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Standard

350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs, Type 38, Class 2, Grade 193, Style 3K-70-PW, Fiber 1

2019-03-12
WIP
AMS3961/1A
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 shall refer to the Quality Assurance section of the base specification, AMS3961. All material qualification and equivalency data has been archived and is available for review upon request. Contact the CMH-17 Secretariat (www.cmh17.org) for additional information.
Standard

350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs, Type 35, Class 1, Grade 190, Fiber 2

2019-03-12
WIP
AMS3961/2A
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 shall refer to the Quality Assurance section of the base specification, AMS3961. All material qualification and equivalency data has been archived and is available for review upon request. Contact the CMH-17 Secretariat (www.cmh17.org) for additional information.
Standard

350 °F Autoclave Cure, Low Flow Toughened Epoxy Prepregs, Type 35, Class 1, Grade 190, Fiber 1

2019-03-12
WIP
AMS3961/3A
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 shall refer to the Quality Assurance section of the base specification, AMS3961. All material qualification and equivalency data has been archived and is available for review upon request. Contact the CMH-17 Secretariat (www.cmh17.org) for additional information.
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.
Standard

Medium Temperature, Out-of-Autoclave, Oven-Vaccum-Bag Cure Epoxy Resin Impregnated Fiber Reinforced Composite Materials, Type 32, Class 1, Grade 145, Intermediate Modulus Fiber

2017-11-13
WIP
AMS6562/6
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the sixth detail spec.
Standard

Medium Temperature, Out-of-Autoclave, Oven-Vaccum-Bag Cure Epoxy Resin Impregnated Fiber Reinforced Composite Materials, Type 32, Class 1, Grade 145, Standard Modulus Fiber 2

2017-11-13
WIP
AMS6562/5
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the fifth detail spec.
Standard

Medium Temperature, Out-of-Autoclave, Oven-Vaccum-Bag Cure Epoxy Resin Impregnated Fiber Reinforced Composite Materials, Type 32, Class 1, Grade 145, Standard Modulus Fiber 1

2017-11-13
WIP
AMS6562/4
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the fourth detail spec.
Standard

Low Initial Temperature Vacuum Bag Only Cure, Medium Toughness Epoxy Prepreg, Type 33, Class 1, Grade 145, Standard Modulus Carbon Fiber

2017-11-10
WIP
AMS6567/1
AMS6567 The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is designed specifically for vacuum-bag-only cure, with an initial low temperature cure followed by a higher temperature post-cure. This material is intended for use in laminate applications with a service temperature up to 250 °F. They are typically used in structural applications requiring high strength and stiffness.
Standard

265°F Vacuum Cure, Epoxy Prepregs Type 42, Class 2, Grade 193, Style 12K-193-SFP-OSI

2017-11-10
WIP
AMS6566/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have one slash/detail specs.
Standard

Autoclave Cure, High Toughness and High Open-Hole Compression Epoxy Prepreg, Type 38, Class 2, Grade 193, Style 3K-PW, Standard Modulus Carbon Fiber

2017-11-10
WIP
AMS6569/2
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. These materials are designed specifically for vacuum bag autoclave cure. These materials are intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.
Standard

Autoclave Cure, High Toughness and High Open-Hole Compression Epoxy Prepreg, Type 33, Class 1, Grade 190, Intermediate Modulus Carbon Fiber

2017-11-10
WIP
AMS6569/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. These materials are designed specifically for vacuum bag autoclave cure. These materials are intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.
Standard

265°F, Autoclave Vacuum Bag Cure, Epoxy Prepreg, Type 40, Class 2, Grade 195, Style 3K-PW, Standard Modulus Carbon Fiber

2017-11-10
WIP
AMS6568/2
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness.
Standard

265°F, Autoclave Vacuum Bag Cure, Epoxy Prepreg, Type 33, Class 1, Grade 148, Intermediate Modulus Carbon Fiber

2017-11-10
WIP
AMS6568/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have three slash/detail specs.
Standard

Low Initial Temperature Vacuum Bag Only Cure, Medium Toughness Epoxy Prepreg, Type 37, Class 2, Grade 193, Style 3K-Pw, Standard Modulus Carbon Fiber

2017-11-10
WIP
AMS6567/2
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is designed specifically for vacuum-bag-only cure, with an initial low temperature cure followed by a higher temperature post-cure. This material is intended for use in laminate applications with a service temperature up to 250 °F. They are typically used in structural applications requiring high strength and stiffness.
Standard

Medium Temperature, Out-of-Autoclave, Oven-Vacuum-Bag Cure Epoxy Resin Impregnated Fiber Reinforced Composite Materials, Type 35, Class 4, Grade 298, Style 6781

2017-11-09
WIP
AMS6562/2
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the second detail spec.
Standard

Medium Temperature, Out-of-Autoclave, Oven-Vacuum-Bag Cure Epoxy Resin Impregnated Fiber Reinforced Composite Materials, Type 36, Class 2, Grade 193, Style 3k-70-PW

2017-11-09
WIP
AMS6562/3
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the third detail spec.
Standard

Medium Temperature, Out-of-Autoclave, Oven-Vacuum-Bag Cure Epoxy Resin Impregnated Fiber Reinforced Composite Materials, Type 35, Class 4, Grade 293, Style 7781

2017-11-09
WIP
AMS6562/1
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 250 °F. The composite may be used for the manufacture of primary and secondary aircraft structure. This is the first slash/detail spec.
Standard

Low Initial Temperature Vacuum Bag Only Cure, Medium Toughness Epoxy Prepregs

2017-11-08
WIP
AMS6567
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is designed specifically for vacuum-bag-only cure, with an initial low temperature cure followed by a higher temperature post-cure. This material is intended for use in laminate applications with a service temperature up to 250 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have two slash/detail specs.
Standard

265°F Vacuum Cure, Epoxy Prepregs

2017-11-08
WIP
AMS6566
The purpose of this specification is to allow procurement of a defined material corresponding to statistically derived material properties published in CMH-17. This material is intended for use in laminate applications with a service temperature up to 180 °F. They are typically used in structural applications requiring high strength and stiffness. This is the base specification and it will have one slash/detail specs.
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