What are the areas of an aircraft that suffers most from G forces? i want to ask this time as to "what are the areas of an aircraft that feels or suffers the most from G forces?". i am asking this in terms of structural design and physical limits of the pilot(the position and seat angle) and the plane.
please try not to limit the airplane model to simple light-aircraft,try to expand it near to military Aviation and other else.

if possible, please try not to use high-falutin words since i'm having a hard time with words in English.

If you can not understand this clearly, i am sorry for my poor English and Grammar, and also i want to elaborate more, but i can't translate it properly at the moment.
Basically 3 places on an airplane see very high concentrations of stress in a small area from in-flight G loads.  In this case we'll say a single engine light aircraft.


Wing root spar fittings on a cantilever wing - the bottom in tension and the top in compression. For a high wing airplane with struts, it will be the strut attachments at each end that join the strut to the fuselage and wing.
The roots of the horizontal tail, same except upside down - bottom in compression and top in tension.
Engine mount attachment to the firewall - top mount in tension and the bottom mount in compression.


Those are the points where flight loads from a lot of mass are concentrated at a single point or set of points during high G loading and are where the structural elements will be heaviest.  For most other areas the loads are distributed over more of a large area.