Ncd Display
For an ILS NCD condition, the CDS displays the localizer and glideslope scales and removes the deviation bar and glideslope pointer.
Fail Display
For invalid ILS data, the CDS replaces the localizer scale and deviation indicator with the amber LOC flag when the localizer receiver fails. The amber G/S flag replaces the glideslope scale and pointer when the glideslope receiver fails.
Test
When you push the test switch, the MMR does a check of the internal operation and its interface with other airplane systems. The test takes approximately 36 seconds. This is the test sequence that shows on the LED status indicators during the test:
0 to 2 seconds - the LRU STATUS, the CONTROL FAIL, and the ANT FAIL LEDs come on red
2 to 4 seconds - the LRU STATUS LED is green and theCONTROL FAIL LED is red
4 to 6 seconds - all LEDs go off
6 to 36 seconds - test status shows.
The LRU STATUS segment shows red when there is an internal failure in the MMR. Green shows that the MMR is operating normally.
The CONTROL FAIL segment shows red when an interface to the MMR has a failure. Green shows that all the interfaces to the MMR are normal.
NOTE: The ANT FAIL LED is not used at this time.
ILS - SELF-TEST
Test
You use the NAV control panels to do an ILS test from the flight compartment. The captain NAV control panel does a test of MMR 1 and the first officer NAV control panel does a test of MMR 2.
You need to set these controls to do an ILS test:
Enter a valid ILS frequency into the active frequency display window on the NAV control panel
Set a course on the DFCS mode control panel that is within
90 Degrees of the airplane heading
Push the test switch on the NAV control panel.
To see the ILS test on the NAV display, you must select the approach (APP) mode on the EFIS control panel mode selector. This is the display sequence that shows on the CDS during the ILS test:
For the first 3 seconds, one dot left of localizer deviation and one dot up of glideslope deviation
For the next 3 seconds, one dot right of localizer deviation and one dot down of glideslope deviation
Displays return to normal indications.
12.15. Marker Beacon System в737.
Подробно рассматривается в [4] рекомендуемой литературы.
General
The marker beacon system supplies visual and aural indications when the airplane flies over airport runway marker beacon transmitters.
Abbreviations and Acronyms
A/P - autopilot
AC - alternating current
ACP - audio control panel
ALT - alternate
AMP - amplifier
B - both
BITE - built-in test equipment
CDS - common display system
DEU - display electronics unit
DME - distance measuring equipment
FDAU - flight data acquisition unit
DU - display unit
FT - functional test
GND - ground
Hz - hertz
I/C - intercom
ILS - instrument landing system
IM - inner marker
I/O - input/output
LCD - liquid crystal display
LED - light emitting diode
LRU - line replaceable unit
MAINT - maintenance
MB - marker beacon
MHz - mega hertz
MM - middle marker
NAV - navigation
NC - not connected
ND - navigation display
NORM - normal
NVM - non-volatile memory
OM - outer marker
PFD - primary flight display
R - range
REU - remote electronics unit
RF - radio frequency
R/T - receive/transmit
RCVR - receiver
STA - station
TFR - transfer
V - voice
V - volt
VHF - very high frequency
VOR - vhf omnidirectional ranging
