TM 55-1510-222-10 tank  cover,  adjacent  to  the  filler  neck.    A  small  sight window in the upper wing skin permits observation of the gage. e. Fuel Management Panel.  The fuel management panel  is  located  in  the  cockpit  overhead  between  the pilot and copilot.  It contains the fuel gages, standby fuel pump   switches,   crossfeed   valve   switch,   fuel   gaging system control switch, and transfer control switches. (1 Fuel   gaging  system  control  switch.      A switch    on    the    fuel    management    panel    (fig.    2-16) placarded    FUEL    QUANTITY,    MAIN    -    AUXILIARY, controls  the  fuel  gaging  system.    When  in  the  MAIN position the fuel gages read the total fuel quantity in the left and right wing fuel system.  When in the AUXILIARY position the fuel gages read the fuel quantity in the left and right auxiliary tanks only. (2) Standby     fuel     pump     switches.          Two switches,  placarded  STANDBY  PUMP  -  ON,  located  in the   fuel   management   panel   (fig.   2-16),   individually control     a     submerged     fuel     pump     located     in     the corresponding   nacelle   tank.      During   normal   aircraft operation both switches should be OFF, so long as the engine-driven fuel pumps are operative. NOTE Both  standby  pump  switches  shall  be off  during  crossfeed  operation.    The loss  of  fuel  pressure  due  to  failure  of an   engine   driven   boost   pump,   will illuminate the MASTER WARNING annunciators  on  the   glareshield,  and will  illuminate  the  respective  #1  FUEL PRESS or #2 FUEL PRESS annunciator on the warning annunciator   panel.      Turning   on   the STANDBY   PUMP   will   extinguish   the FUEL PRESS annunciator. The MASTER WARNING annunciators must be manually reset. (3) Fuel    transfer    control    switches.        Two switches   on   the   fuel   management   panel   (fig.   2-16), placarded AUX XFER OVRD - AUTO individually control operation  of  the  fuel  transfer  pumps.    During  normal operation  both  switches  are  in  AUTO,  which  allows  the system to be automatically actuated by fuel flow to the engine.    If  either  transfer  system  fails  to  operate,  the fault  condition  is  indicated  by  the  MASTER  CAUTION annunciators on the glareshield and a steadily illuminated  amber  #1  NO  FUEL  XFR  or  #2  NO  FUEL XFR annunciator on the caution annunciator panel. Figure 2-19.  Auxiliary Fuel Tank Mechanical Fuel Gage (4) Fuel crossfeed switch.  The fuel crossfeed valve   is   controlled   by   a   3-position   switch   (fig.   2-16), located    in    the    fuel    management    panel,    placarded CROSSFEED - OFF.  Under normal flight conditions the switch  is  left  in  the  OFF  position.    During  emergency single  engine  operation,  it  may  become  necessary  to supply fuel to the operative engine from the fuel system on    the    opposite    side.        The    crossfeed    system    is placarded for fuel selection with a simplified diagram on the overhead fuel control panel.  Place the standby fuel pump switches in the off position when crossfeeding.  A lever  lock  switch,  placarded  CROSSFEED,  is  moved from  the  center  OFF  position  to  the  left  or  to  the  right, depending  on  direction  of  fuel  flow.    This  opens  the crossfeed valve and energizes the standby pump on the side from which crossfeed is desired.  During crossfeed operation  with  firewall  fuel  valve  closed,  auxiliary  tank fuel  will  not  crossfeed.    When  the  crossfeed  mode  is energized, a green FUEL CROSSFEED annunciator on the  caution/  advisory  panel  will  illuminate.    Crossfeed system   operation   is   described   in   Chapter   9.      The crossfeed   valve   is   protected   by   a   5-ampere   circuit breaker placarded CROSSFEED located in the overhead circuit breaker panel (fig. 2-6). 2-37