**ON A/C 151-158, 201-209,
(Ref. Fig. 001C)
**ON A/C 159-199, 210-210,
(Ref. Fig. 001D)
**ON A/C 151-199, 201-210,
Installation Zones and Location Numbers
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
-------------------------------------------------------------------------------1TU DFDR 312 312AR 31-33-55 2TU FDIU 87VU 127 824 31-33-34 6TU ACCELEROMETER-THREE AXIS 145 241JF 31-33-16
**ON A/C ALL
3. System Description__________________
**ON A/C 001-049, 051-099, 101-105,
(Ref. Fig. 002)
The FDIU is connected to different aircraft systems. DATA (parameters) are received in discrete and digital form. The FDIU collects these parameters and converts them for internal processing. A standardized set of flight critical parameters are transmitted in serialized digital form to the DFDR. These parameters are stored on the recorder in data frame cycles. The QAR stores the same data as the DFDR. The FDIU generates aircraft data and sends them to the ARINC 429 output bus. A separate linear accelerometer is installed to provide the FDIU with acceleration data appearing in the center of gravity. The SDAC digitizes the analog signal of the LA and sends it to the FDIU via ARINC 429 bus. The EVENT Button and the Override Button of power interlock are located on the CTL PNL's.
1EFF : ALL 1 31-33-00Page 3 1 1 Aug 01/05R 1 1 1CES 1
Component Location Figure 001 (SHEET 1)
R 1EFF : 1 1 1CES 001-049, 101-105, 1 111 31-33-00 Page 4 May 01/05
Component Location Figure 001 (SHEET 2)
R 1EFF : 1 1 1CES 001-049, 101-105, 1 111 31-33-00 Page 5 May 01/05
R Component Location
R Figure 001A (SHEET 1)
R 1EFF : 051-099, 1 31-33-00 Page 6
1 1 May 01/05
1 1
1CES 1
R Component Location
R Figure 001A (SHEET 2)
R 1EFF : 051-099, 1 31-33-00 Page 7
1 1 May 01/05
1 1
1CES 1
Component Location
Figure 001B (SHEET 1)
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-33-00Page 8 1 1 Aug 01/05 1 1 1CES 1
Component Location
Figure 001B (SHEET 2)
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-33-00Page 9 1 1 Aug 01/05 1 1 1CES 1
R Component Location Figure 001C (SHEET 1)
R 1EFF : 1 1 1CES 151-158, 201-209, 1 111 31-33-00 Page 10 May 01/05
R Component Location Figure 001C (SHEET 2)
R 1EFF : 1 1 1CES 151-158, 201-209, 1 111 31-33-00 Page 11 May 01/05
R Component Location Figure 001D (SHEET 1)
R 1EFF : 1 1 1CES 159-199, 210-210, 1 111 31-33-00 Page 12 May 01/05
R Component Location Figure 001D (SHEET 2)
R 1EFF : 1 1 1CES 159-199, 210-210, 1 111 31-33-00 Page 13 May 01/05
System Block Diagram Figure 002
R 1EFF : 1 1 1CES 001-049, 051-099, 101-105, 1 111 31-33-00 Page 14 Aug 01/05
A. Not Applicable
B. Not Applicable
C. System Architecture
(Ref. Fig. 002, 003, 004)
The basic DFDRS Components are:
-
A Flight Data Interface Unit (FDIU)
-
A Digital Flight Data Recorder (DFDR)
-
A Quick Access Recorder (QAR)
-
A Linear Accelerometer (LA)
-
A Control Panel (CTL PNL)
R - An Event Marker Button (EVENT). The minimum equipment of a basic DFDRS (FDIU, DFDR, LA, CTL PNL and EVENT) must be installed on each aircraft. This is to meet the requirement of the authorities for recording of mandatory parameters.
R **ON A/C 106-149, 211-299, 301-399, 401-499,
(Ref. Fig. 002A) The FDIMS is controlled by the FDIMU. The FDIMU puts together the functions of DFDRS and the AIDS into a single Line-Replaceable-Unit (LRU). These two functions are controlled inside the FDIMU by two separate processor-units (FDIU-part, DMU-part), which operate independently from each other. An internal data-bus does the data-transmission from the FDIU-part to the DMU-part.
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