Weight and Balance Loading Form Model _________________________________________________ Date ____________________________________________________  Serial Number___________________________________________ Reg. Number _____________________________________________  Item Pounds (3,900 max.) Index moment/100 Airplane basic empty weight Front seat occupants Row 2 seats Baggage (200 lb max.) Subtotal  Z ero fuel condition (3,500 max.)  F uel loading (gallons) Subtotal  R amp condition * Less fuel for start, taxi, and takeo ff Subtotal Takeoff  conditio n  L ess fuel to destination (gallons) Landing condition * Fuel for start, taxi, and takeo ff  is normally 24 pounds at a moment index of 28. 2,625 320 290 90 3,325 480 3,805 −24 3,781 −210 3,571 2,864 336 412 150 3,762 562 4,324 −28 4,296 −246 4,050 80 35 Occupant Moments/100 Weight Front seats Arm +105 Row 2 seats Arm +142 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240 250 105 116 126 137 147 158 168 179 189 200 210 221 231 242 252 263 142 156 170 185 199 213 227 241 256 270 284 298 312 327 341 355 Figure 6-6.  Typical weight and balance loading form. Figure 6-7.  Sample weight and moment index for occupants. 6-4 Locate the moment divided by 100 diagonal line for 4,296 and  follow it down until it crosses the horizontal line for 3,781  pounds. These lines cross inside the envelope at the vertical  line for a CG location of 114 (113.6) inches aft of the datum. The maximum allowable takeoff weight is 3,900 pounds, and  this airplane weighs 3,781 pounds. The CG limits for 3,781  pounds are 109.8 to 117.5. The CG of 114 (113.6) inches  falls within these allowable limits.