YA613 - YC413, YK101 - YK104
.
standby altimeter/airspeed
indicator
YD651 - YD655
.
integrated standby flight display
.
standby radio magnetic indicator.
Copyright . The Boeing Company. See title page for details.
Flight Instruments, Displays -PFD/ND System Description 737 Flight Crew Operations Manual
Standby Magnetic Compass
A standard liquid–damped magnetic standby compass is provided. A card located near the compass provides heading correction factors.
Standby Attitude Indicator YA613 - YC413, YK101 - YK104
The standby attitude indicator provides attitude information that is independent of the primary attitude displays. The indicator is powered by the battery bus and remains powered after the loss of all normal AC power as long as battery power is available. The gyro reaches operational speed approximately 60 seconds after power is applied. The indicator requires three minutes to achieve accuracy requirements.
Integrated Standby Flight Display (ISFD) YD651 - YD655
The ISFD displays attitude, airspeed, altitude, ILS, and magnetic heading information. It is connected directly to the auxiliary pitot and alternate static sources. Attitude information is provided by internal inertial sensors. ILS information is provided by the No. 1 ILS receiver. The display receives its heading information from the same source as the captain’s primary flight display. Heading information is not available in polar regions.
Note: The standby magnetic compass must be used to validate heading information.
The battery bus powers the ISFD. Selecting the battery switch ON activates the ISFD. After 10 seconds, an initialization sequence begins that requires 90 seconds to complete. ATT and INIT 90s messages are displayed during initialization. Initialization will stop if airplane movement is excessive and will resume when airplane movement is acceptable for initialization. Upon completion of the initialization sequence, attitude information is displayed.
Detection of a momentary out-of-limit ISFD condition may cause the attitude display to blank and the WAIT ATT or ATT:RST message to display. Operation of the attitude reset switch is required in response to the ATT:RST message. This will reset the horizon line with the airplane symbol.
On the ground, operation of the attitude reset switch must be performed with the airplane stationary. In flight, operation of the attitude reset switch must be performed with the airplane in wings level, non-accelerated flight. During the process, the ATT 10s message displays. Failure to maintain straight and level flight for 10 seconds may result in an ATT:RST message. If the reset attempt is unsuccessful, the ATT:RST message remains displayed and the ISFD does not enter normal operation.
Copyright . The Boeing Company. See title page for details.
10.21.14 September 29, 2005
Flight Instruments, Displays -PFD/ND System Description 737 Flight Crew Operations Manual
Standby Altimeter/Airspeed Indicator YA613 - YC413, YK101 - YK104
Standby altitude and airspeed are displayed on a single indicator.
The standby altimeter receives static pressure from the alternate static ports. Current altitude is displayed digitally. A pointer indicates altitude in hundreds of feet. Barometric setting windows display the barometric setting in both millibars and inches of mercury as set by the barometric setting control. The altimeter has a range of -1000 to 50,000 feet.
The standby airspeed indicator receives ram air pressure from the auxiliary pitot probe and static pressure from the alternate static ports. It provides current airspeed in knots.
Standby Radio Magnetic Indicator
The standby radio magnetic indicator (RMI) displays magnetic heading and VOR/ADF bearing to the station. The RMI is powered by the AC standby bus and remains powered after the loss of all normal AC power as long as battery power is available.
Clocks YA613 - YA687, YA801 - YK104
Two electronic clocks are installed, with two digital displays on each clock. Universal time coordinated (UTC) time, UTC date, manual time or manual date may be set on the upper time display. The lower ET/CHR display is used for either elapsed time or the chronograph. Separate controls are provided for each display.
Each clock is powered by the hot battery bus when the battery bus is not available. The clock reverts to hot battery bus power when the airplane is powered down. The hot battery bus power keeps the time base but does not provide power for the display or output of clock data and the clock reverts to manual mode. When the airplane is powered up and Global Position System (GPS) data is restored, the clock continues to operate in manual mode and will not automatically display UTC time. UTC time can be manually selected by using the TIME/DATE pushbutton.
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