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 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, move, 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.
 D.  The standby airspeed/altimeter indicator provides barometric corrected
 potentiometer signals to the cabin pressurization system (AMM 21-31-00).Total Air Temperature/Static Air Temperature/True Airspeed Indicator
____________________________________________________________________
 A.  The total air temperature/static air temperature/true airspeed (TAT/SAT/TAS) indicator is a digital type display of these flight parameters. The indicator is mounted on the first officers panel and presents the information as a liquid crystal display (LCD) (Ref Fig. 1).
 B.  The TAT, SAT, and TAS displays are selected individually one at a time by pressing the pushbutton on the front of the indicator and the displays appear in the order listed. The range of each display is as follows:
 TAT -99°C to +50°C
 SAT -99°C to +60°C
 TAS 130 to 599 KNOTS
 The digital data for the indicator is supplied from digital air data computer No. 1 on digital data bus No. 2 (Ref Fig. 4 and 5).
Total Air Temperature Probe (Fig. 1 and 4)
___________________________
 A.  The outside air temperature probe contains non-inductive resistive transducer sensing elements and an anti-icing heater. Temperature variations of the slipstream airflow through the probe and sensor causes the element resistance to vary, providing air temperature data to the digital air data computers. In flight, heating of the probe assembly is controlled by a switch on the pilots' overhead panel (Ref 30-31-00).
Digital Air Data Computer (Fig. 1, 4 and 5)
_________________________
 A.  The digital air data computer (DADC) is a solid-state device that uses pitot static pressure and air temperature inputs to compute air data information required by airplane displays and systems. In addition to the above inputs, 115-volt ac and 26-volt ac are provided to multipin connectors at the rear of the computer.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A21ALT
A22
A23

COARSE 1
1 (SH 3)
A24ALT
A25
A26

FINE 1
2 (SH 3)
A4ALT
A5
A6

COARSE 2(FIG 6)
A71ALT
A72
A73

FINE 2(FIG 6)
B31ALT
B32
B33

COARSE 3(FIG 6)
B34ALT
B35
B36

FINE 3
(FIG 6)
A44
A45A/S 13
A46
A74

A75A/S 2
A76(FIG 6)
B23
B24A/S 3
B25(FIG 6)

A14
A15MACH 1
A16(FIG 6)

B66
B67MACH 2
B68(FIG 6)

B28
B29TAS NC
B30
A7

ALT RATE 1 NC
A8
A60

ALT RATE 2
A61(FIG 6)
A12ALT RATE 3 (SH 3)
A13
B37

ALT RATE 4 NC
B38
A10ALT POT OUT
A67TAS POT OUT
A70SAT POT OUT

NC
B21MACH POT 1
B15MACH POT 2
B46CAS POT

+A65A64 1/Q -A63GAIN (22-12-00)A1
BUS 1A2(FIG 5)
B76
BUS 2 (SH 3)
B75(FIG 5)
A56BUS 3A57(FIG 5)
B17BUS 4B18
(FIG 5)
B39ALT VALID 1

NC
B40ALT VALID 2
B41ALT VALID 3

5 B42ALT VALID 4 (FIG 6)B43MACH VALID 1B44MACH VALID 2NC B56TAS/SAT VALIDB57A/S VALID 1
4
B58 A/S VALID 2
(FIG 6)

115V ACPOWER INTERUPT
POWER SUPPLY
POWER
AIR DATA

A59RESET
BRIDGEMODULE
SUPPLY
CMPTR 1

RECTIFIERMONITOR
A49
WARM/COLD START
AUTO XFMR

T98
DC
26V AC

(J4) 26V AC SYNCHRO SYNCHRO DC REF
A38
POWER
A

V REF ACE
A47
AND REF
CAPT ALTM

A53
C

A27
B
INPUT PROCESSORCAPT MACH/STATIC24 MHz
Ps
AS INDPRESSUREOSCILLATOR
XDCR
TIMING
CMPTR 1
　
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