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c) the speed shall be the all-engines operating take-off
climb speed selected by the applicant for use in normal
operation, which shall be at least V2 + 19 km/h (V2 +
10 kt) and which shall be attained as soon as practicable
after lift-off and be maintained throughout the take-off
noise certification test;
d) a constant take-off configuration selected by the applicant
shall be maintained throughout the take-off reference procedure
except that the landing gear may be retracted; and
5.7.2 The test procedures and noise measurements shall
be conducted and processed in an approved manner to yield
the noise evaluation measure designated as effective perceived
noise level, EPNL, in units of EPNdB, as described in
Appendix 2.
5.7.3 Acoustic data shall be adjusted by the methods
outlined in Appendix 2 to the reference conditions specified in
this chapter. Adjustments for speed and thrust shall be made as
described in Section 9 of Appendix 2.
5.7.4 If the mass during the test is different from the mass
at which the noise certification is requested, the necessq
EPNL adjustment shall not exceed 2 EPNdB for take-offs and
I EPNdB for approaches. Data approved by the certificating
authority shall be used to determine the variation of EPNL
with mass for both take-off and approach test conditions.
Similarly, the necessary EPNL adjustment for variations in
approach flight path from the reference flight path shall not
exceed 2 EPNdB.
Annex 16 - Environmental Protection Volume I
5.7.5 For the approach conditions the test procedures
shall be accepted if the aeroplane follows a steady glide path
angle of 3" + 0.5".
5.7.6 If equivalent test procedures different from
the reference procedures are used, the test procedures and all
llietllods for adjusting the results to the reference proccdurcs
shall be approved by the certificating authority. The amounts
of the adjustments shall not exceed 16 EPNdB on take-off and
8 EPNdB on approach, and if the adjustments are more than
8 EPNdB and 4 EPNdB respectively, the resulting numbers
shall not be within 2 EPNdB of the limit noise levels specified
in 5.4.
Note.- Guidance material on the use of equivalent procedures
is provided in tlw Environmental Technical Manual on
the Use of Procedures in the Noise Certification of Aircraft
(Doc 9501)
CHAPTER 6. PROPELLER-DRIVEN AEROPLANES NOT EXCEEDING
8 618 kg - APPLICATION FOR CERTIFICATE OF AIRWORTHINESS
FOR THE PROTOTYPE ACCEPTED BEFORE 17 NOVEMBER 1988
6.1 Applicability
Note 1.- See also Chapter 1, 1.9.
Note 2.- See Attachment E for guidance on interpretation
of these applicability provisions.
The Standards of this chapter shall be applicable to all
propeller-driven aeroplanes, except those aeroplanes specifically
designed for aerobatic purposes or agricultural or fire
fighting uses, of a maximum certificated take-off mass not
exceeding 8 6 18 kg for which:
a) the application for the certificate of airworthiness for the
prototype was accepted, or another equivalent prescribed
procedure was canied out by the certificating authority,
on or after 1 January 1975 and before 17 November
1988, except for derived versions for which an application
for a certificate of ainvorthiness was accepted, or
another equivalent procedure was canied out by the
certificating authority, on or after 17 November 1988, in
which case the Standards of Chapter 10 apply; or
b) a certificate of airworthiness for the individual aeroplane
was first issued on or after 1 January 1980.
6.2 Noise evaluation measure
The noise evaluation measure shall be a weighted overall
sound pressure level as defined in International Electrotechnical
Commission (IEC) Publication No. 179.' The
weighting applied to each sinusoidal component of the sound
pressure shall be given as a function of frequency by the
standard reference curve called "A.
6.3 Maximum noise levels
For aeroplanes specified in 6.1 a) and b), the maximum noise
levels, when determined in accordance with the noise
evaluation method of Appendix 3, shall not exceed the
following:
-a 68 dB(A) constant limit up to an aeroplane mass of
600 kg, varying linearly with mass from that point to
1 500 kg, after which the limit is constant at 80 dB(A)
up to 8 618 kg.
Note.- Where an aeroplane comes within the provisions
of Chapter 10, 10.1.2, the limit of 80 dB(A) applies up to
8 61 8 kg.
6.4 Noise certification
reference procedures
The reference procedure shall be calculated under the following
reference atmospheric conditions:
a) sea level atmospheric pressure of 1 013.25 hPa;
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