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• Airplane in the flight mode of operation (i.e.: WOW indicating air)
• No deploy command for the ground lift dump spoilers
• Brake pedal command for application travel less than 20%
• 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 LOW, MED, or HI
• Both MLG weight on wheels for greater than 5 seconds or wheels spin-up 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 (comparison of channel A and B of the BCU)
• Ground spoilers stowed after having been deployed
GND LIFT
DUMPING
AUTO BRAKE
AUTO
OFF LOW
MED
HI
MANUAL ARM
OFF
AU
F
GX_14_031
AUTOBRAKE Switch
OFF
LO, MED and HI
• Inhibits the autobrake
function.
• Provides a
controlled rate of deceleration
based upon selection.
–
–
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-32 For Training Purposes Only
Sept 04
BCU INTERFACE SCHEMATIC
GX_14_032
BRAKE CONTROL UNIT (BCU)
HYD NO. 2 HYD NO. 3
Pressure
Transducer
X4 (to Eicas)
Pressure
Transducer
(parking brake
applied signal to
the BCU)
Shuttle
Valve (4)
Parking/
Emergency
Brake Valve Push-
Pull Cable
Accumulator
One Way
Check
Valve
PARK/EMER
BRAKE
Dual-Brake
Control Valves
Shutoff Valves
WEIGHT-ON-WHEELS
MAIN LANDING GEAR DOWNLOCK
GEAR UP SELECTED (inhibit wheel rotation)
SPOILER
DEPLOY
NO. 1
SPOILER
DEPLOY
NO. 2
LGECU
FLIGHT
CONTROL
UNIT NO. 1
FLIGHT
CONTROL
UNIT NO. 2
W
H
E
E
L
S
P
E
E
D
O
U
T
P
U
T
FLIGHT
CONTROL
UNIT NO. 1
FLIGHT
CONTROL
UNIT NO. 2
LEFT THRUST
REVERSER
RIGHT THRUST
REVERSER
AUTOBRAKE
PANEL
CHANNEL A
CHANNEL B
CAIMS/EICAS
AND
AUTOBRAKE
RUDDER
PEDAL
For Training Purposes Only
Sept 04
14-33
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
BRAKE TEMPERATURE MONITORING UNIT
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 down. A BTMS OVHT WARN
RESET button is located on the landing gear control panel and is used to reset the
system when the condition no longer exists. Brake cooling charts will determine the
safe range of operation. Refer to brake cooling chart in the Airplane Flight Manual
CSP 700-1.
BRAKE TEMPERATURE MONITORING SCHEMATIC
GX_14_033
WARNING
RESET
WARNING
RESET
HBMU NO. 1 HBMU NO. 1
LEFT
OUTBD
TEMP
LEFT
OUTBD
TEMP
LEFT
INBD
TEMP
LEFT
INBD
TEMP
BRAKE TEMP FAIL
BRAKE TEMP
DAU
NO. 1
IAC IAC
DAU
NO. 2
EICAS
BRAKE OVHT
LEFT
OUTBD
BRAKE
UNIT
RIGHT
OUTBD
BRAKE
UNIT
LEFT
INBD
BRAKE
UNIT
RIGHT
INBD
BRAKE
UNIT
BTMS OVHT WARN RESET
When the system returns to normal
operating temperature, push the
button to reset the system and
cancel the overheat warning.
BTMS OVHT
WARN RESET
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-34 For Training Purposes Only
Sept 04
The BTMU turns the corresponding display (on the EICAS status page) red when a
brake overheat condition exists, and when the wheels are approaching the fuse plug
release temperature. If fuse plug release occurs, the wheel assembly will release the
tire pressure to atmosphere.
A red Warning EICAS message (BRAKE OVHT) accompanies the overheat
condition. The spring-loaded BTMS OVHT WARNING RESET button is mounted to
　
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