General
Single-engine, 4-seat, light aircraft of conventional light alloy construction.
ICAO type designation is ‘R100’.
last update: 5 October 2025
History
Aircraft modified from HR.100, with lighter airframe, new fin and rudder and less powerfull engine. Prototype F-GBAM first flew on 25 March 1977. Aircraft was certified by the DGAC on 19 September 1978. Production ended in 1983.Production standard aircraft had longer cabin side windows and increased fuel capacity compared to prototype.
R.1180TD Aiglon II superseded original R.1180T in production and had a new instrument panel, new cabin furnishings and an external baggage locker door. Apart from the prototype a total of 30 Aiglons and 36 Aiglon IIs were built, although some sources claim more than 70 have been built. French civil aviation schools received a total of 18 R.1180s.
Airframe
Conventional low-wing monoplane of light alloy construction.
wing: Constant chord wing, NACA 23015 section.
landing gear: Fixed tricycle landing gear.
Powerplant
engine: One Lycoming O-360-A3AD horizontally-opposed, air-cooled 4-cylinder engine delivering 180 hp (134 kW). Engine drives a 2-blade fixed pitch metal propeller.
fuel system: Total fuel capacity 258 l (68 USG) in 2 integral wing tanks.
Systems
No information available.
Avionics
Aircraft can be equipped for VFR, Night VFR, and IFR flight.
Accommodation
Four persons seated 2+2 in enclosed cabin, luggage compartment behind seats. Forward half of canopy slides forward for access to cabin. Heating and ventilation standard.
Armament
Not applicable.
Dimensions
External:
· wing span: 9.08 m / 29.79 ft
· overall length: 7.26 m / 23.82 ft
· overall height: 2.38 m / 7.81 ft
· wing area: 15.1 sq m / 163 sq ft
· wing aspect ratio: 5.5
Internal:
· cabin length: 2.00 m / 78.7 in
· cabin width: 1.12 m / 44.1 in
· cabin height: 1.22 m / 48.0 in
Weights & Loads
· max. t-o weight: 1150 kg / 2535 lb
· empty weight: 650 kg / 1433 lb
· wing loading: 76 kg/sq m / 15.6 lb/sq ft
· power loading: 6.4 kg/hp / 14.1 lb/hp
Performance
· max. speed, S/L:
135 kts / 250 km/h
· max. cruise speed, at altitude:
133 KTAS / 246 km/h
· cruise speed (TAS), 65% power, at altitude:
127 kts / 235 km/h
· max. range, 65% power, with reserves:
876 nm / 1622 km
· service ceiling:
16 500 ft / 5029 m
· max. rate of climb:
846 fpm / 4.3 m/s
· stall speed, all up:
58 kts / 107 km/h
· stall speed, flaps down:
50 kts / 93 km/h
· take-off distance over 15 m (50 ft) obstacle:
970 m / 3182 ft
· landing distance over 15 m (50 ft) obstacle:
460 m / 1509 ft