What is the maximum load factor for the utility category flaps-down in the test aircraft?

In the context of aircraft design and certification, the maximum load factor refers to the maximum amount of stress that an aircraft can withstand without structural failure during various attitudes and configurations, including the flaps-up and flaps-down positions. For utility category aircraft, which are designed for a limited range of aerobatic maneuvers, the load factors are different than those of aircraft in other categories like normal or acrobatic.

When the flaps are extended, the stall speed typically increases due to the additional lift they provide at lower speeds, and the aircraft's ability to withstand load factors is reduced compared to when the flaps are retracted. For a utility category aircraft, the structural integrity is designed to support a maximum load factor of 3.0g with the flaps down. This means that the aircraft can safely endure loads up to 3 times the force of gravity while in this configuration.

This load factor limitation is critical for ensuring the safety of the aircraft during maneuvers executed with flaps extended, taking into account that the increased lift and drag conditions can significantly affect how the aircraft responds to various forces during flight. The correct answer reflects this maximum permissible load which the manufacturer has established based on rigorous testing and compliance with aviation regulations.