Dyn'Aero MCR01

Dyn'Aero MCR01
MCR01 VLA
Role	Light Aircraft / Ultralight
Manufacturer	Dyn'Aero
Status	In production
Number built	500+
Developed from	MC100

The Dyn'Aero MCR01 is a two or four seat, low-wing, all-composite carbon fibre light aircraft manufacturing by Societe Dyn'Aéro of Darois, France.^[1]

Development

The MCR01 is a homebuilt variant of the Colomban MC-100 originally designed by Michel Colomban.

The MCR01 program started in July 1994, with the prototype's first flight following in July 1996. The MCR01 UL model was first flown in June 1997. By June 1998 the type had achieved French "ultralight" airworthiness certification of the MCR-UL version, with German certification following in October 1998 and Peruvian certification of the MCR VLA model in December 2000. The "Club version" of the MCR01 was first flown in July 1997, the MCR ULC model in June 1999 and the MCR M model for all-terrain and mountain operations in December 1999.^{[citation needed]}

Design work that would result in the four-seat "MCR4S" version started in September 1998, with the model's first flight in June 2000. In July 2001 the MCR 4S was flown with the turbocharged Rotax 914 powerplant.^{[citation needed]}

Design

A Rotax 912S installed in a Dynaero 'Club'

The two-seat versions of the aircraft are usually fitted with the 100 hp (75 kW) Rotax 912S. However they have also been fitted with the 80 hp (60 kW) Rotax 912 and 115 hp (86 kW) turbocharged Rotax 914. At least one aircraft has been fitted with the 80 hp (60 kW) Jabiru 2200 direct drive engine.^{[citation needed]}

Variants

MCR01 'VLA'

The MCR01 VLA is the standard Very Light Aircraft (VLA) version of the MCR, with combined aileron/flaps, and able to be registered in the 'experimental' category in most countries and flown on a Private Pilot's Licence. The maximum speed is 318 km/h (198 mph or 172 kts) when powered by the Rotax 912S while the stall speed in landing configuration is 87 km/h (54 mph or 47 kts). The wing of this aircraft has a chord as short as 0.80 m and an area of 5.20 m².^{[citation needed]}

MCR01 'CLUB'

The MCR01 CLUB (often called the 'Ban-Bi') is a version with a slightly bigger wing than the VLA, and meets the microlight (ultralight) regulations for Australia and New Zealand and some other countries.

A Dyn'Aero 'MCR01 Club'

The 'Club' has a maximum speed of 300 km/h (184 mph or 160 kts) which makes it one of the fastest Rotax powered aircraft. The wing has a chord of 0.96 m and an area of 6.45 m². The stall speed is 83 km/h (51 mph or 44 kts), which is achieved on the narrow and short wings by having large double slotted flaps that occupy approx 1/3 of the chord and 2/3 of the span, giving a very different wing profile with flaps down from 'clean'. This allows for an unusually large stall/VNE ratio of 3.6.^{[citation needed]}

The takeoff roll is 152 m long and the climb rate 1750 ft/min. The take off weight for the 2 seat versions varies from 450 kg to 544 kg depending on model and country of operation.^{[citation needed]}

The standard fuel capacity is 80 litres in a centre tank, burning 21 L/h at 135kts for a range of 925km (591 miles or 514 nautical miles). At 125kts burning 15 L/h the range is 1200km (766 miles or 666 nautical miles). With the optional long range wet wing tanks adding 70L a side in addition to the 80L centre tank, the total of 220L gives a range of 2500km (1626 miles or 1414 nautical miles) at 135kts, or 3300km (2100 miles or 1830 nautical miles) at 125kts.^{[citation needed]}

MCR01 'ULC'

The MCR01 ULC is similar to the 'Club' but with a larger wing span than the 'Club' in order to lower the stall speed for countries such as the UK where the required ultralight stall speed is 35kts.^{[citation needed]}

MCR '4S'

A Dyn'Aero '4s' during construction

The MCR '4S' is a 4 seater version from the MCR family, and being too heavy for the ultralight class is usually registered in the 'experimental' category. The MCR4s is powered by either the Rotax 912S or the turbo charged Rotax 914 and has an empty weight of around 350 kg combined with a maximum take off weight of 750 kg.^{[citation needed]}

MCR 'Pickup'

The MCR Pickup has the same fuselage as the '4S', but with only two seats in order to fit into the New Zealand and Australian, and some other country's, microlight class. This gives considerable empty interior volume, hence the name 'pickup'.^{[citation needed]}

Accidents and incidents

• On 18 October 2005, MCR-01 OB-1701 suffered a nose landing gear collapse while taxiing before takeoff for a training flight at Las Dunas airport (SPLH), Ica, Peru. Both pilots were uninjured. However, the aircraft suffered significant damage to the nose, engine and propeller. After investigation by the Directorate General of Civil Aviation of Peru it was found that the nose gear strut broke at a point where it was welded to the wheel bracket, and this was probably caused by a combination of fatigue, corrosion and a design fault.^[2] As a result, both MCR-01 aircraft registered in Peru were grounded by the Directorate General of Civil Aviation of Peru and declared unairworthy, until a satisfactory factory redesign of the nose landing gear was made available by Dyn'Aero. Shortly after the accident, Dyn'Aero published a Service Bulletin to encourage MCR owners the inspection of the weld joint between the front leg tube and the wheel bracket.^[3] Finally, a nose gear reinforcement part was made available for mandatory installation by April 2008.^[4]
• On 30 December 2007, MCR-01 G-BZXG crashed on Burgham Park Golf Course, Felton, Northumberland, United Kingdom following the detachment of the empennage in flight. The pilot and his passenger were both seriously injured. An investigation by the Air Accidents Investigation Branch revealed that some designs of attachment lugs for the all-flying tailplane had a design fault. As a result of the accident, on 6 February 2008 all MCR-01 aircraft registered in the United Kingdom were grounded by the Civil Aviation Authority until they had been inspected and new attachment lugs of stainless steel had been fitted if necessary. On 13 February 2009, Dyn'Aéro issued a Service Bulletin requiring inspection of all MCR-01 aircraft, and the replacement of attachment lugs where necessary.^[5] On 22 February 2009, the French Direction Générale de l'Aviation Civile issued an Airworthiness Directive, mandating the Service Bulletin issued by Dyn'Aéro.^[6]

Specifications

Data from ^[7]Brassey's World Aircraft & Systems Directory

General characteristics

• Capacity: 2
• Length: 5.4 m (17 ft 9 in)
• Wingspan: 6.63 m (21 ft 9 in)
• Empty weight: 235 kg (518 lb)
• Gross weight: 450 kg (992 lb)
• Powerplant: 1 × Rotax 912, 60 kW (80 hp)

Performance

• Maximum speed: 300 km/h (186 mph)
• Cruising speed: 250 km/h (155 mph)
• Stall speed: 80 km/h (50 mph)
• Range: 1050 km (652 miles)

References

1. ^ History page
2. ^ "Informe Final CIAA-ACCID-009-2005". Directorate General of Civil Aviation of Peru. September 2007. https://www.mtc.gob.pe/portal/transportes/aereo/ciaa/2005/informe_final_masterofthesky_OB-1701.pdf. Retrieved 15 August 2011. 
3. ^ "Bulletin Service N° BS 05 J 0027". Dyn'Aéro. October 2005. http://www.s313492006.onlinehome.fr/dynaerosa/liens/bs/0028BS05J0027.pdf. Retrieved 15 August 2011. 
4. ^ "Bulletin Service N° BS 08 D 0035". Dyn'Aéro. April 2008. http://www.s313492006.onlinehome.fr/dynaerosa/liens/bs/0033BS08D0035.pdf. Retrieved 15 August 2011. 
5. ^ "Bulletin Service N° BS 08 B 0034". Dyn'Aéro. February 2008. http://www.s313492006.onlinehome.fr/dynaerosa/liens/bs/0032BS08B0034.pdf. Retrieved 15 August 2011. 
6. ^ "AAIB Bulletin: 2/2009 G-BZXG EW/C2007/12/05". Air Accidents Investigation Branch. February 2009. http://www.aaib.gov.uk/cms_resources/Dyn%E2%80%99Aero%20MCR-01%20ULC,%20G-BZXG%2002-09.pdf. Retrieved 15 July 2010. 
7. ^ Taylor 1996, p. 465

• Taylor, Michael J. H. (1996). Brassey's World Aircraft & Systems Directory. London, England: Brassey's. ISBN 1 85733 1981 1. 

External links

• Dyn'Aero company home page
• (English) Dyn'Aero - official website