LAMBERT MISSION M212

TYPE: Four-seat kitbuilt.

PROGRAMME: Design started November 1992; fuselage mockupJuly 1993; construction of proof-of-concept prototype began at Geluveld, Belgium, January 1996; structural test programme completed 23 December 1998; prototype, M212-100 registered G-XFLY in February 2000, was structurally complete by March 2001; all composites work and landing gear completed November 2001; power plant and fuel system work began March 2002 in UK. Public debut in UK at PFA Rally, Cranfield, 21-23 June 2002. First flight planned for December 2002, but had not taken place by May 2003.

CURRENT VERSIONS: Family of aircraft planned around core four-seat version.
M212-100: Prototype. One only to be built.
M212-200: Basic four-seat version, will be available factory-build or as kit; certification to JAR/FAR Pt 23 planned.
M212-300: Proposed two-seat aerobatic trainer; since discontinued.
M212-400: Four-seat tourer with increased fuel and baggage capacity, optional retractable landing gear, maximum take-off weight 1,100 kg (2,425 lb) and range of over 1,000 n miles (1,852 km; 1,151 miles).

CUSTOMERS: Options on 26 kits held in 2001; customers in the Benelux countries, France amd, mostly, the UK.

COSTS: Kit, including engine, propeller and VFR avionics, €110,000 (2003).

DESIGN FEATURES: Designed using CAD and wind tunnel research facilities; will meet FAR Pt 23 and JAR 23 certification criteria. Low-wing monoplane; wings, which have laminar flow, moderate taper and upturned tips. Wing dihedral 5o; incidence at root 2o; twist 2o. Quoted kit build time 800 hours.

FLYING CONTROLS: Conventional and manual. Cable and pushrod actuation. Electrically actuated single-slotted flaps.

STRUCTURE: All-composites, with extensive (95 per cent by weight) use of prepregs; glass and carbon in epoxy resin used for spars and longerons. Fuselage of monocoque construction; wing has dual main spars plus auxiliary spar for further strengthening.

LANDING GEAR: Fixed tricycle type. Mainwheels size 6.00-6, nosewheel 5.00-5 or 6.00-6; Cleveland brakes. Steerable nosewheel, maximum steering angle ±50. Potential for development of retractable version (tailwheel option withdrawn).

POWER PLANT: One 112 kW (150 hp) Zoche ZO-01A radial four-cylinder, two-stroke diesel engine with multifuel capability, driving a three-blade constant-speed propeller. However, prototype fitted with second-hand 112 kW (150 hp) Textron Lycoming O-320-E2D flat-four; MT-Propeller MTV-18-C/175-17d three-blade, constant-speed (electric) propeller; and Gomolzig twin-muffler exhaust. Fuel capacity 120 litres (31.7 US gallons; 26.4 Imp gallons) in single fuselage tank in M212-100 prototype; production examples will have two wing tanks and total capacity of 280 litres (74.0 US gallons; 61.6 Imp gallons). In developed form as four-seat tourer, suitable for engines in 172 to 194 kW (230 to 260 hp) power range.

ACCOMMODATION: Four persons in 2+2 configuration, under one-piece, forward-hinged canopy. Seats and rudder pedals adjustable; dual controls standard.

 

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