3. Fault Confirmation
__________________
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
A. Test
FQIC Attitude Information
The primary source of attitude data, the effective pitch and roll, is the
ADIRS.
The FQIC Channel 1 receives accelerations from the ADIRU-1, and the
Channel 2 from the ADIRU-2.
The data is ARINC coded and identified as good or bad.
The effective pitch and roll is calculated from the ADIRU data when the
longitudinal,lateral, and normal accelerations are considered good.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page C269
Aug 01/05 CES The effective pitch and roll can also be calculated from the points of intersection of the probes with the fuel surface, within each tank. A minimum of three probes are required to calculate these angles. For the wing tanks, only the inner cell probes are used for this purpose. If the ADIRS derived attitudes are available and valid they are always used in preference to attitudes calculated from the data that comes from the probes. If the ADIRS derived attitudes are not available or are not valid for 10 seconds continuously, the attitudes calculated from the probes are used, provided that they are available and valid.
If the ADIRS and probe height derived attitudes are not available or not valid for 30 seconds continuously, default attitudes are used.
NOTE : On the GROUND, the default attitudes are:
____
- the effective pitch angle is set to 0.0 degrees
- the effective roll angle is set to 0.0 degrees.
NOTE : In FLIGHT, the default attitudes are set to those of the nominal
____
cruise conditions:
- the effective pitch angle is set to +2.0 degrees
- the effective roll angle is set to 0.0 degrees.
If a preferred attitude source was not available or not valid and subsequently becomes available for the necessary time (10 seconds for ADIRS data, 30 seconds for probe height data) the preferred source is reselected.
To make this procedure easy it has been assumed that the FQI system, probes, FQIC, are fully serviceable.
(1) Connect an ARINC Reader to the TEST CONNECTOR 198VC on the Panel Plate Relay - 188VU128, and located on the right side of the Aft Electronics Rack 80VU.
(2) Set the ARINC Reader to read the labels that follow:
- LABEL 331 Longitudinal Acceleration
- LABEL 332 Lateral Acceleration
- LABEL 333 Normal Acceleration.
(3) Examine the acceleration outputs for any signs of incorrect operation.
**ON A/C 301-399,
A. Test
FQIC Attitude Information The primary source of attitude data, the effective pitch and roll, is the ADIRS. The data is ARINC coded and identified as good or bad.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : ALL ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page C270
May 01/05 CES The effective pitch and roll is calculated from the ADIRU data when the longitudinal,lateral and normal accelerations are considered good. If the two ADIRUs have all three accelerations identified as good, ADIRU-1 will be choosen. If the above conditions are not met, effective pitch and roll is calculated from points of intersection on the fuel probes with the fuel surface, within each tank. Four probe pairs are used to determine effective pitch and roll and the result averaged to provide effective pitch and roll for the aircraft.
NOTE : On the GROUND, if effective pitch and roll cannot be calculated
____ from the data supplied by the ADIRS or the fuel probes, the default attitudes are:
- the effective pitch angle is set to -0.2 degrees
- the effective roll angle is set to 0.0 degrees.
NOTE : In FLIGHT, if effective pitch and roll cannot be calculated from
____ the data supplied by the ADIRS or the fuel probes, the default attitudes are set to those of the normal cruise conditions:
- the effective pitch angle is set to +2.5 degrees
- the effective roll angle is set to 0.0 degrees.
To make this procedure easy it has been assumed that the FQI system, probes, FQIC, are fully serviceable.
(1) Connect an ARINC Reader to the TEST CONNECTOR 198VC on the Panel Plate Relay - 188VU128, and located on the right side of the Aft Electronics Rack 80VU.
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