(c)
 LRU IDENTIFICATION

 (Ref. Fig. 020)
 This item provides the ADIRU Part Number and Serial Number.
 The Part Number and the Serial Number of the CDU are also
 displayed.

 (d)
 GROUND SCANNING

 (Ref. Fig. 020)
 This item describes the current on-the-ground fault status of the
 selected IR.

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 26 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - Activation of IR Interactive Function
 Figure 017

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 27 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - Activation of ADR Interactive Function
 Figure 018

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 28 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 1/7
 Figure 019

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 29 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 2/7
 Figure 020

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 30 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 (e)
 TROUBLE SHOOTING DATA

 (Ref. Fig. 021)
 This item provides, for each fault message stored in the LAST LEG
 or PREVIOUS LEGS REPORT, additional data required by the
 maintenance for failure investigation.

 (f)
 CLASS 3 FAULTS

 (Ref. Fig. 021)
 This item reports all class 3 faults recorded since the last
 takeoff.

 (g)
 SYSTEM TEST (Ref. Fig. 022) This item activates a complete test of the IR system and presents a report to the user.

 (h)
 INTERFACE TEST (Ref. Fig. 023) This item controls the functional test modes of the selected IR. The test mode is inhibited whenever any of the following conditions exists:

 -ground speed greater than or equal to 20 kts

 -IR in the ATT mode.
 The text displayed describes the various steps of the interface
 test; when you push the line key adjacent to the START TEST
 indication, the following test sequence is run:

 -0-2 seconds BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are energized:
 . ALIGN
 . ON BAT
 . DC FAIL (See nota)
 . IR FAULT
 . IR OFF (See nota)
 . SPARE IR OUT 1 (See nota)
 . SPARE IR OUT 2 (See nota)

 -after 2 seconds BCD, BNR and Discrete Words are output with SSM set to Functional Test and data set as shown in the following tables. Annunciator discretes are de-energized to the previously indicated status.
R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 31 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 3/7
 Figure 021

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 32 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 4/7
 Figure 022

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 33 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1

 ADIRS BITE - IR Main Menu 5/7
 Figure 023

R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 34 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1 NOTE : No associated annunciator in the cockpit.

____
 ----------------------------------------------------------------| | | SELF TEST VALUE | | LABEL | PARAMETER |--------------------------| | | | 0 to 2 s. | After 2 s. | |--------------------------------------------------------------| | 010 | PRESENT POSITION LAT | 188.88.8' | N 22.30.0' | | 011 | PRESENT POSITION LONG | 188.88.8' | E 22.30.0' | | 012 | GROUND SPEED | 6888 Kts | 200 Kts | | 013 | TRACK ANGLE-TRUE | 688.8. | 00.0. | | 014 | MAGNETIC HEADING | 688.8. | 15. | | 015 | WIND SPEED | 688 Kts | 100 Kts | | 016 | WIND DIRECTION-TRUE | 688. | 30. | | 041 | SET LATITUDE | 188.88.8' | N 22.30.0' | | 042 | SET LONGITUDE | 188.88.8' | E 22.30.0' | | 043 | SET MAGNETIC HEADING | 688. | 15. | | 044 | TRUE HEADING | 688.8. | 10. | ----------------------------------------------------------------Table 2 : Output BCD Words
R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-18-00Page 35 1401-499, 1Config-3 Aug 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 | | 076 | GPS ALTITUDE | 10,000 ft | | 101 | GPS HDOP | 4.0 | | 102 | GPS VDOP | 3.0 | | 103 | GPS TRACK ANGLE | 0.0. | | 110 | GPS LATITUDE | N 22.50. | | 111 | GPS LONGITUDE | E 22.50. | | 112 | GPS GROUND SPEED | 200 kts | | 120 | GPS LATITUDE FINE | N 00.00. | | 121 | GPS LONGITUDE FINE | E 00.00. | | 125 | UTC TIME | 12:00:00 | | 130 | GPS HORIZ INTEGRITY LIM | 10.0 NM | | 131 | HYBRID HORIZ INTEGRITY | 5.0 NM | | | LIMIT | | | 132 | HYBRID TRUE HEADING | 10. | | 135 | HYBRID VERTICAL FOM | 300 ft | | 136 | GPS VERTICAL FOM | 100 ft | | 137 | HYBRID TRACK ANGLE | 0.0. | | 143 | TERMINAL AREA HIL | 0.8 NM | | 150 | UTC | 12:00:00 | | 162 | DESTINATION ETA | 06:30:00 | | 163 | ALT WAYPOINT ETA | 06:35:00 | | 165 | GPS VERTICAL VELOCITY | -600 ft/mn | | 166 | GPS N/S VELOCITY | 200 kts | | 174 | GPS E/W VELOCITY | 200 kts | | 175 | HYBRID GROUND SPEED | 200 kts | | 247 | GPS HORIZONTAL FOM | 6.0 NM | | 254 | HYBRID LATITUDE | N 22.50. | | 255 | HYBRID LONGITUDE | E 22.50. | | 256 | HYBRID LATITUDE FINE | N 00.00. | | 257 | HYBRID LONGITUDE FINE | E 00.00. | | 260 | DATE | 1/1/99 | | 261 | HYBRID ALTITUDE | 10,000 ft | | 263 | HYBRID FLIGHT PATH ANGLE| -5.0. | | 264 | HYBRID HORIZONTAL FOM | 7.0 NM | | 266 | HYBRID N/S VELOCITY | 200 kts | | 267 | HYBRID E/W VELOCITY | 200 Kts | | 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. |
　
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