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HYDRAULICS
HYDRAULIC SYSTEM 1 SCHEMATIC
GX_12_016
Heat Exchanger
FIRE PULL
HANDLE
AC
PUMP
1B
1A
RESERVOIR
Case
Drain Fluid
Firewall
Shutoff
Valve
S
OW
OW
S
S
P
P
3000
PSI
DIGITAL
READOUT
EICAS
TO
AIRPLANE
Check valve indicates SYSTEMS
direction of flow
Electrical input
Filter
Relief valve
System pressure
Suction pressure
ITEM OPERATES
Pressure switches
Pump Failure
Display to EICAS
Pressure transducer PSI display to EICAS
Left Engine- PRESSURE MANIFOLD
Driven Pump
LEGEND
1B
OFF
AUTO
ON
O
AU
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
AC POWER CENTER
ELECTRICAL LOGIC
AC BUS 3
M
DISCH
1 2
LPULL
DC EMER BUS
DC POWER
CENTER
CLOSED
P I LOT T R A I N I N G GU I D E
HYDRAULICS
12-16 For Training Purposes Only
Sept 04
HYDRAULIC SYSTEM 2 SCHEMATIC
GX_12_017
Heat Exchanger
FIRE PULL
HANDLE
AC
PUMP
2 B
2A
RESERVOIR
Case
Drain Fluid
Firewall
Shutoff
Valve
S
OW
S
P
3000
PSI
DIGITAL
READOUT
EICAS
TO
AIRPLANE
SYSTEMS
S
P
ITEM OPERATES
Pressure switches
Pump Failure
Display to EICAS
Pressure transducer PSI display to EICAS
PRESSURE MANIFOLD
Right Engine-
Driven Pump
2B
ON ON
OFF
AUTO
OFF
AUTO
O
AU AU
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
AC POWER CENTER
ELECTRICAL LOGIC
AC BUS 2
M
DISCH
1 2
R
PULL
DC EMER BUS
DC POWER
CENTER
CLOSED
OW
Check valve indicates
direction of flow
Electrical input
Filter
Relief valve
System pressure
Suction pressure
LEGEND
For Training Purposes Only
Sept 04
12-17
P I LOT T R A I N I N G GU I D E
HYDRAULICS
HYDRAULIC SYSTEM 3
System 3 includes a reservoir, ACMPs 3A and 3B, RAT pump, manifold with
pressure, return and case drain filters heat exchanger, and ground servicing panel.
Hydraulic overfill bottles for the system are provided and located near system 3
components.
RESERVOIR
System 3 reservoir is located in the lower belly fairing. Fluid quantity and temperature
transducers are located on the reservoir and their indications are displayed on the
HYDRAULIC synoptic page.
ACMP’S 3A AND 3B
System 3 ACMPs are located in the lower belly fairing. System 3A pump is used as
primary pump (runs continuously in the ON position) and 3B as the backup pump.
GX_12_018
Direct
Reading
Gauge
System 3
Reservoir
GX_12_019
3A and
3B Pumps
Filter
Manifold
P I LOT T R A I N I N G GU I D E
HYDRAULICS
12-18 For Training Purposes Only
Sept 04
RAM AIR TURBINE (RAT)
In case of an emergency (example: dual-engine 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. An additional feature is that the RAT pump shares a
common pressure switch with ACMP 3B. The RAT operation is described in Chapter
6, ELECTRICAL of this manual.
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 in the lower belly fairing of the aircraft, and
contains all the features of system 1 and 2.
Fluid quantity and temperature transducers are located on the reservoir and their
indications are displayed 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.
GX_12_020
System 3
Heat Exchanger
For Training Purposes Only
Sept 04
12-19
P I LOT T R A I N I N G GU I D E
HYDRAULICS
GROUND SERVICE PANEL
The ground service panel for system 3 is located on the left side of the fuselage aft of
the wing trailing edge.
RAT AND SYSTEM 3 ACCUMULATORS
A RAT accumulator is used to maintain pressure to the reservoir when 3A and 3B
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