Wheel a320 wheels

Customer : AXM Type : 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.

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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.

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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.

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(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.

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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.

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! A/C WEIGHT ! TIRE DIMENSIONS ! INFLATION PRESSURE ! ! MTOW ! ! UNLOADED / LOADED ! ! ! ! BARS (PSI) BARS (PSI)! !-------------------------!-------------------------!-------------------------! ! 73.5T ! 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 ALL B. Nose Gear Wheel 2659GM , 2660GM (Ref. Fig. 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 - Nose Gear Wheel ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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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, · one standard inflating valve which you can replace by a valve with an incorporated pressure indicator (PSI type), · one overpressure relief valve, · a provision for installation of a transducer for the Tire Pressure Indicating System (optional system). The landing gear manufacturer supplies the axle sleeve installed between the wheel and the axle. Characteristics: · weight: 15.95 kg, including hub cap. It is possible to use either 30 X 8.8 R15 radial tires (basic) or 30 X 8.8 -15 conventional tires (option) on these wheels. ** 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 pressure: 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 / 75.5T ! 30 X 8.8 R15 ! 11.8 (171) / 12.3 (178) ! ! ! 30 X 8.8 - 15 ! 11.8 (171) / 12.3 (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. ------------------------------------------------------------------------------! A/C WEIGHT ! TIRE DIMENSIONS ! INFLATION PRESSURE ! ! MTOW ! ! UNLOADED / LOADED ! ! ! ! BARS (PSI) BARS (PSI)! !-------------------------!-------------------------!-------------------------! ! 73.5T ! 30 X 8.8 R15 ! 11.8 (171) / 12.3 (178) ! ! ! 30 X 8.8 - 15 ! 11.8 (171) / 12.3 (178) ! ------------------------------------------------------------------------------** ON A/C ALL Figure 32-41-00-11800-A / SHEET 1/1 - Main Gear Wheels - Component Location Figure 32-41-00-13200-A / SHEET 1/1 - Main Gear Wheel Figure 32-41-00-13300-A / SHEET 1/1 - Main Gear Wheel Figure 32-41-00-13800-A / SHEET 1/1 - Nose Gear Wheels - Component Location Figure 32-41-00-14000-C / SHEET 1/1 - Nose Gear Wheel Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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32-41-00 PB 201 CONF 00 - WHEELS - MAINTENANCE PRACTICES TASK 32-41-00-910-001-A Tire Mixability Precautions CAUTION:

MAKE SURE THAT YOU OBEY THE SPECIFIED MIXABILITY CONDITIONS. ONLY THE SPECIFIED CONFIGURATIONS ARE PERMITTED BECAUSE OTHER CONFIGURATIONS CAN POSSIBLY: - PREVENT CORRECT OPERATION OF THE BRAKING SYSTEM (DECREASED PERFORMANCE OR NO BRAKING) - PREVENT FREE FALL EXTENSION OF THE LANDING GEAR.

1.

Reason for the Job This procedure gives the tire mixability conditions authorized on aircraft, any other configuration is forbidden.

2

Job Set-up Information A.

Referenced Information REFERENCE DESIGNATION (Ref. 32-41-00-210-003-A). Inspection/Check of the Tire Pressure Radial and Bias Tire Profiles Installed on Same Wheel Axle SHEET 1

Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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Manual : AMM Selected applicability : ALL

RADIAL MAX OD

RADIAL BIAS MAX OD

BIAS

SLR

BIAS MAX OD

32-41-00 - WHEELS

NOTE : THE MAIN REQUIREMENT FOR MIXABILITY IS THE COMPATIBILITY OF THE LOADED RADDII. THEREFORE WHEN A RADIAL TIRE IS INSTALLED WITH AN EQUIVALENT BIAS-PLY TIRE (E.G. 46X17R20 WITH 46X16-20), THEY HAVE THE SAME LOADED RADII (SLR). HOWEVER, A SMALL DIFFERENCE IS POSSIBLE BETWEEN THE UNLOADED OUTSIDE DIAMETER (OD) OF THE TWO TIRES. THIS DIFFERENCE HAS NO EFFECT ON: - STOPPING DISTANCE. - ANTI-SKID TUNING.

N_MM_324100_2_AAM0_01_00

Figure 32-41-00-991-02900-A / SHEET 1/1 - Radial and Bias Tire Profiles Installed on Same Wheel Axle ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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3.

Job Set-up Subtask 32-41-00-941-054-A A.

General (1) Full information is given in LANDING GEARS- TIRES- GENERAL OPERATING PROCEDURES (Ref. SB A320-32-1007).

4.

Procedure Subtask 32-41-00-860-053-J A.

Tire Mixing on the MLG (Ref. Fig. Radial and Bias Tire Profiles Installed on Same Wheel Axle SHEET 1) (1) Allowed mixing 46 x 16 - 20 and 46 x 17 R20 may be mixed without restriction. NOTE: Tire pressures must be checked to the specified values (Ref. AMM TASK 32-41-00-210-003) . Operation is allowed with or without cooling fans. The allowed tire mixing given is applicable to new and retreaded tires. 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).

Subtask 32-41-00-860-054-A B.

Tire Mixing on the NLG NOTE: The mixing of bias tires with radial tires is not permitted on the NLG , because this can cause an unbalance condition. (1) Radial tires (a) You can mix these radial tires : . Bridgestone P/N APR05140 and P/N APR05145 with . Michelin P/N M04201 and P/N M08201 with . Sumitomo P/N SR11261T, P/N SR11262T, P/N SR11263T. (b) For Goodyear radial tires you can mix only: . 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 : . Michelin MATC P/N 039-539-0 and P/N 039-539-1. NOTE: : No other configurations of bias tire mixing are permitted on the NLG

Figure 32-41-00-991-02900-A / SHEET 1/1 - Radial and Bias Tire Profiles Installed on Same Wheel Axle

32-41-00 PB 401 CONF 00 - WHEELS - DEACTIVATION/REACTIVATION TASK 32-41-00-040-001-A Nose Wheel Hubcap Deactivation


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WARNING:

BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

1.

Reason for the Job CDL 32-03 Nose Wheel Hubcap (old CDL reference: 32-2)

2


Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION CHOCK - WHEEL(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S)

Referenced Information REFERENCE DESIGNATION Nose Wheel Hubcap Deactivation/Reactivation SHEET 1


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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 - Nose Wheel Hubcap Deactivation/Reactivation ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 12 of 51



3.


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. (2) Install the CHOCK - WHEEL(S) at the main landing gear.

4.

Procedure (Ref. Fig. Nose Wheel Hubcap Deactivation/Reactivation SHEET 1) Subtask 32-41-00-040-051-A A.

Deactivation of the Nose Wheel Hubcap (1) Remove the screws (2) and the washers (3). (2) Remove the hubcap (1).

5.

Close-up Subtask 32-41-00-942-052-A A.

Remove the safety devices: (1) Remove the warning notice from the cockpit. (2) Remove the wheel chocks at the main landing gear. (3) Make an entry in the log book.

TASK 32-41-00-440-001-A Nose Wheel Hubcap Reactivation WARNING:

BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

1.

Reason for the Job CDL 32-03 Nose Wheel Hubcap (old CDL reference: 32-2)

2


Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION CHOCK - WHEEL(S) SAFETY CLIP - CIRCUIT BREAKER WARNING NOTICE(S) Torque wrench: range to between 0.4 and 0.51 m.daN (35.40 and 45.13 lbf.in)

Referenced Information REFERENCE DESIGNATION Nose Wheel Hubcap Deactivation/Reactivation SHEET 1


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3.


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. (2) Install the CHOCK - WHEEL(S) at the main landing gear.

4.

Procedure (Ref. Fig. Nose Wheel Hubcap Deactivation/Reactivation SHEET 1) Subtask 32-41-00-440-051-A A.

Reactivation of the Nose Wheel Hubcap (1) Install the hubcap (1). (2) Install the washers (3) and the screws (2). (3) Torque the screws (2) to between 0.4 and 0.51 m.daN (35.40 and 45.13 lbf.in).

5.


Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Remove the warning notice(s). (3) Remove the CHOCK - WHEEL(S) at the main landing gear.

TASK 32-41-00-040-002-A Check of the Nose Wheel when one tie bolt is missing 1.

Reason for the Job MMEL 32-41-01A Nose Wheel Tie Bolt (Old MMEL ref: 32-41-01)

2


Referenced Information REFERENCE (Ref. 32-41-12-000-001-A). (Ref. 32-41-12-400-001-A).

3.

DESIGNATION Removal of the NLG Wheel (for corrective action) Installation of the NLG Wheel (for corrective action)


4.

Not applicable

Procedure Subtask 32-41-00-210-073-A A.

Check of the related Nose Wheel (1) Make sure that no broken pieces of the tie bolt are in the wheel. If there are pieces of the tie bolt in the wheel, remove them.


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(2) Do a check of the wheel for damage, no damage is permitted. NOTE: If the wheel is damaged, refer to the AMM (Ref. AMM TASK 32-41-12-000-001) and (Ref. AMM TASK 32-41-12-400-001) to replace the wheel. 5.


Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the log book.

TASK 32-41-00-440-004-A Replacement of the Nose Wheel 1.

Reason for the Job MMEL 32-41-01A Nose Wheel Tie Bolt (Old MMEL ref: 32-41-01)

2



3.

DESIGNATION Removal of the NLG Wheel Installation of the NLG Wheel


4.

Not Applicable


Replacement of the Wheel (1) Remove the related NLG wheel (Ref. AMM TASK 32-41-12-000-001) . (2) Inspection of the wheel (a) Send the wheel to the overhaul facility. (b) Remove and discard the two tie bolts (one on each side) adjacent to the missing one. (c) Refer to the applicable CMM to inspect all of the wheel for damage. (3) Install a new wheel (Ref. AMM TASK 32-41-12-400-001) .

5.


Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items. (2) Delete the entry in the log book.


Page 15 of 51



TASK 32-41-00-040-003-A Check of the Main Wheel when one tie bolt is missing 1.

Reason for the Job MMEL 32-41-02A Main Wheel Tie Bolt (Old MMEL ref: 32-41-02)

2


Referenced Information REFERENCE (Ref. 32-41-11-000-006-A). (Ref. 32-41-11-400-006-A). (Ref. 32-41-11-000-006-A). (Ref. 32-41-11-400-006-A).

3.

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)


4.

Not applicable


Check of the related Main Wheel (1) Remove the related main wheel (Ref. AMM TASK 32-41-11-000-006) . (2) Make sure that no broken pieces of the tie bolt are in the wheel. If there are pieces of the tie bolt in the wheel, remove them. (3) Do a check the wheel for damage, no damage is permitted. NOTE: If the wheel is damaged, refer to the AMM (Ref. AMM TASK 32-41-11-000-006) and (Ref. AMM TASK 32-41-11-400-006) to replace the wheel. (4) Install the main wheel (Ref. AMM TASK 32-41-11-400-006) .

5.


Aircraft Maintenance Configuration (1) Make sure that the work area is clean and clear of tools and other items. (2) Make an entry in the log book.

TASK 32-41-00-440-005-A Replacement of the Main Wheel 1.

Reason for the Job MMEL 32-41-02A Main Wheel Tie Bolt (Old MMEL ref: 32-41-02) MMEL324102A


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2



3.

DESIGNATION Removal of the MLG Wheel Installation of the MLG Wheel


4.

Not Applicable


Replacement of the Wheel (1) Remove the related MLG wheel (Ref. AMM TASK 32-41-11-000-006) . (2) Inspect the associated brakes of the related wheel for damage. (3) Inspection of the wheel (a) Send the wheel to the overhaul facility. (b) Remove and discard the two tie bolts (one on each side) adjacent to the missing one. (c) Refer to the applicable CMM to inspect all of the wheel for damage. (4) Install a new wheel with all the tie bolts (Ref. AMM TASK 32-41-11-400-006) .

5.


Removal of Equipment (1) Make sure that the work area is clean and clear of tools and other items.

(2) Delete the entry in the log book. Figure 32-41-00-991-01000-A / SHEET 1/1 - Nose Wheel Hubcap Deactivation/Reactivation

32-41-00 PB 601 CONF 00 - WHEELS - 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: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

WARNING:

MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR.


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WARNING:

LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. THIS CAN CAUSE A TIRE EXPLOSION AND/OR A WHEEL RIM BURST.

CAUTION:

IF A TIRE OVERSPEED (TIRE SPEED ABOVE THE LIMIT SPECIFIED BY THE TIRE MANUFACTURER) OCCURS DURING A TAKEOFF OR A LANDING, YOU MUST IMMEDIATELY: - REMOVE THE WHEELS FROM THE AIRCRAFT, AND - SEND THE TIRES BACK TO THE TIRE MANUFACTURER TO MAKE SURE THAT THEY ARE SERVICEABLE. ON A318, A319, A320 AND A321 AIRBUS AIRCRAFT, THE LIMIT SPEED IS 225 MPH (195 KTS).

1.

Reason for the Job Self explanatory

2


Consumable Materials REFERENCE (Material No. 08ABC1) (Material No. 08BBD1)

B.

DESIGNATION Aqueous Cleaner-Aircraft Exterior Pressure Spraying Non Aqueous Cleaner-- Isopropyl Alcohol -

Referenced Information REFERENCE DESIGNATION (Ref. 32-41-00-210-003-A). Inspection/Check of the Tire Pressure (Ref. 32-41-00-910-001-A). Tire Mixability Precautions (Ref. 32-41-11-000-006-A). Removal of the MLG Wheel (Ref. 32-41-11-400-006-A). Installation of the MLG Wheel (Ref. 32-41-12-000-001-A). Removal of the NLG Wheel (Ref. 32-41-12-400-001-A). Installation of the NLG Wheel Radial Tire - General Description SHEET 1 Radial Tire - Sectional View SHEET 1 Bias Tire - General Description SHEET 1 Bias Tire - Sectional View SHEET 1 Tire Wear and Deterioration Characteristics SHEET 1 Tire Wear and Deterioration Characteristics- Skid (Flat Spots) SHEET 1 Tire Deterioration Characteristics- Thrown Tread - Peeled Rib SHEET 1 Tire Deterioration Characteristics- Tread Rubber Reversion SHEET 1 Tire Deterioration Characteristics- Chevron Cutting SHEET 1 Tire Deterioration Characteristics- Groove Cracking - Rib Undercutting SHEET 1 Tire Wear and Deterioration Characteristics- Tread Separation - Blister or Bulge SHEET 1 Tire Wear and Deterioration Characteristics- Open Tread Splice SHEET 1 Tire Wear and Deterioration Characteristics- Tread Flaking and Chipping SHEET 1 Tire Wear and Deterioration Characteristics- Tread Chunking SHEET 1 Tire Utilization Limits - Tread cuts depth and length limits SHEET 1


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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 - Radial Tire - General Description ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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TREAD AREA

METALLIC* PROTECTOR

BEAD

BEAD HEEL

SIDEWALL AREA

CENTER PART

SEAT

* : THE METALLIC PROTECTOR IS OPTIONAL, AND DEPENDING ON TIRE MANUFACTURER MAY NOT BE USED ON A RADIAL AIRCRAFT TIRE.

N_MM_324100_6_ABM0_01_00

Figure 32-41-00-991-00200-A / SHEET 1/1 - Radial Tire - Sectional View ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 20 of 51



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 - Bias Tire - General Description ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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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 - Bias Tire - Sectional View ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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NORMAL

EXCESSIVE

OVERINFLATION

UNDERINFLATION

N_MM_324100_6_BCM0_01_00

Figure 32-41-00-991-00700-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 23 of 51



N_MM_324100_6_ACM0_01_00

Figure 32-41-00-991-00300-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Skid (Flat Spots) ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

Page 24 of 51



N_MM_324100_6_ADM0_01_00

Figure 32-41-00-991-00400-A / SHEET 1/1 - Tire Deterioration Characteristics- Thrown Tread - Peeled Rib ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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N_MM_324100_6_BEM0_01_00

Figure 32-41-00-991-00800-A / SHEET 1/1 - Tire Deterioration Characteristics- Tread Rubber Reversion ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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CHEVRON CUTTING

N_MM_324100_6_CHM0_01_00

Figure 32-41-00-991-03600-A / SHEET 1/1 - Tire Deterioration Characteristics- Chevron Cutting ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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N_MM_324100_6_BFM0_01_00

Figure 32-41-00-991-00900-A / SHEET 1/1 - Tire Deterioration Characteristics- Groove Cracking - Rib Undercutting ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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N_MM_324100_6_MCH0_01_00

Figure 32-41-00-991-03000-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Tread Separation - Blister or Bulge ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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N_MM_324100_6_CJM0_01_00

Figure 32-41-00-991-04600-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Open Tread Splice ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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N_MM_324100_6_CLM0_01_00

Figure 32-41-00-991-04700-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Tread Flaking and Chipping ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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N_MM_324100_6_CLN0_01_00

Figure 32-41-00-991-04800-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Tread Chunking ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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12 INCHES MAX (304.8 mm) 2 INCHES MAX (50.8 mm) 1/2 INCH MAX (12.7 mm)

1/2 INCH MAX (12.7 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. (B) CUT PENETRATE THE CARCASS PLIES (BIAS) OR BELT PLIES (RADIAL). (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.

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.

(B) TIRES WITH CUTS THAT EXTEND ACROSS A RIB FROM GROOVE TO GROOVE WHICH ARE DEEPER THAN THE GROOVE ARE NOT SERVICEABLE.

N_MM_324100_6_BGS0_01_00

Figure 32-41-00-991-03100-A / SHEET 1/1 - Tire Utilization Limits - Tread cuts depth and length limits ** ON A/C ALL Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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3.


4.

Not Applicable

Procedure NOTE: The data given is for bias and radial tires and for all Airline Operators. Subtask 32-41-00-210-070-A A.

Visual Inspection of the Wheels (1) On each main gear wheel, examine the drive shroud of the tachometer. (2) Make sure that there are no cracks on the wheel rims. (3) Make sure that there are no leaks on the valves. (4) Make sure that the valve thread is not damaged. Fully tighten the valve cap which seals the valve from dirt and leaks.

Subtask 32-41-00-210-071-A B.

Visual Inspection of the Tires (Ref. Fig. Radial Tire - General Description SHEET 1) (Ref. Fig. Radial Tire - Sectional View SHEET 1) (Ref. Fig. Bias Tire - General Description SHEET 1) (Ref. Fig. Bias Tire - Sectional View SHEET 1) (1) Make sure that the aircraft tires are in the correct condition to continue to operate on the aircraft. Make sure that the tires: · have no air leaks, · have no friction damage, · are worn equally, · have no cuts and flat spots. Remove the wheel when the tire is worn to the base of any groove in one or more points, or if you can see any reinforcing material (metal or fabric). NOTE: Refer to the limits for the use of the tires. (2) Make sure that the tire pressure is in the specified limits (Ref. AMM TASK 32-41-00-210-003) . (3) Obey the tire mixability precautions (Ref. AMM TASK 32-41-00-910-001) . (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. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-11-400-006) or (Ref. AMM TASK 32-41-12-000-001) (Ref. AMM TASK 32-41-12-400-001) . (5) If the tread is not worn equally and if it is necessary, remove the wheel and put it on the opposite axle (Ref. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-11-400-006) or (Ref. AMM TASK 32-41-12-000-001) (Ref. AMM TASK 32-41-12-400-001) ).

Subtask 32-41-00-210-060-A C.

Description of Tire Wear Deterioration Characteristics NOTE: This data is given for information only. (Ref. Fig. Tire Wear and Deterioration Characteristics SHEET 1) (Ref. Fig. Tire Wear and Deterioration Characteristics- Skid (Flat Spots) SHEET 1) (Ref. Fig. Tire Deterioration Characteristics- Thrown Tread - Peeled Rib SHEET 1) (Ref. Fig. Tire Deterioration Characteristics- Tread Rubber Reversion SHEET 1)


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(Ref. Fig. Tire Deterioration Characteristics- Chevron Cutting SHEET 1) (Ref. Fig. Tire Deterioration Characteristics- Groove Cracking - Rib Undercutting SHEET 1) (Ref. Fig. Tire Wear and Deterioration Characteristics- Tread Separation - Blister or Bulge SHEET 1) (Ref. Fig. Tire Wear and Deterioration Characteristics- Open Tread Splice SHEET 1) (Ref. Fig. Tire Wear and Deterioration Characteristics- Tread Flaking and Chipping SHEET 1) (Ref. Fig. Tire Wear and Deterioration Characteristics- Tread Chunking SHEET 1) (1) Normal wear An equal wear of the tread shows that the tire maintenance was correct during the tire life. (2) Uneven wear (a) Usually, under-inflation (inflation pressure less than 90% of the nominal pressure (Refer to table of pressure) (Ref. AMM TASK 32-41-00-210-003) can cause: · too much tread shoulder wear, · high deflection of the tire, with subsequent heat build-up which can cause important internal tire damage. (b) Over inflation (when the tire pressure is more than 105% of the nominal pressure (Refer to table of pressure) (Ref. AMM TASK 32-41-00-210-003) can: · cause too much wear on the center of the tire tread, · increase the risk of Foreign Object Damage (FOD) to the tire. (3) Maximum speed of utilization On A318, A319, A320 and A321 aircraft, 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, hard touch down or sudden steering maneuvers (for the NLG tires). (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. (c) Tread rubber reversion Tread rubber reversion is usually caused by wheel locking on wet or icy runways. 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). WARNING: REMOVE THE VALVE CORE WHEN THE TIRE IS FULLY DEFLATED. REMOVAL OF THE WHEEL VALVE CORE WHEN THE TIRE IS INFLATED CAN EJECT THE CORE WITH HIGH SPEED AND FORCE. THIS CAN CAUSE INJURY TO PERSONS. WARNING: ALWAYS GO NEAR THE WHEELS FROM AN OBLIQUE ANGLE, IN THE DIRECTION OF THE TIRE SHOULDERS. IF YOU DO NOT OBEY THIS INSTRUCTION AND DAMAGE OCCURS TO THE TIRE, PIECES OF THE TIRE CAN CAUSE YOU INJURY. (d) Thrown tread Thrown tread is a total or partial loss of tread that lets you see the carcass plies. Early signs of tread separation can occur in the form of tread bulges, local uneven wear (depression) or local tread/sidewall rubber split. WARNING: DO NOT REMOVE OBJECTS FROM A PRESSURIZED TIRE. THE PRESSURE CAN EJECT OBJECTS WITH MUCH FORCE AND THUS CAUSE INJURY. (e) Tread cuts Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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The definition of cut limits is based on the service experience of each vendor. Because of the different technologies and tire constructions, damage tolerance can be different for each manufacturer. Refer to the relevant vendor's manual for details. Foreign objects that are on the runway, taxiway and parking areas can cause cuts to the tires. 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.

2

Remove the wheel and make sure that the object does not move.

3

Move the wheel to a safe area.

4

Deflate the tire before you remove the object.

5

Do an inspection of the tire at the tire shop.

Chevron cutting Chevron cutting is a tread damage (large number of small Z-,S- or V-shaped cracks) usually in a tire-footprint area. Chevron cutting is usually caused by running and/or braking on cross-grooved runways.

(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. These cracks occur at the bottom of the tread groove. (h) Rib undercutting Rib undercutting is an extension of groove cracking caused by mechanical loading that continues below a tread rib. It can caused tread chunking, peeled rib or thrown tread. (i)

Open tread splice An open tread splice is a crack in the rubber where there is separation of joint or splice.

(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. Tread chunking can be caused by high lateral loading of the tire sometimes caused by tight turning.

(5) Sidewalls damage (a) Cuts or cracks on the sidewall Foreign objects on the operating surfaces frequently cause sidewall cuts. (b) Weathering and radial cracking Weathering and cracking occur when tires are in aggressive environmental conditions. (c) Blisters and bulges They usually are a sign of separation of components. (6) Contamination damage This can be caused by brake oil, tar oil, solvent, chemicals and hydrocarbon based products. The tire must be cleaned with Non Aqueous Cleaner-- Isopropyl Alcohol - (Material No. 08BBD1) and Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No. 08ABC1). After cleaning, push the rubber in the contaminated area. If the rubber is tacky, the wheel must be changed. (7) Circular tire movement on the wheel: (a) Paint a continuous radial line on the tire and the wheel when the tire is installed. (b) If, after the first flight cycle, the circular tire movement is less than 20 degrees: 1

Keep the wheel on the aircraft.

2

Monitor the circular tire movement during the subsequent five flight cycles.


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(c) If, after five flight cycles, the circular tire movement is more than 20 degrees: 1

Replace the wheel.

2

Send the tire to the tire shop for inspection. NOTE: For more information, refer to the tire manufacturer specifications.

** ON A/C ALL PRE COC COCAXM32-001 for A/C 001-008, 102-105, 108-108, 110-121, 123-242, 501-501, 503-503, 601-604, 701-701, 703-703, 707-708, 710-710, 715-715 Subtask 32-41-00-210-052-A D.

Tire Utilization Limits

** ON A/C ALL (Ref. Fig. Tire Utilization Limits - Tread cuts depth and length limits SHEET 1) ** ON A/C ALL PRE COC COCAXM32-001 for A/C 001-008, 102-105, 108-108, 110-121, 123-242, 501-501, 503-503, 601-604, 701-701, 703-703, 707-708, 710-710, 715-715 (1) Tread Surface CONDITION Normal wear

OBSERVATION/ DAMAGE If: - The tread wear is at the bottom of groove at one or more points, or - You can see the reinforced ply (bias tire) or the protector ply (radial tire) at one or more points of the tread surface.

Uneven wear

If the wear limits are reached.

Overspeed

If a tire overspeed (tire speed more than the limit specified by the manufacturer) occurs during take-off or landing.

ACTION Remove the tire immediately. 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 the tire immediately. 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. Send the tires back to the tire manufacturer (with the reason of removal) to make sure that they are serviceable. NOTE: There is no tolerance.


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(2) Tread damage DAMAGE Flat spots

OBSERVATION - 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).

Peeled rib Tread rubber reversion

During the check: - 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.

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): - the cut goes into the outer casing ply (bias tire) or the outer layer (radial tire). - the cut length is more than

ACTION Remove the tire immediately. Keep the tire on the aircraft.

Remove the tire immediately. Remove the tire immediately.

Remove the tire. immediately. 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, if necessary. NOTE: If the tire is still inflated after the aircraft is parked, it is necessary to wait three hours (for tire cooling) before you record the pressure. Then, deflate the tire before removal of the wheel assembly. Remove the tire immediately . Remove the tire immediately.


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DAMAGE

Chevron cutting

Groove Cracking

OBSERVATION 50.8 mm (2 in.) or, - the cut width is more than 3.175 mm (0.125 in.) or, - the cut is not in the limits of one rib. - the cut is in the limits of one rib and the distance between its two ends is more than 12.7 mm (0.5 in.) when measured in the axial direction. (2) The cut or embedded object does not go into the reinforcing ply (bias tire) or the protector ply (radial tire) : - The cut length is more than 304.8 mm (12 in.) or, - The cut width is more than 3.175 mm (0.125 in.) or, - The cut is not in the limits of one rib. - The cut is in the limits of one rib and the distance between its two ends is more than 12.7 mm (0.5 in.) when measured in the axial direction. Because of different technologies and tire constructions, damage tolerance can be different for each manufacturer an even for each tire reference of a given manufacturer. Refer to the applicable vendor manual for details. If there are no cut limits specified in the documentation and if: - The tire is at the limits given for tread cuts - You can see the tread reinforcing ply (bias tire) or the protector ply (radial tire). During the check: - if groove cracking lets you see the reinforcing ply (bias tire) or the protector ply (radial tire) or, - groove cracking undercuts the adjacent rib.

Rib undercutting Open tread splice Tread

If you can see the fabric

ACTION

Remove the tire immediately.


Remove the tire when the crack goes below the rib. Remove the tire immediately. Remove the tire


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DAMAGE chipping and chunking

OBSERVATION

ACTION immediately.

OBSERVATION If you can see the sidewall cords or if they are damaged.

ACTION Remove the tire immediately.

If you can see the sidewall cords


(3) Sidewall damage DAMAGE Cuts or cracks on the sidewall Weathering and radial cracking Blisters and Bulges

Remove the tire immediately . Put marks on the damage area before you deflate the tire for easy identification and analysis by the vendor.

** ON A/C POST COC COCAXM32-001 for A/C 001-008, 102-105, 108-108, 110-121, 123-242, 501-501, 503-503, 601-604, 701-701, 703-703, 707-708, 710-710, 715-715 Subtask 32-41-00-210-052-D D.

Tire Utilization Limits

** ON A/C 001-050, 102-105, 108-108, 110-121, 123-300, 501-501, 503-701, 703-703, 707-708, 710-710, 715-715 (Ref. Fig. Tire Utilization Limits - Tread cuts depth and length limits SHEET 1) ** ON A/C POST COC COCAXM32-001 for A/C 001-008, 102-105, 108-108, 110-121, 123-242, 501-501, 503-503, 601-604, 701-701, 703-703, 707-708, 710-710, 715-715 (1) Tread Surface CONDITION Normal wear

OBSERVATION/ DAMAGE If: - The tread wear is at the bottom of groove at one or more points, or - You can see the reinforced ply (bias tire) or the protector ply (radial tire) at one or more points of the tread surface.

ACTION Remove the tire immediately. 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.

POST COC AXM32-001: For Michelin tires, only for part numbers:


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CONDITION

OBSERVATION/ DAMAGE - M08201 (all indices) - M01103-02 - M13901 (all indices) - M20101-01 If: - The tread wear is at the bottom of groove along more than 1/8 of the circumference, or - You can see the reinforced ply (bias tire) or the protector ply (radial tire) along more than 1/8 of the circumference.

Uneven wear

If the wear limits are reached.

Overspeed

If a tire overspeed (tire speed more than the limit specified by the manufacturer) occurs during take-off or landing.

ACTION

Remove the tire immediately. 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 the tire immediately. 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. Send the tires back to the tire manufacturer (with the reason of removal) to make sure that they are serviceable. NOTE: There is no tolerance.

(2) Tread damage DAMAGE Flat spots

OBSERVATION - 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).

Peeled rib Tread rubber reversion

During the check: - If the tread rubber reversion

ACTION Remove the tire immediately. Keep the tire on the aircraft.

Remove the tire immediately. Remove the tire immediately.


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DAMAGE

OBSERVATION goes to the reinforcing ply (bias tire) or the protector ply (radial tire) or, - If there is shimmy or unbalance.

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): - the cut goes into the outer casing ply (bias tire) or the outer layer (radial tire). - the cut length is more than 50.8 mm (2 in.) or, - the cut width is more than 3.175 mm (0.125 in.) or, - the cut is not in the limits of one rib. - the cut is in the limits of one rib and the distance between its two ends is more than 12.7 mm (0.5 in.) when measured in the axial direction. (2) The cut or embedded object does not go into the reinforcing ply (bias tire) or the protector ply (radial tire) : - The cut length is more than 304.8 mm (12 in.) or, - The cut width is more than

ACTION

Remove the tire. immediately. 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, if necessary. NOTE: If the tire is still inflated after the aircraft is parked, it is necessary to wait three hours (for tire cooling) before you record the pressure. Then, deflate the tire before removal of the wheel assembly. Remove the tire immediately . Remove the tire immediately.


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DAMAGE

Chevron cutting

Groove Cracking

OBSERVATION 3.175 mm (0.125 in.) or, - The cut is not in the limits of one rib. - The cut is in the limits of one rib and the distance between its two ends is more than 12.7 mm (0.5 in.) when measured in the axial direction. Because of different technologies and tire constructions, damage tolerance can be different for each manufacturer an even for each tire reference of a given manufacturer. Refer to the applicable vendor manual for details. If there are no cut limits specified in the documentation and if: - The tire is at the limits given for tread cuts - You can see the tread reinforcing ply (bias tire) or the protector ply (radial tire). During the check: - if groove cracking lets you see the reinforcing ply (bias tire) or the protector ply (radial tire) or, - groove cracking undercuts the adjacent rib.

Rib undercutting Open tread splice Tread chipping and chunking

If you can see the fabric

ACTION



Remove the tire when the crack goes below the rib. Remove the tire immediately. Remove the tire immediately.

(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.

ACTION Remove the tire immediately.

If you can see the sidewall cords

Remove the tire immediately. Remove the tire immediately . Put marks on the damage area before you


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DAMAGE

OBSERVATION

ACTION deflate the tire for easy identification and analysis by the vendor.

** ON A/C ALL TASK 32-41-00-210-003-A Inspection/Check of the Tire Pressure 1.

Reason for the Job Refer to the MPD TASK: 324100-01 CHECK TIRE PRESSURE

2


Fixtures, Tools, Test and Support Equipment REFERENCE No specific

B.

QTY DESIGNATION 1 GAGE - PRESSURE, TIRE

Work Zones and Access Panels ZONE/ACCESS 700

ZONE DESCRIPTION LANDING GEAR AND LANDING GEAR DOORS

C. Referenced Information REFERENCE (Ref. 12-14-32-614-001-A). (Ref. 24-41-00-861-002-A). (Ref. 24-41-00-861-002-A-01). (Ref. 24-41-00-861-002-A-02). (Ref. 32-41-11-000-006-A). (Ref. 32-41-11-400-006-A). (Ref. 32-41-12-000-001-A). (Ref. 32-41-12-400-001-A). 3.

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. THE GAS CAN GO THROUGH THE SKIN AND MAKE BUBBLES IN THE BLOOD. THIS CONDITION CAN KILL YOU.

WARNING:

LET THE BRAKES AND THE WHEELS BECOME COOL BEFORE YOU GO NEAR THE LANDING GEAR. DO NOT APPLY A LIQUID OR GAS DIRECTLY ON A HOT WHEEL OR BRAKE UNIT. THIS CAN CAUSE A TIRE EXPLOSION AND/OR A WHEEL RIM BURST.

A.

Safety Precautions


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WARNING:

4.

BE CAREFUL WHEN YOU INFLATE THE TIRES. USE A PRESSURE REGULATOR (OR PRESSURE RELIEF VALVE) BETWEEN THE PRESSURE SOURCE AND THE TIRE. MAKE SURE THAT THE PRESSURE REGULATOR IS ADJUSTED TO THE CORRECT PRESSURE FOR THE TIRE. IF THE PRESSURE SOURCE DOES NOT HAVE A PRESSURE REGULATOR, THERE IS A RISK OF INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.


Check of the Pressure WARNING: USE ONLY DRY NITROGEN OR OTHER INERT GASES TO INFLATE THE TIRES ON THE MAIN GEAR WHEELS. THE OXYGEN IN THE GAS USED TO INFLATE THESE TIRES MUST NOT BE MORE THAN 5% (VOLUME). IF THE AIRCRAFT IS FAR FROM ITS BASE AND NO DRY NITROGEN IS AVAILABLE, YOU CAN USE AIR FOR THE SERVICING OF THE TIRES IF: - THE OXYGEN IN THE TIRES IS NOT MORE THAN 5% (VOLUME) OR - MAINTENANCE PERSONNEL REMOVE THE AIR FROM THE TIRES AND INFLATE THEM WITH DRY NITROGEN BEFORE 15 HOURS TIME SERVICE. A CHEMICAL REACTION BETWEEN THE OXYGEN IN THE TIRES AND GASES FROM THE INNER LINER CAN CAUSE A TIRE EXPLOSION.

(1) Make sure that the pressure of the tires is correct before the first flight of the day, with the aircraft weight on its wheels. To do this, refer to the pressure table in paragraph 4.B. and use: · A GAGE - PRESSURE, TIRE, or · The wheel-mounted tire-pressure indicators, if installed, or · The Tire Pressure Indicating System (TPIS), if installed. If you use the TPIS: Make sure that circuit breaker 1GV is closed. Energize the aircraft electrical circuit (Ref. AMM TASK 24-41-00-861-002) (Ref. AMM TASK 24-41-00-861-002) (Ref. AMM TASK 24-41-00-861-00 On the ECAM control panel, push the WHEEL key: On the lower ECAM display unit, the WHEEL page comes into view and shows the tire pressures. (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). If you think that the deflection of one or two tires is not correct, do a check of the pressure of all the tires of the aircraft. (b) If possible, do the check when the tires are cold (a tire is cold approximately three hours after its operation). If it is necessary to do the check when the tires are hot, make sure that you do not deflate a hot tire. NOTE: When a tire is hot, its pressure increases. NOTE: If you do the check when the tires are hot, the pressure must be higher than the nominal value. The nominal value is the lower limit of the normal pressure range (given in the pressure table in paragraph 4.B.).


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(c) Record the pressure of all the tires on a same landing gear. Then, record the highest tire pressure. Make sure that the pressure of all the tires is in the same range. 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, in a maximum of three days.

b

If all the pressure values are approximately the same, 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.

c

If the pressure of a hot tire is less than or equal to the minimum of the normal pressure range, this tire is defective (it has a leak or a hole): · Replace the tire and send it for a check (Ref. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-11-400-006) (Ref. AMM TASK 32-41-12-000-001) (Ref. AMM TASK 32-41-12-400-001) . NOTE: If there is a large temperature difference between the departure (cold) and the arrival (hot) airports, the tire pressure at the arrival airport can be higher than the maximum of the Normal Operating Range (NOR). Then, it is necessary to adjust the tire pressure in these conditions: - If the aircraft continues to be operated in a hot area, and - 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).

2

For cold tires: a

3

If all the pressures are approximately the same and in the normal pressure range, no other steps are necessary.

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.

b

Make an entry in the logbook for this tire and monitor the tire pressure for 24 hours. · During the check, if there is an entry in the logbook and if the pressure decreases again for this tire, replace the tire (Ref. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-11-400-006) (Ref. AMM TASK 32-41-12-000-001) (Ref. AMM TASK 32-41-12-400-001) . · If necessary, replace the adjacent tire (refer to the pressure table in paragraph 4.B.).

** ON A/C 801-850 Subtask 32-41-00-210-059-AV B.

Pressure Table NOTE: The tables below show all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. NOTE: These pressure values are for tires with the aircraft weight on the wheels. NOTE: (1): (Ref. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-11-400-006) (Ref. AMM TASK 32-41-12-000-001) (Ref. AMM TASK 32-41-12-400-001) .


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NOTE: (2): - If the aircraft rolled with a flat tire, replace the related wheel and the adjacent wheel. - If you are sure that the pressure loss occurred while the aircraft was in the parked configuration (after the aircraft stopped), replace only the tire with the low pressure. - If you cannot be sure that the wheels did not turn with the tire deflated, you must also replace the adjacent wheel. NOTE: If the tire pressure is incorrect, inflate or deflate the tire to get the correct pressure (Ref. AMM TASK 12-14-32-614-001) . (1) MTOW 73.5T TIRE PRESSURE NLG 30X8.8-15 30X8.8R15 More than 12.9 bars (187 psi)

From 12.3 to 12.9 bars (178-187psi) From 11.7 to less than 12.3 bars (170-178psi) From 11.1 to less than 11.7 bars (161-170psi)

From 9.9 to less than 11.1 bars (144-161psi) From 0 to less than 9.9 bars ( 0-144psi)

TIRE PRESSURE MLG 46X16-20 TIRE CONDITION/ACTION NECESSARY 46X17R20 More than Over-inflation. Make sure that the 14.5 bars measurement is correct with another (210 psi) pressure gage. If it is correct, deflate the tire to the maximum normal pressure. From 13.8 to Normal pressure range. Do not adjust 14.5 bars the tire pressure. (200-210psi) From 13.1 to Inflate the tire to the maximum less than 13.8 bars normal pressure. (190-200psi) From 12.4 to Inflate the tire to the maximum less than 13.1 bars normal pressure. You must measure the (180-190psi) tire pressure again the next day. If the tire is under-inflated again, you must replace the wheel. See NOTE (1) From 11 to You must replace the wheel. less than 12.4 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) and (2) ( 0-160psi)

(2) MTOW 73.5T TIRE PRESSURE MLG 49X17-20 More than 12 bars (174 psi)

TIRE PRESSURE MLG 49X19-20 TIRE CONDITION/ACTION NECESSARY More than Over-inflation. Make sure that the 10.8 bars measurement is correct with another (157 psi) pressure gage. If it is correct, deflate the tire to the maximum normal pressure. From 11.4 to From 10.3 to Normal pressure range. Do not adjust 12 bars 10.8 bars the tire pressure. (165-174psi) (149-157psi) From 10.8 to From 9.8 to Inflate the tire to the maximum less than 11.4 bars less than 10.3 bars normal pressure. Print Date: May 21, 2016 © AIRBUS S.A.S. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT.

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TIRE PRESSURE MLG 49X17-20 (157-165psi) From 10.3 to less than 10.8 bars (149-157psi)

TIRE PRESSURE MLG 49X19-20 TIRE CONDITION/ACTION NECESSARY (142-149psi) From 9.3 to Inflate the tire to the maximum less than 9.8 bars normal pressure. You must measure the (135-142psi) tire pressure again the next day. If the tire is under-inflated again, you must replace the wheel. See NOTE (1) From 9.1 to From 9.3 to You must replace the wheel. less than 10.3 bars less than 8.2 bars See NOTE (1) (132-149psi) (120-135psi) From 0 to From 0 to You must replace the wheel and the less than 9.1 bars less than 8.2 bars adjacent wheel. See NOTE (1) and (2) ( 0-132psi) ( 0-120psi)

** 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 Subtask 32-41-00-210-059-B0 B.

Pressure Table NOTE: The tables below show all the tire pressure values in relation to the aircraft weight (MTOW) and tire sizes. NOTE: These pressure values are for tires with the aircraft weight on the wheels. NOTE: (1): ** ON A/C 001-050, 102-105, 108-108, 110-121, 123-300, 501-701, 703-703, 707-708, 710-710, 715-750 (Ref. AMM TASK 32-41-11-000-006) (Ref. AMM TASK 32-41-11-400-006) (Ref. AMM TASK 32-41-12-000-001) (Ref. AMM TASK 32-41-12-400-001) . NOTE: (2): - If the aircraft rolled with a flat tire, replace the related wheel and the adjacent wheel. - If you are sure that the pressure loss occurred while the aircraft was in the parked configuration (after the aircraft stopped), replace only the tire with the low pressure. - If you cannot be sure that the wheels did not turn with the tire deflated, you must also replace the adjacent wheel. NOTE: If the tire is incorrect, inflate or delfate the tire to get the correct pressure ** ON A/C 001-050, 102-105, 108-108, 110-121, 123-300, 501-701, 703-703, 707-708, 710-710, 715-750 (Ref. AMM TASK 12-14-32-614-001) . (1) MTOW 73.5T / 75.5T


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TIRE PRESSURE NLG 30X8.8-15 30X8.8R15 More than 12.9 bar (187 psi)

TIRE PRESSURE MLG 46X16-20 TIRE CONDITION/ACTION NECESSARY 46X17R20 More than Over-inflation. Make sure that the 14.5 bar measurement is correct with another (210 psi) pressure gage. If it is correct, deflate the tire to the maximum normal pressure. From 12.3 to From 13.8 to Normal pressure range. Do not adjust 12.9 bar 14.5 bar the tire pressure. (178-187 psi) (200-210 psi) From 11.7 to From 13.1 to Inflate the tire to the maximum less than 12.3 bar less than 13.8 bar normal pressure. (170-178 psi) (190-200 psi) From 11.1 to From 12.5 to Inflate the tire to the maximum less than 11.7 bar less than 13.1 bar normal pressure. You must measure the (161-170 psi) (181-190 psi) tire pressure again the next day. If the tire is under-inflated again, you must replace the wheel. See NOTE (1) From 9.9 to From 11 to You must replace the wheel. less than 11.1 bar less than 12.5 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 9.9 bar less than 11 bar adjacent wheel. See NOTE (1) and (2) (144 psi) (160 psi) (2) MTOW 73.5T / 75.5T TIRE PRESSURE MLG 49X17-20 More than 12 bar (174 psi)

TIRE PRESSURE MLG 49X19-20 TIRE CONDITION/ACTION NECESSARY More than Over-inflation. Make sure that the 10.8 bar measurement is correct with another (157 psi) pressure gage. If it is correct, deflate the tire to the maximum normal pressure. From 11.4 to From 10.3 to Normal pressure range. Do not adjust 12 bar 10.8 bar the tire pressure. (165-174 psi) (149-157 psi) From 10.9 to From 9.8 to Inflate the tire to the maximum less than 11.4 bar less than 10.3 bar normal pressure. (158-165 psi) (142-149 psi) From 10.3 to From 9.3 to Inflate the tire to the maximum less than 10.9 bar less than 9.8 bar normal pressure. You must measure the (149-158 psi) (135-142 psi) tire pressure again the next day. If the tire is under-inflated again, you must replace the wheel. See NOTE (1) From 9.2 to From 8.3 to You must replace the wheel. less than 10.3 bar less than 9.3 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 9.2 bar less than 8.3 bar adjacent wheel. See NOTE (1) and (2) (133 psi) (120 psi)


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** ON A/C ALL TASK 32-41-00-210-004-A Check Correct Operation of Wheel Mounted Tire Pressure Indicators 1.

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. NOTE: You must do this check on all the wheels of the aircraft.

2


Fixtures, Tools, Test and Support Equipment REFERENCE No specific No specific No specific

B.

QTY AR AR AR

DESIGNATION ADAPTER - TIRE INFLATION/DEFLATION CART - INFLATION, TIRE, NITROGEN WARNING NOTICE(S)

Work Zones and Access Panels ZONE/ACCESS 700

ZONE DESCRIPTION LANDING GEAR AND LANDING GEAR DOORS

C. Referenced Information REFERENCE (Ref. 12-14-32-614-001-A). 3.

DESIGNATION Nitrogen Filling of the Tires


Safety Precautions (1) In the cockpit, on the center instrument panel 400VU, put WARNING NOTICE(S) to tell persons not to operate the landing gear control lever. (2) In the cockpit, on the steering handwheels (CAPT and F/O) and on the brake pedals, put a warning notice to tell persons not to operate them.

4.


Check of of Wheel Mounted Tire Pressure Indicators Correct Operation (1) Put the CART - INFLATION, TIRE, NITROGEN near the wheel on which you do the check. (2) Remove the tire inflation-valve cap. (3) Install the ADAPTER - TIRE INFLATION/DEFLATION on the tire inflation valve.


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NOTE: Use a pressure gage with the same accuracy as the pressure gage used in shop (scale: 0 to 300 PSI). (4) Lightly deflate the tire and make sure that the pointer of the valve moves. (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. NOTE: THE DIFFERENCE BETWEEN THE TWO INDICATIONS MUST BE EQUAL TO PLUS OR MINUS 5 P.S.I. (6) Inflate the tire again with nitrogen to the correct pressure (Ref. AMM TASK 12-14-32-614-001) . 5.


Removal of Equipment (1) Disconnect the tire inflation cart, the adaptor and the pressure gage. (2) Install the tire inflation-valve cap. (3) Remove the inflation cart from the area.

(4) Remove the warning notices. Figure 32-41-00-991-03000-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Tread Separation Blister or Bulge Figure 32-41-00-991-04600-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Open Tread Splice Figure 32-41-00-991-04700-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Tread Flaking and Chipping Figure 32-41-00-991-04800-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Tread Chunking Figure 32-41-00-991-03100-A / SHEET 1/1 - Tire Utilization Limits - Tread cuts depth and length limits Figure 32-41-00-991-00100-A / SHEET 1/1 - Radial Tire - General Description Figure 32-41-00-991-00200-A / SHEET 1/1 - Radial Tire - Sectional View Figure 32-41-00-991-00300-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics- Skid (Flat Spots) Figure 32-41-00-991-00400-A / SHEET 1/1 - Tire Deterioration Characteristics- Thrown Tread - Peeled Rib Figure 32-41-00-991-00500-A / SHEET 1/1 - Bias Tire - General Description Figure 32-41-00-991-00600-A / SHEET 1/1 - Bias Tire - Sectional View Figure 32-41-00-991-00700-A / SHEET 1/1 - Tire Wear and Deterioration Characteristics Figure 32-41-00-991-00800-A / SHEET 1/1 - Tire Deterioration Characteristics- Tread Rubber Reversion Figure 32-41-00-991-00900-A / SHEET 1/1 - Tire Deterioration Characteristics- Groove Cracking - Rib Undercutting Figure 32-41-00-991-03600-A / SHEET 1/1 - Tire Deterioration Characteristics- Chevron Cutting

End of document


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Wheel a320 wheels

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