Communication & Flight Instruments Flashcards
If the primary airplane power fails how does the PACIS receive power?
emergency lighting battery packs
What does the PACIS provide?
Private voice communication between Flight Deck and Cabin Crewmember (CALL or EMER), visual and aural notification of interphone calls
How many external interphone stations are there and where?
3; left side forward fuselage, REFUEL/DEFUEL panel in right engine nacelle, tail located by CVR and FDR
Where is the ELT located?
dorsal fin, forward of the vertical fin
How does the ELT get power?
internal 7.5 volt alkaline/manganese battery pack
How long does the Cockpit Voice Recorder (CVR) record?
the last two hours
How long does the Flight Data Recorder (FDR) record?
25 hours
When does the FDR begin recording?
anti-collision light set to RED or WHITE, both engines running, airplane is airborne
What happens when the ARCDU is in EMER mode?
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)
How are the ARCDUs powered?
ARCDU 1 - right main, left essential
ARCDU 2 - left main, right essential
ARCDU 1 PA system - hot battery bus (emergency power)
FLIGHT DATA RECORDER caution light
flight data recorder malfunction or it is not energized
MFD 1 and 2 Reversion Selector
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
MFD 1 and 2 PFD position
selects PFD information for display on MFD 1
MFD 1 and 2 NAV position
selects a navigation page in the ARC or FULL format
MFD 1 and 2 SYS position
selects a systems page for display on the MFD
MFD 1 and 2 ENG position
select the engine system page for display on the MFD, ED goes blank and an ‘AVAIL’ message appears in the center
EFIS ADC SOURCE reversion selector
provides the crew with the ability to control the Air Data Computer source
ALL pushbutton
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
EFIS ATT/HDG SOURCE reversion selector
provides the crew with the ability to control the AHRS source on the EFIS
IAS MISMATCH message
ADC 1 and ADC 2 are providing different IAS values
PITCH MISMATCH or ROLL MISMATCH message
inertial sources are providing different pitch and/or roll values
ALT MISMATCH message
ADC 1 and ADC 2 are providing different barometric altitudes
Altitude mismatch threshold
ground - 60 ft
increases to 180 ft at FL 270
Automatic screen reversion
ED fails and is automatically transferred to MFD 1
The Attitude and Heading Reference System (AHRS) consists of:
two AHRS control panels
two Attitude/Heading Reference Units
two remote flux valves
two remote Memory Modules
The Attitude and Heading Reference Units (AHRU 1/AHRU 2) supply specific altitude and heading parameters directly to the following systems:
Electronic Instrumentation System (EIS)
Auto Flight Control System (AFCS)
Stall Protection System (SPS)
The Electronic Instrumentation System (EIS) shows the Attitude and Heading Reference Units (AHRU 1/AHRU 2) parameters that follow:
Electronic Attitude Direction Indicator
Electronic Horizontal Situation Indicator
Altitude
Intertial Vertical Speed Indicators
The AHRUs also supply specific altitude and heading data to the systems that follow through the two Integrated Flight Cabinets (IFC 1, IFC 2):
Flight Data Recorder Flight Data Processing System Weather Radar Ground Proximity Warning System Traffic Collision Avoidance System Central Diagnostic System
The AHRS operating modes are:
Alignment
NORMAL or BASIC mode for attitude
SLAVED or DG mode for heading
When does AHRS alignment mode start and how long does it take?
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
How do the AHRUs work?
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.
Describe AHRS NORMAL mode.
AHRUs use their associated ADUs parameters for attitude and automatically calculates and corrects for errors
Describe AHRS SLAVE mode.
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
Describe AHRS BASIC mode.
automatically activated when the TAS parameter becomes unavailable, causes decreases attitude accuracy, EADI will behave like a conventional mechanical gimbaled gyro
Describe AHRS BASIC mode.
automatically activated when the TAS parameter becomes unavailable, causes decreased attitude accuracy, EADI will behave like a conventional mechanical gimbaled gyro
Two primary channel Air Data Units (ADU 1, ADU 2) function independently and receive inputs from:
two pitot static probes air temperature probe Index Control Panels (ICP 1, ICP 2) Proximity Switch Electronic Unit (PSEU) ADC test switch
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:
cabin pressure control flight guidance flight controls indication Vmo / Mmo warning navigation powerplant operation
The Electronic Instrument System (EIS) displays the following ADU parameters:
Indicated Air Speed on the PFDs
True Airspeed displayed on the MFDs
Static Air Temperature displayed on the ED
What happens to altitude and IVSI when the AHRS is not valid?
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.
