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Standard

VISUAL INSPECTION GUIDE FOR INSTALLED HOSE ASSEMBLIES

1982-03-01
ARP1658
This recommended practice covers visible surface defects on aerospace hose assemblies which have been installed and are functioning within a working environment at the time of visual inspection.
Standard

VISUAL INSPECTION GUIDE FOR INSTALLED HOSE ASSEMBLIES

1986-12-01
ARP1658A
This recommended practice covers visible surface defects on aerospace hose assemblies which have been installed and are functioning within a working environment at the time of visual inspection.
Standard

Test Methods, Hose Assemblies, Polytetrafluoroethylene (PTFE)

2008-02-14
AS2078A
This SAE Aerospace Standard (AS) describes the test methods for flexible PTFE hose and hose assemblies used in aircraft fluid systems in the pressure and temperature ranges defined in specific procurement specifications. It applies to the hose and the hose coupling. The tests and assembly requirements for the connecting end fitting are covered in the procurement specification. This document applies each time that it is referred to in a procurement specification or other definition document.
Standard

Test Methods for Tube-Fitting Assemblies

2011-10-18
AS2094A
This SAE Aerospace Standard (AS) specifies test methods for tube-fitting assemblies used in aircraft fluid systems in the following pressure classes: B (1500 psi or 10500 kPa), D (3000 psi or 21000 kPa), E (4000 psi or 28000 kPa), and J (5000 psi or 35000 kPa) and in temperature types I (-65 to 160 °F or -55 to 70 °C), II (-65 to 275 °F or -55 to 135 °C), and III (-65 to 400 °F or -55 to 200 °C) of AS2001. This document applies each time that it is referred to in a procurement specification or other definition document. Fluids and materials used for the tests are listed in Section 2.
Standard

Test Methods for Tube-Fitting Assemblies

2018-07-12
AS2094B
This SAE Aerospace Standard (AS) specifies test methods for tube-fitting assemblies used in aircraft fluid systems in the following pressure classes: B (1500 psi or 10500 kPa), D (3000 psi or 21000 kPa), E (4000 psi or 28000 kPa), and J (5000 psi or 35000 kPa) and in temperature types I (-65 to 160 °F or -55 to 70 °C), II (-65 to 275 °F or -55 to 135 °C), and III (-65 to 400 °F or -55 to 200 °C) of AS2001. This document applies each time that it is referred to in a procurement specification or other definition document. Fluids and materials used for the tests are listed in Section 2.
Standard

T-bolt and Eye Bolt, A-286 CRES, 1000 °F Fatigue Rated

1991-07-01
AS4108
This specification defines the requirements for A-286 cres T-bolts and eye bolts, with room temperature tensile strength of 160 000 to 190 000 psi, for use with clamps and V-band couplings at 1000°F maximum ambient temperature.
Standard

T-Bolt and Eye Bolt, A286 CRES, 1000 °F Fatigue Rated

2017-04-07
AS4108B
This specification defines the requirements for A286 cres T-bolts and eye bolts, with room temperature tensile strength of a minimum of 160000 psi, for use with clamps and V-band couplings at 1000 °F maximum ambient temperature.
Standard

T-Bolt and Eye Bolt, A286 CRES, 1000 °F Fatigue Rated

2018-01-18
AS4108C
This specification defines the requirements for A286 cres T-bolts and eye bolts, with room temperature tensile strength of a minimum of 160000 psi, for use with clamps and V-band couplings at 1000 °F maximum ambient temperature.
Standard

T-Bolt and Eye Bolt, A-286 CRES, 1,000 °F Fatigue Rated

2015-12-01
AS4108A
This specification defines the requirements for A-286 cres T-bolts and eye bolts, with room temperature tensile strength of a minimum of 160,000 psi, for use with clamps and V-band couplings at 1,000 °F maximum ambient temperature.
Standard

Standardization, Hydraulic Tube Walls

1997-03-01
AS4467
This SAE Aerospace Standard (AS) defines a series of standardized tube walls to be used for high pressure hydraulic tubing. These tube walls are applicable to all homogenous tube materials (i.e., aluminum, steel, titanium) throughout a rated pressure range of 1000 to 8000 psi and a maximum rated operating temperature range of 160 to 450 °F. All future aerospace applications for which a required tube outside diameter/tube wall combination is not presently available shall be selected from the table contained herein (see Figure 1).
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