TASK 72-45-31-200-001-B00 HPT Stage 2 Hub - Examine, Inspection-001

DMC:V2500-A0-72-45-3101-00B-300A-C|Issue No:004.00|Issue Date:2020-08-01

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 72-45-31-200-001-B00 HPT Stage 2 Hub - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-011

2A1302

General

This TASK gives the procedure for the inspection of the stage 2 turbine hub. For the other parts of the stage 2 turbine hub, refer to TASK 72-45-31-200-000 (INSPECTION/CHECK-000).

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 Step. 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 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.

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

Methods 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 72-45-31-220-123 Examine the Stage 2 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 2 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 72-45-31-230-052 Examine the Stage 2 Turbine Hub (01-011) for Cracks

    1. Refer to Figure.

    2. Clean the part. Refer to TASK 72-45-31-100-000 (CLEANING-000).

      NOTE

      When you inspect the stage 2 turbine 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 2 turbine hub

        SPM TASK

        (Dip or Spray)

        1. Cracked.

        1. Reject.

    3. SUBTASK 72-45-31-250-008 Examine the Stage 2 Turbine Hub (01-011) Blade Slot Pressure Face by Eddy Current Inspection

    1. Refer to Figure.

    2. Do a dimensional check of the stage 2 turbine hub blade slot pressure face contact surface. Refer to TASK 72-45-31-200-007 (INSPECTION/CHECK-007).

    4. SUBTASK 72-45-31-220-060 Examine the Stage 2 Turbine Hub (01-011) for Corrosion, Dents, Nicks, Scratches and Blade Slot Tool Marks

    1. Refer to Figure.

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

        1. Corrosion, dents, nicks and scratches.

        1. Damage up to 0.001 in. (0.025 mm) in depth is permitted.

        2. Damage more than Step.

        1. Repair, VRS3238 TASK 72-45-31-300-001 (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 16 fillet radii and slot bottom. No blending permitted.

        2. Damage up to 0.003 in. (0.08 mm) in depth is permitted in Area 17 pressure face. No blending permitted.

        3. Damage up to 0.003 in. (0.08 mm) in depth is permitted in Area 18. No blending permitted.

        4. Damage up to 0.001 in. (0.025 mm) in depth is permitted in Area 19. Blend up to 0.007 in. (0.18 mm) to remove surface damage. Refer to Repair, VRS3238 TASK 72-45-31-300-001 (REPAIR-001).

        2. Inspect blade slots for tool marks.

        1. Tool marks are not permitted in Area 16 fillet radii and slot bottom and Area 17 pressure face. This does not include slot bottom mismatches. This does not include fretting or contact wear. Refer to Tooling card IAE2P16632 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 18 and 19 are permitted.

    5. SUBTASK 72-45-31-220-061 Examine the Stage 2 Turbine Hub (01-011) for Fretted and Galled Diameters

    1. Refer to Figure.

      2. Examine the turbine hub for fretted and galled diameters at Locations 2, 8, 10 and 13.

        1. Fretted and galled.

        1. Repair, VRS3238 TASK 72-45-31-300-001 (REPAIR-001).

    6. SUBTASK 72-45-31-220-062 Examine the Stage 2 Turbine Hub (01-011) for Dents, Nicks, Scratches and Wear on all the Blade Slots, Seal Slots, Hub Lock Slots, Holes and Contact Faces

    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 6.

      2. Seal slots at Locations 4 and 5.

      3. Hub lock slots at Location 3.

      4. Holes at Location 12.

        5. Contact faces at Locations 1 and 8.

          1. Dents, nicks, scratches and wear.

          1. Repair, VRS3238 TASK 72-45-31-300-001 (REPAIR-001).

        6. Contact face at Location 7.

          1. Dents, nicks, scratches and wear.

          1. Repair, VRS3511 TASK 72-45-31-300-010 (REPAIR-010).

        7. Contact face at Location 11.

          1. Dents, nicks, scratches and wear.

          1. Repair, VRS3238 TASK 72-45-31-300-001 (REPAIR-001) or Repair, VRS3644 TASK 72-45-31-300-012 (REPAIR-012) or Repair, VRS3510 TASK 72-45-31-300-009 (REPAIR-009).

            NOTE

            At Location 15 (rear face of the ladder lock lug) a machined step to a maximum of 0.025 in. (0.64 mm) is permitted.

    7. SUBTASK 72-45-31-220-063 Examine the Stage 2 Turbine Hub (01-011) for Fretting, Galling, Corrosion and Wear on the Spline

    1. Refer to Figure.

      2. Examine the turbine hub for fretting, galling, corrosion and wear on the spline at location 9.

        1. Fretting, galling, corrosion and wear.

        1. Repair, VRS3238 TASK 72-45-31-300-001 (REPAIR-001) or VRS3499 TASK 72-45-31-300-008 (REPAIR-008).

    8. SUBTASK 72-45-31-220-120 Examine the Stage 2 HPT Hub for Wear Marks on the Forward Side

    1. Refer to Figure.

      2. Examine the bore for wear at Location 14.

        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.

    9. SUBTASK 72-45-31-220-064 Examine the Stage 2 Turbine Hub (01-011) Diameters

    1. Refer to Figure.

      2. Examine the stage 2 turbine hub at Location 1506, for the rear outer diameter.

        1. If the non-select (worn) dimension is between 17.382 in. and 17.387 in. (441.503 mm and 441.629 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. If the select fit dimension is between 17.3815 in. and 17.3885 in. (441.490 mm and 441.668 mm).

        1. Accept part for select fit only.

        2. Write down the dimension of the diameter.

          NOTE

          This part can be used only if the mating part has a diameter that will result in fit of reference No. 1506. Refer to TASK 72-45-30-440-001-B00 (ASSEMBLY, CONFIG-002).

        3. Other than Step.

        1. Reject.

      3. Examine the stage 2 turbine hub at Location 1505, for the front outer diameter.

        1. If the non-select (worn) dimension is between 17.134 in. and 17.138 in. (435.204 mm and 435.305 mm).

        1. Accept.

        2. Write down the dimension of the diameter.

        2. If the select fit dimension is between 17.129 in. and 17.1401 in. (435.08 mm and 435.36 mm).

        1. Accept part for select fit only.

        2. Write down the dimension of the diameter.

          NOTE

          This part can be used only if the mating part has a diameter that will result in fit of reference No. 1505. Refer to TASK 72-45-00-430-001-A00 (ASSEMBLY, CONFIG-001).

        3. Other than Step.

        1. Reject.

      4. Examine the stage 2 turbine hub at Location 2249, for the rear inner diameter.

        1. If the dimension is between 4.835 in. and 4.836 in. (122.809 mm and 122.834 mm).

          1. Accept.

          1. Write down the dimension of the diameter.

        2. If the dimension is between 4.8345 in. and 4.8364 in. (122.796 mm and 122.844 mm).

          1. Accept part for select fit only.

          1. Cylindricity within plus or minus 0.0005 in. (0.0127 mm).

          2. Write down the dimension of the diameter.

            NOTE

            This part can be used only if the mating part has a diameter that will result in fit of reference No. 2249. Refer to TASK 72-00-45-420-001-A01 (INSTALLATION-001) or TASK 72-40-00-430-006-A00 (ASSEMBLY-006).

        3. Other than (Step or Step) then:

        1. Repair, VRS3790 TASK 72-45-31-300-014 (REPAIR-014).

      5. Examine the turbine hub front inner diameter at Location 1500.

        1. If the dimension is between 5.529 in. and 5.533 in. (140.437 mm and 140.538 mm).

        1. Accept.

        2. Other than Step.

        1. Reject.

    10. SUBTASK 72-45-31-220-065 Examine the Stage 2 Turbine Hub (01-011) for Axial Length

    1. Refer to Figure.

      2. Examine the turbine hub for axial length at Location 1.

        1. If the dimension is between 6.048 in. and 6.056 in. (153.619 mm and 153.822 mm).

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3510 TASK 72-45-31-300-009 (REPAIR-009) or Repair, VRS3644 TASK 72-45-31-300-012 (REPAIR-012).

      3. Examine the turbine hub inner diameter for axial length at Location 4.

        1. If the dimension is between 4.483 in. and 4.503 in. (113.87 mm and 114.38 mm).

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3511 TASK 72-45-31-300-010 (REPAIR-010).

    11. SUBTASK 72-45-31-220-067 Examine the Stage 2 Turbine Hub (01-011) for the Spline Dimension

      CAUTION

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

    1. Refer to Figure.

      2. Examine the turbine hub for the spline tooth wear at Location 6. Use two pins 0.090 in. (2.286 mm) in diameter.

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

        2. Measure the spline tooth wear

          1. Not more than 4.7725 in. (121.222 mm) in diameter.

          1. Accept.

          2. More than Step.

          1. Reject.

            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.

    12. SUBTASK 72-45-31-220-068 Examine the Stage 2 Turbine Hub (01-011) for the Cycle Time of the Part (Cycles)

    1. Refer to Figure.

    2. Examine the turbine hub at Location 3 for the cycle time of the part at each disassembly.

      3. Calculate the new engine run cycles.

      1. Get out part cylces 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 3.

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

      4. Mark the new cycle time of the part on the turbine hub. Refer to SPM TASK 70-05-00-220-501.

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

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

          1. Burns, pitting and selective attack.

          1. Reject.

    13. SUBTASK 72-45-31-220-110 Examine the Stage 2 Turbine Hub (01-011) for Incorrect Marking Location

    1. Refer to Figure.

      2. Examine the Stage 2 turbine hub for incorrect marking at Location 5.

        1. Ink marking only or no marking.

        1. Accept.

        2. Marking of part number that penetrates below disk surface.

        1. Repair, VRS3704 TASK 72-45-31-300-013 (REPAIR-013).

    14. Figure: Stage 2 Turbine Hub Inspection Locations

    Stage 2 Turbine Hub Inspection Locations

    Figure: Stage 2 Turbine Hub Inspection Locations

    Stage 2 Turbine Hub Inspection Locations

    Figure: Stage 2 Turbine Hub, Important FPI Inspection Locations

    Stage 2 Turbine Hub, Important FPI Inspection Locations

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedural steps. (19VC241)