DOC AIRBUS | AMM A320FReplacement of the Flap Interconnecting Strut Rod-End and Locking Device
TASK 27-51-44-960-001-A
Replacement of the Flap Interconnecting Strut Rod-End and Locking Device
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 27-51-44-941-064-A
Subtask 27-51-44-020-056-A
(2) Loosen the locknut (11).
(3) Remove the rod-end (10).
(4) Remove and retain the locking device (12).
(5) Remove the locknut (11) from the rod-end (10). Discard the old rod-end (10).
(6) Install the locknut (11) on the new AIPC 27-51-44-01-010 ROD-END (10).
(7) Install the locking device (12).
(8) Install the new rod-end (10).
(9) Put the interconnecting strut (1) in position in the attachment bracket (6).
(10) Install the bolt (9), the washer (14) and the nut (16).
Subtask 27-51-44-960-051-A
(2) Loosen the locknut (11).
(3) Remove the rod-end (10).
(4) Remove and discard the locking device (12).
(5) Install the new AIPC 27-51-44-01-030 LOCKING DEVICE (12).
(6) Install the rod-end (10).
(7) Put the interconnecting strut (1) in position in the attachment bracket (6).
(8) Install the bolt (9), the washer (14) and the nut (16).
5. Close-up
Subtask 27-51-44-820-055-C
[Rev.10 from 2021]
2026.04.01 06:58:32 UTC
Replacement of the Flap Interconnecting Strut Rod-End and Locking Device
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.
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
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | SAFETY BARRIER(S) |
| No specific | AR | SAFETY CLIP - CIRCUIT BREAKER |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 1.7 and 1.1 m.daN (150.44 and 97.35 lbf.in )  | |
| No specific | Torque wrench: range to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft ) | |
| 98D27504031000 | 1 | PIN-SETTING |
| 98D27803000000 | 1 | LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.12ACC1) | Corrosion Preventive Compound-Heavy Duty Soft Film - |
| (Material No.14QFB1) | Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 581 | FLAP N° 1 |
| 587 | FLAP N° 2 |
| 681 | FLAP N° 1 |
| 687 | FLAP N° 2 |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 15 | COTTER PIN | AIPC 27-51-05-01-100 |
| 10 | ROD-END | AIPC 27-51-44-01-010 |
| 12 | LOCKING DEVICE | AIPC 27-51-44-01-030 |
| 15 | COTTER PIN | AIPC 27-51-85-01-110 |
| REFERENCE | DESIGNATION |
|---|---|
| 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 27-51-00-710-002-A | Operational Test of the Flap Interconnecting Strut and the Flap-Attachment Failure-Detection Sensors |
| TASK 27-51-00-820-003-A | To do a Check of the Flap Rigged Position (with the Sharks Fin) |
| 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 |
Rod-End of Flap Interconnecting StrutSubtask 27-51-44-941-064-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 controls.
Subtask 27-51-44-860-066-A (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 controls.
B. Aircraft Maintenance Configuration
(2) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
(3) Remove the upper kink-seal (2) and the lower kink-seal (3) from the inboard flap (4) and the outboard flap (5) (Ref. AMM TASK 27-54-61-000-002).
(4) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(5) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008).
(6) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
Subtask 27-51-44-865-076-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) 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.
(3) Remove the upper kink-seal (2) and the lower kink-seal (3) from the inboard flap (4) and the outboard flap (5) (Ref. AMM TASK 27-54-61-000-002).
(4) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(5) Fully extend the flaps (Ref. AMM TASK 27-50-00-866-008).
(6) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
C. Open, safety and tag this(these) circuit breaker(s):
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 |
Subtask 27-51-44-020-056-A
A. Preparation for Replacement of the Rod-End and Locking Device
(1) Use a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the:
(3) Remove the nut (16), the washer (14) and the bolt (9).
(4) Disconnect the flap interconnecting strut (1) from the attachment bracket (6).
(5) Pull the actuating rod (7) out of the flap interconnecting strut (1) until it touches the internal limit.
Subtask 27-51-44-960-050-A (1) Use a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the:
- Flap interconnecting strut (1)
- Flap attachment bracket (6).
(3) Remove the nut (16), the washer (14) and the bolt (9).
(4) Disconnect the flap interconnecting strut (1) from the attachment bracket (6).
(5) Pull the actuating rod (7) out of the flap interconnecting strut (1) until it touches the internal limit.
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.
B. Replace the Rod-End of the Interconnecting Strut AssemblyNOTE: You can do this procedure at the same time as you do the procedure to replace the locking device (12).
(1) Remove and discard the lockwire from the locknut (11). (2) Loosen the locknut (11).
(3) Remove the rod-end (10).
(4) Remove and retain the locking device (12).
(5) Remove the locknut (11) from the rod-end (10). Discard the old rod-end (10).
(6) Install the locknut (11) on the new AIPC 27-51-44-01-010 ROD-END (10).
(7) Install the locking device (12).
(8) Install the new rod-end (10).
(9) Put the interconnecting strut (1) in position in the attachment bracket (6).
(10) Install the bolt (9), the washer (14) and the nut (16).
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.
C. Replace the Locking Device of the Interconnecting Strut AssemblyNOTE: You can do this procedure at the same time as you do the procedure to replace the rod-end (10).
(1) Remove and discard the lockwire from the locknut (10). (2) Loosen the locknut (11).
(3) Remove the rod-end (10).
(4) Remove and discard the locking device (12).
(5) Install the new AIPC 27-51-44-01-030 LOCKING DEVICE (12).
(6) Install the rod-end (10).
(7) Put the interconnecting strut (1) in position in the attachment bracket (6).
(8) Install the bolt (9), the washer (14) and the nut (16).
Subtask 27-51-44-820-055-C
A. Adjustment of the Interconnecting Strut (if necessary)
(a) Align the rod-end (10) with the flap until you can install the bolt (9).
(b) If necessary, remove and discard the lockwire from the locknut (11).
(c) Loosen the locknut (11) sufficiently to let you turn the nut (13).
(d) Adjust the nut (13) until you can install the 98D27504031000 PIN-SETTING. Make sure that you can see the threads of the rod-end (10) through the check hole (17). If you cannot see the threads of the rod-end (10) through the check hole (17), do a check of the flap rigging (Ref. AMM TASK 27-51-00-820-003).
(e) Tighten the locknut (11).
(f) Install the washer (14) and the nut (16).
(g) Torque the nut (16) to between 1.7 and 1.1 m.daN (150.44 and 97.35 lbf.in ).
(i) If you loosened the locknut (11), TORQUE it to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft ).
(j) Safety the locknut (11) with14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(3) Remove the 98D27504031000 PIN-SETTING from the inspection/setting hole (8) in the interconnecting strut (1).
(4) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:
Subtask 27-51-44-865-077-A 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 (8) in the interconnecting strut (1). NOTE: The interconnecting strut (1) can have one or two inspection/setting holes (8). If there are two, use the hole that is not blocked by the aircraft structure.
(2) If necessary, adjust the actuating rod (7) of the interconnecting strut (1) so that you can install the 98D27504031000 PIN-SETTING as follows: (a) Align the rod-end (10) with the flap until you can install the bolt (9).
(b) If necessary, remove and discard the lockwire from the locknut (11).
(c) Loosen the locknut (11) sufficiently to let you turn the nut (13).
(d) Adjust the nut (13) until you can install the 98D27504031000 PIN-SETTING. Make sure that you can see the threads of the rod-end (10) through the check hole (17). If you cannot see the threads of the rod-end (10) through the check hole (17), do a check of the flap rigging (Ref. AMM TASK 27-51-00-820-003).
(e) Tighten the locknut (11).
(f) Install the washer (14) and the nut (16).
(g) Torque the nut (16) to between 1.7 and 1.1 m.daN (150.44 and 97.35 lbf.in )
. NOTE: It is possible to have a clearance between the bush and the strut attachment bracket.
(h) Install a new AIPC 27-51-05-01-100 COTTER PIN (15) or AIPC 27-51-85-01-110 COTTER PIN (15). (i) If you loosened the locknut (11), TORQUE it to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft )
. (j) Safety the locknut (11) with
(3) Remove the 98D27504031000 PIN-SETTING from the inspection/setting hole (8) in the interconnecting strut (1).
(4) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:
- Head of the bolt (9)
- Nut (16)
- Washer (14)
- Cotter pin (15).
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-51-44-710-059-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 |
C. 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:
Subtask 27-51-44-860-067-A (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. |
| 1.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. - FLP RH PROX SNSR 2 OR WIRING TO LGCIU 2. |
| | - 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. |
D. Aircraft Maintenance Configuration
(1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(2) Retract the flaps to position 1 (Ref. AMM TASK 27-50-00-866-009).
(3) Install the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION on the flap/slat control lever.
(4) Install the upper and lower kink-seals (2) and (3) to the inboard and the outboard flaps (4) and (5) (Ref. AMM TASK 27-54-61-400-006).
(5) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is removed from the flap/slat control lever.
(6) Make sure that the flaps are fully retracted (Ref. AMM TASK 27-50-00-866-009).
Subtask 27-51-44-710-060-A Subtask 27-51-44-942-058-A (1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(2) Retract the flaps to position 1 (Ref. AMM TASK 27-50-00-866-009).
(3) Install the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION on the flap/slat control lever.
(4) Install the upper and lower kink-seals (2) and (3) to the inboard and the outboard flaps (4) and (5) (Ref. AMM TASK 27-54-61-400-006).
(5) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is removed from the flap/slat control lever.
(6) Make sure that the flaps are fully retracted (Ref. AMM TASK 27-50-00-866-009).
F. 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.