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>04</strong>2498 UNIAIR B300 Installation of 230 V AC - 50 Hz electrical If the holder agrees to permit another person to The installation of this modification by 05.12.2<strong>01</strong>2<br />
distribution on aircraft, toallow passengers to use this certificate toalter the product, the third persons is subject towritten<br />
plug personal electronic devices. According holder shall give the other person<br />
permission of the approval holder and<br />
toSB-UAE-003-12-0<strong>01</strong>.<br />
writtenevidence of that permission.<br />
disposal of the approvedappropriate<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>01</strong>5829 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.<strong>01</strong>918 FAA STC ST00839LA BOMBARDIER DHC-8-100 Installation of GPS Landing System in The approval is limited to<br />
14.07.2006<br />
SERIES<br />
deHavilland DHC-8 aircraft(Validation of FAA Bombardier/deHavilland DHC-8 100 series<br />
STC ST00839LA amended 27/02/2006) aircraft<br />
10<strong>01</strong>6206 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02450 FAA STC ST<strong>01</strong>879LA BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Universal Avionics Vision-1tm Synthetic<br />
3A<br />
System installed in Canadair Challenger CL600<br />
Series.<br />
10<strong>01</strong>6253 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02531 REV. 2 FAA STC ST02070 LA BOMBARDIER CL-600-1A11 (CL- Universal Avionics UNS-1Fw with embedded<br />
600<br />
WAAS. MDL -4 Config (TripleUNS-1Fw FMS<br />
BOMBARDIER CL-600-2A12 (CL- with P/N 10709 #3 GPS-WAAS/Sirius<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Antenna)<br />
10<strong>01</strong>6279 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02568 FAA STC ST<strong>01</strong>763CH-D BOMBARDIER CL-600-1A11 (CL- Installation of Universal Avionics EFI-890R Flat<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Panel Displays and MFD-640.<br />
10<strong>01</strong>6375 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.02698 FAA STC ST<strong>01</strong>640LA BOMBARDIER CL-600-2B16 (6<strong>01</strong>- Installation of Universal Avionoics Radio<br />
3A<br />
Control Units (RCU)<br />
10<strong>01</strong>6614 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.03<strong>04</strong>0 REV. 1 FAA STC ST02<strong>01</strong>2LA CL-600-1A11 (CL-600)<br />
CL-600-2A12 (CL-6<strong>01</strong>)<br />
CL-600-2B16<br />
Installation of Universal Avionics Application<br />
Server Unit (ASU). Minorrevision to ASU FAA<br />
STC ST02<strong>01</strong>2LA, ESTC <strong>EASA</strong>.IM.A.S.03<strong>04</strong>0<br />
None Prior to installation of this modification the<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 />
23.11.2007<br />
06.07.2009<br />
23.11.2007<br />
Restricted to ASN 5<strong>04</strong>2. 03.06.2008<br />
Restricted to the following MDL Configurations:-<br />
3 Application Server Unit (ASU) (ETSO<br />
<strong>EASA</strong>.IM.210.708) with Dual CursorControl<br />
Panels (CCP) (ETSO <strong>EASA</strong>.IM.210.708)<br />
displayed on EFI-890RNavigation Display<br />
(ETSO <strong>EASA</strong>.IM.210.344).-4 Application<br />
Server Unit (AS<br />
10<strong>01</strong>6615 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.03<strong>04</strong>1 FAA STC ST<strong>01</strong>303LA BOMBARDIER CL-600-1A11 (CL- Installation of Universal Avionics UNS-1F/L and 1. Restricted to the following configurations:-3<br />
600<br />
optional UniLink communication system Config: UL-7<strong>01</strong> with SCN 22.X-4 Config: UNS-<br />
BOMBARDIER CL-600-2A12 (CL-<br />
1F with SCN 802.X and A702 Maps2. Prior to<br />
6<strong>01</strong><br />
installation of this modification the installer must<br />
BOMBARDIER CL-600-2B16<br />
determine that the interrelationship between<br />
this modification andan<br />
10<strong>01</strong>6616 UNIVERSAL AVIONICS SYSTEMS <strong>EASA</strong>.IM.A.S.03<strong>04</strong>2 FAA STC ST<strong>01</strong>141LA BOMBARDIER CL-600-1A11 (CL- Installation of Universal Avionics Terrain<br />
600<br />
BOMBARDIER CL-600-2A12 (CL-<br />
6<strong>01</strong><br />
BOMBARDIER CL-600-2B16<br />
Awareness Warning System (TAWS)<br />
10<strong>01</strong>4248 UUDS AERO <strong>EASA</strong>.A.S.<strong>01</strong>470 REV. 2 SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
1. Restricted to the following configuration:-4<br />
Config: Terrain Awareness and Warning<br />
System (TAWS) operating software SCN 11.X<br />
(ETSO <strong>EASA</strong>.IM.21O.<strong>01</strong>70) displayed on MFD-<br />
640 (ETSO <strong>EASA</strong>.IM.21O.905)2. Prior to<br />
installation of this modification the installer m<br />
Prior to installation of this modification the 06.07.2009<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 />
07.<strong>01</strong>.2009<br />
07.<strong>01</strong>.2009<br />
Modification of STC <strong>EASA</strong>.A.S.<strong>01</strong>470 to allow None Prior to installation of this modification it 03.11.2<strong>01</strong>0<br />
the baby to sit down in thebassinet fixed on the<br />
must be determined thatthe<br />
partitions or under the hatracks.<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 />
10034806 V. KELNER PILATUS CENTRE REV. 1 TCCA STC SA02-80 PC-12, PC-12/45, PC-12/47 Installation Feather Inhibit System None The approval holder shall fulfil the 18.10.2<strong>01</strong>1<br />
PC-12/47E<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
10039278 VAN HORN AVIATION, L.L.C. 206B, L, L1, L3, L4 Installation of Replacement Tail Rotor Blades When antenna holder PP-10-A6<strong>01</strong> is installed Prior to installation of this modification it 23.<strong>04</strong>.2<strong>01</strong>2<br />
VNE is limited to 120 kts;When rack PP-10- must be determined thatthe<br />
A421 is installed, carriage of passengers in interrelationship between this modification<br />
front seatsis prohibited;When racks PP-10- and any other previouslyinstalled<br />
A4<strong>01</strong>c or PP-A461 are installed, a maximum of modification and/ or repair will introduce<br />
2passengers in rear seats is permitted no adverse effectupon the airworthiness<br />
of the product.<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 456/<strong>462</strong>
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