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The main gear hydraulically-actuated 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 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 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. It can also be checked with both systems 2 and 3 pressurized and normal brakes applied. However, this second method requires two people to do the check. Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2 LANDING GEAR 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, if required during maintenance operations. DOOR LOCKING PIN GF1510_002 GROUND LOCKING PIN 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. Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005 LANDING GEAR LANDING GEAR BAY OVERHEAT SCHEMATIC FIRE DETECTION/EXTINGUISHING SYSTEM CONTROL UNIT OVERHEAT WARNING OVERHEAT DETECTION FAIL OVERHEAT DETECTION LH RH MAIN LANDING GEAR BAY OVERHEAT DETECTION LOOPS OVERHEAT DETECTOR TO 中国公务机网 www.gongwuji.com 公务机翻译 www.aviation.cn 本文链接地址：庞巴迪环球5000公务机机组操作手册 Bombardier Global-起落架(3) |
