04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
Create successful ePaper yourself
Turn your PDF publications into a flip-book with our unique Google optimized e-Paper software.
<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
Change language