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" Left and Right Thrust Levers < 26° Thrust Lever Angle OR
" Flaps > 27°.
If the radio altimeter is inoperative, the “GEAR” voice warning is a mutable condition. The logic resulting in a “GEAR”
voice warning when the radio altimeter is inoperative is:
" Any gear not down and locked AND
" Radio Altimeter invalid AND
" Left and Right Thrust Levers < 26° Thrust Lever Angle AND
" Altitude < 15 000 feet OR
" Airspeed < 170 KIAS AND Flaps < 3°, OR
" Airspeed < 160 KIAS with Flaps < 13°, OR
" Airspeed < 155 KIAS with Flaps > 13°.
Both the mutable and the non-mutable voice warnings are accompanied by the GEAR (W) CAS message and the affected
gear icon(s) turning red. These visual cues will remain and can not be suppressed as long as the conditions triggering the
original warning persist, regardless of whether valid muting command has been applied. When permitted, muting of the
voice warning is accomplished by pressing the Master Warning/Master Caution switch on the glareshield. The warning
automatically resets in the event that the condition no longer exists. The warning will become active again on a subsequent
landing attempt if the logic conditions are met.
The logic driving the mutable and non-mutable warnings are designed to ensure adequate time to either lock the gear
down or perform a go-around.
REV 1
LANDING GEAR
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 15-01-03
PROXIMITY SENSING SYSTEM (Cont)
LANDING GEAR POSITION AND WARNING SYSTEM (Cont)
The PSEU monitors all gear functions. Any deviation from the selected gear configuration or failure of the uplocks or
downlocks is annunciated on the EICAS in the form of visual and aural messages
LANDING GEAR
MAIN LANDING GEAR
DESCRIPTION
The Main Landing Gear (MLG) consists of two shock strut type, trailing link assemblies. The MLG retracts toward the
centerline of the fuselage. The MLG is hydraulically actuated by the left hydraulic system and electrically controlled by
the PSS.
The MLG are hydraulically retracted into the MLG bay, located in the wing underside, by a side brace actuator. This actuator
is a hydraulic piston-cylinder actuator with an internal segmented down locking mechanism. Each gear is held in the
up lock position with a MLG Uplock Assembly.
COMPONENTS AND OPERATION
Each main landing gear assembly consists of:
- Main Landing Door Mechanism
- Main Fitting
- Side Brace Actuator Assembly
- Nitrogen gas/oil filled Shock Strut
- Trailing Arm Assembly
- Axle with Carbon Brake Assemblies
- Dual Wheels
- Uplock Mechanism
- Extension and Retraction actuator
- Auxiliary Extend Assembly
- Electrical Harnesses and Hydraulic Dressings
MAIN GEAR DOOR
The main gear door is mechanically linked to the main landing gear assembly and moves with the gear during extension
and retraction. Each main gear door is attached to the wing structure with two hinges. The main door structure is made from
a clad-aluminum alloy sheet. A nylon door brush is installed on the bottom edge of the door to create a seal between the
tire and fuselage.
MAIN WHEEL BINS
Each main gear assembly retracts inward into wheel bins that are recessed into the main landing gear bay. The wheel bins
isolate the wheels from the main landing gear bays and prevent tire-thrown debris from damaging the equipment located
within the main landing gear bay. Each wheel bin contains a single loop overheat detection wire to provide a CAS warning
should a wheel overheat. The bins can be removed to allow maintenance personnel access to the main landing gear bay.
MAIN LANDING GEAR UPLOCKS AND DOWNLOCKS
The main landing gear is held in the up-and-locked position by mechanical uplocks. With the gear extended, locking mechanisms
in the side-brace keeps lock the gear in the down position. On the ground, locking pins can be inserted into the side
strut actuator.
LANDING GEAR
Volume 2 Flight Crew Operating Manual Sep 13/2004
15-01-04 CSP 100-6 REV 1
LANDING GEAR (Cont)
CFO1501002_001
MECHANICALLY
UPLOCK OPERATED DOOR
MECHANISM
(AIRFRAME
MOUNTED)
BRAKE WEAR INDICATOR
(TWO PER ASSEMBLY)
BRAKE
ASSEMBLY
TRAILING ARM
UPLOCK ROLLER
(ON THE PIVOT OF
THE MAIN FITTING
AND TRAILING ARM)
MAIN
FITTING
SIDE BRACE
ACTUATOR
EXTENSION/
RETRACTION
ACTUATOR
SHOCK STRUT
MECHANICAL
DOOR LINKAGE
LANDING GEAR
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 15-01-05
　
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