scope:

THE TIRE SHALL BE IN ACCORDANCE WITH THE APPLICABLE REQUIREMENTS OF MIL-T-5041 EXCEPT AS SPECIFIED HEREIN

TIRE DATA (INCH) INFLATED CENTERLINE INFLATED SECTION INFLATED SHOULDER INFLATED SHOULDER DIAMETER WIDTH DIAMETER WIDTH MIN MAX MAX MAX MIN MAX _____________________ ______________________ ____________________ 26.60 27.40 7.40 7.85 24.90 6.95 RIM DATA (INCH) WIDTH FLANGE BETWEEN FLANGE LEDGE LEDGE FLANGE HEEL FLANGE EDGE FLANGES WIDTH DIAMETER WIDTH HEIGHT RADIUS RADIUS RADIUS _________ ________ __________ _______ ________ ________ ________ ________ 6.0 .750 14.0 1.75 1.0 .25 .5 .125

THE TIRE COVERED BY THIS DRAWING SHALL BE SUITABLE FOR USE AND PROVIDE REASONABLE SERVICE LIFE DURING ALL NORMAL OPERATIONS AT TAKE-OFF SPEEDS OF NOT MORE THAN 200 MPH AND LANDING SPEEDS OF NOT MORE THAN 185 MPH.ON ALL TYPES OF RUNWAYS.

THE TIRE SHALL WITHSTAND WITHOUT FAILURE THE FOLLOWING TESTS:

(1) DYNAMIC TEST - THE TIRE SHALL SATISFACTORILY WITHSTAND 50 CYCLES OF TEST "A" FOLLOWED BY 100 CYCLES OF TEST "B" WITHOUT EVIDENCE OF FAILURE. IF A 14 PLY RATING TUBELESS TIRE OF AN APPROVED MIL-T-5041 CONSTRUCTION IS USED, ONLY TEST "A" NEED BE MADE.

TEST A - THE TIRE SHALL BE LANDED AGAINST A FLY WHEEL ROTATING AT A PERIPHERAL SPEED OF 200 MPH (174 KNOTS), THE FLY WHEEL SPEED SHALL THEN BE DECREASED UNTIL A ROLL DISTANCE OF 9000 FEET HAS BEEN COVERED, AT WHICH TIME THE TIRE SHALL BE UNLANDED. THE AVERAGE DECELERATION RATE SHALL BE 4.5 FT/SEC/SEC BETWEEN 200 AND 100 MPH, AND IS UNSPECIFIED BELOW 100 MPH. THE TIRE LOAD SHALL BE INCREASED to 1000 LBS IN 2 TO 4 SECONDS AFTER LANDING AND THEN FURTHER INCREASED LINEARLY WITH TIME TO A VALUE OF 11,000 LBS IN 49 TO 54 SECONDS AFTER LANDING. THE LOAD SHALL THEN BE MAINTAINED AT 11,000 LBS UNTIL THE TIRE IS UNLANDED. THE TIRE DEFLECTION AT RATED LOAD ON FLY WHEEL SHALL BE THE SAME AS OBTAINED WITH THE RATED LOAD AND INFLATION PRESSURE ON A FLAT PLATE. TEST B - THE TEST CYCLE SHALL BE IDENTICAL TO THE LOW SPEED (90 TO 0 MPH) DYNAMIC TEST IN MIL-T-5041. THE TIRE DEFLECTION AT RATED LOAD ON THE FLY WHEEL SHALL BE THE SAME AS OBTAINED WITH THE RATED LOAD AND INFLATION PRESSURE ON A FLAT PLATE.

(2) BURST TEST - FOLLOWING THE ABOVE DYNAMIC TESTS THE SAME TIRE SHALL BE SUBJECTED TO A HYDROSTATIC BURST TEST. THE PRESSURE SHALL BE INCREASED UNTIL THE TIRE FAILS AND THE FAILING PRESSURE REPORTED IN THE QUALIFICATION TEST REPORT.

QUALIFICATION TEST REPORT - THE QUALIFICATION TEST REPORT SHALL LIST THE RESULTS OF ALL QUALIFICATION TESTS AND THE CONSTRUCTION DETAILS OF THE QUALIFICATION TEST SAMPLE IN THE GENERAL FORM SHOWN IN FIGURE 6 OF MIL-T-5041 WITH DIMENSIONS LISTED AT RATED INFLATION. THE REPORT SHALL INDICATE THE MANUFACTURER'S TEST NUMBER TWO (2) COPIES OF THE QUALIFICATION TEST REPORT, TOGETHER WITH THE DATA AND MATERIAL SPECIFIED ABOVE AND IN MIL-T-5041 SHALL BE SUBMITTED TO THE NAVAL AIR SYSTEMS COMMAND, WASHINGTON, DC 20361 ATTENTION: AIR-53032