Ti-6Al-4V at a glance
Where to buy
Designation
| Item | Value |
|---|---|
| Designation | Ti-6Al-4V |
| Class | Titanium |
| Type | alpha-beta titanium alloy |
Properties
| Property | Value | Source |
|---|---|---|
| Against steel and aluminum | 30 % stronger than steel and nearly 50 % lighter; 60 % heavier than aluminum and twice as strong | FAA-H-8083-31, p. 4-85 (the handbook's general statement, not a design value) |
| Against pure titanium | Approximately 3 times stronger | FAA-H-8083-31, p. 4-85 |
| Service temperature | Moderate strength up to 600 °F (315 °C) | FAA-H-8083-31, p. 4-85 |
| Stress relief after cold forming (annealed 6Al-4V) | Above 1,250 °F and below 1,450 °F, held more than 30 minutes and less than 10 hours | FAA-H-8083-31, p. 4-85 |
| Largest hole drilled in one step | 0.1563 in | FAA-H-8083-31, p. 4-86 |
| Heat tint colours | Blue at 700–800 °F, purple at 800–950 °F, gray or black at 1,000 °F or higher | AC 43.13-1B CHG 1, par. 6-181a |
The 30 % and 60 % comparisons are the handbook's own wording. Do not use them in a calculation; use the allowables for the exact condition.
Design allowables — Ti-6Al-4V annealed sheet
0.1875 in and under. MIL-HDBK-5J Table 5.4.1.0(b). A and B bases in ksi unless a unit is shown.
| Property | A basis | B basis | Unit |
|---|---|---|---|
| Ftu, L | 134 | 139 | ksi |
| Ftu, LT | 134 | 139 | ksi |
| Fty, L | 126 | 131 | ksi |
| Fty, LT | 126 | 131 | ksi |
| Fcy, L | 133 | 138 | ksi |
| Fcy, LT | 135 | 141 | ksi |
| Fsu | 87 | 90 | ksi |
| Fbru, e/D = 1.5 | 213 | 221 | ksi |
| Fbru, e/D = 2.0 | 272 | 283 | ksi |
| Property | A basis | B basis | Unit |
|---|---|---|---|
| Fbry, e/D = 1.5 | 171 | 178 | ksi |
| Fbry, e/D = 2.0 | 208 | 217 | ksi |
| Elongation, L (S-basis) | 8 | — | % |
| Elongation, LT (S-basis) | 8 | — | % |
| E | 16.0 | 16.0 | 10³ ksi |
| Ec | 16.4 | 16.4 | 10³ ksi |
| G | 6.2 | 6.2 | 10³ ksi |
| Density | 0.160 | 0.160 | lb/in³ |
Form: sheet; condition: annealed; specification: AMS 4911 and AMS-T-9046 Comp. AB-1; thickness 0.1875 in and under. Bearing values are dry-pin values (MIL-HDBK-5J Section 1.4.7.1). The handbook footnotes the elongation: 8% for 0.025 to 0.062 in and 10% for 0.063 in and above, printed in the A column with the B cell blank. E, Ec, G and density are printed once across all columns. Source: MIL-HDBK-5J (31 Jan 2003), Table 5.4.1.0(b), p. 5-53. MIL-HDBK-5J (2003) is superseded by MMPDS; check current MMPDS before design use. Density 0.160 lb/in³ is about 4.43 g/cm³ (converted), from the same MIL-HDBK-5J table.
Notes from the guide
- Not a source of design allowables. Strength depends on the condition and form. Use MMPDS with the basis; the SRM governs a repair.
- No bend radii on this page. AC Table 4-6 covers aluminum only. The minimum radius chart for the actual alloy and condition comes from the manufacturer or SRM.
- Not a substitute for steel or aluminum. Substitution changes stiffness, weight and galvanic pairs. It is approved-data territory.
Where to buy
Distributors coming soon.
Sources
- FAA-H-8083-31, AMT Handbook — Airframe, Volume 1, Chapter 4 — Working Titanium, pp. 4-85 to 4-86 — description, alloy comparison, forming with stress relief, drilling and isolation.
- FAA AC 43.13-1B CHG 1, Chapter 6 — par. 6-181 — oxide colours, pitting, hydrogen embrittlement and prohibited solvents.
- MIL-HDBK-5J, Metallic Materials and Elements for Aerospace Vehicle Structures — density as used on our kit weight page; the home of the design allowables (Chapter 5, titanium). Cancelled; replaced by MMPDS.
- MIL-HDBK-5J (31 Jan 2003), Table 5.4.1.0(b), p. 5-53 — Ti-6Al-4V annealed sheet, 0.1875 in and under: Ftu, Fty, Fcy, Fsu, Fbru, Fbry, elongation, E, Ec, G and density.
- FAA AC 43.13-1B CHG 1 — Table 4-15, par. 6-181.
- MIL-HDBK-5J, Metallic Materials and Elements for Aerospace Vehicle Structures (31 Jan 2003) — par. 5.4.1.0. Cancelled; superseded by MMPDS.
- MMPDS (formerly MIL-HDBK-5) — the current home of design allowables with A, B and S basis. Cancelled MIL-HDBK-5J was superseded by it. A repair substantiation cites MMPDS or the SRM, not a website.