Aleris AA5024-H116 Aluminum Magnesium Scandium Alloy

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Aleris AA5024-H116 Aluminum Magnesium Scandium Alloy
Categories:	Metal; Nonferrous Metal; Aluminum Alloy; 5000 Series Aluminum Alloy
Material Notes:	Features good weldability, excellent damage tolerance, good corrosion resistance, creep-formability. Aleris AlMgSc alloy AA5024 H116 allows simplification of the manufacturing process of aircraft fuselage components. With AA5024 H116 AlMgSc, stringer reinforced aircraft fuselage components can be either Laser Beam Welded (LBW) or Friction Stir Welded (FSW) when the individual parts are still flat, without any prior treatment. The single or double curvature of the fuselage part required for the aircraft body is achieved by creep forming at elevated temperature. Recommended for use as fuselage skin sheet with medium strength but excellent damage tolerance and corrosion properties and can potentially replace traditionally used 2xxx alloys even as drop-in solution. Temper, AMS and MMPDS registration pending. AA5024 H116 is covered by the Airbus specification AIMS 03-04-055 Information and property data for creep formed and welded (if applicable) sheet provided by Aleris.
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Physical Properties	Original Value	Comments

Density	2.65 g/cc

Mechanical Properties	Original Value	Comments
Tensile Strength, Ultimate	315 MPa @Thickness 1.60 mm	LT Direction
	375 MPa @Thickness 3.00 mm	LT Direction
	375 MPa @Thickness 7.00 mm	LT Direction
	380 MPa @Thickness 3.00 mm	L Direction
	380 MPa @Thickness 7.00 mm	L Direction
	395 MPa @Thickness 1.60 mm	L Direction
Tensile Strength, Yield	305 MPa @Thickness 3.00 mm	L Direction
	305 MPa @Thickness 7.00 mm	L Direction
	305 MPa @Thickness 3.00 mm	LT Direction
	305 MPa @Thickness 7.00 mm	LT Direction
	310 MPa @Thickness 1.60 mm	LT Direction
	315 MPa @Thickness 1.60 mm	L Direction
Elongation at Break	15 % @Thickness 1.60 mm	L Direction
	15 % @Thickness 3.00 mm	L Direction
	15 % @Thickness 7.00 mm	L Direction
	17 % @Thickness 7.00 mm	LT Direction
	18 % @Thickness 3.00 mm	LT Direction
	19 % @Thickness 1.60 mm	LT Direction
Tensile Modulus	72.0 GPa
Compressive Strength	295 MPa @Thickness 7.00 mm	L Direction
	300 MPa @Thickness 7.00 mm	LT Direction
	305 MPa @Thickness 3.00 mm	LT Direction
	305 MPa @Thickness 3.00 mm	L Direction
	315 MPa @Thickness 1.60 mm	LT Direction
	325 MPa @Thickness 1.60 mm	L Direction
Compressive Modulus	74.0 GPa
Fatigue Strength	145 MPa @# of Cycles 1.00e+6	T-L
	145 MPa @# of Cycles 300000	T-L
	175 MPa @# of Cycles 100000	T-L
	180 MPa @# of Cycles 80000	T-L
	190 MPa @# of Cycles 50000	T-L
	290 MPa @# of Cycles 10000	T-L
	365 MPa @# of Cycles 1000	T-L
Fracture Toughness	35.0 MPa-m½	K_e; T-L; Δa_e = 0 mm
	40.0 MPa-m½	K_e; L-T; Δa_e = 0 mm
	90.0 MPa-m½	K_e; T-L; Δa_e = 10 mm
	120 MPa-m½	K_e; T-L; Δa_e = 20 mm
	120 MPa-m½	K_e; L-T; Δa_e = 20 mm
	150 MPa-m½	K_e; L-T; Δa_e = 40 mm
	155 MPa-m½	K_e; T-L; Δa_e = 40 mm
	170 MPa-m½	K_e; L-T; Δa_e = 60 mm
	175 MPa-m½	K_e; T-L; Δa_e = 60 mm
	185 MPa-m½	K_e; L-T; Δa_e = 80 mm

Component Elements Properties	Original Value	Comments
Aluminum, Al	92.95 - 95.95 %	As Balance
Chromium, Cr	<= 0.10 %
Copper, Cu	<= 0.20 %
Iron, Fe	<= 0.40 %
Magnesium, Mg	3.9 - 5.1 %
Manganese, Mn	<= 0.20 %
Other, each	<= 0.05 %
Other, total	<= 0.15 %
Scandium, Sc	0.10 - 0.40 %
Silicon, Si	<= 0.25 %
Titanium, Ti	<= 0.20 %
Zinc, Zn	<= 0.25 %
Zirconium, Zr	0.05 - 0.20 %

Some of the values displayed above may have been converted from their original units and/or rounded in order to display the information in a consistent format. Users requiring more precise data for scientific or engineering calculations can click on the property value to see the original value as well as raw conversions to equivalent units. We advise that you only use the original value or one of its raw conversions in your calculations to minimize rounding error. We also ask that you refer to MatWeb's terms of use regarding this information. Click here to go back to viewing the property data in MatWeb's normal format.

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NALERIS88 / 161566

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