G36095
Flight Spoiler Actuator Quadrant 500
27-61-61 Figure 801 Aug 01/75
Page 802
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
SPEED BRAKE CONTROL SYSTEM - DESCRIPTION AND OPERATION
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 27-61-0, Flight Spoiler Control System), reducing airspeed and to aid braking after touchdown. The spoiler panels are numbered 1 thru 8 from left to right. The flight spoilers, 2, 3, 6, and 7 are located outboard of the engines. Ground spoilers 1 and 8 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 rise equally. When speed brakes are applied on the ground, the ground spoilers will also rise.
B. System control is applied to a speed brake control lever, which is located on the captain's side of the control stand (Fig. 2). Moving the speed brake control lever operates control rods that 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 may also be applied by a speed brake lever actuator. This 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. Subsequently, if either engine thrust lever is positioned 25 degrees forward from engine idle position, the
500
Feb 20/93 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-62-0 Page 1
G36239G43210 G37378
Spoiler Panel Identification 500
27-62-0 Figure 1 Nov 15/67
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
504 Speed Brake Control System Component Location
Feb 20/93 Figure 2 (Sheet 1) 27-62-0
Page 3
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Speed Brake Control System Component Location 546
27-62-0 Figure 2 Aug 15/77
Page 4
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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. Three pushbutton test switches are provided on the center instrument panel. Actuating these switches will test the indicator light control circuit and the actuator circuit.
D. The ground spoilers have two positions, fully retracted or fully raised. The fully raised position for ground spoilers 1 and 8 is 40 degrees. For ground spoilers 4 and 5, the fully raised position is 60 degrees. Ground spoilers 1 and 8 are each actuated directly by a single locking actuator. Ground spoilers 4 and 5 are each actuated by two locking actuators that drive individual linkages (Fig. 2). Hydraulic power for the ground spoilers is from hydraulic system A. This ground spoiler hydraulic pressure does not pass through the spoiler valves on the flight controls hydraulic modular package. Thus, the spoiler switches, which control these valves, have no effect on ground spoiler operation.
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