XtremeAIR XA42, Flight Manual

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Airplane Flight Manual XA42
AFM-XA42-0040-002-A.01
Page 1 Page date:
Chapter 07 24.01.2011
7. DESCRIPTION AND OPERATION OF
AIRCRAFT AND SYSTEMS
7.1 AIRCRAFT
The XA42 is designed and manufactured by
XtremeAir GmbH, Harzstraße 2, Am Flughafen Cochstedt, 39444 Hecklingen, Germany,
in accordance with the EASA CS-23, categories utility and acrobatic, to fulfill normal operations and
acrobatic flying up to the Unlimited aerobatic level.
The aircraft is a two seat, light weight, single engine construction with a carbon fiber reinforced
composite fuselage structure. The primary structure is carbon fiber reinforced composite. The items
are qualified up to 85 °C / 185 °F. To avoid high temperatures, the painting has to meet the
requirements under color specification for composite structure.
The standard aircraft is designed to operate within a range of ambient air temperature from -20 °C to
+38 °C / -4 °F to 100 °F at sea level.
It is possible to start the engine using the aircraft battery at -20 °C / -4 °F without preheating.
7.2 FUSELAGE
The fuselage is made out of carbon-honeycomb sandwich.
Canopy frame and the empennage are part of the fuselage structure. The fuselage also includes the
substructure of the seats and the instrument panels.
The canopy itself is a single carbon fiber reinforced composite part. It opens to the right hand side, is
locked on the left hand side and its opening angle is limited by a strap. Emergency jettison is achieved
by simply unlocking the canopy, while the lower pressure on the upper outside of the canopy will pull
it up and tear it away.
7.3 WING
The wing shell is designed as CFRP sandwich shell which is closed by an aft shear web. An overlap
joint, laminated with the lower wing shell provides bonding of the two wing shells at the wing nose
area. The wing spar is designed as double box-type spar and guided through the fuselage as one
piece. Lateral loads and twisting moments are conventionally transferred to the fuselage through root
ribs combined with a secondary spar and lateral-force bolts. In front area of the spar, there are four
tank ribs laminated to the shells which limit the tank capacity of the integral fuel tanks. Inspection
holes are integrated into the lower wing shell to allow easy inspection of aileron control bell cranks,
which are mounted on a wing rib.
The connection to the fuselage is arranged by two bolts through the spar parallel to the center line of
the fuselage and two shear force bolts at the secondary spars.
Ailerons are designed as “powered ailerons” to reduce pilot’s hand forces, having a separate airfoil
and are hinged at 25% chord. They are actuated through pushrods which act on a CFRP arm bolted
from the bottom to the aileron. This arm extends to 450 mm below the wing and holds so called
“spades”, sandwich plates to reduce aerodynamic aileron forces to a minimum. The aileron shell is
designed as a single-cell CFRP sandwich shell which is reinforced by unidirectional CFRP tapes. The
aileron is hinged in maintenance-free teflon-bearing bushings mounted on GFRP brackets integrated
into the wing connecting ribs.
To prevent flutter the ailerons are weight balanced in the overhanging leading edge.