SAE AMS4341H-2024
Aluminum Alloy, Extrusions, 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511), Solution Heat Treated, Stress Relieved by Stretching, Straightened, and Overaged
- Standard No.
- SAE AMS4341H-2024
- Release Date
- 2024
- Published By
- Society of Automotive Engineers (SAE)
- Latest
- SAE AMS4341H-2024
- Introduction
Standard Evolution Background
AMS4341H, SAE International's latest 2024 revision of the aviation aluminum alloy standard, follows the 13-year implementation of its predecessor, AMS4341G. Key highlights of this revision include the introduction of AS6279, Specification for the Production of Metallic Materials; optimization of ultrasonic testing requirements (elimination of weight requirements); adjustments to the tensile properties table (see Table 1 for comparison); and clarification of exception management (Clause 3.7). This standard applies to 7050-T73511 aluminum alloy extrusions, primarily for aviation structural components requiring both high strength (≥483 MPa) and stress corrosion resistance.
Analysis of Key Technical Requirements
1. Composition Control
Element Minimum Value (wt%) Maximum Value (wt%) Control Significance Zn 5.7 6.7 Major Strengthening Elements Cu 2.0 2.6 Improve Stress Corrosion Resistance Zr 0.08 0.15 Grain refinement 2. Heat Treatment
A three-stage aging system is employed: 250°F (121°C) × 4h → 345°F (174°C) × 8h. Compared to the traditional T73 process, this parameter balances the conflict between strength retention (≥70 ksi) and electrical conductivity (≥40% IACS). Tensile set is strictly controlled within the 1-3% range (Clause 3.2).
Key Performance Indicators
Corrosion Protection Mechanism
The standard innovatively adopts a conductivity-mechanical property correlation control method (clause 3.4.2.1): A conductivity ≥41% IACS is considered qualified; if it is in the 40-40.9% IACS range, the yield strength is required to be ≤69 ksi (476 MPa). A case study of a helicopter rotor joint showed that this control method reduced stress corrosion failures by 83%.
Ultrasonic Testing Grading
Differentiated testing is implemented by thickness (Table 3): Sections 12.7-38.1 mm are classified as Class B (single defects ≤3.2 mm permitted), and sections 38.1-127 mm are classified as Class A (defects ≤1.6 mm).
Implementation Recommendations
- Purchasing Specifications: AMS4341H and section identification number must be clearly marked (Clause 8.5)
- Exception Management: AMS4341H(EXC) must be marked when exceeding the standard size range (Clause 4.4.1)
- Transition Period: AS6279 compliance transformation must be completed within 18 months of the new standard release (Clause 3.8)
SAE AMS4341H-2024 Referenced Document
- ANSI H35.2 American National Standard Dimensional Tolerances for Aluminum Mill Products
- ANSI H35.2M Dimensional Tolerances for Aluminum Mill Products (Metric)
- ASTM B594 Standard Practice for Ultrasonic Inspection of Aluminum-Alloy Wrought Products for Aerospace Applications
- ASTM B660 Standard Practices for Packaging/Packing of Aluminum and Magnesium Products
- ASTM B666/B666M Standard Practice for Identification Marking of Aluminum and Magnesium Products
- ASTM G34 Standard Test Method for Exfoliation Corrosion Susceptibility in 2XXX and 7XXX Series Aluminum Alloys (EXCO Test)
- ASTM G47 Standard Test Method for Determining Susceptibility to Stress-Corrosion Cracking of 2XXX and 7XXX Aluminum Alloy Products
SAE AMS4341H-2024 history
- 2024 SAE AMS4341H-2024 Aluminum Alloy, Extrusions, 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511), Solution Heat Treated, Stress Relieved by Stretching, Straightened, and Overaged
- 2018 SAE AMS4341G-2018 Aluminum Alloy, Extrusions 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated, Stress Relieved by Stretching, Straightened, and Overaged
- 2018 SAE AMS4341F-2018 Aluminum Alloy@ Extrusions 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated@ Stress Relieved by Stretching@ Straightened@ and Overaged (UNS A97050)
- 2011 SAE AMS4341E-2011 Aluminum Alloy, Extrusions 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated, Stress Relieved by Stretching, Straightened, and Overaged
- 2006 SAE AMS4341E-2006 Aluminum Alloy, Extrusions 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated, Stress Relieved by Stretching, Straightened, and Overaged UNS A97050
- 1998 SAE AMS4341D-1998 Aluminum Alloy, Extrusions 6.2Zn 2.3Cu 2.2Mg 0.12Zr Solution Heat Treated, Stress Relieved by Stretching, Straightened, and Overaged
- 1991 SAE AMS4341C-1991 Aluminum Alloy Extrusions 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated@ Stress Relieved@ and Overaged (UNS A97050)
- 1986 SAE AMS4341B-1986 ALUMINUM ALLOY@ EXTRUSIONS 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated@ Stress Relieved and Overaged (UNS A97050)
- 1986 SAE AMS4341A-1986 ALUMINUM ALLOY@ EXTRUSIONS 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511) Solution Heat Treated@ Stress Relieved and Overaged (UNS A97050)
- 1978 SAE AMS4341-1978 ALUMINUM ALLOY@ EXTRUSIONS 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T73511)
