1、 MIL-I-85O3A 58 = 77777Ob 0173587 b fz-. o/-cScf MIL-I-85083A(AS) 26 June 1985 SUPERSEDING 15 November 1977 MIL-A-85083(AS) I -I or This specificat MILITARY SPEC IF ICATION IND ICATOR, ANALOG DISPLAY IP- 722F/AVA- 1 on is approved for use by the Naval Air Systems Command, Department of the Navy, and
2、 is available for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers the design, performance, and acceptance requirements for the Analog Di spl ay Indicator (AD I), IP-722F/AVA-1. indicator generates and displays a contact analog presentat
3、ion which includes a flight command presentation. Converter (RDC) and Forward Looking Infrared (FL IR) information. 2. APPL KABLE DOCUMENTS The The indicator also accepts and displays Radar Data 2.1 Government documents. 2.2 Specifications, standards, and handbooks. Unless otherwise specified, the f
4、ollowing specifications and standards of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified in the solicitation form a part of this specification to the extent specified herei n. SPEC IF KATIONS MIL ITARY MIL-E-1 Electron Tube, Genera
5、l Specification for Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addessed to: Commanding Officer, Naval Air Engineering Center, Systems Engineering and Standardization Department (SESD), Code 93, Lakehurst
6、, NJ. 08733 by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. FSC 5895 DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited rTHIS DOCUNENT CONTAINS 77 PAGES P Provided by IHSNot for
7、 ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-85083A 58 U 9999906 0173588 8 U MIL- 1-85083A(AS) M IL-C-675 M IL-B-5087 M IL-W-5088 M IL-E-5272 L M IL-E-5400 M IL-T-5422 MIL-M-7793 M IL-E-17555 M IL-T-18303 MIL-N-18307 M IL-C-25050 MIL-T-81624 STANDARDS MIL ITARY M
8、 IL-STD-461 C Coating of Glass Optical Elements ( Ant i -Ref 1 ect i on ) Bonding, Electrical and Lightning Protection for Aerospace Systems Wiring; Aerospace Vehicle Envi ronmental Testing , Aeronautical and Associated Equipment, General Specification for Electronic Equipment, Airborne, General Spe
9、cification for Testi ng , Envi ronmental , Ai rborne Electronic and Associated Equipment Meter, Time Totalizing Electronic and Electrical Equipment, Accessories, and Repair Parts; Packaging and Packing of Test Procedures; Preproduction, Acceptance and Life for Aircraft Electronic Equipment, Format f
10、or Nomencl ature and Identi fication for El ectroni cs, Aeronaut i cal and Aeronautical Support Equipment Incl udi ng Ground Support Equipment Colors, Aeronautical Lights and Lighting Equipment, General Requirements for Television Displ ay Requirements for Amendment 1 the Weapons System for Guided W
11、eapon Mark 1 All Mods (WALLEYE) and Guided Weapon, Practice MK 4 MOD 0/1 Electromagnetic Emissions and Susceptabi 1 i ty Requirements for the Control of Electromagnetic Interference Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL- 1-85083A( AS) M
12、 IL-STD-470 M IL-STD-471 Maintainability Verification/ M IL-STD-704 Aircraft Electric Power M IL-STD-781 Maintainability Program for System and Equipment Demonstration/Eval uation Characteristics Reliability Design and Production Acceptance Tests : Exponenti al Di stri buti on Re1 i abi 1 i ty Progr
13、am for Systems and Equipment Deve1 opment and Production MIL-STD-785 M IL-STD-794 Parts and Equipment, Procedures for Packaging and Packing of M IL -S TD-882 System Safety Program Requirements MIL-STD-965 Parts Control Program M IL-STD-2074 MS 17322 Failure Classification for Re1 i abi 1 i ty Testi
14、ng Meter, Time Totalizing, Miniature Digital 115V, 400 Cycle (Copies of specifications, standards, handbooks, drawings, and pub1 ications required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting off
15、icer.) 3. REQUIREMENTS 3.1 First article. subjected to first article inspection (see 4.4 and 6.3). 3.2 Parts, materials, and processes. In the selection of parts and materials, fulfillment of major design objectives shall be the prime consideration. In so doing, the following shall govern: When spec
16、ified, (see 6.2.1), a sample(s) shall be a. Microelectronic techno1 ogy shall be considered and microelectronic items shall be in accordance with the requirements specified herein. Other parts and materials requirements shall be in accordance with MIL-E-5400. c. Nonrepairable subassembl ies shall be
17、 used in accordance with b. M IL-E-5400. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-SO3A 5B m 7799706 0173590 b m MIL- 1-85083A(AS) d. When previously produced models of this equipment did not use- nonrepairable subassemblies, the design
18、 shall not be changed to employ nonrepai rable assembl ies without the approval of the procuri ng act i vi ty . 3.2.1 Nonstandard parts and materials approval. Approval for the use of non-standard parts and materi al s (i ncl udi ng electron tubes, transistors, and diodes) other than microelectronic
19、 devices shall be in accordance with MIL-E-5400. Approval for microelectronic devices shall be in accordance with MIL-STD-965. 3.2.2 Limited-life items. The AD1 shall not contain Limited Life Items which require scheduled replacement within the minimum specified operating life of the AD I. 3.2.3 Mic
20、roelectronic modular assemblies. When used, microelectronic modular assemblies shall meet the requirements of MIL-STD-965. 3.2.4 Modules. Conformal coatings, encapsulants, embedments or potting materi al s used with modul ar assembl ies contai ni ng i ntegrated circuits and discrete parts shall be e
21、asily removable without damage to the assembly. Modul es shall not be hardwired. 3.3 General design and construction. Unless otherwise specified herein, the AD1 shall be in accordance with all the applicable design, construction, and workmanshi p requirements of MIL-E-5400. 3.3.1 Total weight. The t
22、otal weight of the ADI, including light filters but excluding cables, shall be a minimum consistent with good design and shall be not greater than 47 pounds (21.3 kg). for mounting. The total weight shall include provisions 3.3.1.1 Size. The dimensions of the AD1 shall be in accordance with figures
23、1, 2, and 3. 3.3.1.2 Mounting. Mounting provisions for the AD1 shall be in accordance with figure 1. 3.3.1.3 Time totalizing meter. The AD1 shall contain a time totalizing meter, MS 17322, in accordance with MIL-M-7793. figure 1. 3.3.2 Reliability program. in accordance with MIL-STD-785. the ADI, th
24、e program previously approved may be continued unless otherwise specified in the contract or order. The meter shall be mounted as shown in The contractor shall conduct a re1 iability program On a reorder from a contractor who is producing 4 Provided by IHSNot for ResaleNo reproduction or networking
25、permitted without license from IHS-,-,-M IL- 1-85083A( AS) 3 L I # - i f a W 2 Y -!i F a W U - i NOTES : lx TL-5- 1. Dimensions are in inches 2. Un1 ess otherwise noted, to1 erances are rO.010. F IGURE 1. Anal og di spi ay i ndi cator. 5 Provided by IHSNot for ResaleNo reproduction or networking per
26、mitted without license from IHS-,-,-MIL-I-85083A 5 m 979990b 0373592 T M M IL- 1-85083A( AS) 4 Notes : 1. Dimensions are in inches. 2. Unless otherwise noted, tolerances are f 0.010. FIGURE 2. Left indicator lights. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without licen
27、se from IHS-,-,-VIL-I-85083A 58 W 999990b 0173593 1 W M IL- 1-85083A( AS) a U 3 a 4 S 2.48 345 1 r .I75 0- ! I ,250- 112-40 UN-2A CAPTIVE HARDWARE 2 PL 4 I 4.573 PCB .687 c c -2.465- bo2 -351 r -.I95 * OOOb L- 1.47- Notes : 1. Dimensions are in inches. 2. Unless otherwise noted, tolerances are f 0.0
28、10. ,.FIGURE 3. Right indicator lights. 6.037 t*020 -AVIATION YELLOW .I a7 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-85083A 58 M 7799706 0373574 3 MIL- 1-85083A(AS) 3.3.2.1 Operational stability. The AD1 shall operate with satisfactory
29、performance, continuously or intermittently without the necessity for readjustment of any controls which are inaccessible to the operator during normal use. 3.32.2 Operating life. The AD1 shall have a total operating life of 10,000 hours with minimal servicing and replacement of parts. 3.3.2.3 Relia
30、bility. The ADI, including any Built-In-Test (BIT) provisions, shall have an upper test Mean Time Between Failure (MTBF) (o) of 445 hours with 80 percent confidence when- tested and accepted as specified in 4.5.1.3, 3.3.2.4 Storage service life. At any time within, or immediately following an 18 mon
31、th storage period, the AD1 shall be capable of meeting all the requirements of this specification, under any combination of environments specified herein without component or part rep1 acement, readjustment, or other maintenance actions. 3.3.3 Cabling and connections. 3.3.3.1 Cables and connectors.
32、The AD1 shall provide for the use of wiring and connectors i n accordance with MIL-E-5400. 3.3.3.2 Interconnection cabling. The AD1 shall be capable of specified operati on usi ng external wi ri ng i n accordance with the appl i cab1 e requi rement s of MIL-W-5088. Such external wiring shall be unsh
33、ielded, except that a minimum number of the individual wires may be shielded when demonstrated as necessary to meet interference control requirements. 3.3.4 Lighting and controls. 3.3.4.1 Controls. AD1 controls, contro accordance with MIL-E-5400. knobs, and legends shall be in 3.3.4-.2 Indicator lig
34、hts. Unless otherwise specified herein, the AD1 lights shown in figures 2 and 3 shall be in accordance with .MIL-E-5400. 3.3.5 Interchangeability. The AD1 shall be in accordance with the interchangeabil i ty requirements of MIL-E-5400. 3.3.6 Interference control. The generat (EM11 bv the AD1 and the
35、 vulnerabilitv of with th requi rements of M IL-STD-461.“ on of electromagnetic interference the AD1 to EM1 shall be in accordance 3.3.6.1 Conducted and radlated emissions The conducted and radiated emissions of the AD1 shall be controlled in accordance with the limits and requirements of MIL-STD-46
36、1 and as specified herein. 3.3.6.2 Conducted and radiated susceptibility. There shall be no malfunction, change in normal indication or desradation of performance of the AD1 when subjcted to the tests and requirements -specified in MIL-STD-461. 8 1 I 1 t Provided by IHSNot for ResaleNo reproduction
37、or networking permitted without license from IHS-,-,-1 I MIL-1-85083A 58 9999906 0373575 5 M IL- 1-85083A( AS) 3.3.7 Maintainability. The maintainability program, BIT features, construction and packagi ng, provi si ons for test poi nt s , and other mai ntai nabi 1 i ty parameters shall be in accorda
38、nce with MIL-STD-470 and as specified herein. 3.3.7.1 Detail maintainability requirements. 3.3.7.1.1 Preventive maintenance. The AD1 shall not have preventive maintenance requirements. 3.3.7.1.2 Organizational level. Organizational level maintenance shall use rep1 aceabl e assembly (WRA) . defective
39、 ADI, replace it with a ready for issue AD1 and verify system repair using the test mode. 3.3.7.1.2.1 Fault isolation. the unambigous fault isolation to the defective aircraft WRA by means of test mode analysis for at least 95 percent of all possible AD1 faults, when the faults are ranked by frequen
40、cy of occurrence, with a 90 percent confidence 1 evel 1 test mode (see 3.4.13.4.5) (BIT) for fault isolation to the aircraft weapon Thi s 1 evel of mai ntenance shall remove the Ground support equipment (GSE) shall not be required. f BIT shall be incorporated into the AD1 to enable 3.3.7.1.2.2 Remov
41、e and replace. in the aircraft shall be not greater than 12 minutes mean time (exclusive of The time to remove and replace the equipment access time). 3.3.7.1.2.3 Turn around time. The organizational level turn around time shall be the total of the time required for fault isolation, removal and repl
42、acement, and repair verification. The turn around time shall be not greater than 16 minutes mean time. 3.3.7.1.3 Intermediate level. Intermediate level maintenance shall consist of the repair of the AD1 and modules, shop replaceable assembl ies (SRA) , in shops. off-ai kraft 3.3.7.1.3.1 Checkout Equ
43、 SRA, removal 3.3.7.1.3.2 fault detect AD1 re air. -Y pment Mini-SACE AN/ASM-461) for fault detection, isolation to the and replacement of the SRA, and AD1 operational verification. The AD1 shall be compatible with Mini-Shop Automatic SRA repair. SRAS shall have test points available which allow on
44、and isolation to the faulty piece part group. SRA operational verificat-ion is accomplished by test point examination and by the operation of the SRA in the ADI. Repair is c L achieved by the removal and replacement of the identified piece part(s). - 3.3.7.1.3.3 Intermediate level equipment repair t
45、ime. The intermediate level Equipment Repair Time (ERT) shall be the total of the times for removal and replacement of the defective SRA and the removal and replacement of a defective part(s) including fault isolation, access, and secure times. The ERT shall be not greater than 110 minutes. L 9 Prov
46、ided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-5083A 5 7777906 0373576 7 MIL- I-85083A( AS) General maintainability requirements. 3.3.7.2 3.3.7.2.1 Task criteria. Each of the maintenance times specified in 3.3.7.1.2 shall be accomplished with a mi
47、nimum of two maintenance personnel of no higher than intermediate skill (E-5) for at least 95 percent of the maintenance tasks. 3.3.7.2.2 Built-In-Test. Suitable BIT features shall be incorporated into the AD1 to provide the.operator with indications of AD1 readiness and to locate the fault to the m
48、alfunctioning aircraft WRA. using manually activated test pattern(s) displayed on the cathode ray tube (CRT) and shall be capable of unambiguously isolating to the defective aircraft WRA for at least 95 percent of all possible AD1 faults when the faults are ranked in order of their occurrence with a
49、 90 percent confidence level . These features shall be implemented 3.3.7.2.2.1 Test displax. provide a static or dynamic test display. complete capabilities of the AD1 and unambiguously isolate to the WRA. display shall be easily interpreted by the operator and shall not require complex mental calculations. During the test mode (see 3.4.13.4.5), the AD1 shall The test display shall exe
