Answer :
Answer:
The wing lift load at the top of a horizontal circular maneuver can be calculated using the load factor equation, which involves airspeed, gravity, and the radius of the flight path, and then multiplying the load factor by the weight of the aircraft. If this exceeds the FAA's positive load factor limit, it should be capped accordingly.
Explanation:
To solve for the wing lift load at the top of the maneuver, we use the concepts of load factor and centripetal force in a horizontal circular flight path. Given the weight of the aircraft and the radius of the flight path, the load factor can be calculated using the formula:
n = Lift / Weight = (V^2) / (g * r)
where:
V is the airspeed (200 mph converted to ft/s),
g is the acceleration due to gravity (32.2 ft/s^2), and
r is the radius of the path (1,203 ft).
Once the load factor (n) is determined, we multiply it by the weight of the aircraft to find the wing lift load (Lift = n * Weight).
The calculated load will have to be compared with the FAA positive load factor limit of 4.00. If the calculated load exceeds this limit, the wing lift load would be capped at this value to meet the FAA specification.