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The accumulator in the left hydraulic system allows extended parking, or at least six emergency brake pressure applications. Accumulator pressure information is provided to the flight crew by a pressure transducer.
The EICAS indicates normal parking brake engagement or any fault detected in the form of a visual/or aural message.
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
15-01-12 TIRES AND BRAKES (Cont) BRAKE CONTROL SYSTEM
PILOT COPILOT
VALVE
BRAKE
RIGHT
SYSTEM RETURN RIGHT SYSTEM
PRESSURE LEFT HYDRAULIC SYSTEM
RETURN LEFT HYDRAULIC SYSTEM
CFO1501002_033
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
15-01-13
TIRES AND BRAKES (Cont)
MAIN AND PARK/EMER BRAKE ACCUMULATORS
The main and park/emergency brake accumulators are located on the aft side of the underwing fairing support frame. The parking/emergency brake accumulator is connected to a gauge and charge valve that is located in the rear fuselage battery compartment.
A
BRAKE
ACCUMULATOR
PARK/EMERGENCY
BRAKE
ACCUMULATOR
A
CFO1501002_029
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
15-01-14 TIRES AND BRAKES (Cont) ANTI-SKID
DESCRIPTION
The anti-skid function controls brake pressure to prevent skids.The brake control unit provides antiskid protection down to 10 kts to each of the main wheels. Rotation speed of each wheel and its rate of deceleration are sensed by the wheel speed transducers and this data is transmitted to the brake control unit. The brake control unit modulates the hydraulic pressure at the brake to prevent wheel lockup.
The system prevents lockup by comparing the speed of each wheel installed on the same landing gear assembly. It also compares the speed between each wheel of the same brake system, outboard or inboard. For example, if the right inboard wheel rotates at a significantly slower speed than the left inboard, the brake control unit releases the brake on the slower turning wheel. When both paired wheels return to the same speed, the brake control unit reapplies brake pressure.
NOSEWHEEL STEERING
DESCRIPTION
The nosewheel steering is designed to provide safe and reliable directional control of the aircraft during all phases of taxi, takeoff and landing. The nosewheel steering provides electrically controlled and hydraulically powered actuation of the nose landing gear steering actuator mounted on the nose gear assembly. When the nosewheel steering is not armed, or under failure con-ditions, the system continues to provide effective damping to ensure dynamic stability of the nose landing gear.
The Nosewheel Steering System (NWS) is armed by selecting the NWS switch on. The NWS switch is located on the LANDING GEAR control panel and is illuminated when it is in the OFF position. Steering commands are input to the steer-ing control unit (SCU) through the pilot handwheel (full authority, ±65° at the nose wheel) and/or through the rudder pedals (limited authority, ±7° at the nose wheel). Position feedback is provided to the SCU from a position transducer on the NLG. There is no mechanical connection between the flight deck controls and the steering actuators. Nosewheel steering com-mands are transmitted electronically using “steer-by-wire” technology.
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