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816 

14 CFR Ch. I (1–1–18 Edition) 

Pt. 36, App. H 

radar tracking, theodolite triangulation, 
laser trajectography, photo scaling, or dif-
ferential global positioning system. 

(3) The helicopter position along the flight 

path must be related to the noise recorded at 
the noise measuring stations by means of 
synchronized signals recorded at an approved 
sampling rate. The helicopter position must 
be recorded relative to the reference flight 
track during the entire time interval in 
which the recorded signal is within 10 dB of 
PNLTM. Measuring and sampling equipment 
must be approved by the FAA before testing. 

(4) Aircraft performance data sufficient to 

make the corrections required under section 
H36.205 of this appendix must be recorded at 
an FAA-approved sampling rate using FAA- 
approved equipment. 

Section H36.103 Takeoff test conditions. 

(a) This section, in addition to the applica-

ble requirements of sections H36.101 and 
H36.205(b) of this appendix, applies to all 
takeoff noise tests conducted under this ap-
pendix to show compliance with Part 36. 

(b) A test series must consist of at least six 

flights over the flight-track noise measuring 
station (with simultaneous measurements at 
all three noise measuring stations) as fol-
lows: 

(1) An airspeed of either V

y

±5 knots or the 

lowest approved speed ±5 knots for the climb 
after takeoff, whichever speed is greater, 
must be established and maintained through-
out the 10 dB-down time interval. 

(2) The horizontal portion of each test 

flight must be conducted at an altitude of 65 
feet (20 meters) above the ground level at the 
flight-track noise measuring station. 

(3) Upon reaching a point 1,640 feet (500 me-

ters) from the noise measuring station, the 
helicopter must be stabilized at the max-
imum takeoff power that corresponds to 
minimum installed engine(s) specification 
power available for the reference ambient 
conditions or gearbox torque limit, which-
ever is lower. 

(4) The helicopter must be maintained 

throughout the 10 dB-down time interval at 
the best rate of climb speed V

y

±5 knots, or 

the lowest approved speed for climb after 
takeoff, whichever is greater, for an ambient 
temperature of 25 °C at sea level. 

(5) The average rotor speed must not vary 

from the maximum normal operating rotor 
RPM by more than ±1.0 percent during the 10 
dB-down time interval. 

(6) The helicopter must stay within ±10° or 

±65 feet (±20 meters), whichever is greater, 
from the vertical above the reference track 
throughout the 10dB-down time interval. 

(7) A constant takeoff configuration se-

lected by the applicant must be maintained 
throughout the takeoff reference procedure 
with the landing gear position consistent 
with the airworthiness certification tests for 
establishing best rate-of-climb speed, V

y

Section H36.105 Flyover test conditions. 

(a) This section, in addition to the applica-

ble requirements of sections H36.101 and 
H36.205(c) of this appendix, applies to all fly-
over noise tests conducted under this appen-
dix to show compliance with Part 36. 

(b) A test series consists of at least six 

flights. The number of level flights made 
with a headwind component must be equal to 
the number of level flights made with a tail-
wind component with simultaneous measure-
ments at all three noise measuring sta-
tions— 

(1) In level flight cruise configuration; 
(2) At a height of 492 feet ±30 feet (150 ±9 

meters) above the ground level at the flight- 
track noise measuring station; and 

(3) The helicopter must fly within ±10°  or 

±65 feet (±20 meters), whichever is greater, 
from the vertical above the reference track 
throughout the 10 dB-down time interval. 

(c) Each flyover noise test must be con-

ducted— 

(1) At a speed of 0.9V

H

; 0.9V

NE

; 0.45V

H

+ 65 

kts (0.45V

H

+ 120 km/h); or 0.45V

NE

+ 65 kts 

(0.45V

NE

+ 120 km/h), whichever speed is least, 

to be maintained throughout the measured 
portion of the flyover; 

(2) At average rotor speed, which must not 

vary from the maximum normal operating 
rotor RPM by more than ±1.0 percent during 
the 10 dB-down time interval. 

(3) With the power stabilized during the pe-

riod when the measured helicopter noise 
level is within 10 dB of PNLTM. 

(d) The airspeed shall not vary from the 

reference airspeed by more than ±5 knots (9 
km/hr). 

Section H36.107 Approach test conditions. 

(a) This section, in addition to the require-

ments of sections H36.101 and H36.205(d) of 
this appendix, applies to all approach tests 
conducted under this appendix to show com-
pliance with Part 36. 

(b) A test series must consist of at least six 

flights over the flight-track noise measuring 
station (with simultaneous measurements at 
the three noise measuring stations)— 

(1) On an approach slope of 6° ±0.5°; 
(2) At a height of 394 ±33 feet (120 ±10 me-

ters) 

(3) The helicopter must fly within ±10°  or 

±65 feet (±20 meters) lateral deviation toler-
ance, whichever is greater, from the vertical 
above the reference track throughout the 10 
dB-down time interval; 

(4) At stabilized airspeed equal to the cer-

tificated best rate of climb V

y

, or the lowest 

approved speed for approach, whichever is 
greater, with power stabilized during the ap-
proach and over the flight path reference 
point, and continued to a normal touchdown; 
and 

(5) At average rotor speed, which may not 

vary from the maximum normal operating 

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