7010-T7451 (AMS 4205)
Solution treated, stretched and over-aged for high stress-corrosion resistance. The default for thick machined parts loaded in the short-transverse direction.
High-strength aerospace plate
7010 Aerospace Aluminium Plate (T7451, T7651, T7351)
7010 is a zirconium-bearing Al-Zn-Mg-Cu plate alloy that keeps high strength, toughness and stress-corrosion resistance through thick sections. It competes directly with 7050 and is used for machined wing ribs, spars, frames and bulkheads, especially on European programmes. Metline supplies 7010 plate in T7451, T7651 and T7351 to AMS 4205, AMS 4204, AMS 4203 and EN 485, certified and shipped worldwide.
- Alloy
- 7010 (Al-Zn-Mg-Cu-Zr)
- Tempers
- T7451, T7651, T7351
- Thickness
- ≈ 6 – 200 mm
- Specifications
- AMS 4203 · 4204 · 4205 · EN 485
What is 7010 aluminium plate?
7010 was developed in the UK as a thick-plate aerospace alloy. Like 7050, it uses zirconium rather than chromium to control grain structure. Zirconium makes the alloy far less sensitive to quench rate than 7075, so the centre of a thick plate keeps most of the strength and toughness of the surface.
The alloy is supplied in over-aged T7-type tempers that trade a small amount of peak strength for much better resistance to stress-corrosion cracking and exfoliation. T7451 offers the best stress-corrosion resistance in thick sections, T7651 gives higher strength with good exfoliation resistance, and T7351 is the most over-aged and corrosion-resistant condition.
Because the plates are stretched after quenching (the "51" in each temper), residual stresses are low and parts machined from them distort very little. That makes 7010 a natural choice for monolithic machined parts: wing ribs, spar sections, fuselage frames, bulkheads and landing-gear support structure cut from plates 50–150 mm thick.
7010 chemical composition (wt %)
Registered limits for 7010 / EN AW-7010. The nominal composition named in AMS 4204 is 6.2 Zn – 1.8 Cu – 2.4 Mg – 0.13 Zr.
| Element | Minimum | Maximum | Role |
|---|---|---|---|
| Zinc (Zn) | 5.7 | 6.7 | Main strengthening element (with Mg) |
| Magnesium (Mg) | 2.1 | 2.6 | Forms MgZn2 precipitates |
| Copper (Cu) | 1.5 | 2.0 | Strength and stress-corrosion resistance |
| Zirconium (Zr) | 0.10 | 0.16 | Grain control, low quench sensitivity |
| Silicon (Si) | — | 0.12 | Kept low for toughness |
| Iron (Fe) | — | 0.15 | Kept low for toughness |
| Manganese (Mn) | — | 0.10 | |
| Chromium (Cr) | — | 0.05 | Deliberately low |
| Nickel (Ni) | — | 0.05 | |
| Titanium (Ti) | — | 0.06 | Grain refiner |
| Others, each / total | — | 0.05 / 0.15 | |
| Aluminium (Al) | Remainder |
An earlier version of this page gave copper as 0.1 % maximum and zinc as 5.2–6.2 %, with vanadium. Those figures do not describe 7010; the table above shows the registered limits.
Mechanical properties of 7010 plate
Values below are approximate typical figures for plate around 50–100 mm thick, given to compare tempers. Specified minimums in AMS 4203/4204/4205 and EN 485-2 vary with thickness and test direction (L, LT, ST) and fall as plate gets thicker. Design to the specification minimums shown on the certificate.
| Temper | Tensile strength (L) | Yield strength (L) | Elongation | Main benefit |
|---|---|---|---|---|
| T7651 | ≈ 520 – 540 MPa | ≈ 460 – 480 MPa | ≈ 8 % | Highest strength, good exfoliation resistance |
| T7451 | ≈ 500 – 520 MPa | ≈ 430 – 450 MPa | ≈ 8 – 9 % | Best balance of strength, toughness and SCC resistance |
| T7351 | ≈ 470 – 490 MPa | ≈ 390 – 410 MPa | ≈ 9 % | Maximum stress-corrosion resistance |
Physical properties
- Density
- 2.82 g/cm³
- Modulus of elasticity
- ≈ 71 GPa
- Thermal conductivity
- ≈ 150 – 160 W/m·K
- Electrical conductivity
- ≈ 38 – 41 % IACS (used to verify T7 tempers)
- Thermal expansion
- ≈ 23.5 µm/m·°C (20 – 100 °C)
- Melting range
- ≈ 475 – 630 °C
T7451, T7651 or T7351?
7010-T7651 (AMS 4204)
Less over-aged than T7451 for higher strength, with good exfoliation resistance. Used for wing skins and parts where strength governs. AMS 4204 covers 6.35–139.7 mm.
7010-T7351 (AMS 4203)
The most over-aged temper, with the highest stress-corrosion resistance and lower strength. Used where SCC risk is the deciding factor.
Electrical conductivity testing is a fast way to confirm the degree of over-ageing. Each temper has a conductivity window in the specification, and it is checked on every plate.
Specifications and equivalents
| System | Designation / specification |
|---|---|
| SAE AMS | AMS 4203 (T7351), AMS 4204 (T7651), AMS 4205 (T7451) |
| European (EN) | EN AW-7010 [AlZn6MgCu]; plate to EN 485-1/-2/-4; aerospace EN 2xxx/4xxx series where called up |
| UNS | A97010 |
| Airframe OEM specifications | Many OEMs issue their own 7010 plate specifications; tell us the document and revision |
| Inspection | Ultrasonic testing to AMS-STD-2154 or ASTM B594, typically class A or AA for thick plate |
Plate sizes and weights
7010 plate supply range
- Thickness
- About 6 – 200 mm, depending on temper and specification
- Width
- Up to about 2,500 mm
- Length
- Up to about 12,000 mm; cut blanks on request
- Condition
- Mill finish, saw-cut edges; blanks cut to your nesting plan
- Certification
- EN 10204 3.1 with chemistry, tensile, conductivity and ultrasonic results
7010 weighs 2.82 kg per square metre for each millimetre of thickness.
| Thickness (mm) | kg per m² | 1,250 × 2,500 mm plate (kg) |
|---|---|---|
| 10 | 28.2 | 88 |
| 20 | 56.4 | 176 |
| 25 | 70.5 | 220 |
| 40 | 112.8 | 352 |
| 50 | 141.0 | 441 |
| 75 | 211.5 | 661 |
| 100 | 282.0 | 881 |
| 125 | 352.5 | 1102 |
| 150 | 423.0 | 1322 |
Machining and processing
Machining
Excellent. High-speed milling with carbide tools gives fast metal removal; stretched tempers keep thin-walled parts flat.
Welding
Not fusion-welded in aerospace structures because of hot cracking and strength loss. Friction stir welding is possible but must be qualified.
Surface protection
Anodise (sulphuric or boric-sulphuric) and prime. The alloy is not clad, so finished parts always need a protective system.
Forming
Limited at room temperature in T7 tempers. Creep or age forming is used for contoured skins.
Where 7010 plate is used
- Wing structure: ribs, spar sections, upper wing skins and stringer-integral panels
- Fuselage: frames, bulkheads, floor beams and door surrounds machined from thick plate
- Landing gear support: fittings and beams subject to short-transverse loading
- Engine pylons and mounts: machined fittings where stress-corrosion resistance matters
- Defence and space: structural parts needing thick-section strength and toughness
7010 compared with 7050, 7075 and 7475
| Property | 7010-T7451 | 7050-T7451 | 7075-T7351 | 7475-T7351 |
|---|---|---|---|---|
| Quench sensitivity | Low | Low | High | Medium |
| Strength in thick plate | High | High | Medium | Medium |
| Fracture toughness | High | High | Medium | Very high |
| Stress-corrosion resistance | High | High | Very high | Very high |
| Main user base | Europe | Global | Global | Damage-tolerant parts |
7010 and 7050 are close substitutes, and the choice is often set by the airframe programme. 7075-T7351 loses more strength in thick sections, while 7475 is chosen for damage-tolerant skins rather than thick machined parts.
How to order 7010 plate
- SpecifyTemper, specification and revision (AMS 4205, AMS 4204, EN 485 or OEM document), thickness, size and quantity.
- QuoteWe confirm availability, ultrasonic class, certification and delivery terms (EXW, FOB, CIF or DAP).
- CutPlates are saw-cut to size or blanks and marked for traceability.
- ShipInterleaved, wrapped and crated for export with the EN 10204 3.1 certificate.
References and standards
- SAE AMS 4204 – Aluminum Alloy Plate 6.2Zn-1.8Cu-2.4Mg-0.13Zr (7010-T7651)
- SAE AMS 4205 – Aluminum Alloy Plate (7010-T7451)
- SAE AMS 4203 – Aluminum Alloy Plate (7010-T7351)
- EN 485-2 – Aluminium and aluminium alloys: sheet, strip and plate, mechanical properties
- The Aluminum Association – International Alloy Designations and Chemical Composition Limits (Teal Sheets)
7010 aerospace aluminium (aluminum) plate: frequently asked questions
What is the difference between 7010 and 7050?
Both are zirconium-bearing Al-Zn-Mg-Cu thick-plate alloys with similar strength, toughness and stress-corrosion resistance. 7050 has more copper (2.0–2.6 %) and slightly less magnesium; 7010 is more common on European programmes. They are not interchangeable without design approval.
Which 7010 temper should I choose?
T7451 for thick machined parts that see short-transverse loads, T7651 where higher strength and exfoliation resistance are the priority, and T7351 where stress-corrosion resistance must be maximised.
What thickness is 7010 plate available in?
Typically from about 6 mm up to around 200 mm. AMS 4204 (T7651) covers 6.35–139.7 mm; other specifications cover thicker plate.
Can 7010 be welded?
It is not fusion-welded in aircraft structure. Parts are machined from solid and joined with fasteners.
What testing comes with 7010 plate?
Chemistry, tensile tests, electrical conductivity and ultrasonic inspection, reported on an EN 10204 3.1 certificate.
Need 7010 aerospace plate?
Send the temper, specification, thickness and quantity. We will reply with availability, certification and a delivered price.
