CESSNA SECTION 5 PERFORMANCE
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- Eustacia Gladys Stafford
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1 CESSNA SECTION 5 TABLE OF CONTENTS Page Introduction Use of Performance Charts Sample Problem Takeoff Cruise Fuel Required Landing Airspeed Calibration - Normal Static Source Airspeed Calibration - Alternate Static Source Altimeter Correction - Alternate Static Source Pressure Conversion Temperature Conversion Chart ISA Conversion and Operating Temperature Limits Stall Speeds Wind Components Maximum Engine Torque for Takeoff Maximum Engine Torque for Climb AIRPLANES WITH CARGO POD Short Field Takeoff Distance Flaps UP Takeoff Distance Rate of Climb - Takeoff Flap Setting Climb Gradient - Takeoff Flap Setting Maximum Rate of Climb - Flaps UP Climb Gradient - Takeoff - Flaps UP Cruise Climb - Flaps UP KIAS Rate of Climb - Balked Landing Time, Fuel, and Distance to Climb - Maximum Rate of Climb Time, Fuel, and Distance to Climb - Cruise Climb KIAS Cruise Performance Cruise Maximum Torque (Continued Next Page) 208BPHCUS-00 U.S. 5-1
2 SECTION 5 TABLE OF CONTENTS (Continued) CESSNA Page AIRPLANES WITH CARGO POD INSTALLED (Continued) Fuel and Time Required - Maximum Cruise Power ( NM) Fuel and Time Required - Maximum Cruise Power ( NM) 5-60 Fuel and Time Required - Maximum Range Power ( NM) Fuel and Time Required - Maximum Range Power ( NM) 5-62 Range Profile Endurance Profile Time, Fuel, and Distance to Descend Short Field Landing Distance AIRPLANES WITHOUT CARGO POD Short Field Takeoff Distance Flaps UP Takeoff Distance Rate of Climb - Takeoff Flap Setting Climb Gradient - Takeoff Flap Setting Maximum Rate of Climb - Flaps UP Climb Gradient - Takeoff - Flaps UP Cruise Climb - Flaps UP KIAS Rate of Climb - Balked Landing Time, Fuel, and Distance to Climb - Maximum Rate of Climb Time, Fuel, And Distance to Climb - Cruise Climb KIAS Cruise Performance Cruise Maximum Torque Fuel and Time Required Maximum Cruise Power ( NM) Fuel and Time Required Maximum Cruise Power ( NM) Fuel and Time Required Maximum Range Power ( NM) Fuel and Time Required Maximum Range Power ( NM) Range Profile Endurance Profile Time, Fuel, and Distance to Descend Short Field Landing Distance U.S. 208BPHCUS-00
3 CESSNA SECTION 5 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 using average piloting techniques and an airplane and engine in good condition and equipped with a Hartzell propeller. WARNING To make sure that performance in this section can be duplicated, the airplane and engine must be maintained in good condition. Pilot proficiency and proper preflight planning using data necessary for all flight phases is also required to assure expected performance with ample margins of safety. It should be noted that the performance information presented in the range and endurance profile charts allows for 45 minutes reserve fuel at the specified cruise power and altitude. Some indeterminate variables such as engine and propeller condition, and air turbulence may account for variations of 10% or more in range and endurance. Therefore, it is important to utilize all available information to estimate the fuel required for the particular flight. Notes have been provided on various graphs and tables to approximate performance with the INERTIAL SEPARATOR in BYPASS and/or cabin heat on. The effect will vary, depending upon airspeed, temperature, and altitude. At lower altitudes, where operation on the torque limit is possible, the effect of the inertial separator will be less, depending upon how much power can be recovered after the separator vanes have been extended. In some cases, performance charts in this section include data for temperatures which are outside of the ISA Conversion and Operating Temperature Limits chart. This data has been included to aid in interpolation. USE OF CHARTS Performance data is presented in tabular or graphical form to illustrate 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 reasonable accuracy. 208BPHCUS-00 U.S. 5-3
4 SECTION 5 SAMPLE PROBLEM CESSNA The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight of an airplane equipped with a cargo pod. A similar calculation can be made for an airplane without a cargo pod using charts identified as appropriate for this configuration. Assume the following information has already been determined: AIRPLANE CONFIGURATION Takeoff weight Usable fuel (CARGO POD INSTALLED) 8600 Pounds 2246 Pounds TAKEOFF CONDITIONS: Field pressure altitude Temperature Wind component along runway Field length 3500 Feet 16 C (8 C Above Standard) 12 Knot Headwind 4000 Feet (Paved, Level, Dry Runway) CRUISE CONDITIONS: Total distance 650 Nautical Miles Pressure altitude 11,500 Feet Temperature 8 C Expected wind enroute 10 Knot Headwind LANDING CONDITIONS: Field pressure altitude 1500 Feet Temperature 25 C Wind component along runway 12 Knot Headwind Field length 3000 Feet (Paved, Level, Dry Runway) 5-4 U.S. 208BPHCUS-00
5 CESSNA SECTION 5 SAMPLE PROBLEM (Continued) TAKEOFF The Takeoff Distance chart should be consulted, keeping in mind that distances shown are based on the short field technique. Conservative distances can be established by reading the chart at the next higher value of weight, altitude and temperature. For example, in this particular sample problem, the takeoff distance information presented for a weight of 8807 pounds (3994 kg), pressure altitude of 4000 feet and a temperature of 20 C should be used and results in the following: Ground roll Total distance to clear a 50-foot obstacle 1965 Feet 3010 Feet These distances are well within the available takeoff field length. However, a correction for the effect of wind may be made based on information presented in the note section of the takeoff chart. The correction for a 12 knot headwind is: 12 Knots X 10% = 11% Decrease 11 Knots This results in the following takeoff distances, corrected for a 12 knot headwind: Ground roll, zero wind 1965 Feet Decrease in ground roll (1965 feet X 11%) -216 Feet Corrected ground roll 1749 Feet Total distance to clear a 50-foot obstacle, zero wind Decrease in total distance (3010 feet X 11%) Corrected total distance to clear 50-foot obstacle 3010 Feet -331 Feet 2679 Feet (Continued Next Page) 208BPHCUS-00 U.S. 5-5
6 SECTION 5 SAMPLE PROBLEM (Continued) CESSNA TAKEOFF (Continued) The Maximum Engine Torque For Takeoff chart should be consulted for takeoff power setting. For the above ambient conditions, the power setting is: Takeoff Torque 2397 FT-LB The Maximum Engine Torque For Climb chart should be consulted for climb power setting from field elevation to cruise altitude. For the above ambient conditions, the power setting is: Field Elevation Maximum Climb Torque Cruise Altitude Maximum Climb Torque 2189 FT-LB 1713 FT-LB 5-6 U.S. 208BPHCUS-00
7 CESSNA SECTION 5 SAMPLE PROBLEM (Continued) CRUISE The cruising altitude should be selected based on a consideration of trip length, winds aloft, and the airplane s performance. A 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 the Cruise Performance, Cruise Maximum Torque charts, Fuel and Time Required, and the Range and Endurance Profile charts. The Range Profile chart shows range at maximum cruise power and also at maximum range power. For this sample problem, maximum cruise power and 1900 RPM will be used. The Cruise Performance chart for 12,000 feet pressure altitude is entered using 10 C temperature. These values most nearly correspond to the planned altitude and expected temperature conditions. The torque setting for maximum cruise power is 1517 FT-LB torque at 1900 RPM which results in the following: True Airspeed 173 Knots Cruise Fuel Flow 364 PPH 208BPHCUS-00 U.S. 5-7
8 SECTION 5 SAMPLE PROBLEM (Continued) CESSNA FUEL REQUIRED The total fuel requirement for the flight may be estimated using the performance information in the Time, Fuel, and Distance to Climb chart, Cruise Performance chart, and Time, Fuel, and Distance to Descend chart or in the Fuel and Time Required (Maximum Cruise Power) chart and Fuel and Time Required (Maximum Range Power) chart. The longer detailed method will be used for this sample problem, but the use of Fuel and Time Required (Maximum Cruise Power) or Fuel and Time Required (Maximum Range Power) charts will provide the desired information for most flight planning purposes. START UP, TAXI AND TAKEOFF The fuel required for a standard start up, taxi and takeoff is approximately 35 pounds. Additional fuel will be required for extended taxi and hold times and must be accounted for during preflight planning. CLIMB For this sample problem, the Time, Fuel, And Distance To Climb - Maximum Rate Climb chart may be used to determined the time, fuel and distance required for a maximum rate of climb for a weight of 8807 pounds and a temperature 20 C above standard. The difference between the values shown in the table for 4000 feet and 12,000 feet result in the following: Time: Fuel: Distance: 11 Minutes 77 Pounds 22 Nautical Miles (Continued Next Page) 5-8 U.S. 208BPHCUS-00
9 CESSNA SECTION 5 SAMPLE PROBLEM (Continued) FUEL REQUIRED (Continued) DESCENT Similarly, the Time, Fuel, And Distance For Cruise Descent chart shows that a descent from 12,000 feet to Sea Level results in the following: Time: Fuel: Distance: 15 Minutes 77 Pounds 43 Nautical Miles The distances shown on the climb and descent charts are for zero wind. A correction for the effect of wind may be made as follows: Distance during climb with no wind: 22 Nautical Miles Decrease in distance due to wind: (11/60 x 10 knots headwind) - 2 Nautical Miles Corrected distance to climb: 20 Nautical Miles Similarly, the distance for descent may be corrected for the effect of wind and results in the following. Distance during descent with no wind: 43 Nautical Miles Decrease in distance due to wind: (15/60 x 10 knots headwind) - 3 Nautical Miles Corrected distance during descent: 40 Nautical Miles (Continued Next Page) 208BPHCUS-00 U.S. 5-9
10 SECTION 5 SAMPLE PROBLEM (Continued) CESSNA FUEL REQUIRED (Continued) CRUISE The cruise distance is then determined by subtracting the distance during climb and distance during descent from the total distance. Total distance: Distance during climb: Distance during descent: Cruise distance: 650 Nautical Miles - 20 Nautical Miles - 40 Nautical Miles 590 Nautical Miles With an expected 10 knot headwind, the ground speed for cruise is predicted to be: 173 Knots -10 Knots 163 Knots Therefore, the time required for the cruise portion of the trip is: The fuel required for cruise is: 590 Nautical Miles = 3.6 Hours 163 Knots 3.6 hours X 364 pounds/hour = 1311 Pounds A 45-minute reserve requires: 45 X 364 pounds/hour = 273 Pounds 60 (Continued Next Page) 5-10 U.S. 208BPHCUS-00
11 CESSNA SECTION 5 SAMPLE PROBLEM (Continued) FUEL REQUIRED (Continued) The total estimated fuel required is as follows: Engine start, taxi, and takeoff Climb Cruise Descent Reserve Total Fuel Required 35 Pounds +77 Pounds Pounds +77 Pounds Pounds 1773 Pounds 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 takeoff should be used for estimating the landing distance at the destination airport. The estimated landing weight is as follows: Takeoff weight Fuel required for climb, cruise, and descent Landing weight 8600 Pounds Pounds 6827 Pounds The Short Field Landing Distance chart presents landing distance information for the short field technique. The landing distances for a weight of 7000 pounds and corresponding to 2000 feet pressure altitude and a temperature of 30 C should be used and are as follows: Ground roll Total distance to clear a 50-foot obstacle 935 Feet 1740 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. 208BPHCUS-00 U.S. 5-11
12 SECTION 5 CESSNA 5-12 U.S. Figure 5-1 (Sheet 1 of 2) 208BPHCUS-00
13 CESSNA SECTION 5 Figure 5-1 (Sheet 2) 208BPHCUS-00 U.S. 5-13
14 SECTION 5 CESSNA 5-14 U.S. Figure BPHCUS-00
15 CESSNA SECTION 5 PRESSURE CONVERSION Example: Pressure = inches of mercury Pressure = millibars. Figure BPHCUS-00 U.S. 5-15
16 SECTION 5 CESSNA TEMPERATURE CONVERSION CHART 5-16 U.S. Figure BPHCUS-00
17 TEMPORARY REVISION FOR CESSNA PILOT S OPERATING HANDBOOK AND AIRPLANE FLIGHT MANUAL Publication Affected: Model 208B (867 SHP) Garmin G1000, Serials 208B2197 and 208B5000 and On, basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual, Revision 1, dated 22 May Airplane Serial Numbers Affected: Description of Change: Airplanes 208B2197 and 208B5000 and On. Section 5, Performance, page 5-17, ISA Conversion and Operating Temperature Limits, Replace Figure 5-5. Filing Instructions: Insert this temporary revision in the Model 208B (867 SHP) Garmin G1000, Serials 208B2197 and 208B5000 and On, basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual adjacent to page Removal Instructions: This temporary revision must be removed and discarded when Revision 2 has been collated into the basic Pilot s Operating Handbook and FAA Approved Airplane Flight Manual. In Section 5, Performance, page 5-17, ISA Conversion and Operating Temperature Limits, replace Figure 5-5 with the information on the following page: 208BPHCUS-01 TR02
18 TEMPORARY REVISION FOR CESSNA PILOT S OPERATING HANDBOOK AND AIRPLANE FLIGHT MANUAL ISA CONVERSION AND OPERATING TEMPERATURE LIMITS Figure BPHCUS-01 TR02
19 CESSNA SECTION 5 ISA CONVERSION AND OPERATING TEMPERATURE LIMITS CAUTION Do not operate in shaded area of chart. Figure BPHCUS-00 U.S. 5-17
20 SECTION 5 CESSNA 5-18 U.S. Figure BPHCUS-00
21 CESSNA SECTION 5 WIND COMPONENTS NOTE Maximum demonstrated crosswind velocity is 20 knots (not a limitation). Figure BPHCUS-00 U.S. 5-19
22 SECTION 5 CESSNA MAXIMUM ENGINE TORQUE FOR TAKEOFF CONDITIONS: 1900 RPM 60 KIAS INERTIAL SEPARATOR - NORMAL 5-20 U.S. Figure 5-8 (Sheet 1 of 2) 208BPHCUS-00
23 CESSNA SECTION 5 MAXIMUM ENGINE TORQUE FOR TAKEOFF NOTE 1. Torque increases approximately 30 FT-LB from 0 to 60 KIAS. 2. Torque on this chart shall be achieved without exceeding 850 C ITT or percent N g. When the ITT exceeds 825 C, this power setting is time limited to 5 minutes. 3. With the inertial separator in BYPASS, where altitude and temperature do not permit 2397 FT-LB for takeoff, decrease torque setting by 85 FT-LB. 4. With the cabin heater ON, where altitude and temperature do not permit 2397 FT-LB for takeoff, decrease torque setting by 75 FT-LB. Figure 5-8 (Sheet 2 208BPHCUS-00 U.S. 5-21
24 SECTION 5 CESSNA MAXIMUM ENGINE TORQUE FOR CLIMB CONDITIONS: 1900 RPM V y KIAS INERTIAL SEPARATOR NORMAL 5-22 U.S. Figure 5-9 (Sheet 1 of 2) 208BPHCUS-00
25 CESSNA SECTION 5 MAXIMUM ENGINE TORQUE FOR CLIMB NOTE 1. Torque on this chart shall be achieved without exceeding 825 C ITT or percent N g. 2. With the inertial separator in BYPASS, decrease torque setting by 115 FT-LB. 3. With the cabin heater ON, decrease torque setting by 85 FT- LB. Figure 5-9 Sheet 2 208BPHCUS-00 U.S. 5-23
26 SECTION 5 CESSNA 5-24 U.S. Figure 5-10 (Sheet 1 of 5) 208BPHCUS-00
27 CESSNA SECTION 5 Figure 5-10 (Sheet 2) 208BPHCUS-00 U.S. 5-25
28 SECTION 5 CESSNA 5-26 U.S. Figure 5-10 (Sheet 3) 208BPHCUS-00
29 CESSNA SECTION 5 Figure 5-10 (Sheet 4) 208BPHCUS-00 U.S. 5-27
30 SECTION 5 CESSNA 5-28 U.S. Figure 5-10 (Sheet 5) 208BPHCUS-00
31 CESSNA SECTION 5 Figure 5-11 (Sheet 1 of 3) 208BPHCUS-00 U.S. 5-29
32 SECTION 5 CESSNA 5-30 U.S. Figure 5-11 (Sheet 2) 208BPHCUS-00
33 CESSNA SECTION 5 Figure 5-11 (Sheet 3) 208BPHCUS-00 U.S. 5-31
34 SECTION 5 CESSNA 5-32 U.S. Figure BPHCUS-00
35 CESSNA SECTION 5 Figure BPHCUS-00 U.S. 5-33
36 SECTION 5 CESSNA 5-34 U.S. Figure BPHCUS-00
37 CESSNA SECTION 5 Figure BPHCUS-00 U.S. 5-35
38 SECTION 5 CESSNA 5-36 U.S. Figure BPHCUS-00
39 CESSNA SECTION 5 Figure BPHCUS-00 U.S. 5-37
40 SECTION 5 CESSNA This Page Intentionally Left Blank 5-38 U.S. 208BPHCUS-00
41 CESSNA SECTION 5 Figure 5-18 (Sheet 1 of 2) 208BPHCUS-00 U.S. 5-39
42 SECTION 5 CESSNA Figure 5-18 (Sheet 2) 5-40 U.S. 208BPHCUS-00
43 CESSNA SECTION 5 Figure 5-19 (Sheet 1 of 11) 208BPHCUS-00 U.S. 5-41
44 SECTION 5 CESSNA Figure 5-19 (Sheet 2) 5-42 U.S. 208BPHCUS-00
45 CESSNA SECTION 5 Figure 5-19 (Sheet 3) 208BPHCUS-00 U.S. 5-43
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47 CESSNA SECTION 5 Figure 5-19 (Sheet 5) 208BPHCUS-00 U.S. 5-45
48 SECTION 5 CESSNA Figure 5-19 (Sheet 6) 5-46 U.S. 208BPHCUS-00
49 CESSNA SECTION 5 Figure 5-19 (Sheet 7) 208BPHCUS-00 U.S. 5-47
50 SECTION 5 CESSNA Figure 5-19 (Sheet 8) 5-48 U.S. 208BPHCUS-00
51 CESSNA SECTION 5 Figure 5-19 (Sheet 9) 208BPHCUS-00 U.S. 5-49
52 SECTION 5 CESSNA Figure 5-19 (Sheet 10) 5-50 U.S. 208BPHCUS-00
53 CESSNA SECTION 5 Figure 5-19 (Sheet 11) 208BPHCUS-00 U.S. 5-51
54 SECTION 5 CESSNA Figure 5-20 (Sheet 1 of 7) 5-52 U.S. 208BPHCUS-00
55 CESSNA SECTION 5 Figure 5-20 (Sheet 2) 208BPHCUS-00 U.S. 5-53
56 SECTION 5 CESSNA Figure 5-20 (Sheet 3) 5-54 U.S. 208BPHCUS-00
57 CESSNA SECTION 5 Figure 5-20 (Sheet 4) 208BPHCUS-00 U.S. 5-55
58 SECTION 5 CESSNA Figure 5-20 (Sheet 5) 5-56 U.S. 208BPHCUS-00
59 CESSNA SECTION 5 Figure 5-20 (Sheet 6) 208BPHCUS-00 U.S. 5-57
60 SECTION 5 CESSNA Figure 5-20 (Sheet 7) 5-58 U.S. 208BPHCUS-00
61 CESSNA SECTION 5 NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 8% or CABIN HEAT ON, increase time by 4%. Figure 5-21 (Sheet 1 of 2) 208BPHCUS-00 U.S. 5-59
62 SECTION 5 CESSNA NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 11% and fuel by 4%, or CABIN HEAT ON, increase time by 8% and fuel by 4%. Figure 5-21 (Sheet 2) 5-60 U.S. 208BPHCUS-00
63 CESSNA SECTION 5 NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 5% and fuel by 2%, or CABIN HEAT ON, increase time by 5% and fuel by 2%. Figure 5-22 (Sheet 1 of 2) 208BPHCUS-00 U.S. 5-61
64 SECTION 5 CESSNA NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 3% and fuel by 4%, or CABIN HEAT ON, increase time by 2% and fuel by 3%. Figure 5-22 (Sheet 2) 5-62 U.S. 208BPHCUS-00
65 CESSNA SECTION 5 Figure BPHCUS-00 U.S. 5-63
66 SECTION 5 CESSNA Figure U.S. 208BPHCUS-00
67 CESSNA SECTION 5 Figure BPHCUS-00 U.S. 5-65
68 SECTION 5 CESSNA The Page Intentionally Left Blank 5-66 U.S. 208BPHCUS-00
69 CESSNA SECTION 5 Figure 5-26 (Sheet 1 of 5) 208BPHCUS-00 U.S. 5-67
70 SECTION 5 CESSNA 5-68 U.S. Figure 5-26 (Sheet 2) 208BPHCUS-00
71 CESSNA SECTION 5 Figure 5-26 (Sheet 3) 208BPHCUS-00 U.S. 5-69
72 SECTION 5 CESSNA 5-70 U.S. Figure 5-26 (Sheet 4) 208BPHCUS-00
73 CESSNA SECTION 5 Figure 5-26 (Sheet 5) 208BPHCUS-00 U.S. 5-71
74 SECTION 5 CESSNA Figure 5-27 (Sheet 1 of 5) NOTE Figures 5-27 thru 5-43 apply to airplanes configured WITHOUT a cargo pod U.S. 208BPHCUS-00
75 CESSNA SECTION 5 Figure 5-27 (Sheet 2) 208BPHCUS-00 U.S. 5-73
76 SECTION 5 CESSNA 5-74 U.S. Figure 5-27 (Sheet 3) 208BPHCUS-00
77 CESSNA SECTION 5 Figure 5-27 (Sheet 4) 208BPHCUS-00 U.S. 5-75
78 SECTION 5 CESSNA 5-76 U.S. Figure 5-27 (Sheet 5) 208BPHCUS-00
79 CESSNA SECTION 5 Figure 5-28 (Sheet 1 of 3) 208BPHCUS-00 U.S. 5-77
80 SECTION 5 CESSNA 5-78 U.S. Figure 5-28 (Sheet 2) 208BPHCUS-00
81 CESSNA SECTION 5 Figure 5-28 (Sheet 3) 208BPHCUS-00 U.S. 5-79
82 SECTION 5 CESSNA 5-80 U.S. Figure BPHCUS-00
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84 SECTION 5 CESSNA 5-82 U.S. Figure BPHCUS-00
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87 CESSNA SECTION 5 Figure BPHCUS-00 U.S. 5-85
88 SECTION 5 CESSNA This Page Intentionally Left Blank 5-86 U.S. 208BPHCUS-00
89 CESSNA SECTION 5 Figure 5-35 (Sheet 1 of 2) 208BPHCUS-00 U.S. 5-87
90 SECTION 5 CESSNA Figure 5-35 (Sheet 2) 5-88 U.S. 208BPHCUS-00
91 CESSNA SECTION 5 Figure 5-36 (Sheet 1 of 12) 208BPHCUS-00 U.S. 5-89
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93 CESSNA SECTION 5 Figure 5-36 (Sheet 3) 208BPHCUS-00 U.S. 5-91
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98 SECTION 5 CESSNA Figure 5-36 (Sheet 8) 5-96 U.S. 208BPHCUS-00
99 CESSNA SECTION 5 Figure 5-36 (Sheet 9) 208BPHCUS-00 U.S. 5-97
100 SECTION 5 CESSNA Figure 5-36 (Sheet 10) 5-98 U.S. 208BPHCUS-00
101 CESSNA SECTION 5 Figure 5-36 (Sheet 11) 208BPHCUS-00 U.S. 5-99
102 SECTION 5 CESSNA Figure 5-36 (Sheet 12) U.S. 208BPHCUS-00
103 CESSNA SECTION 5 Figure 5-37 (Sheet 1 of 7) 208BPHCUS-00 U.S
104 SECTION 5 CESSNA Figure 5-37 (Sheet 2) U.S. 208BPHCUS-00
105 CESSNA SECTION 5 Figure 5-37 (Sheet 3) 208BPHCUS-00 U.S
106 SECTION 5 CESSNA Figure 5-37 (Sheet 4) U.S. 208BPHCUS-00
107 CESSNA SECTION 5 Figure 5-37 (Sheet 5) 208BPHCUS-00 U.S
108 SECTION 5 CESSNA Figure 5-37 (Sheet 6) U.S. 208BPHCUS-00
109 CESSNA SECTION 5 Figure 5-37 (Sheet 7) 208BPHCUS-00 U.S
110 SECTION 5 CESSNA NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 9% or CABIN HEAT ON, increase time by 6%. Figure 5-38 (Sheet 1 of 2) U.S. 208BPHCUS-00
111 CESSNA SECTION 5 NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 11% and fuel by 4%, or CABIN HEAT ON, increase time by 7% and fuel by 3%. Figure 5-38 (Sheet 2) 208BPHCUS-00 U.S
112 SECTION 5 CESSNA NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 5% and fuel by 2%, or CABIN HEAT ON, increase time by 5% and fuel by 2%. Figure 5-39 (Sheet 1 of 2) U.S. 208BPHCUS-00
113 CESSNA SECTION 5 NOTE 1. Fuel required includes the fuel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea level and 45 minutes reserve. Time required includes the time during a maximum climb and descent. 2. With INERTIAL SEPARATOR in BYPASS, increase time by 2% and fuel by 5%, or CABIN HEAT ON, increase time by 2% and fuel by 3%. Figure 5-39 (Sheet 2) 208BPHCUS-00 U.S
114 SECTION 5 CESSNA Figure U.S. 208BPHCUS-00
115 CESSNA SECTION 5 Figure BPHCUS-00 U.S
116 SECTION 5 CESSNA Figure U.S. 208BPHCUS-00
117 CESSNA SECTION 5 Figure 5-43 (Sheet 1 of 5) 208BPHCUS-00 U.S
118 SECTION 5 CESSNA U.S. Figure 5-43 (Sheet 2) 208BPHCUS-00
119 CESSNA SECTION 5 Figure 5-43 (Sheet 3) 208BPHCUS-00 U.S
120 SECTION 5 CESSNA U.S. Figure 5-43 (Sheet 4) 208BPHCUS-00
121 CESSNA SECTION 5 Figure 5-43 (Sheet 5) 208BPHCUS-00 U.S
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