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 />
10034885 MICRO AERODYNAMICS, INC. FAA STC SA02098SE 65-90, 65-A90, 65-A90-1 Installation of Vortex Generators on the wings If more than five vortex generators, or either This STC has been found compatible 10.05.2<strong>01</strong>1<br />
65-A90-2, 65-A90-3, 65-A90-4 and tail surfaces, andstrakes on the engine nacelle stake are damagedor missing, the with FAA STC SA10747SC dated<br />
B90, C90, C90A, C90GT nacelles.<br />
aircraft is no longer airworthy.<br />
October06, 2006 (<strong>EASA</strong> STC ref<br />
C90GTI, E90, H90<br />
<strong>EASA</strong>.IM.A.S.02863 Rev 1)Prior to<br />
installation of this modification it must be<br />
determined thatthe interrelationship<br />
between this modification and any other<br />
previou<br />
10038573 MICRO AERODYNAMICS, INC. FAA STC#SA<strong>01</strong>681SE 1. PA-34-200, PA-34-200T, Installation of vortex generators on the wings, If more than five vortex generators are The installation of this modification by 27.02.2<strong>01</strong>2<br />
1. PA-34-220T (SENECA III) horizontal and verticaltail surfaces (all models), damaged or missing, the aircraftis no longer third persons is subject towritten<br />
1. PA-34-220T (SENECA IV) and an increase in maximum zero fuel airworthy.<br />
permission of the approval holder and<br />
2. PA-34-220T (SENECA V) weight(PA-34-200T and M20 03 only).<br />
disposal of the approvedappropriate<br />
3. PZL M20 03 "MEWA"<br />
documentation.Prior to installation of this<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>04</strong>0949 MICRO AERODYNAMICS, INC. REV. 2 FAA STC SA<strong>01</strong>161SE PA-32-260, PA-32-300<br />
Installation of Vortex Generators on the wing If the holder agrees to permit another person to The installation of this modification by 11.09.2<strong>01</strong>2<br />
PA-32S-300, PA-32R-300 and tail surface accordingto drawing package use this certificate toalter the product, the third persons is subject towritten<br />
MA2174, revision IR dated 06-Sep-2002 holder shall give the other person<br />
permission of the approval holder and<br />
andinstallation manual MA2175 revision A writtenevidence of that permission.If more than disposal of the approvedappropriate<br />
dated 27-Aug-2003 or later FAAapproved 5 vortex generators are damaged or missing, documentation.Prior to installation of this<br />
revision to either of these documents. the A/C is notairworthy.<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10<strong>04</strong>1846 MICRO AERODYNAMICS, INC. FAA STC SA02226SE DA 42, DA 42NG, DA 42M-NG Installation of vortex generators on the wings None Prior to installation of this modification it 19.10.2<strong>01</strong>2<br />
and tail surfaces.FAA STC SA02226SE<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>5935 MID-CANADA MOD CENTER <strong>EASA</strong>.IM.A.S.02075 SA03-92 Cockpit voice recorder replacement with<br />
Universal CVR 30 or CVR 120<br />
-- 14.12.2006<br />
10036039 MID-CANADA MOD CENTER CESSNA 550, S550 Installation of Rockwell Collins Proline 21 None Prior to installation of this modification it 08.08.2<strong>01</strong>1<br />
Integrated Display Systemwith new VHF<br />
must be determined thatthe<br />
communication transceivers, Navigation<br />
interrelationship between this modification<br />
Receivers withintegral ADF, Distance<br />
and any other previouslyinstalled<br />
Measuring Equipment Transceivers and Mode<br />
modification and/ or repair will introduce<br />
STransponders with Elementary Surveillance<br />
no adverse effectupon the airworthiness<br />
capability, R<br />
of the product.<br />
10038891 MID-CANADA MOD CENTER TCCA STC SA10-16 CL-600-2B19 CMC Electronics CMA-1100, Class II<br />
Electronic Flight Bag (EFB) SystemInstallation<br />
10<strong>04</strong>1743 MID-CANADA MOD CENTER TCCA STC O-LSA09-348/D CL-600-2B19 TrueNorth Satphone Installation Restricted to ASN 8092.<strong>EASA</strong> STC<br />
Nos.10038463 and 10028338 Rev. 2<br />
(Transport Canada STC Nos.O-LSA09-344/D<br />
and C-LSA09-326/D) are pre-requisites to this<br />
approval.<br />
10<strong>01</strong>5913 MILLENNIUM CONCEPTS, INC. <strong>EASA</strong>.IM.A.S.02<strong>04</strong>2 REV. 1 FAA STC SA<strong>01</strong>160WI CESSNA 208<br />
CESSNA 208B<br />
10<strong>04</strong>1159 MILLENNIUM CONCEPTS, INC. REV. 1 FAA STC SA<strong>01</strong>671WI - D 1- G36 - BONANZA<br />
2- G58 - BARON<br />
10<strong>01</strong>6595 MITSUBISHI HEAVY INDUSTRIES<br />
AMERICA<br />
Installation of Executive Interior in Cessna<br />
Models 208, 208B Caravan<br />
Installation of interior configuration per Master<br />
Drawing List2033-MDL<strong>04</strong>0, rev. P, dated 8<br />
February 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 />
21.03.2<strong>01</strong>2<br />
If the holder agrees to permit another person to<br />
use this certificate toalter the product, the<br />
holder shall give the other person<br />
writtenevidence of that permission.<br />
<strong>EASA</strong>.IM.A.S.03006 FAA STC SA1751SW Flight Crew Restraint 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 />
Prior to installation of this modification it 12.10.2<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 />
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 />
documentation. Prior 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> 335/<strong>462</strong><br />
08.02.2008<br />
27.08.2<strong>01</strong>2<br />
22.09.2008
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