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374,295 in.lb / 3904 lb = 95.87 in
3. Locate the values in the diagram in Section 6.4.4 'PERMISSIBLE CENTER OF GRAVITY RANGE'. If the CG positions and related masses fall into the permitted area, the loading condition is allowable.
Our example shows allowable loading conditions (for 1785 kg take-off mass, i.e., M.M 42-088 carried out).
CALCULATION OF DA 42 (Example) Your DA 42
LOADING CONDITION Mass [kg] [lb] Moment [kgm] [in.lb] Mass [kg] [lb] Moment [kgm] [in.lb]
1. Empty mass (from Mass and Balance Report) 1250 2756 2937.5 254,965
2. Front seats Lever arm: 2.30 m (90.6 in) 160 353 368.0 31,982
3. Rear seats Lever arm: 3.25 m (128.0 in) 70 154 227.5 19,712
4. Nose baggage compt. Lever arm: 0.60 m (23.6 in) 5 11 3.0 260
5. Cabin baggage compt. Lever arm: 3.89 m (153.1 in) 10 22 38.9 3,368
6. Baggage extension Lever arm: 4.54 m (178.7 in) 5 11 22.7 1,966
7. De-Icing fluid (if installed; see NOTE on previous page) (1.1 kg/liter) (9.2 lb/US gal) Lever arm: 1.00 m (39.4 in) 27.5 61 27.5 2,403
8. Total mass & total moment with empty fuel tanks (Total of 1. through 7.) 1527.5 3368 3625.1 314,656
9. Usable fuel, main tanks (0.84 kg/liter) (7.01 lb/US gal) Lever arm: 2.63 m (103.5 in) 159 351 418.2 36,329
10. Usable fuel, auxiliary tanks (ifinstalled; O.M 42-056) (0.84 kg/liter) (7.01 lb/US gal) Lever arm: 3.20 m (126.0 in) 84 185 268.8 23,310
11. Total mass & total moment with fuel & de-icing fluid (Total of 8. through 10.) 1770.5 3904 4312.1 374,295
Doc. No. 7.01.05-E Rev. 5 15-Nov-2007 Page 6 - 11
1800175017001650160015501500145014001350130012502.35 2.40 2.45 2.50
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The CG's shown in the following diagrams are those from the example in Section 6.4.3 'CALCULATION OF LOADING CONDITION', rows 8 and 11.
6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE
Center of Gravity Position [m]
The flight CG position must be within the following limits:
Most forward flight CG:
2.35 m (92.52 in) aft of Datum Plane at 1250 kg (2756 lb)
2.35 m (92.52 in) aft of Datum Plane at 1468 kg (3236 lb)
2.40 m (94.49 in) aft of Datum Plane at max. take off mass (see Section 2.7) linear variation in between
Most rearward flight CG:
2.42 m (95.28 in) aft of Datum Plane at 1250 kg (2756 lb)
2.49 m (98.03 in) aft of Datum Plane at 1600 kg (3527 lb)
2.49 m (98.03 in) aft of Datum Plane at max. take off mass (see Section 2.7) linear variation in between
6.4.5 PERMISSIBLE MOMENT RANGE
The flight mass moments shown in the diagram are those from the example in Table 6.4.3
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