With a weight of 3,700 lb, pressure altitude of 22,000 ft, and temperature of -10°C, what is the maximum rate of climb?

With a weight of 3,700 lb, pressure altitude of 22,000 ft, and temperature of -10°C, what is the maximum rate of climb?

• A. 384 ft/min
• B. 305 ft/min
• C. 320 ft/min

Answer: (A)

To determine the maximum rate of climb, it's important to understand how altitude and temperature affect aircraft performance. At higher pressure altitudes, the air density decreases, which can significantly influence the climb performance of an aircraft. In this scenario, a weight of 3,700 lbs at a pressure altitude of 22,000 ft and a temperature of -10°C indicates fairly thin air. To assess the maximum rate of climb, one must apply the aircraft's performance chart or equation that correlates to these specific conditions. The performance data typically reflects the engine performance and aerodynamic capability under the given conditions. The correct answer indicates a maximum rate of climb of 384 ft/min, suggesting that the aircraft maintains a rate of ascent which is a direct result of its engine power overcoming the total weight of the aircraft as well as the increased drag from the less dense air at this altitude. This rate can determine how effectively an aircraft can gain altitude and is influenced not only by weight and altitude but also environmental factors like temperature. Considering the nuances of climb performance, understanding that as pressure altitude increases, climb rates generally decrease illustrates why the derived maximum rate of 384 ft/min would be the most representative of the aircraft's capabilities under the described circumstances. This calculation likely reflects the

To determine the maximum rate of climb, it's important to understand how altitude and temperature affect aircraft performance. At higher pressure altitudes, the air density decreases, which can significantly influence the climb performance of an aircraft.

In this scenario, a weight of 3,700 lbs at a pressure altitude of 22,000 ft and a temperature of -10°C indicates fairly thin air. To assess the maximum rate of climb, one must apply the aircraft's performance chart or equation that correlates to these specific conditions. The performance data typically reflects the engine performance and aerodynamic capability under the given conditions.

The correct answer indicates a maximum rate of climb of 384 ft/min, suggesting that the aircraft maintains a rate of ascent which is a direct result of its engine power overcoming the total weight of the aircraft as well as the increased drag from the less dense air at this altitude. This rate can determine how effectively an aircraft can gain altitude and is influenced not only by weight and altitude but also environmental factors like temperature.

Considering the nuances of climb performance, understanding that as pressure altitude increases, climb rates generally decrease illustrates why the derived maximum rate of 384 ft/min would be the most representative of the aircraft's capabilities under the described circumstances. This calculation likely reflects the