TM 1-1510-225-10 2-67 NOTE In turbulence or during maneuvers, the NO TRANSFER indicator lights may momentarily   illuminate   after   the   auxiliary fuel has completed transfer. d.  Fuel   Transfer   Pumps.     The   auxiliary   tank fuel   transfer   system   automatically   transfers   the   fuel from the auxiliary tank to the nacelle tank without pilot action.      Motive   flow   to   a   jet   pump   mounted   in   the auxiliary  tank  sump  is  obtained  from  the  engine  fuel plumbing  system  downstream  from  the  engine  driven boost  pump  and  routed  through  the  transfer  control motive  flow  valve.   The motive flow valve is energized to the open position, by the control system, to transfer auxiliary  fuel  to  the  nacelle  tank  to  be  consumed  by the engine during the initial portion of the flight.  When an  engine  is  started,  pressure  at  the  engine  driven  boost pump closes a pressure switch, which, after a 30 to   50   second   time   delay   to   avoid   depletion   of   fuel pressure   during   starting,   energizes   the   motive   flow valve.  When auxiliary fuel is depleted, a low-level float switch de-energizes the motive flow valve after a 30 to 60    second    time    delay.        This    time    delay    function prevents   cycling   of   the   motive   flow   valve   due   to sloshing  fuel.    If  the  motive  flow  valve  or  associated circuitry  fails,  the  loss  of  motive  flow  pressure,  when there is still fuel remaining  in the auxiliary fuel tank, is sensed   by   a   pressure   switch   which   illuminates   a yellow left or right indicator light on the fuel management panel, placarded NO TRANSFER.   During engine start, the pilot should note that the   NO TRANSFER indicator light extinguishes 30 to 50 seconds  after  engine  start.    If  auxiliary  tanks  are empty,   the    NO   TRANSFER   indicator   light   will   not illuminate.    A  manual  override  is  incorporated  as  a backup   for   the   automatic   transfer   system.      Manual override  is  initiated  by  placing  the    AUX   TRANSFER  switch,  located  on  the  fuel  management  panel,  to  the OVERRIDE   position.   This   will   energize   the   transfer control  motive  flow  valve.    The  transfer  systems  are protected by two 5-ampere circuit breakers, placarded AUX  TRANSFER  LEFT  /  RIGHT,  located  on  the  left sidewall circuit breaker panel. e.   Fuel   Gauging   System.      Fuel   quantity   is measured by a capacitance-type fuel gauging system.   Two  fuel  gauges,  one  for  the  left  and  one  for  the  right fuel system, read fuel quantity in pounds.  A maximum of   3%   error   may   be   encountered   in   each   system; however,  the  system  is  compensated  for  fuel  density changes due to temperature excursions. f.    Fuel Management Panel. The fuel management    panel    is    located    on    the    left    cockpit sidewall.      It   contains   the   fuel   gauges,   standby  fuel pump  switches,  crossfeed  valve  switch,  fuel  gauging system control switch, NO TRANSFER indicator lights, and auxiliary transfer override switches. (1)   Fuel  Gauging  System  Control  Switch.  A switch    on    the    fuel    management    panel,    placarded FUEL  QUANTITY  MAIN  /  AUXILIARY,  controls  the fuel gauging system.  When the switch is in the  MAIN position, the fuel gauges read the total fuel quantity in the left and right main fuel systems.  When the switch is in the AUXILIARY position, the fuel gauges read the fuel quantity in the left and right auxiliary tanks only. (2)   Standby    Fuel    Pump    Switches.        Two switches   on   the   fuel   management   panel,   placarded STANDBY   PUMP   ON   /   OFF,  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 boost 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    L    FUEL    PRESS    or    R    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)   Auxiliary Fuel Transfer Override Switches.      Two   switches   on   the   fuel   management panel, placarded AUX TRANSFER     OVERRIDE     /   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.    If  either  transfer  system  fails to   operate,   the   fault   condition   is   indicated   by   the MASTER   CAUTION  annunciators  on  the  glareshield and   a   steadily   illuminated   yellow   left    or    right    NO TRANSFER  indicator  light  on  the  fuel  management panel. (4)   Fuel Crossfeed Switch. The fuel crossfeed   valve   is   controlled   by   a   3-position  switch, placarded  CROSSFEED  FLOW / OFF, located on the fuel management panel. 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 system selection with  a  simplified  diagram  on  the  fuel  control