English name: Lion Cub
TYPE: Two-seat lightplane.
PROGRAMME: Design (as Moniot APM-20) started 1992 by Les Industries de Composites d'Auvergne Reunites (ICAR); prototype (F-WWMP) exhibited at Paris Air Show 1995 before first flight on 21 November 1995; third (second flying) aircraft (F-WWXX) exhibited statically at Paris Air Show, June 1997, fitted with JPX flat-four engine, which is not offered on production aircraft. No.4 (also F-WWXX) exhibited at Paris in June 1999 and No.5 (F-GRRE) in 2001. Certified to JAR-VLA 17 May 1999 and to JAR-21 in 2000. First all-carbon fibre, single-engine aircraft to gain JAR-VLA certification. APM-21 will follow at unspecified date. Tailwheel and diesel-engined variants were under consideration in early 2003.
CURRENT VERSIONS: APM-20: Primary trainer As described.
APM-21 Lion: Aerial work version powered by 73.5 kW (98.6 hp) Rotax 912 ULS engine driving a two-blade, constant-speed Hoffmann propeller. Prototype (F-WWMP, modified from prototype Lionceau) demonstrated at Paris Air Show in June 1999.
Four-seat: Under development; no major structural changes.
APM-22 Liondo: Prototype APM-21 equipped with large winglets and exhibited at Paris, 15-22 June 2003, as representative of this UAV proposal, with 24-hour endurance and 556 kg (1,225 lb) MTOW.
CUSTOMERS: Three flying prototypes; one static test airframe (No. 02). Ninth production aircraft (No. 13) exhibited at Paris in June 2003. Break-even point estimated at 200 aircraft.
COSTS: Development cost around FFr10 million. Unit cost FFr620,000, minimally equipped or FFr700,000 with standard equipment (2001). Operating cost FFr350 per hour (1998).
DESIGN FEATURES: Low wing, NACA 63618 aerofoil, thickness/chord ratio 18 per cent, dihedral 3°, incidence 2°, twist 1°.
FLYING CONTROLS: Conventional and manual. Spring elevator tab for pitch trim. Electrically operated slotted flaps to about two-thirds span.
STRUCTURE: Carbon fibre/epoxy.
LANDING GEAR: Fixed tricycle type with spats; oleo-sprung steerable nose leg, composites main legs. Mainwheels and nosewheel diameter 330 mm; maximum pressure 2.35 bar (34 lb/sq in).
POWER PLANT: One 59.6 kW (79.9 hp) Rotax 912A four-cylinder four-stroke driving an Evra AL1 two-blade, fixed-pitch wooden propeller. Fuel capacity 68 litres (18.0 US gallons; 15.0 Imp gallons), of which 65 litres (17.2 US gallons; 14.3 Imp gallons) are usable. Refuelling point on port side of fuselage. Oil capacity 4 litres (1.1 US gallons; 0.9 Imp gallon).
ACCOMMODATION: Two, side by side under rearward-sliding tinted canopy. Dual controls standard. Baggage compartment at rear of seats. Fixed step forward of wing leading-edge on each side.
AVIONICS: Instrumentation: VFR panel standard.
