NAVY MIL-F-17874 B-1965 FUEL SYSTEMS AIRCRAFT INSTALLATION AND TEST OF《飞机燃油系统的安装与测试》.pdf
《NAVY MIL-F-17874 B-1965 FUEL SYSTEMS AIRCRAFT INSTALLATION AND TEST OF《飞机燃油系统的安装与测试》.pdf》由会员分享,可在线阅读,更多相关《NAVY MIL-F-17874 B-1965 FUEL SYSTEMS AIRCRAFT INSTALLATION AND TEST OF《飞机燃油系统的安装与测试》.pdf(34页珍藏版)》请在麦多课文档分享上搜索。
1、NIILFF-17874B20 AUGUST 1965SUPEKSEOIAGMIL-F-I 7874A (WEP)3 mnnumy 1960IMILITARY SPECIFICATIONFUELSYSTEMS:AIRCRAFT,NSTALLATIONmTD TESTOFThis CPccbfcdon w mandatoru Jor I npprern, in this instance mny begranted subject to satisfactory completion ofsuch qualification tests.3.1 .1.? Nmrstanekmf crnnporm
2、ta. Compo-nents in this category will be considered thosewhich do not apply under n specific Gover-nment scificntion or drawing but which arecommercially nvnilable. Approval may begranted on the basis of prior satisfactoryserrice experience and subject to satisfactoryservice in the pnrticulnr applic
3、ation.3.1.1.3 Actu dcvefepmcnt componcnb. Com-ponents in this cntegory will genemlly beconsidered those which must be designed forthe specific airwnft application. Those com-ponents will require the submission by thenireraft manufacturer of deteiled procure-ment speciticntions and envelope drawings
4、inaccordance with Mlf-7032727 for release bythe Government. Procurement specificationsshrill be bnsed upon the npplicnble require-ments of MIL-F-S615, nnd slmll be prepnredin nccordsnce with the nppendix thereto.3.1.2 Component# installation. All eompe-nents shrill be designed to permit ense ofinsta
5、tlnt.ion and removof. Components requir-ing frequent servicing shrdl be installed so esto be eusily accessible, Quick-opening nccessMIL-F-17874Bdoers in the nircrnft skin shell be providedwhere necessnry.3.2 Mnterinfs All mnterinls shrill be suit-nble for the purpese intended. Magnesiumparts shrill
6、not be used in the fuel system.3.3 Design and construction.3.3.1 FUCL The fuel system for recipmcnt-ing engine nircmft shrill be suitable for usewith al) grndes of fuel conforming ventoutlets of aircmft not capable of prolongedoperation in icing shall not be more criticalto ice accumulation than the
7、 baeic airplane(primarily the airplane tlight surfaces), InMIL-F-17874Bbaat type seaplanes and amphibians, all fueltz.nk vents shall terminate above the maxi-mum gross weight water line and shall prevent sea water spiny during takeoff and land-ing from entering the vent system. Ventssems shall conta
8、in no tmps or IOWpointswhtch may collect condeneote which uldfreeze. unless the traps are completelyrlmincd. For aviation gas fueled aircraft,vents shall be so designed thnt the vaporwithin the tnnks is nOt diluted .ith air tObring it toward the lenn mixture range, ex-cept as required to prevent tnn
9、k collapse.3.3.7.1 Eztrcmo f ucl lempmm!um venting.In addition to design of tank vents for reduc-tion of fuel loss at altitude, the vents shallprovide adequate venting or pressure reliefconsistent with tank strength and structuralintegrity under extreme hot fuel conditions.Temperatures shall bo as s
10、pecified in the aiPcraft model specification.3.3.7.2 Vent monitorin sstcna. All aircraftutilizing pressure fueling systems shrdl in-clude provisions for monitoring vent systimor fuel cell pressure during ground refuelingoperations. The system to measure and dis-play this pressure shall require the s
11、pecific.npnmvnl Of the procuring activity.:1.3.7.3 Vent line uisc. Vent line sizes shallbe consistent with climbing, diving, fueling,and defueling requirements. To prevent over-presmrization in the event of failure of afueling control component, tent lines shall becapable of flowing the fuel flow ra
12、te of thelargest refueling shutoff vntve in the fuelsystem nnd the venting air flow requirernentaof the remaining tank(s).3.3.8 Futl fo.w at aliifuffc. A fuel tank pres-sure system shall be provided where neces-sary to prevent fuel loss due to vaporization,fo,nming, or tilling. The nssximum combined
13、fuel loss, for these conditions shall not exceed2 percent, by weight, of the total fuel capsc-ity for any one fueling for jet fuels and 6pement for aviation gas. Where provisiona7Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-iWL- more extremelocati
14、ons will depend upon filler adapter ori-entation and shall require procuring activityapproval prior to adoption. Additional pree-sure fueling/defueling connections, or otherucceseible qw-turss, shall be installed SUIthat the uircreft can bs readily defueledthrough the unit (s) in case of a whee15uPl
15、anding without lifting the aircraft. Forcarrier-based aircraft, particular considera-tion shall be given to access while the sir-cmft is parked close to the edge of the deckand with wings folded. For seapl.znes, theadapters shall be located at one fueling eta-tion, m close to the bow ae practical bu
16、t notmore than 40 feet aft of the bow, located forreceiving, handling and operatiOn Of nOzzlesby personnel within the seaplane at sea andASO located for convenient fueling, whiledocked, by an operation standing along side.The mounting alignment of the adaptirs shallbe with respect to normal approach
17、 with thefueling nozzle. Adjacent location of adaptemshall provide adequate clearance for multiplecoupling of M1N5877 nozzles in sequence(minimum spacing of 15 inches between cen-ters for side-by-side mounting). The numberof pressure fueling adapters shall be as re-quired to satisfy the fueling and
18、defuelingtimes in table V for the various types of air-craft: All pressure fueling adapters shall bebonded to aircraft structure, in accordancewith MIL-B-5087. Grounding jacks shall heprovided at every tank or fuel cell filler open-ing for grounding the pressure and gravityfueling nozzles to the air
19、craft. All pressurefuel filler units which are recessed behindaccess dorms shall incorporate positive provi-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IIIII1,IIIsions whereby the access doom may not bephysically secured unless the safety cap isp
20、roperly installed. Conventional, 3-inch nom-inal diameter, tiller units consisting of MIL.-C-8605 pressure fueling adapter safety capsand adapters conforming to the bayonet lock-ing design detail of MS29514 shall be used.Unless specifically authorized, al! filler unitsshall be seated to the exterior
21、 o/ the m“rcmftto prevent the entrance of fuel c.r fuel vaporsinto the interior parts of the nircmft.3.3.9.3.2 Moximum ftwlisssj prcwsum. Thepressure fueling system rmd each individualtank to be fueled, shall be capable of receiv.ing fuel without arlveme effect upon the air-cmft from ench of the fue
22、ling facilities listedin footnote 1 to fig-ores 7, 8. nnd 9 for allnircmfL Maximum fueling pressure shall notexceed 55 psig for any flow mte and the max-imum surge for any shutoff condition shallnot exceed 120 psig, unless it can be showsthat a 180-peig surge limit cnn he safelyutilized without an i
23、ncrense in weight overthe 120-peig system.%3.9.3.3 Fuc Imml control. The aircraftpressure fueling system shall provide, withinthe aircmft, for nutamatic control of fuellevel to design capacity or capacities and forautomatic fueling flow shutoff for safety oftanks nnrl nircmft when fueling nt any mte
24、up tn the mnximum mte provided by 3.3.9.1.Where any single comnent, subcomponent,or msxilirmy system failure mny result infailure to shut off the fueling flow. rvithattenrhust possible rupturt of tanks nnd aircroft structure. or fnilure to tmnsfer fuel tothe feedtnnk, n secondnry system of shutoffin
- 1.请仔细阅读文档,确保文档完整性,对于不预览、不比对内容而直接下载带来的问题本站不予受理。
- 2.下载的文档,不会出现我们的网址水印。
- 3、该文档所得收入(下载+内容+预览)归上传者、原创作者;如果您是本文档原作者,请点此认领!既往收益都归您。
下载文档到电脑,查找使用更方便
10000 积分 0人已下载
下载 | 加入VIP,交流精品资源 |
- 配套讲稿:
如PPT文件的首页显示word图标,表示该PPT已包含配套word讲稿。双击word图标可打开word文档。
- 特殊限制:
部分文档作品中含有的国旗、国徽等图片,仅作为作品整体效果示例展示,禁止商用。设计者仅对作品中独创性部分享有著作权。
- 关 键 词:
- NAVYMILF17874B1965FUELSYSTEMSAIRCRAFTINSTALLATIONANDTESTOF 飞机 燃油 系统 安装 测试 PDF

链接地址:http://www.mydoc123.com/p-979093.html