Saab 90 Scandia
|Saab 90 Scandia|
|Saab Scandia of SAS at London Airport (Heathrow) in May 1953|
|First flight||November 16, 1946|
|Status||Out of service, one preserved|
The Saab 90 Scandia was a civil passenger aeroplane, manufactured by the Svenska Aeroplan Aktiebolaget (SAAB), in Linköping, Sweden. In 1944, as it was becoming clear that hostilities in Europe (the Second World War) would soon be at an end, SAAB realised that the company had to diversify from purely military endeavours if it were to survive. The board therefore decided to put into action a plan to manufacture a twin-engined, short- to medium-haul passenger aircraft, as a successor for the Douglas DC-3. (This was the same commercially driven stimulus that led to automobile production, with the Ursaab and subsequent Saab 92 passenger vehicles.)
The design of the 90 Scandia was quite similar to the DC-3. The only distinct visible difference was that the 90 had tricycle landing gear while the DC-3 had a tailwheel. The 90 had to compete with the many surplus DC-3s available on the market at the same time, making sales difficult.
Design and development
Development started in February 1944. Takeoff weight was specified at about 11,600 kg, with a range of about 1,000 km. The prototype Saab 90 (Scandia) first flew in November 1946. It was capable of seating 24–32 passengers, with low-speed capability. It was to be fitted with Pratt & Whitney R-2000 engines. It had a single nosewheel and fully retractable landing gear. ABA Swedish Airlines, a predecessor of SAS, ordered 11 examples. The 'Type Certificate' was issued in June 1950. Delivery started in October 1950 but, after testing, specification had changed to the Pratt & Whitney R-2180-E1. Two Brazilian airlines (VASP and Aerovias do Brasil) also ordered a total of six aircraft. The prototype was subsequently converted to a luxury private executive aircraft for the Brazilian industrialist Olavo Fontoura.
The Scandia project was initiated in 1944 by a supposed need (after WW2) for an aircraft carrying 25–30 passengers for a distance of up to 1000 km.
Main design objectives:
- Two Engines
- Long Life
- Economic Operation
The wing was shaped, using NACA profiles, to provide good stalling characteristics. Low wing design was chosen since it provided:
- Less structural weight
- Better safety in an emergency landing
- Possibility for one continuous flap
The wing was built in three pieces. The centre section with engine mounts, and left and right sections which were bolted to the centre section, immediately outboard of the engine nacelles.
The fuselage diameter was chosen to allow for four seats per row. This configuration gave a capacity of 32 passengers. A configuration with wider and more comfortable seats, three seats per row, carrying a total of 24 passengers was also offered. The prototype (90.001) was equipped with 1,450 bhp (1,080 kW) Pratt & Whitney Twin Wasp R2000 engines (changed to 1,650 bhp (1,230 kW) P&W Twin Wasp R2180 on the production version).
The entire aircraft was built of metal except for the rudders which were fabric-covered metal frames.
The prototype (SE-BCA) made its first flight on November 16, 1946. Claes Smith was the pilot. The first flight lasted for 20 minutes. The plane had exceptionally good slow-flying characteristics, with full control down to 110–115 km/h. The stall was slow and preceded by vibrations. The plane also turned out to be easily maneuvered with one engine turned off, which at the time was typically not the case with twin-engined aircraft. Unfortunately the rudder harmony was not satisfactory, with high control forces in some situations. The engine installation also needed redesign.
The prototype flew a total of 154 hours before the winter of 1947/48 when it was parked in the hangar for modifications. The engines were elevated for increased clearance between propeller blades and ground. The cabin, which previously only contained test equipment, was furnished. On February the 7th 1948 the prototype took off again and began the second testing phase. The second phase mainly consisted of performance tests. After 700 hours of test flying it was decided to introduce the following changes to the production planes:
- More powerful engines
- Four-blade Hamilton-Standard propellers
- Spring tabs on rudder and elevators for reduced control forces
In 1947 the prototype had quickly visited Denmark, the Netherlands, Belgium, and Switzerland. In May 1948 it made a one-day trip from Linköping to Newcastle via Oslo. During these flights the prototype had only test equipment on board. No real demonstration flights with potential customers took place. For this reason it was decided to make a real demonstration tour through Europe now that the cabin was properly outfitted.
113 Hours Around Europe
The prototype departed on August 9, 1948. After visits to 11 European countries, SE-BCA returned to Linköping on November 11, 1948. The first stop was in Stockholm. Then in the following order it visited Norway (Oslo), Ireland (Dublin), Great Britain (Prestwick, Gatwick, Jersey), Denmark (Copenhagen), Belgium (Brussels), the Netherlands (Amsterdam), Switzerland (Geneva, Zürich), Portugal (Lisbon, Oporto), Spain (Madrid), France (Paris) and finally Finland. Total flying time was 113 hours with 123 takeoffs and a total distance of 37,200 km. 1,200 passengers were transported. In the Netherlands, Prince Bernhard of the Netherlands flew the plane.
In every town the Scandia was welcomed by the respective airline and local press, but it did not result in any orders. Many airlines also visited Linköping for a closer look and demonstration during the years 1948–49. Some of these were DNL, Fred Olsen, DDL, Aero Oy, Swissair, FAMA, Aerol, Argentinas, KLM, Air Service, Sabena and Garuda.
A second promotional tour was started on August 16, 1949. With six extra fuel tanks, each carrying 400 liters, SE-BCA started a tour that would take it to three continents. This was also the last time it was seen in Sweden.
The first trip went to Paris where the extra fuel tanks were removed. On August 23, SE-BCA arrived to Addis Abeba (Ethiopia). The following day, emperor Haile Selassie went on a demonstration tour. Present on this tour was also Carl von Rosen, who at the time was counsellor for the Ethiopian Air Force. Athen, Kairo, Asmara, Port Sudan and Luxor were also visited on this tour. On this tour the plane was subjected to temperatures of 50°C, with no problems. When the plane returned to Paris the extra fuel tanks were reinstalled.
On September 4, SE-BCA left Paris with destination Pratt & Whitney's home base in Hartford, Connecticut. With stop-overs in Prestwick, Iceland and Greenland, the trip took three days. In Hartford the extra fuel tanks were removed and the interior was refitted. An extensive demonstration program all over the USA followed. Some of the cities visited were New York, Washington, Chicago, Miami, Los Angeles and Houston. In Los Angeles Howard Hughes flew the Scandia, and he praised the design. On October 14 the Scandia returned to Hartford.
The first production Scandias were delivered in 1950. SAS received their eight aircraft between October 1950 and October 1954. SAS initially operated their Scandias on intra-Scandinavian flights. Scheduled services by Scandias were also operated to European cities including Amsterdam, Brussels and London Airport (Heathrow) between 1951 and 1955.
VASP operated their fleet of new and ex-SAS Scandias on intra-Brazilian scheduled flights between October 1950 and late 1966.
The Swedish Air Force put heavy and insistent demands upon the SAAB factory, for the Saab 29 fighter aircraft, which spelled the end of the Scandia project in Sweden, with residual production being undertaken by Fokker, in the Netherlands.
Altogether, only 18 examples were manufactured. The entire SAS fleet was eventually purchased by VASP, in 1957.
A larger version with pressurised cabin called 90B was planned, but never made.
The last flight with a 90 Scandia was on July 22, 1969. The sole surviving Scandia is the 16th built, ex VASP PP-SQR, which is preserved in deteriorating condition by a museum at Bebedouro in the state of São Paulo.
- Saab 90A
- Twin-engined short-range airliner. Main production version.
- Saab 90B
- Proposed version. Not built.
Accidents and incidents
- December 30, 1958: a VASP Saab Scandia 90A-1 registration PP-SQE flying from Rio de Janeiro-Santos Dumont to São Paulo-Congonhas during climb after takeoff had a failure on engine no. 1. The pilot initiated procedures to return to the airport but during the second turn the aircraft stalled and crashed into Guanabara Bay. Of the 34 passengers and crew aboard, 20 died.
- September 23, 1959: a VASP Saab Scandia 90A-1 registration PP-SQV en route from São Paulo-Congonhas to Rio de Janeiro-Santos Dumont during climb after takeoff did not gain enough height and crashed 1 1/2 minutes out of São Paulo killing all 20 passengers and crew.
- November 26, 1962: a VASP Saab Scandia 90A-1 registration PP-SRA en route from São Paulo-Congonhas to Rio de Janeiro-Santos Dumont collided in the air over the Municipality of Paraibuna, State of São Paulo with a private Cessna 310, registration PT-BRQ, en route from Rio de Janeiro-Santos Dumont to São Paulo-Campo de Marte. Both were flying on the same airway AB-6 in opposite directions and failed to have visual contact. The aircraft crashed killing all 23 passengers and crew of the Saab and four occupants of the Cessna.
Only one 90 Scandia, PP-SQR, remains. It stands outdoors in at the Museu de Armas, Veículos e Máquinas Eduardo André Matarazzo in Bebedouro, Brazil. It is said to be complete, but in very bad condition. Saab tried to buy the plane for its 50 year jubilee in 1987, but the owner asked a price Saab thought was unreasonably high.
Data from From Seventeen to Thirty-Nine
- Capacity: 24 or 32 passengers
- Length: 21.30 m (69 ft 10½ in)
- Wingspan: 28.00 m (91 ft 10½ in)
- Height: 7.40 m (24 ft 3½ in)
- Wing area: 85.70 m² (922.5 sq ft)
- Empty weight: 9,960 kg (21,958 lb)
- Max. takeoff weight: 15,900 kg (35,053 lb)
- Powerplant: 2 × Pratt & Whitney R-2180-E Twin Wasp E 14-cylinder radial engine, 1,825 hp (1,361 kW) (with water injection) each
- Maximum speed: 450 km/h (243 knots, 280 mph) at 2,600 m (8530 ft)
- Cruise speed: 340 km/h (183 knots, 211 mph) (normal cruise)
- Range: 2,650 km (1,432 nmi, 1,647 mi)
- Service ceiling: 7,500 m (24,605 feet)
- Rate of climb: 7.5 m/s (1,475 ft/min)
- Aircraft of comparable role, configuration and era
- Stroud 1992, p. 60.
- "ASN Aviation Safety Database results:SAAB Scandia". Aviation Safety Network. Retrieved 29 June 2011.
- "Accident description PP-SQE". Aviation Safety Network. Retrieved 17 August 2011.
- Germano da Silva, Carlos Ari César (2008). "Ponte aérea das doze horas". O rastro da bruxa: história da aviação comercial brasileira no século XX através dos seus acidentes 1928–1996 (in Portuguese) (2 ed.). Porto Alegre: EDIPUCRS. pp. 171–173. ISBN 978-85-7430-760-2.
- "Accident description PP-SQV". Aviation Safety Network. Retrieved 18 August 2011.
- Germano da Silva, Carlos Ari César (2008). "Falha de motor na decolagem". O rastro da bruxa: história da aviação comercial brasileira no século XX através dos seus acidentes 1928–1996 (in Portuguese) (2 ed.). Porto Alegre: EDIPUCRS. pp. 177–181. ISBN 978-85-7430-760-2.
- "Accident description PP-SRA and PT-BRQ". Aviation Safety Network. Retrieved 2 June 2011.
- Germano da Silva, Carlos Ari César (2008). "No céu de Paraibuna". O rastro da bruxa: história da aviação comercial brasileira no século XX através dos seus acidentes 1928–1996 (in Portuguese) (2 ed.). Porto Alegre: EDIPUCRS. pp. 214–216. ISBN 978-85-7430-760-2.
- Green and Swanborough 1987, p. 15.
- Smith 1948, p. 609.
- Green, William and Gordon Swanborough. "From Seventeen to Thirty-Nine: A Saab Half-Century". Air Enthusiast. Thirty-three, May–August 1987. ISSN 0143-5450. pp. 9–25, 60–68.
- "Saab Scandia – Historien om ett trafikflygplan", Anders Annerfalk, Aviatic Förlag, Sweden, 1987, ISBN 91-86642-00-6
- Smith, Maurice A. "Scandia Discussed". Flight, 3 June 1948, pp. 607–613.
- Stroud, John. "Post War Propliners – Part 4". Aeroplane Monthly. September 1992, Vol 20 No 9. ISSN 0143-7240. pp. 56–60.
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