TASK 72-50-53-300-074 Turbine Exhaust Case (TEC) - Repair A Crack On The Strut Trailing Edge, Repair-074 (VRS3641)

DMC:V2500-A0-72-50-5301-02A-627A-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 72-50-53-300-074 Turbine Exhaust Case (TEC) - Repair A Crack On The Strut Trailing Edge, Repair-074 (VRS3641)

Effectivity

FIG/ITEM

PART NO.

21-300

2A2620-01

21-300

2A3111-01

21-300

2A3183-01

21-300

2A1209-01

21-300

2A3183-101

21-300

2A3455-01

21-300

2A4258-01

21-300

2A4263-01

Material of component

PART IDENT

SYMBOL

MATERIAL

Turbine exhaust case

AMS 5616 Stainless steel

Trailing edge strip

AMS 5808 Stainless steel

General

If necessary, remove any tubing, mount rail bushings or nut-plate detail parts that may be affected by welding or heat treatment.

NOTE

To identify the consumable materials, refer to the PCI

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Grinding equipmentLOCALGrinding equipment
Routing equipmentLOCALRouting equipment

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 06-064 FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)LOCALCoMat 06-064
CoMat 03-378 WELDING WIRELOCALCoMat 03-378
CoMat 01-007 ETHYL ALCOHOL C2H5OH (DENATURED)LOCALCoMat 01-007
CoMat 01-001 SOLVENT, DELETED0AM53CoMat 01-001
CoMat 03-378 WELDING WIRELOCALCoMat 03-378

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-53-350-160 Rout out the Cracks in the Joint at the Trailing Edge of the TEC Struts

    1. Refer to: Figure

      2. Rout out the cracks in the joint at the trailing edge of the TEC struts. Rout out the cracks through the entire depth. Remove the minimum quantity of material.

      1. Use a routing ball that is 0.125 in. in diameter.

    2. SUBTASK 72-50-53-230-107 Fluorescent Penetrant Examine the Repair Area

      1. Fluorescent penetrant examine the repair area.

      1. Refer to the SPM TASK 70-23-05-230-501.

    3. If the complete crack is removed, blend the rout areas.

    4. If the crack is not removed, re-rout and fluorescent penetrant inspect (repeat steps 4 and 5).

    3. SUBTASK 72-50-53-110-129 Clean the Areas of the Turbine Exhaust Case to be Repaired

      1. Degrease the areas to be weld repaired.

      1. Use a lint-free cloth made moist with CoMat 01-001 SOLVENT, DELETED.

      2. Clean the areas to be weld repaired.

      1. Use a lint-free cloth made moist with CoMat 01-007 ETHYL ALCOHOL C2H5OH (DENATURED).

    4. SUBTASK 72-50-53-310-077 Weld the Routed Areas in the Turbine Exhaust Case Strut Trailing Edge

    1. Refer to: Figure

      2. Weld the routed areas.

      1. Use CoMat 03-378 WELDING WIRE and the GTAW method.

        Refer to the SPM TASK 70-31-13-310-501.

    5. SUBTASK 72-50-53-350-161 Blend the Weld

      1. Blend the weld flush to 0.000 - 0.01 in. (0.000 to 0.254 mm) above the parent material.

      1. Make sure not to remove the adjacent parent material.

    6. SUBTASK 72-50-53-230-108 Optional, Fluorescent Penetrant Inspect the Repaired Areas

      1. Fluorescent penetrant inspect the repaired areas (optional). Use the medium sensitivity method.

    7. SUBTASK 72-50-53-370-084 Stress-Relieve the Turbine Exhaust Case (Locally)

      1. Locally stress relieve the case.

      1. Refer to the SPM TASK 70-37-13-370-501, Cycle 6A.

    8. SUBTASK 72-50-53-370-083 Stress-Relieve the Turbine Exhaust Case (Furnace)

    1. Remove the 19 helicoils at the bearing compartment cover and two helicoils at the bearing jumper tube boss.

    2. Remove the 13 nut plates at the inner rear flange.

    3. Remove the three nut plates at the carbon seal flange.

      4. Furnace stress relieve the case.

      1. Refer to the SPM TASK 70-37-13-370-501, Cycle 6A.

    9. SUBTASK 72-50-53-210-060 Hardness Check of Repaired Area

      1. Perform hardness check adjacent to the repaired area of the turbine exhaust case.

      1. Hardness must be Rockwell RC 30-38.

    10. SUBTASK 72-50-53-230-129 Fluorescent Penetrant Inspect the Repaired Areas (If Locally Stress-Relieved)

      1. Fluorescent penetrant inspect the repaired areas for cracks.

    11. SUBTASK 72-50-53-230-109 Fluorescent Penetrant Inspect the Repaired Areas (If Furnace Stress-Relieved)

      1. Fluorescent penetrant inspect the case.

      1. Refer to the SPM TASK 70-23-02-230-501.

    12. SUBTASK 72-50-53-350-194 Install the Details if Removed

      1. Install the three nutplates at the carbon seal flange, if applicable.

      1. Repair, VRS3256 TASK 72-50-53-300-069 (REPAIR-069).

      2. Install the 13 nutplates at the inner rear flange.

      1. Repair, VRS3019 TASK 72-50-53-300-054 (REPAIR-054) or Repair, VRS5413 TASK 72-50-53-300-029 (REPAIR-029).

      3. Install the helicoils at the bearing compartment cover and the helicoils at the bearing jumper tube boss.

      1. Repair, VRS3014 TASK 72-50-53-300-046 (REPAIR-046) or Repair, VRS5392 TASK 72-50-53-300-008 (REPAIR-008).

    13. Figure: Repair Details and Dimensions

    Repair Details and Dimensions

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:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:X111X
Supply Number:CoMat 01-001
Type:sp01
Supply Short Name:CoMat 01-001 SOLVENT, DELETED
Supply Name:CoMat 01-001 SOLVENT, DELETED
Specification Groups:
Doc NumberType
wiring harnesses. Where CoMat 01‐001 is specified to clean mechanical components, use one or more of the solvents that SPM TASK 70‐11‐26‐300‐503 specifies as applicable.DELETED. Where CoMat 01‐001 is specified to clean electrical contacts or wiring harnesses, use one or more of the solvents that SPM TASK 70‐11‐57‐110‐501 specifies to clean electrical contacts or
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:LOCAL
Supply Number:CoMat 01-007
Type:sp01
Supply Short Name:CoMat 01-007 ETHYL ALCOHOL C2H5OH (DENATURED)
Supply Name:CoMat 01-007 ETHYL ALCOHOL C2H5OH (DENATURED)
Specification Groups:
Doc NumberType
PMC 9009 (PW REF)Reagent grade
MTH 133 (94%) (MTU REF)Reagent grade
Suppliers:
ManufacturerRemarks
LOCAL
K6835
IE441
24853
Manufacturer Code:LOCAL
Supply Number:CoMat 03-378
Type:sp01
Supply Short Name:CoMat 03-378 WELDING WIRE
Supply Name:CoMat 03-378 WELDING WIRE
Specification Groups:
Doc NumberType
AMS 5817GREEK ASCOLOY
Suppliers:
ManufacturerRemarks
LOCAL
2R602
55596
58401
Manufacturer Code:X222X
Supply Number:CoMat 06-064
Type:sp01
Supply Short Name:CoMat 06-064FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)
Supply Name:CoMat 06-064 FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)
Specification Groups:
Doc NumberType
It is not permitted to mix the selected CoMat 06‐064 letter suffix material with other CoMat 06‐064 letter suffix materials.Where CoMat 06‐064 is specified with no suffix, use one of the CoMat 06‐064 letter suffix materials.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:LOCAL
Tool Number:Grinding equipment
Tool Name:Grinding equipment
Manufacturer Code:LOCAL
Tool Number:Routing equipment
Tool Name:Routing equipment