(d)
Agility Tuning
1) The flight management system provides a ground to J1-16, and K2 energizes. As agility tuning occurs only during AUTO, K1 is energized and the frequency select common is applied, through K1 and K2, to the auto display, and dashes are displayed.
(e)
Test Functions
1) When the airplane LIGHTS master dim and test switch on center instrument panel P2 is in TEST position, relay K3 in the VHF NAV control panel is energized. This illumates the AUTO and MAN switch indicators and applies a test discrete to the AUTO and MANUAL frequency displays. The frequency displays test indication is a flashing 188.88, alternating 2 seconds on and 1 second off.
2) VHF NAV tests are enabled by grounds from the test switches. When a VOR, UP/LT, or DN/RT test is initiated, the flight management system interlock is interrupted.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
34-31-02
ú ú 04 Page 25 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú
34-31-02
ú ú 02 Page 26 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
FIG.9
FIG.9
VHF NAV Control Panel Schematic
Figure 5
AGILITY MODE(FIG. 11)
FREQ SEL
VHFCOMMON
NAVDME
34-55-00)
AUTO TUNENC
AUTO TUNENC FIG. 11
FREQ COMM
10 MHz
1 MHz
NC
MHz0.1
MHz 0.05
10 MHz
DME AND
1 MHz
VHF NAV
MHz0.1TUNING MHz 0.05(FIG. 11)
31 G/S LOC ENGAGE(FIG. 11)VOR TEST
UP/LT TEST
FMS
INTERLOCK
FIG. 15
DN/RT TEST
DME TESTCHASSIS GND
A
737-300/400/500MAINTENANCE MANUAL
(3) Electronic Flight Instrument Displays (Fig. 6)
(a)
The purpose of the electronic flight instruments (EADI's and EHSI's) is to display basic attitude and navigation data. The displays are color CRTs which receive symbol data from the EFIS symbol generator. Navigational format and content are mainly supplied by the FMCS. Attitude data comes from the IRS. Both indicators are also capable of displaying text information such as flight parameters and system status.
(b)
The colors used on the displays generally have the following meanings: 1) GREEN - indicates engaged flight mode annunciations,
dynamic conditions 2) WHITE - indicates present status situation, scales, flight mode annunciations 3) PINK (Magenta) - Indicates command information, pointers, symbols, fly-to condition 4) BLUE (Cyan) - Indicates non active background information
(i.e.
EADI sky) 5) RED - indicates warning 6) YELLOW - indicates cautionary information, faults flags
(i.e.
EADI ground)
7) BLACK - indicates blank areas
(c) EADI
1) The EADIs display basic attitude information, ILS data, radio altitude, and autopilot mode data. They also display fault data (NAV warning flags) for the input systems in the event of a failure. The display consists of a standard attitude display centered on the screen. Text, which represents various flight parameters, is located in each corner of the screen. The localizer pointer and scale are presented below the attitude display while the glide slope pointer and scale are on the right side.
2) The localizer and glide slope deviation pointers and scale display deviation from the respective beam. They indicate the direction that the airplane must go in order to reduce the deviation to zero.
3) For ILS no-computed data (NCD) failures on the EADI, the pointer for the failing channel is removed. For ILS invalid data failures, the pointer and scale for the invalid G/S or LOC channel are removed.
(d) EHSI
1) The EHSI displays flight information in a horizontal format for the full and expanded VOR and ILS modes. It displays standard type HSI information and many other flight parameters in modified formats. It also is used for the WXR display in the MAP, EXP-VOR, and EXP-ILS modes. The VOR or ILS modes are annunciated in the lower left corner of the EHSI with VOR or ILS tuned frequency annunciated in the lower right corner.
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