(7)  
Speed Brake Alert (Fig. 8)

 (a)  An alert is generated if the speed handle is moved beyond armed detent and if at least two throttles are advanced beyond 7.5 degrees TLA or if flaps are in landing range and altitude is more than 15 feet or if the airplane is at an altitude of between 800 and 15 feet. The alert consists of a caution aural, master caution lights and an EICAS message, "SPEEDBRAKE EXT".

 (8)  
Stall Warning

 (a)  
The Stall Warning is discussed in detail in chapter
 27-32-00/001.

 (b)  
Warning of an impending stall is provided by two independent stall warning systems. Both systems are enabled in flight and deactivated on the ground through the air/ground logic.

 (c)  
The warning is given by vibrating both control columns. A control column nudger moves the column forward.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

AIRPLANE

Configuration Module - Speed Brake Alert Function
Figure 8

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400
MAINTENANCE MANUAL

 (d)  
The functions are calculated using airplane dynamic information such as pitch rate, MACH and airspeed. The position of the leading and trailing flaps, landing gear, speed brakes, and air/ground switches are also utilized.

 (e)  
Selecting the stall warning test switches in either the L or R position checks the left and right stall warning systems, respectively. When either the left or right system is tested both control column vibrates. If both systems are tested at the same time, both columns vibrate and control column nudger activates (optional).

 (9)  
Altitude Alert

 (a)  The Altitude Alert System provides crew awareness of Altitude Capture and Deviation. This is provided in the form of indications on the Primary Flight Display (PFD) units for Altitude Capture. For Altitude Deviation in addition to indictions on the PFD there is an aural warning and an EICAS message. The actual altitude is compared against the selected altitude on the Mode Control Panel (MCP). This difference is then compared against predetermined fixed values to determine Capture and Deviation points.

 (10)
 Windshear

 (a)  The windshear warning activates the master warning light and is not subject to takeoff inhibit. The light is deactivated by pushing the master warning reset.

 (11)
 Ground Prox Warning

 (a)  The ground prox warning activates the master warning lights and is not subject to takeoff inhibit. The lights only may be deactivated by the master warning reset.

 (12)
 Resettable Configuration Warning

 (a)  This warning activates the master warning light and the siren and is not subject to the takeoff inhibit. The master warning reset will deactivate both the light and siren.

 (13)
 Non-Resettable Configuration Warning

 (a)  This warning activates the master warning light and the siren. The master warning reset will deactivate the light, but the siren can be deactivated only when the warning input is removed.

 (14)
 Cabin Pressure Warning

 (a)  A cabin pressure warning activates the master warning light and the siren. This warning is subject to the takeoff inhibit.

 (15)
 Over-rotation (optional)

 (a)  Over-rotion senses signals from pitch angle, pitch rate,PSEU, over-rotation, AIR/GND switches and computed airspeed. Annunciation is by stick shaker.
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