1、1. SCOPE . 1.1 This specification covers the general requirements for aircraft antiskid .:. .br_ake control systems and their components. . 2. APPLICABLE DOCUMENTS 2.1 The following documents, of the issue in effect on date of invitation for bids or request for proposal, form a part of this specific
2、ation to the extent specified herein. SPECIFICATIONS Federal QQ-N-290 QQ-P-416 44-2-325 Military MIL-S-4040 MIL-J-5013 MIL-14-5088 MIL-E-5400 MIL-H-5440 MIL-P-5518 MIL-V-5 5 2 9 MIL-R-57 57 Nickel Plating (Electrodeposited) Plating, Cadmium (Electrodeposited) Zinc Coating, Electrodeposited, Requirem
3、ents for Solenoid, Electrical, General Specification for Wheel and Brake Assemblies; Aircraft Wiring, Aircraft, Installation of Electronic Equipment, Airborne, General Specification for Hydraulic Systems, Aircraft, Types I and II, Design, Installation, and Data Requirements for Pneumatic Systems, Ai
4、rcraft; Design, Installation, and Data Requirements for Valves, Hydraulic Directional.Contro1 Relays, Electrical (For Electronic and Communication Type Equipment), General Specification for Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-8075D
5、MIL-R-6 106 MIL-V-7915 MIL-P-8564 MIL-A-8625 MIL-H-8775 MIL-H-8890 MIL-H-8891 MIL-T-10727 MIL-C-26500 MIL-V-27 162 MIL-G-81322 MIL-W-81381 STANDARDS Military MIL-STD-100 MIL-STD-129 MIL-STD-130 MIL-STD-143 MIL-STD-461 MIL-STD-470 MIL-STD-471 MIL-STD-704 MIL-STD-785 MIL-STD-7 90 MIL-STD-794 MIL-STD-8
6、10 ._ Relays , Electric, Aerospace; .General Specification for Valves; Hydraulic, Directional Control, Slide Selector Pneumatic System Components, Aeronautical, General. Specification for Anodic Coatings, for Aluminum and Aluminum Alloys Hydraulic System Components, Aircraft and Missiles, General Sp
7、ecification for Hydraulic Comppents , Type III, (-65OF to +450F) , General Specification for Hydraulic Systems, Manned Flight Vehicles, Type III, Design, Installation, and Data Requirements for Tin Plating; Electrodeposited or Hot-Dipped, for Ferrous and Nonferrous Metals onnectors, General Purpose,
8、 Electrical, Miniature, Circular, Environment Resisting, Established Reliability, General Specificati.on for Valves, Servo Control, Electro-hydraulic, General Specification for Grease, Aircraft, General Purpose Wide Temperature Range Wire, Electric, Polyimide-Insulated, Copper and Copper Alloy Engin
9、eering Drawing Practices Marking for Shipment and Storage Identification Marking of US Military Property Standards and Specifications, Order of Preceden Selection of ce for the Electromagnetic Interference Characteristics Requirements for Equipment Maintainability Program Requirements (For Systems a
10、nd Equipments) Maintainability Demonstration Electric Power, Aircraft, Characteristics and Utilization of Reliability Program for Systems and Equipment, Development and Production Reliability AssuranceProgram for Electronic Parts Specifications Parts and Equipment, Procedures for Packaging .and Pack
11、ing of Environmental Test Methods 2 p- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-8075D MIL-STD-831 Test Reports, Preparation of MIL-STD-882 System Safety Program for Systems and Associated Subsystems MIL-STD-889 Dissimilar Metals and Equi
12、pment: Requirements for PUBLICATIONS Air Force-Navy Aeronautical Bulletin 438 Age Controls of Age-Sensitive Elastomeric Items (Copies of specifications, standards, drawings, and publications required by suppliers in connection with specific procurement functions should be obtained from the procuring
13、 activity or as directed by the contracting officer.) 3. REQUIREMENTS 3.1 Preproduction. This specification makes provisions for preproduction testing. The preproduction testing contained herein is the minimum testing which will meet the preproduction requirements. Final approval will be contin- gen
14、t upon successful completion of these tests and the tests specified in the detail specification including satisfactory demonstration on the intended aircraft. 3.1.1 Safety of flight. Safety of flight is the minimum level of successful testing required before release for first flight. It shall be as
15、identified in section 4 of this document. 3.2 Selection of specification and standards. Specifications .and standards for all materials, parts, and customer certification and approval of processes and equipment, which are not specifically designated herein and which are neces- sary for the execution
16、 of this specification, shall be selected in accordance with procedures established by the procuring activity, except as provided in 3.2.1, 3.2.1 Standard parts. Standard parts (MS or AN) shall be used wherever they are suitable for the purpose and shall be identified on the drawings by their part n
17、umbers, Commercial utility parts, such as screws, bolts, nuts, cotter pins, etc, may be used provided they possess suitable properties and are replaceable by the standard parts without alteration, and provided the corre- sponding standard part numbers are referenced in the parts list, and if practic
18、able, on the suppliers drawings, In the event there is no suitable corresponding standard part in effect on date of invitation for bids, commercial parts may be used provided they conform to all requirements of this specification. Parts shall be selected in accordance with MIL-STD-143. “ 1, Provided
19、 by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-807 51) 3.3 Materials. Materials used in the brake control system components shall be of high quality, suitable for the purpose intended, and shall conform to applicable Government specifications as specifi
20、ed herein. 3.3.1 Dissimilar metals. The-use of dissimilar metals in contact, as defined in MIL-STD-889, shall be avoided. Where complete compliance proves impractical, electrolytic action shall be minimized by plating or some other suitable method of dissimilar surface isolation. 3.3.2 Corrosion res
21、istance. Corrosion prevention is of prime importance and material selection shall be made accordingly; 3.4 Design and construction. Detail design and construction of the components and brake control systems shall conform to the contractor-prepared detail speci- fication and the requirements specifie
22、d herein, The components shall be suitably sealed against dust, dirt, and moisture to insure satisfactory operation in the aircraft environment. The useful life shall be as specified in the detail speci- fication and shall be equal to the aircraft design useful life. 3.4.1 Interface requirements. Th
23、e brake control-system shall be designed to meet the interface requirements of the applicable aircraft including the following: (a) Brake torque characteristics (in accordance with MIL-W-5013) (b) The brake metering system and its components (including line sizes, etc) (c) Expected flow requirements
24、 (d) Strut dynamic characteristics (e) Total aircraft stop performance requirements (in accordance with MIL-W-5013) (f) Dimensional limits I (g) Various tire physical characteristics. 3.4.2 System features. The following are features which may be required for systems in addition to the basic skid co
25、ntrol functions depending upon the air- craft configuration and.landing distance requirements. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.4.2.1 Touchdown protection. Where there is a reasonable.possibi1ity of applying brake pressure before w
26、heel spin-up, the brake control system shall provide continuous release of brake pressure. Strut compression with wheel rotation override intelligence is normally employed to determine that the air- craft is on the ground, wheels are rotating, and the aircraft is ready for braking,. In selecting tou
27、chdown protection, the probability of introducing additional failure modes and failure points should be considered. -3.4.2.2 Failure detectionlfailure mode. The failure detection circuit shall be of the “passive“ type; that is, it will function to provide failure indica- tion, visual or audio, witho
28、ut altering remaining skid control capability. The brake control system shall fail with “brake pressure as metered by the pilot,“ except for systems with four or more control valves, where the affected wheel shall be isolated. Pilot function shall not be required to deactivate the antiskid system in
29、 order to maintain brake metered pressure. 3.4.2.3 Cockpit warning light. A cockpit warning light, preferably mounted in a prominent location within.the pilots field of vision during the landing and braking phase of flight, shall be provided to indicate that there has been a system malfunction and t
30、he brake pressure is as metered. 3.4.2.4 Emergency operation. The brake control system shall function only on the normal braking system. The system shall not degrade braking capability when the aircraft is operated with any alternate or emergency brake system. This design requirement shall apply for
31、 the system turned off as weil as on. 3.4.2.5 System integr.ity testing. If the antiskid system has a built-in self-monitoring test circuit, the pilot test monitoring procedure shall be identical for both ground and inflight system conditions. Normal braking shall be available when system testing is
32、 performed during taxiing or parking conditions o 3.4.3 Reliability. Quantitative reliability requirements shall be established for the brake control system and its components consistent with the weapon system requirements. The program shall be in accordance with MIL-STD-785 and MIL-STD-790. A failu
33、re mode and effect analysis shall be included in .the data requirements. 3.4.4 Maintainability. Quantitative maintainability requirements shall be established for th. brake control system and its components consistent with the weapon system requirements. The program shall be in accordance with MIL-S
34、TD- 470, and the demonstration shall be consistent with MIL-STD-471. The require- ments shall apply to maintenance in the planned maintenance and support environment. Factors to be considered shall include time, rate, complexity, and costs of system and component maintenance. 5 “. “ - Provided by IH
35、SNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.4.4.1 Maintenance tools and equipment. The design shall be such as to accommodate, to the greatest extent, disassembly, reassembly., and service maintenance by use of tools and items of maintenance equipment normal
36、ly avail- able as commercial standard. Design requiring .specially designed maintenance tools and equipment shall be kept to a minimum. 3.4.4.2: Special.support equipment. Special support equipment, if required, shall be designed in accordance with the requirements for the aircraft system and shall
37、include flight-line fault isolation capability of line-replaceable items without breaking aircraft wiring connections. The test equipment Limits shall reflect the effect of brake-induced temperature levels of the wheel speed detectors and valves due to fluid temperature rise. 3.4.5 Transportability.
38、 Any special transportability requirements shall be identified in the detail specification. 3.4.6 Safety. Safety requirements shall be established in accordance with MIL-STD-882. I 3.4.7 Physical characteristics 3.4.7.1 Weight limits. The production weight limits of the brake control system shall be
39、 specified by component in the detail specification. 3.4.7.2 Dimensional limitations. Critical dimensional limitations shall-be specified in the detail specification. 3.4.7.3 Strength. The structural strength of all units of the brake control system shall be such that, when installed, operation will
40、 not be impaired, and no part of the device or its mounting shall show evidence of failure under the maximum imposed mechanical operating loads, accelerations, or wrench torque loads required for making connections. 3.4.8 Electrical-electronic requirements 3.4.8.1 Electronic components. All electron
41、ic assemblies shall be designed in accordance with MIL-E-5400. Special attention shall be given to the follow- ing: moisture-proofing of assemblies, including connectors; providing system component and tolerance compatibility throughout the extremes of the aircraft temperature environment and mainte
42、nance requirements; and tolerance to the electromagnetic interference environment. 3.4.8.2 Electric power requirements. When designed for electrical operation, the brake control system shall conform to all applicable requirements of MIL-STD-704, category B, and shall give specified performance from
43、the power source configuration specified in the detail specification. During power in- terruption, as defined in MIL-STD-704, category B, the system shall revert to “brake pressure as metered by the pilot.“ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS
44、-,-,-MIL-B-8075D 3.4.8.3 Relays. Relays used in the brake control system shall conform to the applicable requirements of MIL-R-6106 and MIL-R-5757. 3.4.8.4 Wiring. Ext-ernal wiring shall be installed in accordance with MIL-W-5088 and shall be of the type specified in MIL-W-81381. Internal wiring sha
45、ll be compatible with accepted industry standards and the configuration. 3.4.8.5 Connectors. Component external connectors shall be in accordance with MIL-(2-26500, threaded type with lock wire. 3.4.9 Hydraulic-pneumatic components 3.4.9.1 Hydraulic equipment - peneral, Hydraulic components shall co
46、nform to the applicable requirements of MIL-H-5440, MIL-H-8775, MIL-H-8890, and MIL-H-8891. 3.4.9.2 Solenoid-operated control valves. Solenoid-operated control valves shall conform to the applicable requirements of MIL-V-7915 or MIL-V-5529. Design of the solenoid shall conform to the applicable requ
47、irements of MIL-S-4040, with the exception that solenoids employing multiple windings will be permitted. 3.4.9.3 Pressure-modulating valves. Pressure-modulating valves shall be designed in accordance with the applicable requirements of MIL-V-27162 and shall be suitable for the brake control system e
48、nvironment with special emphasis upon contamination tolerance, stability with life and temperature, tolerance to service handling, and moisture sealing. 3.4.9.4 Pneumatic equipment. Pneumatic components shall conform to the applicable requirements of MIL-P-5518 and MIL-P-8564. 3.4.10 Lubrication. Lu
49、brication shall be in accordance with MIL-G-81322 with normal maintenance practice. . I 3.5 Perf ormance 3.5.1 The brake control system in conjunction with the aircraft brake system shall provide, within the limits of the aircraft braking environment, a means of safely stopping the aircraft on the required runway length, width, and sur- face condition. The brake control system shall provide a means of controlling brake pressure to maintain wheel rotation w
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