DOC AIRBUS | AMM A320FInstallation of the Torque Shaft
TASK 27-54-45-400-002-A
Installation of the Torque Shaft
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Expendable Parts
D. Referenced Information
3. Job Set-up
Subtask 27-54-45-941-078-A
Subtask 27-54-45-410-051-A
[Rev.10 from 2021]
2026.04.01 06:55:28 UTC
Installation of the Torque Shaft
WARNING:
MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION.
WARNING:
MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION:
BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
1. Reason for the Job- DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.
- DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.
- MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.03FDB1) | Mineral Oil base Grease-Anti-Fretting Paste - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.12ACC1) | Corrosion Preventive Compound-Heavy Duty Soft Film - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 3 | NUTS | AIPC 27-54-45-52-040 |
| 9 | NUTS | AIPC 27-54-45-52-040 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 27-50-00-000-003-A | Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) |
| TASK 27-50-00-400-003-A | Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) |
| TASK 27-54-00-710-001-A | Operational Test of the Flap System |
| TASK 32-12-00-010-001-A | Open the Main Gear Doors for Access |
| TASK 32-12-00-410-001-A | Close the Main Gear Doors after Access |
Torque Shafts - Flap Power TransmissionSubtask 27-54-45-941-078-A
A. Safety Precautions
(1) Make sure that the SAFETY BARRIER(S) are in position.
(2) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the flap/slat controls.
(3) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the landing gear doors.
Subtask 27-54-45-860-064-A (1) Make sure that the SAFETY BARRIER(S) are in position.
(2) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the flap/slat controls.
(3) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the landing gear doors.
B. Aircraft Maintenance Configuration
(2) Make sure that the MLG doors are open (Ref. AMM TASK 32-12-00-010-001).
(3) Make sure that the 460005835 SLEEVE - GROUND LOCK is on the applicable MLG door actuator.
(4) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in the applicable position.
(5) Make sure that the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed on the flap torque shaft (Ref. AMM TASK 27-50-00-400-003), outboard of the removed component.
Subtask 27-54-45-865-062-A WARNING:
MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
(1) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is on the flap/slat control lever on panel 114VU. (2) Make sure that the MLG doors are open (Ref. AMM TASK 32-12-00-010-001).
(3) Make sure that the 460005835 SLEEVE - GROUND LOCK is on the applicable MLG door actuator.
(4) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in the applicable position.
(5) Make sure that the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed on the flap torque shaft (Ref. AMM TASK 27-50-00-400-003), outboard of the removed component.
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
CAUTION:
BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
Subtask 27-54-45-420-064-A - DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.
- DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.
- MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.
A. Preparation for Installation
(1) Clean the parts:
(a) Use a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
(3) Make sure that the parts retained from the removed component are clean and in the correct condition.
(4) Do an inspection of the component interfaces and the adjacent area.
(5) Apply a thin layer of Mineral Oil base Grease-Anti-Fretting Paste - (Material No.03FDB1) to the torque shaft splines.
Subtask 27-54-45-420-051-A (1) Clean the parts:
(a) Use a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean:
- The new AIPC 27-54-45-52-040 NUTS (3) and the new AIPC 27-54-45-52-040 NUTS (9)
- The bolts (4) and (8)
- The flanges of the universal joints (1) and (7)
- The flanges of the torque shaft (2).
WARNING:
WHEN YOU USE COMPRESSED AIR:
- USE THE CORRECT PROTECTION (FACE SHIELD OR GOGGLES)
- DO NOT POINT THE AIRFLOW AT YOURSELF OR OTHER PERSONS.
WARNING:
DO NOT LET COMPRESSED GAS TOUCH YOUR SKIN. THE GAS CAN GO THROUGH THE SKIN AND MAKE BUBBLES IN THE BLOOD. THIS CONDITION CAN KILL YOU.
(a) Use compressed air to dry the cleaned areas. (3) Make sure that the parts retained from the removed component are clean and in the correct condition.
(4) Do an inspection of the component interfaces and the adjacent area.
(5) Apply a thin layer of Mineral Oil base Grease-Anti-Fretting Paste - (Material No.03FDB1) to the torque shaft splines.
B. Installation of the Torque Shaft
(1) Put the retaining ring (5) temporarily in position on the shaft of the universal joint (7).
(2) Install the universal joint (7) to the right-angle gear box 6203CM(6253CM) and attach it with the pin (6) and the retaining ring (5).
(3) Install the universal joint (1) and align its flange with the flange of the universal joint (7).
(4) Install the torque shaft (2) and attach it to the universal joint (1) with the bolts (8) and the nuts (9). Tighten the nuts (9) by hand.
(a) If the dimension is between 6.6 mm (0.260 in.) and 13.25 mm (0.522 in.), do not install a spacer.
(b) If the dimension is between 13.26 mm (0.522 in.) and 16.75 mm (0.659 in.), install one spacer 3.5 mm (0.138 in.) thick, between the torque shaft (2) and the universal joint (7). Use the longer bolts (8).
(c) If the dimension is between 16.76 mm (0.660 in.) and 23.5 mm (0.925 in.), install two spacers, each one 3.5 mm (0.138 in.) thick:
(7) TORQUE the nuts (3) and (9) to between 1.24 and 1.02 m.daN (109.73 and 90.27 lbf.in )
.
(8) Make sure that:
Subtask 27-54-45-916-051-A (1) Put the retaining ring (5) temporarily in position on the shaft of the universal joint (7).
(2) Install the universal joint (7) to the right-angle gear box 6203CM(6253CM) and attach it with the pin (6) and the retaining ring (5).
(3) Install the universal joint (1) and align its flange with the flange of the universal joint (7).
(4) Install the torque shaft (2) and attach it to the universal joint (1) with the bolts (8) and the nuts (9). Tighten the nuts (9) by hand.
NOTE: A replacement torque shaft (2) 6204CM(6254CM), has two flange shims and the longer bolts (8). Use these (if necessary) in the worksteps that follow.
(5) Measure the dimension between the torque shaft (2) and the universal joint (7). (a) If the dimension is between 6.6 mm (0.260 in.) and 13.25 mm (0.522 in.), do not install a spacer.
(b) If the dimension is between 13.26 mm (0.522 in.) and 16.75 mm (0.659 in.), install one spacer 3.5 mm (0.138 in.) thick, between the torque shaft (2) and the universal joint (7). Use the longer bolts (8).
(c) If the dimension is between 16.76 mm (0.660 in.) and 23.5 mm (0.925 in.), install two spacers, each one 3.5 mm (0.138 in.) thick:
- One between the torque shaft (2) and the universal joint (1)
- One between the torque shaft (2) and the universal joint (7).
Use the longer bolts (8).
(7) TORQUE the nuts (3) and (9) to between 1.24 and 1.02 m.daN (109.73 and 90.27 lbf.in )
. (8) Make sure that:
- You cannot see the spline engagement groove at the movable joint
- The dimension A is a minimum of 6.5 mm (0.256 in.) at the movable joint.
C. Application of Special Materials
(1) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to:
Subtask 27-54-45-865-063-A (1) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to:
- The nuts (3) and (9)
- The bolts (4) and (8)
- The flanges of the universal joints (1) and (7)
- The flanges of the torque shaft (2).
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-54-45-710-051-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
E. Operational Test of the Flap System
(1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(2) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001). Make sure that the operation of the torque shafts is satisfactory.
5. Close-up(1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(2) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001). Make sure that the operation of the torque shafts is satisfactory.
Subtask 27-54-45-410-051-A
A. Close Access
(1) Remove the access platform(s).
(2) Remove the 460005835 SLEEVE - GROUND LOCK from each MLG door actuator.
(3) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).
Subtask 27-54-45-942-051-A (1) Remove the access platform(s).
(2) Remove the 460005835 SLEEVE - GROUND LOCK from each MLG door actuator.
(3) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).
B. Removal of Equipment
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the safety barriers.
(3) Remove the WARNING NOTICE(S).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the safety barriers.
(3) Remove the WARNING NOTICE(S).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.