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• [cad:weight_and_performance]

Weight and performance of public transport aeroplanes classified as aeroplanes of performance group A in their certificates of airworthiness

A performance group A aircraft shall not fly for public transport unless the weight at the commencement of the takeoff run satisfies all the following conditions.

Maximum takeoff weight

In determining the maximum takeoff weight, the following must be accounted for:

• aerodrome altitude
• air temperature

Takeoff run, takeoff distance, emergency distance

In determining takeoff run, takeoff distance, and accelerate-stop distance, the following must be accounted for:

• aircraft weight
• aerodrome altitude
• air temperature
• runway surface condition
• runway slope
• not more than 50% of reported headwind, or not less than 150% of reported downwind

Net takeoff flight path

In determining the net takeoff flight path with one engine inoperative, the following must be accounted for:

• aircraft weight
• aerodrome altitude
• air temperature
• not more than 50% of reported headwind, or not less than 150% of reported downwind

The path is from 35' or 50' (as appropriate) to 1500' and obstacles must be cleared by 35', or 50' during a turn of more than 15^o. Obstacles up to the minimum of:

• 60m + 1/2 aircraft wing span + 1/8 distance to end of takeoff distance; or
• 900m

must be accounted for.

Enroute

The aircraft must be capable of continuing flight, with one engine inoperative and maximum continuous thrust on the other engine/s, 2,000' clear of obstacles within 10nm either side of track to the destination or alternate. This requirement may be reduced to 5nm if navigation aids are used. The net flight path gradient must be >0 over the destination at a height of 1,500' agl.

The 2 engine inoperative requirements only need to be considered when the aircraft is more than 90mins from an aerodrome.

An aircraft with 2 engines may not be more than 60mins at the one engine inoperative cruise speed from an alternate (unless under ETOPS).

Maximum landing weight

In determining the maximum landing weight, the following must be accounted for:

• aerodrome altitude
• expected air temperature

The landing weight is limited by the most restrictive of the destination or alternate airports for turbo-jet aircraft, although may be satisfied by an alternate in the case of a turbo-prop or piston engined aircraft.

Landing distance

In determining landing distance, the following must be accounted for:

• aircraft weight
• aerodrome altitude
• ISA air temperature
• runway level slope
• not more than 50% of reported headwind

Both the most suitable runway in still conditions and the expected runway from forecast winds must be accounted for.

See also

AN(HK)O Schedule 15

References

1. AN(HK)O Schedule 15(4)

Categories: CAD (Hong Kong) | Performance