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up to 788 kg and increasing linearly with the logarithm of the
helicopter mass at a rate of 3 decibels per doubling of mass
thereafter.
11.4.2 For helicopters specified in 11.1.4, the maximum
noise levels, when determined in accordance with the noise
evaluation method of Appendix 4, shall not exceed 82 decibels
SEL for helicopters with maximum certificated take-off mass,
at which the noise certification is requested, of up to 1 417 kg
and increasing linearly with the logarithm of the helicopter
Illass at a rate of 3 decibels per doublir~go f rrlass thereafter.
Note.- Helicouters which comulv with the Standards with 11.5 Noise certification reference procedure
<
internal loads may be excepted when carrying external loacls
or external equipment, ifsuch operations are conducted at a
gross mass or with other operating parameters which are in 11.5.1 General conditions
excess of those certijicated for airworthiness with internal
loacls. 11.5.1.1 The reference procedure shall comply with the
appropriate airworthiness requirements and shall be approved
11.1.6 An applicant under 11.1.1, 11.1.2, 1 1.1.3 and by the certificating authority.
1 1.1.4 may alternatively elect to show compliance with
Chapter 8 instead of complying with this chapter. 11.5.1.2 Except as otherwise approved, the overflight
reference procedure shall be as defined in 11.5.2.
11.2 Noise evaluation measure 11.5.1.3 When it is shown by the applicant that the design
characteristics of the helicopter would prevent flight being
The noise evaluation measure shall be the sound exposure conducted in accordance with 11.5.2 the reference procedure
level (SEL) as described in Appendix 4. shall be permitted to depart from the standard reference
ANNEX 16 - VOLUME I 11-11-1 2411 1/05
Annex 16 - Environmental Protection Volume I
procedure, with the approval of the certificating authority, but
only to the extent demanded by those design characteristics
which make compliance with the reference procedures
impossible.
11.5.1.4 The reference procedure shall be established for
the following reference atmospheric conditions:
a) sea level atmospheric pressure of 1 013.25 hPa;
b) ambient air temperature of 25°C;
c) relative humidity of 70 per cent; and
d) zero wind.
11.5.1.5 The maximum normal operating rpm shall be
taken as the highest rotor speed corresponding to the airworthiness
limit imposed by the manufacturer and approved
by the certificating authority for overflight. Where a tolerance
on the highest rotor speed is specified, the maximum normal
operating rotor speed shall be taken as the highest rotor speed
about which that tolerance is given. If rotor speed is automatically
linked with flight condition, the maximum normal
operating rotor speed corresponding with that flight condition
shall be used during the noise certification procedure. If rotor
speed can be changed by pilot action, the highest normal operating
rotor speed specified in the flight manual limitation
section for power-on conditions shall be used during the noise
certification procedure.
1 1.5.2 Reference procedure
11 3.2.1 The reference procedure shall be established as
follows:
a) the helicopter shall be stabilized in level flight overhead
the flight path reference point at a height of 150 m
(492 A) * 15 m (50 ft);
b) a speed of 0.9 VH or 0.9 VNE or 0.45 VH + 120 kmlh
(65 kt) or 0.45 VNE + 120 kmih (65 kt), whichever is the
least, shall be maintained throughout the overflight
procedure. For noise certification purposes, VH is defined
as the airspeed in level flight obtained using the torque
corresponding to minimum engine installed, maximum
continuous power available for sea level pressure
(1 013.25 hPa), 25°C ambient conditions at the relevant
maximum certificated mass. VNE is defined as the not-toexceed
airworthiness airspeed imposed by the manufacturer
and approved by the certificating authority;
c) the overflight shall be made with the rotor speed stabilized
at the maximum normal operating rpm certificated
for level flight;
d) the helicopter shall be in the cruise configuration; and
e) the mass of the helicopter shall be the maximum takeoff
mass at which noise certification is requested.
11.5.2.2 The value of VH andlor VNE used for noise
certification shall be quoted in the app~oved flight manual.
11.6 Test procedures
11.6.1 The test procedures shall be acceptable to the
airworthiness and noise certificating authorities of the State
issuing the certificate.
11.6.2 The test procedure and noise measurements shall be
conducted and processed in an approved manner to yield the
　
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