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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 41, Jul 08, 2004
CSP 700−6
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 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
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
set up for a command
input on the ground.
OFF − Nose wheel
steering will revert to
the freecaster
mode
of operation.
LANDING GEAR
Handle
Controls retraction and
extension of the landing
gear by sending the
command signal to the
LGECU.
UP− Handle must be
pulled out to be moved to
the UP position to retract
the landing gear.
DN − Handle must be
pulled out to be moved to
the DN position to extend
the landing gear.
GF1510_009
NOSE STEER LDG GEAR
HORN PILOT
EVENT
MUTED
LANDING GEAR INDICATION
In flight, the landing gear position indication (pop up display) is removed from EICAS 30 seconds
after all landing gear and slats/flaps indicate up, and no system faults (example: gear, spoilers,
brakes, slat/flap) exist.
Gear Position (Flight Controls) PopUp
Up, down and in transit indication is displayed on the
EICAS primary page.
The pop−up display will appear when the airplane is
configured to any of the following:
Gear selected down.
Slat/flap selection.
Flight spoilers extended.
GF1510_010
GEAR
OUT
30
DN DN DN
ND
STAB
NU
NL RUDDER
LWD RWD
NR
TRIMS
7.2
AIL
LANDING GEAR
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
15−10−12
LANDING GEAR POSITION AND WARNING SYSTEM
The status of the landing gears and landing gear bay doors is determined by the LGECU using inputs
from various proximity sensors. The resulting output is sent to EICAS which monitors the condition
and position display of each system.
　
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