TASK 72-00-32-220-002-A00 LPC/Intermediate Case Module - Examine The Module Outer At Interface B-32, Inspection-002

DMC:V2500-A0-72-00-3200-01B-310A-B|Issue No:001.00|Issue Date:2014-05-01

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

All

Common Information

TASK 72-00-32-220-002-A00 LPC/Intermediate Case Module - Examine The Module Outer At Interface B-32, Inspection-002

General

This TASK is for A1 Engine.

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/Subject 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 (Examine the modular/non-modular interfaces) (INSPECTION/CHECK-000), before you do this TASK.

The policy that is necessary for inspection is given in the SPM TASK 70-20-01-200-501.

NOTE

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

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
IAE 2J13056 Gage, wear0AM53IAE 2J130561

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-32-220-056 Visually Examine the Airfoils of the Fan Outer Outlet Guide Vane at Location 1

    1. Refer to Figure.

      2. Cracked

      1. Reject

        2. Nicked or scratched.

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

          1. Accept

          2. More than Step

          1. Reject

        3. Dented (round bottom).

          1. Not more than 0.010 in. (0.25 mm) in depth

          1. Accept

          2. More than Step

          1. Reject

        4. Missing anodized coating.

          1. Not more than 4.6 sq in. (2967.736 sq mm)

          1. Accept

          2. More than in Step

          1. Reject

    2. SUBTASK 72-00-32-220-057 Visually Examine the Attrition Honeycomb and Filler at Location 2

    1. Refer to Figure and Figure.

      2. Blade tip rub, use IAE 2J13056 Gage, wear 1 off.

        1. Less than a depth of 0.100 in. (2.54 mm) all round compressor (fan) blade rotor path lining

        1. Accept

        2. More than limits Step

        1. Reject

      3. Circumferential scores.

        1. Circumferential scores of any length if they do not run in to front or rear edges of linings around them is sound

        1. Accept

        2. More than Step

        1. Reject

      4. Damage other than A. and B.

      1. Reject

    3. SUBTASK 72-00-32-220-058 Visually Examine the Front Acoustic Skin at Location 3

    1. Refer to Figure.

      2. Damaged

      1. Reject

    4. SUBTASK 72-00-32-220-071 Visually Examine the Rear Acoustic Skin at Location 4

    1. Refer to Figure.

      2. Damaged

      1. Reject

    5. SUBTASK 72-00-32-220-072 Visually Examine the Ice Impact Resistance Skin at Location 5

    1. Refer to Figure.

      2. Damaged

      1. Reject

    6. SUBTASK 72-00-32-220-073 Visually Examine the Acoustic Lining Assembly at Location 6

    1. Refer to Figure.

      2. Damaged

      1. Reject

    7. SUBTASK 72-00-32-220-074 Visually Examine the Fan Case Front Flange at Location 7

    1. Refer to Figure.

      2. Burred

      1. Reject

    8. Figure: Locations at interface B-32

    Locations at interface B-32

    Figure: Inspection tool of attrition lining

    Inspection tool of attrition lining

Requirements After Job Completion

Follow-On Conditions

NONE
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 2J13056
Tool Name:IAE 2J13056 Gage, wear