Wheel a320 wheels
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Description
Customer : AXMType : A318/A319/A320/A321 Rev. Date : Feb 01, 2016 Manual : AMM Selected applicability : ALL 32-41-00 - WHEELS ** ON A/C ALL 32-41-00 - WHEELS 32-41-00 PB 001 CONF 00 - WHEELS - DESCRIPTION AND OPERATION 1. Component Location A. Main Gear Wheels (Ref. Fig. Main Gear Wheels - Component Location SHEET 1) A A A EXAMPLE WHEEL-MLG,4 2650GM WHEEL-MLG,3 2652GM WHEEL-MLG,2 2649GM WHEEL-MLG,1 2651GM N_MM_324100_0_CAM0_01_02 Figure 32-41-00-11800-A / SHEET 1/1 - Main Gear Wheels - Component Location ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Page 1 of 51 Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01, 2016 Manual : AMM Selected applicability : ALL 32-41-00 - WHEELS FIN FUNCTIONAL DESIGNATION 2651GM WHEEL-MLG, 1 2649GM WHEEL-MLG, 2 2652GM WHEEL-MLG, 3 2650GM WHEEL-MLG, 4 B. Nose Gear Wheels (Ref. Fig. Nose Gear Wheels - Component Location SHEET 1) PANEL ZO NE ACCESS DOOR 731 731 741 741 ATA REF 32-41-11 32-41-11 32-41-11 32-41-11 A A WHEEL-NLG,10 2660GM WHEEL-NLG,9 2659GM N_MM_324100_0_EAM0_01_01 Figure 32-41-00-13800-A / SHEET 1/1 - Nose Gear Wheels - Component Location ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Page 2 of 51 Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01, 2016 Manual : AMM Selected applicability : ALL 32-41-00 - WHEELS FIN FUNCTIONAL DESIGNATION 2659GM WHEEL-NLG, 1 2660GM WHEEL-NLG, 2 2. Component Description A. Main Gear Wheel 2649GM , 2650GM , 2651GM , 2652GM (Ref. Fig. Main Gear Wheel SHEET 1) PANEL ZO NE ACCESS DOOR 711 711 ATA REF 32-41-12 32-41-12 FUSE PLUGS MELTING POINT :(361°F) 183°C HEAT SHIELD INFLATING VALVE VENT PORTS FUSE PLUGS MELTING POINT :(572°F) 300°C BALANCING WEIGHT DRIVING KEYS N_MM_324100_0_AAM0_01_00 Figure 32-41-00-13200-A / SHEET 1/1 - Main Gear Wheel ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Page 3 of 51 Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01, 2016 Manual : AMM Selected applicability : ALL 32-41-00 - WHEELS (Ref. Fig. Main Gear Wheel SHEET 1) FORGED ALUMINUM WHEEL HALVES FUSE PLUG INFLATING VALVE RETAINING RING WASHER SLEEVE TIMKEN BEARINGS GREASE SEAL PLUG (FOR TPIS) DRIVING KEYS O-RING N_MM_324100_0_ABM0_01_00 Figure 32-41-00-13300-A / SHEET 1/1 - Main Gear Wheel ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Page 4 of 51 Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01, 2016 Manual : AMM Selected applicability : ALL 32-41-00 - WHEELS The wheels consist of two forged half-wheels made of light alloy. They are attached together with bolts made of high-tensile steel and self-locking nuts. An O-ring seal is put between the two half-wheels. The wheels are equipped with: · taper roller bearings with protective seals, · drive keys for the brake rotor disks, · six fuse plugs which deflate the tire in the event of excessive brake overheat and thus protect against tire burst because of excessive pressure, · one standard inflating valve which you can replace by a valve with an incorporated pressure indicator (PSI type), · a provision for installation of a transducer for the Tire Pressure Indicating System (optional system). Each wheel is installed on the axle with an axle sleeve. Characteristics: · weight: 60.6 kg max. · melting point of the fuse plug: . first set, inside keys: 300 deg.C (572.00 deg.F), . second set, on wheel web: 183 deg.C (361.40 deg.F). These wheels can be equipped with tires of following dimensions: · 46X17 R20 for radial tires · 46X16-20, 49X17-20, 49X19-20 for bias tires. But as the BSCU and the aircraft pin programming depend on the tire dimension (stopping distance, anti skid tuning), you must install the tire corresponding to the aircraft configuration (pin programming, MLG door podger,...). The tire mixability configurations which are authorized are shown in the AMM Task 32-41-00-910-001. ** ON A/C 001-050, 102-105, 108-108, 110-121, 123-300, 501-701, 703-703, 707-708, 710-710, 715-750 EMB SB 00-1108 for A/C 001-006, 102-105, 108-108, 110-121, 123-139, 141-154 EMB SB 00-1152 for A/C 104-105, 117-117, 135-135, 137-137, 140-140, 142-142, 144-144, 146-146, 149-149, 151-151, 153-155, 158-158, 164-164, 168-168, 170-170, 178-180, 182-183 Tire inflation pressures: NOTE: The table below shows all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. ------------------------------------------------------------------------------! A/C WEIGHT ! TIRE DIMENSIONS ! INFLATION PRESSURE ! ! MTOW ! ! UNLOADED / LOADED ! ! ! ! BARS (PSI) BARS (PSI)! !-------------------------!-------------------------!-------------------------! ! 73.5T / 75.5 T ! 46 X 17 R20 ! 13.3 (193) / 13.8 (200) ! ! ! 46 X 16 - 20 ! 13.3 (193) / 13.8 (200) ! ! ! 49 X 17 - 20 ! 11.0 (160) / 11.4 (165) ! ! ! 49 X 19 - 20 ! 9.9 (144) / 10.3 (149) ! ------------------------------------------------------------------------------** ON A/C 801-850 Tire inflation pressures: NOTE: The table below shows all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. ------------------------------------------------------------------------------Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Page 5 of 51 ALL RIGHTS RESERVED.8 (200) ! ! ! 49 X 17 .S.3 (193) / 13.4 (165) ! ! ! 49 X 19 .Customer : AXM Type : A318/A319/A320/A321 Rev.20 ! 13.WHEELS ! A/C WEIGHT ! TIRE DIMENSIONS ! INFLATION PRESSURE ! ! MTOW ! ! UNLOADED / LOADED ! ! ! ! BARS (PSI) BARS (PSI)! !-------------------------!-------------------------!-------------------------! ! 73. Nose Gear Wheel SHEET 1) PREFORMED PACKING WASHER BOLT NUT OUTER HALF BEARING RING RETAINING SEAL INNER HALF BEARING OUTER HALF BEARING WASHER SCREW CAP-ASSY INNER HALF BEARING VALVE ASSY WHEEL HALF ASSY INNER WHEEL HALF ASSY OUTER N_MM_324100_0_CEM0_01_00 Figure 32-41-00-14000-C / SHEET 1/1 .9 (144) / 10.20 ! 9. Date : Feb 01. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .5T ! 46 X 17 R20 ! 13. CONFIDENTIAL AND PROPRIETARY DOCUMENT.20 ! 11. 2660GM (Ref. Nose Gear Wheel 2659GM .0 (160) / 11.A.3 (149) ! ------------------------------------------------------------------------------** ON A/C ALL B. 2016 © AIRBUS S.Nose Gear Wheel ** ON A/C ALL Print Date: May 21.3 (193) / 13. Fig.8 (200) ! ! ! 46 X 16 . Page 6 of 51 . 146-146. They are attached together with bolts made of high-tensile steel and self-locking nuts. 144-144. 141-154 EMB SB 00-1152 for A/C 104-105.3 (178) ! ! ! 30 X 8. The landing gear manufacturer supplies the axle sleeve installed between the wheel and the axle. 140-140. 151-151.3 (178) ! ------------------------------------------------------------------------------** ON A/C ALL Figure 32-41-00-11800-A / SHEET 1/1 . 707-708.15 ! 11.Component Location Figure 32-41-00-14000-C / SHEET 1/1 . 149-149. including hub cap. Characteristics: · weight: 15. 182-183 Tire inflation pressure: NOTE: The table below shows all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes.8 (171) / 12.8 (171) / 12. The wheels are equipped with: · taper roller bearings with protective seals. 501-701.8 R15 radial tires (basic) or 30 X 8. 142-142.15 ! 11. ALL RIGHTS RESERVED. 178-180. ------------------------------------------------------------------------------! A/C WEIGHT ! TIRE DIMENSIONS ! INFLATION PRESSURE ! ! MTOW ! ! UNLOADED / LOADED ! ! ! ! BARS (PSI) BARS (PSI)! !-------------------------!-------------------------!-------------------------! ! 73. 117-117.S.5T / 75.WHEELS The wheels consist of two forged half-wheels made of light alloy. 2016 © AIRBUS S. · one overpressure relief valve. It is possible to use either 30 X 8. 153-155. 703-703. 108-108. 715-750 EMB SB 00-1108 for A/C 001-006.Main Gear Wheel Figure 32-41-00-13800-A / SHEET 1/1 .8 (171) / 12. 135-135.8 R15 ! 11. 137-137.Main Gear Wheels .5T ! 30 X 8.8 (171) / 12. 168-168.Nose Gear Wheels . 108-108. 164-164. ** ON A/C 001-050.3 (178) ! ------------------------------------------------------------------------------** ON A/C 801-850 Tire inflation pressure: NOTE: The table below shows all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. An O-ring seal is put between the two half-wheels. · a provision for installation of a transducer for the Tire Pressure Indicating System (optional system). 158-158. Date : Feb 01. CONFIDENTIAL AND PROPRIETARY DOCUMENT. · one standard inflating valve which you can replace by a valve with an incorporated pressure indicator (PSI type). ------------------------------------------------------------------------------! A/C WEIGHT ! TIRE DIMENSIONS ! INFLATION PRESSURE ! ! MTOW ! ! UNLOADED / LOADED ! ! ! ! BARS (PSI) BARS (PSI)! !-------------------------!-------------------------!-------------------------! ! 73. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .8 .Customer : AXM Type : A318/A319/A320/A321 Rev. 102-105. 123-300. 110-121. 123-139. 102-105.95 kg.8 .A. 110-121.Nose Gear Wheel Print Date: May 21.8 -15 conventional tires (option) on these wheels. 170-170.Component Location Figure 32-41-00-13200-A / SHEET 1/1 .8 R15 ! 11. 710-710.3 (178) ! ! ! 30 X 8.Main Gear Wheel Figure 32-41-00-13300-A / SHEET 1/1 .5T ! 30 X 8. Page 7 of 51 . CONFIDENTIAL AND PROPRIETARY DOCUMENT.MAINTENANCE PRACTICES TASK 32-41-00-910-001-A Tire Mixability Precautions CAUTION: MAKE SURE THAT YOU OBEY THE SPECIFIED MIXABILITY CONDITIONS. Inspection/Check of the Tire Pressure Radial and Bias Tire Profiles Installed on Same Wheel Axle SHEET 1 Print Date: May 21.S. 1.PREVENT CORRECT OPERATION OF THE BRAKING SYSTEM (DECREASED PERFORMANCE OR NO BRAKING) . ALL RIGHTS RESERVED. Referenced Information REFERENCE DESIGNATION (Ref.A.PREVENT FREE FALL EXTENSION OF THE LANDING GEAR. Page 8 of 51 . 2016 © AIRBUS S. 32-41-00-210-003-A). Reason for the Job This procedure gives the tire mixability conditions authorized on aircraft. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Customer : AXM Type : A318/A319/A320/A321 Rev. ONLY THE SPECIFIED CONFIGURATIONS ARE PERMITTED BECAUSE OTHER CONFIGURATIONS CAN POSSIBLY: . Date : Feb 01.WHEELS . any other configuration is forbidden. 2 Job Set-up Information A.WHEELS 32-41-00 PB 201 CONF 00 . A.STOPPING DISTANCE.WHEELS NOTE : THE MAIN REQUIREMENT FOR MIXABILITY IS THE COMPATIBILITY OF THE LOADED RADDII.G. Date : Feb 01.Radial and Bias Tire Profiles Installed on Same Wheel Axle ** ON A/C ALL Print Date: May 21. 2016 Manual : AMM Selected applicability : ALL RADIAL MAX OD RADIAL BIAS MAX OD BIAS SLR BIAS MAX OD 32-41-00 . A SMALL DIFFERENCE IS POSSIBLE BETWEEN THE UNLOADED OUTSIDE DIAMETER (OD) OF THE TWO TIRES. THEREFORE WHEN A RADIAL TIRE IS INSTALLED WITH AN EQUIVALENT BIAS-PLY TIRE (E. N_MM_324100_2_AAM0_01_00 Figure 32-41-00-991-02900-A / SHEET 1/1 . THIS DIFFERENCE HAS NO EFFECT ON: .Customer : AXM Type : A318/A319/A320/A321 Rev. Page 9 of 51 . THEY HAVE THE SAME LOADED RADII (SLR).ANTI-SKID TUNING. 46X17R20 WITH 46X16-20). HOWEVER. .S. CONFIDENTIAL AND PROPRIETARY DOCUMENT. ALL RIGHTS RESERVED. 2016 © AIRBUS S. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . P/N SR11263T.TIRES. 2016 © AIRBUS S. Michelin P/N M04201 and P/N M08201 with . Goodyear P/N 309Q62-1 with P/N 309Q62-2 NOTE: : No other configurations of radial tire mixing are permitted on the NLG (2) Bias tires · You can mix these bias tires : .WHEELS 3. Subtask 32-41-00-860-054-A B. Job Set-up Subtask 32-41-00-941-054-A A. because this can cause an unbalance condition. SB A320-32-1007). CONFIDENTIAL AND PROPRIETARY DOCUMENT.20 and 46 x 17 R20 may be mixed without restriction. P/N SR11262T. 4. Date : Feb 01. Page 10 of 51 . Procedure Subtask 32-41-00-860-053-J A. Tire Mixing on the NLG NOTE: The mixing of bias tires with radial tires is not permitted on the NLG . Tire Mixing on the MLG (Ref.Customer : AXM Type : A318/A319/A320/A321 Rev.WHEELS . (b) For Goodyear radial tires you can mix only: . Sumitomo P/N SR11261T. You can mix 46 x 17 R20 and 46 x 16 -20 tires that are approved for use on your aircraft (from the same or different manufacturers). NOTE: : No other configurations of bias tire mixing are permitted on the NLG Figure 32-41-00-991-02900-A / SHEET 1/1 . Bridgestone P/N APR05140 and P/N APR05145 with . AMM TASK 32-41-00-210-003) . (1) Radial tires (a) You can mix these radial tires : .Radial and Bias Tire Profiles Installed on Same Wheel Axle 32-41-00 PB 401 CONF 00 . Operation is allowed with or without cooling fans. Michelin MATC P/N 039-539-0 and P/N 039-539-1. NOTE: Tire pressures must be checked to the specified values (Ref.DEACTIVATION/REACTIVATION TASK 32-41-00-040-001-A Nose Wheel Hubcap Deactivation Print Date: May 21. Fig.GENERAL OPERATING PROCEDURES (Ref.S. General (1) Full information is given in LANDING GEARS. ALL RIGHTS RESERVED. Radial and Bias Tire Profiles Installed on Same Wheel Axle SHEET 1) (1) Allowed mixing 46 x 16 . The allowed tire mixing given is applicable to new and retreaded tires.A. A. Test and Support Equipment REFERENCE No specific No specific No specific B. Fixtures. ALL RIGHTS RESERVED. Page 11 of 51 .Customer : AXM Type : A318/A319/A320/A321 Rev. Reason for the Job CDL 32-03 Nose Wheel Hubcap (old CDL reference: 32-2) 2 Job Set-up Information A. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .S. QTY AR AR AR DESIGNATION CHOCK .WHEELS WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. Date : Feb 01. 2016 © AIRBUS S. Tools.WHEEL(S) SAFETY CLIP . CONFIDENTIAL AND PROPRIETARY DOCUMENT.CIRCUIT BREAKER WARNING NOTICE(S) Referenced Information REFERENCE DESIGNATION Nose Wheel Hubcap Deactivation/Reactivation SHEET 1 Print Date: May 21. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS. 1. WHEELS A A 10GV A 1 11GV 3 2 N_MM_324100_4_AAM0_01_00 Figure 32-41-00-991-01000-A / SHEET 1/1 . Date : Feb 01. Page 12 of 51 .Nose Wheel Hubcap Deactivation/Reactivation ** ON A/C ALL Print Date: May 21.Customer : AXM Type : A318/A319/A320/A321 Rev. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . 2016 © AIRBUS S.A. ALL RIGHTS RESERVED.S. Page 13 of 51 .WHEELS 3.daN (35. Close-up Subtask 32-41-00-942-052-A A. 2016 © AIRBUS S. Job Set-up Subtask 32-41-00-941-052-A A. ALL RIGHTS RESERVED.4 and 0. Reason for the Job CDL 32-03 Nose Wheel Hubcap (old CDL reference: 32-2) 2 Job Set-up Information A.CIRCUIT BREAKER WARNING NOTICE(S) Torque wrench: range to between 0. CONFIDENTIAL AND PROPRIETARY DOCUMENT. QTY AR AR AR DESIGNATION CHOCK . (2) Remove the hubcap (1).13 lbf. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . (2) Remove the wheel chocks at the main landing gear.Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01.S.40 and 45. Remove the safety devices: (1) Remove the warning notice from the cockpit.A. 1. (3) Make an entry in the log book. (2) Install the CHOCK . 5.51 m.WHEEL(S) at the main landing gear. TASK 32-41-00-440-001-A Nose Wheel Hubcap Reactivation WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. Safety Precautions (1) On the panel 400VU: · put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear control lever. Fig. Fixtures.in) Referenced Information REFERENCE DESIGNATION Nose Wheel Hubcap Deactivation/Reactivation SHEET 1 Print Date: May 21. Nose Wheel Hubcap Deactivation/Reactivation SHEET 1) Subtask 32-41-00-040-051-A A. Procedure (Ref. 4. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS. Test and Support Equipment REFERENCE No specific No specific No specific No specific B. Tools. Deactivation of the Nose Wheel Hubcap (1) Remove the screws (2) and the washers (3).WHEEL(S) SAFETY CLIP . 4. 32-41-12-400-001-A). remove them. 4. Procedure (Ref.13 lbf. Print Date: May 21. 5. ALL RIGHTS RESERVED. Job Set-up Subtask 32-41-00-941-053-A A.40 and 45.51 m.4 and 0.Customer : AXM Type : A318/A319/A320/A321 Rev. DESIGNATION Removal of the NLG Wheel (for corrective action) Installation of the NLG Wheel (for corrective action) Job Set-up Subtask 32-41-00-941-056-A A. (2) Install the washers (3) and the screws (2).WHEEL(S) at the main landing gear.A. Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (3) Torque the screws (2) to between 0. 3. Fig. Reason for the Job MMEL 32-41-01A Nose Wheel Tie Bolt (Old MMEL ref: 32-41-01) 2 Job Set-up Information A. Close-up Subtask 32-41-00-942-053-A A.in). Check of the related Nose Wheel (1) Make sure that no broken pieces of the tie bolt are in the wheel. Page 14 of 51 . (2) Remove the warning notice(s).daN (35. Date : Feb 01.WHEELS 3. If there are pieces of the tie bolt in the wheel. Nose Wheel Hubcap Deactivation/Reactivation SHEET 1) Subtask 32-41-00-440-051-A A.WHEEL(S) at the main landing gear. (3) Remove the CHOCK . CONFIDENTIAL AND PROPRIETARY DOCUMENT. 32-41-12-000-001-A). Referenced Information REFERENCE (Ref. 2016 © AIRBUS S. (2) Install the CHOCK . 2016 Manual : AMM Selected applicability : ALL 32-41-00 . (Ref. Safety Precautions (1) On the panel 400VU: · put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear control lever. Reactivation of the Nose Wheel Hubcap (1) Install the hubcap (1).S. TASK 32-41-00-040-002-A Check of the Nose Wheel when one tie bolt is missing 1. Not applicable Procedure Subtask 32-41-00-210-073-A A. Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. NOTE: If the wheel is damaged. 32-41-12-000-001-A). Referenced Information REFERENCE (Ref. 5. AMM TASK 32-41-12-400-001) . (b) Remove and discard the two tie bolts (one on each side) adjacent to the missing one. refer to the AMM (Ref.S. AMM TASK 32-41-12-000-001) . AMM TASK 32-41-12-400-001) to replace the wheel. (2) Inspection of the wheel (a) Send the wheel to the overhaul facility. (2) Delete the entry in the log book. (3) Install a new wheel (Ref. Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. ALL RIGHTS RESERVED. 4.Customer : AXM Type : A318/A319/A320/A321 Rev. Page 15 of 51 . AMM TASK 32-41-12-000-001) and (Ref.WHEELS (2) Do a check of the wheel for damage. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Reason for the Job MMEL 32-41-01A Nose Wheel Tie Bolt (Old MMEL ref: 32-41-01) 2 Job Set-up Information A. Close-up Subtask 32-41-00-942-055-A A. 3. Close-up Subtask 32-41-00-942-059-A A. 2016 © AIRBUS S. Print Date: May 21. TASK 32-41-00-440-004-A Replacement of the Nose Wheel 1. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Date : Feb 01. (Ref. (2) Make an entry in the log book. DESIGNATION Removal of the NLG Wheel Installation of the NLG Wheel Job Set-up Subtask 32-41-00-941-064-A A. Replacement of the Wheel (1) Remove the related NLG wheel (Ref. 32-41-12-400-001-A). Not Applicable Procedure Subtask 32-41-00-440-055-A A.A. no damage is permitted. 5. (c) Refer to the applicable CMM to inspect all of the wheel for damage. Reason for the Job MMEL 32-41-02A Main Wheel Tie Bolt (Old MMEL ref: 32-41-02) 2 Job Set-up Information A. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . 32-41-11-400-006-A). 5. 32-41-11-000-006-A).S. Close-up Subtask 32-41-00-942-056-A A. (Ref.A. 4. 3. remove them. (4) Install the main wheel (Ref.WHEELS TASK 32-41-00-040-003-A Check of the Main Wheel when one tie bolt is missing 1. (2) Make an entry in the log book. refer to the AMM (Ref. DESIGNATION Removal of the MLG Wheel Installation of the MLG Wheel Removal of the MLG Wheel (for corrective action) Installation of the MLG Wheel (for corrective action) Job Set-up Subtask 32-41-00-941-057-A A. 2016 © AIRBUS S. Reason for the Job MMEL 32-41-02A Main Wheel Tie Bolt (Old MMEL ref: 32-41-02) MMEL324102A Print Date: May 21. Page 16 of 51 . (2) Make sure that no broken pieces of the tie bolt are in the wheel. AMM TASK 32-41-11-000-006) . AMM TASK 32-41-11-400-006) to replace the wheel. Date : Feb 01. Not applicable Procedure Subtask 32-41-00-210-074-A A. ALL RIGHTS RESERVED. NOTE: If the wheel is damaged. 32-41-11-400-006-A). Check of the related Main Wheel (1) Remove the related main wheel (Ref. no damage is permitted. Referenced Information REFERENCE (Ref. (Ref. (3) Do a check the wheel for damage. If there are pieces of the tie bolt in the wheel. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (Ref. AMM TASK 32-41-11-400-006) . Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items.Customer : AXM Type : A318/A319/A320/A321 Rev. AMM TASK 32-41-11-000-006) and (Ref. 32-41-11-000-006-A). TASK 32-41-00-440-005-A Replacement of the Main Wheel 1. AMM TASK 32-41-11-000-006) .THE FLIGHT CONTROL SURFACES . ALL RIGHTS RESERVED.Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .A.THE LANDING GEAR AND THE RELATED DOORS .INSPECTION/CHECK TASK 32-41-00-210-002-A Inspection/Check of the Wheels and Tires WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: . Not Applicable Procedure Subtask 32-41-00-440-056-A A. CONFIDENTIAL AND PROPRIETARY DOCUMENT.S. Referenced Information REFERENCE (Ref. Replacement of the Wheel (1) Remove the related MLG wheel (Ref. 4. 2016 © AIRBUS S. Figure 32-41-00-991-01000-A / SHEET 1/1 . (c) Refer to the applicable CMM to inspect all of the wheel for damage. AMM TASK 32-41-11-400-006) .WHEELS 2 Job Set-up Information A. 32-41-11-400-006-A). WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. (2) Inspect the associated brakes of the related wheel for damage.Nose Wheel Hubcap Deactivation/Reactivation 32-41-00 PB 601 CONF 00 . (Ref.THE FLIGHT CONTROLS . (3) Inspection of the wheel (a) Send the wheel to the overhaul facility. 5. DESIGNATION Removal of the MLG Wheel Installation of the MLG Wheel Job Set-up Subtask 32-41-00-941-065-A A.WHEELS . Page 17 of 51 . Close-up Subtask 32-41-00-942-060-A A. Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items.COMPONENTS THAT MOVE. (2) Delete the entry in the log book. (b) Remove and discard the two tie bolts (one on each side) adjacent to the missing one. (4) Install a new wheel with all the tie bolts (Ref. Print Date: May 21. 3. MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT. 32-41-11-000-006-A). 2016 Manual : AMM Selected applicability : ALL 32-41-00 . 32-41-00-910-001-A).Customer : AXM Type : A318/A319/A320/A321 Rev. 32-41-00-210-003-A).General Description SHEET 1 Radial Tire . 32-41-11-400-006-A). CONFIDENTIAL AND PROPRIETARY DOCUMENT.Tread Rubber Reversion SHEET 1 Tire Deterioration Characteristics.Blister or Bulge SHEET 1 Tire Wear and Deterioration Characteristics.Isopropyl Alcohol - Referenced Information REFERENCE DESIGNATION (Ref. 2016 © AIRBUS S. Date : Feb 01. Removal of the NLG Wheel (Ref.REMOVE THE WHEELS FROM THE AIRCRAFT.A. Reason for the Job Self explanatory 2 Job Set-up Information A. Removal of the MLG Wheel (Ref. THE LIMIT SPEED IS 225 MPH (195 KTS).S.Skid (Flat Spots) SHEET 1 Tire Deterioration Characteristics. CAUTION: IF A TIRE OVERSPEED (TIRE SPEED ABOVE THE LIMIT SPECIFIED BY THE TIRE MANUFACTURER) OCCURS DURING A TAKEOFF OR A LANDING. Consumable Materials REFERENCE (Material No.Tread Flaking and Chipping SHEET 1 Tire Wear and Deterioration Characteristics.Groove Cracking .Sectional View SHEET 1 Bias Tire .Tread cuts depth and length limits SHEET 1 Print Date: May 21.Tread Chunking SHEET 1 Tire Utilization Limits . Installation of the NLG Wheel Radial Tire .General Description SHEET 1 Bias Tire .Open Tread Splice SHEET 1 Tire Wear and Deterioration Characteristics. DO NOT APPLY A LIQUID OR GAS DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. Tire Mixability Precautions (Ref. THIS CAN CAUSE A TIRE EXPLOSION AND/OR A WHEEL RIM BURST. AND . Page 18 of 51 . Installation of the MLG Wheel (Ref.Rib Undercutting SHEET 1 Tire Wear and Deterioration Characteristics. Inspection/Check of the Tire Pressure (Ref. 32-41-12-000-001-A).Thrown Tread . A319. ALL RIGHTS RESERVED.WHEELS WARNING: LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. 08ABC1) (Material No. 1. DESIGNATION Aqueous Cleaner-Aircraft Exterior Pressure Spraying Non Aqueous Cleaner-.Peeled Rib SHEET 1 Tire Deterioration Characteristics.Chevron Cutting SHEET 1 Tire Deterioration Characteristics. ON A318. 32-41-12-400-001-A). YOU MUST IMMEDIATELY: .Sectional View SHEET 1 Tire Wear and Deterioration Characteristics SHEET 1 Tire Wear and Deterioration Characteristics.Tread Separation . 08BBD1) B. A320 AND A321 AIRBUS AIRCRAFT. 32-41-11-000-006-A).SEND THE TIRES BACK TO THE TIRE MANUFACTURER TO MAKE SURE THAT THEY ARE SERVICEABLE. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Radial Tire . CONFIDENTIAL AND PROPRIETARY DOCUMENT. ALL RIGHTS RESERVED. Date : Feb 01.General Description ** ON A/C ALL Print Date: May 21. Page 19 of 51 .WHEELS BELT STRUCTURE: METALLIC PROTECTOR BINDING LAYER N°3 BINDING LAYER N°2 TREAD BINDING LAYER N°1 BREAKER SRIPS CHAFER FLIPPER PLY CASING N°3 PLY CASING N°2 PLY CASING N°1 BEAD WIRE FLIPPER TURNED-UP TURN-UP OF PLY CASING N°2 TURN-UP OF PLY CASING N°1 -THE NUMBER OF PLY CASINGS CAN BE LESS OR MORE THAN 3 -THE NUMBER OF BINDING LAYERS CAN BE LESS OR MORE THAN 3 -THE METALLIC PROTECTOR IS OPTIONAL AND MAY NOT BE USED N_MM_324100_6_AAM0_01_00 Figure 32-41-00-991-00100-A / SHEET 1/1 . 2016 © AIRBUS S.A.S.Customer : AXM Type : A318/A319/A320/A321 Rev. A.WHEELS TREAD AREA METALLIC* PROTECTOR BEAD BEAD HEEL SIDEWALL AREA CENTER PART SEAT * : THE METALLIC PROTECTOR IS OPTIONAL. N_MM_324100_6_ABM0_01_00 Figure 32-41-00-991-00200-A / SHEET 1/1 . 2016 © AIRBUS S. Page 20 of 51 . CONFIDENTIAL AND PROPRIETARY DOCUMENT.S. ALL RIGHTS RESERVED.Customer : AXM Type : A318/A319/A320/A321 Rev. Date : Feb 01.Sectional View ** ON A/C ALL Print Date: May 21. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . AND DEPENDING ON TIRE MANUFACTURER MAY NOT BE USED ON A RADIAL AIRCRAFT TIRE.Radial Tire . General Description ** ON A/C ALL Print Date: May 21. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Customer : AXM Type : A318/A319/A320/A321 Rev.A. Date : Feb 01. ALL RIGHTS RESERVED. 2016 © AIRBUS S.WHEELS TREAD REINFORCING PLY BREAKERS TREAD CORD BODY SIDEWALL PILES CORD BODY INNERLINER BEAD HEEL FLIPPERS CHAFERS BEAD TOE PLY TURNUPS APEX STRIP FLIPPERS WIRE BEADS N_MM_324100_6_BAM0_01_00 Figure 32-41-00-991-00500-A / SHEET 1/1 . 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Page 21 of 51 .Bias Tire .S. ALL RIGHTS RESERVED.Bias Tire . 2016 © AIRBUS S. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .S.WHEELS TREAD (TIRE CROWN) TREAD RIB (TYP) TREAD GROOVE (TYP) SHOULDER AREA TREAD REINFORCEMENT GROOVE DEPTH UNDERTREAD CARCASS PLIES SIDEWALL AREA LINER SIDEWALL BEAD BUNDLES BEAD AREA BEAD TOE BEAD HEEL N_MM_324100_6_BBM0_01_00 Figure 32-41-00-991-00600-A / SHEET 1/1 . Page 22 of 51 .Customer : AXM Type : A318/A319/A320/A321 Rev.A.Sectional View ** ON A/C ALL Print Date: May 21. Date : Feb 01. CONFIDENTIAL AND PROPRIETARY DOCUMENT. WHEELS NORMAL EXCESSIVE OVERINFLATION UNDERINFLATION N_MM_324100_6_BCM0_01_00 Figure 32-41-00-991-00700-A / SHEET 1/1 . CONFIDENTIAL AND PROPRIETARY DOCUMENT. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Date : Feb 01. 2016 © AIRBUS S. Page 23 of 51 .A.Tire Wear and Deterioration Characteristics ** ON A/C ALL Print Date: May 21.Customer : AXM Type : A318/A319/A320/A321 Rev.S. ALL RIGHTS RESERVED. ALL RIGHTS RESERVED.WHEELS N_MM_324100_6_ACM0_01_00 Figure 32-41-00-991-00300-A / SHEET 1/1 .S. 2016 © AIRBUS S. Date : Feb 01. Page 24 of 51 .Customer : AXM Type : A318/A319/A320/A321 Rev.Skid (Flat Spots) ** ON A/C ALL Print Date: May 21. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .A. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Tire Wear and Deterioration Characteristics. 2016 © AIRBUS S. ALL RIGHTS RESERVED.A. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Thrown Tread .Tire Deterioration Characteristics.S.Peeled Rib ** ON A/C ALL Print Date: May 21. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Page 25 of 51 . Date : Feb 01.Customer : AXM Type : A318/A319/A320/A321 Rev.WHEELS N_MM_324100_6_ADM0_01_00 Figure 32-41-00-991-00400-A / SHEET 1/1 . Customer : AXM Type : A318/A319/A320/A321 Rev. 2016 © AIRBUS S.Tire Deterioration Characteristics.S.A.WHEELS N_MM_324100_6_BEM0_01_00 Figure 32-41-00-991-00800-A / SHEET 1/1 . ALL RIGHTS RESERVED. Date : Feb 01. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Tread Rubber Reversion ** ON A/C ALL Print Date: May 21. Page 26 of 51 . CONFIDENTIAL AND PROPRIETARY DOCUMENT. WHEELS CHEVRON CUTTING N_MM_324100_6_CHM0_01_00 Figure 32-41-00-991-03600-A / SHEET 1/1 . Date : Feb 01. ALL RIGHTS RESERVED. 2016 © AIRBUS S.S. Page 27 of 51 . CONFIDENTIAL AND PROPRIETARY DOCUMENT. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Customer : AXM Type : A318/A319/A320/A321 Rev.Chevron Cutting ** ON A/C ALL Print Date: May 21.Tire Deterioration Characteristics.A. A.WHEELS N_MM_324100_6_BFM0_01_00 Figure 32-41-00-991-00900-A / SHEET 1/1 . CONFIDENTIAL AND PROPRIETARY DOCUMENT.Rib Undercutting ** ON A/C ALL Print Date: May 21. Date : Feb 01.S. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Tire Deterioration Characteristics. ALL RIGHTS RESERVED.Groove Cracking . Page 28 of 51 .Customer : AXM Type : A318/A319/A320/A321 Rev. 2016 © AIRBUS S. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Date : Feb 01.Blister or Bulge ** ON A/C ALL Print Date: May 21. Page 29 of 51 .S. ALL RIGHTS RESERVED.A. 2016 © AIRBUS S.Customer : AXM Type : A318/A319/A320/A321 Rev. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Tire Wear and Deterioration Characteristics.WHEELS N_MM_324100_6_MCH0_01_00 Figure 32-41-00-991-03000-A / SHEET 1/1 .Tread Separation . Open Tread Splice ** ON A/C ALL Print Date: May 21. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Tire Wear and Deterioration Characteristics.A.WHEELS N_MM_324100_6_CJM0_01_00 Figure 32-41-00-991-04600-A / SHEET 1/1 .Customer : AXM Type : A318/A319/A320/A321 Rev. Page 30 of 51 . 2016 Manual : AMM Selected applicability : ALL 32-41-00 .S. 2016 © AIRBUS S. Date : Feb 01. ALL RIGHTS RESERVED. 2016 © AIRBUS S. Date : Feb 01. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .A.S. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Customer : AXM Type : A318/A319/A320/A321 Rev. ALL RIGHTS RESERVED.WHEELS N_MM_324100_6_CLM0_01_00 Figure 32-41-00-991-04700-A / SHEET 1/1 . Page 31 of 51 .Tread Flaking and Chipping ** ON A/C ALL Print Date: May 21.Tire Wear and Deterioration Characteristics. A. Page 32 of 51 .Tire Wear and Deterioration Characteristics. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Date : Feb 01.Customer : AXM Type : A318/A319/A320/A321 Rev.WHEELS N_MM_324100_6_CLN0_01_00 Figure 32-41-00-991-04800-A / SHEET 1/1 . CONFIDENTIAL AND PROPRIETARY DOCUMENT.S. 2016 © AIRBUS S. ALL RIGHTS RESERVED.Tread Chunking ** ON A/C ALL Print Date: May 21. WHEELS 12 INCHES MAX (304.Tread cuts depth and length limits ** ON A/C ALL Print Date: May 21.A. TRANSVERSE CUTS (A) TIRES WITH TRANSVERSE CUTS THAT ARE CONTAINED WITHIN A RIB AND PENETRATE INTO THE CARCASS PLIES (BIAS) OR BELT PLIES RADIAL ARE NOT SERVICEABLE. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (C) CUT IS NOT CONTAINED WITHIN ONE RIB TIRES WITH CUTS THAT DO NOT EXPOSE FABRIC ARE NOT SERVICEABLE IF THEY EXCEED THE ABOVE LIMITS.8 mm) 2 INCHES MAX (50.Customer : AXM Type : A318/A319/A320/A321 Rev. 2016 © AIRBUS S. (B) CUT PENETRATE THE CARCASS PLIES (BIAS) OR BELT PLIES (RADIAL).Tire Utilization Limits . (B) TIRES WITH CUTS THAT EXTEND ACROSS A RIB FROM GROOVE TO GROOVE WHICH ARE DEEPER THAN THE GROOVE ARE NOT SERVICEABLE. ALL RIGHTS RESERVED.7 mm) TREAD REINFORCEMENT CUT PROTECTOR PLIES 1/8 INCH MAX (3 mm) 1/8 INCH MAX (3 mm) CARCASS/BELT PLIES CIRCUMFERENTIAL CUTS TIRES WITH CUT THAT PENETRATE THE TREAD REINFORCEMENT/PROTECTOR PLIES ARE NOT SERVICEABLE IF : (A) CUT EXCEEDS THE ABOVE LIMITS. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .S. Page 33 of 51 .7 mm) 1/2 INCH MAX (12.8 mm) 1/2 INCH MAX (12. Date : Feb 01. N_MM_324100_6_BGS0_01_00 Figure 32-41-00-991-03100-A / SHEET 1/1 . · are worn equally. Fig. (4) Make sure that the valve thread is not damaged. Tire Wear and Deterioration Characteristics SHEET 1) (Ref. Not Applicable Procedure NOTE: The data given is for bias and radial tires and for all Airline Operators. (2) Make sure that the tire pressure is in the specified limits (Ref. Fig. Job Set-up Subtask 32-41-00-860-051-A A. NOTE: Refer to the limits for the use of the tires. ALL RIGHTS RESERVED. AMM TASK 32-41-00-910-001) . Subtask 32-41-00-210-070-A A. AMM TASK 32-41-12-400-001) ). Tire Deterioration Characteristics.Sectional View SHEET 1) (1) Make sure that the aircraft tires are in the correct condition to continue to operate on the aircraft. or if you can see any reinforcing material (metal or fabric).Skid (Flat Spots) SHEET 1) (Ref. AMM TASK 32-41-12-400-001) . Fig. AMM TASK 32-41-11-000-006) (Ref.Thrown Tread . AMM TASK 32-41-11-400-006) or (Ref. Page 34 of 51 . Subtask 32-41-00-210-071-A B. AMM TASK 32-41-12-000-001) (Ref. CONFIDENTIAL AND PROPRIETARY DOCUMENT.General Description SHEET 1) (Ref. · have no cuts and flat spots. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Tire Deterioration Characteristics. examine the drive shroud of the tachometer. 4. Visual Inspection of the Wheels (1) On each main gear wheel. Make sure that the tires: · have no air leaks. AMM TASK 32-41-00-210-003) . Subtask 32-41-00-210-060-A C. Tire Wear and Deterioration Characteristics.Customer : AXM Type : A318/A319/A320/A321 Rev. Fig. Date : Feb 01.Sectional View SHEET 1) (Ref.S. Description of Tire Wear Deterioration Characteristics NOTE: This data is given for information only. Visual Inspection of the Tires (Ref. AMM TASK 32-41-11-400-006) or (Ref. (3) Make sure that there are no leaks on the valves. AMM TASK 32-41-11-000-006) (Ref.WHEELS 3. · have no friction damage. Fig. (Ref.General Description SHEET 1) (Ref. Bias Tire .A. (5) If the tread is not worn equally and if it is necessary. remove the wheel and put it on the opposite axle (Ref. (3) Obey the tire mixability precautions (Ref. Fig. (2) Make sure that there are no cracks on the wheel rims. (4) Remove the wheel when the tire shows signs of a tread bulge (make a mark on the bulge before you deflate the tire) (Ref. 2016 © AIRBUS S.Peeled Rib SHEET 1) (Ref. Fully tighten the valve cap which seals the valve from dirt and leaks. Fig. AMM TASK 32-41-12-000-001) (Ref. Bias Tire . Fig. Radial Tire .Tread Rubber Reversion SHEET 1) Print Date: May 21. Radial Tire . Remove the wheel when the tire is worn to the base of any groove in one or more points. Fig. AMM TASK 32-41-00-210-003) can: · cause too much wear on the center of the tire tread. · high deflection of the tire. ALL RIGHTS RESERVED. It is an oval-shaped area in the tread (same as a flat spot) where rubber shows signs of burns (usually caused by hydroplaning on wet or icy runways).Chevron Cutting SHEET 1) (Ref. the maximum operation speed is 225 MPH (195 KTS) (Ground Speed). (4) Tread damage (a) Flat spots Flat spot are caused by locking of the wheel during braking. Fig. (c) Tread rubber reversion Tread rubber reversion is usually caused by wheel locking on wet or icy runways. (2) Uneven wear (a) Usually.S. Tire Wear and Deterioration Characteristics. hard touch down or sudden steering maneuvers (for the NLG tires). under-inflation (inflation pressure less than 90% of the nominal pressure (Refer to table of pressure) (Ref. WARNING: ALWAYS GO NEAR THE WHEELS FROM AN OBLIQUE ANGLE.Open Tread Splice SHEET 1) (Ref. Page 35 of 51 . Tire Wear and Deterioration Characteristics.Blister or Bulge SHEET 1) (Ref. Fig.Tread Separation . Tire Deterioration Characteristics. A319. IF YOU DO NOT OBEY THIS INSTRUCTION AND DAMAGE OCCURS TO THE TIRE. PIECES OF THE TIRE CAN CAUSE YOU INJURY. Fig. THIS CAN CAUSE INJURY TO PERSONS. WARNING: REMOVE THE VALVE CORE WHEN THE TIRE IS FULLY DEFLATED.WHEELS (Ref. Tire Wear and Deterioration Characteristics. (b) Peeled rib A peeled rib usually starts with a cut in the tread and causes a circumferential delamination of the tread rib away from the tire carcass. local uneven wear (depression) or local tread/sidewall rubber split. Tire Wear and Deterioration Characteristics.Customer : AXM Type : A318/A319/A320/A321 Rev. IN THE DIRECTION OF THE TIRE SHOULDERS. 2016 © AIRBUS S. AMM TASK 32-41-00-210-003) can cause: · too much tread shoulder wear. Fig. (d) Thrown tread Thrown tread is a total or partial loss of tread that lets you see the carcass plies. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . THE PRESSURE CAN EJECT OBJECTS WITH MUCH FORCE AND THUS CAUSE INJURY. REMOVAL OF THE WHEEL VALVE CORE WHEN THE TIRE IS INFLATED CAN EJECT THE CORE WITH HIGH SPEED AND FORCE. Fig. A320 and A321 aircraft. (3) Maximum speed of utilization On A318. (b) Over inflation (when the tire pressure is more than 105% of the nominal pressure (Refer to table of pressure) (Ref. Tire Deterioration Characteristics.Tread Flaking and Chipping SHEET 1) (Ref. Date : Feb 01. with subsequent heat build-up which can cause important internal tire damage. · increase the risk of Foreign Object Damage (FOD) to the tire.Tread Chunking SHEET 1) (1) Normal wear An equal wear of the tread shows that the tire maintenance was correct during the tire life.A. WARNING: DO NOT REMOVE OBJECTS FROM A PRESSURIZED TIRE.Rib Undercutting SHEET 1) (Ref. (e) Tread cuts Print Date: May 21. CONFIDENTIAL AND PROPRIETARY DOCUMENT. Early signs of tread separation can occur in the form of tread bulges.Groove Cracking . (h) Rib undercutting Rib undercutting is an extension of groove cracking caused by mechanical loading that continues below a tread rib.WHEELS The definition of cut limits is based on the service experience of each vendor. Tread chunking can be caused by high lateral loading of the tire sometimes caused by tight turning. peeled rib or thrown tread. These cracks occur at the bottom of the tread groove. The tire must be cleaned with Non Aqueous Cleaner-.S. (j) Tread chipping and chunking This is a condition that you can see at the edge of the tread rib where small quantities of rubber start to separate from the tread surface. 2 Remove the wheel and make sure that the object does not move. chemicals and hydrocarbon based products.Customer : AXM Type : A318/A319/A320/A321 Rev.S. 3 Move the wheel to a safe area. after the first flight cycle. Refer to the relevant vendor's manual for details. 2 Monitor the circular tire movement during the subsequent five flight cycles. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 08ABC1). 5 Do an inspection of the tire at the tire shop. (g) Groove cracking Groove cracking can occur after environmental aggression of the rubber (ozone attack for example) or too much mechanical loading of the tire. (b) If. Chevron cutting is usually caused by running and/or braking on cross-grooved runways. (7) Circular tire movement on the wheel: (a) Paint a continuous radial line on the tire and the wheel when the tire is installed. solvent.(Material No. push the rubber in the contaminated area. (i) Open tread splice An open tread splice is a crack in the rubber where there is separation of joint or splice.Isopropyl Alcohol . Page 36 of 51 . the circular tire movement is less than 20 degrees: 1 Keep the wheel on the aircraft. If the tire has an unwanted object in the tread or sidewall: (f) 1 Make a mark of the area where you can see the object with a crayon. 2016 © AIRBUS S. ALL RIGHTS RESERVED. (6) Contamination damage This can be caused by brake oil.A. Because of the different technologies and tire constructions. 08BBD1) and Aqueous Cleaner-Aircraft Exterior Pressure Spraying . It can caused tread chunking. Date : Feb 01. If the rubber is tacky. damage tolerance can be different for each manufacturer. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . (5) Sidewalls damage (a) Cuts or cracks on the sidewall Foreign objects on the operating surfaces frequently cause sidewall cuts. 4 Deflate the tire before you remove the object. (b) Weathering and radial cracking Weathering and cracking occur when tires are in aggressive environmental conditions.(Material No. taxiway and parking areas can cause cuts to the tires.or V-shaped cracks) usually in a tire-footprint area. After cleaning. Chevron cutting Chevron cutting is a tread damage (large number of small Z-. Foreign objects that are on the runway. tar oil. (c) Blisters and bulges They usually are a sign of separation of components. the wheel must be changed. Print Date: May 21. 707-708. 108-108. refer to the tire manufacturer specifications. NOTE: For more information. 601-604.The tread wear is at the bottom of groove at one or more points. 123-242. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . ** ON A/C ALL PRE COC COCAXM32-001 for A/C 001-008. 123-242.WHEELS (c) If. 703-703. Uneven wear If the wear limits are reached. CONFIDENTIAL AND PROPRIETARY DOCUMENT. NOTE: There is no tolerance. 710-710. 110-121. 601-604. 715-715 (1) Tread Surface CONDITION Normal wear OBSERVATION/ DAMAGE If: .A. the circular tire movement is more than 20 degrees: 1 Replace the wheel.You can see the reinforced ply (bias tire) or the protector ply (radial tire) at one or more points of the tread surface. or . 501-501. Overspeed If a tire overspeed (tire speed more than the limit specified by the manufacturer) occurs during take-off or landing.S. Date : Feb 01. 715-715 Subtask 32-41-00-210-052-A D.Customer : AXM Type : A318/A319/A320/A321 Rev. NOTE: If the aircraft is away from the main base (or maintenance base) one flight to the main base (or to a line station where a spare wheel is available) is permitted. 710-710. 503-503. 701-701. Page 37 of 51 . 108-108. Print Date: May 21. 701-701. 703-703. Send the tires back to the tire manufacturer (with the reason of removal) to make sure that they are serviceable. NOTE: If the aircraft is away from the main base (or maintenance base) one flight to the main base (or to a line station where a spare wheel is available) is permitted Remove all the wheels immediately. 102-105. Tire Utilization Limits . Remove the tire immediately. 2016 © AIRBUS S. after five flight cycles. 503-503. ACTION Remove the tire immediately. ALL RIGHTS RESERVED. 501-501. 110-121. Fig.Tread cuts depth and length limits SHEET 1) ** ON A/C ALL PRE COC COCAXM32-001 for A/C 001-008. 102-105. 2 Send the tire to the tire shop for inspection. 707-708. Tire Utilization Limits ** ON A/C ALL (Ref. . Then. it is necessary to wait three hours (for tire cooling) before you record the pressure.WHEELS (2) Tread damage DAMAGE Flat spots OBSERVATION . Print Date: May 21. 2016 © AIRBUS S.If the flat spot goes to the reinforcing ply (bias tire) or the protector ply (radial tire).If the flat spot does not go to reinforcing ply (bias tire) or the protector ply (radial tire) and if there is sufficient groove depth in the flat spot area (refer to the supplier specification).A. NOTE: It is necessary to get pieces of tread from the airport authorities and send them back to home base so that the vendor can make an analysis. Page 38 of 51 . CONFIDENTIAL AND PROPRIETARY DOCUMENT. Remove the tire.If the tread rubber reversion goes to the reinforcing ply (bias tire) or the protector ply (radial tire) or. .If there is shimmy or unbalance. Keep the tire on the aircraft. deflate the tire before removal of the wheel assembly.the cut length is more than ACTION Remove the tire immediately. Date : Feb 01.Customer : AXM Type : A318/A319/A320/A321 Rev. if necessary. . NOTE: If the tire is still inflated after the aircraft is parked. immediately. Thrown tread Tread cuts If there are no cut limits specified in the documentation and if: (1) the cut or embedded object lets you see or goes into the reinforcing ply (bias tire) or the protector ply (radial tire): .S. Remove the tire immediately. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . ALL RIGHTS RESERVED.the cut goes into the outer casing ply (bias tire) or the outer layer (radial tire). Remove the tire immediately. Remove the tire immediately. Peeled rib Tread rubber reversion During the check: . Remove the tire immediately . .The cut is in the limits of one rib and the distance between its two ends is more than 12. 2016 © AIRBUS S.the cut is in the limits of one rib and the distance between its two ends is more than 12.5 in.7 mm (0. Page 39 of 51 . Refer to the applicable vendor manual for details. Date : Feb 01.) when measured in the axial direction. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . .S.The cut length is more than 304. (2) The cut or embedded object does not go into the reinforcing ply (bias tire) or the protector ply (radial tire) : . Remove the tire when the crack goes below the rib.8 mm (12 in.) or. During the check: . Remove the tire immediately.the cut width is more than 3.175 mm (0.) or.The cut width is more than 3.8 mm (2 in.Customer : AXM Type : A318/A319/A320/A321 Rev.The tire is at the limits given for tread cuts .125 in. CONFIDENTIAL AND PROPRIETARY DOCUMENT.5 in. Because of different technologies and tire constructions. If there are no cut limits specified in the documentation and if: . Rib undercutting Open tread splice Tread If you can see the fabric ACTION Remove the tire immediately.the cut is not in the limits of one rib.) or. . ALL RIGHTS RESERVED. . .) when measured in the axial direction.groove cracking undercuts the adjacent rib. damage tolerance can be different for each manufacturer an even for each tire reference of a given manufacturer.175 mm (0.You can see the tread reinforcing ply (bias tire) or the protector ply (radial tire). Remove the tire Print Date: May 21.The cut is not in the limits of one rib.A.125 in. . Remove the tire immediately.WHEELS DAMAGE Chevron cutting Groove Cracking OBSERVATION 50.if groove cracking lets you see the reinforcing ply (bias tire) or the protector ply (radial tire) or.) or.7 mm (0. . Tire Utilization Limits . 501-501. Put marks on the damage area before you deflate the tire for easy identification and analysis by the vendor. 123-242. 102-105. Tire Utilization Limits ** ON A/C 001-050. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . ** ON A/C POST COC COCAXM32-001 for A/C 001-008.The tread wear is at the bottom of groove at one or more points. If you can see the sidewall cords Remove the tire immediately. 503-503. 707-708.Customer : AXM Type : A318/A319/A320/A321 Rev. POST COC AXM32-001: For Michelin tires. (3) Sidewall damage DAMAGE Cuts or cracks on the sidewall Weathering and radial cracking Blisters and Bulges Remove the tire immediately . 701-701. 501-501. 503-503. 703-703. Date : Feb 01. NOTE: If the aircraft is away from the main base (or maintenance base) one flight to the main base (or to a line station where a spare wheel is available) is permitted. Fig. 108-108. ALL RIGHTS RESERVED. 703-703. 710-710. 123-300. 108-108.A. 110-121. 710-710. 102-105. 108-108. 707-708. or . only for part numbers: Print Date: May 21. 715-715 (Ref. 110-121.WHEELS DAMAGE chipping and chunking OBSERVATION ACTION immediately. 707-708. ACTION Remove the tire immediately. 701-701. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 601-604.Tread cuts depth and length limits SHEET 1) ** ON A/C POST COC COCAXM32-001 for A/C 001-008.You can see the reinforced ply (bias tire) or the protector ply (radial tire) at one or more points of the tread surface. OBSERVATION If you can see the sidewall cords or if they are damaged. 110-121. 503-701. 601-604. ACTION Remove the tire immediately. Page 40 of 51 . 715-715 (1) Tread Surface CONDITION Normal wear OBSERVATION/ DAMAGE If: .S. 710-710. 123-242. 501-501. 2016 © AIRBUS S. 715-715 Subtask 32-41-00-210-052-D D. 102-105. 703-703. The tread wear is at the bottom of groove along more than 1/8 of the circumference. NOTE: There is no tolerance.M08201 (all indices) . 2016 Manual : AMM Selected applicability : ALL 32-41-00 . 2016 © AIRBUS S.You can see the reinforced ply (bias tire) or the protector ply (radial tire) along more than 1/8 of the circumference. .If the flat spot goes to the reinforcing ply (bias tire) or the protector ply (radial tire). Page 41 of 51 . Remove the tire immediately.Customer : AXM Type : A318/A319/A320/A321 Rev. Print Date: May 21.If the tread rubber reversion ACTION Remove the tire immediately. ACTION Remove the tire immediately. Remove the tire immediately.S. Peeled rib Tread rubber reversion During the check: . (2) Tread damage DAMAGE Flat spots OBSERVATION . Date : Feb 01. Keep the tire on the aircraft. or . NOTE: If the aircraft is away from the main base (or maintenance base) one flight to the main base (or to a line station where a spare wheel is available) is permitted Remove all the wheels immediately.M13901 (all indices) .If the flat spot does not go to reinforcing ply (bias tire) or the protector ply (radial tire) and if there is sufficient groove depth in the flat spot area (refer to the supplier specification). NOTE: If the aircraft is away from the main base (or maintenance base) one flight to the main base (or to a line station where a spare wheel is available) is permitted. Overspeed If a tire overspeed (tire speed more than the limit specified by the manufacturer) occurs during take-off or landing. Uneven wear If the wear limits are reached.WHEELS CONDITION OBSERVATION/ DAMAGE . CONFIDENTIAL AND PROPRIETARY DOCUMENT. Send the tires back to the tire manufacturer (with the reason of removal) to make sure that they are serviceable.M20101-01 If: .M01103-02 .A. Remove the tire immediately. ALL RIGHTS RESERVED. 2016 © AIRBUS S. Date : Feb 01.The cut length is more than 304. Then. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .7 mm (0. .8 mm (2 in. Page 42 of 51 .A.175 mm (0. NOTE: If the tire is still inflated after the aircraft is parked. Remove the tire immediately. .) or. Thrown tread Tread cuts If there are no cut limits specified in the documentation and if: (1) the cut or embedded object lets you see or goes into the reinforcing ply (bias tire) or the protector ply (radial tire): .If there is shimmy or unbalance.5 in. Remove the tire immediately .the cut width is more than 3. .the cut goes into the outer casing ply (bias tire) or the outer layer (radial tire). .) or. deflate the tire before removal of the wheel assembly.) or.Customer : AXM Type : A318/A319/A320/A321 Rev. if necessary.WHEELS DAMAGE OBSERVATION goes to the reinforcing ply (bias tire) or the protector ply (radial tire) or. (2) The cut or embedded object does not go into the reinforcing ply (bias tire) or the protector ply (radial tire) : . immediately.the cut is not in the limits of one rib.S.8 mm (12 in. . NOTE: It is necessary to get pieces of tread from the airport authorities and send them back to home base so that the vendor can make an analysis. ALL RIGHTS RESERVED. Print Date: May 21. CONFIDENTIAL AND PROPRIETARY DOCUMENT.125 in. it is necessary to wait three hours (for tire cooling) before you record the pressure.The cut width is more than ACTION Remove the tire.the cut is in the limits of one rib and the distance between its two ends is more than 12.the cut length is more than 50.) when measured in the axial direction. . . Remove the tire immediately.125 in.7 mm (0. (3) Sidewall damage DAMAGE Cuts or cracks on the sidewall Weathering and radial cracking Blisters and Bulges OBSERVATION If you can see the sidewall cords or if they are damaged.The cut is not in the limits of one rib. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Customer : AXM Type : A318/A319/A320/A321 Rev. damage tolerance can be different for each manufacturer an even for each tire reference of a given manufacturer. Rib undercutting Open tread splice Tread chipping and chunking If you can see the fabric ACTION Remove the tire immediately. Refer to the applicable vendor manual for details.The cut is in the limits of one rib and the distance between its two ends is more than 12.The tire is at the limits given for tread cuts . Page 43 of 51 . Remove the tire immediately. 2016 © AIRBUS S.) or. Date : Feb 01.175 mm (0. ALL RIGHTS RESERVED.WHEELS DAMAGE Chevron cutting Groove Cracking OBSERVATION 3. During the check: . Remove the tire when the crack goes below the rib.You can see the tread reinforcing ply (bias tire) or the protector ply (radial tire). 2016 Manual : AMM Selected applicability : ALL 32-41-00 .groove cracking undercuts the adjacent rib.S. .if groove cracking lets you see the reinforcing ply (bias tire) or the protector ply (radial tire) or. Because of different technologies and tire constructions. If there are no cut limits specified in the documentation and if: . Remove the tire immediately. If you can see the sidewall cords Remove the tire immediately.A. Remove the tire immediately . .) when measured in the axial direction.5 in. Put marks on the damage area before you Print Date: May 21. ACTION Remove the tire immediately. DESIGNATION Nitrogen Filling of the Tires Energize the Aircraft Electrical Circuits from the External Power Energize the Aircraft Electrical Circuits from the APU Energize the Aircraft Electrical Circuits from Engine 1(2) Removal of the MLG Wheel Installation of the MLG Wheel Removal of the NLG Wheel Installation of the NLG Wheel Job Set-up Subtask 32-41-00-860-052-A WARNING: DO NOT PUT COMPRESSED GAS IN CONTACT WITH YOUR SKIN. ** ON A/C ALL TASK 32-41-00-210-003-A Inspection/Check of the Tire Pressure 1. 32-41-12-000-001-A). (Ref. A. Date : Feb 01. 24-41-00-861-002-A). THIS CONDITION CAN KILL YOU. THE GAS CAN GO THROUGH THE SKIN AND MAKE BUBBLES IN THE BLOOD. Test and Support Equipment REFERENCE No specific B. (Ref.S. WARNING: LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Customer : AXM Type : A318/A319/A320/A321 Rev. 2016 © AIRBUS S.A. 3. Fixtures. Tools. 12-14-32-614-001-A). 24-41-00-861-002-A-02). DO NOT APPLY A LIQUID OR GAS DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. Safety Precautions Print Date: May 21. TIRE Work Zones and Access Panels ZONE/ACCESS 700 ZONE DESCRIPTION LANDING GEAR AND LANDING GEAR DOORS C. 24-41-00-861-002-A-01). THIS CAN CAUSE A TIRE EXPLOSION AND/OR A WHEEL RIM BURST. Page 44 of 51 . (Ref.PRESSURE. (Ref. QTY DESIGNATION 1 GAGE . 32-41-12-400-001-A). 32-41-11-000-006-A). ALL RIGHTS RESERVED. (Ref. Referenced Information REFERENCE (Ref. 32-41-11-400-006-A). Reason for the Job Refer to the MPD TASK: 324100-01 CHECK TIRE PRESSURE 2 Job Set-up Information A. (Ref. CONFIDENTIAL AND PROPRIETARY DOCUMENT.WHEELS DAMAGE OBSERVATION ACTION deflate the tire for easy identification and analysis by the vendor. (Ref. or · The wheel-mounted tire-pressure indicators. Page 45 of 51 . the pressure must be higher than the nominal value. refer to the pressure table in paragraph 4.A. do the check when the tires are cold (a tire is cold approximately three hours after its operation). Energize the aircraft electrical circuit (Ref. A CHEMICAL REACTION BETWEEN THE OXYGEN IN THE TIRES AND GASES FROM THE INNER LINER CAN CAUSE A TIRE EXPLOSION.Customer : AXM Type : A318/A319/A320/A321 Rev.B. with the aircraft weight on its wheels. ALL RIGHTS RESERVED. its pressure increases. if installed. if installed.S. (b) If possible.). and use: · A GAGE . AMM TASK 24-41-00-861-002) (Ref. To do this.MAINTENANCE PERSONNEL REMOVE THE AIR FROM THE TIRES AND INFLATE THEM WITH DRY NITROGEN BEFORE 15 HOURS TIME SERVICE. THE OXYGEN IN THE GAS USED TO INFLATE THESE TIRES MUST NOT BE MORE THAN 5% (VOLUME). AMM TASK 24-41-00-861-00 On the ECAM control panel. do a check of the pressure of all the tires of the aircraft. make sure that you do not deflate a hot tire. USE A PRESSURE REGULATOR (OR PRESSURE RELIEF VALVE) BETWEEN THE PRESSURE SOURCE AND THE TIRE. the WHEEL page comes into view and shows the tire pressures. (1) Make sure that the pressure of the tires is correct before the first flight of the day. IF THE PRESSURE SOURCE DOES NOT HAVE A PRESSURE REGULATOR. Check of the Pressure WARNING: USE ONLY DRY NITROGEN OR OTHER INERT GASES TO INFLATE THE TIRES ON THE MAIN GEAR WHEELS. The nominal value is the lower limit of the normal pressure range (given in the pressure table in paragraph 4. (2) At route stations: (a) Do a visual check of the tires on each landing gear and make sure that they have the same deflection (flatness). NOTE: If you do the check when the tires are hot.THE OXYGEN IN THE TIRES IS NOT MORE THAN 5% (VOLUME) OR .WHEELS WARNING: 4. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . MAKE SURE THAT THE PRESSURE REGULATOR IS ADJUSTED TO THE CORRECT PRESSURE FOR THE TIRE. NOTE: When a tire is hot. IF THE AIRCRAFT IS FAR FROM ITS BASE AND NO DRY NITROGEN IS AVAILABLE. push the WHEEL key: On the lower ECAM display unit. If you think that the deflection of one or two tires is not correct. YOU CAN USE AIR FOR THE SERVICING OF THE TIRES IF: . BE CAREFUL WHEN YOU INFLATE THE TIRES. Date : Feb 01. THERE IS A RISK OF INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT. AMM TASK 24-41-00-861-002) (Ref. Procedure Subtask 32-41-00-210-058-A A. or · The Tire Pressure Indicating System (TPIS). If it is necessary to do the check when the tires are hot. 2016 © AIRBUS S. If you use the TPIS: Make sure that circuit breaker 1GV is closed.B. Print Date: May 21. CONFIDENTIAL AND PROPRIETARY DOCUMENT.PRESSURE. TIRE. AMM TASK 32-41-12-400-001) .). AMM TASK 32-41-11-000-006) (Ref. replace the tire (Ref. it is necessary to adjust the tire pressure in these conditions: . record the highest tire pressure. and . · During the check. AMM TASK 32-41-12-400-001) . CONFIDENTIAL AND PROPRIETARY DOCUMENT. Then. Make sure that the pressure of all the tires is in the same range. this tire is defective (it has a leak or a hole): · Replace the tire and send it for a check (Ref. NOTE: (1): (Ref. if there is an entry in the logbook and if the pressure decreases again for this tire. Print Date: May 21. AMM TASK 32-41-11-000-006) (Ref. 1 For hot tires: a If all the pressure values are approximately the same and higher than the maximum of the normal pressure range: · Do a check of the pressure when the tires are cold. Pressure Table NOTE: The tables below show all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. higher than the minimum of the normal pressure range and less than or equal to the maximum of the normal pressure range: · No other steps are necessary. 2 For cold tires: a 3 If all the pressures are approximately the same and in the normal pressure range. Date : Feb 01. AMM TASK 32-41-11-400-006) (Ref. c If the pressure of a hot tire is less than or equal to the minimum of the normal pressure range.Customer : AXM Type : A318/A319/A320/A321 Rev. Then. · If necessary. Page 46 of 51 . replace the adjacent tire (refer to the pressure table in paragraph 4.B. b Make an entry in the logbook for this tire and monitor the tire pressure for 24 hours. AMM TASK 32-41-12-400-001) . NOTE: If there is a large temperature difference between the departure (cold) and the arrival (hot) airports. AMM TASK 32-41-12-000-001) (Ref. ** ON A/C 801-850 Subtask 32-41-00-210-059-AV B. AMM TASK 32-41-12-000-001) (Ref. 2016 © AIRBUS S. AMM TASK 32-41-11-400-006) (Ref.If the time necessary to let the temperature of the tire decrease to ambient temperature is not sufficient (a tire is cold approximately three hours after its operation).If the aircraft continues to be operated in a hot area. ALL RIGHTS RESERVED.S.WHEELS (c) Record the pressure of all the tires on a same landing gear. b If all the pressure values are approximately the same. AMM TASK 32-41-11-400-006) (Ref.A. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . in a maximum of three days. NOTE: These pressure values are for tires with the aircraft weight on the wheels. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-12-000-001) (Ref. the tire pressure at the arrival airport can be higher than the maximum of the Normal Operating Range (NOR). If the pressure of a tire is less than 90 per cent of the highest pressure on the landing gear: a Inflate the tire to the value of the tire with the highest pressure. no other steps are necessary. 4 bars less than 10. (190-200psi) From 12. you must also replace the adjacent wheel. 2016 © AIRBUS S.3 bars (170-178psi) From 11.Customer : AXM Type : A318/A319/A320/A321 Rev.If the aircraft rolled with a flat tire.A. Do not adjust 14.1 bars (144-161psi) From 0 to less than 9. AMM TASK 12-14-32-614-001) . You must measure the (180-190psi) tire pressure again the next day.8-15 30X8.9 bars ( 0-144psi) TIRE PRESSURE MLG 46X16-20 TIRE CONDITION/ACTION NECESSARY 46X17R20 More than Over-inflation.8 bars normal pressure. From 13.1 to less than 11.9 bars (178-187psi) From 11.4 to Inflate the tire to the maximum less than 13.4 to From 10.1 to Inflate the tire to the maximum less than 13.4 bars See NOTE (1) (160-180psi) From 0 to You must replace the wheel and the less than 11 bars adjacent wheel. See NOTE (1) From 11 to You must replace the wheel. If it is correct. replace the related wheel and the adjacent wheel.7 to less than 12.5 bars the tire pressure.If you cannot be sure that the wheels did not turn with the tire deflated.8 to Normal pressure range.3 to Normal pressure range. See NOTE (1) and (2) ( 0-160psi) (2) MTOW 73. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . If it is correct.8 bars the tire pressure. replace only the tire with the low pressure.8R15 More than 12. Page 47 of 51 .8 to Inflate the tire to the maximum less than 11.7 bars (161-170psi) From 9. (200-210psi) From 13. Do not adjust 12 bars 10. you must replace the wheel.WHEELS NOTE: (2): . If the tire is under-inflated again.5T TIRE PRESSURE NLG 30X8.5T TIRE PRESSURE MLG 49X17-20 More than 12 bars (174 psi) TIRE PRESSURE MLG 49X19-20 TIRE CONDITION/ACTION NECESSARY More than Over-inflation. deflate the tire to the maximum normal pressure. Date : Feb 01.3 bars normal pressure.1 bars normal pressure.If you are sure that the pressure loss occurred while the aircraft was in the parked configuration (after the aircraft stopped). less than 12.9 bars (187 psi) From 12. deflate the tire to the maximum normal pressure.3 to 12. CONFIDENTIAL AND PROPRIETARY DOCUMENT. (165-174psi) (149-157psi) From 10. From 11. Make sure that the 10. ALL RIGHTS RESERVED.S. inflate or deflate the tire to get the correct pressure (Ref. NOTE: If the tire pressure is incorrect.5 bars measurement is correct with another (210 psi) pressure gage.9 to less than 11. Print Date: May 21.8 to From 9. (1) MTOW 73. .8 bars measurement is correct with another (157 psi) pressure gage. Make sure that the 14. . 707-708. Date : Feb 01. 178-180. 168-168. NOTE: (1): ** ON A/C 001-050. CONFIDENTIAL AND PROPRIETARY DOCUMENT. 710-710. 501-701. NOTE: These pressure values are for tires with the aircraft weight on the wheels. NOTE: (2): . 715-750 (Ref. 135-135. 110-121. 108-108.3 to less than 10. ALL RIGHTS RESERVED.8 bars normal pressure. 149-149. 715-750 EMB SB 00-1108 for A/C 001-006. 164-164. 123-300.A. AMM TASK 12-14-32-614-001) . . AMM TASK 32-41-12-000-001) (Ref. 110-121.WHEELS TIRE PRESSURE MLG 49X17-20 (157-165psi) From 10. inflate or delfate the tire to get the correct pressure ** ON A/C 001-050. 102-105. 158-158.If you cannot be sure that the wheels did not turn with the tire deflated. 123-300. 102-105.1 to From 9. . 108-108. You must measure the (135-142psi) tire pressure again the next day.Customer : AXM Type : A318/A319/A320/A321 Rev.S.1 bars less than 8.5T Print Date: May 21. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . See NOTE (1) and (2) ( 0-132psi) ( 0-120psi) ** ON A/C 001-050. Page 48 of 51 .5T / 75. If the tire is under-inflated again. Pressure Table NOTE: The tables below show all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. AMM TASK 32-41-11-400-006) (Ref. 146-146. 710-710. 715-750 (Ref. 710-710. 153-155. 707-708. 108-108. you must replace the wheel. you must also replace the adjacent wheel. 140-140.3 to You must replace the wheel. 108-108. 703-703. replace the related wheel and the adjacent wheel. 703-703. 117-117. 144-144.If the aircraft rolled with a flat tire. 102-105. 703-703.2 bars adjacent wheel. 170-170. AMM TASK 32-41-11-000-006) (Ref. 501-701. 142-142. 501-701. 123-300.8 bars (149-157psi) TIRE PRESSURE MLG 49X19-20 TIRE CONDITION/ACTION NECESSARY (142-149psi) From 9. 110-121. See NOTE (1) From 9. NOTE: If the tire is incorrect. 123-139.3 bars less than 8. 110-121. (1) MTOW 73. 137-137. AMM TASK 32-41-12-400-001) . 707-708. less than 10.3 to Inflate the tire to the maximum less than 9. 102-105. 141-154 EMB SB 00-1152 for A/C 104-105.2 bars See NOTE (1) (132-149psi) (120-135psi) From 0 to From 0 to You must replace the wheel and the less than 9.If you are sure that the pressure loss occurred while the aircraft was in the parked configuration (after the aircraft stopped). 2016 © AIRBUS S. 182-183 Subtask 32-41-00-210-059-B0 B. 151-151. replace only the tire with the low pressure. If the tire is under-inflated again. (178-187 psi) (200-210 psi) From 11.Customer : AXM Type : A318/A319/A320/A321 Rev.5 bar measurement is correct with another (210 psi) pressure gage.8 bar the tire pressure.8 bar normal pressure. Do not adjust 12.3 to You must replace the wheel. you must replace the wheel.9 bar less than 11 bar adjacent wheel. (165-174 psi) (149-157 psi) From 10. Date : Feb 01.A.5 bar the tire pressure.4 bar less than 10. You must measure the (161-170 psi) (181-190 psi) tire pressure again the next day. deflate the tire to the maximum normal pressure.3 to Inflate the tire to the maximum less than 10.9 bar (187 psi) TIRE PRESSURE MLG 46X16-20 TIRE CONDITION/ACTION NECESSARY 46X17R20 More than Over-inflation.1 to Inflate the tire to the maximum less than 12. See NOTE (1) From 9.5 bar See NOTE (1) (144-161 psi) (160-181 psi) From 0 to From 0 to You must replace the wheel and the less than 9.2 bar less than 8.9 bar less than 9. Do not adjust 12 bar 10. From 11. you must replace the wheel.1 bar normal pressure. See NOTE (1) From 9.3 bar normal pressure.8-15 30X8. You must measure the (149-158 psi) (135-142 psi) tire pressure again the next day. Make sure that the 10.8 to Inflate the tire to the maximum less than 11. ALL RIGHTS RESERVED.8 to Normal pressure range. less than 11.3 to From 9.2 to From 8. (170-178 psi) (190-200 psi) From 11. (158-165 psi) (142-149 psi) From 10. If it is correct.3 to From 13. Page 49 of 51 . Make sure that the 14.7 bar less than 13. 2016 © AIRBUS S. less than 10.3 bar See NOTE (1) (133-149 psi) (120-135 psi) From 0 to From 0 to You must replace the wheel and the less than 9. See NOTE (1) and (2) (133 psi) (120 psi) Print Date: May 21. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .8R15 More than 12.3 bar less than 13. See NOTE (1) and (2) (144 psi) (160 psi) (2) MTOW 73.1 to From 12.5T TIRE PRESSURE MLG 49X17-20 More than 12 bar (174 psi) TIRE PRESSURE MLG 49X19-20 TIRE CONDITION/ACTION NECESSARY More than Over-inflation.1 bar less than 12. From 12.3 bar adjacent wheel. deflate the tire to the maximum normal pressure.9 bar 14.4 to From 10.8 bar normal pressure. If it is correct.9 to From 11 to You must replace the wheel. CONFIDENTIAL AND PROPRIETARY DOCUMENT.5 to Inflate the tire to the maximum less than 11.8 bar measurement is correct with another (157 psi) pressure gage.3 bar less than 9.5T / 75.WHEELS TIRE PRESSURE NLG 30X8. If the tire is under-inflated again.7 to From 13.9 to From 9.S.3 to Normal pressure range. (2) Remove the tire inflation-valve cap. (2) In the cockpit. Print Date: May 21. Test and Support Equipment REFERENCE No specific No specific No specific B. Tools. NITROGEN WARNING NOTICE(S) Work Zones and Access Panels ZONE/ACCESS 700 ZONE DESCRIPTION LANDING GEAR AND LANDING GEAR DOORS C. NITROGEN near the wheel on which you do the check.TIRE INFLATION/DEFLATION on the tire inflation valve.TIRE INFLATION/DEFLATION CART . TIRE. on the center instrument panel 400VU. 12-14-32-614-001-A).A. put a warning notice to tell persons not to operate them. 3.WHEELS ** ON A/C ALL TASK 32-41-00-210-004-A Check Correct Operation of Wheel Mounted Tire Pressure Indicators 1. TIRE. (3) Install the ADAPTER . Date : Feb 01. Safety Precautions (1) In the cockpit. on the steering handwheels (CAPT and F/O) and on the brake pedals.INFLATION. QTY AR AR AR DESIGNATION ADAPTER . NOTE: You must do this check on all the wheels of the aircraft. Page 50 of 51 . 4. CONFIDENTIAL AND PROPRIETARY DOCUMENT.Customer : AXM Type : A318/A319/A320/A321 Rev.INFLATION. 2 Job Set-up Information A. 2016 © AIRBUS S. DESIGNATION Nitrogen Filling of the Tires Job Set-up Subtask 32-41-00-941-055-A A. Fixtures. Check of of Wheel Mounted Tire Pressure Indicators Correct Operation (1) Put the CART . put WARNING NOTICE(S) to tell persons not to operate the landing gear control lever. Referenced Information REFERENCE (Ref. ALL RIGHTS RESERVED. Procedure Subtask 32-41-00-210-061-A A.S. 2016 Manual : AMM Selected applicability : ALL 32-41-00 . Reason for the Job Refer to the MPD TASK: 324100-03 CHECK CORRECT OPERATION OF WHEEL MOUNTED TIRE PRESSURE INDICATORS NOTE: This procedure is applicable only on aircraft with a pressure indicator on the valve of the wheels. A. 5.S. (3) Remove the inflation cart from the area.Tire Wear and Deterioration Characteristics.Tire Deterioration Characteristics.Sectional View Figure 32-41-00-991-00300-A / SHEET 1/1 .Tire Utilization Limits . 2016 © AIRBUS S. Removal of Equipment (1) Disconnect the tire inflation cart. (5) On the indicator of the wheel inflation valve: · Make sure that the tire pressure indications agree with the pressure measured on the pressure gage.Tire Wear and Deterioration Characteristics.Tire Wear and Deterioration Characteristics.Tread cuts depth and length limits Figure 32-41-00-991-00100-A / SHEET 1/1 . (2) Install the tire inflation-valve cap.Rib Undercutting Figure 32-41-00-991-03600-A / SHEET 1/1 .Thrown Tread . (4) Remove the warning notices.Bias Tire . Date : Feb 01.Tread Chunking Figure 32-41-00-991-03100-A / SHEET 1/1 . Page 51 of 51 .Tire Deterioration Characteristics.Customer : AXM Type : A318/A319/A320/A321 Rev. (6) Inflate the tire again with nitrogen to the correct pressure (Ref.Tread Separation Blister or Bulge Figure 32-41-00-991-04600-A / SHEET 1/1 .General Description Figure 32-41-00-991-00200-A / SHEET 1/1 .General Description Figure 32-41-00-991-00600-A / SHEET 1/1 .Open Tread Splice Figure 32-41-00-991-04700-A / SHEET 1/1 .Skid (Flat Spots) Figure 32-41-00-991-00400-A / SHEET 1/1 . NOTE: THE DIFFERENCE BETWEEN THE TWO INDICATIONS MUST BE EQUAL TO PLUS OR MINUS 5 P.Tire Wear and Deterioration Characteristics Figure 32-41-00-991-00800-A / SHEET 1/1 .S.Tire Wear and Deterioration Characteristics.Groove Cracking .WHEELS NOTE: Use a pressure gage with the same accuracy as the pressure gage used in shop (scale: 0 to 300 PSI). CONFIDENTIAL AND PROPRIETARY DOCUMENT. Figure 32-41-00-991-03000-A / SHEET 1/1 .Bias Tire .Tire Deterioration Characteristics.Radial Tire .Sectional View Figure 32-41-00-991-00700-A / SHEET 1/1 . AMM TASK 12-14-32-614-001) .Peeled Rib Figure 32-41-00-991-00500-A / SHEET 1/1 .Chevron Cutting End of document Print Date: May 21.Tire Deterioration Characteristics. (4) Lightly deflate the tire and make sure that the pointer of the valve moves.Tread Flaking and Chipping Figure 32-41-00-991-04800-A / SHEET 1/1 . Close-up Subtask 32-41-00-942-054-A A.Tire Wear and Deterioration Characteristics.Tread Rubber Reversion Figure 32-41-00-991-00900-A / SHEET 1/1 . ALL RIGHTS RESERVED. 2016 Manual : AMM Selected applicability : ALL 32-41-00 .Radial Tire . the adaptor and the pressure gage.I.
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