ZLIN Z 242 L ZEUS

<strong>ZLIN Z 242 L</strong> ZEUS

ZLIN Z 242 L ZEUS

<strong>ZLIN Z 242 L</strong> ZEUS

ZLIN Z 242 L ZEUS

<strong>ZLIN Z 242 L</strong> ZEUS

ZLIN Z 242 L ZEUS

<strong>ZLIN Z 242 L</strong> ZEUS

ZLIN Z 242 L ZEUS

<strong>ZLIN Z 242 L</strong> ZEUS

ZLIN Z 242 L ZEUS

<strong>ZLIN Z 242 L</strong> ZEUS

ZLIN Z 242 L ZEUS


ZLIN Z 242 L ZEUS is the best propeller aircraft for elementary, advanced and aerobatic training. It is an ICAO N/U/A category aircraft and is certified to EASA Category A CS23 airworthiness requirements (EASA Type Certificate No. EASA.A.027). It can be used for instrument training, day and night flights (VFR day/night and IFR). 



 

AIRCRAFT STRUCTURE

 

The aeroplane is a low-flying aircraft with all-metal construction and a fixed three-point landing gear with steerable nose gear. The design of the landing gear allows for take-off even on an unpaved runway. The aircraft design is tested and resistant to the full range of extreme weather conditions. Flight operations are possible in both simple and complex meteorological conditions with the possibility of operating the aircraft in climatic conditions from approximately -45°C to +45°C.

The Beringer brake system allows differentiated action of the brake system controls and their independent activation. 

 
  • 1090 kg – Max. take-off weight
  • 1056 km – Max. range
  • +6/-3,5 – Load factor
 
 

 

 

 

ENGINE

 


The aircraft is powered by a 210 HP Lycoming AEIO-390-A1A6 piston engine. The engine has no limitation of operation at full power and there is a time period of 1400 hours between engine overhauls.
 
The aircraft is equipped with a 3-blade MTV-9-B-C/C188-18a constant speed hydraulic propeller.
 
The fuel system and assemblies are designed to provide a reliable fuel supply to the engine under all flight conditions. The powerplant is also certified to use 100 LL aviation gasoline. 

 

  • 210 HP at 2700rpm
  • 29 litres per hour in economic mode



GARMIN AVIONICS

 

The ZLIN Z 242 L ZEUS is equipped with a Garmin G500TXi Glass Cockpit system with colour displays showing flight, navigation and engine information. The Garmin device allows for the recording of complex flight progress. The aircraft is available in three configurations of communication and navigation equipment. 

 



 


AIRCRAFT INTERIOR

 

The cockpit for two pilots side by side with an instructor on the right side is proven by historical experience in flight schools around the world. The configuration of the aircraft controls and instruments in the cockpit allows for single-pilot flights.
 
The cockpit provides excellent visibility during all flight positions. The abnormally spacious cockpit allows the crew to work even in pilot helmets. 
 
The longitudinally adjustable seats are equipped with 5-point safety belts and allow safe exit from the aircraft in emergency situations; they are compatible with rescue parachutes. The cockpit is equipped with a system for dropping the cockpit cover in the event of an in-flight emergency and allows safe and easy emergency exit of the aircraft with a parachute. The aircraft is equipped with a firewall between the engine compartment and the cockpit, and has a fire suppression system built into the engine compartment. 
 









 

Key features

 

  •   Two seats side by side
  •   All aluminium structure
  •   Both sides stick flight control
  •   Easy controllability
  •   High manoeuvrability
  •   Simple and easy maintenance
  •   Category N/U/A
  •   Night and IFR training
  •   Basic military and aerobatic training


Technical data - ZLIN Z 242 L ZEUS

 
 

Category

 

Aerobatics

   

Utility

   

Normal

 
   
▼   Metric
▼  Imperial
 
▼  Metric
Imperial
 
Metric
Imperial
Empty weight   745 kg 1642 lbs   745 kg 1642 lbs   745 kg 1642 lbs
Max. take-off weight   970 kg 2140 lbs   1020 kg 2250 lbs   1090 kg 2400 lbs
Load factor (g)   +6 / -3,5 +6 / -3,5   +5 / -3 +5 / -3   +3,8 / -1,5 +3,8 / -1,5
Take-off distance
(ground roll)
  210 m 689 ft   233 m 764 ft   266 m 873 ft
Take-off distance
(over 50 ft obstacle)
  450 m   1476 ft   495 m   1624 ft   565 m 1854 ft
Max. rate of climb
(sea level)
  5,5 m/s   1080 ft/min   5,0 m/s   980 ft/min   4,25 m/s 850 ft/min
 
Main tanks capacity   2 × 60 litres 2× 16 gals   2 × 60 litres 2× 16 gals   2 × 60 litres 2× 16 gals
Auxiliary tanks capacity                  
Range
(1900 RPM, 10000 ft, max. fuel capacity)
  800 km   431 NM   800 km   431 NM   800 km   431 NM


 
                 

Basic dimensions

                 
   
▼   Metric
▼  Imperial
 
 
 
     
Wing span   9,34 m 30,64 ft            
Length   6,94 m 22,77 ft            
Height   2,95 m 9,68 ft            


 

Engine

 

 

Manufacturer   TEXTRON Lycoming, USA
Type   AEIO-360-A1B6
Max. power (2700 RPM)   210 HP
Max. cruising power (2450 RPM)   150 HP
Economy cruising power (2350 RPM)     130 HP
     

Propeller (constant speed)

   
Manufacturer   MT Propeller, Germany
Type   MTV-9-B-C/C-188-18a (three-blade)

Category

Aerobatics Metric Imperial
Empty weight 745 kg 1642 lbs
Max. take-off weight 970 kg 2140 lbs
Load factor (g) +6 / -3,5 +6 / -3,5
Take-off distance (ground roll) 210 m 689 ft
Take-off distance (over 50 ft obstacle) 450 m 1476 ft
Max. rate of climb (sea level) 5,5 m/s 1080 ft/min
Main tanks capacity 2 × 60 litrů 2× 16 gals
Range (1900 RPM, 10000 ft, max. fuel capacity) 800 km 431 NM
Utility Metric Imperial
Empty weight 745 kg 1642 lbs
Max. take-off weight 1020 kg 2250 lbs
Load factor (g) +5 / -3 +5 / -3
Take-off distance (ground roll) 233 m 764 ft
Take-off distance (over 50 ft obstacle) 495 m 1624 ft
Max. rate of climb (sea level) 5,0 m/s 980 ft/min
Main tanks capacity 2 × 60 litrů 2× 16 gals
Range (1900 RPM, 10000 ft, max. fuel capacity) 800 km 431 NM
Normal Metric Imperial
Empty weight 745 kg 1642 lbs
Max. take-off weight 1090 kg 2400 lbs
Load factor (g) +3,8 / -1,5 +3,8 / -1,5
Take-off distance (ground roll) 266 m 873 ft
Take-off distance (over 50 ft obstacle) 565 m 1854 ft
Max. rate of climb (sea level) 4,25 m/s 850 ft/min
Main tanks capacity 2 × 60 litrů 2× 16 gals
Range (1900 RPM, 10000 ft, max. fuel capacity) 800 km 431 NM

Basic dimensions

Wing span 9,34 m 30,64 ft
Length 6,94 m 22,77 ft
Height 2,95 m 9,68 ft

Engine

Manufacturer TEXTRON Lycoming, USA
Type AEIO-360-A1B6
Max. power (2700 RPM) 210 HP
Max. cruising power (2450 RPM) 150 HP
Economy cruising power (2350 RPM) 130 HP

Propeller (constant speed)

Manufacturer MT Propeller, Germany
Type MTV-9-B-C/C-188-18a (three-blade)


The aircraft electrical power supply is provided by a working voltage of 28V. The electrical systems allow the engine to be started using battery power, but also from an external source. The aircraft is equipped with flash warning light, new elements of landing and taxiing diode headlight located in the left wing and position lights. 

The aircraft can also be equipped with a system to simulate the pilot's actions when retracting and extending the landing gear if the customer so wishes. 
 
The aircraft is delivered with a standard set of ground equipment and has defined sets of spare parts, which are supplied on customer request.
 

 

 

Gallery Z 242 L ZEUS



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