TASK 72-45-30-220-001-A00 HPT Stage 2 Rotor Assembly - Examine, Inspection-001

DMC:V2500-A1-72-45-3000-00A-300A-C|Issue No:003.00|Issue Date:2018-02-01

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 72-45-30-220-001-A00 HPT Stage 2 Rotor Assembly - Examine, Inspection-001

General

The word "reject" is used after an assembly inspection statement to show that a higher level inspection and possible repair to the damaged part is necessary.

Do the higher level inspection procedure as found in the applicable Chapter/Section/Subject of this manual on the damaged part(s). It is not necessary to do the higher level inspection on parts that are serviceable to the interface inspection standard.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-45-30-220-091 Examine the Stage 2 HPT Rotor Assembly 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. Refer to Figure.

      2. Examine the rotor assembly at Locations 7, 9 and 17 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 72-45-30-220-064 Visually Examine the Stage 2 Turbine Blade at Location 1

    1. Refer to Figure.

      2. Examine the blade airfoil and platform for burns.

        1. If burns on the airfoil or platform have gone through the coating

        1. Reject

      3. Examine the blade airfoil and platform coating for nicks and chips.

        1. There are nicks or chips in the airfoil coating that show the base metal

        1. Reject

        2. There are nicks or chips in the coating on the platform at Location 13 or the airfoil fillet radius that show the base metal

        1. Reject

      4. Examine the blade airfoil and platform for cracks.

        1. There are airfoil, airfoil radius or platform radius cracks

        1. Reject

        2. There is a platform crack at Location 13

        1. Reject

        3. There are cracks at Location 14

        1. Accept

      5. Examine the blade airfoil and platform for dents.

        1. The depth of the dent is more than 0.015 in. (0.38 mm)

        1. Reject

        2. The dent has a crack or damaged coating

        1. Reject

        3. The dent has a bottom that is not smooth

        1. Reject

        4. The dent is in the airfoil or platform radius

        1. Reject

        5. A dent is 0.050 in. (1.27 mm) or less from the trailing edge

        1. Reject

      6. Examine the stage 2 HPT blade abrasive tip.

        1. There is base metal that shows on the base metal/tip interface at Location 25

        1. Reject

      2. CAUTION

        FAILURE TO REPLACE AN ADEQUATE NUMBER OF BLADE TIPS MAY REDUCE ENGINE PERFORMANCE AND/OR REDUCE BLADE AND OUTER AIRSEAL REPAIRABILITY.

        NOTE

        If new or fully repaired Stage 2 HPT Duct Segments (BOAS) are to be installed, two thirds of Stage 2 HPT blades must have fully repaired tips. One third of the blades can have complete, partial, or no tip coating.

      7. Examine the blade trailing edge for blocked cooling slots.

        1. A slot is blocked after you try to remove the blockage with a wire probe

        1. Reject

      8. Examine the leading and trailing edges of the blade platform.

        1. The depth of the rubs at Locations 2 and 12 is more than 0.015 in. (0.38 mm)

        1. Reject

    3. SUBTASK 72-45-30-220-065 Visually Examine the Knife-Edge of the Retaining Plate at Location 3

    1. Refer to Figure

      2. Cracks, nicks or bent

      1. Reject

    4. SUBTASK 72-45-30-220-066 Visually Examine the Surface of the Retaining Plate at Location 4

    1. Refer to Figure

      2. Surface damage, dents, scratches, burrs and round-bottom nicks up to 0.004 in. (0.102 mm) in depth with no sharp edges

      1. Accept

      3. Sharp-bottom nicks

      1. Reject

      4. Cracks

      1. Reject

    5. SUBTASK 72-45-30-220-067 Visually Examine the Stage 2 Rear Sideplate Lock and Key Assemblies at Location 5

    1. Refer to Figure

      2. Cracks

      1. Reject

    6. SUBTASK 72-45-30-220-068 Visually Examine the Stage 2 Rear Sideplate Tabs and the Stage 2 Disk Rear Retaining Lugs at Location 6

    1. Refer to Figure

      2. Cracks

      1. Reject

    7. SUBTASK 72-45-30-220-069 Visually Examine the Disk Surface at Location 7

    1. Refer to Figure

      2. Cracks, nicks or dents

      1. Reject

    8. SUBTASK 72-45-30-220-070 Visually Examine the Stage 2 Turbine Disk at the HPT Retaining Nut Mating Face at Location 8

    1. Refer to Figure

      2. Scored or high metal

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

    9. SUBTASK 72-45-30-220-071 Visually Examine the Stage 2 Disk Metering Plug at Location 9

    1. Refer to Figure

      2. Metering plug is not there or you can remove it with your hand (4 locations)

      1. Reject

    10. SUBTASK 72-45-30-220-072 Visually Examine the Stage 2 Disk at Location 10

    1. Refer to Figure

      2. Scored or high metal

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

    11. SUBTASK 72-45-30-220-073 Visually Examine the Stage 2 Disk Splines at Location 11

    1. Refer to Figure

      2. Damage

      1. Reject

    12. SUBTASK 72-45-30-220-087 Visually Examine the Disk Surface at Location 15

    1. Refer to Figure

      2. Ink marking only or no marking

      1. Accept.

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

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

    13. SUBTASK 72-45-00-220-119 Visually Examine the Disk Surface at Location 15

    1. Refer to Figure.

      2. Examine the bore for wear at Location 16.

        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.

    14. Figure: Stage 2 Turbine Rotor Assembly Inspection

    Sheet 1

    Legend
    Stage 2 Turbine Rotor Assembly Inspection

    Sheet 1

    Close

    Figure: Stage 2 Turbine Rotor Assembly Inspection

    Sheet 2

    Legend
    Stage 2 Turbine Rotor Assembly Inspection

    Sheet 2

    Close

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Editorial Fix to update duplicate Subtask 72-45-00-220-109 to 72-45-00-220-119