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When a pump switch is set to AUTO, the pump will automatically start under the
following conditions:
S --AC BUS 2 must be powered for hydraulic pump IB operation,
--AC BUS 1 must be powered for hydraulic pump 2B operation.
S Flaps are out of the 0_ position.
NOTE
AC motor pumps 1B and 2B do not automatically start during
or after an engine failure.
Hydraulic Control Panel
Figure 14---20---2
Hydraulic Control Panel
Overhead Panel
Vol. 1 14--20--4
HYDRAULIC POWER
Systems 1 and 2 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
C. Shutoff Valves
Electrically operated ball type shutoff valves are installed in the suction lines of the
engine driven pumps (1A and 2A). The valves are normally open. Valve position is
indicated on the EICAS, HYD synoptic page.
During an engine fire condition, the corresponding shutoff valve is motored closed when
the ENG FIRE PUSH switchlight is pressed in (See Chapter 10, Fire Protection). Each
shutoff valve can be manually closed by pressing the L or R HYD SOV switchlight on
the hydraulic shutoff panel in the overhead panel.
Vol. 1 14--20--5
HYDRAULIC POWER
Systems 1 and 2 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Systems 1 and 2 --- Shutoff Valves
Figure 14---20---3
Vol. 1 14--20--6
HYDRAULIC POWER
Systems 1 and 2 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Systems 1 and 2 --- Synoptic Page
Figure 14---20---4
Vol. 1 14--20--7
HYDRAULIC POWER
Systems 1 and 2 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Systems 1 and 2 EICAS Indications <1001>
Figure 14---20---5
HYD SOV 1 or 2 CLOSED advisory (green)
Indicates that corresponding shut--off valve has
been closed.
HYD SOV 1 or 2 OPEN caution (amber)
Indicates that the respective shut--off valve is
open with an associated engine fire.
Status Page
Primary Page
Vol. 1 14--20--8
HYDRAULIC POWER
Systems 1 and 2 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
D. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Pumps
HYD SYST AC
PUMP
CONT 1
DC BUS 2 2 F13
HYD SYST AC
PUMP CONT
2
DC BUS 1 1 F14
H d li Indication
HYD SYST
IND 1 DC BUS 2 2 F12
Hydraulic
Systems 1
and 2
HYD SYST
IND 2 DC BUS 1 F13
Fans
HYD SYST
FAN AC BUS 1 A8
HYD SYST
FAN CONT DC BUS 1 1 F12
Shutoff Valves
HYD SOV
R ENG DC
R5
HYD SOV
L ENG
EMERGENCY R6
Vol. 1 14--30--1
HYDRAULIC POWER
System 3 REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. HYDRAULIC SYSTEM N0 3
Hydraulic system No. 3 consists of the following components:
S Two AC motor pumps (identified as 3A and 3B
S Reservoir
S Accumulator
S Three overflow containers
S Pressure and return manifolds
S Case drain filters
S Ground servicing panel
Hydraulic system No. 3 provides pressure to the following systems:
S Ailerons
S Elevators
S Rudder
S Inboard ground spoilers
S Landing gear actuators
S Inboard brakes
S Nosewheel steering
Hydraulic system No. 3 does not have a heat exchanger and does not use the No.1 and No.
2 system heat exchanger for cooling the system fluid. The No. 3 system hydraulic fluid runs
through lines that pass through the fuel tanks thereby allowing the fluid to be cooled through
natural convection.
No. 3 hydraulic system is monitored by:
S Temperature and pressure switches
S Temperature and pressure transducers
S A quantity transducer and gauge
Vol. 1 14--30--2
HYDRAULIC POWER
System 3 Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Hydraulic System 3
Figure 14---30---1
P
SUCTION
PRESSURE
RETURN
CASE DRAIN
DRAIN TO OVERFILL
FILL
ACCUMULATOR
RETURN MANIFOLD
CASE DRAIN
FILTER
RESERVOIR
CHECK VALVE
NITROGEN CHARGING VALVE
AND GAUGE
OVERFLOW
CONTAINER
SYSTEM RETURN BRAKE RETURN
CHECK VALVE
GROUND
SERVICE
FILL
RETURN
FILTER
PRESSURE
TRANSDUCER
TO
HYDRAULIC
SERVICES
PRESSURE
SWITCH
PRESSURE
SWITCH
PRESSURE
RELIEF
VALVE
CHECK
VALVE
CASE DRAIN
FILTER
AC MOTOR
PUMP 3A
AC MOTOR
PUMP 3B
OVERFLOW
CONTAINER
BLEED/RELIEF
　
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