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
is tied to the right hydraulic system. The left, right, and auxiliary systems are controlled from the HYDRAULICS panel,
located immediately to the right of the throttle quadrant on the center pedestal. The hydraulic systems normally operates at
3000 psi and uses Fire Resistant Phosphate Ester based MIL-H-5440 Type II fluid. The left and right hydraulic systems are
both powered by Engine-Driven Pumps (EDPs) which are backed up by a DC Motor-driven Pumps (DCMPs). The left and
right hydraulic systems DCMPs are powered by the electrical DC bus supplied by the generator on the engine opposite the
engine which drives the EDP. Thus, hydraulic power is provided for the left and right systems after any single engine failure.
After the loss of the left and right hydraulic systems, the lower rudder PCU will be powered by the AUX hydraulic
system.
The L DCMP is powered by the R MAIN DC bus. There is no battery backup for the R MAIN DC bus. If the right DC
generator fails, the R MAIN DC bus can be powered by the L DC generator or the APU.
The R DCMP is powered by the L ESS bus. The bus can be powered by the right dc generator or the APU if the left DC
generator fails. If no generators are operational, the R DCMP will only automatically start if the pilot selects the flaps to a
non-zero position. If only one generator is operational on the airplane, then only one of the L or R DCMPs is operational,
(one DCMP is load shed from the good hydraulic system with the R DCMP taking priority over the left DCMP if both EDPs
are failed). AUX DCMP is not load shed for single generator operation.
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 power.
The elevators will be in manual reversion, and the rudder will also be in manual reversion if the auxiliary hydraulic system
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.
REV 2
HYDRAULICS
Volume 2 Flight Crew Operating Manual Sep 13/2004
13-01-02 CSP 100-6 REV 1
LEFT AND RIGHT HYDRAULIC SYSTEM
DESCRIPTION
The major components of the left and right hydraulic system are: Engine-Driven Pumps (EDPs), DC Motor Pumps (DCMPs),
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) Multi-functional spoilers (outboard) Lower Rudder PCU
Ground spoilers (inboard) Ground spoilers (outboard)
Rudder (upper PCU) Rudder (lower PCU)
Left thrust reverser Right thrust reverser
Inboard brakes, emergency Outboard brakes
Nose wheel steering actuator Main landing gear assist actuators
Elevator (inboard PCUs) Elevator (outboard PCUs)
Alternate FLAPS Normal FLAPS supply
Landing Gear Power transfer unit
1
2
A
LANDING GEAR,
STEERING AND
BRAKING
RUDDER
HEAT EXCHANGERS
FLAPS
GROUND
SPOILERS
LEFT
DCMP LEFT
EDP
THRUST
REVERSERS
RIGHT
DCMP
RIGHT
EDP
PTU AUXILIARY
DCMP
LEGEND
LEFT HYDRAULIC SYSTEM
RIGHT HYDRAULIC SYSTEM
AUXILIARY SYSTEM
1
2
2 1
1
1
2
1
2
2
1
1
2
2
1
1
1
2
MULTIFUNCTIONAL
SPOILERS
1
2
CFO1301002_003
2,A
HYDRAULICS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 13-01-03
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
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Bombardier_Challenger_Global_00-Hydraulics(2)
