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>01</strong>5525 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>403 SA5830SW BOMBARDIER CL-600-1A11 (CL- FAA STC SA5830SW. Installation of Radio<br />
25.07.2005<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Master Switch System<br />
10<strong>01</strong>5526 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>4<strong>04</strong> SA7451SW BOMBARDIER CL-600-2B16 Installation of a Dual EFIS Master Switch<br />
System<br />
25.07.2005<br />
10<strong>01</strong>5527 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>405 FAA STC SA7454SW BOMBARDIER CL-600-2B16 Installation of Shepherd Security System 25.07.2005<br />
10<strong>01</strong>5528 RAYTHEON AIRCRAFT SERVICES, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>406 FAA STC SA7459SW BOMBARDIER CL-600-2B16 Installation of a Dual FMS Master Switch<br />
System<br />
10<strong>01</strong>5915 RCM NORMALIZING <strong>EASA</strong>.IM.A.S.02<strong>04</strong>5 SA5202NM COMMANDER AIRCRAFT 112 Validation of FAA STC SA5202NM: Installation<br />
of Lycoming engine model IO-360-C1D6<br />
modified in accordance with STC SE5203NM<br />
& Propeller Hartzell HC-E3YR-1RF/F7392.<br />
10<strong>01</strong>6700 RCM NORMALIZING <strong>EASA</strong>.IM.E.S.<strong>01</strong><strong>01</strong>4 FAA STC SE5203NM LYCOMING ENGINES IO-360-<br />
C1D6<br />
Installation of turbocharger and induction air<br />
intercooler in accordance with “Drawing List<br />
Report No. 1” dated August 20, 1990, orlater<br />
FAA approved revision.<br />
10<strong>01</strong>4230 RECTIMO AVIATION <strong>EASA</strong>.A.S.<strong>01</strong>393 PIPER PA-28-181, ARCHER III GNS 430 installation with MD 41-1488 (HSI<br />
and AP coupled)Installation of GNS 430 and<br />
MD 41-1488 coupled with KI 525A<br />
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 />
25.07.2005<br />
See AFM Supplement No. 1. 25.06.2007<br />
Compatibility of this design change with<br />
previously approved modifications must he<br />
determined by the installer. The installation<br />
should not be incorporated in any engine<br />
unless it is determined that the interrelationship<br />
between this installation and any p<br />
Limited to S/N 2843066 F-GSMDGPS use is<br />
forbidden for BRNAV and approachAuto Pilot<br />
coupling is forbidden under 2000 ft AGL<br />
10<strong>01</strong>5<strong>01</strong>5 RECTIMO AVIATION <strong>EASA</strong>.A.S.03319 PARTENAVIA P68C Installation of a COM/NAV/GPS GARMIN GNS This STC is limited to the S/N 279.<br />
430 (BRNAV without coupling to the auto-pilot)<br />
a COM/NAV GARMIN SL 30, a stormscope L3<br />
WX 500 and an ELT ARTEX ME 406.<br />
22.<strong>01</strong>.2008<br />
10<strong>01</strong>5112 RECTIMO AVIATION <strong>EASA</strong>.A.S.03459 PIPER PA-28R-2<strong>01</strong>T Replacement of : King KX155, KI209 and Applicable to S/N 7803232 F-GHYY.GPS use<br />
Garmin GPS 155 by Garmin GNS430 coupled is limited to Day VFR flights in sight of ground<br />
to HSI and autopilot. Installation of a RMI KI<br />
229.Removal of King KX155, KI209 and<br />
Garmin GPS 155 Installation of King RMI KI<br />
229, Garmin GNS 430 with MD 41 coupled to<br />
HSI KI5<br />
or water.<br />
10034509 REGENT AEROSPACE CORPORATION FAA STC ST02274LA B777-222 Interior modifications in accordance with<br />
Regent Aerospace CorporationMaster Data<br />
List MDL-4100, Revision E, dated November<br />
25, 2009. FAA STCST02274LA refers.<br />
Limited to B777-222 aircraft serial number<br />
30214 only<br />
31.05.2007<br />
20.07.2007<br />
22.09.2008<br />
Prior to installation of this modification it 08.<strong>04</strong>.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 />
10<strong>01</strong>6335 REVUE THOMMEN AG <strong>EASA</strong>.IM.A.S.02644 FAA STC ST10685SC LEARJET 60 Installation of Revue Thommen 3A43 Standby<br />
Altimeter.<br />
12.03.2008<br />
10<strong>01</strong>6337 REVUE THOMMEN AG <strong>EASA</strong>.IM.A.S.02646 FAA STC ST10684SC LEARJET 45 Installation of Revue Thommen 3A43 Standby<br />
Altimeter.<br />
12.03.2008<br />
10<strong>01</strong>5602 ROCKWELL COLLINS AEROSPACE <strong>EASA</strong>.IM.A.S.<strong>01</strong>538 ST<strong>01</strong>205NY BOMBARDIER CL-600-2B16 Installation of Head Up Guidance System<br />
(HGS) Model 2100 (Phase 2)<br />
15.08.2005<br />
10<strong>01</strong>6646 ROCKWELL COLLINS AEROSPACE <strong>EASA</strong>.IM.A.S.03089 REV. 2 FAA STC ST<strong>01</strong>100SE DHC-8-4<strong>01</strong> & DHC-8-402 Updates for Flight Management System (FMS) None<br />
HGS 4100.FAA acceptance letter 130S-09-<br />
387, dated 21.09.2009.<br />
None 12.<strong>04</strong>.2<strong>01</strong>0<br />
10<strong>01</strong>5727 ROCKWELL COLLINS AEROSPACE & <strong>EASA</strong>.IM.A.S.<strong>01</strong>743 REV. 3 FAA STC ST<strong>01</strong>390LA CL-600-2C10, CL-600-2D15 Installation of Head-Up Guidance System None Prior to installation of this modification it 21.<strong>04</strong>.2<strong>01</strong>1<br />
CL-600-2D24, CL-600-2E25 (HGS) Model 4200.Addition of CL-600-2E25<br />
must be determined thatthe<br />
(CRJ 1000) to HGS 4200 STC<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 />
10<strong>01</strong>6677 ROCKWELL COLLINS AEROSPACE & <strong>EASA</strong>.IM.A.S.03193 FAA STC ST0<strong>01</strong>29SE BOMBARDIER DHC-8-100<br />
SERIES<br />
BOMBARDIER DHC-8-200<br />
SERIES<br />
BOMBARDIER DHC-8-300<br />
SERIES<br />
Validation of the FAA STC ST0<strong>01</strong>29SE for the<br />
HGS 2800 on the Dash 8-100/200/300 Series<br />
Aircraft (editorial change).<br />
1. 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.2.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 367/<strong>462</strong><br />
27.<strong>04</strong>.2009
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