TASK 72-41-15-200-005-C00 HPC Stage 7 Rotor Blade - Examine, Inspection-005

DMC:V2500-A0-72-41-1507-00C-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 72-41-15-200-005-C00 HPC Stage 7 Rotor Blade - Examine, Inspection-005

Effectivity

FIG/ITEM

PART NO.

02-270

6A6493

02-285

6A6494

02-300

6A6492C01

02-315

6A6492C01

02-317

6A6492C02

General

This TASK gives the procedure for the inspection of the HP compressor stage 7 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.

The procedure for those parts which must have a crack test is given in Step. 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 72-41-15-280-059 Identify the Stage 7 Rotor Blades

    1. Examine the part number on the base of the blade, refer to 1. Effectivity.

    2. SUBTASK 72-41-15-230-114-002 Examine the Stage 7 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 7 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 72-41-15-220-334 Examine the Stage 7 Rotor Blades Concave and Convex Airfoil Surfaces at Locations 1 and 2

    1. Refer to Figure.

      2. Nicked.

      1. Repair, VRS6013 TASK 72-41-15-300-005 (REPAIR-005).

      3. Nicks or dents.

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

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6013 TASK 72-41-15-300-005 (REPAIR-005).

    4. SUBTASK 72-41-15-220-335 Examine the Stage 7 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 is 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 72-41-15-220-336 Examine the Stage 7 Rotor Blades Leading Edge at Location 3

    1. Refer to Figure.

      2. Cracked or eroded

      1. Repair, VRS6013 TASK 72-41-15-300-005 (REPAIR-005)

      3. Nicks or dents

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

        1. Accept

        2. More than in Step

        1. Repair, VRS6013 TASK 72-41-15-300-005 (REPAIR-005)

    6. SUBTASK 72-41-15-220-337 Examine the Stage 7 Rotor Blades Trailing Edge at Location 4

    1. Refer to Figure.

      2. Cracked or eroded

      1. Repair, VRS6013 TASK 72-41-15-300-005 (REPAIR-005)

      3. Nicks or dents

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

        1. Accept

        2. More than in Step

        1. Repair, VRS6013 TASK 72-41-15-300-005 (REPAIR-005)

    7. SUBTASK 72-41-15-220-338 Examine the Stage 7 Rotor Blades Tips at Location 1050

    1. Refer to Figure.

      2. Cracked

      1. Repair, VRS6053 TASK 72-41-15-300-015 (REPAIR-015)

      3. Rubbed or worn

        1. Within the limits in TASK 72-41-10-040-001 (DISASSEMBLY-001, CONFIG-001)

        1. Accept

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

        1. Repair, VRS6053 TASK 72-41-15-300-015 (REPAIR-015)

    8. SUBTASK 72-41-15-220-339 Examine the Stage 7 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 72-41-15-220-340 Examine the Stage 7 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 72-41-15-220-341 Examine the Stage 7 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 72-41-15-220-342 Examine the Stage 7 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 72-41-15-220-343 Examine the Stage 7 Rotor Locking Blades Slots at Locations 10

    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

    13. SUBTASK 72-41-15-220-344 Examine the Stage 7 Rotor Blades Chordal Checks

    1. Refer to Figure and Figure.

      2. NOTE

        Minimum chordal widths must have profile on LE/TE as per example in Figure.

        Minimum 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 72-41-15-220-465 Examine the Stage 7 Rotor Blades, Length Checks

    1. NOTE

      This is an alternative to measurements taken on the High speed grinding machine to determine blade length acceptance limits.

      Refer to Figure.

    2. Measure the blade length "X".

      3. Between 1.7540 and 1.7610 in. (44.552 and 44.729 mm)

      1. Accept

      4. Between 1.7170 and 1.7530 in. (43.611 and 44.526 mm)

      1. Repair VRS6053, TASK 72-41-15-300-015 (REPAIR-015)

      5. Less than the minimum repair limit given in Repair VRS6053, TASK 72-41-15-300-015 (REPAIR-015)

      1. Reject

    15. SUBTASK 72-41-15-380-151 Replace the Dry Film Lubricant

      1. Apply the dry film lubricant to the blade dovetail

      1. Repair, VRS6496 TASK 72-41-15-300-050 (REPAIR-050)

    16. SUBTASK 72-41-15-220-596 Examine the Stage 7 Rotor Blade Dovetail End Faces and Corners

    1. Refer to Figure and Figure.

      2. NOTE

        Class identification marks as scores.

        Scored

        1. More than 0.002 in. (0.05 mm) in depth

        1. Reject

        2. Location 11 (dovetail end face)

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

          1. Accept

        3. Location 12 (bottom edge radii) - 0.039 in. (1.00 mm) margin to bottom face

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

          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

        4. Location 13 (dovetail edge radius) and location 14 (neck edge radius) - 0.047 in. (1.20 mm) margin to dovetail and neck profile

        1. Reject

        5. Location 15 (under platform fillet radius) - 0.067 in. plus or minus 0.008 in. (1.70 mm plus or minus 0.20 mm)

          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 14)

    17. SUBTASK 72-41-15-220-597 Examine the Stage 7 Rotor Blade Part Marking and Repair Symbol Location

    1. Refer to Figure.

    2. Part marking and repair symbol end face margin.

      3. Location 16 (bottom face)

      1. Accept

      4. location 12 (bottom edge radii)

      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 70-09-00-400-001. Use vibro-engraving equipment

    18. Figure: Stage 7 rotor blades - inspection locations

    Stage 7 rotor blades - inspection locations

    Figure: Stage 7 rotor blades - chordal checks

    Stage 7 rotor blades - chordal checks

    Figure: Stage 7 Rotor Blades - Measure Length "X"

    Stage 7 Rotor Blades - Measure Length "X"

    Figure: Details of typical LE/TE Accept/Reject profiles

    Details of typical LE/TE Accept/Reject profiles

    Figure: Stage 7 Rotor Blade - Dovetail End Faces and Corners

    Sheet 1

    Legend
    Stage 7 Rotor Blade - Dovetail End Faces and Corners

    Sheet 1

    Close

    Figure: Stage 7 Rotor Blade - Dovetail End Faces and Corners

    Sheet 2

    Legend
    Stage 7 Rotor Blade - Dovetail End Faces and Corners

    Sheet 2

    Close

    Figure: Stage 7 Rotor Blade - Dovetail End Faces and Corners

    Sheet 3

    Legend
    Stage 7 Rotor Blade - Dovetail End Faces and Corners

    Sheet 3

    Close

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

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