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 />
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
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