R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 34-22-00Page 5 1201-212, 214-220, 1Config-1 May 01/05 1 1 1CES 1

 Standby Data - Attitude and Heading - Data Indicating
 Figure 003

R 1EFF : 001-049, 051-061, 101-105, 201-203, 1 34-22-00Page 6 1 1 Config-1 May 01/05 1 1 1CES 1

 Standby Data - Attitude and Heading - Data Indicating
 Figure 003A

R 1EFF : 062-099, 151-199, 204-212, 214-220, 1 34-22-00Page 7 1 1 Config-1 May 01/05 1 1 1CES 1 The external gimbal controls the roll rotation. The roll gimbal has unrestricted 360 degrees rotation around the roll axis. The gyro pin axis is maintained in the vertical position by the erection system (unstable pendulum erector) which is removed when the rotor axis deviates more than 9 degrees plus or minus 2 degrees. The accuracy of the vertical position in clean configuration is less than 0.5 degree. The fast resetting of the gyroscopic horizon can be activated by pulling the knob (8) located in the lower R corner of the indicator. The indicator provides the following information :

 -roll angle,
 -pitch angle,
 -instrument failure (RED flag).
 (1)
 Pitch information The aircraft symbol (black and yellow) (7) is fixed. The pitch drum (9), in the center of the instrument is divided into two zones separated by the reference horizon (white) : the upper part is blue, the lower part is brown. The pitch indications are displayed by means of a drum which is graduated between -80 and +80 degrees.

 (2)
 Roll information The roll information is given by a pointer (10) which moves in front of a dial (5) graduated in 10 degrees increments between -30 and +30 degrees.

 (3)
 Failure warning The flag (6) comes into view if a failure is detected in the electrical power supply or if the gyro rotor speed drops below 18,000 RPM.

R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 34-22-00Page 8 1201-212, 214-220, 1Config-1 May 01/05 1 1 1CES 1 STANDBY DATA : INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS)

__________________________________________________________ DESCRIPTION AND OPERATION
_________________________
 1. General_______
 A. ISIS Indicator The Integrated Standby Instrument System (ISIS) indicator replaces the three conventional standby instruments:
 -
the standby altimeter

 -
the standby horizon indicator

 -
the standby airspeed indicator.
 It is located on the center instrument panel.

 B. Standby Compass The standby heading is given 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.
 2. Component Location__________________ (Ref. Fig. 001)
 -------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
 -------------------------------------------------------------------------------2FN COMPASS-STANDBY 210 831 34-22-23 22FN IND-ISIS 401VU 211 34-22-25
 3. System Description__________________
 A. ISIS Indicator
 (1) Initialization function (Ref. Fig. 002) This function corresponds to the initialization phase of the ISIS indicator. As soon as the ISIS indicator is energized, the display shows these four yellow digital boxes for approximately 90 s:
 -ATT for the standby horizon function
 -SPD for the airspeed indicator function, ALT for the altimeter function the standby horizon
 -INIT 90 S for the initialization function. ISIS performs an excessive motion test during the whole initialization phase.
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 ISIS - Component Location
 Figure 001

R 1EFF : 106-149, 213-213, 221-299, 301-399, 1 34-22-00Page 2 1401-499, 1Config-2 Aug 01/05 1 1 1CES 1

 ISIS Indicator - Initialization Display
 Figure 002

R 1EFF : 106-149, 213-213, 221-299, 301-399, 1 34-22-00Page 3 1401-499, 1Config-2 Aug 01/05 1 1 1CES 1 If aircraft motion is detected, the attitude information is flagged and a yellow "ATT:RST" flag with a red ATT flag are displayed at the end of the initialization phase (Ref. Fig. 003) Pressing the RST pushbutton switch more than 2 seconds then restarts the initialization phase. The display also shows the baro reference. Baro reference can be set during the initialization phase.

 (2)
 Standby airspeed indicator function (Ref. Fig. 004)

 (a)
 The standby airspeed indicator function measures the pitot/static pressure differential from the standby air data system and provides airspeed indication in knots. The airspeed indication is displayed by means of a white tape positioned vertically in the left part of the display area. The airspeed scale is linear with five-knot graduations from 5 to 250 kts, ten-knot graduations from 250 to 520 kts and digital values every 20 kts. This tape moves up and down to indicate the A/C actual speed value in front of a fixed yellow reference line. When the airspeed data is not valid, a red SPD flag is displayed in place of the airspeed scale.
　
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