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by a Contracting State that the following situations for
jet aeroplanes and propeller-driven heavy aeroplanes on its
regis- do not require demonstration of compliance with the
provisions of the Standards of Annex 16. Volume I:
a) gear down flight with one or more retractable landing
gear down during the entire flight;
b) spare engine and nacelle carriage external to the skin of
the aeroplane (and return of the pylon or other external
mount); and
I . With no stopway or clearway.
c) time-limited engine andlor nacelle changes, where the
change in type design specifies that the aeroplane may
not be operated for a period of more than 90 days unless
compliance with the provisions of Annex 16, Volume I,
is shown for that change in type design. This applies
only to changes resulting fiom a required maintenance
action.
2.2 Noise evaluation measure
The noise evaluation measure shall be the effective perceived
noise level in EPNdB as described in Appendix 1.
2.3 Noise measurement points
An aeroplane, when tested in accordance with the flight test
procedures of 2.6, shall not exceed the noise levels specified
in 2.4 at the following points:
a) lateral noise measurement point: the point on a line
parallel to and 650 m fiom the runway centre line, or
extended runway centre line, where the noise level is a
maximum during take-off;
b) jlyover noise measurement point: the point on the
extended centre line of the runway and at a distance of
6.5 km from the start of roll; and
c) approach noise measurement point: the point on the
ground, on the extended centre line of the runway, 120 m
(394 ft) vertically below the 3" descent path originating
fiom a point 300 m beyond the threshold On level
ground this corresponds to a position 2 000 m fiom the
threshold.
2.4 Maximum noise levels
2.4.1 The maximum noise levels of those aeroplanes
covered by 2.1.1 above, when determined in accordance with
the noise evaluation method of Appendix 1, shall not exceed
the following:
a) at lateral and approach noise measurement points:
108 EPNdB for aeroplanes with maximum certificated
take-off mass of 272 000 kg or over, decreasing linearly
ANNEX 16 - VOLUME I 11-2-1 24111105
Annex 16 - Environmental Protection Volume I
with the logarithm of the mass at the rate of 2 EPNdB
per halving of the mass down to 102 EPNdB at
34 000 kg, after which the limit remains constant;
b) at flyover noise measurement point: 108 EPNdB for
aeroplanes with maximum certificated take-off mass of
272 000 kg or over, decreasing linearly with the
logarithm of the mass at the rate of 5 EPNdB per halving
of the mass down to 93 EPNdB at 34 000 kg, after
which the limit remains constant.
Note.- See Attachment Afor equationsfor the calculation
of noise levels as ajirnction of take-oflmass.
2.4.2 The maximum noise, levels of those aeroplanes
covered by 2.1.2, when determined in accordance with the
noise evaluation method of Appendix 1, shall not exceed the
following:
2.4.2.1 At lateral noise measurement point
Note.- See Attachment A for equations for the calculation
of noise levels as a function of take-off mass.
2.5 Trade-offs
If the maximum noise levels are exceeded at one or two
measurement points:
a) the sum of excesses shall not be greater than 4 EPNdB,
except that in respect of four-engined aeroplanes powered
by engines with a bypass ratio of 2 or more and for
which the application for a certificate of airworthiness
for the prototype was accepted, or another equivalent
prescribed procedure was carried out by the certificating
authority, before I December 1969, the sum of any
excesses shall not be greater than 5 EPNdB;
b) any excess at any single point shall not be greater than
3 EPNdB; and
106 EPNdB for aeroplanes with maximum certificated take-off c) any excesses shall be offset by corresponding reductions
mass of 400 000 kg or over, decreasing linearly with the at the other point or points.
logarithm of the mass down to 97 EPNdB at 35 000 kg, after
which the limit remains constant.
2.4.2.2 Atjlyover noise memuremen! point
a) Aeroplanes with two engines or less
104 EPNdB for aeroplanes with maximum certificated
take-off mass of 325 000 kg or over, decreasing linearly
with the logarithm of the mass at the rate of 4 EPNdJ3
per halving of mass down to 93 EPNdB, after which the
limit remains constant.
b) Aeroplanes with three engines
As a) but with 107 EPNdB for aeroplanes with maximum
certificated take-off mass of 325 000 kg or over
or
as defined by 2.4.1 b), whichever is the lower.
　
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