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g) a statement indicating compliance with gaseous
pollutant requirements.
1.4 Contracting States shall recognize as valid ernissions
certification granted by the certificating authority of
another Contracting State provided that the requirements
under which such certification was ganted are not less
stringent than the provisions of Volume II of this Annex.
ANNEX 16 - VOLUME 11
CJX4PTER 2. TURBO-JET AND TURBOFAN ENGINES INTENDED FOR
PROPULSION ONLY AT SUBSONIC SPEEDS
2.1 General 2.1.4 Reference conditions
2.1.4.1 Atmospheric conditions
2.1.1 Applicability
The provisions of this chapter shall apply to all turbo-jet and
turbofan engines, as further specified in 2.2 and 2.3, intended
for propulsion only at subsonic speeds, except when certificating
authorities make exemptions for specific engine types
and derivative versions- of such engines for which the type
certificate of the first basic type was issued or other
equivalent prescribed procedure was carried out before
1 January 1965. In such cases an exemption document shall
be issued by the certificating authority. The provisions of this
chapter shall also apply to engines designed for applications
that otherwise would have been fulfilled by turbo-jet and
turbofan engines.
Note.- In considering exemptions, cert$cating authorities
should take into account the probable numbers of such
engines that will be produced and their impact on the
environment. When such an exemplion Is granted, the certi-
3cating authority should consider imposing a time limit on
the future production of such engines for installation on new
aircrafi, although production of such engines us spares
should be permitted inde$nitely.
2.1.2 Emissions involved
'he following emissions shall be controlled for certification
of aircraft engines:
Smoke
Gaseous emissions
Unburned hydrocarbons (HC);
Carbon monoxide [CO); and
Oxides of nitrogen (NO,).
The reference atmospheric conditions shall be ISA at sea
level except that the reference absolute humidity shall be
0.00629 kg waterkg dry air.
2.1.4.2 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:
Opemting mode Thrust setting
Take-off 100 per cent F,,
Climb 85 per cent F,,
Approach 30 per cent F,,
Taxilground idle 7 per cent F,,
2.1.4.3 Reference emissions landing and
take-ofS (LTO) cycle
The reference emissions LTO cycle for the calculation and
reporting of gaseous emissions shall be represented by the
following rime in each operating mode.
Phase
Take-off
Climb
Tim in operating
mode, minutes
0.7
2.2
Approach 4.0
2.1.3 Units of measurement Taxilground idle 26.0
2.1.3.1 The smoke emission shall be measured and
reported in terms of Smoke Number (SN). 2.1.4.4 Fuel spec$cntions
2.1.3.2 The mass (D,) of the gaseous pollutaut HC, CO, The fuel used during tests shall meet the specifications of
or NO, emitted during the reference emissions landing and Appendix 4. Additives used for the purpose of smoke
take-off (Lm) cycle, defined in 2.1.4.2 and 2.1.4.3, shall be suppression (such as organa-metallic compounds) shall not be
measured and reported in grams. present.
ll/ll/93 6 ANNEX 16 - VOLUME I1
Part 1x1 - Chapter 2 Annex 16 - Environmental Protection
2.1.5 Test conditions Hydrocarbons (HC): D,/Foo= 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 Appendix 6); off-take bleeds
and accessory loads other than those necessary for the
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 Appendix 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 after 1 January 1983.
2.2.2 Regulatory Smoke Number
The Smoke Number at any thrust setting 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:
Carbon monoxide (CO): D,/F, = 1 18
Oxides of nitrogen (NOI):
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