NAVY MS14185-1978 TIRE PNEUMATIC AIRCRAFT REBUILT 22 X 6 75-10《22 X 6 75-10飞机整修汽轮胎》.pdf

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1、1 THE TIRE SHALL BE IN ACCORDANCE WITH THE APPLICABLE RE?UIREMEhTS OF MIL-R-7726 EXCEPT AS SPECIFIED HEREIN. STATIC INn. BEAD STATIC )!OLD RATING RATING PSI INCH W“l?S OZ-IN. TREAD DEPTH +37. LBS. RATED HAX. MAX. MAX MIN, -47. SIZE PLY LCIAD PRESS. WIDTH WEIGHT UNBAL. SKID DEFLEC I O o 22X6.75-10 18

2、. L/ 10,600 245 2.05 28.0 10 RIB -30 327, MITRIC: 558.6X171.5-254m - 21 i/ TL- TUBELESS TIRE - 21 AT LEAST FOUR BUT NOT MRE THAN SEVEN - CONTINUOUS CICUMEERENTIAL RIBS. THE GROOVES SHALL BE SHAPED SUCH THAT FOREIGN OBJECTS WILL NOT BECOME TRAPPED BEWEEN THE RIBS. TIRE DATA (INCH) (STATIC TEST TIRE)

3、INFLATED OUTSIDE INFIATED SECTION INFIATED SHOULDER INFYITED SWULDER DIAMETER WIDTH DIAMETER WIDTH MIN. MAX. MIN. MAX. MAX. HAX . 21.35 22.33 6.35 6.96 20.00 6.00 RIM DATA (INCH) WIDTH FLANGE LEDGE LEDGE FIANGE HEEL FIANGE BEWEEN WIDTH DUMETER WIDTH HEIGHT RADIUS RADIUS FIANGES - - - 5.50 0.75 10.06

4、 2.05 1.00 0.50 e625 I THE TIRE COVERED BY THIS DRAWING SHALL BE SUITABLE FOR USE AND PROVIDE REASONABLE SERVICE LIFE DURING ALL NORMAL OPERATIONS AT TAKEOFF AND LANDING SPEEDS INDICATED HEREIN ON ALL TYPES OF RUNWAYS AND ON AIRCRAFT CARRIERS. FOUR TIRES SHALL BE SUBMITPED BY THE CONTRACTOR. THE TIR

5、ES SHALL BE REBUILT USING THE SAME COMPOUhTJS AND PROCESSING TECHNIQUES. TEST INFLATION PRESSURE - UNLESS OTHERWISE SPECIFIED, INFLATION PRESSURE FOR ALL DYNAMIC TESTS SHALL BEmSTED TO EN SURE lIRE DEFLECTION WITHIN DESIGN LIMITS. TIRES SHALL BE EXAMINED AS SPECIFIED BELOW: TIRE 1: DIMENSIONS - THE

6、TIRE SHALL BE INFIATED TO 245 PSI AND ALLOWED TO STAND FOR 4 HOURS MINIMUM AT ROOM TEMPERATURE AFTER WHICH TIME THE PRESSURE DUE TO GROIJTH SHALL BE REPLACED. THE REBUILT TIRE DIMENSIONS AT 320 PSI SHALL BE WITHIN THE DIMENSIONAL LIMITS SPECIFIED ABOVE. DYNAMIC TEST - THE TIRE SHALL WITHSTAND 60 CYC

7、LES OF TEST A, 60 CYCLES OF TEST B 1 CYCLE OF TEST C, 15 CYCLES OF TEST D, AND 20 CYCLES OF TEST E, WITHOUT FAILVRE OR.+ISIBLE DETERIORATION OTHER THAN NORMAL EXPECTED TREAD WEAR, TIRE-2: DYNAMIC TEST - THE TIRE SHALL WITHSTAND 1 CYCLE OF TEST F, 15 CYCLES OF TEST A AND 15 CYCLES OF TEST B WITHOUT E

8、VIDENCE OF FAILURE. DYNAMIC TESTS: TEST B - LANDING - TAXI - THE TIRE SHALL BE IANDED AGAINST A FLYWHEEL ROTATING AT A PERIPHERAL SPEED - O FLYWHEEL SPEED SHALL THEN BE DECREASED UNTIL A ROLL DISTANCE OF APPROXIMATELY 26fEHkABEEN COVERED. THE AVERAGE DECEiXRATION RATE SHALL BE 2 .O2 FEET/SEC/SEC B“V

9、EEN 127 AND 116 MPH, 8.97 FEET/SEC/SEC BEWEEN 116 AND 80 MPH, AND 13.02 FT/SEC/SEC BETWEEN a .:;LIT/ “y y-! r?: “? i . #i,. : NAVY -A6 TITLE Qhrt crnt TIRE, PNEUMATIC, AIRCRAFT, REBUILT, 22X6.75-10 ! 2C:L.Xa ?T SPECl=lCAT:2,4 j:. fXIDX Ci , MIL-R-7726 1 2 CD ,:“,:,672-1 CLII. *.wdiic,l.ii) *wwsrrnim

10、mw VIM rom um ommala. PROJECT NO, 2620-N139 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSL9185 26 9999932 0008373 T I ! i i I i i ! i i 3 i l i i i I $1 , ! I i i l i I o- 8 I 2620 89 ?CIl Ah? O MPA. c:COS% AiTER TAhQING FLiiWEECL AT 23 EIPH FOR

11、 10,000 FEET L!DER 3,100 POUNDS LOAD. THE TEE LOAD SHALL BE INCRWSED TO 2 O00 POUNDS IN 2 Ti:CN LIASRLY INCWSED TO 8 800 hNDS WHEN THE TIRE IS STOPPED AR 24 SECODS. IKDIATELY FOLIAWING THE UND IN, THE TIRE SHALL BE TAXIED ON TL: TEST C - OVERL?AI) TAKDING TAXI - COhDITIONI: AS FOR TEST B EXCEPT THE

12、FDLtOwING: LIhTARLY INCREASE T!B fLiiL LCNi)S FRCX FLiC!ZEL USDER A 5.h POUEID LOAD. O00 POXmS TO 12,003 POUNDS DURING UNDING. TAXI THE TIRE ON THE TEST D - CATAY.7.T MEOW - TlCE TIRE SHALL BE IAh3ED AGAINST A FLYWHEEL ROTATING AT A PERIPERAL sr,;C3 JF LUC Eiil WITH 17,500 POmDS LOAD FOR A DISTANCE

13、OF 300 FEET, THEN VIVIAhDED. FLiT PUTE INFiATIOX PRESSURE SHALL BE USED FOR THIS TEST. 320 RI TEST E - YAW IAATIXG - THE TIRE SHALL BE SUBJECTED TO 10 CYCLES OF TEST El AND 10 CYCLES OF TEST E2 FOR A VXtL OF 20 CYCLES. E WITH A PE-SELECTED 5 DEGREE YAW ARGLE REUTIVE 1 SMLL 9- IIIC“E4SED TO 8C90 POUN

14、DS. OF 200 FEET AT 120 HPH AFTER WHICH TIME THE TIRE IS UNIAhDED. - T3E TIRE SHALL BE IAh“ED AGAINST A FLYWIEELROTATING AT A PERIPHERAL SPEED OF 120 MPH THE TIRE IAhDING LOAD THE DYNAKNETER. TE UIAD WALL BE VATNTAINED FOR A MINIM24 ROLL DISTAKCE E2 - SANE AS E1 EXCEPT THE 5 DEGREE YAW ANGLE SHALL BE

15、 APPLIED IN THE OPmSITE DIRECTION. TEST F - C(i3,IE3 LOAD TEPT - A TIRE INFLATED TO 320 PSI SHALL BE SIMILTANEOUSLY STATIC LOADED WITH A C:.;3 i XAi Ci POUhD VERTICAL LOAD AND 8,000 POUND SIDE LQAD AND HELD FOR 3 SECONDS. TFEnc s:xL BE N;OSLIPPAGE ,: OR mm FAILURE. KOTES : 1. REFERENCED DOCWENTS SHA

16、LL BE OF TE ISSE IN EFFECT OR DATE OF T;rVITATIOh FOR BIDS, OR REQmST FCR FXCPOSAL EXCEPT THAT REFEREEICED ADOZED INDUSTRY DOCfEhiS SHALL GIVE THE DATE OF THE ISSUE ADOPTED. 2. FOR D?rTv FMTLRE PuRPoSSS, THIS STAhDAR TAES PRECEDENCE OVER PROCuRpIEhT DCCLWENTS PZFEREACED HERE IR. 1 I I! II - y- “US. GOVERNMENTPRINTING OFFICE: wm-701a1mr C ,; r Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-