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at the maximum normal operating rpm certificated
for approach;
d) the constant approach configuration used in airworthiness
certification tests, with the landing gear extended,
shall be maintained throughout the approach reference
procedure; and
e) the mass of the helicopter at touchdown shall be the
maximum landing mass at which noise certification is
requested.
8.7 Test procedures
8.7.1 The test procedures shall be acceptablc to the
airworthiness and noise certificating authority of the State
issuing the certificate.
Annex 16 - Environmental Protection Volume I
8.7.2 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.
8.7.3 Test conditions and procedures shall be closely
similar to reference conditions and procedures or the acoustic
data shall be adjusted, by the methods outlined in Appendix 2,
to the reference conditions and procedures specified in this
chapter.
8.7.4 Adjustments for differences between test and reference
flight procedures shall not exceed:
a) for ~ake-of 4.0 EPNdB, of which the arithmetic sum of
Al and the term -7.5 log (QK/Q,.Kr) from A2 shall not
in total exceed 2.0 EPNdB;
b) for overj7ight or approach: 2.0 EPNdB.
8.7.5 During the test the average rotor rpm shall not vary
from the normal maximum operating rpm by more than
*I .0 per cent during the 10 dBdown time period.
8.7.6 The helicopter airspeed shall not vary from the
reference airspeed appropriate to the flight demonstration by
more than *9 kmlh (5 kt) throughout the 10 dBdown time
period.
8.7.7 The number of level overflights made with a headwind
component shall be equal to the number of level
overflights made with a tailwind component.
8.7.8 The helicopter shall fly within *10" or *20 m,
whichever is greater, from the vertical above the reference track
throughout the 10 dB-down time period (see Figure 8-1).
8.7.9 The helicopter height shall not vary during overflight
from the reference height at the overhead point by more
than +9 m (30 ft).
8.7.10 During the approach noise demonstration the helicopter
shall be established on a stabilized constant speed
approach within the airspace contained between approach
angles of 5.5" and 6.5".
8.7.11 Tests shall be conducted at a helicopter mass not
less than 90 per cent of the relevant maximum certificated
mass and may be conducted at a mass not exceeding 105 per
cent of the relevant maximum certificated mass. For each of
the three flight conditions, at least one test must be completed
at or above this maximum certificated mass.
Note.- Guidance material on the use of equivalent procedures
is provided in the Environmental Technical Manual on
the Use of Procedures in the Noise Certification of Aircraft
(Doc 9501).
I PNLTM - 10 PNLTM PNLTM + 10 I
Figure 8-1. Helicopter lateral deviation tolerances
CHAPTER 9. INSTALLED AUXILIARY POWER UNITS (APU)
AND ASSOCIATED AIRCRAFT SYSTEMS
DURING GROUND OPERATIONS
Note.- Standardr and Recommended Practices for this
chapter are not yet developed. In the meantime, guidelines
provided in Attachment C may be used for noise certification
of installed auxiliary power units (APU) and associated
aircraft systems in:
a) aN aircraft for which the application for a certificate of
airworthiness for the prototype was accepted, or
another equivalent prescribed procedure was carried
out by the certijkating authority, on or af2er 6 October
1977; and
b) aircraft of existing type design for which the application
for a change of type design involving the basic APU
installation was accepted, or another equivalent prescribed
procedure was carried out by the certijicating
authority, on or after 6 October 1977.
ANNEX 16 - VOLUME I
CHAPTER 10. PROPELLER-DRIVEN AEROPLANES NOT
EXCEEDING 8 618 kg - APPLICATION FOR CERTIFICATE
OF AIRWORTHINESS FOR THE PROTOTYPE OR DERIVED VERSION
ACCEPTED ON OR AFTER 17 NOVEMBER 1988
10.1 Applicability C) the requirements of b) above apply, but which fail to
meet the noise limits of 10.4 b), the noise limits of
Note 1.- See also Chapter 1. 1.9. 10.4 a) shall apply provided that the application for the
derived version was made before 4 November 2004.
Note 2.- See Attachment E for guidance on interpretation
of these applicability provisions.
10.1.1 The Standards of this chapter shall be applicable to
all propeller-driven aeroplanes and their derived versions, with
　
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