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FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
ELECTRICAL LOGIC
AC BUS 3
SHUT-OFF
FIRE PULL
HANDLE
P
OW
OW Relief Valve
TO
AIRPLANE
SYSTEMS
1A
Filter
S S
Electrical input
Check valve
indicates
direction
of flow
ITEM
Pressure
switches
Pressure
transducer
OPERATES
PSI display to
EICAS
Pump failure
Display to
EICAS
DIGITAL
READOUT
LEGEND
EICAS
DC EMER BUS
GF1310_012a
AC POWER CENTRE
RESERVOIR
DC POWER
PRESSURE MANIFOLD
CENTRE
PSI
3000
ON
OFF
AUTO
1B
CLOSED
DISCH
PULL
1 2
HYDRAULICS
Rev 8, Jan 05, 2006 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−11
HYDRAULIC SYSTEM 2 SCHEMATIC
AC
PUMP
2B
RIGHT ENGINE
DRIVEN PUMP
M
FIREWALL
VALVE
SHUT−OFF
HEAT EXCHANGER
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
AC POWER CENTER
AC BUS 2
P
OW
TO
AIRPLANE
SYSTEMS
2A
S S
DIGITAL
READOUT
EICAS
DC EMER BUS
GF1310_013a
ELECTRICAL LOGIC
RESERVOIR
DC POWER
CENTER
PRESSURE MANIFOLD
FIRE PULL
HANDLE
PSI
3000
CASE DRAIN FLUID
CLOSED
DISCH
PULL
1 2
ON
OFF
AUTO
2B
System pressure
Suction pressure
OW Relief Valve
Filter
Electrical input
Check valve
indicates
direction
of flow
ITEM
Pressure
switches
Pressure
transducer
OPERATES
PSI display to
EICAS
Pump failure
Display to
EICAS
LEGEND
HYDRAULICS
Flight Crew Operating Manual Rev 8, Jan 05, 2006
CSP 700−5000−6
Volume 2
13−10−12
HYDRAULIC SYSTEM 3
System 3 includes a reservoir, ACMPs 3A and 3B, RAT pump, manifold with pressure, return and
case drain filters, hydraulic shutoff valve, heat exchanger and ground servicing panel. Hydraulic
overfill bottles for the system are provided and located near system 3 components.
Reservoir
SYSTEM 3 RESERVOIR
DIRECT READING GAUGE
GF1310_014
System 3 reservoir is located in the lower belly fairing. Fluid quantity and temperature transducers
are located on the reservoir and are indicated on the HYDRAULIC synoptic page.
ACMPs 3A and 3B
3A AND 3B PUMPS
MANIFOLD
GF1310_015
The system 3 ACMPs are located in the lower belly fairing. System 3A pump is used as the
primary pump (runs continuously in the ON position) and 3B as the backup pump.
HYDRAULICS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
13−10−13
HYDRAULIC SYSTEM 3 (CONT'D)
Ram Air Turbine (RAT)
In case of an emergency (example: twoengine
failure), the RAT is deployed and will power an
independent hydraulic pump for system 3. Therefore system 3 has three hydraulic pumps
available to power the system.
The RAT hydraulic pump is mounted at the rear of the RAT. It uses system 3 hydraulic fluid for
emergency operations. The RAT operation is described in the ELECTRICAL Chapter 7 of this
manual.
Heat Exchanger
SYSTEM 3
GF1310_016a
HEAT EXCHANGER
The heat exchanger is positioned in the left fuel feed tank. System 3 heat exchanger has the
same function as systems 1 and 2.
Filter manifold
The filter manifold for system 3 is located on the left side of the aft equipment bay and contains all
the features of system 1 and 2. An additional feature is that the RAT pump shares a common
pressure switch with ACMP 3B.
Fluid quantity and temperature transducers are located on the reservoir and are indicated on the
HYDRAULIC synoptic page.
Two pressure switches and a transducer are part of the pressure manifold and are used to provide
EICAS displays for pump failures and loss of system pressure.
Ground Service Panel
The ground service panel for system 3 is located at the left side of the fuselage, aft of the wing
trailing edge.
HYDRAULICS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
13−10−14
HYDRAULIC SYSTEM 3 (CONT'D)
RAT and System 3 Accumulators
SYSTEM 3 RAT ACCUMULATOR
SYSTEM 3 BRAKE ACCUMULATOR
DIRECT
READING
GAUGE
GF1310_017
A RAT accumulator is used to maintain pressure to the reservoir when 3A and 3B ACMPs are
　
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