WOHA33_103136_84_EOA33-52-0008

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WOHA331031_84_36DIC 103136TitleDOORS - AFT CARGO COMPARTMENT DOOR - INSPECT STRUCTURE FOR CRACKS AND LOOSE/LOST/SHEARED RIVETS(REPETITIVE)Mcd&Rev/厂家工卡&修订日期标题检查后货舱门结构裂纹和铆钉松动、丢失或被剪切(重复)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/4EOA33-52-0008R02机身/AirframeMINP39:00Baseline/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 A330-52-3095R00EOA33-HKG52-0010R02500CY500CYWritten/编写Reviewed/审核Approved/批准2014-04-022014-04-142014-04-15Accomplished完工签署Complete Date完工日期Station维修站PVGREASON & DESCRIPTION/原因及描述有几份报告显示后货舱门隔框叉形接头和位于4号梁处的蒙皮发现铆钉开裂、松 动和丢失或被剪切。还有报告称后货舱门隔框头部和位于1号梁处的蒙皮发现铆 钉松动、丢失或被剪切。故下发EO进行检查。There have been several reports of cracks and loose, missing or sheared rivets found on the AFT Cargo Compartment Door Frame Forks and skin in the area of beam No. 4. Loose, missing or sheared rivets have also been reported on the AFT Cargo Compartment Door Frame Heads and skin in the area of beam No.1. So issue this EO to inspect it. R01改版原因：修改工作步骤，适用性中 删除BLNN。Reason for R01: Revise work steps, remove BLNN from the applicability. R02版修改原因Reason for R02 revision:BLNV转租，增加其适用性。Add BLNV to applicability caused by delivered.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198A24403000000CABLE HOLDING STRAPTO1ALL无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198A52008509000SLING-UNIVERSAL DOORSTO1ALL视情/ON CONDITION298A52208001001TOOLS-R/I,COMPARTMENT DOORSTO1ALL视情/ON CONDITION398F52308860000DEVICE-INSERT, BUSHTO1ALL视情/ON CONDITION498F52308859000DEVICE-POSITIONING, FORK AFTTO1ALL视情/ON CONDITION5EKA330523095-1Expendable ToolingTO1ALL视情/ON CONDITION6DKA330523095-1Durable ToolingTO1ALL视情/ON CONDITION7FEIA330523095-1Capital ToolingTO1ALL视情/ON CONDITION8SK2029C221-01LOCKING SHAFT TOOLINGTO1ALL视情/ON CONDITION9SK2030C221-01LATCHING SHAFT TOOLINGTO1ALL视情/ON CONDITIONPARTS 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1MS24665-374PINAS20ALL视情/ON CONDITION2CML09-016SEALANTCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED3MS24665-357PINAS3ALL视情/ON CONDITION4CML11-026SOLVENT GENERAL PURPOSECH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED5CML15-007CORROSION PREVENTIVE TEMPORARY PROTECTIVE COMPOUNDCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED6CML16-002TOPCOAT GREY (INTRNL APPLIC.)CH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED7CML16-001ANTI-CORROSION PRIMER (POLYURETHANE)CH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED8CML05-002Non Hardening Jointing Putty - Medium Temp. AreaCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED9SP108NWASHER KEYAS10ALL视情/ON CONDITION10CML09-013SEALANTCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED11CML16-018Top Coat Polyurethane - CA8000/XXXXCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED12CML04-004GREASECH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED13CML05-052SELF-ADHES. PVC DISKSCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED14CML16-020WASH PRIMER(0434/9000+0841/9000+7641/3600)CH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED15CML13-002CHEMICAL CONVRSN COATING YELLOW ALUMINUMCH1ALL视情、数量按需/ON CONDITION AND QUANTITY AS REQUIRED16NSA5075-6NUTAS322ALL视情/ON CONDITION17EN6114K3-*BOLTAS322ALL视情/ON CONDITION18523095D04R01KITAS1ALL视情/ON CONDITIONIMPORTANT 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:EOA33-52-0008TITLEDOORS - AFT CARGO COMPARTMENT DOOR - INSPECT STRUCTURE FOR CRACKS AND LOOSE/LOST/SHEARED RIVETS(REPETITIVE)PerfInsp标题检查后货舱门结构裂纹和铆钉松动、丢失或被剪切(重复)工作者检查者A. 通用信息/GENERAL警 告：确认遵守所参考手册的所有警告和注意事项。WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.注 意： 遵守使线束和设备处于良好状态的警示信息。当执行设备维护、修理及改装时，尽可能地保持线束、电气设备及工组区域的洁净，执行下述要求：使用如塑料布、布匹等铺盖在上述设备上；经常性的去除线束、电气设备上的杂物及其他污染物。可减少安装电线时的污染和损伤。若污染,参照ESPM20-55-00处理。CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION.THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.备 注：工作步骤中涉及其他AIRBUS文件时，如果使用的是“参照”字样且有其他可接受的替代方法时，该替代方法可以被使用；如果使用的是“按照”字样时，工作者必须使用指定文件中的工作步骤。NOTE: The accomplishment instructions of this EO refer to procedures included in other AIRBUS documents. When the words refer to are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words in accordance with are included in the instruction, the procedure in the AIRBUS document must be used.备 注：在本EO的接近和关闭程序中不包含恢复测试工作，此举不影响本EO技术目的的实现。工作者可灵活的按需增加或减少接近或关闭程序中的步骤，只要满足本EO的技术目的即可。NOTE: The access and close-up instructions, not comprising return to service tests, in this EO do not constitute or affect the technical intent of the EO. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the EO is met within the set parameters. (1) 标准施工/Standard Practices(a) 执行本EO中使用的耗材规范参考CML。For the material specification (Mat No.) given in this EO, refer to Consumable Material List (CML).(b) 飞机区域的识别，参考AMM 06-20-00, Page Block 001。For the identification of zones, refer to AMM 06-20-00, Page Block 001.(c) 接近盖板的识别，参考AMM 06-41-53, Page Block 001。For the identification of access panels, refer to AMM 06-41-00, Page Block 001.(d) 紧固件的加大信息可从SRM 51-43-00获得。Obtain oversize fastener data in accordance with SRM 51-43-00.(e) 紧固件孔直径、钻削和倒角数据可从SRM 51-44-11获得。Obtain fastener hole diameters and drill and deburr data in accordance with SRM 51-44-11.(f) Hi-Lok的紧固扭矩按照SRM 51-49-00。Torque tighten Hi-Lok fasteners in accordance with SRM 51-49-00.(g) 飞机隔框的识别，参考AMM 06-31-53, Page Block 001。For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.(h) 若使用了选择性替代和代用的紧固件，必须按照SRM 51-40-00查找其关联的螺母/collar。In case alternative and substitute fasteners are to be used, you must check that the associated nut/collar are compatible in accordance with SRM 51-40-00.(i) 当本EO指定紧固件的长度不符合SRM 51章的安装标准时，可根据SRM51章的安装要求更换为长度合适的指定类型的紧固件或替代的经固件。另外，可根据SRM51章使用垫片调节经固件的安装长度。If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51.(j) 紧固件的拆除和安装按照SRM 51-42-00。Remove and install fasteners in accordance with SRM 51-42-11.(k) 在钻削前按照SRM 51-47-00检查所有的边距。Check all edge distances before drilling in accordance with SRM 51-47-00.(l) 使用导向钻和钻套钻削原有的孔。Transfer drill existing holes with a pilot drill and drill bush.(m) 钻埋头窝的数据可从SRM 51-46-11获得。Obtain countersinking data in accordance with SRM 51-46-11.(n) 密封胶的清除和安装按照SRM 51-76-11。Do the removal and installation of sealant in accordance with SRM 51-76-11.(o) 加工区域的表面处理按照SRM 51-75-11。For surface protection of reworked areas in accordance with SRM 51-75-12.(p) 按照SRM 51-48-00进行紧固件孔冷拔。Do the cold expansion of fastener holes in accordance with SRM 51-48-00.(q) 密封胶的刷涂按照SRM 51-76-11。Apply and remove sealant in accordance with SRM 51-76-11.(r) 特殊涂层的刷涂按照SRM 51-24-12。Apply special coatings in accordance with SRM 51-24-12.B. 准备/PREPARATION(1) 在执行维护前确保飞机处于以下基本状态下：The following items shall be considered as the basic Aircraft configuration before you start a maintenance task:-飞机在地面上以起落架静止支撑（地面安全锁和轮档在起落架上安装到位）。Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear).- 发动机关车，反推关闭并锁上。Engine shut down, thrust reversers closed and locked.- 飞机外形干净。Aircraft in clean configuration.- 处于停留刹车状态。Parking brake applied.- 飞机电源断开。Aircraft electrical network de-energized.- 液压系统处于减压状态。Hydraulic systems depressurized.- 可接近驾驶舱和客舱。Access to the cockpit and cabin is available.- 所有的断路器处于关闭状态。All circuit breakers are in closed position.- 所有的控制处于常规、自动或者关闭状态。All controls in NORM, AUTO or OFF position. (2) 参考AMM Task 12-34-24-860-802保证飞机接地。Make sure the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802.(3) 在后货舱门下面放置接近平台。Put the access platform below the AFT Cargo Compartment Door.(4) 参考AMM Task 24-42-00-861-801接通地面电源。Energize the ground service network, refer to AMM Task 24-42-00-861-801.(5) 在后货舱门区域拆除接近盖板822AR, 822BR, 822CR和822DR。Remove access panels 822AR, 822BR, 822CR and 822DR from the AFT Cargo Compartment Door.(6) 参考AMM Task 52-32-15-000-801，按需拆除顶板以便接近。Remove the linings as necessary for access to the inspection areas, refer to AMM Task 52-32-15-000-801.C. 施工步骤/PROCEDURE (1) 详细检查后货舱门隔框叉形接头区域Do a Detailed Inspection of the AFT Cargo Compartment Door Frame Fork Areas(a) 按照NTM 51-90-00在下列位置，详细检查4号梁处的后货舱门外蒙皮和隔框叉形接头内表面，看是否存在裂纹，铆钉松动，剪断或丢失，并在后附记录表中记录检查结果：Do a detailed inspection and record of the outer skin and inner surfaces of the AFT Cargo Compartment Door frame forks at beam 4 for cracks, loose, sheared or missing fasteners at the following frame fork locations, , then record the result:隔框 60, 隔框60A, 隔框62, 隔框62A, 隔框63, 隔框63A, 隔框64, 隔框64A, 隔框61 和隔框61A。参考Fig. A-GBBAA Sheet 01, Fig. A-GBCAB Sheet 01和Fig. A-GBDAA Sheet 01。Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A, in accordance with NTM 51-90-00.Refer to Fig. A-GBBAA Sheet 01, Fig. A-GBCAB Sheet 01 and Fig. A-GBDAA Sheet 01.备 注：紧固件头周围有灰暗的污迹说明紧固件松动。对可能松动的紧固件（检查后），有必要去除连接的材料以确认其状况。NOTE: A black or dark grey stain adjacent to or around the fastener head can show a loose fastener. For all fasteners that are possibly loose (after the inspection), it is necessary to make sure that they can move in relation to the attached material to give their condition. 没有发现裂纹或发现松动、受剪切或丢失的紧固件No cracks, loose, sheared or missing fasteners are found 发现裂纹或发现松动、受剪切或丢失的紧固件 A crack is found or there are loose, sheared or missing fasteners.1 如果没有裂纹，松动，受剪切或丢失的紧固件，继续执行步骤“详细检查后货舱门隔框顶部区域”。If no cracks, loose, sheared or missing fasteners are found go to Do a Detailed Inspection of the AFT Cargo Compartment Door Frame Head Areas.2 如果发现裂纹或发现松动、受剪切或丢失的紧固件：If a crack is found or there are loose, sheared or missing fasteners:a 核查相关检查区域内是否存在修理：Do a check of the inspection area for any existing repair. 如果检查区域If the area has: 没有已存在的修理。No existing repair.且/and 隔框叉型接头之前没有更换过。The frame fork has not been replaced previously. 执行步骤“详细检查后货舱门隔框顶部区域”和“特别详细检查后货舱门隔框叉形接头区域”。Go to Do a Detailed Inspection of the AFT Cargo Compartment Door Frame Head Areas and Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Fork Areas . 如果检查区域If the area has: 发现已存在的修理。An existing repair.或/or 隔框叉型接头之前更换过。The frame fork has been replaced previously. 在下个起飞前联系结构工程师索要进一步的修理措施。Contact Structure Engineer for further instructions before next flight.(2) 详细检查后货舱门隔框顶部区域。Do a Detailed Inspection of the AFT Cargo Compartment Door Frame Head Areas(a) 按照NTM 51-90-00详细检查后货舱门1号梁处的以下位置隔框顶部外蒙皮和内部表面的是否有裂纹，紧固件松动，受剪切或丢失情况，并在后附记录表中记录检查结果：Do a Detailed inspection of the outer skin and inner surfaces of the AFT Cargo Compartment Door frame heads area at beam 1 for cracks, loose, sheared or missing fasteners at the following locations, then record the result:隔框 60, 隔框60A, 隔框62, 隔框62A, 隔框63, 隔框63A, 隔框64, 隔框64A, 隔框61 和隔框61A。参考Fig. A-GBBAA Sheet 01, Fig. A-GBFAA Sheet 01, Fig. A-GBGAA Sheet 01和Fig. A-GBHAA Sheet 01。Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A, in accordance with NTM 51-90-00.Refer to Fig. A-GBBAA Sheet 01, Fig. A-GBFAA Sheet 01, Fig. A-GBGAA Sheet 01 and Fig. A-GBHAA Sheet 01. 没有发现裂纹或发现松动、受剪切或丢失的紧固件No cracks, loose, sheared or missing fasteners are found 发现裂纹或发现松动、受剪切或丢失的紧固件 A crack is found or there are loose, sheared or missing fasteners.(b) 如果没有裂纹，松动，受剪切或丢失的紧固件，执行步骤E“结束工作”。If no cracks, loose, sheared or missing fasteners are found, go to STEP E “ CLOSE UP”.(c) 如果发现裂纹或发现松动、受剪切或丢失的紧固件：If a crack is found or there are loose, sheared or missing fasteners:1 核查相关检查区域内是否存在修理：Do a check of the inspection area for an existing repair.a 如果发现已存在的修理或顶部隔框之前更换过，在下个起飞前联系结构工程师索要进一步的修理措施。If the area has an existing repair or the frame head has been replaced previously, contact Structure Engineer for further instructions before next flight.b 若没有已存在的修理，执行步骤“特别详细检查（SDI）后货舱门隔框顶部区域”。 If the area has no existing repair, go to Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Head Areas .(3) 特别详细检查（SDI）后货舱门隔框叉形接头区域Do a Special Detailed Inspection (SDI) of the AFT Cargo Compartment Door Frame Fork Areas注 释(1): Durable工具：参考DKA-A330-52-3095-1。Durable工具包包含完成本EO所需的最少数量的Durable工具。若需在多架飞机上完成本EO，需根据SIL 51-012确定Durable工具包的数量。NOTE (1): Durable tooling: Ref. DKA-A330-52-3095-1. The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the EO on one aircraft. If the EO is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012.注 释(2): Expendable工具：参考EKA-A330-52-3095-1Expendable工具包包含本EO所需数量的Expendable工具。完成本EO的每架飞机订购一个工具包。NOTE (2): Expendable tooling: Ref. EKA-A330-52-3095-1. The expendable tool kit contains the quantity of expendable tools required to accomplish the EO on one aircraft. Order one expendable tool kit for every aircraft on which this EO is to be accomplished.注 释(3): Capital工具：参考FEI-A330-52-3095-1 Capital工具包中的Capital工具不是本EO专用，通常公司已经有存货或者可以向FTI租借。NOTE (3): Capital tooling: Ref. FEI-A330-52-3095-1. The capital tools provided in this kit are not specific to this EO and are normally already available in operators stock as a longterm investment or can be loaned from FTI.注 释(4)：只有发现裂纹或紧固件松动、受剪切或缺失，并且检查区域没有执行过修理或隔框叉形接头没有更换过的情况下，才需要执行此步骤。NOTE (4): Do this subtask on affected frame forks areas if a crack is found or there are any loose, sheared or missing fasteners and the area has no existing repair.(a) 在4号梁隔框 60, 隔框60A, 隔框62, 隔框62A, 隔框63, 隔框63A, 隔框64, 隔框64A, 隔框61 和隔框61A处。参考Fig. A-GBCAB Sheet 01和Fig. A-GBDAA Sheet 01。At beam 4, on: Frame 60, Frame 60A, Frame 61, Frame 61A, Frame 62, Frame 62A, Frame 63, Frame 63A, Frame 64 and Frame 64A.Refer to Fig. A-GBCAB Sheet 01 and Fig. A-GBDAA Sheet 01. 1 拆除指定的紧固件。Remove the fasteners as specified.2 确保紧固件孔干净和顺滑。Make sure the holes are clean and smooth.3 按照NTM Task 51-10-01-250-801对指定的孔执行特别详细检查-旋转探头方法（程序A）。Do the Special Detailed Inspection - rotating probe method (procedure A) on the specified holes in accordance with NTM Task 51-10-01-250-801. 没有发现裂纹No cracks. 蒙皮上发现裂纹 A crack is found on the skin. 隔框叉形接头上发现裂纹 A crack is found on the frame fork.a 若没发现裂纹：If no crack is found: 对紧固件孔冷拔后安装新的紧固件。Replace the fasteners after cold expansion of the holes.b 若蒙皮上发现裂纹：If a crack is found on the skin: 在下个起飞前联系结构工程师。Contact Structure Engineer before next flight.或/or 更换后货舱门，参照AMM Task 52-32-11-000-801和A