TASK 72-50-22-200-003-F00 LPT Stage 5 Vane - Examine The Stage 5 Turbine Vanes

DMC:V2500-A0-72-50-2205-00F-300A-C|Issue No:003.00|Issue Date:2017-08-01

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 72-50-22-200-003-F00 LPT Stage 5 Vane - Examine The Stage 5 Turbine Vanes

Effectivity

FIG/ITEM PART NO.

01-350

3A3120

General

This TASK gives the procedure for the inspection of the Stage 5 turbine vanes.

Before you do this inspection refer to TASK 72-50-32-200-008-B00.

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

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

All parts must be cleaned before any part is examined. Refer to the TASK 72-50-22-100-000.

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 crack 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 the SPM.

References

Refer to the SPM for data on these items.

Definitions of Damage, 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 the SPM.

Method of testing for crack indications

Chemical processes

Surface protection

NOTE

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

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
IAE 2M14173 Axial deflection gage0AM53IAE 2M14173

1 off

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-22-230-001 Examine the Stage 5 Turbine Vanes for Cracks

    1. Refer to Figure and Figure.

    2. Clean the parts. Refer to TASK 72-50-22-100-000.

      3. Do the tests for cracks on the part that are given below. Use the applicable penetrant procedure.

        PART IDENT TASK/SUBTASK

        Stage 5 turbine vanes

        1. Cracked inner or outer platforms in Area A9.

          1. Not more than 0.010 in. (0.25 mm) maximum depth.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150).

          2. More than in Step but not more than 0.010 in. (0.25 mm) maximum width and 0.0787 in. (2.00 mm) length except area A10.

          1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

          3. Other than in Step or Step.

          1. Reject.

        2. Cracked airfoils in Areas A1 to A8 except Areas A2 and A5.

          1. Not more than 0.010 in. (0.25 mm) maximum width and 0.0787 in. (2.00 mm) maximum length.

          1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

        3. Cracked airfoils in Areas A2 and A5.

          1. Not more than 0.010 in. (0.25 mm) maximum width and 0.0787 in. (2.00 mm) maximum length on one airfoil only.

          1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

    2. SUBTASK 72-50-22-220-001 Examine the Airfoil, Inner and Outer Annulus / Gaspath Surfaces of the Stage 5 Turbine Vanes for Coating Damage

      1. Damaged or not sufficient coating.

        1. Damaged or not sufficient coating in areas total less than 1.000 sqin (645.16 sq mm) per vane airfoil.

        1. Refer to Repair, VRS4621 TASK 72-50-22-300-151 (REPAIR-151).

        2. More than in Step.

        1. Refer to Repair, VRS4622 TASK 72-50-22-300-152 (REPAIR-152).

      2. Blistering, sulphidation.

        1. Do the heat tint test.

        2. Not within limits.

        1. Refer to Repair, VRS4622 TASK 72-50-22-300-152 (REPAIR-152) or Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150).

    3. SUBTASK 72-50-22-220-002 Examine the Stage 5 Turbine Vanes in Area A1 to A9 for Surface Damage

    1. Refer to Figure.

      2. Examine the surface in Area A1.

        1. Nicked, dented, pitted.

          1. Round bottom dents not more than 0.020 in. (0.51 mm) maximum depth, not more than 10 percent of Area A1.

          1. Accept.

          2. Nicked, pitted not more than 0.005 in. (0.13 mm) maximum depth, no raised material.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      3. Examine the surface in Area A2.

        1. Nicked, dented, pitted.

          1. Round bottom dents not more than 0.010 in. (0.25 mm) maximum depth.

          1. Accept.

          2. Nicked, pitted not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      4. Examine the surface in Area A3.

        1. Nicked, dented, pitted in Area A3.1.

          1. Not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          2. More than in Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

        2. Nicked, dented, pitted in Area A3.2.

          1. Not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          2. One round bottom dent per airfoil not more than 0.010 in. (0.25 mm) maximum depth, no coating cracks.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      5. Examine the surface in Area A4.

        1. Nicked, dented, pitted in Area A4.1.

          1. Not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          2. More than in Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

        2. Nicked, dented, pitted in Area A4.2.

          1. Not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          2. Bent not more than 0.020 in. (0.51 mm) maximum deflection and 0.700 in. (17.78 mm) total maximum length each airfoil.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      6. Examine the surface in Area A5.

        1. Nicked, dented, pitted.

          1. Round bottom dents not more than 0.010 in. (0.25 mm) maximum depth.

          1. Accept.

          2. Nicked, pitted not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      7. Examine the surface in Area A6.

        1. Nicked, dented, pitted.

          1. Round bottom dents not more than 0.020 in. (0.51 mm) maximum depth, not visible from other side, not more than 10 percent of Area A6.

          1. Accept.

          2. Nicked, pitted not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      8. Examine the surface in Area A7.

        1. Nicked, dented, pitted.

          1. Round bottom dents not more than 0.010 in. (0.25 mm) maximum depth.

          1. Accept.

          2. Nicked, pitted not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      9. Examine the surface in Area A8.

        1. Nicked, dented, pitted.

          1. Round bottom dents not more than 0.020 in. (0.51 mm) maximum depth, not visible from other side, not more than 10 percent of Area A8.

          1. Accept.

          2. Nicked, pitted not more than 0.005 in. (0.13 mm) maximum depth.

          1. Accept.

          3. More than in Step or Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

      10. Examine the surface in Area A9.

        1. Nicked, dented, pitted

          1. Not more than 0.010 in. (0.25 mm) maximum depth, no raised material.

          1. Accept.

          2. More than in Step.

          1. Refer to Repair, VRS4620 TASK 72-50-22-300-150 (REPAIR-150) or Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

    4. SUBTASK 72-50-22-220-003 Examine the Stage 5 Turbine Vanes Inner Honeycomb Seal

      1. Unbonded.

        1. Any quantity unbonded from the vane.

        1. Refer to Repair, VRS4580 TASK 72-50-22-300-129 (REPAIR-154).

      2. Rub damaged.

        1. Smooth wear pattern, 0.394 in. (10.00 mm) maximum width and 0.060 in. (1.50 mm) maximum depth.

        1. Accept.

        2. More than in Step.

        1. Refer to Repair, VRS4580 TASK 72-50-22-300-129 (REPAIR-154).

    5. SUBTASK 72-50-22-220-004 Examine the Inner and Outer Platform End Faces of the Stage 5 Turbine Vanes for Wear

      1. Fretted.

        1. Not more than 0.002 in. (0.05 mm) maximum depth.

        1. Accept.

        2. More than in Step.

        1. Reject.

    6. SUBTASK 72-50-22-220-005 Examine the Stage 5 Turbine Vanes at Dimension D1 for Wear

    1. Refer to Figure.

      2. Examine the Diameter D1. Use IAE 2M14173 Axial deflection gage.

        1. Not less than 1.181 in. (30.00 mm).

        1. Accept.

        2. Less than in Step.

        1. Reject.

    7. SUBTASK 72-50-22-220-006 Examine the Stage 5 Turbine Vanes at Dimension D2 for Wear

    1. Refer to Figure.

      2. Worn, measure Dimension D2.

        1. Not less than 0.3051 in. (7.75 mm).

        1. Accept.

        2. Less than in Step.

        1. Refer to Repair, VRS4173 TASK 72-50-22-300-048 (REPAIR-048).

    8. SUBTASK 72-50-22-220-007 Examine the Stage 5 Turbine Vanes at Dimension D3 for Wear

    1. Refer to Figure.

      2. Worn, measure Dimension D3.

        1. Not less than 0.150 in. (3.81 mm).

        1. Accept.

        2. Less than in Step but not less than 0.1350 in. (3.43 mm).

        1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

    9. SUBTASK 72-50-22-220-008 Examine the Stage 5 Turbine Vanes at Dimension D4 for Wear

    1. Refer to Figure.

      2. Worn, measure Dimension D4.

        1. Not less than 0.124 in. (3.15 mm).

        1. Accept.

        2. Less than in Step but not less than 0.1094 in. (2.78 mm).

        1. Refer to Repair, VRS4624 TASK 72-50-22-300-154 (REPAIR-154).

    10. Figure: Examine The Stage 5 Turbine Vanes

    Examine The Stage 5 Turbine Vanes

    Figure: Examine The Stage 5 Turbine Vanes

    Examine The Stage 5 Turbine Vanes

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Updated link

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:0AM53
Tool Number:IAE 2M14173
Tool Name:IAE 2M14173 Axial deflection gage