Cessna F406 Caravan II weight & balance
POH figures for the type
- MTOW9360 lb
- MLM9360 lb
- Typical empty5190 lb
- Typical empty CG171.19 in
Envelope chart. Takeoff 6705 lb at 172.8 in.
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PEOPLE
BAGGAGE
FUEL
EMPTY MASS · YOUR AIRCRAFT
Typical for the type, 5190 lb at 171.19 in. Edit it to your aircraft’s own, from its weighing report.
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Data source
POH Section 2 Limitations p. 2-12; Section 6, Figure 6-1, Figure 6-2 (Sheets 1-6), Figure 6-3, Figure 6-4 (pages 34-297 of f406__poh__1986-rev2.pdf) · version type
- Maximum ramp weight 9435 lb (4280 kg). Max takeoff and landing 9360 lb (4245 kg); takeoff may be further limited by brake energy (Fig 5-13), landing by field length (Fig 5-35).
- CG limits as printed in POH 2-13 (gear extended): aft 180.28 in (32.00% MAC) at all weights up to 9435 lb; forward 166.99 in (11.00% MAC) at 6500 lb or less, straight line to 172.42 in (19.58% MAC) at 9360 lb. No minimum weight is printed (the limits apply "at 6500 pounds or less"); the 5000 lb lower edge is drawn below the typical empty weight so the zero-fuel point can be plotted.
- Fuel: 475 gal usable (481.5 total) at 6.70 lb/gal. The arm comes from the Fuel Loading table (Fig. 6-2 Sheet 1), every 100 lb row plus the first (20 lb) and the last two (3180 and 3183 lb): 187.4 in at 20 lb, 184.2 in at 1100 lb, 182.9 in at 2000 lb, 181.76 in full; the moment is interpolated between rows as the table is read.
- MZFM 8500 lb applies with zero wing locker payload.
- Passenger seat arms depend on interior configuration (8, 9/10, 10, 11, 12, 14 seat, with or without toilet); rear seat arms given here are from the sample computation form (178/218/249). Check Figure 6-2 for your configuration (e.g. seats at 168, 174, 175, 192, 196, 210, 218, 224, 245, 248, 252, 270, 280, 296).
- Avionics bay 250 lb and nose bay 350 lb are less installed optional equipment. Bay A 400 lb (200 per side), Bay B 100 lb (50 per side); floor loading max 75 lb/sq ft.
- Cargo interior: cargo bays A-E at FS 170, 197, 224, 251, 278, max 600 lb per bay (24-inch length); aft cabin floor FS 281; toilet FS 285; forward refreshment center FS 162.
- Drainable unusable fuel 44.00 lb at FS 186.70 must be added to weighed empty weight.
- Read from the POH by ZuluCheck; the two machine readings disagreed and this was settled by reading the POH pages by hand, the fuel table included; verify against your own manual.
For reference only. The aircraft’s approved flight manual and weighing report are the final authority.
| Station | Load | Mass lb | Arm in | Moment lb·in/1000 |
|---|---|---|---|---|
| Empty aircraft | 5190 | 171.2 | 888.5 | |
| Seat 1 (pilot) | 175 | 137.0 | 24.0 | |
| Seat 2 (front passenger/copilot) | 0 | 137.0 | 0.0 | |
| Seats 3 and 4 | 0 | 178.0 | 0.0 | |
| Seats 5 and 6 | 0 | 218.0 | 0.0 | |
| Seats 7 and 8 | 0 | 249.0 | 0.0 | |
| Avionics bay | 0 | 32.0 | 0.0 | |
| Nose bay | 0 | 71.0 | 0.0 | |
| Left wing locker | 0 | 211.0 | 0.0 | |
| Right wing locker | 0 | 211.0 | 0.0 | |
| Aft cabin Bay A | 0 | 301.0 | 0.0 | |
| Aft cabin Bay B | 0 | 317.0 | 0.0 | |
| Usable fuel (Jet A, 475 gal) | 200 USG | 1340 | 183.8 | 246.3 |
| Zero fuel | 5365 | 170.1 | 912.5 | |
| Takeoff | 6705 | 172.8 | 1158.8 |
POH Section 2 Limitations p. 2-12; Section 6, Figure 6-1, Figure 6-2 (Sheets 1-6), Figure 6-3, Figure 6-4 (pages 34-297 of f406__poh__1986-rev2.pdf). For reference only; the aircraft’s flight manual and weighing report are the final authority. https://zulucheck.com/wb/type/cessna-f406/
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