TM 1-1510-224-10 (2) Purpose.  This graph is used to determine range  in  nautical  miles  for  various  fuel  loads  and  fuel tank   combinations,   given   pressure   altitude   in   feet   and true  airspeed  in  knots.    Range  allows  for  start,  taxi,  and runup;  includes  cruise  climb  descent;  and  allows  for  45 minutes   reserve   fuel   at   maximum   range   power.      At 16,620   pounds   ramp   weight   the   maximum   zero-fuel weight limitation of 13,100 pounds would be exceeded at fuel loading less than 3520. aw. Maximum Range Power at 1500 RPM. (1) Description.    The  Maximum  Range  Power at  1500  RPM  tables  (fig.    7A-64  through  7A-71)  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 by   approximately   10%.      Fuel   flow   will   decrease   by approximately 5%, and true air speed will be reduced by approximately 10 knots. ax. Range  Profile  Maximum  Range  Power  at  1500 RPM. (1) Description.    The  Range  Profile  Maximum Range  Power  at  1500  RPM  graph  (fig.    7A-72)  depicts range at maximum range power. (2) Purpose.  This graph is used to determine range  in  nautical  miles  for  various  fuel  loads  and  fuel tank   combinations,   given   pressure   altitude   in   feet   and true  airspeed  in  knots.    Range  allows  for  start,  taxi,  and runup;  includes  cruise  climb  descent;  and  allows  for  45 minutes   reserve   fuel   at   maximum   range   power.      At 16,620   pounds   ramp   weight,   the   maximum   zero   fuel weight limitation of 13,100 pounds would be exceeded at fuel loading less than 3520 pounds. ay. Loiter Power at 1700 RPM. (1) Description.      The   Loiter   Power   at   1700 RPM  tables  (fig.    7A-73  through  7A-80)  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, fuel flow, and true airspeed will remain approximately unchanged. az. Endurance Profile Loiter Power. (1) Description.  The Endurance Profile Loiter Power    at    1700    RPM    graph    (fig.        7A-81)    depicts endurance   at   loiter   power   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  various  fuel  loads  and  fuel  tank combinations,   given   pressure   altitude   in   feet   and   true airspeed  in  knots.    Endurance  allows  for  start,  taxi,  and runup;  includes  cruise  climb  descent;  and  allows  for  45 minutes   reserve   fuel   at   maximum   range   power.      At 16,620   pounds   ramp   weight,   the   maximum   zero   fuel weight limitation of 13,100 pounds would be exceeded at fuel loading less than 3520 pounds. ba. Range Profile Full Main Tanks. (1) Description.    The  Range  Profile  Full  Main Tanks graph (fig.  7A-82) depicts range, allowing fuel for start,   taxi,   runup,   cruise   climb   and   descent,   and   45 minutes fuel reserve. (2) Purpose.  This graph is used to determine range in nautical miles for full main tanks, given pressure altitude in feet and true airspeed in knots. bb.  Endurance Profile Full Main Tanks. (1) Description.      The   Endurance   Profile   Full Main   Tanks   graph   (fig.      7A-83)   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  tanks,  given  pressure altitude in feet and true airspeed in knots. bc. Range Profile Full Main and Aux Tanks. (1) Description.    The  Range  Profile  Full  Main and    Aux    Tanks    graph    (fig.        7A-84)    depicts    range, allowing   fuel   for   start,   taxi,   runup,   cruise   climb   and descent, and 45 minutes fuel reserve. (2) Purpose.  This graph is used to determine range in nautical miles for full main and aux tanks, given pressure altitude in feet and true airspeed in knots. 7A-8