TM 55-1500-342-23 of most helicopters, the takeoff and landing gross weight limitations  are  the  same,  and  there  is  no  "zero  fuel" restrictions).        These    values    are    computed    in    the LIMITATIONS table on the lower left-hand comer of the Form F as follows:  (a) Enter the ALLOWABLE GROSS WEIGHT  for  TAKEOFF  and  LANDING.    If  the  aircraft can   have   a   gross   weight   restriction   above   which   all weights must be fuel in the wings (zero wing fuel gross weight),  enter  the  ALLOWABLE  GROSS  WEIGHT  for LIMITING    WING    FUEL    in    the    last    column    of    the LIMITATIONS table. (b)    If      the      aircraft's      ALLOWABLE GROSS  WEIGHT  can  be  limited  by  a  taxiing  and/or ground handling gross weight, use the REMARKS section for subtracting  the  warm  up  and/or  taxi  fuel from    the  maximum  permissible  ground  handling  gross weight.      The   resulting   value   will   be   entered   in   the ALLOWABLE  GROSS  WEIGHT  FOR  TAKEOFF  block of the LIMITATIONS table and a statement similar to the following    will    be    noted    in    the    REMARKS    section: ALLOWABLE GROSS WEIGHT FOR TAKEOFF LIMITED BY MAXIMUM TAXI GROSS WEIGHT. (c) Determine the ALLOWABLE LOAD for   TAKEOFF   by   subtracting   the   TOTAL   AIRCRAFT WEIGHT (reference 12) from the TAKEOFF ALLOWABLE GROSS WEIGHT.  (For most helicopters, this     is     the     only     ALLOWABLE     LOAD     calculation required).        Determine    the    ALLOWABLE    LOAD    for LANDING   by   subtracting   the   OPERATING   WEIGHT (Reference    9)    PLUS    ESTIMATED    LANDING    FUEL WEIGHT (Reference 23) from the LANDING ALLOWABLE     GROSS     WEIGHT.          Determine     the LIMITING WING FUEL ALLOWABLE LOAD by subtracting   the   OPERATING   WEIGHT   (Reference   9) from the LIMITING WING FUEL ALLOWABLE GROSS WEIGHT. (14) Reference 13.  Using same compartment letter designation as shown in Chart E (aircraft diagram) or     on     load     adjuster,     enter     the     number,     weight, compartment,   and   total   weight   and   total   moment   of passengers.      Then   enter   weight,   compartment,   total weight, and total moment of cargo. (15) Reference   14   and   15.      Not   applicable unless specifically required by command policy. (16) The area to the right of the reference 13 is provided  for  aircraft  requiring  Zero  Fuel  Weight.    Zero Fuel Weight Moment, and Zero Fuel c.g.  computations. For helicopters, these blocks are not used.  The required values are determined as follows: (a)    Add   the   weights   and   moments   of OPERATING WEIGHT, (reference 9) and DISTRIBUTION  OF  ALLOWABLE  LOAD  (PAYLOAD), (reference 13).  Enter the calculated total weight in the ZERO  FUEL  WEIGHT  block.    Enter  the  corresponding moment in the ZERO FUEL WEIGHT MOMENT block. (b) Compute   Zero   Fuel   c.g.      for   that weight  and  enter  in  the  ZERO  FUEL  %    MAC    block. (Cross out % MAC and enter value in IN.). (c)    Enter on the LIMITATIONS table in the  ALLOWABLE  GROSS  WEIGHT  (FUEL)  block  any Zero  Fuel  or  Limiting  Wing  Fuel  limitation  set  forth  in the -10 operator's manual or Chart E loading data.  This figure  must  be  compared  with  the  calculated  value  in the   ZERO   FUEL   WEIGHT   block.      If   the   calculated weight exceeds the limits adjust the load accordingly. (d)    The  Zero  Fuel  c.g.    cannot  exceed the forward and aft c.g.  limits at the Zero Fuel Weight. These  may  be  found  in  the  -10  operator's  manual  or Chart  E  loading  data.    If  it  is  within  limits,  enter  the PERMISSIBLE   C.G.      ZERO   FUEL   WEIGHT   forward and    aft    limits    at    the    Zero    Fuel    Weight    in    the LIMITATIONS    table.        If    it    is    not,    adjust    the    load accordingly, and repeat the process. (e) Enter    the    Zero    Fuel    weight    and moment in reference 21. (17) Reference 16.  Enter sum of reference 12 and the compartment totals under reference 13 opposite TAKEOFF CONDITION (Uncorrected). (18) Reference 17.  Enter the TAKEOFF C.G. (Uncorrected)  as  determined  from  weight  and  moment values of reference 16. (19) The weight value from reference 16 must be    compared    with    the    allowable    GROSS    WEIGHT TAKEOFF   as   shown   in   the   LIMITATIONS   table   to ensure    it    is    within    limits.        Use    the    reference    17 TAKEOFF  CONDITION  (Uncorrected)  gross  weight  to determine  the  PERMISSIBLE  C.G.    TAKEOFF  forward and  aft  c.g.    limits  from  the  -10  operator's  manual  or Chart E loading data If the takeoff c.g.  of reference 17 is  within  these  PERMISSIBLE  C.G.    TAKEOFF  limits, and no other corrections are necessary, (i.e.  temporary equipment changes), enter the permissible limits in the Change 2  4-14