- Dyn'Aéro MCR4S
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MCR4S Role 2/4 seat kitbuilt ultralight National origin France Manufacturer Dyn'Aéro First flight 14 June 2000 Developed from Dyn'Aéro MCR01 Variants Dyn'Aéro Twin-R The Dyn'Aéro MCR4S, sometimes known as the Colomban-Robin MCR4S is a four seat development of the French two seat, single engine Dyn'Aero MCR01. It first flew in early 2000 and is sold as a kit for homebuilding in several versions.
Contents
Design and development
The MCR4S is a four seat development of the Dyn'Aéro MCR01 and retains many similarities. Both types are low wing, single engine monoplanes with T-tails. The major changes are an increase in fuselage length to accommodate an extra row of seats with generous windows and the replacement of the flaperons seen on the long span variants of the MCR01, which have wings of about the same span as those of the MCR4S, with slotted flaps.[1]
The wing and all control surfaces of the MCR4S have carbon fibre spars and ribs, to which preformed aluminium skins are glued. The wings have constant chord and carry 3° of dihedral. The ailerons are short, leaving the rest of the trailing edge of each wing divided between two double slotted, three position flaps. Winglets were introduced in 2001 and modified to have straight (in plan) trailing edges from 2002. The MCR4S has a T-tail with an all-moving tailplane. The fin is an integral part of the carbon fibre monocoque fuselage shell which also features a small ventral fin.[1]
The cabin seats up to four, depending on the variant, in two side-by-side rows. Entry is via the large, forward hinged, two piece canopy. Two large windows light the rear seats, the port side one doubling as an emergency exit. A variety of Rotax flat four engines may be fitted, driving a two or three blade propeller, which may have fixed or variable pitch. The MCRS4 has a tricycle undercarriage. The main wheels are mounted on short, vertical legs beneath the wings, as on the Club and ULC variants of the MCR01, with a track of 2.33 m (7 ft 8 in). All undercarriage wheels and legs are faired.[1]
The Dyn'Aéro MCR4S flew for the first time on 14 June 2000.[1]
A ground attack development of the MCR.180, the Pulsartix, appeared at the June 2011 Paris Air Show.[2]
Operational history
The first public appearance of the MCR4S was at the International Air Rally held at Cranfield just nine days after the first flight. French certification was gained in June 2001 (DGAC) and the first customer, aircraft designer Pierre Robin, flew his aircraft shortly afterwards. UK certification (LAA), though sought, had not been achieved by 2009.[1]
In mid-2010, 90 MCR4Ss appeared on the civil aircraft registers of European countries excluding Russia.[3]
Variants
Data from Jane's All the World's Aircraft 2011/12[1]
- Current (2010) versions are based on the MCRS4S-2002 specification.
- MCR2S Ibis
- Two seat configuration with large baggage volume. Rotax 912 engine.
- Pickup
- Two seat, lightened to 260 kg (573 lb) empty. Rotax 912 engine.
- Three seat
- Three seat, powered by a 60 kW (80 hp) Rotax 912 UL or JPX 4TX75 engine.
- Four seat
- Four seat, powered by a 74 kW (99 hp) Rotax 912 UL-S engine.
- Four seat Performance
- Four seat, powered by a 85 kW (113 hp) Rotax 914 UL engine.
- CITEC
- Powered by a Wilksch-120 90 kW (120 hp) two stroke, three cylinder diesel engine.[4]
- MCR R180
- Two seat glider tug, powered by a 134 kW (180 hp) Textron Lycoming O-360-A3a. Slightly greater span and shorter than MCR4S, maximum take-off weight 750 kg (1,653 lb). First flown 2007.
- MCR R180 Limousine
- Announced at Aero 2010 as having Dyn'Aéro Twin-R interior.
- Dyn'Aéro Twin-R
- Twin engine version, first flown March 2011.
Specifications (Four seat Performance)
Data from Jane's All the World's Aircraft 2011/12[1]
General characteristics
- Capacity: 4
- Length: 6.72 m (22 ft 1 in)
- Wingspan: 8.66 m (28 ft 5 in)
- Height: 1.95 m (6 ft 5 in)
- Wing area: 8.15 m2 (87.7 sq ft)
- Empty weight: 320 kg (705 lb) unequipped
- Max takeoff weight: 640 kg (1,411 lb) ; may be as high as 750 kg (1,653 lb)
- Fuel capacity: 120 L9
- Powerplant: 1 × Rotax 914 UL flat four piston engine, turbocharged, air and water cooled, driving constant speed propeller and optimised for cruise at 3,048 m (10,000 ft), 84.6 kW (113.5 hp)
Performance
- Maximum speed: 320 km/h (200 mph; 170 kn)
- Cruising speed: 287 km/h (178 mph; 155 kn) economical
- Stall speed: 83 km/h (52 mph; 45 kn) flaps down
- Range: 1,846 km (1,147 mi; 997 nmi) maximum fuel
- G limits: +3.8/-1.5
- Rate of climb: 4.6 m/s (910 ft/min)
References
- ^ a b c d e f g Jackson, Paul (2011). Jane's All the World's Aircraft 2011-12. Redhill, UK: IHS Jane's. pp. 200–1. ISBN 978-0-7106-2955-5.
- ^ "The Paris Air Show, 2011". Air Britain Aviation World: p.140. September 2011.
- ^ Partington, Dave (2010). European registers handbook 2010. Air Britain (Historians) Ltd. ISBN 978-0-85130-425-0.
- ^ "WAM engines". http://wilksch.net/. Retrieved 2011-07-20.
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