TASK 72-00-00-200-002-B00 Engine General - Examine (Borescope) The HP Compressor (HPC), Inspection-002

DMC:V2500-A5-72-00-0000-04B-312A-B|Issue No:010.00|Issue Date:2020-05-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

V2500-A5 and Post SBE 72-0560 and Post SBE 72-0561

Common Information

TASK 72-00-00-200-002-B00 Engine General - Examine (Borescope) The HP Compressor (HPC), Inspection-002

General

This TASK gives the procedure for the borescope inspection of HP compressor rotor blades and rotor ceramic lining for A5 engines and engines which have SBE 72-0560 (SelectOne Retrofit Standard) and (SelectOne Production Standard) incorporated.

This TASK is only required after engine pass off test. Any damage found must be reported to IAE Technical Services department.

For engines that require no further strip of the HP compressor. Refer to TASK 72-00-00-200-802 SPECIAL PROCEDURES-002.

It is also required that all pass off engines R3 clappers are inspected for overlap, if found report to IAE Technical Services department.

Nicks and dents on airfoils, 0.005 in. (0.127 mm) or less, are considered minor. Minor nicks and dents are acceptable. There is no limit to the number of minor nicks and dents allowed.

Fig/item numbers in parentheses in the procedure agree with those used in the IPC. Only primary Fig/item numbers are used. For the service bulletin alpha variants refer to the IPC.

For all the parts identified in a different Chapter/Section/Subject the applicable Chapter/Section/Subject comes before the Fig/item number.

For the torque tightening procedures refer to SPM TASK 70-41-01-400-501.

Lubricate all threads and abutment faces of nuts and bolts with CoMat 10-077 APPROVED ENGINE OILS, unless other lubricants are referred to in the procedure.

The number for each radial location must be identified in a clockwise direction. These start at the engine top position when you look from the rear of the engine, unless stated differently in the procedure.

NOTE

To identify the consumable materials refer to the PCI.

NOTE

Special tools are identified in the procedure by the tool primary number.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
ACR Torq-Set bit 212-1/4-ACRLOCALTorq-Set
IAE 2F10057 Rotator Kit0AM53IAE 2F100571
IAE 6F10408 Borescope0AM53IAE 6F104081

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 01-003 SOLVENT, DELETEDX111XCoMat 01-003
CoMat 01-076 METHYL ETHYL KETONELOCALCoMat 01-076
CoMat 04-004 JOINTING COMPOUND, LIGHT GRADELOCALCoMat 04-004
CoMat 04-011 JOINTING COMPOUNDLOCALCoMat 04-011
CoMat 10-070 ANTI-SEIZE COMPOUNDX222XCoMat 10-070
CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE)K6835CoMat 10-072
CoMat 10-077 APPROVED ENGINE OILSX333XCoMat 10-077

Spares

NameManufacturerPart Number / IdentificationQuantityRemark
GASKET0AM536A41393

72-41-00, 02-108

GASKET0AM536A41811

72-41-23, 02-108

PACKING - PREFORMEDU1653AS3209-1221

72-60-21, 01-280

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-00-020-067 Remove the Borescope Access Port Blanks

    1. Refer to Figure, Figure and Figure.

      2. Remove the stage 3 borescope access port blanks from HP compressor split case.

      1. Remove the two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-107) that attach inspection port blank A HP COMPRESSOR SPLIT CASE (72-41-31, 01-105) to the compressor case.

      2. Remove the blank.

      3. Remove the stage 3 and 4 borescope access port blanks from HP compressor split case.

      1. Remove the two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-102) that attach inspection port blank B HP COMPRESSOR SPLIT CASE (72-41-31, 01-100) to the compressor case.

      2. Remove the blank.

      4. Remove the stage 5 and 6 borescope access port blanks from HP compressor split case.

      1. Remove the two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-142) that attach inspection port blank C HP COMPRESSOR SPLIT CASE (72-41-31, 01-140) to the compressor case.

      2. Remove the blank.

      5. Remove the stage 7 and 8 borescope access port blanks from HP compressor rear outer case.

      1. Remove the three bolts HPC Rear Outer Case And Related Parts (72-41-23, 02-102) that attach the inspection port blank D HPC Rear Outer Case And Related Parts (72-41-23, 02-100) and the gasket HPC Rear Outer Case And Related Parts (72-41-23, 02-108) to the compressor case.

      2. Remove the blank.

      3. Remove and discard the gasket.

      6. NOTE

        For easier access to the stage 8 to 9 inspection port E, and to avoid damage to the adjacent harness, you can remove clipping points C/P6085, C/P6086 and loosen C/P6073 on the EEC harness.

        Remove the stages 8 and 9, stages 9 and 10 and stages 11 and 12 borescope access port blanks from HP compressor rear outer case.

      1. Remove the three bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102) that attach the inspection port blank ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) and the gasket ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-108) to the compressor case.

      2. Remove the blank.

      3. Remove and discard the gasket.

    2. SUBTASK 72-00-00-220-179 Examine the HP Compressor Rear Case Screw Thread Inserts

      1. Broken, loose, worn, crossed threaded or stripped thread.

      1. Repair, VRS9170 TASK 72-00-00-300-013 (REPAIR-013) with KEENSERTS or Repair, VRS6518 TASK 72-00-41-300-001 (REPAIR-001) with thinwall inserts. KEENSERTS must be replaced at next HPC overhaul.

      2. Inspect for installed KEENSERTS.

      1. Accept, until next HPC overhaul.

    3. SUBTASK 72-00-00-160-056 Clean the Borescope Access Ports

      WARNING

      WHEN YOU USE CoMat 01-003 SOLVENT, DELETED OR CoMat 01-076 METHYL ETHYL KETONE YOU MUST USE THE CORRECT PROTECTIVE CLOTHING. DO NOT GET THE SOLVENT ON YOUR SKIN OR IN YOUR EYES. YOU MUST NOT SMOKE WHEN YOU USE THE SOLVENT AS THE VAPOR CHANGES AND BECOMES TOXIC.

      CAUTION

      DO NOT LET JOINTING COMPOUND GET IN TO THE ENGINE THROUGH THE ACCESS PORTS, CONTAMINATION OF HP COMPRESSOR AND COMPONENT DAMAGE CAN OCCUR.

    1. Refer to Figure.

      2. Remove the used jointing compound from the access ports.

      1. Use a non metallic scraper and a lint free cloth made moist with CoMat 01-003 SOLVENT, DELETED or CoMat 01-076 METHYL ETHYL KETONE. Remove all the used jointing compound from around the access ports.

    4. SUBTASK 72-00-00-420-076 Install the Rotator Kit

    1. Refer to Figure.

      2. NOTE

        The crank cover is installed on the front face of the external gearbox between the engine dedicated alternator (EDA) and the pneumatic starter.

        Remove the crank cover ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-220) from the external gearbox.

      1. Remove the two bolts ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-240) that attach the crank cover to the external gearbox.

      2. Remove the crank cover and discard the packing ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-280).

      3. Install the IAE 2F10057 Rotator Kit 1 off.

      1. Align the holes on the flange of the rotator kit with the fastener holes in the external gearbox.

      2. Install the rotator kit to the external gearbox. Make sure that the rotator kit engages with the hexagonal end of the starter shaft.

      3. Install the two bolts ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-240) and two washers ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-260). Tighten the two bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm) in accordance with SPM TASK 70-41-00-400-501.

      4. Connect to a shop air supply of 90 psi (6.2 bar).

    5. SUBTASK 72-00-00-420-072 Install the Borescope Probe Stages 3 and 3 to 4

    1. Refer to Figure.

    2. Install the IAE 6F10408 Borescope 1 off in the access port of the stage of the compressor you want to examine.

    3. Use a 0.32 in. (8.0 mm) borescope probe.

    6. SUBTASK 72-00-00-420-073 Install the Borescope Probe Stages 5 and 6

    1. Refer to Figure.

    2. Install the IAE 6F10408 Borescope 1 off in the access port of the stage of the compressor you want to examine.

    3. Use a 0.32 in. (8.0 mm) borescope probe.

    7. SUBTASK 72-00-00-420-074 Install the Borescope Probe Stages 7 and 8

    1. Refer to Figure.

    2. Install the IAE 6F10408 Borescope 1 off in the access port of the stage of the compressor you want to examine.

    3. NOTE

      Two ports are provided at this location for access if one port is not aligned with inner case bleed aperture.

      Use a 0.22 in. (5.5 mm) borescope probe.

    8. SUBTASK 72-00-00-420-075 Install the Borescope Probe Stages 8 to 9, Stages 9 to 10 and Stages 11 to 12

    1. Refer to Figure.

    2. Install the IAE 6F10408 Borescope 1 off in the access port of the stage of the compressor you want to examine.

    3. Use a 0.22 in. (5.5 mm) borescope probe.

    9. SUBTASK 72-00-00-210-065 Examine the HP Compressor Rotor Drum Stage 6 to 11 Stator Paths

    1. Refer to Figure.

      NOTE

      100 percent ceramic coating detachment is same as one complete stage liner loss. 200 percent ceramic coating detachment is same as two complete stage liner loss.

      2. Examine the Stage 6 to 11 stator path ceramic coatings.

      1. Stages 6, 7 and 8. Accept not more than 40 percent ceramic coating detachment per stage and not more than 25 percent of bond coating detachment per stage.

      2. Acceptance of up to 100 percent ceramic top coating detachment per stage is allowed for Stages 9, 10, and 11. Stages 6 to 11 accept not more than 340 percent ceramic coating detachment cumulative and not more than 25 percent accumulative bond coating detachment.

      3. Reject the engine if the detachment is more than in Step or Step above.

    10. SUBTASK 72-00-00-220-073 Examine the Stage 3 HP Compressor Rotor Blade Damage

    1. Refer to Figure, Figure and Figure.

      2. Zone A.

        1. Cracked.

        1. Reject.

        2. Nicked.

          1. Not more than 0.060 in. (1.52 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.200 in. (5.08 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

        1. Accept.

      3. Zone B.

        1. Cracked or torn.

        1. Reject.

        2. Nicked

          1. Not more than 0.005 in. (0.127 mm).

          1. Accept.

          2. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

        1. Accept.

      4. Clapper face contact.

        1. More than or equal to 50 percent of clapper face contact. Refer to abutment area shown in detail B.

        1. Accept.

        2. Less than Step.

        1. Reject.

        3. Clapper override (shingling). Refer to repeat view C.

        1. Reject.

        4. Clapper face irregularities. Refer to repeat view C.

        1. Reject.

      5. Zone C.

        1. Cracked.

        1. Reject.

        2. Nicked.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.200 in. (5.08 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

        1. Accept.

      6. Zone D.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than in Step but not more than 0.050 in. (1.270 mm) in depth located on either leading or trailing edge. A minimum distance of 0.205 in. (5.207 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge and trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than in Step but not more than 0.050 in. (1.270 mm) in depth located on either leading or trailing edge. A minimum distance of 0.205 in. (5.207 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge and trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      7. Blade tips.

        1. Missing piece.

        1. Reject.

        2. Discoloration (related to tip rub only).

        1. Accept.

        3. Bent or curled (not related to cracks or tears).

          1. Not more than 5 per cent of dimension X or Y.

          1. Accept.

          2. More than Step.

          1. Reject.

        4. Tip rub (not related to cracks and tears).

        1. Accept.

      8. All areas.

        1. Surface contamination from air-borne abradable liner deposits.

        1. Accept.

    11. SUBTASK 72-00-00-220-155 Examine the Stage 4 and 5 HP Compressor Rotor Blade Damage

    1. Refer to Figure and Figure.

      2. Zone A.

        1. Cracked.

        1. Reject.

        2. Nicks and tears.

          1. Not more than 0.060 in. (1.52 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.180 in. (4.57 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

        1. Accept.

      3. Zone B.

        1. Cracked.

        1. Reject.

        2. Nicks and tears.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. More than Step but not more than 0.180 in. (4.57 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

        1. Accept.

      4. Zone C.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. Stage 4 Blades - More than in Step but not more than 0.050 in. (1.270 mm) in depth located on the leading edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. Stage 5 Blades - More than in Step but not more than 0.050 in. (1.270 mm) in depth located on the trailing edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. Stage 4 Blades - More than in Step.

          1. Reject.

          5. Stage 5 Blades - More than in Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. Stage 4 Blades - More than in Step but not more than 0.050 in. (1.270 mm) in depth located on the leading edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. Stage 5 Blades - More than in Step but not more than 0.050 in. (1.270 mm) in depth located on the trailing edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. Stage 4 Blades - More than Step.

          1. Reject.

          5. Stage 5 Blades - More than Step.

          1. Reject.

      5. Blade tips.

        1. Missing piece.

        1. Reject.

        2. Discoloration (related to tip rub).

        1. Accept.

        3. Bent or curled (not related to cracks or tears).

          1. Not more than 5 per cent of dimension X or Y.

          1. Accept.

          2. More than Step.

          1. Reject.

        4. Tip rub (not related to cracks and tears).

        1. Accept.

      6. All areas.

        1. Surface contamination from air-borne abradable liner deposits.

        1. Accept.

    12. SUBTASK 72-00-00-220-156 Examine the Stage 6 to 12 HP Compressor Rotor Blade Damage

    1. Refer to Figure, Figure, Figure and Figure.

      2. Zone A - All stages.

        1. Cracked.

        1. Reject.

        2. Dented (not related to nicks or tears).

        1. Accept.

      3. Zone A - Stage 6 Rotor blades.

        1. Nicks and tears.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. More than Step.

          1. Reject.

      4. Zone A - stages 7 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.075 in. (1.90 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      5. Zone A - stage 8 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.067 in. (1.70 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      6. Zone A - stage 9 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.060 in. (1.52 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      7. Zone A - stages 10 to 12 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.030 in. (0.76 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.050 in. (1.27 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      8. Zone B - All stages.

        1. Cracked.

        1. Reject.

        2. Dented (not related to nicks or tears).

        1. Accept.

      9. Zone B - Stage 6 Rotor blades.

        1. Nicks and tears.

          1. Not more than 0.015 in. (0.38 mm) in depth.

          1. Accept.

          2. More than Step.

          1. Reject.

      10. Zone B - stage 7 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.015 in. (0.38 mm) in depth.

          1. Accept

          2. Nicks and tears more than Step but not more than 0.075 in. (1.90 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      11. Zone B - stage 8 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.015 in. (0.38 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.067 in. (1.70 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      12. Zone B - stage 9 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.015 in. (0.38 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.060 in. (1.52 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      13. Zone B - stages 10 to 12 rotor blades.

        1. Nicks and tears.

          1. Not more than 0.015 in. (0.38 mm) in depth.

          1. Accept.

          2. Nicks and tears more than Step but not more than 0.050 in. (1.27 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      14. Zone C - Stages 6 rotor blades.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than Step.

          1. Reject.

      15. Zone C - Stage 7 rotor blades.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than in Step but not more than 0.026 in. (0.660 mm) in depth located on the trailing edge. A minimum distance of 0.095 in. (2.413 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than in Step but not more than 0.026 in. (0.660 mm) in depth located on the trailing edge. A minimum distance of 0.095 in. (2.413 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      16. Zone C - Stage 8 rotor blades.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. Accept if greater than Step but less than or equal to 0.012 in. (0.305 mm) in depth and all of the following criteria are met:

          1. A single nick per blade in Zone C, located on the leading edge or contained in less than 0.020 in. (0.508 mm) from the leading edge.

          2. Not more than three nicks per stage.

            NOTE

            Alternative option to perform Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004) for damage that meets criteria of Step.

          3. More than in Step but not more than 0.028 in. (0.711 mm) in depth located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Dents 0.005 in. (0.127 mm) in depth or less on any gas washed surface. No limit to the number.

          1. Accept.

          2. Accept if greater than Step but less than or equal to 0.012 in. (0.305 mm) in depth and all of the following criteria are met:

          1. A single dent in Zone C, located on the leading edge or contained in less than 0.020 in. (0.508 mm) from the leading edge.

          2. Not more than three dents per stage.

            NOTE

            Alternative option to perform Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004) for damage that meets criteria of Step.

          3. More than in Step but not more than 0.028 in. (0.711 mm) in depth located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. More than Step.

          1. Reject.

      17. Zone C - Stage 9 rotor blades.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than in Step but not more than 0.030 in. (0.762 mm) in depth located on either leading or trailing edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge and trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. More than in Step but not more than 0.030 in. (0.762 mm) in depth located on either leading or trailing edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge and trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. More than Step.

          1. Reject.

      18. Zone C - Stage 10 rotor blades.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. Accept if greater than Step but less than or equal to 0.018 in. (0.457 mm) in depth and all of the following criteria are met:

          1. A single nick per blade in Zone C, located on the leading edge or in less than 0.040 in. (1.0 mm) from the leading edge.

          2. Not more than three nicks per stage.

            NOTE

            Alternative option to perform Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004) for damage that meets criteria of Step.

          3. More than in Step but not more than 0.030 in. (0.762 mm) in depth located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Dents 0.005 in. (0.127 mm) in depth or less on any gas washed surface. No limit to the number.

          1. Accept.

          2. Accept if greater than Step but less than or equal to 0.018 in. (0.457 mm) in depth and all of the following criteria are met:

          1. A single dent in Zone C, located on the leading edge or contained in less than 0.040 in. (1.0 mm) from the leading edge.

          2. Not more than three dents per stage.

            NOTE

            Alternative option to perform Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004) for damage that meets criteria of Step.

          3. More than in Step but not more than 0.030 in. (0.762 mm) in depth located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. More than Step.

          1. Reject.

      19. Zone C - Stages 11 to 12 rotor blades.

        1. Cracked or torn.

        1. Reject.

        2. Nicked.

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. Stage 11 - More than in Step but not more than 0.030 in. (0.762 mm) in depth located on the trailing edge. A minimum distance of 0.077 in. (1.956 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. Stage 12 - More than in Step but not more than 0.030 in. (0.762 mm) in depth located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. Stage 11 - More than Step.

          1. Reject.

          5. Stage 12 - More than Step.

          1. Reject.

        3. Dented (not related to cracks, nicks or tears).

          1. Not more than 0.005 in. (0.127 mm) in depth.

          1. Accept, without limit to number.

          2. Stage 11 - More than in Step but not more than 0.030 in. (0.762 mm) in depth located on the trailing edge. A minimum distance of 0.077 in. (1.956 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the trailing edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          3. Stage 12 - More than in Step but not more than 0.030 in. (0.762 mm) in depth located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform measured from the corner closest to the leading edge must be kept. Keep out of fillet area.

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          4. Stage 11 - More than Step.

          1. Reject.

          5. Stage 12 - More than Step.

          1. Reject.

      20. Blade tips.

        1. Missing piece - Stage 6, 7, 9, 10, 11 and 12 rotor blades.

        1. Reject.

        2. Missing piece - Stage 8 rotor blades only.

          1. Not more than 0.060 in. (1.524 mm).

          1. Repair, VRS9653 TASK 72-00-00-300-004 (REPAIR-004).

          2. More than Step.

          1. Reject.

        3. Heat discoloration related to tip rub.

        1. Accept.

        4. Bent or curled (not related to cracks or tears).

          1. Not more than 5 per cent of Dimension X or Y.

          1. Accept.

          2. More than Step.

          1. Reject.

        5. Tip rub (not related to cracks or tears).

        1. Accept.

      21. All areas.

        1. Surface contamination from air-borne abradable liner deposits.

        1. Accept.

    13. SUBTASK 72-00-00-020-068 Remove the Support Equipment

    1. Refer to Figure.

    2. Remove the borescope probe from the engine.

      3. Remove the rotator kit from the external gearbox.

      1. Disconnect shop air supply.

      2. Remove the two bolts and two washers that attach the rotator kit to the external gearbox and remove the rotator kit.

        3. Install the crank cover.

        1. Lightly lubricate a new ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-280) packing 1 off with CoMat 10-077 APPROVED ENGINE OILS and assemble in the crank cover ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-220) groove.

        2. Attach the crank cover ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-220) on the external gearbox with the two bolts ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-240) and two washers ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-260). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm) in accordance with the SPM TASK 70-41-00-400-501.

    14. SUBTASK 72-00-00-160-057 Clean the Borescope Access Port Blanks

      WARNING

      WHEN YOU USE CoMat 01-003 SOLVENT, DELETED OR CoMat 01-076 METHYL ETHYL KETONE YOU MUST USE THE CORRECT PROTECTIVE CLOTHING. DO NOT GET THE SOLVENT ON YOUR SKIN OR IN YOUR EYES. YOU MUST NOT SMOKE WHEN YOU USE THE SOLVENT AS THE VAPOR CHANGES AND BECOMES TOXIC.

    1. Refer to Figure.

      2. Remove the used jointing compound from the mating faces of the access port blanks.

      1. Use a non metallic scraper and a lint free cloth made moist with CoMat 01-003 SOLVENT, DELETED or CoMat 01-076 METHYL ETHYL KETONE.

      2. Remove all the used jointing compound from the mating faces of the blanks.

    15. SUBTASK 72-00-00-420-077 Install the Borescope Access Port Blanks

      CAUTION

      DO NOT LET JOINTING COMPOUND GET IN TO THE ENGINE THROUGH THE ACCESS PORTS, CONTAMINATION OF HP COMPRESSOR AND COMPONENT DAMAGE CAN OCCUR.

    1. Refer to Figure, Figure and Figure.

      2. Install the borescope access port blanks at locations A (stage 3) and B (stage 3 and 4).

      1. Apply a thin layer of CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE to the mating faces of the access ports and access port blanks with a stiff bristle brush or pallet knife. Do not apply jointing compound nearer than 0.12 in. to 0.16 in. (3.0 mm to 4.1 mm) around the access port aperture.

      2. Let the jointing compound dry for at least 10 minutes but not more than 2 hours.

      3. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-107) which attach the access port blank to the compressor case.

      4. Install the stage 3 access port blank A HP COMPRESSOR SPLIT CASE (72-41-31, 01-105) at location A and attach with two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-107).

      5. Install the stage 3 and 4 access port blank B HP COMPRESSOR SPLIT CASE (72-41-31, 01-100) at location B and attach with two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-102).

      6. Torque the bolts to 85 lbf.in. to 105 lbf.in. (10 Nm to 12 Nm).

      7. Torque the bolts again to 85 lbf.in. to 105 lbf.in. (10 Nm to 12 Nm).

      8. Remove unwanted jointing compound from around the access port blank.

      3. Install the stage 5 and 6 borescope access port blank at location C.

      1. Apply a thin layer of CoMat 04-011 JOINTING COMPOUND to the mating faces of the access ports and access port blanks with a stiff bristle brush or pallet knife. Do not apply jointing compound nearer than 0.12 in. to 0.16 in. (3.0 mm to 4.1 mm) around the access port aperture.

      2. Let the jointing compound dry for at least 10 minutes but not more than 2 hours.

      3. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-142) which attach the access port blank to the compressor case.

      4. Install the access port blank HP COMPRESSOR SPLIT CASE (72-41-31, 01-140) and attach the two bolts HP COMPRESSOR SPLIT CASE (72-41-31, 01-142).

      5. Torque the bolts to 85 lbf in. to 105 lbf in. (10 Nm to 12 Nm).

      6. Torque the bolts again to 85 lbf in. to 105 lbf in. (10 Nm to 12 Nm).

      7. Remove unwanted jointing compound from around the access port blank.

      4. Install the stage 7 and 8 borescope access port blanks at locations D.

      1. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts HPC Rear Outer Case And Related Parts (72-41-23, 02-102) which attach the access port blank to the compressor case.

      2. Install the stage 7 and 8 access port blank HPC Rear Outer Case And Related Parts (72-41-23, 02-100) at location D with a new gasket HPC Rear Outer Case And Related Parts (72-41-23, 02-108) and attach with three bolts HPC Rear Outer Case And Related Parts (72-41-23, 02-102).

      3. Torque the bolts to 85 lbf.in. to 105 lbf.in. (10 Nm to 12 Nm).

      4. Torque the bolts again to 85 lbf.in. to 105 lbf.in. (10 Nm to 12 Nm).

      5. Remove unwanted jointing compound from around the access port blank.

      5. Install the borescope access port blanks at locations E (stage 8 and 9), F (stage 9 and 10) and G (stage 11 and 12).

      1. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the nine bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102) which attach the access port blank to the compressor case.

      2. Install the stage 8 and 9, stage 9 and 10 and stage 11 and 12 access port blank ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) at location E, F and G with the three new gasket HPC Rear Outer Case And Related Parts (72-41-23, 02-108) and attach with nine bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102).

      3. Torque the bolts to 85 lbf.in. to 105 lbf.in. (10 Nm to 12 Nm).

      4. Torque the bolts again to 85 lbf.in. to 105 lbf.in. (10 Nm to 12 Nm).

      5. Remove unwanted jointing compound from around the access port blank.

    16. SUBTASK 72-00-00-420-086 Install the Removed and Loosened Clipping Points

    1. Refer to Figure and Figure.

      2. If recommendation in Step is followed, then:

      1. Install the bolt, clamps and nut at clip locations CP6085 and CP6086 on EGT harness Exhaust Gas Temperature (EGT) Harness (71-52-45, 01-005).

      2. Clamp EEC core harness in designed routing at clip location CP6073 on EEC core harness EEC Core Harness And Voltage Divider Harness Assembly (71-52-43, 01-005).

    3. Torque clip stacks CP6085 and CP6073 to 36 lbf.in. to 45 lbf.in. (4.1 Nm to 5.1 Nm).

    17. SUBTASK 72-00-00-220-174 Examine the HP Compressor Stage 6 Rotor Path Coating

      1. NOTE

        The minimum view of the inspection area is specified by rotor path lining segment 3 and 4.

        Liner loss of the Stage 6 Rotor path.

        1. Less than 10 percent liner loss.

        1. Accept.

        2. More than in Step and less than 40% liner loss.

        1. Inspect every 750 flight cycles.

        3. More than in Step.

        1. Reject.

    18. SUBTASK 72-00-00-220-175 Stages 6, 7 and 8 Front and Rear Damper Wires

      1. Damper wire visible.

      1. Reject.

    19. Figure: HP Compressor Borescope Access Ports

    HP Compressor Borescope Access Ports

    Figure: Stage 7 and 8 Borescope Access Ports

    Stage 7 and 8 Borescope Access Ports

    Figure: Stage 7 and 8 Borescope Access Ports

    Stage 7 and 8 Borescope Access Ports

    Figure: HP Compressor Rotor Blade Dimensions

    HP Compressor Rotor Blade Dimensions

    Figure: HP Compressor Rotor Blade Damage Zones

    HP Compressor Rotor Blade Damage Zones

    Figure: HP Compressor Stage 3 Rotor Blade Clapper Face Damage Zones

    HP Compressor Stage 3 Rotor Blade Clapper Face Damage Zones

    Figure: Install the Rotator Kit

    Install the Rotator Kit

    Figure: Typical Leading Edge Nicks and Dents in Zone C (For Stage 8 Rotor Blades Only)

    Typical Leading Edge Nicks and Dents in Zone C (For Stage 8 Rotor Blades Only)

    Figure: Typical Leading Edge Nicks and Dents in Zone C (For Stage 10 rotor blades only)

    Typical Leading Edge Nicks and Dents in Zone C (For Stage 10 rotor blades only)

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Fix Repair links due to duplicate task numbers (CAS-65061-G1D1R6)

Manufacturer Code:0AM53
Enterprise Name:IAE INTERNATIONAL AERO ENGINES AG
BU Name:NULL
Building:SUITE 400
Street:628 HEBRON AVENUE
City:GLASTONBURY
State:CT
Zip Code:06033
Country:USA
Manufacturer Code:K6835
Enterprise Name:MED-LAB LTD
BU Name:MED-LAB LTD
Street:COPELAND ST
City:DERBY
Zip Code:DE1 2PU
Country:GREAT BRITAIN
Phone Number:44-1332-349094
Fax Number:44-1332-371237
Email:sales@med-lab.co.uk
Internet:www.med-lab.co.uk
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:U1653
Enterprise Name:Society Of British Aerospace Companies, LTD.
Manufacturer Code:X111X
Enterprise Name:N/A – DELETED CONSUMABLE MATERIAL
Manufacturer Code:X222X
Enterprise Name:N/A – REFER TO APPLICABLE COMAT SUFFIX
Manufacturer Code:X333X
Enterprise Name:REFER TO V2500 SB ENG-79-0108
Part Number:6A4139
Part Name:GASKET
Manufacturer Code:0AM53
Part Number:6A4181
Part Name:GASKET
Manufacturer Code:0AM53
Part Number:AS3209-122
Part Name:PACKING - PREFORMED
Manufacturer Code:U1653
Manufacturer Code:X111X
Supply Number:CoMat 01-003
Type:sp01
Supply Short Name:CoMat 01-003 SOLVENT, DELETED
Supply Name:CoMat 01-003 SOLVENT, DELETED
Specification Groups:
Doc NumberType
wiring harnesses. Where CoMat 01‐003 is specified to clean mechanical components, use one or more of the solvents that SPM TASK 70‐11‐26‐300‐503 specifies as applicable.DELETED. Where CoMat 01‐003 is specified to clean electrical contacts or wiring harnesses, use one or more of the solvents that SPM TASK 70‐11‐57‐110‐501 specifies to clean electrical contacts or
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:LOCAL
Supply Number:CoMat 01-076
Type:sp01
Supply Short Name:CoMat 01-076 METHYL ETHYL KETONE
Supply Name:CoMat 01-076 METHYL ETHYL KETONE
Specification Groups:
Doc NumberType
METHYL ETHYL KETONE, TECHNICAL GRADE, CERTIFIED TO BSI BS 1940 OR ASTM D740, OR TT-M-261
Suppliers:
ManufacturerRemarks
LOCAL
Manufacturer Code:LOCAL
Supply Number:CoMat 04-004
Type:sp01
Supply Short Name:CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE
Supply Name:CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE
Specification Groups:
Doc NumberType
OMAT: 4/46 (REF RR)HYLOMAR AEROGRADE (PL32), LIGHT GRADE
JCR-025 (JAEC REF)HYLOMAR AEROGRADE (PL32), LIGHT GRADE
MSRR 9055 (RR REF)HYLOMAR AEROGRADE (PL32), LIGHT GRADE
Suppliers:
ManufacturerRemarks
LOCAL
460Y4
CJ731
K3237
Manufacturer Code:LOCAL
Supply Number:CoMat 04-011
Type:sp01
Supply Short Name:CoMat 04-011 JOINTING COMPOUND
Supply Name:CoMat 04-011 JOINTING COMPOUND
Specification Groups:
Doc NumberType
OMAT: 423SILKOLENE 762 DTD 900/4344
Suppliers:
ManufacturerRemarks
LOCAL
IE200
K0007
K6835
k3504
Manufacturer Code:X222X
Supply Number:CoMat 10-070
Type:sp01
Supply Short Name:CoMat 10-070 ANTI-SEIZE COMPOUND
Supply Name:CoMat 10-070 ANTI-SEIZE COMPOUND
Specification Groups:
Doc NumberType
DELETED. USE COMAT 10-070A
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:K6835
Supply Number:CoMat 10-072
Type:sp01
Supply Short Name:CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE)
Supply Name:CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE)
Specification Groups:
Doc NumberType
OMAT: 417BGP CoMat 109 DEFSTAN 80-81 NATO S722
Suppliers:
ManufacturerRemarks
K6835
Manufacturer Code:X333X
Supply Number:CoMat 10-077
Type:sp01
Supply Short Name:CoMat 10-077 APPROVED ENGINE OILS
Supply Name:CoMat 10-077 APPROVED ENGINE OILS
Specification Groups:
Doc NumberType
For V2500-A1/A5/D5 models - Refer to V2500 Service Bulletin ENG-79-0108
For V2500-E5 model - Refer to Service Bulletin E5-79-0001
Suppliers:
ManufacturerRemarks
X333X
Manufacturer Code:0AM53
Tool Number:IAE 2F10057
Tool Name:IAE 2F10057 Rotator Kit
Manufacturer Code:0AM53
Tool Number:IAE 6F10408
Tool Name:IAE 6F10408 Borescope
Manufacturer Code:LOCAL
Tool Number:Torq-Set
Tool Name:ACR Torq-Set bit 212-1/4-ACR