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rudder commands. Be aware of what will happen next during the test.
(b) There are two subtests in the SERVO TEST selection. They are:
1) ZERO COMMAND?
2) SWEEP TEST?
(c) Use the up arrow and down arrow to display the test.
WARNING: THE RUDDER WILL MOVE WHEN THESE TESTS ARE RUN. DAMAGE TO
EQUIPMENT OR INJURY TO PERSONNEL CAN OCCUR. MAKE SURE THERE IN
NO EQUIPMENT OR PERSONNEL NEAR THE RUDDER.
(d) Push the YES switch to start the displayed test.
(e) The ZERO COMMAND test does the following:
NOTE: There will be a delay between the displays. The delay can be up to 10 seconds.
1) RUDDER MOVING is displayed.
2) YD CMD (value) is displayed.
3) LVDT (value) is displayed.
4) END ZERO COMMAND? is displayed.
5) Push the YES switch to end the ZERO COMMAND test. The following will be displayed:
a) RUDDER MOVING
b) TEST EXITING
c) ZERO COMMAND?
(f) Push the down arrow to continue the test, the following displays will show:
1) SWEEP TEST?
(g) Push the YES switch to end the test.
(h) The SWEEP TEST? displays the following when it is run:
1) RUD CMD LEFT
2) LVDT (value)
3) RUD CMD RIGHT
4) LVDT (value)
5) RUD CMD ZERO
6) LVDT (value)
(i) If the test passes:
1) TEST PASSED is displayed
(j) If the test failed, TEST FAILED is displayed followed by a message for the first fault. To
isolate the fault, do this task: FIM 27-32 TASK 801.
(k) Use the MENU switch to return to the SERVO TEST? display.
K. INPUT SIGNAL INTEGRITY TEST
SUBTASK 27-32-00-740-016
(1) Push the MENU switch to display GROUND TESTS?
(a) Push the down arrow to display OTHER FUNCTNS?
(b) Push the YES switch.
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(c) Push the down arrow to display I/O MONITOR?
(d) Push the YES switch to display ARINC429 INPUTS?
(e) Push the YES switch.
(f) Push the down arrow until CDS DEU BUS? is displayed.
(g) Push the YES switch to display WORD 017?
NOTE: Skip the next three steps if WORD 017? does not display.
(h) Push the YES switch.
(i) Verify the SMYD BITE readout values:
1) Between -39 and -29 when the speedbrake lever is in the FLIGHT DETENT position.
2) Between -3 and +3 when the speedbrake lever is in the DOWN position.
(j) Push the MENU switch.
(k) Push the down arrow until WORD 352? is displayed.
(l) Push the YES switch until BIT 27 is displayed.
(m) Verify the SMYD BITE readout values:
1) 1, when the WING ANTI-ICE switch on the P5 Fwd Overhead panel is ON.
2) 0, when the WING ANTI-ICE switch on the P5 Fwd Overhead panel is OFF.
L. If you are finished with the SMYD tests, return the airplane to normal.
SUBTASK 27-32-00-860-010
(1) Push the ON/OFF switch to turn the SMYD BITE display off.
SUBTASK 27-32-00-410-003
(2) Close this access panel:
Number Name/Location
117A Electronic Equipment Access Door
SUBTASK 27-32-00-860-011
(3) If electrical power is no longer necessary, do this task: Remove External Power,
TASK 24-22-00-860-814.
------------------------- END OF TASK ---------------------------
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STALL WARNING TEST MODULE - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of the stall warning test module.
(2) An installation of the stall warning test module.
TASK 27-32-21-000-801
2. Stall Warning Test Module Removal
(Figure 401)
A. Location Zones
Zone Area
212 Flight Compartment - Right
B. Prepare for the Removal
SUBTASK 27-32-21-860-001
(1) Open these circuit breakers and install safety tags:
CAPT Electrical System Panel, P18-2
Row Col Number Name
E 5 C01204 SMYD-1 CMPTR DC
F/O Electrical System Panel, P6-1
Row Col Number Name
B 5 C01206 SMYD-2 CMPTR DC
C. Stall Warning Test Module Removal
SUBTASK 27-32-21-020-001
(1) Remove the stall warning test module [1]:
(a) Hold thestall warning test module [1].
(b) Release the fasteners which attach the stall warning test module [1] to the aft overhead
panel.
(c) Lower the stall warning test module [1] from the aft overhead panel.
(d) Disconnect the electrical connectors from the back of the stall warning test module [1].
(e) Remove the stall warning test module [1].
------------------------- END OF TASK ---------------------------
　
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