WOHA33_1052LNE 3C255_244_EOA33-53-0010

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WOHA331052_244_255适航指令(AD) 1052255TitleFUSELAGE - CONE/REAR FUSELAGE - REINFORCEMENT OF THS SUPPORT STRUTS AT FRAME 91Mcd&Rev/厂家工卡&修订日期标题后机身91号隔框支撑杆的加强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BLNE/1EOA33-53-0010R04AIRP02:00Baseline/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CAD 2013-MULT-11R2,SB A330-53-3204 R3,ASB A330-53-3206 R3,AMOC 10044559, REV.1,AD 2014-0068EOA33-HKG53-0006R03Written/编写Reviewed/审核Approved/批准2014-05-122014-05-142014-05-14Accomplished完工签署Complete Date完工日期Station维修站SHAREASON & DESCRIPTION/原因及描述可配平水平安定面由隔框91支撑。4根斜安装的支撑杆防止隔框产生横向位移。 在飞机的定期维护中发现支撑杆有裂纹。典型的裂纹是纵向的，并发生在支撑杆的端部。在一些飞机上检查发现每一个支撑杆都有几条裂纹。The Trimmable Horizontal Stabilizer (THS) is supported and articulated at Frame 91. Any lateral movement is prevented by 4 diagonal support struts.During maintenance, support struts have been found cracked on some aircraft.The affected area is the strut end and typical cracks are longitudinal. On some aircraft, several cracks per support strut have been found. R01改版原因/Reason for R01:1.新飞机引进，增加BLNP飞机的适用性。 Add the applicability of A/C BLNP for delivery.2.根据AMOC 10044559, REV.1在步骤中加入 备注。 Add Note to the EO for requirement of AMOC 10044559(REV.1). 3.根据SB A330-53-3204R2改版EO。 Revise this EO per SB A330-53-3204R2. R02改版原因/Reason for R02:1.更新依据文件/Update source.2.修改施工步骤/Amend procedure. R03改版 原因/Reason for R03:1.更新依据文件。Update source.2.SB改版修改施工步 骤。Revise work instructions due to SB revision. 3.根据AD要求修改 计划信息。Revise plan information in according with AD requirement.4.飞机转租，增加B-LNV飞机适用性。Add B-LNV A/C applicability due to re-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1MS24665-153(32A3)PINAS8ALL视情/On Condition2MS24665-157PINAS8ALL视情/On Condition3F5357414000000strutAS4ALL视情/On Condition (Manufactured by TAC)4533204D01R00KITAS1ALL必需/As Necessary5CML04TMB2primerCH1ALL按需/As required6CML08BAA9SOLVENT GENERAL PURPOSECH1ALL按需/As required7CML14SBA1CLEANING ABSORCH1ALL按需/As required8CML12ADB1ANTICORROSIONCH1ALL按需/As required9CML06LDG2SEALANTCH1ALL按需/As required1006AEB2SEALING OF JOINTINGCH1ALL按需/As required(等同于CML06AEB2)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:EOA33-53-0010TITLEFUSELAGE - CONE/REAR FUSELAGE - REINFORCEMENT OF THS SUPPORT STRUTS AT FRAME 91PerfInsp标题后机身91号隔框支撑杆的加强工作者检查者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.B. 标准施工/Standard Practices(a) 执行本EO中使用的耗材规范参考CML。For the specification of materials (Mat. No.) that you must use in this EO refer to Consumable Materials List (CML).(b) 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).(c) 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).(d) 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.(e) 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).(f) 紧固件拆装，参考SRM 51-42-00。For the removal and installation of fasteners, refer to SRM 51-42-00. (g) 密封胶的使用，参考SRM 51-24-00。Apply sealant in accordance with SRM 51-24-00.C. 施工准备/ PREPARATION(1) 工作准备/Job Set-up(a) 在执行维护前飞机应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.(b) 参考AMM Task 12-34-24-860-802保证飞机接地。Make sure that the aircraft is electrically grounded (Refer to AMM Task 12-34-24-860-802).(c) 将工作梯摆放到位（91号隔框，维护门312AR以下）。Put access platform(s) in position at Frame 91, below 312AR.(d) 打开维护门312AR。Open the maintenance door 312AR.(e) 打开照明开关4LJ。Set the light switch 4LJ to ON.(f) 打开接近舱门313AL。Open the accessory compartment access door 313AL.D. 施工步骤/PROCEDURE（1）参考Fig. A-GDAAA Sheet 01检查支撑杆端部直径“D”。Do a check of the strut end diameter D, refer to Fig. A-GDAAA.（a）检查支撑杆端部安装是否安装加强夹。Inspect the strut ends for the installation of clamps.1 若已安装加强夹，根据Fig. A-GBAAA Sheet 01拆除加强夹。If clamps are installed, remove the clamps from the THS support struts refer to Fig. A-GBAAA Sheet 01a 从每个支撑杆上拆下下述紧固件From each support strut, remove following fasteners.数量名称件号位置处理方法2NutAS1726-5EItem (4)保留/Retain2WasherNAS1149D0563KItem (3)保留/Retain2BoltNSA501-5-42Item (2)保留/Retain2ClampF5357685020000Item (1)保留/Retainb 去除支撑杆上残留的密封胶并使用下述化工品清洁Remove the remaining sealant from the support struts and clean them with following chemicals名称件号需求Non Aqueous Cleaner-GeneralCML08BAA9按需/As requiredTextile-Lint Free Cotton CML14SBA1按需/As required注：若已安装加强夹，支撑杆的端部直径认为是大于等于43mm (1.69in.)。然后，执行步骤D(2)。NOTE: If clamps are installed then the diameter of the strut end is equal to or more than 43mm (1.69in.). Continue with the inspection detailed in procedure D(2).2 若没有安装加强夹：If clamps are not installed: 若直径大于等于43mm(1.69in.)，执行步骤D(2)。If the diameter D is equal to or more than 43mm (1.69in.), continue with the inspection detailed in procedure D(2). 若直径小于43mm(1.69in.)，执行步骤D(3)。If the diameter D is less than 43mm (1.69in.), continue with the inspection detailed in procedure D(3).(2) 对端部直径大于等于43mm(1.69in.)支撑杆进行高频涡流检查，参考Fig. A-GCAAA。Do a High Frequency Eddy Current Inspection of the support struts with an end dia equal to or more than 43mm(1.69in.), Refer to Fig. A-GCAAA.（a）使用下述化工品清洁支撑杆.Clean the support struts with following chemicals.名称件号需求Non Aqueous Cleaner-GeneralCML08BAA9按需/As requiredTextile-Lint Free CottonCML14SBA1按需/As required(b) 高频涡流检查支撑杆端部裂纹，参考NTM 53-56-10。Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks (Refer to NTM 53-56-10).1. 若没有发现裂纹，则继续执行步骤D.(4)。 No cracks found ，continue with procedure D.(4). 2. 若单个裂纹的最大长度小于15mm(0.59in.)或者最多4道裂纹且总长度小于或等于15mm(0.59in.)，则继续执行步骤D.(4)。Individual crack with a max length less than 15 mm (0.59 in.) or no more than 4 cracks less than or equal to 15 mm (0.59 in.) found on at least one strut end，continue with procedure D.(4).3. 若单个裂纹的最大长度大于或等于15mm(0.59in.)或者裂纹超过4道且总长度小于或等于15mm(0.59in.)，则参考AMM 53-53-11,Page Block 401更换端部直径大于等于43mm(1.69in.)的支撑杆并且继续执行步骤D.(4)。Individual crack with a max length equal to or more than 15 mm (0.59 in.) or more than 4 cracks less than or equal to 15 mm (0.59 in.) found on at least one strut end. Replace the affected strut with a newstrut, which has an end diameter equal to or more than 43mm (1.69in.), before next flight, refer to AMM 53-53-11, Page Block 401 and continue with procedure D.(4) Install the clamps on the THS support struts .(c) 将检查结果报告结构工程师，填写Figure A-GAAAA - Sheet 01 Inspection Report。Report the results of this inspection to structure engineer, refer to Figure A-GAAAA - Sheet 01 inspection Report .(3) 对端部直径小于43mm(1.69in.)支撑杆进行高频涡流检查，参考Fig. A-GEAAA和Figure A-GAAAA - Sheet 01 检查报告。Do a High Frequency Eddy Current Inspection of the support struts with an end dia of less than 43mm，Refer to Fig. A-GEAAA and Figure A-GAAAA- Sheet 01 - Inspection Report.(a) 必要时，使用以下航材清洁支撑杆。If necessary, clean the support struts with:名称件号需求Non Aqueous Cleaner-GeneralCML08BAA9按需/As requiredTextile-Lint Free Cotton CML14SBA1按需/As required (b) 高频涡流检查支撑杆端部裂纹，参考NTM 53-56-10, Page Block 401。Do a High Frequency Eddy Current (HFEC) inspection of the strut ends for cracks in accordance with NTM 53-56-10, Page Block 401.1 若没发现裂纹，继续执行步骤D.(4)。No cracks found, continue with procedure D.(4).2 若发现裂纹，参考AMM 53-53-11, Page Block 401使用新的端部直径大于等于43mm (1.69in.)的支撑杆更换损伤的支撑杆并执行步骤D.(4)。Cracks found on at least one strut end, replace the affected strut with a new strut, which has an end diameter equal to or more than 43mm (1.69in.), refer to AMM 53-53-11, Page Block 401 and continue with procedure D.(4).(c) 将检查结果报告结构工程师，填写Figure A-GAAAA - Sheet 01 Inspection Report。Report the results of this inspection to structure engineer, refer to Figure A-GAAAA - Sheet 01 inspection Report .(4) 在THS支撑杆安装加强夹，参考Fig. A-GBAAA SHEET 01。Install the Clamps at the THS Support Struts, Refer to Fig. A-GBAAA SHEET 01.（a）在Item 1 加强夹的接口表面涂下述化工品。Apply following chemicals to the interface surfaces of the clamps, Item 1.名称件号需求Polysulfide Sealant Low Adhesion Fillet StructureCML06AEB2按需/As required 注 ：在加强夹的两个接口表面以及加强夹和支撑杆之间的接口表面涂密封剂。NOTE: Application of the sealant is required at the interfaces between the two clamp halves and at the interfaces between the clamps and the support struts.(b) 在螺栓Item 2上刷涂下述化工品并在加强夹(F5357685020000) Item 1上安装下述紧固件。Apply following chemicals to the bolts, Item 2 and install following fasteners to CLAMP (F5357685020000) Item 1.名称件号需求Non Hardening Jointing Putty-High Temp.Area-StCML06LDG2按需/As required 序号项目号名称件号数量1Item 1CLAMPF5357685020000162Item 2BOLTNSA5031-5-42163Item 3WASHERNAS1149D0563K164Item 4NUTNAS1726-5E16 (c) 使用下述化工品对密封剂CML06AEB2的可见边缘进行保护。Protect the visible edges of the sealant, CML06AEB2, with followeing chemicals: 名称件号需求Varnish-Electrical Bonding StructureCML04TMB2按需/As required (d) 在安装的加强夹和紧固件上使用下述化工品.On the clamps and fasteners which you have installed, apply following chemicals.名称件号需求Corrosion Preventive Compound-Water Displacing &CML12ADB1按需/As required E. 结束工作close-up(1) 确认工作区域清洁干净，没有遗漏工具和其他设备。Make sure that the work areas are clean and clear of tools and other items of equipment(2) 关闭接近舱门313AL。Close the accessory compartment access door 313AL.(3) 关闭照明开关4LJ。Set the light switch 4LJ to OFF.(4) 关闭维护门312AR。Close the maintenance door 312AR.(5)