a
B
1 ON SOME AIRPLANES THE NORM POSITION IS DOWN AND THE SHUT OFF POSITION IS UP.
Spoiler Control System Component Location Figure 1 (Sheet 2)
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27-61-00
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A
747-400
MAINTENANCE MANUAL
SPOILER CONTROL DIFFERENTIAL MECHANISM (2 LOCATIONS)
CENTRAL LATERAL CONTROL PACKAGE (EXAMPLE)
SPEED BRAKE SEQUENCE MECHANISM
C
Spoiler Control System Component Location
Figure 1 (Sheet 3)
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27-61-00
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747-400
MAINTENANCE MANUAL
(6 AND 7) (8 TO 12)
RATIO CHANGER ACTUATORS
Spoiler Control Hydraulic System Distribution
Figure 2
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27-61-00
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747-400
MAINTENANCE MANUAL
CONTROL
HINGE SUPPORT
PACKAGE
(TYP) 4 PLACES
PISTON
INBOARD FLIGHT SPOILER
Spoiler
Figure 3
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27-61-00
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3. Spoiler Control Differential Mechanisms
_______________________________________
A. The differential mechanisms combine the inputs from the central control actuators and the speed brake sequence mechanism to position the flight spoilers. The differential mechanisms allow the flight spoilers to be used to augment lateral control of the airplane, even when simultaneously being used as speed brakes. Two differential mechanisms are used for controlling operation of the flight spoilers and are located on the forward wheel well bulkhead above the central lateral control packages. Inputs to each differential mechanism includes a lateral input shaft and a speed brake input shaft. Output consists of a right and left output shaft with cable quadrants for cable control inputs to the spoilers.
B. The housing of the differential mechanism contains the spoiler programming cam and related levers and linkages. The cam is mounted on the lateral input shaft contained in the differential mechanism. Rotating the cam programs the lateral control to the spoilers by causing the output cable quadrants to be rotated differentially. The cables then transfer motion along the left or right wings to rotate the spoiler package quadrants and thus position the spoilers. Rotation of the cam creates an up signal to the spoilers on one wing and a down signal to the spoilers on the other wing.
C. A speed brake input only, to the differential mechanism, will cause the flight spoilers on both wings to rise in proportion to actual speed brake input. Simultaneous inputs from aileron and speed brake systems will cause motion of the output quadrants in a combined manner, providing lateral control from flight spoilers with speed brakes on (Ref 27-60-00/1).
4. Outboard Flight Spoiler Control Package
_______________________________________
A. The outboard flight spoiler control package is basically a hydraulically driven actuator. An identical control package is used for each of the four outermost spoiler panels on each wing (No. 1, 2, 3, 4, 9, 10, 11, and 12). The control packages respond to mechanical inputs to the control valves from the captain's control wheel or speed brake control lever. Each control package is trunnion mounted to a support fitting on the wing rear spar. A control package linkage provides control inputs to the control package from a spoiler control quadrant which is also mounted on the support fitting. Hydraulic power is directed to the control package through trunnion fittings. The piston rod end of the control package is attached to the spoiler. Rotation of the spoiler control quadrant displaces a control package input lever and control valve, allowing hydraulic fluid at 3000 psi to be ported to one side of the piston and rod assembly. The input lever provides initial valve displacement, but the control package rotates on its trunnion as it positions the spoiler. Rotation of the control package returns the control valve to the neutral position, stopping hydraulic fluid flow at the desired spoiler position.
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