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Protective systems Aluminum alloys Parts and Components AMS P17 Polymer Matrix Composites Committee Quality, Reliability, and Durability

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Standard

Sandwich Constructions and Core Materials: General Test Methods
2023-04-21
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
2022-10-04
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

Acceptance Criteria Adhesive-Bonded Metal-Faced Sandwich Structures
2022-08-10
CURRENT
AMS3920A
This specification establishes the acceptance criteria and inspection requirements for adhesive-bonded sandwich structures including the metal-to-metal bonding found in these structures, but usage is not limited to such applications and each application should be considered individually.
Standard

Core, Honeycomb, Glass/Phenolic
2022-08-10
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

Automated Manufacture of Continuous Multi-Ply Carbon Fiber/Epoxy Resin Impregnated Broadgoods
2022-06-05
CURRENT
ARP1674A
This document describes a manufacturing method for processing unidirectional carbon fiber/epoxy resin impregnated sheet and tape into multi-ply broadgoods and tape produced on an automated cross-plying machine. Broadgoods or tape of two or more ply configurations may be processed, where ply orientations of 0°, 45°, 90°, and 135° (as examples) may be automatically layed in a programmed sequence. In all configurations, the 0° ply direction is parallel to the length of the broadgoods roll or sheet, or tape.
Standard

Carbon Fiber and Fiberglass Epoxy/Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 42, Class 4, Grade 48, Style 108
2021-03-10
CURRENT
AMS6891/4
The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of this base specification, AMS6891.
Standard

Carbon Fiber and Fiberglass Epoxy/Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 34, Class 4, Grade 294, Style 7781
2021-03-10
CURRENT
AMS6891/3
The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the quality assurance section of this base specification, AMS6891.
Standard

Carbon Fiber and Fiberglass Epoxy/Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 40, Class 1, Grade 196, Style 6K-PW
2020-12-29
CURRENT
AMS6891/2
The intent of this specification is for the procurement of the material listed on the QPL; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of this base specification, AMS6891.
Standard

Carbon Fiber and Fiberglass Epoxy Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 35, Class 1, Grade 191
2020-12-29
CURRENT
AMS6891/1
The intent of this specification is for the procurement of the material listed on the QPL; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of this base specification, AMS6891.
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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