test500-11

THE TWO AIR DATA COMPUTERS (ADC) ARE SUPPLIED WITH STATIC AIR PRESSURE, TOTAL AIR PRESSURE, TOTAL AIR TEMPERATURE AND EACH ADC COMPUTES: Pressure altitude, vertical speed and indicated airspeed (IAS). Pressure altitude, vertical speed, computed air speed (CAS), true air speed (TAS), ground speed (GS) and STD air temperature. (ISA). Pressure altitude, vertical speed, indicated air speed (IAS), true air speed (TAS), total air temperature (TAT) and static air temperature (SAT).

ADC 1 SUPPLIES: CAPT flight instruments, AHRS 1, ADC 1, FDAU, MFC, GPWS pressurization, AFCS. EEC's and TAT/SAT/TAS indicators are supplied according to ADC 1/2 selector on CAPT PANEL. A + B are correct.

ADC 2 SUPPLIES: F/O flight instruments, AHRS 2, FDAU, MFC, pressurization, AFCS and ATC 2 (if installed). F/O flight instruments only. F/O flight instruments and STBY SYSTEM.

AN "ADC 1” FAILURE IS DETECTED BY: Red flags on CPT flight instruments and MASTER CAUTION. Red flags on CPT flight instruments, lost of information on TAS/TAT/SAT indicator and torque amber bugs are lost if ADC SELECTOR in position 1. Red flags on CPT flight instruments, AHRS 1 failure and lost of information on TAS/TAT/SAT indicator.

AN “ADC 2” FAILURE IS DETECTED BY: Red flags on F/O flight instruments and lost of information on TAT/ SAT/TAS indication and torque amber bugs are lost if ADC selector in position 2. Red flags on F/O flight instruments and AFCS failure (AP disconnection). Red flags on F/O flight instruments, and AUTO PRESS failure.

IN CASE OF “ADC” FAILURE: Select the other ADC. Compare valid ADC with the STBY INSTRUMENTS and select the other ADC to restore TAS/TAT/SAT indicator and torque amber bugs. Reset the MASTER CAUTION and select the other ADC.

AIRCRAFT IN FLIGHT, TOTAL DC GEN LOSS: ADC 1 only is supplied. ADC 1 and ADC 2 are supplied. STBY INSTRUMENTS only are available.

THE TWO "AHRS"(ATTITUDE AND HEADING REFERENCE SYSTEM) PROVIDE THE FOLLOWING DATA: Pitch, roll, heading and ground speed. Pitch, roll and heading. Pitch, roll, heading, ground speed and TAS information.

. A/C ON GROUND, THE TWO “AHRS” START THEIR ALIGNMENT PERIOD: Automatically provided aircraft batteries selected ON. Automatically provided a DC and ACW EXT PWR is connected. After first engine start and AHRS 1 and 2 selected ON.

THE " AHRS 1" SUPPLIES: SGU 1, F/O RMI, FDAU, Radar, ASCB BUS. SGU 1, CPT RMI, FDAU, Radar, ASCB BUS. SGU 1, F/O RMI, ASCB BUS.

. THE " AHRS 2" SUPPLIES: SGU 2, CPT RMI, FDAU, Radar, ASCB BUS. SGU 2, F/O RMI, ASCB BUS. SGU 2, CPT RMI, ASCB BUS.

. WHEN THE “ERECT/FAIL” WARNING ILLUMINATES ON ONE “AHRS”: The crew must turn OFF this equipment and perform a switching to the remaining system. The crew must turn OFF this equipment for a 5 minutes period, then start a new alignment process. The crew must press this switch during 15 seconds, while maintaining the aircraft on nonaccelerated flight (straight and level) for gyro erection.

AIRCRAFT IN FLIGHT SUPPLIED BY BATTERIES ONLY: AHRS 1 only is supplied. AHRS 1 and 2 are supplied. STBY INSTRUMENTS only are operating.

WHAT HAPPENS IN CASE OF AN “AHRS” FAILURE?. Single chime, “HDG FAIL” red message on associated EHSI and “ATT FAIL” red message on associated EADI. HDG FAIL red message on associated EHSI and ATT FAIL red message on associated EADI and AP disengages. HDG FAIL red message on associated EHSI and ATT FAIL red message on associated EADI, red flag on opposite RMI and AP remains engaged.

WHAT ACTION SHOULD BE PERFORMED IF AN “AHRS” FAILURE OCCURS?. Pull the circuit breakers on the failed AHRS. Pilot on the side of failed AHRS should select opposite ATT/HDG reference (ATT/HDG push-button). Pilot on the side of failed AHRS should select opposite SGU (SGU push-button).

THE APPEARANCE OF AN AMBER “ATT” MESSAGE ON THE TOP RIGHT OF THE EADI MEANS THAT: Both pilots are using the same AHRS. The AHRS pitch and roll data are not longer provided to the EFIS. The two AHRS disagree on both pitch and roll information (6°or more).

THE APPEARANCE OF AN "HDG" AMBER MESSAGE ON THE TOP RIGHT OF THE EADI MEANS THAT: The two AHRS disagree on heading information (6°or more). The EFIS are no longer provided with the associated heading information. Heading information comes from the other AHRS.

. WHEN THE TWO "AHRS" DISAGREE OF 6° OR MORE, WHAT HAPPENS?. PIT, ROLL or ATT message is displayed on failed EADI. PIT, ROLL or ATT message is displayed on both EADI. PIT, ROLL or ATT message is displayed on both EADI, EFIS COMP amber light on CAP and AP disengages for ATT only.

. WHAT CORRECTIVE ACTION SHOULD BE PERFORMED IF AN "EFIS COMPARISON" FAULT OCCURS?. Pull the circuit breaker of the incorrect AHRS. Pilot on the side of the incorrect AHRS should select opposite ATT/HDG reference (ATT/HDG pushbutton). Compare both EADI to STBY ATT INSTRUMENT then perform steps A and B.

WHAT ARE THE INDICATIONS OF A "SGU" FAILURE, IN PART "A" OR "B”?. Both CRTs of the failed side go black. Both CRTs of the failed side display a red X. A red flag appears on both CRTs.

. WHAT ARE THE INDICATIONS OF A "SGU" FAILURE IN PART “C”?. Both CRTs of the failed side go black. Both CRTs of the failed side display a red X. A red flag appears on both CRTs.

WHAT CORRECTIVE ACTION SHOULD BE PERFORMED IF A SGU FAILURE OCCURS?. Pull the circuit breakers on the failed SGU. Pilot on the side of the failed SGU should select opposite ATT/HDG reference (depress ATT/HDG switch). Pilot on the side of the failed SGU should select opposite SGU reference (depress SGU switch).

. WHAT IS THE INDICATION OF A FAILED CRT?. The failed CRT goes black. The failed CRT displays a red "X". If the autopilot is engaged on the side of the failed CRT, all "upper" modes are lost. Both "B" and "C" are correct.

AFTER FAILURE OF A “CRT”: It should be switched OFF in order to obtain the COMPOSITE MODE on the remaining CRT. SGU push-button should be used to recover the lost display. COMPOSITE MODE appears automatically on the remaining CRT.

WHICH OF THE FOLLOWING METHODS IS/ARE USED TO ADVISE FOR LOSS OF ONE OR MORE INDIVIDUAL READOUTS ON THE EADI AND/OR EHSI: Red crosses appear on scales (LOC/GS/COURSE DEVIATION/SPD). Amber dashes replace digital information (DH/RA/CRS/HDG/DIST/GSPD/ or TTG). Navigation pointers and/or course deviation bars disappear. All of the above are correct.

. AIRCRAFT IN FLIGHT SUPPLIED BY BATTERIES ONLY: SGU 1 and SGU 2 are working. SGU 1 supplies the four CRTs (switching SGU 1 in F/O side). Only CAPT's EADI is working in COMP. MODE if the CAPT's EHSI is in OFF position.

. THE EADI “FAST SLOW” SCALE IS REFERENCED TO WHICH OF THE FOLLOWING?. AIRSPEED INTERNAL BUG sets on CAPT's airspeed indicator. AIRSPEED INTERNAL BUG sets on corresponding airspeed indicator. Selected IAS shown on ADU when in IAS mode.

AIRCRAFT ON GROUND, “FLIGHT RECORDER” OPERATIONS: FLIGHT RECORDER is OFF until one engine is started. FLIGHT RECORDER can be energized by selecting ON the RCDR PB and de-energized by pushing the RESET PB. A + B are correct.

"COCKPIT VOICE RECORDER" OPERATIONS: The last 30 minutes of recording are retained. All recording may be erased by pressing ERASE PB provided the aircraft is on ground and parking brake is set ON. A + B are correct.