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>4439 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02489 REV. 1 BAE 125 -800<br />
Installation of wing mounted Xenon<br />
This STC is approved only for the product<br />
05.09.2006<br />
CO. K<br />
BAE 125 SERIES 800A<br />
Taxi/Landing Light and/or Radom mounted configuration as defined in the approved design<br />
BAE 125 SERIES 800B<br />
Taxi Light<br />
data referred to in the paragraph "Description".<br />
HAWKER 800<br />
Compatibility with other aircraft/engine<br />
HAWKER 800 XP<br />
configurations shall be determined by the<br />
HAWKER 850 XP<br />
installer.<br />
10<strong>01</strong>4440 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02490 BAE 125 -800<br />
Installation of Iridium Satcom C1000 <strong>01</strong>.06.2006<br />
CO. K<br />
HAWKER 800<br />
HAWKER 800 XP<br />
10<strong>01</strong>4527 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02612 BOMBARDIER CL-600-2B19 Installation of RAAS compatible EPGWS Certification Basis of the Change: CS 25 Amdt<br />
28.02.2007<br />
CO. K<br />
BOMBARDIER CL-600-2C10 Computer in CL-600-2B19/-2C10/-2D24 Series 2<br />
BOMBARDIER CL-600-2D24 Aircraft<br />
10<strong>01</strong>4528 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02613 Activation of RAAS function of EGPWS As listed in the AFM 23.02.2007<br />
CO. K<br />
computer in AVRO RJ85/100 Series Aircraft<br />
10<strong>01</strong>4537 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02624 Installation of RAAS compatible EGPWS As listed in the AFM 23.02.2007<br />
CO. K<br />
Computer in ARO RJ85/100 Series Aircraft<br />
10<strong>01</strong>4538 NAYAK AIRCRAFT SERVICE GMBH & <strong>EASA</strong>.A.S.02625 BOMBARDIER CL-600-2B19 Activation of RAAS function of EGPWS Certification Basis of the Change: CS 25 Amdt<br />
23.02.2007<br />
CO. K<br />
BOMBARDIER CL-600-2C10 Computer in CL-600-2B19/-2C10/-2D24 Series 2, additionally CRI F-<strong>01</strong> at Issue 2<br />
BOMBARDIER CL-600-2D24 Aircraft<br />
"HONEYWELL RAAS Airworthiness Approval"<br />
10<strong>01</strong>46<strong>04</strong> NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4612 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4676 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4753 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>48<strong>04</strong> NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4881 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>4971 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>5256 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10<strong>01</strong>5257 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
10028781 NAYAK AIRCRAFT SERVICE GMBH &<br />
CO. K<br />
<strong>EASA</strong>.A.S.02727 DC-3C-S1C3G Installation of emergency exit signs and floor 1. The system must be maintained in<br />
05.02.2007<br />
escape path markings at DC3C series accordance with Maintenance Procedures DC3aircraftInstallation<br />
of emergency exit signs light NY-0532-07 Rev. 0 dated 20 Nov 2006 or later<br />
with power source and installation of<br />
approved revision.2. The system must be<br />
fluorescent floor path markings<br />
operated in accordance with AFM supplement<br />
DC3-NY-0532-08 Rev. 0 dated 20 Nov 2006<br />
or later<br />
<strong>EASA</strong>.A.S.02739 BEECH 1900<br />
BEECH 200<br />
BEECH 300<br />
Installation of HID Nose Gear Lights -- 12.02.2007<br />
<strong>EASA</strong>.A.S.02837 BOEING 737-300 Installation of Galley G2 Varig p/n 25-30-3154<br />
inside aircraft between STA 333.25 and STA<br />
350.50<br />
Elect to comply CS-25 ARNDT. 2 <strong>01</strong>.02.2007<br />
<strong>EASA</strong>.A.S.02939 DC-9-80 (MD-80) SERIES Installation of flight ID capable XPDR and<br />
CTRL<br />
13.<strong>04</strong>.2007<br />
<strong>EASA</strong>.A.S.03007 CESSNA 425 Installation of GTX 330D Mode S Transponder 20.03.2007<br />
<strong>EASA</strong>.A.S.03109 MITSUBISHI MU-2B-40<br />
MITSUBISHI MU-2B-60<br />
<strong>EASA</strong>.A.S.03251 FAIRCHILD SWEARINGEN SA<br />
226<br />
FAIRCHILD SWEARINGEN SA<br />
227<br />
<strong>EASA</strong>.A.S.03709 FAIRCHILD SWEARINGEN SA<br />
226-T(<br />
<strong>EASA</strong>.A.S.03710 PIPER PA-34-200<br />
PIPER PA-34-200T<br />
PIPER PA-34-220T<br />
Installation of XPDR Mode-S System with<br />
Diversity, Garmin GTX 330 D (single or<br />
optional dual installation possible)<br />
Installation of Honeywell MK IV EGPWS,<br />
together with MFD and Thommen Air Data<br />
Computer<br />
Installation of SLAR Surveillance System quick<br />
change roll<br />
Replacement of existing Garmin COM/NAV<br />
and existing Garmin GPS system by Garmin<br />
GNS 530w COM/NAV/GPS system.<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 />
1. Limited to Serial Number T2942. With<br />
SLAR equipment installed, maximum cabin<br />
seating is 4 + 1. Operator Seat must not be<br />
occupied during take-off and landing3. Prior<br />
to installation of this modification the installer<br />
must determine that the int<br />
1. Limited to “Single GNS” – Installation<br />
only2. Prior to installation of this modification<br />
the installer must determine that the<br />
interrelationship between this modification and<br />
any other previously installed modification will<br />
introduce no adverse ef<br />
27.08.2007<br />
14.11.2007<br />
19.02.2009<br />
29.<strong>01</strong>.2009<br />
CESSNA 210 Post Installation Approval and conformity check Limited to S.N 57339 Prior to installation of this modification it 09.02.2<strong>01</strong>0<br />
of avionic system<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 />
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