TASK 72-45-21-200-001 HPT Case - Examine, Inspection-001

DMC:V2500-A0-72-45-2101-00A-300A-C|Issue No:006.00|Issue Date:2018-05-01

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 72-45-21-200-001 HPT Case - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-010

2A0250

01-010

2A0250SL87VA156

01-010

2A1591

01-010

2A1591SL87VA156

01-010

2A1600

01-010

2A1600SL114902

General

This TASK gives the procedure for the inspection of the turbine case assembly. For other turbine case assembly parts, refer to TASK 72-45-21-200-000 (INSPECTION-000).

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

The policy that is necessary for check is given in the SPM TASK 70-20-01-200-501.

All the parts must be cleaned before any part is examined. Refer to the SPM TASK 70-11-03-300-503.

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 which must have a crack test is given in Step. Do the test before the part is visually examined. Limits for cracks are given in the SUBTASK for each part.

A ** following repair 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.

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 the SPM.

References

Refer to the SPM for data on these items.

Definitions of Damage, SPM TASK 70-02-02-350-501

Inspection of Parts, SPM TASK 70-20-01-200-501.

Some data on these items is contained in this TASK. For more data on these items refer to the 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 72-45-21-230-051 Examine the Turbine Case Assembly (01-010) for Cracks

    1. Clean the parts. Refer to TASK 72-45-21-100-000 (CLEANING-000).

    2. Do the test for cracks on the parts that are given below. Use the applicable penetrant procedure.

      PART IDENT

      TASK/SUBTASK

      Turbine case assembly

      3. Cracked

        1. Radially outward cracking from front flange bolt hole.

        1. Repair, VRS1487 TASK 72-45-21-300-010 (REPAIR-010)

          NOTE

          Use VRS1487 if the cracks increase radially outward from the bolt hole surface. Cracks occur at the bolt hole inner diameter surface are not repairable by VRS1487.

        2. Other than in Step.

        1. Reject

    2. SUBTASK 72-45-21-220-053 Examine the Turbine Case Assembly (01-010) Surface

      1. Examine the surface.

        1. Nicks

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs.

          1. Accept

          2. If the depth is between 0.005 and 0.010 in. (0.13 and 0.25 mm).

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

          3. Other than in Step andStep.

          1. Reject

        2. Dents

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs.

          1. Accept

          2. If the depth is between 0.005 in. and 0.010 in. (0.13 and 0.25 mm).

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

          3. Other than in Step andStep

          1. Reject

        3. Scratches

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs.

          1. Accept

          2. If the depth is between 0.005 and 0.010 in. (0.13 and 0.25 mm).

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

          3. Other than in Step andStep.

          1. Reject.

        4. Pit.

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs.

          1. Accept.

          2. If the depth is between 0.005 and 0.010 in. (0.13 and 0.25 mm).

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

          3. Other than in Stepand Step.

          1. Reject.

        5. Erosion.

          1. If the depth is less than 0.005 in. (0.130 mm) with no sharp edges.

          1. Accept.

          2. Other than Step.

          1. Reject.

    3. SUBTASK 72-45-21-220-054 Examine the Turbine Case Assembly (01-010) Slots

    1. Refer to Figure.

      2. Examine the slots at location 1.

        1. Worn.

        1. Reject.

        2. Pits.

          1. Up to 0.003 in. (0.07 mm) in depth.

          1. Accept.

          2. More than in Step.

          1. Reject.

        3. Width of slot.

          1. Up to 0.265 in. (6.73 mm).

          1. Accept.

          2. More than in Step.

          1. Reject

    4. SUBTASK 72-45-21-220-055 Examine the Turbine Case Assembly (01-010) Bolt Holes

    1. Refer to Figure.

      2. Examine the bolt holes at location 2.

        1. Nicks.

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs.

          1. Accept

          2. If the depth is between 0.005 and 0.010 in. (0.13 and 0.25 mm).

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

          3. Other than in Stepand Step.

          1. Reject

        2. Dents.

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs

          1. Accept

          2. If the depth is between 0.005 and 0.010 in. (0.13 and 0.25 mm)

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001)

          3. Other than in Stepand Step.

          1. Reject

        3. Scratches

          1. If the depth is less than 0.005 in. (0.13 mm) with no sharp edges or burrs.

          1. Accept

          2. If the depth is between 0.005 and 0.010 in. (0.13 and 0.25 mm).

          1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

          3. Other than in Stepand Step.

          1. Reject

    5. SUBTASK 72-45-21-220-056 Examine the Turbine Case Assembly (01-010) Threads/Helicoil Insert

    1. Refer to Figure.

      2. Examine the threads of borescope boss at location 3.

        1. Damage

        1. Refer to repair, VRS1985 TASK 72-45-21-300-012 (REPAIR-012).

      3. Examine the threads of TCA boss at location 3.

        1. Damage

        1. Refer to repair, VRS1986 TASK 72-45-21-300-013 (REPAIR-013).

      4. Examine the insert of borescope boss at location 3.

        NOTE

        This step is applicable to installed insert in VRS1985.

        1. Loose, missing or with the internal thread damaged

        1. Refer to repair, VRS1987 TASK 72-45-21-300-014 (REPAIR-014).

      5. Examine the insert of TCA boss at location 3.

        NOTE

        This step is applicable to installed insert in VRS1986.

        1. Loose, missing or with the internal thread damaged

        1. Refer to repair, VRS1988 TASK 72-45-21-300-015 (REPAIR-015).

    6. SUBTASK 72-45-21-220-057 Replace the Turbine Case Assembly (01-010) Clinch Nut

    1. Refer to Figure.

      2. Replace the clinch nut at location 4.

        1. Replace the clinch nut.

        1. Repair, VRS1476 TASK 72-45-21-300-002 (REPAIR-002).

    7. SUBTASK 72-45-21-220-058 Examine the Turbine Case Assembly (01-010) Flanges for Flatness

    1. Refer to Figure.

      2. Examine the flanges for flatness in free state condition.

        1. Flange A at location 5.

          1. Up to 0.010 in. (0.25 mm) in out of flatness.

          1. Accept

          2. More than in Step.

          1. Reject

        2. Flange B at location 6.

          1. Up to 0.010 in. (0.25 mm) in out of flatness.

          1. Accept

          2. More than in Step.

          1. Reject

    8. SUBTASK 72-45-21-220-059 Examine the Turbine Case Assembly (01-010) Locating Pin

    1. Refer to Figure.

      2. Examine the locating pin at location 7.

        1. Evidence of wear.

        1. Accept

        2. Sheared off.

        1. Repair, VRS1478 TASK 72-45-21-300-005 (REPAIR-005).

        3. Bent

        1. Repair, VRS1478 TASK 72-45-21-300-005 (REPAIR-005).

        4. Missing

        1. Repair, VRS1478 TASK 72-45-21-300-005 (REPAIR-005).

        5. Loose fit.

        1. Repair, VRS1478 TASK 72-45-21-300-005 (REPAIR-005).

    9. SUBTASK 72-45-21-220-060 Examine the Turbine Case Assembly (01-010) Bracket

    1. Refer to Figure.

      2. Examine the bracket at location 8.

        1. Broken

        1. Repair, VRS1480 TASK 72-45-21-300-006 (REPAIR-006).

        2. Bent

        1. Repair, VRS1480 TASK 72-45-21-300-006 (REPAIR-006).

        3. Damaged

        1. Repair, VRS1480 TASK 72-45-21-300-006 (REPAIR-006).

        4. Loosened rivet

        1. Repair, VRS1480 TASK 72-45-21-300-006 (REPAIR-006).

    10. SUBTASK 72-45-21-220-061 Examine the Turbine Case Assembly (01-010) First Stage Duct Support Grooves

    1. Refer to Figure.

      2. Examine the first stage duct support grooves at location 10.

        1. Radial width of less than or equal to 0.10 in. (2.56 mm).

        1. Accept

        2. Radial width of greater than 0.10 in. (2.56 mm).

        1. Reject

    11. SUBTASK 72-45-21-220-062 Examine the Turbine Case Assembly (01-010) Snap Diameters

    1. Refer to Figure.

      2. Examine the snap diameter.

        1. Diameter A at location 11 (Reference No. 2253).

          1. Worn/Shrink.

            1. From 28.227 in. to 28.233 in. (716.966 mm to 717.118 mm) in average inner diameter.

            1. Accept

            2. From 28.222 in. to 28.233 in. (716.839 mm to 717.118 mm) in average inner diameter.

            1. Accept the part for select fit only.

              NOTE

              This part can be used only if the mating part has a diameter that will result in a fit of reference No. 2253. Refer TASK 72-00-45-420-001 (INSTALLATION-001) and TASK 72-40-00-430-006 (INSTALLATION-006).

            3. More than 28.233 in. (717.118 mm) and less than 28.253 in. (717.626 mm) in average inner diameter.

            1. Repair, VRS1471 TASK 72-45-21-300-003 (REPAIR-003).

            4. Other than Step, Stepand Step.

            1. Reject

          2. Out of roundness in free state.

            1. Up to 0.035 in. (0.889 mm) in TIR.

            1. Accept

            2. More than Step.

            1. Reject

              NOTE

              1. Diameter B applies when front of flange A and rear surface of flange B are flat with 0.001 in. (0.025 mm) and diameter A and C are around within 0.007 in. (0.178 mm) in free state or constrained.

              2. Constraint contact allowed only on flange A, front and rear surface, flange B, front and rear surface, diameter A and diameter C.

        2. Diameter B at location 12.

          1. Worn/Shrink.

            1. From 27.893 in. to 27.902 in. (708.482 mm to 708.710 mm) in average outer diameter.

            1. Accept

            2. Other than Step.

            1. Reject

        3. Diameter C at location 13 (Reference No. 1510)

          1. Worn/Shrink.

            1. From 28.577 in. to 28.583 in. (725.856 mm to 726.008 mm) in average inner diameter

            1. Accept

            2. From 28.572 in. to 28.583 in. (725.729 mm to 726.008 mm) in average inner diameter

            1. Accept the part for select fit only.

              NOTE

              This part can be used only if the mating part has a diameter that will result in a fit of reference No. 1510. Refer to ASSEMBLY-02 TASK 72-45-20-440-002.

            3. More than 28.583 in. and less than 28.603 in. (726.008 mm and 726.516 mm) in average inner diameter

            1. Repair, VRS1482 TASK 72-45-21-300-008 (REPAIR-008)

            4. Other than in Step, Step and Step.

            1. Reject

          2. Out of roundness in free state.

            1. Up to 0.035 in. (0.889 mm) in TIR.

            1. Accept

            2. More than in Step

            1. Reject

    12. SUBTASK 72-45-21-220-063 Examine the Turbine Case Assembly (01-010, Part No.2A1591 only) Hook

    1. Refer to Figure.

      NOTE

      Refer to Figure to confirm the Area A.

      2. Examine the hook at location 14.

        1. Chipping

          1. Outside area A zone.

          1. Accept

          2. Inside area A zone.

            1. Up to one place per quadrant (90 ARG) and which is less than 0.030 in. (0.76 mm) in depth and 0.500 in. (12.70 mm) length.

            1. Accept

            2. Other than in Step.

            1. Repair, VRS1486 TASK 72-45-21-300-009 (REPAIR-009).

    13. SUBTASK 72-45-21-220-066 Examine the Turbine Case Assembly (01-010) Hook

    1. Refer to Figure.

      2. Examine the hook at location 15.

        1. Worn

        1. From 2.947 in. to 2.953 in. (74.854 mm to 75.006 mm) in dimension A.

          2. Greater than 2.953 in. (75.006 mm) and less than or equal to 2.961 in. (75.209 mm) in dimension A.

          1. Repair, VRS1486 TASK 72-45-21-300-009 (REPAIR-009).

          3. Other than Stepand Step.

          1. Reject

    14. SUBTASK 72-45-21-220-067 Examine the Turbine Case Assembly (01-010) Chamfer Around Pin Hole on the Front Flange Mating Surface

    1. Refer to Figure.

      2. Examine the chamfer around pin hole on the front flange mating surface at location 9.

        1. Nicks, Dents and Scratches.

        1. Repair, VRS1472 TASK 72-45-21-300-001 (REPAIR-001).

        2. Cracks

        1. Reject

    15. Figure: Inspection of the turbine case assembly

    Inspection of the turbine case assembly

    Figure: Inspection of the turbine case assembly

    Inspection of the turbine case assembly

    Figure: Inspection of the turbine assembly

    Inspection of the turbine assembly

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

87VJ905L