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 />
10039195 S-TEC CORPORATION REV. 1 FAA STC SR02344LA BELL 407 Installation of HeliSAS stability augmentation VFR only Prior to installation of this modification it 18.<strong>04</strong>.2<strong>01</strong>2<br />
system and autopilotValidation of FAA STC<br />
must be determined thatthe<br />
SR02344LA<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. If the<br />
10039237 S-TEC CORPORATION FAA STC NO. SA09350 AC-D BEECH 95/B95/B95A/D95A/E95 Installation of S-TEC system 20/30 single and Installer must check availability of <strong>EASA</strong>- The installation of this modification by<br />
two axis Automatic FlightGuidance Systems, approval for one or morereferenced STC when third persons is subject towritten<br />
model ST-808-20/30, according to bulletin N. airplane is modified per that / those STC(s). permission of the approval holder and<br />
908 rev.1dated <strong>01</strong>-Dec-2008 and with Master<br />
disposal of the approvedappropriate<br />
Drawing List N. 921083, Rev. A, dated<strong>01</strong>-Dec-<br />
documentation.Prior to installation of this<br />
2008 or later FAA approved revision<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10039264 S-TEC CORPORATION REV. 1 FAA STC SA09<strong>01</strong>0AC-D SEE <strong>EASA</strong> APPROVED MODEL Installation of S-TEC system 55/55X two axis Installer must check availability of <strong>EASA</strong>- The installation of this modification by 25.<strong>04</strong>.2<strong>01</strong>2<br />
LIST<br />
Automatic Flight GuidanceSystems, model ST- approval for one or morereferenced STC when third persons is subject towritten<br />
589, according to bulletin N. 689 rev.4 dated11- airplane is modified per that / those STC(s). permission of the approval holder and<br />
Jan-2<strong>01</strong>0 and with Master Drawing List N.<br />
disposal of the approvedappropriate<br />
92790, Rev. D, dated11-Jan-2<strong>01</strong>0 or later FAA<br />
documentation. Prior to installation of this<br />
approved revision (14V - System).<br />
modification it must be determined<br />
thatthe interrelationship<br />
10039317 S-TEC CORPORATION FAA STC SA8364SW-D 4<strong>01</strong>, 4<strong>01</strong>A, 4<strong>01</strong>B<br />
Installation of S-TEC system 40/50 single and Installer must check availability of <strong>EASA</strong>- The installation of this modification by 25.<strong>04</strong>.2<strong>01</strong>2<br />
402A, 402B, 402C<br />
two axis Automatic FlightGuidance Systems. approval for one or morereferenced STC when third persons is subject towritten<br />
Installation Model ST-505-40/50 (28V - airplane is modified per that / those STC(s) permission of the approval holder and<br />
System)according to bulletin N. 605 rev.6<br />
disposal of the approvedappropriate<br />
dated 21-Jan-2<strong>01</strong>0 and master drawinglist n.<br />
documentation.Prior to installation of this<br />
92582 rev. F, dated 21-Jan-2<strong>01</strong>0 or later<br />
modification it must be determined<br />
thatthe interrelationship b<br />
10039903 S-TEC CORPORATION FAA STC SA09540 AC-D A99A, B99, C99 Installation of S-TEC system 30 two axis Installer must check availability of <strong>EASA</strong>- The installation of this modification by 31.05.2<strong>01</strong>2<br />
Automatic Flight GuidanceSystems (ST-923), approval for one or morereferenced STC when third persons is subject towritten<br />
in accordance with Master Data List No. ST- airplane is modified per that / those STC(s).If permission of the approval holder and<br />
923-L-00<strong>01</strong>,Revision A, dated 24-Aug-06 or the holder agrees to permit another person to holding and disposal ofthe approved<br />
later FAA approved revision (28V -System). use this certificate toalter the product, the appropriate documentation.Prior to<br />
holder shall give the other pe<br />
installation of this modification it must be<br />
determined thatthe interre<br />
10<strong>04</strong>0585 S-TEC CORPORATION FAA STC SR002346LA BELL 206B, 206L, 206L-1, Installation of HeliSAS stability augmentation VFR only Prior to installation of this modification it 17.07.2<strong>01</strong>2<br />
BELL 206L-3, 206L-4<br />
system and autopilot.Validation of FAA STC<br />
must be determined thatthe<br />
SR02346LA<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. If the<br />
10<strong>04</strong>0647 S-TEC CORPORATION REV. 1 FAA STC NO. SA7178SW-D 210K<br />
T210K<br />
10<strong>04</strong>1971 S-TEC CORPORATION FAA STC SR02345LA AS350B<br />
AS350B1<br />
AS350B2<br />
AS350B3<br />
AS350BA<br />
AS350D<br />
EC130B4<br />
10<strong>04</strong>2<strong>01</strong>3 S-TEC CORPORATION FAA STC NO. SA53<strong>01</strong>SW-D 58<br />
58A<br />
10<strong>04</strong>2477 S-TEC CORPORATION BN-2A-2, BN-2A-8<br />
BN-2A-20, BN-2A-26<br />
BN-2A-6<br />
BN-2B-20, BN-2B-26<br />
Installation of S-TEC manual Electric trim<br />
system, (ST-433), accordingto Bulletin n. 533,<br />
dated 11-May-1988 and Master Drawing List<br />
No. 92474,dated 11-May-1988 or later FAA<br />
approved revision (14V - System).<br />
Installation of HeliSAS stability augmentation<br />
system and autopilot.Validation of FAA STC<br />
SR02345LA.<br />
T210K is eligible also when modified per STC<br />
SA2689SW (RAMmodification). Installer must<br />
check availability of <strong>EASA</strong>-approval for one or<br />
morereferenced STC when airplane is<br />
modified per that / those STC(s). If the holder<br />
agrees to permit another person to us<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 />
17.07.2<strong>01</strong>2<br />
VFR only.<br />
thatthe interrelationship<br />
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. If the<br />
29.10.2<strong>01</strong>2<br />
Installation of S-TEC system 40/50, model ST- FAA / DAS Approved Pilot's Operating The installation of this modification by 31.10.2<strong>01</strong>2<br />
224-40/50, according tobulletin n. 324 dated 22- Handbook and/or Airplane FlightManual third persons is subject towritten<br />
Sep-1983 and Master Drawing List No. Supplement No. 89350 dated 5-Apr-1984 is permission of the approval holder and<br />
92252,dated 22-Sep-1983 (28V - System). required for system 40.FAA / DAS Approved disposal of the approvedappropriate<br />
Pilot's Operating Handbook and/or Airplane documentation. Prior to installation of this<br />
FlightManual Supplement No. 89351 dated 5- modification it must be determined<br />
Apr-1984 is r<br />
thatthe interrelationship<br />
Installation of S-TEC System 55/55X Two-Axis Only applicable to Model BN-2A-6 when This SIC is approved only for the product 31.05.2005<br />
Automatic Flight GuidanceSystem Model modification NB/M/430 and NB/M/631are configuration as defined inthe approved<br />
ST572.<br />
installed.<br />
design data referred to in the paragraph<br />
"Description".Compatibility with other<br />
aircraft/engine configurations shall<br />
bedetermined by the installer. This<br />
certificate shall rem<br />
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