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>5085 SOGERMA SERVICES <strong>EASA</strong>.A.S.03419 DGAC FRANCE STC 072-MJ-0862; E AIRBUS A300 MODEL B2 SPC antenna modificationNote: This STC<br />
supersede DGAC France STC 072-MJ-0862<br />
and <strong>EASA</strong> 2003-3<strong>04</strong>.<br />
1. Valid only for Airbus B2 MSN 003 <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>5086 SOGERMA SERVICES <strong>EASA</strong>.A.S.03420 DGAC FRANCE STC 072-MJ-0861; E AIRBUS A300 MODEL B2 Cargo door modification for use of SPC<br />
antennaNote: This STC supersede DGAC<br />
France STC 072-MJ-0861 and <strong>EASA</strong> 2003-<br />
303.<br />
1. Valid only for MSN 003. <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>5087 SOGERMA SERVICES <strong>EASA</strong>.A.S.03421 <strong>EASA</strong> 20<strong>04</strong>-2363 AIRBUS A300 MODEL B2 Installation of a ground proximity warning<br />
systemNote: This STC supersedes <strong>EASA</strong> STC<br />
20<strong>04</strong>-2363.<br />
1. Only valid for MSN 003. <strong>04</strong>.<strong>01</strong>.2008<br />
10<strong>01</strong>5208 SOGERMA SERVICES <strong>EASA</strong>.A.S.03623 DHC-6-300 S-53-2039 Structural Provision for Insrument Prior to installation of this modification the<br />
27.08.2008<br />
Panel.<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. The install<br />
10<strong>01</strong>6846 SOLOY, LLC <strong>EASA</strong>.IM.R.S.<strong>01</strong>222 FAA STC SR<strong>01</strong>647SE EUROCOPTER FRANCE AS 350 Installation of Honeywell LTS1<strong>01</strong>-700D-2<br />
B2<br />
engine.<br />
10027209 SOLOY, LLC P-<br />
CESSNA 206H, CESSNA T206H Installation of Rolls-Royce 250-B17F/2 series<br />
<strong>EASA</strong>.IM.A.S.03096<br />
engine in a Cessna206H/T206H.<br />
10028355 SOLOY, LLC FAA STC SA<strong>01</strong>985SE 206H, T206H Installation of New Rear Observation Seat in<br />
Cessna 206<br />
10028448 SOLOY, LLC P-<br />
<strong>EASA</strong>.IM.A.S.03237<br />
10028449 SOLOY, LLC P-<br />
<strong>EASA</strong>.IM.A.S.03236<br />
FAA STC SA<strong>01</strong>688SE 206H, T206H Installation of a revised shoulder harness<br />
restraint system and new rearcabin headliner in<br />
a Cessna 206H/T206H<br />
FAA STC SA00858SE 206, U206B, U206C, U206D Installation of Observation Window in Cessna<br />
TU206A, U206E, TU206B<br />
TU206D, TU206E, U206, TU206F<br />
U206A, TU206G, 206H, T206H<br />
U206F, TU206C, U206G<br />
206<br />
See attached Annex. 20.03.2008<br />
None None 14.09.2009<br />
Weight and Balance: Equipment Removed<br />
Item,,Weight (lb),,Station(in)Seat, 2nd Row (2<br />
Seats),,57,,78.0Seat, 3rd Row<br />
(Bench),,36,,105.2 Equipment Installed<br />
Item,,Weight (lb),,Station (in)Seat Assembly<br />
with Armrests,,34.0,,81.7Base Plate<br />
Assembly,,23.2,,81.9<br />
Prior to installation of this modification it 21.12.2009<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 />
N/A 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.<strong>01</strong>.2<strong>01</strong>0<br />
As per FAA STC SA00858SE, "This<br />
modification has been determined to<br />
becompatible with Soloy STC SA2353NM and<br />
airplanes in landplane,floatplane, and skiplane<br />
configuration when modified in accordance<br />
withFAA approved data."Installer must check<br />
availability<br />
Prior to installation of this modification it 12.<strong>01</strong>.2<strong>01</strong>0<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 />
10028758 SOLOY, LLC P-<br />
FAA STC SR00805SE AS350BA Installation of Honeywell LTS1<strong>01</strong>-600A-3A See attached Data Sheet See attached Data Sheet 14.06.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.R.S.<strong>01</strong>457<br />
engine on Eurocopter AS350BAhelicopter.<br />
10<strong>01</strong>5900 SOUTHEAST JET GROUP, INC. <strong>EASA</strong>.IM.A.S.02021 ST00589WI CESSNA 5<strong>01</strong>, CITIATION Installation of Honeywell EDZ-605 Two-Tube<br />
24.08.2006<br />
CESSNA 550 CITATION II Electronic Flight Instrumentation System<br />
CESSNA 551, CITIATIONII<br />
CESSNA S550, (CITIATION S/II)<br />
(EFIS).<br />
10<strong>01</strong>6786 SPACECAM SYSTEMS INC. <strong>EASA</strong>.IM.R.S.<strong>01</strong>128 REV. 1 TCCA STC SH02-6 AS 350 B<br />
Spacecam RAMS Installation Eurocopter (Aerospatiale) Service Bulletin N° Prior to installation of this modification the 25.08.2009<br />
AS 350 B1<br />
53-05 and 53-06 (for Tail Boom Balast) are installer must determinethat the<br />
AS 350 B2<br />
required as part of this installation.This STC is interrelationship between this modification<br />
AS 350 B3<br />
the <strong>EASA</strong> Validation of Transport Canada STC and any otherpreviously installed<br />
AS 350 BA<br />
n° SH02-6 Issue 2, dated June 28, 2005 modification will introduce no adverse<br />
AS 350 D<br />
effect uponthe airworthiness of the<br />
AS 355 E<br />
AS 355 F<br />
AS 355 F1<br />
AS 355 F2<br />
AS 355 N<br />
product. The installati<br />
10<strong>01</strong>4403 SR TECHNICS AIRCRAFT DESIGN <strong>EASA</strong>.A.S.<strong>01</strong>698 BOEING 737-33V Reconfiguration of six Boeing 737-33V from B737-33V Serial Numbers 29337 to 29342<br />
16.03.2006<br />
SERVICE<br />
149TC to 16BC/100TC including installation of inclusive<br />
G2, G7 and LAV E<br />
10<strong>01</strong>4694 SR TECHNICS AIRCRAFT DESIGN <strong>EASA</strong>.A.S.02860 BOEING 747-400 SERIES Reconfiguration of five Boeing B747-400 1) Limited to the following registration<br />
08.10.2007<br />
SERVICE<br />
aircraft to 54J/62W/228Y.<br />
Mark/Serial Number aircraft: G-VFAB/24958,<br />
G-VHOT/26326, G-VBIG/26255,G-<br />
VWOW/32745, G-VROC/32746.2) The<br />
following <strong>EASA</strong> approved STC's must be<br />
installed concurrently with this design<br />
change:<strong>EASA</strong>.A.S.03165<strong>EASA</strong>.IM.A.S.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 417/<strong>462</strong>
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