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 />
100291<strong>01</strong> AEROLITE MAX BUCHER AG P-<strong>EASA</strong>.A.S.03979 REV. 1 BEECH 200 SUPER KING AIR Change to B200 Medical Interior KitP/N Applicable to Beechcraft model B200 S/N BB- Prior to installation of this modification it 25.02.2<strong>01</strong>1<br />
2300<strong>01</strong>-5<strong>01</strong> Change compromises of:- Cargo 20<strong>01</strong> and subsequent<br />
must be determined thatthe<br />
Platform Inst. P/N 230006-502- Stretcher Seat<br />
interrelationship between this modification<br />
Inst. P/N 230<strong>01</strong>5-502- AC Power Kit P/N<br />
and any other previouslyinstalled<br />
0071605-5<strong>01</strong>- Engineering Orders EO-10-<strong>01</strong>0/-<br />
modification and/ or repair will introduce<br />
<strong>01</strong>1/-037 In addition this Major Change covers<br />
no adverse effectupon the airworthiness<br />
mi<br />
of the product.<br />
10029681 AEROLITE MAX BUCHER AG REV. 2 EC135P1(CDS),<br />
EC135P1(CPDS),<br />
EC135P2(CPDS), EC135P2+<br />
EC135T1(CDS), EC135T1(CPDS),<br />
EC135T2(CPDS), EC135T2+<br />
Utility Missions Interior P/N 135736-502 This<br />
major change to <strong>EASA</strong> STC No. 10029681<br />
dated 12.<strong>04</strong>.2<strong>01</strong>0 covers theintroduction/<br />
modification of the following components into<br />
the UtilityMissions Interior P/N 135736-502:-<br />
Introduction of the Seat FWD LH, RH and<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 />
08.08.2<strong>01</strong>2<br />
10029915 AEROLITE MAX BUCHER AG EC135 P1(CDS), EC135 EMS Equipment P/N 135710-502 Limited to: S/N 870 and subsequent The approval holder shall fulfil the 03.05.2<strong>01</strong>0<br />
P1(CPDS),<br />
obligations of Part 21,<br />
EC135 P2(CPDS), EC135 P2+,<br />
Paragraph21A.118A. Prior to installation<br />
EC135 T1(CDS), EC135<br />
of this modification it must be determined<br />
T1(CPDS),<br />
thatthe interrelationship between this<br />
EC135 T2(CPDS), EC135 T2+<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
10030822 AEROLITE MAX BUCHER AG P-<strong>EASA</strong>.R.S.<strong>01</strong>551 REV. 2 A109 SP EMS Kit AW109SP REGAAerolite P/N None Prior to installation of this modification it 15.06.2<strong>01</strong>1<br />
109<strong>01</strong>50-5<strong>01</strong> Changes related to Rev.1 to STC<br />
must be determined thatthe<br />
10030822:- Introduction of the Propaq MD<br />
interrelationship between this modification<br />
Retainer Inst. P/N 109<strong>01</strong>70-503 and<br />
and any other previouslyinstalled<br />
anadditional 'Training Configuration 2' into the<br />
modification and/ or repair will introduce<br />
already certified EMSEquipment P/N 109<strong>01</strong>50-<br />
no adverse effectupon the airworthiness<br />
5<strong>01</strong> (STC EA<br />
of the product.<br />
10030992 AEROLITE MAX BUCHER AG REV. 2 MBB-BK 117 C-2 EMS Equipment P/N 145341-5<strong>01</strong>Change for<br />
Rev. 1 of STC comprises of:Addition of<br />
Configuration 145341-502,and the<br />
following changes compared to the version -<br />
5<strong>01</strong> of the equipment:- Relocation of a Seat<br />
and changes of the Seating configuration.-<br />
Relocatio<br />
Compatibility with NVIS has not been Prior to installation of this modification it <strong>01</strong>.08.2<strong>01</strong>1<br />
demonstrated.Compatibility with TC-holders 3- must be determined thatthe<br />
seat bench has not been demonstrated interrelationship between this modification<br />
forconfiguration P/N 145341-5<strong>01</strong>.<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10032080 AEROLITE MAX BUCHER AG AW139 EMS Equipment P/N 139200-5<strong>01</strong> Limited to: S/N 41226 onwards 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 />
06.10.2<strong>01</strong>0<br />
10033098 AEROLITE MAX BUCHER AG EC135 VIP Equipment P/N 135748-5<strong>01</strong> Reg.: \-\ ,,S/N: Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other<br />
previouslyinstalledmodification and/ or<br />
repair will introduce no adverse effect<br />
upon theairworthiness of the product.<br />
17.12.2<strong>01</strong>0<br />
10036912 AEROLITE MAX BUCHER AG AW139/AB139 EMS Equipment P/N 139-0003670-5<strong>01</strong>This<br />
STC covers 4 EMS cabin configurations and 3<br />
PAX configurations asdescribed in the FMS-<br />
139-0003670-5<strong>01</strong> and according to the<br />
Masterdocument list MDL-11-<strong>01</strong>6 rev N/C.<br />
10038985 AEROLITE MAX BUCHER AG EC135 EMS Equip. P/N 135-00<strong>04</strong>171-5<strong>01</strong>The<br />
equipment includes up to two stretchers, two<br />
seats installed in theforward part of the cabin<br />
and stowage between the two seats.<br />
None The following item are required for the<br />
installation of the STC:-Helicopter must<br />
be in standard configuration AW P/N<br />
3G0000X00231-Cockpit Bulkhead MAG<br />
P/N 6AB1KT002-431 (or equivalent)<br />
must beinstalled for EMS operations.-<br />
Rear Panel Closure Inst. AW P/N 3G<br />
17.10.2<strong>01</strong>1<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 />
28.03.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 29/<strong>462</strong>