807 

Federal Aviation Administration, DOT 

Pt. 36, App. B 

be made at each and every test noise meas-
urement point at its symmetrical position 
on the opposite side of the runway. The 
measurement points are considered to be 
symmetrical if they are longitudinally with-
in 33 feet (

±

10 meters) of each other. 

Section B36.5 Maximum Noise Levels 

Except as provided in section B36.6 of this 

appendix, maximum noise levels, when deter-
mined in accordance with the noise evalua-
tion methods of appendix A of this part, may 
not exceed the following: 

(a) For acoustical changes to Stage 1 air-

planes, regardless of the number of engines, 
the noise levels prescribed under § 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 max-
imum 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 max-
imum 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 en-

gines: 101 EPNdB for maximum weight of 
850,000 pounds or more; for each halving of 
maximum weight (from 850,000 pounds), re-
duce 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 en-

gines: 103 EPNdB for maximum weight of 
882,000 pounds or more; for each halving of 
maximum weight (from 882,000 pounds), re-
duce 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), re-
duce 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, Para-
graph 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 § 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 § 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 condi-
tions 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 ref-
erence procedures and must be approved by 
the FAA. 

(3) Applicants must use the takeoff and ap-

proach reference procedures prescribed in 
paragraphs (b) and (c) of this section. 

(4) [Reserved] 
(5) The reference procedures must be deter-

mined 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 

°

F (25 

°

C, 

i.e.

, ISA + 10 

°

C); 

(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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