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 />
10031536 HONEYWELL INTERNATIONAL INC. P-<br />
FAA STC ST<strong>01</strong>280SE B737-600/-700/-800/-900 Installation of the XK516 HF Transceiver None Prior to installation of this modification it 24.08.2<strong>01</strong>0<br />
<strong>EASA</strong>.IM.A.S.<strong>01</strong>131<br />
System in accordance withMaster Drawing List<br />
must be determined thatthe<br />
756-<strong>01</strong>73-0<strong>01</strong> (and FAA STC ST<strong>01</strong>280SE<br />
interrelationship between this modification<br />
dated 15 October2003)<br />
and any other previouslyinstalled<br />
modification and/ or repair will introduce<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10034246 HONEYWELL INTERNATIONAL INC. FAA STC SR02114NY-D EC135 P2(CPDS), EC135 P2+<br />
EC135 T2(CPDS), EC135 T2+<br />
Installation of a Honeywell Model 15175 VXP<br />
SystemThe Honeywell Model 15175 VXP<br />
System is a Health and Usage<br />
MonitoringSystem that monitors vibration<br />
characteristics of the aircraft toprovide data to<br />
aid aircraft maintenance. The information<br />
provided bythe<br />
10038956 HONEYWELL INTERNATIONAL INC. FAA STC ST00806AT B767-200/ -300 Installation of Aircraft Communications<br />
Addressing and Reporting System(ACARS)<br />
Mark II.<br />
10<strong>01</strong>5981 HORTON STOL-CRAFT INC. <strong>EASA</strong>.IM.A.S.02133 FAA STC SA989CE CESSNA 170A<br />
CESSNA 170B<br />
Installation of STOL Kit(Wing leading edge<br />
cuffs, drooped tips, stall fences and aileron gap<br />
seals)<br />
10<strong>01</strong>6763 HOWARD J. FULLER, JR. <strong>EASA</strong>.IM.R.S.<strong>01</strong>092 FAA STC SR00081BO SCHWEIZER 269 C-1 Operation of rotorcraft on unleaded and leaded<br />
automotive gasoline, 93 minimum antiknock<br />
index (RON+MON)/2 per ASTM Specification<br />
D-439 or D-4814 as noted on placard to be<br />
installed in accordance with H.J.Fuller Jr.<br />
Installation Instructions No. HFJ97269,<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 />
28.03.2<strong>01</strong>1<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 />
26.03.2<strong>01</strong>2<br />
1. Aircraft to be placarded "Intentional Spins<br />
Prohibited".2. This STC is approved only for<br />
the product configuration as defined in the<br />
approved design data referred to in the<br />
paragraph "Description". Compatibility with<br />
other aircraft/engine configur<br />
1. This STC is limited to those model<br />
helicopters equipped with Lycoming HO-360-<br />
C1A engines, modified in accordance with FAA<br />
STC No. SE2563CE.2. Howard J. Fuller, Jr.<br />
Rotorcraft Flight Manual Supplement No. 269-<br />
1, Rev 2 dated July 2, 20<strong>04</strong>, or later approve<br />
10<strong>04</strong>1028 HOWARD J. FULLER, JR. REV. 1 FAA STC SR00086BO R44 Operation of rotorcraft on unleaded automotive 1. This approval is limited to those model<br />
gasoline, 91 minimumantiknock index (RON + helicopters equipped withLycoming O-540-<br />
MON)/2 per ASTM Specification D-439 or D- F1B5 engines modified IAW STC<br />
4814 inaccordance with Howard. J. Fuller SE00663WI(<strong>EASA</strong>.IM.E.S.<strong>01</strong>002). This<br />
Installation Instructions No HJF97<strong>04</strong>4.(This approval is applicable only with the<br />
STC is based on FAA STC SR00086BO dated followingengine power ratings:-,,Maximum<br />
Continuous Power 205 HP (24.7<br />
10<strong>01</strong>5608 HYDRO-AIRE, INC <strong>EASA</strong>.IM.A.S.<strong>01</strong>544 FAA STC SA3339WE BEECH 200, SUPER KING AIR<br />
KING AIR 200<br />
Installation of Power Brake / Skid Control<br />
System<br />
1. Models 200: Hydro-Aire Airplane Falight<br />
Manual Supplement dated on 17 MAY 1977 or<br />
later approved revision.2. Models B200: Hydro-<br />
Aire Airplane Flight Manual Supplement No.<br />
R13-0<strong>01</strong>-100-05 dated 12 MAY 2005 or later<br />
approved revision.3. This STC is approve<br />
<strong>04</strong>.09.2006<br />
23.11.2005<br />
Prior to installation of this modification it 17.08.2<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 />
10<strong>01</strong>4561 IBERIA LINEAS AEREAS DE ESPANA <strong>EASA</strong>.A.S.02661 AIRBUS A321-212 Passenger Cabin Lay-Out Modification for -- 05.09.2006<br />
SOCI<br />
Special Flight<br />
10029481 ICELANDAIR B757-200 Navigation - Dependant Position Determining - None. Prior to installation of this modification it 26.03.2<strong>01</strong>0<br />
Activation of the ADS-Bout function of the<br />
must be determined thatthe<br />
Transponder 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 />
10030954 ICELANDAIR GA8 AIRVAN Installation of TopScan Camera System Only applicable for aircraft / preconditions as<br />
defined in EngineeringOrder, Doc. No. EO-<br />
GTA-2520-03, Rev. IR, dated 28-Jun-2<strong>01</strong>0, or<br />
laterapproved revision.<br />
The installation of this modification by<br />
third persons is subject towritten<br />
permission of the approval holder and<br />
disposal of the approvedappropriate<br />
documentationPrior to installation of this<br />
modification it must be determined<br />
thatthe ,,interrelationship<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 275/<strong>462</strong><br />
02.09.2005<br />
15.07.2<strong>01</strong>0
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