TASK 72-41-15-200-004-A00 HPC Stage 6 Rotor Blade - Examine, Inspection-004

DMC:V2500-A0-72-41-1506-00A-300A-C|Issue No:004.00|Issue Date:2018-02-01

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 72-41-15-200-004-A00 HPC Stage 6 Rotor Blade - Examine, Inspection-004

Effectivity

FIG/ITEM

PART NO.

02-170

6A3338

02-170

6A5586

02-170

6A8463

02-185

6A3339

02-185

6A5587

02-185

6A8464

02-200

6A3340C01

02-200

6A5583C01

02-200

6A8461

02-215

6A3340C01

02-215

6A5583C01

02-215

6A8461

02-217

6A3340C02

02-217

6A5583C02

02-217

6A8462

General

This TASK gives the procedure for the inspection of the HP compressor stage 6 rotor blades.

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.

A ** following repair referenced in this inspection indicates that the repair is not yet published in the current revision of the manual and the part must be rejected. Contact IAE for additional information concerning FAA approved repair date.

The procedure for those parts which must have a crack test is given in SUBTASK 72-41-15-230-054. 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 is 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 72-41-15-280-051 Identify the Stage 6 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 72-41-15-230-054-001 Examine the Stage 6 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 6 Rotor Blades

        SPM TASK 70-23-04-230-501

        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 72-41-15-220-074 Examine the Stage 6 Rotor Blades Concave and Convex Airfoil Surfaces at Locations 1 and 2

    1. Refer to Figure.

      2. Eroded

      1. Repair, VRS6012 TASK 72-41-15-300-004 (REPAIR-004)

      3. Nicks or dents

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

        1. Accept

        2. More than in Step

        1. Repair, VRS6012 TASK 72-41-15-300-004 (REPAIR-004)

    4. SUBTASK 72-41-15-220-199 Examine the Stage 6 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. Examine the surface finish of the rotor blades. Use 10 percent of the rotor blades that have been removed.

        1. Mean surface finish of 16 microinches (0.40 micrometers) or less.

        1. Accept.

        2. If any blade has a mean surface finish in excess of 16 microinches (0.40 micrometers) then all of the blades must be examined.

          1. Examine the surface finish of the rotor blades.

            1. Mean surface finish of 16 microinches (0.40 micrometers) or less.

            1. Accept.

            2. Mean surface finish greater than 16 microinches (0.40 micrometers).

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

    5. SUBTASK 72-41-15-220-137 Examine the Stage 6 Rotor Blades Leading Edge at Location 3

    1. Refer to Figure.

      2. Cracked or eroded

      1. Repair, VRS6012 TASK 72-41-15-300-004 (REPAIR-004)

      3. Nicks or dents

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

        1. Accept

        2. More than in Step

        1. Repair, VRS6012 TASK 72-41-15-300-004 (REPAIR-004)

    6. SUBTASK 72-41-15-220-075 Examine the Stage 6 Rotor Blades Trailing Edge at Location 4

    1. Refer to Figure.

      2. Cracked or eroded

      1. Repair, VRS6012 TASK 72-41-15-300-004 (REPAIR-004)

      3. Nicks or dents

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

        1. Accept

        2. More than in Step

        1. Repair, VRS6012 TASK 72-41-15-300-004 (REPAIR-004)

    7. SUBTASK 72-41-15-220-138 Examine the Stage 6 Rotor Blades Tips at Location 1049

    1. Refer to Figure.

      2. Cracked

      1. Repair, VRS6052 TASK 72-41-15-300-014 (REPAIR-014)

      3. Rubbed or worn

        1. Within the limits in 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, VRS6052 TASK 72-41-15-300-014 (REPAIR-014)

    8. SUBTASK 72-41-15-220-076 Examine the Stage 6 Rotor Blades Dovetail at Location 5

    1. Refer to Figure.

      2. Scored

      1. Reject

      3. Galled.

        1. Up to 0.002 in. (0.05 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    9. SUBTASK 72-41-15-220-077 Examine the Stage 6 Rotor Blades Cheeks at Locations 6 and 7

    1. Refer to Figure.

      2. Galled.

        1. Up to 0.002 in. (0.05 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    10. SUBTASK 72-41-15-220-078 Examine the Stage 6 Rotor Blades Platform at Location 8

    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

      3. Underside of platform fretted.

        1. Front section.

          1. Up to 0.008 in. (0.20 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        2. Rear section.

          1. Up to 0.012 in. (0.30 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

    11. SUBTASK 72-41-15-220-079 Examine the Stage 6 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 72-41-15-220-080 Examine the Stage 6 Rotor Locking Blades Slots at Locations 10

    1. Refer to Figure.

      2. Galled.

        1. Up to 0.012 in. (0.30 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    13. SUBTASK 72-41-15-220-155 Examine the Stage 6 Rotor Blades Chordal Checks

    1. Refer to Figure.

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

      1. Accept

      3. Less than value X

      1. Reject

    14. SUBTASK 72-41-15-220-448 Examine the Stage 6 Rotor Blades, Length Checks

    1. NOTE

      This is an alternative to measurments taken on the High Speed Grinding Machine to determine blade length acceptance limits.

      Refer to: Figure

    2. Measure the blade length "X".

      3. Between 2.329 and 2.336 in. (59.156 and 59.334 mm.)

      1. Accept

      4. Between 2.298 and 2.328 (58.369 and 59.131 mm.)

      1. Repair, VRS6052 TASK 72-41-15-300-014 (REPAIR-014).

      5. Less than the minimum repair limit given in Repair, VRS6052 TASK 72-41-15-300-014 (REPAIR-014).

      1. Reject

    15. SUBTASK 72-41-15-380-103 Replace the Dry Film Lubricant

      1. Apply the dry film lubricant to the blade dovetail

      1. Repair, VRS6495 TASK 72-41-15-300-049 (REPAIR-049)

    16. Figure: Stage 6 rotor blades - inspection locations

    Stage 6 rotor blades - inspection locations

    Figure: Identify the Stage 6 Rotor Blades

    Identify the Stage 6 Rotor Blades

    Figure: Stage 6 rotor blades - chordal checks

    Stage 6 rotor blades - chordal checks

    Figure: Stage 6 rotor blades - measure length "X"

    Stage 6 rotor blades - measure length "X"

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure to update SPM reference. (17VG061A)