Performance Data for Cessna 195

problem, the time, fuel and distance to climb may be determined from Figure 5-7 for normal climb. The difference between the values shown in the table for 2000 feet and 8000 feet results in the following: Time: Fuel: 11 Minutes 2.2 Gallons Distance: 15 Nautical Miles These values are for a standard temperature and are sufficiently accurate for most flight planning purposes. However, a further correction for the effect of temperature may be made as noted on the climb chart. The approximate effect of a nonstandard temperature is to increase the time, fuel and distance by 10% for each 10°C above standard temperature, due to the lower rate of climb. In this case, 1 assuming a temperature 16°C above standard the correction would be: 16°C 10°C -X 10% = 16% Increase With this factor included, the fuel estimate would be calculated as follows: Fuel to climb, standard temperature 2.2 Gallons Increase due to non-standard temperature (2.2 X 16%) 0.4 Gallons Corrected fuel to climb 2.6 Gallons Using a similar procedure for the distance to climb results in 18 nautical miles. The resultant cruise distance is: Total distance Climb distance Cruise distance 172SPHAUS-05 360 Nautical Miles -18 Nautical Miles 342 Nautical Miles (Continued Next Page) U.S. 5-7 SECTION 5 PERFORMANCE CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT SAMPLE PROBLEM (Continued) FUEL REQUIRED (Continued) With an expected 10 knot headwind, the ground speed for cruise is predicted to be: 117 Knots -10 Knots 107 Knots Therefore, the time required for the cruise portion of the trip is: 342 Nautical Miles = 3.2 Hours 107 Knots The fuel required for cruise is: 3.2 hours X 8.9 gallons/hour = 28.5 Gallons A 45-minute reserve requires: 45 60 X 8.9 gallons/hour = 6.7 Gallons The total estimated fuel required is as follows: Engine start, taxi, and takeoff Climb Cruise Reserve Total fuel required 1.4 Gallons 2.6 Gallons 28.5 Gallons 6.7 Gallons 39.2 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. (Continued Next Page) 5-8 U.S. 172SPHAUS-05 CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT SAMPLE PROBLEM (Continued) LANDING SECTION 5 PERFORMANCE A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-11 presents landing distance information for the short field technique. The distances corresponding to 2000 feet and 30°C are as follows: Ground roll Total distance to clear a 50-foot obstacle 650 Feet 1455 Feet A correction for the effect of wind may be made based on information presented in the note section of the landing chart, using the same procedure as outlined for takeoff. DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23°C above standard. This is not to be considered as an operating limitation. Reference should be made to Section 2 for engine operating limitations. 172SPHAUS-05 U.S. 5-9 SECTION 5 PERFORMANCE CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT AIRSPEED CALIBRATION NORMAL STATIC SOURCE CONDITIONS: Power required for level flight or maximum power descent. Flaps UP KIAS 50 60 70 80 90 100 110 120 130 140 150 160 KCAS 56 62 70 78 87 97 107 117 127 137 147 157 Flaps 10° KIAS 40 50 60 70 80 90 100 110 -- KCAS 51 57 63 71 80 89 99 109 www.Bww wwww Flaps FULL KIAS 40 50 60 70 80 85 KCAS 50 56 63 72 81 86 Figure 5-1 (Sheet 1 of 2)* 15-10 U.S. 172SPHAUS-05 CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT AIRSPEED CALIBRATION ALTERNATE STATIC SOURCE SECTION 5 PERFORMANCE CONDITIONS: Power required for level flight or maximum power descent. Flaps UP KIAS KCAS 50 60 70 80 90 100 110 120 130 140 150 160 56 62 68 76 85 95 105 115 125 134 144 154 Flaps 10° KIAS 40 50 60 70 80 90 100 110 KCAS 51 55 60 68 77 86 96 105 Flaps FULL KIAS 40 50 60 70 80 85 - KCAS 49 54 61 69 78 83 NOTE Windows and ventilators closed. Cabin heat, cabin air and defroster on maximum. Figure 5-1 (Sheet 2)* 172SPHAUS-05 U.S. 5-11 SECTION 5 PERFORMANCE CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT TEMPERATURE CONVERSION CHART B3093 120 100 80 60 60 60 40 Degrees - Fahrenheit 20 20 0 -20 -40 -40 -20 0 20 20 40 Degrees Celsius 15-12 U.S. Figure 5-2* 60 60 172SPHAUS-05 SECTION 5 PERFORMANCE CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT STALL SPEED AT 2550 POUNDS CONDITIONS: Power IDLE MOST REARWARD CENTER OF GRAVITY ANGLE OF BANK FLAP 0° 30° 45° 60° SETTINGS KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 48 53 52 57 62 63 76 75 10° 42 45 54 54 70 71 FULL 40 48 43 52 52 57 65 68 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK FLAP 0° 30° 45° 60° SETTINGS KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 48 53 10° 43 51 FULL 40 48 242 52 57 61 63 76 75 46 55 43 52 52 57 65 68 NOTE • • Altitude loss during a stall recovery may be as much as 230 feet. KIAS values are approximate. Figure 5-3* 172SPHAUS-05 U.S. 5-13 SECTION 5 PERFORMANCE Headwind 83094 35 30 50 495 25 85 Tailwind Wind Component - Knots 20 20 15 10 5 CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT CROSSWIND COMPONENT 35 XXX30 Wind Velocity - Knots ☑ 30% ☑ 25 20 40° -50% 60° -70° 80° 0 10 160° 10 Angle between wind "direction and runway: 140°4 90°- #100° 120° 15 05 10 15 20 25 30 35 Crosswind Component - Knots MAXIMUM DEMONSTRATED CROSSWIND VELOCITY Takeoff, Flaps UP Takeoff, Flaps 10° Landing, Flaps 10°. Landing, Flaps FULL 115-14 U.S. Figure 5-4* 20 KNOTS 20 KNOTS 20 KNOTS 15 KNOTS 172SPHAUS-05 CESSNA MODEL 172S NAV III KAP 140 AUTOPILOT SECTION 5 PERFORMANCE SHORT FIELD TAKEOFF DISTANCE AT 2550 POUNDS CONDITIONS: Flaps 10° Full Throttle prior to brake release. Paved, Level, Dry Runway Lift Off: 51 KIAS Zero Wind Speed at 50 Feet: 56 KIAS 0°C 10°C 20°C 30°C 40°C Total Total Feet Feet Total Feet Total Total Feet Feet Pressure Altitude - Feet Gnd To Gnd To Gnd To Gnd To Roll Clear Roll Clear Roll Clear Roll Clear Roll Clear Feet 50 Feet 50 Feet 50 Feet 50 Feet 50 Foot Foot Obst Obst Gnd To Foot Obst Foot Obst Foot Obst Sea Level 1000 2000 860 1465 925 1575 995 940 1600 1010 1720 1090 1025 1755 1110 1890 1195 2035 1690 1070 1810 1150 1945 1850 1170 1990 1260 2135 3000 4000 5000 6000 1495 2605 1615 2830 1745 1285 2190 1380 2355 1125 1925 1215 2080 1310 2240 1410 2420 1515 2605 1235 2120 1335 2295 1440 2480 1550 2685 1660 2880 1355 2345 1465 2545 1585 2755 3075 1705 2975 1825 3205 18753320 2010 3585 7000 1645 2910 1785 3170 1920 3440 8000 1820 3265 1970 3575 2120 3880 2065 3730 2215 4045 2280 4225 2450 4615 NOTE • Short field technique as specified in Section 4. Prior to takeoff from fields above 3000 feet pressure altitude, the mixture should be leaned to give maximum RPM in a full throttle, static run-up. Decrease distances 10% for each 9 knots headwind. For operation with tailwinds up to 10 knots, increase distances by 10% for each 2 knots. For operation on dry grass runway, increase distances by 15% of the "ground roll" figure. 172SPHAUS-05 Figure 5-5* (Sheet 1 of 3) U.S. 5-15