Aluminum 2124

Aging Procedure

Aging, or precipitation hardening in fact, is done at 375 F for a time of approximately 12 hours followed by air cooling.

Annealing Procedure

Annealing is done at 775 F for 2 to 3 hours followed by cooling at 50 F per hour to 500 F. Then air cool.

Applications

Commonly used in the manufacture of aircraft structures.

Cold Workability

Cold working may be done, but the extent of cold working is limited as compared to other aluminum alloys.

Forgeability

No specific data. However the alloy is forgeable.

Formability

Formability of this alloy, which is supplied in plate form, is limited. Severe cold working should be avoided and as with Machinability the optimum condition for forming is the T 851 temper.

Hardening Procedure

Hardening, or strengthening, is accomplished by means of precipitation hardening at 375 F for 12 hours followed by air cooling.

Heat Treatability

The alloy may be solution annealed at 920 F followed by water quench. Precipitation hardening is done at 375 F for 12 hours and air cooling - this produces the T 851 temper.

Hot Workability

No data. It may be advisable to avoid hot working because of the alloy tendency to cracking from heat input.

Machinability

The alloy is machinable by conventional means. Optimum machinability is with the alloy in the T 851 ( precipitation heat treated ) condition.

Other Physical Properties

Electrical conductivity 38% of copper.

Principle Design Features

This alloy is usually supplied in plate form . It responds to heat treatment to develop very good toughness and strength. properties.

Tempering Procedure

Not applicable to this alloy.

Weldability

The alloy has a problem with crack sensitivity during welding. Resistance welding may be successfully used with proper weld procedure. Gas welding and arc welding should be avoided.