Foundation of damage tolerance principles in-service for the
RRJ-95 aircraft structural components
A.A. Shanyavskiy1), 2) *, A.P.
Soldatenkov1), A.A. Toushentsov1)
1) Aviation Register for the Russian Federation,
Airport Sheremetievo-1, PO Box 54, Moscow region, Chimkinskiy State,
141426, Russia
2) Institute of Computer Aided Design, 2nd Brestskaya
street 19/18, Moscow, 123056, Russia
Abstract. Fatigue cracks initiated from holes in several zones
and structural components of the RRJ-95 aircraft frames were
investigated. Using the method of quantitative fractography the crack
growth duration in the brackets of the in-service airframe and in the
wing panels during full-scale bench tests was estimated the spacing of
meso-beach-marks (MBM) and fatigue striations. Applied program of bench
test consisted of blocks of variable loads that were equivalent to the
wing loading in flight and reproducing schematized flight-cycle. It was
shown that the duration of fatigue crack propagation in several
structural components of the RRJ-95 aircraft frames was approximately
the same as for the crack nucleation duration. The total lifetime is
sufficiently long for cracks in the structural components to be detected
and reliably monitored with a large operating time interval between
adjacent inspections.
Keywords : aircraft components, in-service fatigue, variable
amplitude loading, quantitative fractography, crack growth duration,
number of flights