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After switch selection, both FCUs will use the corresponding roll input (unjammed side). This will
enable the MFS to operate through their full range of operation with a single control column input.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−45
SPOILER SYSTEM OPERATION
The spoiler system modes of operations are as follows:
Ground Lift Dumping
Ground lift dumping function commands extension of the spoilers when engines are equal to or
below idle and the ground condition is recognized. Engine throttle lever position is provided by
sensors in the throttle lever assembly.
Ground condition is determined from the airplane height provided by:
· Radio Altimeters (RA).
· Wheel speed, through the Brake Control Unit (BCU).
· WeightOnWheels(
WOW), through the Landing Gear Electronic Control Unit (LGECU).
The ground lift dumping system is fully automated or can be operated manually. Arming,
deployment and retraction is controlled by the FCUs.
In the event of a malfunction, failure of the automatic arming or disarming (automatic retraction),
the ground lift dumping system may be manually armed or manually disarmed through the GND
LIFT DUMP/AUTOBRAKE panel.
Arming
The system is automatically armed when the throttle levers are at the minimum takeoff
position
(30° TLA). To prevent inadvertent deployment during taxi, automatic arming will not latch until a
takeoff speed of 45 knots is reached. The flight compartment ground lift dumping “MANUAL ARM”
switch is provided in case of auto arming failure and to test the system during preflight.
Deployment
All spoilers deploy simultaneously during a rejected takeoff.
The GS deploy first in order to dump the airplane lift; therefore, the logic is split for GS and MFS
operations.
To deploy ground spoilers the system must be armed, engine throttles at idle position (or below)
and two of the three following conditions:
· Radio Altimeter (RA) below 7 feet.
· Left or right main landing gear WOW indication.
· Left or right wheel speed greater than 16 knots.
Radio altimeter and wheel spin will normally be the first conditions satisfied. Deployment of the
MFS is delayed until the airplane is more firmly on the ground to prolong maximum roll control,
through the spoilers roll assist function.
To deploy multifunctional
spoilers the ground lift dumping must be armed, both the left and right
throttles at idle (or below) and:
· Both main landing gear have WOW.
AND
· Left or right wheel speed indication above 16 knots, OR radio altimeter below 7 ft.
When the MFS are commanded for ground lift dumping, roll assist is available for partial
multifunction
spoiler operation.
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−46
SPOILER SYSTEM OPERATION (CONT'D)
Disarm
The logic automatically disarms after the airplane has been on the ground for 40 seconds following
touchdown and the wheel speed has decreased below 45 knots for 30 seconds. Automatic
disarming prevents the spoilers from deploying during taxiing. The system can also be manually
disarmed (turned off) to override the automatic arm/disarm circuits, through the ground lift dumping
“OFF” switch on the “GND LIFT DUMP/AUTOBRAKE” panel located in the centre pedestal.
SPOILER SYSTEM/FCU INTERFACE
The spoiler system operation is under control of two FCUs which have dual modules to control and
monitor the spoiler surfaces in pairs. The FCUs receive input from various airplane systems and
schedule the MFSs either symmetrically or proportionally depending on airplane configuration. The
FCUs also control and monitor the operation of the GS through valves within the ground spoiler
selector valves. Refer to the SPOILER CONTROL AND MONITORING this Chapter.
The FCUs control the priority of spoiler operations for flight and ground phases of operation and
spoiler system malfunctions are reported on the EICAS system.
The FCUs interface with the following systems for spoiler control and monitoring:
· BCU − Brake Control Unit provides wheel speed for Ground Lift Dumping (GLD) logic.
· LGECU − Landing Gear Electronic Control Unit provides WeightOnWheels
(WOW) for GLD
logic.
· DAUs − Data Acquisition Units provide hydraulic pressure data.
· ADCs − Air Data Computers provide airspeed data.
· RA − Radio Altimeter provides height for GLD.
· TQ − Throttle Quadrant assembly provides left and right throttle lever position sensors for GLD
　
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