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DESCRIPTION General 15−10−1 Main Landing Gear Assembly 15−10−1 Main Landing Gear Schematic 15−10−2 Wheel Assemblies 15−10−3 Main Gear/Door Downlock Safety Pins 15−10−4 Main Landing Gear Overheat Detection 15−10−4 Landing Gear Bay Overheat Schematic 15−10−5 Nose Landing Gear Assembly 15−10−6 Nose Landing Gear Schematic 15−10−7 Nose Gear Downlock Safety Pin 15−10−8 Landing Gear Electronic Control Unit (LGECU) 15−10−9 LGECU System Schematic 15−10−9 LGECU Control 15−10−10 LGECU Control Schematic 15−10−11 Landing Gear Control System 15−10−12 Landing Gear Control Panel 15−10−12 Landing Gear Indication 15−10−12 Landing Gear Position and Warning System 15−10−13 Landing Configuration Warning 15−10−14 Gear Warning 15−10−14 Landing Gear Warning Logic 15−10−15 Gear Warning Horn “MUTED” Switch 15−10−17 Retraction and Extension System 15−10−18 Landing Gear Retraction 15−10−18 Landing Gear Extension 15−10−19 Landing Gear Manual Release Handle 15−10−20 Manual Landing Gear Extension 15−10−20 Manual Release Sequence 15−10−21 Landing Gear Manual Release Schematic 15−10−22 Brake Control System 15−10−23 Park/Emergency Brake 15−10−24 Park/Emergency Brake Takeoff Configuration 15−10−25 Brake Control Schematic 15−10−25 LANDING GEAR TABLE OF CONTENTS CHAPTER 15 15−00−1 Rev 2A, Apr 11, 2005 Flight Crew Operating Manual CSP 700−5000−6 Volume 2 15−00−1 Page TABLE OF CONTENTS DESCRIPTION Autobrake System 15−10−26 Autobrake Panel 15−10−26 BCU Interface Schematic 15−10−27 Brake Temperature Monitoring System 15−10−28 Brake Temperature Monitoring Schematic 15−10−28 Nose Wheel Steering System 15−10−29 Nose Wheel Steering Schematic 15−10−30 EICAS Messages 15−10−31 EMS CIRCUIT PROTECTION CB − LDG Gear System 15−20−1 LANDING GEAR TABLE OF CONTENTS Flight Crew Operating Manual Rev 2A, Apr 11, 2005 CSP 700−5000−6 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 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：Bombardier_Global_000-Landing_Gear
