(e) not more than 50 per cent of the reported wind com ponent opposite to the direction of take-off or not les than 150 per cent of the reported wind component in the direction of take-off.
do not exceed the take-off run available, the take-off distance available and the emergency distance available, respectively, at the aerodrome at which the take-off is to be made; in ascertaining b reference to the said flight manual the emergency distance required. the point at which the pilot is assumed to decide to discontinue the take-off shall not be nearer to the start of the take-off run than the point at which, in ascertaining the take-off run required and the take-off distance required, he is assumed to decide to continue the take-off, in the event of power unit failure.
(3) (a) The net take-off flight path with one power unit
inoperative, ascertained by reference to the said fig manual as being appropriate to-
(i) the weight of the aeroplane at the commenczpen
of the take-off run;
(H) the altitude at the aerodrome;
(i) the air temperature at the aerodrome; and (iv) not more than 50 per cent of the reported wind component opposite to the direction of take-off or not less than 150 per cent of the reported wind component in the direction of take-off.
and plotted from a point 35 feet or 50 feet, as appropriate. above the end of the take-off distance required at the aerodrome at which the take-off is to be made to a bright of 1,500 feet above the aerodrome, shows that the act» - plane will clear any obstacle in its path by a vertical interval of at least 35 feet, except that if it is intended that the aeroplane shall change its direction of flight by more than 150 the vertical interval shall not be less tha 50 feet during the change of direction.
(6) For the purpose of sub-paragraph (a) hereof an obstacle shall be deemed to be in the path of the aeroplane if the distance from the obstacle to the nearest point on the ground below the intended line of flight of the aeroplanc does not exceed—
(i) a distance of 200 feet plus half the wing span the aeroplane plus 4th of the distance from such point the end of the take-off distance available measured doug The intended line of flight of the aeroplane; or
(b) 5,000 feet, whichever is the less.
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(c) In assessing the ability of the aeroplane to satisfy this condition, it shall not be assumed to make a change of direction of a radius less than the radius of steady turn specified in the said flight manual.
(4) The aeroplane will in the meteorological conditions expected for the flight, in the event of any one power unit becoming inopera- tive at any point on its route or on any planned diversion therefrom and with the other power units or unit operating within the maximum continuous power conditions specified in the said flight manual, be capable of continuing the flight, clearing by a vertical interval of at least 2,000 feet obstacles within 5 nautical miles either side of the intended track, to an aerodrome at which it can comply with conditions (7) and (8) of this regulation relating to an alternate aerodrome, and on arrival over such aerodrome the slope of the one power unit inoperative net flight path, ascertained by reference to the said flight manual, shall not be less than zero at 1,500 feet above the aerodrome; and in assessing the ability of the acroplane to satisfy this condition it shall not be assumed to be capable of dying at an altitude exceeding the maximum permissible altitude for engine restarting, ascertained by reference to the said fight manual.
(5) The acroplane will in the meteorological conditions expected for the flight, in the event of any two power units becoming inopera- Live at any point along the route or on any planned diversion there- from more than 90 minutes flying time in still air at the all power units operating economical cruising speed from the nearest aerodrome at which it can comply with conditions (7) and (8) of this regulation. relating to an alternate aerodrome, be capable of continuing the flight with all other power units operating within the maximum continuous power conditions specified in the said flight manual, clearing by a vertical interval of at least 2,000 feet obstacles within $ nautical miles either side of the intended track to such an aerodrome, where the slope of the two power unit inoperative net flight path, ascertained by reference to the said flight manual, shall not be less than zero at 1,500 feet above the aerodrome; and in assessing the ability of the seroplane to satisfy this condition it shall not be assumed to be capable of flying at an altitude exceeding the maximum permissible altitude for engine restarting, ascertained by reference to the said flight manual,
(6) The weight of the aeroplane at the intended time of land- ing (hereinafter in this regulation called "the landing weight"), calculated by deducting the estimated weight of the fuel and oil expected to be used on the flight from its weight at the commence- ment of the take-off run, will not exceed any of the maximum landing weights for altitude and temperature ascertained by reference to the said fight manual as being appropriate to the
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