Section III. FUEL/OIL
Fuel loading imposes a restriction on the amount of load
which can be carried. The required fuel must first be
determined, then that weight subtracted from the total
weight of crew and fuel. Weight up to and including the
remaining allowable capacity can be subtracted directly
from the weight of crew and fuel. As the fuel load is
increased, the loading capacity is reduced. Figure 6-3
depicts the density variation of aviation fuel.
FUEL AND OIL DATA
Fuel Moment Table. This table (Table 6-2)
shows fuel moment/100 given US gallons or pounds for
JP-4, JP-5 and JP-8.
Oil Data. Total oil weight is 62 pounds and is
included in the basic weight of the aircraft.
Section IV. CENTER OF GRAVITY
CENTER OF GRAVITY LIMITATIONS.
It is possible to exceed the forward
Center of Gravity limit when the
mission gear is removed.
Center of gravity limitations are expressed in ARM
inches which refers to a positive measurement from the
aircraft's reference datum. The forward CG limit at
11,800 lbs., or less, is 177.0 ARM inches. The forward-
sloping CG limit line is a straight line from 11,800 lbs.
to 16,000 lbs, ending at fuselage station 187.5. At
16,000 lbs., or less, the aft CG limit is 195.1 ARM
inches. The Center of Gravity Limitations Table (Table
6-3) is designed to establish forward and aft CG
Section V. CARGO LOADING
The basic factors to be considered in any loading
situation are as follows:
Cargo shall be arranged to permit access to all
emergency equipment and exits during flight.
considered in the loading of heavy or sharp-edged
containers and equipment. Shorings shall be used to
distribute highly condensed weights evenly over the
All cargo shall be adequately secured to prevent
damage to the aircraft, other cargo, or the item itself.
The cabin airstair door is weight
limited to a maximum of 300 pounds
Loading of cargo is accomplished through the cabin
door (21.5 in. X 50.0 in.) or the cargo door.
All cargo shall be secured with restraints strong enough
to withstand the maximum force exerted in any
direction. The maximum force can be determined by
multiplying the weight of the cargo item by the
applicable load factor. These established load factors
(the ratio between the total force and the weight of the
cargo item) are 1.5 to the side and rear, 3.0 up, 6.6
down, and 9.0 forward.