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>51<strong>01</strong> PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03444 PIPER PA-39 Validation of Foreign Installed Avionics 05.05.2008<br />
10<strong>01</strong>5141 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03499 CESSNA 208 Installation of Garmin GNS430 and GTX330<br />
Mode "S" Transponder.<br />
19.03.2008<br />
10<strong>01</strong>5189 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.A.S.03573 Installation of Garmin GNS430 13.06.2008<br />
10<strong>01</strong>7139 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>240 EUROCOPTER DEUTSCHLAND Installation of Skywatch Traffic Avoidance<br />
MBB-BK<br />
22.05.2006<br />
10<strong>01</strong>7180 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>303 EUROCOPTER FRANCE AS Installation for KLN90B GPS, UNS-1K Flight AS365 NI, S/N 6309. 27.08.2007<br />
365N1<br />
Management System, Devore Recognition<br />
Light System and Whelen Strobe.<br />
10<strong>01</strong>7189 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>326 EUROCOPTER DEUTSCHLAND Installation of Honeywell AR30 Cockpit Voice -- 11.<strong>01</strong>.2007<br />
BK117 C<br />
Recorder<br />
10<strong>01</strong>7245 PHOENIX AEROSPACE LIMITED <strong>EASA</strong>.R.S.<strong>01</strong>442 Installation of Power Line Detector System. Eurocopter Deutschland BK117 Series.RFM<br />
Supplement PADS/FMS/BK117/003<br />
05.03.2008<br />
10029133 PHOENIX AEROSPACE LIMITED P-<strong>EASA</strong>.R.S.<strong>01</strong>515 AS355E, AS355F, AS355F1, Installation of Skywatch L3 Traffic avoidance Not Applicable Not Applicable 08.03.2<strong>01</strong>0<br />
AS355F2, AS355N, AS355NP and Honeywell's KMD250 MFD<br />
10<strong>04</strong>1858 PHOENIX AEROSPACE LIMITED A139 Introduction of SX16 Searchlight System 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 />
11.12.2<strong>01</strong>2<br />
10<strong>04</strong>1863 PHOENIX AEROSPACE LIMITED AW 139 Introduction of an electronic message sign. 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 />
11.12.2<strong>01</strong>2<br />
10030088 PIAGGIO AMERICA, Inc. FAA STC SA10955SC P.180 AVANTI & AVANTI II FAA STC SA10955SC "Installation of a<br />
passenger seating system to replacefive<br />
existing Decrane single seats with Model<br />
FS11<strong>01</strong> single seats"<br />
10<strong>01</strong>6399 PLANE POWER, LTD. <strong>EASA</strong>.IM.A.S.02728 FAA STC SA10682SC Replacement of generator and mechanical<br />
voltage regulator with alternator and electronic<br />
voltage regulator<br />
10<strong>04</strong>0602 PMV ENGINEERING REV. 1 A330-200, A330-300 Installation of provisions for the use of EFB<br />
Class 2 on Airbus A330.This modification deals<br />
with the installation of a dual Class 2Electronic<br />
Flight Bag (EFB) CMC Esterline 'Pilot View'<br />
system on AirbusA330-200/300. The<br />
modification is defined as follows:<br />
10<strong>04</strong>2279 PMV ENGINEERING B747-400 Installation of provisions for the use of EFB<br />
Class 2.<br />
10<strong>01</strong>7116 POLICE AVIATION SERVICES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>098 BELL 412 EP Installation of an L-3 Modular Airborne Data<br />
Recording/Acquisition System (MADRAS)<br />
combined CVR & FDR<br />
10<strong>01</strong>72<strong>04</strong> POLICE AVIATION SERVICES Ltd. <strong>EASA</strong>.R.S.<strong>01</strong>353 MD HELICOPTERS MD902 MTWA Increase with PAS External Stores and<br />
Surveillance Equipment<br />
10033979 POLICE AVIATION SERVICES Ltd. <strong>EASA</strong> STC 20<strong>04</strong>-<br />
3846<br />
REV. 1 EC 135 P1 (CDS)<br />
EC 135 P1 (CPDS)<br />
EC 135 P2 (CPDS)<br />
EC 135 P2+<br />
EC 135 T1 (CDS)<br />
EC 135 T1 (CPDS)<br />
EC 135 T2 (CPDS)<br />
EC 135 T2+<br />
EC 635 P2+<br />
EC 635 T1 (CPDS)<br />
EC 635 T2+<br />
Incubator Installation EC 135Transfer of <strong>EASA</strong><br />
STC No 20<strong>04</strong> 3846 (dated 16/<strong>04</strong>/20<strong>04</strong>) from<br />
PAS Ltd toBond Aviation Group Ltd<br />
None None 20.05.2<strong>01</strong>0<br />
The approval holder shall fulfil the obligations<br />
of Part 21, Paragraph 21.A109<br />
This certificate does not cover the installation<br />
of EDUs which will becover by the operational<br />
evaluation.<br />
<strong>EASA</strong> STC 10<strong>04</strong>09<strong>01</strong> is a prerequisite for this<br />
modification.<br />
13.05.2008<br />
Prior to installation of this modification it 13.07.2<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 />
Prior to installation of this modification it 20.11.2<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 />
03.05.2006<br />
Only those in the above F/M Supplement. 03.<strong>04</strong>.2007<br />
Prior to installation of this modification it 28.02.2<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 />
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