NAVY MIL-E-22285-1959 EXTINGUISHING SYSTEM FIRE AIRCRAFT HIGH-RATE- DISCHARGE TYPE INSTALLATION AND TEST OF《安装与测试高倍率放电式飞机防火灭火系统》.pdf

1、VIL-E-22285 Lb U 7779706 0272077 5 G- mL4-22285( Wep) 11 December 1959 MILITARY SPECIFICATION EXTINGUISHING SYSTEM, FIRE, AIRCRAFT, HIGH-RATE-DISCHARGE “PE, INSTALLATION AM) TEST OF This specification has been approved by the Bureau of Naval Weapons, Department of the Navy 1. SCOPE 1.1 This specific

2、ation covers the installation of high-rate-discharge type fixed fire extinguishing systems for engine spaces and other potential fire zones in aircraft. 2. APPLICABLE DOCUMENTS 2.1 The following specifications, standards, drawings and publication, of the issue in effect on date of inviation for bids

3、, form a part of this specification: SPECIFICATIOS Federal WW-T-787 Tubing, Aluminum Alloy 525, Round, Seamless, Drawn Military MIL-V-6405 MIL-E-7080 Electric Equipment, Piloted Aircraft, Installation and . MIL-T -7 O81 MIL-Ta606 MILB-12218 Bromotrifluoromethane (Liquefied) MIL-c- 22284 MIL-D-70327

4、Valve, Check, Rro-Way, Bromochloronethane, Aircraft Fire . Extinguishing System Selection of, General Specification for Aircraft Hydraulic Quality Tubing, Aluminum Alloy 6061 and 6082 Seamless, Round, Tubing, Steel, Corrosion-Resistant (18-8 Stabilized) Container, Aircraft Fire Extinguishing System,

5、 Bromotri- Drawings, Engineering and Associated Lists fluoromethane, CF3Br STANDARDS Mlitaly MIL-CTD-203 blILSID-250 Ms25103 MC25231 Ms26523 Ms33586 kS33611 Tube Bend Radii Cockpit Controls3 Location and Actuation of, for Fixed Cockpit Controls; Location and Actuation of, for Helicopters Switches, T

6、oggle, Double Pole, Three-Hole riounting mp, Incandescent, Single Contact, Winiature Bayonet Base, . Metals - Definition of Dissimilar Wing Aircraft T-33 Bulb . Handles, Control, Aircraft Fire Extinguisher DRAWINGS Air Force-Naw Aeronautical Standard Drawinas AN742 ANDiO101, Clamp, Plain, Support, L

7、oop-we, Aircraft Tubina. Steel. Corrosion-Resistant, Round, Standard Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-22285 Lb 7777706 OL72OBO L E MIL-E- 22285 (Wep) AND10106 AND10108 Am10375 Tubing - Standard Sizes forAluminum Alloy (52SO) Tubi

8、ng - Standard Sizes for Aluminum Alloy (61s) Round Colors - Fluid Line Identification Round PUBLICATI 3N Air Force - Navy Aeronautical Bulletin No. i43 Specifications and Standards; Use of (irken requesting specifications, standards and publications, refer to both title and number. application to th

9、e Commanding Officer, Naval Aviation Supply however, a fire extin- guishing system shall be instelled in this zone only in experimental air- craft and in those aircraft where the value of the airplane or the personnel carried warrants increased weight for a nominal increase in safety. 3.7 Fire extin

10、guishing agent - The extinguishing agent shall be bromotrifluoromethane (CF3Br) in accordance with Specification MIX-B-12218. concentration of agent et least 15 percent by volume in all parts of the affected zone. This concentration shall persist in each part of the zone for at, least 0.5 second at

11、normal cruising condition, 3.8 Concentration of agent - Actuation of the extinguishing system shall produce a 3.8.1 Quantity of agent - As a design guide, the following formulas may be used . determine the minimum quantity (weight) of agent to be discharged into each engine: (a) -For rough nacelle i

12、nterior with low airflow, and for smooth nacelle interior regardless of airflow, whichever of the following formulas provides the larger value of w: w= 0.05 w - 0.02 + 0.2sWa (b) (c) Where: W = weight of agent inpounds. For rough nacelle interior with high airflow: For deep frame nacelle interior wi

13、th high airflow: W - 3 (.02V + 0.29tJa) W = 0.16V + 0.56tla Wa = pounds of air per second passing through the zone at normal cruisinp, V condition. - net volume of the zone in cubic feet (gross volume of the zone less the volume of major items of equipment). :* .-. 3 Provided by IHSNot for ResaleNo

14、reproduction or networking permitted without license from IHS-,-,-_ . MIL-E-22285 3b W 9999906 0392082 5 MILE- 22285cWep ) Definitions: (1) Low airflow signifies air flow rate of 1 pound or less per second (2) High airfluw signifies air flaw rats exceeding 1 pound per second (3) Smooth nacelle denot

15、es no circumferential ribs protruding into (4) Rough nacelle denotes circumferential ribsptrudxng less than 6 (5) Deep frame nacelle denotes circumferential ribs protruding 6 at cruise. at cruise . nacelle . inches into nacelle. inches or more into nacelle, or nacelle configuration with cavities 6 i

16、nches or more in depth (measured transversely). 3.8.2 Zones outside of nacelles - For potential fire zones not located in nacelles, the formula of 3.B.l(a) may be used. 3.8.3 Added factor for agent loss - The value of W obtained in the formulas-of 36.82 shall be increased by 15 percent to compensate

17、 for agent trapped in the container and lost in wetting the discharge tubing. 3.9 Duretion of discharge - The period of time required to discharge the calculated amount of agent shall be 1 second or less, measured from the time the agent starts to leave the tubing ends until. the required amount of

18、agent has been discharged, Ncnral Weapons,a.-F-s and acceptable to the Bureau of Nam Wgapons. requiremcnts specified herein and shall be subjected to the following tests: tc, check the integrity of the tubing and fLttings from the agent container to the firewall, or as near to the discharge outlet s

19、ystem as possible. Contractors not having laboratory testing facilities satisfactory 4.2 Inspection -. 1000 psig 4.2.2 Outlets - A visual check of the discharge outlets to insure that they are free Container weight - A weight check of the container(s) prior to installation and from foreign matter, a

20、 check of the pressure pge on the container(s) after installation,-to determine that the containers are properly cherged. 4.2.3 4.2.4 of the system. 1i.3 Slectrical continuity - An electrical continuity check of the electrical wiring Installation approval - Preliminary and final approval shall be re

21、nuired for the first or prototype installation of a fire extinguishing system in each model aircraft and following any change of the engine, nacelle configuration or fire extinguishing system. Preliminary approval - Prior to the initial installation of the fire extinguishinp, system, and when applic

22、able after any changes in the engine, nacelle configura- tion, or fire extinguishing system, the contractor shall submit to the Bureau of Naval Weapons for preliminary approval the following design dzta: 4.3.1 4.3.1.1 valve sizes, tubing sizes and wall thicknesses, and discharge outlet sizes. compon

23、ent parts shall be identified by AN or b4S part riders. Schematic diagram - Schematic diagram of the system showing container sizes, When applicable, 11.3.1.2 Quantity of gent - Calculations showing derivations of amounts of agent from air flow and volume figures for all zones protected, and infonna

24、tion as to the direction and location of air flow in esch zone. . 4.3.1.3 Tubing sizes - Calculations showing derivation of tubing sizes and discharge . outlet sizes (v 4.3.1.4 Installation - Preliminaly installation drawing showing location of agent containers, tubing, distribution patAern, and mat

25、erials with respect to the area to be protected. 4.3.1.5 Compartment sealing - Information as to the effectiveness of the method .2f sealing compartments to be protected from the surrounding compartments. 4.3.1.6 4.3.2 Control panel - Layout of control panel in the cockpit. Final approval - The enti

26、re fire extinguishing system shall be mocked-up or installed in the aircraft down to and including distribution tubing and outlets. folloxing tests shall be conducted, nd reports of these tests shall be submittsd to the 3ureau of Naval Weapons for final approval. The - 7 Provided by IHSNot for Resal

27、eNo reproduction or networking permitted without license from IHS-,-,-MIL-E-22285 Lb W 997990b 0392086 2 NIL-E- 22285(Wep) 4.3.2.1 Discharge duration - The system shall be discharged and the duration of discharge shal be timed by means of motion pictures taken at the rate of 32 frapes per second, or

28、 by any other means suitable to the Bureau of Naval Weapons. The pictures (if used) shall be taken from a position forward of all distribution outlets and also from a position opposite the distribution outlets at right angles to the fore and aft line of the aircraft. The structure on which the syste

29、m is set up shall be such that, as nearly as. possible, an unobstructed view can be obtained from all the distribution outlets. discharge duration shall be in accordance with the requirements of this specification. he 4.3.2.2 Distribution test - Under actual or simulated cruise conditions, the syste

30、m shall be discharged, and compliance with 3.8 shall be verified by use of an appropriate method of measuring agent concentration. 5. PREPAFATION FOR DELIVERY 5.1 This section is not applicable to this specification. 6. NOTES 6.1 Intended use - This specification is intended for use in the installat

31、ion of built-in fire extinguishing systems for the protection of aircraft in flight and during ground operations. NOTICE: are used for any purpose other than in connection with a definitely related Government procurement operation, the United States Govern- ment thereby incurs no responsibility nor

32、any obligation whatsoever; and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications or other data, is not to be regarded by implication or otherwise as in aiiy manner licensing the holder or any other person or corporation, or conveying any rights or permission-to manufacture, use, or sell any patented invention that nay in any way be related thereto. When Government drawings, ?ecifications, or other data Y Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-