A modified Cessna 310 has the following specifications:
- Stall speed: 80 mph
- Cruise speed: 200 mph
- Dive speed: 215 mph

When flying near Denver (air density = 0.002 lb-sec²/ft⁴), the FAA specifies load factors including:
- Maximum positive load factor: 4.00
- Minimum negative load factor: -1.5

The aircraft is undergoing a push-down maneuver at 200 mph. Calculate the wing lift load at the top of the maneuver (aircraft is horizontal). Assume a flight path radius of 1,203 ft and a CG offset of $\delta = 6$ inches. (Units: lb)

A) 9,208 lbs
B) 8,236 lbs
C) 10,450 lbs
D) 11,512 lbs

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.