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Aviation History
1961
1961 - 1706.PDF
812 FLIGHT, IS November 1961 Commercial Aircraft of the World . . . max height, 6ft 6iin; usable floor area, 529 sq ft; entrance door dimen-sions, 56in x 30in; max seats, 101 at 34in pitch. Fuel capacity: 7,813 Imp gal. Performance: Opt-cost cruising speed, 452kt (520 m.p.h.) at 23.500ftand i35,OO01b, with fuel consumption of ll,5001b/hr; balanced field length, max take-off weight, sea level, ISA, 6,600ft; sea level, ISA- 15C, 7,450ft: at 5.000ft. ISA, 9,300ft landing field length, max landing weight, sea level, ISA, 6,600ft; range A (91-seat tourist), 2,910n.m. (3,350 st.m.); range B (max fuel), 3.240 n.m. (3,730 st.m.J at 405kt (465 m.p.h.) with 17,1311b; cruise M.74; VNE. 335kt (409 m.p.h.)TAS; VNO. 32Okt (368 m.p.h.) IAS; Vso. 95kt (109 m.p.h.) EAS at 115,0001b. D.H.106 Comet 4C The Comet 4C is the intermediate-range versionof the Comet family. It combines the 4B's longer fuselage with the Comet 4"s wing and fuel tankage; this enables it to carry more payloadthan the Mk 4 at a slight sacrifice in maximum range. Three have been ordered by Mexicana, seven by United Arab Airlines, and four byMEA. RAF Transport Command is to have five. Powerplant: Four Rolls-Royce Avon 524 RA.29/1 turbojets of10,5001b static thrust each. Dimensions: As Comet 4, except length, 118ft.Weights: As Comet 4, except weight less fuel and payload (72-seat first-class). 77,5001b.Payload accommodation: As Comet 4B. Fuel capacity: As Comet 4.Performance: Opt-cost cruising speed. 457kt (525 m.p.h.) at 33.000ft and 135.0001b with fuel consumption of 8,800lb/hr; balanced fieldlength, max take-off weight, sea level. ISA, 6.350ft; sea level. ISA - 15 C. 7.100ft; 5.000ft. ISA. 8,750ft; landing field length, maxlanding weight, sea level, ISA, 6,570ft; range A (max payload), 3,075 n.m. (3,560 st.m.) (91-seat tourist); range B (max fuel). 3.745 n.m.(11,4451b); cruise M.74; VNE, 3O5kt (351 m.p.h.) IAS; VNO. 275ki (317 m.p.h.) IAS; Vso, 99kt (114 m.p.h.) IAS at 115,0001b. D.H.114 Heron 1 and 2 Essentially a scaled-up. four-engined versionof the Dove, the Heron was designed to bring "mainliner" standards to feeder-line routes. The Heron 1 prototype first flew on May 10. 1950.Initial production was of the Mk 1. which featured a fixed nosewheel undercarriage and non-feathering propellers. This version was super-seded in production by the Heron 2. which has a retractable under- carriage and feathering propellers. About 150 Herons have been built, ofwhich over 80 are in airline service. More are used by air forces, executive owners and by the Queen's Flight. Price new is about £60,000 less radio.Particulars below refer to the Heron 2. Powerplant: Four D.H. Gipsy Queen 30 Mk 2s of 250 b.h.p. eachdriving de Havilland Hydromatic 2/1000/2 7ft propellers. Dimensions: Span. 71ft 6in, length. 48ft 6in; height. 15ft 7in; wingarea, 499 sq ft. Weights: Max take-off, 13,5001b; landing, 13,1501b; zero fuel.12,670 Ib; capacity payload. 3.7501b; weight less fuel and payload, 8.9961b (including two crew). Payload accommodation: Cabin volume. 515 cu ft; baggage and freightvolume. 127 cu ft: cabin length, 23ft; max width, 4ft 6in; max height, 5ft 9in; usable floor area. 89 sq ft; dimensions of largest door, 51 in ••.'33.5in: max seats. 17. Fuel capacity: 412 Imp gal (495 US gal). Performance: Cruising speed. 159kt (183 m.p.h.) at 8,000ft and13,0001b; balanced field length, 3.570ft; range B. 1,538 n.m. (1,771 st.m.) at 158kt (183 m.p.h.) with 1,3201b payload. D.H.121 Trident Mk 1 BEA issued a general specification for a"second-generation" jet airliner to the British aircraft industry in July 1956. Not until February 1958. after a long drawn-out political con- DE HAVILLAND COMET 4B reference drawing—see page 800 for key 99 2& FHONT HOLD 223 cu, /; "Flight" operators' 4-!$ 71''
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