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by two forward doors hydraulically actuated by a mechanism located in the nose landing gear bay
area. During normal operation the forward doors open only during gear retraction and extension
(transit) operation. The forward doors are manually deployed by the manual release system and can
be opened for ground maintenance operation when required. The aft door is mechanically linked to
the nose gear and positioned to the open and closed position with each main gear operation.
The nose gear retracts forward into the nose bay area and is held in the retracted position by an
uplock mechanism. During normal operation, a downlock actuator and assist springs within the drag
brace ensures downlock when the gear is extended. The nose gear is actuated by hydraulic system
No. 3 to operate the uplocks (gear and door), downlocks and actuators.
In the event of an hydraulic system failure, a dedicated operating system provides a means to
manually extend (freefall) the gear. As with the main gear, emergency extension of the nose gear is
achieved by pulling the same landing gear manual release handle located on the pedestal in the
flight compartment. Downlock is ensured by two downlock assist springs mounted on the drag brace.
The nose hydraulically actuated doors, gear sequencing and position sensing are controlled and
continuously monitored by the LGECU. Any fault or position deviation detected is annunciated on
EICAS.
LANDING GEAR
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
15−10−6
NOSE LANDING GEAR SCHEMATIC
SHOCK STRUT
NOSE GEAR
DOWNLOCK
DRAG BRACE
DOOR RETRACTION
MANUAL RELEASE
NOSE LANDING DOOR
GEAR UPLOCK
RETRACTION
AFT
ACTUATOR
UPLOCK
ASSEMBLY
ACTUATOR
DOOR
FORWARD DOOR
UPLOCK PIN
STEERING ACTUATOR
(BETWEEN ACTUATORS)
TORQUE LINKS
TOWING)
(DISCONNECT FOR
GF1510_005
LANDING GEAR
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
15−10−7
NOSE GEAR DOWNLOCK SAFETY PIN
A downlock safety pin is installed within the drag brace assembly to secure the nose landing gear in
position while on ground.
DOWNLOCK
ASSIST SPRING
GROUND
LOCKING
PIN
GF1510_006
LANDING GEAR
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
15−10−8
LANDING GEAR ELECTRONIC CONTROL UNIT (LGECU)
The Landing Gear Electronic Control Unit (LGECU) consists of two subsystems
which perform:
· All landing gear control and indication, including WOW.
· Landing gear and landing gear door operations.
· Control, indication and fuselage door status functions (refer to Airplane General Chapter 1 for
fuselage door indications).
LGECU SYSTEM SCHEMATIC
MAIN GEAR ASSEMBLY
NOSE GEAR ASSEMBLY
CONTROL SEQUENCING
GEAR POSITION
AND
LOCKED INDICATION
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 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
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
　
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