820
14 CFR Ch. I (1–1–19 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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