TM 1-1510-224-10 bd. Endurance Profile Full Main and Aux Tanks. (1) Description.  The Endurance Profile Loiter Power     at     1700     RPM     graph     (fig.          7A-85)     depicts endurance,   allowing   fuel   for   start,   taxi,   runup,   cruise climb and descent, and 45 minutes fuel reserve. (2) Purpose.  This graph is used to determine endurance  in  hours  for  full  main  and  aux  tanks,  given pressure altitude in feet and true airspeed in knots. be. One  Engine   Inoperative   Max   Cruise   Power   at 1700 RPM. (1) Description.    The  One  Engine  Inoperative Max   Cruise   Power   at   1700   RPM   tables   (fig.      7A-86 through  7A-93)  show  fuel  flow,  airspeed,  and  torque  for various flight conditions. (2) Purpose.          These     tables     are     used     to determine  fuel  flow  per  engine,  total  fuel  flow,  indicated airspeed,  and  true  airspeed,  given  pressure  altitude  in feet, indicated free air temperature and free air temperature     in     degrees     Celsius,     aircraft     weight     in pounds,    and    torque    per    engine    in    percent.        During operation  with  ice  vanes  extended,  torque  will  decrease approximately 10%, fuel flow will decrease by approximately  6%,  and  true  airspeed  will  be  reduced  by approximately 10 knots. bf. Time, Fuel, and Distance to Descend. (1) Description. The Time, Fuel, and Distance to Descend graph (fig 7A-94) depicts the time, fuel, and distance to descend. (2) Purpose.  This graph is used to determine the  time,  fuel,  and  distance  required  to  descend,  given the beginning and ending pressure altitudes in feet. bg. Climb Balked Landing. (1) Description.      The   Climb   Balked   Landing graph  (fig.    7A-95)  depicts  rate  of  climb  to  be  expected after a balked landing. (2) Purpose.  This graph is used to determine the rate of climb in feet per minute and climb gradient in percent,    given    the    free    air    temperature    in    degrees Celsius,  pressure  altitude  in  feet,  and  aircraft  weight  in pounds.    For  operation  with  ice  vanes  extended,  rate  of climb   will   be   reduced   by   approximately   300   feet   per minute.    Enter  the  graph  at  the  pressure  altitude  from which a go-around would be initiated. bh. Normal Landing Distance Flaps Down. (1) Description.        The    Normal    Landing    Distance Flaps   Down   graph   (fig.      7A-96)   depicts   normal   flaps down landing distance. (2) Purpose.  This graph is used to determine flaps  down  landing  distance,  given  free  air  temperature in    degrees    Celsius,    field    pressure    altitude,    runway gradient    in    %    up    or    down,    and    head    or    tail    wind component  in  knots.    The  wind  grids  include  factors  of 50% for headwinds and 150% for tailwinds. Components  of  reported  winds  may  therefore  be  used directly in the grids.  Weight does not significantly affect landing distance. bi. Landing Distance Flaps Up. (1) Description.    The  Landing  Distance  Flaps Up graph (fig.  7A-97) depicts landing distance with flaps up. (2) Purpose.  This graph is used to determine flaps    up    landing    distance,    given    flaps    down    landing distance.        Landing    with    flaps    full    down    is    normal procedure.    Flaps  up  landings  may  produce  tire  speeds and/or     brake     energies     that     exceed     limitation.          To determine  the  flaps-up  landing  distance,  read  from  the Normal Landing Distance Flaps Down graph, the landing distance   appropriate   to   temperature,   altitude,   runway gradient,   and   wind.      Enter   the   subject   graph   with   the derived value, and read the flaps-up landing distance. bj. Landing  Distance  One  Engine  Inoperative  Flaps Down. (1) Description.      The   Landing   Distance   One Engine    Inoperative    Flaps    Down    graph    (fig.        7A-98) depicts one engine inoperative landing distance. (2) Purpose.  This graph is used to determine one   engine   inoperative   flaps   down   landing   distance, given    the    flaps    down    normal    landing    distance.        To determine  the  one  engine  inoperative  landing  distance, read   from   the   Normal   Landing   Distance   Flaps   Down graph,  the  landing  distance  appropriate  to  temperature, altitude,  runway  gradient,  and  wind.    Enter  the  subject graph  with  the  derived  value,  and  read  the  one  engine inoperative landing distance. 7A-4.  EXAMPLES. The    following    examples    present    calculations    for flight time, block speed, and fuel required for a proposed flight   from   Billings,   Montana,   to   Casper,   Wyoming,   at flight level 250, using the conditions listed below, except as  noted.    The  desired  takeoff  weight  is  16,000  pounds, if possible. 7A-9