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10 kt), with thrust or power stabilized, shall be mamtained
over the measurement point;
Note.- In airworthiness terms VREF is defined as the
"reference landing speed". Under thk definition reference
landing speed means "the speed of the aeroplane,
in a specifed landing configuration, at the point where
it descend through the landing screen height in the
determination of the landing distance for manual
landinp ".
c) the constant approach configuration as used in the
airworthiness certification tests, but with the landing
gear down, shall be maintained throughout the approach
reference procedure;
d) the mass of the aeroplane at the touchdown shall be the
maximum landing mass permitted in the approach
configuration defined in 3.6.3 c) at which noise certification
is requested; and
e) the most critical (that which produces the highest noise
level) configuration with normal deployment of aerodynamic
control surfaces including lift and drag
producing devices, at the mass at which certification is
requested shall be used. This configuration includes all
those items listed in 5.2.5 of Appendix 2 that will contribute
to the noisiest continuous state at the maximum
landing mass in normal operation.
3.7 Test procedures
3.7.1 The test procedures shall be acceptable to the airworthiness
and noise certificating authority of the State issuing
the certificate.
3.7.2 The test procedures and noise measurements shall
be conducted and processed in an approved manner to yield
the noise evaluation measure designated as effective perceived
noise level, EPNL, in units of EPNdB, as described in
Appendix 2.
3.7.3 Acoustic data shall be adjusted by the methods
outlined in Appendix 2 to the reference conditions specified in
this chapter. Adjustments for speed and thrust shall be made as
described in Section 9 of Appendix 2.
3.7.4 If the mass during the test is different from the mass
at which the noise certification is requested, the necessary
EPNL adjustment shall not exceed 2 EPNdB for take-offs and
1 EPNdB for approaches. Data approved by the certificating
authority shall be used to determine the variation of EPNL
with mass for both take-off and approach test conditions.
Similarly the necessary EPNL adjustment for variations in
approach flight path from the reference flight path shall not
exceed 2 EPNdB.
3.7.5 For the approach conditions the test procedures
shall be accepted if the aeroplane follows a steady glide path
angle of 3" * 0.5".
3.7.6 If equivalent test procedures different from the
reference procedures are used, the test procedures and all
methods for adjusting the results to the reference procedures
shall be approved by the certificating authority. The amounts
of the adjustments shall not exceed 16 EPNdB on take-off and
8 EPNdB on approach, and if the adjustments are more than
8 EPNdB and 4 EPNdB respectively, the resulting numbers
shall be more than 2 EPNdB below the noise limits specified
in 3.4.
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).
3.7.7 For take-o& lateral, and approach conditions, the
variation in instantaneous indicated airspeed of the aeroplane
must be maintained within *3 per cent of the average airspeed
between the 10 dB-down points. This shall be determined by
reference to the pilot's airspeed indicator. However, when the
instantaneous indicated airspeed varies from the average
airspeed over the 10 dB-down points by more than A5.5 km/h
(*3 kt), and this is judged by the certificating authority
representative on the flight deck to be due to atmospheric
turbulence, then the flight so affected shall be rejected for
noise certification purposes.
CHAPTER 4. 1.- SUBSONIC JET AEROPLANES -
Application for Certificate of Airworthiness
for the Prototype accepted on or after 1 January 2006
2.- PROPELLER-DRIVEN AEROPLANES OVER 8 618 kg -
Application for Certificate of Airworthiness for the
Prototype accepted on or after 1 January 2006
4.1 Applicability
Note. - See also Chapter I , 1.9.
b) spare engine and nacelle carriage external to the skin of
the aeroplane (and rctum of thc pylon or othcr extcmal
mount); and
4.1.1 The Standards of this chapter shall be applicable to: c) time-limited engine andlor nacelle changes, where the
change in type design specifies that the aeroplane may
a) all subsonic jet aeroplanes, including their derived not be operated for a period of more than 90 days unless
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