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Aviation History
1956
1956 - 0897.PDF
ELECTRA Lockheed L.1U Electro in standard mixed-class form. Drawn at Burbonk in May 19S6. 1 Cloud/collision radar. 2 Pressure bulkheads. 3 Two forged beams carrying nose undercarriage. 4 Twin nosewheel doors. _ . — ., 5 Pressure diaphragm. . . t Cockpit floor. 7 Captain. ,,. 8 First officer. 9 Flight engineer seated at centre console. 10 Supernumerary seat. 11 Direct-vision panel. 12 Vision-in-turn windows. ! 13 Nesa glass windscreens. 14 Control column. 15 Rudder/brake pedals. !< Magnetic compass. 17 Large switch panels in roof. 18 Intercomm. phone. 19 Door, normal opening 2ft, possible 4ft. 20 Hat racks whole length of cabin. 21 Passengers' cool-air and switch panels. 22 Conditioned air to flight deck. 23 Fan. 24 Filter. 25 Heater. 26 Constructional break lines. 27 Sliding plug-type freight door. 28 Passenger-door rails and rollers. 29 Fresh-water tank. 30 N.A.C.A.-type belly intake. 31 Twin air-cycle unit. 32 Condenser/fan unit. 90 911 33 Air from compressors on inboard gearboxes. 34 Central access hatch. 35 Roof ducting, air-conditioning. 36 Conditioned-air riser to 35. 37 Windows 16in x 18in. 38 Wing/fuselage joint, front and rear spars. Tiergency exits.39 E 40 Aileron hydraulic booster unit on rear spar. 41 Pilot-input cables to 40. 42 Brake accumulator. 43 Emergency brake air bottle. 44 Hydraulic pumps. 45 Hydraulic reservoirs, 3,000 Ib/sq in system. 46 Speed-brake panels. 47 Speed-brake screw-jack. 48 Speed-brake hydraulic motor in starboard fillet. 49 Oven. 50 Pressure outflow valves. 51 Inflow valve. 52 Rudder booster unit (port). 53 Elevator booster unit (starboard). 54 Universal joint in elevator tube. 55 Access hatch. 56 Tail electric de-icing, elements to 15-per-cent chord. 57 Tank end-ribs. AIR CONDITIONING BA* LIGHT DECK: CAPTAIN RST OFFICER. FLIGHT ENGINEER SUPERNUMERARY FORWARD RETRACTING NQSEWHEEl -99 V : MAIN PASSENGER •---». : . • . ENTRANCE. WITH AIRSTAIR LOCKHEED L.188 ELECTRA Four Allison 501-D13 turboprops of 3,740 e.h.p. Dimensions: span, 99ft; length, 104ft. 6$ in; overall height, 32ft 11|in; gross wing arei 1,300 sq ft; track, 31ft 2in; inside diameter of fuselage, 128in. Weights: full figures not available, but maximum weight is 113,000 Ib and max. landing weight 95,650 Ib. The following is a breakdown of the weights as at April 1956: empty, 54,000 Ib (55,000 international); operating weight, 57,272 Ib (59,408 int.); payload, 18,000 Ib (66 passengers and 7,110 Ib freight and baggage); 2 hr reserve fuel 7,080 I b (7,220 int.); landing ^eight, 82,352 Ib (84,630 int.); design gross weight, 110,000 Ib; design landing weight, Performance (estimated); not available, except the following: C.A.R. field lengths, 4,950ft (take-off) and 5,040ft (landing) for 1,500-n.m. stage, 5,740 and 5,040ft for 2,000 n.m. and 5,800 and 4,880ft for 2,500 n.m.; 5,000ft runways will be adequate for operations on 1,850-st.m. stages with full payload against a 50-m.p.h. headwind; max. range with 66 passengers and 2± hr reserve fuel is 2,800 st.m.; normal operational climb at "normal take-off weight" at sea level is 2,400ft/min; twin-engine ceiling is 15,000ft. In April the cruising speed curve fell from 410 m.p.h. at very short stage-lengths to 400 m.p.h. at 2,500 st.m.; design limits were then: VD, 405 kt e.a.s. below 8,000ft and Vc, 324 kt e.a.s. below 12,000ft and Mach 0.615 above. AIRSCREW TIPS 40in FROM FUSELAGE ALLISON S10-D13 CONSTANT. SPEED TURBOPROPS WITH REMOTE REDUCTION GEARBOX 1,740 e.h.p. (3.460 s.h.p.) AJROPRODUCTS AIRSCREWS 13ft6indio CARRY-ON LUGGAGE RACKS FLIGHT STATION / MAIN CABIN DOOR \ COAT SPACE \ / EMERGENCY EXITS / EMERGENCY & SERVICE EXIT GALLEY LOUNGE
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