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>5129 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03480 CESSNA P210N Avionics upgradeBy removing:-NSD 360<br />
HISSA-832B Slaving BoxACK A-30 mod 8<br />
Altitude EncoderGMA-340 Audio PanelAnd<br />
installingSN-3500 E-HISSAC 7-35 Airdada<br />
ComputerKG-102A Remote GyroGMA-347<br />
Audio Panel<br />
Reg.: HB-CZB S/N: P-210-0780 05.03.2008<br />
10<strong>01</strong>5262 CHRISTEN-AIRTECH AG <strong>EASA</strong>.A.S.03720 CESSNA 210 Avionics UpgradeBy removing the existing:- Prior to installation of this modification the<br />
11.12.2008<br />
COM/NAV 1 + 2- DME - Mode A/C<br />
installer must determine that the<br />
Transponder- Audio Panel And install the new interrelationship between this modification and<br />
Avionics Systems:- GNS 530W<br />
any other previously installed modification will<br />
COM/NAV/GPS 1- GNS 430W<br />
introduce no adverse effect upon the<br />
COM/NAV/GPS 2 with GI106A GPS/NAV<br />
Indicator- KN 62A DME - GTX 330 Mode S<br />
Transponderairworthiness<br />
of the product. The install<br />
10031914 CHRISTEN-AIRTECH AG TBM 700 A Avionics Upgrade Out: Dual COM-NAV Bendix- Reg.: D-FIRE,,S/N: 137 The approval holder shall fulfil the 21.09.2<strong>01</strong>0<br />
King KX-165A, GPS Apollo MNS21<strong>01</strong>, MFD<br />
obligations of Part 21,<br />
ApolloMX20, Encoder Shadin 8800-T In: COM-<br />
Paragraph21.A109. Prior to installation of<br />
NAV-GPS Garmin GNS-530W & 430W, MFD<br />
this modification it must be determined<br />
Garmin GMX-200, Encoder ACKA-30 Mod. 8<br />
thatthe interrelationship between this<br />
serial<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10036867 CHRISTEN-AIRTECH AG 414A Inst.Traffic alerting<br />
S/N: 414A-0233,,,,D-IMUB The approval holder shall fulfill the 13.10.2<strong>01</strong>1<br />
system/StormscopeRemoved:- NIL Installed:-<br />
obligations of Part 21, §21.A118A.Prior<br />
Garmin GTS800 Traffic Alerting System- L-3<br />
to installation of this modification it must<br />
WX500 Stormscope System<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will<br />
10<strong>01</strong>5968 CIRRUS DESIGN CORPORATION <strong>EASA</strong>.IM.A.S.02119 SA<strong>01</strong>355WI-D CIRRUS SR20 Validation of FAA STC SA<strong>01</strong>355WI-D –<br />
“Installation of Bendix/King KR87 ADF and/ or<br />
KN 62A DME”<br />
10<strong>01</strong>6118 CITATION TECH <strong>EASA</strong>.IM.A.S.02310 FAA STC ST<strong>01</strong>395WI CESSNA 500<br />
Installation of Dual Honeywell AM-250 Digital<br />
CESSNA 5<strong>01</strong><br />
Altimeter and Skylight Avionics Air Data<br />
CESSNA 550<br />
Interface Adapter ADC-602 AIU and<br />
CESSNA 551<br />
associatedequipment to obtain RVSM<br />
REIMS AVIATION CESSNA F 177 approval.<br />
RG<br />
10<strong>01</strong>6006 CLIPPER AVIATION, Inc. <strong>EASA</strong>.IM.A.S.02170 FAA STC ST02318NY BOEING 747-400 FREIGHTER Upper Deck seating arrangement for B747-<br />
400BCF as defined in Weber Aircraft<br />
installation drawing No. 860<strong>01</strong>4 and Clipper<br />
Aviation CLI-2006-003 Rev. A, Master Data<br />
List B747-400BCF<br />
10036123 CLIPPER AVIATION, Inc. FAA STC ST02318NY B747-400 Installation of seating configuration on Upper<br />
Deck of B747-400 Boeingconverted Special<br />
Freighter<br />
10<strong>01</strong>5822 COLUMBIA AVIONICS & AIRCRAFT <strong>EASA</strong>.IM.A.S.<strong>01</strong>894 ST<strong>01</strong>128 BEECH 200<br />
BEECH 200C<br />
BEECH 200CT<br />
BEECH 200T<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B200<br />
BEECH B200CT<br />
BEECH B200T<br />
BEECH B300<br />
BEECH B300C<br />
Installation of Honeywell MK-VIII Enhanced<br />
Ground Proximity Warning System (with or<br />
without optional EFIS-85B/14 Display).<br />
1. The installer must determine, if this design<br />
is compatible with previously approved<br />
modifications. If the holder agrees to permit<br />
another person to use this certification or alter<br />
a product, the holder must give the other<br />
person written evidence of t<br />
This STC is approved only for the product<br />
configuration as defined in the approved design<br />
data referred to in the paragraphs "Description"<br />
and “Associated Technical Documentation”.<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined<br />
15.05.2007<br />
<strong>04</strong>.07.2007<br />
<strong>04</strong>.<strong>04</strong>.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 />
12.08.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 156/<strong>462</strong><br />
28.09.2006
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