TASK 72-00-00-200-002-A00 Engine General - Examine (Borescope) The HP Compressor (HPC), Inspection-002

DMC:V2500-A1-72-00-0000-04A-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-A1

Common Information

TASK 72-00-00-200-002-A00 Engine General - Examine (Borescope) The HP Compressor (HPC), Inspection-002

General

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.

This TASK gives the procedure for the borescope inspection of HP compressor rotor blades and rotor ceramic lining and measure stage 6 VSV bushing wear.

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.

A ** following repair referenced in this inspection indicates that the repair is not yet published in the current revision of the manual and the part must be rejected. Contact IAE for additional information concerning FAA approved repair date.

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 2F10057
IAE 6F10408 Borescope0AM53IAE 6F10408

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

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-00-020-053-A00 Remove the Stage 3 and 5 Borescope Access Port Blanks (Pre SBE 72-0027)

    1. Refer to Figure.

      2. Remove the borescope access port blanks (refer Figure).

        1. Remove the stage 3 borescope blanks (A and B).

        1. Remove the two bolts that attach the blank A ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-100) to the compressor case at the 4 o'clock position, forward of the stage 3 unison ring. Remove the blank.

        2. Remove the two bolts that attach the blank B ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-120) to the compressor case at the 4 o'clock position, to the rear of the stage 3 unison ring. Remove the blank.

        2. Remove the stage 5 borescope blank (C).

        1. Remove the bolt that attaches the stage 6 drag link to the unison ring bracket (refer to Figure).

        2. Move the stage 6 unison ring counterclockwise (when you look forward) until the levers touch the centralizing pads.

        3. Loosen, but do not remove, the two bolts that attach the centralizing pad to the stage 6 unison ring (refer to Figure).

        4. Remove the nuts from each of the two stage 5 levers, adjacent to the borescope blank (refer to Figure).

        5. Remove the two levers and the spacers. Keep the spacers with their applicable levers so that the correct spacers are used for assembly.

        6. With the ACR Torq-Set bit 212-1/4-ACR 1 off remove the two screws that attach the borescope blank C ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-140) to the compressor case and remove the blank.

    2. SUBTASK 72-00-00-020-053-B00 Remove the Stage 3 and 5 Borescope Access Port Blanks (SBE 72-0027)

    1. Refer to Figure, Figure and Figure.

      2. Remove the borescope access port blanks.

        1. Remove the stage 3 borescope blanks (A, B and H).

        1. Remove the two bolts that attach the blank A ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-100) to the compressor case at the 4 o'clock position, forward of the stage 3 unison ring. Remove the blank.

        2. Remove the two bolts that attach the blank B ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-120) to the compressor case at the 4 o'clock position, to the rear of the stage 3 unison ring. Remove the blank.

        3. Remove the two bolts that attach the blank H ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-105) to the compressor case at the 8 o'clock position, forward of the stage 3 unison ring. Remove the blank.

        2. Remove the stage 5 borescope blank (C).

        1. Remove the bolt that attaches the stage 6 drag link to the unison ring bracket.

        2. Move the Stage 6 unison ring counterclockwise (when you look forward) until the levers touch the centralizing pads.

        3. Loosen, but do not remove, the two bolts that attach the centralizing pad to the stage 6 unison ring.

        4. With the ACR Torq-Set bit 212-1/4-ACR 1 off remove the two screws that attach the borescope blank C ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-140) to the compressor case and remove the blank and the blanking plug.

    3. SUBTASK 72-00-00-020-066-A00 Remove the Stage 8 to 12 Borescope Access Port Blanks (Pre SBE 72-0033 and Pre SBE 72-0100)

    1. Refer to Figure.

      2. Remove the three stage 8 to 12 borescope blanks (E, F and G).

      1. Remove the three bolts that attach the borescope blank E ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

      2. Remove the three bolts that attach the borescope blank F ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

      3. Remove the three bolts that attach the borescope blank G ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

    4. SUBTASK 72-00-00-020-066-B00 Remove the Stage 7 to 12 Borescope Access Port Blanks (SBE 72-0033 and Pre SBE 72-0100)

    1. Refer to Figure and Figure.

      2. Remove the four stage 7 to 12 borescope blanks (D, E, F and G).

      1. Remove the three bolts that attach the borescope blank D ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

      2. Remove the three bolts that attach the borescope blank E ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

      3. Remove the three bolts that attach the borescope blank F ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

      4. Remove the three bolts that attach the borescope blank G ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank.

    5. SUBTASK 72-00-00-020-066-C00 Remove the Stage 7 to 12 Borescope Access Port Blanks (SBE 72-0100)

    1. Refer to Figure.

      2. Remove the four stage 7 to 12 borescope blanks (D, E, F and G) (refer to Figure).

      1. Remove the three bolts that attach the borescope blank D ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank and discard the gasket.

      2. Remove the three bolts that attach the borescope blank E ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank and discard the gasket.

      3. Remove the three bolts that attach the borescope blank F ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank and discard the gasket.

      4. Remove the three bolts that attach the borescope blank G ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case at the 4 o'clock position, to the rear of flange FJ. Remove the blank and discard the gasket.

    6. SUBTASK 72-00-00-220-178 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.

    7. SUBTASK 72-00-00-160-051 Clean the Borescope Access Ports

      WARNING

      WHEN YOU USE CoMat 01-076 METHYL ETHYL KETONE METHYL ETHYL KETONE OR CoMat 01-003 SOLVENT, DELETED 1.1.2 TRICHLOROETHYLENE (INHIBITED AND STABILIZED) YOU MUST MAKE SURE THERE IS SUFFICIENT VENTILATION. YOU MUST USE THE CORRECT PROTECTIVE CLOTHING. YOU MUST NOT SMOKE AND DO NOT PUT THE SOLVENT NEAR A SOURCE OF HEAT 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. 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 1.1.2 trichloroethylene (inhibited and stabilized) or CoMat 01-076 METHYL ETHYL KETONE. Remove all the used jointing compound from around the access ports.

    8. SUBTASK 72-00-00-420-053 Install the Rotator Kit

    1. Refer to Figure.

      2. NOTE

        The crank cover is on the front face of the external gearbox between the dedicated alternator 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 nuts and washers which attach the crank cover to the external gearbox.

      2. Remove the crank cover and remove and discard the packing.

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

      1. Align the holes on the flange of the rotator kit with the studs on 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 washers ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-260) and the two bolts ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-240). Tighten the two nuts.

    9. SUBTASK 72-00-00-420-054 Install the Borescope Probe Stages 3 to 6

    1. NOTE

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

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

    10. SUBTASK 72-00-00-420-069 Install the Borescope Probe Stage 7 (SBE 72-0033)

    1. NOTE

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

      Install the IAE 6F10408 Borescope 1 off in the access port of the stage 7 compressor.

    11. SUBTASK 72-00-00-420-071 Install the Borescope Probe Stages 8 to 12

    1. NOTE

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

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

    12. SUBTASK 72-00-00-210-064 Examine the HP Compressor Rotor Drum Stage 6 to 11 Stator Paths

      1. Inspect the Stage 6 to 11 stator path ceramic coatings.

      1. Stages 6, 7 and 8. Accept up to 40 percent ceramic coating detachment per stage providing the bonding coat remains.

      2. Stages 9, 10, and 11. Accept up to 200 percent ceramic coating detachment cumulative providing the bonding coat remains.

      3. Stages 6 to 11. Accept up to 240 percent ceramic coating detachment cumulative providing the bonding coat remains.

      4. Stages 6 to 11. Accept up to 25 percent where both the ceramic coat and the bonding are removed.

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

    13. SUBTASK 72-00-00-220-150 Examine the Stage 3 HP Compressor Rotor Blades

    1. Refer to Figure, Figure and Figure.

      2. Zone A.

        1. Cracked.

        1. Reject.

        2. Nicked and torn (not related to cracks).

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

          1. Accept.

          2. More than in 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 in Step.

          1. Reject.

        3. Dented (not related to cracks).

        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 Step.

          1. Reject.

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

        1. Accept.

      4. Clapper face contact.

        1. Less than 50 percent clapper face contact abutment area F.

        1. Reject.

        2. Clapper overlap D.

        1. Reject

        3. Clapper face irregular wear C and D.

        1. Reject.

      5. Zone C.

        1. Cracked.

        1. Reject.

        2. Nicked and torn.

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

          1. Accept.

          2. Nicks more than in 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 in Step.

          1. Reject.

        3. Dented (not related to cracks).

        1. Accept.

      6. Zone D.

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

          1. Accept.

          2. More than in Step.

          1. Reject.

      7. 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) not more than 5 percent of dimension X or Y.

        1. Accept.

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

        1. Accept

      8. All areas.

        1. Deposits.

          1. Light deposits of abradable atmospheric contamination.

          1. Accept.

    14. SUBTASK 72-00-00-220-151 Examine the Stage 4 and 5 HP Compressor Rotor Blades

    1. Refer to Figure and Figure.

      2. Zone A - All stages.

        1. Cracked

        1. Reject.

        2. Dented.

        1. Accept.

        3. Nicked and torn (not related to cracks).

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

          1. Accept.

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

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

          3. More than in Step.

          1. Reject.

      3. Zone B - All stages.

        1. Cracked or torn.

        1. Reject.

        2. Dented.

        1. Accept.

        3. Nicked (not related to cracks or tears).

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

          1. Accept.

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

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

          3. More than in Step.

          1. Reject.

      4. Zone C - All stages.

        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.

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

          1. Accept.

          2. 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) not more than 5 percent of dimension X or Y.

        1. Accept.

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

        1. Accept.

      6. All areas.

        1. Deposits.

          1. Light deposits of abradable or atmospheric contamination.

          1. Accept.

    15. SUBTASK 72-00-00-220-152 Examine the Stage 6 to 12 HP Compressor Rotor Blades

    1. Refer to Figure and Figure.

      2. Zone A - All stages.

        1. Cracked.

        1. Reject.

        2. Dented.

        1. Accept.

      3. Zone A - Stage 6 Rotor blades.

        1. Nicked and torn (not related to cracks).

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

          1. Accept.

          2. More than in Step.

          1. Reject.

      4. Zone A - Stage 7 rotor blades.

        1. Nicked and torn (not related to cracks).

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

          1. Accept.

          2. More than in 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 in Step.

          1. Reject.

      5. Zone A - Stage 8 rotor blades.

        1. Nicked and torn (not related to cracks).

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

          1. Accept.

          2. More than in 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 in Step.

          1. Reject.

      6. Zone A - Stage 9 rotor blades.

        1. Nicked and torn (not related to cracks).

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

          1. Accept.

          2. More than in 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 in Step.

          1. Reject.

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

        1. Nicked and torn (not related to cracks).

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

          1. Accept.

          2. More than in 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 in Step.

          1. Reject.

      8. Zone B - All stages.

        1. Cracked or torn.

        1. Reject.

        2. Dented

        1. Accept.

      9. Zone B - Stage 6 Rotor blades.

        1. Nicked (not related to cracks or tears).

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

          1. Accept.

          2. More than in Step.

          1. Reject.

      10. Zone B - Stage 7 rotor blades.

        1. Nicked (not related to cracks or tears).

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

          1. Accept.

          2. More than in Step but not more than 0.075 in. (1.90 mm) in depth.

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

          3. More than in Step.

          1. Reject.

      11. Zone B - Stage 8 rotor blades.

        1. Nicked (not related to cracks or tears).

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

          1. Accept.

          2. More than in Step but not more than 0.067 in. (1.70 mm) in depth.

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

          3. More than in Step.

          1. Reject.

      12. Zone B - Stage 9 rotor blades.

        1. Nicked (not related to cracks or tears).

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

          1. Accept.

          2. More than in Step but not more than 0.060 in. (1.52 mm) in depth.

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

          3. More than in Step.

          1. Reject.

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

        1. Nicked (not related to cracks or tears).

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

          1. Accept.

          2. More than in Step but not more than 0.050 in. (1.27 mm) in depth.

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

          3. More than in Step.

          1. Reject.

      14. Zone C - All stages.

        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.

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

          1. Accept.

          2. More than Step.

          1. Reject.

      15. 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. Discoloration (related to tip rub).

        1. Accept.

        4. Bent or curled (not related to cracks or tears) not more than 5 percent of dimension X or Y.

        1. Accept.

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

        1. Accept.

      16. All areas.

        1. Deposits.

          1. Light deposits of abradable or atmospheric contamination.

          1. Accept.

    16. SUBTASK 72-00-00-020-054 Remove the Support Equipment

    1. Remove the borescope probe from the engine.

      2. Remove the rotator kit from the external gearbox.

      1. Remove the two nuts and washers that attach the rotator kit to the external gearbox and remove the rotator kit.

      2. Lightly lubricate a new ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-280) packing1 off with CoMat 10-077 APPROVED ENGINE OILS and install it on the crank cover ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-220).

      3. Attach the crank cover on the external gearbox with the two washers ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-260) and the two nuts ENGINE-MAIN GEARBOX CASE AND FITTINGS (72-60-21, 01-240). Torque the nuts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

    17. SUBTASK 72-00-00-160-052 Clean the Borescope Access Port Blanks

      WARNING

      WHEN YOU USE CoMat 01-076 METHYL ETHYL KETONE OR CoMat 01-003 SOLVENT, DELETED YOU MUST MAKE SURE THERE IS SUFFICIENT VENTILATION. YOU MUST USE THE CORRECT PROTECTIVE CLOTHING. YOU MUST NOT SMOKE AND DO NOT PUT THE SOLVENT NEAR A SOURCE OF HEAT 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. Remove the used jointing compound from the mating faces of the access port blanks.

      1. Use 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 the mating faces of the blanks.

    18. SUBTASK 72-00-00-420-055-A00 Install the Borescope Access Port Blanks Stage 3 and 5 (Pre SBE 72-0027)

    1. Refer to Figure.

      2. Install the borescope access port blanks A, B and C.

      1. Apply a thin layer of CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE to the mating faces of the access ports and the access port blanks with a stiff bristle brush. Do not apply jointing compound nearer than 0.12 to 0.16 in. (3 to 4 mm) to the access port.

      2. Let the jointing compound dry for at least 10 minutes.

      3. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-102) which hold the borescope access port blank A to the compressor case.

      4. Attach the access port blank A ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-100) to the compressor case with the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-102). Torque the screws to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      5. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-122) which hold the borescope access port blank B to the compressor case.

      6. Attach the access port blank B ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-120) to the compressor case with the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-122). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      7. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two screws ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-142) which hold the borescope access port blank C to the compressor case.

      8. Attach the access port blank C ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-140) to the compressor case with the two screws ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-142). Use theACR Torq-Set bit 212-1/4-ACR to torque the screws to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      9. Remove unwanted jointing compound from around the access ports.

        10. CAUTION

          YOU MUST INSTALL THE VSV LEVERS CORRECTLY OR THE COMPRESSOR CAN BE DAMAGED.

          Connect the stage 5 and 6 unison rings.

        1. Install the two levers ACTUATING MECHANISM HP COMPRESSOR VARIABLE VANES (72-41-34, 05-100) with their applicable spacers. Install each of the two nuts ACTUATING MECHANISM HP COMPRESSOR VARIABLE VANES (72-41-34, 05-103) and torque to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

        2. Tighten the two bolts ACTUATING MECHANISM HP COMPRESSOR VARIABLE VANES (72-41-34, 06-682) that attach the centralizing pad to the stage 6 unison ring. Torque the bolts to 36 lbf.in to 45 lbf.in (4 Nm to 5 Nm).

        3. Move the stage 6 unison ring counterclockwise (when you look forward) until the drag link bolt can be installed.

        4. Attach the stage 6 drag link to the unison ring bracket with the bolt V2500-A5-72-41-34-01A-941A-D (72-41-34, 01-436) and the nut V2500-A5-72-41-34-01A-941A-D (72-41-34, 01-432). Torque the nut to 180 lbf.in to 220 lbf.in (20 Nm to 25 Nm).

    19. SUBTASK 72-00-00-420-055-B00 Install the Borescope Access Port Blanks Stage 3 and 5 (SBE 72-0027)

    1. Refer to Figure.

      2. Install the borescope access port blanks A, B, C and H.

      1. Apply a thin layer of CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE to the mating faces of the access ports and the access port blanks with a stiff bristle brush. Do not apply jointing compound nearer than 0.12 to 0.16 in. (3 to 4 mm) to the access port.

      2. Let the jointing compound dry for at least 10 minutes.

      3. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-102) which hold the borescope access port blank A to the compressor case.

      4. Attach the access port blank A ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-100) to the compressor case with the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-102). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      5. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-122) which hold the borescope access port blank B to the compressor case.

      6. Attach the access port blank B ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-120) to the compressor case with the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-122). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      7. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two screws ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-142) which hold the borescope access port blank C to the compressor case.

      8. Attach the access port blank C ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-140) blank and ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-135) blanking plug to the compressor case with the two screws ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-142). Use the ACR Torq-Set bit 212-1/4-ACR 1 off to torque the screws to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      9. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-107) which hold the borescope access port blank H to the compressor case.

      10. Attach the access port blank H ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-105) to the compressor case with the two bolts ENGINE-HP COMPRESSOR SPLIT CASES (72-41-31, 01-107). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      11. Remove unwanted jointing compound from around the access ports.

        12. Connect the stage 5 and 6 unison rings.

        1. Tighten the two bolts ACTUATING MECHANISM HP COMPRESSOR VARIABLE VANES (72-41-34, 06-682) that attach the centralizing pad to the stage 6 unison ring. Torque the bolts to 36 lbf.in to 45 lbf.in (4 Nm to 5 Nm).

        2. Move the stage 6 unison ring counterclockwise (when you look forward) until the drag link bolt can be installed.

        3. Attach the stage 6 drag link to the unison ring bracket with the bolt V2500-A5-72-41-34-01A-941A-D (72-41-34, 01-436) and the nut V2500-A5-72-41-34-01A-941A-D (72-41-34, 01-432). Torque the nut to 180 lbf.in to 220 lbf.in (20 Nm to 25 Nm).

    20. SUBTASK 72-00-00-420-071-A00 Install the Stage 8 to 12 Borescope Access Port Blanks (Pre SBE 72-0033 and Pre SBE 72-0100)

    1. Refer to Figure.

      2. Install the three borescope access port blanks E, F and G.

      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 to 0.16 in. (3 to 4 mm) around the access port.

      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 nine bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102) which hold the borescope access port blanks E, F and G to the compressor case.

      4. Attach the access port blanks E, F and G ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case with the nine bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      5. After at least two minutes, torque the nine bolts again to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      6. Remove unwanted jointing compound from around the access port.

    21. SUBTASK 72-00-00-420-071-B00 Install the Stage 7 to 12 Borescope Access Port Blanks (SBE 72-0033 and Pre SBE 72-0100)

    1. Refer to Figure.

    2. Apply a thin layer of CoMat 04-011 JOINTING COMPOUND to mating surfaces 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 mm to 4 mm) around the access ports.

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

    4. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the three bolts ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-102) which hold the borescope access port blank D to the compressor case.

    5. Attach the access port blank D ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-100) to the compressor case with the three bolts ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-102). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

    6. 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 hold the borescope access port blanks E, F and G to the compressor case.

    7. Attach the access port blanks E, F and G ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case with the nine bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

    8. After at least two minutes, torque all the bolts again to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

    9. Remove unwanted jointing compound from around the access ports.

    22. SUBTASK 72-00-00-420-071-C00 Install the Stage 7 to 12 Borescope Access Port Blanks (SBE 72-0100)

    1. Refer to Figure.

      2. Install the four stage 7 to 12 borescope blanks (D, E, F and G).

      1. Apply CoMat 10-072 ANTISEIZE COMPOUND (MoDISULFIDE) or CoMat 10-070 ANTI-SEIZE COMPOUND to the three bolts ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-102) which hold the borescope access port blank D to the compressor case.

      2. Attach the access port blank D ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-100) to the compressor case with the ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-108) gasket 1 off and the three bolts ENGINE-HP COMPRESSOR REAR OUTER CASE (72-41-23, 02-102). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

      3. 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 hold the borescope access port blanks E, F and G to the compressor case.

      4. Attach the access port blanks E, F and G ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-100) to the compressor case with the ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-108) gaskets 3 off and the nine bolts ENGINE-SECURING FEATURES-HP COMPRESSOR CASES (72-41-00, 02-102). Torque the bolts to 85 lbf.in to 105 lbf.in (10 Nm to 12 Nm).

    23. SUBTASK 72-00-00-220-149 Measure the Stage 6 VSV Bushing Wear

    1. Hold the base of the lever attached to a stator vane, pull radially away from the engine.

    2. Using feeler gage measure the movement in the stator vane between the trunion of the lever arm and the spacer washers. Repeat the procedure for a selection of other stator vanes spread around the circumference of the engine.

      3. Amount of movement in stator vanes.

        1. Up to 0.040 in. (1.02 mm).

        1. Accept.

        2. Other than in Step.

        1. Disassemble, 72-41-00 CONFIG-1 Page 501.

    24. SUBTASK 72-00-00-220-172 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% 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.

    25. SUBTASK 72-00-00-220-173 Stages 6, 7 and 8 Front and Rear Damper Wires

      1. Damper wire visible.

      1. Reject.

    26. Figure: HP Compressor Borescope Access Ports

    HP Compressor Borescope Access Ports

    Figure: HP Compressor Borescope Access Ports

    HP Compressor Borescope Access Ports

    Figure: HP Compressor Borescope Access Ports

    HP Compressor Borescope Access Ports

    Figure: HP Compressor Borescope Access Ports

    HP Compressor Borescope Access Ports

    Figure: HP Compressor Borescope Access Ports

    HP Compressor Borescope Access Ports

    Figure: Install the Rotator Kit

    Install the Rotator Kit

    Figure: HP Compressor Blades

    HP Compressor Blades

    Figure: HP Compressor Blades

    HP Compressor Blades

    Figure: HP Compressor Blades

    HP Compressor Blades

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: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
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