1、;E K-2?-6/ MS26557 REV A 26 m 7997712 0008713 B m . FXOJECT NO. 2620-008 f ED. SUP CLIBI 1 2620 THE TIRE SHALL BE IN ACC0IU)AME WITH THE APPLICABLE REQUIRPIENTS OF SPECIFICATION MIL-T-5041 EXCEVAS SPECIFIED HEREIN PLY STATIC LNFL. BRST BEAD WEIGKT STATIC H)LD DEFLECTION SIZE RATING LOAD PRESS. PRESS
2、. WIDTH LBS. UNBAL. TREAD SKID 4-32 LLrrTING PSI PSI INCH Mi. OZ.-IN. DEPM -47. LBS. RATED MIN. WX. PM . HIN. 44 x 13 26.m 35,000 210 800 3.15 155 25 JIIB .31 322 - if - 21 - 31 11 “L. - TUBELESS TIRE - 21 NEU TIRE - 3/ AT LEAST FOUR BUT NOT H3RE THAN SEVEN COTINUOUS CICCIMFERENTIAL RIBS. - THE TIRE
3、 COVERED BY THIS DRAWING SHALL BE SUITABLE FOR USE AND PROVIDE REASONABLE SERVICE LIFE DURING ALL NOML OPERATIONS AT TAKE-OFF AND LANDING SPEEDS INDICATED HEREIN ON ALL TYPES OF RUNWAYS AND ON AIRCRAFT CARRIERS. THE TIRE SHALL WITHSTAhm WITHOUT FAILURE THE POLWING TESTS: DYNAMIC TEST - THE TIRE SHAL
4、L SATISFACTORILY WITHSTAND 75 CYCLES OF TEST “A“ FOmD BY 75 CYCLES OF TEST “B“ WITHOUT EVIDENCE OF FAILURE. (1) - lZST A TiE TIRE SHALL BE LOADED AGAINST A STATIONARY FLYWHEEL AT 35,000 POUNDS. WHEEL SHALL TEN BE ACCELERATED TO 30 MPH AND TAXIED AT THIS SPEED UIPTIL A TOTAL DISTANCE OF 10 O00 FEET P
5、AS BEEN COVERED, TO “O“ KF“ AhDIHHEDUTELY ACCELERATED AT 3.5 FEETISECISEC AVERAGE (SIHUIATED TA=- OFF) TO 200 MPH. FOR THE FIRST 15 SECOXOS Ahm THEN DEChSED LINEARLY WITH TLW TO 25,000 POUXDJ AFTER 50 SECONDS OF ROLL TH3 LOAD SHALL BE REDUCED TO ZERO POUNDS DURING THC. LAST THE FLY- THE FLYWHEEL SHA
6、LL THEN BE DECELERATED DURING ACCELERATION THE LOAD SHALL BE MAIhTAIhm AT 35,000 P0UM)S 3 SECOXIS OF ROLL. THETOTAL ROLL DISTANCE FOR THESIMUIATED TAKE-OFF SHALL. BE - . - - - -. - - . i2.350 izo0 FEET;-AVEUGE ROLL TZHE SHALL BE APPROXIMATELY 84 SECOXDS; TEST B - THE TIRE SHALL BE LANDED AGAIRST A F
7、LYWHEEL ROTATING AT A SPEED OF 125 HPH. 30 HPH. 10,000 POUNDS IN 4 TO 5 SECONDS; THEN INC-SED LINEARLY TO 20,000 WUHDS IN 12 SECOhmS AFTER IAhDING AND HELD AT THIS LOAD UNTIL THE TOTAL ROLL DISTANCE OF APPROXIMTELY 2.100 FEET WS BEEN COVERED IR 18 TO 19 SECONDS. THE FLYWHEEL SHALL HAVE AN AVEMGE DEC
8、ELERATIOX OF 7.5 FEET/SEC/SEC FROM 125 m TO THE LOAD SHALL INCREASE LINEARLY FROM ZERO POUNDS AT INSTANT OF IAhDING To THE TIRE SHALL THEH BE TAXIED AT 30MPH FOR 13,500 FEET AT THE 20,000 POUND LOAD. (2) BURST TEST - FOLLOWING THE ABOVE DYKAMIC TESTS THE SAKE TIRE SHALL BE SUBJECTED TU A HYDRO- STAT
9、IC BURST TEST. PRESSURE, DESCRIPTION OF FAILUnE AhD LOCATION TION TEST REPORT. THE PRESSIIRG SMLL BE INCREASED UhTIL THE TIRE FAILS AND THE FAILING FAILURE SHALL BE REPORTED IN THE QUALIFICA- AIR RETWTION - AIR RETENTION SHALL BE IN ACCORDANCE WITH MIL-T-5041. IhmTION PRESSURE SHALL BE PSL. WEAR DEF
10、TH INDICATORS - AN EVEN NUMBER OF TREAD WEAR IhmICATORS SK4LL BE EQUIDISTANTLY SPACED AROUND TO Em ALLOWABLE TREAD WEAR TO 1/32 INCH ABOVE THE BOTTOM OF THE TREAD GROOVES. OBLONG HOLES (1 x 114 INCH) OR ROUEID HOLES (5/8 INCH DIAMETER) SHALL BE LOCATED IN THE TREAD RIBS. (1/2 INCH LONG) SHALL BE LOC
11、ATED IN THE TREAD GROOVES. BY DI-VIDING THE CIRCLBIFERENCE OF THE TIRE BY THE LENGTH OF ITS FOOTPRINT AND ADDING ONE WEN THE RESULT YIELDS AX CIDD -DEPR%IC, AIRCRAFT, 44 x 13 HIGH SPEED - AIR FORCE - 70 .TYPE VI1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
