Detailed Inspection of Interconnecting Strut and Attachments

TASK 27-51-44-200-001-A
Detailed Inspection of Interconnecting Strut and Attachments

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.

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:

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
Refer to the MPD TASK: 275144-01
DETAILED INSPECTION OF INTERCONNECTING STRUT AND ATTACHMENTS
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific	1	GAGE - SET, FEELER
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 )
98D27504008000	1	GAGE - GO NO GO
98D27504031000	1	PIN-SETTING
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
98L12003001000	AR	HARNESS,SAFETY

B. Consumable Materials

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 -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
580	LEFT WING FLAPS AND SPOILERS
680	RIGHT WING FLAPS AND SPOILERS

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
14	COTTER PIN	AIPC 27-51-05-01-100
14	COTTER PIN	AIPC 27-51-85-01-220

E. 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 27-51-00-710-002-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 27-51-44-960-001-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
Flap Interconnecting Strut - Inspection/Check ** ON A/C NOT FOR ALL
Flap Interconnecting Strut - Inspection/Check ** ON A/C NOT FOR ALL
Flap Interconnecting Strut - Radial Play

3. Job Set-up
Subtask 27-51-44-941-058-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.

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 27-51-44-860-059-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 applicable upper and lower kink-seals (1) and (2) from the inboard and the outboard flaps (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 (Ref. AMM TASK 27-00-00-080-002).
(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 (Ref. AMM TASK 27-00-00-480-002).
(7) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position, below the applicable zone:

For the left wing, below zone 580
For the right wing, below zone 680.

Subtask 27-51-44-865-068-A

C. Open, safety and tag this(these) circuit breaker(s):

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 27-51-44-020-054-A

D. 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 the:

Flap interconnecting strut
Flap attachment brackets (5) and (8).

(2) Remove and discard the cotter pin (14).
(3) Remove the nut (15), washer (13) and bolt (16).
(4) Disconnect the flap interconnecting strut from the attachment bracket (8).
(5) Pull the actuating rod out of the flap interconnecting strut until it touches the internal limit.

4. Procedure

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.

Subtask 27-51-44-210-053-A

A. Inspection of the Interconnecting Strut and Attachments
(1) Do an inspection of the actuating rod for damage and corrosion.
(2) Do an inspection of the flap interconnecting-strut internal structure, through the inspection holes (7), for damage and corrosion.
(3) Do an inspection of the flap interconnecting strut for:

Cracks
Damage
Corrosion
Damaged paint and sealant
Correct condition of the electrical plugs (4)
Correct condition of the electrical cables (3)
Correct condition of all the fasteners of the attachment brackets (5) and (8)
Correct condition of all the safety devices
Correct condition of the bearings of the flap interconnecting strut, as far as is possible
Correct condition of the bolts (6) and (16), as far as is possible.

(4) Make sure that the rod-end (9) or locking device (11) is not worn or damaged. Replace a worn or damaged rod-end, or a worn or damaged locking device (Ref. AMM TASK 27-51-44-960-001).
(5) Make sure that the word 'TOP' on the flap interconnecting strut is at the top.
(6)

Flap Interconnecting Strut - Radial Play

(a) Make sure that the actuating rod is fully extended.
(b) Do the check of the radial play in the horizontal axis:

Manually push the actuating rod end (in the horizontal axis) until space Y is closed on the other side of the forward bush.
Use a GAGE - SET, FEELER and measure the dimension X (between the actuating rod and the forward bush).
Make sure that the dimension X is not more than 0.4 mm (0.0157 in.). If the dimension X is more than 0.4 mm (0.0157 in.) you must replace the interconnecting strut.

Manually push the actuating rod end (in the vertical axis) until space Y is closed on the other side of the forward bush.
Use a GAGE - SET, FEELER and measure the dimension X (between the actuating rod and the forward bush).
Make sure that the dimension X is not more than 0.4 mm (0.0157 in.). If the dimension X is more than 0.4 mm (0.0157 in.) you must replace the interconnecting strut.

(7) Push the actuating rod into the flap interconnecting strut until it touches the internal limit.
(8) Put the interconnecting strut in position in the attachment bracket (8).
(9) Install the bolt (16), the washer (13) and the nut (15).
(10) Do an operational test of the flap interconnecting strut and the flap-attachment failure-detection sensors (Ref. AMM TASK 27-51-00-710-002).

5. Close-up

NOTE: The subsequent steps must be done after all the maintenance procedures are completed on the flap system.

Subtask 27-51-44-420-056-A

A. Connection of the Interconnecting Strut to the Flap Attachment Bracket

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 interconnecting strut is correctly set, as follows:
(a) Extend the flaps to position 1 (Ref. AMM TASK 27-50-00-866-008).
(b) Install the 98D27504008000 GAGE - GO NO GO in the inspection/setting hole. The strut is correctly set if the gage goes fully into the inspection/setting hole.

NOTE: The 98D27504008000 GAGE - GO NO GO is installed through the inspection/setting hole and a groove in the actuating rod. When the strut is set during its initial installation, the inspection/setting hole and the groove align fully. After flap operation, because of the flap tolerances, the inspection/setting hole and the actuating rod groove will not fully align. This is permitted if the check with the 98D27504008000 GAGE - GO NO GO is satisfactory.

If you can install the 98D27504008000 GAGE - GO NO GO, the interconnecting strut is correctly set. If not, the strut is incorrectly set and must be adjusted.

NOTE: The interconnecting strut can have one or two inspection/setting holes. If there are two, it is necessary use the hole that is not blocked by the aircraft structure.

(c) If the gage does not go fully into the inspection/setting hole:
1 Remove the 98D27504008000 GAGE - GO NO GO.
2 Do the adjustment of the interconnecting strut given in paragraph 5.B.
(d) If no adjustment of the interconnecting strut is necessary:
1 Remove the 98D27504008000 GAGE - GO NO GO.
2 TORQUE the nut (15) to between 1.7 and 1.1 m.daN (150.44 and 97.35 lbf.in )

.
3 Install a new AIPC 27-51-05-01-100 COTTER PIN (14) or AIPC 27-51-85-01-220 COTTER PIN (14).
(2) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:

Head of the bolt (16)
Nut (15)
Washer (13)
Cotter pin (14).

(3) Make sure that the work area is clean and clear of tools and other items.

Subtask 27-51-44-820-054-C ** ON A/C NOT FOR ALL

B. Adjustment of the Interconnecting Strut (if necessary)

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 in the interconnecting strut.

NOTE: The interconnecting strut 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 so that you can install the 98D27504031000 PIN-SETTING as follows:
(a) Align the rod-end (9) with the flap until you can install the bolt (16).
(b) If necessary, remove and discard the lockwire from the locknut (10).
(c) Loosen the locknut (10).
(d) Adjust the nut (12) until you can install the 98D27504031000 PIN-SETTING. Make sure that you can see the threads of the rod-end (9) through the check hole. If you cannot see the threads of the rod-end (9) through the check hole, check the flap rigging (Ref. AMM TASK 27-51-00-820-003).
(e) Tighten the locknut (10).
(f) Install the washer (13) and the nut (15).
(g) TORQUE the nut (15) 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 (14) or AIPC 27-51-85-01-220 COTTER PIN (14).
(i) If you loosened the locknut (10), TORQUE it to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft )

.
(j) Safety the locknut (10) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
(3) Remove the 98D27504031000 PIN-SETTING from the inspection/setting hole in the interconnecting strut.
(4) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:

Head of the bolt (16)
Nut (15)
Washer (13)
Cotter pin (14).

Subtask 27-51-44-820-054-E ** ON A/C NOT FOR ALL

B. Adjustment of the Interconnecting Strut (if necessary)

(1) Install the 98D27504031000 PIN-SETTING in the inspection/setting hole in the interconnecting strut.

NOTE: The interconnecting strut can have one or two inspection/setting holes. If there are two, use the hole that is not blocked by the aircraft structure.

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 (14) or AIPC 27-51-85-01-220 COTTER PIN (14).
(i) If you loosened the locknut (10), TORQUE it to between 5.9 and 5.1 m.daN (43.51 and 37.61 lbf.ft )

Head of the bolt (16)
Nut (15)
Washer (13)
Cotter pin (14).

Subtask 27-51-44-410-059-A

C. Close Access
(1) Remove the access platform(s).

Subtask 27-51-44-865-069-A

D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

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 27-51-44-710-058-A

E. 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 27-51-44-860-058-A

F. 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) Retract the flaps to position 1 (Ref. AMM TASK 27-50-00-866-009).
(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) Install the upper and lower kink-seals (1) and (2) to the inboard and the outboard flaps (Ref. AMM TASK 27-54-61-400-006).
(4) Make sure that the flaps are fully retracted (Ref. AMM TASK 27-50-00-866-009).

Subtask 27-51-44-710-053-A

G. Test
(1) Do an operational test of the flap system (Ref. AMM TASK 27-54-00-710-001).

Subtask 27-51-44-942-054-A

H. 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.

[Rev.10 from 2021] 2026.03.31 23:52:51 UTC