(b)
All circuit breakers for AIR DATA, FLIGHT DIRECTOR, VERTICAL GYRO and VOR/GS systems No. 1 and No. 2.
B. Depress lever latch release trigger allowing lever to move away from handle.
C. Move lever in an opening direction forcing unit away from rack electrical connector.
D. Remove unit from rack mounting.
3. Install Accessory Unit
A. Slide accessory unit into rack mounting with lever latch in open position until lever engages rack-mounted fork.
NOTE: Remove any protective caps or bags from the unit or shelf prior to installation.
B. Move lever latch to locked position (Fig. 401).
C. Check electrical connector mating dimensions and lever latch fork adjustment per 20-10-111, Electrical/Electronic Black Box - MP.
CAUTION: IMPROPER ADJUSTMENT OF ASSEMBLIES ON EQUIPMENT SHELVES MAY CAUSE CIRCUIT MALFUNCTION OR EQUIPMENT DAMAGE
510
Jun 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-26-61 Page 401
G42479
Flight Instrument Accessory Unit Installation 510
34-26-61 Figure 401 Jun 20/90
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
4. Test Accessory Unit
a.
After installation, the following test checks for proper mating of the accessory unit electrical connectors. For a complete operational test of either accessory unit, perform the Flight Director System A/T per 34-26-0/501.
B.
Test Flight Instrument Accessory Unit M160
(1)
Close the circuit breakers opened in par. 2.A.(1) and circuit breakers for the Indicator Lights and Approach Progress Display (APD) Dim and TEST power.
(2)
Depress and hold the bank of captain's and first officer's A/P APD annunciator light caps. Check A/P APD annunciator lights are on bright.
(3)
Position the MASTER DIM/TEST switch on the P2 panel to DIM while holding A/P APD light caps down. Check A/P APD annunciator lights dim.
(4)
Position the MASTER DIM/TEST switch to BRT. Check A/P APD annunciator lights return to bright.
(5)
Release the A/P APD light caps.
(6)
Remove the electrical power if it is no longer necessary.
500
May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-26-61 Page 403
NAVIGATION WARNING SYSTEM - DESCRIPTION AND OPERATION
1. General
A. The navigation warning system compares the output signals from each of the following No. 1 and 2 systems: compass, attitude reference, and VOR/ILS navigation. The signals compared are heading (compass), roll and pitch (attitude reference), and localizer and glide slope deviation (VOR/ILS navigation). When an out-of-tolerance condition exists between any of the output signals, the warning system provides a warning indication through actuation of appropriate warning lights. On GJ ALL EXCEPT B-2509 and B-2510, provisions are also provided to indicate an out of tolerance condition for the Low Range Radio Altimeter system if a second unit is installed. On GJ B-2509 and B-2510, ALT comparison is provided.
B. The system consists of a comparator warning unit and two annunciator panels. The annunciator panels contain the warning lights which light to give a warning indication, and also serve to identify the system malfunctioning. Power to the comparator warning unit is also monitored through the MON PWR warning lights on the annunciator panels which light on loss of ac or dc power to the unit. A test button is provided on the captain's instrument panel and is used to check the operation of the various channels (heading, roll, pitch, localizer deviation, and glide slope deviation) in the system. Location of the components is shown in Fig. 1.
2. Operation
A. The system receives power when the COMPARATOR circuit breakers at the circuit breaker panel P6 are closed (Fig. 2). The heading, and the pitch and roll warning channels operate in a similar manner. Taking the heading warning channel as an example: Two differential resolvers are used for the comparison. The comparison signal is obtained from the resolver in the captain's HSI. The other resolver is in the first officer's HSI. From the transmitter portion of the captain's resolver, heading is transferred to the control transformer portion of the first officer's resolver. Here, a comparison is made between heading as sensed by both compass systems. Any variation in heading produces an output through the transmitter portion of the first officer's resolver to the comparator warning unit. This warning signal is fed to a rectifier and filter time delay circuit before being fed to the threshold detector. The filter time delay prevents nuisance warnings during short duration errors. Under normal operation, the threshold detector senses only signals pertaining to a difference in heading of 6 degrees or greater before providing an output to activate the HDG warning lights.
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