3_ AOA Test
 (Ref. Fig. 040)
 The AOA test function set the AOA test output discrete to
 command the AOA sensor to fixed position greater than the
 stall warning threshold. So, the Flight Warning Computer
 activates the aural stall warning.

 (i)
 Ground Report (Ref. Fig. 035)

 (j)
 Current Status (Ref. Fig. 041) The Current Status function displays on 8 pages the state (as read by the computer) of the discrete inputs, digital inputs (ADM and baro-correction), analog inputs and power condition.

 (3) Inertial Interactive function description
 (a)
 Last Leg Report (Ref. Fig. 042)

 (b)
 Previous Legs Report (Ref. Fig. 042)

 (c)
 LRU Ident (Ref. Fig. 042) The Part Numbers and the Serial Numbers of the ADIRU are displayed.

 (d)
 Ground Scanning (Ref. Fig. 043) The Ground Scanning function performs most of the continuous tests .All tests with an important time delay (temperature ...) are not performed within this function.

 (e)
 Trouble Shooting Data (Ref. Fig. 043) A maximum of sixteen 16-bit words can be recorded for the Trouble Shooting Data.

 (f)
 Class 3 Fault (Ref. Fig. 042)

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 52 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - ADR AOA Test
 Figure 040

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 53 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - ADR Current Status
 Figure 041

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 54 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 1/3
 Figure 042

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 55 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 2/3
 Figure 043

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 56 1 1 Config-1 May 01/05 1 1 1CES 1

 (g)
 System Test (Ref. Fig. 037) The system test function performs power-up tests and various continuous tests to provide a complete status of the IR part of the ADIRS. The layout of the System test pages of the ADR and IR parts are equivalent except of the title ADR which is replaced by IR. It is necessary to re-initialize the system because the navigation data are erased by the test of the RAM performed at the power-up.

 (h)
 Interface Test (Ref. Fig. 044) Initiation of the IR Interface Test shall cause the following sequence to occur:

 -0-2 seconds BCD, BNR and Discrete Words - output with SSM set to Functional Test and data set as shown in next tables. Annunciator discretes shall be energized.
 -Over 2 seconds
 BCD, BNR and Discrete Words - output with SSM set to
 Functionnal Test and data set as shown in next tables.
 Annunciator discretes released to indicated status.

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 57 1 1 Config-1 May 01/05 1 1 1CES 1

 ADIRS BITE - IR Interface Test
 Figure 044

R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-18-00Page 58 1 1 Config-1 May 01/05 1 1 1CES 1

 -----------------------------------------------------------------------
| LABEL | PARAMETER | SELF TEST VALUE | |----------------------------------------------------------------------| 052 | PITCH ANGULAR ACCEL | 5.0. /s/s | | 053 | ROLL ANGULAR ACCEL | 5.0. /s/s | | 054 | YAW ANGULAR ACCEL | 5.0. /s/s | | 310 | PRESENT POSITION LAT | N 22.50. | | 311 | PRESENT POSITION LONG | E 22.50. | | 312 | GROUND SPEED | 200 Kts | | 313 | TRACK ANGLE-TRUE | 00.0. | | 314 | TRUE HEADING | 10.0. | | 315 | WIND SPEED | 100 Kts | | 316 | WIND DIRECTION-TRUE | 30. | | 317 | TRACK ANGLE-MAG | 5. | | 320 | MAGNETIC HEADING | 15. | | 321 | DRIFT ANGLE | -10. (Left) | | 322 | FLIGHT PATH ANGLE | -5. | | 323 | FLIGHT PATH ACCEL | 0.2g | | 324 | PITCH ANGLE | 5. | | 325 | ROLL ANGLE | 45. (Right) | | 326 | BODY AXIS PITCH RATE | 10./s | | 327 | BODY AXIS ROLL RATE | 10./s | | 330 | BODY AXIS YAW RATE | 10./s | | 331 | BODY LONGIT ACCEL | 0.02g | | 332 | BODY LATERAL ACCEL | 0.10g | | 333 | BODY NORMAL ACCEL | 0.10g | | 334 | PLATFORM HEADING | 22.50. | | 335 | TRACK ANGLE RATE | 4.0./s | | 336 | PITCH ATT RATE | 10./s | | 337 | ROLL ATT RATE | 10./s | | 340 | TRACK ANGLE GRID | 10./s | | 341 | GRID HEADING | 20./s | | 360 | POTENTIAL VERT SPEED | -600 ft/mn | | 361 | INERTIAL ALTITUDE | 10,000 ft | | 362 | ALONG TRACK HORIZ ACCEL | 0.02g | | 363 | CROSS TRACK HORIZ ACCEL | 0.02g | | 364 | VERTICAL ACCEL | 0.1g | | 365 | INERTIAL VERT SPEED | -600 ft/mn | | 366 | N-S VELOCITY | 200 Kts (N) | | 367 | E-W VELOCITY | 200 Kts (E) | | 076 | GPS ALTITUDE | 10,000 FT | | 101 | HDOP | 500 | | 102 | VDOP | 500 | | 103 | GPS TRACK ANGLE TRUE-BNR | 00.0. | | 110 | GPS PRES POS-LAT | N22.50. | | 111 | GPS PRES POS-LONG | E22.50. | | 112 | GPS GROUND SPEED-BNR | 200 KTS |
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM NAVIGATION 導(dǎo)航2(87)