The MCR CLUB is a direct evolution of the MCR VLA. It is also a side by side two-seater airplane, it is designed around the same fuselage with an identical cockpit and engine installation. The MCR Club  appears for the first time in 1998. Its construction and design was developed in partnership with an Aviation club for its own use.

The MCR CLUB  has been designed around high safety standards and wings efficiency, providing both extreme exibility and easy flight characteristics.

Equipped with a 80 HP engine and a fix pitch propeller, it is the ideal airplane for intensive use in flight school operations or aviation clubs.

With a 100 HP engine and a constant speed propeller, it becomes an efficient high performance airplane combining fast cruising speed and easy handle characteristics

The MCR CLUB  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 range fuel tanks in the fuselage, (particularly for school or training operations)

Toe operated Hydraulic brakes

Fuselage footsteps 

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

GENERAL CARACTERISTICS

Wing span.................................................... 6,72 m

Wing area .................................................. 6,45 m²

Aspect ratio..................................................... 7,00

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

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

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

Empty weight (Basic version) ........................ 220 kg

Equipped empty weight.................................. 260 kg

Max. Takeoff weight ..................................... 490 kg

Wing loading............................................. 76 kg/m²

 

ENGINE OPTIONS

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

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

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

Rotax 914 turbo charged Engine..................... 100 hp

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

 

V Speed

VSO (stall speed landing configuration) ........ 79 km/h

Va (Manoeuvring speed)............................. 202 km/h

Vne ( Never exceeding speed).................... 300 km/h

Design manoeuvring speed...................... 333 km/h

Vno (Normal Operation Speed)................... 255 km/h

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

Vfe (Flaps extended speed)........................ 165 km/h

PERFORMANCES