When, in January 1917, Capt F M Green became chief aeronautical engineer of the Siddeley-Deasy Motor Car Company, he began the design of a single-seat fighter, the S.R.2. A compact single-bay sesquiplane predominantly of wooden construction with fabric skinning, the S.R.2 was powered by a 320hp A.B.C. Dragonfly nine-cylinder radial engine. Armament comprised two synchronised 7.7mm machine guns.
A contract for six prototypes was reduced to three in mid 1918, the first of these flying in April 1919, by which time the fighter had been officially named Siskin. The first prototype Siskin was subsequently re-engined with an Armstrong Siddeley Jaguar, development in this form continuing after Siddeley Deasy acquired in 1921 the name and goodwill of Sir W G Armstrong Whitworth & Co Ltd, and the Armstrong Whitworth Siskin II emerging in 1922.
Max take-off weight: 989 kg / 2180 lb Empty weight: 664 kg / 1464 lb Wingspan: 8.38 m / 27 ft 6 in Length: 6.48 m / 21 ft 3 in Height: 2.97 m / 9 ft 9 in Wing area: 22.95 sq.m / 247.03 sq ft Max. speed: 233 km/h / 145 mph Ceiling: 7255 m / 23800 ft
Flown for the first time on 20 December 1947, the SM.101 was designed as a six-seat light transport and is powered by a 235 hp Walter Bora radial engine.
Welded steel-tube construction is used with fabric covering. Fowler-type flaps are fitted to the wing and dual controls are fitted.
Engine: 235 hp Walter Bora Wingspan: 54 ft 1 in Wing area: 322 sq.ft Length: 33 ft 6 in Height: 9 ft 9.5 in Empty weight: 2910 lb Loaded weight: 4828 lb Max speed: 149 mpg at SL Cruise: 140 mph at 9020 ft Range: 777 mi Service ceiling: 15,750 ft
n October 1963 Silvercraft SpA flew the XY prototype light helicopter further developed with financial and technical assistance of shareholder SIAI-Marchetti as the all-metal three-seat SH-4, the prototype of which (I-SILX) made its first flight in March 1965.
The SH-4 had a skid undercarriage and a high-set tubular corrugated tailboom with a small fin and tailplane and a two-blade tail rotor and powered by a 235hp (derated to 170hp) Franklin 6A-350-D1B piston engine. The main rotor had two blades and a transverse mass-balanced stabiliser bar.
A pre-production model was displayed at the 1967 Paris Air Show, certification was achieved in September 1968. The first helicopter of all-Italian design and construction to receive both Italian and U.S. certification. The SH-4 went into production at Silvercraft’s works at Sesto Calende in basic form. Variations were the SH-4/A for agricultural use and as the SH-4/C with a supercharged Franklin 6AS-350-D1 engine.
SH-4A
Serious production had begun as SIAI-Marchetti/Silvercraft SH-4, but under name Silvercraft alone deliveries began 1970. Production ceased 1977. Production of a batch of about 50 SH-4s was started at the Sesto Calende works with the aid of Fiat Aviazione (Motori), who manufactured mechanical parts for the rotor transmission, but the firm ran into difficulties over the Franklin engine, which had gone out of production.
A total of 21 SH-4s were completed with individual examples being exported to Brazil, South Africa, France and Holland. One aircraft was delivered to the Italian Air Force.
The company ceased operations in the late 1970s.
SH-4 / SH-4A Engine: Franklin 6AS-350-S1, 235 hp de-rated to 170 hp Main rotor diameter: 29 ft 7.5 in / 9.03 m Fuselage length: 25 ft 1.25 in / 7.65 m Empty weight: 1142 lb / 518 kg MTOW norm: 1900 lb / 862 kg Max cruise: 70 kt / 81 mph / 130 kph ROC: 1180 fpm / 360 m/min Service ceiling: 15,100 ft / 4600 m Range max fuel: 173 nm / 200 mi / 320 km Seats: 3 SH-4A ag capacity: 54 USG / 200 lt / 441 lb / 200 kg External cargo hook: 441 lb / 200 kg Cabin length: 4 ft 9.75 in / 1.47 m Cabin height: 4 ft 0.25 in / 1.24 m
Twin-engined light transport aircraft accommodating eight passengers. The first prototype flew on 24 February 1949. Originally powered with two 500 hp Ranger SVG-770-C1B, the type was modified to take two Pratt & Whitney R-985 Wasp Junior radials and a small batch was built for the Italian Air Force.
Engines: two Pratt & Whitney R-985 Wasp Junior Wingspan: 18 m / 59 ft 1 in Length: 43 ft Height: 11 ft 5 in Empty weight: 7600 lb Max take-off weight: 5050 kg / 11133 lb Max. speed: 330 km/h / 205 mph at 3280 ft Cruise: 180 mph at 11,480 ft Time to 5000ft: 6 mon Service ceiling: 19,700 ft Max range: 932 mi
The prototype for the SF.260 series, known as the F.250, flew for the first time on 15 July 1964. The version developed initially for civil production was manufactured at first under licence from Aviamilano by SIAI-Marchetti and is designated SF.260 (initials in SF.260 denoted design by Stelio Frati). Subsequently SIAI-Marchetti became the official holder of the type certificate and of all manufacturing rights of the SF.260.
A cabin monoplane with a cantilever low wing, the fuselage is an all-metal semi-monocoque structure of relatively thick skins and minimal stringers. The wing has a metal single spar, Friese type ailerons and electric slotted flaps. The wing is NACA 64-212 at the root and NACA 64-210 at the tip. The empennage contains cantilevered flying surfaces, with a manually operated trim tab on the elevator. The retractable tricycle undercarriage has oleo-pneumatic shock absorbers and a steerable nose wheel.
Designed by Stelio Frati and built in Italy, it is a 4 seater low-wing aircraft powered by a 260 hp Lycoming and has been predominantly sold in military versions since first flying in 1966. The SF.260 received FAA certifica¬tion on 1 April 1966.
Production of SF.260s for military use continued into 1987 in three versions: the SF.260M basic trainer, the armed SF.260W Warrior trainer and light attack aircraft, and the SF.260TP, powered by an Allison 250-B17C turboprop in place of the Lycoming 0-540 piston engine of the earlier models. The airframe is common in each case, except for a lengthened fuselage for the turboprop version. The SF.260W and TP have up to four underwing pylons for a variety of light stores, including rocket and gun pods to a maximum of 300kg.
Replacing the earlier C model, the SF.260D is powered by a 260 hp (194 kW) Textron Lycoming O-540-E4A5 engine and has the aerodynamic and structural improvements developed for the military SF260M. The similar SF260W Warrior can also double as a tactical support/liaison aircraft with light weapons. Production continues in 1990 of the SF.260TP, of which more than 60 had been ordered powered by the 350 shp (261 kW) Allison 250-B17D turboprop.
Some 350 SF260s were built in the 14 years since the type first flew. By 1993 more than 700 civil and military SF.260s of all models had been completed, most of which were for export.
Waco Aircraft was founded in 1966 to build SF.260 (as Waco Meteor), and Socata Rallye Commodore (as Waco Minerva).
Waco Meteor
In 1990 the PADC in the Philippines started assembling S 211s, followed by SF 260 TPWs and SF 600 Canguro in agreement with SIAI Marchetti of Italy.
SIAI-Marchetti SF.260 Engine: Lycoming O-540-E4A5, 260 hp TBO: 2000 hr Fuel type: 100LL Propeller type: CS Landing gear type: Tri./Retr Max ramp weight: 2430 lb Gross weight, utility: 2430 lb Gross weight, aerobatic: 2205 lb Landing weight: 2430 lb Empty weight, std: 1664 lb Useful load, std: 766 lb Useable fuel, std: 62 USG Payload, full std. fuel: 377 lb Wingspan: 27 ft. 5 in Overall length: 23 ft. 4 in Height: 7 ft. 11 in. Wing area: 109 sq. ft Wing Loading: 22.3 lbs./sq.ft Power loading: 9.3 lbs./hp Seating capacity: 3/4 Cabin width: 40 in Cabin height: 36 in Cruise speed, 75% power: 186 kt Fuel consumption, 65% power: 12.4 USgph Max range, 75% power: 800 nm Max range, 55% power: 1040 nm Vso: 57 kt Best rate of climb, SL: 1700 fpm Service ceiling: 21,370 ft Takeoff ground roll: 820 ft Takeoff over 50-ft. obstacle: 1610 ft Landing ground roll: 790 ft Landing over 50 ft. obstacle: 1610 ft
SF-260 Engine: Lycoming O-540-E4A5 or D4A5, 260 hp Prop: Hartzell 2 blade CS 76 in Wingspan: 27 ft 5 in Wing area: 108.7 sq.ft. Aileron area total: 8.5 sq.ft. Flaps area total: 12.7 sq.ft. Fin area: 8.05 sq.ft. Rudder area: 5.38 sq.ft. Tailplane area: 14.9 sq.ft. Elevator area: 10 sq.ft. Length: 23 ft Height: 7 ft 7 in Wheel track: 7 ft 5 in Wheel base: 5 ft 3.5 in Tire size mains: 6.00 x 6 Tire size nose: 5.00 x 5 Seats: 3 MTOW normal: 2430 lb MTOW aerobatic: 2095 lb Empty wt: 1488 lb Useful load: 937 lb Wing loading: 22.4 lb/sq.ft Power loading: 9.3 lb/sq.ft Fuel cap wing total/useable: 26 /25.4 USG Baggage capacity: 90 lb Fuel cap tip tanks total/useable: 38 /36.6 USG Max cruise SL: 230 mph Range max cruise 30min res: 1275 sm 75% cruise fuel burn: 19 USG/hr 60% cruise fuel burn: 14 USG/hr Stall: 65 mph Vy: 125 mph ROC SL: 1880 fpm Service ceiling: 21,235 ft Take off ground roll: 790 ft Landing ground roll: 790 ft Landing over 50ft obst: 1610 ft
SF.260C
SF.260D Engine: Textron Lycoming O-540-E4A5, 260 hp (194 kW). Rear seat load limit: 260 lb Max cruise@ 10 000 ft: 186 kts. Max range: 1,100 nm
SF.260E
SF.260M
SF.260TP Engine: 1 x Allison 250-B17D turboprop, 350 shp (261 kW). Span: 8.35 m Length: 7.4 m. Wing area: 10.1 sq.m Empty wt: 750 kg. MTOW: 1300 kg. Warload: 300 kg. Max speed: 380 kph Initial ROC: 660 m / min. Ceiling: 8500+ m T/O run: 300 m. Ldg run: 305 m Fuel internal: 235 (+144) lt. Range: 950 km Endurance: 3hr 20min. Combat radius lo-lo-hi: 150 km
SF.260W Warrior Max take-off weight: 1300 kg / 2866 lb Loaded weight: 830 kg / 1830 lb Wingspan: 8.35 m / 27 ft 5 in Length: 7.1 m / 23 ft 4 in Height: 2.41 m / 8 ft 11 in Wing area: 10.1 sq.m / 108.72 sq ft Max. speed: 305 km/h / 190 mph Ceiling: 4480 m / 14700 ft Range w/max.fuel: 1715 km / 1066 miles Armament: 300kg on underwing pylons
First flying in 1967, in 1968 the S.208 version became available, produced basically as a five-seat, more powerful version of the S.205, with some 60% of its structural components in common.
By February 1973, approximately 80 S.208s had been delivered to customers in Europe and Africa, including 44 S.208Ms to the Italian Air Force for liaison and training duties.
A version for general duties, including agricultural and ambulance work, was developed as the S.208AG.
S.208 Engine: Lycoming O-540-E4A5. 260 hp Wingspan: 35 ft 7.5 in / 10.86 m Length: 26 ft 3 in / 8.00 m Empty weight equipped: 1720 lb / 780 kg MTOW: 3307 lb / 1500 kg Max cruise: 162 kt / 187 mph / 300 kph Range, internal fuel: 647 nm / 746 nm / 1200 km Range Max fuel/tiptanks: 1085 nm / 1250 mi / 2000 km Seats: 5 Cabin length: 5 ft 10.25 in / 1.78 m Cabin width: 3 ft 8,25 in / 1.14 m Cabin height: 4 ft 4 in / 1.32 m Cabin volume: 88.0 cu/ft / 1.5 cu.m
A four-seat development of the SA.202 Bravo, design of the S.205 four-seat all-metal light monoplane was started in March 1964, first flying in 1965, and by April of 1965 three examples had been completed. Each had a 134kW Lycoming engine fitted, but a wide range of versions subsequently became available with different engines and equipment.
Savoia-Marchetti S.205 Article
The S205/22R was never a trainer. It was the retractable version of the 205 with a franklin engine. We also had a 205R which was the same airplane with a Lycoming. The left door was a factory option.
Waco Aircraft Co [2] was founded in 1966 to build Savoia-Marchetti S.205 (as Waco Vela II and Sirius) plus turbosupercharged Taurus derivative
S.205-22/R
S.205 Max take-off weight: 1350 kg / 2976 lb Empty weight: 750 kg / 1653 lb Wingspan: 10.86 m / 36 ft 8 in Length: 8 m / 26 ft 3 in Height: 2.89 m / 10 ft 6 in Wing area: 16.09 sq.m / 173.19 sq ft Max. speed: 295 km/h / 183 mph Ceiling: 6200 m / 20350 ft Range: 1325 km / 823 miles
S.205 18F Engine: Lycoming O-360-A1A, 180 hp Undercarriage: fixed
S.205 18R Engine: Lycoming O-360-A1A, 180 hp Undercarriage: retractable
S.205 20F Engine: Lycoming O-360-A1A, 200 hp Undercarriage: fixed
S.205 20R Engine: Lycoming O-360-A1A, 200 hp Undercarriage: retractable
S.205-22/R / Waco S.220 Vela Engine: Franklin 6A-350-C1, 220 hp Undercarriage: retractable
The three-seat prototype of the amphibian FN-333 flying boat, designed and built by Nardi S.A., flew first on 4 December 1952. Two more prototypes were built by Nardi through the decade. In the wake of the second Nardi prototype, Fiat of Italy also built two FN.333 prototypes, but did not continue with the exercise.
The initial prototype had “guitar-pick” style tailfins, and was powered by a Continental engine with 110 kW (145 HP); there had been thought of fixing the floats to the wingtips and then folding the wing downward after water landing, but the idea didn’t survive close examination.
Following the third Nardi prototype, an exclusive manufacturing licence for the FN-333 was obtained by SIAI Marchetti in March 1959. SIAI Marchetti called the aircraft “Riviera”.
SIAI-Marchetti placed a slightly enlarged four-seat variant in production which had flown in prototype form on 8 December 1954. The first of ten pre-production Rivieras was flown in February 1962.
The Riviera used a tricycle landing gear with the nose gear tucking up into the forward hull, the main gear hinging up to be stowed in the fuselage, as well as retractable floats, hinging up to mate with the wingtips, and no wing bracing. The twin tailfins were of trapezoidal configuration and had forward fillets. Powerplant was a Continental IO-470-P air-cooled flat-six engine with fuel injection, providing 185 kW (250 HP) and driving a two-bladed propeller.
Initial production was devoted to fulfilling orders from the USA were sales were handled by the Lane Aircraft Company which purchased the airframes for assembly by Southwest Airmotive. The first four were delivered to the USA bu mid-January 1963 and more than fifty had been sold by the middle of the year.
About 24 Rivieras were built through the 1960s, the exact number being hard to determine because of double-counting of serials.
Engine: 1 x Continental IO-470-P, 185kW Wingspan: 10.4 m / 34 ft 1 in Length: 7.4 m / 24 ft 3 in Height: 3.2 m / 11 ft 6 in Wing area: 15.0 sq.m / 161.46 sq ft Empty weight: 1030 kg / 2271 lb Max take-off weight: 1485 kg / 3274 lb Max. speed: 285 km/h / 177 mph at SL Cruise 70%: 264 km/h / 164 mph Econ cruise: 137 mph ROC: 1220 fpm Service ceiling: 5600 m / 18350 ft Range w/max.fuel: 1300 km / 808 miles Range w/max.payload: 1000 km / 621 miles Crew: 4
All Aero 