Nose Wheel Steering Control-Principle
Figure 016
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Aircraft Towing Radii - A320
Figure 017
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Aircraft Towing Radii - A319
Figure 017A
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Aircraft Towing Radii - A321
Figure 017B
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1. General
_______
(Ref. Fig. 001)
The control is electrohydraulic with position feedback of the nose wheel
assembly.
The BSCU receives steering inputs then supplies steering outputs to
electrohydraulic valves in the system.
The electrohydraulic valves control the flow of hydraulic fluid to hydraulic
actuators that turn the steering mechanism.
Sensors in the system supply the correct NWS position signals to the BSCU.
This lets the BSCU monitor the operation of the steering mechanism.
A monitoring channel permits:
-detection of the failures
-de-activation of the control in the event of a failure which may cause wheel runaway.
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Nose Wheel Steering - Principle
Figure 001
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2. Component Location__________________
(Ref. Fig. 002, 003, 004)
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
-------------------------------------------------------------------------------1GC XMTR UNIT-N/W STRG HANDWHEEL,CAPT 19VU 211 831 32-51-11 2GC XMTR UNIT-N/W STRG HANDWHEEL,F/O 18VU 212 831 32-51-11 3GC SENSOR-N/W STRG FDBK,CTL CHAN 711 32-51-19 4GC SENSOR-N/W STRG FDBK,MONITORING CHAN 711 32-51-19 5GC ELEC BOX-N/W STEERING,DEACTIVATION 711 32-51-12 6GC SERVO CTL-N/W STEERING 711 32-51-51 7GC SERVO CTL-N/W STEERING 711 32-51-23
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Steering System Handwheel - Component Location
Figure 002
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Steering Control - Component Location
Figure 003
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Selector Valve - Component Location
Figure 004
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3. System Description
__________________
(Ref. Fig. 005)
Nose wheel steering is possible from the cockpit as follows:
During taxi, and more generally at low speed, through action on a handwheel.
There are two identical handwheels: one for the Captain, one for the First
Officer.
In the event of simultaneous operation, the orders that the handwheels give
are algebraically added.
The maximum travel of the wheels is plus or minus 74 deg.
The maximum corresponding travel of the handwheel is plus or minus 75 deg.
However, the law between these two travels is not linear.
(Ref. Fig. 006)
The servoing is active with the aircraft on ground upon impact of the main
landing gear. The steering angle is limited as a function of the aircraft
speed.
During takeoff or landing, and more generally at high speed
-either through action of the Captain (or First Officer) on the rudder
pedals, - or automatically through the autopilot (yaw control). In both cases, the steering angle is limited as a function of the aircraft speed and the origin of the orders. (Ref. Fig. 007, 008)
When the aircraft speed is above 130 knots, the steering is not available.
(Ref. Fig. 007)
If the runway is icy, the pilot can disconnect the control through the
pedals from the steering control.
To obtain this, the pilot presses and holds a pushbutton switch located on
each handwheel.
After takeoff, the nose wheels are automatically centered under the action
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