Printed from Kezuriba (kezuriba.net/en/standards/ams/)
AMSHow AMS Works, with a Quick Reference
Drawings and purchase orders for aircraft and spacecraft parts often show numbers such as "AMS 5643" or "AMS 2759/3". These are specifications issued by the U.S.-based SAE International, calledAerospace Material Specifications. This page explains how to read the numbers and summarizes the 50 process specs and 130 material specs you meet in machining. Titles, revisions, and statuses were checked against public pages such as SAE's; the text of the specifications is not reproduced.
Let's decode
the AMS callout
on your drawing.
?What AMS is
- AMS are aerospace material and process specifications issued by the U.S. standards body SAE International (formally the Society of Automotive Engineers). SAE's aerospace documents include AMS (material specifications) as well as AS (Aerospace Standards), ARP (Aerospace Recommended Practices), and AIR (Aerospace Information Reports).[1][2]
- SAE's standards work is overseen by the Technical Standards Board (TSB). The TSB sits under the SAE Board of Directors, supervises the technical committees, and approves the publication of standards, recommended practices, and information reports. Its rules are in TSB001 (the current edition is dated November 2014).[3]
- SAE documents carry the TSB wording that "use of this report is entirely voluntary, and its applicability and suitability for any particular use is the sole responsibility of the user," and that "SAE reviews each document at least every five years and either reaffirms, revises, or cancels it." They are private-sector standards, not law, and become binding only when called out on a drawing or in a contract.[4]
- AMS is handled by the Aerospace Materials Systems Group (AMSG) under the SAE Aerospace Council. The same group publishes AIR4779, the user's guide to AMS (User's Guide to AMS Specifications; first issued in 1994, latest revision E in August 2026). The table of contents of the AMS index (2009 edition) includes a page titled "SAE Aerospace Council Organization Chart."[5][2]
- AMSG's purpose is to pool its members' knowledge to create and maintain material and process specifications that follow established engineering practice. The documents it issues are AMS, ARP, AIR, and AS.1 source, for reference[6][7]
- How a new AMS gets made (from a 2015 presentation by Battelle, the MMPDS secretariat): (1) the committee confirms the need and the maturity of the technology (support from at least two aerospace users is required); (2) a proposer drafts the specification with help from SAE editorial staff; (3) a 28-day ballot and comment period in the responsible committee; (4) technical comments are resolved by consensus; (5) the final draft is approved by a vote of SAE Aerospace (industry executives); (6) SAE publishes it. Meetings are open to anyone, and most committees meet twice a year. Only committee members can vote, and final approval rests with user-side members only (OEMs, operators, government). Members take part as technical experts, not as representatives of their employers.1 source, for reference[8]
- AMS has a long history. According to the SAE MOBILUS revision histories, AMS2650 was first issued in August 1945, AMS5643 in October 1951, and AMS5047 in November 1954.[9][10][11]
Technical committees and their scope
| Committee | Scope |
|---|---|
| AMS BFinishes Processes and Fluids Committee | Process technologies such as plating, brazing, coatings, and compounds. This committee also issues pyrometry AMS2750, heat treatment of steel parts AMS2759, the list of test methods AMS2350, nickel plating AMS-QQ-N-290, and electroless nickel AMS-C-26074.[12][13][14][15][16] |
| AMS DNonferrous Alloys Committee | Nonferrous metals such as aluminum, magnesium, and copper.[17][18] |
| AMS ECarbon and Low Alloy Steels Committee | Carbon and low-alloy steels, plus steel cleanliness, quality assurance sampling, and similar topics. Heat treatment of steel raw material, AMS-H-6875, also belongs to this committee.[11][19] |
| AMS FCorrosion and Heat Resistant Alloys Committee | Corrosion- and heat-resistant steels such as stainless steel, and heat-resistant alloys such as nickel-base alloys and special steels.[10] |
| AMS GTitanium and Refractory Metals Committee | Titanium, and refractory metals such as beryllium, molybdenum, tantalum, and columbium (niobium).[20][21] |
| AMS KNon Destructive Methods and Processes Committee | Nondestructive testing: penetrant, magnetic particle, X-ray, ultrasonic, eddy current, and others.[22][9] |
| AMS JAircraft Maintenance Chemicals and Materials Committee | Maintenance chemicals for airframes: cleaners, disinfectants, paint strippers, and the like.[23] |
| AMS P, AMS P17, and AMS CEPolymeric Materials CommitteePolymer Matrix CompositesElastomers Committee1 source, for reference | Polymer materials. AMS P17 (Polymer Matrix Composites): composite materials such as prepreg, fibers, resins, adhesives, and core materials. AMS CE (Elastomers Committee): rubber and sealing materials.[24][25] |
| AMS AM | Formally established in 2015 at the request of the FAA. However, the first additive manufacturing material specification, AMS4999, was issued in 2002 by AMS G.[26] |
| AMEC1 source, for reference | Founded in January 1972 as the Aerospace Heat Treat Committee; in July 1974 it was renamed and its scope widened to aerospace metallic materials and processes in general. It joined the SAE Aerospace Materials Division in 1977. It writes new metal material and process specifications, investigates common problems, and runs round-robin tests.[27][28] |
- A 2015 MMPDS presentation says the AMS Division consists of the "AMS Metals Group," the "AMS NonMetals Group," and their committees.1 source, for reference[8]
#How to read the numbers
- The first issue has the number only; with each revision a single letter is added to the end, going A→B→C. Example: AMS5643 (1951) → … → AMS5643W (December 2021).[10]
- In the SAE MOBILUS revision histories, I and O are not used (H is followed by J, N by P). On the other hand, Q, S, X, and Z have been used: AMS5643Q (2007), AMS5643S (2013), AMS2350S (1971), AMS2350X (1973), AMS2350Z (1974). Letters other than I and O are used without gaps.[10][14][17]
- After Z is used up, the suffix moves to two letters. For AMS2350, Z (December 1974) was followed by AA (June 1975), and the sequence continued up to BA (1989). Even with two letters, AI and AO do not exist (AH→AJ, AN→AP).[14]
- In recent editions, even a reaffirmation (Reaffirmed) or stabilization (Stabilized) with no change to the content gets a new letter. Examples: AMS5047F was reaffirmed in 2012 and AMS5047G was stabilized in 2017; AMS1540C was reaffirmed in 2015 and AMS1540D was stabilized in 2018. However, the citation for AMS-STD-2154C reads "reaffirmed September 2005," so in earlier years a reaffirmation did not always change the letter.1 source, for reference[11][23][22]
- A number with a slash is a detail spec under a parent spec. AMS2759 gives the general requirements for heat treatment of steel parts, and AMS2759/3 specifies, "in conjunction with the general requirements of AMS2759," the heat treatment of parts made of precipitation-hardening stainless steel and maraging steel (and, from revision J, secondary-hardening steel). A slash sheet has its own revision letter (example: AMS2759/3J, May 2020).[13][32][33]
- Documents moved over from MIL and Federal specifications keep the same form. AMS-QQ-A-250 is the general specification for aluminum sheet, and the per-alloy detail specifications are slash numbers such as AMS-QQ-A-250/11 (6061).[34][18]
- The SAE MOBILUS product codes drop spaces and hyphens (AMSQQN290B, AMST9046B, AMSH6875C, AMSSTD2154C). On drawings and in documents the number is usually written with separators, as in AMS-QQ-N-290 or AMS 5643.[15][22]
Number classification (from the table of contents of the AMS Index, July 2009 edition)
- The table of contents of the SAE publication "SAE AMS INDEX July 2009" lists how number ranges map to fields. Each range runs from the first to the last document number that existed at that time; it is not a boundary rule (there are unused numbers within the ranges).[2]
| Number range | Field |
|---|---|
| AMS 1320–2175 | Maintenance chemicals and materialsAircraft Maintenance Chemicals and Materials |
| AMS 2201–2279 | Tolerances for dimensions and chemical compositionTolerances |
| AMS 2280–2980 | Quality control and processes (heat treatment, plating, inspection, etc.)Quality Controls and Processes |
| AMS 3002–3970 | Nonmetallic materialsNon-Metallics |
| AMS 4000–4349 | Aluminum alloysAluminum Alloys |
| AMS 4350–4490 | Magnesium alloysMagnesium Alloys |
| AMS 4500–4740 | Copper alloysCopper Alloys |
| AMS 4750–4893 | Other nonferrous alloysMiscellaneous Nonferrous Alloys |
| AMS 4897–4999 | Titanium alloysTitanium Alloys |
| AMS 5010–5132 | Carbon steel (wrought)Wrought Carbon Steels |
| AMS 5210–5225 | Special-purpose nonferrous alloysSpecial Purpose Nonferrous Alloys |
| AMS 5310–5339 | Cast iron and low-alloy steel (castings)Cast Iron and Low Alloy Steels |
| AMS 5340–5412 | Corrosion- and heat-resistant steels and alloys (castings)Cast Corrosion and Heat Resistant Steels and Alloys |
| AMS 5500–5966 | Corrosion- and heat-resistant steels and alloys (wrought; includes stainless, nickel-base, and cobalt-base)Wrought Corrosion and Heat Resistant Steels and Alloys |
| AMS 6240–6550 | Low-alloy steel (wrought)Wrought Low Alloy Steels |
| AMS 6900–6946 | Titanium alloys (a separate block from the 4900 series)Titanium Alloys |
| AMS 7205–7498 | Accessories, fabricated parts, and assembliesAccessories, Fabricated Parts and Assemblies |
| AMS 7510–7735 | Special-property materialsSpecial Property Materials |
| AMS 7800–7918 | Refractory and reactive metalsRefractory and Reactive Materials |
- The same table of contents also has a list page titled "AMS Converted from Military Specifications" and pages for AS, ARP, AIR, and TSB.[2]
- The AMS Index (July 2019 edition) can be searched by subject in seven areas (maintenance chemicals, tolerances, quality control, processes, nonmetallic materials, metals, and parts). It also has a numerical index and cross-reference tables to similar ASTM, AWS, Department of Defense, Federal, and MIL specifications and to UNS numbers.[29]
- "4000s = nonferrous," "5000s = corrosion- and heat-resistant steels and Ni and Co alloys," "6000s = low-alloy steels," and "3000s = nonmetals" broadly match the index. However, not all of the 2000s are processes: the early 2200s are tolerances, and the late 1000s through 2175 are maintenance chemicals. Titanium is in the 6900s as well as the 4900s. The 7000s cover parts, special-property materials, and refractory metals, and brazing filler metals fall under "other alloys" among the metals in the index classification (their number range is unconfirmed).[2]
- Metric-unit versions of AMS carry numbers that start with "MAM" (examples: MAM2242B, MAM2355E).1 source, for reference[30][31]
!What the statuses mean
- Each edition in SAE MOBILUS shows one of the statuses Issued, Revised, Reaffirmed, Stabilized, or Canceled. "Current" is not a MOBILUS status name; it is wording used by sales sites such as DIN Media and AFNOR.[11][20][35]
- Reaffirmed: confirmed at the five-year review as still valid with no change to the content. Examples: AMS2809A (2011), AMS5047F (2012).[4][20]
- Noncurrent: widely used in the past and possibly still needed for existing designs, but recommended not to be specified in new designs. Declared by the Aerospace Materials Division; the document remains available from SAE on request. Example: AMS2650 (made Noncurrent in January 1984, cancelled in August 1989).[9]
- Stabilized: judged to cover fundamental, stable technology that will not change, and removed from the periodic review cycle. The user must check whether the referenced documents and technical requirements are still appropriate. Examples: AMS5047G (2017), AMS-H-6875C (2020), AMS1540D (2018).1 source, for reference[23][36][19]
- Cancelled: replaced by another specification. When a cancelled specification is referenced, the requirements of the latest edition of its replacement must be met, and it remains in the numerical section of the AMS Index together with its replacement. Examples: AMS-T-9046B (2006), AMS-T-9047A (2006), AMS-QQ-A-250/11A (2008), AMS-C-26074C (2011).1 source, for reference[37][21][16]
⇢Transfer from MIL and Federal specifications
- On June 29, 1994, Defense Secretary Perry issued the memorandum "Specifications and Standards—A New Way of Doing Business," adopting the military specification reform report (the PAT report) and ordering its implementation. The policy: do not use MIL specifications without a waiver, use performance specifications and commercial standards instead, and work with industry associations to create commercial standards that replace MIL specifications.[38]
- Transferred specifications take the original number with "AMS-" added: QQ-A-250 → AMS-QQ-A-250, MIL-T-9046 → AMS-T-9046, MIL-H-6875 → AMS-H-6875, MIL-STD-2154 → AMS-STD-2154, MIL-C-26074 → AMS-C-26074, MIL-A-21180 → AMS-A-21180 (the "MIL-" is dropped).[34][39][40]
- SAE editions have been issued since about 1998 (AMS-C-26074 in August 1998, AMS-H-6875 in November 1998, AMS-T-9046 in July 1999, AMS-QQ-N-290 in July 2000). The Notices of Cancellation for the original MIL and Federal specifications were issued between 1999 and 2005.[16][19][21][15]
- The U.S. Department of Defense (DoD) uses industry standards by "adopting" them. Examples: DoD adoption notices were issued for AMS-QQ-N-290 on May 3, 2001, and for AMS-QQ-P-416 on March 28, 2002.1 source, for reference[41][42]
- What happens after the move differs by standard. AMS-T-9046 and AMS-T-9047 were cancelled in May 2006 and split into alloy-specific AMS documents. AMS-H-6875 remains for heat treatment of raw material only (Stabilized in 2020), and heat treatment of parts goes to the AMS2759 family. AMS-STD-2154 continues to be revised; the latest is Rev. E (2021).[21][43][19][22]
- Cancellation notices typically say "AMS-… may be referenced for future procurement," and some point to ASTM for non-aerospace use (QQ-A-250 refers to ASTM B209 for non-aerospace; the 2009 notice for MIL-STD-2154 refers to ASTM E2375 or AMS-STD-2154).[34][44]
- The cancellation notices for the original MIL and Federal specifications were checked against copies of the DoD notices posted on everyspec.com.1 source, for reference[45]
| Current number | Original standard | What it covers |
|---|---|---|
| AMS-QQ-A-250 | QQ-A-250F (Federal specification)2005 (QQ-A-250F Notice 2, cancelled 2005-05-26) | For aerospace or unknown use, see AMS-QQ-A-250 and its detail specifications (slash numbers); for non-aerospace use, ASTM B209. The AMS slash sheets were later cancelled as well: AMS-QQ-A-250/11A (6061) was cancelled in July 2008.Aluminum and Aluminum Alloy Plate and Sheet; General Specification[34][18] |
| AMS-QQ-P-4161 source, for reference | QQ-P-416F (Federal specification)2002 (Notice 1, cancelled 2002-03-28; DoD adoption notice issued the same day) | Cadmium plating. No. 2 in SAE sales on JSA Webdesk in April 2021 (AMS-QQ-P-416F).Plating, Cadmium (Electrodeposited)[63][42][61] |
| AMS-QQ-N-290 | QQ-N-290A (Federal specification)2001 (Notice 1, cancelled 2001-05-03; DoD adoption notice issued the same day) | SAE version first issued in July 2000 by AMS Committee B. Revised in 2007, 2009 and 2015; the latest, Rev. D, is dated October 2021.Nickel Plating (Electrodeposited)[64][41][15] |
| AMS-T-9046 | MIL-T-9046J1999 (Notice 2, cancelled 1999-09-17) | SAE version first issued in July 1999 (AMS Committee G). AMS-T-9046B was cancelled on May 15, 2006 and replaced by alloy-specific AMS documents.Titanium and Titanium Alloy, Sheet, Strip, and Plate[39][21] |
| AMS-T-9047 | MIL-T-9047G2005 (Notice 3, cancelled 2005-02-10) | SAE version first issued in May 2003 (AMS Committee G). AMS-T-9047A was cancelled on May 15, 2006.Titanium and Titanium Alloy Bars (Rolled or Forged) and Reforging Stock, Aircraft Quality[65][66] |
| AMS-H-6875 | MIL-H-6875H1999 (Notice 1, cancelled 1999-02-02) | SAE version first issued in November 1998 (AMS Committee E). Applies only to heat treatment of raw material; parts follow the AMS2759 family. Rev. C was Stabilized in September 2020.Heat Treatment of Steel Raw Materials[67][19] |
| AMS-STD-2154 | MIL-STD-21542004 (Notice 1, cancelled 2004-11-15; ASTM E2375 also allowed by Notice 3 of 2009-01-29) | AMS Committee K. Revisions continue; the latest is Rev. E (July 2021).Inspection, Ultrasonic, Wrought Metals, Process for[40][44][22] |
| AMS-C-260741 source, for reference | MIL-C-26074E / MIL-DTL-26074F1994 (MIL-C-26074E Notice 1, 1994-10-25) / 2003 (MIL-DTL-26074F Notice 1, 2003-02-05) | SAE version first issued in August 1998 (AMS Committee B). Naval nuclear applications were split off into MIL-DTL-32119. AMS-C-26074C is shown as cancelled in July 2011, but MOBILUS also lists a Rev. D dated June 2013.Electroless Nickel Coatings[68][69][16] |
| AMS-A-211801 source, for reference | MIL-A-21180D1999 (Notice 1, cancelled 1999-09-10) | High-strength aluminum castings. Current status on the SAE side is unconfirmed.Aluminum-Alloy Castings, High Strength[70] |
iRelationship to Nadcap, AS9100 and MMPDS
- Nadcap is an accreditation program for special processes run by PRI (Performance Review Institute). PRI is a nonprofit affiliate of SAE, established by SAE as a separate corporation in 1990, when it also started Nadcap (initially for nondestructive testing). Heat treating, welding, chemical processing, coatings and materials testing laboratories were added in 1994.[46]
- In Nadcap, PRI contract auditors audit facilities against criteria agreed by OEMs (aircraft and engine manufacturers). The audited facility pays for the audit, and OEMs require Nadcap as a condition of supplier approval. Accreditation decisions are made by vote of the OEM Task Groups.[46]
- For Nadcap heat treating accreditation, AC7102/S (supplement) and AC7102/8 (pyrometry) must be selected in addition to the base AC7102. AC7102/8 Rev C (applies to audits from July 20, 2025) has a field for selecting AMS2750 as the industry standard.1 source, for reference[47]
- AMS2750 (pyrometry) is the standard for temperature control of heat treatment equipment. It covers temperature sensors, instruments, correction factors, the system accuracy test (SAT), the temperature uniformity survey (TUS) and more. The latest is Rev. H (July 15, 2024, AMS Committee B).[12]
- AS9100 (quality management system standard for aviation, space and defense) is owned by the IAQG (International Aerospace Quality Group) and adds aerospace requirements to the text of ISO 9001. In 2022 the IAQG signed a publishing and distribution agreement with SAE, and from the next revision the number becomes IA9100 (expected to be issued in Q4 2026). AMS covers technical requirements for materials and processes, while AS9100 covers a company's quality system; their roles are different.[48]
- MMPDS is a handbook of design allowables for metallic materials, succeeding the U.S. Air Force MIL-HDBK-5 (the final Rev. J was cancelled in March 2006). It is administered by Battelle under contract to the FAA, and the FAA accepts MMPDS A-basis and B-basis values as meeting FAR 25.613. To add a new alloy to MMPDS, a public material specification is required; except for aluminum, the flow is to create an AMS specification first and then go to MMPDS.1 source, for reference[8][49]
iDifferences from UNS and ASTM
- UNS (Unified Numbering System) is an index number that cross-references metal designations from different countries and organizations; it is not a standard (set of requirements) itself. It is jointly managed by SAE and ASTM and published as SAE HS-1086 / ASTM DS56 (14th edition, 2023).[50]
- An AMS document is often a purchase specification that defines material, form and delivery condition in one standard. Example: the title of AMS5643W is "Steel, Corrosion-Resistant, Bars, Wire, Forgings, Mechanical Tubing, and Rings 16Cr - 4.0Ni - 0.30Cb (Nb) - 4.0Cu Solution Heat Treated, Precipitation Hardenable," so a single alloy (equivalent to 17-4PH), its forms and its condition are all in the title.[10][51]
- By contrast, ASTM A564/A564M (precipitation-hardening stainless steel bars and shapes) covers several grades in one standard, such as 630, 631, 632, XM-16 and XM-25, and the purchaser specifies the delivery condition (solution treated, aged, etc.).[52]
- Besides material specifications, AMS includes common standards for quality assurance sampling and testing (e.g., AMS2355 for aluminum and magnesium wrought products), identification marking (e.g., AMS2809 for titanium wrought products) and tolerances (AMS 2201–2279), which are referenced from the material specifications.[17][20][2]
- The cancellation notice for Federal specification QQ-A-250 points to AMS-QQ-A-250 for aerospace use and ASTM B209 for non-aerospace use, which shows that AMS is positioned as a purchase specification for aerospace.1 source, for reference[34]
→Tracing standards from a drawing note
- In the NASA Johnson Space Center heat treatment process specification PRC-2001 (Rev. I, December 2019), the material block of a drawing lists the "heat-treat condition to be procured" and the "procurement specification (material specification)," and heat treatment is specified by a note that cites the process specification. It states that reheat treatment of raw material is per AMS-H-6875 and material requirements for parts are per AMS 2759.[53]
- The same PRC-2001 states that referenced documents are taken to be the latest revision unless a revision is specified.[53]
- The NASA Johnson Space Center passivation process specification PRC-5002G (January 2021) requires stainless steel passivation per AMS 2700 (nitric acid Method 1 only) and gives "PASSIVATE PER NASA/JSC PRC-5002, TYPE VI" as an example drawing note.[54]
- AMS 2700 is divided into Method 1 (nitric acid; Types 1–8 differ in temperature, presence of sodium dichromate, etc.) and Method 2 (citric acid), and can be specified by method and type, such as "Method 1 Type 2."1 source, for reference[55]
- How purchase orders treat revisions differs by customer. One aircraft parts maker's public purchasing terms say process specifications are "the latest revision," while the terms for another customer say "the revision in effect on the date of the order."1 source, for reference[56]
Process, inspection and general standards (50)
Standards that define how things are made and how they are verified, such as heat treatment, plating and inspection. They may be called from within a material specification or written directly on a drawing.
Heat treatment and temperature control
| Standards | What it covers | Notes for machining and design | Related standards |
|---|---|---|---|
| AMS 2750Current AMS2750HRevised 2024-07-15 | Standard for temperature control of heat treatment furnaces and similar equipment (pyrometry). It sets requirements for sensors such as thermocouples, instruments, furnace classes, correction factors, the system accuracy test (SAT) and the temperature uniformity survey (TUS).Pyrometry[12][71][72] | When outsourcing heat treatment, check that the furnace is controlled per AMS 2750. In Nadcap heat treating accreditation, temperature measurement is audited under AC7102/8, and AMS2750 is listed as its industry standard. | PRI AC7102/8Nadcap Audit Criteria for Heat Treating PyrometryThe temperature measurement part of a Nadcap heat treating audit. AMS2750 is listed as the applicable standard in the scope-of-accreditation documents.JIS C 1602ThermocouplesSimilar field (temperature sensors) |
| AMS 2759Current AMS2759GRevised 2019-04-23 | General rules for heat treatment of steel parts (parent spec). It sets the general requirements for heat treatment done by parts makers and subcontractors, and details for each material are set in slash sheets such as /1 to /12.Heat Treatment of Steel Parts, General Requirements[73][74][67] | — | AMS-H-6875Heat Treatment of Steel Raw MaterialsThe former MIL-H-6875H was cancelled in 1999 and moved to AMS-H-6875 (heat treatment of steel raw material). Heat treatment of parts is handled by the AMS 2759 family.AMS 2750PyrometryFurnace temperature control |
| AMS 2759/1Current AMS2759/1JRevised 2021-08-03 | Requirements for harden-and-temper heat treatment of carbon and low-alloy steel parts to a minimum tensile strength below 220 ksi (1517 MPa). Because hardenability is limited, there is an upper limit on size (section thickness).Heat Treatment of Carbon and Low-Alloy Steel Parts, Minimum Tensile Strength Below 220 ksi (1517 MPa)[75][76][77] | — | AMS 2759/2Low-alloy steel at 220 ksi or aboveChoose by strengthJIS B 6913Hardening and tempering of steelSimilar field |
| AMS 2759/2Current AMS2759/2KRevised 2021-071 source, for reference | Requirements for heat treating low-alloy steel parts to a high strength of 220 ksi (1517 MPa) minimum tensile strength or above.Heat Treatment of Low-Alloy Steel Parts, Minimum Tensile Strength 220 ksi (1517 MPa) and Higher[78][79][80][81] | This strength range falls under the AMS 2649 grinding burn etch inspection (applies to 180 ksi and above) and the post-plating hydrogen embrittlement relief bake (AMS 2759/9). | AMS 2649Etch Inspection of High Strength Steel PartsInspection for burns caused by grinding or machining (rehardening, overtempering)AMS 2759/9Hydrogen Embrittlement Relief (Baking)Post-plating bakeJIS B 6913Hardening and tempering of steelSimilar field |
| AMS 2759/3Current AMS2759/3KRevised 2026-07-21 | Heat treatment requirements, such as solution treatment and aging, for parts made of precipitation-hardening stainless steel (such as 17-4PH), maraging steel and secondary-hardening steel. Steels not listed can also be processed under the manufacturer's recommended conditions.Heat Treatment, Precipitation-Hardening Corrosion-Resistant, Maraging, and Secondary Hardening Steel Parts[82][83][84] | 17-4PH shrinks on aging (about 0.0004–0.0006 mm/mm for Condition A to H900, and about 0.0009–0.0012 mm/mm for H1150). If finishing before aging, allow for the shrinkage. | AMS 2759Heat Treatment of Steel Parts, General RequirementsParent spec |
| AMS 2759/4Current AMS2759/4DRevised 2025-09-18 | Requirements for annealing (solution treatment), stress relief and stabilizing treatment of austenitic stainless steel parts.Heat Treatment, Austenitic Corrosion-Resistant Steel Parts[85][79] | — | AMS 2759/11Stress Relief of Steel PartsWhen specifying stress relief alone |
| AMS 2759/5Current AMS2759/5FRevised 2020-09-291 source, for reference | Requirements for harden-and-temper heat treatment of martensitic stainless steel parts (410, 416, 420, 431, 440C, etc.).Heat Treatment, Martensitic Corrosion-Resistant Steel Parts[86][79] | — | AMS 2759Heat Treatment of Steel Parts, General RequirementsParent spec |
| AMS 2759/6Current AMS2759/6DRevised 2024-07-261 source, for reference | Requirements for gas nitriding controlled by ammonia dissociation rate. The previous edition was titled "Heat Treatment and Gas Nitriding of Low-Alloy Steels" and covered Nitralloy, 4140, 4340, H11 and others.Gaseous Nitriding of Steel Parts, Controlled by Ammonia Dissociation[87][79][88][54][89] | Do not passivate nitrided stainless steel parts (the hardened surface may corrode or pit badly; caution from NASA JSC PRC-5002G). | AMS 2759/10Automated Gaseous Nitriding Controlled by Nitriding PotentialMethod controlled automatically by nitriding potentialAMS 2759/8Ion NitridingIon nitriding (current 8B, 2018-06-11)JIS B 6915Nitriding and nitrocarburizing of steelSimilar field |
| AMS 2759/7Current AMS2759/7FRevised 2026-06-15 | Requirements for carburizing parts made of carburizing steel and for the harden-and-temper that follows. Divided into three classes by quality stringency.Carburizing and Heat Treatment of Carburizing Grade Steel Parts[90][80][91] | After grinding a carburized part, it is subject to AMS 2649 etch inspection for localized uneven carburizing and grinding burn. | AMS 2418Plating, CopperHas been used as stop-off plating on surfaces that must not be carburizedAMS 2649Etch Inspection of High Strength Steel PartsCarburized parts also coveredJIS B 6914Carburizing, carbonitriding, hardening and tempering of steelSimilar field |
| AMS 2759/9Current AMS2759/9ERevised 2018-10-18 | Requirements for baking heat-treated steel parts to drive out hydrogen absorbed during plating, stripping, chemical milling, pickling or etching.Hydrogen Embrittlement Relief (Baking) of Steel Parts[92][93][81] | For high-strength steel (in the NASA JSC PRC-5007 example, 40 HRC / 180 ksi or above; for fasteners, 36 HRC / 160 ksi or above), the bake must start within 4 hours after plating. Check the hardness and strength of parts going out for plating on the drawing. | AMS 2404Plating, Electroless Nickel-PhosphorousPlating specs call out this bakeAMS 2406Plating, Chromium, Hard DepositSame as aboveAMS-QQ-P-416Plating, Cadmium (Electrodeposited)Same as above |
| AMS 2759/11Current AMS2759/11BRevised 2025-07-161 source, for reference | Requirements for thermal stress relief of steel parts. Covers carbon and low-alloy steel, tool steel, precipitation-hardening and maraging steel, and austenitic and martensitic stainless steel.Stress Relief of Steel Parts[94][95] | — | AMS 2759Heat Treatment of Steel Parts, General RequirementsParent spec |
| AMS 2770Current AMS2770RRevised 2020-08-20 | Requirements for heat treatment (solution treatment, aging, etc.) of wrought aluminum alloy parts. Applies to parts makers and subcontractors, and also to distributor heat treatment that changes the temper of stock.Heat Treatment of Wrought Aluminum Alloy Parts[96][97][98] | — | AMS 2772Heat Treatment of Aluminum Alloy Raw MaterialsHeat treatment on the stock maker's side (current 2772H, 2023-03-08). Successor to the former MIL-H-6088JIS H 0001Aluminium, magnesium and their alloys - Temper designationsSimilar field (temper designations such as T6 and T73) |
| AMS 2774Current AMS2774HRevised 2024-08-291 source, for reference | Requirements for heat treatment of nickel alloy and cobalt alloy parts. Additively manufactured parts were added to the scope from revision H.Heat Treatment, Nickel Alloy and Cobalt Alloy Parts[99] | — | AMS 2773Heat Treatment, Cast Nickel Alloy and Cobalt Alloy PartsCastings version |
| AMS 2801Current AMS2801DRevised 2024-03-01 | Requirements for heat treatment (annealing, solution treatment, aging, stress relief, etc.) of titanium and titanium alloy parts. Heat treatment by stock makers, forgers, and casters falls under AMS-H-81200.Heat Treatment of Titanium Alloy Parts[100][101] | — | AMS-H-81200Heat Treatment of Titanium and Titanium AlloysHeat treatment of stock |
| AMS 2769Current AMS2769DRevised 2020-09-221 source, for reference | Procedures and requirements for heat treating parts in a vacuum (reduced-pressure) furnace. Used as a supplement to the primary heat treatment specification.Heat Treatment of Parts in a Vacuum[102] | — | AMS 2750PyrometryFurnace temperature control |
Plating, conversion coatings, and peening
| Standards | What it covers | Notes for machining and design | Related standards |
|---|---|---|---|
| AMS 2700Current AMS2700GRevised 2025-05-27 | Requirements for passivation, which removes free iron and other contaminants from the surface of stainless steel parts. Defines methods (nitric-acid-based, citric-acid-based, etc.), types, and corrosion tests.Passivation of Corrosion Resistant Steels[103][54] | Do not passivate stainless steel that has been surface-hardened by nitriding, carbonitriding, etc., or carburized stainless steel (caution in NASA JSC PRC-5002G: the hardened surface may corrode or pit). | ASTM A967Chemical Passivation Treatments for Stainless Steel PartsThe passivation specification most used in the commercial sector. No directly corresponding JIS standard |
| AMS 2404Current AMS2404KRevised 2024-10-01 | Requirements for electroless nickel-phosphorus plating. Classes are divided by whether there is post-plate heat treatment (e.g., a class heat-treated at 450°F or higher for hardening, and a low-temperature heat-treatment class to improve adhesion on aluminum).Plating, Electroless Nickel-Phosphorous[104][81][105] | Specify coating thickness and class on the drawing. If the base metal is high-strength steel (40 HRC or higher, etc.), a hydrogen embrittlement relief bake within 4 hours after plating is required (NASA JSC PRC-5007E). | AMS 2759/9Hydrogen Embrittlement Relief (Baking)Post-plate bake for high-strength steelJIS H 8645Electroless nickel-phosphorus platingSimilar field |
| AMS 2406Current AMS2406RRevised 2025-12-03 | Requirements for hard chrome plating for wear resistance (plating process and coating thickness, hardness, adhesion, etc.).Plating, Chromium, Hard Deposit[106][107] | — | AMS 2460Plating, ChromiumChromium plating in generalAMS 2759/9Hydrogen Embrittlement Relief (Baking)Post-plate bake for high-strength steelJIS H 8615Chromium plating for engineering purposesSimilar field |
| AMS 2460Current AMS2460BRevised 2023-02-061 source, for reference | Requirements for electroplated chromium. A relatively new specification, introduced in 2007.Plating, Chromium[108] | — | AMS 2406Plating, Chromium, Hard DepositHard chromeJIS H 8615Chromium plating for engineering purposesSimilar field |
| AMS 2417Current AMS2417KRevised 2020-05-261 source, for reference | Requirements for zinc-nickel alloy electroplating and the properties of the coating.Plating, Zinc-Nickel Alloy[109] | — | AMS-QQ-P-416Plating, Cadmium (Electrodeposited)Same family of corrosion-protection platingAMS 2759/9Hydrogen Embrittlement Relief (Baking)Post-plate bake for high-strength steel |
| AMS-QQ-P-416Current AMS-QQ-P-416GRevised 2022-09-081 source, for reference | Requirements for cadmium electroplating. SAE took over the U.S. Federal specification QQ-P-416.Plating, Cadmium (Electrodeposited)[110][111] | — | AMS 2400Plating, CadmiumSAE's own cadmium plating specification (current 2400Y, 2020-07-14)AMS 2759/9Hydrogen Embrittlement Relief (Baking)Post-plate bake for high-strength steel |
| AMS-QQ-N-290StabilizedFinal version AMS-QQ-N-290DRevised 2021-10-12 | Requirements for nickel electroplating on steel, copper alloys, and zinc alloys. Designated Stabilized in 2021 (no further revisions).Nickel Plating (Electrodeposited)[112][113][114] | — | JIS H 8617Nickel and nickel-chromium electroplated coatingsSimilar field |
| AMS 2423Current AMS2423FRevised 2022-07-191 source, for reference | Requirements for hard nickel electroplating and the properties of the coating.Plating, Nickel Hard Deposit[115] | — | AMS-QQ-N-290Nickel Plating (Electrodeposited)General nickel plating (Stabilized)JIS H 8617Nickel and nickel-chromium electroplated coatingsSimilar field |
| AMS 2418Current AMS2418KRevised 2021-12-131 source, for reference | Requirements for copper electroplating. Has been used for anti-galling and for stop-off plating that protects surfaces from carburizing.Plating, Copper[116] | — | AMS 2759/7Carburizing and Heat Treatment of Carburizing Grade Steel PartsStop-off plating counterpart |
| AMS 2469Current AMS2469LRevised 2024-05-16 | Requirements for the process and coating performance of hard anodizing (a dense, hard oxide film) on aluminum and aluminum alloys. Used for wear resistance.Hard Anodic Coating on Aluminum and Aluminum Alloys[117][118][119][120] | About half of the coating thickness grows into the base metal and about half builds up outward (NASA JSC PRC-5006D). Radius the corners (MIL-A-8625 recommends R0.06 in at 0.002 in coating thickness). Check on the drawing whether the dimension applies after or before coating. | AMS 2468Hard Anodic Coating Treatment of Aluminum AlloysAnother specification in the same familyMIL-A-8625Anodic Coatings for Aluminum and Aluminum AlloysType III is hard anodizingJIS H 8603Hard anodic oxide coatings on aluminium and aluminium alloysSimilar field |
| AMS 2471Current AMS2471KRevised 2022-01-281 source, for reference | Requirements for uncolored sulfuric acid anodizing. Used to improve corrosion resistance and as a paint base.Anodic Treatment of Aluminum Alloys, Sulfuric Acid Process, Undyed Coating[121][122][123] | — | AMS 2472Anodic Treatment of Aluminum Alloys, Sulfuric Acid Process, Dyed CoatingsDyed version (current 2472H, 2020-01-13)MIL-A-8625Anodic Coatings for Aluminum and Aluminum AlloysType II is sulfuric acid anodizingJIS H 8601Anodic oxide coatings on aluminium and aluminium alloysSimilar field |
| AMS 2480Current AMS2480KRevised 2024-07-231 source, for reference | Requirements for applying a zinc phosphate coating to iron and steel as a paint base.Zinc Phosphate Treatment Paint Base[124] | — | AMS 2481Phosphate Treatment, AntichafingManganese phosphate (break-in, anti-galling) |
| AMS 2481Current AMS2481LRevised 2025-12-11 | Requirements for applying a manganese phosphate coating to iron and steel to prevent rubbing wear and galling.Phosphate Treatment, Antichafing[125][126] | — | AMS 2480Zinc Phosphate Treatment Paint BaseZinc phosphate as a paint base |
| AMS 2485Current AMS2485MRevised 2024-09-091 source, for reference | Requirements for applying a black oxide coating to parts.Coating, Black Oxide[127][128] | — | AMS 2489Blackening of Steel, Touch-Up MethodBlack oxide for repair work (2489B, 2026-04-01, confirmed in SAE's listing) |
| AMS 2430Current AMS2430URevised 2018-04-09 | Requirements for shot peening, which blasts the surface with shot (metal shot, glass beads, ceramic) to introduce compressive residual stress. Revision U added manual and batch processes alongside automated ones.Shot Peening[129][130][131][132] | The process specification of the predecessor lineage (U.S. Navy NADEP JAX LPS 500, 1995) required machining, deburring, corner radii/chamfers, straightening, and heat treatment of the surface to be peened to be finished before peening. Check the main text for how the current AMS 2430 handles this. | AMS 2432Shot Peening, Computer MonitoredWith computer monitoringAMS-S-13165Shot Peening of Metal PartsWhere the former MIL-S-13165 was transferred. Merged into AMS 2430 in 2007 and cancelledJIS B 2711Shot peening of springsSimilar field |
| AMS 2432Current AMS2432ERevised 2022-10-131 source, for reference | Requirements for shot peening in which conditions such as shot flow rate are continuously monitored and recorded by computer. Includes AMS 2430 and adds to it.Shot Peening, Computer Monitored[133] | — | AMS 2430Shot PeeningBase specification |
NDT and cleanliness
| Standards | What it covers | Notes for machining and design | Related standards |
|---|---|---|---|
| AMS 2640WithdrawnFinal version AMS2640KRevised 1996-04-01 | Specification that defined wet and dry magnetic particle inspection procedures. Cancelled in 1996 and replaced by ASTM E1444.Magnetic Particle Inspection[134][135] | If an old drawing calls out AMS 2640, the work is now normally done to ASTM E1444 (SAE cancellation notice). | ASTM E1444Magnetic Particle TestingSuccessor (stated in SAE's cancellation notice)JIS Z 2320-1Non-destructive testing - Magnetic particle testing - Part 1: General principlesSimilar field |
| AMS 2645WithdrawnFinal version AMS2645KRevised 1995-02-01 | Specification that defined fluorescent penetrant inspection procedures. SAE marked it Superseded in 1995, and its requirements were carried over to ASTM E1417.Fluorescent Penetrant Inspection[136][137] | If an old drawing calls out AMS 2645, do the work to the latest ASTM E1417 (SAE notice). | ASTM E1417Liquid Penetrant TestingSuccessor (stated in SAE's notice)AMS 2644Inspection Material, PenetrantSpecification for penetrant inspection materialsJIS Z 2343-1Non-destructive testing - Penetrant testing - Part 1: General principlesSimilar field |
| AMS 2644Current AMS2644JRevised 2024-08-011 source, for reference | Specification that defines the classification of materials used in penetrant inspection (penetrants, removers, developers, etc.) and the test methods for qualification and quality verification.Inspection Material, Penetrant[138][137] | — | ASTM E1417Liquid Penetrant TestingSpecification for the inspection processJIS Z 2343-2Non-destructive testing - Penetrant testing - Part 2: Testing of penetrant materialsSimilar field |
| AMS 2630Current AMS2630ERevised 2021-11-091 source, for reference | Procedure for pulse-echo ultrasonic inspection (contact and immersion methods, longitudinal and shear waves) of flat plate, round bar, cylinders, and shaped parts thicker than 0.5 in (12.7 mm).Inspection, Ultrasonic, Product Over 0.5 Inch (12.7 mm) Thick[139][140][141] | — | AMS 2632Inspection, Ultrasonic, of Thin Materials 0.50 Inch and UnderThin-section version (current 2632C, 2022-06-02)JIS Z 2344General rules for ultrasonic testing of metallic materials by the pulse echo techniqueSimilar field |
| AMS 2631Current AMS2631GRevised 2022-06-201 source, for reference | Ultrasonic inspection procedure for titanium and titanium alloy bar, billet, and plate (0.25 in or more in thickness or diameter).Ultrasonic Inspection, Titanium and Titanium Alloy Bar, Billet, and Plate[142] | — | AMS-STD-2154Inspection, Ultrasonic, Wrought Metals, Process forUltrasonic inspection of wrought products in generalJIS Z 2344General rules for ultrasonic testing of metallic materials by the pulse echo techniqueSimilar field |
| AMS-STD-2154Current AMS-STD-2154ERevised 2021-07-15 | Uniform method for ultrasonic inspection of wrought products (forgings, bar, plate, etc.) and their products. SAE took over the former MIL-STD-2154.Inspection, Ultrasonic, Wrought Metals, Process for[143][44] | — | MIL-STD-2154Inspection, Ultrasonic, Wrought Metals, Process forCancelled in 2004. AMS-STD-2154 and ASTM E2375 were named as successorsASTM E2375Ultrasonic Testing of Wrought ProductsReplacements named when MIL-STD-2154 was cancelledJIS Z 2344General rules for ultrasonic testing of metallic materials by the pulse echo techniqueSimilar field |
| AMS 2300Current AMS2300NRevised 2026-03-241 source, for reference | Procedure and acceptance criteria for evaluating the cleanliness (low inclusion content) of premium aircraft-quality steel (including hardenable stainless steel) by magnetic particle inspection.Steel Cleanliness, Premium Aircraft-Quality, Magnetic Particle Inspection Procedure[144][145][146] | — | AMS 2301Steel Cleanliness, Aircraft-QualityOne grade below in aircraft qualityAMS 2304Steel Cleanliness, Special Aircraft-QualitySpecial aircraft quality (2304D, 2026-03-13)JIS G 0555Microscopic testing method for the non-metallic inclusions in steelSimilar field (evaluation is by microscope) |
| AMS 2301Current AMS2301MRevised 2026-03-121 source, for reference | Procedure for evaluating the cleanliness of aircraft-quality ferromagnetic steel by magnetic particle inspection (sampling, preparation, inspection, and acceptance).Steel Cleanliness, Aircraft-Quality, Magnetic Particle Inspection Procedure[147] | — | AMS 2300Steel Cleanliness, Premium Aircraft-QualityHigher quality gradeJIS G 0555Microscopic testing method for the non-metallic inclusions in steelSimilar field |
| AMS 2649Current AMS2649ERevised 2024-09-09 | Requirements for etch inspection of high-strength steel parts after heat treatment, checking for grinding burn from aggressive machining or grinding (rehardening, overtempering) and for localized carburizing irregularities.Etch Inspection of High Strength Steel Parts[148][80][149] | Applies to base-metal and carburized low-alloy steel parts of 180 ksi (1240 MPa) or higher. Etching removes about 2.5–12.7 μm from the surface, so allow for it on surfaces with tight finished-dimension tolerances (SAE summary). | AMS 2759/2Heat treatment of low-alloy steel at 220 ksi and aboveFalls within the covered strength rangeAMS 2759/7CarburizingCarburized parts also covered |
| AMS 2175Current AMS2175BRevised 2024-04-251 source, for reference | Specification that divides castings into classes and grades by criticality and defines the NDT methods, sampling frequency, and acceptance criteria.Castings, Classification and Inspection of[150] | — | AMS 2442Magnetic Particle Acceptance Criteria for PartsMagnetic particle acceptance criteria for wrought parts (for comparison) |
| AMS 2442Current AMS2442ARevised 2022-10-201 source, for reference | Criteria for accepting or rejecting the indications found when wrought (ferromagnetic) parts are magnetic particle inspected. Intended for inspection of finished parts after machining is complete.Magnetic Particle Acceptance Criteria for Parts[151][135] | — | ASTM E1444Magnetic Particle TestingInspection procedure sideJIS Z 2320-1Non-destructive testing - Magnetic particle testing - Part 1: General principlesSimilar field |
Common material requirements (tolerances, composition limits, identification, quality)
| Standards | What it covers | Notes for machining and design | Related standards |
|---|---|---|---|
| AMS 2241Current AMS2241TRevised 2022-10-07 | Manufacturing dimensional tolerances (diameter, straightness, etc.) for bar and wire of corrosion- and heat-resistant steel, iron alloys, and titanium and titanium alloys. Revision T added sizes, added requirements for forging stock, and clarified straightness.Tolerances, Corrosion- and Heat-Resistant Steel, Iron Alloy, Titanium, and Titanium Alloy Bars and Wire[152][153] | — | JIS G 4303Stainless steel barsSimilar field (material specifications that include dimensional tolerances) |
| AMS 2248Current AMS2248HRevised 2022-05-12 | The permitted deviation from specified values when the receiving side runs a chemical analysis (check analysis) on parts or stock of high-alloy steels such as corrosion- and heat-resistant steels and maraging steel.Chemical Check Analysis Limits, Corrosion- and Heat-Resistant Steels and Alloys, Maraging and Other Highly Alloyed Steels, and Iron Alloys[154][155][156] | — | AMS 2259Chemical Check Analysis Limits, Wrought Low-Alloy and Carbon SteelsLow-alloy steel and carbon steel versionJIS G 0321Method of product analysis and permissible variations for steel productsSimilar field |
| AMS 2249Current AMS2249KRevised 2024-12-101 source, for reference | Permitted deviation when the receiving side runs a check analysis on titanium and titanium alloy castings and wrought products.Chemical Check Analysis Limits, Titanium and Titanium Alloys[157] | — | AMS 2248Check analysis tolerances for high-alloy steelSame family |
| AMS 2259Current AMS2259GRevised 2023-01-171 source, for reference | Permitted deviation when a check analysis is run on wrought low-alloy steel and carbon steel.Chemical Check Analysis Limits, Wrought Low-Alloy and Carbon Steels[158][159] | — | JIS G 0321Method of product analysis and permissible variations for steel productsSimilar field |
| AMS 2269Current AMS2269GRevised 2022-09-141 source, for reference | Permitted deviation when a check analysis is run on nickel, nickel alloy, and cobalt alloy castings and wrought products.Chemical Check Analysis Limits, Nickel, Nickel Alloys, and Cobalt Alloys[160] | — | AMS 2248Check analysis tolerances for high-alloy steelSame family |
| AMS 2371Current AMS2371MRevised 2025-11-121 source, for reference | Sampling and testing procedures for verifying that wrought products and forging stock of corrosion- and heat-resistant steels and alloys conform to the material specification.Quality Assurance Sampling and Testing, Corrosion- and Heat-Resistant Steels and Alloys, Wrought Products and Forging Stock[161][162] | — | AMS 2374Quality Assurance Sampling and Testing, Corrosion- and Heat-Resistant Steel and Alloy ForgingsForgings version (2374G, 2026-03-12) |
| AMS 2380Current AMS2380HRevised 2024-07-261 source, for reference | Requirements for approval of premium-quality titanium alloy products and for production controls (melting method, definition of a lot, macrostructure, ultrasonic inspection, etc.).Approval and Control of Premium-Quality Titanium Alloys[163] | — | AMS 2631Ultrasonic Inspection, Titanium and Titanium Alloy Bar, Billet, and PlateUltrasonic inspection of titanium |
| AMS 2315Current AMS2315JRevised 2025-05-031 source, for reference | Two methods for determining the delta ferrite content (%) in steel and iron alloys. Used when called out from a material specification.Determination of Delta Ferrite Content[164] | — | — |
Material specifications (130)
A material specification is a purchase specification that defines, in one document, which alloy is supplied in what form and in what condition, along with chemical composition, mechanical properties, tests, and acceptance criteria. Even for the same alloy, numbers differ by bar, plate, or forging, and by condition such as annealed or solution treated. Here we have collected the numbers whose sources were checked on Kezuriba's material pages. For composition, strength, and machinability, see each material's page.
Aircraft steel
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMS 5525 | Sheet, strip and plate. Supplied solution treated at 982°C (revision letter L confirmed on SAE Mobilus) | Steel, Corrosion and Heat-Resistant, Sheet, Strip, and Plate 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V 1800 °F (982 °C) Solution Heat Treated[213] | A286 |
| AMS 5528 | Sheet, strip and plate. Supplied solution treated (Condition A); the user heat treats to TH1050 or RH950 | Steel, Corrosion-Resistant, Sheet, Strip, and Plate 17Cr - 7.1Ni - 1.1Al Solution Heat Treated, Precipitation Hardenable[207][208] | 17-7PH |
| AMS 5529 | Cold-rolled sheet and strip (Condition C). Aged to CH900 | Steel, Corrosion Resistant, Sheet and Strip, 17Cr - 7.1Ni - 1.1Al, Solution Heat Treated and Cold Rolled, Precipitation Hardenable, 0.0015 to 0.050 Inch (0.038 to 1.27 mm) Nominal Thickness[209][210] | 17-7PH |
| AMS 5568 | Welded tube. Solution-treated condition | Steel, Corrosion- and Heat-Resistant, Welded Tubing 17Cr - 7.1Ni - 1.1Al Solution Heat Treated, Precipitation-Hardenable[211][210] | 17-7PH |
| AMS 5604 | Sheet, strip and plate. Supplied solution treated; aged to H900-H1150 | Steel, Corrosion Resistant, Sheet, Strip, and Plate 16.5Cr - 4.0Ni - 4.0Cu - 0.30Cb Solution Heat Treated, Precipitation Hardenable[199][198] | 17-4PH |
| AMS 5618 | Bar, wire and forgings. Consumable electrode vacuum melted. Revision letter K confirmed | Steel, Corrosion-Resistant, Bars, Wire, and Forgings, 17Cr - 0.52Mo (0.95 - 1.20C), (440C), Consumable Electrode Vacuum Melted[224] | 440C |
| AMS 5629 | Bar, wire, forgings, rings and extrusions. Vacuum induction melted plus consumable electrode remelted (ATI: VIM + VAR; Carpenter also VIM-VAR), supplied solution treated | Steel, Corrosion-Resistant, Bars, Wire, Forgings, Rings, and Extrusions 13Cr - 8.0Ni - 2.2Mo - 1.1Al Vacuum Induction Plus Consumable Electrode Melted Solution Heat Treated, Precipitation Hardenable[203][204] | PH13-8Mo |
| AMS 5630 | Bar, wire, forgings and forging stock. Revision letter M confirmed on SAE Mobilus | Steel, Corrosion-Resistant, Bars, Wire, and Forgings and Forging Stock 17Cr - 0.52Mo (0.95 - 1.20C) (440C)[223] | 440C |
| AMS 5643 | Bar, wire, forgings, tubes for machine structural use and rings. Supplied solution treated; the user ages it | Steel, Corrosion-Resistant, Bars, Wire, Forgings, Mechanical Tubing, and Rings 16Cr - 4.0Ni - 0.30Cb (Nb) - 4.0Cu Solution Heat Treated, Precipitation Hardenable[197][198] | 17-4PH |
| AMS 56441 source, for reference | Bar and forgings | Steel Bars and Forgings, Corrosion Heat Resistant, 17Cr - 7Ni - 1Al[212][210] | 17-7PH |
| AMS 5659 | Bar, wire, forgings, rings and extrusions. Consumable electrode remelted (MIL-HDBK-5J writes CEVM = consumable electrode vacuum melted), supplied solution treated | Steel, Corrosion Resistant, Bars, Wire, Forgings, Rings, and Extrusions 15Cr - 4.5Ni - 0.30Cb (Nb) - 3.5Cu Consumable Electrode Remelted Solution Heat Treated, Precipitation Hardenable[200][201] | 15-5PH |
| AMS 5731 | Bar, wire, forgings, tubing and rings. Consumable electrode remelted, solution treated at 982°C only (aging is done by the user). Revision letter M confirmed | Steel, Corrosion- and Heat-Resistant, Bars, Wire, Forgings, Mechanical Tubing, Rings, and Stock for Forgings, Rings, or Heading 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V (A286) Consumable Electrode Remelted, 1800 °F (982 °C) Solution Heat Treated Precipitation Hardenable[214] | A286 |
| AMS 5732 | Bar, wire, forgings, tubing and rings (up to 127 mm diameter). Consumable electrode remelted, solution treated at 982°C + precipitation hardened. Revision letter K confirmed | Steel, Corrosion- and Heat-Resistant, Bars, Wire, Forgings, Mechanical Tubing, Rings, and Stock for Forgings, Rings, or Heading 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V (A286) Consumable Electrode Remelted 1800 °F (982 °C) Solution and Precipitation Heat Treated[215] | A286 |
| AMS 5737 | Bar, wire, forgings and tubing (up to 127 mm diameter). Consumable electrode remelted, solution treated at 899°C + precipitation hardened (the treatment that gives higher tensile and yield strength). Revision letter R confirmed | Steel, Corrosion- and Heat-Resistant, Bars, Wire, Forgings, Mechanical Tubing, and Stock for Forging and Heading 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V (A286) Consumable Electrode Remelted 1650 °F (899 °C) Solution and Precipitation Heat Treated[216] | A286 |
| AMS 58581 source, for reference | Welding grade of sheet, strip and plate (ATI describes it as a restricted composition for welding). This is the title of the page without a revision letter, and the title of the latest revision is not confirmed | STEEL SHEET, STRIP, AND PLATE, CORROSION AND HEAT RESISTANT 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V Multiple Melted, 1800°F (980°C) Solution Heat Treated, Welding Grade[217] | A286 |
| AMS 5862 | Sheet, strip and plate. Consumable electrode remelted, supplied solution treated | Steel, Corrosion-Resistant, Sheet, Strip, and Plate, 15Cr - 4.5Ni - 0.30Cb (Nb) - 3.5Cu, Consumable Electrode Remelted, Solution Heat Treated, Precipitation-Hardenable[202][201] | 15-5PH |
| AMS 5864 | Plate. Vacuum induction melted plus consumable electrode remelted (ATI plate: VIM + ESR), supplied solution treated | Steel, Corrosion-Resistant, Plate, 13Cr - 8.0Ni - 2.2Mo - 1.1Al, Vacuum Induction Plus Consumable Electrode Melted, Solution Heat Treated, Precipitation Hardenable[205][206] | PH13-8Mo |
| AMS 5880 | Bar, wire, forgings and forging stock for bearings. Revision letter F confirmed | Steel, Corrosion-Resistant, Bars, Wire, Forgings and Forging Stock 17Cr - 0.52Mo (0.95 - 1.20C) (SAE 51440C) for Bearing Applications[225] | 440C |
| AMS 6257 | Bar, forgings and tubing. VAR, normalized and tempered condition. C 0.40-0.44 (the page viewed was AMS6257A). Latrobe notes it as the "successor to MIL-S-8844 Class 3" | Steel Bars, Forgings, and Tubing 1.6Si - 0.82Cr - 1.8Ni - 0.40Mo - 0.08V (0.40 - 0.44C) Consumable Electrode Vacuum Remelted Normalized and Tempered[192][193] | 300M |
| AMS 6260 | Bar, forgings and tube. Aircraft quality (air melted). What was seen on the page was AMS6260S | Steel, Bars, Forgings, and Tubing 1.2Cr - 3.2Ni - 0.12Mo (0.07 - 0.13C) (9310)[196] | 9310 |
| AMS 6265 | Bar, forgings, mechanical tubing and stock for forging. Premium aircraft quality by vacuum arc remelting (VAR) (what was seen on the page was AMS6265R) | Steel, Bars, Forgings, Mechanical Tubing and Forging Stock, 1.2Cr - 3.25Ni - 0.12Mo (0.07 - 0.13C) (9310), Vacuum Consumable Electrode Remelted[194][195] | 9310 |
| AMS 6345 | Sheet, strip and plate. Normalized or other heat-treated condition (the version seen on the page was AMS6345F) | Steel, Sheet, Strip, and Plate 0.95Cr - 0.20Mo (0.28 - 0.33C) (SAE 4130) Aircraft Quality, Normalized or Otherwise Heat Treated[181] | 4130 |
| AMS 63481 source, for reference | Bar. Normalized condition (what was seen on the page was the original edition title without a revision letter) | STEEL BARS 0.95Cr - 0.20Mo (0.28 - 0.33C) (SAE 4130) Normalized[182] | 4130 |
| AMS 6350 | Sheet, strip and plate. Aircraft quality (the version seen on the page was AMS6350R) | Steel Sheet, Strip, and Plate, 0.95Cr - 0.20Mo (0.28 - 0.33C) (SAE 4130), Aircraft Quality[180] | 4130 |
| AMS 63511 source, for reference | Sheet, strip and plate. Spheroidize annealed condition | Steel, Sheet, Strip, and Plate, 0.95Cr - 0.20Mo (0.28 - 0.33C) (SAE 4130), Spheroidized[184] | 4130 |
| AMS 6360 | Seamless tube. Normalized or stress relieved (the version seen on the page was AMS6360M) | Steel Tubing, Seamless, 0.95Cr - 0.20Mo (0.28 - 0.33C) (SAE 4130), Normalized or Stress Relieved[183] | 4130 |
| AMS 6370 | Bar, forgings and rings (including flash-welded rings and stock for forging). Aircraft quality | Steel, Bars, Forgings, and Rings, 0.95Cr - 0.20Mo (0.28 - 0.33C) (SAE 4130)[179] | 4130 |
| AMS 6414 | Bar, forgings, mechanical tubing and stock for forging. Premium aircraft quality by vacuum arc remelting (VAR). AMS6414N (revised 2023-03, shown as current on SAE Mobilus) | Steel, Bars, Forgings, Mechanical Tubing, and Forging Stock 0.80Cr - 1.8Ni - 0.25Mo (0.38 - 0.43C) (SAE 4340) Vacuum Consumable Electrode Remelted[185] | 4340 |
| AMS 6415 | Bar, forgings and tube. Air melted aircraft quality (Carpenter and Liberty note Air Melt). What was seen on the page was the AMS6415T title | Steel, Bars, Forgings, and Tubing 0.80Cr - 1.8Ni - 0.25Mo (0.38 - 0.43C) (SAE 4340)[186] | 4340 |
| AMS 6417 | Bar, forgings and tubing. Vacuum arc remelted (VAR). C 0.38-0.43 (the page viewed was AMS6417J; AMS6417L is shown as work in progress (WIP)) | Steel, Bars, Forgings, and Tubing, 1.6Si - 0.82Cr - 1.8Ni - 0.40Mo - 0.08V (0.38 - 0.43C), Consumable Electrode Vacuum Remelted[189][190] | 300M |
| AMS 6419 | Bar, forgings and tubing. VAR. C 0.40-0.45 (the page viewed was AMS6419K) | Steel, Bars, Forgings, and Tubing, 1.6Si - 0.82Cr - 1.8Ni - 0.40Mo - 0.08V (0.40 - 0.45C), Consumable Electrode Vacuum Remelted[191] | 300M |
| AMS 6440 | Bar, forgings, tube and stock for forging of low alloy steel. Aircraft quality, for bearings. Revision letter U confirmed on SAE Mobilus | Steel, Bars, Forgings, Mechanical Tubing, and Forging Stock, 1.45Cr (0.93 - 1.05C) (SAE 52100), Aircraft Quality For Bearing Applications[221] | 52100 |
| AMS 6444 | Bar, forgings, tube and stock for forging. Premium aircraft quality, consumable electrode vacuum remelting. Revision letter R confirmed | Steel, Bars, Forgings, Mechanical Tubing and Forging Stock, 1.45Cr (0.93 - 1.05C) (SAE 52100), Premium Aircraft-Quality, Consumable Electrode Vacuum Remelted[222] | 52100 |
| AMS 64541 source, for reference | Sheet, strip and plate. VAR (what was seen on the page was AMS6454F) | Steel, Sheet, Strip, and Plate 1.8Ni - 0.80Cr - 0.25Mo (0.38 - 0.43C) (SAE 4340) Vacuum Consumable Electrode Remelted[187] | 4340 |
| AMS 64841 source, for reference | Bar, forgings and tube. Normalized and tempered condition (what was seen on the page was AMS6484E) | Steel, Bars, Forgings, and Tubing 0.80Cr - 1.8Ni - 0.25Mo (0.38 - 0.43C) (SAE 4340) Normalized and Tempered[188] | 4340 |
| AMS 6512 | Grade 250 bar, forgings, tube and rings (up to 254 mm in diameter). Aerospace premium quality, consumable electrode vacuum melted, annealed condition. Revision letter J confirmed | Steel, Maraging, Bars, Forgings, Mechanical Tubing, Rings, and Forging Stock 18Ni - 7.8Co - 4.9Mo - 0.40Ti - 0.10Al Consumable Electrode Vacuum Melted, Annealed[219] | 18% Ni maraging steel, 300 grade |
| AMS 6514 | Grade 300 bar, forgings, tube and rings (up to 254 mm in diameter). Aerospace premium quality, vacuum consumable electrode remelted, delivered in the annealed (solution annealed) condition. Revision letter L confirmed on SAE Mobilus | Steel, Maraging, Bars, Forgings, Mechanical Tubing, Rings, and Forging Stock, 18.5Ni - 9.0Co - 4.9Mo - 0.65Ti - 0.10Al (Maraging 300), Premium Aircraft Quality, Consumable Electrode Vacuum Remelted, Annealed[218] | 18% Ni maraging steel, 300 grade |
| AMS 65211 source, for reference | Grade 300 sheet, strip and plate, solution annealed condition. The SAE Mobilus page for revision C states "Cancelled September 2005" (withdrawn). Carpenter still lists it as a corresponding standard for NiMark 250 | Steel Sheet, Strip, and Plate, Maraging, 18.5Ni - 9.0Co - 4.9Mo - 0.65Ti - 0.10Al, Consumable Electrode Melted, Solution Heat Treated[220] | 18% Ni maraging steel, 300 grade |
Titanium and titanium alloys
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMS 4902M | Commercially pure titanium sheet and strip (thickness up to 1 in), annealed. Equivalent to Grade 2 (listed as corresponding by the Japan Titanium Society, ATI, Carpenter and TIMET) | Titanium Sheet, Strip, and Plate Commercially Pure Annealed 40.0 ksi (276 MPa) Yield Strength[226][227] | Pure titanium Grade 2 |
| AMS 4907N | ELI sheet, strip and plate, annealed | Titanium Alloy, Sheet, Strip, and Plate, 6.0Al - 4.0V, Extra Low Interstitial, Annealed[236] | Ti-6Al-4V |
| AMS 4911T | Sheet, strip and plate (thickness up to 4 in), annealed | Titanium Alloy, Sheet, Strip, and Plate, 6Al - 4V, Annealed[232] | Ti-6Al-4V |
| AMS 49191 source, for reference | Sheet, strip and plate, duplex annealed | Titanium Alloy Sheet, Strip, and Plate, 6Al - 2Sn - 4Zr - 2Mo - 0.08Si, Duplex Annealed[245] | Ti-6Al-2Sn-4Zr-2Mo |
| AMS 4928X | Bars, wire, forgings, flash-welded rings and drawn shapes, annealed | Titanium Alloy Bars, Wire, Forgings, Flash-Welded Rings, and Drawn Shapes, 6Al - 4V Annealed[230][231] | Ti-6Al-4V |
| AMS 4930M | ELI bars, wire, forgings and rings, annealed | Titanium Alloy Bars, Wire, Forgings, and Rings, 6Al - 4V, Extra Low Interstitial, Annealed[235] | Ti-6Al-4V |
| AMS 4942H1 source, for reference | Commercially pure titanium seamless tubing, annealed (listed by Carpenter as a Grade 2 standard) | Titanium Tubing, Seamless Annealed, 40.0 ksi (275 MPa) Yield Strength[228][229] | Pure titanium Grade 2 |
| AMS 4943M | Seamless tubing for hydraulic use, annealed | Titanium Alloy, Hydraulic, Seamless Tubing 3.0Al - 2.5V Annealed[237] | Ti-3Al-2.5V |
| AMS 4944N | Seamless tubing for hydraulic use, cold worked and stress relieved | Titanium Alloy Tubing, Seamless, Hydraulic, 3.0Al - 2.5V, Cold Worked, Stress Relieved[238] | Ti-3Al-2.5V |
| AMS 4945J | Seamless tubing for hydraulic use, cold worked and stress relieved, with texture (contractile strain ratio) controlled. The former title states a yield strength of 105,000 psi (724 MPa) | Titanium Alloy Tubing, Seamless, Hydraulic, 3Al - 2.5V, Controlled Contractile Strain Ratio, Cold Worked, Stress Relieved[239] | Ti-3Al-2.5V |
| AMS 4965N | Bars, wire, forgings and rings, solution treated and aged | Titanium Alloy, Bars, Wire, Forgings, and Rings 6.0Al - 4.0V Solution Heat Treated and Aged[233] | Ti-6Al-4V |
| AMS 4967N | Bars, wire, forgings and rings, annealed (in a condition that can be heat treated later) | Titanium Alloy, Bars, Wire, Forgings, and Rings 6.0Al - 4.0V Annealed, Heat Treatable[234] | Ti-6Al-4V |
| AMS 4975 | Bars, wire and flash-welded rings (diameter ≤3.00 in, cross-sectional area ≤16 in²), solution treatment + precipitation treatment. The current edition is AMS4975R (revised 2025-09-12) | Titanium Alloy, Bars, Wire, and Rings, 6.0Al - 2.0Sn - 4.0Zr - 2.0Mo - 0.08Si, Solution and Precipitation Heat Treated[240][241] | Ti-6Al-2Sn-4Zr-2Mo |
| AMS 49761 source, for reference | Forgings and forging stock, solution treatment + precipitation treatment. Titles from edition M onward include "- 08Si" (as written on the SAE page); the current edition is N (2025-09-12) | Titanium Alloy, Forgings, 6.0Al 2.0Sn 4.0Zr 2.0Mo, Solution and Precipitation Heat Treated[242][243][244] | Ti-6Al-2Sn-4Zr-2Mo |
| AMS 49831 source, for reference | Forgings, single solution treatment + aging, 180 ksi tensile strength class (in MIL-HDBK-5J, die forgings under 1 in thick) | Titanium Alloy, Forgings, 10V - 2Fe - 3Al, Consumable Electrode Melted, Single-Step Solution Heat Treated and Aged, 180 ksi (1241 MPa) Tensile Strength[247][201] | Ti-10V-2Fe-3Al |
| AMS 49841 source, for reference | Forgings (section thickness ≤3.0 in) and forging stock, solution treatment + aging, 173 ksi class | Titanium Alloy Forgings 10V - 2Fe - 3Al, Consumable Electrode Melted, Solution Heat Treated and Aged, 173 ksi (1193 MPa) Tensile Strength[248][249] | Ti-10V-2Fe-3Al |
| AMS 49861 source, for reference | Forgings, single solution treatment + overaging, 160 ksi class (emphasis on toughness) | Titanium Alloy, Forgings 10V - 2Fe - 3Al Consumable Electrode Melted, Single-Step Solution Heat Treated and Overaged 160 ksi (1103 MPa) Tensile Strength[250][249] | Ti-10V-2Fe-3Al |
| AMS 4987 | Forgings (section thickness under 4.0 in) and forging stock, solution treatment + overaging, 140 ksi class. The current edition on SAE Mobilus is AMS4987G (2025-02-25) | TITANIUM ALLOY FORGINGS 10V - 2Fe - 3Al Consumable Electrode Melted, Single Solution Heat Treated and Overaged 140,000 psi (965 MPa) Tensile Strength[251][249] | Ti-10V-2Fe-3Al |
| AMS 70261 source, for reference | Pre-alloyed powder for additive manufacturing (established 2021-07-28). Not a standard for wrought material such as forgings or bars | Titanium Ti-5553 (Ti - 5Al - 5Mo - 5V - 3Cr) Powder for Additive Manufacturing[252] | Ti-5Al-5Mo-5V-3Cr |
| AMS-T-90461 source, for reference | Sheet and strip (Comp. AB-4 in the MIL-HDBK-5J table, triplex annealed material). The English title was not confirmed on a public page | Titanium and Titanium Alloy, Sheet, Strip, and Plate(SAE Mobilus. Transferred from MIL-T-9046 in 1999)[201][246] | Ti-6Al-2Sn-4Zr-2Mo |
Nickel alloys
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMS 4544J | Sheet, strip and plate. Annealed (revised 2022-08-26) | Nickel-Copper Alloy, Corrosion-Resistant, Sheet, Strip, and Plate 67Ni - 30Cu Annealed[279][280] | Alloy 400 |
| AMS 4675F | Bar (diameter or across flats 0.093–4.000 in) and forgings and stock for forging (revised 2022-10-26) | Nickel-Copper Alloy, Corrosion-Resistant, Bars and Forgings 67Ni - 30Cu[281][280] | Alloy 400 |
| AMS 5536R | Plate, strip and sheet. Solution treated (revised 2024-03-22) | Nickel Alloy, Corrosion- and Heat-Resistant, Sheet, Strip, and Plate 47.5Ni - 22Cr - 1.5Co - 9.0Mo - 0.60W - 18.5Fe (Alloy X or HX) Solution Heat Treated[276][277] | UNS N06002 |
| AMS 55401 source, for reference | Plate, sheet and strip (listed by Special Metals, VDM and ATI) | SHEET AND STRIP, CORROSION RESISTANT NICKEL CHROMIUM IRON ALLOY(Title on the SAE Mobilus base page. First issued 1940)[263][266][267] | Alloy 600 |
| AMS 5544M | Sheet, strip and plate. Annealed condition (revised 2026-07-21) | Nickel Alloy, Corrosion- and Heat-Resistant, Sheet, Strip, and Plate, 57Ni - 19.5Cr - 13.5Co - 4.2Mo - 3.0Ti - 1.4Al - 0.05Zr - 0.006B (Waspaloy), Consumable Electrode or Vacuum Induction Melted, Annealed[268][269] | UNS N07001 |
| AMS 55961 source, for reference | Plate, strip and sheet. Delivered in the annealed (solution treated) condition | ALLOY SHEET, STRIP, AND PLATE, CORROSION AND HEAT RESISTANT Nickel Base - 19Cr - 3.1Mo - 5.2(Cb + Ta) - 0.90Ti - 0.60Al Consumable Electrode or Vacuum Induction Melted, Annealed(Title on the SAE Mobilus base page. First issued 1964)[256][254][257][258] | Alloy 718 |
| AMS 55991 source, for reference | Plate, sheet and strip (listed by Special Metals, ATI and Haynes) | ALLOY SHEET, STRIP, AND PLATE, CORROSION AND HEAT RESISTANT Nickel Base - 21.5Cr - 9.0Mo - 3.7(Cb + Ta)(Title on the SAE Mobilus base page. First issued 1967)[259][260][262] | Alloy 625 |
| AMS 5662 | Bar, forgings and rings. Delivered as solution treated (premised on aging after machining) | ALLOY BARS, FORGINGS, AND RINGS, CORROSION AND HEAT RESISTANT Nickel Base - 19Cr - 3.1Mo - 5.1(Cb + Ta) - 0.90Ti - 0.50Al Consumable Electrode or Vacuum Induction Melted, Solution Treated[253][254] | Alloy 718 |
| AMS 5663 | Bar, forgings and rings. Solution treated + precipitation hardened (aged) condition | ALLOY BARS, FORGINGS, AND RINGS, CORROSION AND HEAT RESISTANT Nickel Base - 19Cr - 3.1Mo - 5.1(Cb + Ta) - 0.90Ti - 0.50Al Solution and Precipitation Heat Treated Consumable Electrode or Vacuum Induction Melted[255][254] | Alloy 718 |
| AMS 56651 source, for reference | Bar and forgings (listed by Special Metals, ATI and Carpenter as the applicable specification for 600) | Nickel Alloy, Corrosion- and Heat-Resistant, Bars, Forgings, and Rings and Stock for Forgings and Rings 74Ni - 15.5Cr - 8.0Fe(Current AMS5665R, revised 2023-05-30)[263][264][265] | Alloy 600 |
| AMS 56661 source, for reference | Bar, forgings and rings (listed by Special Metals, ATI, Haynes and Carpenter as the applicable specification for 625) | ALLOY BARS, FORGINGS, AND RINGS, CORROSION AND HEAT RESISTANT Nickel Base - 21.5Cr - 9.0Mo - 3.7(Cb + Ta)(Title on the SAE Mobilus base page)[259][260][261] | Alloy 625 |
| AMS 5704L | Forgings (3.25 in. and under) and forging stock. Solution treated + stabilized + aged (revised 2020-08-03. Whether a newer edition exists is not confirmed) | Nickel Alloy, Corrosion and Heat Resistant, Forgings 57Ni - 19.5Cr - 13.5Co - 4.6Mo - 3.0Ti - 1.4Al - 0.05Zr - 0.006B Consumable Electrode or Vacuum Induction Melted 1825 to 1900 °F (996 to 1038 °C) Solution, Stabilization, and Precipitation Heat Treated[270][271] | UNS N07001 |
| AMS 5706N | Bars, forgings, flash-welded rings and forging stock. As solution treated at 996–1038°C (revised 2020-08-04, Active on the SAE page) | Nickel Alloy, Corrosion and Heat-Resistant, Bars, Forgings, and Rings 57Ni - 19.5Cr - 13.5Co - 4.3Mo - 3.0Ti - 1.4Al - 0.006B - 0.05Zr Consumable Electrode or Vacuum Induction Melted 1825 to 1900 °F Solution Heat Treated[272][271] | UNS N07001 |
| AMS 5707N | Bars, forgings and flash-welded rings (3.25 in. and under). Solution treated + stabilized + aged (revised 2017-06-13. Whether a newer edition exists is not confirmed) | Nickel Alloy, Corrosion and Heat-Resistant, Bars, Forgings, and Rings 57Ni - 19.5Cr - 13.5Co - 4.3Mo - 3.0Ti - 1.4Al - 0.05Zr - 0.006B Consumable Electrode Remelted or Vacuum Induction Melted 1825 to 1900 °F (996 to 1038 °C) Solution, Stabilization, and Precipitation Heat Treated[273][271] | UNS N07001 |
| AMS 5708N | Bars, wire, forgings, rings and heading stock. As solution treated at 1079°C (revised 2024-09-11) | Nickel Alloy, Corrosion- and Heat-Resistant, Bars, Wire, Forgings, Rings, Forging, Flash-Welded Rings and Heading Stock 58Ni - 19.5Cr - 13.5Co - 4.3Mo - 3.0Ti - 1.4Al - 0.05Zr - 0.006B (Waspaloy) Consumable Electrode or Vacuum Induction Melted 1975 °F (1079 °C) Solution Heat Treated[274][271] | UNS N07001 |
| AMS 5709K | Bars and forgings. Solution treated at 1079°C + stabilized + aged (revised 2025-05-03, latest in the SAE revision history) | Nickel Alloy, Corrosion- and Heat-Resistant, Bars and Forgings, 58Ni - 19.5Cr - 13.5Co - 4.3Mo - 3.0Ti - 1.4Al - 0.05Zr - 0.006B, Consumable Electrode or Vacuum Induction Melted, 1975 °F (1079 °C) Solution Heat Treated, Stabilized, and Precipitation Heat Treated[275][271] | UNS N07001 |
| AMS 5754P | Bar, forgings, flash-welded rings and forging stock. Solution treated (revised 2024-09-03) | Nickel Alloy, Corrosion- and Heat-Resistant, Bars, Forgings, Rings, and Forging, Ring, and Heading Stock 47.5Ni - 22Cr - 1.5Co - 9.0Mo - 0.60W - 18.5Fe (Alloy X) Solution Heat Treated[278][277] | UNS N06002 |
| AMS 7233D1 source, for reference | Solid rivets (revision D of 1991-01-01. Shown as latest on SAE Mobilus) | RIVETS, SOLID, ALLOY, CORROSION RESISTANT 67Ni - 31Cu[282][280] | Alloy 400 |
Aircraft aluminum alloys
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMS-QQ-A-225/4A1 source, for reference | Rolled, drawn and cold-finished bar, rod and shapes. Reaffirmed 2017-02-17 (derived from federal specification QQ-A-225/4) | Aluminum Alloy, 2014, Bar, Rod, Wire and Special Shapes, Rolled, Drawn, or Cold Finished[293] | A2014 |
| AMS-QQ-A-225/6B1 source, for reference | Rolled, drawn and cold-finished bar and rod. Revised 2018-03-04 (derived from federal specification QQ-A-225/6) | ALUMINUM ALLOY, 2024, BAR, ROD, AND WIRE; ROLLED, DRAWN, OR COLD FINISHED[288] | A2024 |
| AMS-QQ-A-250/30A | 2219 sheet and plate (general requirements in AMS-QQ-A-250). Issued 1997, reaffirmed 2010, Stabilized 2013-12-12. Derived from federal specification QQ-A-250/30 | Aluminum Alloy 2219, Plate and Sheet[294][166] | A2219 |
| AMS-QQ-A-250/3A1 source, for reference | Alclad 2014 sheet and plate (2014 core, clad on both sides with 6003 alloy). Stabilized 2014-03-06. Derived from federal specification QQ-A-250/3 | Aluminum Alloy Alclad 2014, Plate and Sheet[290] | A2014 |
| AMS-QQ-A-250/4B | 2024 sheet and plate (general requirements in AMS-QQ-A-250). Stabilized 2015-02-05. Federal specification QQ-A-250/4 moved into AMS | Aluminum Alloy 2024, Plate and Sheet[283][166] | A2024 |
| AMS-QQ-A-250/5C | Alclad 2024 sheet and plate (2024 core, clad on both sides with 1230 alloy). Revised 2021-05-28 | ALUMINUM ALLOY ALCLAD 2024, PLATE AND SHEET[284][166] | A2024 |
| AMS 4029M | Sheet (T6) and plate (T651), nominal thickness 0.51-101.60 mm. Revised 2022-08-17 | Aluminum Alloy, Sheet and Plate (2014; -T6 Sheet, -T651 Plate) Solution and Precipitation Heat Treated[289][166] | A2014 |
| AMS 4031K | Sheet and plate (O: annealed, F: as fabricated). Revised 2022-08-17 | ALUMINUM ALLOY SHEET AND PLATE 6.3Cu - 0.30Mn - 0.18Zr - 0.10V - 0.06Ti (2219-O) - ANNEALED OR SPECIFIED FABRICATED (2219-F)[296][166] | A2219 |
| AMS 4037R | Sheet (T3) and plate (T351), thickness 0.20-101.60 mm. Revised 2020-08-20 | Aluminum Alloy, Sheet and Plate 4.4Cu - 1.5Mg - 0.60Mn (2024; -T3 Flat Sheet, -T351 Plate) Solution Heat Treated[285][166] | A2024 |
| AMS 4050K | Plate, T7451 (revised 2021-04-22) | Aluminum Alloy, Plate 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T7451) Solution Heat Treated, Stress Relieved, and Overaged[299] | A7050 |
| AMS 4084E | Sheet, T61 (2017-06-15, Stabilized = treated as not to be revised in future) | Aluminum Alloy Sheet 5.7Zn - 2.2Mg - 1.6Cu - 0.22Cr (7475-T61) Solution and Precipitation Heat Treated[308] | A7475 |
| AMS 4089G | Plate (0.250–1.500in), T7651 (revised 2025-02-25) | Aluminum Alloy, Plate, 1.6Cu - 2.2Mg - 0.22Cr - 5.7Zn (7475-T7651), Solution Heat Treated, Stress Relieved by Stretching, and Precipitation Heat Treated[307] | A7475 |
| AMS 4107H | Die forgings (nominal thickness 6.000in or less) and stock for forging, T74 (revised 2023-05-10) | Aluminum Alloy Die Forgings (7050-T74) Solution Heat Treated and Overaged[301] | A7050 |
| AMS 4108G | Hand forgings (nominal thickness 8in or less) and stock for forging, T7452 (revised 2026-04-20. The original edition's title writes the temper as T73652) | Aluminum Alloy, Hand Forgings, 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T7452), Solution Heat Treated, Compression Stress-Relieved, and Overaged[302][303] | A7050 |
| AMS 4120T1 source, for reference | Rolled and cold-finished bar and rod (T4, T351), nominal thickness up to 203.2 mm. Revised 2025-12-04 | Aluminum Alloy, Rolled or Cold-Finished Bars, Rods, and Wire, 4.4Cu - 1.5Mg - 0.60Mn (2024), Solution Heat Treated and Naturally Aged (T4), Solution Heat Treated, Cold Worked, and Naturally Aged (T351) - Material Specification[286] | A2024 |
| AMS 4132J | Die forgings, open-die forgings and rings (nominal thickness 4 in or less) and forging stock, T61 (revised 2026-03-12; first issued in 1957) | Aluminum Alloy, Die and Hand Forgings, and Rolled Rings, 2.3Cu - 1.6Mg - 1.1Fe - 1.0Ni - 0.18Si - 0.07Ti (2618-T61), Solution and Precipitation Heat Treated[309][310] | A2618 |
| AMS 4133F1 source, for reference | Die forgings (up to 4 in thick), open-die forgings (up to 8 in), rolled rings (up to 3 in) and forging stock, T6. Revised 2022-06-09 | Aluminum Alloy Forgings and Rolled Rings 4.4Cu - 0.85Si - 0.80Mn - 0.50Mg (2014-T6) Solution and Precipitation Heat Treated[291] | A2014 |
| AMS 4143G1 source, for reference | Die forgings and open-die forgings (thickness 102 mm or less), rings (wall thickness 63.5 mm or less), T6. Revised 2025-03-25 | Aluminum Alloy Forgings and Rolled or Forged Rings 6.3Cu - 0.30Mn - 0.18Zr - 0.10V - 0.06Ti (2219-T6) Solution and Precipitation Heat Treated[297] | A2219 |
| AMS 4152P1 source, for reference | Extruded bar, rod, shapes and tube (T3), cross-sectional area up to 206 cm². Revised 2025-03-05 | Aluminum Alloy Extrusions, 4.4Cu - 1.5Mg - 0.60Mn (2024-T3), Solution Heat Treated and Cold Worked[287] | A2024 |
| AMS 4153N1 source, for reference | Extruded bar, rod, shapes and tube (T6), cross-sectional area up to 206 cm². Revised 2025-06-17 | Aluminum Alloy, Extrusions 4.5Cu - 0.85Si - 0.80Mn - 0.50Mg (2014-T6) Solution and Precipitation Heat Treated[292] | A2014 |
| AMS 4162G1 source, for reference | Extruded bar, rod, shapes and tube (T8511), diameter or minimum thickness up to 2.999 in, cross-sectional area up to 25 in². Revised 2025-04-14 | Aluminum Alloy, Extrusions, 6.3Cu - 0.30Mn - 0.18Zr - 0.10V - 0.06Ti (2219-T8511), Solution Treated, Stress Relief Stretched, Straightened, and Precipitation Heat Treated[298] | A2219 |
| AMS 4201H | Plate, T7651 (revised 2025-02-25) | ALUMINUM ALLOY PLATE 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T7651)[300] | A7050 |
| AMS 4202F | Plate (0.250–4.000in), T7351 (revised 2025-07-09) | Aluminum Alloy Plate, 5.7Zn - 2.2Mg - 1.6Cu - 0.22Cr (7475-T7351), Solution Heat Treated, Stress Relieved by Stretching, and Precipitation Heat Treated[306] | A7475 |
| AMS 4295D | Sheet and plate (O, F, T31, T351, T37, T81, T851, T87). Stabilized 2013-09-17 | Aluminum Alloy, Sheet and Plate 6.3Cu - 0.30Mn - 0.06Ti - 0.10V - 0.18Zr (2219 - O, F, T31, T351, T37, T81, T851, T87)[295][166] | A2219 |
| AMS 4342G | Extruded bar, wire, profiles and tube, T74511 (revised 2023-09-05. The original edition's title writes the temper as T736511) | Aluminum Alloy, Extrusions 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T74511) Solution Heat Treated, Stress Relieved, Straightened, and Overaged[304][305] | A7050 |
Aircraft copper alloys
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMS 4530 | Sheet, strip and plate. Solution treated (TB00). Edition H (2010) | Copper-Beryllium Alloy Sheet, Strip, and Plate 98Cu - 1.9Be Solution Heat Treated (TB00)[316] | C17200 |
| AMS 4533 | Rod and bar. Solution treated + precipitation hardened (TF00). Current edition is F (2026-01-22) | Copper-Beryllium Alloy Bars and Rods 98Cu - 1.9Be Solution and Precipitation Heat Treated (TF00, formerly AT)[311] | C17200 |
| AMS 4534 | Rod and bar. Solution treated + cold worked + precipitation hardened (TH04). The scope of edition D is up to 3.000in (76.20mm) in diameter or across flats. Latest is edition E (2021) | Copper-Beryllium Alloy Bars and Rods 98Cu - 1.9Be Solution Heat Treated, Cold Worked, and Precipitation Heat Treated (TH04, formerly HT)[312] | C17200 |
| AMS 4535 | Mechanical tubing. Solution treated + precipitation hardened (TF00). Latest is edition E (2022) | Copper-Beryllium Alloy Mechanical Tubing 98Cu - 1.9Be Solution and Precipitation Heat Treated (TF00, formerly AT)[313] | C17200 |
| AMS 45951 source, for reference | Plate, solution treated plus spinodal hardened. The title is taken from the SAE URL and page name. Correspondence with C72900 could not be confirmed in manufacturer materials | Copper Nickel Tin Alloy Plate 77Cu - 15Ni - 8Sn Solution Annealed and Spinodal Hardened (TX 00)[334] | C72900 |
| AMS 4596C | Rod and bar (up to 8.500 in = 216 mm thick), solution treated plus spinodal hardened. Revised 2025-10-20. The original issue and revision A also covered tube | Copper Nickel Tin Alloy, Bars and Rods, 77Cu - 15Ni - 8Sn, Solution Annealed and Spinodal Hardened (TX02, formerly TX00)[326][327][328] | C72900 |
| AMS 4597 | Rod and bar, solution treated plus cold finished plus spinodal hardened (TX TS). Materion states it applies to TS160U rod and bar only | Copper-Nickel-Tin Alloy, Bars and Rods 77Cu - 15Ni - 8Sn Solution Annealed, Cold Finished and Spinodal Hardened (TX TS)[329][330][331] | C72900 |
| AMS 4598B | Tube for mechanical and structural use, solution treated plus spinodal hardened | Copper-Nickel-Tin Alloy, Mechanical Tube, 77Cu - 15Ni - 8Sn, Solution Annealed and Spinodal Hardened (TX02, formerly TX00)[332][328][333] | C72900 |
| AMS 4640 | Aerospace aluminum bronze rod, bar, shapes, tube and forgings. Tempers HR50 (stress relieved after drawing) or TQ50 (quenched and tempered). Latest edition is AMS 4640J (2023-11-10) | Aluminum Bronze, Bars, Rods, Shapes, Tubes, and Forgings, 81.5Cu - 10.0Al - 4.8Ni - 3.0Fe, Drawn and Stress Relieved (HR50) or Temper Annealed (TQ50)[318][319][320] | C63000 |
| AMS 4650 | Rod, bar, shapes and forgings. Solution treated (TB00). Confirmed up to edition N in search results | Copper-Beryllium Alloy, Bars, Rods, Shapes, and Forgings 98Cu - 1.9Be Solution Heat Treated TB00 (A)[314] | C17200 |
| AMS 4651 | Rod and bar. Hard (TD04). Edition C (2018) is current | Copper-Beryllium Alloy, Bars and Rods 98Cu - 1.9Be (CDA 172) Hard Temper (TD04)[315] | C17200 |
| AMS 4870G1 source, for reference | Centrifugal and chill castings, as cast (revised 2025-06). The sae.org page does not list a UNS number, and the correspondence with C95400 rests only on Copper Alloys Ltd's statement | Aluminum Bronze, Centrifugal and Chill Castings, 85Cu - 11Al - 3.6Fe, As Cast[321][322] | C95400 |
| AMS 4871H1 source, for reference | Centrifugal and chill castings, solution treated and tempered (Stabilized 2015-09). The correspondence with C95400 rests only on Copper Alloys Ltd's statement | Aluminum Bronze, Centrifugal and Chill Castings 85Cu - 11Al - 3.6Fe Solution Heat Treated and Tempered[323][322] | C95400 |
| AMS 4872C1 source, for reference | Sand castings, as cast. Cancelled in 1990 (CANCELLED) | Castings, Sand - Aluminum Bronze 85cu 11.2al 3.6fe, as Cast[325] | C95400 |
| AMS 4873G1 source, for reference | Sand castings, solution treated and tempered (revised 2024-09). The correspondence with C95400 rests only on Copper Alloys Ltd's statement | Aluminum Bronze Alloy, Sand Castings, 85Cu - 11Al - 3.6Fe, Solution Heat Treated and Tempered[324][322] | C95400 |
Aluminum alloys (JIS materials)
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMS-QQ-A-225/8B1 source, for reference | Rolled, drawn and cold-finished bar, wire and shapes. Revised 2010-12-29 (derived from Federal Specification QQ-A-225/8) | ALUMINUM ALLOY 6061, BAR, ROD, WIRE, AND SPECIAL SHAPES; ROLLED, DRAWN, OR COLD FINISHED[170] | A6061 |
| AMS-QQ-A-225/9A1 source, for reference | Rolled, drawn and cold-finished bar, wire and shapes. Reaffirmed 2014-07-25 (derived from Federal Specification QQ-A-225/9) | Aluminum Alloy 7075, Bar, Rod, Wire, and Special Shapes; Rolled, Drawn, or Cold Finished[178] | A7075 |
| AMS-QQ-A-250/11A | 6061 sheet and plate (general requirements in AMS-QQ-A-250). The SAE page shows it as Canceled as of 2008-07-15. Derived from federal specification QQ-A-250/11 | Aluminum Alloy 6061, Plate and Sheet[18][166] | A6061 |
| AMS-QQ-A-250/12A | Sheet and plate of 7075 (general requirements are in AMS-QQ-A-250). Stabilized 2013-12-12. Derived from Federal Specification QQ-A-250/12 | Aluminum Alloy 7075, Plate and Sheet[171][172] | A7075 |
| AMS 4027P | Sheet (T6) and plate (T651), thickness 0.15-152.40 mm. Revised 2022-04-29 | Aluminum Alloy, Sheet and Plate 1.0Mg - 0.60Si - 0.28Cu - 0.20Cr (6061; -T6 Sheet, -T651 Plate) Solution and Precipitation Heat Treated[165][166] | A6061 |
| AMS 4045N | Sheet (T6) and plate (T651), thickness 0.20–101.6mm. Revised 2026-09-21 | Aluminum Alloy Sheet and Plate, 5.6Zn - 2.5Mg - 1.6Cu - 0.23Cr, 7075: (-T6 Sheet, -T651 Plate), Solution and Precipitation Heat Treated[173][172] | A7075 |
| AMS 4078L | Sheet (T73) and plate (T7351), thickness over 0.991mm to 101.60mm. A temper that improves stress corrosion cracking resistance by overaging. Revised 2023-11-10 | Aluminum Alloy Sheet and Plate, 5.6Zn - 2.5Mg - 1.6Cu - 0.23Cr, 7075: (-T73 Sheet, -T7351 Plate), Solution Heat Treated and Overaged[174][172] | A7075 |
| AMS 4117M1 source, for reference | Rolled and cold-finished bar and rod and flash-welded rings (T6, T651). Revised 2026-03-25 | Aluminum Alloy, Rolled or Cold-Finished, Bars, Rods, and Wire, and Flash-Welded Rings, 1.0Mg - 0.60Si - 0.28Cu - 0.20Cr (6061; -T6, -T651)[167] | A6061 |
| AMS 4123L1 source, for reference | Rolled and cold-finished bar (T651). Revised 2024-03-04 | Aluminum Alloy, Rolled or Cold Finished Bars and Rods, (7075-T651), Solution and Precipitation Heat Treated[175] | A7075 |
| AMS 4126E1 source, for reference | Die forgings (up to 102mm), hand forgings (up to 152mm) and rolled ring forgings (wall thickness up to 89mm), T6. Revised 2025-04-14 | Aluminum Alloy, Die and Hand Forgings and Rolled Rings, 5.6Zn - 2.5Mg - 1.6Cu - 0.23Cr (7075-T6), Solution and Precipitation Heat Treated[177] | A7075 |
| AMS 4127L1 source, for reference | Die forgings (up to 102mm), hand forgings (up to 203mm) and rings (up to 89mm), T6. Revised 2024-03-01 | Aluminum Alloy, Forgings and Rolled or Forged Rings, (6061-T6), Solution and Precipitation Heat Treated[169] | A6061 |
| AMS 4150P1 source, for reference | Extruded bar, wire, profiles and tube, and flash-welded rings from extrusions (T6). Revised 2024-03-27 | Aluminum Alloy, Extrusions and Rings, 1.0Mg - 0.60Si - 0.28Cu - 0.20Cr - (6061-T6), Solution and Precipitation Heat Treated[168] | A6061 |
| AMS 4154S1 source, for reference | Extruded bar, wire, profiles and tube (T6, T6510, T6511). Revised 2023-11-10 | Aluminum Alloy, Extrusions 5.6Zn - 2.5Mg - 1.6Cu - 0.23Cr (7075-T6, 7075-T6510, 7075-T6511) Solution Heat Treated, Stress Relieved by Stretching when Required and Precipitation Heat Treated[176] | A7075 |
Copper alloys (JIS materials)
| Standards | Form / condition | Title (English) | Material |
|---|---|---|---|
| AMSH7199A (AMS-H-7199)1 source, for reference | Heat treatment of wrought beryllium copper parts (a process specification, not a material specification). Stabilized in the 2013 edition | Heat Treatment of Wrought Copper-Beryllium Alloys, Process for (Copper Alloys: Numbers C17000, C17200, C17300, C17500, and C17510)[317] | C17510 |
📖How to get them
- On SAE MOBILUS (saemobilus.sae.org), anyone can view each specification's title, status, responsible committee, revision history, and scope, but viewing or downloading the full text requires a subscription or login.[10][57]
- SAE AeroPaks are subscription packs that let you download 10, 20, 35, or 50 specifications per year from more than 8,000 aerospace standards. For multi-user subscriptions, get a quote from SAE sales.1 source, for reference[58][59]
- Per-document prices have not been confirmed on SAE's official pages. For reference, at DIN Media, the German standards seller, the PDF of AMS2750H (57 pages) was 194.02 euros (excluding tax). Process specifications with more pages cost more.low[35][60]
- In Japan, SAE AMS can be purchased through the Japanese Standards Association (JSA) Webdesk. In the April 2021 sales ranking of foreign standards, AMS 2750F:2020 (pyrometry) was No. 1, and in the SAE section AMS-QQ-P-416F was No. 2. For SAE standards not listed on Webdesk, inquire through the "product availability check service".[61]
- The National Diet Library's Research Navi says SAE aerospace standards can be found by number, and points to the National Diet Library, the JSA library, prefectural libraries, and university libraries for viewing, and to SAE's official site for purchase.[1]
- Individual standards can also be purchased from the online store of Accuris (formerly IHS's standards business), an SAE partner, which has Japanese-language pages.1 source, for reference[62]
Related pages:ASTM Standards Quick ReferenceStandards correspondence table (JIS, ISO, DIN, ASME)Materials and overseas equivalentsHardness conversion
📚Sources
AMS titles, revisions, and statuses were checked against SAE International's public pages (SAE Mobilus) and standards sales pages, and the explanation of how the system works against public materials from SAE, PRI (Nadcap), the U.S. Department of Defense, and others (confirmed 2026-10-07). Sources for material specifications are the same as on each material's page.
- ndlsearch.ndl.go.jp
- legacy.sae.org
- saemobilus.sae.org
- dsiintl.com
- saemobilus.sae.org
- nxtbook.com
- saemobilus.sae.org
- mmpds.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- wichita.edu
- saemobilus.sae.org
- shotpeener.com
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- everyspec.com
- dinmedia.de
- sae.org
- store.sfs.fi
- govinfo.gov
- everyspec.com
- everyspec.com
- everyspec.com
- everyspec.com
- performancetitanium.com
- everyspec.com
- dsp.dla.mil
- nist.gov
- atimaterials.com
- sma.nasa.gov
- saemobilus.sae.org
- store.astm.org
- boutique.afnor.org
- store.astm.org
- nasa.gov
- nasa.gov
- blog.ansi.org
- airindustriesgroup.com
- saemobilus.sae.org
- sae.org
- sae.org
- store.accuristech.com
- webdesk.jsa.or.jp
- accuristech.com
- everyspec.com
- everyspec.com
- everyspec.com
- saemobilus.sae.org
- everyspec.com
- everyspec.com
- everyspec.com
- everyspec.com
- djgrp.com
- jisc.go.jp
- saemobilus.sae.org
- store.sfs.fi
- saemobilus.sae.org
- boutique.afnor.org
- jisc.go.jp
- boutique.afnor.org
- boutique.afnor.org
- saemobilus.sae.org
- nasa.gov
- saemobilus.sae.org
- store.sfs.fi
- pmpa.org
- saemobilus.sae.org
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- jisc.go.jp
- saemobilus.sae.org
- jisc.go.jp
- saemobilus.sae.org
- boutique.afnor.org
- store.sfs.fi
- dinmedia.de
- saemobilus.sae.org
- store.sfs.fi
- jisc.go.jp
- store.sfs.fi
- saemobilus.sae.org
- dinmedia.de
- store.sfs.fi
- saemobilus.sae.org
- saemobilus.sae.org
- jisc.go.jp
- saemobilus.sae.org
- jisc.go.jp
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- saemobilus.sae.org
- store.sfs.fi
- jisc.go.jp
- store.sfs.fi
- store.sfs.fi
- saemobilus.sae.org
- store.sfs.fi
- nasa.gov
- jisc.go.jp
- store.sfs.fi
- store.sfs.fi
- jisc.go.jp
- store.sfs.fi
- saemobilus.sae.org
- store.sfs.fi
- store.sfs.fi
- saemobilus.sae.org
- saemobilus.sae.org
- shotpeener.com
- everyspec.com
- jisc.go.jp
- store.sfs.fi
- saemobilus.sae.org
- jisc.go.jp
- saemobilus.sae.org
- jisc.go.jp
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- jisc.go.jp
- store.sfs.fi
- saemobilus.sae.org
- store.sfs.fi
- dinmedia.de
- jisc.go.jp
- store.sfs.fi
- saemobilus.sae.org
- store.sfs.fi
- store.sfs.fi
- dinmedia.de
- saemobilus.sae.org
- jisc.go.jp
- saemobilus.sae.org
- store.sfs.fi
- jisc.go.jp
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- store.sfs.fi
- saemobilus.sae.org
- novelis.com
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- novelis.com
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- sae.org
- sae.org
- sae.org
- sae.org
- sae.org
- carpentertechnology.com
- sae.org
- saemobilus.sae.org
- sae.org
- saemobilus.sae.org
- atimaterials.com
- saemobilus.sae.org
- saemobilus.sae.org
- everyspec.com
- sae.org
- saemobilus.sae.org
- atimaterials.com
- standards.sae.org
- atimaterials.com
- saemobilus.sae.org
- clevelandcliffs.com
- sae.org
- atimaterials.com
- saemobilus.sae.org
- sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- titan-japan.com
- saemobilus.sae.org
- carpentertechnology.com
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- saemobilus.sae.org
- sae.org
- sae.org
- saemobilus.sae.org
- sae.org
- saemobilus.sae.org
- sae.org
- sae.org
- timet.com
- sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- specialmetals.com
- sae.org
- sae.org
- atimaterials.com
- saemobilus.sae.org
- specialmetals.com
- atimaterials.com
- saemobilus.sae.org
- saemobilus.sae.org
- specialmetals.com
- atimaterials.com
- saemobilus.sae.org
- vdm-metals.com
- saemobilus.sae.org
- saemobilus.sae.org
- haynesintl.com
- saemobilus.sae.org
- atimaterials.com
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- haynesintl.com
- saemobilus.sae.org
- saemobilus.sae.org
- specialmetals.com
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- alloys.copper.org
- concast.com
- saemobilus.sae.org
- copperalloys.net
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- saemobilus.sae.org
- sae.org
- hkvxni.files.cmp.optimizely.com
- saemobilus.sae.org
- hkvxni.files.cmp.optimizely.com
- concast.com
- sae.org
- concast.com
- saemobilus.sae.org