(2)
Cargo and baggage compartments not occupied by crew or passengers :

(i)
Thermal and acousticinsulation(including coverings) usedin each cargo andbaggage compartment mustbe constructed of materials that meet the requirements setforthinparagraph(a)(1)(ii) ofPartI of thisAppendix.

(ii)
A cargo or baggage compartment de.ned in Sec. 25.857 as Class B or E must have a liner constructed of materials that meet the requirements of paragraph(a)(1)(ii) ofPartI ofthisAppendix and separatedfromthe airplanestructure(exceptfor attachments).In addition, suchliners must be subjected to the 45 degree angle test. The .ame may not penetrate (passthrough)thematerialduring applicationof the .ameorsubsequent to its removal. The average .ame time after removal of the .ame source may not exceed15 seconds,and the averageglowtime may notexceed10 seconds.

(iii) A cargo or baggage compartment de.ned in Sec. 25.857 as Class B, C, D, or E must have .oor panels constructed of materials which meet the requirementsofparagraph(a)(1)(ii) ofPartI of thisAppendix and which are separatedfromthe airplane structure(exceptfor attachments).Such panels must be subjected to the 45 degree angle test. The .ame may not penetrate(passthrough) thematerialduring applicationofthe .ameor subsequent to its removal. The average .ame time after removal of the .ame source may not exceed15 seconds, andthe averageglowtime may not exceed 10 seconds.
(iv) Insulationblankets and covers used toprotect cargo mustbe constructed of materialsthat meetthe requirements ofparagraph(a)(1)(ii) ofPart I of thisAppendix.Tiedown equipment(including containers,bins, and pallets)usedin each cargo andbaggage compartment mustbe constructed of materialsthat meetthe requirements ofparagraph(a)(1)(v) ofPartI of this Appendix.

(3)
Electrical system components : Insulation on electrical wire or cable installed in any area of the fuselage must be self-extinguishing when subjected to the 60 degree test speci.ed in Part I of this Appendix. The average burn length may not exceed3inches,and theaverage .ametimeafterremoval of the .ame source may not exceed 30 seconds. Drippings from the test specimen may not continue to .ame for more than an average of 3 seconds after falling.

(b)
Test Procedures :

(1)
Conditioning : Specimens must be conditioned to 70±5F., and at50percent ±5 percent relative humidity until moisture equilibrium is reached or for 24 hours. Each specimen must remain in the conditioning environment until it is subjected to the .ame.

(2)
Specimen con.guration. Except for small parts and electrical wire and cable insulation, materials must be tested either as a section cut from a fabricated partasinstalledin the airplane or as a specimen simulating a cut section, such asaspecimencutfroma .at sheet of thematerial oramodel of thefabricated part.The specimen may be cutfrom any locationin afabricatedpart; howe-ver, fabricated units, such as sandwich panels, may not be separated for test. Except as noted below, the specimen thickness must be no thicker than the minimum thickness to be quali.ed for use in the airplane. Test specimens of

′
Elodie Roux. Septembre 2003
Appendix F
thick foamparts, such as seat cushions, must be
-inch in thickness.Test spe-cimens of materials that must meet the requirements ofparagraph(a)(1)(v) of Part I of this Appendix must be no more than 1/8-inch in thickness. Elec-trical wire and cable specimens must be the same size as used in the airplane. In the case of fabrics, both the warp and .ll direction of the weave must be tested to determine the most critical .ammability condition. Specimens must be mounted in a metal frame so that the two long edges and the upper edge areheld securelyduringthe verticaltestprescribedin subparagraph(4) of this paragraph and the two long edges and the edge away from the .ame are held securelyduring thehorizontal testprescribedin subparagraph(5) of this paragraph. The exposed area of the specimen must be at least 2 inches wide and 12 inches long, unless the actual size used in the airplane is smaller. The edge to which the burner .ame is applied must not consist of the .nished or protected edge of the specimen but must be representative of the actual cross-sectionof the material orpart asinstalledintheairplane.Thespecimen mustbe mountedinametalframesothat allfouredgesareheld securely and
　
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本文鏈接地址：FAA規(guī)章 美國聯邦航空規(guī)章 Federal Aviation Regulations 4(48)