W DOC AIRBUS | TSM A320F

Steering Deviation During Taxi

TASK 32-51-00-810-823-A
Steering Deviation During Taxi

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. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
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.
1. Possible Causes
  • XMTR UNIT-N/W STRG HANDWHEEL,CAPT [1GC]
  • XMTR UNIT-N/W STRG HANDWHEEL,F/O [2GC]
  • ELAC-1 [2CE1]
  • ELAC-2 [2CE2]
  • BSCU [10GG]
  • steering servovalve
  • adjustment of the nose wheel steering "zero" position
  • NLG torque link plays
  • Nose Wheel Steering gearbox
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
JT2000AIRBUS
1
TOOL-NOSE WHEEL ALIGNMENT
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.03HBD9)
Synthetic Ester base Grease-General Purpose Low Temp -
 C. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 32-42-00-810-921-A
Difference of Temperature between the two Brakes on a Same Gear
TSM TASK 32-42-00-810-922-A
Difference of Average Temperature between the L and R Gears
AMM 05-51-16-200-001
Inspection After Brake Emergency Application or Overheat
AMM 07-11-00-581-003
Lifting of the Aircraft at the Forward Jacking Point, MLG Wheels on the Ground
AMM 07-11-00-586-001
Lowering of the Aircraft at Forward Jacking Point, MLG Wheels on the Ground
AMM 07-12-00-582-001
Jacking of the Nose Landing Gear
AMM 09-10-00-584-002
Towing by the Nose Landing Gear from the Front with a Towbar
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
AMM 24-41-00-862-002
De-energize the Aircraft Electrical Circuits Supplied from the External Power
AMM 27-21-00-820-003
Adjustment of the Rudder Mechanical Control
AMM 27-93-34-000-001
Removal of the ELAC
AMM 27-93-34-400-001
Installation of the ELAC
AMM 29-10-00-863-001
Pressurize the Green Hydraulic System with a Hydraulic Ground Power-Cart
AMM 29-10-00-863-002
Pressurize the Yellow Hydraulic System with a Hydraulic Ground Power-Cart
AMM 29-10-00-864-001
Depressurize the Green Hydraulic System
AMM 29-10-00-864-002
Depressurize the Yellow Hydraulic System
AMM 31-32-00-860-009
Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page
AMM 32-21-00-200-002
General Visual Inspection of the Nose Landing Gear
AMM 32-21-00-200-003
Check of NLG Torque Links for Excessive Play
AMM 32-41-00-210-002
Inspection/Check of the Wheels and Tires
AMM 32-41-00-210-003
Inspection/Check of the Tire Pressure
AMM 32-42-34-000-001
Removal of the Braking/Steering Control Unit (BSCU)
AMM 32-42-34-400-001
Installation of the Braking/Steering Control Unit (BSCU)
AMM 32-51-00-220-001
Check of the N/WS Zero Position (with the Nose-Wheel Alignment Tool)
AMM 32-51-00-820-001
Adjustment of the N/WS Zero Position with Adjusting Tool F26630200 for A/C with N/WS Feedback Sensor-Box P/N C24763000, Rudder Trim Angle as Reference
AMM 32-51-00-820-002
Adjustment of the N/WS Zero Position with Adjusting Tool F26630200 for A/C with N/WS Feedback Sensor-Box P/N C24763000, NLG Centering Cams as Reference
AMM 32-51-00-820-003
Adjustment of the N/WS Zero Position with Adjusting Tool F26630200 for A/C with N/WS Feedback Sensor-Box P/N C24763000 with the Nose-Wheel Alignment Tool
AMM 32-51-11-000-001
Removal of the Transmitter Unit - Nose-Wheel Steering Handwheel
AMM 32-51-11-400-001
Installation of the Transmitter Unit - Nose-Wheel Steering Handwheel
AMM 32-51-19-000-001
Removal of the Nose Wheel Steering Feedback Sensor P/N C24763000
AMM 32-51-19-220-001
Check of the Voltage at the Nose Wheel Steering Feedback Sensor
AMM 32-51-19-400-001
Installation of the Nose Wheel Steering Feedback Sensor P/N C24763000
AMM 32-51-51-000-002
Removal of the Nose Wheel Steering Servo-Valve
AMM 32-51-51-400-002
Installation of the Nose Wheel Steering Servo-Valve
AMM 34-10-00-860-004
IR Alignment Procedure
AMM 34-10-00-860-005
ADIRS Stop Procedure
F Flow Chart of the Steering Deviation During Taxi
F Results table
F CFDIU Menu BSCU CHAN 1(2) STEERING DATA page
F CFDIU Menu - BSCU CHAN 1(2) SYSTEM DATA - Pedal Angle ** ON A/C NOT FOR ALL
F NLG Shock Absorber - Clearance
3. Fault Confirmation
Subtask 32-51-00-710-050-A
A. Test
NOTE: A Nose Wheel Steering (NWS) angle of 0.5 degree (3 degrees rudder trim) or less is permitted. If more than 3 degrees of rudder trim was necessary to keep the aircraft straight during taxi, the cause could be due to side winds or runway camber. To make sure that the problem with the NWS system was not caused by external effects, it is necessary to let the aircraft return to service (after having done some checks) and monitor the aircraft at the next taxi operation. But, when there are 3, or more, aircraft log book entries in the last 10 flights this is an indication that there is a fault in the NWS system. Thus the operator must trouble shoot the NWS system to find the cause of the NWS offset
F Flow Chart of the Steering Deviation During Taxi
NOTE: It is possible that an aircraft can have part of this procedure done and be returned to service to monitor the NWS, then returned again to maintenance engineering for more trouble shooting. When this occurs the procedure must be done from the start each time, to prevent cumulative-errors.
NOTE: It is possible that no rudder trim figure is associated to a report of veering tendency. In this case, and as a conservative measure the NWS angle is considered to be more than 0.5 degree and less than, or equal to 1.5 degrees (more than 3.0 degrees rudder trim and less than, or equal to 8.8 degrees rudder trim).
   (1) Do a check of the Post Flight Report (PFR) and the aircraft log book for NWS and/or braking related problems:
     (a) If there is NWS and/or braking CFDS maintenance message on the PFR, refer to the troubleshooting procedure relative to the triggered warning/message and do the applicable trouble shooting.
     (b) If there is any entry in the log book related to a HOT BRAKES warning, do the inspection applicable to an emergency brake application or overheat AMM 05-51-16-200-001.
     (c) If there is any entry in the log book related to a brake temperature problem, but there is no HOT BRAKES warning, do the applicable trouble shooting (Ref. TSM TASK 32-42-00-810-921) and (Ref. TSM TASK 32-42-00-810-922).
   (2) Do an inspection/check of the NLG tires.
     (a) Do an inspection of the condition of the nose wheel tires for wear or damage AMM 32-41-00-210-002. The two tires must not show damage and must have almost the same wear condition.
NOTE: If you replace only one tire, the condition of the replacement tire (groove depth) must be almost the same as the other installed tire.
     (b) Do a check of the nose wheel tire pressure AMM 32-41-00-210-003.
NOTE: If the tires are hot it is not possible to get an accurate indication, but the two tires must each have almost the same pressure, which must be more than the correct pressure of a cold tire.
   (3) Do a detailed visual inspection of the NLG structure AMM 32-21-00-200-002.
   (4) From the check/inspections in step(1) thru (3):
     (a) If the check/inspections were not ok and fault was corrected, do the step (8).
     (b) If the check/inspection were OK, do the step (5).
   (5) Do a check of the last 10 flight entries in the aircraft log book:
     (a) if the entry for the last flight shows that a rudder trim correction of more than 8.8 degrees was necessary to keep the aircraft straight during taxi, do the fault isolation in Para.4A, before the next flight.
     (b) if there are less than 3 entries in the log book where more than 3 degrees, but less than or equal to 8.8 degrees, of rudder trim was necessary to keep the aircraft straight during taxi, do the step (8).
     (c) if there are more than 3 entries in the logbook where more than 3 degrees, but less than or equal to 8.8 degrees, of rudder trim was necessary to keep the aircraft straight during taxi, do the step (7).
     (d) if there is an entry in the logbook that has put on limit of 10 flights or 5 operating days, whichever is the longest, before the aircraft must returned to maintenance, do the step (6).
   (6) Return the aircraft to service and make a record in the aircraft logbook to monitor the NWS and return the aircraft to maintenance after no more than the number of flights or operating days remaining from the 10 flights or 5 operating days limits whichever is the longest.
   (7) Return the aircraft to service and make record in the aircraft log book monitor the NWS and return the aircraft to maintenance after not more than 10 flights or 5 operating days whichever is the longest.
NOTE: If during the above flight or day limit there is an entry where more than 8.8 degrees of rudder trim was necessary to keep the aircraft straight during taxi:
Do the fault isolation Para.4.A before next flight.
   (8) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation to assess the aircraft lateral deviation, if any, using the rudder trim input.
4. Fault Isolation
Subtask 32-51-00-810-076-A
A. Procedure
   (1) Do the procedure that follows when one of these two conditions has occured :
  • There are 3, or more, logbook entries related to a NWS offset of more than 3 degrees, but less than or equal to 8.8 degrees, rudder trim and the 10 flight or 5 operating day limit has expired.
  • There is 1 entry related to a NWS offset of more than 8.8 degrees of rudder trim.
NOTE: When an Alignment Tool Nose Wheel (JT2000AIRBUS) is not available and it is not possible to do a taxiway test, it is important to continue the trouble shooting from Para. 4.B.
   (2) If the inspection/check in Para. 3.A. was satisfactory, use one of the two procedures that follows, to find the value of the NWS angle :
  • If a NOSE WHEEL ALIGNMENT TOOL (JT2000AIRBUS) is not available, do the taxiway test at step (4).
  • If a NOSE WHEEL ALIGNMENT TOOL is available do step (3).
   (3) Use the NOSE WHEEL ALIGNMENT TOOL to do a nose wheel alignment check AMM 32-51-00-220-001
     (a) Make a record of the NWS angle, as shown on the NOSE WHEEL ALIGNMENT TOOL.
     (b) Using the rudder trim, align the nose wheels to the zero position, as shown on the NOSE WHEEL ALIGNMENT TOOL :
  • If the rudder trim angle necessary to put the NWS to the zero position is equal to, or more than, the rudder trim angle recorded in the aircraft logbook, continue the procedure from Para. 4.B.
  • If the rudder trim angle necessary to put the NWS to the zero position is less than the rudder trim angle recorded in the aircraft logbook, do step (c).
     (c) From the value of the NWS angle recorded in step (a) :
  • If the NWS angle is more than 0.5 degrees, continue the procedure from Para. 4.B.
  • If the NWS angle is less than or equal to 0.5 degrees, do the taxiway test at step (4).
NOTE: There are possible causes of undemanded steering during taxi other than a mechanical offset of the nose-wheel. Thus if the NOSE WHEEL ALIGNMENT TOOL shows the nose wheel angle is in limit, it will be necessary to do the taxiway test to identify the NWS system offset.
   (4) Do the taxiway procedure that follows, to record the rudder trim angle necessary to make the aircraft taxi in a straight line :
     (a) Put the aircraft on a straight lenght of taxiway.
     (b) Make sure that the engines operate at the same power level during taxi.
     (c) Release the parking brake.
     (d) Steer the aircraft with the rudder pedals or the NWS handwheels so that it is aligned with the taxiway centerline.
     (e) When the aircraft is aligned with the centerline, taxi the aircraft at between 10KT and 15KT and keep the aircraft straight with the rudder trim control only, over a distance of 100 meters or more.
     (f) Record the value (+/- X1 degrees) of trim input necessary to keep the aircraft in a straight line.
NOTE: Left (L) rudder is a positive (+) value and right (R) rudder is a negative (-) value.
     (g) Do the procedure in steps (a) thru (e) again, but in the opposite direction along the same length of taxiway.
NOTE: The procedure is done in each direction to make sure that the effects of cross-winds and/or runway cambers are not included in the calculation of the NWS angle.
     (h) Record the value (+/- X2 degrees) of trim input necessary to keep the aircraft in a straight line.
     (i) Calculate the average value X of the two rudder trim input angles from (X1+X2) divided by 2.
  • Make a record of the value of X=(X1+X2)/2.
       1 Example 1: X1 = - 2.5 degrees (R) and X2 = - 3.5 degrees (R), gives an average = - 3.0 degrees (R).
       2 Example 2: X1 = + 2.5 degrees (L) and X2 = - 3.5 degrees (R), gives an average = - 0.5 degrees (R).
     (j) From the value of the average rudder trim input (X) in step (i) :
  • If the input (X) is less than, or equal to 3 degrees do step (5).
  • If the input (X) is more than 3 degrees continue the fault isolation procedure from Para. 4.B.
   (5) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
     (a) Refer to the Close-Up Para (5.A).
Subtask 32-51-00-860-051-B ** ON A/C NOT FOR ALL
B. Configuration
   (1) Make sure that the nosewheels are approximately aligned with the aircraft centerline.
   (2) Make sure that the Towing Lever on the ELEC BOX 5GC is set to the Normal position.
   (3) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
   (4) On the panel 400VU, make sure that the landing-gear control lever is in the DOWN position.
   (5) On the panel 402VU, make sure that the A/SKID & N/W STRG switch is in the ON position.
   (6) Make sure that the N/WS handwheels and the rudder pedals are in the neutral position.
   (7) Do the IR alignment procedure AMM 34-10-00-860-004.
   (8) On the overhead panel, on the FLT CTL panel 23VU, make sure that the ELAC1 pushbutton switch is pushed (FAULT and OFF legends off).
   (9) On the overhead panel, on the FLT CTL panel 24VU, make sure that the ELAC2 pushbutton switch is pushed (FAULT and OFF legends off).
   (10) On the panel 110VU, make sure that the RUD TRIM indicator shows zero.
   (11) Pressurize the Green hydraulic system AMM 29-10-00-863-001
Subtask 32-51-00-860-051-C ** ON A/C NOT FOR ALL
B. Configuration
   (1) Make sure that the nosewheels are approximately aligned with the aircraft centerline.
   (2) Make sure that the Towing Lever on the ELEC BOX 5GC is set to the Normal position.
   (3) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
   (4) On the panel 400VU, make sure that the landing-gear control lever is in the DOWN position.
   (5) On the panel 402VU, make sure that the A/SKID & N/W STRG switch is in the ON position.
   (6) Make sure that the N/WS handwheels and the rudder pedals are in the neutral position.
   (7) Do the IR alignment procedure AMM 34-10-00-860-004.
   (8) On the overhead panel, on the FLT CTL panel 23VU, make sure that the ELAC1 pushbutton switch is pushed (FAULT and OFF legends off).
   (9) On the overhead panel, on the FLT CTL panel 24VU, make sure that the ELAC2 pushbutton switch is pushed (FAULT and OFF legends off).
   (10) On the panel 110VU, make sure that the RUD TRIM indicator shows zero.
   (11) Pressurize the Yellow hydraulic system AMM 29-10-00-863-002
Subtask 32-51-00-865-052-A
C. Table of the circuit breakers used in this procedure:
PANELDESIGNATIONFINLOCATION
** ON A/C ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B11
49VUL/G/LGCIU/SYS1/NORM1GAC09
105VUFLIGHT CONTROLS/ELAC2/STBY SPLY16CE2A02
105VUFLT CTL/ELAC1/STBY SPLY16CE1A01
** ON A/C NOT FOR ALL
121VUENGINE/ENG2/OIL/PRESS2EN2N42
121VUENGINE/ENG1/OIL/PRESS2EN1N40
** ON A/C ALL
121VUHYDRAULIC/BRAKING AND STEERING/SYS2/SPLY4GGM36
121VUHYDRAULIC/BRAKING AND STEERING/SYS2/CTL3GGM35
121VUHYDRAULIC/BRAKING AND STEERING/SYS1/CTL1GGM34
121VUHYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY2GGM33
121VUHYDRAULIC/LGCIU/SYS22GAQ35
121VUHYDRAULIC/LGCIU/SYS1/GRND SPLY52GAQ34
121VUFLIGHT CONTROLS/ELAC2/NORM/SPLY15CE2R20
** ON A/C NOT FOR ALL
121VUOIL/PRESS/ENG210KC2N42
121VUOIL/PRESS/ENG110KC1N40
Subtask 32-51-00-865-053-A
D. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C ALL
49VUFWS/FWC1/SPLY3WWF01
** ON A/C NOT FOR ALL
121VUENGINE/ENG2/OIL/PRESS2EN2N42
121VUENGINE/ENG1/OIL/PRESS2EN1N40
** ON A/C ALL
121VUEIS/FWC2/SPLY2WWQ07
** ON A/C NOT FOR ALL
121VUOIL/PRESS/ENG210KC2N42
121VUOIL/PRESS/ENG110KC1N40
Subtask 32-51-00-810-095-I ** ON A/C NOT FOR ALL
E. Procedure
   (1) Depressurize the Yellow hydraulic system
AMM 29-10-00-864-002.
NOTE: Use the results table to help you record the different values thru the procedure that follows.
F Results table ** ON A/C NOT FOR ALL
   (2) Do a check of the steering angle on the MCDU.
     (a) On the MCDU, get the STEERING DATA for the BSCU CHAN 1 and BSCU CHAN 2:
F CFDIU Menu BSCU CHAN 1(2) STEERING DATA page ** ON A/C NOT FOR ALL
  • On the MCDU, get the SYSTEM REPORT/TEST/L/G page AMM 31-32-00-860-009.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU1 indication.
  • Make sure that the N/WS handwheels and the rudder pedals are in the neutral position.
  • On the BSCU CHAN 1 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
  • Push the line key adjacent to the REFRESH indication.
  • Print the STEERING DATA page of the BSCU CHAN 1.
  • Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/ TEST/L/G page.
  • On the SYSTEM/REPORT/TEST/L/G page, push the line key adjacent to the BSCU2 indication.
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
  • On the MCDU on the STEERING DATA page of the BSCU CHAN 2, push the line key adjacent to the REFRESH indication.
  • Print the STEERING DATA page of the BSCU CHAN 2.
  • Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
     (b) On the MCDU, push the SYSTEM DATA page 3/3 for the BSCU CHAN 1 and CHAN 2:
F CFDIU Menu - BSCU CHAN 1(2) SYSTEM DATA - Pedal Angle ** ON A/C NOT FOR ALL
  • Make sure that the rudder pedals are in the neutral position.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to BSCU1 indication.
  • On the BSCU CHAN 1 page, push the line key adjacent to SPECIFIC DATA indication
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA page 3/3 indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 1/ SYSTEM DATA page 3/3.
  • Push the line key adjacent to the REFRESH indication.
  • Print the SYSTEM DATA page 3/3 of the BSCU CHAN 1.
  • Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to BSCU2 indication.
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 2/ SYSTEM DATA page 3/3.
  • Push the line key adjacent to the REFRESH indication.
  • Print the SYSTEM DATA page 3/3 of the BSCU CHAN 2.
  • Put the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
     (c) Do a check of CAPT,FO, rudder pedal, steering command angle and BSCU RVDT input: SPOTCAP, SPOTFO, Pedal angle, ANGCSG and RVDTCOM parameters:
       1 Make sure that the SPOTCAP value is less than or equal to 0 deg. plus or minus 0.4 deg. for the CHAN 1 and CHAN 2.
       2 Make sure that the SPOTFO value is less than or equal to 0 deg. plus or minus 0.4 deg. for the CHAN 1 and CHAN 2.
       3 Make sure that the pedal angle value is less than or equal to 0 deg. Plus or minus 0.1 deg. For the CHAN 1 and CHAN 2.
F CFDIU Menu - BSCU CHAN 1(2) SYSTEM DATA - Pedal Angle ** ON A/C NOT FOR ALL
       4 Make sure that the ANGCSG value is 0 degree for the CHAN 1 and CHAN 2.
       5 Make sure that the difference between the RVDTCOM CHAN 1 (value A) and RVDTCOM CHAN 2 (value B) is less than or equal to 0.8 degrees.
     (d) If any of the above parameters is out of tolerances, do the applicable steps:
       1 If the SPOTCAP value is more than 0 deg. Plus or minus 0.4 deg. for the CHAN 1 and/or CHAN 2:
  • Replace the XMTR UNIT-N/W STRG HANDWHEEL,CAPT [1GC] AMM 32-51-11-000-001 and AMM 32-51-11-400-001.
  • Do the steps (a) and (c) 1_ again and make sure that the SPOTCAP value is correct for the CHAN 1 and CHAN 2, if not do step 6_.
       2 If the SPOTFO value is more than 0 deg. Plus or minus 0.4 deg. For the CHAN 1 and/or CHAN 2:
  • Replace the XMTR UNIT-N/W STRG HANDWHEEL,F/O [2GC] AMM 32-51-11-000-001 and AMM 32-51-11-400-001.
  • Do the steps (a) and (c) 2_ again and make sure that the SPOTFO value is correct for the CHAN 1 and CHAN 2, if not do step 6_.
       3 If the pedal angle value is more than 0 deg. plus or minus 0.1 deg. for the BSCU CHAN 1 and/or the BSCU CHAN 2:
  • Open the circuit breakers 15CE2 and 16CE2 (the ELAC2 is isolated).
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU1 indication.
  • On the BSCU CHAN 1 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 1/SYSTEM DATA page 3/3.
  • On the SYSTEM DATA page 3/3 of the BSCU CHAN 1, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle value (value A1).
  • Close the circuit breakers 15CE2 and 16CE2 (the ELAC2 is connected).
  • Open the circuit breakers 15CE1 and 16CE1 (the ELAC1 is isolated).
  • On the SYSTEM DATA page of the BSCU CHAN 1, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle value (value B1).
  • On the SYSTEM DATA page of the BSCU CHAN 1, push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU2 indication.
  • On the BSCU CHAN 2 page, push the line key adjacent to the SPECIFIC DATA indication.
  • Close the circuit breakers 15CE1 and 16CE1 (the ELAC1 is connected).
  • Open the circuit breakers 15CE2 and 16CE2 (the ELAC2 is isolated).
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 2/SYSTEM DATA page 3/3.
  • On the SYSTEM DATA page 3/3 of the BSCU CHAN 2, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle (value A2).
  • Close the circuit breakers 15CE2 and 16CE2 (the ELAC2 is connected).
  • Open the circuit breakers 15CE1 and 16CE1 (the ELAC1 is isolated).
  • On the SYSTEM DATA page of the BSCU CHAN 2, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle (value B2).
  • On the MCDU, push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.

  • If the values A1 and/or A2 only are more than 0 deg. plus or minus 0.1 deg.:
    . Replace the ELAC-1 [2CE1] AMM 27-93-34-000-001 and AMM 27-93-34-400-001.
  • If the values B1 and/or B2 only are more than 0 deg. plus or minus 0.1 deg.:
    . Replace the ELAC-2 [2CE2] AMM 27-93-34-000-001 and AMM 27-93-34-400-001.
  • If the values (A1 and B1) and/or (A2 and B2) are more than 0 deg. plus or minus 0.1 deg.:
    . Do a check of the adjustment of the pedal position transducer unit (25CE1, 25CE2) AMM 27-21-00-820-003.
  • Close the circuit breakers 15CE1, 16CE1, 15CE2 and 16CE2.
  • Do steps (b) and (c) 3_ again and make sure that the pedal angle value is correct for CHAN 1 and CHAN 2, if not do the step 6.
       4 If the ANGCSG value is not correct for the BSCU CHAN 1 and/or CHAN 2, do the step 6.
       5 If the difference between the RVDTCOM CHAN 1 (value A) and RVDTCOM CHAN 2 (value B) is not correct, do the step 6.
       6 Replace the BSCU [10GG] AMM 32-42-34-000-001 and AMM 32-42-34-400-001.
       7 Do the steps (a) thru (c) again and make sure that all the parameters are correct for the CHAN 1 and the CHAN 2, then do the step 8.
       8 Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
  • On the overhead panel, on the FLT CTL panel 23VU, make sure that the ELAC1 pushbutton switch is pushed (FAULT and OFF legends off).
  • On the overhead panel, on the FLT CTL panel 24VU, make sure that the ELAC2 pushbutton switch is pushed (FAULT and OFF legends off).
  • Refer to the Close-Up part (5.A) and do the relevant steps.
   (3) If the steering angle on the MCDU is correct, do a check of the servovalve.
     (a) If the Fault Confirmation test was to be done only with the taxiway procedure, put the aircraft in the necessary configuration to let the nosewheels move freely to the left or the right:
       1 If the check is to be done with the nosewheels on ground, do these steps:
NOTE: You will need two 1.2 m (3.94 ft.) square steel plates.
  • Position a steel plate in front of the nosewheels.
  • Apply a thick layer of Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) to the upper surface of the steel plate.
  • Put the other steel plate on the top of the greased steel plate.
  • Move the aircraft and position the nosewheels on the greased steel plates AMM 09-10-00-584-002.
NOTE: The procedure that uses the steel plates cannot be accurate if the friction between the steel plates does not let the nosewheels move freely.
       2 If the check is to be done with the nosewheels off ground, do these steps:
  • Lift the front of the aircraft until the nose wheels are clear of the ground AMM 07-11-00-581-003.
  • Compress the NLG shock absorber with the nosewheel jack until the dimension H
    F NLG Shock Absorber - Clearance ** ON A/C NOT FOR ALL
    is less than 350 mm (13.7795 in.) AMM 07-12-00-582-001.
  • Make sure that there is a sufficient clearance between the jack and the nose wheels to operate the nose wheel steering system.
     (b) Pressurize the Yellow hydraulic system
AMM 29-10-00-863-002.
     (c) On the MCDU, get the STEERING DATA page for the BSCU CHAN 1:
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU1 indication
  • On the BSCU CHAN 1 page, push the line key adjacent to the SPECIFIC DATA indication
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows OPEN.
NOTE: If the STRSELV parameter show CLOSE get the STEERING DATA page for the BSCU CHAN 2
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows OPEN.
     (d) Do a check of the servovalve:
       1 Push and hold the Captain left rudder-pedal fully forward and make sure that the nose wheels move 6 deg. to the left.
       2 Quickly release the rudder-pedal to the neutral position (+0.5 to -0.5 deg.).
       3 Make sure that the nose wheels move back to the 0 deg. position.
       4 When movement of the nose wheels stops, on the MCDU on the STEERING DATA page:
  • Push the line key adjacent to the REFRESH indication.
  • Record the servovalve current ISTRSV parameter (ISV1).
       5 Push and hold the Captain right rudder-pedal fully forward and make sure that the nose wheels move 6 deg. to the right.
       6 Quickly release the rudder-pedal to the neutral position (+0.5 to -0.5 deg.).
       7 Make sure that the nose wheels move back to the 0 deg. position.
       8 When movement of the nose wheels stops, on the MCDU on the STEERING DATA page:
  • Push the line key adjacent to the REFRESH indication.
  • Record the servovalve current ISTRSV parameter (ISV2).
       9 Do these checks:
  • Make sure that 0.5 X (ISV1 + ISV2) is less than or equal to plus or minus 0.50 mA.
  • Make sure that (ISV1 - ISV2) is less than or equal to plus or minus 0.50 mA.
  • make sure that ISV1 or ISV2 is less than or equal to plus or minus 0.50 mA.
       10 If the servovalve currents are not correct:
       11 Do steps (1) to (9) again and do step (e).
     (e) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (4) If the servovalve current is correct, do a check of the BSCU output:
     (a) On the nose wheels deactivation electrical box 5GC, set the lever to TOWING.
     (b) Open the circuit breakers 3GG and 4GG and make sure that the circuit breakers 1GG and 2GG are closed (the BSCU CHAN 1 is in command).
     (c) On the MCDU on the STEERING DATA page for the BSCU CHAN 1:
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows CLOSED.
  • Record the servovalve current ISTRSV parameter (ISV5).
     (d) Open the circuit breaker 2GG and close the circuit breakers 3GG and 4GG (the BSCU CHAN 2 is in command).
     (e) On the MCDU, get the STEERING DATA page for the BSCU CHAN 2:
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU2 indication.
  • On the BSCU CHAN 2 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
     (f) On the MCDU on the STEERING DATA page:
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows CLOSED.
  • Record the servovalve current ISTRSV parameter (ISV6).
     (g) On the nose wheels deactivation electrical box 5GC, set the lever to normal.
     (h) Close the circuit breaker 2GG.
     (i) Make sure that the value of (Isv5-Isv6) is less than or equal to plus or minus 1.92 mA.
     (j) If the value is not correct:
     (k) Do steps (a) thru (i) again and do step (l).
     (l) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS durint the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (5) If the BSCU output is correct, do a check of the NWS angle 3GC value with the NLG centering cams as reference.
     (a) Jack up the front of the aircraft AMM 07-11-00-581-003.
NOTE: In the fully extended position of the shock absorber, the NLG is automatically centered (the nose wheel steering is in the zero position).
     (b) Depressurize the Yellow hydraulic system AMM 29-10-00-864-002.
     (c) On the MCDU on the STEERING DATA page of the BSCU CHAN 1(CHAN 2):
  • Push the line key adjacent to the REFRESH indication,
  • Record the RVDTCOM value.
     (d) Make sure that RVDTCOM value is less than or equal to 0 deg. plus or minus 0.5 deg. for the BSCU CHAN 1 and BSCU CHAN 2.
     (e) If the NWS angle is not correct for the BSCU CHAN 1 and/or BSCU CHAN 2:
       1 If the voltage is out of the specified limits, do the adjustment of the nose wheel steering "zero" position with the NLG centering cams as reference AMM 32-51-00-820-002.
     (f) If an adjustement of the NWS "zero" position with the centering cams as reference was done, return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (6) If the NWS angle 3GC value is correct or if the voltage is in the specified limits, do an inspection/check of the NLG torque link plays AMM 32-21-00-200-003.
     (a) If the NLG torque link plays were adjusted, return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (7) If the NLG torque link plays are correct, do the adjustment of the nose wheel "zero" position:
     (a) With the JT2000AIRBUS TOOL-NOSE WHEEL ALIGNMENT as reference if the tool is available.
  • Do a check of the NWS "zero" position AMM 32-51-00-220-001.
    If the nose wheels offset as shown on the tool display is out tolerance (more than plus or minus 0.5 degree), do the adjustment of the NWS "zero" position AMM 32-51-00-820-003 and do the step (c).
NOTE: There are possible causes of undemanded steering during taxi other a mechanical offset of the nose wheels.
Thus if the NWS angle is correct as shown on the tool display, then it will be necessary to do the tawiway test to get an accurate rudder trim figure.
     (b) With the rudder trim figure as reference if the LASER ALIGNMENT TOOL is not available or if the nose wheels offset as shown on the tool display is within tolerance:
  • Do the taxi check procedure to get an accurate rudder trim figure
       1 Align the aircraft on the centerline.
       2 Make sure that the engines operate at the same power level.
       3 Release the parking brake.
       4 Let the aircraft roll with the rudder pedals or the N/WS handwheels along the centerline.
When the aircraft is aligned, release the rudder pedals and the N/WS handwheels then continue the taxi without input to make an estimate of the deviation.
NOTE: The speed must be between 10 and 15 kts.
       5 Align the aircraft again on the centerline with the rudder pedals or the N/WS handwheels.
       6 Give a rudder trim input opposite the aircraft deviation.
NOTE: Give the rudder trim inputs 1 degree by 1 degree, then 0.5 degree by 0.5 degree to get a fine adjustment.
       7 Do again the procedure and make an estimate of the new deviation.
       8 Align the aircraft again on the centerline and do again this procedure until the aircraft goes straight.Then record the rudder trim value X1.
       9 Do the same procedure on the same taxiway in the opposite direction.
Then record the trim value X2.
NOTE: The procedure is done in each direction to make sure that the effects of cross-winds and/or runway cambers are not included.
       10 Calculate the average X of the two values X1 and X2 that you measured:
X = (X1 + X2)/2
Examples:
X1 = +3.5 degree (L), X2 = +4.1 degree (L)
X = (+3.5 + 4.1)/2 = +3.8 degree (L)
X1 = +6 degree (L), X2 = -2 degree (R)
X = (+6 - 2)/2 = +2 degree (L)
       11 Do the adjustment of the NWS "zero" position AMM 32-51-00-820-001.
     (c) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (8) If the fault continues:
  • If the adjustment of the NWS Zero Position was done with the ALIGNMENT TOOL-NOSE WHEEL (JT2000AIRBUS), do step (7)(b).
   (9) If the fault continues after the gearbox was adjusted with the rudder trim angle as reference, replace the gearbox (3GC) Nose Wheel Steering gearbox AMM 32-51-19-000-001 and AMM 32-51-19-400-001.
Subtask 32-51-00-810-095-J ** ON A/C NOT FOR ALL
E. Procedure
   (1) Depressurize the green hydraulic system AMM 29-10-00-864-001.
NOTE: Use the results table to help you record the different values thru the procedure that follows.
F Results table ** ON A/C NOT FOR ALL
   (2) Do a check of the steering angle on the MCDU.
     (a) On the MCDU, get the STEERING DATA for the BSCU CHAN 1 and BSCU CHAN 2:
F CFDIU Menu BSCU CHAN 1(2) STEERING DATA page ** ON A/C NOT FOR ALL
  • On the MCDU, get the SYSTEM REPORT/TEST/L/G page AMM 31-32-00-860-009.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU1 indication.
  • Make sure that the N/WS handwheels and the rudder pedals are in the neutral position.
  • On the BSCU CHAN 1 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
  • Push the line key adjacent to the REFRESH indication.
  • Print the STEERING DATA page of the BSCU CHAN 1.
  • Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/ TEST/L/G page.
  • On the SYSTEM/REPORT/TEST/L/G page, push the line key adjacent to the BSCU2 indication.
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
  • On the MCDU on the STEERING DATA page of the BSCU CHAN 2, push the line key adjacent to the REFRESH indication.
  • Print the STEERING DATA page of the BSCU CHAN 2.
  • Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
     (b) On the MCDU, push the SYSTEM DATA page 3/3 for the BSCU CHAN 1 and CHAN 2:
F CFDIU Menu - BSCU CHAN 1(2) SYSTEM DATA - Pedal Angle ** ON A/C NOT FOR ALL
  • Make sure that the rudder pedals are in the neutral position.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to BSCU1 indication.
  • On the BSCU CHAN 1 page, push the line key adjacent to SPECIFIC DATA indication.
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA page 3/3 indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 1/ SYSTEM DATA page 3/3.
  • Push the line key adjacent to the REFRESH indication.
  • Print the SYSTEM DATA page 3/3 of the BSCU CHAN 1.
  • Push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to BSCU2 indication.
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 2/ SYSTEM DATA page 3/3.
  • Push the line key adjacent to the REFRESH indication.
  • Print the SYSTEM DATA page 3/3 of the BSCU CHAN 2.
  • Put the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
     (c) Do a check of CAPT, FO, rudder pedal, steering command angle and BSCU RVDT input: SPOTCAP, SPOTFO, Pedal angle, ANGCSG and RVDTCOM parameters:
       1 Make sure that the SPOTCAP value is less than or equal to 0 deg. plus or minus 0.4 deg. for the CHAN 1 and CHAN 2.
       2 Make sure that the SPOTFO value is less than or equal to 0 deg. plus or minus 0.4 deg. for the CHAN 1 and CHAN 2.
       3 Make sure that the pedal angle value is less than or equal to 0 deg. Plus or minus 0.1 deg. For the CHAN 1 and CHAN 2.
F CFDIU Menu - BSCU CHAN 1(2) SYSTEM DATA - Pedal Angle ** ON A/C NOT FOR ALL
       4 Make sure that the ANGCSG value is 0 degree for the CHAN 1 and CHAN 2.
       5 Make sure that the difference between the RVDTCOM CHAN 1 (value A) and RVDTCOM CHAN 2 (value B) is less than or equal to 0.8 degrees.
     (d) If any of the above parameters is out of tolerances, do the applicable steps:
       1 If the SPOTCAP value is more than 0 deg. Plus or minus 0.4 deg. for the CHAN 1 and/or CHAN 2:
  • Replace the XMTR UNIT-N/W STRG HANDWHEEL,CAPT [1GC] AMM 32-51-11-000-001 and AMM 32-51-11-400-001.
  • Do the steps (a) and (c) 1_ again and make sure that the SPOTCAP value is correct for the CHAN 1 and CHAN 2, if not do step 6_.
       2 If the SPOTFO value is more than 0 deg. Plus or minus 0.4 deg. For the CHAN 1 and/or CHAN 2:
  • Replace the XMTR UNIT-N/W STRG HANDWHEEL,F/O [2GC] AMM 32-51-11-000-001 and AMM 32-51-11-400-001.
  • Do the steps (a) and (c) 2_ again and make sure that the SPOTFO value is correct for the CHAN 1 and CHAN 2, if not do step 6_.
       3 If the pedal angle value is more than 0 deg. plus or minus 0.1 deg. for the BSCU CHAN 1 and/or the BSCU CHAN 2:
  • Open the circuit breakers 15CE2 and 16CE2 (the ELAC2 is isolated).
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU1 indication.
  • On the BSCU CHAN 1 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 1/SYSTEM DATA page 3/3.
  • On the SYSTEM DATA page 3/3 of the BSCU CHAN 1, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle value (value A1).
  • Close the circuit breakers 15CE2 and 16CE2 (the ELAC2 is connected).
  • Open the circuit breakers 15CE1 and 16CE1 (the ELAC1 is isolated).
  • On the SYSTEM DATA page of the BSCU CHAN 1, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle value (value B1).
  • On the SYSTEM DATA page of the BSCU CHAN 1, push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU2 indication.
  • On the BSCU CHAN 2 page, push the line key adjacent to the SPECIFIC DATA indication.
  • Close the circuit breakers 15CE1 and 16CE1 (the ELAC1 is connected).
  • Open the circuit breakers 15CE2 and 16CE2 (the ELAC2 is isolated).
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to SYSTEM DATA indication.
  • On the MCDU, push the next page function key twice to get the BSCU CHAN 2/SYSTEM DATA page 3/3.
  • On the SYSTEM DATA page 3/3 of the BSCU CHAN 2, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle (value A2).
  • Close the circuit breakers 15CE2 and 16CE2 (the ELAC2 is connected).
  • Open the circuit breakers 15CE1 and 16CE1 (the ELAC1 is isolated).
  • On the SYSTEM DATA page of the BSCU CHAN 2, push the line key adjacent to the REFRESH indication.
  • Record the value of the pedal angle (value B2).
  • on the MCDU, push the line key adjacent to the RETURN indication to get the SYSTEM REPORT/TEST/L/G page.

  • If the values A1 and/or A2 only are more than 0 deg. plus or minus 0.1 deg.:
    . Replace the ELAC-1 [2CE1] AMM 27-93-34-000-001 and AMM 27-93-34-400-001.
  • If the values B1 and/or B2 only are more than 0 deg. plus or minus 0.1 deg. :
    . Replace the ELAC-2 [2CE2] AMM 27-93-34-000-001 and AMM 27-93-34-400-001.
  • If the values (A1 and B1) and/Or (A2 and B2) are more than 0 deg. plus or minus 0.1 deg.:
    . Do a check of the adjustment of the pedal position transducer unit (25CE1, 25CE2) AMM 27-21-00-820-003.
  • Close the circuit breakers 15CE1, 16CE1, 15CE2 and 16CE2.
  • Do steps (b) and (c) 3_ again and make sure that the pedal angle value is correct for CHAN 1 and CHAN 2, if not do step 6_.
       4 If the ANGCSG value is not correct for the BSCU CHAN 1 and/or CHAN 2, do step 6_.
       5 If the difference between the RVDTCOM CHAN 1 (value A) and RVDTCOM CHAN 2 (value B) is not correct, do the step 6_.
       6 Replace the BSCU [10GG] AMM 32-42-34-000-001 and AMM 32-42-34-400-001.
       7 Do the steps (a) thru (c) again and make sure that all the parameters are correct for the CHAN 1 and the CHAN 2, then do the step 8_.
       8 Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
  • On the overhead panel, on the FLT CTL panel 23VU, make sure that the ELAC1 pushbutton switch is pushed (FAULT and OFF legends off).
  • On the overhead panel, on the FLT CTL panel 24VU, make sure that the ELAC2 pushbutton switch is pushed (FAULT and OFF legends off).
  • Refer to the Close-Up part (5.A) and do the relevant steps.
   (3) If the steering angle on the MCDU is correct, do a check of the servovalve.
     (a) If the Fault Confirmation test was to be done only with the taxiway procedure, put the aircraft in the necessary configuration to let the nosewheels move freely to the left or the right:
       1 If the check is to be done with the nosewheels on ground, do these steps:
NOTE: You will need two 1.2 m (3.94 ft.) square steel plates.
  • Position a steel plate in front of the nosewheels.
  • Apply a thick layer of Synthetic Ester base Grease-General Purpose Low Temp - (Material No.03HBD9) to the upper surface of the steel plate.
  • Put the other steel plate on the top of the greased steel plate.
  • Move the aircraft and position the nosewheels on the greased steel plates AMM 09-10-00-584-002.
NOTE: The procedure that uses the steel plates cannot be accurate if the friction between the steel plates does not let the nosewheels move freely.
       2 If the check is to be done with the nosewheels off ground, do these steps:
  • Lift the front of the aircraft until the nose wheels are clear of the ground AMM 07-11-00-581-003.
  • Compress the NLG shock absorber with the nosewheel jack until the dimension H
    F NLG Shock Absorber - Clearance ** ON A/C NOT FOR ALL
    is less than 350 mm (13.7795 in.) AMM 07-12-00-582-001.
  • Make sure that there is a sufficient clearance between the jack and the nose wheels to operate the nose wheel steering system.
     (b) Pressurize the Green hydraulic system
AMM 29-10-00-863-001.
     (c) On the MCDU, get the STEERING DATA page for the BSCU CHAN 1:
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU1 indication.
  • On the BSCU CHAN 1 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 1/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows OPEN.
NOTE: If the STRSELV parameter shows CLOSE get the STEERING DATA page for the BSCU CHAN 2.
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows OPEN.
     (d) Do a check of the servovalve:
       1 Push and hold the Captain left rudder-pedal fully forward and make sure that the nose wheels move 6 deg. to the left.
       2 Quickly release the rudder-pedal to the neutral position (+0.5 to -0.5 deg.).
       3 Make sure that the nose wheels move back to the 0 deg. position.
       4 When movement of the nose wheels stops, on the MCDU on the STEERING DATA page:
  • Push the line key adjacent to the REFRESH indication.
  • Record the servovalve current ISTRSV parameter (ISV1).
       5 Push and hold the Captain right rudder-pedal fully forward and make sure that the nose wheels move 6 deg. to the right.
       6 Quickly release the rudder-pedal to the neutral position (+0.5 to -0.5 deg.).
       7 Make sure that the nose wheels move back to the 0 deg. position.
       8 When movement of the nose wheels stops, on the MCDU on the STEERING DATA page:
  • Push the line key adjacent to the REFRESH indication.
  • Record the servovalve current ISTRSV parameter (ISV2).
       9 Do these checks:
  • Make sure that 0.5 X (ISV1 + ISV2) is less than or equal to plus or minus 0.50 mA.
  • Make sure that (ISV1 - ISV2) is less than or equal to plus or minus 0.50 mA.
  • Make sure that ISV1 or ISV2 is less than or equal to plus or minus 0.50 mA.
       10 If the servovalve currents are not correct:
       11 Do steps (1) to (9) again and do step (e).
     (e) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (4) If the servovalve current is correct, do a check of the BSCU output:
     (a) On the nose wheels deactivation electrical box 5GC, set the lever to TOWING.
     (b) Open the circuit breakers 3GG and 4GG and make sure that the circuit breakers 1GG and 2GG are closed (the BSCU CHAN 1 is in command).
     (c) On the MCDU on the STEERING DATA page for the BSCU CHAN 1:
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows CLOSED.
  • Record the servovalve current ISTRSV parameter (ISV5).
     (d) Open the circuit breaker 2GG and close the circuit breakers 3GG and 4GG (the BSCU CHAN 2 is in command).
     (e) On the MCDU, get the STEERING DATA page for the BSCU CHAN 2:
  • On the SYSTEM REPORT/TEST/L/G page, push the line key adjacent to the BSCU2 indication.
  • On the BSCU CHAN 2 page, push the line key adjacent to the SPECIFIC DATA indication.
  • On the BSCU CHAN 2/SPECIFIC DATA page, push the line key adjacent to the STEERING DATA indication.
     (f) On the MCDU on the STEERING DATA page:
  • Push the line key adjacent to the REFRESH indication and make sure that the STRSELV parameter shows CLOSED.
  • Record the servovalve current ISTRSV parameter (ISV6).
     (g) On the nose wheels deactivation electrical box 5GC, set the lever to normal.
     (h) Close the circuit breaker 2GG.
     (i) Make sure that the value of (Isv5-Isv6) is less than or equal to plus or minus 1.92 mA.
     (j) If the value is not correct:
     (k) Do steps (a) thru (i) again and do step (l).
     (l) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS durint the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (5) If the BSCU output is correct, do a check of the NWS angle 3GC value with the NLG centering cams as reference.
     (a) Jack up the front of the aircraft AMM 07-11-00-581-003.
NOTE: In the fully extended position of the shock absorber, the NLG is automatically centered (the nose wheel steering is in the zero position).
     (b) Depressurize the Green hydraulic system AMM 29-10-00-864-001.
     (c) On the MCDU on the STEERING DATA page of the BSCU CHAN 1(CHAN 2):
  • Push the line key adjacent to the REFRESH indication,
  • Record the RVDTCOM value.
     (d) Make sure that RVDTCOM value is less than or equal to 0 deg. plus or minus 0.5 deg. for the BSCU CHAN 1 and BSCU CHAN 2.
     (e) If the NWS angle is not correct for the BSCU CHAN 1 and/or BSCU CHAN 2:
       1 If the voltage is out of the specified limits, do the adjustment of the nose wheel steering "zero" position with the NLG centering cams as reference AMM 32-51-00-820-002.
     (f) If an adjustement of the NWS "zero" position with the centering cams as reference was done, return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps
   (6) If the NWS angle 3GC value is correct or if the voltage is in the specified limits, do an inspection/check of the NLG torque link plays AMM 32-21-00-200-003.
     (a) If the NLG torque link plays were adjusted, return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (7) If the NLG torque link plays are correct, do the adjustment of the nose wheel "zero" position:
     (a) with the JT2000AIRBUS TOOL-NOSE WHEEL ALIGNMENT as reference if the tool is available:
  • Do a check of the NWS "zero" position AMM 32-51-00-220-001.
    If the nose wheels offset as shown on the tool display is out tolerance (more than plus or minus 0.5 degree), do the adjustment of the NWS "zero" position. AMM 32-51-00-820-003 and do the step (c).
NOTE: There are possible causes of undemanded steering during taxi other a mechanical offset of the nose wheels.
Thus if the NWS angle is correct as shown on the tool display, then it will be necessary to do the tawiway test to get an accurate rudder trim figure.
     (b) With the rudder trim figure as reference if the LASER ALIGNMENT TOOL is notavailable or if the nose wheels offset as shown on the tool display is within tolerance:
  • Do the taxi check procedure to get an accurate rudder trim figure.
       1 Align the aircraft on the centerline.
       2 Make sure that the engines operate at the same power level.
       3 Release the parking brake.
       4 Let the aircraft roll with the rudder pedals or the N/WS handwheels along the centerline.
When the aircraft is aligned, release the rudder pedals and the N/WS handwheels then continue the taxi without input to make an estimate of the deviation.
NOTE: The speed must be between 10 and 15 kts.
       5 Align the aircraft again on the centerline with the rudder pedals or the N/WS handwheels.
       6 Give a rudder trim input opposite the aircraft deviation.
NOTE: Give the rudder trim inputs 1 degree by 1 degree, then 0.5 degree by 0.5 degree to get a fine adjustment.
       7 Do again the procedure and make an estimate of the new deviation.
       8 Align the aircraft again on the centerline and do again this procedure until the aircraft goes straight.Then record the rudder trim value X1.
       9 Do the same procedure on the same taxiway in the opposite direction.
Then record the trim value X2.
NOTE: The procedure is done in each direction to make sure that the effects of cross-winds and/or runway cambers are not included.
       10 Calculate the average X of the two values X1 and X2 that you measured:
X = (X1 + X2)/2
Examples:
X1 = +3.5 degree (L), X2 = +4.1 degree (L)
X = (+3.5 + 4.1)/2 = +3.8 degree (L)
X1 = +6 degree (L), X2 = -2 degree (R)
X = (+6 - 2)/2 = +2 degree (L)
       11 Do the adjustment of the NWS "zero" position AMM 32-51-00-820-001.
     (c) Return the aircraft to service and make a record in the aircraft log book to monitor the NWS during the next taxi operation and to assess the aircraft lateral deviation, if any, using the rudder trim input.
       1 Refer to the Close-Up part (5.A) and do the relevant steps.
   (8) If the fault continues:
  • If the adjustment of the NWS Zero Position was done with the ALIGNMENT TOOL-NOSE WHEEL (JT2000AIRBUS), do step (7)(b).
   (9) If the fault continues after the gearbox was adjusted with the rudder trim angle as reference, replace the gearbox (3GC) Nose Wheel Steering gearbox AMM 32-51-19-000-001 and AMM 32-51-19-400-001.
5. Close-up
Subtask 32-51-00-860-050-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Close the circuit breakers 2WW, 3WW, 2EN1 and 2EN2.
   (2) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.
   (3) Do the ADIRS stop procedure AMM 34-10-00-860-005.
   (4) Depressurize the Green hydraulic system AMM 29-10-00-864-001.
   (5) Lower the aircraft on its wheels AMM 07-11-00-586-001.
   (6) If the nose wheels are on greased plates, move the aircraft until the nose wheels are off the greased plates. Remove the greased plates AMM 09-10-00-584-002.
   (7) If the NOSE WHEEL ALIGNMENT TOOL is installed, remove it.
   (8) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
   (9) Make sure that the work area is clean and clear of tools and other items.
Subtask 32-51-00-860-050-B ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Close the circuit breakers 2WW, 3WW, 2EN1 and 2EN2.
   (2) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.
   (3) Do the ADIRS stop procedure AMM 34-10-00-860-005.
   (4) Depressurize the Yellow hydraulic system AMM 29-10-00-864-002.
   (5) Lower the aircraft on its wheels AMM 07-11-00-586-001.
   (6) If the nose wheels are on greased plates, move the aircraft until the nose wheels are off the greased plates. Remove the greased plates AMM 09-10-00-584-002.
   (7) If the NOSE WHEEL ALIGNMENT TOOL is installed, remove it.
   (8) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
   (9) Make sure that the work area is clean and clear of tools and other items.
Subtask 32-51-00-860-050-C ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Close the circuit breakers 2WW, 3WW, 10KC1 and 10KC2.
   (2) On the MCDU, push the line key adjacent to the RETURN indication until the CFDS menu page comes into view.
   (3) Do the ADIRS stop procedure AMM 34-10-00-860-005.
   (4) Depressurize the Yellow hydraulic system AMM 29-10-00-864-002.
   (5) Lower the aircraft on its wheels AMM 07-11-00-586-001.
   (6) If the nose wheels are on greased plates, move the aircraft until the nose wheels are off the greased plates. Remove the greased plates AMM 09-10-00-584-002.
   (7) If the NOSE WHEEL ALIGNMENT TOOL is installed, remove it.
   (8) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
   (9) Make sure that the work area is clean and clear of tools and other items.
Subtask 32-51-00-710-051-A
B. After the subsequent flight, make sure that the fault does not continue.
[Rev.8 from Aug 2018] 2026.04.04 04:31:49 UTC
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