spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Pt. 36, App. K

corresponding to the airworthiness limit imposed by the manufacturer. For configurations for which the rotor speed automatically links with the flight condition, use the
maximum normal operating rotor speed corresponding with the reference flight condition. For configurations for which the rotor
speed can change by pilot action, use the
highest normal rotor speed specified in the
flight manual limitation section for the reference conditions.
K6.2 Takeoff Reference Procedure. The takeoff reference flight procedure is as follows:
(a) A constant takeoff configuration must
be maintained, including the nacelle angle
selected by the applicant;
(b) The tiltrotor power must be stabilized
at the maximum takeoff power corresponding to the minimum installed engine(s) specification power available for the
reference ambient conditions or gearbox
torque limit, whichever is lower. The
tiltrotor power must also be stabilized along
a path starting from a point located 1,640
feet (500 m) before the flight path reference
point, at 65 ft (20 m) above ground level;
(c) The nacelle angle and the corresponding best rate of climb speed, or the
lowest approved speed for the climb after
takeoff, whichever is the greater, must be
maintained throughout the takeoff reference
procedure;
(d) The rotor speed must be stabilized at
the maximum normal operating RPM certificated for takeoff;
(e) The weight (mass) of the tiltrotors
must be the maximum takeoff weight (mass)
as requested for noise certification; and
(f) The reference takeoff flight profile is a
straight line segment inclined from the
starting point 1,640 feet (500 m) before to the
center noise measurement point and 65 ft (20
m) above ground level at an angle defined by
best rate of climb and the speed corresponding to the selected nacelle angle and
for minimum specification engine performance.
K6.3 Flyover Reference Procedure. The flyover reference flight procedure is as follows:
(a) The tiltrotor must be stabilized for
level flight along the centerline flyover
flight path and over the noise measurement
reference point at an altitude of 492 ft (150 m)
above ground level;
(b) A constant flyover configuration selected by the applicant must be maintained;
(c) The weight (mass) of the tiltrotor must
be the maximum takeoff weight (mass) as requested for noise certification;
(d) In the VTOL/Conversion mode:
(1) The nacelle angle must be at the authorized fixed operation point that is closest
to the shallow nacelle angle certificated for
zero airspeed;
(2) The airspeed must be 0.9VCON and

(3) The rotor speed must be stabilized at
the maximum normal operating RPM certificated for level flight.
K6.4 Approach Reference Procedure. The approach reference procedure is as follows:
(a) The tiltrotor must be stabilized to follow a 6.0 degree approach path;
(b) An approved airworthiness configuration in which maximum noise occurs must be
maintained;
(1) An airspeed equal to the best rate of
climb speed corresponding to the nacelle
angle, or the lowest approved airspeed for
the approach, whichever is greater, must be
stabilized and maintained; and
(2) The tiltrotor power during the approach
must be stabilized over the flight path reference point, and continue as if landing;
(c) The rotor speed must be stabilized at
the maximum normal operating RPM certificated for approach;
(d) The constant approach configuration
used in airworthiness certification tests,
with the landing gear extended, must be
maintained; and
(e) The weight (mass) of the tiltrotor at
landing must be the maximum landing
weight (mass) as requested for noise certification.
Section K7 Test Procedures
K7.1 [Reserved]
K7.2 The test procedures and noise measurements must be conducted and processed
to yield the noise evaluation measure designated in section K2 of this appendix.
K7.3 If either the test conditions or test
procedures do not comply to the applicable
noise certification reference conditions or
procedures prescribed by this part, the applicant must apply the correction methods described in section H36.205 of Appendix H of
this part to the acoustic test data measured.
K7.4 Adjustments for differences between
test and reference flight procedures must not
exceed:
(a) For takeoff: 4.0 EPNdB, of which the
arithmetic sum of delta 1 and the term Section7.5
log (QK/QrKr) from delta 2 must not in total
exceed 2.0 EPNdB;
(b) For flyover or approach: 2.0 EPNdB.
K7.5 The average rotor RPM must not vary
from the normal maximum operating RPM
by more than Section1.0 percent throughout the 10
dB-down time interval.
K7.6 The tiltrotor airspeed must not vary
from the reference airspeed appropriate to
the flight demonstration by more than Section5 kts
(Section9 km/h) throughout the 10 dB-down time
interval.
K7.7 The number of level flyovers made
with a head wind component must be equal
to the number of level flyovers made with a
tail wind component.
K7.8 The tiltrotor must operate between
Section10 degrees from the vertical or between Section65
feet (Section20 m) lateral deviation tolerance,

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