TASK 73-22-34-200-402 EEC And Terminal Block Assembly - Related Parts - Examine The Electronic Engine Control (EEC) Brackets, Inspection-002

DMC:V2500-A0-73-22-3400-01A-310A-C|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 73-22-34-200-402 EEC And Terminal Block Assembly - Related Parts - Examine The Electronic Engine Control (EEC) Brackets, Inspection-002

Effectivity

FIG/ITEM

PART NO.

01-420

5A0024

01-440

5A0023

01-500

5W1985

01-520

5W8512

General

Refer to Inspection-000 TASK 73-22-34-200-300 for the other EEC parts.

Fig/item numbers in parentheses in the procedure agree with those used in the IPC. Only the primary Fig/item numbers are used. For the service bulletin alpha variants refer to the IPC.

All the parts must be cleaned before they are examined. Refer to Cleaning-000 TASK 73-22-34-100-300.

All the parts must be visually examined for damage, corrosion and wear. 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 relevant SUBTASK. Do the crack test before the part is visually examined.

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 the part until you are sure there are not repairs available. Refer to the instructions in Repair before a discarded part is used again or oversize parts are installed.

Parts which must 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 the 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/SUBTASK number 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 Policy and 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 73-22-34-220-052 Examine the Brackets (01-420, 01-440, 01-500 and 01-520) for Cracks

      1. Examine all the surface for cracks

        1. Cracked

        1. Reject

    2. SUBTASK 73-22-34-220-053 Examine the Surface of the Brackets (01-420, 01-440, 01-500 and 01-520)

      1. Examine all the surface

        1. Nicked

          1. Nicked to depth of 0.002 in (0.05 mm)

          1. Accept

          2. More than in Step.

          1. Repair, VRS6417 (Repair-009) 73-22-34-300-009**.

        2. Dented

          1. Dented to a depth of 0.150 in. (3.8 mm) with a large surface area.

          1. Accept

          2. More than in Step.

          1. Reject

        3. Scratched

          1. Scratched to depth of 0.002 in (0.05 mm)

          1. Accept

          2. More than in Step.

          1. Repair, VRS6417 (Repair-009) 73-22-34-300-009**.

    3. SUBTASK 73-22-34-220-054 Examine the Brackets (01-420, 01-440, 01-500 and 01-520) Bolt Hole

      1. Bolt hole burred

      1. Repair, VRS6417 (Repair-009) 73-22-34-300-009**.

      2. Examine the clip position bolt hole

        1. Worn

          1. If the hole diameter is between 0.221 in. (5.60 mm) and 0.279 in. (7.08 mm) with the distance between the edge of the worn hole and the bracket more than 0.077 in. (1.95 mm).

          1. Accept

          2. Other than in Step.

          1. Reject

      3. Examine the mounting flange bolt hole (01-420, 01-440 and 01-500)

        1. Worn

          1. If the hole diameter is between 0.284 in. (7.20 mm) and 0.357 in. (9.07 mm) with the distance between the edge of the worn hole and the bracket more than 0.097 in. (2.47 mm).

          1. Accept

          2. Other than in Step.

          1. Reject

      4. Examine the mounting flange bolt hole (01-520)

        1. Worn

          1. If the hole diameter is between 0.284 in. (7.20 mm) and 0.357 in. (9.07 mm) with the distance between the edge of the worn hole and the bracket more than 0.137 in. (3.47 mm).

          1. Reject

          2. Other than in Step.

          1. Reject

Requirements After Job Completion

Follow-On Conditions

NONE