1、- m fl43-57 MIL-L-853 14A 30 June 1983 L SUPBRBEDINC 27 December 1982 MIL-L-85314 MILITARY SPECIFICATION LIGHT SYSTEMS, AIRCRAFT, ANTI-COLLISION, STROBE, GENEW SPECIFICATION FOR This specification is approved for use by all Departments and Agencies of the Department of Defense, 1. SCOPE . -. * 1.1 S
2、cope. This specification covers the general require- ments for two types of anti-collision, aircraft lighting strobe systems, The lighting system shall be defined as thg total number of lightheads and power supplies required to provide 360 protctve lighting in the horizontal pane of the aircraft. pr
3、ovided by the lighting system is dependent on the system selected in accordance with the applicable specification sheet. Vertical protective lighting coverage 1*2 Classification, Strobe anti-collision, aircraft light systems shall be of the following types, as specified (see 6.2): Type I - For use w
4、ith 28 volt direct current (VDC) aircraft power source Type II - For use with one phase of a three phase 115 volt alternating current (VAC) 400 hertz (Hz) aircraft power source 2, APPLICABLE DOCUMENTS 2.1 Government documents, 2.1.1 Specifications, stanards, and handbookg, Unless otherwise specified
5、, the following specifications, standards, and handbooks of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDfSS) specified in the solicitation form a part of this specification to the extent specified herein, Beneficial comments (recommendations,
6、 additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commanding Officer, ESSD, Code 93, Naval Air Engiqesring Center, Lakehurst, NJ 08733, by using the self-addreesed Btanderdizstion Docunient Improvement Proposal (DD Form 1426) appeari
7、ng at the end of . thio, document or by letter. I / -3 THIS DOCUMENT CONTAINS 20 PAGES. ;- FSC 6220 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SPECIFICATIONS 3r p.lita.rJ MIL-W-5088 MIL-E-5400 MIL-S-7742 MIL-E-17555 MIL-C-25050 MIL-C-38999 STAND
8、ARD6 Federal FED-STD-395 Military DOD-STD-100 MIL-STD-105 MIL-STD-129 MIL-STD-130 ML-STD-454 MIL-STD-461 MIL-STD-462 MIL-L-85314A Wiring, Aerospace Vehicle Electronic Equipment, Aerospace, General Specification E or Bcrew Threads, Btandard, Optimum Helecteid Geriee, General BpeciEication for Electro
9、nic and Electrical Equipment, Acceeaories and Repair Parts! Packaging and Packing of Color, Aeronautical Light8 and Lighting Equipment, General Requiremente for Connector, Electrical, Circular, Miniature, HI. Density I Quick Disconnect, (Bayonet, Threaded and Breech Coupling) I Environment Reeistant
10、, Removable Crimp and Hermetic golder Contacts, General flpeciftcation for Colors Engineering Drawing Practicee Sampling Procedure8 and Tables for Impection by Attributes Marking for Shipment and Storage Identification Msrlcing of U.6. Military Property Standard General Requiremente for Electronic E
11、quipment Electromagnetic Emission and Susceptibility, Requirements for the Control of Electromagnetic Interference Electromagnetic Enterference Characteristics, Measurement of Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-85324A 62 7777906 OL
12、LLO T W e a a MIL-L-85314A STANPARPS (Continued) . Military_ (Gont inued) MIL-STD-704 ALrcraft, Electr,c Power Characteristics MIE-STD-781 Reliability Testa: Exponential Distribution MIL-STD-794 Parts and Equipment, Procedures or Packaging and Packing of MIL-CTD-810 Envirorimental Test Methods MIL-S
13、TD-831 Test Reports, Preparation of MIL-STD-882 System Safety Program Requirements MIL-STD-88 9 Dissimilar Metals MIL-STD-1568 Materials and Processes for Corrosion Prevention and Control in Aerospace Weapons Systems (Copies of specifications, standards, handbooks, drawings, and publications require
14、d by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.) 3 . REQUIREMENTS . 3.1 Specification sheets. The individual item requirements shall be ae specified herein and in accordance with the appl
15、icable specification sheet. of this specification and the specification sheet, the latter shall govern, (If a specific requirement specified herein is not required for an item, it shall ba as indicated on the specification sheet (e.g., shock - N/A) .) In the event of any conflict between requirement
16、s 3*2 F,irst article. The strobe, anti-collision, aircraft light systems furnished under this specification shall be a product which has been inspected and passed the first article inspection specified herein (see 4.3). * 3.3 Materials and components. Materials and components shall conform to applic
17、able specifications and standards as specified herein and in the applicable specification sheet. not specified herein or in the applicable specification sheet shall be selected in accordance with MIL-E-5400. are not covered by applicable specifications or standards or which are not specifically desc
18、ribed herein or in the applicable specification sheet shall be o the best quality, of the lightest practicable weight and suitable for the purpose intended. Materials and components Materials and components which Materials used shall be self- 3 Provided by IHSNot for ResaleNo reproduction or network
19、ing permitted without license from IHS-,-,-MIL-L- 85 3 14A extinguishing, shall not give off noxious gases in harmul quantitiee, shall not give off gases in quantities sufficient to cause exploston of sealed anclosures, and shall not cause contamination of the contacte or other parts of the system w
20、hen subdected to any of the tests specified herein or environmental conditions encountered in service usage, The selection of materials shall be such ao to provide a shelf life of at least 3 years without affecting the operation of the system, Maintenance action to reform electrolytic capacitore eha
21、ll be pertniesibe ae epecified in 3.12, 3e4 moeionEevention and cuntrol, The materiae and processes coneidered in deeign, the corrosion protection during manufacturing operations, and protective treatment finishes Eiheill be eelected with the guidance of MIL-STD-1568. 3e4 e 1 Metal parts, All metal
22、parts ahall be of a corroeion reeistant material or treated in a matter ta render them adequately resistant to corroeion. 3e4elel Diesiiar metals. DissimiEai: metals as defined in MIL-STD-889 shall not be in direct contact with each other unless appropriately protected against electrolytic corrosion
23、 with protective coatinge, 3,4,2 Protective treatment. When materials are ueed in the construction of the strobe, anti-collision light syetems that are subject to corrosion in salt air or other atmospheric conditions likely to occur during service usage, they shall be protected against such corrosio
24、n in a manner that shall in no way prevent compliance with the performance requirements of this and the applicable specification eheet. Protective coatings that shall chip or scale during normal service Life or under extremes of atmoepheric conditions, shall not be ueed, treatment shall conform to r
25、equirement 15 of MIL-STD-454, Protective 3,4*3 -ngue-proaf materials, Materials which are nutriente for fungi shall not be used where it is practicable to avoid them. Where used and not hermetically sealed, they ehall be treated with a Eungicidal agent acceptable to the acquiring activity, Fungus-pr
26、oof material shall conform to requirement 4 of MIL-STD-454. 3,404 Standard parts. MS and AN etandard parts shall be used where they suit the purpose and shall be identified by their part number. In application8 for which no suitable standard part is in effect on the date of invitation of bid, comerc
27、ial parts may be used, provided they conform to the requirements of this and the applicable specification sheet, 3,4,5 Screw ,threads, Screw threads shall conform to MIL-6-7742, 3,5 Environmental conditions. Unless otherwitiie specified in the applicable specification eheet, the Eight systems shall
28、function ao designed when exposed to any likely combinatian of the following environmental conditions: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-HIL-L-853LLIA 62 7777906 OLLL872 3 MIL-L- 85 3 14A a. b. c. Salt spray as encountered in salt water
29、 operations. d. Sand and dust as encountered in desert operations. e, Vibration shock within the limits of tests, as Temperature from -54 to +71C. Humidity as encountered in all-weather operation, described in 4.6.7. f. From sea level to 50,000 feet altitude. g. In any attitude of the aircraft. * 3.
30、6 Design. The strobe, anti-collision, aircraft lighting systems shall provide the anti-collision lighting as specified in the applicable specification sheet. concept where subassemblies of the major assemblies are easily replaceable as a complete module. In the construction of the light systems, ful
31、l advantage of the design for minimum size and weight, long life, maximum reliability, maintainability and minimum electromagnetic interference (EMI) per the applicable category shall be employed. The light emitted by each system or systems shall provide coverage above and below the horizontal plane
32、 of the aircraft as defined by the applicable specification sheet. The horizontal plane of the aircraft is defined by the longitudinal and lateral axes of the aircraft, The design shall incorporate a modular The horizontal field of coverage shall be 360 degrees. * . 3.6.1 System. The systems consist
33、 of transparent covers, light assemblies and power supplies. operate the system on the aircraft shall not be furnished as components of this system. with the requirements specified herein and the applicable specfication sheet. or dual mode (low and high intensity levels) specified herein and the app
34、licable specification sheet. a remotely located cockpit mounted switch. The control circuitry necessary to Each system shall be capable of operation in accordance The light source(s) shall be single mode (single intensity level) Each mode shall be selectable utilizing J( 3.6.1.1 Mode selection. The
35、system shall be compatible with cockpit mounted switches used to provide control signals for operation of the system. Control signals may include “ON“ - “OFF“, “RED“ - “WHITE“, “UPPER“ - “LOWER“, as applicable and any other control signals deemed necessary for operation of the system. Main aircraft
36、power shall not be used in conjunction with any cockpit mounted control switches. A low power control circuit shall be provided for control of the strobe system. The system shall provide for a rapid connect/disconnect capability between the switch interconnecting wiring and each type power supply as
37、sembly. The switches and their interconnecting wiring with mating connectors shall not be furnished as components of the system. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-85314A 3,6.1,2 Interface design, The design of the systems shall
38、include the interface and installation data required to mate the specific system with the aircraft. However, the interconnecting wiring and electrical connector mating halves for the aircraft shall not be furnished as components of the system, All wiring shall meet the applicable requirements of MIL
39、-W-5088, with the requirements specified herein and the applicable specification sheet utilizing the applicable aircraft power containing the characteristics defined in MIL-STD-704. Performance requirements of this and the applicable specification sheet shall conform with interconnecting wiring from
40、 the power supply(s) to the light sources not exceeding 0.188 OHMS resistance for each mode. Each type system shall operate in accordance 3,6.1.3 Thermal design, The systems shall be designed to incorporate within each assembly any thermal devices necessary to comply with the environmental requireme
41、nts of this and the applicable specification sheet, The design o each type system shall not require any externally supplied heating or cooling devices such as fans, blowers, ducts, etc. Such thermal devices shall be automatically activated and deactivated. 3,6,2 Safety. The intent of MIL-STD-882 sha
42、ll be met in that all hazards associated with the system shall be identified and eliminated or controlled, In addition, the system shall be designed to insure that a system failure shall be limited to the system and shall not afect the safety of the aircraft in which it is installed or other interfa
43、cing systems The system shall be designed to provide for maximum personnel safety as specified herein and the applicable specification sheet and in accordance with MIL-STD-454, requirement number 1, When power shall be removed from the system by any means, the system shall be rendered “electrically
44、safe“ to maintenance personnel who handle system components, assemblies and subassemblies. Electrically safe shall be defined as the removal of all electrical shock hazard to the maintenance technician. in 3.6.1, Provisions for the system squat switch shall be as specified 3,6.2,1 Grounding, Groundi
45、ng of the systems shall comply with MIL-STD-454, requirement number 1. 3,6.2.2 Electrical connectors, The electrical connectors used in condunction with systems wiring shall be as specified in MIL-C- 38999, Series 3 or 4. When not specified, they shall be military qualified connectors utilizing scre
46、w threads or bayonet coupling for their mating. Electrical connectors shall be selected and installed so that contacts on the “live“ or “hot“ side of the connector are socket type rather than pin typa. Electrical connectors used for power, control and light source circuits shall be dissimilar to the
47、 extent that electrical connections cannot be made which would electrically damage any portion of the equipment. * 3,6.2.3 Circuit overload/electrical damage protection. The design of the systems shall be such that in case of either an open or short circuit of any light source, high or low mode, eac
48、h remaining light source shall continue to operate. The power supply shall not Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-L-853L4A 62 m 7977706 OLL1874 7 MIL- 85 3 14A suffer any damage due an external open or shorted condition on the input
49、, output, or control wiring. System will return to normal operation upon removal of a shorted or open condition. 3.6.2.4 Shielding. The lights shall be capable of being shielded to prevent light beams from being directly or indirectly projected into the cockpit or other areas that would interfere with operating personnel. 3.6.3 Modules. The light source assembly shall be designed to provide a light source module(s) incorporating dual/single modes and
