Section 5 – Performance
Cessna 335 · Performance Data
Overview
The document appears to be a performance data manual, but no specific content is available to provide a detailed overview. It is essential to have the actual text to summarize the key information and sections relevant to the Cessna 335.
Document
Source
Originally published by www.firebirdcreative.services. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 20
- File size
- 6.4 MB
- Publisher
- www.firebirdcreative.services
Specifications & performance
Extracted from this document.
Specifications
- Range (nm)
- 476
- Max speed (kt)
- 114
- Fuel capacity (gal)
- 40
- Rate of climb (fpm)
- 73
- Max takeoff weight (lb)
- 2,300
Performance
- Fuel burn (gph)
- 7.1
- Landing over 50ft
- 1,370
- Max crosswind (kt)
- 12
- Takeoff over 50ft
- 1,915
- Landing distance (ft)
- 590
- Takeoff distance (ft)
- 1,075
- Stall speed clean (kt)
- 44
- Stall speed landing (kt)
- 40
V-speeds
- VR
- 52
- VX
- 50
- VY
- 56
- VS1
- 44
- VSO
- 40
Weight & balance
- Useful load (lb)
- 2,250
- Max takeoff weight (lb)
- 2,300
Common. Rarer than 3% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Cessna 335.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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Full document text
CESSNA MODEL 172N SECTION 5 PERFORMANCE TABLE OF CONTENTS SECTION 5 PERFORMANCE Page Introduction Use of Performance Charts Sample Problem Takeoff Cruise • 5-3 5-3 5-3 5-4 5-5 Fuel Required ° Landing 5-5 5-7 Figure 5-1, Airspeed Calibration - Normal Static Source Airspeed Calibration - Alternate Static Source 5-8 5-9 Figure 5-2, Temperature Conversion Chart Figure 5-3, Stall Speeds 5-10 • • 5-11 Figure 5-4, Takeoff Distance - 2300 Lbs 5-12 Takeoff Distance - 2100 Lbs and 1900 Lbs 5-13 Figure 5-5, Rate of Climb 5-14 Range Profile Figure 5-6, Time, Fuel, and Distance to Climb Figure 5-7, Cruise Performance. Figure 5-8, Range Profile - 50 Gallons Fuel Figure 5-9, Endurance Profile Endurance Profile Figure 5-10, Landing Distance 5-15 ° 5-16 - 40 Gallons Fuel 5-17 5-18 40 Gallons Fuel 50 Gallons Fuel 5-19 5-20 5-21 ° 5-1/(5-2 blank) CESSNA MODEL 172N SECTION 5 PERFORMANCE INTRODUCTION Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions, and also, to facilitate the planning of flights in detail and with reasonable accuracy. The data in the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting techniques. It should be noted that the performance information presented in the range and endurance profile charts allows for 45 minutes reserve fuel based on 45% power. Fuel flow data for cruise is based on the recommended lean mixture setting. Some indeterminate variables such as mixture leaning technique, fuel metering characteristics, en- gine and propeller condition, and air turbulence may account for varia- tions of 10% or more in range and endurance. Therefore, it is impor- tant to utilize all available information to estimate the fuel required for the particular flight. USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus- trate the effect of different variables. Sufficiently detailed information is provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasona- ble accuracy. SAMPLE PROBLEM The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typi- cal flight. The following information is known: AIRPLANE CONFIGURATION Takeoff weight Usable fuel TAKEOFF CONDITIONS Field pressure altitude Temperature Wind component along runway Field length 2250 Pounds 40 Gallons 1500 Feet 28°C (16° C above standard) 12 Knot Headwind 3500 Feet 5-3 SECTION 5 PERFORMANCE CESSNA MODEL 172N CRUISE CONDITIONS Total distance Pressure altitude Temperature Expected wind enroute LANDING CONDITIONS Field pressure altitude Temperature Field length TAKEOFF 460 Nautical Miles 5500 Feet 20°C (16°C above standard) 10 Knot Headwind 2000 Feet 25°C 3000 Feet The takeoff distance chart, figure 5-4, should be consulted, keeping in mind that the distances shown are based on the short field tech- nique. Conservative distances can be established by reading the chart at the next higher value of weight, altitude and temperature. For ex- ample, in this particular sample problem, the takeoff distance informa- tion presented for a weight of 2300 pounds, pressure altitude of 2000 feet and a temperature of 30°C should be used and results in the following: Ground roll Total distance to clear a 50-foot obstacle 1075 Feet 1915 Feet These distances are well within the available takeoff field length. However, a correction for the effect of wind may be made based on Note 3 of the takeoff chart. The correction for a 12 knot headwind is: 12 Knots 9 Knots × 10% 13% Decrease This results in the following distances, corrected for wind: Ground roll, zero wind Decrease in ground roll (1075 feet × 13%) Corrected ground roll 1075 140 935 Feet 5-4 50-foot obstacle, zero wind Total distance to clear a Decrease in total distance (1915 feet 13%) Corrected total distance to clear a 50-foot obstacle 1915 249 1666 Feet JJ CESSNA MODEL 172N SECTION 5 PERFORMANCE CRUISE The cruising altitude should be selected based on a consideration of trip length, winds aloft, and the airplane's. performance. A typical cruising altitude and the expected wind enroute have been given for this sample problem. However, the power setting selection for cruise must be determined based on several considerations. These include the cruise performance characteristics presented in figure 5-7, the range profile chart presented in figure 5-8, and the endurance profile chart presented in figure 5-9. The relationship between power and range is illustrated by the range profile chart. Considerable fuel savings and longer range result when lower power settings are used. The range profile chart indicates that use of 65% power at 5500 feet yields a predicted range of 523 nautical miles with no wind. The endu- rance profile chart, figure 5-9, shows a corresponding 4.7 hours. The range figure of 523 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet. Range, zero wind Decrease in range due to wind (4.7 hours 10 knot headwind) Corrected range 523 47 476 Nautical Miles This indicates that the trip can be made without a fuel stop using ap- proximately 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 planned altitude and expected temperature conditions. The engine speed chosen is 2500 RPM, which results in the following: Power True airspeed Cruise fuel flow 64% 114 Knots 7.1 GPH The power computer may be used to determine power and fuel con- sumption more accurately during the flight. FUEL REQUIRED The total fuel requirement for the flight may be estimated using the 5-5 SECTION 5 PERFORMANCE CESSNA MODEL 172N performance information in figure 5-6 and 5-7. For ths sample prob-
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lem, figure 5-6 shows that a climb from 2000 feet to 6000 feet requires 1.3 gallons of fuel. The corresponding distance during the climb is 9 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 non-standard tempera- ture 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, assuming a temperature 16°C above standard, the correction would be: 16°C 10°C × 10% = 16% Increase With this factor included, the fuel estimate would be calculated as fol- lows: Fuel to climb, standard temperature Increase due to non-standard temperature (1.3 × 16%) Corrected fuel to climb 1.3 0.2 1.5 Gallons Using a similar procedure for the distance to climb results in 10 nauti- cal miles. The resultant cruise distance is: Total distance Climb distance Cruise distance 460 -10 450 Nautical Miles With an expected 10 knot headwind, the ground speed for cruise is predicted to be: 114 -10 104 Knots Therefore, the time required for the cruise portion of the trip is: 450 Nautical Miles 104 Knots = 4.3 Hours The fuel required for cruise is: 4.3 hours 7.1 gallons/hour 5-6 = 30.5 Gallons J J J J J J J J J J J J J CESSNA MODEL 172N The total estimated fuel required is as follows: SECTION 5 PERFORMANCE Engine start, taxi, and takeoff 1.1 Climb 1.5 Cruise 30.5 Total fuel required 33.1 Gallons This will leave a fuel reserve of: 40.0 -33.1 6.9 Gallons Once the flight is underway, ground speed checks will provide a more accurate basis for estimating the time enroute and the corres- ponding fuel required to complete the trip with ample reserve. LANDING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-10 presents land- ing 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 590 Feet 1370 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff. 5-7 SECTION 5 PERFORMANCE FLAPS UP AIRSPEED CALIBRATION NORMAL STATIC SOURCE CESSNA MODEL 172N KIAS KCAS 49 449 40 550 229 60 62 770 80 90 80 90 100 110 120 130 140 80 89 99 108 118 128 138 FLAPS 10° KIAS KCAS 49 499 40 50 60 70 50 55 77 680 8 80 85 62 71 80 85 FLAPS 40° KIAS KCAS 4445 40 50 60 47 54 584 680 62 77 70 80 85 71 81 86 5-8 Figure 5-1. Airspeed Calibration (Sheet 1 of 2) JJ J J CESSNA MODEL 172N FLAPS UP NORMAL KIAS ALTERNATE KIAS AIRSPEED CALIBRATION ALTERNATE STATIC SOURCE HEATER/VENTS AND WINDOWS CLOSED 40 39 49 SECTION 5 PERFORMANCE 650 5550 77 51 61 71 82 91 80 60 70 80 90 100 110 90 120 130 140 101 111 121 131 141 FLAPS 10° NORMAL KIAS ALTERNATE KIAS 40 40 40 50 51 659 550 60 61 77 70 80 71 81 885 FLAPS 40° NORMAL KIAS 40 ALTERNATE KIAS 38 550 669 770 60 60 HEATER/VENTS OPEN AND WINDOWS CLOSED 89 80 85 79 83 40 50 60 70 80 90 100 770 80 69 110 120 130 140 59 70 80 89 99 108 118 128 139 FLAPS UP NORMAL KIAS ALTERNATE KIAS 36 49 18 48 FLAPS 10° NORMAL KIAS ALTERNATE KIAS FLAPS 40° NORMAL KIAS 50 60 70 80 85 40 38 49 59 69 79 79 189 69 49 40 09899 84 40 50 60 70 80 85 ALTERNATE KIAS 34 47 57 960 184 67 77 81 WINDOWS OPEN FLAPS UP NORMAL KIAS ALTERNATE KIAS 49 40 26 483 50 60 43 650 57 77 70 888 80 90 70 82 93 100 110 120 130 140 103 113 123 133 143 FLAPS 10° NORMAL KIAS ALTERNATE KIAS 49 40 50 60 70 80 85 25 09 43 57 69 80 85 60 FLAPS 40° NORMAL KIAS ALTERNATE KIAS 229 40 25 50 60 540 659 280 70 80 85 84 960 41 54 67 78 589 Figure 5-1. Airspeed Calibration (Sheet 2 of 2) 5-9 SECTION 5 PERFORMANCE CESSNA MODEL 172N TEMPERATURE CONVERSION CHART 120 100 80 60 FAHRENHEIT 60 DEGREES 40 40 20 20 0 5-10 -20 -40 -40 -20 0 20 40 DEGREES CELSIUS - Figure 5-2. Temperature Conversion Chart 60 60 JJ J CESSNA MODEL 172N STALL SPEEDS SECTION 5 PERFORMANCE CONDITIONS: Power Off NOTES: 1. Maximum altitude loss during a stall recovery may be as much as 180 feet. 2. KIAS values are approximate. MOST REARWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION 0º ANGLE OF BANK 30° 45° 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 2300 10° 40° 200 00 42 50 45 54 50 38 47 40 51 45 གྷg 59 56 36 44 38 42 47 43 52 5551 59 71 54 66 62 MOST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION 0º ANGLE OF BANK 30° 45° 60º KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 47 53 5557 51 57 2300 10° 44 51 47 55 559 56 52 28 63 66 75 61 40° 41 47 47 44 51 49 49 56 83 62 58 260 72 66 Figure 5-3. Stall Speeds 5-11 5-12 512 TAKEOFF DISTANCE MAXIMUM WEIGHT 2300 LBS SHORT FIELD SECTION 5 PERFORMANCE CONDITIONS: Flaps Up Full Throttle Prior to Brake Release Paved, Level, Dry Runway Zero Wind NOTES: 1. 2. 3. 4. Short field 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. For operation on a dry, grass runway, increase distances by 15% of the "ground roll" figure. TAKEOFF 0°C 10°C 20°C 30°C 40°C WEIGHT KIAS LBS LIFT AT OFF 50 FT SPEED PRESS ALT TOTAL FT 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 TOTAL 2300 52 59 SL. 1000 720 1300 775 1390 835 1490 895 1590 960 1700 790 1420 850 1525 915 1630 980 1745 1050 1865 2000 865 1555 930 1670 1000 1790 1075 1915 1155 2055 3000 950 1710 1025 1835 1100 1970 1185 2115 1270 2265 4000 1045 1880 1125 2025 1210 2175 1300 2335 1400 2510 5000 1150 2075 1240 2240 1335 2410 1435 2595 1540 2795 6000 1265 2305 1365 2485 1475 2680 1585 2895 1705 3125 7000 1400 2565 1510 2770 1630 3000 1755 3245 1890 3515 8000 1550 2870 1675 3110 1805 3375 1945 3670 2095 3990 Figure 5-4. Takeoff Distance (Sheet 1 of 2) MODEL 172N CESSNA TAKEOFF DISTANCE 2100 LBS AND 1900 LBS SHORT FIELD REFER TO SHEET 1 FOR APPROPRIATE CONDITIONS AND NOTES. MODEL 172N CESSNA PERFORMANCE SECTION 5 TAKEOFF 0°C 10°C 20°C 30°C 40°C SPEED WEIGHT KIAS LBS PRESS ALT FT TOTAL TOTAL TOTAL TOTAL TOTAL LIFT AT OFF 50 FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS 2100 50 56 S.L. 585 1070 630 1140 680 1220 725 1300 780 1390 1000 640 1165 690 1245 740 1330 795 1420 850 1520 2000 700 1270 755 1360 810 1455 870 1555 935 1665 3000 770 1390 830 1490 890 1595 955 1710 1025 1830 4000 845 1525 910 1640 980 1755 1050 1880 1130 2015 5000 930 1680 1000 1805 1075 1935 1155 2075 1240 2230 6000 1025 1850 1100 1990 1185 2140 1275 2300 1370 2475 7000 1130 2050 1215 2210 1310 2380 1410 2560 1515 2755 8000 1245 2275 1345 2460 1450 2655 1560 2865 1680 3090 1900 17 47 ... 54 S.L 470 865 505 920 540 985 580 1045 620 1115 1000 515 940 550 1005 590 1070 635 1140 680 1215 2000 560 1025 605 1095 645 1170 695 1245 745 1330 3000 615 1115 660 1195 710 1275 760 1365 815 1455 4000 670 1220 725 1305 780 1400 835 1495 895 1595 5000 740 1340 795 1435 855 1535 920 1640 985 1755 6000 810 1470 875 1575 940 1690 1010 1810 1085 1940 7000 895 1620 965 1740 1035 1865 1115 2000 1195 2145 8000 985 1790 1065 1925 1145 2065 1230 2220 1320 2385 5-13 Figure 5-4. Takeoff Distance (Sheet 2 of 2) SECTION 5 PERFORMANCE CONDITIONS: Flaps Up RATE OF CLIMB MAXIMUM Full Throttle NOTE: Mixture leaned above 3000 feet for maximum RPM. CESSNA MODEL 172N PRESS CLIMB RATE OF CLIMB - FPM WEIGHT LBS ALT SPEED FT KIAS -20°C 0°C 20°C 40°C 2300 S.L. 73 875 815 755 695 2000 72 765 705 650 590 4000 71 655 600 545 485 6000 70 545 495 440 385 8000 69 440 390 335 280 10,000 68 335 285 230 12,000 67 230 180 5-14 Figure 5-5. Rate of Climb ردا CESSNA MODEL 172N CONDITIONS: SECTION 5 PERFORMANCE TIME, FUEL, AND DISTANCE TO CLIMB MAXIMUM RATE OF CLIMB Flaps Up Full Throttle Standard Temperature NOTES: 1. 2. 3. 4. Add 1.1 gallons of fuel for engine start, taxi and takeoff allowance. Mixture leaned above 3000 feet for maximum RPM. Increase time, fuel and distance by 10% for each 10°C above standard temperature. Distances shown are based on zero wind. FROM SEA LEVEL WEIGHT LBS PRESSURE ALTITUDE CLIMB RATE OF TEMP SPEED CLIMB ос TIME FUEL USED FT KIAS FPM MIN GALLONS DISTANCE NM 2300 S.L. 15 73 770 0 0.0 0 1000 13 2000 11 3000 9 N N W 73 725 1 0.3 2 72 675 3 0.6 3 72 630 4 0.9 5O 4000 7 71 580 6 1.2 8 5000 5 71 535 8 1.6 10 6000 3 70 485 10 1.9 12 7000 1 69 440 12 2.3 15 8000 -1 69 390 15 2.7 19 9000 -3 68 345 17 3.2 22 10,000 -5 68 295 21 3.7 27 11,000 -7 67 250 24 4.2 32 12,000 -9 67 200 29 4.9 38 Figure 5-6. Time, Fuel, and Distance to Climb 5-15 SECTION 5 PERFORMANCE CRUISE PERFORMANCE CONDITIONS: 2300 Pounds Recommended Lean Mixture CESSNA MODEL 172N 20°C BELOW PRESSURE STANDARD TEMP STANDARD TEMPERATURE 20°C ABOVE STANDARD TEMP RPM ALTITUDE FT % BHP KTAS GPH 2000 2500 --- % BHP 75 % KTAS GPH KTAS GPH BHP 116 8.4 71 2400 72 2300 64 106 111 8.0 67 111 7.5 63 7.1 2200 56 101 6.3 2100 50 95 5.8 47 4000 2550 2500 76 116 8.5 71 2400 68 111 7.6 2300 60 105 6.8 2200 54 100 6.1 51 2100 48 94 5.6 6000 2600 2500 72 116 8.1 2400 64 110 7.2 2300 57 105 6.5 2200 51 99 5.9 49 2100 46 93 5.5 8000 2650 ---- --- ---- 2600 76 120 8.6 2500 68 115 7.7 2400 61 110 6.9 2300 55 104 6.2 2200 49 98 5.7 10,000 2650 76 122 8.5 2600 72 120 8.1 2500 65 114 2400 58 109 2300 52 103 2200 47 97 7.3 6.5 6.0 5.6 12,000 2300 50 2200 2600 68 119 2500 62 114 2400 56 108 102 7.7 64 6.9 6.3 5.8 46 96 5.5 6837 278659 268477 PRJONG FOTD04 Jo341 -60 105 6.7 56 53 100 6.1 50 94 5.6 45 118 8.4 71 115 8.0 64 110 71 105 6.4 54 99 5.9 48 46 93 5.5 44 75 120 8.4 71 115 7.6 60 109 6.8 57 54 104 6.2 52 98 5.7 47 44 92 5.4 42 75 122 8.4 71 71 120 8.0 64 114 7.2 58 109 6.5 52 103 6.0 47 97 5.5 71 122 8.0 61 55 68 119 114 108 7.6 6.8 50 102 45 96 5.4 118 7.2 58 113 6.5 53 107 6.0 48 101 5.6 44 95 5.4 F8607 F607** FU6277 768507 670247 65547 115 7.9 110 7.1 105 6.3 99 5.8 93 5.4 118 7.9 115 7.5 109 6.7 104 6.1 98 5.7 92 5.3 120 7.9 64 114 71 109 6.4 103 5.9 97 5.5 91 5.2 122 7.9 119 7.5 113 6.8 55 108 6.2 102 5.8 45 96 5.4 121 7.5 118 71 58 112 6.5 6.2 52 107 6.0 5.8 48 101 5.6 44 95 5.3 61 117 6.8 111 6.2 51 106 5.8 100 5.5 43 94 5.3 5-16 Figure 5-7. Cruise Performance
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