NOTE: Probe Recovery Factor is 100%.
Static Air Temperature
Static air temperature, displayed on the CDU PROGRESS page, is derived from the TAT by ADC No. 1.
Angle–of–Attack
There are two angle–of–attack sensors, one located on each side of the forward fuselage. The vanes measure airplane angle–of–attack relative to the air mass.
Copyright . The Boeing Company. See title page for details.
December 1, 2000 10.20.5
Flight Instruments, Displays -System Description 737 Operations Manual
Primary Flight Instruments Mach/Airspeed Indicators
Two electric Mach/airspeed indicators display indicated airspeed, Mach, and Vmo
derived from the respective air data computer. The airspeed cursor on each pilot’s indicator can be automatically positioned through the related flight control computer (FCC) using inputs from the flight management computer (FMC) or from the speed selector on the AFDS mode control panel. Each airspeed cursor can also be manually positioned.
Altimeters
Two electric altimeters indicate current altitude in feet, derived from the
respective air data computer. The altimeters have a range of –1,000 to 50,000 feet. On some airplanes, a single pneumatic metric altimeter is installed on the captain’s instrument panel. It utilizes the alternate static source.
Vertical Speed Indicators
Two inertial vertical speed indicators display instantaneous vertical speed derived from the respective inertial reference system.
Clocks
Two electronic clocks are installed, with two digital displays on each clock. Either coordinated universal time (UTC) or local time 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.
Standby Flight Instruments Standby Horizon Indicator
The standby horizon 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.
Standby Altimeter/Airspeed Indicator
Standby altitude and airspeed are displayed on a single indicator.
The standby altimeter indicates current altitude in feet. It receives static pressure
from the alternate static ports. The altimeter has a range of –1,000 to 50,000 feet.
Copyright . The Boeing Company. See title page for details.
10.20.6 December 1, 2000
Flight Instruments, Displays -System Description
737 Operations Manual
The standby airspeed indicator provides current airspeed in knots. It receives ram pressure from the No. 2 auxiliary pitot probe and static pressure from the alternate static ports.
Standby Magnetic Compass
A standard liquid–damped magnetic standby compass is provided. A card located near the compass provides heading correction factors.
Flight Recorder
The flight recorder provides a permanent record on tape of selected operational and systems information such as altitude, heading, acceleration, and airspeed. The recorder is housed in a sealed, fire–resistant container located behind an access door in the aft cabin ceiling.
Operational and systems information is automatically recorded whenever the flight recorder is powered. On the ground, the recorder begins operating as the low oil pressure switch closes during either engine start. Oil pressure switches are bypassed in the air, and the flight recorder is powered even with both engines shut down as long as electrical power is available.
Aircraft Condition Monitoring System (ACMS) (As installed)
The ACMS consists of a digital flight data recorder (DFDR), accelerometer, airborne printer, control display unit (CDU), and digital flight data acquisition unit (DFDAU).
The DFDAU receives signals representing certain flight conditions and airplane systems’ operating performance and converts them to a digital form for recording on the DFDR.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300机组操作手册Flight Crew Operations Manual FCOM 3(2)
