Zenith STOL CH 701 SP weight & balance

Data source

Flight Manual Section 2 Limitations (pages 7-8), Section 6 Weight and balance (pages 16-17) (pages 7-17 of stol-ch701-sp__afm__4th-ed-2003-01.pdf) · version type

• No CG envelope chart is printed; only a CG range of 20-35% MAC (286 mm to 500 mm from datum), valid at all weights up to MTOW 500 kg. The envelope is built as a rectangle from that range; its lower mass bound (263 kg = basic empty weight) is not a printed limit.
• Loading table arms are in metres (moment in kg.m); CG limits are printed in mm and converted to m here (0.286 / 0.500).
• Maximum cockpit weight is printed as 273 kg on page 7 but 237 kg on the cockpit placard (page 8). 237 kg (= 500 - 263) is used; verify against your aircraft.
• Minimum cockpit weight 55 kg.
• Fuel table gives weights rather than volumes: standard fuselage tank 30 kg at -0.20 m, 'D' fuselage tank 16 kg at -0.25 m, long-range wing tanks 42.5 kg at 0.50 m. Tank volumes for the fuselage tanks are not printed. Long-range wing tank capacity is 85 L total and 82 L usable (3 L unusable). The 42.5 kg figure does not match 85 L of fuel; verify. Fuel density is not stated.
• Fuel tank configuration (standard, 'D' tank, long-range wing tanks) is variant dependent.
• Standard empty CG 21.6% MAC (310 mm) with basic empty weight 263 kg. The sample weighing report shows 258 kg at 0.311 m (moment 80.2 kg.m). Use your aircraft's actual weighing.
• MAC 1.43 m.
• Allowable fuel table (crew weight vs baggage 0/9/18 kg) is blank in the sample manual.
• Baggage placard: max 18 kg (40 lb), no loose items.
• 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.