If bit 27 = 1, then the parameter values are shown in print out and
alpha call-up in following units: comfort temperatures ckpt, cab temp: deg F instead of deg C (29.1.242.01, 29.2.242.01,
29.1.244.01, 29.2.244.01,
29.1.245.01, 29.2.245.01)
(11) Flight Phase Detection
R (Ref. Fig. 009) The DMU divide the flight leg into seperate flight phases. The flight phase determination is mainly based on the FWC (Param. 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.
R 1EFF : 001-049, 051-099, 101-105, 1 31-36-00Page 48 1 1 Config-1 May 01/05 1 1 1CES 1
AIDS Flight Phases - Table 11 R Figure 009
R 1EFF : 001-049, 051-099, 101-105, 1 31-36-00Page 49 1 1 Config-1 May 01/05 1 1 1CES 1 +-------------------------------------------+ | Flight | DMU 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 DMU 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:
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 on 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 on per bus basis via the GSE. Only enabled buses are reported with class 3 failures in the case that parameters are not updated.
R 1EFF : 001-049, 051-099, 101-105, 1 31-36-00Page 50 1 1 Config-1 May 01/05 1 1 1CES 1 The class 3 failure message is contain the ATA-chapter, name, the FIN number of the source system and the DMU name and the DMU FIN number. This example explains the message:
ATA-Chapter
I Source System Name
I I Source System FIN Number
I I I DMU Name
I I I I DMU FIN Number
I_____ I_____ I____ I__ I____
732534 EIVMU1 (1KS1) / DMU (1TV)
R 1EFF : 001-049, 051-099, 101-105, 1 31-36-00Page 51 1 1 Config-1 May 01/05 1 1 1CES 1 -----------------------------------------------------------------------| Log. | Item | Description of Function Item | | No. | No. | | |------|-------|------------------------------------------------------|
| | | The DMU uses the FWC flight phases (parameter |
| | | 26.1.126.01 bit 11 to 14 to perform the AIDS |
| | | flight phases as shown in Table 11) |
| | | |
| | A | Parameter |
| | | |
| | B | Logic algorithm |
| | | |
| | B.1 | IVV 1 = 400 FT/M |
| | | |
| | B.2 | IVV 2 = 400 FT/M |
| | | |
| | B.3 | IVV 3 = 400 FT/M |
| | | |
| | B.4 | IVV 4 = 10000 FT/M |
| | | |
| | B.5 | IVV 5 = 10000 FT/M |
| | | |
| | B.6 | SLAT 1 = 5 deg |
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM 指示/记录系统 3(23)
