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measured immediately before, after, or during each test at the
observation points prescribed in Section 2 or this appendix
shall be reported:
a) air temperature and relative humidity; and
b) maximum, minimum and average wind velocities.
4.1.4 Comments on local topography, ground cover, and
events that might interfere with sound recordings shall be
reported.
4.1.5 The following aeroplane information shall be
reported:
a) type, model and serial numbers of aeroplane, engine(s)
and propelle~fs);
b) any modifications or non-standard equipment likely to
affect the noise characteristics of the aeroplane;
number. At a propeller helical tip Mach number above 0.70
and at or below 0.80 no correction is required if the test helical
tip Mach number is within 0.007 of the reference helical tip
Mach number. Above a helical tip Mach number of 0.80 no
correction is required if the helical tip Mach number is within
0.005 of the reference helical tip Mach number. If the test
power at any helical tip Mach number is within 10 per cent of
the reference power, no correction for source noise variation
with power is required. No corrections are to be made for
power changes for fixed pitch propeller-driven aeroplanes. If
test propeller helical tip Mach number and power variations
from reference conditions are outside these constraints,
corrections based on data developed using the actual test
aeroplane or a similar configured aeroplane with the same
engine and propeller operating as the aeroplane being certificated
shall be used as described in Section 4.1 of the Environmental
Technical Manual on the Use of Procedures in the
Noise Certification of Aircraft (Doc 9501).
4.2.2 Correction of noise
received on the ground
The noise measurements made at heights different from 300 m
(985 ft) shall be adjusted to 300 m (985 A) by the inverse
square law.
c) maximum certificated take-off mass;
4.2.3 Performance correction
d) for each overflight, airspeed and air temperature at the
flyover altitude determined by properly calibrated
instruments;
e) for each overflight, engine performance as manifold
pressure or power, propeller speed in revolutions per
minute and other relevant parameters determined by
properly calibrated instruments;
f ) aeroplane height above ground (see 2.3.2);
g) corresponding manufacturer's data for the reference
conditions relevant to 4.1.5 d) and e).
4.2 Data correction
4.2.1 Correction of noise at source
4.2.1.1 When so specified by the certificating authority,
corrections for differences between engine power achieved
during the tests and the power that would be achieved at
settings corresponding to thc highest power in the normal
operating range by an average engine of the type under reference
conditions shall be applied using approved methods.
4.2.1.2 At a propeller helical tip Mach number at or
below 0.70 no correction is required if the test helical tip Mach
number is within 0.014 of the reference helical tip Mach
Note.- The performance correction is intended to credit
higher peformance aeroplanes based on their abiliv to climb
at a steeper angle and to fly the truflc pattern ut a lower
power setting. Also, this correction penalizes aeroplanes with
limited performance capability which results in lower rates of
climb and higher power settings in the traflic pattern.
4.2.3.1 A performance correction determined for sea
level, 15°C conditions and limited to a maximum of 5 &(A)
shall be applied using the method described in 4.2.3.2 and
added algebraically to the measured value.
4.2.3.2 The performance correction shall be calculated by
using the following formula:
where D,, = Take-off distance to 15 m at maximum certificated
take-off mass and maximum take-off
power (paved runway)
WC = Best rate of climb at maximum certificated
take-off mass and maximum take-off power
Vy = Climb speed corresponding to WC at maximum
take-off power and expressed in the
same units.
APP 3-3 24/11/05
Annex I6 - Environmental Protection Volume 1
Note.- When take-off distance is not certificated, t h e m r e
of 610 m for single-engined aeroplanes and 825 m for
multi-engined aeroplanes is used.
4.3 Validity of results
4.3.1 Thc measuring point shall be overflown at least four
times. The test results shall produce an average dB(A) value
and its 90 per cent confidence limits, the noise level being the
arithmetic average of the corrected acoustical measurements
for all valid test runs over the measuring point.
4.3.2 The samples shall be large enough to establish
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