Agusta A.101

Summary

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

A.101
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

Design and developmentEdit

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 stored for preservation at the Museo Agusta at Cascina Costa.

VariantsEdit

A.101D
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.
A.101G
The sole prototype powered by three 1,400 hp (1,044 kW) Rolls-Royce Gnome H.1400 turboshaft engines
A.101H
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: 2
  • Capacity: up to 36 pax / 18 stretchers with 5 attendants / 5,000 kg (11,023 lb) payload
  • Length: 20.19 m (66 ft 3 in) including tail-rotor
  • Width: 4.64 m (15 ft 3 in) rotor blades folded
  • Height: 6.56 m (21 ft 6 in) to top of rotor head
  • Empty weight: 6,850 kg (15,102 lb)
  • Gross weight: 12,400 kg (27,337 lb)
  • Max takeoff weight: 12,900 kg (28,440 lb)
  • Fuel capacity: 2,000 l (530 US gal; 440 imp gal) in fuselage side fairings
  • Powerplant: 3 × Rolls-Royce H.1400 Gnome turboshaft engines, 1,000 kW (1,400 shp) each for take-off
1,250 shp (932.1 kW) maximum continuous
  • Main rotor diameter: 20.4 m (66 ft 11 in)

Performance

  • Maximum speed: 217 km/h (135 mph, 117 kn) at MTOW
241 km/h (150 mph; 130 kn) at 23,150 kg (51,037 lb) AUW
  • Cruise speed: 201 km/h (125 mph, 109 kn) at MTOW
217 km/h (135 mph; 117 kn) at 23,150 kg (51,037 lb) AUW
  • Range: 378 km (235 mi, 204 nmi) at MTOW
402 km (250 mi; 217 nmi) at 23,150 kg (51,037 lb) AUW
  • Service ceiling: 2,950 m (9,680 ft) at MTOW
4,600 m (15,092 ft) at 23,150 kg (51,037 lb) AUW
  • Hover ceiling IGE: 1,400 m (4,593 ft) at MTOW
3,450 m (11,319 ft) at 23,150 kg (51,037 lb) AUW
  • Hover ceiling OGE: 600 m (1,969 ft) at MTOW
2,800 m (9,186 ft) at 23,150 kg (51,037 lb) AUW
  • Rate of climb: 9.7 m/s (1,910 ft/min) at MTOW
14.53 m/s (48 ft/s) at 23,150 kg (51,037 lb) AUW

Avionics
VFR and IFR instrumentation with provision for autostab and autopilot

OperatorsEdit

  Italy

See alsoEdit

Aircraft of comparable role, configuration, and era

ReferencesEdit

  1. ^ Taylor, John W.R., ed. (1969). Jane's All the World's Aircraft 1969-70 (60th ed.). London: Sampson Low, Marston & Company. pp. 123–124.
  2. ^ Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.

Further readingEdit

  • 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.