Agusta A.101

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Agusta A.101 helicopter (1964).jpg
A.101 helicopter in 1964. Third from right is Count Domenico Agusta and fourth is Filippo Zappata
Role Transport helicopter
Manufacturer Agusta
Designer Filippo Zappata
First flight 19 October 1964
Number built 1

The Agusta A.101 (originally designated AZ.101) was a large prototype transport helicopter developed in Italy during the course of the 1960s. Despite prospective orders from the Italian armed forces, no buyers emerged and the project was abandoned in 1971.

Design and development[edit]

The A.101 was of conventional, single-rotor configuration with tricycle undercarriage and powered by triple turboshaft engines. The fuselage was provided with a rear loading ramp and two large sliding troop doors.

The final stage in the A.101's development was to stretch the fuselage by 3 m (10 ft) and upgrade the engines to the more powerful General Electric T58. This resulted in a marked improvement in performance, but in the end, the Italian government opted for variants of the SH-3 Sea King, licence-built by Agusta instead of their own design.

The single prototype is preserved at the Museo Agusta at Cascina Costa.


The original concept by Filippo Zappata exhibited in model form at the Milan Trade Fair in April 1958, also designated AZ.101, acknowledging Zappata's role in the design process. Power was to have been supplied by three 750 hp (559 kW) Turbomeca Turmo engines.
The sole prototype powered by three 1,400 hp (1,044 kW) Rolls-Royce Gnome H.1400 turboshaft engines
A projected up-rated version, stretched by 3 m (10 ft), with tricycle undercarriage and powered by three General Electric T58 turboshaft engines.



Specifications (A.101G configuration)[edit]

Data from Jane's All The World's Aircraft 1969–70[1]

General characteristics

  • Crew: two pilots
  • Capacity: 36 passengers or 5,000 kg (11,025 lb) cargo or 18 stretchers and 5 attendants
  • Length: 20.19 m (66 ft 3 in)
  • Main rotor diameter: 20.40 m (66 ft 11 in)
  • Height: 6.56 m (12 ft 6¼ in)
  • Main rotor area: 327 m2 (3,451 ft2)
  • Empty weight: 6,850 kg (15,100 lb)
  • Gross weight: 12,900 kg (28,440 lb)
  • Powerplant: 3 × Rolls-Royce Gnome H.1400 turboshafts, 1,044 kW (1,400 hp) each


  • Maximum speed: 241 km/h (150 mph)
  • Range: 402 km (250 miles)
  • Service ceiling: 4,600 m (15,090 ft)
  • Rate of climb: 14.5 m/s (2,860 ft/min)

See also[edit]

Aircraft of comparable role, configuration and era


  1. ^ Taylor 1969, pp. 123–124.
  • Taylor, John W. R. (1969). Jane's All The World's Aircraft 1969–70. London: Sampson Low, Marston & Company. ISBN 0-354-00051-9. 
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 40. 
  • Simpson, R. W. (1998). Airlife's Helicopters and Rotorcraft. Ramsbury: Airlife Publishing. pp. 31, 35–36.