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.
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.
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
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.
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 20. Enter the TAKEOFF C.G.
(Corrected), as determined from the weight and moment
values of reference 19.
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
Reference 21. Enter Zero Fuel Weight
and moment. This is normally calculated by subtracting
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.
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
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.
ESTIMATED LANDING FUEL weight and moment and
enter it in the space provided.
Change 7 4-15