TASK 72-60-21-200-001 Crank Cover - Examine The Crank Cover, Inspection-001

DMC:V2500-A0-72-60-2102-00A-300A-C|Issue No:001.00|Issue Date:2013-11-01

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

All

Common Information

TASK 72-60-21-200-001 Crank Cover - Examine The Crank Cover, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-220

4P0084

General

This TASK gives the procedure for the inspection of the crank cover. For the other parts of the main gearbox case and fittings, refer to TASK 72-60-21-200-000 (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.

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 the SPM TASK 70-23-00-230-501. Do the test before the part is visually examined. Limits for cracks are given in the SUBTASK for each part.

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.

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.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-60-21-220-052 Dimensional Inspection of the Cover Crank Drive

    1. Refer to Figure.

      2. Mating seat diameter at location 1.

        1. Diameter.

          1. Between 1.3780 and 1.3740 in. (35.0 and 34.9 mm)

          1. Accept

          2. Between 1.3740 and 1.3701 in. (34.9 and 34.8 mm)

          1. Repair, VRS5016 TASK 72-60-21-300-001 (REPAIR-001)**

          3. Less than Step

          1. Reject

    2. SUBTASK 72-60-21-230-051 Penetrant Inspection of the Crank Cover

    1. Refer to Figure.

      2. Cover.

        1. Do the fluorescent penetrant test. Refer to TASK 70-23-01-230-501.

          1. Cracked

          1. Reject

          2. Through porosity

          1. Reject

    3. Figure: Location - Crank Cover

    Location - Crank Cover

Requirements After Job Completion

Follow-On Conditions

NONE