7075-T73511 - Aluminum Rectangle Bar Extruded

7075-T73511 – Aluminum Rectangle Bar Extruded

Available now on the Airparts.aero Marketplace.

Overview

This is a prime, certified rectangular bar of 7075-T73511 aluminum, one of the highest-strength aluminum alloys available for aerospace applications. The 7075 alloy, with zinc as its primary alloying element, is renowned for its strength properties, which are comparable to many steels. The T73511 temper is a critical, multi-stage thermal and mechanical treatment that provides an exceptional combination of high strength, good fatigue resistance, and, most importantly, excellent resistance to stress corrosion cracking (SCC). This extruded bar is the specified raw material for fabricating flight-critical, primary structural components where maximum strength and reliability are required.

Key Features

• Ultra-High Strength: The 7075 alloy provides one of the highest strength-to-weight ratios of any aluminum alloy. It is the material of choice for components subjected to very high stress.

• Superior Stress Corrosion Cracking (SCC) Resistance: The T73511 temper is a specialized two-stage aging process (overaging) that is specifically designed to make the 7075 alloy highly resistant to stress corrosion cracking. This is a critical property for parts that will be under a constant state of high tensile stress, especially in corrosive environments.

• Excellent Fatigue Resistance: The combination of the alloy composition and the T73511 temper results in a material with excellent resistance to fatigue failure from the millions of stress cycles an airframe experiences.

• Good Machinability: In the T73511 temper, this alloy offers good machinability, allowing for the precise fabrication of complex structural components.

• Certified Aerospace Material: Conforms to the stringent requirements of aerospace and military specifications, typically AMS 4167, AMS 4169, or AMS-QQ-A-200/11, ensuring full traceability, material composition, and mechanical properties.

Technical Specifications

• Alloy Designation: 7075

• Temper: T73511 (Solution Heat Treated, Stress-Relieved by Stretching, Two-Stage Artificially Aged)

• Product Form: Extruded Rectangular Bar

• Governing Specification: AMS 4167 / 4169 / AMS-QQ-A-200/11

• Typical Mechanical Properties:

  • Ultimate Tensile Strength: ~76,000 PSI

  • Yield Strength: ~66,000 PSI

  • Shear Strength: ~45,000 PSI

• Primary Alloying Element: Zinc (Zn)

Aircraft Compatibility

7075-T73511 aluminum is a premium structural material used in the most critical areas of modern high-performance aircraft.

• Common Applications:

  • Primary Airframe Structure: Used to machine wing spars, fuselage bulkheads, and main structural frames.

  • Landing Gear Components: The material of choice for major forged or machined landing gear components, such as trunnions and drag braces.

  • Wing Skins & Stringers: Used for upper wing skins and other components that are primarily under compressive loads.

  • Critical Fittings & Lugs: Used to fabricate the high-strength fittings that connect major sections of the airframe.

Applications

This extruded bar is the raw material for a wide range of aerospace manufacturing and repair tasks:

• OEM Aircraft Manufacturing: The foundational material for building new, type-certified military and commercial aircraft.

• Structural Repair: The specified material for performing certified major structural repairs in accordance with an aircraft's Structural Repair Manual (SRM).

• Component Fabrication: Used to CNC machine high-strength, flight-critical components.

Why Choose 7075-T73511?

The safety of an aircraft is directly dependent on the integrity of its primary structure. 7075-T73511 is an advanced alloy engineered specifically to provide a "fail-safe" material solution. Its high strength handles the loads of flight, while its excellent resistance to stress corrosion cracking prevents the sudden, catastrophic failure that can occur when a high-stress part is exposed to a corrosive environment. By choosing a fully certified and traceable bar of 7075-T73511, you are ensuring that the material has the exact chemical composition and has undergone the complex, multi-stage temper process required to achieve these flight-critical properties.

Order Your 7075-T73511 Aluminum Bar Now

Build and repair with the certified, high-strength material the aerospace industry trusts for its most critical applications. Visit Airparts.aero to inquire about pricing and availability for 7075-T73511 aluminum bar today.

The T73511 temper is a complex but critical process. The "T73" part refers to a two-stage artificial aging process. After the initial solution heat treatment and quench, the material is aged at a lower temperature for a specific time, and then "over-aged" at a slightly higher temperature for another period. This over-aging process coarsens the grain boundary precipitates, which makes the alloy significantly less susceptible to intergranular and stress corrosion cracking (SCC). While this slightly reduces the ultimate strength compared to the peak-aged T6 temper, the massive gain in SCC resistance is a crucial trade-off for long-term structural reliability. The "511" suffix indicates that the material has been stress-relieved by controlled stretching after solution heat treatment but before the artificial aging, which helps to remove internal stresses from the quenching process and improves dimensional stability during machining.

Note: This is a raw material. It must be handled with care to prevent scratches and dents, which can act as stress risers. All fabrication and repairs must be performed in accordance with FAA-approved practices, such as those outlined in AC 43.13-1B, and the specific aircraft's Structural Repair Manual.