2.3Low-Alloy Steels (AISI Grades and Proprietary Grades)

2.3.0.1

Metallurgical Considerations — The AISI or SAE alloy steels contain, in addition to carbon, up to about 1 percent (up to 0.5 percent for most airframe applications) additions of various alloying elements to improve their strength, depth of hardening, toughness, or other properties of interest. Generally, alloy steels have better strength-to-weight ratios than carbon steels and are somewhat higher in cost on a weight, but not necessarily strength, basis. Their applications in airframes include landing-gear components, shafts, gears, and other parts requiring high strength, through hardening, or toughness.

Some alloy steels are identified by the AISI four-digit system of numbers. The first two digits indicate the alloy group and the last two the approximate carbon content in hundredths of a percent. The alloying elements used in these steels include manganese, silicon, nickel, chromium, molybdenum, vanadium, and boron. Other steels in this section are proprietary steels which may be modifications of the AISI grades. The alloying additions in these steels may provide deeper hardening, higher strength and toughness.

These steels are available in a variety of finish conditions, ranging from hot- or cold-rolled to quenched-and-tempered. They are generally heat treated before use to develop the desired properties. Some steels in this group are carburized, then heat treated to produce a combination of high surface hardness and good core toughness.

2.3.0.2 Manufacturing Conditions

Forging — The alloy steels are only slightly more difficult to forge than carbon steels. However, maximum recommended forging temperatures are generally about 50°F lower than for carbon steels of the same carbon content. Slower heating rates, shorter soaking period, and slower cooling rates are also required for alloy steels.

Cold Forming — The alloy steels are usually formed in the annealed condition. Their formability depends mainly on the carbon content and is generally slightly poorer than for unalloyed steels of the same carbon content. Little cold forming is done on these steels in the heat-treated condition because of their high strength and limited ductility.

Machining — The alloy steels are generally harder than unalloyed steels of the same carbon content. As a consequence, the low-carbon alloy steels are somewhat easier to finish machine than their counterparts in the carbon steels. It is usually desirable to finish machine the carburizing and through-hardening grades in the final heat-treated condition for better dimensional accuracy. This often leads to two steps in machining: rough machining in the annealed or hot-finished condition, then finish machining after heat treating. The latter operation, because of the relatively high hardness of the material, necessitates the use of sharp, well-designed, high-speed steel cutting tools, proper feeds, speeds, and a generous supply of coolant. Medium- and high-carbon grades are usually spheroidized for optimum machinability and, after heat treatment, may be finished by grinding. Many of the alloy steels are available with added sulfur or lead for improved machinability. However, resulfurized and leaded steels are not recommended for highly stressed aircraft and missile parts, because of drastic reductions in transverse properties.

Welding — The low-carbon grades are readily welded or brazed by all techniques. Alloy welding rods comparable in strength to the base metal are used, and moderate preheating (200 to 600 °F) is usually necessary. At higher carbon levels, higher preheating temperatures, and often postwelding stress relieving, are required. Certain alloy steels can be welded without loss of strength in the heat-affected zone provided that the welding heat input is carefully controlled. If the composition and strength level are such that the strength of the welded joint is reduced, the strength of the joint may be restored by heat treatment after welding.

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2.3.0.2 Maximum Round Diameters for Low-Alloy Steel Bars (Through Hardening to at Least

2.3.0.2.5

"Heat Treating," ASM Handbook, Volume 4, 1991.

• 2.3.1.3.8(a) Brodrick, R. F., and Rich, E. L., "Evaluation of the Fatigue Properties of SAE 4340. Thermold J, and Tricent Steel Under Axial Loading Conditions," Technical Report No. 588/c39, Lessells and Associates (July 30, 1958) (MCIC 109748).
• 2.3.1.3.8(b) Trapp, W. J., "Elevated Temperature Fatigue Properties of SAE 4340 Steel," WADC TR 52-325, Part I (December 1952).
• 2.3.1.3.8(c) Oberg, T. T., and Ward, E. J., "Fatigue of Alloy Steels at High Stress Levels," Wright Air Dev. Center TR 53-256 (October 1953) (MCIC 108310).
• 2.3.1.3.8(d) Thrash, C. V., "Evaluation of High Strength Steels for Heavy Section Applications," Douglas Aircraft Engineering TR No. LB-32437 (November 29, 1965) (MCIC 70834).
• 2.3.1.4.8(a) Deel, O. L., and Mindlin, H., "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252 (October 1970) (MCIC 79662).
• 2.3.1.4.8(b) Bateh, E. J., "300M Steel Fatigue Program Structural Requirements," Lockheed-Georgia Report No. 72-26-591 (January 5, 1967) (MCIC 74342).
• 2.3.1.4.8(c) Harmsworth, C. L., "Low Cycle Fatigue Evaluation of Titanium 6Al-6V-2Sn and 300-M Steel for Landing Gear Applications," AFML-TR-69-48 (June 1969) (MCIC 75621).
• 2.3.1.4.8(d) Thrash, C. V., "Evaluation of High Strength Steels for DC-10," Douglas Aircraft Company Report No. ETR-DAC-67520 (May 27, 1969) (MCIC 110145).
• 2.3.1.4.8(e) Boswell, L. E., et al., "Fatigue Test for Landing Gear Material 300M Forgings," Vought Corporation Report No. 70-59910-047 (May 22, 1970) (MIL-HDBK-5 Source M-74).
• 2.3.1.4.9(a) Dill, D. H., "Evaluation of Steel Alloys 300M, HP-9Ni-4Co-0.20, HP-9Ni-4Co-0.30, and PH13-8Mo," Report MDC-A2639, McDonnell Aircraft Co., McDonnell Douglas Corp. (December 21, 1973) (MCIC 88136).
• 2.3.1.4.9(b) "B-1 Program da/dN Data for Steel Alloys," Rockwell International Corp., Memorandum to N. D. Moran from E. W. Cawthorne, Battelle, Columbus, Ohio (April 3, 1974) (MCIC 88579).

2.3.0.3

Environmental Considerations — Alloy steels containing chromium or high percentages of silicon have somewhat better oxidation resistance than the carbon or other alloy steels. Elevated-temperature strength for the alloy steels is also higher than that of corresponding carbon steels. The mechanical properties of all alloy steels in the heat-treated condition are affected by extended exposure to temperatures near or above the temperature at which they were tempered. The limiting temperatures to which each alloy may be exposed for no longer than approximately 1 hour per inch of thickness or approximately one-half hour for thicknesses under one-half inch without a reduction in strength occurring are listed in Table 2.3.0.3. These values are approximately 100°F below typical tempering temperatures used to achieve the designated strength levels.

• a Quenched and tempered to $F_{u}$ indicated. If the material is exposed to temperatures exceeding those listed, a reduction in strength is likely to occur.

Low-alloy steels may undergo a transition from ductile to brittle behavior at low temperatures. This transition temperature varies widely for different alloys. Caution should be exercised in the application of low-alloy steels at temperatures below -100°F. For use at a temperature below -100°F, an alloy with a transition temperature below the service temperature should be selected. For low temperatures, the steel should be heat treated to a tempered martensitic condition for maximum toughness.

Heat-treated alloy steels have better notch toughness than carbon steels at equivalent strength levels. The decrease in notch toughness is less pronounced and occurs at lower temperatures. Heat-treated alloy steels may be useful for subzero applications, depending on their alloy content and heat treatment. Heat treating to strength levels higher than 150 ksi $F_{y}$ may decrease notch toughness.

The corrosion properties of the AISI alloy steels are comparable to the plain carbon steels.

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2.3.1.0

Comments and Properties — AISI 4130 is a chromium-molybdenum steel that is in general use due to its well-established heat-treating practices and processing techniques. It is available in all sizes of sheet, plate, and tubing. Bar stock of this material is also used for small forgings under one-half inch in thickness. AISI 4135, a slightly higher carbon version of AISI 4130, is available in sheet, plate, and tubing.

AISI 4140 is a chromium-molybdenum steel that can be heat treated in thicker sections and to higher strength levels than AISI 4130. This steel is generally used for structural machined and forged parts one-half inch and over in thickness. It can be welded but it is more difficult to weld than the lower carbon grade AISI 4130.

AISI 4340 is a nickel-chromium-molybdenum steel that can be heat treated in thicker sections and to higher strength levels than AISI 4140.

AISI 8630, 8735, and 8740 are nickel-chromium-molybdenum steels that are considered alternates to AISI 4130, 4135, and 4140, respectively.

There are a number of steels available with compositions that represent modifications to the AISI grades described above. Four of the steels that have been used rather extensively at $F_{u}=220 \mathrm{ksi}$ are D6AC, Hy-Tuf, 4330V, and 4335V. It should be noted that this strength level is not used for AISI 4340 due to embrittlement encountered during tempering in the range of 500 to $700^{\circ} \mathrm{F}$. In addition, AISI 4340 and 300M are utilized at strength levels of $F_{u}=260 \mathrm{ksi}$ or higher. The alloys, AISI 4340, D6AC, 4330V, 4335V, and 300M, are available in the consumable electrode melted grade. Material specifications for these steels are presented in Tables 2.3.1.0(a) and (b).

The room-temperature mechanical and physical properties for these steels are presented in Tables 2.3.1.0(c) through 2.3.1.0(g). Mechanical properties for heat-treated materials are valid only for steel heat treated to produce a quenched structure containing 90 percent or more martensite at the center. Figure 2.3.1.0 contains elevated temperature curves for the physical properties of AISI 4130 and AISI 4340 steels.

2.3.1.1

AISI Low-Alloy Steels — Elevated temperature curves for heat-treated AISI low-alloy steels are presented in Figures 2.3.1.1.1 through 2.3.1.1.4. These curves are considered valid for each of these steels in each heat-treated condition but only up to the maximum temperatures listed in Table 2.3.0.1(b).

2.3.1.2

AISI 4130 and 8630 Steels — Typical stress-strain and tangent-modulus curves for AISI 8630 are shown in Figures 2.3.1.2.6(a) through (c). Best-fit S/N curves for AISI 4130 steel are presented in Figures 2.3.1.2.8(a) through (h).

2.3.1.3

AISI 4340 Steel — Typical stress-strain and tangent-modulus curves for AISI 4340 are shown in Figures 2.3.1.3.6(a) through (c). Typical biaxial stress-strain curves and yield-stress envelopes for AISI 4340 alloy steel are presented in Figures 2.3.1.3.6(d) through (g). Best-fit S/N curves for AISI 4340 are presented in Figures 2.3.1.3.8(a) through (o).

2.3.1.4

300M Steel — Best-fit S/N curves for 300M steel are presented in Figures 2.3.1.4.8(a) through (d). Fatigue-crack-propagation data for 300M are shown in Figure 2.3.1.4.9.

2.3.1.5

D6AC Steel — Fatigue-crack-propagation data for D6AC steel are presented in Figure 2.3.1.5.9.

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2.3.1.5.9

Feddersen, C. E., et al., "Crack Behavior in D6AC Steel," Report MCIC 72-04, Battelle, Columbus, Ohio (January 1972).