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编制和发布本文件旨在供应商遵守 9100 规定的情况下，就 AQAP-2110 的应用提供相关信息和指南。本文件的发布号为 AQAP-2110-SRD.2 和 IA9137。本文件由 NATO 和行业代表联合编制，供 NATO 和行业内使用，旨在促进 AQAP-2110 和 9100 的使用及对其之间关系的理解。当采购国使用对外军售 (FMS) 作为其采购方式时，可能需要 AQAP。 本文件旨在促进采购方及其 9100 供应商对 AQAP-2110 要求解释的通用性。 本文件内容不具有法律或合同地位，亦不会取代、增加或取消 AQAP-2110 或 9100 的任何要求。 由于可能存在多种条件（取决于工作或过程类型、所用设备和所涉人员的技能等因素），不应将本指南视为包含所有事宜，亦不应将本指南视为强加满足合同要求的具体手段或方法。相关方应意识到，可使用其他手段或方法来满足这些要求。 本指南使用者应谨记，当合同引用了 AQAP 2110，其要求对于供应商和次级供应商具有强制性。

This paper presents, chemistry, test data and processing procedures on a non toxic and environmentally friendly chrome-free conversion coating alternative with the same level of adhesion and secondary corrosion resistance as that found in chrome containing conversion coating systems. Test data from military and independent sources will be presented on secondary coating adhesion, electrical conductivity, filiform and neutral salt-spray corrosion resistance as compared to chromate based systems .on magnesium, aluminum and zinc and their respective alloys. The European “RoSH” initiative will not allow for the presence of any hexavalent chromium on imported electrical components as of July first of 2006. Trivalent chromium based systems generate hexavalent chromium due to the oxidation of the trivalent chromium and as such will not be allowed.

When looking into using PCMCIA PC Cards in the avionics market, three areas must be researched. The first is what are the applications and benefits of using the PC Cards while in flight, followed by the applications and benefits on the ground, and thirdly on how to make a PC Card that would stand up to the rugged avionics environment. PCMCIA PC Cards can be used in all aspects of flight. Three possible applications on the ground are; paperless documentation, modifications, flightline changes. Once airborne, PC Cards can be removed and a different functionality card can be inserted. One PC card socket can be used for many different functions during one flight. Some of the possible applications for PC Cards inflight are; flight plan changes, backup Line Replaceable Units (LRUs), and solid state data collection.

This paper presents the derivation of the equations for circumferential, longitudinal and radial heat transfer conductance for a thin shell toroid or a segment of the toroid. A thin shell toroid is one in which the radius to thickness ratio is greater than 10. The equations for the surface area of a toroid or of a toroidal segment will also be derived along with the equation to determine the location of the centroid. The surface area is needed to determine the radial conductance in the toroid or toroidal segment and the centroid is needed to determine the heat transfer center of the toroid or toroidal segment for circumferential and longitudinal conductance. These equations can be used to obtain more accurate results for conductive heat transfer in toroid which is a curved spacecraft components. A comparison will be made (1) using the equations derived in this paper which takes into account the curvature of the toroid (true geometry) and (2) using flat plates to simulate the toroid.

THIS PAPER REPORTS on the present state of the art in the utilization of refractory metals for air frame and powerplant sheet metal components. By far the most promising of these metals to date is molybdenum. The mechanical and physical properties of molybdenum are well-suited for high-temperature service. The combination of relatively high thermal conductivity, low thermal expansion coefficient, good specific heat, and a reasonably high emissivity of a coated surface make this material suitable for exterior surface application on severely aerodynamically heated components. However, in its usable alloyed forms, molybdenum tends to behave in a brittle manner at room temperature, suffering from a high brittle-to-ductile transition temperature. Other unacceptable properties are the presence of laminations in the material, 45-deg preferred angle cracking, and difficulty of controlling interstitial alloying elements. The authors discuss each of these and the progress made in overcoming them

RADIATION can produce almost instantaneous failure of modern aircraft lubricants, tests at Southwest Research Institute show. Two types of failures demonstrated are rapid viscosity rise and loss of heat conductivity. Furthermore, it was found that lubricants can become excessively corrosive under high-level radiation. Generally speaking, the better lubricants appeared to improve in performance while marginal ones deteriorated to a greater extent under radiation. When the better lubricants were subjected to static irradiation prior to the deposition test, there was a minor increase in deposition number as the total dose was increased.

This specification covers a zinc alloy in the form of die castings.

This specification covers a zinc alloy in the form of die castings.

This specification covers a zinc alloy in the form of die castings.

This paper discusses the advantages and problems associated with the use of “passive” liquid containment systems that utilize liquid intermolecular forces for propellant orientation in reduced or zero gravity environments. Liquid orientation is required to provide reliable engine restart and tank venting operations of space vehicle propulsion systems. Various liquid containment system concepts, and associated design criteria, are presented and general problem areas of interface stability, liquid slosh, and effects of thermal energy are described. Descriptions of present and planned test facilities designed to provide reduced gravity environments and extended time durations are included. It is concluded that additional design criteria in the problem areas discussed must be obtained before “passive” liquid containment systems can replace systems now used in reduced or zero gravity environments.

This specification covers the engineering requirements for electrodepositton of zinc and the properties of the deposit.

This specification covers a zinc alloy in the form of die castings.

This specification covers a zinc alloy in the form of die castings.