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Aviation History
1958
1958-1- - 0140.PDF
142 FLIGHT ling through four underwing sockets can be accomplished in 16 minutes. Flying Controls Fully powered systems (and artificial feel) areused on ailerons and rudder and to vary the incidence of the tailplane, but the elevators are servo-tab operated. Only the innersections of the ailerons are powered, the outer being torsion bar coupled so that they lose effectiveness as speed increases. Poweredcontrols on both ailerons and rudder have provision for manual reversion in the event of hydraulic pressure failure, and the pilot'sloads are said to be not excessively high. The control system also incorporates spoilers along the wing; but these are not operatedin flight and are intended only to increase the loading of the nosewheel during landing. Flaps are double-slotted, of Douglas design similar to thoseemployed on the DC-7C. They are not completely continuous, as a portion in way of the inner engines trails horizontally as thesections arc lowered. Early aircraft will have two rectangular airbrakes under the belly but these will be discontinued. Air Conditioning The cabin is pressurized to the high level of 8.77 lb/sq in (6,700ft at 40,000ft altitude) by air from ram intakes DC-8 . . . ENGINEER'S STATION 1 Weather radar dielectric radome 2 Intake to cabin air system 3 Cabin-air turbo-compressors (55,000 r.p.m.) 4 Turbine exhaust 5 Heat exchanger exhaust 6 Access door 7 Electrically-heated multi-layer glass screen (no wipers) 8 Upper windows each side 9 Forward pressure bulkhead 10 Supernumerary seat 11 Engineers' panel 12 Radio racks (air cooled) 13 Coatj 14 Pre-closing nosewheel-bay doors 15 DO7 type nose gear geometry AIR CONDITIONING BAY DOUGLAS DC-8 Dimansion! (all versions): Span, 139ft 9in: length, 150ft 6in; overall height, 42ft 4in; wing area,2,758 sq ft; sweepback at ± chord, 30 deg; volume of both lower cargo compartments, 1,390 cu ft. Weights: Gross weight (Ib) Max. usable T.O. weight (Ib) Landing weight (Ib) Operating weight empty(Ib) ... Zero fuel weight (Ib) Freight (Ib) Space limited capacity pay- load (Ib) first-classSpacelimited capacity pay- load (Ib) mixed-class ...Spacelimited capacity pay- load (Ib) tourist Level flight speed max. cruise T.A.S. (m.p.h.)30,OOOft at 220,0001b ... C.A.A. T.O. field length (ft) max. T.O. weight ... C.A.A. landing field length(ft) max. landing weight Range with 6,500ft T.O.field length, first-class version (st. m.) Range with 6,500ft T.O. field length, mixed-class version (st. m.) Range with 6,500ft T.O. field length, tourist ver- sion (st. m.) Range, first-class (st. m.)... Range, mixed-class (st. m.) Range, tourist-class (st. m.) Domestic JT3C-6 265,000 265,000 189,000 122,698 161,200 13,900 33,040 37,165 561 9,170 6,680 2,340 2,040 3,900 3,600 Domestic JT4A-3 265.000 265,000 189,000 124,977 164,550 13,900 33,040 37,165 589 7,320 6,630 3,710 3,420 4,100 3,800 Interconti- nental JT4A-3 287,500 287.500 194,000 130,092 170,550 13,900 35.680 37,165 589 8,430 6,850 3,240 3.140 4,5004,390 Interconti- nental Conway 287,500 287,500 194,000 128,082 168,650 13,900 35,680 37,165 591 8,470 6,850 3,380 3,280 4,6804,580 Interconti- nental JT4A-9 310,000 310,000 199,500 132.310 176,500 13,900 35,680 37,165 588 9,220 7,100 5,0304,930 Interconti- nental Conway 310,000 310.000 199,500 130,164 174,600 13,900 35,680 37,165 590 9,050 7,100 5,2005,100 Allowances include noise suppressor, pre- and post-flight fuel, climb, descent, 300 miles reserve and one hr hold at 1.1 Vmd at 15,000ft. 16 Steering cylinders (10 deg each way with rudder, 78 deg by hand- wheel) 17 Retraction jack 18 Galley service door 19 Underfloor hold (door starboard) 20 Wall-fixed slots 21 Attendant's seat 22 Centre-joint butt-strap 23 Centre section tank ("overwater" model only) 24 Centre keel-member (5ft deep) 25 Mainwheel doors (normally closed after undercarriage extension) 26 Windows (18±x15in) 27 Cabin air in: out at floor level 28 Passenger-address speaker 29 Hat racks 30 Emergency exits 31 Emergency doors 32 "Hot wall" panelling 33 Inward-opening freight door 34 Concealed lighting 35 Integral three-spar fin 36 Sloping frames 37 Fibreglass (dielectric) structural isolation 38 Bonded inner skin 39 V.O.R. aerial 40 H.F. aerials (1 and 2) 41 Tailplane screw-jacks 42 Tailplane hydraulic and electric motors 43 Tail de-icing trunk 44 Retractable bumper 45 Integrally-stiffened skin 46 Fully-powered rudder 47 Manual elevators 48 Fuel system runs 49 De-icing duct (cyclic heat) 50 De-icing trunk
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