Performance Data for CESSNA C-165

range profile chart presented in figure 5-8, and the endurance profile chart presented in figure 5-9. The range profile chart illustrates the relationship between power and range. Considerable fuel savings and longer range result when lower power settings are used. For this sample problem with a cruise altitude of 5500 feet and dis- tance of 420 nautical miles, the range profile chart indicates that use of a 75% power setting will necessitate a fuel stop, in view of the anticipated 10 knot headwind component. However, selecting a 65% power setting from the range profile chart yields a predicted range of 477 nautical miles under zero wind conditions. The endurance profile chart, figure 5-9, shows a corresponding 4.4 hours. The range figure of 477 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet. Range, zero wind Decrease in range due to wind 477 44 433 Nautical Miles 1005 Feet Corrected ground roll Total distance to clear a 50-foot obstacle, zero wind 2030 Decrease in total distance (2030 feet x 13%) 264 1766 Feet Corrected total distance to clear 50-foot obstacle These distances are well within the takeoff field length quoted earlier for (4. 4 hours x 10 knot headwind) Corrected range This indicates that the trip can be made without a fuel stop using approxi- mately 65% power. The cruise performance chart, figure 5-7, is entered at 6000 feet altitude and 20°C above standard temperature. These values most nearly correspond to the expected altitude and temperature conditions. The en- gine speed chosen is 2500 RPM, which results in the following: Power True airspeed Cruise fuel flow 62% 109 Knots 7.0 GPH The power computer may be used to determine power and fuel consumption during the flight. 5-4 5-5 SECTION 5 PERFORMANCE FUEL REQUIRED CESSNA MODEL 172M The total fuel requirement for the flight may be estimated using the performance information in figures 5-6 and 5-7. For this sample prob- lem, figure 5-6 shows that a climb from 1000 feet to 6000 feet requires 2.0 gallons of fuel and may be used as a conservative estimate for this problem. This is for a standard temperature (as shown on the climb chart). The approximate effect of a non-standard temperature is to in- crease the time, fuel, and distance by 10% for each 10°C above standard temperature, due to the lower rate of climb. In this case, assuming a temperature 16°C above standard, the correction would be: 16°C x 10% = 16% Increase 10°C With this factor included, the fuel estimate would be calculated as follows: Fuel to climb, standard temperature Increase due to non-standard temperature (2.0 x 16%) Corrected fuel to climb 2.0 0.3 2. 3 Gallons In addition, the distance to climb, as given in figure 5-6, may be correct- ed for non-standard temperature as follows: Distance to climb, standard temperature Increase due to non-standard temperature (14 nautical miles x 16%) Corrected distance to climb The resultant cruise distance is: 14 2 16 Nautical Miles CESSNA MODEL 172M SECTION 5 PERFORMANCE The fuel required for cruise is endurance times fuel consumption: 4. 1 hours x 7.0 gallons/hour = 28.7 Gallons The total estimated fuel required is as follows: Engine start, taxi, and takeoff Climb 1. 1 2. 3 Cruise 28.7 Total fuel required 32. 1 Gallons This will leave a fuel reserve of: 38.0 -32.1 5. 9 Gallons Once the flight is underway, ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the trip with ample reserve. LANDING A procedure similar to the takeoff calculations should be used for estimating the landing distance at the destination airport. Figure 5-10 presents maximum performance technique landing distances for various airport altitude and temperature combinations. The distances corres- ponding to 2000 feet altitude and 30°C should be used and result in the following: Ground roll Total distance to clear a 50-foot obstacle 590 Feet 1370 Feet Total distance Climb distance Cruise distance 420 -16 404 Nautical Miles With an expected 10 knot headwind, the ground speed for cruise is pre- dicted to be: 109 -10 99 Knots A correction for wind may be made based on Note 2 of the landing chart. The distance correction for a 6 knot headwind is: 6 Knots 9 Knots x 10% = 7% Decrease This results in the following wind-corrected figures: Therefore, the time required for the cruise portion of the trip is: 5-6 404 Nautical Miles 99 Knots = 4.1 Hours Ground roll Total distance over a 50-foot obstacle 549 Feet 1274 Feet These distances are well within the landing field length quoted previously for this sample problem. 5-7 SECTION 5 PERFORMANCE FLAPS UP KIAS KCAS FLAPS 10° KIAS KCAS 40 49 499 49 88 40 AIRSPEED CALIBRATION NORMAL STATIC SOURCE 62 680 5550 50 550 60 689 55 62 CESSNA CESSNA MODEL 172M MODEL 172M AIRSPEED CALIBRATION FLAPS UP NORMAL KIAS ALTERNATE KIAS FLAPS 10° NORMAL KIAS ALTERNATE STATIC SOURCE HEATER/VENTS AND WINDOWS CLOSED SECTION 5 PERFORMANCE 40 39 6550 49 50 51 61 60 60 70 80 90 90 100 110 130 71 82 91 101 111 121 131 141 120 140 770 70 80 90 70 80 89 880 100 110 120 130 140 ALTERNATE KIAS 99 108 118 128 138 440 40 40 51 6859 550 60 77 70 80 61 71 81 85 888 85 888 FLAPS 40° RF 70 71 88 80 85 80 85 NORMAL KIAS ALTERNATE KIAS 6660 550 40 88 38 50 70 22 8 80 85 83 70 79 HEATER/VENTS OPEN AND WINDOWS CLOSED 90 100 89 110 120 99 108 118 128 130 140 139 FLAPS 40° 40 50 60 449 KIAS KCAS 70 80 47 54 62 71 81 85 86 $18 17 Figure 5-1. Airspeed Calibration (Sheet 1 of 2) FLAPS UP NORMAL KIAS ALTERNATE KIAS FLAPS 10° NORMAL KIAS ALTERNATE KIAS FLAPS 40° 40 50 40 68 689 60 70 220 36 48 59 70 40 489 669 8880 40 50 60 70 80 85 38 49 59 69 79 84 99 6789 5-8 NORMAL KIAS ALTERNATE KIAS 40 50 60 70 650 6540 770 80 85 184 34 47 57 67 77 81 WINDOWS OPEN 80 90 82 93 100 110 120 130 103 113 123 133 143 140 FLAPS UP NORMAL KIAS 40 ALTERNATE KIAS 26 40 433 50 650 60 57 720 FLAPS 10° NORMAL KIAS ALTERNATE KIAS 49 433 650 40 50 70 80 85 25 43 57 69 80 85 189 8 FLAPS 40° NORMAL KIAS ALTERNATE KIAS 429 40 50 25 41 54 584 60 260 70 80 85 67 78 84 Figure 5-1. Airspeed Calibration (Sheet 2 of 2) 5-9 SECTION 5 PERFORMANCE 120 CESSNA CESSNA MODEL 172M MODEL 172M SECTION 5 PERFORMANCE STALL SPEEDS TEMPERATURE CONVERSION CHART 100 DEGREES FAHRENHEIT 80 80 60 40 40 20 20 0 -20 -40 -40 -20 0 20 40 10 DEGREES CELSIUS 5-10 Figure 5-2. Temperature Conversion Chart 60 60 CONDITIONS: Power Off NOTES: 1. 2. Maximum altitude loss during a stall recovery is approximately 180 feet. KIAS values are approximate. MOST REARWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT LBS FLAP DEFLECTION 0º 30° 45° 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 42 50 45 54 50 50 59 2300 10º 38 47 40 51 45 40° 36 44 38 47 43 && 589 56 52 855 59 71 54 66 51 62 MOST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION 2300 ㅎㅎ 등 0º ANGLE OF BANK 30° 45° 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS 47 42 53 51 44 51 57 47 41 47 44 51 555 57 56 55 52 49 828 63 66 75 61 62 56 58 66 126 72 Figure 5-3. Stall Speeds 5-11 5-12 TAKEOFF DISTANCE MAXIMUM WEIGHT 2300 LBS PERFORMANCE SECTION 5 CONDITIONS: Flaps Up Full Throttle Prior to Brake Release Paved, Level, Dry Runway Zero Wind NOTES: 1. 2. 3. 4. 5. Maximum performance technique as specified in Section 4. Prior to takeoff from fields above 3000 feet elevation, the mixture should be leaned to give maximum RPM in a full throttle, static runup. Decrease distances 10% for each 9 knots headwind. For operation with tailwinds up to 10 knots, increase distances by 10% for each 2 knots. Where distance value has been deleted, climb performance after lift-off is less than 150 fpm at takeoff speed. For operation on a dry, grass runway, increase distances by 15% of the "ground roll" figure. MODEL 172M CESSNA WEIGHT LBS TAKEOFF SPEED KIAS 0°C 10°C 20°C 30°C 40°C PRESS ALT FT LIFT AT OFF 50 FT TOTAL TOTAL TOTAL TOTAL TOTAL GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 2300 52 59 S.L. 1000 850 775 1380 835 1475 895 1575 960 1685 1030 1795 1510 915 1615 980 1725 1050 1845 1125 1970 2000 930 1650 1000 1770 1075 1895 1155 2030 1235 2170 3000 1020 1815 1100 1945 1180 2085 1270 2235 1360 2395 4000 1125 2000 1210 2145 1300 2305 1395 2475 1495 2655 5000 1235 2210 1330 2375 1430 2555 1540 2750 1650 2960 6000 1365 2450 1470 2640 1580 2850 1700 3070 7000 1505 2730 1625 2955 1750 3190 8000 1665 3065 1800 3320 Figure 5-4. Takeoff Distance (Sheet 1 of 2) TAKEOFF DISTANCE 2100 LBS AND 1900 LBS REFER TO SHEET 1 FOR APPROPRIATE CONDITIONS AND NOTES. MODEL 172M CESSNA PERFORMANCE TAKEOFF 0°C 10°C 20°C 30°C SPEED PRESS WEIGHT KIAS ALT LBS FT LIFT AT OFF 50 FT TOTAL TOTAL TOTAL TOTAL GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS 40°C TOTAL 2100 50 50 56 S.L. 630 1000 690 1130 680 1210 725 1290 780 1375 835 1465 1235 740 1320 795 1405 855 1500 915 1600 2000 755 1350 810 1440 870 1540 935 1645 1000 1755 3000 830 1475 890 1580 955 1690 1025 1805 1100 1930 4000 910 1620 980 1735 1050 1860 1125 1990 1210 2130 5000 1000 1780 1075 1910 1155 2050 1240 2195 1330 2355 6000 1100 1965 1185 2115 1275 2270 1370 2435 1465 2615 7000 1215 2180 1305 2345 1405 2520 1510 2715 1620 2920 8000 1340 2425 1445 2615 1555 2815 1675 3040 1795 3280 1900 47 47 54 S.L. 505 915 540 975 580 1035 620 1105 665 1175 1000 550 995 590 1060- 635 1130 680 1205 725 1280 2000 600 1085 645 1155 695 1230 745 1315 795 1400 3000 660 1180 710 1260 $760 1345 815 1435 870 1530 4000 725 1290 775 1380 835 1475 895 1575 955 1680 5000 795 1415 855 1515 915 1620 $985 1735 1055 1850 6000 870 1555 940 1670 1010 1785 1080 1910 1160 2045 7000 960 1715 1035 1840 1110 1975 1195 2115 1280 2265 8000 1060 1900 1140 2040 1225 2190 1320 2350 1415 2520 5-13 Figure 5-4. Takeoff Distance (Sheet 2 of 2) SECTION 5 SECTION 5 PERFORMANCE CESSNA MODEL 172M CESSNA MODEL 172M RATE OF CLIMB CONDITIONS: Flaps Up Full Throttle Mixture Leaned for Maximum RPM During Climb SECTION 5 PERFORMANCE TIME, FUEL, AND DISTANCE TO CLIMB CONDITIONS: Flaps Up Full Throttle Standard Temperature NOTES: 1. 2. 3. 4. Add 1.1 gallons of fuel for engine start, taxi and takeoff allowance. To obtain maximum rate of climb as shown in this chart, lean to maximum RPM during climb. Increase time, fuel and distance by 10% for each 10°C above standard temperature. Distances shown are based on zero wind. FROM SEA LEVEL PRESS CLIMB WEIGHT LBS RATE OF CLIMB - FPM ALT WEIGHT LBS FT SPEED KIAS PRESSURE ALTITUDE FT TEMP °C CLIMB SPEED RATE OF CLIMB TIME FUEL USED KIAS FPM -20°C MIN GALLONS DISTANCE NM 0°C 20°C 40°C 2300 S.L. 78 755 695 630 565 2300 S.L. 15 78 645 0 0.0 0 2000 76 655 595 535 470 4000 74 555 500 440 1000 13 77 605 2 0.3 2 380 6000 72 460 405 350 290 8000 70 2000 11 76 560 3 0.7 4 365 310 255 200 10,000 68 270 215 165 3000 9 75 520 5 1.1 7 12,000 66 175 125 4000 7 74 480 7 1.5 9 Figure 5-5. Rate of Climb 5000 5 73 435 9 1.9 12 6000 3 72 395 12 2.3 16 7000 1 71 355 15 2.8 19 8000 -1 70 315 18 3.3 23 9000 -3 69 270 21 3.9 28 10,000 -5 68 230 25 4.5 11,000 -7 67 185 30 12,000 -9 66 145 36 2%2 33 5.2 40 6.1 48 5-14 Figure 5-6. Time, Fuel, and Distance to Climb 5-15 SECTION 5 PERFORMANCE CRUISE PERFORMANCE CONDITIONS: Recommended Lean Mixture 2300 Pounds SE 5-15 CESSNA MODEL 172M CESSNA MODEL 172M RANGE PROFILE 45 MINUTES RESERVE 38.0 GALLONS USABLE FUEL CONDITIONS: 2300 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind SECTION 5 PERFORMANCE This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the distance during climb as shown in figure 5-6. Reserve fuel is based on 45 minutes at 45% BHP and is 4.3 gallons. PRESSURE ALTITUDE 20°C BELOW STANDARD TEMP STANDARD TEMPERATURE 20°C ABOVE STANDARD TEMP RPM % % KTAS GPH KTAS % GPH KTAS BHP GPH BHP BHP NOTES: 1. 2000 2550 2500 2400 68 2300 61 2200 55 4000 2600 80 2500 72 2400 65 2300 58 2200 52 6000 2650 80 2600 76 2500 2400 2300 56 2200 8000 2700 80 2600 72 2500 2400 59 2300 54 2200 48 10,000 2700 76 2600 69 2500 63 2400 57 2300 51 2200 46 12,000 2650 69 2600 66 2500 60 2400 54 2300 49 2200 44 BRENEEN OPENER INDONE CONDES 268477 80 114 8.8 76 111 8.3 107 7.5 102 6.9 96 6.4 116 8.8 111 7.9 107 7.3 101 6.7 95 6.3 118 8.8 116 8.3 69 111 7.6 62 106 7.0 100 6.5 50 94 6.1 120 116 65 111 105 99 93 999688 8.8 8.0 7.3 6.8 6.4 6.0 45 120 8.4 115 7.6 110 7.1 104 6.6 97 6.2 48 92 5.8 117 7.6 114 7.4 108 6.8 57 102 6.4 51 96 6.0 91 5.7 41 BREEN ET57 PIERRE DECKED NORTE ENERGE 75 113 8.2 71 111 7.8 64 107 7.2 58 101 6.7 52 95 6.2 75 116 8.3 68 111 7.5 61 106 6.9 55 100 6.5 49 93 6.1 75 118 8.2 71 116 7.9 65 110 7.2 59 104 6.7 53 98 6.3 47 92 5.9 75 120 8.3 68 115 7.5 62 109 7.0 56 103 6.6 51 97 6.2 91 5.8 72 120 7.9 65 114 7.3 59 108 6.8 54 102 6.4 96 6.0 43 90 5.7 65 116 7.3 62 113 7.0 106 6.6 100 6.2 46 95 5.9 89 5.5 28272 RENE FREE FENCRE FERRY CECECE BREZZ3 7766 71 113 7.8 67 111 7.5 2. 61 106 6.9 55 99 6.5 49 93 6.1 12,000 71 116 7.8 64 110 7.2 58 104 6.7 53 98 6.3 10,000 47 92 5.9 71 118 7.8 68 115 7.5 62 109 7.0 56 103 6.5 50 97 6.1 45 91 5.8 71 120 7.8 65 114 7.3 59 108 6.8 53 101 6.3 48 96 6.0 ALTITUDE - FEET 6000 43 90 5.7 68 119 7.6 62 112 7.0 56 106 6.6 51 100 6.2 46 95 5.8 2000 41 89 5.5 62 114 59 111 54 105 49 99 43 94 38 88 299955 7.0 6.8 6.4 6.0 5.7 5.3 084073 5-16 Figure 5-7. Cruise Performance 120 KTAS 8000 FULL THROTTI 104 KTAS 94 KTAS 115 KTAS 112 KTAS 91 KTAS 102 KTAS 116 KTAS 109 KTAS 4000 75% POWER 65% POWER + 45% POWER- 55% POWER 88 KTAS 99 KTAS 86 KTAS 112 KTAS 106 KTAS 97 KTAS S.L. 400 420 440 RANGE 460 480 NAUTICAL MILES 500 520 Figure 5-8. Range Profile (Sheet 1 of 2) 5-17 5-18 ALTITUDE FEET SECTION 5 PERFORMANCE RANGE PROFILE 45 MINUTES RESERVE 48.0 GALLONS USABLE FUEL CONDITIONS: 2300 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind 12,000 NOTES: 1. 2. This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the distance during climb as shown in figure 5-6. Reserve fuel is based on 45 minutes at 45% BHP and is 4.3 gallons. 10,000 120 KTAS 8000 6000 FULL THROTTLE 116 KTAS 109 KTAS 4000 2000 75% POWE 104 KTAS 115 KTAS 94 KTAS 91 KTAS 112 KTAS 102 KTAS 65% POWER 45% POWER 55% POWER 112 KTAS 106 KTAS S.L. 560 580 600 620 RANGE NAUTICAL MILES Figure 5-8. Range Profile (Sheet 2 of 2) 88 KTAS 99 KTAS CESSNA MODEL 172M CESSNA MODEL 172M ALTITUDE - FEET ENDURANCE PROFILE 45 MINUTES RESERVE 38.0 GALLONS USABLE FUEL SECTION 5 PERFORMANCE CONDITIONS: 2300 Pounds Recommended Lean Mixture for Cruise Standard Temperature NOTES: 1. 2. This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the time during climb as shown in figure 5-6. Reserve fuel is based on 45 minutes at 45% BHP and is 4.3 gallons. 12,000 10,000 8000 6000 4000 2000 86 KTAS 97 KTAS S.L. 640 660 680 3 75% POWER 65% POWER 55% POWERE 4 ENDURANCE - HOURS 5 Figure 5-9. Endurance Profile (Sheet 1 of 2) 45% POWER 5-19 6