![]() If the inboard tanks are defueled first, the weight of the fuel in the outboard tanks can cause a rearward shift of the center of gravity that can cause the aircraft to tip back on to the tail.Ĭross-feed valves are used to allow fuel to either be moved from tank to tank, or from either tank to either or both engines. On a sweptback wing airplane, defueling procedures usually dictate that the outboard wing tanks be defueled first. It will also shut off the dump valve when the level in the tank gets down to the preset dump shutoff level. ![]() There is a fuel dump limit-valve in each fuel tank that will shut off the flow if the pressure drops below what is needed to supply the engine with adequate fuel. Systems operation may vary from aircraft to aircraft, but the fuel boost pumps alone, or a combination of boost pumps and gravity will be used to jettison fuel. The fuel jettisoning system is usually divided into two separate, independent systems, one for each wing, so that lateral stability can be maintained by jettisoning fuel from the "heavy" wing.Īccording to FAR 23, a fuel jettison system is required for transport category and general aviation aircraft if the maximum takeoff weight exceeds the maximum landing weight. ![]() In addition, the fuel must discharge clear of any part of the airplane. The fuel jettisoning valve must be designed to allow flight personnel the ability to close it during any phase of the jettisoning operation. If an aircraft's landing weight is less than its take-off weight a means must be provided to jettison fuel to achieve a safe landing weight.Īccording to FAR 23, both of the statements in the question are true. Each wing contains either a fixed or an extendable dump chute, depending upon system design. The fuel jettisoning system of an aircraft is usually divided into two separate, independent systems, one for each wing, so that lateral stability can be maintained by jettisoning fuel from the "heavy" wing. allow water and sediment to settle to the drain point. resist surging from changes in the attitude of the aircraft.ġ5. It measures by weight instead of volume.ġ4. Sight glass, mechanical, electrical, and electronic.ġ3. An internal component fuel leak (shutoff valve, selector valve, or crossfeed valve).ġ2. The tank is pressurized with up to 1/2 psi air pressure and liquid soap is added to detect leaks.ġ1. reduces fueling time, eliminates aircraft skin damage, and reduces chances of contamination.ġ0. An underwing or single‐point pressure fueling system.ĩ. compare the fuel quantity in the tank with the indication of the electronic fuel quantity system.Ĩ. To provide an interconnected fuel system so that fuel can be fed from various tanks to any engine.ħ. alerts the flight crew that there may be danger of ice crystals forming in the fuel.ĥ. The structure of the cavity that the cell fits into.Ĥ. Rigid removable cell, bladder‐type cell, integral fuel cellģ. If take off weight is higher than the landing weight, in an emergency these aircraft need to reduce the weight to a specified landing weight.Ģ.
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