TASK 72-45-10-220-001-A00 HPT Stage 1 Rotor Assembly - Examine, Inspection-001

DMC:V2500-A1-72-45-1000-00A-300A-C|Issue No:003.00|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

V2500-A1

Common Information

TASK 72-45-10-220-001-A00 HPT Stage 1 Rotor Assembly - Examine, Inspection-001

General

The word "reject" is used after an interface 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 72-45-10-220-099 Examine the Stage 1 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 3, 4, 7, 10, 16 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 72-45-10-220-070 Visually Examine the Stage 1 Turbine Blade at Location 1

    1. Refer to Figure, Figure and 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

        2. If the burn is on the leading edge and more than five per cent of the airfoil radial length with no indications of hole plugging

        1. Reject

          NOTE

          The blade may not make a full run if there is missing coating.

      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 14 or the airfoil fillet radius that show the base metal.

        1. Reject

          NOTE

          The tip of the trailing edge may have a blend no more than 0.060 in. (0.24 mm) deep, extending from the tip to the middle of the third trailing edge window. Reference Repair, VRS3685, TASK 72-45-14-300-021. This condition is acceptable.

      4. Examine the blade airfoil and platform for cracks.

        1. There is a radial crack in Area A that intersects more than two holes.

        1. Reject.

        2. There is a radial crack in Area B that intersects more than one hole

        1. Reject

        3. There is an axial airfoil crack.

        1. Reject.

        4. There is an airfoil or platform radius crack.

        1. Reject.

        5. There is a platform crack (which does not come from a platform cooling hole) at location 14 that is longer than 0.070 in. (1.778 mm).

        1. Reject.

        6. There is a radial tip crack at location 30 that is longer than 0.090 in. (2.286 mm).

        1. Reject.

      5. Examine the blade airfoil and platform for dents.

        1. The depth of the dent is more than 0.010 in. (0.254 mm).

        1. Reject.

        2. The dent blocks cooling air holes.

        1. Reject.

        3. The dent has a crack or damaged coating

        1. Reject

        4. The dent is in the airfoil or platform radius

        1. Reject

        5. A dent on the trailing edge blocks more than 50 percent of a cooling air slot

        1. Reject

        6. A dent on the trailing edge extends more than 0.100 in. (2.54 mm) along the blade span

        1. Reject

      6. Examine the stage 1 HPT blade abrasive tip.

        1. 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 1 HPT Duct Segments (BOAS) are to be installed, two thirds of Stage 1 HPT blades must have fully repaired tips. One third of the blades can have complete, partial, or no tip coating.

          There is base metal that shows on the base metal/tip interface at location 29

        1. Reject

          NOTE

          The two holes, Index 31, not fully or fully open or fully closed.

      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 edge of the blade platform.

        1. The depth of the rubs at location 12 and 13 is more than 0.015 in. (0.38 mm).

        1. Reject.

    3. SUBTASK 72-45-10-220-071 Visually Examine the Outer Surface of the Outer Seal at Location 11

    1. Refer to Figure.

      2. Scored or grooves.

      1. Reject.

    4. SUBTASK 72-45-10-220-072 Visually Examine the Outer Seal Surfaces at Location 10

    1. Refer to Figure.

      2. Nicks or dents.

      1. Reject.

    5. SUBTASK 72-45-10-220-073 Visually Examine the Knife-Edges of the Outer Seal at Location 9

    1. Refer to Figure.

      2. Chips, cracks, nicks, bent or worn to the base metal.

      1. Reject.

    6. SUBTASK 72-45-10-220-074 Measure the Inner Seal Knife-Edge Diameters at Location 8

    1. Refer to Figure.

      2. If the diameter at location 10 is less than 9.127 in. (231.826 mm).

      1. Reject.

      3. If the diameter at location 9 is less than 9.027 in. (229.286 mm).

      1. Reject.

      4. If the diameter at location 8 is less than 8.927 in. (226.746 mm).

      1. Reject.

    7. SUBTASK 72-45-10-220-075 Visually Examine the Knife-Edges of the Inner Seal at Location 8

    1. Refer to Figure.

      2. Cracks, nicks or bent.

      1. Reject.

    8. SUBTASK 72-45-10-220-076 Visually Examine the Disk Surface at Location 3

    1. Refer to Figure

      2. Nicks or dents

      1. Reject

    9. SUBTASK 72-45-10-220-077 Visually Examine the Stage 1 Disk Metering Plug at Location 4

    1. Refer to Figure

      2. The metering plugs are missing, damaged, and/or have missing or cracked tangs

      1. Reject. Inspect the No.4 bearing rear carbon seal. Refer to TASK 72-43-20-200-002. Report all findings to IAE Technical Services

      3. The metering plug can be removed by hand

      1. Reject

    10. SUBTASK 72-45-10-220-078 Visually Examine the Stage 1 Disk Splines at Location 5

    1. Refer to Figure

      2. Damage

      1. Reject

    11. SUBTASK 72-45-10-220-079 Visually Examine the Stage 1 Disk at Location 6

    1. Refer to Figure

      2. Scored or high metal

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

    12. SUBTASK 72-45-10-220-080 Visually Examine the Cooling Air Holes of the Inner Seal at Location 7

    1. Refer to Figure

      2. Cracks

      1. Reject

    13. SUBTASK 72-45-10-220-081 Visually Examine the Stage 1 HPT Air Seal at Location 2

    1. Refer to Figure

      2. Wear.

        1. Up to 75 percent of the seal knife-edge

        1. Accept

        2. Other than (1)

        1. Reject.

      3. Cracks.

      1. Reject.

    14. SUBTASK 72-45-10-220-107 Visually Examine the Disk Surface at Location 15

    1. Refer to Figure.

      2. Examine the bore for wear at Location 15.

        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.

    15. Figure: Stage 1 Turbine Rotor Assembly Inspection

    Sheet 1

    Legend
    Stage 1 Turbine Rotor Assembly Inspection

    Sheet 1

    Close

    Figure: Stage 1 Turbine Rotor Assembly Inspection

    Sheet 2

    Legend
    Stage 1 Turbine Rotor Assembly Inspection

    Sheet 2

    Close

    Figure: Stage 1 Turbine Rotor Assembly Inspection

    Sheet 3

    Legend
    Stage 1 Turbine Rotor Assembly Inspection

    Sheet 3

    Close

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure to update the figure and location references information. (17VC521)