The MCR ULC specifications were established in 1996, defining it as an ultra-light airplane based on the FAI  requirements.

First flight was done in April 1997

Based on the VLA design, with the same fuselage and engine installation, the FAI ultra-light MCR-ULC was specifically designed for fast cruise and optimized for slow approach speeds.

The ULC characteristics lie in its unique wing design, involving a greater span and area, as well as split double slotted fowler flaps and ailerons

This sophisticated wing concept allows the MCR ULC to reach an unprecedented maximum to stall speed ratio of 4, although it guarantees a very gentle behavior in rough air conditions and a high safety level.

The MCR ULC can be  equipped with a choice of different power plants, but may also be fitted with other options such as : 

Ballistic Recovery System parachute

Oil Pneumatic under carriage ( for intensive use)

Extended ferrying fuel

Toe operated Hydraulic brakes

Fuselage footsteps 

The MCR ULC can be delivered in kit, or ready-to-fly.

The MCR ULC is available in a kit form in respect with the CNSK regulation (specific kit airworthiness certificate) or in the “experimental” category, depending on the registration country.

Ready-to-fly delivered aircraft are in the Ultra-light category

GENERAL CARACTERISTICS

Wing span.................................................... 8,64 m

Wing area .................................................. 8,13 m²

Aspect ratio..................................................... 9,18

Cabin Width .................................................... 1,12

Fuel capacity standard....................................... 80 l

Extended range fuel tanks............................ 2 X 40 l

Empty weight (Basic version) ........................ 230 kg

Equipped empty weight.................................. 270 kg

Max. Takeoff weight ..................................... 472 kg

Wing loading............................................. 58 kg/m²

 

ENGINE OPTIONS

Propeller :Two, or three blades, fix pitch or constant speed

Rotax 912 Engine............................................ 80 hp

Rotax 912S Engine........................................ 100 hp

Jabiru 2200 Engine......................................... 80 hp

 

V Speed

VSO (stall speed landing configuration) ........ 63 km/h

Va (Maneuvering speed)............................. 172 km/h

Vne ( Never exceeding speed).................... 270 km/h

Design maneuvering speed...................... 300 km/h

Vno (Normal Operation Speed)................... 210 km/h

G loading................................................... +4 /-2 g

Vfe (Flaps extended speed)........................ 140 km/h

PERFORMANCES