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.
Aluminum-Lithium (Alloy 2090) Fastening Evaluation for Commercial Aircraft Applications
Sae Technical Papers
Aerofast Conference & Exposition ; 1994
1994-10-01
Conference paper
English
Aluminum-Lithium (Alloy 2090) Fastening Evaluation for Commercial Aircraft Applications
British Library Conference Proceedings | 1994
|DataCite | 1885
ALUMINUM ALLOY PLATE 2.7Cu - 2.2Li - 0.12Zr (2090-T81) Solution Heat Treated, Cold Worked, and Aged
SAE Technical Papers | 1994