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c) The mass of the aeroplane at the brake release shall be
the maximum take-off mass at which the noise
certification is requested.
d) The length of this first phase shall correspond to the
length given in the airworthiness data for a take-off on
a level paved runway.
Second phase
a) The beginning of the second phase corresponds to the
end of the first phase.
b) The aeroplane shall be in the climb configuration with
landing gear up, if retractable, and flap setting
corresponding to normal climb throughout this second
phase.
c) The speed shall be the best rate of climb speed, V,,.
d) Take-off power and, for aeroplanes equipped with
variable pitch or constant speed propellers, rpm shall be
maintained throughout the second phase. If airworthiness
limitations do not permit the application of take-off
power and rpm up to the reference point, then take-off
power and rpm shall be maintained for as long as is
permitted by such limitations and thereafter at maximum
continuous power and rpm. Limiting of time for which
take-off power and rpm shall be used in order to comply
with this chapter shall not be permitted. The reference
height shall be calculated assuming climb gradients
appropriate to each power setting used.
10.6 Test procedures
10.6.1 The test procedures shall be acceptable to the
airworthiness and noise certificating authorities of the State
issuing the certificate.
10.6.2 The test procedures and noise measurements shall
be conducted and processed in an approved manner to yield
the noise evaluation measure in units of L- as described in
Appendix 6.
10.6.3 Acoustic data shall be adjusted by the methods
outlined in Appendix 6 to the reference conditions specified in
this chapter.
10.6.4 If equivalent test procedures are used, the test
procedures and all methods for correcting the results to the
reference procedures shall be approved by the certificating
authority.
Note.- Guidance material on the use of equivalent
procedures is provided in the Environmental Technical Manual
on the Use of Procedures in the Noise Certification of Aircraft
(Doc 9501).
CHAPTER 11. HELICOPTERS NOT EXCEEDING 3 175 kg
MAXIMUM CERTIFICATED TAKE-OFF MASS
11.1 Applicability 11.3 Reference noise measurement point
Note.- See also Chapter 1, 1.9.
1 1. I. 1 The Standards of this chapter shall be applicable to
all helicopters having a n~aximum certificated take-oK mass
not exceeding 3 175 kg for which 11.1.2, 11.1.3 and 11.1.4
apply, except those designed exclusively for agricultural, fire
fighting or external load carrying purposes.
11.1.2 For a helicopter for which the application for the
certificate of airworthiness for the prototype was issued, or
another equivalent prescribed procedure was carried out by the
certificating authority, on or after 1 l November 1993, except
for those helicopters specified in 1 1.1.4, the noise levels of
11.4.1 shall apply.
11.1.3 For a derived version of a helicopter for which the
application for the certificate of airworthiness for a change of
type design was issued, or another equivalent prescribed
procedure was carried out by the certificating authority, on or
after 1 I November 1993, except for those helicopters specified
in 11.1.4, the noise levels of 1 1.4.1 shall apply.
11.1.4 For all helicopters, including their derived
versions, for which thc application for the certificate of airworthiness
for the prototype was accepted, or another equivalent
prescribed procedure was carried out by the certificating
authority, on or afier 2 1 March 2002, the noise levels of 11.4.2
shall apply.
11.1.5 Certification of helicopters which are capable of
carrying external loads or external equipment shall be made
without such loads or equipment fitted.
A helicopter, when tested in accordance with these Standards,
shall not exceed the noise levels specified in 11.4 at a flight
path reference point located on the ground 150 rn (492 ft) vertically
below the flight path defined in the overflight reference
procedure (see 1 1 S.2.1).
Note.- See Attachment H (Guidelines for Obtaining Helicopter
Noise Data for Land-use Planning Purposes) that
defines acceptable supplemental land-use planning (LUP) data
procedures.
11.4 Maximnm noise level
11.4.1 For helicopters specified in 11 .I .2 and 11.1.3, the
maximum noise levels, when determined in accordance with
the noise evaluation method of Appendix 4, shall not exceed
82 decibels SEL for helicppters with maximum certificated
take-off mass, at which the noise certification is requested, of
　
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