WOHA33_1051105_260_EOA33-25-0059

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WOHA331051_260_105适航指令(AD) 1051105TitleReinforce Instrument Panel Bracket 6Mcd&Rev/厂家工卡&修订日期标题加强6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BLNC/2EOA33-25-0059R03机身/AirframeELEC09:00Baseline/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SB A330-25-3548 R0,AD 2014-0127EOA33-HKG25-0034R03Written/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6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改进驾驶舱6号仪表板支架。Cockpit instrument panel bracket 6 cannot sustain any fatigue loads of the Long Range Design Service Goal (DSG). Issue this EO to improve 6 bracket. R01版增加了B-LNV飞机适用性。R01 revision add to 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版修改控制信息和增加分发单位。R03 revision change the control information and add the distribution department.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1CML03HBD9GREASECH1ALL无2253548A04R01KITAS1ALL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 * AMECO Approval No.: JMM001,D101131* Other: * Signature:_ Authorization No.:_ Date:_工卡Job card:EOA33-25-0059TITLEReinforce Instrument Panel Bracket 6PerfInsp标题加强6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 施工步骤：Wouking stips：A. 工作准备/Job set-up (1) Subtask 253548-941-001-001-工作准备Subtask 253548-941-001-001-Job Set-up(a). 在开始维修工作之前，确保飞机处于以下状态：The following items shall be considered at the basic Aircraft configuration before you start a maintenance task.1. 插好起落架安全销以及转弯释压销。Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear).2. 发动机以及反推装置关闭并锁定。Engine shut down, thrust reversers closed and locked.3. 设置好停留刹车。Parking brake applied.4. 飞机断电。Aircraft electrical network de-energized.5. 液压系统释压。Hydraulic systems depressurized. 6. 可以进入驾驶舱及客舱。Access to the cockpit and cabin is available.7. 所有跳开关处于闭合位置。All circuit breakers are in closed position.8. 所有的控制装置处于NORM,AUTO或者OFF位置。All controls in NORM, AUTO or OFF position (b). 参照AMM Task 12-34-24-860-802确定飞机接地。Make sure that the aircraft is electrically grounded, refer to AMM Task12-34-24-860-802. (c). 如果有必要，参照AMM Task 25-11-51-000-801拆下副驾驶座椅（FIN 4MS）If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task25-11-51-000-801. (d). 参照AMM Task 31-63-22-000-801，执行显示组件（DU）（FINs 1WK2和3WK2）拆装的准备程序。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. (e). 确定驾驶舱，235VU面板上的下列按键开关已断开。In the cockpit, on the panel 235VU, make sure that these pushbutton switches arereleased :- BAT 1, BAT 2, APU BAT,- GEN 1, (2), APU GEN,- EXT A (B). (f). 如果有必要，参照AMM Task 33-12-13-000-801拆下灯组件（LU）（14LE）。If necessary, remove the Light Unit (LU) (14LE), refer to AMM Task33-12-13-000-801. (g). 拔出下列跳开关并安装跳开关卡子：Open, safety and tag this (these) circuit breaker(s) : (h). 确保头顶板上的下列按键开关挂上红色警告牌以提醒禁止他人操作：Make sure that there (is) are warning notice(s) in the cockpit to tell persons not tooperate the pushbutton switches on the overhead panel :- 211VU (EMER ELEC PWR)- 235VU (ELEC) (i). 确定APU启动电门处已挂上红色警告牌以提醒禁止他人操作。Make sure that there is (are) warning notice(s) in the cockpit to tell persons not tostart the APU. (j). 确定飞机外部电源连接插座没有连接外部电源A（B）。Make sure that the external connector(s) is (are) not connected to the aircraftreceptacle(s) EXT PWR A (B). (k). 确定121EL门已挂上红色警告牌，警告他人不要连接外部电源。Make sure that there is a warning notice at the access door 121EL to tell personsnot to connect the external power connector(s). (2) Subtask 253548-010-001-001 -拆下/打开以便接近工作区域Subtask 253548-010-001-001 -Remove/Open for Access (a). 参照图A-FBCAA Sheet 01 拆下防护板。Remove the protection plate.Refer to Fig. A-FBCAA Sheet 01. 3（数量）螺柱（Stud）Item（1）保留3（数量）垫圈（Washer）Item（2）保留1（数量）面板（Panel）Item（3）保留 (b). 参照图A-FBCAA Sheet 02拆下仪表盖板组件。Remove the cover assembly panel. 3（数量）螺柱（Stud）Item（5）保留1（数量）面板（Panel）Item（4）保留B. 步骤 (1). Subtask 253548-911-001-004 -更换6号仪表支架Subtask 253548-911-001-004 -Replace the Bracket No. 6. (a). 参照图A-FBBAB Sheet 01和Sheet 02，参照SRM 51-42-00拆下6号仪表支架。In accordance with SRM 51-42-00，remove the bracket No. 6.Refer to Fig. A-FBBAB Sheet 01 and Fig. A-FBBAB Sheet 02.1. 拆下Remove1（数量）螺栓（Bolt）Item（17）丢弃（Discard）1（数量）螺母（Nut）Item（18）丢弃（Discard）1（数量）垫圈（Washer）Item（19）丢弃（Discard）1（数量）插针（Pin）Item（21）丢弃（Discard） 2. 拆下紧固件Remove the fasteners4（数量）螺栓（Bolt）Item（9）丢弃（Discard）4（数量）螺母（Nut）Item（10）丢弃（Discard）3. 拆下支架Remove the bracket1（数量）支架（Bracket）F2511373420000Item（6）丢弃（Discard） 或1（数量）支架（Bracket）F2511373420095Item（6）丢弃（Discard） (b). 参照图A-FBBAB Sheet 03 和 图 A-FBBAB Sheet 04，参照SRM 51-42-00 and SRM 51-44-00安装新支架 Install the new bracket.Refer to Fig. A-FBBAB Sheet 03 and Fig. A-FBBAB Sheet 04.In accordance with SRM 51-42-00 and SRM 51-44-00. 1. 将新支架（item 25）临时固定在上方支架的右侧。Temporarily put the bracket item 25 on the RH side of the upper bracket.a. 如果有必要的话，拆下：If necessary, remove :3（数量）铆钉（Rivet）Item（11）丢弃（Discard）b. 根据原有上支架孔的位置，定位新支架需要钻孔的位置。Mark the position of the hole of the upper bracket on the new bracket.c. 如果拆下了铆钉，需要安装新铆钉If removed, install :3（数量）铆钉（Rivet）ASNA2050DCJ3215Item（6） 2. 在工作台上按照标记的位置钻一个直径在6.5到6.7mm之间的孔。On bench, drill the marked hole to a diameter comprise between 6.5 and 6.7 mm (0.256 and 0.264 in.).3. 用螺栓（item17）将新支架（item 25）固定住。Put the position the new bracket item 25 with the bolt item 17.1（数量）支架（Bracket）F2511470820095Item 251（数量）螺栓（Bolt）NSA5042-04-160Item 17 注释：安装螺栓（item 17）的时候要按需涂抹上件号为03HBD9的合成脂。 NOTE: Install the bolt item 17 with :Synthetic Ester base Grease 03HBD9 as required4. 参照图A-FBBAB Sheet 04测量新支架（item 25）和上方支架连接处的空隙。Measure the clearance between the new bracket item 25 and the upper bracket as show in Fig. A-FBBAB Sheet 04.a. 支架连接处左边的最小余隙为0.35（0.014 in），支架连接处右边的最小余隙为0.65mm（0.026 in）。Check that the minimum clearance are 0.35 mm (0.014 in.) at LHS and0.65 m (0.026 in.) at RHS.5. 参照图A-FBBAB Sheet 03，在新支架（item 25）上钻4个直径在4.788mm（0.189 in）到4.813mm（0.190 in）之间的孔，使新支架与驾驶舱主仪表板的孔的位置匹配。Match and drill the four holes of the cockpit main instrument panel on the new bracket item 25 to a diameter comprised between 4.788 mm (0.189 in.) and 4.813 mm (0.190 in.) as shown on Figure Fig. A-FBBAB Sheet 03.6. 安装Install4（数量）螺栓（Bolt）ABS0114V3-5Item 264（数量）螺母（Nut）NSA5050-3Item 277. 安装螺母（item 18）Install the nut item 181（数量）螺母（Nut）ABS0114V3-5Item 261（数量）垫圈（Washer）NSA5050-3Item 271（数量）（Pin-Cotter）MS24665-71Item 21 注释：螺母（Item 18）拧紧力矩为0.28-0.37m.daN(24.782-32.748 lbd.in) NOTE: Torque the nut item 18 to a value between 0.28 and 0.37m.daN (24.782 and 32.748 lbd.in.). (2). 工卡 253548-410-001-004-恢复/安装拆下的部件 Subtask 253548-410-001-004-Install/Close Items Removed/Opened for access (a).参照AMM Task 31-63-22-400-801安装DU（FINs 1WK2 和 3WK2） Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801. (b).参照图A-FBCAA Sheet 02安装盖板组件。Install the cover assembly plate. Refer to Fig. A-FBCAA Sheet 02.3（数量）螺柱（Stud）Item（5）拆下的保留件1（数量）面板（Panel）Item（4）拆下的保留件 (c).参照图A-FBCAA Sheet 01.，安装防护板。Install the protection plate.Refer to Fig. A-FBCAA Sheet 01.3（数量）螺柱（Stud）Item（1）保留3（数量）垫圈（Washer）Item（2）保留1（数量）面板（Panel）Item（3）保留 (3). 工卡 253548-700-001-001-测试 注释：测试工作要在恢复之前所拆下的部件之后实施。恢复工作参考工卡253548-410-002 001。NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to 253548-410-002 001 Install/Close Items Removed/Opened for access. (a). 在驾驶舱的235VU跳开关面板上，闭合这些开关：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). 拆下红色警告牌Remove the warning notices. (c). 参照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). 取下下列跳开关卡子并闭合跳开关。Remove the Safety clips and tags and close this (these) following circuit breaker(s):(e). 初步测试Preliminary Tests:注释：参照AMM Task 22-97-00-740-801，如果飞机在CAT III的条件下运行，你必须要做LAND CAT III性能测试。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. 在每个断开接头上On each connector which was disconnected- 参照ESPM20-52-20做检查Do the check as defined by ESPM 20-52-20.注释：按照ESPM的程序做功能测试和/操作测试。NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter2. 参照AMM Task 33-13-00-710-801操作测试设备和面板的照明系统。Do the O/T of the Instrument and Panel Integral Lighting, (Refer to AMM Task 33-13-00-710-801).3. 参照AMM Task 33-14-00-710-801操作测试灯光。Do the O/T of Lights, (Refer to AMM Task 33-14-00-710-801)4. 参照AMM Task 21-26-00-710-803操作测试电子设备通风系统。Do the O/T of the Avionics-Equipment Ventilation System, (Refer to AMM Task 21-26-00-710-803).5. 参照AMM Task 22-96-00-740-801对自动飞行系统自检（系统测试）。Do the B/T of the Auto Flight System (SYSTEM TEST), (Refer to AMM Task 22-96-00-740-801).6. 参照AMM Task 31-50-00-710-803操作测试ECAM控制面板。Do the O/T of the ECAM Control Panel,(Refer to AMM Task 31-50-00-710-803) . 7. 参照AMM Task 31-50-00-740-801测试FWS。Do the test of FWS, (Refer to AMM Task 31-50-00-740-801).8. 参照AMM Task 31-60-00-710-802操作测试EIS。Do the O/T of the EIS, (Refer to AMM Task 31-60-00-710-802). (f). 步骤Procedure1. 如果拆下机长/副驾座椅，安装完成后，参照AMM Task 25-11-51-400-801测试座椅功能。If removed, do the test procedure as specified after the Installation of the Captain/First Officer Seat, (Refer to AMM Task 25-11-51-400-801).2. 如果拆下灯组件，在拆下/安装后要参照AMM Task 33-12-