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 10032896 FLIGHT STRUCTURES, Inc. FAA STC ST02160SE-D B737-500 Interior Reconfiguration in accordance with Not Applicable Prior to installation of this modification it 07.12.2010 Flight structures, Inc.(FSI) Master Drawing List must be determined thatthe B0FS003-D01 Installation of new windscreen, interrelationship between this modification stowage bin, stowage bin extension and any other previouslyinstalled kits,moveable under-bin class divider, sidewall modification and / or repair will introduce panel, lowered ceiling paneland asso no adverse effectupon the airworthiness of the product. 10033035 FLIGHT STRUCTURES, Inc. FAA STC ST02161SE-D B737-300 Interior Reconfiguration in accordance with Flight Structure, Inc. (FSI)Master Drawing List B0FS003-D02Installation of new windscreen, stowage bin, stowage bin extension kits,moveable under-bin class divider, sidewall panel, lowered ceiling paneland associ 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. 15.12.2010 10036059 FLIGHT STRUCTURES, Inc. FAA STC SA5738NM B747-400 Installation of an extended upper deck crew rest in accordance withFlight Structures Inc. Master Drawing List 90SF004-D01, Revision E,dated July 13, 1992, or later FAA approved revisions.Validation of FAA STC SA5738NM. ,, None. None. 09.08.2011 10036590 FLIGHT STRUCTURES, Inc. FAA STC ST00695AT-D B747-400 Modification of Upper Deck Crew Rest Compartment in accordance withTimco Master Data List, MDL-01090, Revision E, dated July 22, 1996, orlater FAA approved RevisionValidation of FAA STC ST00695AT-D 10037049 FLIGHT STRUCTURES, Inc. FAA STC ST00840SE B747-400 Reconfiguration of the Main Deck of the B747- 400 series airplane inaccordance with Flight Structures, Inc. Master Drawing List 99FS908- D01Rev. E, dated 10 November 2009 or a later FAA approved revision.Validation of FAA STC ST00840SE ,, 10037365 FLIGHT STRUCTURES, Inc. FAA STC ST00756SE B747-400 Reconfiguration of the Main and Upper Deck of B747-400 series airplanes,in accordance with Flight Structures, Inc. Master Drawing List98FS818-D01 Rev. J, dated November 10, 2009 or a later FAA approvedrevision.Validation of FAA STC ST00756SE. 10039031 FLIGHT STRUCTURES, Inc. FAA STC ST02164SE A330-301/-302/-303 A330-321/-322/-323 A330-341/-342/-343 10041241 FLIGHT STRUCTURES, Inc. FAA STC ST01941SE A300 B4-601/-603/-605R A300 B4-620/-622/-622R A330-300 Cabin reconfiguration.This STC installs new economy class and business class seats togetherwith the replacement of the IFE system. 10042096 FLIGHT STRUCTURES, Inc. FAA STC ST02166SE 747-400 Installation of additional Crew Rest Bunks in the Door 5 Overhead CrewRest. 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. 21.09.2011 None. Heath Tecna. STC ST00484SE must be 27.10.2011 installed concurrently with this STC.,, Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair wi None. Heath Tecna. STC ST00484SE and Rockwell Collins STC 00720LA must beinstalled concurrently with this STC.The approval holder shall fulfill the obligations of Part 21, Paragraph21.A109.Prior to installation of this modification it must be determined thatthe None Modification MCA 190441, supporting installation of Front Row ServiceModules (Muhlenberg ottomans), in accordance with Diehl Services ModulesMaster Drawing List Ref: MDL190441, dated 15 March 2012, is requiredwith this STC embodiment.Prior to installation Validation of FAA Supplemental Type The STC is limited to three A300B4-600 series A copy of this certificate and Flight Certificate (STC) ST01941SEConversion of an model aeroplanes,Manufacturer Serial Number Structures MDL A5FS524-D01 must Airbus A300B4-600 series aeroplanes from a (MSN) 734, 739 and 756.Per the Temporary bemaintained as part of the permanent passengerconfiguration to a freighter Deviation, aeroplanes converted under this records for the modifiedaeroplane(s). configuration (including main deck cargodoor, STC:- are limited to 1,500 flight cycles or 3,300 This STC acts as an AMOC to several interior, and associated systems), in flight hours, whicheveroccurs fi EASA ADs, the list of which can befound accordance in the appendix to this approval c Maximum number of occupants of the Door 5 overhead crew rest is eightpersons. 22.11.2011 30.03.2012 31.08.2012 Prior to installation of this modification it 08.11.2012 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. 04/01/2013 Page 220/462
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10015410 FLIGHT TEST ASSOCIATES, INC EASA.IM.A.S.01124 FAA STC ST01524LA LEARJET 31 Installation of Rosemount Pitot Static Probe 1. This STC is approved only for the product 05.07.2005 LEARJET 35 Part Numbers 856NA1 & 856NA2 configuration as defined in the approved design LEARJET 35A data referred to in the paragraph "Description". LEARJET 36 Compatibility with other aircraft/engine LEARJET 36A configurations shall be determined by the installer. 10015411 FLIGHT TEST ASSOCIATES, INC EASA.IM.A.S.01125 FAA STC ST01525LA LEARJET 31 Installation of Honeywell AZ-252 air data 1. This STC is approved only for the product 06.07.2005 LEARJET 35 computer, Ba-250 barometric altitude display, configuration as defined in the approved design LEARJET 35A AM-250 barometric altimeter, AL-800 altitude data referred to in the paragraph "Description". LEARJET 36 alert controller, and Aerosonic standby Compatibility with other aircraft/engine LEARJET 36A altimeter. configurations shall be determined by the installer. 10015560 FLINT AERO, INC. EASA.IM.A.S.01457 FAA STC SA3232NM CESSNA 206H Installation of 14.9 gallon usable fuel containing 1. Prior to installation of this modification the 23.02.2009 CESSNA T206H lightning resistant wing tips installer must determine that the CESSNA TU206G interrelationship between this modification CESSNA U206G andany other previously installed modification will introduce no adverse effect upon the airworthiness of the product.2. The ins 10016592 FLINT AERO, INC. EASA.IM.A.S.03003 CESSNA 182 CESSNA 182A CESSNA 182B CESSNA 182C CESSNA 182D CESSNA 182E CESSNA 182F CESSNA 182G CESSNA 182J CESSNA 182K CESSNA 182M CESSNA 182N CESSNA 182P CESSNA 182Q CESSNA 182R CESSNA 182S CESSNA 182T CESSNA R182 CESSNA T182, T182T CESSNA TR182 10031241 FLINT AERO, INC. P- EASA.IM.A.S.02712 FAA STC SA3226NM 210G, 210H, 210J, 210K, 210L 210M, 210N T210G, T210H, T210J, T210K T210L, T210M, T210N, P210N 10034927 FLINT AERO, INC. FAA STC SA2529WE 185, 185A, 185B, 185C, 185D 185E, A185E, A185F 10035079 FLINT AERO, INC. FAA STC SA1614WE SEE EASA APPROVED MODEL LIST Auxiliary Internal Wing Fuel Tanks.This STC is a revision of LBA STC SA 1305, dated 14 January 2003. Installation of 16,25 US Gallon usable fuel lightning resistant wing tipfuel tanks Installation of twelve (12) gallon auxiliary fuel tank in each wing inacc. with FAA STC SA2529WE. Installation of one twelve (12) gallon auxiliary fuel tank in eachoutboard wing panel in acc. with FAA STC SA1614WE. None. 15.08.2008 According limitation section of AFM-SFor P210N and T210N following limitation additionally apply:-Wing Tip Aux/ Aux Tank either is less than 7 gals MTOW 3730lbs, MLW3530lbs-Wing Tip Aux/ Aux Tank both are 7 gals or more MTOW 4000lbs, MLW3800lbs Prior to installation of this modification it 03.08.2010 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. If the The limitations and conditions of FAA TCDS Prior to installation of this modification it 13.05.2011 3A24 apply, except asoutlined below: a) Model must be determined thatthe 185 through A185F S/N 18502262 - 89 gal. interrelationship between this modification (85 gal. useable); two32.5 gal. main tanks in and any other previouslyinstalled wings at (+48) and two 12 gal. (11.5 modification and/ or repair will introduce gal.usable) aux. tanks in wings at (+50).b) no adverse effectupon the airworthiness of the product. The limitations and conditions of FAA Aircraft Specification A-799, FAAData Sheets 3A12, 3A17, or FAA Data Sheets A4EU and A18EU or EASA TCDSIM.A.051 apply, except as outlined below of this STC: 1. Fuel Capacity Add "24 gal. (23 gal. useable); two 12 gal. Prior to installation of this modification it 24.05.2011 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 10014390 FLYBE LIMITED EASA.A.S.01676 BAE ATP Cargo Layout for class "E" compartment (LFD) 30.01.2006 10014413 FLYBE LIMITED EASA.A.S.01712 BAE ATP Introduction of Class E Compartment Cargo Layout 10042037 FLYBE LIMITED REV. 1 ERJ 190-100 Embraer ERJ 190 - Installation of Tropospheric STD/LR/IGW/ECJ/SR Airborne Data ReportingSystemThis EASA ERJ 190-200 STD/LR/IGW approval is an update of the EASA approval ref. 10042037Description as per Associated Technical Documentation Restricted to Aircraft Serial Number 2042 & 2052 ALS update as stated in ICA Supplement RE2088-17 Issue 3, dated01/10/2012. 17.01.2006 Prior to installation of this modification it 08.11.2012 must be determined thatthe interrelationship between this modification and any other previouslyinstalledmodification and/ or repair will introduce no adverse effect upon theairworthinessof the product. 04/01/2013 Page 221/462
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04/01/2013 Page 1/462 - EASA

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