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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.

CAPTAIN'S HSI

VHF NAV/DME-1CONTROL PANEL CAPTAIN'S RDDMI F/O'S RDDMI

FMC-CDU
VOR TEST PROCEDURE

VHF NAVTRANSFER SWITCH

CAPTAIN'S HSI
TRANSFER SWITCH

DFCS MODE
CONTROL PANEL

VHF NAV/DME-1
CONTROL PANEL

FMC-CDU VOR TEST PREPARATION
VOR Self-Test PictorialFigure 16

A
737-300/400/500MAINTENANCE MANUAL
 (14) ILS Self-Test Pictorial
 (a)  Figure 17 is a pictorial presentation for system No. 1 ILS (up/left and down/right) self-test preparation and flight instrument display for the ILS self tests. 1) The ILS self-test preparation and procedure described here
 is for the VOR/ILS navigation system No. 1. The test of system No. 2 is performed in the same way, using the controls and indicators for system No. 2.
 2)  Test Preparations a) Prior to testing system No. 1, the following switches
 must be in the indicated positions: VHF NAV Transfer Switch . . . . . . NORMAL CAPT'S HSI Transfer Switch. . . . . VOR/ILS
 b)  Next, select a localizer frequency of 108.10 MHz on the VHF NAV control panel. Observe the ILS status on the sensor status display on the FMC CDU.
 3)  Test Procedure

 a)  To initiate the ILS up/left self-test, press and hold the TEST switch in the UP/LT position, and observe the following displays:
 Captains HSI

____________ Deviation Bar. . . . . . . . . . . . Left 1 Dot G/S Deviation. . . . . . . . . . . . Up 1 Dot Warning Flags. . . . . . . . . . . . *[1] Captains ADI
____________ Runway Symbol. . . . . . . . . . . . Left 1 Dot G/S Deviation. . . . . . . . . . . . Up 1 Dot Warning Flags. . . . . . . . . . . . *[1] Instrument Comparator
_____________________ LOC Light. . . . . . . . . . . . . . ON G/S Light. . . . . . . . . . . . . . ON FMC CDU
_______
 VHF NAV Status . . . . . . . . . . . OK

 *[1]  Warning flags remain in view for 3 |1 seconds, disappear, and 20 |5 seconds after initiating test, reappear and remain in view for as long as self-test is actuated.
 b)  Release the TEST switch and verify all ILS indications return to normal.
 c)  Perform the test again with the switch in the DN/RT position. The indications are similar to UP/LT test, but this time the deviation bar and runway symbol drive right 1 dot, and the glide slope deviation pointer drives down 1 dot.
 d)  Repeat the VOR and ILS self-tests with the VHF NAV transfer switch in BOTH ON 1 position and then in BOTH ON 2 position. Test displays appear on the captain's and first officer's instruments and the instrument comparator LOC and G/S lights are inhibited.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
INSTRUMENT COMPARATOR
PUSH-TO-DIM
MONPWR HDG PITCH ROLL GS LOC ALT
VHF NAV
DH
BOTHBOTH
MG MILES GND SPEED
ON 1 ON 2
NORMAL TEST
20 20 O
VI
L
FAST
R
UP/LT
S
10 10
VHF NAV
HSI
TRANSFER SWITCH
1
DN/RT
10 10
VOR/
SLOW ILS
20 20
A
VHF NAV/DME-1
LERT
CONTROL PANEL
NAV
TEST
CAPTAIN'S HSI
TRANSFER SWITCH

CAPTAIN'S HSICAPTAIN'S ADI
MANUAL
FMCS SENSOR S
LRU LEFTVHF NAVDME OK
FMC-CDU
ILS TEST PROCEDURE (UP/LEFT)
INSTRUMENT COMPARATOR
VHF NAV/DME-1
PUSH-TO-DIM
MON HDG PITCH ROLL GS LOC ALT
CONTROL PANEL
PWR DH
MG MILES GND SPEED
TEST
20 20 O
VI
L
FAST UP/LT
R S
10 10
3
5
3
0
1
DN/RT
　
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