gravity, and contact areas of the individual cargo items
for use in positioning the load.
6-16. CARGO CENTER OF GRAVITY PLANNING.
The cargo loading shall be planned so that the
center of gravity of the loaded aircraft will fall within the
operating limits shown on the Center of Gravity
Loading Diagram. Refer to Figure 6-3. Cargo moment
may be determined by using the Cargo Moment chart,
6-17. 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.
b. The cabin section flooring will withstand a
loading of 200 pounds per square foot for items
supported on the seat tracks. Floor areas where seat
baggage/utility area) will only support 100 pound per
square foot floor loads. Shoring shall be used to
distribute highly condensed weights evenly over the
cargo areas. Use of the floor seat tracks to support
loads is encouraged where possible.
All cargo shall be adequately secured to
prevent damage to the aircraft, other cargo, or the item
6-18. LOADING PROCEDURE.
The cabin airstair door is weight limited to
a maximum of 300 pounds to prevent
possible structural damage.
Loading of cargo is accomplished through the
cabin door (21.5 in. X 46.0 in.) or the cargo door
(52 in. X 52 in.).
6-19. 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.
6-20. RESTRAINT DEVICES.
The aircraft is equipped with full-length seat
tracks which are used to support the cargo and
provide attachment points for the cargo tiedown
devices. Refer to Figure 6-5. When cargo is properly
secured by tiedown devices, it will be restrained from
moving in any direction within the aircraft.
6-21. CARGO RESTRAINING METHOD.
To avoid structural damage, all cargo shall
be restrained in accordance with Beech Kit
Drawing No. 101-5040, which provides the
correct methods for restraint and approved
Cargo is restrained by passing tiedown devices
over and around the cargo and attaching the ends of
the tiedown device to the seat tracks as shown in
Figure 6-5. The number of tiedown devices required
to restrain a given weight of cargo may vary.
6-22. CARGO UNLOADING.
Unloading of cargo shall be accomplished
through the cabin door, or cargo door.
Section VII. CENTER OF GRAVITY
6-23. CENTER OF GRAVITY LIMITATIONS.
The forward Center of Gravity (CG) limit is
188.3 arm inches from 14,000 pounds to 13,500
pounds. From 13,500 pounds down to 11,279 pounds,
the intermediate arm inch values vary linearly to
181 inches. Below 11,279 pounds, the maximum
forward CG remains 181 arm inches.
b. The aft CG limit is 196.4 inches aft of datum
at all weights. The Center of Gravity Loading Diagram
is designed to establish forward and aft CG limitations.