TASK 72-50-10-200-010 LPT Stage 5 (Bladed) Rotor Assembly - Examine, Inspection-010

DMC:V2500-A0-72-50-1050-00A-310A-C|Issue No:002.00|Issue Date:2016-08-01

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 72-50-10-200-010 LPT Stage 5 (Bladed) Rotor Assembly - Examine, Inspection-010

General

This TASK gives the procedure for the inspection of the stage 5 LP turbine bladed rotor.

If there are signs of overheating, refer to TASK 72-50-32-200-008-B00 (INSPECTION/CHECK-008, CONFIG-002) before you do this inspection.

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 where necessary before any part is examined. Refer to TASK 72-50-10-100-008 (CLEANING-008).

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.

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 discarded parts 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.

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 data.

Reference

Refer to the SPM for data on these items.

Definition 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 in 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

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-50-10-220-177 Examine the Stage 5 Rotor Blades for Unlatching

    1. Refer to Figure.

      2. Examine all blades for signs of unlatching visually.

        1. Unlatched blades

        1. Disassemble rotor and reject all unlatched blades. Examine stage 5 disk for cracks. Refer to the SPM TASK 70-23-04-230-501. No cracks are permitted

          NOTE

          Blades are in unlatched condition if the outer shroud interlock between two blades is lost. A circumferential gap between two adjacent blades is visible at outer shrouds. Unlatched blades are axially not in line with the adjacent blade at outer shroud and knife edge seals.

    2. SUBTASK 72-50-10-220-137 Examine the Turbine Rotor for Contamination

      1. Contaminated with foreign matter

      1. Reject

    3. SUBTASK 72-50-10-220-138 Examine the Turbine Rotor for Overheating

      1. Signs of Overheating

      1. Reject

    4. SUBTASK 72-50-10-230-059 Examine the Turbine Rotor for Cracks

      1. Visually examine for cracks. Refer to the SPM TASK 70-21-01-220-501.

        1. Cracked in any area except at locations A15 and A16

        1. Reject

        2. Cracked at locations A15 or A16

          1. Up to a maximum 0.040 in. (1.0 mm) in depth

          1. Repair, VRS4351 TASK 72-50-10-300-006 (REPAIR-006)**

          2. More than in Step

          1. Reject

    5. SUBTASK 72-50-10-220-139 Examine the Turbine Rotor Blades for Surface Defects in Area A1 to A7

      NOTE

      1. This examination includes surface defects which are permitted per production standards, to prevent rejection of acceptable turbine rotor blades.

        All limits apply to each blade of the bladed rotor.

      2. Visually examine locations A1 to A7 for surface defects. Refer to the SPM TASK 70-21-01-220-501.

      3. Surface defects larger than 0.015 in. (0.38 mm) diameter must have a bottom which can be seen.

      4. Surface defects not larger than 0.015 in. (0.38 mm) must be nonbottomed.

      5. A cluster is a defect of four or more surface defects, clearly apart, which must be contained within a 0.200 in. (5.08 mm) diameter circle. In the cluster all surface defects must be 0.015 in. (0.38 mm) or less.

      6. If not differently specified, surface defects of 0.015 in. (0.38 mm) or less must be ignored if they are not found in linear alignment or clusters, or in areas where 0.015 in. (0.38 mm) is the maximum acceptable size.

      7. In areas where 0.015 in. (0.38 mm) is the maximum permitted size, surface defects 0.010 in. (0.25 mm) or less, not in linear alignment or clusters must be ignored.

      1. Visually examine the surface at location A1 (shroud inner and outer side, except fillet radii, hardface area and notch radii). Refer to Figure.

        1. Six defects, each on inner side, outer side or shroud edges 0.046 in. (1.17 mm) maximum diameter, 0.125 in. (3.18 mm) minimum separation

        1. Accept

        2. Five clusters, 0.250 in. (6.35 mm) minimum separation

        1. Accept

        3. More than in Step or Step

        1. Reject

      2. Visually examine the surface at location A2 (hardface areas) where possible. Refer to Figure.

        1. Two defects per area, 0.031 in. (0.79 mm) maximum diameter, clearly separated

        1. Accept

        2. Two linear defects including cracks or lack of fusion, 0.062 in. (1.58 mm) maximum length, clearly separated

        1. Accept

        3. More than in Step and Step or indications at break edge

        1. Reject

      3. Visually examine the surface at location A3 (Fillet radii). Refer to Figure.

        1. Six defects per side on inner or outer radius, 0.031 in. (0.79 mm) maximum diameter, 0.125 in. (3.18 mm) minimum separation

        1. Accept

        2. More than in Step

        1. Reject

      4. Visually examine the surface at location A4 (airfoil area, except fillet radii, leading and trailing edges). Refer to Figure.

        1. Eight defects total per side, at location A4.1, 0.031 in. (0.79 mm) maximum diameter, 0.125 in. (3.18 mm) minimum separation, at location A4.2, 0.046 in. (1.17 mm) maximum diameter, 0.125 in. (3.18 mm) minimum separation

        1. Accept

        2. Five clusters per side, 0.250 in. (6.35 mm) minimum separation

        1. Accept

        3. More than in Step or Step

        1. Reject

      5. Visually examine the surface at location A5 (leading and trailing edges). Refer to Figure.

        1. Six defects per side, per location for a total of 24 not back to back 0.015 in. (0.38 mm) maximum diameter 0.125 in. (3.18 mm) minimum separation

        1. Accept

        2. More than in Step

        1. Reject

      6. Visually examine the surface at location A6 (inner platform, inner and outer side). Refer to Figure.

        1. Six defects, each on inner side and outer side, 0.046 in. (1.17 mm) maximum diameter, 0.125 in. (3.18 mm) minimum separation

        1. Accept

        2. Five clusters, 0.250 in. (6.35 mm) minimum separation

        1. Accept

        3. More than in Step and Step

        1. Reject

      7. Visually examine the surface at location A7 (root). Refer to Figure.

        1. Six defects on each side, front or back, 0.046 in. (1.17 mm) maximum diameter, 0.125 in. (3.18 mm) minimum separation

        1. Accept

        2. More than in Step or defects in radii and break edges

        1. Reject

    6. SUBTASK 72-50-10-220-140 Examine the Turbine Rotor Blades for Surface Defects in Area A8, A9 and A10

    1. Refer to Figure.

      2. Visually examine the surface at location A8 for defects. Refer to Figure.

        1. Dented.

          1. Any number of dents, not more than 0.005 in. (0.13 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        2. Nicked or pitted

        1. Repair, VRS4350 TASK 72-50-10-300-005 (REPAIR-005)

      3. Visually examine the surface at location A9 for defects. Refer to Figure.

        1. Dented.

          1. Any number of dents, not more than 0.005 in. (0.13 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        2. Nicked or pitted.

          1. Any number of nicks, not more than 0.004 in. (0.1 mm) in depth

          1. Accept

          2. More than in Step

          1. Repair, VRS4350 TASK 72-50-10-300-005 (REPAIR-005)

      4. Visually examine the surface at location A10 for defects. Refer to Figure.

        1. Dented, nicked or pitted

        1. Reject

    7. SUBTASK 72-50-10-220-141 Examine the Turbine Rotor for Surface Damage in Area A11

    1. Refer to Figure.

      2. Visually examine the surface for damage in area A11. Refer to Figure.

        1. Nicked and dented.

          1. 0.0004 in. (0.01 mm) maximum depth without lifted material

          1. Accept

          2. More than in Step

          1. Repair, VRS4350 TASK 72-50-10-300-005 (REPAIR-005)

        2. Scratched.

          1. 0.0004 in. (0.01 mm) maximum depth if in a circumferential direction, 0.0002 in. (0.005 mm) maximum depth if in any other direction

          1. Accept

          2. More than in Step

          1. Repair, VRS4350 TASK 72-50-10-300-005 (REPAIR-005)

    8. SUBTASK 72-50-10-220-142 Examine the Turbine Rotor for Surface Damage in Area A12

    1. Refer to Figure.

      2. Visually examine the surface for damage in area A12. Refer to Figure.

        1. Nicked.

          1. 0.001 in. (0.03 mm) maximum depth without lifted material

          1. Accept

          2. More than in Step

          1. Reject

        2. Dented.

          1. 0.002 in. (0.05 mm) maximum depth without lifted material

          1. Accept

          2. More than in Step

          1. Repair, VRS4350 TASK 72-50-10-300-005 (REPAIR-005)

        3. Scratched.

          1. 0.002 in. (0.05 mm) maximum depth if in a circumferential direction, 0.0004 in. (0.01 mm) maximum depth if in any other direction

          1. Accept

          2. More than in Step

          1. Repair, VRS4350 TASK 72-50-10-300-005 (REPAIR-005)

    9. SUBTASK 72-50-10-220-143 Examine the Turbine Rotor for Surface Damage in Area A13

      1. Visually examine the surface in area A13 for damage. Refer to Figure.

        1. Nicked and dented.

          1. 0.0004 in. (0.01 mm) maximum depth

          1. Accept

          2. Other than in Step

          1. Reject

        2. Scratched.

          1. 0.0004 in. (0.01 mm) if in a circumferential direction, 0r 0.0002 in. (0.005 mm) maximum depth in any other direction

          1. Accept

          2. Other than in Step

          1. Reject

    10. SUBTASK 72-50-10-220-144 Examine the Turbine Rotor for Surface Damage in Area A14

      1. Examine the disk for damage in area A14, (at the tie bolt holes). Refer to Figure.

        1. Fretted.

          1. 0.002 in. (0.05 mm) maximum depth

          1. Accept

          2. More than in Step

          1. Reject

        2. Nicked, dented and scratched.

          1. Round bottom dents in lead-in radii 0.005 in. (0.127 mm) maximum depth

          1. Accept

          2. Other than in Step

          1. Reject

    11. SUBTASK 72-50-10-220-145 Examine Knife Edge Seals of the Turbine Rotor for Surface Damage

      1. Examine the airseal surface for damage at location A15. Refer to Figure.

        1. Nicked.

          1. If the depth of the nicks is 0.004 in. (0.1 mm)

          1. Accept

          2. More than in Step

          1. Repair, VRS4351 TASK 72-50-10-300-006 (REPAIR-006)**

        2. Dented.

          1. If the depth of the dents is 0.004 in. (0.1 mm)

          1. Accept

          2. More than in Step

          1. Repair, VRS4351 TASK 72-50-10-300-006 (REPAIR-006)**

        3. Bent.

          1. Up to 0.01 in. (0.25 mm) deflection and 0.040 in. (1.00 mm) depth, if contour is rounded

          1. Accept

          2. More than in Step

          1. Reject

        4. Chipped coating.

          1. Any number of areas, if total not more than 25 percent of circumference

          1. Accept

          2. More than in Step

          1. Reject

    12. SUBTASK 72-50-10-220-146 Examine the Knife Edge Seals of the Turbine Rotor Blades for Surface Damage

      1. Examine the surface at location A16. Refer to Figure.

        1. Dented.

          1. Up to maximum 0.010 in. (0.25 mm) in depth

          1. Repair, VRS4351 TASK 72-50-10-300-006 (REPAIR-006)**

          2. More than in Step

          1. Reject

        2. Nicked or pitted.

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

          1. Repair, VRS4351 TASK 72-50-10-300-006 (REPAIR-006)**

          2. More than in Step

          1. Reject

    13. SUBTASK 72-50-10-220-147 Examine the Turbine Rotor for Corrosion

      1. Visually examine the rotor for corrosion at location A17. Refer to Figure.

        1. Corroded

        1. Reject

    14. SUBTASK 72-50-10-220-188 Examine the Turbine Rotor Snap Diameter for Wear

      1. Visually examine the turbine rotor at location A18. Refer to Figure.

        1. Worn

        1. Reject

    15. SUBTASK 72-50-10-220-148 Examine the Turbine Rotor for Wear

      1. Measure the diameter D1 for wear at the seal fins at 120, 240 and 360 degrees. Get an average dimension. Refer to Figure.

        1. If the sum of the diameters is minimum 43.887 in. (1114.70 mm)

        1. Accept

        2. Less than in Step

        1. Reject

      2. Measure the diameter D2 for wear at 120, 240 and 360 degrees. Get an average dimension. Hand-load the Rotor-Blades in direction shown in Figure to get a correct result.

        1. Up to 36.0330 in. (915.24 mm) minimum

        1. Accept

        2. Less than in Step

        1. Reject

      3. Measure the diameter D3 for wear at 120, 240 and 360 degrees. Get an average dimension. Hand-load the Rotor-Blades in direction shown in Figure to get a correct result.

        1. Up to 36.2692 in. (921.24 mm) minimum

        1. Accept

        2. Less than in Step

        1. Reject

    16. Figure: Examine the LP Turbine Bladed Rotor Stage 5 Areas

    Examine the LP Turbine Bladed Rotor Stage 5 Areas

    Figure: Examine the LP Turbine Bladed Rotor Stage 5 Areas

    Examine the LP Turbine Bladed Rotor Stage 5 Areas

    Figure: Examine the LP Turbine Bladed Rotor Stage 5 Dimensions

    Examine the LP Turbine Bladed Rotor Stage 5 Dimensions

    Figure: Unlatched Blades at LP Turbine Bladed Rotor Stage 5

    Unlatched Blades at LP Turbine Bladed Rotor Stage 5

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Editorial changes -Typing Error