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flight).
PRESSURE – displays hydraulic pressure in pounds per square inch of the pump
with the highest pressure.
1 Hydraulic Display
PRESS
LO
L C R
QTY 0.72 RF
5010
0.40
4850
1.25
4650
HYDRAULIC
1
787 Flight Crew Operations Manual
Hydraulics -
Controls and Indicators
13.10.4 Boeing Proprietary
Hydraulic Synoptic Display
FLT
L REV
NOSE GEAR
& STEERING
FLT
R REV
MAIN
FLAPS
PRIMARY
DEMAND
PRIMARY
DEMAND
ENG
ELEC ELEC
SOV SOV
ENG
ELEC ELEC
RAT
4650 PRESS 5010 PRESS 4850
1.15
L R
L R
ISLN ISLN
C1 C2
0.72
CTRL
FLT
GEAR CTRL
0.40 LO
CTRL
OVHT
RF
LOAD
SHED
AIR – air–driven pump
ELEC – electric–driven pump
ENG – engine–driven pump
ISLN – isolation valve
LO – reservoir quantity low
OF – reservoir quantity over–full
OVHT – pump overheat indication
RAT – ram air turbine pump
RF – reservoir requires refilling
SOV – shutoff valve
Closed valve –
Failed pump –
MULTIFUNCTION DISPLAY
ELEC – electric–driven pump
ENG – engine–driven pump
ISLN – isolation valve
LO – reservoir quantity low
OF – reservoir quantity over–full
OVHT – pump overheat indication
RAT – ram air turbine pump
RF – reservoir requires refilling
SOV – shutoff valve
Closed valve –
Failed pump –
LOAD SHED - load shed indication
787 Flight Crew Operations Manual
Hydraulics -
Controls and Indicators
Boeing Proprietary 13.10.5
Miscellaneous Hydraulic System Controls
Engine Fire Panel
Pull –
• closes the engine–driven pump hydraulic supply shutoff valve
• depressurizes the engine–driven pump.
1 Engine Fire Switches
DISCH DISCH
1 2 1 2
LEFT
RIGHT
ENG BTL
1 DISCH
ENG BTL
2 DISCH
AFT AISLE STAND
1
787 Flight Crew Operations Manual
Hydraulics -
Controls and Indicators
13.10.6 Boeing Proprietary
Flight Control Surface Lockout Switches
Note: No flight crew normal or non–normal procedures require operation of the
flight control surface lockout switches. These switches are for ground
maintenance use only.
NORM – associated flight control surface electronically unlocked.
LOCK – associated flight control surface electronically locked.
Illuminated (amber) – the system lockout has failed.
1 FLIGHT CONTROL SURFACES Lockout Switches (TAIL/WINGS)
2 FLIGHT CONTROL SURFACES Lockout FAIL Light
LOCK FAIL
NORM
LOCK
NORM
TAIL WINGS
FLIGHT CONTROL SURFACES
OVERHEAD PANEL
1
2
787 Flight Crew Operations Manual
Hydraulics Chapter 13
System Description Section 20
Boeing Proprietary 13.20.1
13.20 Hydraulics-System Description Introduction
The airplane has three independent hydraulic systems: left, right, and center. The
hydraulic systems power the:
Flight control system components are distributed so that any one hydraulic system
can provide adequate airplane controllability.
Hydraulic fluid is supplied to each hydraulic pump from the associated system
reservoir. The reservoirs are pressurized by pump outlet pressure (bootstrap).
Left and Right Hydraulic Systems
The left and right hydraulic systems are identical. They differ only in the
components they power.
The left hydraulic system powers:
• flight controls
• the left engine thrust reverser.
The right hydraulic system powers:
• flight controls
• the right thrust reverser.
Left and Right Hydraulic System Primary Pumps
The left and right hydraulic systems each have a primary pump. The left and right
primary pumps are engine–driven by the related left and right engines.
Left and Right Hydraulic System Demand Pumps
The left and right hydraulic systems each have a demand pump. The demand
pumps are electric motor–driven. The demand pumps provide supplementary
hydraulic power for periods of high system demand. The demand pumps also
provide a backup hydraulic power source for the engine–driven primary pumps.
The pumps are controlled by the DEMAND L and R pump selectors. In the ON
position, the demand pump runs continuously. In the AUTO position, the L and R
　
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