-body roll rate in degrees per second (label 327),
 -roll angle in degrees (label 325),
 -body pitch rate in degrees per second (label 326),
 -pitch angle in degrees (label 324),
 -
body yaw rate in degrees (label 330),

 -
body longitudinal acceleration (label 331),

 -
body lateral acceleration (label 332).

 (4)
 Discrete output One discrete output is used for fault/healthy indication. This discrete is grounded when the indicator is out of order and when the OUT OF ORDER message is displayed. (Ref. Fig. 018)

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 ISIS Indicator - OUT OF ORDER Display
 Figure 018

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 6. Component Description
_____________________
 A. External Description
 (Ref. Fig. 019)
 The face of the ISIS indicator has:

 -an ATT/RST pushbutton switch to reset the horizon (attitude) function to the true value,
 -two ( + and - ) brightness adjustment pushbutton switches,
 -
a BUGS pushbutton switch for the display/inhibition of the BUGS function,

 -
a LS pushbutton switch for the engagement/disengagement of the ILS function,

 -
a light sensor,

 -
a BARO rotary knob/pushbutton switch. The pushbutton switch is used to change the barometric pressure (which can be adjusted by the rotary knob) to the standard pressure and back again.

 The back of the ISIS indicator is equipped with a 41-pin connector, a total pressure pneumatic connector (P) and a static pressure pneumatic connector (S).
 B. Internal Description
 (Ref. Fig. 020, 021)
 The ISIS indicator contains the following subassemblies:

 -
a Filtering Board (FIB)

 -
a Power Supply Unit (PSU)

 -an Interface Board (INB)
 -a Pressure Sensor Module (PSM)
 -an Inertial Measurement Unit (IMU)
 -a Control Processor and Graphic Display Module (CPGDM)
 -an Optical Module (OPM).
 (1)
 Filtering board This board includes the rear plate with the two pressure unions for the static and the total pressures and the 41-pin external connector. It ensures protection against electromagnetic interference and lightning strikes.

 (2)
 Power supply unit From the 28VDC, this unit supplies the voltages necessary for the operation of the indicator.

 (3)
 Interface board This board makes the interface between part of the indicator inputs/outputs, the pressure sensors, the inertial sensors, the face, the light box and the CPGDM. It also supplies a clock signal at 20MHz.

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 ISIS Indicator - Component Description
 Figure 019

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 ISIS Indicator - Block Diagram
 Figure 020

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 ISIS Indicator - Location of Internal Components
 Figure 021

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 (4)
 Pressure sensor module This module contains for each system (static pressure and total pressure):

 -
a pressure sensor with a cell (silicon detector),

 -
a sensor memory with an electronic board that shapes the signals and stores the characterization parameters of the sensor.

 (5)
 Inertial measurement unit This unit includes three single-axis rate sensors (with analog outputs) and their temperature probes, two acceleration sensors and their temperature probes, and an electronic board. Its functions are as follows:

 -angular rate measurement,
 -temperature measurement,
 -absolute acceleration measurement,
 -storing of the IMU parameters (sensors, misalignment, identification),
 -
generation of configuration data (IMU presence, two or three accelerometers),

 -
generation of sensor healthy-operation discretes,

 -digitization of the sensor data (analog-to-digital converter).

 (6)
 Control processor and graphic display module This module performs the computing and graphics generation functions. The Control Processing Unit (CPU) part of the CPGDM processes the data received through the INB and directly from the IMU to calculate the operational parameters (altitude, attitude and airspeed). The graphics part converts the data supplied by the CPU into smoothed symbology and drives the Liquid Crystal Display (LCD).
　
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