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MAIN GEAR
ACTUATORS AND
INBOARD BRAKES
GROUND
SPOILERS
No. 3B AC
MOTOR PUMP
LEFT
AILERON
MULTIFUNCTION
SPOILERS
LEFT
THRUST
REVERSER
No. 1A
ENGINE
DRIVEN
PUMP
No. 2A
ENGINE
DRIVEN
PUMP
No. 2B
AC MOTOR
PUMP
Vol. 1 14--10--3
HYDRAULIC POWER
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Hydraulic Systems Diagram
Figure 14---10---2
LEFT AILERON
RUDDER
LEFT AND RIGHT
ELEVATORS
LEFT AND RIGHT
OUTBOARD FLIGHT
SPOILERS
LEFT AND RIGHT
OUTBOARD
SPOILERONS
NO. 1 SYSTEM
AC MOTOR
PUMP (1B)
ENGINE
DRIVEN
PUMP (1A)
LEFT AND RIGHT
OUTBOARD
GROUND SPOILERS
LEFT
THRUST REVERSER
LEFT AND RIGHT
AILERON
RUDDER
LEFT AND RIGHT
ELEVATORS
LEFT AND RIGHT
INBOARD BRAKES
MAIN AND NOSE
LANDING GEAR
LEFT AND RIGHT
INBOARD
GROUND SPOILERS
NOSEWHEEL
STEERING
RIGHT AILERON
RUDDER
LEFT AND RIGHT
ELEVATORS
LEFT AND RIGHT
INBOARD
SPOILERONS
LEFT AND RIGHT
MLG AND NLG ASSIST
ACTUATORS
LEFT AND RIGHT
INBOARD FLIGHT
SPOILERS
RIGHT
THRUST REVERSER
LEFT AND RIGHT
OUTBOARD BRAKES
NO. 3 SYSTEM
AC MOTOR
PUMP (3B)
NO. 2 SYSTEM
AC MOTOR
PUMP (2B)
ENGINE
DRIVEN
PUMP (2A)
AC MOTOR
PUMP (3A)
Vol. 1 14--10--4
HYDRAULIC POWER
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 14--20--1
HYDRAULIC POWER
Systems 1 and 2 REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. HYDRAULIC SYSTEMS 1 AND 2
Hydraulic systems (1 and 2) are identical in construction and operation with each system
consisting of an:
S Engine driven pump (EDP)
S AC motor pump (ACMP)
S Shutoff valve
S Reservoir
S Accumulator
S Overflow container
S Pressure and return manifolds
S Case drain filters
S Ground servicing panel
Both systems share a ram air heat exchanger for fluid cooling. Fluid from each system is not
mixed with the other system as it passes through the heat exchanger. A fan within the heat
exchanger assists in cooling the hydraulic fluid when the aircraft is on the ground.
Each system is monitored by:
S Temperature and pressure switches
S Temperature and pressure transducers
S Quantity transducers and indicating gauges.
NOTE
Figure 14--20--1 represents No. 1 or No. 2 hydraulic
system.
Vol. 1 14--20--2
HYDRAULIC POWER
Systems 1 and 2 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Hydraulic System ( No. 1/2) --- Schematic
Figure 14---20---1
S S
P
T
S
T
NITROGEN CHARGING VALVE
AND GUAGE
PRESSURE SUCTION
FILL
SYSTEM
RETURN
TO HYDRAULIC
SERVICES
ACCUMULATOR
CHECK
VALVE
PRESSURE
MANIFOLD
SAMPLE PORT
(PLUGGED)
CHECK
VALVE
RETURN
MANIFOLD
BLEED/RELIEF
VALVE
OVERFLOW
CONTAINER
SHUT--OFF
VALVE
QUICK
DISCONNECT
ENGINE
DRIVEN
PUMP
CASE DRAIN
FILTER
AC MOTOR
PUMP
TEMP
TRANSDUCER
RESERVOIR
HEAT
EX--
CHANGER
PRESSURE
SWITCH
CASE DRAIN
FILTER
PRESSURE
RELIEF
VALVE
PRESSURE
SWITCH
PRESSURE
TRANSDUCER
CHECK
VALVE
SUCTION
PRESSURE
RETURN
CASE DRAIN
DRAIN TO OVERFLOW
FILL
P
RETURN
FILTER
GROUND SERVICE
PANEL
PRESSURE
FILTER
TEMP
SWITCH
BRAKE RETURN
(SYSTEM 2 ONLY)
Vol. 1 14--20--3
HYDRAULIC POWER
Systems 1 and 2 REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. Engine Driven Pumps
EDP 1A and 2A draw fluid from their respective reservoirs through firewall shutoff
valves. Fluid is pumped to the applicable pressure manifold, filtered and distributed to
the airplane’s hydraulically actuated components.
B. AC Motor Pumps
AC motor pump 1B is powered from AC bus 2 and AC motor pump 2B is powered from
AC bus 1. Each AC motor pump is controlled by a separate toggle switch on the
hydraulic pump control panel located on the overhead panel in the flight compartment.
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