Weight and Balance Loading Form
Model _________________________________________________ Date ____________________________________________________
Serial Number___________________________________________ Reg. Number _____________________________________________
Item Pounds (3,900 max.) Index moment/100
Airplane basic empty weight
Fr ont seat occupants
Ro w 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 takeoff
Subtotal
Takeoff condition
L ess fuel to destination (gallons)
Landing condition
* Fuel for start, taxi, and takeoff 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
Figure 6-6. Typical weight and balance loading form.
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 6-7. Sample weight and moment index for occupants.
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.
Baggage Moments/100
Weight Arm +167
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
17
33
50
67
84
100
117
134
150
167
184
200
217
234
251
267
284
301
317
334
Figure 6-8. Sample weight and moment index for baggage.
Usable Fuel – Arm +117
Gallons Pounds Moment/100
10
20
30
40
50
60
70
80
90
100
60
120
180
240
300
360
420
480
540
600
70
140
211
281
351
421
491
562
632
702
Figure 6-9. Sample weight and moment index for fuel.
4,000
3,900
3,800
3,600
3,500
3,400
3,200
3,000
2,800
2,600
2,400
106 108 110 112 114 116 118
CG inches aft of datum
Weight (lb)
3,900
4,6004,5004,4004,3004,200
4,100
4,000
3,800
3,700
3,600
3,500
3,400
3,100
3,300
3,200
3,000
2,900
2,800
2,700
2,600
Maximum zero fuel weight
Moment/100
Envelope based on the following weight and CG limit data (landing gear down)
Weight condition FWD CG limit Aft CG limit
3,900 pounds (max takeoff/landing) 110.6 117.5
3,250 pounds or less 106.6 117.5
Maximum takeoff
and landing weight
Figure 6-10. Sample moment limits versus weight envelope.