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clearway) of not more than 610 rn at mmimum certiJicoted
mass for ainwthincss.
Nore 2.- These guidelines are not opplicable to aircroj
with vertical rake-off and tonding capubilifies.
I . APPLICABILITY
The following guidelines should be applied to all propcllerdriven
aeroplanes of over 5 700 kg maximum certificated
bkc-ofT mass intended for operation in the shon take-off and
landing (SOL) mode, requiring a runway1 length, compatible
with the relevant take-off nnd lnnding distnncc rcquircmcnts, of
less thsn 6 10 m at maximum certificated mass for airworthiness,
and for which a certificate of airworthiness for the individual
aeroplane was fm issued on or after 1 January 1976.
2. NOISE EVALUATION
a) lateral noise refmence point: the point on a line parallel
to and 300 m from the runway centre line, or extended
runway centre line. where the noise level is a maximum
during take-off or landing, with thc aeroplane opetating
in the STOL mode;
b) j'yover noise reference point: the point on the extended
centre line of the runway 1 500 m from the aan of the
take-off roll; and
c) approach noise rqerence point: the point on the
extended centre line of the runway 900 m from the
runway threshold
4. MAXfMUM NOlSE LEVELS
The maximum noise level at any of the rcfcrence points, when
determined in accordance with the noisc evalual~onm ethod of
Appendix 2. should not exceed 96 EPNdB in the case of
aeroplanes with maximum certificaccd mass of 17 000 kg or
less. this limit increasing linearly witb thc logarithm of mass
at o rntc of 2 EPNdB per doubling of mass in the case of
aeroplanes having maximum certificated mass in excess of
17 000 kg.
MEASURE
The noise evaluation measure should be the effective per- 5. TRADEOFFS
ceived noise level in EPNdB as described in Appendix 2 to
this h e x . If the maximum noise levels are exceeded at one or two
measurement points:
3. NOISE MEASUREMENT
a) the sum of any excesses should no! be greater than
4 EPNdB:
REFERENCE POINTS
b) any excess at any single point should not be greater than
The aeroplane. when tested in accordance with the flight test 3 EPNdB: and
procedure of Section 6. should not exceed the noise levels c) any excesscs should be offsct by a corresponding
specified in Section 4 at the following reference points: reduction a! the other point or points.
6. TEST PROCEDURES
I. With no stopway or clearway 6.1 The take-off rcfercncc procedure should be as follows:
ANNEX 16 - VOLUME I ATT &I
Annex 16 - Environnre~Pl rotection Volume I
a) the aeroplane should be at the maximum take-off
Inass fur wwhlch IIU~SC ccilificalio~i is tcqu~%lcd.
b) the propcllcr mdlor enBm sped (rpm) and cngnc
power setting scheduled for STOL take-off should be
uscd: and
C) thughout Ihe take-off now cert~ficationd cmonstration
test. the airspeed climb gradient, aeroplane attitude and
aeroplane configuration should be those specified in the
flight manual for take-off in the S O L modcr.
6.2 fhe apprmdch reference procedure should be as
follows:
a) the aeroplane should be at the maximum landing mass
for which the noise certification Is requested;
b) througbut the approach nolse cenificat~on demonstration
test. d)c propcUcr and/or cnginc spccd (rpm).
engine powcr sctting, atrspeed, descent gradient, acroplane
attitude and ~roplmc configuration should be
those specified in the flight manual for STOL landing;
and
cl the use of reverse thrust aner landrng should be thc
maximum spcclficd in the flight manual.
7. ADDlTIONAL NOISE DATA
Where so specified by the certificating authority, data permitting
measured noise ievels to be evaluated in terms of the
Aweightcd ovcrall sound pressurc level (dB(A)) should be
provided.
A'ITACHMENT C. GUIDELINES FOR NOISE CERTIFICATION OF
INSTALLED AUXILIARY POWER UNITS (APU) AND ASSOCIATED
AIRCRAFI' SYSTEMS DURING GROUND OPERATION
NOW.- Spe Part 11. Chapter 9.
1.1 The followng guidance material has been preparea
for the information of States establishing noise certification
requirements for installed auxiliary power units (MU) and
associated airctafl system used during normal ground
operation.
1.2 It should apply to installed APU and associated aircraft
systems in all amraft for which the application for a certificate
of airworthiness for the prototype, or another equivalent prescribed
procedure. is made on or after 26 November 198 1.
1.3 For aircran of existing type design, for which the
application for a change of type design involving the bmic
MU installation. or another equivalent prescribed proccdurc,
　
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