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(1)
The aileron control drum houses the aileron control quadrant. The quadrant rotates body cables which drive the lateral control mechanisms in the wheel wells for the left and right main landing gear. Connected to the drum are spoiler RVDT units (Ref 27-61-00, Description and Operation).
(2)
The bus force limiter links both control drums so that they operate in unison. It also provides a two-way breakout in the event a control wheel becomes inoperable. The force limiter is spring-loaded in both directions so that either control wheel can operate independently of the other, if necessary.
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MAINTENANCE MANUAL
65 4321
POGO)
LEFT SPOILERS
Aileron System
Figure 1
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757 MAINTENANCE MANUAL
SEE A
WHEEL) (EACH CONTROL DISCONNECT AUTOPILOT B TRIM INDICATOR (TWO PLACES)
SEE B WHEELS CONTROL
COLUMN CONTROL
LIMITER BUS FORCE COLUMN CONTROL CONTROL QUADRANT
RVDT UNIT (2 PLACES)
CABLES BODY
A
Figure 2 Aileron Control
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MAINTENANCE MANUAL
C. Lateral Feel, Centering, and Trim Mechanism (Fig. 3)
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(1)
The lateral feel, centering, and trim mechanism, located in the wheel well for the left main landing gear, mechanically drives the left aileron PCAs. A control rod connects the mechanism to the lateral control override mechanism in the wheel well for the right main landing gear. The feel, centering, and trim mechanism also has an override cam to allow operation of the right aileron if the left side becomes jammed (the left side has a shearout).
(2)
Two centering springs keep the ailerons in a neutral position when there are no commanded inputs. Command inputs are either manual from the control wheel and cables or hydraulic from the autopilot system. The autopilot lateral control servo (ALCS) cranks input autopilot commands directly to the feel, centering, and trim mechanism.
D.
Aileron Trim Switches (Fig. 3)
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(1)
The aileron trim switches are located on the aft electronic control panel (P8). The trim switches must be operated together to provide electrical input to the trim actuator.
E.
Aileron Trim Actuator (Fig. 3, 10)
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(1)
The aileron trim actuator is mounted on the support box and connected to the feel, centering, and trim mechanism. The actuator receives electrical signals from the trim switches. The trim actuator extends or retracts, adjusting the neutral position.
F.
Lateral Control Override Mechanism (Fig. 4)
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(1)
The lateral control override mechanism is located in the wheel well of the right main landing gear. A control rod connects the lateral control override mechanism to the feel, centering, and trim mechanism so that left and right ailerons respond equally to command inputs. A crank connects the override mechanism to the right ALCS to provide autopilot control. Override springs and a cam allow operation of the left aileron should the right side become jammed.
G.
Aileron Quadrant and Override Mechanism (Fig. 5)
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(1)
The aileron quadrant and override mechanism is located inboard of the PCAs in the wing trailing edge. A control rod connects the quadrant and override to the PCA input crank.
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