TASK 72-50-22-200-001-A00 LPT Stage 7 Vane - Examine, Inspection-001

DMC:V2500-A0-72-50-2207-00A-300A-C|Issue No:002.00|Issue Date:2015-11-01

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 72-50-22-200-001-A00 LPT Stage 7 Vane - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-010

3A0487

01-010

3A1783

General

This TASK gives the procedure for the inspection of the stage 7 turbine vanes. For the other LP turbine nozzle vane parts, refer to TASK 72-50-22-200-000 (INSPECTION/CHECK-000).

Fig/item numbers in parentheses in the procedure agree with those used in 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. Refer to the SPM TASK 72-50-22-100-000 (CLEANING-000).

All 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 72-50-22-230-051. Do the crack test before the part is visually examined. Limits for cracks are given in the SUBTASK for each part.

A ** following any 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 data.

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 could be shown to be necessary at a later date.

All 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 numbers are in the SPM.

References

Refer to the SPM for data on these items.

Definitions of Damage, SPM TASK 70-02-02-350-501

Record and Control of the Lives of Parts, SPM TASK 70-05-00-220-501

Inspection of Parts, SPM TASK 70-20-00-200-501

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

NameManufacturerPart Number / IdentificationQuantityRemark
Dial indicator with ball insertLOCALDial indicator with ball insert
Dial gageLOCALDial gage
Dial indicator with needle insertLOCALDial indicator with needle insert
Illuminated magnifier (portable)LOCALIlluminated magnifier (portable)
Small hole gageLOCALSmall hole gage
External micrometerLOCALExternal micrometer
Dial caliperLOCALDial caliper

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-22-230-051-001 Do a Crack Test on the Stage 7 Turbine Vanes (Fluorescent Penetrant)

    1. Clean the parts. Refer to TASK 72-50-22-100-000 (CLEANING-000).

      2. Do the test for cracks on the part that are given below. Use the applicable penetrant procedure.

        PART

        TASK/SUBTASK

        Stage 7 turbine vanes

        1. Cracked vane outer cluster bonds.

          1. Any number, total one of a complete braze joint for each cluster provided inner cluster bonds are free of cracks

          1. Accept

          2. More than in Step

          1. Reject

        2. Cracked vane inner cluster bonds.

          1. Any number, total half of a complete braze joint for each cluster provided outer cluster bonds are free of cracks

          1. Accept

          2. More than in Step

          1. Reject

        3. Cracked inner or outer platforms at location A9.

          1. Maximum 0.010 in. (0.25 mm) in length

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

          2. More than in Step

          1. Reject

        4. Cracked airfoils

        1. Reject

    2. SUBTASK 72-50-22-230-051-002 Do a Crack Test on the Stage 7 Turbine Vanes (Fluorescent Penetrant)

    1. Clean the parts, Refer to TASK 72-50-22-100-000 (CLEANING-000).

      2. Do the test for cracks on the part given below. Use the applicable penetrant procedure.

        PART

        TASK/SUBTASK

        Stage 7 turbine vanes

        1. Cracked vane outer cluster bonds.

          1. Any number, total one of a complete braze joint for each cluster provided inner cluster bonds are free of cracks

          1. Accept

          2. More than in Step

          1. Reject

        2. Cracked vane inner cluster bonds.

          1. Any number, total half of a complete braze joint for each cluster provided outer cluster bonds are free of cracks

          1. Accept

          2. More than in Step

          1. Reject

        3. Cracked inner or outer platforms at location A9.

          1. Maximum 0.010 in. (0.25 mm) in length

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

          2. More than in Step

          1. Reject

        4. Cracked airfoils

        1. Reject

    3. SUBTASK 72-50-22-220-052 Examine the Stage 7 Turbine Vanes at Location A1 to A9 for Surface Damage

    1. Refer to Figure

      2. Examine the surface at location A1.

        1. Nicked, dented, pitted.

          1. Round bottom dents up to 0.020 in (0.508 mm) maximum depth, up to 10 percent of area A1

          1. Accept

          2. Nicked, pitted up to 0.005 in. (0.127 mm) maximum depth, no raised material

          1. Accept

          3. More than in Step or Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

      3. Examine the surface at location A2.

        1. Nicked, dented, pitted.

          1. Round bottom dents up to 0.010 in (0.254 mm) maximum depth

          1. Accept

          2. Nicked, pitted up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          3. More than in Step or Step

          1. Reject

      4. Examine the surface at location A3.

        1. Nicked, dented, pitted in area A3.1.

          1. Up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          2. More than in Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

        2. Nicked, dented, pitted in area A3.2.

          1. Up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          2. One round bottom dent per airfoil up to 0.010 in (0.254 mm) maximum depth

          1. Accept

          3. More than in Step or Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

      5. Examine the surface at location A4.

        1. Nicked, dented, pitted in area A4.1.

          1. Up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          2. More than in Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

        2. Nicked, dented, pitted in area A4.2.

          1. Up to 0.005 in (0.127 mm) maximum depth

          1. Accept

          2. Bent up 0.020 in (0.508 mm) maximum deflection and 0.700 in. (17.780 mm) total maximum length each airfoil

          1. Accept

          3. More than in Step or Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

      6. Examine the surface at location A5.

        1. Nicked, dented, pitted.

          1. Round bottom dents up to 0.010 in (0.254 mm) maximum depth

          1. Accept

          2. Nicked, pitted up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          3. More than in Step or Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

      7. Examine the surface at location A6.

        1. Nicked, dented, pitted.

          1. Round bottom dents up to 0.020 in. (0.508 mm) maximum depth, not visible from other side, up to 10 percent of surface of area A6

          1. Accept

          2. Nicked. pitted up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          3. More than in Step or Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

      8. Examine the surface at location A7.

        1. Nicked, dented, pitted.

          1. Round bottom dents up to 0.010 in. (0.254 mm) maximum depth

          1. Accept

          2. Nicked, pitted up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          3. More than in Step or Step

          1. Reject

      9. Examine the surface at location A8.

        1. Nicked, dented, pitted.

          1. Round bottom dents up to 0.020 in. (0.508 mm) maximum depth, not visible from other side, up to 10 percent of area A8

          1. Accept

          2. Nicked, pitted up to 0.005 in. (0.127 mm) maximum depth

          1. Accept

          3. More than in Step or Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

      10. Examine the surface at location A9.

        1. Nicked, dented, pitted

          1. Any number, no raised material. Up to 0.010 in. (0.254 mm) maximum depth

          1. Accept

          2. More than in Step

          1. Repair, VRS4031 TASK 72-50-22-300-001 (REPAIR-001).

    4. SUBTASK 72-50-22-220-053 Examine the Stage 7 Turbine Vanes Inner Honeycomb Seal

      1. Examine the inner honeycomb seal.

        1. Not bonded honeycombs

        1. Repair, VRS4032 TASK 72-50-22-300-002 (REPAIR-002) or Repair VRS4061 TASK 72-50-22-300-036 (REPAIR-036).

      2. Examine the inner honeycomb seal for wear. Use a dial gage magnetic stand, a dial indicator with a ball insert and a dial caliper.

        1. Worn, smooth wear pattern, maximum 0.394 in. (10.0 mm) in width and maximum 0.060 in. (1.5 mm) in depth

        1. Accept

        2. More than in Step

        1. Repair, VRS4032 TASK 72-50-22-300-002 (REPAIR-002) or Repair, VRS4061 TASK 72-50-22-300-036 (REPAIR-036).

    5. SUBTASK 72-50-22-220-054 Examine the Stage 7 Turbine Vanes Outer Honeycomb Seal

      1. Examine the outer honeycomb seal.

        1. Not bonded honeycombs

        1. Repair, VRS4033 TASK 72-50-22-300-003 (REPAIR-003).

      2. Examine the outer honeycomb seal for wear. Use a dial gage, a dial indicator with a ball insert and a dial caliper.

        1. Worn, smooth wear pattern, maximum 0.394 in. (10.0 mm) in width and maximum 0.060 in. (1.5 mm) in depth

        1. Accept

        2. More than in Step

        1. Repair, VRS4033 TASK 72-50-22-300-003 (REPAIR-003).

    6. SUBTASK 72-50-22-220-056 Examine the Inner and the Outer Platform End Faces of the Stage 7 Turbine Vanes for Wear

      1. Examine the inner and outer platform end faces for wear. Use adial gage and adial indicator with a needle insert.

        1. Fretted, maximum 0.002 in. (0.051 mm) in depth

        1. Accept

        2. More than in Step

        1. Reject

    7. SUBTASK 72-50-22-220-057 Examine the Stage 7 Turbine Vanes at Location D2

    1. Refer to Figure

      2. Measure the dimension D2. Use a dial caliper.

        1. Worn, between 0.3201 and 0.3141 in. (8.13 and 7.98 mm)

        1. Accept

        2. Other than in Step

        1. Repair, VRS4038 TASK 72-50-22-300-006 (REPAIR-006).

    8. SUBTASK 72-50-22-220-058 Examine the Stage 7 Turbine Vanes at Location D3

    1. Refer to Figure

      2. Measure the dimension D3. Use a small hole gage and an external micrometer.

        1. Worn, between 0.241 and 0.235 in. (6.12 and 5.97 mm)

        1. Accept

        2. Other than in Step

        1. Repair, VRS4036 TASK 72-50-22-300-004 (REPAIR-004).

    9. SUBTASK 72-50-22-220-059 Examine the Stage 7 Turbine Vanes at Location D4

    1. Refer to Figure

      2. Measure the dimension D4. Use a dial caliper.

        1. Worn, between 0.132 and 0.124 in. (3.35 and 3.15 mm)

        1. Accept

        2. Other than in Step

        1. Repair, VRS4037 TASK 72-50-22-300-005 (REPAIR-005).

    10. Figure: Examine the stage 7 turbine vanes

    Examine the stage 7 turbine vanes

    Figure: Examine the stage 7 turbine vanes

    Examine the stage 7 turbine vanes

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Correction of sequence

Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:LOCAL
Tool Number:Dial caliper
Tool Name:Dial caliper
Link not Found
Link not Found
Link not Found
Link not Found
Manufacturer Code:LOCAL
Tool Number:Illuminated magnifier (portable)
Tool Name:Illuminated magnifier (portable)
Link not Found