TASK 72-45-11-200-001-B00 HPT Stage 1 Hub - Examine, Inspection-001

DMC:V2500-A0-72-45-1100-01B-300A-C|Issue No:006.00|Issue Date:2019-05-01

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

All

Common Information

TASK 72-45-11-200-001-B00 HPT Stage 1 Hub - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-011

2A1901

01-010

2A2021

General

This TASK gives the procedure for the inspection of the stage 1 turbine hub.

Fig/Item numbers in parentheses in the procedure agree with those used in the IPC.

The policy that is necessary for inspection is given in SPM TASK 70-20-00-200-501.

All the parts must be cleaned before any part is examined. Refer to SPM TASK 70-10-00-100-501.

All parts must be visually examined for damage, corrosion and wear. Any defects that are not identified in the procedure must be referred to IAE.

The procedure for those parts which must have a crack test is given in SUBTASK 72-45-11-230-052. Do the test before the part is visually examined.

Do not discard any part until you are sure there are no repairs available. Refer to the instructions in Repair before a discarded part is used again or oversize parts are installed.

Parts which should be discarded can be held although no repair is available. The repair of a discarded part could be shown to be necessary at a later date.

All parts must be examined to make sure that all the repairs have been completed satisfactorily.

The practices and processes referred to in the procedure by the TASK numbers are in SPM.

References

Refer to SPM for data on these items.

Definition of Damages, SPM TASK 70-02-02-350-501.

Record and Control of the Lives of Parts, SPM TASK 70-05-00-220-501.

Inspection of Parts, SPM TASK 70-20-00-200-501.

Marking of Parts, SPM TASK 70-09-00-400-501.

Some data on these items is contained in this TASK. For more data on these items refer to SPM.

Method of Testing for Crack Indications.

Chemical Processes.

Surface Protection.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-45-11-220-119 Examine the Stage 1 HPT Hub for Soot and Oil

      CAUTION

      MAKE SURE THAT YOU DO THIS INSPECTION BEFORE YOU CLEAN THE PART OR CLEANING PROCEDURE WILL REMOVE THE INDICATION OF SOOT AND OIL.

      1. Examine the Stage 1 HPT Hub for soot and oil.

        1. No soot or oil.

        1. Accept.

        2. Soot or oil.

        1. Do inspection of HPT for possible oil ignition event. Refer to TASK 72-45-00-200-801. Report all findings to IAE Technical Services.

    2. SUBTASK 72-45-11-220-109 Examine the Stage 1 HPT Hub (01-010) or (01-011) for Wear Marks on the Aft Side

    1. Refer to Figure.

      2. Examine the bore for wear at Location 18.

        1. No wear.

        1. Accept.

        2. Wear marks.

        1. Do inspection of HPT for possible oil ignition event. Refer to TASK 72-45-00-200-801. Report all findings to IAE Technical Services.

    3. SUBTASK 72-45-11-230-052-001 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Cracks

    1. Refer to Figure.

    2. Clean the part. Refer to TASK 72-45-11-100-000 (CLEANING-000).

      NOTE

      When you inspect the hub for cracks, make sure you check the important areas. These areas are shown in Figure.

      3. Do the test for cracks on the part that is given below. Use the applicable penetrant inspection procedure.

        PART IDENT

        TASK/SUBTASK

        Stage 1 turbine hub

        (Dip or Spray)

        1. Cracked.

        1. Reject.

    4. SUBTASK 72-45-11-250-010 Examine the Stage 1 Turbine Hub (01-010) or (01-011) Blade Slot Pressure Face by Eddy Current Inspection

    1. Refer to Figure.

      2. Do a dimensional check of the stage 1 turbine hub blade slot pressure face contact surface.

      1. Refer to TASK 72-45-11-200-003 (INSPECTION-003).

    5. SUBTASK 72-45-11-220-062 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Corrosion, Dents, Nicks, Scratches and Blade Slot Tool Marks

    1. Refer to Figure.

      2. Examine the turbine hub for corrosion, dents, nicks and scratches on all the surfaces except blade slots.

        1. Corrosion, dents, nicks and scratches.

        1. Damage up to 0.001 in. (0.0254 mm) in depth, is permitted.

        2. Damage more than Step.

        1. Repair, VRS3184 TASK 72-45-11-300-001 (REPAIR-001).

      3. Examine the turbine hub for corrosion, dents, nicks, scratches and tool marks in the blade slots.

        1. Corrosion, dents, nicks and scratches.

        1. Damage up to 0.001 in. (0.025 mm) in depth is permitted in Area 19 fillet radii and slot bottom. No blending permitted.

        2. Damage up to 0.001 in. (0.025 mm) in depth is permitted in Area 20. Blend up to 0.007 in. (0.18 mm) to remove surface damage. Refer to Repair, VRS3184 TASK 72-45-11-300-001 (REPAIR-001).

        3. Damage up to 0.003 in. (0.08 mm) in depth is permitted in Area 21, with no raised material or sharp edges. No blending permitted.

        4. Damage up to 0.003 in. (0.08 mm) in depth is permitted in Area 22 pressure face, with no raised material or sharp edges. No blending permitted.

        5. Damage up to 0.004 in. (0.10 mm) is acceptable without repair in Area 23. Blend up to 0.010 in. (0.25 mm) to remove surface damage. Refer to Repair, VRS3184 TASK 72-45-11-300-001 (REPAIR-001).

        2. Inspect blade slots for tool marks.

        1. Tool marks are not permitted in Area 19 fillet radii and slot bottom and Area 22 pressure face. This does not include slot bottom mismatches. This does not include fretting or contact wear. Refer to Tooling card IAE2P16631 for example of tool marks and example of slot bottom mismatches. If any of these unacceptable conditions are observed do not return disk to service and report to IAE Customer Technical Service.

        2. Tool marks up to 0.003 in. (0.08 mm) in Areas 20, 21 and 23 are permitted.

    6. SUBTASK 72-45-11-220-063 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Distorted, Fretted and Galled Diameters

    1. Refer to Figure.

      2. Examine the turbine hub for distorted, fretted and galled diameters at Location 3, 7, 8, 11, 12, 15, 16 and 17.

        1. Distorted, fretted and galled.

        1. Repair, VRS3184 TASK 72-45-11-300-001 (REPAIR-001).

    7. SUBTASK 72-45-11-220-093 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Dents, Nicks, Scratches, Fretted, Galled and Wear on the Axial Stack Surfaces

    1. Refer to Figure.

      2. Examine the turbine hub at Location 13, for dents, nicks, scratches, fretted, galled and wear on the axial stack surface.

        1. Any local wear or damage not more than 0.0005 in. (0.013 mm).

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3508 TASK 72-45-11-300-015 (REPAIR-015).

      3. Examine the turbine at Location 9, for dents, nicks, scratches, fretted, galled and wear on the axial stack surface.

        1. Any local wear or damage not more than 0.0005 in. (0.013 mm).

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3803 TASK 72-45-11-300-013 (REPAIR-013).

    8. SUBTASK 72-45-11-220-064 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Dents, Nicks, Scratches and Wear on all the Blade Slots, Seal Slots, Hub Lock Slots and Holes

    1. Refer to Figure.

      2. Examine the turbine hub for dents, nicks, scratches and wear at the locations that follow.

      1. Blade slots at Location 2.

      2. Seal slots at Locations 1 and 4.

      3. Hub lock slots at Location 6.

        4. Holes at Location 14.

          1. Dents, nicks and scratches.

          1. Damage up to 0.001 in. (0.0254 mm) in depth, is permitted.

          2. Wear or damage more than Step.

          1. Repair, VRS3184 TASK 72-45-11-300-001 (REPAIR-001).

    9. SUBTASK 72-45-11-220-065 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Fretted, Galled, Corrosion and Wear on the Spline

    1. Refer to Figure.

      2. Examine the turbine hub for fretted, galled, corrosion and wear on the spline at Location 10.

        1. Fretted galled, corrosion and wear.

        1. Repair, VRS3184 TASK 72-45-11-300-001 (REPAIR-001).

    10. SUBTASK 72-45-11-220-067 Examine the Stage 1 Turbine Hub (01-010) or (01-011) Diameters

    1. Refer to Figure.

      2. Examine the turbine hub at Location 1503, for the rear outer diameter.

        1. If the dimension is between 18.1185 in. and 18.124 in. (460.210 mm and 460.349 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. Other than Step.

        1. Reject.

      3. Examine the turbine hub at Location 1504, for the front outer diameter.

        1. If the dimension is between 17.758 in. and 17.762 in. (451.054 mm and 451.154 mm).

        1. Accept

        2. Write down the dimension of the diameter.

        2. If the dimension is between 17.753 in. and 17.7625 in. (450.926 mm and 451.168 mm).

        1. Accept part for select fit only.

        2. Write down the dimension of diameter.

          NOTE

          This part can be used only if the mating part has a diameter that will result in fit of reference No. 1504. Refer to TASK 72-45-10-440-001 (ASSEMBLY).

        3. Other than Step.

        1. Reject.

      4. Examine the turbine hub at Location 1502, for the front outer diameter.

        1. If the dimension is between 14.1615 in. and 14.1667 in. (359.703 mm and 359.834 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. Other than Step.

        1. Reject.

      5. Examine the turbine hub at Location 1501, for the front inner diameter.

        1. If the dimension is between 8.618 in. and 8.624 in. (218.898 mm and 219.050 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. Other than Step.

        1. Reject.

      6. Examine the turbine hub at Location 2246, for the front inner diameter.

        1. If the dimension is between 5.101 in. and 5.1025 in. (129.566 mm and 129.603 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. Other than Step.

        1. Reject.

      7. Examine the turbine hub at Location 1515, for the heat shield diameter.

        1. If the dimension is between 5.753 in. and 5.763 in. (146.13 mm and 146.38 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. Other than Step.

        1. Reject.

    11. SUBTASK 72-45-11-220-068 Examine the Stage 1 Turbine Hub (01-010) or (01-011) Front Air Seal Engagement Axial Dimension

    1. Refer to Figure.

      2. Examine the turbine hub front air seal engagement axial dimension at Location 1550 (check at two positions, 180 degrees apart).

        1. If the dimension is between 0.496 in. and 0.503 in. (12.598 mm and 12.776 mm) at two positions.

        1. Accept.

        2. Other than Step.

        1. Reject.

    12. SUBTASK 72-45-11-220-069 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for Axial Length

    1. Refer to Figure.

      2. Examine the turbine hub for the axial length dimension.

      1. Measure the axial length dimension at Location 4.

      2. Find the axial length dimension that is marked on the hub at Location 2.

        3. If the result of the axial dimension taken at Location 4 is 0.001 in. (0.0254 mm) more or less than the dimension marked on the hub at Location 2.

        1. Accept.

        2. Write down the axial length dimension.

        4. Other than Step, examine the surfaces at Location 5 and 6.

          1. The surfaces at Locations 5 and 6 must be parallel in 0.0005 in. (0.013 mm) or less and the surface at Location 5 must be flat in 0.001 in. (0.0254 mm) or less.

          1. Accept.

          2. Other than Step.

          1. Repair, VRS3803 TASK 72-45-11-300-013 (REPAIR-013).

        5. If Step is accepted, mark the turbine hub at Location 2 with the new axial dimension written in Step, followed with the letter A.

        1. Make a mark on the turbine hub at Location 2, refer to SPM TASK 70-09-00-400-501. Electrical contact is only permitted at Location 3.

          2. Examine the electrical contact area at Location 3 for burns, pitting and selective attack.

            1. Burns, pitting or selective attack.

            1. Reject.

      6. Record the final dimension of Location 4 as AA. You can use this recorded dimension AA during assembly process.

    13. SUBTASK 72-45-11-220-071 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for the Spline Dimension

    1. Refer to Figure.

      NOTE

      The length of the pins can not extend more than the distance of the worn area. If the pins extend into an area that is not worn, the measurement is unsatisfactory.

      2. Examine the turbine hub for the spline tooth wear at Location 7. Use two pins 0.090 in. (2.286 mm) in diameter.

      1. CAUTION

        USE ONLY THE SPECIFIED PIN DIAMETER. INCORRECT PIN DIAMETER WILL CAUSE AN UNSATISFACTORY MEASUREMENT.

        Position the two pins, 180 degrees apart between the splines.

        2. Measure the spline tooth wear up to 4.7725 in. (121.222 mm) in diameter.

        1. Accept.

        2. Write down the dimension of the tooth wear.

        3. More than Step.

        1. Reject.

    14. SUBTASK 72-45-11-220-072 Examine the Stage 1 Turbine Hub (01-010) or (01-011) for the Cycle Time of the Part

    1. Refer to Figure.

    2. Examine the turbine hub at Location 2 for the cycle time of the part at each disassembly.

      3. Calculate the new engine run cycles.

      1. Get the part cycles from the engine records since the last shop visit (disassembly) and write the cycles down.

      2. Write down the engine run cycles marked on the part at Location 2.

      3. Add the results of Step and Step. The result is the new engine run cycles.

      4. Mark the new maximum life of the part (cycles) on the turbine hub, refer to the SPM TASK 70-05-00-220-501.

      1. Mark the turbine hub by SPM TASK 70-09-00-400-501 at Location 2. The electrical contact is only permitted at Location 3.

        2. Examine the electrical contact area at Location 3, for burns, pitting and selective attack.

          1. Burns, pitting and selective attack.

          1. Reject.

    15. Figure: Stage 1 Turbine Hub Inspection Locations

    Stage 1 Turbine Hub Inspection Locations

    Figure: Stage 1 Turbine Hub Inspection Locations

    Stage 1 Turbine Hub Inspection Locations

    Figure: Stage 1 Turbine Hub Important FPI Inspection Locations

    Stage 1 Turbine Hub Important FPI Inspection Locations

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised procedure to update inspection location and figures. (17VC295)