SECTION VI. CARGO LOADING
This section contains information and instructions for
loading and securing cargo in the helicopter. t lists and
describes the items of equipment incidental to these op-
erations, instructions for their use, and illustrations where
necessary or desirable. It is not the intent of this section
to teach principles of cargo loading. It is the purpose of
this section to provide detailed information on cargo load-
ing with regard to this helicopter.
6-6-2. Cargo Compartment.
The cargo compartment (fig. 6-6-1) is 366 inches long, 90
inches wide, and 78 inches high. These dimensions are
uniform through out the cargo compartment, unless the
aircraft is configured with HICHS (fig. 6-6-1). The lower
rescue door is opened for rescue operations, aerial load-
ing, and external cargo transport operations. A hydrauli-
cally operated door and ramp provide a means for quick
and efficient straight-in loading and unloading.
Figure 6-6-2 shows the maximum cube size
which can be taken into the helicopter through
either the main cabin entrance, utility hatch,
or cargo loading ramp.
6-6-3. Main Cabin Entrance.
The main entrance door is located on the right side of the
cargo compartment at the forward end and measures 66
inches in height by 36 inches in width. The door is com-
posed of two sections: the upper section rolls inward and
upward to a rest position overhead; the lower section
opens outward and downward and serves as a step in the
6-6-4. Utility Hatch Door.
The utility hatch door is in the center of the cargo
compartment floor between stations 320 and 360. the
door is hinged along its entire forward edge. It opens
upward and forward to expose the lower rescue door and
the cargo hook. The door is unlatched by pressing the
knob labeled PUSH, and is latched by pressing the un-
When opening or closing the lower rescue
door, be certain that the cargo hook is proper-
ly stowed and supported by the restraining
straps. In addition, close the rescue door, us-
ing the actuator only to the point where the
latch can engage; the latches will then lift the
door and compress the door seal.
6-6-5. Lower Rescue Door.
When closed, the lower rescue door forms a part of the
fuselage bottom. It is accessible through the utility hatch
door. The lower rescue door is secured by four latches
centered around the door perimeter. These latches are
connected by linkage to an actuator labeled OPEN and
CLOSED. A handcrank, stowed in spring metal clips on
the left side of the fuselage, is used to unlatch the door
and turn the gears. A drive shaft, which is turned by the
gears, moves the door actuator links. The door opens
downward and aft underneath the fuselage where it re-
mains during operation.
Although tightening of the tiedown straps
may be necessary to reduce internal load
vibrations, excessive tightening of tie-
downs attached to the outboard row of tie-
down fittings will limit the effectiveness of
the isolated cargo floor.
6-6-6. Cargo Compartment Floor.
The floor is made of extruded panels, riveted together in
sections. Raised extruded ridges, running the entire
length of the floor, provided surfaces on which cargo is
moved. The flooring in the cargo compartment contains
sections on either side of the centerline which are
strengthened to serve as vehicle treadways. The flooring
from station 200 to 400 and from buttline 44 left to 44
right, rests on rubber vibration isolators which reduce
overall internal load vibrations. Tiedown fittings (fig.
6-6-3) for securing cargo are installed in the floor. There
are also studs for attaching troop seats, litter supports,
and the base plate for the maintenance crane. The floor-
ing is covered with a walkway compound which provides
a non-skid surface for personnel and for vehicles. In
construction, the ramp floor is identical with the cargo
Whenever possible, place all wheeled ve-
hicles entirely on the treadways between sta-
tions 200 and 400.
6-6-7. Strength Areas.
The weight which the cargo compartment floor (fig.
6-6-4) can support varies. These variations are largely
due to difference in strength of supporting frames and
fuselage construction, not because of varying floor
strength. To gain the maximum benefit from the cargo
compartment floor, the following definitions and weight
limitations must be observed.