1、4 - MSL4LbL REV A 26 = 7777732 0008340 b W THE TIRE SHALL BE IN ACCORDAYCE UITH THE APPLICABLE REQUIREMENTS OF SPECIFICATION MIL-T-5041 EXCEPT AS SPECIFIED HEREIN UAVY - AS STATIC VERT INFL BURST BEAD STATIC MOLD PLY LOAD LOAD PRESS. PRESS. WIDTH WEIGHT UNBAL. SKID DEFLEC. SIZE RATING RATING LBS. PS
2、I PSI INCH POUNDS OZ.-IN. TREAD DEPTH +3% ROCUREMENTSPECIFICATION SUPERSEDES: MIL-T-5041 - 1/ LBS * MIN RATED MIN 2/ MAX MAX MRX - 3/ MIN -4% SHEET 1 OF 2 22 x 6.75-10 18TL 10,600 46,390 245 980 2.05 26.0 10 RIB .26 32% - 1/ TL - TUBELESS TIRE 21 TESTED TIRE OR NEW 3/ AT LEAST FOUR, BUT NOT MORE THA
3、N SEVEN CONTINUOUS RIBS. - THE GROOVES SHRLL BE SHAPED SUCH THAT FOREIGN OBJECTS WILL NOT BECOME TRAPPED BETWEEN THE RIBS. TIRE DATA (IEiCH) INFLATED OUTSIDE INFLATED SECTION INFLATED SHOULDER INFLATED SHOULDER DIAMETER WIDTH DIAMETER UIOTH MIN HAX MIN MAX MX MAX 21.35 22.00 6.35 6.75 19.85 5.95 RIM
4、 DATA (INCH) WIDTH FLANGE LEDGE LEDGE FLANGE HEEL FLANGE BETWEEN WIDTH DIAMETER WIDTH HEIGHT RADIUS RADIUS FLANGES 5.50 I75 10.00 2.05 1 .o0 .so I 625 - - 7 - - THE TIRE COVERED BY THIS DRAWING SHALL BE SUITABLE FOR USE AND PROVIDE REASONABLE SERVICE LIFE OURING ALL NORMAL OPERATIONS AT TAKEOFF AND
5、LANDING SPEEDS INDICATED HEREIN ON ALL TYPES OF RUNWAYS AND ON AIRCRAFT CARRIERS. TEST TIRE NUMBER 1 : BY TEST F SHALL CONSECUTIVELY WITHSTAND THE FOLLOUING TEST SPECTRUM IN ALPHABETICAL SEQUENCE FOLLOWED MINIMUM BURST PRESSURE FOR TEST F SHALL BE 980 PSI: TEST A B C D E CYCLES 60 60 1 15 20 TEST TI
6、RE NUMBER 2: FOLLOWED BY TEST F. TEST TIRE NUMBER 3: TEST A TAXI- TAKEOFF - THE TIRE SHALL BE TAXIED ON THE FLYWHEEL AT 23 MPH FOR 10,000 FEET WTIH 4000 POUNDS LOAD. COMPLETION OF THE TAXI ROLL, THE FLYWHEEL SWILL THEN IhYEDIATELY BE ACCELERATED AT AN AVERAGE RATE OF 12.7 FT/SEC/SEC FROM 23 PPH TO A
7、 SPEED OF 75 MPH AND THEN CONTINUED AT AN AVERAGE RATE OF 6.25 FT/SEC/SEC FROM 75 MPH TO A SPEED OF 201 MPH. 35 TO 36 SECONDS. THE INIZIAL LOAD OF 4000 POUNDS SHALL BE DECREASED LINEARLY WITH TIRE TO 2200 POUNDS AT THE TIME THE TIRE IS UNLANDED. SHALL BE SUBJECTED TO TEST G FOLLOWED BY FIFTEEN CYCLE
8、S OF TEST A AND FIFTEEN CYCLES OF TEST B RESULTS OF TEST F SHALL BE INCLUDED IN THE QUALIFICATION TEST REPORT FOR INFORMATION. SHALL BE SUBJECTED TO TEST H. UP01 THE TIRE SWILL BE UNLANDED AFTER A TAKE-OFF ROLL DISTANCE OF 5750 FEET HAS BEEN COVERED IN APPROXIMATELY TEST B FLYI,IHEEL SPEED SHALL THE
9、N BE DECREASED UNTlL A ROLL DISTANCE OF APPROXIMATELY 2960 FEET HAS BEEN COVERED, DECELERATION RATE SHALL BE 2.02 FTISECISEC BETWEEN 127 MPH AND 116 MPH THEN CONTINUED AT AN AVERAGE DECELERATION RATE Of 6.97 FT/SEC/SEC BETWEEN 116 MPH AND 80 MPH THEN CONTINUED AT AN AVERAGE DECELER4TION RATE OF 13.0
10、2 FT/SEC/SEC BETWEEN BO MPH AND O MPH. INCREASED TO 8800 POUNDS WHEN THE TIRE IS STOPPED AFTER A TOTAL TIME OF 24 SECONDS. LANDING CYCLE, THE TIRE SHALL BE TAXIED ON THE FLYWHEEL AT 23 HPH FOR 10,000 FEET WITH 3700 POUNDS LOAD. TEST C HOWEVER, THE TIRE LOAD SHALL BE INCREASED TO 2000 POUNDS IN 2 SEC
11、ONDS AFTER LANDING AND THEN LINEARLY INCREASED TO 12,000 POUNDS WHEN THE TIRE IS STOPPED AFTER A TOTAL TIME OF 24 SECONDS. ON THE FLYWHEEL AT 23 MPH FOR 10,000 FEET WITH 5,500 POUNDS LOAD. LANDING-TAXI - THE TIRE SHALL BE LAIIDED AGAINST A FLYWHEEL ROTATING AT A PERIPHERAL SPEED OF 127 MPH. THE THE
12、AVERAGE THE TIRE LOAD SHALL BE INCREASED TO 2000 POUNDS IN 2 SECONDS AFTER LANDING AND THEN LINEARLY IMMEDIATELY FOLLOUING THE OVERLOAD LANDING-TAXI - TIME, ACCELERATION, VELOCITY AND DISTANCES SAME AS TEST B. IMMEDIATELY FOLLOWING THE LANDING CYCLE, THE TIRE SHALL BE TAXIED TEST D CATAPULT TAKEOFF
13、- THE TIRE SHALL BE LANDED AGAINST A FLYWHEEL ROTATING AT A PERIPHERAL SPEED OF 106 MPH WITH 17,500 POUNDS LOAD FOR 300 FEET AND THEN UNLANDED. 320 PSI FLAT PLATE INFLATION PRESSURE SHALL BE USED FOR THIS TEST. ENTIRE STANDARD REVISED h I- - a -t r- e O z UI N . _. Other Cust TIRE, PNEUMATIC, AIRCRA
14、FT 22 x 6.75-10 (NAVY) PROJECT NO, 262D-N237 PREVIOUS EDITIONS OF THIS FORM ARE OBSOLETE. ID 1“1672-1 (Lirnlleclccoordinalion) DISTRIBUTION STATEMENT A., Approved for publlc release; dlstributlon is unllmlted. AMSC NIA -% ._ - .- f- -F _ Provided by IHSNot for ResaleNo reproduction or networking per
15、mitted without license from IHS-,-,-FED.SUPCMSS 2620 )ihsiCuat . ROCUREYENTSPECIFICATION HIL-T-5O41 TEST E YAHE0 LANDING TEST - THE TIRE SHALL BE SUWECTED TO 10 CYCLES OF TEST E1 ANO 10 CYCLES OF TEST E2 FOR A TOTAL aF 20 CYCLES. MS14161(AS) TIRE, PNEUMATIC, AIRCRAFT 22 x 6.75-10 (NAVY) SUPERSEDES:
16、SHEET 2 OF 2 TEST 1 PKTELE G EE TIRE YAW ANGLE RELATIVE TO THE DYNAWMETER. THE TIRE LAHDINB LOAD SHALL THEN BE INCREASE0 TO 8000 POUNDS. WICH TIME THE TIRE SHALL BE UNLANDED. 10 CYCLES - THE TIRE SHALL BE LANDED AGAINST A FLYUHEEL ROTATING AT A PERIPHERAL SPEED OF 120 MPH WITH A THE 8000 POUND LOA0
17、SHALL BE MAINTAINED FOR A MINIMUH ROLL DISTANCE OF 200 FEET AT 120 MPH AFTER - TEST E2 Ji0 CYCLES1 - SAME AS E1,EXCEPT THE 5 GEGREE YAW ANGLE SHALL BE APPLIED IN THE OPPOSITE DIRECTION. - TEST F BURST TEST - THE TIRE SHALL BE SUBJECTEDTO A HYDROSTATIC BURST TEST. THE TIRE FAILS. QUALIFICATIOH TEST R
18、EPORT. THE PRESSURE SHALL BE INCREASED UNTIL THE FAILING PRESSURE, DESCRIPTION OF FAILURE AND LOCATION OF FAILURE SHALL BE REPORTED IN THE TEST 0 STOCK OR ARRESTING GEAR CABLE WITH A VERTICAL LOAD OF 46,390 POUNDS. IMEDIATELY FOLLOHING THE RELEASE OF THIS LOAD, THE TIRE SHALL BE SUBJECTED TO THE SAH
19、 LOADING COROITION AT A LOCATION 180 DEGREES IN ROTATICN FROII THE INITIAL POINT OF LOADING. BRUISE TEST - A TIRE INFLATED TO 320 PSI SHALL BE LOADED AGAINST A 1-3/8 DIAMETER LENGTH OF PLAIN ROUND BAR TEST N T7,600 POUND VERT- AND 8,000 POUND SIDE LOAD AND HEL0 FOR 3 SECONDS MINIMVH. LOSS, BEAD U!iS
20、EATING OR TIRE FAILURE. CWEINED LOAD TEST .I A TIRE INFLATED TO 320 PSI SHALL BE SIMULTANEOUSLY STATIC LOADED HITH A CWBINATION THERE SHALL BE NO SLIPPAGE, UALIFICATION TEST REPORT - THE QUALIFICATION TEST REPORT SHALL LIST THE RESULTS OF ALL QUALIFICATION TESTS ANO &l3STRUQIO$ OETAILS()TiHE QUALIFI
21、CATION TEST SAMPLE IN THE GENERAL FORM SHOWH IN FIGURES Z AND 3 OF MIL-T-5041. THE REPORT SHALL LIST THE PANUFACTURERS TEST NUHBER. TOGETHER WITH THE DATA ANO MATERIAL SPECIFIED ABOVE ANO IN MIL-T-5041 I ALONG WITH INFLATED TIRE PROFILES AT 245 AND 320 PSI, TO THE NAVAL AIR SYSTEHS CWND, WASHINGTON,
22、 OC 20361, ATTN: AIQ 53032. SUBMIT 2 COPIES OF THE QUALIFICATIOR TEST REPORT, NOTES: 1. REFERENCED DOCUMENTS SHALL BE OF THE ISSUE IN EFFECT ON DATE OF INVITATION FOR BIDS, OR REQUEST FOR PROPOSAL EXCEPT THAT REFERENCE ADOPTE0 INDUSTRY STANOAROS SHALL GIVE THE DATE OF THE ISSUE ADOPTED. FOR DESIGN F
23、EATURE PURPOSES, THIS STANDARD TAKES PRECEDENCE OVER PROCUREHENT DOCUMENTS REFEREtiCED HEREIN. 2. .A# TITLE I MILITARY STANDA IAVY - AS N c) a - ul c W W L Y) w Y) w ! z L i 3 P Y c P 3 n z $ ? I l - PREVIOUS LOITIONS Of 1HIS FORM ARE OQUHETL DD1“1672-1 (UICWLW *U.& QOVERNMENT PRINTINQ OFFICE 1986 - 60&036/40802 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
