Aluminum 7B04-T62
Temper
GB 7B04
T62 = t6, heat treated by the user
Use when parts were formed/machined in O temper and then re-solution-treated and aged in-house.
Values for the T62 condition
Other 7B04 tempers and conditions
7B04 is listed in 10 conditions; see the grade overview at 7B04.
Compare all 10 conditionsHide
| Condition · open for datasheet | Best for | Yield MPa | Tensile MPa | Elong. % | Hardness | Conductivity |
|---|---|---|---|---|---|---|
Annealed | Pick for maximum formability during sheet forming or deep machining, then re-heat-treat to T6/T73. | 115 | 250 | 16 | 62 HB | 45 % IACS |
T73, stress relieved by stretching | Best combination of toughness, SCC immunity and machining stability for thick plate parts. | 400 | 470 | 11 | 133 HB | 40 % IACS |
Solution heat treated and overaged for stress-corrosion resistance | Pick for forgings and fittings exposed to humid/marine service where stress-corrosion cracking must be eliminated. | 405 | 480 | 11 | 135 HB | 40 % IACS |
Overaged between T73 and T76 | Compromise temper for forgings needing more strength than T73 with most of its SCC resistance. | 430 | 500 | 10 | 140 HB | 38 % IACS |
T74, stress relieved by stretching | Standard aerospace thick-plate temper for wing skins, spars and machined frames — high strength with good toughness and exfoliation resistance. | 440 | 510 | 10 | 143 HB | 38 % IACS |
Overaged for exfoliation-corrosion resistance | Choose for thin sheet/extrusions where exfoliation resistance matters but T73 strength loss is unacceptable. | 450 | 515 | 10 | 145 HB | 37 % IACS |
T76, stress relieved by stretching | Use for machined plate details needing exfoliation resistance and low residual stress. | 450 | 520 | 9 | 146 HB | 37 % IACS |
T62This page T6, heat treated by the user | Use when parts were formed/machined in O temper and then re-solution-treated and aged in-house. | 460 | 530 | 10 | 148 HB | 33 % IACS |
T6, stress relieved by stretching | Choose for peak-strength plate that will be heavily machined and must stay dimensionally stable. | 465 | 535 | 10 | 150 HB | 33 % IACS |
T6Default Solution heat treated and artificially aged | Default peak-strength condition for sheet, extrusions and forgings where static strength governs and SCC exposure is controlled. | 470 | 540 | 11 | 150 HB | 33 % IACS |
What is 7B04-T62?
7B04-T62 is 7B04 in the T62 temper — use when parts were formed/machined in O temper and then re-solution-treated and aged in-house. 7B04-T62 has a yield strength of 460 MPa (66.7 ksi) and a tensile strength of 530 MPa (76.9 ksi) — stronger than 92% of aluminum grades. Elongation at break is 10% and the elastic modulus is 71 GPa (10.3 Msi). 7B04-T62 has a density of 2.85 g/cm³ (0.103 lb/in³), heavier than 96% of aluminum grades. It melts at 477°C (891 °F). T6 is the default condition FabDigit quotes; T62 is available on request or by drawing note.
Advantages
- High strength — 460 MPa (66.7 ksi), better than 92% of aluminum grades
Limitations
- Difficult to weld — 15/100, worse than 96% of aluminum grades
- Needs corrosion protection — 35/100, worse than 85% of aluminum grades
- Limited service temperature — 120°C (248 °F), worse than 79% of aluminum grades
7B04-T62 properties
Typical room-temperature values for 7B04-T62; 20 are specific to this condition. Other listed values are 7B04 reference data and may not represent this condition. Bars are the position among aluminum grades.
Physical3
7B04-T62 has a density of 2.85 g/cm³ (0.103 lb/in³), heavier than 96% of aluminum grades. It melts at 477°C (891 °F).
Mechanical13
7B04-T62 has a yield strength of 460 MPa (66.7 ksi) and a tensile strength of 530 MPa (76.9 ksi) — stronger than 92% of aluminum grades. Elongation at break is 10% and the elastic modulus is 71 GPa (10.3 Msi).
Thermal6
7B04-T62 is rated for continuous service to 120°C (248 °F). It conducts heat at 130 W/m·K (75.1 BTU/hr·ft·°F), worse than 65% of aluminum grades. Thermal expansion is 23.4 µm/m·K (13 µin/in·°F).
Electrical3
7B04-T62 conducts electricity at 33 % IACS, worse than 57% of aluminum grades.
Chemical & Environmental3
Corrosion resistance is fair (35/100), worse than 85% of aluminum grades.
Sustainability4
Producing a kilogram of 7B04-T62 takes about 205 MJ of energy and emits 13 kg of CO₂ — more than 76% of aluminum grades. Typical recycled content is 5%.
Manufacturability7
7B04-T62's machinability is very good (70/100, better than 72% of aluminum grades); weldability poor (15/100); formability poor (20/100).
Values are nominal handbook figures for design screening. Confirm any required mill or lot documentation when quoting.
Working with 7B04-T62
Is 7B04 easy to machine?
Machines freely with sharp carbide tooling, high speed and generous coolant; over-aged T74xx/T73xx plate is preferred for thin-web parts because residual stress and distortion are much lower than in T6.
Can 7B04 be welded?
Not fusion-weldable for structural joints (hot cracking, severe HAZ property loss); join by riveting, bolting, adhesive bonding, resistance spot welding or friction stir welding.
Can 7B04 be formed, bent or molded?
Form in O or freshly quenched W condition; T6/T7 tempers tolerate only large-radius bending, and hot forging/extrusion is done around 380–450 °C followed by full solution treatment and ageing.
What surface finishes work on 7B04?
Chromic or sulfuric acid anodize plus chromate/chromate-free conversion coating and primer is standard aerospace practice; peak-aged T6 parts should be shot-peened or clad and kept out of sustained tensile short-transverse stress to avoid SCC.
7B04 chemical composition (wt %)
Limits by weight percent from the governing specification, written the way the spec states them — a single maximum for impurities, a range for alloying elements, and the base element as balance. Nominal is the typical mid-range value.
| Element | Spec limit (wt %) | Nominal |
|---|---|---|
| Zn | 5 – 6.5 | 5.7 |
| Mg | 1.8 – 2.8 | 2.3 |
| Cu | 1.4 – 2 | 1.7 |
| Mn | 0.2 – 0.6 | 0.35 |
| Cr | 0.1 – 0.25 | 0.17 |
| Feimpurity limit (lower than 7A04) | ≤ 0.25 | — |
| Siimpurity limit | ≤ 0.1 | — |
| Ti | ≤ 0.05 | — |
| Others (each)total ≤ 0.10 | ≤ 0.05 | — |
| Al | balance | — |
7B04-T62 — frequently asked
What is 7B04-T62 used for?
7B04-T62 is typically used for aircraft wing skins, high-strength structural extrusions and aerospace forgings. In short: 7150/7055-class aerospace plate; high strength with usable elongation; machined, not welded.
What is the yield strength of 7B04-T62?
7B04-T62 has a typical yield strength of 460 MPa (66.7 ksi) and a tensile strength of 530 MPa (76.9 ksi) — stronger than 92% of aluminum grades. Strength varies by condition: see the 10 listed tempers.
Is 7B04-T62 easy to machine?
Yes — machinability is rated very good (70/100, better than 72% of aluminum grades). Machines freely with sharp carbide tooling, high speed and generous coolant; over-aged T74xx/T73xx plate is preferred for thin-web parts because residual stress and distortion are much lower than in T6.
Can 7B04-T62 be welded?
Not readily — weldability is rated poor (15/100). Not fusion-weldable for structural joints (hot cracking, severe HAZ property loss); join by riveting, bolting, adhesive bonding, resistance spot welding or friction stir welding.
What surface finishes work on 7B04-T62?
Chromic or sulfuric acid anodize plus chromate/chromate-free conversion coating and primer is standard aerospace practice; peak-aged T6 parts should be shot-peened or clad and kept out of sustained tensile short-transverse stress to avoid SCC.
Can 7B04-T62 be formed, bent or molded?
Form in O or freshly quenched W condition; T6/T7 tempers tolerate only large-radius bending, and hot forging/extrusion is done around 380–450 °C followed by full solution treatment and ageing.
What is the maximum service temperature of 7B04-T62?
7B04-T62 is rated for continuous use to about 120°C (248 °F). Strength falls off well before that limit — check the elevated-temperature data for load-bearing parts.
What is the difference between 7B04-T6 and 7B04-O?
T6 is the default condition — default peak-strength condition for sheet, extrusions and forgings where static strength governs and SCC exposure is controlled. O: pick for maximum formability during sheet forming or deep machining, then re-heat-treat to T6/T73. Yield strength is 470 MPa in T6 versus 115 MPa in O.
Sources
- ASM Handbook Vol.2 — Properties and Selection: Nonferrous Alloys — ASM International (1990)
- MMPDS typical property data for 7000-series aerospace plate (comparison basis) — Battelle/FAA (2023)
Property data is compiled from published supplier and standards handbooks and normalised for comparison. Nothing on this page is a certification — request mill certs, CoC or material test reports with your order.