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
(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:
LIMITED BY MAXIMUM TAXI GROSS WEIGHT.
Determine the ALLOWABLE LOAD
for TAKEOFF by subtracting the TOTAL AIRCRAFT
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
ALLOWABLE GROSS WEIGHT. Determine the
subtracting the OPERATING WEIGHT (Reference 9)
from the LIMITING WING FUEL ALLOWABLE GROSS
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.
Reference 14 and 15. Not applicable
unless specifically required by command policy.
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
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.
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.
Enter the Zero Fuel weight and
moment in reference 21.
Reference 16. Enter sum of reference 12
and the compartment totals under reference 13 opposite
TAKEOFF CONDITION (Uncorrected).
Reference 17. Enter the TAKEOFF C.G.
(Uncorrected) as determined from weight and moment
values of reference 16.
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