Cessna U206G Stationair 6 weight & balance

Data source

POH Section 2 Weight Limits (p. 2-6); Section 6, Figure 6-1, Figure 6-7 (Sample Loading Problem), Figure 6-9 (CG Moment Envelope) and Figure 6-10 (CG Limits) (pages 14-109 of u206g__poh__1978.pdf) · version type

• The Loading Arrangements diagram and Loading Graph were not among the pages provided. Station arms for pilot, center/aft passengers, baggage and fuel are derived from the Sample Loading Problem (moment/1000 divided by weight): pilot 340 lb/12.6 -> 37.1 in; center 340/23.8 -> 70.0; aft 340/34.0 -> 100.0; baggage 96/12.2 -> 127.1; fuel 456/21.9 -> 48.0. Verify against the Loading Graph.
• Seat station ranges are printed: pilot/copilot Sta. 32-43; center passengers standard 69-79, club 63-74; aft passengers standard 94-100, club 98-109. Club seating arms differ from standard.
• Fuel: standard tanks 59 USG usable, long-range tanks 76 USG usable, at 6 lb/USG. Total tank capacity is not printed on these pages. Unusable fuel is at arm 46.0: 2 gal for standard tanks, 4 gal for long-range tanks.
• Cargo areas (max load limited by tie-downs, 200 lb/sq ft floor loading): A Sta. 10-50, B 50-84, C 84-109, D 109-145. Cargo pack Sta. 10-84, max 300 lb. Compute arms from the actual load location.
• Envelope vertices were read from Figure 6-10 (CG limits in inches) and cross-checked against the Figure 6-9 moment envelope. The forward limit is 33.0 in up to 2500 lb, then linear to about 42.5 in at 3600 lb. The aft limit is about 49.7 in. Read values; verify.
• The sample loading shows a ramp weight of 3612 lb with a 12 lb taxi/runup fuel allowance. A maximum ramp weight is not printed as a limit on these pages.
• Typical empty is the sample airplane: 2040 lb, moment/1000 73.5 (arm about 36.0 in).
• Read from the POH by ZuluCheck and checked by a second reading; verify against your own manual.

For reference only. The aircraft’s approved flight manual and weighing report are the final authority.