TASK 72-41-15-200-001-A00 HPC Stage 3 Rotor Blade - Examine, Inspection-001

DMC:V2500-A0-72-41-1503-00A-300A-C|Issue No:008.00|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 72-41-15-200-001-A00 HPC Stage 3 Rotor Blade - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-200

6A3513

01-200

6A3938

General

This TASK gives the procedure for the inspection of the HP compressor stage 3 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

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 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 72-41-15-230-051 Examine the Stage 3 Rotor Blades for Cracks

    1. Refer to Figure and Figure.

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

      NOTE

      During examination of the part special attention must be given to the inspection locations as given in Step to Step.

      3. Do the fluorescent penetrant inspection for cracks.

        PART IDENT

        TASK/SUBTASK

        Stage 3 Rotor Blades

        1. Leading edge (Location 3).

          1. Cracked.

          1. Refer to Step.

        2. Airfoil tips (Location 1046).

          1. Cracked.

          1. Refer to Step.

        3. Groove (Location 1010).

          1. Cracked.

          1. Reject. Reject the cracked blade and the full stage 3 rotor blade set from which it was assembled with.

        4. Dovetail (Location 12) top edge of bedding.

          1. Cracked.

          1. Reject. Reject only the cracked blade(s). Do not reject the full set.

        5. NOTE

          If you can see fluorescent pentrant indications in the dovetail shank, the part must be examined under white light at 6x to 30x binoculars for cracks.

          Dovetail shank (Location 13).

          1. Cracked.

          1. Reject. Reject only the cracked blade(s). Do not reject the full set.

        6. All remaining areas.

          1. Cracked.

          1. Reject. Reject only the cracked blade(s). Do not reject the full set.

    2. SUBTASK 72-41-15-220-051 Examine the Stage 3 Rotor Blades Concave and Convex Airfoil Surfaces at Locations 1 and 2

    1. Refer to Figure.

      2. Eroded.

      1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

      3. Nicks or dents.

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

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

    3. SUBTASK 72-41-15-220-196 Examine the Stage 3 Rotor Blades Concave and Convex Airfoil Surface Finish at Locations 1 and 2

    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 the set.

        2. If any blade is in excess of 16 microinches (0.40 micrometers) then all of the blades must be assessed.

          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).

    4. SUBTASK 72-41-15-220-128 Examine the Stage 3 Rotor Blades Leading Edge at Location 3

    1. Refer to Figure.

      2. Cracked or eroded.

      1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

      3. Nicks or dents.

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

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

    5. SUBTASK 72-41-15-220-052 Examine the Stage 3 Rotor Blades Trailing Edge at Location 4

    1. Refer to Figure.

      2. Eroded.

      1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

      3. Nicks or dents.

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

        1. Accept.

        2. More than in Step.

        1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

    6. SUBTASK 72-41-15-220-129 Examine the Stage 3 Rotor Blades Tips at Location 1046

    1. Refer to Figure.

      2. Cracked.

      1. Repair, VRS6049 TASK 72-41-15-300-011 (REPAIR-011).

      3. Rubbed or worn.

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

        1. Accept.

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

        1. Repair, VRS6049 TASK 72-41-15-300-011 (REPAIR-011).

    7. SUBTASK 72-41-15-220-053 Examine the Stage 3 Rotor Blades Groove at Location 1010

    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. Worn.

        1. If the width of the retaining plate groove is between 0.1016 in. and 0.1055 in. (2.58 mm and 2.68 mm).

        1. Accept.

        2. If the width is more than in Step.

        1. Reject.

    8. SUBTASK 72-41-15-220-054 Examine the Stage 3 Rotor Blades Dovetail at Location 5

    1. Refer to Figure.

      2. Scored.

      1. Reject.

      3. Galled.

      1. Reject.

    9. SUBTASK 72-41-15-220-130 Examine the Stage 3 Rotor Blade Dovetail at Location 12

    1. Refer to Figure.

      2. Scored.

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

        1. Accept.

        2. More than in Step.

        1. Reject.

      3. Galled.

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

        1. Accept.

        2. More than in Step.

        1. Reject.

    10. SUBTASK 72-41-15-220-055 Examine the Stage 3 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.

    11. SUBTASK 72-41-15-220-056 Examine the Stage 3 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.

    12. SUBTASK 72-41-15-220-057 Examine the Stage 3 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.

    13. SUBTASK 72-41-15-220-058 Examine the Stage 3 Rotor Blades Layer at Location 10

    1. NOTE

      The applicable clapper hard coating repair must be done, if the repair limits apply, as the minimum necessary for continued service.

      Refer to Figure.

      2. Wear.

      1. Repair, VRS6236 TASK 72-41-15-300-035 (REPAIR-035) or Repair, VRS9297 TASK 72-41-15-300-058 (REPAIR-058) and Repair, VRS6616 TASK 72-41-15-300-052 (REPAIR-052) if necessary.

    14. SUBTASK 72-41-15-220-059 Examine the Stage 3 Rotor Blades Balancing Plug Hole at Location 11

    1. Refer to Figure.

      2. Burrs.

      1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

      3. Scored.

      1. Repair, VRS6009 TASK 72-41-15-300-001 (REPAIR-001).

    15. SUBTASK 72-41-15-220-152 Examine the Stage 3 Rotor Blades Chordal Checks

    1. Refer to Figure.

      2. Minimum chord Z1, Z2 and Z3 at Location A, B and C to the value of X.

      1. Accept.

      3. Less than value X.

      1. Reject.

    16. SUBTASK 72-41-15-220-484 Examine the Stage 3 Rotor Blades, Length Checks

    1. NOTE

      This is an alternative method 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 5.706 in. (144.920 mm) and 5.711 in. (145.047 mm).

      1. Accept.

      4. Between 5.677 in. (144.190 mm) and 5.705 in. (144.919 mm).

      1. Repair, VRS6049 TASK 72-41-15-300-011 (REPAIR-011).

      5. Less than the minimum repair limit given in Repair, VRS6049 TASK 72-41-15-300-011 (REPAIR-011).

      1. Reject.

    17. SUBTASK 72-41-15-220-527 Examine the Stage 3 Rotor Blades Clapper Height at Location 10

    1. Refer to Figure, Figure and Figure.

    2. Do a clapper height measurement for each blade.

      3. Concave clapper height from datum F.

        1. Dimension (2).

          1. Less than 4.230 in. (107.45 mm) and more than 4.199 in. (106.65 mm)

          1. Accept.

          2. Other than in Step.

          1. Reject.

        2. Dimension (1).

          1. Between 0.0780 in. (1.975 mm) and 0.124 in. (3.15 mm) less than dimension 2.

          1. Accept.

          2. Other than in Step.

          1. Reject.

      4. Convex clapper height from datum F.

        1. Dimension (4).

          1. Less than 4.222 in. (107.25 mm) and more than 4.191 in. (106.45 mm).

          1. Accept.

          2. Other than in Step.

          1. Reject.

        2. Dimension (3).

          1. Between 0.0780 in. (1.975 mm) and 0.124 in. (3.15 mm) less than dimension 4.

          1. Accept.

          2. Other than in Step.

          1. Reject.

    18. SUBTASK 72-41-15-380-076 Apply the Dry Film Lubricant to the Stage 3 Rotor Blades

      1. Apply the dry film lubricant to the blade dovetail

      1. Repair, VRS6486 TASK 72-41-15-300-046 (REPAIR-046).

    19. Figure: Stage 3 Rotor Blades - Inspection Locations

    Stage 3 Rotor Blades - Inspection Locations

    Figure: Stage 3 Rotor Blades - Inspection Locations

    Stage 3 Rotor Blades - Inspection Locations

    Figure: Stage 3 rotor blades - chordal checks

    Stage 3 rotor blades - chordal checks

    Figure: Stage 3 Rotor Blades - Measure Length "X"

    Stage 3 Rotor Blades - Measure Length "X"

    Figure: Stage 3 Blade Clapper Height Dimension

    Stage 3 Blade Clapper Height Dimension

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedural steps to add repair reference. (19VG078)