(5)  Place glide slope signal generators approximately 50 feet from glide slope antenna with the test set antenna at a right angle to airplane centerline.
NOTE:  VOR, localizer, and glide slope deviation indicators have either two or five scale divisions left and right or up and down with full scale deflection to 10 degrees, 2 degrees and 0.7 degree of OFF COURSE signal respectively. These divisions are referred to as dots. Two-dot VOR/LOC indicators are assumed. The following deflections or equivalent should be substituted on airplanes with 5-dot instruments.
Deviation (Degrees)
2-Dot 5-Dot Equivalent Input Indicators Indicators Signal 1000-ohm load (mv) VOR LOC G/S
1/4 1/2 18.8 1.25 0.25 0.087 1/2 1-1/2 37.5 2.5 0.5 0.175 1 2-1/2 75.0 5 1 0.35 2 5 150.0 10 2 0.7
(5.1) Ensure hat any VOR, localizer or glide slope signals, which are required to perform any of the tests, are provided with the respective flag out of view, with an on-course, zero deviation display prior to starting the test.
(6)  
Obtain simulated compass headings by setting up desired heading in DG mode or by using compass synchronization on the appropriate compass system.

(7)  
Observe the following whenever control wheel or control column displacements are being measured:

(a)  
Ensure that controls are in detent or neutral position.

(b)  
Before each test, ensure that hydraulic power is applied to the control system being tested.

(c)  
Ensure that stabilizer trim motor is turned off for all tests requiring control column travel with no reference to stabilizer travel. This may be accomplished by opening autopilot stabilizer trim circuit breaker.

500 
22-11-0 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/90 

CAUTION:  TO PREVENT STABILIZER TRIM MOTOR FROM BURNING OUT, DO NOT OPERATE MORE THAN ONE MINUTE IN EVERY 10 MINUTES.
NOTE:  Performance of tests in accordance with the sequence presented herein is required for items within a given paragraph. All required sequences start from energized systems, with the autopilot disengaged and the respective controls in a neutral condition.
NOTE:  When the aileron engage switch is placed in the ENGAGE position, there may at times be an apparent roll engage transient observed by watching the control wheel move away from center. This is the action of the wings leveling circuit in the autopilot and is entirely normal providing the control wheel error does not exceed 6 degrees. The wheel will recenter after engagement (Ground TP-11 of the roll control channel, while the platform is being recentered) by offsetting the tilt table base (bubble level platform) when the tilt table protractor is set at zero.
May 15/69 22-11-0 Page 504A/504B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(8)  
Provide electrical power to airplane and ensure that the following systems are energized and operating.

(a)  
Hydraulic system B (Ref 29-12-0, Maintenance Practices).

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.

(b)  
Autopilot and yaw damper systems.

(c)  
Attitude reference system (Ref Chapter 34).

(d)  
Compass system (Ref Chapter 34).

(e)  
VOR/GS navigation system (Ref Chapter 34).

(f)  
Low range radio altimeter system (if installed) (Ref Chapter 34).

(g)  
Air data computer (Ref Chapter 34).

(h)  
OMEGA navigation system (Ref Chapter 34).

(9)  
Using altimeter test set, energize radio altimeter at 2000 feet indicated altitude (if installed).

(10)
Check that all control surface areas are cleared of obstructions and personnel.

(11)
Connect adapter assemblies to control wheel hubs.

(12)
Check that flight control A and B switches are on.

NOTE:  The flight control B switch is in the autopilot and yaw damper engage interlock circuit. Hydraulic pressure does not have to be applied for autopilot or yaw damper systems engagement; however, it does have to be applied for systems operation.
C.  Test Autopilot System
(1)  Test roll engage interlocks.
(a)  
With control wheel and column in detent position, engage AIL (roll axis) engage switch on autopilot control panel.

(b)  
Depress autopilot disengage button on captain's control wheel. Observe that roll axis disengages as evidenced by dropping out of the AIL engage switch. Check the autopilot disengage warning lights on the pilot's main panels illuminate momentarily.
　
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