-
IR FAULT legend flashing on the CDU
-
IR 1(2)(3) FAULT message displayed on the upper ECAM DU: IR x MODE SEL...ATT
-SELECT ATT message displayed on the CDU (DATA DISPLAY selector
switch in STS position). The IR is designed so that the ATT mode can be used after BITE has detected failures which will cause excessive NAV mode data errors but does not disable the ATT mode mechanization. However, it is recommended to stay in NAV mode even with excessive navigation errors because of higher accuracy of attitude signals and a more complete signal processing. The ATT mode must always be used after loss of power or a similar situation in flight where a new alignment/leveling is required. The ENTER HEADING message is displayed on the CDU (DATA DISPLAY selector switch in STS position) when the ATT mode is selected until valid heading initialization is received from the MCDU or the CDU. The ATT mode is normally engaged with the aircraft in level flight. A 20-second period is needed with the aircraft in level flight to perform an attitude erection to initialize a "level" attitude. During this period, the data normally computed in ATT mode have SSMs set to NCD. In the event the ATT mode is engaged with the aircraft not in level flight, an erection cut-out function delays erection when yaw rate exceeds 0.5 deg/s and permits erection to continue when yaw rate drops below 0.25 deg/s. Twenty seconds of flight with the erection cut-out switch disengaged is required to erect the attitude.
R **ON A/C 005-049, 051-099, 101-149, 151-199, 201-299, 301-399, 401-499,
B. Indicating Attitude and heading information is computed by the ADIRU (IR portion) and processed by the associated DMC. The attitude data are displayed on the PFD and the heading data are displayed on the PFD, the ND and the RMI. In addition, vertical speed (V/S) is displayed on the PFD and Ground Speed and wind indications are displayed on the ND. In normal configuration, with the ATT/HDG selector switch in NORM position, the IR1 data are displayed on the CAPT PFD, ND and the RMI (Ref. ATA 34-57-00). The IR2 data are displayed on the F/O PFD and ND. The following parameters can be displayed on the CDU liquid crystal display according to the position of the DATA DISPLAY selector switch on the CDU:
-wind (WIND)
-present position (PPOS)
R 1EFF : 005-049, 051-099, 101-149, 151-199, 1 34-14-00Page 82 1201-299, 301-399, 401-499, 1Config-3 Aug 01/05 1 1 1CES 1
-true heading (HDG)
-status of selected system conditions (STS)
-track and ground speed (TK/GS)
-test values (TEST).
The sources of the data displayed are controlled by the SYS DISPLAY
selector switch on the CDU.
R **ON A/C 051-099, 106-149, 204-299, 301-399, 401-499,
(1) Attitude information (Ref. Fig. 013) The aircraft roll and pitch attitude is indicated in the center part of the PFD by a sphere representing a conventional ADI drum. (Ref. 31-64-00 for sphere definition and display).
(a)
Pitch angle information (item A) The A/C present pitch angle is given by the vertical displacements of the pitch attitude scale with respect to the center of the A/C reference. The scale moves behind the cut-sphere shaped window, limited by the lines of an upper and a lower sector. The scale rotates around the center of the A/C reference in accordance with the A/C present roll angle. The pitch scale comprises white reference lines and associated pitch angle values. The lines are given every 2.5 degrees from 0 to 10 degrees, then for the 15 degrees, 20 degrees, 30 degrees, 50 degrees and 80 degrees values. Beyond 30 degrees, red large arrow heads (V-shaped) indicate an excessive attitude and the direction to follow in order to reduce it (item B).
(b)
Roll angle information (item A) A yellow triangle which remains on the line going through the center of the A/C reference and which is perpendicular to the horizon line, moves against the fixed roll scale on the upper contour of the attitude sphere. This fixed roll scale comprises white marks for the 10 degrees, 20 degrees, 30 degrees and 45 degrees significant values, on either side of the zero position (horizontal wings) which is indicated by a small fixed triangle. The 60 degrees roll indication corresponds to the limits of the upper contour of the cut-sphere shaped window.
(c)
Attitude failure In case of attitude failure concerning the pitch and/or roll information the attitude sphere goes out of view and is replaced by a red ATT flag which flashes for a few seconds then remains steady (item C).
R 1EFF : 005-049, 051-099, 101-149, 151-199, 1 34-14-00Page 83 1201-299, 301-399, 401-499, 1Config-3 Aug 01/05 1 1 1CES 1
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