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If the main landing gear system detects an overheat condition, it will be accompanied by a warning
voice advisory as follows:
"GEAR BAY OVERHEAT"
The main landing gear overheat detection system and fault conditions may be tested through the
Electrical Management System (EMS) in the flight compartment (refer to AURAL/VISUAL WARNING
SYSTEM Chapter). Test result messages are displayed on EICAS.
LANDING GEAR
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
15−10−4
LANDING GEAR BAY OVERHEAT SCHEMATIC
FIRE DETECTION/EXTINGUISHING
OVERHEAT
WARNING
OVERHEAT
DETECTION
FAIL
TO
EICAS
LH RH
MAIN LANDING GEAR BAY
OVERHEAT DETECTION LOOPS
OVERHEAT
DETECTION
ELECTRICAL
MANAGEMENT
SYSTEM
OVERHEAT
DETECTOR
SYSTEM CONTROL UNIT
GF1510_004
LANDING GEAR
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
15−10−5
NOSE LANDING GEAR ASSEMBLY
The nose gear assembly consists of:
· Oleopneumatic
shock strut (main fitting).
· Hydraulic extension/retraction actuator.
· Uplock mechanism.
· Drag brace including a downlock mechanism.
· Set of nose gear doors and linkages.
The nose gear bay is completely enclosed by an aft door mechanically linked to the nose gear and
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 of the nose gear is achieved through a mechanical locking device. Two
downlock assist springs mounted on the drag brace assist nose gear extension. System No. 3
hydraulic pressure to the nose gear is maintained while in extended position.
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 2A, Apr 11, 2005
CSP 700−5000−6
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 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
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 2A, Apr 11, 2005
CSP 700−5000−6
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
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Bombardier_Global_000-Landing_Gear(3)
