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Printed page label not indexed. PDF page 53.
the Upper Web along L18 Stiffener Ci) Distribution of Fatigue Failure Dimensions of fatigue cracks, widths between hole edges, and others verified on the fracture surface of the upper web are shown in Table-4 belov. -42-Open official document at PDF page 53AAIC final report: Japan Air Lines Boeing 747SR-100 JA8119
Printed page label not indexed. PDF page 72.
(Reference Material - Addendum 1) Along L18 splice of BS2360 aft pressure bulkhead, fatigue cracks emanating from a number of rivet holes were recognized by electron microscopic observation, as shown in Table-4 of para.2.15.1.5. Analysis and test were conducted forOpen official document at PDF page 72AAIC final report: Japan Air Lines Boeing 747SR-100 JA8119
Printed page label not indexed. PDF page 73.
with rivet holes only) which have flaws at the edge of rivet holes simulating various fatigue cracks, machined as test pieces. The test result indicated that in case of the same material and the same crack size as the accidentOpen official document at PDF page 73AAIC final report: Japan Air Lines Boeing 747SR-100 JA8119
Printed page label not indexed. PDF page 74.
Condition of calculation The weakest part Estimated strength (ps i) ALL parts not fractured (Fatigue cracks the same bay 2 6.9-9.4 as accident aircraft) bay 2 fractured bay 3 6.7-9.0 bay 2 and bay 3 2nd strap: 6.0-6.5 both fracturedOpen official document at PDF page 74AAIC final report: Japan Air Lines Boeing 747SR-100 JA8119
Printed page label not indexed. PDF page 75.
one-row riveting, the stress on the hole edge was high,and judging from the behavior of fatigue cracks existent at hole edges, the fatigue crack was initiated and propagated on the rivet hole in a comparatively early period after the repairOpen official document at PDF page 75AAIC final report: Japan Air Lines Boeing 747SR-100 JA8119
Printed page label not indexed. PDF page 109.
were initiated and propagated. A study was made on the possibility of detecting these fatigue cracks by visual inspection at the time of inspection and maintenance. The crack length detectable by the visual inspection depends on crack length, crack shape,Open official document at PDF page 109AAIC final report: Japan Air Lines Boeing 747SR-100 JA8119