TM 1-1510-218-10 2-123 Table 2-12.  C-12 Caution/Advisory Annunciator Panels  (Continued) NOMENCLATURE COLOR CAUSE FOR ILLUMINATION AIRCRAFT EFFECTIVITY #1 IGN ON ANVIS Green #1   engine   ignition/start   switch   on   or   #1   engine   auto ignition switch armed and engine torque below 20%. All L BL AIR OFF ANVIS Green Left environmental bleed air valve closed. All R BL AIR OFF ANVIS Green Right environmental bleed air valve closed. All #2 IGN ON ANVIS Green #2   engine   ignition/start   switch   on   or   #2   engine   auto ignition switch armed and engine torque below 20%. All #2 VANE EXT ANVIS Green #2 ice vane extended. All #1 AUTOFEATHER ANVIS Green #1 engine autofeather armed with power levers advanced above 90% N₁. All AIR COND N₁ LOW ANVIS Green #2 engine RPM too low for air conditioning load. All EXTERNAL POWER ANVIS Green External power connector plugged in. All FUEL CROSS- FEED ANVIS Green Cross-feed valve open. All BRAKE DEICE ON ANVIS Green Brake deice system activated. All #2 AUTOFEATHER ANVIS Green #2 engine autofeather armed with power levers advanced above 90% N₁. All Two  annunciator panels are installed.  One is a warning  panel  with  red  fault  identification  lights,  and the  other  is  a  caution/advisory  panel  with  yellow  and green   identification   lights.      The   warning   panel   is mounted in the center of the glareshield, Figure 2-17.    The  caution/advisory  panel  is  located  on  the  center subpanel,    just    forward    of    the    control    quadrant.   Illumination    of    a    red    warning    light    signifies    the existence of a hazardous condition requiring immediate  corrective  action.    A  yellow  caution  light signifies  a  condition  other  than  hazardous  requiring pilot   attention.      A   green   advisory   light   indicates   a functional situation.  Refer to Tables 2-11 and 2-12 for a   list   of   causes   for   illumination   of   the   individual annunciator lights. In frontal view, both panels present rows   of   small   opaque   rectangular   indicator   lights.   Word printing on each indicator identifies the monitored   function,   situation,   or   fault   condition;   but cannot be read until the light is illuminated.  The bulbs of  all  annunciator  panel  lights  are tested by activating the annunciator  PRESS  TO  TEST  switch  located  on the right side of the warning panel, or the annunciator test switch located on the right subpanel.  The system is     protected     by     two    5-ampere     circuit     breakers, placarded  ANN PWR and  ANN IND, on the overhead circuit  breaker  panel,  Figure  2-16.    The  annunciator system lights are dimmed when the  MASTER PANEL LIGHTS    switch    is    actuated    and    the    pilot's    flight instrument  lights  are  on.    The  lights  are  automatically reset  to  maximum  brightness  if  any  of  the  following conditions exist. (1)   Main  aircraft  power  (both  dc  generators) is off. (2)   The  INST  INDIRECT  LIGHTS  switch  is on. (3)   The  MASTER PANEL LIGHTS switch is off. (4)   The  MASTER PANEL LIGHTS switch is ON and the PILOT INST LIGHTS switch is OFF. c.   Master  Warning Light  C  D1  .    A  MASTER WARNING    light   (red)   is   provided   for   the   copilot, located on the right side of the glareshield, Figure 2-17.   Any time a warning light illuminates, the MASTER WARNING light will illuminate and will stay illuminated until the condition  is  corrected  and/  or  the MASTER   WARNING   light   is   pressed   to   reset   the circuit.    If  a  new  condition  occurs,  the  light  will  be reactivated  and  the  applicable  annunciator  panel  light will illuminate.