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SPEED BRAKE CONTROL SYSTEM - DESCRIPTION AND OPERATION
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1. General_______
A. The speed brake control system actuates the flight and ground spoilers on both wings to increase drag and reduce lift. The ground spoilers are used only on the ground to aid braking after touchdown. The flight spoilers are used for lateral control (Ref 27-61-00, Flight Spoiler Control System), reducing airspeed and to aid braking after touchdown. The spoiler panels are numbered 0 thru 9 from left to right. The flight spoilers 2, 3, 6, and 7 are located outboard of the engines. Ground spoilers 0, 1, 8, and 9 are located outboard of the flight spoilers. Ground spoilers 4 and 5 are located inboard of the engines (Fig. 1). With lateral controls in neutral, application of speed brakes will cause the corresponding flight spoilers on both wings to raise equally. When speed brakes are applied on the ground, the ground spoilers will also raise.
B. System control is applied to a speed brake control lever located on the captain's side of the control stand (Fig. 2). Moving the speed brake control lever operates control rods which rotate a speed brake forward drum mechanism. The forward drum mechanism is connected by cables to a speed brake quadrant in the right wheel well. The speed brake quadrant operates a ratio changer and provides an input to a spoiler mixer. The spoiler mixer directs the speed brake signals to a ground spoiler control valve and to flight spoiler actuators. A ground spoiler interlock valve is installed in the hydraulic line between the up ports of the ground spoiler actuators and the ground spoiler control valve. The interlock valve is operated by a push-pull cable from the right main gear upper torsion link. With the airplane airborne, the shock strut is extended and the upper torsion link positions the push-pull cable to close the valve. When the airplane touches down, the shock strut is compressed and the push-pull cable opens the valve to actuate the ground spoilers.
C. System control also may be applied by a speed brake lever actuator. The actuator electrically drives the speed brake control lever to cause the speed brakes to raise or lower. Placing the speed brake control lever in an ARMED detent will prepare the actuator for operation. When the main gear wheels begin rotation at touchdown, the actuator will move the speed brake control lever to full up position raising the ground and flight spoilers. If either engine thrust lever is positioned 25 degrees forward from engine idle position, the actuator will move the speed brake control lever into the DOWN detent, lowering the ground and flight spoilers. Indicator lights are provided on the center instrument panel to verify that the system is properly armed. On airplanes with speed brake test switches three pushbutton test switches are provided on the center instrument panel. Actuating the switches will test the indicator light control circuit and the actuator circuit.
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27-62-00
ALL ú ú 02 Page 1 ú Nov 15/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
Spoiler Panel Identification
Figure 1
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27-62-00
ALL ú ú 01 Page 2 ú Feb 20/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
GROUND SPOILER ACTUATOR LINKAGE TO GROUND SPOILERS NO. 8 AND 9
GROUND SPOILER ACTUATOR
RIGHT LANDING GEAR FLEXIBLE DRIVE ROD
TO GROUND
SPOILERS NO. 0,
1 AND 4
UP
DOWN TO SYSTEM A RETURN
RATIO CHANGER
GROUND SPOILER NO. 5
FROM SYSTEM A PRESSURE
GROUND SPOILER CONTROL VALVE
SPOILER MIXER
GROUND
SPOILER
INTERLOCK
VALVE
UPPER
TORSION LINK SPEED BRAKE
INPUT QUADRANT
FWD
SBB
CONTROL CABLES
SBA TO FORWARD DRUM MECHANISM
SEE A
Speed Brake Control System Component Location
Figure 2 (Sheet 1)
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本文链接地址：737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 5(74)
