Abstract: A method for analysing a bonding between two aeronautical parts. The method includes the steps of a) applying a release agent to a first surface to be bonded of a first part and to a second surface to be bonded of a second part, b) applying an adhesive to at least one of the first and second surfaces and positioning these surfaces on top of each other, the adhesive forming an adhesive film after polymerisation, c) separating the parts from each other and removing the adhesive film in one piece, d) analysing the adhesive film. The invention also relates to a method for bonding two aeronautical parts.

Abstract: The invention relates to a method of fabricating a titanium alloy part, the method comprising: heating the part to a temperature T1 so that the temperature of the part is substantially uniform, performing an initial forging operation on the part, followed immediately by quenching the part down to ambient temperature; and heating the part to a temperature T2, followed by a final forging operation on the part at the temperature T2 followed immediately by quenching the part, the final forging operation being suitable for giving the part its final shape; the temperature T1 being higher than the ?-transus temperature of the alloy, the temperature T2 being lower than the ?-transus temperature, the only heating of the part to above the ?-transus temperature being the heating to the temperature T1, the initial forging preceding the final forging, and the initial forging being performed as soon as the temperature of the part is substantially uniform, the method being characterized in that the quenching immediately

Abstract: A method of heat treating a thermomechanical part made of a TA6Zr4DE titanium alloy. A solution-annealing is performed at a temperature lying in the range beta transus ?20° C. and beta transus ?15° C. for a duration lying in the range four hours to eight hours. The method is applicable to fabricating high pressure compressor disks.

Abstract: The present invention provides non-axially symmetrical manufactured parts of thickness less than 10 mm, made of ? or quasi-? titanium alloy, having a core microstructure constituted by whole grains presenting a slenderness ratio greater than 4 and an equivalent diameter lying in the range 10 ?m to 300 ?m. The invention also provides a method of manufacturing the parts by forging.

Abstract: The present invention provides non-axially symmetrical manufactured parts of thickness less than 10 mm, made of ? or quasi-? titanium alloy, having a core microstructure constituted by whole grains presenting a slenderness ratio greater than 4 and an equivalent diameter lying in the range 10 ?m to 300 ?m. The invention also provides a method of manufacturing the parts by forging.

Abstract: The present invention provides non-axially symmetrical manufactured parts of thickness less than 10 mm, made of ? or quasi-? titanium alloy, having a core microstructure constituted by whole grains presenting a slenderness ratio greater than 4 and an equivalent diameter lying in the range 10 ?m to 300 ?m. The invention also provides a method of manufacturing the parts by forging.

Abstract: The present invention provides non-axially symmetrical manufactured parts of thickness less than 10 mm, made of &bgr; or quasi-&bgr; titanium alloy, having a core microstructure constituted by whole grains presenting a slenderness ratio greater than 4 and an equivalent diameter lying in the range 10 &mgr;m to 300 &mgr;m. The invention also provides a method of manufacturing said parts by forging.

Abstract: The invention relates to crystallized 2-dimethylamino-2-parahydroxyphenyl sodium acetate, anhydrous or with 2 molecules of water. The process for preparation thereof comprises heating parahydroxy mandelic acid in dimethylformamide in the presence of a catalytic quantity of a strong acid, such reaction being followed by a sodium hydroxide neutralization. Said product is applied to the production of parahydroxybenzyl cyanide by reacting it with 2-hydroxy isobutyronitrile.