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Zlin Aircraft Z 242 L Airplane Flight Manual

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Serial No.:
Registration Mark:
Manufacturer:
Category:
Certification Basis:
THIS DOCUMENT MUST BE CARRIED IN THE AIRPLANE AT ALL OPERATION TIMES!
THIS AIRPLANE FLIGHT MANUAL IS EASA APPROVED UNDER APPROVAL NO.: 10042932.
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
ISSUE OF REVISION No. 3 IS APPROVED UNDER DOA No. EASA.21J.110 APPROVAL
AIRPLANE FLIGHT MANUAL
Document No. 003.012.1
................................................
................................................
ZLIN AIRCRAFT a.s.
OTROKOVICE 765 02
CZECH REPUBLIC
ACROBATIC
UTILITY
NORMAL
FAR Part 23 as amended trough Amendment 23 - 41 inclusive
FAR Part 36 as amended trough Amendment Amdt. 36 - 20 inclusive
ICAO, Annex 16.
DATE OF APPROVAL: 9.3.2017
Z 242 L
(A)
(U)
(N)
DATE OF APPROVAL: 7.1.2013
Copyright © 2011
ZLIN AIRCRAFT a.s.
765 02 OTROKOVICE
Czech Republic

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Summary of Contents for Zlin Aircraft Z 242 L

  • Page 1 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.
  • Page 2 ZLIN AIRCRAFT a.s. Chapter 0 Z 242 L Flight Manual Technical information 0.3.2 Log of revisions Date of Date of revision Rev. Description / eligibility Pages affected: issue of new incorporation and page signature Implementation of new load 0-5, 0-7, 2-9 1.
  • Page 3 ZLIN AIRCRAFT a.s. Chapter 0 Z 242 L Flight Manual Technical information LIST OF EFFECTIVE PAGES Page No. Date of issue Validity Page No. Date of issue Validity 0 - 1 20.3.2011 2 - 1 20.3.2011 0 - 2 20.3.2011 2 - 2 20.3.2011...
  • Page 4 ZLIN AIRCRAFT a.s. Chapter 0 Z 242 L Flight Manual Technical information Page No. Date of issue Validity Page No. Date of issue Validity 7 - 1 25.2.2017 8 - 1 20.3.2011 7 - 2 25.2.2017 8 - 2 20.3.2011 7 - 3 25.2.2017...

  • Page 5: Table Of Contents

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems SECTION 7 - DESCRIPTION OF THE AIRCRAFT AND ITS SYSTEMS CONTENTS Section Page General 7 - 3 Airframe 7 - 3 Flight controls...
  • Page 6 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system INTENTIONALLY LEFT BLANK REVISION No. 3 7 - 2 EASA Approved 25.2.2017...

  • Page 7: General

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 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.

  • Page 8: Flight Controls

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system FLIGHT CONTROLS The aircraft is provided with a dual control for training purposes. Manual control is levers steering, pedal control is pedals steering.
  • Page 9 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems Trim: 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.

  • Page 10: Instrument Panel

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system INSTRUMENT PANEL Pilot’s compartment 7.7.1 Control stick 19 - Instrument lighting dimmers Intercom pushbutton (IC) 20 - Main spar flange nitrogen pressure Transmitter pushbutton (VHF)
  • Page 11 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems Control stick 19 - Instrument lighting dimmers 20 - Main spar flange nitrogen pressure Transmitter pushbutton (VHF) indicator Canopy arrestment in open position...
  • Page 12 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system NOTES: Items written by italic are delivered as optional equipment only. 7.7.2 Instrument panel This subsection provides a typical instrument equipment illustration. - Airspeed indicator I - Attitude gyro II (Turn and Bank ind.
  • Page 13 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems - Primary Flight Display (PFD) - Accelerometer - Multifunction Flight Display (MFD) - V-A meter - Airspeed indicator I - R.P.M. indicator - Altimeter I...
  • Page 14 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 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).
  • Page 15 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.7.4 Description of the Switches 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.

  • Page 16: Ground Control

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 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.

  • Page 17: Landing Gear

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 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.
  • Page 18 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system Procedure for using the safety belts: Sit down comfortably on the seat, arrange the safety belts to prevent their twisting. Turn the lock-gate “A” into the position „DON“.

  • Page 19: Doors, Windows And Exits

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 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.

  • Page 20: Control Locks

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 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...

  • Page 21: Engine

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.25 ENGINE The engine type TEXTRON LYCOMING AEIO-360-A1B6, piston type, four-stroke, air cooled, flat, right-handed four cylinder engine, with maximum continuous power 200 HP (149 kW) and 2700 R.P.M.
  • Page 22 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 1 - engine cooling flap control 2 - mixture control 3 - propeller control 4 - throttle control 5 - left throttle control Fig.
  • Page 23 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.25.2 Engine oil system The oil tank is contained engine crankcase (1). The oil quantity in the engine crankcase is checked of an oil gauge (16) - the maximum filling is 7,6 litres (8 quart).
  • Page 24 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 7.25.3 Engine instruments The engine run is monitored by the following: The oil pressure: is draw from engine back wall (above the right magneto) and is divided in two branches.
  • Page 25 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.25.5 Engine suction and cooling Engine cooling air is supplied from the of engine front parts covers to the engine cylinders, oil cooler (is located on the right rear sides of inner engine covers) and aggregates.

  • Page 26: Propeller

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 7.25.6 Fuel injection system The engine is equipped with a BENDIX RSA - 5AD1 fuel injection system with manual mixture control and with a stop function for engine shut-off. From the injector (priming pump) (22) is fuel supplied into the fuel distributor (21), from where is fuel supplied to the individual cylinders of injector nozzle (20).

  • Page 27: Fuel System

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.29 FUEL SYSTEM The fuel tanks are located in the wings - the main tanks (2) containing 2x60 l (2x16 U.S.gal) of usable fuel are attached to the main spar in the central nose part of each wing, the auxiliary tanks (19) containing 2x55 l (2x14,5 U.S.gal) of usable fuel are attached at the wing ends before...
  • Page 28 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 1 - fuel tank cap 14 - venting outlet 2 - main fuel tank 15 - single-way flap valve 3.- float gauge 16 - flexible hose 3.- float gauge (aircraft´s up to S/N 074 incl.)

  • Page 29: Brake System

    ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.33 BRAKE SYSTEM The aircraft is equipped with hydraulic disc brakes provided with matalceramic lining and are fitted with automatic clearance adjustment. The brakes are controlled individually by means of brake toe pedals, attached to the pedals of the directional control.

  • Page 30: Power Steering

    The appropriate circuit diagrams of these circuits are detailed illustrated in the Maintenance Manual Z 242 L, Volume I. The main switch opens all circuit except of the ignition and the cockpit lighting. The ignition circuit (magnetos) is controlled by the magneto switch.
  • Page 31 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems Fig. 7-15 Simplified diagram of the electrical system 7.37.1 V-A meter The V-A meter is a combined instrument, which indicates the voltage and the current in the airplane electric network.
  • Page 32 Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 7.37.2 Circuit protection The circuit switches located on the panel between the pilot´s seats and the switches COM/NAV 1 and COM/NAV 2 function as automatic circuit breakers. In case of the circuit overload this switch turns off automatically - turning off is indicated by the switch lever position “OFF”.
  • Page 33 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems Designation of placards in fuses: COM 1, COM 2 (6,3 A) - transceivers 1 and 2 (3,15 A) - navigation equipment (1 A)

  • Page 34: Lighting System

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system Procedure of connecting the external source: External source plug - CONNECT "EXT. POW. SOURCE" switch - ON "EXT. POW. SOURCE" signal light on the annunciator...
  • Page 35 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems Anticollision beacon (optional equipment) The anticollision beacon is located on the rudder top. To turn the anticollision beacon “ON”, use the switch “BEACON”.

  • Page 36: Heating, Ventilating, Defrosting And Air Conditioning

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 7.43 HEATING, VENTILATING, DEFROSTING AND AIR CONDITIONING 7.43.1 Heating The outside air flows through the sump in the front part of the engine bottom covers in two heat exchangers (1), (2) on the exhaust manifold.
  • Page 37 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems 7.43.2 Ventilating Fresh air enters the regulating chamber through the air-intake in front of the sliding canopy frame. The flap valve (3) in the regulation chamber controls and distributes the airflow, the valve is controlled by the string mechanism connected to the push/pull handle (4) on the cockpit central panel.

  • Page 38: Pitot Pressure System

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 7.49 PITOT PRESSURE SYSTEM Total pitot pressure for the airspeed indicator is supplied from the Pitot tube (10), located on the bottom of the left wing. The line is provided by transparent drainage sumps (5), located on the left side of the bottom fuselage cover.
  • Page 39 ZLIN AIRCRAFT a.s. Chapter 7 Z 242 L Flight Manual Description of the aircraft and its systems A – system without alternate static pressure source - only VFR operation B – system with alternate static pressure source (airplanes up to S/N 0659 including) C –...

  • Page 40: Avionics

    Chapter 7 ZLIN AIRCRAFT a.s. Flight Manual Z 242 L Description of the aircraft and its system 7.59 ICING PROTECTION All probes of pitot-static, Pitot tube, stall warning system are provided with electrical heating elements, that prevents the probes against icing.

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