G03092
500 Aileron Transfer Mechanism
Feb 15/67 Figure 6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-0 Page 11
9. Aileron Wing Quadrant
A. An aileron wing quadrant is located within each wing behind the rear spar on the inboard side of each aileron (Fig. 7). Motion of the bus system cables rotates the quadrant about its support shaft. The periphery of the quadrant is grooved to receive two bus system cables and contains clips to secure each end of these cables. The quadrant is attached to a pushrod which is connected to the aileron.
10. Balance Tab Linkage
A. The aileron balance tab linkage connects the aileron tab, through dual pushrods, to the wing structure. The tab motion is controlled by the motion of the ailerons. The tab travel is opposite to aileron travel (Fig. 7).
11. Aileron Power Control Unit
A. Two aileron power control units provide actuation of the ailerons in response to manual inputs from the control columns. The power control units are mounted horizontally in the main wheel well (Fig. 1). The two power control units operate independently from separate hydraulic systems; the lower unit from hydraulic system A pressure and the upper unit from hydraulic system B pressure. Failure of either hydraulic system will render one power control unit inoperative. The remaining unit will continue to operate both ailerons through full range of travel.
B. The aileron power control unit incorporates a main actuator, a gust damping bypass valve, a thermostatic flow control valve (replaced by plug on some airplanes), filters and a dual concentric main control valve operated by a dual input crank (Fig. 8). The main control valve comprises a primary slide acting within a secondary slide. The secondary slide will permit control, should the primary slide become jammed in an open position. An exterior input rod provides actuation of the main control valve from the control system.
C. Rotation of the control wheels rotates the control quadrant torque tube and applies an input to the power control unit input crank. As the input crank displaces the main control valve slide, hydraulic pressure is directed through the valve to move the main actuator piston. Movement of the input crank in the opposite direction displaces the main control valve slide to route hydraulic pressure to the other side of the main actuator piston. The actuator piston rod end is attached to structure, thereby causing the power control package body to extend or retract. Movement of the power control unit will return the input crank to neutral and close the main control valve. This will equalize the pressures on either side of the actuator piston and arrest further motion.
511
27-11-0 Page 12 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/77
G03105 G03131 G03233
528 Aileron and Tab Control Linkage
Aug 15/73 Figure 7 27-11-0
Page 13
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aileron Power Control Unit Schematic 511
27-11-0Page 14 Figure 8 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/75
500 Aileron Hydraulic System Schmatic
May 15/68 Figure 9 27-11-0
Page 15
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. On all airplanes the upper power control unit is equipped to receive input from the autopilot. On some airplanes the lower power control unit is also equipped to receive input from the autopilot. For autopilot equipment on the power control units, refer to Chapter 22, Autoflight. On power control units with equipment to receive autopilot input, the following applies:
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