If the normal braking system is not available, control automatically changes to one of the alternate braking systems (Ref. 32-43-00) or (Ref. 32-44-00).
Alternate braking with anti-skid (Ref. 32-43-00) is a secondary electro-hydraulic braking system. It is automatically available if specified failures occur in the normal braking system. Braking inputs are made only at the brake pedals through a low-pressure hydraulic system. The BSCU controls four servo valves in the system to supply the anti-skid function. The hydraulic pressure that operates the brake pistons is supplied from the Yellow main hydraulic power system (Ref. 29-13-00).
Alternate braking without Anti-skid (Ref. 32-44-00) is the secondary mode of operation of the alternate braking system. Braking inputs are made only at the brake pedals. As electrical power is necessary to operate this system, it is usually used when the aircraft is towed. The hydraulic pressure is supplied from the Yellow main hydraulic power system (Ref. 32-13-00) or accumulators.
The parking brake system (Ref. 32-45-00) is an electro-hydraulic system. It is used to prevent movement of the aircraft when it is parked. It can also be used to stop the aircraft if all other braking systems are not available. The system operates from the accumulators in the alternate braking system.
(1) Brakes and Steering Built-in Test Equipment (BITE) (Ref. 32-46-00)
The BITE has hardware and software for these functions:
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to automatically do a self test at power-up
-
to continuously monitor the related systems for failures
-
to continuously monitor the interface with other specified systems in the aircraft
-
to keep a record of each failure and defect and send this data to other systems in the aircraft
-
to automatically do a functional test of some related systems before a landing
-
to do specified system tests during ground maintenance.
(2) Brake Temperature System (Ref. 32-47-00)
The brake temperature system includes a temperature sensor at each
brake which measures the temperature and sends the data to a brake
temperature monitoring unit. The brake temperatures are shown
automatically on the wheel page of the ECAM System Display (SD)
1EFF : ALL 1 32-00-00Page 22 1 1 Aug 01/05R 1 1 1CES 1
R **ON A/C 051-099, 301-399, 401-499,
(3) Brake Cooling System (Ref. 32-48-00)
The brake cooling system is a manually controlled system that decreases the temperature of the brakes when they are too hot. The system is usually used on the ground but can also be used in flight if a landing is necessary immediately. The system includes a P/BSW and an electrically operated fan in each MLG wheel. The P/BSW has: - a HOT light that shows if the temperature of a brake is more than a specified value - an ON light that shows when the switch is pushed in (selected ON).
**ON A/C 051-099,
(4) Tire Pressure Indicating System (TPIS) (Ref. 32-49-00)
TPIS includes an electronic sensor on each wheel and a Tire Pressure Indicating Computer (TPIC). The TPIC controls and monitors the operation of the system and sends data to other interfaced systems.
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
E. Steering (Ref. 32-51-00)
The steering system is controlled by the BSCU (Ref. 32-46-00). The steering system changes the direction of the aircraft when it moves on the ground. The system uses the Green main hydraulic-power system (Ref. 29-11-00) to operate a steering mechanism which changes the direction of the NLG wheels. Two handwheel transmitters in the cockpit supply the primary steering inputs to the BSCU. The rudder pedals and the autopilot supply secondary input to the BSCU through the flight control primary computers. The system operation can be cancelled to let the nose wheels move freely during aircraft ground movement.
R **ON A/C 401-499,
R R R R R R E. Steering (Ref. 32-51-00) The steering system is controlled by the BSCU (Ref. 32-46-00). The steering system changes the direction of the aircraft when it moves on the ground. The system uses the Yellow main hydraulic-power system (Ref. 29-13-00) to operate a steering mechanism which changes the direction of
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