Federal Aviation Administration, DOT

Pt. 36, App. B

be made at each and every test noise measurement point at its symmetrical position
on the opposite side of the runway. The
measurement points are considered to be
symmetrical if they are longitudinally within 33 feet (Section10 meters) of each other.

spaschal on DSK3GDR082PROD with CFR

Section B36.5 Maximum Noise Levels
Except as provided in section B36.6 of this
appendix, maximum noise levels, when determined in accordance with the noise evaluation methods of appendix A of this part, may
not exceed the following:
(a) For acoustical changes to Stage 1 airplanes, regardless of the number of engines,
the noise levels prescribed under Section 36.7(c) of
this part.
(b) For any Stage 2 airplane regardless of
the number of engines:
(1) Flyover: 108 EPNdB for maximum
weight of 600,000 pounds or more; for each
halving of maximum weight (from 600,000
pounds), reduce the limit by 5 EPNdB; the
limit is 93 EPNdB for a maximum weight of
75,000 pounds or less.
(2) Lateral and approach: 108 EPNdB for
maximum weight of 600,000 pounds or more;
for each halving of maximum weight (from
600,000 pounds), reduce the limit by 2 EPNdB;
the limit is 102 EPNdB for a maximum
weight of 75,000 pounds or less.
(c) For any Stage 3 airplane:
(1) Flyover.
(i) For airplanes with more than 3 engines:
106 EPNdB for maximum weight of 850,000
pounds or more; for each halving of maximum weight (from 850,000 pounds), reduce
the limit by 4 EPNdB; the limit is 89 EPNdB
for a maximum weight of 44,673 pounds or
less;
(ii) For airplanes with 3 engines: 104
EPNdB for maximum weight of 850,000
pounds or more; for each halving of maximum weight (from 850,000 pounds), reduce
the limit by 4 EPNdB; the limit is 89 EPNdB
for a maximum weight of 63,177 pounds or
less; and
(iii) For airplanes with fewer than 3 engines: 101 EPNdB for maximum weight of
850,000 pounds or more; for each halving of
maximum weight (from 850,000 pounds), reduce the limit by 4 EPNdB; the limit is 89
EPNdB for a maximum weight of 106,250
pounds or less.
(2) Lateral, regardless of the number of engines: 103 EPNdB for maximum weight of
882,000 pounds or more; for each halving of
maximum weight (from 882,000 pounds), reduce the limit by 2.56 EPNdB; the limit is 94
EPNdB for a maximum weight of 77,200
pounds or less.
(3) Approach, regardless of the number of
engines: 105 EPNdB for maximum weight of
617,300 pounds or more; for each halving of
maximum weight (from 617,300 pounds), reduce the limit by 2.33 EPNdB; the limit is 98

EPNdB for a maximum weight of 77,200
pounds or less.
(d) For any Stage 4 airplane, the flyover,
lateral, and approach maximum noise levels
are prescribed in Chapter 4, Paragraph 4.4,
Maximum Noise Levels, and Chapter 3, Paragraph 3.4, Maximum Noise Levels, of the
International Civil Aviation Organization
(ICAO) Annex 16, Environmental Protection,
Volume I, Aircraft Noise, Third Edition,
July 1993, Amendment 7, effective March 21,
2002. [Incorporated by reference, see Section 36.6].
(e) For any Stage 5 airplane, the flyover,
lateral, and approach maximum noise levels
are prescribed in Chapter 14, Paragraph 14.4,
Maximum Noise Levels of ICAO Annex 16,
Volume I, Amendment 11-B (Incorporated by
reference, see Section 36.6).
Section B36.6 Trade-Offs
Except when prohibited by sections
36.7(c)(1) and 36.7(d)(1)(ii), if the maximum
noise levels are exceeded at any one or two
measurement points, the following conditions must be met:
(a) The sum of the exceedance(s) may not
be greater than 3 EPNdB;
(b) Any exceedance at any single point
may not be greater than 2 EPNdB, and
(c) Any exceedance(s) must be offset by a
corresponding amount at another point or
points.
Section B36.7 Noise Certification Reference
Procedures and Conditions
(a) General conditions:
(1) All reference procedures must meet the
requirements of section 36.3 of this part.
(2) Calculations of airplane performance
and flight path must be made using the reference procedures and must be approved by
the FAA.
(3) Applicants must use the takeoff and approach reference procedures prescribed in
paragraphs (b) and (c) of this section.
(4) [Reserved]
(5) The reference procedures must be determined for the following reference conditions.
The reference atmosphere is homogeneous in
terms of temperature and relative humidity
when used for the calculation of atmospheric
absorption coefficients.
(i) Sea level atmospheric pressure of 2116
pounds per square foot (psf) (1013.25 hPa);
(ii) Ambient sea-level air temperature of 77
SectionF (25 SectionC, i.e., ISA + 10 SectionC);
(iii) Relative humidity of 70 per cent;
(iv) Zero wind.
(v) In defining the reference takeoff flight
path(s) for the takeoff and lateral noise
measurements, the runway gradient is zero.
(b) Takeoff reference procedure:
The takeoff reference flight path is to be
calculated using the following:
(1) Average engine takeoff thrust or power
must be used from the start of takeoff to the

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