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                      PART III - HANDLING
                      
              tank selector switch from AUTO to REAR until the
              contents reduce to below 1,300 lb. then set the switch
              to WING.  A check that the associated level light
              comes on at approx. 650 lb. will verify that all fuel
              has been correctly transferred

        (ii)  If changeover to the wing tanks does not function
              automatically, shown by the magnetic indicator still
              pointing to REAR at a fuel state less than approx
              1,300 lb., set the tank selector switch from AUTO
              to WING.  If the magnetic indicator still points to
              REAR a fault in the changeover system has
              occurred.  The amount shown on the contents gauge
              will include unusable fuel in the wing tank i.e.,
              539lb., but only the front tank fuel (770 lb.) should
              be relied upon as being available to the engine.  This
              condition can be verified by noting at what fuel
              state the amber low-level lights come on.
              
        (iii) Provided slow forward throttle movements and
              small changes in  attitude are made, the engine will
              continue to  run satisfactorily down to zero gauge
              readings, but at low level states steep climbs and/or
              sudden application of power should be avoided,
              particularly when overshooting, as this will cause
              fuel in the tanks to move away from the booster-
              pumps, resulting in a possible fuel starvation and
              flame extinction.  Therefore at low fuel states
              minimum power consistent with safety should be
              used, steep attitudes avoided and a glide approach
              planned.  If a flame-out occurs, a relight may be
              obtained by adopting a nose-down attitude and
              pressing the relight button.  The amount of unusable
              fuel increases with sudden forward acceleration
              and/or nose-up attitude:  rig tests reveal the
              following:-
              
              Angle between fuel           Unusable fuel lb.
              surface and fuselage             per side
                     datum
                     
                       10°                       123
                       20°                       200
                       30°                       230

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