Weight and Balance

Occupants Minimum Maximum Usable Fuel Weight Moment Moment Front Seat Rear Seats 100 100 Main Wing Tanks Arm 75 Arm 85 Arm 121 2,400 1,848 2,057 Moment Moment Gallons Weight Moment Weight 100 Weight 100 2 2 , , 4 4 1 2 0 0 1 1 , , 8 8 5 6 6 3 2 2 , , 0 0 6 7 5 4 100 120 102 120 145 2,430 1,871 2,083 5 30 22 130 110 130 157 2,440 1,879 2,091 10 60 45 140 119 140 169 2,450 1,887 2,100 15 90 68 FUEL TANK 150 128 150 182 2,460 1,894 2,108 20 120 90 160 136 160 194 2,470 1,092 2,117 25 150 112 170 144 170 206 2,480 1,911 2,125 30 180 135 180 153 180 218 2,490 1,921 2,134 35 210 158 190 162 190 230 40 240 180 200 170 200 242 2,500 1,932 2,143 44 264 198 2,510 1,942 2,151 2,520 1,953 2,160 2,530 1,963 2,168 2,540 1,974 2,176 2,550 1,984 2,184 2,560 1,995 2,192 2,570 2,005 2,200 2,580 2,016 2,208 2,590 2,026 2,216 BAGGAGE AREA OIL 2,600 2,037 2,224 2,610 2,048 2,232 2,620 2,058 2,239 Minimum Maximum 2,630 2,069 2,247 *Oil Baggage or 5th Weight Moment Moment 2,640 2,080 2,255 Seat Occupant 100 100 2,650 2,090 2,263 Quarts Weight Mo 10 m 0 e n t Arm 140 2,100 1,617 1,800 2 2 , , 6 6 6 7 0 0 2 2 , , 1 1 0 1 1 2 2 2 , , 2 2 7 7 1 9 10 19 5 FUEL TANK Weight Mo 1 m 00 e n t 2 2 , , 1 1 1 2 0 0 1 1 , , 6 6 2 3 5 2 1 1 , , 8 8 0 1 8 7 2 2 , , 6 6 8 9 0 0 2 2 , , 1 1 2 3 3 3 2 2 , , 2 2 8 9 7 5 *Included in basic empty weight 2,130 1,640 1,825 10 14 2,140 1,648 1,834 2,700 2,144 2,303 20 28 2,150 1,656 1,843 2,710 2,155 2,311 Empty Weight ~ 2,015 30 42 2,160 1,663 1,851 2,720 2,166 2,319 MOM/ 100 ~ 1,554 40 56 2,170 1,671 1,860 2,730 2,177 2,326 50 70 2,180 1,679 1,868 2,740 2,188 2,334 60 84 2,190 1,686 1,877 2,750 2,199 2,342 Moment Limits vs Weight 70 98 2,760 2,210 2,350 Moment limits are based on the following weight and 80 112 2,200 1,694 1,885 2,770 2,221 2,358 center of gravity limit data (landing gear down). 90 126 2,210 1,702 1,894 2,780 2,232 2,366 Weight Forward AFT 100 140 2,220 1,709 1,903 2,790 2,243 2,374 Condition CG Limit CG Limit 110 154 2,230 1,717 1,911 2,950 lb (takeoff 82.1 84.7 120 168 2,240 1,725 1,920 2,800 2,254 2,381 or landing) 130 182 2,250 1,733 1,928 2,810 2,265 2,389 2,525 lb 77.5 85.7 140 196 2,260 1,740 1,937 2,820 2,276 2,397 2,475 lb or less 77.0 85.7 150 210 2,270 1,748 1,945 2,830 2,287 2,405 160 224 2,280 1,756 1,954 2,840 2,298 2,413 Sample Loading Problem Weight Mo1m70ent 238 2,290 1,763 1,963 2,850 2,309 2,421 180 252 2,300 1,771 1,971 2,860 2,320 2,426 Basic empty weight 2,015 119,0554 266 2,310 1,779 1,980 2,870 2,332 2,436 Fuel main tanks (44 gal) 264 200198 280 2,320 1,786 1,988 2,880 2,343 2,444 *Front seat passengers 300 210254 294 2,330 1,794 1,997 2,890 2,354 2,452 220 308 2,340 1,802 2,005 2,900 2,365 3,460 *Rear seat passengers 190 230230 322 2,350 1,810 2,014 2,910 2,377 2,468 Baggage 30 24042 336 2,360 1,817 2,023 2,920 2,388 2,475 250 350 2,370 1,825 2,031 2,930 2,399 2,483 260 364 2,380 1,833 2,040 2,940 2,411 2,491 Total 2,799 2,27 2 8 7 / 0 100 378 2,390 1,840 2,048 2,950 2,422 2,499 * Interpolate or, as in this case, add appropriate numbers. 10-9 AERA GNITAES way.) Once this has been done for each item, total the weight Table Method and moments and draw a line for both weight and moment The table method applies the same principles as the on the CG envelope graph. If the lines intersect within the computational and graph methods. The information envelope, the aircraft is loaded within limits. In this sample and limitations are contained in tables provided by the loading problem, the aircraft is loaded within limits. manufacturer. Figure 10-9 is an example of a table and a Figure 10-9. Loading schedule placard.