SAE AS 5778-1997 Covers Aircraft Components General Requirements for《飞机组件护盖的一般要求》.pdf

1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there

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4、 (outside USA)Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AS5778 AEROSPACESTANDARDAS5778 Issued 1997-08 Reaffirmed 2017-11 Covers, Aircraft Components, Gen

5、eral Requirements For RATIONALE AS5778 has been reaffirmed to comply with the SAE Five-Year Review policy. NOTICEThis document has been taken directly from U.S. Military Specification MIL-C-5778D and contains only minor editorial and format changes required to bring it into conformance with the publ

6、ishing 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 001) pertaining to accelerated adoption of government specifications and standards. TSB rules p

7、rovide 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 standard format, and (c) the exclusion of any qualified product list (QPL) sections.1. SCOPE:1.

8、1 Scope:This specification covers general requirements for covers intended to protect the following aircraft parts:Cockpit Fuselage CanopyEngine ArmamentPropeller or Rotor Miscellaneous1.2 Classification :Covers shall be of the following types, as specified (see 6.2):Type I - Waterproof Fabric Mater

9、ial (see 3.3.1.1)Type II - Coated Material (see 3.3.1.2)2. APPLICABLE DOCUMENTS:2.1 Government documents :2.1.1 Specifications and standards : The following specifications and standards form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these docum

10、ents are those listed in the issue of the Department of Defense Index of Specifications and Standards (DODISS) and supplement thereto, cited in the solicitation (see 6.2).SPECIFICATIONSFEDERALT-T-881 Twine, Cotton, SeineV-F-106 Fastener, Slide, InterlockingCCC-C-419 Cloth, Duck, Cotton, Unbleached,

11、Plied-Yarns (Army and Numbered)CCC-D-950 Dyeing and Aftertreating Processes for Cotton ClothsPPP-B-601 Box, Wood, Cleated-PlywoodPPP-B-636 Box, Shipping FiberboardMILITARYMIL-P-116 Preservation, Methods ofMIL-W-5665 Webbing, Textile, Cotton WarpMIL-C-10799 Cloth, Coated Cotton, Vinyl Coated, Fire an

12、d Mildew ResistantMIL-R-17343 Rope, NylonMIL-C-20696 Cloth, Coated, Polyster or Goop, Synthetic, Nylon, WaterproofMIL-F-21840 Fastener Tapes, Hook and Loop SyntheticMIL-M-46032 Fungus Resistant Treatment for Sandbags: Cooper ProcessesSTANDARDSFEDERALFED-STD-595 ColorsFED-STD-751 Stitches, Seams and

13、StitchingSAE INTERNATIONAL AS5778 Page 2 of 17_ 2.1.1 (Continued):MILITARYMIL-STD-100 Engineering Drawing PracticesMIL-STD-129 Marking for Shipment and StorageMIL-STD-130 Identification Marking of U.S. Military PropertyMIL-STD-147 Palletized Unit LoadsMIL-STD-831 Test Reports, Preparation ofMIL-STD-

14、2073-1 DoD Material Procedures for Development and Application of Packaging RequirementsMS20230 Grommet, Metallic, Plain and Spur, With Washer, Type I and Type IIIMS51700 Streamer, Warning(Unless otherwise indicated, copies of federal and military specifications, and standards, are available from: S

15、tandardization Documents Order Desk Bldg. 4D, 700 Robbins Avenue Philadelphia, PA 19111-5094)2.1.2 Other Government documents, drawings, and publications : The following other Government documents, and publications form a part of this document to the extent specified herein. Unless otherwise specifi

16、ed, the issues are those cited in the solicitation.Commercial Item DescriptionA-A-52094 Thread, Cotton(Unless otherwise indicated, copies of commercial item descriptions are available from: Standardization Documents Order Desk Bldg. 4D, 700 Robbins Avenue Philadelphia, PA 19111-5094)2.2 Non-Governme

17、nt publication :The following document(s) form a part of this document to the extent specified herein. Unless otherwise specified, the issues of the documents which are DoD adopted are those listed in the issue of the DODISS cited in the solicitation. Unless otherwise specified, the issues of docume

18、nts not listed in the DODISS are the issues of the documents cited in the solicitation (see 6.2).American Society for Testing and Materials (ASTM)ASTM D 3951 Standard Practice for Commercial Packaging(Application for copies of this ASTM should be addressed to American Society for Testing and Materia

19、ls, 1916 Race Street, Philadelphia, PA 19103-1183).SAE INTERNATIONAL AS5778 Page 3 of 17_ 2.3 Order of precedence :In the event of a conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes a

20、pplicable laws and regulations unless a specific exemption has been obtained.3. REQUIREMENTS:3.1 First article:When specified (see 6.4), a sample shall be subjected to first article inspection (see 6.4) in accordance with 4.4.3.2 General :In addition to the requirements herein, the requirements spec

21、ified on the drawings for covers for the particular model of aircraft shall also apply.3.3 Materials :Materials shall be as specified herein. Where materials are not specifically designated, they shall be designed or selected to be suitable for the purpose.3.3.1 Fabric Material :3.3.1.1 Type I:Unles

22、s otherwise specified, Type I materials shall be as specified in 3.3.1.1.1 thru 3.3.1.1.4.3.3.1.1.1 Transparent plastic canopies : Material conforming to MIL-C-10799 shall be used in the covers for transparent plastic canopies such as the bombardier and pilot compartments, nose section, turrets and

23、sight blisters.3.3.1.1.2 Engine covers : Material for engine covers shall conform to MIL-C-10799, type II, class 4.3.3.1.1.3 Warning streamers : Warning streamers, when specified (see 6.2), shall be in accordance with MS51700-12. The streamers shall be long enough to permit at least a 12 inch length

24、 exposure when the cover is installed on the aircraft.3.3.1.1.4 All other covers : For covers not specified in 3.3.1.1.1 thru 3.3.1.1.3, the material shall conform to CCC-C-419, type III, 12.29 ounces per square yard. The material shall be finished in accordance with CCC-D-950, type I, class B.3.3.1

25、.2 Type II: Unless otherwise specified (see 6.2), the material for type II covers shall conform to MIL-C-20696, type I, class 2. Warning streamers shall be the same as for type I.SAE INTERNATIONAL AS5778 Page 4 of 17_ 3.3.2 Thread: Unless otherwise specified, all thread used for sewing shall be in a

26、ccordance withA-A-52094, ticket No. 16, 4 ply, type II, and shall be the same color as the cover material.3.3.3 Metal fittings: Grommets, eyelets, and fasteners shall conform to the applicable service use.3.3.4 Webbing (type I): Unless otherwise specified, the webbing used for attaching the covers a

27、nd for all binding and reinforcement shall conform to MIL-W-5665, and shall be the same color as the cover material.3.3.5 Tie cord:Unless otherwise specified, the tie cord used for attaching covers and holding them in place shall be 1/4 inch rope conforming to MIL-R-17343.3.3.6 Twine:Unless otherwis

28、e specified, the twine used for wrapping ends of the tie cords shall conform to T-T-881.3.3.7 Mildew proofing :The cotton thread, webbing, and ropes used in engine covers shall be treated in accordance with MIL-M-46032, type I organic solvent dispersion method, except the permissible weight increase

29、 shall be 15 percent maximum and the metallic copper content shall be 0.3 0.1 percent by weight.3.3.8 Interlocking fasteners (type I) :Except as otherwise specified herein, interlocking slide fasteners shall conform to V-F-106, type IV, style No. 1 or 3, class B, size H, wire-stirrup pull, metal-zin

30、c alloy with natural finish, color 613 of FED-STD-595. An 18 1/2 inch fabric thong shall be looped through the wire-stirrup pull and shall be capable of withstanding a tension pull of at least 100pounds.3.4 Design and construction :The covers shall be so designed that when installed they will fit ne

31、atly and completely cover the part of the aircraft for which they are intended. The edges of the covers shall fit snugly to prevent ingress of driving rain, snow, or dust. The covers shall not contain any wrinkles or lines of stress concentration. The method of padding valleys on the edges of the co

32、vers shall be in accordance with figure I.3.4.1 Stretch loading :The covers, when installed, shall be adjustable to and capable of withstanding a stretch loading of not less than 2 pounds per inch of width in all directions.3.4.2 Seams and stitching :The seams and stitching used in the manufacture o

33、f covers shall be in accordance with FED-STD-751.3.4.2.1 Type I:All sewing shall be done with stitch type 301 to form a type LSc-2 seam with 3/4 inch gage. There shall be not less than four nor more than eight stitches per inch.3.4.2.2 Type II: All sewing shall be done with stitch type 401 to form a

34、 type LSc-2 seam with 3/4 inch gage. There shall be not less than four nor more than eight stitches per inch.SAE INTERNATIONAL AS5778 Page 5 of 17_ FIGURE 1. Method of padding valleys on edge of engine and cockpit covers.3.4.3 Hems:Covers shall have a hem 1-1/2 inches wide on all free edges. Each ed

35、ge of each hem shall have one row of stitching.3.4.4 Slits:Slits shall be provided for obstructions such as struts, stay wires, shafts, or other aircraft parts. Slits shall extend to the nearest free edge, unless another position is specified. Unless otherwise specified, the edges of each slit shall

36、 be closed by means of an interlocking fastener installed as shown on figure 2. Means for attaching and securing covers shall be accomplished by means of ties, straps, ropes or fasteners on the edge to permit fastening them around fuselage, wings, or some adjacent fittings. The hardware or fittings

37、used for securing the cover shall be padded and the padding permanently attached, by sewing around the periphery, to prevent contact with the aircraft skin.3.4.5 Patches:The covers shall be provided with reinforcement patches where they come in contact with sharp corners or projections.3.4.6 Engine

38、or transmission covers : The engine or transmission cover shall extend beyond the fire wall and the propeller or rotor hub. Typical designs are shown on figures 3 through 7.SAE INTERNATIONAL AS5778 Page 6 of 17_ FIGURE 2. Cover closure.FIGURE 3. Typical cover for air-cooled-engines (3-blade propelle

39、r)SAE INTERNATIONAL AS5778 Page 7 of 17_ FIGURE 4. Typical cover for air-cooled engine (2-blade propeller)FIGURE 5. Typical cover for liquid-cooled engines (3-blade propeller)SAE INTERNATIONAL AS5778 Page 8 of 17_ FIGURE 6. Typical cover for air-cooled engines (4-blade propeller)FIGURE 7. Typical no

40、se cover for jet aircraft engine.SAE INTERNATIONAL AS5778 Page 9 of 17_ 3.4.6.1 Fasteners: Engine covers around the nacelles shall be closed with interlocking fasteners as specified herein. The interlocking fastener shall be offset 5 1 from the vertical centerline of the engine.3.4.6.2 Sleeves for h

41、ot air duct : Two sleeves, each approximately 8 inches long and 13 inches in diameter, shall be attached to each engine cover to serve as a hot air duct when the free end of the sleeve is attached to a heater. One sleeve shall be so located as to coincide with the opening into the accessories compar

42、tment of the engine. The other sleeve shall be located at the nose section of the cowling. A piece of type I lightweight webbing conforming to MIL-W-5665, approximately 52 inches long and 1/2 inch wide, shall be sewn at the midpoint to each sleeve near its open end. The color of the webbing shall ap

43、proximately match the color of the cover.3.4.6.3 Sleeve for propeller or rotor blades : A sleeve approximately 10 inches long and of sufficient diameter to fit the propeller or rotor blade shall be attached to the engine or transmission cover for each propeller blade or rotor.3.4.6.4 Grommets:Plain

44、grommets conforming to MS20230 shall be placed on the underside of the cover to permit excess oil drainage.3.4.7 Propeller and rotor blade covers : The propeller and rotor blade covers shall match the respective engine cover propeller sleeves or rotor head cover blade sleeves. A typical design is sh

45、own on figure 8.FIGURE 8. Typical propeller and rotor blade coverSAE INTERNATIONAL AS5778 Page 10 of 17_ 3.4.8 Fuselage and armament covers : These covers shall be for the bombardier and pilot compartments, turrets, sight blisters, and all other gun openings.3.4.9 Miscellaneous covers : Covers for v

46、entilation duct openings, tail and nose wheel openings, landing gear wells, and any opening too large to be covered with 2-inch masking tape shall be provided, unless justification by the weapon system manufacturer can be substantiated that covers are not required.3.4.10 Snap Fasteners (type II):Junctions between cover components, shall be secured with snap fasteners as shown on figure 9.3.4.11 Fastening tapes :Fastening tapes conforming to MIL-F-21840, type II