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B. Electrical power for system No. 1 is provided by the 28V DC ELEX PWR-1 bus on load control center P18. Electrical power for system No. 2 is provided by the 28V DC ELEX PWR-2 bus on load control center P6.
Mach/Airspeed Indicator
_______________________
A. A mach/airspeed indicator is installed on each pilot's instrument panel. The mach/airspeed indicator's maximum operating airspeed (Vmo) pointer displays Vmo as a function of airspeed and altitude. The indicator's overspeed limit switch provides an output signal to the mach airspeed aural warning clacker in the aural warning unit module whenever the Vmo is exceeded or the mach airspeed warning test switch on the flight recorder-mach airspeed warning module is pushed.
B. When a mach airspeed fault condition is detected, the Vmo failure warning flag will appear in the face of the mach/airspeed indicator and the Vmo overspeed limit switch will be inhibited from producing an overspeed warning.
Mach Airspeed Aural Warning Clacker
___________________________________
A. The mach airspeed aural warning clacker is located in the aural warning unit module mounted on the forward electronics control panel P9. Two clackers, one for each system, are installed in the aural warning unit module. The clacker will sound, at approximately 8Hz, whenever the airplane exceeds mach airspeed limits or during a system test. The aural warning clacker gives a warning signal that is different from the aural warnings for other systems (Ref Chapter 31, Aural Warning System).
Mach Airspeed Warning Test Switch
_________________________________
A. The MACH AIRSPEED WARNING TEST switch is located on the flight recorder-mach airspeed warning module installed in the aft overhead panel P5. Two switches, No. 1 and No. 2, are installed on the panel, one switch for each system. The MACH AIRSPEED WARNING TEST switch is used to do a test of the mach airspeed warning system. When you push the switch, the overspeed limit switch in the mach/airspeed indicator closes. This supplies a ground to the aural warning clacker in the aural warning unit module. The clacker sounds until the test switch is released.
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A 737-300/400/500MAINTENANCE MANUAL
PILOTS' AFT
OVERHEAD PANEL
SEE B
CAPTAIN'S
INSTRUMENT FIRST OFFICER'S
PANEL SEE A INSTRUMENT PANEL
SEE A
FWD ELECTRONICS CONTROL PANEL
SEE C
MACH
AIRSPEED WARNING TEST TEST NORMAL
FLIGHT RECORDER
NO 1 NO 2
OFF
A
MACH AIRSPEED INDICATOR MACH AIRSPEED WARNING MODULE
A B
MACH AIRSPEED AURAL WARNING CLACKERS
FWD
AURAL WARNING UNIT MODULE C
Mach Airspeed Warning System Component Location Figure 1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
28V DC ELEX PWR-1 P18-2
28V DC ELEX PWR-2 P6-1
ALTITUDE 1000 FT
40
30
20
10
0
UNIT MODULE (STA 205)
MAXIMUM Mmo/Vmo GRAPH
Mach Airspeed Warning System Schematic Figure 2
T81261
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A 737-300/400/500MAINTENANCE MANUAL
5. Operation (Fig. 2)
_________
A. Functional Description
(1)
Maximum operating airspeed (Vmo) is determined by the mach/airspeed indicator from airspeed and altitude inputs from the digital air data computer. The relation between Vmo and Mmo is shown by the graph in Fig. 2.
(2)
Below 25,968 feet of altitude the airplane airspeed is limited to 340 knots computed airspeed. Above 25,968 feet the airplane maximum mach (Mmo) is limited to 0.820 mach. When mach is held constant the maximum airspeed decreases as altitude increases. Vmo is shown by a pointer on the mach/airspeed indicator.
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