-
the MASTER CAUT lights on the glareshield come on
-
the Single Chime (SC) sounds
-
the CHECK HDG message appears on the PFDs and NDs.
(d)
NAV GPS 1(2) FAULT
(Ref. Fig. 023)
The GPSSUs are monitored by the three ADIRUs using the status
word sent by the GPSSU and the BITE of the IR partion.
This message is accompanied by:
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page 94 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
NAV IR 1(2)(3) fault message
Figure 018
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page 95 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
NAV IR 1+2 FAULT Message
Figure 019
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page 96 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
NAV IR 1+3 (2+3) FAULT Message
Figure 020
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page 97 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
NAV ATT DISCREPANCY Message
Figure 021
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page 98 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
NAV HDG DISCREPANCY Message
Figure 022
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page 99 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
NAV GPS - Fault Messages
Figure 023
1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-14-00Page A0 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
-activation of the MASTER CAUT lights on the glareshield panel
-aural warning: single chime (SC).
D. ADIRUs Performance Criteria
(1)
History The inertial parameters to be considered to evaluate the level of performance of an inertial system after flight completion are:
-
the radial position error (in NM)
-
the residual ground speed error (in kts).
Depending on their magnitude noticed at the end of the flight, the
concerned inertial system(s) shall or shall not be removed from the
aircraft.
(2)
Radial position error In order to address the statistical term of this requirement with the most relevant approximation, the removal criteria use a limit based on the recording of the radial position error on two consecutive flights. The use of a two-strike method presents the advantage to decrease the removal rate of healthy units that have shown, by chance, or by an inaccurate position entry at alignment, a radial position error beyond the specified criterion. The removal boundaries described on the figure present three different areas: (Ref. Fig. 024)
-
Area 1 - ADIRU OK all the time
-
Area 2 - ADIRU to be checked after second flight
-
Area 3 - ADIRU to be replaced.
NOTE : Area 2 is applicable when the residual radial position error
____ ranges within the limits described in following Para.
(a) Lower limit for removal criteria The integration of the drift rate results in a lower limit for the radial position error: Radial position error (NM) = (2 (NM/h) * T (h)) + Offset (NM) The presence of an offset is necessary to avoid the unjustified removal of healthy units subject to the natural Schuler effects and to the Present Position inaccuracies entered during initialization. It should be pointed out that the adverse impacts of such inaccuracies over the radial position error will reveal stronger for short flight durations (below 1.5 hour).
-Flight duration < 1.5 FH: The lower limit of the grey band is fixed at 5 NM.
-1.5 FH < Flight duration < 10 FH:
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ADIRU RPE removal criteria
Figure 024
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The lower limit of the grey band is fixed at 2T + 2.
-Flight duration > 10 FH: The lower limit of the grey band is fixed at 22 NM.
(b) Upper limit for removal criteria
-Flight duration < 1.5 FH: The upper limit of the grey band is fixed at 7.5 NM.
-1.5 FH < Flight duration < 10 FH: The upper limit of the grey band is fixed at 3T + 3.
-Flight duration > 10 FH: The upper limit of the grey band is fixed at 33 NM.
(3) Residual Ground Speed Error The residual ground speed for each IR is determined at the end of the flight when the aircraft has come to a complete stop.
(a)
Check of the residual ground speed can be made:
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