49.045 结构和结构元件 标准查询与下载

SAE AIR805C-2011 商用运输飞机喷气式风挡除雨系统

The purpose of this information report is to present factors which affect the design and development of jet blast windshield rain removal systems. Rain removal system design will generally be unique to specific aircraft. Design of these systems typically requires a preliminary design for the system based on available empirical data to be followed with a laboratory development program and a flight test validation program. Published windshield rain removal performance test data is available only for limited windshield configurations.

Jet Blast Windshield Rain Removal Systems for Commercial Transport Aircraft

SAE AS8017C-2011 防撞击灯光系统的最低生产标准

This SAE Aerospace Standard (AS) establishes minimum performance standards for new equipment anticollision light systems. This Aerospace Standard defines minimum light intensity in terms of "effective intensity" as defined in paragraph 3.5 of this standard and specified vertical and horizontal directions about the longitudinal and vertical axis of the airplane. It will also define flash rate and color for the anticollision light system. It is not intended that this standard require the use of any particular light source such as Xenon, LED or any other specific design of lamp.

Minimum Performance Standard for Anticollision Light Systems

SAE ARP6404-2011 航空器轮胎电阻测试

This document points to a standard ASTM test method utilized by land vehicle manufacturers and others to provide the electrical resistance of a tire. It is desired that this ASTM test method is also used with aircraft tires. This method will assure that more accurate repeatable data is provided to those in the aerospace industry who request it. The purpose of this ARP is to define a test procedure for determining the electrical resistance of an aircraft tire.

Aircraft Tire Electrical Resistance Test

SAE AS8037B-2011 飞机的位置灯的最低性能标准

This Aerospace Standard (AS) establishes minimum performance standards for new equipment position lights. 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

SAE ARP5660A-2011 除冰设施操作规程

The purpose of this document is to provide guidelines for the standardization of safe operating procedures to be used in performing the services and maintenance at Designated Deicing Facilities (Central Deicing Facilities/Remote Deicing Facilities) that are necessary for proper de-icing/anti-icing of aircraft on the ground and performing of associated checks in accordance with the various approved ground icing programs, while considering applicable local environmental, operational and economic requirements. This document should be used by regulators and airport authorities to develop and standardize approvals and permits for the establishment and operation of a DDF. The coordination of stakeholders is required prior to the approval of design plans for a deicing facility. Operating procedures must be agreed to, in writing, by all air operators, airport authorities, regulators and service providers prior to commencing deicing operations.

Deicing Facility Operational Procedures

SAE AS5901B-2010 SAE AMS1424 和 SAE AMS1428 飞机除冰/防冰液的喷水和耐高湿测试方法

This document establishes the minimum requirements for an environmental test chamber, and test procedures to carry out anti-icing performance tests according to the current materials specification for aircraft deicing/anti-icing fluids. The primary purpose for such a test method is to determine the anti- icing endurance under controlled laboratory conditions of SAE AMS1424 Type I and AMS1428 Type II, III and IV fluids.

Water Spray and High Humidity Endurance Test Methods for SAE AMS1424 and SAE AMS1428 Aircraft Deicing/Anti-Icing Fluids

SAE AS21240-2010 - 65到+ 250℉自润滑式平头套筒轴承

This part sheet is being updated and re-formatted from MS21240 Rev D to the SAE AS 21240

Bearing, Sleeve, Plain, Self Lubricating -65 to +250 °F

SAE AIR5567A-2010 刹车盘催化氧化测试方法

The scope of the test method is to provide stakeholders including fluid manufacturers, airport operators, brake manufacturers, aircraft constructors, aircraft operators and airworthiness authorities with a relative assessment of the effect of deicing chemicals on carbon oxidation. This simple test is only designed to assess the relative effects of runway deicing chemicals by measuring mass change of contaminated and bare carbon samples tested under the same conditions. It is not possible to set a general acceptance threshold oxidation limit based on this test method because carbon brake stack oxidation is a function of heat sink design and the operating environment.

Test Method for Catalytic Carbon Brake Disk Oxidation

SAE AIR4566A-2010 防撞起落架设计

The intent of this SAE Aerospace Information Report (AIR) is to document the design requirements and approaches for the crashworthy design of aircraft landing gear. This document covers the field of commercial and military airplanes and helicopters. This summary of crashworthy landing gear design requirements and approaches may be used as a reference for future aircraft.

Crashworthy Landing Gear Design

ASTM F520-10 航空航天用透明材料的环境耐受性的标准试验方法

This test method, when applied to aerospace transparencies of either monolithic glass/plastic or laminated combinations, is a measure of the ability of the transparency to withstand the effects of artificially induced environments. The test may be used on configurations employing electrically conductive coatings, and also to evaluate the integrity of noncoated materials. The resistance of the transparent enclosure to environmental effects may vary appreciably depending on the size, geometry, material of construction, coating integrity, coating density, and other factors.1.1 This test method covers determination of the effects of exposure to thermal shock, condensing humidity, and simulated weather on aerospace transparent enclosures. 1.2 This test method is not recommended for quality control nor is it intended to provide a correlation to actual service life. 1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard. 1.3.1 Exceptions8212;Certain inch-pound units are furnished in parentheses (not mandatory) and certain temperatures in Fahrenheit associated with other standards are also furnished. 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 Test Method for Environmental Resistance of Aerospace Transparencies

ASTM F330-10 航空航天用透明外壳鸟撞试验的标准试验方法

This test method may be used for: bird impact testing of aircraft crew compartment transparencies and supporting structure to verify the design; compilation of test data for use in verification of future transparency and supporting structure design and analytical methods; and comparative evaluation of materials.1.1 This test method covers conducting bird impact tests under a standard set of conditions by firing a packaged bird at a stationary transparency mounted in a support structure. 1.2 The values stated in inch-pound units are to be regarded as standard. The values given in parentheses are mathematical conversions to SI units that are provided for information only and are not considered standard. 1.3 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. For specific hazard statements, see Section 8.

Standard Test Method for Bird Impact Testing of Aerospace Transparent Enclosures

SAE ARP5672-2009 航空器的雨滴静电干扰检定

Aircraft surface precipitation static (p-static) charge can be generated when aircraft fly through ice particles, rain, snow and dust. However, in the context of p-static protection, this document is used for providing guidance for any thing that charges the outer surface of the aircraft (e.g. engine exhaust). P-static discharges from the aircraft can disrupt aircraft communication, navigation, and surveillance radios, and can damage aircraft radomes and windshields. This SAE Aerospace Recommended Practice (ARP) defines design considerations for aircraft p-static control and related methods to verify acceptable aircraft p-static performance. This ARP addresses p-static charging due to the aircraft flying through ice particles, rain, snow and dust. It does not address other triboelectric charging that may be present in an aircraft, such as triboelectric fuel charging or environmental control system or air conditioning static charging. It does not address electrostatic charging created by passengers or crewmembers, or electrostatic discharge hazards to electronics and systems. The purpose of this document is to provide information and guidance concerning an acceptable means, but not the only means, of compliance with Parts 23, 25, 27, and 29 (23.867, 25.899, 27.610, and 29.610) of the Federal Aviation Regulations (FAR) and European Aviation Safety Agency (EASA), applicable to aircraft for protection against the adverse effects of precipitations static. This ARP provides general information on aircraft surface p-static charging mechanisms and the impact p-static has on aircraft systems. It addresses elements of effective aircraft p-static control design. Finally, it defines methods for verifying acceptable aircraft p-static control. Accordingly, this material is neither mandatory nor regulatory in nature and does not constitute a regulation. Aircraft p-static control should be addressed early in the aircraft design to be effective. Effective aircraft design features and effective verification methods will result in an aircraft that can be operated in p-static charging conditions without adverse impact to the aircraft systems. The existing reports and guidance do not provide standards for aircraft design to control p-static or standard methods to verify acceptable aircraft p-static control. This document provides acceptable approaches to design effective aircraft pstatic control, and provides acceptable methods to verify the design effectiveness. Existing aircraft certification regulations in Title 14 CFR 25.899, 27.610(d) and 29.610(d), specifically address aircraft pstatic control. These regulations include the requirement to minimize the accumulation of electrostatic charge in order to reduce to an acceptable level the effects of static electricity on the functioning of essential electrical and electronic equipment. Compliance may be shown by bonding the components to the airframe, or incorporating other acceptable means to dissipate the static charge. Title 14 CFR 23 is an exception, as it does not specifically address aircraft p-static control, however p-static is considered a foreseeable operating condition, so all aircraft designed for operation in instrument meteorological conditions (IMC) should have certified p-static control. Prior to this document, the absence of specific standards or guidance material resulted in inconsistent application and verification of the requirements for aircraft p-static control.

Aircraft Precipitation Static Certification

SAE AS21151E-2009 -65至300°F温度的II型自调整机身双排精密度外螺纹、有杆端滚珠轴承

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

SAE AIR5800-2009 着陆轮胎预转

This SAE Aerospace Information Report (AIR) applies to landing gear tires and airframe structure for all types and models of civil and military aircraft having tires as part of the landing This report describes the advantages and disadvantages of prerotating tires prior to landing, and explains why this practice is not generally adopted. Two potential benefits of this practice are considered: 1) Tire wear and 2) Spin-up loads on the landing gear and aircraft structure.

Tire Prerotation at Landing

SAE ARP1311C-2009 起落装置结构和机理

This SAE Aerospace Recommended Practice (ARP) applies to landing gear structures and mechanisms (excluding wheels, tires, and brakes and other landing gear systems) for all types and models of civil and military aircraft. All axles, wheel forks, links, arms, mechanical and gas/oil shock struts, downlock and uplock assemblies, braces, trunnion beams, and truck beams etc., that sustain loads originating at the ground, and that are not integral parts of the airframe structure, should be designed and validated in accordance with this document. Hydraulic actuators (retraction, main and nose gear steering, positioning, damping, etc.) should also be included in this coverage. System level, non-structural components such as retraction/extension valves, controllers, secondary structure and mechanisms in the airframe (e.g., manual release mechanisms, slaved doors) as well as equipment that is located in the cockpit are not addressed in this ARP. This document establishes minimum recommended design requirements and validation for landing gear structure and mechanisms. In addition, recommended guidelines regarding priorities in landing gear structural design particularly in the early design stages is provided.

Landing Gear Structures and Mechanisms

ASTM F428-09(2014) 航空航天用玻璃外壳抗划痕硬度的标准试验方法

4.1 Scratches exist on all glass surfaces. Often there are very fine scratches from cleaning operations that are not visible when looking through the glass. Visible scratches may be distracting to the observer looking through the transparency. Therefore, a procedure to define the severity scratches is useful. A visual standard is used because it is not practical to measure the dimensions of the fine scratches in the scope of this test method. 1.1 This test method covers the visual inspection of scratches on the glass surface of aerospace transparent enclosures. 1.2 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard. 1.3 This standard may involve hazardous materials, operations, and equipment. 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 Test Method for Intensity of Scratches on Aerospace Glass Enclosures

ASTM F548-09(2014) 航空航天用透明塑料抗划痕硬度的标准试验方法

4.1 Scratches exist on all transparent plastic surfaces. Usually they are very fine scratches from cleaning operations that are not visible when looking through the plastic. Deeper scratches may result from careless cleaning or handling. While these may not be deep enough to affect the structural integrity of the part, their appearance in certain locations may be distracting to the observer looking through the plastic. Therefore, a procedure to define these scratches is useful. 1.1 This test method covers the visual inspection of shallow or superficial scratches on the surface of aerospace transparent plastic materials. 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 Test Method for Intensity of Scratches on Aerospace Transparent Plastics

SAE AS4052B-2008 密封装置设计:刮具、起重装置、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 in Table 1, is a variant of SAE AS 4716, the accepted gland standard for MS28775, O-ring packing seals. Piston rod diameters, gland internal diameters, groove sidewall angles and the surface finish are all defined by SAE AS 4716, but the gland outer retaining wall diameter is changed. The traditional scraper design installed into the glands detailed in Table 1 typically utilize components made from urethane or nitrile materials. These scraper designs, while still acceptable, must be reviewed in consideration to deicing, cleaners and disinfectant fluids applied to or in contact with the landing gear, as the materials of construction for the installed scrapers may not be compatible to these fluids. Exposure of the scraper to incompatible fluids is likely to reduce the performance of the scraper. In addition, an alternative scraper gland is also covered by this document and shown in Table 2. It is also a variant of AS4716, however this gland has a reduced atmospheric gland lip and profiled lead in geometry to allow for a PTFE jacket metal spring energized scraper to be installed. The advantages of the PTFE jacket metal spring energized scraper design is that the materials of construction are chemically inert, greatly reducing the possibility of negative performance due to incompatibility with deicers, cleaners and disinfectant fluids. SAE AS 4088 is similar to the hardware design in Table 1 of this document, which 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. This document is intended to present a groove which will accommodate an improved scraper/wiper ring assembly design and is not intended to obsolete the MS33675 gland standard.

Gland Design: Scraper, Landing Gear, Installation

SAE AS21151D-2008 -65～300℉、II型机身自调外螺纹精密双排杆端滚珠轴承

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

SAE ARP1070C-2008 全部航空器兼容性用防滑制动控制系统的设计和测试

This document recommends minimum requirements for antiskid brake control to provide total aircraft systems compatibility. Design and operational goals, general theory, and functions, which should be considered by the aircraft brake system engineer to attain the most effective skid control performance, are covered in detail. Methods of determining and evaluating antiskid system performance are discussed. While this document specifically addresses antiskid systems which are a part of a hydraulically actuated brake system, the recommended practices are equally applicable to brakes actuated by other means, such as electrically actuated brakes. To recommend minimum antiskid brake control design practices, laboratory and aircraft test requirements to provide total aircraft system compatibility.

Design and Testing of Antiskid Brake Control Systems For Total Aircraft Compatibility