Aquila A210 weight & balance

Data source

AFM FM-AT01-1010-100E Section 2 para 2.7 and 2.8; Section 6 para 6.2.1, 6.4.1 (Loading Graph), 6.4.2 (Weight and Moment Determination) (pages 24-124 of a210-at01__afm__fm-at01-1010-100e-b04.pdf) · version type

• Envelope built from Section 2.8 text only: forward limit 31% MAC = 427 mm, rearward limit 40% MAC = 523 mm aft of datum, with no mass-dependent breaks printed; the 6.4.3 'Approved C.G. Range and Mass Moment Limits' chart was not among these pages. The lower mass bound of 0 is a placeholder, not a printed value - verify against the 6.4.3 chart.
• CG limits are printed in mm; converted to m (0.427 / 0.523) to match the station arms, which the manual gives in m.
• Seat lever arm 0.515 m is from the example table. The Loading Graph shows seat lines for the most forward position (about 220 kg at 100 kgm, roughly 0.455 m) and the most rearward position (about 220 kg at 131 kgm, roughly 0.595 m). Seat position affects the CG.
• Loading Graph seat lines end at 220 kg, apparently a combined pilot plus passenger figure. No per-seat maximum is printed.
• Fuel tank capacity and usable fuel are not printed on these pages. The example uses 109.6 L usable fuel, and the empty mass includes 10.4 L unusable fuel. Density 0.72 kg/L is stated.
• Typical empty mass is the AFM example: 490 kg and 210 kgm, giving an arm of 0.429 m, including unusable fuel, oil and coolant. Use the individual aircraft's weighing report.
• Example loaded CG is 453 mm at 670.9 kg.
• 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.