The Air Navigation (General) Regulations 2005

Weight and performance of public transport aeroplanes designated as aeroplanes of performance group Z

7.—(1) For the purposes of article 44(6), an aeroplane registered in the United Kingdom, in respect of which there is in force under article 44(5) a permission designating the aeroplane as being of performance group Z, shall not fly for the purpose of public transport unless the weight of the aeroplane at the commencement of the take-off run is such that the following sub-paragraphs as apply to that aeroplane are satisfied.

(2) Sub-paragraphs (5) and (6) apply to all aeroplanes to which this paragraph applies.

(3) Sub-paragraphs (7) to (24) inclusive apply to all aeroplanes to which this paragraph applies—

(a)of which the specified maximum total weight authorised exceeds 5,700 kg; or

(b)of which the specified maximum total weight authorised does not exceed 5,700 kg, and which comply with neither paragraphs (a) nor (b) of sub-paragraph (5).

(4) Sub-paragraphs (25) to (36) apply to all aeroplanes to which this paragraph applies of which the specified maximum total weight authorised does not exceed 5,700 kg, and which comply with either or both of paragraphs (a) and (b) of sub-paragraph (5).

(5) For the purposes of sub-paragraphs (1) and (2) either—

(a)the wing loading of the aeroplane shall not exceed 20 lb per square foot; or

(b)the stalling speed of the aeroplane in the landing configuration shall not exceed 60 knots; or

(c)the aeroplane shall be capable of a gradient of climb of at least 1 in 200 at an altitude of 5,000 feet in the specified international standard atmosphere, with any one of its power units inoperative and the remaining power unit or units operating within the maximum continuous power conditions specified.

(6) The weight of the aeroplane at the commencement of the take-off run shall not exceed the maximum take-off weight, if any, specified for the altitude and the air temperature at the aerodrome at which the take-off is to be made.

(7) Subject to sub-paragraph (9) the distance required by the aeroplane to attain a height of 50 feet, with all power units operating within the maximum take-off power conditions specified shall not exceed the take-off run available at the aerodrome at which the take-off is to be made.

(8) Subject to sub-paragraph (9) the distance required by the aeroplane to attain a height of 50 feet with all power units operating within the maximum take-off power conditions specified, when multiplied by a factor of either 1.33 for aeroplanes having two power units or by a factor of 1.18 for aeroplanes having four power units, shall not exceed the accelerate—stop distance available at the aerodrome at which the take-off is to be made.

(9) For the purposes of sub-paragraphs (7) and (8) the distance required by the aeroplane to attain a height of 50 feet shall be that appropriate to—

(a)the weight of the aeroplane at the commencement of the take-off run;

(b)the altitude at the aerodrome;

(c)the air temperature at the aerodrome;

(d)the condition of the surface of the runway from which the take-off will be made;

(e)the slope of the surface of the aerodrome in the direction of take-off over the take-off run available and the accelerate-stop distance available, respectively; and

(f)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.

(10) Subject to sub-paragraphs (12), (13) and (14), in the conditions mentioned in sub-paragraph (11) the take-off flight path of the aeroplane shall show that the aeroplane will clear any obstacle in its path by a vertical interval of at least 35 feet except that if it is intended that an aeroplane shall change its direction by more than 15° the vertical interval shall be not less than 50 feet during the change of direction.

(11) The conditions mentioned in sub-paragraph (10) are—

(a)that one power unit is inoperative and the remaining power unit or units are operating within the maximum take-off power conditions specified in sub-paragraph (12); and

(b)the take off path is plotted from a point 50 feet above the end of the appropriate factored distance required for take-off under sub-paragraph (8) at the aerodrome at which the take-off is to be made.

(12) The maximum take-off power conditions specified in sub-paragraph (11)(a) are those appropriate to—

(a)the weight of the aeroplane at the commencement of the take-off run;

(b)the altitude at the aerodrome;

(c)the air temperature at the aerodrome; and

(d)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.

(13) For the purpose of sub-paragraph (10) 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 does not exceed—

(a)a distance of 60 metres plus half the wing span of the aeroplane, plus one-eighth of the distance from such point to the end of the take-off distance available, measured along the intended line of flight; or

(b)900 metres,

whichever is the less.

(14) In assessing the ability of the aeroplane to satisfy sub-paragraph (10), it shall not be assumed the aeroplane will make a change of direction of a radius less than a radius of steady turn corresponding to an angle of bank of 15°.

(15) Subject to sub-paragraph (17), in the circumstances and conditions referred to in sub-paragraph (16) the aeroplane shall be capable of continuing the flight, clearing obstacles within 10 nautical miles either side of the intended track, by a vertical interval of at least—

(a)1,000 feet when the gradient of the flight path is not less than zero; or

(b)2,000 feet when the gradient of the flight path is less than zero,

to an aerodrome at which it can comply with sub-paragraph (10), and on arrival over such aerodrome the flight path shall have a gradient of not less than zero at 1,500 feet above the aerodrome.

(16) The following are the circumstances and conditions referred to in sub-paragraph (15)—

(a)the meteorological conditions expected for the flight;

(b)in the event of any one power unit becoming inoperative at any point on its route or on any planned diversion from it; and

(c)with the other power unit or units, if any, operating within the maximum continuous power conditions specified.

(17) For the purpose of sub-paragraph (15) the gradient of climb of the aeroplane shall be taken to be 1 per cent. less than that specified.

(18) In the meteorological conditions expected for the flight and at any point on its route or on any planned diversion from it the aeroplane shall be capable of climbing at a gradient of at least 1 in 50, with all power units operating within the maximum continuous power conditions specified 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 from it specified in, or calculated from the information contained in, the operations manual relating to the aeroplane; and

(b)the minimum altitudes necessary for compliance with sub-paragraphs (15) and (19), as appropriate.

(19) If, on the route to be flown or on any planned diversion, the aeroplane will:

(a)be engaged in a flight over water; and

(b)at any point during such flight it may be more than 90 minutes flying time in still air from the nearest shore,

it shall be capable of complying with the requirements of sub-paragraph (20) in the event of two power units becoming inoperative during such time and with the other power units, if any, operating within the maximum continuous power conditions specified.

(20) The requirements referred to in sub-paragraph (19) are:

(a)that the aeroplane is capable of continuing the flight, having regard to the meteorological conditions expected for the flight;

(b)clearing all obstacles within 10 nautical miles either side of the intended track by a vertical interval of at least 1,000 feet; and

(c)to an aerodrome at which a safe landing can be made.

(21) The landing weight of the aeroplane shall not exceed the maximum landing weight, if any, specified for the altitude and the expected air temperature for the estimated time of landing at the aerodrome at which it is intended to land and at any alternate aerodrome.

(22) Subject to sub-paragraph (23) the distance required by the aeroplane to land at the aerodrome at which it is intended to land from a height of 50 feet shall not exceed 60 per cent. of the landing distance available on—

(a)the most suitable runway for a landing in still air conditions; and

(b)the runway that may be required for landing because of the forecast wind conditions; provided that if an alternate aerodrome is designated in the flight plan, the landing distance required at the aerodrome at which it is intended to land shall not exceed 70 per cent. of that available on the runway.

(23) For the purpose of sub-paragraph (22) the distance required to land from a height of 50 feet shall be taken to be that appropriate to—

(a)the landing weight;

(b)the altitude at the aerodrome;

(c)the temperature in the specified international standard atmosphere appropriate to the altitude at the aerodrome;

(d)a level surface in the case of runways usable in both directions;

(e)the average slope of the runway in the case of runways usable in only one direction;

(f)still air conditions in the case of the most suitable runway for a landing in still air conditions; and

(g)not more than 50 per cent. of the forecast wind component opposite to the direction of landing or not less than 150 per cent. of the forecast wind component in the direction of landing in the case of the runway that may be required for landing because of the forecast wind conditions.

(24) Subject to paragraph (25), the distance required by the aeroplane to land from a height of 50 feet at any alternate aerodrome shall not exceed 70 per cent. of the landing distance available on—

(a)the most suitable runway for a landing in still air conditions; and

(b)the runway that may be required for landing because of the forecast wind conditions.

(25) For the purpose of sub-paragraph (24) the distance required to land from a height of 50 feet shall be determined in the manner provided in sub-paragraph (23).

(26) If the aeroplane is engaged:

(a)on a flight at night; or

(b)when the cloud ceiling or visibility prevailing at the aerodrome of departure or forecast for the estimated time of landing at the aerodrome of destination at which it is intended to land or at any alternate aerodrome are less than 1,000 feet and one nautical mile respectively,

it shall be capable of climbing at a gradient of at least 1 in 200 at an altitude of 2,500 feet in the specified international standard atmosphere with any one of its power units inoperative and with the remaining power unit or units, if any, operating within the maximum continuous power conditions specified.

(27) Subject to sub-paragraph (29), the distance required by the aeroplane to attain a height of 50 feet with all power units operating within the maximum take-off power conditions specified, shall not exceed the take-off run available at the aerodrome at which the take-off is to be made.

(28) Subject to sub-paragraph (29), the distance required by the aeroplane to attain a height of 50 feet, with all power units operating within the maximum take-off power conditions specified, when multiplied by a factor of 1.33 shall not exceed the accelerate-stop distance available at the aerodrome at which the take-off is to be made.

(29) For the purposes of sub-paragraphs (27) and (28) the distance required by the aeroplane to attain a height of 50 feet shall be that appropriate to—

(a)the weight of the aeroplane at the commencement of the take-off run;

(b)the altitude at the aerodrome;

(c)the temperature in the specified international standard atmosphere appropriate to the altitude at the aerodrome or, if greater, the air temperature at the aerodrome less 15° centigrade;

(d)the slope of the surface of the aerodrome in the direction of take-off over the take-off run available and the accelerate-stop distance available respectively; and

(e)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.

(30) The take-off flight path of the aeroplane, with all power units operating within the maximum take-off power conditions specified, appropriate to—

(a)the weight of the aeroplane at the commencement of the take-off run;

(b)the altitude at the aerodrome;

(c)the temperature in the specified international standard atmosphere appropriate to the altitude at the aerodrome, or, if greater, the air temperature at the aerodrome less 15° centigrade;

(d)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

(e)plotted from a point 50 feet above the end of the factored distance required for take-off under sub-paragraph (28), at the aerodrome at which the take-off is to be made,

shall show that the aeroplane will meet the requirements of sub-paragraph (31).

(31) The requirements referred to in sub-paragraph (30) are that the aeroplane shall clear any obstacle lying within 60 metres plus half the wing span of the aeroplane on either side of its path by a vertical interval of at least 35 feet. In assessing the ability of the aeroplane to satisfy this sub-paragraph it shall not be assumed to make a change of direction of a radius less than a radius of steady turn corresponding to an angle of bank of 15°.

(32) The aeroplane shall be capable of continuing the flight so as to reach a point above a place at which a safe landing can be made at a suitable height for such landing:

(a)in the meteorological conditions expected for the flight;

(b)in the event of any power unit becoming inoperative at any point on its route or on any planned diversion from it; and

(c)with the other power unit or units, if any, operating within the maximum continuous power conditions specified.

(33) The aeroplane shall be capable of climbing at a gradient of at least 1 in 50, with all power units operating within the maximum continuous power conditions specified at the altitudes referred to in paragraph (34) in the meteorological conditions expected for the flight and at any point on its route or any planned diversion.

(34) The altitudes referred to in paragraph (33) are:

(a)the minimum altitudes for safe flight on each stage of the route to be flown or on any planned diversion from it specified in, or calculated from, the information contained in the operations manual relating to the aeroplane; and

(b)the minimum altitudes necessary for compliance with paragraph (32).

(35) If on the route to be flown or any planned diversion from it the aeroplane will:

(a)be engaged on a flight over water;

(b)during which, at any point, it may be more than 30 minutes flying time in still air from the nearest shore; and

(c)in the event of one power unit becoming inoperative during such time and with the other power unit or units, if any, operating within the maximum continuous power conditions specified,

the aeroplane shall be capable of climbing at a gradient of at least 1 in 200 at an altitude of 5,000 feet in the specified international standard atmosphere.

(36) The landing weight of the aeroplane shall not exceed the maximum landing weight, if any, specified for the altitude and the expected air temperature for the estimated time of landing at the aerodrome at which it is intended to land and at any alternate aerodrome.

(37) Subject to sub-paragraph (38) the distance required by the aeroplane to land at the aerodrome at which it is intended to land and at any alternate aerodrome from a height of 50 feet shall not exceed 70 per cent. or, if a visual approach and landing will be possible in the meteorological conditions forecast for the estimated time of landing, 80 per cent. of the landing distance available on—

(a)the most suitable runway for a landing in still air conditions; and

(b)the runway that may be required for landing because of the forecast wind conditions.

(38) For the purposes of sub-paragraph (37) the distance required to land from a height of 50 feet shall be taken to be that appropriate to—

(a)the landing weight;

(b)the altitude at the aerodrome;

(c)the temperature in the specified international standard atmosphere appropriate to the altitude at the aerodrome;

(d)a level surface in the case of runways usable in both directions or the average slope of the runway in the case of runways usable in only one direction; and either

(e)still air conditions in the case of the most suitable runway for a landing in still air conditions; or

(f)not more than 50 per cent. of the forecast wind component opposite to the direction of landing or not less than 150 per cent. of the forecast wind component in the direction of landing in the case of the runway that may be required for landing because of the forecast wind conditions.