Regulation 4 Noise certificate requirements for UK registered propeller driven aeroplanes

(1)

This regulation shall apply to any civil propeller-driven aeroplane registered in the United Kingdom and falling within one of the categories set out in Volume 1 of Annex 16/1981.

(2)

Subject to regulation 6, an aeroplane to which this regulation applies shall not be used in the territories of member States or EEA States unless there is in force in respect of that aeroplane a noise certificate granted by the CAA certifying that—

(a)

in the case of an aeroplane with a maximum certificated take-off mass which exceeds 5,700 kilograms, other than an aeroplane to which sub-paragraphs (e), (f) or (g) applies, which in the opinion of the CAA—

(i)

(a)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness before 6 October 1977, or

(b)

conforms to a derived version of such a prototype aeroplane, and

(ii)

was first issued with a certificate of airworthiness on or after 26 November 1981,

the aeroplane meets the standards specified in Part II, Chapter 2 of Volume I of Annex 16/1988, less sections 2.1 and 2.4.2 of that Chapter;

(b)

in the case of an aeroplane with a maximum certificated take-off mass which exceeds 5,700 kilograms, other than an aeroplane described in section 6.1.1 of Part II of Volume 1 of Annex 16/1988 and other than an aeroplane to which sub-paragraph (h) applies, which in the opinion of the CAA—

(i)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 1 January 1985 and before 17 November 1988, or

(ii)

conforms to a derived version of such a prototype aeroplane,

the aeroplane meets the standards specified in Part II, Chapter 3 of Volume I of Annex 16/1988;

(c)

in the case of an aeroplane with a maximum certificated take-off mass which exceeds 9,000 kilograms which in the opinion of the CAA—

(i)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 17 November 1988, or

(ii)

conforms to a derived version of such a prototype aeroplane,

the aeroplane meets the standards specified in Part II, Chapter 3 of Volume I of Annex 16/1988;

(d)

in the case of an aeroplane with a maximum certificated take-off mass which exceeds 5,700 kilograms, other than an aeroplane to which sub-paragraphs (f), (g) or (h) applies, which in the opinion of the CAA—

(i)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 6 October 1977 and before 1 January 1985, or

(ii)

conforms to a derived version of such a prototype aeroplane,

the aeroplane meets the standards specified in Part II, Chapter 5 of Volume I of Annex 16/1988;

(e)

in the case of an aeroplane with a maximum certificated take-off mass which does not exceed 9,000 kilograms which in the opinion of the CAA—

(i)

(a)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness before 1 January 1975, or

(b)

conforms to a derived version of such a prototype aeroplane being a derived version in respect of which the CAA accepted an application to modify the certificate of airworthiness for the prototype before 17 November 1988, and

(ii)

was either first issued with a certificate of airworthiness on or after 1 January 1980 or first registered in the United Kingdom on or after that date,

the aeroplane meets the standards specified in Part II, Chapter 6 of Volume I of Annex 16/1988;

(f)

in the case of an aeroplane with a maximum certificated take-off mass which does not exceed 9,000 kilograms which in the opinion of the CAA—

(i)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 1 January 1975 and before 17 November 1988, or

(ii)

the aeroplane meets the standards specified in Part II, Chapter 6 of Volume I of Annex 16/1988,

(g)

in the case of an aeroplane with a maximum certificated take-off mass which does not exceed 9,000 kilograms which in the opinion of the CAA—

(i)

conforms to a derived version of a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 1 January 1975 and before 17 November 1988, and

(ii)

in respect of which the CAA accepted an application to modify the certificate of airworthiness for the prototype on or after 17 November 1988,

the aeroplane meets the standards specified in Part II, Chapter 10 of Volume I of Annex 16/1988;

(h)

subject to sub-paragraph (i), in the case of an aeroplane with a maximum certificated take-off mass which does not exceed 9,000 kilograms and which in the opinion of the CAA—

(i)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 17 November 1988, or

(ii)

conforms to a derived version of such a prototype aeroplane,

the aeroplane, meets the standards specified in Part II, Chapter 10 of Volume I of Annex 16/1988;

(i)

in the case of an aeroplane with a maximum certificated take-off mass which does not exceed 9,000 kilograms and which in the opinion of the CAA—

(i)

conforms to a prototype aeroplane being a prototype in respect of which the CAA accepted an application for a certificate of airworthiness on or after 17 November 1998 and before 17 November 1993, or

(ii)

the areoplane, if it is unable to meet the standards specified in Part II, Chapter 10 of Volume I of Annex 16/1988, meets the standards specified in Part II, Chapter 6 of Volume I of Annex 16/1988;

(j)

in the case of any other aeroplane, the aeroplane complies with requirements which are at least equal to the applicable standards specified in Part II, Chapters 2, 5 or 6 of Volume 1 of Annex 16/1981.