Exhaust Emissions from In-Use General Aviation Aircraft (2016)

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90 Several considerations apply to the data that follow: 1. Emission indices were calculated based on a fuel composition of 3067 grams of CO2 per kilogram of fuel for AVGAS 100 LL and 3160 grams of CO2 per kilogram of fuel for Jet A. The value for AVGAS was determined based on a fuel analysis of three AVGAS samples. 2. For safety reasons, including aircraft stability and engine temperature, not all aircraft could achieve maximum power on the ground. These states and other states not accessed are marked with the symbol “—”. 3. Piston engine power states have been defined based on how the pilot would usually operate the aircraft. Two alternate measures of engine state are included: the fraction of maximum achieved propeller speed on the ground (% max RPM) and the fraction of maximum fuel flow (% max fuel flow). The fuel flow measure is expected to be most linear with thrust for propeller aircraft. 4. Fuel flow gauges and readouts are not present in the cockpits of many aircraft. When fuel flow data was not available, it was derived from engine manuals as described in Appendix J. 5. The research team included four separate measures of PM emission indices. These catego- ries were based on recent recommendations and discussions of the SAE E-31 Committee on aircraft exhaust emission measurements and the ICAO CAEP Working Group 3 on emissions, but are extended to include total particle quantities as well as non-volatile particle quantities. The four measures are (1) non-volatile PM number nvPMn; (2) total PM number tPMn; (3) non-volatile PM mass nvPMm; and (4) total PM mass tPMm. 6. Comparison of PM emissions between different sampling systems requires the consideration of line losses (See Appendix I). Emission Index Data Tables A P P E N D I X P

--------------------------------Engine Stateb.---------------------------------- --------------------------------Engine State---------------------------------- Unique ID Engine Make Engine Model HPa # Engines Class T/O C/O Cruise AppFinal App Taxi Idle T/O C/O Cruise AppFinal App Taxi Idle --------------------------------% of max propellor speed----------------------- - --------------------------------% of max fuel flow------------------------ Recommended for Subs„tu„on in EDMS/AEDT Lycoming O-320 150-160 1 100% 100% 91% 70% 69% 46% 34% 98% 98% 80% 41% 39% 18% 12% Individual Engine Tests 1 Rotax 912 100 1 100% 100% 90% 66% 66% 58% 57% 72% 72% 50% 30% 30% 22% 13% 2 Connental O-200-A 100 1 -- -- -- -- -- 46% -- -- -- -- -- -- 19% -- 3 Connental O-200-A 100 1 100% 100% 90% 71% 71% 41% 24% 90% 90% 70% 44% 44% 21% 14% 4 Connental O-200-A 100 1 100% 100% 96% 64% 48% 40% 40% 90% 90% 82% 37% 25% 20% 20% 5 Connental O-200-A 100 1 100% 85% 100% 65% 65% 46% 29% 90% 62% 90% 38% 38% 23% 15% 6 Connental O-200-A 100 1 100% 100% 100% 83% 63% 46% 30% 90% 90% 90% 60% 35% 23% 16% 7 Lycoming O-235-L2C 115 1 100% 100% 94% 77% 47% 43% 33% 98% 98% 81% 49% 20% 18% 14% 8 Lycoming O-235-L2C 115 1 100% 100% 93% 77% 48% 43% 37% 98% 98% 81% 50% 21% 19% 15% 9 Lycoming O-235-L2C 115 1 100% 100% 100% 67% 67% 67% 33% 98% 98% 98% 37% 37% 40% 14% 10 Lycoming O-320-E2D 150 1 100% 100% 94% 68% 68% 51% 31% 100% 100% 86% 37% 37% 21% 11% 11 Lycoming O-320-E2D 150 1 99% 99% 93% 57% 57% 43% 30% 100% 100% 86% 25% 25% 16% 11% 12.1 Lycoming O-320-E2D 150 1 100% 100% 100% 91% 68% 45% 36% 100% 100% 100% 79% 37% 18% 13% 12.2 Lycoming O-320-E2D 150 1 100% 100% 95% 68% 68% 55% 39% 100% 100% 92% 37% 37% 24% 14% 13 Lycoming O-320-E2D 150 1 -- -- -- 52% 65% 43% 30% -- -- -- 22% 34% 16% 11% 14 Lycoming O-320-E2D 150 1 98% 98% 96% 74% 56% 35% 31% 99% 99% 92% 45% 25% 12% 11% 15 Lycoming O-320-E2D 150 1 100% 100% 72% 70% 70% 43% 28% 100% 100% 58% 39% 39% 16% 10% 16 Lycoming O-320-E2D 150 1 100% 100% 92% 67% 63% 50% 41% 100% 100% 81% 35% 31% 20% 15% 17 Lycoming O-320-E2G 150 1 100% 100% 90% 69% 73% 48% 27% 100% 100% 77% 39% 43% 19% 10% 18 Lycoming O-320-E2G 150 1 100% 100% 96% 87% 70% 46% 33% 100% 100% 92% 69% 39% 18% 12% 19 Lycoming O-320-E3D 150 1 100% 100% 96% 67% 67% 42% 26% 100% 100% 93% 35% 35% 16% 9% 20 Lycoming O-320-B2C 160 1 Helicopter 102% 102% 75% -- -- -- 58% 100% 100% 43% -- -- -- 24% 21 Lycoming O-320-B2C 160 1 Helicopter -- -- 75% -- -- -- -- -- -- 43% -- -- -- -- 22 Lycoming O-320-D2J 160 1 -- -- -- -- -- 48% 32% -- -- -- -- -- 18% 10% 23 Lycoming O-320-D3G 160 1 100% 100% 100% 57% 100% 43% 33% 100% 100% 100% 23% 100% 15% 11% 24 Lycoming O-320-D3G 160 1 102% 102% 91% 65% 65% 43% 31% 100% 100% 75% 31% 31% 15% 10% 25 Lycoming O-320-D3G 160 1 100% 100% 91% 81% 72% 64% 34% 100% 100% 75% 53% 40% 30% 11% 26 Lycoming O-320-D3G 160 1 100% 100% 96% 58% 54% 42% 35% 100% 100% 87% 25% 22% 14% 11% 27 Lycoming O-320-H2AD 160 1 92% 92% 88% 68% 68% 40% 32% 75% 75% 66% 35% 35% 14% 11% 28 Lycoming O-320-H2AD 160 1 99% 99% 95% 91% 82% 45% 37% 94% 94% 84% 73% 54% 17% 13% 29 Franklin 6A4-165 165 1 100% 100% 91% 77% 45% 45% 32% 100% 100% 79% 50% 18% 18% 11% 30 Lycoming O-360-A4M 180 1 100% 100% 95% 64% 64% 45% 40% 96% 96% 62% 35% 35% 15% 14% 31 Lycoming O-360-C2E 180 1 100% 100% 91% 66% 68% 45% 40% 62% 62% 45% 28% 31% 18% 16% 32.1 Lycoming O-360-F1A6 180 1 100% 97% 88% 85% 77% 42% 31% 100% 92% 70% 62% 48% 15% 10% 32.2 Lycoming O-360-F1A6 180 1 100% 94% 90% 61% 61% 45% 24% 100% 84% 73% 28% 28% 17% 8% 33 Lycoming O-360-A1A 180 2 97% 94% 88% 57% 57% 34% 37% 95% 88% 71% 26% 26% 12% 20% 34 Lycoming O-360-A1G6D 180 2 100% 93% 85% 81% 74% 37% 41% 106% 83% 66% 58% 46% 14% 22% 35 Lycoming IO-360-L2A 160 1 Fuel Injected 100% 100% 99% 69% 69% 48% 36% 100% 100% 64% 14% 14% 18% 12% 36 Lycoming IO-360-A3B6D 200 1 Fuel Injected 99% 99% 70% 74% 78% 48% 30% 98% 98% 37% 25% 31% 11% 10% 37 Lycoming IO-360-C1C6 200 1 Fuel Injected 100% 100% 91% 58% 50% 38% 26% 76% 76% 61% 25% 19% 19% 13% 38 Lycoming IO-360-C1C6 200 1 Fuel Injected 102% 102% 81% 64% 64% 51% 37% 100% 100% 56% 32% 32% 20% 13%

--------------------------------Engine Stateb.---------------------------------- --------------------------------Engine State---------------------------------- Unique ID Engine Make Engine Model HPa # Engines Class T/O C/O Cruise AppFinal App Taxi Idle T/O C/O Cruise AppFinal App Taxi Idle --------------------------------% of max propellor speed----------------------- - --------------------------------% of max fuel flow------------------------ 39 Lycoming IO-520-1AB5 230 1 Fuel Injected 100% 100% 100% 77% 77% 45% 35% 100% 100% 56% 44% 44% 16% 15% 40 Connental O-470-11 230 1 -- -- 87% 65% 65% 39% 26% -- -- 71% 36% 36% 16% 10% 41 TCM O-470-U 230 1 100% 100% 100% 68% 45% 45% 36% 100% 100% 61% 30% 16% 14% 3% 42 Lycoming O-540-B4B5 235 1 100% 96% 84% 80% 56% 52% 40% 95% 84% 59% 52% 25% 22% 15% 43 Lycoming O-540-A1D5 250 1 100% 96% 92% 65% 65% 42% 26% 96% 85% 75% 32% 32% 15% 9% 44 Lycoming O-540-J3C5D 250 1 100% 100% 78% 63% 63% 37% 31% 100% 100% 52% 33% 33% 15% 13% 45 Lycoming IO-540-C4B5 250 2 Fuel Injected -- -- -- -- -- -- 25% -- -- -- -- -- -- 11% 46 Lycoming IO-540-C4B5 250 2 Fuel Injected 100% 94% 86% 51% 51% 47% 28% 100% 92% 73% 25% 25% 22% 13% 47.1 Lycoming IO-540-C4B5 250 2 Fuel Injected 100% 100% 92% 80% 88% 42% 33% 98% 62% 54% 61% 50% 18% 15% 47.2 Lycoming IO-540-C4B5 250 2 Fuel Injected 100% 100% 92% 68% 68% 56% 31% 100% 100% 87% 42% 42% 29% 14% 48 TCM IO-540-BB 285 1 Fuel Injected -- 98% 94% 82% 82% 45% 25% -- 90% 80% 56% 56% 18% 10% 49 Lycoming IO-540-K1G5D 300 1 Fuel Injected 93% 93% 90% 82% 82% 49% 37% 72% 72% 64% 51% 51% 19% 13% 50 Connental IO-550-N 300 1 Fuel Injected -- -- -- -- -- -- 30% -- -- -- -- -- -- 15% 51 TCM TSIO-520-C 300 1 Fuel Injected 96% 85% 96% 67% 67% 43% 27% 76% 61% 76% 34% 34% 16% 10% 52 TCM IO-550-C 300 2 Fuel Injected -- -- 96% 75% 75% 43% 33% -- -- 89% 50% 50% 22% 17% 53 Unknown (Skybolt Experimental) 1 -- -- -- -- -- 30% -- -- -- -- -- -- 11% -- 54 Garre“ AiResearch TPE331-6-252B 750 2 Turboprop 100% 100% 98% 98% 98% 91% 76% 100% 89% 56% 51% 51% 42% 26% 55 Pra“ & Whitney Canada PT6A-60A 1050lbs 2 Turboprop -- -- 80% -- -- 60% 52% -- -- 80% -- -- 60% 52% 56 Williams FJ44-1AP 1965lbs 2 Turbofan -- -- -- -- -- 43% -- -- -- -- -- -- -- 57 General Electric CF34-3A1 9140lbs 2 Turbofan 86% 86% 67% 56% 56% 30% 26% 100% 100% 50% 38% 38% 18% 16% Engine Family Averages Replicates Connental O-200 100 5 100% 96% 96% 71% 62% 44% 31% 90% 83% 83% 45% 35% 21% 16% Lycoming O-235 115 3 100% 100% 96% 73% 54% 51% 34% 98% 98% 87% 45% 26% 26% 14% Lycoming O-320 150-160 20 100% 100% 91% 70% 69% 46% 34% 98% 98% 80% 41% 39% 18% 12% Lycoming O-360 180 6 99% 96% 90% 69% 67% 41% 36% 93% 84% 65% 40% 36% 15% 15% Lycoming IO-360 200 4 100% 100% 85% 66% 65% 46% 32% 94% 94% 54% 24% 24% 17% 12% Lycoming O-540 235-250 3 100% 97% 85% 69% 61% 44% 32% 97% 90% 62% 39% 30% 18% 13% Lycoming IO-540 250-285 6 98% 97% 91% 73% 74% 48% 30% 92% 83% 72% 47% 45% 21% 13% Upper Limit on Engine Family Averages at 95% Confidence Connental O-200 100 100% 120% 112% 99% 93% 52% 52% 90% 128% 114% 78% 61% 26% 25% Lycoming O-235 115 100% 100% 112% 99% 102% 110% 42% 98% 98% 129% 78% 66% 81% 18% Lycoming O-320 150-160 104% 104% 109% 95% 91% 59% 49% 111% 111% 116% 78% 76% 26% 19% Lycoming O-360 180 103% 104% 98% 98% 87% 54% 52% 133% 114% 91% 81% 59% 21% 29% Lycoming IO-360 200 103% 103% 125% 89% 102% 63% 49% 130% 130% 93% 47% 52% 30% 16% Lycoming O-540 235-250 100% 107% 116% 109% 82% 76% 63% 109% 128% 113% 87% 49% 35% 26% Lycoming IO-540 250-285 109% 106% 99% 110% 116% 62% 43% 136% 127% 107% 86% 79% 34% 17%

--------------------------------Engine Stateb.---------------------------------- --------------------------------Engine State---------------------------------- Unique ID Engine Make Engine Model HPa # Engines Class T/O C/O Cruise AppFinal App Taxi Idle T/O C/O Cruise AppFinal App Taxi Idle --------------------------------% of max propellor speed----------------------- - --------------------------------% of max fuel flow------------------------ Preexis‚ng Data FOCAc.,e. 100% 85% 65% 45% manual ICAOd. 100% 85% 30% 7% manual FAEED162 diverse Prop-200hp 150 100% 75% 53% 53% 11% 11% FAEED160 diverse Prop-300hp 225 100% 74% 46% 46% 8% 8% FAEED165 diverse Prop-500hp 350 100% 79% 38% 38% 10% 10% FOCA diverse Prop>500hp 1200 100% 20% 10% 10% 0% 0% FAEED159 TCM O-200 100 100% 100% 56% 56% 18% 18% FOCA Lycoming O-320-E2A 160 100% 80% 48% 48% 13% 13% FAEED163 Lycoming IO-320-DIAD 160 Fuel Injected 100% 66% 41% 41% 9% 9% FOCA Lycoming O-360-A3A 180 100% 85% 45% 45% 13% 13% FOCA Lycoming IO-360-A1B6 200 Fuel Injected 100% 78% 46% 46% 10% 10% FAEED160 TCM TSIO-360-C 225 Fuel Injected 100% 74% 46% 46% 8% 8% FOCA Lycoming O-540-J3C5D 235 100% 84% 40% 40% 10% 10% FOCA Lycoming IO-540-T4A5D 260 Fuel Injected 100% 89% 44% 44% 15% 15% FOCA TCM IO-550-B 300 Fuel Injected 100% 99% 54% 54% 21% 21% FOCA Lycoming TSIO-520-WB 325 Fuel Injected 100% 85% 52% 52% 23% 23% FAEED165 Lycoming TIO-540-J2B2 350 Fuel Injected 100% 79% 38% 38% 10% 10% ICAO General Electric CF34-3A1 100% 82% 29% 29% 12% 12% ICAO Honeywell AS907-1-1A 100% 83% 30% 30% 14% 14% EDMS ConŽnental 6-285-B 92% 100% 50% 50% 43% 43% EDMS CurŽss-Wright R-1820 100% 74% 28% 28% 8% 8% EDMS Lycoming IO-320-D1AD Fuel Injected 100% 67% 41% 41% 8% 8% EDMS Lycoming IO-360-B Fuel Injected 100% 70% 36% 36% 8% 8% EDMS Lycoming O-200 100% 100% 56% 56% 18% 18% EDMS Lycoming O-320 100% 75% 52% 52% 11% 11% EDMS Lycoming TIO-540-J2B2 Fuel Injected 100% 79% 38% 38% 10% 10% EDMS Lycoming TSIO-360-C Fuel Injected 100% 74% 46% 46% 9% 9% EDMS Pra’ & Whitney Canada PT6A-60A 1050lbs Turbofan 100% 91% 52% 52% 18% 18% EDMS Pra’ & Whitney Canada PT6A-114 600lbs Turbofan 100% 89% 50% 50% 18% 18% EDMS Pra’ & Whitney Canada PT6A-67 1200lbs Turbofan 100% 91% 52% 52% 19% 19% EDMS Pra’ & Whitney Canada PT6a-66 850lbs Turbofan 100% 92% 54% 54% 21% 21% Blank entries indicate that the data was not available or not of high enough quality to produce a value. The symbol "--" indicates that this engine state was not measured. a. in lieu of horse power, turbofan engine power is stated in pounds of thrust b. The % of max propellor RPM achievable on the ground is used to convert a propellor RPM into a % power. c. The FOCA (Swiss Federal AviaŽon OrganizaŽon) power states are listed. d. The ICAO (InternaŽonal Civic AviaŽon OrganizaŽon) power states are listed (% pounds of thrust). e. FOCA data has power states that are measured based on a % of the maximum fuel flow.