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all propeller-driven aeroplanes-, including their derived versions,
of over 5 700 kg maximum certificated take-off
mass for which either the application for a certificate of
airworthiness for the prototype was accepted, or another
equivalent prescribed procedure was carried out by the
certificating authority, on or after 6 October 1977 and before
I January 1985.
5.1.3 The Standards of Chapter 2, with the exception of
Sections 2.1 and 2.4.2, shall be applicable to derived versions
and individual aeroolanes of over 5 700 kg maximum certificated
take-off mass' and to which ~tandariso f Chapter 6 do
not apply and are of the type for which the application for a
5.1.5 Notwithstanding 5.1.2 to 5.1.4, it may be recognized
by a Contracting State that the following situations for
jet aeroplanes and propeller-driven heavy aeroplanes on its
registry 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
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 from a required maintenance
action.
5.2 Noise measurements
5.2.1 Noise evaluation measure
certificate of airworthiness for the prototype was accepted, or
another equivalent prescribed procedure was carried out by The noise evaluation measure shall be the effective perceived
the certificating authority, before 6 October 1977, and for
noise level in EPNdB as described in Appendix 2.
which a certificate of airworthiness for the individual
aeroplane was issued on or after 26 November 198 1. 5.3 Noise measurement points
5.1.4 The Standards of Chapter 3, with the exception of
Section 3.1, shall be applicable to all propeller-driven 5.3.1 Reference noise measurement points
aeroplanes, including their derived versions, of over 5 700 kg
An aeroplane, when tested in accordance with these Standards,
shall not exceed the noise levels specified in 5.4 at the
1. With no stopway or clearway. following points:
ANNEX 16 - VOLUME I 11-5-1 24/11/05
Annex I6 - Environmental Protection Volume I
a) lateral reference noise measurement point: the point on
a line parallel to and 450 m from the runway centre line,
or extended runway centre line, where the noise level is
a maximum during take-off;
b) jlyover reference 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 reference noise measurement point: the point
on the ground, on the extended centre line of the runway,
2 000 m from the threshold. On level ground this corresponds
to a position 120 m (394 ft) vertically below the
3' descent path originating from a point 300 m beyond
the threshold.
5.3.2 Test noise measurement points
5.3.2.1 If the test noise measurement points are not
located at the reference noise measurement points, any corrections
for the difference in position shall be made in the same
manner as the corrections for the differences between test and
reference flight paths.
5.3.2.2 Sufficient lateral test noise measurement points
shall be used to demonstrate to the certificating authority that
the maximum noise level on the appropriate lateral line has
been clearly determined. Simultaneous measurements shall be
made at one test noise measurement point at a symmetrical
position on the other side of the runway.
5.3.2.3 The applicant shall demonstrate to the certificating
authority that during flight test, latemiand flyover noise levels
were not separately optimized at the expense of each other.
5.4 Maximum uoise levels
The maximum noise levels, when determined in accordance
with the noise evaluation method of Appendix 2, shall not
exceed the following:
a) at lateral reference noise measurement point;
96 EPNdB constant limit for aeroplanes with maximum
take-off mass, at which the noise certification is
requested, up to 34 000 kg and increasing linearly
with the logarithm of aeroplane mass at the rate of
2 EPNdB per doubling of mass from that point until the
limit of 103 EPNdB is reached, after which the limit is
constant;
b) at jlyover reference noise memurement point:
　
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