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The AURAL — GEAR is non-mutable if the following conditions are met: ó Any of the gear not down and locked AND ó Radio Altimeter valid and Radio Altimeter < 500 feet AND ó Left and Right Thrust Levers < 26° Thrust Lever Angle OR ó 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:
ó
Any gear not down and locked AND
ó Radio Altimeter invalid AND
ó
Left and Right Thrust Levers < 26° Thrust Lever Angle AND
ó Altitude < 15 000 feet OR
ó Airspeed < 170 KIAS AND Flaps < 3°, OR
ó Airspeed < 160 KIAS with Flaps < 13°, OR
ó 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 subse-quent 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.
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
15-01-02 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 actu-ator 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
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