TM 1-1510-223-10 NOTE Circuit  breakers  should  not  be  reset  more than once until the cause of circuit malfunction     has     been     determined     and corrected. 2. Nonessential circuit - Do not reset. (3.)  Essential circuit - Reset once. g. BATTERY CHARGE Annunciator Illuminated.          If the     BATTERY     CHARGE     caution annunciator    illuminates    during    normal    cruise    flight, perform the following: (1.)  Battery  ammeter - Check, note indication, and monitor for increasing load.  If load continues to increase, turn battery switch OFF. (2.)  BATTERY switch - OFF. NOTE The battery may be turned back ON only for gear   and   flap   extension   and   approach   to landing.    Battery  may  be  usable  after  a  15 20 minute cool down period. (3.)  BATTERY   switch   (landing   gear/nap   extension only) - ON. h. AVIONICS MASTER POWER Switch Failure. If   the   AVIONICS   MASTER   POWER   Switch   fails   to operate in the ON position, perform the following: (1.)  AVIONICS  MASTER  CONTR  circuit  breaker  - Pull. NOTE The   avionics   power   relay   is   normally   hot Pulling   the   AVIONICS   MASTER   CONTR circuit   breaker   will   remove   power   to   the relay,  thus  allowing  electrical  power  to  the associated busses. i. BAT FEED FAULT Annunciator Illuminated. If     the BAT FFEED FAULT caution annunciator illuminates, perform the following: (1.)  BATTERY switch - RESET, then ON. 9-28.  EMERGENCY DESCENT. The   following   procedure   assumes   the   structural integrity  of  the  aircraft  and  smooth  flight  conditions.    If structural  integrity  is  in  doubt,  limit  speed  as  much  as possible, reduce rate of descent if necessary, and avoid high    maneuvering    loads.        For    emergency    descent, perform the following: 1. POWER levers - IDLE 2. PROP levers - HIGH RPM. 3. Flaps - APPROACH 4. Gear - DN. 5. Airspeed - 179 KIAS (0.472 Mach) maximum. NOTE Windshield defogging may be required. 9-29.  FLIGHT CONTROL MALFUNCTIONS. Use   the   following   procedures,   as   applicable,   for flight control malfunctions. a. Autopilot   Emergency   Disconnection.      The autopilot   can   be   disengaged   by   any   of   the   following methods: 1. Pressing   the   AP   &      YD/TRIM   DISC   switch (control wheels). 2. Pressing  the  AP  ENGAGE  pushbutton  on  the autopilot controller (pedestal extension). 3. Pressing   the   GO-AROUND   switch   (left   power lever, yaw damper will remain on). 4. Pulling   the   AP   CONTR   and   AFCS   DIRECT circuit breakers (overhead control panel). 5. Setting   AVIONICS   MASTER   POWER   switch (overhead control panel) to the off (aft) position. 6. Setting   aircraft   MASTER   SWITCH   (overhead control panel) to the OFF position 7. Setting the AUTO PLT power switch (over-head control panel) to off position. b. Yaw Damp Emergency Disconnection.   The yaw  damp  can  be  disengaged  by  any  of  the  following methods: 1. Pressing   the   AP   &      YD/RIM      DISC   switch (control wheels). 2. Pressing  the  AP  ENGAGE  pushbutton  on  the autopilot controller (pedestal extension). 3. Setting  the  RUDDER  BOOST/YAW  CONTROL TEST  switch  (pedestal  extension)  to  the  YAW CONTROL TEST position 4. Pulling   the   AP   CONTR   circuit   breaker   (over- head control panel). 5. Pulling   the   RUDDER   BOOST   circuit   breaker (overhead control panel). 9-11