1、.* - , ia JULY 1959 SUPERSEDING MlL-1-19461 (AER) IO APRIL I956 WLITARY SPECIPICATION PLOTTING BOARD, TACTICAL DISPUY, PT- Aircraft, Installation o! Electronlc Equipment, Aircraft, Qenera 8pecU- cation for Testing, Environrnen$l, Aircraft Electrdc Equipment Provided by IHSNot for ResaleNo reproducti
2、on or networking permitted without license from IHS-,-,-I i MIL-P-394b3A 66 . _.- - _ - -. ,- - I , ._ - .-.- .* . ML-P- 1946lA(Aer) i MIL-1-6181 , MIL-E-7894 . . _. -. MiL-D-18300 . . - r MIL-T-18303 .et : .- L. . MIL-N-18 307 . BTAN ADS . Military M 25245 PUBLICATIONS . Bureau of Aeronautics BAR-3
3、00 . 2.2 Availability of Documents: I 9999906 O329963 m interference Limits, Tests and Design Require- mente, Aircraft Electrical and Electronic Equlp- ment I Electric Power, Aircraft Characteristics of Design Data Requkements for Contract6 Covering Airborne Electronics Equipment . . Teet Proceduree
4、; Preproduction and Inspection, For Aircraft Electronlc Equipment, Format for . Nomenclature and Nameplates for Airborne Elec- . trbnic and Aesociated Equipment . ! Connections, input Power Airborne Electronic Equipment; 28-Volt DC, 115-Volt Single-Phase AC, or ll5/200 Volt 3-Phase AC, or Combina- t
5、ions I Material Changes and Material Bulletins, Preparation of I B :() Whenrequesting applicable iocuments give both the ttle and number. All requests shall be made via the cogni7-t Inspector of Naval Material or Bureau of Aero- nautics Representative. (2) Copies of this specfication and applicable
6、documents may be obtained upon applica- tion to the Commanding Officer, Naval Aviation Supply Depot, (CDS), Philadelphia 11, Pennsylvania. 2.3 Precedence of Documents - When the requirements of the contract, this specification or applicable subsidiary specifications are in conflict, the following pr
7、ecedence shall apply: (1) Contract - The contract shall have precedence over all refcrenced documente. subsidiary documents. Devhtions from this specification, or from subsidiary documents where applicable, may be made only upon written approval. 1 (2) This Specification - This specification shall h
8、ave precedence over all apilicable i I I (3) Referenced Specifications - Any referenced Rpecification shall have precedence dver all applicable subsidiary specifications.referenced therein. Ail relerenced specfi- cations shall apply to the extent specified. I . 9.1 Parts and Materials - In the selec
9、tion of ports and materials, fulfillment of major design -. objectivas be the prime consideration. In 80 doing the following shall govern: i 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-(1) Parts and material8 as approved by Specification MJL-E-
10、MOO ohall be given firrt consideration. (2) When the characterstics of etardard 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 mat nearly meet or exceed the requirements o
11、f the respective standard parts and material specification. (3) When a nonstandard part is used, the meeting of general material requirements euch as nonfiammable, fungus resistant, nontoxic, etc., ami the meeting of environmental conditions as required by Specification ML-E-5400 or MIL-T-5422 shall
12、 be of prime consde ration, (4) in the selection of parts, the above conslderations shall apply if the assembly is to be built for detail part maintenance. in the event that the entire aseernbly-is hlt to be expended, the assembly shall be so constructed and the quality of the individual parts shall
13、 be of such that the unit as a whole will pass material, electrical and en- vironmental tests. Any assembly built to be expended ehail be approved f16st by the Bureau of Aeronai tics. (6) Nonmagnetic materials eh11 be used for aii parts, except where magnetic materials are required. 3.1.1 Nonstandar
14、d Parts and Material Approd - Approval for the use of nonstandard parte and materials shbadtld-S-pecif!cation MIL-E-5400, except as Glows: . (1) Mechanical parts shall be submitted as nonstandard parte only when the material requirements of Specification ML-E-5400 are not met. (2) Nonstandard parts
15、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 however, before comidera- tion fcr approval, the contractor shall submit the following information. (a) Quantitative data
16、 on the electrical advantages and mechanical adequacy of the proposed tube over the most nearly equivalent type on the acceptable listings, (b) Test data and performance limits of the tube which must be maintained to in- . sure satisfrctory and reliable performance in the equipment. (c) information
17、as to whet!r the tube manufacturer lias received MiUtary or Navy *3,1.2.1 Electron Tube Complement -. A tube coziy?emec+ report shall be prepared in accord- ance with Specification MIL-E-4682 and submitted to the Bureau of Aeronautics for review and approval prior to preproduction testing. The tube
18、complement shall include ail electron tube types (including crystal diodes and transistors) used in the equipment, I qualification approval Tor the particular tube. . - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . MIL-P- 19461A(Aer) . _ . r I.
19、 4 3.2 - -sign and Construction: 1 * 3,2,1 General 2 The equipment shall conform with all the applicable reguirements of Specification Mlt-E-5400 .- Ilor design, construction and workmanship, unless otherwlse specified herein, Y* 3.2.2 Total Weight - The total might of the equipment, excluding cable
20、s, shall be a, mW- mum consistent with good design and shall not exceed 12-1/2 pounds, * 3.2.3 Operating Life - 3.2.3.1 Reliable Operating Lifz - The equipment shall have a reliable operating life of at least 600 hours without removal for bench servicing. Parte requiring servicing or replacement at
21、the end of this interval to renew this service Life shall be specified by the manufacturer. a 3.2.3.2 Tofal Operating Life - The equipment shall have a minimum total operating lfe of 2000 hours with reasonable servicing and replacement of parts, Parte requirhg replacemerd within this interva and the
22、 life of such parts shall be specified by the manufacturer. 3.2.4 Cabling and Connections - 3.2.41 Cables and Connectors - The equipment shall provide for the use of cables and con- nectors in accordance with Specification MIL-E-5400, All electrical connections to the PT-42Q/A shall be made through
23、a single MS standard connector. usingexternal wiring in accordance with the applicable requirements of Specification MIL-W-5088. The external wiring ehall be unehielded. External cables and that portion of the connectors attached to the cables shall not be supplied a8 part of the equipment. * 3.2.4.
24、2 interconnection Cabling - The equipment shall be capable of satisfactory operation * 3.2.4.3 input Power Connection - input power connections shall be in accorciaiice with MS 26245. I * 3.28 Nomenclature and Nameplates - Nomenclature assignment and nameplate approval for equipaent identification s
25、hall be in accordance with Specification M!L-N-lP307. A durable name- plate shall be securely attached to the exterior of the PT-429/A. AI1 markliige shall be legible and durable. * 3.2.-6: Interference Control - The generationof radio interference bp ihe equipment shall be controlled wIthin the lim
26、its of Specification MIL-1-6161. . . minimum specified herein and shall automatically resume normal operation when the voltage returns 3.2.7 Undervoltage Protection - The equipment shall not be damaged by voltages below the . within limits. * 3.2.6 gtzdard Condition6 - The following conditions shall
27、 be used to establsh normal Temperature Vibration None Humidity Input power voltage Service Conditions - The plotting board shall operate under any of the environmental i. performance characteristics under standard conditions Pnd for making laboratory bench teste, Room ambient (30 f 10C) Room ambien
28、t up to 90% relative humLdity 115 I 1.OV AC and/or 27.5 t0.5 V DC I. *. Altitude Normal ground 3.2,9 servlce condilion6 ooEble cornhination of these condition6 a8 specified in Specification MIL-E-6400 for Class 1 equipment except it shall not be required to operate above 16,000 feet altitude. . S. 2
29、.10 Input Power Requirements - The equipment shall meet all applicable rewfremente of Specification MIL-4 and Shall give specified performance from the foliowing power source6 with characteriatics 88 defined InSpecificatIon MIL-E-7804 having Iimib as specified hereinafter. The total power required a
30、hall nol exceed 100 Watte. . - - I 4 - -4 -I - - _ - I_. _.- -. _c_ - -_ . . -_-_ ., - -.- - _ .7- _- - . - . . -v- _ , . - - . .i _._L. F - -_I,-. . _ _ - . . I .- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- -. WIL-P-194bLA bb 7797906 0129766 3
31、 I .- - (i) AC Power (Single Phase) 115-Volt Constant Frequency (Type I) Operating voltage limits . Operating frequency limite Reduced performance voltige limite . (2) DC Power 28-Volt System -_I_ Operating voltage limits IdIL-P- 19461AfAer) 106 to 125 volte 360 to 440 cps (see paragraph 5.2.7) 24 t
32、o 30 volts i 3.2.11 . AC Limits - There are no requirements for performance at frequencies blow 960 cps. Down to 200 cycles the voltage shaii be considered as maintained within the operating limits, Below 200 cycles, the voltage shall be considered as varying proportionally with the frequency, with
33、zero voltage existing at aero frequency. Power Input Circuit - The negative side of the d-c power lhe ehah be internally grounded to the frame of the indicator. The 115-volt 400-cycle power input terminale to the PT-429/A . 3.2.12 , ehali be isolated from the frame. to the PT-429/A. 1 * 3.3 Performa
34、nce * 9.3.1 General - Unless otherwise specified, values set forth to establiLi the requirement8 for satisfactory performance apply to performance under standard conditions, When reduced perform- ance under environmental test conditions is acceptable, tolerances or values setting forth acceptable va
35、r:ations .mm the performance under standard conCitions will be specified. The termA used through- out the remalnder of this specification are defined as follows: “Bugclrefers to the carriage which supports the lamp and lens system and the pro- Track refers to motion of the bug across the screen when
36、 simulating the motion of jected spot of light representing the position of the aircraft. the aircraft. - Slew refers to the process whereby the bug is moved to a desired spot on the screen Range Scale (ahbreviated SCALE on the front panel) refers to the number of nautical Mode refers to indicator c
37、ondition of operation, %na1 In uts - The bug shall be positioned by 2 synchro eignals obtained from , . . by use of approprbte controls. miles represented by the diameter of the screen. 33.2 Eclipse-Pioneer Type%? one revolution of the arrow shall represent 360 in azimuth. The indlcator shall provid
38、e 28 volts ac 1/4 amp. excitation at line frequency for he heading synchro transmitter. Bug Follow-up Speed and Accuracy - The bug shall follow input signals representlng 200 knote on the 10 mile range and 400 knots on the 25 and 100 mile ranges. “he accuracy shall De within 1/32 inch. Accuracy of T
39、rue Heading Arrow - The accuracy shall be within 1.5 degrees. 3.3.3 3.3.4 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-:. I ! , i i -“-. - .I MIL-P- i946lA(Aer) . 5.4 . Detail Requirements - :I 3.4.1 ing detail requirements. Plotting Board, Tact
40、ical Display PT-428/A - This equipment shall meet the follow- o 3.4,l.l Function - The function of the PT-429/A equipment is to plot and display input data o 3.4.1.2 Form Factor and Mounting - Refer to figure 1 for data on dimensions and mounting. representing aircraft ground miles traveled arid air
41、craft true heading. The pT-429/A shall be provided with a suitable mounting pad capable of supporting the weight of the instrument and accessible from the rear of the indicator. No external shock mounts are required, o 5.4.1.3 Weight - The unit weight is 12 ibs 8 oz., excluding cables. 3.4.1.4 Mecha
42、nical Design - The instrument shail be designed so that the various functions . required by this specification and indicated in the block diagram (figure 2) are accomplished, The PT-429/A shall meet all of the requirements ,of MIL-E-5400 except as notcd herein. figure 1. The motion of the aircraft a
43、hali be indicated as a moving spot of light projected on a screen. 3.4.1.5 Front Panel - The general layout of the front panel of the indicator shall conform to I 3.4.1.6 Screen - The she, markings ard general construction of the screen shall conform to figure 1. .- 3.4.1.7 Screen - Lighting - Low l
44、evel red lighng shall be provided for lhe purpose of read- ing the scale graduations along the bearing line, grid lines, compass rose and any marks that may be made on the front surface of the screen. in order to adjust the intensity of the screen lighting, a control marked ILLUMINATION SCREEN, shal
45、l be provided on the front panel of the PT-429/A. At 28 volts d.c. the brightness of the screen shall be between 0.4 and 3.0 ft. lamberts. eter by .010“thick transparent plastic overlays on the top surface of the screen. The clips shall not. protrude awe the front surfiace of the panel. 3.4.1.9 Bug
46、- The bug shall project a l/rl“diameter spot of light on the top surface of the matte finished rotatable grid diak (see figure . The spot of lighl shall contain an arrow representing . is c-ed at a rate of 3 rpm, The shank of the arrow shall contain a cross mark to locate the center . of the bug. 3.
47、4.1.10 Bug Lighting - The brightness of the bug shall be adjustable by means of a control, marked ILLUMINATION-BUG, located on the front panel of the PT-42O/A. The maximum intensity of the light shall be sufficient to make the bug clearly visible in direct. sunlight, but in no case shall it be lees
48、than 250 ft. lamberts. Provlsions shall be made for convenent replacement of the lamp used as a source of light for the bug. . of the bug anywhere within an 8-1/4“diameter crcle concentric wiih the center of the screen, No damage ehaii occur to the indicator if the input signals are allowed to overr
49、ide the limits of travcl of thebug. 3,.4.1.12 Bug Drive Mechanism - The bug shaU be driven in North-South and East-West di- rections by means of lead scfewB wi iridlcated in figure 2, 3.4.1.13 Controle - The front panel of the indicator shall contain the following controls loca- ted.pe shown in figure l. All markinge on the front panel shall be illuminated with red light, 5.4.1
