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The aircraft gross weight (also known as the all-up weight (AUW)) is the total aircraft weight at ''any moment'' during the flight or ground operation.〔Airplane Design Dr, Jan Roskam 1985〕〔Synthesis of Subsonic Airplane Design〕〔Aircraft Design Projects ISBN 0-7506-5772-3〕 An aircraft's gross weight will decrease during a flight due to fuel and oil consumption. An aircraft's gross weight may also vary during a flight due to payload dropping or in-flight refuelling. At the moment of releasing its brakes, the gross weight of an aircraft is equal to its takeoff weight. During flight, an aircraft's gross weight is referred to as the ''en-route weight'' or ''in-flight weight''. ==Design weight limits (structural design weights)== An aircraft's gross weight is limited by several weight restrictions in order to avoid overloading its structure or to avoid unacceptable performance or handling qualities while in operation. Aircraft gross weight limits are established during an aircraft's design and certification period and are laid down in the aircraft's type certificate and manufacturer specification documents. The absolute maximum weight capabilities of a given aircraft are referred to as the ''structural weight limits''. The structural weight limits are based on aircraft maximum structural capability and define the envelope for the CG charts(both maximum weight and CG limits). An aircraft's structural weight capability is typically a function of when the aircraft was manufactured, and in some cases, old aircraft can have their structural weight capability increased by structural modifications. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Aircraft gross weight」の詳細全文を読む スポンサード リンク
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