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Aviation History
1961
1961 - 1722.PDF
Commercial Aircraft of the World . . . floor area (less flight deck), 169 sq ft; dimensions of largest door,68in 45in; max number of seats, 23 at 30in pitch. Fuel capacity: 459 Imp gal.Performance: Opt-cost (i.e., typical) cruising speed at 10,000ft and 21,3801b. 205kt: corres s.f.c, 0.68Ib/hr/s.h.p.; take-off field length.max take-off weight, ISA, 3,900ft; landing field length, max landing weight, ISA. 3.715ft; range A (max payload), 300 n.m.; range B (maxfuel), 1,050 n.m.; corres payload, 5,500 Ib; VNE. 242kt IAS; VNO. 208kt IAS; Vso, at max landing weight, full flaps, 65kt IAS. MH-262 Super Broussard This is the pressurized version of theMH-260, the prototype of which is said to be due to fly before the year's end. Last June it was expected that the first aircraft would flyin mid-1962 and be certificated and delivered in July 1963. Basic cost would be about £120,000. MH-280 Super Broussard This is the designation of the MH-260 or MH-262 with Lycoming T53s of similar power to that of the Bastan. MH-350 Broussard Major Resembling in appearance a scaled-downSuper Broussard. this is a twin-engined "big brother'" of the successful single-engined Broussard. of which some 400 have now been built. The first prototype is being built at Rheims and is due to fly in March 1962. Powerplant: Two Continental GIO-470A piston engines of 310 h.p. each. Dimensions: Span, 50ft; length, 35ft; wing area. 301 sq ft. Weights: Max take-off (freight version). 6,9501b; weight empty. 4,3801b; capacity payload, 2.0001b.Performance: Max cruising speed, 159 m.p.h.; take-off distance, max weight, to 50ft, 1,530ft; landing distance, over 50ft, 985ft; range A(max payload, with allowances). 100 n.m.; range B (max fuel, with allowances), 350 n.m.; corres payload. 1,5001b. NAMC Ninon Aeroplane Manufacturing Co Ltd, Daido Building, No 46, l-chome, Minami-Sakumacho, Shiba, Minato-ku, Tokyo, Japan. YS-11 The manufacture of the YS-11 turboprop airliner was firstproposed by the Japanese Ministry of International Trade and Industry in 1956. The major aircraft manufacturers set to work on projectstudies, and in the following year, with a government subsidy, the six largest aircraft manufacturing companies combined forces to launch thebasic design work. These six companies were: Mitsubishi Heavy- Industries. Reorganized Ltd; Kawasaki Aircraft Co Ltd; Fuji Heavy-Industries Ltd; Shin Meiwa Industry Co Ltd; Japan Aircraft Manu- facturing Co Ltd; and Showa Aircraft Industry Co Ltd. In May 1957 these companies formed the Transport Aircraft Develop-ment Association, with the object of co-ordinating their efforts in design work, preparation of specifications, wind tunnel tests and constructionof a full-size mockup. In June 1959. the Ninon Aeroplane Manufactur- ing Co was established under the Aircraft Industries Promotion Lawwith capital jointly provided by the Government and the private com- panies concerned to succeed the Transport Aircraft DevelopmentAssociation and to be responsible for the production and sales of the YS-11. The board of directors is composed of representatives of theGovernment and of the "big three"—Mitsubishi, Fuji and Kawasaki. The paid up capital of the company was 3.750 million yen (about£3.75m) in October 1961. of which 2",050 million yen (£2".05m) was subscribed by the Government and 1.700 million yen (£1.7m) by theprivate companies. The capital is to be raised to reach a total of 4,700 million yen (£4.7m) in 1962. Production of the YS-11 is carriedout with the close co-operation of the six companies, as follows:— NAMC are responsible for design, production, quality controland sale of the YS-11. Others concerned are: Mitsubishi, fuselage and final assembly; Kawasaki, wings and engine nacelles: Fuji, tail unit:Shin Meiwa, rear fuselage: Japan Aircraft, ailerons and flaps; Showa Aircraft, honeycomb structural components. The aircraft is powered by the most-developed Rolls-Royce Dart(RDa.10/1) engines, and the fuselage accommodates 52-60 passengers. The company estimate a demand for more than 150 aircraft between1963-70 for domestic routes and export. The Japan Self-Defence Agency included 10 YS-11 Ms (military version of the YS-11) in itsfive-year defence programme commencing fiscal year 1962, and All Nippon Airways announced their intention to purchase more than 25YS-lls. Japan Maritime Safety Agency may also have two YS-lls for search and rescue. The first prototype YS-11 is due to fly in the middle of March 1962,and the first production aircraft is scheduled to go into operation on Japanese domestic routes during the second half of 1963. Basic price: 360 million yen (£360,000) approximately, excludingradio, autopilot, radar, etc. Powerplant: Two Rolls-Royce Dart RDa.10/1 Mk 542 turbopropsof 3,060 e.h.p. driving Dowty Rotol 14ft 6in propellers. Dimensions: Span, 105ft; length, 86ft 3in; height empty, 30ft; wingarea, 1,020 sq ft. Weights: Max take-off, 50,2651b; max landing, 48,0471b; zero fuel, 44 0921b; capacity payload, 12,1301b; weight less fuel and payload, 31,'9881b. Pavload accommodation: Cabin volume, 2,125 cu ft; baggage and freight volume, 390 cu ft; cabin length, 44ft lin; max internal width, 828 FLIGHT, 23 November 1961 Artist's impression of the Piaggio-Douglas PD-808 light jet transport 8ft lOin; max height, 6ft 6 in; max usable floor area, 340 sq ft; dimen-sions of largest doors, 33in by 66in; max seats, 60 at 34in pitch. Fuel capacity: 1,560 Imp gal (1,870 US gal).Water-methanol capacity: 106 Imp gal (127 US gal). Performance: Opt-cost (i.e., typical) cruising speed at 20,000ft and48.0471b. 257kt; corres s.f.c, O.633lb/s.h.p./hr; take-off field length ISA, SL, max take-off weight, 2,890ft; landing field length, SL, 3,790ftrange A (max payload), 710 n.m.; range B (max fuel), 1,680 n.m., corres payload, 5.4001b; VNE, 275kt EAS below 13,000ft, 245kt EASbelow 13.000ft; Vso 72kt EAS. Operators' drawing of YS-11: page 823 NORD AVIATION Societe Nationale de Constructions Aeronau-tiques du Nord, 12 bis A venue Bosquet, Paris 7e. France. Nord 2502 Noratlas The Nord 2502 is a development of the Nord2500 transport designed for the French Air Force, which was the basis for a series of variations. The prototype 2500, the 2501 powered by twoBristol Siddeley Hercules 758s of 2,040 b.h.p. each, first flew on Septem- ber 10, 1949. By 1951 a civil 45-seater (or cargo) version ofthe.2501 hadalso been designed and orders placed by UAT and by an operator in Israel. The 2502 differs from its predecessor in that it is equipped with twoTurbomeca Mabores in wing-tip nacelles to improve take-off perform- ance. UAT, who operate six 2052s, introduced the type into service ontheir African routes in 1954. Other operators are Arkia (two) and Air Algerie (two). Other developments, not in quantity production, are: Nord 2503(Pratt & Whitney R-2800-CB17s); Nord 2506 (as 2502 but with air- brakes, re-designed flaps and landing gear adjustable for height, nowcancelled) and Nord 2508 (as 2501 but with Pratt & Whitney" R-2800- CB17s of 2,500 h.p. and two-stage supercharging). Powerplant: Two (Bristol Siddeley Hercules 758/759 of 2,040 b.h.p.each, built under licence by SNECMA, driving Rotol R. 108 propellers. (Optional: two 8801b. Turbomeca Mabore turbojets.) Dimensions: Span, 110ft 3in; length. 72ft 0|in; height, empty.19ft 10*in; wing area, 1.089 sq ft. Weights: Max take-off. 5O.7OOlb; max landing, 48.5001b; zero fuel.46,7201b; capacity payload, 16.6401b; weight less fuel and payload, 30.0801b. Payload accommodation: Cabin, baggage or freight volume, 1.800 cu ft:cabin length, 32ft 4iin; max width, 9ft; max height, 6ft 7in; max usable floor area, 233.6 sq ft; dimensions of largest door, 7ft 2Jin; maxnumber of seats, 45. Fuel capacity: 1,120 Imp gal (1,345 US gal). Performance: Cont cruising speed, 170kt (195 m.p.h.) at 9,840ft and50.0001b; corres fuel consumption, 0.244 st.m./lb; balanced field length, sea level, ISA, 2,085ft; at sea level, ISA - 15 C. 2.340ft; at 5.000ft,ISA, 2,565ft; landing distance from 50ft. 2.625ft; range A (max payload). 686 n.m. (790 st.m.); range B (max fuel), 1,480 n.m. (1,710 st.m.) correspayload. 12.7101b; corres cruise speed, 161kt (186 m.p.h.). Transall C.160 Planned as a first co-operative venture between theFrench and German industries (although Nord 2501s have been built in Germany in quantity) is the Rolls-Royce Tyne-powered C.160.Primarily a military freighter for NATO, the C.160 is also offered for commercial use. Participants, grouped under the name Transall. areNord Aviation for France, and Hamburger Flugzeugbau. Weser Flugzeugbau and Blume-Leichtbau und Flugtechnik for Germany.The project is a freighter with rear ramp-loading and an undercarriage retracting into twin pods on the fuselage. Agreement was reached inMarch 1960 to build three prototypes plus two further airframes for static and fatigue testing. The first three prototypes will be built by Nordin France and first flight was originally scheduled for July 1962. The second and third aircraft should fly respectively six and eight monthslater. Basic price is stated to be about £650.000. Powerplant: Two Rolls-Royce Tyne RTy.20 turboprops of 6,100e.h.p. driving de Havilland 18ft propellers, and two RB.I53 booster jets. Dimensions: 131ft 3in; length, 103ft 6in; height empty. 36ft 7in; wingarea, 1,722.23 sq ft. Weights: Max take-off, 106,9251b; max landing, 100.9701b; zero fuel,90.0571b; capacity payload, 33.0691b. Pavload accommodation: Cabin volume, 4,800 cu ft; cabin length,42ft 8in; max internal width, 10ft 4in; max height. 9ft 9in; max usable floor area, 602.8 sq ft: dimensions of largest door, 7O.8in . 78.7in;max seats, 80. Performance: Opt-cost (i.e.. typical) cruising speed, 275kt at 25,000ft;corres fuel consumption, 0.087 n.m./Ib; take-off distance, 1,970ft; landing distance. 1,970ft; range B (max fuel), 2,430 n.m. with fuel allowances. PEKING AERONAUTICAL INSTITUTE Peking, ChinesePeople's Republic. Peking NR.1 First flown on September 4, 1958, the Peking NR.l isbelieved to be the first aeroplane designed and built in Communist China. It appears to be similar in purpose to the Dove; it carries eight pas-sengers on rather more power—two 520 h.p. piston engines. A general arrangement drawing appeared in Flight of April 24. 1959, page 587.Span is approximately 57ft lOin and length 42ft 7in. Cruising speed is given as 162kt (186 m.p.h.) and range as 665 n.m. (670 st.m.). Cruisingheight is quoted as 15.750ft. PIAGGIO Via Antonio Cecchi 6, Genova, Italy. Piaggio P.I66 The first of three prototypes of the Piaggio P. 166 flewon November 26, 1957, and production deliveries started at the end of April 1959. About 20 aeroplanes have now been delivered and 21 are tobe supplied as executive VIP transports to the Aeronautica Militare.
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