Loads on Aircraft Structures Questions and Answers

Answer: A

Correct answer: 1 and 2 only

Statements 1 and 2 are correct: the impact is a dynamic event in which gear, tyres and airframe interact, and drop testing the complete gear is how the analysis is validated. Statement 3 is wrong - a static equilibrium calculation cannot capture the peak, because the peak depends on how fast the energy is absorbed, not merely on how much there is.

Answer: B

Correct answer: A-2, B-1, C-4, D-3

Each case sizes the structure that carries its particular load. An engine failure at low speed produces the largest asymmetric yawing load, sizing the fin and rear fuselage. A rolling pull-out loads the outer wing and the aileron attachments. A heavy landing sizes the undercarriage and its backup structure. And transonic buffet is a repeated, oscillatory load, so what it governs is fatigue life rather than static strength.

Answer: C

Steady flight in smooth air produces a constant load and contributes nothing to the fatigue spectrum beyond the mean stress. The other three all produce fluctuating loads that accumulate damage over the aircraft's life.

Answer: D

Load analysis produces the numbers that stress analysis then works to: a peak value for static strength and a spectrum for fatigue, resolved separately for every part of the airframe. Everything downstream in structural design depends on getting these right.

Answer: A

Recorded touchdown decelerations above a threshold trigger a defined inspection of the gear, its attachments and the surrounding structure, because the energy absorbed may have exceeded the design case. Modern aircraft log the data automatically rather than relying on the crew's judgement.

Answer: B

Recorded accelerations and speeds let an operator compare the aircraft's real usage against the spectrum assumed at design, and adjust inspection intervals if it is being flown more harshly or more gently. It informs the maintenance programme rather than replacing it.

Answer: C

The design spectrum assumes a mix of flight conditions, and an operator flying mostly low and in turbulence exceeds the gust content assumed. Usage monitoring exists precisely to detect this so that inspection intervals can be shortened.

Answer: D

Damage accumulating at twice the assumed rate halves the number of flights before the same total is reached, giving 30,000. The response is not necessarily retirement but a revised inspection programme reflecting the actual usage.

Answer: A

Both are true and the second explains the first. Since the inspection programme is built on an assumed usage, an aircraft that departs from it needs its intervals revised. Recorded data makes that judgement quantitative rather than a matter of opinion.

Answer: B

The first two are correct. The third overstates what monitoring does: it informs the inspection programme and can adjust its intervals, but damage tolerance still depends absolutely on finding cracks by inspection before they become critical.