1.1 本试验方法包括测定航空涡轮燃料中形成固体碳氢化合物晶体的温度。 1.2 此测试方法旨在覆盖−80的温度范围 °C至20 °C；然而，在 12.4 只演示了凝固点在−42范围内的燃料的试验方法 °C至−60 °C。 1.3 以国际单位制表示的数值应视为标准。本标准不包括其他计量单位。 1.4 本标准并非旨在解决与其使用相关的所有安全问题（如有）。本标准的使用者有责任在使用前制定适当的安全、健康和环境实践，并确定监管限制的适用性。 有关具体的警告语句，请参阅 7.1 , 7.3 和 7.5 . 1.5 本国际标准是根据世界贸易组织技术性贸易壁垒委员会发布的《关于制定国际标准、指南和建议的原则的决定》中确立的国际公认的标准化原则制定的。 ====意义和用途====== 5.1 航空燃料的凝固点是燃料保持不含固体碳氢化合物晶体的最低温度。这些晶体可以限制通过飞机燃料系统的燃料流动。飞行过程中，飞机油箱中的燃油温度通常会降低，具体取决于飞机速度、高度和飞行持续时间。燃油的凝固点必须始终低于最低工作燃油温度。 5.2 石油调配操作需要精确测量凝固点。 5.3 该试验方法产生的结果与试验方法等效 386年2月 并将结果精确到0.1 °C，精度比试验方法有所提高 386年2月 该测试方法还消除了测试方法所需的大部分操作员时间和判断 386年2月 . 5.4 当规范要求测试方法时 386年2月 ，不要替代此测试方法或任何其他测试方法。

1.1 This test method covers the determination of the temperature below which solid hydrocarbon crystals form in aviation turbine fuels. 1.2 This test method is designed to cover the temperature range of −80 °C to 20 °C; however, 2003 Joint ASTM/IP Interlaboratory Cooperative Test Program mentioned in 12.4 has only demonstrated the test method with fuels having freezing points in the range of −42 °C to −60 °C. 1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard. 1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use. For specific warning statements, see 7.1 , 7.3 , and 7.5 . 1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee. ====== Significance And Use ====== 5.1 The freezing point of an aviation fuel is the lowest temperature at which the fuel remains free of solid hydrocarbon crystals. These crystals can restrict the flow of fuel through the fuel system of the aircraft. The temperature of the fuel in the aircraft tank normally decreases during flight depending on aircraft speed, altitude, and flight duration. The freezing point of the fuel must always be lower than the minimum operational fuel temperature. 5.2 Petroleum blending operations require precise measurement of the freezing point. 5.3 This test method produces results which have been found to be equivalent to Test Method D2386 and expresses results to the nearest 0.1 °C, with improved precision over Test Method D2386 . This test method also eliminates most of the operator time and judgment required by Test Method D2386 . 5.4 When specification requires Test Method D2386 , do not substitute this test method or any other test method.