(f)  
Press ENT (no) to step display to LAND VERIFY.

(g)  
Press ENG (yes) to step display to MINI LAND.

(h)  
Press ENT (no) to step display to FULL LAND.

(i)  
Perform actions prompted on CDU display then press ENG (yes) to step display or continue test.

(j)  
Select desired channel by pressing ENG (yes) for channel A or ENT (no) to select channel B.

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505 
22-11-01 Page 524  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/85 

(7) FULL LAND VERIFY Test Chart (Test Group 33 for A, 83 for B)
(a)  Symptom Tests 
SUBTEST/DISPLAY  LIBRARY TEST  TESTS 
.1  1  DISCRETES 
.2  50  BLANK ANN 
.2  57  TO/GA 
.2  63  VOR/LOC ANN 
.2  64  G/S ANN 
.2  66  SINGLE CHAN ANN 
.3  67/68  ILS DEV WARN (OPTIONAL) 
.4  38  MCP PUSHBUTTONS 
.5  47  MCP COURSE DISP 
.6  6  ENG INTLKS 
.7  4  D/A 
.8  24  R ATT. RATE 
.9  28  P ATT. RATE 
.10  9  NAV RCVR INTFC 
.11  10  SINGLE CHAN APP LOGIC 
.12  37  RAD ALT INTFC 
.13  26  APPROACH 
.14  30  ALT RATE 
.15  35  DADC ANALOG 
.16  36  ACCEL INTFC 
.17  17  VG INTFC 
.18  18  COMPASS INTFC 
.19  33  ALPHA 

Feb 20/85 22-11-01
Page 525
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(b)  Surface Tests
SUBTEST/DISPLAY LIBRARY TEST TESTS
.20 27 ELEV CONT .21 22 AIL CONT .22 29 STAB TRIM .23 34 FLAPS .24 11 DUAL APP
(c)  
At completion of BITE, switch PDC to any mode except STBY. Verify that A/P warning lights (extinguish and AFCS mode control panel displays are restored to normal.

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

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22-11-01 Page 526  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/85 

AILERON SOLENOID VALVE - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1.  General
A.  An aileron solenoid valve is externally mounted on left end of B aileron power unit and may be installed but not used on A aileron power unit (Fig. 401).
2.  Remove Solenoid Valve
A.  Depressurize hydraulic systems A and B (Ref 29-11-0 and 29-12-0 MP).
WARNING:  PRESSURIZING HYDRAULIC SYSTEMS WILL SUPPLY POWER TO RUDDER, AILERON, ELEVATOR, SPOILER AND SPEED BRAKE SYSTEMS. CARE SHOULD BE TAKEN TO ISOLATE OR TAG SYSTEMS NOT BEING TESTED TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE AND EQUIPMENT.
B.  Remove mounting bolts and lift valve and seal plate from power unit (Fig. 401).
C.  Cover all openings.
3.  Install Solenoid Valve
A.  Verify seal plate and O-rings are satisfactory or replace.
B.  Lubricate O-rings with BMS 3-11 fluid and install valve and seal plate on power unit (Fig. 401).
C.  Install mounting bolts and tighten to 40-50 pound-inches torque.
D.  Lockwire bolts.
E.  Pressurize hydraulic system B (Ref 29-12-0).
WARNING:  MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, OUTBOARD SPOILERS AND RUDDER SYSTEMS. SURFACES AND CONTROLS MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
F.  Check for leakage and operation of valve (Ref Aileron Solenoid Valve -A/T).
Jun 20/85 22-11-11 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

H19181
Aileron Solenoid Valve Installation  500 
22-11-11Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/67 

AILERON SOLENOID VALVE -ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1.  Aileron Solenoid Valve Test
A.  General
(1)  This test ensures that the aileron solenoid valve operates properly and assumes that the rest of the autopilot is operating normally.
B.  Prepare to Test Aileron Solenoid Valve
(1)  
Pressurize hydraulic system B (Ref 29-12-0, Maintenance Practices).
　
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