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 10017056 PARAVION TECHNOLOGY INC. EASA.IM.R.S.01487 BELL 206, BELL 407 Vent Control Certification. 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. 11.08.2008 10017061 PARAVION TECHNOLOGY INC. EASA.IM.R.S.01496 FAA STC SR00654DE 206L-3, 206L-4, BELL 407 Rotary Latch Belts Installation. Prior to installation of this modification the 03.09.2008 BELL 206A, 206B, 206L, 206L-1, 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. 10017064 PARAVION TECHNOLOGY INC. EASA.IM.R.S.01500 FAA STC SR00532DE BELL 212, ,412, 412EP ENHANCED VISION INSTALLATION (This Prior to installation of this modification the 23.09.2008 STC has been classified as “BASIC” by the installer must determine that the FAA in accordance with FAA Order 8110.52 interrelationship between this modification and and has been approved using the PTVP any other previously installed modification Procedures.) will introduce no adverse effect upon the airworthiness of the product. 10017065 PARAVION TECHNOLOGY INC. EASA.IM.R.S.01501 FAA STC SR00603DE BELL 206, BELL 407 Enhanced Vision Installation. 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. 23.09.2008 10033806 PARAVION TECHNOLOGY INC. EASA.IM.R.S.01558 FAA STC SH2735NM MD 369D, 369E, 369H, 369HE Pneumatic Door Opener (PDO) This EASA None Prior to installation of this modification it 23.06.2009 MD 369HS, 500N, 600N STC supersedes and is a revision of LBA STC must be determined thatthe 0426/3036. interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. The in 10039011 PARAVION TECHNOLOGY INC. FAA STC SR00743DE BELL 429 Installation of structural provisions for a blade fold kit in accordancewith Paravion Technology Master Drawing List, Report No DL-429BF- 100,Revision A, dated December 30, 2011. 10041121 PARKER HANNIFIN FAA STC SH363NE AS 365N2, AS 365N3 SA 365N, SA 365N1 10041145 PARKER HANNIFIN FAA STC SH362NE AS355E, AS355F, AS355F1, AS355F2 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. 29.03.2012 Installation of Parker 1C44-2 fuel pump in None. If the holder agrees to permit another 22.08.2012 accordance with Installation Manual SP1C44-2. person to use this certificate toalter the product, the holder shall give the other person writtenevidence of that permission. Prior to installation of this modification it must be determined thatthe interrelationship Installation of Parker 1C44-2 Fuel Pump 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. 23.08.2012 10041148 PARKER HANNIFIN FAA STC SR153CH AS 332 L, AS 332 L1 Installation of Parker 1C64-15 Fuel Pump 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. 24.08.2012 10027890 PARKER HANNIFIN CORPORATION P- EASA.IM.A.S.03272 REV. 1 FAA STC SA01376CH PC-12, PC-12/45, PC-12/47, PC-12/47E EASA Validation of STC SA01376CH None 1) Prior to installation of this modification 04.12.2009 the installer mustdetermine that the interrelationship between this modification and anyother previously installed modification will introduce no adverse effectupon the airworthiness of the product. 2) The inst 04/01/2013 Page 354/462
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10039114 PARKER HANNIFIN CORPORATION FAA STC SA619GL 1. C90A, C90GT, C90GTI EASA Validation of FAA STC None Prior to installation of this modification it 10.04.2012 2. 65-90, 65-A90 SA619GLInstallation of Parker Hannifin Main must be determined thatthe 2. 65-A90-1 (JU-21A) Wheel and Brake Conversion Kit PartNumbers interrelationship between this modification 2. 65-A90-4 (RU-21E, RU-21H) 199-90 in accordance with Parker Hannifin and any other previouslyinstalled 2. B90, C90, E90, H90 (T-44A) Conversion KitInstallation Manual IM 199-90, modification and/ or repair will introduce Revision J, dated January 7, 2009, orlater FAA no adverse effectupon the airworthiness approved of the product. 10033420 PARMA-TECHNIK, S.R.O. 1. M 137A, M 137AZ 2. M 332, M 332A, M 332AK 3. M 337, M 337A, M 337AK Prolongation of TBO for the M137, M332 and M337 engines in serviceaccording to the procedure No. WMS - OS/09/04 (Definition document)under the AP DOA Parma Technik organization No. M332, 137, 337/001 10037491 PATS AIRCRAFT L.L.C. FAA STC ST01725NY-D B737-900ER Installation of ten auxiliary fuel tank system configurationsValidation of STC ST01725NY-D Approved configurations are the following: Configuration 1: ,,Installation of a Five-Cell Auxiliary Fuel System inthe forward and aft cargo compartments in accorda 10027222 PATS AIRCRAFT LLC P- EASA.IM.A.S.03142 10027223 PATS AIRCRAFT LLC P- EASA.IM.A.S.03235 REV. 1 FAA STC ST00365NY-D CL-600-2B19 Revisions to Auxiliary Fuel System Structural Provisions none none 19.01.2011 Configurations 1 & 5:,,PATS Aircraft, LLC. Airplane Flight ManualSupplement No. 221 for a Five-Cell (1 Fwd/4 Aft) Auxiliary Fuel System,revision IR dated January 30, 2009 is required. Approved for aircraftwith NGS. Configurations 2 & 6:,,PATS Aircraft, L PATS Aircraft, LLC. Airplane Flight Manual Supplement No. 200, RevisionB, FAA approved 11 June 2009, is required with configurations 5 and 6. REV. 2 FAA STC ST01730NY-D CL-600-2B19 Installation of an Executive Interior In this installation the maximum passenger seating capacity is limitedto 15. 10016198 PEMCO WORLD AIR SERVICES EASA.IM.A.S.02438 REV. 2 FAA STC SA2968SO BOEING 737-400 Modification of floor in accordance with Pemco World Air Services, Inc. Master Data list, Report No. 2316, revision “K”, dated June15, 2006, or later EASA approved revision. 10016199 PEMCO WORLD AIR SERVICES EASA.IM.A.S.02439 REV. 2 FAA STC SA2969SO BOEING 737-400 Installation of a cargo door in accordance with Pemco World Air Services, Inc. Master Data list, Report No. 2373, revision “T”, dated June 15, 2006, or later EASA approved revision. 10016200 PEMCO WORLD AIR SERVICES EASA.IM.A.S.02440 FAA STC SA2970SO BOEING 737-400 Installation of a Class “E” Cargo Compartment and passenger interior configuration in accordance with with Pemco World Air Services, Inc. Master Data list, Report No. 2374, revision “S”, dated June 15, 2006, or later EASA approved revision. 10035332 PEMCO WORLD AIR SERVICES EASA STC 2004- 3750 REV. 1 FAA STC SA2971SO B737-300 Installation of a Cargo Loading System in acc with MDL 2337 rev X dated12/07/2010Modification of the STC FAA SA2971SO to increase from 121 pax to 148 paxaccording to drawing 90945-507/607 10016480 PENTASTAR AVIATION, L.L.C. EASA.IM.A.S.02832 FAA STC ST01759CH FALCON 50 FALCON 900 FALCON 900EX Instructions for Continued Airworthiness (ICA), Pemco Report No 2917, Revision C, dated January 18, 2006, or later EASA approved revision, is a required part of this STC, and must be incorporated into the operator’s maintenance program. - Airplane Flight manual Supplement (AFMS), Report P03-003FM Rev 7, or later EASA approved revision.- Instructions for Continued Airworthiness (ICA), Pemco Report No 2917, Revision C, dated January 18, 2006, or later EASA approved revision, is also a - Airplane Flight manual Supplement (AFMS), Report P03-003FM Rev 7, dated April 27th 2007 or later EASA approved revision.- Instructions for Continued Airworthiness (ICA), Pemco Report No 2917, Revision C, dated January 18, 2006, or later EASA approv EASA Validation of FAA approved STC 1. See those of original FAA STC ST01759CHUpgrade of a Rockwell Collins ST01759CH.2. Prior to installation of this SAT-906 SATCOM system by modification of modification the installer must determine that Rockwell Collins SDU-906 Satellite Data Unit the interrelationship between this modification and HPA-901A High Power Amplifier and the and any other previously installed modification installation of a Rockwell Collins HST-900 High will introduce no adverse effec Speed Prior to installation of this modification it 12.12.2011 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. Prior to installation of this modification it 12.07.2012 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 12.07.2012 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. 24.06.2008 24.06.2008 07.05.2007 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. 16.06.2011 04/01/2013 Page 355/462 01.04.2009
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04/01/2013 Page 1/462 - EASA

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