Printed from Kezuriba (kezuriba.net/en/materials/ti-5553/)
Ti-5Al-5Mo-5V-3Cr
ISO S (heat-resistant alloys & titanium)Near-beta (metastable beta) titanium alloy (for high-strength structures). Standard: No public standard specifying the composition of wrought material was found. SAE's AMS 7026 is a standard for powder for additive manufacturing.
🌐JIS and international equivalents
“Close” means composition or properties are not exactly the same. Before substituting, check the values in each standard.
| System | Designation | Number | Relation | Confidence |
|---|---|---|---|---|
| UNS | Ti-5Al-5Mo-5V-3Cr | No public standard specifying the composition of wrought material was found. SAE's AMS 7026 is a standard for powder for additive manufacturing | — | |
| UNS | — | — | Not confirmed | |
| JIS | — | — | Not confirmed | |
| GB | — | — | Not confirmed |
Differences between the equivalents (from the sources)
- UNS : No UNS number was found in primary sources. A search result summary mentioned "UNS R58640", but R58640 is assigned in ATI's datasheet to Ti-3Al-8V-6Cr-4Mo-4Zr (equivalent to Beta C), so this is incorrect
- JIS : No JIS equivalent (not found in primary sources)
- GB : Not confirmed
📄Related specifications (AMS, ASTM etc.)
Specifications called up on purchase orders and drawings. AMS are SAE aerospace material specifications, split by product form (bar, plate, forging), melting practice and heat treatment. Standard texts are paid, so only titles and scopes checked on the publishers’ public pages are shown.
| Spec | Scope | Confidence |
|---|---|---|
| AMS 7026 | Titanium Ti-5553 (Ti - 5Al - 5Mo - 5V - 3Cr) Powder for Additive ManufacturingPre-alloyed powder for additive manufacturing (established 2021-07-28). Not a standard for wrought material such as forgings or bars | One source / reference[2] |
All ASTM standards on Kezuriba: ASTM standards quick reference.
✈Main aerospace uses (as stated in the sources)
- Landing gear[1][7]
- Structural parts (Aubert & Duval writes "Structural parts")[1]
- Developed as a replacement for Ti-10V-2Fe-3Al for some airframe structural parts (as stated in a peer-reviewed paper)[8]
- Used in the landing gear of the Boeing 787 and Airbus A350 (as stated in a peer-reviewed paper; not confirmed in primary sources from the airframe manufacturers)[7]
⚗Chemical composition (mass %)
Ranges differ between specifications, so each one has its own column (dark figures agree in several sources, light figures come from one source).
| Element | Spec ① | Spec ② | Spec ③ | Spec ④ |
|---|---|---|---|---|
| Al | 4.4 – 5.7[6] | — | — | — |
| Mo | — | 4.0 – 5.5[6][7] | — | — |
| V | — | 4.0 – 5.5[6][7] | — | — |
| Cr | — | 2.5 – 3.5[6][7] | — | — |
| Fe | — | — | 0.3 – 0.5[7] | — |
| Zr | — | — | ≤ 0.4[7] | — |
| O | — | — | ≤ 0.2[7] | — |
| N | — | — | ≤ 0.1[7] | — |
| C | — | — | ≤ 0.1[7] | — |
| H | — | — | — | — |
| Ti | — | — | — | Balance[1][6] |
- Spec ① Standard range of AMS 7026 (powder for additive manufacturing). Cited by a peer-reviewed paper (Dammulla et al., ACS Omega 2024)
- Spec ② Range given in two peer-reviewed papers (Dammulla 2024 as a value of AMS 7026; Syed 2024 without naming the source standard)
- Spec ③ Range given in a peer-reviewed paper (Syed et al., Materials 2024). Source standard not stated
- Spec ④ Aubert & Duval, peer-reviewed paper
⚖Density
4.64 g/cm³
One source / reference[1]
Aubert & Duval's value only. Beta transus 860°C (same source)
Calculate weight in Ti-5Al-5Mo-5V-3Cr →💪Mechanical properties
“Reference” values are not specified minimums from the standard but figures published by makers and others.
| Condition | Tensile MPa | Yield MPa | Elong. % | Hardness | Type of value |
|---|---|---|---|---|---|
| Solution treatment + aging (STA), room temperature | 1050–1250 | 1000–1100 | 5–12 (5d) | — | Typical value (Aubert & Duval; stated explicitly as not a guaranteed value). K1C 55 MPa√m One source / reference[1] |
| Beta annealed, slow cooled + aged (BASCA), room temperature | 1100 | 950 | 6 (5d) | — | Typical value (Aubert & Duval; stated explicitly as not a guaranteed value). K1C 70 MPa√m One source / reference[1] |
| Specified value of a standard (wrought material) | — | — | — | — | Specified value. No publicly available AMS or ASTM standard for wrought material was found, so not_found Not confirmed |
1 MPa ≈ 145 psi (0.145 ksi). Hardness conversion · unit converter
🔧Machinability notes (as stated in the sources)
- ISO classification: S (titanium alloys)[3][5]
- ISCAR machinability rating (average): 51% for solution treated + aged material (HRC 36–44) and 57% for BASCA material (HRC 34–36). The reference is annealed Ti-6Al-4V = 100%. Among the hardest to cut in the same table[5]
- ISCAR: Ti-10V-2Fe-3Al and Ti-5Al-5Mo-5V-3Cr (VST 5553) hold an important position in structural parts, but high-productivity machining has become a challenge for the industry[5]
📚Sources
Primary sources (public documents from makers, industry associations and standards bodies), numbered where each value is cited. Many are in Japanese.
- aubertduval.com https://www.aubertduval.com/wp-content/uploads/2024/12/Ti5553_GB.pdf
- saemobilus.sae.org https://saemobilus.sae.org/standards/ams7026-titanium-ti-5553-ti-5al-5mo-5v-3cr-powder-add…
- sandvik.coromant.com https://www.sandvik.coromant.com/en-us/knowledge/materials/workpiece-materials
- sumitool.com https://www.sumitool.com/downloads/cutting-tools/general-catalog/assets/pdf/a.pdf#page=18
- iscar.co.za https://iscar.co.za/Catalogs/Publication/english_1/machining_titanium/machining_titanium_0…
- pmc.ncbi.nlm.nih.gov https://pmc.ncbi.nlm.nih.gov/articles/PMC11308016/
- pmc.ncbi.nlm.nih.gov https://pmc.ncbi.nlm.nih.gov/articles/PMC11313518/
- redalyc.org https://www.redalyc.org/journal/474/47450521003/movil/