TASK 72-31-11-200-002-F00 LPC Fan Blade - Examine The LPC Fan Blade

DMC:V2500-A0-72-31-1101-00F-310A-C|Issue No:003.00|Issue Date:2019-02-01

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 72-31-11-200-002-F00 LPC Fan Blade - Examine The LPC Fan Blade

Effectivity

FIG/ITEM

PART NO.

01-300

6A7614

01-300

6A7654

01-300

6A7655

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 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 SPM.

References

Refer to 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 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 3R19401 Perspex template c/c Assembly C and D0AM53IAE 3R194011
IAE 3R19403 Perspex template c/c Assembly C and D0AM53IAE 3R194031

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-31-11-220-174 Examine the LPC Rotor Blade Assembly (01-300) for Damage

      1. Examine for electrical arc burns.

        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.

        1. Arc burned.

        1. Reject.

    2. SUBTASK 72-31-11-220-175 Examine the LPC Rotor Blade Assembly (01-300) for Crack 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 72-31-11-220-176 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 72-31-11-220-177 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 72-31-11-220-178 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 72-31-11-220-179 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.

    7. SUBTASK 72-31-11-220-180 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. Not more than 0.007 in. (0.17 mm) in depth.

            1. Accept.

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

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

            3. More than in Step.

            1. Reject.

          2. Critical area 1.

            1. Not more than 0.004 in. (0.10 mm) in depth.

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

            2. More than in Step and not more than 0.012 in. (0.30mm) in depth.

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

            3. More than in Step.

            1. Reject.

          3. Critical area 2.

            1. Not more than 0.007 in. (0.17 mm) in depth.

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

            2. More than in Step.

            1. Reject.

          4. Critical area 3.

            1. Not more than 0.004 in. (0.10 mm) in depth.

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

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

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

            3. More than in Step.

            1. Reject.

          5. Critical area 4.

            1. Not more than 0.004 in. (0.10 mm) in depth.

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

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

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

            3. More than in Step.

            1. Reject.

        2. Surface finish.

          1. Not more than 25 microinches (0.63 micrometers).

          1. Accept.

          2. More than in Step.

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

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

        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.

        1. Galled or scored.

          1. Not more than 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).

    8. SUBTASK 72-31-11-220-187 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.

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

            2. More than in Step.

            1. Reject.

        2. Bends.

          NOTE

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

          1. General.

            1. More than one bend.

            1. Reject.

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

            1. Reject.

            3. Untwist.

            1. Reject.

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

            1. 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, VRS1026 TASK 72-31-11-300-025 (REPAIR-025).

    9. SUBTASK 72-31-11-220-181 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. Bends.

          NOTE

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

          1. General.

            1. More than one bend.

            1. Reject.

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

            1. Reject.

            3. Untwist.

            1. Reject.

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

            1. 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, VRS1026 TASK 72-31-11-300-025 (REPAIR-025).

    10. SUBTASK 72-31-11-220-188 Examine the LPC 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, VRS1026 TASK 72-31-11-300-025 (REPAIR-025).

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

        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/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 72-31-11-220-182 Examine the LPC Rotor Blade Assembly (01-300) Dovetail

      CAUTION

      MAKE SURE THAT NMSB 72-0386 IS COMPLIED WITH.

    1. 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. 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 72-31-11-220-183 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 72-31-11-220-184 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 8.

        1. Unbond.

        1. Repair, VRS1022 TASK 72-31-11-300-009 (REPAIR-009).

        2. Missing.

        1. Repair, VRS1022 TASK 72-31-11-300-009 (REPAIR-009).

    14. SUBTASK 72-31-11-220-185 Examine the LPC Rotor Blade Assembly (01-300) Corner

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

      2. Examine the corner at location 9.

        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).

          2. More than in Step.

          1. Reject.

    15. SUBTASK 72-31-11-220-186 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 locations.

      1. Repair, VRS1023 TASK 72-31-11-300-021 (REPAIR 021).

    16. Figure: Locations on the LPC Rotor Blade Assembly

    Locations on the LPC Rotor Blade Assembly

    Figure: Locations on the LPC Rotor Blade Assembly

    Locations on the LPC Rotor Blade Assembly

    Figure: Locations on the LPC Rotor Blade Assembly

    Locations on the LPC Rotor Blade Assembly

    Figure: Locations on the LPC Rotor Blade Assembly

    Locations on the LPC Rotor Blade Assembly

    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
Change Type:

Added step reference (18VG342)

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 3R19401
Tool Name:IAE 3R19401 Perspex template c/c Assembly C and D
Manufacturer Code:0AM53
Tool Number:IAE 3R19403
Tool Name:IAE 3R19403 Perspex template c/c Assembly C and D