WOHA33_2422256_622_EOA33-53-0030

Hong Kong Airlines Limited香港航空有限公司03110-01Hong Kong Airlines MEDHong Kong Airlines LimitedWO NO/工作指令号SEQ NO/序列号WOHA332422_622_256重要修理/改装 适航指令(AD) DIC 2422256TitleFuselage - Forward Fuselage - Reinforce Circumferential Joint at FR 31 Between Stringer 7LH And Stringer 8RHMcd&Rev/厂家工卡&修订日期标题机身-前机身-FR31 STGR 7LH-STGR 8RH之间环向对接带加强改装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BLNX/1EOA33-53-0030R01机身/AirframeSMTI /PNT /NDT40:00/04:00/04:00Baseline/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 A330-53-3244R01,AD EASA 2016-0207,CAD CAD 2016-A330-01EOA33-HKG53-0018R01Written/编写Reviewed/审核Approved/批准2016-12-022016-12-092016-12-11Accomplished完工签署Complete Date完工日期Station维修站PVGREASON & DESCRIPTION/原因及描述随着广布疲劳损伤分析（WFD）,已证明有些区域在达到设计使用时限前需做加强。位于FR31 STGR 7LH-STGR 8RH之间的环向对接带已确定属于需加强的区域。为了增加此环向对接带（FR31 STGR 7LH-STGR 8RH）的结构使用寿命，下发EO对此环向对接带进行加强。Following Widespread Fatigue Damage (WFD) analysis, it has been demonstrated that some areas require reinforcement before reaching the Design Service Goal (DSG). The circumferential joint at Frame (FR)31 between Stringer (STGR)7 LH and STGR8 RH has been identified as such an area.For extend the structural life of the circumferential joint at Frame (FR)31 between Stringer (STGR)7 LH and STGR8 RH,issue EO to reinforce this circumferential join. R01版改版 原因/Reason of R01 revision：1、将此EO升级为AD控制。Update this EO to AD control.2、依据A330-53-3244R01修改施工步骤。Revise the work instructions in according with A330-53-3244R01.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1FTIA330533243-1Capital toolingTO1ALLN/A2DKA330533244-1Durable ToolingTO1ALL参考Figure A-GBBAA - Sheet 05/refer to Figure A-GBBAA - Sheet 053EKA330533244-1Expendable toolingTO1ALLN/ATOOLS 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1CML06AAC1INTERFAY SEALANTCH1ALL数量按需/Quantities As Required2CML08BAA9SOLVENT GENERAL PURPOSECH1ALL数量按需/Quantities As Required3CML14SBA1CLEANING ABSORCH1ALL数量按需/Quantities As Required4CML06AAA1SEALANTCH1ALL数量按需/Quantities As Required5CML12ADB1ANTICORROSIONCH1ALL数量按需/Quantities As Required6CML04EAC2ANTI-CORROSION PRIMER (POLYURETHANE)CH1ALL数量按需/quantity as required7CML04JAA3Top Coat Polyurethane - CA8000/XXXXCH1ALL数量按需/Quantities As Required8CML04CMA2WASH PRIMER(0434/9000+0841/9000+7641/3600)(Metaflex FCR Pri)CH1ALL数量按需/Quantity as required9533244D01R00KITAS1ALL1EAPARTS 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,D.101131* HKE Approval No: AI /218/1215, JMM 133 * Other: * Signature:_ Authorization No.:_ Date:_工卡Job card:EOA33-53-0030TITLEFuselage - Forward Fuselage - Reinforce Circumferential Joint at FR 31 Between Stringer 7LH And Stringer 8RHPerfInsp标题机身-前机身-FR31 STGR 7LH-STGR 8RH之间环向对接带加强改装工作者检查者警 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符合要求的状态的警示信息。当执行设备维护、修理及改装时，始终保持线束、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；经常性的清除线束、电气设备上的杂物及其他污染物。这些预防措施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 WIRINGIN 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.注 释：本EO中的施工步骤参考了包含在其他空客文件中的步骤。当出现“参考”字样时，工作者可以使用可接受的替代步骤。当出现“按照”的字样时，必须按照空客文件中的步骤执行。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.注 释：接近和关闭步骤不包含返回使用测试，在本EO中，不构成或影响本EO的技术意图。因此，只要本EO的技术意图符合设定的参数，工作者可以视情况忽略或增加接近和/或关闭步骤以增加维修工作的灵活性。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.注释：报废的部件必须按照运营人的规定妥善处理。NOTE: Discarded parts must be managed at the operators discretion.注释：此EO包含的飞机维护指南必须确保飞机的可持续性适航要求。对于此EO所包含的指南有任何偏离，联系空客获取下一步的指南和批准。NOTE: This EO contains the instructions for the on-aircraft maintenance necessary to ensure the continued airworthiness of the aircraft.For any deviations to the instructions contained herein, contact Airbus for further instructions and approval.A. 标准施工/Standard Practices1. 对于EO中的化工品标准，参考CML手册。For the specification of materials (Mat. No.) given in this EO, refer to Consumable Materials List (CML).2. 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 001.3. 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 001.4. 接近盖板识别，参考AMM 06-41-53, Page Block 001。For the identification of access panels, refer to AMM 06-41-53, Page Block 001.5. 紧固件拆装，参考SRM 51-42-00。Remove and install fasteners in accordance with SRM 51-42-00.6. 紧固件孔冷拔按照SRM 51-48-00。Do the cold working of fastener holes in accordance with SRM 51-48-00.7. 按照SRM 51-44-11获取紧固件孔直径和钻孔及去毛刺的数据。Obtain fastener hole diameters and drill and deburr data in accordance with SRM 51-44-11.8. 对金属结构划窝，按照SRM 51-46-11。Do the countersinking of metallic structure in accordance with SRM 51-46-11.9. 对设备、结构和所有零件进行保护以避免损伤。Protect the areas to prevent damage to the equipment and structure and all the parts.10. 密封胶的使用，按照SRM 51-76-11 和SRM 51-24-00。Apply sealant in accordance with SRM 51-76-11 and SRM 51-24-00.11. 参考AMM Task 20-21-11-911-001拧紧标准螺纹紧固件。To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001.12. 紧固件的互换和替换，根据SRM 51-43-00。Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.13. 如果有紧固件选择和替代，必须按照SRM 51-40-00 Mating Part栏确认相关的螺母/螺帽是否匹配。If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 Mating Partcolumn.14. 假如本EO规定的紧固件长度不符合SRM 51章的安装要求，则可以使用符合SRM 51章安装要求的相同规范或已批准的替代件。另外，按照SRM 51章对紧固件的长度使用垫圈。If the length of any fastener specified in this EO 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 51.15. 将拆下的保留件放进有标识的塑料袋中并系在相应部件上。Put all the retained hardware in identified plastic bags and attach the bags to the related unit.16. 保护跳开关的措施，参考AMM Task 20-16-00-912-801。For circuit breaker safety precautions, refer to AMM Task 20-16-00-912-801.17. 恢复漆层，参考SRM 51-75-12。Renew the protective finish in accordance with SRM 51-75-12.18. 在必须拆下的部件上挂上挂签以使后续安装更容易。Tag all the parts you must remove and retain to make the subsequent installation easier.B. 施工准备/PREPARATION1. 工作准备/Job Set-up注释：在开始维护检查前，如下的项目必须作为基本飞机构型加以考虑：- 飞机地面停放在起落架上（起落架安全销和轮挡必须在起落架上安装到位）- 发动机关车，反推关闭并锁定- 飞机处于空机状态- 设置停留刹车- 飞机电路关断- 液压系统卸压- 到驾驶舱和客舱的接近门可用- 所有跳开关在闭合位置- 所有控制器在NORM, AUTO或OFF位置NOTE: The items given in this note 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 the wheel 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.a. 确保飞机静电接地，参考AMM Task 12-34-24-860-802。Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802.b. 对飞机放油，参考AMM Task 12-11-28-650-801。Defuel the aircraft, refer to AMM Task 12-11-28-650-801.c. 遵守一般的飞机顶升说明,按照SRM 51-51-00。Obey the general jacking instructions in accordance with SRM 51-51-00.d. 遵守飞机的顶升步骤，参考AMM Task 07-11-00-581-801。Obey the maintenance jacking procedure, refer to AMM Task 07-11-00-581-801.e. 执行附件02的顶升程序，是为了安装外部对接带加强件。For the jacking procedure for the installation of the external joint reinforcement straps, refer to Appendix 02 .f. 在FR31 STGR7LH到STGR8RH之间的修理区域放置接近平台。Put an access platform in position at FR31 between STGR7 LH and STGR8 RH.C. 步骤/PROCEDURE注 意：以下施工步骤必须按顺序执行，不能同时施工。这是为了防止对飞机造成损伤。CAUTION: THE FOLLOWING SUBTASKS MUST BE PERFORMED SEQUENTIALLY AND NOT CONCURRENTLY. THIS IS TO PREVENT DAMAGE TO THE AIRCRAFT.注 释：本EO中描述的步骤只有在相同区域事先没有执行过空客修理/修理改进的情况下才能执行。万一发现先前的修理，联系结构工程师获取进一步的指导。NOTE: The procedure as described in this EO is to be performed if no AIRBUS repair and/or repair improvement has been previously performed in the same area. In case of repairs performed previously, please contact structure engineer for further instructions.1. 在环向对接带FR31 STGR7 LH 和STGR8 RH 之间，拆除紧固件。Remove Fasteners from the Circumferential Joint atFR31 between STGR7 LH and STGR8 RH.a. 在环向对接带FR31，STGR7 LH 和STGR8 RH 之间，把下列加强件临时放置到对应的位置上，并在机身蒙皮上画出轮廓线。参考Fig. A-GBAAA Sheet 01,Fig. A-GBAAA Sheet 02 和 Fig. A-GBAAA Sheet 03。At FR31, between STGR7 LH and STGR8 RH, refer to Fig. A-GBAAA Sheet 01,Fig. A-GBAAA Sheet 02 and Fig. A-GBAAA Sheet 03, temporarily put these items in position and mark the outline on the fuselage skin. b. 拆除临时放置在机身上的加强件。Remove the items that were temporarily put in position.c. 在机身改装区域，用蜡笔标示出必须拆除的紧固件。Identify the fasteners that must be removed in the modification area with a wax pencil.d. 在FR31 STGR7 LH 和STGR8 RH 之间，参考Fig. A-GBAAA Sheet 01, Fig. A-GBAAA Sheet 02 和 Fig. A-GBAAA Sheet 03，拆除以下部件：At FR31, between STGR7 LH and STGR8 RH, refer to Fig. A-GBAAA Sheet 01, Fig. A-GBAAA Sheet 02 and Fig. A-GBAAA Sheet 03, remove:695 Rivet/铆钉 Discard/报废注 释：小心不能损伤到紧固件孔。NOTE: Be careful not to damage the holes.e. 使用以下航材清洁紧固件孔：Clean the fastener holes with:Textile - Lint Free Cotton 14SBA1 As required/按需made moist with/蘸Non Aqueous Cleaner General 08BAA9 As required/按需2. 在FR31 STGR7 LH 和STGR8 RH 之间，通过旋转探头检查紧固件孔。Inspect Fastener Holes at FR31 between STGR7 LH and STGR8 RH by Rotating Probe Testinga. 在FR31 STGR7 LH 和STGR8 RH 之间，检查所有受影响紧固件孔的直径，参考Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02, Fig. A-GBBAA Sheet 03, Fig. A-GBCAA Sheet 01, Fig. A-GBCAA Sheet 02,Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 和 Fig. A-GBCAA Sheet 05.At FR31, between STGR7 LH and STGR8 RH, do a check of the diameter of all the affected fastener holes, refer to Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02, Fig. A-GBBAA Sheet 03, Fig. A-GBCAA Sheet 01, Fig. A-GBCAA Sheet 02,Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBCAA Sheet 05.1) 确认紧固件孔直径不等于或大于最大的初始孔直径。Make sure that the hole diameter is not equal to or more than the maximum starting hole diameter.紧固件孔直径是否不大于或等于最大的初始孔直径：If hole diameter is not equal to or more than the maximum starting hole diameter：是/YES 否/NO 2) 如果紧固件孔直径等于或大于最大的初始孔直径，在执行下个步骤前联系结构工程师。If the hole diameter is equal to or more than the maximum starting hole diameter, contact structure engineer before the next step.(1). 如果紧固件孔直径不等于或不大于最大的初始孔直径，执行下一步。If the hole diameter is not equal to or more than the maximum starting hole diameter, do the next step.b. 在FR31，STGR7 LH 和STGR8 RH 之间，用旋转探头检查所有受影响的紧固件孔，参考NTM Task 51-10-01-250-801。At FR31, between STGR7 LH and STGR8 RH, do a rotating probe test of all the affected fastener holes, refer to NTM Task 51-10-01-250-801.1) 假如发现裂纹，联系结构工程师。If cracks are detected, contact structure engineer.是否发现裂纹/Cracks are detected or not:是/YES 否/NO 2) 假如未发现裂纹，执行下一步。If no cracks are detected, do the next step.3. 在FR31 STGR7 LH和STGR8 RH之间环向对接带的外搭接带、楔形件和填片，改装紧固件孔。Modify the Fastener Holes of the External Strap, Wedges and Shim at Circumferential Joint FR31 between STGR7 LH and STGR8 RHa. 在FR31 STGR7 LH和STGR8 RH之间，把下列加强件临时放置在机身蒙皮，参考Fig. A-GBBAA Sheet 01。At FR31, between STGR7 LH and STGR8 RH, refer to Fig. A-GBBAA Sheet 01, temporarily put these items in position on the outer fuselage skin.b. 把旧孔引到加强件上。Transfer drill the existing fastener holes.注 释：在这一步骤，不能把孔铰到最终直径。NOTE: Do not ream the holes to the final diameter at this step.注 释:确保紧固件孔的边距满足SRM 51-47-00的要求NOTE: Make sure that the edge distance of the fasteners is in accordance with SRM 51-47-00.c. 拆除加强件、间隙片和楔形件，并对紧固件孔去毛刺和清洁。Remove the doublers, shims and wedges, de-burr and clean.d. 把下列加强件放置到对应的位置上：Put these items in position:注 释：为避免对接带的移动，按需临时安装紧固件。NOTE: Install temporary fasteners as necessary to prevent strap movement.e. 在FR31 STGR7 LH 和 STGR8 RH 之间，冷拔紧固件孔，依据SRM 51-48-00，参考Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02, Fig. A-GBBAA Sheet 03。At FR31, between STGR7 LH and STGR8 RH, do the cold working of the fastener holes, refer to Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02, Fig. A-GBBAA Sheet 03,and in accordance with SRM 51-48-00.(1). 参考Fig. AGBBAA Sheet 03，将紧固件孔扩大至初始孔直径，使用FTI工具：Oversize the fastener holes to the starting hole diameter, refer to Fig. AGBBAA Sheet 03, use FTI tool list No.:DKA330533244-1 Durable tooling 1(2). 清洁钻孔区域，使用：Clean the drilled area with:Textile - Lint Free Cotton 14SBA1 As required/按需made moist with/蘸Non Aqueous Cleaner General 08BAA9 As required/按需(3). 对紧固件孔进行冷拔，使用FTI工具：Do the cold working of the fastener holes, use FTI tool list No.:注 释：套筒的开口缝隙须背离蒙皮边缘或长桁端头。NOTE: Insert the sleeves with the slot turned away from edge of skin or end of stringer.(4). 拆除套筒。Remove the split sleeves.(5). 清洁钻孔区域，使用：Clean the drilled area with:Textile - Lint Free Cotton 14SBA1 As required/按需made moist with/蘸Non Aqueous Cleaner General 08BAA9 As required/按需(6). 将紧固件孔铰至Fig. A-GBBAA Sheet 03所示的最终直径用，用FTI工具：Ream the fastener holes to the final hole diameter given in Fig. A-GBBAA Sheet 03, use FTI tool list No.:DKA330533244-1 Durable tooling 1(7). 对加强带上的紧固件孔划窝。Countersink fastener holes in the strap.(8). 对没被加强带覆盖的紧固件孔划窝。Countersink reused fastener holes in the skin not covered by the strap.(9). 用下列材料清洁紧固件孔。Clean the fastener holes with:Textile - Lint Free Cotton 14SBA1 As required/按需made moist with/蘸Non Aqueous Cleaner General 08BAA9 As required/按需(10). 依据SRM 51-75-12，恢复紧固件孔保护层，