NAVY MS14178 REV A-1984 TIRE PNEUMATIC AIRCRAFT 24 X 6 5-14 FABRIC REINFORCED TREAD (200 KNOTS)《 24 X 6 5-14纤维增强螺纹(200 节)飞机汽轮胎》.pdf

1、MS14378 REV A 26 W 7777732 00083b7 8 m .- -o EE/ 8 2 6 p ZEz: C. - :pa : - fi E 0 p 2: =z :E;$ FED. SUP CLASS 2620 MIL IT ARY STANDARD TITLE “A. NAVY *AS ithncusi TIRE PNEUMATIC, AIRCRAFT, 24x6:5-14, FABRIC REINFORCED TREAD (200 JCNOTS) ROCUREMENT SPECIFIUTION SUPERSEDES: SHEET 1 OF 3 MIL-T-5041 PUT

2、E Na Pm IIVIOUS amimm o. TYI ma OMLCTK. PROJECT NO. 2620-N236 DD ,gR:,672-1 (Lfmi*d c*mrdiimti*n) THE TIRE SHALL BE IN ACCORDANCE WITH THE APPLICABLE REOUIREMNTS OF MIL-T-5041 EXCEPT AS SPECIFIED HEREIN - - SIZE PLY STATIC VERT. IHFL BURST BEAD WEIGHT STATIC TREAD MOLD DEFLEC RATING LOAD LOAD PRESS.

3、 PRESS. WIDTH POUNDS UNBAL SKID +3% POUNDS MIN. MN. MIN. MAX. MAX, MIN. RATING POUNDS PSI PSI IN MAX. OZ-IN DEPTH -4% 14x6-5-14 LI18TL 12,900 54,500 375 - 2/3500 1.55 35 15 - J/RIB 0.30 32 i/ TL-TUBELESS. HOWEVER THE TIRE SHALL BE CONPATIBLE FOR USE WITH A TUBE. - 21 NWTIRE 3 AT LEAST THREE BT NOT H

4、ORE THAN SEVEN CONTINUOUS CIRCUMFERENTIAL GROOVES. WIDE GROOVE CONCEPT SHALL BE USED WITH RADIUS AT BOTTOM OF GROOVES TO PRECLUDE STRESS RISERS AND CIRCUMFERENTIAL CRACKING FABRIC REINFORCED TREAD :IRE C RIM DATA: SEE FIGURE 1 HE TIRE COVERED BY THIS DRAWING SHALL BE SUITABLE FOR USE AND PROVIDE REA

5、SONABLE SERVICE LIFE DURING ALL !ORMAL OPERATIONS AT TAKEDFF AND LANDING SPEEDS INDICATED HEREIN ON ALL TYPES OF RUNWAYS AND ON AIRCRAFT .ARRIERS. :WE TIRES SHALL BE USED FOR OUALIFICATION TESTING. THE TIRES SHALL BE TESTED AS FOLLOWS: :IRE 1: SHALL WITHSTAND WITHOUT FAILURE, TEST A, 25 CYCLES OF TE

6、ST B, THEN BE SUBJECTED TO TEST E (HYDROSTATIC BURST TEST). :IRE 2: SHALL WITHSTAND WITHOUT FAILURE, 1 CYCLE OF TEST C, 50 CYCLES TEST D, THEN BE SUBJECTED TO TEST E (HYDROSTATIC BURST TEST). -IRE 3: SHALL BE SUBJECTED TO TEST E (HYDROSTATIC BURCT TEST). ?EST A - BRUISE TEST - A NEW TIRE SHALL BE IN

7、FLATED WITH AIR TO 480 PSI AND LOADED AGAINST A ONE AND IIREETEINCH (1 3/8“) DIAMETER LENGTH OF PLAIN ROUND BAR STOCK OR CABLE. A VERTICAL LOAD OF 54,500 POUNDS SHALL BE APPLIED WITH THE VERTICAL CENTER-LINE OF THE NOUNTED TIRE MAKING AN ANGLE OF 87 DEGREES WITH THE PUTEN, INMEDIATELY FOLLOWING THE

8、RELEASE OF THIS LOAD THE TIRE SHALL BE SUBJECTED TO THE SAME LOADIKG CONDITION AT A SPOT 180 DEGREES FROM THE INITIAL POINT OF LOADING. TIRE PRESSURE LEAKAGE AFTER THIS TEST SHALL NOT EXCEED 20 PSI. EST B - DYNAMIC TEST. 1. TEST TIRE DEFLECTION PROCEDURE. AFTER COMPLETING TEST A, THE TIRE SHALL UNDE

9、RGO STATIC DEFLECTION AS SPECIFIED IN MIL-T-50ltl EXCEPT THAT THE INFLATION PRESSURE SHALL BE 410 TO 415 PSI. RECORDED FOR USE IN PARA. 2, BELOW. 2 LANDING. THE TIRE SHALL BE LOADED TO RATED LOAD AGAINST THE DYNAHQKETER FLYWHEEL. THE INFLATTfMTRkSSURE SHALL BE VARIED TO PRODUCE TK3 SAME DISTANCE DET

10、ERMINED IN PARA. 1, ABOVE. THE LOAD SHALL BE RELEASED. THE TIRE SHALL THEN BE LANDED AGAINST THE FLYWEEL ROTATING AT A PERIPHERAL SPEED OF 195 MPH. THE FLYWHEEL SPEED SHALL BE DECREASED UNTIL A ROLL DISTANCE OF 6,120 FEET HAS BEEN COVERED, AT WHICH TIM3 THE TIRE SHALL BE UNLANDED. THE AVERAGE DECELE

11、RATION RATE SHALL BE 6.6 FT/SEC/SEC THROUGHOUT THE RUN. SHALL BE INCREASED TO 5,600 POUNDS WITHIN ONE SECOND OF LANDING AND FURTHER INCREASED LINEARLY WITH TIHE TO A MAXDflBf OF 12,900 WUNDS WITHIN 14 TO 16 SECONDS AFTER LANDING. THE LOAD SHALL THEN BE MAINTAINED AT 12,900 POUNDS UNTIL THE TIRE IS U

12、NLANDED AT APPROXI- MATELY 41 SECONDS FROX TIME OF LANDING, THE DISTANCE FROM THE AXLE CENTER-LINE TO THE LOAD SURFACE SHALL BE DETERMINED ANI THE TIRE LOAD PEST C - YAW TEST, C RELATIVE TO THE DYNAMOMETER. INCREASE LOADING UNTIL THE TIRE IS LOADED WITH A RADIAL LOAD (IN THE TmL PUNE PERPENDICULAR T

13、O FLYWHEEL) OF 12,900 WUNDS. AFTER TRAVELING A DISTANCE OF 300 FEET AT FULL LOAD. THE TIRE SHALL BE SUBJECTED TO 25 CYCLES OF TEST C1 AND 25 CYCLES OF TEST Cp. - THE TIRE INFLATED TO 375 FSL (CORRECTED FOR FLYWHEEL CLRVATURE) SHALL BE LANDED ON A FIWHEEL ROTATING AT A PERIPHERAL SPEED OF 30 WH SET A

14、T A PRESELECTED 3 DEGREE YAW ANGLE THE TIRE SHALL BE UNLANDED PEST - - D- - C2 - WITH THE DYNAMOMETER FLYWHEEL AND THE LOAD APPLIED ON THE TIRE INBOARD SIDE. THE TIRE SHALL BE TAXIED ON THF, FLYWHEEL AT 30 KPH FOR 10,000 FEET WITH 12 900 POUNDS LOAD. O F THE TAXI ROLL 30 MPH TO 230 MI“. BEEN COVERED

15、 IN APPROXIMATELY 53 TO 55 SECONDS. FOR THE FIRST 6 SECONDS AFTER THE START OF THE TAKE-OFF ROLL, DECREASED LINEARLY WITH TIME TO 1,SQQ POUNDS AT 5UKCONDS AFTER THE $TAR%0F-TWkKE-OFF ROLL AND DECREASED TO ZERO POUNDS THE SAFE AS THAT OBTAINED WITH THE RATED LOAD AND INFLATION PRESSURE ON A FLAT PLAT

16、E. SAFE AS C1 EXCEPT THE 3 DEGREE YAW ANGLE SHALL BE APPLIED IN THE OPPOSITE DIRECTION. TAXI/TAKEOFF. THE VERTICAL CENTERLINE OF THE MOUNTED TIRE SHALL MAKE AN AKGLE OF 87 DEGREES WN COMPLETION THE FLYWHEEL SHALL BE ACCELERATED AT AN AVERAGE RATE OF 6.2 FT/SEC/SEC FROH THE TIRE SHALL BE UNLANDED AmR

17、 A TAKEOFF ROLL DISTANCE OF 9,000 FEET HAS THE LOAD SHALL BE MAINTAINED AT 12,900 POUNDS AT THE TIJE THE TIRE ISENDED. TE TIRE DEFLECTION AT RATED LOAD ON THE FLYWHEEL SHALL BE PROBLEM WARD COPY Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-d u I 2

18、620 TEST E - IIYDROSTATIC BURST TEST. THE TIRE SHALL BE SUBJECTED TO A HYDROSTATIC BURST TEST, THE PRESSURE IL THE TIRE FAILS, THE FAILURE PRESSURE, DESCRIPTION OF FAILURE AND AIR RP,TEiTION - TkE TIRE SHALL BE INFLATED TO A PRESSURE OF 480 PSI AND ALLOWED TO STAND FOR A PERIOD mT WHICH TIME THE PRE

19、SSURE DROP DUE TO GROWTH SHALL BE REPLILCED. AN ADDITIONAL 24 HOURS AT WHICH TIME THE PRESSURE SHALL BE MEASURED AND THE TIRE INSPECTED. PRESSURE LOSS SHALL KOT EXCEED 5 PERCENT. OTIER APPEARAXCE OR PERFOREAKCE DEFECTS, THE TIRE SHALL THEN STAND THE AIR THERE SHALL BE NO SIDEWALL BLISTERS, TREAD SEP

20、ARATION OR LOAD DEFLECTION - LOAD DEFLECTION CURVES FOR ItFLATION PRESSURES OF 205, 275, 315, 375, 435, 465, 535, BE PREPARED FOR THE FOLLOWING CONDITIONS: A. STATIC LOAD VS DEFLECTION B. IMPACT LOAD VS DEFLECTION C. IMPACT ENERGY VS DEELECTION FOOTPRINTS - FOOTPRINT AREAS SHALL BE PREPARED AS F0LU)

21、WS: Ar FOOTPRINT AREA VS PERCENT DEFLEXTION CURVE B. LOAD REOUIRED TO BOTTOM THE TIRE INFLATED TO 450 PSI C. FOOTPRINT AREAS AT RATED INFLATION PRESSURE AND STATIC AND BOTTOM LOAD CONDITIONS. INCLUDE FLAT TIRE AND NORMAL ROLLING RADIUS. D. FULL SCALE PRINT OF ACTUAL FOOTPRINT AT RATED LOAD AND PRESS

22、URE I.IARKIIO - IN ADDITION TO THE MARKING REQUIRED BY SPECIFICATION MIL-T-5041 RATIKG MARKItXS, THE DRAWING NUMBER M 14178“ FXLTTXBRIC TREAD“ srmL BE ERGRAVED OR EMBOSSED ON ONE SIDE WALL IN THE ICINITY OF THE SIZE AND PLY SECTION - REPRESENTATIVE SECTIONS OF THE QUALIFIED TIRE DESIGN SHALL BE SUBM

23、IITED, ONE SECTION EACH TIRES tWMBER 1 AND 2 THAT HAVE BEEN SUBJECTED TO REOUIRED TESTING. OUALIPICATION TEST REPORT - THE OUALIFICATION TEST REPORT SHALL LIST THE RESULTS OF ALL OUALIFICATION _. - . &STS AND-UCTION DETAILS OF THE QUALIFICATION TEST SAMPIE IN THE GENERAL FORM SHOWN IN FIGURES 2&7 OF

24、 MIL-T-5041 WITH DIKEh3IONS LISTED AT RATED INFLATION AND 480 PSI. EVLMIPACTURERTS TEST NUMBER %O COFIES OF THE I)UALIFICATION TEST REPORT I.fA“ERIAL SPECIFIED ABOVE Ab IN MIL-T-5041 SHALL BE FORWARDED TO THE NAVAL AIR SYSTEMS CoMt.IAND, WASH- THE REPORT SHALL LIST THE TOGETHER WITH THE DATA AND INc

25、TOXj DC 20361 ATTENTION: AIR-53032 KOTES : 1. REFERENCED DOCUMENTS SHALL BE OF THE ISSUE IN EFFECT ON DATE OF INVITATIOXS FOR BIDS OR REQUEST FOR PROPOSAL EXCEPT THAT REFERENCE ADOPTED INDUSTRY STANDARDS SHALL GIVE THE DATE OF THE ISSUE ADOPTED. 2. FOR DESIGN FEATURE PURPOSES, THIS STANDARD TAKES PR

26、EDEDENCE OVER PROC- DOCLMENTS REFERENCED HEREIN. 1 MILITARY STANDARD *A, NAVY-AS TITLE Ihn Oirt TIRE FNEWTIC AIRCRAFT MS14178(AS) 2!5-14, FABIC REINFORCED TREAD (20n OTS) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSLLi37B REV A 26 9999932 00083

27、71 b FEO. SUP CLASS 2620 DS Y r DIA TIRE DIMENSIONS (INCH) RATED INEIATION PRESSURE GROW AT GROWN AND THROWN MIN. MAX. 480 PSI (MAX.) MX. OUTSIDE DIA. (Do) 23.60 24.20 24.80 24.80 SECTION WIDTH (W) 6.25 6.65 6.95 SHOULDER Di. (Da) 22.40 SHOULDER WIDTH (Ws) 5.90 FIGURE 1 I MILITARY STANDARD A. NAVY -

28、AS TITLE iitm Gist MS I41 78(AS) TIRE, PNEW4TIC, AIRCRAFT 246.5-14, FABRIC REINFORCED TREAD (200 KNOTS) ROCUREMENT SPECIFICATION SUPERSEDES: SHEET -i OF MIL-T-5041 PLATE NO. m7i DD 672- 1 (Limited c.wdir.tim j *IVIWI IMIQ o. TYI m- ME OMLKI.- * U.S. GOVERNMENT PRINTING OFFICE 1984-705-040/A1002 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-