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 2)  The inverting buffer output signals enable two sets of logic circuits. These circuits control two identical owl aural generators. The output signals are then routed through the preamplifiers to the loudspeakers to provide the owl aural sound. The owl aural generators function in a leader/follower manner same as the siren generators.
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 (d)  
The siren/owl modules supply amplification of the bell/chime warnings and the ground proximity voice.

 (e)  
AIRPLANES WITH TCAS; The Siren/Owl modules also amplify the TCAS aural outputs.

 (6)  Takeoff Configuration Warning Module Function (Fig. 7)
 (a)  
The Takeoff Configuration warning module provides aural and visual warnings for improper airplane configuration during takeoff. The module receives a dual input of +12 volts dc from power supply modules A and B. Each voltage input line is diode-isolated and fuse protected.

 (b)  
Seven areas are monitored for takeoff configuration warning. These are the flaps, slats, horizontal stabilizer, speed brake, parking brake, air/ground logic, and N1.

 (c)  
The takeoff warning logic is armed by signals from the air/ground relay(s) and N1. The air/ground relay(s) must be in the ground position and N1 from either engine must be greater than 66.7 percent. The enabled output of the takeoff arm logic circuit is routed to the four arm/warning logic circuits.

 (d)  
One of the arm/warning logic gates is enabled for each of the following conditions: 1) The FLAPS message logic circuit is enabled when one of the

 following conditions occur: a) When the leading edge slats are not in the takeoff position. b) When the trailing edge flaps are not in the takeoff position of 1, 5, 15, or 20.
 2)  The STABILIZER message logic circuit is enabled when the horizontal stabilizer is not in the takeoff position (green band).
 3)  The PARKING BRAKE message logic circuit is enabled when the parking brake is in the SET position. 4) The SPOILERS message logic circuit is enabled when the speed brake handle is not in the down detent position.
 (e)  The output signal from each message logic circuit is applied to the latch circuit in the thrust lever logic path. This holds the warning condition after the thrust lever is returned to the idle position. It is then removed when the warning condition is corrected.
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