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in this case.
NOTE
NOTE
HYDRAULIC POWER
For Training Purposes Only
May 03
13-9
P I LOT T R A I N I N G GU I D E
Accumulator and Reservoirs
System 3 has an accumulator that stores nominal hydraulic pressure to satisfy
instantaneous demands of aircraft systems and dampen pressure surges within the
system. The accumulator is precharged with nitrogen to 1500 psi.
System 3 reservoir is the largest of the three hydraulic systems with a capacity of 11.14
liters (2.94 U.S. Gal.). It is filled via the ground service panel located in the right main
wheel well.
During preflight, a visual inspection should include a check for accumulator pressure
at 1500 psi. With the exception of the accumulator gauge, system 3 components are
not readily accessible with the wheel well bins installed.
Hydraulic System 3 Accumulator Gauge
Figure 13-6
P604_13_019
HYDRAULIC POWER
13-10 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Controls and Indicators
The HYDRAULIC Panel provides the system controls; the EICAS Hydraulic
Synoptic Page provides a pictorial representation of the system status, and the EICAS
Primary and Status pages provide the system caution and advisory messages
respectively (see Figures 13-7 to 13-9 and Table 13-1).
HYDRAULIC Panel
HYDRAULIC Panel
Figure 13-7
HYDRAULIC
ON
OFF
AUTO
ON
OFF
AUTO
ON
OFF
AUTO
OFF
ON
1 3A 3B 2
Hydraulic Pump 1B and 2B Switches
ON
OFF
AUTO
– On the ground, pump operates continuously; in flight,
pump operates if cross-side engine generator is on-line.
– Pump is off.
– Pump operates automatically whenever flaps are
extended and the cross-side engine generator is on-line.
Hydraulic Pump 3A Switch
ON
OFF
– Pump operates continuously.
– Pump is off.
Hydraulic Pump 3B Switch
ON
OFF
AUTO
– Pump operates continuously.
– Pump is off.
– Pump operates automatically
whenever flaps are extended and
either engine generator is on-line.
: With generators 1 and 2 off, hydraulic
pump 3B is load shed when AUTO is selected.
(See System 3 schematic, fig. 13-5)
: Whenever the ADG is deployed and
supplying electrical power to the aircraft, hydraulic
pump 3B will automatically operate regardless of
switch position. (See System 3 schematic, fig. 13-5)
NOTE 1
NOTE 2
P604_13_006
HYDRAULIC PANEL
HYDRAULIC POWER
For Training Purposes Only
Jan 04
13-11
P I LOT T R A I N I N G GU I D E
Hydraulic Synoptic Page
EICAS Hydraulic Synoptic Page Color Coding (1 of 2)
Figure 13-8
Fluid Quantity Symbol
and Readout
Hydraulic Fluid
Temperature Readout
Hydraulic Shutoff Valve
Position Indicatior
Engine-Driven Pump
Input Line
Pressure Manifold
Input Line
System Distribution Table
1B 3A 3B 2B
3050
PSI
3000
PSI
2950
PSI
INBD
BRAKES
PSI
3000
OUTBD
BRAKES
PSI
3000
RUDDER
L ELEVATOR
L AILERON
FLT SPLR
GND SPLR
RUDDER
L ELEVATOR R
L AILERON R
LDG GEAR
N/W STEER
NOSE DOOR
RUDDER
ELEVATOR R
AILERON R
FLT SPLR
MLG AUX ACT
1A 2A
Pressure Manifold
Output Line
Hydraulic Pressure
Readout
Reservoir
Output Lines
P604_13_017
Pump Output Line
Description
Hydraulic Fluid
Temperature Readout
Hydraulic Fluid Symbol
and Quantity Readout
Hydraulic Shutoff Valve
Position Indicator
80 °C
49%
HYDRAULIC
95 °C
82%
15 °C
76%
Reservoir Output
Line
Symbol
70 °C
110 °C
- - - °C
Condition
Hydraulic fluid temperature is less than 96°C
Hydraulic fluid temperature is greater than or equal to 96°C
Invalid data
Hydraulic fluid quantity is between 45% and 85%
Hydraulic fluid quantity is less than 45% or more than 85%
Invalid data
Hydraulic shutoff valve is open
Hydraulic shutoff valve is closed after actuation of the
respective ENG FIRE PUSH switch/light
Invalid data
- - %
80%
35%
Sufficient fluid quantity in reservoir (> 2%)
Insufficient fluid quantity in reservoir (< 2%)
49%
0%
Engine-Driven Pump
Electrically-Driven Pump
Engine-Driven Pump
HYDRAULIC POWER
　
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