Section III. FUEL/OIL
6-11. FUEL LOAD.
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 passengers, baggage and fuel. Weight up to
and including the remaining allowable capacity can be
subtracted directly from the weight of passengers,
baggage and fuel. As the fuel load is increased, the
loading capacity is reduced.
6-12. FUEL AND OIL DATA.
Fuel Moments Table. This table (Table 6-2)
shows fuel moment/100 given US gallons or pounds for
JP-4 and JP-5.
Oil Data. Total oil weight is 62 pounds and is
included in the basic weight of the aircraft. Servicing
information is provided in Section XII of Chapter 2.
Section IV. CENTER OF GRAVITY
6-13. CENTER OF GRAVITY LIMITATIONS.
The forward Center of Gravity
limit may be exceeded 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
11,279 Lbs. or less is 181.0 ARM inches. At 14,200
Lbs. or less, the aft CG limit is 196.4 ARM inches. The
Center of Gravity Limitations Tables (Tables 6-4 or 6-5)
are designed to establish forward and aft CG limitations.
Section V. CARGO LOADING
6-14. LOAD PLANNING.
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.
6-15. LOADING PROCEDURE.
Loading of cargo is accomplished through the cabin
door (21.5 in. X 50.0 in.) or the cargo door (52.0 in. X
6-16. SECURING LOADS.
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.
Change 2 6-12