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                           PART 1-DESCRIPTIVE

        lever (18) marked JETTISON-FUEL TANKS posi-
        tioned on the left of the pilot's seat. (See para.47)

   5.   Oil system

   (i)  There is no oil tank, but the power unit has a sump which
        contains about 1½ gallons of oil for lubricating the engine-
        driven accessories and the impeller bearings.
   (ii) The oil pressure and the oil temperature gauges (40) are
        fitted on the left-hand side of the instrument panel.

   MAIN SERVICES        

   6.   Pneumatic system

   (i)  An engine-driven compressor charges a bottle for the
        operation of the brakes.  The triple pressure gauge (32)
        on the right-hand side of the instrument panel, shows the
        available pneumatic pressure; when fully charged this
        should be 450 lb./sq. in. and should give a pressure of
        150 lb./sq. in. at each brake.
        This pressure will still be available for the brakes should
        the pressure in the bottle fall as low as 240 lb./sq. in.
   (ii) An engine-driven vacuum pump provides suction for the
        blind flying instruments and for deflating the canopy seal.        

   7.   Electrical system

   (i)  An engine-driven generator charges two 12-volt batteries
        connected in series.  These in turn supply the whole of
        the electrical system at 24 volts, except the automatic
        engine starting.
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A.L.1  | (ii)  A generator warning light (26) at present mounted on the top right-hand side of
Para. 7|       the instrument panel will be removed later by a retrospective Mod. 850 to a position
(ii)     |       on the left-hand side of the instrument panel level with the fuel pressure warning
        |        light (19) and as far inboard as possible.  This warning light indicates when the
        |        voltage of the generator falls appreciably below the voltage of the batteries.  It is
        |        wired directly to the batteries and will, therefore, be on continuously whilst the
        |        engine is not running, irrespective of the position of the master switch.

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   (iii)The master switch (2), with GROUND and FLIGHT posi-
        tions, is fitted on the port cockpit wall.  Two external
        sockets are fitted, one on each side of the fuselage, below
        the wing.  The port socket is for normal ground test
        purposes, and is marked RADIO TEST SOCKET.  The

15

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