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Aviation History
1961
1961 - 1723.PDF
FLIGHT, 23 November 1961 829 Latest to operate the Twin Pioneer is Sierra Leone Airways Commercial Aircraft of the World . . . Although designed as an executive aeroplane, the P. 166 can be deliveredin a number of versions, for cargo, ambulance, survey, etc. In the ten-seat high-density version, it is employed as a feederliner by severalairlines, among which are: Ansett-Mandated Airlines (New Guinea). Papuan Air Transport (New Guinea), Deutsche Nah-Luftverkehr(Germany), Deutsche Taxiflug (Germany). Powerplant: Two Lycoming GSO-480-BIC6 piston engines driving7ft 9in Piaggio P1O33-G4/BS or Hartzell HC-83 2O-2CL/L9333 three- bladed propellers. Dimensions: Span, 46ft 9in; length, 38ft lin; height empty, 16ft 5in;wing area, 286 sq ft. Weights: Max take-off. 8,1151b; max landing, 8.1151b; capacity pay-load, 1.8301b; weight less fuel and payload, 5.5601b. Pay load accommodation: Cabin volume, 300 cu ft; baggage and freightvolume, 87 sq ft; cabin length, lift 8in; max internal width, 5ft 2in; max height. 5ft 9in; max usable floor area, about 60 sq ft; dimensionsof largest door, 53in • 26in plus 41in ' llin optional; seats, 6-8. Fuel capacity: 185 Imp gal (222 US gal). Performance: Typical cruise speed. 163kt (188 m.p.h.) at 10.000ft and8,115lb; corres fuel consumption, 29 Imp gal/hr; range A (max pay- load), 562 n.m. (647 st.m.); range B (max fuel), 1.040 n.m. (1.200 st.m.);VNE, 192kt IAS; VNO. 152kt IAS; Vso, 64.5kt EAS. Piaggio Douglas PD-808 Announced on April 21, 1961, this light jet6/10-seat transport is a Douglas design which will be developed and built by Piaggio in Italy. PD-808 is the commercial business-executiveversion of the project, which is intended initially to meet Italian Air Force requirements. The arrangement between the two companiesprovides that Douglas will sell and service the PD-808 throughout most of the world, and may eventually manufacture the aircraft in the USunder certain customer and production-rate conditions. Two aircraft are being built, the first being scheduled to fly late in 1962. Deliveryis offered in 1963. Powerplant: Two GE CJ610-1 turbojets of 2.85OIb static take-offthrust at SL; or alternatively two Bristol Siddeley Viper 20 turbojets of 3.0001b static take-off thrust at SL. Dimensions: Span, 40ft 8in (with tip-tanks); area, 225 sq ft; length,39ft 6in. Weights: Max take-off, 15.0001b: max landing. 14.3001b; capacitypayload, 2,0001b; weight empty. 7.5271b. Fuel capacity: 835 US gal, including tip-tanks of 112.5 US gal each.Performance: (G.E. engines) Max cruising speed. 40.000ft. 520 m.p.h.; max flight duration, four hours; take-off FA A field length. 3,900ft:take-off over 50ft obstacle. 2.770ft; landing over 50ft. 2.350ft; approach speed, 119 m.p.h. I arszawski O.srodekPOLAND Warsaw Aircraft Design Centre,Konstrukiji Lotniczych. WSK-Okecie, Poland. MD-12 Evolved from the earlier and smaller CSS-12 twin-enginedaircraft to a Polskie Linie Lotnicze (LOT) specification, this Polish light transport was first shown publicly on September 6. 1959. Thedesign of Prof Dr Francisyek Misztal and Prof Lesyek Duleba. the MD-12 is intended for use mainly as a passenger/cargo or all-cargotransport on'short-haul domestic routes. Other versions coverambulance. agricultural and survey duties, for which the short-field, characteristicsof the MD-12 are said to be suitable. The low wing has slotted ailerons. Powerplant: Four Narkiewicz WN-3 air-cooled radial piston enginesof 340 b.h.p. each. Dimensions: Span. 69ft llin: length. 51ft lOin; height. 19ft; wingarea, 592 sq ft. Weights: Max take-off, 16,5301b; payload. 4.1881b, weight less fueland payload, 10.9121b. Pavload accommodation: Storage for 5501b baggage; max seats. 20.Fuel capacity. 209 Imp gal (250 US gal). Performance: Cruise speed, 1 54kt (177 m.p.h.) at 8,200ft; take-off to50ft with engine cut on take-off, 2,625ft; full-payload range (including 30min reserve fuel), 378 n.m. (435 st.m.). POTEZ Etablissements Henry Potez, 46 Avenue Kleber, Paris XVI,France. Potez 840 First flown on April 25. 1961, the Potez 840 is a four-engined executive transport and feederliner. A production batch of 25 has been laid down by Potez, who are financing the project, and a firmorder for 25 is said to have been placed by Turbo Flight Inc. a US business corporation. A second 840 is due to fly in the near future.Delivery to a commercial operator can be made early in 1963, and price of a production aircraft is quoted as "less than $400,000"' (£150,000).The reasons given by Potez for the choice of four Astazous instead of two Bastans are: superior performance in the engine-out case; passengerpreference; ease of ferrying back to base, following an engine failure; superior reverse-thrust performance for landing (quoted as 800ft);and, with the use of 60° of flap, maximum exploitation of slipstream effect. Potez are putting special emphasis on their ability to support the840 with a comprehensive after-sales service. Potez 840 Powerplant: Four Turbomeca Astazou II of 523 s.h.p. each drivingRatier Figeac 7fi propellers. Dimensions: Span, 63ft 8in; length. 52ft; height empty. 17ft Sin:wing area, 377sq ft. Weights: Max take-off. 18,7OOIb; max landing. 17.8001b; zero fuel,16.0001b; capacity payload, 4.7641b. Payload accommodation: Cabin volume. 670 cu fI; baggage andfreight volume. 82 cu ft: cabin length. 22ft 10 in: max internal width. 6fi; max height. 5 ft 9in; max usable floor area. S>I sq ft; dimensions oflargest door, 25in 54in; max seats, 24; at 33in pitch, 16. Fuel capacity: 446 US gal. Performance: Opt-cost (i.e., typical) cruising speed. 280kl at 20.000ft and 17.8001b; corres fuel consumption. 2.45 n.m. gal; lakc-off field length (SR 422 B). 3,280ft; landing field length. 3.730ft; range A (max payload), 970 n.m.; range B (max fuel), 1.000 n.m.; corrcs payload 3.1601b; cruise Mach number. 0.61; VNE, 300kt IAS; VNO, 270kt IAS Vso, 77kt IAS. Potez 840 Executive Powerplant: As above. Dimensions: As above. Weights: Max take-off, 19,6001b; max landing. 17.8001b; zero fuel,13,7OOIb; max capacity payload. 4.0001b: weiuht less fuel and payload 11.3601b. Payload accommodation: As above, except: max seats. 10. Fuel capacity: 872 US gal.Performance: Opt-cost (i.e., typical) cruising speed. 278kt at 20.000ft and 16.5001b; corres fuel consumption. 2.45 n.m./gal; take-off fieldlength (SR 422 B). 3,780ft: landing field length, 3.260ft; range A (max payload), 1.000 n.m.; range B (max fuel). 2.140 n.m.; corres payload,2,0001b; placard speeds, as above. SAAB Srenska Aeroplan Aktiebolaget. Linkoping. Sweden.Scandia A-2 Although the Scandia first flew 15 years ago—on November 16. 1946—15 of the total of 18 thai were built are still inservice (with VASP). The aircraft was designed to meet the then-current ICAO and CAA requirements for passenger transport aircraft and wasintended for short and medium stages. The first order was placed by SAS in 1948 and the Scandia was introduced into service in 1950. Powerplant: Two Pratt & Whitney R-2180-E1 Twin Wasps of 1,650b.h.p. driving 12ft 3in Hamilton Standard Hydromatic propellers. Data appeared in Flight for November 20, 1959, page 614.Saab 105 Designed primarily as a military and civil trainer and liaison aircraft, this twin-jet project, shown in model form at the Paris Salon inMay, could also be used in an executive role. A prototype is being built at Linkoping, target date for the first flight being early 1963. At presentthe project is being financed entirely by Saab, although strong Govern- ment interest is said to have been expressed. As an executive aircraft,the 105 seats four or five passengers, while for airline pilot training there is side-by-side seating, and two or three pupils can be accommo-dated in the rear of the cabin for navigational training. Flight reference: June 1. 1961. Powerplant: Two Turbomeca ducted fans of 1.5401b static thrusl each.Dimensions: Span. 31ft 2in; length. 34A 5in: height, 8ft lOin; wing area, 175 sq ft. Weights (executive version): Max take-off. 7.8961b; equipped weight,4.5401b: manufacturer's weight empty. 4,4401b; max landing, 7.7331b. Performance: Max continuous cruising speed. 450 m.p.h.; balancedfield length. 2.890fi: landing distance from 50ft. 3,180ft; range at normal cruising speed. 1.450 st.m. SCOTTISH AVIATION Prestwick Airport. Ayrshire. Scotland.Twin Pioneer A 16-seat feederliner with true STOL capability, the Twin Pioneer is specifically intended for operations in remote areas ofthe world where available runway lengths are striclly limited. The proto- type flew on June 25, 1955, and the first production aircraft followedrather less than a year later, on April 28. 1956. The latest version is the Series 3, in which 625 h.p. Alvis Leonides engines replace the 550 h.p.Leonides of the earlier series. Most operators are converting their Twin Pioneers 10 Series 3 standard. Five Twin Pioneers have been modified by Scottish at the request ofPhilippine Air Lines, and supplied with Pratt & Whitney R-1340 Wasps; little structural change was required. Another specialized variant ofthe Twin Pioneer supplied to the Rio Tinto Finance & Exploration Co has a 9ft increase in wingspan with the installation of pods on the wingtips carrying electro-magnetic equipment for geographical survey. Some 25 Twin Pioneers have now been manufactured for civil use andairline operators include de Kroonduif (3). Philippine Air Lines (5). Borneo Airways (3). Sierra Leone Airways (2). Flight descriptions:July 1. I960 (air test): September 4, 1959; November 1. 1957; July 6. 1956; and September 30, 1955. Basic price £66.500 less radio.Twin Pioneer Series 3 Powerplant: Two Alvis Leonides 531/8B piston engines of 625 b.h.p.driving de Havilland propellers. Dimensions: Span. 76ft 6in; length, 45ft 3in; height, 12ft lin; wingarea. 670 sq ft. Weights: Max take-off. 14.6001b: max landing, 14,6001b; zero fuel,14.6001b; capacity payload. 3.5501b; weight less fuel and payload, 10.2001b. Pavload accommodation: Cabin volume. 730 cu ft; baggage andfreight volume. 99 cu ft; cabin length, 22ft 8in; max width, 6ft; max height, 5ft 9in: dimensions of largesf door, 5ft 3in 3ft 1 lin; max seats.18 Fuel capacity: 241 Imp gal (standard), 371 Imp gal (long range). Performance: Cont cruise speed, 122kt (140 m.p.h.) at 8,000ft and14,6001b: corres fuel consumption, 43 gal/hr; take-off field length, ISA, sea level, 1,150ft; ground run to unstick, 520ft; landing distance,ISA, sea level, 1,150ft; range A (max payload), 218 n.m. (250 st.m.); range B (max fuel), 684 n.m. (789 st.m.).
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