′
Elodie Roux. Septembre 2003
Appendix F
FAR25.F3 :[AppendixF–PartIII–TestMethod toDetermineFlamePene-tration Resistance of Cargo Compartment Liners.]
(a)
[Criteria for Acceptance.
(1)
At least three specimens of cargo compartment sidewall or ceiling liner panels must be tested.
(2)
Eachspecimen tested must stimulate the cargo compartment sidewall or ceiling linerpanel,including anydesignfeatures, such asjoints,lamp assemblies, etc., the failure of which would a.ect the capability of the liner to safety contains a .re.
(3)
There must be no .ame penetration of any specimen within 5 minutes after applicationofthe .amesource, andthepeaktemperaturemeasured at4inches above the upper surface of the horizontal test sample must not exceed 400'F.
(b)
Summary of Method. This method provides a laboratory test procedure for measu-ringthecapability of cargocompartmentlining materialstoresist .amepenetration with a2gallonperhour(GPH)#2Gradekeroseneorequivalentburner .resource. Ceilingand sidewalllinerpanels maybe testedindividuallyprovided aba.eis used to simulate the missing panel. Any specimen that passes the test as a ceiling liner panel may be used as a sidewall liner panel.
(c)
Test Specimens.
1818
(1) The specimentobetested must measure16±inches(406±3mm)by 24±
inches(610±mm).
(2) The specimens must be conditioned at 70'F. ± 5'F.(21'C. ± 2'C.) and 55% ± 5% humidity for at least 24 hours before testing.
(d) Test Apparatus. The arrangement of the test apparatus, which is shown in Figure 3 of Part II and Figure 1 through 3 of this Part of Appendix F, must include the components described in this section. Minor details of the apparatus may vary, depending on the model of the burner used.
(1)
Specimen Mounting Stand.The mounting standfor the test specimens consists of steel angles as shown in Figure 1.
(2)
Test Burner. The burner to be used in testing must–
(i)
Be a modi.ed gun type.
(ii)
Use a suitable nozzle and maintain fuel pressure to yield a 2 GPH fuel .ow.Forexample: an80degreenozzlenominally rated at2.25GPH and operated at85poundsper squareinch(PSI) gagetodeliver2.03GPH.
(iii) Havea12inch(305 mm) burner extensioninstalled atthe end ofthe drafttube with an opening6inches(152mm) high and11inches(280 mm) wide as shown in Figure 3 of Part II of this Appendix.
(iv) Have aburnerfuelpressure regulatorthatis adjustedtodeliver a nominal
2.0 GPH of #2 Grade kerosene or equivalent. Burner models whichhavebeen used successfullyin testing are theLenoxMo-delOB-32,CarlinModel200CRD andparkModelDPL.Thebasicburneris described in FAA PowerplantEngineeringReportNo. 3A, StandardFire Test Apparatus and Procedures for Flexible Hose Assemblies, dated March 1978;
however, the test setting speci.ed in this Appendix di.er in some instances from those speci.ed in the report.
(3) Calorimeter.
(i) The calorimeter to be used in testing must be a total heat .ux Foil Type Gardon Gage of an appropriate range (approximately 0 to 15.0 British thermal unit (BTU) per ft.2sec., 0-17.0 watts/cm2). The calorimeter must be mounted in a 6 inch by 12 inch (152 by 305 mm) by 3 inch
4
(19 mm) thick insulating block which is attached to a steel angle bra-cket for placement in the test stand during burner calibration as shown in Figure 2 of the Part of this Appendix.
(ii) The insulating block must be monitored for deterioration and the moun-ting shimmed as necessary to ensure that the calorimeter face is parallel to the exit plane of the test burner cone.
1
(4) Thermocouples. The seven thermocouples to be used for testing must be
16
inch ceramic sheathed, type K, grounded thermocouples with a nominal 30 American wiregage(AWG) size conductor.The seven thermocouples must be attached to a steel angle bracket to form a thermocouple rake for placement in the stand during burner calibration as shown in Figure 3 of this Part of this Appendix.
中國(guó)航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 4(52)
