DESCRIPTION
General 12−10−1
Fuel Specifications 12−10−2
Fuel System Synoptic Page 12−10−3
AC Boost Pumps 12−10−3
DC Auxiliary Pumps 12−10−3
Center Transfer Pumps 12−10−4
Fuel Control Panel 12−10−4
Fuel Tanks 12−10−5
Service Points 12−10−5
Vent System 12−10−6
Vent System Schematic 12−10−6
Transfer System 12−10−7
Center Transfer 12−10−7
Wing Transfer 12−10−7
Auto Wing Transfer 12−10−8
Manual Wing Transfer 12−10−8
Crossfeed 12−10−8
Engine Feed System 12−10−11
Engine Feed System Indication 12−10−11
APU Fuel Feed 12−10−13
Fuel Quantity and Indication 12−10−14
Flight Management Display 12−10−15
Refuel/Defuel System 12−10−16
Refuel/Defuel Panel 12−10−17
Normal Fuel Loading 12−10−18
Gravity Refueling 12−10−18
Pressure Refueling 12−10−18
Manual Refueling 12−10−19
Suction Defueling 12−10−19
Pressure Defueling 12−10−19
Fault Reporting 12−10−19
Error Messages 12−10−19
INHIBIT 12−10−20
FULL 12−10−20
LOAD ERROR 12−10−20
FUEL
TABLE OF CONTENTS
CHAPTER 12
12−00−1
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−00−1
Page
TABLE OF CONTENTS
DESCRIPTION
IMBAL 12−10−20
REPEATER 12−10−20
FAILED 12−10−20
FMQGC − FAILURE 12−10−20
Refueling Distribution 12−10−21
Refuel/Defuel Schematic 12−10−22
Fuel ReCirculation
System 12−10−23
Fuel Filters, Quantity and Temperature Readouts 12−10−25
Fuel Pump Displays 12−10−26
Fuel Shutoff Displays 12−10−27
Fuel Synoptic Page Symbols 12−10−28
EICAS Philosophy 12−10−28
Fuel Management Quantity Gauging System (FMQGS) 12−10−28
FMQGC Schematic 12−10−29
EICAS Messages 12−10−30
EMS CIRCUIT PROTECTION
CB − Fuel System 12−20−1
FUEL
TABLE OF CONTENTS
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
Volume 2
12−00−2
Page
GENERAL
Fuel is contained in a wet wing box structure, which is sealed to form three main separate wing tanks
(left wing, right wing and center wing). The tanks are vented to atmosphere and slightly pressurized
by an air scoop located on the lower surface of each wing. A scavenge pump purges fuel from the
vent lines and a climb vent, located in each main wing tank, provides ventilation when the airplane is
in a nose up attitude.
Each engine is supplied with fuel from its respective feed tank which contains two alternating current
or AC primary pumps and one Direct Current (DC) back up boost pump. The transfer system
maintains the feed tanks full during all attitudes and provides automatic transfer of fuel from the
center tank to the main wing tanks.
Lateral balance between left and right main tanks is controlled automatically by the Fuel
Management and Quantity Gauging Computer (FMQGC) or manually through switch selections in
the flight compartment.
FGF1210_001
ENGINE DRIVEN
PUMPS
AC MOTOR PUMPS
AC MOTOR PUMPS
(TRANSFER)
CENTER TANK
MAIN WING TANK
DC PUMPS
(START, EMERGENCY
FEED TANKS
AND WING TRANSFER)
(ENGINE FEED)
Flight deck control is provided on the overhead panel and fuel quantity and warnings are displayed
on EICAS.
A single point pressure refuel/defuel adapter is provided which is connected to a manifold containing
shutoff valves. Pressure refueling can be done either automatically or manually. Gravity filling is
provided for each tank.
FUEL
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
12−10−1
GENERAL (CONT'D)
A dual channel FMQGC continuously monitors the following:
· Fuel quantity indicating
· Left, right engine and APU feed
· Wing to wing balance (wing XFER)
· Center tank transfer
· Refuel/defuel
· Fuel recirculation
Any fault detected by the fuel system computer is annunciated on Engine Indication and Crew
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：Bombardier_Global_000-Fuel
