Weight and Balance Data

Note to Pilots: Always double-check the data provided on the aircraft pages against the latest weight and balance data stored in each aircraft. Pilots are reminded that it is their responsibility to ensure that they are in compliance with 14 CFR 91.103.

Plane 739UL
Gross Weight (lbs) 2400
Empty Weight (lbs) 1462.7
Useful Load 937.3
Arm (inches) 39.1
Moment (E. Wt. x Arm) / 1000 57.289
Usable fuel Wt (6 lbs/ga) 240
Fuel Arm 46.0
Fuel Moment (/1000), full fuel 11.0
Oil Weight/Moment 15/-0.2
Front Seat Arm (inches) 38.5
Rear Seat Arm (inches) 79.5
Baggage Area Arm (areas1 / 2) 95.0
CG Limits at Gross Wt. 94.3 to 113.8

at 2050 lbs

74 to 97.3

at 1950 lbs

67.5 to 92

at 1350 lbs

n/a

na = not applicable
* = not available, but negligible

To determine whether weight and balance are within limits,
1. Multiply each weight by appropriate arm (result = moment),
2. Divide each product by 1000 (result = moment /1000), listed above as Moment,
3. Add all moments together,
4. Compare sum to CG limit range.

Sample Loading Problem

N4312R, Cessna 172M Weight x Arm = Moment
(lbs-in/1000)
Empty Weight 1446.5 38.5 55.7
Oil 15 -13.3 -0.2
Usable Fuel 228 47.8 10.9
Pilot and Front Passengers 340 37.1 12.6
Rear Passengers 260 73 19
Baggage Area 1 (120 max) 10 90.9 0.9
Baggage Area 2 (50 max) 0 108-142 0
Total 2299.5 98.9

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