標準號：SAE AS 5830-2006
中文標準名稱：非螺紋撓性固定空腔、載流、自粘合組合聯軸器采購規范
英文標準名稱：Coupling Assembly, Threadless, Flexible, Fixed Cavity, Current Carrying, Self-Bonding, Procurement Specification FSC 4730
標準類型：V32
發布日期：2006/9/1 12:00:00
實施日期：1999/12/31 12:00:00
中國標準分類號：V32
國際標準分類號：49.050
引用標準：ANSI/NCSL Z 540.1-1994;ASME Y14.5M-1994;ASTM D 1193-2006;ASTM D 6210-2006;SAE AMS-R-25988-1998;SAE AMS-WW-T-700;SAE AMS-WW-T-700A-2001;SAE ARP 5412-1999;SAE ARP 5416-2005;SAE AS 478M-2006;SAE AS 568B-2001;SAE AS 4060-1995;SAE AS 5831-2006;SAE AS 5832-2006
適用范圍：This aerospace specification defines the requirements for a threadless, flexible, conductive, self-bonding coupling assembly which, when installed on fixed cavity ferrules, provides a flexible, current carrying connection for joining tubing and components in aircraft fuel, vent and other systems. The assembled coupling is designed to provide interchangeability of parts and components between qualified manufacturers for the service life of the aircraft system. The assembled coupling is for use from -65 to +200 °F at nominal operating pressures (125 psig for -08 through -64 and 30 psig for -72 through -88). This aerospace specification is a departure from prior qualification practices for assembled couplings. Prior practice sought to validate this type of assembled coupling design by conducting a sequence of tests on sets of coupling assemblies. There were multiple test sequences and each was conducted on a different set of coupling assemblies. Each of these test sequences challenged a particular design feature of the coupling assembly. No single coupling assembly was expected to survive all of the required tests. FAR 23.954, FAR 25.954 and FAR 25.981 certification requirements have identified the need for high-current capable flexible fluid couplings. The coupling assembly does not require inspection and maintenance to remain current capable for the life of the aircraft. It is important to simulate the in-service wear and damage experienced by the assembled coupling if it is to remain capable of carrying current for the life of the aircraft. The test procedures in this specification simulate a worst case wear and damage condition for the assembled couplings. Interchangeability of vendor parts must be qualified by design, test and/or analysis.