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versions, other than aeroplanes which require a runway1 compliance with the provisions of Annex 16, Volume I,
length of 610 m or less at maximum certificated mass is shown for that change in type design. This applies
for airworthiness, in respect of which either the appli- only to changes resulting from a required maintenance
cation for a certificate of airworthiness for the prototype action.
was accepted, or another equivalent prescribed procedure
was carried out by the certificating authority, on
or after 1 January 2006;
b) all propellerdriven aeroplanes, including their derived
4.2 Noise measurements
4.2.1 Noise evaluation measure
versions, of over 8 618 kg maximum certificated takeoff
mass, for which either the application for a certifi- The noise evaluation measure shall be the effective perceived
cate of airworthiness for the prototype was accepted, or noise level in EPNdB as described in Appendix 2.
another equivalent prescribed procedure was carried out
by the certificating authority, on or after 1 January 2006; 4.3 Reference noise measurement points
and
4.3.1 An aeroplane, when tested in accordance with these
c) all subsonic jet aeroplanes and all propeller-driven aero- Standards, shall not exceed the maximum noise level specified
planes certificated originally as satisfying Annex 16, Val- in 4,4 of the noise measured at the points specified in
ume 1, Chapter 3 or Chapter 5, for which recertification Chapter 3, 3.3.1 a), b) and c).
to Chapter 4 is requested.
Note.- Guidance material on applications for recertifi- 4.3.2 Test noise measurement points
cation is provided in the Environmental Technical Manual on
the Use of Procedures in the Noise Certification of Aircraft ~ h ,pr ovisions of chapter 3, 3.3.2, relating to test noise
(Doc 9501). measurement points shall apply.
4.1.2 Notwithstanding 4.1.1, 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 rcquirc 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;
1. With no stopway or clearway.
4.4 Maximum noise levels
4.4.1 The maximum permitted noise levels are defined in
Chapter 3, 3.4.1.1, 3.4.1.2 and 3.4.1.3, and shall not be
exceeded at any of the measurement points.
4.4.1.1 The sum of the differences at all three measurement
points between the maximum noise levels and the
maximum permitted noise levels specified in Chapter 3,
3.4.1.1, 3.4.1.2 and 3.4.1.3, shall not be less than 10 EPNdB.
ANNEX 16 - VOLUME I 11-41 2411 1105
Annex 16 - Environmental Protection
4.4.1.2 The sum of the differences at any two measurement
points between the maximum noise levels and the
corresponding maximum permitted noise levels specified in
Chapter 3, 3.4.1.1, 3.4.1.2 and 3.4.1.3, shall not be less than
2 EPNdB.
4.5 Noise certification reference procedures
The noise certification reference procedures shall be as
specified in Chapter 3, 3.6.
Volume I
4.6 Test procedures
The test procedures shall be as specified in Chapter 3, 3.7.
4.7 Recertification
For aeroplanes specified in 4.1.1 c), recertification shall be
granted on the basis that the evidence used to determine
compliance with Chapter 4 is as satisfactory as the evidence
associated with aeroplanes specified in 4.1.1 a) and b).
CHAPTER 5. PROPELLER-DRIVEN AEROPLANES OVER 5 700 kg -
APPLICATION FOR CERTIFICATE OF AIRWORTHINESS FOR THE PROTOTYPE
ACCEPTED BEFORE 1 JANUARY 1985
5.1 Applicability maximum take-off mass, for which either the application for
a certificate of airworthiness for the prototype was accepted,
Note 1.- See also Chapter 1, 1.9. or another equivalent prescribed procedure was carried out by
the certifi~atinga uthority, on or after 1 January 1985.
Note 2.- See Attachment E for guidance on interpretation
of these applicability provisions. Note.- The Standards in Chapters 2 and 3 although developed
previously for subsonic jet aeroplanes are considered
5.1.1 The Standards defined hereunder are not applicable suitable for application to other aeroplane types regardless of
to: the type of power installed.
a) aeroplanes requiring a runway1 length of 610 m or less
at maximum certificated mass for airworthiness;
b) aeroplanes specifically designed for fire fighting;
c) aeroplanes specifically designed for agricultural purposes;
d) aeroplanes to which the Standards of Chapter 6 apply;
and
e) aeroplanes to which the Standards of Chapter 10 apply.
5.1.2 The Standards of this chapter shall be applicable to
　
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