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the airplane is in takeoff
parameters.
"NO TAKEOFF"
BRAKE CONTROL SCHEMATIC
The following schematic is an overview of the components contained within the brake control system.
ONE WAY ACCUMULATOR
HYD #2 HYD #3
PARKING/EMERGENCY
BRAKE VALVE
DUAL
BRAKE
CONTROL
VALVES
SHUTOFF
VALVES
SHUTTLE VALVE (4)
PUSHPULL
CABLE
CHECK VALVE
PRESSURE
TRANSDUCER X4
(to EICAS)
PRESSURE
TRANSDUCER
BRAKE
CONTROL
UNIT
PARK/EMER
BRAKE
(parking brake applied
signal to the BCU)
NOTE
The return system is not shown
in this schematic.
GF1510_028
LANDING GEAR
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
15−10−25
AUTOBRAKE SYSTEM
Autobrake function is provided for landing only. A flight compartment mounted AUTOBRAKE switch
provides selection of three deceleration levels and an “OFF” position. The switch is spring loaded to
the “OFF” position when not activated or disabled. The three deceleration levels are indicated as LO,
MED and H (4,8 and 13 ft sec².
AUTOBRAKE PANEL
AUTOBRAKE Switch
OFF − Inhibits the autobrake
function.
LO, MED and HI − Provides a
controlled rate of deceleration
based upon selection.
GF1510_029
GND LIFT
DUMPING
AUTO BRAKE
Deceleration rates are calculated from the reference wheel speed. If the rate difference is more than
a predetermined rate of knots, it will cancel the autobrake function and the switch will return to the
“OFF” position automatically.
All of the following conditions must be met to “arm” the autobrake and hold the switch in the selected
position:
· Switch selected to either LO, MED or HI.
· Airplane in the flight mode of operation (example: WOW indicating air).
· No deploy command for the ground spoilers.
· Brake pedal application less than 20% travel .
· Wheel speed at zero velocity.
· No autobrake or brake control faults.
The autobrake will apply when all of the following conditions are met:
· Autobrake switch selected to either LO, MED or HI.
· Both MLG weight on wheels for greater than 5 seconds or wheels spinup
greater than 50
knots.
· Ground spoilers commanded to deploy.
The autobrake will “disarm” (release the deceleration control and command the AUTOBRAKE switch
to rotate to the “OFF” position) under any of the following conditions:
· Autobrake switch selected to “OFF” at any time.
· Brake pedal application of greater than 20% travel.
· Any autobrake or brake control fault during autobrake operation.
· Wheel speed signal invalid (determined by a comparison of channel A and B of the BCU).
· Ground spoilers stowed after having been deployed.
LANDING GEAR
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
15−10−26
BCU INTERFACE SCHEMATIC
ACCUMULATOR
ONE WAY
CHECK VALVE
HYD #2 HYD #3
PARKING/EMERGENCY
BRAKE VALVE
DUAL
BRAKE
CONTROL
VALVES
SHUTOFF
VALVES
SHUTTLE VALVE (4)
PUSHPULL
CABLE
RUDDER PEDALS
LGECU
CHANNEL A
CHANNEL B
SPOILER
SPOILER
WEIGHTONWHEELS
FLIGHT
O
UTP
UT
LEFT THRUST
RIGHT THRUST
REVERSER
REVERSER
DEPLOY
#2
DEPLOY
#1
CAIMS/EICAS
AND AUTOBRAKE
MAIN LANDING GEAR DOWNLOCK
GEAR UP SELECTED (inhibit wheel rotation)
PRESSURE
TRANSDUCER X4
(to EICAS)
PRESSURE
TRANSDUCER
CONTROL
UNIT #1
FLIGHT
CONTROL
UNIT #2
BRAKE CONTROL UNIT (BCU)
WHEEL SPEED
TRANSDUCER (4)
FLIGHT
CONTROL
UNIT #1
FLIGHT
CONTROL
UNIT #2
W
H
EEL
S
PEE
D
AUTOBRAKE
PANEL
PARK/EMER
BRAKE
GF1510_030
LANDING GEAR
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
15−10−27
BRAKE TEMPERATURE MONITORING SYSTEM
The Brake Temperature Monitoring System (BTMS) consists of four sensors each mounted in a
brake housing and the Heater current/Brake temperature Monitor Unit (HBMU). Brake temperature is
indicated in the flight compartment on the EICAS status display when the landing gear is selected
　
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