WOHA33_11462C155_320_EOA33-53-0015

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WOHA331146_320_155适航指令(AD) DIC 1146155TitleFuselage Frame/Stringer Attachments - Inspection/RepairMcd&Rev/厂家工卡&修订日期标题机身隔框/桁条连接处的检查和修理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/1EOA33-53-0015R00机身/AirframeMDIC84:00Baseline/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AD 2014-0197,SB A330-53-3202R00,SB A330-53-3212R00,SB A330-53-3213R00,SB A330-53-3214R00,SB A330-53-3216R00,SB A330-53-3217R00,SB A330-53-3218R00,SB A330-53-3219R00EOA33-HKG53-0010R00Written/编写Reviewed/审核Approved/批准2014-12-042014-12-042014-12-04Accomplished完工签署Complete Date完工日期Station维修站PVGREASON & DESCRIPTION/原因及描述交付前，在对A330-200F一些飞机各机身区域检查时，发现有紧固件丢失情况， 若不及时发现和修复，可能会导致裂纹的产生并扩展，从而降低机身机构的完整性。故下发本EO执行检查。 During inspection of various fuselage areas on some A330-200F aeroplanes on the production line, prior to delivery, some fasteners were found missing.This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage.So issue this EO to inspect it.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1CML06AAA1SEALANTCH1ALL数量按需/Quntity2533216D01R01KITAS1ALL无3533217D01R01KITAS1ALL无4533218D01R01KITAS1ALL无5533219D01R01KITAS1ALL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:EOA33-53-0015TITLEFuselage Frame/Stringer Attachments - Inspection/RepairPerfInsp标题机身隔框/桁条连接处的检查和修理工作者检查者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。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.IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.B. 标准施工/Standard Practices (a) 飞机隔框的识别，参考AMM 06-31-53, Page Block 001。For the identification of Frame (FR) numbers (Refer to AMM 06-31-53, Page Block 001).(b) 飞机区域的识别，参考AMM 06-20-00, Page Block 001。For the identification of aircraft 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 06-41-53, Page Block 001. (d) 紧固件拆装，参考SRM 51-42-00。 Remove and install fasteners, in accordance with SRM 51-42-00.(e) 标记所有你拆装的部件，以便于后续安装Tag all the parts you must remove and retain to make the subsequent installation easier. (f) 参考AMM Task 20-21-11-911-801拧紧紧固件。To torque tighten the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801).(g) 参照SRM 51-43-00，获取紧固件的备用和替代信息Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.(h) 若备用和替代紧固件已经在飞机上使用，请确保相关的螺母/套环与SRM 51-40-00 Mating Part栏中的数据相一致If alternative and substitute fasteners have to be used, you must make sure that theassociated nut/collar are compatible in accordance with SRM 51-40-00 Mating Part column.(i) 钻孔和去毛刺，参考SRM 51-44-11Obtain fastener hole diameters and drill and de-burr data in accordance with SRM 51-44-11.(j) 紧固件的间隙和斜度，请参考SRM 51-47-00Obtain fastener spacing and margin data in accordance with SRM 51-47-00.(k) 对于钻铆钉孔：For the drilling of rivet holes:- 使用软铅笔标记铆钉孔位置Use a soft lead pencil and make marks to show the position of the rivet holes.- 在钻紧固件孔时，确保边距合适Make sure that you have the correct edge clearance before you drill the fastener holes.- 若没有给出，铆钉孔直径的公差为+0.1 mm (+0.004 in.)If not shown otherwise, the tolerance for the rivet hole diameter is +0.1 mm (+0.004 in.).- 若没有给出，铆钉孔位置的公差为+/-0.2 mm (+/-0.007 in.)If not shown otherwise, the tolerance for the rivet hole position is +/-0.2 mm (+/-0.007 in.).- 用导向孔钻枪和钻孔套导出原有的孔Transfer-drill the existing holes with a pilot drill and a drill bush.- 用直径为2.5mm(0.0984in)导向孔钻枪钻新的紧固件孔，然后增加孔的直径到你需要的尺寸Drill new fastener holes with a pilot drill of 2.5 mm (0.0984 in.) diameter.Increase the hole diameter to the correct size for the fastener which you must install.- 孔去毛刺Deburr the holes.(l) 剪裁铆钉到需要的长度Cut the rivets to the necessary length.(m) 参考SRM 51-46-11，埋头紧固件孔Countersink the fastener holes in accordance with SRM 51-46-11.(n) 参考SRM 51-24-00，使用密封胶Apply sealant in accordance with SRM 51-24-00.(o) 参考AMM Task 20-21-11-911-801，对标准螺纹紧固件磅力矩To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.(p) 参考SRM 51-75-12，重新恢复表面抛光Renew the protective finish in accordance with SRM 51-75-12.(q) 若本EO规定的紧固件长度不能满足SRM Chapter 51给出的安装标准，则可以使用满足SRM Chapter 51安装要求的相同规格或者被批准的替代紧固件，另外，参考SRM Chapter 51 有可能需要安装垫片If the length of any fastener specified in this EO does not meetinstallation standards given in SRM Chapter 51, then a fastener of the samespecification, or an approved substitute, with a length which meets the installationstandards given in SRM Chapter 51 may be used. In addition, washers may beinstalled for fastener grip length in accordance with SRM Chapter 51.C. 施工准备/ PREPARATION (1) 工作准备/Job Set-up(a) 在开始维护工作前，请确认执行以下工作：The following items shall be considered as the basic Aircraft configuration beforeyou start a maintenance task:- 飞机停留在位（地面安全锁和轮挡放置在位）Aircraft on the ground resting on landing gear (the ground safety locks and thewheel chocks are in position on the landing gear).- 发动机关车，反推关闭并锁定Engine shut down, thrust reversers closed and locked.- 飞机构型整洁Aircraft in clean configuration.- 设置停留刹车Parking brake applied.- 飞机已断电Aircraft electrical network de-energized.- 液压系统已释压Hydraulic systems depressurized.- 可方便进入客舱和驾驶舱Access to the cockpit and cabin is available.- 所有跳开关在闭合位All circuit breakers are in closed position.- 所有的控制元件在NORM, AUTO或者OFF位All controls in NORM, AUTO or OFF position.(b) 飞机静电接地，参考AMM Task 12-34-24-860-802Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802.(c) 将工作梯放置到前货舱门821Put access platform(s) in position, below the FWD cargo compartment door 821. (d) 参考AMM 52-31-00, Page Block 001，打开前货舱门821Open the FWD cargo-compartment door 821, refer to AMM 52-31-00, Page Block 001.(e) 参考AMM Task 25-23-43-000-802，在主货舱内右隔框FR35处，拆下衬里面板 242DW, 242EW, 242FW and 242GWIn the Main-Deck Cargo Compartment, at Frame 35 RH, remove the lining panels242DW, 242EW, 242FW and 242GW, refer to AMM Task 25-23-43-000-802.(f) 参考AMM Task 53-00-00-000-802，拆下前货舱地板131NG, 131DF, 132DF, 132FG, 132HG and 132KG,In the FWD cargo-compartment, remove floor panels 131NG, 131DF, 132DF,132FG, 132HG and 132KG, refer to AMM Task 53-00-00-000-802.(g) 参考AMM Task 25-52-00-000-801.拆下前货舱的侧壁板132NXIn the FWD cargo-compartment, remove the sidewall panels 132NX, refer to AMMTask 25-52-00-000-801.(h) 参考AMM Task 25-80-00-000-801，按需拆下绝缘层以接近工作区域Remove the insulation blankets as necessary to get access to the work areas, referto AMM Task 25-80-00-000-801.(i) 将工作梯放置到后货舱门822Put access platform(s) in position, below the AFT cargo compartment door 822.(j) 参考AMM Task 52-30-00-010-801，打开后货舱门822Open the AFT cargo-compartment door 822, refer to AMM Task 52-30-00-010-801 (k) 参考AMM Task 25-55-22-000-801，拆下主舱货舱（MDCC）的衬板262WW 和 262XWIn the Main-Deck Cargo Compartment (MDCC), remove the lining panels262WW and 262XW, refer to AMM Task 25-55-22-000-801.(l) 参考AMM Task 53-00-00-000-803，拆下后货舱地板152VK 和 152WKIn the AFT cargo-compartment, remove floor panels 152VK and 152WK, refer to AMM Task 53-00-00-000-803.(m) 参考AMM Task 25-53-00-000-801.拆下后货舱的侧壁板 51HW, 151JW,151QW, 151RW, 152HW, 152JW, 152MW 和 152NWIn the AFT cargo-compartment, remove the sidewall panels 51HW, 151JW,151QW, 151RW, 152HW, 152JW, 152MW and 152NW, refer to AMM Task 25-53-00-000-801 (n) 参考AMM Task 25-53-00-000-801，拆下后货舱顶板151FC 和 152FCIn the AFT cargo-compartment, remove the ceiling panels 151FC and 152FC, referto AMM Task 25-53-00-000-801(o) 参考AMM Task 25-80-00-000-801，按需拆下绝缘层以接近工作区域Remove the insulation blankets as necessary to get access to the work areas, referto AMM Task 25-80-00-000-801.(p) 参考AMM Task 52-30-00-010-803，打开散货舱门823Open the bulk cargo-compartment door 823, refer to AMM Task 52-30-00-010-803.(q) 参考AMM Task 25-55-22-000-801在主舱货舱(MDCC)，拆下衬板261XW，261YW, 261ZW, 261DX, 261EX, 261FX, 262JX, 262QX, 262RX, 262UX和262WX,In the Main-Deck Cargo Compartment (MDCC), remove the lining panels 261XW,261YW, 261ZW, 261DX, 261EX, 261FX, 262JX, 262QX, 262RX, 262UX and262WX, refer to AMM Task 25-55-22-000-801.(r) 参考AMM Task53-00-00-000-803，拆除后货舱地板152WKIn the AFT cargo-compartment, remove the floor panel 152WK, refer to AMM Task53-00-00-000-803.(s) 参考AMM Task25-53-00-000-801，拆除后货舱顶板151KCIn the AFT cargo-compartment, remove ceiling panel 151KC, refer to AMM Task25-53-00-000-801.(t) 参考AMM Task53-00-00-000-804，拆除散货舱地板162BFIn the bulk cargo-compartment, remove the floor panel 162BF, refer to AMM Task53-00-00-000-804.(u) 参考AMM Task 25-54-00-000-001，拆除散货舱侧壁板162EWIn the bulk cargo-compartment, remove the sidewall panel 162EW, refer to AMMTask 25-54-00-000-001.(v) 参考AMM Task 25-55-22-000-801，在主舱货舱（MDCC），拆下衬板261QQ 和261RQIn the Main-Deck Cargo Compartment (MDCC), remove the lining panels 261QQand 261RQ, refer to AMM Task 25-55-22-000-801.(w) 参考AMM Task53-00-00-000-804，在拆下散货舱的地板162EFIn the bulk cargo-compartment, remove the floor panel 162EF, refer to AMM Task53-00-00-000-804.(x) 参考AMM Task 25-54-00-000-001，拆下散货舱门的侧壁板162FW, 162RW, 162VW 和162WWIn the bulk cargo-compartment, remove the sidewall panel 162FW, 162RW, 162VWand 162WW, refer to AMM Task 25-54-00-000-001.(y) 参考AMM Task 25-80-00-000-801，按需拆下绝缘层Remove the insulation blankets as necessary to get access to the work areas, referto AMM Task 25-80-00-000-801.D. 检查/INSPECTION(A)SUBTASK A330-53-3202-对区域13和14，隔框19到37.4的丢失或不合格的紧固件进行检查SUBTASK A330-53-3202- FUSELAGE - FORWARD FUSELAGE INSPECTION FOR SUSPECTED MISSING/NON - CONFORMING FASTENERS AT SECTION 13 AND 14 FR19 TO FR37.41. 施工步骤/PROCEDURE (1) 在隔框19，STGR52/STGR53左侧，详细检查丢失紧固件At FR19, STGR52/STGR53 LH, do a Detailed Inspection for Missing Fasteners (a) 参考Fig. A-GFAAA Sheet 01，对隔框19，STGR52/STGR53左侧，详细检查丢失紧固件At Frame 19 between STGR52/STGR53 LH, do a detailed inspection for missingfasteners, refer to Fig. A-GFAAA Sheet 01:1) 若件号DAN6-6-4，直径为4.8mm（0.189in）紧固件安装在如图 Fig. A-GCAAA Sheet 01, View B的位置，则不需要在此位置做修理，执行如下工作步骤：If the 4.8 mm (0.189 in.) diameter fasteners, Part Number (PN) DAN6-6-4, areinstalled at the locations as shown in Fig. A-GCAAA Sheet 01, View B, norepair is necessary at this location, do the worksteps which follow: a 在Table 1中记录检查结果。Write the result of the inspection in the Inspection Report sheet refer to Table 1.b 转到步骤D.(A)1.(2)，对隔框20和STGR43 LH，执行安装紧固件的详细检查Go to step D.(A)1.(2) At FR20 and STGR43 LH, do a Detailed Inspection for the Installation of Fasteners .2) 若直径4.8mm(0.189in)的紧固件，并未安装在如图Fig. A-GCAAA Sheet 01, View B 所在位置，执行以下步骤If the 4.8 mm (0.189 in.) diameter fasteners are not installed at the locationsas shown in Fig. A-GCAAA Sheet 01, View B, do the worksteps which follow: a 详细检查如图Fig. A-GCAAA Sheet 01, View B所示的，紧固件邻近区域的 损伤、变形或者裂纹Do a detailed inspection of the adjacent fasteners for damage,deformations or cracks, as shown in Fig. A-GCAAA Sheet 01, View B: 若在紧固件邻近区域发现损伤或者裂纹，请在下个飞行循环前联系结构 结构工程师获取进一步的修理If you find damage or cracks at the adjacent fasteners, contactStructure engineer for further instructions before the next flight. 若在紧固件邻近区域没有发现损伤或者裂纹，请按照SUBTASKA330-53-3216 在下个飞行循环前完成改装If you do not find damage or cracks at the adjacent fasteners,accomplish Modification SUBTASK A330-53-3216 at thislocation before next flight.b 在Table 1中记录检查结果。 Write the result of the inspection in the Inspection Report sheet,refer to Table 1(2) 对隔框20和STGR43左侧的安装紧固件执行详细检查At FR20 and STGR43 LH, do a Detailed Inspection for the Installation of Fasteners (a) 参考Fig. A-GFBAA Sheet 01，对隔框20和STGR43左侧的安装紧固件执行详细检查At Frame 20 and STGR43 LH, do a detailed inspection for the installation offasteners, refer to Fig. A-GFBAA Sheet 01: 1) 若件号PN EN6081D6，直径为4.8mm(0.189in)的紧固件按照如图Fig. A-GCBAA Sheet 01和Fig. A-GCBAASheet 02, View C安装在位，不需要修理执行以下步骤：If the correct 4.8 mm (0.189 in.) diameter fasteners, PN EN6081D6, areinstalled at the locations shown in Fig. A-GCBAA Sheet 01 and Fig. A-GCBAASheet 02, View C, no repair is necessary at this location, do the workstepswhich follow: a 在Table 1中记录检查结果Write the result of the inspection in the Inspection Report sheet, refer to Table 1.b 请转到步骤D.(A)1.(3),在隔框21和隔框22左侧，对丢失紧固件执行详细检查Go to step D.(A)1.(3), At FR21 and FR22 LH, do a Detailed Inspection for Missing Fasteners .2) 若有直径为4.0mm(0.157in)的紧固件安装（硬铝铆钉）在如图Fig. A-GCBAA Sheet 01 和Fig. A-GCBAA Sheet02, View C的位置，请执行如下步骤：If there are fasteners of 4.0 mm (0.157 in.) diameter installed (dural rivets) atthe locations as shown in Fig. A-GCBAA Sheet 01 and Fig. A-GCBAA Sheet02, View C, do the worksteps which follow:a 参考图Fig. A-GCBAA Sheet 02, View C，拆下并报废直径4.0mm(0.157in) 的紧固件，并在下次飞行循环根据SUBTASKA330-53-3216前完成改装Refer to Fig. A-GCBAA Sheet 02, View C, remove and discard the 4.0mm (0.157 in.) diameter fasteners and accomplish Modification SUBTASK A330-53-3216 at this location before the next flight.b 在Table 1中记录检查结果Write the result of the inspection in the Inspection Report sheet, refer to Table 1.3) 若无紧固件安装在如图Fig. A-GCBAA Sheet 01和Fig. A-GCBAA Sheet 02, View C 的位置，执行以下工作：If no fasteners are installed at the locations shown in Fig. A-GCBAA Sheet 01and Fig. A-GCBAA Sheet 02, View C, do the worksteps which follow:a 按照图Fig. AG-CBAA Sheet 02, View C，详细检查内侧隔框法兰的表面保护层损伤 和邻近紧固件的情况（可能有剪切紧固件或者损伤的表面保护层）Do a detailed inspection for damage to the surface protection of theinner frame flange and the condition of the adjacent fasteners (possiblesheared fastener(s) or damaged surface protection), as shown in Fig. A-GCBAASheet 02, View C. 若在内隔框法兰和/或邻近紧固件发现损伤，请在下次飞行循环前联系结构工程师If you find damage to the surface protection of the inner frameflange and/or at the adjacent fasteners, contact structure engineer for furtherinstructions before the next flight. 若在内侧隔框法兰或邻近紧固件处未发现损伤，请根据SUBTASKA330-53-3216在下次飞行前完成改装If you do not find damage at the inner frame flange or adjacentfasteners, accomplish Modification SUBTASK A330-53-3216 atthis location before the next flight.注 释：存在导向孔NOTE: Pilot holes exist.b 在Table 1中记录检查结果Write the result of the inspection in the Inspection Report sheet, refer to Table 1.(3) 在FR21 和FR22 左侧，详细检查丢失的紧固件At FR21 and FR22 LH, do a Detailed Inspection for Missing Fasteners(a) 参考Fig. A-GFCAA Sheet 01，在FR21 和FR22 左侧，详细检查丢失的紧固件At Frame 21 and Frame 22 LH, do a detailed inspection for missing fasteners,