WOHA33_1035BLNG 3C258_236_EOA33-25-0055

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WOHA331035_236_2581035258TitleCockpit Door Reliability Improvement.Mcd&Rev/厂家工卡&修订日期标题改进驾驶舱门的可靠性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BLNG/3EOA33-25-0055R02客舱/CabinAVIO/ELEC/TRIM01:00/36:00/02:00Baseline/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 A330-25-3516 R01EOA33-HKG25-0028R02Written/编写Reviewed/审核Approved/批准2014-09-252014-09-252014-09-26Accomplished完工签署Complete Date完工日期Station维修站HKGREASON & DESCRIPTION/原因及描述对驾驶舱门的一些部件进行改进，使驾驶舱门组件功能更加可靠。Change some of the cockpit door fittings to make the cockpit door assembly function better. R01版依据SBA330-25-3516R01修改了航材信息和工作步骤。R01 revised material and procedure per SB A330-25-3516R01. R02版， 依据SR:SEMBL-2014-1088349修改航材信息和工作步骤。R02 revised material and procedure refer SR:SEMBL-2014-1088349.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1NSA938361-05CONNECTORAS1BLNG无2NSA934121-01CCONNECTOAS1BLNG无3253516A01R00KITAS1BLNG无4ABS0221HPlacardAS1ALL无5253516D01R02KITAS1ALL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:EOA33-25-0055TITLECockpit Door Reliability Improvement.PerfInsp标题改进驾驶舱门的可靠性工作者检查者警 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. 工作步骤Working steps(1) 改装驾驶舱门锁机构Modify the cockpit door latch mechanism(a)拆下驾驶舱门锁机构盖子Remove the covers of the cockpit door latch mechanism 1 参考Fig. A-GBAAA Sheet 01, View A和AMM Task 52-51-21-000-801拆下下列部件Remove refer to Fig. A-GBAAA Sheet 01, View A and AMM Task 52-51-21-000-801.4 紧固件Fastener Item (4) 保留Retain4 堵头Plug Item (1) 保留Retain4 螺钉Screw Item (2) 保留Retain4 垫片Washer Item (3) 保留Retain1 盖子Cover Item (5) 保留Retain1 盖子Cover Item (6) 保留Retain(b) 拆下中间锁, 更换填隙垫片Remove the center latch of the cockpit door latch mechanism for replacement of distance washers1 参考Fig. A-GBAAA Sheet 01, View A和AMM Task 52-51-21-000-801拆下下列部件Remove refer to Fig. A-GBAAA Sheet 01, View A and AMM Task 52-51-21-000-801.1 中间锁机构Center Latch Mechanism Item (10) 保留Retain4 盖子Cap Item (14) 废弃Discard4 螺钉Screw Item (13) 保留Retain4 垫片Washer Item (12) 保留Retain4 垫片Washer Item (11) 废弃Discard(c) 在中间锁机构中安装新填隙垫片Install the center latch of the cockpit door latch mechanism with new distance washers1参考Fig. A-GBAAA Sheet 01, View C 和 AMM Task 52-51-21-400-801安装下列部件 Install refer to Fig. A-GBAAA Sheet 01, View C and AMM Task 52-51-21-400-801.1 中间锁机构Center Latch Mechanism Item (10) 保留Retained at removal4 垫片Washer NAS1149C0332R Item 114 垫片Washer Item (12) 保留Retained at removal4 螺钉Screw Item (13) 保留Retained at removal4 盖子Cap NSA936603CC0100 Item 142参考AMM Task 52-51-21-400-801调节锁机构Adjust the latch mechanism refer to AMM Task 52-51-21-400-801.(d) 安装驾驶舱门锁盖子Install the covers of the cockpit door latch mechanism1参考Fig. A-GBAAA Sheet 01, View B 和 AMM Task 52-51-21-400-801安装下列部件 Install refer to Fig. A-GBAAA Sheet 01, View B and AMM Task 52-51-21-400-801.4 紧固件Fastener Item (4) 保留Retained at removal4 堵头Plug Item (1) 保留Retained at removal4 螺钉Screw Item (2) 保留Retained at removal4 垫片Washer Item (3) 保留Retained at removal1 盖子Cover Item (5) 保留Retained at removal1 盖子Cover Item (6) 保留Retained at removal(2) 拆下驾驶舱门的限动电门317LG Remove the cockpit door limit switch 317LG(a) 拆下驾驶舱门的限动电门317LGRemove the cockpit door limit switch 317LG1 参考Fig. A-GBBAA Sheet 01, View C ,Fig. A-GWAAA Sheet 01, Fig. A-GHAAA Sheet 01, lines 1 and 3和 AMM Task 52-51-11-000-802拆下下列部件 Remove refer to Fig. A-GBBAA Sheet 01, View C ,Fig. A-GWAAA Sheet 01, Fig. A-GHAAA Sheet 01, lines 1 and 3.and AMM Task 52-51-11-000-802.2 螺钉Screw NAS1102E08-6 Item (21) 废弃Discard1 板Plate A2527532221400 Item (22) 废弃DiscardFIN 317LG1 限动电门Switch-Limit NSA932034-02 Item (20) 废弃Discard(b) 在原有的限动电门孔上安装接线压板 Install a blanking plate to the originated limit switch hole1 参考Fig. A-GBCAA Sheet 01, View C,Fig. A-GWAAA Sheet 01,Fig. A-GHAAA Sheet 01, lines 2 and 4安装下列部件Install refer to Fig. A-GBCAA Sheet 01, View C,Fig. A-GWAAA Sheet 01,Fig. A-GHAAA Sheet 01, lines 2 and 4.1 板Plate F2527645320000 Item 232 螺钉Screw NAS1102E08-6 Item 21(3) 更换驾驶舱门泡沫带Replace the cockpit door foam tape(a) 拆下驾驶舱门泡沫带Remove the cockpit door foam tape1 参考Fig. A-GBDAA Sheet 01拆下下列部件Remove refer to Fig. A-GBDAA Sheet 014 泡沫带Foam Tape Item (25) 废弃Discard(b) 安装驾驶舱门泡沫带 Install the cockpit door foam tape1 参考Fig. A-GBDAA Sheet 01安装下列部件Install refer to Fig. A-GBDAA Sheet 014 泡沫带Foam Tape F2527645200000 Item 25(c) 重新识别驾驶舱门Re-identify the cockpit door1按照附表01件号识别清单，重新识别驾驶舱门。 Re-identify the cockpit door in accordance with the list given in: Appendix 01 - Parts to be re-identified list2参考AMM 11-00-00. Fig. A-GBEAA Sheet 01 View C.填写SB号和驾驶舱门件号。 Fill in a placard with the Service Bulletin number and the new cockpit door part number.Refer to AMM 11-00-00. Fig. A-GBEAA Sheet 01 View C.3所需航材 Use the material:1 标牌Placard-Identification ABS0221H Item 304 按照Fig. A-GBEAA Sheet 01, View B.安装标牌。Install the placard, Item 30, as shown on Fig. A-GBEAA Sheet 01, View B.(4) 改装主设备架821VU和822VU的线路。Modify the wiring in the Main Rack-Shelves 821VU and 822VU.(a) 参考AMM Task 23-73-34-000-801拆下并保留CIDS (FINs 101RH and 102RH)。Remove and retain the CIDS (FINs 101RH and 102RH), refer to AMM Task 23-73-34-000-801.注意： 线路改装完这些计算机还要重新安装。NOTE: These computers have to be installed again after the modification of the wiring.(b)参考Fig. A-FBAAA Sheet 01，ESPM 20-33-00 和 ESPM 20-52-21改装主设备架821VU和822VU的线路。 Modify the wiring in the Main Rack-Shelves 821VU and 822VU: Refer to Fig. A-FBAAA Sheet 01Refer to ESPM 20-33-00 Refer to ESPM 20-52-211 参考线路图Fig. AFWAAA Sheet 01和Fig. A-FHAAA Sheet 01图表中的1-4，改装线路接头。Modify the connections of the wires as shown on the wiring diagram Fig. AFWAAA Sheet 01 and as given in the Hook-up Chart lines:- 1 thru 4, refer to Fig. A-FHAAA Sheet 01, use contacts supplied in:1 线束Bundle F9000095229695(5) 改装右继电器盒752VU和主支架821VU和822VU之间的线路。 Modify the wiring between the RH Relay Box 752VU and the Main Rack-Shelves 821VU and 822VU.(a) 参考图1，安装1504VD。 Installation the 1504VD refer to FIG 1.1.在752VU上安装1504VD。（1504VD：二极管：NSA934121-01C, 底座：NSA938361-05）Installation the 1504VD on 752VU.(FIN 1504VD: Mount diode NSA934121-01C and Connector NSA938361-05 ).2. 修改AMM参考信息“检查压力传感器”的章节是52-51-00-040-807而不是52-51-00-806.Correction of typo AMM reference for the “check of the pressure rate sensor” is 52-51-00-040-807 instead of 52-51-00-806.3. 修改AMM参考信息“操作测试驾驶舱门锁机构”的章节是52-51-21-400-801而不是52-51-00-400-801.Correction of “operational test of the cockpit door latch mechanism”please read 52-51-21-400-801 instead of 52-51-00-400-801.4. 确认堵盖安装在锁扣中心，必须重新安装和使用。Confirmation that the cap on the center latch, needs to be re-used and re-installed.(b) 参考Fig. A-FBAAA Sheet 01，ESPM 20-33-00，ESPM 20-52-21在右继电盒752VU和主支架821VU和822VU之间安装导线。Install the wiring between the RH Relay Box 752VU and the Main Rack-Shelves 821VU and 822VU: Refer to Fig. A-FBAAA Sheet 01 Refer to ESPM 20-33-00 Refer to ESPM 20-52-211 参考线路图Fig. A-FWBAA Sheet 01和Fig. A-FHBAA Sheet 01图表中的1-4，安装线路。Install the wires as shown on the wiring diagram Fig. A-FWBAA Sheet 01 and as given in the Hook-up Chart lines:- 1 thru 4, refer to Fig. A-FHBAA Sheet 01, supplied in:1 线束Bundle F90000952296952 参考ESPM 20-33-44和ESPM 20-25-51安装易拉得卡子。 Attach the wires with: Refer to ESPM 20-33-44 Refer to ESPM 20-25-51150 易拉得Tie-Cable NSA935401-03150 易拉得Tie-Cable NSA935401-053 参考AMM Task 23-73-34-400-801安装CIDS (FINs 101RH and 102RH)。 Install the CIDS (FINs 101RH and 102RH), refer to AMM Task 23-73-34-400-801.注释： 拆下后保存好计算机。NOTE: These computers were retained at removal.(6) 改装右侧继电盒752VU中的设备和线路。Modify the Equipment and the Wiring in the RH Relay Box 752VU.(a) 参考Fig. A-FBAAA Sheet 01 和 Fig. A-FBBAA Sheet 01，AMM 11-00-00, Page Block 201，AMM Task 20-21-11-911-801，AMM Task 20-21-15-912-801，SRM 51-42-00改装右侧继电盒752VU的设备。Modify the equipment in the RH Relay Box 752VU: Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBBAA Sheet 01 Refer to AMM 11-00-00, Page Block 201 Refer to AMM Task 20-21-11-911-801 Refer to AMM Task 20-21-15-912-801 Refer to SRM 51-42-001参考Fig. A-FBBAA Sheet 01和ESPM 20-51-20，AMM Task 20-28-00-912-802在0B009XB位置处安装下列部件。 Install in position 0B009XB: Refer to Fig. A-FBBAA Sheet 01 Refer to ESPM 20-51-20Refer to AMM Task 20-28-00-912-802FIN 18MQ1 继电器Relay E0666D28A0 Item 100FIN 18MQA1 基座Base E0247A0S Item 1011 保持架Retainer-Assy,Relay Base E0427-01 Item 102attach with:1 螺钉Screw NAS1100-04-6 Item 1053 螺母Nut MS21042-04 Item 1042 垫片Washer ASNA2397-3L Item 1032 如图A-FBBAA Sheet 01在18MQ处继电器旁边粘贴标牌。Near the Relay, bond the placards identified 18MQ and the blue placard as shown in Fig. A-FBBAA Sheet 01, supplied in:1 标牌Placard Set F9100095215295(b) 参考Fig. A-FBAAA Sheet 01改装右侧继电盒752VU的线路。Modify the wiring in the RH Relay Box 752VU: Refer to Fig. A-FBAAA Sheet 011 按照线路图A-FWCAA Sheet 01和参考Fig. A-FHCAA Sheet 01表格中1-8安装电线。Install the wires as shown on the wiring diagram Fig. A-FWCAA Sheet 01 and as given in the Hook-up Chart lines:- 1 thru 8, refer to Fig. A-FHCAA Sheet 01, supplied in:1 线束Bundle F90000952296952 参考ESPM 20-33-44和ESPM 20-25-51绑线。Attach the wires with: Refer to ESPM 20-33-44 Refer to ESPM 20-25-51150 易拉得Tie-Cable NSA935401-03150 易拉得Tie-Cable NSA935401-05(7) 改装电子舱和驾驶舱24MQ面板之间的线路。Modify the wiring between the Avionics Compartment and the 24MQ Panel in the Cockpit.(a)参考Fig. A-FBAAA Sheet 01，ESPM 20-33-00，ESPM 20-52-21改装电子舱和驾驶舱24MQ面板之间的线路。 Modify the wiring between the avionics compartment and the 24MQ panel in the cockpit:Refer to Fig. A-FBAAA Sheet 01 Refer to ESPM 20-33-00 Refer to ESPM 20-52-211 如图A-FWDAA Sheet 01和表Fig. A-FHDAA Sheet 01中-1所示拆除电线。Remove the wire as shown on the wiring diagram Fig. A-FWDAA Sheet 01 and as given in the Hook-up Chart line:- 1, refer to Fig. A-FHDAA Sheet 01.2 如图A-FWDAA Sheet 01和表Fig. A-FHDAA Sheet 01中-1所示安装电线。Install the wires as shown on the wiring diagram Fig. A-FWDAA Sheet 01 and as given in the Hook-up Chart lines:- 2 thru 4, refer to Fig. A-FHDAA Sheet 01, supplied in:1 线束Bundle F90000952296953 参考ESPM 20-33-44和ESPM 20-25-51绑线。Attach the wires with: Refer to ESPM 20-33-44 Refer to ESPM 20-25-51300 易拉得Tie-Cable NSA935401-03300 易拉得Tie-Cable NSA935401-05B. 测试TEST(1)通电Energize Electrical Network.(a)按压驾驶舱235VU面板上的下列开关: 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) 拆除警告提示。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) 拆下跳开关卡子关闭跳开关。Remove the safety clips and/or tags and close/unlock these circuit breakers:(2) 工卡253516-700-201-001-测试Subtask 253516-700-201-001 - Test (a) 准备Preparation1 拆下跳开关卡子闭合跳开关。 Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s):(b) 步骤Procedure1 参考AMM Task 52-51-00-400-801对驾驶舱门锁机构操作检查。Do the operational test of the cockpit door latch mechanism (Refer to AMMTask 52-51-00-400-801).2 参考AMM Task 52-51-00-710-801对驶舱门锁系统(CDLS)操作检查。Do the operational test of the cockpit door lock system (CDLS) (Refer to AMMTask 52-51-00-710-801).3 参考AMM Task 52-51-00-710-802操作检查驾驶舱门常规通道。Do the operational test of the cockpit door routine access (Refer to AMM Task52-51-00-710-802).4 参考AMM Task 52-51-00-710-803操作检查驾驶舱门紧急通道。Do the operational test of the cockpit door emergency access (Refer to AMMTask 52-51-00-710-803).5 参考AMM Task 52-51-00-040-806对压率传感器检查。 Do the check of the pressure rate sensor (Refer to AMM Task52-51-00-040-806).(3) 工卡253516-700-001-001-测试Subtask 253516-700-001-001 Testing注 释：测试工作要在所有部件恢复安装后执行。NOTE: This test procedure is to be accomplished after the installation of the equipment removed for access, refer to SUBTASK 253516-942-001 001 Close-up(a) 初步测试Preliminary Test: 注释：如果飞机在CAT III的条件下运行，那么你要参考AMM Task 22-97-00-740-801做LAND CAT III的测试。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 参考ESPM 20-52-20对每个断开的电接头检查。On each connector which was disconnected:- Do the checks as defined by ESPM 20-52-20.注 释：按照ESPM程序中的要求做功能和操作测试。NOTE: The functional test and/or operational test requested by this ESPM procedure is given hereafter.2 参考AMM Task 33-13-00-710-801对仪表和面板的灯光做操作测试。Do the Operational Test of the Instrument and Panel Integral Lighting, refer to AMM Task 33-13-00-710-801.3 参考AMM Task 33-14-00-710-801做灯光测试。Do the Operational Test of Lights, refer to AMM Task 33-14-00-710-801.4 参考AMM Task21-26-00-710-803对电子舱通风系统做操作测试。Do the Operational Test of the Avionics-Equipment Ventilation System , refer to AMM Task 21-26-00-710-803.5 参考AMM Task 22-96-00-740-801做自动飞行系统的自检测试。Do the BITE Test of the Auto Flight System (SYSTEM TEST), refer to AMMTask 22-96-00-740-801.6 参考AMM Task 31-50-00-710-803对ECAM控制面板测试。Do the Operational Test of the Electronic Centralized Aircraft Monitoring(ECAM) Control Panel, refer to AMM Task 31-50-00-710-803.7 参考AMM Task 31-50-00-740-801对飞行警告系统测试。Do the test of the Flight Warning System (FWS), refer to AMM Task 31-50-00-740-801.8 参考AMM Task 31-60-00-710-802对电子仪表系统测试。Do the Operational Test of the Electronic Instrument System (EIS), refer to AMM Task 31-60-00-710-802.(b) 步骤Procedure:1 参考AMM Task 23-73-34-400-801在CIDS安装后按照规定做个测试。Do the test procedure as specified after the installation of the CIDS director, refer to AMM Task 23-73-34-400-801.2 测试设备Test of the equipments:a 对于FINs 1502VD和18MQFor FINs 1502VD and 18MQ:没有 None (covered by equipment test).b 电接头测试(FINs 1181VC, 1524VC, 1526VC, 1528VC, 1534VC, 1734VC, 2542VC)和接线端测试(FINs 980VT ,1052VT, 1500VT and 2600VT)Tests of the connectors (FINs 1181VC, 1524VC, 1526VC, 1528VC, 1534VC, 1734VC, 2542VC) and tests of the terminal blocks (FINs 980VT ,1052VT, 1500VT and 2600VT): 没有None (covered by equipment test).C.结束Close-up(1)工卡253516-942-201-001-结束 Subtask 253516-942-201-001 - Close-up (a) 确保工作区域干净没有任何工具和其它设备。Make sure that the work areas are clean and clear of tools and other items of equipment.(b) 关闭驾驶舱门。Close the cockpit door.(2) 恢复所有为了接近而拆下的部件。 Subtask 253516-41