TM 1-1510-218-10 8A-14 g.   AUTOFEATHER switch – ARM. h.   AUTO IGN switches – Off. H 4.   Overspeed  governors  and  rudder  boost  – Check as required. a.   RUDDER BOOST switch – On. b.   PROP levers – HIGH RPM. c.   LEFT PROP GOV TEST switch – Hold in TEST position. d.   Left    POWER    lever    –    Increase    until propeller   is   stabilized   at   1830   RPM   – 1910  RPM.    Continue  to  increase  until rudder   movement   is   noted.      Observe ITT/TGT   and   torque   limits   and   PROP remains    stabilized    at    1830    RPM    – 1910 RPM. e.   POWER lever – Retard to IDLE. f.    Repeat  steps  c.,  d.,  and  e.  for  the  right engine. H 5.   Primary governors – Check as required. a.   POWER levers – Set 1800 RPM. b.   PROP   levers   –   Retard   to   FEATHER detent. Note propellers stabilize between 1600 and 1640 RPM. c.   PROP    levers    –    HIGH    RPM.        Note propellers return to 1800 RPM. H 6.   Engine ice vanes – Check. a.   ICE VANES – On/EXTENDED. (1)   Both advisory lights illuminated. (2)   Both bypass doors extended. (3)   Maximum   time   for   (1)   and   (2)   is 15 seconds. b.   ICE VANES – Off/RETRACTED. (1)   Both advisory lights extinguish. (2)   Both bypass doors retracted. (3)   Maximum   time   for   (1)   and   (2)   is 15 seconds. 7.   CONDITION levers – HIGH IDLE. 8.   POWER levers – IDLE. H 9.   Anti-ice/deice systems – Check. a.   Prop  deice  –  Check.    When  MANUAL mode    is    selected,    note    rise    on    DC loadmeter.         When     AUTO     mode     is selected,  monitor  prop  ammeter  for  the appropriate    number    of    seconds    and ensure    the    indicator    remains    in    the normal operating range the entire time. b.   Windshield heat – Check. Note increases   on   the   loadmeter   and   cycle through both normal and high settings. NOTE If    windshield    heat    is    needed    prior    to takeoff, use NORMAL setting for a minimum  of  15  minutes  prior  to  selecting HIGH  to  provide  adequate  preheating  and minimize the effects of thermal shock.  The windshield  heat  thermostat  will  invalidate the check in OAT above 20 to 30 C. c.   All anti-ice/deice switches – OFF. d.   Surface deice system – Check. H 10.  Vacuum and pneumatic system – Check. a.   LEFT BLEED AIR VALVE – OFF. (1)   Pneumatic    and    suction    pressures remain normal. (2)   L BL AIR OFF annunciator illuminates. (3)   Both    BL    AIR    FAIL    annunciators remain extinguished. b.   RIGHT BLEED AIR VALVE – OFF. (1)   Pneumatic    and    suction    pressures read zero. (2)   Both BL AIR OFF and BL AIR FAIL annunciators illuminated. c.   LEFT BLEED AIR VALVE – ON/OPEN. (1)   Pneumatic    and    suction    pressures return to normal. (2)   L BL AIR FAIL annunciator extinguished. d.   RIGHT BLEED AIR VALVE – ON/OPEN. (1)   R BL AIR OFF annunciator extinguished. (2)   Both    BL    AIR    FAIL    annunciators extinguished. H 11.  Automatic   Flight   Control   System   –   When the PC determines that an autopilot check is required, check as follows: a.   Altitude alert.