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Aviation History
1957
1957 - 1587.PDF
1 November 1957 1 Warm air to cockpit 2 Single static vent to safety devices3 Pi tot head 4 Windscreen de-icing fluid pressure connection 5 Nesa glass heated windscreens 6 Triple windscreen wipers and alcohol spray-bars 7 Direct-vision panels 8 Cockpit pressure dome 9 Unpressurized fairing 10 Windscreen de-icing fluid tank 11 Icing inspection lamp II V.H.F. (No. 1) oeriol 13 V.H.F. (No. 2) aerial 14 Nosewheel steering wheel 15 Aerotherrn pilots' seats 16 Rudder-pedal units with toe-brakes 17 Bendix PB.10A autopilot motor group 18 Main radio crate (remainder in underfloor freight hold) 19 Cockpit door 20 Nosewheel steering cylinders 21 Towing point (scissor-link released) 22 Crew fixed oxygen 23 Hydraulic cupboard 24 Non-flushing-type toilets 25 Ship's library 26 Public address (Bendix) 27 Duplicated A.D.F. aerials (Marconi 7092C) 675 53 Firewall and fire access panels 54 Fire-suppression bottle; three spray rings m nacelle 55 Rotol accessory gearbox on each engine driving Godfrey cabin blowers (three only), generators, hydraulic pumps and airscrew de- icing alternators FREIGHT COMPARTMENT, ALTERNATIVELY LOUNGE WITH REAR WINDOWS EMERGENCY EXITS, 7 WINDOWS. 4 STARBOARD SIDE AND 3 PORT SIDE REAR LUGGAGE BAY PRESSURE BULKHEAD MOVED BACK 65m AIR-CONDITIONING BAT GALLEY AND REAR ENTRANCE VESTIBULE STRENGTHENED REAR FUSELAGE AND TAIL STRENGTHENED WING STRUCTURE TO ALLOW FOR OPERATION AT 67.5001b OCCASIONAL SEAT FOR TWO FLIGHT ATTENDANTS WATER-METHANOL TANK BAY 55 Imp gol EACH SIDE DOUBLE-SLOTTED FLAPS STRENGTHENED UNDERCARRIAGE AND BRAKES WITH HIGHER ENERGY ABSORPTION Payload-range performance (upper) and operating costs for the Viscount 810/840. Payload-range is for I.S.A. con- ditions and max. payloads (including catering and four crew) limited by zero fuel weight, and includes reserves for taxying, take-off and landing; 45 min. holding at 5,000ft, and 230 st.m. diversion. The cost curves are cal- culated to the Lockheed method, slightly modified to suit the British aircraft. 14 13 \ V.BAX CV 81O \ V8K> V84O V.. " \ \ — \ \ 28 Ice-guard 19 Passengers' service panel under light luggage rack 30 Sliding curtains (no sunblinds) 31 Chair-back tables 32 Emergency exit external release 33 Flap motor and gearbox 34 Flop torque tube and driving chains 35 Flap guide rails and radius arms 36 Aileron control pressure-seal 37 Aileron control run 38 Intercooler airflow (flush intake) 39 Conditioned-air duct 40 Galley equipment 41 Baggage bay door 42 Double-skinned leading edge of wing, fin and tailplane 43 De-icing air outlets 44 H.F./Loran aerial (for ferry only) 45 V.O.R. and I.L.S. localizer aerials 46 "Pounder"-type anti-collision bea- con 47 Static dischargers 48 Navigation lights 49 Tank-bay linings perforated for rubber retaining studs.50 Bag-type fuel tanks 51 Airflow through oil cooler 52 Electric de-icing pads 56 Cabin blower delivery duct (intake on nacelle inner flank) 57 Main engine mounting point 58 Vickers 14in-stroke undercarriage. Dunlop tyres, wheels, steel-disc brakes with Maxaret59 Retraction jack 60 Retraction bay and door linkage 61 Jet-pipes 62 Tank-access panels 63 Pacitor gauge covers 64 Float-switch covers 65 Gravity-filling points (pressure re- fuelling below wing) 66 Landing lamp 67 Access to outer-plane attachment bolts 68 Irving-balanced split ailerons, skew- bar operated 69 Nine ribs only in each wing, plus light chordwise members 70 Outer cowling petal with hinged top section; inner carries lower cowling 71 Trim tabs 72 Balance tab 73 Anti-balance tab 74 Spring/servo tab 75 Servo/trim tab 16 10 CD it! 2OO 400 OOO TOO 1,000 RANGE (st.miles) 1-4 12 1.2OO V4OO take the even higher power offered by the R.Da.ll Dart engines (Mark 541). The power offered by this 2,350 e.h.p. Dart develop- ment can thus be utilized by the basic 810 airframe, which is then designated 840. This is the true 400 m.p.h. Viscount. AIRFRAME The Viscount 810/840 airframe differs from previous models in the general strengthening made to increase the structural I.A.S. limit by about 50 m.p.h. In general, these changes are: (1) strengthened nacelles; (2) strengthened wing rib and spar structure and heavier gauge skin in the inner wings; (3) strengthened undercarriage and higher-energy-absorption brakes; (4) reinforced rear fuselage to withstand higher tail loads; (5) stronger tail; (6) horn-balanced rudder for more powerful control. Fuselage Open channel frames are notched to receive angle stringers to which the skin is flush riveted. The complete fuse-
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