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 />
10039279 S.E.A.M. DA40D Installation of two Garmin GNS 430 W Installation of this design change is limited to Prior to installation of this modification it 23.<strong>04</strong>.2<strong>01</strong>2<br />
systems, two GA 35 GPS antennas, aGMA airplane S/N D4-002 andit must be performed must be determined thatthe<br />
340 audiopanel, a GTX 330 Mode S<br />
by authorised SEAM technical personnel.This interrelationship between this modification<br />
transponder, a King KN-62A DME andCobham design change is approved for B-RNAV and any other previouslyinstalled<br />
antennas CI 292-2 (VHF), CI 105 (DME), CI operation without coupling ofthe GNS 430 W modification and/ or repair will introduce<br />
102 (MKR)<br />
systems to an autopilot.The airplane mu no adverse effectupon the airworthiness<br />
of the product.<br />
10<strong>04</strong>0057 S.E.A.M. REV. 1 P.68 C, P.68 TC (OBSERVER) Installation of Aspen EFD 1000 Pro EFIS and<br />
Mid Continent MD41annunciator according to<br />
SEAM modification n° 2622/11.<br />
10<strong>04</strong><strong>01</strong>61 S.E.A.M. B90, C90, E90 Installation of a Garmin GTS 8xx series Traffic<br />
Advisory System<br />
Initial installation of this design change must be Prior to installation of this modification it 15.06.2<strong>01</strong>2<br />
performed byauthorised SEAM technical must be determined thatthe<br />
personal.This installation is approved for interrelationship between this modification<br />
BRNAV operations with coupling toGarmin and any other previouslyinstalled<br />
GNS 430 or GNS 430 W system and to modification and/ or repair will introduce<br />
Century III autopilot.The modified airplane must no adverse effectupon the airworthiness<br />
of the product.<br />
Initial Installation of this design change must be<br />
performed byauthorized SEAM technical<br />
personnel. The modified aircraft must be<br />
equipped with:-TAS antennas installed<br />
according to SEAM modification No.<br />
2465/11approved under <strong>EASA</strong>.10<strong>01</strong>4783-A<br />
Garmin G600 EFI<br />
10<strong>04</strong>1160 S.E.A.M. 56TC, A56TC, 58, 58A, G58, 95, Installation of Garmin GNS 430 W system, GA Installation of this design change must be<br />
95-55, 95-A55, 95-B55,<br />
35 GPS antenna, GMA 340audiopanel and Mid performed by authorised SEAMtechnical<br />
95-B55A, 95-B55B, 95-C55, Continent MD 41 annunciator according to personnel.This installation is approved for<br />
95-C55A, D55, D55A, E55, E55A, SEAMmodification n°3823/12.<br />
BRNAV operations without coupling toan<br />
B95, B95A, D95A, E95<br />
autopilot.Used of GPS for SID/STAR and<br />
approach procedures is not<br />
authorised.Software upgrad<br />
10029549 S.E.I. SERVIZI ELICOTTERISTICI ITAL P-<strong>EASA</strong>.R.S.<strong>01</strong>549 MD HELICOPTERS 369HS Installation of Emergency Locator Transmitter<br />
(ELT), Artex C406-2HM, P/N369-25543-1<strong>01</strong><br />
10<strong>01</strong>6296 S.I.P. TECHNICAL SERVICES <strong>EASA</strong>.IM.A.S.02593 REV. 1 FAA STC ST09367SC DC-9-81 (MD-81)<br />
DC-9-82<br />
DC-9-83<br />
10<strong>01</strong>6297 S.I.P. TECHNICAL SERVICES <strong>EASA</strong>.IM.A.S.02594 FAA STC ST09389SC DC-9-82<br />
DC-9-83<br />
10<strong>01</strong>6331 S.I.P. TECHNICAL SERVICES <strong>EASA</strong>.IM.A.S.02640 FAA STC NO. ST9949SC BOEING DC-9-81 (MD-81)<br />
BOEING DC-9-82 (MD-82)<br />
BOEING DC-9-83 (MD-83)<br />
Installation of dual Canadian Marconi CMA 900 Prior to installation of this modification the<br />
FMS with GPS sensor (This is a revision of the installer must determine that the<br />
STC ST09367SC already validated by ENAC interrelationship between this modification and<br />
on 2 December 1997 and amended on 5 May any other previously installed modification will<br />
1998 to implement the PRNAV capability.) introduce no adverse effect upon the<br />
airworthiness of the product. The install<br />
Installation of Single Canadian Marconi CMA<br />
900 FMS with GPS Sensor.<br />
Installation of required sensor and interface for<br />
existing DFDR and FDAU to meet FAR<br />
121.344.<br />
10030551 S4A SOLUTIONS FOR AVIATION, S.L. EC135 P2+ Installation of an Iridium Satellite Telephone on<br />
board<br />
10<strong>04</strong>2171 S4A SOLUTIONS FOR AVIATION, S.L. C-212-200 "Installation of Iridium satellite phone". A<br />
satellite phone is added tothe airplane. This<br />
satellite phone is not located in the cockpit and<br />
itis used only by an operator located at the rear<br />
of the passenger cabin,according to "Plan de<br />
Certification A1203-<br />
Prior to installation of this modification it 14.06.2<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 24.08.2<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 />
Not Applicable Not Applicable 31.03.2<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 install<br />
20.12.2007<br />
05.03.2008<br />
10.06.2008<br />
Not Applicable 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 />
23.06.2<strong>01</strong>0<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 />
12.11.2<strong>01</strong>2<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 387/<strong>462</strong>
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