曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
. Based on a fuel density of 6.75 lb/USG (0.809 kg/litre), rounded to the nearest 5 lb or 5 kg. Fuel Mass is provided for reference only and should not be considered limiting.
Gravity Refuel (Airplane Level)
Fuel Tank Fuel Mass .
Right 6500 lb 2950 kg
Left 6500 lb 2950 kg
Left & Right 13 000 lb 5900 kg
. Based on a fuel density of 6.75 lb/USG (0.809 kg/litre), rounded to the nearest 50 lb or 25 kg. Fuel Mass is provided for reference only and should not be considered limit-ing.
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
12-01-02
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
12-01-03
LEGEND
MOTIVE FUEL LINESREFUEL/DEFUEL LINESFUEL FEED LINES
APU L ENGINE R ENGINE
CFO1201002_007
FUEL
FUEL TANK SYSTEM (Cont) COMPONENTS AND OPERATIONS TANK CONSTRUCTION
The wing tanks are integral type fuel tanks that use a wet wing design and are sealed with a fuel resistant sealant.
FUEL TANK SYSTEM (Cont)
WATER DRAIN VALVES
There are three water drain valves in each wing. One for the collector tank, one for the wing tank, and one for the surge tank, which is located in the outboard area of each wing. They are used to drain water and contaminates that collect in the fuel tanks and to complete the removal of remaining fuel during defueling. If contamination is suspected all tanks should be drained until the fuel is clear of water or other contaminates.
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
12-01-04 FUEL TANK SYSTEM (Cont)
FLAPPER CHECK VALVES
Each wing tank incorporates flapper check valves that are attached to the internal wing ribs. These valves prevent outward flow of the fuel during wing low maneuvers.
VENT SYSTEM
The tanks are vented through interconnecting vent lines to NACA scoops (low drag vents) located on the lower surface of the wing trailing edges (one per wing).
During operations on the ground and in flight, the NACA scoops provide static ventilation of the tanks and relieve air pres-sure differential caused by the refueling process, thermal expansion of the fuel, or altitude variation in flight.
Surge bays located outboard of both wing tanks provide additional expansion volume for the vent system to prevent fuel spillage. Each surge bay holds 53.6 lbs of fuel and flapper valves are located between the surge bays and tanks to prevent outward flow of fuel from the tanks.
FUEL DISTRIBUTION
DESCRIPTION
There are two separate fuel distribution systems. One feeds the left engine, and the other feeds the right engine and APU.
ENGINE FUEL FEED
The primary fuel feed to each engine is independently provided from its respective tank. The feed line is pressurized by means of an ejector taking its motive flow from the high pressure stage of the engine fuel system. This high pressure fuel is delivered to the ejector nozzle. The same high pressure source is also used to drive the scavenge ejector. The primary ejector is totally self energized by its respective engine and is not reliant on any other power source for its control or oper-ation. Proper operation of the primary feed ejector is signaled by a pressure switch located at the ejector outlet.
中国公务机网 www.gongwuji.com
公务机翻译 www.aviation.cn
本文链接地址：庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-燃油(4)
| 
