Date
:
11-15-19
Revision: 2
5.7.3-2
VASHON AIRCRAFT RANGER R7 MAINTENANCE MANUAL
GENERAL
The fuselage structure is of monocoque design in which the outer skin carries the major part of
the load. Bulkheads and stiffeners are present but primarily for the purpose of stabilizing the
outer skin such that it can carry greater loads than if it were not supported. Because the outer
skin contributes such a large percentage of the load carrying capability of the fuselage, dents,
cracks, or other defects in the skin must be carefully scrutinized and evaluated in order to
ensure that there is no loss in load carrying capacity.
The majority of the structural parts in the fuselage are produced from sheets of inherently
corrosion resistant 6061-T6 aluminum using a CNC turret punch press
. The machine cut “flat
patterns”
which require forming
are either hydropress formed over dedicated “formblocks” or
bent using a press-brake machine.
The predominant method for joining parts is with blind rivets although solid rivets and threaded
fasteners (screws and/or bolts and nuts) are used where the fasteners either must be
removable or where high shear-strength fasteners are required.
Figure 5.7.3.1 Fuselage structure with skin hidden.
