I like the approach you are making here Caldrail.
As a very poor mathematician , I appreciate your simplification of these problems.
I do feel the need to point out, though , that your suggestion that the engine represents the largest part of the mass of the aircraft is , I fear , over simplified. ( I understand the need for simplification in order for those like me to understand at all, yet the discussion needs a bit more info for consideration , I think). Surely , the engine is the single most massive component ,
but on examination , one must acknowledge that to say it is the most massive part of the structure (especially when fully loaded)
is not accurate.
The mass of the Wright R-2600-20 Radial engine (dry - no oil , no lube) is 930 kg *
The unloaded takeoff mass of a TBM is 4,783 kg
The max-loaded takeoff mass of a TBM is 8,115 kg
In the case of the unloaded TBM , the mass of the engine represents 19.4 % of the total mass ;
In the case of the fully loaded TBM , the mass of the engine represents only 11.5 % of the total mass.
Thus the properties of the floats need to account for both a mass variation of the range of 3,332 Kg and the variations of the C of G that the various loadout alternatives represent.
* all weights from wiki
I am not trying to contradict your effort , but to further develop it.
I appreciate your excellent article.
Thanks
Kopfdorfer