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E. Yaw Damper Interface Test
(1) Check system configuration.
(a)
Press ON/OFF on the YDC BITE panel. Observe that ENTER BITE? is displayed on the panel.
(b)
Within 10 seconds press YES. Observe that PLEASE WAIT is temporarily displayed followed by EXISTING FAULTS? on the YDC BITE panel. Observe the AUTOPILOT DISENGAGE WARNING lights illuminate steadily.
(c)
Press down arrow until OTHER FUNCTNS? is displayed.
(d)
Press YES. Observe that SYSTEM CONFIG? is displayed on the panel.
(e)
Press YES. Observe that S/W VRSN XXXXXXXX is displayed on the panel. The actual values for XXXXXXXX is irrelevant.
(f)
Press down arrow. Note the information displayed on the panel. It should display either APL TYPE 100/200 or APL TYPE 1/200 RQ.
(g)
Press ON/OFF. Observe that TURN DISPLAY OFF? is displayed on the panel.
(h)
Press YES. Observe that DISPLAY OFF is temporarily displayed followed by the panel blanking. Observe the AUTOPILOT DISENGAGE WARNING lights are not illuminated.
NOTE: Steps (2) and (4) apply only for aircraft with APL TYPE 1/200 RQ, identified in Yaw Damper Interface test step (1)(f).
(2) Prepare for roll simulation.
(a) If dual Inertial Navigation System (INS) has been installed on the aircraft 1) Ensure that the MSU mode selector switch is set to the OFF position. 2) Install the Attitude Slew Test Plug (Litton Part Number 456058-01) on INU test
connector J4. 3) Position the MSU switch to STBY. The INS CDU Warn lamp will start continuous flashing.
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4) For LTN-72RL models, key in the date including leading zeros (e.g. 100780 for July 10, 1980) on the INS CDU. Press ENT to accept date.
5) For LTN-72 and LTN-74R models, position the INS CDU Display selector switch to POS.
6) For LTN-72RL models, press POS.
(b) If dual INS has not been installed
1) Unbolt the Captain's VG-1 vertical gyro from mount.
(3) Prepare YDC BITE for interface test.
(a)
Press ON/OFF on the YDC Bite Panel. Observe that ENTER BITE? is displayed on the panel.
(b)
Within 10 seconds, press YES. Observe that PLEASE WAIT is temporarily displayed followed by EXISTING FAULTS? on the YDC BITE panel.
(c)
Press down arrow until OTHER FUNCTIONS? is displayed on the panel.
(d)
Press YES. Observe that SYSTEM CONFIG? is displayed on the panel.
(e)
Press down arrow. Observe that I/O MONITOR? is displayed on the panel.
(f)
Press YES. Observe that ANALOG I/O? is displayed on the panel.
(g)
Press YES.
NOTE: Step (h) should be omitted for aircraft with APL TYPE 100/200, identified in Yaw Damper Interface test step (1) (f).
(h)
Press down arrow until the panel displays roll att XXX.X deg.
NOTE: It should be noted that step (4)(a)1) will take approximately 2 minutes to complete. The YDC BITE panel will shut off with approximately 5 minutes of inactivity. Therefore, if step (4)(a)1) is to be performed, it should occur as soon as possible.
(4) Simulate roll.
(a) If dual Inertial Navigation System (INS) has been installed on the aircraft
1) Enter a simulation roll angle of 15° +/-2° on the INS CDU. Approximately 2 minutes after achieving Status 80, the gimbals will start to slew. a) To enter desired roll angle:
1 For LTN-72 and LTN-72R models, press 6E or W4 on the INS CDU keypad. 2 For LTN-72RL models, press N/6E or L/W4.
NOTE: If the INU is facing aft (INU handles facing aft) and 6E or N/6E is pressed, the INU will provide right wing down or roll right. If the INU is facing forward, left wing down or roll left will be provided. The opposite applies to W4 and L/W4.
3 Enter degrees and minutes of roll. Each segment must have two
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