text: The effect on range is much dependent on 
  the airplane configuration. When the pro- 
  peller on the’inoperative engine is feathered, 
  the added drag is at a minimum, but there is 
  trim drag ,required to balance 
  added the 
  the unsymmetrical power. When both these 
  sources of added drag are accounted for, the 
  ,is reduced but not by significant 
  (L/D)- 
  amounts. Generally, if the specific fuel con- 
  sumption and propeller efficiency do not deteri- 
  orate, the maximum specific range is not greatly 
  the 
  reduced. On 
  power required must .be furnished by the one 
  remaining engine and this. usually requires 
  more than the,maximum cruise-rating of the 
  powerplant.i As a result the powerplant can- 
  not be operated in the auto-lean or manual 
  lean, power range and the specific ,fuel con- 
  sumption increasesgreatly! Thus, noticeable 
  loss of range must be anticipated when one 
  engine fails on the twin-engine airplane. The 
  failure of oneengine on the four (or more) 
  engine airpla,W may allow the required, power 
  to be,develo,ped:by.the three remaining power- 
  plants operating in an economical power range. 
  If the airplane is clean, at low altitude, and 
  low gross weight, ,the failure of one engine is 
  not likely to cause a, loss of range. However, 
  then loss. of ‘two engines is likely ‘to cause a 
  considerable loss of range. 