W DOC AIRBUS | AMM A320F

Installation of the Steady Bearing

TASK 27-84-44-400-003-A
Installation of the Steady Bearing

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.
FIN: 6021CM
FIN: 6071CM
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
SAFETY BARRIER(S)
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
No specific
AR
WARNING NOTICE(S)
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.06AEA1)
Polysulfide Sealant-Low Adhesion Brushable -
(Material No.06AEB2)
Polysulfide Sealant-Low Adhesion Fillet Structure
(Material No.08BAA9)
Non Aqueous Cleaner-General - -
(Material No.12ACC1)
Corrosion Preventive Compound-Heavy Duty Soft Film -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
FOR [6021CM] (SLAT STEADY BEARING)
521GB
FOR [6071CM] (SLAT STEADY BEARING)
621GB
 D. Referenced Information
REFERENCE
DESIGNATION
TASK 27-50-00-400-003-A
Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)
TASK 27-84-00-710-001-A
Operational Test of the Slat System
TASK 27-84-45-400-008-A
Installation of the Torque Shafts
3. Job Set-up
Subtask 27-84-44-941-064-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 the cockpit to tell persons not to operate the slat controls.
Subtask 27-84-44-860-052-A
B. Aircraft Maintenance Configuration
   (1) Make sure that the access platform is in position below the applicable torque shaft.
   (2) Make sure that the 98D27803500001 LOCKING TOOL ZERO POS or 98D27803500002 LOCKING TOOL ZERO POS is on the slat/flap control lever.
   (3) Make sure that the applicable torque shaft (26) is removed (Ref. AMM TASK 27-84-45-400-008):
     (a) FOR [6021CM] (SLAT STEADY BEARING)
remove the torque shaft FIN 6020CM
     (b) FOR [6071CM] (SLAT STEADY BEARING)
remove the torque shaft FIN 6070CM.
   (4) Make sure that the applicable access panel(s) have been removed:
     (a) FOR [6021CM] (SLAT STEADY BEARING)
remove 521GB
     (b) FOR [6071CM] (SLAT STEADY BEARING)
remove 621GB.
   (5) Make sure that a 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. AMM TASK 27-50-00-400-003) as follows:
  • on the torque shaft inboard of the removed component
  • on the torque shaft outboard of the removed component.
Subtask 27-84-44-865-052-A
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
** ON A/C ALL
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
4. Procedure
Subtask 27-84-44-420-061-A
A. Preparation for Installation
   (1) Use a Textile-Lint free Cotton - (Material No.14SBA1) with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the component interface and/or the adjacent area.
   (2) Do an inspection of the component interfaces and the adjacent area.
   (3) Make sure that the parts retained from the removed component are clean and in the correct condition.
   (4) Apply a layer of Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) or Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) to the:
  • mating faces of the steady bearing (22) and the nose rib (23)
  • shanks of the bolts (21).
Subtask 27-84-44-420-062-A
B. Installation of the Steady Bearing FIN 6021CM (6071CM)
   (1) Attach the steady bearing (22) to the torque shaft (25) and the nose rib (23) with:
  • the bolts (21) and the nuts (24).
   (2) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:
  • bolts (21)
  • nuts (24)
  • flange of the steady bearing (22).
Subtask 27-84-44-865-055-A
C. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
** ON A/C ALL
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
Subtask 27-84-44-410-050-A
D. Close Access
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Install the applicable torque shaft (26) (Ref. AMM TASK 27-84-45-400-008):
     (a) FOR [6021CM] (SLAT STEADY BEARING)
install the torque shaft FIN 6020CM
     (b) FOR [6071CM] (SLAT STEADY BEARING)
install the torque shaft FIN 6070CM.
   (3) Install the applicable access panel:
     (a) FOR [6021CM] (SLAT STEADY BEARING)
install 521GB
     (b) FOR [6071CM] (SLAT STEADY BEARING)
install 621GB.
Subtask 27-84-44-865-056-A
E. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
** ON A/C ALL
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
Subtask 27-84-44-710-052-A
F. Test
   (1) Do an operational test of the slat power-transmission system (Ref. AMM TASK 27-84-00-710-001).
5. Close-up
Subtask 27-84-44-942-052-A
A. Removal of Equipment
   (1) Remove the safety barriers.
   (2) Remove the WARNING NOTICE(S).
   (3) Remove the access platform(s).
   (4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.03.31 23:56:53 UTC
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