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The CG is the point on the longitudinal axis through which all of the weight acts vertically downward. Chapter 3 Page 23 © G LONGHURST 1999 All Rights Reserved Worldwide Weight and Balance Theory ANSWER 13. Page 2-3 Example 2-5 MTOW MLW MZFW + 52000 kgs + 46000 kgs + 43000 kgs DOW - 30,000 kgs - 30,000 kgs - 30,000 kgs Fuel - 10,000 kgs - 5,000 kgs –– Traffic Load + 12000 kgs + 11000 kgs +13,000 kgs Maximum Traffic Load = 11,000 kgs ANSWER 14. Page 1-4. No ANSWER 15. Page 3-4 Paragraph 14. The Manufacturer ANSWER 16.
Define a Newton. QUESTION 19. How does stalling speed change if the CG moves to the AFT of the envelope? QUESTION 20. What determines the value of the maximum zero fuel weight. Chapter 3 Page 21 © G LONGHURST 1999 All Rights Reserved Worldwide Weight and Balance Theory ANSWERS: ANSWER 1. Page 1-4 ANSWER 2. Page 1-4. Dry operating weight ANSWER 3. Page 2-1. Taxi fuel will be used before take-off. 5t which does not exceed MTOW. 5t which does not exceed MLW ANSWER 4. Page 3-3 ANSWER 5. Page 1-4. Zero fuel weight – Dry operating weight = Traffic load ANSWER 6.
The nose-wheel is 45 inches forward of the datum and the main wheels are 55 inches aft of the datum. The weights measured through each wheel are: Left Hand Main Wheel 810 lb. Right Hand Main Wheel 815 lb. Nose-Wheel 320 lb. Determine the weight of the aircraft, and the position of the aircraft CG relative to the datum. SOLUTION The situation is as shown at Figure 3-7. FIGURE 3-7 Chapter 3 Page 17 © G LONGHURST 1999 All Rights Reserved Worldwide Weight and Balance Theory The calculation is now completed as follows: Nose-Wheel Weight Arm Moment 320 lb.
Aircraft Mass & Balance Tutorial - PPSC