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MAGNET
Magnetic Level Indicators
(MLI) (5)
Push and rotate MLI core with
a screwdriver to the unlocked
position to deploy.
CENTER TANK MLI
LEFT SIDE ONLY
WING TANK INBOARD MLI
LEFT AND RIGHT
WING TANK OUTBOARD MLI
LEFT AND RIGHT
For MLI readings conversion, refer to
FCOM Vol. 2, SUPPLEMENTARY
PROCEDURES, FUEL SYSTEM.
NOTE
Vol. 1 13--60--9
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Pitch and Roll Inclinometers
Figure 13---60---7
PITCH INCLINOMETER
ROLL INCLINOMETER
Vol. 1 13--60--10
FUEL SYSTEM
Fuel Quantity Gauging REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
B. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Fuel Quantity
Control
FUEL SYST
CONT
BATTERY
BUS 1 M11
Gauging FUEL SYST
CONT
DC
ESSENTIAL 2 U11
Vol. 1 14--00--1
HYDRAULIC POWER
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
CHAPTER 14 --- HYDRAULIC POWER
Page
TABLE OF CONTENTS 14--00
Table of Contents 14--00--1
INTRODUCTION 14--10
Introduction 14--10--1
SYSTEMS 1 AND 2 14--20
Hydraulic Systems 1 and 2 14--20--1
Engine Driven Pumps 14--20--3
AC Motor Pumps 14--20--3
Shutoff Valves 14--20--4
System Circuit Breakers 14--20--8
HYDRAULIC SYSTEM 3 14--30
Hydraulic Systems 3 14--30--1
AC Motor Pumps 14--30--3
System Circuit Breakers 14--30--6
LIST OF ILLUSTRATIONS
INTRODUCTION
Figure 14--10--1 Hydraulic Systems Overview 14--10--2
Figure 14--10--2 Hydraulic Systems Diagram 14--10--3
SYSTEMS 1 AND 2
Figure 14--20--1 Hydraulic System (No. 1/2) -- Schematic 14--20--2
Figure 14--20--2 Hydraulic Control Panel 14--20--3
Figure 14--20--3 Systems 1 and 2 -- Shutoff Valves 14--20--5
Figure 14--20--4 Systems 1 and 2 -- Synoptic Page 14--20--6
Figure 14--20--5 Systems 1 and 2 EICAS Indications 14--20--7
SYSTEM 3
Figure 14--30--1 Hydraulic System 3 14--30--2
Figure 14--30--2 Hydraulic System 3 Control Panel 14--30--3
Figure 14--30--3 Hydraulic Synoptic Page 14--30--4
Figure 14--30--4 Hydraulic EICAS Indications 14--30--5
Vol. 1 14--00--2
HYDRAULIC POWER
Table of Contents Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 14--10--1
HYDRAULIC POWER
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. INTRODUCTION
Hydraulic power is provided by three independent systems designated 1, 2 and 3. All
systems operate at a nominal pressure of 3000 psi (20,685 kPa). Systems 1 and 2 are
serviced by ground service panels located in the aft equipment bay. System 3 is serviced by
a ground service panel located on the right side of the fuselage, aft of the wing root.
Each system has two hydraulic pumps; a main pump (A) for normal power and a backup
pump (B) for supplementary power. System 1 and 2 main pumps are engine driven pumps
(EDP). System 1 EDP (1A) is driven by the left engine and system 2 EDP (2A) is driven by
the right engine. System 1 and 2 backup pumps (1B and 2B) are AC motor pumps (ACMP).
Both pumps for System 3 are ACMPs. System 3 main pump (3A) normally runs
continuously, while the backup pump (3B) is available during periods of high flow
requirments. Pump 3B is automatically powered, during an AC power failure, by the air
driven generator (ADG) when it is deployed.
The hydraulic systems supply power to operate the rudder, elevators, ailerons, spoilerons,
flight spoilers, ground spoilers, thrust reversers, wheel brakes, nosewheel steering and
landing gear extension and retraction. Rudder, elevators and ailerons are powered by more
than one hydraulic system to prevent loss of critical flight controls.
Vol. 1 14--10--2
HYDRAULIC POWER
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Hydraulic Systems --- Overview
Figure 14---10---1
BRAKE
CONTROL
VALVES
NOSE LANDING GEAR
NOSE WHEEL STEERING
ALTERNATE GEAR
EXTEND ACTUATORS
AND OUTBOARD BRAKES
LEFT
ELEVATOR
RIGHT
ELEVATOR
MULTIFUNCTION
SPOILERS
RIGHT
AILERON
No. 3B AC
MOTOR PUMP
GROUND
SPOILERS
RIGHT
THRUST
REVERSER
No. 1B
AC MOTOR
PUMP
RUDDER
SYSTEM 1
SYSTEM 2
SYSTEM 3
NL
GAUXILIARY
ACTUATOR
　
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