TASK 72-41-15-200-008-A00 HPC Stage 10 Rotor Blade - Examine, Inspection-008

DMC:V2500-A0-72-41-1510-00A-300A-C|Issue No:006.00|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 72-41-15-200-008-A00 HPC Stage 10 Rotor Blade - Examine, Inspection-008

Effectivity

FIG/ITEM

PART NO.

02-570

6A3255

02-570

6A5639

02-570

6A6563

02-585

6A3256

02-585

6A5640

02-600

6A3254C01

02-615

6A3254C01

02-617

6A3254C02

General

This TASK gives the procedure for the inspection of the HP compressor stage 10 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 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 72-41-15-230-058. 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 72-41-15-280-055 Identify the Stage 10 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 72-41-15-230-058-001 Examine the Stage 10 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 10 Rotor Blades

        1. Leading edge.

          1. Cracked.

        2. Airfoil tips.

          1. Cracked.

          1. Refer to TASK 72-41-15-200-007-A00, SUBTASK 72-41-15-220-144.

        3. All remaining areas.

          1. Cracked

          1. Reject.

    3. SUBTASK 72-41-15-220-103 Examine the Stage 10 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 VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

      3. Eroded

      1. Repair VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

    4. SUBTASK 72-41-15-220-203 Examine the Stage 10 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 20 microinches (0.50 micrometres) or less.

      1. Accept.

      3. Mean surface finish greater than 20 microinches (0.50 micrometres).

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

    5. SUBTASK 72-41-15-220-145 Examine the Stage 10 Rotor Blades Leading Edge at Location 3

    1. Refer to Figure.

      2. Cracked

      1. Repair VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

      3. Nicks or dents

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

        1. Accept

        2. More than in Step

        1. Repair VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

      4. Eroded

      1. Repair VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

    6. SUBTASK 72-41-15-220-104 Examine the Stage 10 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 VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

      3. Eroded

      1. Repair VRS6016, TASK 72-41-15-300-008 (REPAIR-008)

    7. SUBTASK 72-41-15-220-146 Examine the Stage 10 Rotor Blades Tips at Location 1053

    1. Refer to Figure.

      2. Cracked

      1. Repair VRS6056, TASK 72-41-15-300-018 (REPAIR-018)

      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 VRS6056, TASK 72-41-15-300-018 (REPAIR-018)

    8. SUBTASK 72-41-15-220-105 Examine the Stage 10 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 72-41-15-220-106 Examine the Stage 10 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 72-41-15-220-107 Examine the Stage 10 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 72-41-15-220-108 Examine the Stage 10 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 72-41-15-220-109 Examine the Stage 10 Rotor Locking Blades Slots at Location 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 72-41-15-220-159 Examine the Stage 10 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 72-41-15-220-451 Examine the Stage 10 Rotor Blades, Length Checks

    1. NOTE

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

      Refer to Figure.

    2. Measure the blade length "X".

      3. Between 1.1010 and 1.1090 in. (27.965 and 28.169 mm)

      1. Accept

      4. Between 1.0690 and 1.100 in. (27.153 and 27.94 mm)

      1. Repair VRS6056, TASK 72-41-15-300-018 (REPAIR-018)

      5. Less than the minimum repair limit given in Repair VRS6056, TASK 72-41-15-300-018 (REPAIR-018)

      1. Reject

    15. SUBTASK 72-41-15-220-568 Examine the Stage 10 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 - bottom edge radii in 0.047 in. (1.20 mm) edge margin

        1. Refer to the SPM TASK 70-35-03-300-501 to remove score

        3. Location 10 - dimensionally examine the edge

          1. Radius is between 0.020 and 0.030 in. (0.50 and 0.76 mm)

          1. Accept

          2. Other than in Step

          1. Repair external edge to radius between 0.020 and 0.030 in. (0.50 and 0.76 mm), refer to the SPM TASK 70-35-03-300-501

        4. Location 11 - dovetail edge radius in 0.087 in. (2.20 mm) edge margin

        1. Reject

        5. Location 12 - neck edge radius in 0.087 in. (2.20 mm) edge margin

        1. Reject

        6. Location 13 - under platform corner radius in 0.087 in. (2.20 mm) edge margin

          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 edge radius (location 12)

          2. More than in Step

          1. Reject

    16. SUBTASK 72-41-15-220-569 Examine the Stage 10 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 - bottom edge radii more than 0.047 in. (1.20 mm)

      1. Accept

      5. location 10 - bottom edge radii in less than 0.047 in. (1.20 mm)

      1. Refer to the SPM TASK 70-35-03-300-501 to remove marks

      6. Location 10 - dimensionally examine the edge.

        1. Radius is between 0.020 and 0.030 in. (0.50 and 0.76 mm)

        1. Accept

        2. Other than in Step

        1. Repair external edge to radius between 0.020 and 0.030 in. (0.50 and 0.76 mm), refer to the SPM TASK 70-35-03-300-501

      7. Do the identification marking again if removed by step (3)

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

      8. Do the Step, Step or Step again.

      1. Complete 0.047 in. (1.20 mm) or more edge margin

    17. Figure: Stage 10 rotor blades - inspection locations

    Stage 10 rotor blades - inspection locations

    Figure: Identify the stage 10 rotor blades

    Identify the stage 10 rotor blades

    Figure: Stage 10 rotor blades - chordal checks

    Stage 10 rotor blades - chordal checks

    Figure: Stage 10 rotor blades - measure length "X"

    Stage 10 rotor blades - measure length "X"

    Figure: Stage 10 Rotor Blade - Dovetail End Faces and Corners

    Stage 10 Rotor Blade - Dovetail End Faces and Corners

    Figure: Stage 10 Rotor Blade - Dovetail End Faces and Corners

    Stage 10 Rotor Blade - Dovetail End Faces and Corners

    Figure: Stage 10 Rotor Blade - Dovetail End Faces and Corners

    Stage 10 Rotor Blade - Dovetail End Faces and Corners

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Corrected Figure 3 dimensions. (17VG175)