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 />
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
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