfiguration of Virgin Atlantic Airways B747- none Associated instructions for continued 24.02.2<strong>01</strong>1<br />
400 from LHR to LGWconfiguration in<br />
airworthiness, included in SRTechnics<br />
accordance with SR Technics Master Data<br />
Report C-747-25-10<strong>01</strong>-CS-13 Rev. 3,<br />
ListC747-25-10<strong>01</strong>-MDL-<strong>01</strong>, Rev 3 or later<br />
must be incorporated in theaircraft<br />
approved revisions<br />
maintenance documentation<br />
10<strong>01</strong>4568 SR TECHNICS SWITZERLAND Ltd. <strong>EASA</strong>.A.S.02672 REV. 1 A319-112 In-Flight telecommunication equipment - MSN 1077, 1084, 1089, 1136, 1147, 1155, Prior to installation of this modification it 10.02.2<strong>01</strong>1<br />
antenna installation(partial removal of GTE 1170, 1209, 1277<br />
must be determined thatthe<br />
Airfone System installed by FAA STC<br />
interrelationship between this modification<br />
ST0<strong>01</strong>29NY-Dand SA1693GL) The Revision 1<br />
and any other previouslyinstalled<br />
was issued to reflect the transfer from SR<br />
modification and/ or repair will introduce<br />
TechnicsIreland to SR Technics Switzerland<br />
no adverse effectupon the airworthiness<br />
LTD<br />
of the product<br />
10029069 SR TECHNICS SWITZERLAND Ltd. REV. 1 B747-400 Reconfiguration of Virgin Atlantic Airlines B747- This STC is limited to the following<br />
Prior to installation of this modification it 24.02.2<strong>01</strong>1<br />
400 Aft Upper Deck inaccordance with SR A/C:1.,,B747-4Q8, G-VFAB, Tab # RT945, must be determined thatthe<br />
Technics Master Data List C747-25-1005-MDL MSN 24958.2.,,B747-4Q8, G-VHOT, Tab # interrelationship between this modification<br />
Rev. 0. orlater approved revisions<br />
RT946, MSN 26326.3.,,B747-4Q8, G-VBIG, and any other previouslyinstalled<br />
Tab # RT947, MSN 26255.4.,,B747-41R, G- modification and/ or repair will introduce<br />
VWOW, Tab # RM052, MSN 32745.5.,,B747- no adverse effectupon the airworthiness<br />
41R, G-VROC, Tab # RM053,<br />
of the product.<br />
10031834 SR TECHNICS SWITZERLAND Ltd. REV. 3 B767-300 Cabin reconfiguration - Air Seychelles 767-<br />
300Aircraft reconfiguration by replacing the<br />
existing J-class seat with anew electrically<br />
powered seat. There are adaptations to the<br />
existingPSU, Y-class cabins to suit new layout.<br />
10034187 SR TECHNICS SWITZERLAND Ltd. A330-300 Virgin Atlantic Airways (VAA) A330-300 EIS<br />
Cabin Reconfiguration (59W /255Y).This STC<br />
reconfigures the cabin layout from 48 W class<br />
seat / 265 Yclass seat to 59 W class seat / 255<br />
Y class seat, with associatedadaptations.<br />
10038294 SR TECHNICS SWITZERLAND Ltd. A310 Amiri Flight A310-300 Cabin RefurbishmentBy<br />
refurbish the existing Cabin by:- Removal of the<br />
existing seats and installation of new seats in<br />
theFirst, Business and Economy class.-<br />
Replace the existing IFE system- Installation of<br />
a new VCC, class dividers,<br />
10<strong>04</strong>0981 SR TECHNICS SWITZERLAND Ltd. A340-541 VIP Cabin RefurbishmentThe modification<br />
consist of the following items:-,,Refurbishment<br />
of existing cabin materials-,,Deletion of a<br />
double seat and installation of aft stowage-<br />
,,Installation of a book cabinet-,,Upgrade of the<br />
IFE equipment (monitors, playe<br />
10<strong>04</strong>2831 SR TECHNICS SWITZERLAND Ltd. A330-223 Cabin reconfigurationBy changing the existing<br />
Air Berlin Business Class InteriorConfiguration<br />
into a new Etihad Business Class Interior<br />
Configuration.<br />
10038822 ST AEROSPACE MOBILE, INC. FAA STC ST13005AT-T B757-200 Conversion of Passenger Configuration to<br />
Cargo/Passenger CombinationConfiguration<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.11.2<strong>01</strong>2<br />
1-,,This STC must be implemented together<br />
with <strong>EASA</strong> STC ref : 10031808Rev <strong>01</strong> (and<br />
associated Approved Model List), or later<br />
revisions approvedby <strong>EASA</strong>. 2-,,This STC is<br />
applicable to A330-300 following MSN :-,,1195<br />
-,,12<strong>01</strong> -,,1206 -,,1215 -,,1231<br />
Prior to installation of this modification it 14.03.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
S/N: 0667 A7-AFE Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
03.02.2<strong>01</strong>2<br />
S/N: <strong>04</strong>95 A7-HHH Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10.08.2<strong>01</strong>2<br />
S/N: <strong>04</strong>03 / <strong>04</strong>32 / <strong>04</strong>44 / <strong>04</strong>54 / <strong>04</strong>69 / <strong>04</strong>76 /<br />
<strong>04</strong>93The IFE System must be deactivated for<br />
any flight before EMI testing isfinally<br />
accomplished.For any other limitation refer to<br />
the existing AMES AFMS, Doc.<br />
No.AFS_M1480<strong>01</strong><strong>01</strong>_MGR_06102<strong>01</strong>1, latest<br />
approved Rev<br />
This STC is limited to a/c serial number 25622<br />
onlyAs per the Temporary Deviation a/c<br />
converted under this STC cannot beoperated<br />
after 23/12/2<strong>01</strong>3 unless incorporating design<br />
changes to theMain Deck Cargo Door.This<br />
STC cannot be installed on aeroplanes with<br />
Approval is valid only for MSN mentioned<br />
aboveDue to some missing passenger<br />
seats placards, the Airline<br />
ServicesLimited Engineering Change<br />
Notice, C330-25-07<strong>04</strong>-ECN-03, Rev. 2,<br />
needs tobe accomplished prior the first<br />
passenger flight on 27. December<br />
2<strong>01</strong>2.Pr<br />
An approved Cargo Loading System<br />
must be installed concurrently<br />
beforeoperations.An approved FWD 9g<br />
barrier must be installed concurrently<br />
beforeoperations.ST Aerospace Minor<br />
Modifications EDC/<strong>EASA</strong>/DOA/023 and<br />
EDC/<strong>EASA</strong>/DOA/41must be installed<br />
concurrently<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 418/<strong>462</strong><br />
20.12.2<strong>01</strong>2<br />
22.03.2<strong>01</strong>2
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027268 STANDARD AERO FAA STC ST02756CH-D 737-600, -700, -800, -900, Installation of an in flight entertainment (IFE) see limitations and conditions on STC FAA Prior to installation of this modification it 17.09.2009<br />
737-900ER<br />
system<br />
ST02756CH-D<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10028167 STANDARD AERO FAA STC ST<strong>01</strong>991CH MF50 <strong>EASA</strong> Validation of FAA STC<br />
ST<strong>01</strong>991CHInstallation of an L3<br />
Communications (Fairchild) Model F1000 Flight<br />
DataRecorder (FDR) System in accordance<br />
with Garrett Aviation ServicesDrawing List,<br />
Doc. Number 1002382 Revision H, dated <strong>04</strong>th<br />
June 20<strong>04</strong> orlater revisio<br />
10029879 STANDARD AERO FAA STC SE02357NY PT6A-135A Installation of the Pratt & Whitney Canada,<br />
PT6A-135, dual fuel feedline configuration in<br />
accordance with Standard Aero, Inc.<br />
EngineeringReport, 0<strong>01</strong>-07-<strong>01</strong>, Rev. 0, dated<br />
February 07, 2007.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.12.2009<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
28.<strong>04</strong>.2<strong>01</strong>0<br />
10032484 STANDARD AERO REV. 1 FAA STC SA02367NY F90 KING AIR Installation of Pratt and Whitney Canada PT6A- None Prior to installation of this modification it 23.11.2<strong>01</strong>0<br />
135A Engines.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035155 STANDARD AERO FAA STC ST02803CH-D EMB-135ER, EMB-135LR,<br />
EMB-135KE, EMB-135KL,<br />
EMB-145, EMB-145MP, EMB-<br />
145EP,<br />
EMB-145ER, EMB-145MR,<br />
EMB-145LR, EMB-145XR<br />
Installation of a Honeywell KHF-1050 HF<br />
System.<br />
10038105 STANDARD AERO FAA STC ST02912CH-D MF50 Installation of an interior refurbishment and a<br />
pocket doorValidation of FAA STC N°<br />
ST02912CH-D<br />
10<strong>04</strong><strong>01</strong>81 STANDARD AERO FAA STC SA02715CH-D 1. 200<br />
1. 200C<br />
2. B200<br />
2. B200C<br />
Installation of Pratt & Whitney PT6A-52<br />
Engines in accordance withStandard Aero<br />
Master Data List document number 1<strong>01</strong>6151,<br />
Revision "A",dated June <strong>01</strong>, 2009 or later FAA<br />
approved revision.<br />
10<strong>04</strong>1237 STANDARD AERO REV. 2 FAA STC ST03038CH-D GV Reconfiguration of a Cabin Floorplan<br />
Arrangement<br />
10<strong>01</strong>5708 STAR AVIATION Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>7<strong>01</strong> REV 1 FAA STC ST02943AT BOEING 777-200<br />
BOEING 777-300<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.05.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>01</strong>.2<strong>01</strong>2<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.06.2<strong>01</strong>2<br />
1. The installer must determine whether this<br />
design change is compatiblewith previously<br />
approved modifications.2. If the holder agrees<br />
to permit another person to use this<br />
certificateto alter the product, the holder shall<br />
give the other person writtenevide<br />
Installation of Connexion by Boeing Next 11. Airworthiness Limitations Section of the<br />
Generation Antenna and Satellite Data Instruction for Continuous Airworthiness,<br />
SystemNote: This Revision reflects the transfer document numbers R44-<strong>04</strong>03, revision B,<br />
of this STC from Flight Structures, Inc. to Star dated 22nd July 2005 for -200 series, R44-<br />
Aviation, Inc.<br />
0218, revsion B, dated 20th October 20<strong>04</strong> for -<br />
300 series, or later FAA approved revis<br />
Prior to installation of this modification it 05.09.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 419/<strong>462</strong><br />
05.09.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5850 STAR AVIATION Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>950 ST02989AT CESSNA 500<br />
The modification will consist of a composite<br />
12.05.2006<br />
CESSNA 5<strong>01</strong><br />
structure with a metal faceplate wich will be<br />
CESSNA 550<br />
fitted over the center of the existing<br />
CESSNA 551<br />
Glareshield. An area of the existing glareshield<br />
CESSNA S550<br />
will be removed to allow for wires to be routed<br />
to the annunciators and switc<br />
10036456 STAR AVIATION Inc. P-<br />
<strong>EASA</strong>.IM.A.S.00285<br />
REV. 1 FAA STC ST02861AT B747-400 Installation of Connexion by Boeing Next<br />
Generation Antenna and SateliteData System<br />
in accordance with Star Aviation Inc. Master<br />
Data ListR44-<strong>01</strong>63, Revision CP, Dated May<br />
12, 2<strong>01</strong>1 or later approved revision<br />
10<strong>04</strong>1648 STAR AVIATION Inc. <strong>EASA</strong>.IM.A.S.00286 REV. 1 FAA STC ST02942AT 747-400 Installation of Cabin Wireless Local Area<br />
Network (CWLAN) in accordancewith Star<br />
Aviation Inc. Master Data List R44-<strong>01</strong>75,<br />
Revision G, datedOctober 13, 20<strong>04</strong>, or later<br />
FAA approved revisions and<br />
Provisionalinstallation of a Panasonic Avionics<br />
Corporation eXP<br />
10<strong>01</strong>6830 STARFLEX L.L.C. <strong>EASA</strong>.IM.R.S.<strong>01</strong>2<strong>01</strong> FAA STC SH7962SW-D EUROCOPTER FRANCE AS<br />
355F2<br />
Installation of two Allison 250-C20R engines<br />
and enhanced anti-torque system in<br />
accordance with AHC drawing list 355A82-<br />
1755 Revision D dated November 5, 1990 or<br />
later FAA approved revision<br />
10<strong>01</strong>6832 STARFLEX L.L.C. <strong>EASA</strong>.IM.R.S.<strong>01</strong>203 SH7961SW-D Installation of two Allison 250-C20R engines in<br />
accordance with AHC drawing list 355A82-<br />
1753 Revision H dated November 5, 1990 or<br />
later FAA approved revision<br />
10035635 STARFLEX L.L.C. AS 355 F1, AS 355 F2 Compliance of C20R installation with BCAR<br />
10035081 STC ACQUISITION, LLC FAA STC ST<strong>01</strong>567LA G-1159 (GULFSTREAM II)<br />
G-1159A (GULFSTREAM III)<br />
G-1159B (GULFSTREAM IIB)<br />
Section G and confirmation ofability of C20R to<br />
fly one engine inoperative profiles.<br />
Installation of a pylon mounted ejector system<br />
with new design thrustreversers, to show<br />
compliance with ICAO Annex 16, Volume 1,<br />
Amendment 9,Chapter 3 noise requirements.<br />
None Aircraft Flight Manual Supplement R44-<br />
0300 Rev. IR dated October 16,20<strong>04</strong> is a<br />
required part of this STC.Instruction for<br />
Continued Airworthiness Star Aviation<br />
Document No #R44-0273, Rev. D, dated<br />
June 20, 2<strong>01</strong>1 must be made available to<br />
theoperator at the ti<br />
None AFM Supplement R44-0293, Revision A,<br />
dated October 18, 20<strong>04</strong> shall be onboard<br />
the modified aircraftInstructions for<br />
Continued Airworthiness Document #<br />
R44-<strong>01</strong>82 Rev. IRdate June 16, 20<strong>04</strong>,<br />
Document # R44-290, Rev. IR dated July<br />
15, 20<strong>04</strong> andDocument # R44-<strong>04</strong>27<br />
1. The present STC is the validation of the FAA<br />
STC SH7962SW-D, last amended on <strong>01</strong><br />
February 2006.2. Compatibility of this<br />
modification with previously approved<br />
modifications of the aircraft must be<br />
determined by the installer.<br />
1. The present STC is the validation of the FAA<br />
STC SH7961SW-D, last amended on <strong>01</strong><br />
February 2006.2. Compatibility of this<br />
modification with previously approved<br />
modifications of the aircraft must be<br />
determined by the installer.<br />
none When fitted with STC<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>203, the AS355F1 is<br />
certificated asGroup A under BCAR<br />
Section G ("Equivalent to Category A" in<br />
accordancewith JAR OPS 3, ACJ OPS<br />
3.480 (a)(1)&(a)(2)) when the<br />
followingconditions are met (as listed in<br />
Model G-1159, (Gulfstream II)1),,Aircraft<br />
without Aircraft Service Change (ASC) 81,<br />
“62,500 PoundIncreased Gross Weight<br />
Modifications, or those with a Maximum<br />
(ramp)weight less than 62,500 lb are not<br />
eligible for this modification.2),,Aircraft with<br />
ASC 200<br />
09.09.2<strong>01</strong>1<br />
23.10.2<strong>01</strong>2<br />
16.<strong>01</strong>.2007<br />
16.<strong>01</strong>.2007<br />
06.07.2<strong>01</strong>1<br />
the TCDS <strong>EASA</strong>.R.146)<br />
Prior to installation of this modification it 24.05.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4128 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>238 REV 1 DC-9-80 (MD-80) SERIES Introduction of FlightVu Cabin Surveillance<br />
System<br />
21.06.2006<br />
10<strong>01</strong>4129 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>239 BOEING 757-200 Introduction of SSR Mode S Enhanced<br />
Surveillance<br />
30.05.2005<br />
10<strong>01</strong>4131 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>241 BAE ATP Rework to Landing Gear Emergency Up-Lock<br />
Release Mechanism<br />
15.11.2005<br />
10<strong>01</strong>4185 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>323 REV 1 FOKKER F.27 MARK 500<br />
FOKKER F.27 MARK 600<br />
Use of TRA-45A Display Indicator 30.<strong>01</strong>.2006<br />
10<strong>01</strong>4209 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>361 REV 1 BAE ATP Introduction of Class E Compartment for LFD<br />
Modified Aircraft.<br />
1. Flight Manual Supplement S21.FMS-0008; 09.<strong>04</strong>.2008<br />
10<strong>01</strong>4210 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>362 REV 1 BAE ATP Introduction of Freight Loading & Restraint This major change is limited to embodied into a<br />
09.<strong>04</strong>.2008<br />
System for LFD Modified Aircraft.<br />
Bae aircraft previously modified for the<br />
installation of a large cargo door at the rear of<br />
the fuselage in accordance with Bae Service<br />
Bulletin ATP-52-036 and with the installation of<br />
a main cabin Class 'E' c<br />
10<strong>01</strong>4211 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>363 BAE ATP Installation of AAR Freight Loading System This STC may only be embodied into BAe ATP<br />
aircraft previously modified for the installation<br />
of a large cargo door at the rear of the<br />
fuselage, in accordance with British Aerospace<br />
Service Bulletin SBATP-52-036 (Modification<br />
M6<strong>01</strong>38A), with a barrier net in<br />
30.<strong>01</strong>.2006<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 420/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4252 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>477 BOEING 757-200 Introduction of Honeywell MKV Enhanced<br />
Ground Proximity Warning System (EGPWS)<br />
22.09.2005<br />
10<strong>01</strong>4253 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>478 BOEING 757-200 Introduction of Honeywell GNSSU Receiver 22.09.2005<br />
10<strong>01</strong>4344 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>606 LOCKHEED L1<strong>01</strong>1 - TRISTAR Introduction of a stand-alone GPS receiver 22.03.2006<br />
10<strong>01</strong>4392 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>681 SAAB SF340A<br />
Saab 340 Class E Cargo CompartmentThis -- 12.02.2007<br />
SAAB SF340B<br />
significant major change, designed by STC WP-<br />
<strong>EASA</strong>.A.S.<strong>01</strong>681Twenty One Limited, will<br />
convert the main passenger cabin to a class E<br />
cargo compartment for the carriage of freight<br />
10<strong>01</strong>4417 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>738 SAAB 340<br />
SAAB 340B<br />
Saab 340 Bulk Cargo Restraint System (as<br />
defined in document S21 MDL-0034). This<br />
major change will introduce transverse nets at<br />
discrete positions in the aircraft main cabin<br />
(converted to Class E under STC Twenty One<br />
Limited major change S21.25-63-1<strong>01</strong>5) to<br />
10<strong>01</strong>4418 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>739 SHORTS SD3-60 Introduction of ACAS II & Single Mode S<br />
Transponders with Elementary Surveillance.<br />
10<strong>01</strong>4443 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02494 BAE ATP Introduction of Rockwell Collins ACAS II and<br />
Dual Mode S Transponder System<br />
10<strong>01</strong>4446 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02499 CESSNA 550 CITATION II Introduction of an AirCell Satellite Telephone<br />
System ST 3100 to the aircraft.This<br />
modification installs the handset into an arm<br />
rest on the rear starboard side of the aircraft.<br />
The Satellite Phone Transceiveris installed in<br />
the mid cabin drinks stowage on<br />
10<strong>01</strong>4447 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02500 BOEING 767-200-300 Introduction of SSR Mode S Enhanced<br />
Surveillance System.<br />
10<strong>01</strong>4477 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02539 BAE 146 Introduction of T2 CAS Collision Avoidance &<br />
Terrain Awareness System<br />
10<strong>01</strong>4522 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02605 AIRBUS A310 SERIES Installation of Honeywell MK V EGPWS.This<br />
supplemental Type Certificate installs a Terrain<br />
Awareness Warning System.<br />
This STC must be used in conjunction with<br />
<strong>EASA</strong> STC <strong>EASA</strong>.A.S.<strong>01</strong>681 "Saab 340 Class<br />
E Cargo Compartment".<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This design change should be embodied<br />
concurrently with or after the embodiment of<br />
STC Twenty One Limited minor design change<br />
S21.23-29-1000.<br />
23.<strong>04</strong>.2007<br />
13.03.2006<br />
16.02.2006<br />
09.06.2006<br />
Boeing 767-200/300 series.It is a condition of<br />
12.10.2007<br />
this STC that transponders of different<br />
manufacturers must not be intermixed, refer to<br />
STC 21 IPC supplement S21.TEC-0033 for<br />
further details.<br />
- 22.05.2006<br />
10<strong>01</strong>4523 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02606 BOEING 727 SERIES Introduction of Emergency Locator Transmitter 15.06.2006<br />
10<strong>01</strong>4564 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02664 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Introduction of Passenger Cabin Interior 22.06.2006<br />
10<strong>01</strong>4597 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02717 BAE ATP Rework of LH Passenger Door 11.05.2007<br />
10<strong>01</strong><strong>462</strong>8 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02766 BAE 146/AVRO 146 SERIES Introduction of T2CAS Collsion Avoidance &<br />
Terrain Awareness Warning System<br />
-- 03.11.2006<br />
10<strong>01</strong>4667 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02824 BOEING 757-200 SERIES Reduction of Over-Wing Emergency Exits from This STC is approved only for the product<br />
22.12.2006<br />
4 to 2.<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>4683 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02846 SD3-60 Introduction of Honeywell MK VI EGPWS 07.12.2006<br />
10<strong>01</strong>4711 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02883 BAE 146 Introduction of Hoenywell RDR-4B Weather<br />
Radar System<br />
10.07.2007<br />
10<strong>01</strong>4723 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.02900 FOKKER F.27 MARK 050 Introduction of Rockwell Collins Dual ADF-60 Instructions for Continued Airworthiness: STC<br />
20.06.2007<br />
FOKKER F.27 MARK 0502 System in the F27 Mark 200. This installation Tewnty One Limited Change Supplement<br />
FOKKER F.27 MARK 06<strong>04</strong> replaces the existing Bendix Dual ADF Manual document S21.TEC-0094 Revision 0,<br />
FOKKER F.27 MARK 100 System.In accordance with STC Twenty One dated 21/03/2002, or later <strong>EASA</strong> approved<br />
FOKKER F.27 MARK 200 Limited Master Drawing List document S21. revision.<br />
FOKKER F.27 MARK 300 MDL-0264 dated 14/12/2006 or later <strong>EASA</strong><br />
FOKKER F.27 MARK 400<br />
FOKKER F.27 MARK 500<br />
FOKKER F.27 MARK 600<br />
FOKKER F.27 MARK 700<br />
appr<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 421/<strong>462</strong><br />
28.11.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4814 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03022 REV 2 BOMBARDIER CL-600-2B19 Introduction of Passenger Cabin interior. <strong>EASA</strong> STC No. <strong>EASA</strong>.IM.A.S.<strong>01</strong>752 must be<br />
fitted.Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon<br />
16.<strong>01</strong>.2009<br />
10<strong>01</strong>4900 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03130 737- 600, 700, 800, 900<br />
Installation of Cabin Vu-123 Cabin Surveillance<br />
737-200, 300, 400, 500,<br />
System.<br />
10<strong>01</strong>4918 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03164 BOMBARDIER CL-600-2B16 (6<strong>04</strong>) Introduction of Passenger Cabin Interior. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>4997 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03297 REV 1 BOEING 767-200<br />
BOEING 767-300<br />
10<strong>01</strong>5<strong>01</strong>8 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03324 CESSNA 500, CITATION<br />
CESSNA 550<br />
10<strong>01</strong>5068 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03394 AIRBUS A318<br />
AIRBUS A319<br />
AIRBUS A320<br />
AIRBUS A321<br />
23.<strong>01</strong>.2008<br />
25.08.2008<br />
Introduction of CabinVu-123 Cabin Surveillance<br />
System<br />
20.05.2008<br />
Introduction of Dual GNS-430/530 05.05.2008<br />
Introduction of Wingspeed XLLink<br />
Communications and Data Management<br />
System<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5109 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03452 BOMBARDIER CL-600-2B19 Introduction of Passenger Cabin interior. 07.03.2008<br />
10<strong>01</strong>5115 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03464 SAAB SF340A Rework of Class E cargo role of QC variant Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
19.12.2008<br />
10<strong>01</strong>5176 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03553 BOEING 737-300 Carriage of Horses & Grooms 1. This design change is applicable to Boeing<br />
737-300 aircraft converted under FAA STC<br />
SA2968SO, SA2969SO, and SA2970SO &<br />
SA2971SO as previously been validated by the<br />
UK CAA under Airworthiness Approval Note<br />
AAN 24984.2. The certification basis has b<br />
10<strong>01</strong>5185 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03568 BOMBARDIER BD-700-1A11 Introduction of Passenger Cabin Interior. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
23.12.2008<br />
10<strong>01</strong>5199 STC TWENTY ONE LIMITED <strong>EASA</strong>.A.S.03590 BOEING 767-200 Introduction of Change 7.0 ACAS II and Dual<br />
Mode S<br />
12.06.2008<br />
10<strong>01</strong>7185 STC TWENTY ONE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>318 AS 355 F1 Introduction of Skylark 2 Radar. <strong>01</strong>.02.2007<br />
10<strong>01</strong>7212 STC TWENTY ONE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>368 R44<br />
R44 II<br />
Installation of removable crop spraying<br />
equipment onto Robinson R 44 & R 44 II<br />
helicopters<br />
1. Certified in Restricted Category2. All<br />
limitation of RFM supplement apply3. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modifica<br />
10026853 STC TWENTY ONE LIMITED P-<strong>EASA</strong>.A.S.03708 REV. 1 BOMBARDIER CL-600-2B19 Introduction of Wireless Local Area Network. 1. Prior to installation of this modification 20.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
10028521 STC TWENTY ONE LIMITED BD-700-1A10 Customized Aircraft Completion - ASN 9251. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.<strong>01</strong>.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 422/<strong>462</strong><br />
29.10.2008<br />
07.<strong>04</strong>.2009<br />
<strong>01</strong>.08.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029416 STC TWENTY ONE LIMITED P-<strong>EASA</strong>.A.S.03895 BD-700-1A10 Customized Aircraft Completion - ASN 9266 None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.03.2<strong>01</strong>0<br />
1003<strong>01</strong>61 STC TWENTY ONE LIMITED 1. CESSNA 337<br />
2. REIMS CESSNA 337<br />
Introduction of Bubble Windows Restricted to un-pressurized versions of the<br />
Cessna/Cessna Reims 337aircraft<br />
10030229 STC TWENTY ONE LIMITED P-<strong>EASA</strong>.A.S.03972 B757-200/ -300 Introduction of Air Conditioning Filter Installation of STC21 Limited Minor Change<br />
S21.21-15-10<strong>04</strong>, must beembodied prior<br />
to, or concurrent with, this STC<br />
10030237 STC TWENTY ONE LIMITED P-<strong>EASA</strong>.A.S.03926 SAAB SF340A, SAAB 340B Rework of the Class E Compartment for<br />
inclusion of a courier seatingarea for up to 5<br />
occupants, S21.25-63-1355.<br />
10030991 STC TWENTY ONE LIMITED REV. 1 L-410 UVP-E20 CARGO<br />
L-410 UVP-E9<br />
L-410 UVP, L-410 UVP-E,<br />
10031459 STC TWENTY ONE LIMITED F 406 Installation of Thales I-MASTER A-Flight Radar<br />
Turret<br />
<strong>EASA</strong>.A.S.<strong>01</strong>681 R1 and <strong>EASA</strong>.A.S.<strong>01</strong>738<br />
must be installed<br />
Prior to installation of this modification it 31.05.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it <strong>04</strong>.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it <strong>04</strong>.06.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Introduction of under wing emergency exits. None None 11.06.2<strong>01</strong>2<br />
10031662 STC TWENTY ONE LIMITED CL-600-2B16 Introduction of Swift Broadband 1. The Airworthiness Approval of the wireless<br />
system does not constituteOperational<br />
Approval for the use of transmitting PEDs on<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.08.2<strong>01</strong>0<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
board of theaircraft. Operational Approval must and any other previouslyinstalled<br />
be obtained from the responsibledivision of the modification and/ or repair will introduce<br />
operational authority of the ai<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031863 STC TWENTY ONE LIMITED B757-200 Introduction of CabinVu-123 Cabin Surveillance None Prior to installation of this modification it 20.09.2<strong>01</strong>0<br />
System<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10031961 STC TWENTY ONE LIMITED BD-700-1A10 Customized Aircraft Completion - ASN 9365 none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.09.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 423/<strong>462</strong><br />
02.09.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
100320<strong>01</strong> STC TWENTY ONE LIMITED DC-9-11, DC-9-12, DC-9-13, Introduction of Cabin Vu-123 Cabin<br />
None Prior to installation of this modification it 30.09.2<strong>01</strong>0<br />
DC-9-14, DC-9-15, DC-9-15F, Surveillance System<br />
must be determined thatthe<br />
DC-9-21, DC-9-31, DC-9-32,<br />
interrelationship between this modification<br />
DC-9-32 (VC-9C), DC-9-32F,<br />
and any other previouslyinstalled<br />
DC-9-32F (C-9A, C-9B),<br />
modification and/or repair will introduce<br />
DC-9-33F, DC-9-34, DC-9-34F,<br />
no adverse effectupon the airworthiness<br />
DC-9-41, DC-9-51,<br />
DC-9-81(MD-81),DC-9-82(MD-82),<br />
DC-9-83(MD-83),DC-9-87(MD-87),<br />
MD-88, MD-90-30, 717-200<br />
of the product<br />
10032098 STC TWENTY ONE LIMITED BOMBARDIER CL600-2B19 Removal of Divan Seating Restriction This design change will allow the removal of an<br />
existing limitation onoccupation of the<br />
forwardmost seating position on the installed<br />
divan(<strong>EASA</strong> STC No. <strong>EASA</strong>.A.S.03452 and<br />
<strong>EASA</strong>.A.S.03022 refers). If the arrester block<br />
installation assembly becomes unservic<br />
10032232 STC TWENTY ONE LIMITED CESSNA 206H, T206H Introduction of Stand-By Battery Power Supply<br />
in accordance withS21.MDL-0770, issue 2,<br />
dated 14/10/2<strong>01</strong>0<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.10.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
19.10.2<strong>01</strong>0<br />
10033452 STC TWENTY ONE LIMITED B757-200 Carriage of Horses & Grooms in Freighter a/c This design change is applicable to Boeing 757- Prior to installation of this modification it 21.<strong>01</strong>.2<strong>01</strong>1<br />
200 aircraft convertedunder Boeing's Special must be determined thatthe<br />
Freighter Programme, approved by the UK interrelationship between this modification<br />
CAA underAirworthiness Approval Note AAN and any other previouslyinstalled<br />
27308 (acceptable to <strong>EASA</strong> under the modification and/ or repair will introduce<br />
<strong>EASA</strong>Grandfather provisions).<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10034641 STC TWENTY ONE LIMITED REV. 3 PA-31 Introduction of Chin Mount and re-located Pitot<br />
tubes.<br />
10034714 STC TWENTY ONE LIMITED REV. 1 PA-31 Introduction of an Enlarged Window and<br />
Sensor Turret<br />
Not to be flown in icing conditions with the chin<br />
mount and aerodynamicfairing installed.The<br />
installation of a sensor turret is<br />
prohibited.Limitations as defined in AFMS<br />
S21.FMS-0072 Issue 3.<br />
Limited to aircraft serial numbers 31-7712054<br />
& 31-815 onlyNot to be flown in icing<br />
conditionsLimitations as defined in AFMS<br />
S21.FMS-0077 Issue 1 dated 20/<strong>04</strong>/2<strong>01</strong>1<br />
10034734 STC TWENTY ONE LIMITED REV. 1 PA-31 Introduction of a Belly Pod Not to be flown in icing conditions with the belly<br />
pod installedLimitations as defined in AFMS<br />
S21.FMS-0080 Issue 2 dated 31/10/2<strong>01</strong>2<br />
Prior to installation of this modification it 29.05.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 27.<strong>04</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 22.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035173 STC TWENTY ONE LIMITED B737-300 Introduction of Number 2 Galley Assembly None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.06.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 424/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10035193 STC TWENTY ONE LIMITED EMB-145 Introduction on EMB-145 of Saftglo<br />
none Prior to installation of this modification it 03.06.2<strong>01</strong>1<br />
photoluminescent FPEEPMS<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10035344 STC TWENTY ONE LIMITED A320-214 Custom Interior A320 Jubilee This design change approval is applicable on<br />
Aircraft model AirbusA320-214, aircraft serial<br />
number 4199.<br />
This STC has associated a supplement to 16.06.2<strong>01</strong>1<br />
the original TC Holder's EWISInstructions<br />
for Continued Airworthiness. This<br />
supplement is included inthe document<br />
JUBL-CCR-400-EWA "Instructions for<br />
continued airworthiness(EWIS source<br />
document)" Prior to installatio<br />
10035624 STC TWENTY ONE LIMITED BD-700-1A11 Customized Interior Completion - ASN 9308 Restricted to ASN 9308 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.07.2<strong>01</strong>1<br />
10036234 STC TWENTY ONE LIMITED 767-300 Omnibus Modification for the Approval of Air none Prior to installation of this modification it 24.08.2<strong>01</strong>1<br />
New Zealand EngineeringOrders Embodied on<br />
must be determined thatthe<br />
the A/C<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10036644 STC TWENTY ONE LIMITED CL-600-2B16 Introduction of Corporate Interior Restricted to ASN 5616 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.09.2<strong>01</strong>1<br />
10036793 STC TWENTY ONE LIMITED B777-200, B777-200LR,<br />
B777-300, B777-300ER, B777F<br />
10037523 STC TWENTY ONE LIMITED P-<strong>EASA</strong>.A.S.03880 A318, A319, A320, A321 Introduction of an Avionica Mini Quick Access<br />
Recorder MK III withCellular Module<br />
Introduction of CabinVu 123 Cabin Surveillance None. Prior to installation of this modification it 06.10.2<strong>01</strong>1<br />
System.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
02.12.2<strong>01</strong>1<br />
10039188 STC TWENTY ONE LIMITED A319-115 Introduction of Custom Interior This design change approval is applicable on This STC has associated a supplement to 16.<strong>04</strong>.2<strong>01</strong>2<br />
Aircraft model AirbusA319-115, aircraft serial the original TC Holder’s EWISInstructions<br />
number <strong>462</strong>2. Any subsequent change to the for Continued Airworthiness. This<br />
modes of operation of the WLAN<br />
supplement KCJ1approvedunder<br />
this design change will require 0000RR100"Instructions for continued<br />
a re-examination to determine ifthe complianc airworthiness (EWIS)" is included in<br />
theSupplement S21.TEC-0356 Issue 1 or<br />
later approv<br />
10039812 STC TWENTY ONE LIMITED REV. 1 B737 Activation of a Controller-Pilot Data-Link 1. This CPDLC installation have to be used Prior to installation of this STC it must be 29.05.2<strong>01</strong>2<br />
Communications [CPDLC]capability on only during the cruise flightphase above FL determined that theinterrelationship<br />
Spectralux "D-LINK" ACARS VDL Mode 2 285.2.This CPDLC installation have to be used between this modification and any other<br />
transceiver.<br />
only for non-time criticalmessages.<br />
previouslyinstalled modification and / or<br />
repair will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 425/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong><strong>04</strong>93 STC TWENTY ONE LIMITED CL-600-2A12 Introduction of Swift Broadband none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
06.07.2<strong>01</strong>2<br />
10<strong>04</strong>0691 STC TWENTY ONE LIMITED PA-31 Provisions for the installation of a Sensor Turret With a sensor turret installed, flight into known<br />
or forecast icingconditions is<br />
prohibited.Limitations as defined in AFMS<br />
S21.FMS-0091 Issue 1The installation and<br />
subsequent operation of a sensor turret<br />
requires aseparate approval.<br />
Prior to installation of this modification it 19.07.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>1363 STC TWENTY ONE LIMITED B757-200/-200PF/-300 Introduction of Antenna Mounting Provision None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.09.2<strong>01</strong>2<br />
10<strong>04</strong>1598 STC TWENTY ONE LIMITED BOEING 767-200/-300 Introduction of Iridium Antenna. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.10.2<strong>01</strong>2<br />
10<strong>01</strong>5317 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.00244 FAA STC SA5321SW-D BOEING 767-300ER Reconfiguration of passenger cabin interior 1. Subject to compliance with the provisions<br />
from 2<strong>04</strong> passengers to 250 passengers in of Part 21 Subpart E, this STC and associated<br />
accordance with DER Services Inc. Master data shall remain valid until surrendered,<br />
Document List (MDL) Report No. MDL-A20<strong>04</strong>- withdrawn or otherwise terminated.2. If<br />
026-1 dated 15 June 20<strong>04</strong>, or later <strong>EASA</strong> transfer of this Certificate is requested under<br />
approved revisions<br />
Part 21A.116, the STC will<br />
10<strong>01</strong>5320 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.00268 REV. 1 FAA STC SA09290AC-D PIPER PA-32-260<br />
PIPER PA-32-300<br />
10<strong>01</strong>5321 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.00269 REV. 2 FAA STC SA8906SW-D PA-28-151, PA-28-161<br />
PA-28-181, PA-28-2<strong>01</strong>T<br />
PA-28-236<br />
10<strong>01</strong>5326 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.00281 REV. 1 FAA STC SA09386AC-D GRUMMAN AA-5<br />
GRUMMAN AA-5A<br />
GRUMMAN AA-5B<br />
Installation of S-TEC System 20/30 Single Axis 1. Subject to compliance with the provisions<br />
and Two Axis Automatic Flight Guidance of Part 21 Subpart E, this STC and associated<br />
Systems Model ST-733-20/30 SA09290AC-D. data shall remain valid until surrended,<br />
withdrawn or otherwise terminated2. If<br />
transfer of this Certificate is requested under<br />
Part 21A.116 the STC will be re<br />
Installation of S-TEC System 55/55X Two Axis<br />
Automatic Flight GuidanceSystem Model ST-<br />
568.<br />
Installation of S-TEC System 30 Single and<br />
Two Axis Automatic Flight Guidance System,<br />
Model ST-840-30, FAA STC SA09386AC-D<br />
14.10.20<strong>04</strong><br />
10.09.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
14.09.2<strong>01</strong>0<br />
1. Subject to compliance with the provisions of<br />
Part 21 Subpart E, this STC and associated<br />
data shall remain valid until surrendered,<br />
withdrawn or otherwise terminated.2. If transfer<br />
of this certificate is requested under Part<br />
21A.116, the STC will be reis<br />
10<strong>01</strong>5327 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.00289 FAA STC SA09264AC-D CESSNA F182-Q Installation of S-TEC System 30 Two Axis 1. <strong>EASA</strong> Approved Pilot's Operating<br />
Automatic Flight Guidance System, Model ST- Handbook and/or Airplane Flight Manual<br />
718/30, according to Bulletin No. 818, dated Supplement, dated October 21, 20<strong>04</strong> is<br />
July 30, 1997 and Master Drawing List No. required for Reims-Cessna Model F182Q for S-<br />
921<strong>01</strong>6, dated July 30, 1997 or later FAA TEC System 30 or later <strong>EASA</strong> approved<br />
approved revisions of the above data (28 Vol revisions of the above supplement.2.<br />
Compatibility of<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 426/<strong>462</strong><br />
11.09.2008<br />
28.10.20<strong>04</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5362 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.00676 REV. 2 FAA STC SA09254AC-D PIPER PA-28-140<br />
Installation of S-Tec System 20/30 Single and 1. Limitation according FAA STC SA09254AC-<br />
11.09.2008<br />
PIPER PA-28-150<br />
Two Axis Automatic Flight Guidance Systems, D2. Compatibility of this modification with other<br />
PIPER PA-28-160<br />
Model ST-711-20/30According FAA-STC previously approved modifications must be<br />
PIPER PA-28-180<br />
SA09254AC-D<br />
determined by the installer3. This STC is<br />
PIPER PA-28-235<br />
approved only for the product configuration as<br />
defined in the approved design da<br />
10<strong>01</strong>5381 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>066 REV. 1 FAA STC SA8896SW-D CESSNA 210L<br />
CESSNA 210M<br />
CESSNA 210N<br />
CESSNA 210R<br />
CESSNA T210L<br />
CESSNA T210M<br />
CESSNA T210N<br />
CESSNA T210R<br />
10<strong>01</strong>5383 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>07 REV. 1 CESSNA 177<br />
CESSNA 177A<br />
CESSNA 177B<br />
10<strong>01</strong>5397 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>099 FAA STC SA09502AC-D AVIATION AIRCRAFT A-1<br />
AVIATION AIRCRAFT A-1A<br />
AVIATION AIRCRAFT A-1B<br />
Installation of S-TEC System 55/55X Two Axis 1. As defined in the Limitations and Conditions<br />
Automatic flight Guidance System, Model ST- section of FAA STC SA8896SW-D, latest<br />
566, according to Bulletin No 666, Rev 2 dated approved revision2. Prior to installation of this<br />
1-25-<strong>01</strong> or later approved revisions<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
andany other previously i<br />
Installation of S-TEC Sysytem 20/30 Single<br />
and Two-axis Automatic Flight Guidance<br />
Systems.<br />
Installation of S-TEC System 30 ALT Altitude<br />
Hold System, Model ST-881<br />
10<strong>01</strong>5419 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>142 REV. 1 FAA STC SA09130AC-D PILATUS PC 6 SERIES Installation of Meggitt Avionics S-TEC Autopilot<br />
55/55X<br />
1. Subject to compliance with the provisions<br />
of Part 21 Subpart E, this STC and associated<br />
data shall remain valid until surrendered,<br />
withdrawn or otherwise terminated.2. If<br />
transfer of this Certificate is requested under<br />
Part 21A.116, the STC will b<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
1. Limited to PC-6/B1-H2; PC-6/B2-H2; PC-<br />
6/B2-H4 and PC-6/B2-H4 when modified with<br />
underwing fuel tanks2. If stabilizer electricaltrim<br />
interrupt switch S<strong>04</strong>3 is installed, the<br />
optional trim wiring in accordance with detail<br />
"A" on S-TEC drawing No 99213 Rev<br />
10<strong>01</strong>5441 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>181 FAA STC SA09<strong>01</strong>8AC-D CESSNA A185F Installation of S-TEC System 55/55X Two Axis Cessna Model A185F & Cessna Model A185F<br />
Automatic Flight Guidance System, Model ST- when equipped with STC SA1441WE<br />
596. Bulletin No.696 Revision 3 dated February (Robertson STOL) or STC SA968CE (Horton<br />
2 20<strong>01</strong> & Master Drawing List No. 928<strong>01</strong> STOL) and/or STC SA2529WE (Internal Tip<br />
Revision C dated February 2 20<strong>01</strong> or later<br />
approved revision (28 volt system). S-TE<br />
Tanks)<br />
10<strong>01</strong>5442 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>182 FAA STC SA09195AC-D COMMANDER 112, 112B, 112TC, Installation of S-TEC System 55/55X wo Axis This STC is approved only for the product<br />
COMMANDER 112TCA, 114, Automatic Flight Guidance Ssytem. Model ST- configuration as defined in the approved design<br />
114A<br />
658, in accordance with FAA STC SA09195AC-data<br />
referred to in the paragraph "Description".<br />
D.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5455 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>2<strong>01</strong> FAA STC SA09283AC-D NAVION A (L-17B)<br />
Installation of S-TEC System 20/30 Single and 1. This STC is approved only for the product<br />
NAVION B<br />
Two Axis Automatic Flight Guidance System configuration as defined in the approved design<br />
NAVION G<br />
Model ST-724-20/30 in accordance with FAA data referred to in the paragraph "Description".<br />
NAVION H<br />
STC SA09283AC-D<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5478 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>232 REV. 1 FAA STC SA5112SW-D PIPER PA-30<br />
Installation of S-TEC System 60 Two Axis 1. This STC is also eligible on the concerned<br />
PIPER PA-39<br />
Automatic Flight Guidance System Model ST- model when modified per STC SA727WE. 2.<br />
127. FAA STC SA5112SW-D<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircra<br />
10<strong>01</strong>5555 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>452 REV. 1 FAA STC SA09147AC-D CESSNA 152<br />
CESSNA A152<br />
10<strong>01</strong>5556 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>453 REV. 1 FAA STC SA09148AC-D CESSNA F152<br />
CESSNA FA-152<br />
Installation of S-TEC System 40/50 Single and<br />
Two Axis Automatic Flight Guidance System,<br />
Model ST-628, according to Bulletin No 728,<br />
dated 3-29-96 or later approved revisions<br />
Installation of S-TEC System 40/50 Single and<br />
Two Axis Automatic Flight Guidance System,<br />
Model ST-628, according to Bulletin No 728,<br />
dated 3-29-96 or later approved revisions<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 427/<strong>462</strong><br />
09.09.2008<br />
10.09.2008<br />
<strong>01</strong>.03.2005<br />
10.09.2008<br />
25.07.2005<br />
28.<strong>04</strong>.2005<br />
30.05.2005<br />
09.09.2008<br />
10.09.2008<br />
10.09.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5557 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>454 REV. 1 FAA STC SA5302SW-D CESSNA 210 Installation of S-TEC System 40/50 Single and 1. As defined in the Limitations and Conditions<br />
09.09.2008<br />
Two Axis Automatic Flight Guidance System, section of FAA STC SA5302SW-D, latest<br />
Model ST-212-40/50, according to Bulletin No approved revision2. Prior to installation of this<br />
312, dated 3-21-88 or later approved revisions modification the installer must determine that<br />
the interrelationship between this modification<br />
andany other previously i<br />
10<strong>01</strong>5558 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>455 REV 1 FAA STC SA09628AC TWIN COMMANDER AIRCRAFT<br />
690C<br />
TWIN COMMANDER AIRCRAFT<br />
690D<br />
TWIN COMMANDER AIRCRAFT<br />
695<br />
TWIN COMMANDER AIRCRAFT<br />
10<strong>01</strong>5559 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>456 FAA STC SA5242SW-D<br />
695A<br />
AERMACCHI F 260 B<br />
AERMACCHI F 260 C<br />
AERMACCHI F 260 D<br />
Installation of S-TEC/Meggitt MAGIC <strong>01</strong>298-07-<br />
<strong>01</strong>-005 Digital Flight Control SystemFAA STC<br />
SA09628AC<br />
10<strong>01</strong>5588 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>499 FAA STC SA09239AC-D CESSNA F172-N Installation of S-TEC System 20/30 Single and<br />
tow Axis Automatic Flight Guidance Systems<br />
10<strong>01</strong>56<strong>04</strong> S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>540 REV. 1 FAA STC SA7209SW-D CESSNA 337D<br />
CESSNA 337E<br />
CESSNA 337F<br />
CESSNA 337G<br />
CESSNA 337H<br />
CESSNA P337H<br />
CESSNA T337D<br />
CESSNA T337E<br />
CESSNA T337F<br />
CESSNA T337G<br />
CESSNA T337H<br />
CESSNA T337H-SP<br />
10<strong>01</strong>5606 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>541 REV. 1 FAA STC SA7210SW-D REIMS AVIATION F-337E<br />
REIMS AVIATION F-337F<br />
REIMS AVIATION F-337G<br />
REIMS AVIATION F-337H<br />
REIMS AVIATION FT-337E<br />
REIMS AVIATION FT-337F<br />
REIMS AVIATION FT-337GP<br />
REIMS AVIATION FT-337HP<br />
10<strong>01</strong>5633 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>589 FAA STC SA7805SW-D PIPER PA-28R-180<br />
PIPER PA-28R-200<br />
PIPER PA-28R-2<strong>01</strong><br />
PIPER PA-28R-2<strong>01</strong>T<br />
10<strong>01</strong>5634 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>590 FAA STC SA7815SW-D PIPER PA-23<br />
PIPER PA-23-160<br />
10<strong>01</strong>5669 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>645 REV 1 FAA STC SA09214AC-D CESSNA 172R<br />
CESSNA 172S<br />
10<strong>01</strong>5783 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>839 FAA STC SA09522AC-D BEECH 95<br />
BEECH B95A<br />
BEECH D95A<br />
BEECH E95<br />
Airplane with S-TEC/Meggit <strong>01</strong>298-07-<strong>01</strong>-005<br />
Digital Flight Control System is prohibited from<br />
flight into known icing condition. STC<br />
SA<strong>01</strong>627CH, Meggit EFIS installation is<br />
required for this modification. Compatibility of<br />
this design with previously approved<br />
Installation of S-TEC System 40/50, Single and 1. Only eligible on model F260B when<br />
Two Axis Automatic Flight Guidance Systems equipped with Aileron Assemblies P/N SF260-<br />
Model ST-235-40/50FAA STC SA5242SW-D 02-05-<strong>01</strong> (L.H.) and P/N SF260-02-05-02<br />
(R.H.)2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragrap<br />
Installation of S-TEC System 60 Two Axis<br />
Automatic Flight Guidance System with<br />
Optional Autotrim System, Model ST-314,<br />
according toBulletin No 414, dated 3-14-90 or<br />
later approved revision<br />
Installation of S-TEC System 60 Two Axis<br />
Automatic Flight Guidance System with<br />
Optional Autotrim System, Model ST-314,<br />
according toBulletin No 414, dated 3-14-90 or<br />
later approved revisions.<br />
Installation of S-TEC Manual Trim System<br />
(field installation) i.a.w. MDL 92549 Rev A<br />
STC SA7815SW-D, Installation of S-TEC<br />
System 60 Two Axis Automatic Flight<br />
Guidance System, Model ST-486<br />
Installation of S-TEC System 30 ALT Altitude<br />
Hold Sytem, Model ST-673, according to<br />
Bulletin No 773, Revision 4 dated 9-22-98 or<br />
later approved revision<br />
Also eligible on the above models when<br />
modified by 180 HP Engine conversion. <strong>EASA</strong><br />
approval of this STC must be ckecked.This<br />
STC is issued as result of the validation of the<br />
S-TEC Corporation STC No SA09239AC-D<br />
approved by the FAA on June 26, 1997.<br />
1. Eligble when above models are modified per<br />
FAA STC SA1627WE (Robertson STOL<br />
Conversion)2. Eligible when the above models<br />
are modified per FAA STC SA937CE (Horton<br />
STOL Craft Conversion)3. It is the operator's<br />
responsibility to ensure the above mentioned<br />
1. Eligible when the above models are<br />
modified per FAA STC SA1627WE<br />
(Robertson STOL Conversion).2. Eligible<br />
when the above models are modified per FAA<br />
STC SA937CE (Horten STOL Craft<br />
Conversion).3. It is the operators<br />
responsibility to ensure the a<br />
Limited to Installations without the trim monitor<br />
system<br />
1. Eligible on models modified per STC<br />
SA5<strong>04</strong>WE and/or STC SA824WE.2. Eligible<br />
on models modified per STC SA461SW,<br />
SA636SW, SA671SW and 899SW3.<br />
Instructions for continued airworthiness acc.<br />
Doc. P/n 81431 5. Maintenance Instructions 2.-<br />
4. must be performed<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
Installation of S-TEC System 55/55X Two Axis FAA/DAS Approved Pilot’s Operating<br />
Automatic Flight Guidance System, Model ST- Handbook and / or FAA Approved Airplane<br />
898.<br />
Flight Manual Supplement P/N 892113 dated 2-<br />
18-02 or later approved revision, is required for<br />
Beech models 95 and B95.FAA/DAS<br />
Approved Pilot’s Operating Handbook and / or<br />
FAA Approv<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 428/<strong>462</strong><br />
17.10.2006<br />
13.03.2006<br />
<strong>04</strong>.08.2005<br />
12.09.2008<br />
09.09.2008<br />
30.<strong>01</strong>.2006<br />
17.02.2006<br />
10.09.2008<br />
17.10.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5784 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>840 FAA STC SA8908SW-D CESSNA 335<br />
Installation of S-TEC System 55/55X Two Axis Eligible to be used on aircraft 340 and 340A<br />
26.09.2006<br />
CESSNA 340<br />
Automatic Flight Guidance System, Model ST- when modified per FAA STC SE4327SW<br />
CESSNA 340A<br />
575<br />
(RAM Engine Conversion only if this STC has<br />
been <strong>EASA</strong> approved.<br />
10<strong>01</strong>5786 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>842 REV 1 FAA STC SA09000AC-D VULCANAIR P68 B<br />
Installation of S-TEC System 55 two axis 1. Also eligible on the above models with<br />
10.09.2008<br />
VULCANAIR P68 C<br />
automatic flight guidance system, model ST- Camera Port2. This STC is approved only for<br />
VULCANAIR P68 C-TC<br />
585, in accordance with FAA STC SA the product configuration as defined in the<br />
09000AC-D<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations<br />
10<strong>01</strong>58<strong>01</strong> S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>866 FAA STC SA09527AC-D TWIN COMMANDER AIRCRAFT Installation of S-TEC Digital Flight Control If airplane is modified by STC SA236CH<br />
20.10.2006<br />
690<br />
System (autopilot) Part Numbers <strong>01</strong>284 or (Garrett TPE 331-10T-515 engines), STC<br />
TWIN COMMANDER AIRCRAFT <strong>01</strong>298-<strong>01</strong>-<strong>01</strong>-002 or <strong>01</strong>-3<strong>04</strong>-<strong>04</strong>-<strong>01</strong>-008, SA3861NM ("Q" tip propellers), or STC<br />
690A<br />
(MAGIC 2100) (ST-902) in Twin Commander SA1359GL (winglets), installer must check<br />
TWIN COMMANDER AIRCRAFT 690, 690A and 690B, also if modified by any of availability of <strong>EASA</strong>-approval.<br />
690B<br />
the following STC’s: STC SA236CH (Garrett<br />
TPE<br />
10<strong>01</strong>5802 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>867 REV. 1 FAA STC SA09007AC-D CESSNA 182P<br />
Installation of S-TEC System 55/55X Two Axis This STC is approved only for the product<br />
10.09.2008<br />
CESSNA 182Q<br />
Automatic Flight Guidance System Model ST- configuration as defined in the approved design<br />
587.<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>58<strong>04</strong> S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>869 FAA STC SA09008AC-D CESSNA F182-P<br />
Installation of S-TEC System 55/55X Two Axis<br />
26.<strong>04</strong>.2006<br />
CESSNA F182-Q<br />
Automatic Flight Guidance System Model ST-<br />
587.<br />
10<strong>01</strong>5827 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>916 FAA STC SA5125SW-D PIPER PA-28R-180<br />
Installation of S-TEC System 60 Two Axis 1. FAA Approved Supplement to Pilot’s<br />
11.10.2006<br />
PIPER PA-28R-200<br />
Automatic Flight Guidance System, Model ST- Operating Handbook and / or FAA Approved<br />
PIPER PA-28R-2<strong>01</strong><br />
137, with Optional Autotrim System.<br />
Airplane Flight Manual, P/N 89176-1, dated 06-<br />
PIPER PA-28R-2<strong>01</strong>T<br />
21-90,or later approved revision, is required for<br />
Piper Models PA-28R-2<strong>01</strong> and PA-28R-<br />
2<strong>01</strong>T.2. FAA Approved Supplement to Pilot’s<br />
Ope<br />
10<strong>01</strong>59<strong>01</strong> S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02027 FAA STC SA9232AC-D CESSNA 210G<br />
Installation of S-TEC System 20/30 Single and 1. Also eligible on Models T210G, T210H and<br />
27.06.2006<br />
CESSNA 210H<br />
Two Axis Automatic Flight Guidance System, T210J when modified per FAA STC<br />
CESSNA 210J<br />
Model ST-687-20/30<br />
SA2689SW (RAM Modification)2. FAA/DAS<br />
CESSNA T210G<br />
Approved Suppllemental Flight Maual, P/N<br />
CESSNA T210J<br />
891412, dated 30 May 1997, is required for<br />
Cessna Models 210G, T210G, 210H, T210H,<br />
210J and T210J and<br />
10<strong>01</strong>5902 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02028 FAA STC SA09237AC-D CESSNA 172M<br />
Installation of S-TEC System 20/30 Single and 1) Also eligible on the above models when<br />
26.06.2006<br />
CESSNA 172N<br />
Two Axis Automatic Flight Guidance Systems, modified by 180 H.P. Engine Conversion.2)<br />
Model ST-674-20/30<br />
FAA/DAS Approved Supplemental Flight<br />
Manual, P/N 891423, dated 16 June 1997 is<br />
required for S-TEC System 20 for Cessna<br />
Model 172M and the above model when<br />
modified by 180 H<br />
10<strong>01</strong>5905 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02031 FAA STC SA09313AC-D BEECH A35<br />
Installation of S-TEC System 20/30 Single and Also eligible on Model 35 when modified per<br />
12.06.2006<br />
BEECH B35<br />
Two Axis Automatic Flight Guidance Systems, STC SA1-460 (Auxiliary Wing Tip Fuel<br />
BEECH C35<br />
Model ST-757-20/30<br />
Tanks).FAA/DAS approved supplemental flight<br />
BEECH D35<br />
manual, P/N 89160, dated 12-05-97 is required<br />
BEECH E35<br />
for Beech model 35 and this model when<br />
BEECH F35<br />
modified per STC SA1-460 (Auxiliary Wing Tip<br />
BEECH G35<br />
F<br />
10<strong>01</strong>5922 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02055 FAA STC SA09009AC-D CESSNA 182E<br />
Installation of S-TEC System 55/55X Two Axis FAA/DAS Approved Supplemental Flight<br />
19.10.2006<br />
CESSNA 182F<br />
Automatic Flight Guidance System, Model ST- Manual, Part No. 891174, Rev. 2, dated 6-11-<br />
CESSNA 182G<br />
588 in Cessna 182E, 182F, 182G, 182H, <strong>01</strong>, or later approved revisions, is required for<br />
CESSNA 182H<br />
182J,182K, 182L, 182M, and 182N, also when Cessna Models 182E, 182F, and<br />
CESSNA 182J<br />
modified per STC SA1382WE (Robertson 182G.FAA/DAS Approved Supplemental Flight<br />
CESSNA 182K<br />
STOL)<br />
Manual, Part No. 891175, Rev. 2, dated 6-11-<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
<strong>01</strong>, or lat<br />
10<strong>01</strong>5927 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02063 REV. 1 FAA STC SA7199SW-D BEECH 100<br />
Installation of S-TEC Yaw Damper System, 1. Also eligible on Models 100 and B1000<br />
17.10.2006<br />
BEECH A100<br />
Model ST-302<br />
when modified per STC SA3823NM (Lower Aft<br />
BEECH B100<br />
Fuselage Strakes).2. Also eligible on Model<br />
A1000 when modified per STC SA3828NM<br />
(Lower Aft Fuselage Strakes) with or without<br />
STC SA16779SO (750 S.H.P. Engines).3.<br />
Flight Ma<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 429/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5928 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02064 REV. 1 FAA STC SA7198W-D BEECH 100<br />
Installation of S-TEC Systems 65 Two Axis 1. Also eligible on Models 100, A100 and<br />
17.10.2006<br />
BEECH A100<br />
Automatic Flight Guidance System, Model ST- B1000 when modified per STC SA3828NM<br />
BEECH B100<br />
3<strong>01</strong><br />
(Lower Aft Fuselage Strakes).2. Also eligible<br />
on Model A100 when modified per STC<br />
SA1679SO (750 S.H.P. Engines).3. Airplane<br />
Flight Manual Supplement, P/N 89827S, dated<br />
9-29-89 is<br />
10<strong>01</strong>5996 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02152 FAA STC SA09124AC-D PIPER PA-60-6<strong>01</strong>P<br />
Installation of S-TEC 55/55X two axis 1. According to AFMS, Section 2 Operating<br />
29.08.2006<br />
PIPER PA-60-602P<br />
automatic flight control system in Aerostar Limitation2. Instructions for continued<br />
models<br />
airworthiness acc. Doc. P/N 81319 Rev. 23.<br />
Maintenance Instructions 2.-4. must be<br />
performed every 100 flight hours or once every<br />
calender year, whichever comes first<br />
10<strong>01</strong>6052 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02224 FAA STC SA09262AC-D CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA 182T<br />
Installation of S-TEC System 20/30 Single and<br />
Two Axis Automatic Flight Guidance System,<br />
Model ST-718-20/30 in Cessna 182Q, 182R<br />
and T182, also when modified per STC<br />
SA1382WE (Robertson STOL)<br />
For 182Q the maximum aft c.g. is limited to<br />
46.0 inches aft of datum when autopilot is<br />
installedInstaller must check availability of<br />
<strong>EASA</strong>-approval for Robertson STOL STC No.<br />
when aeroplane is modified per that STC<br />
10<strong>01</strong>6053 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02225 FAA STC SA09218AC-D GRUMMAN GA-7 Installation of S-TEC System 55/55X Two Axis --<br />
Automatic Flight Guidance System, Model ST-<br />
661 in Grumman American GA-7<br />
14.12.2006<br />
10<strong>01</strong>6054 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02226 FAA STC SA09316AC-D CESSNA R182<br />
Installation of S-TEC System 20/30 Single and This STC is approved only for the product<br />
18.12.2006<br />
CESSNA TR182<br />
Two Axis Automatic Flight Guidance System, configuration as defined in the approved design<br />
Model ST-759-20/30 in Cessna R182, and data referred to in the paragraph "Description".<br />
TR182.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>6080 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02264 FAA STC SA092<strong>01</strong>AC-D CESSNA 172R<br />
Installation of S-TEC System 55/55X Two Axis This STC is approved only for the product<br />
16.<strong>01</strong>.2007<br />
CESSNA 172S<br />
Automatic Flight Guidance System, Model ST- configuration as defined in the approved design<br />
563 in Cessna 172R and 172S<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
10<strong>01</strong>6103 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02293 FAA STC SA09160AC-D PIPER PA-32-260<br />
PIPER PA-32-300<br />
PIPER PA-32R-300<br />
10<strong>01</strong>6146 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02347 FAA STC SA09397CA-D PIPER PA-31<br />
PIPER PA-31-300<br />
PIPER PA-31-325<br />
PIPER PA-31-350<br />
Installation of S-TEC System 55/55X Two Axis<br />
Automatic Flight Guidance System, Model ST-<br />
640<br />
Installation of S-TEC System 65 Two Axis<br />
Automatic Flight Guidance System with<br />
Autotrim, Model ST-849, and with Optional<br />
Flight Director/Steering Horizon.<br />
10<strong>01</strong>6175 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02403 FAA STC SA09139AC-D PIPER PA-44-180 Installation of S-TEC Manual Electric Trim<br />
System, Model ST-619, in above mentioned<br />
airplane Type / Variant<br />
10<strong>01</strong>6194 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02431 FAA STC SA8886SW-D CESSNA 206<br />
CESSNA P206<br />
CESSNA P206A<br />
CESSNA P206D<br />
CESSNA P206E<br />
CESSNA TP206C<br />
CESSNA TP206D<br />
CESSNA TU206B<br />
CESSNA TU206C<br />
CESSNA TU206D<br />
CESSNA TU206E<br />
CESSNA TU206G<br />
CESSNA U206<br />
CESSNA U206B<br />
CESSNA U206C<br />
CESSNA U206D<br />
CESSNA U206E<br />
CESSNA U206F<br />
CESSNA U206G<br />
This STC is also eligible on:- PA-31 and PA-<br />
31-300 when modified per STC SA970SO,-<br />
PA-31-325 when modified per STC<br />
SA00<strong>04</strong>8SE,- PA-31-350 when modified per<br />
STC SA1151SO and / or any of STC<br />
SA5796NW, STC SA0<strong>01</strong>92SE, STC<br />
SA00039SE, STC SA0<strong>01</strong>26SE.I<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
Installation of S-TEC System 55/55X Two Axis This STC is also eligible on variants 206, P206,<br />
Automatic Flight Guidance System, Model ST- U206, P206A, TP206A, U206A, TU206A,<br />
556 in above mentioned airplane Types / P206B, TP206B, U206B, TU206B, P206C,<br />
Variants, also when modified per STC as listed TP206C, U206C, TU206C, P206D, TP206D,<br />
in 3.5 (Limitations and Conditions)<br />
U206D, TU206D, P206E, TP206E, U206E,<br />
TU206E, U206F, and TU206F when converted<br />
to 28 Volt electri<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 430/<strong>462</strong><br />
14.12.2006<br />
28.02.2007<br />
23.02.2007<br />
15.06.2007<br />
05.07.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6196 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02434 FAA STC SA09352AC-D Installation of S-TEC System, Model 20/30 This STC is eligible on variants M-5-210C, M-5-<br />
03.07.2007<br />
Single and Two Axis Automatic Flight Guidance 235C, M-6-235, MX-7-180, M-7-235, M-7-<br />
Systems, Model ST-810<br />
235A, M-7-235B, M-7-235C and MX-7-235 in<br />
landplane, floatplane, or amphibian<br />
configuration.This STC is eligible on variants<br />
MX-7-180A, MX-7-180B, MX-7-180C, MXT-7-<br />
180, MXT<br />
10<strong>01</strong>6203 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02445 FAA STC SA09287AC-D PIPER 31 AND SERIES<br />
Installation of S-TEC System, Model 20/30 Prior to installation of this modification the<br />
26.07.2007<br />
PIPER PA-28R-180<br />
Single and Two Axis Automatic Flight Guidance installer must determine that the<br />
PIPER PA-28R-200<br />
Systems, Model ST-729<br />
interrelationship between this modification and<br />
PIPER PA-28R-2<strong>01</strong>T<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>6278 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02567 FAA STC SA09251AC-D PIPER PA-28-161<br />
PIPER PA-28-181<br />
PIPER PA-28-236<br />
10<strong>01</strong>6317 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02623 REV. 1 FAA STC SA090<strong>01</strong>AC-D CESSNA 310I<br />
CESSNA 310J<br />
CESSNA 310K<br />
CESSNA 310L<br />
CESSNA 310N<br />
CESSNA 310P<br />
CESSNA 310Q<br />
CESSNA 310R<br />
CESSNA T310P<br />
CESSNA T310Q<br />
CESSNA T310R<br />
10<strong>01</strong>6405 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02734 FAA STC SA09298AC-D PIPER PA-31<br />
PIPER PA-31-325<br />
10<strong>01</strong>6425 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02763 FAA STC SA09132AC-D CESSNA 172M<br />
CESSNA 172N<br />
10<strong>01</strong>6442 S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.02787 FAA STC SA09233AC-D PIPER PA-28-161<br />
PIPER PA-28-181<br />
PIPER PA-28-236<br />
10<strong>01</strong>66<strong>04</strong> S-TEC CORPORATION <strong>EASA</strong>.IM.A.S.03<strong>01</strong>9 FAA STC SA09257AC-D PIPER PA-28-140<br />
PIPER PA-28-150<br />
PIPER PA-28-160<br />
PIPER PA-28-180<br />
PIPER PA-28-235<br />
10028097 S-TEC CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03269<br />
FAA STC SA5357SW-D PA-28-151, PA-28-161,<br />
PA-28-181, PA-28-236,<br />
PA-28-2<strong>01</strong>T<br />
10028331 S-TEC CORPORATION FAA STC SA094<strong>01</strong>AC-D (ST-853) 4<strong>01</strong>, 4<strong>01</strong>A, 4<strong>01</strong>B<br />
402A, 402B, 402C<br />
Installation of S-TEC System 20/30 Single and<br />
Two Axis Automatic Flight Guidance Systems,<br />
Model ST-703-20/30.<br />
This STC is also eligible on: - PA-28-151<br />
when modified per STC SA2969SW (180 HP<br />
Engine Conversion)If airplane is modified per<br />
the above mentioned STC, installer must check<br />
availability of <strong>EASA</strong>-approval.<br />
Installation of S-TEC System 55/55X Two Axis This STC is also eligible on variants 310K,<br />
Automatic Flight Guidance System, Model ST- 310L, and 310N when modified per STC<br />
594, also when modified per FAA STC as SA412SO (300 H.P. Colemill Conversion).This<br />
listed in 3.5 (Limitations and Conditions). STC is also eligible on variants T310P, and<br />
T310Q when modified per STC SA2750SW<br />
(RAM Modification.Installer must check availab<br />
Installation of S-TEC SYSTEM 55/55X Two This STC is also eligible on Models PA-31<br />
Axis Automatic Flight Guidance System, Model when modified per STC SA970SO (350 hp<br />
ST-751, also when modified per FAA STC as Colemill Conversion)This STC is also eligible<br />
listed in 3.5 (Limitations and Conditions). on Model PA-31-325 when modified per STC<br />
SA00<strong>04</strong>8SE (Vortex Generators System).Prior<br />
to installation of this modification the insta<br />
Installation of S-TEC System 55/55X Two Axis Prior to installation of this modification the<br />
Automatic Flight Guidance System, Model ST- installer must determine that the<br />
612 in Cessna 172M and 172N.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of S-TEC System 30 ALT Altitude<br />
Hold System, Model ST 684 (28 Volt System)<br />
Installation of S-TEC System 30 ALT Altitude<br />
Hold System, Model ST-712 (14 Volt System)<br />
Installation of S-TEC Manual Electric Trim<br />
System, Model ST-156 (14 VoltSystem)<br />
Installation of S-TEC System 55/55X Two Axis<br />
Automatic Flight GuidanceSystem, Model ST-<br />
853 (28 Volt System)<br />
The approval holder shall fulfil the obligations<br />
of Part 21, Paragraph 21.A109<br />
1 Prior to installation of this modification the<br />
installer must verify the availability of <strong>EASA</strong><br />
approval for one or more mentioned STC(s)<br />
when the product is modified per that/those<br />
STC(s).1 Prior to installation of this<br />
modification the installer mu<br />
Compatibility of this modification with other<br />
previously approvedmodifications must be<br />
determined by the installer. The Approval of<br />
the installation of this system is not applicable<br />
tospecific aircraft having other previously<br />
approved modifications, unless<br />
Compatibility of this modification with other<br />
previously approvedmodifications must be<br />
determined by the installer.The Approval of the<br />
installation of this system is not applicable<br />
tospecific aircraft having other previously<br />
approved modifications, unlessi<br />
22.10.2007<br />
22.11.2007<br />
22.05.2008<br />
08.05.2008<br />
13.05.2008<br />
14.<strong>01</strong>.2009<br />
Prior to installation of this modification it <strong>01</strong>.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 17.12.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 431/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029937 S-TEC CORPORATION FAA STC SA09140AC-D 210, 210A, 210B, 210C Installation of S-TEC System 55/55X Two Axis None The installation of this modification by <strong>04</strong>.05.2<strong>01</strong>0<br />
Automatic Flight GuidanceSystem, Model ST-<br />
third persons is subject towritten<br />
621 (14 Volt System)<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
10032286 S-TEC CORPORATION FAA STC SA8910SW-D BEECH S35, V35, V35A AND Installation of S-TEC System 55/55X Two Axis This STC is also eligible on Beech models The installation of this modification by 22.10.2<strong>01</strong>0<br />
V35B<br />
Automatic Flight GuidanceSystem, Model ST- S35, V35, V35A, and V35B whenmodified by third persons is subject towritten<br />
577 (14 Volt System)<br />
STC SA1035WE (turbocharged engine) or permission of the approval holder and<br />
STC SA5223NM (turbonormalizing system) disposal of the approvedappropriate<br />
and any combination of the following STCs: documentation.Prior to installation of this<br />
STCSA09074SC (vortex generators), STC modification it must be determined<br />
SA4-1629 (tip<br />
thatthe interrelationship b<br />
10032336 S-TEC CORPORATION FAA STC SA09320AC-D CESSNA F182P, F182Q Installation of S-TEC System 20/30 Single and This STC is also eligible on Cessna models The installation of this modification by 28.10.2<strong>01</strong>0<br />
Two Axis Automatic FlightGuidance Systems, F182P and F182Q when modifiedby: 1. STC third persons is subject towritten<br />
Model ST-762-20/30 (14 Volt System) SA485SW (Wren conversion) and STC permission of the approval holder and<br />
SA3825SW (260 H.P. engineconversion) or 2. disposal of the approvedappropriate<br />
STC SA950CE (Horton STOL) and/or STC documentation.Prior to installation of this<br />
SA2285CE (Hortonflap gap seals) and STC modification it must be determined<br />
SA3825SW (260 H.P.<br />
thatthe interrelationship b<br />
10032443 S-TEC CORPORATION FAA STC SA7818SW-D 35-C33, F33C Installation of S-TEC System 40/50 Single and none Compatibility of this modification with 08.11.2<strong>01</strong>0<br />
Two Axis Automatic FlightGuidance Systems,<br />
other previously approvedmodifications<br />
Model ST-492-40/50 (28 Volt System)<br />
must be determined by the installer.Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previously<br />
10032444 S-TEC CORPORATION FAA STC SA7819SW-D 35-C33, F33C Installation of S-TEC Manual Electric Trim none Compatibility of this modification with 08.11.2<strong>01</strong>0<br />
System, Model ST-493 (28 VoltSystem)<br />
other previously approvedmodifications<br />
must be determined by the installer.Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previously<br />
10033463 S-TEC CORPORATION FAA STC SA84<strong>01</strong>SW-D TB9, TB10, TB20, TB21, TB200 Installation of S-TEC System 55/55X Two Axis Optional Autotrim System not eligible on If the holder agrees to permit another 24.<strong>01</strong>.2<strong>01</strong>1<br />
Automatic Flight GuidanceSystem, Model ST- Socata model TB 9, TB 10, andTB 200 (Group person to use this certificate toalter the<br />
547 (28 Volt System)<br />
Aerospatiale)<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
10033582 S-TEC CORPORATION FAA STC SA5210SW-D H35, J35, K35, M35, N35, P35 Installation of S-TEC 40/50 Single and Two None The installation of this modification by 28.<strong>01</strong>.2<strong>01</strong>1<br />
Axis Automatic FlightGuidance Systems, Model<br />
third persons is subject towritten<br />
ST-188-40/50 (14V - System)<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10033820 S-TEC CORPORATION FAA STC SA09285AC-D PA-31-350<br />
Installation of S-TEC 20/30 Single and Two This STC is also eligible on models PA-31 and The installation of this modification by 10.02.2<strong>01</strong>1<br />
PA-31, PA-31-300, PA-31-325 Axis Automatic FlightGuidance Systems, Model PA-31-300 when modifiedper FAA STC third persons is subject towritten<br />
ST-727-20/30 (28V - System)<br />
SA970SO (350 H.P. Colemill Conversion) This permission of the approval holder and<br />
STC is also eligible on model PA-31-325 when disposal of the approvedappropriate<br />
modified per FAA STCSA00<strong>04</strong>8SE (Vortex documentation. Prior to installation of this<br />
Generator System) This STC is also eligible on modification it must be determined<br />
m<br />
thatthe interrelationship<br />
10038328 S-TEC CORPORATION FAA STC SA8392SW-D PA-32-3<strong>01</strong>, PA-32-3<strong>01</strong>T<br />
Installation of S-TEC system 55/55X Two Axis Installer must check availability of <strong>EASA</strong>- The installation of this modification by 07.02.2<strong>01</strong>2<br />
PA-32R-3<strong>01</strong>, PA-32R-3<strong>01</strong>T Automatic Flight GuidanceSystems, Model ST- approval for one or morereferenced STC when third persons is subject towritten<br />
534 (14V - System).<br />
airplane is modified per that / those STC(s) permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10038425 S-TEC CORPORATION FAA STC SA09307AC-D 4<strong>01</strong>/4<strong>01</strong>A/4<strong>01</strong>B/402A/402B/402C Installation of S-TEC system 20/30 single and Installer must check availability of <strong>EASA</strong>- The installation of this modification by 15.02.2<strong>01</strong>2<br />
two axis Automatic FlightGuidance Systems. approval for one or morereferenced STC when third persons is subject towritten<br />
Installation Model ST-743 (28V - System) airplane is modified per that / those STC(s) permission of the approval holder and<br />
according tobulletin N. 843.<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 432/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10039195 S-TEC CORPORATION REV. 1 FAA STC SR02344LA BELL 407 Installation of HeliSAS stability augmentation VFR only Prior to installation of this modification it 18.<strong>04</strong>.2<strong>01</strong>2<br />
system and autopilotValidation of FAA STC<br />
must be determined thatthe<br />
SR02344LA<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
10039237 S-TEC CORPORATION FAA STC NO. SA09350 AC-D BEECH 95/B95/B95A/D95A/E95 Installation of S-TEC system 20/30 single and Installer must check availability of <strong>EASA</strong>- The installation of this modification by<br />
two axis Automatic FlightGuidance Systems, approval for one or morereferenced STC when third persons is subject towritten<br />
model ST-808-20/30, according to bulletin N. airplane is modified per that / those STC(s). permission of the approval holder and<br />
908 rev.1dated <strong>01</strong>-Dec-2008 and with Master<br />
disposal of the approvedappropriate<br />
Drawing List N. 921083, Rev. A, dated<strong>01</strong>-Dec-<br />
documentation.Prior to installation of this<br />
2008 or later FAA approved revision<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10039264 S-TEC CORPORATION REV. 1 FAA STC SA09<strong>01</strong>0AC-D SEE <strong>EASA</strong> APPROVED MODEL Installation of S-TEC system 55/55X two axis Installer must check availability of <strong>EASA</strong>- The installation of this modification by 25.<strong>04</strong>.2<strong>01</strong>2<br />
LIST<br />
Automatic Flight GuidanceSystems, model ST- approval for one or morereferenced STC when third persons is subject towritten<br />
589, according to bulletin N. 689 rev.4 dated11- airplane is modified per that / those STC(s). permission of the approval holder and<br />
Jan-2<strong>01</strong>0 and with Master Drawing List N.<br />
disposal of the approvedappropriate<br />
92790, Rev. D, dated11-Jan-2<strong>01</strong>0 or later FAA<br />
documentation. Prior to installation of this<br />
approved revision (14V - System).<br />
modification it must be determined<br />
thatthe interrelationship<br />
10039317 S-TEC CORPORATION FAA STC SA8364SW-D 4<strong>01</strong>, 4<strong>01</strong>A, 4<strong>01</strong>B<br />
Installation of S-TEC system 40/50 single and Installer must check availability of <strong>EASA</strong>- The installation of this modification by 25.<strong>04</strong>.2<strong>01</strong>2<br />
402A, 402B, 402C<br />
two axis Automatic FlightGuidance Systems. approval for one or morereferenced STC when third persons is subject towritten<br />
Installation Model ST-505-40/50 (28V - airplane is modified per that / those STC(s) permission of the approval holder and<br />
System)according to bulletin N. 605 rev.6<br />
disposal of the approvedappropriate<br />
dated 21-Jan-2<strong>01</strong>0 and master drawinglist n.<br />
documentation.Prior to installation of this<br />
92582 rev. F, dated 21-Jan-2<strong>01</strong>0 or later<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10039903 S-TEC CORPORATION FAA STC SA09540 AC-D A99A, B99, C99 Installation of S-TEC system 30 two axis Installer must check availability of <strong>EASA</strong>- The installation of this modification by 31.05.2<strong>01</strong>2<br />
Automatic Flight GuidanceSystems (ST-923), approval for one or morereferenced STC when third persons is subject towritten<br />
in accordance with Master Data List No. ST- airplane is modified per that / those STC(s).If permission of the approval holder and<br />
923-L-00<strong>01</strong>,Revision A, dated 24-Aug-06 or the holder agrees to permit another person to holding and disposal ofthe approved<br />
later FAA approved revision (28V -System). use this certificate toalter the product, the appropriate documentation.Prior to<br />
holder shall give the other pe<br />
installation of this modification it must be<br />
determined thatthe interre<br />
10<strong>04</strong>0585 S-TEC CORPORATION FAA STC SR002346LA BELL 206B, 206L, 206L-1, Installation of HeliSAS stability augmentation VFR only Prior to installation of this modification it 17.07.2<strong>01</strong>2<br />
BELL 206L-3, 206L-4<br />
system and autopilot.Validation of FAA STC<br />
must be determined thatthe<br />
SR02346LA<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
10<strong>04</strong>0647 S-TEC CORPORATION REV. 1 FAA STC NO. SA7178SW-D 210K<br />
T210K<br />
10<strong>04</strong>1971 S-TEC CORPORATION FAA STC SR02345LA AS350B<br />
AS350B1<br />
AS350B2<br />
AS350B3<br />
AS350BA<br />
AS350D<br />
EC130B4<br />
10<strong>04</strong>2<strong>01</strong>3 S-TEC CORPORATION FAA STC NO. SA53<strong>01</strong>SW-D 58<br />
58A<br />
10<strong>04</strong>2477 S-TEC CORPORATION BN-2A-2, BN-2A-8<br />
BN-2A-20, BN-2A-26<br />
BN-2A-6<br />
BN-2B-20, BN-2B-26<br />
Installation of S-TEC manual Electric trim<br />
system, (ST-433), accordingto Bulletin n. 533,<br />
dated 11-May-1988 and Master Drawing List<br />
No. 92474,dated 11-May-1988 or later FAA<br />
approved revision (14V - System).<br />
Installation of HeliSAS stability augmentation<br />
system and autopilot.Validation of FAA STC<br />
SR02345LA.<br />
T210K is eligible also when modified per STC<br />
SA2689SW (RAMmodification). Installer must<br />
check availability of <strong>EASA</strong>-approval for one or<br />
morereferenced STC when airplane is<br />
modified per that / those STC(s). If the holder<br />
agrees to permit another person to us<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
17.07.2<strong>01</strong>2<br />
VFR only.<br />
thatthe interrelationship<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. If the<br />
29.10.2<strong>01</strong>2<br />
Installation of S-TEC system 40/50, model ST- FAA / DAS Approved Pilot's Operating The installation of this modification by 31.10.2<strong>01</strong>2<br />
224-40/50, according tobulletin n. 324 dated 22- Handbook and/or Airplane FlightManual third persons is subject towritten<br />
Sep-1983 and Master Drawing List No. Supplement No. 89350 dated 5-Apr-1984 is permission of the approval holder and<br />
92252,dated 22-Sep-1983 (28V - System). required for system 40.FAA / DAS Approved disposal of the approvedappropriate<br />
Pilot's Operating Handbook and/or Airplane documentation. Prior to installation of this<br />
FlightManual Supplement No. 89351 dated 5- modification it must be determined<br />
Apr-1984 is r<br />
thatthe interrelationship<br />
Installation of S-TEC System 55/55X Two-Axis Only applicable to Model BN-2A-6 when This SIC is approved only for the product 31.05.2005<br />
Automatic Flight GuidanceSystem Model modification NB/M/430 and NB/M/631are configuration as defined inthe approved<br />
ST572.<br />
installed.<br />
design data referred to in the paragraph<br />
"Description".Compatibility with other<br />
aircraft/engine configurations shall<br />
bedetermined by the installer. This<br />
certificate shall rem<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 433/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4400 STEINBEIS FLUGZEUG- UND<br />
<strong>EASA</strong>.A.S.<strong>01</strong>695 DG LS8-T LS8-th Hydraulic extension systemExchange of This STC is approved only for the product<br />
06.07.2006<br />
LEICHTBAU G<br />
the electric driven engine extension system to a configuration as defined in the approved design<br />
hand-driven hydraulic system<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10034286 STEINBEIS FLUGZEUG- UND<br />
P-<strong>EASA</strong>.A.S.03832 LS 6 & LS 6-A STC: "Winglet Retrofit" / "Nachrüstung mit None Prior to installation of this modification it 23.03.2<strong>01</strong>1<br />
LEICHTBAU G<br />
Winglets"<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10<strong>01</strong>5396 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>098 ST02993AT BOEING 747-400 Installation of SafTGIo Inc. Photoluminescent 1. The photoluminescent FPEEPMS is only<br />
floor proximity emergency escape path eligible for installation on aircraft model<br />
marking system (FPEEPMS) in accordance numbers with interior arrangements approved<br />
with SafTGIo MDL Report M39-2, rev. B dated in the SafTGIo MDL, incorporating SafTGIo<br />
October 11, 20<strong>04</strong> or later FAA-approved drawing SG-B747 rev B dated October 7, 20<strong>04</strong><br />
revision<br />
or later FAA-approved revision.2. El<br />
10<strong>01</strong>5428 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>161 FAA STC ST02691AT AIRBUS A300 MODEL B2<br />
AIRBUS A300 MODEL B4<br />
AIRBUS A310-200<br />
AIRBUS A310-300<br />
10<strong>01</strong>5429 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>163 FAA STC ST02664AT AIRBUS A340-200<br />
AIRBUS A340-300<br />
10<strong>01</strong>5430 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>164 REV. 1 FAA STC ST02529AT ATR 42-200/-300/-320/-500<br />
ATR 72-1<strong>01</strong>/-102/-2<strong>01</strong>/-202/-211<br />
ATR 72-212/-212A<br />
Installation of SafTGlo photoluminiscent floor<br />
proximity emergency escape path marking<br />
system (FPEEPMS). - Validation of FAA STC<br />
No. ST02691AT).<br />
Installation of SafTGlo photoluminescent floor<br />
proximity emergency escape path marking<br />
system (FPEEPMS) – Validation of FAA STC<br />
N° ST02664AT<br />
Installation of SafTGlo Photoluminescent Floor<br />
Proximity EmergencyEscape Path Marking<br />
System (PFPEEPMS).(Validation of FAA STC<br />
ST02529AT)The STC installs a<br />
photoluminescent aisle path marking<br />
system(PFPEEPMS).This revision <strong>01</strong> adds<br />
ATR 72 aircraft models in<br />
10<strong>01</strong>5431 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>165 FAA STC ST02637AT BOEING 717-200 Installation of SaftGlo Inc. Phtoluminescent<br />
floor proximity emergency escape path<br />
marking system (FPEEPMS)<br />
10<strong>01</strong>5432 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>166 FAA STC ST<strong>01</strong>641AT BOEING 727-100 SERIES<br />
BOEING 727-200 SERIES<br />
10<strong>01</strong>5433 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>168 FAA STC ST02221AT BOEING 757-200<br />
BOEING 757-300<br />
10<strong>01</strong>5434 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>169 FAA STC ST02521AT BOEING 767-200 SERIES<br />
BOEING 767-300 SERIES<br />
Installation of a phtoluminiscent Floor Proximity<br />
Emergency Escape Path Marking System<br />
according to Diversified Aviation Services Inc<br />
FAA STC No. ST<strong>01</strong>641AT.<br />
Installation of SafTGlo Inc. Phtoluminescent<br />
floor proximity emergency escape path<br />
marking system (FPEEPMS)<br />
Installation of SaftGlo Inc. Phtoluminescent<br />
floor proximity emergency escape path<br />
marking system (FPEEPMS)<br />
1. The approval of this STC is limited to the<br />
identified aircraft models with interior<br />
arrangements approved in the SafTGlo MDL<br />
No.L66-2 Revision D, dated 16 MAR 20<strong>04</strong>, for<br />
Airbus A300 incorporating SafTGlo Drawings<br />
SGA300 and for A310 incorporating SafTGlo<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.2. The approval<br />
16.03.2005<br />
06.09.2005<br />
16.11.2005<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.<strong>04</strong>.2<strong>01</strong>1<br />
Cabin and exit lightning levels must be<br />
measured for acceptability on each installation<br />
in accordance with STG Aerospace Report<br />
No.P51-12, Revision A dated November 13,<br />
2002 and P51-10, Revision I.R., dated August<br />
15, 2002 or later approved revisions<br />
Cabin and exit lighting levels must be<br />
measured for acceptability on each installation<br />
in accordance with STG Aerospace Report No.<br />
L21-12, Revision I.R. dated September 22,<br />
2000 an L21-10, Revision I.R., dated<br />
September 21, 2000 or later approved<br />
revisions<br />
Cabin and exit lighting levels must be<br />
measured for acceptability on each installation<br />
in accordance with STG Aerospace Report No.<br />
M40-12, Revision A dated October 11, 20<strong>01</strong><br />
and M40-10. Revision C, dated May 6. 2002 or<br />
later approved revisions<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 434/<strong>462</strong><br />
26.08.2005<br />
21.09.2005<br />
26.07.2005<br />
26.07.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5435 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>170 FAA STC ST02687AT BOMBARDIER CL-600-2B19 Installation of SaftGlo Inc. Phtoluminescent Cabin and exit lighting levels must be<br />
28.07.2005<br />
BOMBARDIER CL-600-2C10 floor proximity emergency escape path measured for acceptability on each installation<br />
marking system (FPEEPMS)<br />
in accordance with STG Aerospace Report No.<br />
M41-12, Revision A dated June 30, 2002 and<br />
M41-10, Revision I.R, dated June 5, 2003 or<br />
later approved revisions.<br />
10<strong>01</strong>5437 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>175 FAA STC ST02131AT DC 10-30 CF SERIES<br />
DC 10-30 SERIES<br />
DC-10-10 SERIES<br />
MD-11<br />
10<strong>01</strong>5438 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>176 FAA STC ST<strong>01</strong>893AT BOMBARDIER DHC-7-100<br />
BOMBARDIER DHC-7-102<br />
10<strong>01</strong>5439 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>179 FAA STC ST02406AT FOKKER F.28 MARK 0070<br />
FOKKER F.28 MARK <strong>01</strong>00<br />
FOKKER F.28 MARK 1000<br />
FOKKER F.28 MARK 2000<br />
FOKKER F.28 MARK 3000<br />
FOKKER F.28 MARK 4000<br />
10<strong>01</strong>6295 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.02592 REV. 2 FAA STC ST03465AT B737-300/-400/-500<br />
B737-700/-800/-900<br />
10<strong>01</strong>6490 STG AEROSPACE INC. <strong>EASA</strong>.IM.A.S.02846 FAA STC ST<strong>01</strong>829A BOEING 737-100<br />
BOEING 737-200<br />
BOEING 737-300<br />
BOEING 737-400<br />
BOEING 737-500<br />
BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-800<br />
BOEING 737-900<br />
Installation of SaftGlo Inc. Photo luminescent<br />
floor proximity emergency escape path<br />
marking system in accordance with FAA STC<br />
ST02131AT<br />
10028318 STG AEROSPACE INC. FAA TCDS T000<strong>01</strong>SE B777-200 Installation of SafTGlo, Inc photoluminescent<br />
floor proximity emergencyescape path marking<br />
system<br />
10028633 STG AEROSPACE INC. P-<br />
<strong>EASA</strong>.IM.A.S.03118<br />
REV. 2 FAA STC ST03629AT B767-200, -300 Installation of STG Aerospace PowerSmart<br />
Emergency Primary Power System(WEPPS).<br />
10028634 STG AEROSPACE INC. REV. 1 FAA STC ST03692AT B757-200 Installation of STG Aerospace PowerSmart<br />
Emergency Primary Power System(WEPPS).<br />
1. The Photoluminescent FPEEPM is only<br />
eligible for installation on aircraft model<br />
numbers with interior arrangements approved<br />
in the STG Aerospace document K17-2<br />
Reviosn C, dated February 7, 2003,<br />
incorporating STG Aerospace drawing SG-<br />
15.11.2005<br />
Installation of SaftGlo Inc. Phtoluminescent<br />
DC10 rev B ISNT DWG<br />
Cabin and exit lighting levels must be<br />
28.07.2005<br />
floor proximity emergency escape path measured for acceptability on each installation<br />
marking system (FPEEPMS)<br />
in accordance with DAS Report No. G34-12,<br />
Revision A dated April 16, 1999 and G34-10,<br />
Revision A, dated April 17, 1999 or later<br />
approved revisions.<br />
Installation of photo luminescent floor proximity 1. The Photoluminescent FPEEPM is only<br />
emergency escape path marking system FAA eligible for installation on aircraft model<br />
15.11.2005<br />
STC ST02406AT<br />
numbers with interior arrangements approved<br />
in the STG Aerospace document H61-2<br />
Reviosn F, dated October 4, 20<strong>04</strong>,<br />
incorporating STG Aerospace drawing SG-F28<br />
rev D, dated Aug<br />
Installation of an STG Aerospace PowerSmart None If non-rechargeable lithium batteries used 08.08.2<strong>01</strong>1<br />
Wireless Emergency PrimaryPower System<br />
in this installation are notTSO-C142 and<br />
(WEPPS) in accordance with STG Master<br />
DO-227 compliant, or if rechargeable<br />
Drawing List (MDL)No. 71430000<br />
batteries are used inthis installation,<br />
additional requirements may apply. Any<br />
change to theLithium chemistry of the<br />
battery is conside<br />
Installation of the SAFTGLO Non-electrical The photo luminescent Floor Proximity<br />
14.<strong>04</strong>.2008<br />
Photoluminescent Escape Path Marking Emergency Escape Path Marking System is<br />
System to include all 737 models.<br />
only eligible for installation on aircraft model<br />
numbers with interior arrangements approved<br />
in the SafTGlo MDL No. E74-2, Rev. I.R. for<br />
the B 737 incorporating SafTGlo Drawing S<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.12.2009<br />
None If the non-rechargeable lithium batteries<br />
used in this installation arenot TSO-C142<br />
and DO-227 compliant, or if rechargeable<br />
batteries are usedin this installation,<br />
additional requirements may apply. Any<br />
change tothe Lithium chemistry of the<br />
battery is con<br />
03.03.2<strong>01</strong>1<br />
None If the non-rechargeable lithium batteries<br />
used in this installation arenot TSO-C142<br />
and DO-227 compliant, or if rechargeable<br />
batteries are usedin this installation,<br />
additional requirements may apply. Any<br />
change tothe Lithium chemistry of the<br />
battery is con<br />
23.03.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 435/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10031520 STG AEROSPACE INC. REV. 1 FAA STC ST02311AT DHC-8-102, -103, -106, -2<strong>01</strong> Installation of SaftGlo Inc. Photoluminescent Cabin interior arrangement must be approved Prior to installation of this modification it 16.03.2<strong>01</strong>1<br />
DHC-8-202, -3<strong>01</strong>, -302, -4<strong>01</strong> floor proximity EscapePath Marking System in accordance with SaftGloMDL, Report must be determined thatthe<br />
DHC-8-402<br />
(PFEEPMS)<br />
Number M07-2, Rev. H, dated 1 August 2007 interrelationship between this modification<br />
incorporatingSaftGlo drawing SG-DHC8, Rev. and any other previouslyinstalled<br />
E, dated 1 August 2007.Electrically-lit door exit modification and/ or repair will introduce<br />
marker lighting levels and cabin lighti<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0330 STG AEROSPACE INC. REV. 1 FAA STC ST03684AT 777-200/300/300ER Validation of FAA STC #ST03684AT<br />
(Installation of SafTGloPhotoluminescent<br />
Escape Path Marking System)<br />
10039197 STRAIGHT FLIGHT, Inc. CESSNA 510 Modification of the aircraft interior to allow for<br />
two configurations:1) Observer configuration<br />
and2) back to the Type Certificated standard<br />
Executive configuration inaccordance with<br />
Straight Flight Master Drawing List Document<br />
No.4979-MDL-<strong>01</strong>, Revision B,<br />
10<strong>01</strong>5479 STRUCTURAL INTEGRITY<br />
ENGINEERING<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>233 SA6073NM BEECH 99<br />
BEECH 99A<br />
BEECH B99<br />
BEECH C99<br />
Structural Life Extension of Wing Spars<br />
according to FAA STC SA6073NM as<br />
amended on 30 December 1993.<br />
10033267 SUPERVAN SYSTEMS, LTD. REV. 1 FAA STC SA10841SC 208, 208B Installation of the Honeywell TPE331-12JR<br />
engine and HartzellHC-B4TN-5QL/LT10890-<br />
N(K) propeller and associated components<br />
inaccordance with FAA STC SA10841SC, last<br />
amended December 15, 2<strong>01</strong>0.<br />
10<strong>01</strong>4781 SWS CERTIFICATION SERVICES LTD <strong>EASA</strong>.A.S.02979 AIRBUS A320 SERIES<br />
BOEING 717<br />
BOEING 727<br />
BOEING 737<br />
BOEING 747<br />
BOEING 757<br />
BOEING 767<br />
BOEING DC-9<br />
EMBRAER ERJ 135 SERIES<br />
EMBRAER ERJ 145 SERIES<br />
MD-11<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.07.2<strong>01</strong>2<br />
According limitations section of AFMS. This<br />
approval is limited to theinstallation and use of<br />
a 40 Cubic Foot occupant Oxygen supply<br />
tankonly.<br />
According to FAA STC SA6073NM and as<br />
further defined below.Compliance with the<br />
Airworthiness Limitations contained in the<br />
above referenced documents extends the<br />
existing 20,000 flight hour Beech fatigue life<br />
limits for wing spars of Beechcraft 99, 99A,<br />
B99<br />
If the holder agrees to permit other person to<br />
use this certificate toalter the product, the<br />
holder shall give the other person<br />
writtenevidence of that permission.For Cessna<br />
208: This STC is limited to standard version<br />
(without cargopod) to serial numbers<br />
Installation of STG Aerospace SafTGlo As defined in SWS Certification Ltd. Design<br />
Photoluminiscent Bulkhead/ Divider Exit Signs. report 30<strong>01</strong>-DR-0<strong>01</strong>, Issue 1 or later <strong>EASA</strong><br />
approved issue.<br />
10<strong>01</strong>5139 SWS CERTIFICATION SERVICES LTD <strong>EASA</strong>.A.S.03495 BAE 146 STG Aerospace Wireless Emergency Primary<br />
Power System (WEPPS) Installation.<br />
10032329 SWS CERTIFICATION SERVICES LTD REV. 1 BOEING B747-300<br />
BOEING B747-400<br />
Installation of SaftGlo Inc. Photoluminescent<br />
Floor Proximity EmergencyEscape Path<br />
Marking System (FPEEPMS) in accordance<br />
with SWSCertification Services Design Report<br />
3<strong>04</strong>6-DR-<strong>01</strong> Rev. 2, dated 27 August2<strong>01</strong>0 or<br />
later approved revision.<br />
10<strong>04</strong>0318 SWS CERTIFICATION SERVICES LTD REV. 1 A340-312 This modification intends to:The proposed<br />
major change is to install the AmSafe Airbag<br />
System todemonstrate compliance to<br />
CS25.562(c)(5) when the Panasonic eX2<br />
seatbackmonitor is installed. The monitor is to<br />
be electrically integrated withthe rest of the P<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification it 17.<strong>04</strong>.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
02.<strong>01</strong>.2006<br />
Prior to installation of this modification it 10.<strong>01</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
19.06.2007<br />
08.12.2008<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.11.2<strong>01</strong>0<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.10.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 436/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0913 SWS CERTIFICATION SERVICES LTD REV. 1 B747-8 Installation of the Aeroloft(TM) Overhead No passenger allowed in the cabin. Prior to installation of this modification it 11.12.2<strong>01</strong>2<br />
Sleeping Compartmentimmediately forward of<br />
must be determined thatthe<br />
the Overhead Crew Rest. Two configurations<br />
interrelationship between this modification<br />
are certified:1. With lounge module2. Without<br />
and any other previouslyinstalled<br />
lounge module and with following<br />
modification and/ or repair will introduce<br />
peculiarities:2.1 Stair module is located aft to<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5622 TACA INTERNATIONAL AIRLINES <strong>EASA</strong>.IM.A.S.<strong>01</strong>574 - AIRBUS A320-233 Automatic ELT Provisions installlation and<br />
activation<br />
10<strong>01</strong>5623 TACA INTERNATIONAL AIRLINES <strong>EASA</strong>.IM.A.S.<strong>01</strong>575 - AIRBUS A320-233 Automatic ELT- Provisions installation and<br />
activation<br />
10<strong>01</strong>5624 TACA INTERNATIONAL AIRLINES <strong>EASA</strong>.IM.A.S.<strong>01</strong>576 A320-233 Equipment and furnishing - delivery<br />
configuration of passenger cabin - 180 pax<br />
10<strong>01</strong>5667 TACA INTERNATIONAL AIRLINES <strong>EASA</strong>.IM.A.S.<strong>01</strong>643 AIRBUS A320-233 Equipment and furnishing - Delivery<br />
configuration of passenger cabin - 180 pax<br />
10<strong>01</strong>5703 TACA INTERNATIONAL AIRLINES <strong>EASA</strong>.IM.A.S.<strong>01</strong>690 - AIRBUS A320-233 Autoflight - Activate FMGC Nav data base to<br />
400Kwords - Pin programming<br />
10032788 TALON AEROSPACE LLC FAA STC ST03574AT SEE <strong>EASA</strong> APPROVED MODEL Anti Collision Light installationThis STC installs<br />
LIST<br />
a new model of Anti Collision Light.<br />
10<strong>04</strong>2345 TAMARACK AEROSPACE GROUP, INC. FAA STC SA02216SE SR20/SR22 Removal of mechanical link between engine<br />
throttle control and propeller RPM control.<br />
Installation of a separate RPM control lever,<br />
linkagebetween Cirrus RPM cable/cam<br />
followers, center console to<br />
accommodatethree-lever configuration, new<br />
knobs for all lev<br />
10030951 TASS INC FAA STC ST00593SE-D B747-400 Active Noise Reduction Headset Installation<br />
Provisions in accordancewith BF Goodrich<br />
Master Drawing List D2000-396, sheet 1,<br />
Revision New,dated November 22, 2000 or<br />
later FAA/DAS approved revision.Validation of<br />
FAA STC ST00593SE-D<br />
10031609 TASS INC FAA STC ST00583SE-D B757-200 Installation of Passenger Accommodations -<br />
STC ST00583SE-D<br />
This STC is limited to A320 MSN 561 20.10.2005<br />
This STC is limited to A320-233 MSN 558 20.10.2005<br />
This STC is limited to the A320 MSN 561 26.05.2005<br />
This STC is Limited to the A320 MSN 558. 26.10.2005<br />
1. This STC is limited to the A320 MSN`s<br />
558 and 561<br />
<strong>04</strong>.11.2005<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>01</strong>.12.2<strong>01</strong>0<br />
SR20 serial numbers 1005 through 1885;<br />
SR22 serial numbers 0002 and subsequent<br />
without Garmin PerspectiveAvionics<br />
Installation; SR20 airplanes equipped with<br />
Hartzell BHC-J2YF-1BF/F7694<br />
propellerassemblies must have a placard<br />
installed reading "Avoid operat<br />
Prior to installation of this modification it 26.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None None 15.07.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.08.2<strong>01</strong>0<br />
10<strong>01</strong>4381 TATENHILL AVIATION Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>665 PILATUS PC-12/45 Substantiation of Garmin AT GPS400<br />
installation for IFR<br />
20.06.2006<br />
10<strong>01</strong>4412 TATENHILL AVIATION Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>711 CESSNA F182-Q Design data and equipment installation in order --<br />
to approve the aircraft for IFR.<br />
08.<strong>01</strong>.2007<br />
10<strong>01</strong>4909 TATENHILL AVIATION Ltd. <strong>EASA</strong>.A.S.03153 CESSNA 500 Approval of a Mode S EHS ATC System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10.07.2008<br />
10<strong>01</strong>4923 TATENHILL AVIATION Ltd. <strong>EASA</strong>.A.S.03170 CESSNA 500 Approval of a Mode S EHS ATC System. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10<strong>01</strong>5168 TATENHILL AVIATION Ltd. <strong>EASA</strong>.A.S.03538 CESSNA 525 Dual Garmin GPS/NAV/COM Upgrade. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 437/<strong>462</strong><br />
23.09.2008<br />
26.05.2008
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>7132 TATENHILL AVIATION Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>225 AGUSTA A-109 C Design Data for Compliance with UK CAA<br />
Generic requirement 4 by Installation of a<br />
battery Low Voltage Indicator<br />
07.<strong>04</strong>.2006<br />
10<strong>01</strong>7133 TATENHILL AVIATION Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>227 AGUSTA A-109 AII Approval of Low Voltage Warning Light and<br />
Associated Flight Manual Supplement<br />
Agusta A109AII Series 31.08.2006<br />
10<strong>01</strong>7208 TATENHILL AVIATION Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>360 AGUSTA A-109 AII Approval of replacement “TOT” gauges 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
06.03.2009<br />
10<strong>01</strong>7220 TATENHILL AVIATION Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>377 AGUSTA A-109 Dessign data compliance with Generic As per AFM Supplement TAL-TAD FMS 18<br />
26.07.2007<br />
Requirement No. 4.<br />
Revision A.<br />
10026831 TATENHILL AVIATION Ltd. P-<strong>EASA</strong>.A.S.3878 PA-24-400<br />
Approval of an Aspen EFD1000 Primary Flight STC approved for Piper PA24 series 1) Prior to installation of this modification 13.08.2009<br />
PA-24, PA-24-250, PA-24-260, Display (PFD)<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10026846 TATENHILL AVIATION Ltd. P-<strong>EASA</strong>.A.S.03879 F182-P, F182-Q, FR-182 Approval of an Aspen EFD1000 Primary Flight<br />
Display (PFD)<br />
10028330 TATENHILL AVIATION Ltd. P-<strong>EASA</strong>.A.S.03956 BEECH 200 Design data to provide European approval of<br />
FAA STC: SA5254NM<br />
10029450 TATENHILL AVIATION Ltd. M20, M20A, M20B, M20C, M20D Installation of Aspen EFD1000 Primary Flight<br />
M20E, M20F, M20G, M20J, M20K<br />
M20L, M20R, M20S, M20TN<br />
Display (PFD)<br />
10033913 TATENHILL AVIATION Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10034482 TATENHILL AVIATION Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10035157 TATENHILL AVIATION Ltd. 1. PA-44-180, PA-44-180T<br />
2. PA-34-220T<br />
3. PA-34-200, PA-34-200T<br />
Design Data for the Approval of a Honeywell<br />
KFD840 Primary FlightDisplay (PFD).<br />
Design Data for the Approval of a Honeywell<br />
KFD840 Primary FlightDisplay (PFD).<br />
Design data for the approval of a Honeywell<br />
KFD840 Primary FlightDisplay (PFD)<br />
STC approved for F182P, F182Q and FR182<br />
series types only<br />
1) Prior to installation of this modification 17.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
Serial number BB-877 only Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.12.2009<br />
This change is limited to the configuration of The installation of this modification by 25.03.2<strong>01</strong>0<br />
aircraft, equipment type,functions and software third persons is subject towritten<br />
versions as listed in <strong>EASA</strong> approved<br />
permission of the approval holder and<br />
DesignReport, Doc. No. TAD.02209, Revision disposal of the approvedappropriate<br />
B, dated 23-Mar-2<strong>01</strong>0<br />
documentation. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.02.2<strong>01</strong>1<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
07.<strong>04</strong>.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
30.05.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 438/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10036731 TATENHILL AVIATION Ltd. SEE <strong>EASA</strong> APPROVED MODEL Design Data for the approval of a Honeywell None. Prior to installation of this modification it <strong>04</strong>.10.2<strong>01</strong>1<br />
LIST<br />
KFD840 Primary FlightDisplay (PFD).<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039139 TATENHILL AVIATION Ltd. 1. PA-34-220T<br />
2. PA-34-200, PA-34-200T<br />
2. PA-34-220T<br />
3. PA-44-180, PA-44-180T<br />
Approval of a Transponder System in<br />
accordance with AMC 20-2<br />
10<strong>04</strong>1362 TC INTER-INFORMATICS A.S. B737-800 D27 Cabin layout reconfiguration This STC is to be installed only of the<br />
followings aircraft serialnumbers: 38<strong>01</strong>8;<br />
394<strong>04</strong>; 39394; 38025; 38027; 30295; 37076;<br />
37077; 30719and 35275.<br />
10<strong>01</strong>5625 TDG AEROSPACE INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>577 FAA STC SA6<strong>04</strong>2NM DC-9-81 (MD-81)<br />
DC-9-82 (CF6)<br />
DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
MD-11<br />
10<strong>01</strong>6121 TDG AEROSPACE INC <strong>EASA</strong>.IM.A.S.02314 REV. 1 FAA STC ST<strong>01</strong>950LA BOEING 757-200<br />
BOEING 757-300<br />
10<strong>01</strong>6450 TDG AEROSPACE INC <strong>EASA</strong>.IM.A.S.02796 FAA STC ST02076LA BOEING 737-600<br />
BOEING 737-700<br />
BOEING 737-700C<br />
BOEING 737-800<br />
BOEING 737-900<br />
Installation of NOFOD Overwing Anti-Ice<br />
System<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>2<br />
1. Flight Manual Supplement TDG Doc No E93-<br />
096 Rev D dated 27 September or later<br />
approved revision2. Instructions for Continued<br />
Airworthiness TDG Doc E93-109 Revision P<br />
dated 11 February 20033. This STC is<br />
approved only for the product configuration as<br />
def<br />
Universal Fault Interrupter (UFI) Installation The UFI is a Critical Design Control<br />
Configuration Limitation (CDCCL) item. Its<br />
operation and instructions for maintenance and<br />
inspection must be performed in accordance<br />
with the TDG Instructions for Continued<br />
Airworthiness (document 20-3200-00<strong>01</strong>, rev. D<br />
1<br />
Universal Fault Interrupter Installation Kit for<br />
B737NG.<br />
100326<strong>04</strong> TDG AEROSPACE INC FAA STC ST02285LA B767-200, -300, -300F Installation of Universal Fault Interrupter (UFI)<br />
for Centre Wing FuelTank Electrical Fault<br />
Protection.<br />
10<strong>01</strong>6729 TECH-TOOL PLASTICS, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>032 FAA STC NO SR03<strong>01</strong>6AT BELL 407 Installation of windows for Bell 407 Model<br />
Helicopters in accordance with:-the FAA STC<br />
SR03<strong>01</strong>6AT dated 7/1/2005.-Master Drawing<br />
List 407-1000-100, dated 23/2/20<strong>04</strong>.<br />
10030363 TECH-TOOL PLASTICS, Inc. FAA STC SR09127RC-D AS350 B, AS350 B1, AS350 B2<br />
AS350 B3, AS350 BA, AS350 D<br />
Installation of a Vertical Sliding Window in the<br />
Right and/or Left HandSliding DoorFAA STC<br />
SR09127RC-D<br />
10036624 TECH-TOOL PLASTICS, Inc. FAA STC SR03641AT EC 120 B Replace the existing Eurocopter EC120 B<br />
windows with Tech-Tool Plastics,Inc.<br />
replacement windows(Note: This approval<br />
constitutes the <strong>EASA</strong> validation of the FAA<br />
STCSR03641AT, Issued by the FAA on June<br />
30, 2<strong>01</strong>1)<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
If the aeroplane has supplemental (high flow)<br />
jettison pumps installed,the installation of this<br />
STC requires them to be deactivated. This<br />
STC approves accomplishment of the<br />
deactivation procedures for thesupplemental<br />
(high flow) jettison pumps (designator<br />
1. The compatibility of this design change<br />
with other previously approved modifications<br />
must be determined by the installer.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
Prior to installation of this STC it must be<br />
determined that theinterrelationship<br />
between this STC and any other<br />
previously installedmodification and / or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
11.09.2<strong>01</strong>2<br />
05.09.2005<br />
19.<strong>04</strong>.2007<br />
25.08.2008<br />
Prior to installation of this modification it 17.11.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
20.09.2005<br />
data referred to in the paragraph<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.06.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.09.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 439/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037086 TECH-TOOL PLASTICS, Inc. FAA STC SR03640AT EC130 B4 Installation of Replacement WindowsThis STC None. Eurocopter EC130 B4 Maintenance and 31.10.2<strong>01</strong>1<br />
is the validation of FAA STC SR03640AT<br />
Repair Manual is also required partof this<br />
STC and must be incorporated into the<br />
operator's maintenanceprogram.Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modif<br />
10037490 TECH-TOOL PLASTICS, Inc. FAA STC SR09133RC-D AS 355 E<br />
AS 355 F<br />
AS 355 F1<br />
AS 355 F2<br />
AS 355 N<br />
10038180 TECH-TOOL PLASTICS, Inc. FAA STC SH5822SW AS355E, AS355F, AS355F1<br />
AS355F2, AS355N<br />
10038186 TECH-TOOL PLASTICS, Inc. FAA STC SH5797SW AS350B, AS350B1, AS350B2<br />
AS350B3, AS350BA, AS350D<br />
Installation of a Vertical Sliding Window in the<br />
Right Hand or Left HandSliding Door in<br />
accordance with Drawing List 350A82-1750,<br />
Revision B,dated 08/25/00.<br />
Installation of Tech-Tool performed acrylic<br />
plastic windshield inaccordance with Tech-Tool<br />
Drawing List (Doc 35<strong>01</strong>-2023) No 1, Rev<br />
A,dated 08/28/09 (FAA STC SH5822SW)<br />
Installation of Tech-Tool performed acrylic<br />
plastic windshield inaccordance with Tech-Tool<br />
Drawing List (Doc 35<strong>01</strong>-2023) No 1, Rev<br />
A,dated 08/28/09 (FAA STC SH5797SW)<br />
Both configurations cannot be installed<br />
concurrently (Right Hand andLeft Hand).<br />
Prior to installation of this modification it 30.11.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>01</strong>.2<strong>01</strong>2<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.<strong>01</strong>.2<strong>01</strong>2<br />
10038761 TECH-TOOL PLASTICS, Inc. FAA STC SR09<strong>04</strong>6RC AS 350 B, BA, B1, B2, B3, D Installation of a reverse slide camera window None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.03.2<strong>01</strong>2<br />
10038762 TECH-TOOL PLASTICS, Inc. FAA STC SR09<strong>04</strong>5RC AS 355 E, F, F1, F2, N Installation of a reverse slide camera window None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
12.03.2<strong>01</strong>2<br />
10039763 TECH-TOOL PLASTICS, Inc. <strong>EASA</strong>.IM.R.S.<strong>01</strong>53 REV. 1 MBB-BK 117 A-1<br />
MBB-BK 117 A-3<br />
MBB-BK 117 A-4<br />
MBB-BK 117 B-1<br />
MBB-BK 117 B-2<br />
MBB-BK 117 C-1<br />
MBB-BK 117 C-2<br />
10039788 TECH-TOOL PLASTICS, Inc. REV. 1 FAA STC SH8755SW AS 355 E<br />
AS 355 F<br />
AS 355 F1<br />
AS 355 F2<br />
AS 355 N<br />
10039789 TECH-TOOL PLASTICS, Inc. FAA STC SH8754SW AS 350 B1<br />
AS 350 B2<br />
AS 350 B3<br />
AS 350 BA<br />
AS 350 D<br />
AS350 B<br />
Installation of Tech-Tool Plastics,<br />
Inc.Replacement Windows in EUROCOPTER<br />
MBB-BK 117 Installation of windows in<br />
accordance with Tech-Tool Plastics, Inc.Master<br />
Drawing List No. BK117-1000-100 i.a.w. FAA<br />
STC No. SR02867AT<br />
None. If the holder agrees to permit another<br />
person to use this certificate toalter the<br />
product, the holder shall give the other<br />
person writtenevidence of that<br />
permission.Prior to installation of this<br />
modification it must be determined<br />
22.05.2<strong>01</strong>2<br />
Installation of aft Cabin Comfort Windows none<br />
thatthe interrelationship<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
25.05.2<strong>01</strong>2<br />
Installation of aft Cabin Comfort Windows none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 440/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4414 TELAIR INTERNATIONAL AB <strong>EASA</strong>.A.S.<strong>01</strong>713 AIRBUS A319<br />
Installation of Sliding Carpet Loading System in N/A 13.02.2006<br />
AIRBUS A320<br />
Airbus A319/320/321 in accordance with Telair<br />
AIRBUS A321<br />
International AB Master Document List (MDL)<br />
10<strong>01</strong>6023 TELAIR INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02191 REV. 1 FAA STC ST00837 LA BOEING 747-400<br />
BOEING 747-400F<br />
Installation of a Cargo Handling System on the<br />
lower deck of the B747-400, -400F<br />
10<strong>01</strong>6031 TELAIR INTERNATIONAL INC. <strong>EASA</strong>.IM.A.S.02200 REV. 1 FAA STC ST0<strong>04</strong>59LA BOEING 747-400SF Installation of a Cargo Handling System on the<br />
main deck of the B747-400SF inaccordance<br />
with FAA approved Telair International Index<br />
List ER 193100 Rev. N/Cdated October 21,<br />
1997 or later approved revisions.Validation of<br />
FAA STC ST0<strong>04</strong>59LA<br />
10036235 TELAIR INTERNATIONAL INC. P-<br />
<strong>EASA</strong>.IM.A.S.03066<br />
10036236 TELAIR INTERNATIONAL INC. P-<br />
<strong>EASA</strong>.IM.A.S.03067<br />
REV. 1 FAA STC 02365LA B747-8F Lower Deck Cargo Handling System,<br />
Installation<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
1. The installation of this modification by third<br />
persons is subject to writtenpermission of the<br />
approval holder2. Prior to installation of this<br />
modification the installer must determine that<br />
theinterrelationship between this modification<br />
and any other pre<br />
12.<strong>01</strong>.2009<br />
11.12.2008<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.08.2<strong>01</strong>1<br />
REV. 1 FAA STC 02367LA B747-8F Main Deck Cargo Handling System, Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
26.08.2<strong>01</strong>1<br />
10036941 TELAIR INTERNATIONAL INC. REV. 1 FAA STC ST02367LA 747-8F Main Deck Cargo Handling System, Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
20.10.2<strong>01</strong>1<br />
10036942 TELAIR INTERNATIONAL INC. REV. 1 FAA STC ST02365LA 747-8F Lower Deck Cargo Handling System,<br />
Installation<br />
10038077 TELAIR INTERNATIONAL INC. FAA STC ST02365LA 747-8 Installation of a Lower Deck Cargo Handling<br />
System<br />
10<strong>01</strong>5896 TELEDYNE BATTERY PRODUCTS <strong>EASA</strong>.IM.A.S.02<strong>01</strong>6 FAA STC SA1<strong>01</strong>3SO BEECH B99<br />
BEECH C90<br />
BEECH E90<br />
BEECH F90<br />
Replace existing nickel-cadmium battery with<br />
Gill BB638/T series lead-acid battery<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
20.10.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
17.<strong>01</strong>.2<strong>01</strong>2<br />
1) Beech C90 Serial Numbers LJ590 and after,<br />
E90 Serial Numbers LW58 and after, F90<br />
Serial Numbers LA-2 and after, B99 Serial<br />
Numbers U146 and U148 through U164.2)<br />
FAA approved Airplane Flight Manual<br />
Supplement, dated August 3, 1978, (C90, E90,<br />
B99), or Ja<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 441/<strong>462</strong><br />
22.05.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5897 TELEDYNE BATTERY PRODUCTS <strong>EASA</strong>.IM.A.S.02<strong>01</strong>7 SA1<strong>01</strong>6SO BEECH 200<br />
Replace existing nickel-cadmium battery with FAA approved Teledyne Battery Products<br />
23.05.2006<br />
BEECH 200C<br />
Teledyne G-6381E lead-acid battery or with Airplane Flight Manual Supplement, dated<br />
BEECH 200CT<br />
Teledyne G-6381ES Sealed Recombinant lead- August 3, 1978, for G-6381E battery, or March<br />
BEECH 200T<br />
acid storage battery<br />
21, 20<strong>01</strong>, for G-6381ES battery, or later<br />
BEECH 300<br />
approved revisions is required as part of this<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200C<br />
BEECH B200T<br />
BEECH B300C<br />
installation.<br />
10<strong>01</strong>5898 TELEDYNE BATTERY PRODUCTS <strong>EASA</strong>.IM.A.S.02<strong>01</strong>8 SA1<strong>01</strong>7SO BEECH 65-90<br />
Replace existing nickel-cadmium battery with<br />
23.05.2006<br />
BEECH 65-A90<br />
Teledyne Battery Model No. G-638E, G-6381E<br />
BEECH 65-A90-1<br />
BEECH A100<br />
BEECH B90<br />
BEECH C90<br />
BEECH E90<br />
or G-6381ES<br />
10<strong>01</strong>6852 TELEDYNE BATTERY PRODUCTS <strong>EASA</strong>.IM.R.S.<strong>01</strong>228 SR<strong>01</strong>406LA BELL 206A<br />
Aircraft Battery Replacement with Alternative -- 14.09.2006<br />
BELL 206B<br />
Designs – Replace existing nickel-cadmium<br />
BELL 206L<br />
batteries with Teledyne Battery Products Model<br />
BELL 206L-1<br />
BELL 206L-3<br />
G-641S battery<br />
10<strong>01</strong>6853 TELEDYNE BATTERY PRODUCTS <strong>EASA</strong>.IM.R.S.<strong>01</strong>229 SR<strong>01</strong>427LA MD HELICOPTERS 369A Aircraft Battery Replacement with Alternative<br />
07.06.2006<br />
MD HELICOPTERS 369D<br />
MD HELICOPTERS 369E<br />
MD HELICOPTERS 369F<br />
MD HELICOPTERS 369FF<br />
MD HELICOPTERS 369H<br />
MD HELICOPTERS 369HM<br />
MD HELICOPTERS 369HS<br />
MD HELICOPTERS 500N<br />
MD HELICOPTERS 600N<br />
Designs<br />
10<strong>01</strong>6928 TELEDYNE BATTERY PRODUCTS <strong>EASA</strong>.IM.R.S.<strong>01</strong>314 FAA STC ST1186SO BELL 212<br />
Validation of FAA STC SH1186SO Aircraft<br />
20.06.2007<br />
BELL 412<br />
BELL 412 EP<br />
Battery Replacement with Alternative Designs<br />
10027424 TELEDYNE CONTROLS - FLIGHT DATA P-<strong>EASA</strong>.A.S.034<strong>01</strong> MD-80 SERIES Installation of Wireless Quick Access Recorder. None. Prior to installation of this modification the 12.09.2009<br />
COM<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
10033194 TELEDYNE CONTROLS - FLIGHT DATA P-<strong>EASA</strong>.A.S.03937 B737-600/-700/-800/-900/-900ER Installation of enhanced airborne data loader This modification is only applicable to 737 Prior to installation of this modification it 22.12.2<strong>01</strong>0<br />
COM<br />
on Boeing 737 seriesaircraft<br />
aircraft that already havean ADL installed or must be determined thatthe<br />
have provisions for installation of an<br />
interrelationship between this modification<br />
ADL.Compatibility must be established for and any other previouslyinstalled<br />
each aircraft.<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4159 TELEDYNE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>290 BOEING 767-300 Installation of Teledyne Controls Optical Quick<br />
Access recorder (OQAR) P/N 224800<br />
10<strong>01</strong>4562 TELEDYNE LIMITED <strong>EASA</strong>.A.S.02662 MD80 SERIES Installation of Optical Quick Access Recorder. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
10039512 TELEDYNE LIMITED <strong>EASA</strong>.A.S.<strong>01</strong>198 REV 1 767-200, 767-300/-300F Installation of Wireless Quick Access Recorder None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 442/<strong>462</strong><br />
26.10.2005<br />
05.07.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10027900 TELEDYNE TECHNOLOGIES, INC. FAA STC ST02172LA B747-100, 747-200, 747-200B Installation of Teledyne Controls Wireless None None 13.11.2009<br />
B747-200C, 747-200F, 747-300 Ground Link - Quick AccessRecorder (WQAR)<br />
B747-400, 747-400F<br />
in accordance with FAA approved Teeldyne<br />
Controls MasterData List Document No. MDL<br />
2243800-747 Revision "-" Appendix A,<br />
datedOctober 21, 2008 or later approved<br />
revisions V<br />
10031056 TELEDYNE TECHNOLOGIES, INC. REV. 1 FAA STC ST0<strong>04</strong>98LA B757-200 Installation of Aircraft Communications, None Prior to installation of this modification it 23.07.2<strong>01</strong>0<br />
Addressing and Reporting System(ACARS)<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032418 TELEDYNE TECHNOLOGIES, INC. B777-200, B777-200LR, B777-300<br />
B777-300ER, B777F<br />
10033914 TELEDYNE TECHNOLOGIES, INC. P-<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>234<br />
FAA STC ST<strong>01</strong>778LA A300B2-1A, -1C, -203<br />
A300B2K-3C<br />
A300B4-2C, -103, -203<br />
A300B4-6<strong>01</strong>, -603, -605R<br />
A300B4-620, -622R<br />
A300C4-605 VARIANT F<br />
A300F4-605R, -622R<br />
A310-203, -2<strong>04</strong>, -221, -222<br />
A310-3<strong>04</strong>, -322, -324, -325<br />
10<strong>01</strong>4312 TENENCIA Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>557 REV. 1 1. BEECH 58PA<br />
2. BEECH 58/58A<br />
3. BEECH G58<br />
Installation of Wireless Ground Link - Quick<br />
Access Recorder (WQAR)This STC consists in<br />
the installation of the WQAR on Boeing 777<br />
series.<br />
Installation of Wireless Ground Link - Quick<br />
Access Recorder (WQAR) This STC consists<br />
in the installation of the WQAR on<br />
AirbusA300/A310/A300-600 series.<br />
This STC is applicable to the following WQAR Prior to installation of this modification it <strong>04</strong>.11.2<strong>01</strong>0<br />
p/n (2243800-xxx) :- 2243800-61- 2243800-62- must be determined thatthe<br />
2243800-63- 2243800-64- 2243800-71- interrelationship between this modification<br />
2243800-73- 2243800-77- 2243800-79- and any other previouslyinstalled<br />
2243800-81<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
This STC is applicable to the following WQAR Prior to installation of this modification it<br />
p/n (2243800-xxx) :- 2243800-21 - 2243800-31 must be determined thatthe<br />
18.02.2<strong>01</strong>1<br />
- 2243800-33 - 2243800-35 - 2243800-37 - interrelationship between this modification<br />
2243800-39 - 2243800-42 - 2243800-43 - and any other previouslyinstalled<br />
2243800-44 - 2243800-62 - 2243800-63 - modification and/ or repair will introduce<br />
2243800-64 - 2243800-71 - 2243800-73 - no adverse effectupon the airworthiness<br />
2243800-<br />
of the product<br />
Hawker Beechcraft Baron Steep Approach Hawker Beechcraft Model 58PA S/N TJ-256 Prior to installation of this modification it 26.05.2<strong>01</strong>0<br />
Landing Certification This Certification at andHawker Beechcraft Model 58 S/N TH-1967 must be determined thatthe<br />
Revision 1 of the STC ref. <strong>EASA</strong>.A.S.<strong>01</strong>557 only.<br />
interrelationship between this modification<br />
includesadditional aeroplane models compared<br />
and any other previouslyinstalled<br />
to the initial issue of the STC<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>4396 TENENCIA Ltd. <strong>EASA</strong>.A.S.<strong>01</strong>690 BAE JETSTREAM 3100 Installation of Dual Mode S Transponders &<br />
Honeywell CAS 67A TCAS II.<br />
<strong>04</strong>.<strong>01</strong>.2006<br />
10<strong>01</strong>4498 TENENCIA Ltd. <strong>EASA</strong>.A.S.02561 BAE ATP Installation of No. 2 ECS Pack 23.10.2006<br />
10<strong>01</strong>4514 TENENCIA Ltd. <strong>EASA</strong>.A.S.02589 LOCKHEED 188 Installation of Mode S Transponders for<br />
Enhanced Surveillance<br />
None 11.05.2006<br />
10<strong>01</strong>4583 TENENCIA Ltd. <strong>EASA</strong>.A.S.02689 BAE 146<br />
Installation of Single or Dual Universal UNS-1L RNAV Approaches are not permitted for<br />
06.09.2006<br />
BAE 146/AVRO 146 SERIES or UNS-1K+ Flight Management System installation with electronic-mechanical<br />
instruments<br />
10<strong>01</strong>4710 TENENCIA Ltd. <strong>EASA</strong>.A.S.02882 BAE 146/AVRO 146 SERIES Installation of Cockpit Door Locking<br />
BAE Systems Modification HCM50303C. 12.12.2006<br />
BAE 146/RJ SERIES<br />
System.The modification to the Cockpit Door<br />
provides the ability for the Cabin Crew to<br />
access the Cockpit in the case of Pilot<br />
Incapacitation.<br />
10<strong>01</strong>4746 TENENCIA Ltd. <strong>EASA</strong>.A.S.02929 BAE ATP Lead Acid Battery Installation. 1. Applicable only to aeroplanes that are<br />
fitted with an appropriately approved Class E<br />
Cargo Compartment used only for the carriage<br />
of cargo.2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship betwee<br />
27.<strong>01</strong>.2009<br />
10<strong>01</strong>4758 TENENCIA Ltd. <strong>EASA</strong>.A.S.02947 AIRBUS A300 B4<br />
Installation of dual Universal UNS-1L or UNS- The installation of this STC has a prerequisite<br />
22.02.2008<br />
AIRBUS A300 MODEL B2 1K+ Flight Management System (FMS)This aircraft configuration.This STC is only<br />
modification allows complying with Precision applicable on aircraft :1. in which the following<br />
RNAV operations in designated European modifications have been embodied :- FAA<br />
airspace.<br />
STC ST<strong>01</strong>113CH, accepted by <strong>EASA</strong> under<br />
the grandfather rights ruling of the<br />
10<strong>01</strong>4765 TENENCIA Ltd. <strong>EASA</strong>.A.S.02955 BOEING 737 Installation of Mode S Transponders for<br />
Enhanced Surveillance.<br />
- Limited to installation on Boeing 737-82R<br />
S/N 29329 only.- The Operators Minimum<br />
Equipment List (MEL) should be revised to<br />
include the requirements for Mode S<br />
Transponders and Elementary and Enhanced<br />
Surveillance in accordance with Boeing Aircraft<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 443/<strong>462</strong><br />
31.05.2007
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4771 TENENCIA Ltd. <strong>EASA</strong>.A.S.02963 BOEING 757-200 Installation of Mode S Transponders for Certification Basis as per TCDS including:JAA<br />
03.<strong>04</strong>.2007<br />
Enhanced Surveillance<br />
TGL 13, revision 1, <strong>01</strong>/06/2003<strong>EASA</strong> AMC 20-<br />
13, 22/12/2006<br />
10<strong>01</strong>5039 TENENCIA Ltd. <strong>EASA</strong>.A.S.03352 AVRO RJ VIP Interior Installation. S/N E3386 only. 19.05.2008<br />
10<strong>01</strong>5160 TENENCIA Ltd. <strong>EASA</strong>.A.S.03529 REV. 1 AVRO 146-RJ70 VIP Installation 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
19.06.2009<br />
10<strong>01</strong>5251 TENENCIA Ltd. <strong>EASA</strong>.A.S.03696 EMBRAER EMB-135 SERIES EMB 135 Electronic Flight Bag installation None 29.05.2009<br />
10<strong>01</strong>5265 TENENCIA Ltd. <strong>EASA</strong>.A.S.03727 BOEING 747-400 SERIES Installation of 3 AD Aerospace FV-0315 1. Tenencia Ltd. Instruction for Continued<br />
16.<strong>04</strong>.2009<br />
External Camera’s and 1 AD Aerospace FV- Airworthiness, Report TEN 587/4, issue 1, shall<br />
0610 Video Transmission Unit in accordance be incorporated in the aircraft maintenance<br />
with Tenencia Ltd modification TEN 587 Issue documentation.2. Tenencia Ltd Operations<br />
1, or later approved revisions.<br />
Manual Supplement, report TEN 587/7 Iss. 1,<br />
shall be incorporated in the A<br />
10<strong>01</strong>5269 TENENCIA Ltd. <strong>EASA</strong>.A.S.03741 BOEING 757 78 Seat Installation / This modification consists Prior to installation of this modification the<br />
of: - Removal of existing 200 Economy Seats, - installer must determine that the<br />
30.03.2009<br />
Installation of 78 First Class Seats including 3 interrelationship between this modification and<br />
Club 4 installations, 2 at the forward and 1 at any other previously installed modification will<br />
the aft end of the cabin.<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>7107 TENENCIA Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>082 AS 355 F, AS 355 N Installation of a Gyron 935 Camera mounted<br />
on the centerline of the aircraft in front of the<br />
nose<br />
05.<strong>04</strong>.2006<br />
10<strong>01</strong>7207 TENENCIA Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>359 EUROCOPTER FRANCE AS 350 Gyron 935 camera installation on the AS 350<br />
06.03.2007<br />
SERIE<br />
series a/c.<br />
10028847 TENENCIA Ltd. P-<strong>EASA</strong>.A.S.03872 REV. 2 AVRO 146-RJ100 Avro 146-RJ100 Amiri Flight VIP Installation. Serial number E3387 only. The VIP lavatory is fitted with fire<br />
protection equipment (smokedetection<br />
and a built in fire extinguisher in the waste<br />
compartment inaccordance with the<br />
requirements in JAR/CS 25.854) even<br />
though theaircraft's certification basis<br />
does not require this. H<br />
26.<strong>01</strong>.2<strong>01</strong>1<br />
10032387 TENENCIA Ltd. MK050, MK0502 Installation of a Universal Avionics Terrain As contained in Ten supplement 1 issue 1 to Prior to installation of this modification it 02.11.2<strong>01</strong>0<br />
Awareness and WarningSystem (TAWS) the Fokker F27 Mk 0502flight manual must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032536 TENENCIA Ltd. P-<strong>EASA</strong>.A.S.03438 BOEING 747-200<br />
BOEING 747-300<br />
Installation of a Dual Honeywell HT-9100 FMS<br />
per ModificationDescription TEN 539 Boeing<br />
747-200 Dual Honeywell HT9100 GNSS<br />
NavigationManagement System Installation,<br />
Issue 4 dated 10 November 2<strong>01</strong>0<br />
10033233 TENENCIA Ltd. AVRO 146-RJ85 Modification TEN 655, AVRO 146-RJ85,<br />
Installation of 3R and 4R Galleysand No. 3<br />
VHF COMM<br />
10033789 TENENCIA Ltd. F27 MK 050 & F27 MK 0502 Installation of a Single UNS-1Lw Universal<br />
Avionics Flight ManagementSystem.<br />
This STC is applicable to aircraft that have<br />
previously been modified inaccordance with<br />
STC ST<strong>01</strong>841CH / IM.A.S.<strong>01</strong>660 GPS<br />
Antenna Provisionsinstallation and have dual<br />
Honeywell Roll Computers P/N 2590623-914<br />
or-915<br />
STC ST<strong>01</strong>841CH / IM.A.S.<strong>01</strong>660 GPS<br />
Antenna Provisions must be<br />
installedtogether with dual Honeywell Roll<br />
Computers P/N 2590623-914 or -915<br />
AFM supplement TEN SUPPLEMENT 1<br />
for the Boeing 747 series Flight<br />
Manualsshall be on board of the modified<br />
12.11.2<strong>01</strong>0<br />
Serial numbers E2323 and E2325 only.<br />
aircraft Repo<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.<strong>01</strong>.2<strong>01</strong>1<br />
AFM Supplement TEN/FOKKER F27/002<br />
Issue 1<br />
Prior to installation of this modification it 08.02.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 444/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10034446 TENENCIA Ltd. B737-300, -400, -500, -600 Cockpit Door Surveillance System Not applicable Prior to installation of this modification it 05.<strong>04</strong>.2<strong>01</strong>1<br />
B737-700, -800, -900<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10034998 TENENCIA Ltd. A318, A319, A320, A321 1 NET In-flight Entertainment (IFE) System<br />
Installation<br />
10035<strong>04</strong>7 TENENCIA Ltd. A319, A320, A321 ALL MODELS "Installation of provisions for the use of a Class<br />
2 Dual GoodrichElectronic Flight Bag (EFB)<br />
Smart Display System"<br />
Not applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
18.05.2<strong>01</strong>1<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
23.05.2<strong>01</strong>1<br />
10035689 TENENCIA Ltd. BAE 146 SERIES 200 EWIS Assessment for VIP Cabin Interior Serial number E2079 only. <strong>EASA</strong> STC 10027954 Revision 1 issued<br />
to Aviation Traders Ltd is aprerequisite<br />
for the implementation of this STC.Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyins<br />
10037413 TENENCIA Ltd. P-<strong>EASA</strong>.A.S.03871 A300-600 SERIES Cockpit Door Monitoring SystemInstallation of<br />
the AD Aerospace "Cabin Vu" cockpit door<br />
monitoringsystem (video monitor, monitor<br />
control panel, video switch unit andthree<br />
cameras) in accordance with Tenencia Ltd<br />
Modification Report(Master Data List) TEN 656<br />
10039138 TENENCIA Ltd. A319-111/-112/-113/-114/-115<br />
A319-131/-132/-133<br />
A320-111/-211/-212/-214/-215<br />
A320-216/-231/-232/-233<br />
A321-111/-112/-131/-211/-212<br />
A321-213/-231/-232<br />
10<strong>04</strong>0700 TENENCIA Ltd. AVRO 146 SERIES RJ100<br />
AVRO 146 SERIES RJ115<br />
AVRO 146 SERIES RJ70<br />
AVRO 146 SERIES RJ85<br />
BAE 146 SERIES 100<br />
BAE 146 SERIES 200<br />
BAE 146 SERIES 300<br />
12.07.2<strong>01</strong>1<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
25.11.2<strong>01</strong>1<br />
In-Seat Power Supplies None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>04</strong>.2<strong>01</strong>2<br />
ADS-B Out Surveillance Configuration using transponder part number Prior to installation of this modification it 20.07.2<strong>01</strong>2<br />
751-7800-11005 does not meet<strong>EASA</strong> AMC 20- must be determined thatthe<br />
24 for ADS-B NRA. Emergency<br />
interrelationship between this modification<br />
Status/Emergency Indicator arenot provided. and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 445/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5423 TEXAS SKYWAYS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>154 FAA STC SA09133SC CESSNA 182<br />
Installation of Teledyne Continental Motors IO- The approval is only valid in combination with<br />
07.07.2006<br />
CESSNA 182A<br />
550-F engine and Hartzell or McCauley the installation of STC <strong>EASA</strong>.A.S.<strong>01</strong>374<br />
CESSNA 182B<br />
Propeller in acc. with Texas Skyways Spec. (Gomolzig GmbH, Germany)<br />
CESSNA 182C<br />
TS0028, Rev. 1, or later approved Revision<br />
CESSNA 182D<br />
CESSNA 182E<br />
CESSNA 182F<br />
CESSNA 182G<br />
CESSNA 182H<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA F182-P<br />
CESSNA F182-Q<br />
and TS0034<br />
10<strong>01</strong>5424 TEXAS SKYWAYS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>155 FAA STC SA10070SC CESSNA 180<br />
Installation of Hartzell 3-blade Propeller in acc. The approval is only valid with latest <strong>EASA</strong><br />
07.07.2006<br />
CESSNA 180A<br />
with Texas Skyways Doc. 5<strong>01</strong>6-0000, Rev. E, approved Noise Certificate<br />
CESSNA 180B<br />
CESSNA 180C<br />
CESSNA 180D<br />
CESSNA 180E<br />
CESSNA 180F<br />
CESSNA 180H<br />
CESSNA 180J<br />
CESSNA 180K<br />
CESSNA 182<br />
CESSNA 182A<br />
CESSNA 182B<br />
CESSNA 182D<br />
CESSNA 182E<br />
CESSNA 182F<br />
CESSNA 182G<br />
CESSNA 182H<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA 185<br />
CESSNA 185A<br />
CESSNA 185B<br />
CESSNA 185C<br />
CESSNA 185D<br />
CESSNA 185E<br />
CESSNA 207<br />
or later approved Revision<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 446/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5425 TEXAS SKYWAYS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>156 FAA STC SA09964SC CESSNA 180<br />
Installation of engine mount heat shields in acc.<br />
07.07.2006<br />
CESSNA 180A<br />
with Texas Skyways Doc. 5<strong>01</strong>8-1<strong>01</strong>, dated 12<br />
CESSNA 180B<br />
CESSNA 180C<br />
CESSNA 180D<br />
CESSNA 180E<br />
CESSNA 180F<br />
CESSNA 180G<br />
CESSNA 180H<br />
CESSNA 180J<br />
CESSNA 180K<br />
CESSNA 182<br />
CESSNA 182A<br />
CESSNA 182B<br />
CESSNA 182C<br />
CESSNA 182D<br />
CESSNA 182E<br />
CESSNA 182F<br />
CESSNA 182G<br />
CESSNA 182H<br />
CESSNA 182J<br />
CESSNA 182K<br />
CESSNA 182L<br />
CESSNA 182M<br />
CESSNA 182N<br />
CESSNA 182P<br />
CESSNA 182Q<br />
CESSNA 182R<br />
CESSNA F182-P<br />
CESSNA F182-Q<br />
Oct 20<strong>01</strong>, or later approved Revision<br />
10<strong>01</strong>6688 TEXAS SKYWAYS, INC. <strong>EASA</strong>.IM.E.S.<strong>01</strong>000 FAA STC SE09131SC Removal of fuel injection system and induction Approval of this change in type design applies<br />
06.<strong>04</strong>.2006<br />
system and installation of carburetor in to the above engine model only. Compatibility<br />
accordance with Texas Skyways, Inc. of this modification with previously approved<br />
Specification TS0030, dated <strong>01</strong> May 1995 or modifications must be determined by the<br />
FAA later approved revision, based on FAA installer. A copy of this Certificate must be<br />
Supplemental Type Certificate Number<br />
SE09131SC<br />
maintained as part of the perma<br />
10038267 THALES AVIONICS Inc. REV. 1 FAA STC NO. ST02411LA 777-200 In-Flight Entertainment (IFE) System<br />
Concurrent installation of the following STCs Prior to installation of this modification it 03.02.2<strong>01</strong>2<br />
Installation<br />
are required for theinstallation of this STC:1) must be determined thatthe<br />
Flight Structures, Inc. <strong>EASA</strong> STC No. interrelationship between this modification<br />
10<strong>01</strong>5720, Business Class SeatInstallation.2) and any other previouslyinstalled<br />
Northwest Aerospace Technologies, Inc. modification and/ or repair will introduce<br />
<strong>EASA</strong> STC No. 10038268 (<strong>EASA</strong>Project No. no adverse effectupon the airworthiness<br />
00<br />
of the product.<br />
10<strong>04</strong>1205 THALES AVIONICS Inc. FAA STC ST02431LA A321-211, A321-212,<br />
A321-213, A321-231,<br />
A321-232<br />
Installation of Thales Avionics IFS TopSeries In- This STC must be installed in conjunction with<br />
Flight Entertainment(IFE) System<br />
<strong>EASA</strong> STC 10<strong>04</strong>07<strong>04</strong> -Aerospace Engineering<br />
Solutions (AES) - Introduction of Twin Class<br />
CabinConfiguration<br />
10<strong>04</strong>2547 THALES AVIONICS Inc. A321-211,-212,-213,-231,-232 Installation of Thales Avionics IFS TopSeries In- This STC must be installed in conjunction with<br />
Flight Entertainment(IFE) System.<br />
10<strong>04</strong>2295 THE BOEING COMPANY <strong>EASA</strong>.IM.A.S.03158 FAA STC ST<strong>01</strong>697SE B737-700/-800 Lower Cabin Altitude (LCA) modification: cabin<br />
altitude reversion to 6,500 ft in lieu of 8,000 ft<br />
at 41,000 ft flight altitude. Modification in<br />
accordance with Boeing's "Master document<br />
listfor Lower Cabin Altitude modification"<br />
D926A200.<br />
<strong>EASA</strong> STC 10<strong>04</strong>07<strong>04</strong> -Aerospace Engineering<br />
Solutions (AES) - Introduction of Twin Class<br />
CabinConfiguration.<br />
Prior to installation of this modification it 29.08.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification it 07.12.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
See <strong>EASA</strong> Approved Annex Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. A sur<br />
22.11.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 447/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>6326 THE BOEING COMPANY - <strong>EASA</strong>.IM.A.S.02635 FAA STC SA2123CE-D AMENDED 19 BOEING 747-2B5B Conversion of Passenger Airplane to dedicated This approval is limited to ariplane model B747-<br />
28.<strong>01</strong>.2008<br />
Special Freighter with Main Deck Side Cargo 200B S/N 22482 and S/N 22485.Boeing<br />
Door in accordance with Boeing Drawing List Commercial Airplane Groupe - Wichita Dvision,<br />
document D3-8857, Section V, Appendix 31, Airplane Flight Manual Supplement dated 9<br />
Rev.CN<br />
September 1991 or revision for AFM D6-<br />
13703.3B5 or later approved revisions of this<br />
10<strong>01</strong>6519 THE BOEING COMPANY - <strong>EASA</strong>.IM.A.S.02891 Conversion of Passenger Airplane to Main<br />
Deck Side Cargo Door Dedicated Special<br />
Freighter as defined by FAA approved Boeing<br />
Document D800-10610-7, Revision New or<br />
later FAA approved revisions. (Validation of<br />
FAA STC ST00252WI-D)<br />
10<strong>01</strong>6644 THE BOEING COMPANY - <strong>EASA</strong>.IM.A.S.03085 REV. 1 FAA STC SA2124CE-D BOEING 747-200B Conversion of Passenger Airplane to Main<br />
Deck Side Cargo Door Dedicated Special<br />
Freighter in accordance with Boeing Drawing<br />
List document D3-8857, Section V, Appendix<br />
33, Rev. CS.<br />
10<strong>01</strong>5813 THE GOODYEAR TIRE & RUBBER<br />
COMPANY<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>882 FAA STC ST03183AT 1. AIRBUS A330<br />
2. AIRBUS A340<br />
Installation of Goodyear Radial Tire Size<br />
1050x395R16, P/N 109Q89 1 on Airbus A330<br />
and A340 Nose Landing Gear according to<br />
FAA STC ST03183AT<br />
10038928 THE NORDAM GROUP, Inc. REV. 1 FAA STC ST09034SC A319, A320, A321 Installation of C & X Band Fuselage Nose<br />
Radome Shell<br />
10<strong>01</strong>4219 THIELERT AIRCRAFT ENGINES GMBH <strong>EASA</strong>.A.S.<strong>01</strong>380 REV. 4 APEX DR 400 RP, 400/120D<br />
APEX DR 400/140B<br />
APEX DR 400/180R, 400/200R<br />
10<strong>01</strong>4287 THIELERT AIRCRAFT ENGINES GMBH <strong>EASA</strong>.A.S.<strong>01</strong>527 REV. 6 LBA EMZ SA1295 172F, 172G, 172H, 172I, 172K,<br />
172L, 172M, 172N, 172P, 172R<br />
172S<br />
F 172F, F 172G, F 172H<br />
F 172K, F 172L, F 172M, F 172N<br />
F 172P<br />
10<strong>01</strong>4364 THIELERT AIRCRAFT ENGINES GmbH <strong>EASA</strong>.A.S.<strong>01</strong>632 REV. 8 LBA-EMZ SA 1377 PA 28-140, PA 28-150<br />
PA 28-151, PA 28-160<br />
PA 28-161, PA 28-180<br />
1. Installation of TAE 125 engine2. Installation<br />
of TAE 125-02-99 engine and installation of<br />
FADEC BackupBattery3. Installation of TAE<br />
125-02-114 engine<br />
FAA Approved Airplane Flight Manual<br />
Supplement to Airplane Flight Manual D6-<br />
35747 for Boeing Model 747-200B is required<br />
to support this modification of applicable<br />
airplanes as identified in table 1 of Boeing Doc.<br />
D800-10610-7, Rev. New or later FAA<br />
approve<br />
1. Prior to installation of this modification the<br />
installer must determine that<br />
theinterrelationship between this modification<br />
and any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.2. The ins<br />
06.10.2008<br />
09.02.2009<br />
19.09.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.03.2<strong>01</strong>2<br />
Installation of TAE 125-02-114 is limited to DR<br />
400 models with S/N 2574and upwards.<br />
Prior to installation of this modification it 11.<strong>04</strong>.2<strong>01</strong>1<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Major Change to STC <strong>EASA</strong>.A.S.<strong>01</strong>527, This STC supersedes LBA-EMZ SA<br />
Prior to installation of this modification the 21.05.2<strong>01</strong>0<br />
Revision 5:1.,,Installation of engine TAE 125- 1295Power/Rotational speed TAE 125-<strong>01</strong> & installer must determinethat the<br />
<strong>01</strong> in accordance with InstallationManual IM-20- TAE 125-02-99:Take off power: 99 kw at 2300 interrelationship between this modification<br />
<strong>01</strong> and Type Design Definition Doc. No: TDD- min -1 (Propellerspeed)Max. continious power: and any otherpreviously installed<br />
20-<strong>01</strong>;2.,,Installation of engine TAE 125-02-99 99 kw at 2300 min -1 (Propellerspeed) Fuel: modification will introduce no adverse<br />
in accordance with InstallationManual Service Bulletin TM TAE 6<strong>01</strong>-0005MTOW: effect uponthe airworthiness of the<br />
Model Cessna<br />
product.<br />
1. Installation of engine TAE 125-<strong>01</strong> in 1. This STC supersedes LBA-EMZ SA 1377. Prior to installation of this modification it 10.05.2<strong>01</strong>2<br />
accordance with InstallationManual IM-40-<strong>01</strong> 2. Power/Rotational Speed: For TAE 125-<strong>01</strong> must be determined thatthe<br />
and Type Design Definition Doc. No.: TDD 40- and 125-02-99 installations:Take of power: 99 interrelationship between this modification<br />
<strong>01</strong>.2. Installation of engine TAE 125-02 in Kw at 2300 min-1 (Propellerspeed)Max. and any other previouslyinstalled<br />
accordance with InstallationManual IM-40-02 continuous power: 99 Kw at 2300 min-1 modification and/ or repair will introduce<br />
and Type Design Definition Doc. No.: TDD (Propellerspeed) For TAE 125-02-114 no adverse effectupon the airworthiness<br />
installations:Ta<br />
of the product.<br />
10<strong>01</strong>4442 THIELERT AIRCRAFT ENGINES GmbH <strong>EASA</strong>.A.S.02492 CIRRUS SR22 Installation of engine Centurion 4.0 in<br />
accordance to Type Design Definition Doc.<br />
No.: TDD-70-<strong>01</strong>Engine: Centurion<br />
4.0Propeller: MTV-14-D/195-30bCertification<br />
Basis: see CRI A-1max. Take Off Power:<br />
228 kw at 2300 min-1 (Propeller-RPM)max.<br />
Contin<br />
10<strong>01</strong>4452 THIELERT AIRCRAFT ENGINES GmbH <strong>EASA</strong>.A.S.02505 CESSNA 172 Installation of Universal Fuel System This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 448/<strong>462</strong><br />
12.02.2007<br />
07.02.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4500 THIELERT AIRCRAFT ENGINES GmbH <strong>EASA</strong>.A.S.02565 REV. 2 CESSNA TU206G<br />
For Cessna U206F and TU206F:Engine:<br />
28.<strong>04</strong>.2008<br />
CESSNA U206F<br />
Centurion 4.0 BE-221Propeller: MTV-9-<br />
CESSNA U206G<br />
D/210-58Certification Basis: See CRI Almax.<br />
Take Off Power 221 kW at 2300 min-1<br />
(Propeller RPM)max. Continuous Power 221<br />
kWat 2300 min-1 (Propeller RPM)Fuel: See<br />
Se<br />
10<strong>01</strong>5310 THIELERT AIRCRAFT ENGINES GmbH <strong>EASA</strong>.E.S.<strong>01</strong>000 Installation of the FADEC G6 in accordance Engines having been converted via this STC<br />
03.08.2007<br />
with Installation Manual IM-80-<strong>01</strong>, Conversion may be identified as IO-580-B1A-EThe data in<br />
Instruction CI-80-<strong>01</strong> and Type Design Definition the TCDS <strong>EASA</strong>.IM.E.027 remains valid,<br />
Doc. No.: TDD-80-<strong>01</strong>.<br />
except the following:Weight of the engine<br />
equipped with FADEC: 207.49 kg (457.44<br />
lbs)Dimensions: Overall Height:<br />
10<strong>01</strong>5458 THIELERT AIRCRAFT ENGINES GmbH <strong>EASA</strong>.IM.A.S.<strong>01</strong>2<strong>04</strong> FAA STC ST10298SC-D DR 140B, DR 180R, DR 200R Installation of WX-1000E Stormoscope System 1. This installation is eligible for airplanes S/N<br />
28.06.2005<br />
ROBIN DR 400 RP, DR 120D,<br />
052 and subsequent with Collins Pro Line 4,<br />
version 6.1 avionics system2. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "Descri<br />
10036328 THIELERT AIRCRAFT ENGINES GMBH P-<strong>EASA</strong>.A.S.02566 DA 40 D Installation of engine TAE 125-02-114 in<br />
accordance with ConversionInstruction CI-50-<br />
02S DA 40 Issue/Revision: 1/0 and the Type<br />
DesignDefinition Document No: 50-<strong>01</strong><br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
<strong>01</strong>.09.2<strong>01</strong>1<br />
10<strong>01</strong>4379 THOMSONFLY LTD. <strong>EASA</strong>.A.S.<strong>01</strong>657 BOEING 757-200 Introduction of Security Cameras 07.12.2005<br />
10<strong>01</strong>4411 THOMSONFLY LTD. <strong>EASA</strong>.A.S.<strong>01</strong>708 BOEING 767-300 Introduction of BE Aerospace Spectrum Seat 05.03.2007<br />
10<strong>01</strong>4461 THOMSONFLY LTD. <strong>EASA</strong>.A.S.02521 BOEING 767-300 Introduction of STG Aerospace Photo-<br />
Luminescent Passenger Emergency Escape<br />
Path Lightning System<br />
Cabin & Exit Lightning levels must be<br />
measured for acceptability on each installation<br />
in accordance with Thomsonfley Technical<br />
Engineering Order TEO/767/1463 Issue 2<br />
dated 26 April 2006 or later approved revision.<br />
10<strong>01</strong>6435 THUNDER BAY AVIATION LIMITED <strong>EASA</strong>.IM.A.S.02775 TCCA STC SA<strong>04</strong>-55 BOMBARDIER DHC-6 Double and Single Utility Seats for DHC-6. 19.03.2008<br />
10033486 TIMCO AEROSYSTEMS REV. 1 FAA STC ST03143AT-D 747-400, 747-400 (BCF), Installation of a Rockwell Collins Aero H+ None Prior to installation of this modification it <strong>04</strong>.02.2<strong>01</strong>1<br />
747-400F<br />
Satcom System in accordancewith TIMCO<br />
must be determined thatthe<br />
Master Data List <strong>04</strong>T089L<strong>01</strong>, Rev. IR, dated<br />
interrelationship between this modification<br />
November 25, 2005or later FAA approved<br />
and any other previouslyinstalled<br />
revision<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10035902 TIMCO AEROSYSTEMS FAA STC ST00552AT B747-400 SERIES Installation of a Collins Satcom update from<br />
900 SDU to 906 SDU (dataonly) in accordance<br />
with <strong>Page</strong> Avjet Master Drawing List 94-17,<br />
InitialRelease, dated June 17, 1994, or later<br />
FAA approved Revision. ,,<br />
None. None. 26.07.2<strong>01</strong>1<br />
10036655 TIMCO AEROSYSTEMS FAA STC ST<strong>01</strong>959AT-D 747-400 Installation of a Ball Camera Entertainment<br />
system per Timco Master DataList<br />
99T057L0<strong>01</strong> Rev. C, dated November 8, 1999<br />
or later FAA approvedrevision.Validation of<br />
FAA STC ST<strong>01</strong>959AT-D<br />
02.05.2006<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
27.09.2<strong>01</strong>1<br />
10038130 TIMCO AEROSYSTEMS REV. 1 FAA STC ST03884AT-D 767-300 Installation of LCD Monitor Upgrade None <strong>EASA</strong> accepts the use of FAA<br />
(Acceptable Means of Compliance) Issue<br />
PaperC-1 (Stage 4, Closed <strong>01</strong>/082008)<br />
as being applicable to this project. Future<br />
changes to this STC that impact on the<br />
agreed means ofcompliance to this IP<br />
must be considered as a Major Le<br />
21.05.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 449/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0972 TIMCO AEROSYSTEMS FAA STC NO. ST03928AT-D 777-300 Audio/Video On-Demand & In-seat Power none JADE/JAMCO STC ST02107SE-D must 10.08.2<strong>01</strong>2<br />
System Installation.<br />
be installed to or concurrently withthis<br />
STC.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair<br />
10<strong>01</strong>5495 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>257 REV. 1 FAA STC ST03068AT-D BOEING 767-300 Cabin Standardization in accordance with This approval should not be extended to other<br />
<strong>01</strong>.12.2006<br />
TIMCO Master Data List 03T<strong>01</strong>2L0<strong>01</strong>, revision aircraft of this model on which other previoulsy<br />
D, dated November 30th, 2006, or later FAA approved modifications are incorporated<br />
approved revision.<br />
unless it is determined by the installer that the<br />
interrelationship between this change and any<br />
of those other previously<br />
10<strong>01</strong>5545 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>433 FAA STC ST03197AT BOEING 737-800 Complete interior reconfiguration in accordance 1. Compatibility of this design change with<br />
with TIMCO Aviation Services, Inc MDL, report other previously approved modifications must<br />
17.07.2006<br />
<strong>04</strong>T1<strong>01</strong>L0<strong>01</strong>, revision "C", dated December be determined by the installer.2. This STC is<br />
07, 2005, or later <strong>EASA</strong> approved revision approved only for the product configuration as<br />
defined in the approved design data referred to<br />
in the paragraph "De<br />
10<strong>01</strong>56<strong>01</strong> TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>537 FAA STC ST03107AT-D BOEING 767-300 Interior Reconfiguration 15.12.2005<br />
10<strong>01</strong>5636 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>592 FAA STC ST<strong>01</strong>929AT-D BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
Installation of Flight Data Recorder Expanded<br />
Parameters with a Plessey FDAU<br />
Limited to: 99T037C002 for DHC-8-<br />
100/20000T029C009 for DHC-8-<br />
300Maintenance required: pitch, roll and yaw<br />
position transducers and strings have to be<br />
detailed visually inspected and checked for<br />
smooth operation acc. MRB interval 2C<br />
10<strong>01</strong>5637 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>593 FAA STC ST03135AT-D BOEING 767-300 Installation of Rockwell Collins ACARS CMU-<br />
900<br />
28.11.2005<br />
10<strong>01</strong>5831 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>922 REV 1 FAA STC ST03372AT BOEING 767-300 Installation of Lower Lobe Crew Rest Module 1. This approval should not be extended to<br />
16.<strong>01</strong>.2008<br />
(CRM) and Main DeckVestibule in in<br />
other Aircraft of this model on which other<br />
accordance with Timco Master data List previously approved modifications are<br />
<strong>04</strong>T1<strong>04</strong>L0<strong>01</strong>, Rev H, dated December 7, 2007 incorporated unless it is determined by the<br />
or later approved revisions approved by <strong>EASA</strong> installer that the interrelationship between this<br />
in accordance with <strong>EASA</strong> ED Decision<br />
20<strong>04</strong>/<strong>04</strong>/CF (or<br />
change and any other previously ap<br />
10<strong>01</strong>5910 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.02037 FAA STC ST03107AT-D BOEING 767-300 Interior Reconfiguration 16.08.2006<br />
10<strong>01</strong>5974 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.02125 FAA STC ST03300AT-D AIRBUS A321 Installation of a doghouse (storage container) in Limitations and Conditions specified in FAA<br />
18.<strong>01</strong>.2007<br />
the bulk cargo compartment.<br />
STC ST03300AT-D remain applicable.<br />
10<strong>01</strong>5998 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.02155 FAA STC ST03342AT-D BOEING DC-9-87 (MD-87) Installation of a Door Safety Strap 1. TIMCO’s Instructions For Continued<br />
24.10.2006<br />
BOEING MD-88<br />
Airworthiness 06T005R<strong>01</strong>4, Rev. IR dated<br />
June 8, 2006, is a required part of this STC.2.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph<br />
10<strong>01</strong>6002 TIMCO AVIATION SERVICES INC. <strong>EASA</strong>.IM.A.S.02163 FAA STC ST<strong>01</strong>216AT-D AIRBUS A300 Installation of Airshow 210 System -- 08.10.2006<br />
10027196 TIMCO AVIATION SERVICES INC. FAA STC ST00696AT-D B747-400 Installation of Collins SAT-906 SatCom System None Prior to installation of this modification it 14.09.2009<br />
with Ball Antenna's inaccordance with Timco<br />
must be determined thatthe<br />
Master Data List MDL-<strong>01</strong>068, Revision M,<br />
interrelationship between this modification<br />
datedOctober 27, 1999 or later approved<br />
and any other previouslyinstalled<br />
revision.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1003<strong>04</strong>07 TIMCO AVIATION SERVICES INC. FAA STC ST03820AT-D B767-300 Interior reconfiguration, B767-300Validation of<br />
FAA STC ST03820AT-D The aircraft will have<br />
the seating configuration changed to<br />
addadditional coach (Y) class seating,<br />
additional seat track installationwith associated<br />
structural modifications, removal of a<br />
10<strong>01</strong>4179 TMC AERO <strong>EASA</strong>.A.S.<strong>01</strong>316 AIRBUS A330-243 This STC deals with the installation of a TMC The approval of this modification is limited to<br />
stretcher. All documents related to this STC are the Airbus A330-243. the lmitations and<br />
listed in the STC form A330-25-23. The conditions defined in the <strong>EASA</strong> Datasheet are<br />
associated "Fiche de Modification" from<br />
Corsair is referenced 25-137 Rev. 1 ( or later<br />
<strong>EASA</strong>-approved revision )<br />
applicable.<br />
19.07.2006<br />
As per FAA STC ST03820AT-D Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.06.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 450/<strong>462</strong><br />
02.06.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4180 TMC AERO <strong>EASA</strong>.A.S.<strong>01</strong>317 BOEING 737-400 Temporary Installation of a Stretcher that is 1. Operation of the aircraft with stretcher<br />
29.08.2005<br />
fitted on the Passengers Seat Track<br />
installed is limited to 100 FH per year2. The<br />
limitations as descrabied in the AFM<br />
Supplement Doc Ref AFMS25-0317 apply<br />
10<strong>01</strong>4181 TMC AERO <strong>EASA</strong>.A.S.<strong>01</strong>318 BOEING 747 The installation of stretchers mounted on the 1. The maximum number of passengers<br />
12.07.2005<br />
seat tracks in passenger cabin of the Boeing allowed when two stretchers are installed shall<br />
747 for the transport of patients, as described be determined.2. When three or more<br />
in Corsair Fiche de Modification no. 25-136 stretchers are installed transport of passengers<br />
is not allowed.<br />
10033808 TOST GMBH FLUGZEUGGERAETEBAU <strong>EASA</strong>.A.S.03948 LBA STC 0326/XXX HUSKY A-1A, A1-B Installation of Tow Cable retractor Winch with None Prior to installation of this modification it 23.06.2009<br />
Guillotine to Husky A-1A,A-1B. Extension of<br />
must be determined thatthe<br />
LBA STC 0326/xxx, dated 21 October 1992.<br />
interrelationship between this modification<br />
This STC is a revision to and supersedes LBA<br />
and any other previouslyinstalled<br />
STC 0326/xxx, dated 21October 1992.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
10028946 TQAS - TOTAL QUALITY AND AIRCRAFT B737-500 Installation of Floor proximity emergency photo<br />
luminescent path.<br />
10031790 TQAS - TOTAL QUALITY AND AIRCRAFT A310-3<strong>04</strong> Cabin Modification to Full EconomyCabin<br />
Reconfiguration from a 18C/184Y seats<br />
configuration to a 224Yseats configuration<br />
10<strong>01</strong>4421 TRANSAIRCO S.A. <strong>EASA</strong>.A.S.<strong>01</strong>742 FOCA STC 23-15-0<strong>01</strong> ISS2 PILATUS PC-12<br />
PILATUS PC-12/45<br />
PILATUS PC-12/47<br />
10<strong>01</strong>4671 TRANSAIRCO S.A. <strong>EASA</strong>.A.S.02831 PILATUS PC-12<br />
PILATUS PC-12/45<br />
PILATUS PC-12/47<br />
10<strong>01</strong>4751 TRANSAIRCO S.A. <strong>EASA</strong>.A.S.02936 MYSTERE FALCON 900 MODE S TRANSPONDER WITH<br />
ENHANCED SURVEILLANCE CAPACITY<br />
10<strong>01</strong>4789 TRANSAIRCO S.A. <strong>EASA</strong>.A.S.02990 FOCA STC 31-31-05 FAN JET<br />
FAN JET FALCON SERIES<br />
C,D,E,F<br />
MYSTERE FALCON 20 C5, D5,<br />
E5<br />
MYSTERE FALCON 20 F5<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
22.02.2<strong>01</strong>0<br />
Limited to MSN 573 Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
14.09.2<strong>01</strong>0<br />
Aircell 3100 Iridium SATCOM Installation This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
07.09.2006<br />
F.D.S.FD932 DVD Player Installation None 08.11.2006<br />
AVIONICA mini QARAVIONICA mini QUAR<br />
P/NNote: This STC supersedes FOCA STC<br />
FOCA 31-31-05, dated 09.09.2002<br />
10<strong>01</strong>5474 TRANSAIRCO S.A. <strong>EASA</strong>.IM.A.S.<strong>01</strong>226 - MYSTERE FALCON 50 Replacement of existing HONEYWELL MK II<br />
GPWS and COLLINS MFD-85 with a<br />
UNIVERSAL Terrain Awareness and Warning<br />
system (TAWS) and a UNIVERSALMFD-640<br />
This STC is approved only for those Mystere<br />
Falcon MF-900 aircraft excluding Falcon 900C<br />
version and incorporating at least:• Dual<br />
Collins TDR-94D Mode “S” ATC Transponders<br />
compliant with Elementary Surveillance and•<br />
Single or dual GPS receiver.Compa<br />
1. Valid for Dassault Aviation:- Fan Jet Falcon<br />
Basic- Fan Jet Falcon Series C, D, E, F-<br />
Mystère-Falcon 20 Series C5, D5, E5, F52.<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs<br />
1. This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph "Description".<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
10<strong>01</strong>5621 TRANSAIRCO S.A. <strong>EASA</strong>.IM.A.S.<strong>01</strong>573 - FALCON 20 Incorporation of Mode S EHS capability<br />
installer.2. Limited to F<br />
1. Limited to Falcon 20 S/N 237; 257; 307;<br />
341; 389; 4262. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations sh<br />
10<strong>01</strong>5700 TRANSAIRCO S.A. <strong>EASA</strong>.IM.A.S.<strong>01</strong>688 - PC-12, PC-12/45 Structural installation of Honeywell KA-815<br />
TCAS I Antennas<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 451/<strong>462</strong><br />
13.02.2007<br />
23.<strong>01</strong>.2007<br />
19.08.2005<br />
14.09.2006<br />
09.03.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5753 TRIAD INTERNATIONAL MAINTENANCE <strong>EASA</strong>.IM.A.S.<strong>01</strong>786 FAA STC ST03200AT BOEING 737-800 Complete interior reconfiguration in accordance<br />
with TIMCO Aviation Services, Inc MDL, report<br />
<strong>04</strong>T1<strong>01</strong>L500, revision “D”, dated December 08,<br />
2005, or later <strong>EASA</strong> approved revision<br />
20.07.2006<br />
10029274 TRIUMPH INSTRUMENTS BURBANK Inc. <strong>EASA</strong>.IM.A.S.03255 REV. 1 FAA STC ST02236LA CL-600-2B19, CL-600-2C10<br />
CL-600-2D15, CL-600-2D24<br />
Triumph Replacement Hydraulic Accumulators. None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.03.2<strong>01</strong>0<br />
10034472 TRIUMPH INSULATION SYSTEMS, L.L.C. REV. 1 FAA STC ST02<strong>01</strong>3LA B767-200 Insulation Blanket Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
11.<strong>04</strong>.2<strong>01</strong>1<br />
10026913 TROLLTUNE CORPORATION P-<br />
<strong>EASA</strong>.IM.A.S.03179<br />
FAA STC SA03608AT 182P AND 182Q (SEE<br />
ATTACHMENT)<br />
Increased Maximum Gross Takeoff Weight<br />
(MGTOW). This STC allows a 150 lbIncrease<br />
in MGTOW from 2950 to 3100 lbs. There is no<br />
change to themaximum landing weight of 2950<br />
lbs.<br />
10<strong>01</strong>3953 TROYES AVIATION <strong>EASA</strong>.A.S.0<strong>04</strong>93 REV. 2 CESSNA F177-RG Installation of sliding panel on the front left and<br />
right door windows amd rear right<br />
window.Addition of new S/N 087 F-BURU on<br />
None. 1. Prior to installation of this modification 21.08.2009<br />
the installer mustdetermine that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product.2. The insta<br />
Limited to F177RG S/N <strong>01</strong>12, 0065 and S/N<br />
087 F-BURU.<br />
10<strong>01</strong>3954 TROYES AVIATION <strong>EASA</strong>.A.S.0<strong>04</strong>94 REV. 3 CESSNA F177RG<br />
STC <strong>EASA</strong>.A.S.0<strong>04</strong>93.<br />
Installation of a camera sight door under the Applicability F177RG S/N <strong>01</strong>12, 0065, 103, The approval holder shall fulfil the 29.03.2<strong>01</strong>0<br />
fuselage.Addition of new aircraft to STC<br />
<strong>EASA</strong>.A.S.0<strong>04</strong>94 Revision 2.<br />
087 F-BURU and S/N 51 F-HBAG.<br />
obligations of Part 21,Paragraph21.A109.<br />
10<strong>01</strong>4266 TROYES AVIATION <strong>EASA</strong>.A.S.<strong>01</strong>495 REV. 3 REIMS CESSNA F177-RG Provisions for three attachments in the right Limited to: F177RG S/N <strong>01</strong>12, 0065, 103, 153 1) Prior to installation of this modification 06.10.2009<br />
side of the instrumentpanel in accordance with and 087 F-BURU; S/N 051D-EMEN<br />
the installer mustdetermine that the<br />
the STC <strong>EASA</strong>.A.S.<strong>01</strong>495R1: adjunction of a<br />
interrelationship between this modification<br />
newserial number "S/N 051"<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. 2) The inst<br />
10<strong>01</strong>4285 TROYES AVIATION <strong>EASA</strong>.A.S.<strong>01</strong>522 CESSNA 340A FAM n° 47 - Limitation of MTOW to 2699 kg s/n 340A-<strong>04</strong>51 23.02.2006<br />
10<strong>01</strong>4642 TSA TRANSAIRCO S.A. <strong>EASA</strong>.A.S.02792 PILATUS PC-12<br />
PILATUS PC-12/45<br />
PILATUS PC-12/47<br />
AFT Refreshment Galley and OvenRefer to<br />
master certification documents list TS PC12-<br />
25.30.02MCL<br />
10<strong>01</strong>5718 TTF AEROSPACE, LLC <strong>EASA</strong>.IM.A.S.<strong>01</strong>716 FAA STC ST00231BO BOEING 737-800 Installation of Yokohama forward Lavatory E<br />
and Yokohama aft lavatory K and attendant<br />
seat in accordance with TTF Aerospace MDL<br />
TTF-05T026-<strong>01</strong> Rev B, dated February 24,<br />
2006<br />
1. Limited to serial number 321 and later;2.<br />
Galley power and microwave oven use is not<br />
approved during take-off and landing phases of<br />
flight and during emergency or abnormal<br />
procedures;3. When aft refreshment galley is<br />
installed, the luggage area<br />
Limited to installation on Boeing 737-800 S/N<br />
28325, 3<strong>04</strong>70, 32277 and 32278<br />
only.Installation of FAA STC <strong>01</strong>533LA<br />
requiredInstruction for airworthiness 9ICA, TTF<br />
Aerospace Document TTF-05T026-18 revision<br />
new, dated February 13, 2006 or later FAA<br />
accepted re<br />
10<strong>01</strong>6453 TTF AEROSPACE, LLC <strong>EASA</strong>.IM.A.S.02799 FAA STC ST<strong>01</strong>195SE BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
Installation of a Reinforced Flight Deck Door. 16.06.2008<br />
10<strong>01</strong>5250 TUIFLY GmbH <strong>EASA</strong>.A.S.03692 B737-800 Cabin Configuration Change to 52BC plus 6YC Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
05.11.2008<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 452/<strong>462</strong><br />
28.02.2008<br />
21.11.2006<br />
06.<strong>04</strong>.2006
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>5258 TUIFLY GmbH <strong>EASA</strong>.A.S.03711 B737-700, B737-800 Installation of Water Boiler P/N: 666<strong>01</strong>-1<strong>01</strong>- 1. Prior to installation of this modification the<br />
15.<strong>04</strong>.2009<br />
00<strong>01</strong> as an alternative to Coffee Maker P/N: installer must determine that the<br />
64753-0<strong>01</strong>-003.<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>7090 TURBOMECA <strong>EASA</strong>.R.S.00753 REV. 2 AS350B, B1, BA, B2, B3 Installation of Sand Filter (Engine air inlet None. Prior to installation of this modification it 17.06.2<strong>01</strong>0<br />
EC130B4<br />
protection)Notes: Revision 1 to this STC<br />
must be determined thatthe<br />
reflects:1. the transfer of <strong>EASA</strong> STC<br />
interrelationship between this modification<br />
<strong>EASA</strong>.R.S.00753 from CGTM to<br />
and any other previouslyinstalled<br />
Turbomeca;2. updates of the Associated<br />
modification and/ or repair will introduce<br />
Technical Documentation package<br />
no adverse effectupon the airworthiness<br />
followingDOA minor changes<br />
of the product.<br />
10<strong>01</strong>7287 TURBOMECA <strong>EASA</strong>.R.S.<strong>01</strong>536 DGAC FRANCE STC NO 84-SF-1122 EUROCOPTER FRANCE AS 350<br />
B<br />
EUROCOPTER FRANCE AS 350<br />
B1<br />
EUROCOPTER FRANCE AS 350<br />
B2<br />
EUROCOPTER FRANCE AS 350<br />
Installation of HESIS thermic camera system<br />
manufactured by SAGEM<br />
1. Only Turbomeca personal or specifically<br />
trained mechanics are allowed to install fixed<br />
parts and components of the HESIS kit.2. Prior<br />
to installation of this modification the installer<br />
must determine that the interrelationship<br />
between this modificati<br />
10<strong>01</strong>6861 TYLER CAMERA SYSTEMS <strong>EASA</strong>.IM.R.S.<strong>01</strong>237 REV. 1 FAA STC SR<strong>01</strong>272LA<br />
BA<br />
R44, R44 II Installation of Tyler ROB-0<strong>01</strong> Universal Mount Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>.12.2007<br />
10<strong>01</strong>6594 U.S. TECHNICAL CONSULTANTS, INC. <strong>EASA</strong>.IM.A.S.03005 FAA STC ST02409CH-D DC-9-83 (MD-83)<br />
DC-9-87 (MD-87)<br />
FAA STC No. ST02409CH-D “NavAero t-<br />
BagC22 Electronic Flight Bag”<br />
10029398 U.S. TECHNICAL CONSULTANTS, INC. FAA STC ST02161LA B757-200, B757-300 Installation of navAero t.BagC2 Electronic<br />
Flight Bag<br />
10033897 U.S. TECHNICAL CONSULTANTS, INC. FAA STC ST02320LA B767-200, -300, -300F, -400ER Installation of Class 2 Electronic Flight Bag<br />
(EFB) provisions.<br />
10<strong>01</strong>4236 UNI AIR ENTREPRISE <strong>EASA</strong>.A.S.<strong>01</strong>399 CORVETTE SN 6<strong>01</strong> SN 028 &<br />
008<br />
10<strong>01</strong>3932 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.00305 REV. 1 CITATION 550 - Installation of Digital Data Recorder<br />
SSUFDR Allied Signal (TSO-C124) in<br />
accordance with Master Data List No.<br />
UAE.<strong>01</strong>1.02 Issue0 dated 16 August 20<strong>04</strong>, or<br />
later <strong>EASA</strong> approved Revision.- Installation<br />
of a Digital Flight Data Recorder.Note:<br />
10<strong>01</strong>40<strong>04</strong> UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.<strong>01</strong><strong>04</strong>1 BEECH C90A<br />
Revision 1<br />
Installation of a Concorde RG-380E Sealed<br />
Lead Acid Battery.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
05.<strong>01</strong>.2009<br />
16.<strong>01</strong>.2009<br />
Not Applicable Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.03.2<strong>01</strong>0<br />
Any equipment that is connected to the Prior to installation of this modification it 17.02.2<strong>01</strong>1<br />
electrical power provisionscertified by this STC must be determined thatthe<br />
must be tested in accordance with<br />
interrelationship between this modification<br />
therequirementsof navAero Inc.’s Electrical and and any other previouslyinstalled<br />
EnvironmentalSubstantiation for Lithium based modification and/ or repair will introduce<br />
battery in navAero t-bag C22 EFB SystemD no adverse effectupon the airworthiness<br />
of the product.<br />
Deviation to SB 34-12 replacement of mount 1. This STC applies to MSN 028 and MSN 008<br />
C24-C25 in accordance with MDL UAE 008.05 only.2. This STC is approved only for the<br />
Rev. 1 dated 8/07/2005. Installation of product configuration as defined in the<br />
horizontal mount between frames C24 and approved design data referred to in the<br />
C26 instead of vertical one between frames paragraph "Description". Compatibility with<br />
C24 and C25.<br />
other aircraft/engine configurations shall be<br />
1. AFM Supplement UAE No. 46 Revision 0<br />
dated 16 August 20<strong>04</strong> or later <strong>EASA</strong> approved<br />
revision is a required part of this STC.2. This<br />
STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraph<br />
1. Supplemental Airplane Fight Manual No<br />
UAE/52 (French language) must be used with<br />
this modification.2. Modification limited to<br />
Beechcraft C90A s/n LJ-1361.3. This STC is<br />
approved only for the product configuration as<br />
defined in the approved design data r<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 453/<strong>462</strong><br />
25.07.2005<br />
06.02.2009<br />
11.<strong>04</strong>.2005
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>01</strong>4805 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03008 FALCON 20 CABIN INTERIOR REFURBISHMENT This STC is approved only for Mystere Falcon<br />
20-E5 aircraft serial number 302.Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modification will<br />
15.05.2007<br />
10<strong>01</strong>4824 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03037 BEECH 300<br />
BEECH 300C<br />
10<strong>01</strong>4825 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03038 REV 1 BEECH 300<br />
BEECH 300C<br />
FMS upgrade from UNS-1K to UNS-1K+ for<br />
compliance with P-RNAV<br />
Dual Installation of Collins TDR-94D with CTL-<br />
92E for compliance with Enhanced<br />
Surveillance capability.<br />
This change is limited to the following serial<br />
numbersB300: S/N FL-111 thru FL-380;<br />
and FL-382B300C: S/N FM-9 thru FM-11;<br />
and FN-2 and subsequentThis change is<br />
limited to the configuration of aircraft /<br />
equipment type as listed under Item I – ‘De<br />
This change is limited to the following serial<br />
numbers:B300: S/N FL-111 thru FL-380; and<br />
FL-382B300C: S/N FM-9 thru FM-11; and FN-<br />
2 and subsequent.This change is limited to the<br />
configuration of aircraft/equipment type as<br />
listed under Item I - Description D<br />
10<strong>01</strong>4853 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03077 BEECH B300 Installation of a Digital Flight Data Recorder 1. This STC is limited to the following<br />
S/N:Beech B300 S/N FL-111 through FL-380,<br />
FL-382Beech B300C S/N FM-9 through FM-<br />
11, FN-2 and after2. Prior to installation of<br />
this modification the installer must determine<br />
that the interrelationship between th<br />
10<strong>01</strong>4875 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03100 Upgrade of ATC transponders for elementary<br />
surveillance (Mode S). To add elementary<br />
surveillance functionality in the ATC<br />
transponder and repalce KFS-578A control box<br />
by PS-578 to comply the ECAC airspace<br />
requirements in accordance with Master Data<br />
List MD<br />
10<strong>01</strong>4951 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03215 MYSTERE FALCON 50 Antenna and Cables installation provisions for<br />
satellite communication system.<br />
1. STC nor applicable to Falcon 50EX<br />
version aircraft;2. Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously installed modification<br />
will introduce no ad<br />
Design change applicable to Mystere Falcon<br />
20 aircraft serial number 311.<br />
Design change applicable to Mystere Falcon<br />
20 aircraft serial number 311.<br />
10<strong>01</strong>5156 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03523 MYSTERE FALCON 20 Installation of a forward partition door between<br />
entry area and cabin<br />
10<strong>01</strong>5172 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.03546 MYSTERE FALCON 20 Installation of a passenger entertainment audio<br />
and video system in the cabin.<br />
10<strong>01</strong>5241 UNI AIR ENTREPRISE SAS P-<strong>EASA</strong>.A.S.03669 REV. 1 MYSTERE FALCON 50 (MF50) Iridium telecommunication system<br />
Installation limited to those Mystere Falcon 50<br />
installationThis change is a revision of STC (MF50) aircraftpreviously modified i.a.w. Uni<br />
<strong>EASA</strong>.A.S.03669.This change allows Air Enterprise S.A.S. Supplemental<br />
installation of an alternative P /N of<br />
TypeCertificate (STC) "Antenna and cables<br />
transceiverand handsets as well as alternative installation provisions forsatellite<br />
location.<br />
communication system" approved under<br />
<strong>EASA</strong>.A.S.03<br />
10031744 UNI AIR ENTREPRISE SAS MYSTERE FALCON 20 Enhanced Mode "S" compliance<br />
upgrade.Transponder and FMS software<br />
upgrade to meet the requirements for mode"S"<br />
Enhanced Surveillance downlink parameters.<br />
10031773 UNI AIR ENTREPRISE SAS <strong>EASA</strong>.A.S.00307 REV. 1 CESSNA 550 (CITATION II) Installation of Honeywell EGPWS Mark VIIIThe<br />
STC has been revised to implement the<br />
alternative EGPWS computer P/N965-1210-<br />
020 and the alternative EGPWS Configuration<br />
Module P/N700-1710-020.<br />
The approval holder shall fulfill the<br />
obligations of Part 21,Paragraph<br />
21A.109. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ o<br />
30.<strong>04</strong>.2007<br />
11.09.2007<br />
06.06.2007<br />
06.09.2007<br />
18.06.2008<br />
19.05.2008<br />
19.05.2008<br />
13.08.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.09.2<strong>01</strong>0<br />
Limited to: S/N 550-00<strong>01</strong> through 550-0733<br />
The maintenance tasks referred in Supplement<br />
to Cessna 550 MaintenanceManual ref.<br />
EGPWS UAE No 4 Revision 6 are required.<br />
The audio declutterfunction must be disabled.<br />
Prior to installation of this modification it 10.09.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 454/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037035 UNI AIR ENTREPRISE SAS 200 Installation of gear override and steep This STC is applicable to aircraft s/n BY-91. Prior to installation of this modification it 26.10.2<strong>01</strong>1<br />
approach switches on TWASTW-950.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10038465 UNI AIR ENTREPRISE SAS MF50 Enhanced Mode "S" compliance upgradeThis<br />
modification consists in the upgrade from mode<br />
"S" transponderelementary surveillance to<br />
mode "S" transponder enhanced surveillance<br />
tomeet the European airspace mandate for<br />
mode "S" EHS downlink parameters.<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.02.2<strong>01</strong>2<br />
10039277 UNI AIR ENTREPRISE SAS MF 20GF Installation of Patch Iridium Antenna. None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
23.<strong>04</strong>.2<strong>01</strong>2<br />
10<strong>04</strong>1337 UNI AIR ENTREPRISE SAS MF900 Installation of Iridium Satcom System ICS-<br />
120B.<br />
None. None. 07.09.2<strong>01</strong>2<br />
10<strong>01</strong>4173 UNIAIR <strong>EASA</strong>.A.S.<strong>01</strong>306 BEECH C90A Compliance with the B-RNAV requirements for 1. This STC is limited to aircraft s/n LJ-1303.2.<br />
20.07.2005<br />
the GPS System Trimble 2000 Approach + GPS System Trimble 2000 Approach +<br />
installation already approved with IFR<br />
priviledge.<br />
10<strong>01</strong>4237 UNIAIR <strong>EASA</strong>.A.S.<strong>01</strong>400 CORVETTE SN 6<strong>01</strong> Deviation to SB 34-12 - replacement of ADF in 1. This STC is limited to S/N 028 and S/N<br />
accordance with MDL UAE <strong>01</strong>0.05 rev 1 dated 0082. This STC is approved only for the<br />
28.07.2005<br />
11/07/05.Installation of ADF60 according to product configuration as defined in the<br />
option 85 aerospatiale instead of ADF approved design data referred to in the<br />
206.Installation of option 85 on second ADF paragraph "Description". Compatibility with<br />
position instead of first position.Idmode other aircraft/engine configurations shall be<br />
dete<br />
10<strong>01</strong>5036 UNIAIR <strong>EASA</strong>.A.S.03349 REV. 1 MYSTERE FALCON 50 Installation of 220 VAC Electrical Power Supply None The approval holder shall fulfil the 10.<strong>04</strong>.2<strong>01</strong>2<br />
and Distribution inCabinNote: This STC<br />
obligations of Part 21,<br />
constitutes the extension of the approval<br />
Paragraph21.A109. Prior to installation of<br />
granted under<strong>EASA</strong> STC ref.<br />
this modification it must be determined<br />
<strong>EASA</strong>.A.S.03349 dated 19 May, 2008, to a<br />
thatthe interrelationship between this<br />
secondconfiguration.<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10<strong>01</strong>5037 UNIAIR <strong>EASA</strong>.A.S.03350 REV. 1 MYSTERE FALCON 50 Installation of an In-Flight Passenger<br />
STC limited to those Mystere Falcon 50 The approval holder shall fulfil the 10.<strong>04</strong>.2<strong>01</strong>2<br />
Entertainment System in Cabin.Note: This STC (MF50) aircraft on which UniAirSTC 10<strong>01</strong>5036 obligations of Part<br />
constitutes the extension of the approval Revision 1 "Installation of 220 VAC Electrical 21,Paragraph21.A109.Prior to installation<br />
granted under<strong>EASA</strong> STC ref.<br />
Power Supplyand Distribution in Cabin" has of this modification it must be determined<br />
<strong>EASA</strong>.A.S.03350 dated 19 May, 2008, to a been embodied.<br />
thatthe interrelationship between this and<br />
secondconfiguration.<br />
any other previously installedand/ or<br />
repair will introduce no adverse<br />
10027898 UNIAIR P-<strong>EASA</strong>.A.S.03693 MF900 Installation of a Flight Data Recorder This design change is applicable on the basic<br />
Mystere Falcon 900aircraft, as per MF900<br />
designation on <strong>EASA</strong> TCDS.A.062<br />
10031335 UNIAIR <strong>EASA</strong>.A.S.00306 REV. 1 CESSNA CITATION II 550 Installation of a multi-functions display 1. AFM Supplement UAE No 47 issue 1<br />
Honeywell type KMD-850 todisplay information Revision 1 dated 14 September 20<strong>04</strong>or later<br />
form the following systems:,,- ACAS II (CAS <strong>EASA</strong>-approved revision, is a required part of<br />
67A),,- EGWPS (MK VIII) and,,- Weather radar this STC2. Or AFM Supplement UAE No 15<br />
(ART 2000 or RS-181A)<br />
issue 2 revision 2 (for MSN 0609) orrevision 5<br />
(for MSN <strong>01</strong>90) or later <strong>EASA</strong>-approved<br />
revisio<br />
Prior to installation of this modification it 13.11.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Prior to installation of this modification the 02.06.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 455/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>2498 UNIAIR B300 Installation of 230 V AC - 50 Hz electrical If the holder agrees to permit another person to The installation of this modification by 05.12.2<strong>01</strong>2<br />
distribution on aircraft, toallow passengers to use this certificate toalter the product, the third persons is subject towritten<br />
plug personal electronic devices. According holder shall give the other person<br />
permission of the approval holder and<br />
toSB-UAE-003-12-0<strong>01</strong>.<br />
writtenevidence of that permission.<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>01</strong>5829 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.<strong>01</strong>918 FAA STC ST00839LA BOMBARDIER DHC-8-100 Installation of GPS Landing System in The approval is limited to<br />
14.07.2006<br />
SERIES<br />
deHavilland DHC-8 aircraft(Validation of FAA Bombardier/deHavilland DHC-8 100 series<br />
STC ST00839LA amended 27/02/2006) aircraft<br />
10<strong>01</strong>6206 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02450 FAA STC ST<strong>01</strong>879LA BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Universal Avionics Vision-1tm Synthetic<br />
3A<br />
System installed in Canadair Challenger CL600<br />
Series.<br />
10<strong>01</strong>6253 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02531 REV. 2 FAA STC ST02070 LA BOMBARDIER CL-600-1A11 (CL- Universal Avionics UNS-1Fw with embedded<br />
600<br />
WAAS. MDL -4 Config (TripleUNS-1Fw FMS<br />
BOMBARDIER CL-600-2A12 (CL- with P/N 10709 #3 GPS-WAAS/Sirius<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Antenna)<br />
10<strong>01</strong>6279 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02568 FAA STC ST<strong>01</strong>763CH-D BOMBARDIER CL-600-1A11 (CL- Installation of Universal Avionics EFI-890R Flat<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Panel Displays and MFD-640.<br />
10<strong>01</strong>6375 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02698 FAA STC ST<strong>01</strong>640LA BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Installation of Universal Avionoics Radio<br />
3A<br />
Control Units (RCU)<br />
10<strong>01</strong>6614 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.03<strong>04</strong>0 REV. 1 FAA STC ST02<strong>01</strong>2LA CL-600-1A11 (CL-600)<br />
CL-600-2A12 (CL-6<strong>01</strong>)<br />
CL-600-2B16<br />
Installation of Universal Avionics Application<br />
Server Unit (ASU). Minorrevision to ASU FAA<br />
STC ST02<strong>01</strong>2LA, ESTC <strong>EASA</strong>.IM.A.S.03<strong>04</strong>0<br />
None Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
23.11.2007<br />
06.07.2009<br />
23.11.2007<br />
Restricted to ASN 5<strong>04</strong>2. 03.06.2008<br />
Restricted to the following MDL Configurations:-<br />
3 Application Server Unit (ASU) (ETSO<br />
<strong>EASA</strong>.IM.210.708) with Dual CursorControl<br />
Panels (CCP) (ETSO <strong>EASA</strong>.IM.210.708)<br />
displayed on EFI-890RNavigation Display<br />
(ETSO <strong>EASA</strong>.IM.210.344).-4 Application<br />
Server Unit (AS<br />
10<strong>01</strong>6615 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.03<strong>04</strong>1 FAA STC ST<strong>01</strong>303LA BOMBARDIER CL-600-1A11 (CL- Installation of Universal Avionics UNS-1F/L and 1. Restricted to the following configurations:-3<br />
600<br />
optional UniLink communication system Config: UL-7<strong>01</strong> with SCN 22.X-4 Config: UNS-<br />
BOMBARDIER CL-600-2A12 (CL-<br />
1F with SCN 802.X and A702 Maps2. Prior to<br />
6<strong>01</strong><br />
installation of this modification the installer must<br />
BOMBARDIER CL-600-2B16<br />
determine that the interrelationship between<br />
this modification andan<br />
10<strong>01</strong>6616 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.03<strong>04</strong>2 FAA STC ST<strong>01</strong>141LA BOMBARDIER CL-600-1A11 (CL- Installation of Universal Avionics Terrain<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Awareness Warning System (TAWS)<br />
10<strong>01</strong>4248 UUDS AERO <strong>EASA</strong>.A.S.<strong>01</strong>470 REV. 2 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
1. Restricted to the following configuration:-4<br />
Config: Terrain Awareness and Warning<br />
System (TAWS) operating software SCN 11.X<br />
(ETSO <strong>EASA</strong>.IM.21O.<strong>01</strong>70) displayed on MFD-<br />
640 (ETSO <strong>EASA</strong>.IM.21O.905)2. Prior to<br />
installation of this modification the installer m<br />
Prior to installation of this modification the 06.07.2009<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
07.<strong>01</strong>.2009<br />
07.<strong>01</strong>.2009<br />
Modification of STC <strong>EASA</strong>.A.S.<strong>01</strong>470 to allow None Prior to installation of this modification it 03.11.2<strong>01</strong>0<br />
the baby to sit down in thebassinet fixed on the<br />
must be determined thatthe<br />
partitions or under the hatracks.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product. The in<br />
10034806 V. KELNER PILATUS CENTRE REV. 1 TCCA STC SA02-80 PC-12, PC-12/45, PC-12/47 Installation Feather Inhibit System None The approval holder shall fulfil the 18.10.2<strong>01</strong>1<br />
PC-12/47E<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10039278 VAN HORN AVIATION, L.L.C. 206B, L, L1, L3, L4 Installation of Replacement Tail Rotor Blades When antenna holder PP-10-A6<strong>01</strong> is installed Prior to installation of this modification it 23.<strong>04</strong>.2<strong>01</strong>2<br />
VNE is limited to 120 kts;When rack PP-10- must be determined thatthe<br />
A421 is installed, carriage of passengers in interrelationship between this modification<br />
front seatsis prohibited;When racks PP-10- and any other previouslyinstalled<br />
A4<strong>01</strong>c or PP-A461 are installed, a maximum of modification and/ or repair will introduce<br />
2passengers in rear seats is permitted no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 456/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10028237 VAN RIEMSDIJK ROTTERDAM B.V. P-<strong>EASA</strong>.A.S.03898 B747-400F NXE-0506 Special Cargo Container 125” X The location of the cargo container is limited to None. 10.12.2009<br />
196” with part number 136.020.<br />
the positionsmentioned in the W&B<br />
Control and Loading Manual<br />
supplementRRM510.<br />
10031360 VAN RIEMSDIJK ROTTERDAM B.V. REV. 3 B747-200F/-400F/-400BCF/-8F Approval of NXE-0506 Special Cargo The location of the cargo container is limited to Prior to installation of this modification it 08.08.2<strong>01</strong>2<br />
Container 125" X 196" with PartNumber the positionsmentioned in the W&B must be determined thatthe<br />
136.020 and RZX-0506 Special Cargo Control and Loading Manual Supplement interrelationship between this modification<br />
Container 125" X 196" withPart Number RRM510(B747-400F/-400BCF), and any other previouslyinstalled<br />
136.050 for use in B747 series Freighters RRM520 (B747-200F) and RRM544 (B747- modification and/ or repair will introduce<br />
8F)<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032842 VAN RIEMSDIJK ROTTERDAM B.V. REV. 1 B747-200F, 400F RGX-0517 Special Cargo Container 238,5" x<br />
96" with Part number136.080-000<br />
10<strong>01</strong>5733 VENTURA AEROSPACE , Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>755 REV 1 FAA STC ST<strong>01</strong>806LA BOEING 737-400 Installation of a 9g Cargo Barrier according to<br />
FAA STC ST<strong>01</strong>806LARevision to existing<br />
<strong>EASA</strong> STC <strong>EASA</strong>.IM.A.S.<strong>01</strong>755 (737-400<br />
added).<br />
10038866 VENTURA AEROSPACE , Inc. FAA STC ST02115LA B757-200 Installation of 9g Forward Cargo Barrier on the<br />
Main Deck<br />
10<strong>01</strong>6125 VIDEO TECHNOLOGY SERVICES, Inc. <strong>EASA</strong>.IM.A.S.02318 FAA STC ST<strong>01</strong>998NY BOEING 767-300 1. Configuration 1: Installation of LCD Monitor<br />
System2. Configuration 2: Installation of LCD<br />
Monitor System<br />
10027220 VIDEO TECHNOLOGY SERVICES, Inc. FAA STC ST02720NY B767-200, 300 Installation of Digital Video Player (DVP) on a<br />
B767 a/c<br />
10036188 VIDEO TECHNOLOGY SERVICES, Inc. FAA STC ST03006NY A340-200/300/600 Title: LCD Monitor SystemsDescription:<br />
Installation of LCD Monitors and Digital Player<br />
replacingCRT Monitors and Cassette<br />
Recorders in the same locations using the<br />
samemounting provisions, cables and<br />
connectors.Validation of FAA ST03006NY<br />
dated August 4, 2<br />
The loading limitations of the RGX container Prior to installation of this modification it 24.02.2<strong>01</strong>1<br />
are according to thelimitations in the applicable must be determined thatthe<br />
W&B manuals for the NAS3610 interrelationship between this modification<br />
SizeCode G ULD's<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
1) Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification<br />
andany other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product. The insta<br />
To be installed on a/c converted to a<br />
Combination Passenger/ Freighterby ST<br />
Aerospace Inc, <strong>EASA</strong> STC 10038822.<br />
1. If the holder agrees to permit another<br />
person to use this certificate to alter the<br />
product, the holder shall give the other person<br />
written evidence of that permission.2. The<br />
aircraft must be maintained in accordance with<br />
Video Technology Services,<br />
28.05.2008<br />
Prior to installation of this modification it 20.03.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
05.06.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.09.2009<br />
None. Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
18.08.2<strong>01</strong>1<br />
10<strong>04</strong>2226 VIDEO TECHNOLOGY SERVICES, Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>071 FAA STC ST<strong>01</strong>089NY 767-200, 767-300 23.03.2005<br />
10030509 VIH AEROSPACE Inc. TCCA STC SH09-54 S92A Triple Stacking Litter System<br />
InstallationValidation of TCCA STC SH09-54<br />
Issue 1<br />
None None 21.06.2<strong>01</strong>0<br />
10<strong>04</strong>0358 VIH AEROSPACE Inc. REV. 1 TCCA STC SH08-29 S-92A LHS Crew Bubble Window Installation None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.08.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 457/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032527 VIKING AIR LIMITED TCCA STC SA10-69 DHC-6 SERIES 400 Installation of RW Martin Air Conditioning None Prior to installation of this modification it 12.11.2<strong>01</strong>0<br />
System in accordance withTCCA STC SA10-<br />
must be determined thatthe<br />
69.<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>5333 VISIONSAFE CORPORATION <strong>EASA</strong>.IM.A.S.00354 REV. 6 FAA STC ST00892LA SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of Emergency Vision Assurance<br />
System (EVAS,TM). Change toSTC<br />
<strong>EASA</strong>.IM.A.S.00354 Issue 4, update of relating<br />
approved model listissue 4<br />
10<strong>01</strong>5744 VISIONSAFE CORPORATION <strong>EASA</strong>.IM.A.S.<strong>01</strong>774 FAA STC ST<strong>01</strong><strong>01</strong>2WI BOMBARDIER CL-600-1A11 (CL- Installation of Emergency Vision Assurance<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
BOMBARDIER CL-600-2B19<br />
System (EVAS TM)<br />
10<strong>01</strong>6007 VISIONSAFE CORPORATION <strong>EASA</strong>.IM.A.S.02172 REV. 1 FAA STC ST<strong>01</strong>057W1 BOMBARDIER BD-700-1A10<br />
BOMBARDIER BD-700-1A11<br />
10<strong>01</strong>6<strong>04</strong>5 VISIONSAFE CORPORATION <strong>EASA</strong>.IM.A.S.02216 FAA STC ST00892LA AIRBUS A330-2<strong>01</strong><br />
AIRBUS A330-202<br />
AIRBUS A330-203<br />
AIRBUS A330-223<br />
AIRBUS A330-243<br />
AIRBUS A330-3<strong>01</strong><br />
AIRBUS A330-321<br />
AIRBUS A330-322<br />
AIRBUS A330-323<br />
AIRBUS A330-341<br />
AIRBUS A330-342<br />
AIRBUS A330-343<br />
10<strong>01</strong>6155 VISIONSAFE CORPORATION <strong>EASA</strong>.IM.A.S.02357 FAA STC ST00731LA BOEING 767-200<br />
BOEING 767-300 SERIES<br />
None Prior to installation of this modification the<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
1) Certification Basis: applicable requirements<br />
of a. r. TCDSs2) This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurati<br />
Installation of Emergency Vision Assurance See AFMSPrior to installation of this<br />
System (EVAS) model: 107 STC-191 and 107 modification the installer must determine that<br />
STC-192Validation of FAA STC the interrelationship between this modification<br />
ST<strong>01</strong>057WIMDL: Midcoast Aviation 35- and any other previously installed modification<br />
416G0<strong>01</strong> Rev A or Vision Safe No. 206 Rev will introduce no adverse effect upon the<br />
H or later <strong>EASA</strong> approved revisionsFAA Letter airworthiness of the product.<br />
of SoC:<br />
Installation of Emergency Vision Assurance<br />
System (EVASTM) / <strong>EASA</strong> Validation of FAA<br />
approved Supplemental Type Certificate<br />
ST00892LA. 1. Boeing 737-600, -700, -700C, -<br />
800 and -9002. Airbus 330-2<strong>01</strong>, -202, -203, -<br />
223, 243; Airbus 330-3<strong>01</strong>, -321, 322, -323, -3<br />
Installation of Emergency Vision Assurance<br />
System (EVAS) in accordance with FAA<br />
Approved Vision Safe Corporation Master<br />
Drawing List Number 144, Revision “C” dated<br />
June 9, 1999, or later FAA Approved<br />
Revisions. Vision Safe Corporation Airplane<br />
1003<strong>04</strong>83 VISIONSAFE CORPORATION FAA STC ST00892LA BD100-1A10<br />
Flight Manua<br />
Installation of Emergency Vision Assurance<br />
System (EVAS) Model107STC-235 and<br />
107STC-236 on Bombardier BD-100-<br />
1A10<strong>EASA</strong> Validation of FAA approved<br />
Supplemental Type Certificate ST00892LA<br />
10027778 V-PLANE ENGINEERING GMBH P-<strong>EASA</strong>.A.S.03977 PC-12, PC-12/45, PC-12/47,<br />
PC-12/47E<br />
10028296 V-PLANE ENGINEERING GMBH P-<strong>EASA</strong>.A.S.03978 ERJ170-100STD, LR<br />
ERJ170-200STD, LR<br />
¿ Vision Safe Corporation Instructions for<br />
Continued Airworthiness, Rev. <strong>04</strong>, dated March<br />
2006.<br />
This installation should not be incorporated in<br />
any aircraft unless it is determined that the<br />
interrelationship between this installation and<br />
any previously approved configuration will not<br />
introduce any adverse effect upon the<br />
airworthiness of the aircraft<br />
Heavy Duty Floor Heavy Duty Floor P/N <strong>01</strong>27258 is limited to<br />
from S/N 1<strong>01</strong> to S/N 999except S/N 545 with<br />
configuration in accordance with Bucher<br />
OMME<strong>01</strong>4-16-<strong>01</strong> Heavy Duty Floor P/N<br />
<strong>01</strong>27470 and P/N <strong>01</strong>27470-4<strong>01</strong> is limited to<br />
from S/N10<strong>01</strong> on which configuration in<br />
accordance wit<br />
product. The installati<br />
28.06.2<strong>01</strong>1<br />
22.12.2005<br />
10.02.2009<br />
23.07.2007<br />
30.03.2007<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
17.06.2<strong>01</strong>0<br />
Prior to installation of this modification it 03.11.2009<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
Installation of a removable stretcher None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.12.2009<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 458/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10030059 West Pacific Air, LLC <strong>EASA</strong>.IM.A.S.03276 FAA STC SA<strong>01</strong>156SE B36TC Installation of a Pratt and Whitney PT6A-21 Model B36TC Only The MT propeller option on Compatibility of this modification has only 24.<strong>04</strong>.2<strong>01</strong>2<br />
engine flat rated to 500HPat 2,200 RPM, and the original FAA STC is not <strong>EASA</strong> approved been demonstrated with theKing 150,<br />
Hartzell model HC-E4N-3N/D8292 and HC- atthis time. In order to install the MT propeller Bendix/King 225 and King FFC 200<br />
E4N-3N/D8292(B,K)-2 propellers. This compliance with EU noiseand environmental Automatic Flight ControlSystems. For<br />
certificate has been first issued on 17 May standards must be shown.<br />
operation with other AFCS systems it is<br />
2<strong>01</strong>0 but has beenre-issued for administrative<br />
the installerresponsibility to demonstrate<br />
rea<br />
correct operation. Prio<br />
10<strong>01</strong>5916 WESTERN AVIONICS <strong>EASA</strong>.IM.A.S.02<strong>04</strong>8 TCCA STC SA<strong>04</strong>-26 ISSUE 3 FAIRCHILD SWEARINGEN SA Installation of Honeywell EGPWS Mark VI/VIII<br />
23.10.2006<br />
226 SE<br />
computer, air data computer, circuit breakers,<br />
FAIRCHILD SWEARINGEN SA annunciators, flap position switch, OATprobe,<br />
227 SE<br />
GPS antenna, cockpit speaker and associated<br />
wiring according Transport Canada<br />
Supplemental Type Certification SA<strong>04</strong>-26,<br />
10<strong>01</strong>6<strong>04</strong>1 WESTERN AVIONICS <strong>EASA</strong>.IM.A.S.02210 TCCA STC SA<strong>01</strong>-155 ISSUE 5 DE HAVILLAND CANADA DHC6-<br />
300<br />
10<strong>01</strong>6683 WESTERN AVIONICS <strong>EASA</strong>.IM.A.S.C.<strong>01</strong>00<br />
2<br />
TCCA STC SA03-13; <strong>EASA</strong>.IM.A.S. BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-102<br />
BOMBARDIER DHC-8-103<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
BOMBARDIER DHC-8-311<br />
BOMBARDIER DHC-8-315<br />
10028593 WESTERN AVIONICS TCCA STC SA09-65 DHC-8-102, -103, -106<br />
DHC-8-2<strong>01</strong>, -202<br />
DHC-8-3<strong>01</strong>, -311, -314, -315<br />
10029332 WESTERN AVIONICS REV. 1 TCCA STC SA03-53 ISSUE 1 DHC-8-102, -103, -106,<br />
DHC-8-2<strong>01</strong>, -202, -3<strong>01</strong>,<br />
DHC-8-311, -314, -315<br />
1003<strong>04</strong>55 WESTERN AVIONICS TCCA STC SA03-42 DHC-8-102, DHC-8-103,<br />
DHC-8-106,<br />
DHC-8-2<strong>01</strong>, DHC-8-202,<br />
DHC-8-3<strong>01</strong>, DHC-8-302<br />
10030955 WESTERN AVIONICS TCCA STC SA<strong>04</strong>-96 DHC-8-102/-103/-106<br />
DHC-8-2<strong>01</strong>/-202<br />
DHC-8-3<strong>01</strong>/-302<br />
Installation or Upgrade of a Honeywell MK VI<br />
Enhanced Ground Proximity Warning System<br />
(EGPWS)<br />
Approval is limited to the CIC Air Data<br />
Module.This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraphs "Description" and “Associated<br />
Technical Documentation”. Compatibility with<br />
other air<br />
Installation ((Upgrade)) of a Single or Dual 1. Installation (Upgrade) of the Single or Dual<br />
Universal Avionics UNS-1C+ or UNS-1E Flight Universal Avionics UNS-1+ or UNS-1E Flight<br />
Management System (FMS)<br />
Management System (FMS) is to be done<br />
inaccoedance with Transport Canada<br />
approved Western Avionics Engineering<br />
Orders 71967-4<strong>01</strong> Revision 5 dated 17<br />
September 20<strong>04</strong> (9<br />
Standby Altimeter InstallationTCCA STC SA09- None Special condition H-<strong>01</strong> (ICA-EWIS) not<br />
65, dated 07 August 2009<br />
applicable. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse e<br />
Primus 800 Weather Radar InstallationTCCA<br />
STC SA03-53, Issue 1, dated<br />
28.05.2003.Removal of the limitation for<br />
Instructions for Continued Airworthinesson<br />
Electrical Wiring Interconnection System -<br />
EWIS ICA - in accordancewith Special<br />
Condition H-<strong>01</strong> "Enhanc<br />
Collins Proline II InstallationTCCA STC SA03-<br />
42, Is. 1, dated 8 May 2003<br />
Second ADF InstallationTCCA STC SA<strong>04</strong>-98,<br />
Issue 1 dated 23 December 20<strong>04</strong><br />
A previously approved Weather Radar System<br />
installation is aprerequisite for the installation.<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
12.<strong>01</strong>.2007<br />
20.05.2005<br />
27.<strong>01</strong>.2<strong>01</strong>0<br />
30.11.2<strong>01</strong>0<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
16.06.2<strong>01</strong>0<br />
None Special Condition H-<strong>01</strong> (ICA-EWIS) not<br />
applicable Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will introduce no adverse ef<br />
10037518 WESTERN AVIONICS DHC-6-1/-100/-200/-300 Installation of Garmin GPS 155XL for None Prior to installation of this modification it 02.12.2<strong>01</strong>1<br />
supplemental IFR Navigation in acc.with TCCA<br />
must be determined thatthe<br />
STC SA<strong>01</strong>-93, Issue 1<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 459/<strong>462</strong><br />
16.07.2<strong>01</strong>0
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10<strong>04</strong>0641 WESTERN AVIONICS TCCA STC SA10-1<strong>04</strong> DHC-8-102,DHC-8-103,DHC-8- Installation of a Western Avionics PicoCube Structual and antenna provision in accordance Prior to installation of this modification it 16.07.2<strong>01</strong>2<br />
106<br />
Communications SystemTCCA STC SA10- with the latest applicableissue of <strong>EASA</strong> STC must be determined thatthe<br />
DHC-8-2<strong>01</strong>,DHC-8-202,DHC-8- 1<strong>04</strong>, Issue 2<br />
MOT.21NE2.139 are required.<br />
interrelationship between this modification<br />
3<strong>01</strong><br />
and any other previouslyinstalled<br />
DHC-8-311,DHC-8-314,DHC-8-<br />
modification and/ or repair will introduce<br />
315<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6705 WESTERN PROPELLER (PACIFIC) Ltd. <strong>EASA</strong>.IM.P.S.<strong>01</strong>003 TCCA STC SP96-1 Installation of a Zero Stop Latch AssemblyTo<br />
hold the propeller in zero pitch during engine<br />
start to prevent float and ski equipped aircraft<br />
from surging forward during transition from<br />
feather to beta range. In accordance with the<br />
data contained in Western<br />
10029<strong>04</strong>9 WESTERN PROPELLER (PACIFIC) Ltd. <strong>EASA</strong>.IM.A.S.02907 FAA TC A37CE CESSNA 208A, 208B Installation of a modified McCauley<br />
3GFR34C703 Propeller incorporating aZero<br />
Latch System.<br />
10<strong>01</strong>5762 WIGGINS AIRWAYS, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>798 FAA STC ST00052BO RAYTHEON 1900D Validation of FAA STC ST00052BO<br />
Incorporation of a Rockwell Collins TCAS 94<br />
System (TCAS II) with TTR-921 Change 7.0<br />
R/T, dual TVI-920 TA/RA/VSI Indicators dual<br />
TDR-94D Mode S Transponders, CTL-92T<br />
TCAS Control and CTL-92 Transponder<br />
10029626 WINGLET TECHNOLOGY LLC P-<br />
<strong>EASA</strong>.IM.A.S.02964<br />
Control<br />
CESSNA 750 Installation of Elliptical Winglets on Cessna 750<br />
aircraftRemoval of existing wingtips and<br />
installation of elliptical winglets,structural<br />
reinforcement of the wings and LED position &<br />
anti-collisionlights.<br />
10<strong>01</strong>5353 WIPAIRE Inc. <strong>EASA</strong>.IM.A.S.006<strong>01</strong> REV. 4 FAA STC SA<strong>01</strong>795CH AT-802, AT-802A Installation of Wipaire Model 10000<br />
Amphibious floats per Wipaire Inc.STC<br />
SA<strong>01</strong>795CH, FAA approved July 8, 2<strong>01</strong>1.<br />
10<strong>01</strong>5657 WIPAIRE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>633 FAA STC SA00674CH CESSNA 172 SERIES Installation of Wipaire Model 2100<br />
Amphibian/Seaplane floats on Cessna/Reims<br />
Aviation 172/F172 Models as defined in the<br />
AML.<br />
10<strong>01</strong>5832 WIPAIRE Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>923 FAA STC SA2CH BOMBARDIER DHC-6 SERIES<br />
300<br />
Installation of Wipaire Model 13000<br />
Amphibious Landing Gear.<br />
10<strong>01</strong>5891 WIPAIRE Inc. <strong>EASA</strong>.IM.A.S.02<strong>01</strong>1 FAA STC SA610GL Installation of Wipaire Model 6000 or 6100<br />
Seaplane or Amphibious Floats<br />
10028790 WIPAIRE Inc. FAA STC SA<strong>01</strong>397NY 208, 208B Installation of ERDA, Inc. Executive Seat,<br />
Model 3058 and folding tablesin acc. with FAA<br />
STC SA<strong>01</strong>397NY.<br />
10029642 WIPAIRE Inc. FAA STC SA914NE CESSNA 206 SERIES Installation of Wipaire, Inc. wing tip extensions<br />
in accordance to FAASTC SA914NE.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
23.<strong>01</strong>.2009<br />
none Prior to installation of this modification the 23.07.2009<br />
installer must bedetermined that the<br />
interrelationship between this modification<br />
and anyother previously installed<br />
modification will introduce no adverse<br />
effectupon the airworthiness of the<br />
product. The instal<br />
This STC does not comply with requirements<br />
05.<strong>04</strong>.2006<br />
for Mode S elementary surveillance or for<br />
Mode S enhanced surveillance.Compatibility of<br />
this design change with other previously<br />
approved modifications must be determined by<br />
the installer<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
08.<strong>04</strong>.2<strong>01</strong>0<br />
FAA STC No. SA<strong>01</strong>795CH "Limitations and Prior to installation of this modification it 31.08.2<strong>01</strong>1<br />
Conditions", amended July 8,2<strong>01</strong>1. 1. FAA must be determined thatthe<br />
approved Airplane Flight Manual Supplements: interrelationship between this modification<br />
AT-802A amphibian, dated March 13, 2003 AT- and any other previouslyinstalled<br />
802A landplane, dated October 7, 2003 AT- modification and/ or repair will introduce<br />
802 amphibian, dated September 29, 2008 AT- no adverse effectupon the airworthiness<br />
802<br />
of the product.<br />
1. FAA Supplemental Type Certificate<br />
SA332GL is required for models 172I, 172J,<br />
172K and 172L when installed in accordance<br />
with Wipaire Drawing 10D1-6<strong>01</strong>2.2. FAA<br />
Supplemental Type Certificate SA332GL is<br />
optional for models 172M, 172N and 172P<br />
when installed<br />
Restricted to Amphibious or Seaplane<br />
Operation for Aircraft with PT6-27 Engines<br />
only.<br />
21.06.2006<br />
10.10.2007<br />
20.06.2006<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
09.02.2<strong>01</strong>0<br />
Placard "VNE = 165 Knots" is required with this Prior to installation of this modification it 08.<strong>04</strong>.2<strong>01</strong>0<br />
installation.<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 460/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10029679 WIPAIRE Inc. FAA STC SA1470GL 1) CESSNA 206H, T206H Installation of right front cabin door in None Prior to installation of this modification it 12.<strong>04</strong>.2<strong>01</strong>0<br />
2) CESSNA 206, P206, P206A, accordance with Wipaire, Inc.installation<br />
must be determined thatthe<br />
P206B, P206D, P206E, U206, drawing number 3D1-11<strong>01</strong><br />
interrelationship between this modification<br />
TP206C, TP206D, TU206C,<br />
and any other previouslyinstalled<br />
TU206D<br />
modification and/ or repair will introduce<br />
TU206E, TU206F, TU206G<br />
no adverse effectupon the airworthiness<br />
U206A, U206B, U206C, U206D,<br />
U206E, U206F, U206G, TP206A,<br />
of the product.<br />
10030272 WIPAIRE Inc. FAA STC SA00059WI CESSNA 208, 208B Installation of the Wipaire Single Point Fueling None Prior to installation of this modification it 08.06.2<strong>01</strong>0<br />
System on Cessna 208i.a.w. FAA STC<br />
must be determined thatthe<br />
SA00059WI<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10031133 WIPAIRE Inc. FAA STC SA02808CH DHC-6-200, -300 Installation of nine passenger executive seating<br />
system in accordancewith FAA STC<br />
SA02808CH<br />
10032352 WIPAIRE Inc. P-<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>058<br />
FAA STC SA<strong>01</strong>916CH AIR TRACTOR AT-802, AT-802A Installation of vortex generators. Installation of<br />
Wipaire stallimprovement array in accordance<br />
with Wipaire installation drawing No.7A1-4407<br />
Revision B, dated April 27,2<strong>01</strong>0 for the AT-<br />
802A model andinstallation drawing No.<br />
10<strong>04</strong>245, Revision B, dated April<br />
10<strong>04</strong>1960 WIPAIRE Inc. FAA STC SA1311GL CESSNA 208 Modification of Cessna 208 in accordance with<br />
FAA STC SA1311GL:1) Installation of Wipaire<br />
Model 8000 Amphibian/Seaplane floats or2)<br />
Installation of Wipaire Model 8750<br />
Amphibian/Seaplane floats andinstallation of<br />
vortex generators iaw. Wipaire STC SA270CH<br />
(<br />
10<strong>01</strong>5702 WORLDWIDE AIRCRAFT SERVICES Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>69 REV. 1 AEROSPATIALE ATR 42-200<br />
AEROSPATIALE ATR 42-300<br />
AEROSPATIALE ATR 42-320<br />
AEROSPATIALE ATR 42-500<br />
AEROSPATIALE ATR 72-1<strong>01</strong><br />
AEROSPATIALE ATR 72-102<br />
AEROSPATIALE ATR 72-2<strong>01</strong><br />
AEROSPATIALE ATR 72-202<br />
AEROSPATIALE ATR 72-211<br />
AEROSPATIALE ATR 72-212<br />
AEROSPATIALE ATR 72-212A<br />
10<strong>01</strong>5808 WORLDWIDE AIRCRAFT SERVICES Inc. <strong>EASA</strong>.IM.A.S.<strong>01</strong>877 FAA STC ST00798WI FAIRCHILD SWEARINGEN SA<br />
227-AC<br />
FAIRCHILD SWEARINGEN SA<br />
227-AT<br />
FAIRCHILD SWEARINGEN SA<br />
227-BC<br />
FAIRCHILD SWEARINGEN SA<br />
227-CC<br />
FAIRCHILD SWEARINGEN SA<br />
227-DC<br />
Passenger to all cargo conversion of ATR-42/-<br />
72 series aircraft.ATR-42 is modified in<br />
accordance with Worldwide Aircraft Services<br />
Master Drawing List DL42-25-0<strong>01</strong> Rev G dated<br />
JAN 22, 20<strong>04</strong>.ATR-72 is modified in<br />
accordance with Worldwide Aircraft Services<br />
Ma<br />
Installation of Fairchild Digital Flight Data<br />
Recorder F800 or F1000 in Fairchild aircraft<br />
SA227-AT, -AC, BC, CC, DC in accordance<br />
with Worldwide Aircraft Services Certification<br />
Drawing list No; DL227-31-06 Revision A,<br />
dated May 14, 1999 or later approved<br />
100319<strong>01</strong> WORLDWIDE AIRCRAFT SERVICES Inc. FAA STC SA4872SW SA226-T, SA226-AT Installation of 2 Garrett AiResearch engines<br />
Model TPE 331-10UA-5<strong>01</strong>G orTPE 331-10UA-<br />
511G<br />
none Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
28.07.2<strong>01</strong>0<br />
FAA STC No. SA<strong>01</strong>916CH "Limitations and<br />
conditions”, amended May 24, 2<strong>01</strong>0<br />
1.,,Airplanes not incorporating STC SA270CH,<br />
with Model 8000 floats: Airspeed Limits:,,VA at<br />
8000 lbs. = 143 KIAS Maximum Weight:,,8000<br />
lbs. ,,Take off and Flight ,,7800 lbs. ,,Landing<br />
(Water and Land) ,,8035 lbs.,,Ramp ,,,, C.G.<br />
Range,,Take off and Flight<br />
The FAA approved Airplane Flight Manual<br />
Supplement must be on board the aircraft at all<br />
times.This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
othe<br />
Prior to installation of this modification it 05.11.2<strong>01</strong>0<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
Prior to installation of this modification it 26.10.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
24.11.2005<br />
02.11.2007<br />
according limitation section of AFM-S Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.If the<br />
21.09.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 461/<strong>462</strong>
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032538 ZF LUFTFAHRTTECHNIK GmbH REV. 2 MBB-BK 117 C-2 Main Gear Box Eurocopter BK117<br />
- This conversion can only be performed by the Prior to installation of this modification it 13.06.2<strong>01</strong>2<br />
C2Conversion of the Main Gear Box from MBB- STC holder.- After conversion to Main Gear must be determined thatthe<br />
BK117 C-1 built standard PartNumber (P/N) Box P/N B632K10<strong>01</strong>-051 this is only to interrelationship between this modification<br />
11712005<strong>01</strong> to MBB-BK117 C-2 built standard beinstalled on MBB-BK117 C-2 helicopters. and any other previouslyinstalled<br />
P/NB632K10<strong>01</strong>-051 within the scope of a<br />
modification and/ or repair will introduce<br />
major overhaul, as documented in theZF<br />
no adverse effectupon the airworthiness<br />
Luftfahrttechnik (Z<br />
of the product<br />
10031<strong>01</strong>8 ZIM FLUGSITZ GmbH A310-300 Replacement of E/C seats by ZIM E/C seats,<br />
Type ECO-<strong>01</strong>This STC consists in replacing<br />
the existing seats by Type ECO-<strong>01</strong>seat.<br />
10<strong>04</strong>2845 ZIM FLUGSITZ GmbH REV. 1 B737-800 Installation of ZIM Flugsitz ECO-<strong>01</strong> EC Seats in 1) The In-Seat IFE system shall not be used<br />
a B737-800 Cabin<br />
during Taxi, Take-Off andLanding.2) The ZIM<br />
Flugsitz ECO-<strong>01</strong> EC Seats installation in<br />
accordance with thisSTC islimited to the<br />
following B737-800 aircraft S/N 41<strong>04</strong>7 and<br />
41190.<br />
10<strong>01</strong>3965 ZOREX AIR TRANSPORT <strong>EASA</strong>.A.S.00659 REV. 1 FAIRCHILD SWEARINGEN SA<br />
226-TC<br />
COMM/NAV/GPS Garmin GNS430<br />
Installation, for B-RNAV Operation, and COMM<br />
Bendix King KY196A Installation, both for 8.33<br />
kHz standard.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.07.2<strong>01</strong>0<br />
1. The aircraft is approved for dual pilot B-<br />
RNAV operation, subjected to the conditions,<br />
limitations and procedures contained in: .<br />
Anexo 8 al Programa de Certificación "Aircraft<br />
Flight Manual Supplement", Ed. inicial.2. This<br />
STC is approved only fo<br />
Prior to installation of this STC it must be<br />
determined that theinterrelationship<br />
between this STC and any other<br />
previously installedmodification and / or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> <strong>462</strong>/<strong>462</strong><br />
21.12.2<strong>01</strong>2<br />
25.<strong>04</strong>.2006
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