Based on previous types Z-42 / Z-142 / Z-43, of which more than 750 pieces were made, the ZLIN Z-143L has been in serial production since 1995.
The plane is designed for:

Basic and advanced training in civil or military air schools
Aerobatic training
Optional glider and banner towing
Night + IFR training and flying
Ground observation, naval and coast patrol
Air taxi, tourist, light business and family flying
The plane can be operated in Normal and Utility categories, within load limitations of +4.4 / -1.76 g factor.
The plane is certified in the Czech Republic, Slovakia, Switzerland, Bulgaria, Germany, JAR and FAA certificates.

The Z-143L is a single engine, four seat, low wing, cantilever monoplane of whole metal structure. The seat arrangement is 2 + 2. lt is powered by a , type O-540-J3A5 with a three blade, hydraulic pitch controlled propeller, Mühlbauer type MTV-9-B/195-45a or a Hartzell type HC-C3YR-4BF/FC 6890 propeller.
The Aircraft complies with the very strict Swiss noise regulations and is certified in the lowest and therefore cheapest noise class, and that is class D.

LANDING GEAR
The non-retractable, tricycle landing gear consists of the main landing gear and the nose gear. The main landing gear wheels are equipped with hydraulic disc-brakes including automatic clearance adjustment. Wheels can be delivered with Barum or Good Year tyres.

CONTROL SYSTEM
The aircraft is provided with dual stick- and rudder-controls . Elevator and ailerons are tie-rod operated, the rudder is tie-rod and additional cable operated. The nose wheel is coupled with the rudder control. The aircraft is equipped with elevator and rudder trims, ailerons are trimmed by fixed tabs.

FUEL AND OIL SYSTEM
The main fuel tanks are situated in the wing leading edge with a capacity of 2 x 61 litres (2 x 16.1 US gallons). The auxiliary fuel tanks are attached to the wing tips (2 x 51 litres / 2 x 13.4 US gallons). The oil tank is apart of the engine.

ELECTRICAL SYSTEM
The electrical system is of single-wire type (+ pole). The nominal DC voltage is 28 V. The primary power source is the 1600 W generator (alternator). As an auxiliary power source serves a 19 Ah capacity battery. All electical systems and equipment are protected by circuit braker switches. The power source is secured by a second battery to guarantee internal power supply at all times.

AVIONICS
Avionics packages based on Bendix King Silver Crown equipment, available in option.

GUARANTEE AND WARRANTY
Moravan provides warranty, on the assumption of normal use of the plane, of 200 flight hours or for a one year period after acceptance, whichever comes first. Moravan guarantees technical service for a lifetime of 3500 flight hours for the airframe with respect to operational limitations and maintenance procedures. The service period will be prolonged based on operational and technical structure conditions.
12 months for engine under Lycoming warranty card, 12 months for propeller under Mühlbauer warranty card and 18 months for Bendix King avionics under B/K warranty card.

TECHNICAL SERVICES
All technical information concerning the plane manufactured by Moravan Inc. are distributed by bulletin service.

Engine Manufacturer
TEXTRON Lycoming, USA Type O-540-J3A5

Power
Max take-off 175 kW (235 HP)
2400 RPM max contin. 175 kW (235 HP)
2400 RPM cruising 75% MC 130 kW (175 HP)
2200 RPM cruising 60% MC 104 kW (140 HP)

Propeller Manufacturer
MT PROPELLER Entwicklung, Germany
Type MTV-9-B/195-45a
Number of blades 3
Diameter 1950 mm

Aircraft Dimensions
Wing span 10.14 m 33.25 ft
Length 7.58 m 24.86 ft
Height 2.91 m 9.55 ft
Wheel track 2.44 m 8.00 ft

STANDARD EQUIPMENT

Power plant and accessories
Lycoming O-540-J3A5 engine
Propeller Mühlbauer or Hartzell, 3 blades
Propeller spinner
Dry air filter
Dual ignition
Electric starter
Engine mounts with dampers
Engine oil cooler
Carburetor

Fuel system
2 x 16.1 US gallon main tanks (wing roots)
2 x 13.4 US gallon auxiliary tanks (wing tips) Fuel sampling cup
Fuel pump [engine driven]
Fuel pump [electric]
Individual fuel tank drains

Airframe and landing gear
4 places, 2 + 2 configuration
Welded steel tube central fuselage
Anodized aluminum skin
Barum or Good Year tyres
Fixed tricycle landing gear of nose type
Hydraulic disc brake system
Main spar nitrogen pressurized
Hydropneumatic nose wheel strut with shimmy damper
Sliding canopy with lock
Balanced rudder, ailerons and elevator

Cabin features
Adjustable cloth and vinyl seats
Adjustable cabin ventilation and heater
Dual map pocket
Baggage compartment
Dual headset hangers
Canopy lock
Aircraft tow bar

Flight and ground controls
Dual stick controls (tie rod operated)
Wing flaps control
Engine throttle control
Dual toe activated brake control
Fuel shut off valve
Parking brake
Mixture control
Propeller control
Carburetor warm up control

Electrical system
28 volt, 19 Ah battery
Battery and electrical system circuit brakers Emergency T&B indicator power supply
External auxiliary power supply socket
Fused avionics circuits
Generator
Master switch
Rocker switches

Instrumentation
Air speed indicator
Altimeter
Vertical speed indicator
Turn & Bank indicator
Exhaust gas temperature gauge
G-meter
Magnetic compass
Manifold pressure indicator
Oil temperature / pressure, fuel pressure gauge
Quadruple fuel tank gauge
Spar stress gauge
Stall warning horn
Systems annunciator lights
Engine RPM indicator
Cylinder head temperature indicator

External features
Priming (ground) coat
Canopy cover
Heated pitot tube and ram pressure sensing unit
Pitot and static system water separation
Quick release access panel on wings and fuselage
Left and right boarding steps

Lights
Halogen taxi and landing lights
Rotating beacon

Fire protection and safety features
Ejection canopy with dual quick release handles
Four point release seatbelt harness
Fireproofed hoses in engine compartment
Firewall
Fire extinguisher
Medical box

Aircraft documentation
Aircraft Flight Manual
Engine and Propeller Operators Manuals
Maintenance Manual Vol I

The S-TEC system 55 is designed specifically to be integrated into the aircraft radio panel with other avionics, combining the programmer, computer, annunciator and servo amplifier functions into one compact panel mount unit.
The system 55 roll axis has heading select, VOR/Localizer/approach front and back course intercept and tracking. It can be interfaced with RNAV, GPS, or Loran systems, and all radio couplers are standard.

Features of the roll computer:
Receives signal inputs from directional gyro
Computes roll servo commands for stabilization, turns, radio intercepts and tracking
Pilot selectable intercept angles

Features of the pitch computer:
Receives signal inputs from altitude pressure transducer, accelerometer, glideslope deviation indicator and vertical speed modifier control
Computes pitch servo commands for vertical speed, altitude hold and automatic glideslope intercept and tracking, from below the glideslope and manual coupling from above

Available Options:
Remote annunciator (required with flight director option)
Flight director steering horizon
Slaved horizontal situation indicator
Automatic elevator pitch trim
Altitude / vertical speed selector alerter
Yaw damper / rudder trim system

	Basic S-TEC System 55 interfaced with an existing HSI-system including heading mode, VOR/LOC - intercept and tracking, glide slope (GS) capture and tracking, vertical speed command for climb and descent control, altitude hold, controls wheel steering (CWS) and VOR/LOC/GS off course deviation warning (For autotrim see Option A)
	Directional Gyro (if no HSI-system is installed)
	Option A Autotrim The autotrim system provides automatic elevator trim follow-up when the pitch axis of the autopilot is engaged. In addition a control wheel mounted manual trim command switch is provided for electric trim operation when autopilot is not used.
	Option B Mode annunciator, flight director indicator The annunciator indicates all the actual autopilot modes. The option with a liquid crystal display remote unit is required if a flight director is installed.
	Only mode annunciator without flight director installation
	Option C Altitude preselect / alerter The altitude and vertical speed selector indicator allows to preselect altitudes and rates of climb or descent for the autopilot. In addition to these basic functions the selector provides an altitude alert mode, a decision height alert mode, an altitude read out from the encoder, and a barometric calibration in inches of mercury or millibar.
	Option D Dual stick control Dual stick control allows the autopilot system and manual pitch on both sides. The Pilot (lefthand control stick) has the priority of the trim function.
	Option E GPS/VHF NAV switching HSI/autopilot approx. Select source for navigation: GPS or VHF NAV.

Zlin 143L is equipped with a powerful Lycoming 0-540-J3A5 (or IO-540) engine, which is limited to 235 HP. Many airplanes all over the world fly with this thrustworthy engine.
Thanks to the limitation the handling of the oil pressure controlled three blade constant speed propeller is very easy, because every thinkable power setting, even maximum manifold pressure and min / max RPM, cannot harm the engine. Therefore basic pilot training is no problem.

AIRCRAFT OPTIONAL AVIONICS

Silver Crown of Bendix King

L242 861601 Avionics package I
KY96A COMM Transceiver
KT76A Transponder
AT3000 Altitude encoder remote unit

L242 861602 Avionics package II
KY96A COMM Transceiver
KT76A Transponder
AT3000 Altitude encoder remote unit

L242 8621 Avionics package III
KA134 Audio control console / Intercom
KY96A COMM Transceiver
KT76A Transponder
AT3000 Altitude encoder remote unit

L242 8613 Avionics package IV
KMA24 H-70 Audio control console / Intercom KX165 NAV / COMM Transceiver (incl. VOR / LOC / GS indic. KI 204)
KR87 Digital ADF (incl. ADF ant KA 44B & ADF indic. KI 227)
KT76A Transponder
AT3000 Altitude encoder remote unit

L143 861404 Avionics package V
KMA24 H-70 Audio control console / Intercom KX 165 NAV / COMM Transceiver (incl. VOR / LOC / GS indicator KI 206)
KR87 Digital ADF (incl. ADF ant. KA 44B & ADF ind. KI 227)
KT76A Transponder
KR21 Marker receiver
AT3000 Altitude encoder remote unit

L242 8615 Avionics package VI
KMA24 Audio control console
KX155 NAV / COMM Transceiver (incl. VOR / LOC / GS indicator KI 204)
KN62A Complete panel-mounted digital DME KR87 Digital ADF (incl. ADF ant. KA 44B & ADF indicator KI 227)
KY96A COMM Transceiver
KT76A Transponder
AT3000 Altitude encoder remote unit

L143 861401 Avionics package VII
KMA24 Audio control console
KX155 NAV / COMM Transceiver 2 pcs (incl. VOR / LOC / GS indicator KI 204, 2 pcs)
KN 62A Complete panel-mounted digital DME KR87 Digital ADF (incl. KA 44B ant. & ADF ind. KI 227) KT76A Transponder
AT3000 Altitude encoder remote unit

L143 861402 Avionics package VIII
KMA 24H-70 Audio control console / Intercom KX155 NAV / COMM Transceiver 2 pcs (incl. VOR / LOC indicator KI 203 and VOR / LOC / GS indicator KI 204)
KN62A Complete panel-mounted digital DME KR87 Digital ADF (incl. ADF ant. KA 44B & ADF ind. KI 227)
KT76A Transponder
KR21 Marker receiver
AT3000 Altitude encoder remote unit

L243 8611 Avionics package IX
KA134 Audio control console
KY196A COMM Transceiver 2 pcs
KNS81 Integrated navigation system (RNAV) (incl. VOR / LOC / GS ind. KI 206)
KR87 Digital ADF (incl. ADF ant. KA 44B & ADF ind. KI 227)
KT71 Transponder
KR21 Marker receiver
KN63 Complete digital DME (incl. KDI 572 DME ind.) 5035-P2-P44 Encoding altimeter

L242 8611 Avionics package X
KMA 24H-70 Audio control console / Intercom KY196A COMM Transceiver
KNS81 Integrated navigation system (incl. VOR / LOC / GS ind. KI 206)
KX165 NAV / COMM Transceiver
KR87 Digital ADF (incl. ADF ant. KA 44B & ADF ind. KI 227)
KT71 Transponder
KR21 Marker receiver
KN63 Complete digital DME (incl. KDI 572 DME ind.) 5035-P2-P44 Encoding altimeter
KCS55A HSI NAV (incl. KI 525A HSI, KG 102A directional gyro KMT 112 magn. slaving transmitter, KA 51B slave CTL)

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