- 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 : Right (R) rudder is a negative (-) value and left (L)
____ rudder is a positive (+) 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.
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 (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 (L) and X2 = - 3.5 degrees (R),

_ gives an average = - 3.0 degree (R).
 2 Example 2: X1 = + 2.5 degrees (L) and X2 = - 3.5 degrees (R),
_ gives an average = - 0.5 degree (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). R
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399, R
 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
 (Ref. AMM TASK 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 (Ref. AMM TASK 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).

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 (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 (Ref. AMM TASK 29-10-00-863-001)

R **ON A/C 401-499,
R B. Configuration
R (1) Make sure that the nosewheels are approximately aligned with the R aircraft centerline. R (2) Make sure that the Towing Lever on the ELEC BOX 5GC is set to the
R Normal position.
R (3) Energize the aircraft electrical circuits R (Ref. AMM TASK 24-41-00-861-002). R (4) On the panel 400VU, make sure that the landing-gear control lever is
　
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