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UPLOCK
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GF1510_023
LEGEND
Cable Circuit Control Linkage
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
LANDING GEAR
BRAKE CONTROL SYSTEM
The main wheels have carbon disk brakes. They are controlled by the Brake Control Unit (BCU) using an anti-skid system, with auto-braking capability.
Refer to BRAKE CONTROL SCHEMATIC in this Chapter to support the information that follows.
The brake control system provides hydraulic services to the outboard brakes (hydraulic system 2) and the inboard braking systems (hydraulic system 3). Hydraulic system 3 will also provide pressure to all brakes via shuttle valves for parking/emergency brake application. Brake systems 2 and 3 have an accumulator (backup) for emergency operation in case of hydraulic system failure. The system 3 accumulator is also monitored to provide flight compartment indication of available parking/emergency accumulator pressure. Hydraulic volumetric fuses are installed at each brake supply line to provide system protection against line rupture.
Two brake shutoff valves control the inlet pressure to the brake control valves and are used to:
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Turn off hydraulic power to the brake control valves during flight.
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Shut off pressure in the event of uncommanded braking.
The hydraulic inlet porting of the brakes has a shuttle valve. Brake shuttle valves are used to isolate brake control function from park/emergency brake function. Four shuttle valves are used, one for each brake. The shuttle valve provides the higher of the two input pressures (either brake control/anti-skid or parking/emergency brake) to the brake.
Pilot and/or copilot brake input is provided by four brake pedal transducers. The signal is processed by the BCU and commands appropriate brake pressure. If a failure or unreliable signal is present, a pilot/copilot brake fault message will display on EICAS. Wheel speed is monitored by four transducers installed in each main wheel axle and these signals are used for anti-skid control valve operation. The brake and anti-skid control system interfaces with the BCU for autobrake capability.
The BCU provides the brake control system with built-in-test equipment (BITE) and the following protections:
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Gear retract braking (stops wheel rotation, after take-off).
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Inhibiting normal gear braking in flight.
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Independent wheel anti-skid.
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Locked wheel and touchdown protection.
In the air mode (no WOW signal), the BCU configures the airplane to a full brake dump to prevent wheel lock up on touchdown. The touchdown protection system is cancelled to allow modulated braking once a predetermined wheel spin-up signal is present or airplane WOW is detected. The BCU will cancel hydraulic power to any wheel which is sensed to be at an abnormal deceleration rate (example: locked wheel).
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