INPUT
NORMAL
1ACTIVITY SSM
SELECTLOGIC
TWO SSM VALID
GS í 60 KTS
FAIL
L SSM VALID
SQ1 F/D ON
SELECT L PARAMETER ACTIVITY CMD ENGA
SOFTWAREL X-CHANNEL VALID
HARDWARER SSM VALID
CWS ENGA
IRS, SURF
R PARAMETER R POS, RWY
LOCAL FAIL
ACTIVITY 1FOR THE FOLLOWING
HDG VOTE
FAIL
R X-CHANNEL VALID PARAMETERS:
ANY FAIL
GS . 40 KTS
LOGIC
LOGIC
LOCAL STAB. POS VALID PITCH ANGLE, PITCH RATE,
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 SEL ANGLE, MAG TRACK ANGLE
R X-CHANNEL VALID MATRIX (SSM)
VERT ACCEL, LATERALINPUT
APP SEL B 2
ACCEL, NORM ACCEL, CROSSSELECT
TK ACCEL, ALONG TK ACCEL,
PITCH
MODE
FLT PATH ACCEL. SEL RWYSQ
3 HDG; STAB. POS; FLAP
LOGIC G/S ACTIVE4 2
POS; AIL SURF POS, ELEVFAIL
SURF POS, RUD SURF POSRA . 1500'
ONE SSM VALID
5
SELECT ILS FREQ CHANGE 6
2 RADIO SIGNALS: G/S DEV,ARM/
R
LOC DEV, RADIO HEIGHTENGAGE
GO AROUND SEL 6
SELECTED3 LOC DEV
RA í 400'
DATA
LOGIC
4 G/S DEV SQ
A
5 RADIO HEIGHT
ROLL
RADIO 6 LOC DEV & G/S DEV
MODE LOC ACTIVE
SIGNALS
LOGIC
B R
7 FOR ATTITUDE RATE ANDLOGIC
VOTE ACCELERATION SIGNALSGND IS USED NOTSELECTED DATAFLIGHT CONTROL COMPUTER (EXAMPLE)
Autopilot/Flight Director System Signal Source Fault Detection (SSFD) Schematic
Figure 10 (Sheet 2)
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757 MAINTENANCE MANUAL
(b)
Discrete SSFD Process perform a majority vote of three discretes.
(c)
Force Select SSFD process selects one data source for use by all FCCs. All ADC data and ADC source IRU data (inertial altitude and inertial vertical speed) are force selected.
C. Autopilot/Flight Director System MCDP Monitor and Test (Fig. 11)
(1)
The MCDP provides a manual test of the ASAs. The ASA test verifies the proper operation of the front panel test and reset switches.
(2)
The FCC provides the following system interface tests:
(a)
ARINC 429 inputs from system units are checked in two ways. First, the FCC checks the sign status matrix to verify the validity of the incoming data. The buffer memory locations on the I/O data path assembly are also periodically checked to determine if the data words have been updated. If the words have not been updated, then a fault is assumed and the data words at the tested memory locations are not used.
(b)
Discrete input and output interfaces are monitored by software which detects shorted wires. These monitors are used for the caution/warning and autoland status annunciator inputs and outputs as well as the engage and arm solenoid power, trim outputs, engage and arm commands and inputs. The interface monitor circuits are tested, as appropriate, at power up or prior to engagement of autopilot/autoland.
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MAINTENANCE MANUAL
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本文链接地址：757 AMM 飞机维护手册 自动飞行 AUTOFLIGHT 2(17)
