TASK 72-41-15-300-004 HPC Stage 6 Rotor Blade - Repair Damage By Material Removal, Repair-004 (VRS6012)

DMC:V2500-A0-72-41-1506-00A-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 72-41-15-300-004 HPC Stage 6 Rotor Blade - Repair Damage By Material Removal, Repair-004 (VRS6012)

Effectivity

FIG/ITEM

PART NO.

ASSEMBLY

02-170

6A3338

A

02-170

6A7406

B

02-170

6A8322

B

02-170

6A8463

A

02-170

6A8797

C

02-185

6A3339

A

02-185

6A7407

B

02-185

6A8323

B

02-185

6A8464

A

02-185

6A8798

C

02-200

6A3340C01

A

02-200

6A7405C01

B

02-200

6A8320

B

02-200

6A8461

A

02-200

6A8732

C

02-215

6A3340C01

A

02-215

6A7405C01

B

02-215

6A8320

B

02-215

6A8461

A

02-215

6A8732

C

02-216

6B1494

C

02-217

6A3340C02

A

02-217

6A7405C02

B

02-217

6A8321

B

02-217

6A8462

A

02-217

6A8733

C

General Data

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

This repair gives the instruction to remove damage on the HP compressor rotor blade(s), stage 6 by material removal.

You can mix a scallop and/or complete edge dress to a given rotor blade, if the maximum limit for any one of these is not exceeded.

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 6, to restore the 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 70-11-08-300-503
SPM TASK 70-23-04-230-501
SPM TASK 70-23-05-230-501
SPM TASK 70-35-03-300-501

NOTE

  1. It is possible that some materials in the Consumable Materials chart cannot be used for some or all of the necessary applications. Before you use the materials, make sure the types, quantities and applications of the materials necessary are legally permitted in your location. All persons must obey all applicable federal, state, local and provincial laws and regulations when it is necessary to work with these materials.

  2. To identify the consumable materials, refer to the Overhaul Processes and Consumables Index (PCI).

  3. Other necessary consumable materials are referred to in the SPM TASKs.

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 72-41-15-110-182 Chemically Clean (DELETED)

    1. This subtask has been deleted.

    2. SUBTASK 72-41-15-230-130 Do a Crack Test (DELETED)

    1. This subtask has been deleted.

    3. SUBTASK 72-41-15-220-586 Visually Examine (DELETED)

    1. This subtask has been deleted.

    4. SUBTASK 72-41-15-350-056-A00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 6, Assembly A

    1. Refer to 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 material removal.

      1. Refer to the blending limits shown below:

        AD 1.060 in. (26.92 mm).

        AE 2.280 in. (57.91 mm).

        AG 1.103 in. (28.02 mm).

        AH 1.107 in. (28.12 mm).

        AK 1.150 in. (29.21 mm).

        AL 0.100 in. (2.50 mm).

        AM 0.010 in. (0.25 mm).

        AV 0.500 in. (12.70 mm).

      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 a radial direction.

    5. SUBTASK 72-41-15-350-056-B00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 6, Assembly B

    1. Refer to 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 below:

        AD 1.120 in. (28.45 mm).

        AE 2.290 in. (58.17 mm).

        AG 1.137 in. (28.87 mm).

        AH 1.080 in. (27.46 mm).

        AK 1.150 in. (29.21 mm).

        AL 0.100 in. (2.50 mm).

        AM 0.010 in. (0.25 mm).

        AV 0.500 in. (12.70 mm).

      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 area is to be in the radial direction.

    6. SUBTASK 72-41-15-350-056-C00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 6, Assembly C

    1. Refer to 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 below:

        AD 1.120 in. (28.45 mm).

        AE 2.290 in. (58.17 mm).

        AG 1.135 in. (28.83 mm).

        AH 1.087 in. (27.62 mm).

        AK 1.150 in. (29.21 mm).

        AL 0.100 in. (2.50 mm).

        AM 0.010 in. (0.25 mm).

        AV 0.500 in. (12.70 mm).

      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 a radial direction.

    7. SUBTASK 72-41-15-220-164 Examine the Repaired HP Compressor Rotor Blade(s), Stage 6, Assembly A, Assembly B, and Assembly C

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

      2. Do a visual inspection and measure the dimensions of the leading, trailing edges, and airfoil surfaces.

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

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

    8. SUBTASK 72-41-15-110-119 Do a Swab Etch

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

      1. Refer to SPM TASK 70-11-08-300-503.

    9. SUBTASK 72-41-15-230-064 Do a Crack Test

      1. Do a penetrant crack test on the repaired area(s) by the 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 72-41-15-380-056 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, Assembly B, And Assembly C

    Repair Details And Dimensions - Assembly A, Assembly B, And Assembly C

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

    Repair Details And Dimensions - Assembly A, Assembly B, And Assembly C

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

    Repair Details And Dimensions - Assembly A, Assembly B, And Assembly C

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

    Repair Details And Dimensions - Assembly A, Assembly B, And Assembly C

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure in its entirety. (19VG363)