TASK 72-00-31-220-002 LPC Fan Module - Examine The LPC Fan Module Front Face at Interface A-31, Inspection-002

DMC:V2500-A5-72-00-3100-02A-310A-B|Issue No:001.00|Issue Date:2014-05-01

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

V2500-A5

Common Information

TASK 72-00-31-220-002 LPC Fan Module - Examine The LPC Fan Module Front Face at Interface A-31, Inspection-002

General

Refer to TASK 72-00-00-200-000 (Examine the modular/non modular interfaces) (INSPECTION/CHECK-000), before you do this TASK.

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

The word 'reject' is used after an interface inspection statement to show that a higher level inspection and possible repair to the damaged part is necessary. Do the higher level inspection procedure as found in the applicable Chapter/Section/Subject of this manual on the damaged part(s). It is not necessary to do the higher level inspection on parts that are serviceable to the interface inspection standard.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-31-220-062 Visually Examine the Stage 1 Fan Blades at Location 1, and

    1. Refer to Figure, Figure, Figure and Figure.

      2. Visually examine the stage 1 fan blades at area Ar.

        1. Cracked

        1. Reject

        2. Nicked, dented, scored or scratched.

          1. Up to 0.008 in. (0.20 mm) in depth

          1. Accept

          2. More than in Step

          1. Repair, VRS1050 TASK 72-00-31-300-004 (REPAIR-004)

        3. Arc-burn

        1. Reject

        4. NOTE

          An arc burn is evident by a small circular or semi-circular heat affected area on the blade surface that may contain a shallow pitting, melting or cracking. Visually a dark blue oxide discolouration is associated with the heat affected area.

          Erosion

        1. Accept

      3. Visually examine the stage 1 fan blades at area Br.

        1. Cracked

        1. Reject

        2. Nicked, dented, scored or scratched.

          1. Up to 0.008 in. (0.20 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        3. Arc-burn

        1. Reject

      4. Visually examine the stage 1 fan blades at area At.

        1. Cracked

        1. Reject

        2. Nicked, dented, scored or scratched.

          1. Up to 0.025 in. (0.63 mm) in depth

          1. Accept

          2. More than in Step

          1. Repair, VRS1050 TASK 72-00-31-300-004 (REPAIR-004)

        3. Arc-burn

        1. Reject

        4. Erosion

        1. Accept

      5. Visually examine the stage 1 fan blades at area Bt.

        1. Cracked

        1. Reject

        2. Nicked, dented, scored or scratched.

          1. Up to 0.025 in. (0.63 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        3. Arc-burn

        1. Reject

      6. Visually examine the stage 1 fan blades at area Ct.

        1. Cracked

        1. Reject

        2. Nicked, dented, scored or scratched.

          1. Up to 0.008 in. (0.20 mm) in depth

          1. Accept

          2. More than in Step

          1. Reject

        3. Arc-burn

        1. Reject

      7. Visually examine the stage 1 fan blade tips at area F.

        1. Cracked

        1. Reject

        2. Nicked, dented, scored or scratched.

          1. Up to 0.0008 in. (0.20 mm)

          1. Accept

          2. More than in Step

          1. Reject

        3. Bent

        1. Reject

      8. Visually examine the stage 1 fan blades at the leading edge tips.

        1. Bent

        1. Reject

      9. NOTE

        This step is possible when the annulus fillers or the blade have been removed.

        Visually examine the stage 1 fan blades at area Cr.

        1. Cracked, nicked, dented, scored or scratched

        1. Reject

        2. Arc-burn

        1. Reject

      10. Visually examine the stage 1 fan blades convex and concave surfaces at the annulus line areas.

        1. Worn.

          1. Up to 0.008 in. (0.20 mm)

          1. Accept

          2. More than in Step

          1. Reject

      11. Visually examine the stage 1 fan blades.

        1. Bent.

          1. Up to one bend in a blade

          1. Accept

          2. More than in Step

          1. Reject

          3. Up to three bent blades in the fan rotor assembly

          1. Accept

          4. More than in Step

          1. Reject

          5. Blade untwist

          1. Reject

        2. Circumferential deviation (X).

          1. Not more than a maximum of 0.2 in. (5.08 mm) if axial length of bend (Y) is not less than eight times circumferential deviation (X)

          1. Accept

          2. Not more than a maximum of 0.2 in. (5.08 mm) if radial length of bend (Z) is not less than 15 times circumferential deviation (X)

          1. Accept

          3. Any bending does not go in to the panel area by more than 2.0 in. (50.8 mm) from the leading edge

          1. Accept

          4. Other than in Step, Step or Step

          1. Reject

      12. Visually examine the stage 1 fan blade tips and airfoil surfaces for discolouration/blueing.

        1. If there is discolouration/blueing on the blade tips and on no more than 0.25 in. (6.35 mm) of the adjacent airfoil surfaces radially from the blade tip

        1. Accept

        2. If there is discolouration/blueing on the blade tips and on more than 0.25 in. (6.35 mm) of the adjacent airfoil surfaces radially from the blade tip

        1. Reject

    2. SUBTASK 72-00-31-280-052 Do a Transient Acoustic Propagation Test of the Stage 1 Fan Blades

      1. Do a transient acoustic propagation test

      1. Refer to TASK 72-00-00-200-010 (INSPECTION/CHECK-010)

    3. SUBTASK 72-00-31-220-063 Visually Examine the LP Compressor Annulus Fillers at Location 2

    1. Refer to Figure.

      2. Platform.

        1. Missing anti-erosion coating

        1. Reject

        2. Cracked, dented, nicked and/or scratched

        1. Reject

      3. Rubber seals.

        1. Raised above the annulus line provided that they are not detached from the annulus filler and that they have no cracks

        1. Accept

        2. Detached (partially or completely).

          1. Up to 6

          1. Repair, VRS1108 TASK 72-00-31-300-003 (REPAIR-003)

          2. NOTE

            Only one seal per annulus fillers permitted to be partially or completely detached.

            More than in Step

          1. Reject

        3. Missing (partially or completely).

          1. Up to 6

          1. Accept

          2. NOTE

            Only one seal per annulus fillers permitted to be partially or completely detached.

            More than in Step

          1. Reject

    4. SUBTASK 72-00-31-220-064 Visually Examine the Front Retaining Ring Snap Diameter at Location 3

    1. Refer to Figure.

      2. Scored

      1. Reject

    5. SUBTASK 72-00-31-220-065 Visually Examine the Front Retaining Ring at Location 4

    1. Refer to Figure.

      2. Scored

      1. Reject

      3. Shank nut.

        1. Damaged

        1. Reject

    6. SUBTASK 72-00-31-220-066 Visually Examine the Washer Plate at Location 5

    1. Refer to Figure.

      2. Unbond

      1. Reject

    7. Figure: Locations at interface A-31

    Locations at interface A-31

    Figure: Stage 1 fan blades

    Stage 1 fan blades

    Figure: Stage 1 fan blades

    Stage 1 fan blades

    Figure: Stage 1 fan blades

    Stage 1 fan blades

Requirements After Job Completion

Follow-On Conditions

NONE