i wonder if the coeff of thermal expansion (CTE) of the composite is much greater than aluminium and may allow more aircraft growth and contraction such that wire chaffing might occur?
Maybe twice as much as aluminium, I am not sure about type of resin:
Aluminium 22.2 . 10-6 m/mK
Epoxy, castings resins & compounds, unfilled 55 . 10-6 m/mK
That means ca 1 mm per 1°C for hole long fuselage. Fuselage is getting shorter at FL so wires are not tighten but some movement surely exists.
2 simple-simon: Interesting hypothesis...