49.045 结构和结构元件 标准查询与下载

SAE AS27642B-2002 (R)特轻型机身用滚珠轴承.代替1998年7月23日作废的MS27642G.FSC 3110

(R) Bearing, Ball, Airframe, Extra Light Duty Should Be Used Instead of MS27642G, Which Was Cancelled on 23 July 1998; FSC 3110TABLE 1 - BEARING DIMENSIONS AND MAXIMUM TORQUETABLE 2 - BEARING ECCENTICITIES AND LOADS

(R) Bearing, Ball, Airframe, Extra Light Duty Should Be Used Instead of MS27642G, Which Was Cancelled on 23 July 1998; FSC 3110

SAE AS27641B-2002 (R)中型抗摩擦机架用滚珠轴承

(R) Bearing, Ball, Airframe, Anti-Friction, Intermediate DutyTABLE - DIMENSIONS AND LOADS

(R) Bearing, Ball, Airframe, Anti-Friction, Intermediate Duty

ASTM F790-02 航空塑料透明外壳材料测试标准指南

1.1 This guide is intended to summarize the standard test methods available on individual and composite materials utilized in fabrication of aerospace plastic transparent enclosures. As such, it is intended to specifically include transparent thermoplastics, transparent elastomers, and reinforced plastics, whether thermoplastic or thermosetting.1.2 This guide is intended as an aid in the search for test methods pertinent to Aerospace Plastic Transparent Enclosures. It should be understood that all methods listed may not apply to all enclosures.1.3 The standards included refer to the properties or aspects listed in Table 1. The properties or aspects are listed in alphabetical order and the descriptions used are intended to facilitate the search.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 and health practices and determine the applicability of regulatory limitations prior to use.

Standard Guide for Testing Materials for Aerospace Plastic Transparent Enclosures

SAE AIR4777A-2002 在飞机机轮及制动器生产及运行期间采用的无损检测(NDI)方法

This SAE Aerospace Information Report (AIR) identifies current nondestructive inspection (NDI) methods used to insure product integrity and maximize "in service" life of the major structural components of aircraft wheel and brake assemblies.

Nondestructive Inspection (NDI) Methods Used During Production and Operation of Aircraft Wheels and Brakes

ARMY MIL-STD-1477 C VALID NOTICE 1-2002 军用系统演示符号(公制)

MIL-STD-1477C(MI), dated 30 September 1996, has been reviewed and determined to be valid for use in acquisition.

SYMBOLS FOR ARMY SYSTEMS DISPLAYS (METRIC)

SAE ARP5904-2002 航空加油机结冰

This SAE Aerospace Recommended Practice (ARP) document establishes criteria and recommended practices for the use of airborne icing tankers to aid in design and certification of aircraft ice protection systems and components. Several icing tankers are described, along with their capabilities and suggested use. Sample data for these tanker spray systems are included, shown with 14 CF R Parts 25 and 29, Appendix C icing envelopes for continuous maximum and intermittent maximum icing conditions. (Note: In the remainder of this document, the phrase "Appendix C icing envelopes" will be used for brevity.) This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances. The purpose of this document is to support the objective of the "FAA Inflight Aircraft Icing Plan" of establishing acceptance criteria for icing tankers. To this purpose, the document surveys existing airborne icing tanker technology and provides guidance for the acceptance of icing tanker information for certification purposes. The document provides some, but not all, criteria that shall be considered when selecting and using an icing tanker for artificial inflight icing tests. Use of an airborne icing tanker to obtain certification information shall be negotiated with and approved by a certification office, and included in the certification plan for the aircraft.

Airborne Icing Tankers

SAE AS8037A-2001 飞机位置灯的最低性能标准

This Aerospace Standard (AS) establishes minimum performance standards for position lights for nighttime operation. It is intended to describe suitable means for compliance with current Federal Aviation Regulations defining minimum position light requirements. This Aerospace Standard defines minimum light intensity in terms of candelas in vertical and horizontal directions about the longitudinal, vertical, and lateral axes of the aircraft. It also defines color tolerances in terms of limiting chromaticities for the light emitted from the position lights. It is not intended that this standard require the use of any particular light source such as quartz-halogen, incandescent, or any other specific design of lamp.

Minimum Performance Standard for Aircraft Position Lights

NAVY QPL-24702-6-2001 一次性液压过滤元件的一般规格(米制)

This list has been prepared for use by or for the Government in the acquisition of products covered by the subject specification and such listing of a product is not intended to and does not connote endorsement of the product by the Department of Defense

FILTER ELEMENTS, HYDRAULIC, DISPOSABLE, GENERAL SPECIFICATION FOR (METRIC)

NAVY QPL-AS23899-1-2001 听觉保护器

This list has been prepared for use by or for the Government in the acquisition of products covered by the subject non-government standard, and such listing of a 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 adopted issue of the applicable non-government standard. 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 or otherwise affect the obligation of the manufacturer to comply with the non-government standard requirements.

AURAL PROTECTOR, SOUND [Superseded: NAVY QPL-23899 -10 CANC NOTICE 1, NAVY QPL-23899 -10, NAVY QPL-23899 -9, NAVY QPL-23899 -8, NAVY QPL-23899 -7, NAVY QPL-23899 -6, NAVY QPL-23899 -5, NAVY QPL-23899 -4, NAVY QPL-23899 -3, NAVY QPL-23899 -2, N

SAE AS21151C-2001 轴承，球头，杆端，双列，精密，外螺纹，自调心，机身，II 型，-65° 至 300°F

Bearing, Ball, Rod End, Double Row, Precision, External Thread, Self-Aligning, Airframe, Type II, -65 Degrees to 300 Degrees F FSC 3110TABLE1 - DASH NUMBERSTABLE2 - ENGINEERING DATA

Bearing, Ball, Rod End, Double Row, Precision, External Thread, Self-Aligning, Airframe, Type II, -65° to 300°F

SAE ARP5429-2001 使用等效损伤谱的降落装置疲劳试验

This SAE Aerospace Recommended Practice (ARP) applies to fatigue testing of landing gear and landing gear components. Advancements in fatigue analysis methodology, combined with larger and faster computers, have led to more thorough and accurate fatigue life predictions. Traditional methodology involved the analysis of block loading spectra using S-N curves excluding the effect of plastic strain, residual stresses and the effect of the loading sequence. Todays methodology employs strain-life analysis combined with the application of Neubers equation and the effects of the loading sequence to determine the true state of stress of every load set in a flight-by-flight spectrum. While providing the ability to analyze the real world our advancements in analytical methodology have surpassed the practicality of physical testing. While it is relatively simple to analyze a flight-by-flight spectrum, the cost and time required to test a flight-by-flight spectrum is prohibitive. The purpose of this document is to provide a method and rationale for creating a physical test spectrum which is significantly reduced from the analytical spectrum and yet provides an accurate accumulation of the analytical damage for all critical areas of the article under test. While the focus of this document is the fatigue testing of landing gear, the approach is applicable to most mechanical structures subject to safe life fatigue analyses.

Landing Gear Fatigue Tests with Equivalent Damage Spectra

SAE AIR5388-2001 独特的机轮和制动器设计

This SAE Aerospace Information Report (AIR) has been prepared by a panel of the SAE A-5A Committee and is presented to document unique design approaches used for aircraft wheels and brakes. The purpose of this AIR is to describe wheel and brake designs possessing unique features or approaches to allow them the meet the requirements of the particular airplane for which they were intended. Wherever possible, the requirements driving these design and the lessons learned are documented. This AIR is intended to document the ingenuous solutions that have lead eventually to the wheel and brake designs in use today and pointing to the brakes for tomorrow.

Unique Wheel and Brake Designs

SAE AS6053-2001 飞机起落架减震器撞击测试

This specification covers definition of landing impact tests which are to be conducted on landing gear assemblies including shock absorbers, suggested instrumentation for the tests and required data of the resulting test report. It is intended to standardize impact test procedures on landing gear shock absorbers and to provide sufficient data to allow evaluation of the design with respect to requirements of MIL-L-8552 and MIL-S- 8959 as applicable.

Tests, Impact, Shock Absorber Landing Gear, Aircraft

SAE AIR4253A-2001 带有遥控自动驾驶仪飞行操纵系统的飞机用传动系统的描述

This information report (AIR) provides design information of various contemporary aircraft fly-by-wire flight control actuation systems that may be useful in the design of future actuation systems for similar applications. This AIR provides a description of representative state-of-the-art, fly-by-wire (FBW) actuation systems used in flight control systems of manned aircraft. It presents the basic characteristics, hardware descriptions, redundancy concepts, functional schematics, and discussions of the servo controls, failure monitoring, and fault tolerance. All existing FBW actuation systems are not described herein; however, those most representing the latest designs are included. While this AIR is intended as a reference source of information for future aircraft actuation system designs, the exclusion or omission of any other appropriate actuation system or subsystem should not limit consideration of their use on future aircraft.

Description of Actuation Systems for Aircraft with Fly-By-Wire Flight Control Systems

SAE AS4052A-2001 密封装置设计:铲运机起落架装置安装

This SAE Aerospace Standard (AS) covers an alternate gland design for the installation of scraper/wiper rings in the lower end of landing gear shock struts for the purpose of contaminant exclusion. The defined scraper gland covered by this document, as shown, is a variant of MIL-G-5514, the accepted gland standard for MS28775. Piston diameters, gland internal diameters, and the groove sidewall angles and surface finish are defined by MIL-G-5514, but the gland outer retaining wall diameter is changed. AS4088 is similar to this document, but was developed by SAE A-6 for flight control and general purpose cylinders. It differs from this document primarily by the clearance between the rod (piston) and outer gland wall. Since landing gears are more susceptible to dirt contamination, the additional clearance provides a larger path to allow excessive dirt accumulation to exit the gland.

Gland Design: Scraper, Landing Gear, Installation

SAE ARP1821A-2001 飞机地面浮选分析法

This SAE Aerospace Recommended Practice (ARP) includes recommended ground flotation analysis methods for both paved and unpaved airfields. The purpose of this document is to identify the recommended aircraft ground flotation analysis methods that should be used for aircraft landing gear design.

Aircraft Ground Flotation Analysis Methods

SAE AS26805-2001 气体压缩机装置的一般要求

This specification covers the general requirements for the design and construction of air/gas compressor units (see 6.4.1). The detail requirements for a particular air compressor unit shall be as specified in the individual equipment specification for that particular air compressor unit (see 6.2).

Compressor Units, Air/Gas, General Requirements for

SAE AIR5396-2001 积冰条件下飞行器的表征

This SAE Aerospace Information Report (AIR) provides various graphical displays of atmospheric variables related to aircraft icing conditions in natural clouds. It is intended as a review of recent developments on the subject, and for stimulating thought on novel ways to arrange and use the available data. Included in this Report is FAR 25 (JAR 25) Appendix C, the established Aircraft Icing Atmospheric Characterization used for engineering design, development, testing and certification of civilian aircraft to fly in aircraft icing conditions.

Characterization of Aircraft Icing Conditions

ARMY MIL-HDBK-765 NOTICE 2-2001 用于安全设计的多相电力系统指导方针

This notice should be filed in front of MIL-HDBK-765(MI), dated 14 July 1988.

GUIDELINES FOR SAFE DESIGN OF POLYPHASE ELECTRICAL SYSTEMS

SAE ARP1107B-2001 有人驾驶飞机的尾部缓冲器

This document provides recommended practices for the design, installation, qualification, and operational requirements of the tail bumper for piloted aircraft. This recommended practice covers the fixed structure, or independent energy absorbing system affixed to the airframe to afford protection to the control surfaces, engine and other portions during ground handling, take-off and landing.

Tail Bumpers for Piloted Aircraft