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take-ofS (LTO) cycle)
3.1.3 Units of measurement The reference emissions LTO cycle for the calculation and
reporting of gaseous emissions shall be represented by the
3.1.3.1 The smoke emission shall be measured and following time in each operating mode*
reported in t e n r of Smoke Number (SN).
Time in operating
3.1.3.2 The mass (D,) of the gaseous pollutants HC, Phase mode, minutes
CO, or NO, emitted during the reference emissions landing Take-off 1.2
and take-off (LTO) cycle, defined in 3.1.5.2 and 3.1.5.3 shall
be measured and reported in grams. Climb 2.0
Descent 1.2
3.1.4 Nomenclature
Approach 2.3
Taxilground idle 26.0
Throughout this chapter, where the expression F*,,',, is used,
it s h d be replaced by Fo0 for engines which do not employ 3.1.5.4 Fuel spec$cations
afterburning. For taxilground idle thrust setting, F,, shall be
used in all cases.
3.1.5 Reference conditions
The fuel used during tests shall meet the specifications of
Appendix 4. Additives used for the purpose of smoke
suppression (such as organo-metallic compounds) shall not be
present.
3.1.5,l Atmospheric conditions
3.1.6 Test conditions
The reference atmospheric conditions shall be ISA at sea
level except that the reference absolute humidity shall be 3.1.6.1 The tests shall be made with the engine on its
0.00629 kg waterkg dry air. test bed.
ANNEX 16 - VOLUME I1 9 l-l/ll/93
Annex 16 - Environmenhl Protection Volume ll
3.1.6.2 The engine shall be representative of the standardengine and reference ambient conditions, divided by
certificated configuration (see Appendix 6); off-take bleeds the coefficient corresponding to the number of engines tested,
and accessory loads other than those necessary for the as shown in Appendix 6.
engine's basic operation shall not be simulated.
3.1.6.3 Measurements made for determination of
emission levels at the thrusts specified in 3.1.5.2 shall be 3.4 Information requlred
made with the afterburner operating at the level normally
used, as applicable. Note.- The infonnarion required is divided into three
groups: 1) general information to identi' the engine
3.1.7 When test differ from the reference cha~a~teri~tthiecf~ue,l used and the method of data analysis;
conditions in 3.1.5, the test,results shall be corrected to the 2) the data obtained from the engine test(#); and 3) the
reference conditions by the methods given in Appendix 5. results derivedfrom the test data
3.2 Smoke
3.4.1 The following information shall be provided for
each engine type for which emissions certification is sought:
a) engine identification;
b) rated output (in kilonewtons);
3.2.1 Regulatory Smoke Number
c) rated output with afterburning applied, if applicable
The Smoke Number at any thrust setting when measured and (in kilonewtons);
computed in accordance with the procedures of Appendix 2
and converted to a characteristic level by the procedures of d) reference pressure ratio;
Appendix 6 shall not exceed the regulatory level determined
from the following formula: e) fuel specification reference;
Regulatory Smoke Number = 83.6 (F*,)~."~ f ) fuel hydrogenlcarbon ratio;
or a value of 50, g) the methods of data acquisition;
whichever is lower
h) the method of making corrections for ambient
Note.- Certiflcarinx authoriries may alternatively accept conditions; and
values determined using afterburning provided that the
validity of these data is adequately demonstrated. i) the method of data analysis.
3.4.2 Test information
3.3 Gaseous emissions The following informarion shall be provided for each engine
tested for certification purposes at each of the thrust settings
specified in 3.1.5.2. The information shall be provided after
3.3.1 Regulatory levels correction to the reference ambient conditions where
applicable:
Gaseous emission levels when measured and computed in
accordance with the procedures of Appendix 3 or Appendix a) fuel flow (lulograms/second);
5, as applicable, and converted to characteristic levels by the
procedures of Appendix 6 shall not exceed the regulatory b) emission index (grams/kilograrn) for each gaseous
levels determined from the following formulas: pollutant;
Hydrocarbons (HC): DpF*,, = 140(0.92)"00 c) percentage of thrust contributed by afterburning; and
Carbon monoxide (CO): DplF*,, = 4 550(1r,,)-1,03 d) measured Smoke Number.
Oxides of nitrogen (NOJ: DP/F*,, = 36 + 2 . 4 2 ~ ~ ~
3.4.3 Derived tnformation
Note.- The clzaracterisric level of the Smoke Number or
gaseous pollutant emissions is the mean of the values of all 3.4.3.1 The following &rived information shall be
the engines tested, measured and corrected to the reference provided for each engine tested for certificatioi~p urposes;
　
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