AIR FORCE MIL-PRF-38135 C-1997 INDICATOR INDICATED AIRSPEED AVU-19A STANDBY《AVU-19A型待命指示空速指示器》.pdf

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1、? MIL-PRF-38135C 9999906 2055981 729 m 4 INCH-POUND I MIL-PRF-3 8 13 5C(USAF) 25 NOVEMBER 1997 SUPERSEDING 11 MARCH 1971 MIL-1-3 8 13 5B(USAF) PERFORMANCE SPECIFICATION INDICATOR, INDICATED AIRSPEED AW-lgA, STANDBY This specification is approved for use by the Department of the Air Force and is avai

2、lable for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers the standby, integrally-lighted, 1 -7/8 inch, round dial pitot static airspeed indicator, designated AW- 19/A. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this s

3、ection are cited in sections 3 and 4 of this specification. These lists do not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of these lists, document users are caut

4、ioned that they must meet the requirements specified in the documents cited in sections 3 and 4 of this specification, whether or not they are listed. 2.2 Government documents. 2.2.1 Specification and standards. The following specification and standards form a part of this document to the extent spe

5、cified herein. Unless otherwise specified, the applicable issues of these documents are those listed in the specific issue of the Department of Defense Index of Specifications and Standards (DoDISS) and supplement thereto, cited in the solicitation (see 6.2). SPECIFICATION DEPARTMENT OF DEFENSE Bene

6、ficial comments (recommendations, additions, deletions) and any pertinent data that may be of use in improving this document should be addressed to: Oklahoma City Air Logistics Center/TICLA, 3001 StaffDrive, Suite lAEl-lOlA, Tinker AFB, OK 73 145-3036, by using the Standardization Document Improveme

7、nt Proposal (DD Form 1426) appearing at the end of this document or bv letter. AMSC N/A FSC 6610 Licensed by Information Handling ServicesMIL-C- 14806 t flIL-PRF-38L35C Ob 2055982 bb5 MIL-PRF-3 8 13 5C(USAF) * Coating, Reflection Reducing For Instrument Cover Glasses and Lighting Wedges STANDARDS FE

8、DERAZ, FED-STD-595 Colors Used In Government Procurement DEPARTMENT OF DEFENSE MS28 105 MS33558 MS33585 MS33638 MS33649 Cover Glass, Aircraft Instrument Dial Numerals and Letters, Aircrafl Instrument Diai, Standard Form of Pointer, Dial, Standard Design of Aircraft Instrument Cases, Instrument, Flan

9、ge Mounted, Aircraft Bosses, Fluid Connection - internai Straight Thread (Unless otherwise indicated, copies of the above specification and standards are available from the Defense Automated Printing Service, 700 Robbins Avenue, Building 4D, Phiiadelphia, PA 191 11-5094.) 2.3 Non-Government publicat

10、ions. The following documents form a part of this document to the extent specified herein. Unless otherwise specified, the applicable issues of the documents which have been adopted by the DoD are those listed in the specific issue of the DoDISS cited in the solicitation. Unless otherwise specified,

11、 the documents not listed in the DoDISS are the issues of the documents cited in the solicitation (see 6.2). AMERICAN NATIONAL STANDARDS INSTITUTFYAMERICAN SOCIETY FOR QUALITY (ANSVASQ) ANSVASQ 21.4 Sampling Procedures and Tables for Inspection by Attributes OD-adopted) (Application for copies shoul

12、d be addressed to American Society for Quality, P.O. Box 3066, Milwaukee, WI 53201-3066, or to the American National Standards Institute, 11 West 42nd Street, 13th Floor, New York, NY 10036.) AMERICAN SOCIETY FOR TESTING AND MATEWS (ASTM) ASTM B117 Standard Practice for Operating Salt Spray (Fog) Ap

13、paratus OD-adopted) (Application for copies should be addressed to American Society for Testing and Materiais, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.) 2 Licensed by Information Handling ServicesMIL-PRF-38L35C . 9999906 2055983 5Tl 4 MIL-PRF-3 8 13 5 COJSAF) RADIO TECHNICAL COMMISSI

14、ON FOR AERONAUTICS (RTCA) RTCA/DO- 160 - Environmental Conditions and Test Procedures for Airborne Equipment (Application for copies should be addressed to RTCA Inc., 1 140 Connecticut Avenue, NW, Suite 1020, Washington, DC 20036-400 1 .) 2.4 Order of precedence. In the event of a conflict between t

15、he text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 First article. When specified (see 6.2), a sample sha

16、ll be subjected to first article inspection in accordance with 4.2. 3.2 Recycled. recovered. or environmentally Dreferable materials. Recycled, recovered, or environmentally preferable materials should be used to the maximum extent possible provided that the materid meets or exceeds the operational

17、and maintenance requirements, and promotes economically advantageous life cycle cost. 3.3 Materials. All materials sha be suitably treated to resist corrosion due to electrolytic decomposition, ngus, salt spray, and any other atmospheric condition that may be encountered during operational use or st

18、orage. Non-magnetic materials shall be used, where feasible. The use of toxic chemicals, hazardous substances, or ozone depleting chemicals shall be avoided, whenever feasible. 3.4 Interface. 3.4.1 u. The case shall conform to MS33638 for the 2-inch nominal size except as shown on figure 1. The beze

19、l and that part of the case visible from the cockpit side of the instrument panel shall be finished in lusterless black, color number 37038 of FED-STD-595. The pitot and static pressure bosses shall be marked with a P and an S as shown in figure 1. 3.4.2 Cover glass. The cover glass shall conform to

20、 MS28105-7 and shall be sealed into the bezel. 3.4.3 Reflection reducing coating. The cover glass surface shall be coated to reduce reflection according to MIL-C-14806. 3.4.4 Electrical connector. The electrical connector shall conform to figure 1. 3.4.5 Dial markinm. AU dial markings shall be perma

21、nently and legibly marked and shall conform to figure 2 and table I. Ail letters and numbers shall conform to MS33558. Ail markings not otherwise specified shall be finished in lusterless black, color number 37038 of FED-STD-595. 3 Licensed by Information Handling ServicesMIL-PRF-38L35C m 9999906 20

22、55984 438 m Marking Numerals 100-hot graduations 50-knot graduations 1 O-knot graduations USAF MIL-PRF-38 135C(USAF) Height or length Width Color (see note 3) O. 140 0.020 lusterless white, 37875 0.171 0.020 lusterless white, 37875 O. 156 0.020 lusterless white, 37875 O. 140 0.015 lusterless white,

23、37875 O. 047 0.020 lusterless black. 37038 TABLE I. Dial markings AIRSPEED KNOTS X 100 O. 047 0.020 lusterless black, 37038 0.093 0.020 lusterless white, 37875 I AVU-l9/A I O. 047 I 0.020 I lusterless black. 37038 3.5 Performance. 3.5.1 Operation. The indicator shall display the indicated airspeed (

24、IAS) as a function of the difference between pitot and static pressures. 3.5.2 Maintainability. The indicator shall be repairable without the use of special tools. 3.5.3 Reliability. The indicator shall have a mean time between failures (MTBF) of 1,200 hous. 3.5.4 hize. The indicator shall display t

25、he IAS over a range of 60 to 850 knots. The pointer shall move continuously (without ratch-) while indicating IAS. 3.5.5 Overpressure. The indicator shall withstand overpressure of 10 inches of water at the static port and 73 inches of Hg at the pitot port 3.5.6 Magnetic effect. The indicator shail

26、cause a fiee compass to deflect no more than lo when revolved about a short-bar magnetic compass with a field intensity of O. 17 to O. 19 oersted. 3.5.7 Case leakaee. The case leakage shall cause a change of pressure of no more than 0.01 inch Hg per minute. / 3.5.8 Static pressure. The pointer shall

27、 not change position due to internal leakage more than 1 hot when a pressure sufficient to cause full-scale deflection is applied. 3.5.9 Scale error. The scale error (see 6.3.1) of the indicator shatt be within the tolerances specified in table II. 4 Licensed by Information Handling Services3 MIL-PR

28、F-38135C W 9999906 2055985 374 600 700 800 4 MIL-PRF-3 8 13 5C(USAF) 21.109 20 30.816 20 43.009 20 TABLE II. Scale error tolerances Indicated airspeed 60 to 200 201 to 850 (knots) Tolerance 3 10 (hots) 3.5.11 Position error. The position error shall be within the tolerances in table III. TABLE III.

29、Friction and position error tolerances 3.5.12 Dielectric strend. The indicator shali withstand application of 5OOVac between the pins and case for 5 seconds without insulation breakdown. 3.5.13 Dial and cover glass location. The distance between the front surface of the bezel and the outside of the

30、cover glass shall be 0.062 inch or less. The distance between the inside surface of the cover glass and the dial shall O. 125 inch or less. 3.5.14 Pointer. There shd be no oscillation in excess of f5 knots of the pointer while the indicator is vibrated. The pointer shall be adjustable. The pointer s

31、hall conform to MS33585-8 and shall be finished in lusterless white, color number 37875 of FED-STD-595. 3.5.15 Limitation of pointer movement. The airspeed pointer movement shall be limited to 3 58O of clockwise rotation from the no pressure position. 3.5.16 Linhtinn characteristics. The lighting ch

32、aracteristics (intensity and color) shall be as specified by the procuring activity (see 6.2), and shall operate on Wac. Licensed by Information Handling ServicesMIL-PRF-3L3SC m Ob 205598b 200 m c MIL-PRF-3 8 13 5C(USAF) e 3.5.17 DamDhg. The the for the pointer to go fiom full scale to 120 knots sha

33、ll be between 0.8 and 2.0 seconds (see 6.4). 3.5.18 Weight. The indicator shail weigh 1.25 pounds or less. 3.5.19 m. The dial shall conform to figure 2. 3.6 Item identification. The indicator shall be permanently and legibly marked with the following information: a. Mandacturers name. b. Manufacture

34、rs CAGE code. c. Manufacturers part number. d. Mandacturers lot number. e. National Stock Number (NSN). f. Date of manufacture. 3.7 Interchangeabiiity. Ail parts having the same mandacturers part number shail be functionaly and dimensiody interchangeable. 3.8 Environmental conditions. 3.8.1 Temperat

35、ure. The indicator shall operate fiom -65 to 160F with a scale error of k5 knots in addition to the scale error in table II. 3.8.2 Vibration. 3.8.2.1 Vibration error. The indicator shall withstand vibration at an amplitude of 0.003 to 0.005 inch at a frequency of 500 to 3,000 Hz with an error less t

36、han 5 knots at an IAS of 200 knots. 3.8.2.2 Vibration tolerance. The indicator shail withstand vibration at an amplitude of 0.018 to 0.020 inch at frequencies of 1,000,2,000, and 3,000 Hz for a period of 3 hours with an error less than 5 knots at an IAS of 200 knots. 3.8.2.3 Resonance. The indicator

37、 shall have no resonant frequency between 500 and 3,000 Hz. 3.8.3 Humidity. The indicator shall operate in humidity up to 95 percent. 3.8.4 Acceleration. The indicator shall operate with applied acceleration forces up to 20g. 3.8.5 Sand and dust. The indicator shall operate after exposure to sand an

38、d dust. 4. VERIFICATION 4.1 Classification of inspections. The inspection requirements specified herein are classified as follows: a. First article (see 4.2). 6 Licensed by Information Handling ServicesMIL-PRF-3L35C m 0b 2055987 it47 m * MIL-PRF-3 813 5C(USAF) b. Conformance (see 4.3). 4.2 First art

39、icle inspection. When required (see 6.2), first article inspection shall be pedomed on nine indicators. Three indicators shail be subjected to ali tests except reliability. The remaining six indicators shall only be subjected to the reliability test. 4.3 Conformance inspection. Confomance inspection

40、 shall consist of the following: a. Individual tests (see 4.3.1). b. Samphg tests (see 4.3.2). 4.3.1 Individual tests. Each indicator shd be subjected to the following tests: a. Examination (see 4.6.1). b. Scale error (see 4.6.4). c. Friction error (see 4.6.5). d. Case leakage (see 4.6.10). e. Stati

41、c pressure test (see 4.6.1 1). f. Lighting (see 4.6.14). 4.3.2 Sampling; tests. Indicators, sampled according to ANSYASQ 21.4, shail be subjected to the foiiowing tests: a. b. d. e. f. g. h. C. 1. j- k. Overpressure (see 4.6.8). Magnetic effect (see 4.6.9). Case leakage (see 4.6.10). Dielectric stre

42、ngth (see 4.6.12). Pointer oscillation (see 4.6.13). Damping (see 4.6.15). Low temperature (see 4.6.16). High temperature (see 4.6.17). Vibration error (see 4.9.18). Vibration tolerance (see 4.6.19). Pointer zero position error (see 4.6.23). 4.4 Test conditions. Unless otherwise specified (see 6.2),

43、 all tests shall be performed in accordance with the test conditions specified in the applicable test method document or applicable paragraph in this specification. 4.4.1 Standard atmospheric condition. Unless otherwise specified in this specification or the applicable test method document, ail test

44、s shall be performed at ambient pressure altitude and temperature. 4.4.2 Tapping. Unless otherwise specified in this specification, the indicator shall be tapped before a test reading is taken. 7 Licensed by Information Handling ServicesMIL-PRF-38135C 9999906 2055988 083 c 4.4.3 Attitude. Unless oth

45、erwise specifled in this specification or the applicable test method document, the indicator shall be tested in the normal operating position. 4.5 Reauirements cross reference matrix. Table IV provides a cross reference matrix of the section 3 requirements tested or verified in the paragraphs below.

46、 Table IV. Reauirements cross-reference matrix 4.6 Tests. 4.6.1 Examination. The indicator shal be inspected to determine compliance with the requirements specified herein with respect to materials, interface, markings, colors, weight, maintainability, item identification, pointer, limitation of poi

47、nter movement, pointer zero position, fighting, Interchangeability, and dimensions. 4.6.2 Funms. The indicator, including applicable external connectors, shall be subjected to the f?ungus test in RTCA/DO-160. The indicator shall then be subjected to the inchiduai tests. 4.6.3 Sait fog. The indicator

48、 shaU be subjected to the sait fog test in accordance with ASTM B117 for 50 hours. The indicator shall then be subjected to the indiviw tests. 4.6.4 Scale error. The indicator shall be subjected to the pressures specified in table II, fjrst with increasing pressure, then with decreasing pressure. Fo

49、r increasing pressure, the pressure shaii be brought up to but not exceed the pressure required to give the desired reading and for decreasing pressure, the pressure shall be brought down to but not below the pressure required to give the desired reading. At each test point, the scale errors shall be within the tolerance in table II. 8 Licensed by Information Handling ServicesMIL-PRF-38135C = 9999906 2055989 TIT 1 * MIL-PR.F-38135C(USAJ?) 4.6.5 Friction error. The indicator shall be tested for fnction at the 60, 100, 150, 200, 300, 400, 500, 600,700, and 800-kn