W DOC AIRBUS | AMM A320F

Detailed Inspection of Bonding Leads Located on the Following Movable Surfaces: Elevator, Rudder, Flaps, Flap Track Fairings, Slats, Spoilers, Ailerons,.......

TASK 24-92-00-210-024-A
Detailed Inspection of Bonding Leads Located on the Following Movable Surfaces: Elevator, Rudder, Flaps, Flap Track Fairings, Slats, Spoilers, Ailerons,.......

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: 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.
CAUTION: BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
  • 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.
ZONE: 300
ZONE: 500
ZONE: 600
ZONE: 700
ZONE: 800
1. Reason for the Job
Refer to the MPD TASK: 202800-01
DETAILED INSPECTION OF BONDING LEADS LOCATED ON THE FOLLOWING MOVABLE SURFACES: ELEVATOR, RUDDER, FLAPS, FLAP TRACK FAIRINGS, SLATS, SPOILERS, AILERONS, LANDING GEAR DOORS AND PASSENGER/CREW DOORS
Do this inspection on the movable surfaces that follow:
  • Flaps
  • Flap track fairings
  • Slats
  • Spoilers
  • Ailerons
  • Elevator
  • Rudder
  • Nose landing gear doors
  • Main landing gear doors
  • Passenger/crew doors.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE
No specific
AR
MIRROR - INSPECTION
No specific
AR
SAFETY BARRIER(S)
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
No specific
AR
WARNING NOTICE(S)
98D27803000000
1
LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
 B. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
300
STABILIZERS AND TAIL UNIT
500
LEFT WING
600
RIGHT WING
700
LANDING GEAR AND LANDING GEAR DOORS
800
DOORS
325BL, 325BR, 325CL, 325CR, 325DL, 325DR, 325EL, 325ER, 334BB, 334DB, 334FB, 334GB, 334HB, 344BB, 344DB, 344FB, 344GB, 344HB, 521AB, 522FB, 522NB, 522SB, 571AB, 573AB, 573BB, 573CB, 575AB, 575AT, 575BB, 575CB, 575DB, 575EB, 575FB, 575GB, 575KB, 575LB, 575MB, 590AB, 590BB, 621AB, 622FB, 622NB, 622SB, 671AB, 673AB, 673BB, 673CB, 675AB, 675AT, 675BB, 675CB, 675DB, 675EB, 675FB, 675GB, 675KB, 675LB, 675MB, 690AB, 690BB, 831FZ, 831GZ, 832FZ, 832GZ, 841FZ, 841GZ, 842FZ, 842GZ
522AB, 622AB
522YB, 622YB
 C. Referenced Information
REFERENCE
DESIGNATION
TASK 20-28-00-912-802-A
Electrical Bonding - General Maintenance Procedure
TASK 24-41-00-861-002-A
Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01
Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02
Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A
De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01
De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02
De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 25-23-46-000-001-A
Removal of the Door Linings from the Forward Passenger/Crew Doors
TASK 25-23-46-000-002-A
Removal of the Door Linings from the Aft Passenger/Crew Doors
TASK 25-23-46-400-001-A
Installation of the Door Linings on the Forward Passenger/Crew Doors
TASK 25-23-46-400-002-A
Installation of the Door Linings on the Aft Passenger/Crew Doors
TASK 27-50-00-866-008-A
Extension of the Flaps on the Ground
TASK 27-50-00-866-008-A-01
Extension of the Flaps/Slats on the Ground
TASK 27-50-00-866-009-A
Retraction of the Flaps on the Ground
TASK 27-50-00-866-009-A-01
Retraction of the Flaps/Slats on the Ground
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
TASK 29-10-00-863-001-A
Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-002-A
Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A
Pressurize the Blue Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A-01
Pressurize the Blue Hydraulic System with the Blue Electric Pump
TASK 29-10-00-864-001-A
Depressurize the Green Hydraulic System
TASK 29-10-00-864-002-A
Depressurize the Yellow Hydraulic System
TASK 29-10-00-864-003-A
Depressurize the Blue Hydraulic System
TASK 29-14-00-614-001-A
Depressurization of the Hydraulic Reservoirs
TASK 29-14-00-614-002-A
Pressurization of the Hydraulic Reservoirs through the Ground Connector
TASK 29-14-00-614-002-A-01
Pressurization of the Hydraulic Reservoirs with the Auxiliary Power Unit (APU)
TASK 32-00-00-481-002-A
Installation of the Safety Devices on the Landing Gear Doors
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
TASK 32-22-00-010-001-A
Nose Gear Doors - Ground Doors Opening
TASK 32-22-00-410-001-A
Nose Gear Doors - Ground Doors Closing
TASK 52-10-00-010-001-A
Opening of the Passenger/Crew Door
TASK 52-10-00-410-001-A
Closing of the Passenger/Crew Door
TASK 55-13-11-000-001-A
Remove/Open of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels
TASK 55-13-11-400-001-A
Install/Close of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels
TASK 55-33-13-010-002-A
Opening/Removal of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 55-33-13-410-002-A
Closing/Installation of the Trailing Edge Access-Panels of the Vertical Stabilizer
TASK 57-41-37-000-004-A
Removal of the Pressure Relief Panels
TASK 57-41-37-000-006-A
Removal of the Access Panels
TASK 57-41-37-400-002-A
Installation of the Pressure Relief Panels
TASK 57-41-37-400-006-A
Installation of the Access Panels
TASK 57-51-37-000-002-A
Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB)
TASK 57-51-37-000-004-A
Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)
TASK 57-51-37-000-005-A
Removal of the Access Panels 575KB(675KB), 575LB(675LB), 575MB(675MB)
TASK 57-51-37-000-007-A
Removal of the Access Panel
TASK 57-51-37-000-011-A
Removal of the Access Panels
TASK 57-51-37-400-002-A
Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB)
TASK 57-51-37-400-004-A
Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB)
TASK 57-51-37-400-005-A
Installation of the Access Panels 575KB(675KB), 575LB(675LB), 575MB(675MB)
TASK 57-51-37-400-007-A
Installation of the Access Panel
TASK 57-51-37-400-011-A
Installation of the Access Panels
F Bonding Leads located on Movable Surfaces
3. Job Set-up
Subtask 24-92-00-861-055-A
A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
Subtask 24-92-00-941-052-A
B. Safety Precautions
   (1) Install the ground safety locks on the landing gear doors (Ref. AMM TASK 32-00-00-481-002).
   (2) Put a WARNING NOTICE(S) in position to tell persons not to pressurize the hydraulic systems:
  • On the ground service panel 197CB.
  • In the cockpit, on the HYD/FUEL panel 40VU.
   (3) Put a WARNING NOTICE(S) in position in the cockpit to tell persons not to operate the flight controls.
   (4) Put a WARNING NOTICE(S) in position on the panel 400VU to tell persons not to operate the landing gear doors.
   (5) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
Subtask 24-92-00-860-086-A
C. Aircraft Maintenance Configuration
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) Extend the slats to the fully extended position (Ref. AMM TASK 27-80-00-866-004).
   (2) Extend the flaps to the fully extended position (Ref. AMM TASK 27-50-00-866-008).
   (3) Install the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION on the flap/slat control lever.
   (4) Depressurize the aircraft hydraulic systems
(Ref. AMM TASK 29-10-00-864-001), (Ref. AMM TASK 29-10-00-864-003) (Ref. AMM TASK 29-10-00-864-002).
   (5) Depressurize the hydraulic reservoirs (Ref. AMM TASK 29-14-00-614-001).
Subtask 24-92-00-865-050-A
D. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B11
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B09
49VUFLIGHT CONTROLS/SEC1/NORM/SPLY21CE1B08
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB07
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
49VUAUTO FLT/FAC1/28VDC5CC1B04
49VUAUTO FLT/FAC1/26VAC14CC1B03
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B06
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B04
49VUFLIGHT CONTROLS/SEC1/NORM/SPLY21CE1B03
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB02
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
49VUAUTO FLT/FAC1/28VDC5CC1H10
49VUAUTO FLT/FAC1/26VAC14CC1H09
** ON A/C ALL
105VUFLIGHT CONTROLS/ELAC2/STBY SPLY16CE2A02
105VUFLT CTL/ELAC1/STBY SPLY16CE1A01
105VUFLT CTL/SEC1/STBY SPLY22CEB01
121VUAUTO FLT/RUDDER/TRIM/IND15CCM20
121VUAUTO FLT/FAC2/28VDC5CC2M19
121VUAUTO FLT/FAC2/26VAC14CC2M18
121VUFLIGHT CONTROLS/WTB/FLP/SYS212CVP20
121VUFLIGHT CONTROLS/FLP/CTL AND/MONG/SYS28CVQ21
121VUFLIGHT CONTROLS/SEC3/SPLY21CE3Q19
121VUFLIGHT CONTROLS/SEC2/SPLY21CE2Q18
121VUFLIGHT CONTROLS/THS ACTR/MOT319CE3Q17
121VUFLIGHT CONTROLS/THS ACTR/MOT119CE1Q16
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
121VUFLIGHT CONTROLS/ELAC2/NORM/SPLY15CE2R20
122VUFLIGHT CONTROLS/WTB/FLP/SYS110CVS07
Subtask 24-92-00-010-078-A ** ON A/C NOT FOR ALL
E. Get Access
   (1) Open the MLG doors (Ref. AMM TASK 32-12-00-010-001).
   (2) Open the NLG doors (Ref. AMM TASK 32-22-00-010-001).
   (3) Open the passenger/crew doors (Ref. AMM TASK 52-10-00-010-001).
   (4) Remove the door lining panels (Ref. AMM TASK 25-23-46-000-001) (Ref. AMM TASK 25-23-46-000-002):
   (5) Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the applicable zone.
   (6) Remove the access panels.
     (a) For the flaps:
       1 For the left wing, remove the access panels:
       2 For the right wing, remove the access panels:
     (b) For the spoilers:
       1 For the left wing, remove the access panels:
       2 For the right wing, remove the access panels:
   (7) Remove the access panels.
     (a) For the slats:
     (b) For the ailerons:
       1 For the left wing, remove the access panels:
       2 For the right wing, remove the access panels:
     (c) For the elevators:
     (d) For the rudder:
Subtask 24-92-00-010-078-C ** ON A/C NOT FOR ALL
E. Get Access
   (1) Open the MLG doors (Ref. AMM TASK 32-12-00-010-001).
   (2) Open the NLG doors (Ref. AMM TASK 32-22-00-010-001).
   (3) Open the passenger/crew doors (Ref. AMM TASK 52-10-00-010-001).
   (4) Remove the door lining panels (Ref. AMM TASK 25-23-46-000-001) (Ref. AMM TASK 25-23-46-000-002):
   (5) Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE in position below the applicable zone.
   (6) Remove the access panels.
     (a) For the flaps:
       1 For the left wing, remove the access panels:
       2 For the right wing, remove the access panels:
     (b) For the spoilers:
       1 For the left wing, remove the access panels:
       2 For the right wing, remove the access panels:
   (7) Remove the access panels.
     (a) For the slats:
     (b) For the ailerons:
       1 For the left wing, remove the access panels:
       2 For the right wing, remove the access panels:
     (c) For the elevators:
     (d) For the rudder:
4. Procedure
Subtask 24-92-00-220-061-A
A. General Inspection Recommendations
   (1) Do a detailed inspection of the bonding leads on the movable surfaces that follow:
  • MLG, NLG and passenger/crew doors
  • Flaps
  • Flap track movable fairings
  • Spoilers
  • Surfaces between slats 2 and 3, 3 and 4, 4 and 5
  • Slat tracks No. 1, No. 5 and No. 11
  • Ailerons
  • Elevators
  • Rudder.
NOTE: Use an MIRROR - INSPECTION, if necessary.
   (2) During the inspection, replace all the bonding leads if they are found broken or if more than 25 per cent of their strands are damaged (Ref. AMM TASK 20-28-00-912-802).
NOTE: Because it is not possible to know with precision the number of damaged strands when a bonding lead is damaged: 25 per cent is equal to 1/4 of the section (i.e.: 3.25 mm2 (0.01 in.2) for a section of 13 mm2 (0.02 in.2) or 1.75 mm2 (0.00 in.2) for a section of 7 mm2 (0.01 in.2)).
   (3) If you cannot replace all the bonding leads before the planned aircraft release, the bonding lead installations that follow are satisfactory.
Subtask 24-92-00-220-062-A ** ON A/C NOT FOR ALL
B. Inspection of the Bonding Leads Installed on the Flaps, Flap Track Fairings, Slats, Spoilers, Ailerons, Nose Landing-Gear Doors, Main Landing-Gear Doors and Passenger/Crew Doors
   (1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory:
     (a) Movable surface bonded with two leads:
  • If one lead is broken and less than 25 percent of the strands of the other bonding lead is damaged.
     (b) Movable surface bonded with three leads:
  • If two leads are broken and less than 25 percent of the strands of the other bonding lead is damaged.
   (2) Replace all the remaining broken or damaged bonding leads in less than 24 months or 7500 flight hours or 5000 flight cycles (the one that occurs first).
Subtask 24-92-00-220-063-A ** ON A/C NOT FOR ALL
C. Inspection of the Elevator Bonding Leads
   (1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory:
     (a) Bonding lead installed near the elevator tip:
  • If less than 25 percent of its strands is damaged.
     (b) And for the other bonding leads installed on the elevator:
  • If only one lead is broken or has more than 25 percent of its strands damaged and the other bonding leads have less than 25 percent of their strands damaged.
   (2) Replace all the remaining broken or damaged bonding leads in less than 24 months or 7500 flight hours or 5000 flight cycles (the one that occurs first).
Subtask 24-92-00-220-064-A ** ON A/C NOT FOR ALL
D. Inspection of the Rudder Bonding Leads
   (1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the installations that follow are satisfactory:
     (a) Bonding leads installed on the rudder hinge arms No. 1 and 7 (on the top and bottom part of the rudder):
  • If less than 25 percent of their strands are damaged.
     (b) And for bonding leads installed on the rudder hinge arms No. 2, 3, 4, 5 and 6:
  • If only one lead is broken or has more than 25 percent of its strand damaged
  • And if the other bonding leads have less than 25 percent of their strands damaged.
   (2) Replace all the remaining broken or damaged bonding leads in less than 120 days or 750 flight hours or 750 flight cycles (the one that occurs first).
Subtask 24-92-00-220-062-B ** ON A/C NOT FOR ALL
E. Inspection of the Bonding Leads Installed on the Flaps, Flap Track Fairings, Slats, Spoilers, Ailerons, Nose Landing-Gear Doors, Main Landing-Gear Doors and Passenger/Crew Doors
   (1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory:
     (a) Movable surface with two bonding leads:
  • If one bonding lead is broken and less than 25 percent of the strands of the other bonding lead are damaged.
     (b) Movable surface with three bonding leads:
  • If two bonding leads are broken and less than 25 percent of the strands of the other bonding lead are damaged.
   (2) Replace all the remaining broken or damaged bonding leads in less than 24 months or 7500 flight hours or 5000 flight cycles (the one that occurs first).
Subtask 24-92-00-220-063-B ** ON A/C NOT FOR ALL
F. Inspection of the Elevator Bonding Leads
   (1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory:
     (a) Bonding lead installed near the elevator tip:
  • If less than 25 percent of its strands are damaged.
     (b) And for the other bonding leads installed on the elevator:
  • If only one bonding lead is broken or has more than 25 percent of its strands damaged and the other bonding leads have less than 25 percent of their strands damaged.
   (2) Replace all the remaining broken or damaged bonding leads in less than 24 months or 7500 flight hours or 5000 flight cycles (the one that occurs first).
Subtask 24-92-00-220-064-B ** ON A/C NOT FOR ALL
G. Inspection of the Rudder Bonding Leads
   (1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the installations that follow are satisfactory:
     (a) Bonding leads installed on the rudder hinge arms No. 1 and 7 (on the top and bottom parts of the rudder):
  • If less than 25 percent of their strands are damaged.
     (b) And for bonding leads installed on the rudder hinge arms No. 2, 3, 4, 5 and 6:
  • If only one bonding lead is broken or has more than 25 percent of its strands damaged
  • And if the other bonding leads have less than 25 percent of their strands damaged.
   (2) Replace all the remaining broken or damaged bonding leads in less than 120 days or 750 flight hours or 750 flight cycles (the one that occurs first).
5. Close-up
Subtask 24-92-00-410-078-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) Install these access panels.
     (a) For the slats:
     (b) For the ailerons:
       1 For the left wing, install the access panels:
       2 For the right wing, install the access panels:
     (c) For the elevators:
     (d) For the rudder:
   (2) Install the access panels.
     (a) For the flaps:
       1 For the left wing, install the access panels:
       2 For the right wing, install the access panels:
     (b) For the spoilers:
       1 For the left wing, install the access panels:
       2 For the right wing, install the access panels:
   (3) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).
   (4) Close the NLG doors (Ref. AMM TASK 32-22-00-410-001).
   (5) Install the door lining panels 831FZ 841FZ 831GZ 841GZ, 832FZ 842FZ 832GZ 842GZ (Ref. AMM TASK 25-23-46-400-001) (Ref. AMM TASK 25-23-46-400-002).
   (6) Close the passenger/crew doors (Ref. AMM TASK 52-10-00-410-001).
Subtask 24-92-00-410-078-C ** ON A/C NOT FOR ALL
A. Close Access
   (1) Install these access panels.
     (a) For the slats:
     (b) For the ailerons:
       1 For the left wing, install the access panels:
       2 For the right wing, install the access panels:
     (c) For the elevators:
     (d) For the rudder:
   (2) Install the access panels.
     (a) For the flaps:
       1 For the left wing, install the access panels:
       2 For the right wing, install the access panels:
     (b) For the spoilers:
       1 For the left wing, install the access panels:
       2 For the right wing, install the access panels:
   (3) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).
   (4) Close the NLG doors (Ref. AMM TASK 32-22-00-410-001).
   (5) Install the door lining panels 831FZ 841FZ 831GZ 841GZ, 832FZ 842FZ 832GZ 842GZ (Ref. AMM TASK 25-23-46-400-001) (Ref. AMM TASK 25-23-46-400-002).
   (6) Close the passenger/crew doors (Ref. AMM TASK 52-10-00-410-001).
Subtask 24-92-00-865-052-A
B. 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/ELAC1/NORM/SPLY15CE1B11
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B09
49VUFLIGHT CONTROLS/SEC1/NORM/SPLY21CE1B08
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB07
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB06
49VUAUTO FLT/FAC1/28VDC5CC1B04
49VUAUTO FLT/FAC1/26VAC14CC1B03
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B06
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B04
49VUFLIGHT CONTROLS/SEC1/NORM/SPLY21CE1B03
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB02
49VUFLIGHT CONTROLS/SLT/CTL AND MONG/SYS15CVB01
49VUAUTO FLT/FAC1/28VDC5CC1H10
49VUAUTO FLT/FAC1/26VAC14CC1H09
** ON A/C ALL
105VUFLIGHT CONTROLS/ELAC2/STBY SPLY16CE2A02
105VUFLT CTL/ELAC1/STBY SPLY16CE1A01
105VUFLT CTL/SEC1/STBY SPLY22CEB01
121VUAUTO FLT/RUDDER/TRIM/IND15CCM20
121VUAUTO FLT/FAC2/28VDC5CC2M19
121VUAUTO FLT/FAC2/26VAC14CC2M18
121VUFLIGHT CONTROLS/WTB/FLP/SYS212CVP20
121VUFLIGHT CONTROLS/FLP/CTL AND/MONG/SYS28CVQ21
121VUFLIGHT CONTROLS/SEC3/SPLY21CE3Q19
121VUFLIGHT CONTROLS/SEC2/SPLY21CE2Q18
121VUFLIGHT CONTROLS/THS ACTR/MOT319CE3Q17
121VUFLIGHT CONTROLS/THS ACTR/MOT119CE1Q16
121VUFLIGHT CONTROLS/SLT/CTL/SYS27CVR21
121VUFLIGHT CONTROLS/ELAC2/NORM/SPLY15CE2R20
122VUFLIGHT CONTROLS/WTB/FLP/SYS110CVS07
Subtask 24-92-00-860-087-A
C. Put the aircraft back to its initial configuration.
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Pressurize the aircraft hydraulic systems
(Ref. AMM TASK 29-10-00-863-001), (Ref. AMM TASK 29-10-00-863-003) and (Ref. AMM TASK 29-10-00-863-002).
   (3) Pressurize the hydraulic reservoirs (Ref. AMM TASK 29-14-00-614-002).
   (4) Retract the slats (Ref. AMM TASK 27-80-00-866-005).
   (5) Retract the flaps (Ref. AMM TASK 27-50-00-866-009).
   (6) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
   (7) Remove the WARNING NOTICE(S).
   (8) Remove the access platform(s).
Subtask 24-92-00-862-068-A
D. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
[Rev.10 from 2021] 2026.04.01 04:51:13 UTC
"Aviabrain" 2025