TM 1-1510-224-10 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   200C,   5998   feet,   15,199   pounds, 0.3%     uphill     runway     gradient,     10     knots     headwind component, and read the following: Ground Roll ..................................................1857 ft Total Distance Over 50-Foot Obstacle............4702 ft (3) Abnormal landing distances.  The landing distances  for  one  engine  inoperative  or  flaps  retracted can be determined as shown below. Landing  Distance  -  One  Engine  Inoperative  -  Flaps Down: Enter   the   graph   with   the   normal   landing   distance determined    in    paragraph    (2)    above    and    read    the following: Landing Distance - One Engine Inoperative - Over 50-Foot Obstacle - Flaps Down........................ 5834 feet Landing Distance - Flaps Up: Enter  the  graph  with  the  normal  landing  distance  of 4702  feet  as  determined  in  paragraph  (2)  above  and  a landing weight of 15,199 Ibs, and read the following: Flaps-Up Landing Distance Over 50-Foot Obstacle................................................... 7138 feet Approach Speed ...................................... 136 knots (4) Climb - balked landing.  Enter the graph at 20C,  6400  feet  (see  note  2  on  graph),  15,199  pounds, and read the following results: Rate of climb ......................................... 1444 ft/min Climb Gradient................................................ 9.6% p. Enroute   Instrument   Corrections.      Errors are  introduced  to  measured  airspeed  and  temperature readings   as   a   result   of   the   aircraft   speed.      For   this example,    it    has    been    assumed    that    the    aircraft    is established in level cruise flight between CZI and CPR. Pilot's Indicated Airspeed...........................158 KIAS Indicated Pressure Altitude ..................... 25,000 feet Indicated Free Air Temperature....................... -35C (1) Airspeed     calibration     -     normal     system Graph.        Enter    the    flaps-up    graph    at    the    indicated airspeed  value  of  158  knots,  read  up  reference  line  and trace left to obtain the following results: Calibrated Airspeed.................................. 161 knots (2) Altimeter     correction - normal system Graph.        Enter    the    flaps-up    graph    at    the    indicated airspeed  value  of  158  knots,  read  up  to  the  25,000-foot reference   line   and   trace   left   to   obtain   the   following results: Altimeter Correction ....................................+69 feet Add this result to the indicated pressure altitude value of 25,000 feet to obtain the corrected altitude. Actual Pressure Altitude ......................... 25,061 feet (3) Indicated outside air temperature correction   Graph.      Enter   the   graph   at   the   calibrated airspeed   value   of   161   knots,   read   right   to   the   actual pressure  altitude  of  25,051  feet  and  down  to  obtain  the following result: Temperature Correction ................................. 5.2C Compute the free air temperature by subtracting the  temperature  correction  of  5.20C  from  the  indicated temperature of -350C to obtain: Free Air Temperature..................................-40.2C. Table 7-5.  Example Fuel Flow (Ibs/hr) WEIGHT POUNDS ISA ISA +5°C ISA 10°C 16,000 744.0 - 686.0 15,000 745.0 716.25 687.5 14,000 746.0 - 689.0 Total Fuel Flow = 716.25 Ibs/hr Reserve Fuel = 45 minutes x 716.25 Ibs/hr =537 lbs BT06333 7-17