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10.2 Noise evaluation
measure
a cirtificated take-oET mass not exceeding 8 618 kg, except The noise evaluation measure shall be the maximum
those aeroplanes specifically designed for aerobatic purposes noise le )v,,,Le(l as defined in Appendix 6.
and agricultural or fire fighting uses and self-sustaining
powered sailplanes.
10.1.2 For an aeroplane for which the application for the 10.3 Reference noise
certificate of airworthiness tor the prototype or for all derived measurement points
versions was accepted, or another equivalent prescribed
procedure was carried out by the certificating authority, on or 10.3.1 An aeroplane, when tested in accordance with
after 17 November 1988, except for those aeroplanes specified these Standards, shall not exceed the noise level specified in
in 10.1.4, the noise limits of 10.4 a) shall apply. 10 4 at the take-off reference noise measurement point.
10.1.3 For aeroplanes specified in 10.1.2 which fail to 10.3.2 The take-off reference noise nleasurelnent point is
comply with the Standards this and where the a ~ ~ l i - the point on the extended centre line of the runway at a distance
cation for the certificate of airworthiness for the protome or all of 500 the start of take-off roll.
derived versions was accepted, or another equivalent prescribed
procedure was canied out by the certificating authority, before
17 November 1993, the Standards of Chapter 6 shall apply.
10.4 Maximum noise levels
10.1.4 For single-engined aeroplanes, except those
aeroplanes specifically designed for aerobatic purposes and The maximum noise levels determined in accordance with the
agricultural or fire fighting uses, self-sustaining powered noise evaluation method of Appendix 6 shall not exceed the
sailplanes, float planes and amphibians, for which: following:
a) the application for the certificate of airworthiness for the
prototype or their derived versions was accepted, or
another equivalent procedure was carried out by the
certificating authority, on or after 4 November 1999, the
noise limits of 10.4 b) shall apply;
b) an application for the certificate of airworthiness for the
derived version was accepted, or other procedure was
carried out, on or after 4 November 1999, but for which
the application for the certificate of airworthiness for the
prototype, or another equivalent procedure was carried
out by the certificating authority, before 4 November
1999, the noise limits of 10.4 b) shall apply;
a) for aeroplanes specified in 10.1.2 and 10.1.4 c), a
76 dB(A) constant limit up to an aeroplane mass of
600 kg varying linearly from that point with the
logarithm of aeroplane mass until at 1 400 kg the limit
of 88 dB(A) is reached after which the limit is constant
up to 8 618 kg; and
b) for aeroplanes specified in 10.1.4 a) and b), a
70 dB(A) constant limit up to an aeroplane mass of
570 kg increasing linearly from that point with the
logarithm of aeroplane mass until at 1 500 kg the
limit of 85 dB(A) is reached after which the limit is
constant up to 8 618 kg.
ANNEX 16 - VOLUME I 11-10-1 2411 1/05
Annex 16 - Environmental Protection Volume I
10.5 Noise certification
reference procedures
10.5.1 General conditions
10.5.1.1 The calculations of reference procedures and
flight paths shall be approved by the certificating authority.
10.5.1.2 Except in conditions specified in 10.5.1.3, the
take-off reference procedure shall be that defined in 10.5.2.
10.5.1.3 When it is shown by the applicant that the design
characteristics of the aeroplane would prevent flights being
conducted in accordance with 10.5.2, the reference procedures
shall:
a) depart from the reference procedures defined only to the
extent demanded by those design characteristics which
make compliance with the procedures impossible; and
b) be approved by the certificating authority.
10.5.1.4 The reference procedures shall be calculated
under the following atmospheric conditions:
a) sea level atmospheric pressure of 1 013.25 hPa;
b) ambient air temperature of 15"C, i.e. ISA;
c) relative humidity of 70 per cent; and
d) zero wind.
10.5.1.5 The acoustic reference. atmospheric conditions
shall be the same as the reference atmospheric conditions for
flight.
10.5.2 Take-off reference procedure
The take-off flight path shall be calculated taking into account
the following two phases.
First phase
a) Take-off power shall be used from the brake release
point to the point at which the height of 15 m (50 ft)
above the runway is reached.
b) A constant take-off configuration selected by the applicant
shall be maintained throughout this first phase.
　
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