TM 1-1510-223-10 Table 7-4.  Example Time, Fuel, and Distance TIME FUEL DISTANCE ITEM MIN POUNDS NM Start, Runup, Taxi, and Takeoff Acceleration 0.0 120 0 Climb 22.0 341 57 Cruise 21.9 284 101 Descent 130 171 59 TOTAL 56 9 916 217 Block Speed: 217 NM Divided by 56 9 Minutes = 229 Knots. BT03669 Maximum   zero   fuel   weight   limitation   will   not   be exceeded Anytime  the  zero  fuel  weight  exceeds  the  maximum zero    fuel    weight    limit,    the    excess    weight    must    be offloaded   from   payload   only   (i   e.,   not   from   fuel).      If desired,  additional  fuel  may  then  be  added.    However, the  foregoing  calculations  will  remain  unchanged  only  if the   fuel   added   is   equal   in   weight   to   the   payload   off- loaded,  since  only  then  will  the  ramp  weight  and  takeoff weight remain the same as before. n. Range and Endurance.     Estimates  of  the  effect of   fuel   load   and   power   setting   on   aircraft   range   and endurance   can   be   determined   from   the   Range   and Endurance  Profile  graphs.    The  range  of  a  mission  at normal  cruise  power  can  be  determined  by  entering  the RANGE  PROFILE  NORMAL  CRUISE  POWER  graph  at 25,000 feet, reading right to the anticipated fuel load and down  to  the  resulting  range.    This  chart  indicates  that  a fuel  load  as  low  as  1500  pounds  would  be  sufficient  for the  planned  217  nautical  mile  mission  from  Billings  to Casper.  The available range with full main and auxiliary tanks  (3631  pounds)  for  a  flight  at  25,000  feet  can  be determined to be 910 nautical miles.  If additional range is   required,   either   a   higher   altitude   or   a   lower   power setting could be selected.  To determine the range with a maximum  fuel  load,  enter  the  RANGE  PROFILE  FULL MAIN AND AUX TANKS graph at 25,000 feet, read right to  the  desired  power  setting  and  down  to  the  resulting range.      This   chart   shows   that   for   a   full-fuel   mission, range  can  be  increased  from  910  to  973  nautical  miles by reducing power to maximum  range power. The  aircraft  endurance  can  be  determined  from  the various endurance profile graphs in a similar manner. It should be noted that these graphs are all based on standard  day  temperatures,  and  the  range  graphs  are also  based  on  zero  wind  If  forecast  temperatures  differ from  standard  values  or  if  headwinds  are  expected,  a more rigorous mission analysis should be accomplished. o. Landing Example . (1) Weight.    The  estimated  landing  weight  is determined  by  subtracting  the  fuel  usage  expected  for the trip from the ramp weight: Ramp Weight ...............................................16,120 Fuel Usage Expected for Total Trip  ...........(-)916 Ibs Landing Weight .  ................................... 15,204 lbs Maximum Landing Weight (Chapter 5 - LIMITA- TIONS) .................................................. 15,400 lbs Anytime the maximum landing weight limitation would be exceeded,  off-load  the  excess  from  useful  load  prior  to takeoff, or burn off the excess from excess fuel (i e., not from reserve fuel) before landing. (2) Normal     landing     distance     flaps     down. Enter   the   graph   at   20°C,   5998   feet,   15,204   pounds, 0.3%     uphill     runway     gradient,     10     knots     headwind component, and read the following: Landing Distance Over 50-Foot Obstacle   ......3437 ft Table 7-5.  Example Fuel Flow (Ibs/hr) WEIGHT POUNDS ISA ISA +5°C ISA 10°C 16,000 747.0 --- 688.0 15,000 748.0 718.75 689.5 14,000 749.0 --- 691.0 Total Fuel Flow = 718.75 Ibs/hr Reserve Fuel = 45 minutes x 718.75 Ibs/hr =539 lbs BT3T670 Change 2  7-11