PART IV-EMERGENCY HANDLING

AL4
Para. 80
(Contd.)           ensure a clean jettison the speed must be in excess of 140 knots, with
Page 74           the hood fully closed and its control switch at OFF.  There is a risk of
                     damage to the aircraft controls and injury to the pilot if the hood is
                     not fully closed before it is jettisoned. Successful hood jettison trials
                     have been carried out between 110 and 280 knots.

              (b)  Mod. 347 embodied
                    When mod. 347 is embodied the hood is also jettisoned when either
                    ejection seat firing handle is pulled. Successful hood jettison trials
                    have been carried out between 110 and 280 knots.
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     81.  G.G.S. emergency lowering

          The G.G.S. is automatically lowered on jettisoning the
          hood provided that electrical power is available. It may
          be lowered manually by striking the knob on the port
          side a sharp blow.
          

     82.  Electrical system failures

     (a)  Generator failures

          (i)  If one generator fails, the output of the other is
               sufficient to meet all electrical demands.
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AL4               (ii)    If both generators fail, the battery will last for only a short time,
Para. 82                 probably in the order of 5 to 10 minutes. Set the V.I. tailplane
(a)(ii), (b)                to -1°.  Switch off all non-essential electrical services, and
Page. 74                 reduce altitude as quickly as possible to below 12,000 ft. When
                            at or below 12,000 ft. reduce and maintain r.p.m. below 7,000
                            and switch off the fuel master switch. Note that only the front
                            and centre tank booster pumps will operate following double
                            generator failure provided that battery power is available.
                            Switch the alternative electrical supply for the turn and slip
                            indicator to EMERG and return to base without delay.

           (b)    Inverter failure

                    If No. 1 inverter fails, automatic change-over to No. 2 intoner takes
                    place and the flight instruments will continue to operate. (See para.
                    16 (b) (i).
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     83.  Emergency trimming

     (a)  If the normal operating system for the V.I. tailplane
          becomes unserviceable in flight, trimming may be
          accomplished by operating the duplicate trim switch on
          the port console. Rate of operation of this is slow
          regardless of speed selected on the FAST/SLOW switch.

     (b)  If the tailplane runs away due to failure of the main trim
          switch, it can be overridden by use of the duplicate trim
          switch on the port console. However, as corrective action
          is being taken, operate the MAIN TRIM ISOLATION
          switch in order to prevent the tail from running away
          again when the duplicate switch is released.

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