曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)者

15−10−2
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 gear extension in this Chapter.
The main gear hydraulicallyactuated
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 fusible
plugs are installed in each main wheel to release excessive air pressure caused by heat buildup
in the wheel/tire assembly.
Two brake wear indicator pins are installed on each brake assembly to provide a visual indication
of brake wear remaining in the disc stack. When the end of the wear indicator pin is flush with the
top of the indicator housing, the brake must be serviced.
NOTE
The brake wear indicator pins must be checked with the parking
brake applied and No. 2 and No. 3 hydraulic systems pressurized.
LANDING GEAR
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
15−10−3
MAIN GEAR/DOOR DOWNLOCK SAFETY PINS
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 installed on the inboard door actuator
assembly.
DOOR LOCKING PIN
GROUND LOCKING PIN
GF1510_002
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 FIRE
PROTECTION Chapter 9 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 by a warning
voice advisory as follows:
"GEAR BAY OVERHEAT"
The main landing gear overheat detection system and fault conditions may be tested through the
Electrical Management System (EMS) in the flight compartment (refer to AURAL/VISUAL WARNING
SYSTEM Chapter). Test result messages are displayed on EICAS.
LANDING GEAR
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
15−10−4
LANDING GEAR BAY OVERHEAT SCHEMATIC
FIRE DETECTION/EXTINGUISHING
OVERHEAT
WARNING
OVERHEAT
DETECTION
FAIL
TO
EICAS
LH RH
MAIN LANDING GEAR BAY
OVERHEAT DETECTION LOOPS
OVERHEAT
DETECTION
ELECTRICAL
MANAGEMENT
SYSTEM
OVERHEAT
DETECTOR
SYSTEM CONTROL UNIT
GF1510_004
LANDING GEAR
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
15−10−5
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.
The nose gear bay is completely enclosed by an aft door mechanically linked to the nose gear and
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰(zhàn)者手冊7(77)