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Aviation History
1963
1963 - 0707.PDF
\AH x«2 A4- rss 5o D2 Wing supply duct D3 Telescopic and swivelling supply pipes to Kruger flaps D4 Telescopic supply pipes to slats D5 Provision for duct up fin spar D6 Hose around tailplane fulcrum (not at present fitted) D7 Engine intake, bullet and inlet guide- vane anti-icing D8 Centre-engine duct anti-iced for ward of this point D9 Hot air overboard from dorsal VHF antenna DIO Pitot tubes, static ports, and water- drain masts electrically heated Dll Nesa-glass cockpit windows E Electric and hydraulic power El 40-kVA generator on each engine constant-speed drive E2 24V, I lA-hr Ni-Cd battery E3 External power socket E4 Cable raceways used throughout (typical shown on centre-engine cowl) E5 Electrical service bay aft of nose- wheel box: transformers, rectifiers, etc E6 Taxi lamp on nosewheel E7 Turn-off lamp in wing root E8 Landing lamps in wing root and in Kruger flaps (total four) E9 Wing inspection split-beam lamp EIO Rotating anti-collision beacon (simi lar unit below) Ell Fixed wing-tip lights EI2 Oscillating-mirror lights at wing-tip and tail fairing EI3 Toilets, ceiling, and cove strip lights EI4 Interior service lights: freight holds (12), wheel bays (6), equipment bays (22), in fin box (4) and on ventral airstair (15) EI5 Electrically heated forward hold for specialized loads EI6 40kVA a.c. generator on APU EI7 Cooling air to EI6 EI8 Hydraulic service bay by ventral stairs: 3,000lb/sq in A and B systems; Skydrol 500A fluid; seamless steel tubing; no banjo fittings; all male joints EI9 System A pump on left and centre engines. B system is electro- hydraulic F Fuel system Fl No I integral tank; 1,700 US (1,416 Imp) gal F2 No 2 tank: integral in inner wing, plus two bag-tanks in centre-section: 3,600 US (2,997 Imp) gal F3 No 3 integral tank; 1,700 US (1,416 Imp) gal F4 Space for optional 500 US (416 Imp) gal bag-tank F5 Surge tank F6 Jettison pipe F7 Boost pumps (two in each outer tank: four in centre tank) F8 Vent system in wing stringers to scoop under tip F9 Typical fuel-level unit FI0 Tank-end ribs Fl I Pressure fuelling point (two sockets) L Load furnishing LI Toilets L2 Galleys l_3 P.a. telephone on console L4 Water fountain and book rack L5 Stewards' occasional seat L6 Translucent screen L7 Cot (one of four) L8 Passenger service units, adjustable for seat-pitch L9 Paper-honeycomb hat-racks LI0 First-class (double) seats Lit Tourist (triple) seats LI2 Seat-back tables LI3 Moulded plastic window-surrounds LI4 Pressurized titanium water tank, 40 US (33 Imp) gal LIS Tank compressor for ground use LI6 P.a. speakers in hat-racks: music from tape machine LI7 Adjustable foot-rest on passenger seats LI8 Captain LI9 First Officer L20 Engineer (panel removed) L2I First observer L22 Second observer L23 Window blinds L24 Potable water servicing point P Powerplant (for detailed illustration see back of page) PI Pratt & Whitney JT8D-I turbofans: I4,000lb-thrust P2 Three-point engine mountings P3 Centre-engine rear mounting P4 Detachable nose-cowls P5 Acoustic ("tuned") panels in intakes P© Air bleeds at 6th, 8th, and 13th stages P7 Fan section P8 Low-pressure section P!5 PI6 PI8 PI9 P.9 RIO Rll R12 High-pressure section Combustion section Turbine section Reverser door pneumatic actuator Cooling air to constant-speed drive on centre engine Drains manifold and extraction system All ancillaries grouped below engine AiResearch GTC85 APU mounted in wheel-bay keel member APU exhaust through door on upper wing surface APU intake APU combustion chamber Radio and electronics Weather-radar scanner and wave guide Weather-radar receiver under cock pit floor Glide-slope aerial VHF No I dorsal aerial ADF sense aerials in centre-engine cowl VOR in fin HF probe aerial (optional, chosen by Lufthansa) Doppler, ATC I & 2. VHF 2 & 3, ADF 'oops I & 2, marker beacon, and DMET I & 2, along belly centre line Access hatch to electronics service bay Front rack: instrument amplifiers and computers, glide-slope and VOR units, autopilot control chan nels and air-data sensors, yaw- damper couplers, weather-radar auxiliary unit, stall-warning and air-data computers, flight director VG compass units and fight-recover Rear rack: components of air- conditioning, fire-detection and fuel-flow systems; landing-gear and anti-skid control, makers, ATC transponders, DMET, VHF, Selcal, ADF, public-address, and taped music and announcements Cooling air overboard from elec tronics S Safety systems 51 Engine fire-suppression bottles 52 Portable extinguishers at three points in cabin 53 Oxygen cylinders accessible from hold (two for passengers, one for crew) 54 Oxygen "on" control in cabin floor 55 Oxygen overboard dump 56 Portable oxygen cylinders and emergency equipment 57 Escape ropes, by cockpit windows and above (Sit) 58 Inflatable escape chutes on passenger and galley doors 59 Firewalls SI0 Drop-down oxygen masks in pas senger service units (automatic if cabin-altitude exceeds 14,000ft) SI I Four 26in x 38in escape hatches over wing U Undercarriage Ul Shock-strut with angled upper leg U2 Sway brace and downlock U3 Drag strut U4 Forged trunnion beam and link U5 Shock-strut filler U6 Torsion links U7 49 x 17m tyres U8 Walking-beam type actuator U9 Double-fold wheel-bay doors UIO Jacking and towing point U 11 Anti-skid equipment UI2 Nosewheel brake, with anti-skid UI3 Twin 32 x I I.Sin nylon ply tyres UI4 Twin steering cylinders and cables UlS Nosewheel steering tiller in cockpit UI6 Nosewheel fulcrum U17 Nosewheel jack UI8 Leg-well doors UI9 Wheel-well doors (normally pre- closed) U20 Main wheels retracted
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