Post WW2

SIAI Marchetti SF.250 / SF.260 / Aviamilano F.250 / Waco Meteor

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SF.260

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.

SIAI Marchetti SF.250 / SF.260 Article

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.

Gallery

Aviamilano F.250
Engine: Lycoming 250 hp.

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

Savoia-Marchetti S.208

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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.

Savoia-Marchetti S.208 Article

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

Savoia-Marchetti S.205 / Waco Vela II / Taurus

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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

SIAI-Marchetti FN-333 Riviera / Nardi FN-333

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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

Nardi FN.333

SIAI-Marchetti / Savoia-Marchetti

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Societa Idrovolanti Alta Italia
Siai-Marchetti Societa Per Azioni

The original company was founded in 1915 as SIAI (Società Idrovolanti Alta Italia – Seaplane company of Northern Italy). After World War I gained the name Savoia, when it acquired the Società Anonima Costruzioni Aeronautiche Savoia, an Italian aircraft company founded by Umberto Savoia in 1915.

The name Marchetti was added when chief designer Alessandro Marchetti joined the company in 1922. Savoia-Marchetti gained prominence with the successful S.55 flying boat. Savoia-Marchetti became famous for its flying boats and seaplanes, which set numerous endurance and speed records. Favoured by Air Marshal Italo Balbo, the company began rapidly prototyping and developing a number of other aircraft, increasingly focusing on warplanes in the lead-up to World War II. However, most of S.M.’s manufacturing capabilities were destroyed in World War Two. It was renamed SIAI-Marchetti in 1943.

Since 1946 engaged in overhaul and repair work and developed new aircraft. SIAI-Marchetti only survived in postwar Italy by building trucks and railway equipment. However it still struggled with insolvency for 6 years after the war before declaring bankruptcy in 1951.

In 1953, the company reopened. Types have included SA.202 Bravo trainer produced jointly with FFA in Switzerland; S.205 four-seater and S.208 development. First flew SF.250 aerobatic trainer in July 1964; became highly successful SF.260 production aircraft for civil and military use (initials in SF.260 denoted design by Stelio Frati). In 1968 company formed a Vertical Flight Division, but increasing helicopter work became associated with Agusta and Elicotteri Meridionale. SM.1019 light multipurpose high-wing monoplane followed 1969, SF.600 Canguro transport 1979 (recently taken over by VulcanAir), and S211 jet trainer and light attack aircraft 1981.

Agusta, which had acquired 30% of SIAI-Marchetti in 1970, had increased its stake to about 60% by 1973 and reached complete ownership in 1983.

Company taken over by Aermacchi January 1997.

Short SD3.360 / 360

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The 360 is a growth development of the 330 with more power, and a three foot stretch ahead of the wing and a redesigned rear fuselage and tail surfaces. An extra six seats (in two rows) were accommodated by stretching the cabin and deleting the 330’s rear loading ramp, and the tail arrangement was changed to a conventional single fin.

Short SD3.360 / 360 Article

The prototype 360 flew on 1 June 1981 and the type entered service in December 1982. First introduced with Pratt & Whitney Canada PT6A-45R engines, the Shorts 360-300 version has 1,424 shp (1062 kW) PT6A-67R turboprops with six-bladed propellers and other refinements to produce about 18 per cent more thrust at take-off.

164 examples were sold up until 1991.

SD3.60
Engines: 2 x P&W PT6-65AR, 1403 shp
Props: Hartzell 5-blade, 111-in
Seats: 36
Length: 70.9 ft
Height: 23.7 ft
Wingspan: 74.7 ft
Wing area: 453 sq.ft
Wing aspect ratio: 12.3
Maximum ramp weight: 25,800 lb
Maximum takeoff weight: 25,700 lb
Standard empty weight: 16,600 lb
Maximum useful load: 9200 lb
Maximum landing weight: 25,400 lb
Wing loading: 56.7 lbs/sq.ft
Power loading: 9.7 lbs/hp
Maximum usable fuel: 3840 lb
Best rate of climb: 1010 fpm
Service ceiling: 20,000 ft
Maximum speed: 211 kt
Normal cruise @ 7,000ft: 160 kt
Fuel flow @ normal cruise: 975 pph
Endurance at normal cruise: 3.4 hr
Stalling speed clean: 94 kt
Stalling speed gear/flaps down: 78 kt
Turbulent-air penetration speed: 158 kt

Short 360-300
Engines: 2 x Pratt & Whitney PT6A-67R turboprops, 1062kW / 1,424 shp
Prop: 6 blade
Max take-off weight: 12290 kg / 27095 lb
Wingspan: 22.8 m / 75 ft 10 in
Length: 21.58 m / 71 ft 10 in
Height: 7.27 m / 24 ft 10 in
Wing area: 42.18 sq.m / 454.02 sq ft
Cruise speed: 400 km/h / 249 mph
Range w/max.payload: 745 km / 463 miles

Short SD3-30 / 330 / C-23 Sherpa

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330-200

The prototype of the Shorts SD3-30 30-passenger unpressurized commuter airliner; later redesignated Shorts 330, was derived from the smaller Skyvan, with a fuselage stretched to accommodate 30 passengers while retaining the Skyvan’s twin tail fin, but including a semi-retractable undercarriage.

Short SD3-30 / 330 Article

The Short SD3-30 prototype (G-BSBH), a 30-passenger airliner powered by twin turboprop engines, was flown for the first time at Belfast, Northern Ireland on 22 August 1974, and the first entered service with the Canadian airline Time Air on 24 August 1976, although the first order had been placed by Command Airways of Pouglikeepsie, New York.

Versions available included the standard 330-200, the Sherpa civil freighter, and the 330-UTT utility tactical transport.

The USAF operated 18 twin-turboprop Sherpa/330-UTT from Zweibrucken in West Germany, providing a distribution service for high-priority spares in Europe. Designated C-23A, the aircraft were ordered in March 1984 to fulfil the European Distribution System Aircraft (EDSA) requirement. Two Sherpas were delivered in November 1984, and the remaining 16 by the end of 1985.

The C-23A is a freighter version of the Shorts 330-200, retaining many features of the civilian model including the forward freight door. An hydraulically operated rear cargo door/ramp is incorporated in the Sherpa, thus allowing through loading. Up to seven C08 or four LD3 cargo containers or two half-ton vehicles can be accommodated, and utility passenger operations may also be undertaken. The C-23A first flew on August 6, 1984, and is powered by two 893kW Pratt & Whitney Canada PYT6A-45R turboprops.

Designated C-23B, the first of 10 Shorts Super Sherpas for the US Army National Guard made its first flight in 1990. The aircraft are similar to the 18 C-23A Sherpas used by the US Air Force, but have more powerful Pratt & Whitney Canada PT6A-65AR turboprops, strengthened wings, five-bladed propellers and air-operable rear freight doors for supply dropping.

Lacking the rear loading ramp of the Sherpa, the Shorts 330-UTT (Utility Tactical Trans¬port) can carry a maximum payload of 3,630kg. Typical loads include 33 troops, 30 paratroops, or 15 stretchers. Range with 30 fully armed troops is greater than 1,100km. Two inward opening rear side doors are provided for para¬dropping. Customers for the 330-UTT include the Royal Thai Army and Royal Thai Police.

Nearly 100 had been delivered by 1990, and a total of 141 Short 330s were built before production ended in 1992.

Gallery

SD3-30
Engines: 2 x P&WAC PT6A-45, 1120 hp
Seats: 33
Wing loading: 48.6 lb/sq.ft
Pwr loading: 9.8 lb/hp
Max TO wt: 22,000 lb
Operating wt: 14,230 lb
Equipped useful load: 7770 lb
Payload max fuel: 3930 lb
Range max fuel/cruise: 690 nm/3.5 hr
Range max fuel / range: 785 nm/ 5.5 hr
Service ceiling: 18,500 ft
Max cruise: 190 kt
Max range cruise: 144 kt
Vmc: 77 kt
Stall: 73-89 kt
1.3 Vso: 95 kt
ROC: 1130 fpm
SE ROC: 210 fpm @ 101 kt
SE Service ceiling: 9500 ft
Min field length: 3650 ft
Fuel cap: 3840 lb

SD3.30
Engines: 2 x P&W PT6A-45A, 1156 shp
Props: Hartzell 5-blade, 111-in
Seats: 30
Length: 58 ft
Height: 16.2 ft
Wingspan: 78.6 ft
Wing area: 453 sq.ft
Wing aspect ratio: 12.3
Maximum ramp weight: 22,500 lb
Maximum takeoff weight: 22,400 lb
Standard empty weight: 14,700 lb
Maximum useful load: 7800 lb
Zero-fuel weight: 21,140 lb
Maximum landing weight: 22,100 lb
Wing loading: 49.5 lbs/sq.ft
Power loading: 9.7 lbs/hp
Maximum usable fuel: 3840 lb
Best rate of climb: 1070 fpm
Certificated ceiling: 19,000 ft
Maximum single-engine rate of climb: 210 fpm @ 105 kt
Single-engine climb gradient: 120 ft/nm
Single-engine ceiling: 6750 ft
Maximum speed: 204 kt
Normal cruise @ 10,000ft: 197 kt
Fuel flow @ normal cruise: 890 pph
Endurance at normal cruise: 3.9 hr
Stalling speed clean: 89 kt
Stalling speed gear/flaps down: 74 kt
Turbulent-air penetration speed: 157 kt

330/UTT
Engine: 2 x P&WAC PT6A turboprop
Installed pwr: 1785 kW
Span: 22.8 m
Length: 17.7 m
Wing area: 42.1 sq.m
Empty wt: 6445 kg
MTOW: 11,160 kg
Payload: 3630 kg
Cruise speed: 372 kph
Initial ROC: 360 m / min
Ceiling: 6100 m
T/O run: 415 m
Ldg run: 235 m
Fuel internal: 2546 lt
Range/payload: 1390 km with 2330 kg
Capacity: 33 pax

C-23A Sherpa
Engine: 2 x P&WAC PT6A
Installed pwr: 1785 kW
Span: 22.8 m
Length: 17.7 m
Wing area: 42.1 sq.m
MTOW: 10,390 kg
Payload: 3175 kg
Cruise speed: 350 kph
Initial ROC: 360 m / min
Ceiling: 6100 m
T/O run (to 15m): 1036 m
Ldg run (from 15m): 1225 m
Fuel internal: 2032 lt
Range/payload: 1240 km with 2270 kg
Capacity: 33 pax

C-23A
Engines: 2 x Pratt Whitney PT6A-45R turboprops, 900kW
Max take-off weight: 10390 kg / 22906 lb
Loaded weight: 6680 kg / 14727 lb
Payload: 3175kg / 7000 lb
Wingspan: 22.76 m / 75 ft 8 in
Length: 17.69 m / 58 ft 0 in
Height: 4.95 m / 16 ft 3 in
Wing area: 42.1 sq.m / 453.16 sq ft
Cruise speed: 352 km/h / 219 mph
Ceiling: 6000 m / 19700 ft
Range w/max.payload: 370-1240 km / 230 – 771 miles
Crew: 3

Short 330 / C-23 Sherpa