(b)
11C7, CSEU 1L DC or FLT CONT ELEC 1L DC
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757 MAINTENANCE MANUAL
(c) (d) (e) (f) (g) (h) 11C8, CSEU 2L AC or FLT CONT ELEC 2L AC11C9, CSEU 2L DC or FLT CONT ELEC 2L DC11G17, CSEU 1R AC or FLT CONT ELEC 1R AC11G18, CSEU 1R DC or FLT CONT ELEC 1R DC11G27, CSEU 2R AC or FLT CONT ELEC 2R AC11G28, CSEU 2R DC or FLT CONT ELEC 2R DC
(2) S 216-080Make sure the amber SPOILERS light on the P5 panel is off.
(3) S 866-081Push the RESET switch on all four PSMs. Stop for 31 seconds.
NOTE:____ If it is necessary, temporarily open these circuit breakers to set the PSM Faultball:
11J2, EICAS CMPTR L 11J29, EICAS CMPTR R
(4) S 216-082Make sure the PSM faultballs are black.
(5) S 866-116Remove the power from the left, right, and center hydraulic systems (Ref 29-11-00/201).
(6) S 866-102Do the activation procedure for the thrust reverser (Ref 78-31-00/201).
(7) S 866-103Remove the electrical power if it is not necessary (Ref 24-22-00/201).
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MAINTENANCE MANUAL
FLIGHT CONTROL SYSTEM ELECTRONICS UNIT (CSEU) - DESCRIPTION AND OPERATION
_________________________________________________________________________
1. General (Fig. 1)
_______
A. The Control System Electronics Unit (CSEU) is a collection of flight control modules and four power supply modules. The CSEU is energized by its own power supply modules.
B. The CSEU interfaces with other primary airplane systems to provide the computation and control functions for yaw damping (Ref 22-21-00), stabilizer trim (Ref 27-41-00), elevator travel limit (Ref 27-31-00), rudder control authority (Ref 27-21-00), and spoiler deployment (Ref 27-61-00).
C. The system consists of independent left and right CSEUs. All modules are line replaceable units (LRU). Equivalent modules can be changed between equivalent shelf positions on the left and right CSEUs.
D. The left CSEU is on the top E3-1 shelf, and the right CSEU is on the top E4-1 shelf. These shelves are found in the main electronics equipment center. Access is thru the electronics access door, 119BL, found on the bottom of the fuselage, aft of the nose wheel well.
E. The CSEU consists of these modules (and equipment numbers):
(1)
Yaw damper module (YDM) (M522 LH; M523 RH)
(2)
Rudder ratio changer module (RRC) (M528 LH; M529 RH)
(3)
Stabilizer trim/elevator asymmetry limit module (SAM) (M524 LH; M525 RH)
(4)
Spoiler control module (SCM)
(M530, M531, M532 LH; M533, M534, M535 RH)
(5)
Power supply module (PSM) (M536, M537 LH; M538, M539 RH)
F.
The CSEU modules provide the electrical interface between the sensors and the signal sources. These include the air/ground logic sensors, the hydraulic pressure sense signals, the pilot's and first officer's flight control transducers, and the control surfaces transducers and actuators.
G.
Built-In-Test Equipment (BITE) in the CSEU modules supply continuous monitor features specified for the monitor circuits. When the CSEU is powered, the background is continuously monitored for faults, and the inflight failure data is stored.
2. Component Details (Fig. 2)
_________________
A. Yaw Damper Module (YDM)
(1)
The YDM gets the sensor inputs from these systems:
(a)
Air Data Computer
(b)
Inertial Reference Unit
(c)
AIRPLANES WITH THE -122 AND SUBSEQUENT YAW DAMPER MODULES; Modal Suppression Accelerometer
(2)
The YDM uses these inputs to dampen undesirable sideslip and roll and to provide turn coordination and gust load relief. If one of the YDMs fails, the other YDM takes over all control functions. The two YDMs supply rudder commands which drive the yaw damper servos. These servos control the rudder mechanical linkage and the rudder power control actuators. Refer to 22-21-00 for more information.
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