TASK 72-50-22-200-003-C00 LPT Stage 5 Vane - Examine, Inspection-003

DMC:V2500-A0-72-50-2205-00C-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-C00 LPT Stage 5 Vane - Examine, Inspection-003

Effectivity

FIG/ITEM

PART NO.

01-350

3A2305

General

This TASK gives the procedure for the inspection of the stage 5 turbine vanes.

Fig/item numbers in parentheses in the procedure agree with those used in the IPC.

A ** following any repair referenced in this inspection indicates that the repair is not yet published in the current revision of this manual and the part must be rejected. Contact IAE for additional information concerning FAA approved data.

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 the 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 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 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
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 72-50-22-230-095 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 parts that are given below. Use the applicable penetrant procedure.

      PART IDENT

      TASK/SUBTASK

      Stage 5 Turbine Vanes

      3. Cracked inner or outer platforms.

        1. Cracks up to 0.01 in. (0.254 mm) maximum depth

        1. Repair, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

        2. More than in Step

        1. Reject

      4. Cracked airfoils

      1. Reject

    2. SUBTASK 72-50-22-220-188 Examine the Airfoil, Inner and Outer Annulus/ Gaspath Surface of the Stage 5 Turbine Vanes for Coating Damage

      1. Damaged or not sufficient coating.

        1. Damaged or not sufficient coating in areas total less than 1.00 sq in (645.16 sq mm) per vane airfoil

        1. Repair, VRS4249 TASK 72-50-22-300-044 (REPAIR-044).

        2. Other than in Step

        1. Repair, VRS4250 TASK 72-50-22-300-045 (REPAIR-045) or Repair, VRS4262 TASK 72-50-22-300-046 (REPAIR-046).

      2. Sulphided, burned surfaces do the heat tint test per SPM TASK 70-28-00-280-501 and SPM TASK 70-28-01-280-501

      1. Repair, VRS4262 TASK 72-50-22-300-046 (REPAIR-046) or Repair, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

    3. SUBTASK 72-50-22-220-188-A00 Examine the Stage 5 Turbine Vanes at Location A1 tp 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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

      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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

        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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

      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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

        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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

      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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

      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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

      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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

      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, VRS4178 TASK 72-50-22-300-043 (REPAIR-043).

    4. SUBTASK 72-50-22-220-189 Examine the Stage 5 Turbine Vanes Inner honeycomb Seal

      1. Visually and dimensionally examine. Use dial gage, dial gage magnetic stand, dial indicator with ball insert and dial caliper.

        1. Unbonding.

          1. Any quantity unbonded from the vane

          1. Repair, VRS4331 TASK 72-50-22-300-063 (REPAIR-063).

        2. Worn.

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

          1. Accept

          2. More than in Step

          1. Repair, VRS4331 TASK 72-50-22-300-063 (REPAIR-063).

    5. SUBTASK 72-50-22-220-191 Examine the Inner and the Outer Platform End Faces of the Stage 5 Turbine Vanes for Wear

      1. Dimensionally examine. Use dial gage and dial indicator with needle insert.

        1. Fretted.

          1. 0.002 in. (0.051 mm) maximum depth

          1. Accept

          2. More than in Step

          1. Reject

    6. SUBTASK 72-50-22-220-190 Examine the Stage 5 Turbine Vane at Dimension D1 for Distortion

    1. Refer to Figure.

      2. Examine the diameter D1. Use IAE 2M14173 Axial deflection gage 1 off.

        1. Not less than 1.181 in. (30.00 mm)

        1. Accept

        2. Less than Step

        1. Reject

    7. SUBTASK 72-50-22-220-192 Examine the Stage 5 Turbine Vanes at Location D2 for Wear

    1. Refer to Figure

      2. Dimensionally examine at location D2. Use dial caliper.

        1. Worn.

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

          1. Accept

          2. Other than in Step

          1. Repair, VRS4173 TASK 72-50-22-300-048 (REPAIR-048).

    8. SUBTASK 72-50-22-220-193 Examine the Stage 5 Turbine Vanes at Location D3 for Wear

    1. Refer to Figure

      2. Dimensionally examine at location D3. Use small hole gage and external micrometer.

        1. Worn.

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

          1. Accept

          2. Other than in Step

          1. Reject

    9. SUBTASK 72-50-22-220-194 Examine the Stage 5 Turbine Vanes at Location D4 for Wear

    1. Refer to Figure

      2. Dimensionally examine at location D4. Use dial caliper.

        1. Worn.

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

          1. Accept

          2. Other than in Step

          1. Reject

    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