ASTM F3062/F3062M-19 飛機(jī)動(dòng)力裝置安裝的標(biāo)準(zhǔn)規(guī)范

1.1 This specification covers minimum requirements for the installation and integration of powerplant system units. 1.2 This specification is applicable to small aeroplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.” 1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to the ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. 1.4 References within this standard normally refer to documents in United States legal system. Appendix X1 cross references documents in the legal system of other countries of corresponding content. 1.5 Units—The values stated are SI units followed by imperial units in brackets. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard. 1.6 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use. 1.7 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

Standard Specification for Aircraft Powerplant Installation

ASTM F3066/F3066M-17 飛機(jī)動(dòng)力裝置安裝危險(xiǎn)減輕的標(biāo)準(zhǔn)規(guī)格

1.1 This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes. 1.2 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. 1.3 Units—The values stated are SI units followed by imperial units in brackets. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard. 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use. 1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

Standard Specification for Aircraft Powerplant Installation Hazard Mitigation

SAE ARP755C-2013 飛機(jī)推進(jìn)系統(tǒng)性能配置命名和術(shù)語

Aircraft Propulsion System Performance Station Designation and Nomenclature

SAE ARP1625B-2013 冷氣系統(tǒng)發(fā)射物或投射物的設(shè)計(jì)、安裝、試驗(yàn)和要求

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This aerospace recommended practice covers the design, installation, tests and data requirements of stored cold gas blowdown systems or subsystems for use in guided projectiles and tactical missiles. The term system, hereafter, refers to units which function as aerodynamic surface control devices, valve actuated control devices, reaction control devices and sensing/control devices.

Cold Gas Systems, Missile or Projectiles Design, Installation, Tests and Requirements for

SAE AS6029A-2013 用于飛行安全的激光控制措施性能標(biāo)準(zhǔn)

This document provides guidance for laser operators and aviation authorities to determine the performance criteria that laser hazard control measures shall meet for the operation of an outdoor laser system in navigable airspace. The document does not cover systems intended to deliberately aim and or track lasers at aircraft except for FAA approved purposes, such as visual warning systems, search and rescue, etc. Aircraft operations to be protected include all types that can be reasonably expected to operate in the affected area, which are traveling at speeds and altitudes defined in the Performance/Functional Requirements section. This document does not add

Performance Criteria for Laser Control Measures Used for Aviation Safety

SAE AS91D-2013 雙旋轉(zhuǎn)螺旋槳軸端(備有螺旋槳的軸承)

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist.

Propeller Shaft Ends, Dual Rotation (Propeller Supplied Bearing)

SAE AS90B-2013 鋁合金螺旋槳葉片軸尺寸規(guī)格

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist.

Propeller Blades Aluminum Alloy, Shank Dimensions for

SAE ARP244B-2013 推進(jìn)器控制安裝清除

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This envelope applies to controls for use on reduction gear sections designed after date of issue.

Propeller Control Installation Clearance

ISO 22072:2011 航空航天.電動(dòng)靜液壓執(zhí)行器(EHA).采購規(guī)范中需規(guī)定的特性

This International Standard defines the general characteristics, reduirements and design data to be included in the procurement technical specification of an electrohydrostatic actuator (EHA) to be used to power aircraft control surfaces or other moving parts of an aerospace vehicle. This type of actuator is an alternative to the hydraulically powered servo-control actuators that are currently Used. ltis intended that this International Standard cover the unidue reduirements of EHASs.

Aerospace - Electrohydrostatic actuator (EHA) - Characteristics to be defined in procurement specifications

GJB 7081-2010 機(jī)載正前方控制板通用規(guī)范

本標(biāo)準(zhǔn)規(guī)定了機(jī)載正前方控制板的要求、質(zhì)量保證和交貨準(zhǔn)備。 本標(biāo)準(zhǔn)適用于戰(zhàn)斗機(jī)及教練機(jī)機(jī)載正前方控制板。

General specification for airborne up front control panel

GJB 624.15A-2010 軍用飛機(jī)科研試飛訓(xùn)練要求 第15部分：飛機(jī)環(huán)境控制

本部分規(guī)定了有人駕駛固定翼飛機(jī)進(jìn)行環(huán)境控制科研試飛訓(xùn)練的通用要求。 本部分適用于有人駕駛固定翼飛機(jī)環(huán)境控制科研試飛訓(xùn)練的技術(shù)準(zhǔn)備、組織實(shí)施與評(píng)價(jià)。特種用途固定翼軍用飛機(jī)可參照?qǐng)?zhí)行。

Training requirement of flight test research for military aircraft.Part 15:Aircraft environment control

GJB 624.13A-2010 軍用飛機(jī)科研試飛訓(xùn)練要求 第13部分：機(jī)載武器火控

本部分規(guī)定了有人駕駛固定翼飛機(jī)進(jìn)行機(jī)載武器火控科研試飛訓(xùn)練的通用要求。 本部分適用于有人駕駛固定翼飛機(jī)機(jī)載武器火控科研試飛訓(xùn)練的技術(shù)準(zhǔn)備、組織實(shí)施與評(píng)價(jià)。特種用途固定翼軍用飛機(jī)可參照?qǐng)?zhí)行。

Training requirements of flight test research for military aircraft.Part 13:Airborne weapon fire control

GJB 624.17-2010 軍用飛機(jī)科研試飛訓(xùn)練要求 第17部分：飛行控制

本部分規(guī)定了有人駕駛固定翼飛機(jī)進(jìn)行飛行控制科研試飛訓(xùn)練的通用要求。 本部分適用于有人駕駛固定翼飛機(jī)飛行控制科研試飛訓(xùn)練的技術(shù)準(zhǔn)備、組織實(shí)施與評(píng)價(jià)。特種用途固定翼軍用飛機(jī)可參照?qǐng)?zhí)行。

Training requirements of flight test research for military aircraft.Part 17:Flight control

ARMY MIL-HDBK-762 VALID NOTICE 2-2006 無控火箭的空氣動(dòng)力學(xué)設(shè)計(jì)

MIL-HDBK-762, dated 24 October 2000, has been reviewed and determined to be valid for use in acquisition.

DESIGN OF AERODYNAMICALLY STABILIZED FREE ROCKETS

ISO 22072:2005 航空航天.電動(dòng)流體靜力傳動(dòng)裝置(EHA).采購規(guī)范中定義的特性

This International Standard defines the general characteristics, requirements and design data to be included in the procurement technical specification of an electrohydrostatic actuator (EHA) to be used to power aircraft control surfaces or other moving parts of an aerospace vehicle. This type of actuator is an alternative to the hydraulically powered servocontrol actuators that are currently used. It is intended that this International Standard cover the unique requirements of EHAs. Test methods are defined in a separate ISO document.

Aerospace - Electrohydrostatic actuator (EHA) - Characteristics to be defined in procurement specifications

ARMY MIL-HDBK-762 VALID NOTICE 1-2000 無控火箭的空氣動(dòng)力學(xué)設(shè)計(jì)

MIL-HDBK-762, dated 17 July 1990, has been reviewed and determined to be valid for use in acquistion.

DESIGN OF AERODYNAMICALLY STABILIZED FREE ROCKETS

MH/T 6007-1998 飛機(jī)清洗劑

本標(biāo)準(zhǔn)規(guī)定了飛機(jī)清洗劑的技術(shù)要求、試驗(yàn)方法、質(zhì)量檢驗(yàn)規(guī)定、包裝、標(biāo)志、運(yùn)輸和貯存。 本標(biāo)準(zhǔn)適用于可生物降解、水基、水稀釋、環(huán)保型飛機(jī)清洗劑。

aircraft cleaner

HB/Z 223.10-1997 飛機(jī)裝配工藝 操縱面吻合性檢查

本標(biāo)準(zhǔn)規(guī)定了飛機(jī)操縱面吻合性檢查的內(nèi)容、技術(shù)要求和檢查方法等。 　　本標(biāo)準(zhǔn)適用于各型飛機(jī)操縱面的吻合性檢查。

Conformity Check of Control Surfaces in Aircraft Assembly Process

HB 7282-1996 民用航空器動(dòng)力裝置火警探測(cè)系統(tǒng)（熱敏和火焰接觸型）最低性能要求

本標(biāo)準(zhǔn)規(guī)定了以活塞式和渦輪工發(fā)動(dòng)機(jī)為動(dòng)力的民用航空器上所用的動(dòng)力裝置火警探測(cè)系統(tǒng)必須滿足的最低性能要求。 　　本標(biāo)準(zhǔn)適用于以下基本類型的火警探測(cè)系統(tǒng)或其組合： 　　a.Ⅰ型──熱敏型（設(shè)定報(bào)警溫度）當(dāng)探測(cè)系統(tǒng)的傳感器所處環(huán)境溫度高于預(yù)先設(shè)定的報(bào)警溫度時(shí)，應(yīng)發(fā)出的警信號(hào)； 　　b.Ⅱ型──熱敏型（設(shè)定上升速率）當(dāng)探測(cè)系統(tǒng)的傳感器所處環(huán)境溫度的上升速率在預(yù)先設(shè)定值以上時(shí)，應(yīng)發(fā)出報(bào)警信號(hào)； 　　c.Ⅲ型──火焰接觸型　當(dāng)探測(cè)系統(tǒng)的傳感器處在火焰中與火焰體接觸時(shí)，應(yīng)發(fā)出報(bào)警信號(hào)。

Minimum performance requirements for civil aircraft powerplant fire detection systems (heat sensitive and flame contact types)

HB 7276-1996 民用航空器Halon 1301滅火系統(tǒng)最低性能要求

本標(biāo)準(zhǔn)規(guī)定了民用航空器火區(qū)固定式Halon1301滅火系統(tǒng)必須滿足的最低安全性能要求。 　　本標(biāo)準(zhǔn)適用于民用航空器火區(qū)固定式Halon1301滅火系統(tǒng)。

Minimum Performance Requirements for Civil Aircraft Halon 1301 Fire Extinguishing System