100 lb max 60 lb max Datum Front seats +37 Rear seats +74 Baggage B +116 Fuel +46.6 Baggage A +97 88 gal usable EWCG 36.1 Figure 5-2.  Airplane loading diagram. moments for all onboard fuel, personnel, equipment, cargo,  and baggage that is not included in the aircraft’s basic empty  weight (BEW).  Figure 5-4  is a sample of a typical equipment  list where many of the pertinent weights and moment values  can be found.  As part of preflight planning, fill in the blanks in the  worksheet with the specific data for the flight. The following  weights were used to complete the sample weight and balance  worksheet in  Figure 5-3 . Pilot ................................................................120 lb Front seat passenger .......................................180 lb Rear seat passenger ........................................175 lb Fuel (88 gal) ...................................................528 lb Baggage A ......................................................100 lb Baggage B ........................................................50 lb Multiply each item’s weight by its arm to determine the  moment. Then, determine the total weight and the sum of  the moments. Divide the total moment by the total weight to  determine the CG in inches from the datum. For this example,  the total weight is 3,027 pounds and the CG is 43.54 inches  aft of the datum (a negative result would have indicated a  CG forward of the datum).  To determine whether or not the airplane is properly loaded  for this flight, use the CG limits chart.  [Figure 5-5]  Draw a  line vertically upward from the CG of 43.54 inches and one  horizontally to the right from the loaded weight of 3,027  pounds. These lines cross inside the envelope, which shows  the airplane is properly loaded for takeoff, but 77 pounds  overweight for landing. Note that for this sample chart, the  envelope is defined by the solid black line that indicates  CG limits at or below maximum weight for takeoff  and landing. There is an additional region identified by a  segmented black line that includes weights suitable only for  takeoff. It is important to note these subtle differences as they  may or may not be found in every POH/AFM. A worksheet, such as the one shown in  Figure 5-3,  provides  a means to record and compute pertinent weights, arms, and  The manual computational method uses weights, arms, and  moments. It relates the total weight and CG location to a CG  limits chart similar to those included in the Type Certificate Data Sheet (TCDS) and the Pilot’s Operating Handbook/ Aircraft Flight Manual (POH/AFM). An important part of preflight planning is determining that  the aircraft is loaded so its weight and CG location are within  the allowable limits. The methods of accomplishing this are  the manual computational method using weights, arms, and  moments; the chart method using weight and moment indexes  [Figure 5-2];  and the loading graph method, which eliminates  the need for some mathematical calculations . Figure 5-1.  Weight and balance data needed to determine proper  loading of a small airplane. Manual Computational Method 5-2 Determining the Loaded Weight and CG 3,200 3,000 2,800 2,600 2,400 2,200 2,000 1,800 32  34  36  38  40  42  44  46  48 Fuselage station (in) Loaded aircraft weight (lb) Airplane basic empty weight  1,874.0 lb, EWCG +36.1 CG range  (+40.9) to (+46.0) at 3,100 lb (+33.0) to (+46.0) at 2,250 lb or less Straight line variation between points  given Empty weight CG range  None Maximum weight  3,100 lb takeoff/flight 2,950 lb landing No. of seats  4 (2 front at +37.0) (2 rear at +74.0) Maximum baggage  160 lb Area A (100 lb at +97.0) Area B (60 lb at +116.0) Fuel capacity  92 gal (88 gal usable); two 46 gal integral tanks in wings at +46.6 Oil capacity  12 qt (−15)