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the coefficient corresponding to the number of engines tested.
as shown in Appendix 6.
a) emission rate, i.e. emission index x fuel flow,
(gramslsecond) for each gaseous pollutant;
b) total gross emission of each gaseous pollutant measured
over the LTO cycle (grams);
2.4 Information required c) values of ~ ~ / if;or , each gaseous pollutant
(gramslkilonewton); and
Note.- The information required is divided into three
groups: I ) general infonnation to identify the engfne characteristics.
the fuel used and the method of data analysis; 2) the
data obtained from the engine tesqs); and 3) the results derived
from the test data.
d) maximum Smoke Number.
2.4.3.2 The characteristic Smoke Number and gaseous
pollutant emission levels shall be provided for each engine
type for which emissions certification is sought.
2.4.1 General information Note.- The chamcteristic level of the Smoke Number or
gaseous pollutant emissions is the mean of the values of all the
engines tested, measured and corrected to the reference
standard engine and reference ambient conditions, divided by
the coejicient corresponding to the number of engines tested,
as shown in Appendix 6.
The following information shall be provided for each engine
type for which emissions certification is sought:
a) engine identification;
CHAPTER 3. TURBO-JET AND TURBOFAN ENGINES INTENDED FOR
PROPULSION AT SUPERSONIC SPEEDS
3.1 General
3.1.1 Applicability
The provisions of this chapter shall apply to all turbo-jet and
turbofan engines intended for propulsion at supersonic speeds
whose date of manufacture is on or after 18 February 1982.
3.1.2 Emissions involved
The following emissions shall be controlled for certification of
aircraft engines:
Smoke
Gaseous emissions
Unburned hydrocarbons (HC);
Carbon monoxide (CO); and
Oxides of nitrogen (NO,).
3.1.3 Units of measurement
3.1.3.1 The smoke emission shall be measured and
reported in terms of Smoke Number (SN).
3.1.3.2 The mass (Dp) of the gaseous pollutants HC, CO,
or NO, emitted during the reference emissions landing and
take-off (LTO) cycle, defined in 3.1.5.2 and 3.1.5.3 shall be
measured and reported in grams.
3.1.4 Nomenclature
Throughout this chapter, where the expression F*, is used, it
shall be replaced by F, for engines which do not employ
aftexbuming. For Wground idle thrust setting, F, shall be
used in all cases.
3.1.5 Reference conditions
3.1.5.1 Ahtospheric conditions
The reference atmospheric conditions shall be ISA at sea
level except that the reference absolute humidity shall be
0.00634 kg waterlkg dry air.
3.1.5.2 Thrust settings
The engine shall be tested at sufficient power settings to define
the gaseous and smoke emissions of the engine so that mass
emission rates and Smoke Numbers corrected to the reference
ambient conditions can be determined at the following specific
percentages of rated output as agreed by the certificating
authority.
Operating mode
Take-off
Climb
Thrust setting
100 per cent F*,
65 per cent F*,
Descent 15 per cent F*,
Approach
Taxitground idle
34 per cent F*,
5.8 per cent F,
3.1.5.3 Reference emissions landing and
rake-off (LTO) cycle)
The reference emissions LTO cycle for the calculation and
reporting of gaseous emissions shall be represented by the
following time in each operating mode.
, Phase
Take-off
Climb
Descent
Approach
Taxitground idle
Time in operating
mode. minutes
1.2
3.1.5.4 Fuel specifiations
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.
3.1.6 Test conditions
3.1.6.1 The tests shall be made with the engine on its
test bed.
ANNEX 16 - VOLUME I1 9 -mims
No. 5
Annex 16 - Environmental Protection Volume 11
3.1.6.2 The engine shall be representative of the standard engine and reference ambient conditions, divided by
certificated configuration (see Appendix 6); off-take bleeds the coeficient corresponding to the number of engines tested,
and accessory loads other than those necessary for the engine's as shown in Appendix 6.
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 made
3.4 Information required
with the afterburner operating at the level normally used, as Note.- The infontdon required is divided into three
　
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