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• If radio altitude is not available, at any time the landing gear is extended.
If the flight spoilers are not stowed with the aircraft in takeoff mode, a CONFIG SPOILERS
warning EICAS message and aural warning will be displayed/sounded.
20° Detent Mechanism
A 20° detent mechanism prevents asymmetrical deployment of the flight spoilers in the event
of a disconnected input linkage. The PCU control valves are spring-loaded retracted, but the
detent mechanism will apply force to hold a mid-position if the spoiler has been deployed to
greater than 20°. When on the ground with hydraulic pressure available, a sensor on each
detent mechanism will generate a FLT SPLRS caution EICAS message, and cause the
appropriate flight spoiler outline to turn amber on the flight control synoptic page, if the spoiler
position does not correspond to the detent position.
FLIGHT CONTROLS
Description
Vol. 2 10−10−14
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
SECONDARY FLIGHT CONTROLS (CONT'D)
Flight and Ground Spoilers − Schematic
Figure 10−10−10
FLIGHT CONTROLS
Description
Vol. 2 10−10−15
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
SECONDARY FLIGHT CONTROLS (CONT'D)
Ground Spoilers
The inboard spoiler panels on each wing are the ground spoilers. The ground spoilers have only
two positions: retracted or fully deployed to 45°. A single actuator, powered by hydraulic system
1, operates each ground spoiler.
After touchdown or during a rejected takeoff, the ground spoilers extend to dump lift and
increase drag to assist in aircraft braking. Ground spoiler deployment is normally automatic, but
can be activated manually by the pilot.
In the automatic or manual modes, arming, deployment and retraction is controlled by the
proximity sensor electronic unit (PSEU). The PSEU monitors inputs from the following:
• Ground spoiler arming switch
• Thrust lever position microswitch
• Ground spoiler surface position
• Flight spoiler lever position switch
• 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 status and FLIGHT CONTROLS synoptic pages,
using white arrows which move upward toward lines, indicating relative extension (for 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 10−10−16
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
SECONDARY FLIGHT CONTROLS (CONT'D)
Ground Spoilers Arming Logic
Figure 10−10−11
FLIGHT CONTROLS
Description
Vol. 2 10−10−17
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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
• 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 still 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 flashing STALL and Master Warning lights on
the glareshield, and a warbler aural warning. The stick pusher only activates when the signal from
　
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