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PART I-DESCRIPTIVE


          instability of flow, i.e. surge, the surplus air is bled off
          through air-bleed valves and the guide vanes are held in
          the maximum swirl position.  When the normal flight
          r.p.m. are reached, the air-bleed valves arc closed and
          the guide vanes move progressively to the minimum
          swirl position which occurs at 7,200 r.p.m.

     (b)  No noticeable change in r.p.m. or thrust occurs when the
          air-bleeds change over, nor do the guide vanes have any
          noticeable effect on engine operation. However, until
          the guide vanes reach the minimum swirl position at
          about 7,200 r.p.m. the compressor is not operating at
          maximum efficiency.

     13.  Engine instruments and anti-icing control

     (a)  The tachometer, jet pipe temperature gauge and oil
          pressure gauge are grouped on the starboard side of the
          instrument panel.

     (b)  Anti-icing control

          NOTE.-Use of this system is at present prohibited.

          The on/off switch (11) for the automatic anti-icing
          system is on the port wall.  When set to on, hot air is bled
          from the engine and fed to the engine intakes.  The system
          is intended only for icing prevention and is not intended
          for de-icing purposes.

     MAIN SERVICES

     16.  Electrical system (24 volt)
     
     (a)  D.C. supply

          (i)  Two 6,000-watt engine-driven generators supply the
               whole of the electrical system and charge a single
               24 volt aircraft battery. Two magnetic indicators,
               (55) one for each generator, on the upper starboard
               coaming show white when their respective generator
               is not supplying power. Generator cut-in speed is
               approximately 1,900 r.p.m.

19

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