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1. Empty mass (from Mass and Balance Report) 735 1620 1820 158,000 2. Front seats Lever arm: 2.30 m (90.6 in) 150 331 345 29,989 3. Rear seats Lever arm: 3.25 m (128.0 in) 150 331 487.5 42,368 4. Baggage Lever arm: 3.65 m (143.7 in) 0 0 0 0 5. Total mass and total moment with empty fuel tanks (Total of 1.-4.) 1035 2282 2652.5 230,357 6. On-board usable fuel (0.84 kg/liter) (7.01 lb/US gal) Lever arm: 2.63 m (103.5 in) 100.8 222 265.10 23,001 7. Total mass and total moment with full fuel tanks (Total 5. plus 6.) 1135.8 2504 2917.60 253,357 8. The total moments from rows 5 and 7 (2652.5 and 2917.6 kgm) (230,357 and 253,357 in.lb) must be divided by the related total mass (1035 and 1135.8 kg respectively) (2282 and 2504 lb) and then located in Diagram 6.4.4 'PERMISSIBLE CENTER OF GRAVITY RANGE'. As in our example CG positions (2.562 m and 2.569 m respectively) (100.95 and 101.18 in) and masses fall into the permitted area, this loading condition is allowable. % Doc. No. 6.01.05-E Revision 2 30-Apr-2003 Page 6 - 9
% % % % % % % % % % % % % % % % % % % % % % CALCULATION OF LOADING CONDITION DA 40 D (Example) Your DA 40 D 中国通航网 www.ga.cn 通航翻译 www.aviation.cn 本文链接地址:钻石40飞机飞行手册 DA 40 Airplane Flight Manual(49) |