Posted Sunday, June 1, 2008 @ 03:24 AM
YOU'RE JOKING!!!!
Tell him to..........
There are no wing weight specs in the manual.
What on earth would he want that for?
All you need is the total aeroplane weight (empty).
We weighed both of ours with no fuel, taking the mainwheel weight and tailwheel weight in the stable, tail-down attitude (to get total weight) then weighed just the tailwheel with the aeroplane in the level attitude and subtracted that from the total for the mainwheel weight. That way you don't have to have your aeroplane balanced precariously on one wheel with the tail high in the air and a good chance of damage.
Figures for VH-HDO
1) Aircraft empty but prepared for service with oil, battery and full fuel system, but no fuel in tank: Weights Mainwheel 259.8 kg, moment = 17,666.4 kg mm. Tailwheel 25.6 kg, moment = 104960 kg mm. Total 285.4 kg (Manual quotes ‘about 270 kg’ in one place, 275 kg, elsewhere, and the original French manual quotes a maximum empty weight limit of 280 kg.), moment = 122,626.4 kg mm, C of G = 429.66 mm (30.69%) aft of datum (manual quotes empty C of G at 279 kg as 310 - 441 mm aft, or 22.1% to 31.5% MAC).
2) As before (no fuel), but with a normally dressed pilot aboard: Weights Mainwheel 328.8 kg moment = 22,358.4 kg mm. Tailwheel 36.7 kg, moment = 150,470 kg mm. Total 365.5 kg, moment = 172,828. C of G = 472.85 (33.8%) aft of datum (limits are 300 to 490 mm, 21.5% to 35%).
3) Aircraft prepared for service with oil, battery and full fuel system, including full fuel tank: Weights Mainwheel 288.4 kg moment = 19,611.2 kg mm. Tailwheel 23.3 kg, moment = 95,530 kg mm. Total 311.7 kg, moment = 115,141.2 kg mm, C of G = 369.4 mm aft of datum (26.4% MAC).
4) Aircraft prepared for service with oil, battery and full fuel system, including full fuel tank, and with normally dressed pilot aboard: Weights Mainwheel 355.9 kg moment = 24201.2 kg mm. Tailwheel 34.0 kg, moment = 139,400 kg mm. Total 389.9 kg (Manual MTOW is 390 kg), moment = 163,601.2 kg mm,
C of G = 419.6 mm (29.97%) aft of datum (limits are 300 to 490 mm, 21.5% to 35%).
So, Empty Weight is Total 285.4 kg
Weight of fuel = 26.3 kg = 37 lit (manual quotes 38 lit), Arm of Fuel = -284.6 mm
And, weight of pilot = 80.1 kg (correct within 1 kg), Arm of pilot = 905.9 mm
5) By calculation, aircraft at aerobatic weight, with pilot and 15 litres of fuel, weight should be 376.2 kg (max aerobatic weight is 370 kg) and the C of G is at 387.9 mm AOD (27.7% MAC) (limits are still 300 to 490 mm).
So, the aircraft’s weight is at least 6.5 kg too great, but its C of G is close to the middle of its range.
Good luck.
Yours, Bob
