(8)  
Drive elevator trailing edge up and verify that voltage decreases (this ensures that sensor is set to correct side of null). If not correct, repeat steps (5) thru (7) until correct null is obtained.

(9)  
Lockwire thumb nut on microadjustment rod.

595 
22-11-301 Page 502  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/86 

E.  Restore Airplane to Normal
(1) 
 Disconnect VTVM

(2)  
Remove test cable and reconnect sensor connectors to airplane wiring.

(3)  
Remove test set cables and reconnect D1681 to A/P actuator A and D1687 to A/P actuator B.

(4)  
Remove test set power cable.

(5)  
Install tail cone access panel.

(6)  
Remove electrical and hydraulic power if no longer required.

2.  A/P Elevator Actuator/Position Sensor
A.  Prepare to Test
(1)  
Provide electrical and hydraulic power.

(2)  
Check that hydraulic system A and B switches on P5 panel are positioned to ON and that FLT CONT SYS circuit breaker on P6 panel is closed.

WARNING:  MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR AND TAB SURFACES. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.

(3)  
Check that all autopilot, attitude, compass and air data systems circuit breakers are closed on P6 and P18 load control centers.

B.  Test Actuator/Sensor
(1)  
Place autopilot A (or B as applicable) engage switch to CWS. Observe that CWS ROLL and CWS PITCH is annunciated.

(2)  
Push on control column, note increase in pressure required to move control column and check that elevator moves down.

(3)  
Pull on control column and check that elevator moves up.

(4)  
Return control column to center and disengage autopilot.

(5)  
Remove electrical and hydraulic power if no longer required.

580 
Oct 20/86  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  22-11-301 Page 503 

AFCS COMPUTER - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1.  General
A.  The AFCS computer is retained in the electronic rack with a pair of cam-action levers which hook over forks on the shelf.
2.  Remove Computer
A.  Open all autopilot circuit breakers on P6 and P18 load control centers.
B.  Release computer by pressing triggers, then pull ejection levers simultaneously.
C.  Remove computer.
3.  Install Computer
A.  Place computer in rack and simultaneously push ejection levers up until levers are latched  per 20-10-111, Electrical/Electronic Black Box - Removal/Installation.
CAUTION:  IMPROPER ADJUSTMENT OF FORK ASSEMBLIES ON EQUIPMENT SHELF MAY CAUSE CIRCUIT MALFUNCTION OR EQUIPMENT DAMAGE.
B.  Close all autopilot circuit breakers.
C.  Conduct BITE check of computer (Ref AFCS Computer - Adjustment/Test).
May 15/81 22-11-331 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

AFCS COMPUTER - ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1.  AFCS Computer Test
A.  General
(1)  
An installation test of the AFCS computer is provided by BITE on configuration III interim systems.

(2)  
Prepare AFCS for BITE by providing electrical power to autopilot, PDC, attitude reference, compass, VHF NAV, LRRA, air data, auto throttle and flight instruments.

B.  Perform Computer BITE Test
(1)  
Select PDC CDU to autopilot BITE by selecting STBY, pressing RCL, (-) then selecting page 5 (autopilot BITE).

(2)  
Select NO (ENT) to SYMPTOM/PIREP and GROUND FUNCT to enter VERIFICATION mode (YES), step system thru LRU component list to obtain FCC INTERFACE test No. (25). Select desired channel to be tested.

NOTE:  Additional confidence in autoland performance can be obtained by performing FULL LAND BITE check test No. (33) or (83).

(3)  
Perform BITE INITIALIZE steps and required actions as requested on CDU and perform computer BITE.

(4)  
Follow instructions to provide system diagnostic routine if a BITE fails. Replace indicated component and recycle system thru BITE until system passes.

(5)  
Remove hydraulic and electrical power if no longer required.

Feb 20/85 22-11-331 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
　
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