Robin Aiglon

Development

The Aiglon is an all-metal low-wing monoplane with a fixed tricycle landing gear and powered by a nose-mounted 180 hp (134 kW) Lycoming O-360-A3AD or a Lycoming O-360-A3A engine. It was based on the early HR100 but had a lighter airframe and new fin and rudder. The prototype first flew on 25 March 1977 and the production version with detail improvements was certified on 19 September 1978.

Variants

R.1180 Aiglon

Prototype, one built

R.1180T Aiglon

Production variant with longer cabin side windows, 30 built.

R.1180TD Aiglon II

A R.1180T with a new instrument panel, improved cabin furnishing and an external baggage locker, 36 built.

Specifications (R.1180)

Data from

General characteristics

Crew: 1

Capacity: 3

Length: 7.26 m (23 ft 9¾ in)

Wingspan: 9.08 m (29 ft 9½ in)

Height: 2.38 m (7 ft 9¾ in)

Wing area: 15.10 m² (162.54 ft²)

Empty weight: 650 kg (1433 lb)

Gross weight: 1150 kg (2535 lb)

Powerplant: 1 × Lycoming O-360-A3AD flat-four piston engine, 134 kW (180 hp)

Performance

Maximum speed: 251 km/h (156 mph)

Range: 1625 km (1009 miles)

Service ceiling: 5030 m (16,505 ft)