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The main and nose landing gear assemblies use proximity sensors to provide air and ground sensing. This is accomplished by two sensors (referred to as Weight-On-Wheels or WOW) on each assembly.
All hydraulically actuated doors, uplocks, downlocks and nose shock strut (centering) use sensors to determine their position for gear operation.
Landing gear status and position is visually displayed on EICAS and aurally annunciated in the flight compartment. The anti-skid, nosewheel steering indication and status are also displayed on EICAS and interface with the central aircraft maintenance information system or CAIMS for failure detection and isolation. Brake temperature monitoring is displayed on the EICAS status display.
MAIN LANDING GEAR ASSEMBLY
Each main landing gear assembly consists of:
.
Main fitting.
.
Trailing arm.
.
Side brace actuator.
.
Extension/retraction actuator.
.
Uplock mechanism.
.
Oleo-pneumatic shock strut.
.
Door linkages.
Each main gear retracts inward and up into the main landing gear bay and is mechanically held in the retracted position by an uplock mechanism. The gears are mechanically locked in the extended position by internal locking side brace actuators. During normal operation, the uplock and downlock mechanisms are hydraulically actuated to release the main gears.
Hydraulic System 3 is maintained to the side brace actuators while the gear is extented. This serves as a secondary safety feature.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
LANDING GEAR
MAIN LANDING GEAR SCHEMATIC
UPLOCK MECHANISM (AIRFRAME MOUNTED)
MECHANICALLY
OPERATED
DOOR
FORWARD VIEW
EXTENSION/RETRACTION
ACTUATOR HYDRAULICALLY OPERATED DOOR
SIDE BRACEMAIN FITTING ACTUATOR
MECHANICAL DOOR LINKAGE SHOCK STRUT
UPLOCK ROLLER (ON THE PIVOT OF THE MAIN FITTING AND TRAILING ARM)
TRAILING ARM
BRAKE ASSEMBLY
BRAKE WEAR INDICATOR REARWARD VIEW (TWO PER ASSEMBLY)
GF1510_001
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
LANDING GEAR
MAIN LANDING GEAR SCHEMATIC (CONT'D)
The main landing gear is completely enclosed by four doors. Two outboard doors (one for each main) hinged to the belly fairing are mechanically linked outboard on each main gear assembly and positioned to the open and closed position with each main gear operation. Two inboard doors (one for each main) are hinged to the keel (centre) beam of the airplane. The inboard doors are hydraulically operated to open on selection of gear retraction or extension and to close when the gear is fully up or down. The inboard doors are manually deployed by the manual release system and can be opened for ground maintenance operation when required.
Hydraulic system No. 3 is used to release all gear and door uplocks, downlocks, nose gear actuator, (extension and retraction) and main gear side brace actuators during normal extension. The main gear extension/retraction actuators (used to raise and lower the main gear) are powered by hydraulic system No. 2 and will also assist gear extension for manual gear operation. A manual extension of the gear can be achieved by pulling the landing gear manual release handle located on the pedestal in the flight compartment. For operation, refer to MANUAL LANDING GEAR EXTENSION in this Chapter.
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