DOC AIRBUS | AMM A320FExamine the Fan Case Liner Panel and the Panel Rubber Seal [IAE]
TASK 72-32-87-200-010-B
Examine the Fan Case Liner Panel and the Panel Rubber Seal
1. Reason for the Job
This TASK is for V2500-A5 engines.
This TASK gives the procedure for the inspection of the Fan Caser Liner Panel and Panel Rubber Seal.
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 72-32-87-941-059-A ** ON A/C NOT FOR ALL
Subtask 72-32-87-210-053-A ** ON A/C NOT FOR ALL
Subtask 72-32-87-410-058-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:45:51 UTC
Examine the Fan Case Liner Panel and the Panel Rubber Seal
1. Reason for the Job
This TASK is for V2500-A5 engines.
This TASK gives the procedure for the inspection of the Fan Caser Liner Panel and Panel Rubber Seal.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 2M (6 FT) |
| No specific | AR | WARNING NOTICE(S) |
| 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 72-32-87-000-010-B | Removal of the Panel Rubber Seals |
| TASK 72-32-87-000-011-B | Removal of the Fan Case Liner Panels |
| TASK 72-32-87-300-010-A | Repair the Crack in the Fan Case Liner Panel - VRS1802 |
| TASK 72-32-87-400-010-B | Installation of the Panel Rubber Seals |
| TASK 72-32-87-400-011-B | Installation of the Fan Case Liner Panels |
| 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 |
Fan Case Liner Panel and Panel Rubber SealSubtask 72-32-87-941-059-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 72-32-87-010-058-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. Get Access
(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR.
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Put the ACCESS PLATFORM 2M (6 FT) in to position.
Subtask 72-32-87-040-058-A ** ON A/C NOT FOR ALL (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR.
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
(2) Put the ACCESS PLATFORM 2M (6 FT) in to position.
C. Deactivate the thrust reverser.
Subtask 72-32-87-010-060-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. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
Subtask 72-32-87-941-058-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
E. Put the support equipment into position
(1) Put the workmat in position in the intake cowl.
4. Procedure(1) Put the workmat in position in the intake cowl.
NOTE: Make sure that the red warning pennants on the workmat can be seen external to the aircraft. Make sure that the workmat has sufficient dimensions to give full protection to the lower half of the intake cowl.
Subtask 72-32-87-210-053-A ** ON A/C NOT FOR ALL
A. Examine the fan case liner panels.
(1) Examine the fan case liner panels for cracks, nicks, scores, scratches and damage holes (material that is not there).
(a) If they are cracked, up to 6 in. (152.4 mm) in length, accept them, provided that they are replaced (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011) or repaired, refer to VRS1802 (Ref. AMM TASK 72-32-87-300-010), within 125 flight hours or 25 flight cycles, whichever occurs first.
(b) If they have nicks, scores or scratches, up to 0.020 in (0.5 mm) in depth, accept them.
(c) If they have nicks, scores or scratches more than in (b), accept them, provided that they are replaced (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011) or repaired, refer to VRS1802 (Ref. AMM TASK 72-32-87-300-010), within 125 flight hours or 25 flight cycles, whichever occurs first.
(d) If they have damage holes (material that is not there), up to 2 in.(50.8 mm) diameter, accept them, provided:
1 They are replaced (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011) or repaired, refer to VRS1802 (Ref. AMM TASK 72-32-87-300-010), within 125 flight hours or 25 flight cycles, whichever occurs first.
2 The loose pieces are removed.
(e) If they have damage that is more than in (a) or (d),replace them (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011), within 50 flight hours or 10 flight cycles, whichever occurs first, provided :
1 The loose pieces are removed.
2 Examine those damages after 5 flight cycles, and remove loose pieces if they are found .
Subtask 72-32-87-210-054-A ** ON A/C NOT FOR ALL (1) Examine the fan case liner panels for cracks, nicks, scores, scratches and damage holes (material that is not there).
(a) If they are cracked, up to 6 in. (152.4 mm) in length, accept them, provided that they are replaced (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011) or repaired, refer to VRS1802 (Ref. AMM TASK 72-32-87-300-010), within 125 flight hours or 25 flight cycles, whichever occurs first.
(b) If they have nicks, scores or scratches, up to 0.020 in (0.5 mm) in depth, accept them.
(c) If they have nicks, scores or scratches more than in (b), accept them, provided that they are replaced (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011) or repaired, refer to VRS1802 (Ref. AMM TASK 72-32-87-300-010), within 125 flight hours or 25 flight cycles, whichever occurs first.
(d) If they have damage holes (material that is not there), up to 2 in.(50.8 mm) diameter, accept them, provided:
1 They are replaced (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011) or repaired, refer to VRS1802 (Ref. AMM TASK 72-32-87-300-010), within 125 flight hours or 25 flight cycles, whichever occurs first.
2 The loose pieces are removed.
(e) If they have damage that is more than in (a) or (d),replace them (Ref. AMM TASK 72-32-87-000-011) and (Ref. AMM TASK 72-32-87-400-011), within 50 flight hours or 10 flight cycles, whichever occurs first, provided :
1 The loose pieces are removed.
2 Examine those damages after 5 flight cycles, and remove loose pieces if they are found .
B. Examine the panel rubber seals for cracks, nicks, scores and scratches.
(1) Missing Material
Replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) within 25 flight hours or 5 flight cycles, whichever occurs first. Any loose pieces must be removed prior to the next flight.
(2) Cracks
(a) Any number of cracks up to 0.50 in. (12.7 mm) long are acceptable, if they are not intersecting any other cracks and are not extending from a bolt hole. Examine these cracks again at 750 flight hours, 750 flight cycles or 4 months and replace the seal at next shop visit.
(b) One crack per bolt hole is acceptable, if they are in the panel area A or panel area B. Examine these cracks again at 750 flight hours, 750 flight cycles or 4 months and replace the seal at next shop visit.
(c) Up to ten cracks are acceptable, if they are not crossing the three areas (panel area A, panel area B and fillet area), and if they are not intersecting any other cracks. Examine these cracks again at 750 flight hours, 750 flight cycles or 4 months and replace the seal at the next shop visit.
(d) If there are cracks that are more than (a), (b) or (c), and if any of the cracks are not intersecting each other, replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) within 50 flight cycles, provided:
1 The loose pieces are removed.
2 Examine for cracks after 35 flight cycles and thereafter every 5 flight cycles.
3 The cracks do not go through from the outer end to the inner end of the seal.
(e) If there are cracks that are more than (d), replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) within 50 flight hours or 10 flight cycles, whichever occurs first, provided :
1 The loose pieces are removed.
2 Examine those damages after 5 flight cycles, and remove loose pieces if they are found .
(3) Nicks, Scores and Scratches
(a) If there are nicks, scores and scratches, up to 0.030 in. (0.76 mm) in depth, accept them.
(b) If there is damage that is more than (a), examine damage again at 750 flight hours, 750 flight cycles or 4 months and replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) at next shop visit.
5. Close-up(1) Missing Material
Replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) within 25 flight hours or 5 flight cycles, whichever occurs first. Any loose pieces must be removed prior to the next flight.
(2) Cracks
(a) Any number of cracks up to 0.50 in. (12.7 mm) long are acceptable, if they are not intersecting any other cracks and are not extending from a bolt hole. Examine these cracks again at 750 flight hours, 750 flight cycles or 4 months and replace the seal at next shop visit.
(b) One crack per bolt hole is acceptable, if they are in the panel area A or panel area B. Examine these cracks again at 750 flight hours, 750 flight cycles or 4 months and replace the seal at next shop visit.
(c) Up to ten cracks are acceptable, if they are not crossing the three areas (panel area A, panel area B and fillet area), and if they are not intersecting any other cracks. Examine these cracks again at 750 flight hours, 750 flight cycles or 4 months and replace the seal at the next shop visit.
(d) If there are cracks that are more than (a), (b) or (c), and if any of the cracks are not intersecting each other, replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) within 50 flight cycles, provided:
1 The loose pieces are removed.
2 Examine for cracks after 35 flight cycles and thereafter every 5 flight cycles.
3 The cracks do not go through from the outer end to the inner end of the seal.
(e) If there are cracks that are more than (d), replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) within 50 flight hours or 10 flight cycles, whichever occurs first, provided :
1 The loose pieces are removed.
2 Examine those damages after 5 flight cycles, and remove loose pieces if they are found .
(3) Nicks, Scores and Scratches
(a) If there are nicks, scores and scratches, up to 0.030 in. (0.76 mm) in depth, accept them.
(b) If there is damage that is more than (a), examine damage again at 750 flight hours, 750 flight cycles or 4 months and replace them (Ref. AMM TASK 72-32-87-000-010) and (Ref. AMM TASK 72-32-87-400-010) at next shop visit.
Subtask 72-32-87-410-058-A ** ON A/C NOT FOR ALL
A. 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):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
(3) Remove the workmat from the intake cowl
(4) Remove the access platform(s).
Subtask 72-32-87-440-055-A ** ON A/C NOT FOR ALL Subtask 72-32-87-410-060-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):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
(3) Remove the workmat from the intake cowl
(4) Remove the access platform(s).