DOC AIRBUS | AMM A320FInspection of the Fan Case Assembly [IAE]
TASK 72-32-85-200-010-B
Inspection of the Fan Case Assembly
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 72-32-85-941-067-A ** ON A/C NOT FOR ALL
Subtask 72-32-85-220-054-A ** ON A/C NOT FOR ALL
Subtask 72-32-85-410-102-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 13:00:44 UTC
Inspection of the Fan Case Assembly
1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE |
| No specific | AR | MAT - WORK |
| No specific | AR | WARNING NOTICE(S) |
| IAE1N20444 | 1 | TOOL-TAPPING |
| IAE2J13056 | 1 | GAGE - WEAR |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| FOR [1000EM1] (ENGINE-1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [1000EM2] (ENGINE-2) | |
| 447AL, 448AR, 461AL, 462AR | |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 71-13-00-010-010-A | Opening of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 71-13-00-410-010-A | Closing of the Fan Cowls 437AL(447AL),438AR(448AR) |
| TASK 72-00-00-200-022-B | Inspection of the LP Compressor Fan Blades and Fan Case Acoustic Linings |
| TASK 72-31-00-000-010-B | Removal of the LP Compressor (Fan) Module |
| TASK 72-31-00-400-010-B | Installation of the LP Compressor (Fan) Module |
| TASK 72-31-11-000-010-B | Removal of the LP Compressor Fan Blades |
| TASK 72-31-11-400-010-C | Installation of the LP Compressor Fan Blades |
| TASK 72-32-85-300-020-A | Repair by Replacement of the Acoustic Linings - VRS1845 |
| TASK 72-32-85-300-021-A | Repair by Replacement of the Anti-ice Impact Panels - VRS1844 |
| TASK 72-32-85-300-022-A | Repair by Replacement of the Attrition Linings - VRS1843 |
| TASK 72-32-85-300-042-A | Repair of the Fan Case - VRS1806 - Post SBE 72-0160 |
| TASK 72-32-85-300-047-B | Repair of the Fan Case Acoustic Linings by bonding - VRS1511 |
| TASK 72-32-85-300-802-A | Repair of the Fan Case V-Groove - VRS1995 |
| TASK 72-32-85-350-015-A | Repair of the Fan Case - VRS1824 - PRE SBE 72-0160 |
| TASK 72-32-85-350-016-A | Repair of the Fan Case Acoustic Lining - VRS1827 |
| TASK 72-32-85-350-017-A | Repair of the Fan Case Anti-ice Impact Panels - VRS1826 |
| TASK 72-32-85-350-018-A | Repair of the Fan Case Attrition Lining Down to the GRC Layer - VRS1825 |
| TASK 72-32-85-350-019-A | Repair of the Blue Filler - VRS1828 |
| TASK 72-32-85-350-042-A | Repair of the Fan Case Attrition Lining Below the Glass Reinforced Composite (GRC) Layer - VRS1946 |
| TASK 78-30-00-040-012-A | Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance |
| TASK 78-30-00-440-012-A | Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance |
| TASK 78-32-00-010-010-A | Opening of the Thrust Reverser Halves |
| TASK 78-32-00-410-010-A | Closing of the Thrust Reverser Halves |
Wear measurement of the Attrition LiningSubtask 72-32-85-941-067-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
Subtask 72-32-85-010-062-A ** ON A/C NOT FOR ALL (1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
B. Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR
Subtask 72-32-85-040-052-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR
C. Deactivate the Thrust Reverser
Subtask 72-32-85-010-060-A ** ON A/C NOT FOR ALL WARNING:
MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012). D. Get Access
(1) Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 72-32-85-010-102-A ** ON A/C NOT FOR ALL (1) Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
E. Remove the LP Compressor (fan) Module (Ref. AMM TASK 72-31-00-000-010) , or Remove the LP Compressor (Fan) Blades and Fillers (Ref. AMM TASK 72-31-11-000-010).
Subtask 72-32-85-941-132-A ** ON A/C NOT FOR ALL F. Put the support equipment in to position
(1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in to position to give access to the engine for the inspection task.
(2) Put the MAT - WORK in to position in the fan case.
4. Procedure(1) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in to position to give access to the engine for the inspection task.
(2) Put the MAT - WORK in to position in the fan case.
NOTE: Make sure that the workmat has sufficient dimensions to give full protection to the lower half of the fan case surface.
Subtask 72-32-85-220-054-A ** ON A/C NOT FOR ALL
A. Wear Measurement of the Attrition Linings
(1) Measure the depth of damage using the IAE2J13056 GAGE - WEAR off, or equivalent.
(a) Position IAE2J13056 GAGE - WEAR on the fan case so that gage body straddles the attrition lining.
(b) Align the rear corner of the wear gage front side with the split line of the hook and the attrition lining.
(c) Measure the basic distance between the measurement surface of the IAE2J13056 GAGE - WEAR and the original surface of the attrition lining with the vernier caliper or equivalent depth measurement equipment.
(d) Measure the damaged area with same as above procedure.
(2) Calculate the actual damage depth
A = Basic distance (Result of step (1) (c)).
B = Distance of damaged area (Result of step (1) (d)).
C = Actual depth of damage.
Subtask 72-32-85-210-065-A ** ON A/C NOT FOR ALL (1) Measure the depth of damage using the IAE2J13056 GAGE - WEAR off, or equivalent.
(a) Position IAE2J13056 GAGE - WEAR on the fan case so that gage body straddles the attrition lining.
(b) Align the rear corner of the wear gage front side with the split line of the hook and the attrition lining.
(c) Measure the basic distance between the measurement surface of the IAE2J13056 GAGE - WEAR and the original surface of the attrition lining with the vernier caliper or equivalent depth measurement equipment.
(d) Measure the damaged area with same as above procedure.
(2) Calculate the actual damage depth
A = Basic distance (Result of step (1) (c)).
B = Distance of damaged area (Result of step (1) (d)).
C = Actual depth of damage.
| C = B - A |
B. Examine the Attrition Lining (6) for Rubs, Gouges and Scores
(1) Blade tip rubs are acceptable, if:
(a) The maximum depth of the rubbing is less than 0.158 in. (4.01 mm).
(2) Wear, gouges and galls on the attrition linings are acceptable, if the following limits are not exceeded.
(a) The Glass Reinforced Composite (GRC) layer is not damaged.
(b) The maximum dimension of the damaged area is less than 3.00 in. (76.2 mm) measured in the axial width and 10.0 in. (254.0 mm) in the circumferential width.
(c) A total of five areas of damage within (a) and (b) are acceptable, if they are separated by a distance equal to the maximum dimension of the nearest damaged area.
(d) Any number of damaged areas within (a) whose maximum dimensions are less than 1.0 in. (25.4 mm) measured in the axial width and 1.5 in. (38.1 mm) in the circumferential width are acceptable, if they are separated by at least 3.0 in. (76.2 mm) of undamaged lining.
(3) Circumferential scores on the attrition linings are acceptable, if the limits that follow are not exceeded.
(a) The GRC layer is not damaged.
(b) Scores of any length are acceptable, if the lining around them is undamaged.
(4) Damage more than in (1), (2) and (3) is acceptable, if:
(a) The GRC layer is not damaged.
(b) The linings will have been repaired within 10 flight hours or 5 flight cycles whichever is sooner
(a) If the damaged area is less than 20 percent of each attrition lining
(7) Unbond on the linings is acceptable, if the limits that follow are not exceeded:
(b) The unbond area(s) are less than 5 percent of each attrition lining panel, without area of step (a).
(c) The lining panel will be repaired within 10 flight hours or 5 flight cycles whichever is the sooner (Ref. AMM TASK 72-32-85-350-042).
(8) Unbond more than (7) is acceptable if:
(a) The damaged area is less than 10 percent of the total area of each attrition lining panel.
(b) The lining panel will be repaired within 5 flight hours or 2 flight cycles whichever is the sooner (Ref. AMM TASK 72-32-85-350-042).
(9) Unbond more than (8) (Ref. AMM TASK 72-32-85-350-042).
Subtask 72-32-85-210-066-A ** ON A/C NOT FOR ALL (1) Blade tip rubs are acceptable, if:
(a) The maximum depth of the rubbing is less than 0.158 in. (4.01 mm).
(2) Wear, gouges and galls on the attrition linings are acceptable, if the following limits are not exceeded.
(a) The Glass Reinforced Composite (GRC) layer is not damaged.
(b) The maximum dimension of the damaged area is less than 3.00 in. (76.2 mm) measured in the axial width and 10.0 in. (254.0 mm) in the circumferential width.
(c) A total of five areas of damage within (a) and (b) are acceptable, if they are separated by a distance equal to the maximum dimension of the nearest damaged area.
(d) Any number of damaged areas within (a) whose maximum dimensions are less than 1.0 in. (25.4 mm) measured in the axial width and 1.5 in. (38.1 mm) in the circumferential width are acceptable, if they are separated by at least 3.0 in. (76.2 mm) of undamaged lining.
(3) Circumferential scores on the attrition linings are acceptable, if the limits that follow are not exceeded.
(a) The GRC layer is not damaged.
(b) Scores of any length are acceptable, if the lining around them is undamaged.
(4) Damage more than in (1), (2) and (3) is acceptable, if:
(a) The GRC layer is not damaged.
(b) The linings will have been repaired within 10 flight hours or 5 flight cycles whichever is sooner
- repair, refer to VRS1825 (Ref. AMM TASK 72-32-85-350-018)
(a) If the damaged area is less than 20 percent of each attrition lining
- repair, refer to VRS1946 (Ref. AMM TASK 72-32-85-350-042).
- repair with VRS1946 (Ref. AMM TASK 72-32-85-350-042).
- After the repair VRS1946, repair within 10 flight hours or 5 flight cycles whichever is sooner, refer to VRS1843 (Ref. AMM TASK 72-32-85-300-022).
(7) Unbond on the linings is acceptable, if the limits that follow are not exceeded:
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 IAE1N20444 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 results of the tap test, if necessary.
(a) The unbond area(s) are less than 5 percent at the edge of each attrition lining panel. (b) The unbond area(s) are less than 5 percent of each attrition lining panel, without area of step (a).
(c) The lining panel will be repaired within 10 flight hours or 5 flight cycles whichever is the sooner (Ref. AMM TASK 72-32-85-350-042).
(8) Unbond more than (7) is acceptable if:
(a) The damaged area is less than 10 percent of the total area of each attrition lining panel.
(b) The lining panel will be repaired within 5 flight hours or 2 flight cycles whichever is the sooner (Ref. AMM TASK 72-32-85-350-042).
(9) Unbond more than (8) (Ref. AMM TASK 72-32-85-350-042).
C. Examine the Acoustic Linings (4) for unbond, cracks, dents and scores
(2) Scores not more than 0.002 in. (0.05 mm) in depth and less than 1 in. (25.4 mm) in length are acceptable.
(3) Damage more than in (2) is acceptable, if:
(a) The depth of the scores does not exceed 0.004 in. (0.1 mm).
(b) The linings will have been repaired within 500 flight hours or 250 flight cycles whichever is sooner - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016).
(4) Smooth dents in the linings are acceptable, if the limits that follow are not exceeded:
(a) The dents are less than 2.17 in. (55.0 mm) in diameter.
(b) The bond between the perforated skin and honeycomb is not broken.
(5) Damage more than in (4) is acceptable, if:
(a) The dents are less than 0.22 in. (5.5 mm) in depth.
(b) The linings will be repaired within 350 flight hours or 400 flight cycles whichever is sooner (Ref. AMM TASK 72-32-85-350-016).
(6) Damage more than in (3) or (5) is acceptable, if:
(a) The linings will be repaired within 250 flight hours or 125 flight cycles whichever is sooner (Ref. AMM TASK 72-32-85-350-016).
(7) Visually examine the bond of the acoustic lining, if you can see the unbond of the acoustic lining - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1511 (Ref. AMM TASK 72-32-85-300-047).
(8) Unbond in the linings is acceptable, if the limits that follow are not exceeded:
(b) The unbond area(s) are less than 20 percent in area B of each acoustic lining panel.
(c) The lining will be repaired within 50 flight hours or 25 flight cycles whichever is sooner - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1511 (Ref. AMM TASK 72-32-85-300-047).
(9) Unbond more than (8) is acceptable, if:
(a) The damaged area is less than 30 percent of the total area of each acoustic lining panel.
(b) The lining will be repaired within 10 flight hours or 5 flight cycles whichever is sooner - repair, refer to VRS1827 or VRS1511 (Ref. AMM TASK 72-32-85-350-016).
(10) Unbond more than (9) and perforated skin still attached - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1511 (Ref. AMM TASK 72-32-85-300-047).
(11) Missing perforated skin is acceptable, if:
(a) An inspection of the LP Compressor Fan Blades is accomplished (Ref. AMM TASK 72-00-00-200-022).
(b) Not more than one acoustic lining perforated skin is completely missing.
(c) The lining will be repaired within 10 flight hours or 5 flight cycles whichever is the sooner - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1845 (Ref. AMM TASK 72-32-85-300-020).
(12) Damage more than (9) - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1845 (Ref. AMM TASK 72-32-85-300-020).
(13) If the area repaired with VRS1827 and/or VRS1511 in steps (1), (3) and (5) to (12) is less than 30 percent of the total fan case acoustic lining area, accept.
(14) If the area repaired with VRS1827 and/or VRS1511 area in steps (1), (3) and (5) to (12) is more than 30 percent of the total fan case acoustic lining area, replace within 10 flight hours or 5 flight cycles whichever is sooner - repair, refer to VRS1845 (Ref. AMM TASK 72-32-85-300-020).
Subtask 72-32-85-210-067-A ** ON A/C NOT FOR ALL CAUTION:
CHECK THE TOTAL REPAIR AREA PRIOR TO STARTING THE REPAIR. DO NOT CARRY OUT REPAIR BY FILLING THE ACOUSTIC LININGS IF THE TOTAL REPAIRED AREA EXCEEDS 30 PERCENT OF THE TOTAL FAN CASE ACOUSTIC LINING AREA.
(1) If there are cracks - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016). (2) Scores not more than 0.002 in. (0.05 mm) in depth and less than 1 in. (25.4 mm) in length are acceptable.
(3) Damage more than in (2) is acceptable, if:
(a) The depth of the scores does not exceed 0.004 in. (0.1 mm).
(b) The linings will have been repaired within 500 flight hours or 250 flight cycles whichever is sooner - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016).
(4) Smooth dents in the linings are acceptable, if the limits that follow are not exceeded:
(a) The dents are less than 2.17 in. (55.0 mm) in diameter.
(b) The bond between the perforated skin and honeycomb is not broken.
(5) Damage more than in (4) is acceptable, if:
(a) The dents are less than 0.22 in. (5.5 mm) in depth.
(b) The linings will be repaired within 350 flight hours or 400 flight cycles whichever is sooner (Ref. AMM TASK 72-32-85-350-016).
(6) Damage more than in (3) or (5) is acceptable, if:
(a) The linings will be repaired within 250 flight hours or 125 flight cycles whichever is sooner (Ref. AMM TASK 72-32-85-350-016).
(7) Visually examine the bond of the acoustic lining, if you can see the unbond of the acoustic lining - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1511 (Ref. AMM TASK 72-32-85-300-047).
(8) Unbond in the linings is acceptable, if the limits that follow are not exceeded:
NOTE: Do a check of the acoustic lining for unbond by the tap test. The acoustic lining is tapped, or hit lightly, with a metallic coin (not less than 1.0 in. (25.4 mm)) or a small metal rod with a ball end or IAE 1N20444, tapping tool. 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 results of the tap test, if necessary.
(a) The unbond area(s) are less than 7 percent in area A of each acoustic lining panel. (b) The unbond area(s) are less than 20 percent in area B of each acoustic lining panel.
(c) The lining will be repaired within 50 flight hours or 25 flight cycles whichever is sooner - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1511 (Ref. AMM TASK 72-32-85-300-047).
(9) Unbond more than (8) is acceptable, if:
(a) The damaged area is less than 30 percent of the total area of each acoustic lining panel.
(b) The lining will be repaired within 10 flight hours or 5 flight cycles whichever is sooner - repair, refer to VRS1827 or VRS1511 (Ref. AMM TASK 72-32-85-350-016).
(10) Unbond more than (9) and perforated skin still attached - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1511 (Ref. AMM TASK 72-32-85-300-047).
(11) Missing perforated skin is acceptable, if:
(a) An inspection of the LP Compressor Fan Blades is accomplished (Ref. AMM TASK 72-00-00-200-022).
(b) Not more than one acoustic lining perforated skin is completely missing.
(c) The lining will be repaired within 10 flight hours or 5 flight cycles whichever is the sooner - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1845 (Ref. AMM TASK 72-32-85-300-020).
(12) Damage more than (9) - repair, refer to VRS1827 (Ref. AMM TASK 72-32-85-350-016) or VRS1845 (Ref. AMM TASK 72-32-85-300-020).
(13) If the area repaired with VRS1827 and/or VRS1511 in steps (1), (3) and (5) to (12) is less than 30 percent of the total fan case acoustic lining area, accept.
(14) If the area repaired with VRS1827 and/or VRS1511 area in steps (1), (3) and (5) to (12) is more than 30 percent of the total fan case acoustic lining area, replace within 10 flight hours or 5 flight cycles whichever is sooner - repair, refer to VRS1845 (Ref. AMM TASK 72-32-85-300-020).
D. Examine the Anti-ice Impact Panel (5), for Damage and Scores
(1) Many damage marks or indentations provided the GRC skin is not penetrated, are acceptable.
(2) Damage more than in (1) is acceptable, if:
(a) The panels will have been repaired within 50 flight hours or 25 flight cycles whichever is sooner - repair, refer to VRS1826 (Ref. AMM TASK 72-32-85-350-017).
(b) The damaged area is less than 20 percent of each anti-ice impact panel.
(3) Damage more than (2) - repair, refer to VRS1844 (Ref. AMM TASK 72-32-85-300-021).
Subtask 72-32-85-210-068-A ** ON A/C NOT FOR ALL (1) Many damage marks or indentations provided the GRC skin is not penetrated, are acceptable.
(2) Damage more than in (1) is acceptable, if:
(a) The panels will have been repaired within 50 flight hours or 25 flight cycles whichever is sooner - repair, refer to VRS1826 (Ref. AMM TASK 72-32-85-350-017).
(b) The damaged area is less than 20 percent of each anti-ice impact panel.
(3) Damage more than (2) - repair, refer to VRS1844 (Ref. AMM TASK 72-32-85-300-021).
E. Examine the Flanges (1), the Outer Surface (2), the Inner Surface (3) and the V-groove (12) for Nicks, Scratches, Galls or Scores and Bolt Hole Burrs.
PRE SBE 72-0160
(1) Nicks, scratches, galls or scores in the outer surface and the inner surface - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
(2) Nicks, scratches, galls or scores in the V-Groove - repair, refer to VRS1995 (Ref. AMM TASK 72-32-85-300-802).
(3) Bolt hole burrs - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
Subtask 72-32-85-210-117-A ** ON A/C NOT FOR ALL PRE SBE 72-0160
(1) Nicks, scratches, galls or scores in the outer surface and the inner surface - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
(2) Nicks, scratches, galls or scores in the V-Groove - repair, refer to VRS1995 (Ref. AMM TASK 72-32-85-300-802).
(3) Bolt hole burrs - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
F. Examine the Flanges (1) the Outer Surface (2), the Inner Surface (3) and the V-groove (12) for Nicks, Scratches, Galls or Scores and Bolt Hole Burrs
SBE 72-0160: Weight reduced fan case assembly
(1) Nicks, scratches, galls or scores in the outer surface and the inner surface - repair, refer to VRS1806 (Ref. AMM TASK 72-32-85-300-042).
(2) Nicks, scratches, galls or scores in the V-Groove - repair, refer to VRS1995 (Ref. AMM TASK 72-32-85-300-802).
(3) Bolt hole burrs - repair, refer to VRS1806 (Ref. AMM TASK 72-32-85-300-042).
Subtask 72-32-85-210-069-A ** ON A/C NOT FOR ALL SBE 72-0160: Weight reduced fan case assembly
(1) Nicks, scratches, galls or scores in the outer surface and the inner surface - repair, refer to VRS1806 (Ref. AMM TASK 72-32-85-300-042).
(2) Nicks, scratches, galls or scores in the V-Groove - repair, refer to VRS1995 (Ref. AMM TASK 72-32-85-300-802).
(3) Bolt hole burrs - repair, refer to VRS1806 (Ref. AMM TASK 72-32-85-300-042).
G. Examine the Hook (8) and the Flexible Ring Surface (9) for Nicks, Dents or Scores
PRE SBE 72-0160
(1) Nicks, dents or scores in the hook and on the flexible ring surface - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
Subtask 72-32-85-210-118-A ** ON A/C NOT FOR ALL PRE SBE 72-0160
(1) Nicks, dents or scores in the hook and on the flexible ring surface - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
H. Examine the Hook (8) and the Flexible Ring Surface (9) for Nicks, Dents or Scores
SBE 72-0160: Weight reduced fan case assembly
(1) Nicks, dents or scores in the hook and on the flexible ring surface - repair, refer to VRS1806 (Ref. AMM TASK 72-32-85-300-042).
Subtask 72-32-85-210-070-A ** ON A/C NOT FOR ALL SBE 72-0160: Weight reduced fan case assembly
(1) Nicks, dents or scores in the hook and on the flexible ring surface - repair, refer to VRS1806 (Ref. AMM TASK 72-32-85-300-042).
I. Examine the Blue Filler (7) for Damage and Erosion
(1) Erosion of the blue filler between the anti ice impact panel and the acoustic lining that is not more than 0.2 in. (5.08 mm) in depth, is acceptable.
(2) Damage that is more than in (1) - repair within 160 flight hours or 80 flight cycles , whichever is sooner, refer to VRS1828 (Ref. AMM TASK 72-32-85-350-019).
Subtask 72-32-85-210-071-A ** ON A/C NOT FOR ALL (1) Erosion of the blue filler between the anti ice impact panel and the acoustic lining that is not more than 0.2 in. (5.08 mm) in depth, is acceptable.
(2) Damage that is more than in (1) - repair within 160 flight hours or 80 flight cycles , whichever is sooner, refer to VRS1828 (Ref. AMM TASK 72-32-85-350-019).
J. Examine the Groove (10) for Galls, Scores or Scratches
PRE SBE 72-0160
(1) Galls, scores or scratches in the groove - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
5. Close-upPRE SBE 72-0160
(1) Galls, scores or scratches in the groove - repair, refer to VRS1824 (Ref. AMM TASK 72-32-85-350-015).
Subtask 72-32-85-410-102-A ** ON A/C NOT FOR ALL
A. Install the LP Compressor (Fan) Module (Ref. AMM TASK 72-31-00-400-010), or Install the LP Compressor Blades and Filler (Ref. AMM TASK 72-31-11-400-010).
Subtask 72-32-85-410-063-A ** ON A/C NOT FOR ALL B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
(3) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(4) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(5) Remove the support equipment
(a) Remove the workmat from the fan case.
(b) Remove the access platform(s).
Subtask 72-32-85-440-052-A ** ON A/C NOT FOR ALL Subtask 72-32-85-410-064-A ** ON A/C NOT FOR ALL (1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
(3) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(4) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(5) Remove the support equipment
(a) Remove the workmat from the fan case.
(b) Remove the access platform(s).