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Viewing 1 to 30 of 245
2017-11-13
WIP Standard
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.
2017-11-13
WIP Standard
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.
2017-11-13
WIP Standard
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.
2017-11-10
WIP Standard
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.
2017-11-10
WIP Standard
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.
2017-11-10
WIP Standard
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.
2017-11-10
WIP Standard
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.
2017-11-10
WIP Standard
AMS6568/3
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 180 °F. They are typically used in structural applications requiring high strength and stiffness.
2017-11-10
WIP Standard
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.
2017-11-10
WIP Standard
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.
2017-11-10
WIP Standard
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.
2017-11-09
WIP Standard
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.
2017-11-09
WIP Standard
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.
2017-11-09
WIP Standard
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.
2017-11-08
WIP Standard
AMS6569
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. This is the base specification and it will have two slash/detail specs.
2017-11-08
WIP Standard
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.
2017-11-08
WIP Standard
AMS6565
Establish a new AMS for dry carbon fabric for Hexcel SGP196P IM7 plain weave fabric.
2017-11-08
WIP Standard
AMS6562
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 basic spec and it will have three slash/detail specs.
2017-11-08
WIP Standard
AMS6568
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.
2017-11-08
WIP Standard
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.
2017-10-30
WIP Standard
AIR5431A
This SAE Aerospace Information Report (AIR) offers information about the use of support tooling for composite repair processes, as well as descriptions of some of the different tooling materials used and their applications. If the repair document requires the use of tooling, refer to this AIR for additional information.
CURRENT
2017-09-27
Standard
AS1339H
This Aerospace Standard (AS) defines the requirements for a lightweight polytetrafluoroethylene (PTFE) lined, metallic reinforced, hose assembly suitable for use in high temperature, 400 °F, high pressure, 3000 psi, aircraft hydraulic systems, also for use in pneumatic systems which allow some gaseous diffusion through the PTFE wall.
2017-07-13
WIP Standard
AIR4938C
This is a general curriculum that has been developed to identify the minimum knowledge and skill requirements of a composite and/or metal bond repair technician/specialist. This revision changes the document from an all-inclusive curriculum into a modular set of curricula. Teaching levels have been assigned to the curriculum to define the knowledge, skills and abilities graduates will need to make composite repairs. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter - lecture and laboratory. These minimums may be exceeded, and may include an increase in the total number of training hours and/or increases in the teaching levels.
CURRENT
2017-06-05
Standard
AIR4938B
This is a general curriculum that has been developed to identify the minimum knowledge and skill requirements of a composite and/or metal bond repair technician/specialist. This revision changes the document from an all-inclusive curriculum into a modular set of curricula. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need to make repairs to composite or metalbond structure. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter including lecture and laboratory. These minimums may be exceeded and may include an increase in the total number of training hours and/or increases in the teaching levels. Each curriculum is a subpart of this document. Part 1 is the General Composite Structure Bonded Repair curriculum, independent of the application. Part 2 is the Commercial Aircraft Composite Structure Bonded Repair curriculum.
2017-05-26
WIP Standard
ARP4977A
This SAE Aerospace Recommended Practice (ARP) describes standard methods for drying commercial aircraft composite structures prior to repair and gives general guidelines on use and applicability. It addresses the removal of liquids that have collected inside the structures through open damage, microcracks, or porosity and the removal of absorbed moisture from the composite material. The methods described in this document shall only be used when specified in an approved repair document or with the agreement of the original equipment manufacturer (OEM) or regulatory authority. If this document is used for the drying of materials other than thermosetting composite materials, the fitness for this purpose must be determined by the user. The purpose of this document is to provide a set of standard drying methods that may be referenced in repair documents produced by airlines or airframe and engine manufacturers.
2017-04-21
WIP Standard
AS153J
Add integral silicone cuff max length and OD to flared parts standards
2017-04-21
WIP Standard
AS154H
Add integral silicone cuff max length and OD to flared parts standards
Viewing 1 to 30 of 245

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