'megan' you may find useful info in NATOPS, here is some info:
A-5A AIRCRAFT NATOPS Flight Manual NAVY MODEL
1965
https://docdro.id/GxkZXeu (PDF 61Mb) or
http://aviationarchives.********.com/search?q=vigilante
HORIZONTAL STABILIZERS
The horizontal stabilizers, constructed in two one-piece slabs, are attached to spindle fittings on the fuselage below the vertical stabilizer. These control surfaces have a travel range of 15 degrees leading edge up and 18 degrees leading edge down. Changes in pitch trim are made by small movements of the entire surface. Changes in lateral (roll) trim are accomplished by differential deflection of the horizontal stabilizers.
VERTICAL STABILIZER
The vertical stabilizer is a one-piece, all-movable surface. Total surface travel is 16 degrees; 8 degrees either side of center. Vertical stabilizer travel is regulated by a ratio-changing mechanism controlled by the position of the wing flaps. Stabilizer travel varies linearly from 2 degrees left or right ( with flaps up) to 8 degrees left or right (with flaps down 25 degrees or more). A position light, buddy tanker signal lights, and a fuel overboard vent are installed in a fairing on the trailing edge of this surface.
WARNING
Avoid abrupt, large magnitude, longitudinal control motions in maneuvering flight. If the stall warnings of lateral control deterioration, moderate to heavy airframe buffet and rudder pedal shaker actuation are ignored, or if extreme control motions cause the aircraft to depart abruptly from controlled flight, the aircraft may enter a developed spin from which recovery is highly unlikely.
WARNING
INTENTIONAL SPINS ARE PROHIBITED. During the spin test program, a spin mode was encountered from which no satisfactory recovery, using the production design control system, was possible.
WARNING
In the event the post-stall gyration progresses to a fully developed spin, it is highly unlikely that recovery can be effected.