V11 航空与航天用金属铸锻材料 标准查询与下载

SAE AMS6424F-2012 0.80Cr 1.8Ni 0.25Mo (0.49-0.55C)钢筋,锻件和管材

This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. These products have been used primarily for parts 3.5 in. (90 mm) and under in nominal section-thickness at time of heat treatment requiring a through-hardening steel capable of developing hardness as high as 40 HRC and also parts with thicker cross-section which require proportionately lower hardness, but usage is not limited to such applications.

Steel Bars, Forgings, and Tubing 0.80Cr 1.8Ni 0.25Mo (0.49-0.55C)

SAE AMS6317J-2012 125 ksi (862 MPa)拉力强度1.8Ni 0.25Mo (0.38-0.43C) (4640)热处理钢棒材和铸件

This specification covers an aircraft-quality, low-alloy steel in the form of heat treated bars and forgings. These products have been used typically for parts with sections 1.0 inch (25 mm) and under in nominal thickness requiring a minimum tensile strength of 125 ksi (862 MPa), but usage is not limited to such applications.

Steel Bars and Forgings 1.8Ni 0.25Mo (0.38-0.43C) (4640) Heat Treated, 125 ksi (862 MPa) Tensile Strength

SAE AMS6280L-2012 0.50Cr 0.55Ni 0.20Mo (0.28-0.33C)钢棒材,铸件和环材(SAE 8630)

This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, flash welded rings, and stock for forging or flash welded rings. These products have been used typically for parts with sections 0.500 inch (12.70 mm) and under in thickness at the time of heat treatment, requiring a through-hardening steel capable of developing hardness as high as 35 HRC when properly hardened and tempered and also parts of greater thickness but requiring proportionately lower hardness, but usage is not limited to such applications.

Steel Bars, Forgings, and Rings 0.50Cr 0.55Ni 0.20Mo (0.28-0.33C) (SAE 8630)

SAE AMS6330H-2012 0.65Cr 1.25Ni (0.33-0.38C)钢棒材,铸件和管材

This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. These products have been used typically for parts 0.750 inch (19.05 mm) and under in nominal section thickness at time of heat treatment requiring a through-hardening steel capable of developing minimum tensile strength of 180 ksi (1241 MPa) at the section center when properly hardened and tempered and for parts of greater section thickness but requiring proportionately lower strength, but usage is not limited to such applications.

Steel Bars, Forgings, and Tubing 0.65Cr 1.25Ni (0.33-0.38C)

SAE AMS2280C-2012 痕量元素控制,镍合金铸件

This specification establishes maximum permissible limits for trace elements in nickel alloy castings. These products have been used typically for limited use to achieve premium-quality material for highly-stressed rotating parts, such as turbine blades, where control of trace elements is required to maintain elevated-temperature tensile, stress-rupture, creep, and low-cycle fatigue properties, but usage is not limited to such applications.

Trace Element Control, Nickel Alloy Castings

DIN EN 3464:2012 航空航天系列.6 mm

BS EN 4500-001:2012 航空航天系列. 金属材料. 材料标准的起草和表述规则. 一般规则

Aerospace series. Metallic materials. Rules for drafting and presentation of material standards. General rules

BS EN 4500-004:2012 航空航天系列. 金属材料. 材料标准制定和表述规则. 钛和钛合金特定规则

Aerospace series. Metallic materials. Rules for drafting and presentation of material standards. Specific rules for titanium and titanium alloys

BS EN 4500-005:2012 航空航天系列. 金属材料. 材料标准的起草和表述规则. 钢材特殊规则

Aerospace series. Metallic materials. Rules for drafting and presentation of material standards. Specific rules for steels

BS EN 4050-1:2012 航空航天系列. 金属材料的试验方法. 棒材, 板材, 锻坯和锻件的超声波检查. 一般要求

Aerospace series. Test method for metallic materials. Ultrasonic inspection of bars, plates, forging stock and forgings. General requirements

BS EN 4500-003:2012 航空航天系列. 金属材料. 材料标准的起草和表述规则. 耐热合金特殊规则

Aerospace series. Metallic materials. Rules for drafting and presentation of material standards. Specific rules for heat resisting alloys

BS EN 4050-2:2012 航空航天系列 金属材料试验方法 棒材、板材、锻坯和锻件的超声波检查 性能试验

Aerospace series. Test method for metallic materials. Ultrasonic inspection of bars, plates, forging stock and forgings. Performance of test

SAE AMS4232C-2012 溶液热处理、冷加工及沉淀热处理的铝合金挤压型材2.7Cu 2.2Li 0.12Zr (2090-T86)

This specification covers an aluminum alloy in the form of extruded bars, rods, and profiles. These extrusions have been used typically for parts in structural applications requiring strength similar to 7050-T6 alloy with good exfoliation resistance and with a lower density of approximately 7.8%, but usage is not limited to such applications.

Aluminum Alloy Extrusion 2.7Cu 2.2Li 0.12Zr (2090-T86) Solution Heat Treated, Cold Worked, and Precipitation Heat Treated

SAE AMS4917H-2012 溶液热处理的钛合金薄板材、带材和板材13.5V 11Cr 3.0Al

This specification covers a titanium alloy in the form of sheet, strip, and plate through 4.00 inches (101.6 mm).. This material has been used typically for parts to be formed in the solution heat treated condition and subsequently precipitation heat treated, requiring high strength-to-weight ratio and stability up to 550 °F (288 °C) in the precipitation heat treated conditions, but usage is not limited to such applications. This alloy may have poor crack propagation resistance in the precipitation heat treated condition. Certain processing procedures and service conditions may cause these products to become subject to stress-corrosion cracking; ARP982 reco

Titanium Alloy Sheet, Strip, and Plate 13.5V 11Cr 3.0Al Solution Heat Treated

SAE AMS4474-2012 溶液热处理、冷加工和人工老化的铝合金薄板材4.0Cu 1.0Li 0.40Mg 0.35Ag 0.13Zr (2195-T8)

This specification covers an aluminum alloy in the form of sheet and plate.

Aluminum Alloy, sheet 4.0Cu 1.0Li 0.40Mg 0.35Ag 0.13Zr (2195-T8) Solution Heat Treated, Cold Worked, and Artificially Aged

SAE AMS2774D-2012 热处理锻造镍合金和钴合金零件

This specification specifies the engineering requirements for heat treatment, by part fabricators (users) or their vendors or subcontractors, of parts made of wrought nickel or cobalt alloys, of raw materials during fabrication, and of fabricated assemblies in which wrought nickel or cobalt alloys are the primary structural components.

Heat Treatment Wrought Nickel Alloy and Cobalt Alloy Parts

SAE AMS2261K-2012 镍、镍合金和钴合金条材、棒材及线材的公差

This specification covers established manufacturing tolerances applicable to bars, rods, and wire of nickel, nickel alloy, and cobalt alloys ordered to inch-pound dimensions. These tolerances apply to all conditions, unless otherwise noted. The term "excl" is used to apply only to the higher figure of a specified range. Where the terms "nickel", "nickel-copper", "nickel-chromium", "nickel-molybdenum", "nickel-molybdenum-chromium", and "cobalt" are used without qualification, they refer to both non-heat-treatable and heat-treatable alloys as applicable, unless otherwise noted.

Tolerances, Nickel, Nickel Alloy, and Cobalt Alloy, Bars, Rods, and Wire

SAE AMS6327K-2012 热处理,抗拉强度125 ksi (862 MPa)0.50Cr 0.55Ni 0.25Mo (0.38 0.43C) (SAE 8740)钢筋和钢锻件

This specification covers an aircraft-quality, low-alloy steel in the form of bars and forgings. These products have been used typically for parts, such as nuts, bolts, and screws, 1.50 inch (38.1 mm) and under in section thickness, requiring a minimum tensile strength of 125 ksi (862 MPa) but usage is not limited to such applications.

Steel Bars and Forgings 0.50Cr 0.55Ni 0.25Mo (0.38 0.43C) (SAE 8740) Heat Treated, 125 ksi (862 MPa) Tensile Strength

SAE AMS6328M-2012 0.50Cr 0.55Ni 0.25Mo (0.48 0.53C) (8750)钢筋、铸件和管件

This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. These products have been used typically for parts 0.80 inch (20.3 mm) and under in nominal section thickness at time of heat treatment requiring a through-hardening steel capable of developing hardness as high as 50 HRC when properly hardened and tempered and for parts of greater thickness but requiring proportionally lower hardness, but usage is not limited to such applications.

Steel Bars, Forgings, and Tubing 0.50Cr 0.55Ni 0.25Mo (0.48 0.53C) (8750)

SAE AMS4416A-2012 2.9Cu-1.7Li-0.4Mg-0.4Ag-0.10Zr溶解热处理,使用拉伸和人工老化应力释放的铝合金挤压轮廓(2196-T8511)

This specification covers an aluminum-lithium alloy in the form of extruded profiles. These extrusions have been used typically for machined parts requiring dimensional stability during machining processes, and high strength, but usage is not limited to such applications. Certain processing procedures may cause this product to become susceptible to stress-corrosion cracking; ARP823 recommends practices to minimize such conditions.

Aluminum Alloy, Extruded Profiles (2196-T8511) 2.9Cu 1.7Li 0.4Ag 0.10Zr Solution Heat Treated, Stress Relieved by Stretching and Artificially Aged