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Standard

Coupling Assembly, Self-Sealing, One Side Only, Hydraulic

2019-01-10
CURRENT
AS1896B
This document establishes the requirements for aircraft, hydraulic couplings, self-sealing one side only, for use in Type II hydraulic systems ( 65 to +275 °F temperature range) as defined by MIL H 5440. The purpose being to connect a hose or tube to a standard MS33656, MS33514, or MIL F 85421, or MIL-F-85720 fitting, and to provide the self-sealing feature on the hose or tube side of the connection.
Standard

Sleeve, Hose Assembly, Fire Protection

2019-01-07
CURRENT
AS1072F
This standard defines the requirements for bulk protective sleeve to provide fire resistance for aircraft hose assemblies, which will enable these assemblies to meet the requirements of AS1055. NOTE: Use of this sleeve does not eliminate the need to demonstrate that the sleeved assemblies will meet the applicable requirements of AS1055.
Standard

Qualification of Hydraulic Tube Joints to Specified Flexure Fatigue Requirements

2019-01-03
WIP
ARP1258C
This SAE Aerospace Recommended Practice (ARP) establishes the method for qualification testing of tube joints and fitting attachments, using the flexure test method described in ARP1185. This qualification test method allows the determination of S-N type stress versus cycles or D-N type deflection versus cycles curves, as illustrated in AIR1418 as an alternate to flexure testing to a minimum endurance stress level.
Standard

Fittings, 24° Cone Flareless, Fluid Connection, 3000 psi

2019-01-03
CURRENT
AS18280G
This SAE Aerospace Standard (AS) establishes the requirements for 24° cone flareless fluid connection fittings and nuts, internally or externally swaged, preset, or welded sleeves for use in aircraft fluid systems at nominal operating pressures up to and including 3000 psi.
Standard

Hose Assembly, Polytetrafluoroethylene, Metallic Reinforced, Up to 1500 psi and 450 °F, Hydraulic and Pneumatic

2018-12-19
CURRENT
AS1946F
This SAE Aerospace Standard (AS) defines the requirements for polytetrafluoroethylene (PTFE) lined, metallic reinforced, hose assemblies suitable for use in aerospace hydraulic, fuel, and lubricating oil systems at temperatures between 67 °F and 450 °F for Class I assemblies, -67 °F and 275 °F for Class II assemblies, and at nominal pressures up to 1500 psi. The hose assemblies are also suitable for use within the same temperature and pressure limitations in aerospace pneumatic systems where some gaseous diffusion through the wall of the PTFE liner can be tolerated. The use of these hose assemblies in pneumatic storage systems is not recommended. In addition, installations in which the limits specified herein are exceeded, or in which the application is not covered specifically by this standard, for example oxygen, shall be subject to the approval of the procuring activity.
Standard

Flexure Testing of Hydraulic Tubing Joints and Fittings

2018-12-17
WIP
ARP1185C
This SAE Recommended Practice (ARP) establishes flexure test procedures to determine and classify the fatigue strengths of reconnectable or permanent hydraulic tube joints. The procedure is intended for conducting flexure tests of fittings and joints for hydraulic tubing materials such as AMS 5561 (21Cr-6Ni-9Mn) steel or AMS 4944 (3AL-2.5V) titanium. A mean stress is applied by holding system pressure in the specimens and flexing in a rotary or planar bending test machine.
Standard

Prestressing (Autofrettaging) of Hydraulic Tubing Lines

2018-12-17
WIP
AIR1379B
This AIR is intended to describe and document a process presently in use for proof testing, which at the same time improves the fatigue life of 304 1.8 hard CRES and 3A1-2.5V CWSR titanium hydraulic tubing lines. Aerospace Information Report (AIR) 1419 "Inlet Total Pressure Distortion Considerations for Gas Turbine Engines" documents engineering information for use as reference material and for guidance. Inlet total-pressure distortion and other forms of flow distortion that can influence inlet/engine compatibility require examination to establish their effect on engine stability and performance. This report centers on inlet-generated total-pressure distortion measured at the Aerodynamic Interface Plane (AIP), not because this is necessarily the sole concern, but because it has been given sufficient attention in the aircraft and engine communities to produce generally accepted engineering practices for dealing with it.
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