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down. A “BTMS OVHT WARN RESET” button is located on the landing gear control panel and is
used to reset the system when the condition no longer exists. Brake cooling charts will determine the
safe range of operation. Refer to brake cooling chart in the Airplane Flight Manual CSP 700−1.
BRAKE TEMPERATURE MONITORING SCHEMATIC
HBMU#1
WARNING
RESET
EICAS
BRAKE TEMP FAIL
BRAKE TEMP
DAU BRAKE OVHT
#1
LEFT
OUTBD
LEFT
INBD
TEMP TEMP
BTMS OVHT WARN RESET
When the system returns to normal
operating temperature, push the
button to reset the system and
cancel the overheat warning.
LEFT
OUTBD
BRAKE
UNIT
IAC HBMU#2
WARNING
RESET
DAU
#2
RIGHT
OUTBD
RIGHT
INBD
TEMP TEMP
IAC
LEFT
OUTBD
BRAKE
UNIT
LEFT
OUTBD
BRAKE
UNIT
LEFT
OUTBD
BRAKE
UNIT
GF1510_031
The BTMU turns the corresponding display (on the EICAS status page) red when a brake overheat
condition exists and when the wheels are approaching the fuse plug release temperature. If fuse plug
release occurs, the wheel assembly will release the tire pressure to atmosphere.
Green range: 00−05
White range: 06−16
Red range: 17 and greater
BRAKE TEMPERATURE
INDICATORS
GF1510_032
BRAKE TEMP
03 03 03 03
A red EICAS message and a resettable warning will accompany the overheat condition. Resetting
the system (when the condition no longer exists) will cancel the warning and display the numerical
color values according to their sensors actual temperature.
LANDING GEAR
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
15−10−28
NOSE WHEEL STEERING SYSTEM
The steering control system is electrically controlled and hydraulically actuated.
The nose wheel steering system is armed from a switch on the landing gear control panel in the flight
compartment. It is activated once the WOW signal and nose landing gear downandlocked
signals
are present. Steering commands are input to the Electronic Control Unit ( ECU) through the pilot’s
hand wheel (full authority ± 75°) and/or the rudder pedals (limited authority ± 7.5°).
NOTE
If handwheel and rudder pedal input commands are received at the
same time, the ECU will sum these inputs to a maximum of ± 75°.
Nose wheel position feedback is provided to the SCU by 2 transducers mounted on the steering
actuators. The Steering Control Unit (SCU) controls an electrohydraulic
servovalve
in the hydraulic
manifold (mounted on the nose gear assembly), which ports hydraulic pressure to each of the
steering actuators as required. The steering actuators (mounted on the main fitting of the nose gear)
operate in a push/pull manner to rotate the steering collar. Mechanical torque links are provided to
transmit the movement of the steering collar to the nose wheels.
The steering commands are processed by the SCU and No. 3 hydraulic system pressure is routed
through the system, when the landing gear is selected down.
In the air mode, the nose wheel is centered electrically by the SCU and mechanically by centering
cams as the shock strut extends under its own weight.
When the steering system is disarmed or with no WOW signal, the nose wheel steering will revert to
free caster and shimmy damping to ensure stability within the nose wheel circuit. In the free caster
mode of operation, steering is accomplished only through differential braking and differential thrust.
The SCU continuously monitors the nose wheel steering system and any fault within the system will
be displayed as a caution message. Fault detection will result in nosewheel steering system shut
down and the system will then operate in free caster mode of operation.
LANDING GEAR
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
15−10−29
NOSE WHEEL STEERING SCHEMATIC
NO.3 HYDRAULIC
SYSTEM
TO EICAS
STEERING HANDWHEEL
PILOT’S SIDE PANEL
NOSE WHEEL
STEERING SWITCH
NOSE LANDING
GEAR DOWN
AND LOCKED
WOW
ELECTRONIC
CONTROL
UNIT
STEERING MANIFOLD
NOSE
WHEEL
STEERING
ACTUATORS
P
RUDDER PEDALS
LGECU
ASSEMBLY
GF1510_033
NOSE STEER
LANDING GEAR
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
15−10−30
EICAS MESSAGES
　
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