NAVY MIL-O-19838-1956 OIL SYSTEMS AIRCRAFT INSTALLATION AND TEST OF《飞机加油系统的安装和测试》.pdf

1、MIE.0.19838 (Am) 12 hcember 1956 MIUTARY SPECIFICATION AM, TEST OF On SYSIDSX AIRCRAFT, INSThWITON This specification has been approved by the Bureau of Aeronautics, Department of the Navy 1. SCOPE . 1.1 scope: This specification cooera the general. requirements for design, functional operation, ins

2、tallation, and testing of oil systems for piloted aircraft, target drones arid guidad missiles, ond shall be followed except a3 othervise suthoriwd by the Bureau of Aeronautics for each design. 1.2 Classification; This is a performance specification. 2. JltPLICABLE, DOCUMENTS 2.1 The following speci

3、fications, publications, and drawings of the issue ia effect- on the date of invttation for bids, fonn a part of this specification. SPECIFICATIONS: MIL-T-5579 MI L-H-5 593 MITCV-5636 MILG5637(Aso) MIL-T-6396(ASO) Mn-G8678(AER) MIL-D-8706(AER) 1tF-1787k ( AER) MIL-S-7742 MIL-1-18802 (AER) MIL-W-25i1

4、iO(ASG) MIL-F-5577 mmos MIL-C-724fl(ASG) Tanks; Self-Sealing Oil, Aimraft Hoso; Aircraft, Low-Pressure, Flexible Coolers, Lubricatm Oil, Aircraft, Tubular Valves; Oil Cooler (Temperatwo Regulating with Surge Protection) Tanks, Fuel, Oil, Water-Alcohol, Coolant Fluid Aircraft, Non- Self-Sealing, remo

5、vable Cooling Requirements of Power Plant Installations Data, Design; Contract Requirements for Aircraft Fuel Systems; ficraft, Installation and Test of Screw Threads, Standard, Aeronautical Installation of Fuel arsi OU Lines and Cannections in Kaval Aircraft Weight and Balance Centro1 Data (for air

6、planes and Rotorcraft) Cap and Adapter Unit, Tank Filler Fittings; Self-Sealing and Bladder Type Tank, Aircraft AN4103 MU24 ANIi125 E28034 AN10056 Fitting EM, Standard Bimsnsions for Floped Tubo Connection . Valvedg Cmler Temperature Regulating with Surge Protection Coder-Lubricathg Oil, Aircraft Tu

7、bular, Elliptical Cooler-Lubricating Oil, Aircraft Tubular, Round and Gasket Seal . Bulbs, Temperatuire, Electrical Rosistenco (-7OOC to +30O0C) PUBLICATIONS Air Force-Navy Aeronautical !3Lletins Specifications and Standards, use of Valve, Oil Dilution and Separatey Mounted PrimFng SoleEoid Provided

8、 by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-KLL- Q.19838 er) -i Bureau of Aeronautics TecMcal Order No. 37-54 Application hnd Instructions for use of Mrcraft and meine Lubricating OiL be 1957 rcplacanent T.O. if avail.) (When requesting specifications, p

9、ublications and drawinr-s refer to both “uitle and numberr Copies of this specification and applicable specif ications nay be obtained upon application to the Cornanding Officer, Naval Aviation Supply Depot, Philadelphia li, Pennsylvania, Attentionr Code ODFT) 2.2 OTHER PUBLICATONS: The following do

10、cumenta form a part of this specification unla8 othoruiee irdicated, the issue in effect on date of invitation for bids shall apply, National Advisory Committee for Aeronautics Report T.N. 3182 - Manual of the International Civil Aviation Organization (5CAO) Standard Atrasphere. (Copio8 of this publ

11、ication may be obtained fran the Research Information Division, National Advisory Conunittee for Aeronautics, i512 H. Street K.W., Washington, D. C,). 3. REQUIREI?ENTS 3.1 COHPQIIEGTS; The approval and installation of components under the requirements ofthis specification applies to functional compo

12、nents as distinl;uished from such other components as lines, fittings, tanks and associatod coaponcnts. Functional components Ku1 eno orally include the follcwingr Valves, filters, finer units, filler caps, oil coolers, pressure regdiators, and oil tank pressure control unite. 3.1.1 CO:.SONEKTC AFPT

13、IOYAL: All functional coniponents enployed In the oil system shall bo or approved types and shall have passed the qualification test3 required in the applicab1.e specifications. A list of all functiond components chal be submitted to the Bureau of Aeronautics, under the requtrements of this specific

14、ation and spsci- fication MiL-D-8706(AGR), for review and approval prior to procurerruit of these com- ponents by tho contractor, identifmg data, including the following a8 applicable, Components Usted for approval shail include sufficient a, Nmo of Component be Vendors P/N and/or drawing number C.

15、Applicable Oovernmcnt Specifications and Drawings (and deviations, if any d. Present Qualification or A:proval Status er Mrcraft Manufacturerta Drawings and P/N f, Aircraft Menufactureris Procurcncnt Specification 3.1.1.1 STA3X2. CCX.lrOEiEKTCr Components in this category are those which are covered

16、 by applicable Qualified Products List, Government Specifications, and drawings. conganents which aro listed on an applicable Cionciito Milch wo not U approval In this instmca mny bo granted subject to satisfactory completion of such qualification test8. 3.1.1.2 CTANDLW coilPO:,Xll Components in thi

17、s catecory WU be considered those which do not apply undor a specific Government mocification or drawing but wuch are comercially available. Approval may be granted on the basis of prior aatiofnctory service exprience and subject to eatisfactory service in the particulor application# Those Those com

18、ponents currently undergoing Government - I. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-wable oil capacity reqiiire by the detau specification. a

19、ssemblies capable of enduring a 2WF flsare for five minutes without leakage. Protective sleevoer sholl be providod to Tire roof the lhas. Installation of these lines shall be in accordance with -eon(mf. 3.4.2.1 PFtOPD FEATHE3EK3 LIhEs: Propeller fluid lines shall be approved flexible 3.4.3 EXPANSION

20、 AND FO/Ltlm:G SACZ space see paragraph 3,17),- 3,4,3.2r1 TIJ%B-JGT ENGINES: Expansion aem downstream of the auxiliary fuel pump or booster pump subject to the requiremsnts of paragraph 3.707 above. inlet line between the oil tank and the engine. shall be located as far from the engine oil pressure

21、pump as practicable In order to nsuro thorou1:h rnixinl: of the diluent and oil. prior to enterin: tho enqine. with a #43 (bOWOlt resljriction shall be located in the dilution line at the point where the diluent is obtained, 3.7,9.2 The diluent shaL1 be added to the lubricating OU system in the engi

22、ne oil The point where the diluent is added 3.t1410 Restric5or FiCtirq .I Fxcopt whore otherwise spacifed, a auitnbla fitting I 88 close 88 practicable to the restrictor fitting, 507.12 Manual Shut-Off Vaive. 3r7.12rl A manual shutyoff valve of approved type shall be mounted in the oil dilution line

23、s at the point where the diluent is added to the oil The purpose of this shut-off valve is to isolate the dilution line and obviate the following hazardar I 5 1. Loss of oil pressure due to failure or puncture of the line between the I dilution oolenoid and the oil inlet line, with consequent lose o

24、f engine oil pump 2. Excessive dilution resulting from possible leakage through the clilution solenoide 3,765242 The manual shut-off valve ohall be so located na to be convenient for operation before and after dilution. The locations of the dilution solenoid valve and the manual shut-off valve may b

25、e exchanged if this exchange will make the shut-off valve more cofivenient for operhtion. However, the solenoid and manual valves shall be at opposite extremities of tiilo dilution line. be included to.divert the flow of oil into the warm-cp compartment of the 012 tank durin: dilutid regardless of t

26、he oil, teniperature. The type, location, and arran6h required for normal operation of the auxiliary fuel pump. 3.8 Tho identical oil dilu%iom system to be used in pyoduction aircraft shell be hstd.14 in an exparimental airplane and toated. jdl accordance with applicablr) sub- paragraphs of paragrap

27、h b below. compartments and diverter valve installations are required if the circulation time based on normaj. mission oil capacity divided by noml sated power engine-oil-flow-rate, as epecified j.n the engine specification, exceeds 1 minute and 2 minutes for land-based airplanes. above, the capacit

28、y shall be approximately equal 30 one-tenth of engine-oil-flow-rete at normal rated power, as specified in the engine specification, plus 2 gallons. up compartments and divertor valve provisions may be incorporated in smaller tanks to minimize oil dilution expansion space requirements under the prov

29、isions of. paragraph 3.9 up PROVISION (RECIROCATNO ENGINES): warm-up provjsions in the firm sf for carrier-based airplanes If a warm-up coxpartment is required by the Warm- 3.4.3.1. : Wm-up prcwisions for turbo-prop 3.U. SIUT-OFF VALVE ANI CONTROL (IXJLTI-HIGIE!E AEIPLANES) : Oil shuboff valves shal

30、l be provided for each engine of all multi-engine airplanes. Frovision shall be made in rnulti-er?Ci Ilhe expansion and foaming space requiremnts of paragragh 3mze representative of reasonable ta:,k desim and lubricating system characteristics, Deaeration provisions may be incorporated with a reduct

31、ion of the foam space reciuirments of paragraph 3.4.3.1. and/or increase in fom space shall be izovidcsl as necessary to prevent excessive tank pressures or overboard discharge of oil dw to the engine foanw characteristics or compromise of tank design characteristics. 3.15 SJT , AIWL.Z;ES) t l;ines

32、for transferring make-up oil. from a control location to service oil tanks of each engine, tho total capacity of usable oil may be reduced to one thirty-fifth (by volume) of maximm ferry or overload fuel capacity except that the usable oil capcity of the enaine asmice tanks shall be not less than on

33、e twenty-fifth (by volune) of norinal mission fuel load, When make-up oil is carried in stored containers, an auxiliary make-up oil tank is not required, Tno oil transfer syston shaU be capab10 of satisfactory oporation at flight ambient air terneratures of -65%. 3.18 Off; QUAEILZTY GkCGNGt Multi-en

34、gine Patrol, Utility, and Transport class airplanes shall be equipped iith an oil nuantity :GE OIL C!iRATKX!l (RECIPROCkTIHG ENGINES ONLY); Scavenge oil strainer 4.1 5nl:PCING: Not applicable. 4.2 ItiSPICTIOti: Not aplicable. 4.3 TEStSt The following tests shall be conducted and a report thereon sha

35、ll be submfttcdests“ umler this specsf ication include computation and analysis as wel as physical tests as noted, purpoees, 8 complete schernatic arrarupment of the aircraft oil system together with a Tne report sHa include, for infornation arici reference -. - - - 8 #F, _-. , =_= Provided by IHSNo

36、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-0-17838 71 m 7779706 O102772 7 m J-*2s- d MIL- 0-19838 (Aec) listhg by rinafscturer and part nuhber of ail functional com?onents as defined in paragraph 3.1. Where tests are reported separately, they shall be sumitt

37、ed as addenda or ancnclments to the basic 09 system report rather than by separate report titleq Tosts listed in this specification which are not applicable to an airplane shall be listed by title uith appropriate notation rather than omitted from refererice in the oil system test report. 4.4 EQUIRL

38、EhT: Not applicable. 4.5 PWCXDRE b.s.1 The oil system tests as specified herein shall be conducted by the contractor to demonstrate satisfactory lurrication and oil system installation on pre-production aircraft. requirements of MIL-D-8706(AER). A report shall be subitted in accordance with the 4.5.

39、2 Test Conditions - The tests shall be performed as described heroin. 4.5.3 %ere power plmt Fnstallation test methods otherthan these described herein must be used, they shall be brieflydescribed and data submitted to facilitate comparisons with the standard procedure. 4.5.4 Calibration of instrumen

40、ts - W instruments shall be calibrated bimodately prior to the power plant installation tsts and ,a frequent intervals during the tosts. 4.6 E8GINE OIL SYSTEII TEJ“T The purpose of this test is to determine if the engine oil system operatX:.lfactoriry, maintains necessary oil pressure, and is free f

41、rom w.cessive oil discharge from tho breathers. the engine model specification, shall be maintained by the temperature controls. 4,6.1 Test Requirement - Normal engine oil inlet tenperature, as specified by 4.62 Instrumentation - The instrumentation to record the data as follows: (1) (2) Temperature

42、 Oil in. (3) Temperature Oil out. (4) Temierature Free Air. (5) Air Speed. (6) Pressure Altitude. (7) Hanifold Pressure (reciprocating engines only). (8) Engine Cil Pump Pressure (inlet and outlet). (10) Blower Setting (reciprocating engines only) . (U) lbrqueme ter Reading (reciprocating and turbo-

43、prop installations) where applicable. (12) Time (clock the). (13) Oil Cooler Lnlet Pressure. (14) Mixture Setting (reciprocating engines ow). (15) Scavenge Pump discharge pressure, (16) Tailpipe Temperature (turbine encines only). (17) Tailpipe area (urbine engines only) . 4.6.3 Procedure - The test

44、s shall be as iojaowst %mperature, Cylinder Head, spark plug asket or inbedded type (cockpit instrument) (reciprocating engines ow f. (9) RPM. * (a) With a one-fuu* filled tank, flipht tests 3haXL be nade atthe flight . attitudes, including slip, clW and dive attitudes, required hi th a2picabl.e air

45、plane detail specification. any desired altitude, to maximm allowable airplane velocity ad shall be preceded by a Tho flight test shall be made at any desired af.t;itude. (b) The dive tests shall be made at normal rated engine RPM and Power and from Provided by IHSNot for ResaleNo reproduction or ne

46、tworking permitted without license from IHS-,-,-puah-over made at the maximuin allowable neaative acceleration specified in the apjdicaole I desim apcificationr (o) The normal rated pomr climb test shall be started Immediately after take-off and trminated at service cefiing. (d) With a one-fourth fU

47、lod tank, airplanes which may be inverted in flight shall be flown inverted for ten seconds. Rated engine Ri“ and power shaU be malntaine, 0 I k,Gr.ution switch should be at least 75$ o% the nonnal fuel operating pressure. fuel as specified in +he engine model specification at any ambient alr temper

48、ature. off shall be accomplished within five minutes after starting the engine. (Grade U00 oil shall be used in all reciprocatini:, aircraft engines or operation ar 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-boil-off time a8 ordinates, plotte

49、d a .ahst tinte of dilution a abscisaa. Tebulate fuel pr008ur68, actual tho, oil tank levels, RPM, free air temperature, etc., au applicable, In plotting the curve of dilutiorr against time, the shut- time on the airplane and enf$.ne at tho start of tho test, the Qctane rating and grade of the fuel, grade and specification nue submittI . . ., II . . w 3 P ac Irl c w ci 34 a IL *. 9 O Provided by IHSNot for Res