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 B.  The CIWS annunciators provide a general failure warning indication. Specific fault identification is accomplished by inspecting the flight instruments for the presence of warning flags.
 4.  Self-Test Switch
________________
 EFFECTIVITY
 
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 A.  Instrument warning self-test switches are installed on each pilot's flight instrument panel. The CIWS computer and the annunciator lights may be tested by pressing the test switch. When the test switch is pressed, all the annunciators will come on, indicating that the computer is functioning. 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 attitude comparator aural warning units may also be tested by pressing the test switch. The aural warning units will come on when the test switch is pressed.
 5.  Attitude Comparator Aural Warning Unit (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)
 A.  Attitude Comparator aural warning units are installed on each pilot's lower auxiliary panel. When the Attitude error signals from the ADI's exceed a preset amount, the aural warning units will come on along with the INST WARN and ATT lights. The aural warning units will operate intermittently in synchronization with the INST WARN lights. When the attitude error is corrected or when the PRESS TO RESET is pressed on the CIWS annunciator display, the aural warning units will go off.
 6.  Operation (Fig. 3)
_________
 A.  Functional Description
 (1)  General
 (a)  
The central instrument warning computer monitors attitude, radio altimeter, localizer glide slope and heading thru each subsystem module and the master warning module. When failures occur, they are displayed by the INST WARN annunciator light. 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 attitude comparator aural warning unit will also sound when an error occurs in the attitude system.

 (b)  
The attitude error signals and resolver excitation are monitored through the attitude comparison module and master warning module. When failure occurs it is displayed by both the INST WARN and ATT 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, the attitude comparator aural warning units will also sound.

 (c)  
Self-test features are provided to check each subsystem warning module. When the self-test is initiated all annunciator lights will illuminate. 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 attitude comparator aural warning units will also sound.

 (d)  
The input power and internal power supply of the computer are monitored through the power supply modules. When failure occurs it is displayed by the MON annunciator light. The INST WARN light does not come on.

 EFFECTIVITY
 
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 (2)  
Master Warning (Fig. 3)

 (a)  
When all monitored and arming signals (28 volts dc) from the captain's interface systems (Gl through G4) are present and within the prescribed magnitude, the resulting output signals from Gl through G4 is 0. These signals are combined with the TEST signals from the self-test control at G14, and as a result there is no output from the computer. When one or more input signals are lost, a logic one output is produced. This signal is delayed to prevent nuisance signals from triggering the logic.

 (b)  
The low range radio altimeter, glide slope, and localizer output signals are inhibited unless corresponding arming signals are present.

 (c)  
The output signals from G1 thru G4 are fed into the pulse generator. The output of the pulse generator is connected to the SET input of the flip-flop. The SET pulse triggers the flip-flop causing the reset (NOT FAIL) output to go to logic zero and the set (FAIL) output to go to logic one.

 (d)  
The set (FAIL) output (logic one) is combined with the 1.5-Hz oscillator signal at G12 producing a logic one output. G12 output is fed into the captain's master warn lamp driver. The driver output illuminates the captain's INST WARN lamp at a 1.5-Hz per second rate. The lamp is extinguished or reset by pushing the PUSH TO RESET. When this is done, a ground is applied to the RESET logic of the flip-flop circuit causing the set (FAIL) output to go to logic zero and the reset (NOT FAIL) to go to logic one. The output of G12 goes to logic zero removing the signal from the INST WARN lamp. 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 G12 output is also fed to the captain's aural warning unit. If the attitude error signal is present, the driver output will operate the aural warning unit at the 1.5-Hz per second rate. When the PUSH TO RESET button is pressed, the aural warning unit will go off.
　
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