1、NIL-I-855b bb 77777b OLLi5Li02 I I MIL-I-85506(AS) 14 November 1 983 FI1 L ITARY SPEC IF I CAT I ON INDICATOR, INDICATED AIRSPEED, STANDBY TYPES I, II, AND III ,-l6 -3 This specification is approved for use by the Naval Air Systems Command, Department of the Navy and is available for use by all Depa
2、rtments and Agencies of the Department of Defense. 1. SCOPE. 1.1 Scope. This specification establishes the performance, design, and test iuirernents for Standby Indicated Airspeed Indicators Types I,. II, and, III. airspeed indicators develop indicated airspeed as a function of the difference .betwe
3、en pitot and static pressures. i ntegral ly 1 i ghted, nomi na1 2-inch di al covering the ai rspeed range as applicable to indicator type. 1.2 Classification. fication are as follows: The The airspeed is to be displayed on an The types of airspeed indicators covered by this speci- Range Case Di al A
4、i rspeed Lighting Shape Di spl ay TY Pe a. I 30-650 Knots White (IPL) Square 1 pointer 1 pointer b. II 60-850 Knots White (IPL) 20-600 Knots Idhite (IPL) Square 2 pointer -Round I c. III I rea I 1 Beneficial conments (recommendations, additions, deletions) and any pertinent data wnich may be of use
5、in improving this document should be addressed to: Conmanding Officer, Naval Air Engineering Center, Engineering Specifications and Standards Department (ESSD) Code 93, Lakehurst, NJ 08733, by using the self-addressed Standardization Document Improvement Proposal (DD Fom 1426) , appearing at the end
6、 of this document or by letter. 1 1 . i- FSC 6610 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_ MIL-I-550b 66 9999906 0345403 -6 W MIL-I-85506( AS) 2. APPLICABLE DOCUMENTS 2.1 Government document s. 2.1.1 Specifications and standards. Unless othe
7、rwise specified, the following specifications and standards of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified in the solici- tation form a part of this specification to the extent specified herein. SPEC IF ICATIONS Federal P P P -
8、B -63 6 - Boxes, fi berboard Mi i i tary, MIL-P-116 - Preservation-Packaging, Methods of DOD -D-lOOO/l - Drawi ngs Engineering and Associated Data M IL-B-5087 - Bonding, Electrical and Lighting Protection for Aerospace Systems MIL-W-5088 - Wiring, Aircraft, Installation of MIL -Ed5400 - Electronic E
9、qui pment, Airborne, General Specification for M IL-C -5541 M IL-S -7742 M IL-A-8625 MI L-C -1 4806 - Chemical Films for Aluminum and Aluminum - Screw Threads, Standard, Optimum Selected Al 1 oys Seri es ; General Speci fi cat i on for - Anodic Coatings, for Aluminum Alloys and Al umi num - Coating,
10、 Reflection Reducing for Instrument Cover Glasses and Lighting Wedges M IL -T -1 8303 - Test Procedures : Preproduction, Acceptance and Li fe for Ai rcraft El ectronic Equi pment M IL -N -1 830 7 - Nomencl ature and Namepl ates for Aeronaut i cal Electronic and Associated Equipment MIL-P-23408 - P1
11、ati ng , Ti n-cadmi um (Ei ectrodeposi ted) MIL -C-2 5050 MIL -L -25467 - Col ors, Aeronautical Lights and Lighting - Lighting, Integral, Aircraft Instrument, Equipment , General Requirements for General Specification for 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without
12、 license from IHS-,-,-M IL-L -271 60 MIL-B -27497 MIL-G-81704 STANDARDS Federal FED-STD-595 Mi 1 i tary MIL-STD-105 MIL-STD-129 MIL -STD -1 43 MIL-STD -147 MIL -STD -454 MIL-STD-471 MIL-STD-704 MIL-STD-749 MI L-STD-781 MIL-STD-794 MIL -STD -810 MIL -STD-859 M IL -STD -1 524 MIL-I -85506 (AS ) - Ligh
13、ting , Instrument, Integral , White General Speci fi cat i on for - Bearing, Jewel, Sapphire or Ruby Synhetic - G1 ass, Ai rcraft Instruments, Lighting Wedges and Cover - Colors - Sampling Procedures and Tables for Inspection by Attributes - Marking for Shipment and Storage - Specifications and Stan
14、dards, Order of Pre- cedence for the Selection of - Palletized Unit Loads (40“ x 48“ 4 Way Partial and 4 Way Pallets) - Standard General Requirements for Electronic Equipment - Maintainability Demonstration - Electric Power, Aircraft, Characteristics and Utilization of - Preparation and Submission o
15、f Data for ap- proval of Non-Standard Electronic Parts - Re1 iabil ity Tests, Exponential Distribution - Parts and Equipment, Procedure for Packaging - Envi ronmental Test Methods and Packing of - Standard Cal ibration Table for Aeronautical - Table of Differential Pressure in Relation Pressure Meas
16、uring Equi pment to Cal i brated Airspeed 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DRAWINGS MS 2 7 5 60 MS33558 MI L-I -85506 (AS) - 2 3/8 Square Instrument, Standard Dimension for - Numeral s and Letters, Ai rcraft Instrument Dial Standard
17、Form of MS33585 - Pointer, Dial Standard M S 33 63 8 - Case, Instrument, F1 ange Mounted, Ai rcraft MS 3 3 649 - Bosses, Fluid Connection, Internal Straight Thread 2,1.2 Other Government publ ications. The following Government publ ication forms a part of this specification to the extent specified h
18、erein. Department of Defense Standardi tat i on SD -6 - Provisions Governing Qualification (Copies of specifications, standards, drawings, and publ ications required by manufacturers ir connection with specific acquisition functions should be obtained from the contracting activity or as directed by
19、the contracting officer.) this specification and the references cited herein, the text of this specification shall take precedence. 2.1.3 Order of precedence. In the event of a conflict between the text of 3, REQUIREMENTS 3.1 Qualification. The indicators furnished under this specification shall be
20、products which are qualified for listing on the a plicable Qualified Products List at the time set for opening of bids (see 4.4 and E.4). 3.2 Parts and materials. 3.2.1 General . Parts and materials shall meet the requirements of MIL-E-5400 for Class 2 equipment. 3.2.1.1 Nonstandard parts. Standard
21、MS and AN parts shall be used where they suit the purpose. When no standard part is available, a nonstandard part may be used with prior approval of the procuring activity (see 6.2.1). approval of the use of nonstandard parts and materials shall be obtained by the contractor as out1 i ned in MIL-STD
22、-749. Selection and 3.2.1.2 Selection of specifications and standards. Specifications and stan- dards for necessary commodities and services not specified herein shall be selected in accordance with MIL-STD-143. 3.2.2 Materi al s. 4 Provided by IHSNot for ResaleNo reproduction or networking permitte
23、d without license from IHS-,-,-MIL-I-5506 66 = 7777706 01115406 1 a a f a 3.2.2.1 Metals. Metals shall be of the corrosion-resistant type unless suit- 3.2.2.2 Nonferrous material s. Nonferrous material s shall be used for al 1 parts ably protected to resist corrosion during the life of the instrumen
24、t. of the indicator except where ferrous materials are essential. 3.2.2.3 Nonmagnetic materials. Nonmagnetic materials shall be used for all parts except where magnetic materials are essential. materials are required shall be reported to the procuring activity. 3.2.2.4 Dissimilar metals. Unless prot
25、ected against electrolytic corrosion by means of a protective coating, intimae contact of dissimilar metals shall be avoided. Dissimilar metals are defined in MIL-STD-454, requirement 16. The extent to which magnetic (See 6.2). 3.2.2.5 Protective treatment. When materials which are used in the const
26、ruc- tion of the airspeed indicator are subject to deterioration when exposed to climatic and environmental conditions likely to occur during service life, they shall be protected against such deterioration in a manner that will in no way prevent com- pliance with the performance requirements of thi
27、s specification. The use of any protective coating that will crack, chip, or scale with age or extremes of climatic and environmental conditions shall be avoided. 3.2.2.6 Fungus-proof materi al s. Materi al s that are nutrients for fungi shall not be used where it is practical to avoid them. Where u
28、sed and not hermetically sealed, they shall be treated with a fungicidal agent acceptable.to the procuring activity (see 6.2). 3.2.2.7 Toxic and corrosive fumes. The materials, as installed in the air- speed indicator and under the conditions specified herein, shall not liberate del- eterious or cor
29、rosive fumes. This shall include any fungicidal agents that are used. 3.2.2.8 Aluminum alloy parts. Aluminum alloy parts shall be covered with an anodic film conforming to MIL-A-8625, except that the dial, small holes, case in- serts, and fine pitch gear teeth need not be anodized. satisfactorily ma
30、y be coated in accordance with MIL-C-5541. Parts which do not anodize 3.2.2.9 Com onents The electronic and mechanical components shall be in ac- cordance with MI -* E 5 OO. 3.2.2.10 Jewel bearings. All sapphire and ruby jewel bearings used in the air- speed indicator shall be in accordance with MIL
31、-B-27497. 3.2.2.11 Threads. The threads of all machine screws shall be in accordance with MIL-S-7742. 3.3 Design and construction. The indicator shall conform with all applicable requirements of MIL-E-5400 concerning design, construction, and workmanship. design shall include minimum size and weight
32、 consistent with maximum reliability and operability. In any case, it is a condition f final acceptance that the equip- ment manufactured chal 1 meet al 1 the requirements of this specification. and any appl icabl e acceptable test documents. The 5 Provided by IHSNot for ResaleNo reproduction or net
33、working permitted without license from IHS-,-,-MIL-1-85506 bb W 9999706 0345407 3 M 4.8375 i nches 2.385 inches 2.385 inches 1.25 pounds 4.938 inches 2.385 inches 2.385 inches 1.25 pounds 7.090 inches 2.385 inches 2.385 inches 1.25 pounds MIL-I -85506( AS) 12.287 centimeters 6.058 centimeters 6.058
34、centimeters 0.568 kilograms 12.542 centimeters 6.058 centimeters 6.058 centimeters 0.568 kilograms 18.009 centimeters 6.058 centimeters 6.058 centimeters O. 568 ki 1 ograms 3.3.1 Physical characteristics. 3.3.1.1 Description. Operation of the indicator shall be accomplished me- chanically by means o
35、f a precision mechanism which drives a pointer(s), applicable to type, to indicate airspeed on a fixed dial. An integral vibrator shall not be necessary to meet the performance requirements as specified herein. The indicator shall be integrally lighted. All principle dimensions and locations of part
36、icular features shall be detailed in table I and figures 1, 2, and 3 for indicator types I, II, and III, respectively. 3,3,1.2 Case. The airspeed indicator case shall conform to MS33638 or MS27560 as applicable to type except as noted herein. The outline dimensions and the ex- ternal connections of
37、the indicator case shall conform to figures 1, 2, and 3 for indicator types I, II, and III, respectively. The body and mounting flange of the case shall be made of lightweight nonmagnetic metal, uniform in texture. The body shall be finished in a durable black finish, and the mounting flange shall b
38、e finished with a durable lusterless black finish, Color No. 37038 of FED-STD-595. The back of the mounting flange shall be tin plated in accordance with MIL-P-23408 to allow electrical grounding to the aircraft instrument panel for compliance with the requirements of MIL-B-5087. TABLE I. Weight and
39、 dimensions for the indicator Parameter Type I Indicator Length Width Height - 1/ Weight Type II Indicator Length - Width Height i/ Weight _ - - Type III Indicators Length Width Height - 1/ Weight Value (maximum) I - 1/ Weight of airspeed indicator is without connecting fittings and mounting screws.
40、 3.3,1.3 Pitot and static pressure ports. The pitot pressure boss shall be in accordance with MS33649-4 and the static pressure boss shall be in accordance with MS33649-6. The pressure bosses shall be located in the general locations shown in figures 1, 2, and 3 for indicator types I, II, and III, r
41、espectively. A 150-200 wire mesh filter screen (either stainless steel or monel) shall be installed in the static port to prevent dirt particles from entering the case. The inside of the case around each boss and the electrical receptacle shall be sufficiently strong to prevent damage to the case wh
42、en high torques are applied to the connections during installation and removal in an aircraft. For storage, shipment, and handling pur- 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-8550b 66 W 77777Ob 0345408 5 W MIL-I -85506 (AS ) poses, a
43、 vented plug of acceptable material and design shall be provided for. the pressure ports. 1/16 inch in diameter. to prevent the entry of particles which the manufacturer would consider detrimental to the indicators performance. 3.3.1.4 Application of pressure. The pitot pressure shall be applied to
44、the inside of the pressure capsule and the static pressure to the interior of the case. 3.3.1.5 Capillary. A sufficient length of approved capillary tubing having a minimum inside diameter of 0.020 inch, or some other acceptable restric- tion, shall be incorporated in the indicator case between the
45、pitot connection in the rear of the case and the diaphragm capsule. The effect of this restriction shall be such that the indicator will meet the requirements of the damping test specified herein. The plugs shall incorporate a vent consisting of a hole at least The plugs shall also incorporate suita
46、ble filtering material 3.3.2 Re1 i abi 1 i ty . 3.3.2.1 Reliability program. The contractor shall establish a reliability assurance test program in accordance with MIL-STD-781. 3.3.2.2 Operational stability. The airspeed indicator shall meet the performance requirements of this specification when op
47、erated continuously or intermittently, for a period of at least 1000 hours. be necessary to readjust any controls that are inaccessible to the operator during normal use. During this time, it shall not 3.3.2.3 Operating life. The airspeed indicator shall have a minimum operating O life of 10,000 hou
48、rs with reasonable servicing and replacement of parts. 3.3.2.4 Reliability in mean-time-between-failure (MTBF). The airspeed indi- cator shall have a minimum acceptable MTBF 0, of.1-,000 hours as specified in MIL-STD-781. 3.3.3 Cabling and connections. 3.3.3.1 Electrical receptacle. The electrical r
49、eceptacle, used to interface with aircraft wirinq, shall be of the type specified in figures 1, 2, and 3 and shall be connected as specified in figures 1, 2, and 3 for-indicators type I, II, and I I I, respectively. cap for Shi ppi ng, storage, and hand1 i ng purposes. The electrical receptacle shall be protected with a sui tab1 e c 3.3.3.2 Case grounding. The case shall be internally grounded as shown in fig- ures 1, 2, and 3 for indicator types I,
