NAVY MS14196-1981 TIRE PNEUMATIC AIRCRAFT 18 X 5 7 - 8 00 (NAVY) FABRIC REINFORCED TREAD《18 X 5 7 - 8 00(NAVY)纤维增强飞机汽轮胎》.pdf

《NAVY MS14196-1981 TIRE PNEUMATIC AIRCRAFT 18 X 5 7 - 8 00 (NAVY) FABRIC REINFORCED TREAD《18 X 5 7 - 8 00(NAVY)纤维增强飞机汽轮胎》.pdf》由会员分享，可在线阅读，更多相关《NAVY MS14196-1981 TIRE PNEUMATIC AIRCRAFT 18 X 5 7 - 8 00 (NAVY) FABRIC REINFORCED TREAD《18 X 5 7 - 8 00(NAVY)纤维增强飞机汽轮胎》.pdf（4页珍藏版）》请在麦多课文档分享上搜索。

1、-. d B MSLLiLSb 2b m 7777712 0008382 O m k-29-1 reo. suc CLAU I 2620 THE TIRE UUU BE IN ACCORMNCE WITH TiE APPLIUBLE REpUIREIIEHTS of SPECIFICATION MIL-T-5641 EXCEPT AS SPECIFIED HEREIN WOLD STATIC VERT. INFL. iRST BEAD STATIC TEAD SKID #FLC SIZE PLY LOAD LOAD PRESS PRESS WIDTH MIGHT IMALAIICEOZ. DE

2、PTH + 3% WTIIIG IuTIffi LBS. PSI PSI IN. LES. W. INCH - 42 LBS. RATED WIN. W. MAX. 1X5.7-8.00 14TL 1/ 6.m 45.W 215 970 2J 1.H) 15.5 2.5 RIE 3/ C.ti 32 1/ TLTUBELESS y IEWTIRE a AT LEAST FWR, BUT T ME TKW SEVEN INSOFAR AS PRACTICABLE TO PREVENT FOREIGN OBJECTS FROH EEING TRAPPED EETUEEN THE RIBS. FAB

3、RIC REINFORCED TREAD. RIES. TH TREAD GROOVES SHALL BE SHAPED, TIRE AM, RIM DATA: SEE FIGURE 1 THE TIRE COVERED BY THIS DRAWING SHALL BE SUITABLE FOR USE AND PROVIM REASONABLE SERVICE LIFE WRING ALL NOWU OPERATIN Al TAKEOFF AHD LANDING SPEEDS INDICATED HEREIN ON ALL TYPES OF RUNUAYS MD ON AIRCRAFI CA

4、RRIERS. A WINIIIM W3EVEN TIRES SHALL BE USED FOR QUALIFICATIDN. TECtUiIQES. THE TIRES SHALL BE EXAMINED AS FOLLOWS: AU TIRES SHAlL BE WILT UsIffi THE Un: W“Ds AND PROCESSIffi DIIEtSIIOWS: AU TIRES SHALL BE INFLATED TO DPERATING PRESSURE AND ALLCUED TD STAND 4M)URSHINIiUH AT RWH TERERATURE AFIER UHIM

5、 THE PRESSURE LOSS DUE TO GRWH SHALL BE REPLACED. MITHIN THE LIHITS OF FIGURE 1. WRING ME ENVELOPE COCIPLIAHCE PORTIDN OF DYNAMIC TWIN6 TO WEMINE GROWN ANO THROVN WLIANCE (FIGURE 1) TIRES 1, 2 L 3: TIRES SHALL BE INFLATED TO GIVE A RATED DEFLECTION AT RATED LOAD. ALL TIRES SHALL CONSECUTIVELY YITHST

6、I 21 CYCLES OF TEST A. 2 CYCLES OF TEST E, 2 CYCLES OF TEST C, 25 CYCLES OF TEST D, 1 CYCLE OF TEST E A)a) 1 CYCLE of TEST F IN THAT ORDER. THE TIRE DIHEHSIONS AT 400 PSI SHALL BE IN ADDITION, DYNAMIC TEST TIRE MHER ONE SHALL BE EASUREO PMITDGRAPHIC PRODF OR PHOTOS OF AH ACCURATE WURII DEVICE YWIyIf

7、fi ENVELOPE CWLIANCE (FIGURE 1) SHALL BE OBTAINED FOR TREimeER 1 AS FOLLWS: (oa POUD-T is SEW AFTER START OF ROLL, THEN LIIIURLY omREAsm TO 5,000 ms AT wIm OF LIFT-OFF. TEST B - OVERLOAD TAKEOFF - THE TIRE SHALL BE TAXIED ON THE FLYHIEEL AT 40 MPH FOR 9.m FEET WITH 9,350 NDS L KIER A TAKEOFF ROLL OF

8、 5.000 FEET HAS BEEN COVEREO IN APPROXIMTELY 28 TO 29 SECONDS. LOA0 OF 9.350 POUHDS SHALL BE DECREASED LINEARLY WITH TIME TO 8.900 WONDS AT 14 SECONDS AFTER THE START OF THE ROLL, THEN FURTHER DECRWED TO 7,200 POUWDS AT THE POINT OF LIFT OFF. THE INITIAL TC3 C - TAKEOFF AT 5 000 FEET ALTITUDE ON A H

9、OT DAY - THE TIRE SHALL BE TAXIED ON THE FLYWHEEL AT 40 WH H D COWLETION OF THE TAXI ROLL THE FLYWEEL SHALL BE P;THE:ECEEO AVERAGE RATE OF 8.95 FT/SEC/SEC FRW O WH TO 247 RH. TM TIRE SHALL BE UNLANDED AFTER A TAKEOFF ROLL DISTANCE OF 7,300 FEET HAS BEEN COVERED IN APPROXIMTELY 40 TO 41 SECONDS. THE

10、INITIAL LOAD (6.200 PWNDS) SHALL BE MAINTAINED FOR THE FIRST 7 SECONDS OF THE TAKEOFF ROLL THEN DECREASED LINEARLY WITH TIME TO 5,750 WUNDS AT 30 SECONDS #TER THE START AHD TO 5.000 WONOS AT THE POINT OF LIFTOFF. TEST D - WOIffi - THE TIRE SHALL BE LANDED AGAINST A FLYWHEEL ROTATIffi AT A PERIPHERAL

11、 SPEED OF 1% CIPH. =“EL SPEED SHALL BE DECREASED AT AN AVERAGE DECELERATION RATE OF 8.50 FT/SEC/SEC FROM 1% TO 40 WH. THE INITIAL TIRE LOAD SHALL BE 1O.MtO WUNOS AT TOUCHWWN LINEARLY MUIEASEO TO 3.600 POUNDS WITHIN . THE MDING ROLL.0ISTANCE OF 4,350 FT SHALL BE COVERED IN APPROXIMATELY 26 TO 27 SECO

12、NDS. i SECOND, THEN LINEARLY INCREASED-TO 5,000 POUNDS AFTER 4.350-FT. THE TIRE SHALLTHEN BE TAXIED THE FLYWHEEL FOR 9.m FT AT MOWH WITH A 4.60 Pam LOAD; AFTER TE TAXI. THE 4,000 POUND LOAD SHALL BE WINTAINEO On THE TIRE FOR A HINIW OF 15 IIINiJTES. TEST E - TAXI TO SIMJLATE SIDE LOAD DURING TURNING

13、 - WE CYCLE Of TESTESHALL WNSIST OF 25 CYCLES OF TEST BE AS SPECIFIED FOR EACH CONDITION. YAW ANGLE RELATIVE TO THE DYHAHOMETER. THE LOADING SHALL BE ACCOMPLISHED BY ROLLING THE WHEEL AT A THE VERIFICATION OF THE SPECIFIED LOADINGS IS REQUIRED. SIDE LOAD DEFLECTIOHS SHALL BE RECORDEO. Ei IIIBOMD YAW

14、 TEST (25 CYCLES) 1. 2. WO TIRE ON FLYHHEEL WITH A PRESELECTED YAW AHGLE WICH WILL GIVE THE REWIRED LOADING. INCREASE THE LOADING ON THE TIRE WITH A IUDIAL LOAD (IN THE WHEEL PLANE) OF 4.680 POUNDS ANO A SIM LOAD (PERPENDICULAR TO THE WHEEL PLANE) OF 2,575 POUNDS ACTING IIIBOARO. MINTAIN THIS LOAD F

15、OR THE REMAINDER OF THE CYCLE. S. INLAND THE TIRE WEN A DISTANCE OF 300 FEET HM BEEN WLETED WITH FULL LOAD. E2“- OUTBOARD YAW TEST (25 CYCLES) SAIIE AS Ei“ EXCEPT WITH THE SIDE LOAD CMIPONEHT ACTIN6 OUTBOARD. #TERNATE SIDE LOAD TEST - SAHE AS E “ AND “E EXCEPT IF WLE TO PERFORM CALIBRATIM( TESTS -T

16、AXLE TO VERIFY SIDE hOS. TESTS MITLINED SHALL BE LOAD WE TO TREAD ABRASION. THE YAU ANGLE USE0 FOR THE SIWLATEO TURNING WITH THE VERTICAL LOAD OF 4,680 PONOS TO ALLOW FOR A DECREASE INSIDE TEST F - TAXI OUT. REJECT RETuw( TO STATION - THIS TEST SKUL CWSIST Of 3 WES: PHASE 1: TAXI THE TIRE ON THE FLY

17、WHEEL FOR 4.00 FEET AT 6,200 POUNDS LOAD AT 46 WH. STOP THE FLYHHEEL UNDER FULL LOAD. REPEAT THIS THREE (3) TIMES SUCH THAT A TOTAL DISTANCE OF 12,000 FEET IS COVERED IN NO WE THAN 210 SECONDS. PHASE 2: (A) HILE UNDER THE 6,2M WUND Lw), ICMEDIATELY ACCELERATE THE FLYWHEEL AT A HINIW RATE OF 12 FT/SE

18、C/SEC TO 98 RH. MINTAIN THE 98 CtPH SPEED FOR 3 TO 4 SECONDS. (B) DECELERATE AT AN AVERAGE RATE OF 7.9 FTISECISEC! TO ZERO (O) SPEED IN 18 to 19 SECONDS. WE 3: WUTAIN THE 6.200 WO LW ANO TAXI TH TIRE FOR 12,000 FEET AT 46 IPH. THIS PHASE SHAU rmT EXCEED 190 SECONDS. MILITARY STAN DA RD mu kGii TXE,

19、-TIC, AIRCRAFT, 18 X 5.7 - 8.00 MS14196 (AS) (HAW) FMRIC IlfIffORtEO TREAD I I#uwunprc*UTr*c OF Licensed by Information Handling Services1 L MS343Sb 26 9999932 0008384 4 M WOTES: 1. REFERENCED CU13EHTS SHALL BE OF THE ISSUE IN EFFECT ON DATE OF IHVITATIDNS FOR BIDS, OR REQUEST FOR PROPOSAL EXCEPT TH

20、AT REFERENCE ADOPTED IWUSTRY STANDARDS SHALL GIVE THE DATE OF THE ISSUE ADOPTED. FOR DESIGN FEATURE PURPOSES, THIS STANDARD TAKES PRECEDENCE OVER PROCUREMENT DOCUMENTS REFERENCED HEREIN. 2. . TEST C - UBLE MWISE TEST - A Mw TIRE INFLATED TO 350 - IW PSI (MIER MIHG PWSSW) -1HST A 1.375 INCH DIMETER S

21、TEEL UBLE OR PLAIW ROUND BAR STOCK RESTING RELEASED MD RE-APPLIED AT A LOUTIOH 180 FRW THE. INITIAL POINT OF LMDING. b-L SHALL BE ACCELERATED AT AN AVERAGE RATE OF 14.0 FT/SEC/SEC FROM D TO 57 M“. THE TIRE SHALL BE UNLANED AFTER A ROLL DISTANCE OF 250 FEET HAS BEEN COVERED IN AFPROXIHATELY 6 SECOHDS

22、. WITHIN 1.42 SECONDS; DECREASED LINEARLY TO 27.D FWHDS AT 2.60 SECONDS, THEW MCREASED LIHEARLY TO 18,oOO POUNDS AFTER 6 SECOS AT WICH TIME THE TIRE IS UNWED. ON A FLAT PLATE DIRECTLY MER THE AXLE. A VERTICM. LOAD OF 45s000 WVMK SHALL BE APPLIED, TEST H - CATAPULT CONDITION Il - TIRE IHFLATION PRESS

23、URE SHALL BE 350 - 400 PSIS CMIRECTED FOR FLYWHEEL THE INITIAL LOAD OF 18.DD PDUiDS SHALL BE INCREASED LINEARLY TO 36,400 POUNDS f - CATAPULT NMDITION 12. TIRE IFLATION PRESSURE SHALL BE 350 - 400 PSI UYIRECTED FOR FLYWHEEL APPRDXIMTELY 6 SECONDS. THE IWITIAL LOAD OF 22.BM) WUNDS SHALL BE IHCREMED L

24、INEARLY TO 31.800 POUNDS. WN DECEASED TO 15.800 POUNDS AT 6 SECONDS AT MICH TIRE THE TIRE IS WANDED. WITHIN 1.42 SECaDS,-DECREASED-EiNARLY-T 23,600 6Uh-fi P%-SEC&S , TEST J - BURST TEST - THE TIRE SHALL BE SUBJECTED TO A HTDRDSTATIC BURST TEST. THE PRESSURE SHALL BE C?!%WIL THE TIRE FAILS. BE REPORT

25、ED IN THE QUALIFICATION TEST REPORT. THE FAILIHG PRESSURE. ESCRIPTIOW OF FAILURE AND LOCATION SHALL AIR KfEWIoH - nU TIRE SHRlL BE INFLATED TD A PRESSURE OF 350 PSI AND ALLOWED TO STAND FM1 A PERIOD OF 24 HOURS AT TIHE THE PRESSURE SHALL BE MEASURED AND THE TIRE INSPECTED. BE NU SIDEWALL BLISTERS, T

26、READ SEPARATION OR MHER APPEARANCE OR PERFWNCE DEFECTS. TIE THE PRESSURE DROP WE TO GROVTH SHALL BE REPLACED. THE TIRE SHALL THEN STAND AN MOITIDtiAL 24 HOURS AT WICH THE AIR PRESSURE LOSS SHALL NOT EXCEED 5 PERCENT. THERE SHALL INFLATED PROFILE - A SKETCH OF THE TIRE PROFILE AT THE RATED INFLATTIOH

27、 PRESSURE AND 4DD PSI SWLL BE PREPARED AND INCLUDED ICs PART DF THE QUALIFICATION TEST REPORT. ALIFICATIOH TEST REPORT - THE QUALIFICATIM( TEST REPORT SHALL LIST THE RESLTS OF ALL QUALIFICATION TESTS AND CNSTRUCTlDN TAILS DF THE QUALIFICAT ION TEST SAMPLE IN THE GEHERAL FORM SHOWN IN FIGURE 6 OF HIL

28、-T-5041 WITH DIMENSIONS LISTED AT RATED INFLATIW AND 350 PSI. TWO COPIES OF THE QALIFICATION TEST REPORT, TOGETHER YITH THE DATA AND IIATERIAL SPECIFIED ABDVE AND IN MIL-T-5041 SHALL BE FORWARDED TO THE WAVAL AIR SYSTES CoCHAHD, WASHINGTON, OC 20361, ATTENTION: AIR-53D32. THE REPORT SHALL LIST THE W

29、“FACTURERS TEST NUIBER. , . f j II . , Licensed by Information Handling ServicesI CEO. IUC CLASS MSZllLb 26 m 9999932 0008385 b m I 2620 6 4.250 -1 r SCALE: “E I 8.00 DIA. 6ROm 6 THROWH TIRE DIIYNSIOI(S (INCH) RATED INFUTION PRESSUIE 350 PSI IWLATION PRESSURE 6RO“ e350 PSI 350 PSI, 230 RH WTSIDE DIA

30、. (Oo) 17.3 17.90 CIAX. - HIN. - M. - M. WIX. - MIN. i7.45 18.00 18.50 18.90 0.45 6.80 6.10 6a.10. SECTION WIDTH (U) 5.35 1.70 SHWLOER DIA, (O,) - 16.20 1.00 WOULMR UIDTH (U,) - WIuS (Ri) 1.50 - NE #)I(TouR of M AIRCRAFT TIRE SHALL NOT EXCEED THE ENVELOPE SWN AWE. THIS CONDITIDN MIST BE MET BEFORE T

31、O GROUM, SPEEDS RAHGING FRW O to 230 19H UITH THE TIRE INFLATED TO THE REWIRED RATED PRESSURES. SIaYAU WN TESTED TO ntE DVWIC PORTION OF THIS WIR. WRING, AND MIER THE OYWIC TESTING PORTION OF QUALIFICATION TESTING MD HILE THE TIRE IS ROTATING EQUIVALET THE TIRE SWL . FIT A WEEL OF SUITABLE WTERIAL UITH A COMWR PER THE DINENSIOHS AnD WTLIM S“ WE YITHOUT CHAFIN OF THE FIWRE 1 MIL IT ARY ST AN DA R I A HAW-Al TITU hGI8 TIRF. PI(EUIAT1C AIRWAFT, 18 X 5.7 - 8.00 (MWl, FABRIC REINFORCED TREM .j 1 MI4196 (AS) -MT#af(c*tOn mP$mE& Licensed by Information Handling Services