美国航行情报汇编 AERONAUTICAL INFORMATION PUBLICATION AIP 1(76)

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Chapter 3 
3.1.1  For type design change applications made after 14 August 1989, if an airplane is a Stage 3 airplane prior to a change in type design, it must remain a Stage 3 airplane after the change in type design regardless of whether Stage 3 compliance was required before the change in type design. 
3.3.1 a) 2)  The U.S. has no equivalent provision in 14 CFR Part 36. 
3.3.2.2  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). 14 CFR Part 36 does not require symmetrical measurements to be made at each and every point for propeller.driven airplane sideline noise determination. 
3.6.2.1 c)  Under 14 CFR Part 36, during each test take.off, simultaneous measurements should be made at the sideline noise measuring stations on each side of the runway and also at the take.off noise measuring station. If test site conditions make it impractical to simultaneously measure take.off and sideline noise, and if each of the other sideline measurement requirements is met, independent measurements may be made of the sideline noise under simulated flight path techniques. If the reference flight path includes a power cutback before the maximum possible sideline noise level is developed, the reduced sideline noise level, which is the maximum value developed by the simulated flight path technique, must be the certificated sideline noise value. 

3.6.2.1 d)  14 CFR Part 36 specifies the day speeds and the acoustic reference speed to be the minimum approved value of V2 +10 kt, or the all.engines operating speed at 35 feet (for turbine.engine powered airplanes) or 50 feet (for reciprocating.engine powered airplanes), whichever speed is greater as determined under the regulations constituting the type certification basis of the airplane. The test must be conducted at the test day speeds ±3 kt. 
3.7.4  If a take.off test series is conducted at weights other than the maximum take.off weight for which noise certification is requested: a) at least one take.off test must be at or above that maximum weight; b) each take.off test weight must be within +5 or .10 percent of the maximum weight. If an approach test series is conducted at weights other than the maximum landing weight for which certification is requested: a) at least one approach test must be conducted at or above that maximum weight; b) each test weight must exceed 90 percent of the maximum landing weight. Total EPNL adjustment for variations in approach flight path from the reference flight path and for any difference between test engine thrust or power and reference engine thrust or power must not exceed 2 EPNdB. 
Chapter 5 
5.1.1  Applies to all large transport category aircraft (as they do to all subsonic turbo.jet aircraft regardless of category). Commuter category aircraft, propeller.driven airplanes below 8,640 kg (19,000 lb) are subject to 14 CFR Part 36, Appendix F or to Appendix G, depending upon the date of completion of the noise certification tests. 
Chapter 6 
6.1.1  Applies to new, all propeller.driven airplane types below 19,000 lb (8,640 kg.) in the normal, commuter, utility, acrobatic, transport, or restricted categories for which the noise certification tests are completed before 22 December 1988. 
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. 
　
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