Puneet Varma (Editor)

Robin HR100

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Top speed
  
325 km/h

Length
  
7.59 m

Wingspan
  
9.08 m

Manufacturer
  
Robin Aircraft

Robin HR100 Robin HR100 210 Safari II Photos AirplanePicturesnet

Cedric flow on robin hr100 210


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

Contents

Robin HR100 Robin HR100 Specifications A photo

Cedric flew on robin hr100 210


Development

Robin HR100 Robin HR100 Specifications Technical Data Description

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.

Robin HR100 Robin HR100 210 Safari II Photos AirplanePicturesnet

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.

Robin HR100 HR100 Specifications A photo

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.

Variants

Robin HR100 httpsuploadwikimediaorgwikipediacommonsthu
HR.100 Royal
1969 Prototype with a 180hp (134kW) Lycoming O-360 engine, one built.
HR.100/180
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.
HR.100/235TR
Experimental HR.100 with an enlarged tail and retractable landing gear and a 235hp Lycoming O-540-B engine, one built.
HR.100/250TR
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

 France
  • French Air Force
  • French Navy

    • Specifications (HR.100/285)

    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)

    • Performance

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

    • References

    Robin HR100 Wikipedia
    (Text) CC BY-SA


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