TASK 72-38-11-200-002-A00 Inlet Cone Assembly - Examine, Inspection-002

DMC:V2500-A0-72-38-1101-01A-310A-C|Issue No:002.00|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 72-38-11-200-002-A00 Inlet Cone Assembly - Examine, Inspection-002

Effectivity

FIG/ITEM

PART NO.

01-200

5A0015

General

This TASK gives the procedure for the inspection of the inlet cone.

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 SPM TASK 72-38-11-100-000 (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.

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.

A** following 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 date.

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

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

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

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-38-11-220-064 Examine the Inlet Cone Outer Surface

    1. Refer to Figure.

      2. Examine the outer surface at Location 1.

        1. Eroded.

          1. Erosion of polyurethane coating

          1. Accept

          2. Varnish coating colored gray

          1. Repair, VRS1466 TASK 72-38-11-300-001 (REPAIR-001)

          3. Varnish coating colored black with white spiral mark

          1. Repair VRS1458 TASK 72-38-11-300-010 (Repair-010)

        2. Scored, gouged or grooved.

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

          1. Accept

          2. More than in Step

          1. Reject

        3. Cracked

        1. Reject

        4. Delaminated

        1. Reject

        5. Missing coating (polyurethane and/or varnish coating).

          1. Not more than 0.315 sqin. (2.03 sqcm) per missing coating area and within five places

          1. Repair, VRS1473 TASK 72-38-11-300-008 (Repair-008)

          2. More than in Step

          1. Repair, VRS1458 TASK 72-38-11-300-010 (Repair-010) or VRS1466 TASK 72-38-11-300-001 (Repair-001)

      3. Examine the outer surface at Location 8.

        1. Scored.

          1. Not more than 0.005 in. (0.12 mm) in depth

          1. Accept

        2. Cracked

        1. Reject

        3. Delaminated.

          1. Around pin holes.

          1. Repair, VRS1461 TASK 72-38-11-300-015 (REPAIR-015).

          2. Around bolt holes.

            1. Not more than 0.019 in. (0.50 mm) in depth within the area not more than 0.19 in. (5.0 mm) from the hole edge.

            1. Accept.

            2. More than in Step.

            1. Reject.

          3. Flange edge.

            1. Not more than 0.078 in. (2.00 mm) in depth, not more than 0.31 in. (8.00 mm) in radial width and not extended into the area within 0.083 in. (2.1 mm) from the hole edge.

            1. Repair, VRS1507 TASK 72-38-11-300-016 (REPAIR-016).

            2. More than in Step.

            1. Reject.

          4. Any other area of Step, Step and Step.

          1. Reject.

        4. Missing laminate layer or chipped.

          1. Around bolt holes.

            1. Not more than ten percent of each washer seat surface.

            1. Accept.

            2. More than in Step.

            1. Reject.

          2. Any other area of Step.

          1. Reject.

    2. SUBTASK 72-38-11-220-065 Examine the Inlet Cone Inner Surface

    1. Refer to Figure.

      2. Examine the inner surface at Location 2.

        1. Cracked

        1. Reject

        2. Delaminated

        1. Reject

    3. SUBTASK 72-38-11-220-066 Examine the Inlet Cone Tip

    1. Refer to Figure.

      2. Examine the tip at Location 3.

        1. Missing

        1. Repair, VRS1462 TASK 72-38-11-300-002 (REPAIR-002)

        2. Loss of bond securing tip

        1. Repair, VRS1462 TASK 72-38-11-300-002 (REPAIR-002)

        3. Tip securely bonded to inlet cone with filler missing

        1. Repair, VRS1462 TASK 72-38-11-300-002 (REPAIR-002)

    4. SUBTASK 72-38-11-220-067 Examine the Inlet Cone Rear Face

    1. Refer to Figure.

      2. Examine the segment face at Location 4.

        1. Cracked.

        1. Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

        2. Galled.

          1. Up to 0.003 in. (0.07 mm) in depth.

          1. Accept.

          2. More than in Step.

          1. NOTE

            Repair using Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017) if the damage cannot be removed by Repair, VRS1701 TASK 72-38-11-300-018 (REPAIR-018).

            Repair, VRS1701 TASK 72-38-11-300-018 (REPAIR-018), Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

      3. Examine the flange rear face at Location 12.

        1. Delaminated.

          1. Not more than 0.078 in. (2.00 mm) in depth, not more than 0.31 in. (8.00 mm) in radial width and provided that the area where the segment is not attached.

          1. Repair, VRS1507 TASK 72-38-11-300-016 (REPAIR-016).

          2. More than in Step.

          1. Reject.

    5. SUBTASK 72-38-11-220-068 Examine the Inlet Cone Snap Diameter

    1. Refer to Figure.

      2. Examine the snap diameter at Location 5.

        1. Scored.

          1. Not more than 0.003 in. (0.07 mm) in depth.

          1. Accept.

          2. More than in Step

          1. Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

        2. Worn.

          1. If the average snap diameter measured at 8 equally spaced positions is between 14.2914 in. and 14.2992 in. (363.000 and 363.201 mm).

          1. Accept.

          2. If the average snap diameter measured at 8 equally spaced positions is more than 14.2992 in. (363.201 mm).

          1. Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

    6. SUBTASK 72-38-11-220-069 Examine the Inlet Cone Bolt Holes

    1. Refer to Figure.

      2. Examine the bolt holes at Location 6.

        1. Damaged (thread marks and scratches).

          1. Up to 0.005 in. (0.12 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        2. Cracked (bore and around of the holes)

        1. Reject

    7. SUBTASK 72-38-11-220-070 Examine the Inlet Cone Dowel Pin

    1. Refer to Figure.

      2. Examine the dowel pin at Location 7.

        1. Missing or loose.

        1. Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

        2. Distorted.

        1. Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

    8. SUBTASK 72-38-11-220-071 Examine the Inlet Cone Balance Weight

    1. Refer to Figure.

      2. Examine the balance weights at Location 9.

        1. Glass fabric delaminated

        1. Repair, VRS1464 TASK 72-38-11-300-005 (REPAIR-005)

        2. Balance weights disengaged

        1. Repair, VRS1464 TASK 72-38-11-300-005 (REPAIR-005)

    9. SUBTASK 72-38-11-220-085 Examine the Inlet Cone Mounting Flange

    1. Refer to Figure.

      2. Examine the mounting flange at Location 10.

        1. Unbonded.

        1. Repair, VRS1467 TASK 72-38-11-300-003 (REPAIR-003) or Repair, VRS1617 TASK 72-38-11-300-017 (REPAIR-017).

    10. SUBTASK 72-38-11-220-174 Examine the Fairing Mating Surface Around Six Bolt Holes Adjacent to the Dowel Pins

    1. Refer to Figure.

      2. Examine the fairing mating surface at location 11.

        1. Depression.

          1. Any amount.

          1. Repair, VRS1431 TASK 72-38-11-300-013 (REPAIR-013).

    11. Figure: Locations On The Inlet Cone

    Locations On The Inlet Cone

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure to update inspection criteria and figure. (87VJ283N)