TASK 72-41-15-300-003 HPC Stage 5 Rotor Blade(s) - Repair Surface Damage By Material Removal, Repair-003 (VRS6011)

DMC:V2500-A0-72-41-1505-00A-655A-C|Issue No:004.00|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 72-41-15-300-003 HPC Stage 5 Rotor Blade(s) - Repair Surface Damage By Material Removal, Repair-003 (VRS6011)

Effectivity

FIG/ITEM

PART NO.

SERVICE BULLETIN

ASSEMBLY

01-800

6A3335

70-0024

A

01-800

6A3637

-

A

01-800

6A3941

72-0035

A

01-800

6A4198

70-0726

B

01-800

6A8449

72-0490

A

01-800

6A8451

72-0490

B

01-800

6B1346

72-0587

C

Material of component

PART INDENT

MATERIAL

Stage 5

HP Compressor Rotor Blade(s), Stage 5

Titanium Alloy

General Data

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

This TASK gives the procedure to remove damage on the HP compressor rotor blade(s), Stage 5 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. (0.050 mm), it is necessary to glass bead peen the HP compressor rotor blade(s), stage 5, 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 number are in 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 70-11-08-300-503
SPM TASK 70-23-04-230-501
SPM TASK 70-23-05-230-501
SPM TASK 70-35-03-300-501

NOTE

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.

NOTE

To identify the consumable materials refer to the Overhaul Processes and Consumable Index (OPCI) Manual.

NOTE

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 72-41-15-220-285 Visually Examine the Blade (DELETED)

    1. This subtask has been deleted.

    2. SUBTASK 72-41-15-350-055-A00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 5, Assembly A

    1. For Assembly A, 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 1.280 in. (32.51 mm).

        AE 3.060 in. (77.72 mm).

        AG 1.518 in. (38.56 mm).

        AH 1.399 in. (35.54 mm).

        AK 1.654 in. (42.011 mm).

        AL 0.118 in. (2.997 mm).

        AM 0.010 in. (0.25 mm).

        AV 0.800 in. (20.32 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.

    3. SUBTASK 72-41-15-350-055-B00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 5, Assembly B

    1. For Assembly B, 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 1.310 in. (33.27 mm).

        AE 3.020 in. (76.71 mm).

        AG 1.510 in. (38.34 mm).

        AH 1.450 in. (36.84 mm).

        AK 1.654 in. (42.011 mm).

        AL 0.118 in. (2.997 mm).

        AM 0.010 in. (0.25 mm).

        AV 0.800 in. (20.32 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.

    4. SUBTASK 72-41-15-350-055-C00 Remove Damage from the HP Compressor Rotor Blade(s), Stage 5, Assembly C

    1. For Assembly C, 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 1.310 in. (33.27 mm).

        AE 3.020 in. (76.71 mm).

        AG 1.506 in. (38.24 mm).

        AH 1.458 in. (37.03 mm).

        AK 1.654 in. (42.011 mm).

        AL 0.118 in. (2.997 mm).

        AM 0.010 in. (0.25 mm).

        AV 0.800 in. (20.32 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 72-41-15-220-163 Examine the Repaired HP Compressor Rotor Blade(s), Stage 5

    1. For Assembly A, B, and C, 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. 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).

    6. SUBTASK 72-41-15-110-118 Do a Swab Etch

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

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

    7. SUBTASK 72-41-15-230-063 Do a Crack Test

      1. Do a penetrant crack test on the repaired blades 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.

    8. SUBTASK 72-41-15-380-055 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).

    9. 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)