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 10016558 MICRO AERODYNAMICS, INC. EASA.IM.A.S.02942 REV 1 FAA STC SA00834SE CESSNA 182C Installation of vortex generators on the wings 1. Prior to installation of this modification the 27.10.2008 CESSNA 182D and tail surfaces in accordance with the installer must determine that the CESSNA 182E provisions of AML SA00834SE. interrelationship between this modificationand CESSNA 182F any other previously installed modification CESSNA 182G will introduce no adverse effect upon the CESSNA 182H CESSNA 182J CESSNA 182K CESSNA 182L CESSNA 182M CESSNA 182N CESSNA 182P CESSNA 182Q CESSNA 182R CESSNA 182S CESSNA 182T CESSNA F182-P CESSNA F182-Q CESSNA FR-172-E CESSNA FR-172-F CESSNA FR-172-G CESSNA FR-172-H CESSNA FR-172-J CESSNA FR-172-K CESSNA FR-182 CESSNA R172E/F/G/H/J/K CESSNA R182 CESSNA T182T CESSNA TR182 airworthiness of the produc 10016576 MICRO AERODYNAMICS, INC. EASA.IM.A.S.02974 REV. 1 FAA STC SA01266SE PA-32-301, PA-32-301T Installation of vortex generators on the wings If more than five vortex generators are Prior to installation of this modification the 10.02.2010 PA-32-301FT, PA-32-301XTC and tail surfaces inaccordance with the damaged or missing, the Aircraftis not installer must determinethat the PA-32R-301(HP), PA-32R-301T provisions of AML SA01266SE. airworthy. interrelationship between this modification PIPER PA-32R-301(SP) and any otherpreviously installed modification will introduce no adverse effect uponthe airworthiness of the product. The installati 10016663 MICRO AERODYNAMICS, INC. EASA.IM.A.S.03126 REV 1 FAA STC SA01646SE CESSNA 172 Installation of vortex generators on the wings Prior to installation of this modification the 17.03.2009 CESSNA 175 and tail surfaces in accordance with the installer must determine that the CESSNA 180 provisions of AML SA01646SE. interrelationship between this modification and CESSNA 180A any other previously installed modification will CESSNA 180B introduce no adverse effect upon the CESSNA 180C CESSNA 180D CESSNA 180E CESSNA 180F CESSNA 180G CESSNA 180H CESSNA 180J CESSNA 180K CESSNA 182 CESSNA 182A CESSNA 182B CESSNA 185 CESSNA 185A CESSNA 185B CESSNA 185C CESSNA 185D CESSNA 185E CESSNA A185E CESSNA A185F airworthiness of the product.The installa 10031549 MICRO AERODYNAMICS, INC. FAA STC SA00834SE 1. 150F, 150G, 150H, 150J Installation of vortex generators on the wings Approval of this change in type design applies Prior to installation of this modification the 25.08.2010 1. 150K, 150L, 150M, A150K and vertical tailsurfaces on Cessna 150/152 to the aircraft listed onAML SA01065SE only. installer must determinethat the 1. A150L, A150M, 152, A152 (see applicabel Model list). This approval should not be extended to interrelationship between this modification 2. F150G, F150H, F150J otheraircraft on which other previously and any otherpreviously installed 2. F150K, F150L, F150M, approved modification areincorporated unless modification will introduce no adverse 2. FA150K, FA150L, F152, FA152 it is determined that the relationship effect uponthe airworthiness of the product. The installati 04/01/2013 Page 334/462
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10034885 MICRO AERODYNAMICS, INC. FAA STC SA02098SE 65-90, 65-A90, 65-A90-1 Installation of Vortex Generators on the wings If more than five vortex generators, or either This STC has been found compatible 10.05.2011 65-A90-2, 65-A90-3, 65-A90-4 and tail surfaces, andstrakes on the engine nacelle stake are damagedor missing, the with FAA STC SA10747SC dated B90, C90, C90A, C90GT nacelles. aircraft is no longer airworthy. October06, 2006 (EASA STC ref C90GTI, E90, H90 EASA.IM.A.S.02863 Rev 1)Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previou 10038573 MICRO AERODYNAMICS, INC. FAA STC#SA01681SE 1. PA-34-200, PA-34-200T, Installation of vortex generators on the wings, If more than five vortex generators are The installation of this modification by 27.02.2012 1. PA-34-220T (SENECA III) horizontal and verticaltail surfaces (all models), damaged or missing, the aircraftis no longer third persons is subject towritten 1. PA-34-220T (SENECA IV) and an increase in maximum zero fuel airworthy. permission of the approval holder and 2. PA-34-220T (SENECA V) weight(PA-34-200T and M20 03 only). disposal of the approvedappropriate 3. PZL M20 03 "MEWA" documentation.Prior to installation of this modification it must be determined thatthe interrelationship b 10040949 MICRO AERODYNAMICS, INC. REV. 2 FAA STC SA01161SE PA-32-260, PA-32-300 Installation of Vortex Generators on the wing If the holder agrees to permit another person to The installation of this modification by 11.09.2012 PA-32S-300, PA-32R-300 and tail surface accordingto drawing package use this certificate toalter the product, the third persons is subject towritten MA2174, revision IR dated 06-Sep-2002 holder shall give the other person permission of the approval holder and andinstallation manual MA2175 revision A writtenevidence of that permission.If more than disposal of the approvedappropriate dated 27-Aug-2003 or later FAAapproved 5 vortex generators are damaged or missing, documentation.Prior to installation of this revision to either of these documents. the A/C is notairworthy. modification it must be determined thatthe interrelationship b 10041846 MICRO AERODYNAMICS, INC. FAA STC SA02226SE DA 42, DA 42NG, DA 42M-NG Installation of vortex generators on the wings None Prior to installation of this modification it 19.10.2012 and tail surfaces.FAA STC SA02226SE 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. 10015935 MID-CANADA MOD CENTER EASA.IM.A.S.02075 SA03-92 Cockpit voice recorder replacement with Universal CVR 30 or CVR 120 -- 14.12.2006 10036039 MID-CANADA MOD CENTER CESSNA 550, S550 Installation of Rockwell Collins Proline 21 None Prior to installation of this modification it 08.08.2011 Integrated Display Systemwith new VHF must be determined thatthe communication transceivers, Navigation interrelationship between this modification Receivers withintegral ADF, Distance and any other previouslyinstalled Measuring Equipment Transceivers and Mode modification and/ or repair will introduce STransponders with Elementary Surveillance no adverse effectupon the airworthiness capability, R of the product. 10038891 MID-CANADA MOD CENTER TCCA STC SA10-16 CL-600-2B19 CMC Electronics CMA-1100, Class II Electronic Flight Bag (EFB) SystemInstallation 10041743 MID-CANADA MOD CENTER TCCA STC O-LSA09-348/D CL-600-2B19 TrueNorth Satphone Installation Restricted to ASN 8092.EASA STC Nos.10038463 and 10028338 Rev. 2 (Transport Canada STC Nos.O-LSA09-344/D and C-LSA09-326/D) are pre-requisites to this approval. 10015913 MILLENNIUM CONCEPTS, INC. EASA.IM.A.S.02042 REV. 1 FAA STC SA01160WI CESSNA 208 CESSNA 208B 10041159 MILLENNIUM CONCEPTS, INC. REV. 1 FAA STC SA01671WI - D 1- G36 - BONANZA 2- G58 - BARON 10016595 MITSUBISHI HEAVY INDUSTRIES AMERICA Installation of Executive Interior in Cessna Models 208, 208B Caravan Installation of interior configuration per Master Drawing List2033-MDL040, rev. P, dated 8 February 2012. 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. 21.03.2012 If the holder agrees to permit another person to use this certificate toalter the product, the holder shall give the other person writtenevidence of that permission. EASA.IM.A.S.03006 FAA STC SA1751SW Flight Crew Restraint 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 installa Prior to installation of this modification it 12.10.2012 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. The installation of this modification by third persons is subject towritten permission of the approval holder and disposal of the approvedappropriate documentation. Prior to installation of this modification it must be determined thatthe interrelationship 04/01/2013 Page 335/462 08.02.2008 27.08.2012 22.09.2008
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04/01/2013 Page 1/462 - EASA

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