(3)
Monitors its own operation through primary and secondary power circuits and through internal self-test features.
(4)
Provides a manual reset to the master warning module in the computer and a dimming feature to the attitude comparison and computer monitor annunciator lights.
On AF ALL; AT ALL; AZ ALL; GN ALL; MD ALL; SN ALL; VM ALL; IB 406-499;
LH 011-099; PLUS ATLAS AIRPLANES INCORPORATING SB 34-2059, provides a manual reset to the captain's and first officer's attitude comparator aural warning units.
C. The CIWS interfaces with the following systems through the different switching networks (Fig. 2).
(1)
The Magnetic Heading Reference System (34-21-00) supplies magnetic heading flag signals to the CIWS computer.
(2)
The VOR/ILS System (34-31-00) supplies localizer (LOC) and glide slope (GS) flag signals to the computer.
(3)
The Low Range Radio Altimeter System (34-33-00) supplies radio altimeter flag and 1500-foot trip signals directly to the computer. The 50-foot trip signal is fed to AP/FD accessory box 2, which disables the glide slope warning channel at 50-foot altitude to minimize nuisance warnings on passing the glide slope station.
(4)
The Low Range Radio Altimeter System (34-33-00) supplies radio altimeter flag and 1500-foot trip signals directly to the computer.
(a)
XA all except AF 121, 122, 157, 161, 183, 184; the 50-foot trip signal is fed to AP/FD accessory box 2, which disables the glide slope warning channel at 50-foot altitude to minimize nuisance warnings on passing the glide slope station.
(b)
AF 121, 122, 157, 161, 183, 184; the 50-foot trip signal is fed to the AFC accessory boxes 1 and 2, which disables the glide slope warning channel at 50-foot altitude to minimize nuisance warnings on passing the glide slope station.
EFFECTIVITY
ALL 30 Page 1 Sep 25/9434-44-00
MASTER WARNING
ANNUNCIATOR
TEST SWITCH
ATTITUDE COMPARISON WARNING
COMPUTER ANNUNCIATOR
MONITOR ANNUNCIATOR
CIWS ANNUNCIATOR
AF ALL; AT ALL; AZ ALL; GN ALL; MD ALL;
SN ALL; VM ALL; IB 406-499; LH 011-099;
PLUS ATLAS AIRPLANES INCORPORATING SB 34-2059
Central Instrument Warning System Component Location Figure 1
EFFECTIVITYALL
799 Page 2
34-44-00
Aug 25/85
(5)
The Inertial Navigation System (34-41-00) supplies the computer with attitude flag signals and true heading flag signals.
(6)
XA all except AF 121, 122, 157, 161, 183, 184; the Flight Director (34-26-00) and Autoflight (Chapter 22) systems provide glide slope (GS) and localizer (LOC) capture signals thru the AP/FD accessory box 2 to the computer.
(7)
AF 121, 122, 157, 161, 183, 184; the Flight Director (34-26-00) and Autoflight (Chapter 22) systems provide glide slope (GS) and localizer (LOC) capture signals through the AFC accessory boxes 1 and 2 to the computer.
(8)
The Attitude Director Indicator supplies flag signals and attitude error signals to the computer for cross-channel attitude comparison between captain's and first officer's ADI's.
(9)
The Horizontal Situation Indicator supplies flag signals to the computer.
(10)
The Electrical Power System (24-22-00) supplies 115-volt ac power to the central instrument warning system. Computer operating power is supplied from the 115-volt ac flight instrument bus No. 2. Computer monitoring power is supplied from 115-volt ac essential flight instrument bus.
2. CIWS Computer
_____________
A. The CIWS computer is installed on shelf E1-1 in the main equipment center. The computer comprises solid-state digital circuits packaged on plug-in cards. The logic circuits accept 28-volt dc flag warning signals and differential resolver error signals through level detectors. Logic circuits process the monitored inputs and supply outputs to drive the CIWS annunciators. The computer contains self-test and monitoring features. On AF ALL; AT ALL; AZ ALL; GN ALL; MD ALL; SN ALL; VM ALL; IB 406-499; LH 011-099; PLUS ATLAS AIRPLANES INCORPORATING SB 34-2059, the computer also drives the attitude comparator aural warning units.
3. CIWS Annunciators
_________________
A. Separate CIWS annunciator displays are installed on each pilot's flight instrument panel. Each annunciator display consists of a master comparison light (INST WARN), an attitude comparison light (ATT), and a computer monitor light (MON) which indicate the status of selected duplicate navigation systems. When the computer detects an error between the inputs from a dual system, the INST WARN light will flash or the INST WARN light will flash and the ATT light will come on. When power is lost to the CIWS computer, the MON light will come on; INST WARN light does not come on. Dimming circuits are also provided for the ATT and MON lights. When the PRESS TO RESET is pressed, the INST WARN light will go out and other light(s) will dim and remain on until the discrepancy is corrected. On AF 121, 122, 161, 172 thru 190, 193 and LH 056, detection of a new error will cause the associated light to come on bright. Previously dimmed lights will remain dim.
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