(e)  
Connect tab pushrods to elevator tab. Ensure bushings are installed and bolts face each other.

(f)  
Adjust elevator tab (Ref 27-31-0, A/T).

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AILERON AND AILERON TRIM CONTROL SYSTEM - DESCRIPTION AND OPERATION
1.  General
A.  The aileron and aileron trim control system provides airplane lateral control. The ailerons are assisted by the flight spoilers. See 27-61-0. There is one aileron and balance tab on each wing. Rotation of either aileron control wheel results in movement of the ailerons, and movement of the flight spoilers. The ailerons are powered by two independent hydraulic power control units connected to separate hydraulic systems. Either power unit is capable of providing full power control in response to aileron control system inputs. In the event of total hydraulic failure, lateral control is maintained manually. Manual control forces are minimized by aileron balance tabs and hinged balance panels. The balance tabs are mechanically connected by rods to the wing structure.
B.  The aileron control system is actuated by rotation of either the captain's or first officer's aileron control wheel. The control wheels rotate control wheel drum and aileron control bus drums. (See figure 1.) Aileron control bus cables (ACBA & ACBB) between the aileron control bus drums provide an interconnect between the captain's and the first officer's aileron control wheels. Aileron control cables (AA & AB) from the captain's control wheel drum attach to an aileron control quadrant; which through a shaft, drives two cranks and two input rods. Each input rod connects to a power control unit. Also mounted on the control quadrant shaft is a cam which engages with a spring-loaded roller for the purpose of centering and trim. Each aileron power control unit is connected to a crank on a bus drum; to which aileron bus system cables are fastened. The aileron bus system cables (ABSA & ABSB) lead to left and right aileron wing quadrants. The ailerons are actuated through a control rod, by the aileron wing quadrants. During manual operation, the ailerons are manually operated by pilot effort. The forces are transmitted from the control wheel through the power unit input linkage stops. This establishes a direct mechanical link from the control wheel to effect aileron displacement.
C.  Hydraulic power is furnished to the aileron control system by two functionally independent 3000 psi systems. Hydraulic power from both systems is controlled by the flight control shutoff valves in the flight control hydraulic modular packages. Refer to 27-00 Flight Controls. The modular packages are located in the left and right main wheel wells, where the absence of wheel well doors assures quick and convenient access. Two FLT CONTROLS shutoff valve switches together with two low pressure warning lights are located on the overhead panel. System A is powered by two engine-driven pumps and system B by two electric motor pumps.
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E63706 G03078
Aileron Control System Component Location  500 
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D.  The ailerons consist of two aluminum control surfaces with fiberglass balance tabs. The ailerons with aileron balance tabs are mounted outboard of the outboard flaps behind the rear spar of each wing (Fig. 1 and 2).
　
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