Final answer:
The G limits for asymmetric gear/flaps are determined based on the specific aircraft and its design. Engineers establish G limits to ensure the aircraft can handle the forces it may encounter during flight. The G limits for asymmetric gear/flaps take into account the negative effects of asymmetrical forces on an aircraft's landing gear and flaps.
Step-by-step explanation:
The G limits for asymmetric gear/flaps are determined based on the specific aircraft and its design. The G limit refers to the maximum load factor that an aircraft can withstand without experiencing structural damage. The structural integrity of an aircraft is crucial for safe flight, so engineers establish G limits to ensure the aircraft can handle the forces it may encounter during flight.
For example, a typical commercial airliner may have a G limit of around 2.5 to 3.5. This means that the aircraft can handle a load factor up to 2.5 to 3.5 times its weight without risking structural failure or damage. The G limits for asymmetric gear/flaps take into account the negative effects of asymmetrical forces on an aircraft's landing gear and flaps, and engineers design these components to withstand the expected loads.
It's important to note that G limits can vary depending on the specific aircraft and its certification requirements. Therefore, it is essential for pilots to consult the aircraft's manual or refer to the aircraft's type certificate data sheet to ascertain the precise G limits for asymmetric gear/flaps for a particular aircraft.