Where are jack points typically located on an aircraft? I realised that full gear swing tests require an aircraft to be fully jacked up; and I think it would make sense to locate the jack points close to the landing gears themselves, on the same load-bearing structures (e.g., main wing spar), since those structures are already designed to support the weight of the aircraft.

Is that generally the case, and are there considerations where designers would locate the jack points elsewhere (and presumably have to specially reinforce these other locations)?
Yes indeed, at strong points such as landing gear structure, engine support, or wing strut. The jacks need to be out of the way of the swinging doors of course, but as close as possible to the fuselage.







This one has a special design man leg jack.