TASK 72-00-44-220-002 Stage 1 Turbine Nozzle Assembly - Examine The Stage 1 Turbine Nozzle Assembly Rear Face At Interface M-44, Inspection-002

DMC:V2500-A0-72-00-4400-00A-300A-B|Issue No:003.00|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 72-00-44-220-002 Stage 1 Turbine Nozzle Assembly - Examine The Stage 1 Turbine Nozzle Assembly Rear Face At Interface M-44, Inspection-002

General

The word "Reject" after an interface inspection statement requires that further detailed inspection or repair as applicable, of the affected area be accomplished using data in the applicable ATA section of the part in question. Contact IAE for FAA approved data if the referenced TASK is not in the manual.

Refer to TASK 72-00-00-200-001 (examine the modular/non-modular interfaces) before you do this TASK.

The policy that is necessary for inspection is given in the SPM TASK 70-20-01-200-501.

Installation of modules that are near the maximum interface limits can result in decreased module run times.

Use a bright light and a 3X magnifying glass to find surface cracks.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-44-220-068 Visually Examine the Support Assembly Outer Flange Bolt Holes at Location 1

    1. Refer to Figure.

      2. Cracks

      1. Reject

    2. SUBTASK 72-00-44-220-084 Examine the Support Assembly Outer Flange Bolt Holes at Location 2

    1. Refer to Figure.

    2. Clean the bolt holes per SPM TASK 70-11-26-300-503 (PW equivalent SPOP 208).

    3. Perform local FPI per SPM TASK 70-23-05-230-501 (high sensitivity) (or equivalent PW SPOP 70).

    4. Examine the flange bolt holes carefully.

      5. If you find any indication.

      1. Reject.

    3. SUBTASK 72-00-44-220-069 Visually Examine the Support Assembly Front and Rear of the Outer Flange Area at Location 2

    1. Refer to Figure.

      2. Round bottom dents up to 0.250 in. (6.350 mm) in diameter and 0.010 in. (0.254 mm) deep

      1. Accept

      3. Wear up to 25 percent of the contact surface

      1. Accept

      4. Other than Step or Step

      1. Reject

    4. SUBTASK 72-00-44-220-070 Visually Examine the Rear Turbine Seal of the Stage 1 Turbine Nozzle Assembly at Location 3

    1. Refer to Figure.

      2. Hardface is gone on less than 10 percent of the contact surface

      1. Accept

      3. Distortion

      1. Reject

      4. Loose on the vane support

      1. Reject

      5. Hardface is gone for more than 10 percent of the contact surface

      1. Reject

    5. SUBTASK 72-00-44-220-071 Visually Examine the Stage 1 Turbine Vanes at Location 4

    1. Refer to Figure.

      2. Concave or convex side axial cracks up to 1.500 in. (38.100 mm) long and/or concave or convex side radial cracks up to 1.500 in. (38.100 mm) long. All cracks must be less than 0.050 in. (1.270 mm) wide and must not have connected loop cracks more than 0.400 in. (10.160 mm) long or look like this will occur

      1. Accept

      3. One inner and/or outer platform crack less than 0.500 in. (12.700 mm) long. No platform radius cracks parallel to the fillet are permitted. A maximum of one crack on each vane is permitted that extends from the airfoil concave or convex surface to a platform

      1. Accept

      4. No limit to surface burns. No burn holes are permitted

      1. Accept.

      5. No limit to platform burns. No burn holes are permitted.

      1. Accept.

      6. Trailing edge burns less than 25 percent of chord length from the trailing edge and less than 0.500 in. (12.700 mm) (five cooling slots) in width except as given in Step.

      1. Accept.

      7. Trailing edge burns in the inner three cooling slots.

      1. Reject.

      8. No limit to chipped or spalled ceramic coat

      1. Accept

      9. No limit to round bottom dents up to 0.010 in. (0.254 mm) deep

      1. Accept

      10. Other than Step thru Step

      1. Reject

    6. SUBTASK 72-00-44-220-072 Visually Examine the Duct Segment at Location 5

    1. Refer to Figure.

      2. Damaged knife-edges

      1. Reject

      3. Blocked cooling holes

      1. Reject

    7. SUBTASK 72-00-44-220-073 Visually Examine the Bolt Holes of the Cooling Duct at Location 6

    1. Refer to Figure.

      2. Wear or cracks

      1. Reject

    8. SUBTASK 72-00-44-220-074 Visually Examine the Honeycomb Seal Lands at Location 7

    1. Refer to Figure.

      2. Knife edge rub less than 0.030 in. (0.762 mm)

      1. Accept

      3. Other than Step

      1. Reject

    9. SUBTASK 72-00-44-220-075 Visually Examine the Cooling Holes of the Cooling Duct at Location 8

    1. Refer to Figure.

      2. Blocked

      1. Reject

    10. SUBTASK 72-00-44-220-076 Measure the Outer Seal Land Diameters at Locations 9, 10 and 11

    1. Refer to Figure.

      2. If the diameter at location 9 is more than 11.515 in. (292.481 mm)

      1. Reject

      3. If the diameter at location 10 is more than 11.615 in. (295.021 mm)

      1. Reject

      4. If the diameter at location 11 is more than 11.715 in. (297.561 mm)

      1. Reject

    11. SUBTASK 72-00-44-220-077 Measure the Inner Seal Land Diameters at Locations 12 and 13

    1. Refer to Figure.

      2. If the diameter at location 12 is more than 9.095 in. (231.013 mm)

      1. Reject

      3. If the diameter at location 13 is more than 9.195 in. (233.553 mm)

      1. Reject

    12. Figure: Locations at Interface M-44

    Locations at Interface M-44

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Corrected the step reference. (20VC271)