TASK 72-50-53-300-056 Turbine Exhaust Case (TEC) - Nickel Plate The Rear Outer Flange, Repair-056 (VRS3070)

DMC:V2500-A0-72-50-5301-03A-647A-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 72-50-53-300-056 Turbine Exhaust Case (TEC) - Nickel Plate The Rear Outer Flange, Repair-056 (VRS3070)

Effectivity

FIG/ITEM PART NO.

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

PART IDENT

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.

NOTE

To identify the consumable materials refer to the PCI.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Workshop inspection equipmentLOCALWorkshop inspection equipment
Grinding machineLOCALGrinding machine
FurnaceLOCALFurnace
Magnifying glass, 4XLOCALMagnifying glass
Vibrating marking pencilLOCALVibrating marking pencil

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-067 STRIPPABLE COATING71410CoMat 02-067

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-53-320-084 Machine the Rear Face of the Rear Outer Flange of the Turbine Exhaust Case

    1. Refer to Figure.

      2. Machine the rear face of the rear outer flange.

      1. Keep the removal of material to the minimum necessary to remove the damage and to permit sufficient plating thickness.

        Flange thickness must be 0.120 in. (3.05 mm) minimum after you remove the damage.

    2. SUBTASK 72-50-53-230-083 Examine the Turbine Exhaust Case

      1. Fluorescent penetrant inspect the turbine exhaust case.

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

        No cracks are permitted.

    3. SUBTASK 72-50-53-380-052 Apply a Mask to the Turbine Exhaust Case

      1. Apply a mask to the areas of the turbine exhaust case that are not to be plated.

    4. SUBTASK 72-50-53-330-061 Nickel Plate the Rear Face of the Rear Outer Flange of the Turbine Exhaust Case

    1. Refer to Figure.

      2. Nickel plate the rear face of the rear outer flange.

      1. Apply nickel plate to a sufficient thickness to permit finish machining. Plating outside the repair area is permitted but must be removed.

    3. Remove the mask.

    5. SUBTASK 72-50-53-110-100 Clean the Turbine Exhaust Case

      1. Clean the turbine exhaust case.

      1. Flush the case with cold water.

        Flush the case with hot water.

        Dry the case with air blast.

    6. SUBTASK 72-50-53-370-069 Bake after Nickel Plate

      1. Bake the turbine exhaust case after nickel plate.

      1. Put the case into a furnace at 350 to 400 deg F (176 to 204 deg C) for three hours.

        Do this process as soon as possible in less than four hours after nickel.

        plate.

    7. SUBTASK 72-50-53-220-178 Examine the Turbine Exhaust Case

      1. Do a visual inspection of the plating for finish, cracks and bond.

      1. The plate must have a constant color.

        No circumferential cracks are permitted.

        No roughness or blisters are permitted.

    8. SUBTASK 72-50-53-320-085 Machine the Rear Face of the Rear Outer Flange of the Turbine Exhaust Case

      1. Machine the rear face of the rear outer flange after nickel plate.

      1. Refer to Figure.

    9. SUBTASK 72-50-53-220-179 Examine the Repair

      1. Examine the turbine exhaust case after nickel plate.

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

        Use a 4X magnifying glass to examine for cracks. The normal network of cracks that are emphasized by grinding are permitted.

        The thickness of the plate after finish machining must be a minimum of 0.0006 in. (0.015 mm).

    10. SUBTASK 72-50-53-350-091 Identify the Repair

      1. Mark VRS3070 on the repaired turbine exhaust case adjacent to the part number.

      1. Make a permanent mark by the procedure given in the SPM TASK 70-09-00-400-501.

        Use a vibrating marking pencil.

        Remove high metal caused by marking the number.

    11. Figure: Repair Details and Dimensions

    Repair Details and Dimensions

Requirements After Job Completion

Follow-On Conditions

NONE
Manufacturer Code:71410
Enterprise Name:HENKEL CORPORATION (WAS: TURCO PRODUCTS, INC)
BU Name:HENKEL CORPORATION (WAS: TURCO PRODUCTS, INC)
Street:32100 STEPHENSON HIGHWAY
City:MADISON HEIGHTS
State:MI
Zip Code:48071
Country:USA
Phone Number:1-248-583-9300
Fax Number:1-248-583-2976
Internet:www.aerospace.henkel.com
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:71410
Supply Number:CoMat 02-067
Type:sp01
Supply Short Name:CoMat 02-067 STRIPPABLE COATING
Supply Name:CoMat 02-067 STRIPPABLE COATING
Specification Groups:
Doc NumberType
TURCO 5580-G PMC 1835
Suppliers:
ManufacturerRemarks
71410
Manufacturer Code:LOCAL
Tool Number:Furnace
Tool Name:Furnace
Link not Found
Link not Found
Link not Found
Manufacturer Code:LOCAL
Tool Number:Workshop inspection equipment
Tool Name:Workshop inspection equipment