TM  1-1520-240-10 8-2-8            * 20.   Cyclic trim — Check GND position. F* 21.  Rotor blades — Check position. Make sure that a rotor blade is not within  30_ of the centerline of the fuselage throughout con- trol check. * 22.   AFCS SYSTEM SEL switch — Check as fol- lows: a.   Select individual system and check oppo- site AFCS caution capsule remains on. b.   Select BOTH and check both AFCS cau- tion capsules go out. c.   AFCS SYSTEM SEL switch — OFF. LF* 23.   Flight   control   travel   and   hydraulics   — Check as follows: (For thru flights, complete steps  b  thru  e  with  FLT  CONTR  switch  — BOTH). CAUTION If a helicopter is parked on a slope greater than 4_, longitudinal stick travel may be re- stricted  to  less  than  7  inches  forward  (up slope) or 4 inches aft (down slope). NOTE Mixing of flight control inputs during ground op- eration on a single hydraulic system should be avoided. If the Flight Controls are moved rapidly or erratically during the control check, unusual vibrations may be felt, or flight boost hydraulic fail indication may result. NOTE Check caution capsules as the check is being performed.   With   slow   smooth   flight   control inputs,  check  each  axis  individually  thru  full travel for smoothness of operation. Check for corresponding  movement  of  the  fore  and  aft rotors during the check. a.   FLT CONTR hydraulic switch — 1 ON. b.   Check cyclic for freedom of movement in all quadrants. Check for a minimum of  7  inches  forward  and  4  inches  aft travel. c.   Check thrust through full travel for free- dom of movement and magnetic brake for proper operation. d.   Check pedals through full travel for free- dom of movement. e.   Position the cyclic and pedals at neutral, thrust at ground detent. f.   FLT CONTR hydraulic switch — 2 ON, Repeat steps b thru e. g.   FLT CONTR hydraulic switch — BOTH. 24.   Avionics — Perform operational check and set as required. O 25.   HUD — Program as required. NOTE If the DECU display is other than 88, place the ENG COND levers to STOP, turn B/U PWR switch  off,  and  remove  all  power  from  the DECU by pulling the respective ENGINE PRI and REV CONT circuit breakers on the PDP. Reset circuit breakers and perform another DECU prestart BIT. If other than 88’s consult DECU Fault Code List/Matrix in Chapter 2. LF* 26.   ^714ADECU PRESTART BIT — Perform as follows: a.   B/U PWR switch — ON. b.   Wait until ENG FAIL, FADEC, and REV caution lights go out. c.   ENG COND levers — GND. F d.   DECUs — Check displays read 88. e.   ENG COND LEVERS — STOP. 27. 712 ENGINE BEEP TRIM switch (NO. 1 & 2) — Decrease for 8 seconds. * 28.   Ignition Lock switch — ON. F* 29.  Area — Clear for start. CAUTION Personnel must stay clear of the EAPS for exhaust when the fans are operating. Sand and debris within the EAPS will be ejected. NOTE The EAPS fans have high start up electrical power requirements. To prevent an overload, the fans must be turned on one at a time. The first fan must be allowed to stabilize for 10 - 15 seconds before the second fan is turned on. O* 30. EAPS  Fans  —  On  (delay  10-15  seconds between turning on NO. 1 and NO. 2). CAUTION The flight controls must be manned any time the helicopter is on the ground with rotors turning. NOTE Either engine may be started first.