34-29-21
ú ú 02 Page 401 ú Nov 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
C. Procedure
S 864-048
(1) Make sure these circuit breakers are open:
(a) P6 Circuit Breaker Panel
1) COMPARATOR-MON
2) COMPARATOR-PWR
S 434-014
(2)
Connect the electrical connector to the annunciator module.
S 424-007
(3)
Attach the annunciator module to the instrument panel with the screws or module retainer.
S 864-009
(4)
Supply electrical power (Ref 24-22-00/201).
S 864-010
(5)
Close these circuit breakers and remove the DO-NOT-CLOSE tags:
(a) P6 Circuit Breaker Panel
1) COMPARATOR-MON
2) COMPARATOR-PWR
S 744-016
(6) Push and hold the PUSH TO TEST switch on the comparator monitor unit.
(a)
Make sure all six amber annunciator lights come on.
(b)
AIRPLANES WITH A COLLINS -002 COMPARATOR MONITOR UNIT; Make sure the red MON PWR light comes on.
S 864-018
(7)
Push the PUSH-TO-DIM bar.
(a) Make sure the annunciator lights dim.
(8)
Release the PUSH-TO-DIM bar.
S 864-019
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-29-21
ú ú 04 Page 402 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
S 744-023
(9)
Release the PUSH TO TEST switch.
S 864-013
(10)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-29-21
ú ú 02 Page 403 ú Jul 15/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
VOR/ILS NAVIGATION SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________
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, control panel and a localizer antenna. A flight instrument accessory unit is shared by both systems. The attitude director indicator (ADI), horizontal situation indicator (HSI) and radio digital distance magnetic indicator (RDDMI) on each flight instrument panel provide the VOR/ILS navigation displays. Location of the components is shown in Fig. 1. The battery bus and the standby bus in load control center P18 and electronic bus 2 in load control center P6 supply 115 volts ac and 28 volts dc to the VOR/ILS navigation systems through the VOR/LOC, GS and instrument transformer circuit breakers.
C. VOR/LOC course deviation information is displayed by the course deviation bar in the HSI and by the localizer pointer (runway symbol) in the ADI. Glide slope (GS) information is displayed by the vertical pointer in the ADI and HSI. VOR station bearing information is displayed by the pointers in the RDDMI. VOR/LOC and GS information is supplied to the digital flight control system (DFCS) computers and to the instrument warning system. GS deviaiton information is also supplied to the ground proximity warning system (GPWS) computer. The VOR/LOC station identification audio is monitored through the airplane audio integrating system (AMM 23-50-00).
D. Switching is provided to enable either system to feed both captain's and first officer's ADI's and HSI's and the GPWS computer. Switching is accomplished through the VHF NAV transfer relays, and controlled through the VHF NAV transfer switch. In addition, the HSI transfer switches select either the VOR/ILS navigation system or the flight management computer system (FMCS) (AMM 34-62-00) to drive the HSI navigation displays.
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