There are different ways to define Va, but that doesn't mean they're all correct
No there isn't.
The definition of Va is "VA means design maneuvering speed". That is the FAA definition. As you say no mention of "stall" exists in the definition. The definition in itself tells you absolutely zip. For an understanding of what Va is, and trying to acomplish, you need to refer to 23.335, which is centred basically around the stall and structual strength.
PittsS2A has put it very well in his post.
Further guidance is provided by (note the stall reference);
§ 23.1507 Operating maneuvering speed.
The maximum operating maneuvering speed, VO, must be established as an operating limitation. VO is a selected speed that is not greater than VS√n established in §23.335(c).
I do recall that if at Va you input full up elevator and full aileron you could well damage the airframe.
Rolling 'g' limits, at least on those I've flown, were two thirds of the normal limit. I assume that derives from (b) below;
§ 23.349 Rolling conditions.
The wing and wing bracing must be designed for the following loading conditions:
(a) Unsymmetrical wing loads appropriate to the category. Unless the following values result in unrealistic loads, the rolling accelerations may be obtained by modifying the symmetrical flight conditions in §23.333(d) as follows:
(1) For the acrobatic category, in conditions A and F, assume that 100 percent of the semispan wing airload acts on one side of the plane of symmetry and 60 percent of this load acts on the other side.
(2) For normal, utility, and commuter categories, in Condition A, assume that 100 percent of the semispan wing airload acts on one side of the airplane and 75 percent of this load acts on the other side.
(b) The loads resulting from the aileron deflections and speeds specified in §23.455, in combination with an airplane load factor of at least two thirds of the positive maneuvering load factor used for design. Unless the following values result in unrealistic loads, the effect of aileron displacement on wing torsion may be accounted for by adding the following increment to the basic airfoil moment coefficient over the aileron portion of the span in the critical condition determined in §23.333(d):
Δ c m=−0.01δ
where—
Δ c mis the moment coefficient increment; and
δ is the down aileron deflection in degrees in the critical condition.
A good paper on Va is here
http://http://www.flightlab.net/Flig...aneuvering.pdf
As the referred paper says "here’s a conservative, inclusive, legalistic mouthful: Maneuvering speed, VA, is the maximum speed, at a given weight and configuration, at which any one (and only one) flight control surface can be abruptly and fully deflected—not to include rapid control surface reversals—without causing aircraft damage."