Removal of the Cable Quadrant

TASK 27-21-46-000-001-A
Removal of the Cable Quadrant

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.

ZONE: 140
ZONE: 310
ZONE: 325

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE
No specific	1	ACCESS PLATFORM 2M (6 FT)
No specific	1	ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
98A27901002000	1	PIN-RIGGING,RUDDER CONTROL
98D27207547000	1	PIN-RIGGING
98D27207548000	1	PIN-RIGGING

B. Consumable Materials

REFERENCE	DESIGNATION
No specific	lockwire 0.6 mm (0.024 in.)

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
140	CENTER WING
310	FUSLG TAIL SECTION AFT OF AFT PRESS BHD
325	VERTICAL STABILIZER TRAILING EDGE
312AR, 325AL, 325BL, 811
231BG, 231JG
241BF, 241FF

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 29-00-00-864-001-A	Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action
TASK 29-10-00-863-003-A	Pressurize the Blue Hydraulic System with a Hydraulic Ground Power-Cart
TASK 29-10-00-863-003-A-01	Pressurize the Blue Hydraulic System with the Blue Electric Pump
TASK 52-41-00-010-002-A	Open the Avionics Compartment Doors for Access
TASK 53-22-12-000-001-A	Removal of the Cabin Floor Panels
TASK 53-32-12-000-002-A	Removal of the Cabin Floor Panels
Location of the Rudder Control Rigging Pin
Location of the Rigging Pins
Cable Quadrant ** ON A/C NOT FOR ALL
Cable Quadrant ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 27-21-46-010-050-A ** ON A/C NOT FOR ALL

A. Get Access
(1) Put the ACCESS PLATFORM 10M (33 FT) - ADJUSTABLE in position at zone 325.
(2) Open the access panels 325AL 325BL at the trailing edge of the vertical stabilizer.
(3) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position at zone 312.
(4) Open the access door 312AR.
(5) Put the ACCESS PLATFORM 2M (6 FT) under the access door 811.
(6) Open the access door 811 (Ref. AMM TASK 52-41-00-010-002).
(7) Remove the floor panels 241BF 241FF (Ref. AMM TASK 53-32-12-000-002).

Subtask 27-21-46-010-050-B ** ON A/C NOT FOR ALL

Subtask 27-21-46-865-053-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	AUTO FLT/FAC1/28VDC	5CC1	B04
49VU	AUTO FLT/FAC1/26VAC	14CC1	B03
** ON A/C NOT FOR ALL
49VU	AUTO FLT/FAC1/28VDC	5CC1	H10
49VU	AUTO FLT/FAC1/26VAC	14CC1	H09
** ON A/C ALL
121VU	AUTO FLT/RUDDER/TRIM/IND	15CC	M20
121VU	AUTO FLT/FAC2/28VDC	5CC2	M19
121VU	AUTO FLT/FAC2/26VAC	14CC2	M18

Subtask 27-21-46-860-050-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.

C. Aircraft Maintenance Configuration

Location of the Rudder Control Rigging Pin

Location of the Rigging Pins

(1) Energize the aircraft electrical circuits. (Ref. AMM TASK 24-41-00-861-002)
(2) Pressurize the Blue hydraulic system with the electric pump. (Ref. AMM TASK 29-10-00-863-003)
(3) Put the rudder pedals in the neutral position.
(4) On the center pedestal, on the panel 110VU, make sure that the RUD TRIM indicator shows 0.
(5) Depressurize the Blue hydraulic system and put it in the maintenance configu ration (Ref. AMM TASK 29-00-00-864-001).
(6) Make sure that the Green and Yellow hydraulic systems are depressurized and put them in the maintenance configuration (Ref. AMM TASK 29-00-00-864-001).
(7) On the overhead panel 23VU, release the FLT CTL/FAC 1 pushbutton switch. The OFF legend comes on.
(8) On the overhead panel 24VU, release the FLT CTL/FAC 2 pushbutton switch. The OFF legend comes on.
(9) Put the WARNING NOTICE(S) in the cockpit to tell persons not to operate the flight controls.
(10) De-energize the aircraft electrical circuits. (Ref. AMM TASK 24-41-00-862-002)
(11) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the Green, the Yellow and the Blue hydraulic systems.
(12) Put the 98D27207548000 PIN-RIGGING (20) in the mixer of the artifical feel unit.
(13) Put the 98D27207547000 PIN-RIGGING (21) in the cable quadrant (1).
(14) Put the 98A27901002000 PIN-RIGGING,RUDDER CONTROL (22) in the interconnecting lever for the rudder pedals and keep the tension regulator blocked in the neutral position.

Subtask 27-21-46-865-050-A

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	AUTO FLT/FAC1/28VDC	5CC1	B04
49VU	AUTO FLT/FAC1/26VAC	14CC1	B03
** ON A/C NOT FOR ALL
49VU	AUTO FLT/FAC1/28VDC	5CC1	H10
49VU	AUTO FLT/FAC1/26VAC	14CC1	H09
** ON A/C ALL
121VU	AUTO FLT/RUDDER/TRIM/IND	15CC	M20
121VU	AUTO FLT/FAC2/28VDC	5CC2	M19
121VU	AUTO FLT/FAC2/26VAC	14CC2	M18

4. Procedure
Subtask 27-21-46-020-050-A

A. Removal of the Cable Quadrant
(1) Disconnect the cables (10) from the cable quadrant (1).

WARNING: WEAR GLOVES WHEN YOU TOUCH THE CABLES. IF YOU DO NOT, INJURY CAN OCCUR.

(a) Open the locking clips (30) and turn the turnbuckles (31) until you can remove the ends of the cables (10) from the levers (3).
(b) Remove the cables (10) from the cable quadrant (1).
(c) Keep the cables (10) clear of the cable quadrant (1).
(2) Disconnect the control rod (2) from the cable quadrant (1).
(a) Remove and discard the cotter pin (15).
(b) Remove the nut (16) and the washer (17) from the screw (19).
(c) Remove the screw (19).
(d) Move the control rod (2) clear of the lever arm (4).
(e) Safety the bush (18) in the lever arm (4) with lockwire 0.6 mm (0.024 in.)
(3) Disconnect the cable quadrant (1) from the aircraft structure.
(a) Remove and discard the cotter pins (5).
(b) Remove the nuts (6) and the washers (7) from the screws (8),(9).
(c) Hold the cable quadrant (1) in position.
(d) Remove the screws (8) from the top connection positions.
(e) Remove the screws (9) from the bottom connection positions.
(f) Remove the cable quadrant (1).

NOTE: Identify the screws (8) and the screws (9) for installation in the same positions.

[Rev.10 from 2021] 2026.03.31 23:48:32 UTC