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757 MAINTENANCE MANUAL
 (3)  S 864-035Momentarily set the ON-NORM-TEST switch on the FDEP to the TEST position.
 (4)  S 704-037Make sure the SYSTEM indicator goes off.
 (5)  S 864-038Remove electrical power if it is not necessary (AMM 24-22-00/201).

 
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757 MAINTENANCE MANUAL
 AIRPLANE CONDITION MONITORING SYSTEM - DESCRIPTION AND OPERATION
________________________________________________________________
 1.  General (Fig. 1)_______
 A.  The airplane condition monitoring system (ACMS) collects and records operational data to permit detailed analysis of airplane performance and maintenance requirements. This data is acquired by the acquisition unit. The data is recorded on magnetic tape in a quick access recorder.
 B.  The ACMS consists of a digital flight data acquisition management unit (DFDAMU), the FMC CDU, and a quick access recorder (QAR).
 C.  The DFDAMU is shared with the digital flight data recorder system. It is located on E3-3 of the main equipment center. The DFDAMU receives and processes selected airplane parameters for recording. The DFDAMU is a dual-microprocessor controlled unit. One microprocessor provides the processed parameter signals to be recorded by the digital flight data recorder (Ref 31-31-00). The second microprocessor provides processed parameter signals to be recorded by the QAR.
 D.  The QAR is located on E3-3 of the main equipment center. It records the parameter data on magnetic tape. The tape cartridge has a capacity of 14 hours of data storage. The tape cartridge is replaceable. The QAR is able to search for and replay data from a specified GMT reference, and return to the current recording position.
 2.  Component Details (Fig. 1)_________________
 A.  Digital Flight Data Acquisition Management Unit (DFDAMU)
 (1)  
The DFDAMU is located on the E3-3 shelf of the main equipment center. The DFDAMU has two sub-circuitry assemblies, the digital data acquisition unit assembly and the data management unit (DMU) assembly. The DMU is a microprocessor controlled unit that sequentially receives all selected airplane systems, sensor and flight data. The acquired data is scaled and reformatted into digital format. The DMU outputs this data to the QAR and the CDU.

 (2)  
The DMU sub-circuit assembly is also programmable to meet individual airline requirements in collecting and displaying airplane data. This can be accomplished by using the carry-on data loader which is carried to the cockpit and connected to the P61 panel.

 (3)  
The DMU FAIL indicator is located on the front panel of the DFDAMU. The DMU FAIL indicator comes on to indicate that the component has failed. The ATE connector is provided to connect external test equipment.
　
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