TASK 72-44-30-200-001-A00 Inner Combustion Chamber Assembly - Examine, Inspection-001

DMC:V2500-A0-72-44-3000-00A-310A-C|Issue No:003.00|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 72-44-30-200-001-A00 Inner Combustion Chamber Assembly - Examine, Inspection-001

Effectivity

FIG/ITEM PART NO.

01-401

2A1374

General

This TASK gives the procedure for the inspection of the combustion chamber inner liner. For the other part of the combustion chamber inner liner, refer to TASK 72-44-30-200-000 (INSPECTION-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 SPM TASK 70-20-00-200-501.

All the parts must be cleaned before any part is examined. Refer to SPM TASK 70-10-00-100-501.

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.

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 SPM.

Use a bright light and a 3X magnifying glass to find surface cracks.

References

Refer to SPM for data on these items.

Definitions of Damage, SPM TASK 70-02-02-350-501.

Inspection of Parts, SPM TASK 70-20-01-200-501.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-44-30-220-051 Examine the Combustion Chamber Inner Liner (01-401) for Cracks, Holes, Burns and Distortion in the Liner Segments

    1. Refer to Figure.

      2. Examine the inner liner for cracks, holes, burns and distortion in the liner segments, rows 1 thru 5.

        1. Cracks.

          1. Any amount of cracks. The cracks are not longer than 0.050 in. (1.27 mm) on the trailing edge at location 1

          1. Accept

          2. Other than (a)

          1. Repair, VRS3173 TASK 72-44-30-300-001 (REPAIR-001)

        2. Holes

        1. Repair, VRS3173 TASK 72-44-30-300-001 (REPAIR-001)

        3. Burns.

          1. The burns are no more than 0.100 in. (2.54 mm) (location 2) from the trailing edge. An axial burn on the trailing edge is no more than 0.015 in. (0.381 mm) in depth. Surface burns in location 2 are no more than 0.015 in. (0.381 mm) in depth

          1. Accept

          2. Other than (a)

          1. Repair, VRS3173 TASK 72-44-30-300-001 (REPAIR-001)

        4. Distortion.

          1. The clearance under the cooling pins at location 3 is a maximum of 0.050 in. (1.27 mm). Circumferentially adjacent segments at location 4 are not aligned by a maximum of 0.050 in. (1.27 mm)

          1. Accept

          2. Other than (a)

          1. Repair, VRS3173 TASK 72-44-30-300-001 (REPAIR-001)

    2. SUBTASK 72-44-30-220-052 Examine the Combustion Chamber Inner Liner (01-401) for Wear that is Not Smooth on the Rear Flange-to-Vane Platform Seal Face

    1. Refer to Figure.

      2. Examine the inner liner shell at location 5 for wear that is not smooth on the rear flange-to-vane platform seal face.

        1. Wear that is not smooth.

          1. If the wear at the vane contact points is a maximum of 0.010 in. (0.25 mm) in depth

          1. Accept

          2. If the wear at the vane contact points is a maximum of 0.020 in. (0.51 mm) in depth

          1. Repair, VRS3265 TASK 72-44-30-300-002 (REPAIR-002)

          3. If the wear at the vane contact points is a maximum of 0.030 in. (0.76 mm) in depth

          1. Repair, VRS3813 TASK 72-44-30-300-021 (72-4-30, REPAIR 021)

          4. Other than (a), (b) or (c)

          1. Reject

    3. SUBTASK 72-44-30-220-053 Examine the Combustion Chamber Inner Liner (01-401) Nut Channel for Nuts that are Not There, Cracks and Pieces that are Broken Away

    1. Refer to Figure.

      2. Examine the inner liner nut channel at location 6 for nuts that are not there, cracks and pieces that are broken away.

        1. Nuts that are not there, cracks or pieces that are broken away

        1. Repair, VRS3264 V2500-A0-72-44-3001-00A-920A-C (REPAIR-003)

    4. SUBTASK 72-44-30-220-054 Examine the Combustion Chamber Inner Liner (01-401) for Wear and Chipped or Spalled Hardface and for Hole Cracks on the Rear Mount Flange

    1. Refer to Figure.

      2. Examine the inner liner at location 7 for wear and chipped or spalled hardface on the rear mount flange.

        1. Wear.

          1. If the base metal does not show

          1. Accept

          2. Other than (a)

          1. Repair, VRS3170 TASK 72-44-30-300-004 (REPAIR-004)

        2. Chipped or spalled hardface.

          1. If the area of chipped or spalled hardface is not more than 10 percent of the total coated area. The area of chipped or spalled hardface must not be more than 10 percent of the axial width of the coated area

          1. Accept

          2. Other than (a)

          1. Repair, VRS3170 TASK 72-44-30-300-004 (REPAIR-004)

      3. Examine the inner liner for hole cracks on the rear mount flange.

        1. Cracks.

          1. If the hole cracks go from the flange hole to the outside diameter of the flange

          1. Repair, VRS3741 TASK 72-44-30-300-019 (REPAIR-019)

          2. Other than (a)

          1. Reject

    5. SUBTASK 72-44-30-220-055 Examine the Combustion Chamber Inner Liner (01-401) for Nuts that are Not There

    1. Refer to Figure.

      2. Examine the inner liner at location 8 for nuts that are not there.

        1. Nuts that are not there

        1. Repair, VRS3173 TASK 72-44-30-300-001 (REPAIR-001)

    6. SUBTASK 72-44-30-220-056 Examine the Combustion Chamber Inner Liner (01-401) for Loose, Oval-Shaped Washers

    1. Refer to Figure.

      2. Examine the inner liner at location 9 for loose, oval-shaped washers.

        1. Loose washers

        1. Replace washers by Repair, VRS3173 TASK 72-44-30-300-001 (REPAIR-001)

    7. SUBTASK 72-44-30-220-057 Examine the Combustion Chamber Inner Liner (01-401) for Cracks, Dents, Burn Holes and Blocked Holes

    1. Refer to Figure.

      2. Examine the inner liner at location 11 for cracks, dents, burn holes and blocked holes.

        1. Cracks.

        1. Repair, VRS3174 TASK 72-44-30-300-005 (REPAIR-005).

        2. Dents.

          3. Less than 0.010 in. (0.25 mm) in depth and 1.0 sqin (645.16 sqmm) in area.

          1. Accept.

          4. Other than Step.

          1. Repair, VRS3174 TASK 72-44-30-300-005 (REPAIR-005).

        2. Burn holes.

        1. Repair, VRS3174 TASK 72-44-30-300-005 (REPAIR-005).

        3. Blocked holes.

        1. Reject.

      3. Examine the inner liner at Location 14 for cracks on the shell.

        1. Axial cracks not more than 0.100 in. (2.54 mm) long that are at least 0.250 in. (6.35 mm) apart.

        1. Accept.

        2. Axial cracks on the trailing edge of Row 5 that are not more than 0.125 in. (3.175 mm) long that are at least 0.100 in. (2.540 mm) apart, or look like they will go through each other and permit material to break off.

        1. Repair, VRS3745 TASK 72-44-30-300-020 (REPAIR-020).

        3. Other than Step and Step.

        1. Reject.

      4. Examine the inner liner at Location 15 for cracks on the rear flange.

        1. Cracks which extend from the boltholes.

        1. Repair, VRS3745 TASK 72-44-30-300-020 (REPAIR-020).

        2. Other than Step.

        1. Reject.

      5. Examine the inner liner at Location 16 for cracks on the outer shell.

        1. Axial cracks not more than 0.100 in. (2.54 mm) long that are at least 0.250 in. (6.35 mm) apart.

        1. Accept.

        2. Axial cracks on the trailing edge of Row 5 that are not more than 0.125 in. (3.175 mm) long that are at least 0.100 in. (2.540 mm) apart, or look like they will go through each other and permit material to break off.

        1. Repair, VRS3745 TASK 72-44-30-300-020 (REPAIR-020).

        3. Other than Step and Step.

        1. Reject.

    8. SUBTASK 72-44-30-220-058 Examine the Combustion Chamber Inner Liner (01-401) for Wear and Chipped or Spalled Hardface on the Front Outside Diameter Seal

    1. Refer to Figure.

      2. Examine the inner liner at location 12, for wear and chipped or spalled hardface on the front outside diameter seal.

        1. Wear.

          1. If the base metal does not show.

          1. Accept.

          2. Other than (a).

          1. Repair, VRS3169 TASK 72-44-30-300-007 (REPAIR-007).

        2. Chipped or spalled hardface.

          1. If the area of chipped or spalled hardface is not more than 10 percent of the total coated area. The area of chipped or spalled hardface must not be more than 10 percent of the axial width of the coated area.

          1. Accept.

          2. Other than (a).

          1. Repair, VRS3169 TASK 72-44-30-300-007 (REPAIR-007).

    9. SUBTASK 72-44-30-220-059 Examine the Combustion Chamber Inner Liner (01-401) for the Length

    1. Refer to Figure.

      2. Examine the inner liner at location 1 for the length.

        1. Length.

          1. If the length is between 9.030 and 9.135 in. (229.362 and 232.029 mm)

          1. Accept

          2. Other than (a)

          1. Reject

    10. SUBTASK 72-44-30-220-060 Examine the Combustion Chamber Inner Liner (01-401) for the Axial Dimension of the Rear Support and Thickness of the Rear Mount Flange

    1. Refer to Figure.

      2. Examine the inner liner for the axial dimension of the rear support at location 2004.

        1. Axial dimension.

          1. If the axial dimension is between 0.830 and 0.845 in. (21.08 and 21.46 mm)

          1. Accept

          2. Other than (a)

          1. Repair, VRS3265 TASK 72-44-30-300-002 (REPAIR-002) or Repair, VRS3813 TASK 72-44-30-300-021 (REPAIR-021)

      3. Examine the inner liner for the thickness of the rear mount flange (Reference No. 2300).

        1. If the thickness is equal or more than 0.156 in. (3.96 mm)

        1. Accept

        2. If the thickness is less than 0.156 in. (3.96 mm) and equal or more than 0.140 in. (3.56 mm)

        1. Repair, VRS3170 TASK 72-44-30-300-004 (REPAIR-004)

    11. SUBTASK 72-44-30-220-061 Examine the Combustion Chamber Inner Liner (01-401) for the Rear Inside Diameter

    1. Refer to Figure.

      2. Examine the inner liner at location 3 for the rear inside diameter (Reference No. 2000).

        1. Diameter.

          1. If the diameter is between 19.392 in. (492.557 mm) and 19.400 in. (492.76 mm)

          1. Accept

          2. More than 19.400 in. (492.760 mm)

          1. Repair, VRS3266 TASK 72-44-30-300-008 (REPAIR-008)

          3. Less than 19.392 in. (492.557 mm)

          1. Repair, VRS3628 TASK 72-44-30-300-017 (REPAIR-017)

    12. SUBTASK 72-44-30-220-062 Examine the Combustion Chamber Inner Liner (01-401) Front Outside Diameter Seal for the Diameter and Out-of-Roundness

    1. Refer to Figure.

      2. Examine the inner liner at location 4 for the diameter of the front outside diameter seal (Reference No. 2265).

        1. If the diameter is between 16.619 and 16.631 in. (422.12 and 422.43 mm)

        1. Accept

        2. Write down the dimension of the diameter.

        2. If the diameter is between 16.616 and 16.618 in. (422.05 and 422.10 mm)

        1. Accept part for select fit only

          NOTE

          This part can be used only if the mating part has a diameter that will result in fit of reference No. 2265. Refer to TASK 72-00-44-420-001-001 (INSTALLATION-001) or TASK 72-40-00-430-005 (ASSEMBLY-005).

        2. Write down the dimension of the diameter.

        3. Other than (1) or (2)

        1. Repair, VRS3306 TASK 72-44-30-300-009 (REPAIR-009)

      3. Examine the inner liner at location 4 for the out-of-roundness of the front outside diameter seal.

        1. Out-of-roundness.

          1. If the out-of-roundness is not more than 0.120 in. (3.05 mm)

          1. Accept

          2. Other than (a)

          1. Repair, VRS3306 TASK 72-44-30-300-009 (REPAIR-009)

    13. Figure: Combustion Chamber Inner Liner Inspection Locations

    Combustion Chamber Inner Liner Inspection Locations

    Figure: Combustion Chamber Inner Liner Inspection Locations

    Combustion Chamber Inner Liner Inspection Locations

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised steps. (17VC582)