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Time and date no longer display if APU battery bus power is removed. However,
all internal clock functions continue to operate and the correct time and date
display when power is restored. All display and internal clock functions fail if the
main hot battery bus power is removed. The clock must be reset when battery
power is restored.
Display System Information Sources
Pitot Static System
The pitot static system provides pitot pressure and static pressure to the air data
computers, standby airspeed indicator, standby altimeter, and elevator feel
computer.
October 1, 2000
747 Operations Manual
Flight Instruments, Displays -
System Description
Copyright © The Boeing Company. See title page for details.
D6-30151-425 10.20.7
Pitot Static Diagram
Air Data Computer (ADC) System
The ADC system supplies air data information to various airplane systems. Air
data information enables the EIUs to display altitude, airspeed, Mach, and air
temperature.
COMPUTERS
ELEVATOR FEEL
PITOT
CAPTAIN'S STATIC AND
FIRST OFFICER'S STATIC
AUXILIARY STATIC
ALTERNATE STATIC
LEFT AIR DATA
COMPUTER
RIGHT AIR DATA
COMPUTER
CAPTAIN'S STATIC
STANDBY
AIRSPEED
STANDBY
ALTIMETER
ALTERNATE STATIC SOURCE
LOWER UPPER
LOWER UPPER
AUX STATIC 1
AUX STATIC 2
FIRST OFFICER'S STATIC
AUX
PITOT 1
STATIC LEFT
2
PITOT
AUX
STATIC RIGHT
October 1, 2000
747 Operations Manual
Copyright © The Boeing Company. See title page for details.
10.20.8 D6-30151-425
Flight Instruments, Displays -
System Description
There are two ADCs, left and right. Each ADC receives inputs from AOA sensors,
TAT probes, pitot static system, and barometric settings from the EFIS control
panels sent through the related CDUs . Either ADC can provide flight information
to the Captain’s and F/O’s flight instruments, depending on the position of the Air
Data Source selectors. Normally, each ADC provides flight information to the
PFD and ND on its related side.
Angle–of–Attack (AOA)
There are two angle–of–attack vanes, one located on each side of the forward
fuselage. The vanes measure airplane angle–of–attack relative to the air mass.
Total Air Temperature (TAT)
Left and right dual total air temperature probes sense outside air temperature
(OAT) and heat of compression. TAT displays on primary EICAS. TAT indication
on the ground approximates OAT.
Static Air Temperature (SAT)
Left and right dual static probes sense static air temperature. SAT displays on
Progress page 2.
December 01, 1999
747 Operations Manual
Flight Instruments, Displays Chapter 10
Primary Flight Displays (PFDs) Section 30
Copyright © The Boeing Company. See title page for details.
D6-30151-425 10.30.1
Introduction
PFDs present a dynamic color display of parameters necessary for flight path
control. PFDs provide the following information:
Failure flags display for airplane system failures. Displayed information is
removed or replaced by dashes if no valid information is available to the display
system (because of out–of–range or malfunctioning navigation aids). Displays are
removed when a source fails or when no system source information is available.
Flight mode annunciations are described in Chapter 4, Automatic Flight.
TCAS resolution advisories are described in Chapter 15, Warning Systems.
PFD time critical warnings display in large capital letters between the attitude
display and the compass rose. Refer to Chapter 15, Warning Systems.
Typical PFD Displays
Typical PFD configurations for six phases of flight follow. The autopilot, LNAV,
and VNAV are active for climb, cruise, descent, approach, and landing. The AFDS
approach mode is used for approach and landing.
• flight mode annunciation
• airspeed
• altitude
• vertical speed
• attitude
• steering information
• radio altitude
• instrument landing
system display
• approach minimums
• heading/track indications
• time critical warnings
December 01, 1999
747 Operations Manual
Copyright © The Boeing Company. See title page for details.
10.30.2 D6-30151-425
Flight Instruments, Displays -
Primary Flight Displays (PFDs)
PFD Takeoff Display
140
10 10
10 10
20
80
100
130 MAG
V1
LNAV VNAV
TO/GA
29.83 IN.
VR
HOLD TO/GA
　
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