TM 55-1510-221-10
Section III. FUEL/OIL
6-11. FUEL LOAD.
6-12. FUEL AND OIL DATA.
Fuel loading imposes a restriction on the
amount of load which can be carried. The required
fuel must first be determined, then that weight sub-
tracted 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.
a.
Fuel Moment Table. This table (Table 6-2)
shows fuel moment/ 100 given US gallons or pounds
for JP-4 and JP-5.
b.
Oil Data. Total oil weight is 62 pounds and
is included in the basic weight of the aircraft. Servic-
ing information is provided in Section XII of Chap-
ter 2.
Section IV. CENTER OF GRAVITY
6-13. CENTER OF GRAVITY LIMITATIONS.
Removal of mission gear may result in
exceeding the forward center-of-gravity
limit.
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.
The forward-sloping CB limit line from 11,279 Lbs.
to 13,500 Lbs., and straight up to 15,000 Lbs., is
fuselage station 188.3. At 15,000 Lbs. or less, the aft
CG limit is 195.1 ARM inches. The Center of Grav-
ity Limitations Table (Table 6-4) is designed to
establish forward and aft CG limitations.
Section IV. Cargo Loading
6-14.
LOAD PLANNING. The basic factors to be
considered in any loading situation are as follows:
a.
Cargo shall be arranged to permit access to
all emergency equipment and exits during flight.
b.
Floorboard structural capacity shall be con-
sidered in the loading of heavy or sharp-edged con-
tainers and equipment. Shorings shall be used to dis-
tribute highly condensed weights evenly over the
cargo areas.
c. All cargo shall be adequately secured to
prevent damage to the aircraft, other cargo, or the
item itself.
6-15. LOADING PROCEDURE.
NOTE
The cabin door is weight limited to a
maximum of 300 pounds to prevent pos-
sible structural damage.
Loading of cargo is accomplished through the
cabin door (21.5 in. X 50.0 in.) or the cargo door
(52.0 in. X 52.0 in).
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 deter-
mined 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.
6-14
