• Source: Agusta A.101

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.




Design and development


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.




Variants


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)



Data from Jane's All The World's Aircraft 1969–70General characteristics
Crew: 2
Capacity: up to 36 pax / 18 stretchers with 5 attendants / 5,000 kg (11,000 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 × de Havilland H.1400 Gnome turboshaft engines, 1,000 kW (1,400 shp) each for take-off
1,250 shp (930 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
Cruise speed: 201 km/h (125 mph, 109 kn) at MTOW
Range: 378 km (235 mi, 204 nmi) at MTOW
Service ceiling: 2,950 m (9,680 ft) at MTOW
Hover ceiling IGE: 1,400 m (4,600 ft) at MTOW
Hover ceiling OGE: 600 m (1,970 ft) at MTOW
Rate of climb: 9.7 m/s (1,910 ft/min) at MTOW
Avionics
VFR and IFR instrumentation with provision for autostab and autopilot




See also


AgustaWestland AW101

Aircraft of comparable role, configuration, and era

SNCASE SE.3200 Frelon




References






Further reading



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.

Kata Kunci Pencarian:

• Agusta
• AgustaWestland AW101
• Daftar pesawat terbang VTOL
• Sinema Islandia
• Daftar rumah sakit di Indonesia
• Daftar film Indonesia tahun 2023
• Daftar tokoh Minangkabau
• Proyek Strategis Nasional
• Malaysia Airlines Penerbangan 370
• Daftar film Indonesia tahun 2018
• Agusta A.101
• Agusta
• AgustaWestland AW101
• A101
• AgustaWestland AW109
• MV Agusta F4 series
• List of aircraft (0–Ah)
• List of aircraft used by Italian Air Force
• US-101
• Bell 204/205