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The dual brake control system independently controls the braking of each main wheel by modulating the pressure outputs of the appropriate brake control valve. This modulation is controlled by the BCU which monitors individual wheel speed and deceleration through the wheel speed transducers.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
LANDING GEAR
BRAKE CONTROL SYSTEM (CONT'D)
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. The signal for brake pressure indication (systems 2 and 3) is derived from four electrically redundant brake pressure transducers positioned prior to each shuttle valve. One pressure transducer channel is linked to BCU channel A, the other to channel B for each
system.
INBOARD BRAKE OUTBOARD BRAKE PRESSURE READOUT Displays pressure in the outboard brake system.
Green . NORM will appear
GF1510_024
Amber . LO PRESS
1400 psi.
White .
3,200 psi
Park/Emergency Brake
Selection of the PARK/EMER BRAKE handle mounted on the centre pedestal will allow 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 transducer will provide a parking brake applied signal to the BCU and a message to the EICAS.
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.
GF1510_025
Emergency proportional braking can also be commanded through the same handle. No anti-skid protection is available when proportional 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 accumulator pressure (Hydraulic synoptic page), provides indication for normal brake pressure, parking brake, No. 3 hydraulic failure or emergency brake application.
"NORMAL BRAKE FAIL"
If the normal brake system fails, it will be accompanied by a warning voice advisory and a warning “NORM BRAKE FAIL”message.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
LANDING GEAR
BRAKE CONTROL SYSTEM (CONT'D)
Park/Emergency Brake Take-off Configuration
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