EFTA01734810.pdf

Pin. Engr. 0434 A/C Reg. A6DFR Work Order Rev Date: 04-Aug-I3 14:18:46 Date Raised : 09 Jun I3 W/O Number : 19162 Aircraft keg : A6DFR Due Date : Start Date : os ri 04 Aug 14 Completion Date : .08 Aug W Planned MEI : 0 Actual MH : 0.00 RO yat L SETT Company : Due at Aircraft Hours : 0.00 Performed at Aircraft Hours : 1 .44(kri%NA o Due at Aircraft Cycles : 0 Performed at Aircraft Cycles : \66A Description : _ ENGINE#I INSTALLATION Code Maintenance Description Position Item MEI Actual Mil Completed Task Card WS Del e opt ion: GE AIRCRAFT ENGINE CFM56-7-B27 SERIES 737-Sic 71-040/ P/N: CFM56-7-82M33 PINS/NI ISII.48-• ri-C i - 4_0 I 0 737-SL-71-049 2 PIN Description: GE AIRCRAFT ENGINE CFM56-7-B27 SERIES SWC873-71-015 PM: CFM56-7-827/B3 PIN SIN: diet 13 -+G i -4.0 I 0 SWCB73-71-020 TWO 19162 Page: I of 2 Printed 04 Aug 13 EFTA_R1_00013342 EFTA01734810  Pln. Engr. 0434 A/C Reg. A6DFR Technical Work Order Date Raised : 09 Jun 13 TWO PLANNING STATEMENT I Aircraft Registration: A6DFR Aircraft Type: 8737-700 A.M.S. Ref: 6,"i Ms Station: OMAA AMS Revision Date: 4Pe /3 Check: e 4. 4 /A/ z 4(0 . tevsnItz 4-7,6,c/ Assurance: I hereby certify that all mandatory, current schedulred and non-scheduled requirements due are included in this W/O to the latest revision / issue. FOR CMR : the paperwork issued in this W/O reflects the accurate current mandatory MODS status and scheduled maintenance status. Planning Engineer: Date: 4. S • .43. CHECK CONTROLLER I LAE STATEMENT Item 2 to be filled in by Controlling LAE prior to the return of the TWO to tech records 2 Check Controller I LAE Final Clearance: This W/0 has been carried out and all task cards. work documents and NRCs are correctly stamped/closed and accounted for. In this respect, this W/O can be considered complied with and closed. This W/O has been complied with using the following main) approval: Presidential Flight UAF. GCAA EM/PFD/89 or Royal Jet UAE GCAAAMO/I53/05 or Other (detail as applicable,. This W/O has been carried out referring to AMM revWon Check Supv: 0 U.T.C.: A 0 Date: c •\ TWO COMPLIANCE UPDATE 3 Technical Records: Task Cards. NRCs and all other documents required, checked for correct completion and are all accounted Sign: Date: /42 / 6 S /7 13 for. 4 Planning Engineer: Paper work checked and all significant items noted. Information passed on to des elopment as required. Sign: Date: 5 Technical Records: TWO closed is IRAN. Compliances. updated. All NRCs emceed. Component / MOD status updated as required. Sign: Date: al' e TWO 19162 Page: 2 of 2 Printed 04 Aug 13 EFTA_R1_00013343 EFTA01734811  wo TIC I I AT' Type: ra rd No: 737.5471-049 Task Card Engineering Order PiN:1 EMS6 7-1127:113 IS N:1 itine"t lama: Sequence Rev No I Task MOD Origin Doc . at laptit Date: MMus : 0.00 Rev Date - 16-Feb-11 Trade Origin Ref: 737-a-71-049 Task Interval. No. Men 0.00 Revised By : 1108 Zone ATA Ref : 71 TITLE AFT ENGINE MOUNT THRUST LINK DESIGN IMPROVEMENT - INTRODUCTION OF -ROTATION A R MlaterbliTooh BacmmxDocummts Access: 310A2040-7 (DMI2 NOT4N Work Step Task Details Performed Certified 1 Observe all cautions & warnings as specified in the relevant section of the AMM. 2 CAUTION: DO NOT REMOVE THE TWO THRUST LINKS AT THE SAME TIME. THE ENGINE CAN MOVE REARWARD AND DAMAGE ENGINE FAIRINGS. THE MOVEMENT WILL ALSO MASS IT VERY DIFFICULT TO RE-INSTALL THE PAWL PINS. Remove the forward end of the LEFT thrust link Ill as per AMM Subtask 71-21-02-020-001-F00: A. Remove the LPT cooling air tube. B. Remove the nut (3] and end cap (2) at forward end of the thrust link [1]: i) PAWL PINS WITH A SPRING LOADED PAWL; Hold the spring-loaded pawl in while you remove the nut [3]. NOTE: You can use the thread protector, a metal or hard plastic tube, or another nut to hold the pawl in. ii) PAWL PINS WITH A COTTER PIN; Remove the cotter pin before you remove the nut (3). C. Remove the pawl pin (5] and washer [4] from the forward end of thrust link. OwDleWnDaW:5/8/1) Defect Sinnaturrttesed: e :Lr l :r ® Certifies that the work specified except as otherwise specified was earned out in accordance w Ph CAR 145 and in respect to that work the aweralUaweraft component is considered If for release to service. Print Date: 04 Ate4 Page I of 7 EFTA_R1_00013344 EFTA01734812  WO MUM TIC III • Task Card Engineering Order CF.%156.7.itrb11.3 -Meta- cr./ r7o i) Remove the washer [6] if it is installed. a) The washer [6] is the recommended installation. 3 Install the forward end of the LEFT thrust link [1] as per AMM Subtask 71-21-02-420-001-F00: A. Apply the D00006 Never-Seez NSBT-8N compound to the threads, shank and below the head of the pawl pins [S] and to the bushings and bores (Views A-A and B-8). B. Install the pawl pin [5], washer [4] and washer [6] at the forward end of the thrust link: i) The chamfered side of the washer [6] faces the spherical bearing C. Install the end cap (2] and nut [3]: i) Make sure the flat side of the end cap [2] is against the shoulder of the pin. ii) PAWL PINS WITH A SPRING LOADED PAWL; Make sure the spring-loaded pawl is in the extended position after you install the nut [3]. D. Tighten the nut [3] or the head of the pawl pin [51 to 290-510 pound-inches (32.8-57.6 Newton meters). NOTE: You can apply the torque to the nut or the head of the pin. E. PAWL PINS WITH A COTTER PIN; Install the cotter pin. F. Install the LPT cooling air tube. 4 CAUTION: DO NOT REMOVE THE TWO THRUST LINKS AT THE SAME TIME. THE ENGINE CAN MOVE REARWARD AND DAMAGE ENGINE FAIRINGS. THE MOVEMENT WILL ALSO MARE IT VERY DIFFICULT TO RE-INSTALL Conviction Date 57 V I 3 Defect Ras fL : A Y 6) Signature Certifies that the work specified except as otherwise specified was carried out in accordance w ah CAR 145 ndto respec to that work the aircraft/aircraft conponent is considered 14 for release to service. Print Date: 04-Aur.13 Page 2 of 7 EFTA_R1_00013345 EFTA01734813  wo A/C Type: Card No: 737-SL-71449 • Task Card Engineering Order P/N: CPM%-7.827/83 WM: -*Stun1 - 4-4 17 to THE PAWL PINS. Remove the forward end of the RIGHT thrust link (1) as per ANN Subtask 71-21-02-020-001-F00: D. Disconnect the T3 sensor from the T3 sensor bracket and the T3 sensor bracket from the engine. E. Remove the nut (3) and end cap [2) at forward end of the thrust link (11 : i) PAWL PINS WITH A SPRING LOADED PAWL; Hold the spring-loaded pawl in while you remove the nut [31 NOTE: You can use the thread protector, a metal or hard plastic tube, or another nut to hold the pawl in. ii) PAWL PINS WITH A COTTER PIN; Remove the cotter pin before you remove the nut [3). F. Remove the pawl pin (51 and washer (4) from the forward end of thrust link. i) Remove the washer (6) if it is installed. a) The washer (61 is the recommended installation. 5 Install the forward end of the RIGHT thrust link (1] as per AMM Subtask 71-21-02-420-001-F00: A. Apply the D00006 Never-Seez NSBT-BN compound to the threads, shank and below the head of the pawl pins (51 and to the bushings and bores (Views A-A and B-B). .12 1 B. Install the pawl pin [5), washer [4] and washer (6] at the forward end of the thrust link: i) The chamfered side of the washer (6) faces the spherical bearing C. Install the end cap (2) and nut (3]: Conpletion Date O5: Defect Raisedre — Sognature .112 Cendes that the work speoled except as otherwise specified was carried out in accordance w qh CAR 145 and Or rapect to that work the aircraft/aircraft component is considered f I for release to service. Print Dale: 0.1.46p13 Page 3 of 7 EFTA_R1_00013346 EFTA01734814  WO IIIW T/C MIT Mill VIEIli IIIEll ripe: f a d \o: 3 I -'1-O4" Task rd NC al Mr- WO: Si]: AIIIIIIIL—ill Engineering Order CIAI56-74127133 '11.411-0 1) Make sure the flat side of the end cap (2] is against the shoulder of the pin. ii) PAWL PINS WITH A SPRING LOADED PAWL; Make sure the spring-loaded pawl is in the extended position after you install the nut (3). D. Tighten the nut [3) or the head of the pawl pin (51 to 290-510 pound-inches (32.8-57.6 Newton meters). NOTE: You can apply the torque to the nut or the head of the pin. E. PAWL PINS WITH A COTTER PIN; Install the cotter pin. F. Re-connect the T3 sensor bracket to the engine and the T3 sensor to the T3 sensor bracket. Ccapieem : 5/ / / Defect Raised Y QC signawmt eL Certifies that the work specified except as otherwise speeded was carried out in accordance w sh CAR 145 and ir respec to that work the aircraft/eke:aft conponer* is considered It for release to service. Prat Date: 04-At '; Page 4 of 7 EFTA_R1_00013347 EFTA01734815  WO ~~~IUI1IRIIm~uA TIC 1 11111111III IIIICIII 11 ILI II 11111' I I -"I • Task Card A.:Cited WO 1)762 :u Engineering Order CC r)I56.7-827/B3 , ( 7-0 7374.7M Mel . BB J Rae 43. ON 148010 PMA Cud: Stress Jot VIP Cuebnn (6) rt_earns PentedbyPtAll IC Feb 2011,09 US, DO NOT USE AFTER: Mei) 71-21-02/401 FIG. EFFECTNITY: CFMSS ENGINES> BB/ ALL /FT Midler [3] NUT [2] END CAP 1 -; >- DI THRUST LINK (5] PAW PH [4) WASHER (4) WASTER Id WASHER (te PAVA. IA WEND CAP .451 C.) wur a (1/1HRUIST LINK THRUST LAW MOM: ROIII THRUST UNK IS SHOWN, LEFT THRUST LINK IS OPPOSITE O PITTING EFTA_R1_00013348 EFTA01734816  wo III!' MO TIC IIIIMill MAINEMBININ Task Card Engineering Order CFM54.7..827513 73I ,Gll NAM fib J 0633A101.OBJ Prnied by PAM 16,662011.10:36 46 Rry 43 - O.1162010 iSLAWArtSCO' DO NOT USE AFTER. PMA CuM. Bush inn JO I VIP ClanomaN) (Bail 71-21-02/401 FIG. EFFECTIVITY. CFN156 ENGINES P. BBJ ALL I.:I WASHER (1) THRUST UNK THRUST UM< FITTING ra END CAP fal NUT (EXAMPLE) B-B N" APPLY ANTI-SEIZE COMPOUND AS INDICATED EFTA_R1_00013349 EFTA01734817 1 W° IIIIIiILIJlIII,lUIIII Ti° A/C Type: 3 -Nt 71-049 Task Card we%2 ze-361 1.9162› • Engineering Order CFM56-7-B27513 SM: RS41-tee. gaff 131-617111 AMA . 8B J • 13637A101•BBJ PrimedbyPM& 16 Feb 2011.1D37 35 Rev 43 0e15/21)10 gueireensre DO NOT USE AFTER: PIRA Bust Business is I VIP Cuslorned(f) (80J) 71-2142/401 FIG. EFFECTIVITY: CFM68 ENGINES > BBJ ALL LPT COOLING AJR1USE 0 EFTA_R1_00013350 EFTA01734818 W/O: 19162 Seq No. : 1 Print Date: O8/O4/2O13 Task Card 737-SL-71-O49 PN: CFM56-7-827/B3 SN: 888148 Image Attachment: 1 cf 3 Description: AFT ENGINE MOUNT THRUST LINK DESIGN IMPROVEMENT - INTRODUCTION OF ANTI-ROTATION WASHER T3l.WINII AWN •OIS D633At0141BJ Bar 43. Oct 16/2010 linnisobyPhilA 16F eb 30/1.09:17:63 MIA Dust: Business i MELO 'VIP custiorner00 p_.er.crn:sea DOS/9113SE Ant R: 71-21-02/401 FIG. EFFECTIVITY: CFM5G ENGINES > 8 BJ ALL • ft] misuser UNA( c) er£ AFT MOM WAR rii a‘ A Is3 HUT s.,. cc II THRUST GBP Oq 0 EVID ER PAWL PIN I4) WASHER II %MASHER q PAWL MN IW WASHER FAD RI END CAP (31 NUT' III 'MMUS UNIC c ) THRUST LINC lytM MOUT THRUST LINIC IS SHOWN ',roma LEFT THRUST LINK LS OPPOSITE. Figure 401. Thrust Link InstslIstIon Sheet 1 Paw, 11a 1 OOZING ono tiviErArf -Copetvlie•teeptabs.iw.....••• ••• EFTA_R1_00013351 EFTA01734819 W/O: 19162 Seq No.: 1 Print Date: 08/04/2013 Task Card: 737-SL-71.049 PN: CFM56-7-B27/B3 SN: 888148 Image Attachment 2 of 3 Description: AFT ENGINE MOUNT THRUST LINK DESIGN IMPROVEMENT- INTRODUCTION OF ANTI-ROTATION WASHER 7374/7/4n AMA - as .1 0423411444JOJ PARIS by P MA: le Fab 2011,10:SA4e Re* 4J. Oct 164014 AMA Cum: Suelnes Jet /VIP cueftwre(sI aim:rave DO NOT USE AFTER: 030J) 71-21-02/401 FIG. EFFECTIVITY: CFNISS ENGINES > BUJ ALL WASHER DB PAWL PIN WASHEI ' (31NUT [I] THRUST [21END CAP LINK THRUST UNK 113 THRUST FITTING LINK [2] END APT CAP 846111E [4[ WASHER tal NUT MOUNT [53 PAWL PIN btu (EXAMPLE) (exAmsn_e) A-A B-B [—> APPLY ANTI-SEIZE COMPOUND AS INDICATED. Figure 401. Thrust Link Installation Sheet 2 Pew-1,41 !: tint. -C.pitkItfr• vip,teitatUe• -11. ral. eer b•dnat, EFTA_R1_00013352 EFTA01734820 WIO: 19162 Seq No. : 1 Print Date: 08/04/2013 Task Card: 737-SL-71-049 PN: CFM56-7-827/83 SN: 888148 Image Attachment: 3 of 3 Description: AFT ENGINE MOUNT THRUST LINK DESIGN IMPROVEMENT - INTRODUCTION OF ANTI-ROTATION WASHER 737.1117141 AMU . 00 J - 01013AI01-007 MTh:4 byPIAA: 16 Feb 20I 1, 10.37 35 RIM 4) - ors i4/2o1 PIN n went". Jed /VIP Conomes(s) eltorinravar DO NOT USE AFTER: 030.0 71-21-02/401 FIG. EFFECTIVITY: GENRE ENGINES > BUJ ALL LPT COOLING /STUBS Flaunt 401. Thrust Link Installation Sheet 3 Pape 1 Cl 1 1OO4C fat!P.RRRT. Care 1Ak 0- palate.Mot • so tot pay brake& EFTA_R1_00013353 EFTA01734821 2 WO T/C ImviI IIIA IIIIIIIII A/C lYpe: t a No SN% ( 11- 3 - 1.0111 • Task Card WO: 19162 Special Work Card PrN: CFM5 7-3127tB3 NN 141114 -g3{4 Input: Sequence: Rev No 0 Task: CC 1:kupn Doc: SWC Input Date : MMus - 0.00 Rev Date: 31-Ai-13 Trade: O lam Ref SWC873.71.015 ['ask Interval No. Men 000 Revised ft • 1108 Zone: ATA ad 71 TITLE CFM56-7B ENGINE INSTALLATION Completion Date : Si 243 Defect Raised : Signature Certifies that the work specified except as otherwise specified was carried out in accordance w ith CAR 145 and is teapot to that work the aercraftfaircraft conponent is considered fit for release to service. Print Date: 04-Aug 13 Page I of I I EFTA_R1_00013354 EFTA01734822 2 WO Una IIU T/C IUIIIIII111111 IIII % (. l•pe ( d\ SA ( I ,3.71-020 Task Card W0: 19142 Special Work Card PEN: CIN156-7-Ii27113 SA: JOIXIM . %laterialgools Reference Docuornts Access: 362A 2976P2 I 856A 1616(302 856A2645O05 856A3700O02 A00160 A RINC 615 DATA WADER AS3208-06 1300676 C71020-91 C71022-6/PFD4I4 C11026-I/PED415 C78019-15 C78020-14 (18023-I COM-1532 COM-2462 CP1039 000006 000015 D00070 D00106 1)00467 000510 D00601 D00623 FR70077-100 M70077-200 0)0018 (300034 600270 002061 032314 0)2345 (i50065 MOBIL Jr II SPL-I521 SP1,1829 SPL-2417 STD-1054 STD-I110 STD-1157 STD-13882 STD-163 STD-3906 STD-585 Work FIT Ps Similar System Nlanitertanee 1'a k Step Task Details (•••sn ukaAne• rr•Ile• • Peri rim I Certified Defect Raised : Signature . t Certifies that the work specified except as otherwise specified was caned out in accordance with CAR 145 and m respec to Mal week the aircraft/aircraft corrponent is considered fa for release to service. l'rin t Dale: On-Aug-13 Page 2 of I I EFTA_R1_00013355 EFTA01734823 2 wo IIIIfII IIIIIIItII II T/C HMI IIIII :VC Type: C St ( 103-71.020 Task Cant 19162 Special Work Card : C FAI56.7- B27/83 SA: aeaus c- 1 Observe all cautions and warnings as specified in the relevant section of the AMM. 2 Prepare the Airplane for the Installation of the Power Plant, as per AMM Task 71-00-02-400-801-F00, Paragraph G. 3 Record the inventory installed on the serviceable engine being prepared for installation. Part Description Part No Test El Serial No Regd. Inlet Cowl YES / NO TAI Valve YES / NO IDG YES / NO C Hydraulic Pump YES / NO -...s... QAD - Hydraulic YES / NO ;.? Pump Primary Nozzle Assy YES / NO Fwd Plug Assy YES / NO Aft Plug Assy YES / NO YES / NO YES / NO YES / NO 4 --' Completion Date : fjs _ rib Defect Ras Y N Signature , Certtlies that the work specified except as otherw ise specified was carted oul in accordance win CAR ;IS respec to that watt the aircraft/aircraft component is considered N for release to service. Print Date: 04-Aug. 13 Page 3 of I I EFTA_R1_00013356 EFTA01734824  2 WO INTIM T/C INNM IIIIIIIflIIIIIiiIIIIIYII II pe: Ca d No: Ss% C B73.71-020 • Task Card NC Reg: Special Work Card I' CIN156-7- R27/83 S/N: agent 2-1-6 Test Part Description Part No Serial No Regd. * YES / NO YES / NO YES / NO YES / NO YES / NO * Reference 737-700/800 AMM Task 71-00-00-800-811-F00 (Power Plant Test Reference Table) 4 Prepare for installation of a serviceable power plant as per 8737 AMM task 71-00-02-400-801-F00, Paragraph F: A. Make sure the configuration of the engine to be installed is compatible with the airplane and thrust reversers, as per AMM Subtask 71-00-02- 210-010-F00. B. Make sure the Flight Management Computer MEDB Software, thrust reverser configuration, and the opposite engine EEC software are compatible with the new engine. C. Make sure that the configuration of the primary exhaust nozzle and the airplane strut are compatible, as per AMM Subtask 71-00-02-210-013- F00. D. Install the compression rod assembly on the 12 o'clock strut of the replacement engine, as per AMM Subtask 71-00-02-900-001-F00. E. Carry out Fluorescent Penetrant Inspection of the forward and aft mount bolts (if the same forward and aft mount bolts from the removal procedure Coripletton Date : .5/, /3 Defect Raised : N.Et 1 Span-trek Certifies that the work specified except as otherwise specified was carried out in accordance with CAR 1i5 and n respect to that work the aircraft/aircraft component is considered I it 'Cit release to service. Prim( Date: 04-Aug I 3 Page 4 of I I EFTA_R1_00013357 EFTA01734825 2 wo TIC A/C Type: Card No: SW0173-714120 Task Card Special Work Cant P/N: CF5064.B27/113 SN: are used again), as per AMM Subtask 71-00-02-230- 001-F00. F. Carry out check of the self-locking feature of the four barrel nuts of the forward engine mount, as per AMM Subtask 71-00-02-210-003-F00. G. Carry out check of the self-locking feature of the four barrel nuts of the aft engine mount, as per AMM Subtask 71-00-02-210-004-F00. H. Carry out a check of the aft engine mount for the correct installation of the center link, as per AMM Subtask 71-00-02-212-001-FO1 I. Carry out a visual check for worn wires at the forward transponder of the upper engine Fire Detector, as per AMM Subtask 71-00-02-210-007- F00. J. Carry out a check of the Fuel Control Module, P5- 2 and the installed HMU for the correct operation of the ENG VLV CLOSED light, as per AMM Subtask 71-00-02-210-008-F00. S Install the Serviceable Engine, as per AMM Task 71- 00-2-400-801-F00, Paragraph G. 6 Apply the final torque to the forward and aft engine mount bolts, as per AMM Task 71-00-02-400-801-F00, Subtask 1-00-02-420-006-F00 and as follows: a) Tighten the forward engine mount bolts to 1080- 1320 pound-inches (122-149 Newton meters) (90-110 pounds-foot).Record Torque Wrench Info: S/N: emtV1 177) -2) Calib. due date: \\EIC A1-. ) b) Tighten the aft engine mount bolts to 1920-2340 pound-inches (217-264Newton meters) (160-195 pounds-foot). Record Torque Wrench Info: Convetion Cele : / ?/1 Defect RstseV Sgnature! Certifies that the work specified except as otherwise specified was carried out in accordance with CAR 145 and n respec to that work the arcraft/arcraft corrponerd is considered fa for retease to service. Print Date: 04 Aue 13 Page 5 of II EFTA_R1_00013358 EFTA01734826 2 WO IIII IIIOIIII T/C IIIGNIN III MIN ve T,pe Card No S‘‘( B 3.71.020 Task Card Alt Special Work Card l'' : CIA156-7.1,127/B3 SIN: S/N: j R -71qc Calib. due date: DEC )1, 7 Carry out duplicate inspection of the installation of the forward and aft engine mount bolts. Inspector Time Date Signature #1 lase O 4 -ezt -% 3 #2 ieVC C -08-is 8 A. Connect Fan Case Connections on the Left Side, as per NIH Task 71-00-02-400-801-F00, Paragraph H. B. Carry out duplicate inspection of the Fan Case Connections on the Left Side (refer to AMM Task 71-00-02-400-801-F00, Paragraph H): Inspector Time Date Signature 13n) #2 1310 0-0-11 9 A. Connect Fan Case Connections on the Right Side, as per AIM Task 71-00-02-400-801-F00, Paragraph I. B.Carry out duplicate inspection of the Fan Case Connections on the Right Side (refer to AMM Task 71-00-02-400-801-F00, Paragraph I): Inspector Time Date Signature #1 1310 Ii_ -4 Ott -OZ - VI -.4::----c- Con:eaten Date :51 g Defect Raised : Signature Certifies that the work specified except as othenv ise specified was carried out in accordance with CAR 145 and h respec to that work the aircraft/aircraft component is considered fit 'or release to service. Prima Date: 04-Aug-13 Page 6 of I I EFTA_R1_00013359 EFTA01734827 2 WO IlIN T/C IN BIM 11115111111}1ll ljpe: and N:( SS ( 14.3-"1.920 Task Card 19162 Special Work Card P/N: CFM56.7.B27/B3 /N: -/J43{14S ;cc #2 1-L,20 e) ( -494-13 10 A. Connect Core Area Connections on the Left Side, as per AMM Task 71-00-02-400-801-F00, Paragraph J.