Operational Test of the Flap Interconnecting Strut and the Flap-Attachment Failure-Detection Sensors

TASK 27-51-00-710-002-A
Operational Test of the Flap Interconnecting Strut and the Flap-Attachment Failure-Detection Sensors

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.

1. Reason for the Job
Refer to the MPD TASK: 275100-02
OPERATIONAL CHECK OF FLAP INTERCONNECTING STRUT AND FLAP DISCONNECT PROXIMITY SENSORS
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
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 )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.12ACC1)	Corrosion Preventive Compound-Heavy Duty Soft Film -

C. Expendable Parts

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

D. Referenced Information

REFERENCE	DESIGNATION
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 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 27-51-44-820-001-A	Adjustment of the Interconnecting Strut
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 29-10-00-864-001-A	Depressurize the Green Hydraulic System
TASK 29-10-00-864-002-A	Depressurize the Yellow Hydraulic System
TASK 31-32-00-860-006-A	Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page
TASK 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
Flap Interconnecting Strut

3. Job Set-up
Subtask 27-51-00-941-052-A

A. Safety Precautions
(1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
(2) Put the WARNING NOTICE(S) in position to tell persons not to operate the flight controls.

Subtask 27-51-00-860-056-A

B. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(2) Get access to the flight controls (F/CTL) page on the MCDU (Ref. AMM TASK 31-32-00-860-006).
(3) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(4) Move the flaps:

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.

(a) Extend the flaps to the 10 degrees position (slat and flap control lever position 1) (Ref. AMM TASK 27-50-00-866-008).
(5) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is on the flap/slat control lever.
(6) Depressurize the Green and the Yellow hydraulic systems (Ref. AMM TASK 29-10-00-864-001) (Ref. AMM TASK 29-10-00-864-002).

Subtask 27-51-00-865-057-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 27-51-00-010-051-A

D. Get Access
(1) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the wing at zones 580 and 680.
(2) Remove the lower kink seals of the two wings (Ref. AMM TASK 27-54-61-000-002).
(3) If necessary: Also remove the upper kink seals of the two wings (Ref. AMM TASK 27-54-61-000-002).

Subtask 27-51-00-020-051-A

E. Disconnect the Interconnecting Strut

Flap Interconnecting Strut

(1) Make a mark on the interconnecting strut (1) for correct position of the actuating rod (holes in the eye-end and bracket are aligned).
(2) Hold the flap interconnecting struts (1).
(3) Remove and discard the cotter pins (2).
(4) Remove the nuts (3), the washer (4) and the bolts (5).

Subtask 27-51-00-865-058-A

F. 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 27-51-00-865-061-A

G. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	L/G/LGCIU/SYS1/NORM	1GA	C09
121VU	HYDRAULIC/LGCIU/SYS2	2GA	Q35
121VU	HYDRAULIC/LGCIU/SYS1/GRND SPLY	52GA	Q34

4. Procedure
Subtask 27-51-00-710-056-A

A. Operational Test of the Flap Interconnecting Strut and the Flap-Attachment Failure-Detection Sensors

NOTE: Use one of the Multipurpose Control and Display Units (MCDU) for the test.

(1) Do this test:

ACTION	RESULT
1.At the LH flaps: push in the actuating rod of the flap interconnecting strut until it comes in contact with the stop.	At the LH flap interconnecting strut: the sensors give a 'target far' signal to the SFCC.
	In the cockpit: a single chime sounds an amber MASTER CAUT light comes on. On the upper ECAM DU: the F/CTL FLAPS LOCKED message comes on the ALIGNMENT FAULT message comes on.
2.On Panel 130VU (131VU): push (in) the MASTER CAUT pushbutton switch (P/BSW).	On Panel 130VU (131VU): the amber MASTER CAUT light goes out.
3.On the MCDU: push the line key < SFCC 1.	On the MCDU: the SFCC 1 menu shows. NOTE: As an alternative, you can use the SFCC 2 menu but do not change SFCC menu's during the test procedure.
4.Push the line key SYSTEM STATUS FLP >.	SFCC 1 SYSTEM STATUS FLAP CHECK LH DRIVE INTEGRITY shows.
5.Push the line key < RETURN frequently until the SYSTEM REPORT/TEST - F/CTL menu is shown.
6.At the LH flaps: move the actuating rod into the correct position.
7.Open the circuit breakers 6CV and 8CV.	The SFCC 1 and SFCC 2 are de-energized.
8.Close the circuit breakers 6CV and 8CV.	The failure conditions are reset.
	On the upper ECAM DU: the F/CTL FLAPS LOCKED message goes out the ALIGNMENT FAULT message goes out.
9.Push the line key F/CTL >.	the SYSTEM REPORT/TEST - F/CTL menu shows.
10.Push the line key < SFCC 1.	the SFCC 1 menu shows. NOTE: As an alternative, you can use the SFCC 2 menu but do not change SFCC menu's during the test procedure.
11.Push the line key SYSTEM STATUS FLP >.	the MCDU shows SFCC 1 SYSTEM STATUS FLAP NO FAULTS.
12.Push the line key < RETURN frequently until the SYSTEM REPORT/TEST - F/CTL menu is shown.
13.At the LH flaps: pull out the actuating rod of the flap interconnecting strut until it comes in contact with the stop.	At the LH flap interconnecting strut: the sensors give a 'target far' signal to the SFCC.
	In the cockpit: a single chime sounds an amber MASTER CAUT light comes on. On the upper ECAM DU: the F/CTL FLAPS LOCKED message comes on the ALIGNMENT FAULT message comes on.
14.On Panel 130VU (131VU): push (in) the MASTER CAUT P/BSW.	On Panel 130VU (131VU): the amber MASTER CAUT light goes out.
15.Push the line key F/CTL >.	the SYSTEM REPORT/TEST - F/CTL menu shows.
16.Push the line key < SFCC 1.	the SFCC 1 menu shows. NOTE: As an alternative, you can use the SFCC 2 menu but do not change SFCC menu's during the test procedure.
17.Push the line key SYSTEM STATUS FLP >.	the MCDU shows SFCC 1 SYSTEM STATUS FLAP CHECK LH DRIVE INTEGRITY.
18.Push the line key < RETURN frequently until the SYSTEM REPORT/TEST - F/CTL menu is shown.
19.At the LH flaps: move the actuating rod into the correct position.
20.Open the circuit breakers 6CV and 8CV.	The SFCC 1 and SFCC 2 are de-energized.
21.Close the circuit breakers 6CV and 8CV.	The failure conditions are reset.
	On the upper ECAM DU: the F/CTL FLAPS LOCKED message goes out the ALIGNMENT FAULT message goes out.
22.Push the line key F/CTL >.	the SYSTEM REPORT/TEST - F/CTL menu shows.
23.Push the line key < SFCC 1.	the SFCC 1 menu shows. NOTE: As an alternative, you can use the SFCC 2 menu but do not change SFCC menu's during the test procedure.
24.Push the line key SYSTEM STATUS FLP >.	the MCDU shows SFCC 1 SYSTEM STATUS FLAP NO FAULTS.
25.Push the line key < RETURN frequently until the SYSTEM REPORT/TEST - F/CTL menu is shown.
26.Do the steps 1 thru 25 again for the RH flap interconnecting strut.
27.Push the line key < RETURN frequently until the CFDS menu page is shown.

5. Close-up
Subtask 27-51-00-865-059-A

A. 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 27-51-00-420-053-B

B. Connect the Interconnecting Strut

NOTE: The installation of the rod eye-end of the LH interconnecting strut is given. The installation of the rod eye-end of the RH interconnecting strut is the same.

(1) Hold the rod eye-end of the interconnecting strut in position to the outer flap.
(2) Install the bolt (5), the washer (4) and the nut (3).
(3) TORQUE the nut (3) to between 1.7 and 1.1 m.daN (150.44 and 97.35 lbf.in )

.
(4) Install the new AIPC 27-51-05-01-100 COTTER PIN (2) or AIPC 27-51-85-01-220 COTTER PIN (2).
(5) Do a check of the adjustment of the interconnecting strut and if necessary adjust the interconnecting strut (Ref. AMM TASK 27-51-44-820-001).
(6) Apply a layer of the Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to:

The head of the bolt (5)
The nut (3)
The washer (4)
The cotter pin (2).

Subtask 27-51-00-410-051-A

C. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the lower kink seals of the two wings (Ref. AMM TASK 27-54-61-400-006).
(3) If removed: Install the upper kink seals of the two wings (Ref. AMM TASK 27-54-61-400-006).

Subtask 27-51-00-865-060-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 27-51-00-860-055-A

E. Aircraft Configuration
(1) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
(2) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(3) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 27-51-00-942-067-A

F. Removal of Equipment
(1) Remove the safety barriers.
(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 06:58:35 UTC