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the axis.
2.2.3 c) Relative humidity and ambient temperature over the sound path between the aircraft and 10 meters
above the ground at the noise measuring site is such that the sound attenuation in the 8 kHz
one−third octave band is not greater than 12 dB/100 meters and the relative humidity is between
20 and 95 percent. However, if the dew point and dry bulb temperature used for obtaining relative
humidity are measured with a device which is accurate to within one−half a degree Celsius, the
sound attenuation rate shall not exceed 14 dB/100 meters in the 8 kHz one−third octave band.
2.2.3 d) Test site average wind not above 12 kt and average cross−wind component not above 7 kt.
2.3.4 The aircraft position along the flight path is related to the recorded noise 10 dB downpoints.
2.3.5 At least one take−off test must be a maximum take−off weight and the test weight must be within +5
or −10 percent of maximum certificated take−off weight.
Appendix 2
2.2.1 A minimum of two symmetrically placed microphones must be used to define the maximum
sideline noise at the point where the aircraft reaches 305 meters.
31 JULY 08
AIP
United States of America
GEN 1.7−66
15 MAR 07
Nineteenth Edition Federal Aviation Administration
2.2.2 When a multiple layering calculation is required, the atmosphere between the airplane and the
ground shall be divided into layers. These layers are not required to be of equal depth, and the
maximum layer depth must be 100 meters.
2.2.2 b) 14 CFR Part 36 specifies that the lower limit of the temperature test window is 36 degrees
Fahrenheit (2.2 degrees Celsius). Annex 16 provides 10 degrees Celsius as the lower limit for the
temperature test window.
14 CFR Part 36 does not specify that the airport facility used to obtain meteorological condition
measurements be within 2,000 meters of the measurement site.
2.2.2 c) 14 CFR Part 36 imposes a limit of 14 dB/100 meters in the 8 kHz one−third octave band when the
temperature and dew point are measured with a device which is accurate to within one−half a degree
Celsius.
2.2.3 14 CFR Part 36 requires that the limitations on the temperature and relative humidity test window
must apply over the whole noise propagation path between a point 10 meters above the ground and
the helicopter. Annex 16 specifies that the limitations on the temperature and relative humidity test
window apply only at a point 10 meters above the ground.
14 CFR Part 36 requires that corrections for sound attenuation must be based on the average of
temperature and relative humidity readings at 10 meters and the helicopter. Annex 16 implies that
the corrections for sound absorption are based on the temperature and relative humidity measured at
10 meters only.
3.2.6 No equivalent requirement.
3.4.5 For each detector/integrator the response to a sudden onset or interruption of a constant sinusoidal
signal at the respective one−third octave band center frequency must be measured at sampling times
0.5, 1.0, 1.5, and 2.0 seconds after the onset or interruption. The rising responses must be the
following amounts before the steady−state level:
0.5 seconds: 4.0 ± 1.0 dB
1.0 seconds: 1.75 ± 0.75 dB
1.5 seconds: 1.0 ± 0.5 dB
2.0 seconds: 0.6 ± 0.5 dB
3.4.5 (Note 1) No equivalent provision in 14 CFR Part 36.
3.5.2 No equivalent requirement.
5.4 14 CFR Part 36 requires that the difference between airspeed and groundspeed shall not exceed
10 kt between the 10 dB down time period.
8.4.2 14 CFR Part 36 specifies a value of −10 in the adjustment for duration correction. Annex 16
specifies a value of −7.5.
9.1.2, 9.1.3 14 CFR Part 36 always requires use of the integrated procedure if the corrected take−off or approach
noise level is within 1.0 dB of the applicable noise limit.
Appendix 6
4.4.1 The microphone performance, not its dimensions, is specified. The microphone must be mounted
1.2 meters (4 feet) above ground level. A windscreen must be employed when the wind speed is in
excess of 9 km/h (5 kt).
5.2.2 a) Reference conditions are different. Noise data outside the applicable range must be corrected to
77 degrees F and 70 percent humidity.
5.2.2 c) There is no equivalent provision in 14 CFR Part 36. Fixed−pitch propeller−driven airplanes have a
special provision. If the propeller is fixed−pitch and the test power is not within 5 percent of
reference power, a helical tip Mach number correction is required.
31 JULY 08
AIP
United States of America
GEN 1.7−67
15 MAR 07
Federal Aviation Administration Nineteenth Edition
　
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