(e)
Simulate airspeed of 280 KTS to Air Data Computer #1. Observe that the panel displays CAS qpot between -3.4 and -4.8.
(f)
Turn off air data test set.
(8)
Shutdown BITE
(a)
Press ON/OFF on the YDC BITE panel. Observe that TURN OFF DISPLAY? displays on the panel.
(b)
Press YES. Observe that DISPLAY OFF temporarily displays followed by the panel blanking. Observe the AUTOPILOT DISENGAGE WARNING lights are not illuminated.
NOTE: Disregard other Master Caution annunciator lights that illuminate.
F. Test Yaw Damper Interlocks
(1)
Engage YAW DAMPER engage switch. Observe that YAW DAMPER warning light and FLT CONT annunciator light extinguish within 3 seconds.
(2)
Press either MASTER CAUTION light. Open YAW DAMPER AC circuit breaker. Observe that YAW DAMPER engage switch moves to the OFF position after approximately 2 to 5 seconds. Observe that the YAW DAMPER warning light, the FLT CONT annunciator light, and both MASTER CAUTION lights illuminate.
(3)
Press either MASTER CAUTION light. Close the YAW DAMPER AC circuit breaker. Wait 15 seconds and then engage the YAW DAMPER engage switch. Open the YAW DAMPER DC circuit breaker. Observe that YAW DAMPER engage switch moves to the OFF position and that the YAW DAMPER warning light, the FLT CONT annunciator light, and both MASTER CAUTION lights illuminate.
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G. Test Yaw Damper Indicator Lights
(1)
With the yaw damper disengaged, observe that the YAW DAMPER warning light is illuminated on P5-3 Flight Controls Module, that the FLT CONT annunciator light is illuminated on the Left Master Caution Annunciator on the P7 Light Shield Panel, and that the Master Caution, left, and Master Caution, right, warning lights are illuminated on the P7 Light Shield Panel.
(2)
Place LIGHTS switch on center instrument panel first in DIM position, then in BRT position. Observe that YAW DAMPER warning light dims and then illuminates brightly.
(3)
Press either MASTER CAUTION light. Observe that both MASTER CAUTION lights and FLT CONT annunciator light go out, and that YAW DAMPER warning light remains illuminated.
(4)
Momentarily press Left Master Caution Annunciator. Observe that both MASTER CAUTION lights and FLT CONT annunciator light illuminate.
H. Hold Down Forces Test
(1)
Open Handle Levers on the YDC assembly.
(2)
Close Handle Lever to the point where the bottom corner of the lever just makes contact with the Fork Assembly.
(3)
Measure the distance between the tip of the lever and the position of the tip of the lever when fully closed. Distance should be between 0.35 and 0.45 inches.
(4)
If necessary, adjust the Jamnut Fork Adjustment Point as follows:
(a)
With the plug on the rear of the unit fully engaged and the handle lever on the front of the unit at a dimension within tolerance.
(b)
Adjust forks by rotating to a position where they start to exert pressure on the locking lever.
(5)
Fully close the Handle Levers to properly seat the YDC in the rack.
(6)
Ensure proper adjustment by unlatching Handle Levers, closing to the point of contact with the Fork Assembly, and verifying the dimension is within tolerance.
(7)
If necessary, repeat steps (4) thru (6) until dimension is within tolerance.
(8)
Fully close Handle Levers.
3. Restore Aircraft to Normal Configuration
A. Disengage yaw damper.
B. Disconnect pressure source from pitot static system (Ref 34-12-00).
C. Determine whether there is further need for electrical power on aircraft; if not, remove external power (Ref 24-22-00).
D. Determine whether there is further need for hydraulic power on aircraft; if not, remove hydraulic power (Ref 29-15-00).
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May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-12-01 Page 509
RUDDER SOLENOID AND TRANSFER VALVES - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA thru N241WA GJ B-2509 and B-2510
1. General (Fig. 401)
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