WOHA33_2422254_621_EOA33-53-0026

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_621_254重要修理/改装 适航指令(AD) DIC 2422254TitleFuselage - Forward Fuselage - Reinforce Longitudinal Butt Joints In Section 13Mcd&Rev/厂家工卡&修订日期标题机身 - 前机身 - 对Section 13的纵向对接带进行加强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/1EOA33-53-0026R02机身/AirframeAIRP /SMTI /NDT08:30/18:00/05:00Baseline/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 A330-53-3239R01,AD 2016-0207,CAD 2016-A330-01EOA33-HKG53-0021R02Written/编写Reviewed/审核Approved/批准2016-12-022016-12-142016-12-16Accomplished完工签署Complete Date完工日期Station维修站PVGREASON & DESCRIPTION/原因及描述广布疲劳分析显示在到达DSG前有一些区域需要加强。FR22-FR26/28,STGR-1L处 的纵向对接带就处于这些区域中。故下发本EO对FR22-FR26/28,STGR-1L处的纵向对接带进行加强。Following Widespread Fatigue Damage (WFD) analysis, it has been demonstrated that some areas require reinforcement before reaching the Design Service Goal (DSG). The longitudinal butt joint on Stringer (STGR)1 LH, from Frame (FR)22 to FR26/28 has been identified as such an area. So issue this EO to introduces a modification to reinforce the longitudinal butt joint on STGR1 LH, from FR22 to FR26/28. R01版改版原因/Reason for R01 revision:1.依据SB A330-53-3239R01将本EO定义为重要改装。 Set this EO as Major Modification according to SB A330-53-3239R01.2.依据SB A330-53-3239R01加入施工步骤及工具航材。 Add work instructions and spares/tool information, according to SB A330-53-3239R01. R02版改版原因/Reason of R02 revision：此EO升级为AD/CAD控制，并在依据文件中增加AD2016-0207/CAD2016-A330-01.This EO is upgraded as AD/CAD control.Add AD2016-0207/CAD2016-A330-01 into sources columnTOOLS/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1CML08BBF1MEKTO1ALL数量按需/QUANTITY AS REQUIREDTOOLS 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12905O-RING SEALAS1ALLN/A2CML06AAB1SEALANTCH1ALL数量按需/QUANTITY AS REQUIRED,或/or CML06ABF13CML06AAC1INTERFAY SEALANTCH1ALL数量按需/QUANTITY AS REQUIRED4CML14DBB1RELEASE AGENTCH1ALL数量按需/QUANTITY AS REQUIRED5CML08BAA9SOLVENT GENERAL PURPOSECH1ALL数量按需/QUANTITY AS REQUIRED6CML03FAB1VASILINECH1ALL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 REQUIRED(BAC 7568)10CML06AEB2SEALERCH1ALL数量按需/QUANTITY AS REQUIRED11CML04CMA2WASH PRIMER(0434/9000+0841/9000+7641/3600)(Metaflex FCR Pri)CH1ALL数量按需/QUANTITY AS REQUIRED12533239D02R02KITAS1ALLN/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1CML04TMB2primerCH1ALL视情，数量按需/On condition and QUANTITY AS REQUIRED2CML12ABC1CORROSION PREVENTIVE COMPOUND, TEMPORARYCH1ALL视情，数量按需/On condition and QUANTITY AS REQUIRED3CML04QAB2primerCH1ALL视情，数量按需/On condition and QUANTITY AS REQUIREDIMPORTANT 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:EOA33-53-0026TITLEFuselage - Forward Fuselage - Reinforce Longitudinal Butt Joints In Section 13PerfInsp标题机身 - 前机身 - 对Section 13的纵向对接带进行加强工作者检查者A. 通用信息/GENERAL警 告：确认遵守所参考程序中的所有警告和注意事项。WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONSINCLUDED IN THE REFERENCED PROCEDURES.注 意： 遵守使线束和设备处于良好状态(电气性和机械性均可用)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、电气设备及工作区域的洁净，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。这样可减少安装电线时的污染和损伤。若污染，参考ESPM 20-55-00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; ASNECESSARY 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的施工步骤中包含了其他文件中或本EO其他部分中的步骤。当出现“参考”字样时，工作者可以使用被所属局方所接受的替代步骤。当出现“按照”字样时，则必须按照给定的步骤执行。NOTE: The accomplishment instructions of this EO include procedures given in other documents or in other sections of the EO. 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：手册名以缩写表示。NOTE: Manual titles are referred to by acronyms.注 释：本EO被（或将被）AD定义为强制性执行工作。完工指令中的步骤D和E必须被执行（RC）以符合AD要求。其他步骤为推荐执行，可以用不同于EO中给出的其他可接受的步骤替代，只要按要求执行了RC步骤，且能够将飞机恢复至正常运营状态。NOTE: This EO is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs D and E in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the EO, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition.注 释：本EO包含为保障飞机持续适航的机上维护说明。 对于此处包含的说明，若发现任何偏离情况，请联系结构工程师，由空客提供进一步说明及批准。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 structure engineer for further instructions and approval from AIRBUS.注 释：报废的零件须由工作者妥善处理。NOTE: Discarded parts must be managed at the operators discretion.B. 标准施工/Standard Practices -Subtask 533239-910-201-001(a) 本EO中的材料规格牌号或规范号参考CML。For the specification of materials (Mat. No.) given in this EO, refer to Consumable Materials List (CML).(b) 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.(c) 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.(d) 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.(e) 紧固件的拆装，按照SRM 51-42-00。Remove and install fasteners in accordance with SRM 51-42-00.(f) 按照SRM 51-44-00和SRM 51-44-11，获取紧固件孔尺寸信息和钻孔去毛刺数据。Obtain fastener hole diameters and drill deburr data in accordance with SRM 51-44-00 and SRM 51-44-11.(g) 金属结构上的沉孔处理，按照SRM 51-46-11。Do the countersinking of metallic structure in accordance with SRM 51-46-11.(h) 完成本EO需要的修理垫片，按照SRM 51-71-15。To accomplish this EO it is necessary to use the repair washers in accordance with SRM 51-71-15.(i) 标准螺纹紧固件磅力矩，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.(j) 紧固件的替代数据获取，按照SRM 51-43-00。Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.(k) 如不得不使用替代或备用紧固件，必须按照“Mating Part”栏，确保其与螺帽/collar相搭配。If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with Mating Part column.(l) 如果本EO所指定的任意紧固件的长度不符合SRM51章给出的安装标准，则可以使用相同规范的或者经批准的替代件，只要其长度满足SRM51章的安装标准。另外，对于紧固件杆长可以安装垫片，按照SRM51章。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.(m) 防护此区域，防止设备、结构和所有零件发生损伤。Protect the areas to prevent damage to the equipment and structure and all the parts.(n) 将所有保留的零件放入标识袋中，并与相关组件一同放置。Put all the retained hardware in identified plastic bags and attach the bags to the related unit.(o) 跳开关安全注意事项，参考AMM Task 20-16-00-912-801。For circuit breaker safety precautions, refer to AMM Task 20-16-00-912-801.(p) 漆层的修复按照SRM 51-75-12。Repair the paint coatings in accordance with SRM 51-75-12.(q) 面漆的恢复按照SRM 51-21-00。Renew the protective finish in accordance with SRM 51-21-00.(r) 密封胶的刷涂按照SRM 51-24-00和SRM 51-76-11。Apply sealant in accordance with SRM 51-24-00 and SRM 51-76-11.C. 准备/PREPARATION (1) 工作准备/Job Set-up - Subtask 533239-941-201-001注 释：开始维修工作前，以下条目应视为基本飞机构型： -飞机在地面上以起落架静止支撑（地面安全销在起落架上安装到位，轮挡放置在位）。 -发动机关车，反推关闭并锁上。 -飞机处于空机状态 -处于停留刹车状态 -飞机电源断开 -液压系统处于卸压状态 -到驾驶舱和客舱的接近可用 -所有的跳开关闭合 -所有的控制处于NORM、AUTO或者OFF位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 12-34-24-860-802确保飞机静电接地。Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802.(b) 在隔框22和隔框26/28之间，左侧STGR1的附近合适位置，放置工作梯。Put an access platform in position at STGR1 LH, from FR22 to FR26/28.(c) 执行拆除VHF天线的工作准备步骤，参考AMM Task 23-12-11-000-801。Do the Job Set-up procedure as specified in the Removal of the VHF Antenna, refer to AMM Task 23-12-11-000-801.(2) 拆除以接近 / Remove for Access - Subtask 533239-010-201-001(a) 拆除保护衬板，以接近FR22到FR26/28之间，左侧STGR1，参考AMM Task 25-55-22-000-801。Remove the protective linings to gain access to STGR1 LH between FR22 and FR26/28, refer to AMM Task 25-55-22-000-801.(b) 拆除空调管路，以接近FR22到FR26/28之间，左侧STGR1，参考AMM Task 21-20-00-010-801。Remove air conditioning ducts to gain access to STGR1 LH between FR22 and FR26/28, refer to AMM Task 21-20-00-010-801.(c) 拆除隔热毯，移开电子线路（不断开），以接近FR22到FR26/28之间，左侧STGR1，参考AMM Task 25-80-00-000-801。Remove the insulation blankets and move electrical wires (without disconnection) to gain access to STGR1 LH between FR22 and FR26/28, refer to AMM Task 25-80-00-000-801.D. PROCEDURE / 程序注 释：本EO所提供的步骤在确认相同区域先前没有执行过依据空客文件的修理和/或改装方可实施。如果有之前执行过的修理，请联系结构工程师获取进一步措施。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) 拆除FR22到FR23之间的VHF1天线/ Remove the VHF1 Antenna between FR22 and FR23 - Subtask 533239-020-201-001(a) 在FR22到FR23之间，左侧和右侧STGR1之间，参考Fig. A-GBCAA Sheet 01 和 AMM Task 23-12-11-000-801，拆除VHF1天线，FIN 4RC1。From FR22 to FR23 and between STGR1 LH and STGR1 RH, refer to Fig. A-GBCAA Sheet 01 and refer to AMM Task 23-12-11-000-801, remove the VHF1 Antenna, FIN 4RC1:(2) 拆除FR22到FR26/28之间位于左侧STGR1的纵向对接处的紧固件/ Remove Fasteners from the Longitudinal Butt Joint at STGR1 LH between FR22 and FR26/28 - Subtask 533239-020-202-001(a) 在FR22到FR26/28之间，左侧STGR1，参考Fig. A-GBBAA Sheet 01 和 Fig. A-GBBAA Sheet 02，临时将加强片Item 1和Item 2安放在位，并在机身上标出其轮廓。On STGR1 LH between FR22 and FR26/28, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02, temporarily put Doublers, Item 1 and Item 2 in position and mark the outline on the fuselage skin.(b) 将临时安放件从原位移除。Remove the items that were temporarily put in position.(c) 用蜡笔在改装区域标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FR22到FR26/28之间，左侧STGR1，参考Fig. A-GBAAA Sheet 01 和 Fig. A-GBAAA Sheet 02，拆除：On STGR1 LH, between FR22 and FR26/28, refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02, remove:注 释：当心不要损伤到孔。NOTE: Be careful not to damage the holes.(e) 清洁紧固件孔，使用：Clean the fastener holes with:(3) 旋转探头检查位于FR22到FR26/28之间左侧STGR1的紧固件孔/ Inspect Fastener Holes at STGR1 LH between FR22 and FR26/28 by Rotating Probe Testing - Subtask 533239-832-201-001(a) 在FR22到FR26/28之间，左侧STGR1，检查紧固件孔径，参考Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02 和 Fig. A-GBBAA Sheet 03。On STGR1 LH between FR22 and FR26/28, do a check of the diameter of the fastener holes, refer to Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02 and Fig. A-GBBAA Sheet 03.(b) 确保孔径小于最大最终孔径。Make sure that the hole diameter is not equal to or more than the maximum final hole diameter.(c) 如果孔径等于或大于最大孔径，在执行下一步骤之前联系结构工程师。If the hole diameter is equal to or more than the maximum hole diameter, contact structure engineer before the next step.(d) 如果孔径小于最大孔径，执行下一步骤。If the hole diameter is not equal to or more than the maximum hole diameter, do the next step.(e) 在FR22到FR26/28之间，左侧STGR1，旋转探头检查拆除紧固件后的孔，参考NTM Task 51-10-01-250-801, Fig. A-GBAAA Sheet 01 和 Fig. A-GBAAA Sheet 02。On STGR1 LH between FR22 and FR26/28, do a rotating probe inspection of the holes of the removed fasteners, refer to NTM Task 51-10-01-250-801, Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.是否发现裂纹/If cracks detected：o是/Yes o否/No1 如果发现裂纹，在下次飞行前联系结构工程师。If cracks are detected, contact structure engineer before the next step.裂纹修理执行文件编号/Repair document No. for crack repair： 2 如果没有发现裂纹，执行下一步骤。If no cracks are detected, do the next step.(4) 在FR22到FR26/28之间左侧STGR1的纵向对接处安装外部搭接带/ Install External Strap and Fasteners to the Longitudinal Butt Joint at STGR1 LH between FR22 and FR26/28 - Subtask 533239-420-201-001(a) 在FR22到FR26/28之间，左侧STGR1，将受影响紧固件孔钻并铰至紧固件表格中给定的最终孔径，参考Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02, Fig. A-GBBAA Sheet 03，按照SRM 51-44-11。At STGR1 LH between FR22 and FR26/28, drill and ream the affected fastener holes to the final hole diameter given in the fastener table, refer to Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02, Fig. A-GBBAA Sheet 03 and in accordance with SRM 51-44-11.(b) 清洁紧固件孔，使用：Clean the fastener holes with:(c) 按需填充现有的埋头窝，按照SRM 51-71-15。If necessary fill the existing countersinks in accordance with SRM 51-71-15.(d) 在FR22到FR26/28之间，左侧STGR1，参考Fig. A-GBBAA Sheet 01, 视图B 和 Fig. A-GBBAA Sheet 03，关闭固定螺帽的紧固件孔，湿安装：At STGR1 LH between FR22 and FR26/28, refer to Fig. A-GBBAA Sheet 01, View B and Fig. A-GBBAA Sheet 03, close the fastener holes of the anchor nuts, wet install:(e) 在FR22到FR26/28之间，左侧STGR1，参考Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02 和 Fig. A-GBBAA Sheet 03，湿安装：At STGR1 LH between FR22 and FR26/28, refer to Fig. A-GBBAA Sheet 01, Fig. A-GBBAA Sheet 02 and Fig. A-GBBAA Sheet 03, wet install:(f) 在搭接带和紧固件处恢复表面防护，按照SRM 51-75-12。Restore the surface protection on the strap and fasteners accordance with SRM 51-75-12.(g) 在紧固件处恢复防水涂层，按照SRM 51-23-12，使用：Restore the water repellent coating on the fasteners in accordance with SRM 51-23-12, use:(5) 安装FR22到FR23之间的VHF1天线/ Install the VHF1 Antenna between FR22 and FR23 - Subtask 533239-420-202-001(a) 在FR22到FR23之间，左侧和右侧STGR1之间，参考F