WOHA33_2632232_627_EOA33-53-0050

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WOHA332632_627_2322632232TitleFuselage - Center Fuselage - Optimise Belly Fairing Lateral Frame 53.2Mcd&Rev/厂家工卡&修订日期标题机身-中机身-机腹整流罩侧向53.2隔框优化改装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BLNV/9EOA33-53-0050R05机身/AirframeSMTL /AIRP32:00/08:00Baseline/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 A330-53-3253/R00EOA33-HKG53-0036R03Written/编写Reviewed/审核Approved/批准2016-11-252016-11-292016-11-29Accomplished完工签署Complete Date完工日期Station维修站PVGREASON & DESCRIPTION/原因及描述在例行维护期间，在A330飞机机腹整流罩辅助结构53.2隔框处的侧向隔框位置发现多起损伤。在大多数情况下，位于中央开口区域（左侧和右侧）的53.2隔框位置的机腹整流罩侧向隔框翻边发现有裂纹。故下发本EO使用增强设计的新构型隔框更换53.2隔框处机腹整流罩侧向隔框(左、右侧)，以保持机腹整流罩53.2处隔框的结构完整性。Several damages have been detected during routine maintenance task, on A330 belly fairing sub structure, on the lateral frame at Frame 53.2. In most of the cases, the Frame 53.2 belly fairing lateral frame inner flange has been found cracked in central cut-out area (LH and RH sides). So issue this EO to replace the Frame 53.2 belly fairing lateral frame (LH and RH sides) by a new shaped one with enhanced design to maintain the structural integrity of the belly fairing Frame 53.2.R01改版原因/Reason for R01：1.根据SBIT-15-0107 Rev 00，修改索赔信息。Revise WARRANTY INFO refer to SBIT-15-0107 Rev 00.2.增加飞机BLNQ的适用性。Add the appicability of BLNQ. R02改版原因/Reason for R02：飞机转租，增加BLNN飞机的适用性。Add the applicability of A/C BLNN due to aircraft sublease.R03改版原因/Reason for R03：二手飞机引进，增加BLNR,BLNS,BLNT,BLNU飞机的适用性。Add the applicability of A/Cs BLNR,BLNS,BLNT,BLNU due to used aircrafts delivery.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1CML06AAB1SEALANTCH1ALL数量按需/Quantity as required2CML04TMB2primerCH1ALL数量按需/Quantity as required3CML06AAC1INTERFAY SEALANTCH1ALL数量按需/Quantity as required4CML08BAA9SOLVENT GENERAL PURPOSECH1ALL数量按需/Quantity as required5CML06AAA1SEALANTCH1ALL数量按需/Quantity as required6CML10ABC1CHEMICAL CONVRSN COATING YELLOW ALUMINUMCH1ALL数量按需/Quantity as required7CML12ADB1ANTICORROSIONCH1ALL数量按需/Quantity as required8CML04EAC2ANTI-CORROSION PRIMER (POLYURETHANE)CH1ALL数量按需/Quantity as required9CML04JAA3Top Coat Polyurethane - CA8000/XXXXCH1ALL数量按需/Quantity as required10533253A01R00KITAS1ALLN/A11533253A02R00KITAS1ALLN/APARTS 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 * HKE Approval No: AI /218/1215, JMM 133 * HNAT Approval No.: D.101115, JMM 047* CASL Approval No: AI / 101 / 798 * AMECO Approval No.: D.101131, JMM 001* HNAT- North West Approval No.: D.500023, JMM 049 * HAECO Approval No: DAI / 1 / 853 * SMECO Approval No.: D.400009, JMM 081* HNAT- YN Approval No.: D.4108, JMM 134 * TAECO Approval No.: DAI / 89 / 1295 * CEA Approval No.: D.200002, JMM 112 * HNAT Approval No.: D.3039, JMM 076 * THAECO Approval No.: D.101661, JMM 124 * CEA-Jiangsu Approval No.: D.200047, JMM 117 * SPRING Approval No.: D.200081, JMM 121 * SIAEC Approval No: AWI / 01 * STARCO Approval No.: D.200078,JMM 039* GAMECO Approval No.: D.300001, JMM 006* THAI Approval No.: AI / 147 / 0910 * Other: * Signature:_ Authorization No.:_ Date:_工卡Job card:EOA33-53-0050TITLEFuselage - Center Fuselage - Optimise Belly Fairing Lateral Frame 53.2PerfInsp标题机身-中机身-机腹整流罩侧向53.2隔框优化改装工作者检查者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；定期的去除线束、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 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.注 释： “参考”部分的内容可以用等效的认可程序替代。但“按照”部分必须遵守。NOTE: When the words refer to are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words in accordance with are used then the given procedure must be followed.注 释： 接近和恢复说明不包括恢复至可用状态的测试，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： 施工步骤内的手册标题为缩略词。NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Aircraft Maintenance Manual (AMM)Consumable Material List (CML)ATA Common Support Data Dictionary (CSDD),Chapter 2Elec. Std. Practices Manual (ESPM)Standards Manual (SM)B. 标准施工/Standard Practices1. 本EO的材料规范参考CML。For the specification of materials (Mat. No.) given in this EO, refer to Consumable Material List (CML).2. 飞机隔框识别参考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. 飞机接近盖板识别参考AMM 06-41-53, Page Block 001。For the identification of access panels, refer to AMM 06-41-53, Page Block 001.5. 标准螺纹紧固件的拧紧力矩参考AMM Task 20-21-11-911-801。To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.6. 紧固件的拆除和安装按照SRM 51-42-00。Remove and install fasteners in accordance with SRM 51-42-00.7. 密封胶的刷涂按照SRM 51-24-00。Apply sealant in accordance with SRM 51-24-00.8. 重新恢复表面保护涂层按照SRM 51-75-12。Renew the protective finish in accordance with SRM 51-75-12.9. 钻孔及紧固件孔直径按照SRM 51-44-00。Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.10. 参考ESPM 20-51-20和AMM Task 20-28-00-912-801关于接合。For the electrical bonding, refer to ESPM 20-51-20 and AMM Task 20-28-00-912-801.11. 紧固件的替代信息按照SRM 51-43-00。Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.12. 若必须使用紧固件的替代，必须保证按照SRM 51-40-00配套件栏相应的螺帽/虎克帽相匹配。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 Part column.13. 若本EO中指定的紧固件长度不符合SRM51章中的安装标准，可使用相同规格的或批准替代的长度符合SRM51章安装标准的紧固件。此外，按照SRM51章根据紧固件夹紧长度安装垫片。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 51.14. 按照SRM 51-47-00遵守紧固件的间距和边距要求。Respect Fastener Spacing and Margin data in accordance SRM 51-47-00.15. 剪切铆钉至需要的长度。Cut the rivets to the necessary length.C. 施工准备/PREPARATION1. 工作准备/Job Set-up注 释：在开始维护检查前，本注释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（起落架地面安全销以及机轮轮挡在位）-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-驾驶舱和客舱可接近-所有电路跳开关处于闭合位置-所有控制器在正常、自动或关断位置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. 参考AMM Task 12-34-34-860-802确保飞机已接地。Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-34-860-802.b. 在飞机147和148区域放置接近平台。Put an access platform in position at zones 147 and 148.2. 拆除/打开接近左侧 Remove/Open for Access LH Sidea. 参考AMM Task 32-12-00-010-801打开主起落架门734。Open the Main Land Gear door 734, refer to AMM Task 32-12-00-010-801.b. 参考AMM Task 53-36-41-000-801拆除53.2隔框处的挡板。Remove the Baffles at Frame 53.2, refer to AMM Task 53-36-41-000-801.c. 如果需要，参考AMM Task 53-35-13-000-801拆除197EB接近面板。If necessary, remove the Access-Panel 197EB, refer to AMM Task 53-35-13-000-801.d. 如果需要，参考AMM Task 53-35-11-000-801拆除147BB翼身整流罩。If necessary, remove the Wing-to-Fuselage Fairing 147BB, refer to AMM Task 53-35-11-000-801.3. 拆除/打开接近右侧 Remove/Open for Access RH Sidea. 参考AMM Task 32-12-00-010-801打开主起落架门744。Open the Main Land Gear door 744, refer to AMM Task 32-12-00-010-801.b. 参考AMM Task 53-36-41-000-801拆除53.2隔框处的挡板。Remove the Baffles at Frame 53.2, refer to AMM Task 53-36-41-000-801.c. 如果需要，参考AMM Task 53-35-13-000-801拆除198EB接近面板。If necessary, remove the Access-Panel 198EB, refer to AMM Task 53-35-13-000-801.d. 如果需要，参考AMM Task 53-35-11-000-801拆除148BB翼身整流罩。If necessary, remove the Wing-to-Fuselage Fairing 148BB, refer to AMM Task 53-35-11-000-801. D. 施工步骤/PROCEDURE1. 拆除左侧的机腹整流罩53.2侧向隔框Remove the Belly Fairing Lateral Frame 53.2 on LH Side警 告：保证连杆及接头在位以保持位置。WARNING: LET THE ROD AND THE FITTING IN PLACE TO KEEP THE POSITION.a. 参考Fig. A-FBAAB，按照SRM 51-42-00拆下左侧机腹整流罩53.2侧向隔框。Remove the belly fairing lateral Frame 53.2 on LH side，Refer to Fig. A-FBAAB，In accordance with SRM 51-42-00.注 释：拆除项目（1）接头，需要拆除并保留机腹整流罩面板上的14颗螺钉和垫片。NOTE: To remove the Fitting Item (1), it is necessary to remove and retain the 14 Bolts and Washers from the Belly Fairing Panels.1 Fitting F5331736220000 Item (1) DiscardAttached with:13 Rivet Item (3) Discard29 Rivet Item (4) Discard29 Bush Item (5) Discard注 释：使用如下清洁剂清洁表面和相关区域：NOTE: Clean the surface and the area with:Non Aqueous 08BAA9 As requiredCleaner-General2. 拆除右侧机腹整流罩53.2侧向隔框Remove the Belly Fairing Lateral Frame 53.2 on RH Side警 告：保证连杆和接头在位以保持位置。WARNING: LET THE ROD AND THE FITTING IN PLACE TO KEEP THE POSITION.a. 参考Fig. A-FBAAB，按照SRM 51-42-00拆下右侧机腹整流罩53.2侧向隔框。Remove the belly fairing lateral Frame 53.2 on RH side，Refer to Fig. A-FBAAB，In accordance with SRM 51-42-00.注 释：拆除项目（2）接头，需要拆除并保留机腹整流罩面板上的14颗螺钉和垫片。NOTE: To remove the Fitting Item (2), it is necessary to remove and retain the 14 Bolts and Washers from the Belly Fairing Panels.1 Fitting F5331736220100 Item (2) DiscardAttached with:13 Rivet Item (3) Discard29 Rivet Item (4) Discard29 Bush Item (5) Discard注 释：使用如下清洁剂清洁表面和相关区域：NOTE: Clean the surface and the area with:Non Aqueous 08BAA9 As requiredCleaner-General3. 对左侧新的机腹整流罩53.2侧向隔框钻孔Drill the New Belly Fairing Lateral Frame 53.2 on LH Sidea. 参考Fig. A-FBCAA，以及按照SRM 51-42-00, SRM 51-44-00和SRM 51-47-00，将如下接头临时放到位：Temporarily put in position，Refer to Fig. A-FBCAA，In accordance with SRM 51-42-00, SRM 51-44-00 and SRM 51-47-00.1 Fitting F0041347820000 Item 1b. 若拆除了197EB接近面板参考AMM Task 53-35-13-400-801恢复面板。If removed, install the Access-Panel 197EB, refer to AMM Task 53-35-13-400-801.c. 若拆除了机翼-机身整流罩147BB参考AMM Task 53-35-11-400-801恢复面板。If removed, install the Wing-to-Fuselage Fairing 147BB, refer to AMM Task 53-35-11-400-801.d. 对项目1接头进行钻孔，保证接头上的孔与结构和机腹整流罩接近面板上的孔对准。Drill holes on the fitting item 1 to align with the existing holes of the structure and the Belly Fairing Access-Panels.e. 根据需要拆除197EB接近面板，参考AMM Task 53-35-13-000-801。If necessary, remove the Access-Panel 197EB, refer to AMM Task 53-35-13-000-801.f. 根据需要拆除机翼-机身整流罩147BB，参考AMM Task 53-35-11-000-801。If necessary, remove the Wing-to-Fuselage Fairing 147BB, refer to AMM Task 53-35-11-000-801.g. 拆下项目1接头。Remove the fitting item 1.4. 对右侧新的机腹整流罩53.2侧向隔框进行钻孔 Drill the New Belly Fairing Lateral Frame 53.2 on RH Sidea. 参考Fig. A-FBCAA，以及按照SRM 51-42-00, SRM 51-44-00和SRM 51-47-00，将如下街头临时放到位：Temporarily put in position，Refer to Fig. A-FBCAA，In accordance with SRM 51-42-00, SRM 51-44-00 and SRM 51-47-00.1 Fitting F0041347820100 Item 2b. 若拆除了198EB接近面板参考AMM Task 53-35-13-400-801恢复面板。If removed, install the Access-Panel 198EB, refer to AMM Task 53-35-13-400-801.c. 若拆除了机翼到机身整流罩148BB参考AMM Task 53-35-11-400-801恢复面板。If removed, install the Wing-to-Fuselage Fairing 148BB, refer to AMM Task 53-35-11-400-801.d. 对项目2接头进行钻孔，保证接头上的孔与结构和机腹整流罩接近面板上的孔对准。Drill holes on the fitting item 2 to align with the existing holes of the structure and the Belly Fairing Access-Panels.e. 根据需要拆除198EB接近面板，参考AMM Task 53-35-13-000-801。If necessary, remove the Access-Panel 198EB, refer to AMM Task 53-35-13-000-801.f. 根据需要拆除机翼到机身整流罩148BB，参考AMM Task 53-35-11-000-801。If necessary, remove the Wing-to-Fuselage Fairing 148BB, refer to AMM Task 53-35-11-000-801.g. 拆下项目2接头。Remove the fitting item 2.5. 在工作台上安装新的左侧机腹整流罩53.2侧向隔框上的螺帽On Bench, Install the Nuts of the New LH Belly Fairing Lateral Frame 53.2a. 对项目1上的孔进行铰孔并去毛刺，处理至Fig. A-FBCAA Sheet 04所示的最终尺寸。Ream and deburr the holes on the fitting item 1, to the final dimensions given in Fig. A-FBCAA Sheet 04.注 释：使用如下的清洁剂清洁孔、表面和相关区域。NOTE: Clean the holes, the surface and the area with:Non Aqueous 08BAA9 As requiredCleaner-General注 释：钻孔后使用如下材料对项目1隔框上的14个孔进行保护。NOTE: Protect after drilling, the 14 holes of the base plate of the Frame Item 1, with:Surface 10ABC1 As requiredPretreatment-LightAlloys ChemicalConverPrimer 04EAC2 As requiredPolyurethane Paint-Corrosion InhibitingTop Coat 04JAA3 As requiredPolyurethane-External Structureb. 在项目1接头上安装项目6螺帽，参考Fig. A-FBBAA、 AMM Task 20-28-00-912-801、 ESPM 20-51-20，按照SRM 51-40-00、 SRM 51-42-00、 SRM 51-43-00 和 SRM 51-44-00。Install the nuts item 6 on the fitting item 1，Refer to Fig. A-FBBAA，Refer to AMM Task 20-28-00-912-801，Refer to ESPM 20-51-20，In accordance with SRM 51-40-00, SRM 51-42-00, SRM 51-43-00 and SRM 51-44-00.1) 参考Fig. A-FBBAA Sheet 01，将如下拖把螺帽临时放到位。Temporarily put in position，Refer to Fig. A-FBBAA Sheet 01.14 Nut-Plate NAS1791A3-2 Item 62) 对项目1接头上的28个孔进行钻孔，保证接头上的孔与项目6螺帽上的孔对准。Drill 28 holes on the fitting item 1 to align with the existing holes of the nuts item 6.3) 拆下项目6螺帽。Remove the nuts item 6.4) 对项目1接头上的孔进行铰孔并去毛刺，处理至Fig. A-FBBAA Sheet 01所示的最终尺寸。Ream and deburr