737-300/400/500
MAINTENANCE MANUAL

CABLES TO 
TRANSFER 
MECHANISM 
SEE  A  WHEEL WELL 
FORWARD 
BULKHEAD 
SPOILER 
CONTROL 
QUADRANT 
GROUND SPOILER 
RATIO  CONTROL VALVE 
FWD  CHANGER 
SPOILER  INPUT ROD 
RATIO 
CHANGER 
SPOILER MIXER 
WHEEL WELL 
CEILING 

(4 PLACES) SHEAR RIVETS 
SPOILER OUTPUT QUADRANTS 
AILERON SPRING CARTRIDGE AILERON BUS DRUMS 
A 
Spoiler Ratio Changer and Mixer Figure 4 

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 ALL  ú ú 01 Page 7 ú Oct 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
RATIO CHANGER INPUT ROD
RIGGING PIN HOLE
SPEED BRAKE
INPUT QUADRANT

LEFT SPOILER OUTPUT QUADRANT
WSA
WSB
TWO PART LINK
AILERON
BUS DRUM

SBA
SPEED BRAKE INPUT QUADRANT
SBB
UP
WSA
LEFT SPOILER OUTPUT QUADRANT
WSB
UP
A 737-300/400/500MAINTENANCE MANUAL
RIGHT SPOILER OUTPUT QUADRANT
WSA
WSB
RIGGING PIN HOLE
RATIO CHANGER INPUT ROD
BELL CRANK
ROLLERS
RIGGING PIN HOLE
RIGGING
AILERON
PIN HOLE
CAM
PIVOT POINT STRUCTURE PIVOT SHAFT
CABLES SBA = SPEED BREAKES UP SBB = SPEED BREAKES DOWN WSA = SPOILERS UP WSB = SPOILERS DOWN
AILERON SPRING CARTRIDGE SPOILER CONTROL
QUADRANT
LEVER
TO GROUND SPOILER CONTROL VALVE
UP
WSA

RIGGING PIN HOLE
RIGHT SPOILER OUTPUT QUADRANT
WSB
UP
Spoiler Ratio Changer and Mixer Schematic
Figure 5

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 C.  Counterclockwise rotation of the speed brake input quadrant repositions the linkage in the mixer and results in an "up" signal to both left and right output quadrants. Conversely, clockwise rotation results in a "down" signal at both output quadrants. The speed brake input quadrant is mounted on the no-back device. The no-back is irreversible and will prevent movement of the input quadrant in either direction unless activated by the motion of the speed brake control lever. Aileron signals received by the spoiler mixer from the ratio changer rotate the cam inside the mixer. Clockwise rotation of the cam repositions the linkage in the mixer. This moves the left output quadrant to provide an "up" signal and the right output quadrant to provide a "down" signal. Conversely, counterclockwise rotation of this cam provides a "down" signal to the left output quadrant and an "up" signal to the right output quadrant. Simultaneous inputs from aileron and speed brake systems will cause motion of these output quadrants in a combined manner, providing lateral control from flight spoilers with speed brakes on.
SPOILER PANEL  INPUT ARM 
ACTUATOR LINK 
SPOILER ACTUATOR 
SHEAR RIVET 
(2 PLACES) 

FWD
FILTER
TYPICAL OF FLIGHT SPOILERS NO. 2, 3, 6 AND 7
SPOILER ACTUATOR QUADRANT
Flight Spoiler Actuator
Figure 6

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 5.  Flight Spoiler Actuators
________________________
 A.  A spoiler actuator is used to position each of the flight spoilers (Fig. 6). Each of the identical actuators includes a cylinder, actuator rod and piston, control valve, filter, thermostat valve, relief check valve, blow-down check valve, extension check and thermal relief valve, snubber check valve, and overtravel pistons. Each actuator is trunnion mounted to a support fitting on the wing rear spar. An actuator link provides control inputs to the actuator from a spoiler control quadrant mounted on the support fitting. Hydraulic power is directed to the actuator through trunnion fittings. The piston rod end of the actuator is attached to the spoiler. Rotation of the spoiler control quadrant displaces an actuator input lever and the control valve, allowing hydraulic fluid at 3000 psi to be ported to one side of the piston and rod assembly. The input lever remains stationary after the initial displacement, but the actuator rotates on its trunnion as it positions the spoiler. Rotation of the actuator returns the control valve to the neutral position, stopping hydraulic fluid flow as the desired spoiler position.
　
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