text: the maximum positive lift capability of this 
  airplane is 4 “g” at 200 knots, 9 g at 300 knots, 
  16 g at 400 knots, etc. Any load factor above 
  this line is unavailable aerodynamically, i.e., 
  the subject airplane cannot fly above the line of 
  maximum lift capability. Essentially the same 
  situation exists for negative lift flight with the 
  exception that the speed necessary to produce a 
  given negative load factor is higher than that 
  to produce the same positive load factor. Gen- 
  erally, the negative CL,., is less than the posi- 
  tive CL,., and the airplane may lack sufficient 
  control power to maneuver in this direction. 
  
  The occurrence of any one of these items could 
  cause structural damage or failure of the pri- 
  mary structure. A reasonable accounting of 
  these items is required during the design of an 
  airplane to prevent such occurrences in the re- 
  quired operating regions. The limit airspeed 
  of an airplane may be any value between termi- 
  nal dive speedand 1.2 times the maximum level 
  flight speed,depending on the aircraft type and 
  mission requirement. Whatever the resulting 
  limit airspeed happens to be, it deserves due 
  respect. 
  
  Thus, the airplane in flight 