ZLIN Z 242 L GURU
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
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
- 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.
Complex data is collected in real-time on two large, adjustable, high-resolution screens.
AIRCRAFT INTERIOR

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