7475 Aluminum T7751

metal

7475 Aluminum T7751 is a zinc-aluminum-magnesium-copper alloy in the overaged T7751 temper, providing tensile strengths of 435–470 MPa with improved stress-corrosion cracking (SCC) resistance through controlled precipitation. This condition is used in aircraft fuselage skins and fastener applications where resistance to sustained tensile stress in saltwater environments is critical, sacrificing some peak strength for enhanced fracture toughness and corrosion durability.

aerospacestructural

Compliance & Regulations

?Conflict Free?FDA?RoHS?REACH?TSCA?Prop 65

7475 Aluminum/7475 Aluminum T7751

Units:

si imperial

Property	Value	Unit	Conditions
Compressive Modulus(Ec)	10,500	ksi	22°C · Sheet
Poisson's Ratio(ν)	0.3300	-	22°C
Shear Modulus(G)	3,800	ksi	22°C · Sheet
Young's Modulus(E)	10,000	ksi	22°C · Sheet

Rows with are inherited from the base material

Verified Unverified Low confidence (<80%) Link to source

Property	Value	Unit	Conditions	Source
Density(ρ)	0.1010	lb/in³	22°C

Rows with are inherited from the base material

Verified Unverified Low confidence (<80%) Link to source

Regulatory Screening

Environmental

Safety & Biocompatibility

Quality & Standards

RoHS, REACH, and Prop 65 statuses are validated against official substance lists (ECHA SVHC Candidate List, OEHHA Prop 65, RoHS Annex II). Other regulations are estimated from composition and material classification. All screening is a starting point for due diligence — always verify with your supplier before making compliance decisions.

7475 Aluminum T7751

Mechanical Properties

Physical Properties

Regulatory Screening

Environmental

Safety & Biocompatibility

Quality & Standards