Zlin Aircraft Z 242 L Technical specifications

AIRPLANE FLIGHT MANUAL
Z 242 L
Document No. 003.012.1
Serial No.: ................................................
Registration Mark: ................................................
Manufacturer: ZLIN AIRCRAFT a.s.
OTROKOVICE 765 02
CZECH REPUBLIC
Category: ACROBATIC (A)
UTILITY (U)
NORMAL (N)
Certification Basis: FAR Part 23 as amended trough Amendment 23 - 41 inclusive
FAR Part 36 as amended trough Amendment Amdt. 36 - 20 inclusive
ICAO, Annex 16.
THIS DOCUMENT MUST BE CARRIED IN THE AIRPLANE AT ALL OPERATION TIMES!
THIS AIRPLANE FLIGHT MANUAL IS EASA APPROVED UNDER APPROVAL NO.: 10042932.
DATE OF APPROVAL: 7.1.2013
The English version has been translated with care and is accurate to the best of editor’s
knowledge. However in all official matters the original Czech version is the authoritative
document.
THIS AIRPLANE FLIGHT MANUAL SUPERSEDES ALL “AIRPLANE FLIGHT MANUALS OF THE
Z 242 L AIRCRAFT” ISSUED IN ENGLISH VERSION, WHICH ARE NOT MARKED ON THE TITTLE
PAGE WITH DOCUMENT NUMBER 003.012.1
Copyright © 2011
ZLIN AIRCRAFT a.s.
765 02 OTROKOVICE
Czech Republic
ISSUE OF REVISION No. 3 IS APPROVED UNDER DOA No. EASA.21J.110 APPROVAL
DATE OF APPROVAL: 9.3.2017

ZLIN AIRCRAFT a.s. Chapter 0
Z 242 L Flight Manual Technical information
REVISION No. 3
25. 2. 2017 EASA Approved 0 - 5
0.3.2 Log of revisions
Rev.
No.
Description / eligibility
Pages affected:
Date of
issue of new
page
Date of revision
incorporation and
signature
1
Implementation of new load
spectrum
0-5, 0-7, 2-9
1. 6. 2013
2
Formal corrections in FM
(correction of values for
weight and C/G position
calculation, correction of
inner dimensions of cockpit
and correction of english
translation)
0-5, 0-7, 0-8, 1-12, 4-24,
6-9, 6-10, 6-11, 6-12
8. 6. 2016
3
Formal corrections in FM
(correction of typical
versions of instrument panel
and pilot cockpit pictures,
correction of designation of
circuit switches for aircraft
valid from S/N 0814 incl.
0-5, 0-7, 0-9, 7-1 to 7-36
25. 2. 2017

ZLIN AIRCRAFT a.s. Chapter 0
Z 242 L Flight Manual Technical information
REVISION No. 3
25. 2. 2017 EASA Approved 0 - 7
0.4 LIST OF EFFECTIVE PAGES
Page No.
Date of issue
Validity
Page No.
Date of issue
Validity
0 - 1
0 - 2
0 - 3
0 - 4
0 - 5
0 - 6
0 - 7
0 - 8
0 - 9
0 - 10
0 - 11
0 - 12
1 - 1
1 - 2
1 - 3
1 - 4
1 - 5
1 - 6
1 - 7
1 - 8
1 - 9
1 - 10
1 - 11
1 - 12
1 - 13
1 - 14
1 - 15
1 - 16
1 - 17
1 - 18
20.3.2011
20.3.2011
20.3.2011
20.3.2011
25.2.2017
20.3.2011
25.2.2017
8. 6. 2016
25.2.2017
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
8. 6.2016
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
2 - 1
2 - 2
2 - 3
2 - 4
2 - 5
2 - 6
2 - 7
2 - 8
2 - 9
2 - 10
2 - 11
2 - 12
2 - 13
2 - 14
2 - 15
2 - 16
2 - 17
2 - 18
2 - 19
2 - 20
2 - 21
2 - 22
2 - 23
2 - 24
3 - 1
3 - 2
3 - 3
3 - 4
3 - 5
3 - 6
3 - 7
3 - 8
3 - 9
3 - 10
3 - 11
3 - 12
3 - 13
3 - 14
3 - 15
3 - 16
3 - 17
3 - 18
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
1. 6. 2013
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011

ZLIN AIRCRAFT a.s. Chapter 0
Z 242 L Flight Manual Technical information
REVISION No. 3
25. 2. 2017 EASA Approved 0 - 9
Page No.
Date of issue
Validity
Page No.
Date of issue
Validity
7 - 1
7 - 2
7 - 3
7 - 4
7 - 5
7 - 6
7 - 7
7 - 8
7 - 9
7 - 10
7 - 11
7 - 12
7 - 13
7 - 14
7 - 15
7 - 16
7 - 17
7 - 18
7 - 19
7 - 20
7 - 21
7 - 22
7 - 23
7 - 24
7 - 25
7 - 26
7 - 27
7 - 28
7 - 29
7 - 30
7 - 31
7 - 32
7 - 33
7 - 34
7 - 35
7 - 36
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
25.2.2017
8 - 1
8 - 2
8 - 3
8 - 4
8 - 5
8 - 6
8 - 7
8 - 8
8 - 9
8 - 10
9 - 1
9 - 2
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011
20.3.2011

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 - 1
SECTION 7 - DESCRIPTION OF THE AIRCRAFT AND ITS
SYSTEMS
CONTENTS
Section Page
7.1 General 7 - 3
7.3 Airframe 7 - 3
7.5 Flight controls 7 - 4
7.7 Instrument panel 7 - 6
7.11 Ground control 7 - 12
7.13 Wing flaps 7 - 12
7.15 Landing gear 7 - 13
7.17 Baggage compartment 7 - 13
7.19 Seats, seat belts and shoulder harnesses 7 - 13
7.21 Doors, windows and exits 7 - 15
7.23 Control locks 7 - 16
7.25 Engine 7 - 17
7.27 Propeller 7 - 22
7.29 Fuel system 7 - 23
7.33 Brake system 7 - 25
7.35 Power steering 7 - 26
7.37 Electrical system 7 - 26
7.39 Lighting system 7 - 30
7.43 Heating, ventilating, defrosting and air conditioning 7 - 32
7.49 Pitot pressure system 7 - 34
7.51 Static pressure system 7 - 34
7.57 Stall warning or angle of attack system 7 - 34
7.59 Icing equipment 7 - 36
7.61 Avionics 7 - 36
7.65 Cabin features 7 - 36

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 2 EASA Approved 25.2.2017
INTENTIONALLY LEFT BLANK

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.

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 4 EASA Approved 25.2.2017
7.5 FLIGHT CONTROLS
The aircraft is provided with a dual control for training purposes. Manual control is levers
steering, pedal control is pedals steering.
a) Longitudinal control:
The elevator is controlleed by means of the control stick vie levers, rocker levers and
control rods. Diagram of longitudinal control is illustrated on Fig. 7-1.
b) Lateral control:
The ailerons are controlled by means of the control stick via levers and control rods. The
aileron deflections are differentiated. Diagram of lateral control is illustrated on Fig. 7-1.
c) Directional control:
The rudder is controlled by means of pedals of the directional control via control rods, a
gate and cable system. The control of the rudder is combined with the steering of nose
landing gear. Diagram of directional control is illustatrated on Fig. 7-1.
The Rudder pedals R.H. and L.H. of rudder control are lengthways adjustable in the range
75 mm. Rudder pedals adjustment is executed by control handle situated under control
panel before every seat.
Fig. 7-1 Diagram of aircraft control

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 - 5
d) Trim:
1) Longitudinal Trim:
is mechanical type. Consist of the control wheel of longitudinal trim (located on the
central panel between the front seats), cable system, with controls a self-locking
screw mechanism, from which the motion is transferred onto the trim tab of the
elevator via a doubled control rod.
The longitudinal trim is illustrated in Fig. 7-2.
Sense of control:
(i) turning the control wheel forwards - makes the aircraft nose heavy
(ii) Turning the control wheel backwards - makes the aircraft tail heavy
NOTE:
The trim tab is in neutral position when the mark on the longitudinal trim indicator is
set to “TAKE-OFF”.
Fig. 7-2 Diagram of longitudinal trim
2) Directional Trim:
is of mechanical type, controlled by means of a small wheel for directional trim
(located on the central panel between the front seats); this controls the spring
prestress, which induces the balance forces in the pedals control system.

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 6 EASA Approved 25.2.2017
7.7 INSTRUMENT PANEL
7.7.1 Pilot’s compartment
1 - Control stick 19 - Instrument lighting dimmers
2 - Intercom pushbutton (IC) 20 - Main spar flange nitrogen pressure
3 - Transmitter pushbutton (VHF) indicator
4 - Canopy arrestment in open position 21 - Wing flap lever
5 - Lever for canopy emergency jettisoning 22 - Longitudinal trim
6 - Outside air thermometer 23 - Directional trim
7 - Adjustable pedals set handle 24 - Headphone connection socket
8 - Magnetic compass I 25 - Fuel selector valve
9 - Towing gear control 26 - Control stick lock
10 - Ventilation and heating control 27 - Switches
11 - Ignition switch 28 - Fuses
12 - Master switch 29 - Ventilation windows
13 - Throttle control 30 - Portable fire extinguisher
14 - Annunciator lights 31 - Seat position adjustment lever
15 - Signalisation check pushbutton 32 - Brake pedal
16 - Propeller control 33 - COM/NAV 1, COM/NAV 2 switches
17 - Mixture control 34 - Alternative static pressure source
18 - Parking brake control (ASPS) regulation screw
35 - Alternative static pressure source
(ASPS) switch-valve
Fig. 7-3A Typical arrangement of pilot’s compartment up to S/N 0791 incl.