TASK 72-00-42-220-004 Combustion System - Examine The Outer Combustion Chamber Assembly Rear Face at Interface K-42/60, Inspection-004

DMC:V2500-A0-72-00-4200-00A-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 72-00-42-220-004 Combustion System - Examine The Outer Combustion Chamber Assembly Rear Face at Interface K-42/60, Inspection-004

General

The word 'reject' after an interface inspection statement requires that further detailed inspection or repair as applicable, of the affected area be accomplished using data in the applicable ATA section of the part in question. Contact IAE for FAA approved data if the referenced TASK is not in the manual.

Refer to TASK 72-00-00-200-001 (examine the modular/non-modular interfaces) before you do this TASK.

The policy that is necessary for inspection is given in the SPM TASK 70-20-01-200-001.

You can do the inspections that follow if the stage 1 turbine nozzle assembly is removed (Refer to TASK 72-00-44-020-001-001).

Installation of modules that are near the maximum interface limits can result in decreased module run times.

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

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-42-220-078 Visually Examine the Segment Nuts and Washers of the Outer Combustion Chamber Assembly at Location 1

    1. Refer to Figure.

      2. Nuts that are not there or loose washers

      1. Reject

    2. SUBTASK 72-00-42-220-079 Visually Examine the Shell of the Outer Combustion Chamber Assembly that you can see at Location 2

    1. Refer to Figure.

      2. Dents less than 0.010 in. (0.254 mm) deep and 1.000 sq in. (645.000 sq mm) in area

      1. Accept

      3. Burn holes, cracks or blocked holes

      1. Reject

    3. SUBTASK 72-00-42-220-080 Visually Examine the Rear Outside Diameter Seal of the Outer Combustion Chamber Assembly at Location 3

    1. Refer to Figure.

      2. Local wear if the base metal does not show. If base metal does show, it must be less than 20 percent of the total coated area and less than 20 percent of the axial width of the coated area

      1. Accept

      3. Chipped or spalled hardface is less than 20 percent of the total coated area. Chipped or spalled hardface must be less than 20 percent of the width of the coated area

      1. Accept

      4. Other than Step or Step

      1. Reject

    4. SUBTASK 72-00-42-220-081 Visually Examine the Combustion Chamber Liner Segments at Location 4

    1. Refer to Figure.

      2. There are segment cracks less than 1.000 in. (25.40 mm). All cracks must be more than 0.700 in. (17.78 mm) from a circumferential edge

      1. Accept

      3. There is edge burnback less than 0.400 in. (10.16 mm) in row 1 or less than 0.200 in. (5.08 mm) in rows 2, 3, 4 or 5. There can be no damage to the rails around the igniter holes in the igniter segment or no attachment post can be seen

      1. Accept

      4. There is no limit to surface burns

      1. Accept

      5. There are up to three burn holes on outer combustion chamber liner assembly that are less than 0.200 in. (5.08 mm) long. There can be only one burn hole on a segment, no damage to the rails around the igniter holes in the igniter segment, no combustion hole damage or no attachment post can be seen

      1. Accept

      6. There is spalled, chipped or cracked ceramic coating

      1. Accept

      7. There is a combustion chamber segment that has cracks and/or burns that can possibly cause a piece of segment metal more than 0.500 in. (12.70 mm) long to break off

      1. Reject

      8. Other than Step, Step, Step, Step, or Step

      1. Reject

    5. SUBTASK 72-00-42-220-082 Visually Examine the Fuel Nozzles at Location 5

    1. Refer to Figure.

      2. All fuel nozzle end cap cracks or burns

      1. Accept

      3. Damage other than Step

      1. Reject

    6. SUBTASK 72-00-42-220-084 Visually Examine the Fuel Nozzle Guide Deflectors at Location 6

    1. Refer to Figure.

      2. Spalled, chipped or surface burns in ceramic coat

      1. Accept

      3. Any length cracks that do not intersect or look like they will intersect

      1. Accept

      4. Burnback of the outside edge diameter of less than 0.150 in. (3.81 mm)

      1. Accept

      5. Other than Step, Step or Step

      1. Reject

    7. SUBTASK 72-00-42-220-085 Visually Examine the Liner (Bulkhead) Segments at Location 7

    1. Refer to Figure.

      2. There are cracks less than 0.100 in. (2.540 mm)

      1. Accept

      3. There are cracks up to 0.500 in. (12.700 mm) long that are at least 90 degrees apart. Cracks can not go through each other or be possible for this to occur

      1. Accept

      4. There is no limit of surface burns

      1. Accept

      5. There is a maximum of two segments that have one burn hole up to 0.200 in. (5.080 mm) long. One burn hole for each segment maximum

      1. Accept

      6. There is a bulkhead segment that has cracks and/or burns that can possibly cause a piece of segment metal more than 0.500 in. (12.700 mm) long to break off

      1. Reject

      7. Other than Step, Step, Step or Step

      1. Reject

    8. SUBTASK 72-00-42-220-086 Visually Examine the Front Inside Diameter Seal of the Outer Combustion Chamber Assembly at Location 8

    1. Refer to Figure.

      2. Local wear if the base metal does not show. If base metal does show, it must be less than 20 percent of the total coated area and less than 20 percent of the axial width of the coated area

      1. Accept

      3. Chipped or spalled hardface is less than 20 percent of the total coated area. Chipped or spalled hardface must be less than 20 percent of the width of the coated area

      1. Accept

      4. Other than Step or Step

      1. Reject

    9. Figure: Locations at Interface K-42/60

    Locations at Interface K-42/60

Requirements After Job Completion

Follow-On Conditions

NONE