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Aviation History
1956
1956 - 0893.PDF
6 July 1956 DOUBLE-TIER BAGGAGE COMPARTMENT WATER/METHANOL BAG TANK 32 Imp gal ACCESS PANEL TO ENGINE- DRIVEN ACCESSORIES DOUBLE SLOTTED FLAP INTEGRAL FUEL TANK 565 Imp gal EACH SIDE LONG-RANGE FUEL BAG TANKS 75 Imp gal EACH SIDE 3ING EDGE ACHABLE FOR 1ESS TO FUEL- IK MANHOLES tensile stresses in the regions of cut-outs and discontinuities, and alldouble cabin window assemblies are clamped in position to allow differential movement between the transparency and the surroundingstructure. The entire bottom wing surface tensile material is free from cut-outs.Only single heat-treated L72 and L64 is used, and the stress level under ultimate loads has been kept low consistent with latest available S/Ncurves for well designed joints to ensure long life. Appropriate chord- wise joints are designed so that the end load-carrying joint-plates are CO-PILOT & NAVIGATOR RADIO STOWAGE GALLEY broken chordwise every few inches to isolate cracking, should it occur,and also to facilitate individual inspection. Where loads are carried through concentrated pins, these are madean interference fit by the use of split-tapered bushes to prevent fretting. All bearing stresses have been deliberately kept low for the samereasons. The fuselage structure, pressurized to 5.50 Ib/sq in (8,000ft at25,000ft), is constructed as two separate components, the front fuselage housing crew, radio, electrical panels and so forth, and the rear maincabin housing the payload. The wing box structure is comprised of five separate sections, thecentre-section incorporating the engine installations, two semi-integral tanks each of 5b5 Imp gal capacity, and the outer wings with provisionin each for an additional 75 Imp gal. An extensive static and fatigue-test programme has been agreed withthe A.R.B., and the second fuselage and centre-section wing will be subjected to combined pressure cycles and tail-unit gust loads represent-ing a typical flight pattern in the R.A.E. water tank. This will be followed by a combined pressure and lateral gust high proof-test in thetank, and later the usual static ground tests will be carried out in the company's test frame. The second wing will be subjected initially to a combined repeatflight-load and integral fuel tank pressure-test to check tank sealing under load, to be followed by static tests. Critical wing joint specimenswill also be subjected to fatigue tests. The tricycle undercarriage is manufactured by Dowty Equipment,and takes the form of short sturdy units free from the effects of dynamic springback. Twin wheels and low-pressure tubeless tyres are fittedto both the main and nose legs. The undercarriage is hydraulically actuated, the down-locks of both the main and nose gear being of theinternal type; when the undercarriage is extended, the jacks act aB drag struts. The up-locks are external. POWERPLANT. The Rolls-Royce Dart RDa.6 Mark 512 engineseach give 1,730 e.h.p. for take-off. As indicated under the Weights and Performance table, this may be increased on production aircraft. Four-bladed 10ft airscrews are fitted, of either Rotol or de Havillandmanufacture, and a synchronization system is available. In the main, the installation is basically similar to that of the Viscount and everyendeavour has been made to maintain a high interchangeability standard between aircraft. Fire precautions, fire access and blow-out panels,ventilation of zones, control runs, shrouds, jet pipe and cowling design have all been developed with the assistance of Rolls-Royce. To provide maximum access for servicing, petal-type cowlings arefitted. By releasing a minimum number of toggle fasteners, the cowling can be opened up completely back to the fireproof bulkhead at the rearof Zone 2. The accessory gearbox driving the alternator, generator, cabin supercharger, hydraulic pump and tacho-generator is readilyaccessible by removing the access panel on the top of the nacelle in Zone 3. Access to the de-icing heat exchanger and jet pipe in Zone 3is achieved by removing the rear nacelle fairing, which is attached by quick-release fasteners. When this is removed, the complete jet pipeand heat exchanger installation is exposed for service and maintenance or removal. Engine controls are of the push-pull type; all control rods are adjust-able for length with indexed lever positions, and provide a rigid control system free from lost movement.An investigation into the effect on performances of fitting RDa.7 Typical layout for a DOOR TO long-range executive TOILET BAGGAGE HOLD Accountant providing for UILL up to eight berths. CAPTAIN CREW CLOAKS BAGGAGE CREW & PASSENGER ENTRANCE
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