04/01/2013 Page 1/462 - EASA

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EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10031520 STG AEROSPACE INC. REV. 1 FAA STC ST02311AT DHC-8-102, -103, -106, -201 Installation of SaftGlo Inc. Photoluminescent Cabin interior arrangement must be approved Prior to installation of this modification it 16.03.2011 DHC-8-202, -301, -302, -401 floor proximity EscapePath Marking System in accordance with SaftGloMDL, Report must be determined thatthe DHC-8-402 (PFEEPMS) Number M07-2, Rev. H, dated 1 August 2007 interrelationship between this modification incorporatingSaftGlo drawing SG-DHC8, Rev. and any other previouslyinstalled E, dated 1 August 2007.Electrically-lit door exit modification and/ or repair will introduce marker lighting levels and cabin lighti no adverse effectupon the airworthiness of the product. 10040330 STG AEROSPACE INC. REV. 1 FAA STC ST03684AT 777-200/300/300ER Validation of FAA STC #ST03684AT (Installation of SafTGloPhotoluminescent Escape Path Marking System) 10039197 STRAIGHT FLIGHT, Inc. CESSNA 510 Modification of the aircraft interior to allow for two configurations:1) Observer configuration and2) back to the Type Certificated standard Executive configuration inaccordance with Straight Flight Master Drawing List Document No.4979-MDL-01, Revision B, 10015479 STRUCTURAL INTEGRITY ENGINEERING EASA.IM.A.S.01233 SA6073NM BEECH 99 BEECH 99A BEECH B99 BEECH C99 Structural Life Extension of Wing Spars according to FAA STC SA6073NM as amended on 30 December 1993. 10033267 SUPERVAN SYSTEMS, LTD. REV. 1 FAA STC SA10841SC 208, 208B Installation of the Honeywell TPE331-12JR engine and HartzellHC-B4TN-5QL/LT10890- N(K) propeller and associated components inaccordance with FAA STC SA10841SC, last amended December 15, 2010. 10014781 SWS CERTIFICATION SERVICES LTD EASA.A.S.02979 AIRBUS A320 SERIES BOEING 717 BOEING 727 BOEING 737 BOEING 747 BOEING 757 BOEING 767 BOEING DC-9 EMBRAER ERJ 135 SERIES EMBRAER ERJ 145 SERIES MD-11 none Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 25.07.2012 According limitations section of AFMS. This approval is limited to theinstallation and use of a 40 Cubic Foot occupant Oxygen supply tankonly. According to FAA STC SA6073NM and as further defined below.Compliance with the Airworthiness Limitations contained in the above referenced documents extends the existing 20,000 flight hour Beech fatigue life limits for wing spars of Beechcraft 99, 99A, B99 If the holder agrees to permit other person to use this certificate toalter the product, the holder shall give the other person writtenevidence of that permission.For Cessna 208: This STC is limited to standard version (without cargopod) to serial numbers Installation of STG Aerospace SafTGlo As defined in SWS Certification Ltd. Design Photoluminiscent Bulkhead/ Divider Exit Signs. report 3001-DR-001, Issue 1 or later EASA approved issue. 10015139 SWS CERTIFICATION SERVICES LTD EASA.A.S.03495 BAE 146 STG Aerospace Wireless Emergency Primary Power System (WEPPS) Installation. 10032329 SWS CERTIFICATION SERVICES LTD REV. 1 BOEING B747-300 BOEING B747-400 Installation of SaftGlo Inc. Photoluminescent Floor Proximity EmergencyEscape Path Marking System (FPEEPMS) in accordance with SWSCertification Services Design Report 3046-DR-01 Rev. 2, dated 27 August2010 or later approved revision. 10040318 SWS CERTIFICATION SERVICES LTD REV. 1 A340-312 This modification intends to:The proposed major change is to install the AmSafe Airbag System todemonstrate compliance to CS25.562(c)(5) when the Panasonic eX2 seatbackmonitor is installed. The monitor is to be electrically integrated withthe rest of the P Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product. The install Prior to installation of this modification it 17.04.2012 must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 02.01.2006 Prior to installation of this modification it 10.01.2011 must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 19.06.2007 08.12.2008 none Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 08.11.2010 none Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 24.10.2012 04/01/2013 Page 436/462
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10040913 SWS CERTIFICATION SERVICES LTD REV. 1 B747-8 Installation of the Aeroloft(TM) Overhead No passenger allowed in the cabin. Prior to installation of this modification it 11.12.2012 Sleeping Compartmentimmediately forward of must be determined thatthe the Overhead Crew Rest. Two configurations interrelationship between this modification are certified:1. With lounge module2. Without and any other previouslyinstalled lounge module and with following modification and/ or repair will introduce peculiarities:2.1 Stair module is located aft to no adverse effectupon the airworthiness of the product. 10015622 TACA INTERNATIONAL AIRLINES EASA.IM.A.S.01574 - AIRBUS A320-233 Automatic ELT Provisions installlation and activation 10015623 TACA INTERNATIONAL AIRLINES EASA.IM.A.S.01575 - AIRBUS A320-233 Automatic ELT- Provisions installation and activation 10015624 TACA INTERNATIONAL AIRLINES EASA.IM.A.S.01576 A320-233 Equipment and furnishing - delivery configuration of passenger cabin - 180 pax 10015667 TACA INTERNATIONAL AIRLINES EASA.IM.A.S.01643 AIRBUS A320-233 Equipment and furnishing - Delivery configuration of passenger cabin - 180 pax 10015703 TACA INTERNATIONAL AIRLINES EASA.IM.A.S.01690 - AIRBUS A320-233 Autoflight - Activate FMGC Nav data base to 400Kwords - Pin programming 10032788 TALON AEROSPACE LLC FAA STC ST03574AT SEE EASA APPROVED MODEL Anti Collision Light installationThis STC installs LIST a new model of Anti Collision Light. 10042345 TAMARACK AEROSPACE GROUP, INC. FAA STC SA02216SE SR20/SR22 Removal of mechanical link between engine throttle control and propeller RPM control. Installation of a separate RPM control lever, linkagebetween Cirrus RPM cable/cam followers, center console to accommodatethree-lever configuration, new knobs for all lev 10030951 TASS INC FAA STC ST00593SE-D B747-400 Active Noise Reduction Headset Installation Provisions in accordancewith BF Goodrich Master Drawing List D2000-396, sheet 1, Revision New,dated November 22, 2000 or later FAA/DAS approved revision.Validation of FAA STC ST00593SE-D 10031609 TASS INC FAA STC ST00583SE-D B757-200 Installation of Passenger Accommodations - STC ST00583SE-D This STC is limited to A320 MSN 561 20.10.2005 This STC is limited to A320-233 MSN 558 20.10.2005 This STC is limited to the A320 MSN 561 26.05.2005 This STC is Limited to the A320 MSN 558. 26.10.2005 1. This STC is limited to the A320 MSN`s 558 and 561 04.11.2005 None Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 01.12.2010 SR20 serial numbers 1005 through 1885; SR22 serial numbers 0002 and subsequent without Garmin PerspectiveAvionics Installation; SR20 airplanes equipped with Hartzell BHC-J2YF-1BF/F7694 propellerassemblies must have a placard installed reading "Avoid operat Prior to installation of this modification it 26.11.2012 must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. None None 15.07.2010 None Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 30.08.2010 10014381 TATENHILL AVIATION Ltd. EASA.A.S.01665 PILATUS PC-12/45 Substantiation of Garmin AT GPS400 installation for IFR 20.06.2006 10014412 TATENHILL AVIATION Ltd. EASA.A.S.01711 CESSNA F182-Q Design data and equipment installation in order -- to approve the aircraft for IFR. 08.01.2007 10014909 TATENHILL AVIATION Ltd. EASA.A.S.03153 CESSNA 500 Approval of a Mode S EHS ATC System. Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product. The install 10.07.2008 10014923 TATENHILL AVIATION Ltd. EASA.A.S.03170 CESSNA 500 Approval of a Mode S EHS ATC System. Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product. The install 10015168 TATENHILL AVIATION Ltd. EASA.A.S.03538 CESSNA 525 Dual Garmin GPS/NAV/COM Upgrade. Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product. The install 04/01/2013 Page 437/462 23.09.2008 26.05.2008
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04/01/2013 Page 1/462 - EASA

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