(4)
Rudder trim position indicator is located at the Aft Electronics Control Panel, P8. The indicator is electrically driven by a position transmitter in the trim actuator.
(5)
Aileron trim position indicators are located on top of the hub of each control wheel. Trim is indicated by the physical offset of the control wheel.
(6)
The flight control position indications are displayed on the auxiliary Engine Indicating and Crew Alerting System (EICAS) display when the Flight Controls Maintenance Page is selected (Ref 31-61-00/001). The pointers indicate the position of the inboard and outboard ailerons, inboard and outboard elevators, and upper and lower rudders. A position transmitter at each of the control surface drives the corresponding pointer.
6. Autoflight Hydraulic Components (Fig. 5)
_______________________________
A. Hydraulic components used in autoflight control include:
(1)
Left and right Central Lateral Control Package (CLCP)
(2)
Lateral Autopilot Servo (LAS)
(3)
Left, center, and right Elevator Autopilot Servo (EAS)
(4)
Left, center, and right Rollout Power Control Package (RPCP)
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MAINTENANCE MANUAL
AUTOPILOT SERVOS
Autoflight Hydraulic Components Location
Figure 5
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MAINTENANCE MANUAL
(5)
Left and right Stabilizer Trim Control Module (STCM)
(6)
Upper and lower Rudder Power Control Module (RPCM)
B. The right CLCP (right autopilot), and the LAS are mounted on the vertical rigging beam in the left wheel well. The left CLCP (left autopilot), is mounted in the right wheel well (Fig. 6 and 7). The CLCPs use mechanical inputs or autopilot electrical inputs to drive the aileron power control packages (PCPs).
C. The left, center, and right EASs are mounted on the stabilizer hinge bulkhead just forward of the top end of the aft quadrant torque tube (Fig. 8). Looking down from above the torque tube, the left and right EASs are mounted on the right side of the torque tube. The center EAS is mounted on the left side of the torque tube. The EASs use mechanical inputs or autopilot electrical inputs to drive the elevator PCPs.
D. The left, center, and right RPCPs are mounted to structure between the upper and lower rudders, in the vertical stabilizer forward of the rudder hinge and aft of the rear spar (Fig. 9). The RPCPs use autopilot electrical inputs to move rudders through the rudder ratio changers and the RPCMs.
E. The left and right STCMs are located in the stabilizer jackscrew area (Fig. 10). The STCMs use mechanical input or electrical inputs to move the jackscrew actuator assembly.
F. The upper and lower RCPMs are located in the vertical stabilizer forward of the rudder hinge and aft of the rear spar (Fig. 11). The RPCMs use mechanical input or yaw damper electrical input commands to control hydraulic flow to the rudder actuators, which provide a mechanical output to move the rudders.
7. Hydraulic Power Distribution (Fig. 12 and 13)
____________________________
A. Four hydraulic systems supply hydraulic power to many airplane systems. The hydraulic supply shutoff valves shut off hydraulic power to the flight control hydraulic components completely. The wing shutoff valves remove hydraulic power to the flight control hydraulic components in the wings. The tail shutoff valves remove hydraulic power to the flight control hydraulic components in the tail area.
B. Aileron Components
(1) The left and right CLCPs are dual actuators which receive hydraulic power from two systems. The right CLCP that is controlled by the right autopilot, is located in the left wheel well and receives power from systems 1 and 2; the left CLCP that is controlled by the left autopilot, is located in the right wheel well and receives power from systems 3 and 4.
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