ATR Flight Instruments

FLIGHT INSTRUMENTS P1 AIR DATA SYSTEMAA

1.10.10 060 NOV 01

10.1 DESCRIPTION The flight environment data are provided by three independent air data systems : - Two main systems, - One standby system. MAIN SYSTEMS Aircraft is equipped with two independent AIR DATA COMPUTERS (ADC). Each computer is supplied with : - static air pressure provided by its specific static ports, - total air pressure provided by its specific pitot probe, - total air temperature provided by its specific TAT probe. Probes and ports are located on the LH and RH side of the fuselage and are electrically heated. From this data, each ADC computes : pressure altitude, vertical speed, Indicated Air Speed (IAS), True Air Speed (TAS), Total Air Temperature (TAT), Static Air Temperature (SAT).

ADC 1 supplies : - CAPT flight instruments (altimeter, airspeed ind., vertical speed ind.), - other systems : AHRS 1, FDAU, MFC, GPWS, pressurization, AFCS, ATC 1 and ATC 2 through TCAS control box, and TCAS through ATC 1and ATC 2 (if installed and mode S only). ADC 2 supplies : - F/O flight instruments (altimeter, airspeed ind., vertical speed ind.), - other systems : AHRS 2, FDAU, MFC, pressurization, AFCS, ATC 1 and ATC 2 Note : If ATC 2 mode S is installed, ADC 2 supplies TCAS through ATC 1 and ADC 2 EEC's, TAT/SAT/TAS indicator are supplied either by ADC 1 and ADC 2 according to ADC selector on capt panel. STANDBY SYSTEM The standby system consist of : - two static ports, - a pitot probe. These supply raw data directly to the standby airspeed ind. and the standby altimeter.R Mod : 3832 or 8259 ATR 42 Model : 400/500


1.10.10 080 NOV 00

10.1 DESCRIPTION

(See schematic p. 9/10)

The flight environment data are provided by three independent air data systems : - two main systems, - one standby system. MAIN SYSTEMS Aircraft is equipped with two independent AIR DATA COMPUTERS (ADC). Each computer is supplied with : - static air pressure provided by its specific static ports, - total air pressure provided by its specific pitot probe, - total air temperature provided by its specific TAT probe. Probes and ports are located on the LH and RH side of the fuselage and are electrically heated. From this data, each ADC computes : - pressure altitude, - vertical speed, - Indicated Air Speed (IAS), - True Air Speed (TAS), - Total Air Temperature (TAT), - Static Air Temperature (SAT). ADC 1 supplies : - CAPT flight instruments (altimeter, airspeed ind., vertical speed ind.), - other systems : AHRS 1, FDAU, ATC 1, MFC, GPWS, pressurization, AFCS. ADC 2 supplies : - F/O flight instruments (altimeter, airspeed ind., vertical speed ind.), - other systems : AHRS 2, FDAU, MFC, pressurization, AFCS and ATC 2 (if installed). EEC's, TAT/SAT/TAS indicator and GPS are supplied either by ADC 1 or ADC 2 according to ADC selector on capt panel. STANDBY SYSTEM The standby system consist of : - two static ports, - a pitot probe. Standby airspeed ind. and standby altimeter are directly supplied by raw data.

R Mod : 3952 or 4890 or 5021 or 5022

ATR 42 Model : 400/500


1.10.10 150 NOV 01

10.1 DESCRIPTION The flight environment data are provided by three independent air data systems : - Two main systems, - One standby system. MAIN SYSTEMS Aircraft is equipped with two independent AIR DATA COMPUTERS (ADC). Each computer is supplied with : - static air pressure provided by its specific static ports, - total air pressure provided by its specific pitot probe, - total air temperature provided by its specific TAT probe. Probes and ports are located on the LH and RH side of the fuselage and are electrically heated. From this data, each ADC computes : pressure altitude, vertical speed, Indicated Air Speed (IAS), True Air Speed (TAS), Total Air Temperature (TAT), Static Air Temperature (SAT).

ADC 1 supplies : - CAPT flight instruments (altimeter, airspeed ind., vertical speed ind.), - other systems : AHRS 1, FDAU, MFC, GPWS, pressurization, AFCS, ATC 1 and ATC 2 through TCAS control box, and TCAS through ATC 1 and ATC (if installed and mode S only). ADC 2 supplies : - F/O flight instruments (altimeter, airspeed ind., vertical speed ind.), - other systems : AHRS 2, FDAU, MFC, pressurization, AFCS, ATC 1 and ATC 2 Note : If ATC 2 mode S is installed, ADC 2 supplies TCAS through ATC 1 and ATC 2 EEC's, TAT/SAT/TAS indicator and GPS are supplied either by ADC 1 or ADC 2 according to ADC selector on capt panel. STANDBY SYSTEM The standby system consist of : - two static ports, - a pitot probe. These supply raw data directly to the standby airspeed ind. and the standby altimeter.R Mod : (3832 or 8259) + (3952 or 4890 or 5021 or 5022) ATR 42 Model : 400/500


1.10.10 001 NOV 01

STANDBY ALTIMETER (Mb Counter)

TOFA-01-10-10-005-A010AA1

Baroset value Is displayed in millibars (875 to 1 050 mb). Baroset knob Sets barometric reference on mb counter. Altitude pointer One revolution of pointer represents 1000 ft altitude change. Altitude counter The digital counter is equipped with three drums indicating ten thousands, thousands and hundreds of feet. A black and white flag marks the LH drum (ten thousands) when altitude is between 0 and 9999 ft. An orange and white flag marks the two LH drums (ten thousands and thousands) when altitude is below 0 ft. Note : Allowable deviation between normal altimeter indications and between normal and standby altimeter indications : FL (ft) NORM/NORM (ft) 55 60 70 NORM/STBY (ft) 70 150 200

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4

R R R R R R R

0 5.000 10.000

20.000 25.000

100 120

260 300

ATR 42 Model : 400/500


1.10.10 001 NOV 01


TOFA-01-10-10-005-A010AA1


2

3

4

R R R R R R R

0 5.000 10.000

20.000 25.000

100 120

260 300

ATR 42 Model : 400/500

NOV 01

R Mod : 3832 or 8259

ATR 42 Model : 400/500


1.10.10 001 NOV 01


TOFA-01-10-10-005-A010AA1


2

3

4

R R R R R R R

0 5.000 10.000

20.000 25.000

100 120

260 300

ATR 42 Model : 400/500


1.10.10 080 MAY 98

TCAS VERTICAL SPEED INDICATOR (TCAS FUNCTION NOT AVAILABLE)

1

Vertical speed pointer Indicates rate of climb/descent from 0 to 6000 ft/mn. From 0 to 1000 ft/mn the scale is graduated in 100 ft/mn increments, and from 1000 to 6000 ft/mn in 500 ft/mn increments. Display accuracy is 40 ft/mn.

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Vertical speed flag - Appears if the indicator is not able to display vertical speed information - In that case, the vertical speed pointer disappears when V/S flag appears. Test When depressed, indicator will display a test pattern. Light sensort Not available

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4 5

Mod : 4541

ATR 42 Model : 400/500

NOV 01

R Mod : 3832 or 8259

ATR 42 Model : 400/500


1.10.10 001 NOV 97

10.3

ELECTRICAL SUPPLY / SYSTEM MONITORING

ELECTRICAL SUPPLY EQUIPMENT R ADC 1 / ADC 2 R R R R R CAPT airspeed ind. and vertical speed ind. TAS/Temperature ind. CAPT altimeter + recording FDAU F/O airspeed ind. and vertical speed ind. F/O altimeter Standby altimeter vibrator SYSTEM MONITORING The following conditions are monitored by visual alerts : - Loss of ADC See ADC FAULT procedure in chapter 2.05.12. - Incorrect ADC switching See ADC SW FAULT procedure in chapter 2.05.12. DC BUS SUPPLY (C/B) DC EMER BUS (Primary on overhead panel ADC 1/2 EMER) HOT EMER BAT BUS (Back-up on overhead panel ADC 1/2 HOT) - Nil AC BUS SUPPLY (C/B) - Nil - Nil -

26 VAC STBY BUS (on overhead panel ASI VSI ALTM) 26 VAC STBY BUS (on overhead panel ALTM) 26 VAC BUS 2 (on overhead panel ASI VSI) 26 VAC BUS 2 (on overhead panel ALTM) - Nil -

- Nil - Nil - Nil DC BUS 1 (on overhead panel STBY ALTM)

ATR 42 Model : 400/500

FLIGHT INSTRUMENTS P 9/10 AIR DATA SYSTEMAA

1.10.10 060 NOV 01

10.4 SCHEMATIC

R Mod : 3832 or 8259

ATR 42 Model : 400/500

NOV 00

Mod : 3952 or 4890 or 5021 or 5022

ATR 42 Model : 400/500

FLIGHT INSTRUMENTS P 9/10 AIR DATA SYSTEMAA

1.10.10 150 NOV 01

10.4 SCHEMATIC

R Mod : (3832 or 8259) + (3952 or 4890 or 5021 or 5022)

ATR 42 Model : 400/500

FLIGHT INSTRUMENTS P3 EFISAA

1.10.30 001 NOV 98

8

Lateral ARM & CAPTURE See chapter 1.04.10. Vertical ARM 1 CAPTURE See chapter 1.04.10. Flight Director Command bars (magenta) Display computed commands to capture and maintain a desired flight path. The commands are satisfied by flying the aircraft symbol to the command bars. Glideslope and Localizer indication . Deviation from ILS glideslope is indicated by an index on a scale which is marked by dots. . Deviation from localizer is indicated by an index on a scale which is marked by dots. Note : Indexes and scales are visible only when an ILS frequency is selected on the related NAV control box. DH indication and annunciator . Displays the selected decision height in feet (blue), and the "DH" letters in white. When selected DH is set to zero, DH information disappears from EADI. Maximum selectable Decision Height is 990 ft. . When aircraft radio-altitude reaches selected decision height + 100 ft, a white box appears near the radio altitude information on EADI. When aircraft radio-altitude becomes lower than selected decision height, the amber "DH" symbol illuminates inside the white box. Radio altitude indication Displays in blue the radio-altitude and in white the RA letters. When radio-altitude indication is not valid, this information is replaced by amber dashes. Range of readable radio-altitude is from - 20 ft to 2500 ft. Above 2500 ft, radio altitude information is not displayed. See chapter 1.15.30.ATR 42 Model : 400/500

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1.10.30 001 NOV 97

EFIS CONTROL PANEL (ECP)

1

FULL/ARC pb Repetitive action on this pb alternately selects FULL mode and ARC mode on EHSI. At power up, FULL mode is automatically displayed. GSPD/TTG pb Repetitive actions on this pb alternately selects Groundspeed (GSPD) and Time to go (TTG) on EHSI display. At power up, Groundspeed is displayed. This pb is inoperative in composite mode. ADI/DIM/DH/TST knobs - Outer knob (ADI DIM) is used to select EADI ON/OFF and to set brightness. Automatic setting is also performed when ambient brighness changes. - Inner knob (DH TST) is used to set decision height from - 10 to 990 ft. Depressing it enables a test of the EFIS system and radio altimeter : . Test of the EFIS is only functional on the ground, all failure messages appear on EFIS. . Radio altimeter test is performed in flight as well as on ground. RA indication displays 100 ft on EADI. CAUTION : In flight, the RA test provides the radar with altitude information which trigger undue GPWS alerts.

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R R R R

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HSI/DIM/WX/DIM knobs - Outer knob (HSI DIM) is used to select EHSI ON/OFF and to set brightness. Automatic setting is also performed when ambient brighness changes. - Inner knob (WX DIM) is used to select ON/OFF weather radar traces, and to set average brightness in relation to other traces. N 1 BRG (0) selector To select blue bearing pointer to VOR 1 or to ADF 1. On OFF position, blue pointer disappears from EHSI. N 2 BRG () selector To select green bearing pointer to VOR 2 or to ADF 2. On OFF position, green pointer disappears from EHSI.ATR 42 Model : 400/500

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1.10.30 080 NOV 00

EFIS CONTROL PANEL (ECP)

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FULL/ARC pb Repetitive action on this pb alternately selects FULL mode and ARC mode on EHSI. At power up, FULL mode is automatically displayed. GSPD/TTG pb Repetitive actions on this pb alternately selects Groundspeed (GSPD) and Time to go (TTG) on EHSI display. At power up, Groundspeed is displayed. This pb is inoperative in composite mode. ADI/DIM/DH/TST knobs - Outer knob (ADI DIM) is used to select EADI ON/OFF and to set brightness. Automatic setting is also performed when ambient brighness changes. - Inner knob (DH TST) is used to set decision height from - 10 to 990 ft. Depressing it enables a test of the EFIS system and radio altimeter : . Test of the EFIS is only functional on ground, all failure messages appear on EFIS. . Radio altimeter test is performed in flight as well as on ground. RA indication displays 100 ft on EADI. CAUTION : In flight, the RA test provides the radar with altitude information which trigger undue GPWS alerts. HSI/DIM/WX/DIM knobs - Outer knob (HSI DIM) is used to select EHSI ON/OFF and to set brightness. Automatic setting is also performed when ambient brighness changes. - Inner knob (WX DIM) is used to select ON/OFF weather radar traces, and to set average brightness in relation to other traces. N 1 BRG (0) selector To select blue bearing pointer to VOR 1 or to ADF 1 or to GPS active waypoint. On OFF position, blue pointer disappears from EHSI. Note : RNV1 position is inoperative when MAP display is active. N 2 BRG () selector To select green bearing pointer to VOR 2 or to ADF 2 or to GPS active waypoint. On OFF position, green pointer disappears from EHSI. Note : RNV2 position is inoperative when MAP display is active. Refer to 1.15.60.ATR 42 Model : 400/500

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R Mod : 3952 or 4890 or 5021 or 5022

FLIGHT INSTRUMENTS P2 FLIGHT RECORDERSAA

1.10.50 001 NOV 00

50.2 CONTROLS FLIGHT DATA ENTRY PANEL (FDEP)

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R R R R R R R

5 6

Data display Date and time may be displayed and selected through the UPDATE pb 3 (successive pressures) and the Data entry panel 2 (except when 8 and 9 position of its first left thumbwheel is selected). Data entry panel Enables (through 4 thumbwheels) to insert different data : hour, minutes, month, day, year, flight number and maintenance data. UPDATE pb Data displayed are updated as following : - first left thumbwheel of Data entry panel must be on 9 position. S First sequence : hours and minute - UPDATE pb depressed, the display flashes - insert hour and minutes on data entry panel - UPDATE pb depressed, correction is taken into account and is displayed for 5 seconds. The following sequence must be initiated during these 5 seconds. S Second sequence : month and day Repeat first sequence and insert month and day. S Third sequence : year. Repeat first sequence and insert year. Note : Once data are inserted, reset the flight number on data entry panel. Events pb When momentarily depressed, the tape records are marked to identify a special event. STATUS FDAU light Illuminates amber when the FDAU is failed. STATUS SYST light Illuminates amber when : - the DFDR is failed or - the DFDR or QAR (if installed) electrical power is lost. or - QAR (if installed) 80 % full.ATR 42 Model : 400/500

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ATR Flight Instruments