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Tecnam P2012
Tecnam P2012
  • 🏁Introduction
    • Welcome
    • Difference Training
    • FAQ
  • 📓Aircraft Flight Manual
    • Section 1 - General
    • Section 2 - Limitations
    • Section 3 - Emergency Procedures
    • Section 4 - Normal Procedures
    • Section 5 - Performance
    • Section 6 - Weight & Balance
    • Section 7 - Airframe and Systems Description
    • Section 8 - Supplements
      • AUTOPILOT GFC700
      • TKS ICE PROTECTION
      • GCU 477 FMS KEYBOARD
      • AIR CONDITIONING
      • MEDEVAC / SMP CONFIG
  • ⭐SPECIAL FEATURES
    • Integrated Tablet / EFB
    • Key Bindings
    • Paintkit
    • Full Flight Video
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  1. Aircraft Flight Manual

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.

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Last updated 1 year ago

The pilot is responsible for ensuring the correct useful load loading.

WEIGHT AND BALANCE DETERMINATION FOR FLIGHT

To determine weight and balance for flight, proceed as follows:

  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. 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. Repeat the procedure described in 2 for the front and rear baggage loads and TKS Anti-ice liquid (if installed).

  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. 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. 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. 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

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