text: (2) Optrating ftrcngth limits will define the 
  upper limits of maneuvering load factors 
  which will not damage the primary struc- 
  ture of the airplane. These limits must not 
  be exceeded in normal operations because of 
  the possibility of structural damage or 
  failure. 
  
  (3) Thwt or power limits will define the 
  ability of the airplane to turn at constant 
  altitude. The limiting condition would al- 
  low increased load factor and induced drag 
  until 
  the drag equals the maximum thrust 
  available from the powerplant. Such a case 
  would produce the maximum turning capa- 
  bility for maintaining constant altitude. 
  The first illustration of figure 2.30 shows 
  limits  how the aerodynamic and structural 