Z 242 L ZEUS
Z 143 LSi GENIUSZLIN Z 242 L ZEUS
ZLIN Z 242 L ZEUS
ZLIN Z 242 L ZEUS
ZLIN Z 242 L ZEUS
ZLIN Z 242 L ZEUS
ZLIN Z 242 L 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
Video Z 242 L
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ENGINE
The aircraft is powered by a 200 HP Lycoming AEIO-360-A1B6 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.
- 200 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 |
|||||
| 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 | ||||
|
|
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Basic dimensions |
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▼ 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) | 200 HP | |
| Max. cruising power (2450 RPM) | 150 HP | |
| Economy cruising power (2350 RPM) | 126 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) | 200 HP | |
| Max. cruising power (2450 RPM) | 150 HP | |
| Economy cruising power (2350 RPM) | 126 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.
