F. Brakes and Steering Built-in Test Equipment (Ref. 32-46-00)
The BSCU includes hardware and software which:
-continuously monitors the systems for failures
-does automatic system tests at specified times
-permits specified system tests during ground maintenance.
G. Brake System Temperature Monitoring System (Ref. 32-47-00)
The system continuously measures the temperature of each brake. It has a sensor on each brake and a Brake Temperature Monitoring Unit (BTMU) for each pair of brakes.
The brake temperatures are shown on the WHEEL page. When a brake becomes too hot:
-
the EWD gives a warning message and instructions (during specified flight phases)
-
the MASTER CAUT lights come on
-an aural warning is given.
H. Tire Pressure Indicating System (TPIS) (Ref. 32-49-00) (optional)
The TPIS automatically monitors the landing-gear tire pressures and continuously shows the values on the WHEEL page.
The system includes an electronic pressure sensor in each wheel and a Tire Pressure Indicating Computer (TPIC). The TPIC controls the operation of the system and sends data to other systems in the aircraft. It supplies data and warnings if the pressures are unsatisfactory.
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4. Power Supply____________
A. Electrical Power Supplies
(Ref. Fig. 002)
B. Hydraulic Power Supplies
Refer to 29-11-00 and 29-13-00
5. Interface_________
(Ref. Fig. 003)
6. Component Description_____________________
A. Operation/Control
(1) Normal braking (Ref. 32-42-00)
In the manual braking mode, operation of the brake pedals causes a signal to be sent to the BSCU. The BSCU energizes the brake selector valve and the servovalves which supply the correct pressure to the brake units (Ref. 32-42-00). The BSCU automatically releases the pressure (servovalve control) in the necessary brakes during anti skid control.
In the automatic braking mode the BSCU uses the braking program that is set to control the rate of the aircrafts deceleration. The BSCU starts the braking program when the necessary specified conditions are available. It calculates the correct brake pressure required and controls the servovalves to get the correct deceleration rate.
The BSCU also controls the anti skid function. To do this it compares the actual wheel speeds with the aircraft speed. The BSCU then releases the brake of the wheel that starts to be in a skid condition.
The BSCU also puts the brakes on for a short time during retraction of the landing gear.
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Electrical Power Supplies-Schematic
Figure 002
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Interface
Figure 003
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1 1 Config-2 Aug 01/05
1 1
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(2)
Alternate braking with anti skid (Ref. 32-43-00)
When the brake pedals are operated a signal is sent to the ABCU. The ABCU controls the system pressure that goes to the brakes. In the anti skid function, the BSCU sends anti skid currents to the ABCU which substracts them to the pressure control currents sent to the Direct Drive Valve to release the pressure to prevent wheel locking.
(3)
Alternate braking without anti skid (Ref. 32-44-00)
When the brake pedals are operated a signal is sent to the ABCU.The ABCU controls the Direct Drive Valves in the system to set the necessary pressure at each pair of brake units.
(4)
Parking braking (Ref. 32-45-00)
When the PARK BRK control switch is set to ON (applied) it sends an electrical signal to energise an electrohydraulic control valve.The other braking modes are disconnected, the brakes are supplied with Yellow high pressure or accumulator pressure. The parking brake control valve limits the pressure. The CONFIG PARKING BRAKE ON message appears on the upper ECAM DU when:
-the parking-brake control switch is in the ON (applied) position - one engine is at full throttle.
(5)
Ground Tests and BITE (Ref. 32-46-00)
The BITE function of the braking/steering control unit (BSCU)
permanently monitors the electrical control and regulation functions
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