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 />
10030772 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR02035SE AS355E, AS355F, AS355F1, Cargo Hook Kit model 200-352-00 None Applies only to Eurocopter model 07.07.2<strong>01</strong>0<br />
AS355F2, AS355N, AS355NP<br />
rotorcraft listed above which areequipped<br />
with a cargo swing type suspension<br />
system. Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other previou<br />
10032737 ONBOARD SYSTEMS INTERNATIONAL <strong>EASA</strong>.IM.R.S.00592 REV. 1 FAA STC SR00850SE 206L, 206L-1, 206L-3, 206L-4<br />
407<br />
10<strong>04</strong>0250 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR02217SE EC135 P1(CDS), EC135<br />
P1(CPDS)<br />
EC135 P2 (CPDS), EC135 P2+<br />
EC135 T1(CDS), EC135<br />
T1(CPDS)<br />
EC135 T2(CPDS), EC135 T2+<br />
EC635 T1 (CPDS), EC635 P2+<br />
EC635 T2+<br />
Cargo Hook Kit model 200-260-00 and 200-<br />
260-<strong>01</strong>This change adds an additional cargo<br />
hook<br />
10<strong>04</strong><strong>04</strong>40 ONBOARD SYSTEMS INTERNATIONAL FAA STC SR<strong>01</strong>694SE BO 105 S, BO 105 LS A-3 Validation of FAA STC SR<strong>01</strong>694SE - Cargo<br />
Hook Kits<br />
10038238 ONE SKY AVIATION FAA STC SA02387AK 1- 58, 58A, G58, 95-B55, E55<br />
2- A36, G36, A36TC, B36TC,<br />
2- F33A, F33C<br />
10038364 ONE SKY AVIATION FAA STC SA02372AK 1. B200, B200C, B200CT, B200T<br />
1. B200GT, B200CGT<br />
1. B300, B300C<br />
2. C90GT, C90GTI<br />
Applies only to those Bell Helicopter models<br />
listed above previouslyequipped with Bell<br />
Helicopter Cargo Hook Suspension<br />
System206-706-341-5, 206-706-341-1<strong>01</strong> or<br />
206-706-341-109 and eitherBreeze-Eastern<br />
cargo hooks 17149-2, 17149-6 or Onboard<br />
Systems Cargoho<br />
Cargo Hook Kit. Limited to helicopters equipped with cargo<br />
hook assembly P/N AS22-44.<br />
Fabrication and Installation of Exterior LED<br />
Lighting Suite inaccordance with FAA STC<br />
SA02387AK.Fabrication and Installation of<br />
Exterior LED Lighting Suite on theBeechcraft<br />
Baron and Bonanza series aircraft in<br />
accordance to MasterData List No. 20 16 00,<br />
Re<br />
Installation of the Max-Viz® Enhanced Vision<br />
System (EVS) Model-1500 onHawker<br />
Beechcraft Corporation B200/B300/C90 Series<br />
aircraft equippedwith a Rockwell Collins<br />
ProLine 21 Adaptive Flight Display (AFD)<br />
havingthe video capability upgrade Part No 822-<br />
1753-<br />
10<strong>04</strong>0870 ORCON CORPORATION B737-200/-200C/-300/-400/-500 Thermal/acoustic insulation system for Boeing<br />
737 series aircraft:insulation blankets<br />
installation.<br />
10<strong>04</strong>1532 ORCON CORPORATION FAA STC ST<strong>01</strong>834LA B757-200/-200PF Validation of FAA STC ST<strong>01</strong>834LA related to<br />
Installation of InsulationBlanket<br />
10<strong>04</strong>2039 ORCON CORPORATION FAA STC ST02350LA CL600-2B19 Orcon Thermal/Acoustic Insulation System for<br />
Bombardier Challenger 850Series Aircraft<br />
This STC is restricted to installation of cargo<br />
hook kits model200-387-00 and model 200-<br />
388-00. Not included are cargo hook kits<br />
model200-302-00 and model 200-303-00.<br />
Prior to installation of this modification it 26.11.2<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 />
Prior to installation of this modification it 20.06.2<strong>01</strong>2<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 />
Prior to installation of this modification it 03.07.2<strong>01</strong>2<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 />
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 />
30.<strong>01</strong>.2<strong>01</strong>2<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 />
10027300 OREGON AERO, INC. FAA STC SA<strong>01</strong>597SE LC41-550FG (C400) Installation of replacement seats -as indicated in Engineering Manual Instruction<br />
for ContAW EM-<strong>01</strong>-<strong>01</strong>, RevB, or later FAA<br />
approved revisions-only for LC41-550FG S/N<br />
41002 through 41108, 415<strong>01</strong> through 41800<br />
and4110<strong>01</strong> and onwards<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
09.02.2<strong>01</strong>2<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 />
31.07.2<strong>01</strong>2<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 />
25.09.2<strong>01</strong>2<br />
None None 05.11.2<strong>01</strong>2<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
holding and disposal ofthe approved<br />
appropriate documentation. Prior to<br />
installation of this modification it must be<br />
determined thatthe i<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 352/<strong>462</strong><br />
18.09.2009
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