A.L.1                      PART III - HANDLING
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                 In the normal unstick attitude, the angle between fuel surface
                 and aircraft datum is approx. 23°, at which angle approx. 208lb.
                 per side are unusable.

         (h)  Fuel gauge errors

                 (i)  The fuel contents gauges have been found to give erroneous
                      indications due to temperature effects on the electrical gauging
                      system.  The magnitude of the error depends on both temperature
                      and time.  Low temperatures at high altitude give gauge under-
                      reading; high temperatures at high speeds at low altitude give
                      gauge over-reading.
                      
                 (ii) To assess the gauge error the readings of the contents gauges
                      should be checked immediately the front tanks low level warn-
                      ing lights come on.  The difference between the total gauge
                      readings and 1,300 lb. indicates the gauge inaccuracy.  This
                      figure should be applied to all gauge readings for the remainder
                      of the flight at the same operating conditions.  During a descent
                      from altitude, if the assessed inaccuracy was a gauge under-
                      reading, the gauges will progressively become more accurate and
                      may eventually tend to over-read.
                      
         58.  Engine performance and handling
         
         (a)  Take-off
         
              (i)   The r.p.m. are governed at 8,000, at which max. thrust is ob-
              tained, but at full throttle this figure will vary with O.A.T.
              whilst still maintaining max. thrust.  Below are the relevant
              figures:-
                              +15°C and above           8,000 r.p.m.
                              +10°C                             7,985 r.p.m.
                                  0°C                             7,950 r.p.m.
                               -10°C                             7,910 r.p.m.
              At full power check that the oil pressure is 25 lb./sq. in. min.

              (ii)   Malfunctioning of the swirl vane system will allow the engine
                     to reach max. r.p.m. without producing max. thrust.  Therefore
                     to verify that max. thrust is being obtained the following check
                     should be carried out:-

                         1.  Max r.p.m. is not obtained at part throttle.
                         2.  The aircraft begins to creep forward against the brakes
                              at 7,000-7,200 r.p.m.
                         3.  The rate of acceleration is normal when the brakes are
                              released.
                         4.  The j.p.t. is more than 560°C.
                         
                     If, at 17,500 lb., the take-off is abandoned at a speed of 100 knots
                     the aircraft will take approximately 750 yards to stop from the
                     point at which the brakes are applied.  If it is decided to abandon
                     the take-off and the length of runway remaining is short, the
                     throttle should be set to the H.P. cock OFF position.

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