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
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ZLIN AIRCRAFT a.s. Chapter 0
Z 242 L Flight Manual Technical information
REVISION No. 3
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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.

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 - 7
1 - Control stick 19 - Instrument lighting dimmers
2 - - 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. 7-3B Typical arrangement of pilot’s compartment from S/N 0792 incl.

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 8 EASA Approved 25.2.2017
NOTES:
1) Items written by italic are delivered as optional equipment only.
7.7.2 Instrument panel
This subsection provides a typical instrument equipment illustration.
1 - Airspeed indicator I
2 - Attitude gyro I
3 - Altimeter I
4 - Turn and Bank indicator I
5 - Directional gyro (HSI indicator)
6 - Vertical speed indicator I
7 - ADF indicator
8 - Clock
9 - VOR/ILS indicator
10 - DME indicator
11 - R.P.M. indicator
12 - Manifold pressure gauge
13 - Airspeed indicator II
14 - Attitude gyro II (Turn and Bank ind. II)
15 - Altimeter II
16 - Four-pointer engine indicator
17 - Four-pointer fuel gauge indicator
18 - Vertical speed indicator II
19 - CHT/EGT indicator
20 - Accelerometer
21 - V-A meter
22 - V-A meter (alternative location)
23 - Avionics block
24 - Engine hours counteri
Fig. 7-4A Example of instrument panels up to S/N 0791 incl.
NOTES:
Instruments written by bold are delivered as basic equipment.
Holes for not installed instruments are covered by blind sheets.
The actual representation of the instrument panel with real equipment of a particular aircraft is
presented in the Chapter 9 - SUPPLEMENTS.

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 - 9
1A - Primary Flight Display (PFD)
1B - Multifunction Flight Display (MFD)
2 - Airspeed indicator I
3 - Altimeter I
4 - Turn and Bank indicator I
5 - Four-pointer engine indicator
6 - Directional Gyro (HIS indicator)
7 - Vertical speed indicator I
8 - Four-pointer fuel gauge indicator
9 - CHT/EGT indicator
10 - Clock
11 - Accelerometer
12 - V-A meter
13 - R.P.M. indicator
14 - Manifold pressure gauge
15 - Engine hours counter
16 - ELT remote switch
17 - Avionics block
Fig. 7-4B Example of instrument panels from S/N 0792 incl.
NOTES:
Instruments written by bold are delivered as basic equipment.
Holes for not installed instruments are covered by blind sheets.
The actual representation of the instrument panel with real equipment of a particular aircraft is
presented in the Chapter 9 - SUPPLEMENTS.

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 10 EASA Approved 25.2.2017
7.7.3 Annunciator lights
The annunciator lights panel is located in the upper part of the instrument panel. The inclinate
lampshade is located above the panel to decrease the intensity of panel lights (at night
operation).
(1) (yellow)
L FUEL
LOW LEVEL
(2) (yellow)
R FUEL
LOW LEVEL
(3) (yellow)
GENERATOR
(4) (yellow)
EXT. POWER
SOURCE
(5) (red)
OIL PRESS
LOSS
(6) (yellow)
STALL. WARN.
FAILURE
(7) (green)
PITOT
HEATING
(8) (green)
STATIC
HEATING
(6) (white)
STALL. WARN.
INACTIVE
(7) (white)
PITOT
TEST
(8) (white)
STATIC
TEST
NOTES:
No. (1) - L FUEL LOW LEVEL - fuel rest in the left tank.
No. (2) - R FUEL LOW LEWEL - fuel rest in the right tank.
No. (3) - GENERATOR - generator (voltage drop below 26,2 V in the electric system).
No. (4) - EXT. POWER SOURCE - external source of electric connected.
No. (5) - OIL PRESS LOSS - oil pressure drop below 170 kPa (25 p.s.i.).
No. (6) - STALL. WARN. FAILURE (from S/N 0651 to S/N 0740) or
STALL. WARN. INACTIVE (from S/N 0741 and up) - stall warning circuit is opened
with the microswitch controlled by depresion of the main landing gear leg.
No. (7) - PITOT TEST (from S/N 0651 to S/N 0689) or
PITOT HEATING (from S/N 0691 and up) - Pitot tube and stall speed probe heating.
No. (8) - STATIC TEST (from S/N 0651 to S/N 0689) or
STATIC HEATING (from S/N 0691 and up) - static pressure probes heating
Fig. 7-5 Annunciator lights

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 - 11
7.7.4 Description of the Switches
a) In the middle instrument panel is the “MASTER SWITCH”, which turns off all circuits
including the emergency source of electrical power, except of the cockpit light and engine
ignition.
b) In the middle instrument panel between the seats is located of Circuit switches:
"LANDING LIGHT" - turns “ON” and “OFF” the landing light
"TAXI LIGHT" - turns “ON” and “OFF” the taxi light
"BEACON" - turns “ON” and “OFF” the anti-collision beacon and the
supplementary lighting
(applicable for aircrafts up to S/N 0813 incl. and from S/N 0814
only optional)
“MAP LIGHT” - turns “ON” and “OFF” the supplementary lighting
(applicable from S/N 0814 incl.)
"POSITION LIGHTS" - turns “ON” and “OFF” the position lights
"LIGHTING" - turns “ON and “OFF” the lighting of instruments and placards
"STROBE LIGHTS" - turns “ON” and “OFF” the strobe lights (if installed)
"EXT.POW.SOURCE" - connects or disconnets the electrical system to or from the
external source
"BATTERY" - connects or disconnects the battery to or from the network
"GENER." - connects the alternator to or from the network
"FUEL PUMP" - turns “ON” and “OFF” the electrical fuel pump
“ENGINE INSTR." - turns “ON” and “OFF” the fuel meters, the four pointer indicator
(fuel pressure, oil temperature, oil pressure, fuel consumption
gauge) and the engine hour counter (if installed)
"FLIGHT INSTR." - turns “ON” and “OFF” the attitude gyro(s), turn and bank
indicator(s), directional gyro, annunciator check, stall warning,
annunciator check of the stall warning circuit opening, fuel low
level signalling and minimum oil pressure signalling.
"PITOT HEATING" - turns “ON” and “OFF” the heating of the probe of total pressure
and of the stall speed warning probe
"STATIC HEATING" - turns “ON” and “OFF” the heating of static pressure probes
c) In the middle instrument panel are located switches "COM/NAV 1" and
"COM/NAV 2" (if installed), which turn on and off the radiocommunication and navigation
equipment.
d) In the right instrument panel are located switches “EMERGENCY SWITCH COM1” and
“EMERGENCY SWITCH ADF/NAV” (if installed), which enable to turn on the transmitter 1
and the signal monitoring for ADF and NAV1 in case of the audio control console failure.
NOTE:
The sense of the switches function:
TURNED “ON” - forward or upward position of the lever,
TURNED “OFF” - backward or downward position of the lever
CAUTION:
DO NOT OPERATE ANY SWITCH UNLESS YOU ARE EXACTLY FAMILIAR WITH ITS
FUNCTION.

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 12 EASA Approved 25.2.2017
7.11 GROUND CONTROL
When moving on the ground with the ground crew, use the control shaft mounted on the front
wheel axis. Maximum front wheel angle is 38 grades on either side of the axis of the aircraft.
7.13 WING FLAPS
Wing flaps are slot type, all-metal, mechanical controlled by means of a lever located between the
seats. Wing flaps have 3 arrested positions: RETRACTED (0o), TAKE-OFF (14o), LANDING (37o).
The arrestment is controlled by a pushbutton located on a lever. The wing flaps are extended by
moving the lever upward.
CAUTION:
NEVER STEP ON THE WING FLAPS - THESE MIGHT BE SERIOUSLY DAMAGED. EXTEND
THE FLAPS INTO THE POSITION “TAKE-OF” DURING EMBARKING OF THE OCCUPANTS
OR PILOT´S - THE RISK OF DAMAGE BY UNINTENTIONAL STEPPING IS REDUCED WITH
FLAPS IN THIS POSITION.
(flaps are arrested only in position “TAKE-OFF” and “LANDING”).
Fig. 7-6 Diagram of wing flaps 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 - 13
7.15 LANDING GEAR
Fixed tricycle landing gear consists of themain landing gear and nose landing gear.
The main landing gear is comprised of flat-steel springs, which are attached to the fuselage
main spar.
The nose landing gear is attached by means of struts to the first bulkhead of airframe fuselage.
The nose landing gear is provided with a hydropneumatic shock absorber and with a shimmy
damper.
The landing gear wheels are made of a light alloy with hydraulic disc brakes.
The nose wheel is not brakes.
7.17 BAGGAGE COMPARTMENT
The baggage compartment (rear shelf in cockpit) is located behind headrests of the pilot´s seat
and it is accessible from the cockpit. The floors of the baggage compartment are provided with
fastening straps and elastic for baggage put.
CAUTION:
THE BAGGAGE MUST ALLWAYS BE PROTECTED AGAINST MOVEMENT BY MEANS OF
STRAPS.
7.19 SEATS, SEAT BELTS AND SHOULDER HARNESSES
a) Seats
Pilot seats are adjustable in the longitudinal direction into 5 automatically arrested
positions. The position adjustment lever is located to the bottom of the seat front part.
After moving the lever upwards the seat is released for adjustment.
b) Safety belts
Both seats are provided with 5-point safety belts, which consists of ventral belts, two
shoulder straps, crotch belts and the lock “A”.
The safety belts lock “A” is controlled by turning the lock-gate on the front part, adjustable
in three positions:
1) Position „LOCKED“, green point
- fastening straps are locked
2) Position „DON“, yellow point
- position for inserting pawls into the lock
3) Position „RELEASE“
- position for releasing the pawls

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 14 EASA Approved 25.2.2017
Procedure for using the safety belts:
1) Sit down comfortably on the seat, arrange the safety belts to prevent their twisting.
2) Turn the lock-gate “A” into the position „DON“.
3) Slide the pawls of the straps free ends into the lock body.
4) Turn the lock-gate “A” into the position „LOCKED“.
5) To shorten the straps lenght, pull the free ends of the straps.
6) To release the belts, turn the lock-gate “A” into the position „RELEASE“; in this
position all three pawls are released. After being released, the lock-gate turns to the
position „DON“ automatically.
c) Headrests
The pilot seats are equpped with headrests, which are vertically adjustable into 5
positions. Individually positions are arrested by springs. To readjust the headrests
position, push or pull in the desired direction of rest adjustment.
A
seat position lever
adjustment
Fig. 7-7 - Seat and Safety Belt installation with detail of safety belt lock
A

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 - 15
7.21 DOORS, WINDOWS AND EXITS
The aircraft is equipped with cockpit canopy. The canopy is opened by sliding forward and it is
provided with an emergency jettisoning mechanism. Securing the cockpit canopy in its open
position on ground enables the arrestment lever, located on the canopy frame left side. Canopy
lock is controlled by a door handle located on the top of the canopy frame. In closed position the
handle points backward. To open the canopy, rotate the lever through 180oforward and slide the
canopy forward. The canopy can be locked from outside by key during airplane parking.
Canopy emergency jettisoning:
The lever for emergency release is located both on the left and on the right sides of the cockpit,
it is painted red and provided with a seal. The lever is controlled a sliding mechanism to the
airframe, which unlocked the pins connecting canopy frame with airframe sleight bell in strip
guide. The emergency jettisoning handles do not control canopy lock opening!
1 - sliding canopy 1 - canopy emergency jettisoning lever
2 - cockpit glass 2 - cockpit canopy hinges
3 - cooling windows 3 - door handle with lock for cockpit opened
4 - installation of emergency hammer (see 7.65)
Fig. 7-8 Diagram of cockpit sliding canopy with emergency jettisoning mechanism

Chapter 7 ZLIN AIRCRAFT a.s.
Description of the aircraft and its system Flight Manual Z 242 L
REVISION No. 3
7 - 16 EASA Approved 25.2.2017
7.23 CONTROL LOCK
During the airplane parking, the control stick can be locked by meams of a red latch, which is
located beneath the left instrument panel closer to central panel. The pilot gets the information
about the manual control being locked by means of:
a) the abnormal position of the stick (control sticks are push and right position)
b) the warning placard "WARNING - CONTROL LOCKED", appears after the control has
been engaged
Fig. 7-9 Control lock system