1、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CONFIDENTIAL MIL-T-5422 MIL-I- 6181 Testing, Environmental, Aircrft Electronic Equipment Interference Limits, Tests and Design Requirements, Aircraft Electrical and Electronic Equipment MIL-(2-6781 Cont
2、rol Panel; Aircraft Equipment, Rack or Console Mounted MIL- L- 00680 5 Lacquer, Camouflage MIL-E-7894 Electric Power, Aircraft Characteristics of MIL-L-25467 Lighting, Integral, Instrument, General Specification For MIL-P-17555 Preparation for Delivery of Electronic Equipment, Miscellaneous Electric
3、al Equipment (Except Rotating Electrical Equipment) and Associated Repair Parts Test Procedures, Preproduction and Inspection, For Aircraft Electronic Equipment, Format For Nomenclature and Nameplates for Airborne Electronic and Associated Equipment MIL-T-18303 MIL-N-18307 STANDARDS Military MS 2524
4、5 - Connections, Input Power Airborne Electronic Equipment; 28-Volt DC, 115-Volt Single-phase AC, or 115/200 Volt 3-Phase AC, or Combinations MS 28053 Meter, Time Totalizing, 400-cycle PUBLICATIONS Bureau of Aeronautics SAR-300 - Mater ia1 Changes and Mater ia1 Bulletins, Preparation of Availability
5、 of Documents: -_- - 2.2 (1) When requesting applicable documents, give both title and number of each. Requests for all documents required in connection with specific procurement functions shall be made via the cognizant Inspector of Naval Material, Bureau of Aeronautics Representative, or Contracti
6、ng Officer. (a) Copies of this specification, applicable specifications, and publications may be obtained upon application to the Commanding Officer, Naval Aviation Supply Depot, (CDS), 5801 Tabor Avenue, Philadelphia 20, Pennsylvania, Copies of applicable drawings may be obtained upon application t
7、o the Commanding Officer, U. S. Naval Avionics Facility, Indianapolis 18, Indiana, (b) CONFIDENTIAL 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-1-22231 5 777770b 01508Lt 3 CONFIDENTIAL MIL-1-2223 l(Aer) 2.3 Precedence of Documents - When th
8、e requirements of the contract, this specification or appmTe-sFlZ6iary specifications are in conflict, the fllowing precedence shall apply: Contract - The contract shall have precedence over all referenced documents. - This Specification - This specification shall have precedence over all app7icabll
9、emary documents. Deviations from this specification, or from subsidiary documents where applicable, may be made only upon written approval. Referenced Specifications - Any referenced specification shall have precedence over all applkable subsidiary specifications referenced therein. All referenced s
10、pecifications shall apply to the extent specified. (I) (2) (3) 3. REQUIREMENTS 3.1 Parts, Materials and Processes - In the selection of parts, materials and processes, fulfillment of majorgn-bjectivesall be the prime consideration. In so doing . the following shall govern: (1) Parts, materials and p
11、rocesses as approved by Specification MIL-E-5400 shall be given first consideration. When the characteristics of standard MIL parts and materials are such that their use will not fulfill the requirements because of size, weight, performance or other reasons, material and parts shall be used which mo
12、st nearly meet or exceed the requirements of the respective standard parts and material specification. (2) (3) When a nonstandard part is used, the meeting of general material requirements such as nonflammable, fungus resistant, nontoxic, etc. , and the meeting of environmental conditions as require
13、d by Specification MIL-E-5400 or MIL-T-5422 shall be of prime consideration. (4) In the selection of parts, the above considerations shall apply if the assembly is to be built for detail part maintenance. In the event that the entire assembly is built to be expended, the assembly shall be constructe
14、d and the quality of the individual parts shall be such that the unit as a whole will pass material, electrical and environmental tests, Any assembly built to be expended shall be approved first by the Bureau of Aeronautics. 3.1.1 Nonstandard Parts and Material Approval - Approval for the use of non
15、- standard parts and materials shall be obtained as outlined in Specification MIL-E-5400, except as follows: (1) Mechanical parts shall be submitted as nonstandard parts only when the material requirements of Specification MIL-E-5400 are not met. CONFIDENTIAL 3 Provided by IHSNot for ResaleNo reprod
16、uction or networking permitted without license from IHS-,-,-MIL-1-2223 l(Aer) CONFIDENTIAL (2) Nonstandard parts of an electrical nature as defined in Specification MIL-E-5400, shall be approved before the preproduction model of the equipment is submitted for tests, The request for approval shall be
17、 forwarded to the Bureau of Aeronautics before the part is purchased or fabricated, In addition to or in lieu of the Nonstandard Part Data Sheet, the contractor shall submit an itemized list of the parts, their sources, .and the contractors drawing or purchase specification covering the parts, Tubes
18、 (Electron) - Electron tubes shall not be used except where the use of semi-co3uctors would not be practicable. (3) (4) Dissimilar Metals - In certain applications, such as in lubricated gears anabll bearings requiring intimate contact between dissimilar metals, and where passivation is impractical,
19、 dissimilar metals may be used in intimate contact, - Plastic Window - Pending qualified suppliers of plastic windows in accordancewith Specification MIL-P-80, material in accordance with Specification MIL-P-5425 may be used. Ferrous Al.loys - Passivation shall not be required for enclosed lubricate
20、d mechanical working parts made of corrosion resistant ferrous alloys where close tolerances must be held, such as gears, bearings, cams and shafts. Electron Devices - The choice and application of electron devices used in the (5) (6) 3.1.2 equipment shall be Ta55ordanceWth the following requirement
21、s and in the sequence noted: (I) MIL-E-4682 (2) The use of any electron device not meeting the requirements of (1) above must be approved by the Bureau of Aeronautics; however, before consideration for approval, the contractor shall submit the following information: (a) Quantitative data on the elec
22、trical advantages and mechanical adequacy of the proposed tube over the most nearly equivalent type on the acceptable listings. Test data and performance limits of the tube which must be maintained to insure satisfactory and reliable performance in the equipment, Information as to whether the tube m
23、anufacturer has received Military r Navy qualification approval for the particular tube, (b) (c) 3.1.2.1 Electron Device Complement - An electron device complement report shall be prepared in accordancep%cifcL-E-4682 and submitted to the Bureau of Aero- nautics for review and approval prior to prepr
24、oduction testing, Design and Construction General - The equipment shall conbrm with all the applicable requirements -.-_- 3.2 3,2.1 of Specification MIL-0 Class 2 equipment for design, construction, and workmanship, unless otherwise specified her ein. CONFIDENTIAL 4 Provided by IHSNot for ResaleNo r
25、eproduction or networking permitted without license from IHS-,-,-MIL-1-22231 58 m 77777Ob 0350850 1 m CONFIDENTIAL MIL -1-22231fAer) 3.2. 2 Total Weight - The total weight of the equipment, excludirig CakJleS, shall be a minimum consstent with good design and shall not exceed 14 pounds. 3.2.3 normal
26、 performant-Xez-under standard conditions and for making laboratory bench tests. Standard Conditions - The following conditions shall be used to establish Temperature Altitude Normal ground Vibration None Humidity Input power voltage Service Conditions - The equipment shall operate under any of the
27、environ- Room ambient (30“ + 10OC) Room ambient up to 90% relative humidity 115 f 1. O V AC and/or 27.5 rt O. 5 V DC 3.2.4 mental service cond-ions or reasonable combination of these conditions as specified in Specification MIL-E-5400 for Class 2 equipment, except as follows: 3.2.4. 1 Vibration - Wh
28、en mounted directly to a mounting panel without vibration isolators, the equiptl operate within specified performance limits when the mounting panel is submitted to continuous sinusoidal vibration within the frequency range of 5 to 500 cycles per second and having a double amplitude as defined by fi
29、gure 1. 3.2.4.2. Gunfire - When mounted directly to a mounting panel, he equipment shall operate within specmrformance limits while the mounting plate is subjected to 6000 impact shocks representative of gunfire, consisting of 1000 shocks of 25g f 10% peak magnitude in opposite directions along each
30、 of 3 mutually perpendicular axes, each shock impulse having a time duration of 5 milliseconds f 50%. 3.2.4. 3 Crash Safety - When mounted directly to a mounting panel, the equipment shall withstand at least 12 impact shocks of 30g f 10% peak magnitude applied to the mounting plate, consisting of 2
31、shocks in opposite directions along each of 3 mutually perpendicular axes and each shock impulse having a time duration of 11 milliseconds rt 10%. Bending and distortion shall be permitted; however, there shall be no failure of the attaching points and the.equipment shall remain in place. 3.2.4. 4 m
32、ent shall be capabXofiZhstanding a continuous load factor of 7. O, caused by aircraft accelerations, in opposite directions along each of three mutually perpendicular axes, Permanent degradation in performance or structural yielding shall not occur below 115 per cent of the design load factor. Struc
33、tural failure shall not occur below 150 per cent of the design load factor. Design Load Factor - When mounted directly to a mounting panel, the equip- 3.2.4. 5 Altitude - The altitude range shall be O - 60,000 feet (30 inches of mercury to 2 inches of mercr CONFIDENTIAL 5 Provided by IHSNot for Resa
34、leNo reproduction or networking permitted without license from IHS-,-,-MILI-22231(Aer) CONFIDENTIAL 3.2.5 Interchangeability - The equipment shall meet the interchangeability requirements as specified in Specification MIL-E-5400. Unless otherwise specified, interchangeability shall be measured again
35、st a model supplied by the Bureau of Aeronautics. performance limits of this specification continuously or intermittently for at least 200 hours without internal maintenance adjustments, or replacement of parts. The equipment shall provide a total life of 2000 hours, with reasonable maintenance adju
36、stments and replacement of parts. Maintenance Provisions and Field Testing - Provisions for maintenance shall be as specified in Specification mLm.cific test points and test facilities shall be provided to the greatest extent practicable for ease of field testing and maintenance. 3,2.6 Reliabi!ity -
37、 The equipment shall operate within the environmental and 3.2.7 3.2,7. 1 Tools - Special tools, as required, shall be supplied in a separate kit as part of this equipment-nd shall be kept to an absolute minimum, A list of special tools shall be submitted to the procuring agency, Undervoltage Protect
38、ion - The equipment shall not be damaged by voltages below the minimumpTcified herein-all automatically resume normal operation when the voltage returns within limits, Control Panels - All rack or console mognted control panels shall conform to the applicable requii.ements of Specification MIL-C-678
39、1, The configuration of all control panels must be approved by the Bureau of Aeronautics prior to preproduction testing. 3.2.8 382.9 3.2.10 Cabling and Connections - 3.2.101 Cables and Connectors - The equipment shall provide for the use of cables and connectors in aZEElance. with Specification MIL-
40、E-5400. 3.2.10.2 Interconnection Cabling - The equipment shall be capable of satisfactory operation using extrnal-Sringnaccoraance with the applicable requirements of Specification MIL-W-5088. The external wiring shall be unshielded, except that a minimpm number of the individual wires may be shield
41、ed when demonstrated as necessary to meet interference control requirements and provided the assembly of the cable to its plugs may be easily accomplished. External cables and that portion of the connectors attached to the cables shall not be supplied as part of the equipment. shall apply with these
42、 of a mrnimum of interconnecting shielded conductors. appqoval for equipment identificafwshall be in accordance with Specification MIL-N- 18307. 3.2. 11 Interference - The interference requirements of Specification MIL-1-6181 3.2. 12 Nomenclature and Nameplates - Nomenclature assignment and nameplat
43、e 3.3 3.3.1 Detail Requirements Indicator, Azimuth-Elevation-Range IP- 446/APG- 53A - The indicator shall - -_- meet the following requirements and shall give satisfactory performance when installed as a component of the Radar Set AN/APG-53A. modes defined in the succeeding paragraphs. Range and mod
44、e switching shall be accomplished by providing six external connections, which may be grounded by external switching for various combinations of range and mode. 3,3,1,1 Display - The indicator shall provide circuitry as required for the display CONFIDENTIAL 6 Provided by IHSNot for ResaleNo reproduc
45、tion or networking permitted without license from IHS-,-,-MIL-1-22231 58 = 777770b 0150852 5 MIL-1-2223 1 (Aer) CONFIDENTIAL 3. 3. 1. 1. 1 Range Only - The range only mode shall display a horizontal line approximately half the width of the display aperture centered laterally about the vertical cente
46、rline of the display aperture. This horizontal line shall be deflected vertically to indicate range from O to 10 nautical miles, The line width shall be l/lB-inch i 1/32-inch and the lower edge shall be ysed for range measurements. The line shall be straight and horizontal within 1/32-inch throughou
47、t the range of vertical deflection. The input signal for the range-only mode will be a d-c voltage having a scale factor of 20 volts per nautical mile. The load impedance imposed on the range voltage source shall be in excess of one megohm. 3.3. 1. 1. 2 Elevation-Range - The elevation-range mode sha
48、ll display elevation angles from 10 degrees above the airplane velocity vector to 15 degrees below the velocity vector against linear horizontal slant range scales of O to 10 and O to 20 nautical miles. Range increases from left to right. The O degree elevation reference line shall be horizontal and
49、 located vertically as shown in figure 2. The display shall be intensity modulated. (1) Input signals for the elevation-range mode will be as follows: Trigger - 93 ohms impedance; plus 50 i 15 volts; O. 6 to 1. O microsecond duration Video - 100 ohms impedance; the input will have a dynamic range of 20 db varying from . 2 V to 2 volts. In the elevation - range mode an altitude clearance marker will be mixed with the video. The clear
