MIL-S-23284.pdf

MILITARY SPECIFICATION

STEEL FORGINGS, CARBON AND ALLOY, FOR SHAFTS,

NUTS, COUPLINGS, AND STOCKS (RUDDERS AND

INCH-POUNDI

MIL-S-23284A(SH)

35 June 1990

SUPERSEDING

(See 6.4)

SLEEVES, PROPELLER

DIVING PLANES)

This specification is approved for use within the Naval Sea Systems Command, Department of the Navy, and is available for use by all Departments and Agencies of the Department of Defense.

1. SCOPE

1.1 Scope. This specification covers carbon and alloy steel forgings for torsional shafts, including propulsion shafts for ships, sleeves, couplings , propeller nuts, rudder stocks, di~’ing plane stocks, and related parts.

1.2 Classification. The forgings shall be made from the following classes of steel, as specified (see 3.4 and 6.2.1):

Class 1 - Nickel-molybdenum steel Class 2 - Nickel-molybdenum steel Class 3 - Carbon steel Class 4 - Carbon steel Class 5 - Nickel-chromium molybdenum steel Class 6 - Nickel-chromium molybdenum steel

2. APPLICABLE DOCUMENTS

2.1 Government documents.

Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to:

Commander, Naval Sea Systems Command, SEA 55Z3, Department of the Navy, Washington, DC 20362-5101 by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter.

AMSC N/A AREA FC)RG

QI_S-T~IBIJTIONSTATEMENT A ~lpproved for public release; distribution unlimited—----.-—-.—.--....—.-............-..

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MIL-S-23284A(SH)

2.1.1 Specifications and standards. The following specifications and standards form a part of this specification to the extent specified herein.

Unless otherwise specified, the issues of these documents shall be those listed in the issue of the Department of Defense Index of Specifications and

Standards (DoDISS) and supplement thereto, cited in the solicitation.

SPECIFICATIONS

FEDEIUL

A-A-1894

MILITARY

MIL-C-16173

MIL-L-19140

STANDARDS

MILITARY

MIL-STD-22

MIL-STD-248

MIL-STD-271

MIL-STD-278

MIL-STD-”731

MIL-STD-792

MIL-STD-1684

- Paper, Kraft, Treated (Fire Resistant).

- Corrosion Preventive Compound, Solvent Cutback, Cold-Application.

- Lumber and Plywood, F’ire-retardent Treated.

Welded Joint Design.

- Welding and Brazing Procedure and

Performance Qualification.

Requirements for Nondestructive Testing Methods.

Welding and Casting Standard.

- Quali~y of Wood Members for Containers and

Pallets.

- Identification Marking Requirements for

Special Purpose Components.

- Control of Heat Treatment.

MIL-STD-2073-1 - DoD Materiel Procedures for Development and Application of Packaging Requirements.

(Copies of specifications and standards required by contractors in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting activity. )

2.2 Other publications . The following documents form a part of this specification to the extent specified herein. Unless otherwise specified, the issues of the documents which are DoD adopted shall be those listed in the issue of the DoDISS specified in the solicitation. Unless othewise specified, the issues of documents not listed in the DoDISS shall be the issue of the nongovernment documents which is current on tl~edate of the solicitation.

AMERICAN NATIONAL STANDARDS INSTITUTE (ANSI)

B46.1 - Surface Texture (Surface Roughness, Waviness, and Lay) . (DoD adopted)

(Application for copies should be addressed to the American National Standards Institute, Inc., 1430 Broadway, New york, ~ 10018”)

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AMERICAN SC)CIETY FOR TES”I’INGAND MATERIALS (ASTM)

A 370 - Standard Test Methods and Definitions for

Mechanical Testing, of Steel Products. (DoD adopted) A 700 - Standard Praccices for Packaging, Marking and

Loading Methods for Steel Products for Domestic Shipment. (DoD adopted)

A 751 - Standard Methods, Practices, and Definitions for Chemical Analysis of Steel Products.

EIO- Standard Test Method for Brinell Hardness of Metallic Materials. (DoD adopted)

E45 - Standard Practice for Determining the Inclusion Content of Steel. (DoD adopted)

E 112 - Standard Methods for Determining Average Grain Size. (DoD adopted)

~ :8: Standard XCtk,od of Macrcctch Testing, Inspcctior., and Rating Steel Products, Comprising Bars, Billets, Blooms, and Forgings. (DoD adopted)

E 616 - Standard Terminology Relating to Fracture Testing.

(Application for copies should be addressed to the American Societ>- for Testing and Materials, 1916 Race Street, Philadelphia, PA 19103.)

iliU:.&L-’:Ui:ltiU.:AiLJLd:;&AKdG ,Ai:LuL!A2i pU!iiicii:LG:iJ JAI-L i4ULiJlJL~j] d~ailuk~:~ from the organizations which prepare or which distribute the documents. These documents also may be available in or through libraries or other informational sen’ices .)

2.3 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein (except for associated detail specifications, specification sheets or MS standards), the text of this specification shall take precedence. Nothing in this specification, however.

shall supersede applicable laws and regulations unless a specific exemption has been obtained.

3. REQUIREMENTS

3.1 First article. First article inspection is required for all classes of material listed herein (see 4.3 and 6.3) unless othemise specified (see 6.2.1).

3.2 Mel~il~. Unless ~tl~eL-wisespecified (see 6.2.1), steel shall be cast in metal molds or continuous cast, and shall be electric furnace steel or vacuum induction melted (VIM) steel. Primary melting may incorporate separate degassing or refining and may be followed by secondary melting using electroslag remelting (ESR) or vacuum arc remelting (VAIL).

3.2.1 &assin<. Unless otherwise specified (see 6.2.1), molten steel shall b~ vacuun degassed prior to or during pouzing of the material to remove objectionable gasses, particularly hydroger). When VAR is used, vacuum degassing of the primary melt is optional.

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3.2.2 Recovered materials. Unless otherwise specified herein, all material covered by this specification shall be new and may be fabricated using recovered materials to the maximum extent practicable without jeopardizing the intended use. The term “recovered materials” means materials which have been collected or recovered from solid waste and reprocessed to become a source of raw materials, as opposed to virgin raw materials. When specified (see 6.2.1), virgin raw material may be required for critical applications .

3.3 For~inz vrecess. The original cross-sectional area of the ingot shall be at least three times the cross-sectional area of the main body of the forging. Flanges and other enlargements on forgings need not be reduced to the ratio of 3 to 1, but shall be reduced to a ratio of not less than 1,7 CO

1. Total reduction of cross-sectional area shall also be sufficient so that the material conforms to the requirements of this specification. If bored ingots are used, che wall uf the ingot shall be reduced to at lease one-half its original thickness, or the reduction of cross-sectional area shall be at a ratio 3 to 1. When an upsetting operation is employed, or the forging is expanded on a mandrel, the metal shall be worked to an extent not less than specified above, but in no fixed ratio between the cross-sectional area of the ingot and that of the forging.

3.3.1 centerline. When ingots or forgings are bored, the bored hole shall include the centerline of the ingots or forgings.

3.4 Chemical com~osition. The chemical composition of the forgings shall conform to table I (see 4.4.3.1. 1,)within the allowable check analysis limits of table 11, Copyright Naval Sea Systems Command (Ship Systems) Provided by IHS Licensee=Portsmouth Naval Shipyard/5960068007, User=Hayes, Jerod

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MIL-S-2328GA(SH)

3.4.1 Heat analysis. The heat analysis shall conform to the specified chemical analysis with the excepcion clmt analyses for bismuth, cadmium, lead and zinc are not required (see table I and 4.4.2.1).

3.4.2 Check analysis variation. Check analysis variations of the elements shall not be over the upper limits or under the lower limits by more than the percentages listed in table II. Check analysis variations are not allowed for heat analysis.

TABLE II. Allowable check analvsis variations (wei~ht percent).

Cross-sectional area, square inches ~

Element 100 or less

Classes 1 and 2 Carbon 0.01 Manganese 0.03 Phosphorous None Sulfur None Silicon 0.02 Nickel 0.07 Chromium 0.03 Molybdenum 0.03 Vanadium None

Classe s 3 and 4 Carbon None Manganese 0.03 Phosphorous 0.008 Sulfur 0.008 Silicon 0.02

Classes 5 and 6 Carbon None Manganese 0.04 Phosphorous None sulfur None Silicon 0.02 Nickel 0.07 Chromium 0.06 Molybdenum 0.04 Vanadium 0.02 Copper None

~t Cross-sectional area

Over 100 to Over 200 to Over 400 to Over 800 200, incl. 400, incl. 800, incl.

CJ.01

0.04 None None 0.02 0.07 0.04 0.04 None

None 0.04 0.010 0.010 0.02

None 0,04 None None 0,02 0.07 0.06 0.04 0.02 None

0.02 0.05 None None 0.03 0.07 0.04 0.05 None

None 0.05 0.010 0.010 0.03

None 0.05 None None 0.03 0.07 0.06 0,05 0.02 None

0.02 0,06 None None 0.04 0.07 0.05 ().06 None

None 0.06 0.010 0.010 0.04

None 0.06 None None 0.04 0.07 0.07 0.06 0.02 None

0.02 0.07 None None 0.04 0.07 0.05 0.07 None

None 0,07 0.015 0.015 0.04

None 0.07 None None 0.04 0.07 0.07 0.07 0.02 None is the maximum area intercepted by a plane normal to the principal forging axis in the final heat-treated configuration.

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3.5 Mechanical pro~erties. After all heat treatments, including stress relief, the forgings shall meet the requirements for mechanical properties specified in table 111 (see 4.4.3.1.4). If it is not practical to test for mechanical properties after stress relief, a section of prolongation may be subjected to a simulated stress relief and tested (see 3.9) with the exceptior~ that all mechanical testing required for acceptance shall be performed. In the case where mechanical property data are required from each end of che forging and the manufacturer wishes to perform simulated stress relief, a section of prolongation from each end of the forging shall be subjected co simulated stress relief. It is not intended that mechanical properties be determined following stress relief of weld clad areas.

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TABLE III. )4echanical DroDercies .

Class 1 Class 2 Class 3 Class 4 Class 5 Class 6

YieJd strength at 0.01. 75,000 55,000 45,000 35,000 75,000 90,000 percent offset, pounds per square inch (lb/in’) minimum

Yield strength at 0.2 percent offset lb/in2 minimum y

Tensile strength, lb/inz 95,000/ 80,000/ 75,000/ 60,000/ 105,000/ 110,000/ 115,000 100,000 95,000 80,000 130,000 140,000

Elongation in 2 inches, longitudinal, percent

Elongation in 2 inches, transverse , percent ~

Reduction of area, longitudinal, percent

Reduction of area, transverse, percent ~

Charpy V-notch impact (foot pounds) ~ Test temperature, degrees Fahrenheit (’F) plus 10*3 minus 30 * 3 plus 28&3

Brinell hardness 10-mM standard ball 3000-Kil.ogram load ~

20 22 22 25 20 18

17 19 19 22 18 16

45 45 45 45 45 45

30 30 30 40 40 40

35 35

190-261 162-209 152-200 120-165 190-261 228-294

~ When transverse properties are required (see 6,2.1), this applies to shaft couplings, sleeves, and as specified for similar parts.

z/ Average of three tests, minimum. No test shall be below the average required minimum by more than 5 foot-pounds.

~ Impact values shall be recorded.

~ See 3.7.3.

.j~/T:)1,~1reportccl for infOrmati.0~10111*{.

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MLL-S-23284A{SH)

3.7 Dimensions. Finished dimensions of the forgings shall be as specified on the forging sketches or drawings. The rough forgings shall have sufficient stock to permit satisfactory finishing and provide for removal of test specimens (see 4.4.3.1.2 and 4,4.3.2.1).

3,7.1 ~trai~htenin~ of ciistorted for~in~s. If finished dimension cannot be met because of distortion, no corrective action shall be taken other than as specified, Straightening shall be performed at any stage of manufacture as required to meet the finished dimensions specified. When straightening is required after final temper for properties, a stress relief shall be performed at 50”F below the final tempering temperature.

3.7.2 ~i nzs. Each forging shall be forged as closely as possible to the finished (as supplied) shape and size.

3.7.2.1 ~iscard. Sufficient discard shall be Caken from each ingot to insure freedom from piping and to meet the microstructural (see 3.8.4) and nonmetallic inclusion requirement (see 3.8.5).

3.7,3 Multiple unit for~in~s. If practicable, when multiple unit forgings are used, the forgings shall.be machined apart to separate the individual units before heat treatment. For multiple unit forgings containing a variety of units with different section thicknesses, sample material representing each type of unit with a different section thickness shall be tested for mechanical properties. In this case, all units from one forging shall be heat treated in the same furnace charge and the sample material shall remain integrally attached to the part until after heat treatment is completed. For multiple unit forgings, each unit shall exhibit an average Brinell hardness, for three test determinations, that conforms to table III and that is within 20 points Brinell of the average hardness reported for the forgings which were tested for mechanical properties (see 4.4.3,1.5).

3.7,4 Hollow for~in~s from solid cylindrical forzinm. Where hollow forgings are to be machined from solid cylindrical forgings, the forgings shall be bored before heat treatment. If it is not practical to bore prior to heat treatment, impact specimens shall be removed from the minimum distance possible below the final inside diameter of the component except that the test location is not required to be deeper than mid radius of the solid cross section.

3.7.5 For@z s wei~hinsz 1000 pounds or less. Unless otherwise specified (see 6.2.1), after heat treatment each forging weighing 1000 pounds or less shall be Brinell hardness tested as specified in 4.4.3.1.5 and shall conform to table III.

3.8 J-lesttreatment. The contractor shall determine the detailed heat treatment that shall produce forgings to meet the requirements of this specificari.on. As appropriate for the required properties, the classes shall be either normalized and tempered, or quenched and tempered. For the quench and tempered condition, the forgings shall be normalized before heat treating (heating, quenching, and tempering) for properties and, when necessary, stress relief annealed after tempering.

3.8.1 Quenched and tempered for-. Quenched and tempered forgings s}lnllhe rol~,~hm~~hjn~rl and rol.t~bh~red, a~ applicable, prior to he~ting.

quenching, ~ancitemperin~,. If a spray quench is used} the number and location

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3.8.1.1 Horizontal quenching. When horizontal quenching is employed for hollow forgings, a mechanism (e.g. water lance) shall be used to ensure that the inside diameter of the component receives adequate quenchant flow.

3.8.2 Heat treating eauinment and controls. Continuous or automatic heat treating equipment may be employed, provided it produces heat treated material to meet the requirements of this specification. For the particular loading and size range of the pieces being heat treated, the temperature recording equipment shall be proven to correlate with actual temperature of the material and shall be maintained and calibrated on a regular basis. The LeLxIp~LaLuKe of che furnace cha~ge shall be recorded during the heating, holding and cooling cycles of the heat treatment. After the-charge reaches the selected temperature control setting, furnaces shall maintain the temperature of any point of the furnace charge within plus or minus 25”F.

3.8.2,1.Heat treatment eauirment and Procedures. Heat treating equipment and procedures shall be in accordance with MIL-sTD-1684, when specified (see 6.2,1),

3.8.2.2 JkaL ~reatment records. A record oi the cime and temperature of all heat treatments shall be available for inspection by the contracting activity.

3.8.3 Stress relief temperature. Unless othemise specified (see 6.2.1), the stress relieving temperature shall be at least 50”F below the tempering temperature and shall be not less than 1.050°F.

3.8.3.1 Cooling rate. For classes 1, 2, 3, and 4 stress relief shall be followed by furnace cooling to 600”F under uniform conditions at an average rate not to exceed 150”F per hour. The part may be cooled in still air when the temperature of the part is below 600”F. Report cooling rate for classes 5 and 6.

3.8.4 Microstructure. Specimens from all forgings, when examined at a magnification of 100 diameters, shall show a homogeneous structure; that is, one in which the normal constituents are evenly distributed, free from decided segregation of any constituents, or excessive inclusions (see 3.8.5). The material, when examined at a magnification of 100 diameters, shall have a grain size of 5 or finer (see 4.4.3.1.6). The area under examination shall show at least 95 percent of the structure with a grain size of number 5 or finer. Tests shall be in accordance with ASTM E 112.

3,.9,5 NOr-metallic ir.cl’~sioncOntertt SpecimPns frOm al] final forgings shall be examined for inclusion content in accordance with ASTM E 45, rne~hod A. The inclusion con~ent shall not exceed:

A 3.Ot 1.5h B 2.5t l.Oh* C 3.Ot 1.5h D 2.ot I.Oh*

*M~yjml.]m~~lC)W~~)l~:~]jamett!l-of hea~w nxide inclusion is 0.002 inch as determined by reference to ASTM E 45,”nwthod A-

1G

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M11.-s-23284A(sl-l)

3.9 Stress relief simulation. When specified (see 6.2.1), material to simulate stress relief treatments shall be heat treated in accordance with 4.4.3.1.8.

3.9.1 Weldment. When specified (see 6.2.1), a full section integral prolongation of material shall be welded, ground flush with the surface and subjected to simulated stress relief treatment in accordance with 4.4.3.1.8, After stress relief, testing shall be performed in accordance with weld procedure qualification requirements of MIL-STD-248.

3.1O Surface finish. The surface roughness of the forging shall not exceed 250 microinches roughness height rating in accordance with ANSI B46.1.

The depth of scale, pits, or other defects shall not exceed 0.015 inch (0.381 millimeters (mm)) and shall not result in an undergauge condition. Isolated, individual pits not over 0,030 inch (0.762 mm) deep or within 6 inches (150 ‘an~ Uf Lddli t3Llliii slkill be wcep~d’ble pluvided L~Ie foLgiIAg Lltickness siml.1nu~ be reduced below the specified minimum (see 4.4.3.1.2, 4.4.3:1.3.1, and 4.4.3,1.3.2).

3.11 Soundness. Sufficient discard shall be taken from each ingot to ensure freedom from pipe and undue. segregation.. Unless otherwise specified herein, the forgings shall be uniform in quality and shall not contain bursts, pipe, flakes, cracks, undue segregation, hard spots, porosity, SeaIIIS, laps, slivers, scabs, or forged in scale. Unless otherwise specified (see 6.2.1), L1;ciu~gi~~g~ SlAdAl AAO~~uL~Laillcieieccs LIAdLexceed LIIeaccepLaIwe Cxlwrid o~ appendix A.

3.12 Flame cuttir.q, Flame cutting in the bore or metal removal from the bore by thermal means is not permitted. Flame cutting or metal removal from outer surfaces by any thermal means is not permitted after heat treatment.

3.13 $tabilitv. Material shall be furnished in a stable condition to withstand, for an indefinite time, the development of external or internal cracks.

3.14 Microstructure. The microstructure shall be determined for first article (see 4.4.3.1.7). Deep acid etched forgings up to and including 36 square inches shall be equal to or better than S-3, R-2, and C-3 plates of ASTM E 381. Sizes over 36 and including 100 square inches shall be equal to or better than S-3, R-3 and C-3. For sizes in excess of 100 square inches, microstructure requirements shall be as specified (see 6,2.1).

3.15 Repair of defects.

3.15.1 Removal of defects by Erindi~

or chimzrg . Defects may be removed by grinding or chipping provided the areas involved are well flared into the surrounding areas and sufficient stock is left to allow subsequent finishing. ‘I’heareas involved shall bE magnetic particle tested in accordance ~-ithMIL-STD-271 to ensure that the defects have been completely removed.

3.15.2 RePa~r welding. Unless otherwise specified (see 6.2.1), repair welding shall not be permitted.

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3.15.3 Repair procedures. When permitted by the contracting activity (see 6.2.1), weld repair shall be performed in accordance with MIL-STD-278.

Unless otherwise specified (see 6.2.1), welding procedure and performance qualification shall be in accordance with MIL-STD-248 prior to welding.

3.16 Cleani~ and Preservation of forzing surface. Before the forgings are accepted by the contracting activity, the forging surfaces shall be descaled preserved for the specified environment and exposure duration (see 6.2.1). Markings and identification of forgings and test pieces shall be presened with a protective coating, type P-19, in accordance with MIL-P-116 to prevent corrosion so that markings shall be discernible and legible without removing the protective coating.

3.17 licable f brica tion documen t. If applicable, the fabrication document for the forgin~ shall be specified (see 6.2.1).

3.18.1 Marking. Individual forgings shall be marked with the following information order as follows:

(a) Military specification number, revision number, and alloy class, as in KIL-S-23284A-CLX.

(b) Heat or forging number (traceability code).

(c) Manufaccurec’s name, trademark or symbol.

(d) Final tempering temperature in “F as in TT XXXX F.

(e) Stress relief temperature in “F as in SR XXXX F.

(f) Drawing or die number.

3.18.2 ~re~aration for marking. Markings shall be in accordance with MIL-STD-792. Markings shall be clearly made following surface preparation by machining, grinding or polishing to assure readily discernible identification marking. Unless otherwise specified (see 6.2.1), the forgings shall be marked only in areas that will not be removed by final machining. Special ❑arkings shall be as specified (see 6.2.1).

3.18.3 MarkinP exce~tions. If all the markings in 3.18.1 cannot be applied because of size or space limitations, then permanent marking shall be applied using the order specified in 3.18.1 (abbreviations shall be permitted). If there are size or space limitations, the forgings shall be packaged (bundled or boxed) and each package shall be identified with a metal or oil proof tag securely affixed to the package. The tags shall contain all the information specified in 3.18.1.

4. QUALITY ASSUIWNCE PROVISIONS

4.1 ~esDonsibilitv for insDecti~ . Unless othemise specified in the contract or purchase order, the contractor is responsible for the performance of all inspection 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 [he ~p(+cific’afion WIIPYP s..Ich i~lsper?ifInc;alp deempd nec~’ss~r’}~1.0as:51.lre supplies and services conform to prescribed requirements.

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MIL-s-23284 A(SN)

4.1.1 ~es~onsibilitv for complian CR. All items must meet all requirements of sections 3 and 5. The inspection set forth in this specification shall become a part of the contractor’s overall inspection system or quality program. The absence of any inspection requirements in the specification shall not relieve the contractor of the responsibility of assuring that all products or supplies submitted to the Government for acceptance comply with all requirements of the contract. Sampling in quality conformance does not authorize submission of known defective material, either indicated defective

4.2 specified

(a) (b)

4.3 or actual, nor does it commit the Government to acceptance of material.

Cla ssification of inspections. The inspection requirements herein are classified as follows:

First article inspection (see 4.3).

Quality conformance inspection (see 4.4).

Fir t articls e insDection. First article inspection shall consist of all examinations and tests as specified herein.

4,3.1 First article sa~~q~, The first article sample shall consist of.-—— .—.— .

sufficient ma~erial. from one heat to obtain measurements of the notch toughness, mechanical properties of the materials, its weldability, response to stress relief, and the first article inspection.

4.3.2 First articl e insDection reDort. When specified in the contract or order, a first article inspection report shall be prepared (see 6.2.2 and appendix B).

4.4 Oualitv conform ante inspection. Quality conformance inspection shall consist of the inspections specified in 4,4.3. When specified in the contract or order, a certificate of compliance shall be prepared (see 6.2.2 and appendix C) .

4,4.1 &@.

4.4.1.1 Lot for chemical com~osition. Each heat for ingot cast and each ladle for strand cast steel.shall be a lot for chemical analysis. In the case of continuous casting, each bloom, billet or slab utilized for reforging shall be considered a lot. For remelted vacuum arc remelt or electroslag remelt products, a lot for analysis consists of the products of each remelted ingot of each melt. In the case of secondary melting or ladle refining, each charged vessel is considered a lot for heat analysis.

4.4.1.2 Lot for tensile and impact tests.

4.4.1.2.1 Forzin~s with an as heat treated weiAt of less than 1.000

QQuDLk. unless otherwise specified (see 6.2.1), all forgings Of one design, produced from the same heat or melt, and heat treated in the same furnace charge , shall constitute a lot.

4.4.1.2.2 ForziQgS with an as heat treated wei~ht of 1.000 Pounds or more . Unless otherwise specified (see 6.2.1), each forging shall constitute a lot.

1 ‘-l A .)

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4.4. 1.3 ~t for visual and dimensional test. Unless otherwise specified (see 6.2.1), each forging shall constitute a lot.

4.4.1.4 Lot for ultrasonic, xnametic ~article and dve Denetrant tests.

Unless otherwise specified (see 6,2.1), each forging shall constitute a lot.

4.4.1.5 t f’r microstructure. The lot for inicrostruccuse tests shall be as specified (se: 6.2.1).

4.4.2 Sam~ling.

4.4.2.1 Samle for chemical analvsis. One sample from a forging in each lot shall be taken for chemical analysis or in the case of propulsion shafting, one sample shall be taken from each end of the forging. If more than one heat is used for a forging, a sample shall be taken from each end of the forging and analyzed separately. In addition, when three or more heats are used for a single forging, heat analyses from each heat shall be required and shall conform to 3.4.1. Samples shall be taken at the mid-radius of solid forgings and at the mid-wall thickness of hollow forgings, near the end of the forging, usually in a prolongation. Each sample for chemical analysis shall consist of at least 2 ounces of chips and shall be free of oil, grit or other foreign matter, Solid samples shall be taken in lieu of chips when the analysis is made by the spectrographic method.

4.4,2.2 Sampl~nE for-mechanical tests, One sample from a forging in each lot shall be taken for mechanical tests. Forgings for shafts, sleeves, rudder stocks and diving plane stocks shall have one sample removed from each end of a forging in each lot. For forgings with large flanges or other enlargements , the cross-sectional area of each prolongation shall be approximately the same as the average cross -sectional area of the rough forging, exclusive of flanges or enlargements.

4,4,3 Inspection.

4.4.3.1 Tests and examinations.

4.4.3.1.1 Chemical analysis. The samples selected in accordance with

4.4.2.1 shall be analyzed in accordance with ASTM A 751 and shall conform to 3 4,

4.4.3.1.2 J)imensional ins~ection. Each forging shall be dimensionally inspected and shall conform to 3.7 and 3.10.

4.4.3.1.3 Soundness inspection.

4.4,3.1.3.1 Visual insDectioQ. Each forging shall be visually examined i~ft~r final heat trparment, stress relief, and machining. The entire foI:&iI..[, surface (including bores) shall be visually examined in accordance with MIL-STD-2’71 and shall conform to 3.10 and 3,11.

4.4.3.1.3.2 MaEnetic particle inspection. Unless othemise specified (see 6.2.1), all exterior surfaces of each forging from each lot shall be inspected in accordance with the appendix and shall conform to the acceptance criteria or shall be rejected. For~jngs shall he in the finish machined condition and shaL1.have a suit:at)le~ir~j.sll(see 3,10). When 21~!.OWe(i,defects

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4.4.3.1.3.3 Ultrasonic inspection. Forgings 3/4 inch (19 mm) or greater in section thickness shall be ultrasonically inspected in accordance with appendix A. When specified (see 6.2.1), each forging of less than 3/4-inch

(19-mm) thickness shall be ultrasonically inspected in accordance with the appendix A. Sections of forgings which exceed limits of ultrasonic examination requirements shall be repaired in accordance with 3.15.

4.4.3.1.4 fiechanical uroner~. Unless othenrise specified (see 6.2.1), each lot shall be inspected in accordance with ASTM A 370 and shall conform to

3.5. Mechanical property tests shall be performed after the final heat treating operation, including the stress relieving treatment.

4.4.3.1.5 Brinell hardness tests. Brinell hardness tests shall be conducted in accordance with ASTM E 10. The test shall be conducted subsequent to heat treatment and at least three determinations shall be conducted on each unit.

4.4.3.1.6 Grain size deterrnination~. The actual grain size of the material offered for acceptance shall be determined in accordance with ASTM E 112 and shall meet the requirements of 3.8.4.

4.4.3.1.7 I.nsDection for microstructure. The microstructure on the final forging product prolongation shall be determined and shall conform to 3,14.

4.4.3.1.8 $tress relief simulation. Material to simulate stress relief treatments shall be heat treated in accordance with the following:

(a) Sample material shall remain attached to the forging during heat treatment and shall be taken from an integral prolongation. After heat treatment, and prior to stress relief, the sample material shall be removed from the forging. Sufficient sample material shall be obtained for impact testing in the non-stress relieved condition. Impact testing in the non-stress relieved condition shall duplicate Charpy V-notch tests required for acceptance with respect to quantity, location, depth and orientation. Remaining material shall be subjected to the simulated stress relief.

(b) Simulated stress relief heat treatment of sample material shall be identical to that of production forgings in every respect. This shall include, but shall not be limited to, stress relief temperature , time at stress relief temperature, number of stress relief heating cycles, and maximum cooling rate for each cycle from the stress relief temperature.

(c) Total time at temperature for stress relief of sample material shall be equal to the total time anticipated for stress relief of the production forging.

(d) The average cooling rate for the stress relieving temperature to 600°F shall be determined and recorded. Sample material may be air cooled after the material temperature is reduced to 600°F.

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MIL-S-23284A(Sli)

4.4.3.1.8.1 Weld procedures. Welding shall be in accordance with MIL-sTD-278. Weld procedure and performance qualification shall be in accordance with MIL-STD-248.

4.4.3.1.8.1.1 Blectrodes. Low hydrogen electrodes compatible with S-1 materials for class 3 and 4 base materials and with S-llA materials for class 1, 2, 5, and 6 base materials shall be used.

4.4.3.1.8.1.2 ld Om . The weld shall be circumferential for cylindrical pieces. The weld shall conform to plate requirements for other shapes. The depth of the weld joint shall be 1 inch, or 1/2 the wall thickness of hollow forgings, or 1/2 the thickness of solid forgings, whichever is less. A weld joint design in agreement with B2J.1 of MIL-STD-22 shall be used except a maximum incline of 7 degrees shall be allowed on the non-beveled edge. Impact specimens shall be removed from the non-beveled edge.

4.4.3.1,8.1.3 Imuact specimens . Impact specimens shall be removed as near as practical to mid-depth of the weld joint. The longitudinal axis of heat affected zone specimens shall be perpendicular to the “non-beveled” (maximum bevel of 7 degrees) face of the weld joint. The notch opening shall face the free surface of the piece. They shall be polished and etched to define the heat affected zone prior to machining the notch. Coupons shall be cut in such a manner as to include as much as possible of the heat affected zone in the resulting fracture.

4.4.3.2 Test specimens.

4.4.3.2.1 Trees of specimens. The test specimens shall conform to the largest test specimens which can be produced from the test prolongation in accordance with ASTM A 370.

4.4.3.2.2 Cation of test s~ecimen s. For solid shafts, rudder stocks, diving plane stocks and propeller nuts, the specimens shall be taken at a distance from the end of the forging equal to at least the radius. For hollow forgings, the specimens shall be taken at a distance from the end of the forging equal to at least the wall thickness.

4.4.3.2.3 n~itudinal test sDeclulem

. Longitudinal test specimens shall be taken from a full-size prolongation of the forging in the direction in which the material is most drawn.

4.4.3.2.4 ‘Jsansverse Lest s~ecimens. Transverse test specimens shall be taken from a full-size prolongation of the forging in the direction perpendicular to which the metal is most drawn. When it is impractical to obtain transverse test specimens, longitudinal test specimens shall be taken from the appropriate locations.

4.4.3.2.5 Tensile specimens. In the case of shafts, stocks, sleeves, and couplings, tensile specimens shall be taken from each end of each forging.

For solid shafts or stocks, the specimens shall be taken as shown on figure 1.

For hollow shafts or stocks, the specimens shall be taken as shown on figure

2. For couplings and sleeves, the specimens shall be taken as show on figure 3, For propeller nuts, the specimens shall be taken as shorn on figure 4.

1.6 v

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MIL-S-232B4A(SH)

4.4.3.2.6 Microstructure s~ecimens. The microstructure test specimens shall be in accordance wi~h ASTM E 381.

4.4.3.2.7 Charpy V-notch s~ecimens. For shafts, stocks and sleeves, a group of three Charpy V-notch specimens shall be taken from each end of each forging for each test temperature, Other forgings shall have a group of three charpy V-notch specimens removed from one end of the forging. Specimens shall be taken at mid-radius for solid forgings and at mid-wall thickness for hollow forgings (see figures 1, 2, 3, and 4). Specimen and notch position shall be in accordance with the C-L orientation of ASTM E 616 for the crack plane orientation code for bars and hollow cylinders.

4.4.3.2.8 ~rinell hardness determination. At least three hardness test determinations on the outside diameter spaced 120 degrees apart shall be made on each forging in an area representing the heaviest section of each forging wilicl~is LO subsequently be mac-nined.

4.4.3.2.9 Grain size determination. Two cross-sectional grain size specimens shall be obtained from undeformed ends of two broken mechanical property acceptance test specimens from each lot and tested. When a lot consists of more than one forging the two specimens (mid-wall or mid-radius specimens) shall be obtained from different forgings. For those forgings with test areas provided on each end of the forging, one specimen shall be obtainecl from each test area of two forgings in the lot or from one forging if the lot uonsiscs of one forging. At the option of the contractor, samples may be taken from material adjacent to the acceptance mechanical property specimens in lieu of samples taken from broken mechanical property acceptance test specimens.

4.4.3.2.10 Macroscopic etch snecimens. Cross-sectional specimens for the macroscopic etch test shall.cor.sist of material. approximately l,t2-ir.ch thick cut from each end of the forging and subject to a hot acid etch.

4.4.3.2.11 Micro scoDic specimens. One or more cross-sectional specimens shall be taken from each location where a tensile specimen is taken.

When a broken tensile or Charpy impact specimen is used for this test, the microscopic specimen shall be taken from the unbroken end of the specimen.

4.4.3.2.12 Nonmetallic inclusion content specimens. One longitudinal specimen shall be taken from each end of each hollow forging as shown i.n figure 5. The specimen shall be removed a minimum of l-inch below the outside surface. In the case of propeller nuts and couplings, only one specimen shall be taken.

4.4.3.2.13 S~ecimens reauired when multiDle Darts are forzed from one

w. When multiple parts are made and heat treated as one forging, both ends of the forging shall be sampled, Location and number of specimens f-or tlic!sampling required !;hall1:)6:g<)ver”n(!(jby the largest: or pri.ncipdl t(>I”lJ,in~,s of the combined farging. Tests will not be required for the individual pieces when tests are made on the forging as a whole.

4.5 Resubmittal of re~ected for~in~s or lots.

A

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Retests shall be allowed and shall be in accordance with this section.

4.5.2 Identification and separation of reiected lots. The contractor shall keep rejected lots identified and separate from acceptable lots until the rejected lots are withdrawn by the contractor or demonstrated as meeting specification requirements.

4.5.3 ~eiected for~s or lots . A rejected forging or lot shall be resubmitted for acceptance testing at the contractor’s option provided the forging or forging lot is reworked, reheat treated, or retempered to COrreCt the nonconforming condition and reinspected to all applicable requirements of this specification at the contractor’s expense.

4.5.4 Reiection if more than one viece. When a rejected lot consists of more tlmr.onc piccc, each remaining piccc in the lot other than the noncon-forming piece may be tested for the nonconforming characteristic and each piece that conforms to specification requirements shall be offered for acceptance.

4.5.5 Retests (tensile test). One retest shall be permitted if any test characteristic fails to meet specification requirements.

4.5.6 ~etests (Char~v impact~. One retest of three new specimens shall be permitted if the average vaiue of :he three initial specimens equals or exceeds 25 foot-pounds at 10”F for class 1 or class 2, or equals or exceeds 15 foot-pounds at 28°F for classes 3 and 4, or equals or exceeds 30 foot-pounds at minus 35°F for classes 5 and 6. The values of each of the retest specimens shall equal or exceed the required average values.

4.5.7 Retests (defective materials~. If results of mechanical tests do not conform to the specified requirements because a flaw is found in the specimen during testing, a retest may be allowed if the defect is not caused by ruptures, cracks, or flakes in the steel.

4$6 ~. S’mpl’ packs? and ‘he inspectionof‘he presentation, packing and marking for shipment, stowage and storage shall be in accordance with the requirements of section 5 and the documents specified therein,

5. PACKAGING

5.1 General.

5.1.1 Naw fire-retardant requirements.

a. ‘heated lumber and Plvwood. When specified (see 6.2.1), all lumber and plywood including laminated veneer material used in shipping container and pallet construction, members, blocking, bracing, and reinforcing shall be fire-retardant treated material conforming to MIL-L-19140 as follows:

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Levels A and B - Type 11 - weather resistant.

Category 1 - general use.

Level C - Type 1 - non-weather resistant.

Category 1 - general use.

5.2 preservation. Preservation shall be level A or commercial as specified (see 6.2.1).

5.2.1 @vel A.

5.2,1.1 Presentation application. Machined or finished surfaces of forgings shall be protected with an application of preservative conforming to grade 1 or grade 4 of MIL-C-16173.

5.2,1,2 ~rau. Forgings without presemation application, shall be individually wrapped with a minimum of two thicknesses of 40-pound basic weight kraft paper. Forgings with preservative application, two thicknesses of equal weight greaseproof paper shall be used for wrapping. When complete wraping is not pratical because of configuration, size or weight, the finished or polished surface(s) shall be provided protection from damage with suitable covers. When specified (see 6.2.1), the kraft paper shall be fire resistant meeting the requirements of A-A.-1894.

5 9 9 ~~~er~+a~..&.& Unless otherwise Gpccified (see 6.2.1), commercial preservation (packaging) shall be in accordance with the requirements for “castings” of ASTM A 700, section 14.

5.3 Packing. Packing shall be level A, B, C, or commercial as specified (see 6.2.1).

5.3.1 General requirements for Ievels A. B. and C. Shipping containers selected (see 5.3.2) shall be of minimum weight and cube of uniform size and construction, and contain identical quantities of identical forgings of one size, melt or lot number. Forgings that are packed into containers shall be blocked, braced or otherwise secured to prevent their movement and damage.

Forging having projections that may be damaged during handling, shipment and storage shall have the projections protected with batten strips.

5.3.2 Levels A. B. and C containers. Forgings shall be packed in nailed wood, wood cleated plywood or wirebound boxes, or in open or covered wood or wirebound crates as specified in MIL-STD-2073-lA, Appendix C for the level of packing specified (see 5.3) and herein. Unless otherwise specified (see 6.2.1), containers selection shall be at the option of the supplier.

5.3,2.1 Packin~a uantitv and weizht.

5.3.2.1.1 ~mall. fow (fini.shedor nolish ed and other>. Forgings weighing less than 200 pounds shall be packed individually, or in multiple units in boxes (see 5.3.2). Unless otherwise specified (see 6.2.1), the gross weight of boxes shall not exceed 500 pounds. Boxes exceeding 100 pounds shall be modified with skids in accordance with the applicable box specification.

%mll for~.ggs...glgb.?.r-)-)..5.3,2 1 1.1 k_......_...-._-._ For:ings, in lieu of boxing, mav be bundled for shipment, unless by so doing the forgings may be subject to damage . Bundles shall be secured or reinforced with tensioned steel strapping

--s . . --------

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5.3.2.1.2 Lar~e f.or~in~. Forgings weighing more than 500 pounds shill-l be packed individually, or in multiple units in crates (see 5.3.2). Unless otherwise specified (see 6.2.1), the gross weight of crates shall not exceed 1000 pounds. Open type crates shall be provided with flexible, reinforced, waterproof, barrier material shrouds. Plastic shrouds shall be of minimum

0.006 inch thickness. Shrouds shall be secured to prevent damage and loss during handling, shipment and storage.

5.3.3 Comxnercial. Unless otherwise specified (see 6.2.1), commercial packing (packaging) shall be in accordance with the requirements for ‘castings” in ASTM A 700, section 14 and herein.

5.3.3.1 Container modification. Shipping containers exceeding 100 pounds gross weight shall be provided with a minimum of two, 3- by 4-inch nominal wood skids laid flat, or a skid- or still-type base which will support the material and facilitate handling by mechanical handling equipment during shipment , srowa~e and stot-a~~

S.fiMarking.

5.4.1 J#evels A. 3. and c Irladditior~ to any special Larking required (see 6.2.1), 3.18 and herein, interior (unit) packs, shipping containers and bundles shall be marked including bar coding in accordance wtih MIL-STD-2073- 1.A.

5.4.2 Commercial. In addition to any special marking required (see 6.2,1), 3.18 and herein and unless otherwise specified (see 6.2.1), marking shall be in accordance with the requirements for “castings” in ASTM A 700, section 14. Bar coding in accordance with MIL-STD-2073-1A shall apply.”

6. NOTES

6.1 Jntended IJst?, The six classes of steel are used to make torsional shafts, shafts for ships, sleeves, couplings, propeller nuts, rudder stocks, diving plane stocks, and related parts.

6.2 grderi.n~ data.

6.2,1 ~cauisition zeauiremen~s, Acquisi~ion documents should specify the following:

(a) Title, number, and date of this specification.

(b) The class of steel required (see 1.2).

(c) When first article inspection is required (see 3.1).

(d) Melting practices, if other than specified (see 3.2).

(e) When vacuum degassing is not required…