A320飞机维护手册 AMM 指示/记录系统 3(68)_航空信息_民用航空_通用航空

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26.1.126.01 or 26.2.126.10 Bits 14 to 11). The determination of a new flight phase is independent from the previously encountered flight phase.
+-------------------------------------------+ | Flight |FDIMU Internal Flight Phase Coding | | Phase | Bit: | | Number | 17 | 16 | 15 | 14 | 13 | 12 | 11 | ---------------------------------------------| | 1.0 | 0 | 0 | 0 | 1 | 0 | 1 | 0 | | 1.1 | 0 | 0 | 0 | 1 | 0 | 1 | 1 | | 2.0 | 0 | 0 | 1 | 0 | 1 | 0 | 0 | | 3.0 | 0 | 0 | 1 | 1 | 1 | 1 | 0 | | 4.0 | 0 | 1 | 0 | 1 | 0 | 0 | 0 | | 5.0 | 0 | 1 | 1 | 0 | 0 | 1 | 0 | | 5.1 | 0 | 1 | 1 | 0 | 0 | 1 | 1 | | 6.0 | 0 | 1 | 1 | 1 | 1 | 0 | 1 | | 7.0 | 1 | 0 | 0 | 0 | 1 | 1 | 0 | | 7.1 | 1 | 0 | 0 | 0 | 1 | 1 | 1 | | 8.0 | 1 | 0 | 1 | 0 | 0 | 0 | 0 | | 9.0 | 1 | 0 | 1 | 1 | 0 | 1 | 0 | | 10.0 | 1 | 1 | 0 | 0 | 1 | 0 | 0 | +--------------------------------------------+
(12) Data Filtering The FDIMU contains software to perform data filtering for up to 300 parameters. The filtered parameters are used for logical decisions. The filter characteristics are as shown below:
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-36-00Page 66 1 1 Config-2 Aug 01/05 1 1 1CES 1

AIDS Flight Phases - Table 11
Figure 007

R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-36-00Page 67 1 1 Config-2 Aug 01/05 1 1 1CES 1

t FO = OFV + -------* (NRV - OFV) T
Where: FO = Filter Output OFV = Old Filtered Value t = Samples/sec T = Filter Time Constant NRV = New Raw Value
The time constant T is modifiable via ground software.
For discrete words the appropriate bits are observed. Those bits
shall remain stable for at least 3 consecutive samples before
incorporating the new status into logic decisions.

(13) Class 3 Failure Messages If no data is received from one of the DITS ports for longer than 60 sec, a class 3 failure is reported to the CFDS. It is possible to enable/disable the bus monitoring one per bus basis via the GSE. Only enabled buses are reported with class 3 failures in the case that parameters are not updated. The class 3 failure message shows the ATA-chapter, name, the FIN number of the source system and the FDIMU name and the FDIMU FIN number. This example explains the message:
ATA-Chapter I Source System Name I I Source System FIN Number I I I Name I I I I FIN Number I_____ I_____ I____ I__ I____ 732534 EIVMU1 (1KS1) / FDIMU (10TV)
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 31-36-00Page 68 1 1 Config-2 Aug 01/05 1 1 1CES 1 **ON A/C 151-199, 201-210,

C. General Functions of DMU
(1) Identification of Location The design of the DMU allows its use in A/C with different input parameters and different tasks for data evaluation, if the appropriate programs are implemented. To ensure this capability, the unit is able to identify A/C type information on the FDIU ARINC 429 DITS data bus. Depending on the occurance of specific conditions or events, the DMU is trigger predefined actions. As a result of specific trigger conditions AIDS reports may be generated or data may be recorded on the DAR (optional) or stored in the DMU internal Smart Access Recorder (SAR). Print reports can be either printed out on the cockpit printer or transmitted via ACARS (optional). SAR data are also retrieved via the Portable Data Loader PDL or MDDU. Functions which are specific to A/C type (CFMI or IAE engines) are indicated in the respective logic definition.
(a) Identification of A/C Type The A/C type is programmed by an adequate DMU pin programming as shown below:
+---------------------------------+ | No | A/C Type | Program Discrete| | | | 1 | 2 | 3 | |----|----------|-----|-----|-----|
| 1 | A320 | 0 | 0 | 0 |
| | | | | |
| 2 | A320 | 1 | 0 | 0 |
| | | | | |
| 3 | A320 | 0 | 1 | 0 |
| | | | | |
| 4 | A320 | 1 | 1 | 0 |
| | | | | |
| 5 | A321 | 0 | 0 | 1 |
| | | | | |
| 6 | A319 | 1 | 0 | 1 |
| | | | | |
| 7 | SPARE | 0 | 1 | 1 |
| | | | | |
| 8 | SPARE | 1 | 1 | 1 |