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Standard

Cargo Restraint Straps – Utilization Guidelines

2017-11-13
CURRENT
ARP5595B
This Aerospace Recommended Practice aims at providing general utilization guidelines and calculation methods adequate to guarantee the effectiveness and ultimate load strength of tie-down/lashing arrangements performed to restrain cargo on board civil transport aircraft during flight: Cargo loaded and tied down onto airworthiness approved air cargo pallets, themselves restrained into aircraft lower deck, main deck or upper deck cargo systems meeting the restraint requirements of air cargo pallets approved in accordance with NAS 3610 or AS36100, or Additional tie-down on aircraft structure when necessitated by pallet maximum gross mass or centre of gravity location, or Individual pieces of cargo, or pieces of cargo placed onto an unrestrained (“floating”) pallet into either lower deck, main deck or upper deck containerized cargo compartments of an aircraft, or Individual pieces of load loaded in non-containerized (bulk loaded) baggage or cargo compartments.
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

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

Hose Assembly, Heated, 125 psig, Lined Silicone, Potable Water, Procurement Specification

2017-11-13
CURRENT
AS5420G
This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, integrally heated silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems with an environmental operating temperature range of -65 °F (-54 °C) to +160 °F (+71 °C).
Standard

Unmanned Systems (UxS) Control Segment (UCS) Architecture: Architecture Technical Governance

2017-11-13
WIP
AS6522A
The UCS technical governance comprises a set of policies, processes, and standard definitions to establish consistency and quality in the development of architecture artifacts and documents. It provides guidance for the use of adopted industry standards and modeling conventions in the use of Unified Modeling Language (UML) and Service Oriented Architecture Modeling Language (SoaML), including where the UCS Architecture deviates from normal UML conventions. This document identifies the defining policies, guidelines, and standards of technical governance in the following subjects: - Industry standards adopted by the AS-4UCS Technical Committee: These are the industry standards and specifications adopted by AS-4UCS in the generation and documentation of the architecture. - UCS Architecture Development: UCS specific policies on the development of the UCS Architecture. The AS-4UCS Technical Committee governance policies are intentionally minimal.
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

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

Directory of Databases Part I - Whole Body Anthropometry Surveys

2017-11-10
WIP
SAE5145A
This SAE Aerospace Information Report (AIR) lists whole body anthropometric surveys and provides current sources for the survey raw data and summary statistics. The purpose of this directory is to provide a single source for accessing anthropometric survey data for human modelers, human factors specialists, and other interested in anthropometric data. It is not meant to provide detailed data on each survey, but to provide readers with enough information to allow them to make a decision about which surveys are of possible application to their work. The reader can then obtain further information and actual data from the listed points of contact.
Standard

Plating, Brush, Tin

2017-11-09
CURRENT
AMS2451/12A
This specification covers the engineering requirements and process for brush plating of tin by electrodeposition. It shall be used, in conjunction with AMS2451, for general purpose tin deposits.
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