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>01</strong>6481 LEARJET INC. <strong>EASA</strong>.IM.A.S.02834 FAA STC ST<strong>01</strong>730LA-D BOMBARDIER CL-600-2B16 (6<strong>04</strong>) FAA STC ST<strong>01</strong>730LA-D, Installation of an Prior to installation of this modification the<br />
24.06.2008<br />
Aircell Axxess II Iridium Satcom System. installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6570 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02967 FAA STC ST00994WI-D LEARJET 60 Cockpit Speaker Mute FunctionFAA STC Prior to installation of this modification the<br />
06.10.2008<br />
ST00994WI-D<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the product.<br />
10<strong>01</strong>6574 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02972 FAA STC ST<strong>01</strong>421WI-D LEARJET 60 Airshow 410 System Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
16.09.2008<br />
10<strong>01</strong>6575 LEARJET Inc. <strong>EASA</strong>.IM.A.S.02973 FAA STC ST<strong>01</strong>424WI-D LEARJET 60 Emergency power supply #1 Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
10<strong>01</strong>6600 LEARJET INC. <strong>EASA</strong>.IM.A.S.03<strong>01</strong>3 FAA STC ST10380SC BOMBARDIER BD-700-1A10 Replacement of Low Back Seats with High<br />
Back Seats.<br />
1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product. The i<br />
10<strong>01</strong>6611 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03031 FAA STC ST<strong>01</strong>370WI-D LEARJET 60 Honeywell HF Communication System. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>6618 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03<strong>04</strong>9 FAA STC ST<strong>01</strong>402WI-D LEARJET 60 Collins Pro Line 21 Avionics InstallationFAA<br />
STC ST<strong>01</strong>402WI-D<br />
10<strong>01</strong>6619 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03050 FAA STC ST<strong>01</strong>422WI-D LEARJET 60 Interior Upgrade (Floor Plans A, B, C & D)FAA<br />
STC ST<strong>01</strong>422WI-D<br />
10<strong>01</strong>6651 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03099 REV. 2 FAA STC SA8199NM-D BD-700-1A10 FAA STC SA8199NM-D, Installation of a Full<br />
Authority Cabin Temp Control.<br />
10<strong>01</strong>6682 LEARJET Inc. <strong>EASA</strong>.IM.A.S.03205 FAA STC ST006<strong>04</strong>WI LEARJET 31A Installation of stand-alone Garmin GPS-165<br />
Global Positioning System (VFR Navigation<br />
Only).<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The inst<br />
16.09.2008<br />
23.12.2008<br />
27.10.2008<br />
13.11.2008<br />
13.11.2008<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 />
16.12.2<strong>01</strong>0<br />
Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.The installa<br />
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28.<strong>04</strong>.2009
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