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>6178 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02407 FAA STC SA29NW CESSNA 4<strong>01</strong><br />
Robertson STOL ModificationInstallation of As referred in FAA STC SA29NW:Max. Flap<br />
19.03.2008<br />
CESSNA 402<br />
fowler flaps, flap actuated droop ailerons, flap Extension Speed VFE : 10° Flap 195 mph<br />
actuated trim and anti-servo rudder trim tab in (CAS) 30°<br />
accordance with Drawing List No. 24<br />
Flap 145 mph (CAS)Min. Single Engine<br />
Control Speed VMC : 10° Flap 83 mph<br />
(CAS)<br />
10<strong>01</strong>6339 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02649 FAA STC SA80RM CESSNA 550 Installation of Extended Range Fuel Tank and Cessna Service Bulletin 34-15 or 34-23 (ref.<br />
11.06.2008<br />
relocation of Aft Pressure Bulkhead.<br />
Note 7 in TCDS A22CE, latest rev.) must be<br />
incorporated unless modified aircraft with full<br />
cabin tank fuel, minimum crew and required<br />
ballast is within maximum zero fuel weight and<br />
C.G. limits.<br />
10<strong>01</strong>6340 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02650 FAA STC SA174RM CESSNA 550 Installation of an extended width cabin door. 03.07.2008<br />
10<strong>01</strong>6443 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02788 FAA STC SA1689WE CESSNA 172P Installation of drooped ailerons in flaps down 1. Floatplane Models 172A thru 172H are<br />
13.05.2008<br />
mode, contoured wing leading edges, except only eligible with Franklin Engines 6A-350-C1<br />
for 172M, 172N, and 172P), and wing per STC SA340NW (215HP) or 6A-350-C2<br />
stallfences.<br />
per STC SA1334WE (180 HP). 2. Fixed tabs<br />
as shown on R/STOL Systems, Inc. Drawing<br />
10-100 required on Floatplane Model 172E.<br />
Th<br />
10<strong>01</strong>6447 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02793 REV. 1 FAA STC SA8829SW CESSNA 500<br />
Installation of Inertial Reel Assy.´s on Pilot and None. Prior to installation of this modification it 06.12.2<strong>01</strong>2<br />
CESSNA 550 CITATION II Co-Pilot ShoulderHarnessIn accordance with<br />
must be determined thatthe<br />
Sierra Master Drawing List, SI220-000, rev. A,<br />
interrelationship between this modification<br />
date28 March 1994.Validation of FAA approval<br />
and any other previouslyinstalled<br />
STC SA8829SW.This is an amendment to<br />
modification and/ or repair will introduce<br />
<strong>EASA</strong>.IM.A.S.02793 to include Cess<br />
no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>01</strong>6463 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02809 FAA STC SA8437SW CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION II)<br />
10<strong>01</strong>6464 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02810 FAA STC SA09<strong>01</strong>1SC CESSNA 550 CITATION II<br />
CESSNA S550<br />
10<strong>01</strong>6465 SIERRA INDUSTRIES Ltd. <strong>EASA</strong>.IM.A.S.02811 REV. 1 FAA STC SA09229SC CESSNA 500<br />
CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION S/II)<br />
10030649 SIERRA INDUSTRIES Ltd. REV. 1 FAA STC SA3634SW 206H, T206H LANDPLANES<br />
P206 A, D, E LANDPLANES<br />
U206 LANDPLANES A, B, D<br />
U206 LANDPLANES E, F, G<br />
Installation of radome quick release<br />
mechanism.FAA STC SA8437SW.<br />
Gear Horn Silence Switch,FAA STC<br />
SA09<strong>01</strong>1SC<br />
Installation of Gas Cylinder Nose baggage<br />
Door OpenersIn accordance with Sierra Master<br />
Drawing List, SI380-000, rev. C, date24 Sept<br />
1996.Validation of FAA approval STC<br />
SA09229SC.This is an amendment to<br />
<strong>EASA</strong>.IM.A.S.02811 to include Cessna Model<br />
500 asan app<br />
Auxiliary Fuel System: Installation of three<br />
auxiliary bladder type fueltanks in each wing in<br />
accordance with FAA STC SA3634SW,<br />
revision 4,dated 30.03.2<strong>01</strong>0. This <strong>EASA</strong> STC<br />
is a revision of LBA STC (EMZ) 0393/673,<br />
673a, dated05.05.1993.<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 install<br />
28.03.2008<br />
27.03.2008<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 />
06.12.2<strong>01</strong>2<br />
- Cessna P206 A, D and E model landplanes<br />
(S/N P206-<strong>01</strong>61 throughP206-00647) -<br />
Cessna U206 model landplanes A, B,<br />
D, E, F, G (S/N U206-<strong>04</strong>38through<br />
U206-<strong>04</strong>649) - Cessna 206H and T206H<br />
model landplanes (S/N 206-080<strong>01</strong> to present<br />
andS/N T206-080<strong>01</strong> to pre<br />
10036302 SIERRA INDUSTRIES Ltd. FAA STC ST02363LA HAWKER 800XP Installation of Honeywell TFE731-50R Engines. Limited to Hawker 800XP aircraft fitted with<br />
Honeywell SPZ-8000 AvionicsSystem,<br />
and:Winglets installed under Hawker<br />
Beechcraft (HBC) Mod Kit 140-1703 -Service<br />
Bulletin 57-3810, <strong>EASA</strong> approval ref<br />
<strong>EASA</strong>.IM.A.C.<strong>01</strong>451.<br />
10037473 SIERRA INDUSTRIES Ltd. FAA STC SA1435WE 180H Installation of drooped ailerons in flap down<br />
mode, re-contoured wingleading edge in<br />
accordance with FAA STC SA1435WE.<br />
Prior to installation of this modification it 17.10.2<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 30.08.2<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 />
S/N 18051446 through 18052284<br />
Prior to installation of this modification it 29.11.2<strong>01</strong>1<br />
onlyInstallation of SC-100 Stall Warning must be determined thatthe<br />
system is not included.CG range: straight line interrelationship between this modification<br />
between points- Amphibian with (+42.2 ) to and any other previouslyinstalled<br />
(+43.9) @ 2950 lb.- EDO 597-2790 (+36.0) to modification and/ or repair will introduce<br />
(+43.9) @ 2258 lb. or lessControl Surface no adverse effectupon the airworthiness<br />
Movement<br />
of the product<br />
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