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and having features which retain the basic core engine and
combustor design of the original model and for which other
factors, as judged by the certificating authority, have not
changed.
Note.- Attention is drawn to the difference between the
definition of "derived version of aircraft" in Volume I of
Annex 16 and the definition of "derivative version" in this
Volume.
Smoke Number. The dimensionless term quantifying
smoke emissions (see 3 of Appendix 2).
Take-off phase. The operating phase defined by the time
during which the engine is operated at the rated output.
TaxiJground idle. The operating phases involving taxi and
idle between the initial starting of the propulsion engine(s)
and the initiation of the take-off i.011 and between the time of
runway turn-off and final shutdown of all propulsion
engine($).
Oxides of nitrogen. The sum of the amounts of the nitric Unburned hydrocarbons. The total of hydrocarbon
oxide and nitrogen dioxide contained in a gas sample compounds of all classes and molecular weights contained in
calculated as if the nitric oxide were in the form of nitrogen a gas sample, calculated as if they were in the form of
dioxide. methane.
ANNEX 16 - VOLUME I1 4111199
No. 4
CHAPTER 2. SYMBOLS
Where the following symbols are used in Volumc I1 of this Fb, Rated output with afterburning applied
Annex, they have the meanings ascribed to them below:
HC Unburned hydrocarbons (see dcfinition)
CO Carbon monoxide
NO Nitric oxide
D, Tbc mass of any gaseous pollutant crnitted during NO, Nitrogen dioxide
the refercnce emissions landing a11d takc-off cycle
NO, Oxidcs of nitrogcn (see definition)
F,, Thrust in Internarional Standard Atmosphere (ISA),
sea level conditions, for the given operating modc SN S~nokcN umber (see dcfinition)
F,, Rated output (see definition) .no, Rcference pressure ratio (see definition)
ANNEX 16 - VOLUME I1
Part ZZZ - Chapter 2 Annex 16 - Environmental Protection
2.1.5 Test conditions Hydrocarbons (HC): D,,/F,, = 19.6
2.1.5.1 The tests shall be made with the engine on its
test bed.
2.1.5.2 The engine shall be representative of the
certificated configuration (see Appcndix 6); off-take bleeds
and accessory loads other than those necessary for thc
engine's basic operation shall not be simulated.
2.1.6 When test conditions differ from the reference
conditions in 2.1.4 the test results shall be corrected to the
reference conditions by the methods given in Appcndix 3.
2.2 Smoke
2.2.1 Applicability
The provisions of 2.2.2 shall apply to engines whose date of
manufacture is on or aftcr 1 January 1983.
2.2.2 Regulatory Smoke Number
The Smoke Number at any thrust sctting when measured and
computed in accordance with the procedures of Appendix 2
and converted to a characteristic level by the procedures of
Appendix 6 shall not exceed the level determined from the
following formula:
Regulatory Smoke Number = 83.6 ( F ~ ~ ) - ~ - ~ ~ ~
or a value of 50,
whichever is lower
2.3 Gaseous emissions
2.3.1 Applicability
The provisions of 2.3.2 shall apply to cngincs whose rated
output is greater than 26.7 kN and whose date of manufacturc
is on or after 1 January 1986 and as further specified for
oxides of nitrogen.
2.3.2 Regulatory levels
Gaseous emission levcls when measured and computed in
accordance with the procedures of Appcndix 3 and converted
to characteristic lcvels by the procedures of Appendix 6 shall
not cxcccd the regulatory levcls determined from the
following formulas:
Carbon monoxide (CO): D,/F,, = 118
Oxides of nitrogen (NO,):
a) for engines of a type or model for which the datc of
manufacture of the first individual production model
was on or before 31 Dcccmbcr 1995 and for which
the datc of manufacture of the individual enginc was
on or before 31 December 1999.
b) for engines of a type or model for which the date of
manufacture of the first individual production model
was aftcr 31 December 1995 or for which the date of
manufacture of the individual engine was after
31 December 1999.
c) for engines of a type or model for which the date of
manufacture of the first individual production model
was after 3 1 December 2003:
1) for engines with a pressure ratio of 30 or less:
i) for engines with a maximum rated thrust of
more than 89.0 kN:
D, IF,, = 19 + 1 .6n,,
ii) for cngines with a maximum rated thrust of
more than 26.7 kN but not more than 89.0
kN:
D, IF,, = 37.572 + 1 . 6-~ 0.~208~7F oO
2) for engines with a prcssurc ratio of more than 30
　
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