W DOC AIRBUS | AMM A320F

Adjustment of the Interconnecting Strut

TASK 27-51-44-820-001-A
Adjustment of the Interconnecting Strut

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: 580
ZONE: 680
1. Reason for the Job
To adjust the rigged position of the interconnecting strut
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific
AR
SAFETY BARRIER(S)
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft ) T
98D27504031000
1
PIN-SETTING
98D27803000000
1
LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
98L12003001000
1
HARNESS,SAFETY
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.14QFB1)
Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
580
LEFT WING FLAPS AND SPOILERS
680
RIGHT WING FLAPS AND SPOILERS
 D. Referenced Information
REFERENCE
DESIGNATION
TASK 27-00-00-080-002-A
Removal of the Flap/Slat Control-Lever Locking Tool (98D27803000000)
TASK 27-00-00-480-002-A
Installation of the Flap/Slat Control-Lever Locking Tool (98D27803000000)
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 27-51-00-820-003-A
To do a Check of the Flap Rigged Position (with the Sharks Fin)
TASK 27-51-44-960-001-A
Replacement of the Flap Interconnecting Strut Rod-End and Locking Device
TASK 27-54-00-710-001-A
Operational Test of the Flap System
TASK 27-54-61-000-002-A
Removal of the Flap Kink-Seals and Cushion-Seals
TASK 27-54-61-400-006-A
Installation of the Flap Kink-Seals and Cushion-Seals
TASK 31-32-00-860-006-A
Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page
F Adjustment of the Interconnecting Strut ** ON A/C NOT FOR ALL
F Adjustment of the Interconnecting Strut ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 27-51-44-941-063-A
A. Safety Precautions
   (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
   (2) Put a WARNING NOTICE(S) in position to tell persons not to operate the flap/slat controls.
WARNING: BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.
   (3) Put on and attach a 98L12003001000 HARNESS,SAFETY before you start work in the work area.
Subtask 27-51-44-860-064-A
B. 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 flaps to position 1 (Ref. AMM TASK 27-50-00-866-008).
   (2) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever (Ref. AMM TASK 27-00-00-480-002).
   (3) Remove the lower kink seal, the cushion seals and the upper kink seals from the flaps (Ref. AMM TASK 27-54-61-000-002).
   (4) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position:
  • For the left wing, below zone 580
  • For the right wing, below zone 680.
Subtask 27-51-44-865-074-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/FLP/CTL AND MONG/SYS16CVB07
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB02
** ON A/C ALL
121VUFLIGHT CONTROLS/FLP/CTL AND/MONG/SYS28CVQ21
4. Procedure
Subtask 27-51-44-210-058-A
A. Inspection
   (1) Do an inspection of the rod-end (4) and the locking device (located between the locknut (1) and the nut (2)), for wear or damage. Replace a worn or damaged rod-end, or a worn or damaged locking device (Ref. AMM TASK 27-51-44-960-001).
Subtask 27-51-44-820-053-B
B. Adjustment of the Interconnecting Strut
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
   (1) Install the 98D27504031000 PIN-SETTING in the inspection/setting hole of the interconnecting strut (3).
NOTE: The interconnecting strut (3) can have one or two inspection/setting holes. If there are two, use the hole that is not blocked by the aircraft structure.
   (2) If necessary, adjust the actuating rod of the interconnecting strut (3) until you can install the 98D27504031000 PIN-SETTING as follows:
     (a) If necessary, remove and discard the lockwire from the locknut (1).
     (b) Loosen the locknut (1) sufficiently to let you turn the nut (2).
     (c) Adjust the nut (2) until you can install the 98D27504031000 PIN-SETTING.
     (d) Make sure that you can see the threads of the rod-end (4) through the check hole.
     (e) If you cannot see the threads of the rod-end (4) through the check hole, do a check of the flap rigging (Ref. AMM TASK 27-51-00-820-003).
     (f) Torque the locknut (1) to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft ) T.
     (g) Safety the locknut (1) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
   (3) Remove the 98D27504031000 PIN-SETTING from the hole in the interconnecting strut (3).
Subtask 27-51-44-865-075-A
C. Make sure that this(these) circuit breaker(s) is(are) closed:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB07
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB02
** ON A/C ALL
121VUFLIGHT CONTROLS/FLP/CTL AND/MONG/SYS28CVQ21
Subtask 27-51-44-710-056-A
D. Test
   (1) Get access to the flight controls (F/CTL) page of the MCDU (Ref. AMM TASK 31-32-00-860-006).
   (2) Do this test of the flap interconnecting strut and the flap-attachment failure-detection sensors:
ACTION
RESULT
On the MCDU:
On the MCDU:
1.Push (in) the line key < SFCC 1.
  • the MCDU shows the SFCC 1 page.
2.Push (in) the line key SYSTEM STATUS FLP >.
  • the MCDU shows the SFCC 1 SYSTEM STATUS FLAP page. These subsequent messages must not occur:
    - FLP 1 NO SFCC 2 DATA CHECK WIRING & SFCC 2
    - FLP 1 FAULTY FLP 2 DATA CHECK SFCC 1 OR 2
    - NO LGCIU 1 DATA CHECK WIRING TO FLP 1
    - FLP LH PROX SNSR 1 MISADJUSTMENT and FLP LH PROX SNSR 2 OR WIRING TO LGCIU 2
    - FLP LH PROX SNSR 1 OR WIRING TO LGCIU 1
    - FLP LH PROX SNSR 2 OR WIRING TO LGCIU 2
    - FLP RH PROX SNSR 1 MISADJUSTMENT and FLP RH PROX SNSR 2 OR WIRING TO LGCIU 2
    - FLP RH PROX SNSR 1 OR WIRING TO LGCIU 1
    - FLP RH PROX SNSR 2 OR WIRING TO LGCIU 2.
3.Push (in) the line key <RETURN.
  • the MCDU shows the SFCC 1 page.
4.Push (in) the line key <RETURN.
  • the MCDU shows the SYSTEM REPORT/TEST PAGE.
5.Push (in) the line key < SFCC 2.
  • the MCDU shows the SFCC 2 page.
6.Push (in) the line key SYSTEM STATUS FLP >.
  • the MCDU shows the SFCC 2 SYSTEM STATUS FLAP page. These subsequent messages must not occur:
    - FLP 2 NO SFCC 1 DATA CHECK WIRING & SFCC 1
    - FLP 2 FAULTY FLP 1 DATA CHECK SFCC 1 OR 2
    - NO LGCIU 2 DATA CHECK WIRING TO FLP 2
    - FLP LH PROX SNSR 2 MISADJUSTMENT and FLP LH PROX SNSR 1 OR WIRING TO LGCIU 1
    - FLP LH PROX SNSR 1 OR WIRING TO LGCIU 1
    - FLP LH PROX SNSR 2 OR WIRING TO LGCIU 2
    - FLP RH PROX SNSR 2 MISADJUSTMENT and FLP RH PROX SNSR 1 OR WIRING TO LGCIU 1
    - FLP RH PROX SNSR 1 OR WIRING TO LGCIU 1
    - FLP RH PROX SNSR 2 OR WIRING TO LGCIU 2.
Subtask 27-51-44-710-057-A
E. Complete Test
   (1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever on panel 114VU (Ref. AMM TASK 27-00-00-080-002).
   (2) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001).
   (3) Remove the access platform(s).
5. Close-up
Subtask 27-51-44-410-057-A
A. Close Access
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 work area is clean and clear of tools and other items.
   (2) Install the lower kink seal, the cushion seals and the upper kink seals on the flaps (Ref. AMM TASK 27-54-61-400-006).
   (3) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
Subtask 27-51-44-942-057-A
B. Removal of Equipment
   (1) Remove the SAFETY BARRIER(S).
   (2) Remove the WARNING NOTICE(S).
   (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.04.01 06:56:51 UTC
"Aviabrain" 2025