TASK 72-50-53-300-083 Turbine Exhaust Case (TEC) - Weld Patch Repair The Strut, Repair-083 (VRS3743)

DMC:V2500-A0-72-50-5301-03A-627A-C|Issue No:003.00|Issue Date:2015-05-01

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 72-50-53-300-083 Turbine Exhaust Case (TEC) - Weld Patch Repair The Strut, Repair-083 (VRS3743)

Effectivity

FIG/ITEM

PART NO.

02-300

4B8060

02-300

4B8068

21-300

2A1209-01

21-300

2A2620-01

21-300

2A3111-01

21-300

2A3183-01

21-300

2A3455-01

21-300

2A3183-101

21-300

2A4258-01

21-300

2A4263-01

Material of component

DESCRIPTION

SYMBOL

MATERIAL

Turbine exhaust case

-

Corrosion and heat resistant steel

General

Price and availability - refer to IAE

The practices and processes referred to in the procedure by the TASK numbers are in the SPM.

Remove adjacent hardware which will interfere with or be affected by the strut repair such as tubes, mount rail bushings, to nut plate details.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Silicon carbide rag wheelLOCALSilicon carbide rag wheel

or equivalent

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 01-007 ETHYL ALCOHOL C2H5OH (DENATURED)LOCALCoMat 01-007
CoMat 03-378 WELDING WIRELOCALCoMat 03-378
CoMat 06-063 FLUORESCENT PENETRANT (POST-EMULSIFIED MEDIUM SENSITIVITY)LOCALCoMat 06-063
CoMat 06-064 FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)LOCALCoMat 06-064
CoMat 06-061 DELETED0AM53CoMat 06-061

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-53-320-164 Remove the Damaged Area in the Turbine Exhaust Case Strut Airfoil

      CAUTION

      DO NOT REMOVE PARENT MATERIAL FROM STRUT STAND-UPS, LEADING EDGE DETAIL, OR TRAILING EDGE DETAIL.

    1. Refer to Fig. 72-53-50-990-152.

      2. Cut the area in the strut airfoil to remove the damaged area.

      1. Refer to Fig. 72-53-50-990-152 to see the repairable areas. You must fully remove cracked or damaged areas. Do not cut in areas that extend into weld joints, strut stand-ups and leading or trailing edge details.

    2. SUBTASK 72-50-53-320-165 Make a Patch to Repair the Damaged Strut Airfoil

      1. For PN 4B8060 or 4B8068, make a patch from 0.043 in. to 0.051 in. (1.092 mm to 1.295 mm) thick AMS 5508 sheet stock or AMS 5616 bar stock.

        For all other part numbers, make a patch from 0.051 in. to 0.056 in. (1.295 mm to 1.422 mm) thick AMS 5508 sheet stock or AMS 5616 bar stock.

      1. Make all patches fit the area where you removed the material with a 0.020 in. (0.51 mm) gap between the patch and the strut opening.

      2. Stress-relieve the patch.

      1. Refer to the SPM TASK 70-37-28-370-501. The hardness must be Rockwell 30 to 38 or equivalent.

      3. Make the patch material in the shape of the strut.

      1. Compare the contour of the patch to the contour of adjacent struts that had no damage or repair. The strut contour that you repaired must agree with the adjacent struts in 0.025 in. (0.64 mm).

    3. SUBTASK 72-50-53-110-187 Clean the Areas to be Welded

      1. Polish all areas to be welded and the inside and outside surfaces of the strut and patch.

      1. Use a silicon carbide rag, wheel or equivalent.

      2. Clean the weld areas inside and outside of the strut and the patch.

      1. Use a lint-free cloth. Refer to the SPM TASK 70-11-26-300-503. Use CoMat 01-007 ETHYL ALCOHOL C2H5OH (DENATURED).

    4. SUBTASK 72-50-53-310-083 Weld the Patches onto the Strut Airfoil

    1. Refer to Figure.

      2. Tack weld the patch to replace the damaged area. Tack welds must be 1.5 to 2.0 in. (38.1 to 50.8 mm) apart around the patch.

      3. Examine the patch for correct strut contour. If necessary, break the tack weld, correct the contour of the patch and tack weld the patch again.

      1. The patch contour that you repaired must agree with the adjacent areas that were not damaged or repaired in 0.025 in. (0.64 mm).

      4. Weld the patch onto the turbine exhaust case strut.

      1. Refer to the SPM TASK 70-31-02-310-501-008. Use CoMat 03-378 WELDING WIRE and the GTAW method. Full weld penetration is necessary.

    5. SUBTASK 72-50-53-350-199 Blend the Weld Bead on the Strut Patch

      1. Blend the weld bead 0.000 to 0.010 in. (0.00 to 0.25 mm) above adjacent surfaces.

      1. Blends must be smooth and continous. No steps are permitted.

    6. SUBTASK 72-50-53-370-100-001 Stress-Relieve the Repaired Area (Local)

      1. Locally stress-relieve the repaired area.

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

    7. SUBTASK 72-50-53-370-100-002 Stress-Relieve the Repaired Area (Oven)

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

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

      2. Remove the nut plates from the inner rear flange.

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

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

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

      4. Stress-relieve the case in an oven.

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

    8. SUBTASK 72-50-53-230-137-001 Examine the Repaired Areas (After Local Stress-Relief)

      1. Examine the case after local stress-relief.

    9. SUBTASK 72-50-53-230-137-002 Examine the Repaired Areas (After Stress-Relief in an Oven)

      1. Examine the case after stress-relief in an oven.

    10. SUBTASK 72-50-53-350-200 Install the Detail Parts

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

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

      2. Remove the nut plates from the inner rear flange.

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

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

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

    11. SUBTASK 72-50-53-220-250 Examine the Turbine Exhaust Case After Repair

      1. Examine the dimensions of the turbine exhaust case.

      1. Refer to TASK 72-50-53-200-000 (INSPECTION/CHECK-000).

    12. Figure: Repair Details and Dimensions

    Repair Details and Dimensions

    Figure: Repair Details and Dimensions

    Repair Details and Dimensions

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Added AMS 5616 bar stock to the procedure. (14VC394)

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: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:0AM53
Supply Number:CoMat 06-061
Type:sp01
Supply Short Name:CoMat 06-061 DELETED
Supply Name:CoMat 06-061 DELETED
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
0AM53
Manufacturer Code:X222X
Supply Number:CoMat 06-063
Type:sp01
Supply Short Name:CoMat 06-063 FLUORESCENT PENETRANT (POST-EMULSIFIED MEDIUM SENSITIVITY)
Supply Name:CoMat 06-063 FLUORESCENT PENETRANT (POST-EMULSIFIED MEDIUM SENSITIVITY)
Specification Groups:
Doc NumberType
It is not permitted to mix the selected CoMat 06‐063 letter suffix material with other CoMat 06‐063 letter suffix materials. Where CoMat 06‐063 is specified with no suffix, use one of the CoMat 06‐063 letter suffix materials.
Suppliers:
ManufacturerRemarks
X222X
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:Silicon carbide rag wheel
Tool Name:Silicon carbide rag wheel