WOHA33_1051LNC 3C83_253_AT-720000-290-833

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WOHA331051_253_83ETOPS 培训方式105183通用类/GenericTitleBorescope Inspection of Inner and Outer Combustion Chamber Assemblies and First Stage Vanes (AP-8 and AP-9) for Engine with Talon II CombustorMcd&Rev/厂家工卡&修订日期标题孔探检查有talon II 型号燃烧室发动机的内、外侧燃烧室组件及一级静子叶片(AP-8 and AP-9)AMM 72-00-00-290-833 2014-01-01A/C/飞机号Subtask No/工卡号JC Rev/工卡版本号Workarea/工作区域Skill/工种Man Hour/工时BLNCAT-720000-290-833HR001000动力/PowerplantNDT12:00MP Item/MP号Baseline/依据MP REV/ MP版本号Station/维修站Threshold/首检Interval/重复检HA33-724100-P1-1MPD 724100-P1-1,MRB 72.41.00/01-PWIssue 2 Revision 3PVG700 CY,2400 FH700 CY,2400 FHAccess Panels/接近盖板Zones/区域Written/编写Approved/批准415BL 416BR 417AL 418AR 425BL 426BR 427AL 428AR413 4232014-02-252014-02-26TOOLS/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1856A1321FIBERSCOPE SET(孔探设备-光纤孔探仪)TO1ALL(必需/Necessary)或等效工具2PWA88012PIN-LOCK,DIRECTIONAL CONTROL VALVETO1ALL(必需/Necessary)3PWA88003PUMP, HYDRAULIC - THRUST REVERSER DOORTO1ALL(必需/Necessary)4856A1320RIGID BORESCOPE KIT(孔探设备-刚性孔探仪)TO1ALL(必需/Necessary)或等效工具5PWA88004SLING, SUPPORT - THRUST REVERSERTO1ALL(必需/Necessary)6PWA86411导向管-孔探用TO1ALL(必需/Necessary)7TT-I-735异丙醇-Non Aqueous Cleaner-Isopropyl AlcoholTO1ALL(必需/Necessary)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1AMS5687LOCKWIREAS1ALLlockwire0.032in dia2ST1142-012GASKETAS1ALL(必需/Necessary)3ST1146-08GASKETAS1ALL(必需/Necessary)4673049GASKETAS1ALL(必需/Necessary)适用性参考IPC5PWA36001ANTISEIZECH1ALL(必需/Necessary)(P06-023)参考AMM7230006512640GASKETAS8ALL(必需/Necessary)数量按需7AMS58850.8mm 保险丝AS1ALL(必需/Necessary)8P03-001Oil, Lubricating, Turbine EngineCH1ALL(必需/Necessary)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152U022GASKETAS1ALL适用性参考IPC/(视情/As Necessary)2P06-021COMPOUND ANTIGALLINGCH1ALL(视情/As Necessary)357T844GASKETAS1ALL适用性参考IPC/(视情/As Necessary)PARTS INFORMATION/部件信息:NOTE: The component in PN,SN form is need to do periodic maintenance. For the return repair or retrofit，the form is PN,SN of the removed component. And the PN-IN,SN-IN would be written according to new parts after finish. For the non- returns(such as weight, test)，the form is PN,SN of the on-wing maintenance component. And fill the PN-IN,SN-IN with bias after finish.注释：件号、序号栏指需要定期执行维修工作的部件。对于要求更换拆下返厂工作的部件，该栏指拆下件、序号信息。完成工作后装上件号和序号栏请填写相关装机件信息；对于在位执行工作的（如称重、测试等），该栏指在位工作部件件、序号信息，完成工作后装上件号和序号请用斜线画去。PN/件号SN/序号ATA/章节ZONE/区域FIN/代码LOCATION/装机位置PW4170P73501072420A3300003RH ENGINEPN-IN装上件号SN-IN装上序号REMOVAL REASON AND COMPONENT TASK REQUEST拆件原因及其部件工作要求TASK NOTE工作注释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 Applivable) 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:_HA33-724100-P1-1 W/O:1051 AC:BLNC页码，2 / 51工卡Job card:HA33-724100-P1-1TITLEBorescope Inspection of Inner and Outer Combustion Chamber Assemblies and First Stage Vanes (AP-8 and AP-9) for Engine with Talon II CombustorPerfInsp标题孔探检查有talon II 型号燃烧室发动机的内、外侧燃烧室组件及一级静子叶片(AP-8 and AP-9)工作者检查者Borescope Inspection of Inner and Outer Combustion Chamber Assemblies and First Stage Vanes (AP-8 and AP-9) for Engine with Talon II Combustor 孔探检查内、外侧燃烧室组件及一级静子叶片(AP-8 and AP-9) （安装talon II 型号燃烧室的发动机）Airlines Note: ALL the PW Engines have been post SB PW4G-100-72-179.航空公司注释：我司A330（装有PW发动机）的飞机已经执行过SB PW4G-100-72-179。1. Job Set-up/准备工作 A. Energize the ground service network T 接通地面勤务电源(AMM TASK 24-42-00-861-801)。 B. Safety Precautions/安全预防 T (1) Make sure that the engine 1 （2）shutdown occurred not less than 5 minutesbefore you do this procedure. 确认在开始这项工作前发动机至少关车超过5分钟。C. Get Access to the Avionics Compartment T 接近电子舱(1) Put the access platform in position at the access door 811 . 在电子舱接近门811下放置工作梯。(2) Open the access door 811 . 打开接近门811。(3) Open the protective door of the AC/DC emergency power-center 740VU. 打开AC/DC应急电源中心保护门740VU。D. Open, safety and tag this(these) circuit breaker(s): T 拔出跳开关，装安全夹并挂警告牌：PANELDESIGNATIONFINLOCATIONFOR 4030EM1722VUFADEC B ENG 113KS1D44742VUFADEC A ENG 112KS1Q73FOR 4030EM2722VUFADEC B ENG 213KS2K49742VUFADEC A ENG 212KS2Q74E. Get Access/接近 T (1) Open the left and right aft fan cowl doors (Ref. AMM TASK 71-13-00-010-802) : 打开左右侧后风扇整流罩（参考AMM TASK 71-13-00-010-802）：(a) FOR 4030EM1 415BL 416BR (b) FOR 4030EM2 425BL 426BRF. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-040-804) . T 确认反推装置限动(参考AMM TASK 78-30-00-040-804)。G. Get Access/接近 T (1) Open the left and right thrust reverser cowl doors : 打开左右侧反推（参考AMM TASK 78-30-00-010-801）：(a) FOR 4030EM1 417AL 418AR (b) FOR 4030EM2427AL 428AR(2) Put the adjustable access platform in position. 将接近平台放置在位。2. Procedure/步骤 A. Removal of the Access Port Plug from the Diffuser Case 从扩散机匣中拆下接近堵头Airlines Note: ALL the PW Engines have been post SB PW4G-100-72-179.航空公司注释：我司A330（装有PW发动机）的飞机已经执行过SB PW4G-100-72-179。 (1) Remove six AP-8 access port plugs, and if necessary, the T3 probe, from the diffuser case as follows: 从扩散机匣上卸掉6个AP-8孔探接近堵头，按需卸下T3探头:NOTE: Table 601 shows more specifications for the plugs at the AP-8 location. 注 释：AP-8孔探接近堵头详细位置见表格601。NOTE: All the borescope access port plugs are an orange color for easyidentification. 注 释：为便于辨认，所有孔探接近堵头都是橙色。(a) Inspect the combustion chamber through AP-8 for damage. T 通过AP-8检查燃烧室是否有损伤。(Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.1) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.2) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.3) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.4)(b) Remove the lock wire or safety cable from the plugs that will be removed. M 剪掉堵头上的保险丝拆下堵头。(c) Use a standard 3/8 in. (9.5 mm) socket drive extension and a breaker bar M or ratchet to remove the AP-8 plugs. 用3/8 (9.5 mm)套筒和棘轮或卡啦板拆下AP-8堵头。(d) If necessary, remove the EGT/T3 harness T-3 from probe as follows: M 按需从探头上拆卸EGT/T3电缆束：(Ref. Fig. 654/TASK 72-00-00-991-366 SHEET 654.1)1 Remove the four nuts (1) and (3) and the four washers (2) and (4). 拆下四个螺母（1）和（3），及四个垫圈（2）和（4）。2 Lift the harness off of the T3 probe. 使电缆束脱离T3探头。3 Remove the harness from the spring clip adjacent to the T3 probe. 将电缆束从T3探头临近的弹簧夹子上拔出。(e) Remove the T-3 probe attached to the diffuser case at approximately the M 1:30 oclock position as follows: 按下列步骤拆下大致位于1：30方向连接在扩散机匣上的T-3探头：1 Remove the lockwire or safety cable from the two bolts (5). 剪掉两个螺栓（5）上的保险丝。2 Remove the two bolts (5) from the probe (6). 从探头（6）上拆下两个螺栓（5）。3 Remove the T3 probe (6) and gasket (7). 拆下T3探头（6）和垫圈（7）。4 Remove the bushing (8). 拆下轴衬（8）。5 Remove the bracket (10) and gasket (9). 拆下支架（10）和垫圈（9）。6 Discard all the old gaskets. 报废所有旧的垫圈。(f) Clean the oil off of the T3 probe with Material No P11-014 M (Isopropyl Alcohol (Material No. P11-014) . 用清洁剂异丙醇（NO.P11-014）清洁T3探头上的油污。(g) Remove the AP-8 plugs (total six plugs and T3 probe) and gaskets (7), T (9) and (31) for the examination of the combustion chamber assembly. 拆下AP-8堵头（共6个堵头和T3探头）和垫圈（7）(9)及（31）检查燃烧室组件NOTE: Although there are six AP-8 plugs, it is not necessary to remove all sixplugs for every combustion chamber borescope inspection. Remove the number of AP-8 plugs that are necessary to do a 100 percentinspection of the combustion chamber assembly. 注 释：虽然共有6个AP-8堵头，但并不需要全部拆下，仅需拆下能够满足检查整个燃烧室组件的堵头即可。Borescope Access Port (AP) Data Table 601孔探接近堵头详细数据 601表格Access Port & (Stage)Angular Location, Clockwise from RearGasket P/NPlug P/Nplug Thread LubricantPlug Torque lb-in. (N.m)AP-845 degrees (1:30 oclock)51264050A725P06-023 or P06-054 40-50 (4.519 - 5.649)AP-8127 degrees (4:30 oclock)51264050A725P06-023 or P06-054 40-50 (4.519 - 5.649)AP-8172 degrees (6:00 oclock)51264050A725P06-023 or P06-054 40-50 (4.519 - 5.649)AP-8225 degrees (7:30 oclock)51264050A725P06-023 or P06-054 40-50 (4.519 - 5.649)AP-8277 degrees (9:00 oclock)51264050A725P06-023 or P06-054 40-50 (4.519 - 5.649)AP-8338 degrees (11:00 oclock)51264050A725P06-023 or P06-054 40-50(4.519 - 5.649)CAUTION: THE TEMPERATURES IN THE AREA OF THE ENGINE TO BEEXAMINED WITH THE BORESCOPE MUST BE LESS THAN 150 DEG.F (65.6 DEG.C). DAMAGE CAN RESULT TO THE BORESCOPE EQUIPMENT IF THE GASPATH OR METAL TEMPERATURES ARE MORE THAN 150 DEG.F (65.6 DEG.C). IF YOU CAN COMFORTABLY TOUCH THE CASES ADJACENTTO THE BORESCOPE PORT, IT IS SAFE TO DO THE BORESCOPE INSPECTION. 注 意：发动机孔探区域的温度必须低于150华氏度（65.6摄氏度），否则将会造成孔探设备损坏。如果你触摸孔探探头附近的材料感觉温度宜人，那么进行孔探检查就是安全的。B. Borescope Inspection Procedure for the Inner and Outer Combustion Chamber Assemblies and First Stage Turbine Vanes (AP-8) 对内、外燃烧室组件及涡轮一级静子叶片孔探检查(AP-8)。(1) Carefully put a flexible borescope through each of the access ports (AP-8) for T the examination of the combustion chamber assembly. 小心地将柔性孔探仪穿过每个接近探孔（AP-8）对燃烧室组件检查。(Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.1)(Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.2) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.3) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.4)NOTE: A flexible borescope is necessary for the borescope inspection of thecombustion chamber. Since holes in the combustion liner do not exactly align with the AP-8 ports in the diffuser case. 注 释：选择柔性探头对燃烧室孔探检查是由必要的。用柔性探头能够使你从一个接近探孔观察到更大的区域。(Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.1) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.2) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.3) (Ref. Fig. 653/TASK 72-00-00-991-358 SHEET 653.4)Do not use a rigid borescope. 不要使用刚性孔探仪。(2) Carefully examine the inner combustion chamber assembly liner segments T for damage. (Ref. Fig. 655/TASK 72-00-00-991-258 SHEET 655.1)详细检查内侧燃烧室组件是否有损伤。(3) Carefully examine the outer combustion chamber assembly liner segments for damage. T 详细检查外侧燃烧室组件是否有损伤。(4) Carefully examine the combustion chamber bulkhead segments for damage. T 详细检查燃烧室加强隔框是否有损伤。(5) Carefully examine the fuel injector end caps and guides for damage. T 详细检查燃油喷嘴端盖和导孔是否有损伤。(6) Technical names are given for combustion chamber parts for this inspection T procedure. Use the names shown when you write inspection reports to prevent errors. 在本次检查中，使用到了燃烧室区域的术语。为防止出错，填写检查结果时请使用图示中显示的名字。(Ref. Fig. 656/TASK 72-00-00-991-359 SHEET 656.1) (Ref. Fig. 656/TASK 72-00-00-991-359 SHEET 656.2)(a) Use the part names shown in the figures for all the different parts and shapesof the inner and outer combustion chamber assembly. 对于内、外侧燃烧室组件不同区域，使用图中的部件名字。(b) See the figures for the specifications of the names of axial, radial, andcircumferential for the inner and outer combustion chamber assemblies. 内、外燃烧室组件轴向，径向和轴向的说明参考图。(7) Technical names for combustion chamber damage. Use the names that follow T when you write about damage in inspection reports. 燃烧室的损伤命名。填写损伤报告时使用以下名字。 (Ref. Fig. 656/TASK 72-00-00-991-359 SHEET 656.1) (Ref. Fig. 656/TASK 72-00-00-991-359 SHEET 656.2)(Ref. Fig. 657/TASK 72-00-00-991-360 SHEET 657.1)(Ref. Fig. 658/TASK 72-00-00-991-361 SHEET 658.1)(a) Burned material is an area in which a louver is discolored, distorted, or liner segment material is not there. 材料烧伤是指的某处散热环材料退色，变形或散热环唇口缺损。(b) A burn streak is an axial damage area on liner segments with burned material and material that is not there. 烧伤带是指轴向多个散热环烧伤形成的损伤带，并伴随着材料的损失。(c) A hole is an area which has burned fully through a liner segment. Holesfrequently occur with burn streaks. 烧孔是由燃烧室的墙壁被烧穿形成的，烧孔经常伴随着烧伤带。(8) To help you measure the crack or damage length, use the figures that follow. T 参考以下图例可以帮助你测量裂纹或损伤的长度：(Ref. Fig. 659/TASK 72-00-00-991-362 SHEET 659.1)(Ref. Fig. 660/TASK 72-00-00-991-363 SHEET 660.1)These figures give combustion hole dimensions for reference. 这些图给出了烧孔直径作为参考。(9) Permitted service damage limits for the combustion chamber assembly are as follows: T 以下是燃烧室组件的可允许损伤极限：(a) Borescope inspection limits are shown in tabular form. See Table 602. 孔探损伤限制见下表602。(b) The permitted service damage limits shown in Table 602 are calculated from structural analysis specifications only. If the parts are operated when damaged to the maximum limits, it is possible that the parts cannot be repaired at overhaul. 表格602中所示的允许损伤极限仅源于结构分析。如果部件的损伤达到最大极限时继续运行，有可能导致部件在大修中不可修。(c) If the combustion chamber assembly is damaged to the Regular Inspection Interval limits (shown in Table 602) the engine can continue in service. This engine must have the combustion chamber examined again atthe Regular Inspection Interval. 如果燃烧室组件损伤程度在表602中所述的定期检查间隔限制中，那么发动机可以继续服役。必须在定期检查间隔内对该发动机再次检查。NOTE: See the Aircraft Maintenance Planning Document for the time limitsfor each type inspection interval. 注 释：每种检查间隔请参考飞机维修方案。(d) If the combustion chamber assembly is damaged to the Reduced InspectionInterval limits (half the Regular Inspection Interval) the engine can continue in service. This engine must have the combustion chamber examined againat the Reduced Inspection Interval. 如果燃烧室组件损伤程度在降低检查间隔限制范围内（1/2定期检查间隔），发动机可以继续服役。必须在降低后的检查间隔内对该发动机燃烧室再次检查。(e) If the combustion chamber assembly is damaged to the Additional ReducedInspection Interval limits (1/4 the Regular Inspection Interval) the engine can continue in service. This engine must have the combustion chamber examined again at the Additional Reduced Inspection Interval. 如果燃烧室组件的损伤程度达到进一步降低检查间隔的要求(1/4定期检查间隔)，发动机可以继续服役。必须在进一步降低检查间隔内对该发动机燃烧室再次检查。(f) If the combustion chamber assembly is damaged more than the Additional Reduced Inspection Interval limits, the engine cannot continue in service. It is permitted to ferry the aircraft for a maximum of fifty hours only to a repair station. This engine must be removed for repair of the combustion chamberassembly. 如果燃烧室组件的损伤程度达到更深一步降低检查间隔限制的要求，那么该发动机不能继续服役。只允许最多50个小时内将飞机送到维修站。必须拆下该发动机对燃烧室组件修理。Combustion Chamber Area Borescope Inspection Damage Limits Table 602燃烧室允许损伤限制表格602(Ref. Fig. 661/TASK 72-00-00-991-364 SHEET 661.1) (Ref. Fig. 661/TASK 72-00-00-991-364 SHEET 661.2) (Ref. Fig. 661/TASK 72-00-00-991-364 SHEET 661.3) (Ref. Fig. 661/TASK 72-00-00-991-364 SHEET 661.4) (Ref. Fig. 661/TASK 72-00-00-991-364 SHEET 661.5) (Ref. Fig. 661/TASK 72-00-00-991-364 SHEET 661.6)(Ref. Fig. 662/TASK 72-00-00-991-365 SHEET 662.1) (Ref. Fig. 662/TASK 72-00-00-991-365 SHEET 662.2) COMBUSTION CHAMBER PERMITTED DAMAGE LIMITS燃烧室允许损伤限制EXAMINE检查DAMAGE损伤DISPOSITION描述Liner segments with combustion holes or igniter holes for cracks (with or without burning)带有燃烧孔或点火孔的衬板上的裂纹（裂纹无论有无烧伤）One axial crack for the full length of the segment and through a combustion or igniter hole.一个轴向裂纹贯穿整个衬板并且穿过一个燃烧孔或点火孔。Permitted for regular inspection interval. 对于定期检查间隔，该损伤是允许的One axial crack with burning downstream of any combustion or igniter hole. Hole width of distress must be less than diameter of hole.一个位于燃烧孔或点火孔下游的轴向烧伤裂纹，烧伤宽度必须小于燃烧孔或点火孔直径。Permitted for regular inspection interval. 对于定期检查间隔，该损伤是允许的Two axial cracks, each for the full length of the segment and through a combu