TM 1-1510-224-10 e. Takeoff Weight The following examples illustrate the use of graphs which may restrict takeoff weight. NOTE Do  not  exceed  the  maximum  takeoff weight limitation of 16,500 pounds. (1) Maximum  takeoff  weight  as  limited  by  tire speed.    Enter  the  graphs  at  15C,   3499   ft,   10   knots headwind component, and read: Flaps Up......... Exceeds Structural Limit of 16,500 lbs Flaps Approach.... Exceeds Structural Limit of 16,500 lbs (2) Maximum takeoff weight to achieve positive one-engine-inoperative climb at liftoff.  Enter the graphs at 3499 feet pressure altitude, 15C, and read: Flaps Up................................................ 16,500  lbs Flaps Approach ...................................... 16,500 lbs (3) Maximum  enroute  weight  for  50-ft/minute one-engine-inoperative climb. To determine the maximum  takeoff  weight,  the  weight  of  the  fuel  used  to reach the MEA is added to the maximum enroute weight obtained     from     the     Service     Ceiling     -     One     Engine Inoperative  graph  (fig.    7-38).    Use  the  Time,  Fuel,  and Distance  to  Cruise  Climb  graph  (fig.    7-39)  to  determine the  weight  of  the  fuel  used  to  climb.    Use  the  Cruise Power tables to determine the weight of the fuel used to cruise to each MEA. Enter the Service Ceiling - One Engine Inoperative  graph  (fig.    7-38)  at  the  conditions  for  each enroute   MEA.      For   example,   enter   the   graph   at   the highest  MEA  altitude  of  9000  feet,  and  trace  right;  enter again at the MEA FAT of -4C,  and  trace  up.    Read  the maximum  enroute  weight  at  the  MEA  at  the  intersection of the tracings. Maximum    enroute    weight    for    50-ft/min    one- engine-inoperative climb: 8000 ft, 0°C.... Exceeds Structural Limit of 16,500 lbs 9000 ft, -4°C... Exceeds Structural Limit of 16,500 lbs 7600 ft, 0°C.... Exceeds Structural Limit of 16,500 lbs Since   these   weights   are   all   greater   than   the maximum takeoff weight limitation of 16,500 Ibs, there is no additional limitation to meet enroute weight requirements.  Anytime the value is less than 16,500 lbs, add   the   fuel   required   to   climb,   plus   any   fuel   used   in cruise   before   reaching   each   MEA,   to   determine   the maximum allowable takeoff weight to meet the requirement for each route segment of the trip. f. Minimum    Static    Takeoff    Power    (Ice    Vanes Retracted).  Enter the graph at 15°C FAT and 3499 feet pressure altitude: Minimum Static Takeoff Power....................... 93.5% g. Takeoff Speeds.  Tables are provided for takeoff decision  speed  (VI),  rotation  speed  (VR),  takeoff  safety speed  (V2),  and  all-engines  takeoff  safety  speed  (VWs) In  order  to  determine  the  takeoff  speeds  for  15°C  FAT, 3499  feet  pressure  altitude,  and  16,000  pounds  takeoff weight,  enter  the  tables  at  2000  ft  and  4000  ft  pressure altitude, 100C and 20°C FAT, and 16,000 pounds takeoff weight,  then  interpolate  to  find  the  actual  values  for  the specified conditions: V₁ ...... 116 KTS (flaps up), 108 KTS (flaps approach) V_R...... 124 KTS (flaps up), 113 KTS (flaps approach) V₂ ...... 128 KTS (flaps up), 114 KTS (flaps approach) V₅₀..... 140 KTS (flaps up), 126 KTS (flaps approach) h. Minimum  Field  Length.    The  following  example illustrates  the  use  of  graphs  which  may  restrict  takeoff weight    due    to    field    length    available    under    existing conditions. (1) Takeoff distance.  Enter the graphs at 15 C,   3499   feet   pressure   altitude,   16,000   pounds,   1.9% downhill    runway    gradient,    and    10    knots    headwind component, and obtain the following results: Ground Roll (flaps up) ...................................3511 ft Takeoff Distance (flaps up) ............................4864 ft Ground Roll (flaps approach..........................2909 ft Takeoff Distance (flaps approach)..................3886 ft (2) Accelerate-stop distance. Enter the graphs   at   15C,   3499   feet   pressure   altitude,   16,000 pounds,  1.9%  downhill  runway  gradient,  and  10  knots headwind component, and obtain the following results: Accelerate-Stop Distance (flaps up) ...............5877 ft Accelerate-Stop Distance (flaps approach).....4972 ft (3)  Accelerate-go  distance.    Enter  the  graphs  at  15C, 3499    feet    pressure    altitude,    16,000    pounds,    1.9% downhill    runway    gradient,    and    10    knots    headwind component, and obtain the following results: Accelerate-Go Distance (flaps up)..................7172 ft Accelerate-Go Distance (flaps approach)........5069 ft The   minimum   recommended   runway   length   is the  longest  of  the  distances  determined  above  for  the selected flap 7-11