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# Section 6 - Weight & Balance

This section describes the procedure for establishing the basic empty weight and the moment of the aircraft. Loading procedure information is also provided.

## WEIGHT AND BALANCE DETERMINATION FOR FLIGHT

To determine weight and balance for flight, proceed as follows:
1. 1.
Read the most recent values of the Empty A/C weight and corresponding moment from the Aircraft Weighing Record and write them in the Weight and C.G.- Form.
2. 2.
Write the weight and moment of the pilot/co-pilot and occupant(s) in the Weight and C.G. - Form (Table 6-1). Calculate the moment as: Moment = weight X arm where the arm is read in Table 6-1. Alternatively, the moment can be read from the Loading Diagram (Figure 6-3).
3. 3.
Repeat the procedure described in 2 for the front and rear baggage loads and TKS Anti-ice liquid (if installed).
4. 4.
Sum the weights to obtain the zero fuel weight condition and write it in the Weight and C.G - Form (Table 6-1). The zero fuel weight must not exceed its limit value provided in Section 2 and reported in Table 6-1.
5. 5.
Write weight and moment of the usable fuel in the Weight and C.G. - Form (Table 6-1). Determine the fuel moment using the procedure of step 2.
6. 6.
The total weight can be obtained summing zero fuel condition and usable fuel weights; the resulting moment is, instead, obtained summing all moments; report take-off condition (weight and moment) in the Weight and Balance C.G. - Form (Table 6-1).
7. 7.
To obtain the landing weight and moment, subtract from the take-off condition values the weight and moment of the total fuel required. These values are reported in the Weight and Balance C.G. - Form (Table 6-1). Write the landing values Weight and Balance C.G. - Form (Table 6-1).
Locate on the Weight-Moment Envelope (Figure 6-4) the points (weights and moment) corresponding to the take-off and landing conditions. If the points fall within the envelope, the loading condition meets the weight and balance requirements.

#### Weight-Moment Envelope 