ZLIN AIRCRAFT a.s.
Chapter 7
Z 242 L Flight Manual
Description of the aircraft and its systems
REVISION No. 3
25.2.2017
EASA Approved
7 - 3
7.1
GENERAL
This Chapter provides basic technical description of Z 242L aircraft systems and other
information necessary to the operation of the aircraft.
The optional equipment and the navigation/communication equipment is described in the
Chapter 9 - SUPPLEMENTS.
7.3
AIRFRAME
a)
Fuselage:
is of mixed structure. The central supporting part is a latticework, being welded of steel
tubes and covered by a body made of hard light alloy sheets and of glassfibre composite.
The rear part is a semimonocoque construction. The front and the rear part of the
fuselage are connected by means of four bolts. The sliding canopy is opened by sliding
forward.
b)
Wing:
is of all-metal structure provided with a main and an auxiliary spar. Two wing halves are
attached to the fuselage. The main spar of the wing is connected with the centre-section
in the fuselage by means of two expandable bolts/bushings provided with conical pins.
The upper bolt is oriented vertically, the lower one horizontally. The rear auxiliary spar is
connected with the fuselage by means of a horizontally oriented cylindrical bolt. The wing
skin is made of hard light-alloy aluminium clad sheets. The wing flaps and ailerons are
slotted, all-metal, and identical in construction and dimensions. The ailerons are provided
with fixed balance tabs. The wing ends are terminated with composite wing tips to reduce
the induced drag.
c)
Empennage:
are of all-metal cantilever structure - covered with hard aluminium sheet. Both the rudder
and the elevator are partially mass-balanced. The elevator is provided with one balance
tabs and one being controllable for longitudinal trim. The rudder is provided with a fixed
balance tab.