text: The static strength requirement is the con- 
  sideration given to the effect of simple static 
  loads with none of the ramifications of the 
  repetition or cyclic variation of loads. An 
  important reference point in the static strength 
  requirement is the “limit 
  condition. 
  When the aircraft is at the design conligura- 
  there will be some maximum of load 
  tion, 
  which would be anticipated from the mission 
  requirement of the airplane. For example, a 
  fighter or attack type aircraft, at the design 
  configuration, may encounter a very peak load 
  factor of 7.5 in the accomplishment of its mis- 
  sion. Of course, such an aircraft may be sub- 
  ject to load factors of 3, 4, 5, 6, 1, etc., but no 
  more than 7.5 should be required to accom- 
  plish the mission. Thus, the limit load condi- 
  tion is the maximum of loads anticipated in 
  normal operation of 
  Various 
  types of aircraft will have different limit 
  load 
  factors according to the primary mission of 
  the aircraft. 
  Typical values are tabulated 
  below: 
  Type of aircraft: 
  
  load” 
  
  hbi”< 
  limi, hi,orror 
  7.5 
  7.5 
  3.0 or 2.5 