TASK 72-50-53-200-003-A00 Turbine Exhaust Case (TEC) - Examine, Inspection-003

DMC:V2500-A0-72-50-5301-00A-300A-C|Issue No:004.00|Issue Date:2020-02-01

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

All

Common Information

TASK 72-50-53-200-003-A00 Turbine Exhaust Case (TEC) - Examine, Inspection-003

Effectivity

FIG/ITEM PART NO.

02-300

4B8060

02-300

4B8068

01-001

4A8014

01-001

4A8025

General

This TASK gives the procedure for the inspection of the turbine exhaust case assembly. For the other parts of the turbine exhaust case assembly refer to TASK 72-50-53-200-000 (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 70-20-01-200-501.

All the parts must be cleaned before any part is examined. Refer to the SPM TASK 70-11-03-300-503.

If the instrumentation bushing, PN 4P8009 (02-140), is not loose, inspection of the Turbine Exhaust Case is permitted with the instrumentation bushing in position.

Alternate datum to Surfaces X and Z are available. Refer to Figure.

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 test before the part is visually examined.

A ** following a repair referenced in this inspection indicates that the repair is not yet published in the current revision of the manual and the part must be rejected. Contact IAE for additional information concerning FAA approved repair data.

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 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.

Methods of Testing for Crack Indications

Chemical Processes

Surface Protection

NOTE

To identify the consumable materials refer to the PCI.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Workshop Inspection Equipment0AM53Workshop Inspection Equipment
Hydraulic test pumpLOCALHydraulic test pump
IAE 2F10183 Fixture0AM53IAE 2F101831
IAE 2F10330 Adapter,leak test Scavenge tube0AM53IAE 2F103301
IAE 2F10331 Plug0AM53IAE 2F103311
IAE 2F10332 Bracket0AM53IAE 2F103321
IAE 6F10056 Borescope equipment, 4 mm or 6 mm, video borescope0AM53IAE 6F100561
IAE 6F10029 Air flow test cart0AM53IAE 6F100291

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 10-077 APPROVED ENGINE OILSX333XCoMat 10-077

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-53-230-052 Do a Crack Test on the Turbine Exhaust Case (01-001) (Fluorescent Penetrant)

      NOTE

      Do Repair, VRS3655 TASK 72-50-53-300-076 (REPAIR-076) after you do full turbine exhaust case or local fluorescent penetrant inspections.

    1. Refer to Figure, Figure and Figure.

    2. Clean the parts. Refer to TASK 72-50-53-100-000 (CLEANING-000).

      3. Do the test for cracks on the parts that are given below. Use the applicable penetrant procedure.

        PART IDENT TASK/SUBTASK

        Turbine exhaust case

        1. Through porosity

        1. Reject

          2. Cracks.

            1. Not more than two strut airfoil cracks that are not more than 0.500 in. (12.70 mm) each in length. Cracks must be separated by a minimum of 2.00 in. (50.8 mm). Cracks on solid leading edges of instrumented struts are not permitted

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            2. Strut trailing edge cracks

            1. Repair, VRS3641 TASK 72-50-53-300-074 (REPAIR-074)

            3. U-shaped cracks around the trailing edge strut stand-ups not more than 1.00 in. (25.4 mm) per side. Cracks must be non-linear and a minimum of 1.00 in. (25.4 mm) from the rear flange

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            4. Outer case cracks not more than 1.000 in. (25.40 mm) in length. Cracks must not be on or between upper stiffening rails. Cracks must be a minimum of 2.500 in. (63.50 mm) from the front flange and a minimum of 1.000 in. (25.40 mm) from the rear flange

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            5. Inner case cracks not more than 1.00 in. (25.4 mm) in length. Cracks must not be more than 1.300 in. (33.02 mm) from forward edge of inner case wall

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            6. Cracks on the ID and/or OD weld bead of struts not more than 5.250 in. (133.35 mm) in length

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            7. Strut trailing edge cracks not more than 1.250 in. (31.75 mm) in length

            1. Repair, VRS3641 TASK 72-50-53-300-074 (REPAIR-074)

            8. Strut cracks not more than 3.50 in. (88.9 mm) along the heat affected zone of the leading edge weld bead. Refer to Figure

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            9. Flange bolt hole cracks which go from the bolt hole to the flange OD

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

              NOTE

              Bolt hole cracks which go into the case wall are not permitted.

            10. Inner cone weld seam cracks not more than 1.00 in. (25.4 mm). Cracks must be in the initial weld seams.

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            11. Rear inner flange cracks that are not more than 1.00 in. (25.4 mm) in length

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            12. Strut airfoil cracks that are more than 0.50 in. (12.7 mm) in length. Cracks on solid leading edges of instrumented struts are not permitted

            1. Repair, VRS3743 TASK 72-50-53-300-083 (REPAIR-083)

            13. Front outer fairing cracks along weld bead not more than 6.00 in. (152.4 mm) long with 1.00 in. (25.2 mm) minimum separation between cracks. Refer to Location 12 on Figure

            1. Repair, VRS3522 TASK 72-50-53-300-073 (REPAIR-073)

            14. Other than Step thru Step.

            1. Reject

      4. Drain the fluorescent penetrant from the struts

      1. Repair, VRS3655 TASK 72-50-53-300-076 (REPAIR-076)

    2. SUBTASK 72-50-53-220-056 Examine the External and Internal Surfaces of the Turbine Exhaust Case Assembly (01-001)

      1. Examine the external surfaces and the gaspath surfaces including the inner/outer case walls and struts for corrosion pits, dents, nicks or surface corrosion.

        1. Less than 0.025 in. (0.64 mm) in depth and 0.500 in. (12.70 mm) long

        1. Accept

        2. More than Step

        1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

        3. Surface corrosion

        1. Accept. You can remove corrosion with a wire brush or steel wool

    3. SUBTASK 72-50-53-220-057 Examine the Turbine Exhaust Case (01-001) Oil Feed Tube at Location 1

    1. Refer to Figure.

      2. Clearance between the tube and the strut heatshield at location 2.

        1. More than 0.080 in. (2.03 mm)

        1. Loosen the oil feed tube supporting brackets and re-align the tube

      3. Chafing wear at the point where it penetrates the strut cover.

        1. Evident chafing wear

        1. Repair, VRS5390 TASK 72-50-53-300-006 (REPAIR-006)

      4. Any quantity of coke or carbon inside the tube. Use a 4 mm or 6 mm flexible video borescope. The inside surfaces of the tube must appear smooth, round and free of coke or blockage nodules or flakes.

        1. Coke or carbon

        1. Clean, Refer to TASK 72-50-53-100-002 (CLEANING-002, CONFIG-001)

      5. Pressure leak.

        1. Do a pressure leak check as follows:

        1. Install IAE 2F10183 Fixture 1 off to the oil feed tube

        2. Connect the hydraulic test pump to the adapter on the outer oil feed tube flange

        3. Apply oil pressure to the tube. Open the purge valve to bleed off the air. When all air is vented from the system, close and tighten the purge valve

        4. Apply an oil pressure of 370 psig (2400 kPa). Hold the test pressure for at least 1 minute. Leakages are not permitted

        2. Leakages not because of malfitting of blanking

        1. Repair, VRS5390 TASK 72-50-53-300-006 (REPAIR-006)

      3. Release the pressure, disconnect the pump assembly and remove the fixture

    4. SUBTASK 72-50-53-220-058 Examine the Turbine Exhaust Case (01-001) Oil Scavenge Tube at Location 4

    1. Refer to Figure.

      2. Clearance between the tube and the strut heatshield at location 5.

        1. More than 0.10 in. (2.5 mm)

        1. Loosen the oil scavenge tube supporting brackets and recenter the tube

      3. Chafing wear.

        1. Evident chafing wear

        1. Repair, VRS5391 TASK 72-50-53-300-007 (REPAIR-007)

      4. Any quantity of coke or carbon inside the tube. Use a 4 mm or 6 mm flexible video borescope. The inside surfaces of the tube must appear smooth, round and free of coke or blockage nodules or flakes.

        1. Coke or carbon

        1. Clean, refer to TASK 72-50-53-100-002 (CLEANING-002, CONFIG-001)

      5. Pressure leak.

        1. Do a pressure leak check as follows:

        1. Install IAE 2F10331 Plug 1 off into the oil scavenge tube hole into No. 5 bearing compartment.

        2. Install IAE 2F10332 Bracket 1 off into the No. 5 bearing compartment.

        3. Attach IAE 2F10330 Adapter,leak test Scavenge tube 1 off to the outer oil scavenge tube flange.

        4. Connect IAE 6F10029 Air flow test cart 1 off to the adapter.

        5. Apply an air pressure of 15 psig (100 kPa). Hold the test pressure for at least 1 minute.

        2. Leakages not because of malfitting of the plug

        1. Repair, VRS5391 TASK 72-50-53-300-007 (REPAIR-007)

      3. Release the pressure, disconnect the hose and remove the fixture.

    5. SUBTASK 72-50-53-220-059 Examine the Turbine Exhaust Case (01-001) Oil Tubes Flanges

      1. Worn

      1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

    6. SUBTASK 72-50-53-220-060 Examine the Turbine Exhaust Case (01-001) Mount Lugs at Location 6 and the Stiffening Rails at Location 7

    1. Refer to Figure.

      2. Damaged

      1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

    7. SUBTASK 72-50-53-220-080 Examine the Turbine Exhaust Case (01-001) Load Sharing Fitting Bolt Holes at Location 8

    1. Refer to Figure.

      2. Threads.

        1. Crossed or stripped

        1. Repair, VRS5353 TASK 72-50-53-300-032 (REPAIR-032**)

    8. SUBTASK 72-50-53-220-061 Examine the Turbine Exhaust Case (01-001) Helicoils

      1. Loose, not there or with internal thread damage

      1. Repair, VRS5392 TASK 72-50-53-300-008 (REPAIR-008)

    9. SUBTASK 72-50-53-220-062 Examine the Turbine Exhaust Case (01-001) Mount Bushings at Location 9

    1. Refer to Figure.

      2. Inner diameter.

        1. Worn.

          1. Between 1.1875 and 1.1885 in. (30.163 and 30.188 mm)

          1. Accept

          2. More than 1.1885 in. (30.188 mm)

          1. Repair, VRS5393 TASK 72-50-53-300-009 (REPAIR-009)

        2. Scored.

          1. Not more than 0.004 in. (0.10 mm)

          1. Accept

          2. Between 0.004 and 0.008 in. (0.10 and 0.20 mm)

          1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

          3. More than 0.008 in. (0.20 mm)

          1. Repair, VRS5393 TASK 72-50-53-300-009 (REPAIR-009)

    10. SUBTASK 72-50-53-220-063 Examine the Turbine Exhaust Case (01-001) Ground Handling Bushings at Location 10

    1. Refer to Figure.

      2. Inner diameter.

        1. Worn.

          1. Between 0.5905 and 0.5912 in. (15.000 and 15.018 mm)

          1. Accept

          2. More than 0.5912 in. (15.018 mm)

          1. Repair, VRS5394 TASK 72-50-53-300-010 (REPAIR-010)

        2. Scored.

          1. Not more than 0.004 in. (0.10 mm)

          1. Accept

          2. Between 0.004 and 0.008 in. (0.10 and 0.20 mm)

          1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

          3. More than 0.008 in. (0.20 mm)

          1. Repair, VRS5394 TASK 72-50-53-300-010 (REPAIR-010)

    11. SUBTASK 72-50-53-220-064 Examine the Turbine Exhaust Case (01-001) Struts at Location 11

    1. Refer to Figure.

      2. Kiel heads.

      1. Kiel heads must be open and free from FOD on the inner surfaces.

      2. Damage on the outer surfaces of the kiel heads can be removed by blend.

      3. Leading and trailing edges.

        1. Damage.

          1. Not more than 0.015 in. (0.38 mm) deep

          1. Accept

          2. More than (a)

          1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

        2. Dented.

          1. Not more than 0.125 in. (3.18 mm) by 1.00 in. (25.4 mm) radial length

          1. Accept

      4. Other surfaces.

        1. Nicked or dented.

          1. Not more than 0.008 in. (0.20 mm) in depth and 0.500 in. (12.70 mm) in length with no adjacent cracks

          1. Accept

          2. More than (a)

          1. Repair, VRS5389 TASK 72-50-53-300-005 (REPAIR-005)

        2. Strut airfoil damage that is more than (a), with no damage to the solid leading edges of instrumented struts

        1. Repair, VRS3743 TASK 72-50-53-300-083 (REPAIR-083)

    12. SUBTASK 72-50-53-220-065 Examine the Turbine Exhaust Case (01-001) Front Outer Flange at Location 12

    1. Refer to Figure.

      2. Front face at location 20.

        1. Worn

        1. Repair, VRS5397 TASK 72-50-53-300-013 (REPAIR-013)

        2. Cracked

          1. In the area above the horizontal centerline of the bolt holes

          1. Reject

      3. Inner diameter at location 19.

        1. Worn.

          1. Between 38.652 and 38.672 in. (981.77 and 982.28 mm) in diameter

          1. Accept

          2. More than 38.672 in. (982.28 mm)

          1. Repair, VRS5398 TASK 72-50-53-300-014 (REPAIR-014)

      4. Boltholes.

        1. Worn or elongated.

          1. Less than or equal to 0.330 in. (8.38 mm) in length

          1. Accept

          2. More than 0.330 in. (8.38 mm) in length

          1. Repair, VRS3804 TASK 72-50-53-300-087 (REPAIR-087) or Repair, VRS5399 TASK 72-50-53-300-015 (REPAIR-015)

    13. SUBTASK 72-50-53-220-066 Examine the Turbine Exhaust Case (01-001) Rear Outer Flange at Location 13

    1. Refer to Figure.

      2. Rear face at location 15.

        1. Parallelism.

          1. In 0.0098 in. (0.250 mm) FIR in relation to surface Z

          1. Accept

          2. More than (a)

          1. Repair, VRS5400 TASK 72-50-53-300-016 (REPAIR-016) or Repair, VR3732 TASK 72-50-53-300-078 (REPAIR-078).

        2. Worn

        1. Repair, VRS5400 TASK 72-50-53-300-016 (REPAIR-016) or Repair, VR3732 TASK 72-50-53-300-078 (REPAIR-078).

      3. Inner diameter at location 16.

        1. Worn.

          1. Between 33.0182 and 33.0236 in. (838.662 and 838.799 mm) in diameter

          1. Accept

          2. More than 33.0236 in. (838.799 mm)

          1. Repair, VRS3731 TASK 72-50-53-300-080 (REPAIR-080)

        2. Concentricity.

          1. In 0.016 in. (0.41 mm) FIR in relation to system W

          1. Accept

          2. More than (a)

          1. Repair, VRS3731 TASK 72-50-53-300-080 (REPAIR-080)

        3. Perpendicularity.

          1. In 0.002 in. (0.05 mm) FIR in relation to surface H

          1. Accept

          2. More than (a)

          1. Repair, VRS3731 TASK 72-50-53-300-080 (REPAIR-080)

    14. SUBTASK 72-50-53-220-067 Examine the Turbine Exhaust Case (01-001) Rear Inner Flange at Location 14

    1. Refer to Figure.

      2. Rear face at location 17.

        1. Wear or damage.

          1. Less than 0.035 in. (0.89 mm) in depth

          1. Repair, VRS5403 TASK 72-50-53-300-019 (REPAIR-019) or Repair, VRS3654 TASK 72-50-53-300-077 (REPAIR-077) or Repair, VRS3799 TASK 72-50-53-300-086 (REPAIR-086)

          2. More than 0.035 in. (0.89 mm) in depth

          1. Reject

      2. Parallelism.

        3. In 0.012 in. (0.30 mm) FIR in relation to surface Z

        1. Accept

        4. More than (a)

        1. Repair, VRS5403 TASK 72-50-53-300-019 (REPAIR-019) or Repair, VRS3654 TASK 72-50-53-300-077 (REPAIR-077)

    15. SUBTASK 72-50-53-220-068 Examine the Turbine Exhaust Case (01-001) Self Locking Shank Nut on Rear Inner Flange at Location 18

    1. Refer to Figure.

      2. Loose, not there or with internal thread damaged

      1. Repair, VRS5413 TASK 72-50-53-300-029 (REPAIR-029)

    16. SUBTASK 72-50-53-220-009 Examine the Turbine Exhaust Case (01-001) Thermal Blanket at Location 21

    1. Refer to Figure.

      2. Nicked or dented.

        1. All quantity, 0.125 in. (31.75 mm) deep or less, unless sharp edges, cracks or tears occur

        1. Accept

        2. More than 0.125 in. (31.73 mm) deep or with sharp edges, cracks or tears

        1. Repair, VRS5405, TASK 72-50-53-300-021 (REPAIR-021)

    17. SUBTASK 72-50-53-220-070 Examine the Turbine Exhaust Case (01-001) Cover Bore at Location 22

    1. Refer to Figure.

      2. Worn.

        1. Between 7.1936 and 7.1976 in. (182.718 and 182.818 mm) in diameter

        1. Accept

        2. More than 7.1976 in. (182.818 mm)

        1. Repair, VRS5406 TASK 72-50-53-300-022 (REPAIR-022)

    18. SUBTASK 72-50-53-220-071 Examine the Turbine Exhaust Case (01-001) Bearing Retainer Bore at Location 23

    1. Refer to Figure.

      2. Worn.

        1. Between 5.5906 and 5.5930 in. (142.000 and 142.063 mm) in diameter

        1. Accept

        2. More than 5.5930 in. (142.063 mm)

        1. Repair, VRS5407 TASK 72-50-53-300-023 (REPAIR-023)

      3. Concentricity.

        1. In 0.002 in. (0.05 mm) in relation to surface J

        1. Accept

        2. More than (1)

        1. Repair, VRS5407 TASK 72-50-53-300-023 (REPAIR-023)

    19. SUBTASK 72-50-53-220-072 Examine the Turbine Exhaust Case (01-001) Bearing Bore at Location 24

    1. Refer to Figure.

      2. Worn.

        1. Between 5.5209 and 5.5228 in. (140.232 and 140.278 mm) in diameter

        1. Accept

        2. More than 5.5228 in. (140.278 mm)

        1. Repair, VRS5408 TASK 72-50-53-300-024 (REPAIR-024)

      3. Runout.

        1. In 0.0059 in. (0.15 mm) FIR in relation to system W

        1. Accept

        2. More than (1)

        1. Repair, VRS5408 TASK 72-50-53-300-024 (REPAIR-024)

    20. SUBTASK 72-50-53-220-073 Examine the Turbine Exhaust Case (01-001) Bearing Shoulder at Location 25

    1. Refer to Figure.

      2. Perpendicularity.

        1. In 0.0020 in. (0.05 mm) FIR in relation to surface J

        1. Accept

        2. More than (1)

        1. Repair, VRS5409 TASK 72-50-53-300-025 (REPAIR-025)

    21. SUBTASK 72-50-53-220-074 Examine the Turbine Exhaust Case (01-001) Oil Seal Housing at Location 26

    1. Refer to Figure.

      2. Worn.

        1. Between 5.1969 and 5.1984 in. (132.000 and 132.040 mm) in diameter

        1. Accept

        2. More than 5.1984in. (132.040 mm)

        1. Repair, VRS5410 TASK 72-50-53-300-026 (REPAIR-026)

      3. Concentricity.

        1. In a diameter of 0.003 in. (0.07 mm) FIR in relation to surfaces X and Z

        1. Accept

        2. More than (1)

        1. Repair, VRS5410 TASK 72-50-53-300-026 (REPAIR-026)

    22. SUBTASK 72-50-53-220-075 Examine the Turbine Exhaust Case (01-001) Air Seal Housing at Location 27

    1. Refer to Figure.

      2. Worn.

        1. Between 5.5512 and 5.5551 in. (141.000 and 141.100 mm) in diameter

        1. Accept

        2. More than 5.5551 in. (141.100 mm)

        1. Repair, VRS5410 TASK 72-50-53-300-026 (REPAIR-026)

      3. Concentricity.

        1. In a diameter of 0.003 in. (0.07 mm) FIR in relation to surfaces X and Z

        1. Accept

        2. More than (1)

        1. Repair, VRS5410 TASK 72-50-53-300-026 (REPAIR-026)

      4. Nicked, dented or scratched at area A.

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

        1. Accept

        2. More than (1)

        1. Repair, VRS5410 TASK 72-50-53-300-026 (REPAIR-026)

      5. Grooved circumferentially at area B.

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

        1. Accept

        2. More than (1)

        1. Repair, VRS5410 TASK 72-50-53-300-026 (REPAIR-026)

      6. Raised material at area B

      1. Repair, VRS5410 TASK 72-50-53-300-026 (72-50-53 REPAIR 026)

    23. SUBTASK 72-50-53-220-076 Examine the Turbine Exhaust Case (01-001) Front Flange Locating Pin Hole at Location 28

    1. Refer to Figure.

      2. Worn.

        1. Between 0.2578 and 0.2589 in. (6.548 and 6.576 mm) in diameter

        1. Accept

        2. More than 0.2589 in. (6.576 mm)

        1. Repair, VRS5411 TASK 72-50-53-300-027 (REPAIR-027) or Repair, VRS3804 TASK 72-50-53-300-087 (REPAIR-087) or Repair, VRS5399 TASK 72-50-53-300-015 (REPAIR-015)

      3. True position.

        1. Within 0.004 in. (0.10 mm) diameter in relation to surface W

        1. Accept

        2. More than 0.004 in. (0.10 mm) diameter in relation to surface W

        1. Repair, VRS5411 TASK 72-50-53-300-027 (REPAIR-027) or Repair, VRS3804 TASK 72-50-53-300-087 (REPAIR-087) or Repair, VRS5399 TASK 72-50-53-300-015 (REPAIR-015)

    24. SUBTASK 72-50-53-220-077 Examine the Turbine Exhaust Case (01-001) Feed and Scavenge Oil Tubes Mating Surfaces at Location 29

    1. Refer to Figure.

      2. Worn.

        1. Not more than 0.001 in. (0.03 mm) in depth

        1. Accept

        2. More than (1)

        1. Repair, VRS5412 TASK 72-50-53-300-028 (REPAIR-028)

    25. SUBTASK 72-50-53-220-078 Examine the Turbine Exhaust Case (01-001) Oil Jet Mating Diameter at Location 30

    1. Refer to Figure.

      2. Worn.

        1. Between 0.5906 and 0.5916 in. (15.000 and 15.027 mm) in diameter

        1. Accept

        2. More than 0.5916 in. (15.027 mm) in diameter

        1. Repair, VRS5414 TASK 72-50-53-300-030 (REPAIR-030**)

    26. SUBTASK 72-50-53-220-079 Examine the Turbine Exhaust Case (01-001) Oil Transfer Tube Mating Diameter at Location 31

    1. Refer to Figure.

      2. Worn.

        1. Between 0.4724 and 0.4735 in. (12.000 and 12.027 mm) in diameter

        1. Accept

        2. More than 0.4735 in. (12.027 mm)

        1. Repair, VRS5415 TASK 72-50-53-300-031 (REPAIR-031**)

      3. True position.

        1. In a diameter of 0.010 in. (0.25 mm) FIR in relation to surface M

        1. Accept

        2. More than (1)

        1. Repair, VRS5415 TASK 72-50-53-300-031 (REPAIR-031**)

    27. SUBTASK 72-50-53-220-238 Examine the Turbine Exhaust Case (01-001) Feed and Scavenge Tube Mating Surfaces and Internal Passages for Coke or Blockages at Location 32

    1. Refer to Figure.

      2. Internal passages are clean, free from restrictions, blockages

      1. Accept

      3. Coke or carbon

      1. NOTE

        The nozzle, elbow and strainer need to be checked. They must be free of any loose coke or particles, which can block all nozzles in operation.

    28. SUBTASK 72-50-53-220-260 Examine the Turbine Exhaust Case P4.9 Probe Boss Threads and EGT Thermocouple Boss Threads

    1. Refer to Figure.

      2. Thread damage at the 3, 4, 6, 7, 8, 10 and 11 vane locations

      1. Repair, VRS3763 TASK 72-50-53-300-085 (REPAIR-085)

    29. SUBTASK 72-50-53-220-274 If You Remove the Instrumentation Bushing (02-140), Examine the Turbine Exhaust Case (02-300) Instrumentation Bushing Bore

    1. Refer to Figure.

      2. Examine the bore at Location 1 for the diameter

        1. Between 0.4330 and 0.4338 in. (10.998 and 11.018 mm)

        1. Accept

        2. More than 0.4338 in. (11.018 mm) and to a maximum of 0.4400 in. (11.176 mm)

        1. Repair, VRS3068 TASK 72-50-53-300-088 (Repair-088)

    30. Figure: Locations - Turbine Exhaust Case

    Sheet 1

    Legend
    Locations - Turbine Exhaust Case

    Sheet 1

    Close

    Figure: Locations - Turbine Exhaust Case

    Sheet 2

    Legend
    Locations - Turbine Exhaust Case

    Sheet 2

    Close

    Figure: Locations - Turbine Exhaust Case

    Sheet 3

    Legend
    Locations - Turbine Exhaust Case

    Sheet 3

    Close

    Figure: Locations - Turbine Exhaust Case

    Sheet 4

    Legend
    Locations - Turbine Exhaust Case

    Sheet 4

    Close

    Figure: Locations - Turbine Exhaust Case

    Sheet 5

    Legend
    Locations - Turbine Exhaust Case

    Sheet 5

    Close

    Figure: Locations - Turbine Exhaust Case

    Sheet 6

    Legend
    Locations - Turbine Exhaust Case

    Sheet 6

    Close

    Figure: P4.9 Probe Boss and EGT Thermocouple Boss Locations Turbine Exhaust Case

    Sheet 7

    Legend
    P4.9 Probe Boss and EGT Thermocouple Boss Locations Turbine Exhaust Case

    Sheet 7

    Close

    Figure: Turbine Exhaust Case - Crack Inspection

    Turbine Exhaust Case - Crack Inspection

    Figure: Turbine Exhaust Case - Leading Edge Weld Area Inspection Location

    Turbine Exhaust Case - Leading Edge Weld Area Inspection Location

    Figure: Turbine Exhaust Case Instrumentation Bushing Bore Inspection Location

    Turbine Exhaust Case Instrumentation Bushing Bore Inspection Location

    Figure: Turbine Exhaust Case - Alternate Datum

    Turbine Exhaust Case - Alternate Datum

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Correct step reference and link (CAS-54967-K1H4L5)

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:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:X333X
Enterprise Name:REFER TO V2500 SB ENG-79-0108
Manufacturer Code:X333X
Supply Number:CoMat 10-077
Type:sp01
Supply Short Name:CoMat 10-077 APPROVED ENGINE OILS
Supply Name:CoMat 10-077 APPROVED ENGINE OILS
Specification Groups:
Doc NumberType
For V2500-A1/A5/D5 models - Refer to V2500 Service Bulletin ENG-79-0108
For V2500-E5 model - Refer to Service Bulletin E5-79-0001
Suppliers:
ManufacturerRemarks
X333X
Manufacturer Code:LOCAL
Tool Number:Hydraulic test pump
Tool Name:Hydraulic test pump
Manufacturer Code:0AM53
Tool Number:IAE 2F10183
Tool Name:IAE 2F10183 Fixture
Manufacturer Code:0AM53
Tool Number:IAE 2F10330
Tool Name:IAE 2F10330 Adapter,leak test Scavenge tube
Manufacturer Code:0AM53
Tool Number:IAE 2F10331
Tool Name:IAE 2F10331 Plug
Manufacturer Code:0AM53
Tool Number:IAE 2F10332
Tool Name:IAE 2F10332 Bracket
Manufacturer Code:0AM53
Tool Number:IAE 6F10029
Tool Name:IAE 6F10029 Air flow test cart
Manufacturer Code:0AM53
Tool Number:IAE 6F10056
Tool Name:IAE 6F10056 Borescope equipment, 4 mm or 6 mm, video borescope
Manufacturer Code:0AM53
Tool Number:Workshop Inspection Equipment
Tool Name:Workshop Inspection Equipment