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 />
10031520 STG AEROSPACE INC. REV. 1 FAA STC ST02311AT DHC-8-102, -103, -106, -2<strong>01</strong> Installation of SaftGlo Inc. Photoluminescent Cabin interior arrangement must be approved Prior to installation of this modification it 16.03.2<strong>01</strong>1<br />
DHC-8-202, -3<strong>01</strong>, -302, -4<strong>01</strong> floor proximity EscapePath Marking System in accordance with SaftGloMDL, Report must be determined thatthe<br />
DHC-8-402<br />
(PFEEPMS)<br />
Number M07-2, Rev. H, dated 1 August 2007 interrelationship between this modification<br />
incorporatingSaftGlo drawing SG-DHC8, Rev. and any other previouslyinstalled<br />
E, dated 1 August 2007.Electrically-lit door exit modification and/ or repair will introduce<br />
marker lighting levels and cabin lighti<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0330 STG AEROSPACE INC. REV. 1 FAA STC ST03684AT 777-200/300/300ER Validation of FAA STC #ST03684AT<br />
(Installation of SafTGloPhotoluminescent<br />
Escape Path Marking System)<br />
10039197 STRAIGHT FLIGHT, Inc. CESSNA 510 Modification of the aircraft interior to allow for<br />
two configurations:1) Observer configuration<br />
and2) back to the Type Certificated standard<br />
Executive configuration inaccordance with<br />
Straight Flight Master Drawing List Document<br />
No.4979-MDL-<strong>01</strong>, Revision B,<br />
10<strong>01</strong>5479 STRUCTURAL INTEGRITY<br />
ENGINEERING<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>233 SA6073NM BEECH 99<br />
BEECH 99A<br />
BEECH B99<br />
BEECH C99<br />
Structural Life Extension of Wing Spars<br />
according to FAA STC SA6073NM as<br />
amended on 30 December 1993.<br />
10033267 SUPERVAN SYSTEMS, LTD. REV. 1 FAA STC SA10841SC 208, 208B Installation of the Honeywell TPE331-12JR<br />
engine and HartzellHC-B4TN-5QL/LT10890-<br />
N(K) propeller and associated components<br />
inaccordance with FAA STC SA10841SC, last<br />
amended December 15, 2<strong>01</strong>0.<br />
10<strong>01</strong>4781 SWS CERTIFICATION SERVICES LTD <strong>EASA</strong>.A.S.02979 AIRBUS A320 SERIES<br />
BOEING 717<br />
BOEING 727<br />
BOEING 737<br />
BOEING 747<br />
BOEING 757<br />
BOEING 767<br />
BOEING DC-9<br />
EMBRAER ERJ 135 SERIES<br />
EMBRAER ERJ 145 SERIES<br />
MD-11<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 />
25.07.2<strong>01</strong>2<br />
According limitations section of AFMS. This<br />
approval is limited to theinstallation and use of<br />
a 40 Cubic Foot occupant Oxygen supply<br />
tankonly.<br />
According to FAA STC SA6073NM and as<br />
further defined below.Compliance with the<br />
Airworthiness Limitations contained in the<br />
above referenced documents extends the<br />
existing 20,000 flight hour Beech fatigue life<br />
limits for wing spars of Beechcraft 99, 99A,<br />
B99<br />
If the holder agrees to permit other person to<br />
use this certificate toalter the product, the<br />
holder shall give the other person<br />
writtenevidence of that permission.For Cessna<br />
208: This STC is limited to standard version<br />
(without cargopod) to serial numbers<br />
Installation of STG Aerospace SafTGlo As defined in SWS Certification Ltd. Design<br />
Photoluminiscent Bulkhead/ Divider Exit Signs. report 30<strong>01</strong>-DR-0<strong>01</strong>, Issue 1 or later <strong>EASA</strong><br />
approved issue.<br />
10<strong>01</strong>5139 SWS CERTIFICATION SERVICES LTD <strong>EASA</strong>.A.S.03495 BAE 146 STG Aerospace Wireless Emergency Primary<br />
Power System (WEPPS) Installation.<br />
10032329 SWS CERTIFICATION SERVICES LTD REV. 1 BOEING B747-300<br />
BOEING B747-400<br />
Installation of SaftGlo Inc. Photoluminescent<br />
Floor Proximity EmergencyEscape Path<br />
Marking System (FPEEPMS) in accordance<br />
with SWSCertification Services Design Report<br />
3<strong>04</strong>6-DR-<strong>01</strong> Rev. 2, dated 27 August2<strong>01</strong>0 or<br />
later approved revision.<br />
10<strong>04</strong>0318 SWS CERTIFICATION SERVICES LTD REV. 1 A340-312 This modification intends to:The proposed<br />
major change is to install the AmSafe Airbag<br />
System todemonstrate compliance to<br />
CS25.562(c)(5) when the Panasonic eX2<br />
seatbackmonitor is installed. The monitor is to<br />
be electrically integrated withthe rest of the P<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 will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Prior to installation of this modification it 17.<strong>04</strong>.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 />
02.<strong>01</strong>.2006<br />
Prior to installation of this modification it 10.<strong>01</strong>.2<strong>01</strong>1<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 />
19.06.2007<br />
08.12.2008<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 />
08.11.2<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 />
24.10.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 436/<strong>462</strong>
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