TASK 72-45-00-200-002-A00 HPT Stage 2 Air Seal - Examine, Inspection-002

DMC:V2500-A0-72-45-0012-00A-300A-C|Issue No:002.00|Issue Date:2017-11-01

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 72-45-00-200-002-A00 HPT Stage 2 Air Seal - Examine, Inspection-002

Effectivity

FIG/ITEM

PART NO.

01-080

2A0487

General

This TASK gives the procedure for the inspection of the stage 2 HPT air seal. For the other parts of the HP turbine rotor and stator assembly, refer to TASK 72-45-00-200-000 (INSPECTION/CHECK-000).

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

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

All the parts must be cleaned before any part is examined. Refer to TASK 72-45-00-100-000 (CLEANING-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 SUBTASK 72-45-00-230-054. Do the 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

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Balancing fixtureLOCALBalancing fixture

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

CAUTION

THIS PART MUST BE INSPECTED BY THE FOLLOWING STEPS BEFORE IT IS REPLACED. THIS INSPECTION IS REQUIRED TO CONFIRM THAT NO IRREGULAR SERVICE EXPERIENCE OCCURED. FAILURE TO COMPLY WITH THESE REQUIREMENTS WILL RESULT IN DAMAGE TO THE ENGINE AND/OR AIRCRAFT.
PERFORM SUBTASK 72-45-00-220-173 TO EXAMINE FOR THE PRESENCE OF SOOT AND OIL.
CLEAN THE PART BY TASK 72-45-00-100-002.
FPI THE PART FOR CRACK INDICATIONS BY SUBTASK 72-45-00-230-054-001.
PERFORM THE SUBTASK 72-45-00-220-112 TO INSPECT BORE AXIAL DIMENSION.
IF THE BORE AXIAL DIMENSION WAS OUT OF LIMITS, PERFORM ALL THE SUBTASKS OF THIS INSPECTION AND REPORT ALL FINDINGS TO IAE TECH SERVICES.

Procedure

    1. SUBTASK 72-45-00-220-173 Examine the Stage 2 HTP Air Seal (01-080) 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 air seal for soot and oil at location 1.

        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 72-45-00-230-054-001 Examine the Stage 2 HPT Air Seal (01-080) for Cracks

    1. Refer to Figure

    2. Clean the Part. Refer to the TASK 72-45-00-100-000 (CLEANING-000).

      3. NOTE

        When you inspect the seal for cracks make sure you check the important areas. These areas are shown in Figure.

        Do the test for cracks on the part that is given below. Carefully examine fillet radii, the knife-edge seals at location 1, the web at location 4, and the tab at location 5. Use the applicable penetrant procedure.

        PART IDENT

        TASK/SUBTASK

        Stage 2 HPT Air Seal

        SPM TASK

        (Dip or spray)

        1. Cracks that go into the base metal at the knife edges, Location 1

        1. Repair, VRS3207 TASK 72-45-00-300-004 (REPAIR-004)

        2. NOTE

          If the crack originates at the fillet radius (outer diameter side) and extends through to the inner diameter side, reject the HPT stage 1 hub HPT Stage 1 Hub (72-45-11, 01-011), HPT stage 2 hub ENGINE-STAGE 2 TURBINE HUB (72-45-31, 01-011) and HPT stage 1 air seal - rear ENGINE-STAGE 1 AIR SEAL (REAR) (72-45-15, 01-020).

          Cracks found in the front fillet radius

        1. Reject

        3. NOTE

          Refer to Step for cracked coating on the knife-edge seals.

          Cracks that go into the base metal at locations other than the knife-edges or front fillet radius

        1. Reject

    3. SUBTASK 72-45-00-220-066 Examine the Stage 2 HPT Air Seal (01-080) for Scratches, Nicks, Dents and Corrosion

      1. Examine the air seal for scratches, nicks, dents and corrosion.

        1. Scratches, nicks, dents, or corrosion

        1. Repair, VRS3208 TASK 72-45-00-300-002 (REPAIR-002)

    4. SUBTASK 72-45-00-220-067 Examine the Stage 2 HPT Air Seal (01-080) for Chipped or Cracked Plasma Spray Coating on the Knife-Edge Seals

    1. Refer to Figure

      2. Examine the air seal at location 1, for chipped or cracked plasma spray coating on the knife-edge seal (4 locations).

        1. Chipped coating.

          1. If the base metal does not show

          1. Accept

          2. Other than (a)

          1. Repair, VRS3209 TASK 72-45-00-300-003 (REPAIR-003) or VRS3207 TASK 72-45-00-300-004 (REPAIR-004)

        2. Cracked coating.

          1. If the cracks do not look like they go into the base metal

          1. Repair, VRS3209 TASK 72-45-00-300-003 (REPAIR-003) or VRS3207 TASK 72-45-00-300-004 (REPAIR-004)

          2. Cracks that go into the knife edge base metal

          1. Repair, VRS3207 TASK 72-45-00-300-004 (REPAIR-004)

          3. Cracks that go into the pedestal

          1. Reject

    5. SUBTASK 72-45-00-220-068 Examine the Stage 2 HPT Air Seal (01-080) for Wear on the Rear Contact Faces

    1. Refer to Figure

      2. Examine the air seal at location 3, for wear on the rear contact face.

        1. Wear

        1. Repair, VRS3208 TASK 72-45-00-300-002 (REPAIR-002)

      3. Examine the air seal at location 2, for wear on the rear contact face.

        1. Wear up to 0.002in. (0.051 mm)

        1. Accept

        2. Other than (1)

        1. Repair, VRS3208 TASK 72-45-00-300-002 (REPAIR-002)

    6. SUBTASK 72-45-00-220-069 Examine the Stage 2 HPT Air Seal (01-080) for Wear on the Sides of the Front Tabs

    1. Refer to Figure

      2. Examine the air seal at location 5, for wear on the sides of the front tabs.

        1. Wear.

          1. Up to 0.005 in. (0.127 mm) depth

          1. Accept

          2. Other than (a)

          1. Reject

    7. SUBTASK 72-45-00-220-070 Examine the Stage 2 HPT Air Seal (01-080) for Wear on the Front Contact Faces

    1. Refer to Figure

      2. Examine the air seal at location 6, for wear on the front contact faces (4 locations).

        1. Wear.

          1. Up to 0.002 in. (0.050 mm) in depth

          1. Accept

          2. Other than (a)

          1. Repair, VRS3208 TASK 72-45-00-300-002 (REPAIR-002) and/or VRS3211, TASK 72-45-00-300-006 (REPAIR-006)

    8. SUBTASK 72-45-00-220-174 Examine the Stage 2 HPT Air Seal (01-080) for Wear Marks on the Bore

    1. Refer to Figure and Figure.

      2. Examine the air seal for wear marks on the bore.

        1. No wear marks

        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.

    9. SUBTASK 72-45-00-220-071 Examine the Stage 2 HPT Air Seal (01-080) for the Axial Length

      NOTE

      If the measured axial length in a free condition is not satisfactory, a held condition is permitted. All dimensions apply when Surfaces F and G are flat by 0.002 in. (0.051 mm), Diameter D maintains a clearance envelope of 17.136 in. (436.254 mm) diameter, and Diameter E maintains a clearance envelope of 18.126in. (460.40 mm) diameter in a free or held condition. Hold the air seal only on Surfaces F and G and Diameters D and E.

    1. Refer to Figure.

      2. Examine the air seal at location 1, for the axial length.

        1. Axial length.

          1. If the axial length is between 2.739 and 2.749 in. (69.57 and 69.82 mm)

          1. Accept

          2. Other than (a)

          1. Reject

      2. Record the average dimension as AB. This recorded dimension AB will be used during assembly process.

    10. SUBTASK 72-45-00-220-072 Examine the Stage 2 HPT Air Seal (01-080) for Wear on the Front Flange Diameter, the Knife-Edge Seal Diameters, and the Rear Flange Diameter

      NOTE

      If the measured diameters in a free condition are not satisfactory, a held condition is permitted. All dimensions apply when Surfaces F and G are flat by 0.002in. (0.051 mm), Diameter D maintains a clearance envelope of 17.136in. (436.254 mm) diameter, and Diameter E maintains a clearance envelope of 18.126in. (460.426 mm) diameter in a free or held condition. Hold the air seal only on Surfaces F and G and Diameters D and E.

    1. Refer to Figure

      2. Examine the air seal at location 1505, for wear on the rear flange diameter.

        1. If the diameter is between 17.126 and 17.1355 in. (435.000 and 435.242 mm)

        1. Accept

        2. Write down the dimension of the diameter.

        2. NOTE

          This part can be used only if the mating part has a diameter that will result in fit of reference No. 1505. Refer to TASK 72-45-00-430-001-A00 (ASSEMBLY, CONFIG-001).

          Other than (1)

        1. Repair, VRS3315 TASK 72-45-00-300-007 (REPAIR-007)

      3. Examine the air seal at location 1579, for wear on the knife-edge seal diameters (4 locations).

        1. If the average diameter of the four knife-edges is 19.146in. (486.305 mm) or more, no diameters are less than 19.142in. (486.207 mm) and the coating is not fully worn from the tips of the knife-edges

        1. Accept

        2. Write down the dimension of the diameters.

        2. Other than (1)

        1. Repair, VRS3209 TASK 72-45-00-300-003 (REPAIR-003)

      4. Examine the air seal at location 1503, for wear on the front flange diameter.

        1. If the diameter is between 18.117 and 18.1265in. (460.172 and 460.413 mm)

        1. Accept

        2. Write down the dimension of the diameter.

        2. NOTE

          This part can be used only if the mating part has a diameter that will result in fit of reference No. 1503. Refer to TASK 72-45-00-430-001-A00 (ASSEMBLY, CONFIG-001).

          Other than (1)

        1. Repair, VRS3210 TASK 72-45-00-300-008 (REPAIR-008)

    11. SUBTASK 72-45-00-220-073 Examine the Stage 2 HPT Air Seal (01-080) for the Engine Cycles of the Part

    1. Refer to Figure

    2. Examine the air seal at Location 2, for the total engine cycles that was marked before (at each disassembly).

      3. Calculate the new total number of engine cycles for the air seal (You can get the new engine cycles from the engine operating records).

      1. Add the new engine cycles since the last inspection to the engine cycles that is marked on the air seal.

    4. Do not install the air seal if the total number of engine cycles is more than the maximum cycles given in TASK 05-10-01-200-001-A00 (GROUP A PARTS LIVES, CONFIG-001).

      5. Mark the new total number of engine cycles on the air seal.

      1. Electrical contact is only permitted at location 5.

      2. Mark the air seal at location 2.

        3. Examine the air seal at location 5, for electrical contact, burns, pitting and selective attack.

          1. Electrical contact

          1. Accept

          2. Burns, pitting, or selective attack

          1. Reject

    12. SUBTASK 72-45-00-220-112 Examine the Stage 2 HPT Air Seal (01-080) for the Bore Axial Position

    1. Refer to Figure.

    2. Measure and make a record of the dimension at location 4 at six places circumferentially. The measurements must be equally spaced at an 8.200 in. (208.28 mm) radius reference location.

    3. Measure and make a record of the dimension at location 3 at six places circumferentially. The measurements must be equally spaced at the same location as the dimension at location 4.

      4. Subtract the dimension at location 3 from the dimension at location 4 at each circumferential location.

        1. If the dimension is between 0.570 and 0.614 in. (14.48 and 15.60 mm)

        1. Accept

        2. Other than Step.

        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.

    13. Figure: Stage 2 HPT Air Seal Inspection Locations

    Sheet 1

    Legend
    Stage 2 HPT Air Seal Inspection Locations

    Sheet 1

    Close

    Figure: Stage 2 HPT Air Seal Important Inspection Locations

    Sheet 2

    Legend
    Stage 2 HPT Air Seal Important Inspection Locations

    Sheet 2

    Close

    Figure: Stage 2 HPT Air Seal Inspection Locations

    Stage 2 HPT Air Seal Inspection Locations

    Figure: Stage 2 HPT Air Seal Inspection Locations

    Stage 2 HPT Air Seal Inspection Locations

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure to add inspection criteria. (16VC282)

Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:LOCAL
Tool Number:Balancing fixture
Tool Name:Balancing fixture