04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
04/01/2013 Page 1/462 - EASA
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<strong>EASA</strong> STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue<br />
10032896 FLIGHT STRUCTURES, Inc. FAA STC ST02160SE-D B737-500 Interior Reconfiguration in accordance with Not Applicable Prior to installation of this modification it 07.12.2<strong>01</strong>0<br />
Flight structures, Inc.(FSI) Master Drawing List<br />
must be determined thatthe<br />
B0FS003-D<strong>01</strong> Installation of new windscreen,<br />
interrelationship between this modification<br />
stowage bin, stowage bin extension<br />
and any other previouslyinstalled<br />
kits,moveable under-bin class divider, sidewall<br />
modification and / or repair will introduce<br />
panel, lowered ceiling paneland asso<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10033035 FLIGHT STRUCTURES, Inc. FAA STC ST02161SE-D B737-300 Interior Reconfiguration in accordance with<br />
Flight Structure, Inc. (FSI)Master Drawing List<br />
B0FS003-D02Installation of new windscreen,<br />
stowage bin, stowage bin extension<br />
kits,moveable under-bin class divider, sidewall<br />
panel, lowered ceiling paneland associ<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and / or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
15.12.2<strong>01</strong>0<br />
10036059 FLIGHT STRUCTURES, Inc. FAA STC SA5738NM B747-400 Installation of an extended upper deck crew<br />
rest in accordance withFlight Structures Inc.<br />
Master Drawing List 90SF0<strong>04</strong>-D<strong>01</strong>, Revision<br />
E,dated July 13, 1992, or later FAA approved<br />
revisions.Validation of FAA STC SA5738NM. ,,<br />
None. None. 09.08.2<strong>01</strong>1<br />
10036590 FLIGHT STRUCTURES, Inc. FAA STC ST00695AT-D B747-400 Modification of Upper Deck Crew Rest<br />
Compartment in accordance withTimco Master<br />
Data List, MDL-<strong>01</strong>090, Revision E, dated July<br />
22, 1996, orlater FAA approved<br />
RevisionValidation of FAA STC ST00695AT-D<br />
10037<strong>04</strong>9 FLIGHT STRUCTURES, Inc. FAA STC ST00840SE B747-400 Reconfiguration of the Main Deck of the B747-<br />
400 series airplane inaccordance with Flight<br />
Structures, Inc. Master Drawing List 99FS908-<br />
D<strong>01</strong>Rev. E, dated 10 November 2009 or a<br />
later FAA approved revision.Validation of FAA<br />
STC ST00840SE ,,<br />
10037365 FLIGHT STRUCTURES, Inc. FAA STC ST00756SE B747-400 Reconfiguration of the Main and Upper Deck of<br />
B747-400 series airplanes,in accordance with<br />
Flight Structures, Inc. Master Drawing<br />
List98FS818-D<strong>01</strong> Rev. J, dated November 10,<br />
2009 or a later FAA<br />
approvedrevision.Validation of FAA STC<br />
ST00756SE.<br />
10039031 FLIGHT STRUCTURES, Inc. FAA STC ST02164SE A330-3<strong>01</strong>/-302/-303<br />
A330-321/-322/-323<br />
A330-341/-342/-343<br />
10<strong>04</strong>1241 FLIGHT STRUCTURES, Inc. FAA STC ST<strong>01</strong>941SE A300 B4-6<strong>01</strong>/-603/-605R<br />
A300 B4-620/-622/-622R<br />
A330-300 Cabin reconfiguration.This STC<br />
installs new economy class and business class<br />
seats togetherwith the replacement of the IFE<br />
system.<br />
10<strong>04</strong>2096 FLIGHT STRUCTURES, Inc. FAA STC ST02166SE 747-400 Installation of additional Crew Rest Bunks in<br />
the Door 5 Overhead CrewRest.<br />
None Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
21.09.2<strong>01</strong>1<br />
None. Heath Tecna. STC ST0<strong>04</strong>84SE must be 27.10.2<strong>01</strong>1<br />
installed concurrently with this STC.,,<br />
Prior to installation of this modification it<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair wi<br />
None. Heath Tecna. STC ST0<strong>04</strong>84SE and<br />
Rockwell Collins STC 00720LA must<br />
beinstalled concurrently with this<br />
STC.The approval holder shall fulfill the<br />
obligations of Part 21,<br />
Paragraph21.A109.Prior to installation of<br />
this modification it must be determined<br />
thatthe<br />
None Modification MCA 19<strong>04</strong>41, supporting<br />
installation of Front Row ServiceModules<br />
(Muhlenberg ottomans), in accordance<br />
with Diehl Services ModulesMaster<br />
Drawing List Ref: MDL19<strong>04</strong>41, dated 15<br />
March 2<strong>01</strong>2, is requiredwith this STC<br />
embodiment.Prior to installation<br />
Validation of FAA Supplemental Type The STC is limited to three A300B4-600 series A copy of this certificate and Flight<br />
Certificate (STC) ST<strong>01</strong>941SEConversion of an model aeroplanes,Manufacturer Serial Number Structures MDL A5FS524-D<strong>01</strong> must<br />
Airbus A300B4-600 series aeroplanes from a (MSN) 734, 739 and 756.Per the Temporary bemaintained as part of the permanent<br />
passengerconfiguration to a freighter<br />
Deviation, aeroplanes converted under this records for the modifiedaeroplane(s).<br />
configuration (including main deck cargodoor, STC:- are limited to 1,500 flight cycles or 3,300 This STC acts as an AMOC to several<br />
interior, and associated systems), in<br />
flight hours, whicheveroccurs fi<br />
<strong>EASA</strong> ADs, the list of which can befound<br />
accordance<br />
in the appendix to this approval c<br />
Maximum number of occupants of the Door 5<br />
overhead crew rest is eightpersons.<br />
22.11.2<strong>01</strong>1<br />
30.03.2<strong>01</strong>2<br />
31.08.2<strong>01</strong>2<br />
Prior to installation of this modification it 08.11.2<strong>01</strong>2<br />
must be determined thatthe<br />
interrelationship between this modification<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
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