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Aviation History
1964
1964 - 2035.PDF
r~in-m~r'~ ••"" deck of Super Frelon 02, described in column 2 below SUPER FRELON... pressor turbine and two-stage free turbine. The latter drives the out- put shaft through a spur gear which reduces speed from 23,150 to 5,700 r.p.m.; the gas-producer section runs at 33,500 r.p.m. All three engines are handled as a single powerplant, with an electrical con- stant-speed governor for the rotor. There is an automatic starting panel and three fuel-flow levers which give individual idling control, but the power lever is collective for all three. Engine controls are mounted in the cockpit roof. The twist-grip on the collective-pitch lever is used only when the rotor speed governor has been switched off. Other Systems Dual flying controls are fitted, with bent sticks having inverted pistol-grip handles, and straight pull-up collective- pitch levers. The dual rudder pedals have toe-operated brakes. The stabilizing tailplane is not adjustable in flight for trim. Hydraulic power to the cyclic and collective servo jacks is supplied continuously from two independent systems, only one of which feeds the tail- rotor servo. If one system fails the other supplies full control assistance; should the faulty system be that to the tail rotor, pedal loads remain acceptable. A full autopilot system is standard. Cockpit layout is simple, with a central console, surmounted by a rectangular dash panel, and side and roof panels for secondary instruments and switches. The pilots' seats are adjustable for height and leg reach. The extensive glazing includes large knockout emergency-exit panels on each side and a hinged DV panel for ea_ch pilot. Wipers, washers and de-icing heaters are fitted to both windscreens. Communication and navigation radios are mounted behind the pilots, and there is room for a jump seat. Normal entry is through a door in the bulkhead between the cockpit and main cabin. Left, economical cruise plotted against gross weight; right, payload excluding mission fuel and crew of two) versus range 12 5- 100 | — - -• _ - - ._ h • ... — I .. L. •t i --*-• —j—• ...i— -~f~ i — '- 5 j - . -- [ I"+" j - - - _ j-V 1 I 1 p — ...u i I n-i- i -4 T ~^ 14 I 24 26 Gross weight, lb 1000 12,000' 10, 000' 8, 000 6,000 4, 000 2, oon 0' •— 5 n$& b b ! t j. > \f C* ^.i>. 1 1 i— Limited by gross weight -^ Limited by capacity of fuel cells .4 | \ o 100 200 300 400 500 Range, n. m.
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