WOHA33_1594121_148_EOA33-53-0015

Hong Kong Airlines Limited香港航空03110-01Hong Kong Airlines MEDHong Kong Airlines LimitedWO NO/工作指令號SEQ NO/序列號WOHA331594_148_121適航指令(AD) DIC 1594121TitleFuselage Frame/Stringer Attachments - Inspection/RepairMcd&Rev/廠家工卡&修訂日期標題機身隔框/桁條連接處的檢查和修理A/C/飛機號/組別EO JC No./EO工卡EO JC Rev/工卡版本W(wǎng)orkarea/工作區(qū)域Skill/工種Man Hour/工時BLNW/1EOA33-53-0015R00機身/AirframeMDIC84:00Baseline/依據(jù)Operator EO/營運人EOEO Rev/EO版本W(wǎng)ork Type/工作類別Threshold/首檢Interval/重復(fù)檢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/編寫Reviewed/審核Approved/批準2014-12-042014-12-042014-12-04Accomplished完工簽署Complete Date完工日期Station維修站PVGREASON & DESCRIPTION/原因及描述交付前，在對A330-200F一些飛機各機身區(qū)域檢查時，發(fā)現(xiàn)有緊固件丟失情況， 若不及時發(fā)現(xiàn)和修復(fù)，可能會導(dǎo)致裂紋的產(chǎn)生并擴展，從而降低機身機構(gòu)的完整性。故下發(fā)本EO執(zhí)行檢查。 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/必須工具ITEM項目P/N件號DESCRIPTION名稱EQTP類型QTY數(shù)量APP適用性Conditions note互換信息及備注TOOLS IF NECESSARY/視情工具ITEM項目P/N件號DESCRIPTION名稱EQTP類型QTY數(shù)量APP適用性Conditions note互換信息及備注PARTS AND MATERIAL/航材NOTE:OPERATOR MUST GET AND INSTALL THE PARTS THAT CORRESPOND TO THE RELATIVE WORKORDER NO.注釋：請工作者嚴格按照工作指令號領(lǐng)取預(yù)定的航材裝機PARTS AND MATERIAL NECESSARY/必須航材ITEM項目P/N件號DESCRIPTION名稱EQTP類型QTY數(shù)量APP適用性Conditions note互換信息及備注1CML06AAA1SEALANTCH1ALL數(shù)量按需/Quntity2533216D01R01KITAS1ALL無3533217D01R01KITAS1ALL無4533218D01R01KITAS1ALL無5533219D01R01KITAS1ALL無PARTS AND MATERIALIF NECESSARY/視情航材ITEM項目P/N件號DESCRIPTION名稱EQTP類型QTY數(shù)量APP適用性Conditions note互換信息及備注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標題機身隔框/桁條連接處的檢查和修理工作者檢查者A. 通用信息/GENERAL警 告：確認遵守所參考手冊的所有警告和注意事項。WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES.注 意： 遵守使線束和設(shè)備處于良好狀態(tài)的警示信息。當執(zhí)行設(shè)備維護、修理及改裝時，盡可能地保持線束、電氣設(shè)備及工組區(qū)域的潔凈，執(zhí)行下述要求：使用如塑料布、布匹等鋪蓋在上述設(shè)備上；經(jīng)常性的去除線束、電氣設(shè)備上的雜物及其他污染物。這些預(yù)防措施可減少安裝電線時的污染和損傷。若污染,參照ESPM20-55-00處理。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. 標準施工/Standard Practices (a) 飛機隔框的識別，參考AMM 06-31-53, Page Block 001。For the identification of Frame (FR) numbers (Refer to AMM 06-31-53, Page Block 001).(b) 飛機區(qū)域的識別，參考AMM 06-20-00, Page Block 001。For the identification of aircraft zones (Refer to AMM 06-20-00, Page Block 001). (c) 接近蓋板的識別，參考AMM 06-41-53, Page Block 001。For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (d) 緊固件拆裝，參考SRM 51-42-00。 Remove and install fasteners, in accordance with SRM 51-42-00.(e) 標記所有你拆裝的部件，以便于后續(xù)安裝Tag all the parts you must remove and retain to make the subsequent installation easier. (f) 參考AMM Task 20-21-11-911-801擰緊緊固件。To torque tighten the standard threaded fasteners (Refer to AMM Task 20-21-11-911-801).(g) 參照SRM 51-43-00，獲取緊固件的備用和替代信息Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.(h) 若備用和替代緊固件已經(jīng)在飛機上使用，請確保相關(guān)的螺母/套環(huán)與SRM 51-40-00 Mating Part欄中的數(shù)據(jù)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) 鉆孔和去毛刺，參考SRM 51-44-11Obtain fastener hole diameters and drill and de-burr data in accordance with SRM 51-44-11.(j) 緊固件的間隙和斜度，請參考SRM 51-47-00Obtain fastener spacing and margin data in accordance with SRM 51-47-00.(k) 對于鉆鉚釘孔：For the drilling of rivet holes:- 使用軟鉛筆標記鉚釘孔位置Use a soft lead pencil and make marks to show the position of the rivet holes.- 在鉆緊固件孔時，確保邊距合適Make sure that you have the correct edge clearance before you drill the fastener holes.- 若沒有給出，鉚釘孔直徑的公差為+0.1 mm (+0.004 in.)If not shown otherwise, the tolerance for the rivet hole diameter is +0.1 mm (+0.004 in.).- 若沒有給出，鉚釘孔位置的公差為+/-0.2 mm (+/-0.007 in.)If not shown otherwise, the tolerance for the rivet hole position is +/-0.2 mm (+/-0.007 in.).- 用導(dǎo)向孔鉆槍和鉆孔套導(dǎo)出原有的孔Transfer-drill the existing holes with a pilot drill and a drill bush.- 用直徑為2.5mm(0.0984in)導(dǎo)向孔鉆槍鉆新的緊固件孔，然后增加孔的直徑到你需要的尺寸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) 剪裁鉚釘?shù)叫枰拈L度Cut the rivets to the necessary length.(m) 參考SRM 51-46-11，埋頭緊固件孔Countersink the fastener holes in accordance with SRM 51-46-11.(n) 參考SRM 51-24-00，使用密封膠Apply sealant in accordance with SRM 51-24-00.(o) 參考AMM Task 20-21-11-911-801，對標準螺紋緊固件磅力矩To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801.(p) 參考SRM 51-75-12，重新恢復(fù)表面拋光Renew the protective finish in accordance with SRM 51-75-12.(q) 若本EO規(guī)定的緊固件長度不能滿足SRM Chapter 51給出的安裝標準，則可以使用滿足SRM Chapter 51安裝要求的相同規(guī)格或者被批準的替代緊固件，另外，參考SRM Chapter 51 有可能需要安裝墊片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. 施工準備/ PREPARATION (1) 工作準備/Job Set-up(a) 在開始維護工作前，請確認執(zhí)行以下工作：The following items shall be considered as the basic Aircraft configuration beforeyou start a maintenance task:- 飛機停留在位（地面安全鎖和輪擋放置在位）Aircraft on the ground resting on landing gear (the ground safety locks and thewheel chocks are in position on the landing gear).- 發(fā)動機關(guān)車，反推關(guān)閉并鎖定Engine shut down, thrust reversers closed and locked.- 飛機構(gòu)型整潔Aircraft in clean configuration.- 設(shè)置停留剎車Parking brake applied.- 飛機已斷電Aircraft electrical network de-energized.- 液壓系統(tǒng)已釋壓Hydraulic systems depressurized.- 可方便進入客艙和駕駛艙Access to the cockpit and cabin is available.- 所有跳開關(guān)在閉合位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) 飛機靜電接地，參考AMM Task 12-34-24-860-802Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-860-802.(c) 將工作梯放置到前貨艙門821Put access platform(s) in position, below the FWD cargo compartment door 821. (d) 參考AMM 52-31-00, Page Block 001，打開前貨艙門821Open the FWD cargo-compartment door 821, refer to AMM 52-31-00, Page Block 001.(e) 參考AMM Task 25-23-43-000-802，在主貨艙內(nèi)右隔框FR35處，拆下襯里面板 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) 參考AMM Task 53-00-00-000-802，拆下前貨艙地板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) 參考AMM Task 25-52-00-000-801.拆下前貨艙的側(cè)壁板132NXIn the FWD cargo-compartment, remove the sidewall panels 132NX, refer to AMMTask 25-52-00-000-801.(h) 參考AMM Task 25-80-00-000-801，按需拆下絕緣層以接近工作區(qū)域Remove the insulation blankets as necessary to get access to the work areas, referto AMM Task 25-80-00-000-801.(i) 將工作梯放置到后貨艙門822Put access platform(s) in position, below the AFT cargo compartment door 822.(j) 參考AMM Task 52-30-00-010-801，打開后貨艙門822Open the AFT cargo-compartment door 822, refer to AMM Task 52-30-00-010-801 (k) 參考AMM Task 25-55-22-000-801，拆下主艙貨艙（MDCC）的襯板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) 參考AMM Task 53-00-00-000-803，拆下后貨艙地板152VK 和 152WKIn the AFT cargo-compartment, remove floor panels 152VK and 152WK, refer to AMM Task 53-00-00-000-803.(m) 參考AMM Task 25-53-00-000-801.拆下后貨艙的側(cè)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) 參考AMM Task 25-53-00-000-801，拆下后貨艙頂板151FC 和 152FCIn the AFT cargo-compartment, remove the ceiling panels 151FC and 152FC, referto AMM Task 25-53-00-000-801(o) 參考AMM Task 25-80-00-000-801，按需拆下絕緣層以接近工作區(qū)域Remove the insulation blankets as necessary to get access to the work areas, referto AMM Task 25-80-00-000-801.(p) 參考AMM Task 52-30-00-010-803，打開散貨艙門823Open the bulk cargo-compartment door 823, refer to AMM Task 52-30-00-010-803.(q) 參考AMM Task 25-55-22-000-801在主艙貨艙(MDCC)，拆下襯板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) 參考AMM Task53-00-00-000-803，拆除后貨艙地板152WKIn the AFT cargo-compartment, remove the floor panel 152WK, refer to AMM Task53-00-00-000-803.(s) 參考AMM Task25-53-00-000-801，拆除后貨艙頂板151KCIn the AFT cargo-compartment, remove ceiling panel 151KC, refer to AMM Task25-53-00-000-801.(t) 參考AMM Task53-00-00-000-804，拆除散貨艙地板162BFIn the bulk cargo-compartment, remove the floor panel 162BF, refer to AMM Task53-00-00-000-804.(u) 參考AMM Task 25-54-00-000-001，拆除散貨艙側(cè)壁板162EWIn the bulk cargo-compartment, remove the sidewall panel 162EW, refer to AMMTask 25-54-00-000-001.(v) 參考AMM Task 25-55-22-000-801，在主艙貨艙（MDCC），拆下襯板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) 參考AMM Task53-00-00-000-804，在拆下散貨艙的地板162EFIn the bulk cargo-compartment, remove the floor panel 162EF, refer to AMM Task53-00-00-000-804.(x) 參考AMM Task 25-54-00-000-001，拆下散貨艙門的側(cè)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) 參考AMM Task 25-80-00-000-801，按需拆下絕緣層Remove the insulation blankets as necessary to get access to the work areas, referto AMM Task 25-80-00-000-801.D. 檢查/INSPECTION(A)SUBTASK A330-53-3202-對區(qū)域13和14，隔框19到37.4的丟失或不合格的緊固件進行檢查SUBTASK A330-53-3202- FUSELAGE - FORWARD FUSELAGE INSPECTION FOR SUSPECTED MISSING/NON - CONFORMING FASTENERS AT SECTION 13 AND 14 FR19 TO FR37.41. 施工步驟/PROCEDURE (1) 在隔框19，STGR52/STGR53左側(cè)，詳細檢查丟失緊固件At FR19, STGR52/STGR53 LH, do a Detailed Inspection for Missing Fasteners (a) 參考Fig. A-GFAAA Sheet 01，對隔框19，STGR52/STGR53左側(cè)，詳細檢查丟失緊固件At Frame 19 between STGR52/STGR53 LH, do a detailed inspection for missingfasteners, refer to Fig. A-GFAAA Sheet 01:1) 若件號DAN6-6-4，直徑為4.8mm（0.189in）緊固件安裝在如圖 Fig. A-GCAAA Sheet 01, View B的位置，則不需要在此位置做修理，執(zhí)行如下工作步驟：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中記錄檢查結(jié)果。Write the result of the inspection in the Inspection Report sheet refer to Table 1.b 轉(zhuǎn)到步驟D.(A)1.(2)，對隔框20和STGR43 LH，執(zhí)行安裝緊固件的詳細檢查Go to step D.(A)1.(2) At FR20 and STGR43 LH, do a Detailed Inspection for the Installation of Fasteners .2) 若直徑4.8mm(0.189in)的緊固件，并未安裝在如圖Fig. A-GCAAA Sheet 01, View B 所在位置，執(zhí)行以下步驟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 詳細檢查如圖Fig. A-GCAAA Sheet 01, View B所示的，緊固件鄰近區(qū)域的 損傷、變形或者裂紋Do a detailed inspection of the adjacent fasteners for damage,deformations or cracks, as shown in Fig. A-GCAAA Sheet 01, View B: 若在緊固件鄰近區(qū)域發(fā)現(xiàn)損傷或者裂紋，請在下個飛行循環(huán)前聯(lián)系結(jié)構(gòu) 結(jié)構(gòu)工程師獲取進一步的修理If you find damage or cracks at the adjacent fasteners, contactStructure engineer for further instructions before the next flight. 若在緊固件鄰近區(qū)域沒有發(fā)現(xiàn)損傷或者裂紋，請按照SUBTASKA330-53-3216 在下個飛行循環(huán)前完成改裝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中記錄檢查結(jié)果。 Write the result of the inspection in the Inspection Report sheet,refer to Table 1(2) 對隔框20和STGR43左側(cè)的安裝緊固件執(zhí)行詳細檢查At FR20 and STGR43 LH, do a Detailed Inspection for the Installation of Fasteners (a) 參考Fig. A-GFBAA Sheet 01，對隔框20和STGR43左側(cè)的安裝緊固件執(zhí)行詳細檢查At Frame 20 and STGR43 LH, do a detailed inspection for the installation offasteners, refer to Fig. A-GFBAA Sheet 01: 1) 若件號PN EN6081D6，直徑為4.8mm(0.189in)的緊固件按照如圖Fig. A-GCBAA Sheet 01和Fig. A-GCBAASheet 02, View C安裝在位，不需要修理執(zhí)行以下步驟：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中記錄檢查結(jié)果Write the result of the inspection in the Inspection Report sheet, refer to Table 1.b 請轉(zhuǎn)到步驟D.(A)1.(3),在隔框21和隔框22左側(cè)，對丟失緊固件執(zhí)行詳細檢查Go to step D.(A)1.(3), At FR21 and FR22 LH, do a Detailed Inspection for Missing Fasteners .2) 若有直徑為4.0mm(0.157in)的緊固件安裝（硬鋁鉚釘）在如圖Fig. A-GCBAA Sheet 01 和Fig. A-GCBAA Sheet02, View C的位置，請執(zhí)行如下步驟：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 參考圖Fig. A-GCBAA Sheet 02, View C，拆下并報廢直徑4.0mm(0.157in) 的緊固件，并在下次飛行循環(huán)根據(jù)SUBTASKA330-53-3216前完成改裝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中記錄檢查結(jié)果Write the result of the inspection in the Inspection Report sheet, refer to Table 1.3) 若無緊固件安裝在如圖Fig. A-GCBAA Sheet 01和Fig. A-GCBAA Sheet 02, View C 的位置，執(zhí)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 按照圖Fig. AG-CBAA Sheet 02, View C，詳細檢查內(nèi)側(cè)隔框法蘭的表面保護層損傷 和鄰近緊固件的情況（可能有剪切緊固件或者損傷的表面保護層）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. 若在內(nèi)隔框法蘭和/或鄰近緊固件發(fā)現(xiàn)損傷，請在下次飛行循環(huán)前聯(lián)系結(jié)構(gòu)工程師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. 若在內(nèi)側(cè)隔框法蘭或鄰近緊固件處未發(fā)現(xiàn)損傷，請根據(jù)SUBTASKA330-53-3216在下次飛行前完成改裝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 釋：存在導(dǎo)向孔NOTE: Pilot holes exist.b 在Table 1中記錄檢查結(jié)果Write the result of the inspection in the Inspection Report sheet, refer to Table 1.(3) 在FR21 和FR22 左側(cè)，詳細檢查丟失的緊固件At FR21 and FR22 LH, do a Detailed Inspection for Missing Fasteners(a) 參考Fig. A-GFCAA Sheet 01，在FR21 和FR22 左側(cè)，詳細檢查丟失的緊固件At Frame 21 and Frame 22 LH, do a detailed inspection for missing fasteners,