04/01/2013 Page 1/462 - EASA

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EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10032527 VIKING AIR LIMITED TCCA STC SA10-69 DHC-6 SERIES 400 Installation of RW Martin Air Conditioning None Prior to installation of this modification it 12.11.2010 System in accordance withTCCA STC SA10- must be determined thatthe 69. interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 10015333 VISIONSAFE CORPORATION EASA.IM.A.S.00354 REV. 6 FAA STC ST00892LA SEE EASA APPROVED MODEL LIST Installation of Emergency Vision Assurance System (EVAS,TM). Change toSTC EASA.IM.A.S.00354 Issue 4, update of relating approved model listissue 4 10015744 VISIONSAFE CORPORATION EASA.IM.A.S.01774 FAA STC ST01012WI BOMBARDIER CL-600-1A11 (CL- Installation of Emergency Vision Assurance 600 BOMBARDIER CL-600-2A12 (CL- 601 BOMBARDIER CL-600-2B16 BOMBARDIER CL-600-2B19 System (EVAS TM) 10016007 VISIONSAFE CORPORATION EASA.IM.A.S.02172 REV. 1 FAA STC ST01057W1 BOMBARDIER BD-700-1A10 BOMBARDIER BD-700-1A11 10016045 VISIONSAFE CORPORATION EASA.IM.A.S.02216 FAA STC ST00892LA AIRBUS A330-201 AIRBUS A330-202 AIRBUS A330-203 AIRBUS A330-223 AIRBUS A330-243 AIRBUS A330-301 AIRBUS A330-321 AIRBUS A330-322 AIRBUS A330-323 AIRBUS A330-341 AIRBUS A330-342 AIRBUS A330-343 10016155 VISIONSAFE CORPORATION EASA.IM.A.S.02357 FAA STC ST00731LA BOEING 767-200 BOEING 767-300 SERIES None Prior to installation of this modification the installer must determinethat the interrelationship between this modification and any otherpreviously installed modification will introduce no adverse effect uponthe airworthiness of the 1) Certification Basis: applicable requirements of a. r. TCDSs2) This STC is approved only for the product configuration as defined in the approved design data referred to in the paragraph "Description". Compatibility with other aircraft/engine configurati Installation of Emergency Vision Assurance See AFMSPrior to installation of this System (EVAS) model: 107 STC-191 and 107 modification the installer must determine that STC-192Validation of FAA STC the interrelationship between this modification ST01057WIMDL: Midcoast Aviation 35- and any other previously installed modification 416G001 Rev A or Vision Safe No. 206 Rev will introduce no adverse effect upon the H or later EASA approved revisionsFAA Letter airworthiness of the product. of SoC: Installation of Emergency Vision Assurance System (EVASTM) / EASA Validation of FAA approved Supplemental Type Certificate ST00892LA. 1. Boeing 737-600, -700, -700C, - 800 and -9002. Airbus 330-201, -202, -203, - 223, 243; Airbus 330-301, -321, 322, -323, -3 Installation of Emergency Vision Assurance System (EVAS) in accordance with FAA Approved Vision Safe Corporation Master Drawing List Number 144, Revision “C” dated June 9, 1999, or later FAA Approved Revisions. Vision Safe Corporation Airplane 10030483 VISIONSAFE CORPORATION FAA STC ST00892LA BD100-1A10 Flight Manua Installation of Emergency Vision Assurance System (EVAS) Model107STC-235 and 107STC-236 on Bombardier BD-100- 1A10EASA Validation of FAA approved Supplemental Type Certificate ST00892LA 10027778 V-PLANE ENGINEERING GMBH P-EASA.A.S.03977 PC-12, PC-12/45, PC-12/47, PC-12/47E 10028296 V-PLANE ENGINEERING GMBH P-EASA.A.S.03978 ERJ170-100STD, LR ERJ170-200STD, LR ¿ Vision Safe Corporation Instructions for Continued Airworthiness, Rev. 04, dated March 2006. This installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of the aircraft Heavy Duty Floor Heavy Duty Floor P/N 0127258 is limited to from S/N 101 to S/N 999except S/N 545 with configuration in accordance with Bucher OMME014-16-01 Heavy Duty Floor P/N 0127470 and P/N 0127470-401 is limited to from S/N1001 on which configuration in accordance wit product. The installati 28.06.2011 22.12.2005 10.02.2009 23.07.2007 30.03.2007 None Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 17.06.2010 Prior to installation of this modification it 03.11.2009 must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. Installation of a removable stretcher None Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 16.12.2009 04/01/2013 Page 458/462
EASA STC no. STC holder Old STC ref. Revision Level Foreign/NAA STC ref. Model Description Limitations Conditions Date of issue 10030059 West Pacific Air, LLC EASA.IM.A.S.03276 FAA STC SA01156SE B36TC Installation of a Pratt and Whitney PT6A-21 Model B36TC Only The MT propeller option on Compatibility of this modification has only 24.04.2012 engine flat rated to 500HPat 2,200 RPM, and the original FAA STC is not EASA approved been demonstrated with theKing 150, Hartzell model HC-E4N-3N/D8292 and HC- atthis time. In order to install the MT propeller Bendix/King 225 and King FFC 200 E4N-3N/D8292(B,K)-2 propellers. This compliance with EU noiseand environmental Automatic Flight ControlSystems. For certificate has been first issued on 17 May standards must be shown. operation with other AFCS systems it is 2010 but has beenre-issued for administrative the installerresponsibility to demonstrate rea correct operation. Prio 10015916 WESTERN AVIONICS EASA.IM.A.S.02048 TCCA STC SA04-26 ISSUE 3 FAIRCHILD SWEARINGEN SA Installation of Honeywell EGPWS Mark VI/VIII 23.10.2006 226 SE computer, air data computer, circuit breakers, FAIRCHILD SWEARINGEN SA annunciators, flap position switch, OATprobe, 227 SE GPS antenna, cockpit speaker and associated wiring according Transport Canada Supplemental Type Certification SA04-26, 10016041 WESTERN AVIONICS EASA.IM.A.S.02210 TCCA STC SA01-155 ISSUE 5 DE HAVILLAND CANADA DHC6- 300 10016683 WESTERN AVIONICS EASA.IM.A.S.C.0100 2 TCCA STC SA03-13; EASA.IM.A.S. BOMBARDIER DHC-8-100 SERIES BOMBARDIER DHC-8-102 BOMBARDIER DHC-8-103 BOMBARDIER DHC-8-200 SERIES BOMBARDIER DHC-8-300 SERIES BOMBARDIER DHC-8-311 BOMBARDIER DHC-8-315 10028593 WESTERN AVIONICS TCCA STC SA09-65 DHC-8-102, -103, -106 DHC-8-201, -202 DHC-8-301, -311, -314, -315 10029332 WESTERN AVIONICS REV. 1 TCCA STC SA03-53 ISSUE 1 DHC-8-102, -103, -106, DHC-8-201, -202, -301, DHC-8-311, -314, -315 10030455 WESTERN AVIONICS TCCA STC SA03-42 DHC-8-102, DHC-8-103, DHC-8-106, DHC-8-201, DHC-8-202, DHC-8-301, DHC-8-302 10030955 WESTERN AVIONICS TCCA STC SA04-96 DHC-8-102/-103/-106 DHC-8-201/-202 DHC-8-301/-302 Installation or Upgrade of a Honeywell MK VI Enhanced Ground Proximity Warning System (EGPWS) Approval is limited to the CIC Air Data Module.This STC is approved only for the product configuration as defined in the approved design data referred to in the paragraphs "Description" and “Associated Technical Documentation”. Compatibility with other air Installation ((Upgrade)) of a Single or Dual 1. Installation (Upgrade) of the Single or Dual Universal Avionics UNS-1C+ or UNS-1E Flight Universal Avionics UNS-1+ or UNS-1E Flight Management System (FMS) Management System (FMS) is to be done inaccoedance with Transport Canada approved Western Avionics Engineering Orders 71967-401 Revision 5 dated 17 September 2004 (9 Standby Altimeter InstallationTCCA STC SA09- None Special condition H-01 (ICA-EWIS) not 65, dated 07 August 2009 applicable. Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse e Primus 800 Weather Radar InstallationTCCA STC SA03-53, Issue 1, dated 28.05.2003.Removal of the limitation for Instructions for Continued Airworthinesson Electrical Wiring Interconnection System - EWIS ICA - in accordancewith Special Condition H-01 "Enhanc Collins Proline II InstallationTCCA STC SA03- 42, Is. 1, dated 8 May 2003 Second ADF InstallationTCCA STC SA04-98, Issue 1 dated 23 December 2004 A previously approved Weather Radar System installation is aprerequisite for the installation. Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 12.01.2007 20.05.2005 27.01.2010 30.11.2010 None Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 16.06.2010 None Special Condition H-01 (ICA-EWIS) not applicable Prior to installation of this modification it must be determined thatthe interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse ef 10037518 WESTERN AVIONICS DHC-6-1/-100/-200/-300 Installation of Garmin GPS 155XL for None Prior to installation of this modification it 02.12.2011 supplemental IFR Navigation in acc.with TCCA must be determined thatthe STC SA01-93, Issue 1 interrelationship between this modification and any other previouslyinstalled modification and/ or repair will introduce no adverse effectupon the airworthiness of the product. 04/01/2013 Page 459/462 16.07.2010
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04/01/2013 Page 1/462 - EASA

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