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>4763 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02953 CESSNA 425 Replacement of one existing Transponder This change is limited to the configuration of<br />
11.05.2007<br />
System by a Garmin GTX 330D Mode-S aircraft / equipment type as listed under Item 4.<br />
Transponder System<br />
in Engineering Order, Doc. No. 2037527-EO,<br />
Issue 3, dated <strong>04</strong>-May-2007 or later approved<br />
issuePrior to installation of this modification the<br />
installer must dete<br />
10<strong>01</strong>4767 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02959 CESSNA 500, CITATION Installation of Honeywell Multi-Function Radar 1. Prior to installation of this modification the<br />
16.02.2009<br />
CESSNA 550 CITATION II (MFRD) and an optional Honeywell Primus installer must determine that the<br />
CESSNA S550, (CITIATION S/II) Radar System, if the existing radar is interrelationship between this modification and<br />
incompatible with the MFRD.<br />
any other previously installed modification will<br />
introduce no adverse effect upon the<br />
airworthiness of the product.2.<br />
10<strong>01</strong>4777 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02975 CESSNA 650 CITATION III Installation of Honeywell TRA-45A Terrain Aircraft Serial No. 650-0037 with FOCA STC<br />
29.05.2007<br />
CESSNA 650 CITATION VI Display/ Radio Altimeter Indicator.<br />
Z34-44-05 installed as defined in Scandinavian<br />
CESSNA 650 CITATION VII<br />
Avionics Modification Reference 2037690.<br />
10<strong>01</strong>4778 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.02976 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4800 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03003 SAAB 340B<br />
SAAB SF340A<br />
10<strong>01</strong>4807 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03<strong>01</strong>1 CESSNA 5<strong>01</strong>, CITIATION<br />
CESSNA 551, CITIATIONII<br />
10<strong>01</strong>4809 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03<strong>01</strong>3 BEECH 200<br />
BEECH 200C<br />
BEECH 300<br />
BEECH 300LW<br />
BEECH B300<br />
BEECH B300C<br />
10<strong>01</strong>4823 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03036 CESSNA 500, CITATION Installation of a single diversity Mode-S<br />
transponderGarmin GTX 330D and a new top<br />
antenna.<br />
10<strong>01</strong>4879 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03107 REV. 1 CESSNA 650 CITATION III<br />
CESSNA 650 CITATION VI<br />
CESSNA 650 CITATION VII<br />
10<strong>01</strong>4910 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03154 LEARJET 31<br />
LEARJET 31A<br />
LEARJET 35<br />
LEARJET 35A<br />
LEARJET 36<br />
LEARJET 36A<br />
10<strong>01</strong>4957 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03227 REV. 1 DC-9-10 SERIES<br />
DC-9-20 SERIES<br />
DC-9-30 SERIES<br />
DC-9-40 SERIES<br />
DC-9-50 SERIES<br />
DC-9-81 (MD-81)<br />
DC-9-82<br />
DC-9-83<br />
DC-9-87 (MD-87)<br />
MD-88<br />
MD-90<br />
10<strong>01</strong>4965 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03238 CESSNA 5<strong>01</strong><br />
CESSNA 551<br />
10<strong>01</strong>5008 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03308 CESSNA 500, CITATION<br />
CESSNA 550 CITATION II<br />
CESSNA S550 (CITATION II)<br />
Installation of Sandel ST3400 TAWS System. <strong>04</strong>.<strong>04</strong>.2007<br />
Installation of Universal UNS-1L/K+, FMSsystem.<br />
N/A 13.<strong>04</strong>.2007<br />
Installation of a Honeywell CAS 67A ACAS II This change is limited to the configuration of<br />
03.<strong>04</strong>.2007<br />
System and a Dual MST 67A Mode S aircraft / equipment type as listed under Item 4.<br />
Transponder System<br />
in Engineering Order, Doc. No. 2038224-EO,<br />
Issue 2, dated 21-Mar-2007 or later approved<br />
issue.<br />
Installation of Universal UNS-1L (-1K+) FMS This change is limited to the configuration of<br />
aircraft / equipment type as listed under Item 4.<br />
in Engineering Order, Doc. No. 2037417-EO,<br />
Issue 2, dated 09-Feb-2007 or later approved<br />
issue.<br />
13.02.2007<br />
Mode S Upgrade of existing Honeywell<br />
Transponder System RCZ-833 to comply with<br />
ICAO requirements for Mode S ELS and<br />
EHS.Minor change to <strong>EASA</strong>.A.S.03107:AFM<br />
Supplements for different Downlinked Aircraft<br />
Parameters.Mode S Upgrade of existing<br />
Honeywell Transpo<br />
Installation of a SANDEL ST3400 TAWS<br />
System (Class A)<br />
Mode S elementary and enhanced Upgrade of<br />
existing dual transponder system.<br />
Dual installation of Transponder Mode S<br />
System, MST 67A with PS 550 or PS 578A<br />
Mode S Control Panel, with ELS and EHS<br />
capability.<br />
Installation of Honeywell GNS-XLS FMS and<br />
L3 Standby horizon Reference System.<br />
According to EUROCONTROL definition this<br />
equipment with approval <strong>EASA</strong>.A.S.03036 is<br />
non-EHS compliant.Prior to installation of this<br />
modification the installer must determine that<br />
the interrelationship between this modification<br />
and any other previously insta<br />
As defined in Scandinavian Avionics<br />
Modification ref 2037689.As defined in<br />
Scandinavian Avionics Modification ref<br />
2037689.<br />
Previous required aircraft configuration:All<br />
models equipped with:• Compatible Air Data<br />
Computers with ARINC 429 interface, and•<br />
Analogue Radio Altimeter interface (except<br />
ARINC 552) such asRockwell Collins ALT-<br />
50/50A , ALT-55 or Honeywell RT-200/300,<br />
and\<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 />
This change is limited to the configuration of<br />
aircraft / equipment type as listed under Item 4.<br />
in <strong>EASA</strong> approved Engineering Order, Doc.<br />
No. 2<strong>04</strong>1564-EO, Issue 2, dated 13-Aug-2007<br />
or later approved issue<br />
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06.06.2007<br />
20.11.2007<br />
22.02.2008<br />
24.07.2008<br />
26.09.2007<br />
28.11.2007