TM 1-1510-225-10 7-3 (5)   and   (6)      Maximum   weight   allowable   to achieve   a   single   engine   climb,   flaps   0%   and   40%. Refer   to   Figures   7-15   and   7-16,   Takeoff   Weight   to Achieve   Positive   One   Engine   Inoperative   Climb   at Liftoff, Flaps UP and Flaps APPROACH. Enter each of the graphs at the pressure altitude of   4000   ft.,   trace   to   the   right   until   intersecting   the correct   temperature   line,   +30    C,   then   trace   down vertically   and   read   the   maximum   allowable   takeoff weight for these conditions.  For Flaps  UP  it is 14,000 pounds.  For Flaps  APPROACH  it  is  12,750  pounds. Enter those takeoff weight limitations in the appropriate blocks of the TOLD card. (7)   and  (8)    Maximum  Weight  to  accomplish Accelerate   and   Stop   distance,   flaps   0%   and   40%. Refer  to  Figures  7-22  and  7-26,  Accelerate  –  Stop, Flaps UP and Flaps APPROACH. Enter   each   of   the   graphs   on   the   right   vertical scale, ACCELERATE-STOP FIELD LENGTH  ~ FEET, at  the  field  length  available.    In  this  example  there  is no runway overrun, therefore the field length available is the runway length of 6000 feet.  Mark that line as a baseline,  it  becomes  the  limit  for  maximum  allowable takeoff weight. Enter  the  left  side  of  the  graph  at  the  OUTSIDE AIR TEMPERATURE ~  C  at  the  forecast  temperature of   +30.      Trace   up   vertically   until   intersecting   the correct   PRESSURE   ALTITUDE   ~   FEET   line,   4000 feet.      Trace   to   the   right   until   intersecting   the   first REFERENCE    LINE.        Because    the    point    on    the REFERENCE  LINE  for  Flaps   UP  is  above  the  6000 feet     runway     length,     maintain     the     same     relative distance  between  the  guidelines  and  trace  down  until intersecting  the  6000  feet  field  length  line.    From  that point,   trace   down   vertically   to   read   the   maximum allowable takeoff weight that will allow accomplishment of   an   acceleration   to  V₁   and   stop.      The   maximum allowable takeoff weight is 12,800 pounds. Using  Figure  7-26,  utilize  the  chart  in  the  same manner.    In  this,  case  the  point  on  the  REFERENCE LINE  for  Flaps   APPROACH   is   below   the   6000   feet field  length  line,  the  accelerate-stop  distance  is  5,100 feet   and   accelerate   –   stop   can   be   accomplished   at 14,000 pounds. For  Flaps   UP   the   maximum   takeoff   weight   to achieve   Accel/Stop   is   12,800   pounds.      For   Flaps APPROACH  it  is  14,000  pounds.    Enter  those  takeoff weight   limitations   in   the   appropriate   blocks   of   the TOLD card. (9)   Maximum Weight Allowable To Accomplish the Required Single Engine Climb Gradient.    Refer  to  Figure  7-31  Climb  –  One  Engine Inoperative. A  3.3%  single  engine  climb  gradient  is  required for  all  IFR  takeoffs.    In  the  absence  of  any  Departure Procedure  (DP)  or  other  requirement,  the  3.3%  climb gradient    line    is    the    baseline    for    determining    the maximum  allowable  takeoff  weight  in  order  to  achieve that single engine climb gradient. In this example, the weather forecast for the time of  departure  is  400  feet  overcast  and  1  mile  visibility with    rain    and    haze.        The    non-standard    takeoff minimums for Airport A are 500 foot ceiling and 2 miles visibility. However, the departure may be accomplished using standard AR 95-1 takeoff minimums if a single engine climb gradient of 250 feet per  nm  can  be  achieved.    Therefore,  the  maximum allowable   takeoff   weight   to   achieve   a   single   engine climb gradient of 250 feet per nm must be determined. In Figure  7-31,  to  use  the  CLIMB  GRADIENT   ~ % scale, the required gradient of 250 feet per nautical mile must be converted to a percentage.  The method is   included   in   the   Climb   Conversion   portion   of   the TOLD  card.    The  feet  per  nautical  mile  are  divided  by 6076   (the   number   of   feet   in   a   nautical   mile)   and multiplied    by    100,    yielding    the    climb    gradient    in percent. For this example divide 250 feet per nautical mile by  6076,  then  multiply  by  100  in  order  to  convert  to  a percentage. 250 6076 x 100 = 4.1% From  the  CLIMB  GRADIENT   ~   %   scale   trace horizontally   from   4.1%   to   the   left   onto   the   graph   in order   to   establish   the   baseline   limit   for   maximum takeoff  weight  in  order  to  achieve  the  required  single engine climb gradient of 4.1%. Now,   enter   the   graph   at   the   OUTSIDE   AIR TEMPERATURE ~ C scale at +30  C.    Trace  up  until intersecting the 4000 feet PA line, trace horizontally to the   right   until   intersecting   the   REFERENCE   LINE. Because the intersecting point on the reference line is below  the  4.1%  baseline,  maintain  the  same  relative distance   between   the   guidelines   and   trace   up   until intersecting  the  4.1%  baseline.    From  that  point,  trace down to read the maximum allowable takeoff weight in order   to   achieve   a   single   engine   climb   gradient   of 4.1%.