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Available inboard and outboard brake pressure supply is continuously monitored and
displayed on the EICAS hydraulic synoptic page, and any abnormal brake pressure
detected is displayed on EICAS in the form of a message.
PARK/EMERGENCY BRAKE
Selection of the PARK/EMER BRAKE handle mounted on the center pedestal will
allow the flow of hydraulic system No. 3 pressure to the shuttle valves of all brake
assemblies and apply the brakes. Mechanical linkages, connected by a push/pull cable,
transfer manual inputs from the parking brake lever to the parking brake valve. For
parking brake application extend the handle to its full extended (lock) position. A
pressure switch provides a parking brake applied signal to the BCU and messages to
the EICAS.
INBD
BRAKES
PSI
3000
OUTBD
BRAKES
NORM
1A
3000
PSI
3000
PSI
3000
PSI
2A
GX_14_026
INBOARD BRAKE
PRESSURE Readout
Green
Amber
White
Displays in increments of
50 psi, pressure in the
inboard brake system.
• – between 1,800
and 3,200 psi.
• 1,800 psi.
• > 3,200 psi.
– <
–
OUTBOARD BRAKE
PRESSURE Readout
NORM
LO PRESS
Displays pressure in the
outboard brake system.
•
Green >1400 psi
•
Amber <1400 psi
–
–
PARK/EMER
BRAKE
PARK/EMER
BRAKE
PARK/EMER BRAKE Handle
• Direct pull to full up position will lock
the handle (in the extend position) for
parking. The handle must be pulled up
prior to pressing the parking brake
button to disengage the locking
mechanism.
• Gradual pull will provide mechanical
proportional braking in an emergency
condition to stop the airplane if
required.
STOWED
Antislip
SET
GX_14_027
For Training Purposes Only
Sept 04
14-29
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
Emergency proportional braking can also be commanded through the same handle. No
antiskid protection is available when emergency braking is selected. Emergency brake
application is based on the amount of travel selected by the pilot. A slow steady pull is
recommended for best results.
Flight Compartment indication of hydraulic No. 3 pressure (Hydraulic synoptic page),
provides indication for normal brake pressure, parking brake, hydraulic No. 3 failure,
or emergency brake application.
If the normal brake system fails, it will be accompanied by a warning voice advisory
and a warning NORM BRAKE FAIL message.
Park/Emergency Brake Takeoff Configuration
A takeoff configuration warning in the form of a voice advisory NO TAKEOFF and a
red EICAS message PARK BRAKE ON will be annunciated if the PARK/EMER
BRAKE handle is set and the throttles advanced for takeoff.
GX_14_028
“NORMAL BRAKE FAIL”
GX_14_029
“NO TAKEOFF”
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-30 For Training Purposes Only
Sept 04
BRAKE CONTROL SCHEMATIC
The following schematic is an overview of the components contained within the brake
control system.
GX_14_030
BRAKE
CONTROL
UNIT
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
PARKING/EMER
BRAKE
Dual
Brake
Control
Valves
Shutoff
Valves
For Training Purposes Only
Sept 04
14-31
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
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 HI (4, 8 and
13ft sec2).
AUTOBRAKE PANEL
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
　
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