Project Number: Document Reference: Document Revision: Date of lssue :

Transcription

1 Project Number: Document Reference: Document Revision: Date of lssue : EAD Acrocpac Chemin des Vergers U24La Bastided6Joudam France EADAso$.ce RoLte de Tarbes 3lJTOTo,Dlbuille FrarDe

2 lssued by First Release Second Release

3 Ref. Rev Date Page 1. PLANNTNG 1NFORMAT1ON ,I PURPOSE OF THE DOCUMENT EFFECTIVITY Aircraft REASON DESCRIPTION APPROVAL MANPOWER... 5 '1.7 MATERIAL TOOLING WEIGHTANDBALANCE , ELECTRICALEFFECTS Accomplishment rnstructions Preparation

4 Ref. Rev. Date 1.3 REASON An operator has requested the installation of an Emergency Locator Transmitter (ELT) system onboard 8737 series aircraft. 1.4 DESCRIPTION This Service Bulletin will :. lnstall an ELT Control PanelAssy on the Overhead Panel Pilot's P5.. lnstalla 1 amp ELT C/B on the Load Control Center Panel P6.. Install an ELT Unit on a dedicate tray in the aircraft rear top fuselage on STA857.. Install a wiring harness.. lnstall an ELT antenna on the upper fuselage on STA APPROVAL These instructions relate to MAS number JM-B Rev. B which has been approved by EAD Aerospace under the Authority of DGAC-F, DOA number F.JA.13. The technical information contained in this document is approved by EAD Aerospace under the Authority of DGAC-F, DOA number F.JA.13"

5 MANPOWER These estimates assumes that the work will be done by experienced personnel, aircraft and tools ready, and may need to be revised upwards to suit operatols circumstances. The estimates do not include the time to prepare, plan or inspect the work and certification tests. Manufacture and procurement of parts and tools, drying times for paints' sealant' etc, and general administration works are also not included'

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7 1 Remote Panel pure MineralVaseline or Petroleum Mat. No. O4-O12 As required Electrical Bonding coating (Blue color) Mat. No As required

8 Ref. Rev. Date 2.3.'l Accomplishment instructions 2.4 GENERAL PreParation a) Remove ceiling panels between pilot's overhead panel and sta867 in order to gain access to raceway S' b) Remove insulation blanket between sta827 and sta847 to get access to the work area for the antenna installation' 2.5 ELECTRICAL MODIFICATION ELT Unit Installation Refer to figure 3 and EAD Aerospace KitPL ln the AFT cabin compartment, on the top of fuselage area between STAB47 and stab67 in axis ot strlnier s-31, install the tray and the ELT Unit on the tray. a) The tray : 1. Install the ELT tray (item 30) with rivets (Qty: 8ea)' NOTE:TheinstallershoulduserivetsP/NNAS1O97AD6'ltemnotprovidedinthekit' b) ELT Unit: 2 nsta theeltunit(item2)withscrews(item28)andwashers(item27). 3. nsta the p acard (item 7) identified as.' D,, in front of the ELT Unit Wire Installation, Overhead Panel Refer to figures 1 and 2, EAD Aerospace Document DC and EAD Aerospace KitPL O1 4 tn the Etectrical Load c/b panel (p6-3), install the ELT C/B (item 9) and placards identification (item 8) identified,, "ilt" on the front side of the panel and identified as 'C9260" on the rear side of the panel at position D2' 5. Install wires in accordance with the hook-up charts EAD Aerospace Document DC using the hardware items as sl"own in figure 2' WARNING : you should put the wires across the hole of the ELT end cap before installing the wires on the Plug. 6. Do a continuity test of all wires' 7. Attach the wires with cable ties (items 12 and 15), as required'

9 Wire Installation, Cabin Compartment Refer to figure 4, EAD Aerospace Document DC3O2{ and EAD Aerospace Kit PL Route the wires from the pilot's Overhead Panel (P5) in the.cockpit to the ELT Unit in the cabin compartment between STA847/5TA867 on the existing cable support on raceway S with cable support (item 24) as shown in figure 4 detaila' lnstall wires rn accordance with the hook-up charts EAD Aerospace Document DC302- OSgg-Of using the hardware items as shown infigure 2' Do a continuity test of all wires. Attach the wires with cable ties (items 12 and 15)' as required' lnstall coaxial cables (items 4 and 5) from ELT Unit to antenna as shown in figure 4 and connect them. segregate coax cables using spacers (item 29) and cable ties (item 15) as shown in figure 4 detail B. STRUCTURAL MODIFICATION ELT Antenna Installation Refer to figures 5 and 6 and EAD Aerospace KitPL21U ' Locate Doubler (item 1) and retaining plate (item 2) as shown in figure 6, centered between STA827/STA847 and stgr 1 and stgr 2L' Match driil all parts. Maintain proper edge distance and rivet spacing. Remove and replace existing rivets as shown in figure 6' Use fasteners of at least the same diameter as the existing fasteners being replaced' NOTES : The material of the substitute fastener must not be weaker than that of the fastener being removecl. The next larger fastener diameter must be used if the fastener hole is oversized' Maintain proper edge distance and rivet spacing. Fill existing countersunk holes covered by the Doubler with countersunk washer or equivalent. Countersunk Doubler as requirec ' Maintain a nominalfastener pitch of 4D (minimum) and 8D (maximum)' lnstall fastener wet. Apply sealant (item 5) to the surface of Doubler Plate (item 1), retaining plate (item 2) and rivets litem 4) (prior to installation) per aircre ft maintenance manual procedures' tnstall Doubler Plate (item 1) using rivets (item 4) as shown in figure 6' Do not install fasteners rivets of retaining plate (item 2)'

10 Clean interior surface of aircraft and restore finish. Spray corrosion inhibitor (item 6) to inside surfaces of aircraft skin and retaining plate' Temporally place antenna and retaining plate (item 2), drill through retaining and doubler plate (item 1) at antenna fasteners holes' Remove antenna (item 3) and put rivets of retaining plate (item 2) through all parts' Drillthrough all parts through dome nuts (item 8) rivet holes of retaining plate (item2) and installdome nuts (item 8) with rivets (ltem 7)' Clean antenna base, and mating aircraft fuselage areas wtth approved solvent per aircraft maintenance manual Procedures. NOTES. lf necessary place shims between aircraft skin and retaining plate' Place antenna (item 3) of kit PL in position and secure to retaining plate using 5 screws (item 3) of kilpl o1, see figure 5' Measure the bonding resistance between the countersunk hole of the antenna adlacent structure with a milliohmmeter. Make sure that the bonding resistance not more than 5 milliohms. lnstall the last screw (item 3) and tighten all screws diagonally opposite' Apply sealant to the head of the screws. Make the contour of the sealant on the screws and around antenna smooth CLOSE.UP close allaccess on the aircraft to normal operating condition. TEST WARNINGS :.NoTIFYAt{YNEARBYA RTRAFFICcoNTRoLBEFoREPERFoRM NGTHE TEST.. PERFORM THE TEST WITHIN THE FIRST 5 MINUTES OF THE HOUR (UTC)'. PERFORM THE TEST DURTNG 5 SECONDS MAXIMUM'

11 Tune 12L 5 MHz emergency frequency on any VHF control unit and :

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