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A757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNTS - DESCRIPTION AND OPERATION1 . GeneralA. The forward and aft lower engine mounts hold the engine and are attachedat six locations. The forward engine mount is attached to the rearflange of the intermediate case at three locations. The aft engine mountis attached to the double flange on the top of the turbine exhaust caseand at points approximately 35 degrees on the side of the centerline.The lower engine mounts are made to remove the force of the engine thrustand the vertical and side loads. The lower engine mounts can becomelarger in the axial and radial directions when the temperature increases.2 . Component Details (Fig. 1)A. Forward Lower Engine Mount(1) The forward lower engine mount holds the engine at three locations:a shear-pin fitting and two thrust links. The shear pin isinstalled into a mating hole in the rear flange of the intermediatecase and held by four bolts. The two thrust links are attached tothe rear flange of the intermediate case on one side of the shearpin fitting and to the aft end of the mount assembly. The forwardlower engine mount attaches to the strut with four vertical tensionbolts.B. Aft Lower Engine Mounts(1) The aft lower engine mount holds the engine at three points on thedouble flange of the turbine exhaust case. The aft lower enginemount includes two tangential links and a center link which attachesto the same mount fitting. The mount fitting attaches to the strutwith four vertical tension bolts.A757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESENGINE MOUNT - MAINTENANCE PRACTICES1 . GeneralA. This procedure has two tasks, inspect the inner bolts of the enginethrust link clevis mount and retouque both the inner and outter bolts ifany are loose.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. Procedure:(1) Examine the inner bolts of the engine thrust link clevis mount.(a) Bolts with tamper-proof putty:If the tamper-proof putty on the bolt head and putty on theclevis mount are not aligned this indicates possible boltmovement or loosening and is not acceptable.(b) If loosening is incicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).(c) Bolts without tamper-proof putty:Use an inspection merror and light source to visually inspectbolts and washers for visible looseness.(d) If loosening is indicated retorque both the inner and outerclevis mount bolts (AMM 71-21-00/201).TASK 71-21-00-422-038-P002 . Thrust Link Clevis Mount Bolts Retorque - Special Procedure_A. General(1) This task is required after any evidence is seen of loosening of theengine thrust link clevis mount bolts.B. Access(1) Location Zones410 Left Engine Nacelle420 Right Engine NacelleC. ProcedureS 022-016-P00(1) Retorque the bolts which attach the engine thrust link clevis mountat the location closest to the fan exit case to 190 - 215 in-lbs(21.47 - 24.29 Nm).(a) Continue to torque the 4 bolts in a repeated pattern until noloss of torque occurs.EFFECTIVITY_OeA757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINESD. ProcedureS 016-031-P00(1) Open the fan cowl panels (AMM 71-11-04/201).S 046-032-P00WARNING: DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THEOPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OFTHE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TOEQUIPMENT.(2) Do this procedure: Thrust Reverser Deactivation for GroundMaintenance (AMM 78-31-00/201).S 016-033-P00(3) Open the core cowl panels (AMM 71-11-06/201).S 016-034-P00WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN THETHRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CANCAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.(4) Open the thrust reversers (AMM 78-31-00/201).S 226-035-P00(5) ON ENGINES WITHOUT SB 757-71-0037;measure the clearance between the inner and outer metal componentsof the vibration isolator (across the top outboard elastomer).(a) If the clearance is less than 0.06 inch, replace the vibrationisolator the next time the engine is removed(AMM 71-21-03/401).S 226-046-P00(6) ON ENGINES WITH SB 757-71-0037;measure the clearance between the indicator lines located on thesides of the inner and outer members of the vibration isolator.NOTE: Clearance measurements are taken from either the top of bothindicator lines or from the bottom of both indicator lines.A757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINES(a) If the clearance is greater than 0.07 inch, replace thevibration isolator the next time the engine is removed(AMM 71-21-03/401).(b) Examine the shim packs for worn, delaminated or missing shims.1) If the shims are worn, delaminated, or missing, remove thecomplete shim pack from the location that has damage.2) Examine the cowling, compressor case and engine stator vanesystem components for loose shims.3) Replace the vibration isolator the next time the engine isremoved (AMM 71-21-03/401).E. Put the airplane back to its initial condition.S 416-036-P00WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THETHRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, YOU CANCAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.(1) Close the thrust reversers (AMM 78-31-00/201).S 416-037-P00(2) Close the core cowl panels (AMM 71-11-06/201).S 416-039-P00(3) Close the fan cowl panels (AMM 71-11-04/201).TASK 71-21-00-226-048-P006. ENGINES WITH LM-433-SA42 AND LM-433-SA43 VIBRATION ISOLATORS;Vibration Isolator Clearance for the Forward Engine Mount (Fig. 602A)A. General(1) This task does a check of the vibration isolator clearance for theforward engine mount.(2) A drift measurement is taken to make sure that the isolator has notdrifted to the hard stops.(3) The drift measurement is taken in the lateral direction only, usingthe drift indicator marks on the aft side of the isolator.A757MAINTENANCE MANUAL/ / /PW2000 SERIESENGINES(4) This drift measurement gives an rough inspection of the isolator.To get a more accurate measurement, the isolator must be removed andinspected.(5) The 757 aircraft wing has approximately a 5-degree slope from thewing box. This upward slope of the wing places an inboard side loadon the isolator causing the isolator to translate. Once theisolator has translated .15 inch (3.81 mm) laterally, it contactsthe lateral stops. To make sure that the isolator is not on thestops during cruise, a measurement is taken on the ground with theengine weight on the isolator.(6) Since a 1 g load is always pulling inboard, the drift will beinboard. The outer member will always move inboard, no matter if itis on the left or right wing of the airplane.(7) The forward isolator has drift marks on its side as shown inFigure 602A, Sheet 1. When the isolator has no drift, the marks onthe inner and outer members line up with a ruler, as shown in theclose-up view.B. References(1) AMM 71-11-04/201, Fan Cowl Panels(2) AMM 71-11-06/201, Core Cowl Panels(3) AMM 71-21-01/401, Lower Forward Engine Mount(4) AMM 71-21-03/401, Forward Engine Mount Isolator(5) AMM 78-31-00/201, Thrust Reverser SystemC. Access(1) Location Zones411 Left Engine421 Right Engine(2) Access Panels413AL/414AR Fan Cow