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E.  Localizer and glide slope deviation are compared separately in two comparators. The signals are modified and amplified before being fed to threshold detectors. The operations performed on the localizer and glide slope deviation signals are identical. If the output from either comparator (localizer, or glide slope) exceeds a certain predetermined value, the appropriate threshold detector will provide an output to the associated warning lights. In order to prevent operation of the comparators, other than when the deviation signals are present, they are activated by mode signals. When both navigation units are in the ILS mode, 28 volts dc is applied to both comparators (provided the nav transfer switch is in normal position). After a suitable time delay, the comparators become active. In the case of the glide slope comparator, in addition to the navigation units being in the ILS mode, the glide slope high level (Super) flag signals must be present. With the super flag signals present, the glide slope comparator will be activated. The glide slope super flag signals appear only when glide slope receivers are activated, and glide slope signals of a predetermined value are present to them. The localizer and glide slope channels are not activated when the VHF NAV transfer switch is set to BOTH ON 1 or BOTH ON 2.
F.  The warning lights remain on for as long as a fault condition exists. The lights can be dimmed by pushing on them. The lights will remain dimmed until the fault is cleared, at which time they are automatically reset to their original (bright) condition.
G.  The comparator warning unit and the lights may be tested by pressing the test button. When the button is depressed, all the warning lights (except MON PWR) will light, indicating that the comparator warning unit is functioning.
H.  A switch and several test lights are provided on the comparator warning unit for system test purposes (Fig. 1).
557 
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5C8  Navigation Warning System Schematic 
Jun 20/85  Figure 2 (Sheet 2)  34-29-0 
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NAVIGATION WARNING SYSTEM -ADJUSTMENT/TEST
EFFECTIVITY

GJ ALL EXCEPT B-2509 and B-2510
1.  Navigation Warning System Test
A.  General
(1)  Prior to performing test procedures for the navigation warning system, determine that the VOR/ILS navigation, flight director, compass, and vertical gyro systems are operational.
B.  Equipment and Materials
(1)  
Signal generator - Instrument Flight Research Corp., Inc., type NAV-401L, or equivalent (2 required)

(2)  
Calibrated tilt table (2 required)

C.  Prepare to Test Navigation Warning System
(1)  
Open vertical gyro CB's on P6 and P18 circuit breaker panels.

CAUTION:  IF GYROS HAVE BEEN OPERATING, TURN OFF POWER BEFORE REMOVING VERTICAL GYRO AND ALLOW APPROXIMATELY 15 MINUTES FOR GYROS TO COAST DOWN. IF UNIT IS REMOVED TOO SOON, GYROSCOPIC PRECESSION COULD RESULT IN DAMAGE TO THE GYRO.

(2)  
Install vertical gyros 1 and 2 on tilt tables and level.

(3)  
Connect external electrical power and energize P6 and P18 circuit breaker panels.

(4)  
Check that following CB's are closed: NO. 1 and NO. 2 INSTRUMENTS, NO. 1 and NO. 2 NAVIGATION, and FLT DIR-1 and 2.

(5)  
Turn on signal generators, allow to warm up and calibrate as indicated in signal generator instruction manual.

D.  Test Navigation Warning System
(1)  Test Power, Dim and Self-Test
(a)  
Place VERTICAL GYRO, COMPASS, and VHF NAV transfer switches on overhead panel in NORMAL position.

(b)  
Synchronize both compass systems.

(c)  
Check that captain's and first officer's instrument warning panel lights are out.

(d)  
Open comparator power circuit breaker. Check that MON PWR lights on instrument warning panels come on.

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(e)  
Push either captain's or first officer's instrument warning panel face. Check that warning lights dim.

(f)  
Close comparator power circuit breaker. Check that MON PWR lights go out.

(g)  
Press comparator test button on captain's instrument panel. Check that all lights except MON PWR lights on instrument warning panels come on.
　
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