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R2160


Production of the first R2160 aircraft began in Canada in 1981, but Canadian pro-duction ceased in 1984 when the line was re-turned to France. It was not until the early 1990s that the R2160 got a facelift for the growth of the trainer market foreseen at that time. With dual control joysticks and produced at the Dijon works of Avions Pierre Robin, the R 2000 series of all-metal lightplanes was introduced by the company in 1977 to replace the HR 200.

In general appearance, the R 2000 and HR 200 are similar, the most obvious external difference being the former’s enlarged tail unit, with a long ventral fin, designed to improve the lateral control and handling. The wing has been extensively modified, with an NACA 23015 profile instead of the earlier NACA 64A5 15, and a small increase in chord and area. Many changes have been made in the construction methods, with new tooling throughout for the metal aircraft in the Robin line, which included the R 1000 (formerly HR 100) as well as the R 2000.

The prototype of the R 2000 series flew on 15 January 1976 and a pre-production example followed on 15 July 1976, the latter having a 160 hp engine and therefore being, in effect, a prototype of the variant now in production as the R 2160. An aerobatic version of the latter is also available (certificated 1978), in which the AEIO-320 engine is used, with an inverted flight fuel system, and the same basic aircraft is offered with a 108 hp engine, in which guise it is marketed as the R 2100.

The Alpha 160 is renamed 2160. For unusual-attitude flight, the R2160’s all-aluminium alloy, semi-monocoque structure is built to the strength of FAR 23 and is certified to +6/-3g. The flap system is electric and gives up to 35deg.
The R2120 U (the certified model name) are refered to as the Alpha 120T (Trainer). The Alpha 120T is a non-aerobatic derivative of the Alpha 160A. Powered by a Lycoming O-235, and fitted with dual control sticks, throttles and differential brakes.

Certification of the R2120U, R2160 (265 and up), and R2160I is under NZ TC A-15.

2100
Engine: One 108 hp Lycoming O-235H
Fuel capacity 264 Imp gal (120 1)
Max speed at sea level, 138 mph (222 km/h)
Cruising speed at 75% power, optimum altitude, 124 mph (200 km/h)
Service ceiling, 12,500 ft (3 810 m)
Initial rate of climb, 710 ft/min (3,60 m/sec)
Range, 520 mls (838 km)
Empty weight: 1,167 lb (530 kg)
Max take-off weight: 1,718 lb (780 kg)
Wing Span, 27 ft 4 in (8,33 m)
Length, 23 ft 3½  in (7,10 m)
Height, 6 ft 1l½ in (2,13 m)
Wing area, 140 sq ft (13,00 sq.m)
Accommodation: 2

2112 Alpha
Engine: Lycoming O-235, 112 hp

2120U (Alpha 120T)

Engine: One 108 hp Lycoming O-235
Prop: 2 blade Sensenich fixed
Cruise: 105 kt
Fuel cap: 31.7 USG
Range: 550 nm
Loading: +6 / -3G

2160 (Alpha 160A)
Engine: One 160 hp Lycoming O-320-D2A or one 160 hp Lycoming AEIO-320
Prop: Sensenich 74-DM-685-2-64
Fuel capacity 264 Imp gal (120 1)
Vne: 178 kts
Vno: 127 kts
Max X-wind: 18 kts
Max speed at sea level, 160 mph (257 km/h)
Cruising speed at 75% power, 7500 ft, 130 kts (242 km/h)
Service ceiling, 15,000 ft (4572 m)
Initial rate of climb, 1,020 ft/min (5,20 m/sec)@ 78 kts
Best angle of climb: 70 kts
Range, 418 mls (673 km)
Stall: 51-63 kts
Empty weight: 1,211 lb (550 kg)
Max take-off weight: Utility 1984 lbs, aerobatic 1,764 lb (800 kg)
Max baggage: 77 lbs
Span, 27 ft 4 in (8,33 m)
Length, 23 ft 3½ in (7,10 m)
Height, 6 ft 1l½ in (2,13 m)
Wheel track: 9 ft 6in
Wing area, 140 sq ft (13,00 sq.m)
Accommodation: 2
Aerobatic
Load factor: +6/-3

2160 Sport
Engines: 1 x 160 hp Lycoming O-320-D2A
Prop: two-blade Sensenich fixed-pitch
Seats: 2
Useful load: 550 lb
Max range: 410 sm
Wingspan: 8.33 m
Length: 7.10 m
Height: 2.13 m
Under-carriage: Fixed oleo-pneu-matic, steerable nose wheel
Stall: clean: 63 kts, with flap: 51 kts
Max Cruise: 150 mph
Cruise: 2,450 rpm @ 8,000 ft: 130 kts
Range: 363 nm with reserves
Fuel cap: standard tanks: 120 lt, optional160 lts
Maximum wt: 900 kg
Empty Wt: 580 kg

 

 


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