The changes between the Yellow high-pressure system and the
accumulator are automatic and reversible.
The brake Yellow-pressure triple-indicator shows the pressure of the
accumulator. The operation of the pushbutton which controls the
Yellow electric pump fills the power accumulator.
The accumulator can supply at least seven full brake applications.
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Brake System - Schematic
Figure 002
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Brake System - Schematic
Figure 002A
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1
(4) Parking Brake
When the PARK BRK control switch is set to ON (applied):
-
the other braking modes are disconnected,
-
the brakes are supplied with Yellow high pressure or accumulator
pressure. The parking-brake electrical control-valve limits the pressure. The return lines are shut off to permit to hold the brakes on for a minimum of twelve hours. The red warning light flashes. 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.
C. Auto Brake This system:
-decreases the number of flight crew actions if an acceleration-stop
(MAX mode) occurs, - or keeps the deceleration to a pre-set limit (LOW or MED) when landing. The flight crew pushes the LO, MED or MAX pushbutton switch to arm the system. The blue ON legend on the lower half of the pushbutton switch comes on if the Normal braking is operational. The ground spoiler extension command starts the braking action. The Green DECEL legend on the upper half of the pushbutton switch comes on:
-when you get the set deceleration rate, i.e.: 2 m/s 2 in LOW mode or 3
m/s 2 in MED mode,
- or when you get a 0.27 g deceleration in the MAX mode.
The auto brake system is disengaged and disarmed:
-
if one (or more) of the arming conditions is (or are) lost,
-
if you apply sufficient pressure to the pedals with the aircraft on the
ground (takeover through brake pedals). The failure of the auto brake is shown on the upper ECAM DU before and after the selection.
D. Brake Temperature System The brake temperature system:
-measures the temperature at each of the four brakes,
-shows the temperature values on the lower ECAM DU,
-tells the flight crew to delay take off or extend the gear (messages on the upper ECAM DU).
E. Ground Tests and BITE The BITE function of the braking/steering control unit (BSCU) permanently monitors the electrical control and regulation functions. The faults found are memorized and shown on the CFDIU.
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F. Brake Cooling Fans The brake cooling fans permit high speed cooling of the brakes. They thus decrease the turnaround time of the aircraft if you make short flights with high energy braking. One fan is installed on each wheel of the main gear. A BRK FAN pushbutton switch is used to operate the fans. When the brakes are hot, the HOT legend of the pushbutton switch comes on.
**ON A/C 051-099,
G. Tire-Pressure Indicating System (TPIS) The TPIS shows the pressure of the tires of the main gear and nose gear on the lower ECAM DU.
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_____________________________________________
1. General_______
The wheels and their related system of brakes let you control the movement
of the aircraft on the ground.
The wheels are described in chapter 32-41-00.
There are two brake systems (normal and alternate) that can independently
operate the brake units. The alternate system has diferent modes of
operation. The systems and their modes of control and operation are given in
the chapters that follow:
-Normal Braking (Ref: 32-42-00).
-
Alternate Braking with Anti Skid (Ref: 32-43-00).
-
Alternate Braking without Anti Skid (Ref: 32-44-00).
-Parking/Ultimate Emergency Braking (Ref: 32-45-00).
The brake systems have a computer which has Built-In Test Equipment (BITE). This continuously monitors the operation of the brake and steering systems (Ref: 32-46-00).
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