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Hydraulic pump 3A normally runs continuously while pump 3B is used as an essential pump for
takeoff,
approach, landing and in support of the primary pump 3A in the event of failure.
Emergency Hydraulic Power
In the event that all normal electrical power is lost, a Ram Air Turbine (RAT) is deployed and will
power an independent hydraulic pump for system 3.
Hydraulic Accumulators
The RAT uses an accumulator to maintain pressure at the reservoir for system 3 hydraulic
operation. Two additional hydraulic accumulators are installed on the airplane and are used by the
brake control system. One is used for brake system 2 and the other for brake system 3 operation.
HYDRAULICS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−1
DISTRIBUTION TABLE SCHEMATIC
NO. 1 SYSTEM NO. 3 SYSTEM NO. 2 SYSTEM
AC
MOTOR
PUMP
ENGINE
DRIVEN
PUMP
RUDDER RUDDER
LEFT AND
RIGHT AILERON
RIGHT
LEFT AND RIGHT
RIGHT ELEVATOR
LEFT AND RIGHT
OUTBOARD
BRAKES
WHEEL
STEERING
(2 A) (2 B)
AC
MOTOR
PUMP
(3 B)
AC
MOTOR
PUMP
(3 A)
AC
MOTOR
PUMP
(1 B)
LEFT AND RIGHT
GROUND SPOILERS
PARK/EMER
LANDING GEAR
NOSE
AILERON
ELEVATOR
DOORS
GEAR
MULTIFUNCTION
LEFT AND RIGHT
MULTIFUNCTION
GEAR
INBOARD AND
BRAKES
LEFT
REVERSER
RUDDER
LEFT
AILERON
LEFT
ELEVATOR
ENGINE
DRIVEN
PUMP
RIGHT
REVERSER
LEFT AND RIGHT
GROUND SPOILERS
(1 A)
RAT
PUMP
MAIN LANDING
SPOILERS
SPOILERS
GF1310_001
HYDRAULICS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
13−10−2
HYDRAULIC SYSTEM INDICATION
The HYDRAULIC synoptic page provides an overview of normal system status and RAT deployment
as represented below.
Hydraulic reservoirs, valve positioning and pump operations are pictorially displayed. System
temperatures, fluid quantities and pressures are represented digitally. Flow lines connect
components and legends display system status.
HYDRAULIC SYNOPTIC PAGE
GF1310_002
70°C 68°C 70°C
HYDRAULIC
1B 3A 3B 2B
INBD
BRAKES
2900
PSI
OUTBD
BRAKES
NORM
PSI PSI PSI
2950 3000 2950
RUD
ELEV R
AIL R
FLT SPLRS
GEAR
REVERSER R
RUD
L ELEV R
L AIL R
GND SPLRS
GEAR
NOSE STEER
RUD
L ELEV
L AIL
FLT SPLRS
GND SPLRS
L REVERSER
PARK/EMER BRAKE
1A 2A
62 % 64 % 62 %
64 %
3A RAT 3B
PSI
3000
Reservoir
AC Motor
Pump Status
Engine Driven
Pump Status
Hydraulic Fluid
Temperature
Readout
Firewall Shutoff
Valve Position
Hydraulic
Pressure
Readout
Hydraulic Fluid
Quantity
Readout
RAT Deployed
HYDRAULIC
SYSTEM #3
The synoptic page and hydraulic panel control switches are detailed later in this Chapter.
HYDRAULIC CONTROL PANEL
GF1310_003
HYDRAULIC
ON
OFF
AUTO
ON
OFF
ON
OFF
AUTO
ON
OFF
AUTO
1B 3A 3B 2B
The hydraulic control panel is located on the overhead panel in the flight compartment. There are
four switches which control electrically operated pumps for each system.
HYDRAULICS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−3
SYSTEMS OVERVIEW SCHEMATIC
GF1310_004
CENTRAL HYDRAULIC
SYSTEM COMPONENTS
FILTERS
RESERVOIR
RELIEF VALVE
PRESS/TEMP SENSING
LEGEND
RAT PUMP
AILERON
MULTIFUNCTIONAL
SPOILERS
ELEVATOR
HEAT EXCHANGER
LANDING GEAR,
STEERING AND BRAKES
RUDDER
REVERSER
GROUND SPOILER
SYSTEM 3 RAT (FORWARD)
SYSTEM 2 BRAKE
ACCUMULATOR
SYSTEM 3 BRAKE (AFT)
ACCUMULATORS
System pressure 2
Engine driven pump
System pressure 1 AC motor pump RAT hydraulic pump
System pressure 3
HYDRAULICS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
13−10−4
HYDRAULIC SYSTEM 1 AND 2
Each system includes an EDP, reservoir, ACMP, manifolds with pressure, return and case drain
filters, hydraulic shutoff valve, heat exchanger and ground servicing panel. Hydraulic overfill bottles
　
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