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thelowersurface of each wing.
Inflight,theNACA scoops supply ram air to slightlypressurize thewingtanks.
Ontheground,thetanks are ventedtoatmosphere throughtheNACA scoopsto preventpressure buildup within thetanks causedbythe refuelingprocess orfrom thermal expansion ofthefuel.
NOTE
Duringclimb,fuelcouldenterthecentertankfromthe vent system. This fuel can cause erroneous center tankquantityindications ashigh as300lbs (135kg).
Fueltank capacities for pressure fuelingoperation:
TANK USABLE FUEL UNUSABLE FUEL TOTAL FUEL
Left Wing 4760 lb (2159 kg) 20.4 lb (9.2 kg) 4780.4 lb (2168.2 kg)
Right Wing 4760 lb (2159 kg) 20.4 lb (9.2 kg) 4780.4 lb (2168.2 kg)
Center 4998 lb (2267 kg) 6.8lb(3kg) 5004.8 lb (2270 kg)
Total 14518 lb (6585.2 kg) 47.6 lb (21.6 kg) 14565 lb (6606.8 kg)
Fueltank capacities for gravityfuelingoperation:
TANK USABLE FUEL UNUSABLE FUEL TOTAL FUEL
Left Wing 4488 lb (2036 kg) 20.4 lb (9.2 kg) 4508.4 lb (2145.2 kg)
Right Wing 4488 lb (2036 kg) 20.4 lb (9.2 kg) 4508.4 lb (2145.2 kg)
Center 4930 lb (2236 kg) 6.8lb(3kg) 4936.8 lb (2239 kg)
Total 13906 lb (6308 kg) 47.6 lb (21.6 kg) 13953.6 lb (6329 kg)
Flight Crew Operating Manual MASTER
CSP A-
013
FUEL SYSTEM Fuel Storage Vol. 1 13-
20-
2
REV 56, Jan 31/03
VENTLINETUBING
NACA SCOOP NACA
SCOOP MOTIVE TO ENGINES MOTIVE FLOW FLOW
Collector Tank and Vent System ---General
Figure 13---20---1
Flight Crew Operating Manual MASTER
CSP A-
013
FUEL SYSTEM Vol. 1 13-
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