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Chapter 8
General 14 CFR Part 36 (Section 36.1 (h)) defines Stage 1 and Stage 2 noise levels and Stage 1 and Stage 2
helicopters. These definitions parallel those used in 14 CFR Part 36 for turbo−jets and are used
primarily to simplify the acoustical change provisions in Section 36.11.
14 CFR Part 36 (Section 36.805(c)) provides for certain derived versions of helicopters for which
there are no civil prototypes to be certificated above the noise level limits.
8.1.1 a) Applicable to new helicopter types for which application for an original type certificate was made
on or after 6 March 1988.
8.1.1 b) Applicable only to “acoustical changes’’ for which application for an amended or supplemental type
certificate was made on or after 6 March 1988.
8.4 14 CFR Part 36 Appendix H specifies a slightly different rate of allowable maximum noise levels as
a function of helicopter mass. The difference can lead to a difference in the calculated maximum
noise limits of 0.1 EPNdB under certain roundoff condition.
8.6.3.1 b) Does not include the VNE speeds.
8.7 14 CFR Part 36 Appendix H does not permit certain negative corrections. Annex 16 has no
equivalent provision.
8.7.4 EPNL correction must be less than 2.0 EPNdB for any combination of lateral deviation, height,
approach angle and, in the case of flyover, thrust or power.
Corrections to the measured data are required if the tests were conducted below the reference
weight.
Corrections to the measured data are required if the tests were conducted at other than reference
engine power.
8.7.5 The rotor speed must be maintained within one percent of the normal operating RPM during the
take−off procedure.
8.7.8 The helicopter shall fly within ±10 from the zenith for approach and take−off, but within ±5 from
the zenith for horizontal flyover.
31 JULY 08
AIP
United States of America
GEN 1.7−65
15 MAR 07
Federal Aviation Administration Nineteenth Edition
Chapter 10
General Exception from acoustical change rule given for aircraft with flight time prior to 1 January 1955 and
land configured aircraft reconfigured with floats or skis.
10.1.1 Applies to new, amended, or supplemental type certificates for propeller−driven airplanes not
exceeding 8,640 kg (19,000 lb) for which noise certification tests have not been completed before
22 December 1988.
10.4 The maximum noise level is a constant 73 dBA up to 600 kg (1,320 lb). Above that weight, the limit
increases at the rate of 1 dBA/75kg (1 dBA/165 lb) up to 85 dBA at 1,500 kg (3,300 lb) after which
it is constant up to and including 8,640 kg (19,000 lb).
10.5.2, second
phase, d)
For variable−pitch propellers, the definition of engine power is different in the second segment of
the reference path. Maximum continuous installed power instead of maximum power is used.
Chapter 11
11.1 14 CFR Part 36 Appendix J was effective 11 September 1992 and applies to those helicopters for
which application for a type certificate was made on or after 6 March 1986.
11.4 14 CFR Part 36 Appendix J specifies a slightly different rate of allowable maximum noise levels as
a function of helicopter mass. The difference can lead to a difference in the calculated maximum
noise limits of 0.1 EPNdB under certain roundoff condition.
11.6 14 CFR Part 36 Appendix J prescribes a ±15 meter limitation on the allowed vertical deviation
about the reference flight path. Annex 16 has no equivalent provision.
PART V
General No comparable provision exists in U.S. Federal Regulations. Any local airport proprietor may
propose noise abatement operating procedures to the FAA which reviews them for safety and
appropriateness.
Appendix 1
General Sections 3, 8, and 9 of Appendix 1 which contain the technical specifications for equipment,
measurement and analysis and data correction for Chapter 2 aircraft and their derivatives differ in
many important aspects from the corresponding requirements in Appendix 2 which has been
updated several times. 14 CFR Part 36 updates have generally paralleled those of Appendix 2 of
Annex 16. These updated requirements are applicable in the U.S. to both Stage 2 and Stage 3
aircraft and their derivatives.
2.2.1 A minimum of two microphones symmetrically positioned about the test flight track must be used to
define the maximum sideline noise. This maximum noise may be assumed to occur where the
aircraft reaches 305 meters (1,000 feet), except for four−engine, Stage 2 aircraft for which 439
meters (1,440 feet) may be used.
2.2.2 No obstructions in the cone defined by the axis normal to the ground and the half−angle 80 from
　
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