FFVS J-22

In 1939-1940, the Swedish air force had only a single fighter wing, equipped with 50-60 Gloster Gladiators with the Swedish designation J 8 (J = Jakt, interceptor or fighter). The government decided to equip two new wings and a total of 264 fighters of the types Seversky Republic EP-1 and Vultee Vanguard 48C 1 were ordered in the USA. 60 of the 120 EP-1s were delivered via Petsamo and were given the Swedish designation J 9. In July 1940 all export of fighters from the USA was stopped by a US Government embargo.
An indigenous fighter design was required, but with SAAB busy producing its B17 bomber, Flygforvaitninggens Verkstad (FFVS) was formed and designer Bo Lundberg was appointed to design a machine using non-strategic materials.
The air force chief instructed the aircraft designer Bo Lundberg to start planning for a Swedish made fighter. Lundberg had been in charge of the Swedish Air Commission in USA and before that chief designer of Götaverken’s aircraft division during the time they designed the GP 8 bomber which competed with SAAB 18 and the cancelled GP 9 fighter.
When Lundberg returned to Sweden at the end of 1940, he had already started planning for the new fighter. Requirements was that it should use the same engine as EP-1, STWC-3, a Swedish made Pratt and Whitney Twin Wasp, should be small and light, be made of components that could be made by a large number of subcontractors. The project was designated P 22 and a temporary air force branch was instituted to run the project, Flygförvaltningens Verkstad i Stockholm (FFVS).
The aircraft was from the outset designed for the Pratt&Whitney Twin Wasp, an American engine not available to Sweden. Even worse, the Severskies using the same engine had been delivered without spare engines so the shortage was really acute!
However, Flygmotor at Trollhättan started an ambitious programme to copy an original Pratt&Whitney Twin Wasp engine – without any drawings or material data at all. Working hard, they almost managed to meet the schedule. In 1942, to compensate for the lag in the engine project, Sweden managed to purchase a batch of 100 engines from the French Vichy regime via Germany. The Swedish-made engines, designated STWC-3, proved very good. One of them was still flying in the late 1980s, now mounted in one of the Swedish Airforce’s last flying C-47s.
Since the GV GP 9 was designed to use aluminum, it couldn’t be used as a basis for the new fighter, but its landing gear where the wheels were rotated as the were retracted back into the fuselage was used. The landing gear was made to accept skis, but as the air force’s ability to clear snow off runways had improved, they never were fitted on J 22.
Since a wooden wing couldn’t be made strong enough if it was made thin enough for a fast fighter, so the aircraft was made of steel tubing covered with moulded birch plywood.
The windshield was made either of 6 mm laminated Gemax or acrylic. The center part was 60 mm thick for ballistic protection.
The first prototype of the aircraft which was to be designated J 22 was built in the workshop of Flygtekniska Försöksanstalten (FFA) near Bromma airport, and first flew on September 20,1942, and deliveries began to F9 at Gothenburg in September 1943.
Both protypes crashed, one probably due to oxygen starvation of the pilot, the other due to engine failure during landing.
Of the 17000 component parts, 12000 were made at 500 subcontractors all over Sweden, with final assembly in a hangar at Bromma, except for the final 18 which were assembled at the air force central workshop at Arboga (CVA), which was set up in 1944 to be the central maintenance facility.

198 aircraft were built and delivered 1943-46. Of these the first 143 were of the version J 22A and the rest J 22B. The only difference between them was that J 22A was armed with two 13.2 mm and two 8 mm guns in the wings, and J 22B with four 13.2 mm guns. The sight was a fixed reflex sight.
The J 22 was a light and very manoeuvrable aircraft with good acceleration but when it entered service it was no match for the fighters then current. Tests were made against the P-51 after the war and even if the J 22 could hold its own for a while, especially with a skilled pilot, there is no doubt that the Mustang was the better fighter by a safe margin.
In 1945 J 22A was redesignated J 22-1, J 22B into J 22-2 and S 22 became S 22-3. The last ones were retired in 1952.
Nine J 22A were converted into reconnaissance aircraft in 1946 and redesignated S 22 (S = Spaning, reconnaissance) and converted back into fighters in 1947.

Engine: STWC-3, 1065 hp
Span: 10 m
Length: 7.8 m
Height: 3.6 m
Wing area: 16 sq.m
Empty weight: 2020 kg
Combat weight: 2835 kg
Fuel load:525 litres
Max speed: 575 km/h
Cruise speed: 440 km/h
Landing speed: 140 km/h
Range: 1270 km
Endurance: 2.9 h
Max altitude: 9300 m
Armament: 2 x 13.2 mm + 2 x 8 mm guns or 4 x 13.2 mm

J22B
J22B

FFV-Aerotech BA.14 Starling

Construction of the BA-14 Starling recreational trainer, designed by Bjorn Andreasson, began 1987.

First flying on 25 August 1988, the BA-14 SE-KFV was the result of a partnership between MFI and FFV Aerotech. The two seat BA-14 is powered by a 115hp Lycoming O-235 and is almost wholly of composite construction, one of its purposes being to allow FFV Aerotech to gain additional experience in the design of primary structure, production, testing and certification with this type of material.

It became a joint venture project between MFI and FFV Aerotech, but later redesigned by MFI to FAR Pt 23A. Development delayed by other work, but resumption of flight testing apparently still awaited.

Engine : Lycoming O 235, 85 hp
Length : 21.654 ft / 6.6 m
Height : 8.858 ft / 2.7 m
Wingspan : 37.402 ft / 11.4 m
Wing area : 122.71 sq.ft / 11.4 sq.m
Max take off weight : 1797.1 lb / 815.0 kg
Weight empty : 1058.4 lb / 480.0 kg
Max. weight carried : 716.6 lb / 325.0 kg
Max. speed : 124 kt / 230 km/h
Landing speed : 40 kt / 75 km/h
Cruising speed : 103 kt / 190 km/h
Initial climb rate : 590.55 ft/min / 3.0 m/s
Service ceiling : 11155 ft / 3400 m
Wing load : 14.56 lb/sq.ft / 71.0 kg/sq.m
Range : 346 nm / 640 km
Crew : 2

FFT / Gesellschaft Fur Flugzeug- Und Faserverbund-Technologie Mbh

Gyroflug Ingenieursgesellschaft Mbh was founded 1978 to develop the SC 01 Speed Canard as full production aircraft based on U.S. Rutan VariEze. 1989 renamed FFT / Gesellschaft Fur Flugzeug- Und Faserverbund-Technologie Mbh, and became subsidiary of Justus Dornier Group 1984. Also developed manned and unmanned surveillance versions, but this program halted. Also took over development of FFA-2000 trainer from FFA, becoming Eurotrainer 2000A.

FFG Prag Fg227

The quarter scale FFG Prag Fg227 was powered by 6 ILO 2 stroke engines rated at 21hp each. It was a ¼ scale BV.238 built by students at Prag under the direction of Dipl.Ing. Ludwig Karch.

A quarter-scale testbed called the FGP 227, registered as BQ+UZ, was deemed necessary to test the aerodynamics and water handling.

Intended to allow flight tests to commence from the manufacturers airfield, the FGP 227 refused to take-off from the grass airfield.

The aircraft was dismantled and transported to Erprobungsstelle See, Travemünde (E-Stelle – flying boat testing station). During transport French prisoners of war loading the wing onto flat-bed trucks allowed it to fall from a crane causing damage which was not repaired until September 1944.

Flight tests commenced in September 1944 as soon as the repairs were completed, but all six engines stopped due to fuel starvation soon after take-off, resulting in a heavy landing on the water. The FGP 227 was again repaired after which the aircraft flew several more times. By this time construction and testing of the BV 238 had started, so no useful data was gleaned from the programme.

Powerplant: 6 × ILO F 12/400 air-cooled two-stroke piston engines, 15.7 kW (21.1 hp) each
Propellers: 3-bladed fixed pitch propellers
Wingspan: 15.25 m (50 ft 0 in)
Length: 11.95 m (39 ft 2 in)
Height: 3.54 m (11 ft 7 in)
Wing area: 24.24 sq.m (260.9 sq ft)
Empty weight: 1,250 kg (2,756 lb)
Gross weight: 1,640 kg (3,616 lb)
Crew: 2

FFA FFA-2000

The FFA Flugzeugwerke FFA-2000 was built for the Swissair training school to replace Piaggio P-149s. After starting studies in 1986, FFA began full development testing of a 10 ft / 3 m span model in the FAF wind-tunnel at Emmen was followed by the decision in February 1988 to build two prototypes, and the Swissair order for eight aircraft was placed on 25 April.

The FFA-2000 is largely of composite construction, using a wing designed in Germany by Gyroflug-FFT.

FFT / Gesellschaft Fur Flugzeug- Und Faserverbund-Technologie Mbh took over development of FFA-2000 trainer from FFA, becoming Eurotrainer 2000A.

Engine: Porsche PFM 3200, 217 hp
Seats: 2

FFA AS.202 Bravo

The Bravo first flew in March 1969, with a 112kW engine, as the 202/15. After completing an agreement with SIAI-Marchetti to produce the AS.202 Bravo, the Swiss developed the AS.202/18A. This suffix indicated its uprated 180-hp (134-kW) Lycoming engine and full aerobatic capability. The Swiss company Flug- und Fahrzeugwerke AG Altenrhein flew the first example (HB-HEY) of the AS.202/18A, a two/three-seat aerobatic development of the Italian SIAI-Marchetti AS.202 Bravo on 22 August 1974. These were followed by the 195kW 202/26 in 1978. Civilian and military operators have bought 166 Bravos up to 1987.

FFA AS.202 Bravo Article

AS.202/15
Engine: Lycoming O-320-E2A, 150 hp
Wingspan: 31 ft 11.75 in / 9.75 m
Length: 24 ft 7.25 in / 7.50 m
Empty weight: 1388 lb / 630 kg
Max payload: 595 lb / 270 kg
Max cruise 75% 8000ft/2440m: 114 kt / 131 mph / 211 kph
ROC SL: 633 fpm / 193 m/min
Service ceiling: 14.000 ft / 4265 m
Max range: 498 nm / 574 mi / 925 km
Seats: 2
Cabin length: 7 ft 0.5 in / 2.15 m
Cabin width: 3 ft 4.25 in / 1.02 m
Cabin height: 3 ft 7.25 in / 1.10 m
Rear baggage: 220 lb / 100 kg

AS.202 Bravo
Engine: 1 x Lycoming AEIO-540, 195 kW.
Span: 9.8 m.
Length: 7.5 m.
Wing area: 13.9 sq.m.
Empty wt: 795 kg.
MTOW: 1200 kg.
Warload: 195 kg.
Max speed: 265 kph.
Initial ROC: 360 m / min.
Ceiling: 5700 m.
T/O run: 185 m.
Ldg run: 210 m.
Fuel internal: 160 lt.
Range: 850 km.

FFA AS 202 / 18A Bravo
Length: 24.606 ft / 7.5 m
Height: 9.186 ft / 2.8 m
Wingspan : 32.152 ft / 9.8 m
Wing area : 149.62 sqft / 13.9 sq.m
Max take off weight : 2381.4 lb / 1080.0 kg
Weight empty : 1565.6 lb / 710.0 kg
Max. weight carried : 815.9 lb / 370.0 kg
Max. speed : 130 kts / 241 km/h
Landing speed : 49 kts / 90 km/h
Cruising speed : 110 kts / 203 km/h
Initial climb rate : 787.40 ft/min / 4.00 m/s
Service ceiling : 16995 ft / 5180 m
Wing load : 15.99 lbs/sq.ft / 78.00 kg/sq.m
Range : 616 nm / 1140 km
Engine :
Lycoming AEIO 360 B1F, 132 hp
Crew : 2

AS 202-18A-3 Bravo

AS.202/26 Bravo
Engine: 1 x Lycoming AEIO-540, 195 kW.
Span: 9.8 m.
Length: 7.5 m.
Wing area: 13.9 sq.m.
Empty wt: 795 kg.
MTOW: 1200 kg.
Warload: 195 kg.
Max speed: 265 kph.
Initial ROC: 360 m / min.
Ceiling: 5700 m.
T/O run: 185 m.
Ldg run: 210 m.
Fuel internal: 160 lt.
Range: 850 km.

FFA P-16

FFA was awarded development contract July 1952 for P-16.04 interceptor/ground-attack aircraft with Armstrong Siddeley Sapphire, first flown April 28,1955. Fitted with leading-edge flaps, the first prototype had a wing thickness/chord ratio of between 5 and 6%. The second prototype was reduced to 4% and a higher powered turbojet.

P-16.04

The airframe is low wing, with 20o sweepback. Swept tail surfaces, have a variable incidence tailplane mounted mid-way up the fin, with conventional rudder and elevators. The ailerons can be lowered with Fowler flaps to provide additional flap area. Full-span leading edge flaps and an air-brake is fitted on each side of the rear fuselage. A tricycle undercarriage, with twin wheels on each unit, main wheels retracting inwards into the fuselage and the nose wheel retracts reward.

Internal fuel capacity is 550 gal, including fixed wingtip tanks. The is provision for two 100 gal underwing jettisonable tanks. Armament is two 30mm Hispano cannon in the nose and 44 air-to-air unguided rockets in fuselage pack.

The prototype Mk.III first flew in March 1960.

Mk.III

Program cancelled by Swiss Government but continued as private venture until June 1960; five aircraft built.

The P-16 wing formed the basis of the Gates Learjet design.

1st prototype
Engine: Armstrong Siddley Sapprire A.S.Sa.6, 7900 lb
Loaded weight: 17,857 lb
Max speed: 630 mph approx.
Armament: 2 x 30mm Oerlikon 302RK cannon

Engine: Armstrong-Siddeley Sapphire Sa.7
Length: 11.14 m
Span: 12.3 m
Max T/O weight: 11700 kg
Weapons load: 3000 kg
Max. horizontal speed: 1140 km/h / M 0.92
Altitude: 14000 m
T/O and Landing roll: < 500 m
Range: 1480 km

P-16 Mk.III
Engine: Bristol Siddeley Sapphire, 11,000 lb
Wingspan: 36 ft 7 in
Wing area: 320 sq.ft
Length: 46 ft 9 in
Height: 13 ft 5 in
Empty weight: 15,520 lb
MTOW: 27,795 lb
Internal fuel: 550 gal
Max speed: 696 mph SL
Service ceiling: 46,000 ft
Max range: 620 mi
Armament: 2 x 30mm Hispano cannon
Hardpoints: 4
Wheel track: 10 ft 2 in
Wheel base: 18 ft

FFA / Flug- und Fahrzeugwerke AG

Founded 1948, the reorganized Swiss Domier-Werke Alntenrhein, Flug- und Fahrzeugwerke AG discontinued development of Morane-Saulnier piston-engined fighters after completing prototype D-3803. Awarded development contract July 1952 for P-16.04 interceptor/ground-attack aircraft with Armstrong Siddeley Sapphire, first flown April 25,1955. Program canceled by Swiss Government but continued as private venture until June 1960; five aircraft built. Participated in license-production programs for de Havilland Vampire and Venom, Pilatus P-3, Mirage IIIRS, and HIS. Designed and manufactured Diamant glassfiber sailplane. Currently named FFA Flugzeugwerke Altenrhein AG., continues to produce (under original agreement with SIAI-Marchetti signed in 1967) the AS-202 Bravo two-seat trainer/aerobatic aircraft (first flown 1969). FFA-2000 programme was transferred to FFT.