-------------------------------------------------------------------------------| Normal Inflation Mode | |-----------------------------------------------------------------------------| | Main and Nose Wheels | |-----------------------------------------------------------------------------| | Absolute Pressure | Differential Pressure | |---------------------------------|-------------------------------------------| | Comparison of each tire pressure| Comparison of the pressure of the two | | with an absolute minimum | wheels on the same axle. The difference is| | threshold. This threshold is | given in % (ROM) in relation to the | | given in % (ROM) in relation to | highest value of the two pressures | | the nominal pressure wired at | concerned. | | the computer connector. | | |---------------------------------|-------------------------------------------| | Takeoff | Flight + Landing | Takeoff | Flight + Landing | |--------------|------------------|------------------|------------------------| | Main | Nose | Main | Nose | Main | Nose | Main | Nose | | wheels|wheels|wheels| wheels | wheels| wheels| wheels | wheels | | 11 % | 11 % | 26 % | 26 % | 15 % | 15 % | 21 % | 21 % | -------------------------------------------------------------------------------
C. Warning
 (1) Pressure warning The TPIS computer sends a pressure warning to the upper ECAM DU. This warning is function of the result of the comparison of the tire pressure with the absolute and differential pressure thresholds. (Ref. Fig. 008)
 1EFF : 051-099, 1 32-49-00Page 10 1 1 May 01/05 1 1 1CES 1

 Lower ECAM DU - WHEEL Page
 Figure 007
 1EFF :  051-099,  1  32-49-00 Page 11 
1  1  May 01/05
 1  1
 1CES  1

 Absolute and Differential Pressure Thresholds
 Figure 008

 1EFF : 051-099, 1 32-49-00Page 12 1 1 May 01/05 1 1 1CES 1 The faults are memorized in a nonvolatile memory. The tire pressure warning is inhibited during takeoff when the aircraft speed is higher than 80 Kts.

 (2)
 Fault indication of the measurement channel The causes for the fault indication of the measurement channel are:

 -Out-of-range measurement ; sensor or connecting cable faulty. The fault indication is triggered after confirmation of the fault
 i.e. at most, two cycles after detection of the fault.
 -Erratic measurements ; wheel electronic module faulty. The fault indication is only triggered if the fault continues during seven interrogation cycles.
 -No measurement aquisition: failure of the electrical supply of the electronic module. The fault indication is triggered, at most, two cycles after detection of the fault.
 The fault is memorized in a nonvolatile memory.
 These two types of fault:

 -measurement channel,
 -pressure, can only be written in the nonvolatile memory if the engines are running: this prevents false warnings during wheel change.

 (3)
 Computer failure warning Computer failure is memorized in the nonvolatile memory as soon as the self-test detects the failure of one of the following components: ROM, RAM, timers, EPROM, multiplexer.

 (4)
 Digital outputs This table contains all the output parameters in digital form. They are sorted as per the numerical order of their output label. The following table gives:

 -SYS LABEL SDI: (SDAC,FWC,DMC,...) Output label for which the parameter is available.
 -PARAMETER DEFINITION: Parameter name.
 -RANGE ACCURACY: Measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy.
 -UNIT: Unit in which the digital value is transmitted.
 -SIG BIT: Indicates whether a sign bit is available.
 -DATA BITS: Number of bits used by the parameter in the label.
 -UPD/MSEC: Output transmission interval. The refresh rate is given in milliseconds.
 -CODE :
 BNR: binary data word
 BCD: binary coded decimal data word
 ISO: data word coded in ISO5 code

 1EFF : 051-099, 1 32-49-00Page 13 1 1 May 01/05 1 1 1CES 1

 DIS: discrete data word
 HEX: hexadecimal coded
 HYB: mixed code

 -ALPHA CODE: Indicates the parameter mnemonic code.
 -SOURCE ORIGIN: Parameter source computer or system.
 -------------------------------------------------------------------------------| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | -------------------------------------------------------------------------------|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| | | | | | | | | | |CONV | -------------------------------------------------------------------------------| 170 . 01 |DSCRT DATA| |PSI | | 6 |200 |DIS | | | | |WORD | | | | | | | | | | | | | | | | | | | | | |MAIN WHEEL|Bit status 1| | | 11| | | | | | |1 TYRE | | | | | | | | | | |PRESSURE | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |MAIN WHEEL|Bit status 1| | | 12| | | | | | |2 TYRE | | | | | | | | | | |PRESSURE | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |MAIN WHEEL|Bit status 1| | | 13| | | | | | |3 TYRE | | | | | | | | | | |PRESSURE | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |MAIN WHEEL|Bit status 1| | | 14| | | | | | |4 TYRE | | | | | | | | | | |PRESSURE | | | | | | | | | | |WARNING | | | | | | | | | | | | | | | | | | | | | |SPARE | | | | 15| | | | | | | | | | | | | | | | | |SPARE | | | | 16| | | | | | | | | | | | | | | | | |SPARE | | | | 17| | | | | | | | | | | | | | | | | |SPARE | | | | 18| | | | | | | | | | | | | | | | | |NOSE WHEEL|Bit status 1| | | 19| | | | |
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM LANDING GEAR 起落架8(49)