ASTM D4054-1993(2003) Standard Practice for Evaluating the Compatibility of Additives with Aviation-Turbine Fuels and Aircraft Fuel System Materials《添加剂与航空涡轮机燃料和飞机燃烧体系材料相容性评价的标准实施规.pdf

《ASTM D4054-1993(2003) Standard Practice for Evaluating the Compatibility of Additives with Aviation-Turbine Fuels and Aircraft Fuel System Materials《添加剂与航空涡轮机燃料和飞机燃烧体系材料相容性评价的标准实施规.pdf》由会员分享，可在线阅读，更多相关《ASTM D4054-1993(2003) Standard Practice for Evaluating the Compatibility of Additives with Aviation-Turbine Fuels and Aircraft Fuel System Materials《添加剂与航空涡轮机燃料和飞机燃烧体系材料相容性评价的标准实施规.pdf（3页珍藏版）》请在麦多课文档分享上搜索。

1、Designation: D 4054 93 (Reapproved 2003)An American National StandardStandard Practice forEvaluating the Compatibility of Additives with Aviation-Turbine Fuels and Aircraft Fuel System Materials1This standard is issued under the fixed designation D 4054; the number immediately following the designat

2、ion indicates the year oforiginal adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 This practice covers procedures r

3、equired to determinethe compatibility of additives proposed for aviation turbinefuels with both standardized fuels and the materials commonlyused in commercial aircraft fuel system construction.1.2 Satisfactory evidence of compatibility using this prac-tice is required by the ASTM Guidelines for Add

4、itive Approval(Research Report D02-1125)2for additives specified in Speci-fication D 1655 and also by individual aircraft and enginemanufacturers as well as government agencies.1.3 Compatibility data resulting from these procedures rep-resent only part of the performance information required foraddi

5、tive approval.1.4 The actual level of acceptance is established by theindividual approving groups.1.5 While efforts are made to maintain the list of fuel systemmaterials to be tested and to keep it current, users of thispractice must recognize that these lists are subject to continu-ing revision to

6、meet the needs of equipment manufacturers.1.6 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulator

7、y limitations prior to use.2. Referenced Documents2.1 ASTM Standards:D 156 Test Method for Saybolt Color of Petroleum Prod-ucts (Saybolt Chromometer Method)3D 1266 Test Method for Sulfur in Petroleum Products(Lamp Method)3D 1655 Specification for Aviation Turbine Fuels3D 2624 Test Methods for Electr

8、ical Conductivity of Avia-tion and Distillate Fuels Containing a Static DissipatorAdditive3D 3227 Test Method for (Thiol Mercaptan) Sulfur in Gaso-line, Kerosine, Aviation Turbine, and Distillate Fuels(Potentiometric Method)3D 3602 Field Test Method for Water Separation Character-istics of Aviation

9、Turbine Fuels4D 3948 Test Methods for Determining Water SeparationCharacteristics of Aviation Turbine Fuels by PortableSeparometer5D 4308 Test Method for Electrical Conductivity of LiquidHydrocarbons by Precision Meter5D 4952 Test Method for Qualitative Analysis of ActiveSulfur Species in Fuels and

10、Solvents (Doctor Test)53. Summary of Practice3.1 These procedures are laboratory techniques for estab-lishing additive compatibility with commercial aviation turbinefuels, with additives previously approved in standard fuels andwith the fuel system components used in commercial aircraft,including ta

11、nk coatings, sealants, and elastomers. Tests areconducted with Jet A/A-1 fuel at four times the maximumadditive concentration as recommended by the additive sup-plier. Immersion tests, with fuel system components only, areconducted in the more severe Reference Test Fluids, TT-S-735,Types III and VII

12、. The time and temperature of immersion testsare representative of aircraft use conditions and immersedcomponents are evaluated after exposure, using industry stan-dard methods. Comparisons are made with representativecomponents exposed to the base fluid with and withoutadditive.NOTE 1Data obtained

13、with Jet A/A-1 fuels can be applicable to Jet Bfuel or to aviation fuels specified by other organizations, with theagreement of the approving air frame/engine manufacturer.4. Significance and Use4.1 Additives are generally used to enhance a fuel propertysuch as oxidation stability or to improve fuel

14、 performance byproviding corrosion inhibition, protection against icing, metaldeactivation, and so forth. However, their use can adverselyaffect other fuel properties or the ground-handling systems for1This practice is under the jurisdiction of ASTM Committee D02 on PetroleumProducts and Lubricants

15、and is the direct responsibility of Subcommittee D02.J0 onAviation Fuels.Current edition approved June 10, 2003. Published August 2003. Originallyapproved in 1981. Last previous edition approved in 1998 as D 405493 (1998).2Supporting data have been filed at ASTM International Headquarters and maybe

16、obtained by requesting Research Reports RR:D02-1125 and D02-1137.3Annual Book of ASTM Standards, Vol 05.01.4Discontinued. See 1994 Annual Book of ASTM Standards, Vol 05.02.5Annual Book of ASTM Standards, Vol 05.02.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken,

17、PA 19428-2959, United States.fuels. Application of the procedures of this practice is intendedto disclose these adverse effects.4.2 Combinations of additives may exhibit antagonisticeffects on fuel properties or performance. Compatibility testingwith previously approved additives is intended to disc

18、lose suchantagonistic effects of incompatibilities.4.3 Fuel system components such as sealants, coatings, andelastomers are normally selected because of their resistance toa Reference Test Fluid, which is designed to be more severe tocomponents than standard fuels. Application of the proceduresof th

19、is practice is intended to disclose adverse effects ofadditives beyond the effects of the Reference Test Fluids.5. Procedure AAdditive Effects on Fuel5.1 Base Fuel required for Procedures A and B must meetthe Jet A or Jet A-1 requirements of Specification D 1655 andbe clay treated in accordance with

20、 the procedure of TestMethod D 3948, Appendix X1, “Preparation of ReferenceFluid Base.” It should exhibit a rating of 98 WSIM after claytreating by Test Methods D 3602 or D 3948. About 75 L (20gal) of base fuel is required for Procedures A and B. Store thebase fuel in clean epoxy-coated metal contai

21、ners and recheckthe WSIM rating after three months of storage.5.2 Prepare the test fuel by blending four times the maxi-mum recommended concentration of the additive into 38 L (10gal) of base fuel.NOTE 2If the maximum solubility level is below this concentration,prepare the test fuel accordingly.5.3

22、 All ASTM D 1655 specification tests and the followingadditional tests, should be run on the base fuel and the test fuel:D 3602 or D 3948 water separationD 2624 electrical conductivityD 156 Saybolt color bright and clear-visual inspection5.4 If tests on test fuel exceed the limits of D 1655, rerun a

23、second test fuel containing only the maximum recommendedconcentration of additive in accordance with 5.3 and report.6. Procedure BAdditive Compatibility with OtherAdditives6.1 Prepare duplicate test blends by mixing 100 mL of basefuel containing four times the maximum recommended con-centration of t

24、he candidate additive to 100 mL of base fuelcontaining, in turn, each of the previously approved additives(other than oxidation inhibitors) at four times their maximumrecommended concentrations. The resultant blend contains twotimes the maximum recommended concentration of eachadditive.NOTE 3Approve

25、d additives are listed in Specification D 1655 butProcedure B may also be applied to additives approved for aviation fuelsby other organizations.6.2 Divide each of the mixtures described in 6.1 into twoclear, tall glass containers (100 mL each). Put the duplicatesamples into dark, cold storage at 17

26、.8C (0F) for 24 h.Inspect immediately after removal from cold storage, forindications of precipitation, cloudiness, darkening, or othervisual evidence of incompatibility.6.3 Warm the samples inspected from cold storage, shake toremix any separated components, and hold at 38C (100F) for24 h. Inspect

27、them again for visual evidence of incompatibilityimmediately after cooling to room temperature. Keep fuelsamples in dark storage during conditioning and betweeninspections.NOTE 4Photographs are a useful record of results of compatibilitytesting.7. Procedure CAdditive Compatibility with FuelSystem Co

28、mponents7.1 Formulate the jet reference liquid required for conduct-ing fluid immersion tests as follows:Jet Reference Fluid, TT-S-735, Type IIIToluene (TT-T-548) 30 VolumesIsooctane (TT-S-735, Type I or ASTMReference Grade)70 VolumesJet Reference Fluid, TT-S 735, Type VIIToluene (TT-T-548) 30 volum

29、esCyclohexane (D 3055 or technicalgrade)60 volumesIsooctane (TT-S-735, Type I or ASTMReference Grade)10 volumesDitertiary butyl disulfideA1 volumeTertiary butyl mercaptan 0.015 6 0.0015weight % ofother four componentsAThe ditertiary dibutyl disulfide shall be doctor sweet in accordance with theDocto

30、r Test in Test Method D 4952.7.1.1 When tested for mercaptan and total sulfur in accor-dance with Test Methods D 3227 and D 1266, respectively, thereference fluid shall have the following properties:Mercaptan sulfur content, 0.0050 6 0.0005 weight % (1)Total sulfur content, 0.400 6 0.005 weight % (2

31、)Store the fluid out of contact with light in containers that areinert to the fluid ingredients. (Welded aluminum, nongalva-nized welded steel, or glass containers are suitable.) If not usedwithin 90 days after blending, retest the fluid for mercaptan andtotal sulfur content.7.2 Prepare reference te

32、st fluids by blending four times themaximum recommended concentration of the additive into thespecified Jet Reference Fluid.7.3 Fuel system materials subject to immersion tests in JetReference Fluid and in Reference Test Fluid are listed in Table1.7.4 Detailed testing procedures for each class of fu

33、el systemcomponents appear in Research Report D02-11372on file atASTM Headquarters. When conducted by an approved labo-ratory,6these testing procedures provide data acceptable toaircraft manufacturers or other approving agencies.7.5 In general, each fuel system material is subject to specialapplicat

34、ion and curing techniques and then each test specimenis immersed in both the specified Jet Reference Fluid andReference Test Fluid containing additive for varying times atspecified temperatures. These details as well as the techniquesfor inspecting specimens for failure are described in ResearchRepo

35、rt D02-1137.26An approved laboratory is Boeing Technology Services, Box 3707, Seattle, WA98124.D 4054 93 (2003)28. Report8.1 Laboratory results from Procedures A, B, and C shouldbe compiled and reported as evidence of additive compatibility.9. Keywords9.1 additives; aviation fuel additives; compatib

36、ility; fuelsystemASTM International takes no position respecting the validity of any patent rights asserted in connection with any item mentionedin this standard. Users of this standard are expressly advised that determination of the validity of any such patent rights, and the riskof infringement of

37、 such rights, are entirely their own responsibility.This standard is subject to revision at any time by the responsible technical committee and must be reviewed every five years andif not revised, either reapproved or withdrawn. Your comments are invited either for revision of this standard or for a

38、dditional standardsand should be addressed to ASTM International Headquarters. Your comments will receive careful consideration at a meeting of theresponsible technical committee, which you may attend. If you feel that your comments have not received a fair hearing you shouldmake your views known to

39、 the ASTM Committee on Standards, at the address shown below.This standard is copyrighted by ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,United States. Individual reprints (single or multiple copies) of this standard may be obtained by contacting ASTM at

40、the aboveaddress or at 610-832-9585 (phone), 610-832-9555 (fax), or serviceastm.org (e-mail); or through the ASTM website(www.astm.org).TABLE 1 Aircraft Fuel System ComponentsA(a) Integral Fuel Tank Sealants:Polysulfide, manganese cured, MIL-S-8802 (PR 1440 and Pro Seal 890)Polysulfide, chromate cur

41、ed, MIL-S-8802 (PR1422)(b) Integral Fuel Tank Coatings:Amine cured epoxyBPolyurethane, MIL-C-27725, Type II (PR1560M)Buna 8A/8N, MIL-S-4383 (EC776SR)(c) Integral Fuel Tank Substrates (Metals):Aluminum 7075-T6 bare, QQ-A-250/127075-T6 chromic acid anodized per MIL-A-86257075-T6 alodined per MIL-C-554

42、1, Class 1A (Alodine 1200 or Iridite 14)Titanium (6AL-4V) AMS 4967/MIL-T-9046, Type III, Comp C.Steel (4130), cadmium plated per QQ-P-416, Class 2, Type II(d) Elastomers:Nitrile, Buna 8N, MIL-R-6855, Class I, Grade 70Fluorosilicone, MIL-R-25988, Class I, Grade 60Fluorocarbon, MIL-R-83248, Type II, C

43、lass 1, Grade 75(e) Bladder Cells:Polyurethane, Vithane, Goodyear BTC-69 (compound No. 80C29)Polyurethane, Vithane, Goodyear BTC-86 (compound No. 82C39)AThis list of materials to be tested has not been revised since 1981; anup-to-date list is being developed.BSuitable materials are identified in RR:D02-1137.2D 4054 93 (2003)3