Communication & Flight Instruments

Question 1

If the primary airplane power fails how does the PACIS receive power?

Answer 1

emergency lighting battery packs

Question 2

How many external interphone stations are there and where?

Answer 2

3; left side forward fuselage, REFUEL/DEFUEL panel in right engine nacelle, tail located by CVR and FDR

Question 3

Where is the ELT located?

Answer 3

dorsal fin, forward of the vertical fin

Question 4

How does the ELT get power?

Answer 4

internal 7.5 volt alkaline/manganese battery pack

Question 5

How long does the Cockpit Voice Recorder (CVR) record?

Answer 5

the last two hours

Question 6

How long does the Flight Data Recorder (FDR) record?

Answer 6

25 hours

Question 7

When does the FDR begin recording?

Answer 7

anti-collision light set to RED or WHITE, both engines running, airplane is airborne

Question 8

What happens when the ARCDU is in EMER mode?

Answer 8

the pilots headset and microphones are directly routed to VHF1
the pilots interphone and navigation receiver are directly routed to the headset
audio level is fixed for VHF 1 and INT
(same for copilots ARCDU)

Question 9

How are the ARCDUs powered?

Answer 9

ARCDU 1 - right main, left essential
ARCDU 2 - left main, right essential
ARCDU 1 PA system - hot battery bus (emergency power)

Question 10

FLIGHT DATA RECORDER caution light

Answer 10

flight data recorder malfunction or it is not energized

Question 11

MFD 1 and 2 Reversion Selector

Answer 11

provides the pilot with the ability to select any page for display on the MFD 1 and to control the EFIS reversion after display failures

Question 12

MFD 1 and 2 PFD position

Answer 12

selects PFD information for display on MFD 1

Question 13

MFD 1 and 2 NAV position

Answer 13

selects a navigation page in the ARC or FULL format

Question 14

MFD 1 and 2 SYS position

Answer 14

selects a systems page for display on the MFD

Question 15

MFD 1 and 2 ENG position

Answer 15

select the engine system page for display on the MFD, ED goes blank and an ‘AVAIL’ message appears in the center

Question 16

EFIS ADC SOURCE reversion selector

Answer 16

provides the crew with the ability to control the Air Data Computer source

Question 17

ALL pushbutton

Answer 17

with the MFD 1 or 2 selector set to SYS, ALL pushbutton cycles through all available systems, will continue to remain operative after an Engine and System Integrated Display control panel power loss

Question 18

EFIS ATT/HDG SOURCE reversion selector

Answer 18

provides the crew with the ability to control the AHRS source on the EFIS

Question 19

IAS MISMATCH message

Answer 19

ADC 1 and ADC 2 are providing different IAS values

Question 20

PITCH MISMATCH or ROLL MISMATCH message

Answer 20

inertial sources are providing different pitch and/or roll values

Question 21

ALT MISMATCH message

Answer 21

ADC 1 and ADC 2 are providing different barometric altitudes

Question 22

Altitude mismatch threshold

Answer 22

ground - 60 ft

increases to 180 ft at FL 270

Question 23

Automatic screen reversion

Answer 23

ED fails and is automatically transferred to MFD 1

Question 24

The Attitude and Heading Reference System (AHRS) consists of:

Answer 24

two AHRS control panels
two Attitude/Heading Reference Units
two remote flux valves
two remote Memory Modules

Question 25

The Attitude and Heading Reference Units (AHRU 1/AHRU 2) supply specific altitude and heading parameters directly to the following systems:

Answer 25

Electronic Instrumentation System (EIS) Auto Flight Control System (AFCS) Stall Protection System (SPS)

Question 26

The Electronic Instrumentation System (EIS) shows the Attitude and Heading Reference Units (AHRU 1/AHRU 2) parameters that follow:

Answer 26

Electronic Attitude Direction Indicator Electronic Horizontal Situation Indicator Altitude Intertial Vertical Speed Indicators

Question 27

The AHRUs also supply specific altitude and heading data to the systems that follow through the two Integrated Flight Cabinets (IFC 1, IFC 2):

Answer 27

``` Flight Data Recorder Flight Data Processing System Weather Radar Ground Proximity Warning System Traffic Collision Avoidance System Central Diagnostic System ```

Question 28

The AHRS operating modes are:

Answer 28

Alignment NORMAL or BASIC mode for attitude SLAVED or DG mode for heading

Question 29

When does AHRS alignment mode start and how long does it take?

Answer 29

automatically starts at the end of a 5 second power on self test, parameters are available approximately 20 seconds after alignment mode is started; manual realignment mode takes approximately 60 seconds on the ground and 90 seconds in flight

Question 30

How do the AHRUs work?

Answer 30

Uses vertical and direction gyros and accelerometers to sense rate of airplane movement which provide pitch, roll, and heading information. AHRS delivers a baro-inertial vertical speed and a baro-inertial altitude to each PFD. AHRS selects ADC input according to the ADC source reversion controlled by Crew.

Question 31

Describe AHRS NORMAL mode.

Answer 31

AHRUs use their associated ADUs parameters for attitude and automatically calculates and corrects for errors

Question 32

Describe AHRS SLAVE mode.

Answer 32

AHRU slaves its internal heading with analog magnetic heading information as calculated from analog signals from the flux valve and automatically compensates for heading errors

Question 33

Describe AHRS BASIC mode.

Answer 33

automatically activated when the TAS parameter becomes unavailable, causes decreases attitude accuracy, EADI will behave like a conventional mechanical gimbaled gyro

Question 34

Describe AHRS BASIC mode.

Answer 34

automatically activated when the TAS parameter becomes unavailable, causes decreased attitude accuracy, EADI will behave like a conventional mechanical gimbaled gyro

Question 35

Two primary channel Air Data Units (ADU 1, ADU 2) function independently and receive inputs from:

Answer 35

``` two pitot static probes air temperature probe Index Control Panels (ICP 1, ICP 2) Proximity Switch Electronic Unit (PSEU) ADC test switch ```

Question 36

The Air Data System (ADS) senses static pressure, pitot pressure, and static air temperature and converts it into electronic data which is used by the following systems:

Answer 36

``` cabin pressure control flight guidance flight controls indication Vmo / Mmo warning navigation powerplant operation ```

Question 37

The Electronic Instrument System (EIS) displays the following ADU parameters:

Answer 37

Indicated Air Speed on the PFDs True Airspeed displayed on the MFDs Static Air Temperature displayed on the ED

Question 38

What happens to altitude and IVSI when the AHRS is not valid?

Answer 38

When the AHRS altitude is not valid, the PFD displays uncorrected ADC altitude only. Therefore, altitude is only failed when selected ADC is failed, independently of AHRS altitude validity. Loss of AHRS or ADC will cause IVSI FAIL, until a manual reversion is performed.

Question 39

What does the PACIS provide?

Answer 39

Private voice communication between Flight Deck and Cabin Crewmember (CALL or EMER), visual and aural notification of interphone calls