Editing Maximum takeoff weight (section)

==Certification standards==
Certification standards applicable to the airworthiness of an aircraft contain many requirements. Some of these requirements can only be met by specifying a maximum weight for the aircraft, and demonstrating that the aircraft can meet the requirement at all weights up to, and including, the specified maximum.  This limit is typically driven by structural requirements – to ensure the aircraft structure is capable of withstanding all the loads likely to be imposed on it during the takeoff,<ref>{{cite book | last=Torenbeek | first=E. | title=Synthesis of Subsonic Airplane Design: An introduction to the preliminary design of subsonic general aviation and transport aircraft, with emphasis on layout, aerodynamic design, propulsion and performance | publisher=Springer Netherlands | year=2013 | isbn=978-94-017-3202-4 | url=https://books.google.com/books?id=6nX7CAAAQBAJ&pg=PA272 | access-date=2023-10-22 | page=272}}</ref> and occasionally by the [[maximum flight weight]].<ref>{{cite book | last=Niu | first=C. | title=Airframe Structural Design: Practical Design Information and Data on Aircraft Structures | publisher=Conmilit Press | year=1988 | isbn=978-962-7128-04-5 | url=https://books.google.com/books?id=EHdGAAAAYAAJ&pg=PA585 | access-date=2023-10-22 | page=585 }}</ref>