MIL-T-9046J 1 January 1983 ‘SUPERSEDING MIL-T-9046H 14 March 1974 MILITARY SPECIFICATION TITANIUM AND TITANIUM ALLOY, SHEET, STRIP, AND PLATE This specification is approved for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers aircraft quality titanium and titantun alloy metal sheet, strip and plate products. 1.2 Classification. Products shall be of the following compositions and con- ditions, as specified (see 6.2.1, 6.5 and Tables I and IX): 1.2.1 Composition. Commercially pure titanium (CP) Yield strength Code designation minimum, ksi 1/ cP-1 70.0 cP-2 55.0 cp-3 40.0 cpa 25.0 Alpha titanium alloys (A) Code designation Composition A-l SA1-2.5S0 a2 SA1-2.58n (ELT) 2/ A-3 6A1-2Cb-1Ta-0.8Mo AG BA1-1Mo~1V Teneficial comments (recomendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Engineering Specifications and Standards Department (Code 93), Naval Engineering Center, Lakehurst, NJ. 08733, by using the self-addressed Standardization Document Improve- ment Proposal (DD Form 1426) appearing at the end of this document or by letters FSC 9535eee eee MIL-T-90463 Alpha-beta titanium alloys (AB) Code designation Composition AB-1 eal AB-2 6Aal-4V (ELI) AB-3 6a1-6V-2Sn ABM 4 6A1-28n-42r-2H0 AB-5 3A1-2.5V AB-6 ayn Beta titanium alloys (8) Code designation Composition Bel 13V-11¢r-3AL B-2 11. 5Mo~62r-4.58" 3-3 3A1-8V-6Cr-4Mo~42r Bd 8Mo-8V-2Fe-3A1 1/ 1,0 ksi = 1000 psi 2/ ELT means “extra low interstitials.” 1.2.2 Condition. Code Description (treatmer A Annealed DA Duplex annealed Ta Triplex annealed ST Solution treated STA Solution treated and aged. (when multiple STA conditions are specified herein for a given alloy, as in table IV, the applicable aging temperature shall be added in pa~ rentheses as a suffix.) 2, APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specifications, standards, and handbooks. Unless otherwise specified, the folloving shecitications, standards, and handbooks of the issue listed in that issue st the Department of Defense Index of Specifications and Standards (DoDISS) spect fied in the solicitation form a part of this specification to the extent specified herein. SPECIFICATIONS MILITARY MIL-H-81200 - ~—=—sHeat Treatment of Titanium and Titanium Alloys.MIL-T-9046 ‘STANDARDS FEDERAL FED-STD-151 - Metals, Test "tethods. MILITARY MIL-STD-105, - Sampling Procedures and Tables for Inspection by Attributes. MIL-STD-129 - Marking for Shipment and Storage. MIL-STD-163 ~ Steel Mill Products Preparation for Shipment and Storage. MIL-STD-410 - Nondestructive Testing Personnel Qualification and Certification (Eddy Current, Liquid Penetrant, Magnetic Particle, Radiographic and Ultrasonic). (Copies of specifications, standards, handbooks, drawings, and publications required by marufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.) 2.2 Other publications, The following docunents form a part of this specifi- cation to the extent specified herein. The issues of the documents which are in- dicated as DoD adopted shall be the issue listed in the current DoDISS and the supplement thereto, if applicable. AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) ASTM A 480 ~ General Requirements for Flat-Rolled’ Stainless and Heat Resisting Steels in Form of Plate, Sheet and Strip. ASTM E8 - Tension Testing of Metallic Materials. ASTM E120 - Titanium and Titanium-Base Alloys, Chemical Analysis of. ASTM £146 - Zirconium and Zirconium Alloys, Chemical Analysis of. ASTM E290 - Semi-Guided Bend Test for Ductility of Metallic Materials. (Application for copies should be addressed to the American Society for. Testing and Materials, 1916 Race Street, Philadelphia. PA 19103.) SAE AEROSPACE MATERIAL SPECIFICATIONS (AMS) AMS 2242 - Tolerances - Corrosion and Heat Resistant Steel and Iron Base Alloy Sheet, Strip and Plate and Titanium and Titanium Alloy Sheet, Strip and Plate. AMS 2249 - Chemical Check Analysis Limits - Titanium and Titanium Alloys. aMS 2631 - Ultrasonic Inspection of Titanium Alloys. AEROSPACE RECOMMENDED PRACTICE (ARP) ARP 982A - Minimizing Stress Corrosion in Wrought Heat Treatable Titanium Alloys.———Ee=-«~E=s—assSSSsSsSSSSS MIL-T-90463 (Application for copies should be addressed to-SAE, 400 Commonwealth Drive, Warrendale, PA 15096.) (Industry association specifications and starlards are generally available for reference from libraries. They are also distributed among technical groups and using Federal agencies.) 2.3 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein, the text of this specification shall take precedence. 3. REQUIRENENTS 3.1 Material. Material for products supplied in accordance with this specifi- cation shall be multiple melted. The final melting cycle shall be consumable electrode practice under vacuum, The initial and intermediate melting cycles, as applicable, shall be consumable practice under vacuum, unless otherwise specified (see 6.2.1). When specified in the purchase documents, the first melting cycle shall be nonconsumable practice under vacuum or inert gas at a pressure no greater than 250 mm of mercury and shall employ an electrode tip of either graphite or water-cooled copper. 3.2 Finis 3.2.1 Sheet and strip. Sheet and strip shall have a surface finish comparable to corrosion resisting steel number 2D finish in accordance with ASTN A 480. Pro duct shall be free of surface contamination by oxygen (alpha case), hydrogen, nitrogen or other such harmful contaminants. 3.2.2. Plate, Unless otherwise specified, plate shall have a surface finish comparable to corrosion resisting steel number 1 finish in accordance with ASTM A 480. Product shall be free of surface contamination by oxygen (alpha case), hydro~ gen, nitrogen or other such harmful contaminants. 3.3 Chemical composition, The chemical composition, as determined by heat or lot analysis, shall be as specified in Table I. 3.3.1 Check analysis, Chemical composition variations shall meet the require- ments of AMS 2249, 3.4 Tensile properties. 3.4.1 Commercially pure and alpha-titanium alloys. Tensile properties shall conform to Table II. 3.4.2 Alpha-beta titanium alloys. Tensile properties shall conform to Table III for the condition ordered. 3.4.2.1 Property capabilities. Any specified property capability shall be demonstrated when specified (see 6.2.1). 3.4.2.1.1 Solution treated and aged. Except for composition 6Al-2Sn-42r-2Ho, products supplied in the annealed condition shall be capable of meeting the solutionMIL-T-90463 treated (ST) and solution treated and aged (STA) tensile properties specified in table II, when heat treated to these conditions in accordance with MIL-H-81200. 3.4.2.1.2 Aged. Products supplied in the solution treated (ST) condition shall meet the solution treated and aged (STA) tensile properties, when aged to this condition in accordance with MIL-H-81200. 3.4.2.2 Composition 6A1-2Sn-42r-2Mo_(AB-4). 3.4.2.2.1 Property capability. Any specified property capability shall be demonstrated when specified (see 6.2.1). 3.4.2.2.1.1 Triplex annealed. Sheet and strip supplied in the duplex annealed (DA) condition shall meet the triplex annealed (TA) tensile properties, when heat treated to this condition in accordance with MIL-H-81200. 3,4,2,2.1,2 Duplex annealed. Plate supplied in the annealed (A) condition shall meet the duplex annealed (DA) tensile properties, when heat treated to this con dition in accordance with MIL-H-81200, 3.4.2.3 Composition 6A1~4V (AB-1). 3.4,2.3.1 Property capability - sheet, strip and plate. Sheet, strip and plate supplied in the annealed condition shall meet the minimum tensile properties of Condition A, Table III, after exposure to a temperature of 718 + 14°C (1325° + 25°F) for a period of 20 + 2 minutes, such exposure to be followed by cooling in air. After temperature exposure and cooling, a minimum of 0.001 inch shall be removed from all surfaces of the sample prior to testing. Sufficient material shall be removed so as to insure compliance of the sample with the requirements of 3.2.1 and 3.2.2. Property capability shall be demonstrated when specified (see 6.2.1). 3.4.3 Beta titanium alloys. Tensile properties shall conform to Table IV for the condition ordered 3.4.3.1 Property capability ~ solution treated and aged. Products supplied in the solution treated (ST) condition shall meet the solution treated and aged (STA) tensile properties specified in Table IV, when aged to this condition in accordance with MIL-H-81200. Property capability shall be demonstrated when specified (see 6.2.1). 3.5 Bending. Sheet and strip products supplied in the annealed or solution treated condition shall withstand transverse bending at room temperature to an angle of 105-degrees on a radius equal to the "bend factor" times the nominal product thickness without evidence of cracking when examined at 20X magnification. Bend factors shall be as specified in Table V. Transverse bending shall consist of bends where the centerline of the bend is parallel to the principal rolling direction of the product. 3.6 Heat treatment. Products shall be heat treated in accordance with MIL-H- 81200. 3.7 Ultrasonic quality.NEE eee rere reeeecee eee eeEEreSeSeee eee EeEEEIaSaEaEEE MIL-T-9046 3.7.1 Alpha and alpha-beta titanium plate. Unless otherwise specified (see 6.2.1), alpha and alpha-beta titanium plate, 0.500 to 4.000 inches thick, shall meet the Class Al requirements of AMS 2631. 3.7.2 Commercially pure and beta titanium alloy plate. When specified (see 6.2.1), commercially pure and beta titanium alloy plate shall meet ultrasonic quality standards agreed upon by the acquiring activity and producer (see 6.2.1). 3.8 Microstructure. Except for 6Al-2Cb-ITa-0.8Mo plate and the beta titanium alloys, the microstructure of products supplied in accordance with this specifi- cation shall be representative of final processing below the beta transus. Micro- structure shall not be cause for rejection unless the products show definite non- conformance to the requirement of processing below the beta transus or to micro- graph standards agreed upon by the acquiring activity and the contractor. 3.9 Dimensional tolerances. Unless otherwise specified (see 6.2.1), di- mensional tolerances shall conform to the following requirements. 3.9.1 Length, straightness, thickness, and width. Tolerances for these di- mensions shall conform to AMS 2242. 3.9.2 Flatness, 3.9.2.1 Sheet _and strip tolerance. Flatness tolerances for sheet and strip shall conform to Table VI, except that these tolerances shall not apply to coiled products. 3.9.2.2 Single and duplex annealed plate tolerance. Flatness tolerances for single and duplex annealed plate shall conform to Table VII. Unless otherwise specified (see 6.2.1), flatness tolerances for plate in Conditions ST and STA shall be twice the values specified in Table VII. 3.10 Identification of product. Each sheet, strip and plate shall be marked on one face with the basic nunber and revision letter of this specification, heat number, composition, heat treat condition, producer's name or trademark and nominal thickness. This identity shall be placed in the respective locations specified below. The characters shall be of such size as to be clearly legible and shall be applied using a suitable marking fluid whose residue shall contain not more than traces of halogen-bearing compounds and shall be capable of being removed in hot alkaline cleaning solution without rubbing. The markings shall have no deleterious effect on the material or its performance and shall be sufficiently stable to with- stand normal handling. 3.10.1 Flat strip 6 inches and under in width. Flat strip 6 inches and under in width shall be marked in oné or more lengthwise rows of characters recurring at intervals not greater than 3 feet. 3.10.2 Flat sheet, flat strip over 6 inches in width and plate. Flat sheet, flat strip over 6 inches in width and plate shall be marked in lengthwise rows of characters recurring at intervals not greater than 3 feet, the rows being spaced not more than 6 inches apart and alternately staggered.MIL~T-9046J 3.10.3 Coiled sheet and strip. Coiled sheet and strip shall be marked both near the outside and inside ends, except that if coiled on a core, the inside iden- tification may be embossed on a durable tag or label securely attached to the core. 3.11 Norkmanship. The product shall be uniform in quality and condition, free from harmful alloy segregation and surface contamination by oxygen, nitrogen or other contaminant and foreign material, It shall be clean, sound, snooth, and free from cracks, seams, grind marks and other defects detrimental to the fabrication or performance of arts. 4, QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection. Unless otherwise specified in the contract or purchase order, the contractor is responsible for the performance of all in- spection requirements as specified herein. Except as otherwise specified in the contract or purchase order, the contractor may use his own or any other facilities suitable for the performance of the inspection requirements specified herein, unless disapproved by the Government. The Government reserves the right to perform any of the inspections set forth in the specification where such inspections are deemed necessary to assure supplies and services conform to prescribed requirements. 4.2 Classification of inspection. The inspection specified herein is clas- sified as quality conformance inspection. 4.3 Quality conformance inspection. The quality conformance inspection shall consist of all the inspections and tests specified herein. 4.3.1 Sampling. 4.3.1.1 Inspection lot. A lot shall consist of all sheet, strip or plate of the same heat, condition, size and thickness processed at the same tine. 4.3.1.2 Procedure. Sampling procedure for each heat or lot for determining conformance to the requirements of this specification shall conform to Table VIII. 4.4 Methods of inspection and test. 4.4.1 Visual examination, Samples of products selected in accordance with Table VIIL shall be visually examined for conformance to the identification (see 3.10) and workmanship (see 3.11) requirements. 4.4.2 Microstructure examination. One polished and etched metallographic speci men, of as many aS required to cover the product thickness from center to surface, shall be prepared from each sample selected in accordance with Table VIII. The specimens shall be examined at a magnification of 200X to 250X for conformance to the microstructure (see 3.8) and freedom from alloy segregation (see 3.11) require- ments and at a magnification of 100X to 200X for freedom from surface contamination by oxygen (alpha case) and other harnful contaminants as specified in 3.11. 4.4.3 Dimensional inspection. Samples selected in accordance with Table VIII for dimensional inspection shall be measured for conformance with the specified dimensions (see 6.2.1) and dimensional tolerances (sec 3.9) requirements.eee Eee reece eee Ereeeeeecee eee eee eeeeeereeeeeeeeee ee erEeeO MIL-T-90465 4.4.4 Ultrasonic inspection. Unless the ultrasonic quality requirement is waived by the acquiring activity (see 6.2.1), each plate, 0.500 inches and over in thickness, shall be inspected in accordance with AMS 2631 for conformance to the ultrasonic quality requirements of 3.7 through 3.7.2, as applicable. Ultrasonically inspected products shall be identified as agreed upon by the acquiring activity and producer (see 6.2.1). 4.4.4.1 Inspection personnel. Ultrasonic inspection shall be performed only by personnel qualified and certified in accordance with MIL-STD-410, 4.4.5 Packaging. Each shipment shall be inspected for conformance to the pack- ing and marking requirements specified in 3.10 and Section 5. 4.4.6 Chemical analysis. Conformance with the chemical composition requirenents shall be determined either by heat or lot analysis of samples selected in accordance with Table VIII using ASTM E 120 methods for chemical analysis or FED-STD-151, Method 112.2, for spectrochemical analysis. Hydrogen shall be analyzed by the hot extraction method specified in ASTM E 146 and shall be determined on each lot as shipped. Other analytical methods may be used with the written approval of the acquiring activity. 4.4.6.1 Referee method. In case of a dispute, the results of chemical analysis by the ASTM E 120 method shall govern. 4.4.7 Tension tests. Conformance to the mechanical property requirements shall be determined by testing at least two specimens (one longitudinal and one trans- verse) in the condition ordered (see 6.2.1) from each sample selected in accordance with Table VIII, except that transverse specimens are not required for strips under S-inches wide. In addition, an equal quantity of specimens shall be aged and tested to determine conformance to the Condition STA tensile properties as specified in 3.4.2.1.2 and 3.4.3.1 when material is supplied in the solution treated (ST) con- dition. Tension tests shall be accomplished in accordance with the following pro- visions. 4.4.7.1 Tension specimen configuration. The tension specimens shall conform to the following configurations in accordance with ASTM E 8: a. For product thickness up to 0.375 inch, standard "sheet-type" rectangular tension specimens shall be used. >. For product thickness equal to or greater than 0.375 inch, sub- standard round tension specimens with a 0.250 inch diameter reduced test scction shall be used. 4.4.7.2 Tension specimen preparation. Unless the lot consists of only one unit, Rot more than one specimen per grain direction per test condition shall be taken from each sample. Longitudinal specimens shall be prepared in such a manner that the longitudinal axis of the specimen 4s parallel to the principal rolling direction of the sample. Transverse specimens shall be prepared in such a manner that the longitudinal axis of the specimen is perpendicular to the principal rolling di- rection of the sample.MEL.-T-9046I 4.4.7.3 Tension test methed. Tension tests shall be accomplished in accordance with ASTM F 8, except the rate of strain shall be 0.003 to 0.007 inch/inch per minute through the yield strength and then is increased so as to produce failure Jn approximately one additional minute, In case of dispute, the results of referee tengion tests performed on a tensile machine having 2 strain pacer and using 2 strain rate of 0,005 in/in per min. through the yield strength and a minimum Crosshead speed of 0.10 inch per minute above the yield strength shall govern. 4.4.8 Bend tests. Conformance to the sheet and strip transverse bending re- quirements shall be deternined by testing at least two full-thickness specimens from aech let, Two separate bends shall be made on each specimen so that each surface is tested in tension, Specimens and test methods shall conform to the following pro- visions. 4.4.8.1 Bend specimens, Full thickness specimens by one inch wide shall be taken from the test samples selected in accordance with Table VIII. The length dimension shall be perpendicular to the principal rolling direction of the sample. Whenever possible, each specimen shail be long enough to permit two separate bends in accordance with 4.4.8, otherwise, the minimum quantity of ‘specimens stipulated in 4 4.8 shall be doubled to permit testing both surfaces of each sample sheet or strip. 4.4.8.2 Bend test methods. Bend tests shall conform to the V-block, U-channel or free-bend test method, In case of dispute, the results of bend tests using the V-block method shall govern. 4.4.8.2.1 Veblock test method, Tooling shall conform to the general configu= ration of Figure 1, The dies shall be wide enough to accommodate the entire width Of the bend specimens. The test speed shall be two to three inches per minute and the pressure shall be maintained on the bend specimen for at léast five seconds after the dies are fully closed. 4.4.8.2.2 UsChannel test method. Tooling shall consist of a conventional punch and U-channel. The specimens shall be bent to an angle of at least 105-degrees amound the required bend radius and, after removal from the fixture and allowing for springback, the angle shall he equal to or greater than 90-degrees. 4.4.8.2.3 Free-bend test method. Bend tests shall be accomplished in accordance with AST E 290. 7 4.5 Rejection and retests. 4.5.1 Rejection, Failure of the test samples to meet the requirements of this specification shall be cause for rejection of the represented lot, except that retesting in accordance with 4.5.2 shall be permitted in the case of nonconformance to the tensile and bend property requirements. 4.5.2 Retests. At the discretion of the producer, a rejected lot may be re- tested as specified below.MIL-T-90463 4.5.2.1 Flat products. All failed sample units from the original sample shall be excluded from the retest lot. Four new sample units shall be taken and tested in accordance with 4.4.7 and 4.4.8, as applicable. Failure of any retest specinen to meet the applicable property requirements shall be cause for rejection of the entire lot and no further retesting shall be permitted, 4.5.2.1,1 Retest lot. If the retest lot is accepted, the producer may at his discretion retest each sample unit which shows failure at one end only. Units which show failure at both ends shall not be retested and shall be rejected. Each sample unit acceptable for retesting of tensile properties shall be retested as follows: Two test specimens shall be taken from the failed end in either or both directions, longitudinal and transverse, which shoved unacceptable tensile proper- ties, and these specimens shall be tested in accordance with 4.4.7. Each sample unit for bend retesting shall be retested as follows: Two bend test specimens shall be taken fron the failed end and tested in accordance with 4.4.8. If any retest shows that bend or tensile properties do not conform to the requirements of Tables II, III, IV and V, as applicable, then the parent unit may be cut back at the failed end and further restested until either: (2) both ends show acceptable properties, or (b) the length of material remaining in the parent unit is less than the miniaum Specified length in the acquisition documents, vhichever first occurs. Acceptance or rejection of the parent unit shall then be made as appropriate. 4.5.2.2 Cotled products. Sample coils which show failure to meet tensile or bend property requirenents at both ends shall not be retested and shall be rejected. pample coils which show unacceptable tensile or bend properties at one end only may be retested at the producer's discretion. Specimens shall be taken and tested in the manner prescribed in 4.5.2.1.1., Failures of retests are cause for cutting back the failed end and further retesting until the coiled material either shows: (a) acceptable properties at both ends, or (b) is below minimum length oT weight speci- fied, whichever first occurs. Disposition of the coil shall then be made as appropriate. 4.5.3 Replacement of test specimens. Replacement of test specimens for reasons other than inferior or defective material shall be in accordance with FED-STD-1S1_ PACKAGING 5.1 Preservation-packaging., Not applicable. 5-2 Packing. Packing shall be Level A or C, as specified (see 6.2.1). 3.2,1 Sorting. Unless otherwise specified, the products shall be separated by composition, heat, size and condition when packed for shipment. 3.2.2 Level A - for domestic shipment and storage, and overseas shipment. Products shall be packed in accordance with the requirements of HIL-STD<163, as referenced for stainless steel. 5.2.3 Level C - minimum military packing (for domestic shipment) with inmediate use _at_initial destination. Packages which require overpacking for acceptance by the carrier shall be packed in exterior-type shivping containers in a manner that will assure safe transportation at lowest rate to the point “of delivery. Container shall meet, as a minimum, the requirements of rules and regulations applicable to the mode of transportation. 10MIL-T-9046I 5.3 Marking of shipment. In addition to any special marking required by the contract oF purchase order (see 6.2.1), shipping containers shall be marked tn sonerdance with MIL-STD-129. The identification shall consist of the following information listed in che order shown: a, National stock no. or other identification number as specified in the purchase document. 1/ : b. TITANIUM AND TITANIUM ALLOY, SHEET, STRIP OR PLATE (as applicable). c. Heat number. 4. Lot number. e. Size (thickness by width by Length). £. number and revision letter of this specification, including latest amendment if any. g- Composition. hh. Heat treatment condition. i. Gross weight. 4. Manufacturer's name or trademark. 1/ ‘The contractor shall enter the nationai stock number specified in the acquisition document or as furnished by the acquiring activity. When the national stock number is not provided or available from the acquiring activity, leave space therefor and gneer the stock number or other identification when provided by the acquiring activity. 6. NOTES 6.1 Intended use. The products acquired under this specification are intended for structural applications in airborne vehicles and equipnent. 6.2 Ordering data. 6.2.1 Acquisition requirenents. Acquisition documents should specify the following: a, Title, number, revision letter and amendnent number (if any) of this specification. b. Composition (see 1.2.1) and heat treat condition (see 1.2.2). ¢. Product form (plate, sheet or strip, as applicable), size (thickness, width and length) and quantity. 4. Melting practice of initial and intermediate melts if other than consumable electrode under vacuum (see 3.1). ueee Ee MIL-T-90463 ©, Demonstrations of property capability (see 3.4.2.1, 3.4.2.2, 3.4.2.3 and 3.4.3.1). f, Minimum elongation value for commercially pure, alpha and alpha-beta Products under 0.025 inch in thickness; and for beta products under 0.012 inch in thickness (see Tables II, III and IV), Whether ultrasonic quality is waived (see 3.7.1 and 4.4.4). 4h. Specify ultrasonic quality standards when required for commercially pure or beta alloy plate (see 3.7.2), 4. Define microstructure standards, if agreed upon, in accordance with 3.8, J. Flatness tolerances for sheet sizes greater than 36 inches in width (see 3.9.2.1 and Tables VI and VII). Kk, Flatness tolerances for products in Condition ST or STA 1f other than specified in 3.9.2.2. 1, Additional marking (see 4.4.4). m. Selection of applicable level of packing, 1.e., whether domestic oF overseas (Level A or C) packing is required (see 5.2), $-3 Setess corrosion. Certain processing procedures and service conditions may cause these titanium products to be subject to stress corrosion cracking. ARP 982 Feconmends practices to minimize the susceptibility to such stress corrosion crack« ing. 6.4 Definition. S-4-1 Sheet. A flat rolled product up co and including 0.187 inch in thickness and twenty-four (24) inches and over in width. 6.4.2 Strip. A flat rolled product up to and including 0.187 inch in thickness and generally furnished with slit, sheared, or slit and edge rolled in widths up to twenty-four (24) inches, inclusive; or with finished dram or rolled edges tn widths over 1-1/4 inches to twelve (12) inches, inclusive. 6.4.3 Plate. A flat rolled product of 0.188 inch and ovér in thickness and over 12 inches in width with the width at least five times the thickness, 6.4.4 Capability. The words "shall be capable of" are used herein to indicate gharacteristics or properties required in the product but for which testing of each jot is not required. However, if such testing 1s performed, products noe conforming fo the requirements of this specification shall be subject to rejection, 6-5 Gross-reference composition classifications. Table 1% shows the correlation between the composition classifications used in this specification and some of che earlier revisions, 12MIL-T-9046) 6.6 Revised classification coding system. The classification coding system introduced in this specification (see 1.2.1) is designed to satisfy the following criteria: a. Brevity, the importance of which is emphasized by the fifteen (15) digit restriction of the federal system for product identi- fication, ordering and cataloging. b. Adaptability across a range of specifications and documents such fas, NIL-T-81556, MIL-R-81588, MIL-T-9047 and MIL-HDBK-S. ase of recognition of grade of purity and alloy composition. 6.6.1 Design of coding system. 6.6.1.1. Identification of type classes. The coding system uses one or two jetters to identify the type class into which each grade or alloy falls. These letters are keyed to the four class names which are in wide use. Such coding is brief and makes for easier recognition than coding through the use of Roman numerals, Thus, "CP" is used to identify titanium of commercial purity grades; "A" identifies ALLLALPHA titanium alloys; "AB" identifies ALPHA~BETA alloys; and “B" identifies all-BETA alloys. 6.6.1.2 Number coding of CP grades and alloys. 6.6.1-2.1 Numbering of CP grades. The order of numbering CP titanium grades follow directly the order of increasing purity with respect to oxygen concentration. This sequence is the reverse of the order of changes in yield strength. Such nunerical sequencing was selected, because the thrust of development of the CP grades has generally been in the direction of increased purity, for example, CPS snd CP-6 for the two grades of weld filler metal. It does not appear that there gill be anv additional effort to strengthen CP titanium by increasing oxygen con- centration beyond that of CP-1. 6.6.1.2.2 Numbering of alloys. The order of numbering alloys generally follows the historical and present breadth and volume of usage of each alloy. Thus, 5Al- DisSn is coded acl; 6AI-AV is coded AB+1; and 13V-11Cr-3Al is coded Bl. The tin AB allev, although of greater age than AB-1, has not enjoyed the usage of AB-l and is assigned a higher number, namely AB-6. 6.6.2 UNS coding system. This coding system has been considered for adoption into the subject specification. However, the system has not been adopted because ite product code designations are not brief and make product identification dif- ficult and subject to error without the use of a catalog. Custodian: Preparing activity: Army ~ Navy AS Navy - Air Force - 20 (Project 9535-0242) Review activities: Army ~ AR, AV, GL, MT Navy - 0S, Sit Air Force - 99 DLA - 1S Dod ~ NS 1BIEEE OEE PEPE Cs TABLE T. Chemical composition, percent by weight. a a] om aot | san. js-s0- [2.90- [= ~ ~ 7 Selec fare j.s0 fo.os [0.05 [0.020 [0.20] - 0.40 an ° 7 - ‘ apie 7m i Tet Pare Ty Belo) ee P= Ps aap ae i 238 : tes Es g z tn 6.00 1.00 7 a is wo fi =] =P Page] f= foam fos] eam eos foul - | ove s us dem. fur] - tarfiat| ~ fess sete tel 1 = | | fasefosed — - frso-foos ou] = | owTABLE 1. Chemical composition, percent by weight. - Continued 1/ Balance is titanium. 2/ Hydrogen shall be determined on each lot of the product as shipped. Material shall meet this requirement when analyzed. ements each shall be 0.10 percent maximum. 3/ Need not be determined. Unless otherwise noted, other e: MIL-T-90465 4] Iron plus oxygen shall not exceed 0.32 percent. 5/ Other elements shall be 0.05 percent maximum each. 6/ Maximum, unless otherwise specified. T/ 0.35 - 1,00 percent Cu. 8/ 0,13 Si percent maximum. 9/ "Min ys" = minimum yield strength at 0.2 percent offset, kst- J0/ "ELI" = extra low interstitials. LI/ All alloys in this category shall have 0.005 percent yetrium maxinun. TABLE II, Commercial! ure and alpha titanium alloy sheet, strip and Plate annealed tensile properties. 1/7 — Classification Thickness, Tensile | Yield strength at | Elongation, and nominal inches strength, 0.2-percent percent composition 4 ksi ‘offset, ksi | in 2-inches or 4D —| cP=4 | 1.000 & Unde: 2/ —' A Inder 35 25 - 45 24 zy cP-3 1.000 & Under 50 40 - 65 20 2 cP-2 1.000 & Under 65 55 - 80 18 a cP-1 1.000 & Under 80 70 - 95 I= 2 1,500 & Under 120 113 lo = rarer 11500 - 4.000] 115 110 10 0.008 - 0.014 100 95 6 Ac2 (SA1-2.58n) (ELT) | 0.014 - 0.024] 100 95 8 0.024 - 1.000 100 95 10 A3 (6A1-2Cb-1Ta-0.8Mo) 10.1875 - 4.000 103 95 10 0.008 - 0.014 | 145 (135) 135 (120) 6 0.014 - 0.024 | 145 (135) 135 (120) 8 . “aMo- 0.024 = 0.1875) 145 (135) 135 (120) 10 (10) at COAST INoR1¥) lo.ig7s - 0.500 145 (130) 135 (120) 10 (10) y 0.500 - 1.000 }140 (130)] 130 (120) 10 (10) 1.000 - 2.000 | 130 (125) 120 (115) 10 (10) 2.000 - 2.500 |130 (120) 120 (110) 10 (8) 2.500 - 4.000 |120 (120) 110 (110, 8 8) [2-500 120 20) | (0) @ | 15| ALLT ~¥Uabd TABLE IT, Commercially pure and alpha titanium alloy sheet, strip and plate annealed tensile properties. - Continued 1/ A/ Minimun tensile properties except where a yield strength range 1s specified. properties apply in both the longitudinal and transverse directions aad ace for condition A (annealed), unless othervise noted, 2/ For thickness under 0.025 inch, elongation values shall be as ‘agreed upon by the acquiring activity and contractor (see 6-2-1). 3/ Values in parentheses apply to condition DA (duplex annealed). A/ Thickness given as X.XXX - X.XXX shall be read as "over ---- to -o-- inclusive." TABLE TIT. Alpha-beta titanium alloys sheet, strip and plate minimum tensile properties. 1/ elaei fication Condition Tateinee, Tesetie soninal ? aia otinety hal = * O.062 6 oer De ie featcany 0.062 = ae 1% ° 9 120 10 7 0.032 6 beder wv 730 (eat) 7 e032 = 0.095 7 130 (ws) . we 0.032 6 Onaer Te co v7 a2 - 0.048 us ‘ o.049 = outers Ms 3 0.1075 = 0.790 us . 0.750 ~ 1.600 10 ‘ 1,000 ~ 2.009 us bs ‘ Tee r 0.008 = 6.014 Be Te = (arty cen 0.014 = 0.02 0 120 . 0.01 = 1.000 bo no » 1.000 = 3.009 5 ns 1 a 7 0.024 Under 15 1 = 1 Tey Ce 2.026 0.1475 iss Ms = 10 way 0.1875 = 2,000 130 0 wy 2000 = 4.000 us bs soy = 21075 a w Toy a Ey 1875 6 Under 10 16 7 wy 0.1835 - 1.500 v0 Wo . 1.300 = 2.500 160 10 ‘ 2.500 = 4.009 130 uo ‘ rn 0.082 & Une Ds ws wa 2.082 = 1.000 bs ns ® 000 10 0 © % 0.057 © Under 1 Bs va 62 ~ 0.1875 us by fo aa 7 1.000" Uraer w » oe ont ae 7 O.1875 © uaaer cry Toe we ay 16MIL-1-9046J TABLE ITI. Alpha-beta titanium alloys sheet, strip and plate jninimum tensile properties. - Continued 1/7 Minimum tensile properties except as otherwise specified. Unless otherwise moved, properties apply in both the longitudinal and transverse directions. For thicknesses under 0.025 inch, elongation values shall be as agreed upon by the acquiring activity and contractor (see 6.2.1). a Elongation value in parentheses is for transverse direction only- Spread between tensile strength and yield strength shall be 15 ksi minimum, Thickness given as X.XKK - X.XXX shall be read as “over X.XXX to X.XXK, inclusive. TABLE IV. Beta titanium alloys sheet, strip and plate ninimun tensile properties. 17 ve iste i © tie 7 coe-tter-aA0) x Ho, » sr 13 7 7 * an sneo a » tt sm 3 7 00) a) Ps 7 omtesn-seeetvoctar) y (eee mv Feta) y ae 2.1015 6 baer 8 a0, a Or1aTs © Uoder Ts a0) 130 7nee EE eee MIL~7-9046I TABLE IV. Beta titanium alloys sheet, strip and plate ninimun tensile properties. - Continued 1/ Minimum tensile properties apply in both the longitudinal and transverse directions. Flongation value in parentheses applies in the transverse direction only. Condition ST (solution treated) is synonymous with solution anneal and condition A for beta titanium alloys. Fer thickness under 0.012 inch, elongation values shall be as agreed upon by the acquiring activity and purchaser (sce 6.2.1). Thickness given as X.XXX ~ X.XXK shall be read as "over X.XKK to X.XX, inclusive." Ys values are maximum for these alloys and sizes in ST condition. TABLE V. Bend factors for annealed or solution treated sheet and strip products. | Somercteily pure titanius Classification and nominal Bend factor | eae! Product thickness Product thickness 0.069 and under | over 0.069 to 0.1875, (inch) Ancl, (inch) cP=4 1 cP-3 2 cP-2 2 cP-1 2 ‘Alpha titanium alloys Ac1 (5A1-2.58n) 4.0 4-2 (SA1-2.58n) (ELI) 4.0 45 4-3 (6A1-2Cb=1Ta-0. 840) au a 4-4 (8Al~1Mo~1V) 4.5 (G0) 2/ 5.0 (4.5) 2/ Alpha-beta titanium alloys AB-1 (641-4) 4 AB-2 (6A1~4V) (ELI) 4 AB-3_ (6A1-6V-2Sn) 4 AB-4 (6A1-2Sn-421-2Mo) 4 AB-5 (3A1-2,5V) 2 AB~6 (Btn) 6 Beta titanium alloys B-1 (13V-11¢r-3a1) 3.0 B-2 (11.5Mo-62r-4.55n) 3.0 B-3 (3A1-8V-6Cr-GMo~42r) 3.5 B-4 (8No-8V-2Fe-3A1) 3.5TABLE V. Bend factors for annealed or solution treated sheet and strip products. ~ Continued Not applicable. Values in parentheses apply to duplex annealed condition. TABLE VI. Sheet flatness tolerances. Heat treat Product size Max. permissible condition Width, inch | Thickness, inch variation in of product cv] 3 flatness, percent 2/ { A 36 and under | 0,024 and under 3 0.024 = 0.1875 ay ST 36 and under | 0,069 and under 5 0.069 - 0.1875 3 STA 36 and under | 0.024 and under 5 0.024 - 0.087 3 For larger widths, maximum permissible percent variation in flatness shall be as agreed upon by the acquiring activity and supplier (see 6.2.1). Percent variation in flatness shall be determined from the expression Percent = 2 x 100 where: L = Distance in inches between contact points of a straight edge laid in any direction on the product. H = Perpendicular distance in inches from the straight edge to the product at point of greatest separation. Tolerances shall be as follows: 3 percent for commercially pure sheet. 5 percent for alloy sheet. Tolerances shall be as follows: 2 percent for commercially pure sheet. 3 percent for alloy sheet, ‘Thicknesses given as X-XXX - X.XXX shall be read as “over X.XXX to X.XXX, inclusive. 19TABLE VII. NIL-T-90465 Flatness tolerance for annealed and duplex annealed plate. aU ate thcknessy saches 37 ches 2 ne onus om + cory 0.999 Las wn ane re | sre ase fore | are une | oan | asne sa se | ane se ve ae one | ons | une an | ans fa iar nine ue ane nae one 18 bine ae oe oe Applicable to plate up to fifteen (15) feet in length or to any fifteen 36 inches, the maximum permissible variation in flatness shall be not The shorter dimension specified shall be greater than 0.250 inch. considered the width. Perpendicular distance at point of greatest separation from plate to straight edge or horizontal flat surface in contact with plate. feet of longer plates, except that if the longer dimension is under Thicknesses given as X.XXX - X.XXK shall be read as "over X.KKXK to X.XXX inclusive.” 20MIL-T-9046I TABLE VIII. Quality tonformance sampling (see 4.1, 4.3, 4.4.6 Jad 4.5.2). 7 Teapection ‘Saople os eee wor . Vous ™ Tandon seep le per MIL STOW IOS, aaoteatton oratey opeceton level ity agu ef 133 poreene defective con ™ Aandow samples per NIL-STD-105, Lespection Syete ee : peste mn t = ‘ lcrostrwceare at m Unit of sample is ingot. NA indicates "not applicable”. Unit of sample is one piece of plate, sheet, strip or one coil, as applicable. ‘The sample footage shall consist of equal lengths of strips taken from head and tail of each coil in the lot prior to shearing or slitting into multiple coils. Either heat or lot analysis is acceptable, except that hydrogen shall be determined on each lot (see 4.4.6). Complete ingot analysis shall be available to the acquiring activity. For coiled products, both the outside and inside ends of each coil shall be analyzed for hydrogen. Annealed -and solution treated conditions only. Only one random sample shall be required for microstructure examination of sheet and strip. ‘The sample size shall be based only on the applicable sample size code letter corresponding to the specified inspection level of MIL-STD-105. 2MIL-T-9046I TABLE IX. CrosS-reference composition classification. cro TRE Ra sar) Tyre 1 > Gonmerctatly pore Type 1 Gomerciatly pore | Comercisily pare anton tieaatee Tieanioe Comp. A anal oyed comps lamar on Cone. = anal oped y come. naldoped on o'tetey> cow. € = wnattoped cong 6 Paap oe ot " on Fiype Tt Alpe titannan ilo Tore Bp mies Pip sane alloy [ap cae os comp. comm. = Sin"2.550 idee at com y Gems 2 TSAR Se ema) | SA.Se0 (ELT) re 3 x ‘y x x $41-206-110-0.00 Galn2eb- 184-0. bs Tree HIT = Aiphacbeta ettanius | Alpnarbets Alloys ‘Niphe-bee Hheanhen alley | Alphecbece eitantr aloe ‘loys com. A = oe » es Gow. 8 = Gieme-ay x. Y. omy. 6 > eaten comp. & eur-uv aly fame. D> gaLcay (x41) np. 9 = ealaty a amp ES Stlcera Ste cen. a3 comp. datas 2se ‘y con. ay A24-te a camp. 117 gat-ttoe T ghictecere v ‘ar ws yy ‘7 ‘eve gieentum alloy tier ete eleanian alloy vetterssar tcnteesa “t Lssaastzeet 50 = ” Skicmvescr-aiesaze ey Broce tre-dah a 1/ This type and corresponding compositions deleted in their entirety. 2/ No composition equivalent to that of (AIA Proposed Revision to MIL-T-9046H). 3/ Deleted composition. 4/ No composition equivalent to that of MIL~T-9046H. 3/ Al has upper limit of 6.75 percent instead of 6,50 percent as in MIL~T-9046H. 6/ Nominal composition: 3A1-2.5V, UJ Listed as AB-5 in this document. 22MIL-T-9046I FEMALE DIE R= Bend radius in accordance with 3.5. x = 0,010 inch minimum to prevent galling and binding. FIGURE 1. Closed 105 degree bend angle V-block dies. ‘4#US, GOVERNMENT PRINTING OFFICE: 1983-608-094/829 23