Pt. 36, App. H

14 CFR Ch. I (1-1-18 Edition)

radar tracking, theodolite triangulation,
laser trajectography, photo scaling, or differential 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 FAAapproved equipment.

nshattuck on DSK9F9SC42PROD with CFR

Section H36.103 Takeoff test conditions.
(a) This section, in addition to the applicable requirements of sections H36.101 and
H36.205(b) of this appendix, applies to all
takeoff noise tests conducted under this appendix 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 follows:
(1) An airspeed of either Vy Section5 knots or the
lowest approved speed Section5 knots for the climb
after takeoff, whichever speed is greater,
must be established and maintained throughout 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 meters) from the noise measuring station, the
helicopter must be stabilized at the maximum takeoff power that corresponds to
minimum installed engine(s) specification
power available for the reference ambient
conditions or gearbox torque limit, whichever is lower.
(4) The helicopter must be maintained
throughout the 10 dB-down time interval at
the best rate of climb speed Vy Section5 knots, or
the lowest approved speed for climb after
takeoff, whichever is greater, for an ambient
temperature of 25 SectionC at sea level.
(5) The average rotor speed must not vary
from the maximum normal operating rotor
RPM by more than Section1.0 percent during the 10
dB-down time interval.
(6) The helicopter must stay within Section10Section or
Section65 feet (Section20 meters), whichever is greater,
from the vertical above the reference track
throughout the 10dB-down time interval.
(7) A constant takeoff configuration selected 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, Vy.

Section H36.105 Flyover test conditions.
(a) This section, in addition to the applicable requirements of sections H36.101 and
H36.205(c) of this appendix, applies to all flyover noise tests conducted under this appendix 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 tailwind component with simultaneous measurements at all three noise measuring stations - 
(1) In level flight cruise configuration;
(2) At a height of 492 feet Section30 feet (150 Section9
meters) above the ground level at the flighttrack noise measuring station; and
(3) The helicopter must fly within Section10Section or
Section65 feet (Section20 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 conducted - 
(1) At a speed of 0.9VH; 0.9VNE; 0.45VH + 65
kts (0.45VH + 120 km/h); or 0.45VNE + 65 kts
(0.45VNE + 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 Section1.0 percent during
the 10 dB-down time interval.
(3) With the power stabilized during the period 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 Section5 knots (9
km/hr).
Section H36.107 Approach test conditions.
(a) This section, in addition to the requirements of sections H36.101 and H36.205(d) of
this appendix, applies to all approach tests
conducted under this appendix 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
the three noise measuring stations) - 
(1) On an approach slope of 6Section Section0.5Section;
(2) At a height of 394 Section33 feet (120 Section10 meters)
(3) The helicopter must fly within Section10Section or
Section65 feet (Section20 meters) lateral deviation tolerance, whichever is greater, from the vertical
above the reference track throughout the 10
dB-down time interval;
(4) At stabilized airspeed equal to the certificated best rate of climb Vy, or the lowest
approved speed for approach, whichever is
greater, with power stabilized during the approach 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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