Section V. MISSION EQUIPMENT
Section VI. CARGO LOADING
6-14. AIR CARGO FEATURES.
The 245 cubic foot cabin area is easily converted
for mixed or all cargo use by removing passenger
seats and a partial partition, Figure 6-6. A top-hinged
cargo door with an opening 52 inches wide by
52 inches high, is provided on the left side of the
fuselage to admit bulk cargo D1 T The floor is
designed to support 200 pounds per square foot when
supported by the seat tracks. The areas where seat
track support is not possible will support 100 pounds
per square foot floor loading. Seat tracks are to be
used for securing cargo containers.
6-15. AERIAL DELIVERY SYSTEM.
Procedures for aerial delivery of personnel
and cargo have not been developed.
The cargo door is a structural panel and
shall be closed for flight.
There are no provisions for static lines; however,
free fall parachute operations may be accomplished.
The cabin door may be removed for flight by installing
Beech Aircraft Corporation Kit 100-4006. Flights with
the door removed must be in accordance with the
Federal Aviation Administration approved flight manual
supplement, which accompanies this kit.
6-16. PREPARATION OF GENERAL CARGO.
Before loading cargo, loading personnel should
determine such data as weight, dimensions, center of
gravity, and contact areas of the individual cargo items
for use in positioning the load.
6-17. 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 Center of Gravity Limitations
graph, Figures 6-7 and 6-8. Cargo moment may be
determined by using the Cargo Moment chart, Figure
6-18. 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 and bulkhead structural capacity
shall be considered in the loading of heavy or sharp
edged containers and equipment. Shorings shall be
used to distribute 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
6-19. LOADING PROCEDURE.
a. Loading of cargo is accomplished through
the cabin door C or cargo door D T .
6-20. 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 3.0
down, and 9.0 forward.
6-21. 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, Figure 6-9. When cargo is properly secured
by tiedown devices, it will be restrained from moving in
any direction within the aircraft.