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B.  Movement of the elevator during flight in either direction from faired, causes a pressure differential between upper and lower balance bays. This pressure acts upon the balance panels to assist elevator movement.
C.  Access to the balance panels is through the balance bay access panel on the underside of the stabilizer. Balance weights are attached to the aft surface of each balance panel.
D.  Seals are situated around the periphery of the balance panels and idler hinge panels and across the lower surfaces of the hinges. The seals are a dacron and silicone rubber composition and are used to minimize air flow from one side of the balance panel bay to the other.

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5.  Control Columns
A.  The two control columns (Fig. 3) provide primary control of the airplane about the pitch and roll axes. Forward and aft motion of either control column actuates the elevators to provide control of the airplane about its lateral axis. Rotating a control wheel on either column operates the ailerons and spoilers to provide control about the longitudinal axis.
B.  The control columns are mounted at each end of the quadrant torque tube. Motion is transmitted from the column to the torque tube through mating face splines. The lower end of a shaft inside each column outer housing is connected to the aileron and spoiler control systems through a spade universal. A bevel gear located at the upper end of this shaft is driven by a mating bevel gear connected to the control wheel. The control column wiring harness originates at a terminal block in the lower nose section and is routed up through a conduit inside the control column outer housing. At the top of the column the wire bundle is wrapped loosely four times around the hub of the control wheel bevel gear and then routed inside the control wheel. The wires for the stabilizer trim control switch, autopilot disengage switch, and microphone switch, are routed to the outboard horn of the control wheel. At the outboard horn, the wires are then connected to the appropriate switches. The wires for the stabilizer trim control switch are first routed to a terminal block in the control wheel spoke and then to the control switch. A memory device, consisting of three rotatable digital readout discs, is incorporated in the inboard horn of the control wheel. The wires for the memory device light are routed through the inboard horn of the control wheel. A stall warning shaker is mounted on the forward face of the captain's control column. Wiring provisions for the stall warning shaker are also included in the control column. Felt dust seals are fastened to the control cabin floor. A spherical dust cover fastened to the column, contacts these seals to restrict airflow around the base of the control column.
6.  Elevator Forward Control Quadrants
A.  The elevator forward control quadrants are aluminum alloy forgings, suspended from the quadrant torque tube and located in the lower nose section (Fig. 3). The elevator control cables are located in grooves along the lower surface of each forward control quadrant. Each cable is secured at the quadrant. A pitch transducer is installed in each forward control quadrant. For more detailed information, refer to Chapter 22, Auto Flight. Access to the forward control quadrants is through the forward access door at station 211, just forward of the nose wheel well door.
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 Control Columns  500 
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7.  Elevator Aft Control Quadrants
A.  The elevator aft control quadrants are four individual segments mounted on the input torque tube in the empennage. (See figure 1.) The two upper segments are connected to the elevator up cables (EB) and the lower segments to the elevator down cables (EA). Aft movement of the control column will displace the elevator up cables (EB) forward, and forward movement of the control column will displace the elevator down cables (EA) forward.
8.  Elevator Feel Computer
A.  The elevator feel computer supplies controlled system A and system B hydraulic pressures to the elevator feel control unit. The feel computer is mounted to structure within the empennage, adjacent to the stabilizer front spar. (See figure 4.) The computer is a dual unit, its housing divided to accommodate identical components for system A as for system B. Internal components for each system include a Q-diaphragm, force balance valve, relief valve and a stabilizer actuated cam. Also housed within the unit body is a feel differential pressure switch.
　
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