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logic.
· SFCU − Slat/Flap Control Unit provides flap position for Proportional Lift Dumping (PLD).
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−47
SPOILER FCU INPUT SCHEMATIC
ROLL
SEL
PLT
ROLL
ROLL
SEL
CPLT
ROLL
GND LIFT
DUMPING
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−48
SPOILER CONTROL AND MONITORING
Spoiler control and monitoring of the MFS and ground spoilers are as follows:
MultiFunctional
Spoilers
The MFS PCUs are hydraulically powered and electrically controlled. The FCU controls each PCU
servo valve and uses an integral sensor to determine their position. The PCUs incorporate a
hydraulic lock to prevent upfloat in the event of a hydraulic failure. The MFS surfaces use a
proximity sensor to detect that the surface is retracted.
The FCU provides monitoring of the PCU command, PCU response to the command, spoiler
surface through the proximity sensor and detection of interface electrical failures.
When a MFS panel failure is detected, the opposite panel will automatically be disabled, in order to
ensure lift dumping remains symmetrical.
Ground Spoilers
An electrically controlled ground spoiler selector valve is used to provide hydraulic pressure to
single actuators (at each panel), to either retract or extend a left or right pair of ground spoilers.
The FCU must energize two valves within the ground spoiler selector valve for a pair of ground
spoilers to deploy. Proximity sensors are used for monitoring and indication and to detect whether
a ground spoiler panel is retracted or not.
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.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−49
SPOILER EICAS MESSAGES
CONFIG SPOILERS
FLT SPOILERS FAIL
ROLL SPOILERS FAIL
GND LIFT DUMP
FLT SPLR DEPLOYED
SPLR LEVER FAIL
ROLL SELECT
"NO TAKEOFF"
Displayed during takeoff,
if
FLIGHT CONTROLS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
10−10−50
SPOILER EICAS MESSAGES (CONT'D)
FLT SPOILERS FAULT
GND LIFT DUMP
SPLRS/STAB IN TEST
NO TAKEOFF
GND LIFT DUMP OFF
GLD MANUAL ARM
PLT ROLL SPLRS
CPLT ROLL SPLRS
takeoff
(example: trims,
LIFT DUMPING switch
is selected to MANUAL ARM.
LIFT DUMPING switch
is selected OFF.
FLIGHT CONTROLS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
10−10−51
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 antiiced)
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 weightonwheels
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:
AngleOfAttack
(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
selfregulating
heaters controlled and monitored by the Heater and Brake temperature Monitor Unit
(HBMU) located in the vanes. The heaters provide the sensors with deicing
　
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