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Agusta A.101G / AZ-101G



Filippo Zappata's Agusta A.101D project was introduced at the Milan Trade Fair in April 1958, in the form of a model.
The prototype was first flown on 19 October 1964 by test pilot Ottorino Lancia.

The single prototype underwent visible external modifications during development under the direction of engineers Bellavita and Lovera and was fitted with a twin nose wheel assembly and longer fairings on each side of the fuselage, which was also extended by grafting in a new section. The helicopter performed service trials involving rapid embarkation and disembarkation through the two lateral sliding doors and tail ramp. It could carry two pilots and 35 equipped troops, or a 5000kg load. The development period involved over 400 flying hours in addition to those on the rotor test rig.

The first prototype was fitted with three Rolls-Royce Bristol-Gnome H.1200 turbine engines of 1250shp, and later Gnome H-1400s of 1400shp. The airframe, with a gross weight of 12800kg and a length of sixty-six feet, had a rear ramp and twin sliding troop doors.

The A.101 was examined by interested foreign parties visiting Cascina Costa and was displayed at the Turin Air Show in June 1966.

By autumn 1966 the A.101 was ready for large-scale production, but no decision was made by the authorities. In 1968 the helicopter appeared at the Turin Air Show in camouflage finish and was tested at an all-up weight of 13500kg. At the end of autumn 1968 the A.101G was transferred to Praticadi Mare military airport outside Rome for a series of trials which were completed in summer 1971. The aircraft made a few more flights, but was considered out-of-date. The A.101G was originally designated AZ.101G, the second initial denoting the responsibility of Ing. Filippo Zappata.

Agusta had reworked the A.101H by redesigning the fuselage and some basic dynamic components. The fuselage was extended by 3 metre and more powerful General Electric T58 turbine engines were installed. This programme was cancelled in 1971 in favour of production under license of foreign aircraft such as Sikorsky and Boeing-Vertol helicopters.

Engine: 3 x Bristol-Siddley "Gnome H. 1400" turboshaft, 1030kW
Main rotor diameter: 19.8m        
Length: 20.2m
Height: 6.6m                
Take-off weight: 11500kg
Empty weight: 6400kg            
Max speed: 225km/h
Cruising speed: 203km/h            
Rate of climb: 12.3m/s
Service ceiling: 3950m            
Range max fuel: 383km
Crew: 3                    
Passengers: 35


Engines: 3 x Bristol-Siddeley Gnome, 1250 shp
Main rotors: 5 blades
Tail rotor: 6 blades
Max gross weight: 24,900 lb
Empty weight: 12,566 lb
Top speed: 160 mph
Cruise speed: 140 mph
Range: 1270 mi




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