Aluminum-Lithium (Alloy 2090) Fastening Evaluation for Commercial Aircraft Applications
Date Published: 1994-10-01
Paper Number:941844
DOI: 10.4271/941844
Citation:
Roubinet, D., Shoe, D., and Moon, G., "Aluminum-Lithium (Alloy 2090) Fastening Evaluation for Commercial Aircraft Applications," SAE Technical Paper 941844, 1994, doi:10.4271/941844.
Author(s):
David G. Roubinet - Boeing Commercial Airplane Group
Daniel M. Shoe - Boeing Commercial Airplane Group
Gary Moon - Boeing Commercial Airplane Group
During design of the 777 Airplane, light gage, near net section 2090-T86 extrusions were considered to reduce aircraft weight. The need to evaluate effects of fastener installation on 2090-T86 was indicated by a previous study documenting problems due to low short transverse tensile strength.
Tests by Boeing installing fasteners into holes using interference fits showed 2090-T86 was more susceptible to damage from fastening than previously reported. Damage consisted of cracks normal to the short transverse direction around the periphery of the fastener hole. This report documents the test program conducted at Boeing.
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