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Standard

Structural Weldbonding of Aluminum Structures

1990-10-01
CURRENT
ARP1675
This SAE Aerospace Recommended Practice describes the aluminum weldbonding process for fabrication of secondary aircraft structural assemblies possessing excellent strength, fatigue life, and environmental durability.
Standard

Core, Honeycomb, Glass/Polyimide

2001-04-01
CURRENT
AMS3712C
This specification covers expanded honeycomb core made of glass cloth impregnated with polyimide resin and supplied in the form of blocks, slices, and ordered shapes.
Standard

Core, Honeycomb, Glass/Phenolic Bias Weave Fiber Construction

1998-08-01
CURRENT
AMS3716C
This specification covers expanded honeycomb core made from glass fabric impregnated with phenolic resin and oriented so the fabric weave is on the 45-degree bias with the ribbon direction and supplied in the form of blocks, slices, and ordered shapes.
Standard

Core, Honeycomb, Glass/Phenolic

2004-05-03
CURRENT
AMS3715D
This specification covers honeycomb core made of glass fabric impregnated with phenolic resin and supplied in the form of blocks, slices, and ordered shapes.
Standard

Sandwich Constructions and Core Materials; General Test Methods

1999-06-01
CURRENT
AMSSTD401
This standard covers the general requirements and methods for testing sandwich core materials and for testing sandwich construction of the types used primarily in aircraft structures. This standard does not include test methods applicable only to a specific product; such test methods are included in the detailed specifications for the product.
Standard

Adhesive, Film Form Metallic Structural Sandwich Construction

1999-08-01
CURRENT
AMSA25463
This specification covers the requirements for adhesives in film form for bonding metal facings to metal cores and to metal components of sandwich panels which are intended for use in primary and secondary structural airframe parts that may be exposed to temperatures up to 500°F (260°C).
Standard

Surface Preparation and Priming of Aluminum Alloy Parts for High Durability Structural Adhesive Bonding

2018-11-15
WIP
ARP1524B
This Aerospace Recommended Practice (ARP) describes the processing system and techniques for the surface preparation and priming of aluminum alloy parts for structural adhesive bonding to achieve optimum bondline durability, corrosion resistance, and manufacturing producibility. While this surface preparation has been developed and validated for two high strength aluminum alloys, 2024 and 7075, in the hardened condition it is expected to be applicable to other alloys and tempers. This surface preparation system has been validated for use with 180 degrees F (82 degrees C) and with 250 degrees F (121 degrees C) curing elastomer-modified epoxy adhesive and corrosion-inhibiting primer. The processes described herein are the result of laboratory evaluation of structural and durability performance.
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