FOREIGN ARM
FOREIGN ENGA
CROSSMONITORSWHEEL DISCONNECT
TO REL L FCCCMD REQUESTCHANNEL
&
SQ
ELEV/AIL MONITORS TO REL R FCC
ENGA INITIATION
FOREIGN IN CMDENGA
MULTI ENGALOCALIZER CAPTINIT LOCAL CAMOUT
G/S CAPTELEV/AILFOREIGNPITCH/ROLL
RAD ALT<1500 FT ENGA RELAY
FOREIGN
SIGNAL(SH 3) ENGA
MULTI-ARM INITYAW MODE
CAMOUT
I/OB ENGA REMOVAL FAULTG/A
AUTOTRIM VALID 1
D
LOGIC &
MAN. DISCR
MODE RUD FOREIGN IN CMDAUTOTRIM VALID 2
PROCESS/(SH 3)
ENGA REMOVAL CONDMON
(SH 3)J
ENGA & EQUAL-
MONITORS FLARE ENGA(SH 3)K IZATION
IN AIRAIL SVO
AIL
SOFTWARE
DETENT
TO OTHERELEV SVO
ELEV
AIL SURFLOGICHARDWARE LOCAL
RUD
FCC'S
LVDT
G/A MODEELEV SURFDETENT
MONITOR RUD SURF
TRANS G/A TO CRUISERUD SVO28V DC ILS
TO ILS RCVRLVDT
LOCAL FIRST IN CMDTUNE INH
AND CONTROLMON
2 IN CMD3 IN CMD LOCALIZER ENGAGEDPANELGLIDESCOPE ENGAGED RA
TO RADIOTWO SAME AUTOLAND FAILURETWO SAME INNER LOOP FAILURETEST INH ALTIMETERL DETENTRMTR/RCVR
R DETENT
SOURCERAD ALT<200 FT (ALERT HEIGHT)
SELECTA/L
BUS ISOLFAULT
SQ BUS ISO
RELAY DETECTMONR
G/A MODE
LAND 3MAN. DISCR ELEV/AIL & RUD SVO ENGA
LAND 3
L ELEV/AIL & RUD SVO ENGA
ROLL
LOCAL AIL/ELEV & RUD SVO ENGA
MODE
LAND 2TO CAPT &
LOGICLAND 2 F/O ASA'S
NOLAND 3
ASA RESET
ANY CHANNEL FAIL
PITCH
MODEFULL TIME NO LAND3 NO A/LLOGIC ANY TWO CHANNELS FAIL
APPROACH RESET ONE SHOT
AUTO. RESET NOTES:
FLIGHT CONTROL COMPUTER
1 INHIBIT LOGIC LOW2 NECESSARY FOR3TRUE IF FULL4ALL OUTPUT SIGNALSDURING POWER UP ONLY APPROACH METHOD II TIME NO LAND OPTION ARE WRAPPED AROUND
ELEV/AIL SERVOS
Autopilot/Flight Director System Arm and Engage Logic Schematic
Figure 8 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. GUN 051 ú
22-11-00
ú ú 07 Page 25 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
D01619
A
757
MAINTENANCE MANUAL
D01621
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-11-00
ALL ú ú 08 Page 26 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
(f)
GUN 001-050, 052-999; after the arm solenoids are energized, an engage request acceptance signal is sent to the MCP. This signal causes the MCP to illuminate the appropriate CWS or CMD switch/light. The appropriate engage solenoids are also energized.
(g)
The appropriate engage solenoids are then energized if the FCC is not inhibited. The FCC remains in the ARM state if: 1) rudder solenoid is energized 2) aileron or elevator servos fail or servo loops not verified 3) FCC program pin status not valid
(h)
Once engaged, the A/P channel transitions from CMD to OFF if: 1) FCC memory failed or self test monitors are not verified 2) rudder solenoid is energized 3) aileron or elevator servo or servo loop failed 4) any two identical inner loop sensors failed or invalid 5) electrical power monitor detects a failure 6) aileron exceedance detector monitor detects a failure 7) ALT HLD or override function cannot be performed 8) autopilot disengage switch pressed 9) Manual electric stabilizer trim requested by pitot.
(i)
An engage request accepted signal is sent to the EFIS symbol generators for mode annunciation on the EADI. The cross-channel data buses allow each FCC to provide its engage status to the other two.
(7) Multichannel Autopilot Engage
(a)
GUN 051; multichannel CMD engage requests are initiated when the approach mode is selected and two or three MCP engage switches are placed in the CMD position. MCP software activity and engage request transmission is the same as single channel engagement. Each engage request is sent to its appropriate FCC. FCC software and hardware monitors determine if the engage requests can be implimented.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 自動飛行 AUTOFLIGHT 1(102)
