TM 55-1510-219-10 control   clockwise   from   OFF   turns   the   lights   on   and increases their brilliance. (3) Engine instrument lights.  Each individual engine instrument contains internal lamps for illumination.  The circuit is protected by a 7 1/2ampere circuit  breaker  placarded  FLT  INST  on  the  overhead circuit breaker panel (fig.  2-26).  Control is provided by a rheostat switch placarded ENGINE INST LIGHTS OFF BRT on the overhead control panel (fig.  2-18).  Turning the  control  clockwise  from  OFF  turns  the  lights  on  and increases their brilliance. (4) Flood light.  A single overhead flood light is installed.  It provides overall illumination of the entire cockpit  area.    The  circuit  is  protected  by  a  5-ampere circuit    breaker    mounted    beneath    the    battery    and connected  to  the  emergency  battery  bus.    Control  is provided  by  a  rheostat  switch  placarded  OVERHEAD FLOODLIGHT-OFF-BRT on the overhead control panel (fig.    2-18).    Turning  the  control  clockwise  from  OFF turns the light on and increases its brilliance. (5) Overhead   panel   lights.      Lamps   on   the overhead  circuit  breaker  panel,  control  panel,  and  fuel management   panel   are   protected   by   a   7   1/2ampere circuit     breaker     placarded     LIGHTS     OVHD     on     the overhead  circuit  breaker  panel  (fig.    2-26).    Control  is provided  by  a  rheostat  switch  placarded  OVERHEAD PANEL    LIGHTS-OFF-BRT    on    the    overhead    control panel (fig.  2-18).  Turning the control clockwise from off turns the lights on and increases their brilliance. (6) Subpanel  and  console  lights.    Lights  on the   pilot's   and   copilot's   subpanels,   console   edge   lit panels and pedestal extension panels are protected by a 7 1/2-ampere circuit breaker placarded LIGHTS SUBPANEL    &    CONSOLE    on    the    overhead    circuit breaker  panel  (fig.    2-26).    Control  is  provided  by  two rheostat  switches  placarded  SUBPANEL  or  CONSOLE LIGHTS-OFF-BRT  on  the  overhead  control  panel  (fig. 2-18).  Turning the control clockwise from OFF turns the lights on and increases their brilliance. (7) Free air temperature light.  Two post lights are  mounted  adjacent  to  the  free  air  temperature  gage on  the  left  cockpit  sidewall  trim  panel.    The  circuit  is protected  by  a  7  1/2-ampere  circuit  breaker  placarded FLT INST on the overhead circuit breaker panel (fig.  2- 26).      Control   is   provided   by   a   push   button   switch adjacent to the gage.  No intensity control is provided. b. Cabin Lighting. (1) Interior   lights.      Three   cabin   lights   are installed  in  the  overhead  trim.    The  circuit  is  protected by a 10-ampere circuit breaker placarded CABIN on the overhead  circuit  breaker  panel  (fig.    2-26).    Control  is provided    by    a    switch    placarded    CABIN    LIGHTS- BRIGHT-DIM-OFF on the subpanel (fig. 2-6). (2)    Threshold  and  spar  cover  lights.    A  spar cover light is installed on the left side of the sunken aisle immediately  aft  of  the  main  spar  cover.    Both  circuits are  protected  by  a  5-ampere  circuit  breaker  mounted beneath  the  battery  and  connected  to  the  emergency battery  bus.    Both  lights  are  controlled  by  the  switch mounted  forward  of  the  airstair  door.    If  the  lights  are illuminated,   closing   the   cabin   door   will   automatically extinguish them. (3) Dome  light.    A  dome  light  is  installed  in the   baggage   area,   in   the   overhead.      The   circuit   is protected    by    a    5-ampere    circuit    breaker    mounted beneath  the  battery  and  connected  to  the  emergency battery  bus.    Control  is  provided  by  a  switch  mounted adjacent to the light. (4) Cabin utility light.    There  is  a  cabin  utility light  adjacent  to  each  cabin  light.    Each  utility  light  is individually controlled by a rheostat placarded OFF-ON- BRT on the back of the light.  There is a momentary ON switch   in   the   center   of   the   rheostat.      Each   light   is capable of producing a red or white spotlight by turning the selector on the front of the light.  To remove the light from  the  stationary  position,  loosen  the  retaining  screw directly below the light escutcheon and pull down on the light.  The light is connected to the light housing by an 11  inch  coiled  cord  that  extends  to  approximately  50 inches.  The CABIN LIGHTS switch must be on for utility lamps to operate. 2-76.  EMERGENCY LIGHTING. a. Description.    An  independent  battery  operated lighting   system   is   installed.      The   system   is   actuated automatically  by  shock,  such  as  a  forced  landing.    It provides    adequate    lighting    inside    and    outside    the fuselage to permit the crew to read instruction placards and locate exits.  An inertia switch, when subjected to a 2 3 G shock, will illuminate interior lights in the cockpit, forward and aft cabin areas, and exterior lights aft of the emergency  exit  and  aft  of  the  cabin  door.    The  battery power  source  is  automatically  recharged  by  the  aircraft electrical system. b. Operation.        An    emergency    lights    override switch, located on the overhead control panel (fig.  218), is  provided  to  turn  the  system  off  if  it  is  accidentally actuated.      The   switch   is   placarded   EMERG   LIGHTS OVRD  OFF-RESET-AUTO-TEST.    Should  the  system accidentally actuate, placing the switch in the momentary OFF RESET position will extinguish 2-69