WOHA33_961108_253_EOA33-25-0057

Hong Kong Airlines Limited香港航空03110-01Hong Kong Airlines MEDHong Kong Airlines LimitedWO NO/工作指令号SEQ NO/序列号WOHA33961_253_108适航指令(AD) 961108TitleINSPECT AND REPLACE OF COCKPIT INSTRUMENT PANEL BRACKET 7.Mcd&Rev/厂家工卡&修订日期标题检查和更换驾驶舱7号仪表板支架A/C/飞机号/组别EO JC No./EO工卡EO JC Rev/工卡版本Workarea/工作区域Skill/工种Man Hour/工时BLND/2EOA33-25-0057R03机身/AirframeAVIO/ELEC03:00/20:00Baseline/依据Operator EO/营运人EOEO Rev/EO版本Work Type/工作类别Threshold/首检Interval/重复检AD 2014-0127,ASB A330-25-3538EOA33-HKG25-0029R03Written/编写Reviewed/审核Approved/批准2014-06-032014-06-032014-06-03Accomplished完工签署Complete Date完工日期Station维修站PVGREASON & DESCRIPTION/原因及描述驾驶舱7号仪表板支架不能承受由远程航线飞机长期的震动所产生的疲劳载荷。 下发此EO更换和检查驾驶舱7号仪表板支架。Cockpit instrument panel bracket 7 cannot sustain any fatigue loads of the Long Range Design Service Goal (DSG). Issue this EO to replace and inspect 7 bracket. R01 版增加B-LNV飞机适用性。R01 revision add B-LNV aircraft applicability. R02版修改依据文件信息:增加AD控制信息。R02 revision the source information:add the AD control information. R03版修改控制信息和 工作步骤。R03 revision change the control information and work step.TOOLS/工具TOOLS NECESSARY/必须工具ITEM项目P/N件号DESCRIPTION名称EQTP类型QTY数量APP适用性Conditions note互换信息及备注TOOLS IF NECESSARY/视情工具ITEM项目P/N件号DESCRIPTION名称EQTP类型QTY数量APP适用性Conditions note互换信息及备注PARTS AND MATERIAL/航材NOTE:OPERATOR MUST GET AND INSTALL THE PARTS THAT CORRESPOND TO THE RELATIVE WORKORDER NO.注释：请工作者严格按照工作指令号领取预定的航材装机PARTS AND MATERIAL NECESSARY/必须航材ITEM项目P/N件号DESCRIPTION名称EQTP类型QTY数量APP适用性Conditions note互换信息及备注1MS24665-71COTTER PINAS1ALL无2NSA5060-3NUTAS1ALL无3ASNA2050DEJ4020RivetAS4ALL无4CML03HBD9GREASECH1ALL无5NSA5042-04-160BOLTAS1ALL无6NSA5325-3WASHERAS1ALL无7F2511012820095BRACKETAS1ALL无PARTS AND MATERIALIF NECESSARY/视情航材ITEM项目P/N件号DESCRIPTION名称EQTP类型QTY数量APP适用性Conditions note互换信息及备注IMPORTANT NOTE:In the event of any discrepancies between the Chinese instruction and the English instruction, the English procedure should prevail.Record Additional Work/Findings(If Applicable) Reference No. Certificate of Release to Service (* Tick as appropriate # Different crews should perform the work on each of the systems)Certifies that the work specified, except as otherwise specified, was carried out in accordance with HKAR-145and in respect to that work, The aircraft / aircraft components are considered ready for Release to Service. HKA Approval No: AI / 135 / 706 * HNAT Approval No.: JMM 076, D3039 * HNAT Approval No.: JMM 047, D101115* HNAT Approval No.: JMM 049, D500023 * CASL Approval No: AI / 101 / 798 * TAECO Approval No.: DAI / 89 / 1295 * HAECO Approval No: DAI / 1 / 853 * SIAEC Approval No: AWI / 01 * STARCO Approval No.: JMM 039, D.200078 * SMECO Approval No: JMM 081, D.400009 * Other: * Signature:_ Authorization No.:_ Date:_工卡Job card:EOA33-25-0057TITLEINSPECT AND REPLACE OF COCKPIT INSTRUMENT PANEL BRACKET 7.PerfInsp标题检查和更换驾驶舱7号仪表板支架工作者检查者警 告：确认遵守包括参考程序在内的所有警告和注意信息。WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONSINCLUDED IN THE REFERENCED PROCEDURES.A. 准备PREPARATION(1) 工卡253538-941-003-001 准备Subtask 253538-941-003-001 - Job Set-up(a) 执行工作前先要确认下列项目是否正确：- 起落架已安装地面安全销，轮挡摆放正确- 发动机已关闭，反推关闭并锁定- 飞机干净- 已刹车- 飞机已断电- 液压系统已没有压力- 驾驶舱和客舱可接近- 所有跳开关处于闭合位置- 所有控制装置电门在正常，自动或关闭位置The following items shall be considered as the basic Aircraft configuration before you start a maintenance task:- Aircraft on the ground resting on landing gear (the ground safety locks and thewheel chocks are in position on the landing gear).- Engine shut down, thrust reversers closed and locked.- Aircraft in clean configuration.- Parking brake applied.- Aircraft electrical network de-energized.- Hydraulic systems depressurized.- Access to the cockpit and cabin is available.- All circuit breakers are in closed position.- All controls in NORM, AUTO or OFF position.(b) 参考AMM Task 12-34-24-860-802确保飞机接地。Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802.(c) 在登机门831或841处放置登机梯。Put the access platform in position door 831 or 841.(d) 参考AMM Task 52-10-00-010-801打开登机门831或841Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.(e) 如有必要参考AMM Task 25-11-51-000-801拆除副驾驶座椅。If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task 25-11-51-000-801.(f) 参考AMM Task 31-63-22-000-801中的显示组件拆除程序做准备工作。 Do the Job Set-up procedure as specified in the removal of the Display Unit(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.(g) 确保驾驶舱235VU面板上的开关已关闭。In the cockpit, on the panel 235VU, make sure that these pushbutton switches are released:- BAT 1, BAT 2, APU BAT,- GEN 1, (2), APU GEN,- EXT A (B).(h) 如有必要参考AMM Task 33-12-13-000-801拆除灯光组件。If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task 33-12-13-000-801.(i) 拔出跳开关并装上跳开关卡子。Open, safety/lock and tag these circuit breakers:(j) 确保驾驶舱内的警告提示在明显位置以提醒其他人员不许操作顶板上的开关。Make sure that there are warning notices in the cockpit to tell persons not tooperate the pushbutton switches on the overhead panels:- 211VU (EMER ELEC PWR)- 235VU (ELEC)(k) 确保驾驶舱内的警告提示在明显位置以提醒其他人员不许启动APU。Make sure that there are warning notices in the cockpit to tell persons not to start the APU.(l) 确保外部电源接头没有连接到飞机EXT PWR A (B)上。Make sure that the external connectors are not connected to the aircraft receptacles EXT PWR A (B).(m) 确保121EL接进门处的警告标识可以提醒人员不要接通外接电源。Make sure that there is a warning notice at the access door 121EL to tell personsnot to connect the external power connectors.(2) 工卡253538-010-003-001 拆下/打开来接近Subtask 253538-010-003-001 - Remove/Open for Access(a) 参考图A-FBCAA Sheet 01拆下保护板。Remove the protection plate. Refer to Fig. A-FBCAA Sheet 013 Stud Item (1) Retain3 Washer Item (2) Retain1 Panel Item (3) Retain(b) 参考图A-FBCAA Sheet 02拆下盖子。Remove the cover assembly panel. Refer to Fig. A-FBCAA Sheet 023 Stud Item (5) Retain1 Panel Item (4) Retain(c) 参考AMM Task 31-63-22-000-801拆下显示组件。Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.B.参考图A-FBAAA 和 A-FFAAA对7号支架做详细检查Detailed inspection the bracker No.7 refer to FIG A-FBAAA and A-FFAAA, make sure have crack or no. (1) 如检查7号支架和相关区域未发现裂纹，则执行步骤C更换工作。 If check the bracker No.7 and install area cant found crack, please accomplish step C.(2) 如检查7号支架和相关区域发现有裂纹，则终止此份EO，将检查结果反馈至客舱工程中心：。并且飞机不能放行。 If check the bracker No.7 and install area found have crack, please stop this EO,and feedback the check result to cabin engineering center: . And this aircraft cant despatch.C.更换7号支架 Replace the bracket No.7 (1) 工卡253538-833-002-004 更换7号支架Subtask 253538-833-002-004 - Replace the Bracket No. 7. (a) 参考图A-FBDAC并按照SRM 51-42-00拆下7号支架。Remove the bracket No. 7. Refer to Fig. A-FBDAC In accordance with SRM 51-42-00.1 拆除下列部件Remove:1 Axis Item (17) Discard1 Nut Item (18) Discard1 Washer Item (19) Discard1 Pin Item (21) Discard2 拆除铆钉： 拆下四个铆钉头 用钻将个铆钉完全拆下，原有孔尺寸要在4.07和4.16 毫米之间 (0.160和0.164英寸) Remove the rivets:- Remove the head of the four rivets.- Drill four holes through the cockpit main panel to remove the four rivets and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and 0.164 in).4 Rivet Item (12) Discard3 拆下支架。Remove the bracket:1 Bracket F2511012820000 Item (16) Discard(b) 参考图A-FBDAC并按照SRM 51-42-00和SRM 51-44-00安装支架。Install the new bracket. Refer to Fig. A-FBDAC In accordance with SRM 51-42-00 and SRM 51-44-00.1 在右上部支架处临时摆放项目16支架Temporarily put the bracket item 16 on the RH side of the upper bracket.a 在新支架上按照上部支架孔的位置做标记。 Mark the position of the hole of the upper bracket on the new bracket.2 在平台上钻孔，直径在6.5和6.7毫米(0.256和0.264 英寸)之间On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7mm (0.256 and 0.264 in).3 将螺栓17放到新支架16中安装。Put in position the new bracket item 16 with the bolt item 17.Install:1 Bracket F2511012820095 Item 161 Bolt NSA5042-04-160 Item 17注释：安装螺栓时按需涂油脂03HBD9NOTE: Install the bolt item 17 with:Synthetic Ester Base Grease-General Purpose Low T 03HBD9 As required4 如图A-FBDAC Sheet 04所示，测量新支架16和上部支架之间的间隙。Measure the clearance between the new bracket item 16 and the upper bracket as show in Fig. A-FBDAC Sheet 04a 左侧最小间隙为0.35毫米(0.014 英寸)，右侧0.65毫米(0.026 英寸)Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and0.65 mm (0.026 in) at RHS.5 按照结构的原有孔，在支架16上钻孔。 Drill the holes in the bracket item 16 to align with the holes of the structure.6 安装4颗铆钉15 Install:4 Rivet ASNA2050DEJ4020 Item 157 安装螺母18Install the nut item 18:1 Nut NSA5060-3 Item 181 Washer NSA5325-3 Item 191 Pin-Cotter MS24665-71 Item 21注释： 拧紧螺母18的扭矩要在0.28 和 0.37 mdaN(24.782 and 32.748 lbf.in)之间NOTE: Torque the nut item 18 to a torque value between 0.28 and 0.37 mdaN (24.782 and 32.748 lbf.in).(2) 工卡253538-410-004-001 安装/恢复拆下的部件Subtask 253538-410-004-001 - Install/Close Items Removed/Opened for access(a) 参考AMM Task 31-63-22-400-801安装显示组件。Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.(b) 参考图Fig. A-FBCAA Sheet 02安装盖子。Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 023 Stud Item (5) Retained at removal1 Panel Item (4) Retained at removal(c) 参考图A-FBCAA Sheet 01安装保护板。Install the protection plate. Refer to Fig. A-FBCAA Sheet 013 Stud Item (1) Retained at removal3 Washer Item (2) Retained at removal1 Panel Item (3) Retained at removalD.测试 TEST (1) 工卡253538-700-005-001 测试Subtask 253538-700-005-001 Test 注释： 参考工卡253538-410-004 001完成部件恢复后再进行测试工作。NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 253538-410-004 001 Install/Close Items Removed/Opened for access(a) 在驾驶舱235VU板处按下下列电门。In the cockpit, on the panel 235VU, push these pushbutton switches:- BAT 1, BAT 2, APU BAT,- GEN 1, (2), APU GEN,- EXT A (B).(b) 拆下警告提示。Remove the warning notices.(c)参考AMM Task 24-41-00-861-801给飞机通电。 Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.(d) 拆除下面位置的跳开关卡子。Remove the safety clips and/or tags and close/unlock these circuit breakers: (e) 测试Preliminary test:注释：如果飞机在CAT III状况下运行，需要参考AMM Task 22-97-00-740-801做LAND CAT III能力测试NOTE: If the aircraft is operated in actual CAT III conditions, you must also do the LAND CAT III capability test, refer to AMM Task 22-97-00-740-801.1 在每个断开的接头处按照ESPM 20-52-20做检查。On each connector which was disconnected:- Do the checks as defined by ESPM 20-52-20.注释：按照ESPM手册程序做功能和操作测试NOTE: The functional test and/or operational test (OT) requested by this ESPM procedure is given hereafter.2 参考AMM Task 33-13-00-710-801对仪表和面板灯光做操作测试。Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task33-13-00-710-801.3 参考AMM Task 33-14-00-710-801对灯光操作测试。Do the OT of Lights, refer to AMM Task 33-14-00-710-801.4 参考AMM Task 21-26-00-710-803对电子设备通风系统做操作测试。Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task21-26-00-710-803.5 参考AMM Task 22-96-00-740-801对自动飞行系统做操作测试。Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task22-96-00-740-801.6 参考AMM Task 31-50-00-710-803对ECAM做操作测试。Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.7 参考AMM Task 31-50-00-740-801对FWS做测试。Do the test of the FWS, AMM Task 31-50-00-740-801.8 参考AMM Task 31-60-00-710-802对EIS做操作测试。Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.(f) 安装显示组件后参考AMM Task 31-63-22-200-802做测试。Do the test procedure as specified after the installation of the DU (FINs 1WK2 and3WK2), refer to AMM Task 31-63-22-200-802.(g) 如果已拆下副驾驶员座椅，在恢复安装后参考AMM Task 25-11-51-400-801做测试程序。If removed, do the test procedure as specified after the installation of the Fi