1962-HKRS30-8-53_Part02 — Page 16

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within the maximum continuous power conditions specified, at the following allitudes-

(a) the minimum altitudes for safe fight on each stage of the route to be down or on any planned diversion therefrom 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 condition 13. 15. If on the route to be flown or any planned diversion therefrom the aeroplan

will be engaged in a flight over water during which at any point it may be more than 30 minutes flying time in still air from the pearest shore, il vill in the event of one power unit becoming inoperative during such time and with the other power unit or units operating within the maximum continues power conditions specified, 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.

16. The landing weight of the aeroplane will not exceed the maximum landing weight, if any, specified for the altitude and the expected air temperature fœ the estimated time of landing at the aerodrome at which it is intended u land and at any alternate aerodrome.

17. The distance required by the aeroplane to land from a height of 50 feet dees not, at the aerodrome at which it is intended to land and at any alternate aerodrome, 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-

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

(ii) the runway that may be required for landing because of the forecull

wind conditions,

the distance required to land from a height of 50 feet being taken to be that appropriate to-

(a) the landing weight;

(6) the altitude at the aerodrome;

(c) the temperature in the specified international standard atmosphere appro

priate to the altitude at the aerodrome;

(d) 6) a level surface in the case of runways usable in both directions

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

(e) (1) still air conditions in the case of the most suitable runway for 1

landing in still air conditions;

(i) not more than 50 per cent of the forecast wind component opposle 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 ruowy that may be required for landing because of the forecast wind conditions.

SECOND SCHEDULE.

CONDITIONS APPLICABLE TO ABROPLANES CLASSIFIED AS AEROPLANES OF PERFORMANCE GROUP A IN THEIR CERTIFICATES OF AIRWORTHINESS,

{reg. 7)

1. That weight does not exceed the maximum wake-off weight for altitude and temperature specified for the altitude and the air temperature at the aero- drome at which the take-off is to be made.

2. The take-off run, take-off distance and the emergency distance respectively

required for take-off, specified as being appropriate to-

(2) the weight of the aeroplane at the commencement of the lake-off noi

(5) the altitude at the aerodrome;

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(c) the air temperature at the aerodrome;

th the slops of the surface of the aerodrome in the direction of take-off over the take-off run available, the take-off distance available and emer· gency distanoc available, respectively; and

(2) 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,

do not exceed the wake-off run, the take-off distance and the emergency distance available, respectively, at the aerodrome at which the take-off is to be made; in ascertaining 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.

1. (1) The net take-off flight path with one power unit inoperative, specified as

being appropriate to-

(a) the weight of the aeroplane at the commencement of the take-off run; (6) the altitude at the aerodrome;

(c) the air temperature at the aerodrome, and

(

not more than 50 per cent of the reported wind component opposite to the direction of take-off or not leas than 150 per cent of the reported wind compantat 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 height of 1,500 feet above the aerodrome, shows that the acroplane will clear any obstacle in its path by a vertical interval of at least 35 feel except that if it is intended that the acroplane shall change its direc tion of flight by more than 15' the vertical interval shall not be less than 50 feet during the change of direction.

2) For the purpose of paragraph (1) 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 aeroplane does Bot exceed

(2) a distance of 200 fest plus half the wing span of the aeroplane plus one-eighth of the distatice from such point to the end of the take-off distance available, measured along the intended line of flight of the acroplane; or

(6) 5,000 feet,

whichever in the less.

In assessing the ability of the acroplane 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.

4. The aeroplane will, in the meteorological conditions expected for the flight, in the event of any one power unit becoming inoperative at any point on ils route or on any planned diversion therefrom and with the other power units or unit operating within the maximum continuous power conditions specified, 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 incoded track, to an aerodrome at which it can comply with condition 7. relating to an alternate aerodrome, and on arrival over such aerodrome the Badient of the specified net flight path with one power unit inoperative shall not be less than zero ut 1,500 feet above the aerodrome; and io assessing the ability of the aeroplane to satisfy this condition it shall not be assumed to be capable of flying at an altitude exceeding the specified maximum permissible altitude for power unit restarting.