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 10038915 MECAER AVIATION GROUP S.P.A. MBB-BK117 C-2 EC145 VIP MB Interiors Drawing No. None Prior to installation of this modification it 23.03.2012 6EC10000X001-001 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. 10039438 MECAER AVIATION GROUP S.P.A. REV. 1 AW109SP Installation of Cabinet Five Star P/N 6A10AD002-001 in AW109SP.Modification in accordance with MECAER Notice of Design Change NDC6A10AD-003 issue A dated 24/04/2012. This STC approval does not include the installation of the in-flightentertainment equipment inside the Cabinet Five Star. 10042023 MECAER AVIATION GROUP S.P.A. AW139 Ballast Installation P/N 6AB1AD018-001 This STC is only installable on AW139 Helicopters equipped withAgustaWestland Active Vibration Control System P/N 4G1830F00111 or4G1830F00211. 10015810 MEGGITT (ADDISON), Inc. EASA.IM.A.S.01879 FAA STC NO ST09494SC CESSNA 182S CESSNA 182T CESSNA T182T 10016754 METRO AVIATION, Inc. EASA.IM.R.S.01083 FAA STC SH3880SW EUROCOPTER DEUTSCHLAND MBB-BK Installation of an R134a vapour cycle airconditioning system Installation of a Vapor Cycle Air Conditioner in accordance with FA STC SH3880SW 10016780 METRO AVIATION, Inc. EASA.IM.R.S.01120 FAA STC SR01606NY-D EUROCOPTER DEUTSCHLAND Installation of Spectrolab SX-5 Starbust MBB-BK searchlight according to FAA STC SR01606NY- D 10016823 METRO AVIATION, Inc. EASA.IM.R.S.01188 REV. 1 FAA STC SR09163RC EUROCOPTER EC 135 Installation of mechanically driven vapor cycle Prior to installation of this modification the air condition system i.a.w. FAA STC installer must determine that the SR09163RC as amended by 18-06- interrelationship between this modification and 2007.Major change to EASA STC any other previously installed modification will EASA.IM.R.S.01188, addition of models and introduce no adverse effect upon the incorporation of technical modifications. airworthiness of the product. The install 10016976 METRO AVIATION, Inc. EASA.IM.R.S.01377 FAA STC SR09230RC EUROCOPTER DEUTSCHLAND EC-135 10035563 MICHELIN NORTH AMERICA, INC. FAA STC ST03642AT CL-600-2C10, CL-600-2D15 CL-600-2D24 10015379 MICRO AERODYNAMICS, INC. EASA.IM.A.S.01058 FAA STC SA00763SE PIPER PA-30 PIPER PA-39 Prior to installation of this modification it 16.05.2012 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. Prior to installation of this modification it 05.11.2012 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. This STC is approved only for the product 10.04.2006 configuration as defined in the approved design data referred to in the paragraph "Description". Compatibility with other aircraft/engine configurations shall be determined by the installer. 1. This STC is approved only for the product 31.05.2005 configuration as defined in the approved design data referred to in the paragraph "Description". Compatibility with other aircraft/engine configurations shall be determined by the installer. None 13.09.2006 Installation of landing gear skid extensions 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 Installation of Michelin's tire(s) P/N 029-901-0 on the main gear and/orP/N 036-897-0 on the nose landing gear of Bombardier CL-600- 2C10,CL-600-2D15, CL-600-2D24 aircraft wheel assembly. Installation of Vortex Generators on the Wing 1. This STC is approved only for the product leading edge, and vertical fin surfaces.Drawing configuration as defined in the approved design Package MA2122 Rev. IR dated 25 October data referred to in the paragraph "Description". 1999, or later approved revision.AFM Compatibility with other aircraft/engine Supplement for PA-30 & PA-39 dated 13 July configurations shall be determined by the 2005.Installation Manual MA2123 Rev. IR da installer. 14.04.2008 26.11.2007 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. 30.06.2011 04/01/2013 Page 332/462 08.08.2005
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10015979 MICRO AERODYNAMICS, INC. EASA.IM.A.S.02131 FAA STC SA00887SE CESSNA 206 Installation of vortex generators on the wings, 1. If more than Five vortex generators are 20.09.2006 CESSNA 206H tail surfaces and vertical fin damaged or missing, the aircraft is not CESSNA 207 airworthy2. This STC is approved only for the CESSNA 207A product configuration as defined in the CESSNA P206 approved design data referred to in the CESSNA P206A CESSNA P206B CESSNA P206C CESSNA P206D CESSNA P206E CESSNA T206H CESSNA T207 CESSNA T207A CESSNA TP206A CESSNA TP206B CESSNA TP206C CESSNA TP206D CESSNA TP206E CESSNA TU206A CESSNA TU206B CESSNA TU206C CESSNA TU206D CESSNA TU206E CESSNA TU206F CESSNA U206 CESSNA U206A CESSNA U206B CESSNA U206C CESSNA U206D CESSNA U206E CESSNA U206F CESSNA U206G paragraph "Description". Compatibility with oth 10016088 MICRO AERODYNAMICS, INC. EASA.IM.A.S.02275 FAA STC SA00831SE CESSNA 172A-S Installation of vortex generators on the wings Approval of this change in type design applies 13.04.2007 CESSNA 172RG and tail surfaces in accordance with the to the aircraft listed on AML SA00831SE only. CESSNA 175A-C provisions of AML SA00831SE. This approval should not be extended to other CESSNA P172D aircraft on which other previously approved modification are incorporated unless it is determined that the relationsh 10016354 MICRO AERODYNAMICS, INC. EASA.IM.A.S.02675 FAA STC SA00941SE CESSNA 210G,H,J,K,L,M,N, CESSNA P210N CESSNA T210G CESSNA T210J, T210H CESSNA T210K CESSNA T210L CESSNA T210M CESSNA T210N Installation of vortex generators on the wing and tail surfaces. 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 333/462 27.02.2008
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04/01/2013 Page 1/462 - EASA

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