TYPE: Two-seat lightplane.
PROGRAMME: Certified in France in mid-1978 and in USA (FAR Pt 23 Aerobatic and Utility category) 15 November 1982. Some aircraft assembled in Canada (1983-85). Production then ceased, but restarted in France January 1994.
CURRENT VERSIONS: R 2160 D: Baseline version, as described below.
R 2160i: Certified 8 July 1998, with 119 kW (160 hp) Textron Lycoming AEIO-320-D2B fuel-injected flat-four. Four delivered by end of 2002, including two to CATC training college in Thailand.
Alpha 160A: Aerobatic version.
Alpha 160Ai: Aerobatic version of R 2160i.
Alpha 160T: Basic trainer, introduced 2002.
CUSTOMERS: Total of over 133 sold in Europe, Australia, New Zealand, Canada and USA by late 2002, including 97 in first series.
DESIGN FEATURES: Generally as Robin R 2120, but with extended rudder chord, underfin and other detail changes. Wing section NACA 23015; dihedral 6o 20'; incidence 3o at root.
FLYING CONTROLS: Manual. Conventional fully balanced slotted ailerons and horn-balanced rudder without tabs. All-moving tailplane with anti-balance tabs each side. Slotted flaps.
STRUCTURE: Aluminium alloy wing spars and skinning; semi-monocoque fuselage.
LANDING GEAR: Non-retractable tricycle type with fairing, oleo-pneumatic shock-absorber and tyre (380x150) on each leg. Cleveland disc brakes on mainwheels. Nosewheel steering through rudder bar.
POWER PLANT: One 119 kW (160 hp) Textron Lycoming o-320-D2A flat-four engine, driving a Sensenich 74DM6S5-2-64 two-blade, fixed-pitch aluminium propeller. Provisional design studies completed for installation of 134 to 149 kW (180 to 200 hp) engine. Christen inverted oil system standard. Fuselage fuel tank, capacity 120 litres (31.7 US gallons; 26.4 Imp gallons). If operated in Utility category, optional fuel tank of 160 litres (42.3 US gallons; 35.2 Imp gallons).
ACCOMMODATION: Two seats side by side.
SYSTEMS: 12 V 24 Ah electrical system.
AVIONICS: Flight: VOR, ADF, ILS, GPS and other items, at customer's choice.
Instrumentation: Blind-flying panel optional.
