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 />
10039720 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02977CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02977CH None Prior to installation of this modification it <strong>04</strong>.06.2<strong>01</strong>2<br />
"Installation of a medical floorliner in<br />
must be determined thatthe<br />
accordance with RSG AeroDesign Master<br />
interrelationship between this modification<br />
Document List00A02160003, No Revision,<br />
and any other previouslyinstalled<br />
dated February 23, 2<strong>01</strong>1, or later FAA<br />
modification and/ or repair will introduce<br />
approvedrevisions"<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10039721 SNAKY CREEK ENTERPRISES, LLC FAA STC SR02980CH AW109SP <strong>EASA</strong> Validation of FAA STC SR02980CH<br />
"Installation of an interior panelsystem in<br />
accordance with RSG AeroDesign Master<br />
Document List00A021600<strong>01</strong>, No Revision,<br />
dated February 23, 2<strong>01</strong>1, or later FAA<br />
approvedrevisions"<br />
10<strong>04</strong>1098 SNAKY CREEK ENTERPRISES, LLC FAA STC SA02488CH PC-12<br />
PC-12/45<br />
PC-12/47<br />
Air Ambulance Conversion Install air<br />
ambulance conversion in accordance with<br />
Spectrum AeromedInc. Master Drawing List<br />
6<strong>04</strong>5DL, dated July 23, 2007 or later<br />
FAAapproved revisions.<br />
10<strong>01</strong>4506 SOCATA <strong>EASA</strong>.A.S.02576 TBM 700 STC 34.0<strong>01</strong>.06/Gamin GNS530 TAWS. TBM 700 equipped Garmin GNS 530 only s/n<br />
to 433 excepted 269.<br />
10<strong>01</strong>4524 SOCATA <strong>EASA</strong>.A.S.02607 TB 200 Validation of definition specificities of TB200 STC 53.0<strong>01</strong>.06 applicable to TB200 s/n 1633<br />
S/N 1633 aircraft, compared to TB200 GT<br />
certified aircraft definition<br />
only<br />
10<strong>01</strong>5065 SOCATA <strong>EASA</strong>.A.S.03391 SOCATA TBM 700 Installation of a multi-functions display Garmin This revision can be installed on TBM 700 s/n<br />
GMX 200 connected to already installed to 433 when equipped with EADS SOCATA<br />
equipments (weather radar, COM/NAV/GPS, optional Modifications n° OPT 70-23-<strong>01</strong>9, OPT<br />
Traffic Advisory System).<br />
70-23-<strong>01</strong>8, OPT 70-34-<strong>04</strong>7 and OPT 70-34-<br />
<strong>04</strong>0.The installation can be performed only by<br />
EADS SOCATA technical staff according to t<br />
10029243 SOCATA P-<strong>EASA</strong>.A.S.03962 REV. 4 TB 20<br />
TB 21<br />
Installation of Garmin G500 EFIS Interfaced<br />
with a dual Garmin GNS430W/530W<br />
communication and navigation system, for IFR<br />
B-RNAV/P-RNAVoperations with coupling to<br />
autopilot.Revision 3 of the STC including the<br />
extent to RNP LNAV and LPV<br />
approachoperations.Re<br />
10<strong>04</strong>0655 SOCATA DHC-6 SERIES 300 Avionics upgrade based on Garmin G600 EFIS<br />
and GNS 430 W system,according to<br />
SOCATA modification file n° STC.00.0<strong>01</strong>.11<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 />
18.05.2<strong>01</strong>2<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 />
21.08.2<strong>01</strong>2<br />
The modified airplane must be equipped with:-<br />
an attitude indicator, an airspeed indicator, an<br />
altitude indicator, amagnetic heading indicator<br />
and a radionavigation indicator<br />
independentfrom the G500 EFIS,- a<br />
third radionavigation or radiocommunciati<br />
This design change is limited to airplanes s/n<br />
292, 298, 300, 730 and745. Initial installation<br />
must be performed by authorised Socata<br />
technicalpersonel. This avionics installation is<br />
approved for IFR operations in<br />
BRNAV,PRNAV, RNP approach LNAV and<br />
LPV app<br />
10<strong>04</strong>2727 SOCATA TB20, TB21 Installation of TAS Garmin GTS800 This STC is not applicable to airplanes<br />
equipped with a 14 V electricalsystem.Initial<br />
Installation of this design change must be<br />
performed byauthorized SOCATA<br />
personal.Modified airplanes must be equipped<br />
with Socata modification No.34-0<strong>01</strong>-009<br />
approved unde<br />
10028245 SOCATA SAS P-<strong>EASA</strong>.A.S.03961 REV. 2 TBM 700 N Installation of a Honeywell HF KHF 1050<br />
communication system on aircraftTBM 700 N<br />
equipped with Garmin 1000 Glass Cockpit<br />
System - Update forICA inclusion<br />
30.<strong>01</strong>.2008<br />
20.07.2006<br />
06.02.2008<br />
Prior to installation of this modification it 23.10.2<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 />
Prior to installation of this modification it 17.07.2<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 />
Prior to installation of this modification it 14.12.2<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 />
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 />
26.08.2<strong>01</strong>0<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 412/<strong>462</strong>
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