TASK 72-32-85-200-001-D00 Fan Case - Examine, Inspection-001

DMC:V2500-A0-72-32-8501-00D-300A-C|Issue No:003.00|Issue Date:2018-11-01

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 72-32-85-200-001-D00 Fan Case - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-100

5W0149

01-100

5W0169

01-100

5W0172

01-100

5W0195

01-100

5W0197

01-100

5W0198

01-100

5W0218

01-100

5W0220

01-100

5W0221

01-100

5W0223

01-100

5W0225

01-100

5W0226

01-100

5W0307

01-100

5W0313

General

This TASK gives the procedure for the inspection of the fan case assembly.

The policy that is necessary for inspection is given in SPM TASK 70-20-10-200-501.

All parts must be cleaned before any part is examined. Refer to SPM TASK 70-10-00-100-501.

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 parts is visually examined. Limits for cracks are given in the SUBTASK for each part.

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.

Part 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 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 the data on these items

Definitions of damages, SPM TASK 70-02-02-350-501

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

NOTE

To identify the consumable materials refer to the PCI.

NOTE

Special tools are identified in the procedure by the tool primary number.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
IAE 2J13056 Gage, wear0AM53IAE 2J130561
Tool tappingLOCALIAE 1N204441

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-224 SILICONE ADHESIVE POLYESTERTAPELOCALCoMat 02-224

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-32-85-230-056 Examine the Fan Case Assembly for Cracks

    1. NOTE

      For the method to the part, refer to SPM TASK 70-11-26-300-503.

      Clean the part. Refer to TASK 72-32-85-100-000 (CLEANING-000).

      2. Do the crack test on the part that is given below. Use the applicable penetrant inspection procedure.

        PART IDENT

        TASK/SUBTASK

        Fan case assembly

        NOTE

        Use CoMat 02-224 SILICONE ADHESIVE POLYESTERTAPE and polyethylene sheet to protect anti-ice impact, attrition and acoustic linings.

        1. Cracked.

        1. Reject.

    2. SUBTASK 72-32-85-220-107 Examine the Fan Case Assembly (01-100) Flange

    1. Refer to Figure.

      2. Examine the flange at Location 1.

        1. Galled.

        1. Repair, VRS1805 TASK 72-32-85-300-042 (REPAIR-042).

        2. Bolthole edge burred.

        1. Repair, VRS1805 TASK 72-32-85-300-042 (REPAIR-042).

        3. Elongated bolthole due to wear at Flange FE.

          NOTE

          Except four holes of 0.629 inch (16.000 mm) in diameter at 3 o'clock and 9 o'clock positions and the bushing hole at Location 11.

        1. Repair, VRS1992 TASK 72-32-85-300-058 (REPAIR-058).

    3. SUBTASK 72-32-85-220-108 Examine the Fan Case Assembly (01-100) Outer Surface and Inner Surface

    1. Refer to Figure.

      2. Examine the outer surface and inner surface at locations 2 and 3.

        1. Nicked or dented.

        1. Repair, VRS1805 TASK 72-32-85-300-042 (REPAIR-042).

        2. Bolthole edge burred.

        1. Repair, VRS1805 TASK 72-32-85-300-042 (REPAIR-042).

    4. SUBTASK 72-32-85-220-109 Examine the Fan Case Assembly (01-100) Blue Filler

    1. Refer to Figure.

      2. Examine the blue filler at Location 4.

        1. Erosion

        1. Repair, VRS1823 TASK 72-32-85-300-039 (REPAIR-039)

    5. SUBTASK 72-32-85-220-110 Examine the Fan Case Assembly (01-100) Hook

    1. Refer to Figure.

      2. Examine the hook at Location 5.

        1. Scored or dented

        1. Repair, VRS1805 TASK 72-32-85-300-042 (REPAIR-042)

    6. SUBTASK 72-32-85-220-111 Examine the Fan Case Assembly (01-100) Flexible Ring Surface

    1. Refer to Figure.

      2. Examine the flexible ring surface at Location 6.

        1. Nicked, dented or scored.

        1. Repair, VRS1805 TASK 72-32-85-300-042 (REPAIR-042).

    7. SUBTASK 72-32-85-220-112 Examine the Fan Case Assembly (01-100) Attrition Lining

    1. Refer to Figure and Figure.

      2. Examine the attrition lining at Location 7.

        1. Wear, Rubs.

          1. Use IAE 2J13056 Gage, wear. Less than 0.158 in. (4.00 mm) in depth around circumference.

          1. Accept.

          2. More than in Step and damaged to the depth of the Glass Reinforced Composite (GRC) layer.

          1. Repair, VRS1819 TASK 72-32-85-300-019 (REPAIR-019).

        2. Gouges, scores and dent.

          1. Damage to the depth of the GRC layer.

          1. Repair, VRS1819 TASK 72-32-85-300-019 (REPAIR-019).

          2. Damaged deeper than the GRC layer and not more than 4 sqin. (25.8 sqcm) attrition lining.

          1. Repair, VRS1820 TASK 72-32-85-300-020 (REPAIR-020).

          3. More than in Step.

          1. Repair, VRS1840 TASK 72-32-85-300-036 (REPAIR-036).

          4. Unbond.

            NOTE

            Check the attrition lining for unbond by tap testing. The attrition lining is tapped or hit lightly, with a metallic coin (not less than 1 in. (25.4 mm) ) or small metal rod with a ball end or Tool tapping. If the unbond is present directly below the point of impact, a change in pitch (hollow sound) will be emitted from the attrition lining. Plot the result of the tap test, if necessary.

            1. Damaged area is less than 20 percent of the total area of each attrition lining.

            1. Repair, VRS1820 TASK 72-32-85-300-020 (REPAIR-020).

            2. More than in Step.

            1. Repair, VRS1840 TASK 72-32-85-300-036 (REPAIR-036).

    8. SUBTASK 72-32-85-220-113 Examine the Fan Case Assembly (01-100) Anti Ice Impact Panel

    1. Refer to Figure.

      2. Examine the anti ice impact panel at Location 8.

        1. Tear, peeled and dent the GRC skin.

          1. Less than 30 percent of each anti ice impact panels.

          1. Repair, VRS1821 TASK 72-32-85-300-037 (REPAIR-037).

          2. More than in Step.

          1. Repair, VRS1841 TASK 72-32-85-300-038 (REPAIR-038).

        2. Loose, unbond.

          NOTE

          Check the anti-ice impact panel for unbond by tap testing. The anti-ice impact panel is tapped or hit lightly, with a metallic coin (not less than 1 in. (25,4 mm) ) or small metal rod with a ball end or Tool tapping. If the unbond is present directly below the point of impact, a change in pitch (hollow sound) will be emitted from the anti-ice impact panel. Plot the result of the tap test, if necessary.

          1. Less than 30 percent of each anti-ice impact panels.

          1. Repair, VRS1821 TASK 72-32-85-300-037 (REPAIR-037).

          2. More than in Step.

          1. Repair, VRS1841 TASK 72-32-85-300-038 (REPAIR-038).

    9. SUBTASK 72-32-85-220-114 Examine the Fan Case Assembly (01-100) Acoustic Lining

    1. Refer to Figure.

      2. Examine the acoustic lining at Location 9.

        1. Crack, tear, score and peeled or missing perforation sheet.

          1. Less than 20 percent of the total circumference of the acoustic linings.

          1. Repair, VRS1822 TASK 72-32-85-300-040 (REPAIR-040).

          2. More than in Step.

          1. Repair, VRS1842 TASK 72-32-85-300-041 (REPAIR-041).

        2. Smooth dent.

          1. Any smooth dent less than 0.1 in. (2.54 mm) in depth and less than 1.0 in. (25.4 mm) in diameter.

          1. Accept.

          2. More than Step and less than 20 percent of the total circumference of the acoustic linings.

          1. Repair, VRS1822 TASK 72-32-85-300-040 (REPAIR-040).

          3. More than in Step.

          1. Repair, VRS1842 TASK 72-32-85-300-041 (REPAIR-041).

        3. Dent, kinked or raised perforation sheet.

          1. Less than 20 percent of the total circumference of the acoustic linings.

          1. Repair, VRS1822 TASK 72-32-85-300-040 (REPAIR-040).

            2. More than in Step.

            1. Repair, VRS1842 TASK 72-32-85-300-041 (REPAIR-041).

        4. Loose, unbond.

          NOTE

          Check the acoustic lining for unbond by tap testing. The acoustic lining is tapped or hit lightly, with a metallic coin (not less than 1 in. (25.4 mm) ) or small metal rod with a ball end or Tool tapping. If the unbond is present directly below the point of impact, a change in pitch (hollow sound) will be emitted from the acoustic lining. Plot the result of the tap test, if necessary.

          1. Less than 20 percent of the total circumference acoustic linings.

          1. Repair, VRS1822 TASK 72-32-85-300-040 (REPAIR-040).

          2. More than in Step.

          1. Repair, VRS1842 TASK 72-32-85-300-041 (REPAIR-041).

    10. SUBTASK 72-32-85-220-159 Examine the Fan Case Assembly (01-100) Tower Shaft Tube Bore

    1. Refer to Figure

      2. Examine the tower shaft tube bore at location 10.

        1. Worn.

          1. If the diameter is up to 2.189 in. (55.61 mm)

          1. Accept

          2. More than in Step.

          1. Repair, VRS1413 TASK 72-32-85-300-047 (REPAIR-047).

    11. SUBTASK 72-32-85-220-160 Examine the Fan Case Assembly (01-100) Bushes

    1. Refer to Figure.

      2. Examine the bush at Location 11.

        1. Worn on the bore.

          1. If the diameter is up to 0.633 in. (16.1 mm).

          1. Accept.

          2. More than in Step.

          1. Repair, VRS1712 TASK 72-32-85-300-046 (REPAIR-046).

        2. Nicked, dented, scored and scratched on the bore.

          1. Up to 0.02 in. (0.5 mm).

          1. Accept.

          2. More than in Step

          1. Repair, VRS1712 TASK 72-32-85-300-046 (REPAIR-046).

        3. Axially loose missing bushes.

        1. Repair, VRS1712 TASK 72-32-85-300-046 (REPAIR-046). Rotation of the bush is permissible.

    12. SUBTASK 72-32-85-220-161 Examine the Fan Case Assembly (01-100) Bushes

    1. Refer to Figure.

      2. Examine the bush at Location 12.

        1. Worn on the bore.

          1. If the diameter is up to 0.194 in. (4.95 mm).

          1. Accept.

          2. More than in Step

          1. Repair, VRS1712 TASK 72-32-85-300-046 (REPAIR-046).

        2. Nicked, dented, scored and scratched.

          1. Up to 0.02 in. (0.5 mm).

          1. Accept.

          2. More than in Step

          1. Repair, VRS1712 TASK 72-32-85-300-046 (REPAIR-046).

        3. Axially loose missing bushes

        1. Repair, VRS1712 TASK 72-32-85-300-046 (REPAIR-046). Rotation of the bush is permissible.

    13. SUBTASK 72-32-85-220-162 Examine the Fan Case Assembly (01-100) Anchor Nuts

    1. Refer to Figure.

      2. Examine the anchor nuts at Location 13.

        1. Loose or damaged.

        1. Repair, VRS1418 TASK 72-32-85-300-012 (REPAIR-012).

    14. SUBTASK 72-32-85-220-163 Examine the Fan Case Assembly (01-100) Screw Thread Inserts of the Oil Seal Tube Mount Land

    1. Refer to Figure.

      2. Examine the screw thread inserts at Location 14.

        1. Loose or damaged.

        1. Repair, VRS1419 TASK 72-32-85-300-013 (REPAIR-013).

    15. SUBTASK 72-32-85-220-192 Examine the Fan Case Assembly (01-100) V-Groove

    1. Refer to Figure.

      2. Examine the V-Groove at Location 15.

        1. Nicked, dented, pitted, galled or scored

        1. Repair, VRS1800 TASK 72-32-85-300-055 (REPAIR-055).

    16. Figure: Fan Case Assembly - Inspection/Check

    Fan Case Assembly - Inspection/Check

    Figure: Inspection Tool of Attrition Lining

    Inspection Tool of Attrition Lining

    Figure: Locations on the Fan Case Assembly

    Locations on the Fan Case Assembly

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the inspection criteria for fan case assembly and figure 1. (93VJ801H)

Change Type:

Added PN 5W0313. (93VJ801J)

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:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:LOCAL
Supply Number:CoMat 02-224
Type:sp01
Supply Short Name:CoMat 02-224 SILICONE ADHESIVE POLYESTER TAPE
Supply Name:CoMat 02-224 SILICONE ADHESIVE POLYESTERTAPE
Specification Groups:
Doc NumberType
FLASHTAPE 2
Suppliers:
ManufacturerRemarks
LOCAL
IE532
85670
Link not Found
Manufacturer Code:0AM53
Tool Number:IAE 2J13056
Tool Name:IAE 2J13056 Gage, wear