Fiat BR.20 Cicogna

A medium bomber, the Fiat BR.20 Cicogna (stork) series was nearing obsolescence by the outbreak of World War II. Designed by Ingeniere Celestino Rosatelli, and owing much of its design to the Fiat APR.2 commercial transport, the Fiat B.R.20 prototype flew first on 10 February 1936.

Fiat BR.20 Cicogna Article

Powered by two 745kW Fiat A.80 RC.41 radial engines, the B.R.20 possessed a maximum speed of 430km/h at 4000m, and was armed with two 7.7mm and one 12.7mm machine-guns.
The first unit of the Regia Aeronautica to receive B.R.20s was the 13º Stormo BT stationed at Lonate Pozzolo: the 7º Stormo BT, also at Lonate, received Fiat B.R.20s in February 1937.
Elements of the 7º and 13º Stormi BT were despatched to Spain in May 1937 for combat experience, while other B.R.20s were exported to Japan, and saw service with indifferent results in China and Manchuria as the JAAF’s Army Type 1 Model 100 Heavy bomber. Modified nose contours, increased armour protection and revised armament featured in the B.R.20M, of which 264 were produced.

When Italy declared war on 10 June 1940 the Regia Aeronautica had 162 Fiat B.R.20s and B.R.20Ms in commission with the 7º, 13º, 18º and 43º Stormi BT. The first bombing mission was made on 13 June when 19 B.R.20Ms of the 13º Stormo BT attacked installations at Hyeres and Fayence in southern France. A detachment of 80 B.R.20MS of the 13º and 43º Stormi BT were sent to the Belgian airfields of Chieveres and Melsbroeck in late September 1940 to assist the Luftwaffe in its bombing campaign against England. As part of the Corpo Aereo Italiano the B.R.20Ms suffered losses as a result of crew failings and fighter attacks. The campaign in Greece saw the 116º Gruppo (37º Stormo) in action from bases in Albania, followed by action over Crete, and on a day and night attacks against Malta. In the USSR B.R.20MS of the 38º and 116º Squadriglie operated from August 1942 in the southern sector.

Fifteen of the improved B.R.20bis model were produced. These were powered by two 932kW Fiat A.82 RC.42S engines, had additional 7.7mm machine-guns and a power-operated dorsal turret. Early in 1943 the B.R.20M bomber had been withdrawn from active service with the Regia Aeronautica, units being re-equipped either with CANT Z.1007s or with Savoia-Marchetti S.M.79S.
Production totalled 602 of all marks.

In 1938 the JAAF purchased 80 BR.20 bombers for use in China, designated Type-I Italian Type. Western sources originally called it ‘Mikado’. It appeared in code lists as ‘Ruth’.

JAAF BR.20

FIAT BR. 20 Cicogna
Engine: 2 x FIAT A. 80 RC.41, 986 hp / 745kW
Length: 53 ft 2 in / 16.2 m
Height: 14.108 ft / 4.3 m
Wingspan: 70 ft 10 in / 21.56 m
Wing area: 796.536 sqft / 74.0 sq.m
Max take off weight: 21829.5 lb / 9900.0 kg
Weight empty: 14112.0 lb / 6400.0 kg
Max. speed: 267 mph / 233 kts / 432 km/h at 4000m
Cruise speed: 340 km/h / 211 mph
Service ceiling: 29528 ft / 9000 m
Wing loading: 27.47 lb/sq.ft / 134.0 kg/sq.m
Range w/max.fuel: 1620 nm / 3000 km
Armament: 1x MG 12,7mm, 2x MG 7,7mm, 1600kg Bomb.
Crew: 4-5

B.R.20M

B.R.20bis
Engines: two 932kW Fiat A.82 RC.42S

Fiat G.12

The first prototype flew in May 1941.

The 23 seat G-12L had a longer fuselage and carried more passengers.

G.12LB

Gallery

G.12C
Engine: 3 x FIAT A.74 RC 42, 574kW
Wingspan: 28.6 m / 93 ft 10 in
Length: 20.16 m / 66 ft 2 in
Height: 4.9 m / 16 ft 1 in
Wing area: 113.5 sq.m / 1221.70 sq ft
Max take-off weight: 12800 kg / 28219 lb
Loaded weight: 8890 kg / 19599 lb
Max. Speed: 396 km/h / 246 mph
Cruise speed: 308 km/h / 191 mph
Ceiling: 8000 m / 26250 ft
Range: 1740 km / 1081 miles
Crew: 3
Passengers: 14

G.12L
Engines: 3 x Fiat A.74 RC.42, 770 hp.
Crew: 4.
Pax cap: 13.

G.12LB
Engines: 3 x Bristol Pegasus 48, 730 hp.
Crew: 4.
Pax cap: 13.

Fiat G.5

G.5bis

The Fiat G.5 tandem two-seat touring and training monoplane was produced in 1933 in two versions, the G.5 with a 140 hp Fiat A.54 radial engine, and the G.5bis with a 205 hp Fiat A.70 radial.

The prototype G.5 was powered by a 142 hp Fiat A.60 four cylinder inverted inline engine. The wing structure was entirely wood and the fuselage a welded steel-tube structure. Dual controls were fitted and the aircraft is fully aerobatic.

The G.5 was also produced as a three-seater.

G.5
Engine: 140 hp Fiat A.54

G.5bis
Engine: 205 hp Fiat A.70
Max speed: 143 mph
Cruise: 126 mph
Ceiling: 18,900 ft
Range: 478 mi
Empty weight: 1280 lb
Loaded weight: 1898 lb
Wing span: 34 ft 1.5 in
Length: 25 ft 9 in
Height: 7 ft 11.75 in

Fiat AS.1 / AS.2 / TR.1

AS.1

The Fiat AS.1 was a light touring aircraft developed in Italy in the late 1920s. It was a basic and conventional design: a parasol wing monoplane with tailskid undercarriage and seating for two in tandem open cockpits. The type proved extremely popular, and the production run would eventually extend to over 500 machines, with roughly half of these purchased by the Regia Aeronautica as trainers and liaison aircraft. Construction was of wood throughout, covered by plywood, fabric, and (around the nose) metal. A later development, designated TR.1 featured a metal structure instead.

TR.1

AS.1s were used successfully in a number of competitions and record-breaking events. In August 1929, they participated in the Challenge 1929 international contest, and in January 1930, an AS.1 piloted by Renato Donati with mechanic Gino Capannini was used to set endurance, distance, and altitude records in its class (29 hr 4 min 14 sec, 2,746.2 km/1,706.4 mi, and 6,782 m/22,251 ft respectively). On 28 December 1932, Furio Niclot and Mariano Lanciani used a specially-engined example to set the seaplane altitude record in its class (7,362 m/24,154 ft), then swapping wheels for pontoons, the same aircraft went on to set the equivalent landplane record two days later (9,282 m/30,453 ft). Long-distance feats included flights from Rome to Mogadishu and Vercelli to Tokyo (both by Francis Lombardi and Gino Capannini) and an aerial circumnavigation of Africa (27,600 km/17,150 miles) in 54 days by Francis Lombardi, Count Lodovico Mazzotti, and Mario Rasini).

AS.2

Variants

AS.1 – initial version with Fiat A.50 engine
AS.1 Idro – floatplane version
AS.1 Sci – ski-equipped version
AS.2 – version with strengthened structure and Fiat A.50S engine
TR.1 – version with metal structure and enclosed cabin

AS.1
Engine: 1 × Fiat A.50, 67 kW (90 hp)
Length: 6.10 m (20 ft 0 in)
Wingspan: 10.40 m (34 ft 2 in)
Height: 2.53 m (8 ft 4 in)
Wing area: 17.5 sq.m (188 sq.ft)
Empty weight: 450 kg (990 lb)
Gross weight: 690 kg (1,520 lb)
Maximum speed: 158 km/h (98 mph)
Range: 1,000 km (621 miles)
Service ceiling: 6,800 m (22,310 ft)
Crew: 1, pilot
Capacity: 1 passenger

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

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