曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營(yíng)店坑蒙拐騙欺詐消費(fèi)者

E.  The indicator generates a VMO signal for controlling the maximum operating airspeed pointer mechanism in the indicator. The indicator also provides an output signal to actuate an aural warning when maximum operating speed is exceeded.
F.  The air data computers provide a valid signal to the indicators. Monitoring within the indicator of the maximum operating airspeed display output signal and the maximum operating airspeed function switch is capable of detecting the following conditions; 1) absence of the altitude valid signal from the air data computer, 2) loss of electrical power to the indicator, 3) failure of indicator power supply, 4) open circuit in interlocks. When a fault condition is detected, a VMO flag in the indicator will come into view and the maximum operating airspeed switch will be inhibited from producing an airspeed warning.
G.  The indicators have a self-test capability for the maximum operating airspeed switch. Operation of the mach airspeed warning test switch results in an overspeed aural warning unless failure monitoring within the indicator detects a fault condition. The aural warning input is switched to external ground through the indicator airspeed switch. Power to the indicators is 26 volts ac through circuits breakers located on circuit breaker panel P18 for the captain's indicator and P6 for the first officer's indicator.
5C8 
Feb 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-12-01 Page 3 

3.  Vertical Speed Indicator
A.  Vertical speed or rate of climb indicators are provided for the pilots. These indicators are operated by corrected altitude rate signals from the air data computers. The rate of change of altitude is indicated by a radial pointer in thousands of feet per minute. Incorporated in the instrument is a power supply, reference voltage supply, a demodulator, amplifier and motor differential mechanism to provide readings of instantaneous vertical speed. A failure monitor will show an OFF flag in the event of electrical power loss, loss of flag power from ADC, loss of input signal and internal malfunction (Fig. 3)
4.  Electric Altimeter
A.  Electric altimeters are provided for the pilots. Each altimeter is an electric drum-pointer type that receives altitude information from the central air data computer. The altitude is displayed in 1000-, 100-, and 20-foot increments on drum counters and in 100-and 20-foot increments by a pointer which reads against a fixed scale. The range of the altimeter is from -1000 to 50,000 feet with altitudes below sea level displayed by the rotating pointer and a NEG flag covering the counter drums. A red warning flag will cover the counter drums in the event of a failure. The failure monitor will show the flag in the event of the following: loss of electrical power to the indicator, loss of flag power from the CADC, excessive servo null voltage, loss of input synchro signal and internal indicator malfunction. A barometric pressure setting knob is provided to adjust the pressure setting which is displayed in both millibars and inches of mercury (Fig. 4).
B.  The captain's altimeter provides coarse and fine altitude synchro signals for the altitude alert system.
5C8 
34-12-01 Page 4  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/89 

K84719
553  Electric Altimeter 
May 20/82  Figure 4 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-12-01 Page 5 

5.  Standby Airspeed/Altimeter Indicator
A.  The standby airspeed/altimeter indicator is a combination of two flight instruments which presents an integrated display of indicated airspeed and altitude. The indicator is installed on the center instrument panel (Fig. 5).
B.  The standby pneumatic airspeed indicator gives indicated airspeed 60 to 450 knots. A diaphragm within the instrument case is actuated by differential pressure from the airplane pitot static system. The diaphragm expands or contracts in proportion to the difference between the pressure around it and the pressure in it. This information is transferred from the diaphragm to the drum counter through mechanical linkage. The pointer shows indicated airspeed on a drum graduated in knots.
C.  The standby altimeter is a drum-pointer type having a range of -1000 to 50,000 feet. The pointer, which indicates feet in hundreds, moves once around the dial for each 1000 feet of altitude. The drums display feet in thousands and hundreds. Indicators on the face of the altimeter show barometric pressure in inches of mercury and millibars. The barometric pressure is set by rotating the knob on the front of the instrument. An instrument vibrator is provided in the altimeter to shake the instrument to prevent errors caused by mechanical linkage friction. Power to the vibrator is supplied through a circuit breaker on panel P18.
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 導(dǎo)航 NAVIGATION 1(27)