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landing gear is assisted to the down-and-locked position by two tension springs and by
airflow.
C. Wheels and Tires
Each wheel has a pressure relief plug (overpressure valve) and an inflation valve.
Refer to the Aircraft Maintenance Manual for tire pressure adjustment.
REV 56, Jan 31/03
Vol. 1 16--20--12
LANDING GEAR
Nose and Main Landing Gear
Flight Crew Operating Manual MASTER
CSP A--013
Four heat sensitive fusible plugs are installed in each main wheel to release excessive
air pressure caused by heat build--up. The fusible plugs protect the main wheel tires
from bursting, that could occur under heavy braking activity.
Wheel mounted tire pressure gauges, installed on all six wheels, directly measure the
pressure of the tire. <0044>
Vol. 1 16--30--1
REV 56, Jan 31/03
LANDING GEAR
Proximity Sensing System
Flight Crew Operating Manual
CSP A--013
MASTER
1. PROXIMITY SENSING SYSTEM
The proximity sensor system (PSS) includes the proximity sensor electronics unit (PSEU)
and associated proximity sensors, proximity switches and microswitches installed throughout
the aircraft. The PSS provides five basic functions:
S Normal landing gear positioning control,
The PSS provides the signals that command the landing gear to extend and retract and
the nose gear doors to open and close.
S Landing gear position indication,
The PSS monitors landing gear position and provides indication and position status to the
EICAS.
S Weight-on-wheels indication,
The PSS monitors landing gear strut compression and provides indication of air or ground
status to the aircraft systems that require the information.
S Fuselage door indication,
The PSS monitors the fuselage door positions and provides inputs to the EICAS for
indication on the primary page, status page and door synoptic page. (refer to Chapter 6).
S Thrust reverser indication,
The PSS monitors and reports to EICAS the (stowed/unstowed) status of the left and
right thrust reversers (refer to Chapter 20).
The PSEU, after processing sensor inputs, generates outputs that are used to control the
landing gear position. The PSEU also reports system status and provides control data to
other aircraft systems.
Continuous and periodic tests are performed by the PSEU to monitor specific aircraft
systems health and status. Landing gear position and status are displayed on the engine
indication and crew alerting system (EICAS) primary page. The landing gear position
indication is removed 30 seconds after the landing gear is in the up and locked position with
the flaps at 0 degrees.
REV 56, Jan 31/03
Vol. 1 16--30--2
LANDING GEAR
Proximity Sensing System
Flight Crew Operating Manual MASTER
CSP A--013
Landing Gear Functional Schematic <MST>
Figure 16---30---1
ATTITUDE HEADING
REFERENCE SYS
AIR TRAFFIC CONTROL
TRANSPONDERS 1,2
TRAFFIC ALERT
COLLISION
AVOIDANCE SYS
GROUND PROXIMITY
WARNING SYSTEM
FLIGHT DATA
RECORDER
DATA
CONCENTRATOR
UNITS
SPOILER ELECTRONIC
CONTROL UNITS
(1A--1C, 2A--2C)
NOSE WHEEL
STEERING:
. DOWN LOCK
. WOW1,2
CABIN PRESSURE
CONTROLLER
AVIONICS
COOLING SYS
CLOCK
GEAR HANDLE
DOWNLINK
SIGNS:
. NOSMOKING
. FASTEN
SEAT BELT
NOSE GEAR
SOLENOIDS:
. EXTEND
. RETRACT
MAIN LANDING
GEAR
SOLENOIDS:
. EXTEND
. RETRACT
DOOR SELECT
VALVE:
. OPEN
. CLOSED
COMMUNICATIONS:
COCKPIT
VOICE
RECORDER
INTERCOM
WOW1
WOW2
LGC/
DOOR
LGC/
DOOR
DC BAT
DC BAT
DC BAT
DC BAT
DC BUS 1
DC BUS 2
DC ESS BUS
DC BUS 1
SENSORS
INBD GROUND
SPOILER STOWED
OUTBD GROUND
SPOILER STOWED
PARK BRAKE
SOV CLOSED
MAIN LANDING
GEAR:
. WOW1,2
. UPLOCK
NOSE GEAR:
. WOW1,2
. DOWLOCK 1,2
. UPLOCK
. OLEO EXTEND
NOSE DOOR:
. L/R CLOSED
. UPLOCK
DOOR CLOSED:
. COCKPIT EMERG
HATCH
. AFT EQPT
BAY DOOR
. OVERWING
DOORS LH/RH
. AVIONICS BAY
. SERVICE/EMERG
. BAGGAGE
COMPARTMENT
HANDLE LOCKED:
. PAX DOOR
INNER/OUTER
. SERVICE/EMERG
INNER/OUTER
. BAGGAGE
COMPARTMENT
. AVIONICS BAY
DATA
FLAPS >0,
>30
CABIN PRESSURE
>10,000
PARK BRAKE
SOV ON
THRUST LEVERS
4 DEGREES
NOSE GEAR
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