2024-T3-.02 - Aluminum Sheet 0.02" Thick

2024-T3-.02 – Aerospace Grade Aluminum Sheet (0.020" Thickness)

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The 2024-T3-.02 is a high-strength, cold-finished aluminum alloy sheet with a nominal thickness of 0.020 inches (0.51 mm). Renowned for its exceptional strength-to-weight ratio and high fatigue resistance, 2024-T3 is the industry standard for aircraft structural applications. This specific gauge is a staple in the aerospace industry, primarily utilized for the fabrication of aerodynamic skins, fairings, and non-structural interior panels where weight minimization is critical but structural integrity cannot be compromised.

As a "T3" tempered alloy, this material has been solution heat-treated, cold-worked, and naturally aged to a substantially stable condition. Typically supplied in an Alclad (Aluminum Clad) configuration, the 2024 core is metallurgically bonded to thin layers of high-purity aluminum on both sides. This cladding provides essential galvanic corrosion protection, which is vital because the high copper content of the 2024 core—while providing superior strength—is inherently susceptible to intergranular corrosion. For the structural mechanic and aerospace engineer, 2024-T3-.02 represents the ideal balance of formability and mechanical performance for light-to-medium airframe surfacing.

Key Features

• Superior Fatigue Resistance: Engineered to withstand cyclic loading, making it the preferred choice for fuselage skins subjected to pressurization cycles.

• High Strength-to-Weight Ratio: Provides the structural rigidity of heavier alloys at a significantly lower density, optimized for fuel efficiency and payload capacity.

• Excellent Machinability: Can be easily drilled, routed, and sheared with precision while maintaining crisp edge margins.

• Solution Heat-Treated (T3): Cold-worked following heat treatment to increase yield strength through strain hardening without sacrificing ductility.

• Alclad Protection: Features a pure aluminum surface layer that acts as a sacrificial anode, preventing environmental degradation of the high-strength core.

Technical Specifications

• Part Number: 2024-T3-.02 (or AMS-QQ-A-250/5)

• Weight Per Lineal Foot: 0.29 Pounds
• This material meets the following specs: ASTM- B209, AMS- 4037, AMS- QQ-A-250/4

• Thickness: 0.020 inches (0.508 mm)

• Alloy: 2024 (Aluminum-Copper)

• Temper: T3 (Solution Heat-Treated, Cold-Worked, Naturally Aged)

• Finish: Alclad (Pure Aluminum Cladding)

• Tensile Strength (Ultimate): 63,000–70,000 psi

• Yield Strength: 42,000–47,000 psi

• Elongation at Break: 10%–15% (gauge dependent)

• Density: 0.101 lb/in³ (2.78 g/cm³)

• Governing Specifications: AMS 4037, AMS-QQ-A-250/4 (Bare), AMS-QQ-A-250/5 (Alclad)

• Certification: FAA-PMA Approved for structural repair/manufacturing

Aircraft Compatibility

• Cessna 100/200/300 Series: Used extensively for wing skins and fuselage panels.

• Piper PA-28/PA-32 Series: Common gauge for control surface skins (flaps and ailerons).

• Beechcraft Bonanza/Baron: Utilized for various aerodynamic fairings and access plates.

• Experimental Airframes: Standard skin material for Van’s RV series and other high-performance kit aircraft.

• Note: Always consult the aircraft's Structural Repair Manual (SRM) to verify the required alloy, temper, and gauge for the specific zone being repaired.

Applications

• Fuselage Skins: The primary "skin" material for light aircraft.

• Aerodynamic Fairings: Shaping of wing-to-fuselage and tailcone transitions.

• Internal Ribs & Bulkheads: Fabricating light-duty structural supports.

• Control Surfaces: Skinning of elevators, rudders, and trim tabs.

Why Choose 2024-T3-.02?

In aerospace structural repair, material substitution is a high-risk endeavor. Choosing genuine 2024-T3 aluminum ensures that the repair or fabrication matches the Modulus of Elasticity and Ultimate Tensile Strength of the original design. Using lower-grade "commercial" aluminum or an incorrect temper (like T0 or T4) can lead to premature fatigue cracking or catastrophic structural failure under G-loading. By utilizing 2024-T3-.02, you are adhering to the engineering standards that have defined safe aviation for over 70 years.

The mechanical performance of 2024-T3 is derived from its status as a precipitation-strengthened alloy, where copper (typically 4.4%) serves as the primary alloying element. During the solution heat-treatment process, the copper atoms are dissolved into a solid solution; the subsequent T3 tempering involves cold-working the material, which introduces dislocations into the crystal lattice. These dislocations, combined with the natural aging process where CuAl_2 precipitates form, create barriers to slip, effectively increasing the metal's yield strength through strain hardening.

In the .020-inch gauge, the material exhibits significant anisotropic behavior; the grain orientation (longitudinal vs. transverse) must be considered during the layout of repair patches to ensure maximum fracture toughness. The Alclad surface is particularly critical for this thickness; because the core is only 0.020" thick, any pitting corrosion could quickly reach the critical crack length, leading to a rapid loss of structural integrity. The cladding acts as a sacrificial layer with a lower electrode potential, ensuring the structural core remains cathodic and protected from the environment.

Note: 2024-T3 is a structural material. It should not be welded, as the localized heat will destroy the T3 temper and lead to "hot cracking" in the heat-affected zone (HAZ). All joints must be made using mechanical fasteners (rivets or bolts). Ensure that the bend radius exceeds the minimum specified for the thickness to prevent grain separation. All fabrication must be performed by a certified A&P mechanic or under the supervision of a Repair Station in accordance with AC 43.13-1B.

Documentation

• FAA AC 43.13-1B - Chapter 4: Metal Structure, Welding, and Brazing

• AMS-QQ-A-250/5 - Aluminum Alloy 2024, Plate and Sheet, Alclad