Special Detailed Inspection of Outer Wing Inboard Flap Track 2 Flap Pivot Bolt Assembly

TASK 57-52-00-220-007-A
Special Detailed Inspection of Outer Wing Inboard Flap Track 2 Flap Pivot Bolt Assembly

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

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.

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: 531
ZONE: 631

1. Reason for the Job
Refer to the MPD TASK: 575252-01

NOTE: The effectivity of this task is ALL. To know if this task is applicable for your aircraft, refer to the MPD task applicability and the weight variant data given in the SRM introduction.

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	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 20.0 and 15.0 m.daN (147.49 and 110.62 lbf.ft )
98D27504083000	1	EXTRACTOR - PIN TRACKS 2 AND 3
98D27504084000	1	EXTRACTOR - PIN, TRACK 4
98D27504111000	1	SLAVE PIN-TRACK 2 & 3
98D27504112000	1	PIN - SLAVE

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.03GBB1)	Synthetic Oil base Grease-General Purpose Clay Thickened -
(Material No.03GBC1)	Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. -
(Material No.08BAA9)	Non Aqueous Cleaner-General - -
(Material No.14SBA1)	Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
531	FLAP TRACK 2 FAIRING
631	FLAP TRACK 2 FAIRING

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
5	cotter pin	AIPC 27-54-46-04-035
3	crushable spacer	AIPC 27-54-46-04-080
5	cotter pin	AIPC 27-54-46-22-010
3	crushable spacer	AIPC 27-54-46-22-030

E. Referenced Information

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 27-54-00-710-001-A	Operational Test of the Flap System
TASK 57-55-11-010-001-A	To Lower the Flap Track No. 2 Movable Fairing for Access
TASK 57-55-11-410-001-A	To Lift the Flap Track No. 2 Movable Fairing after Access
NTM 575252
SRM 575200	(for corrective action)
Flap Track 2 Pivot Bolt - Detail ** ON A/C NOT FOR ALL
Flap Track 2 Pivot Bolt - Detail ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 57-52-00-941-063-A

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

Subtask 57-52-00-860-101-A

B. Aircraft Maintenance Configuration
(1) Fully extend the flaps (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) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE below the applicable wing trailing edge at flap track 2, zone 531(631).

Subtask 57-52-00-865-074-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1	6CV	B07
121VU	FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2	8CV	Q21

Subtask 57-52-00-010-061-A

D. Get Access
(1) Lower the flap track 2 fairing (Ref. AMM TASK 57-55-11-010-001).

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 57-52-00-020-052-C ** ON A/C NOT FOR ALL

A. Preparation for Inspection

WARNING: USE PROTECTIVE GOGGLES WHEN YOU REMOVE OR INSTALL A COTTER PIN. EACH TIME YOU REMOVE A COTTER PIN DURING THE TASK, DISCARD IT IMMEDIATELY. A LOOSE COTTER PIN CAN CUT YOU OR MAKE YOU BLIND.

(1) Remove these items:

The cotter pin (5)
The nut (4)
The crushable spacer (3)
The nut (6) and the washer (7)
The locking plate (2)
The splined bush (1).

(2) Discard the cotter pin (5) and the crushable spacer (3).
(3) Install the 98D27504083000 EXTRACTOR - PIN TRACKS 2 AND 3 on the pivot bolt assembly (9).
(4) Remove the pivot bolt assembly:

CAUTION: THE FLAP TO CARRIAGE BOLT ASSEMBLY HAS AN INNER AND AN OUTER BOLT WHICH MAKE ONE PART. DO NOT APPLY AN END OR A TORSION FORCE TO THE INNER BOLT BECAUSE THIS WILL CAUSE DAMAGE TO THE ASSEMBLY. APPLY FORCE TO THE OUTER BOLT ONLY WHEN YOU REMOVE/INSTALL THE BOLT ASSEMBLY.

(a) Remove the pivot bolt assembly (9) from the flap carriage using the 98D27504083000 EXTRACTOR - PIN TRACKS 2 AND 3. Install the 98D27504111000 SLAVE PIN-TRACK 2 & 3 at the same time as the pivot bolt assembly (9) is removed.
(5) Remove the 98D27504083000 EXTRACTOR - PIN TRACKS 2 AND 3 from the pivot bolt assembly (9).
(6) Carefully remove the rivet (11) and remove the inner bolt (12) from the outer bolt (10).
(7) Use a Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the inner bolt (12) and the outer bolt (10).

Subtask 57-52-00-020-052-D ** ON A/C NOT FOR ALL

A. Preparation for Inspection

WARNING: USE PROTECTIVE GOGGLES WHEN YOU REMOVE OR INSTALL A COTTER PIN. EACH TIME YOU REMOVE A COTTER PIN DURING THE TASK, DISCARD IT IMMEDIATELY. A LOOSE COTTER PIN CAN CUT YOU OR MAKE YOU BLIND.

(1) Remove and discard the cotter pin (5).
(2) Remove the nut (4).
(3) Remove and discard the crushable spacer (3).
(4) Install the 98D27504084000 EXTRACTOR - PIN, TRACK 4 onto the pivot bolt assembly (9).

NOTE: Make sure that you screw the extractor pin fully onto the threads. This will hold the locking ring in position and let it be compressed by the bushes and bearing. The extractor pin does not cover the locking ring.

(5) Remove the pivot bolt assembly:

(a) Remove the pivot bolt assembly (9) using the 98D27504084000 EXTRACTOR - PIN, TRACK 4 to push the pivot bolt assembly (9) through the bushes and bearing. Install the 98D27504112000 PIN - SLAVE at the same time as the pivot bolt assembly (9) is removed.

NOTE: If necessary, the flap must be lifted with the hoist and sling sufficiently to release the weight off the bolts (9).

(6) Remove the 98D27504084000 EXTRACTOR - PIN, TRACK 4 from the pivot bolt assembly (9).
(7) Carefully remove the rivet (11) and remove the inner bolt (12) from the outer bolt (10).
(8) Remove the nut (6) and the washer (7).
(9) Remove the locking plate (2) and the splined bush (1).
(10) Use a Textile-Lint free Cotton - (Material No.14SBA1) , made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean the inner bolt (12) and the outer bolt (10).

Subtask 57-52-00-280-062-B

B. Special Detailed Inspection of Outer Wing Inboard Flap Track 2 Flap Pivot Bolt Assembly
(1) Do a special detailed inspection of the inner bolt (12) and the outer bolt (10) NTM 575252.

NOTE: If the bolts are damaged, refer to the SRM 575200 for a repair procedure. If a repair procedure is not included in the SRM refer to AIRBUS.

Subtask 57-52-00-420-052-C ** ON A/C NOT FOR ALL

C. Installation of the Pivot Bolt Assembly
(1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Assemble the pivot bolt assembly (9) as follows:
(a) Apply a thin layer of Synthetic Oil base Grease-General Purpose Clay Thickened - (Material No.03GBB1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) to the inner bolt (12).
(b) Install the inner bolt (12) in the outer bolt (10).
(c) Attach the inner bolt (12) to the outer bolt (10) with a new rivet (11) (NSA5414-40-000).
(3) Apply a thin layer of Synthetic Oil base Grease-General Purpose Clay Thickened - (Material No.03GBB1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) to the splined bush (1) and to the pivot bolt assembly (9).

CAUTION: DO NOT REMOVE THE RETAINING WIRE RING FROM THE CARRIAGE BOLT ASSEMBLY. IF YOU DO, YOU MUST INSTALL A NEW CARRIAGE BOLT ASSEMBLY TO KEEP THE FAIL SAFE FUNCTION.

(4) Install the 98D27504083000 EXTRACTOR - PIN TRACKS 2 AND 3 on the pivot bolt assembly (9).
(5) Install the pivot bolt assembly (9) in the flap carriage with the 98D27504083000 EXTRACTOR - PIN TRACKS 2 AND 3. At the same time remove the 98D27504111000 SLAVE PIN-TRACK 2 & 3 from the flap carriage.

NOTE: Make sure that you install the extractor tool fully on to the threads of the pivot bolt assembly (9). This will let the carriage bushes compress the retaining ring (8) as the pivot bolt (9) is installed.

(6) Remove the 98D27504083000 EXTRACTOR - PIN TRACKS 2 AND 3 from the pivot bolt assembly.

CAUTION: MAKE SURE THAT THE SPLINED BUSH IS FULLY ENGAGED WITH THE SPHERICAL BEARING. THIS PREVENTS DAMAGE TO THE PARTS.

(7) Install the splined bush (1) correctly over the pivot bolt assembly (9).
(8) Install locking plate (2) on the splined bush (1).
(9) Install a new AIPC 27-54-46-22-030 crushable spacer (3) and the nut (4).
(10) TORQUE the nut to between 20.0 and 15.0 m.daN (147.49 and 110.62 lbf.ft )

WARNING: USE PROTECTIVE GOGGLES WHEN YOU REMOVE OR INSTALL A COTTER PIN. EACH TIME YOU REMOVE A COTTER PIN DURING THE TASK, DISCARD IT IMMEDIATELY. A LOOSE COTTER PIN CAN CUT YOU OR MAKE YOU BLIND.

(11) Safety the nut (4) with a new AIPC 27-54-46-22-010 cotter pin (5).
(12) Install the washer (7) and the nut (6).

Subtask 57-52-00-420-052-D ** ON A/C NOT FOR ALL

C. Installation of the Pivot Bolt Assembly
(1) Make sure that the parts retained from the removed component are clean and in the correct condition.
(2) Assemble the pivot bolt assembly (9) as follows:
(a) Apply a thin layer of Synthetic Oil base Grease-General Purpose Clay Thickened - (Material No.03GBB1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) to the inner bolt (12).
(b) Install the inner bolt (12) in the outer bolt (10).
(c) Attach the inner bolt (12) to the outer bolt (10) with a new rivet (11) (NSA5414-48-000).
(3) Apply a thin layer of Synthetic Oil base Grease-General Purpose Clay Thickened - (Material No.03GBB1) or Synthetic Oil base Grease-General Purpose Lithium Thickened Low Temp. - (Material No.03GBC1) to the splined bush (1) and to the pivot bolt assembly (9).

CAUTION: DO NOT REMOVE THE RETAINING WIRE RING FROM THE CARRIAGE BOLT ASSEMBLY. IF YOU DO, YOU MUST INSTALL A NEW CARRIAGE BOLT ASSEMBLY TO KEEP THE FAIL SAFE FUNCTION.

(4) Install the 98D27504084000 EXTRACTOR - PIN, TRACK 4 on the pivot bolt assembly (9).
(5) Install the pivot bolt assembly (9) in the flap carriage with the 98D27504084000 EXTRACTOR - PIN, TRACK 4. At the same time remove the 98D27504112000 PIN - SLAVE from the flap carriage.

(6) Remove the 98D27504084000 EXTRACTOR - PIN, TRACK 4 from the pivot bolt assembly.

CAUTION: MAKE SURE THAT THE SPLINED BUSH IS FULLY ENGAGED WITH THE SPHERICAL BEARING. THIS PREVENTS DAMAGE TO THE PARTS.

(7) Install the splined bush (1) correctly over the pivot bolt assembly (9).
(8) Install locking plate (2) on the splined bush (1).
(9) Install a new AIPC 27-54-46-04-080 crushable spacer (3) and the nut (4).
(10) TORQUE the nut to between 20.0 and 15.0 m.daN (147.49 and 110.62 lbf.ft )

WARNING: USE PROTECTIVE GOGGLES WHEN YOU REMOVE OR INSTALL A COTTER PIN. EACH TIME YOU REMOVE A COTTER PIN DURING THE TASK, DISCARD IT IMMEDIATELY. A LOOSE COTTER PIN CAN CUT YOU OR MAKE YOU BLIND.

(11) Safety the nut (4) with a new AIPC 27-54-46-04-035 cotter pin (5).
(12) Install the washer (7) and the nut (6).

Subtask 57-52-00-420-052-G ** ON A/C NOT FOR ALL

DELETED

Subtask 57-52-00-410-081-A

D. Close Access
(1) Lift the flap track 2 fairing (Ref. AMM TASK 57-55-11-410-001).

Subtask 57-52-00-865-075-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
49VU	FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1	6CV	B07
121VU	FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2	8CV	Q21

Subtask 57-52-00-860-102-A

F. Aircraft Maintenance Configuration
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
(3) Retract the flaps (Ref. AMM TASK 27-50-00-866-009).

Subtask 57-52-00-710-050-A

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

5. Close-up
Subtask 57-52-00-942-062-A

A. Removal of Equipment
(1) Remove the access platform(s).
(2) Remove the WARNING NOTICE(S).
(3) Remove the safety barriers.
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

[Rev.8 from Aug 2017] 2026.04.02 06:31:19 UTC