Normally, an aircraft will yield acceptable flight characteristics if the CG is located somewhere near 25 percent of the average chord - which is one-fourth of the distance back from the leading edge of the mean aerodynamic chord (average wing section). CG is often expressed as a percentage of MAC for larger aircraft. An imaginary airfoil that has the same aerodynamic characteristics as the actual airfoil. CG range is the distance between the forward and aft limits.Īn imaginary line drawn through an airfoil from its leading edge to its trailing edge.Īverage distance from the leading edge to the trailing edge of the wing. The forward and aft locations beyond which the CG must not be located during takeoff, flight or landing. It is the theoretical “mass center” of the aircraft. The point about which an aircraft would balance if it were possible to suspend it at that point, expressed in inches from the datum. Used to simplify the W&B computations for larger aircraft (heavy weights x long arms = huge numbers). Product of the weight of an item multiplied by its arm expressed in pound-inches.Ī moment divided by a constant such as 100, 1,000 or 10,000. The zero fuel weight figure may be found in either the aircraft Type Certificate Data Sheet or the approved Aircraft Flight Manual. All weight over and above MZFW must be in the form of fuel in the wings. Based on the wings’ ability to tolerate bending stresses (wing-bending limit).Ħ. Maximum weight that can be concentrated in the fuselage (pilots plus payload).ĥ. Zero fuel weight for a particular flight is the basic operating weight plus payload.Ĥ. The maximum permissible weight of an aircraft with no disposable fuel or oil.ģ. The tailplane offsets the rotational force created by the moment caused by the center of lift being in a different position than the center of gravity. In essence, this is exactly what airplane stability is. Zero fuel weight sets a maximum allowable weight that can be carried in the fuselage in order to eliminate the possibility of destructive wing-bending stress.Ģ. The airplane will remain stable if you can always balance the moments created at different points. These loads increase dramatically as weight in the fuselage increases. The wings flex up and down with turbulence, applying severe bending loads at the wing roots. Maximum Allowable Zero Fuel Weight (MZFW)ġ. Usable fuel only, not the fuel in the lines or trapped in the sumps. Includes all fixed ballast, unusable fuel, normal operating level of oil and total quantity of hydraulic fluid (transport aircraft only). Total weight of the aircraft, including crew, ready for flight, but without payload or fuel (sometimes excludes the crew). Empty weight is defined as the total weight of an aircraft including all fixed ballast, unusable fuel, undrainable oil, total quantity of engine coolant and total quantity of hydraulic fluid, and excluding crew, payload, usable fuel and drainable oil.
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