DLA MIL-DTL-6484 D-2007 LIGHTS COCKPIT UTILITY AIRCRAFT GENERAL SPECIFICATION FOR《通用技术条件航行器驾驶员座舱用灯》.pdf

《DLA MIL-DTL-6484 D-2007 LIGHTS COCKPIT UTILITY AIRCRAFT GENERAL SPECIFICATION FOR《通用技术条件航行器驾驶员座舱用灯》.pdf》由会员分享，可在线阅读，更多相关《DLA MIL-DTL-6484 D-2007 LIGHTS COCKPIT UTILITY AIRCRAFT GENERAL SPECIFICATION FOR《通用技术条件航行器驾驶员座舱用灯》.pdf（10页珍藏版）》请在麦多课文档分享上搜索。

1、 This specification is approved for use by all DeDefense. 1. SCOPE 1.1 This specification is a geaircraf1.2 following types as specified (see 6.2). 2. APPLIC2.1 standard. This section does not recommensure threquiremMIL-DTL-6484D 9 February 2007SUPERSEDINGINCH-POUND AMSC Provided by IHSNot for Resal

2、eNo reproduction or networking permitted without license from IHSDETAIL SPECIFICATION MIL-L-6484C6 December 1965LIGHTS, COCKPIT UTILITY, AIRCRAFT GENERAL SPECIFICATION FOR partments and Agencies of the Department of neral specification for cockpit utility lights intended for use in t for map reading

3、 and as a general utility light. Classification. The cockpit utility lights covered by this specification will be of the Type I with mounting base Type II without mounting base ABLE DOCUMENTS General. The documents listed in this section are specified in section 3, 4, or 5 of this include documents

4、cited in other sections of this standard or ended for additional information or as examples. While every effort has been made to e completeness of this list, document users are cautioned that they must meet all specified ents of documents cited in sections 3, 4, or 5 of this standard, whether or not

5、 they are listed. Inactive for new design after 11 June 1999 Comments, suggestions, or questions on this document should be addressed to: Defense Supply Center Philadelphia, ATTN: DSCP-NASA, 700 Robbins Ave, Philadelphia, PA 19111-5096 or emailed to dscpg&ispeccommentsdla.mil. Since contact informat

6、ion can change, you may want to verify the currency of this address information using the ASSIST Online database at http:/assist.daps.dla.mil/N/A FSC 6220 -,-,-MIL-DTL-6484D 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications, standards, and handboo

7、ks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-DTL-5541 Chemical Conversion Coatings on Aluminum and Aluminum Alloys MIL-A-8625 Anodic

8、Coatings for Aluminum and Aluminum Alloys MS17245 Light, Cockpit, Utility MS17246 Mounting Base, Cockpit Utility MS27424 Clip Assembly, Cockpit Utility Light DEPARTMENT OF DEFENSE STANDARDS MIL-STD-130 Identification Marking of U.S. Military Property MIL-STD-202 Electronic and Electrical Component p

9、arts MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests (Copies of these documents are available online at http:/assist.daps.dla.mil/quicksearch/ or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) 2.3 Non-Government

10、publications. The following documents form a part of this specification to the extent specified herein. Unless otherwise specified, these documents are those cited in the solicitation or contract. SOCIETY OF AUTOMOTIVE ENGINEERS (SAE) SAE-AS25050 Colors, Aeronautical Lights and Lighting Equipment, G

11、eneral Requirements for (Copies of these documents are available from http:/www.sae.org or the Society of Automotive Engineers, Inc., 400 Commonwealth Drive, Warrendale, PA 15096-0001.) 2.4 Order of precedence. In the event of a conflict between the text of this document and the reference cited here

12、in, 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 Qualification. The cockpit light assemblies furnished under this specification and the applicable specifica

13、tion sheet or MS17245 shall be a product which has been tested, and passed the qualification tests specified herein, and has been listed on or approved for listing on the applicable qualified products list. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from I

14、HS-,-,-MIL-DTL-6484D 3.2 Components. The cockpit utility light shall consist of the following major components: Item No. Paragraph No. Item Name 1 3.8.1 Housing Assembly 2 3.8.2 Focusing device 3 3.8.3 Rheostat 4 3.8.4 Lamp socket 5 3.8.5 Filter assembly 6 3.8.6 Switch 7 3.8.7 Mounting base 8 3.8.7.

15、1 Mount 9 3.8.8 Cord 10 3.8.9 Lamp 3.3 Precedence. When the requirements of this specification and the applicable specification sheet or MS17245 are in conflict, the requirements of the specification sheet or MS17245 shall govern. 3.4 Selection of specifications and standards. Specifications and sta

16、ndards for necessary commodities and services not specified herein shall be selected as provided in 3.4.1. 3.4.1 Standard parts. Standard parts (AN, MS, etc.) shall be used wherever they are suitable for the purpose, and shall be identified on the drawings by their part numbers. Commercial utility p

17、arts such as screws, bolts, nuts, cotter pins, etc., may be used, provided they possess suitable properties and are replaceable by the standard parts without alteration, and provided the standard part numbers are referenced in the parts list and on the contractors drawings. In the event there is no

18、suitable corresponding standard part in effect on date of invitation for bids, commercial parts may be used provided they conform to all requirements of this specification and applicable specification sheet or MS drawing. 3.5 Materials 3.5.1 Protective treatment. When materials are used in the const

19、ruction of the cockpit light assemblies that are subject to deterioration when exposed to climatic and environmental conditions likely to occur during service usage, they shall be protected against such deterioration in a manner that will in no way prevent compliance with the performance requirement

20、s of this 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. 3.6 Design and construction. The design of all cockpit utility light assemblies shall be of sufficiently rugged construction to w

21、ithstand the shocks, vibrations, and other conditions incident to shipping, storage and their installation on aircraft. The cockpit light assemblies shall be no larger than the envelope dimensions and shall operate on voltage as shown in the applicable specification sheet or MS drawing. Assemblies o

22、f slightly different design will be considered as meeting the requirements providing the specified and limiting dimensions, mounting holes, connections and other requirements of this specification and the applicable specification sheet or MS drawing are met. 3.6.1 Adjustment. The light assemblies sh

23、all be so constructed that adjustments and repairs can be easily made by personnel of operating units without the use of special tools. 3.6.2 Insulation. The insulation of each cord and light assembly shall withstand a breakdown test, without failure, when a minimum of 750 volts RMS AC is applied. 3

24、.7 Performance. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-6484D 3.7.1 Environmental. The cockpit light assemblies shall be capable of operating under the following environmental conditions: a. A temperature range of -54 to +71C. b. Ex

25、posure to atmosphere containing salt-laden moisture. c. Exposure to airborne sand and dust particles encountered in normal and desert operation. d. A relative humidity of 95 percent at a temperature of 49C. e. Vibration incident to use on aircraft. f. Rough handling incident to storage and use on ai

26、rcraft. 3.7.1.1 Low-temperature storage. The light assemblies shall withstand storage at a low temperature of -62C. 3.8 Details of components. The components of cockpit light assemblies shall be as stated in the following paragraphs, unless otherwise stated in the applicable specification sheet or M

27、S drawing. 3.8.1 Housing assembly. The housing assembly shall consist of the outer case, rheostat, lamp socket, momentary switch, mounting provisions, and means for selecting either red or white color spot or flood or either red or white color flood only as specified in the applicable specification

28、sheet or MS drawing. 3.8.1.1 Housing. The lamp and lamp focusing mechanism, the color filter and filter selector mechanism, and the momentary switch and the light intensity rheostat shall be mounted in non-corrosive or corrosive resistant metal or impact resistant plastic housing. 3.8.2 Focusing dev

29、ice. If required in the applicable specification sheet or MS drawing, a means shall be provided so that the light emitted may be adjusted to a small spot or to a wide flood of light as selected by the operator. The focusing device shall be so designed that it will not get out of adjustment and so th

30、at the lens and lens housing will not become detached from the light assembly by the vibration normally encountered in aircraft. 3.8.3 Rheostat. If required in the applicable specification sheet or MS drawing, a rheostat control with an “off ” position shall be installed in the housing and connected

31、 into the lamp circuit to control the light output. The rheostat shall have a maximum resistance of 200 to 250 ohms, unless otherwise specified in the applicable specification sheet or MS drawing, and shall be of sufficient size to handle the current required for the lamp specified. Rotation of the

32、rheostat in a clockwise rotation from the detented “off ” position shall increase the lamp intensity until it reaches the mechanical stop position. The rheostat knob shall be of a serrated or indented configuration and large enough for ease of operation. The rheostat shall be connected in such a man

33、ner that the protective shell around the rheostat, if metal, is in the ground side of the circuit. The rheostat shall have mechanical stops to prevent damage to the control portion of the unit. Optional locations for the rheostat are at the rear of the light or on the side of light adjacent to the m

34、ounting and to the rear of the mounting. 3.8.4 Lamp socket. The cockpit light assembly shall be designed with a lamp socket to accommodate a lamp as specified in the applicable specification sheet or MS drawing. 3.8.5 Filter assembly. If required in the applicable specification sheet or MS drawing,

35、a filter assembly consisting of a filter of plastic or glass and suitable mechanism for color selection shall be securely fastened within the cockpit light assembly. The filter assembly shall be an integral part of the light, and so designed as to be readily adjusted to emit white light or colored l

36、ight in accordance with SAE-AS25050. A positive lock of a type to prevent accidental change from colored light to white light or white light to colored light shall be provided. The filter shall be identification red unless otherwise specified in the applicable specification sheet or MS drawing. 3.8.

37、6 Switch. If required in the applicable specification sheet or MS drawing, a spring-loaded momentary “on” switch shall be provided at the rear of the cockpit light assembly. The switch shall be so connected that when it is closed, the lamp will be energized with the rheostat cut out of the circuit.

38、4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-6484D 3.8.7 Mounting base. The light shall be provided with a mounting base, manufactured in accordance with MS17246 unless specified without a mounting base by adding “A” to MS part number. T

39、he force required to remove the light out of the mounting base shall be greater than 1 and less than 5 pounds. 3.8.7.1 Mount. The mount on the cockpit light assemblies shall be designed for installing the lights in the MS17246 mounting base. The design of the mount shall be one of two types, straigh

40、t or offset. The straight mount shall be such as to permit the beam of the light assembly to be raised or lowered not less than 35 degrees above or below a plane through the axis of symmetry of the assembly. The offset mount shall be capable of rotating the beam of the light not less than 90 degrees

41、 in a plane perpendicular to the surface of the mounting base. Both mounts as specified in applicable specification sheets or MS drawings shall be capable of rotating the beam of the light 360 degrees parallel to the mounting surface. 3.8.7.1.1 Clip assembly. The cockpit light assemblies when used o

42、n some aircraft require an alligator clip for mounting and fastening to the pilots clipboard, map table, etc. MS27424, Clip Assembly, has been designed specifically for use with the MS17246 for this purpose. The clips are to be stocked separately, but may be procured with the cockpit light assemblie

43、s if they are for production aircraft or initial installations. Extra clip/base assemblies may be provided in aircraft requiring both the fixed and the clip bases so that they may be removed from the fixed base and placed in the clip/base assembly (see 6.2). 3.8.8 Cord. The cockpit light assemblies

44、shall be furnished complete with a molded coiled-type retractable two-conductor cord. The conductors shall be stranded and shall be no smaller than size No. 23 AWG (.0226 inch diameter). Unless otherwise specified in the applicable specification sheet or MS drawing, the maximum length of the coiled

45、cord shall be not greater than 11 inches with a helical diameter approximately .875 inches in the fully retracted position, and shall have an extended length of not less than 50 inches when a two pound weight is hung on the free end of the coiled section at room temperature, approximately 25 degrees

46、 centigrade. The cord shall be such that it will return to its normal coiled position when the weight is removed. The cord shall have one end connected to the light either at the rear of the light or on the side adjacent to and to the rear of the mount. The other end of the cord shall have the outer

47、 jacket removed for approximately 1.50 inches from the end. The wire insulation inside or the outer jacket shall be white for the positive lead and black for the negative lead. The wire insulation shall be stripped back from the end of each wire approximately .375 inches and the exposed stranded wir

48、e shall be tinned. 3.8.8.1 Terminals. The light assemblies shall be supplied without terminals to the outer end of cord as shown on applicable military standard (MS) drawing or specification sheet. 3.8.9 Lamp. The lamp used in the assembly shall be as specified in the applicable specification sheet

49、or MS drawing. One lamp shall be supplied installed on each cockpit light assembly. 3.9 Light distribution. The light distribution shall be as specified in the applicable specification sheet, MS drawing, or as stated herein. The light assembly when operated to emit or corrected to 3.5 mean spherical candle-power and not filtered shall produce a spot or flood light of approximately uniform intensity e