(2)
Open the access doors 325BL, 325BR, 325CL, 325CR.
Subtask 27-25-00-865-050
B. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AUTO FLT/FAC1/28VDC 5CC1 B04 49VU AUTO FLT/FAC1/26VAC 14CC1 B03 121VU AUTO FLT/RUDDER/TRIM/IND 15CC M20 121VU AUTO FLT/FAC2/28VDC 5CC2 M19 121VU AUTO FLT/FAC2/26VAC 14CC2 M18
Subtask 27-25-00-860-051
C. Aircraft Maintenance Configuration
(1)
Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
(2)
On the overhead panel 23VU, make sure that the FLT CTL/FAC1 pushbutton switch is pushed (on this pushbutton switch, the OFF and FAULT legends are off).
(3)
On the overhead panel 24VU, make sure that the FLT CTL/FAC2 pushbutton switch is pushed (on this pushbutton switch, the OFF and FAULT legends are off).
(4)
On the center pedestal, on the panel 110VU, make sure that the RUD TRIM indicator shows O.
(5)
Pressurize the aircraft hydraulic systems (Ref. TASK 29-23-00-863-001) (Ref. TASK 29-24-00-863-001) (Ref. TASK 29-10-00-863-003).
(6)
On the tail cone, make sure that the lower part of the rudder trailing edge is aligned at 0 +3 -3 mm (0.0000 +0.1181 -0.1181 in.) with the center of gravity of the triangle NSA950200. If it is not the case, do the adjustment of the rudder neutral position with the refererence triangle (Ref. TASK 27-24-00-820-001). (Ref. Fig. 501/TASK 27-25-00-991-002)
(7)
Install the PIN - RIGGING (98D27207546000) (1) or RIGGING PIN SUPSD BY 98D27207545000 TO 98D27207549000 (98D27207516000) pin (98D27207516090) on the input lever of the lower servocontrol (2). (Ref. Fig. 502/TASK 27-25-00-991-001)
4. Procedure_________
(Ref. Fig. 502/TASK 27-25-00-991-001)
Subtask 27-25-00-820-050
A. Adjustment of the Rudder Position Indication
(1) Push the pin (4) of the transducer unit (5).
NOTE : The pin (4) is part of the transducer unit (5).
____
You must push the pin (4) freely. If this is not the case, adjust the length of the rod (3) as follows :
Tolerance Range for the Rudder Surface at the Zero Position
Figure 501/TASK 27-25-00-991-002
Rigging - Location
Figure 502/TASK 27-25-00-991-001
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(a)
Cut and remove the lockwire from the nuts.
(b)
Loosen the nuts.
(c)
Release the lockwashers.
(d)
Adjust the length of the rod (3) until you can push the pin (4) freely.
(e)
Engage the lockwashers.
(f)
Tighten the nuts.
(g)
Make sure that the adjustment is correct after you have tightened the nuts.
(h)
Safety the nuts with Lockwire corrosion resistant steel dia 0.8 mm (0.03 in.).
(i)
Remove the rigging pin (1) from the input lever of the lower servocontrol (2). (Ref. Fig. 502/TASK 27-25-00-991-001)
(j)
Make sure that the pin (4) is disengaged from the input lever of the transducer unit (5).
Subtask 27-25-00-710-050
B. Operational Test
(1) Do the operational test of the rudder control mechanism (Ref. TASK 27-24-00-710-001).
5. Close-up
________ Subtask 27-25-00-860-050
A. Put the aircraft back to its initial configuration
(1)
Depressurize the aircraft hydraulic systems (Ref. TASK 29-23-00-864-001) (Ref. TASK 29-24-00-864-001) (Ref. TASK 29-10-00-864-003).
(2)
Make sure that the work area is clean and clear of tool(s) and other items.
(3)
De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
Subtask 27-25-00-410-050
B. Close Access
(1)
Close the access doors 325BL, 325BR, 325CR, 325CL.
(2)
Remove the access platform(s).
TRANSDUCER UNIT - RUDDER POSITION (42WV) - REMOVAL/INSTALLATION
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