WOHA33_4919135_319_AT-H78-30-R00-002

Hong Kong Airlines LimitedHong Kong Air Cargo Carrier Limited香港航空有限公司香港货运航空有限公司F-D-099Hong Kong Airlines MEDHong Kong Airlines LimitedWO NO/工作指令号SEQ NO/序列号WOHA334919_319_135DM AD 4919135Training and Qualification/培训和资格Technical Record/技术记录ETOPSAD CAOTitleTRENT700 Engine Thrust Reverser Lower Beam Inspection/RepairMcd&Rev/厂家工卡&修订日期标题TRENT700发动机反推下部横梁区域检查/修理EASA AD2018-0148R1CAD 2018-A330-03R1SB A330-78-3023 R00VSB RB211-78-AH677 R0A/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BLNVAT-H78-30-R00-002HR001001动力/PowerplantAIRP/NDT05:00/02:30MP Item/MP号Baseline/依据MP REV/ MP版本号Station/维修站Threshold/首检Interval/重复检HA33-78-COME-020EASA AD2018-0148,SBA330-78-3023,SB78-AH677ISS 3 REV 0PVGNOTE,3300 CY,730 CAAccess Panels/接近盖板Zones/区域Written/编写Approved/批准NONE4002019-04-232019-04-25TOOLS/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1HU80955IMMOBILISERTO1ALL必需/Necessary2HU55148PUMP - HAND, HYDRAULIC TRUTO1ALL必需/Necessary32-069-69-0002ProbeTO1ALL必需/Necessary4OMAT262Temporary marker Felt/Fibre tipTO1ALL必需/Necessary5USN60超声波探伤仪-新型彩色带方波TO1ALL必需/Necessary(其他等效设备/Other equivalent equipment)6SIGMATEST 2-069电导率仪TO1ALL必需/Necessary(其他等效设备/Other equivalent equipment)799D51407291001试块TO1ALL必需/Necessary(其他等效试块/Other equivalent test specimen)899D55109001000试块TO1ALL必需/Necessary(其他等效试块/Other equivalent test specimen)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198A24403000000CABLE HOLDING STRAPTO1ALL视情/On condition2FK24273COVER - COMMON NOZZLE ASSEMBLYTO1ALL视情/On condition3OMAT2/101Lint free cloth 不起毛布TO1ALL视情/On condition4ZBKZB电动刻字笔TO1ALL视情/On conditionPARTS 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1ASNA2001T4-5SCREWAS2ALL视情/On condition2ASNA2397C10LWASHERAS1ALL视情/On condition3NAS6403U1BOLT HEX HEADAS1ALL视情/On condition4NSA5050-4CNUTAS2ALL视情/On condition5OMAT1/257CLEANERCH1ALL视情/On condition6OMAT402Petroleum jellyCH1ALL视情/On condition7OMAT8/107sealantCH1ALL视情/On condition8OMAT175DChromate Conversion Coating for AluminiumCH1ALL视情/On condition9NAS1587-5CWASHERAS9ALL视情/On condition10NSA5057-5NUTAS9ALL视情/On condition11OMAT8/154ADHESIVECH1ALL视情/On condition12MS21250-05016BOLTAS7ALL视情/On condition1391B456-00SHIMAS2ALL视情/On condition1491B216-00SHIMAS2ALL视情/On condition15OMAT7/205PRIMERCH1ALL视情/On condition1691B458-00SHOULDERED BUSHING LOCKAS3ALL视情/On condition1791H119-00Kit, Latch L7 Bush RepairAS1ALL视情/On condition(包含/Including:NAS5050-4C 1EA, 91H124-00 1EA,91H122-01 1EA, 91H123-01 1EA)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HDTR3415LTR94178428A3304306*RH ENG 4130KS2PN-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 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:_AT-H78-30-R00-002 HR001001 W/O:4919 AC:BLNV页码：3 / 54工卡Job card:HA33-78-COME-020TITLETRENT700 Engine Thrust Reverser Lower Beam Inspection/RepairPerfInsp标题TRENT700发动机反推下部横梁区域检查/修理工作者检查者WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE INPOSITION BEFORE YOU START A TASK ON OR NEAR:- THE FLIGHT CONTROLS- THE FLIGHT CONTROL SURFACES- THE LANDING GEAR AND THE RELATED DOORS- COMPONENTS THAT MOVEMOVEMENT OF THE COMPONENTS CAN KILL OR INJURE PERSONS.警 告：工作开始之前，请确保安全设备和警告声明放置于正确的位置： 飞控系统 飞控系统舵面 起落架及相关舱门 作动部件 部件的作动会导致人员受伤。WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE CORRECTLY INSTALLED ON THE LANDING GEAR. THIS PREVENTS UNWANTED MOVEMENT OF THE LANDING GEAR.警 告：确保起落架正确地安装安全销，可防止起落架意外作动。WARNING: YOU MUST BE CAREFUL WHEN YOU WORK ON THE ENGINE AFTER THE ENGINE T IS SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME AFTER SHUTDOWN AND BURN YOU.警 告：在发动机关车后进行发动机部件的维护工作必须小心烫伤。发动机部件的余热会保持很久可能造成烫伤。WARNING: MAKE SURE THAT THE ENGINE IS SHUTDOWN NOT LESS THAN FIVE MINUTES,BEFORE YOU START WORKING ON THE ENGINE.警 告：执行工作时，确保发动机停止运转超过5分钟。WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE INJURY. IF YOU GET AN INJURY, PUT IT IN COLD WATER FOR 10 MINUTES. THEN GET MEDICAL AID.警 告：不戴劳保手套不能接触发动机未冷却部件，否则会造成烫伤。若发生烫伤，将烫伤部位浸在凉水中10分钟，然后寻求医疗救治。WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.警 告：在反推区域工作时需要执行反推限动，如果没有执行反推限动，可能会导致反推工作造成人员受伤或飞机损坏。WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.警 告：确认遵守所参考手册中所有的警告和注意事项。a. Refer to AMM TASK 78-30-00-010-803-A and Figure.2, access to the thrust reverser inspection T areas.参考AMM TASK 78-30-00-010-803-A及图2，接近反推检查区域。b. 6 oclock beam detailed visual and special detailed inspections.6点钟位置横梁特别详细检查和详细目视检查。 CAUTION: YOU MUST NOT START A CONDUCTIVITY INSPECTION WITHIN AN HOUR, AFTER THE ENGINE IS SHUTDOWN AND COWL OPENED. THE ENGINE WILL REMAIN HOTIMMEDIATELY AFTER ENGINE SHUTDOWN AND CAN CAUSE BURNS AND DAMAGE TO THE CONDUCTIVITY PROBE EQUIPMENT.注 意：在发动机停车并打开整流罩后，一小时之内禁止启动电导检查。发动机的余热可能导致导电探头设备烧伤和损坏。NOTE: This inspection requires NDT competence; refer to Airbus NTM Chapter 51-00-00 NDT for requirement.注 释：此工作要求NTD探伤能力，参考Airbus NTM 51-00-00要求执行。For L/H C-duct, complete the inspection per step c & e & g.对于左侧反推请参照步骤c & e & g进行。For R/H C-duct, complete the inspection per step d & f & g.对于右侧反推请参照步骤d & f & g进行。c. LH C-duct special detailed inspection - 6 oclock beam conductivity test.左侧反推特别详细检查-6点钟横梁电导性测试。CAUTION: YOU MUST NOT START A CONDUCTIVITY INSPECTION WITHIN AN HOUR, AFTER THE ENGINE IS SHUTDOWN AND COWL OPENED. THE ENGINE WILL REMAIN HOTIMMEDIATELY AFTER ENGINE SHUTDOWN AND CAN CAUSE BURNS AND DAMAGE TO THE CONDUCTIVITY PROBE EQUIPMENT.注 意：在发动机停车并打开整流罩后，一小时之内禁止启动电导检查。发动机的余热可能导致导电探头设备烧伤和损坏。NOTE: This inspection requires NDT competence; refer to Airbus NTM Chapter 51-00-00 for requirement.注 释：此工作要求NTD探伤能力，参考Airbus NTM 51-00-00要求执行。1. Inspect the Left C-Duct 6 oclock beams with eddy current to test the conductivity for detecting NDT the thermally impacted area, for the procedure only refer to Airbus NTM Chapter 51-10-12.使用电导率测试设备，检查左侧反推6点钟位置横梁，参考Airbus NTM 51-10-12，测试电导率，检测热影响区域。2. Remove the latches 6 and 7, refer to AMM Chapter 78-32-45. Retain all the bolts, washers, T shims and nuts for further installation if they are serviceable. Refer to AIPC 78-32-45 Figure 60if part replacement is needed.参考AMM 78-32-45，拆下锁手柄6，7，参考AIPC 78-32-45 Figure 60视情更换拆下的螺栓、垫片、薄垫片、螺帽等相关部件。3. Record the special detailed inspection data in the table 1. T 在表1中记录特别详细检查的数据。 4. Mark the conductivity reference points with a temporary marker, OMat 262. Refer to Figure 5. NDT 使用临时标记笔OMAT 262，参照图5，标记电导率参考点。5. Make sure that the calibration blocks and materials to be inspected are at the same NDT temperature.确保校准块和所检查的材料温度相同。6. Make sure that the paint coating in the inspection area is within the limits of the NDT equipment, refer to Airbus NTM Chapter 51-10-00.参考Airbus NTM 51-10-00，确认检测区域的漆层在检查设备允许范围内。NOTE: Remove the paint, if the thickness is outside the limits of the conductivity. The measurementwill not be accurate, if you do not remove the excess paint thickness.注 释：如果漆层厚度超过电导率极限，需祛除多余漆层，若漆层不祛除，可能会测量不准确。7. Connect the 90 probe with the conductivity portable equipment. NDT 将90探头连接到便携电导率设备上。8. Make sure that a frequency of 60 KHz is selected. NDT 确保频率选择为60 KHz。9. Adjust the instrument in accordance with the equipment manufacturers instructions. NDT 按照设备制造商的说明调试仪器。10. Measure the conductivity at the reference points #A thru #D in the reference area and record NDT the results in the table 1 (LH C-Duct). Refer to Figure 5.参考图5，测量参考区域参考点#A 到 #D的电导率，并将结果记录在表1中（LH C-Duct）。NOTE: Alternative conductivity measurement eddy current probe or instrument can be used, if they meet the requirements of this procedure.注 释：可以使用代替的符合程序要求的电导率测量涡流探头或仪器。11. Calculate the average a = (A+B+C+D)/4 of these measurements and record it in the table 1. NDT 计算A,B,C,D测量值的平均值a（平均值a = (A+B+C+D)/4），并记录在表1中。12. Measure the conductivity in the Pin Hole fitting areas for latch 6 and 7 Front and Rear sides NDT and record the highest value for latch 6 and 7 Front and Rear sides in the table 1. The measured area shall be from the back to the edge of the pin hole cavity with a height, referenced HF or HR, of 57 mm (2.25 in.). Refer to Figures 6 & 7.测量锁6和7前后侧的销孔安装区域的电导率，并在表1中记录此区域测量的最大值。被测量的区域参照图6和图7，即HF或HR，高度为57mm（2.25 in.）。13. Calculate the Conductivity Max deviation for latch 6 and 7: difference between the highest NDT value and the average reference (Value max. average reference). Record it in the table 1.计算锁6和7的电导率最大偏差：最高值与平均值之间的差值（最大值 - 平均值a），并记录在表1中。14. Make a plot of the Thrust Reverser Unit life (Flight Cycles) and %IACS deviation to the NDT applicable Figures as per the results recorded in table 1. Refer to Figure 13 for example.根据表1记录的结果，绘制反推组件使用寿命（飞行循环）和IACS偏差的关系图表，样例见图13。15. Refer to the the Thrust Reverser Unit life (Flight Cycles) and %IACS deviation to the NDT applicable Figures, comply with Figure.9 or Figure.10 (Refer to Fig.14 or Sheet 3 to select ).If it should be performmed SB 78-J078 or replaced the C-Duct, report to PPE. Fill in the next inspection interval in Sheet 1.根据反推组件使用寿命（飞行循环）和IACS偏差的关系图表与图9或图10（参考图14或者表3选择）进行对比判断，如果需执行SB 78-J078或更换反推通知发动机工程师。在表1中填写下次检查间隔。d. RH C-duct special detailed inspection - 6 oclock beam conductivity test.右侧反推特别详细检查-6点钟横梁电导性测试。CAUTION: YOU MUST NOT START A CONDUCTIVITY INSPECTION WITHIN AN HOUR, AFTER THE ENGINE IS SHUTDOWN AND COWL OPENED. THE ENGINE WILL REMAIN HOTIMMEDIATELY AFTER ENGINE SHUTDOWN AND CAN CAUSE BURNS AND DAMAGE TO THE CONDUCTIVITY PROBE EQUIPMENT.注 意：在发动机停车并打开整流罩后，一小时之内禁止启动电导检查。发动机的余热可能导致导电探头设备烧伤和损坏。NOTE: This inspection requires NDT competence; refer to Airbus NTM Chapter 51-00-00 for requirement.注 释：此工作要求NTD探伤能力，参考Airbus NTM 51-00-00要求执行。1. Inspect the Right C-Duct 6 oclock beams with eddy current to test the conductivity for NDT detecting the thermally impacted area, for the procedure only refer to Airbus NTM Chapter 51-10-12.使用电导率测试设备，检查右侧反推6点钟位置横梁，参考Airbus NTM 51-10-12，测试电导率，检测热影响区域。2. Remove the latch covers. Refer to Figure 4. Retain all the bolts, washers and nuts for further NDT installation if they are serviceable. Refer to CMM 78-30-20 Figure 38 Graphic 78-30-20-991-838-A01 if part replacement is needed.参考图4，拆下反推锁保护罩，并视情更换拆下的螺栓、垫片、螺帽等相关部件。如需更换参考CMM 78-30-20 0 Figure 38 Graphic 78-30-20-991-838-A01。3. Record the special detailed inspection data in the table 2. NDT 在表2中记录特别详细检查数据。4. Mark the conductivity reference points with a temporary marker, OMat 262. Refer to Figure 5. NDT 使用临时标记笔OMAT 262，参照图5，标记电导率参考点。5. Make sure that the calibration blocks and materials to be inspected are at the same NDT temperature.确保校准块和所检查的材料温度相同。6. Make sure that the paint coating in the inspection area is within the limits of the NDT equipment, refer to Airbus NTM Chapter 51-10-00.参考 Airbus NTM 51-10-00，确认检测区域的漆层在检查设备允许范围内。NOTE: Remove the paint, if the thickness is outside the limits of the conductivity. The measurement will not be accurate, if you do not remove the excess paint thickness.注 释：如果漆层厚度超过电导率极限，需祛除多余漆层，若漆层不祛除，可能会测量不准确。7. Connect the 90 probe with the conductivity portable equipment. NDT 将90探头连接到便携导电设备上。8. Make sure that a frequency of 60 KHz is selected. NDT 确保频率选择为60 KHz。9. Adjust the instrument in accordance with the equipment manufacturers instructions. NDT 按照设备制造商的说明调试仪器。10. Measure the conductivity at the reference points #A thru #D in the reference area and record NDT the results in the table 2 (RH C-Duct). Refer to Figure 5.参考图5，测量参考区域参考点#A 到 #D的电导率，并将结果记录在表2中（RH C-Duct）。NOTE: Alternative conductivity measurement eddy current probe or instrument can be used, if they meet the requirements of this procedure.注 释：可以使用代替的符合程序要求的电导率测量涡流探头或仪器。11. Calculate the average a = (A+B+C+D)/4 of these measurements and record it in the table 2. NDT 计算A,B,C,D测量值的平均值a（平均值a = (A+B+C+D)/4），并记录在表2中。12. Measure the conductivity in IFS Flange area and record the highest value for IFS NDT Flange in the table 2. The measured area shall be with a width, referenced WF, of 14 mm (0.55 in.). Refer to Figure 8.测量IFS法兰区域的电导率，并在表2中记录测量的最大值。测量区域的宽度WF应为14 mm（0.55 in）。 参考图8。13. Calculate the Conductivity Max deviation for IFS Flange: difference between the NDT highest value and the average reference (Value max. average reference). Recordit in the table 2.计算IFS法兰区域电导率的最大偏差：最高值与平均值之间的差值（最大值 - 平均值a）。 并记录在表2中。14. Make a plot of the Thrust Reverser Unit life (Flight Cycles) and %IACS deviation to the NDT applicable Figures as per the results recorded in table 2. Refer to Figure 13 for example.根据表2记录的结果，绘制反推组件使用寿命（飞行循环）和IACS偏差的关系图表，样例见图13。15. Refer to the the Thrust Reverser Unit life (Flight Cycles) and %IACS deviation to the NDT applicable Figures, comply with Figure.11 or Figure.12(Refer to Fig.14 or Sheet 3 to select ). If it should be replaced the C-Duct, report to PPE. Fill in the next inspection interval in Sheet 2.根据反推组件使用寿命（飞行循环）和IACS偏差的关系图表与图11或图12（参考图14或表3选择）进行对比判断。如果需更换反推通知发动机工程师。在表2中填写下次检查间隔。e. LH C-Duct Detailed Visual Inspection and Special Detailed Inspection of the 6 oclock beam 5, 6 & 7 latches and Outer Fixed Structure (OFS) rear areas.左侧反推6点钟横梁和锁5,6,7及外部固定结构区域详细目视检查。1. Record the general data in the Record Data Sheet Table 1. T 将数据记录在记录数据表1中。2. Check the pin holes shouldered bushings of latches 6 and 7 for bush migration. T Refer to Figure 3.参考图3，通过晃动的方式进行锁6，7对应销孔的轴肩衬套的检查。NOTE: This step is not required on latch 7 post SB 78-J078.(Judge the configuration per the modified nameplate whether marked with SB 78-J078)注 释：此步骤对于锁7的的检查要求，只适用于未执行SB 78-J078的反推。（可通过改装铭牌判断：若改装铭牌上刻有SB 78-J078，则执行此SB，否则未执行