The loaded weight for this fl ght is 5,064 pounds, and the CG  is located at 42.47 inches aft of the datum. To determine that the weight and CG are within the allowable  range, refer to the CG range chart in  Figure 6-4 . Draw a line  vertically upward from 42.47 inches from the datum and one  horizontally from 5,064 pounds. These lines cross inside the  envelope, showing that the airplane is properly loaded. As mentioned in the previous chapter, anything that can be  done to make careful preflight planning easier makes flying safer. Many manufacturers furnish charts in the Pilot’s  Operating Handbook/Aircraft Flight Manual (POH/AFM)  that use weight and moment indexes rather than weight, arm,  and moments. The charts also help reduce errors by including  tables of moment indexes for the various weights. The Chart Method Using Weight and Moment  Indexes Consider the loading for this particular flight The pilot completes a chart like the one in  Figure 6-6  using  moment indexes from tables in  Figures 6-7  and  6-8 . The moments divided by 100 in the index column are found  in the charts in  Figures 6-7  through  6-9 . If the exact weight  is not in the chart, interpolate between the weights that are  included. When a weight is greater than any of those shown  in the charts, add the moment indexes for a combination of  weights to get that which is desired. For example, to get the  moments divided by 100 for the 320 pounds in the front seats,  add the moment index for 100 pounds (105) to that for 220  pounds (231). This gives the moment index of 336 for 320  pounds in the front seats.  Refer again to  Figures 6-2  and  6-3 . Use the formula in  Figure 6-5  to find the CG in percent MAC. The loaded CG is located at 36.3 percent MAC. Usethe moment limits versus weight envelope in  Figure 6-10 to determine if the weight and balance conditions are  within allowable limits for both takeoff and landing at the  destination. The moment limits versus weight envelope is an  enclosed area on a graph of three parameters. The diagonal  line representing the moment divided by 100 crosses the  horizontal line representing the weight at the vertical line  representing the CG location in inches aft of the datum. When  the lines cross inside the envelope, the aircraft is loaded  within its weight and CG limits. Determining the CG in Percentage of Mean  Aerodynamic Chord (MAC) Figure 6-5.  Finding CG in percent MAC. Figure 6-4.  Sample CG range chart. 5,200 5,000 4,800 4,600 4,400 4,200 4,000 32  34  36  38  40  42  44 Inches from the datum Weight (lb) CG in % MAC CG in inches from LEMAC x 100 MAC = 22.37 x 100 61.6 = 36.3% MAC = Takeoff: – 3,781 lb and 4,296 moment divided by 100 Landing: – 3,571 lb and 4,050 moment divided by 100 The loaded CG is 42.47 inches aft of the datum. The MAC is 61.6 inches long. The LEMAC is located at station 20.1. The CG is 42.47 – 20.1 = 22.37 inches aft of LEMAC. Cruise fuel flow = 16 gallons per hou Estimated time en route = 2 hours, 10 minutes Reserve fuel = 45 minutes = 12 gallons Total required fuel = 47 gallons 6-3