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 />
10<strong>04</strong>0951 LEARJET Inc. <strong>EASA</strong> STC NO. 1426 REV. 1 FAA STC ST<strong>01</strong>122SE-D LEARJET 35/35A/36/36A Group Aircraft Approval for RVSM. Validation The following items listed in the Limitations and Prior to installation of this modification it 07.08.2<strong>01</strong>2<br />
of FAA STC ST<strong>01</strong>122SE-D dated 14 April Conditions section ofthe FAA STC<br />
must be determined thatthe<br />
2<strong>01</strong>0. Note: This approval constitutes an ST<strong>01</strong>122SE-D, dated April 14 2<strong>01</strong>0, are interrelationship between this modification<br />
update to <strong>EASA</strong> STC ref. N° 1426 dated2 excluded from <strong>EASA</strong>approval of this STC, and any other previouslyinstalled<br />
December 2003 (LBA STC TA0751, dated 27 because they are related to a configuration(C- modification and/ or repair will introduce<br />
November 2003) in order toreflect the 21A) that has not been validated by <strong>EASA</strong>:§ 4 no adverse effectupon the airworthiness<br />
compatibility o<br />
Grou<br />
of the product.<br />
10031894 LEARJET, INC REV. 1 FAA STC ST02025LA-D 31A Installation of Northrop Grumman Dual LITEF<br />
LCR-100 AHRSFAA STC ST02025LA-D<br />
(issued March 10, 2<strong>01</strong>0)<br />
Previous or concurrent requirement for this<br />
installation is an approvedinstallation of the<br />
LCR-93 AHRS in accordance with Learjet<br />
ECR 4467.<br />
10035128 LEARJET, INC FAA STC SA8182NM-D BD-700-1A10 Modification of the Forward Water Fill Panel This installation modifies the existing water fill<br />
panel installationinstalled by Bombardier Inc.<br />
Engineering Drawing MDC9000-<strong>01</strong>42-1<br />
only(Previously approved under <strong>EASA</strong> STC<br />
No. <strong>EASA</strong>.IM.A.S.02336)<br />
Prior to installation of this modification it 20.09.2<strong>01</strong>0<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 27.05.2<strong>01</strong>1<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 />
10029566 LEES AVIONICS Ltd. COMMANDER 112, 114 Installation of Garmin G500/G600 PFD/ND This change is limited to the configuration<br />
defined in Change StatementCS1097-<strong>01</strong> Issue<br />
2 or later approved revision.<br />
None <strong>01</strong>.<strong>04</strong>.2<strong>01</strong>0<br />
10033384 LEES AVIONICS Ltd. LEARJET 35, LEARJET 35A Installation of single or dual Universal Avionics Refer to Flight Manual Change Sheet FCMS- Prior to installation of this modification it 17.12.2<strong>01</strong>0<br />
UNS-1Lor UNS-1LW FMS (Flight Management 1159, issue 1<br />
must be determined thatthe<br />
System)<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 />
10036361 LEES AVIONICS Ltd. P-<strong>EASA</strong>.A.S.02912 1900, 1900C, 1900D<br />
200, 200C, 200CT, 200T, A200<br />
A200C, A200CT, B200, B200C<br />
B200CGT, B200CT, B200GT,<br />
B200T<br />
TAWS-B Installation. 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 />
02.09.2<strong>01</strong>1<br />
10036482 LEES AVIONICS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>567 BELL 412 Installation of the Spectrolab search light SX16. None. None. 16.09.2<strong>01</strong>1<br />
10036506 LEES AVIONICS Ltd. P-<strong>EASA</strong>.R.S.<strong>01</strong>570 BELL 412 Installation of the UNS-1E FMS. This kit/STC can be installed on helicopter that<br />
has installed the kitDualBendix/King ED551A<br />
EHSI, <strong>EASA</strong> approved <strong>EASA</strong>.R.S.<strong>01</strong>445.<br />
10036591 LEES AVIONICS Ltd. SEE <strong>EASA</strong> APPROVED MODEL<br />
LIST<br />
10039936 LEES AVIONICS Ltd. BN2A-20, BN2A-21, BN2A-26,<br />
BN2A-27, BN2A-8,<br />
BN2A-9, BN2B-20,<br />
BN2B-21, BN2B-26, BN2B-27<br />
None. 14.09.2<strong>01</strong>1<br />
GNS430W/GNS530W Installation for BRNAV None The approval holder shall fulfil the<br />
obligations of Part 21,<br />
Paragraph21.A109. Prior to installation of<br />
this modification it must be determined<br />
thatthe interrelationship between this<br />
modification and any other<br />
previouslyinstalled modification and/ or<br />
repai<br />
30.09.2<strong>01</strong>1<br />
Garmin G600 PFD/ND. 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 />
<strong>04</strong>.06.2<strong>01</strong>2<br />
10034642 LETH & ASSOCIATES, LLC FAA STC ST<strong>01</strong>857SE 757-200 Max Zero Fuel Weight Increase Only applicable to a/c converted to Freighter by Prior to installation of this modification it 18.<strong>04</strong>.2<strong>01</strong>1<br />
Precision ConversionsSTC (ref:<br />
must be determined thatthe<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>423)<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 />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 311/<strong>462</strong>
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