27-09-00
ALL ú ú 04 Page 20 ú Jun 20/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
(f) Alternate manual trim mode:
1) AIRPLANES WITH THE MANUAL STAB TRIM LEVERS ON THE CONTROL STAND: The alternate manual trim mode is controlled by inputs to the manual stab trim levers on the center control stand. When you push these levers, you send commands through a mechanical linkage that moves cables.
2) AIRPLANES WITH THE ALTERNATE STAB TRIM SWITCHES ON THE CONTROL STAND; The alternate manual trim mode is controlled by inputs to the alternate stab trim switches on the center control stand.
3) These input commands bypass the SAM and send its trim command directly to the stabilizer trim control module (STCM). Refer to 27-41-05/201 for more information on the STCM.
(5)
CSEU fault annunciation (Fig. 7).
(a)
Fault monitor circuits monitor electrical networks and supply fault annunciation and warning of failures in each CSEU module. The fault annunciations are the applicable amber lights on pilots' overhead panels, P5.
(b)
The Engine Indication and Crew Alerting System (EICAS) display on pilots' center instrument panel supplies the EICAS messages via the EICAS computers. The applicable module faultballs on the face of the module or the applicable fault indications in the module memory also latch. 1) A minor maintenance failure, such as a PSM FAIL discrete,
or a first failure of any monitored function in either CSEU, supplies a CSEU failure signal to the EICAS display through the EICAS computers.
2) Maintenance messages appear on the display when the ECS/MSG button on the EICAS maintenance panel (located on side panel P61 in flight deck) is selected.
3) A more serious failure, such as the double failure of a redundant module (SAM or RRC), or the failure of an output device that makes crew awareness and possible corrective action necessary, makes the appropriate amber light come on, on the P5 panel.
B. CSEU BITE (Fig. 7)
(1) Each CSEU module faceplate contains faultballs or fault lights (or a BITE display) as part of the continuous BITE monitor function to identify the faults down to the LRU level, which includes the intermittent faults, within its system.
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27-09-00
ALL ú ú 07 Page 21 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
34MODULEMODULE FAULT
FAULT
FAULT-
DISPLAY
FAULT-
FAULT
BALLDRIVER
BALL
LOGIC A
DRIVER
DRIVER
NO. 1FAULT LOGIC
VOLTAGE
(SOFTWARE)
REGULATOR
B
FAULT
+28V DC
OTHER PSM
MISSING
MAINT
FAIL
PSMFAULT 1 NO. 2
FAULT
CSEU PWR SUPPLY 1L
LOGICMONITOR +28V DC
+28V DC
MAINT MAINT
FAULT 2 FAULT
SPOILER CONT 3L
SAME AS
CSEU PWR
SUPPLY 1L
INTERNALS
SAME AS
INTERNALS
CSEU PWR SUPPLY 2L
LEFT RUDDER
RATIO
CHANGER
RIGHT RUDDER RATIO
INTERNALS
CHANGER
SAME AS
CSEU PWR
SUPPLY 1L
INTERNALS SAME AS
LEFT STABILIZER
TRIM/ELEVATOR
CSEU PWR SUPPLY 1R
ASYMMETRYLIMIT MODULE
INTERNALSRIGHT STABILIZER TRIM/SAME ASELEVATOR ASYMMETRYCSEU PWRLIMIT MODULESUPPLY 1L
SAM
MODULEFAULT CSEU PWR SUPPLY 2R FAULT-
SAM FAULT-BALL
BALL LATCHDRIVER AND DRIVER
1 AIRPLANES WITHOUT
-122 AND SUBSEQUENT
YAW DAMPER MODULES GROUND TEST
& SELECT
SAM2 AIRPLANES WITH
NO. 1NO. 1-122 AND SUBSEQUENT FAULT
TIMING LOGIC
NO. 2 NO. 2 YAW DAMPER MODULES
OTHER3
SAM VALID
-100 SERIES SPOILERENGAGE LOGIC FAULTS DETECTED
AIRPLANES WITHLATCHING &MAINT MAINT
CONTROL MODULESBY SAM
FAULT
FAULT 4
AIRPLANES WITH-200 SERIES SPOILER LEFT RUDDER RATIO CHANGER LEFT STABILIZER TRIM/ELEVATORCONTROL MODULES ASYMMETRY LIMIT MODULE
CSEU Fault Annunciation Schematic
Figure 7 (Sheet 1)
2 LINESX 8 CHARS
ONOFF
MENU
YES NO
NO. 1NO. 2
INTERNALS
SAME AS
SPOILER
CONT 3L
SPOILER CONT 3R
INTERNALS
SAME AS
SPOILER
CONT 3L
SPOLER CONT 2L
1
IRU DADC YDACT
HYDLVDT AIR/GND
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