Aquila A211 G weight & balance

Data source

POH/AFM FM-AT01-1010-102 Section 2.7, 2.8; Section 6.2, 6.4.1 Loading Graph, 6.4.2 Weight and Moment Determination (pages 22-102 of a211g-at01-100b__afm__fm-at01-1010-102-100b-dvfr-a09.pdf) · version type

• Chart 6.4.3 (Approved C.G. Range and Moment Limits, page 6-10) was not among the pages provided; envelope built from Section 2.8 constant CG limits: forward 16.8 in (0.427 m), aft 20.6 in (0.523 m) aft of datum, up to MTOW 1653 lb. No minimum flight weight is printed, so the lower edge is drawn at 0 lb; verify against chart 6.4.3.
• Seats are adjustable: arm 19.1 in (0.484 m) with seat fully forward, 22.8 in (0.580 m) with seat fully aft; interpolate for intermediate positions. Stations are given at the forward position - use the actual seat position.
• Manual also gives metric values: MTOW 750 kg, seat 0.484-0.580 m, baggage 1.3 m (max 40 kg), fuel 0.325 m, fuel density 0.72 kg/L.
• Fuel tank total/usable capacity not printed on these pages (example uses 26.5 USG / 100 L usable). Unusable fuel 2.74 USG (10.4 L) is included in the empty weight.
• Typical empty weight is the example in Table 6.4.2 (1116 lb at 17.3 in; weighing example gives 17.34 in) - use the actual aircraft's Weighing Report.
• Maximum landing weight equals MTOW (1653 lb). No maximum ramp or zero-fuel weight printed.
• 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.