Federal Aviation Administration, DOT

Pt. 36, App. J

with the logarithm of the helicopter weight
(mass) at a rate of 3.0 EPNdB per halving of
the weight (mass) down to 86 EPNdB, after
which the limit is constant.
(ii) For flyover - For a helicopter having a
maximum certificated takeoff weight of
176,370 pounds (80,000 kg) or more, the noise
limit is 104 EPNdB, which decreases linearly
with the logarithm of the helicopter weight
(mass) at a rate of 3.0 EPNdB per halving of
the weight (mass) down to 84 EPNdB, after
which the limit is constant.
(iii) For approach - For a helicopter having
a maximum certificated takeoff weight of
176,370 pounds (80,000 kg) or more, the noise
limit is 109 EPNdB, which decreases linearly
with the logarithm of the helicopter weight
(mass) at a rate of 3.0 EPNdB per halving of
the weight (mass) down to 89 EPNdB, after
which the limit is constant.
(b) Tradeoffs. Except to the extent limited
under Section 36.11(b) of this part, the noise limits
prescribed in paragraph (a) of this section
may be exceeded by one or two of the takeoff, flyover, or approach calculated noise levels determined under section H36.203 of this
appendix if
(1) The sum of the exceedances is not
greater than 4 EPNdB;
(2) No exceedance is greater than 3 EPNdB;
and
(3) The exceedances are completely offset
by reduction in the other required calculated
noise levels.
[Amdt. 36-14, 53 FR 3541, Feb. 5, 1988; 53 FR
4099, Feb. 11, 1988; 53 FR 7728, Mar. 10, 1988, as
amended by Amdt. 36-54, 67 FR 45237, July 8,
2002; Amdt. 36-25, 69 FR 31234, June 2, 2004;
Amdt. 36-25, 69 FR 41573, July 9, 2004; Amdt.
36-30, 79 FR 12045, Mar. 4, 2014; FAA Doc. No.
FAA-2015-3782, Amdt. No. 36-31, 82 FR 46131,
Oct. 4, 2017]

J36.109 Measurement of helicopter noise received
on the ground.
J36.111 Reporting requirements.
J36.113 [Reserved]
PART C - NOISE EVALUATION AND CALCULATION
UNDER Section 36.803

J36.201 Noise evaluation in SEL.
J36.203 Calculation of noise levels.
J36.205 Detailed data correction procedures.
PART D - NOISE LIMITS PROCEDURE UNDER

Section 36.805
J36.301 Noise measurement, evaluation, and calculation.
J36.303 [Reserved]
J36.305 Noise limits.
PART A - REFERENCE CONDITIONS

Section J36.1 General.
This appendix prescribes the alternative
noise certification requirements identified
under Section 36.1 of this part and subpart H of this
part for helicopters in the primary, normal,
transport, and restricted categories having
maximum certificated takeoff weight of not
more than 7,000 pounds including:
(a) The conditions under which an alternative noise certification test under subpart
H of this part must be conducted and the alternative measurement procedure that must
be used under Section 36.801 of this part to measure
the helicopter noise during the test;
(b) The alternative procedures which must
be used under Section 36.803 of this part to correct
the measured data to the reference conditions and to calculate the noise evaluation
quantity designated as Sound Exposure
Level (SEL); and
(c) The noise limits for which compliance
must be shown under Section 36.805 of this part.
Section J36.3 Reference Test Conditions.

APPENDIX I TO PART 36 [RESERVED]
APPENDIX J TO PART 36 - ALTERNATIVE
NOISE CERTIFICATION PROCEDURE
FOR HELICOPTERS UNDER SUBPART H
HAVING A MAXIMUM CERTIFICATED
TAKEOFF WEIGHT OF NOT MORE
THAN 7,000 POUNDS
PART A - REFERENCE CONDITIONS

Sec.
J36.1 General.
J36.3 Reference Test Conditions.
J36.5 [Reserved]

spaschal on DSK3GDR082PROD with CFR

PART B - NOISE MEASUREMENT PROCEDURE
UNDER Section 36.801

J36.101 Noise certification test and measurement
conditions.
J36.103 [Reserved]
J36.105 Flyover test conditions.
J36.107 [Reserved]

(a) Meteorological conditions. The following
are the noise certification reference atmospheric conditions which shall be assumed to
exist from the surface to the helicopter altitude:
(1) Sea level pressure of 2116 pounds per
square foot (76 centimeters mercury);
(2) Ambient temperature of 77 degrees
Fahrenheit (25 degrees Celsius);
(3) Relative humidity of 70 percent; and
(4) Zero wind.
(b) Reference test site. The reference test
site is flat and without line-of-sight obstructions across the flight path that encompasses the 10 dB down points of the A-weighted time history.
(c) Level flyover reference profile. The reference flyover profile is a level flight, 492
feet (150 meters) above ground level as measured at the noise measuring station. The reference flyover profile has a linear flight
track and passes directly over the noise

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