text: the airplane were at a 60’ bank and lift were 
  not provided to produce the exact load factor 
  of 2.0, the aircraft would be accelerating in the 
  vertical direction as well as the horizontal di- 
  rection and the turn would not be steady. 
  Also, any sideforce on the aircraft due to 
  sideslip, etc., would place the resultant aero- 
  dynamic force out of the plane of symmetry 
  perpendicular to the lateral axis and the turn 
  would not be coordinated. 
  
  would be to provide the endurance thrust with 
  some engine(s) shut down and the remaining 
  engine(s) operating at a more efficient power 
  output. This technique would cause a mmi- 
  mum loss of endurance if at low altitude. The 
  feasibility of such a procedure is dependent 
  on many operational factors. 
  
  In all cases, the airplane should be in the 
  cleanest possible external configuration because 
  the specific endurance is directly proportional 
  to the (L/D). 
  MANEUVERING PERFORMANCE ,...s’ 
  turning flight, 
  
  As a consequence of the increase lift 
  
  the 
  airplane is not in static equilibrium for there 
  must be developed the unbalance of force to 
  produce the acceleration of the turn. During 
  a steady coordinated turn, the lift 
  is inclined 
  to produce a horizontal component of force to 
  equal the centrifugal force of the turn. 
  In 
  addition, the steady turn is achieved by pro- 
  ducing a vertical component of lift which is 
  equal to the weight of the airplane. Figure 
  2.28 illustrates the forces which act on the 
  airplane in a steady, coordinated turn. 
  
  When the airplane is’in 