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>6554 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02936 FAA STC ST02536CH AIRBUS A330-3<strong>01</strong><br />
Activation of Honeywell Runway Awareness Prior to installation of this modification the<br />
03.09.2008<br />
AIRBUS A330-302<br />
and Advisory System (RAAS).<br />
installer must determine that the<br />
AIRBUS A330-303<br />
interrelationship between this modification and<br />
AIRBUS A330-321<br />
any other previously installed modification<br />
AIRBUS A330-322<br />
will introduce no adverse effect upon the<br />
AIRBUS A330-323<br />
AIRBUS A330-341<br />
AIRBUS A330-342<br />
AIRBUS A330-343<br />
airworthiness of the product.<br />
10<strong>01</strong>6555 ARMSTRONG AEROSPACE Inc. <strong>EASA</strong>.IM.A.S.02937 FAA STC ST02537CH AIRBUS A340-311<br />
Activation of Honeywell Runway Awareness Prior to installation of this modification the<br />
08.<strong>01</strong>.2009<br />
AIRBUS A340-312<br />
and Advisory System(RAAS)<br />
installer must determine that the<br />
AIRBUS A340-313<br />
interrelationship between this modification and<br />
AIRBUS A340-642<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10029877 ARMSTRONG AEROSPACE Inc. FAA STC ST02776CH B737-300, B737-500 Activation of Honeywell Runway Awareness None Prior to installation of this modification it 28.<strong>04</strong>.2<strong>01</strong>0<br />
and Advisory System (RAAS)<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 />
10031966 ARMSTRONG AEROSPACE Inc. FAA STC ST02778CH 747-400, 747-400 (BCF)<br />
747-400F<br />
10031995 ARMSTRONG AEROSPACE Inc. FAA STC ST02376CH ATR72-2<strong>01</strong>,ATR72-202,ATR72-<br />
212<br />
Activation of Honeywell Runway Awareness &<br />
Advisory System (RAAS) inaccordance with<br />
Armstrong Aerospace Master Data List DOC<br />
No.DC1<strong>04</strong>-7007-00 Revision D,dated<br />
November 9,2009 or later FAA aproved<br />
revision.Validation of FAA STC ST02778CH<br />
<strong>EASA</strong> Validation of FAA STC ST02376CH (as<br />
amended by FAA on 24th June2<strong>01</strong>0)<br />
regarding: Installation of a Rockwell Collins HF-<br />
9000 HF Radio System in accordancewith<br />
Armstrong Aerospace Master Data List, Doc.<br />
Number DC1<strong>04</strong>-4033-00,Revision E, dated<br />
27th May 2<strong>01</strong><br />
10034747 ARMSTRONG AEROSPACE Inc. FAA STC ST02939CH-D B737-800 Validation of FAA STC ST02939CH-<br />
DPANASONIC DMPES - In flight<br />
Entertainment System installation<br />
None Armstrong Aerospace Airplane Flight<br />
Manual Supplement for B747-400series<br />
aircraftDoc. No. DC303-7007-00 Rev.- is<br />
required on board the aircraft.<br />
27.09.2<strong>01</strong>0<br />
None After the analysis performed by<br />
Armstrong Aerospace in accordance<br />
withSpecial Condition <strong>EASA</strong> CRI H-0<strong>01</strong><br />
no additional specific EWIS ICAS<br />
taskshave been identified for this <strong>EASA</strong><br />
STC validation with regards thosealready<br />
identified and approved to the original<br />
30.09.2<strong>01</strong>0<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 />
27.<strong>04</strong>.2<strong>01</strong>1<br />
10038436 ARMSTRONG AEROSPACE Inc. FAA STC ST02947CH B737-800 Validation of FAA STC ST02947CH:<br />
1) Modification in accordance with this STC It must be determined that the activation 02.03.2<strong>01</strong>2<br />
Installation and activation of aPanasonic Global requires prior or concurrentmodification in of the Panasonic GlobalCommunications<br />
Communications Suite (GCS) system in accordance with <strong>EASA</strong> STC 10038435.2 )The Suite (GCS) System Provisions (<strong>EASA</strong><br />
accordance withArmstrong Aerospace Master activation of the Panasonic Global<br />
STC 10038435) inaccordance with this<br />
Data List DC1<strong>04</strong>-9<strong>04</strong>3-00, Revision A, dated Communications Suite (GCS)System STC and their interrelationships between<br />
22December 2<strong>01</strong>1.<br />
Provisions (<strong>EASA</strong> STC 10038435) in and anyother previously installed STC,<br />
accordance with this STC<br />
modification and / or r<br />
10<strong>04</strong>0305 ARMSTRONG AEROSPACE Inc. FAA STC ST03085CH B747-400 Installation of provisions for Panasonic Global<br />
Communications Suite(GCS) System in<br />
accordance with Armstrong Aerospace Inc.<br />
Master DataList DC1<strong>04</strong>-9027-00 Rev. D dated<br />
April 25, 2<strong>01</strong>2, or later<br />
approvedrevision.Validation of FAA STC<br />
ST03085CH<br />
10<strong>04</strong><strong>04</strong>70 ARMSTRONG AEROSPACE Inc. FAA STC ST02948CH 767-300 Installation of Board Connect In-Flight<br />
Entertainment System<br />
None -These provisions are for a Panasonic<br />
Global Communications Suite<br />
(GCS)System. The installation and<br />
activation of the GCS system is to be<br />
inaccordance with a separate approval.<br />
Additional approval is required forthe<br />
installation of additional GCS system eq<br />
This system is intended to provide internet<br />
connection and e-mailservices using portable<br />
electronic devices (PEDs). Any other<br />
intendedfunction of this equipment will require<br />
further certification approval.<br />
22.06.2<strong>01</strong>2<br />
Prior to installation of this modification it 05.07.2<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 />
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