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c) Aeroplanes with four engines or more
2.6 Test procedures
2.6.1 Take-off test procedure
2.6.1.1 Average take-off thrust2 shall be used fiom the
start of take-off to the point at which a height of at least 210 m
(690 ft) above the runway is reached and the thrust thereafter
shall not be reduced below that thrust which will maintain a
climb gradient of at least 4 per cent.
2.6.1.2 A speed of at least V2 + 19 km/h (V2 + 10 kt)
shall be attained as soon as practicable after lift-off and be
maintained throughout the take-off noise certification test.
2.6.1.3 A constant take-off configuration selected. by the
applicant shall be maintained throughout the take-off noise
certification demonstration test except that the landing gear
may be retracted.
As a) but with 108 EPNdB for aeroplanes with maxi- 2.6.2 Approach test procedure
mum certificated take-off mass of 325 000 kg or over
2.6.2.1 The aeroplane shall be stabilized and following a
or 3" * 0.5" glide path.
as defined by 2.4. I b), whichever is the lower. 2.6.2.2 The approach shall be made at a stabilized
airspeed of not less than 1.3 Vs + 19 kmlh (1.3 Vs + 10 kt)
2.4.2.3 At approach noise measurement point with thrust stabilized during approach and over the measuring
point and continued to a normal touchdown.
108 EPNdB for aeroplanes with maximum certificated take-off
mass of 280 000 kg or over, decreasing linearly with the
logarithm of the mass down to 101 EPNdJ3 at 35 000 kg, after 2. Take-off thrust representative of the mean characteristics of the
which the limit remains constant. production engine.
Part II - Chapter 2 Annex I6 - Environmenlal Protection
2.6.2.3 The configuration of the aeroplane shall be with
maximum allowable landing flap setting.
Note.- Guidance material on the use of equivalent procedures
is provided in the Environmental Technical Manual on
the Use of Procedures in the Nnise Certification of Aircraft
(Doc 9501).
CHAPTER 3. 1.- SUBSONIC JET AEROPLANES -
Application for Certificate of Airworthiness
for the Prototype accepted on or after
6 October 1977 and before 1 January 2006
2.- PROPELLER-DRIVEN AEROPLANES OVER 5 700 kg -
Application for Certificate of Airworthiness
for the Prototype accepted on or after
1 January 1985 and before 17 November 1988
3.- PROPELLER-DRIVEN AEROPLANES OVER 8 618 kg -
Application for Certificate of Airworthiness
for the Prototype accepted on or after
17 November 1988 and before 1 January 2006
3.1 Applicability
Note 1.- See also Chapter 1, 1.9.
Note 2.- See Attachment E for guidance on interpretatinn
of these applicability provisions.
3.1.1 The Standards of this chapter shall be applicable to:
a) all subsonic jet aeroplanes, including their derived
versions, other than aeroplanes which require a runway1
length of 610 m or less at maximum certificated mass
for airworthiness, in respect of which either the application
for a certificate of airworthiness for the prototype
was accepted, or another equivalent prescribed procedure
was carried out by the certificating authority, on
or after 6 October 1977 and before 1 January 2006;
b) all propeller-driven aeroplanes, including their derived
versions, of over 5 700 kg maximum certificated take-off
mass (except those described in Chapter 6, 6.1). for
which either the application for a certificate of airworthiness
for the prototype was accepted, or another equivalent
prescribed procedure was carried out by the
certificating authority, on or after 1 January 1985 and
before 17 November 1988, except where the Standards
of Chapter 10 apply; and
c) all propeller-driven aeroplanes. including their derived
versions, of over 8 618 kg maximum certificated takeoff
mass, for which either the application for a
1. With no stopway or clearway.
certificate of airworthiness for the prototype was
accepted, or another equivalent prescribed procedure
was carried out by the certificating authority, on or after
17 November 1988 and before I January 2006.
3.1.2 Notwithstanding 3.1.1, it may be recognized by a
Contracting State that the following situations for jet aeroplanes
and propeller-driven heavy aeroplanes on its registry do
not require demonstration of compliance with the provisions of
the Standards of Annex 16, Volume I:
a) gear down flight with one or more retractable landing
gear down during the entire flight;
b) spare engine and nacelle carriage external to the skin of
the aeroplane (and return of the pylon or other external
mount); and
c) time-limited engine andlor nacelle changes, where the
　
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