blis243_232_eoa33-25-0055 - r04

1、EOA33-25-0055 R04 2014-10-271 / 48页码，Hong Kong Airlines Limited航空03110-01Hong Kong Airlines MEDHong Kong Airlines LimitedWO NO/工作指令号 1052SEQ NO/序列号 243WOHA331052_232_243TitleCockpit 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 S

2、kill/工种 Man Hour/工时 BLNE/3EOA33-25-0055R04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 A330-25-3516R01EOA33-HKG25-0028R04Written/编写 2014-10-27Reviewed/审核 2014-10-27Approved/批准 2014-10-27Accomplished完工签署 Complete Date完工日

3、期 Station维修站 SHAREASON & 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

4、和工作步骤。R02 revised material and procedure refer SR:SEMBL-2014-1088349. R03 版修改了工作步骤。 R03 revised procedure. R04 版修改了工作步骤。 R04 revised procedure.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 QT

5、Y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 1NSA938361-05CONNECTORAS1B

6、LNE无 2NSA934121-01CCONNECTOAS1BLNE无 EOA33-25-0055 R04 2014-10-272 / 48页码，3253516A01R00KITAS1BLNE无 4ABS0221HPlacardAS1ALL无 5253516D01R02KITAS1ALL无 PARTS AND MATERIALIF NECESSARY/视情航材ITEMP/NDESCRIPTIONEQTPQTYAPPConditions note项目件号名称类型数量适用性互换信息及备注 IMPORTANT NOTE: In the event of any discrepancies betwe

7、en 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 s

8、pecified, except as otherwise specified, was carried out in accordance with HKAR-145 and 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*

9、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: *

10、Signature: Authorization No.: Date: EOA33-25-0055 R04 2014-10-273 / 48页码，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 CAUTIONS INCLUDED IN THE REFERENCED PROCED

11、URES.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 mechanism1 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Fastene

12、rItem (4)保留Retain4堵头PlugItem (1)保留Retain4螺钉ScrewItem (2)保留Retain4垫片WasherItem (3)保留Retain1盖子CoverItem (5)保留Retain1盖子CoverItem (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 52-51-2

13、1-000-801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 MechanismItem (10)保留Retain4盖子CapItem (14)废弃Discard4螺钉ScrewItem (13)保留Retain4垫片WasherItem (12)保留Retain4垫片WasherItem (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 doo

14、r 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 EOA33-25-0055 R04 2014-10-274 / 48页码，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 Install refer to Fig. A-GBAAA Sheet 01, View C and AMM T

15、ask 52-51-21-400-801.1中间锁机构Center Latch MechanismItem (10)保留Retained at removal4垫片Washer NAS1149C0332RItem 114垫片WasherItem (12)保留Retained at removal4螺钉ScrewItem (13)保留Retained at removal4盖子Cap NSA936603CC0100Item 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-

16、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FastenerItem (4)保留Retained at removal4 堵 头PlugItem (1)保留Retained at remov

17、al4 螺 钉ScrewItem (2)保留Retained at removal4 垫 片WasherItem (3)保留Retained at removal1 盖 子CoverItem (5)保留Retained at removal1 盖 子CoverItem (6)保留Retained at removal(2) 拆下驾驶舱门的限动电门317LGRemove 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

18、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ScrewNAS1102E08-6Item (21)废弃Discard1板PlateA252753

19、2221400Item (22)废弃Discard FIN 317LG1限动电门Switch-LimitNSA932034-02Item (20)废弃DiscardEOA33-25-0055 R04 2014-10-275 / 48页码，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 (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

20、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PlateF2527645320000Item 232螺钉Screw NAS1102E08-6Item 21(3) 更换驾驶舱门泡沫带 Replace the cockpit door foa

21、m 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 TapeItem (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 TapeF2527645200000Item

22、 25(c) 重新识别驾驶舱门 Re-identify the cockpit door1按照附表01件号识别，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 listEOA33-25-0055 R04 2014-10-276 / 48页码，工卡 Job card:EOA33-25-0055TITLECockpit Door Reliability Improvement.PerfInsp标题 改进驾驶舱门的可

23、靠性 工作者 检查者 2参考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 ABS0221HItem 304 按照Fig. A-GBEAA Sheet 0

24、1, 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 AM

25、M 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 0

26、1 Refer 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 supp

27、lied in: 1线束BundleF9000095229695(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.EOA33-25-0055 R04 2014-10-277 / 48页码，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 (a) 参

28、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 typ

29、o AMM reference for the “check of the pressure rate sensor” is52-51-00-040-807 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.

30、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

31、. 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B

32、undle 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 NSA935401-05EOA33-25-0055 R04 2014-10-278 / 48页码，工卡 Job card:EOA33-25-0055TITLECockpit Door Reliability Improvement.PerfInsp标题 改

33、进驾驶舱门的可靠性 工作者 检查者 3 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 752

34、VU.(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

35、 Block 201 Refer to AMM Task20-21-11-911-801 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 20-51-20 Refer to AMM Task 20-28-00-912-8

36、02FIN 18MQ1继电器Relay E0666D28A0Item 100 FIN 18MQA1基座BaseE0247A0SItem 1011保持架Retainer-Assy,Relay Base E0427-01Item 102 attach with:1螺钉Screw NAS1100-04-6Item 1053螺母Nut MS21042-04Item 1042垫片Washer ASNA2397-3LItem 1032 如图A-FBBAA Sheet 01在18MQ处继电器旁边粘贴标牌。 EOA33-25-0055 R04 2014-10-279 / 48页码，工卡 Job card:EO

37、A33-25-0055TITLECockpit Door Reliability Improvement.PerfInsp标题 改进驾驶舱门的可靠性 工作者 检查者 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 SetF9100095215295(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

38、 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BundleF90000952296952 参

39、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

40、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 d

41、iagram 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-FHD

42、AA Sheet 01, supplied in:1线束BundleF9000095229695EOA33-25-0055 R04 2014-10-2710 / 48页码，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 3 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-Cabl

43、e 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 24-41-00-86

44、1-801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 cli

45、p(s) and/or tag(s) and close/unlock this (these) circuit breaker(s):(b) 步骤 Procedure1 参考AMM Task 52-51-21-400-801对驾驶舱门锁机构操作检查。 Do the operational test of the cockpit door latch mechanism (Refer to AMM Task 52-51-21-400-801).2 参考AMM Task 52-51-00-710-801对驶舱门锁系统(CDLS)操作检查。 EOA33-25-0055 R04 2014-10-27

46、11 / 48页码，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 Do the operational test of the cockpit door lock system (CDLS) (Refer to AMM Task 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 routin

47、e access (Refer to AMM Task 52-51-00-710-802).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 AMM Task 52-51-00-710-803).5 参考AMM Task 52-51-00-040-807对压率传感器检查。 Do the check of the pressure rate sensor (Refer to AMM Task 52-51-00-040-8

48、07).(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 T

49、ask 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 20-52-2

50、0.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-

51、00-710-801做灯光测试。 Do the Operational Test of Lights, refer to AMM Task 33-14-00-710-801.EOA33-25-0055 R04 2014-10-2712 / 48页码，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 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 Avio

52、nics-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 AMM Task 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 Centraliz

53、ed 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 Syst

54、em (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18MQ For FINs 1502VD and 18MQ:没有 None (covered by equipment test).b