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Gear Warning Horn “MUTED” Switch 15−10−15
Retraction and Extension System 15−10−16
Landing Gear Retraction 15−10−16
Landing Gear Extension 15−10−17
Landing Gear Manual Release Handle 15−10−18
Manual Landing Gear Extension 15−10−18
Manual Release Sequence 15−10−19
Landing Gear Manual Release Schematic 15−10−20
Brake Control System 15−10−21
Park/Emergency Brake 15−10−22
Park/Emergency Brake Takeoff
Configuration 15−10−23
Brake Control Schematic 15−10−23
Autobrake System 15−10−24
Autobrake Panel 15−10−24
LANDING GEAR
TABLE OF CONTENTS
CHAPTER 15
15−00−1
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
15−00−1
Page
TABLE OF CONTENTS
DESCRIPTION
BCU Interface Schematic 15−10−25
Brake Temperature Monitoring System 15−10−26
Brake Temperature Monitoring Schematic 15−10−26
Nose Wheel Steering System 15−10−27
Nose Wheel Steering Schematic 15−10−28
EICAS Messages 15−10−29
EMS CIRCUIT PROTECTION
CB − LDG Gear System 15−20−1
LANDING GEAR
TABLE OF CONTENTS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
15−00−2
Page
GENERAL
The landing gear system is a retractable tricycle type consisting of two main landing gear assemblies
and a steerable nose landing gear assembly. Each assembly is equipped with a conventional
oleopneumatic
shock strut. On the ground, all three landing gear assemblies are secured with gear
locking pins. The landing gear bays fully enclose the gears when retracted.
Normal extension and retraction is electrically controlled by the Landing Gear Electronic Control Unit
(LGECU) and hydraulically operated by systems 2 and 3.
Emergency extension of the landing gear system is enabled through a manual release handle
located 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 brakebywire
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 WeightOnWheels
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 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.
· 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 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.
LANDING GEAR
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
15−10−1
MAIN LANDING GEAR SCHEMATIC
UPLOCK
MECHANISM
(AIRFRAME
MOUNTED)
EXTENSION/RETRACTION
SIDE BRACE
SHOCK STRUT
BRAKE
ASSEMBLY
TRAILING ARM
MAIN FITTING
HYDRAULICALLY
MECHANICALLY
OPERATED
DOOR
OPERATED
DOOR
FORWARD VIEW
MECHANICAL DOOR
ACTUATOR
LINKAGE
BRAKE WEAR
INDICATOR
(TWO PER
ASSEMBLY)
UPLOCK ROLLER
(ON THE PIVOT OF
THE MAIN FITTING
AND TRAILING ARM)
ACTUATOR
REARWARD VIEW
GF1510_001
LANDING GEAR
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
　
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