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SECU2
COMMAND MONITOR
OUTBD INBD
2 3 4
1
OUTBD INBD
INBD OUTBD
4 3 2
1
OUTBD INBD
GSSV1
SOV
3
SOV
1
SOV
2
GSSV2
SOV
3
SOV
1
SOV
2
LEFT MAIN
28 VDC
ARINC 429
LEFT MAIN
28 VDC
OFF MANUAL
ARM
AUTO
GND SPOILERS
FLIGHT SPOILER
CONTROL LEVER
LEFT
THROTTLE
IDLE
SWITCHES
RIGHT
THROTTLE
IDLE
SWITCHES
R
HYD
L
HYD
R
HYD
L
HYD
L
HYD
R
HYD
L
HYD R
HYD
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-02-12 CSP 100-6 REV 1
SECONDARY FLIGHT CONTROLS (Cont)
GROUND SPOILERS
DESCRIPTION
After touchdown or during a rejected takeoff, the inboard and outboard ground spoilers in conjunction with the multifunction
spoilers are extended to spoil lift and increase drag to assist in aircraft braking. The ground spoilers function is normally
automatic but can be activated manually by the pilot. The ground spoilers have no in-flight function.
COMPONENTS AND OPERATION
The ground spoiler function is selected by the three position GND SPOILERS switch as follows:
- OFF — Disables the ground spoilers by disarming the function
- AUTO — Automatically arms the ground spoilers for landing and rejected takeoff in conjunction with throttle
lever angle, wheel speed, weight on wheels and radio altitude
- MANUAL ARM — Arms the ground spoilers regardless of the inputs required to arm in the AUTO position
When deployed, the ground spoiler panels extend to 60° and the multifunctional panels extend to 45°, however, only the
multifunction panels respond to control wheel roll assist inputs. Ground spoilers deploy when the inputs for ground spoiler
deploy logic are throttles at IDLE, and 2 of the 3 following criteria are met: radio altitude less than 7 ft, weight on wheels,
and wheelspeed greater than 16 kt.
The position of all panels are shown on the EICAS FLIGHT CONTROLS synoptic page. Green arrows and position scales
indicate relative deflection of the surfaces.
Inboard and outboard ground spoilers are limited to two positions, either up or down. The spoilers are
continuously monitored and any fault detected is displayed on the appropriate EICAS screen.
CFO1005002_006
MANUAL
ARM
GND SPOILERS
OFF
ROLL SPOILERS
OFF
AUTO
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-02-13
SECONDARY FLIGHT CONTROLS (Cont)
TAKEOFF CONFIGURATION WARNING SYSTEM
DESCRIPTION
The takeoff configuration warning system monitors the position of the flaps, flight spoilers, parking brake, autopilot, aileron,
rudder, roll and pitch disconnect, and horizontal stabilizer trims, to ensure that they are in a safe configuration for takeoff.
COMPONENTS AND OPERATION
The warning system is armed when the airplane is on the ground. If one or more of the monitored systems is in an unsafe
takeoff configuration and both throttles are at or above the climb (CLB) detent, the master warning lights flash, aural alerts
sound and warning messages are presented. The configuration warning indications are canceled by correctly positioning
the applicable control or retarding the thrust levers.
PROXIMITY SENSING SYSTEM
DESCRIPTION
The proximity sensing system (PSS) consists of the proximity sensing electronic unit (PSEU), proximity sensors and proximity
switches. The proximity sensing system monitors aircraft systems for correct operation and configuration.
COMPONENTS AND OPERATION
PROXIMITY SENSING ELECTRONIC UNIT
The proximity sensing electronic unit (PSEU) processes information received from landing gear position, WOW position,
thrust reverser position and fuselage door position and provides instructions to other aircraft systems.
Proximity switches and sensors measure the physical relationship between two aircraft components. If the components are
close together, the sensors and/or switches provide a “near” signal. If the components are separated, a “far” signal is generated.
The PSS uses this information to generate appropriate signals for use by other aircraft subsystems.
The PSEU receives inputs from sensors and controls the takeoff configuration warning system.
Failure of the proximity sensing system is indicated on the EICAS.
STALL PROTECTION SYSTEM
DESCRIPTION
The stall protection system (SPS) provides the flight crew with aural, visual, and tactile (stick shaker) indications of an
impending stall. If the pilot does not take corrective action, the system activates the stick pusher mechanism.
　
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