two sets of numbers from one another, but given the fact that  the numbers read zero at sea level, it is known that the time  to climb from sea level to 8,000 feet is 10 minutes. It is also  known that 21 pounds of fuel is used and 20 NM is covered  during the climb. However, the temperature is 22 °C, which is  7° above the standard temperature of 15 °C. The notes section  of this chart indicate that the findings must be increased by ten  percent for each 7° above standard. Multiply the findings by  ten percent or .10 (10  ×  .10 = 1, 1 + 10 = 11 minutes). After  accounting for the additional ten percent, the findings should  read 11 minutes, 23.1 pounds of fuel, and 22 NM. Notice that  the fuel is reported in pounds of fuel, not gallons. Aviation  fuel weighs six pounds per gallon, so 23.1 pounds of fuel is  equal to 3.85 gallons of fuel (23.1 ÷ 6 = 3.85).  The next example is a cruise and range performance chart.  This type of table is designed to give TAS, fuel consumption,  endurance in hours, and range in miles at specific cruise  configurations. Use  Figure 11-27  to determine the cruise and  range performance under the given conditions.  Find 5,000 feet pressure altitude in the first column on the  left side of the table. Next, find the correct rpm of 2,400  in the second column. Follow that line straight across and  read the TAS of 116 mph and a fuel burn rate of 6.9 gallons  per hour. As per the example, the aircraft is equipped with  a fuel carrying capacity of 38 gallons. Under this column,  read that the endurance in hours is 5.5 hours and the range  in miles is 635 miles.  Cruise power setting tables are useful when planning cross- country flights. The table gives the correct cruise power  settings, as well as the fuel flow and airspeed performance  numbers at that altitude and airspeed.  Refer to  Figure 11-28  for this sample problem. First, locate  the pressure altitude of 6,000 feet on the far left side of the  table. Follow that line across to the far right side of the table  under the 20 °C (or 36 °F) column. At 6,000 feet, the rpm  setting of 2,450 will maintain 65 percent continuous power  at 21.0 "Hg with a fuel flow rate of 11.5 gallons per hour and  airspeed of 161 knots.  The last cruise chart referenced is a cruise performance graph.  This graph is designed to tell the TAS performance of the  airplane depending on the altitude, temperature, and power  setting. Using  Figure 11-30,  find the TAS performance based  on the given information.  First, move up the left side of the graph to 5,000 feet and  standard temperature. Follow the line straight across the  graph until it intersects the 65 percent line under both the  reserve and no reserve categories. Draw a line straight down  from both intersections to the bottom of the graph. At 65  percent power with a reserve, the range is approximately  522 miles. At 65 percent power with no reserve, the range  should be 581 miles.  Another type of cruise chart is a best power mixture range  graph. This graph gives the best range based on power  setting and altitude. Using  Figure 11-29,  find the range at  65 percent power with and without a reserve based on the  provided conditions.  Figure 11-27.  Cruise and range performance.  Sample Problem 8  Sample Problem 7  Sample Problem 6  Notes  Conditions  ALT  2,500  5,000  7,500  10,000  GAL/  Hour  9.7  8.6  7.8  7.2  6.7  6.3  9.0  8.1  7.4  6.9  6.5  6.0  8.4  7.7  7.1  6.7  6.2  7.6  7.3  6.9  6.4  6.0  Endr.  hours  3.9  4.4  4.9  5.3  5.7  6.1  4.2  4.7  5.1  5.5  5.9  6.3  4.5  4.9  5.3  5.7  6.1  5.0  5.2  5.5  5.9  6.3  Range miles  525  570  600  620  630  625  565  600  625  635  630  600  625  645  640  640  650  655  650  635  Endr.  hours  4.9  5.6  6.2  6.7  7.2  7.7  5.3  5.9  6.4  6.9  7.4  7.9  5.7  6.2  6.7  7.2  7.7  6.3  6.5  7.0  7.5  8.0  Range miles  660  720  760  780  795  790  710  760  790  805  795  755  790  810  820  810  810  820  830  825  800  %  BHP  86  79  72  65  58  52  82  75  68  61  55  49  78  71  64  58  52  70  67  61  55  49  TAS  MPH  134  129  123  117  111  103  134  128  122  116  108  100  133  127  121  113  105  129  125  118  110  100  38 gal (no reserve)  48 gal (no reserve) RPM  2,700  2,600  2,500  2,400  2,300  2,200  2,700  2,600  2,500  2,400  2,300  2,200  2,700  2,600  2,500  2,400  2,300  2,650  2,600  2,500  2,400  2,300  Gross weight—2,300 lb.  Standard conditions  Zero wind  Lean mixture  Maximum cruise is normally limited to 75% power.  Pressure Altitude...............................................5,000 feet RPM..................................................................2,400 rpm Fuel Carrying Capacity..................38 gallons, no reserve OAT....................................................................Standard Pressure Altitude...............................................5,000 feet Pressure Altitude at Cruise................................6,000 feet  OAT..................................................36 °F above standard 11-24 