W DOC AIRBUS | AMM A320F

Inspection of the Wing Leading Edge

TASK 57-41-00-200-001-A
Inspection of the Wing Leading Edge

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: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:
  • THE FLIGHT CONTROLS
  • THE FLIGHT CONTROL SURFACES
  • THE LANDING GEAR AND THE RELATED DOORS
  • COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.
WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
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
ACCESS PLATFORM 4M (13 FT)
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.08BAA9)
Non Aqueous Cleaner-General - -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Referenced Information
REFERENCE
DESIGNATION
TASK 27-80-00-866-004-A
Extending the Slats on the Ground
TASK 27-80-00-866-005-A
Retracting the Slats on the Ground
SRM 572100
 (for corrective action)
F Wing Leading Edge
3. Job Set-up
Subtask 57-41-00-941-050-A
A. Safety Precautions
   (1) Put WARNING NOTICE(S) in the cockpit to tell persons not to operate the flaps or slats.
   (2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
Subtask 57-41-00-860-058-A
B. Aircraft Maintenance Configuration
   (1) Fully extend the slats (Ref. AMM TASK 27-80-00-866-004).
   (2) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
   (3) Put the ACCESS PLATFORM 4M (13 FT) in position below the applicable wing leading edge, zones 521 (621) and 522 (622).
Subtask 57-41-00-865-050-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
4. Procedure
Subtask 57-41-00-110-058-A
A. Preparation for Inspection
   (1) Use a Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean these areas:
  • the fuselage/wing-fillet fairing
  • the NACA ram-air inlet
  • the leading edge surfaces
  • the leading edge access panels
  • the joint between the leading edge structure and the wing tip
  • above the nacelles
  • the leading edge surfaces behind the slats.
Subtask 57-41-00-210-050-B
B. Inspection
   (1) Examine the fuselage/wing-fillet fairing to make sure that:
  • there is no distortion of the skins
  • there is no damage
  • there are no loose rivets
  • there is no corrosion.
NOTE: If necessary, refer to the SRM 572100 fort he correct repair procedure.
   (2) Examine the leading edge surfaces to make sure that:
  • there are no loose rivets
  • there is no damage
  • there is no corrosion.
NOTE: If necessary, refer to the SRM 572100 fort he correct repair procedure.
   (3) Examine the access panels to make sure that:
  • there are no loose fasteners
  • there is no damage.
NOTE: If necessary, refer to the SRM 572100 fort he correct repair procedure.
   (4) Examine the outboard part of the leading edge and the inboard part of the wing tip to make sure that:
  • there is no distortion
  • there are no loose rivets
  • there is no damage
  • there is no corrosion.
NOTE: If necessary, refer to the SRM 572100 fort he correct repair procedure.
   (5) Examine the area above the nacelles to make sure that:
  • there are no loose rivets
  • there is no corrosion
  • there is no distortion.
NOTE: If necessary, refer to the SRM 572100 fort he correct repair procedure.
   (6) Examine the leading edge surfaces behind the slats to make sure that:
  • there is no distortion
  • there is no damage
  • there are no loose rivets
  • there is no corrosion.
  • the condition of the abrasion-resistant finish on the top surface is good (Ref. Fig. 601, dimension 'X')
NOTE: If necessary, refer to the SRM 572100 fort he correct repair procedure.
5. Close-up
Subtask 57-41-00-865-051-A
A. 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 57-41-00-860-059-A
B. Aircraft Configuration
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Remove the access platform(s).
   (3) Retract the slats (Ref. AMM TASK 27-80-00-866-005).
Subtask 57-41-00-942-050-A
C. Removal of Equipment
   (1) Remove the WARNING NOTICE(S).
   (2) Remove the safety barriers.
   (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.04.02 06:30:56 UTC
"WTRUIB" 2025