49.050 航空航天发动机和推进系统 标准查询与下载

SAE AIR4782A-2008 消防龙头阀和耦合器的历史背景

This SAE Aerospace Information Report (AIR) presents historical information and background data related to hydrant valves and couplers used in worldwide ground refueling of commercial aircraft (hereafter generically referred to as hydrant devices). Military hydrant devices are not included since their mission requirements demand approaches that may differ.1.1 PurposeThe purpose of this document is to provide definitions, background and educational information for use by design engineers, users of the systems and other interested parties who are involved with hydrant devices and associated equipment.1.2 Field of ApplicationSoon after World War II, the military techniques for underwing refueling of turbine-engined aircraft were adopted for use on commercial aircraft. Advantages include significantly improved safety, convenience and rapidity of refueling.Refueling systems for commercial aircraft evolved to comprise five basic elements, as follows:a. Hydrant systems (or supply systems)b. Hydrant couplers (hydrant system to servicer systems)c. Servicer system (hydrant to aircraft)d. Aircraft couplings (service systems to aircraft fuel systems)e. Aircraft fuel systems Element (d), the aircraft couplings, are now true worldwide standards, having been adopted for military and commercialaircraft of all countries, and controlled by international standard documents.This document applies to the hydrant valve portions element (a), the entire element (b) and applicable portions of element (c). Some references to other elements are included, where pertinent.

Hydrant Valve and Coupler Historical Background

SAE AIR1903-2008 航空器无自动力系统

An airplane fuel tank inerting system provides an inert atmosphere in a fuel tank to minimize explosive ignition of fuel vapor.This AIR deals with the three methods of fuel tank inerting systems currently used in operational aircraft: (1) on-board inert gas generation systems (OBIGGS), (2) liquid/gaseous nitrogen systems and (3) Halon systems. The OBIGGS andnitrogen systems generally are designed to provide full-time fuel tank fire protection; the Halon systems generally are designed to provide only on-demand or combat-specific protection.This AIR does not treat the subject of Explosion Suppression Foam (ESF) that has been used for fuel tank explosion protection on a number of military aircraft. ESF is a totally passive, full-time protection system with multiple andsimultaneous hit capability up to 23 mm. The primary disadvantages of foam are weight, reduction of usable fuel, and theadded maintenance complexity when the foam must be removed for tank maintenance or inspection. AIR4170A is anexcellent reference for the use of ESF for fuel tank explosion protection [1].

Aircraft Inerting Systems

STANAG 3609-2008 固定航空燃油接收、储存和分配系统的维护标准

STANDARDS FOR MAINTENANCE OF FIXED AVIATION FUEL RECEIPT, STORAGE AND DISPENSING SYSTEMS

SAE AIR5871-2008 燃气涡轮发动机用预兆

1.1 PurposeThis document applies to prognostics of gas turbine engines and its related auxiliary and subsystems. Its purpose is to define the meaning of prognostics with regard to gas turbine engines and related subsystems, explain its potential and limitations, and to provide guidelines for potential approaches for use in existing condition monitoring environments. It also includes some examples.1.2 Field of ApplicationThis document seeks to meet the increasing interest in gas turbine engine prognostics. Specifically, the document tries to provide a timely guideline for applying prognostic technologies to enhance the capability of current monitoring and diagnostic systems. Some examples are provided that are intended to illustrate different approaches and methodologies.

Prognostics for Gas Turbine Engines

BS EN 4300:2008 航空航天系列.发动机项目的识别标识.设计标准

This standard:  describes the location and the layout of the marks of the item;  describes the marking processes to be used according to the environment and the function of the items;  determines the selection conditions of the marks;  determines the compatibility conditions of the marking processes with the constitution, the production and the use of the items. This document applies to aerospace engine items and shall be used in conjunction with EN 4301.

Aerospace series - Identification marking of engine items - Design standard

DS/EN 4300:2008 航空航天系列 发动机项目的识别标记 设计标准

This standard:- describes the location and the layout of the marks of the item;- describes the marking processes to be used according to the environment and the function of the items;- determines the selection conditions of the marks;- determines the compatibility conditions of the marking processes with the constitution, the production and the use of the items.This document applies to aerospace engine items and shall be used in conjunction with EN 4301.

Aerospace series - Identification marking of engine items - Design standard

EN 4300:2008 航空航天系列.发动机项目的识别标识.设计标准

This standard: describes the location and the layout of the marks of the item; describes the marking processes to be used according to the environment and the function of the items; determines the selection conditions of the marks; determines the compatibility conditions of the marking processes with the constitution, the production and the use of the items.This document applies to aerospace engine items and shall be used in conjunction with EN 4301.

Aerospace series - Identification marking of engine items - Design standard

CEN EN 4300-2008 航空航天系列 发动机项目识别标志 设计标准

This standard: ? describes the location and the layout of the marks of the item; ? describes the marking processes to be used according to the environment and the function of the items; ? determines the selection conditions of the marks; ? determines the compatibility conditions of the marking processes with the constitution, the production and the use of the items. This document applies to aerospace engine items and shall be used in conjunction with EN 4301.

Aerospace series - Identification marking of engine items - Design standard

SAE ARP5757-2008 发动机元部件试验导则

This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs. The purpose of this document is to provide guidance on demonstrating compliance with aircraft engine certification authority requirements for engine components. Many complete engine tests are done as part of the overall engine substantiation and certification process. But often during the engine testing process it is not practical to exercise all of the components of the engine to the extreme environmental limits each will encounter during operation in service. A simple example is during on the ground engine demonstrations the various components may not be exposed to the range of ambient temperature that will exist in the aircraft application. Additional tests or analysis may be required to demonstrate that the component will operate successfully throughout the range of ambient temperature conditions. There are a number other environmental conditions and combinations of conditions that can best be evaluated at the engine component or subsystem level. This ARP is written to address the engine components associated with a new engine program certification. But the guidance may also be used for validating design changes to previously certified engines. However, when using this ARP for substantiating design changes, all test parameter levels, times, and pass/fail criteria should be reviewed to make sure they are adequate for the already certified engine application.

Guidelines for Engine Component Tests

SAE ARP5783-2008 健康和使用监控指标监测的监控器

This recommended practice applies to vibration monitoring systems for rotorcraft and fixed-wing drive trains, airframes, propulsion systems, electric power generators, and flight control systems. It addresses all aspects of metrics, including what to measure, how to measure, and how to evaluate the results. The objective of this document is to provide recommendations for evaluating the performance of vibration based diagnostic algorithms in vehicle Health and Usage Monitoring Systems.

Health and Usage Monitoring Metrics Monitoring the Monitor

SAE ARP4418A-2008 航空器发动机气源放气中发动机和APU产生污染物的取样和测量用实施规程

Aircraft propulsion engine and APU manufacturers shall demonstrate that air provided to the aircraft cabin is of acceptable quality. This ARP provides the basic information required to perform an engine bleed air quality certification test. This document provides the recommended levels and describes the measurement procedures required for the quantification of gaseous and particulate contaminants, which may be present in aircraft engine bleed air. Recommended techniques for engine sampling and sample transfer are given, together with specific analytical methodology, for each of the contaminants listed in Section 3. Recommendations are also made for an engine test format and for the allowance of ambient air quality on the measured engine contaminant concentration levels. The list and recommended limits of contaminants in Table 1 are considered appropriate for the certification and passenger safety requirements of both civil and military aircraft. If testing is performed on the aircraft, the operator should be aware that other sources of contamination may be present.

(R) Procedure for Sampling and Measurement of Engine and APU Generated Contaminants in Bleed Air Supplies from Aircraft Engines

ASTM F2689-08 无人飞机系统用往复式火花点火式发动机的设计和制造的标准实施规程

This practice provides designers and manufacturers of engines for unmanned aircraft systems design requirements and criteria to use in designing and manufacturing engines. Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers'' guidance. Compliance with this specification is intended to demonstrate an adequate level of reliability in accordance with the UAS safety objectives.1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for unmanned aircraft systems. 1.2 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 Design and Manufacture of Reciprocating Spark Ignition Engines for Unmanned Aircraft Systems

KS W 4020-2007(2012) 装备的飞机推进系统

Installation of aircraft propulsion system, general specification for

SAE AS17107A-2007 1型标准轻型航空发电机和电动发电机主用的环形球轴承

(R) BEARING, BALL, ANNULAR, PRIMARILY FOR AIRCRAFT GENERATORS AND MOTOR-GENERATORS, STANDARD LIGHT, TYPE I

(R) BEARING, BALL, ANNULAR, PRIMARILY FOR AIRCRAFT GENERATORS AND MOTOR-GENERATORS, STANDARD LIGHT, TYPE I

TIA SP 3-4426-AD10-D-1-2007 4对100 Ohm 6类电缆敷设的传输性能规范

An impedance controlled measurement fixture consists of a device designed to provide controlled 4 interconnections to the DUT. The fixture provides an interface that is designed to maintain correct 5 DM and CM impedance of the pairs in the transmission

Transmission Performance Specifications for 4- Pair 100 Ohm Augmented Category 6 Cabling To be published as TIA-568-B.2-10

SAE AS478N-2007 识别标记方法

This standard provides the following: a. definition of terms pertaining to marking; b. symbols for marking location; c requirements and restrictions for permanent markings; d. types of marking methods; e. rules for designating marking methods; and f. table listing marking methods. To define and control marking methods, and to provide a method for specifying desired marking methods on aerospace engineering drawings of parts and assemblies. Standard revised to replace cancelled military specification TT-L-50.

Identification Marking Methods

ARINC 633-2007 AOC空中地面和信息交换格式

AOC AIR-GROUND DATA AND MESSAGE EXCHANGE FORMAT

AOC AIR-GROUND DATA AND MESSAGE EXCHANGE FORMAT

SAE AS5877A-2007 航空器压力加注嘴用详细规范

This SAE Aerospace Standard (AS) prescribes requirements for the various types of nozzles that are used for refueling of aircraft fitted with pressure fuel servicing systems. It is to be used as a replacement for MIL-N-5877, MS29520 and for all commercial applications. Classification: The nozzles specified herein shall be classified in accordance with Table 1. Type I nozzles are primarily used by the US military services; Type II nozzles are primarily used in commercial service. Field of Application: This specification is for all nozzles that are utilized either in commercial or military applications where the aircraft system utilizes pressure fuel-servicing systems. The nozzle shall be compatible with and mate with the international aircraft adapter fitting in accordance to ISO 45 Aircraft Pressure Refueling Connections. Nozzle Configuration: The nozzle shall conform to the design interface envelope of Figure 1 of this document. The inlet configuration outside of the envelope is at the manufacturer's option and may be designed to have an angled, straight or variable configuration to meet individual requirements. The envelope restrictions are mandatory to assure that aircraft fuel system manufacturers and nozzle manufacturers have a common interface with which to work. This will assure compatibility between the available nozzles and the aircraft refueling system adapters. The nozzle may be configured to include various features and be available in various inlet configurations including, but not necessarily limited to those shown in Table 2.

Detailed Specification for Aircraft Pressure Refueling Nozzle

TIA-1106-2007 CCAT应用的安全分组结构

The present document specifies the bearer specific part of secured packets structure. Thegeneric part is specified in ETSI TS 102 225 [13].

Secured Packet Structure for CCAT Applications

SAE ARP1587B-2007 航空燃气涡轮发动机监测系统指南

This SAE Aerospace Recommended Practice (ARP) examines the whole construct of an Engine Health Management (EHM) system. This keystone document gives a top-level view and addresses EHM description, benefits, and capabilities, and provides examples. This ARP purposely addresses a wide range of EHM architectures to demonstrate possible EHM design options. This ARP is not intended as a legal document and does not provide detailed implementation steps, but does address general implementation concerns and potential benefits. Other SAE documents (Aerospace Standards, Aerospace Recommended Practices, and Aerospace Information Reports) address specific component specifications, procedures and "lessons learned". The purpose of this ARP is to provide an Aircraft Gas Turbine Engine Health Management System Guide for commercial and government operators, aircraft manufacturers, engine producers and equipment suppliers. This guide is provided for program managers to obtain a sufficiently detailed understanding of EHM systems to make funding decisions. Similarly, it can be used by design personnel to obtain a systems perspective as well as references to guides on detail design of all aspects of an EHM system.

Aircraft Gas Turbine Engine Health Management System Guide