DLA MIL-DTL-25866 C-2010 LIGHT EMERGENCY EXIT AIRCRAFT LEU-1 A.pdf

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1、Comments, suggestions, or questions on this document should be addressed to Defense Supply Center Richmond, ATTN: DSCR-VEB, 8000 Jefferson Davis Highway, Richmond, VA 23297-5616, or e-mailed to STDZNMGTdla.mil. Since contact information can change, you may want to verify the currency of this address

2、 information using the ASSIST database at https:/assist.daps.dla.mil/. AMSC N/A FSC 6220 INCH-POUND MIL-DTL-25866C 24 May 2010 SUPERSEDING MIL-L-25866B 24 October 1969 DETAIL SPECIFICATION LIGHT, EMERGENCY EXIT, AIRCRAFT LEU-1/A This specification is approved for use by all Departments and Agencies

3、of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers one type of emergency exit light for cargo-type aircraft, designated LEU-1/A. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3 and 4 of this specification. This section do

4、es 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 this list, document users are cautioned that they must meet all specified requirements of the documents cite

5、d in sections 3 and 4 of this specification, whether or not they are listed. 2.2 Government documents. 2.2.1 Specifications and standards. The following specifications and standards form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents

6、 are those cited in the solicitation or contract. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-25866C 2 DEPARTMENT OF DEFENSE SPECIFICATIONS MIL-B-18 - Batteries, Non-Rechargeable, Dry MIL-DTL-5541 - Chemical Conversion Coatings on Aluminu

7、m and Aluminum Alloys MIL-A-8625 - Anodic Coatings for Aluminum and Aluminum Alloys MS35059 - Switch, Toggle, Two Pole, Sealed Toggle DEPARTMENT OF DEFENSE STANDARDS MIL-STD-130 - Identification Marking of U.S. Military Property MIL-STD-202 - Electronic and Electrical Component Parts MIL-STD-810 - E

8、nvironmental Engineering Considerations and Laboratory Tests (Copies of these documents are available online at https:/assist.daps.dla.mil/ or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) 2.3 Non-government publications. The following d

9、ocument forms 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. ASME INTERNATIONAL ASME Y14.100 - Engineering Drawing Practices (Copies of this document are available online at http:/www.

10、asme.org/ or from ASME International, Three Park Avenue, New York, NY 10016-5990.) ASTM INTERNATIONAL ASTM B117 - Operating Salt Spray (Fog) Apparatus (Copies of this document are available online at http:/www.astm.org/ or from ASTM International, 100 Barr Harbor Drive, P.O. Box C700, West Conshohoc

11、ken, PA 19428-2959.) SAE INTERNATIONAL SAE AMS-QQ-P-416 - Plating, Cadmium (Electrodeposited) (Copies of this document are available from http:/www.sae.org/ or from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001.) Provided by IHSNot for ResaleNo reproduction or networking permi

12、tted without license from IHS-,-,-MIL-DTL-25866C 3 2.4 Order of precedence. Unless otherwise noted herein or in the contract, in the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, s

13、upersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 First article. When specified (see 6.2), a sample shall be subjected to first article testing in accordance with 4.2. 3.2 Components. The light shall consist of: Item No. Quantity Description

14、 Requirement 1 1 Housing 3.6 2 1 Base plate 3.7 3 1 Reflector 3.8 4 1 Lens 3.9 5 2 Lamp 3.10 6 1 Manual switch 3.11 7 1 Inertia switch 3.12 8 1 Power failure relay 3.13 9 4 Batteries 3.14 3.3 Materials. 3.3.1 Fungus-proof materials. Materials that are nutrients for fungi shall not be used where it i

15、s practical to avoid them. Where used and not hermetically sealed, they shall be treated with a fungicidal agent acceptable to the procuring activity. However, if they will be used in a hermetically sealed enclosure, fungicidal treatment will not be necessary. 3.4 Design and construction. The light

16、shall be designed and constructed so that no parts will work loose in service. It shall be built to withstand the strain, vibrations, and other conditions incident to shipping, storage, installation, and service. 3.4.1 Adjustment and repair. The light shall be so constructed that adjustments and rep

17、airs (including replacement of lamp and batteries) can be made easily by the personnel of operating units, with tools normally available commercially. 3.4.2 Installation. The light shall be designed for installation near each exit of the aircraft cabin so that the light beam will be directed to illu

18、minate the exit in an efficient manner. All parts shall be suitably enclosed to prevent tampering or damage. 3.4.3 Portability. The light shall be so designed that it can be easily and quickly removed from its mounting position. The device used to secure the light in its mounting position shall hold

19、 the light in place during the conditions specified in 3.5. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-25866C 4 3.4.3.1 Handle. A handle shall be provided for carrying the light. The configuration of the handle to be provided shall be su

20、bject to approval by the procuring activity. 3.4.4 Lights of different construction. Lights of slightly different construction will be considered to be in accordance with the requirements, provided the specified and limiting dimensions, mounting holes, connections, and all other requirements specifi

21、ed herein are met and the design is approved by the procuring activity. 3.5 Performance. Unless otherwise specified, the light shall be capable of operating satisfactorily under the following conditions: a. Temperature ranging from -65 to 160 F (-54 to 71 C), except for reduction in-battery capacity

22、. b. Pressures ranging from 30 to 13.7 inches of mercury (inHg) (approximately an altitude of 20,000 feet). c. Relative humidity up to 95 percent including conditions wherein condensation takes place in the form of both water and frost. d. Sand and dust particles as will be encountered in desert are

23、as. e. Exposure to salt-sea atmosphere. f. Operation in an explosive vapor within or surrounding the equipment. g. Vibration incident to service use. h. Acceleration and shock forces as anticipated. i. Underwater operation. 3.5.1 Illumination (photometric). The light shall be designed in such a mann

24、er as to provide the following illumination. When properly installed and operated at rated lamp voltage, the candlepower distribution in any plane containing an axis which passes through the light center and is perpendicular to the mounting plate (0 degree axis) shall equal or exceed the values in t

25、able I. TABLE I. Candlepower distribution. Candlepower Minimum width with respect to 0 axis 7 -5 to +5 5 -10 to +10 3 -15 to +15 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-25866C 5 3.6 Housing. The housing shall be designed in such a man

26、ner as to support the light and it may utilize as much of the base plate area as required. If the housing obstructs the mounting holes, the light shall be so designed that the mounting holes are readily accessible when the cover of the housing is removed. 3.7 Base plate. The design of the light shal

27、l incorporate a plate to provide a supporting base for the housing. The light shall be such that it may be attached directly to the cabin structural members or to a suitable bracket by means of the mounting holes in the base plate. The mounting holes and a hole to accommodate the electrical receptac

28、le mounted on the housing shall be located as shown on figure 1. 3.7.1 Flight axis. The base plate shall be marked to indicate the proper positioning alignment of the light with the flight axis of the aircraft. The light shall be indexed with respect to the base plate. 3.8 Reflector. The light shall

29、 be provided with a suitable polished-aluminum reflector. 3.9 Lens. The light shall be provided with a white-plastic diffusing lens. 3.10 Lamp. The light shall be furnished with a single-contact miniature-flanged base, B-3.5 bulb, 2.38 volts, 0.50 ampere, commercial, PR-2 flashlight lamp. The light

30、shall be provided with a spare lamp complete with lamp holder to be mounted conveniently inside the housing. If lamp is of a type requiring continuous recharge of batteries from ship power source, a pilot light shall indicate when power is on and recharging batteries. 3.11 Manual switch. The light s

31、hall be provided with an MS35059-21 switch. The positive terminal of the self-contained battery power supply shall be attached to the center (OFF) terminal of this switch. One of the ON terminals shall be connected directly to the lamp. The circuit from the second ON terminal shall pass through the

32、set of normally closed contacts of the power failure relay, and thence to the lamp. When the switch is in this second ON position, the light shall then be armed for automatic operation by the power failure relay. The switch shall be located either in the light housing or external to the housing. 3.1

33、2 Inertia switch. The light shall be provided with an inertia switch, which will automatically energize the light when subjected to a deceleration of 2 0.5 gravity (G). The direction of maximum sensitivity (minimum impact force required to energize the light) shall be as marked on the base plate. Th

34、e inertia switch shall be so designed that the light will not come on when subjected to incident vibration as encountered in aircraft. If the inertia switch is of the maintained contact type, it shall incorporate a push button, mechanical reset device so that the light may quickly be rearmed for aut

35、omatic operation. If the inertia switch is comprised of a momentary contact device in conjunction with a holding relay, a single circuit, normally closed push-type switch may be utilized as a means of breaking the circuit of the holding relay in order to rearm the light for automatic operation. The

36、switch shall be located either in the light housing or external to the housing. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-25866C 6 3.13 Power failure relay. The light shall be provided with an approved relay, which has a set of normally

37、 closed contacts. The coil of the relay shall be energized in the armed position from the aircraft electrical power circuits (28 volts direct current (VDC). The operation of the relay shall be such that whenever the aircraft electrical power fails or is turned off, the contacts will be closed and th

38、e lamp will be automatically energized from the self-contained battery power supply. 3.13.1 Rearming circuit. The light shall be so designed that it can be rearmed by the light switch, and remotely rearmed if so connected. Figure 2 illustrates a circuit by which this requirement may be obtained. Oth

39、er circuits will be acceptable provided the requirements are met. If the light is to be de-energized and rearmed remotely, the control switch shall be connected to terminal C. 3.13.2 Electrical connections. Four 8-32 screw-type terminals shall be provided to connect the power and control circuits (i

40、f applicable) to the light. The terminals shall be marked A, B, C, and D. Terminal A shall connect to the +28 VDC circuit and terminal B shall connect to ground (-28 VDC circuit). Terminal C is provided for remote de-energization and rearming of the light if required. 3.13.3 Light turn-on feature. P

41、rovisions shall be incorporated so that upon removal of the light from its mounting plate, the light will automatically energize in the ON position. This may be accomplished either physically or electrically. 3.14 Batteries. The light shall be powered by four standard BA-30 cells conforming to MIL-B

42、-18. The batteries shall be arranged in series parallel, so as to provide a nominal open-circuit voltage of 3 volts. The batteries shall be used only to provide power for the lamp and under no conditions shall be used as a power source for any other component part of the light such as a relay or oth

43、er device. Unless otherwise specified (see 6.2), the batteries shall not be furnished with the light. 3.15 Interchangeability. All parts having the same manufacturers part number shall be functionally and dimensionally interchangeable. The drawing number requirements of ASME Y14.100, numbering, codi

44、ng, and identification section, shall govern changes in the manufacturers part numbers. 3.16 Dimensions. The dimensions of the light shall remain within the envelope specified in figure 1. 3.17 Weight. The weight of the light with lamp and batteries installed shall be not more than 3.5 pounds. 3.18

45、Finishes and protective coatings. 3.18.1 Aluminum-alloy parts. Aluminum-alloy parts shall be covered with an anodic film in accordance with MlL-A-8625, except as follows: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-25866C 7 a. Small holes

46、 need not be anodized. b. Aluminum alloys that do not anodize satisfactorily shall be coated with a chemical film in accordance with MIL-DTL-5541. c. Where the primary purpose of the treatment is to afford a suitable paint base, chemical treatments in accordance with MIL-DTL-5541 may be used in lieu

47、 of anodizing. d. Castings containing nonaluminum-alloy integral inserts may be treated with a chemical film in accordance with MIL-DTL-5541. e. When abrasion resistance is a factor, chemical films in accordance with MIL-DTL-5541 shall not be used in lieu of anodizing. 3.18.2 Steel parts. Steel part

48、s shall be cadmium plated, where practicable, in accordance with SAE AMS-QQ-P-416, type II or III, and of a class that is adequate to achieve the degree of protection required. 3.19 Operating instructions. Instruction plates containing operating instructions such as ON, OFF, RESET, shall be permanen

49、tly affixed to the light. The lettering shall be clearly legible and permanently marked. 3.20 Wiring diagram. A circuit diagram with a legend describing the electrical components of the light shall be permanently attached to the interior of the housing or other surface where practicable. The diagram shall be legible and protected against destruction by any of the tests specified in section 4. Proper met