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) The disposable load combinations must include each fuel and oil load in the range from zero fuel and oil to the selected maximum fuel and oil load. A structural reserve fuel condition, not exceeding 45 minutes of fuel under the
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartC:Structure. Section25.343:Design fuel and oil loads.
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- 2014-12-11
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- 2014-12-11
(a) The control system must be designed as follows for control surface loads due to ground gusts and taxiing downwind:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartC:Structure. Section25.415:Ground gust conditions.
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- 2014-12-11
(a) If wing flaps are to be used during takeoff, approach, or landing, at the design flap speeds established for these stages of flight under § 25.335(e) and with the wing flaps in the corresponding positions, the airplane is assumed to be subjected to symmetrical maneuvers and gusts. The resulting limit loads must correspond to the conditions determined as follows:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartC:Structure. Section25.345:High lift devices.
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The structure supporting any engine or auxiliary power unit must be designed for the loads including the gyroscopic loads arising from the conditions specified in §§ 25.331, 25.341(a), 25.349, 25.351, 25.473, 25.479, and 25.481, with the engine or auxiliary power unit at the maximum rpm appropriate to the condition. For the purposes of compliance with this section, the pitch maneuver in § 25.331(c)(1) must be carried out until the positive limit maneuvering load factor (point A2 in § 25.333(b)) is reached.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartC:Structure. Section25.371:Gyroscopic loads.
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- 2014-12-11
A rough air speed, VRA, for use as the recommended turbulence penetration airspeed in § 25.1585(a)(8), must be established, which
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartG:Operating limitations and information. Section25.1517:Rough air speed.
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- 2014-12-11
This European Standard defines the characteristics of cable ties with either internal or external serrations manufactured entirely from plastics material, for installation under controlled tension on aircraft cable harnesses. It shall be used together with EN 4056-001.
Aerospace series - Cable ties for harnesses - Part 004: Plastic cable ties - For operating temperatures - 55 ��to 105 ��and - 55 ��to 150 ��- Product standard
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- 49.060
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- 2014-12
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This European Standard specifies the characteristics, installation and mounting dimensions for plug-in relay bases for use with two and four poles double throw relays in accordance with EN 2548-001. Relay bases in accordance with this standard shall be used at ambient temperatures between -70 °C and 125 °C and at altitudes up to 25000 m.
Aerospace series - Bases for 10 A electromagnetic plug-in relays@ two and four poles double thrown - Part 001: Technical specification
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- 49.060
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- 2014-12
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(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
In the landing configuration, the steady gradient of climb may not be less than 3.2 percent, with the engines at the power or thrust that is available 8 seconds after initiation of movement of the power or thrust controls from the minimum flight idle to the goaround power or thrust setting
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.119:Landing climb: All-engines-operating.
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- 2014-11-04
(a) Stall warning with sufficient margin to prevent inadvertent stalling with the flaps and landing gear in any normal position must be clear and distinctive to the pilot in straight and turning flight.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.207:Stall warning.
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(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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(a) Takeoff; landing gear extended. In the critical takeoff configuration existing along the flight path (between the points at which the airplane reaches VLOF and at which the landing gear is fully retracted) and in the configuration used in § 25.111 but without ground effect, the steady gradient of climb must be positive for two-engine airplanes, and not less than 0.3 percent for three-engine airplanes or 0.5 percent for four-engine airplanes, at VLOF and with
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.121:Climb: One-engine-inoperative.
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(a) For land planes and amphibians, the following applies:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.237:Wind velocities.
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(a) For the en route configuration, the flight paths prescribed in paragraph (b) and (c) of this section must be determined at each weight, altitude, and ambient temperature, within the operating limits established for the airplane. The variation of weight along the flight path, accounting for the progressive consumption of fuel and oil by the operating engines, may be included in the computation. The flight paths must be determined at a speed not less than VFTO, with
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.123:En route flight paths.
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(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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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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(a) Additional operating limitations must be established as follows:
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartG:Operating limitations and information. Section25.1533:Additional operating limitations.
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(a) Engine type certificate. (1) Each engine must have a type certificate and must meet the applicable requirements of part 34 of this chapter.
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartE:Powerplant. Section25.903:Engines.
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(a) The horizontal distance necessary to land and to come to a complete stop (or to a speed of approximately 3 knots for water landings) from a point 50 feet above the landing surface must be determined (for standard temperatures, at each weight, altitude, and wind within the operational limits established by the applicant for the airplane):
Aeronautics and space. Part25:Airworthiness standards: transport category airplanes. SubpartB:Flight. Section25.125:Landing.
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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
