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and 12 of this Annex.
Item 16. The overflight noise level in the corresponding
unit for documents issued under Chapters 6, 8
and 1 1 of this Annex.
Item 17. The take-off noise level in the corresponding
unit for documents issued under Chapters 8 and
10 of this Annex.
Item 18. Statement of compliance, including a reference
to Annex 16, Volume I.
Item 4. Nationality or common mark and registration
marks. Item 19. Date of issuance of the noise certification
document.
Item 5. Manufacturer and manufacturer's designation of
aircraft. Item 20. Signature of the off~ccris suing it.
Item 6. Aircraft serial number. 1.6 Item headings on the noise certification documents
shall be uniformly numbered in Arabic numerals, as indicated
Item 7. Engine manufacturer, type and model. in 1.5, so that on any noise certification document the number
will, under any arrangement, refer to the same item heading,
Item 8. Propeller type and model for propeller-driven except where the information in Items I through 6 and Items 18
aeroplanes. through 20 is given in the certificate of airworthiness, in which
ANNEX 16 - VOLUME I 11-1-1 24/11/05
Annex 16 - Environmental Protection Volume I
case the numbering system of the certificate of airworthiness
according to Annex 8 shall prevail.
1.7 An administrative system for implementation of noise
certification documentation shall be developed by the State of
Registry.
Note.- See Attachment G for guidance on the formar and
structure of noise certification documentation.
1.8 Contracting States shall recognize as valid a noise certification
granted by another Contracting State provided that
the requirements under which such certification was granted
are at least equal to the applicable Standards specified in this
Annex.
1.9 A Contracting State shall suspend or revoke the noise
certification of an aircraft on its register if the aircraft ceases
to comply with the applicable noise Standards. The State of
Registry shall not remove the suspension of a noise
certification or grant a new noise certification unless the aircraft
is found, on reassessment, to comply with the applicable
noise Standards.
1.10 Unless otherwise specified in this volume of the
Annex, the date to be used by Contracting States in determining
the applicability of the Standards in this Amex shall be the date
of application for a type certificate, or the date of application
under an equivalent prescribed procedure by the certificating
authority. The application shall be effective for a duration equal
to the period applied in the designation of the airworthiness
regulations appropriate to the aircraft type, except in special
cases where the certificating authority accepts an extension of
this period.
1.11 When this period of effectivity is exceeded, the date
to be used in determining the applicability of the Standards in
this Amex shall be thc date of issuc of thc typc certificate, or
the date of issue of approval under an equivalent prescribed
procedure, less the duration of effectivity.
CHAPTER 2. SUBSONIC JET AEROPLANES - APPLICATION FOR
CERTIFICATE OF AIRWORTHINESS FOR THE PROTOTYPE ACCEPTED
BEFORE 6 OCTOBER 1977
2.1 Applicability
Note.- See also Chapter 1. 1.9.
2.1.1 The Standards of this chapter shall be applicable to
all subsonic jet aeroplanes for which either the application for
a certificate of airworthiness for the prototype was acceptcd, or
another equivalent prescribed procedure was carried out by the
certificating authority, before 6 October 1977, except those
aeroplanes:
a) requiring a runway length1 of 610 m or less at maximum
certificated mass for airworthiness; or
b) powered by engines with a bypass ratio of 2 or more and
tor which a certificate of airworthiness for the individual
aeroplane was first issued before 1 March 1972; or
c) powered by ebgines with a bypass ratio of less than 2
and 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, before 1 January 1%9, and for
which a certificate of airworthiness for the individual
aeroplane was first issued before 1 January 1976.
2.1.2 The Standards of this chapter shall also be applicable
to derived versions of all aeroplanes covered by 2.1.1 for which
the application for certification of a change in type design was
accepted, or another equivalent procedure was carried out by
the certificating authority, on or after 26 November 198 1.
2.1.3 Notwithstanding 2.1.1 and 2.1.2, it may be recognized
　
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