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 />
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
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