PART III-MANAGEMENT OF SYSTEMS

         be left there and the engine opened up slowly to the
         desired r.p.m. Idling r.p.m. will be high and landing
         must be carried out with caution.

     54. Management of the pressurising and demisting systems

     (a) The control wheel for regulating the supply and tempera-
         ture of the pressurised air must be set to OFF, HOT or
         REDUCE when the aircraft is on the ground with the
         engine running, in order to avoid overheating the cold
         air unit. COLD or MIX must not be selected on the
         ground.

     (b) It is recommended that the cockpit is pressurised immedi-
         ately after take-off. If not, the pressure warning light
         will come on at about 17,000 ft. The pressure control
         should then be operated and the warning light will go
         out as pressure builds up.

     (e) In conditions where hood misting is anticipated, the
         control wheel should be at HOT, the r.p.m. should be
         kept as high as practicable and the ventilators in the
         gallery pipes closed to give maximum flow of hot air to
         the windscreen.

     (d) To reduce temperature at high altitudes, the control
         wheel should be moved to MIX or COLD, since move-
         ment to REDUCE may result in a reduction of cockpit
         pressure.

     55. Management of the electrical system

     (a) Push in the GROUND/FLIGHT switch before starting
         and check that the turn and slip indicator starts up.
         Then set the FLIGHT INST switch ON and check that
         the artificial horizon OFF flag disappears, that the Mk.
         4F compass annunciates and that the magnetic indicator
         remains white.
-----------------------------------------------------------------
Page 34 (b)   After starting, when the generator is on line, check that auto-
Para. 55       changeover occurs as shown by the magnetic indicator turning black.
(b)              If the indicator reverts to white at any stage before becoming airborne,
A.L.1           increase r.p.m. and if necessary press the reset pushbutton. With
                  F.T.C. Mod. 101 fitted auto-changeover occurs before engine idling
                  r.p.m. are reached.  In this case if the indicator reverts to white
                  the No. 1 inverter system is unserviceable.

                  WARNING.-Do not operate the button if auto-changeover occurs
                  in flight.

34