DOC AIRBUS | AMM A320FVisual Inspection of the Core Nozzle [CFMB]
TASK 78-11-11-210-041-A
Visual Inspection of the Core Nozzle
This inspection criteria is only for those portions of the nozzle that can be observed on-wing. Therefore, the limits and remarks do not apply to the attach ring and forward non-accessible areas of the nozzle. Inspection of these areas should be done at the next component removal from the engine.
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 78-11-11-941-050-A ** ON A/C NOT FOR ALL
Subtask 78-11-11-210-050-A ** ON A/C NOT FOR ALL
Subtask 78-11-11-410-066-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 03:56:10 UTC
Visual Inspection of the Core Nozzle
ZONE: 400
1. Reason for the JobThis inspection criteria is only for those portions of the nozzle that can be observed on-wing. Therefore, the limits and remarks do not apply to the attach ring and forward non-accessible areas of the nozzle. Inspection of these areas should be done at the next component removal from the engine.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 1M(3 FT) |
| No specific | AR | WARNING NOTICE(S) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| FOR [1000EM1] (ENGINE-1) | |
| 437AL, 438AR, 451AL, 452AR | |
| FOR [1000EM2] (ENGINE-2) | |
| 447AL, 448AR, 461AL, 462AR | |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 71-13-00-010-040-B | Opening of the Fan Cowl Doors |
| TASK 71-13-00-410-040-B | Closing of the Fan Cowl Doors |
| TASK 78-11-11-000-041-A | Removal of the Core Nozzle Assembly |
| TASK 78-11-11-400-041-A | Installation of the Core Nozzle Assembly |
| TASK 78-30-00-081-041-B | Make the Thrust Reverser Serviceable after Maintenance |
| TASK 78-30-00-481-041-B | Make the Thrust Reverser Unserviceable for Maintenance |
| TASK 78-36-00-010-040-B | Opening of the Thrust Reverser Doors |
| TASK 78-36-00-410-040-B | Closing of the Thrust Reverser Doors |
Core Exhaust NozzleSubtask 78-11-11-941-050-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 78-11-11-010-050-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 cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Put the ACCESS PLATFORM 1M(3 FT) in position.
Subtask 78-11-11-040-051-A ** ON A/C NOT FOR ALL Subtask 78-11-11-010-053-A ** ON A/C NOT FOR ALL (1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Put the ACCESS PLATFORM 1M(3 FT) in position.
D. Open the thrust reverser doors (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
4. Procedure(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR
Subtask 78-11-11-210-050-A ** ON A/C NOT FOR ALL
A. Visual Inspection of the Core Nozzle
(1) Do a visual inspection of the core nozzle assembly as follows. Use proper lighting to illuminate the inner and outer skins:
Subtask 78-11-11-210-050-D ** ON A/C NOT FOR ALL (1) Do a visual inspection of the core nozzle assembly as follows. Use proper lighting to illuminate the inner and outer skins:
| INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Inner skin for: NOTE: It is permitted to have polish marks on the inner skin surface. | | |
| A.Crack | 1 in. (25.4 mm) maximum length | Stop-drill ends with 0.0625 in. (1.59 mm) drill. Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 6 in. (152.4 mm) maximum total of all cracks | |
| | 4 in. (101.6 mm) minimum separation from other cracks | |
| 2.Outer skin for: | | |
| A.Crack | 0.25 in. (6.35 mm) maximum length | Stop-drill ends with 0.125 in. (3.17 mm) drill. Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 2 in. (50.8 mm) maximum total of all cracks | |
| | 2 in. (50.8 mm) minimum separation from other cracks | |
| | No crack permitted in the forward 17 in. (0.43 m) segment | Replace exhaust nozzle (Ref. AMM TASK 78-11-11-000-041) and (Ref. AMM TASK 78-11-11-400-041). |
| B.Wear | Maximum depth 0.006 in. (0.152 mm) | |
| 3.Forward bulkhead for: | | |
| A.Crack | No crack permitted | Replace exhaust nozzle (Ref. AMM TASK 78-11-11-000-041) and (Ref. AMM TASK 78-11-11-400-041). |
| B.Gouge or scratch | 0.010 in. (0.25 mm) maximum depth | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 1.5 in. (38.09 mm) maximum length | |
| 4.Inner and outer pylon seals for: | | |
| A.Wear | Outer seal may be fully worn or not there. | Outer seal wear is permitted for flight. Replace seal at next shop visit. |
| | Inner seal may not be worn. | Replace exhaust nozzle (Ref. AMM TASK 78-11-11-000-041) and (Ref. AMM TASK 78-11-11-400-041). |
| 5.Inner and outer skins for: NOTE: It is permitted to have polish marks on the inner skin surface. | | |
| A.Dent | 2.50 in. (63.5 mm) maximum diameter | OK for flight. Make smooth the contour at next shop visit. |
| | 0.25 in. (6.35 mm) maximum depth | |
| | 0.25 in. (6.35 mm) minimum radius | |
| B.Gouge or scratch | 0.010 in. (0.25 mm) maximum depth | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/ 24 calendar months (whichever the earliest) |
| | 1.5 in. (38.1 mm) maximum length Gouges deeper than 0.010 in. (0.25 mm) and less than 0.12 in. (3.04 mm) in length may be removed by drilling 0.190 in. (4.82 mm) hole in outer skin only. | |
| C.Missing or damaged rivets | Maximum of 5 percent missing or damaged rivets. There must be at least one good rivet between any two that are missing or damaged. | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
A. Visual Inspection of the Core Nozzle
(1) Do a visual inspection of the core nozzle assembly as follows. Use proper lighting to illuminate the inner and outer skins:
5. Close-up(1) Do a visual inspection of the core nozzle assembly as follows. Use proper lighting to illuminate the inner and outer skins:
| INSPECT/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS |
|---|---|---|
| 1.Inner skin for: NOTE: It is permitted to have polish marks on the inner skin surface. | | |
| A.Crack | 1 in. (25.4 mm) maximum length | Stop-drill ends with 0.0625 in. (1.59 mm) drill. Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 6 in. (152.4 mm) maximum total of all cracks | |
| | 4 in. (101.6 mm) minimum separation from other cracks | |
| 2.Outer skin for: | | |
| A.Crack | 0.25 in. (6.35 mm) maximum length | Stop-drill ends with 0.125 in. (3.17 mm) drill. Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 2 in. (50.8 mm) maximum total of all cracks | |
| | 2 in. (50.8 mm) minimum separation from other cracks | |
| | No crack permitted in the forward 17 in. (0.43 m) segment | Replace exhaust nozzle (Ref. AMM TASK 78-11-11-000-041) and (Ref. AMM TASK 78-11-11-400-041). |
| B.Wear | Maximum depth 0.006 in. (0.152 mm) | |
| 3.Forward bulkhead for: | | |
| A.Crack | No crack permitted | Replace exhaust nozzle (Ref. AMM TASK 78-11-11-000-041) and (Ref. AMM TASK 78-11-11-400-041). |
| B.Gouge or scratch | 0.010 in. (0.25 mm) maximum depth | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 1.5 in. (38.09 mm) maximum length | |
| 4.Inner and outer pylon seals for: | | |
| A.Wear | Outer seal may be fully worn or not there. | Outer seal wear is permitted for flight. Replace seal at next shop visit. |
| | Inner seal may not be worn. | Replace exhaust nozzle (Ref. AMM TASK 78-11-11-000-041) and (Ref. AMM TASK 78-11-11-400-041). |
| 5.Inner and outer skins for: NOTE: It is permitted to have polish marks on the inner skin surface. | | |
| A.Dent | 2.50 in. (63.5 mm) maximum diameter | OK for flight. Make smooth the contour at next shop visit. |
| | 0.25 in. (6.35 mm) maximum depth | |
| | 0.25 in. (6.35 mm) minimum radius | |
| B.Gouge or scratch | 0.010 in. (0.25 mm) maximum depth | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 1.5 in. (38.1 mm) maximum length Gouges deeper than 0.010 in. (0.25 mm) and less than 0.12 in. (3.04 mm) in length may be removed by drilling 0.190 in. (4.82 mm) hole in outer skin only. | |
| C.Missing or damaged rivets | Maximum of 5 percent missing or damaged rivets. There must be at least one good rivet between any two that are missing or damaged. | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| 6.Chevron for: NOTE: No damage is allowed at the 12 O'clock area adjacent to the pylon. | | |
| A.Crack | 0.40 in. (10.16 mm) maximum length | Stop-drill ends with 0.250 in. (6.35 mm) drill. Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| B.Dent | 1.50 in. (38.1 mm) maximum diameter | OK for flight. Make smooth the contour at next shop visit. |
| | 0.15 in. (3.81 mm) maximum depth | |
| | 0.30 in.(7.62mm) minimum from edge of part | |
| C.Gouge or Scratch | 0.10 in. (2.54 mm) maximum depth | Monitor at 750 Flight Hours/750 Flight Cycles/4 calendar months (whichever the earliest). Permanent repair at next 7500 Flight Hours/7500 Flight Cycles/24 calendar months (whichever the earliest) |
| | 1.50 in. (38.1 mm) maximum length | |
| D.Bend (aft edge) | 1.50 in. (38.1 mm) maximum at tip | OK for flight. Make smooth the contour at next shop visit. |
| | Maximum of two bent | |
Subtask 78-11-11-410-066-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 doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(3) Remove the access platform(s).
Subtask 78-11-11-440-057-A ** ON A/C NOT FOR ALL Subtask 78-11-11-410-050-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 doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR
(3) Remove the access platform(s).