DOC AIRBUS | AMM A320FInspection of the Fan Exit Vane Assembly [IAE]
TASK 72-32-88-200-012-A
Inspection of the Fan Exit Vane Assembly
1. Reason for the Job
This TASK is for V2500-A5 engines Pre SBE 70-0377
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 72-32-88-941-060-A ** ON A/C NOT FOR ALL
Subtask 72-32-88-210-051-A ** ON A/C NOT FOR ALL
Subtask 72-32-88-942-052-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:45:56 UTC
Inspection of the Fan Exit Vane Assembly
1. Reason for the Job
This TASK is for V2500-A5 engines Pre SBE 70-0377
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 | MAT - WORK |
| 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 72-32-88-300-011-A | Repair of the Fan Exit vane Assembly - VRS1817 |
| 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 Exit Vane AssemblySubtask 72-32-88-941-060-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 72-32-88-010-065-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):
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(4) Put the ACCESS PLATFORM 2M (6 FT) in to position.
Subtask 72-32-88-040-056-A ** ON A/C NOT FOR ALL (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(4) Put the ACCESS PLATFORM 2M (6 FT) in to position.
C. Deactivate the Thrust Reverser
Subtask 72-32-88-010-066-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 72-32-88-941-061-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 in position in the fan case.
(1) Put the ACCESS PLATFORM 2M (6 FT) in to position to give access to 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) in to position to give access to the inspection task.
(2) Put the MAT - WORK in to position in the fan case.
NOTE: Make sure the workmat has sufficient dimensions to give full protection of the lower half of the fan case.
Subtask 72-32-88-210-051-A ** ON A/C NOT FOR ALL
A. Examine the Fan Exit Vane Assembly
(1) Examine the areas A and C of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they have nicks or scratches, up to 0.02 in. (0.5 mm) in depth, accept them.
(c) If they are nicked or scratched more than in (b) and up to 0.040in. (1.01mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked or scratched more than in (c) and up to 0.080in. (2.03mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 10 flight hours or 5 flight cycles whichever the sooner.
(e) If they are nicked or scratched more than in (d), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011).
(f) If they are dented, up to 0.04in. (1.01mm) in depth, accept them.
(g) If they are dented more than in (f) and up to 0.080in. (2.03mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(h) If they are dented more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 10 flight hours or 5 flight cycles whichever the sooner.
(i) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(j) If they are corroded more than in (i), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(2) Examine the area B of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they have nicks, scratches and dents, up to 0.010 in. (0.25 mm) in depth, accept them.
(c) If they are nicked, scratched or dented more than in (b) and up to 0.020in. (0.50mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked, scratched or dented more than in (c) and up to 0.040in. (1.01mm) in depth, replace the vane assembly within 10 flight hours or 5 flight cycles whichever the sooner.
(e) If they are nicked, scratched or dented more than in (d), reject them.
(f) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(g) If they are corroded more than in (f) and up to 0.010in. (0.25mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 10 flight hours or 5 flight cycles whichever the sooner.
(3) Examine the areas D and F of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they have nicks or scratches, up to 0.004 in. (0.10 mm) in depth, accept them.
(c) If they are nicked or scratched more than in (b) and up to 0.020in. (0.50mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If nicks or scratches are more than in (c), reject them.
(e) If they are dented, up to 0.020 in. (0.50 mm) in depth, accept them.
(f) If they are dented more than in (e), replace the vane assembly within 50 flight hours or 25 flight cycles whichever the sooner.
(g) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(4) Examine the areas E and G of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they are nicked or scratched, up to 0.004in. (0.10mm) in depth, accept them.
(c) If they are nicked or scratched more than in (b) and up to 0.039in. (1.00mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked or scratched more than in (c), reject them.
(e) If they are dented up to 0.039in. (1.00mm) in depth, accept them.
(f) If they are dented more than in (e), replace the vane assembly within 50 flight hours or 25 flight cycles whichever the sooner.
(g) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(5) Examine the area H of the fan exit vane assembly for cracks, nicks, scratches, dents or corrosion.
(a) If they are cracked, reject them.
(b) If they are nicked or scratched, up to 0.004in. (0.10mm) in depth, accept.
(c) If they are nicked or scratched more than in (b) and up to 0.011in. (0.30mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked or scratched more than in (c), reject them.
(e) If they are dented, up to 0.011in. (0.30mm), in depth, accept them.
(f) If they are dented more than in (e), replace the vane assembly within 50 flight hours or 25 flight cycles whichever the sooner.
(g) If they are corroded, up to 0.005in. (0.12mm) in depth, accept.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(6) Examine the joint between the vane and resin.
(a) If they show signs of unbond at the joint between the vane and the resin of the inner of the outer platform, accept them if:
1 The unbonds are less than 0.120in. (3.04mm) in depth.
2 The unbonds are less than 0.600in. (15.24mm) in depth and less than 1.400in. (35.56mm) in length for each vane end.
3 An unbond that is more than that in (2_) is permitted on one vane end for each vane assembly.
(b) If the unbonds are more than in (a), replace the vane assembly within 10 flight hours or 5 flight cycles whichever the sooner.
5. Close-up(1) Examine the areas A and C of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they have nicks or scratches, up to 0.02 in. (0.5 mm) in depth, accept them.
(c) If they are nicked or scratched more than in (b) and up to 0.040in. (1.01mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked or scratched more than in (c) and up to 0.080in. (2.03mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 10 flight hours or 5 flight cycles whichever the sooner.
(e) If they are nicked or scratched more than in (d), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011).
(f) If they are dented, up to 0.04in. (1.01mm) in depth, accept them.
(g) If they are dented more than in (f) and up to 0.080in. (2.03mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(h) If they are dented more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 10 flight hours or 5 flight cycles whichever the sooner.
(i) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(j) If they are corroded more than in (i), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(2) Examine the area B of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they have nicks, scratches and dents, up to 0.010 in. (0.25 mm) in depth, accept them.
(c) If they are nicked, scratched or dented more than in (b) and up to 0.020in. (0.50mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked, scratched or dented more than in (c) and up to 0.040in. (1.01mm) in depth, replace the vane assembly within 10 flight hours or 5 flight cycles whichever the sooner.
(e) If they are nicked, scratched or dented more than in (d), reject them.
(f) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(g) If they are corroded more than in (f) and up to 0.010in. (0.25mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 10 flight hours or 5 flight cycles whichever the sooner.
(3) Examine the areas D and F of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they have nicks or scratches, up to 0.004 in. (0.10 mm) in depth, accept them.
(c) If they are nicked or scratched more than in (b) and up to 0.020in. (0.50mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If nicks or scratches are more than in (c), reject them.
(e) If they are dented, up to 0.020 in. (0.50 mm) in depth, accept them.
(f) If they are dented more than in (e), replace the vane assembly within 50 flight hours or 25 flight cycles whichever the sooner.
(g) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(4) Examine the areas E and G of the fan exit vane assembly for cracks, nicks, scratches, dents and corrosion.
(a) If they are cracked, reject them.
(b) If they are nicked or scratched, up to 0.004in. (0.10mm) in depth, accept them.
(c) If they are nicked or scratched more than in (b) and up to 0.039in. (1.00mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked or scratched more than in (c), reject them.
(e) If they are dented up to 0.039in. (1.00mm) in depth, accept them.
(f) If they are dented more than in (e), replace the vane assembly within 50 flight hours or 25 flight cycles whichever the sooner.
(g) If they are corroded, up to 0.005in. (0.12mm) in depth, accept them.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(5) Examine the area H of the fan exit vane assembly for cracks, nicks, scratches, dents or corrosion.
(a) If they are cracked, reject them.
(b) If they are nicked or scratched, up to 0.004in. (0.10mm) in depth, accept.
(c) If they are nicked or scratched more than in (b) and up to 0.011in. (0.30mm) in depth, repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(d) If they are nicked or scratched more than in (c), reject them.
(e) If they are dented, up to 0.011in. (0.30mm), in depth, accept them.
(f) If they are dented more than in (e), replace the vane assembly within 50 flight hours or 25 flight cycles whichever the sooner.
(g) If they are corroded, up to 0.005in. (0.12mm) in depth, accept.
(h) If they are corroded more than in (g), repair per VRS1817 (Ref. AMM TASK 72-32-88-300-011) within 50 flight hours or 25 flight cycles whichever the sooner.
(6) Examine the joint between the vane and resin.
(a) If they show signs of unbond at the joint between the vane and the resin of the inner of the outer platform, accept them if:
1 The unbonds are less than 0.120in. (3.04mm) in depth.
2 The unbonds are less than 0.600in. (15.24mm) in depth and less than 1.400in. (35.56mm) in length for each vane end.
3 An unbond that is more than that in (2_) is permitted on one vane end for each vane assembly.
(b) If the unbonds are more than in (a), replace the vane assembly within 10 flight hours or 5 flight cycles whichever the sooner.
Subtask 72-32-88-942-052-A ** ON A/C NOT FOR ALL
A. Remove the support equipment
(1) Remove the wormat from the fan case.
Subtask 72-32-88-410-063-A ** ON A/C NOT FOR ALL (1) Remove the wormat from the fan case.
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):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 72-32-88-440-054-A ** ON A/C NOT FOR ALL Subtask 72-32-88-410-064-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):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR