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The brake wear indicator pin must be checked with the parking
brakes applied and No. 3 hydraulic system pressurized. It can
also be checked with both systems 2 and 3 pressurized and
normal brakes applied. However, this second method requires
two people to do the check.
For Training Purposes Only
Sept 04
14-5
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
MAIN GEAR/DOOR DOWNLOCK SAFETY PIN
A downlock safety pin is installed at the end of the side brace assembly to secure the
main landing gear in position while on ground. A door locking pin is available for
installation on the inboard door actuator assembly, if required during maintenance
operations.
MAIN LANDING GEAR OVERHEAT DETECTION
The main landing gear overheat detection system consists of single-loop heat sensing
elements, installed in both main landing gear bays. The overheat detection system
continuously monitors the heat sensing elements in the main landing gear area. Any
overheat condition or system fault detected by the monitoring system is annunciated
on EICAS in the form of a main landing gear bay overheat warning message, or main
landing gear overheat fail caution message. Refer to Chapter 9, FIRE PROTECTION
for additional information on main landing gear bay overheat fault and fail messages.
If the main landing gear system detects an overheat condition it will be accompanied
with a warning voice advisory as follows:
The main landing gear overheat detection system and fault conditions may be tested
through the Electrical Management System or EMS in the flight compartment. Refer
to Chapter 7, ELECTRONIC DISPLAY SYSTEM. Test result messages are displayed
on EICAS.
GX_14_002
GROUND
LOCKING
PIN
DOOR
LOCKING
PIN
FWD
REMOVE O BEF
T
RE G FLI H
GX_14_003
“GEAR BAY OVERHEAT”
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-6 For Training Purposes Only
Sept 04
LANDING GEAR BAY OVERHEAT SCHEMATIC
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
GX_14_004
ELECTRICAL
MANAGEMENT
SYSTEM
LH RH
MAIN LANDING GEAR BAY
OVERHEAT DETECTION LOOPS
TO EICAS
FIRE DETECTION/EXTINGUISHING
SYSTEM CONTROL UNIT
OVERHEAT
WARNING
OVERHEAT
DETECTION
FAIL
OVERHEAT
Overheat
Detector
DETECTION
For Training Purposes Only
Sept 04
14-7
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
NOSE LANDING GEAR SCHEMATIC
The nose gear bay is completely enclosed by an aft door, mechanically linked to the
nose gear, and by two hydraulically-actuated forward doors. During normal operation,
the forward doors open only during gear retraction and extension (transit) operation.
The forward doors can be manually opened 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 ensure downlock when the gear is extended. The
GX_14_005
Drag
Brace
Shock
Strut
Retraction
Actuator
Door
Unlock
Steering
Actuators
Torque
Link
Assembly
Door Retraction
Actuator
Aft
Door
Downlock
Nose Landing
Gear Uplock
Uplock Pin
(between Actuators)
Nose Gear
Forward Door
Manual Release
Cable
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-8 For Training Purposes Only
Sept 04
nose gear is actuated by hydraulic system No. 3 to operate the uplocks (gear and door),
downlocks and actuators.
In the event of a hydraulic system failure, a dedicated operating system provides a
means to manually extend (free fall) 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
　
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