SKYCAR EVO is and evolution of the basic SKYCAR designed to comply with more demanding needs and requests of customers to have more flexibility, more specifically to:

Improve the payload range of the airplane.
Increase the aerodynamic efficiency.
Improve the use of the airplane in rugged environment and unpaved runaway operations.
Reduce operative and maintenance costs.
The main features of the airplane include the adoption of winglet and tip extentions that provide a wider wingspan (form 12mt of basic SKYCAR to 13.2mt of EVO) associated with increase the MTOW and the MZFW. Certification is expected by end of 2016

SKYCAR is designed for a single pilot IFR operations.
The cockpit design philosophy is to keep it simple, but use state-of-the-art technology. It’s completely “glass cockpit” drives for:

Enhancing situational awareness;
Improving system monitoring and control;

The design is based on an integrated digital avionics suite, which concentrates most of avionic functions, and uses of a large-scale colour displays. In addition, dual sensor configuration increases A/C reliability.

The suite completely integrates flight instruments, autopilot, communication, navigation, optional weather radar and lightning warning systems, interfaces to engine indication and crew alerting, and to other aircraft systems, providing a highly reliable system designed for ease of operation and reduced cockpit workload.
The design implements comprehensive integrated architecture both for baseline and optional functions and equipment.

Aircraft Dimensions

Fuselage height 2,55 m – 8,37 ft
Fuselage length 8,92 m – 29,27 ft
Wingspan 13,2 m – 43,31 ft
Cabin volume 4,98 m3 – 176 ft3
Max seating capacity 5
Fuel tank capacity 2×250 lt – 2×66 US Gal


Engine Manufacturer Lycoming IO-360 C1E6
Engine power 200 HP
Propeller Two-bladed Variable Pitch
Fuel consumption 36 lt/h – 9,5 US Gal /h (each engine)
Fuel type Avgas

Basic Avionics Package

#1 Primary Flight Display (PFD)
#1 Multi Function Display (MFD)
#1 Analogy Interface Unit
#2 Air Data Attitude Heading Reference System (ADAHRS)
#1 GPS/WAAS Receiver
#2 VHF Communication Radio/ VHF Nav function and GPS Receiver
#1 Two – axis fail-safe Auto Flight Control System (AFCS),
#1 Audio Panel with Marker Beacon
#1 Mode-S ATC Transponder
#1 Emergency Locator Transmitter Tx
#2 Engine Monitoring System

Instrument System

Electrical Stand-by Instrument System provides triple architecture redundancy with the following equipments:
1# Electrical Attitude Indicator – 2 inch
1# Airspeed indicator – 2 inch
1# Altitude Indicator – 2 inch
1# Magnetic Compass

Optional Avionics Package

#1 2nd Co-pilot Primary Flight Display (PFD)
#1 2nd Co-pilot Multi Function Display (MFD)
#1 ADF Receiver
#1 DME Receiver
#1 Radar Altimeter
#1 Weather Radar Sensor
#1 Stormscope ®
#1 TAS

Design Weigth & Loading

MTOW 2150 kg – 4740 lb
Useful Load 570 kg – 1260 lb
Baggage Allowance 334 kg – 736 lb


Vmax 289 km/h – 156 kts
Cruise speed 75% 265 km/h – 143 kts
Stall speed 113 km/h – 61 kts
Pratical ceiling 5500 m – 18000 ft
Take off run 364 m – 1194 ft
Take off distance 469 m – 1539 ft
Landing run 399 m – 1309 ft
Landing distance 614 m – 2014 ft
Rate of climb 6 m/s – 1175 ft/min
Range 55% ‘Best Economy’ 810 NM
Range 65% ‘Best Economy’ 755 NM
Range 75% ‘Best Power’ 600 NM