From Wikipedia, the free encyclopedia
French light aircraft
The
Dyn'Aero MCR01
is a two-seat, low-wing, all-composite
carbon fibre
light aircraft
that was originally manufactured by
Dyn'Aero
and is now available in kit form and ready-to-fly through
SE Aviation
.
[1]
Development
[
edit
]
The MCR01 is a variant of the
Colomban MC-100
Ban-bi originally designed by
Michel Colomban
.
[2]
Variants
[
edit
]
A Dyn'Aero MCR01 'ULC'
A
Rotax 912S
installed in a Dyn'Aero MCR01 'CLUB'
- MCR01 'VLA' (Sportster)
- The MCR01 VLA (Sportster) is the
JAR-VLA
(Very Light Aircraft) version of the MCR, with combined
flaperons
, for the amateur-built category in most countries and flown with a
Private Pilot Licence
. The maximum speed is 318 km/h (198 mph or 172 kn) when powered by the 100 hp (75 kW)
Rotax 912ULS
while the stall speed in landing configuration is 87 km/h (54 mph or 47 kn). The wing of this aircraft has a
chord
as short as 0.80 m (31 in) and an area of 5.20 m
2
. While the early version of the kit was intended to have wings made from bonded aluminium sheet like the
Colomban MC-100
, this skin has been replaced with carbon fibre as can be seen on photographs shown by Dyn'Aero Australia and New Zealand: "Note the advanced state of the wings behind the fuselage... The black colour is the natural colour of the carbon fibre before priming".
[3]
Nowadays, everything in the plane is made out of carbon fiber. Even rudder pedals are carbon fiber.
[4]
The design features a
T-tail
.
[5]
The wings of the aircraft are easily removed from the fuselage so that the whole aircraft can be towed and stored in a trailer.
[
citation needed
]
- MCR01 Club
- The MCR01 Club is a version with a slightly bigger wing than the VLA, and less responsive controls for club and school
flight training
use.
[6]
- MCR01 'ULC'
- The MCR01 ULC is designed to comply with the
Federation Aeronautique Internationale
microlight rules. It has a 8.64 m (28.3 ft) span wing with an area of 8.13 m
2
(87.5 sq ft) and a stall speed of 63 km/h (39 mph). Cruise speed is 271 km/h (168 mph) when equipped with a 80 hp (60 kW)
Rotax 912UL
engine.
[5]
- MCR '4S'
- 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
homebuilt aircraft
category. The MCR4s is powered by either the 100 hp (75 kW)
Rotax 912ULS
or the turbocharged 115 hp (86 kW)
Rotax 914
and has a standard empty weight of 350 kg (772 lb) and a maximum takeoff weight of 750 kg (1,653 lb).
[5]
Accidents and incidents
[
edit
]
- 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.
[7]
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 to inspect the weld joint between the front leg tube and the wheel bracket.
[8]
Finally, a nose gear reinforcement part was made available for mandatory installation by April 2008.
[9]
- 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'Aero issued a Service Bulletin requiring inspection of all MCR-01 aircraft, and the replacement of attachment lugs where necessary.
[10]
On 22 February 2009, the
French
Direction Generale de l'Aviation Civile
issued an
Airworthiness Directive
, mandating the Service Bulletin issued by Dyn'Aero.
[11]
Specifications
[
edit
]
Data from
[12]
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:
490 kg (992 lb)
- Powerplant:
1 ×
Rotax 912
, 60 kW (80 hp)
Performance
- Maximum speed:
318 km/h (198 mph, 172 kn)
- Cruise speed:
300 km/h (186 mph, 162 kn)
[13]
- Stall speed:
80 km/h (50 mph, 43 kn)
- Range:
1,050 km (652 mi, 567 nmi)
- Rate of climb:
7.00 m/s (1,378 ft/min)
References
[
edit
]
- ^
"SE Aviation"
.
- ^
MCR01 Information Pack
, page 2, Lyndhurst Touchdown Services Limited, UK, 24 April 1998.
- ^
"Dyn'Aero Australia and NZ"
. Archived from
the original
on 8 February 2013
. Retrieved
3 March
2013
.
- ^
Video presentation by DynAero - fast forward 5 min into the video
- ^
a
b
c
Bayerl, Robby; Martin Berkemeier; et al.:
World Directory of Leisure Aviation 2011-12
, page 42 and 99-100. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
- ^
Tacke, Willi; Marino Boric; et al:
World Directory of Light Aviation 2015-16
, page 97. Flying Pages Europe SARL, 2015.
ISSN
1368-485X
- ^
"Informe Final CIAA-ACCID-009-2005"
(PDF)
. Directorate General of Civil Aviation of Peru. September 2007. Archived from
the original
(PDF)
on 30 September 2011
. Retrieved
15 August
2011
.
- ^
"Bulletin Service N° BS 05 J 0027"
(PDF)
. Dyn'Aero. October 2005
. Retrieved
15 August
2011
.
[
permanent dead link
]
- ^
"Bulletin Service N° BS 08 D 0035"
(PDF)
. Dyn'Aero. April 2008
. Retrieved
15 August
2011
.
[
permanent dead link
]
- ^
"Bulletin Service N° BS 08 B 0034"
(PDF)
. Dyn'Aero. February 2008
. Retrieved
15 August
2011
.
[
permanent dead link
]
- ^
"AAIB Bulletin: 2/2009 G-BZXG EW/C2007/12/05"
(PDF)
. Air Accidents Investigation Branch. February 2009
. Retrieved
15 July
2010
.
- ^
Taylor 1996, p. 465
- ^
"DynAero"
. Dyn'Aero.
External links
[
edit
]