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>5183 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03563 Replacement of existing COM 1 / 2 and NAV 1 This change is limited to the configuration of<br />
/ 2 systems by Garmin GNS 530 (GNS #1) and aircraft / equipment type as listed under Item<br />
17.06.2008<br />
Garmin GNS 430 (GNS #2)<br />
4. of <strong>EASA</strong> approved Engineering Order, Doc.<br />
No. 2<strong>04</strong>6711-EO, Issue 1, dated 21-Apr-2008<br />
or later approved issue.<br />
10<strong>01</strong>5194 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03580 BAE 125 -800 SERIES<br />
HAWKER HS 125-600 SERIES<br />
HAWKER HS 125-700 SERIES<br />
Installation of a Digital Flight Data Recorder. 1. Prior to installation of this modification the<br />
installer must determine that the<br />
interrelationship between this modificationand<br />
any other previously installed modification<br />
will introduce no adverse effect upon the<br />
airworthiness of the produc<br />
10<strong>01</strong>5274 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.A.S.03769 LEARJET 55 Dual Universal UNS-1F FMS Installation. • 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.• Th<br />
10<strong>01</strong>7138 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>237 EUROCOPTER DEUTSCHLAND Installation of Bendix/King Radar Altimeter<br />
BO-105<br />
System KRA 405/405B<br />
10<strong>01</strong>7188 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>325 EUROCOPTER FRANCE EC 120<br />
B<br />
10<strong>01</strong>7234 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>412 EUROCOPTER FRANCE EC 120<br />
B<br />
10<strong>01</strong>7235 SCANDINAVIAN AVIONICS A/S <strong>EASA</strong>.R.S.<strong>01</strong>413 EUROCOPTER FRANCE EC 120<br />
B<br />
VHF COMM, XPDR, ICS, Directional Gyro and<br />
Attitude Indicator.<br />
Installation of Avionics System Garmin GNS<br />
480 / Honeywell KY-96A / Garmin GTX 33 as<br />
defined in Engineering Order 2<strong>04</strong>2580-EO .<br />
Installation of several avionics system as<br />
definened into Engineering.Order No. 2<strong>04</strong>2316<br />
10028447 SCANDINAVIAN AVIONICS A/S P-<strong>EASA</strong>.A.S.03759 REV. 1 A318, A319, A320, A321<br />
– EO issue 2<br />
Installation of provisions for the use of Dual<br />
navAero Electronic FlightBag Class 2 (EFB)<br />
System<br />
10033960 SCANDINAVIAN AVIONICS A/S B200 Provisions for and installation of a SLAR and a<br />
Homer antenna.<br />
10<strong>01</strong>3976 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>01</strong>4039 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>01</strong>4148 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
10<strong>01</strong>4696 SCANDINAVIAN AVIONICS DESIGN<br />
GMBH<br />
<strong>EASA</strong>.A.S.0097 REV. 2 550 (CITATION BRAVO)<br />
550 (CITATION II)<br />
560 (CITATION ULTRA)<br />
560 (CITATION V)<br />
S550 (CITATION S/II)<br />
<strong>EASA</strong>.A.S.<strong>01</strong>112 REV. 2 CESSNA 525<br />
CESSNA 525A<br />
<strong>EASA</strong>.A.S.<strong>01</strong>268 REV. 1 1. SA226-TC, SA227-AC<br />
1. SA227-BC<br />
2. A226-T, SA226-AT<br />
2. SA226-T(B), SA227-AT<br />
2. SA227-TT<br />
<strong>EASA</strong>.A.S.02863 REV. 1 1. A226-T, SA226-AT<br />
1. SA226-T(B), SA227-AT<br />
1. SA227-TT<br />
2. SA226-TC, SA227-AC<br />
2. SA227-BC<br />
1. The installation of this STC is not approved<br />
for Night VFR approved aircraft.2. Prior to<br />
installation of this modification the installer must<br />
determine that the interrelationship between<br />
this modification and any other previously<br />
installed modific<br />
This change is limited to Rotorcraft equipped<br />
with Garmin GNS 480 Installation.<br />
15.06.2009<br />
17.<strong>04</strong>.2009<br />
21.<strong>04</strong>.2006<br />
09.10.2007<br />
19.03.2008<br />
<strong>04</strong>.<strong>04</strong>.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 />
12.<strong>01</strong>.2<strong>01</strong>0<br />
Applicable for serial number BB-1936 only. 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 />
Installation of an L3 Digital Flight Data Limited to:S/N 550-00<strong>01</strong> through 550-0733<br />
Recorder Revision 2 was raised due to missing (Citation II)S/N 550-08<strong>01</strong> through 550-1136<br />
technical document references inRevision 1 (Citation Bravo)S/N 560-00<strong>01</strong> through 560-<br />
0259 (Citation V)S/N 560-0260 through 560-<br />
0538 (Citation Ultra)S/N S550-00<strong>01</strong> through<br />
S550-<strong>01</strong>60 (Citation S/II)<br />
Installation of dual GTX 330D Mode S<br />
Transponder systems.Installation of dual GTX<br />
330D Mode S Transponder systems.<br />
Installation of Honeywell CAS 67A ACAS II<br />
System with dual Mode STransponder<br />
1. According to Engineering Order 2<strong>01</strong>9974-<br />
EO-05, Issue 41. According to Engineering<br />
Order 2<strong>01</strong>9974-EO-05, Issue 4<br />
This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2027<strong>04</strong>6-EO, Issue 2, dated<br />
25-Oct-2<strong>01</strong>0, or later approved issue.<br />
Installation of Sandel ST3400 TAWS System This change is limited to the configuration of<br />
aircraft / equipment typeas listed under<br />
Chapter 4. in <strong>EASA</strong> approved Engineering<br />
Order, Doc. No.2035640-EO, issue 4, dated<br />
25-Oct-2<strong>01</strong>0, or later approved issue.<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<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 b<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 b<br />
<strong>04</strong>/<strong>01</strong>/2<strong>01</strong>3 <strong>Page</strong> 397/<strong>462</strong><br />
22.02.2<strong>01</strong>1<br />
05.10.2<strong>01</strong>0<br />
25.02.2008<br />
08.11.2<strong>01</strong>0<br />
08.11.2<strong>01</strong>0
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