TASK 72-41-15-200-010-A00 HPC Stage 12 Rotor Blade - Examine, Inspection-010

DMC:V2500-A0-72-41-1512-00A-300A-C|Issue No:005.00|Issue Date:2018-05-01

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 72-41-15-200-010-A00 HPC Stage 12 Rotor Blade - Examine, Inspection-010

Effectivity

FIG/ITEM

PART NO.

02-770

6A3261

02-770

6A5643

02-770

6A6565

02-785

6A3262

02-785

6A5644

02-800

6A3260C01

02-815

6A3260C01

02-817

6A3260C02

General

This TASK gives the procedure for the inspection of the HP compressor stage 12 rotor blades. This procedure has been revised to include the Identification Markings introduced by SBE 72-0172.

Nicks and dents 0.005 in. (0.13 mm) or less are acceptable without limit to the airfoil and gas washed surface of the platforms.

Fig/item numbers in parentheses in the procedure agree with those given in the IPC. Only the primary Fig/item numbers are used. For the service bulletin alpha variants refer to the IPC.

The policy that is necessary for inspection is given in the SPM TASK 70-20-01-200-501.

All the parts must be cleaned before any part is examined.

All the parts must be visually examined for damage, corrosion and wear. Any defects that are not identified in the procedure must be referred to IAE.

The procedure for those parts which must have a crack test is given in SUBTASK 72-41-15-230-060. Do the crack test before the part is visually examined.

Do not discard any part until you are sure there are no repairs available. Refer to the instructions in Repair before a discarded part is used again or oversize parts are installed.

Parts which should be discarded can be held although no repair is available. The repair of a discarded part can be shown to be necessary at a subsequent date.

All the parts must be examined to make sure that all the repairs have been completed satisfactorily.

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

References

Refer to the SPM for data on these items:

Definition of Damage, SPM TASK 70-02-02-350-501,

Inspection of Parts, SPM TASK 70-20-01-200-501.

Some data on these items are contained in this TASK. For more data on these items refer to the SPM:

Method of Testing for Crack Indications,

Chemical Processes,

Surface Protection.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-41-15-280-057 Identify the Stage 12 Rotor Blades

    1. Refer to Figure.

      2. Examine the part number and the symbol on the base of the blade.

      1. Refer to the table in Figure, if the part number on the blade is shown in A and has the symbol shown in B, then the part number should be read as that shown in C.

    2. SUBTASK 72-41-15-230-060-001 Examine the Stage 12 Rotor Blades for Cracks

    1. Clean the parts. Refer to TASK 72-41-15-100-000 (CLEANING-000).

      2. Do the test for cracks on the parts that are given below.

        PART IDENT

        TASK/SUBTASK

        Stage 12 Rotor Blades

        1. Leading edge.

          1. Cracked.

          1. Refer to Step.

        2. Airfoil tips.

          1. Cracked.

          1. Refer to Step.

        3. All remaining areas.

          1. Cracked

          1. Reject.

    3. SUBTASK 72-41-15-220-117 Examine the Stage 12 Rotor Blades Concave and Convex Airfoil Surfaces at Locations 1 and 2

    1. Refer to Figure.

      2. Nicks or dents

        1. Up to 0.005 in. (0.13 mm) in depth

        1. Accept

        2. More than in Step

        1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

      3. Eroded

      1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

    4. SUBTASK 72-41-15-220-205 Examine the Stage 12 Rotor Blades Concave and Convex Airfoil Surface Finish at Locations 1 and 2, Platform at Location 8 and Root Radius at Location 9

    1. Refer to Figure.

      2. Mean surface finish of 16 microinches (0.40 micrometres) or less.

      1. Accept.

      3. Mean surface finish greater than 16 microinches (0.40 micrometres).

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

    5. SUBTASK 72-41-15-220-149 Examine the Stage 12 Rotor Blades Leading Edge at Location 3

    1. Refer to Figure.

      2. Cracked

      1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

      3. Nicks or dents

        1. Up to 0.005 in. (0.13 mm) in depth

        1. Accept

        2. More than in Step

        1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

      4. Eroded

      1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

    6. SUBTASK 72-41-15-220-118 Examine the Stage 12 Rotor Blades Trailing Edge at Location 4

    1. Refer to Figure.

      2. Nicks or dents

        1. Up to 0.005 in. (0.13 mm) in depth

        1. Accept

        2. More than in Step

        1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

      3. Eroded

      1. Repair, VRS6018 TASK 72-41-15-300-010 (REPAIR-010)

    7. SUBTASK 72-41-15-220-150 Examine the Stage 12 Rotor Blades Tips at Location 1054

    1. Refer to Figure.

      2. Cracked

      1. Repair, VRS6058 TASK 72-41-15-300-039 (REPAIR-039)

      3. Rubbed or worn.

        1. In the limits of TASK 72-41-10-040-001-A00 (DISASSEMBLY, CONFIG-001)

        1. Accept

        2. Identified as too short in TASK 72-41-10-040-001-A00 (DISASSEMBLY, CONFIG-001)

        1. Repair, VRS6058 TASK 72-41-15-300-039 (REPAIR-039)

    8. SUBTASK 72-41-15-220-119 Examine the Stage 12 Rotor Blades Dovetail at Location 5

    1. Refer to Figure.

      2. Scored

      1. Reject

      3. Galled.

        1. Not more than 0.002 in. (0.05 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    9. SUBTASK 72-41-15-220-120 Examine the Stage 12 Rotor Blades Cheeks at Locations 6 and 7

    1. Refer to Figure.

      2. Galled.

        1. Not more than 0.002 in. (0.05 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    10. SUBTASK 72-41-15-220-121 Examine the Stage 12 Rotor Blades Platform at Location 8

    1. Refer to Figure.

      2. Nicks or dents

        1. Not more than 0.005 in. (0.13 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    11. SUBTASK 72-41-15-220-122 Examine the Stage 12 Rotor Blades Root Radius at Location 9

    1. Refer to Figure.

      2. Nicks or dents

        1. Up to 0.005 in. (0.13 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    12. SUBTASK 72-41-15-220-123 Examine the Stage 12 Rotor Locking Blades Slots at Locations 10

    1. Refer to Figure.

      2. Galled.

        1. Not more than 0.002 in. (0.05 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    13. SUBTASK 72-41-15-220-161 Examine the Stage 12 Rotor Blades Chordal Checks

    1. Refer to Figure.

      2. Minimum chord at Z1 and Z2 at location A and B to the value X

      1. Accept

      3. Less than value X

      1. Reject

    14. SUBTASK 72-41-15-220-453 Examine the Stage 12 Rotor Blades, Length Checks

    1. NOTE

      This is an alternative method to measurements taken on High Speed Grinding Machine to find the permitted blade length limits.

      Refer to Figure.

    2. Measure the blade length "X".

      3. Between 1.0520 and 1.0600 in. (26.720 and 26.924 mm)

      1. Accept

      4. Between 1.0180 and 1.0510 in. (25.857 and 26.695 mm)

      1. Repair, VRS6058 TASK 72-41-15-300-039 (REPAIR-039)

      5. Less than the minimum repair limit given in Repair, VRS6058 TASK 72-41-15-300-039 (REPAIR-039)

      1. Reject

    15. SUBTASK 72-41-15-220-580 Examine the Stage 12 Rotor Blade, Dovetail End Faces and Corners

    1. NOTE

      Class identification markings as scores.

      Refer to Figure and Figure.

      2. Scored.

        1. Location 9 - end face

        1. Accept

        2. Location 10 - margin to bottom face

          1. More than 0.039 in. (1.00 mm)

          1. Accept

          2. Less than 0.039 in. (1.00 mm)

          1. Refer to the SPM TASK 70-35-03-300-501 to remove score. Repair corner radius equal to adjacent edges which are not repaired

      3. Location 11 and 12 - margin to dovetail and neck profile.

        4. More than 0.047 in. (1.20 mm)

        1. Accept

        5. Less than 0.047 in. (1.20 mm)

        1. Reject

      6. Location 13 - under platform fillet radius (0.067 in. plus or minus 0.008 in. (1.70 mm plus or minus 0.20 mm)).

        7. Until the intersection of radius

        1. Accept

        8. On radius

          1. Not more than 0.002 in. (0.05 mm) in depth

          1. Polish to remove score 1x depth. Refer to the SPM TASK 70-35-03-300-501. Do not polish into neck radius (location 12)

          2. More than in Step

          1. Reject

    16. SUBTASK 72-41-15-220-581 Examine the Stage 12 Rotor Blade, Part Marking and Repair Symbol Location

    1. Refer to Figure.

    2. Part marking and repair symbol end face edge margin.

      3. Location 14 - bottom faces

      1. Accept

      4. Location 10 - margin to bottom face

        1. More than 0.039 in. (1.00 mm)

        1. Accept

        2. Less than 0.039 in. (1.00 mm)

        1. Refer to the SPM TASK 70-35-03-300-501 to remove score. Repair corner radius equal to adjacent edges which are not repaired

      5. Do the identification marking again if removed by step (2)

      1. Refer to the SPM TASK 70-09-00-400-501, SUBTASK 70-09-00-400-001. Use vibro-engraving equipment

    6. Do the step (2) again

    17. Figure: Stage 12 rotor blades - inspection locations

    Stage 12 rotor blades - inspection locations

    Figure: Identify the stage 12 rotor blades

    Identify the stage 12 rotor blades

    Figure: Stage 12 rotor blades - chordal checks

    Stage 12 rotor blades - chordal checks

    Figure: Stage 12 rotor blades - measure length "X"

    Stage 12 rotor blades - measure length "X"

    Figure: Stage 12 Rotor Blade - Dovetail End Faces and Corners

    Stage 12 Rotor Blade - Dovetail End Faces and Corners

    Figure: Stage 12 Rotor Blade - Dovetail End Faces and Corners

    Stage 12 Rotor Blade - Dovetail End Faces and Corners

    Figure: Stage 11 Rotor Blade - Dovetail End Faces and Corners

    Stage 11 Rotor Blade - Dovetail End Faces and Corners

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Corrected Figure 3 dimensions. (17VG175)