TASK 72-00-45-220-002-A00 HPT Assembly - Examine The HPT Assembly Front Face At Interface M-45, Inspection-002 - Pre SBE 72-0190

DMC:V2500-A1-72-00-4500-01A-300A-B|Issue No:004.00|Issue Date:2020-05-01

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 and Pre SBE 72-0190

Common Information

TASK 72-00-45-220-002-A00 HPT Assembly - Examine The HPT Assembly Front Face At Interface M-45, Inspection-002 - Pre SBE 72-0190

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/Suject 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.

Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) (examine the modular/non-modular interfaces) before you do this TASK.

The policy that is necessary for inspection is given in the SPM TASK 70-20-01-200-001.

Decreased module run time will result if you install modules that are near the maximum interface limits.

Erosion damage - Indications having a weathered, abraded, or corroded appearance.

All parts must be visually examined for damage, corrosion and wear. All defects (distress, missing hardware etc.) that are not identified in the procedure must be documented and referred to IAE Technical Services.

NOTE

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

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
IAE 1P16046 Removal/Installation fixture0AM53IAE 1P16046
IAE 1P16222 Fixture0AM53IAE 1P162221
IAE 1P16543 Removal/Installation fixture0AM53IAE 1P16543

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-45-220-080 Visually Examine the Bolt Holes of the Case Flange at Location 1

    1. Refer to Figure.

      2. Surface damage, dents, scratches, burrs and round bottom nicks up to 0.010 in. (0.254 mm) deep with no sharp edges.

      1. Accept

      3. Sharp bottom nicks

      1. Reject

      4. Cracks

      1. Reject

    2. SUBTASK 72-00-45-220-254 Examine the Bolt Holes of the Case Flange at Location 1

    1. Refer to Figure.

    2. Clean the bolt holes per SPM TASK 70-11-26-300-503 (PW equivalent SPOP 208).

    3. Perform local FPI per SPM TASK 70-23-05-230-501 (high sensitivity) (or equivalent PW SPOP 70).

    4. Examine the flange bolt holes carefully.

      5. If you find any indication.

      1. Reject.

    3. SUBTASK 72-00-45-220-081 Visually Examine the Case Flange at Location 2

    1. Refer to Figure.

      2. Surface damage, dents, scratches, burrs and round bottom nicks up to 0.010 in. (0.254 mm) deep with no sharp edges

      1. Accept

      3. Sharp bottom nicks

      1. Reject

      4. Cracks

      1. Reject

    4. SUBTASK 72-00-45-220-082 Visually Examine the Surface of the Case at Location 3

    1. Refer to Figure.

      2. Surface damage, dents, scratches, burrs and round bottom nicks up to 0.010 in. (0.254 mm) deep with no sharp edges

      1. Accept

      3. Sharp bottom nicks

      1. Reject

      4. Cracks

      1. Reject

    5. SUBTASK 72-00-45-220-083 Visually Examine the Hardface on the Outer Airseal Supports at Location 4

    1. Refer to Figure.

      2. Chipped or spalled on more than 10 percent of the hardface area

      1. Reject

    6. SUBTASK 72-00-45-220-084 Visually Examine the Diameter of the Case Flange at Location 5

    1. Refer to Figure.

      2. Round bottom dents up to 0.250 in. (6.350 mm) in diameter and up to 0.010 in. (0.254 mm) in depth

      1. Accept

      3. Wear up to 25 percent of the contact surface

      1. Accept

      4. Other than A or B

      1. Reject

    7. SUBTASK 72-00-45-220-085 Visually Examine the Stage 1 Ceramic Outer Airseals at Location 6

    1. Refer to Figure.

      2. There is metal from the blades on the airseals

      1. Accept

      3. Any segment that has spalling or chipping down to the metal layer (dark color layer) for not more than:

        1. 50 per cent of the ceramic

        1. Accept

      4. Cracks in the ceramic (white) layer of the coating

      1. Accept

      5. Other than Step, Step or Step

      1. Reject

    8. SUBTASK 72-00-45-220-086 Measure the Stage 1 Turbine Blade Tip Clearance at Location 7

    1. Refer to Figure.

    2. NOTE

      This fixture is required to do this inspection. The HP turbine case assembly must be held for this inspection. Also the IAE 1P16046 Removal/Installation fixture or IAE 1P16543 Removal/Installation fixture is installed when you remove the HP turbine rotor and stator assembly from the engine. Do not remove this fixture when you do the inspection.

      Install the IAE 1P16222 Fixture 1 off to the front flange of the HP turbine case assembly.

      3. Measure at eight equally spaced locations in the axial center of the rub groove. Do not rotate the rotor.

        1. More than 0.077 in. (1.956 mm) (average of eight measurements)

        1. Reject

    9. SUBTASK 72-00-45-220-087 Visually Examine the Stage 1 Turbine Blades at Location 8

    1. Refer to Figure.

      2. Nicks and dents on the airfoil.

        1. If the nick or dent is in area A or B and is more than 0.200 in. (5.080 mm)

        1. Reject

      3. Erosion or burns on the airfoil or platforms.

        1. If the erosion or burn is on the leading edge and is more than 20 percent of the airfoil radial length

        1. Reject

        2. If the erosion or burn on the leading edge has changed the shape of the airfoil

        1. Reject

        3. If the erosion or burn on the airfoil or platform has gone through the coating. This does not include burns on the leading edge

        1. Reject

        4. If the erosion or burn on the airfoil trailing edge in the inner 50 percent of area A is more than 0.050 in. (1.270 mm) axially

        1. Reject

        5. If the erosion or burn on the airfoil trailing edge in the outer 50 percent of area A is more than 0.070 in. (1.778 mm) axially, but does not include the tip

        1. Reject

        6. If the erosion or burn on the blade tip is more than 0.060 in. (1.52 mm) radially

        1. Reject

          NOTE

          For reference, the concave side tip cooling holes are 0.080 in. (2.032 mm) from the tip.

          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, TASK 72-45-14-300-021. This condition is acceptable.

      4. Cracks on the airfoil.

        1. If the crack is in area A or B and is more than 0.050 in. (1.270 mm)

        1. Reject

        2. If the crack in area A or B goes from a burned area and both the burn and the crack is more than 0.050 in. (1.270 mm)

        1. Reject

        3. If the crack in area C is more than 0.070 in. (1.778 mm)

        1. Reject

        4. If the crack in area C goes from a burned area and both the burn and the crack is more than 0.070 in. (1.778 mm)

        1. Reject

        5. If a radial crack on the airfoil starts at the blade tip and is more than 0.120 in. (3.048 mm). The number of cracks is not important

        1. Reject

      5. Cracks on the platform.

        1. If there are cracks that are longer than 0.080 in. (2.032 mm)

        1. Reject

        2. If there is a crack that goes through the platform to the airfoil fillet radius. The number of cracks is not important

        1. Reject

      6. Discoloration and/or deposits on the airfoil or platform

      1. Accept

    10. SUBTASK 72-00-45-220-088 Visually Examine the Outer Surface of the Outer Seal at Location 9

    1. Refer to Figure.

      2. Scored or grooves

      1. Reject

    11. SUBTASK 72-00-45-220-089 Visually Examine the Outer Seal Surface at Location 10

    1. Refer to Figure.

      2. Nicks or dents

      1. Reject

      3. Look for sign of soot or oil.

      1. If signs of soot and oil are found, inspect the High Pressure Turbine for possible oil ignition event. Refer to TASK 72-45-00-200-801.

      2. Report all findings to IAE Technical Services.

    12. SUBTASK 72-00-45-220-090 Visually Examine the Knife-Edges of the Outer Seal at Location 11

    1. Refer to Figure.

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

      1. Reject

    13. SUBTASK 72-00-45-220-091 Measure the Inner Seal Knife-Edge Diameters at Locations 12, 13 and 14

    1. Refer to Figure.

      2. If the diameter at location 14 is less than 9.127 in. (231.826 mm)

      1. Reject

      3. If the diameter at location 13 is less than 9.027 in. (229.286 mm)

      1. Reject

      4. If the diameter at location 12 is less than 8.927 in. (226.746 mm)

      1. Reject

    14. SUBTASK 72-00-45-220-092 Visually Examine the Knife-Edges of the Inner Seal Location 15

    1. Refer to Figure.

      2. Cracks

      1. Reject

      3. Nicks or bent

      1. Repair, VRS3199 TASK 72-45-13-300-001 (REPAIR-001)

    15. SUBTASK 72-00-45-220-093 Visually Examine the Disk Surface at Location 16

    1. Refer to Figure.

      2. Nicks or dents

      1. Reject

    16. SUBTASK 72-00-45-220-094 Visually Examine the Stage 2 Turbine Disk at the HPT Retaining Nut Mating Face at Location 17

    1. Refer to Figure.

      2. Scored or high metal up to 0.005 in. (0.127 mm) in depth.

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

    17. SUBTASK 72-00-45-220-095 Visually Examine the Stage 2 Disk at Location 18

    1. Refer to Figure.

      2. Scored or high metal up to 0.005 in. (0.127 mm) in depth.

      1. Repair, VRS 3238 TASK 72-45-31-300-001 (REPAIR-001)

    18. SUBTASK 72-00-45-220-096 Visually Examine the Stage 2 Disk Splines at Location 19

    1. Refer to Figure.

      2. Damage

      1. Reject

    19. SUBTASK 72-00-45-220-097 Visually Examine the Stage 1 Disk Splines at Location 20

    1. Refer to Figure.

      2. Damage

      1. Reject

    20. SUBTASK 72-00-45-220-098 Visually Examine the Stage 1 Disk at Location 21

    1. Refer to Figure.

      2. Scored or high metal up to 0.005 in. (0.127 mm) in depth.

      1. Repair, VRS 3184 TASK 72-45-11-300-001 (REPAIR-001)

    21. SUBTASK 72-00-45-220-099 Visually Examine the Cooling Air Holes of the Inner Seal at Location 22

    1. Refer to Figure.

      2. Cracks

      1. Reject

      3. There are signs of soot and oil.

      1. If signs of soot and oil are found, inspect the High Pressure Turbine for possible oil ignition event. Refer to TASK 72-45-00-200-801.

      2. Report all findings to IAE Technical Services.

    22. SUBTASK 72-00-45-220-205 Visually Inspect the TOBI Seal Inner Diameter at Location 24

    1. Refer to Figure.

      2. There is scored high material, damage, and/or erosion

      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. There are signs of soot and oil.

      1. If signs of soot and oil are found, inspect the High Pressure Turbine for possible oil ignition event. Refer to TASK 72-45-00-200-801.

      2. Report all findings to IAE Technical Services.

    23. SUBTASK 72-00-45-220-206 Visually Inspect All of the Metering Plugs of the Stage 1 Disk at Location 23

    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

    24. SUBTASK 72-00-45-220-246 Visually Inspect Area of HPT Stage 1 Hub between Inner and Outer Air Seal at Location 25

      1. There are signs of soot and oil.

      1. If signs of soot and oil are found, inspect the High Pressure Turbine for possible oil ignition event. Refer to TASK 72-45-00-200-801.

      2. Report all findings to IAE Technical Services.

    25. Figure: Locations at Interface M-45

    Sheet 1

    Legend
    Locations at Interface M-45

    Sheet 1

    Close

    Figure: Locations at Interface M-45

    Sheet 2

    Legend
    Locations at Interface M-45

    Sheet 2

    Close

    Figure: Locations at Interface M-45

    Sheet 3

    Legend
    Locations at Interface M-45

    Sheet 3

    Close

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Added new subtask and revised figure. (19VC115)

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 1P16046
Tool Name:IAE 1P16046 Removal/Installation fixture
Manufacturer Code:0AM53
Tool Number:IAE 1P16222
Tool Name:IAE 1P16222 Fixture
Manufacturer Code:0AM53
Tool Number:IAE 1P16543
Tool Name:IAE 1P16543 Removal/Installation fixture