TM 1-1510-223-10 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, 0C....Exceeds Structural Limit of 16,200 lbs 9000 ft, -4C...Exceeds Structural Limit of 16,200 lbs 7600 ft, 0C…Exceeds Structural Limit of 16,200 lbs Since    these    weights    are    all    greater    than    the maximum takeoff weight limitation of 16,200 Ibs, there is no additional limitation to meet enroute weight requirements.  Anytime the value is less than 16,200 Ibs, 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 trp. f. Minimum    Static    Takeoff    Power    (Ice    Vanes Retracted).   Enter the graph at 15C FAT and 3499 feet pressure altitude: Minimum Static Takeoff Power ...................... 93.7% g. Takeoff Speeds.    Tables  are  provided  for  take- off   decision   speed   (VI),   rotation   speed   (VR),   takeoff safety  speed  (V2),  and  all-engines  takeoff  safety  speed (V50.) 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, 10C and 20C FAT, and 16,000 pounds takeoff weight,  then  interpolate  to  find  the  actual  values  for  the specified conditions: Flaps up  .........................................Flaps Approach V₁  .............................................116 KTS, 107 KTS V_R ...............................................22 KTS, 112 KTS V₂ .   .......................................... 127 KTS, 116 KTS V₅₀  ............................................ 140 KTS, 128 KTS 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 15C,  3499  feet  pressure  altitude,  16,000  pounds,  1.9% downhill    runway    gradient,    and    10    knots    headwind component, and obtain the following results: Takeoff Distance (FLAPS UP) .......................4967 ft Takeoff Distance (FLAPS APPROACH)   ........3892 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)  ..........5802 ft Accelerate-Stop Distance (FLAPS APPROACH). 4739 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) ...............6583 ft Accelerate-Go Distance (FLAPS APPROACH) .5357 ft The    minimum    recommended    runway    length    is    the longest    of    the    distances    determined    above    for    the selected  flap  setting.    The  accelerate-go  distance  (flaps up)   would   exceed   the   available   runway   length,   so   a flaps-approach  takeoff  must  be  calculated  if  it  is  desired to  allow  for  the  accelerate-go  distance  (which  is  not  a regulatory requirement, but a recommended practice). i. Takeoff  Path  One  Engine  Inoperative.    Graphs are provided to estimate the horizontal distance required to  reach  a  height  of  1500  feet,  or  the  minimum  climb gradient  required  to  clear  an  obstacle  along  the  takeoff flight path.  If clearance of obstacles beyond the runway is   required,   these   results   may   restrict   takeoff   weight accordingly. The   takeoff   distance   extends   from   brake   release   to reference zero, which is the point at which the aircraft is 50  feet  above  the  runway.    The  net  takeoff  flight  path begins at liftoff and consists of the following segments: 1. The first segment climb extends from liftoff to    the    point    where    the    landing    gear completes     the     retraction     cycle.          The airspeed is maintained at V₂. 2. The  second  segment  climb  begins  at  the end  of  the  first  segment  and  extends  to 500  feet  above  the  runway.    The  airspeed during the second segment is V₂. 3. The acceleration and flap retraction segment  consists  of  an  acceleration  from V₂ to V_ENR at a constant height of 500 feet. If    a    flaps-approach    takeoff    was    made, begin flap retraction at V_ENR. 4. The third segment climb begins when one- engine-inoperative climb speed is reached and  flaps  are  fully  retracted  at  500  feet, and 7-6  Change 2