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greater than 2 are 107 EPNdB for maximum weights of 385,000 kg (850,000 lb) or more, reduced
by 4 dB per halving of the weight down to 92 EPNdB for maximum weights of 28,700 kg
(63,177 lb) or less. Aircraft with a by−pass ratio less than 2 only need meet the Stage 2 limits.
2.5.1 Trade−off sum of excesses not greater than 3 EPNdB and no excess greater than 2 EPNdB.
2.6.1.1 For airplanes that do not have turbo−jet engines with a by−pass ratio of 2 or more, the following
apply:
a) four−engine airplanes − 214 meters (700 feet);
b) all other airplanes − 305 meters (1,000 feet).
For all airplanes that have turbo−jet engines with a by−pass ratio of 2 or more, the following apply:
a) four−engine airplanes − 210 meters (689 feet);
b) three−engine airplanes − 260 meters (853 feet);
c) airplanes with fewer than three engines − 305 meters (1,000 feet).
The power may not be reduced below that which will provide level flight for an engine inoperative
or that will maintain a climb gradient of at least 4 percent, whichever is greater.
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.
31 JULY 08
AIP
United States of America
GEN 1.7−64
15 MAR 07
Nineteenth Edition Federal Aviation Administration
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.
　
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