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Aviation History
1981
1981 - 1240.PDF
A Trim tab + 30° -15° +M/ Rudder / ' /\i 30° ^^^ZJ Trim ±2 —<-~"f Air brakes ® </S L 50° Lift spoiler '(Flaps up) \ 30° Spoiler ' IFlapsup) Aileron t20° 20 Flaps (Landing) Servo tab Aileron down -6° A Servo tab ±18° Key 1 Upward-hingeing dielectric nose- cone housing RCA weather radar and glideslope aerial 2 Access to forward avionics bay 3 VOR/localiser antenna (both sides) 4 Forward pressure-bulkhead 5 Forward-retracting nosewheel, steering through ± 70° by means of the captain's hand wheel (reduced angle through the rudder pedals and copilot steering optional) 6 Two-crew flightdeck with fully adjustable Teleflex seats (third seat optional) 7 Windscreen wipers and electric ally de-iced and demisted wind screen panels (rear windows open inward for emergency exit) 8 Overhead control panel 9 Glareshield housing autopilot and flight director 10 Centre console housing Com, Nav and engine controls 11 Main avionics and electrics bay (housing one or two 28V Nicad batteries) 12 Stringerless nose with integrally machined frames 13 Abutment-type passenger doors with emergency escape chutes (folding airstairs standard at front, optional at rear) 14 Toilets 15 Galley 16 Cabin attendant's folding seat 17 Chemically etched one-piece fuse lage side panels with separate window-frame reinforcement 18 Inverted V stringers Redux- bonded to fuselage skins. Fuselage frames are a triple-element, fail safe design, and there are no stringer/frame cleats 19 Aluminium alloy honeycomb floor- panels supported on transverse floor beams 20 Forward cargo hold (abutment type door 53in x 43in) 21 Rear cargo hold (abutment type door 36in x 41 in. Front and rear cargo volume 660ft^) 22 Five and six-abreast seating (100 seats ?t 33in pitch, or 109 seats at 29in pitch) 23 Fully insulated cabin side-walls 24 Overhead storage bins 25 Cabin service and emergency doors (front and rear) 26 Rear pressure dome incorporating seals 27 Two-spar fin torsion box, stringers bonded to skin 28 Garrett AiResearch GTCP36-I00 auxiliary power unit housed in titanium fireproof compartment 29 Bifurcated ram-air intake to left and right air conditioners 30 Access door to Normalair-Garrett environmental control system (in corporates tail bumper) 31 Variable airbrake operated by hydraulic jack 32 Duplex hydraulically powered rudder 33 Continuous two-spar fixed tail- plane with manually operated elevator (servo tab + Q-feel) 34 Bleed-air de-iced leading edges (all surfaces except fin) 35 Pipes carrying bleed-air to en vironmental control system and fuel to auxiliary power unit 36 Back-to-back, machined fuselage frames (two of the three in corporate undercarriage pivots) 37 Wing box/fuselage attachment links (two each side) 38 One-piece, integrally machined wing spars with crack retarding stiffener 39 One-piece, integrally machined „ ribs 40 Single-piece upper and lower skins for each wing (thickness- tapered with Redux-bonded stringers) 41 Detachable leading edge 42 Manually operated ailerons (sup plemented by hydraulically powered outboard spoilers) 43 Lift spoilers with automatic operation at touchdown 44 Single, tabbed Fowler flap, extend ing across 80 per cent of span (incorporates slot behind outer spoiler) 45 Flap-drive hydraulic motor 46 Pitch-trim corrector 47 Torque driveshaft and limiters 48 Chain and sprocket drive to flap screwjack and carriage 49 Glassfibre reinforced plastic flap- track fairings 50 Engine pylon front and rear attachment points (built-in sway links on front) 51 Forward engine mounting 52 Rear engine mounting 53 Bleed-air ducts 54 Avco Lycoming ALF502R-3 two- spool turbofan (6,7001b take-off thrust) 55 Fire extinguisher bottles (two in each pod) 56 Engine oil tank and accessories 57 Hydraulic bay housing two in dependent 3,000 p.s.i. systems, including reservoirs and accumu lators 58 Pressurised water tank (20gal, 8 usable) 59 Dowty wide-track, trailing link undercarriage, incorporating multi-disc carbon brakes 60 Retraction and strut-breaker jacks 61 Integral fuel tanks. One in each wing and one in centre-section. Total capacity 2540 Imp gal (3,050 US gal) 62 Single-point pressure refuel/defuel panel (right wing only) 63 Collector tank with twin electric booster-pumps and single hy draulically driven standby 64 Vent box (top hat stringers bonded to upper skin serve as vent pipes) 65 Overwing fillers (one in each wing) 66 Rear wing fuselage fillets may be used as wing tanks (300 Imp gal each) 67 Flying control run to elevator and rudder in fairleads through floor beams 68 Aileron and trim cable run-out through pressure seals in fuselage 69 Wing/fuselage inspection lights 70 Landing lights 71 Cabin air discharge-valve 72 No I VHF Com aerial 73 No I ADF loop aerial (second aerial optional)
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