Search Results

This aerospace specification defines the requirements for metric weld fittings and machine weldments using an orbiting welding head suitable for use on cold worked 3A1-2.5V titanium and 21Cr-6Ni-9Mn CRES tubing and associated fittings. This specification is equivalent to AS1576 except for metric dimensions and standards.

This specification covers a premium aircraft-quality alloy steel in the form of welding wire.

This specification covers a premium aircraft-quality alloy steel in the form of welding wire.

A state of the art proprietary method for aluminum-to-aluminum joining in the automotive industry is Resistance Spot Welding. However, with spot welding (1) structural performance of the joint may be degraded through heat-affected zones created by the high temperature thermal joining process, (2) achieving the double-sided access necessary for the spot welding electrodes may limit design flexibility, and (3) variability with welds leads to production inconsistencies. Self-piercing rivets have been used before; however they require different rivet/die combinations depending on the material being joined, which adds to process complexity. In recent years the introductions of screw products that combine the technologies of friction drilling and thread forming have entered the market. These types of screw products do not have these access limitations as through-part connections are formed by one-sided access using a thermo-mechanical flow screwdriving process with minimal heat.

New Refill Friction Stir Spot Welding (Refill FSSW) was performed for the aluminum alloys used for aircrafts. Joints were examined to evaluate its performances, such as tensile shear strength and strength of heat affected zone, with using various surface conditions. As a result of examination, significant lap shear strength by using shoulder plunging method was achieved with shorter process time. Even with the alodine coated aluminum alloys, strong and good quality joints can be made. And finally, actual prototype components were experimentally produced with Refill FSSW robot. Fine preproduction parts with no distortion and sufficient quality were obtained. Refill FSSW will be able to be regarded as suitable for fabrication of aircraft components.

This Aerospace Standard (AS) is to be used to supplement AS7110. In addition to the requirements contained in AS7110, the requirements contained herein shall apply to suppliers seeking NADCAP accreditation for percussion stud welding.

This Aerospace Standard (AS) is to be used to supplement AS7110. In addition to the requirements contained in AS7110, the requirements contained herein shall apply to suppliers seeking Nadcap accreditation for percussion stud welding.

This document has been declared "CANCELLED" as of March 2007 and has been superseded by PRI AC7110/9. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index noting that it is superseded by PRI AC7110/9. Cancelled specifications are available from SAE.

This document describes the materials, equipment, and processing techniques used in fabricating high-strength or high-modulus graphite-fiber-reinforced polysulfone laminates for structural applications for service up to 120°C (250°F).

This document describes the materials, equipment, and processing techniques used in fabricating high-strength or high-modulus carbon-fiber-reinforced polysulfone laminates for structural applications for service up to 120°C (250°F).

No scope available.

This Aerospace Standard (AS) is to be used to supplement AS7110. In addition to the requirements contained in AS7110, the requirements contained herein shall apply to suppliers seeking NADCAP accreditation for gas tungsten arc fusion spot welding.

This Aerospace Standard (AS) is to be used to supplement AS7110. In addition to the requirements contained in AS7110, the requirements contained herein shall apply to suppliers seeking NADCAP accreditation for foundry in-process welding of castings.

This document has been declared "CANCELLED" as of March 2007 and has been superseded by PRI AC7110/11. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index noting that it is superseded by PRI AC7110/11. Cancelled specifications are available from SAE.

This document has been declared "CANCELLED" as of March 2007 and has been superseded by PRI AC7110/10. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index noting that it is superseded by PRI AC7110/10. Cancelled specifications are available from SAE.