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 B.  The ailerons are controlled by conventional control wheels in the flight compartment as shown (Fig. 2). The control wheels are bussed together using drums and cables below the control columns. Control cables connect the drum at the captains control column to a cable quadrant in the left wing gear wheel well. The quadrant includes a trim mechanism and also provides artificial feel to the aileron control system. Output of the trim and feel mechanism provides input to the hydraulically powered left and right central lateral control packages (CLCPs) (Fig. 2). The CLCPs also receive input from the airplane autopilot system.
 C.  The mechanical input to the CLCPs positions internal control valves which cause the CLCPs to provide a hydraulically powered output. The upper piston rod of each CLCP is connected to a spoiler differential which controls operation of the five flight spoilers in the respective wing (AMM 27-61-00/001). The lower piston rod of each CLCP is connected to an aileron programmer.

Aileron Control System Functional Diagram
Figure 1

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 D.  The output of each aileron programmer is transmitted to the respective wing through cables which attach to an aileron power package control quadrant at each surface. Each inboard aileron control quadrant is connected directly to the power package through control linkage. Each outboard aileron control quadrant is connected to the power package through an outboard aileron lockout mechanism. The lockout mechanism prevents the outboard ailerons from operating when the group A LE flaps are fully retracted. The lockout mechanism is actuated by an electric actuator that receives power through the Stabilizer Trim/Rudder Ratio Module (SRM).
 E.  Aileron trim is accomplished by use of the aileron arming and trim control momentary switches on the pilots' control stand. The switches control the aileron trim actuator which adjusts the trim and feel mechanism neutral position. The mechanism provides input to the right CLCP (right autopilot) which, in turn, repositions the lateral control system's neutral point, thereby establishing a change in lateral trim.
 2.  Ailerons (Fig. 3)
________
 A.  The inboard and outboard ailerons are conventional frame structures consisting of metal spars and ribs with skins of fiberglass honeycomb construction. Each aileron is positioned by a single hydraulic power package connected directly to the aileron. The inboard ailerons are designed for a full travel of 20 degrees up and 20 degrees down, available at all times. The outboard ailerons are designed to operate only during slow flight, and become operable by extending the TE flaps. At a flap extension greater than 1 unit, full outboard aileron travel of 25 degrees up through 15 degrees down is available.
 3.  Aileron Control Load Limiter (Fig. 2)
____________________________
 A.  The aileron control load limiter performs two functions. It provides an alternate system for moving the ailerons in the event either body cable system should jam and, it incorporates a lost motion feature which prevents undesired feedback of cable system motion into the aileron control wheels.
 B.  In normal operation, rotational movement of either control wheel is transmitted to the ailerons through the left body control cables. The right body control cables constitute a standby system and, normally, will not impart motion to ailerons.
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FLIGHT CONTROL HYDRAULIC SHUTOFF MODULE PANEL
SEE F
AILERON CONTROL WHEEL AND DRUM
SEE B
ELECTRICAL SYSTEM CARD FILE (REF)
CABLES TO TRIM AND FEEL MECHANISM P7 PANEL
P6 PANEL AILERON/RUDDER TRIM CONTROL PANEL
SEE A
L, R STABILIZER TRIM/ RUDDER RATIO MODULES (REF)
AILERON TRIM INDICATOR
SEE E
RUDDER TRIM 105 0 510
NOSE LEFT UNITS NOSE RIGHT AILERON
LEFT
AILERON TRIM
WING ARMING SWITCH DOWN
AILERON TRIM CONTROL SWITCH
　
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