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Note I.- For [he rill-)uror aircra/l in aeruplanc mode,
rllew is no mprim~~nmoi se level.
6.1.3 Except in conditions specified in 6.1.4. the take-OK
overflight and appmach reference pmedures should be those
defined in 6.2, 6.3 and 6.4. respectively.
6.1.4 When it is shown by the applicant that the design
characteristics of the tilt-rotor aircraft would prevent a flighl
from bcii~g conducted it\ accordance with 6.2. 6.3 or 6.4. the
reference procedures should:
a) depart 6om the reference procedures defined in 6.2, 6.3
or 6.4 only to the extent demanded by those design
characteristics which make compliilnce with the rcfcrence
procedures impossible; and
No~e2 .- 17TOU~.or~r~ermsioodne is all qpproved con$@rr.- b) be approved by the certificating authority,
otrons andjlight mode.? ~2ilerrr he aksrgn operating rotor speed
is flrar wed for hover operazion~ 6.1.5 The rtference procedures shol~ld be c3tablished for
the following rekrence atmospheric conditions:
C) AI tile approach jlighr p t h reference point: 1 10 EPN dB
for tilt-rotor a~rcraft in VTOUconversion mode with a) sea level atmospheric pressure of 1 0 13.25 hPa;
maximum cernficated take-off mass, at which the noise b) ambient air temperature of 2S6C, i.e. TSA + 10°C;
certification is requested, of 80 MX) kg and over and
decreasing lincarly with the logarithmof the tilt-rotor c) relative hurnid~ty of 70 per cent; and
aircraft mass at a rate of 3 EPNdB per halving of rnass
down to 90 EPNdB after which the lirnit is constant. d) zero wind.
Note.-- The equations for the colatlotion of noise levels as
a function of rake@ moss presented in Section 8 of
Aftochmenr A, for Conditions Described in Chapter. 8, are
consisfenf wit11 the maximum noise levels dejined in these
guidelines.
5. TRADE-OFFS
[f the maximum noise levels arc exceeded at one or two
measurement points:
a) the sum of excesses should not be greater than 4 EPNdB;
6.1.6 In 6.2 d), 6.3 d) and 6.4 c), the maximum normal
operating rpm should be taken as the highest rotor speed fbr
each reference procedure corresponding to the airworthiness
litnit imposed by the manufacturer and approved by the certificating
authority. Where a tolerance on the highest mtor speed
is specified, the maximum normal operating rotor speed
should be taken as the highest rotor speed about which that
tolerance is given. If the rotor speed is automatically linked
with the flight condition, the maximum normal operating rotor
speed corresponding with that night condition should be used
during the nose certification procedure. If the mtor speed can
be changed by pilot action, the highest n m a l rotor speed
specified in the flight manual limitation section for powerdn
conditions sbwld lx used during the noise certification
b) any excess at any single point should not bc water than procedure for Lhe correspondmg night condition.
3 EPNdB; and
c) any excess should be offset by correspondi~~regd uctions 6.2 Take-off reference procedure
at the other point or points.
The take-off reference flight pmcedure should be established
as follows:
6. NOISE CERTIFICATION
REFERENCE PROCEDURES
a) a constant take-off configuration, including nacelle
angle, selected by the applicant should be maintained
throughout the take-off reference procedure:
6.1 General conditions b) the tilt-rotor aircraft should be stabilized at the maxirnum
&-off power corresponding to minimum
6.1.1 The nferencc procedures should cornply with the installed engine@) specification power available for the
appropriate airworthiness rquiremcnts. reference ambient conditions or gearbox torque lirnit,
whichever is lower. nnd along a path starting from a
6.1.2 The reference procedures and flight paths should be pomt located 500 m prior to the flight path reference
approved by the certificating authority. point, at 20 m (65 ft) above the ground;
24/11/05 ATT F-2
Attachment F Annex I6 - Environrnenfaf Protembn
C) the nacelle angle and the corresponding best rate of
chmb speed, or the lowest approved speed for the climb
after take-off, whichever is the greater, should be maintained
throughout rhe take+ff reference procedure:
dl the steady climb should be made with the rotor speed
stabilized at the maximum n m a l operating rpm certificated
for take-off;
e) the mass of the tilt-rotor aircraft should be the rnaximurn
take-off mass at which noise certification is requested;
and
comsponding 0.9VMCP or 0.9VM0. whichever IS
lesser, cemficated for level flight.
Note f .- I.br noise certification purposes. VbKp is
defined as the maximrim operatiilg limit airspeed for
　
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