04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
You also want an ePaper? Increase the reach of your titles
YUMPU automatically turns print PDFs into web optimized ePapers that Google loves.
<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>7285 DRF STIFTUNG LUFTRETTUNG <strong>EASA</strong>.R.S.<strong>01</strong>533 EUROCOPTER DEUTSCHLAND Title: Installation of a L-3 SSCVR Cockpit 1. Prior to installation of this modification the<br />
<strong>04</strong>.05.2009<br />
BK117 B<br />
Voice RecorderDescription: Optional<br />
installer must determine that the<br />
Installation of a Cockpit Voice Recorder. The interrelationship between this modification and<br />
installation is in accordance with DRF change any other previously installed modification will<br />
no. 135, MDL MD-117-31-32-000<strong>01</strong>.<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10029942 DRF STIFTUNG LUFTRETTUNG MBB-BK 117 B-2, MBB-BK 117 C- Installation of Garmin GNS 530 FMS<br />
Not Applicable The approval holder shall fulfil the <strong>04</strong>.05.2<strong>01</strong>0<br />
1<br />
COM/NAV System and TCAS-1 Sky 899TCAS<br />
obligations of Part 21,<br />
Paragraph21A.118A. Prior to installation<br />
of this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repa<br />
10031819 DRF STIFTUNG LUFTRETTUNG MBB-BK117B-2, MBB-BK117 C-1 Installation of second directional gyro None Prior to installation of this modification it 16.09.2<strong>01</strong>0<br />
systemInstallation of a second directional gyro<br />
must be determined thatthe<br />
system for IFR operation basedon DRF Major<br />
interrelationship between this modification<br />
Change Project 240 and defined in MD-117-34-<br />
and any other previouslyinstalled<br />
20-000<strong>01</strong>.<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product<br />
10033429 DRF STIFTUNG LUFTRETTUNG P-<strong>EASA</strong>.R.S.<strong>01</strong>563 BK117 C-1 Title: Installation of Modular Airborne Data<br />
Recording/AcquisitionSystem<br />
(MADRAS)Description: Optional Installation of<br />
a Cockpit Voice and Flight DataRecorder<br />
System. The installation is in accordance with<br />
DRF change no.111, MOL MD-117-31-<br />
32-00003 Re<br />
10<strong>04</strong>1970 DRF STIFTUNG LUFTRETTUNG MB BK 117 C-2 Installation of a TETRA Digital Radio System<br />
into a NVIS certifiedCockpit.<br />
10<strong>01</strong>6181 DRIESSEN AIRCRAFT INTERIOR<br />
SYSTEMS<br />
10<strong>01</strong>6292 DRIESSEN AIRCRAFT INTERIOR<br />
SYSTEMS<br />
10<strong>01</strong>6552 DRIESSEN AIRCRAFT INTERIOR<br />
SYSTEMS<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. The in<br />
23.06.2009<br />
Required premodification: <strong>EASA</strong> approval<br />
<strong>EASA</strong> 10034057 (ECD major changeE-1807).<br />
This rotorcraft employs Night Vision Imaging<br />
System lighting, commonlynamed NVIS<br />
lighting, that has been certified to ensure the<br />
aircraft iscompatible with night vision goggl<br />
<strong>EASA</strong>.IM.A.S.02410 FAA STC ST00826LA AIRBUS A340-300 Installation of Lower Deck Mobile Crewrest. 1. The limitations and conditions as<br />
referenced in FAA STC ST00826LA apply.2.<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
The change has undergone NVIS 29.10.2<strong>01</strong>2<br />
compatibility engineering evaluation. Prior<br />
to installation of this modification it must<br />
be determined thatthe interrelationship<br />
between this modification and any other<br />
previouslyinstalled modification and/ or<br />
repair will intr<br />
<strong>EASA</strong>.IM.A.S.02588 REV. 1 FAA STC ST00843LA BOEING 757-200 SERIES Galley installation. None. Prior to installation of this modification the 18.02.2<strong>01</strong>0<br />
installer must determinethat the<br />
interrelationship between this modification<br />
and any otherpreviously installed<br />
modification will introduce no adverse<br />
effect uponthe airworthiness of the<br />
product. The installati<br />
<strong>EASA</strong>.IM.A.S.02932 BOEING 747-200B<br />
BOEING 747-200C<br />
Installation of a TBO Container. The installation should not be incorporated in<br />
any aircraft unless it is determined that the<br />
relationship between this installationand any<br />
previously approved configuration will not<br />
introduce any adverse effect upon the<br />
Airworthiness of the Aircraft. The a<br />
10037862 DUGAN KINETICS, L.L.C. FAA STC ST02127SE DC-9-81/-82/-83/-87, MD-88 Thrust Reverser/Installation of ejector thrust<br />
reverser on Pratt &Whitney Turbofan JT8D-<br />
217, -217A, 217C or -219 Engines as per FAA<br />
STCST02127SE dated 08 Apr. 2<strong>01</strong>1.<br />
Refer to FAA STC ST02127SE. Refer to FAA STC ST02127SE. 03.<strong>01</strong>.2<strong>01</strong>2<br />
10<strong>01</strong>5358 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.00657 FAA STC ST00515WI LEARJET 35<br />
Installation of an Allied Signal CAS 67A Traffic 1. This STC is approved only for the product<br />
<strong>04</strong>.<strong>04</strong>.2005<br />
LEARJET 35A<br />
Alert & Collision Avoidance (TCAS II). (STC configuration as defined in the approved design<br />
LEARJET 36<br />
ST00515WI)<br />
data referred to in the paragraph "Description".<br />
LEARJET 36A<br />
Compatibility with other aircraft/engine<br />
configurations shall be determined by the<br />
installer.<br />
10<strong>01</strong>5417 DUNCAN AVIATION, INC. <strong>EASA</strong>.IM.A.S.<strong>01</strong>139 FAA STC ST00546WI LEARJET 60 Installation of a Universal Avionics Inc. UNS-1B 1. For certification basis refer to FAA TCDS<br />
11.<strong>04</strong>.2005<br />
FMS (Dual).<br />
A10CE.2. This STC is approved only for the<br />
product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configurations shall b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 188/<strong>462</strong><br />
22.08.2007<br />
<strong>04</strong>.07.2008
Change language