V35 航空器及其附件综合 标准查询与下载
共找到 548 条与 航空器及其附件综合 相关的标准，共 37 页
(a) Nonprecipitation conditions. For nonprecipitation conditions, the following apply:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartD:Design and construction. Section25.773:Pilot compartment view.
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- 2014-11-04
(a) For airplanes intended for use where icing may be expected, there must be a means to prevent or remove hazardous ice accumulation on propellers or on accessories where ice accumulation would jeopardize engine performance.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartE:Powerplant. Section25.929:Propeller deicing.
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- 2014-11-04
For each airspeed indicating system, the following apply:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartF:Equipment. Section25.1323:Airspeed indicating system.
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- 2014-11-04
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- 2014-11-04
Each angle of attack system sensor must be heated or have an equivalent means of preventing malfunction in the heavy rain conditions defined in Table 1 of § 25.1323, the mixed phase and ice crystal conditions as defined in part 33, Appendix D, of this chapter, the icing conditions defined in Appendix C of this part, and the following icing conditions specified in Appendix O of this part:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartF:Equipment. Section25.1324:Angle of attack system.
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- 2014-11-04
(a) Each instrument with static air case connections must be vented to the outside atmosphere through an appropriate piping system.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartF:Equipment. Section25.1325:Static pressure systems.
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- 2014-11-04
(a) If certification for flight in icing conditions is sought, in addition to the requirements of § 25.1419, an airplane with a maximum takeoff weight less than 60,000 pounds or with reversible flight controls must be capable of operating in accordance with paragraphs (a)(1), (2), or (3), of this section.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartF:Equipment. Section25.1420:Supercooled large drop icing conditions.
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- 2014-11-04
(a) The takeoff speeds prescribed by § 25.107, the accelerate-stop distance prescribed by § 25.109, the takeoff path prescribed by § 25.111, the takeoff distance and takeoff run prescribed by § 25.113, and the net takeoff flight path prescribed by § 25.115, must be determined in the selected configuration for takeoff at each weight, altitude, and
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.105:Takeoff.
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- 2014-11-04
(a) The takeoff path extends from a standing start to a point in the takeoff at which the airplane is 1,500 feet above the takeoff surface, or at which the transition from the takeoff to the en route configuration is completed and VFTO is reached, whichever point is higher. In addition
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.111:Takeoff path.
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- 2014-11-04
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- 2014-11-04
(a) Each fuel tank must be able to withstand, without failure, the vibration, inertia, fluid, and structural loads that it may be subjected to in operation.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartE:Powerplant. Section25.963:Fuel tanks: general.
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- 2014-10-02
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- 2014-10-02
(a) General. For castings used in structural applications, the factors, tests, and inspections specified in paragraphs (b) through (d) of this section must be applied in addition to those necessary to establish foundry quality control. The inspections must meet approved specifications. Paragraphs (c) and (d) of this section apply to any structural castings, except castings
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartD:Design and construction. Section25.621:Casting factors.
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- 2014-10-02
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- 2014-10-02
(a) It must be shown by operation tests that when portions of the control system subject to pilot effort loads are loaded to 80 percent of the limit load specified for the system and the powered portions of the control system are loaded to the maximum load expected
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartD:Design and construction. Section25.683:Operation tests.
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- 2014-10-02
(a) The landing gear system must be designed so that when it fails due to overloads during takeoff and landing, the failure mode is not likely to cause spillage of enough fuel to constitute a fire hazard. The overloads must be assumed to act in the upward and aft directions in combination with side loads acting inboard and outboard. In the absence of a more rational analysis, the side loads must be assumed to be up to 20 percent of the vertical load or 20 percent of the drag load, whichever is greater.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartD:Design and construction. Section25.721:General.
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(a) Each compartment for the stowage of cargo, baggage, carry-on articles, and equipment (such as life rafts), and any other stowage compartment, must be designed for its placarded maximum weight of contents and for the critical load distribution at the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to those emergency landing conditions of § 25.561(b)(3) for which the breaking loose of the contents of such compartments in the specified direction could
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartD:Design and construction. Section25.787:Stowage compartments.
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Fuel system components in an engine nacelle or in the fuselage must be protected from damage that could result in spillage of enough fuel to constitute a fire hazard as a result of a wheels-up landing on a paved runway under each of the conditions prescribed in § 25.721(b).
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartE:Powerplant. Section25.994:Fuel system components.
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- 2014-10-02
(a) Compliance with the strength and deformation requirements of this subpart must be shown for each critical loading condition. Structural analysis may be used only if the structure conforms to that for which experience has shown this method to be reliable. In other cases, substantiating tests must be made to load levels that are sufficient to verify structural behavior up to loads specified in § 25.305.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartC:Structure. Section25.307:Proof of structure.
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This European Standard specifies the characteristics of the fluid fittings, flanged, 90° elbowed, sealing by O-ring, for 0,8 mm thick tubes. NOTE Flanged fitting installation hole and assembly, see EN 3633 and TR 3634.
Aerospace series - Fluid fittings@ flanged@ 90��lbowed - Sealing by O-ring for 0@8 mm thick tubes
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- 2014-10
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本指导性技术文件规定了民用飞机机载系统和设备合格审定的软件保证和开发准则。 本指导性技术文件适用于民用飞机机载系统和设备中软件开发，发动机软件开发也可参考使用。 本指导性技术文件不包括软件运行方面的合格审定问题，也不包括申请人的组织结构、申请人与供应商的关系和职责划分、人员的资质等问题。
Assurance guidance for software in airborne systems and equipment certification for civil aircraft
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- 49.090
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- 2014-07-09
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- 2014-11-01
本指导性技术文件规定了民用飞机综合模块化航空电子系统(IMA)的开发、综合、验证、认证过程与方法、参与者的职责以及关键特性的要求。本指导性技术文件适用于民用飞机IMA研发全过程。
Development and certification guidance of IMA for civil aircraft
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- 49.090
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- 2014-07-09
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- 2014-11-01
本标准规定了民用飞机污水排出系统的组成、功能、性能等设计要求和验证要求。 本标准适用于民用运输类飞机，其他飞机可参考使用。
General requirements of civil aircraft waste system
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- 2014-07-09
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- 2014-11-01
本指导性技术文件规定了机载电子硬件概念设计、初始认证以及后续为保证持续适航进行的证后产品改进的整个过程要求，并提供了相关指南。 本指导性技术文件适用于与机载电子硬件设计生命周期相关的开发和认证活动。 本指导性技术文件涉及的机载电子硬件包含（但不局限于）以下硬件项： 外场可更换单元（LRU）；电路板部件；包含宏功能的用户定制的微代码部件，如专用集成电路（AISC）和可编程逻辑器件（PLD）；采用集成工艺的部件，如混合电路和多芯片组件（MCM）；商用货架产品（COTS）部件。
Assurance guidance for civil aircraft electronic hardware certification
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- 49.090
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- 2014-07-09
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- 2014-11-01
