TASK 72-41-15-200-006-B00 HPC Stage 8 Rotor Blade - Examine, Inspection-006

DMC:V2500-A0-72-41-1508-00B-300A-C|Issue No:009.00|Issue Date:2021-02-01

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 72-41-15-200-006-B00 HPC Stage 8 Rotor Blade - Examine, Inspection-006

Effectivity

FIG/ITEM

PART NO.

02-370

6A4908

02-385

6A4909

02-400

6A4910C01

02-415

6A4910C01

02-417

6A4910C02

General

This TASK gives the procedure for the inspection of the HP Compressor Stage 8 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 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 72-41-15-230-113. 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 numbers are in SPM.

References

Refer to 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 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 72-41-15-230-113-001 Examine the Stage 8 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 8 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.

    2. SUBTASK 72-41-15-220-323 Examine the Stage 8 Rotor Blades Concave and Convex Airfoil Surfaces at Locations 1 and 2

    1. Refer to Figure.

      2. Nicked.

      1. Repair, VRS6014 TASK 72-41-15-300-006 (REPAIR-006).

      3. Scored.

        1. Along the Airfoil Chord - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch along the airfoil chord.

          1. Accept.

          2. If stylus hesitates or catches on the airfoil chord.

          1. Reject.

        2. Along the span of the airfoil surface.

        1. Reject.

    3. SUBTASK 72-41-15-220-324 Examine the Stage 8 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 micrometers) or less.

      1. Accept.

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

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

    4. SUBTASK 72-41-15-220-325 Examine the Stage 8 Rotor Blades Leading Edge at Location 3

    1. Refer to Figure.

      2. Cracked.

      1. Repair, VRS6014 TASK 72-41-15-300-006 (REPAIR-006).

      3. Nicked.

      1. Repair, VRS6014 TASK 72-41-15-300-006 (REPAIR-006).

      4. Eroded.

      1. Repair, VRS6014 TASK 72-41-15-300-006 (REPAIR-006).

    5. SUBTASK 72-41-15-220-326 Examine the Stage 8 Rotor Blades Trailing Edge at Location 4

    1. Refer to Figure.

      2. Nicked.

      1. Repair, VRS6014 TASK 72-41-15-300-006 (REPAIR-006).

      3. Eroded.

      1. Repair, VRS6014 TASK 72-41-15-300-006 (REPAIR-006).

    6. SUBTASK 72-41-15-220-327 Examine the Stage 8 Rotor Blades Tips at Location 1051

    1. Refer to Figure.

      2. Cracked.

      1. Repair, VRS9054 TASK 72-41-15-300-030 (REPAIR-030).

      3. Rubbed or worn.

        NOTE

        This is an alternative to Step. If measurements taken during limits from disassembly (TASK 72-41-10-040-001-B00 or TASK 72-41-10-040-001-C00) have not been supplied, Step can be skipped.

        1. Within the limits in TASK 72-41-10-040-001-B00 (DISASSEMBLY-001) or TASK 72-41-10-040-001-C00 (DISASSEMBLY-001).

        1. Accept.

        2. Identified as too short in TASK 72-41-10-040-001-B00 (DISASSEMBLY-001) or TASK 72-41-10-040-001-C00 (DISASSEMBLY-001).

        1. Repair, VRS9054 TASK 72-41-15-300-030 (REPAIR-030).

      4. Tip coating eroded.

        1. NOTE

          The instruction to apply a new layer is optional, refer to Repair, VRS6053 TASK 72-41-15-300-015, SUBTASK 72-41-15-340-054 (Repair-015).

          Apply a new layer to blade tip.

        1. Repair, VRS6153 TASK 72-41-15-300-034 (REPAIR-034).

    7. SUBTASK 72-41-15-220-328 Examine the Stage 8 Rotor Blades Dovetail at Location 5 (All Remaining Faces and/or Areas on Dovetail Excluding the Dovetail End Faces and Corners Addressed in Step)

      NOTE

      Damage of any kind is not allowed on the bedding areas (pressure faces) of the dovetail other than what is permitted in Step.

    1. Refer to Figure.

      2. Scored.

        1. Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch.

          1. Accept.

          2. If stylus hesitates or catches.

          1. Reject.

      3. Galled.

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

        1. Accept.

        2. More than in Step.

        1. Reject.

      4. Imperfections - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the imperfection does not display sharp edges, raised material, burrs, or a dark bottom.

        1. Accept.

        2. If stylus hesitates or catches, the imperfection displays sharp edges, raised material, burrs, or a dark bottom or the imperfection is located on the bedding area (pressure face).

        1. Reject.

      5. Nicks or dents - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the nick or dent does not display sharp edges, raised material, or burrs.

        1. Accept.

        2. If stylus hesitates or catches, the nick or dent displays sharp edges, raised material, burrs, or the nick or dent is located on the bedding area (pressure face).

        1. Reject.

    8. SUBTASK 72-41-15-220-329 Examine the Stage 8 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.

      3. Scored - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch.

        1. Accept.

        2. If stylus hesitates or catches.

        1. Reject.

      4. Imperfections - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the imperfection does not display sharp edges, raised material, burrs, or a dark bottom.

        1. Accept.

        2. If stylus hesitates or catches, the imperfection displays sharp edges, raised material, burrs, or a dark bottom.

        1. Reject.

      5. Nicks or dents - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the nick or dent does not display sharp edges, raised material, or burrs.

        1. Accept.

        2. If stylus hesitates or catches, the nick or dent displays sharp edges, raised material, or burrs.

        1. Reject.

    9. SUBTASK 72-41-15-220-330 Examine the Stage 8 Rotor Blades Platform at Location 8

    1. Refer to Figure.

      2. Nicks or dents.

        1. On top/gas washed face of the platform.

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

          1. Accept.

          2. More than in Step.

          1. Reject.

        2. On the bottom/non-gas washed face of the platform - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch and the nick or dent does not display sharp edges, raised material, or burrs.

          1. Accept.

          2. If stylus hesitates or catches, the nick or dent displays sharp edges, raised material, or burrs.

          1. Reject.

      3. Fretted.

        1. Front section on the bottom/non-gas washed face of the platform.

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

          1. Accept.

          2. More than in Step.

          1. Reject.

        2. Rear section on the bottom/non-gas washed face of the platform.

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

          1. Accept.

          2. More than in Step.

          1. Reject.

      4. Scored.

        1. On top/gas washed face of the platform - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch on the platform surface.

          1. Accept.

          2. If stylus hesitates or catches on the platform surface.

          1. Reject.

        2. On the bottom/non-gas washed face of the platform - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch on the platform surface and one or more of the following criteria is met.

            One score of any length.

            Two adjacent scores, one of which is less than 0.472 in. (12 mm) in length and the scores are clearly separated.

          1. Accept.

          2. If stylus hesitates or catches on the platform surface or the criteria in Step is not maintained.

          1. Reject.

      5. Imperfections.

        1. On the bottom/non-gas washed face of the platform - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch and the imperfection does not display sharp edges, raised material, burrs, or a dark bottom.

          1. Accept.

          2. If stylus hesitates or catches, the imperfection displays sharp edges, raised material, burrs, or a dark bottom.

          1. Reject.

    10. SUBTASK 72-41-15-220-331 Examine the Stage 8 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.

      3. Scored.

        1. Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

          1. If stylus does not hesitate or catch along the chord.

          1. Accept.

          2. If stylus hesitates or catches on the chord.

          1. Reject.

      4. Imperfections - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the imperfection does not display sharp edges, raised material, burrs, or a dark bottom.

        1. Accept.

        2. If stylus hesitates or catches, the imperfection displays sharp edges, raised material, burrs, or a dark bottom.

        1. Reject.

    11. SUBTASK 72-41-15-220-332 Examine the Stage 8 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.

    12. SUBTASK 72-41-15-220-333 Examine the Stage 8 Rotor Blades Chordal Checks

    1. Refer to Figure.

      2. 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.

    13. SUBTASK 72-41-15-220-459 Examine the Stage 8 Rotor Blades, Length Checks

    1. Refer to Figure.

    2. NOTE

      This is an alternative to measurements taken during disassembly (TASK 72-41-10-040-001-B00 or TASK 72-41-10-040-001-C00). If Step has been accomplished, Step can be skipped.

      Measure the blade length "X".

      3. Between 1.4680 in. and 1.4760 in. (37.287 mm and 37.490 mm).

      1. Accept.

      4. Between 1.4390 in. and 1.4680 in. (36.551 mm and 37.287 mm).

      1. Repair, VRS9054 TASK 72-41-15-300-030 (REPAIR-030).

      5. Less than the minimum repair limit given in Repair, VRS9054 TASK 72-41-15-300-030 (REPAIR-030).

      1. Reject.

    14. SUBTASK 72-41-15-220-619 Examine the Stage 8 Rotor Blades Front and Rear Lip at Location 17

    1. Refer to Figure.

      2. Scored - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch.

        1. Accept.

        2. If stylus hesitates or catches.

        1. Reject.

      3. Imperfections - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the imperfection does not display sharp edges, raised material, burrs, or a dark bottom.

        1. Accept.

        2. If stylus hesitates or catches, the imperfection displays sharp edges, raised material, burrs, or a dark bottom.

        1. Reject.

      4. Nicks and dents - Inspect with SPM TASK 70-21-00-220-501 with a 0.020 in. (0.50 mm) radius stylus.

        1. If stylus does not hesitate or catch and the nick or dent does not display sharp edges, raised material, or burrs.

        1. Accept.

        2. If stylus hesitates or catches, the nick or dent displays sharp edges, raised material, or burrs.

        1. Reject.

    15. SUBTASK 72-41-15-380-150 Replace the Dry Film Lubricant

      1. Apply the dry film lubricant to the blade dovetail.

      1. Repair, VRS6497 TASK 72-41-15-300-051 (REPAIR-051).

    16. SUBTASK 72-41-15-220-606 Examine the Stage 8 Rotor Blade Dovetail End Faces and Corners

    1. Refer to Figure and Figure.

      2. Scored.

        NOTE

        Deleted.

        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) - margin to dovetail and neck profile.

          1. Equal to or more than 0.039 in. (1.00 mm).

          1. Accept.

          2. Less than 0.039 in. (1.00 mm).

          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 72-41-15-220-607 Examine the Stage 8 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.

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

    18. Figure: Stage 8 Rotor Blades - Inspection Locations And Orientation

    Stage 8 Rotor Blades - Inspection Locations And Orientation

    Figure: Stage 8 Rotor Blades - Chordal Checks

    Stage 8 Rotor Blades - Chordal Checks

    Figure: Stage 8 Rotor Blades - Measure Blade Length "X"

    Stage 8 Rotor Blades - Measure Blade Length "X"

    Figure: Stage 8 Rotor Blade - Dovetail End Faces and Corners

    Sheet 1

    Legend
    Stage 8 Rotor Blade - Dovetail End Faces and Corners

    Sheet 1

    Close

    Figure: Stage 8 Rotor Blade - Dovetail End Faces and Corners

    Sheet 2

    Legend
    Stage 8 Rotor Blade - Dovetail End Faces and Corners

    Sheet 2

    Close

    Figure: Stage 8 Rotor Blade - Dovetail End Faces and Corners

    Sheet 3

    Legend
    Stage 8 Rotor Blade - Dovetail End Faces and Corners

    Sheet 3

    Close

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the inspection procedure and figure. (20VG156)