Description And Operation Of Aircraft And Systems; The Aircraft; Fuselage - Extra 200 Information Manual

Pilot´s Operating Handbook
EXTRA 200
7.1

THE AIRCRAFT

The aircraft EXTRA 200 is designed and developed by EXTRA Flugzeugproduktions- und
Vertriebs- GmbH, Dinslaken 46569 Hünxe, Federal Republic of Germany, in accordance
with the U.S. Federal Aviation Regulations, part 23, categories normal and acrobatic to fulfil
the primary flight training, normal operation rules and acrobatic training up to the unlimited
acrobatic level.
EXTRA 200 is a light weight, robust, single piston-engined, two-seat aircraft with a fuselage
structure in tig-welded steel-tube construction.
The landing gear, wing, and tail are made of epoxy, reinforced with glass- and carbonfiber.
The items are qualified up to 72°C (161,6°F). Not to exceed this temperature limit an appro-
priate colour specification for composite structure is given by the manufacturer document
EA-03205.19.
To check the temperature inside the cockpit (potential "green house" effect) a reversible
temperature indicator (STRUCTURAL OVERHEAT INDICATOR) is applied on the upper
side of the wing main spar in the carry-through section. After reaching the temperature limit
of 72°C (161,6°F) the word "RISK" appears on the red spot of this structural overheat
indicator immediately and flying is prohibited. When the structure cools down below this
temperature limit the word "RISK" disappears and you may go on with the preflight checklist.
a) Below 72°C (161,6°F)
STRUCTURAL
OVERHEAT
INDICATOR
EXTRA
The standard aircraft is designed to operate within a range of ambient air temperature from -
20°C to +44°C (-4°F to 111°F) at sea level. It is possible to start the engine using the aircraft
battery at -20°C (-4°F) without preheating. Below -10°C (+14°F) OAT a special oil breather
line must be adapted (available as kit).
7.2

FUSELAGE

The fuselage structure consists of a steel tube construction integrating the wing and empen-
nage connections as well as the seats. The fuselage except the rear lower part, is faired
with an aramid/carbon laminate shell. Within the exhaust area stainless steel sheet metal is
used. The upper fuselage body surface is one part from firewall to vertical stabilizer includ-
ing the correlated canopy frame. Only the lower rear part of the fuselage is covered with
Ceconite
Page Date: 28. February 2006
Page Date: 20. April 2002
DESCRIPTION AND OPERATION
OF AIRCRAFT AND SYSTEMS
CAUTION:
While the word
appears, flying
is prohibited !
®
102.

Description and Operation of Aircraft and Systems

SECTION 7
b) At 72°C (161,6°F) or above
STRUCTURAL
OVERHEAT
RISK
INDICATOR
EXTRA
Section 7
CAUTION:
While the word
RISK
RISK
appears, flying
is prohibited !
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