Robin HR100

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Robin HR.100
D-EKRF Robin HR.100 250TR Tiara (EHLE 1993-05-22).jpg
Robin HR.100/250TR Tiara aircraft D-EKRF, at Lelystad Airport (EHLE), 22 May 1993
Role Four-seat light monoplane
National origin France
Manufacturer Avions Pierre Robin
First flight 1969
Produced 1969-1976
Number built 178
Developed from Robin DR.200

The Robin HR100 is a French four-seat light monoplane built by Avions Pierre Robin as metal-winged version of the Robin DR253 Regent.


The prototype of the Robin HR100 was the prototype DR253 Regent which was rebuilt with metal wings and powered by a 180 hp (134 kW) Lycoming O-360 engine. It first flew on 3 April 1969 as the Robin HR100/180. The HR100 is a low-wing cantilever monoplane with a conventional cantilever tail unit and a fixed tricycle landing gear. A number of different variants were produced in the 1970s. From 1972 a high-powered improved version was produced as the HR100/285 with a 285 hp (213 kW) Continental Tiara 6-285B engine and retractable landing gear and airframe modifications.

French Air Force HR.100/250 communications aircraft at Nancy Essey airfield in 1977

The French Air Force ordered a number of HR.100/250 aircraft in the mid 1970s and these were used for communications and other duties.

A two-seat trainer version was developed as the HR200, and a modified version with a lighter airframe and new fin and rudder was developed as the R1180 Aiglon in 1977.


HR.100 Royal
1969 Prototype with a 180hp (134kW) Lycoming O-360 engine, one built.
1976 Prototype with a 180hp (134kW) Lycoming O-360 engine, one built.
HR.100/200B Royal
Initial production version with a 200hp (149kW) Lycoming IO-360 engine.
HR.100/210 Safari
Production version with a 210hp (157kW) engine, 113 built of both 200B Royal and 210 Safari variants.
Experimental HR.100 with an enlarged tail and retractable landing gear and a 235hp Lycoming O-540-B engine, one built.
HR.100/235 with a 250hp (186kW) Lycoming IO-540-C4B5 engine, 24 built.
HR.100/285TR Tiara
HR.200/235 with a 285hp (213kW) Continental Tiara 6-285 engine, 37 built
HR.100/320 4+2
Experimental version with two extra children's seats, one built


Military operators[edit]


Specifications (HR.100/285)[edit]

Data from The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985), 1985, Orbis Publishing, Page 2799

General characteristics

  • Capacity: 4
  • Length: 7.59 m (24 ft 10¾ in)
  • Wingspan: 9.08 m (29 ft 9½ in)
  • Height: 2.71 m (8 ft 10¾ in)
  • Wing area: 15.20 m2 (163.62 ft2)
  • Empty weight: 840 kg (1852 lb)
  • Gross weight: 1400 kg (3086 lb)
  • Powerplant: 1 × Teledyne Continental Tiara 6-285 flat-six piston engine, 213 kW (285 hp)


  • Maximum speed: 325 km/h (202 mph)
  • Range: 2130 km (1323 miles)
  • Service ceiling: 5700 m (18,700 ft)

See also[edit]

Related development


  • The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985), 1985, Orbis Publishing, Page 2799
  • R.W.Simpson, Airlife's General Aviation, Airlife Publishing, England, 1991, ISBN 1-85310-194-X