Aileron Control System Component Location
Figure 1 (Sheet 1)
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A
737-300/400/500
MAINTENANCE MANUAL
PRESSURE
AILERON DECK AILERON
CONTROL POWER
QUADRANT CONTROL UNITS
AB ABSA
AILERON
CONTROL AA ABSB CARTRIDGE SPRING
QUADRANT
SHAFT
INPUT AILERON
ROD BUS
CRANK DRUMS
ABSB
AILERON ABSA
TRIM
ACTURATOR INPUT
ROD
CENTERING
SPRING
(2 LOCATIONS)
AUTOPILOT PCU
INPUT ROD TRIM
MECHANISM
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Aileron Control System - Component Location
Figure 1 (Sheet 2)
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A
737-300/400/500MAINTENANCE MANUAL
D. The ailerons are constructed of graphite/epoxy over a nomex honeycomb core for weight savings. The ailerons with aileron balance tabs are mounted outboard of the outboard flaps behind the rear spar of each wing (Fig. 1 and 2).
E. The aileron bus system cables (ABSA and ABSB), are routed along the rear spar of each wing and connect each of the aileron wing quadrants to the bus drum. The bus system cables are provided with a cable slack take-up device in each wing. This device consists of a spring attached to the axis of the outboard turnaround pulley.
F. The base of the first officer's control column is equipped with a transfer mechanism. The transfer mechanism allows normal control wheel motion to be transmitted through the cables on the captain's control column only. If a malfunction occurs which jams the aileron control system, lateral control is achieved by the spoiler system operated directly by cables from the first officer's control column. When this occurs, the first officer will have to exert a maximum force of 117 pounds to overcome the spring in the transfer mechanism and operate the spoilers.
G. The aileron trim system repositions the ailerons and control wheels electrically to a neutral or trimmed (wings level) position (Fig. 3). The trim indicator on the control wheels shows the amount of trim in trim units.
2. Aileron_______
A. The ailerons are of graphite/epoxy construction with upper and lower skins of graphite/epoxy tape and nomex honeycomb core. An aileron balance tab is attached to the rear spar of the aileron by four hinge bearings. The aileron is provided with four hinge bearings attached to the front spar. Access panels are provided for each hinge bearing. Individual bearings may be replaced without removing the aileron. The leading edge of the aileron extends forward between the hinge bearings and is connected to one balance panel in bay No. 3.
B. The aileron control rod connects the aileron to the aileron wing quadrant. Dual pushrods that connect the balance tab to the wing structure pass through the aileron.
C. The aileron and balance tab are independently balanced. The aileron is statically balanced as a component. The balance tab is statically balanced by adding or installing weights to the balance panel. The number of weights required is subject to the weight of the balance tab.
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