V35 航空器及其附件综合 标准查询与下载

HJB 362.2-2006 机载电子设备综合自动测试系统通用要求 第2部分：硬件平台

General Requirements for Integrated Automatic Test System of Airborne Electronic Equipment Part 2: Hardware Platform

GJB 5575-2006 飞机腐蚀控制手册编制要求

本标准规定了飞机腐蚀控制手册的编制要求。 本标准适用于军用飞机腐蚀控制手册（以下简称手册）的编制。

Requirement for preparation of aircraft corrosion control manual

GJB 626A-2006 军用固定翼飞机和旋翼机科研试飞风险科目

本标准规定了有人驾驶军用固定翼飞机和旋翼机科研试飞风险科目的定义、划分准则、分类、内容和实施要求。 本标准适用于军用固定翼飞机和旋翼机科研试飞风险科目的划分和确定：是制定试飞大纲，实施新机设计定型试飞和进行科研试飞训练时认定风险类别的依据。

Risky subjects of flight test research for military fixed wing airplane and rotorcraft

GJB 625A-2006 军用固定翼飞机和旋翼机科研试飞复杂科目

本标准规定了有人驾驶军用固定翼飞机和旋翼机科研试飞复杂科目的定义、划分准则、分类和内容。 本标准适用于军用飞机科研试飞复杂科目的确定：是制定试飞大纲，实施新机设计定型试飞和进行科研试飞训练时认定复杂科目的依据。

Complex subjects of flight test research for military fixed wing airplane and rotorcraft

GJB 5560-2006 飞机基本重量检查单与装载数据手册编制要求

本标准规定了飞机基本重量检查单与装载数据手册的编制要求与格式。 本标准适用于飞机基本重量检查单与装载数据手册的编制。

Requirements for preparation of aircraft basic weight checklists and loading data manual

GJB 5562-2006 飞机维护手册编制要求

本标准规定了飞机维修手册的编写内容、格式、方法及出版等基本要求。 本标准适用于军用飞机维修手册的编写。

Requirement for preparation of aircraft maintenance manual

GJB 5602-2006 下投式探空测风系统通用规范

本规范规定了下投式探空测风系统的性能要求、质量保证规定和交货准备等。 本规范适用于以飞行器为空中工作平台的下投式探空测风系统的研制、生产和验收。

General specification for dropsonde-winding system

GJB 1C-2006 机载悬挂物和悬挂装置接合部位的通用设计准则

本标准规定了军用飞机的机载悬挂物和悬挂装置接合部位的通用设计准则，作为机载悬挂物和悬挂装置的设计依据。 本标准适用于机载悬挂物和悬挂装置的设计。

General design criteria of airborne stores suspension equipment interface

GJB 5551-2006 飞机非核生存力通用准则

本标准规定了军用飞机非核生存力的通用准则。 本标准适用于各类军用固定翼飞机和旋翼类飞机。

General criteria of nonnuclear survivability for the aircraft

GJB 5567-2006 飞机定期检查和维护规定的编制要求

本标准规定了飞机定期检查和维护规定的编制要求。 本标准适用于军用飞机定期检查和维护规定手册的编制。

Requirement for preparation of aircraft periodic inspection and maintenance rules

SAE AS5420B-2006 125输出压力、含硅氧烷的加热饮用水软管组件的采购规范

This SAE Aerospace Standard (AS) covers the requirements for a flexible, lightweight, low pressure, self-extinguishing, integrally heated silicone hose assembly. The hose has a fully fluorinated fluoropolymer inner liner and is primarily intended for use in aircraft potable water systems with an environmental operating temperature range of -65 °F (-54 °C) to +160 °F (+71 °C).

Hose Assembly, Heated, 125 psig, Lined Silicone, Potable Water, Procurement Specification

ASTM F2501-06 无人飞行器系统耐飞行的标准实施

Designing, manufacturing, testing, and maintaining an unmanned aircraft system to comply with industry standards and recommended practices supports development of a certification package that helps ensure its reliability and can lead to its airworthiness certification. Government aviation authorities’ airworthiness certification processes exist to provide some level of assurance that critical systems will operate reliably and pose minimal risk to persons and property. The use of proven standards and practices in the design, manufacture, and test of these systems, especially for the mission critical components, contributes to this goal, as well as streamlining the certification process and simplifying the system test requirements. While developing to a set of standards and practices will not guarantee certification, the ability to show compliance with established standards provides the basis for a well-documented certification approval package. Compliance with established standards and practices also provides assurance that a given component will function as intended in the specified environment and conditions. The standards cited in these practices have been developed by recognized standards-developing agencies; some are accepted by government aviation authorities as an acceptable means of compliance with airworthiness requirements. By their inclusion in these practices, they are considered to be consensus-based for unmanned aircraft-related purposes.1.1 These practices identify existing regulations, standards, specifications, and handbooks to guide the design, manufacture, test, repair, and maintenance of unmanned aircraft systems and their components.1.2 ApplicabilityThese practices apply to unmanned, powered, fixed wing aircraft and rotorcraft systems seeking government aviation authority approval in the form of airworthiness certificates, flight permits, or other like documentation. It is intended to be used as a reference by unmanned aircraft system designers and manufacturers, as well as by procurement authorities, to help ensure the airworthiness of these systems.1.3 These practices provide a starting point for developing a standards-based airworthiness certification package for consideration by regulatory authorities. It lists those top-level standards applicable to the major subsystems and components of an unmanned aircraft system. It assumes that Original Equipment Manufacturer (OEM)-provided subsystems and components, purchased and installed as a unit (for example, Global Positioning Systems), are themselves built to applicable standards that are not necessarily listed in these practices. These practices include standards for technologies that are currently in use in unmanned aircraft, as well as those that are not yet, but could be used in the future (for example, radioisotope thermoelectric generators).1.4 Suggested changes, corrections, or updates should be forwarded to Committee F38.1.5 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 and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practices for Unmanned Aircraft System Airworthiness

ASTM F2415-06 轻型运动自转旋翼机的持续适航系统的标准实施规程

The purpose of this practice is to establish a method by which safety of flight issues are discovered, evaluated, and corrected for the purpose of maintaining operational safety of a light sport gyroplane aircraft.1.1 This practice covers continued operational safety monitoring of light sport gyroplane aircraft.1.2 This practice applies to light sport gyroplane aircraft seeking civil aviation authority approval in the form of flight certificates, flight permits, or other like documentation. This practice applies to kit and ready-to-fly aircraft supplied by a manufacturer.1.3 The values stated in SI units are to be regarded as the standard. The values given in parentheses are for information only.;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 and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Continued Airworthiness System for Light Sport Gyroplane Aircraft

GJB 5450-2005 直升机飞行模拟器鉴定要求

本标准规定了直升机飞行模拟器（以下简称模拟器）不同等级的鉴定要求和方法。 本标准适用于训练用模拟器。工程研究用模拟器的鉴定可参照使用。

Identify requirements for helicopter flight simulator

GJB 5449-2005 直升机飞行模拟器通用要求

本标准规定了直升机飞行模拟器（以下简称模拟器）的系统组成和不同等级要求，以及模拟器的直升机飞行、综合航空电子、运动、视景等系统的功能、性能、结构设计等通用要求。 本标准适用于训练用模拟器。工程研究用的模拟器也可参照使用。

General requirements for helicopter flight simulator

GJB 5431-2005 飞机结构防水和排水设计要求

本标准规定了飞机结构防水和排水设计要求。 本标准适用于军用飞机（但不适用于水上飞机）。

Requirements of design on watertightness and drainage for aircraft structure

DLA QPL-52525-14-2005 可重复使用的附件并夹成两半软管配件一般规格

This list has been prepared for use by or for the Government in the acquisition of products covered by Specification MIL-DTL-52525. Listing of a product is not intended to and does not connote endorsement of the product by the Department of Defense.

FITTINGS, HOSE, REUSABLE, FIELD-ATTACHABLE AND CLAMP-HALVES, GENERAL SPECIFICATION FOR

DLA QPL-27272-15-2005 中压高温聚四氟乙烯软管配件一般规则

product is not intended to and does not connote endorsement of the product by the Department of Defense. All products listed herein have been qualified under the requirements for the product as specified in the latest effective issue of the applicable specification. This list is subject to change without notice; revision or amendment of this list will be issued as necessary. The listing of a product does not release the supplier from compliance with the specification requirements.

FITTINGS, POLYTETRAFLUOROETHYLENE HOSE, HIGH-TEMPERATURE, MEDIUM-PRESSURE, GENERAL SPECIFICATION FOR

ARMY MIL-PRF-32002 C VALID NOTICE 1-2005 重型防水材质战斗机

The activities above were interested in this document as of the date of this document. Since organizations and responsibilities can change, you should verify the currency of the information above using the ASSIST Online database at http://assist.daps.dla.mil

COVER MATERIAL, VEHICLE, COATED TACTICAL AND COMBAT, HEAVY-DUTY, WATERPROOF

SAE AIR5642-2005 直升机综合性能的安装功率损耗影响

The purpose of this SAE Aerospace Information Report (AIR) is to illustrate the effect of installation power losses on the performance of a helicopter. Installation power losses result from a variety of sources, some associated directly with the basic engine installation, and some coming from the installation of specific items of aircraft mission specific equipment. Close attention must be paid to the accurate measurement of these losses so that the correct aircraft performance is calculated. Installation power losses inevitably result in a reduction in the overall performance of the aircraft. In some cases, careful attention to detail will allow specific elements of the overall loss to be reduced with immediate benefit for the mission performance of the aircraft. When considering items of equipment that affect the engine, it is important to understand the effect these will have on overall aircraft performance to ensure that mission capability is not unduly compromised. Alternatively, a clear understanding of these effects at the aircraft design stage may have an influence on the initial choice of engine size to ensure that mission performance targets are subsequently met. This report aims to give a general understanding of the effect of installation power losses on helicopter performance by the use of a set of example calculations.

The Effect of Installation Power Losses on the Overall Performance of a Helicopter