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After-class Test 1

You are required to finish the test within 20 minutes.

The aircraft structure must remain substantially intact after experiencing:

the design ultimate load times a 1.5 factor of safety

the design limit load plus the design ultimate load

the design limit load times a 1.5 factor of safety

A fail safe structure:

is changed before its predicted life is reached

has redundant strength which will tolerate a certain amount of structural damage

has a programmed inspection cycle to detect and rectify faults

A safe life structure:

is changed before its predicted life is reached

should not fail until a predicted number of fatigue cycles has been achieved

will only fail after a known number of operations of hours of use

Of the airframe stresses, ( ) is a combination of compression, tension and shear.

____________

Which design philosophy is applied for the following spar?

fail safe

damage tolerant

safe life

During testing, when a ( ) is applied to the structure, it must not suffer any permanent deformation.

Proof Load

Design Limit Load

Design Ultimate Load

The metal showed in the picture below suffered from:

oxidation corrosion

stress corrosion

electrochemicalcorrosion

In the diagram shown, what strain is being produced in the vertical pin?

Shear

Torsion

Tension

The maximum load that the aircraft designer expect the airframe to be subject to in operation is:

desine limit load

design ultimate load

proof load

Safe life on an aircraft is based on:1.calendar time2.total flying hours3.landings4.pressure cycles

only 2

1 and 2 are correct

any combination of all of the statements are taken into consideration