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pins are inserted by the ground crew.
Vol. 1 16--20--6
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Landing Gear Controls
Figure 16---20---4
Landing Gear Lever Down Lock
Prevents inadvertent landing gear up
selection when on ground.
When airborne, a weight--off--wheels signal
from the PSEU disengages the lock to
permit a gear up selection.
Landing Gear Lever
Used to retract and extend landing gear.
Landing Gear Control Panel
Centre Instrument Panel
DN LCK REL
Used to manually release the landing gear
lever down lock.
Considerable force is required to operate the
landing gear manual release system.
NOTE
Vol. 1 16--20--7
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Landing Gear EICAS Indications <1001>
Figure 16---20---5
NOSE DOOR OPEN warning (red)
Indicates that either nose landing gear
door is not closed after gear is up.
GEAR DISAGREE warning (red)
Indicates that landing gear position does not
agree with landing gear control handle position.
HORN MUTED status (white)
Indicates that landing gear warning
horn has been manually muted.
NOSE
DOOR
GEAR
DISAGREE
L or R MLG FAULT status (white)
Indicates that left or right actuator shuttle
valve or the pressure switch have failed in
the closed position (for MLG downlocked)
OR
Left or right actuator pressure switch has
failed in open position (for MLG uplocked).
Primary Page
Status Page
Vol. 1 16--20--8
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. Alternate Landing Gear Extension
If a failure occurs in the landing gear control system or in hydraulic system No. 3, the
landing gear can still be extended by pulling the landing gear manual release handle.
When the manual release handle is pulled, the main landing gear uplocks are released
by mechanical means, and at the same time a bypass valve dumps hydraulic system
No. 3 pressure from the normal extension and retraction hydraulic circuits. This will
permit the landing gear to partially extend under its own weight. The manual release
handle also positions a downlock assist valve to direct hydraulic system No. 2 pressure
to the main landing gear auxiliary actuators and to the nose gear uplock manual
release actuator.
The main landing gear is assisted to the down-and-locked position by the main gear
auxiliary actuators and the nose landing gear is assisted to the down-and-locked
position by airflow and two tension springs.
B. 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.
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 against
tire burst that could occur under heavy braking activity.
C. Landing Gear Doors
The landing gear doors are mechanically linked to the landing gear. The doors close
when the gear retracts and open when the gear extends.
Vol. 1 16--30--1
LANDING GEAR
Proximity Sensing System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
1. PROXIMITY SENSING SYSTEM
The proximity sensor system (PSS) includes the proximity sensor electronics unit (PSEU)
and associated proximity sensors and proximity switches 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 extend and retract
solenoids to change the position of the landing gear.
S Landing gear position indication
The PSS monitors landing gear position and provides indication of the position status of
the landing gear.
S Weight-on-wheels indication
The PSS monitors landing gear strut compression and provides indication of air or ground
status of the aircraft.
S Fuselage door indication
The PSS monitors fuselage door position, latches and lock status and provides indication
of the status of the doors (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
landing gear position, report status and provide control data for other systems.
　
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