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MAIN/NOSE
GEAR AND DOOR
CONTROL VALVES
WEIGHTONWHEELS
LOGIC
PROCESSING
AIRPLANE
MAIN/NOSE
GEAR
AND
DOOR
POSITIONS
SYSTEMS
LANDING GEAR
ELECTRONIC CONTROL
UNIT GF1510_007
LDG GEAR
LANDING GEAR
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
15−10−9
LGECU CONTROL
The LGECU receives gear position commands (current or new) from the landing gear control handle
in the flight compartment. The handle is compared with actual gear position and WOW for each
landing gear assembly. The landing gear system includes proximity sensors for gear and door
positioning and locked position monitoring.
The EICAS monitors the information received from the LGECU and generates status and warning
messages when certain conditions are met.
The landing gear door, control and indications system provides three basic functions:
· Landing gear sequencing control − The system performs logic on handle position, landing gear
and door positions, WOW and gear lock inputs. It provides the signals that command the
landing gear, landing gear door and lock actuators that change the position of the landing gear
based on this input logic.
· Landing gear, door and fuselage door position indication − The system monitors door position
inputs, landing gear door inputs, landing gear position inputs and provides indication of the
position status of airplane doors and landing gear.
· WeightOnWheels
indication − The system monitors landing gear strut compression (sensor
input) and provides indication of the air or ground status of the airplane. WeightOnWheel
sensors on each landing gear assembly report to the LGECU and are divided into two
classifications, WOW 1 and WOW 2 inputs. In addition, the system monitors its own circuitry
and provides fault information to the central airplane information maintenance system or
CAIMS and/or EICAS system.
The LGECU is divided into two subsystems
which provide control and indication to the landing gear
system.
Subsystem
A functions include:
· WOW #1 (WOW sensor input logic).
· Landing gear control and secondary position indication.
· Landing gear door control.
Subsystem
B functions include:
· WOW #2 (WOW sensor input logic).
· Landing gear primary position indication.
· Landing gear door indication.
· Fuselage door Status.
LANDING GEAR
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
15−10−10
LGECU CONTROL SCHEMATIC
EICAS
LANDING
GEAR
AND GEAR
DOOR
CONTROL
WOW
GEAR UP
AND
DOWNLOCK
BITE
(BuiltInTest)
BACKUP
DOWNLOCK
INDICATION
PRIMARY
DOWNLOCK
INDICATION
WOW DOORS
AND
DOWNLOCK
BITE
(BuiltInTest)
SUBSYSTEM
A
LANDING GEAR CONTROL
LANDING GEAR UP INDICATION
(Primary)
LANDING GEAR UNSAFE
INDICATION (Primary)
LANDING GEAR DOWN
INDICATION (Secondary)
DOOR INDICATION
LANDING GEAR IN TRANSITION
INDICATION (Primary)
SUBSYSTEM
B
LANDING GEAR DOWN
INDICATION (primary)
DOOR INDICATION (Fuselage)
LANDING GEAR IN TRANSITION
INDICATION (Secondary)
LANDING GEAR UP INDICATION
(Secondary)
LANDING GEAR UNSAFE
INDICATION (Secondary)
SUBSYSTEM
A SUBSYSTEM
B
GF1510_008
LANDING GEAR
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
15−10−11
LANDING GEAR CONTROL SYSTEM
The landing gear control panel is located on the centre pedestal. The landing gear control handle is
located in the centre of the control panel and is equipped with a solenoid lock which prevents
inadvertent up selection with the airplane on the ground (WOW) signal. In the event of a solenoid
lock malfunction (in flight), a downlock release switch (DN LCK REL) on the landing gear control
panel permits up selection of the handle by overriding the solenoid lock.
LANDING GEAR CONTROL PANEL
DOWN LOCK RELEASE
(Spring loaded, solenoid activated)
Select and hold in the down position to manually override
the control lever solenoid locking mechanism.
HORN MUTED Switch
Mutes the landing gear warning horn for certain
airplane configurations. The "MUTED" white
legend will display when the switch is selected.
NOSE WHEEL
STEERING Switch
ARMED − Circuit is
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Bombardier_Global_000-Landing_Gear(4)
