(3)
LS pushbutton switch This pushbutton switch located in the right top part of the indicator enables the display of the LS bars (LOC and G/S) (if the corresponding pin-program is activated) in place of the magnetic heading indications.
(4)
BARO selector knob This grey barometric selector knob located in the right bottom corner of the indicator, enables to display the standard barometric pressure or the barometric correction whose value can be adjusted by turning the knob.
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ISIS Indicator - Attitude Reset Display
Figure 025
R 1EFF : 106-149, 213-213, 221-299, 301-399, 1 34-22-00Page 37 1401-499, 1Config-2 Aug 01/05 1 1 1CES 1 This knob is used for the selection of the altitude and airspeed bugs.
(5) Brightness control The ISIS indicator has a manual and automatic display brightness control device, located on its face. The brightness ensures the readability in all environmental lighting conditions expected in service. After a long power supply interrupt on ground (>200 ms), an average brightness value is selected. In other cases, the last memorized brightness value is selected. The pushbutton switches are lighted for night vision in accordance with the general cockpit selection.
8. Test____
A. BITE Description
(1) General The ISIS indicator is fitted with an internal flight/ground information in order to manage the BITE and to prevent maintenance mode activation in flight. The test is inhibited when the internal computed airspeed is greater than 60 kts.
NOTE : The ISIS indicator complies with ABD0018, ABD0048 and ABD0100
____
Specification.
The ISIS indicator is able to display maintenance data when the BUGS and the LS pushbutton switches are pushed simultaneously (at least 2 s). In this case, a menu with two items is shown on the Liquid Crystal Display (LCD).
(a) OTHER DATA menu When the key adjacent to the OTHER DATA item (-) is pushed, a specific menu made of two items (LRU IDENT and ENGINEERING DATA) is shown.
-LRU IDENT item (Ref. Fig. 026) Allows to display the P/N and the S/N of the ISIS indicator, the configuration of the equipment (optional functions activated) and the functional time counter.
-ENGINEERING DATA item (Ref. Fig. 027) The engineering data provides correlation parameters and snapshot data concerning the failure displayed.
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ISIS Indicator - LRU IDENT Menu
Figure 026
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ISIS Indicator - ENGINEERING DATA Menu
Figure 027
R 1EFF : 106-149, 213-213, 221-299, 301-399, 1 34-22-00Page 40 1401-499, 1Config-2 Aug 01/05 1 1 1CES 1 In addition the engineering data enables to display the functional time counter.
(b) TESTS menu When the key adjacent to the TESTS item (+) is pushed, a specific menu made of two items (FUNCTIONAL TEST (110s) and DISPLAY TEST) is shown.
-DISPLAY TEST item (Ref. Fig. 028) The display test function enables to display white and black screens to check LCD screen state/quality.
-FUNCTIONAL TEST (110s) item (Ref. Fig. 029) When the key adjacent to the FUNCTIONAL TEST (110s) item (+) is pushed, the functional test is started and the message IN PROGRESS 110s is shown in the middle of the display area. At the end of the test, the message TEST OK is shown on the display area. In case of fault detection, the BITE displays a message.
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ISIS Indicator - DISPLAY TEST Menu
Figure 028
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ISIS Indicator - FUNCTIONAL TEST Menu
Figure 029
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Post SB 34-1280 For A/C 213-213,
STANDBY DATA : INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS)
__________________________________________________________ DESCRIPTION AND OPERATION
_________________________
1. General_______
A. Standby Heading The standby heading is performed by a magnetic compass that is an independent instrument which provides the flight crew with the A/C magnetic heading. It is installed on the top of the windshield center post and allows a check of the heading provided by the main sources of the heading system. It acts in standby when these systems are inoperative.
B. Standby Attitude The standby attitude is performed by a gyroscopic horizon that is an independent instrument which provides the flight crew, with a constant indication of the aircraft attitude. It is contained in a 3 ATIs case and installed on the center instrument panel. It allows a check of the attitude provided by the main sources of attitude system. It acts in standby when these systems are inoperative.
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