TM 55-1500-342-23 space   provided   in   the   limitations   table.      Enter   the uncorrected  weight  and  c.g.    values  from  reference  16 and  reference  17  into  the  blocks  at  reference  19  and reference 20 respectively. NOTE The  c.g.    charts  and  tables  in  the  Chart  E and  -10  operator's  manual  are  not  accurate enough to use near the forward and aft c.g. limits.    In  those  instances  when  the  actual c.g.    is  very  close  to  the  aircraft  limits,  the c.g.      must   be   arithmetically   calculated   to ensure the necessary accuracy. (20) Reference  18.    When  the  takeoff  weight of reference 16 and/or the takeoff c.g.  of reference 17 are   not   within   permissible   takeoff   weight   and/or   c.g. limits,   changes   in   the   amount   or   distribution   of   load (reference    13)    are    required.        The    necessary    load adjustments   must   be   noted   in   the   CORRECTIONS columns on the left-hand portion of the Form F.  Enter a brief description of the necessary load adjustment in the left-hand  column  with  the  weight  and  moment  listed  in the columns provided.  Sum all the weight and moment increases and/or decreases to obtain the net change (+ or -) in the amount or distribution of the load.  Transfer the  total  weight  and  moment  adjustment  to  the  spaces provided for CORRECTIONS (if required) at references 18. NOTE If     there     are     any     temporary     equipment changes  listed  on  DA  Form  2408-13-1/2408- 13-1-E  or  DA  Form  2408-1412408-14-E,  they should   be   considered   changes   in   aircraft loading.    These  changes  should  be  entered with  the  notation  "EQUIPMENT  CHANGES" near the top of the CORRECTIONS table.  A brief     description,     weight     and     moments should be entered in the columns below this notation.  These entries should be treated as a variation in loading and applied to the total entered in reference 18. (21) Reference  19.    In  the  space  provided  for TAKEOFF  CONDITION  (corrected),  enter  the  sum  of reference 16 and reference 18.  (Add if reference 18 is positive.    If  it  is  negative,  subtract  reference  18  from reference 16). (22) Reference 20.  Enter the TAKEOFF C.G. (Corrected), as determined from the weight and moment values of reference 19. (23) The weight value from reference 19 must again be compared with the allowable GROSS WEIGHT TAKEOFF   as   shown   in   the   LIMITATIONS   table   to ensure  compatibility.    At  the  reference  19  TAKEOFF CONDITION (Corrected) gross weight, again determine the PERMISSIBLE C.G.  TAKEOFF forward and aft c.g. limits from the -10 operator's manual or Chart E loading date.    Re-check  the  takeoff  c.g.    of  reference  20  to ensure  it  is  within  the  PERMISSIBLE  C.G.    TAKEOFF limits.    Enter  these  limits  in  the  space  provided  in  the LIMITATIONS table. (24) Reference  21.    Enter  Zero  Fuel  Weight and moment.  This is normally calculated by subtracting TAKEOFF FUEL (Reference 10) from corrected TAKEOFF  CONDITION  (reference  19).    If  "Zero  Fuel weight limitations apply, this figure will match the values appearing to the right of reference 13. (25)  Reference  22.    Enter  weight  and  moment  of  any aerial supply load(s) to be dropped before landing. NOTE If   the   aircraft   has   no   Zero   Fuel   Weight limitations,  but  it  appears  that  c.g.    at  the Zero  Fuel  Weight  may  exceed  the  aircraft's forward  or  aft  c.g.    limits,  a  further  check must     be     made.          The     procedures     are described   in   paragraph   (16)   above.      This procedure must be applied to any analogous situation not already taken into consideration.    Examples  might  include  the unanticipated  jettisoning  of  external  stores, relocation   of   passengers,   etc.      Enter   the results   of   this   Zero   Fuel   (or   similar)   c.g. calculations   in   the   REMARKS   section.      It should  include  a  notation  such  as  "Center- of-gravity at the Zero fuel Weight (or with the auxiliary   fuel   tanks   released,   or   whatever) has  to  be  checked  and  the  c.g.    is  (is  not) within limits." Amplify the remarks if the c.g. is not within limits. (26) Reference 23. Determine the ESTIMATED  LANDING  FUEL  weight  and  moment  and enter it in the space provided. Change 7  4-15