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Fluid temperature and reservoir quantity are displayed on the EICAS status
display and hydraulic synoptic display. The letters RF display next to the reservoir
quantity indication when refill is required. RF is inhibited in flight. The letters LO
replace RF when a system low quantity exists. Hydraulic quantity levels fluctuate
with variations in temperature and as devices that use hydraulic power activate.
• primary flight controls
• autopilot servos
• spoilers
• stabilizer trim
• elevatorfeel
• landing gear
• flaps
• brakes
• steering.
December 01, 1999
747 Operations Manual
Copyright © The Boeing Company. See title page for details.
13.20.2 D6-30151-425
Hydraulics -
System Description
For a single hydraulic system failure, the inoperative items display on the
hydraulics synoptic above the affected system graphic. If multiple hydraulic
systems are inoperative, additional items common to those systems display above
the single system items and are connected by indentifying lines to the failed
systems.
A hydraulic fluid shutoff valve is installed in the fluid supply line to each EDP. If
an engine fire switch is pulled, the related hydraulic fluid shutoff valve closes, the
EDP depressurizes, and the related demand pump operates.
Load Assignments
Systems 1 and 4 power the trailing edge flaps, landing gear, normal brakes (SYS
4), alternate brakes (SYS 1), and steering. Systems 1 and 4 also provide redundant
power to the primary flight controls.
Systems 2 and 3 power the primary flight controls, stabilizer trim, and elevator
feel. System 2 also powers the alternate brakes and lower yaw damper. System 3
powers the upper yaw damper.
Systems 1, 2, and 3 power the related center, right, and left autopilot servos.
Systems 2, 3, and 4 power the spoilers.
December 01, 1999
747 Operations Manual
Hydraulics -
System Description
Copyright © The Boeing Company. See title page for details.
D6-30151-425 13.20.3
Hydraulic System Diagram
FEEL
ELEVATOR
TRIM
STABILIZER
ALTERNATE ALTERNATE NORMAL
PUMP
AIR DRIVEN
MTR PMP MTR PUMP
(AUX)
MTR PUMP
LEFT OUTBD LEFT INBD
ACTUATION
LEFT INBD
INBD T.E.
LEFT OUTBD
ACTUATION
PUMP (DEMAND)
DRIVEN
ENGINE
(DEMAND)
ELECTRIC
PUMP
DRIVEN
ENGINE
(DEMAND)
ELECTRIC
PUMP
DRIVEN
ENGINE
RIGHT INBD
ACTUATION
BRAKES
UPPER RUDDER
AILERON AILERON
BRAKES
AILERON
RIGHT OUTBD
1
LOWER RUDDER
AILERON
RIGHT INBD
ELEVATOR
5, 6, 7, 8
SPOILERS
FLAPS
OUTBD T.E.
ELEVATOR
RIGHT OUTBD
WING GEAR
1, 4, 9, 12
SPOILERS
LEFT
ENGINE AIR DRIVEN
(DEMAND)
PUMP
ELECTRIC
DRIVEN
BRAKES
2, 3, 10, 11
SPOILERS
RIGHT
AUTOPILOT
FLAPS
BODY GEAR
STEERING
BODY GEAR
ELEVATOR ELEVATOR
NOSE GEAR
STEERING
NOSE GEAR
3 4
SYSTEM SYSTEM
PUMP
AUTOPILOT
SYSTEM
2
SYSTEM
CENTER
AUTOPILOT
December 01, 1999
747 Operations Manual
Copyright © The Boeing Company. See title page for details.
13.20.4 D6-30151-425
Hydraulics -
System Description
Hydraulic Systems 1, 2, and 3 Diagram
CUTOFF
RUN BLEED
DISCH
A B
1
*
T
Q
P
P
P
TO
USING
COMPONENTS
FROM
SYSTEM
AIR
FROM
USING
COMPONENTS
FLAPS
PRESS
ON
SYS
FAULT
PRESS
OFF
AUTO
ON
N
I
G
N
E
D
N
A
M
E
D
E
1
1
*
NOTE: SYSTEMS 2 & 3 USE ELECTRIC MOTOR DRIVEN DEMAND PUMPS
1 Hydraulic System 1 only
December 01, 1999
747 Operations Manual
Hydraulics -
System Description
Copyright © The Boeing Company. See title page for details.
D6-30151-425 13.20.5
Hydraulic Systems Diagram 4
FLAPS
SYSTEM
FROM
USING
COMPONENTS
CUTOFF
RUN
PRESS
ON
SYS
FAULT
PRESS
OFF
AUTO
ON
4
N
I
G
N
E
X
U
A
&
D
N
A
M
E
D
E
AUX M
AIR
BLEED
DISCH
B A
4
Q
P
P
P
　
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