Can someone ‘splain this to me? I have no idea if I have it right, or not.

As I understand it, maneuvering speed is the speed above which the
aircraft may be damaged due to full control movements. Below that
speed, the plane will stall before damage occurs. I also understand
that maximum lift changes as the square of the speed, while stall speed
changes as the square root of the weight.

So, if I have an aircraft traveling at twice stall speed, it will have 4
g’s acceleration prior to stalling. If I double the weight, the stall
speed increases by 1.41, so maneuvering speed also increases by 1.41 –
assuming that the aircraft is rated a 4 g’s at both weights.
Or, to put it conversely, the maneuvering speed varies inversely
proportionately to the square root of the weight change – if I double
the weight, the maneuvering speed increases by 41%.

Do I have that right?

So, assume I am flying at 1410 lbs. weight and traveling at 4 times
stall speed. If I reduce weight to 1000 lbs., and pull back on the
stick, won’t the aircraft stall with exactly the same load on the wings,
although now 5.6 g’s? (4 * 1410 or 5640 lbs)?

Does the issue for maneuvering speed now become the motor mounts,
battery box, seats. etc? If I’m certain that the weak point is not
these things, but the main airframe itself, can I use the maneuvering
airspeed for maximum weight?

Next - how about maximum structural cruising speed?