SAE-AS-398B-2001-R2008.pdf
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1、AEROSPACE STANDARD AS398 REV. B Issued1947-07 Reaffirmed 2008-02 Revised2001-07 Superseding AS398A Direction Instrument, Magnetic, Non-Stabilized Type (Magnetic Compass) FOREWORD Changes in this Revision are format/editorial only. 1.SCOPE: This Aeronautical Standard covers two basic types of instrum
2、ents as follows: Type I - Direct Reading Type II - Remote Indicating 1.1Purpose: To specify minimum requirements for non-stabilized magnetic direction instruments for use in aircraft, the operation of which may subject the instrument to the environmental conditions specified in Paragraph 3.3. 2.REFE
3、RENCES: NACA Report 1235 3.GENERAL REQUIREMETNS: 3.1Material and Workmanship: 3.1.1Materials: Materials shall be of a quality which experience and/or tests have demonstrated to be suitable and dependable for use in aircraft instruments. 3.1.2Workmanship: Workmanship shall be consistent with high-gra
4、de aircraft instrument manufacturing practice. SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, in
5、cluding any patent infringement arising therefrom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2008 SAE International All r
6、ights reserved. No part of this publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside US
7、A and Canada) Tel: 724-776-4970 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org -,-,- SAE AS398 Revision B - 2 - 3.2Identification: The following information shall be legibly and permanently marked on the instrument or attached thereto: (a) Name of In
8、strument (b) Aeronautical Standard AS398B (c) Manufacturers part number (d) Manufacturers serial number or date of manufacture (e) Manufacturers name and/or trademark (f) Rating, if applicable (Electrical, Vacuum, etc.) 3.3Environmental Conditions: The following conditions have been established as d
9、esign requirements only. Tests shall be conducted as specified in Sections 5, 6 and 7. 3.3.1Temperature: When installed in accordance with the instrument manufacturers instructions, the instrument shall function over the range of ambient temperature shown in Column A below and shall not be adversely
10、 affected by exposure to the range of temperature shown in Column B below: 3.3.2Humidity: The instrument shall function and shall not be adversely affected when exposed to any relative humidity in the range from 0 to 95% at a temperature of approximately 32 C. TABLE 1 Instrument Location A B Heated
11、Areas (Temperature Controlled)-30 to 50 C-65 to 70 C Unheated Areas (Temperature Uncontrolled)-55 to 70 C-65 to 70 C -,-,- SAE AS398 Revision B - 3 - 3.3.3Vibration: When installed in accordance with the instrument manufacturers instructions, the instruments shall function and shall not be adversely
12、 affected when subjected to vibrations of the following characteristics: 3.3.4Altitude: The instrument shall function and shall not be adversely affected when subjected to a pressure and temperature range equivalent from -1000 feet to 40,000 feet standard altitude per NACA Report 1235, except as lim
13、ited by application of Paragraph 3.3.1. The instrument shall not be adversely affected when subjected to a pressure of 50 in Hg absolute. 3.4Radio Interference: The instrument shall not be the source of objectionable interference, under operating conditions at any frequencies used on aircraft either
14、 by radiation or feed-back, in radio equipment installed in the same aircraft as the instrument. 3.5Magnetic Effect: The magnetic effect of the instrument shall not adversely affect the operation of other instruments installed in the same aircraft. TABLE 2 Instrument Location in Airframe Cycles Per
15、Second Maximum Double Amplitude (Inches) Maximum Acceleration Power Plant Mounted 5 - 1500.100 20 g Wings and Empennage 5 - 5000.036 10 g Fuselage 5 - 5000.036 5 g Panel or Rack (with 5 - 500.0201.5 g Shockmounts) -,-,- SAE AS398 Revision B - 4 - 4.DETAIL REQUIREMENTS: 4.1Indicating Method: One of t
16、he following methods of indication shall be employed: Method IHorizontal drum dial with fixed lubbers line. Graduations move to the right for right turns. Method IIRotating vertical dial with fixed lubbers line. Dial rotates counter-clockwise for right turns. Method IIIRotating pointer with fixed gr
17、aduated dial. Pointer rotates clockwise for right turns. Dial position may be settable. 4.2Operating Limits: During straight flight the instrument shall indicate magnetic headings, throughout the 360 degree scale range, during dives, climbs or banks up to at least 20 degrees displacement from level
18、flight. 4.3Dial Markings: 4.3.1Graduations: The indicators shall be provided with degree graduations at intervals not to exceed 5 degrees, with major graduations every 10 degrees and with numerical markings at intervals not greater than 30 degrees, except that the 0, 90, 180 and 270 degree positions
19、 shall be marked N, E, S and W respectively. 4.3.2Visibility: Index and dial markings shall be visible from any point within the frustum of a cone the side of which makes an angle of 30 degrees with the perpendicular to the dial and the small diameter of which is the aperture of the instrument case.
20、 At least two numerals shall be simultaneously visible. 4.3.3Finish: Unless otherwise specified by the user, matte white material shall be applied to major graduations, numerals and pointers. Non-functional surfaces shall be a durable dull black. 4.4Power Variations: All units shall properly functio
21、n with 15% variation in DC voltage and/or 10% variation in AC voltage and a 5% frequency variation. 4.5Compensation Provisions: Means shall be provided for compensating for semi-circular deviation. Compensating effect shall be between 15 and 40 degrees in each direction for each axis when adjusted f
22、or maximum effect. -,-,- SAE AS398 Revision B - 5 - 4.6Power Malfunction Indication: Means shall be incorporated in the instrument to indicate when adequate power (voltage and/or current) is not being made available to all phases required for the proper operation of the instrument. The indicating me
23、ans shall indicate a failure or a malfunction in a positive manner. 5.TEST CONDITIONS: 5.1Atmospheric Conditions: Unless otherwise specified, all tests required by this Aeronautical Standard shall be conducted at an atmospheric pressure of approximately 29.92 inches of mercury, at an ambient tempera
24、ture of approximately 25 C and at a relative humidity of not greater than 85 percent. When tests are conducted with atmospheric pressure or temperature substantially different from these values, allowance shall be made for the variations from the specified conditions. 5.2Vibration (to minimize frict
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