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The airframe structure must remain substantially intact after experiencing:
  • A
    The design ultimate load times a 1.5 safety factor.
  • B
    The design limit load plus the design ultimate load.
  • C
    Three times the safety factor.
  • D
    The design limit load times 150%.
081.06.02.01.02: Define limit and ultimate load factor, and explain what can happen if these values are exceeded.

Limit and Ultimate Load Factor

Limit load (factor) is the maximum load (factor) to be expected in service.
Ultimate load (factor) is the failing load of the structure.
  • Safety factor = Ultimate load/Limit load = 1.5 for aviation
Certain manoeuvres have the potential risk to cause deformation or structural failure if the ultimate load is exceeded. The safety factor on the airframe is 1.5. Failure of the structure will not occur at the load factor of 2.5, but at 2.5 × 1.5 = 3.75 g.

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