TASK 72-31-11-200-002-D00 LPC Fan Blade - Examine The LPC Fan Blade

DMC:V2500-A0-72-31-1101-00D-310A-C|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

All

Common Information

TASK 72-31-11-200-002-D00 LPC Fan Blade - Examine The LPC Fan Blade

Effectivity

FIG/ITEM

PART NO.

01-300

6A7649

01-300

6A7650

General

This TASK gives the procedure for the inspection of the LPC rotor blade assembly. For the other LP compressor blades and fillers parts, refer to TASK 72-31-11-200-000 (INSPECTION/CHECK-000).

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

All the parts must be cleaned before any part is examined. Refer to TASK 72-31-11-100-000 (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 test before the part is visually examined.

Following the crack test procedure make sure that fluorescent penetrant is thoroughly removed from fan blade root coating

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

Inspection of Parts, SPM TASK 70-20-01-200-501

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
IAE 3R19397 Perspex template c/c Assembly A and B0AM53IAE 3R193971
IAE 3R19399 Perspex template c/c Assembly A and B0AM53IAE 3R193991

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-31-11-220-148 Examine the LPC Rotor Blade Assembly (01-300) for Damage

      1. 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, remelting or cracking. Visually a dark blue oxide discoloration is associated with the heat-affected area.

        Examine for electrical arc burns.

        1. Arc burned

        1. Reject

    2. SUBTASK 72-31-11-280-056 Examine the LPC Rotor Blade Assembly (01-300) for Cracks Indications

      1. Transient acoustic propagating (TAP) examine for crack. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000).

        PART IDENT

        TASK/SUBTASK

        LPC rotor blade assembly

        TASK 72-00-00-200-000 (INSPECTION/CHECK)

        1. Evidence of vacuum

        1. Accept

        2. Lack of vacuum

        1. Reject

    3. SUBTASK 72-31-11-250-007 Examine the LPC Rotor Blade Assembly (01-300) for Leading Edge Cracks

      1. Do the eddy current inspection of the leading edge for cracks, refer to TASK 72-00-00-200-000 (INSPECTION/CHECK).

        PART IDENT

        TASK/SUBTASK

        LPC rotor blade assembly

        TASK 72-00-00-200-000 (INSPECTION/CHECK)

        1. Cracks

        1. Reject

    4. SUBTASK 72-31-11-270-010 Examine the LPC Rotor Blade Assembly (01-300) for Debond at Dovetail Location

      1. Do the ultrasonic inspection of the dovetail for debond at location 6. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK).

        PART IDENT

        TASK/SUBTASK

        LPC rotor blade assembly

        TASK 72-00-00-200-000 (INSPECTION/CHECK)

        1. Cracks

        1. Reject

    5. SUBTASK 72-31-11-220-149 Examine the LPC Rotor Blade Assembly (01-300) for Panel Defects

      1. Do the C scan inspection and examine for panel defects and cracks. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK).

        PART IDENT

        TASK/SUBTASK

        LPC rotor blade assembly

        TASK 72-00-00-200-000 (INSPECTION/CHECK)

        1. Panel Defects/Cracks

        1. Reject

    6. SUBTASK 72-31-11-230-077 Examine the LPC Rotor Blade Assembly (01-300) for Cracks

    1. Clean the parts. Refer to TASK 72-31-11-100-000, (CLEANING-000).

      2. Do the crack test on the parts that are given below.

        PART IDENT

        TASK/SUBTASK

        LPC rotor blade assembly

        1. Blade tips.

          1. If there are cracks on no more than 0.050 in (1.27 mm) of the adjacent airfoil surfaces radially from the blade tip

          1. Accept

          2. If there are cracks on more than 0.050 in (1.27 mm) of the adjacent airfoil surfaces radially from the blade tip

          1. Reject

        2. Rest of LPC rotor blade assembly

        1. Reject

      3. Following the crack test procedure make sure that fluorescent penetrant is thoroughly removed from fan blade root coating.

      1. Moderately clean the components (immersion), repeat three times. Refer to the SPM TASK 70-11-03-300-503, SUBTASK 70-11-03-300-001-001.

    7. SUBTASK 72-31-11-220-150 Examine the LPC Rotor Blade Assembly (01-300) Concave and Convex Airfoil Surfaces

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

      2. Examine the concave and convex airfoil surfaces at locations 1 and 2.

        1. Nicked, scored, scratched or dented.

          1. Non-critical areas.

          1. Up to 0.007 in. (0.17 mm) in depth

          2. Accept

          3. Between 0.007 in. and 0.015 in. (0.17 and 0.38 mm)

          4. Repair, VRS1003TASK 72-31-11-300-008 (REPAIR-008)

          2. Critical area 1.

          1. Up to 0.004 in. (0.10 mm) in depth without high metal

          2. Accept and apply Repair, VRS1724 (REPAIR-026)

          3. More than in Step and up to 0.012 in (0.30 mm) in depth

          4. Repair, VRS1003 TASK 72-31-11-300-008 (REPAIR-008)

          5. More than inStep

          6. Reject

          3. Critical area 2.

          1. Up to 0.007 in. (0.17 mm) in depth

          2. Repair, VRS1003, TASK 72-31-11-300-008 (REPAIR-008)

          3. More than in Step

          4. Reject

          4. Critical area 3.

          1. Up to 0.004 in. (0.10 mm) in depth

          2. Accept and apply Repair, VRS1724 TASK 72-31-11-300-026 (REPAIR-026)

          3. More than in Step and up to 0.015 in. (0.38 mm) in depth provided panel thickness is not more than 10 percent below the minimum limit quoted on the template after the blend repair

          4. Repair, VRS1003 TASK 72-31-11-300-008 (REPAIR-008)

          5. More than in Step

          6. Reject

          5. Critical area 4.

          1. Up to 0.004 in. (0.10 mm) in depth

          2. Accept and apply Repair, VRS1724 TASK 72-31-11-300-026 (REPAIR-026)

          3. More than in Step and up to 0.015 in. (0.38 mm) in depth provided panel thickness is not more than 5 percent below the minimum limit quoted on the template after the blend repair

          4. Repair, VRS1003 TASK 72-31-11-300-008(REPAIR-008)

          5. More than in Step

          6. Reject

        2. Surface finish.

          1. Up to 25 microinches (0.63 micrometers)

          1. Accept

          2. More than in Step

          1. Repair, VRS1025 TASK 72-31-11-300-010 (REPAIR-010)

      3. NOTE

        This inspection gives an acceptance limit with no dressing requirement. If airfoil dressing is specified at another part of inspection, then all damage must be repaired.

        Examine the concave and convex airfoil surfaces at locations 1 and 2 in the contact area with the annulus filler.

        1. Galled or scored.

          1. Up to 0.004 in. (0.10 mm) in depth

          1. Accept

          2. More than in Step

          1. Repair, VRS1003, TASK 72-31-11-300-008 (REPAIR-008)

        2. Polyurethane paint peeling.

          1. Any quantity of polyurethane paint peeling

          1. Accept

    8. SUBTASK 72-31-11-220-151 Examine the LPC Rotor Blade Assembly (01-300) Leading Edge

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

      2. Examine the leading edge at location 3.

        1. Eroded.

          1. Critical area

          1. Reject

          2. Non-critical area.

          1. Erosion not more than 0.138 in. (3.50 mm) reduction in chord

          2. Repair, VRS1064, TASK 72-31-11-300-030 (REPAIR-030)

          3. More than in (i)

          4. Reject

        2. NOTE

          The maximum number of bent blades in any fan rotor assembly must not be more than two.

          Bends.

          1. General.

          1. More than one bend

          2. Reject

          3. Bend contains kinks, creases, tears, cracks or nicks

          4. Reject

          5. Untwist

          6. Reject

          7. Transition between the undamaged airfoil and bent area is not smooth

          8. Reject

          2. Circumferential deviation (X) not more than a maximum of 0.20 in. (5.08 mm) and within the following limits (i) to (iii)

          1. Accept

        3. The axial length of the bend (Y) is not less than 8 times circumferential deviation (X).

        4. The radial length of bend (Z) is not less than 15 times circumferential deviation (X).

        5. Bends do not go into panel area by more than 2.0 in. (50.8 mm) from the leading edge.

          6. Circumferential deviation (X) greater than 0.20 in. (5.08 mm)

          1. reject

        3. Damage not in Step or Step

        1. Repair, VRS1002, TASK 72-31-11-300-007 (REPAIR-007)

    9. SUBTASK 72-31-11-220-152 Examine the LPC Rotor Blade Assembly (01-300) Trailing Edge

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

      2. Examine the trailing edge at location 4.

        1. NOTE

          The maximum number of bent blades in any fan rotor assembly must not be more than two.

          Bends.

          1. General.

          1. More than one bend

          2. Reject

          3. Bend contains Kinks, creases, tears, cracks or nicks

          4. Reject

          5. Untwist

          6. Reject

          7. Transition between the undamaged airfoil and bent area is not smooth

          8. Reject

          2. Circumferential deviation (X) not more than a maximum of 0.20 in. (5.08 mm) and within the following limits, (i) to (iii)

          1. Accept

        3. The axial length of the bend (Y) is not less than 8 times circumferential deviation (X).

        4. The radial length of bend (Z) is not less than 15 times circumferential deviation (X).

        5. Bends do not go into panel area by more than 2.0 in. (50.8 mm) from the trailing edge.

          6. Circumferential deviation (X) greater than 0.20 in. (5.08 mm)

          1. Reject

        2. Damage not in Step

        1. Repair, VRS1002 TASK 72-31-11-300-007 (REPAIR-007)

    10. SUBTASK 72-31-11-220-153 Examine the Rotor Blade Assembly (01-300) Blade Tip

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

      2. Examine the blade tip at location 5.

        1. Damaged

        1. Repair, VRS1002 TASK 72-31-11-300-007 (REPAIR-007)

      3. Examine the blade tips for discolouration/bluing/cracks caused by heat/contact with the fan case attrition lining.

        1. If there is discolouration/bluing 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/bluing 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

        3. If there is scoring on the blade tips caused by contact with the fan case attrition lining

        1. Accept

    11. SUBTASK 72-31-11-220-231 Examine the LPC Rotor Blade Assembly (01-300) Dovetail

    1. CAUTION

      MAKE SURE THAT NMSB 72-0387 IS COMPLIED WITH.

      Refer to Figure, Figure and Figure.

      2. Examine the dovetail at location 6 except location 21.

        1. Nicked, scored, scratched or dented.

          1. Less than 0.016 in. (0.42 mm) in depth

          1. Repair, VRS1066 TASK 72-31-11-300-031 (REPAIR-031)

          2. More than in Step

          1. Reject

      3. Examine the dovetail at location 21.

        1. Scoring of root flank Metco 58 coating.

          1. Less than 0.004 in. (0.1 mm) deep, not more than 0.006 in. (0.15 mm) wide and no longer than 0.6 in. (15 mm) long provided that the underlying titanium is not visible and/or that the location is not at the edge of bedding

          1. Accept

          2. More than in Step provided the underlying titanium is not scored

          1. Repair VRS1067 TASK 72-31-11-300-032, (REPAIR-032)

          3. More than in Step

          1. Reject

        2. Localised gouges or chips in Metco 58 coating.

          1. Less than 0.015 sqin (10 sqmm) in total area provided the underlying titanium is not visible or that the location is not at the edge of bedding

          1. Accept

          2. More than in Step provided the underlying titanium is not nicked or dented

          1. Repair, VRS1067 TASK 72-31-11-300-032, (REPAIR-032)

          3. More than in Step

          1. Reject

        3. Flaking or debond of Metco 58 from root flanks

        1. Repair, VRS1067 TASK 72-31-11-300-032, (REPAIR-032)

    12. SUBTASK 72-31-11-220-154 Examine the LPC Rotor Blade Assembly (01-300) Dovetail End Faces

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

      2. Examine the faces at location 7.

        1. Nicked, scored, scratched, dented or galled.

          1. Up to 0.006 in (0.15 mm) in depth

          1. Repair, VRS1066 TASK 72-31-11-300-031, (REPAIR-031)

          2. More than in Step

          1. Reject

    13. SUBTASK 72-31-11-220-155 Examine the LPC Rotor Blade Assembly (01-300) Rear Pin

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

      2. Examine the rear pin at location 8.

        1. Worn.

          1. Not more than 0.017 in (0.43 mm)

          1. Accept

          2. More than in Step

          1. Reject

    14. SUBTASK 72-31-11-220-156 Examine the LPC Rotor Blade Assembly (01-300) Pin

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

      2. Examine the pin at location 9.

        1. Loose

        1. Reject

    15. SUBTASK 72-31-11-220-157 Examine the LPC Rotor Blade Assembly (01-300) Chocking Pads

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

      2. Examine the chocking pads at location 10.

        1. Unbond

        1. Repair, VRS1028 TASK 72-31-11-300-013, (REPAIR-013)

        2. Missing

        1. Repair, VRS1028 TASK 72-31-11-300-013, (REPAIR-013)

    16. SUBTASK 72-31-11-220-158 Examine the LPC Rotor Blade Assembly (01-300) Corner

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

      2. Examine the corner at location 11.

        1. Nicked, scored, scratched, dented or galled.

          1. Up to 0.012 in (0.30 mm) in depth

          1. Repair, VRS1066 TASK 72-31-11-300-031, (REPAIR-031)

    17. SUBTASK 72-31-11-380-063 Apply Dry Film Lubricant at Dovetail Location

    1. Refer to Figure.

      2. On completion of all the blade repairs, apply dry film lubricant at dovetail location

      1. Repair, VRS1021 TASK 72-31-11-300-011, (REPAIR-011)

    18. Figure: Locations on the LPC Rotor Blade Assembly

    Sheet 1

    Legend
    Locations on the LPC Rotor Blade Assembly

    Sheet 1

    Close

    Figure: Locations on the LPC Rotor Blade Assembly

    Sheet 2

    Legend
    Locations on the LPC Rotor Blade Assembly

    Sheet 2

    Close

    Figure: Locations on the LPC Rotor Blade Assembly

    Sheet 3

    Legend
    Locations on the LPC Rotor Blade Assembly

    Sheet 3

    Close

    Figure: Locations on the LPC Rotor Blade Assembly

    Sheet 4

    Legend
    Locations on the LPC Rotor Blade Assembly

    Sheet 4

    Close

    Figure: LPC Rotor Blade Assembly

    LPC Rotor Blade Assembly

    Figure: LPC Rotor Blade Assembly

    LPC Rotor Blade Assembly

Requirements After Job Completion

Follow-On Conditions

NONE
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:0AM53
Tool Number:IAE 3R19397
Tool Name:IAE 3R19397 Perspex template c/c Assembly A and B
Manufacturer Code:0AM53
Tool Number:IAE 3R19399
Tool Name:IAE 3R19399 Perspex template c/c Assembly A and B