TASK 72-41-15-300-007 HPC Stage 9 Rotor Blade - Repair Damage By Material Removal, Repair-007 (VRS6015)

DMC:V2500-A0-72-41-1509-00A-655A-C|Issue No:002.00|Issue Date:2021-08-01

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 72-41-15-300-007 HPC Stage 9 Rotor Blade - Repair Damage By Material Removal, Repair-007 (VRS6015)

Effectivity

FIG/ITEM

PART NO.

ASSEMBLY

02-470

6A3252

A

02-470

6A4366

A

02-470

6A4420

A

02-470

6A4726

B

02-470

6A6566

B

02-470

6A8751

B

02-485

6A3253

A

02-485

6A4367

A

02-485

6A4846

B

02-485

6A5637

A

02-485

6A5638

A

02-485

6A5645

B

02-485

6A8752

B

02-500

6A3251C01

A

02-500

6A4211C01

B

02-500

6A4365C01

A

02-500

6A4419C01

A

02-500

6A8749

B

02-515

6A3251C01

A

02-515

6A4211C01

B

02-515

6A4365C01

A

02-515

6A4419C01

A

02-515

6A8749

B

02-517

6A3251C02

A

02-517

6A4211C02

B

02-517

6A4365C02

A

02-517

6A4419C02

A

02-517

6A8750

B

Material of component

DESCRIPTION

MATERIAL

Stage 9

HP compressor rotor blades

Nickel chromium alloy

General

This repair must only be done when the instruction to do so is given in 72-41-15 Inspection/Check.

This repair gives the instruction to remove damage on the HP compressor rotor blade(s), stage 9 by material removal.

Rotor blades must be repaired as soon as damage or wear is monitored, to get back HP compressor efficiency and extend the rotor blade life.

Material removal from the HP compressor rotor blade airfoil fillet radius is not permitted.

When the depth of cut away material is more than 0.002 in. (0.05 mm), it is necessary to glass bead peen the HP compressor rotor blade(s), stage 9, to restore the airfoil surface condition, refer to Repair, VRS6150 TASK 72-41-15-300-040 (REPAIR-040).

The practices and processes referred to in the procedure by the TASK/SUBTASK number are in the SPM.

Related Repairs

HP Compressor - Stage 3 to 12 - Rotor Blades - Restore Airfoil Surface condition, Refer to Repair, VRS6150 TASK 72-41-15-300-040 (REPAIR-040).

NOTE

Equipment and materials necessary to do this repair are in the SPM TASKS given below:
SPM TASK 70-11-39-300-503
SPM TASK 70-23-04-230-501
SPM TASK 70-23-05-230-501
SPM TASK 70-35-03-300-501

NOTE

To identify the consumable materials refer to the PCI.

Preliminary Requirements

Pre-Conditions

Action/ConditionData Module/Technical Publication
Make sure all the necessary cleaning and inspection procedures are done before this repair.

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-41-15-110-186 Chemically Clean (DELETED)

    1. This subtask has been deleted.

    2. SUBTASK 72-41-15-230-105 Do a Crack Test (DELETED)

    1. This subtask has been deleted.

    3. SUBTASK 72-41-15-220-289 Visually Examine (DELETED)

    1. This subtask has been deleted.

    4. SUBTASK 72-41-15-350-059 Remove Damage from the HP Compressor Rotor Blade(s), Stage 9, Assembly A, and B

    1. Refer to Figure, Figure, Figure, Figure, and Figure.

    2. Refer to SPM TASK 70-35-03-300-501.

      3. Remove damage on the leading and trailing edges by blending.

      1. Refer to the blending limits shown in the figures.

      4. Remove damage on the airfoil surfaces by blending.

      1. The maximum depth to remove the damage must not be more than 0.005 in. (0.13 mm).

      2. The minimum diameter of the repaired area is to be 50 times the depth.

      3. The last polish is to be in the radial direction.

    5. SUBTASK 72-41-15-350-059-B00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 9, Assembly B (DELETED)

    1. This subtask has been deleted.

    6. SUBTASK 72-41-15-220-167 Examine the Repaired HP Compressor Rotor Blade(s), Stage 9, Assembly A, and B

    1. Refer to Figure, Figure, Figure, Figure, and Figure.

      2. Do a visual inspection and measure the dimensions of the leading edges and airfoil surface(s).

      1. Discard the blades, if more than the limits specified.

      2. Make sure the maximum depth of the repair on the airfoil surface(s) is not more than 0.005 in. (0.13 mm).

    7. SUBTASK 72-41-15-220-167-B00 Examine the Repaired HP Compressor Rotor Blade(s), Stage 9, Assembly B (DELETED)

    1. This subtask has been deleted.

    8. SUBTASK 72-41-15-110-122 Do a Swab Etch

      1. Clean and swab etch the repaired area(s).

      1. Refer to the SPM TASK 70-11-39-300-503.

    9. SUBTASK 72-41-15-230-067 Do a Crack Test

      1. Do a penetrant crack test on the repaired area(s) by one of the procedures that follow:

      1. Refer to SPM TASK 70-23-05-230-501, ultra high sensitivity. Cracks are not permitted.

      2. Refer to SPM TASK 70-23-04-230-501.

    10. SUBTASK 72-41-15-380-059 Restore the Airfoil Surface Condition

      1. NOTE

        This SUBTASK is necessary to restore the airfoil surface condition only when the depth of cut away material is more than 0.002 in. (0.05 mm).

        Restore the airfoil surface condition.

      1. Refer to Repair, VRS6150, TASK 72-41-15-300-040 (REPAIR-040).

    11. Figure: Repair Details And Dimensions - Assembly A And Assembly B

    Repair Details And Dimensions - Assembly A And Assembly B

    Figure: Repair Details And Dimensions - Assembly A

    Repair Details And Dimensions - Assembly A

    Figure: Repair Details And Dimensions - Assembly B

    Repair Details And Dimensions - Assembly B

    Figure: Repair Details And Dimensions - Assembly A And Assembly B

    Repair Details And Dimensions - Assembly A And Assembly B

    Figure: Repair Details And Dimensions - Assembly A And Assembly B

    Repair Details And Dimensions - Assembly A And Assembly B

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure in its entirety. (19VG363)