曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
The AUX DCMP is powered by the L ESS bus. There is battery backup for this bus, but the battery size is limited and only powers this DCMP for the last few minutes of flight. The L ESS bus can be powered by the R DC generator or the APU if the L DC generator fails.
In case of total generator failure, the pilot can select the AUX DCMP off until just prior to landing to conserve battery pow-er. The elevators will be in manual reversion, and the rudder will also be in manual reversion if the auxiliary hydraulic sys-tem fails. In addition, roll assist with roll spoilers will be lost. The ailerons are strictly manually controlled through cables and pulleys. Due to the loss of flaps, thrust reversers, and lift dumping devices, the aircraft landing distances will be significantly increased.
May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6
13-01-01 LEFT AND RIGHT HYDRAULIC SYSTEM
DESCRIPTION
The major components of the left and right hydraulic system are: Engine-Driven Pumps (EDPs), DC Motor Pumps (DC-MPs), Firewall Shutoff Valves (SOVs), control valves, fluid reservoirs, and sensors for monitoring and control for each system. The left and right hydraulic systems each have separate fuel/hydraulic fluid heat exchangers in their respective wing fuel tank. With the exception of the EDPs, and heat exchangers, the major components are located in the aft equipment compartment. The EDPs are mounted on the engine accessory gearboxes.
LEFT HYDRAULIC SYSTEM: RIGHT HYDRAULIC SYSTEM: AUX HYDRAULIC SYSTEM:
Multi-functional spoilers (inboard) Ground spoilers (inboard) Rudder (upper PCU) Left thrust reverser Inboard brakes, emergency Nose wheel steering actuator Elevator (inboard PCUs) Alternate FLAPS Landing Gear Multi-functional spoilers (outboard) Ground spoilers (outboard) Rudder (lower PCU) Right thrust reverser Outboard brakes Main landing gear assist actuators Elevator (outboard PCUs) Normal FLAPS supply Power transfer unit Lower Rudder PCU
CFO1301002_003
AUXILIARY SYSTEM
A
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
13-01-02 LEFT AND RIGHT HYDRAULIC SYSTEM (Cont)
COMPONENTS AND OPERATION ENGINE-DRIVEN PUMPS
The left and right hydraulic systems are each powered by an Engine Driven Pump (EDP). It is flange-mounted to the engine gearbox and driven through a splined input shaft. The pumps are a variable-delivery, piston type, that maintain a nominal system pressure of 3000 psi. The EDPs operate any time the engines are turning. Pressure switches located in the pump outflow lines provide low-pressure indications to the flight crew. The discharge, suction and case drains ports of the pump include quick-disconnect fittings and are connected directly to the aircraft systems through hoses. The case drain port is located on the top side of the pump near the mounting flange for maximum case drain cooling of pump components. This location also assures bleeding of air after installation of a new pump. The pump incorporates a solenoid isolation/actuation valve to reduce discharge pressure and torque when energized. During an engine windmill restart, the solenoid will be ac-tivated by the FADEC to depressurize the pump.The left EDP flow and left DCMP flow combines in the left filter manifold. The right EDP flow and right DCMP flow combines in the right filter manifold. The hydraulic fluid is never mixed between the left and right systems.
中国公务机网 www.gongwuji.com
公务机翻译 www.aviation.cn
本文链接地址：庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-液压(3)
|
