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25 Cards in this Set
- Front
- Back
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Engine Fuel feed is normally supplied from the
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Related collector tank
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The tail tank system consists of
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Two saddle tanks and the tail cone tank
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Fuel in the tail tank system is transferred under control of the
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Fuel Computers (FSCU)
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The fuel system contro unit
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Controls tail fuel transfer, fuel quantity indicating and pressure refueling
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Avgas may be used in quantities not exceeding
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No avgas is allowed
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Which fuel tanks may be gravity fueled
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Wing and Auxilary Tanks
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When gravity fueling what percent full can you achieve
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93%
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Rotor burst zone protection is provided for the
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Tail to Aux tank fuel transfer line
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Manual control of fuel transfer is
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Selected by the TAIL TANK TRANSFER MANUAL OVRD switchlight
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The Main and Aux tanks are ventilated by
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Interconnected vent systems supplied from to NACA vents
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Main and Aux tank overpressure during pressure refueling is prevented by
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Poppet type relief valves on the underside of the wing and aux tanks
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Tail tank overpressure during pressure refueling is prevented by
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A poppet type valve located on the left side of the vertical stabilizer
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During normal operations, float valves regulate fuel quantity to 93% in the
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Main tanks
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Display of the AUTO TAIL XFER INHIB caution EICAS message indicates
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Low pressure is detected in the rotor burst protection shroud on the tail tank trasfer line
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Fuel quantity is indicated via
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By the fuel computer (FSCU) which monitors capacitance probes and attitude signals
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If the left BOOST PUMP switch is pushed, then
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Both boost pumps operate if left main ejector output pressure is low
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Motive flow pressure in the right engine feed system is provided by
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By the engine fuel control unit for operation of all ejector pumps
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The engine fuil shutoff valve in the right engine feed line is controlled by
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The related ENG FIRE PUSH switchlight
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Opening of the fuel dump valve drains fuel from the
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The tail tank system only and is used only for CG control
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The L TO AUX switchlight controls
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Fuel transfer from the left main tank to the center auxilary tank
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The GRAVITY switchlight controls
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The Gravity crossfeed valve which interconnects the main tanks
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The FUEL INBALANCE caution EICAS message is displayed when
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A fuel imbalance between the main tanks exceeds 800lbs while in flight with the flaps retracted
A fuel imbalance between the main tanks exceeds 400lbs while on the ground or when flaps are extended in flight |
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The FUEL/DEFUEL control panel located at the fuselage right wing fairing is powered from
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The APU battery direct bus
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During pressure fueling or defueling, the respective fuel pressure must not exceed
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50psi/-8psi
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When fueling or defueling the aircraft, the fuel im balance between wing tanks must not exceed
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2500lbs
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