TASK 72-50-53-300-013 Turbine Exhaust Case (TEC) - Plasma Coat The Front Face Of The Front Flange, Repair-013 (VRS5397)

DMC:V2500-A1-72-50-5301-00A-609A-C|Issue No:002.00|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

V2500-A1

Common Information

TASK 72-50-53-300-013 Turbine Exhaust Case (TEC) - Plasma Coat The Front Face Of The Front Flange, Repair-013 (VRS5397)

Effectivity

FIG/ITEM

PART NO.

01-001

4A8014

01-001A

4A8025

Material of component

DESCRIPTION

SYMBOL

MATERIAL

Turbine exhaust case

Corrosion and heat resistant

iron base alloy

General

Price and availability - none

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

NOTE

  1. To identify the consumable materials refer to the PCI.

  2. Consumable materials are given in the SPM.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 03-096 PLASMA SPRAY POWDERLOCALCoMat 03-096

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-53-320-055 Machine the Front Face of the Front Flange

    1. Refer to: Figure

      2. Machine the front face of the front flange.

      1. The pre-spraying dimension must be between 11.5862 to 11.5787in. (294.29 to 294.10 mm) in relation to surface H after the removal of the damage.

        Remove all damage and wear.

        Keep the removal of material to the minimum necessary to remove the damage.

    2. SUBTASK 72-50-53-230-056 Examine the Front Face

      1. Do the fluorescent penetrant inspection for cracks.

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

        No cracks are permitted.

        NOTE

        This step is required if the method of machining in Step (4) was grinding. For all other methods, this step is optional.

    3. SUBTASK 72-50-53-110-055 Clean the Turbine Exhaust Case

      1. Degrease by aqueous cleaning.

      1. Refer to the SPM TASK 70-11-03-300-503.

    4. SUBTASK 72-50-53-120-062 Prepare the Front Face of the Front Flange

    1. Refer to Figure.

      2. Prepare the surface of part for plasma and other thermal spray coating.

      1. Refer to the SPM TASK 70-34-18-380-501.

    3. Use proper maskants.

      4. Clean the turbine exhaust case.

      1. Clean with dry air blast.

    5. SUBTASK 72-50-53-370-053 Metal Plasma Spray the Front Face of the Front Flange

    1. Refer to Figure.

    2. Mask the areas of the turbine exhaust case not to be sprayed.

      3. Preheat the surface to be sprayed.

      1. Preheat temperature: 194 to 248 deg F (90 to 120 deg C).

      4. Metal plasma spray the front face of the front flange.

      1. Refer to the SPM TASK 70-34-03-340-501.

        Spraying distance

        5.315 in. (135 mm)

        Spraying angle

        90 degrees

        Component rotation speed

        50 rpm

        Gun traverse speed

        9.84 in/min (250 mm/min)

        Maximum working temperature

        392 deg F (200 deg C)

    5. Remove the mask.

      6. Clean the turbine exhaust case.

      1. Clean with dry air blast.

    6. SUBTASK 72-50-53-220-085 Examine the Turbine Exhaust Case

      1. Do the visual inspection of the coating for good adhesion.

      1. No cracks or separation from the parent material are permitted.

        Do again the process if cracks are evident.

    7. SUBTASK 72-50-53-320-056 Machine the Front Face of the Front Flange

    1. Refer to: Figure

      2. Machine the front face of the front flange.

      1. The last dimension must be between 11.6098 to 11.5902in. (294.890 to 294.390 mm) in relation to surface H.

        The perpendicularity of the front face must be in 0.002in. (0.05 mm) in relation to diameter X.

        Chamfer where necessary.

    8. SUBTASK 72-50-53-220-086 Examine the Coated Area

    1. Refer to Figure.

      2. Do the visual inspection.

      1. No cracks or separation from the parent material are permitted.

        Do again the process if cracks are evident.

    9. SUBTASK 72-50-53-350-056 Record the Repair

      1. Vibration peen VRS5397 adjacent to the part number.

      1. Refer to the SPM TASK 70-09-00-400-501. Use vibration peen method with 0.006 in. (0.15 mm) maximum depth.

    10. Figure: Repair Details and Dimensions

    Repair Details and Dimensions

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Editorial correction due to conversion

Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:LOCAL
Supply Number:CoMat 03-096
Type:sp01
Supply Short Name:CoMat 03-096 PLASMA SPRAY POWDER
Supply Name:CoMat 03-096 PLASMA SPRAY POWDER
Specification Groups:
Doc NumberType
AMPERIT 298.442 OR AMPERIT 299.442
Suppliers:
ManufacturerRemarks
LOCAL
IAE15
IE252