04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
You also want an ePaper? Increase the reach of your titles
YUMPU automatically turns print PDFs into web optimized ePapers that Google loves.
<strong>EASA</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>
Change language