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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 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 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：Bombardier_Global_000-Fuel
