1、SAE-AS18259ADOPTION NOTICESAE-AS18259, “WINDOW, INSTALLATION OF, ANTI-ICING, DE-GREASING,AND WASHING SYSTEMS“, was adopted on 17-SEP-97 for use by theDepartment of Defense (DoD). Proposed changes by DoDactivities must be submitted to the DoD Adopting Activity:Commander, Naval Air Warfare Center, Air
2、craft Division, Code414100B120-3, Highway 547, Lakehurst, NJ 08733-5100. Copies ofthis document may be purchased from the Society of AutomotiveEngineers 400 Commonwealth Drive Warrendale, Pennsylvania, UnitedStates, 15096-0001. http:/www.sae.org/_Custodians: Adopting Activity:Navy - ASArmy - AVNavy
3、- ASAir Force - 99FSC 15GPDISTRIBUTION STATEMENT A: Approved for public release; distributionis unlimited.SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and enginee ring sciences. The use of this report is entirelyvoluntary, and i
4、ts applicability and suitability for any particular use, including any patent infringement arising therefrom, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invit es your written comme
5、nts and suggestions.Copyright 1997 Society of Automotive Engineers, Inc.All rights reserved. Printed in U.S.A.QUESTIONS REGARDING THIS DOCUMENT: (412) 772-8510 FAX: (412) 776-0243TO PLACE A DOCUMENT ORDER: (412) 776-4970 FAX: (412) 776-0790400 Commonwealth Drive, Warrendale, PA 15096-0001AEROS PACE
6、STANDARDSubmitted for recognition as an American National StandardAS18259Issued 1997-08I nstallation of W indow A nti -I cing , D e -G reasing, and W ashing S ystems(G eneral S pecification F or )NOTICEThis document has been taken directly from U.S. Military Specification MIL-I-18259(Aer) and contai
7、ns only minor editorial and format changes required to bring it into conformance with the publishing requirements of SAE technical standards.The original Military Specification was adopted as an SAE standard under the provisions of the SAE Technical Standards Board (TSB) Rules and Regulations (TSB 0
8、01) pertaining to accelerated adoption of government specifications and standards. TSB rules provide for (a) the publication of portions of unrevised government specifications and standards without consensus voting at the SAE Committee level, (b) the use of the existing government specification or s
9、tandard format, and (c) the exclusion of any qualified product list (QPL) sections.1. SCOPE:1.1 This specification covers the general requirements for the design and installation of fluid anti-icing, de-greasing, and washing systems installed in military aircraft.2. APPLICABLE DOCUMENTS:2.1 The foll
10、owing specifications, standards, and publications of the issue in effect on date of invitation for bids, form a part of this specification:SAE AS18259 - 2 -2.1.1 Specifications:MilitaryMIL-S-6625 Spray Equipment, Aircraft Windshield, Anti-IcingMIL-V-7173 Vibration Tests of Fuel, Oil, and Miscellaneo
11、us Tanks; Process forNavy - Bureau of AeronauticsSD-24 General Specification for Design and Construction of Naval Aircraft2.1.2 Standards:Air Force-Navy Aeronautical DesignAND10049 Bosses - Straight Internal Thread EngineAND10056 Fitting End - Standard Dimensions for Flared Tube Connection and Gaske
12、t SealAND10064 Fittings - Installation of Universal and Bulkhead Flared Tube2.1.3 Publications:Air Force-Navy Aeronautical BulletinNo. 143 Specifications and Standards; Use of2.2 Availability of Specifications, Publications and Drawings:2.2.1 When requesting specifications, publications and drawings
13、 refer to both title and number.2.2.2 Copies of this specification and applicable specifications may be obtained upon application to the Commanding Officer, U.S. Naval Air Station, Johnsville, Pennsylvania, Attention: Technical Records Division.SAE AS18259 - 3 -3. REQUIREMENTS:3.1 Drawings and Diagr
14、ams:Prior to installation of any fluid type anti-icing, de-greasing or washing system the contractor shall submit for approval of the procuring activity two copies of pertinent drawings, material lists and diagrams showing details of the installation. The drawings shall include the proposed location
15、 of components in the aircraft, the name and specification of the basic fluid, anti-freeze additives, and pressurizing medium if used, tank and system pressures, capacity, tank construction details, tank and system proof pressures, safety features, and operational sequence of controls. Prior to fina
16、l acceptance of any system results of flight tests including photographs or sketches showing the distribution of fluid over the surface to be cleaned shall be submitted to the Bureau of Aeronautics for approval of flow pattern. A good fluid flow distribution pattern is considered one which shows flu
17、id over the entire area to be cleaned. In addition, photographs of the pump, tank(s), and controls showing actual installation in the aircraft shall be submitted to the Bureau of Aeronautics.3.2 Components:The system shall consist of the spray equipment components specified in Specification MIL-S-66
18、25, with such plumbing, electrical controls and wiring as necessary. In lieu of using a metering pump with electrical controls the design may utilize a pressurized tank with adequate controls for adjusting flow rate and pressure. In either type of system the applicable material, design and construct
19、ion, interchangeability and workmanship requirements apply to the design and installation of system components which are not specifically referred to herein. The design and installation of the system and components shall comply with all applicable requirements of Specification SD-24.3.2.1 Fluids: Al
20、l fluids used in the system shall be compatible with window materials and with other materials which the fluid may contact.3.2.2 Selection of Materials: Specifications and standards for all materials, parts, and Government certification and approval of processes and equipment which are not specifica
21、lly designated herein, and which are necessary for the execution of this specification, shall be selected in accordance with ANA Bulletin No. 143, except as provided in the following paragraph.3.2.2.1 AN or MS Standard Parts: AN or MS standard parts shall be used wherever they are suitable for the p
22、urpose, and shall be identified on the drawing by their part numbers. Commercial utility parts such as screws, bolts, nuts, cotter pins, etc., may be used, provided they possess suitable properties and are replaceable by the AN or MS standard parts without alteration, and provided the corresponding
23、AN or MS part numbers are referenced in the parts list and, if practicable, on the contractors drawings. In the event there is no suitable corresponding AN or MS standard part in effect on date of invitation for bids, commercial parts may be used provided they conform to all requirements of this spe
24、cification.SAE AS18259 - 4 -3.3 Tanks:3.3.1 Filling: Tanks shall be readily removable for filling or shall be accessible for filling without removing. Tanks shall be so located that they may be filled in flight. The tank shall be so located that rupture or leakage of toxic fumes or liquids will not
25、enter the cockpit, cabin, or other enclosure housing personnel.3.3.2 Pressurizing: For pressurized systems the tank shall include provisions for pressurizing.3.3.3 Instruction Markings: Instructions shall be provided on either the tank or the aircraft structure, near the filler neck and so located a
26、s to be easily readable. The instructions for filling, and pressurizing if applicable, shall be simple and complete, using letters 1/2 inch high, and include the following information, as applicable:FILL WITH:(Name and Specification number of fluid or fluids)WHEN CHANGING FLUIDS DRAIN AND FLUSH WITH
27、 _CAPACITY _PRESSURIZE WITH _ TO _ psig(Additional filling instructions or data considered necessary)3.4 Pressure Relief Valves and Safety Discs:The design of the system shall include pressure relief valves or other safety features as required to prevent overpressurizing or excess pressure due to th
28、ermal expansion.3.5 Drain:Systems utilized for dual purposes shall provide a means for draining and flushing the system at the lowest point.3.6 Threaded Fittings:AN and MS straight threaded fittings only shall be used and shall be assembled and connected in accordance with Drawings AND10049, AND1005
29、6, and AND10064.3.7 Supports:All tubing shall be rigidly supported. Tube supports shall be such as to prevent injury to the tubing. The maximum spacing between supports shall not exceed 24 inches, except that where tubes support fittings the spacings shall be suitably reduced.SAE AS18259 - 5 -3.8 Sp
30、ray Tube:The spray tube shall be designed to provide adequate anti-icing, de-greasing and washing with minimum fluid consumption.3.9 Controls:Controls shall be conveniently located with respect to operating personnel.3.9.1 Control Markings: Controls shall be marked to indicate their function, and no
31、rmal, minimum and maximum fluid flow where applicable.3.10 Gauge:A suitable gauge shall be provided for indicating the amount of fluid in tanks exceeding one gallon capacity. The gauge shall be so located in the aircraft as to be plainly visible to operating personnel during flight.3.11 Loss of Flui
32、d:The system shall be such that there will be no loss of fluid during flight maneuvers of the aircraft.3.12 De-Greasing:De-greasing systems are required on reciprocating engine aircraft to remove oil film from windows.4. QUALITY ASSURANCE PROVISIONS:4.1 Classification of Tests:4.1.1 Preproduction Te
33、sts: The first of any new model of equipment and the first of any installation in a new model aircraft shall be subjected to all the tests of this specification.4.1.2 Inspection Tests: Inspection tests are conducted on each installation. Inspection tests shall consist of Examination of System, Proof
34、 Pressure, and Ground test.4.2 Examination of System:Each system and component thereof not covered by detail specifications, shall be carefully examined to determine conformance with all installation requirements not covered by tests.4.3 Proof Pressure:The tank and other system components shall be s
35、ubjected to the specified proof pressure and shall show no leakage or other evidence of malfunctioning.SAE AS18259 - 6 -4.4 Ground Test:The controls shall be operated, to obtain minimum and maximum rate of fluid flow. Fluid from all openings of the spray tube shall contact the window.4.5 Flight Test
36、:The fluid flow pattern and the rate of fluid consumption shall be determined at normal cruising and maximum continuous operating speed of the aircraft. The fluid flow pattern shall indicate good coverage consistent with the approved photographs of the proto-type model. The rate of fluid consumption
37、 shall not exceed the specified rate.4.6 Vibration:The first of each new model of fluid tank shall be vibrated in accordance with the requirements of Specification MIL-V-7173. The tank used for vibration testing shall not be used in a production airplane.4.7 Rejection and Retest:Any defects discover
38、ed during the inspection and testing of the prototype installation shall be corrected by the contractor. Such corrective measures as may be found necessary shall likewise be incorporated in all subsequent installations. Failure of any component or unit of a system to conform to any one of the requir
39、ements of this specification or failure to function properly in any other respect shall be cause for rejection of the installation. A system which has been rejected may be reworked or have components or units replaced to correct the defects and resubmitted for acceptance. Before resubmitting, full p
40、articulars concerning previous rejection and the action taken to correct the defects found in the original shall be furnished to the Inspector.5. PREPARATION FOR DELIVERY:5.1 Not applicable to this specification.6. NOTES:6.1 Use:The systems covered by this specification are used for anti-icing, de-greasing, and washing of windshields, side panels, bombers windows, camera windows and other transparencies of military aircraft.PREPARED BY SAE COMMITTEE AGE-2, AIR CARGO & AIRCRAFT GROUND EQUIPMENT & SYSTEMS
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