LOST MOTION DEVICE PICK-UP
INBD PICK-UP LUG
AFT
Aileron Transfer Mechanism
Figure 7
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A 737-300/400/500MAINTENANCE MANUAL
8. Aileron Control Linkage
_______________________
A. The aileron control input rods connect the artificial feel, centering and trim mechanism to the aileron power control units (Fig. 1). The input rods connect the aileron control cable quadrant torque tube to the input levers of the power control units. An aileron spring cartridge is connected to the output crank on the aileron bus drum. The spring cartridge connects to a crank and provides lateral control input signals to the spoiler system.
B. The aileron control linkage furnishes system inputs for the operation of the power control unit and thus provides aileron action. During manual reversion, the power unit input crank contacts stops on the power unit housing to manually move the power units and operate the aileron.
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. 8). Motion of the bus system cables rotates the quadrant about the 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 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. 8).
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, filters, and a dual concentric main control valve operated by a dual input crank (Fig. 9). 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 crank provides actuation of the main control valve from the control system.
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A
737-300/400/500
MAINTENANCE MANUAL
CABLE ABSA CABLE ABSB
CABLE ABSB CABLE ABSA PUSHROD
AILERON HINGE POINT (4 PLACES) AILERON AILERON WING QUADRANT
WS 520.82
TAB CONTROL RODS FWD TAB MASTS AILERON BALANCE TAB
Aileron and Tab Control Linkage
Figure 8
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A
737-300/400/500MAINTENANCE MANUAL
MAIN ACTUATOR
GUST DAMPING
BYPASS VALVE
PRESSURE PORT
FLOW RESTRICTOR 1
MAIN CONTROL VALVE
1 737 SERVICE LETTER 27-071-B RETURN PORT CALLS FOR REPLACEMENT OF FLOW RESTRICTOR (FIXED RESISTOR).
Aileron Power Control Unit Schematic Figure 9
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