TM  1-1520-240-10 8-2-16            14.   PWR XFER 1 and 2 switches — ON. 15.   Cyclic trim indicators — Check GND indica- tion, manually program if necessary. WARNING Personnel injury or death may occur and damage to the airframe and rotor system will occur if the forward or aft rotor head rotor blade droop stop(s) on the aft rotor head are not engaged. After engine run-up and before flight, or shut down if flight is not  conducted,  the  flight  engineer  will scan the ground in the immediate area of the aircraft for evidence of detached droop stops. Prior to moving Engine Condition Levers (ECL) from ground to stop, flight engineer will, to the best extent possible, determine if the interposer blocks on the aft rotor head are in position and that all forward and aft droop stops are attached. If an interposer block or droop stop are not in place, the flight engineer will notify the pilot in command.  All non essential per- sonnel will evacuate the aircraft to a safe location.  If  possible,  crew  will  contact maintenance and attempt to engage inter- poser block with high pressure stream or prepare  aircraft  for  shutdown  in  such  a way as to minimize damage to aircraft and components and prevent injury to person- nel.  If  interposer  blocks  appear  to  be  in place and no droop stops are missing, the flight engineer will clear the pilot to shut- down the first engine. After the first engine is shut down, the flight engineer will ob- serve the rotor tip path of the forward and aft  rotor  heads.  A  rotor  blade  drooping significantly lower than the other blades indicates  a  missing  droop  stop.  In  this case the remaining running engine’s ECL should be advanced until sufficient rotor RPM is achieved to lift rotor blades off the stops  to  insure  no  blade  contact  with airframe and maintenance is contacted to prepare  aircraft  for  an  emergency  shut- down  that  will  minimize  damage  to  the aircraft and injury to the personnel. NOTE Aft  landing  gear  ground  proximity  switches are   not   actuated   during   a   water   landing. Therefore, longitudinal cyclic pitch actuators must be manually set to ground position prior to engine shutdown on the water. 16.   ENG COND levers — GND, start 2 minutes cool-down. NOTE If DECU display is other than 88, refer to the DECU BIT Fault Code List/Matrix. F 17. 714A DECU  SHUTDOWN  BIT  —  Check displays read 88. 18.   FUEL CONTR switches — Set as follows: a.   XFEED switch — Close. b.   FUEL PUMP switches — OFF.   c.   REFUEL STA switch — As required. WARNING Personnel injury or death may occur and damage to the airframe and rotor systems will occur if the forward or aft rotor head rotor blade droop stop(s) are missing or the interposer blocks on the aft rotor head are not engaged. Prior to moving Engine Condition  Levers  (ECL)  from  ground  to stop, the flight engineer will, to the best extent possible, determine if the interpos- er  blocks  on  the  aft  rotor  head  are  in position and that all forward and aft droop stops are attached. If an interposer block or  droop  stop  is  not  in  place,  the  flight engineer will notify the pilot in command. If  the  interposer  blocks  appear  to  be  in place  and  no  droop  stops  missing,  the flight engineer will clear the pilot to shut down the first engine. After the first engine is shut down, the flight engineer will ob- serve the rotor tip path of the forward and aft  rotor  heads.  A  rotor  blade  drooping significantly lower than the other blades indicates a missing droop stop. F 19.   DROOP STOPS — Engaged. 20. ENG  COND  levers  —  STOP  after  2 minute cool-down. NOTE Monitor   temperatures   during   shutdown.   If temperatures  rise  above  350_C,  motor  en- gine    immediately    until    temperature    de- creases below 260_C. Both engines cannot be motored at the same time. 21.   Avionics — OFF. FO 22.   Radar Altimeters — OFF. O  23. EAPS FAN Switches — OFF.