COMPARATOR WARNING UNIT - REMOVAL/INSTALLATION
1. General
A. The comparator warning unit is rack mounted on rack E3-4 in the main equipment center. Electrical connections are made at the rear of the unit.
2. Remove Comparator Warning Unit
A. Open COMPARATOR-MON and COMPARATOR-PWR circuit breakers on P6 load control center.
B. Carefully remove comparator warning unit from mount (Ref 20-10-0, E/E Rack Mounted Components).
3. Install Comparator Warning Unit
A. Ensure COMPARATOR-MON and PWR circuit breakers are open.
B. Position comparator warning unit in mount and secure.
C. Test comparator warning unit electrical connections as follows:
(1)
Provide power to P6 load control center.
(2)
Close circuit breakers opened in par. 2.A. above.
(3)
Comparator warning unit and lights may be tested by pressing TEST button. When button is depressed, all annunciator lights except MON PWR will illuminate, indicating that comparator warning unit is functioning.
NOTE: Annunciator lights can be dimmed by pushing on PUSH-TO-DIM bar.
(4)
Remove electrical power if no longer required (Ref 24-22-0, Electrical Power).
597
Feb 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-29-11 Page 401
NAVIGATION WARNING ANNUNCIATOR - REMOVAL/INSTALLATION
1. General
A. The navigation warning (instrument comparator) annunciators are installed on the captain's and first officer's main instrument panels.
2. Remove Navigation Warning Annunciator
A. Open COMPARATOR-MON and COMPARATOR-PWR circuit breakers on P6 load control center.
B. Remove attaching screws or module retainer.
C. Disconnect electrical connector from annunciator module.
D. Remove annunciator module from instrument panel.
3. Install Navigation Warning Annunciator
A. Ensure COMPARATOR-MON and PWR circuit breakers are open.
B. Connect electrical connector to annunciator module.
C. Secure annunciator module to instrument panel with attaching screws or module retainer.
D. Test annunciator electrical connections as follows:
(1)
Provide electrical power to P6 load control center.
(2)
Close circuit breakers open in par. 2.A. above.
(3)
Comparator warning unit and lights may be tested by pressing TEST button. When button is depressed, all annunciator lights except MON PWR will illuminate, indicating that comparator warning unit is functioning.
NOTE: Annunciator lights can be dimmed by pushing on PUSH-TO-DIM bar.
(4)
Remove electrical power if no longer required (Ref 24-22-0 Electrical Power).
597
Feb 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-29-21 Page 401
VOR/ILS NAVIGATION SYSTEMS - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The VHF omnidirectional range (VOR) and instrument landing system (ILS) provides information of airplane position with respect to, and deviation from a selected VOR course, or localizer (LOC) and glide slope approach beams. Information is also provided of airplane magnetic bearing to the VOR ground station under reception.
B. Two systems, captain's and first officer's, are installed. Each is comprised of the following components: navigation unit (combined VOR/ILS receiver and instrumentation unit), VOR antenna, GS antenna and control panel. Location of the components is shown in Fig. 1. The standby bus supplies 115 volts ac and 28 volts dc to the system through VOR/LOC, GS and instrument circuit breakers on P18, load control center.
C. VOR/LOC course deviation information is displayed by the course deviation bar in the horizontal situation indicator (HSI) and by the localizer pointer (runway symbol)in the attitude director indicator (ADI). Glide slope (GS) information is displayed by the GS pointer in the ADI and HSI. VOR station bearing information is displayed by the pointers in the radio magnetic deviation indicators (RMI). VOR/LOC and GS information is also supplied to the flight director computers and to the autopilot. GS deviation information is also supplied to the ground proximity warning system (GPWS) computer. The ADI and HSI are described under 34-26-0, Flight Director System, and the RMI under 34-21-0, Compass System.
D. Switching is provided to enable either system to feed both captain's and first officer's indicators, flight director computers, the autopilot, and the GPWS computer. Switching is accomplished through the NAV transfer relays, and controlled through the VOR/ILS (VHF NAV) transfer switch.
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