Pipistrel Virus SW 121, Pilot Operating Handbook

Page: 137 / 226

7-5
Virus SW 121
Pilot Operating Handbook
POH-121-00-40-001
PAGE REV. 0
PAGE
SECTION 7
AIRPLANE DESCRIPTION
APPROVED
7.1 INTRODUCTION
This section provides a basic description and operation of the standard air-
plane and its systems. Optional equipment described within this section is
identified as optional.
NOTE: Some optional equipment, primarily avionics, may not be described
in this section. For description and operation of optional equipment not de-
scribed in this section, refer to Section 9, Supplements.
7.2 AIRCRAFT STRUCTURE
7.2.1 FUSELAGE
The fuselage is designed as a carbon fiber honeycomb-sandwich construc-
tion using aramide as inner laminate in the cockpit area. The main bulkhead
is designed as a carbon / honeycomb sandwich. The undercarriage is at-
tached directly to the engine mount, which is attached to the main bulkhead.
The firewall is made out of CFRP prepreg honeycomb sandwich. It has a
ceramic insulation with stainless steel sheet on top. In the baggage compart-
ment there is a CFRP container for the ballistic rescue system. Primary and
secondary control rods are covered by CFRP fairings to protect them from
luggage. The baggage compartment floor is made out of CFRP. It is bolted to
the bulkheads and to the CFRP tunnel, that covers the elevator control rod.
The back rest is made out of GFRP and fixed to the bulkhead by velcro for
easy access to the baggage compartment. The cabin floor is also the lower
seat structure and made out of CFRP with aramide. The external structure
is covered by a protective acrylic paint coating, which has already been ap-
plied in the mold.
7.2.2 WINGS
The detachable wing is a single spar cantilever wing. The left and right wing
are connected by two bolts through the spar ends. The wing structure is
made mostly from carbon fibre. The main spar shear web and the root ribs
are made from glass fibre. This is for visual inspection and easier damage
detection reasons. The spar caps are produced using carbon roving. The
wing spar is designed as double-T-type spar. Lateral loads and twisting mo-
ments are conventionally transferred to the fuselage through root ribs and
lateral-force bolts.