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Avionics Switch Console Installation Manual -p132

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P132 CONSOLE INSTALLATION MANUAL MDL GA107 Rev R STC SH4747NM Canada STC# SH93-83 ANAC-Brazil CHST# 2007S06-08, -09 19717 EAGLE COPTERS USA INC. South, Suite E101, Kent WA 98032 | Phone: 800-546-2210 FAX 253-867-5619 www.eaglecopters.com 62nd Avenue LEGAL NOTICE The information contained in this document is provided solely under the condition that the Recipient of this document agrees to the terms and conditions of the Non-Disclosure and Proprietary Rights Agreement listed below. By accessing this document past this page, you are agreeing to be bound by this Non-Disclosure and Proprietary Rights Agreement. Non-Disclosure and Proprietary Rights Agreement Recipient recognizes and acknowledges that Eagle Copters USA and its affiliates (“Eagle”) possess certain Proprietary information and materials, which constitute a valuable, special, and unique asset of Eagle. As used herein, the term “Proprietary information and materials” includes, without limitation, all information and materials belonging to, used by, or in the possession of Eagle relating to its products, processes, technology, inventions, patents, developments, and trade secrets of every kind and character, but shall not include: (1) Information that was already in the public domain, (2) Information that subsequently becomes public domain through no act or omission by the Recipient. Recipient hereby acknowledges that all of the Proprietary information and materials are and shall continue to be the exclusive property of Eagle, whether or not disclosed to or entrusted to the custody of Recipient. Recipient further hereby acknowledges that all Proprietary information and materials have been disclosed or made available to him solely for the purpose of assisting him in incorporating, using, or maintaining equipment provided by Eagle. Recipient hereby agrees not to disclose, or allow to be disclosed, any Proprietary information or material of Eagle, in whole or in part, to any person or entity, for any reason or purpose whatsoever. Recipient further agrees that Recipient shall not use any Proprietary information or materials of Eagle for Recipient’s own purposes or for the benefit of any other person or entity except Eagle, whether such use consists of duplication, removal, oral use or disclosure, the transfer of any Proprietary information or materials in any manner, or any other unauthorized use, unless given prior written consent by Eagle. Recipient further agrees that Recipient will not allow the reverse engineering of any Eagle products. Recipient further agrees that Recipient shall use information provide, for installation or application, to one aircraft only for each product purchased, unless the purchase agreement specifically authorizes the use on more than one aircraft. Continuing past this page constitutes acceptance of the above agreement. (End of Agreement) Page 1 of 1 I.DATE U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STAI\DARDS January 15,2015 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.MAKE 3.MODEL NO. 4.TYPE Airbus Helicopters Note I Helicopter (Airplane, Engine,Propeller, etc.) 5.NAME OF APPLICANT Eagle Copters USA, Inc. LIST OF DATA 7. TITLE 6. IDENTIFICATION Eagle Copters USA, Inc. Master Drawing List, "Electrical System Upgrade" GAl07 Revision R Dated 11612015 Note 1: Eligible Models are AS350B, BA, Bl,B2, 83, C, D, Dl --onA--,--, 8. PURPOSE OF DATA Structural approval of an update removing obsolete modifications supporting STC SH4747NM. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 27 .301 , 27 .303 , 27 .305, 27 .307 (a), 27 .561, 27 .601, 27 .603 , 27 .605, 27 .607 , 27 .609, 27 27 .6t3, 27 .6ll , .619, 27 .625 10. CERTIFICATION - Under the authority vested by direotion ofthe Administrator and in accordance with conditions and limitations of appointment under l4 CFR Part 183, data listed above dnd on attoched sheets rumbered _!UA_ have been examincd in accordance with estdblished procedures and found to comply with applicable requirements ofth€ Airworthiness Standards list€d. I (\lr€) Therefore r I E Recommend approval ofthese dats Approve thcae d.tr l. srcNAruRE(s) oF DESTcNA2EA{NGrN EERTNG REnREsENT Jeremy Mccren.h"{ FAA Form 8110-3 rr ry{tsl )- //-r%h- /Z (03/10) SUpERSEDES pREvrous EDrrroN 12. DESIGNATION NUMBER(S) DERT.636444-NM 13. CLASSTFTCATTON(S) Structures Electrical System Upgrade STC SH4747NM MASTER DRAWING LIST GA107 Rev R 1/6/2015 NOTE: LR X X X X X X X X X X X X IN LR COLUMN INDICATES CHANGE FROM LAST REVISION LEVEL DRAWING NO. GA107-1 GA107-6 GA107-7 GA107-12 G10251-1 G10251-2 G10251-3 G10251-4 G10251-5 G10251-6 G10252 G10253-1 G10253-3 G10253-5 G10253-7 G10254 G10255 G10256 G10257 G10268-10 G10269 G10270-1 G10270-2 G10283 G10283-4 G10284 G12091 G12100 G12108 G12109 G12112 G12113 G12132-1 G12132-2 G12132-2073087 SHEET REV DATE TOTAL Shts. ---------------------1 1 ---1 -1 1 1 1 --- G Q -B R M F H J G F H F F F G E B B D E A A F C B -D --A -S D 12/5/14 12/5/14 6/14/05 12/5/14 12/5/14 11/25/14 8/30/07 6/27/13 11/25/13 8/30/07 7/28/11 1/05/13 8/30/07 8/30/07 8/30/07 8/30/07 6/28/03 8/30/07 8/30/07 7/22/08 12/5/14 1/10/03 1/10/03 12/5/14 07/28/11 12/5/14 12/15/98 11/21/07 12/15/98 12/15/98 8/07/09 12/15/98 9/17/14 3/04/10 7 18 5 3 5 2 1 1 4 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 3 1 3 1 1 1 1 16 1 Installation Instructions P132 Installation Instructions Service Bulletin Dimmer Power Supply Installation Instructions P132 Console Assembly Standard Parts List P132 Console Assembly Overview P132 Console Sub-Assembly Diode Block Assembly Switch & CB Rail Assembly Details Terminal Block Assembly P132 Aft Wall Switch Rail Upper CB Rail Middle CB Rail Lower CB Rail P132 Console Side Walls P132 Console Bracket Insulation P132 Console Side Wall Assembly Auxiliary Circuit Breaker Rail Circuit Breaker Bracket MEB BOX Top Overlay Side Overlay P132 Labels and Placard Definition P132 Console Labels for Rigid Type CB Rails Accessory Relays and CB Installation Cable 20 GA Wire Connector/Wire Part List Cable 18 GA Wire Cable 16 GA Wire Cable 10 GA Wire Cable 8 GA Wire Console Wiring Instructions & Notes Console Wiring -- A 3/04/10 1 Console Wiring Page 1 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X X X X DRAWING NO. G12132-2073273 G12132-2073274 G12132-2073368 G12132-2073476 G12132-2074280 G12132-2074280B2 G12132-3 G12132-3073087 G12132-3073273 G12132-3073274 G12132-3073368 G12132-3073476 G12132-3074280 G12132-3074280B2 G12132-4 G12132-4073087 G12132-4073273 G12132-4073274 G12132-4073368 G12132-4073476 G12132-4074280 G12132-4074280B2 G12132-5 G12132-5073087 G12132-5073273 G12132-5073274 G12132-5073368 G12132-5073476 G12132-5074280 SHEET REV DATE TOTAL Shts. -- A 3/04/10 1 Console Wiring -- B 5/12/10 1 Console Wiring -- A 5/12/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- E 12/5/14 1 Console Wiring -- A 12/5/14 1 Console Wiring -- F C 3/04/10 3/04/10 1 Console Wiring 1 Console Wiring E 12/05/12 1 Console Wiring D 3/04/10 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- E 12/5/14 1 Console Wiring -- A 12/5/14 1 Console Wiring -- E 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- C 8/14/13 1 Console Wiring -- -- 8/15/13 1 Console Wiring -- C 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- A 3/04/10 1 Console Wiring B 3/04/10 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- D 8/14/13 1 Console Wiring ---- -- Page 2 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X X X X DRAWING NO. G12132-5074280B2 G12132-6 G12132-6073087 G12132-6073273 G12132-6073274 G12132-6073368 G12132-6073476 G12132-6074280 G12132-6074280B2 G12132-7 G12132-7073087 G12132-7073273 G12132-7073274 G12132-7073368 G12132-7073476 G12132-7074280 G12132-7074280B2 G12132-8 G12132-8073087 G12132-8073273 G12132-8073274 G12132-8073368 G12132-8073476 G12132-8074280 G12132-8074280B2 G12132-9 G12132-9073087 G12132-9073273 G12132-9073274 SHEET REV DATE TOTAL Shts. -- -- 8/15/13 1 Console Wiring -- C 10/10/07 1 Console Wiring -- A 03/23/09 1 Console Wiring -- A 5/6/08 1 Console Wiring -- A 3/23/09 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- B 8/14/13 1 Console Wiring -- A 12/5/14 1 Console Wiring -- D 3/04/10 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- B 3/04/10 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- B 8/14/13 1 Console Wiring -- -- 8/15/13 1 Console Wiring -- C 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- A 5/6/08 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- B 8/14/13 1 Console Wiring -- -- 8/15/13 1 Console Wiring -- C 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- A 5/6/08 1 Console Wiring Page 3 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X X X X X DRAWING NO. G12132-9073368 G12132-9073476 G12132-9074280 G12132-9074280B2 G12132-10 G12132-10073087 G12132-10073273 G12132-10073274 G12132-10073368 G12132-10073476 G12132-10074280 G12132-10074280B2 G12132-11 G12132-11073087 G12132-11073273 G12132-11073274 G12132-11073368 G12132-11073476 G12132-11074280 G12132-11074280B2 G12132-12 G12132-12073273 G12132-12073368 G12132-12074280 G12132-12074280B2 G12132-13073087 G12132-13073087P122 G12132-13073257 SHEET REV DATE TOTAL Shts. -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- C 12/5/14 1 Console Wiring -- -- 8/15/13 1 Console Wiring -- C 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- A 5/6/08 1 Console Wiring -- C 3/23/09 1 Console Wiring -- -- 4/06/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- C 8/14/13 1 Console Wiring -- -- 8/15/13 1 Console Wiring -- D 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- -- 10/10/07 1 Console Wiring -- A 5/12/10 1 Console Wiring -- A 5/12/10 1 Console Wiring -- -- 2/05/13 1 Console Wiring -- E 12/5/14 1 Console Wiring -- A 12/5/14 1 Console Wiring -- D 10/10/07 1 Console Wiring, Optional Avionics -- -- 10/10/07 1 Console Wiring, Optional Avionics -- -- 4/06/10 1 Console Wiring, Optional Avionics -- C 8/14/13 1 Console Wiring, Optional Avionics -- -- 8/15/13 1 Console Wiring -- B 3/23/09 1 Console Breaker Layout -- B 3/23/09 1 Console Breaker Layout -- A 3/23/09 1 Console Breaker Layout Page 4 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X DRAWING NO. G12132-13073257P122 G12132-13073273 G12132-13073273P122 G12132-13073274 G12132-13073274P122 G12132-13B G12132-13B-P122 G12132-13B1 G12132-13B1-P122 G12132-13B2 G12132-13B2-P122 G12132-13D G12132-13D-P122 G12132-13073368 G12132-13073368P122 G12132-13073476 G12132-13073476P122 G12132-13074280 G12132-13074280B2 G12132-13074280P122 G12132-13074280B2P122 G12132-14073087 G12132-14073087P122 SHEET REV DATE TOTAL Shts. -- B 3/23/09 1 Console Breaker Layout -- A 5/6/08 1 Console Breaker Layout -- A 5/6/08 1 Console Breaker Layout -- B 3/23/09 1 Console Breaker Layout -- B 3/23/09 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- B 10/10/07 1 Console Breaker Layout -- A 10/10/07 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- -- 4/06/10 1 Console Breaker Layout -- -- 4/06/10 1 Console Breaker Layout -- -- 2/05/13 1 Console Breaker Layout -- -- 2/05/13 1 Console Breaker Layout -- C 12/5/14 1 Console Breaker Layout -- A 12/5/14 1 Console Wiring -- B 12/5/14 1 Console Breaker Layout -- A 12/5/14 1 Console Wiring -- -- 10/10/07 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout Page 5 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X DRAWING NO. G12132-14073273 G12132-14073273P122 G12132-14073274 G12132-14073274P122 G12132-14B G12132-14B2 G12132-14B2-P122 G12132-14073368 G12132-14073368P122 G12132-14073476 G12132-14073476P122 G12132-14074280 G12132-14074280B2 G12132-14074280P122 G12132-14074280B2P122 G12132-15073087 G12132-15073087P122 G12132-15073273 G12132-15073273P122 G12132-15073274 G12132-15073274P122 G12132-15B G12132-15B-P122 SHEET REV DATE TOTAL Shts. -- A 5/6/08 1 Console Breaker Layout -- A 5/6/08 1 Console Breaker Layout -- B 3/23/09 1 Console Breaker Layout -- B 3/23/09 1 Console Breaker Layout -- -- 10/10/07 1 Console Breaker Layout -- B 10/10/07 1 Console Breaker Layout -- A 10/10/07 1 Console Breaker Layout -- -- 4/06/10 1 Console Breaker Layout -- -- 4/06/10 1 Console Breaker Layout -- -- 2/05/13 1 Console Breaker Layout -- -- 2/05/13 1 Console Breaker Layout -- C 8/14/13 1 Console Breaker Layout -- -- 8/15/13 1 Console Wiring -- A 8/14/13 1 Console Breaker Layout -- -- 8/15/13 1 Console Wiring -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout -- A 3/23/09 1 Console Switch Layout Page 6 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X X X DRAWING NO. G12132-15B2 G12132-15B2-P122 G12132-15073368 G12132-15073368P122 G12132-15073476 G12132-15073476P122 G12132-15074280 G12132-15074280B2 G12132-15074280P122 G12132-15074280B2P122 G12132-16 G12132-16073087 G12132-16073273 G12132-16073274 G12132-16073368 G12132-16073476 G12132-16074280 G12132-17 G12132-17073087 G12132-17073273 G12132-17073274 G12132-17073368 G12132-17073476 G12132-17074280 G12132-18 G12132-18073087 G12132-18073273 SHEET REV DATE TOTAL Shts. -- C 3/23/09 1 Console Switch Layout -- B 3/23/09 1 Console Switch Layout -- -- 4/06/10 1 Console Switch Layout -- -- 4/06/10 1 Console Switch Layout -- -- 2/05/13 1 Console Switch Layout -- -- 2/05/13 1 Console Switch Layout -- C 8/14/13 1 Console Switch Layout -- -- 8/15/13 1 Console Wiring -- A 8/14/13 1 Console Switch Layout -- -- 8/15/13 1 Console Wiring -- C 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 4/06/10 1 Console Wiring, Optional Circuit -- -- 2/05/13 1 Console Wiring, Optional Circuit -- B 8/14/13 1 Console Wiring, Optional Circuit -- C 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 4/06/10 1 Console Wiring, Optional Circuit -- -- 2/05/13 1 Console Wiring, Optional Circuit -- B 8/14/13 1 Console Wiring, Optional Circuit -- C 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 10/10/07 1 Console Wiring, Optional Circuit Page 7 of 11 DESCRIPTION GA107 Rev R 1/6/15 LR X X X X X X X X X DRAWING NO. G12132-18073274 G12132-18073368 G12132-18073476 G12132-18074280 SHEET REV DATE TOTAL Shts. -- -- 10/10/07 1 Console Wiring, Optional Circuit -- -- 4/06/10 1 Console Wiring, Optional Circuit -- -- 2/05/13 1 Console Wiring, Optional Circuit -- -- 8/14/13 1 Console Wiring, Optional Circuit G12132-21 -- G 02/10/11 1 G12132-23 G12132-23P122 G12132-23074280 G12132-23074280B2 G12132-24 G12132-26 G12132-27 G12132-28 G12132-29 G12132-30 G12132-31 G12132-32 -- C 12/5/14 1 Emergency Floats Electrical, P122 and P132 Console Wiring Console Wiring -- C 12/5/14 1 Console Wiring -- C 12/5/14 1 Console Wiring -- A 12/5/14 1 Console Wiring --------- C -----B C 6/29/10 10/10/07 10/10/07 10/10/07 10/10/07 10/10/07 02/10/11 3/04/10 1 1 1 2 1 1 1 2 G12132-33 -- -- 3/2/09 1 G12132-34 G12132-35 --- --- 3/04/10 5/12/10 2 1 G12132-36 -- -- 08/30/11 1 Dimmer Pot Assy Console Wiring, Optional Circuit Console Wiring, Optional Circuit Console Wiring, Optional Circuit Console Wiring, Optional Circuit Console Wiring, Optional Circuit Console Wiring, Optional Circuit Console Wiring, Optional Dual Hydraulics Twist Grip Circuit (SB 67.00.33) P132 and P122 Console Wiring Console Wiring, Mod 350A07-3368 Console Wiring, Master Cutoff Bypass Circuit Alternate Cargo Hook Power - P122 and P132 Consoles -- B 8/14/13 1 Console Wiring -- -- 8/15/13 1 Console Wiring ------1 1 1 1 1 1 1 1 1 1 1 1 1 C A A A B B -A A C A B G A A D C A C 8/30/07 8/30/07 7/13/01 6/15/00 6/30/10 6/30/10 4/5/02 4/21/08 8/30/07 11/15/11 2/20/03 4/21/08 6/24/14 2/20/03 2/20/03 6/27/13 1/05/13 4/23/08 4/17/08 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 Console Bus Bar Mount for Collective Hold-down Switch Housing Spacer Washer Top Legend Side Legend Wire Shield Dimmer Control Assembly DZUS Rail Shim P122 Console Assembly Console Body Assembly Console Body Circuit Breaker Door Assembly Circuit Breaker Door Door Cover Connector Bracket Assembly Connector Bracket Overlay Assembly Overlay Housing G12132-37074280 G12132-37074280B2 G12135 G12136 G12138 G12139 G12141 G12142 G12298 G12301 G12307 G12310 G12310-1 G12310-1-1 G12310-2 G12310-2-1 G12310-2-2 G12310-5 G12310-5-1 G12310-6 G12310-6-1 Page 8 of 11 DESCRIPTION GA107 Rev R 1/6/15 X DRAWING NO. G12310-6-2 G12310-7 G12310-7-1 G12310-8 G12310-9 G12310-10 G12310-11 G12310-12 G12310-13 G12310-14 G12310-15 G12310-16 G12311 G12316 G12324 G12425 G12426 G12733 G12741-1 G12741-2 G12741-9 G12899 G12948 G12957 G13075 G13117 X G13122 X X X X X X X X X X G13123 G13123-1 G13124 G13125 G13127 G13127-1 G13128 G13128-1 G13128-2 G13129 ----------- A A A -A ----A 08/21/13 6/24/13 08/21/13 5/03/13 08/21/13 5/03/13 5/03/13 5/03/13 5/03/13 12/5/14 1 1 1 1 1 1 1 1 1 1 X G13132 -- A 4/05/2013 5 X X X X G13133 G13133-1 G13134 G13134-1 G13134-2 G13135 G13135-1 G13137 G13137-1 AS350-Z1 AS350-Z2 ---------1 1 A B A B ---A A - 4/05/2013 4/17/2013 4/05/2013 4/17/2013 11/29/12 11/29/12 11/29/12 4/05/2013 4/05/2013 6/2/00 6/2/00 1 1 1 1 1 1 1 1 1 1 1 LR X X X X X X X SHEET REV DATE 1 1 1 1 1 1 1 1 1 1 1 1 -1 1 1 1 ----------- -C C A -------A C A A --A B B A ------ 1/10/03 11/15/11 1/05/13 2/20/03 1/10/03 1/10/03 1/10/03 1/10/03 1/10/03 1/10/03 1/10/03 11/25/13 12/5/14 3/26/04 3/26/04 8/12/04 8/12/04 10/10/07 5/03/13 5/03/13 6/24/13 1/05/07 8/30/07 10/10/07 3/25/10 5/02/13 TOTAL Shts. 1 1 1 1 1 1 1 1 1 1 1 1 6 1 1 1 1 1 1 1 1 1 1 1 1 1 A 08/21/13 6 Page 9 of 11 DESCRIPTION Overlay Circuit Board Switch Plate Assembly Switch Plate Forward Cover Plate Hinge (CB Door) Hinge (Switch Plate) CB Label 9 Position CB Label 10 Position CB Label 12 Position Bracket Terminal Block Support Bushing P122 Installation Instructions RH Cyclic Stick LH Cyclic Stick RH Cyclic Stick (Bendix grip) LH Cyclic Stick (Bendix grip) Fitting Cover Plate Cover Plate Cover Plate Cover Plate Dzus Rail Fitting Dimmer Power Supply Wire Shield P122 Console Installation – Post Mod 350A074280 LH Wall Assembly LH Wall RH Wall Assembly LH Cover Plate Aft Wall Assembly Aft Wall DZUS Rail Assembly DZUS Rail Shim DZUS Rail Wire Shield P132 Console Installation – Post MOD 350A074280 RH Vertical Support Assy RH Vertical Support LH Vertical Support Assy LH Vertical Support LH Vertical Brace Lateral Brace Assy Lateral Brace Cover Plate Assy Cover Plate Z1 Generator Regulator Card Z2 Generator Over-voltage Protection Card GA107 Rev R 1/6/15 LOG OF REVISIONS REVISION LEVEL IR A B C D F DATE OF REVISION 7/26/89 11/19/90 8/7/93 7/25/95 Not Released Not Released 4/7/1999 G 1/15/2004 ALL H 4/16/2004 ALL I 8/12/2004 ALL J 10/12/2007 ALL K 5/6/2008 ALL L 7/23/2008 ALL E PAGES DESCRIPTION OF CHANGE APPROVAL ALL ALL ALL ALL Initial Release Revised for AS350 B2 Revised for AS350 BA Add Option 1 GLH GLH GLH GLH ALL Reformatted, updated instructions Updated and added history New GLH Incorporated ECO’s 1059, 1060, 1061, 1062, 1063, 1064, 1065, 1066, 1067, 1072, 1087, 1093 & 1106, revised GA107-2; added GA107-2 Option 1 & 2 Rotorcraft Flight Manual Supplements; Renamed GA107-1 Incorporated ECO-1089, 1111, removed GA107-2 Option 1 & 2 Rotorcraft Flight Manual Supplements; added GA107-2P132 Rotorcraft Flight Manual Supplement Added G12425 & G12426 cyclic sticks for “Bendix” grip installations. Updated GA107-2-P132 Rotorcraft Flight Manual Supplement & GA107-6-P132 Installation Instructions to add these as optional parts Incorporated ECO-1119, ECO1136, & ECO-1185 Incorporated ECO-1405, & ECO1423 adding the P148 & P149 Consoles Incorporated ECO-1415 updating P132 Console installation instructions for EASA approval CLB Page 10 of 11 CLB CLB CLB CLB CLB GA107 Rev R 1/6/15 REVISION LEVEL M DATE OF REVISION 9/25/2008 PAGES DESCRIPTION OF CHANGE APPROVAL ALL Revised instructions and RFMS to clarify color coding of switches in the following documents: GA107-2, GA107-2-P132, GA1072-P148, GA107-2-P149, GA107-3, GA107-6, GA107-10, G12132-1, G12132-3, G12132-3-073087, G12132-3-073273, G12132-3073274, G12132-32, G12210, G12211-10, G12211-13, G122127, G12212-10, G12212-13 CLB N 10/27/2010 ALL Incorporated ECO’s 1436, 1438, 1463, 1464, 1466, 1469, 1470 & 1476; Updated RFMS’ GA107-2, GA107-2-P132, GA107-2-P148, GA107-2-P149 NOT ISSUED Incorporated ECO’s 1479, 1480, 1491, 1493, 1494, 1497, & 1506. Removed RFMS’ GA107-2, GA107-2-P132, GA107-2-P148 & GA107-2-P149 Incorporated ECO-1506 Rev A for SB AS350-01.00.66 Incorporated ECO-1507, 1508, 1509, 1510, 1511, 1512, 1513, 1530, 1533, 1536, and 1537 CLB O P 01/07/2013 ALL Q 02/12/2013 ALL R 1/6/2015 ALL Page 11 of 11 CLB CLB CLB CLB GA107 Rev R 1/6/15 U.S. DEPARTMENT OF TRANSPORTATION I.DATE FEDERAL AVTATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS April 2,2015 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.MAKE 3.MODEL NO. 4.TYPE Airbus Helicopters Note I Helicopter ]ANT (Airplane, Engine,Propeller, etc.) Eagle Copters USA, Inc. LIST OF DATA 6. IDENTIFICATION 7. TITLE Eagle Copters USA, Inc. Engineering Change Order ECO-1538 Revision A Dated 4lll20l5 Note 1: Eligible Models are AS350B, BA, Bl,B2,83, C, D, Dl onA S. PURPOSE OF DATA Structural approval of an optional cover supporting STC SH4747NM. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 27 27.301,27.303,27.305,27.307(a),27.561,27.601,27.603,27.605,27.607,27.609,27.611, .613,27 .619, 27 .625 10. CERTIFICATION - Under the authority vested by direction ofthe Administrator and in accordance with condilions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets nurDbered _L have been examined in acoordance with establishcd procedurcs and found to cofiply with applicable tequi.ements ofthc Airworthiness Standards listed. ! I AVe) Therefore r r. srcNAruRE(s) oF lxl Recommend spproval ofthese dats Approve thcse datr DEsrcNAy',rf Jeremy Mccrenahan NGTNEERTNG REpREy)d nlftsl (L 4 f%. 17 L'v- // FAA Form 8110-3 (03/10) SUpERSEDES pREvrous EDrrroN 12. DESTGNATTON NUMBER(S) DERT-636444.NM 13. CLASSTFTCATTON(S) Structures ENGINEERING CHANGE ORDER Date: 4/01/2015 ECO No: ECO- 1538 Rev: A STC: SH4747NM MDL: GA107 Rev: R STC Title: Electrical System Upgrade Effective for: Production; or Listed Aircraft Only: Primary Documents Effected: See list below Description of Change: Minor updates to P132 BOM; Added FOD cover to P132. Updated Bus bar connection figures. Detailed Explanation: GA107-1: Page 5, updated Figure 2 to correct the fastener order. G10251-1: was updated as follows: Item 16 added alternate part number SL2-0025-ER0201 Item 20 description was “locking toggle”. G10251-5 Sheet 2: item 15 was item 22 on Center Switch Rail Assembly. Sheet 4: Updated Bus Bar connection detail to correct the fastener order. G10251-6: Added FN1 and revised trimming note to be optional for P122 consoles. G12310-2: Updated Bus Bar connection detail to correct the fastener order. G13138: added as an optional cover installation along with G13138-1 cover detail. ECO DOCUMENT LIST NOTE: CH X X X X X in CH (change) column indicates change from last revision level. DOC No. G107-1 G10251-1 G10251-5 G10251-6 G12310-2 G13138 G13138-1 PAGES 7 5 4 1 1 1 1 REV H S L H H --- DATE 4/01/15 3/6/15 4/01/15 4/01/15 4/01/15 3/5/15 3/5/15 DESCRIPTION Installation Instructions P132 Console Standard Parts List Switch and CB Rail Assy Details Terminal Block Assembly CB Door Assembly Cover Installation Cover ECO LOG OF REVISIONS REVISION LEVEL PAGES - DATE OF REVISION 3/9/15 A 4/01/2015 ALL ALL DESCRIPTION OF CHANGE APPROVAL Initial Release Revised GA107-1, G10251-5, G102516, and G12310-2 CLB CLB EAGLE COPTERS USA INC. 19717 62nd Avenue South, Suite E101, Kent WA 98032 | Phone: 800-546-2210 www.eaglecopters.com ECO-1538 Rev A GA107.doc Page 1 of 1 U.S. DEPARTMENT OF TRANSPORTATION I.DATE FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS August 25, 2015 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.LIAKE 3.MODEL NO. 4.TYPE (Airplane, Engine,l)ropeller, Airbus Helicopters Note I Helicopter etc.) 5.NAME OF APPLICANT Eagle Copters USA, Inc. LIST OF DATA 6. IDENTIFICATION ECO- 7. TITLE Eagle Copters USA, Inc. Engineering Change Order l54r Revision A Dated 812012015 Note l: Eligible Models are AS350B, BA, Bl,B2, 83, C, D, D1 onA S. PURPOSE OF DATA Structural approval of an console changes supporting STC SH4747NM. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 27 .301 , 27 .303 , 27 .305, 27 .307 (a), 27 .561 , 27 .601 , 27 .603 , 27 .605, 27 .607 , 27 .609, 27 .617 .613, 27 .619, 27 .625 , 27 10, CDRTIFICATION - Under th€ authority vested by direction ofthe Administrator and in accordance with conditions and limitations of appointment under 14 CFR Parr | 83, data listed above and on attached she€ts numbered _L have been examined in accordance with established procedures and found to comply with applicable requirements ofthe Airworthiness Standards listed. | (r#e) Therefore t l. SI G NATU Jeremy R E( s) oF DE SI fl E Reconncnd approvrl ofthese drta Approve these datr GNpF}{{'IG Mccrenaha( INEE RI NG R E PRE SE ryTAT L - //^r%h // FAA Form 8l l0-3 (03/r0) SUpERSEDES pREvrous EDrrroN r, "F I2. DESIGNATION NUMBER(S) I3. CLASSIFICATION(S) DERT-636444.NM Structures ENGINEERING CHANGE ORDER Date: 8/20/2015 ECO No: ECO- 1541 Rev: A STC: SH4747NM MDL: GA107 Rev: R STC Title: Electrical System Upgrade Effective for: Production; or Listed Aircraft Only: Primary Documents Effected: See list below Description of Change: Various minor changes to aid console production. Detailed Explanation: GA107-1: Added sections 1.7 & 1.8 defining the use of ty-wraps and protective sleeving on wire harnesses. G10251-1: Added Item #103 Cable Ties; updated p/n for items #85 & #86; Added G10256 -11 thru 14 & -18; Added G10254-1 & -2. G10251-5: Sht 1, added item #31 lock washer under item #90 screw head. Sht 3, revised G10251-58 item #17 to G10256-18 insulation. G10251-6: Revised pictorially to show all installed washers and nuts. G10256: Revised material to be formex with adhesive applied to one side. This required adding opposite hand parts with new dash numbers to be used on the G10257-2 LH side wall assy. G10257: Updated -2 LH side wall assy to use the new insulation part numbers. G12310: Expanded the drawing to 3 sheets to add new views defining the assembly steps in more detail. Updated the BOM to include cable harness assembly detail parts for reference. Added shipping brace G12310-17 that is removed before installation into aircraft. G12310-2: Added item #17 hole plug with FN1. Updated circuit breaker table with additional part numbers approved for use. G12310-5: Added Sht 2 detailing the terminal strip installation. Previously, this was referenced to the P132 console instructions. G12310-6: Added item #7 hole plug with FN1. G12310-7: Updated switch table with additional part numbers approved for use. Removed P148 and P149 wiring note as these consoles have been discontinued for production. G12310-17: New shipping brace detail part. EAGLE COPTERS USA INC. 19717 62nd Avenue South, Suite E101, Kent WA 98032 | Phone: 800-546-2210 www.eaglecopters.com ECO-1541 Rev A GA107.doc Page 1 of 2 ECO DOCUMENT LIST NOTE: CH X X in CH (change) column indicates change from last revision level. DOC No. GA107-1 G10251-1 G10251-5 G10251-6 G10256 G10257 G12310 G12310-2 G12310-5 G12310-6 G12310-7 G12310-17 PAGES 9 5 4 1 1 1 3 1 2 1 1 1 REV J T N J C C D J E B D -- DATE 5/19/15 5/19/15 8/20/15 5/19/15 5/19/15 5/19/15 5/19/15 5/19/15 5/19/15 5/19/15 5/19/15 5/19/15 DESCRIPTION Installation Instructions P132 Console Standard Parts List Switch and CB Rail Assembly Terminal Block Assembly Insulation P132 Console Side Wall Assy P122 Console Assy RH CB Door Assy Connector Bracket Assy Overlay Assy Switch Plate Assy Shipping Brace ECO LOG OF REVISIONS REVISION LEVEL A DATE OF REVISION 6/4/15 8/20/15 PAGES ALL ALL DESCRIPTION OF CHANGE APPROVAL Initial Release Revised G10251-5 CLB CLB EAGLE COPTERS USA INC. 19717 62nd Avenue South, Suite E101, Kent WA 98032 | Phone: 800-546-2210 www.eaglecopters.com ECO-1541 Rev A GA107.doc Page 2 of 2 Electrical System Upgrade STC SH4747NM Installation Instructions GA107-1 Rev J 5/19/2015 1.0. INTRODUCTION. The Eagle Copters Electrical System Upgrade STC provides for replacement of the factory standard center electrical console that has push-button switches & fuses and replaces them with a system of toggle switches and circuit breakers as a complete replacement console. The console comes in two basic designs that the installer may choose to use depending on their specific requirements. 1.1. The P122 Switch Console holds up to 24 Mil-Spec sealed toggle switches and up to 60 Mil-Spec circuit breakers. It comes pre-wired and assembled from Eagle Copters custom configured to match the installer’s aircraft wiring requirements. This console also features an LED backlit switch legend and an internal dimmer power supply and control that allow independent dimming of the console to any desired level for maximum crew comfort during night operations. For P122 Console installations, refer to: G12311 P122 Installation Instructions. GA107-1 Rev J Page 1 of 9 1.2. The P132 Avionics Console holds up to 20 MilSpec sealed toggle switches and up to 60 Mil-Spec circuit breakers. It comes pre-wired and assembled from Eagle Copters custom configured to match the installer’s aircraft wiring requirements. This console features a central avionics bay for mounting up to 10.4” of avionics and radios. This console also features LED backlit switch legends and an internal dimmer power supply and control that allow independent dimming of the console to any desired level for maximum crew comfort during night operations. For P132 Console installations, refer to: GA107-6 P132 Installation Instructions. This STC also contains optional modifications that may be installed to suit the installer’s specific needs. These include: 1.3. P176 Dimmer Power Supply: This is a direct plug-in replacement for Eurocopter Dimmer 31L P/N 55670 (ref 704A46814049) used in all AS350 models manufactured Post-MOD 350A07-1182. Refer to: GA107-12 P176 Dimmer Power Supply Installation Instructions. 1.4. Airframe Ground Points Upgrade. This modification is Optional at the installer’s discretion, and improves the reliability of the airframe ground points. Refer to Section 2 of this document for instructions on this modification. 1.5. Auxiliary Circuit Breaker Rail G10268-10. This modification adds a bracket under the Instrument panel on the Pilot’s side. This bracket provides a mounting location for up to 12 circuit breakers, 3 switches, an ELT switch and KA51B Slave Accessory switch group. Refer to Section 3 of this document for instructions on this modification. 1.6. Accessory Relays and Circuit Breakers. This modification adds Accessory Relays and Circuit Breakers for non-essential equipment. Refer to Section 4 of this document for instructions on this modification. GA107-1 Rev J Page 2 of 9 1.7. For all modifications listed in this STC, wire bundles may be secured as required using nylon cable ties (Ty-Wraps) as listed in the tables below. Cat. No. TY23M TY24M TY25M Cat. No. PLT2M-M PLT31-M 1.8. Cable Tie Selection Chart Thomas & Betts Brand Max. Body Length Wire Width In. Bundle In. Dia. In. .091 3.62 .62 .140 5.50 1.12 .184 7.31 1.75 Cable Tie Selection Chart Panduit Brand Max. Body Length Wire Width In. Bundle In. Dia. In. .098 8.00 2.00 .145 11.40 3.00 Tensile Strength Lb. 18 40 50 Tensile Strength Lb. 18 40 For all modifications listed in this STC, and at the installers discretion, wire bundles may have protective expandable sleeving applied. Ref: ICO-RALLEY p/n’s XPF-1/8, XPF-1/4, XPF-3/8, XPF-1/2, XPF-3/4. The original electrical system including the battery, starter generator and distribution system is unchanged. 2. Airframe Ground Points Upgrade This modification improves the reliability of the airframe ground points and is optional at the installer’s discretion. NOTE: Route all new wires along existing bundles. See FAA AC43.13-1B, Chapter 11, Section 15 for acceptable methods for routing, lacing and securing bundles. 2.1. Remove ground terminal blocks 1N, 2N, 3N, 4N, 9N, 10N, and 13N. (see section 90.00.10, sheet 1 of the latest revision of AS350 Wiring Diagram Manual for location of ground terminal blocks). 2.2. Remove the wires from each ground terminal. Strip insulation from wires and crimp an insulated #10 ring terminal of the correct size on to each wire. Refer to Table 1 for correct terminal/wire usage. Use the installation tools recommended by the terminal manufacturer. GA107-1 Rev J Page 3 of 9 Table 1 Manufacturer Stud Size Color Wire Size (AWG) AMP P/N AMP or equivalent 4 Red 22-16 31880 AMP or equivalent 6 Red 22-16 36150 AMP or equivalent 6 Red 22-16 36152 AMP or equivalent 8 Red 22-16 31886 AMP or equivalent 10 Red 22-16 36154 AMP or equivalent 1/4 Red 22-16 31894 AMP or equivalent 6 Blue 16-14 36158 AMP or equivalent 8 Blue 16-14 320565 AMP or equivalent 10 Blue 16-14 36160 AMP or equivalent 6 Yellow 12-10 35107 AMP or equivalent 8 Yellow 12-10 35108 AMP or equivalent 10 Yellow 12-10 35109 2.3. Using a 1/2” diameter burnishing brush, clean to bare metal on both sides of the area around the holes where the original ground terminal blocks were attached. This cleaned area must now be corrosion-proofed. This is done by acid etch, rinsing with water and the application of alodine using a small brush, sponge or cloth soaked in alodine solution. Allow the alodine to soak the cleaned area for several minutes, rinse with water and dry the contact area. Use 1 ea. AN526-1032R14 screw, 5 ea. NAS1149F0363P washers and 2 ea. MS21042-3 locknuts for each group of up to 4 ground terminals. 2.4. Install the grounds at each location per AC 43.13-1B, Chapter 11, Section 15, Tables 11-14, 11-15, 11-16. Add additional ground points as needed. Cover completed grounds with standard green lacquer (Vernelec 43022, Airbus ECS2228.10 or equivalent). GA107-1 Rev J Page 4 of 9 3. Auxiliary Circuit Breaker Rail G10268-10 This modification is Optional at the installers discretion. This modification adds the Aux Circuit Breaker Rail under the Instrument panel on the Pilot’s side. This bracket provides a mounting location for up to 12 circuit breakers, 3 switches, an Artex ELT control panel and KA-51B control panel. 3.1. Remove vent cable from vent support (350A25-1342-21) 3.2. Remove and discard vent support. FIGURE 1 3.3. Position the Aux Circuit Breaker Rail as shown in Figure 1 onto bottom of the Instrument panel Support Tube. Back drill the support tube in 4 places 0.129 Dia (#30 Drill) using the Aux Circuit Breaker Rail as a guide. 3.4. Install Rail to Support tube using (4) CR3213-4-3 “Cherrymax” rivets (or equivalent), mount Aux Circuit Breaker Rail to the support tube. 3.5. Use the slotted inboard hole of the Aux Circuit Breaker Rail to remount the pilot’s vent cable. 3.6. Install desired circuit breakers and switches into holes provided in rail. Ensure that the circuit breakers are connected to the correct “PP” buss for correct load distribution. See Airbus Helicopters WDM chapter 39 for each system’s “PP” assignment. GA107-1 Rev J Page 5 of 9 3.7. Use buss bar P/N G12135-x if multiple breakers are to be joined to a common buss. The “x” in the buss bar part number represents the number of breakers to be connected together. Example: for 2 breakers, use buss bar G12135-2. Circuit Breaker spacing is for MS26574-xx Circuit Breakers or equal. 3.8. Buss wires are attached to the buss bar as shown in Figure 2. FIGURE 2 3.9. See Table 1 for ring terminal part numbers. 3.10. For circuits requiring #8 AWG wire, use wire P/N M22759/16-8-9 and ring terminals AMP #33460 (#10-32) at one end and AMP #324061 (#8-32) at circuit breaker end. Install rubber boots MS25171-2S over #8 ring terminals. 3.11. Switch and circuit breaker wires for optional installation can be fabricated from #6 ring terminals #36152, #18 AWG wire P/N M22759/16-18-9 and butt splices #320559. Route and secure wire bundles IAW AC 43.13-1B, Chapter 11, Section 15. 3.12. Optionally, the installer may mount an ARTEX ELT control panel in the space provided using the hardware supplied with the control panel. 3.13. Optionally, the installer may mount a KA-51B control panel in the space provided using the hardware supplied with the control panel. 3.14. Install a placard above each switch and circuit breaker. Optionally, the installer may use Legend Strip G10268-10-LS using (5) #4-40 x .31 screws (MS35206-214 or 4C31PPMSB). GA107-1 Rev J Page 6 of 9 4. Accessory Relays and Circuit Breakers This modification is Optional at the installer’s discretion. This modification adds Accessory Relays and Circuit Breakers for non-essential equipment. 4.1. Refer to drawing G10284 for additional installation instructions. 4.2. Master Electrical Box (MEB) Modifications. 4.2.1. Refer to Sheet 1 of G10284. 4.2.2. Attach CBF1 – CBF3 to mounting bracket G10269-1 and Bus Rail G10269-3. 4.2.3. Install Terminal Bridge G10269-5 to terminal block. 4.2.4. Temporarily install the CBF1 - CBF3 / bus rail assembly onto terminal strip as shown in view A-A. 4.2.5. As shown in View A-A, Use mounting bracket as a guide to locate and drill (2) 0.156 Dia mounting holes for mounting bracket into the side of the MEB Case. 4.2.6. Remove CBF1 – CBF3 / bus rail assembly from Terminal Strip and install bus wires onto the Circuit Breakers. 4.2.7. Reattach CBF1 - CBF3 / bus rail assembly onto terminal strip. 4.2.8. Attached CBF1 – CBF3 to MEB wall using Doubler G10269-2 and (2) #6-32 x .5 pan head screws (MS35206-230). 4.2.9. Repeat Steps 4.2.2 - 4.2.8 for CBF4 using Bus Rail G10269-8. 4.2.10. Label each circuit breaker with designator and function. Ex. “CBF1 Avionics”. 4.2.11. Locate existing hole in frame adjacent to airframe ground point 4N, see detail view D-D. Using a 1/2” diameter burnishing brush, clean to bare metal on both sides of the area around the hole. Spot alodine area around hole to protect the bare metal. 4.2.12. Install ground stud as shown in view D-D. This ground point may be used for the CBF4 circuit and/or other installer defined circuits. Use Table 1 to select the correct ring terminal for the installed wire. 4.3. Accessory Relay Installation. 4.3.1. Refer to Sheet 2 of G10284. 4.3.2. Note: This installation shows the mounting of three relays on the LH side keel beam at STA 91.54 . At the installer’s discretion, they may choose to install only one or two relays, depending on the specific accessory system requirements. 4.3.3. The installation shown is typical and for reference only. At the installer’s discretion, the relays may be relocated to an alternate location to avoid interference with pre-existing equipment. 4.3.4. Using doubler G10269-9 as a guide, layout and drill mounting points. 4.3.5. Install doublers and nutplates using rivets shown in View F-F. 4.3.6. Install Relays using hardware shown in View E-E. 4.3.7. Install wiring connection to relays and secure cable harness. 4.3.8. Label each Relay with designator and function. Ex. “Avionics Master”. GA107-1 Rev J Page 7 of 9 4.4. Accessory Wiring Installation. 4.4.1. Refer to Sheet 3 of G10284 for instructions on fabricating cable harness. 4.4.2. The circuitry shown represents a typical ENG configuration of one avionics bus controlled by a separate switch and two accessory buses controlled by one switch located in the P122/P132 switch console. Other configurations may require only a single avionics master circuit and no accessory circuits, or a second avionics master circuit, etc. 4.4.3. Unless otherwise noted, all shielded wire is M27500-(ga)TG(n)T14 and all unshielded wire is M22759/16-(ga)-9, where (ga) is the wire gauge and (n) is the number of wires inside the shield. 4.4.4. All Bonding and Grounding will be done in accordance with AC 43.13-1B, Chapter 11, Section 15. 4.4.5. All G12113-xxx wires are 8 GA unshielded. All G12091-xxx wires are 20 GA unshielded. The wire numbers shown are examples. At the installer’s discretion, different wire numbers may be used , provided that they uniquely identify each wire and the gauge of the wire. 4.4.6. When Routing wires through the MEB case, use existing feed-thru grommets on the FWD outboard area. 4.4.7. When installing wires to the circuit breakers, a service loop of 3-4 inches should be left at each wire with respect to the circuit breaker it is associated with. 4.4.8. All 8 GA wire terminations should have 1” of black heatshrink tubing (3/8” dia) applied over the barrel of the terminal and the first 1/2” of the wire. 4.4.9. Route wires G12113-xxxx along the left side of ship following wire PP6E and secure at the same locations. 4.4.10. Route wires G12113-xxxx and G12091-xxxx along left side of ship following existing cable runs up to P122/P132 console to connect with the designated bus or switch circuit. 4.4.11. Test continuity through each installed circuit breaker and relay before applying power. GA107-1 Rev J Page 8 of 9 L OG O F R EVISIONS REVISION LEVEL -A B C D E DATE OF REVISION 7/26/98 11/19/90 8/7/93 7/25/95 12/15/98 1/15/2004 PAGES DESCRIPTION OF CHANGE APPROVAL All Pages All Pages All Pages All Pages All Pages All Pages GLH GLH GLH GLH GLH CLB F G 4/25/08 12/5/14 All All H J 4/01/15 5/19/15 5 3 Initial Release Revised for AS350B2 Revised for AS350BA Added Option 1 Text Change Renamed document and removed P132 Console Added P148 & P149 consoles Removed P148 & P149 and obsolete modifications. Updated format and company name to Eagle Copters Revised fastener order for Figure 2 Added sections 1.7 & 1.8 GA107-1 Rev J CLB CLB CLB CLB Page 9 of 9 STC SH4747NM RFMS for AS350 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT for AS350 Series Helicopter Registration Number: Serial Number: _ ----- Electrical System Upgrade This installed in accordance with STC SH4747NM requires this supplement to be included in the FAA Approved Rotorcraft Flight Manual for the aircraft, only if any of the modifications shown in this Rotorcraft Flight Manual Supplement have been installed. The STC covers many modifications to the aircraft that are not listed in this supplement, and therefore do not require this supplement. THIS ROTORCRAFT FLIGHT MANUAL SUPPLEMENT IS FOR AIRCRAFT WITH P132 CONSOLE INSTALLED This supplement only adds to the basic Rotorcraft Flight Manual. For limitations, normal procedures, emergency procedures and performance information not contained herein, consult the FAA Approved Rotorcraft Flight Manual. .J4--., ~ FAA Approval: Manager, r'i!. SeattleAircraft CertificationOffice ( Page 1 of 10 l,1AR - 4 2011 GA107-2-P132Rev F.doc STC SH4747NM RFMS for AS350 LOG Rev. Date OF REVISIONS Description level A 4/16/2004 8/12/04 Initial Release Added two new cyclic stick pIn's for bendix installations B 10/12107 C 9/25/08 0 E 7/17109 10/26/10 F 2/10/11 grip Adds section 3.9 for Master Cutoff switch and 3.11 for the Direct Battery Switch; updates section 3.3. 3.5. and 3.7 Removed section 6 FiQures Revised color coding of switches in 3.3: removed 42 for reseltinQ circuitbreakers Added Section 3.12 for switch dimmer control Added Section 4.2 for Generator Reset function Added Section 3.13 for Float Arm switch and 4.3 for the Float Innate switch. lenend Note: The approval for the revision is implemented FAA Approval signature on the cover page. Page 2 of 10 MAR - 4 2011 GA 107-2-P132 by the Rev F.doc STC SH4747NM RFMS for AS350 TABLE OF CONTENTS SECTION PAGE 1 GENERAL 2 LIMITATIONS 3 NORMAL PROCEDURES 4 EMERGENCY 5 PERFORMANCE Page 3 of 10 INFORMATION 4 5 6-9 PROCEDURES IAAR - 4 2011 10 10 GA107-2-P132 Rev F.doc STC SH4747NM 1. RFMS for AS350 GENERAL INFORMATION 1.1. The electrical system in this rotorcraft has been modified by changing fuses to circuit breakers, and push button switches to toggle switches, as well as various other optional changes. 1.2. An optional instrument light modification replaces the factory instrument panel lighting with post lighting for the instruments. An optional Auxiliary Circuit Breaker Panel provides space in front of the pilot for switches and circuit breakers. 1.3. Some of the circuits have been wired differently from the factory original wiring, although the functional operation is unchanged. Refer to the installation documents when performing electrical maintenance on this aircraft Page 4 of 10 MAR - 4 2011 GA107-2-P132 Rev F.doc STC SH4747NM RFMS for AS350 2. LIMITATIONS 2.1. Cyclic travel restricted by pilot's or copilot's leg The P132 Console could limit cyclic travel toward the console if the Pilot's or Copilot's leg is wedged between the console and the cyclic. This may not be noticed except during flights requiring cyclic movements near lateral limits (such as with a substantial lateral C.G. loading, high crosswinds, or slope landings). To address the potential of flight control restriction, this aircraft has been modified with replacement Pilot and Copilot Cyclic Sticks. Before flight, the pilot must verify that the factory pilot and copilot cyclic sticks have been replaced with Geneva RH Cyclic Stick G12316-26 or G12425-26 for the RH seat position and Geneva LH Cyclic Stick G12324-26 or G12426-26 for the LH seat position. 2.2. Placard, located on aft wall of P132 Console. MAXIMUM INSTALLED RADIO WEIGHT: 30 LBS Page 5 of 10 '~AR - 4 2011 GA107-2-P132Rev F.doc STC SH4747NM 3. RFMS for AS350 NORMAL PROCEDURES 3.1. Push button switches on the console switch panel have been replaced with toggle switches. When a procedure calls for the "pushed" position for a switch, move the correct toggle switch to the ON position. For most switches, the ON position is toward the nose of the aircraft, or toward the ceiling if mounted on a vertical panel. Some switches may be a center-off type of switch with two on positions. 3.2. For a center-off type of switch, the label will designate the action performed in each non-center position. For example, the anti-collision light switch is normally a center-off switch. The label: ANTI-COL ALL I TAIL indicates that the up position turns on all strobe lights attached to this switch, and the down position turns on only the tail strobe light. When you see the slash character think of it this way: UP I DOWN. 3.3. The HYDRAULIC TEST (or HYD or ACCU TEST) and MASTER CUTOFF switches are locking toggle style. Some of the remaining switches may optionally be locking toggle or normal toggle type switches. For locking toggle type switches, pull out on the toggle while moving it to disengage the locking feature. The MASTER CUTOFF switch, and no other, is color coded RED. The HYDRAULIC TEST switch, and no other, is color coded YELLOW. Other switch toggles may optionally be color coded using colors other than red or yellow to help identify the switch. Page 6 of 10 MAR - 4 2011 GA 107-2-P132 Rev F.doc STC SH4747NM RFMS for AS350 3.4. If the WARN I FIRE TEST switch of switch, then move the switch toggle to test all of the Caution Panel warning the switch toggle in the down direction Warning System. is a center-off type in the up direction lights, and move to test the Fire 3.5. Most of the switch and circuit breaker locations are optional and will vary from aircraft to aircraft. Be sure to familiarize yourself with the arrangement of switches and circuit breakers in this particular aircraft. 3.6. Fuses have been replaced by circuit breakers. The circuit breaker plunger can be pulled out to the OFF position. The plunger will "pop" out if the corresponding circuit is over-loaded. The circuit breaker can be reset by pushing in the plunger. 3.7. Circuit breakers may be located on the P132 Console, the optional Auxiliary Circuit Breaker Panel, inside the Master Electrical Box, and are marked to identify the associated circuit. 3.8. The typical installation contains circuit breakers and switches for functions that may not be applicable to this particular aircraft. The non-applicable circuit breakers and switches may be re-Iabeled and wired for another function at the discretion of the installer, or they may be left uninstalled, otherwise they must be labeled to indicate that they are not used. Page 7 of 10 MAR - 4 2011 GA107-2-P132 Rev F.doc STC SH4747NM RFMS for AS350 3.9. Aircraft that are post-mod 350A07-3273 are factory equipped with an Emergency Switch mounted on the instrument panel. Pre-mod aircraft are factory equipped with a Master switch in the factory console. In either case, this switch has been removed and replaced with the MASTER CUTOFF switch on the P132 console. 3.10. Leaving the MASTER CUTOFF switch in the cutoff position (toggle toward the nose) provides power to certain devices, which will cause the battery to run down if this switch is left in the cutoff position when the aircraft is parked, regardless of the position of the BAT-EXT POWER switch. 3.11. If the aircraft is equipped with a Direct Battery Bus, leaving the DIRECT BATTERY switch in the ON position (toggle toward the nose) provides power to certain devices, which will cause the battery to run down if this switch is left in the ON position when the aircraft is parked, regardless of the position of the BAT-EXT POWER switch. 3.12. The console switch legends are illuminated. Dimmer control for the legends is controlled by the rotary knob located on the RH side of the console under the switch rail. Turning the knob clockwise increases the brightness for the legends. Page 8 of 10 'AAR - 4 2011 GA107-2-P132Rev F.doc STC SH4747NM RFMS for AS350 3.13. For consoles equipped with a FLOAT ARM switch: Prior to takeoff over water, first check the FLOAT INFLATE switch to make sure it is OFF and covered. Next, ensure that the FLOAT ARM switch is in the armed position. Verify that the two FLOAT ARM amber indicator lights are illuminated. Page 9 of 10 'JAR - 4 2011 GA 107-2-P132 Rev F.doc STC SH4747NM 4. RFMS for AS350 EMERGENCY PROCEDURES 4.1. Moving the MASTER CUTOFF switch toward the aircraft nose disconnects most electrical power to aircraft equipment. The ROTOR TACH and the Pilot's overhead fioodlights continue to receive power when the MASTER CUTOFF switch is in the cutoff position. Any installed equipment that is connected directly to the battery will continue to have power as well. 4.2. To engage the Generator Reset function, move the toggle of the GENERATOR ON I RESET switch to the aft position and hold in place for 2 seconds. Also, there is no GENE or GENE RST breaker on the P132 console; its function is handled by the CRANK breaker, located on the right side of the P132 console. 4.3. For consoles equipped with a FLOAT ARM switch: The FLOAT INFLATE switch is located on the cyclic stick mounted to the tube below the grip. To activate the switch, open up the cover and fiip the toggle. Refer to the fioat manufacturer's RFMS for procedures on infiating the fioats. 5. PERFORMANCE No change to basic Flight Manual. Page 10 of 10 \lAR - 4 2011 GA107-2-P132 Rev F.doc P132 Console Installation Instructions GA107-6 Rev Q 12/5/2014 GA107-6 Rev Q Page 1 of 18 1.00 INTRODUCTION and GENERAL INFORMATION 1.10 These Installation Instructions cover the installation of the P132 Console into the AS350 series helicopter. 1.20 Study all documents associated with this installation prior to starting work on the aircraft. 1.30 The P132 Console installation consists of the replacement of the factory original Switch pedestal with the P132 Console, including the installation of toggle switches and circuit breakers. 1.40 The P132 console is both taller and wider than the Airbus Helicopters original console, which may limit cyclic travel under certain conditions. Modifications to the flight controls are required to correct this and these are described in section 4.00. 1.50 The switch layout and circuit breaker layout varies between the various AS350 series models. Confirm that you are using the diagrams appropriate for your AS350 model. 1.60 The Airbus Helicopters AS350 Wiring Diagram Manual (WDM) and Maintenance Manual (MWC) are required to perform this alteration. Mod levels concerning electrical systems for the specific helicopter determine which schematics in the WDM should be used. Several of the drawings refer to these manuals. 1.70 The existing Airbus Helicopters wire labeling system is used outside the console where appropriate. 1.80 Wire labels associated with the console may use the format: G12132-4-03. This example wire label indicates that the particular wire is to be found on drawing number G12132-4, with the -03 identifying the particular wire on that drawing. Other label formats may be used, and are described on the G12132 Instructions pages. 1.90 Document G12132 consists of instructions, notes, schematics, layouts, and misc. information pertaining to the console for installation and follow-on maintenance. 1.100 All wires installed by this STC are AN20 gauge, except as noted on the drawings. 1.110 The AS350 Standard Practices Manual Chapter 20.02.01.410 through .415 should be read and followed as a guide for this work. 1.120 Familiarize yourself with the electrical system revision level for the aircraft that you will install this console on. Examine the wiring for undocumented modifications as well. Also determine the optional equipment that has been or will be installed. 1.130 The wiring document, G12132, lists several variations and choices that the installer must decide on. It will be easier to make these determinations and gather useful information before you dismantle the aircraft. 1.140 The information contained in G12132 will be used for several purposes. Make two photo copies of this document to use as working copies before you start the installation, in order to preserve the original document. 1.141 While performing the installation, make notes and show customization on the "Notes Copy" of the working copies. 1.142 Use the other "Done Copy" of the working copies to mark off each wire and component as you complete the installation of that wire, or other component in order to accurately keep track of your progress. 1.143 Upon completion of the installation, make a copy of the "Done Copy" to use for test purposes. As you test each component and function, mark off the test results on the "Done Copy" to keep track of your progress. After testing and corrections, the "Notes" working copy should represent the final “As Built” configuration. GA107-6 Rev Q Page 2 of 18 1.150 The console labels for the circuit breakers are normally provided with the console kit. However, the installer may use any labeling method that provides clear indication of the circuit breaker's function. 1.160 This installation is a major rewiring of the electrical system for the aircraft. You should anticipate all of the possible failure modes in order to prevent them. For example, some of the failure modes possible are obvious, such as a defective switch, circuit breaker, diode, connector, or a simple wiring error. Some of the less obvious failure modes are: 1.161 A terminal is crimped improperly, resulting in an intermittent connection 1.162 A diode is in the circuit backwards 1.163 A connector pin is not correctly seated, resulting in an open or intermittent connection 1.164 A connector pin is bent, resulting in an open, or intermittent connection 1.165 A connector pin is bent, resulting in a short to an adjacent pin 1.166 Metal shavings are inside a connector, resulting in intermittent short circuits 1.167 A wiring error connects two circuits together, resulting in confusing behavior 1.168 A wiring error connects some of the wires to the wrong terminals of a switch 1.169 A wiring error connects the wire to the wrong pin of a connector 1.170 Powering up the aircraft or a circuit with wiring errors can result in damage to very expensive components. The best defense against wiring errors and damage is to double check each step of the installation as each step is made. Later, have someone else re-check each step of the installation. Do not apply power to the aircraft until all errors have been corrected. 1.180 Take extra precautions in establishing that the wiring diagrams provided are really suitable for your aircraft. Also, your aircraft may have had some undocumented changes made to it, or some undiscovered wiring errors. 1.190 When the installation is complete, the aircraft weight and balance records will need to be updated. This STC does not provide weight and balance information because there is a significant variation in the weight of items removed and items installed from one installation to the other. Therefore, the installer must keep track of the weight and location of items removed, and the weight and location of new items installed throughout the installation process in order to be able to calculate the change in aircraft weight and balance when the installation is complete. This is not required if the aircraft will be weighed after the installation is complete. 1.200 The console provides for much of the standard helicopter optional equipment. Most helicopters will not have all of the optional equipment installed. The installer may, at the installer’s discretion, use any of the unneeded switches and circuit breakers for other uses. Normally, this optional use will not change the wiring in the console, but will change the switch and circuit breaker labels and possibly the switch type and circuit breaker amp rating. 1.210 The console provides mounting locations for installer provided additional circuit breakers, to be used for installer defined optional uses. These circuit breakers may, at the installer’s discretion, use the G12135-x bus bars either whole or cut into smaller segments, as appropriate. The installer must document these additions and add that documentation to the final “As Built” document set. 1.220 The wiring information provided primarily pertains to the console. Installer provided wiring external to the console should be documented and added to the final "As Built" wiring document package. GA107-6 Rev Q Page 3 of 18 1.230 Document G12132-1 specifies required locations for certain switches, and required grouping of certain circuit breakers based on supply bus restrictions. The location of the remaining switches and circuit breakers is optional. The installer may at the installer’s discretion, change the location of these remaining switches and circuit breakers to suit the particular installation, provided that the final labeling matches the final configuration. 1.240 The G12132 document includes examples of optional alternate functions for some switches; e.g. G12132-30 shows how to rewire the Sand Filter switch for use with the FDC/Aerofilter “Engine Alternate Air” system. 1.250 The Master Cutoff and Hydraulic Test must have locking toggles. For all other switches installed, the toggle may be either non-locking or locking, at the installer’s discretion, regardless of how the console was supplied from Eagle Copters. 1.260 Switch toggles may be color-coded to help identify the switch. RED color coding is REQUIRED for the Master Cutoff switch, and may not be used elsewhere. YELLOW color coding is REQUIRED for the Hydraulic Test switch, and may not be used elsewhere. Any color that is clearly distinguishable from these may optionally be used for any other switch. Color may be applied by the use of paint, a plastic coating or cover, vinyl dip, or other methods that do not interfere with the operation of the switch. 2.00 INSTALL AVIONICS INTO CONSOLE 2.10 Observe weight limitation when installing avionics into console. 2.20 Establish suitable mounting position for each device that mounts in the console. 2.30 Mount each device using suitable fasteners in accordance with appropriate documentation, such as device manufacturer's installation instructions. 2.40 Wire these optional devices in a suitable way, to allow easy servicing of the devices and the console. Power for the devices may come from an existing unneeded circuit breaker, or additional circuit breakers may be installed in the unused circuit breaker positions within the console. 2.50 Clean entire console of all foreign materials to prevent short circuits and other effects of contamination. 2.60 GA107-6 Rev Q Page 4 of 18 3.00 AIRCRAFT PREPARATION 3.10 Disconnect aircraft battery. 3.20 For aircraft pre mod 350A07-3273, the following instructions apply: 3.21 Remove perimeter screws from original Switch Panel and raise to unbolt PP5E, PP6E and PP9E wires from their buses. Remove center console switches and fuse connectors from their boards. 3.22 Disconnect 301 and 302 from the 30 PCB. 3.23 Remove console assembly, P/N 350A61-1601-xxxx, retaining its attaching hardware. 3.24 Remove the 30 PCB for later reinstallation, retaining its mounting hardware. 3.30 For aircraft post mod 350A07-3273, the following instructions apply: 3.31 Remove perimeter screws from original Switch Panel and raise to unbolt 1PP5E, 1PP37E and 3PP23E wires from their buses. Remove center console switches and fuse connectors from their boards. 3.32 Remove console assembly, P/N 350A61-2686-xxxx, retaining its attaching hardware. 3.33 Remove any electrical devices mounted to the aft wall of the instrument panel support structure (radio bay) as these may interfere with the installation of the new console. This would include Pitot Heat relay 129F, and for the B2 only: Fire Detection relay 19W and Mounting Rail 20W. Feed their cables back through the floor opening and relocate them near Ground Point 19N. 3.34 There is an Emergency switch located on the instrument panel, whose function was performed by the Master switch pre-mod 3273. The console circuitry is NOT compatible with the Emergency switch and it must be disconnected and removed from the instrument panel. Its function is replaced by the Master Cutoff switch on the console. 3.35 For aircraft which retain the original Airbus Helicopters instrument panel pedestal, there is a circuit breaker panel (31ALPHA32) located on the right side of the pedestal. These circuits may be reassigned to circuit breakers on the P132 Console and the breakers removed from the panel. If all of the breakers are removed from this panel, then the installer may, at their discretion, cover the empty panel with cover plate G12899. 3.40 The P132 Console will limit cyclic travel toward the console if the Pilot’s and/or Copilot’s leg is trapped between the console and the cyclic. This may not be noticed except during flights requiring cyclic movements near lateral limits (such as with a substantial lateral C.G. loading or sloped landings). To address the potential of flight control restriction, replacement of the cyclic sticks must be done in accordance with Airbus Helicopters maintenance documents and Service Bulletin GA107-7. GA107-6 Rev Q Page 5 of 18 4.00 AIRFRAME MODIFICATIONS NOTE: For aircraft that are post-MOD 350A07-4280 (Multi-Bloc Console), begin at step 4.49. INSTRUMENT PANEL PEDESTAL ANGLED ALUMINUM BOX ORIGINAL CONSOLE Fig. 1 4.10 Modifying Airbus Helicopters Instrument Panel Pedestal. 4.11 There are two styles of Airbus Helicopters instrument panel pedestals. The newer style has the angled box component (see figures) as a separate piece of aluminum that is riveted to the forward right-hand side wall of the instrument panel pedestal. In both cases there are support angles on both inside walls of the original pedestal that are riveted to the sides and bolted to the floor. These angle supports are used as the forward support for the P132 Console, and as guidelines for removing the angled aluminum box. MAKE CUT AFT OF RIVET LINE, AND ALONG AFT EDGE OF ANGLED SUPPORT OLD STYLE NEW STYLE (ONE PIECE) (ANGLED PIECE RIVETED ON) REMOVE RIVETS BOTH SIDES Fig. 2 4.12 Remove the bolts attaching the aft section of the box to the floor. GA107-6 Rev Q Page 6 of 18 REMOVE RIVETS  BEFORE REMOVAL AFTER REMOVAL CUT LINE VIEW FROM ABOVE Fig. 3 4.13 Remove and discard the 4 nutplates from the aft side of the supports. Fig 4 4.14 Remove the angled box from the instrument panel support using figures 1 through 4 as a guide. 4.15 Remove the 2 bolts holding the shelf to the aft angle supports see fig 4. 4.16 Place the assembled console in position and install the three aft floor bolts. GA107-6 Rev Q Page 7 of 18 4.17 Obtain best fit between console and the structure shown in figure 5. Drill holes in forward face of console that line up with intended mounting holes in aircraft angle supports and shelf mounting holes. Install #10-32 screws, washers and locknuts through aircraft angle supports and shelf mounting holes to attach console to instrument panel support structure. 4.20 Install two bolts into the floor for each side of console. Enlarge holes if necessary for best fit. 4.30 For aircraft pre mod 350A07-3273, refer to Fig. 5 to mount the 30 circuit board assembly onto the inside right hand side wall of the instrument panel support structure, using original hardware and components. Optionally, the 30 panel may be mounted elsewhere, with wire lengths adjusted as necessary. 4.40 For aircraft pre mod 350A07-3273, install 350A61-1614-30 clear plastic guard after installing 301 and 302 connectors. Fig. 5 4.49 For aircraft that are post-MOD 350A07-4280 (Multi-Bloc Console), refer to drawing G13132 for structural modifications required to install the P132 Console. 4.50 Route all new wires along existing bundles. See FAA AC43.13-1B, chapter 11 for acceptable methods for routing, lacing and securing bundles. 4.60 Modify landing light circuit in accordance with G12132-4. GA107-6 Rev Q Page 8 of 18 4.70 Wire Connectors P1, P2, and the optional P3, in accordance with all pages of G12132 and the following instructions. Organize and label airframe the airframe wires assigned to the new connectors that will mate with the console connectors. Group the wires into separate bundles for each connector. 4.80 Trim the length of the wires appropriate for mating with the console connectors. Slide strain relief over each bundle. 4.90 Strip off a suitable length of wire insulation to allow the wire strands to be visible through the witness hole when inserted into rear of the connector terminal. When a 22 gauge wire must be crimped into a #16 connector terminal, take a second 22 gauge wire to be used as a filler wire and strip 1/2" long. Insert both 22 gauge wires into the terminal and crimp with the tool set for 20 gauge wire. Then cut off the filler wire flush with the terminal. 4.100 Crimp appropriate terminals onto appropriate wires, using suitable crimping tool. Then, hold each wire in one hand and pull the wire terminal with the other hand to determine that the crimp is strong enough to hold the wire securely. 4.110 Clean and inspect connectors and contacts to insure that no foreign matter is present to interfere with the contacts or foul connector. 4.120 Insert terminals into the correct hole of the connector body with a suitable installation tool. Be careful to observe upper & lower case letter designators for contact locations. It is usually easier to start with the center positions and install wires from the center toward the outside edge, basically in reverse alphabetical order. 4.130 Make sure all contacts are seated fully and are straight. Install strain relief clamps by wrapping wire bundle with rubber tape as required to make clamp effective. 4.140 Check all connectors for bent or oxidized contacts, proper seating of contacts, and remove any foreign material that might cause connector mating problems or short circuits. 4.150 Carefully connect P1 to J1, P2 to J2, and P3 to J3. Secure connectors to prevent strain on wires and to prevent connectors from causing harm to adjacent items. 4.160 Complete the installation of the console by installing fasteners, securing cables, wires, and connectors. GA107-6 Rev Q Page 9 of 18 4.170 Install collective hold-down strap (350A27-3107-126) onto collective hold-down mount (G12136) located on aft wall of console using (2) AN3-3A bolts and (2) NAS1149F0332P washers (see figure below). To insure that the strap does not inadvertently hook the collective during normal operation, the strap should be formed as shown in the figure. The dimensions shown are approximate and are to be used as a guide, as each console installation will vary slightly, requiring the strap to be formed to match the installation. When formed correctly, the strap will naturally touch the console aft wall, requiring it to be flexed in order to hook the collective. Be sure to adjust the strap height as required in Maintenance Manual 67.10.00.501 Section 3.3. Maintain a minimum gap of .118 inches (3mm) between the end of the hooking lock and the strap. 0.118 MIN. ~ 2-1/2" ~ 2" GROMMET ~ 3/8" COLLECTIVE HOLD-DOWN STRAP FORMING DETAIL COLLECTIVE GENEVA P132 CONSOLE COLLECTIVE HOLD-DOWN STRAP Optional use of Spring-Loaded Strap At the installers discretion, the installer may choose in place of the above listed modification to use an Airbus Helicopters “spring-loaded” style strap, Kit # 350A27-0350-0071. See Airbus Helicopters IPC section 67.10.20 for a detailed parts list of the kit. 4.180 In addition to section 4.170 above, Airbus Helicopters Service Bulletin SB 67-00-37 (SB) requires inspecting the gap between the strap and the hooking lock to the same specification. This STC requires compliance with the SB. However, this STC allows for the substitution of the Eagle Copters Hooking Lock in place of the part number listed in the SB at the installer’s discretion. For p/n 350A27-3155-22 use G12733. For p/n 350A27-3155-21 or 350A08-236320 use G12957. 4.190 Prepare the aircraft for return to service. GA107-6 Rev Q Page 10 of 18 5.00 FUNCTION TEST PROCEDURE 5.10 Test all electrical systems and equipment on the aircraft, not just what is listed in this section. Refer to the aircraft flight manual and its supplements for operational information, as well as the documents used for installation. 5.20 The function test must establish that an electrical device or system functions correctly. Functions "correctly" means more than just checking that the device operates. You must also determine that a device only operates when it should. (For example, a device that is normally powered through a switch should be checked to determine that the device is not also getting power from another source, as a result of wiring errors. Make sure that this device is actually powered off when the switch is in the off position.) 5.30 As you perform the Function Test, correct each problem right away. (Do not test everything first and then fix problems all at once, as you may cause damage by proceeding with the testing after a problem is discovered.) Once a test is completed satisfactorily, initial in the space provided for that test and proceed to the next test. 5.40 This test is being performed after a major rewiring of the electrical system for the entire aircraft. You should anticipate all of the possible failure modes in order to perform this test adequately. For example, some of the failure modes possible are obvious, such as a defective switch, circuit breaker, diode, connector, or a simple wiring error. Some of the less obvious failure modes are: 5.41 a terminal is crimped improperly, resulting in an intermittent connection 5.42 a diode is in the circuit backwards 5.43 a connector pin is not correctly seated, resulting in an open or intermittent connection 5.44 a connector pin is bent, resulting in an open, or intermittent connection 5.45 a connector pin is bent, resulting in a short to an adjacent pin 5.46 metal shavings are inside a connector, resulting in intermittent short circuits 5.47 a wiring error connects two circuits together, resulting in confusing behavior 5.48 a wiring error connects some of the wires to the wrong terminals of a switch 5.49 a wiring error connects the wire to the wrong pin of a connector 5.410 a wire is sized incorrectly for the circuit breaker rating 5.50 There are more failure modes than can be listed here. Powering up the aircraft or a circuit can result in the damage to very expensive components. The best defense against mistakes and damage is to double check each step of the installation as each step is made. Later, have someone else re-check each step of the installation. 5.60 All switches should be in the off position and circuit breakers should be in the tripped position when the aircraft battery is connected. Then, only turn on switches and circuit breakers as called for in the Function Test. GA107-6 Rev Q Page 11 of 18 5.70 Function Test Procedure 1 (used for most devices) 5.71 Check that the device is truly powered off. 5.72 Close the breaker for that device by pressing in the plunger. 5.73 Check that the device is powered on if the breaker powers the device directly, or that the device is still powered off if the power needs to pass through a switch. 5.74 Turn on the switch for the device and check for proper operation. 5.75 Turn off the switch and pull the circuit breaker plunger to the tripped position at the completion of the test. 5.80 Once a test for a device has been completed satisfactorily, you may operate that device as needed to perform the tests that follow. 5.90 Function Test abbreviations for actions to take: 5.91 Check SW: Make sure that the device only operates with the correct switch in the on position. Follow Function Test Procedure 1. 5.92 Check CB: Make sure that the correct circuit breaker provides power to the correct device only. Follow Function Test Procedure 1. 5.100 The Function Test is normally performed in the sequence listed. It is the installer's responsibility to establish the test parameters and sequence for the particular aircraft. 5.110 The Function Test listed here is a minimum test. The installer must modify the test as required to suit the particular aircraft and the equipment installed. 5.120 As you perform the function test, review the circuitry being tested using both the G12132 documents and the Airbus Helicopters Wiring Diagram Manual. Make sure that you are testing everything that could be faulty, not just what is listed in this test procedure. 5.130 Some of the function tests will be performed with the engine running. Prior to starting the engine, the aircraft should be made ready for engine starting and running operations. Follow the procedures in the aircraft flight manual. For example, the pilot seat and pilot tailrotor control pedals should be installed, tools, materials, and debris should be safely cleared from the aircraft. All precautions must be taken to insure safe running of the engine. GA107-6 Rev Q Page 12 of 18 FUNCTION TEST PROCEDURE Use the column that matches the aircraft model to perform the correct functional test Note: *B2 refers to B2 models Post–Mod 350A07-3273 Circuit Procedure BAT-EXT Power Function Test Procedure 1. Aircraft power is on only when this switch is on. After satisfactorily completing the testing of this switch, leave this switch on for the following tests. Function Test Procedure 1. With BAT-EXT PWR switch on, turning MASTER CUTOFF on shuts off power to everything except rotor tach, pilot’s overhead floodlights, and items wired directly to battery. (depending on model also check for power to other engine monitoring instruments) Turn this switch off after its test is completed satisfactorily. Function Test Procedure 1 (Warn / Fire Test switch in forward position). Warning panel lights should illuminate. Function Test Procedure 1 (Warn / Fire Test switch in aft position). ENG FIRE panel light should illuminate. Function Test Procedure 1 (Warn / Fire Test switch in aft position). ENG FIRE panel light should illuminate. Gong tone will sound. Function Test Procedure 1 MASTER CUTOFF Warn Light Test Fire Test Fire Test Fuel Pump Fuel Pump 2 T-4 (EGT) Instrument Lights, Switches 1 and 2 Position Lights Anti-Col Light Taxi Light Landing Light Pitot Heat Hydraulic Checks. Model B, BA,B1, B2, C, D, D1 Initials Function Test Procedure 1. Also observe that FUEL.P warning light illuminates if both pumps are not pumping. Function Test Procedure 1. Not applicable for non-powered T-4 indicators. Function Test Procedure 1 for each switch. When both are on, each dimmer pot works separately. When one switch is off, the other dimmer circuit controls the brightness for both dimmer lighting groups. Function Test Procedure 1. Function Test Procedure 1. Optionally, there may be additional strobe lights controlled by this switch. If so, then all strobe lights should illuminate when this switch is in the position labeled ALL, and only the designated strobe should illuminate when in the opposite position. If this is not a center-off type of switch, then only the tail strobe light will be controlled by this switch. Function Test Procedure 1. First, confirm that the landing light relay wiring and circuitry has been changed from Airbus Helicopters’s standard to the configuration shown on G12132-4. After confirming that the wiring matches G12132-4, proceed with Function Test Procedure 1. Function Test Procedure 1. Pitot tube becomes hot only when switch is on. Perform Function Test in accordance with Maintenance Manual Instructions. GA107-6 Rev Q Page 13 of 18 Model *B2 B3 Initials Circuit Procedure Avionics Master Function Test Procedure 1. Oil Cooling Fan Electric Clock Open switch at 30E; Fan OFF. Jumper terminals at 30E; Fan On Function Test Procedure 1. Check that fuel quantity reading follows tank quantity Function Test Procedure 1. Compare reading with the reading of a calibrated voltmeter. Function Test Procedure 1. Meter powered only when MGB oil pressure switch is open (from low oil pressure). Function Test Procedure 1. Meter powered only when MGB oil pressure switch is open (from operating oil pressure) and collective switch is closed (Collective UP), or if landing gear crosstube deflection switch is used then switch indicates that helicopter is off the ground. See circuit for details. Function Test Procedure 1. Open and close circuit breaker to observe that power flag retracts. Check that internal lights function if installed. Function Test Procedure 1. Open and close circuit breaker to observe that power flag retracts. Check that internal lights function if installed. Function Test Procedure 1. Open and close circuit breaker to observe that power flag retracts. Check that internal lights function if installed. Function Test Procedure 1. Cargo Hook Function Test Procedure 1. Ext. Load System Function Test Procedure 1. Sand Filter Function Test Procedure 1. Windshield Wiper (1 & 2) Power Outlet Function Test Procedure 1. Cabin Lights (front & rear) Hoist Function Test Procedure 1. AC Inverter Function Test Procedure 1. Voltage Converter Bleed Valve Function Test Procedure 1. Confirm that output voltage is suitable for specific installation. Function Test Procedure 1. Spraying Option Function Test Procedure 1. Fuel Flow Indicator Function Test Procedure 1. VEMD Function Test Procedure 1. ASU or VHIU Function Test Procedure 1. Fuel Quantity Volt Meter Hour Meter, Run Time Hour Meter, Maintenance Time Attitude Gyro Directional Gyro (D.G.) Turn & Bank Gyro Initials Function Test Procedure 1. Function Test Procedure 1. GA107-6 Rev Q Page 14 of 18 Initials Circuit Procedure GOV (FADEC) (B3 only) All Optional Circuits Function Test Procedure 1. Crank Function Test Procedure 1. Switch on runs engine starter motor without igniters firing. Function Test Procedure 1. Crank engine and observe normal operation. Function Test Procedure 1. After performing all tests and procedures necessary for a safe engine start, start the engine in accordance with instructions in the flight manual and check for correct operation of all related systems and circuits. Then perform the tests that follow with the engine running at idle. Function Test Procedure 1. Switch fuel pump(s) on and off and observe normal indication on gauge. Function Test Procedure 1. With engine running, check for normal indication on gauge. Function Test Procedure 1. With engine running, check for normal indication on gauge. Function Test Procedure 1. The center-off position should result in the aircraft being powered from the battery only. The up position should put the generator on the bus, with an increase in bus voltage indicated. (Adjust generator voltage if required.) For aircraft with the Generator Reset function installed, press the test switch in the master electrical box to simulate an over-voltage event. The generator should now be off line, even though the generator switch is still in the on position. Move the generator switch to the down RESET position and then to the ON position. The generator should come back on line. Function Test Procedure 1. Does Arm / Disarm sequence properly with Warning Light? Function Test in Accordance with Flight Manual instructions. Function Test Procedure 1. Observe normal operation Ng Indicator Engine Start Fuel Pressure (Quad Gauge) Oil Pressure (Quad Gauge) Oil Temp (Quad Gauge) Generator Switch Warning Horn Torque Indicator Rotor Tach Engine Shutdown End of Test Initials Function Test Procedure 1 and/or other tests as appropriate. Function Test Procedure 1. Observe normal operation with Master Cutoff switch off (normal) and on (electrical shed). Perform normal engine shutdown procedure defined in the flight manual. Check for proper operation of all systems and circuits. Turn off all switches. Function test completed satisfactorily by: ___ ____________ ___________ Name, Title, A&P No. Date GA107-6 Rev Q Page 15 of 18 Initials REMARKS (Customization, variations, model specific variations, etc) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 REMARKS SECTION COMPLETED BY: ___ ____________ ___________ Name, Title, A&P No. Date GA107-6 Rev Q Page 16 of 18 6.00 RETURN TO SERVICE 6.10 After satisfactory completion of this installation and testing, put the aircraft back into airworthy condition. First perform one last inspection of the aircraft electrical system, consisting of the following: 6.11 Check that connectors are properly mated 6.12 Check that wires are not chafing 6.13 Check that all screws are tight 6.14 Check that all nuts are tight 6.15 Check for signs of overheating on all electrical components 6.16 Check for foreign objects that could cause interference 6.17 Check for deterioration of labels 6.18 Check for failed light bulbs or LEDs in back-lighted panels 6.19 Check for loose toggles for toggle switches 6.110 Check for faulty components 6.20 Update the aircraft weight and balance records. 6.30 Update the aircraft equipment list. 6.40 Install the GA107-2-P132 FLIGHT MANUAL SUPPLEMENT in the appropriate place in the aircraft flight manual. Be sure to fill in the blanks on the cover page to show the aircraft registration number and serial number. 6.50 Prepare an FAA form 337 documenting this installation. 6.60 After testing and corrections, the "Notes" working copy of the installation document set should represent the final configuration. With the installation and testing complete, neatly mark the appropriate notes, corrections, and customizations onto the original document set, which becomes the “As Built” document set. Add additional pages if necessary. Write the aircraft serial number and model number on each page of the documents. Make copies of the “As Built” document set (G12132 plus any additional pages) and attach a copy of the FAA form 337 for this installation. Distribute the form 337 with the attached documents, as specified below:  One set must be placed into the aircraft records for future maintenance on the aircraft electrical system and console.  One set should be attached to the work order under which the installation was performed, if a work order was used.  One set must be sent to Eagle Copters for record keeping purposes. 6.70 Make an aircraft log book entry to document this installation. 6.80 Distribute the FAA form 337 in accordance with FAA requirements. 6.90 Perform any other functions needed to properly return an aircraft to service. 6.100 When properly installed, there is no further action required for continued airworthiness. The aircraft manufacturer's normal maintenance actions will cover all maintenance required for this electrical system. 6.110 When performing maintenance or troubleshooting on the aircraft electrical system, the “As Built” document set must be referred to along with the Airbus Helicopters Wiring Diagram Manual. GA107-6 Rev Q Page 17 of 18 L OG O F R EVISIONS REV LEVEL -A B DATE OF REVISION 6/21/02 9/3/03 3/29/04 C D E 8/12/04 6/14/05 3/08/06 F 8/30/07 G 4/30/08 H 7/22/08 J K 9/25/08 3/23/09 L 3/14/11 M 1/04/13 N 11/25/13 P 6/24/14 Q 12/5/14 DESCRIPTION OF CHANGE APPROVAL Initial Release, replaces GA107-3E-ECO-1061B Added options for cyclic travel limitations Removed options for cyclic travel limitations and added sections 4.52 & 4.53 Added section 4.54 for Bendix Grip installations Revised section 4.50 & 5.180 Added section 5.190 for replacement of Collective lock button with Fitting G12733 Added section 4.45 and 4.60 for aircraft post mod 350A073273 using the direct battery bus, B3 emergency bus post mod 350A07-3087, and mod 350A07-3257 Updated section 5.180 and 5.190 for collective strap adjustment and fitting installation requirements Updated section 5.180 collective fitting gap requirement to .15 inches (4mm) for EASA certification. Updated section 1.320 switch color coding specification. Corrected part number for cover plate to G12899 in sections 4.45 & 4.62; updated the functional test procedure Restructured section 4.00 to separate instructions for pre-mod and post-mod 350A07-3273; qualified paragraphs 5.30 and 5.40 as being for pre-mod 350A07-3273 only Added Step 5.49 for installing the P132 Console in place of EC MOD 350A07-4280 Multi-Bloc Console. Revised Section 5.180 to add mounting hardware for the installation of Collective Strap Mounting Block G12316. Revised Section 5.190 for SB 67-00-37; Replaced OEM name of “Eurocopter” with “Airbus Helicopters” throughout the document. Removed references to GA107-3 and removed assembly instructions (Section 2). Revised all section numbering. Updated format and company name to Eagle Copters CLB CLB CLB GA107-6 Rev Q Page 18 of 18 CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB SERVICE BULLETIN GA107-7 June 14, 2005 1.1 Subject: Cyclic Stick Interference with P132 Console 1.2 Effectivity: Eurocopter AS350 Series helicopters with Geneva Aviation P132 Console installed 1.3 Description: Helicopters equipped with the Geneva Aviation P132 Console installed under STC SH4747NM, may encounter a problem of restricted cyclic stick travel. The P132 console is both taller and wider than the Eurocopter original console, and may limit cyclic travel under certain conditions. The pilot’s left leg may interfere with cyclic movement due to crowding by the console. With dual controls installed, the right leg of the person in the left seat might also cause reduced cyclic travel. The P132 Console will limit cyclic travel toward the console if the Pilot’s or Copilot’s leg is wedged between the console and the cyclic. This may not be noticed except during flights requiring cyclic movements near lateral limits (such as with a substantial lateral C.G. loading, high crosswinds, or slope landings). To address the potential of flight control restriction, this Service Bulletin provides for replacing the factory pilot and copilot cyclic sticks with Geneva RH Cyclic Stick G12316-26 and Geneva LH Cyclic Stick G12324-26. 1.4 Compliance: By the operator upon receipt of this service bulletin, comply with section 2.0 within 60 days. 1.5 Approval: FAA Seattle Aircraft Certification Office approved this service bulletin. 1.6 Manpower: 1 mechanic, 8 hours labor. GA107-7 Rev -- 6/14/2005 Page 1 of 5 1.7 Material: Geneva RH cyclic stick G12316-26 Geneva LH cyclic stick G12324-26 Optionally, for “Bendix” cyclic grip installations use: Geneva RH cyclic stick G12425-26 Geneva LH cyclic stick G12426-26 1.8 Weight and Balance: No Change 2.0 Instructions: 2.1 Replacement of the factory pilot cyclic stick and copilot cyclic stick is required. Replacement of the cyclic sticks must be done in accordance with Eurocopter maintenance documents and these instructions. Replacement of cyclic sticks: Refer to Eurocopter maintenance documents for additional removal and installation procedures. Install the Geneva Aviation G12316-26 RH cyclic stick and G12324-26 LH cyclic stick into the flight control from which the original was removed. If the cyclic tube cannot be easily inserted, match fitting of the parts is required to achieve a slip fit using hand pressure only. The flight control's mating diameter may be out of round and the cyclic stick may be out of round. Gently squeeze the out-ofround parts to eliminate the out-of-roundness. The cyclic tube may also be of greater diameter than the hole into which it is to slide. In this case, lightly sand the cyclic stick's area of interference using 400 grit paper and polish to match the finish of the unsanded areas. Blend sanded area into the unsanded surface to provide a smooth transition without edges. Sand the minimum amount required to achieve a snug slip fit. The fastener holes in either end of the stick may require match fitting to the mating parts to achieve a slip fit for the fastener. GA107-7 Rev -- 6/14/2005 Page 2 of 5 2.2 Modification of Pistol Grip. If the base of the grip has a flange that sticks out to help support the hand, remove 3/8” of this flange as shown in Figure 1 below. Sand the cut areas smooth. This step will be easier to perform if it is done after the grip is removed from the original stick during the stick replacement step. Both the Pilot and Copilot grips are to be modified. .38 Before Trimming After Trimming FIGURE 1 GA107-7 Rev -- 6/14/2005 Page 3 of 5 2.3 Copilot cyclic stand (receptacle) modification. This modification prevents the factory original copilot cyclic stick from being installed inadvertently into the aircraft. Only a Geneva Aviation LH cyclic stick G12324-26 will be able to be installed once this modification is completed. Remove the copilot cyclic stick stand (ref. p/n 350A27159403) from the aircraft. Install blind rivet as shown in Figure 2. Reinstall cyclic stand into aircraft and install Geneva Aviation LH cyclic stick G12324-26 into stand as detailed in section 2.1. INSTALL BLIND PULL RIVET MS20600AD-4-1 OR CR3213-4-1 1.06 FIGURE 2 GA107-7 Rev -- 6/14/2005 Page 4 of 5 2.4 For installations using a “Bendix” Cyclic Grip (the cyclic stick has a right angle bend at the top), use p/n G12425-26 in place of G12316-26 and use G1242626 in place of G12324-26. 2.5 Once the modifications have been completed, add Rotorcraft Flight Manual Supplement GA107-2-P132 Rev A dated 8/12/2004 to the flight manual and make a log book entry of compliance with this service bulletin. LOG OF REVISIONS REVISION LEVEL -- DATE OF REVISION 6/14/05 DESCRIPTION OF CHANGE Initial Release, replaces SB2004.01 dated 8/12/04 GA107-7 Rev -- 6/14/2005 APPROVAL CLB Page 5 of 5 G10251-1 Revision T, 5/19/2015 P132 Console Standard Parts List ITEM QTY UNITS --1 2 3 4 5 6 7 8 9 10 11 12 1 1 1 1 1 1 1 1 1 1 1 1 1 3 ea ea ea ea ea ea ea ea ea ea ea ea ea ea G10254-1 G10254-2 G10257-1 G10257-2 G10253-1 G10253-2 G10253-3 G10253-4 G10253-5 G10253-6 G10253-7 G10253-8 G10252 G10255 13 4 ea 6C25PFHS 14 15 52 2 ea ea 6C25PPMSB 6C37SHCA 16 17 17 17 17 17 17 17 17 17 17 17 17 17 17 18 19 20 20 20 20 30 1 1 1 1 in ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea 39-311 G10256-1 G10256-2 G10256-3 G10256-4 G10256-5 G10256-6 G10256-7 G10256-8 G10256-9 G10256-11 G10256-12 G10256-13 G10256-14 G10256-18 6C125HF4U6 G12136 MS24523-21 MS24523-23 MS24523-26 MS24527-27 1 1 1 1 1 1 1 1 1 1 32 1 0 5 1 0 PART NUMBER DESCRIPTION CONSOLE SIDE WALL, RH CONSOLE SIDE WALL, LH CONSOLE SIDE WALL, RH ASSEMBLY CONSOLE SIDE WALL, LH ASSEMBLY RAIL - SWITCH RAIL - SWITCH RAIL - CIRCUIT BREAKER RAIL - CIRCUIT BREAKER RAIL - CIRCUIT BREAKER RAIL - CIRCUIT BREAKER RAIL - CIRCUIT BREAKER RAIL - CIRCUIT BREAKER AFT WALL SWITCH BRACKET SCREW, 6-32 X 1/4" 100 deg. Flat HEAD (ALTERNATE: MS24693S24) SCREW, 6-32 X 1/4" PAN HEAD Phillips, BLK (ALTERNATE: 35206-226) SCREW, 6-32 X 3/8" CAP HEAD, BLK 1/4" GROMMET, Linear Edge (ALTERNATE: SL2-0025-ER0201) FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE FORMEX INSULATION, SELF-ADHESIVE STAND OFF MOUNT, COLLECTIVE HOLDDOWN SWITCH - SPDT, ON-OFF-ON SWITCH - SPDT SWITCH - SPDT, M-ON SWITCH - SPDT, CENTER OFF, M-OFF-M G10251-1 Rev T Page 1 of 5 ITEM QTY UNITS 20 20 20 20 20 20 20 20 1 8 0 0 1 1 0 2 ea ea ea ea ea ea ea ea 20 21 1 0 ea ea 21 0 ea 21 0 ea 21 0 ea 21 25 ea 21 0 ea 21 0 ea 21 12 ea 21 12 ea 21 7 ea 21 5 ea 21 22 23 24 25 26 28 29 1 4 4 5 2 6 1 4 ea ea ea ea ea ea ea ea 30 31 32 34 35 36 37 6 22 4 1 6 22 1 ea ea ea ea ea ea ea PART NUMBER DESCRIPTION MS24524-21 MS24524-23 MS24524-26 MS24524-27 MS24524-31 MS24658-23D MS24659-21A MS24659-23D SWITCH - DPDT, CENTER OFF, ON-OFF-ON SWITCH - DPDT, ON-ON SWITCH - DPDT, M-ON SWITCH - DPDT, CENTER OFF, M-OFF-M SWITCH - DPDT, ON-OFF-M SWITCH - SPDT, LOCKING TOGGLE, ON-ON SWITCH - DPDT, LOCKING TOGGLE, ON-OFF-ON SWITCH - DPDT, LOCKING TOGGLE, ON-ON SWITCH - DPDT, M-ON-M MS27407-3 (ALTERNATE: SL2-0025-ER0201) 7274-2-1/2 CIRCUIT BREAKER, 0.5 AMP CIRCUIT BREAKER, 1 AMP 7277-2-1 (ALTERNATES: 4200-002-1, MS26574-1) CIRCUIT BREAKER, 1.5 AMP 7277-2-1-1/2 (ALTERNATES: 4200-002-105, MS26574-1.5) CIRCUIT BREAKER, 2 AMP 7277-2-2 (ALTERNATES: 4200-002-20, MS26574-2) CIRCUIT BREAKER, 2.5 AMP 7277-2-2-1/2 (ALTERNATES: 4200-002-205, MS26574-2.5) CIRCUIT BREAKER, 3 AMP 7277-2-3 (ALTERNATES: 4200-002-3, MS26574-3) CIRCUIT BREAKER, 4 AMP 7277-2-4 (ALTERNATE S: 4200-002-4, MS26574-4) CIRCUIT BREAKER, 5 AMP 7277-2-5 (ALTERNATE S: 4200-002-5, MS26574-5) CIRCUIT BREAKER, 7.5 AMP 7277-2-7-1/2 (ALTERNATE S: 4200-002-705, MS26574-7.5) CIRCUIT BREAKER, 10 AMP 7277-2-10 (ALTERNATE S: 4200-002-10, MS26574-10) CIRCUIT BREAKER, 15 AMP 7277-2-15 (ALTERNATE S: 4200-002-15, MS26574-15) CIRCUIT BREAKER, 20 AMP 7277-2-20 (ALTERNATES: 4200-002-20, MS26574-20) 6C31SHCA SCREW, 6-32 X 5/16" CAP HEAD, BLK MS35206-217 SCREW, 4-40 X 1/2" PAN HEAD PHILLIPS MS21044N04 4-40 NYLOCK NUT 4N75FENZZ WASHER, 1/8" ID , 3/4" OD, NOMINAL DIMENSIONS FP-301 1/4" BL HEATSHRINK, 1/4" X 1-1/4", BLK (ALTERNATE: FIT-221) G10283-2 PLACARD, TERMINAL BOARD 6C56PPMS SCREW 6-32 X 9/16" (ALTERNATE: MS35206-231) DIODE, 3A, 50VDC MIN, (ALTERNATES:MR750 - MR760, 6A05-T 6A1-T, 6A2-T, 6A4-T, 6A6-T, 6A10-T) MS35338-136 #6 LOCK WASHER (ALTERNATE: 6NSLWS) FTH-7A-RT-UVB-C TIE DOWN G10283-10 I.D. LABEL (on inside) 2643 1/2" HOLE PLUG (ALTERNATE: 8603) 2633 7/16" HOLE PLUG G10270-1 SWITCH OVERLAY PANEL TOP G10251-1 Rev T Page 2 of 5 ITEM QTY UNITS 38 2 ea G10270-2 PART NUMBER 39 40 41 42 43 44 45 20 2 2 2 1 1 8 ea ea ea ea ea ea ea 46 1 ea G12139 G12135-12 G12135-10 G12135-9 MS27212-2-6 MS18029-2S-6 MS35489-20 TB100-14B or 1-1546306-4 47 48 49 50 1 A/R A/R 6 ea ea ea ea G10283-3 MS21042-3 NAS1149F0332P MS35207-262 51 1 ea G12132 53 54 54 55 55 56 56 58 58 59 59 60 61 62 63 64 65 66 67 68 69 70 70 70 70 70 70 70 1 1 1 1 1 1 1 1 1 1 1 A/R A/R A/R A/R A/R A/R A/R A/R A/R A/R 1 1 1 1 1 1 1 ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea ea G10283-1 MS3471L22-55P MS3476L22-55S MS3471L24-31P MS3476L24-31S MS3471L24-31S MS3476L24-31P M85049/51-1-22N M85049/52-1-22N M85049/51-1-24N M85049/52-1-24N MS35338-43 M22759/16-20-9 M22759/16-16-9 33460 36160 36152 320559 326882 320562 35149 G12132-11-01 G12132-11-02 G12132-11-03 G12132-11-04 G12132-11-13 G12132-11-14 G12132-11-15 DESCRIPTION SWITCH OVERLAY PANEL RIGHT & LEFT SPACER (ALTERNATE FOR SIDE RAILS ONLY NAS1149F0863P) BUS BAR, TOP ROW BUS BAR, MIDDLE ROW BUS BAR, BOTTOM ROW TERMINAL BLOCK, 6 ea 10-32 STUDS COVER FOR MS27212-6 TERMINAL BLOCK GROMMET TERMINAL STRIP, 14 POSITION, .375" SPACING (Cooper-Bussman or Tyco) LABEL FOR TERMINAL STRIP – TEXT VARIES BASED ON CABLE HARNESS USED (ITEM 51) LOCK NUT 10-32 WASHER, FLAT, #10 SCREW, 10-32 X 7/16" PAN HEAD Phillips CABLE HARNESS ASSY, See G12132 for A/C model and MOD level specific configuration details. PLACARD, MAXIMUM AVIONICS WEIGHT CONNECTOR, WITH 55 PINS CONNECTOR, WITH 55 SOCKETS CONNECTOR, WITH 31 PINS CONNECTOR, WITH 31 SOCKETS CONNECTOR, WITH 31 SOCKETS CONNECTOR, WITH 31 PINS BACKSHELL BACKSHELL BACKSHELL BACKSHELL #10 LOCK WASHER WIRE 20ga WIRE 16ga LUG, #10 RING, 8 GA WIRE BLUE CRIMP TERMINAL, 14-16ga wire to #10 screw RED CRIMP TERMINAL, 16-22ga wire to #6 screw RED CRIMP TERMINAL, 16-22ga wire butt splice BLUE CRIMP TERMINAL, 14-16ga wire to #6 screw BLUE CRIMP TERMINAL, 14-16ga wire butt splice YELLOW CRIMP TERMINAL, 10-12ga wire to #6 screw BUS WIRE ASSEMBLY BUS WIRE ASSEMBLY BUS WIRE ASSEMBLY BUS WIRE ASSEMBLY BUS WIRE ASSEMBLY (OPTIONAL) BUS WIRE ASSEMBLY (OPTIONAL) BUS WIRE ASSEMBLY , B3 ONLY G10251-1 Rev T Page 3 of 5 ITEM QTY UNITS 71 75 76 77 A/R 4 4 1 ea ea ea ea 31805 MS24693S270 MS21042L3 G10283-4 PART NUMBER 78 1 ea G10283-5 79 1 ea G10283-6 80 1 ea G10283-7 81 1 ea G10283-8 82 85 86 87 88 89 90 91 94 94 94 95 95 96 1 3 3 6 1 1 1 3 2 1 1 2 2 24 ea ea ea ft ea ea ea ea ea ea ea ea ea ea G10283-9 18RA-251T 18RA-2577 M22759/16-22-9 G12132-24 G12298 G12301 875 G12307 G12307-LH-SCM G12307-RH-SCM G12948-23 G12948-27 MS35206-228 98 99 100 101 102 103 103 103 103 103 36 2 1 A/R 1 A/R A/R A/R A/R A/R ea ea ea ea ea ea ea ea ea ea 4C25PPMSB 0304 G13117 MS35207-262 G13129 TY23M TY24M TY25M PLT2M-M PLT31-M DESCRIPTION YELLOW CRIMP TERMINAL, 10-12ga wire to #10 screw SCREW 10-32 X 3/8 FLAT HEAD NUT, LOCKING 10-32 LABEL, CIRCUIT BREAKER ASSIGNMENT - TOP RIGHT LABEL, CIRCUIT BREAKER ASSIGNMENT - MIDDLE RIGHT LABEL, CIRCUIT BREAKER ASSIGNMENT - BOTTOM RIGHT LABEL, CIRCUIT BREAKER ASSIGNMENT - TOP LEFT LABEL, CIRCUIT BREAKER ASSIGNMENT - MIDDLE LEFT LABEL, CIRCUIT BREAKER ASSIGNMENT - BOTTOM LEFT TAB TERMINAL, .250 F.I. FEMALE TERMINAL, .250 F.I. WIRE 22ga FOR OVERLAY PIGTAILS IN CONSOLE DIMMER POT ASSEMBLY SHIELD DIMMER CONTROL PCB 1/8” NYLON SPACER (KEYSTONE) DZUS RAIL SHIM (OPTIONAL) DZUS RAIL SHIM (OPTIONAL - ALTERNATE) DZUS RAIL SHIM (OPTIONAL - ALTERNATE) DZUS RAIL (OPTIONAL - ALTERNATE) DZUS RAIL (OPTIONAL) #6-32 x .375 PAN HEAD SCREW (OPTIONAL) SCREW, 4-40 X 1/4" PAN HEAD Phillips, BLK (ALTERNATE: 35206-213) ARROW CLIP (HEYCO) WIRE SHIELD (FORMEX) SCREW, PANHEAD, #10-32 X 7/16 WIRE SHIELD (FORMEX) (optional in place of G13117) CABLE TIE, .091 x 3.62 CABLE TIE, .140 x 5.50 CABLE TIE, .184 x 7.31 CABLE TIE, .098 x 8.00 CABLE TIE, .145 x 11.40 Note: The quantities provided and used will vary from installation to installation. G10251-1 Rev T Page 4 of 5 LOG OF REVISIONS REVISION LEVEL G H DATE OF REVISION 8/30/07 3/23/09 J 5/13/10 K 7/28/11 L M N 1/05/2013 5/03/2013 6/27/2013 P 11/25/2013 Q R 11/25/2014 12/05/2014 S 3/6/2015 T 5/19/2015 PAGES DESCRIPTION OF CHANGE All Pages Reformatted and retabulated All Pages Added MS27407-3 switch (item 20); retabulated All Pages Replaced MR760 (Item 30) with 6A05-T and added alternates; retabulated All Pages Added G12132-073368 wiring harness (Item 51) and alternates for items 21, 94 and 95; updated P/N and/or description for items 20, 21, 32, 46, 47, 51, 91; retabulated 2 Item # 29 was 6C50PPMS 4 Items # 99 & 100 added 2&3 Item # 31 Qty was 14; Item # 46 added second vendor part number 3&4 Items 48, 49 & 60 Qty was 12; Added Items 64, 65, 69 , 71 & 101 4 Item # 102 G13129 Added 4 Updated part numbers for items #85 and #86 ALL Item 16 added alt p/n Item 20 was “locking toggle” 4 Added Item #103 Cable Ties; Revised part numbers for #85 & #86; Added G10256-11 thru -14 & -18; Added G10254-1 & -2 G10251-1 Rev T APPROVAL CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB CLB Page 5 of 5 6 4 5 2 3 1 REVISIONS REV APPROVED/DATE DESCRIPTION REDRAWN; ADDED SHEET 2; J3 WAS P3; REVISED FN1 TO ALLOW TERMINAL STRIPS TO BE MOUNTED IN BOTH LOCATIONS; REMOVED OBSOLETE PLACARD FROM RH SIDE OF CONSOLE 8/30/07 CLB K ITEM 51 WAS 70 6/28/10 CLB L ADDED VIEW C-C ; ADDED WIRE SHIELD (100) & CLIPS (99) 5/3/13 CLB M ITEM 102 ADDED TO VIEW C-C 11/25/14 J F F CLB 1 2 51 E E 34 I.D.LABEL MOUNTED ON INSIDE WALL 3 J1 10.45 54 AVIONICS BAY D W F 58 J2 55 J3 59 56 LEFT SIDE ISO VIEW 59 (OPTIONAL) D D 6.35 TOP VIEW VIEW A-A 9.01 SEE VIEW B-B FOR DEPTH RESTRICTIONS IN AVIONICS BAY 12.61 C D W F RIGHT SIDE ISO VIEW A NOTES A C 2.32 .33 16.47 C 12.89 CENTER SWITCH RAIL OVERLAY CENTER SWITCH RAIL 2 SEE DRAWING SERIES G12132 FOR DETAILS ON THE CABLE HARNESS ASSY 3 DZUS RAIL OPTION: ITEM (#) 94 MOUNTED TO SIDEWALLS USING #96; #95 MOUNTED TO #94 USING #96. 4 PLACARD #53: MAXIMUM INSTALLED RADIO WEIGHT 30 LBS WIRE BUNDLE DIODE BLOCK RAIL MAXIUM INSTALLED RADIO WEIGHT 30 LBS 6.30 B THE INSTALLER MAY, AT THEIR DESCRETION, MOUNT THE TERMINAL STRIP(S) IN EITHER THE UPPER AND/OR LOWER LOCATIONS PROVIDED. .56 1.21 2.97 1 9.25 BUS TERMINAL BLOCK RAIL 4 AFT VIEW BUS TERMINAL BLOCK RAIL (ALTERNATE LOCATION) 1 P132 AVIONICS SWITCH CONSOLE P/N G10251 WEIGHT: APPROX. 18 LBS, THE WEIGHT WILL VARY DEPENDING ON NUMBER OF SWITCHES, CIRCUIT BREAKERS AND OPTIONS INSTALLED. THE INSTALLER MUST WEIGH THE CONSOLE BEFORE INSTALLATION AND RECORD THE WEIGHT IN THE AIRCRAFT EQUIPMENT LIST. SIDEWALL FWD SEE G10251-1 FOR BOM LIST; SEE G10251-3, -4, -5 & -6 FOR SUB-ASSEMBLY DETAILS. DRAWN A BREAK SHARP EDGES VIEW B-B UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: THIS VIEW SHOWS THE APPROXIMATE DEPTH RESTRICTIONS FOR RADIOS INSTALLED INTO THE AVIONICS BAY FRACTIONS 1/8" DECIMAL .X .050 .XX .030 .XXX .010 CLB DATE CHECKED DATE DESIGNED DATE ANGLES 2 APPROVED 5 4 3 2 A 8/30/07 Title CLB DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 6 B SECOND CENTER SWITCH RAIL (SCM) OPTION: THE INSTALLER MAY, AT THE INSTALLERS DESCRETION, INSTALL A SECOND CENTER SWITCH RAIL (SCM) AND OVERLAY. INSTALL #12 & #37 NEXT TO THE FIRST CENTER SWITCH RAIL USING SCREWS #14 & #15. DRILL MOUNTING HOLES IN SIDE WALL AS NEEDED TO MOUNT THE SCM. WIRING OF THE SCM IS COVERED IN G12132-1. RIGHT SIDE VIEW 12.94 C P132 CONSOLE ASSEMBLY OVERVIEW G10251-2 GA107 E 1 Drawing Number Pro No: SIZE REV Scale: 1:2 Sheet M 1 of 2 6 5 4 2 3 1 REVISIONS REV APPROVED/DATE DESCRIPTION SEE SHEET 1 FOR REVISION INFORMATION G10251-5-9 CENTER SWITCH RAIL ASSEMBLY F F 4X 14 G10251-5-2 LH SWITCH RAIL ASSEMBLY G10251-4 DIODE BLOCK ASSEMBLY 16 2X 12 5 E 18 32X G10251-5-1 RH SWITCH RAIL ASSEMBLY 6 E 14 32X 14 4X G10251-5-3 UPPER RH CB RAIL ASSEMBLY G10251-5-5 MIDDLE RH CB RAIL ASSEMBLY D G10251-5-4 UPPER LH CB RAIL ASSEMBLY D G10251-5-7 LOWER RH CB RAIL ASSEMBLY G10251-5-6 MIDDLE LH CB RAIL ASSEMBLY C C G10251-5-8 LOWER LH CB RAIL ASSEMBLY G10251-3 CONSOLE SUB-ASSEMBLY 2X 99 B B 100 OR 1 102 5 APPLY LOC-TITE 242 (BLUE) TO THREADS ON SIDEWALL END, 32 PLACES 6 COVER FWD BOTTOM STANDOFF FOR EACH RAIL WITH HEATSHRINK (#26), 8 PLACES DRAWN A BREAK SHARP EDGES VIEW C-C UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: FRACTIONS 1/8" DECIMAL .X .050 .XX .030 .XXX .010 CLB DATE CHECKED DATE DESIGNED DATE ANGLES 2 APPROVED Title CLB DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 6 5 4 3 2 A 8/30/07 P132 CONSOLE ASSEMBLY OVERVIEW Drawing Number Pro No: G10251-2 E GA107 1 SIZE REV Scale: 1:2 Sheet M 2 of 2 6 4 5 2 3 1 REVISIONS REV F APPROVED/DATE DESCRIPTION REDRAWN TO SHOW -3 SUB-ASSEMBLY 8/30/07 CLB F F 11 45 8X E E 8X 14 76 4X D D 32 4X 2 C C 19 75 4X 2 G10251-6 TERMINAL BLOCK ASSEMBLY 1 13 4X B B 1 1 APPLY LOC-TITE 242 (BLUE) TO THREADS 2 TRIM TO CLEAR TERMINAL BLOCK G10251-3 CONSOLE SUB-ASSEMBLY DRAWN A BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: FRACTIONS 1/8" DECIMAL .X .050 .030 .XX .XXX .010 CLB DATE CHECKED DATE DESIGNED DATE ANGLES 2 APPROVED 8/30/07 Title CLB DATE 5 4 3 2 P132 CONSOLE SUB-ASSEMBLY 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 6 A Drawing Number Pro No: G10251-3 E GA107 1 SIZE REV Scale: 1:1 Sheet F 1 of 1 REVISIONS REV X12014 COVER (KEYSTONE) #6-32 SCREW, SUPPLIED WITH BARRIER STRIP 4X 29 DD1 (KEYSTONE) 2 PLACES DESCRIPTION APVR/DATE F REDRAWN AND REFORMATTED 8/30/07 CLB G ITEM 51 WAS 70 6/28/10 CLB H REPLACED SHIMS WITH #31 6/27/13 CLB 31 8X 31 51 WIRE BUNDLE ASSY G12132 46 47 APPLY LOC-TITE #242 (BLUE) TO THREADS OF DIODE SCREWS 30 DIODE, FORM LEADS TO FIT 1 2 3 4 5 7 6 8 9 10 12 11 13 14 DIODE CONNECTIONS ARE DEFINED IN G12132. REFER TO THE PARTICULAR DRAWINGS THAT RELATE TO YOUR AIRCRAFT VERSION, MOD LEVEL, OR INSTALLATION-SPECIFIC CONFIGURATION C A D1 C A D2 C A D3 C A C D4 A D5 VIEW LOOKING AFT DIODE BLOCK SCHEMATIC -- OBSERVE DIODE POLARITY! -- C A D6 A C D7 BREAK SHARP EDGES DESIGNED DATE CLB UNLESS OTHERWISE DRAWN SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: CHECKED FRACTIONS DECIMAL ANGLES .050 .X 2 1/8" APPROVED .XX .030 CLB .XXX .010 8/30/07 DATE DATE Title DATE DIODE BLOCK ASSEMBLY 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. Drawing Number G10251-4 Pro No: GA107 SIZE B REV Scale: 1:1 Sheet -- H of REVISIONS REV SUPPLIED WITH SWITCH 2 39 38 35 APVR/DATE F ADDED OPTIONAL DIMMER INSTALLATION G ADDED SHEETS 2&3 AND CENTER RAIL ASSEMBLY 8/30/07 CLB H ITEM 51 WAS 70; ITEM 24 WAS 92 6/28/10 CLB 4/5/02 CLB SHEET 4 & BUSS WIRE TO BUSS J ADDED RAIL CONNECTION K SHT 2: REPLACED ITEM 22 WITH ITEM 15 L SHT 4: REVISED FASTENER SEQUENCE 1: ADDED ITEM 31; M SHT SHT 3: REVISED G10251-5-8 ITEM #17 22 20 DESCRIPTION 11/25/13 CLB 3/6/15 CLB 4/1/15 CLB 5/19/15 CLB TO G10256-18 INSULATION 1 N 8/20/15 CLB SHT 4: REVISED FASTENER SEQUENCE SUPPLIED WITH SWITCH SUPPLIED WITH ITEM #88 89 3 88 G10256-9 17 INSULATION SUPPLIED WITH ITEM #90 24 31 91 51 G12132 WIRE BUNDLE ASSY 1 FOR UNUSED SWITCH LOCATIONS 2 OPTIONAL SUBSTITUTE: NAS1149F0863P LH & RH SWITCH RAILS ONLY 90 G10251-5-1 RH SWITCH RAIL ASSEMBLY BREAK SHARP EDGES DESIGNED CLB UNLESS OTHERWISE DRAWN SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: CHECKED FRACTIONS DECIMAL ANGLES .050 .X 2 1/8" APPROVED .030 .XX CLB .XXX .010 DATE 8/30/07 DATE DATE Title DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. SWITCH AND CB RAIL ASSEMBLY DETAILS Drawing Number G10251-5 Pro No: GA107 SIZE B REV Scale: none Sheet N 1 of 4 REVISIONS REV DESCRIPTION APVR/DATE SEE SHEET 1 FOR REVISION HISTORY 38 15 22 1 35 35 SUPPLIED WITH SWITCH 39 1 37 SUPPLIED WITH SWITCH 2 20 12 SUPPLIED WITH SWITCH 39 4 G10256-5 INSULATION 17 20 G10251-5-9 CENTER SWITCH RAIL ASSEMBLY G10251-5-2 LH SWITCH RAIL ASSEMBLY BREAK SHARP EDGES 1 2 FOR UNUSED SWITCH LOCATIONS OPTIONAL SUBSTITUTE: NAS1149F0863P LH & RH SWITCH RAILS ONLY DESIGNED CLB UNLESS OTHERWISE DRAWN SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: CHECKED FRACTIONS DECIMAL ANGLES .050 .X 2 1/8" APPROVED .030 .XX CLB .XXX .010 DATE 8/30/07 DATE DATE Title DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. SWITCH AND CB RAIL ASSEMBLY DETAILS Drawing Number G10251-5 Pro No:GA107 SIZE B REV Scale: none Sheet N 2 of 4 REVISIONS REV DESCRIPTION APVR/DATE SEE SHEET 1 FOR REVISION HISTORY 5 80 98 6 G10251-5-3 UPPER RH CB RAIL ASSY G10256-6 INSULATION 17 G10251-5-4 UPPER LH CB RAIL ASSY 77 G10256-6 17 INSULATION 7 81 SUPPLIED WITH ITEM #21 8 40 40 G10251-5-5 MIDDLE RH CB RAIL ASSY 21 G10256-7 INSULATION 17 17 G10256-7 INSULATION G10251-5-6 MIDDLE LH CB RAIL ASSY 78 41 9 82 41 10 3 79 G10256-8 17 INSULATION 36 17 42 G10256-18 INSULATION G10251-5-8 LOWER LH CB RAIL ASSY G10251-5-7 LOWER RH CB RAIL ASSY BREAK SHARP EDGES 42 3 FOR UNUSED CB LOCATIONS DESIGNED CLB UNLESS OTHERWISE DRAWN SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: CHECKED FRACTIONS DECIMAL ANGLES .050 .X 2 1/8" APPROVED .030 .XX CLB .XXX .010 DATE 8/30/07 DATE DATE Title DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. SWITCH AND CB RAIL ASSEMBLY DETAILS Drawing Number G10251-5 Pro No: GA107 SIZE B REV Scale: none Sheet N 3 of 4 REVISIONS REV DESCRIPTION APVR/DATE SEE SHEET 1 FOR REVISION HISTORY 60 BUSS RAIL 49 40 or 41 or 42 101 48 63 or 64 or 71 70 BUSS WIRE BREAK SHARP EDGES BUSS WIRE TO BUSS RAIL CONNECTION DESIGNED CLB UNLESS OTHERWISE DRAWN SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: CHECKED FRACTIONS DECIMAL ANGLES .050 .X 2 1/8" APPROVED .030 .XX CLB .XXX .010 DATE 8/30/07 DATE DATE Title DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. SWITCH AND CB RAIL ASSEMBLY DETAILS Drawing Number G10251-5 Pro No: GA107 SIZE B REV Scale: none Sheet N 4 of 4 REVISIONS 12 23 REV DESCRIPTION G REDRAWN AND REFORMATED; ADDED TRIMMING DETAIL FOR ITEM #44 8/30/07 CLB H ADDED FN1; REVISED TRIMING NOTE EFFECTIVITY 5/01/15 CLB J REVISED PICTORIALLY TO SHOW ALL INSTALLED WASHERS AND NUTS 5/19/15 CLB APVR/DATE 16 25 28 43 24 44 24 WIRE TERMINAL 1 4.6 .19 .19 49 1 60 1 48 1 BREAK SHARP EDGES TRIM ITEM #44 AS SHOWN (OPTIONAL FOR P122 CONSOLE) R.3 TYP FOR EACH STUD LOCATION (USED OR NOT) DESIGNED CLB UNLESS OTHERWISE DRAWN SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: CHECKED FRACTIONS DECIMAL ANGLES .050 .X 2 1/8" APPROVED .030 .XX CLB .XXX .010 DATE 8/30/07 DATE DATE Title DATE 8/30/07 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. TERMINAL BLOCK ASSEMBLY Drawing Number G10251-6 Pro No: GA107 SIZE B REV Scale: 1:1 Sheet -- J of REVISIONS REV LOC DESCRIPTION APPROVED/DATE 1/10/03 CLB ADDED ITEM 7, NVIS FILTER A G10270-1 TOP OVERLAY SIZE: .38 x 1.50 x 6.35 WEIGHT: 3 oz MAX CURRENT: 0 - 28VDC, 1 AMP MAX 1 6 3 1 5 7 OPTIONAL NOTES: 4 UNLESS OTHERWISE NOTED OPTIONAL: TEXT MAY BE ENGRAVED, STAMPED OR PRINTED ON PART AS DESIRED 2 1 6 8 6 6 1 1 2 QTY. 7 6 5 4 3 2 1 ITEM NO. G12141-1 MS24693-2 OR EQUAL G12251-1 G12141 G10271-3 G10271-1 875K-ND PART NO. DRAWN BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: FRACTIONS 1/8" DECIMAL .X .050 .XX .030 .XXX .010 ANGLES 2 CLB APPLY LOC-TITE (BLUE, 242) TO THREADS GENEVA OLANDER GENEVA GENEVA GENEVA GENEVA DIGIKEY SUPPLIER DATE CHECKED DATE DESIGNED DATE NVIS FILTER SCREW, 100° FLAT HEAD #4-40 x 1/4 SPACER - TOP OVERLAY TOP LEGEND TOP CB ASSY TOP OVERLAY NYLON SPACER - #4 x .125 LG DESCRIPTION 5/31/02 Geneva Aviation www.GenevaAviation.com Title APPROVED GLH DATE TOP OVERLAY 5/31/02 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. Drawing Number Pro No: REV G10270-1 GA107 SIZE C Scale: 1:1 A REVISIONS REV LOC DESCRIPTION APPROVED/DATE 1/10/03 CLB ADDED ITEM 6, NVIS FILTER A G10270-2 SIDE OVERLAY SIZE: .38 x 1.50 x 11.90 WEIGHT: 5 oz MAX CURRENT: 0 - 28VDC, 1 AMP MAX 1 5 2 4 6 OPTIONAL NOTES: 3 UNLESS OTHERWISE NOTED OPTIONAL: TEXT MAY BE ENGRAVED, STAMPED OR PRINTED ON PART AS DESIRED 1 7 7 7 7 1 1 QTY. 1 6 5 4 3 2 1 ITEM NO. G12142-1 MS24693-2 OR EQUAL G12251-2 G12142 G10271-4 G10271-2 PART NO. DRAWN BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES TOLERANCES ARE: FRACTIONS 1/8" DECIMAL .X .050 .XX .030 .XXX .010 ANGLES 2 CLB APPLY LOC-TITE (BLUE, 242) TO THREADS GENEVA OLANDER GENEVA GENEVA DIGIKEY GENEVA SUPPLIER DATE CHECKED DATE DESIGNED DATE NVIS FILTER SCREW, 100° FLAT HEAD #4-40 x 1/4 SPACER - SIDE OVERLAY SIDE LEGEND SIDE OVERLAY CB SIDE OVERLAY DESCRIPTION 5/31/02 Geneva Aviation www.GenevaAviation.com Title APPROVED GLH DATE SIDE OVERLAY 5/31/02 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. Drawing Number Pro No: REV G10270-2 GA107 SIZE C Scale: 1:1 A 4 3 1 2 REVISIONS DESCRIPTION REV A APPROVED/DATE REVISED TO SHOW G13133, G13134, AND G13137 AS REV A PARTS 4/05/13 CLB D D C C POST-MOD 350A07-4280 INSTALLATION OF P132 AVIONICS CONSOLE THESE INSTRUCTIONS ARE TO BE USED WITH P132 CONSOLE INSTALLATION INSTRUCTIONS GA107-6. B B A 12 2 22208BC050016L EUROCOPTER BOLT, 5MM X 16MM 11 1 22208BC050014L EUROCOPTER BOLT, 5MM X 14MM 10 11 22208BC050012L EUROCOPTER BOLT, 5MM X 12MM 9 14 23111AG050LE EUROCOPTER WASHER, 5MM FLAT 8 10 A0164TK050S012X EUROCOPTER SCREW, TI, M5 X 12MM 7 8 22542K040 EUROCOPTER LOCKNUT, M4 6 8 22272BC040012L EUROCOPTER PAN HEAD SCREW M4 X 12MM 5 1 G13137 GENEVA COVER PLATE 4 1 G13135 GENEVA LATERAL BRACE ASSY 3 1 G13134 GENEVA LH VERTICAL SUPPORT ASSY 2 1 G13133 GENEVA RH VERTICAL SUPPORT ASSY 1 1 G10251 GENEVA P132 AVIONICS CONSOLE ITEM NO. QTY. PART NUMBER VENDOR DESCRIPTION BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES DRAWN CLB DATE CHECKED DATE Design DATE 1/02/13 TOLERANCES ARE: FRACTIONS DECIMAL ANGLES .X .050 2 1/8" .XX .030 .XXX .010 Title Approval CLB DATE 1/02/13 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 4 3 2 A P132 CONSOLE INSTALLATION POST MOD 350A07-4280 Drawing Number Pro No: G13132 GA107 1 SIZE REV D A Scale: none Sheet 1 of 5 3 4 1 2 REVISIONS DESCRIPTION REV APPROVED/DATE SEE SHEET 1 FOR REVISION HISTORY D D 4 3 6 4 2 C C 6 5 5 7 7 6 6 7 VIEW LOOKING FORWARD LH SIDE VIEW RH SIDE VIEW B B POST-MOD 350A07-4280 REMOVAL OF MULTIBLOC CENTER CONSOLE INSTRUCTIONS: 1. REMOVE LH SIDE ACCESS PANEL UNDER INSTRUMENT PANEL. A 2 REMOVE 30 ALPHA CIRCUIT BREAKER PANEL ON FWD RH SIDE WALL. 3 REMOVE ALL RADIOS, AUDIO PANELS, AND OTHER AVIONICS DEVICES MOUNTED WITHIN THE CONSOLE. 4 REMOVE ALL SWITCH PANELS (130A, 131A, 132A, 133A, 134A) INSTALLED IN THE CONSOLE. 5 REMOVE 16ALPHA & 44 ALPHA CB PANELS FROM SIDE OF CONSOLE. 6 REMOVE SCREWS FROM SIDE WALL SECURING CONSOLE TO FWD SUPPORT STRUCTURE. 7 THESE INSTRUCTIONS ARE TO BE USED WITH P132 CONSOLE INSTALLATION INSTRUCTIONS GA107-6. REMOVAL OF ALL COMPONENTS TO BE DONE PER EC MAINTENANCE MANUAL AND STANDARD PRACTICES MANUAL. BREAK SHARP EDGES REMOVE SCREWS SECURING CONSOLE TO FLOOR AND REMOVE CONSOLE FROM A/C. UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES DRAWN CLB DATE CHECKED DATE Design DATE 1/02/13 TOLERANCES ARE: FRACTIONS DECIMAL ANGLES .X .050 2 1/8" .XX .030 .XXX .010 Title Approval CLB DATE 1/02/13 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 4 3 2 A P132 CONSOLE INSTALLATION POST MOD 350A07-4280 Drawing Number Pro No: G13132 GA107 1 SIZE REV D A Scale: none Sheet 2 of 5 3 4 1 2 REVISIONS DESCRIPTION REV APPROVED/DATE SEE SHEET 1 FOR REVISION HISTORY 8 10 D D 8 LATERAL BRACE 10 8 A A RH VERTICAL SUPPORT LH VERTICAL SUPPORT C GROUND 11 BLOCK "90N" LH VERTICAL SUPPORT C GROUND 11 BLOCK "89N" 8 VIEW LOOKING FORWARD LH SIDE VIEW B INSTRUCTIONS: 8 REMOVE SCREWS SECURING RH VERTICAL SUPPORT TO FLOOR, LATERAL BRACE AND BOTTOM OF ENTABLATURE. REMOVE RH VERTICAL SUPPORT FROM A/C. 9 REMOVE SCREWS SECURING LATERAL BRACE TO THE SHELF AND LH VERTICAL SUPPORT. REMOVE LATERAL BRACE FROM A/C. 10 REMOVE SCREWS SECURING LH VERTICAL SUPPORT TO FLOOR, SHELF AND BOTTOM OF ENTABLATURE. REMOVE LH VERTICAL SUPPORT FROM A/C. 11 B SHELF POST-MOD 350A07-4280 REMOVAL OF CONSOLE SUPPORT STRUCTURE REMOVE GROUND BLOCKS "89N" & "90N" FROM LH VERTICAL SUPPORT AND RETAIN WITH MOUNTING HARDWARE FOR LATER INSTALLATION. 9 9 10 LH VERTICAL SUPPORT A THESE INSTRUCTIONS ARE TO BE USED WITH P132 CONSOLE INSTALLATION INSTRUCTIONS GA107-6. 8 REMOVAL OF ALL COMPONENTS TO BE DONE PER EC MAINTENANCE MANUAL AND STANDARD PRACTICES MANUAL. LATERAL BRACE RH VERTICAL SUPPORT BREAK SHARP EDGES VIEW A-A UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES DRAWN CLB DATE CHECKED DATE Design DATE 1/02/13 TOLERANCES ARE: FRACTIONS DECIMAL ANGLES .X .050 2 1/8" .XX .030 .XXX .010 Title Approval CLB DATE 1/02/13 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 4 3 2 A P132 CONSOLE INSTALLATION POST MOD 350A07-4280 Drawing Number Pro No: G13132 GA107 1 SIZE REV D A Scale: none Sheet 3 of 5 3 4 1 2 REVISIONS DESCRIPTION REV APPROVED/DATE SEE SHEET 1 FOR REVISION HISTORY 2X 2X 7 2X 2X 6 ENTABLATURE 6 .66 7 .50 D D RH SIDE WALL 13 3X 15 4 2X 8 B 3 8 3 12 2 LH VERTICAL SUPPORT ASSY GROUND 16 BLOCK "90N" 13 8 13.79 14 RH VERTICAL SUPPORT ASSY 4X 4X 6 8 13 TRIM EDGE B 8 C LATERAL BRACE ASSY .25 7.54 7 GROUND 16 BLOCK "89N" C 8 3.54 2.25 10 INSTRUCTIONS: 12 INSTALL LH VERTICAL SUPPORT ASSY G13134 USING HARDWARE SHOWN. CREATE ELECTRICAL BOND BETWEEN SUPPORT, FLOOR STRUCTURE AND ENTABLATURE PER EC SPM. VERIFY CONTINUITY AFTER ASSEMBLY. 13 TEMPORARILY INSTALL RH VERTICAL SUPPORT ASSY G13133. LAYOUT AND TRIM RH SIDE WALL AS SHOWN. LAYOUT AND DRILL (3) .25 MOUNTING HOLES AS SHOWN IN RH SIDE WALL TO MATCH MOUNTING HOLES IN G13133. DISASSEMBLE AND DEBURR SHARP EDGES. 14 INSTALL RH VERTICAL SUPPORT ASSY G13133 USING HARDWARE SHOWN. CREATE ELECTRICAL BOND BETWEEN SUPPORT, FLOOR STRUCTURE AND ENTABLATURE PER EC SPM. VERIFY CONTINUITY AFTER ASSEMBLY. 15 INSTALL LATERAL BRACE ASSY G13135 USING HARDWARE SHOWN. 16 INSTALL GROUND BLOCKS "89N" & "90N" ONTO G13135 LH VERTICAL SUPPORT ASSY USING HARDWARE SHOWN OR USING ORIGINAL HARDWARE. CREATE ELECTRICAL BOND BETWEEN GROUND BLOCK AND SUPPORT PER EC SPM. VERIFY CONTINUITY AFTER ASSEMBLY. 30° VIEW LOOKING FORWARD LH SIDE VIEW B 10 8 RH SIDE VIEW B SHELF POST-MOD 350A07-4280 INSTALLATION OF P132 CONSOLE SUPPORT STRUCTURE 8 8 2X 2X 10 9 9 THESE INSTRUCTIONS ARE TO BE USED WITH P132 CONSOLE INSTALLATION INSTRUCTIONS GA107-6. 10 INSTALLATION OF ALL COMPONENTS TO BE DONE PER EC MAINTENANCE MANUAL AND STANDARD PRACTICES MANUAL. 3 4 2 A BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES VIEW B-B DRAWN CLB DATE CHECKED DATE Design DATE 1/02/13 TOLERANCES ARE: FRACTIONS DECIMAL ANGLES .X .050 2 1/8" .XX .030 .XXX .010 Title Approval CLB DATE 1/02/13 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 4 3 2 A P132 CONSOLE INSTALLATION POST MOD 350A07-4280 Drawing Number Pro No: G13132 GA107 1 SIZE REV D A Scale: none Sheet 4 of 5 3 4 1 2 REVISIONS DESCRIPTION REV APPROVED/DATE SEE SHEET 1 FOR REVISION HISTORY C 1 D D 1 4X 4X 9 10 17 18 5 19 C C C 18 2X 2X 10 9 D D VIEW C-C LOOKING FWD 18 2X 2X 10 9 RH SIDE VIEW LH SIDE VIEW B 12 9 11 9 9 B 12 VIEW D-D ROTATED 90 CW POST-MOD 350A07-4280 INSTALLATION OF P132 AVIONICS CONSOLE INSTRUCTIONS: 17 ENLARGE (4) MOUNTING HOLES TO .25 ON FWD EDGE OF P132 CONSOLE FRAME FOR MOUNTING TO VERTICAL SUPPORTS G13133 AND G13134. MOUNTING HOLES MAY BE SLOTTED TO ALIGN WITH NUTPLATES. 18 MOUNT P132 CONSOLE TO FLOOR AND FRAME USING HARDWARE SHOWN. INSTALL OEM GUARD 350A76-3045-20 UNDER CONSOLE BEFORE MOUNTING TO FLOOR. 19 INSTALL COVER PLATE G13137 INTO RH SIDE WALL. THESE INSTRUCTIONS ARE TO BE USED WITH P132 CONSOLE INSTALLATION INSTRUCTIONS GA107-6. INSTALLATION OF ALL COMPONENTS TO BE DONE PER EC MAINTENANCE MANUAL AND STANDARD PRACTICES MANUAL. A BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES DRAWN CLB DATE CHECKED DATE Design DATE 1/02/13 TOLERANCES ARE: FRACTIONS DECIMAL ANGLES .X .050 2 1/8" .XX .030 .XXX .010 Title Approval CLB DATE 1/02/13 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 4 3 2 A P132 CONSOLE INSTALLATION POST MOD 350A07-4280 Drawing Number Pro No: G13132 GA107 1 SIZE REV D A Scale: none Sheet 5 of 5 4 3 1 2 REVISIONS DESCRIPTION REV APPROVED/DATE D D REPLACE EXISTING SCREW WITH #6-32 X .31 PAN HEAD SCREW 2 PLACES (6C31PPMSB) COVER G13138-1 C C DETAIL A THIS INSTALLATION IS APPLICABLE FOR THE P132 CONSOLE. B THIS INSTALLATION PROVIDES COVERS FOR THE FOWARD OPENINGS OF THE SWITCH AND CIRCUIT BREAKER RAILS TO PREVENT LOOSE ITEMS (FOD) FROM ENTERING THE RAILS. COVER G13138-1 B THIS INSTALLATION IS OPTIONAL AT THE INSTALLERS DESCRETION. THE INSTALLTION SHOWN IS FOR THE RIGHT SIDE OF THE CONSOLE. THE INSTALLATION ON THE LEFT SIDE OF THE CONSOLE IS IDENTICAL, EXCEPT SUBSTITUTE COVER G13138-2 IN PLACE OF G13138-1. REPLACE EXISTING SCREW WITH #6-32 X .31 PAN HEAD SCREW 2 PLACES (6C31PPMSB) DETAIL B A BREAK SHARP EDGES UNLESS OTHERWISE SPECIFIED DIMENSIONS ARE IN INCHES DRAWN CLB DATE CHECKED DATE Design DATE 3/5/15 TOLERANCES ARE: FRACTIONS DECIMAL ANGLES .X .050 2 1/8" .XX .030 .XXX .010 Title Approval CLB DATE 3 2 COVER INSTALLATION 3/5/15 THIS DOCUMENT INCLUDES INFORMATION PROPRIETARY TO GENEVA AVIATION AND SHALL NOT BE USED OR DUPLICATED BY ANYONE WITHOUT THE WRITTEN PERMISSION OF GENEVA AVIATION, INC. 4 A Drawing Number Pro No: G13138 GA107 1 SIZE REV D -- Scale: NONE Sheet 1 of 1

Avionics Switch Console Installation Manual -p132

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