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• Ground spoiler arming switch;
• Thrust lever position microswitches;
• Ground spoiler surface position;
• Flight spoiler lever position switch; and
• Anti-skid control unit (wheel speed).
In the event of a malfunction or failure of the automatic arming and disarming logic, the ground
spoiler system may be manually armed or disarmed through the GND SPOILERS panel, located
on the center pedestal.
Spoiler position is indicated on both the EICAS page and FLIGHT CONTROLS synoptic page,
using white arrows which move upward toward lines, indicating relative extension (for the flight
spoilers only), and full extension (for both flight and ground spoilers). When the flight and ground
spoilers are fully retracted, all EICAS spoiler icons and position arrows disappear.
Ground Spoiler Arming Logic
The ground spoiler circuit must be armed before deployment can take place. The ground
spoilers are armed or disarmed by the three-position GND SPOILERS switch, located on the
center pedestal next to the flight spoiler control lever. The ground spoiler system can be armed
either automatically or manually as follows:
FLIGHT CONTROLS
Description
Vol. 2 10−10−15
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
SECONDARY FLIGHT CONTROLS (CONT'D)
Ground Spoilers Arming Logic
Figure 10−10−11
FLIGHT CONTROLS
Description
Vol. 2 10−10−16
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
STALL PROTECTION SYSTEM
The stall protection system (SPS) provides the flight crew with aural, visual and tactile (stick shaker)
indications of an impending stall and, if no corrective action is taken, will activate a stick pusher to
prevent the aircraft from entering a full stall.
Stall Protection System Computer
A dual-channel SPS computer monitors the following inputs:
• Angle of attack – LH, RH angle-of-attack vanes;
• Lateral acceleration – inertial reference system (IRS);
• Flap position; and
• Pressure altitude – air data computers (ADCs).
The SPS uses these inputs to continuously calculate angle-of-attack (AOA) trip points while in
flight. The AOA trip points are biased with the lateral accelerometers (sideslip and skid), flap
position and pressure altitude.
As the trip point is approached, continuous ignition is activated. If the AOA continues to increase,
the stick shaker activates and the autopilot disengages. If the AOA still continues to increase, the
stick pusher activates, along with red STALL annunciation displayed left of the ADI, and Master
Warning lights on the glareshield, and a warbler aural warning. The stick pusher only activates
when the signals from both channels of the SPS computer are in agreement.
NOTE
The crew should initiate approved recovery techniques at the first
indication of an impending stall (i.e., recognition of proximity of
low-speed cue at airframe buffet, at autoignition, or any time the stick
shaker or pusher activates).
In the event of an AOA increase rate greater than one degree per second, the SPS computer
lowers the AOA trip points to activate the aural, visual and tactile indications at a lower AOA. This
prevents the aircraft’s pitching momentum from carrying it through the stall warning/stick pusher
sequence into the stall.
Stick Pusher Disconnect
The stick pusher subsystem is armed when both STALL PROT PUSHER switches, located on the
pilot and copilot side panels, are ON. An acceleration switch will disconnect the stick pusher to
prevent an unusual attitude, if less than +0.5 ’G’ is reached during pusher operation. The pusher
may also be disabled momentarily by pushing the AP/SP DISC button on the pilot’s or copilot’s
control wheels. This will disconnect the pusher only as long as either button is held in. In the event
of a malfunction, the stick pusher may be deactivated by switching either STALL PROT PUSHER
switch to OFF (located on the side panels). To enable pusher operation, both switches must be
returned to the ON position.
NOTE
The stick shaker is always armed. The STALL PROT PUSHER
switches affect only the stick pusher function.
FLIGHT CONTROLS
Description
Vol. 2 10−10−17
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
STALL PROTECTION SYSTEM (CONT'D)
Stall Protection System − Schematic
Figure 10−10−12
FLIGHT CONTROLS
Description
Vol. 2 10−10−18
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
　
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