M7359 PSM 2LFCE 2R AC
P7 OVERHEAD CIRCUIT E1-2 ELECTRONICS SHELF BREAKER PANEL
NOTE: NO. 1 AND 2 LEFT POWER SUPPLIES SHOWN. NO. 1 AND 2 RIGHT POWER SUPPLIES SIMILAR.
FCE Power Supplies Schematic
Figure 2
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3. Stabilizer Trim/Rudder Ratio Module
___________________________________
A. The two stabilizer trim/rudder ratio modules provide control, and fault detection and indication for the stabilizer trim, rudder ratio changer, and aileron lockout systems. The SRMs receive inputs from the flight control computers, air data computers, flight deck controls, flap control unit, and other sources. These inputs are used to generate output signals to the stabilizer trim control modules, rudder ratio changer actuator, aileron lockout actuator, EFIS/EICAS Interface Units, and other airplane systems.
B. Each SRM contains BITE for fault detection and isolation. Faults with an SRM or associated LRU are transmitted to EICAS where a fault message will be displayed. Specific fault information will be stored in the CMC for retrieval during later maintenance. A ground functional test of the aileron lockout and rudder ratio changer systems can be performed with the Central Maintenance Computer.
4. Yaw Damper Module
_________________
A. The two Yaw Damper Modules provide automatic control and fault detection for Dutch Roll damping and structural body mode suppression. The YDMs receive inputs from the inertial reference units, the air data computers, the system accelerometers, the rudder power control modules, the air/ground relay, the hydraulic systems, the Central Maintenance Computer, and other sources. These inputs are processed by the YDM to generate output signals to the yaw damper portion of the rudder power control modules.
B. Each YDM contains BITE for fault detection and isolation purposes. Faults with the YDM or associated LRU's can cause a caution or status message to be displayed on EICAS. Specific fault information will be stored in the Central Maintenance Computer for retrieval during later maintenance. A test of the Yaw Damper system can be initiated with the Central Maintenance Computer.
5. Power Supply Module
___________________
A. The 4 power supply modules provide the power required for operation of the FCE system. Each module supplies multiple regulated +5, +15, and -15 volts dc and unregulated 26 volts ac power sources to the FCE modules and and their sensors.
6. Operation__________________________
(Figs. 2 and 3)
A. Functional Description
(1)
The power supply modules provide regulated +5, +15, and -15 volts dc and unregulated 26 volts ac to the FCE modules and their sensors. Details of the operation of the individual modules are given in the references listed in the general information section above.
B.
Control
(1)
Operation of the Power Supply Modules is automatic. No control functions are exercised. Control of the FCE modules is detailed in the references listed in the general information section above.
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FCE Air/Ground, Hydraulics, and ADC Inputs Block Diagram
Figure 3
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FLIGHT CONTROLS ELECTRONICS (FCE) - MAINTENANCE PRACTICES
_________________________________________________________
1. General_______
A. This procedure contains two tasks. The tasks are the removal and the installation of the power supply module (PSM) for the flight controls electronics.
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