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noise level and to carry out a field check, at one or
more frequencies, of the overall sensitivity of the measuring
system after or before the measurement of the noise level for
a sequence of aircraft uperaliuns.
Note 2.- I f ; due to the microphone being placed in a
structure above the ground, it is impracticable for operating
personnel to calibrate it directly because of its inaccessibility,
it can be useful to provide a calibrated sound source at the
microphone location. This sound source can be a small loudspeakel;
an electrostatic actuatoc or similar device.
4.2 Monitoring concerns the noise produced by a single
aircraft flight, by a series of flights or by a specified type of
aircraft, or by a large number of operations of different
aircraft. Such noise levels vary, for a specific monitoring
location, with variations in flight procedures or meteorological
conditions. In interpretation bf the results of a monitoring
procedure, consideration should therefore be given to the
statistical distribution of the measured noise levels. In
3. This publication was first issued in 1965 by the Central Office of describing the results of a monitoring procedure an appropriate
the International Eleceotechnical Co-ission, 3 rue de VarembC, description of the distribution of the observed noise levels
Geneva, Switzerland. should be provided.
APP 5-3
APPENDIX 6. NOISE EVALUATION METHOD FOR NOISE CERTIFICATION
OF PROPELLER-DRIVEN AEROPLANES NOT EXCEEDING 8 618 kg -
APPLICATION FOR CERTIFICATE OF AIRWORTHINESS FOR
THE PROTOTYPE ACCEPTED ON OR AFTER 17 NOVEMBER 1988
Note.- See Part ZI, Chapter 10.
1. INTRODUCTION
Note 1.- This noise evaluation method includes:
a) noise certification test and measurement conditions,
b) noise unit;
c) measurement of aeroplane noise received on the ground;
d) a~&stments to test data; and
e) reporting of data to the certificating authority and
validity of results.
Note 2.- The instructions and procedures given in the
method are clearly delineated to ensure uniformity during
compliance tests and to permit comparison between tests of
various types of aeroplanes, conducted in various geographical
locations. The method applies only to aeroplanes within
the applicabilig clauses of Part II, Chapter 10.
2. NOISE CERTIFICATION TEST AND
MEASUREMENT CONDITIONS
2.1 General
This section res scribes the conditions under which noise
2.2.2 The tests shall be carried out under the following
atmospheric conditions:
a) no precipitation;
b) relative humidity not higher than 95 per cent and not
lower than 20 per cent and ambient temperature not
above 35OC and not below 2OC;
c) average wind speed shall not exceed 19 kmlh (10 kt) and
crosswind average wind speed shall not exceed 9 km/h
(5 kt);
Note.- Average wind speed is defined over a 30-
second time period.
d) no other anomalous meteorological conditions that would
significantly affect the noise level of the aeroplane when
the noise is recorded at the measuring points specified by
the certificating authority; and
e) the meteorological measurements must be made between
1.2 m and 10 m above ground level. If the measurement
site is within 2 000 m of an airport meteorological
station, measurements from this station may be used.
2.3 Aeroplane testing procedures
certification tests shall be conducted and the measurement
procedures that shall be used to measure the noise made by the 2.3.1 The test procedures and noise measurement proaeroplane
for which the test is conducted. cedure shall be acceptable to the airworthiness and noise
certificating authorities of the State issuing the certification.
2.2 General test conditions
2.2.1 Locations for measuring noise from an aeroplane in
flight shall be surrounded by relatively flat terrain having no
excessive sound absorption characteristics such as might be
caused by thick, matted or tall grass, shrubs or wooded areas.
No obstructions which significantly influence the sound field
from the aeroplane shall exist within a conical space above the
measurement position, the cone being defined by an axis
normal to the ground and by a half-angle 75' from this axis.
2.3.2 The flight test programme shall be initiated at the
maximum take-off mass for the aeroplane, and the mass shall
be adjusted to maximum take-off mass after each hour of flight
time.
2.3.3 The flight test shall be conducted at Vy f 9 knl/h
(5 kt) indicated airspeed.
2.3.4 The aeroplane position relative to the flight path
reference point shall be determined by a method independent
ANNEX 16 - VOLUME I APP 6-1 24/11/05
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