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The actuators at each ground spoiler panel incorporates a hydraulic lock to prevent upfloat in the event of a hydraulic failure. Each of the two FCUs controls and monitors one of the two pairs of ground spoilers.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
SPOILER EICAS MESSAGES
"NO TAKE-OFF"
Displayed during take-off, if
CONFIG SPOILERS
FLT SPOILERS FAIL ROLL SPOILERS FAIL GND LIFT DUMP FLT SPLR DEPLOYED SPLR LEVER FAIL ROLL SELECT
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
SPOILER EICAS MESSAGES (CONT'D)
take-off (example: trims,
FLT SPOILERS FAULT
GND LIFT DUMP
SPLRS/STAB IN TEST NO TAKEOFF
GND LIFT DUMP OFF
GLD MANUAL ARM LIFT DUMPING switch
PLT ROLL SPLRS is selected OFF.
LIFT DUMPING switch CPLT ROLL SPLRS
is selected to MANUAL ARM.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
STALL PROTECTION
The Stall Protection System (SPS) provides the flight crew with aural, visual and feel (stick shaker) indications of an impending stall. Following these events and no corrective action is taken, the system activates the stick pusher mechanism, preventing the airplane from entering the stall.
The stall protection system consists of two (electrically anti-iced) angle of attack sensors, a dual channel computer, two stick shakers, a stick pusher system and mach sensing to back up the air data computers. Each channel of the computer controls a stick shaker. The computer provides two independent signals to the pusher system logic. Both channels of the computer must agree to activate the stick pusher system based on similar system inputs.
The stall protection function is inhibited when both weight-on-wheels inputs indicate on ground or calibrated airspeed is recognized to be less than 70 kts.
The stall protection computer continuously monitors the SPS and faults detected are sent to EICAS for aural and/or visual annunciation.
STALL PROTECTION COMPONENTS
The stall protection system consists of the following components:
Angle-Of-Attack (AOA) Vane
Two AOA vanes are mounted on the forward fuselage (left and right) of the airplane. They rotate to align with the prevailing airflow to measure the direction of the airflow relative to the fuselage.
AOA VANE
GF1010_061
The vanes provide information to both channels of the stall protection computer. There are self-regulating heaters controlled and monitored by the Heater and Brake temperature Monitor Unit (HBMU) located in the vanes. The heaters provide the sensors with de-icing and anti-icing capability in icing conditions.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
STALL PROTECTION COMPONENTS (CONT'D)
Mach Transducer (On airplanes 9002 thru 9158)
The mach transducer control is installed on the right side of the flight compartment, below the copilot’s side console. It is connected to the pitot-static system through a selector/isolator switch. The mach transducer receives electrical input and pressure through connectors and supplies secondary mach information to the channels of the Stall Protection Computer (SPC). The ADCs supply primary mach data to the channels of the (SPC).
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