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89 EPNdB constant limit for aeroplanes with maximum
take-off mass, at which the noise certification is
requested, up to 34 000 kg and increasing linearly with
the logarithm of aeroplane mass at the rate of 5 EPNdB
per doubling of mass from that point until the limit of
106 EPNdB is reached, after which the limit is constant;
and
c) at approach rejerence noise memurement point:
98 EPNdB constant limit for aeroplanes with maximum
take-off mass, at which the - noise certification is
requested, up to 34 000 kg and increasing linearly
with the logarithm of aeroplane mass at the rate of
2 EPNdB per doubling of mass from that point until the
limit of 105 EPNdB is reached, after which the limit is
constant.
Note.- See Attachment A for equationsfor the calculation
of noise levels os afinction of take-oflmass.
5.5 Trade-offs
If the maximum noise levels are exceeded at one or two
measurement points:
a) the sum of excesses shall not be greater than 3 EPNdB;
b) any excess at any single point shall not be greater than
2 EPNdB; and
c) any excesses shall be offset by corresponding reductions
at the other point or points.
5.6 Noise certification
reference procedures
5.6.1 General conditions
5.6.1.1 The reference procedures shall comply with the
appropriate airworthiness requirements.
5.6.1.2 The calculations of rererence procedures and flight
paths shall be approved by the certificating authority.
5.6.1.3 Except in conditions specified in 5.6.1.4, the
take-off and approach reference procedures shall be those
defined in 5.6.2 and 5.6.3 respectively.
5.6.1.4 When it is shown by the applicant that the design
characteristics of the aeroplane would prevent flight being
conducted in accordance with 5.6.2 and 5.6.3, the reference
procedures shall:
a) depart from the reference procedures defined in 5.6.2
and 5.6.3 only to the extent demanded by those
design characteristics which make compliance with the
procedures impossible; and
Part II - Chapter 5 Annex 16 - Environmental Protection
b) be approved by the certificating authority. e) the mass of the aeroplane at the brake release shall be
the maximum take-off mass at which the noise certifi-
5.6.1.5 The reference procedures shall be calculated cat~onis requested.
under the following reference atmospheric conditions:
5.6.3 Approach reference procedure
a) sea level atmospheric pressure of 1 013.25 hPa;
The approach reference flight path shall be calculated as
b) ambient air temperature of 25"C, i.e. ISA + 10°C except follows:
that at the discretion of the certificating authority, an
alternative reference ambient air temperature of 15"C, a) the aeroplane shall be stabilized and following a 3" glide
i.e. ISA may be used; path;
c) relative humidity of 70 per cent; and
d) zero wind.
b) the approach shall be made at a stabilized airspeed of not
less than 1.3 Vs + 19 km/h (1.3 Vs + 10 kt) with power
stabilized during approach and over the measuring point
and continued to a normal touchdown;
5.6.2 Take-off reference procedure c) the constant approach configuration used in the airworthiness
certification test, but with the landing gear
The take-off flight path shall be calculatbd as follows: down, shall be maintained throughout the approach
reference procedure;
a) average take-off power shall be used from the start of d) the mass of the aeroplane at the touchdown shall be
take-off to the point where at least the height above run- the maximum landing mass permitted in the approach
way level shown below is reached. The take-off power configuration defined in 5.6.3 c) at which noise
used shallbe the maximum available for normal oper- certification is requested; and
ations as scheduled in the ~erformance section of the
aeroplane flight manual for the reference atmospheric e) the most critical (that which produces the highest noise
conditions given in 5.6.1.5. levels) configuration at the mass at which certification is
requested, shall be used.
1) aeroplanes with two engines or less - 300 m
(984 ft);
2) aeroplanes with three engines - 260 m (853 ft); 5.7 Test procedures
3) aeroplanes with four engines or more - 210 m 5.7.1 The test procedures shall be acceptable to the
(689 ft); airworthiness and noise certificating authority of the State
issuing the certificate.
b) upon reaching the height specified in a) above, the power
shall not be reduced below that required to maintain:
1) a climb gradient of 4 per cent; or
2) in the case of multi-engined aeroplanes, level flight
with one engine inoperative;
whichever power is the greater;
　
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