AU744335B2

AU744335B2 - Leadless free-cutting copper alloy

Info

Publication number: AU744335B2
Application number: AU10541/99A
Authority: AU
Inventors: Keiichiro Oishi
Original assignee: Sambo Copper Alloy Co Ltd
Current assignee: Mitsubishi Shindoh Co Ltd
Priority date: 1998-10-12
Filing date: 1998-11-16
Publication date: 2002-02-21
Anticipated expiration: 2018-11-16
Also published as: EP1600517A3; EP1045041A4; JP2000119775A; DE69832097T2; AU1054199A; DE69832097D1; EP1600516A2; EP1600517A2; EP1045041B1; EP1559802A1; DE69838115T2; EP1600516B1; TW421674B; DE69838115D1; EP1600516A3; EP1600517B1; EP1045041A1; JP3734372B2; EP1600515B1; EP1600515B8

Description

VERIFIED TRANSLATION OF PCT TITLE OF THE INVENTION LEAD-FREE FREE-CUTTING COPPER ALLOYS BACKGROUND OF THE INVENTION 1. Field of The Invention The present invention relates to lead-free free-cutting copofe W 2. Prior Art Among the copper alloys with a good machinability are bronze alloys such as that having the JIS designation H5111 BC6 and brass alloys such as those having the JIS designations l13250-C3604 and 03771. These alloys are enhanced in machinability by the addition of 1.0 to 6.0 percent, by weight, of lead, and provide an industrially satisfactory machinability. Because of their excellent machinability, those lead-contained copper alloys have been an important basic material for a variety of articles such as city water faucets, water supply/drainage metal fittings and valves.

However, the application of those lead-mixed alloys has been greatly limited in recent years, because lead contained therein is an environmental pollutant harmful to humans. That is, the lead-contained alloys pose a threat to human health and environmental hygiene because lead is contained in metallic vapor that is generated in the steps of processing those alloys at high temperatures, such as in melting and casting operations. There is also a concern that lead contained in water system metal fittings, valves, and other components made of those alloys will dissolve out into drinking water.

On that ground, the United States and other advanced countries have been moving to tighten the standards for lead-contained copper alloys, drastically limiting the permissible level of lead in copper alloys in recent years.

In Japan, too, the use of lead-contained alloys has been increasingly ~St -t PAWPD0CS\Sp-c\7481530pgs.do.- 4112/01 restricted, and there has been a growing call for development of free-cutting copper alloys with a low lead content.

SUMMARY OF THE INVENTION The present invention seeks to provide a lead-free copper alloy which does not contain the machinability-improving element lead, yet is quite excellent in machinability and can be used a safe substitute for the conventional free cutting (easy-to-cut) copper alloy that has a high lead content, with concomitant environmental hygienic problems. The lead-free copper alloy of the present invention also permit recycling of chips without problems. Thus, the present invention presents a timely answer to the mounting call for restriction of leadcontaining products.

The present invention further seeks to provide a lead-free copper alloy that has hight corrosion resistance as well as excellent machinability, and is suitable as basic material for cutting works, forgings, castings, and other applications, thus having a very hight practical value. The cutting works, forgings, castings, and other applications include city water faucets, water supply/drainage metal fittings, valves, stems, hot water supply pipe fittings, shaft and heat exchanger parts.

The present invention still further provides a lead-free copper alloy with high strength and wear resistance as well as machinability. This lead-free copper alloy is suitable as basic material for the manufacture of cutting works, forgings, castings, and other uses requiring high strength and wear resistance such as, for example, bearings, bolts, nuts, bushes, gears, sewing machine parts, and hydraulic system parts. Hence, this embodiment of the present invention has a very high practical value.

The present invention further provides a lead-free copper alloy with excellent high-temperature oxidation resistance as well as machinability, which alloy is suitable as basic material for the manufacture of cutting works, forgings, castings, and other uses where high thermal oxidation resistance is essential, e.g., nozzels for kerosene oil and gas heaters, burner heads, and gas nozzles for hotwater dispensers. Hence, this embodiment of the present invention too has very -2- PA\WPD0CS"0Swm%74 91530pgsgd 14/1 VO I high practical value.

The copper alloys of the present invention are as follows: 1. A lead-free free-cutting copper alloy with an excellent machinability, which is composed of 69 to 79 percent, by weight, of copper, 2.0 to 4.0 percent, by weight, of silicon, and the remaining percent, by weight, of zinc. For purpose of simplicity, this copper alloy will be hereinafter called the "first invention alloy." In a preferred embodiment of the first invention alloy as claimed there is provided a lead-free free-cutting copper alloy which comprises 71 to 76 percent, by weight, of copper; 2.4 to 3.7 percent, by weight, of silicon; and the remaining percent, by weight, of zinc.

Lead does not form a solid solution in the matrix but instead disperses in a granular form to improve the machinability of an alloy. Silicon enhances the easy-to-cut property of an alloy by producing a gamma phase (in some cases, a kappa phase) in the structure of metal. That way, both act to improve alloy machinability, though they are quite different in their respective contributions to the properties of the alloy. On the basis of that recognition, silicon is added to the first invention alloy in place of lead so as to bring about a high level of machinability meeting industrial requirements. That is, the first invention alloy is improved in machinability through formation of a gamma phase with the addition of silicon.

The addition of less than 2.0 percent, by weight, of silicon cannot form a gamma phase sufficient to provide industrially satisfactory machinability.

With increases above 2.0 weight-percent in the addition of silicon, the machinability improves. But with the addition of more than 4.0 percent, by weight, of silicon, the machinability will not improve proportionally. A problem is, however, that silicon has a high melting point and a low specific gravity and is also liable to oxidize. If silicon alone is fed in a simple substance into a furnace in an alloy melting step, silicon will float on the molten metal and be oxidized into oxides of silicon (or silicon oxide), hampering production of a -3- $~vruw,. silicon-containing copper alloy. In making an ingot of silicon-containing copper alloy, therefore, silicon is usually added in the form of a Cu-Si alloy, which boosts the production cost. In the light of the cost of making the alloy, too, it is not desirable to add silicon in a quantity exceeding the saturation point where machinability improvement levels off, 4.0 percent by weight.

Experimentation has shown that when silicon is added in an amount of 2.0 to percent, by weight, it is desirable to hold the content of copper to 69 to 79 percent, by weight, in consideration of its relation to the content of zinc in order to maintain the intrinsic properties of the Cu-Zn alloy. For this reason, the first invention alloy is composed of 69 to 79 percent, by weight, of copper and 2.0 to 4.0 percent, by weight, of silicon. The addition of silicon improves not only the machinability but also the flow of the molten metal in casting, strength, wear resistance, resistance to stress corrosion cracking, hightemperature oxidation resistance. Also, the ductility and dezincification resistance will be improved to some extent.

2. A lead-free free-cutting copper alloy, also with an excellent machinability, which is composed of 69 to 79 percent, by weight, of copper; to 4.0 percent, by weight, of silicon; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. This second copper alloy will be hereinafter called the "second invention alloy." That is, the second invention alloy is composed of the first invention alloy and at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium.

Bismuth, tellurium, and selenium, like lead, do not form a solid solution in the matrix but disperse in granular form to enhance machinability through a mechanism different from that of silicon. Hence, the addition of those elements along with silicon could further improve the machinability beyond the level obtained by the addition of silicon alone. From this finding, the second invention alloy is provided in which at least one element selected from among bismuth, tellurium, and selenium is mixed to further improve the machinability obtained by the first invention alloy. The addition of bismuth, tellurium, or selenium in addition to silicon produces a high machinability such that complicated forms can be freely cut at a high speed. But no improvement in machinability can be realized from the addition of bismuth, tellurium, or selenium in an amount less than 0.02 percent, by weight. However, those elements are expensive as compared with copper. Even if the addition exceeds 0.4 percent by weight, the proportional improvement in machinability is so small that the addition beyond that does not pay economically. What is more, if the addition is more than 0.4 percent by weight, the alloy will deteriorate in hot workability such as forgeability and cold workability such as ductility.

While there might be a concern that heavy metals like bismuth would cause problems similar to those of lead, addition of a very small amount of less than 0.4 percent by weight is negligible and would present no particular problems.

Based upon these considerations, the second invention alloy is prepared with the addition of bismuth, tellurium, or selenium kept to 0.02 to 0.4 percent by weight. The addition of those elements, which positively affect the machinability of the copper alloy though a mechanism different from that of silicon, as mentioned above, would not affect the proper contents of copper and silicon. On this ground, the contents of copper and silicon in the second invention alloy are set at the same level as those in the first invention alloy.

3. A lead-free free-cutting copper alloy that also has excellent machinability which is composed of 70 to 80 percent, by weight, of copper; 1.8 to 3.5 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 1.0 to 3.5 percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; and the remaining percent, by weight, of zinc. This third copper alloy will be hereinafter called the "third invention alloy." T Pe Tin works the same way as silicon. That is, if tin is added to the Cu-Zn alloy, a gamma phase will be formed and the machinability of the Cu-Zn alloy will be improved. For example, the addition of tin in an amount of 1.8 to percent by weight would bring about a high machinability in the Cu-Zn alloy containing 58 to 70 percent, by weight, of copper, even if silicon is not added.

Therefore, the addition of tin to the Cu-Si-Zn alloy can facilitate the formation of a gamma phase and further improve the machinability of the Cu-Si-Zn alloy.

The gamma phase is formed with the addition of tin in an amount of 1.0 or more percent by weight, and gammaphase formation reaches the saturation point at 3.5 percent, by weight, of tin. If tin exceeds 3.5 percent by weight, the ductility will drop instead. With the addition of tin in amounts less than percent by weight, on the other hand, no gamma phase will be formed. If the addition is 0.3 percent or more by weight, then tin will be effective in uniformly dispersing the gamma phase formed by silicon. Machinability is improved through that effect of dispersing the gamma phase. In other words, the addition of tin in amounts of not less than 0.3 percent by weight improves the machinability of the alloy.

Aluminum is, too, effective in promoting the formation of the gamma phase. The addition of aluminum together with tin or in place of tin could further improve the machinability of the Cu-Si-Zn alloy. Aluminum is also effective in improving the strength, wear resistance, and high-temperature oxidation resistance as well as the machinability and also in minimizing the specific gravity. If the machinability is to be improved at all, aluminum will have to be added in amounts of at least 1.0 percent by weight. However, the addition of more than 3.5 percent by weight does not produce proportional results, and instead adversely affects ductility, as is the case with aluminum.

As for phosphorus, it has no property of forming the gamma phase as in the cases of tin and aluminum. However, phosphorus works to uniformly disperse and distribute the gamma phase formed as a result of the addition of silicon alone or with tin and/or aluminum. In that way, improvement in 6 machinability through gamma phase formation is further enhanced. In addition to dispersing the gamma phase, phosphorus helps to refine the crystal grains in the alpha phase in the matrix, improving hot workability and also strength and resistance to stress corrosion cracking. Furthermore, phosphorus substantially increases the flow of molten metal in casting. To produce such results, phosphorus will have to be added in an amount not smaller than 0.02 percent by weight. But if the addition exceeds 0.25 percent by weight, no proportional effect is obtained. Instead, there will be a decrease in hot forging properties and in extrudability.

In consideration of those observations, the third invention alloy is improved in machinability by adding to the Cu-Si-Zn alloy at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 1.0 to 3.5 percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus.

Meanwhile, tin, aluminum and phosphorus are to improve the machinability by forming a gamma phase or dispersing that phase, and work closely with silicon in promoting the improvement in machinability through the gamma phase. In the third invention alloy mixed with silicon along with tin, aluminum or phosphorus, therefore, silicon does not work alone. Machinability is improved not only by the silicon, but by tin, aluminum, or phosphorus, and thus the required addition of silicon is smaller than that in the second invention alloy in which the machinability is enhanced by adding bismuth, tellurium, or selenium. That is, those elements bismuth, tellurium, and selenium contribute to improving the machinability, not by acting on the gamma phase but by dispersing in the form of grains in the matrix. Even if the addition of silicon is less than 2.0 percent by weight, silicon along with tin, aluminum, or phosphorus will be able to enhance the machinability to an industrially satisfactory level as long as the percentage of silicon is 1.8 or more percent by weight. But even if the addition of silicon is not larger than percent by weight, the effect of silicon in improving machinability is saturated and is not promoted any further in the cases where tin, aluminum, or 7 ICi:-~n~hX; phosphorus is added, when the silicon content exceeds 3.5 percent by weight.

On this ground, the addition of silicon is set at 1.8 to 3.5 percent by weight in the third invention alloy. Also, in consideration of the added amount of silicon and also the addition of tin, aluminum, or phosphorus, the content range of copper in this third invention alloy is slightly raised from the level in the second invention alloy and is set at 70 to 80 percent by weight as preferred content of copper.

4. A lead-free free-cutting copper alloy also with an excellent easy-to- v cut machinability) feature which is composed of 70 to 80 percent, by weight, of copper; 1.8 to 3.5 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 1.0 to percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. This fourth copper alloy will be hereinafter called the "fourth invention alloy."1 The fourth invention alloy thus contains at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium, in addition to the components in the third invention alloy. The grounds for adding those additional elements and setting the amounts to be added are the same as given for the second invention alloy.

A lead-free free-cutting copper alloy having excellent machinability and exhibiting a high degree of corrosion resistance, which is composed of 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 0.02 to 0.25 percent, by weight, of phosphorus, 0.02 to 0.15 percent, by weight, of antimony, and 0.02 to 0.15 percent, by weight, of arsenic- and the remaining percent, by weight, of zinc. This fifth copper alloy will be 'S 5' hereinafter called the "fifth invention alloy." vv The fifth invention alloy thus contains at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 0.02 to 0.25 percent, by weight, of phosphorus, 0.02 to 0.15 percent, by weight, of antimony, and 0.02 to 0.15 percent, by weight, of arsenic, in addition to the first invention alloy.

Tin is effective in improving not only the machinability but also the corrosion resistance properties (dezincification resistance and erosion corrosion resistance) and forgeability of the alloy. In other words, tin improves the corrosion resistance in the alpha phase matrix and, by dispersing the gamma phase, the corrosion resistance, forgeability, and stress corrosion cracking resistance. The fifth invention alloy is thus improved in corrosion resistance by such property of tin and in machinability mainly by adding silicon. Therefore, the contents of silicon and copper in this alloy are set at the same as those in the first invention alloy. To raise the corrosion resistance and forgeability, on the other hand, tin would have to be added in an amount of at least 0.3 percent by weight. But even if the addition of tin exceeds 3.5 percent by weight, the corrosion resistance and forgeability will not improve in proportion to the added amount of tin. The addition of amounts of tin in excess of percent by weight is, therefore, uneconomical.

As described above, phosphorus disperses the gamma phase uniformly and at the same time refines the crystal grains in the alpha phase in the matrix, thereby improving the machinability and also the corrosion resistance properties (dezincification resistance and erosion corrosion resistance), forgeability, stress corrosion cracking resistance, and mechanical strength. The fifth invention alloy is thus improved in corrosion resistance and other properties by such properties of phosphorus and in machinability mainly by adding silicon. The addition of phosphorus in a very small quantity, that is, 0.02 or more percent by weight can produce beneficial results. But the addition in an amount of more than 0.25 percent by weight would not produce proportional benefits, and instead would reduce hot forgeability and 771 S4v i extrudability.

Just as with phosphorus, antimony and arsenic in a very small quantities 0.02 or more percent by weight are effective in improving the dezincification resistance and other properties. But their addition in amounts exceeding 0.15 percent by weight would not produce results in proportion to the quantity mixed. Instead, it would lower the hot forgeability and extrudability, as would phosphorus applied in excessive amounts.

Those observations indicate that the fifth invention alloy is improved in machinability and also corrosion resistance and other properties by adding at least one element selected from among tin, phosphorus, antimony, and arsenic, in quantities within the aforesaid limits, in addition to the same quantities of copper and silicon as in the first invention copper alloy. In the fifth invention alloy, the additions of copper and silicon are set at 69 to 79 percent by weight and 2.0 to 4.0 percent by weight respectively the same level as in the first invention alloy in which any other machinability improver than silicon is not added because tin and phosphorus work mainly as corrosion resistance improvers like antimony and arsenic.

6. A lead-free free-cutting copper alloy, also with excellent machinability and with high corrosion resistance, which is composed of 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 0.02 to 0.25 percent, by weight, of phosphorus, 0.02 to 0.15 percent, by weight, of antimony, and 0.02 to 0.15 percent, by weight, of arsenic; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. This sixth copper alloy will be hereinafter called the "sixth invention alloy." The sixth invention alloy thus contains at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium, in m~ a addition to the components in the fifth invention alloy. The machinability of the alloy is improved by adding silicon and at least one element selected from among bismuth, tellurium, and selenium as in the second invention alloy and the corrosion resistance and other properties are raised by using at least one element selected from among tin, phosphorus, antimony, and arsenic as in the fifth invention alloy. Therefore, the additions of copper, silicon, bismuth, tellurium, and selenium are set at the same levels as those in the second invention alloy, while the contents of tin, phosphorus, antimony, and arsenic are adjusted to the levels of the same elements in the fifth invention alloy.

7. A lead-free free-cutting copper alloy, also with excellent machinability v V and with excellent high strength features and high corrosion resistance, which is composed of 62 to 78 percent, by weight, of copper; 2.5 to 4.5 percent, by weight, of silicon; at least one element selected from among 0.3 to percent, by weight, of tin, 0.2 to 2.5 percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; and at least one element selected from among 0.7 to 3.5 percent, by weight, of manganese and 0.7 to percent, by weight, of nickel; and the remaining percent, by weight, of zinc. The seventh copper alloy will be hereinafter called the "seventh invention alloy."-

J

Manganese and nickel combine with silicon to form intermetallic compounds, which may be represented by the formulas MnxSiy or NixSiy, which intermetallic compounds are evenly precipitated in the matrix, thereby raising the wear resistance and strength of the alloy containing them. Thus the addition of manganese and/or nickel improves high strength features and wear resistance. Improved effects are exhibited when manganese and nickel are added in amounts not less than 0.7 percent by weight, respectively. But the saturation state is reached at 3.5 percent by weight, and even if the addition is increased beyond that, no proportional results will be obtained. The addition of silicon is set at 2.5 to 4.5 percent by weight to match the addition of manganese or nickel, taking into consideration the consumption to form 11 ^s intermetallic compounds with those elements.

It is also noted that tin, aluminum, and phosphorus help to reinforce the alpha phase in the matrix, thereby improving strength, wear resistance, and also machinability. Tin and phosphorus disperse the alpha and gamma phases, by which the strength, wear resistance, and machinability are improved. Tin in an amount of 0.3 or more percent by weight is effective in improving the strength and machinability. However, if the addition exceeds percent by weight, ductility will decrease. For this reason, the addition of tin is set at 0.3 to 3.0 percent by weight, to raise the high strength features and wear resistance in the seventh invention alloy and also to enhance the machinability thereof. Aluminum also contributes to improving the wear resistance, and exhibits its effect of reinforcing the matrix when added in amounts of 0.2 or more percent by weight. But if the addition exceeds percent by weight, there will be a decrease in ductility. Therefore, the addition of aluminum is set at 0.2 to 2.5 weight-percent in consideration of improvement of machinability. Also, the addition of phosphorus disperses the gamma phase and at the same time refines the crystal grains in the alpha phase in the matrix, thereby improving hot workability as well as the strength and wear resistance. Furthermore, phosphorus is very effective in improving the flow of molten metal in casting. Such results will be produced when phosphorus is added in the range of 0.02 to 0.25 percent by weight. The content of copper is set at 62 to 78 percent by weight, in view of the addition of silicon and the bonding of silicon with manganese and nickel.

8. A lead-free free-cutting copper alloy, also with excellent machinability v and with excellent high strength features as well as high wear resistance, comprises 62 to 78 percent, by weight, of copper; 2.5 to 4.5 percent, by weight, of silicon; at least one element selected from among 0.3 to percent, by weight, of tin, 1.0 to 2.5 percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; and at least one element selected from among 0.7 to 3.5 percent, by weight, of manganese and 0.7 to 12 p ~-urr~ l~?ji'ii~^ r~i bi*. r rls percent, by weight, of nickel; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. The eighth copper alloy will be hereinafter called the "eighth invention alloy." The eighth copper alloy contains at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium in addition to the components in the seventh invention alloy. While high-strength features and wear resistance as high as in the seventh invention alloy are secured, the eighth invention alloy is further improved in machinability by the addition of at least one element selected among bismuth and other elements which are effective in raising the machinability through a mechanism different from that exhibited by silicon. The reasons for adding machinability improvers such as bismuth and others and deciding on the quantities thereof to be added are the same as those given for the second, fourth, and sixth invention alloys.

The grounds for adding the other elements, that is, copper, zinc, tin, manganese, and nickel, and setting the contents thereof, are the same as given for the seventh invention alloy.

9. A lead-free free-cutting copper alloy also with excellent machinability v coupled with a good high-temperature oxidation resistance which is composed of 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to 1.5 percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; and the remaining percent, by weight, of zinc. The ninth copper alloy will be hereinafter called the "ninth invention alloy." Aluminum is an element which improves the strength, machinability, wear resistance, and also high-temperature oxidation resistance. Silicon, too, has a property of enhancing the machinability, strength, wear resistance, resistance to stress corrosion cracking, and also high-temperature oxidation resistance of an alloy, as mentioned above. Aluminum works to raise the hightemperature oxidation resistance when the aluminum is added in amounts of not less than 0.1 percent by weight, together with silicon. But when increasing the addition of aluminum beyond 1.5 percent by weight, no proportional results can be expected. For this reason, the addition of aluminum is set at 0.1 to 1.5 percent by weight.

Phosphorus is added to enhance the flow of molten metal in casting.

Phosphorus also works to improve the aforesaid machinability, dezincification resistance, and high-temperature oxidation resistance, in addition to the flow of molten metal. Those effects are exhibited when phosphorus is added in an amount not smaller than 0.02 percent by weight. But even if phosphorus is used in an amount of more than 0.25 percent by weight, it will not result in a proportional increase in effect. For this reason, the addition of phosphorus is set at 0.02 to 0.25 percent by weight.

While silicon is added to improve the machinability of an alloy as mentioned above, it is also capable of increasing the flow of molten metal as is phosphorus. The effect of silicon in improving the flowability of molten metal is exhibited when it is added in an amount not smaller than 2.0 percent by weight. The range of the addition of silicon for improving the flowability of molten metal overlaps that for improvement of the machinability thereof.

Taking both of these factors into consideration, the addition of silicon is set in the range 2.0 to 4.0 percent by weight.

A lead-free free-cutting copper alloy also with excellent v machinability and good high-temperature oxidation resistance which is composed of 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to 1.5 percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of chromium and 0.02 to 0.4 percent, by weight, of titanium; and the remaining percent, by weight, of zinc. The tenth copper alloy will be hereinafter called the "tenth invention alloy." v Chromium and/or titanium are added in order to improve high- S14 temperature oxidation resistance. Good results can be expected especially when they are added together with aluminum to produce a synergistic effect.

Those effects are exhibited when the addition is 0.02 percent or more by weight, whether they are used alone or in combination. The saturation point is 0.4 percent by weight. In consideration of these observations, the tenth invention alloy contains at least one element selected from among 0.02 to 0.4 percent by weight of chromium and 0.02 to 0.4 percent by weight of titanium in addition to the components of the ninth invention alloy, and thus is an improvement over the ninth invention alloy with regard to the hightemperature oxidation resistance of the alloy produced.

11. A lead-free free-cutting copper alloy also with excellent machinability and a good high-temperature oxidation resistance which is composed of 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to 1.5 percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among .0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. The eleventh copper alloy will be hereinafter called the "eleventh invention alloy." V The eleventh invention alloy contains at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium, in addition to the components of the ninth invention alloy. While having as high a high-temperature oxidation resistance as the ninth invention alloy, the eleventh invention alloy is further improved in machinability by the addition of at least one element selected from among bismuth and other elements which are effective in raising machinability through a mechanism other than that exhibited by silicon.

12. A lead-free free-cutting copper alloy also with excellent machinability and a good high-temperature oxidation resistance which is composed of 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to 1.5 percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of chromium, and 0.02 to 0.4 percent by weight of titanium; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. The twelfth copper alloy will be hereinafter called the "twelfth invention alloy." The twelfth invention alloy contains, in addition to the components of the tenth invention alloy, at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium. While as high a high-temperature oxidation resistance as in the tenth invention alloy is obtained, the twelfth invention alloy is further improved in machinability by adding at least one element selected from among bismuth and other elements which are effective in raising the machinability through a mechanism other than that exhibited by silicon.

13. A lead-free free-cutting copper alloy, also with further improved V machinability, is obtained by subjecting any one of the preceding invention alloys to a heat treatment for 30 minutes to 5 hours at a temperature of from 400 0 C to 600 0 C. This thirteenth copper alloy will be hereinafter called the "thirteenth invention alloy." The first to twelfth invention alloys contain machinability improving elements such as silicon and have an excellent machinability because of the addition of such elements. Of those invention alloys, the alloys with a high copper content which have large amounts of other phases mainly alloys having a kappa phase percentage greater than the total percentage of their alpha, beta, gamma, and delta phases together can further improve in 16 i OF' machinability in a heat treatment. As a result of the specified heat treatment, the kappa phase turns into a gamma phase. The gamma phase finely disperses and precipitates to further enhance the machinability of the alloy.

The present alloys with high copper content are high in ductility of the matrix and low in absolute quantity of gamma phase, and therefore are excellent in cold workability. But in cases where cold working, such as caulking and cutting, are required, the aforesaid heat treatment is very useful.

In other words, among the first to twelfth invention alloys, those which are high in copper content with gamma phase in small quantities and kappa phase in large quantities (hereinafter referred to as the "high copper content alloy") undergo a change in phase from the kappa phase to the gamma phase during the heat treatment. As a result, the gamma phase is finely dispersed and precipitated, and the machinability of the alloy is improved. In practice, during the manufacturing process of castings, expanded metals, and hot forgings, the materials are often force-air-cooled or water cooled depending on the forging conditions, productivity after hot working (hot extrusion, hot forging, etc.), working environment, and other factors. In such cases, among the first to twelfth invention alloys, those with a low content of copper (hereinafter called the "low copper content alloy") are rather low in the content of the gamma phase and contain beta phase. During the heat treatment, the beta phase changes into the gamma phase, and the gamma phase is finely dispersed and precipitated, whereby the machinability is improved.

Experiments show that heat treatment is especially effective: with high copper content alloys, where the mixing ratio of copper and silicon to other added elements (except for zinc) A is given as 67 Cu 3Si aA; and with low copper content alloys, where the mixing ratio of copper and silicon to other added elements (except for zinc) A is given as 64 Cu 3Si aA. It is noted that is a coefficient. The coefficient is different depending on the added element A. For example, with tin, a is 0.5; aluminum, phosphorus, antimony, 0; arsenic, 0; manganese, and nickel, In accordance with the present invention, heat treatment at a temperature of less than 400 0 C is not economical and practical, because the aforesaid phase change will proceed slowly and much time will be needed to obtain satisfactory results. At temperatures over 600 0 C, on the other hand, the kappa phase will grow or the beta phase will appear, bringing about no improvement in machinability. From a practical viewpoint, therefore, it is contemplated that the heat treatment be performed for 30 minutes to 5 hours at 400 0 C to 600 0

C.

BRIEF DESCRIPTION OF THE DRAWING Fig. 1 shows perspective views of cuttings formed in cutting a round bar of copper alloy by lathe.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Example 1 As the first series of examples of the present invention, cylindrical ingots with compositions given in Tables 1 to 35, each 100 mm in outside diameter and 150 mm in length, were hot extruded into a round bar 15 mm in outside diameter at 750 C to produce the following test pieces: first invention alloys Nos. 1001 to 1008, second invention alloys Nos. 2001 to 2011, third invention alloys Nos. 3001 to 3012, fourth invention alloys Nos. 4001 to 4049, fifth invention alloys Nos. 5001 to 5020, sixth invention alloys Nos. 6001 to 6105, seventh invention alloys Nos. 7001 to 7030, eighth invention alloys Nos.

8001 to 8147, ninth invention alloys Nos. 9001 to 9005, tenth invention alloys Nos. 10001 to 10008, eleventh invention alloys Nos. 11001 to 11007, and twelfth invention alloys Nos. 12001 to 12021.

Also, cylindrical ingots with the compositions given in Table 36, each 18 'A ~j~i ~i i~ 100 mm in outside diameter and 150 mm in length, were hot extruded into a round bar 15 mm in outside diameter at 750 0 C to produce the following test pieces: thirteenth invention alloys Nos. 13001 to 13006. That is, No. 13001 is an alloy test piece obtained by heat-treating an extruded test piece with the same composition as first invention alloy No. 1005 for 30 minutes at 580 0

C.

No. 13002 is an alloy test piece obtained by heat-treating an extruded test piece with the same composition as No. 13001 for two hours at 450 0 C. No.

13003 is an alloy test piece obtained by heat-treating an extruded test piece with the same composition as first invention alloy No. 1007 under the same conditions as for No. 13001 for 30 minutes at 580 0 C. No. 13004 is an alloy test piece obtained by heat-treating an extruded test piece with the same composition as No. 13007 under the same conditions as for 13002 for two hours at 450 0 C. No. 13005 is an alloy test piece obtained by heat-treating an extruded test piece with the same composition as first invention alloy No. 1008 under the same conditions as for No. 13001 for 30 minutes at 580 0 C. No.

13006 is an alloy test piece obtained by heat-treating an extruded test piece with the same composition as No. 1008 and heat-treated under the same conditions as for 13002- for two hours at 450 0

C.

As comparative examples, cylindrical ingots with the compositions as shown in Table 37, each 100 mm in outside diameter and 150 mm in length, were hot extruded into a round bar 15 mm in outside diameter at 750 0 C to obtain the following round extruded test pieces: Nos. 14001 to 14006 (hereinafter referred to as the "conventional alloys"). No. 14001 corresponds to the alloy JMS C 3604, No. 14002 to the alloy CDA C 36000, No. 14003 to the alloy JIS C 3771, and No. 14004 to the alloy CDA C 69800. No. 14005 corresponds to the alloy JIS C 6191. This aluminum bronze is the most excellent of those expanded copper alloys having a JIS designation with regard to strength and wear resistance. No. 14006 corresponds to the naval brass alloy JIS C 4622 and is the most excellent of the expanded copper alloys having a JIS designations with regard to corrosion resistance.

19 To study the machinability of the first to thirteenth invention alloys in comparison with the conventional alloys, cutting tests were carried out. In the cutting tests, evaluations were made on the basis of cutting force, condition of chips, and cut surface condition.

The tests were conducted in this way: The extruded test pieces obtained as described above were cut on the circumferential surface by a lathe mounted with a point noise straight tool at a rake angle of 8 degrees and at a cutting rate of 50 meters/minute, a cutting depth of 1.5 mm, a feed of 0.11 mm/rev. Signals from a three-component dynamometer mounted on the tool were converted into electric voltage signals and recorded on a recorder. From the signals were then calculated the cutting resistance. It is noted that while, to be perfectly exact, an amount of cutting resistance should be judged by three component forces cutting force, feed force, and thrust force, the judgement was made on the basis of the cutting force of the three component forces in the present example. The results are shown in Table 38 to Table 66.

Furthermore, the chips from the cutting work were examined and classified into four forms to as shown in Fig. 1. The results are enumerated in Table 38 to Table 66. In this regard, the chips in the form of a spiral with three or more windings as in Fig. 1 are difficult to process, that is, recover or recycle, and could cause trouble in cutting work as, for example, getting tangled with the tool and damaging the cut metal surface. Chips in the form of an arc with a half winding to a spiral with about two windings as shown in Fig. 1 do not cause such serious trouble as the chips in the form of a spiral with three or more windings yet are not easy to remove and could get tangled with the tool or damage the cut metal surface. In contrast, chips in the form of a fine needle as in Fig. 1 or in the form of an arc as will not present such problems as mentioned above and are not bulky as the chips in and and easy to process. But fine chips as still could creep into the sliding surfaces of a machine tool such as a lathe and cause mechanical trouble, or could be dangerous because they could stick into the worker's finger, eye, or other body parts. Taking these factors into account, it is appropriate to consider that the chips in are the best, and the second best is the chips in Those in and are not good. In Table 38 to Table 66, the chips judged to be as shown in and are indicated by the symbols "o and respectvely.

In addition, the surface condition of the cut metal surface was checked after cutting work. The results are shown in Table 38 to Table 66. In this regard, the commonly used basis for indication of the surface roughness is the maximum roughness (Rmax). While requirements are different depending on the application field of brass articles, the alloys with Rmax 10 microns are generally considered excellent in machinability. The alloys with 10 microns Rmax 15 microns are judged as industrially acceptable, while those with Rmax> 15 microns are taken as poor in machinability. In Table 38 to Table 65, the alloys with Rmax 10 microns are marked those with 10 microns Rmax 15 microns are indicated in and those with Rmax 15 microns are represented by a symbol As is evident from the results of the cutting tests shown in Table 38 to Table 66, the following invention alloys are all equal to the conventional leadcontained alloys Nos. 14001 to 14003 in machinability: first invention alloys Nos. 1001 to 1008, second invention alloys Nos. 2001 to 2011, third invention alloys Nos. 3001 to 3012, fourth invention alloys Nos. 4001 to 4049, fifth invention alloys Nos. 5001 to 5020, sixth invention alloys Nos. 6001 to 6105, seventh invention alloys Nos. 7001 to 7030, eighth invention alloys Nos. 8001 to 8147, ninth invention alloys Nos. 9001 to 9005, tenth invention alloys Nos.

10001 to 10008, eleventh invention alloys Nos. 11001 to 11007, and twelfth invention alloys Nos. 12001 to 12021. Especially with regard to formation of the chips, those invention alloys are favorably compared not only with the conventional alloys Nos. 14004 to 14006 with a lead content of not higher than 21 ,?ts r~yw~ z .~ZS 0.1 percent by weight but also with Nos. 14001 to 14003 which contain large quantities of lead.

Also to be noted is that, as is clear from Tables Nos. 38 to thirteenth invention alloys Nos. 13001 to 13006 are improved over first invention alloys No. 1005, No. 1007, and No. 1008 with the same composition as the thirteenth invention alloys in machinability. It is thus confirmed that a proper heat treatment can further enhance machinability in accordance with the present invention.

In another series of tests, the first to thirteenth invention alloys were examined in comparison with the conventional alloys in hot workability and mechanical properties. For this purpose, hot compression and tensile tests were conducted the following way.

First, two test pieces first and second test pieces in the same shape, mm in outside diameter and 25 mm in length, were cut out of each extruded test piece obtained as described above. In the hot compression tests, the first test piece was held for 30 minutes at 700 0 C, and then compressed 70 percent in the direction of axis to reduce the length from mm to 7.5 mm. The surface condition after the compression (700 0

C

deformability) was visually evaluated. The results are given in Table 38 through Table 66. The evaluation of deformability was made by visually checking for cracks on the side of the test piece. In Table 38 Table 66, the test pieces with no cracks found are marked those with small cracks are indicated by and those with large cracks are represented by a symbol The second test pieces were subjected to tensile testing by conventional testing procedures to determine their tensile strength, in N/mm 2 and their elongation, in As the test results of the hot compression and tensile tests in Table 38 through Table 66 indicate, it was confirmed that the first to thirteenth invention alloys are equal to or superior to the conventional alloys Nos. 14001 to 14004 and No. 14006 in hot workability and mechanical properties and are ~m~~4tn~4r~v44nZ W4 I suitable for industrial use. The seventh and eighth invention alloys in particular have the same level of mechanical properties as the conventional alloy No. 14005, the aluminum bronze alloy which is highest in strength of the expanded copper alloys having ]IS designations. Thus, the seventh and eighth invention alloys are characterized by prominent high strength features.

Furthermore, the first to six and ninth to thirteenth invention alloys were subjected to dezincing corrosion and stress corrosion cracking tests in accordance with the test methods detailed in ISO 6509 and IS H 3250, respectively, in order to examine their corrosion resistance and resistance to stress corrosion cracking in comparison with the conventional alloys.

In the dezincification corrosion test conducted according to the ISO 6509 method, a sample taken from each extruded test piece was imbedded in a phenolic resin material in such a way that part of the side surface of the sample is exposed, the exposed surface being perpendicular to the extrusion direction of the extruded test piece. The surface of the sample was polished with emery paper No. 1200, and then ultrasonic-washed in pure water and dried. The sample thus prepared was dipped in a 12.7 g/ aqueous solution of cupric chloride dihydrate (CuCI 2 .2 H 2 0) 1.0% and left standing for 24 hours at C. The sample was taken out of the aqueous solution and the maximum depth of dezincification corrosion was determined. The measurements of the maximum dezincification corrosion depth are given in Table 38 to Table 50 and Table 61 to Table 66.

As is clear from the results of dezincification corrosion tests shown in Table 38 to Table 50 and Table 61 to Table 66, the first to fourth invention alloys and the ninth to thirteenth invention alloys are excellent in corrosion resistance and compare favorably to the conventional alloys Nos. 14001 to 14003 containing great amounts of lead. Also it was confirmed that especially the fifth and sixth invention alloys, which seek improvement in both machinability and corrosion resistance, are very high in corrosion resistance, being superior in corrosion resistance to the conventional alloy No. 14006, a Ji 23 ~lixc~-- I-l ~u ;n: naval brass which is the most resistant to corrosion of all the expanded alloys having a JIS designation.

In stress corrosion cracking tests conducted in accordance with the test method described in JIS H 3250, a 150-mm-long sample was cut out from each extruded test piece. The sample was bent with its center placed on an arc-shaped tester with a radius of 40 mm in such a way that one end and the other end form an angle of 45 degrees. The test sample thus subjected to a tensile residual stress was degreased and dried, and then placed in an ammonia environment in the desiccator with a 12.5% aqueous ammonia (ammonia diluted in the equivalent of pure water). The test sample was held some 80 mm above the surface of aqueous ammonia in the desiccator. After the test sample was left standing in the ammonia environment for periods of two hours, 8 hours, and 24 hours, the test sample was taken out from the desiccator, washed in sulfuric acid solution 10%, and examined for cracks under a magnifier of 10 magnifications. The results are given in Table 38 to Table 50 and Table 61 to Table 66. In those tables, the alloys which have developed clear cracks when held in the ammonia environment for two hours are marked The test samples which had no cracks after two hours but were found to be clearly cracked at 8 hours are indicated by The test samples which had no cracks at 8 hours, but were found to have clear cracks at 24 hours were indicated by The test samples which were found to have no cracks at all at 24 hours are identified by the symbol As is indicated by the results of the stress corrosion cracking tests reported in Table 38 to Table 50 and Table 61 to Table 66, it was confirmed that not only the fifth and sixth invention alloys which seek improvement in both machinability and corrosion resistance but also the first to fourth invention alloys and the ninth and thirteenth alloys in which nothing particular was done to improve corrosion resistance were both equal to conventional alloy No. 14005, an aluminum bronze alloy containing no zinc, in stress corrosion cracking resistance, and were superior in stress corrosion cracking 24 7WIT RWRVTW ~i~ resistance to the conventional naval brass alloy No. 14006, the alloy having highest corrosion resistance of all of the expanded copper alloys identified by JIS designations.

In addition, oxidation tests were carried out to study the hightemperature oxidation resistance of the ninth to twelfth invention alloys in comparison with the conventional alloys. A test piece in the shape of a round bar with the surface cut to a outside diameter of 14 mm and the length cut to mm was prepared from each of the following extruded test pieces: No.

9001 to No. 9005, No. 10001 to No. 10008, No. 11001 to No. 11007, No.

12001 to No. 12021, and No. 14001 to No. 14006. Each test piece was then weighed to measure the weight before oxidation. After that, the test piece was placed in a porcelain crucible and held in an electric furnace maintained at 500 0 C. After the passage of 100 hours, the test piece was taken out of the electric furnace and was weighed to measure the weight after oxidation. The increase in weight by oxidation was calculated from the measurements before and after oxidation. It is understood that the increase due to oxidation is an amount, in mg, of increase in weight by oxidation per 10 cm 2 of the surface area of the test piece and is calculated by the equation: increase in weight by oxidation, mg/1b cm 2 (weight, mg, after oxidation weight, mg, before oxidation) x (10 cm 2 surface area, in cm 2 of test piece). The weight of each test piece increased after oxidation. This increase was brought about by hightemperature oxidation. When subjected to a high temperature, oxygen combines with copper, zinc, and silicon to form Cu 2 O, ZnO, SiO 2 respectively.

Thus, an increase of oxygen contributes to the weight gain. It can be said, therefore, that the smaller in weight increase by oxidation of the alloy, the more excellent in high-temperature oxidation resistance. The results obtained are shown in Table 61 to Table 64 and Table 66.

As is evident from the test results shown in Table 61 to Table 64 and Table 66, the ninth to twelfth invention alloys are equal to conventional alloy No. 14005, an aluminum bronze alloy ranking high in resistance to high- \~RA4/ temperature oxidation among the expanded copper alloys having JIS designations. Thus, it was confirmed that the ninth to twelfth invention alloys are very excellent in machinability and that they are resistant to hightemperature oxidation as well.

Example 2 As the second series of examples of the present invention, cylindrical ingots with compositions given in Tables 14 to 31, each 100 mm in outside diameter and 200 mm in length, were hot extruded into a round bar 35 mm in outside diameter at 700 0 C to produce the following test pieces: seventh invention alloys Nos. 7001a to 7030a and eighth invention alloys Nos. 8001a to 8147a. In parallel, cylindrical ingots with compositions given in Table 37, each 100 mm in outside diameter and 200 mm in length, were hot extruded into a round bar 35 mm in outside diameter at 700 0 C to produce the following alloy test pieces: Nos. 14001a to 14006a, as second comparative examples (hereinafter referred to as the "conventional alloys"). It is noted that the alloys Nos. 7001a to 7030a, Nos. 8001a to 8147a, and Nos. 14001a to 14006a are identical in composition with the aforesaid copper alloys Nos. 7001 to 7030, Nos. 8001 to 8147, and Nos. 14001 to No. 14006, respectively.

These seventh invention alloys Nos. 7001a to 7030a and eighth invention alloys Nos. 8001a to 8147a were put to wear resistance tests in comparison with the conventional alloys Nos. 14001a to 14006a. The tests were carried out in the following manner. Each extruded test piece thus obtained was cut on the circumferential surface, holed, and cut down into a ring-shaped test piece 32 mm in outside diameter and 10 mm in thickness (that is, length in the axial direction). The test piece was then fitted around a free-rotating shaft, and a roll 48 mm in outside diameter placed in parallel with the axis of the shaft was urged against the test piece under a load of 50 kg.

The roll was made of stainless steel having the JIS designation SUS 304.

Then, the SUS 304 roll and the test piece put in rotational sliding contact with the roll were rotated at the same rate of revolutions/minute 209 r.p.m. with multipurpose gear oil dropping to the circumferential surface of the test piece.

When the number of revolutions reached 100,000, the SUS 304 roll and the test piece were stopped,, and the weight difference between the start and the end of rotation, that is, the loss of weight by wear, in mg, was determined. It can be said that the alloys which show less loss of weight by wear are higher in wear resistance. The results are given in Tables 67 to 77.

As is clear from the wear resistance test results shown in Tables 67 to 77, these tests showed that seventh invention alloys Nos. 7001a to 7030a and eighth invention alloys Nos. 8001a to 8147a were excellent in wear resistance as compared with not only conventional alloys Nos. 14001a to 14004a and 14006a but also No. 14005a, which is an aluminum bronze alloy characterized by the highest wear resistance of the expanded copper alloys having JIS designations. From comprehensive considerations of the test results including the tensile test results, it may be concluded that the -seventh and eighth invention alloys are excellent in machinability and that they also possess higher strength features and wear resistance than does the aluminum bronze which is the highest in wear resistance of all the expanded copper alloys listed in the JIS designations.

The reference to any prior art in this specification is not, and should not be taken as, an acknowledgment or any form of suggestion that that prior art forms part of the common general knowledge in Australia.

Throughout this specification and the claims which follow, unless the context requires otherwise, the word "comprise", and variations such as "comprises" or comprising", will be understood to imply the inclusion of a stated integer or step or group of integers or steps but not the exclusion of any other integer or step or group of integers or steps.

27 ;-~CV12Vt er rrV'tV$%Vfl~s~V-' P:\WPDOCS\Hjw\Sp\7481530pgs.d.-14/12OI Amendments have been made to the claims which follow and new claims have been proposed to more closely define the invention. The claim amendments are based on various preferred embodiments as described and exemplified in the description. However, for the purpose of maintaining integrity of the text of the disclosure, substantial amendments have not been made to the description in light of the claim amendments. It is submitted that there is no disconformity in the specification as a consequence of amendment of the claims given the limitation of claim scope of various preferments of the invention described.

-27A 'A S t U C [Table 1] N o.

1001 1002 1003 1004 1005 1006 1007 1008 alloy composition (wt%) Cu Si Zn 70.2 2.1 remainder 74.1 2.9 remainder 74.8 3.1 remainder 77. 6 3. 7 remainder 78. 5 3.2 remainder 73.3 2.4 remainder 77.0 2.9 remainder 69. 9 2. 3 remainder [Table 2] alloy composition (wt%) No. Cu Si Bi Te Se Zn 2001 74.5 2.9 0.05 remainder 2002 74. 8 2. 8 0. 25 remainder 2003 75. 0 2. 9 0.13 remainder 2004 69.9 2.1 0.32 0.03 remainder 2005 72. 4 2. 3 0. 11 0. 31 remainder 2006 78.2 3.4 0.14 0.03 remainder 2007 76.2 2. 9 0.03 0.05 0.12 remainder 2008 78. 2 3.7 0.33 remainder 2009 73.0 2.4 0.16 remainder 2010 74.7 2.8 0.04 0.30 remainder 2011 76.3 3.0 0.18 0.12 remainder [Table 3] alloy composition (wt%) No. Cu Si Sn Al P Zn 3001 71.8 2.4 3.1 remainder 3002 78.2 2. 3 3. 3 remainder 3003 75.0 1.9 1.5 1.4 remainder 3004 74.9 3. 2 0.09 remainder 3005 71.6 2.4 2.3 0.03 remainder 3006 76.5 2.7 2. 4 0.21 remainder 3007 76.5 3.1 0.6 1. 1 0.04 remainder 3008 77.5 3.5 0. 4 remainder 3009 75. 4 3. 0 1. 7 remainder 3010 76.5 3. 3 0.21 remainder 3011 73.8 2. 7 0. 04 remainder 3012 75.0 2.9 1.6 0.10 remainder [Table 4] alloy composition N o.

A 001 401 70. 8 Su Ii I S nIA I lB iI Te S.e Z n 1.9 0. 36 remainder 1 9_ 0.36 4- 0. 03 remainder 3fJJ 4V 0.03-.

4003 73. 2 2. 5 1. 9 0. 15 1remainder 4004 72. 3 2. 4 0. 6 0. 29 0.23 remainder 4005 74. 2 2. 7 2. 0 0. 03 0. 26 remainder 4006 75. 4 2. 9 0. 4 0. 31 0. 03 remainder 4007 71. 5 2. 1 2. 6 0. 11 0. 05 0. 23 remainder 4008 79. 1 1. 9 3. 3 0. 28 remainder 4009 76. 3 2. 7 1. 2 0. 13 remainder 4010 77. 2 2. 5 2. 0 0. 07 remainder 4011 79. 2 3. 1 1. 1 0. 04 0. 06 remainder 4012 76. 3 2. 3 1. 3 0. 13 0. 04 remainder 4013 77.4 2. 6 2. 6 0. 22 0. 03 remainder 4014 .77. 9 2. 2 2. 3 0. 09 0. 05 0. 11 -remainder 4015 73. 5 2. 0 2.9 1. 2 0. 23 remainder 4016 76. 3 2. 5 0. 7 3. 2 0. 04 remainder 4017 75. 5 2. 3 1. 2 2. 0 0. 12 remainder 4018 77. 1 2. 1 0. 9 3. 4 0. 03 0. 03 remainder 4019 72.9 3.2 3.3 1.7 0.11 0.04 remainder 4020 74. 2 2. 8 2. 7 1. 1 0. 33 0. 03 remainder [Table N alloy composition (wt%) No Cu S i S n AlI B i T e Se P Zn 4021 74.2 2.3 1.5 2.3 0.07 0.05 0.09 remainder 4022 70. 9 2. 1 11 0. 11 remainder 4023 74. 8 3. 1 0. 07 0. 06 remainder 4024 76. 3 3. 2 0. 05 0. 02 remainder 4025 78. 1 3. 1 0. 26 0. 02 0. 15 remainder 4026 71.1 2.2 0. 13 0. 02 10. 05 remainder 4027 74. 1 2. 7 0. 03 0. 06 0. 03 0. 03 remainder 4028 70. 6 1. 9 3. 2 0. 31 0. .04 remainder 4029 73. 6 2. 4 2. 3 0. 03 0. 04 remainder 4030 73. 4 2. 6 1. 7 0. 31 0. 22 remainder 4031 74. 8 2. 9 0. 5 0. 03 0. 02 0. 05 remainder 4032 73. 0 2. 6 0. 7 0. 09 0. 02 0. 08 1remainder 4033 74. 5 2. 8 10. 03 0. 12 0. 05 remainder 4034 77. 2 3. 3 1. 3 0. 03 0. 12 0. 04 remainder 4035 74. 9 3. 1 0. 4 0. 02 0. .05 0. 05 0. 08 remainder 4036 79. 2 3. 3 2. 5 0. 05 12 remainder 4037 74. 2 2. 6 1. 2 0. 12 0. 05 remainder 4038 77. 0 2. 8 1. 3 05 0. 20 remainder 4039 76. 0 2. 4 3. 2 0. 10 0. 04 0. 05 remainder 4040 74. 8 2. 4 1. 1 0. 07 0. 04 0. 03 remainder 7.

OF

[Table 6] ~11nv cnnrnn~it.inn (wt%) N o.

Af)A1 allov_ -nnsto r C u 77 9 B i P L 4- 4 4 1 I 27 0. 33 0.05 0.05 remainder 2A remainde 4042 78. 0 2.6 5 0. 03 0. 02 0. 10 0. 14 remainder 4043 72. 5 2. 4 1. 9 1. 1 0. 12 0. 03 remainder 4044 7 6. 0 2. 6 0. 5 2. 0 0. 20 0. 07 remainder 4045 77.5 2.6 0.7 3.1 0.21 0.12 remainder 4046 75. 0 2. 6 0. 8 2. 2 0. 04 0. 05 0. 06 remainder 4047 ,71.0 1.9 3.1 1.0 0.15 0.02 0.04 remainder 4048 73. 3 2. 1 2. 6 1. 2 0. 04 0. 03 0. 05 remainder 4049 74. 8 2. 5 0. 6 1. 1 0. 03 0. 03 0. 04 0. 07 remainder [Table 7] N alloy composition (wt%) No Cu S i S n P S b A s Z n 5001 69. 9 2. 1 3. 3 remainder 5002 74. 1 2. 7 0. 21 remainder 5003 75. 8 2. 4 0. 14 remainder 5004 77. 3 3. 4 05 remainder 5005 .73. 4 2. 4 2. 1 0. 04 ____remainder 5006 75. 3 2. 7 0. 4 0. 04 remainder 5007 70. 9 2. 2 2. 4 0. 07 remainder 5008 71. 2 2. 6 1. 1 0. 03 0. 03 remainder 5009 77. 3 2. 9 0. 7 0. 19 0. 03 remainder 5010 78. 2 3. 1 0. 4 0. 09 0. 15 remainder 5011 72.5 .2.1 2.8 0.02 0.10 0.03 remainder 5012 79. 0 3. 3 0. 24 0. 02 remainder 5013 75. 6 2. 9 0. 07 0. 14 remainder 5014- 74.8 3.0 0.11 0.02 remainder 5015 74. 3 2. 8 0. 06 0. 02 0. 03 remainder 5016 72.9 2.5 remainder 5017 77. 0 3. 4 0. 14 remainder 5018 76. 8 3. 2 0. 7 0. 12 remainder 5019 74. 5 2. 8 1. 8 remainder 5020 74. 9 3. 0 0. 20 0. 05 remainder [Table 8] N alloy composition (wt%) N. Cu S i Sn B i Te P Sb As Zn 6001 69.6 2.1 3.2 0.15 remainder 6002 77. 3 3. 7 0. 5 0. 02 0. 23 remainder 6003 75. 2 2. 4 11. 1 0. 33 10. 12 remainder 6004 7-0. 9 2. 3 3. 1 0. 11 0. 03 remainder 6005 78. 1 2. 7 0. 6 0. 14 0. 02 0. 07 remainder 6006 74. 5 2. 6 1. 5 0. 21 0. 10 0. 04 remainder 6007 74.7_ 3. 2 2. 1 0.,05 0. 02 0. 12 remainder 6008 73.8 2.5 0.7 0.31 0.03 0.02 0.10 remainder 6009 74. 5 2. 9 0. 05 0. 19 remainder 6010 78. 1 3. 1 0. 11 0. 15 remainder 6011 74. 6 3. 3 0. 02 0. 22 remainder 6012 69. 9 2. 3 0. 35 0. 08 0. 02 remainder 6013 73.2 2.6 0.21 0.03 0.07 remainder 6014 76. 3 2. 9 0. 07 0. 09 0. 02 remainder 6015 74. 4 2. 8 0. 19 0. 13 0. 03 0. 02 remainder 6016 70. 5 2. 3 2. 9 0. 10 0. 02 remainder 6017 74. 7 2. 4 0. 9 0. 31 0. 04 0. 05 remainder 6018 78. 1 3. 8 0. 6 0. 02 0. 33 0. 07 remainder 6019 69. 4 2. 0 3. 4 0. 11 0. 03 0. 03 remainder F6020 77. 8 2. 8 0. 5 10. 06 0. 11 0. 21 10. 02 remainder [Table 9] N alloy composition (wt%) No Cu S i S n B i T e S e P S b A s Z n 6021 74. 2 2. 6 0. 6 0. 20 0. 03 0. 02 0. 14 remainder 6022 75. 8 3. 3 1. 8 0. 03 0. 06 0. 11 0. 02 remainder 6023 74. 4 2. 6 1. 5 0. 09 0. 12 0. 03 0. 02 0. 06 remainder 6024 77. 3 3. 1 0. 02 0. 25 0. 08 ____remainder 6025 70. 5 2. 4 0. 12 0. 04 0. 06 0. 03 remainder 6026 74. 3 2. 9 0. 24 0. 02 0. 13 0. 11 remainder 6027 69. 8 2. 3 0. 34 0. 03 0. 21 0. 02 0. 02 Iremainder 6028 74. 5 2. 9 0. 03 0. 11 0. 13 remainder 6029 78. 4 3. 2 0. 02 0. 08 0. 04 0. 05 remainder 6030 73. 8 -3.0 0. 08 0. 31 0. 23 remainder 6031 72. 8 2. 5 1. 6 0. 11 0. 36 remainder 6032 78. 1 3. 7 0. 5 0. 03 0.,02 0. 05 ____remainder 6033 77. 2 2. 8 0. 6 0. 09 0. 04 0. 07 remainder 6034 76. 9 3. 8 0. 4 0. 03 1 0.06 0. 07 remainder 6035 74. 1 2. 3 3. 3 0. 06 0. 03 0. 02 0. 05 remainder 6036 69. 8 2. 0 2. 5 0. 31 0. 12 0. 03 0. 06 remainder 6037 74. 9 3. 0 1. 1 0.,07 0. 21 0. 12 0. 02 remainder 6038 72. 6 2. 8 6 0. 20 0. 05 0. 21 0. 07 0. 03 remainder 6039 69. 7 2. 3 0. 23 0. 06 0. 10 remainder 6040 75. 4 3. 0 0. 02 0. 09 0. 11 0. 03 remainder -V 3/ cc F~\ R I R W- [Table 1 0] N o. alloy composition 6041 73. 2 2. 5 0. 11 0. 36 0. 05 0. 02 remainder 6042 78. 2 3. 7 0. 03 0. 04 0. 03 0. 04 0. 10 remainder 6043 7f7. 8 2. 8 0. 09 0. 02 0. 04 remainder 6044 73. 4 2. 6 0. 16 0. 06 0. 03 0. 02 remainder 6045 7.2 2. 4 0. 35 0. 14 0. 08 remainder 6046 70. 3 2. 5 1. 9 0. 09 0. 05 0. 03 remainder 6047 74. 5 3. 6 2. 2 0. 02 0. 20 0. 04 0. 04 remainder 6048 73. 8 2. 9 1. 2 0. 03 0. 10 0. 05 0. 12 remainder 6049 69. 8 2. 1 3. 1 0. 32 0. 03 10. 05 0. 13 remainder 6050 74. 2 2. 2 0. 6 0. 19 0. 11 0. 02 0. 02 0. 03 remainder 6051 74. 8 3. 2 0. 5 0. 03 0. 07 0. 03 0. 05 02 remainder 6052 78.0 2.8 0.6 0.06 0.04 0.11 0.11 0.03 remainder 6053 76. 3 2. 4 0. 8 0.05 0. 03 0. 22 0. 03 0. 04 0. 03 remainder 6054 74.2 2.6 0.21 0.02 0.04 0.05 remainder 6055 78. 2 2. 9 0. 16 0. 08 0. 03 0. 21 0. 03 remainder 6056 72. 3 2. 5 0. 08 0. 36 0. 02 0. 10 0. 04 remainder 6057 69. 8 2. 4 0. 36 0. 04 0. 04 0. 06 0. 07 0. 02 remainder 6058 74. 6 3. 1 0. 05 0. 09 0. 04 0. 14 remainder 6059 73. 8 2. 5 0. 08 0. 05 0. 03 0. 02 0. 04 remainder 6060 174. 9 2. 7 0. 03 0. 16 02 03 remainder [Table 1 1] N alloy composition (wt%) No Cu S i S n T e S e P S b A s Z n 6061 69.7 2.6 3.1 0.26 ____remainder 6062 74. 2 3. 2 0. 6 0. 03 0. 04 remainder 6063 74. 9 2. 6 0. 7 0. 14 0. 14 1remainder 6064 73. 8 3. 0 0. 4 0. 07 0.1 13 remainder 6065 78. 1 3. 3 0. 8 0. 02 0. 12 0. 02 remainder 6066 72. 8 2. 4 1..2 0. 32 0. 03 0. 05 remainder 6067 173. 6 2. 7 2. 1 0. 03 0. 07 0. 02 remainder 6068 72. 3 2. 6 0. 5' 0. 16 0. 02 0. 04 0. 03 remainder 6069 70. 6 2. 3 0. 33 0. 09 remainder 6070 76. 5 3. 2 .0.14 0. 21 0. 03 remainder 6071 74. 5 3. 1 0. 05 0. 03 0. 03 remainder 6072 72.8 2.7 0.08 0.13 remainder 6073 78. 0 3. 8 0. 04 0. 02 0. 12 remainder 6074 73. 8 2. 9 0. 20 0. 10 remainder 6075 74. 5 2. 9 0. 07 0. 04 0. 10 0. 02 remainder 6076 73.6 3.2 2.1 0.04 0.07 remainder 6077 74. 1 5 0. 8 0. 21 0. 18 0. 05 remainder 6078 77. 8 2. 9 0. 6 0. 11 0. 05 0. 07 remainder 6079 71. 5 2. 1 1. 1 0. 06 0. 03 0. 06 remainder 6080 172. 6 2. 3 0. 5 0. 15 0. 23 0. 11 0. 02 remainder [Table 1 2]1 alloy composition N o.

rnQ1 C u 7A NZ n. Te 9 0.03 0. 03 0. 20 0. 02 remainder 6082 7. 6 2. 2 2. 6 0. 32 0. 05 0. 13 0. 03 remainder 6083 73. 7 2. 6 0. 8 0. 14 0. 16 0. 06 0. 02 0. 03 remainder 6084 7 4. 5 3. 1 0. 04 0. 04 0. 05 ____remainder -085 7 2-.8 2.7 0.09 0.21 0.04 0.02 remainder 86 -7-62 3. 3 0. 03 0. 04 0. 11 0. 04 remainder 6 087 73.8 2.7 0.11 0.03 10.02 0.04 0. 03 remainder 6088 74. 9 2. 9 0. 05 0. 31 0. 05 remainder 60O8 9 75. 8 2. 8 0. 08 0. 04 0. 03 0. 14 remainder 6090 73. 6 2. 4 0. 27 0. 10 0. 06 remainder 6091 72. 4 2. 2 3. 2 0. 33 ____remainder 6092 75. 0 3. 2 0 6 0. 05 0. 10 remainder 6093 76. 8 3. 1 0. 5 0. 04 0. 11 remainder 6094 74. 5 2. 9 0. 7 0. 08 0. 15 remainder 6095 73. 2 2. 7 1. 2 0. 12 0. 06 0. 03 remainder 6096 69.6 2.4 2.3 0.14 0.04 0.02 remainder 6097 74. 2 2. 8 0. 8 0. 07 0. 02 0. 03 remainder 6098 74. 4 2. 9 0. 8 0. 06 10. 03 10. 03 0. 03 remainder 6099 74. 8 3. 1 0. 09 0.04 remainder 6100 73.9 2.8 0.05 0.10 0.04 __remainder [Table 1 3] N alloy composition (wt%) No Cu S i S e P Sb As Zn 6101 76. 1 3. 0 0. 04 0. 05 0. 02 remainder 6102 74. 5 2. 8 0. 03 0. 04 0. 02 0. 03 remainder 6103 74. 3 2. 6 0. 31 0. 04 remainder 6104 75. 0 3. 3 0. 06 0. 02 0. 05 remainder 6105 73. 9 2. 9 0. 10 0. 11 remainder t~tn~z~ [Table 1 4] N o.I.S alloy composition_(wt%) AlI Mn 7001 7001a 62. 9 2. 7 2. 6 2. 2 remainder 7002a 64. 8 3. 4 1. 8 3.1 remainder 7003a 7003a 68. 2 4. 1 0. 6 1. 9 1. 5 remainder 7004 7004a 66. 5 3. 5 1. 9 0. 9 1. 9 remainder 7005a 7005a 71. 3 3. 7 0. 4 1. 8 2. 3 remainder 7006 73.6 2.9 0.7 .2.1 1.3 0.8 remainder 7006a 7007a 70.1 3.2 0.5 1.4 0. 11 1.8 remainder _7008a 7008a 77.1 4.2 0 8 2.3 0.03 1.8 remainder 7009a 7009a 67.3 3.7 2.6 0.2 0.08 0.9 1.8 remainder 700 7010a 75.5 3. 9 2. 3 0. 8 remainder [Table 1 N alloy composition (wt%) No Cu S i S n AlI P Mn N i Z n 7011a 69. 8 3. 4 0. 3 1. 3 remainder _7012a 7012a 71. 2 4. 0 1. 4 2. 1 1. 2 remainder 7013 73.3 3. 9 2. 0 0. 03 3. 2 remainder 7014a 7014a 65. 9 2. 9 0. 3 0. 21 1. 3 remainder 7015a 7015a 68. 8 3. 9 1. 1 0. 05 0. 9 2. 0 remainder 7016a 7016a 68. 1 4. 0 0. 4 0. 04, 2. 8 remainder 7017a 7017a 63. 8 2. 6 2. 7 0. 19 0. 9 remainder 7018 7018a 66. 7 3. 4 1. 3 0. 07 1. 2 0. 8 remainder 70O19a 67.2 3.6 0.21 1.9 remainder 7020a 69.1__3.8 -7020a OF z [Table 1 6] N o. Ci alloy composition S i Z n 7021 72. 1 4. 3 0. 07 2. 0 0. 8 remainder 7022a 7022a 71. 3 3. 9 1. 1 3. 1 remainder 7023a 7023a 70. 5 35 1. 6 2. 3 remainder 7024a 7024a 70. 0 3. 6 1. 5 3. 2 remainder 7025 7025a 69. 3 2. 7 2.1 1 0. 9 remainder 7026a 70. 2 3. 5 1. 4 2.1 remainder 7027a 7027a 65. 0 2. 8 2. 6 2. 3 0. 8 remainder 7028a 7028a 69. 8 3. 6 1. 5 1. 7 2. 4 remainder 7029a 71. 0 3. 6 0. 4 0. 3 2. 2 remainder 7030.

73a 68. 4 4. 2 2. 6 3. 3 remainder [Table 1 7] N alloy composition (wt%) No Cu S i S n AlI B i T e S e M n Z n 8001a 62. 6 2. 6 2. 6 0. 31 1. 9 remainder 8002a 8002a 65.3 3.4 1.8 0. 11 0.02 2.5 remainder 8003 8003a 66. 4 4. 2 0. 5 0. 05 0. 03 3. 4 remainder 8004a 72. 1 4. 4 0. 4 0. 06 0. 05 0. 02 2. 8 remainder 8005a 8005a 67.4 3.3 2.3 0.31 0.9 remainder 8006aI 8006a 63. 8 2. 8 2. 9 0. 06 0. 07 2. 1 remainder 8007a 8007a 71. 5 3. 9 1. 5 0. 20 1. 4 remainder 8008 8008a 64. 2 2. 9 2. 4 0. 3 0. 28 2. 1 remainder 8009a 68. 8 3. 4] 1. 0 1. 5 0. 07 0. 20 1. 7 remainder 8010 8010a 65. 3 2. 8 0. 05 0. 13 2.2 remainder L L A- S T 0

OFQC\

[Table 1 8]1 alloy composition (wt%) N o.

N oI Bi ~nTi1 e S e P Mn Z n 8011. 66.8 .3.3 1.9 2.1 0.04 0.05 0.05 2.3 remainder 8011a 8012 75. 1 4. 1 0. 4 2. 4 0. 03 1. 8. remainder 8013 _74. 2 3.9 0.5 1. 8 0. 10 0. 04 1. 7 remainder 8013a 8014 8014a 77.1 4.2 0.4 2.1 0.32 2.0 remainder 8015a 8016 _64. 4 2. 9 2. 7 0. 23 0. 09 0. 13 1. 8 remainder 8016aI 8017a 68. 3 3. 6 0. 4 0. 05 0. 05 0. 04 2. 2 remainder 8018a 8018a 73. 2 4. 3 0. 5 0. 06 0. 02 0. 11 0. 02 3. 1 remainder 8019 8019a 72. 4 4. 1 0. 7 0. 14 0. 21 2. 1 remainder 80201 8020a 169. 5 3. 7 0. 7 0. 06 0. 04 0. 05 1. 9 remaine [Table 1 9] alloy composition (wt%) No Cu S i S n AlI B i 'e Se P Mn Zn 8021 8021a 64. 2 3. 4 2. 5 0. 31 0. 03 1. 9 remainder 8022a 8023 8023a 67. 1 3. 6 0. 4 0. 5 0. 04 0. 05 0. 05 12. 0 remainder 8024 8024a 73. 2 4. 0 0. 5 2. 1 0. 03 0.,05 0. 12 2. 4 remainder 8025a 68. 8 3. 5 0. 4 1. 8 0. 12 0. 03 0. 03 0. 04 1. 8 remainder 8026aI 8026a_ 66.5 3.4 1.2 0.3 0.24 0.21 1.7 remainder 8027 27a 64. 8 3. 0 1. 3 1. 2 0. 16 0. 10 0. 06 1. 5 remainder 8028 8028a 71. 2 3. 9 0. 4 1. 0 0. 14 0. 03 2. 6 remainder 8029 82a 68. 1 3. 6 0. 2 0. 05 2. 0 remainder S 09 8030 8030a 64. 9 2. 9 0. 3 0. 28 0. 08 1. 0 remainder I

OF~

i f, i, F [Table 2 0]1 N ~alloy composition (wt%) 01 7. .9 21 0 70. 04 0. 8 remainder 802 77.2 4.3 2.3 0.03 0.25 0.04 2.8 remainder 03 64. 7 2. 8 2. 2 0. 33 0. 9 remainder 04 69. 3 3. 5 1. 6 0. 03 0. 03 1. 8 remainder -83 712 38 150. 21 2. 0 remainder 06 70.6 3.7 0.3 0.04 0. 13 1.7 remainder 07 69 7 3.8 1.4 0.12 0.04 0.04 1.8 remainder 08 70.7 4.2 1.5 0.03 0.16 0.03 3.3 remainder 09 70.4 3.9 0.2 0.15 0.10 0.02 0.04 2.2 remainder 800 68. 8 3. 7 0. 4 0. 05 0. 12 1. 9 remainder [Table 2 1] N ~alloy composition (wtOO No Cu S i S n AlI B i T e S e P Mn N i Z n -8041a 70.3 3.9 0.2 0.20 0.03 0.22 2.1 remainder 8042a -8042a 74.6 4.3 2.1 0.12 0.03 2.4 remainder 8043a -8043a 77. 0 4. 5 0.03 0.12 1.7 remainder 8044a reane -8044a 70.6 3.9 0.10 0.06 0.04 2.6reanr 8045a 8045a 74.2 4.3 0.11 0.21 0.16 2.8 remainder 8046a 8046a 69.9 3.8 0.06 0.11 0.03 0.08 1.2 remainder 8047a 8047a 66.8 3.4 0.09 0.06 2.2 remainder 8048a 8048a 71.3 4.2 0.04 0.05 0.05 1.4 remainder 8049- 72. .4 4. 1 0.12 0.09 2.7 remainder 8050a1 8050a 62. 9 j 2. 8 2J8 0.12 1.5 remainder SOF i* [Table 2 2] N o. Cu S alloy composition_(wt%) r T nIAI j.Bi ITe ISerNil Zn 805CZ1 64. 8 3. 1 0. 08 0.03 remainder 8052 68. 9 3. 9 0. 3 0. 03 0. 06 1. 8 remainder- 8052a 8053a -8054 66. 5 3. 8 0. 9 0. 31 2. 2 remainder 8054a 8055a -80556 73.28 4.4 3 1.310.0 0. 05 3. 3 remainder 8056a -8057a 74.1 2 3.84 1.5 3 0.0 03 1.87 remainder 8057a -8057a 670.1 3. .8 1.5 1.96 0.06 1.89 remainder 8058a -8058a 67.9 2.96 2. 3 0.16 0.0 6 0.0 .9 remainder 8059a x8060a 66. 6 3. 5 1. 8 0. 2 0. 10 0. 05 0. 05 1. 2 remainder [Table 2 3] alloy composition No Cu S i S n AlI B i T e S e P N i Z n 8061a 67.6 3.6 0.4 0.6 0.30 1.8 remainder 8062a 8062a 68. 8 3. 0 0. 6 2. 1 0. 08 0. 03 1. 1 remainder 8063a -8063a 71.2 4.1 2.4 0.8 0.31 2.2 remainder 8064a -8064a 68. 2 3. 6 2. 6 0. 04 0. 05 1. 5 remainder 8065a -8065a 63. 9 2. 9 2. 3 0. 32 0. 02 0. 08 0. 8 remainder 8066a -8066a 70. 5 3. 9 1. 1 0. 05 0. 05 0. 05 2. 2 remainder 8067 67.7 3.7 1.2 0.09 0.03 0.02 0.04 2.0 remainder 8067a____ 8068 8068a 66.6 3.5 1.4 0.06 0. 04 2.6 remainder 8069a 8069a- 72.63 4.01 0.460.0 0.104 0.05 3.20 remainder 8070a [Table 2 4] N o. Cu- Si Sn -8071a 75. 6 3. 9 0. 5 8072a 02 71. 2 3. 4 0. 7 alloy composition_(wt%) I Te I Se Ni 0. 21 0.21 remainder I I I i i t 0. 18 0.10 0. 14 remainder 8073 68.5 3.7 0.7 1.2 0.03 0.08 0.03 1.9 remainder 8073a 8074a 8075a 64.39 3.3 2 2.8 0. 4 2 0. 03 0.04 050 1.58 remainder 8075a 80756 65.8 3 4.03 2.58 0.62 0.0 06 1 0.05 1.75 remainder 8076a 8077a 68.8 34 2.1 .6 0.05 0.13 0.03 2.7 remainder 8077a 80787a 7.0 3 4.1 42..2 5 00.01031 2.14 remainder 8078a 8078a 77.0 4.8 11.2 0.0 13 2 2.1 remainder 8079a 8080 8080a 68. 2 3. 6 .13 0. 04 0. 05 2. 6 remainder [Table 2 5]1 N alloy composition (wt%) No Cu S i AlI B i T e S e P N i Z n -8081a 67.3 3.4 0.8 0.05 0.06 0.03 1.7 remainder 8082a 8082a 70.4 3.9 1.2 0.05 2.2 remainder.

8083a -8083a 73. 6 3. 9 1. 3 0. 21 0. 06 3. 1 remainder 8084a -8084a 68. 8 3. 8 1. 2 0. 18 2. 6 remainder 8085a -8085a 67. 5 3. 5 L:2 0. 04 0. 16 1. 8 remainder 8086a -8086a 64. 9 2. 9 1. 6 0. 08 0. 04 0. 05 1. 5 remainder 8087a -8087a 76. 3 4. 3 1. 5 0. 29 0. 05 0. 10 2. 8 remainder 8088a -8088a 65. 8 2. 8 2. 3 0. 16 0. 06 0. 03 0. 05 1. 3 remainder 8089a 808968a 66. 7 13. 3 2. 1 0. 32 0. 03 1. 8 remainder 8090a. 69. 2 14. 0 1. 2 0. 11 0. 02 0. 10 2. 5 remainder

T

[Table 2 6] alloy composition (wt%) N o. Cu Si Sn Al Bi Te Se P Mn Ni Zn 8091 70.6 3.8 1 3 0.14 0.05 1.7 remainder 8091a 8092 67.2 3.4 0.05 0.04 2.0 remainder 8092a 8093 65.8 3.2 0.15 0.03 0.06 1.2 remainder 8093a 8094 67.7 3.7 0.06 0.10 0.08 2. 1. remainder 8094a 8095 64 7 2 9 0.31 0.04 0.05 0. 09 1. 5 remainder 8095a 8096 66.5 3.6 0.18 0.21 2.3 remainder 8096a 8097 67.3 3.8 0.08 0.05 0.12 2.2 remainder 8097a 8098 65.9 3 6 0.21 0.20 2.5 remainder 8098a 8099 64.9 3.6 0.4 0.18 0.8 2.6 remainder 8099a 8100 67. 3 3. 8 1.8 0.03 0.06 1.9 1. 0 remainder 8100a [Table 2 7] alloy composition (wt%) No. Cu Si Sn Al Bi Te Se Mn Ni Zn 8101 8101 62. 9 2. 9 2.4 0.20 0.16 1.3 0.9 remainder 8101a 8102 66.3 3.4 0.5 0.04 0.04 0.05 1.5 0.8 remainder 8102a 8103 65.8 3.8 2.6 0.03 1.4 1.2 remainder .8103a 8104 8104 64. 7 3. 6 2. 7 0. 25 0. 03 1. 3 1. 6 remainder 8104a1 8105 8105 70.4 3.9 1.8 0.07 1.0 2.0 remainder 8105a 8106 70.3 3.8 0.4 1.8 0.05 2.3 0.7 remainder 8106a 8107 81 72.1 3.7 0.4 2.1 0.03 0.05 1.3 1.2 remainder 8107a 8108 0 69.8 3.8 0.6 1.5 0.05 0.05 1.5 2.1 remainder 8108a 8109 81 75.4 4.2 0.6 1. 8 0.05 0.04 0.04 2.3 1. 1 remainder 8109a 8110 S. 66.4 3.5 2.5 0.2 0.12 1.6 0.9 remainder 8110a [Table 2 8] No Cu Si S 8111 64.9 3.3 1 ___alloy composition n I AlI Bi I. Te I Se]I P 1MnN Z n 0. 3 0. 08 0. 05 remainder 8112a 70.0 3.8 1.2 0.5 0.03 1.5 0.8 remainder 8113a 72.0 3.9 1. 1 0.25 0.20 2.4 0.9 remainder 8114a 8114a 66.5 3.6 1.2 0.06 0.04 0.05 1.3 1. 1- remainder 8115a 8115a 67. 0 3. 5 1. 3 0. 12 0. 04 0. 08 0. 9 1. 2 remainder 81-1a1 8116a_ 64. 0 2. 8 2. 6 0. 30 0. 08 0. 03 0. 05 0. 8 1. 0 remainder 81176 7.a. .300 eane 8 117a 8118a 66.4 3.8 2.4 0.05 0.15 0.03 1.0 1.6 remainder k8119 -8119a 70.2 3.9 0.5 0.30 0.07 1.7 0.9 remainder 8120a -8120a 73.1 4.2 0.5 2.3 0.04 0. 14 2.0 1. 1 remainder [Table 2 9] Nalloy composition No Cu S i S n AlI B i TPe S e P Mn N i Z n 8121a 71. 0 3. 6 0. 6 2. 3 0. 03 0. 12 0. 20 1. 8 1. 0 remainder 8122a 8122a 70. 0 3. 5 0. 5 1. 8 0. 06 0. 03 0. 10 1. 2 1. 3 remainder 8123a 8123a 66.5 3.4 0.5 0.7 0.30 0.03 0.02 0.03 1.0 1.5 remainder 8124aI 8124a 68.8 3.9 1.2 0.2 0.06 0.05 1.0 1.2 remainder 8125a 8125a 64. 9 3. 0 1. 8 0. 5 0. 25 0. 05 0. 05 1. 1 0. 8 remainder 8126 -63.7 2.9 2.7 1.0. 0.31 0. 03 1.2 0.8 remainder 8127a 8127a 70.4 3.9 0.2 0.04 1.6 1.3 remainder 8128a 8128a 66. 5 3. 6 0. 3 0. 02 0. 04 1. 2 1. 1 remainder 8129a 8129a 67. 3 3. 7 0. 7 0. 03 0. 08 1. 3 1. 2 remainder 8130 I II 8130a 66. 0 3. 4 0. 7 0. 22 10. 06 10. 04 1 11. 3 11. 0 reane F o) *MT~ 41 41. WZ [Table 3 0] alloy composition (wt%) N No. Cu Si Al Bi Te IS e- P M i Z 8131a 68.0 3.8 0.8 0.05 1. 1 1 .4 remainder 8132a -8132a 70. 0 3. 4 2. 1 0. 03 0. 22 0. 9 1. 1 remainder 8133a -8133a 75.5 4.2 2.2 0.05 1.2 1.9 remainder 8134a 8134a 68. 5 3. 8 1. 8 0. 10 0. 04 1. 4 1. 6 remainder 8135a 8135a 76. 5 4. 3 2. 1 0. 03 0. 10 0. 15 1. 6 1. 3 remainder 8136a 8136a 66. 5 3. 6 1. 2 0. 05 0. 16 0. 05 1. 2 1. 3 remainder .8137a -8137a 72.0 4.1 1.0 0.04 0.03 0.02 0.07 1.3 2.2 remainder 8138a -8138a 70. 2 4. 0 1. 0 0. 04 0. 03 2. 1 1. 4 remainder 8139a 8139a 66. 8 3. 8 0. 5 0. 32 0. 03 0. 03 1. 2 1. 6 remainder 8140a 8140a 67.3 3.9 0.4 0.05 0.03 1.8 1.0 remainder [Table 3 1] alloy composition (wt%) No Cu Si B i T e S e P Mn N i Z n 8141a 66.5 3.6 0.05 0.05 1.5 1.2, remainder 8142a 8142a_ 63. 9 2. 9 0. 30 0. 03 0. 04 1. 2 0. 9 remainder 8143a 8143a 68.4 3.8 0.03 0.05 0.12 0.9 2.5 remainder 8144a 8144a 65. 8 3. 4 0. 10 0. 05 0. 02 0. 03 1. 0 1. 4 remainder 8145 8145a 70 5 3. 9 0. 12 0. 05 2. 6 0. 8 remainder 8146.

8146a 72. 0 4. 2 0. 04 0. 05 0. 18 1. 0 2. 4 remainder- 8147a1 68. 0 3. 7 0. 20 0. 06 1. 5 1. 0 remainder 0Ez Q V [Table 3 2]1 a lloy copsition No Cu -Si AlI P Z n 9001 '72. 6 2. 3 0. 8 j0. 03 remainder 9002 74. 8 2. 8 1. 3 0. 09 remainder 9003 77. 2 3. 6 0. 2 j0. 21 remainder 900 900 75~ 7 1. 1 1 0. 07 remainder 4 75.7 5 78. 0 0.7 1 0.12 remainder [Table 3 3]1 N alloy composition (wt%) No Cu S i AlI P C r Ti Zn 10001 74. 3 2. 9 0. 6 0. 05 0. 03 [remainder -1000-2 74. 8 3. 0 0. 2 0. 12 0. 32 1remainder 10003 74. 9 2. 8 0. 9 0. 08 0. 33 remainder 10004 77. 8 3. 6 1. 2 0. 22 0. 08 remainder 10005 71. 9 2. 3 1. 4 0. 07 0. 02 0. 24 remainder 10006 76. 0 2. 8 1. 2 0. 03 0. 15 remainder 10007 75. 5 3. 0 0. 3 0. 06 0. 20 remainder F10008 71. 5 2. 2 0. 7 0. 12 0. 14 0. 05 remainder [Table 3 4] N alloy composition No Cu S i AlI P B i T e S e Z n 11001 74. 8 2. 8 1. 4 0. 10 0. 03 remainder- 11002 76.1 3.0 0.6 0.06 0.21 remainder 11003 78. 3 3. 5 1. 3 0. 19 0. 18 remainder 11004 71.7 2.4 0.8 0.04 0.21 0.03 remainder 11005 73. 9 2. 8 0. 3 0. 09 0. 33 0. 03 remainder 11006 74.8 2.8 0.7 0.11 0.16 0.02 remainder 11007 178. 3 3. 8 1. 1 10. 05 0. 22 05 0. 04 remainderj [Table 3 alloy composition (wt%) Co Cu Si -A I B i ITe Se P C i Z 12001 73.8 2.6 0.5 0.21 0.05 0.11 remainder 12002 76. 5 3.2 0.9 0.03 0. 11 0.03 remainder 12003 78. 1 3.4 1.3 0.09 0. 20 0. 05 remainder 12004 70. 8 2. 1 0.6 0.22 0.06 0. 08 0. 32 remainder 12005 77.8 3.8 0.2 0.02 0.03 0.03 0.26 remainder 12006 74. 6 2.9 0.7 0.15 0.02 0. 10 0.06 remainder 12007 73. 9 2. 8 0. 3 0.04 0.05 0.16 0. 03 0. 18 remainder 12008 75.7 2.9 1.2 0.03 0. 12 0.05 remainder 12009 72. 9 2. 6 0.5 0. 33 0. 04 0. 12 remainder 12010 76.5 3.2 0. 3 0.32 0. 03 0. 35 remainder 12011 71.9 2.5 0.8 0.19 0.03 0.03 0.03 remainder 12012 74.7 2.9 0.6 0.07 0.05 0. 21 0.06 remainder 12013 74.8 2.8 1.3 0.04 0.21 0. 06 0.26 remainder 12014 78.2 3. 8 1. 1 0.22 0.05 0.03 0. 04 0.24 remainder 12015 74.6 2.7 1.0 0.15 0. 03 0.02 0.10 remainder 12016 75.5 2.9 0.7 0.22 0. 05 0. 34 0.02 remainder 12017 76.2 3.4 0.3 0.05 0. 12 0.08 0.31 remainder 12018 77.0 3.3 1. 1 0.03 0.14 0. 03 0. 05 0.03 remainder 12019 73.7 2.8 0.3 0.32 0.03 0. 10 0.03 0.19 remainder 12020 74.8 2.8 1.2 0.02 0.14 0. 05 0.14 0.05 remainder 12021 74.0 2.9 0.4 0.07 0.05 0.05 0.08 0.11 0.26 remainder [Table 3 6 alloy composition heat treatment 0. C u S i Z n temperature time 13001 78. 5 3. 2 remainder 580°C 13002 78. 5 3. 2 remainder 450°C 2hr.

13003 77. 0 2. 9 remainder 580'C 13004 77. 0 2. 9 remainder 450°C 2hr.

13005 69. 9 2. 3 remainder 580°C 13006 69. 9 2. 3 remainder 450°C 2hr.

V~4~'ZSkv 2 4~SC W~-~t~V~t'ZS Table 3 7] N _alloy composition (wt%) No Cu Si Sn Al Mn Pb Fe Ni Zn 14001 58.8 0.2 3.1 0.2 remainder 14001a 14002 61.4 0.2 3.0 0.2 remainder 14002a 14003 59.1 0.2 2.0 0.2 remainder 14003a 14004 69.2 1.2 0.1 remainder- 14004a 14005 14005 remainder 9.8 1.1 3.9 1.2 14005a 1 14006 140a 61. 8 1.0 0. 1 remainder 14006a Table 3 8 corrosion hot work- mechanical stress machinability resistance ability properties resistance N o. form conditi- cutti- maximum 7 0 0°C tensile elongat- corrosion of on of ng depth of deformabi- strength ion cracking chipp- cut force corrosion lity (N/mm 2 resistance ings surface (g m) 1001 A A 1 4 6 2 9 0 0 470 32 A.

1002 0 122 210 0 524 36 0 1003 0 119 190 0 543 34 0 1004 0 126 170 A 590 37 0 1005 A 0 1 3 4 1 5 0 A 532 42 0 1006 A 129 230 0 490 34 0 1007 A 0 132 170 A 512 41 0 1008 A A 1 3 7 270 0 501 31 A Table 3 9] 1 machinability 4 form of chippi no5s condition of cut surface cutting force

(N)

corrosion resistance maximum depth of corrosion (urnm) 7 0 0 °C deformability hot workability tensil streng

(N/

mechanical properties_ e elongatgth ion mm 2

I

stress resistance corrosion cracking resistance 2001 0 0 116 190 O 523 34 0 2002 0 117 190 0 508 36 0 2003 0 118 180 0 525 36 0 2004 0 119 280 A 463 28 A 2005 0 119 240 A 481 30 0 2006 0 119 170 A 552 36 0 2007 O 116 180 0 520 41 0 2008 0 115 140 A 570 34 0 2009 0 117 200 A 485 31 0 2010 0 114 180 0 507 34 0 2011 O 115 170 A 522 33 0 Table 4 0 corrosion hot work- mechanical stress machinability resistance ability properties resistance N o. form conditi- cutti- maximum 7 0 0 °C tensile elongat- corrosion of on of ng depth of deformabi- strength ion cracking chipp- cut force corrosion lity (N/mm' resistance ings surface m) 3001 A 128 40 0 553 26 0 3002 0 126 130 A 538 32 0 3003 O 12 6 50 0 52 6 28 0 3004 0 0 119 <5 0 533 36 0 3005 O 125 50 0 525 28 0 3006 0 120 <5 0 546 38 0 3007 O0 1 2 1 <5 O 5 5 2. 3 4 0 3008 O 12 2 80 0 570 36 0 3009 0 0 123 50 0 541 29 0 3010 O0 1 18 <5 0 560 35 0 3011 O0 119 20 0 502 34 0 3012 O 120 <5 O 534 31 0 r~ Table 4 11 machinability corrosion resistance hot workability form of chippincgs condition of cut surface cutting force

(N)

maximum depth of corrosion (urn) 7 0 0 C deformability tensi stren

(N/

mechanical properties le elongatgth ion 'mm 2 stress resistance corrosion cracking resistance 4001 0 1 1 9 4 0 A 51 2 2 4 0 4002 0 1 2 2 5 0 0 54 3 3 0 0 4003 0 1 2 3 .5 0 0 53 3 3 0 0 4004 0 1 1 7 8 0 A 5 2 0 3 1 '0 4005 1 19 5 0 0 5 3 5 3 2 0 4006 0 1 1 6 6 0 0 5 3 2 3 1 0 4007 0 0 1 2 2 5 0 0 52 8 2 6 0 4008 0 1 2 4 1 00 A 5 5 4 3 0 0 4009 0 1 1 9 1 3 0 0 54 2 3 4 0 4010 0© 0 1 1 9 1 2 0 5 6 2 3 5 0 4011 0 1 22 1 00 0 56 3 3 4 0 4012 0 1 1 9 1 3 0 0 5 2 4 4 0 0 4013 0 1 2 0 1 1 0 0 5 4 8 3 7 0 4014 0 1 2 0 1 20. A 5 3 9 3 6 0 4015 0 1 2 1 4 0 0 52 8 2 8 0 4016 0 1 2 2 6 0 0 59 7 3 2 0 4017 0 1 2 0 50 52 0 3 3 .0 4018 0 12 3 6 0 0 55 3 3 1 0 4019 0 11 8 4 0 0 6 0 6 2 4 0 4020 1 0 1 2 0 4 0 0 56 1 2 6 0 1 w A Table 4 2] corrosion hot work- mechanical stress machinability resistance ability properties resistance N o. form conditi- cutti- maximum 7 0 0 °C tensile elongat- corrosion of on of ng depth of deformabi- strength ion cracking chipp- cut force corrosion lity (N/mm 2 resistance ings surface (g mn) 4021 0 1 2 0 50 0 540 29 0 4022 1 2 3 <5 0 487 32 A 4023 0 1 1 7 <5 0 524 34 0 4024 0 1 1 7 40 0 541 37 0 4025 0 1 1 5 <5 A 526 43 0 4026 0 1 2 2 30 0 498 30 A 4027 0 1 1 8 30 0 5 1 6 35 0 4028 O 1 2 0 <5 0 529 27 0 4029 0 1 2 1 <5 0 5 4 4 28 0 4030 0 1 1 8 <5 0 536 30 0 4031 0 1 1 6 <5 0 524 31 0 4032 0 1 1 4 <5 0 5 1 5 32 0 4033 0 1 1 8 <5 0 5 1 9 37 0 4034 0 1 1 8 <5 0 582 31 0 4035 0 1 1 7 <5 0 538 32 0 4036 0 1 1 8 <5 A 600 34 0 4037 0 117 20 0 523 34 0 4038 0 1 1 6 <5 A 539 38 0 4039 0 1 1 8 20 0 5 4 4 34 0 4040 0 117 40 0 5 2 2 31 0 Table 4 3] corrosion hot work- mechanical stress machinability resistance ability properties resistance N o. form conditi- cutti- maximum 7 0 0°C tensile elongat- corrosion of on of ng depth of deformabi- strength ion cracking chipp- cut force corrosion lity (N/mm 2 resistance ings surface (g m) 4041 0 1 2 0 20 0 565 31 0 4042 0 119 <5 0 567 34 0 4043 1 2 1 <5 0 5 3 0 29 0 4044 0 1 2 0 <5 0 548 31 0 4045 0 1 2 1 <5 0 572 32 0 4046 0 1 1 9 <5 0 579 29 0 4047 0 0 123 <5 0 542 26 0 4048 0 1 2 3 <5 0 540 28 0 4049 0 1 2 0 <5 0 539 33 0 &a'^i^^^gtss~iMs~lsga5777Ws,, Table 4 4 y corrosion hot work- mechanical stress machabilitresistance ability properties resistance N o. form conditi- cutti- maximum 7 0 0°C tensile elongat- corrosion of on of ng depth of deformabi- strength ion cracking chipp- cut force corrosion lity (N/mm 2 resistance ings surface (g m) 5001 A 1 27 30 5 0 1 25 0 5002 0 1 1 9 <5 5 2 4 37 0 5003 A 135 1 0 0 488 41 0 5004 1 2 6 2 0 A 55 2 3 8 0 5005 O 1 2 3 <5 5 1 8 29 0 5006 1 2 2 <5 5 2 0 34 0 5007 L A 125 <5 0 507 23 O 5008 O 122 <5 0 515 30 0 5009 0 1 2 4 <5 0 544 35 0 5010 0 123 <5 A 536 36 0 5011 A 12 6 <5 5 1 1 2 7 5012 0 124 <5 5 9 6 36 0 5013 0 119 <5 0 519 39 0 5014 0 122 <5 0 523 37 O 5015 0 123 <5 0 510 40 0 5016 0 1 2 0 2 0 0 4 9 0 3 5 A 5017 0 1 2 1 <5 0 573 40 0 5018 0 1 2 0 <5 0 5 4 9 39 0 5019 0 1 2 2 5 0 0 5 37 3 0 0 5020 1 0 118 <5 0 5 2 1 37 0 Table 4 5 r machinability corrosion reai tanc hot workahi ]i tv mechanical properties essac ility- N o. form of chipp- 1 no.

condition of cut surface cutting force

(N)

maximum depth of corrosion (um) 7 0 0 C deformability tensile strength (N/mm 2 elongation stress resistance corrosion cracking resistance 6001 0 1 2 1 30 0 5 1 2 24 0 6002 0 1 2 2 <5 0 5 7 4 31 0 6003 0 1 1 7 <5 A 5 0 1 32 0 6004 0 1 2 0 <5 0 5 1 4 26 '0 -6005 0 1 2 1 <5 A 525 42 0 6006 0 0 1 1 5 <5 0 5 1 4 32 0 6007 0 1 2 0 <5 0 548 27 0 6008 0 1 1 9 <5 0 5 0 3 30 0 6009 0 1 1 7 <5 0 5 2 2 38 0 6010 0 1 2 2 <5 A 527 41 0 6011 0 119 <5 0 536 32 0 6012 0 1 2 3 20 0 478 27 A 6013 0 1 1 8 <5 0 506 30 0 6014 0 1 1 8 <5 O 5 2 5 39 0 6015 0 0 114 <5 0 5 0 3 35 0 6016 0 1 2 2 40 0 5 2 6 27 0 6017 0 1 1 9 <5 A 5 0 7 30 0 6018 0 1 2 1 <5 0 5 8 9 31 0 6019 0 12 0 <5 0 508 25 0 6020 0 121 <5 A 504 43 0 [Table 4 6] machinability corrosion resistance hot workability mechanical properties form of chipp- 1 nayc condition of cut iirfacf cutting force

(N)

maximum depth of corrosion (urn') 7 00°

C

deformability tensile strength (N/mm 2 elongation st: re

CO:

crn re; ress sistance rrosion acking sistance 6021 0 1 1 6 <5 O 501 33 0 6022 0 120 <5 0 5 4 7 29 0 6023 0 0 1 1 9 <5 0 5 2 3 30 0 6024 0 1 2 0 <5 A 5 2 5 40 '0 6025 0 1 2 0 <5 0 496 30 0 6026 0 0 114 <5 0 5 1 8 34 0 6027 0 1 1 9 <5 0 487 28 A 6028 0 1 1 8 <5 0 524 35 0 6029 0 1 2 2 <5 A 540 41 0 6030 0 1 1 8 <5 0 .5 1 1 29 0 6031 0 1 1 9 40 0 5 1 9 28 0 6032 0 1 2 0 <5 0 572 32 0 6033 0 1 2 3 <5 A 5 1 5 36 0 6034 0 1 2 2 <5 0 5 8 0 35 0 6035 0 123 <5 0 5 1 7 27 0 6036 0 1 2 1 <5 0 503 26 0 6037 0 0 1 1 7 <5 0 5 3 6 30 0 6038 0 116 <5 0 506 30 0 6039 0 1 2 0 <5 0 4 8 5 28 A 6040 0 0 116 <5 0 5 2 8 36 0

-I^

Okn^ Table 4 7] corrosion hot work- mechanical stress machinability resistance ability properties resistance N o. form conditi- cutti- maximum 7 0 0°C tensile elongat- corrosion of on of ng depth of deformnnabi- strength ion cracking chipp- cut force corrosion lity (N/mm 2 resistance ings surface (Cum) 6041 0 1 1 7 <5 0 4 9 6 30 0 6042 0 1 2 0 <5 A 574 34 0 6043 0 1 2 3 10 A 506 43 0 6044 0 1 1 5 10 0 5 0 0 30 '0 6045 0 1 1 9 20 A 485 27 A 6046 0 1 21 40 0 5 1 2 24 0 6047 0 1 2 3 <5 0 557 25 0 6048 0 1 2 0 <5 0 526 30 0 6049 0 1 2 0 <5 0 502 24 0 6050 0 1 2 4 <5 0 4 8 0 31 0 6051 0 0 1 1 7 <5 0 5 3 4 32 0 6052 0 1 2 3 <5 A 523 38 0 6053 0 1 2 3 <5 0 5 0 6 39 0 6054 0 .1 1 5 <5 0 4 8 5 31 0 6055 0 1 2 2 <5 A 5 1 2 44 0 6056 0 1 2 0 <5 0 4 8 0 33 A 6057 0 1 2 1 <5 0 479 25 A 6058 0 0 1 1 6 <5 0 525 34 0 6059 0 1 1 9 20 0 482 35 0 6060 0 0 1 1 8 30 0 5 1 3 38 0 *^K^^^''K5i^'iSg^WWS5y3':^f*- Table 4 8]1 machinability form of.

chipp- 1 nflS condition of cut cutting force corrosion resistance maximum depth of corrosion 7 0 0 0

C

deformabi- 1 ity tensile strength (N/mm 2 hot workability mechanical properties elongation

M%

stress resistance corrosion.

cracking resistance 6061 0 1 23 3 0 0 5 30 2 2 0 6062 0 1 19 1 0 0 5 38 3 3 0 6063 0 1 18 <5 0 5 04 3 7 0 664 0 1 21 5 0 5 26 3 0 0 6065 0 1 23 5 0 5 65 3 5 0 6066 0 1 20 5 .0 5 01 2 5 0 6067 0 1 19 0 5 26 2 6 0 6068 0 1 22 5 .0 5 02 3 0 0 6069 0 1 24 5 0 4 84 2 8 A 6070 0 0 1 1 5 5 0 5 48 3 7 0 6071 0 1 18 5 0 5 30 3 4 0 6072 0 1 19 5 0 5 15 3 0 0 6073 0 1 21 <5 AL 5 79 3 5 0 6074 0 1 17 5 0 5 17 3 2 0 6075 Q 0 1 17 5 0 5 13 3 8 0 6076 0 1 22 4 0 0 5 35 2 8 0 6077 0 0 1 19 5 0 4 90 3 0 0 6078 0 1 22 <5 AL 5 13 4 0 0 6079 0 1 18 5 0 15 24 13 0 0 6080 1 0 13 5 0 14 82 13 5 0 Table 4 9] machinabilitY mechanical stress corrosion resistance hot workability mechanical properties 4 T N o.

form of chippings condition of cut surface cutting force

(N)

maximum depth of .corrosion (Am) 7 0 0 °C deformability tensile strength (N/mm 2 elongation

(M)

stress resistance corrosion cracking resistance 11R <5 1 0) 1 536 1 34 1 0 6082 0 1 2 3 <5 0 5 1 0 2 5 0 6083 0 1 1 9 <5 0 5 0 4 32 0 6084 0 1 1 7 <5 0 5 3 3 34 "O 6085 0 1 1 8 1 0 0 5 0 1 3 0 0 6086 0 1 1 7 <5 0 54 5 37 0 6087 0 1 19 <5 0 5 0 3 34 0 6088 0 0 1 1 5 <5 0 52 6 36 0 6089 0 1 1 9 <5 0 5 1 4 3 9 0 6090 0 0 1 2 1 2 0 A 4 8 0 3 5 0 6091 0 1 2 2 3 0 0 5 1 6 2 4 0 6092 0 1 1 8 <5 0 5 3 2 3 0 0 6093 0 1 9 <5 0 5 3 9 34 0 6094 0 0 1 7 <5 0 5 2 8 3 2 0 6095 0 1 9 <5 0 5 0 7 3 0 0 6096 0 1 2 2 <5 0 5 0 8 2 2 0 6097 0 11 7 <5 0 5 1 0 3 1 0 6098 0 1 1 7 <5 0 5 2 7 3 2 0 6099 0 1 1 6 <5 0 5 2 9 3 4 0 6100 0 0 1 1 9 <5 0 5 1 5 32 0 -oT 0 Table 5 0 machinability corrosion resistance hot workability mechanical properties N o.

6101 form of chippings 0 condition of cut surface cutting force

(N)

maximum depth of corrosion m) 70 0°C deformability tensile strength (N/mm') elongation

M%

stress resistance corrosion cracking resistance I I I t I* 115 <5 530 6102 0 1 8 <5 0 5 12 3 6 0 6103 0 1 9 <5 0 5 0 1 35 0 6104 0 1 1 7 <5 0 5 3 5 32 0 6105 0 1 1 7 <5 0 5 1 7 37 0 Table 5 1] hot work- mechanical ability properties N o. form conditi- cutti- 7 0 0°C tensile elongatof on of ng deformabi- strength ion chipp- cut force lity

(M)

ings surface (N) 7001 A 1 3 8 0 6 7 0 1 8 7002 A 1 3 6 0 7 1 2 2 0 7003 0 0 1 3 2 0 7 8 3 2 3 7004 0 1 3 8 0 7 3 6 2 1 7005 0 0 1 3 6 0 7 8 5 2 3 7006 A 1 3 9 0 7 0 0 2 4 7007 A 0 1 3 8 0 7 0 7 2 3 7008 0 1 3 1 0 8 0 5 2 2 7009 0 1 3 6 0 7 6 8 1 9 7010 0 1 3 5 0 7 7 8 2 3 7011 A 0 1 3 7 0 6 7 7 2 3 7012 0 1 3 4 0 8 0 0 2 1 7013 0 1 33 0 8 1 9 2 2 7014 A 0 1.38 0 64 1 2 1 7015 0 1 3 4 0 76 4 2 3 7016 0 1 2 9 0 7 5 9 2 0 7017 A 0 1 3 9 0 6 3 8 1 8 7018 0 1 3 5 0 7 1 7 2 0 7019 1- 0 1 3 6 0 6 9 4 2 4 7020 A 0 1 3 8 0 7 1 2 2 Table 52] machinability hot workability mechanical properties hot work -mechanical abiliy proertie form of chippi ntcs condition of cut surface cutting force

(N)

7 0 0°C deformability tensile strength (N/mm 2 elongation 7021 0 1 3 0 0 754 24 7022 A 1 3 4 0 7 8 0 23 7023 O 133 0 765 22 7024 0 1 3 5 0 772 23 7025 A 0 1 3 8 0 6 8 7 2 4 7026 0 0 1 3 5 0 7 1 8 2 4 7027 A 1 3 6 0 7 4 2 18 7028 A 0 1 3 8 0 7 8 5 2 0 7029 0 134 0 7 0 3 2 3 7030 0 1 3 5 0 8 2 0 18 3] hot work- mechanical machinability ability properties N o. form conditi- cutti- 7 0 0 °C tensile elongatof on of ng deformabi- strength ion chipp- cut force lity (N/mm 2 ings surface 8001 0 0 132 0 655 8002 0 1 2 9 0 7 0 8 17 8003 0 1 2 7 0 7 6 8 8004 0 1 2 8 0 7 8 5 18 8005 0 1 3 1 0 7 1 4 16 8006 0 134 0 680 16 8007 0 132 0 764 17 8008 0 1 3 0 0 673 16 8009 0 1 3 2 0 7 5 9 18 8010 0 1 3 2. 0 7 5 1 8011 0 134 0 767 17 8012 0 0 1 2 8 0 796 18 8013 1 2 9 0' 784 18 8014 0 0 1 2 9 0 802 17 8015 0 1 3 3 0 679 8016 0 0 13 0 0 706 16 8017 0 1 2 9 0 707 18 8018 0 1 3 1 0 780 16 8019 0 1 2 8 0 768 16 8020 0 1 3 2 0 723 19 Table 5 4 machinability hot workability mechanical properties I N o. form of chippi narC condition of cut Qi irfflri cutting force

(N)

7 0 0°C deformability tensile strength (N/mm 2 elongation 8021 0 1 3 4 0 765 16 8022 0 1 3 2 0 7 7 0 16 8023 0 1 3 1 0 746 18 8024 0 132 0 8 1 6 19 8025 0 129 0 7 5 9 18 8026 0 1 3 0 0 7 2 6 1 7_ 8027 0 0 1 3 3 0 7 0 3 1 7 8028 0 1 3 2 0 7 3 7 18 8029 0 129 0 719 8030 0 1 3 3 0 645 23 8031 0 1 2 9 0 764 22 8032 0 1 3 1 0 790 19 8033 0 1 3 3 0 6 7 4 2 0 8034 0 131 0 7 4 8 23 8035 0 1 2 9 0 7 7 7 22 8036 0 1 3 1 0 7 2 5 23 8037 0 1 2 8 0 770 21 8038 0 1 3 1 0 815 18 8039 0 1 2 7 0 739 24 8040 0 130 0 721 22 Table hot work- mechanical machinabiliability properties N o. form conditi- cutti- 7 0 0 °C tensile elongatof on of ng deformabi- strength ion chipp- cut force lity (N/mm 2 ings surface 8041 0 1 2 8 0 7 3 5 23 8042 0 127 0 822 18 8043 0 1 3 1 0 7 8 0 18 8044 0 1 2 6 0 7 2 6 21 8045 0 1 2 8 0 7 6 6 2 2 8046 0 1 2 7 0 7 1 2 23 8047 O 1 2 8 0 6 7 4 21 8048 0 1 2 9 0 7 5 3 24 8049 0 127 0 768 22 8050 0 1 3 2 0 6 9 1 17 8051 0 1 3 1 0 7 1 7 17 8052 0 1 2 8 0 7 3 9 21 8053 0 1 2 8 0 7 3 0 22 8054 0 127 0 735 8055 0 1 3 4 0 8 1 8 8056 0 1 3 2 0 8 1 2 16 8057 0 1 3 1 0 7 5 5 18 8058 0 1 3 3 0 6 5 9 8059 0 1 3 2 0 7 4 0 17 8060 0 130 0 7 1 4 19 Table 5 6 machinability hot workability mechanical properties r form of chippi ns condition of cut surface cutting force

(N)

7 0 0°C deformability tensile strength (N/mm 2 elongation 8061 0 1 2 9 0 7 0 5 2 1 8062 0 13 1 0 6 9 0 2 2 8063 0 133 0 8 1 1 1 8 8064 1 3 1 0 7 4 6 1 7 8065 0 1 33 0 6 5 2 1 9 8066 0 1 3 0 0 7 5 8 1 9 8067 0 1 2 9 0 7 3 4 1 9 8068 0 1 3 1 0 7 1 0 1 7 8069 0 1 3 1 0 7 6 7 8070 0 1 3 1 0 75 3 18 8071 0 1 2 9 0 7 9 2 1 9 8072 0 1 3 1 0 7 3 6 2 1 8073 0 1 3 0 0 7 6 7 2 2 8074 0 1 3 2 0 6 7 9 1 9 8075 0 1 3 4 0 7 2 8 1 7 8076 0 133 0 795 16 8077 0 1 33 0 7 1 6 1 8 8078 0 1 3 2 0 8 0 9 1 8 8079 0 1 2 9 0 7 5 8 22 8080 0 13 0 0 72 4 21 St-4$A Table 5 7 1 machinability hot workability mechanical properties form of chippi ngS condition of cut surface cutting force

(N)

7 0 0C deformability tensile strength (N/mm elongation 8081 0 1 3 2 0 7 0 6 2 3 8082 0 1 3 .0 0 7 6 8 23 8083 0 1 2 8 0 7 7 4 2 8084 0 1 2 9 0 7 6 5 2 2 8085 0 1 3 0 0 7 2 9 2 3 8086 0 1 33 0 6 8 7 2 4 8087 1 3 1 0 7 9 8 2 0 8088 0 1 3 2 0 6 9 9 2 3 8089 0 1 3 0 0 7 4 0 2 1 8090 0 1 3 2 0 7 8 2 1 8 8091 0 1 2 9 0 7 6 3 2 2 8092 0 1 3 0 0 6 8 0 2 2 8093 0 1 3 1 0 6 5 5 2 3 8094 0 1 2 8 0 7 1 4 2 1 8095 0 1 3 2 0 6 3 8 2 4 8096 0 1 2 8 0 6 8 9 2 2 8097 0 1 2 9 0 7 1 1 2 1 8098 0 1 3 0 0 6 9 3 2 0 8099 0 1 2 7 0 70 2 2 1 8100 0 1 2 9 0 7 2 4 1 8 E~a W in~ Table 5 8] I I rnachinability hot workability mechanical properties

I

N o.

8101 810 9 form of chippings condition of cut surface cutting force

(N)

70 0 0C deformability tensile strength (N/mm 2 elongation I

I

1 3 1 S 0 685 1 8 J no) 1 3 2 690 8103 0 1 33 0 7 4 4 17 8104 1 3 0 0 7 2 6 1 7 8105 0 1 33 0 75 1 1 9 8106 0 1 3 0 0 75 2 2 1 8107 0 1 3 1 0 760 21 8108 0 1 3 2 0 7 4 8 2 2 8109 0 1 3 0 0 8 0 7 1 8 8110 0 1 33 0 73 9 1 6 8111 0 1 3 2 0 71 7 17 8112 0 0 1 3 4 0 76 3 8113 0 12 9 0 74 5 22 8114 0 1 3 2 0 7 2 2 2 0 8115 0 1 3 0 0 70 6 1 7 8116 0 1 33 0 68 4 1 9 8117 0 1 3 2 0 74 0 1 8 8118 0 1 3 3 0 76 5 16 8119 0 1 2 8 0 73 3 22 8120 0 1 3 1 0 8 1 9 1 9 Table 5 9] S machinability form of chippings condition of cut surface cutting force

(N)

hot workability 7 0 0 C deformability tensile strength (N/mm elongation mechanical properties I I 8121 P199 1 3 0 0 788 v I 1 I (6) 131 755 8123 0 1 2 7 0 7 1 1 2 1 8124 O 1 3 0 0 76 3 2 0 8125 0 1 3 1 0 68 7 1 8 8126 0 1 3 4 0 70 6 1 7 8127 0 1 2 8 0 73 0 2 2 8128 0 1 3 0 0 70 2 23 8129 0 1 3 2 0 72 7 2 1 8130 0 1 3 0 0 7 0 1 2 4 8131 0 1 2 9 0 74 5 2 2 8132 0 1 3 2 0 74 9 2 1 8133 0 1 3 0 0 82 6 1 8 8134 0 12 8 0 77 0 2 0 8135 0 1 2 9 0 8 2 8 17 8136 0 O 1 2 9 0 74 6 2 0 8137 0 1 3 0 0 78 4 2 3 8138 0 1 3 1 0 77 9 2 1 8139 0 1 2 8 0 7 1 0 2 2 8140 0 1 3 1 0 71 7 22 Table 6 0]1 machinability N o.

R1A1 form of chippings co ndition of cut surface cutting force

(N)

hot workability 7 00 0

C

deformabi- 1 ity mechanical properties tensile strength (N/mm 2 elongation

M%

I 13 C6 8 67 2 2 8142 0 1 30 0 6 35 2 0 8 14-3 0 1 29 0 7 10 2 3 _144 0 1 30 0 6 62 2 4 8145 (Q 0 1 28 0 7 28 2 3 8146 0 0 1 29 0 753 2 1 8147 0 0 1 30 0 7 09 2 4

OS

0 Table 6 1] corrosion hot work- mechanical stress high-temperature machinability resistance ability properties resistance oxidation N o. form conditi- cutti- maximum 7 0 0°C tensile elongat- corrosion ht increase in weight of on of ng depth of deformabi- strength ion cracking by by oxidation chipp- cut force corrosion lity (N/mm 2 resistance 0 ings surface m) 9001 A 1 3 2 2 0 0 5 0 0 37 0 0. 3 9002 0 122 <5 0 564 35 0 0. 2 9003 0 1 2 3 <5 0 5 8 5 39 0 0. 9004 0 118 <5 0 5 5 8 34 0 0. 2 9005 A 0 1 3 2 <5 A 5 9 3 37 0 0. 3 Table6 2] corrosion hot work- mechanical stress high-temperature machinability resistance ability properties resistance oxidation N o. form conditi- cutti- maximum 7 0 0 C tensile elongat- corrosion increase in weight of on of ng depth of deformabi- strength ion cracking i by oxidation chipp- cut force corrosion lity (N/mm 2 resistance g/10 c (e g/10 cm ings surface m) 10001 0 124 <5 0 534 35 0 0. 3 10002 0 1 2 0 <5 0 5 4 0 33 0 0. 2 10003 0 1 2 2 <5 0 5 3 9 38 0 0. 2 10004 0 1 2 4 <5 0 5 7 5 40 0 0. 1 10005 A. 1 2 8 <5 0 5 1 2 33 0 0. 1 10006 0 1 2 0 2 0 0 5 6 0 3 5 0 0. 1 10007 0 1 1 9 0 5 3 6 36 0 0. 3 10008 A 0 1 3 2 <5 0 5 0 1 31 A 0. 1 Table 6 3] machi y corrosion hot work- mechanical stress high-temperature machinability resistance ability properties resistance oxidation N o. form conditi- cutti- maximum 7 0 0°C tensile elongat- corrosion increase in weight of on of ng depth of deformabi- strength ion cracking i by oxidation chipp- cut force corrosion lity (N/mm resistance (m g/10 c m 2 ings surface (um) (gl cm 11001 0 1 1 7 <5 0 5 4 0 36 0 0. 2 11002 0 1 1 7 <5 0 5 3 7 34 0 0. 3 11003 0 1 2 1 <5 A 5 7 3 38 0 0. 2 11004 0 1 1 9 30 0 5 1 2 3 0 0 0. 3 11005 0 0 1 1 4 <5 A 5 1 8 30 0 0. 4 11006 0 118 <5 0 5 3 5 32 0 0. 3 11007 0 1 1 9 <5 A 5 8 6 37 0 0. 2 [Table 6 4]1 corrosion hot work- mechanical stress high-temperature machinability resistance ability properties resistance oxidation N o. form conditi- cutti- maximum 7 0 00(2 tensile elongat- corrosion ices nwih of on of ng depth of deformabi- strength ion cracking increiaeinwih chipp- cut force corrosion lity (N/mm 2 M resistance b xdto ings surface (gum) (mg/0cm 2 12001 0 1 21 5 0 5 12 3 2 0 0. 2 12002 0 1 19 5 0 5 44 3 6 0 0. 2 12003 0 0 1 23 5 0 5 70 3 8 0 0. 1 12004 0 1 24 5 A 4 95 3 1 A 0. 2 12005 0 1 23 3 0 A 5 83 3 2 0 0. 3 12006 0 1 18 5 0 5 37 3 3 0 0. 2 12007 0 1 18 2 0 0 5 16 3 0 0 0. 2 12008 0 1 17 5 0 5 43 3 8 0 0. 1 12009 0 -1 22 2 0 0 5 01 3 2 0 0. 2 12010 0 1 19 3 0 0 5 46 3 5 0 0. 2 12011 0 1 21 2 0 0 5 16 3 1 0 0. 1 12012 0 1 17 5 0 5 39 3 3 0 0. 2 12012 0 1 21 5 0 5 44 3 3 0 0. 1 12014 (9 0 1 21 5 A 5 90 3 7 0 0. 1 12015 0 1 20 2 0 0 5 28 3 2 0 0. 1 12016 0 1 17 5 0 5 35 3 3 0 0. 1 12017 (0 0 1 21 5 0 5 77 3 5 0 0. 2 12018 0 1 20 5 A 5 86 3 7 0 0. 1 12019 0 1 15 5 0 5 20 3 1 0 0. 2 12020 0 1 18 5 0 5 49 3 4 0 0. 1 12021 0© 0 1 16 5 0 5 33 3 4 0 0. 1 1 [Table 65]_

T

machinabilitY corrosion resistance hot workability mechnical properties N o.

13001 form of chippings co ndition of cut cutting force maximum depth of corrosion (g M) 14 0 7 0 0 0

C

deformabi- 1 ity tensile strength (N/mm 2 elongation

M%

stress resistance corrosion cracking resistance surac 1 A 5 521 1 3 13002 0 1 26 1 30 A 524 4 1 0 13003 0 1 27 1 50 A 500 3 8 0 13004 0 1 27 1 60 A 508 3 8 0 13005 0 1 28 1 80 0 4 83 3 5 0 13006 0 1 29 1 70 0 4 88 3 7 0 I'll, Table 6 6 corrosion hot work- mechanical stress high-temperature machinability resistance ability properties resistance oxidation N o. form conditi- cutti- maximum 7 0 0 C tensile elongat- corrosion i e in i. ncrease in weight of on of ng depth of deformabi- strength ion cracking by by oxidation chipp- cut force corrosion lity (N/mm 2 resistance mg/ 2 (mg/10 cm ings surface (gm) 14001 0 0 103 1100 A 4 0 8 37 xx 1. 8 14002 0 0 10 1 1000 x 3 8 7 39 xx 1. 7 14003 0 A 1 1 2 1 0 5 0 0 4 1 4 38 xx 1. 7 14004 x 0 2 2 3 9 00 0 4 3 8 38 x 1. 2 14005 x 0 178 350 A 7 3 5 28 0 0. 2 14006 x 0 2 1 7 6 00 0 4 2 5 3 9 x 1. 8 [Table 6 7] N o.

7001a 7002a 7003a 7004a 7005a 7006a wear resistance weight loss by wear (mg/1OOOOOrot.) 1. 3 0. 8 0. 9 1. 4 1. 3 1. 7 [Table 6 8 wear resistance N o. weight loss by wear (ng/lOOOOOrot.) 7021a 1. 3 7022a 0. 9 7023a 1. 2 7024a 1. 0 7025a 2. 3 7026a 1. 7 7027a 1. 8 7028a 1. 1 7029a 1. 7030a 1. 4 7007a 1. 8 7008a 1. 2 7009a 0. 8 7010a 2. 4 7011a 1. 9 7012a 1. 2 7013a 1. 1 7014a 2. 7 7015a 1. 4 7016a 1. 3 7017a 1. 6 7018a 1. 4 7019a 1. 9 7020a 1. Zr,, 4 Zri~V~rV rr~" r ;Thr,, -<ast. J Table 6 9 N o.

8001a 8002a 8003a 8004a 8005a 8006a 8007a 8008a 8009a 8010a wear resistance weight loss by wear (mg/1OOOOOrot.) 1. 4 1. 1 0. 9 1. 2 1. 8 1. 3 1. 5 1. 0 1. 2 0. 7 [Table 7 0 wear resistance N o. weight loss by wear (mg/lOOOrot.) 8021a 1. 0 8022a 1. 4 8023a 1. 4 8024a 0. 8 8025a 1. 2 8026a 1. 4 8027a 1. 9 8028a 0. 9 8029a 1. 4 8130a 2. 2 8131a 2. 1 8132a 1. 0 8133a 2. 4 8134a 1. 4 8135a 1. 2 8136a 1. 8137a 1. 3 8138a 0. 8 8139a 1. 4 8140a 1. 8011a 1. 0 8012a 1. 3 8013a 1. 4 8014a 1. 3 8015a 1. 5 8016a 0. 9 8017a 1. 4 8018a 0. 9 8019a 1. 0 8020a 1. 5 r I 1 11 Table 7 1] wear resistance N o. weight loss by wear (mg/lOOOOOrot.) 8041a 1. 5 8042a 1. 3 8043a 1. 6 8044a 1. 2 8045a 1. 0 8046a 2. 0 8047a 1. 6 8048a 1. 7 8049a 1. 3 8050a 1. 5 8051a 1. 0 8052a 1. 5 8053a 1. 3 8054a 1. 2 8055a O. 7 8056a 0. 9 8057a 1. 6 8058a 2. 4 8059a 1. 6 8060a 1. 9 [Table 7 2] wear resistance N o. weight loss by wear (mg/lOOOOOrot.) 8061a 1. 6 8062a 1. 9 8063a 1. 2 8064a 1. 7 8065a 2. 0 8066a 1. 4 8067a 1. 8068a 1. 2 8069a 0. 9 8070a 1. 0 8071a 1. 7 8072a 1. 9 8073a 1. 6 8074a 1. 6 8075a 1. 8 8076a 0. 8 8077a 1. 3 8078a 1. 2 8079a 1. 4 8080a 1. 3 -^^R.T.SKtt: I I [Table 7 3]1 wear resistance N a. weight loss by wear (mg/lOOOO0rot.) 8081a 1. 6 8082a 1. 3 8083a 1. 0 8084a 1. 2 8085a 1. 5 8086a 1. 6 8087a 1. 1 8088a 2. 0 8089a 1. 4 8090a 1. 2 8091a 1. 5 8092a 1. 6 8093a 2. 1 8094a 1. 5 -&095a 1. 9 8096a 1. 5 8097a 1. 5 8098a 1. 4 8099a 1. 1 8100a 0. 9 [Table 7 4]1 wear resistance N o. weight loss by wear (ig/lOOGO0rot.) 8101 1. 4 8102 1. 3 8103 0. 8 8104 0. 8 8105 0. 7 8106 0. 9 8107 1. 2 8108 1. 1 8109 1. 0 8110 0. 7 8111 0. 8 8112 1. 2 8113 0. 9 8114 1. 2 8115 1. 1 8116 1. 4 8117 1. 1 8118 0. 9 8119 1. 1 8120 0. 9 72..

A

4< 1 <PAt4~$P2~CW49 >7<4 1 P C Table 7 5] [Table 7 6]1 8121a 8122a 8123a 8124a wear resistance weight loss by wear (nmg/100000rot.) 1. 0 1. 0 1. 2 0. 8 N o.

8125a 1 1 8126a 9 8127a 1. 3 8128a 1. 4 8129a 1. 3 8130a 1. 8131a 1. 2 8132a 1. 3 8133a 0. 8 8134a 1 0 8135a 0. 8 8136a 1. 3 8137a 1. 1 8138a 0. 9 8139a 1. 2 8140a 1. 0 wear resistance weight loss by wear 8141a j 1. 4 8142a 1. 8 8143a 1. 6 8144a 1. 9 8145a 1. 1 8146a 1. 2 8147a 1. 4 [Table 7 7] wear resistance N o. weight loss by wear (ig/iQOOQ0rot.) 14001a 50 0 14002a 6 2 0 14003a 52 0 14004a 45 0 14005a 2 14006a 60 0 ut~:~ciz~n~t C.

Claims

2.4 to 3.7 percent, by weight, of silicon; and the remaining percent, by weight, of zinc. 2. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc.
3. A lead-free free-cutting copper alloy which comprises 70 to percent, by weight, of copper; 1.8 to 3.5 percent, by weight, of silicon; at least one element selected from among 0.3 to, 3.5 percent, by weight, of tin, 1.0 to percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; and the remaining percent, by weight, of zinc.
4. A ead-free free-cutting copper alloy which comprises 70 to percent, by weight, of copper; 1.8 to 3.5 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 1.0 to percent, by weight, of aluminum, and 0.02 to 0.25 percent, -by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weig ht, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; .and the remaining percent, by weight, of zinc. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 0.02 to ~RA 74 0.25 percent, by weight, of phosphorus, 0.02 to 0.15 percent, by weight, of antimony, and 0.02 to 0.15 percent, by weight, of arsenic, and the remaining percent, by weight, of zinc.
6. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.5 percent, by weight, of tin, 0.02 to 0.25 percent, by weight, of phosphorus, 0.02 to 0.15 percent, by weight, of antimony, and 0.02 to 0.15 percent, by weight, of arsenic; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc.
7. A lead-free free-cutting copper alloy which comprises 62 to 78 percent, by weight, of copper; 2.5 to 4.5 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.0 percent, by weight, of tin, 0.2 to percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; and at least one element selected from among 0.7 to 3.5 percent, by weight, of manganese and 0.7 to 3.5 percent, by weight, of nickel; and the remaining percent, by weight, of zinc.
8. A lead-free free-cutting copper alloy which comprises 62 to 78 percent, by weight, of copper; 2.5 to 4.5 percent, by weight, of silicon; at least one element selected from among 0.3 to 3.0 percent, by weight, of tin, 0.2 to 2.5 percent, by weight, of aluminum, and 0.02 to 0.25 percent, by weight, of phosphorus; and at least one element selected from among 0.7 to 3.5 percent, by weight, of manganese and 0.7 to 3.5 percent, by weight, of nickel; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium, and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc.
9. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to percent, by weight, of aluminum; and 0.02 to 0.25 percent, by weight, of phosphorus; and the remaining percent, by weight, of zinc. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of chromium and 0.02 to 0.4 percent, by weight, of titanium; and the remaining percent, by weight, of zinc.
11. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc.
12. A lead-free free-cutting copper alloy which comprises 69 to 79 percent, by weight, of copper; 2.0 to 4.0 percent, by weight, of silicon; 0.1 to percent, by weight, of aluminum; 0.02 to 0.25 percent, by weight, of phosphorus; at least one element selected from among 0.02 to 0.4 percent, by weight, of chromium, and 0.02 to 0.4 percent by weight of titanium; at least one element selected from among 0.02 to 0.4 percent, by weight, of bismuth, 0.02 to 0.4 percent, by weight, of tellurium and 0.02 to 0.4 percent, by weight, of selenium; and the remaining percent, by weight, of zinc. 76 5
13. A lead-free free-cutting copper alloy as defined in claim 1, claim 2, claim.3, claim 4, claim 5, claim 6, claim 7, claim 8, claim 9, claim 10, claim 1 1, or claim 12, which is subjected to a heat treatment for 30 minutes to 5 hours at 400 to 60.0 0 C.
14. A lead-free free-cutting copper alloy as claimed in any preceding claim, a process for its preparation and/or a use thereof substantially as herein described with reference to the Examples and/or drawings. DATED this 6th day of December 2001 SAMBO COPPER ALLOY CO LTD By its Patent Attorneys DAVIES COLLISON CAVE 77