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LANDING GEAR
BCU INTERFACE SCHEMATIC
RUDDER PEDALS
AUTOBRAKE
PANEL
FLIGHT CONTROL UNIT #1
FLIGHT CONTROL UNIT #2
LEFT THRUST
REVERSER
RIGHT THRUST REVERSER
HYD #3
PUSH-PULL
CABLE
PARK/EMER
BRAKE
GF1510_030
LGECU
FLIGHT CONTROL UNIT #1
FLIGHT CONTROL UNIT #2
ONE WAY CHECK VALVE
HYD #2
PRESSURE
TRANSDUCER X4 (to EICAS)
BRAKE CONTROL UNIT (BCU)
WEIGHT-ON-WHEELS W
H
MAIN LANDING GEAR DOWNLOCK
E
GEAR UP SELECTED (inhibit wheel rotation)
OE UL
T
SPOILER DEPLOY CHANNEL A P U T S P E
#1 E
D
SPOILER CAIMS/EICAS
DEPLOY AND AUTOBRAKE
#2
CHANNEL B
ACCUMULATOR
SHUT-OFF PARKING/EMERGENCYVALVES BRAKE VALVE
DUAL
BRAKE
CONTROL
VALVES
PRESSURE TRANSDUCER
SHUTTLE VALVE (4)
WHEEL SPEED
TRANSDUCER (4)
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
LANDING GEAR
BRAKE TEMPERATURE MONITORING SYSTEM
The Brake Temperature Monitoring System (BTMS) consists of four sensors each mounted in a brake housing and the Heater current/Brake temperature Monitor Unit (HBMU). Brake temperature is indicated in the flight compartment on the EICAS status display when the landing gear is selected 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
BTMS OVHT WARN RESET
When the system returns to normal operating temperature, push the
button to reset the system and cancel the overheat warning.
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.
BRAKE TEMPERATURE
Green range: 00.05
GF1510_032
INDICATORS
White range: 06.16
Red range: 17 and greater
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.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
LANDING GEAR
NOSE WHEEL STEERING SYSTEM
The steering control system is electrically controlled and hydraulically actuated.
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