04/01/2013 Page 1/462 - EASA

EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue
10017011 PRATT & WHITNEY EASA.IM.R.S.01424 FAA STC ST00049BO, LBA RC 1048 ROBINSON R22
Installation of a Pratt & Whitney Engine 1. Federal Aviation Administration approval of
04.03.2008
ROBINSON R22 ALPHA Services, Inc. Health Usage Monitoring System the HUMS installation was determined on a
ROBINSON R22 BETA
(HUMS) Model 1022, P/N HUMS-A-030-1 non-interference basis. Operation of
maintenance must not be predicated on the
HUMS.
10017012 PRATT & WHITNEY EASA.IM.R.S.01425 FAA STC SR00067BO, LBA STC RC EUROCOPTER FRANCE AS 350 Installation of a Pratt & Whitney Engine 1. Federal Aviation Administration approval of
04.03.2008
B
Services, Inc. Health Usage Monitoring System the HUMS installation was determined on a
EUROCOPTER FRANCE AS 350 (HUMS) Model 1122, P/N HUMS-A-070-I, non-interference basis. Operation of
B1
Revision B
maintenance must not be predicated on the
EUROCOPTER FRANCE AS 350
B2
EUROCOPTER FRANCE AS 350
BA
HUMS.
10026953 PRATT & WHITNEY P-
FAA STC ST00261BO FALCON 2000EX EASA Validation of FAA STC
Instructions for Continued Airworthiness (ICA) Prior to installation of this modification it 26.08.2009
EASA.IM.A.S.03229
ST00261BO:Installation of Pratt & DTU-G-260-7, Revision Cdated 26th May must be determined thatthe
Whitney Engine Services, Inc
2009 or later revisions shall be made available interrelationship between this modification
DataTransmission Unit (DTU) in accordance to theoperator at the time of installation and any other previouslyinstalled
with Pratt & Whitney EngineServices,
modification and/ or repair will introduce
Inc, Master Document List DTU-T-100-6,
no adverse effectupon the airworthiness
Revision F dated 23rdJuly 2009, or l
of the product.
10028632 PRATT & WHITNEY EASA.IM.A.S.03230 GULFSTREAM 200 17.07.2009
10039147 PRATT & WHITNEY ENGINE SERVICES,
FAA STC SA00303BO C90GT, C90GTI ADAS for Hawker Beechcraft Model C90GT, None Prior to installation of this modification it 12.04.2012
IN
C90GTiInstallation of the Pratt & Whitney
must be determined thatthe
Engine Services ADAS in accordancewith Pratt
interrelationship between this modification
& Whitney Engine Services’ Installation Manual
and any other previouslyinstalled
DAAS-G-010-6,Revision B, dated April 7,
modification and/ or repair will introduce
2010, or later FAA approved revision.
no adverse effectupon the airworthiness
of the product.
10039150 PRATT & WHITNEY ENGINE SERVICES,
IN
FAA STC SA00295BO 1. B200, B200C, B300, B300C
2. 300
ADAS for Hawker Beechcraft Model B200,
B200C, 300, B300, B300CInstallation of the
Pratt & Whitney Engine Services’ Master
DocumentList No. DAAS-T-100-3, Revision D,
dated May 13, 2010, or laterFAA-approved
revision.
10016093 PRECISE FLIGHT, Inc. EASA.IM.A.S.02280 REV. 2 FAA STC SA01708SE SR22, SR22T Installation of Cirrus Fixed Oxygen System - according limitation section of AFM-S- max
altitude extension up to 25.000 ft, if operated
acc. Limitationsection of AFM-S
10016858 PRECISE FLIGHT, Inc. EASA.IM.R.S.01234 REV. 1 FAA STC SH3319NM SEE EASA APPROVED MODEL
LIST
Precise Flight PulseLite Control System.
Adding MDHI 369 and 500Nmodels.
10016859 PRECISE FLIGHT, Inc. EASA.IM.R.S.01235 FAA STC SA00701SE ROBINSON R22 & R44 Installation of Precise Flight Pulslite System in
accordance with Precise Flight, Inc.
Engineering drawings 590P0001, Rev. -,
dated26 January, 1999 and 590P0002, Rev. -,
dated 26 January 1999 or later approved
revision in Robinson R22 model or R44 model
he
10017060 PRECISE FLIGHT, Inc. EASA.IM.R.S.01494 FAA STC SR01821SE R22 MARINER
R22, R22 ALPHA, R22 BETA
Installation of a Precise Light HID Aviation
Lighting System according to FAA STC
SR01821SE.
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.
12.04.2012
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 productIf the h
Approval for the physical installation of the Prior to installation of this modification it 08.04.2011
PulseLite Control Unitwill be required if there is must be determined thatthe
no specific reference provided inEngineering interrelationship between this modification
Drawing List 001P0001, revision B, dated May and any other previouslyinstalled
1, 2002, orlater FAA approved revision. modification and/ or repair will introduce
no adverse effectupon the airworthiness
of the product.
1. 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 i
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20.07.2007
14.11.2008