Earlier, in August 1978, P.Z.L. Swidnik concluded an agreement with the Spitfire Helicopter Company of Media, Pennsylvania, US allowing them to market a modified version of the Kania (itself an Mil Mi-2 verion) in Western countries under the name Spitfire Taurus. This differed primarily from the standard Polish version by introducing uprated Allison 250-C28 turboshaft engines, each with a take-off rating of 373kW fed by a large common intake; revised nose contours and sporting a ventral fin. However, the company has since gone out of business, and it is not known if any conversions were completed.

Taurus
Engine: 2 x Isotov 350P, 400 shp
TBO: 3500 hr
Main rotor: 48.3 ft
Seats: 9
Length: 39.2 ft
Height: 12.3 ft
Max ramp weight: 7400 lb
Max takeoff weight: 7400 lb
Standard empty weight: 5166 lb
Max useful load: 2234 lb
Max landing weight: 7400 lb
Max sling load: 1763 lb
Disc loading: 4 lbs/sq.ft
Power loading: 9.3 lbs/hp
Max usable fuel: 1472 lb
Max rate of climb: 900 fpm
Service ceiling: 13,300 ft
Hover in ground effect: 6,900 ft
Hover out of ground effect: 7900 ft
Max speed: 147 kt
Normal cruise @ 3000 ft: 128 kt
Fuel flow @ normal cruise: 435 pph
Endurance @ normal cruise: 2.8 hr

The Spitfire Mark I was a utility helicopter built in the United States in the late 1970s and intended for series production. In essence, the Mark I was an Enstrom F-28 that was modified to use an Allison 250 turboshaft engine and geared transmission in place of the original piston engine and system of vee belts. The resulting powerplant installation was lighter and more compact, which allowed for additional cargo or fuel.

Spitfire Helicopters’ parent company, Fetsko Aviation Sales and Transportation began work on the prototype in January 1976, and on a number of pre-production aircraft in February 1977. Fetsko displayed a mockup of the concept at the National Maintenance and Operations Meeting at Reading, Pennsylvania in June 1976.

The prototype (registered N4890) first flew in December 1978. By May 1979, Spitfire had supplemental approval for the turbine conversion and by July, the company reported that it had sold 42 examples of the Mark I and Mark II and expected to build 60 aircraft during 1980. The engine installation on production models was to be slightly further forward than on the prototype.

The Spitfire II derivative of the Enstrom uses a new four seat front fuselage and the Allison engine with Enstrom rotor and rear fuselage.

Other projects included Spitfire Mark IV with auxiliary propulsion engines at tips of stub wings.

However, Spitfire remained dependent on Enstrom to supply airframes for remanufacture, and Enstrom distanced itself from the project somewhat. Competing plans by Enstrom and Spitfire to market Polish-built Mil Mi-2 helicopters in the United States might have contributed to the friction. In Spitfire’s version of the deal, Polish manufacturer PZL-Świdnik would also contribute to the Spitfire manufacturing efforts. By November 1979, Enstrom refused to supply airframes to Spitfire.

The situation improved somewhat in the 1980s, and Spitfire president Jack Fetsko reported in May 1983 that relations with Enstrom had improved to the point where the two companies could “talk programs”. By that time, costs had increased from $US 165,000 expected in 1979 to $US 285,000 but Spitfire had taken deposits for 50 Mark Is, and had a firm sale for the first production aircraft. Together with companies Sodian and Soprea, Spitfire formed a new venture, Spitfire Helicopters International, to manufacture the Mark I and Mark II in Málaga, Spain.

Nothing came of the joint venture, and Spitfire’s attempts to market F-28 derivatives came to an end. In the 1990s, Enstrom marketed its own turbine-powered version of the F-28 as the Enstrom 480.

Mark 1
Engine: Allison 250-C20B, 420 shp
TBO: 3500 hr
Main rotor: 32 ft
Seats: 3
Length: 29.4 ft
Height: 9.2 ft
Max ramp weight: 2350 lb
Max takeoff weight: 2350 lb
Standard empty weight: 1292 lb
Max useful load: 1058 lb
Max landing weight: 2350 lb
Disc loading: 2.9 lbs/sq.ft
Power loading: 5.6 lbs/hp
Max usable fuel: 469 lb
Max rate of climb: 1550 fpm
Service ceiling: 15,000 ft
Hover in ground effect: 13,400 ft
Hover out of ground effect: 8000 ft
Max speed: 112 kt
Normal cruise @ 3000 ft: 96 kt
Fuel flow @ normal cruise: 180 pph
Endurance @ normal cruise: 2.4 hr
Range: 308 mi

Mark II Tigershark
Engine: 420hp Allison 250-C20B
Rotor: 31’11”
Useful load: 1175 lb
Max speed: 135 mph
Cruise: 120 mph
Seats: 4

Mark IV
Engine: 420hp Allison 250-C20B
Rotor dia: 33’4″
Length: 30’0″
Useful load: 2100 lb
Max speed: 215 mph
Cruise: 201 mph
Range: 482 mi
Seats: 4-5