Cessna 402C Businessliner weight & balance

Data source

POH Section 2 Weight Limits / Center of Gravity Limits (p. 2-6); Section 6 Figures 6-1, 6-2 (Sheets 1-3), 6-3; Micro VG AFM Supplement C402C-AFMS-1 (pages 25-289 of 402c__poh__flighttest-rev6-1998.pdf) · version type

• Maximum ramp weight 6885 lb.
• CG limits are from the Section 2 text (no chart): aft 160.67 in at 6850 lb or less; forward 151.58 in at 6850 lb, 149.08 in at 5800 lb or less, straight-line between. No minimum weight is printed; the envelope's lower edge at 4225 lb (sample basic empty weight) is a placeholder only.
• MAC 62.65 in, LEMAC at 139.37 in.
• Fuel: the arm comes from the Fuel weight and moment table (Fig. 6-2 Sheet 1), every row from 5 to 206 gal at 6.0 lb/gal: about 166.7 in at 5 gal, 163.0 in at 50 gal, 162.2 in at 100 gal, 161.0 in at 206 gal; the moment is interpolated between rows as the table is read. The table prints moment/100 in whole numbers, so the arm of the lightest rows is only good to about 1 in. 206 gal is the largest table entry; tank total capacity is not printed on these pages.
• Seat arms shown are for the Businessliner 8-seat layout. Utiliner 10-seat arms: seats 1-2 137, 3-4 162, 5-6 190, 7-8 218, 9-10 246 in. Utiliner cargo layout: cargo A 176.2, B 198.7, C 221.2, D 243.7 in.
• Aft cabin Bay A is 400 lb (200 lb per side) and Bay B is 100 lb (50 lb per side). Avionics and nose bay limits are reduced by any installed optional equipment.
• Cargo configuration: max cargo aft of front spar 2000 lb; total cabin load aft of station 238.1 not to exceed 600 lb; max 500 lb in any 22.5 in length of cabin floor.
• Drainable unusable fuel 41.0 lb at 165.2 in is added to the basic empty weight.
• Typical empty arm is computed from the sample: 4225 lb, moment/100 6526.6. Use your own airplane's weighing data.
• If the Micro VG gross weight increase supplement (C402C-AFMS-1) is installed: ramp 7250 lb, takeoff 7210 lb, landing 6850 lb. MZFW stays 6515 lb, except that from 151.0 in it rises linearly to 6750 lb at 151.9 in and continues aft at 6750 lb to 160.66 in. The aft-envelope extension above 6850 lb is not shown on these pages.
• Seat arms assume the occupant CG is at the specified location (9 in forward of the seat back/bottom intersection).
• 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.