Z 242 L GURU
Z 143 LSi GENIUSZLIN Z 242 L GURU
ZLIN Z 242 L GURU
MASTER OF CHAMPIONS. SIMPLICITY AND POWER
ZLIN Z 242 L GURU
All-metal, aluminum structure of the aircraft
ZLIN Z 242 L GURU
High performance and easy to control
ZLIN Z 242 L GURU
Easy maintenance at minimum cost
ZLIN Z 242 L GURU
Monitoring the safe-life of the aircraft
ZLIN Z 242 L GURU
MASTER OF CHAMPIONS. SIMPLICITY AND POWER
ZLIN Z 242 L GURU
All-metal, aluminum structure of the aircraft
ZLIN Z 242 L GURU
High performance and easy to control
ZLIN Z 242 L GURU
Easy maintenance at minimum cost
The ZLIN Z 242 L GURU training and fully aerobatic two-seat aircraft demonstrates a good balance between usefulness and superb flight capabilities. It is the result of challenging the ideas and experience of both pilots and engineers to deliver a pleasant and purposeful, yet safe flight experience.
AIRCRAFT STRUCTURE
A unique all-metal riveted airframe. The main beam of the central wing is furnished with a structural nitrogen overpressure control. The landing gear is also designed to operate on unpaved runways.
- 1090 kg – Max. take-off weight
- 1056 km – Max. range
- +6/-3,5 – Load factor
Videos Z 242L
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The low-wing airplane concept
and cabin structure allow unlimited and perfect visibility thanks to non-replicable construction solutions and is an advantage during flight. It offers excellent orientation when landing, taxiing, and in the event of an emergency escape from the cockpit.
The safe-life system
is used to monitor and evaluate the lifetime of an airplane. This exceeds 20,000 flight hours.
ENGINE
The American Textron Lycoming injection engine, coupled with a constant speed propeller together with excellent airplane flight characteristics and precise and responsive control, allows for all training flight maneuvers to be carried out.
The powerful engine
allows mastering demanding requirements, primarily by novice pilots. Engine operating time at maximum revolutions is unlimited.
The MTV-9-B-C / C-188-18
three-blade composite propeller
. The propeller is hydraulically adjustable with constant speed.
- 200 HP at 2400rpm
- 29 litres per hour in econ. mode
GARMIN AVIONICS
Garmin G500 multifunctional avionics adapted for the ZLIN Z 242 L GURU integrates all basic flight and engine instruments into digital screens.
The
3D terrain viewing feature
is an invaluable tool. The system is set for maximum use and intuitive control. It allows pilots to gain a unique view of the situation and thus increase crew safety.
Complex data is collected in real-time on two large, adjustable, high-resolution screens.
AIRCRAFT INTERIOR
The spatially exclusive design of the all-glass canopy allows a perfect overview of what is happening around the ZLIN. The canopy opens reliably in all situations in a simple forward motion. It is equipped with a stopping mechanism and an emergency jettison system.
The layout of the control elements and instruments
contributes to the comfort of the crew. The training aircraft can be controlled from both pilot seats independently.
Ergonomically and precisely shaped adjustable seats are a must component of a ZLIN aircraft today.
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 GURU
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) | |
