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NOTE
The nosewheel steering system cannot be reengaged unless the steering angle is less than 55 degrees, and the NOSE STEER switch is selected to OFF and then to ARMED again.
Electronic Control Unit (ECU)
The nosewheel steering electronic control unit (ECU) controls the electrohydraulic valve that directs hydraulic system 3 pressure to the steering actuator to turn the nosewheels. Nosewheel position feedback is sent to the ECU from transducers mounted on the steering actuator assembly.
In the air, the nose wheel is centered electronically by the ECU, and mechanically by centering cams as the oleo extends.
The ECU continuously monitors the nosewheel steering system. Any faults detected are annunciated on EICAS. Fault detection will result in steering system shutdown. When the steering system is shut down due to a fault, or manually disarmed, nosewheel steering reverts to the free-castering mode (which allows nosewheel deflection up to 99 degrees either side of center), and the STEERING INOP caution EICAS message is displayed.
LANDING GEAR/BRAKES Description Vol. 2 15.10.13
Oct 05/06
ENSURE THAT THE NOSEWHEEL ASSEMBLY IS CLEAR OF PERSONNEL AND TOWING EQUIPMENT BEFORE SELECTING THE NOSEWHEEL STEERING SWITCH TO THE ARMED POSITION.
Steering Tiller
Figure 15.10.7
LANDING GEAR/BRAKES Description Vol. 2 15.10.14
Oct 05/06
Description
Dual-wheel assemblies are installed on each main landing gear strut, and each main wheel is equipped with a carbon brake disc assembly. The nose gear has two wheels, and uses chine tires to eject ground water away from the aircraft engines.
Components and Operation
Each wheel of the main landing gear is equipped with self-adjusting multidisc carbon brakes. Hydraulic system 3 powers the brakes of the inboard wheels, and hydraulic system 2 powers the brakes of the outboard wheels. A parking brake function is available at both the inboard and outboard brakes. Anti-skid protection is provided.
Each main wheel has four fusible plugs that melt to prevent tire burst, in the event of an overheated wheel or brake condition.
Brake application is initiated by pressing the brake pedals, which are mechanically linked to the four associated brake control valves. The brake control valves meter hydraulic pressure to the brakes through anti-skid control valves.
During gear retraction, hydraulic pressure from the nose landing gear is directed to the brake control valves to stop main wheel rotation (in-flight braking).
In case of failure of hydraulic systems 2 or 3, accumulators in both hydraulic brake systems provide pressure for approximately six brake applications with the anti-skid selected off. Loss of either hydraulic system 2 or 3 results in a 50% reduction in braking capability. Braking remains symmetrical, and anti-skid is available at the working brakes.
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本文链接地址：庞巴迪挑战者605公务机机组操作手册 CL605-起落架 LANDING GEAR(7)
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