04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
Create successful ePaper yourself
Turn your PDF publications into a flip-book with our unique Google optimized e-Paper software.
<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10037822 AMES - AEROSPACE AND<br />
A330-2<strong>01</strong>, -202, -203<br />
A330-200 Cabin reconfigurationThis STC The following modifications, in accordance with Prior to installation of this modification it 22.12.2<strong>01</strong>1<br />
MECHANICAL<br />
A330-223, -243<br />
installs mainly new B/C and Y/C seats and new their aircraftapplicability, are<br />
must be determined thatthe<br />
In-FlightEntertainment system, according to prerequisites to the installation of this STC :- interrelationship between this modification<br />
various cabin configurations.<br />
AMES Minor Change ref :<br />
and any other previouslyinstalled<br />
M1480<strong>01</strong>10.11082<strong>01</strong>1 (Approved under modification and/ or repair will introduce<br />
AMES DOA<strong>EASA</strong>.21J.299)- AMES Minor no adverse effectupon the airworthiness<br />
Change ref : M1480<strong>01</strong>11.1108<br />
of the product<br />
1003<strong>01</strong>18 AMICALE DE VOLTIGE AERIENNE (AVA) REV. 1 CAP 232 Evolution of of CAP 232 to CAP 332<br />
SC.Revision 1: Modifications majeures<br />
applicables aux CAP23X et 332 SC<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 />
28.07.2<strong>01</strong>1<br />
10<strong>01</strong>5819 AM-SAFE INCORPORATED <strong>EASA</strong>.IM.A.S.<strong>01</strong>891 FAA STC ST<strong>01</strong>866LA JETSTREAM 4100 SERIES Installation of AMSAFE Aviation Inflatable<br />
Restraint (AAIR) System on Front Row<br />
Passenger Seats of the Jetstream 4100 Series<br />
Not valid for Jetstream Model 4124 17.05.2006<br />
10<strong>01</strong>5412 AMSAFE, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>128 FAA STC SA<strong>01</strong>700LA. CESSNA 172R<br />
CESSNA 172S<br />
CESSNA 177<br />
CESSNA 206H<br />
10<strong>01</strong>5687 AMSAFE, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>672 SA<strong>01</strong>7<strong>01</strong>LA AVIAT HUSKY A-1<br />
AVIAT HUSKY A-1A<br />
AVIATION AIRCRAFT A-1B<br />
10031<strong>01</strong>0 AMSAFE, Inc. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10031808 AMSAFE, Inc. REV. 1 FAA STC ST02152LA SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
Installation of AMSAFE Aviation Infatable<br />
Restraint (AAIR) System.<br />
Installation of Am-Safe Aviation Inflatable<br />
Restraint System on pilot and copilot<br />
seatsValidation of FAA STC SA<strong>01</strong>7<strong>01</strong>LA<br />
Isuued December 06, 20<strong>04</strong><br />
Installation of AmSafe Aviation Inflatable<br />
Restraints in Non 23.562certified Airplanes in<br />
accordance with Model Specific Master Data<br />
Listidentified on AML SA02276AK , Rev J ,<br />
dated 10 Dec. 2009<br />
AmSafe Aviation Inflatable Restraint (AAIR)<br />
System on various transportcategory airplanes.<br />
This revision <strong>01</strong> extends the applicability of<br />
AAIR to Reynard Reverbseat fitted on A330-<br />
300 airplanes, operated by Virgin Atlantic<br />
Airways.<br />
10<strong>01</strong>5973 AMTECH AERONAUTICAL LIMITED <strong>EASA</strong>.IM.A.S.02124 SA02-132, ISSUE NO.3 LOCKHEED 382G Oil Dispersant Spraying System Installation on<br />
Lockheed 328G aircraft.<br />
1. 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 />
The Electronic Module P/N 508358-409 and<br />
the Inflator Assembly P/N 508794-4<strong>01</strong> must be<br />
replaced every seven (7) years<br />
If Installation of the Shoulder Harness is not to<br />
approved Data definedin the STC a separate<br />
approval has to be obtained<br />
1-,,For the installation of approved seats<br />
modified by installation ofthe AmSafe Inflatable<br />
Restraint System in a specific cabin<br />
layout,compliance to 25.561 must be<br />
demonstrated for the individual seat at<br />
itsspecific location within the approval project<br />
fo<br />
Operation in accordance with Airplane Flight<br />
Manual Supplement FMS2439<strong>01</strong> Rev. 4 dated<br />
November 4, 2005 or later TCCA approved<br />
revision in conjunction with AFI Operating<br />
Manual OP2439 Rev. 3 dated August 2005 or<br />
later TCCA approved revision.Instructions for<br />
10<strong>01</strong>6638 AMTECH AERONAUTICAL LIMITED <strong>EASA</strong>.IM.A.S.03078 TCCA STC C-LSA06-378/D LEARJET 45 AirCell Axxess II Iridium SatcomTCCA LSTC C- 1 Prior to installation of this modification the<br />
LSA06-378/D<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 Th<br />
10034839 AMTECH AERONAUTICAL LIMITED TCCA STC SA09-51, ISSUE NO. 1 CL-600-2C10<br />
CL-600-2D15<br />
CL-600-2D24<br />
Installation of a Rosemount Aerospace Angle<br />
of Attack Sensor.<br />
Model additions to the FAA Approved<br />
Model List Rev J , dated 10 Dec<br />
2009have to be applied to <strong>EASA</strong>Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modific<br />
22.<strong>04</strong>.2005<br />
30.11.2005<br />
21.07.2<strong>01</strong>0<br />
Prior to installation of this modification it 14.03.2<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 />
<strong>01</strong>.02.2007<br />
06.<strong>01</strong>.2009<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 />
05.05.2<strong>01</strong>1<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 75/<strong>462</strong>
Change language