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Manual Release System handle in the flight compartment.
Each landing gear assembly has twin wheels and tires. The main wheels have
hydraulically powered and electrically actuated carbon brakes, controlled through a
brake-by-wire system. Main landing gear overheat detection is available. Antiskid
protection and automatic braking is provided.
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 antiskid, nosewheel steering indication
and status are also displayed on EICAS and interface with the Central Aircraft
Maintenance Information System (CAIMS) for failure detection and isolation. Brake
temperature monitoring is displayed on the EICAS status display.
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-2 For Training Purposes Only
Sept 04
DESCRIPTION
MAIN LANDING GEAR
Each main landing gear assembly consists of:
• Main fitting
• Trailing arm
• Side brace actuator
• Extension/retraction actuator
• Uplock mechanism
• Oleopneumatic 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 gear is
mechanically locked in the extended position by internal locking side brace actuators.
During normal operation, the uplock and down lock mechanisms are hydraulically
actuated to release the main gear.
Hydraulic System 3 is maintained to the side brace actuators while the gear is
extended. This serves as a secondary safety feature.
For Training Purposes Only
Sept 04
14-3
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
MAIN LANDING GEAR SCHEMATIC
Side Brace
Actuator
Shock Strut
Uplock Roller
(on the pivot of
the main fitting
and trailing arm)
Main Fitting
Extention / Retraction
Actuator
Mechanical Door
Linkage
Trailing Arm
UPLOCK MECHANISM
(AIRFRAME MOUNTED)
Brake
Assembly
Brake Wear
Indicator
(two per assembly)
Hydraulically
Operated Door
Mechanically-
Operated Door
GX_14_001
FWD
FWD
P I LOT T R A I N I N G GU I D E
LANDING GEAR AND BRAKES
14-4 For Training Purposes Only
Sept 04
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 to the outboard
section of 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 (center) 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 can be deployed by the manual release system for ground
maintenance operations 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 GEAR EXTENSION in this chapter.
The main gear doors, sequencing and position sensing, are controlled and
continuously monitored by the LGECU. Any fault or position deviation detected is
displayed on EICAS.
WHEEL ASSEMBLIES
The airplane has four (carbon type) braked main wheels, two per main gear and two
free rolling nose wheels. The main and nose wheels are fitted with tubeless tires. Four
heat sensitive fuse plugs are installed in each main wheel to release excessive air
pressure caused by heat build-up in the wheel/tire assembly.
Two brake wear indicator pins are installed on each brake assembly to provide a visual
indication of brake wear. When the end of the wear indicator pin is flush with the top
of the indicator housing, the brake must be serviced.
NOTE
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