TASK 72-50-22-200-003-A00 LPT Stage 5 Vane - Examine, Inspection-003

DMC:V2500-A0-72-50-2205-00A-300A-C|Issue No:003.00|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 72-50-22-200-003-A00 LPT Stage 5 Vane - Examine, Inspection-003

Effectivity

FIG/ITEM

PART NO.

01-350

3A0025

General

This TASK gives the procedure for the inspection of the stage 5 turbine vanes. For the other LP turbine nozzle vanes, refer to TASK 72-50-22-200-000 (INSPECTION-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 70-20-00-200-501.

All the parts must be cleaned before any part is examined. Refer to 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 72-50-22-230-053. Do the crack test before the part is visually examined.

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

NOTE

Special tools are identified in the procedure by the tool primary number.

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
Small hole gageLOCALSmall hole gage
External micrometerLOCALExternal micrometer
Dial caliperLOCALDial caliper
IAE 2M14173 Axial deflection gage0AM53IAE 2M141731

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-22-230-053-001 Do a Crack Test on the Stage 5 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 IDENT TASK/SUBTASK

        Stage 5 Turbine Vanes

        1. Cracked vane outer cluster bonds.

          1. Any number, total one of a complete braze run for each assembly

          1. Accept

          2. More than in Step

          1. Reject

        2. Cracked vane inner cluster bonds.

          1. Any number, total a half of a complete braze run for each assembly

          1. Accept

          2. More than in Step

          1. Reject

        3. Cracked inner or outer platforms at location A9.

          1. Cracks up to 0.010 in. (0.254 mm)

          1. Repair, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

          2. More than in Step

          1. Reject

        4. Cracked airfoils

        1. Reject

    2. SUBTASK 72-50-22-230-053-002 Do a Crack Test on the Stage 5 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 IDENT

        TASK/SUBTASK

        Stage 5 Turbine Vanes

        1. Cracked vane outer cluster bonds.

          1. Any number, total one of a complete braze run for each assembly

          1. Accept

          2. More than in Step

          1. Reject

        2. Cracked vane inner cluster bonds.

          1. Any number, total a half of a complete braze run for each assembly

          1. Accept

          2. More than in Step

          1. Reject

        3. Cracked inner or outer platforms at location A9.

          1. Cracks up to 0.010 in. (0.254 mm)

          1. Repair, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

          2. More than in Step

          1. Reject

        4. Cracked airfoils

        1. Reject

    3. SUBTASK 72-50-22-220-070 Examine the Stage 5 Turbine Vanes at Location A1 to A9 for Syrface 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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

      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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

        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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

      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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

        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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

      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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

      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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

      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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

      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, VRS4050 TASK 72-50-22-300-014 (REPAIR-014).

    4. SUBTASK 72-50-22-220-071 Examine the Stage 5 Turbine Vanes Inner Honeycomb Seal

      1. Unbonding.

        1. Any quantity unbonded from vane

        1. Repair, VRS4051 TASK 72-50-22-300-015 (REPAIR-015)

      2. Wear. Use a dial gage, a dial indicator with a ball insert and a dial caliper.

        1. Smooth wear pattern, 0.394 in. (10.00 mm) maximum width and 0.060in. (1.5 mm) maximum depth

        1. Accept

        2. More than in Step

        1. Repair, VRS4051 TASK 72-50-22-300-015 (REPAIR-015).

    5. SUBTASK 72-50-22-220-073 Examine the Inner and the Outer Platform End Faces of the Stage 5 Turbine Vanes for Wear

      1. Fretted. Use adial gage and adial indicator with a needle insert.

        1. 0.002 in. (0.051 mm) maximum depth

        1. Accept

        2. More than in Step

        1. Reject

    6. SUBTASK 72-50-22-220-072 Examine the Stage 5 Turbine Vanes at Location D1 for Distortion

    1. Refer to Figure

      2. Measure the dimension D1. Use the IAE 2M14173 Axial deflection gage 1 off.

        1. Between 1.229 and 1.203 in. (31.22 and 30.56 mm)

        1. Accept

        2. Other than in Step

        1. Reject

    7. SUBTASK 72-50-22-220-074 Examine the Stage 5 Turbine Vanes at Location D2

    1. Refer to Figure

      2. Worn. Use a dial caliper.

        1. Between 0.3201 and 0.3141 in. (8.13 and 7.98 mm)

        1. Accept

        2. Other than in Step

        1. Repair, VRS4056 TASK 72-50-22-300-018 (REPAIR-018).

    8. SUBTASK 72-50-22-220-075 Examine the Stage 5 Turbine Vanes at Location D3

    1. Refer to Figure

      2. Worn. Use a small hole gage and an external micrometer.

        1. Between 0.158 and 0.150 in. (4.01 and 3.81 mm)

        1. Accept

        2. Other than in Step

        1. Repair, VRS4054 TASK 72-50-22-300-016 (REPAIR-016).

    9. SUBTASK 72-50-22-220-076 Examine the Stage 5 Turbine Vanes at Location D4

    1. Refer to Figure

      2. Worn. Use a dial caliper.

        1. Between 0.132 and 0.124 in. (3.35 and 3.15 mm)

        1. Accept

        2. Other than in Step

        1. Repair, VRS4055 TASK 72-50-22-300-017 (REPAIR-017).

    10. Figure: Examine the stage 5 turbine vanes

    Examine the stage 5 turbine vanes

    Figure: Examine the stage 5 turbine vanes

    Examine the stage 5 turbine vanes

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Correction of sequence

Manufacturer Code:0AM53
Enterprise Name:IAE INTERNATIONAL AERO ENGINES AG
BU Name:NULL
Building:SUITE 400
Street:628 HEBRON AVENUE
City:GLASTONBURY
State:CT
Zip Code:06033
Country:USA
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:0AM53
Tool Number:IAE 2M14173
Tool Name:IAE 2M14173 Axial deflection gage
Link not Found