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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
Aft Transfer Pumps 12−10−4
Centre 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
Centre Transfer 12−10−8
Wing Transfer 12−10−8
Auto Wing Transfer 12−10−8
Manual Wing Transfer 12−10−9
Crossfeed 12−10−9
Aft Transfer 12−10−11
Engine Feed System 12−10−13
Engine Feed System Indication 12−10−14
APU Fuel Feed 12−10−15
Fuel Quantity and Indication 12−10−16
Flight Management Display 12−10−17
Refuel/Defuel System 12−10−18
Refuel/Defuel Panel 12−10−19
Normal Fuel Loading 12−10−20
Gravity Refueling 12−10−21
Pressure Refueling 12−10−21
Manual Refueling 12−10−22
Suction Defueling 12−10−22
Pressure Defueling 12−10−22
Fault Reporting 12−10−23
Error Messages 12−10−23
INHIBIT 12−10−23
FUEL
TABLE OF CONTENTS
CHAPTER 12
12−00−1
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
12−00−1
Page
TABLE OF CONTENTS
DESCRIPTION
FULL 12−10−23
LOAD ERROR 12−10−23
IMBAL 12−10−23
REPEATER 12−10−23
FAILED 12−10−24
FMQGC − FAILURE 12−10−24
Refueling Distribution 12−10−24
Fuel ReCirculation
System (On airplanes with SB 700−28−034 incorporated) 12−10−24
Refuel/Defuel Schematic 12−10−27
Fuel Filters, Quantity and Temperature Readouts 12−10−28
Fuel Pump Displays 12−10−29
Fuel Shutoff
Displays 12−10−30
Fuel Synoptic Page Symbols 12−10−31
EICAS Philosophy 12−10−31
Fuel Management Quantity Gauging System (FMQGS) 12−10−31
FMQGC Schematic 12−10−32
EICAS Messages 12−10−33
EMS CIRCUIT PROTECTION
CB − Fuel System 12−20−1
FUEL
TABLE OF CONTENTS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
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 centre wing) and a smaller quantity of fuel is carried in a separate aft
fuselage tank. 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 electrical boost pumps. The transfer
system maintains the feed tanks full during all attitudes and provides automatic transfer of fuel from
the centre tank and aft tanks 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.
GF1210_001
ENGINE DRIVEN
PUMPS
AC MOTOR PUMPS
AC MOTOR PUMPS
(TRANSFER)
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 wing tank.
FUEL
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
12−10−1
GENERAL (CONT'D)
A dual channel FMQGC continuously monitors the following:
· Fuel quantity indicating.
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