1994-10-01
Aluminum-Lithium (Alloy 2090) Fastening Evaluation for Commercial Aircraft Applications 941844
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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TECHNICAL PAPER
Mechanical Joining Characteristics of Aluminum-Lithium in a Production Environment
912640
TECHNICAL PAPER
Mechanical Joining Characteristics of Aluminum-Lithium in a Production Environment
912640
BOOK
Metallic Materials Properties Development and Standardization (MMPDS) Handbook - 12
