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Oct 05/06
Flight and Ground Spoilers . Schematic Figure 10.10.10
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.
FLIGHT CONTROLS Description Vol. 2 10.10.15
Oct 05/06
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:
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Ground spoiler arming switch;
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Thrust lever position microswitches;
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Ground spoiler surface position;
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Flight spoiler lever position switch; and
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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 10.10.16
Oct 05/06
Ground Spoilers Arming Logic
Figure 10.10.11
FLIGHT CONTROLS Description Vol. 2 10.10.17
Oct 05/06
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:
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Angle of attack – LH, RH angle-of-attack vanes;
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Lateral acceleration – inertial reference system (IRS);
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Flap position; and
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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.
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