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Aviation History
1964
1964 - 1642.PDF
FLIGHT International, 28 May 1964 899 Working in close collaboration with the design engineers at Belfast, our artist has depicted a typical basic production Turbo-Skyvan. Though it is of highly unorthodox aerodynamic proportions, only minor refinements have been proved necessary as a result of the development flying to date with the prototype; most of the alterations that will be incorporated in production aircraft have been to lighten and simplify the structure Powerplant Two Turbomeca Astizou X turboprop: each rated at 632 s.h.p.; 8ft 2.4in dia Racier Figeac FH76 propellers, fully feathering and reversible with electric operation. Dimensions Span, 64ft lin; length, 39ft lOin; height, 15ft; wheelbase, 15ft 4in; track, 13ft 8in; height of floor and ramp sill for loading, 2ft 6in; unobstructed cabin height, 6ft 6in; minimum cabin width, 6ft 2in; cabin floor length, 16ft; wing area, 373 sq ft. Weights Max take-off, 12,5001b; max landing, 12,5001b; APS (freight version), 7,7001b; zero fuel, ll,700lb; max payload, 4,0001b; max fuel, 1,4501b. Performance Take-off field length to 50ft, 2,020ft (ISA, sea level, gross weight); max continuous cruise, 205-211 m.p.h. t.a.s. (sea level to 20,000ft); 75 per cent max continuous cruise, approx 185 m.p.h. t.a.s. at all altitudes; landing distance from 50ft, 2,670ft (ISA, sea level, 12,0001b); Vc, 197 m.p.h. e.a.s.; Vne, 241 m.p.h. e.a.s. 1 Pierced light-alloy frames and ribs 2 Non-buckling light-alloy skin 3 Inner (corrugated) skins Reduxed to outers 4 Inner skins unbroken, root to tip 5 Overhead escape hatch 6 External buttstraps 7 Direct-vision window 8 Raised flight-deck 9 Electro-Hydraulics nose 10 Electro-Hydraulics power pack 11 Folding steps to doors and emer- gency hatch 12 Spar carry-through above top skin 13 Single-pin spar root fittings 14 Freight lashing points 15 Access doors to 14, four each side 16 Main rear-hinged loading door 17 Operating winch for 16 18 Box-section beams by door cut-out 19 60.5 x 20in door each side 20 Wing bracing strut 21 Main-gear beams 22 Strut anchorage on wing sub-spar 23 Main gear fulcrum 24 NACA 63A-4I4 section 25 16.5in by I2in windows (some I2in by I2in) 26 Rubber door-sealer strip 27 Compression strut 28 Co-pilot seat (pilot's removed) 29 Downward-vision windows 30 Pitot head 31 Fresh air to fuselage 32 Outside-air-temperature probe 33 E2B compass 34 Inspection panels C Flying Controls Cl Floor-mounted control wheels C2 Ducts for flying controls Power, pitch and trim controls Aileron and flap push-rods Geared tabs Aileron hinges Three-piece elevator Horn-balanced rudders Hydraulic flap-jack with flap- balance linkage CIO Aileron-droop mechanism Cl I Flap hinge and operating brackets F Fuel Fl 175 Imp gal in four bag-tanks F2 Fillers F3 Collector tank and feed valves F4 Fuel pipes to F3 FS Tank interconnectors P Powerplant PI Astazou X turboprop, 8ft 2±in-dia propeller, 2,065 r.p.m. Power governed by pitch; reverse pitch for braking Solid aluminium-alloy blades Engine air intake Airflow through oil cooler Simple tubular engine-mountings Jetpipe Fuel and feathering controls PI0 Oil tank integral with reduction- gear casing PI I Generator/starter unit PI2 Auto-feathering pitots R Radio and Electronics Rl Radio equipment below cockpit R2 Radio controls on overhead panel R3 Collins VHF aerial R4 VOR aerial RS Anti-coflision beacon R6 Landing lamps for strut fairings R7 Two Varley l7A-hr lead/acid batteries under floor R8 Belly-mounted aerials: marker beacon, APF loop, ADF seme; glide-slope below nose R9 HF aerial on fin (optional) W Weather Equipment Wl Goodrich leading-edge de-icer boots (optional) W2 Electrically de-iced propellers W3 Windscreen de-icing fluid tank W4 Windscreen wipers and spray nozzles W5 De-icing not required on strut and u/c platform W6 Icing inspection light A.
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