Sling 4 HW weight & balance

Data source

POH DC-POH-001-X-G-2.2 Rev 2.2, Section 6.3 (CG Arms), 6.4 (CG Envelope), 6.5, 6.7 (Example), 6.8 (pages 39-177 of sling-4-hw-high-wing__poh__rev-2-2.pdf) · version type

• Envelope is printed in %MAC; converted to arm with the manual's formula arm(mm) = 1728 + %MAC x 13.40 (MAC 1340 mm, LEMAC 1728 mm). Vertices: 18%/600, 18%/950, 21%/1120, 33%/1120, 33%/750, 28%/600 kg. The 18% and 33% limits are given in the manual as 1969 mm and 2170 mm.
• MTOW is printed as maximum all-up weight (MAUW) 1120 kg (2469.17 lb). No separate landing, zero-fuel or ramp mass printed.
• No maximum loads for seats or baggage areas, and no fuel tank capacities or fuel density, appear on these pages. Check Section 2 limitations for baggage limits and the fuel capacity. The volume unit L is assumed, as fuel volumes are not printed here.
• Long range tanks (arm 1850 mm) are shown on the arms diagram only. Main tanks are 1927 mm. Use the tank arm applicable to your aircraft.
• Typical empty mass of 600 kg at 2025 mm is from the example loading in 6.7. Use the actual weighed empty mass and CG of your aircraft.
• Check both the forward CG (full take-off fuel) and the aft CG (landing fuel) for each flight, as the manual requires.
• Main gear arm is 2384 mm and nose wheel arm is 517 mm, for weighing.
• 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.