The MCR ULC specifications were established in 1996, defining it as an ultra-light airplane based on the FAI requirements, and first flown in April 1997. Based on the Sportster 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 MCR ULC characteristics lie in its wing design, involving a greater span and area, as well as split double slotted fowler flaps and ailerons.
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 , and fuselage footsteps. Engine options include the 80 hp Rotax 912, 100 hp Rotax 912S, and 80 hp Jabiru 2200.
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

The MCR ULC R is a direct evolution of the MCR ULC, available in kit form in respect with the CNSK regulation (specific kit airworthiness certificate) or in the “experimental” category, depending on the registration country.
Engine options include the 80 hp Rotax 912, 100 hp Rotax 912S, 100 hp turbo charged Rotax 914, and 80 hp Jabiru 2200.

The MCR M is a tail wheel evolution of the MCR ULC R, first flown in December 1999.
The MCR M 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.

Turbo, rescue parachute, autopilot. Price 2009: 100000 EURO

MCR ULC
Wing span; 8.64 m
Wing aera; 8.13 sq.m
Aspect ratio; 9.18
Cabin Width; 1.12 m
Fuel capacity standard; 80 lt
Extended range fuel tanks; 2 x 40 lt
Empty weight Basic version; 230 kg
Equipped empty weight; 270 kg
Max. Takeoff weight; 472 kg
Wing loading; 58 kg/sq.m
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

Engine; Rotax 912, 80 hp
Cruising 75%, FL 0; 250 km/h
Cruising 75%, FL 80; 270 km/h
Fuel consumption 75%; 17,1 lt/hr
Range ,std Tanks 75%; 1245 km
Cruising 65% FL110; 265 km/h
Fuel consumption 65%; 14,8 lt/hr
Range ,std Tanks 65%; 1432 km
Takeoff roll; CS. Prop; 140 m
Climb rate FL 0, CS; 1750 fpm

Engine; Rotax 912S, 100 hp
Cruising 75%, FL 0; 271 km/h
Cruising 75%, FL 80; 293 km/h
Fuel consumption 75%; 21,3 lt/hr
Range ,std Tanks 75%; 1097 km
Cruising 65% FL110; 288 km/h
Fuel consumption 65%; 18,5 lt/hr
Range ,std Tanks 65%; 1264 km
Takeoff roll; CS. Prop; 112 m
Climb rate FL 0, CS. Prop; 1950 fpm

MCR ULC R
Wing span; 8.64 m
Wing aera; 8.13 sq.m
Aspect ratio; 9.18
Cabin Width; 1.12 m
Fuel capacity standard; 80 l
Extended range fuel tanks; 2 x 40 lt
Empty weight Basic version; 230 kg
Equipped empty weight; 270 kg
Max. Takeoff weight; 490 kg
Wing loading; 60 kg/sq.m
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

Engine; Rotax 912, 80 hp
Cruising 75%, FL 0; 250 km/h
Cruising 75%, FL 80; 270 km/h
Fuel consumption 75%; 17,1 lt/hr
Range ,std Tanks 75%; 1245 km
Cruising 65% FL110; 265 km/h
Fuel consumption 65%; 14,8 lt/hr
Range ,std Tanks 65%; 1432 km
Takeoff roll; CS. Prop; 140 m
Climb rate FL 0, CS. Prop; 1750 fpm

Engine; Rotax 912S, 100 hp
Cruising 75%, FL 0; 271 km/h
Cruising 75%, FL 80; 293 km/h
Fuel consumption 75%; 21,3 lt/hr
Range ,std Tanks 75%; 1097 km
Cruising 65% FL110; 288 km/h
Fuel consumption 65%; 18,5 lt/hr
Range ,std Tanks 65%; 1264 km
Takeoff roll; CS. Prop; 112 m
Climb rate FL 0, CS. Prop; 1950 fpm

MCR M
Wing span; 8.64 m
Wing aera; 8.13 sq.m
Aspect ratio; 9.18
Cabin Width; 1.12 m
Fuel capacity standard; 80 lt
Extended range fuel tanks; 2 x 40 lt
Empty weight Basic version; 230 kg
Equipped empty weight; 270 kg
Max. Takeoff weight; 544 kg
Wing loading; 67 kg/sq.m
VSO (stall speed landing configuration); 70 km/h
Va (Maneuvering speed); 191 km/h
Vne ( Never exceeding speed); 315 km/h
Design maneuvering speed; 350 km/h
Vno (Normal Operation Speed); 221 km/h
G loading; +4 /-2 g
Vfe (Flaps extended speed); 140 km/h

Engine; Rotax 912, 80 hp
Cruising 75%, FL 0; 250 km/h
Cruising 75%, FL 80; 270 km/h
Fuel consumption 75%; 17,1 lt/hr
Range ,std Tanks 75%; 1245 km
Cruising 65% FL110; 265 km/h
Fuel consumption 65%; 14,8 lt/hr
Range ,std Tanks 65%; 1432 km
Takeoff roll; CS. Prop; 140 m
Climb rate FL 0, CS. Prop; 1750 fpm

Engine; Rotax 912S, 100 hp
Cruising 75%, FL 0; 271 km/h
Cruising 75%, FL 80; 293 km/h
Fuel consumption 75%; 21,3 lt/hr
Range ,std Tanks 75%; 1097 km
Cruising 65% FL110; 288 km/h
Fuel consumption 65%; 18,5 lt/hr
Range ,std Tanks 65%; 1264 km
Takeoff roll; CS. Prop; 112 m
Climb rate FL 0, CS. Prop; 1950 fpm

DynAero MCR MiniCruiser
Stall: 49 kt / 56 mph / 91 kmh
Cruise: 172 kt / 198 mph / 319 kmh
VNE: 175 kt / 201 mph / 324 kmh
Empty Weight: 250 kg / 551 lbs
MTOW Weight: 490 kg / 1080 lbs
Climb Ratio: 1750 ft/min / 9 m/s
Glide Ratio: 10
Take-off distance (50ft obstacle): 200 ft / 61 m
Landing distance (50ft obstacle): 350 ft / 107 m

The MCR range of aircraft is a result of 20 years research and development by Michel Colomban and the modern manufacturing techniques developed by DynAero. Michel Colomban was for many years an engineer and aerodynamicist and was associated with Morane-Saulnier, Potez and Aerospatiale.

MCR-01 stands for Michael Colomban Revolution –(series) 01, a carbon-based evolution of the Colomban MC100. When first designed and produced marketing was aimed at the plans-built community. It was successful in Europe.

When Colomban conceived the kit version he decided it would be easier to produce if its structure was all composite with a metal skin on the wing. By slightly enlargening the wing, eliminating the flaps and incorporating flaperons, the designer saved weight, but the all-composite wing was stronger.

Many engines have been used including the 100 hp Rotax 912S and JPX.

Manufactured by American Ghiles Aircraft as the Lafayetti 4S, it uses the Rotax 912S or 914 engine.

The wing and fuselage skin is made from layers of kevlar and carbon-fibre sandwich, with the control surfaces constructed from foam ribs supported by carbon spars and fused to an aluminium skin. Fitted with a constant-speed prop, almost ¾ span double slotted Fowler flaps, and of composite construction. First flown in 1996, the MCR 01 ULM employed double slotted flaperons, but it was soon discarded for separate flap and aileron.

At Epinal, Dyn’Aero showed a new version of the Ban-Bi with a redesigned wing and tail, the longer wing being now 27.1 ft instead of the 21.7 in the 21.7 in the normal kit. French regulations required a lower stall speed and this wing reduces it from 54 mph to 39 mph.

The initial design program started in early 1994, and the MCR Sportster flew for the first time in July 1996
The MCR Sportster is a side by side two-seater airplane with incredible performance and capability. Fast and agile, the VLA was specially designed to reach top speed while providing the most enjoyable experience to pilots.
The MCR Sportster is a very high performance aircraft, that can cruise as fast as 300 km/h with only a 100 hp engine, at very low cost. The Sportster has a direct control system and can be equipped with a choice of different power plants, but may also be fitted with other options including Ballistic Recovery System parachute, extended range wing tanks, and toe operated hydraulic brakes. Engine options include 80 hp Rotax 912, 100 hp Rotax 912S, 100 hp Rotax 914 turbo charged, and 80 hp Jabiru 2200.
The MCR Sportster 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.

The MCR CLUB is a direct evolution of the MCR Sportster. 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.
Equipped with a 80 HP engine and a fix pitch propeller, it is for intensive use in flight school operations or aviation clubs.
With a 100 HP engine and a constant speed propeller, it becomes an high performance airplane with fast cruising speed.

The MCR CLUB can be equipped with a choice of different power plants. Engine options include 80 hp Rotax 912, 100 hp Rotax 912S, 100 hp Rotax 914 turbo charged, and 80 hp Jabiru 2200. Other options including 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, and 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.

In 1999, another WINGGRID demonstrator was tested by the French, and Christopher Robin equipped an MCR-01 with winggrid. A comparative study with a conventional MCR-01 and another equipped with Winglets studied by ONERA was performed.

Gallery

Dyn’Aero MCR-01 Ban-Bi
Engine: Rotax / JPX
Wing span: 6.63 m
Wing area: 5.2 sq.m
MAUW: 450 kg
Empty weight: 230 kg
Fuel capacity: 88 lt
Max speed: 300 kph
Cruise speed: 267 kph
Minimum speed: 83 kph
Climb rate: 7 m/s
Seats: 2
Fuel consumption: 16.7 lt/hr
Kit price VLA fast build (1998): £16,500

Ghiles Lafayette / MCR-01
Engine; Rotax 912S, 100 hp
Wingspan; 22 ft 1 in
Wing area; 69.46 sq.ft
Aspect ratio; 7
Wing loading; 15.6 lb/sq.ft
Rate of climb; 1485 fpm
Length; 18 ft 5 in
Cabin width; 44 ft
Fuel capacity; 21 USG
Supplemental fuel tank; 24 USG
Empty weight; 508 lb
Equipped weight; 596 lb
MTOW; 1081 lb
Takeoff speed; 49 mph
Max maneuvering speed; 125 mph
Vne; 186 mph
Design speed; 207 mph
Max flap extension; 103 mph

DynAero MCR-01 ULC Ban-Bi
Engine: Rotax 912S, 80 hp.
Prop: Electric MT 3 blade constant speed.
Wing span: 29 ft.
Chord: 30 in constant.
Stall: 34 kt / 39 mph / 63 kmh
Cruise at 75% power, 141 kts
VNE: 160 kt / 184 mph / 296 kmh
ROC: 1500 fpm.
Glide ratio: 1:16.
Empty Weight: 250 kg / 551 lbs
MTOW Weight: 450 kg / 992 lbs
Take-off distance (50ft obstacle): 540 ft / 165 m
Range: 840 sm @ 162 mph.
Price 2009: 33804 EURO

MCR 01 UL
Empty weight: 230 kg
Wing span: 8.28 m
Wing area: 7.95 sq.m
Fuel capacity: 88 lt
Engine: Rotax 912, 80 hp
MAUW: 450 kg
Seats: 2
Max speed: 282 kph
Cruise speed: 271 kph
Minimum speed: 63 kph
Climb rate: 10 m/s
Fuel consumption: 17.7 lt/hr
Price (1998): 400,000 Fht
Kit price (1998): 160,000 Fht

Ban-Bi Club – U/C: Nose wheel.
Ban-Bi Montagne – U/C: tail wheel.
Ban-Bi ULM

VLA
Engine: Rotax 912, 80 hp.
MTOW stall: 52 mph.
Empty wt: 441 lbs.
MTOW: 1078 lbs.
Range: 930 sm @ 180 mph.