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 10016326 THE BOEING COMPANY - EASA.IM.A.S.02635 FAA STC SA2123CE-D AMENDED 19 BOEING 747-2B5B Conversion of Passenger Airplane to dedicated This approval is limited to ariplane model B747- 28.01.2008 Special Freighter with Main Deck Side Cargo 200B S/N 22482 and S/N 22485.Boeing Door in accordance with Boeing Drawing List Commercial Airplane Groupe - Wichita Dvision, document D3-8857, Section V, Appendix 31, Airplane Flight Manual Supplement dated 9 Rev.CN September 1991 or revision for AFM D6- 13703.3B5 or later approved revisions of this 10016519 THE BOEING COMPANY - EASA.IM.A.S.02891 Conversion of Passenger Airplane to Main Deck Side Cargo Door Dedicated Special Freighter as defined by FAA approved Boeing Document D800-10610-7, Revision New or later FAA approved revisions. (Validation of FAA STC ST00252WI-D) 10016644 THE BOEING COMPANY - EASA.IM.A.S.03085 REV. 1 FAA STC SA2124CE-D BOEING 747-200B Conversion of Passenger Airplane to Main Deck Side Cargo Door Dedicated Special Freighter in accordance with Boeing Drawing List document D3-8857, Section V, Appendix 33, Rev. CS. 10015813 THE GOODYEAR TIRE & RUBBER COMPANY EASA.IM.A.S.01882 FAA STC ST03183AT 1. AIRBUS A330 2. AIRBUS A340 Installation of Goodyear Radial Tire Size 1050x395R16, P/N 109Q89 1 on Airbus A330 and A340 Nose Landing Gear according to FAA STC ST03183AT 10038928 THE NORDAM GROUP, Inc. REV. 1 FAA STC ST09034SC A319, A320, A321 Installation of C & X Band Fuselage Nose Radome Shell 10014219 THIELERT AIRCRAFT ENGINES GMBH EASA.A.S.01380 REV. 4 APEX DR 400 RP, 400/120D APEX DR 400/140B APEX DR 400/180R, 400/200R 10014287 THIELERT AIRCRAFT ENGINES GMBH EASA.A.S.01527 REV. 6 LBA EMZ SA1295 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172R 172S F 172F, F 172G, F 172H F 172K, F 172L, F 172M, F 172N F 172P 10014364 THIELERT AIRCRAFT ENGINES GmbH EASA.A.S.01632 REV. 8 LBA-EMZ SA 1377 PA 28-140, PA 28-150 PA 28-151, PA 28-160 PA 28-161, PA 28-180 1. Installation of TAE 125 engine2. Installation of TAE 125-02-99 engine and installation of FADEC BackupBattery3. Installation of TAE 125-02-114 engine FAA Approved Airplane Flight Manual Supplement to Airplane Flight Manual D6- 35747 for Boeing Model 747-200B is required to support this modification of applicable airplanes as identified in table 1 of Boeing Doc. D800-10610-7, Rev. New or later FAA approve 1. Prior to installation of this modification the installer must determine that theinterrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product.2. The ins 06.10.2008 09.02.2009 19.09.2006 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. 27.03.2012 Installation of TAE 125-02-114 is limited to DR 400 models with S/N 2574and upwards. Prior to installation of this modification it 11.04.2011 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. Major Change to STC EASA.A.S.01527, This STC supersedes LBA-EMZ SA Prior to installation of this modification the 21.05.2010 Revision 5:1.,,Installation of engine TAE 125- 1295Power/Rotational speed TAE 125-01 & installer must determinethat the 01 in accordance with InstallationManual IM-20- TAE 125-02-99:Take off power: 99 kw at 2300 interrelationship between this modification 01 and Type Design Definition Doc. No: TDD- min -1 (Propellerspeed)Max. continious power: and any otherpreviously installed 20-01;2.,,Installation of engine TAE 125-02-99 99 kw at 2300 min -1 (Propellerspeed) Fuel: modification will introduce no adverse in accordance with InstallationManual Service Bulletin TM TAE 601-0005MTOW: effect uponthe airworthiness of the Model Cessna product. 1. Installation of engine TAE 125-01 in 1. This STC supersedes LBA-EMZ SA 1377. Prior to installation of this modification it 10.05.2012 accordance with InstallationManual IM-40-01 2. Power/Rotational Speed: For TAE 125-01 must be determined thatthe and Type Design Definition Doc. No.: TDD 40- and 125-02-99 installations:Take of power: 99 interrelationship between this modification 01.2. Installation of engine TAE 125-02 in Kw at 2300 min-1 (Propellerspeed)Max. and any other previouslyinstalled accordance with InstallationManual IM-40-02 continuous power: 99 Kw at 2300 min-1 modification and/ or repair will introduce and Type Design Definition Doc. No.: TDD (Propellerspeed) For TAE 125-02-114 no adverse effectupon the airworthiness installations:Ta of the product. 10014442 THIELERT AIRCRAFT ENGINES GmbH EASA.A.S.02492 CIRRUS SR22 Installation of engine Centurion 4.0 in accordance to Type Design Definition Doc. No.: TDD-70-01Engine: Centurion 4.0Propeller: MTV-14-D/195-30bCertification Basis: see CRI A-1max. Take Off Power: 228 kw at 2300 min-1 (Propeller-RPM)max. Contin 10014452 THIELERT AIRCRAFT ENGINES GmbH EASA.A.S.02505 CESSNA 172 Installation of Universal Fuel System This STC is approved only for the product 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. 04/01/2013 Page 448/462 12.02.2007 07.02.2006
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10014500 THIELERT AIRCRAFT ENGINES GmbH EASA.A.S.02565 REV. 2 CESSNA TU206G For Cessna U206F and TU206F:Engine: 28.04.2008 CESSNA U206F Centurion 4.0 BE-221Propeller: MTV-9- CESSNA U206G D/210-58Certification Basis: See CRI Almax. Take Off Power 221 kW at 2300 min-1 (Propeller RPM)max. Continuous Power 221 kWat 2300 min-1 (Propeller RPM)Fuel: See Se 10015310 THIELERT AIRCRAFT ENGINES GmbH EASA.E.S.01000 Installation of the FADEC G6 in accordance Engines having been converted via this STC 03.08.2007 with Installation Manual IM-80-01, Conversion may be identified as IO-580-B1A-EThe data in Instruction CI-80-01 and Type Design Definition the TCDS EASA.IM.E.027 remains valid, Doc. No.: TDD-80-01. except the following:Weight of the engine equipped with FADEC: 207.49 kg (457.44 lbs)Dimensions: Overall Height: 10015458 THIELERT AIRCRAFT ENGINES GmbH EASA.IM.A.S.01204 FAA STC ST10298SC-D DR 140B, DR 180R, DR 200R Installation of WX-1000E Stormoscope System 1. This installation is eligible for airplanes S/N 28.06.2005 ROBIN DR 400 RP, DR 120D, 052 and subsequent with Collins Pro Line 4, version 6.1 avionics system2. This STC is approved only for the product configuration as defined in the approved design data referred to in the paragraph "Descri 10036328 THIELERT AIRCRAFT ENGINES GMBH P-EASA.A.S.02566 DA 40 D Installation of engine TAE 125-02-114 in accordance with ConversionInstruction CI-50- 02S DA 40 Issue/Revision: 1/0 and the Type DesignDefinition Document No: 50-01 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 01.09.2011 10014379 THOMSONFLY LTD. EASA.A.S.01657 BOEING 757-200 Introduction of Security Cameras 07.12.2005 10014411 THOMSONFLY LTD. EASA.A.S.01708 BOEING 767-300 Introduction of BE Aerospace Spectrum Seat 05.03.2007 10014461 THOMSONFLY LTD. EASA.A.S.02521 BOEING 767-300 Introduction of STG Aerospace Photo- Luminescent Passenger Emergency Escape Path Lightning System Cabin & Exit Lightning levels must be measured for acceptability on each installation in accordance with Thomsonfley Technical Engineering Order TEO/767/1463 Issue 2 dated 26 April 2006 or later approved revision. 10016435 THUNDER BAY AVIATION LIMITED EASA.IM.A.S.02775 TCCA STC SA04-55 BOMBARDIER DHC-6 Double and Single Utility Seats for DHC-6. 19.03.2008 10033486 TIMCO AEROSYSTEMS REV. 1 FAA STC ST03143AT-D 747-400, 747-400 (BCF), Installation of a Rockwell Collins Aero H+ None Prior to installation of this modification it 04.02.2011 747-400F Satcom System in accordancewith TIMCO must be determined thatthe Master Data List 04T089L01, Rev. IR, dated interrelationship between this modification November 25, 2005or later FAA approved and any other previouslyinstalled revision modification and/ or repair will introduce no adverse effectupon the airworthiness of the product 10035902 TIMCO AEROSYSTEMS FAA STC ST00552AT B747-400 SERIES Installation of a Collins Satcom update from 900 SDU to 906 SDU (dataonly) in accordance with Page Avjet Master Drawing List 94-17, InitialRelease, dated June 17, 1994, or later FAA approved Revision. ,, None. None. 26.07.2011 10036655 TIMCO AEROSYSTEMS FAA STC ST01959AT-D 747-400 Installation of a Ball Camera Entertainment system per Timco Master DataList 99T057L001 Rev. C, dated November 8, 1999 or later FAA approvedrevision.Validation of FAA STC ST01959AT-D 02.05.2006 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. 27.09.2011 10038130 TIMCO AEROSYSTEMS REV. 1 FAA STC ST03884AT-D 767-300 Installation of LCD Monitor Upgrade None EASA accepts the use of FAA (Acceptable Means of Compliance) Issue PaperC-1 (Stage 4, Closed 01/082008) as being applicable to this project. Future changes to this STC that impact on the agreed means ofcompliance to this IP must be considered as a Major Le 21.05.2012 04/01/2013 Page 449/462
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04/01/2013 Page 1/462 - EASA

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