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 the FMA fault bit in the appropriate mode's data word is set high. The data word is sent to the EFIS/EICAS Interfacing Unit (EIU) which draws a yellow line through the PFD failed mode annunciation. If the FCC(s) set the sign status matrix (SSM) bits in the pitch and/or roll data word to NCD, the EIU will bias the F/D command bars from view. When a FCC is in the F/D mode, NCD in the SSM of the data word causes the EIUs to bias the F/D command bars from view.
 (3)  Autopilot Warning Annunciation
 (a)  
Disengagement of the only engaged FCC causes the following: 1) The red master WARNING light illuminates 2) The main EICAS display shows an AUTOPILOT DISC message in

 red.
 3) A two-tone siren sounds

 (b)  
Two WARN outputs are generated for each of these warning functions. One WARN output uses software logic and is inhibited by a loss of normal power or a computer failure. The second WARN output uses hardware logic that is powered by 28 vac standby power. This ensures a valid warning if normal power is lost.

 (c)  
Signal Generation

 1)  Latches are set when the FCC is engaged in CMD or the servos are armed. If the FCC subsequently disengages, an A/P WARN 1 and A/P WARN 2 signal is issued if no other FCC is engaged. All outputs are generated anytime either autopilot disengage switch is operated.

 (d)  
Reset

 1)  When the autopilot is disengaged with the A/P disengage switch, pressing the switch again resets the disengage warnings. Reset of an autopilot disengage warning due to any other means of disconnect is achieved by pressing the control wheel disengage switch once.
 D.  Autopilot/Flight Director System Signal Source Fault Detection (SSFD) (Fig. 9)
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 22-14-00
 ALL  ú ú 02 Page 15 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

ENABLE2EQUALIZATION
MID PITCH &
ROLLLOCAL DATALOCAL DATA VALUESELECTED DATA
INPUT
SELECTORMODE7
MONITOR
LOGIC ENABLE
A LOCAL FAILENABLE
FAULT
DETECTION
LOCAL COMPUTATION (SSFD)
L DATACROSS
SAME AS LOCAL L DATA
LOCAL FAIL
CHANNEL

FAIL
MONITOR

L COMPUTATION (SSFD)L FAIL
ANY FAIL SELECTED
LOGIC
PARAMETERFAILARM/
R DATA TWO FAIL
SAME AS LOCAL R DATA
ENGAGE
INPUTLOGIC
SELECT
R COMPUTATION (SSFD) R FAIL
FAILLOCAL SIGN STATUSSELECT
MATRIX VALID
LOCAL PARAMETER

INPUT
NORMAL
1ACTIVITYSSM
SELECT LOGIC
TWO SSM VALID
GS í 60 KTS
FAIL
L SSM VALID
SQ 1 F/D ON
SELECT L PARAMETER ACTIVITYCMD ENGA
SOFTWAREL X-CHANNEL VALID
HARDWARER SSM VALID
IRS, SURF
R PARAMETERR POS, RWY
LOCAL FAIL
ACTIVITY 1FOR THE FOLLOWING
HDG VOTE
FAIL
R X-CHANNEL VALID
PARAMETERS:LOCAL STAB. POS VALIDANY FAIL
GS . 40 KTS
LOGIC PITCH ANGLE, PITCH RATE,
LOGIC TWO FAIL
L STAB. POS VALID
ROLL ANGLE, ROLL RATE,L X-CHANNEL VALID
ONE SSM VALID
MAG HDG, YAW RATE, TRUER STAB. POS VALID
HDG, GND SPD, TRUE TRACK
SIGN STATUS LOC SELANGLE, MAG TRACK ANGLE,
R X-CHANNEL VALID MATRIX (SSM) VERT ACCEL, LATERAL
APP SELB  2 ACCEL, NORM ACCEL, CROSSTK ACCEL, ALONG TK ACCEL,
INPUT
SELECTFLT PATH ACCEL, SEL RWY
PITCH
3SQ
MODEHDG, STAB. POS, FLAPLOGIC G/S ACTIVE 4
2
POS, AIL SURF POS, ELEVFAIL
SURF POS, RUD SURF POSRA . 1500'
ONE SSM VALID
5
SELECT ILS FREQ CHANGE 6 2RADIO SIGNALS: G/S DEV,
R
LOC DEV, RADIO HEIGHT
GO AROUND SEL
ARM/
6
RA í 400'

SELECTED
ENGAGE
3 LOC DEV
LOGIC

DATA
A

4G/S DEVSQ
5RADIO HEIGHTROLLRADIO
6LOC DEV & G/S DEVMODE LOC ACTIVE
SIGNALS
LOGIC

B
R
7 FOR ATTITUDE RATE AND
VOTEACCELERATION SIGNALS,
GND IS USED, NOT
SELECTED DATAFLIGHT CONTROL COMPUTER LOGIC
AFDS Signal Source Fault Detection (SSFD) Schematic
Figure 9

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