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>4856 SELL GmbH <strong>EASA</strong>.A.S.03080 REV. 1 BOEING 777-300 Galley Reconfiguration and Replacement for Limited to B777-300 serial numbers: 28680,<br />
31.10.2007<br />
Emirates Airlines<br />
28687, 29062, 29063, 29064, 29067, 29395,<br />
29396, 32697, 32699, 32700, 32702<br />
10<strong>01</strong>4275 SERAM SARL <strong>EASA</strong>.A.S.<strong>01</strong>511 CESSNA 337D Installation of one KX 155A Immunity FM, one 1. This STC is limited to Cessna 337D SN 337-<br />
23.08.2005<br />
GNS430 and GI106A with BRNAV capability 1<strong>04</strong>8. 2. Autopilot coupled with GNS 430<br />
forbidden. 3. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
10<strong>04</strong>2367 SERAM SARL SEE <strong>EASA</strong> APPROVED MODEL Installation of a Garmin GNS 430/A/W/AW Initial installation of this design change must be Prior to installation of this modification it 27.11.2<strong>01</strong>2<br />
LIST<br />
system, a GA 35/56 GPS antenna,a GI 106A performed byauthorised SERAM technical must be determined thatthe<br />
CDI indicator, a Bendix/King KX 155<br />
personnel. This installation is approved for interrelationship between this modification<br />
NAV/COM system, aKI-203/4/8/9 VOR/ILS VFR, IFR, RNAV and RNP<br />
and any other previouslyinstalled<br />
indicator, a KN 62A DME receiver, GPS Approachoperations without coupling of modification and/or repair will introduce<br />
annunciationlights and AV22, KA60, CI 105 navigation systems to an autopilot or aflight no adverse effectupon the airworthiness<br />
antennas.<br />
director. LPV<br />
of the product.<br />
10<strong>01</strong>6022 SHADIN AVIONICS <strong>EASA</strong>.IM.A.S.02188 ST02115CH CESSNA 500<br />
CESSNA 550<br />
CESSNA 560<br />
CESSNA S550<br />
Validation of FAA STC ST02115CHInstallation<br />
of a dual Shadin "ADC 6000 System RVSM<br />
Capable": hardware provisions for RVSM<br />
cpability.<br />
This STC does not provide RVSM capability to<br />
the aircraft (compliance to RVSM airworthiness<br />
requirements are not part of this STC):a<br />
separate STC has to be applied.Airplane Flight<br />
Manual Supplement, Shadin Document No.<br />
DN2807A-006, Revision B, dated 23 Sep<br />
10<strong>01</strong>6036 SHADIN AVIONICS <strong>EASA</strong>.IM.A.S.02205 FAA STC SA02098CH CESSNA 5<strong>01</strong> Validation of FAA STC SA02098CH – The installer must determine, if this design is<br />
“Installation of dual Shadin ADC 6000 Air Data compatible with previously approved<br />
Computer System” for RVSM capability 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 that pe<br />
10034421 SHADIN AVIONICS FAA STC SE578GL SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10034457 SHADIN AVIONICS FAA STC SH582GL BELL 206B, B-1, L, L-1, L-3<br />
BELL 407<br />
Fuel Flow Transducer Installation / Installation<br />
of Shadin fuel flowtransducer in the fuel line<br />
between the fuel control unit (FCU) and thefuel<br />
injector.<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 />
07.12.2006<br />
10.<strong>04</strong>.2007<br />
<strong>04</strong>.<strong>04</strong>.2<strong>01</strong>1<br />
Installation of Digital Fuel Flow Meter. None. Rotorcraft modified in accordance with<br />
Shadin Report 4119 must have theengine<br />
modified in accordance with <strong>EASA</strong> STC<br />
10034421(FAA STC SE578GL).Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modificatio<br />
08.<strong>04</strong>.2<strong>01</strong>1<br />
10<strong>01</strong>5809 SHOWA AIRCRAFT USA INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>878 ST<strong>01</strong>621SE BOEING 747-400 Installation of an Upper Deck Galley on Boeing 18.12.2006<br />
10<strong>01</strong>5846 SIDDHIS AERONAUTICAL DESIGN<br />
CORP.<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>946 REV 3 TCCA STC SA97-71, ISSUE 6 BOMBARDIER CL-600-1A11 (CL- Installation of Fin Mounted Radome/ Antenna<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3A<br />
BOMBARDIER CL-600-2B16 (6<strong>01</strong>-<br />
3R<br />
BOMBARDIER CL-600-2B16 (6<strong>04</strong>)<br />
BOMBARDIER CL-600-2B19<br />
(SERIES<br />
System (Structural Provisions only).<br />
1. The installation shall be visually inspected<br />
for external damage every 1200 hours and for<br />
lightning damage every flight in severe<br />
weather.2. The total weight of the antenna<br />
and the installed equipment shall not exceed<br />
18.1 kg.3. The additional<br />
10<strong>01</strong>5842 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.<strong>01</strong>937 FAA STC ST09559AC CESSNA C5<strong>01</strong> Installation of Williams/ Rolls FJ44-2Aengines The installer must determine, if this design is<br />
in accordance with FAA STC ST09559AC and compatible with previously approved<br />
Sierra Ind. Drawing SI360-000, dated modifications. If the holder agrees to permit<br />
27.02.2002. or later FAA approved Revision. another person to use this certification to alter<br />
a product, the holder must give the other<br />
person written evidence of that pe<br />
10<strong>01</strong>5851 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.<strong>01</strong>951 ST09630AC CESSNA 5<strong>01</strong> Installation of Meggitt Engine Instrument<br />
Display System according to FAA STC<br />
ST09630AC.<br />
The installer must determine, if this design is<br />
compatible with previously approved<br />
modifications. If the holder agrees to permit<br />
another person to use this certification to alter<br />
a product, the holder must give the other<br />
person written evidence of that pe<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 402/<strong>462</strong><br />
29.05.2007<br />
08.03.2007<br />
15.03.2007
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