Flight Design MC weight & balance

Data source

AOI AA 04300001 Rev. 00, Section 2.4 (p. 2-2), Section 6.1 and 6.3 (pp. 6-1, 6-5), Loading Diagram (p. 6-7), Permissible Moment Range (p. 6-8), Permissible CG Range (p. 6-9) (pages 14-63 of mc-lsa__aoi__aa04300001-rev00.pdf) · version type

• CG range 318-392 mm aft of datum is the currently valid range; design rear limit is 458 mm (18.0 in) but is temporarily restricted to 392 mm (15.4 in) pending flight tests.
• Envelope lower mass bound of ~400 kg is read from the chart lines in the moment and CG charts; it is not stated as a number. The printed limits are only fwd 318 mm, aft 392 mm, max 600 kg.
• MTOM 600 kg (1320 lb; p. 2-2 says 1322 lb); national regulations may impose a lower limit.
• Fuel tank capacity and usable fuel are not printed on these pages; fuel density 0.725 kg/L (6.05 lb/USG) is from the manual.
• Baggage: 25 kg per side, 50 kg total; both sides share arm 1.042 m. Actual limits per aircraft come from the weighing record.
• typicalEmpty uses the illustrative example (375.6 kg, 124.2 kg*m, arm 0.331 m computed), which the manual says does not correspond to a real aircraft. Nominal empty weight with minimum equipment is 358 kg (no arm given). Use your aircraft's weighing record.
• Check CG both with takeoff fuel and with empty tanks.
• 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.