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HYDRAULIC SYSTEM 3 SCHEMATIC
AC BUS 4 AC BUS 1
HEAT EXCHANGER
FLAPS OR SLATS OUT OF ZERO
PRIMARY PUMP PRESSURE SWITCH
ELECTRICAL LOGIC
P
TO
AIRPLANE
SYSTEMS
S S
PUMP
AC
3B
PRESSURE MANIFOLD
OW
ITEM
Pressure
switches
Pressure
transducer
OPERATES
S
P PSI display to
EICAS
Pump failure
Display to
EICAS
GF1310_019
PUMP
AC
3A
RESERVOIR
AC POWER CENTRE
DIGITAL
READOUT
EICAS
PSI
3000
System pressure
Suction pressure
CASE DRAIN FLUID
OW Relief Valve
Filter
Electrical input
Check valve
indicates
direction
of flow
LEGEND
HYDRAULIC
ON
OFF
ON
OFF
AUTO
3A 3B
HYDRAULICS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
13−10−18
RAT DEPLOYMENT HYDRAULIC SCHEMATIC
OW
HEAT EXCHANGER
P
TO
AIRPLANE
SYSTEMS
S S
PUMP
AC
3A
AC
3B
PUMP
AC POWER CENTRE
AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4
AIR/GROUND SENSING
AIRPLANE CONFIGURATION
RAT
RAT
PUMP
ITEM
Pressure
switches
Pressure
transducer
OPERATES
S
P PSI display to
EICAS
Pump failure
Display to
EICAS
GF1310_020
ACCUMULATOR
PRESSURE MANIFOLD
RESERVOIR
NO POWER ON ALL AC BUSSES
DIGITAL
READOUT
EICAS
PSI
3000
System pressure
Suction pressure
CASE DRAIN FLUID
OW Relief Valve
Filter
Electrical input
Check valve
indicates
direction
of flow
LEGEND
HYDRAULICS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
13−10−19
ACMP POWER AND DISTRIBUTION
Electrical power and distribution using the ACMPs are described as follows:
ACMPs 1B and 2B
Hydraulic systems 1 and 2 are each powered by one EDP used as the primary system pump.
Each primary pump is backed up by a single ACMP (one per system) during high flow demand
flight phases or failure of the primary pump in flight.
The ACMP is also used for system ground maintenance operation with the control switch in the
ON position. Each ACMP is powered by one of the electrical AC busses supplied by the generator
installed on the opposite engine (ACMP 1B is connected to AC bus #3 and ACMP 2B is connected
to AC bus #2). This will ensure operation of both hydraulic systems 1 and 2 in the case of a single
engine failure.
When only one generator is operating, AC busses #2 and #3 are shed. Since their respective AC
busses are disconnected during single generator operation, ACMPs 1B and 2B are automatically
load shed.
ACMPs 3A and 3B
Hydraulic system 3 is powered by two ACMPs: 3A as the primary system pump and 3B as the
back-up pump. Each pump is powered by a different AC bus (ACMP 3A is connected to AC bus
#4 and ACMP 3B is connected to AC bus #1). In the event of one, two or three generator failures,
both 3A and 3B ACMPs will receive power from one of the remaining generator. AC bus 1 and AC
bus 4 are both powered during single generator operation.
ACMP ELECTRICAL POWER SCHEMATIC
Left Engine Right Engine
PUMP
Electrical Flow
Generator
ACMP
Electrical AC BUS
GEN
AC BUS
LEGEND
ACMP Priority 3A, 3B, 2B, 1B
GF1310_021
GEN
1
GEN
2
GEN
4
GEN
3
AC BUS 1 AC BUS 2 AC BUS 3 AC BUS 4
3B 2B
ACMP
3A
ACMP
1B
ACMP ACMP
EXTERNAL AND APU ELECTRICAL PUMP OPERATION
External AC power has the capability to power all ACMPs for ground operation when the hydraulic
control switch is selected to the ON position.
During ground operation with either the APU or external ground power as the source of electrical
power, the AUTO mode of operation is not available. On ground with APU as the single source of
electrical power, only one pump at a time is allowed to run with 3A, 3B, 2A and 1B in priority.
In flight with the APU as the single source of electrical power, two pumps only (3A and 3B) are
allowed to run to prevent overloading of the generator.
HYDRAULICS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
13−10−20
RESERVOIR QUANTITY LIMITS
The table below describes the range of values between the upper and lower fluid quantity limits for
each system. The green brackets [ are variable in size and in combination with the filling and digital
　
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