Unclassified aircraft: conditions

With reference to Article 17 of the Order a public transport aeroplane having no performance group classification in the certificate of airworthiness relating to the aeroplane issued or rendered valid by the Governor shall not fly or attempt to fly unless the following conditions are satisfied– (1) The weight and performance of the aeroplane at the commencement of the take-off run are such that either– (a) the wing, loading of the aeroplane does not exceed 20 lb. per square foot; or (b) the stalling speed of the aeroplane in the landing configuration does not exceed 60 knots; or (c) the aeroplane, with any one of its engines inoperative and the remaining engine or engines operating within the maximum continuous power conditions specified in the certificate of airworthiness, performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, shall be capable of a gradient of climb of at least 1 in 200, at an altitude of 5,000 feet above mean sea level in air having Civil Aviation 73 a temperature of 5.10 centigrade and a pressure of 843 millibars. (2) The weight of the aeroplane at the commencement of the take-off run does not exceed any of the following weights– (a) the weight, if any, specified in the performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor as being the maximum take-off weight appropriate either to the height above mean sea level of, and the air temperature at, the aerodrome at which the take-off is to be made, or to the height above mean sea level of such aerodrome; (b) the weight at which the aeroplane, with all engines operating within the maximum take- off power conditions specified in the certificate of airworthiness, performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, is capable of attaining a height of fifty feet within the following distance– (i) if the aeroplane has one or two engines the take-off run available or seventy- five per cent. of the emergency distance available, whichever is the less, at the aerodrome at which the take-off is to be made; (ii) if the aeroplane has more than two engines-the takeoff run available or eighty-five per cent. of the emergency distance available, whichever is the less, at the aerodrome at which the take- off is to be made. 74 Civil Aviation (c) the weight at which the aeroplane, with all engines operating within the maximum take- off power conditions specified in the certificate of airworthiness, performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, is, after passing the end of the emergency distance available, capable of clearing by a safe margin any obstacle, the distance from which to the nearest point on the ground below the intended line of flight of the aeroplane does not exceed 200 feet plus half the wing span of the aeroplane. (3) The aeroplane will, in the meteorological conditions expected for the flight in the event of one engine becoming inoperative at any point on its route or on any planned diversion therefrom and with the other engine or engines, if any, operating within the maximum continuous power conditions specified in the certificate of airworthiness, performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, be capable of continuing the flight so as to reach a point above– (a) an aerodrome at which a safe landing can be made at a suitable height for such landing; or (b) if the aeroplane has a maximum total weight authorised in its certificate of airworthiness not exceeding 12,500 lbs. and complies with either condition (1)(a) or condition (1)(b) hereof, a place at which a safe landing can be made at a suitable height for such landing. (4) The aeroplane will, in the meteorological conditions expected for the flight, at any point on its route or on any planned diversion therefrom, be capable of climbing at a gradient of at least one in fifty, with all engines operating within the maximum continuous power conditions specified in the Civil Aviation 75 certificate of airworthiness, performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, at the following altitudes– (a) the minimum altitudes for safe flight on each stage of the route to be flown or of any planned diversion therefrom stated in, or calculated from the information contained in, the operations manual; (b) the minimum altitudes on each stage of the route to be flown or of any planned diversion therefrom at which it is necessary to fly to ensure that, in the event of one engine becoming inoperative and with the other engine or engines, if any, operating within the maximum continuous power conditions specified in the certificate of airworthiness, performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, the aeroplane is capable of continuing the flight so as to reach a point above– (i) an aerodrome at which a safe landing can be made at a height suitable for such landing; or (ii) if the aeroplane has a maximum total weight authorised in its certificate of airworthiness not exceeding 12,500 lbs. and complies with either condition (1)(a) or condition (1)(b) hereof, a place at which a safe landing can be made at a height suitable for such landing. (5) If on the route to be flown the aeroplane will be engaged in a flight over water during which at any time it may be more than ninety minutes flying time in still air from the nearest 76 Civil Aviation shore, it will, in the event of one engine becoming inoperative during such time and with the other engine or engines, if any, operating within the maximum continuous power conditions specified in the certificate of airworthiness, performance schedule or flight manual relating to the aeroplane, issued or rendered valid by the Governor, be capable of climbing at a gradient of at least one in two hundred at an altitude of 5,000 feet above mean sea level in air having a temperature of 5.1° centigrade and a pressure of 843 millibars. (6) The weight of the aeroplane at the intended time of landing calculated by deducting the estimated weight of the fuel expected to be used on the flight from its weight at the commencement of the take-off run will not exceed any of the following weights– (a) the weights, if any, specified in the performance schedule or flight manual relating to the aeroplane issued or rendered valid by the Governor, as the maximum landing weights appropriate either to the heights above mean sea level of, and the air temperatures forecast for the estimated times of landing at, the aerodrome at which it is intended to land and any alternate aerodrome, or to the heights above mean sea level of such aerodromes; (b) the weight at which the aeroplane is capable of landing safely in still air conditions in not more than seventy per cent., or, if a visual approach and landing will be possible in the meteorological conditions forecast for the estimated time of landing, in not more than eighty per cent. of the landing distance available at the aerodrome at which it is intended to land or at any alternate aerodrome; and Civil Aviation 77 (c) the weight at which the aeroplane is capable of landing safely in the wind conditions forecast for the estimated time of landing, regard being had to not more than fifty per cent. of the forecast wind component opposite to the direction of landing, or to not less than one hundred and fifty per cent of the forecast wind component in the direction of landing, in not more than seventy per cent., or if a visual approach and landing will be possible in the meteorological conditions forecast for the estimated time of landing is not more than eighty per cent., of the landing distance available at the aerodrome at which it is intended to land or at any alternate aerodrome.