TM 1-1510-224-10 s. Net   Take-off   Flight   Path   First   Segment   Flaps Up. (1) Description.    The  Net  Take-off  Flight  Path First Segment Flaps Up graph (fig.  7-20) depicts the net climb   gradient   for   the   first   segment   of   a   one   engine inoperative climb. (2) Purpose.  This graph is used to determine the   climb   gradient   in   %   for   a   one   engine   inoperative climb   from   liftoff   until   the   landing   gear   completes   the retraction  cycle,  given  free  air  temperature  in  degrees Celsius,  field  pressure  altitude  in  feet,  takeoff  weight  in pounds,  and  head  or  tail  wind  in  knots.    For  operation with ice vanes extended, decrease net climb gradient by 1.2 percentage points. t. Net Take-off Flight Path Second Segment Flaps Up. (1) Description.    The  Net  Take-off  Flight  Path Second Segment Flaps Up graph (fig.  7-21) depicts the net   climb   gradient   for   the   second   segment   of   a   one engine inoperative climb. (2) Purpose.  This graph is used to determine the   climb   gradient   in   %   for   a   one   engine   inoperative climb   from   completion   of   the   landing   gear   retraction cycle,  until  reaching  500  feet  above  the  runway,  given free  air  temperature  in  degrees  Celsius,  field  pressure altitude   in   feet,   takeoff   weight   in   pounds,   and   wind component   in   knots.      For   operation   with   ice   vanes extended, decrease net climb gradient by 1.2 percentage points. u. Horizontal   Distance   From   Reference   Zero   to Third Segment Climb Flaps Up. (1) Description.  The Horizontal Distance from Reference Zero to Third Segment Climb Flaps Up graph (fig.  7-22) depicts the horizontal distance traveled to the third segment climb of a one engine inoperative climb. (2) Purpose.  This graph is used to determine the    horizontal    distance    required    for    a    one    engine inoperative  climb  from  a  point  50  feet  above  the  runway (reference zero) to a point where the third segment climb has been reached, given free air temperature in degrees Celsius,  field  pressure  altitude  in  feet,  takeoff  weight  in pounds,  and  head  or  tail  wind  component  in  knots.    For operation   with   ice   vanes   extended,   increase   free   air temperature by 11°C before entering graph. v. Maximum    Take-off    Weight    to    Achieve    One engine Inoperative Climb at Liftoff Flaps Approach. (1) Description. The Maximum Take-off Weight    to    Achieve    Positive    One-engine    Inoperative Climb at  Liftoff  Flaps  Approach  graph  (fig.    7-23)  provides  the one  engine  inoperative  liftoff  climb  performance  weight limit    as    a    function    of    field    pressure    altitude    and temperature. (2) Purpose.  This graph is used to determine the  maximum  weight  at  which  the  aircraft  can  take  off and   achieve   a   positive   rate   of   climb   after   an   engine failure  at  liftoff,  given  field  pressure  altitude  in  feet  and free  air  temperature  in  degrees  Celsius.    For  operation with  ice  vanes  extended,  add  1500  feet  to  field  pressure altitude before entering graph. w. Maximum   Take-off   Weight   as   Limited   by   Tire Speed Flaps Approach. (1)Description.        The    Maximum    Take-off    Weight    as Limited by Tire Speed Flaps Approach graph (fig.  7-24) provides the takeoff tire speed weight limit as a function of     field     pressure     altitude,     temperature,     and     wind component. (2) Purpose.  This graph is used to determine the  maximum  weight  at  which  the  aircraft  can  take  off and not exceed tire limitations, given free air temperature in degrees Celsius, field pressure altitude in feet, and head or tail wind component in knots. x. Take-off Speeds Flaps Approach. (1) Description.    The  Take-off  Speeds  Flaps Approach table (fig.  7-25) allows selection of the proper takeoff  speeds  for  takeoff  weight,  pressure  altitude,  and temperature. (2) Purpose.    This  table  is  used  to  determine V,   ,   V,   V2,   and   V50   for   each   takeoff,   given   free   air temperature in degrees Celsius, field pressure altitude in feet, and takeoff gross weight in pounds. y. Take-off Distance Flaps Approach. (1) Description.    The  Take-off  Distance  Over 50   Foot   Obstacle   Flaps   Approach   graph   (fig.      7-26) depicts   the   relationship   of   takeoff   distance   to   free   air temperature,    field    pressure    altitude,    takeoff    weight, runway gradient, and wind component. (2) Purpose.  This graph is used to determine the ground roll and total distance required to take off and clear  a  50  foot  obstacle,  given  free  air  temperature  in degrees  Celsius,  field  pressure  altitude  in  feet,  aircraft takeoff  weight  in  pounds,  runway  gradient  in  %  up  or down,  and  head  or  tail  wind  component  in  knots.    For operations  with  ice  vanes  extended,  increase  distance by 22%.  Consult 7-4