text: the pitch motion which adds to the restoring 
  moment from the basic static stability. 
  The 
  principal source of this additional pitching 
  moment is illustrated in figure 4.15. 
  
  During a pull-up the airplane is subject to 
  an angular rotation about the lateral axis and 
  the horizontal tail will experience a component 
  of wind due to the pitching velocity. The 
  vector addition of this component velocity to 
  the flight velocity provides a change in angle 
  of attack for the tail and the change in lift on 
  the tail creates a pitching moment resisting 
  the pitching motion. Since the pitching mo- 
  ment opposes the pitching motion but is due 
  to the pitching motion, the effect is a damping 
  in pitch. Of course, the other components of 
  the airplane may develop resisting moments 
  the 
  to pitch damping but 
  and contribute 
  horizontal 
  is usually the largest contri- 
  tail 
  bution. The added pitching moment from 
  pitch damping will effect a higher stability 
  in maneuvers than is apparent in steady flight. 
  From this consideration, the neutral point for 
  maneuvering flight will be aft of the neutral 
  point for unaccelerated flight and in most cases 
  will not be a critical 
  If the airplane 
  item. 
  demonstrates static stability 
  in unaccelerated 
  flight, it will most surely demonstrate stability 
  in maneuvering flight. 