Introduction; Aircraft Structure; Fuselage - Pipistrel ALPHA Trainer LSA Pilot Operating Handbook

ALPHA Trainer LSA
Pilot Operating Handbook
7.1
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.
7.2
7.2.1
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
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 moments are con-
ventionally transferred to the fuselage through root ribs and lateral-force bolts.
The wing shell is designed as a 2-cell CFRP sandwich shell which is
closed by a rear shear web to which the flaperons are attached. The
wings are connected as it is classic with gliders by two spar ends
being connected with two main bolts. There is also the third mid-
dle bolt to provide torsion stiffness mating the wings to the fuselage.
POH-162-00-40-001
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INTRODUCTION

AIRCRAFT STRUCTURE

FUSELAGE

WINGS
SECTION 7
AIRPLANE DESCRIPTION
PAGE
7-5