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Aviation History
1989
1989 - 1927.PDF
62 Ballscrew aclualors (four), may be hand cranked for maintenance 63 Reverser pylon tracks 64 Cascades 65 Sound attenuation air-intake 66 Exhaust nozzle attachment iug (both 67 Engine cowlings and access doors (Kevlar mouldings) 68 Three-spare fin torsion box covered with chemically etched stringer stiffened skin panels 69 Continuous two-spar variable- incidence tailplane 70 Tailplane leading-edge thermal de-icing duct 71 Tailplane, fin ttps (Kevlar mouldings) 72 One-piece rudoer 73 Autopilot rudder servo 74 Yaw dampers (two) trim actuator, and preload Spring 75 Input bellcrank to triple hydraulic actuators 76 Autopilot elevator servo 77 Artificial feel unit (two) 78 Horizontal stabiliser actuator 79 Horizontal stabiliser pivot point 80 Elevator hydraulic actuators with centring springs (two) 81 Modified leading edge on tailplane 82 Air intake to air conditioning 83 Primary and secondary heat exchanger, exhaust (both sides) 84 Retractable air scoop for APU 85 Self-contained APU 86 APU exhaust 87 External air start point 88 Removable tailcone (Kevlar structure) 89 Two 29in x 90in mainwheels incorporating anti-skid carbon disc brakes 90 Free-tailing, trailing-link type undercarriage and air/oil shock absorbing strut 91 Hydraulic reaction jack 92 Kevlar door panels fitted with brush 93 Wings'fuse I age attachment fittings (total six) Tim Half \:JL John Marsdenf Montreal Rudder 33' left and right • ••. .: ••: -•... • • ••.• 1 Elevator 23.6 up 18.4rdown •v T I O N A L 94 Continuous strengthened two-spar wing torsion box, stiffened with integrally milled stringer skin panels (sealed for fuel tanks), trailing edge extended 10 per cent in chord 95 Shear web fuel tank end ribs 96 Wing tip extension of 36in 97 Wing inspection panels 98 Wing lets 99 Chemically etched skin panels (Kevlar tip panels) 100 Overwing tank-iillers 101 Single pressure-refuelling/defuelling point, on right side of aircraft (shown on left side tor clarity, total capacity 1,400 US gal 102 Outer wing tanks 103 Main wing tanks [total capacity 700 US gal each wing 104 tank vent line 105 Overboard ejector nozzle 106 Fuel storaae movement control pipes 107 Modified section on outboard wing leading edge 108 Wing leading-edge thermal anti-icing duct. 109 Auxiliary wingspar 110 Aileron hydraulic power control unit (two) and cable tension requlalor 111 Spoi'er panels 'tour on eacii wing) 112 Sooiler power control units (two hvdrauiically actuated, fly-by-wire) 113 On/off spoiler control unit (aluminium honeycomb core panels) 114 Flap actuator gearbox (electrically actuated) 115 Double slotted flaps (fixed vane outboard, articulated vane inboard) 116 Flap screw jacks (tour per wing, interconnected to prevent asymmetric operation) 117 External hinge brackets and flap/door linkage 118 Landing and taxi lamps (both-sides) 119 Navigation and strobe lights 120 Upper rotating beacon 121 White identification light 122 Static discharge wick;-, glassfibre- reinforced plastic 123 VHP No 1 aerial 124 Transponders 1 and 2 125 ADF loop antenna 126 VHF No 2 aerial 127DME1 128DME2 129 Radio altimeter 130 Markerantenna 131 ELT antenna 132 HF antenna in tin leading edge 133 VOR/ILS antenna both sides S Reed Business Publishing 1989 FLIGHT INTERNATIONAL 17 June 1989 49
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