Reporting Flashcards
THE MPC UNIT INCLUDES THE FOLLOWING:
FLIGHT DATA ACQUISITION UNIT
DATA MANAGEMENT UNIT
THE AIRCRAFT PERFORMANCE MONITORING INPUTS INCLUDE:
PRESSURE ALTITUDE, SAT, IAS, ENG TQ
PROP ROTATION SPEED, LANDING GEAR AND FLAPS SENSOR INPUT
AIRCRAFT WEIGHT REQUIRING FLIGHT CREW SELECTION BEFORE EACH TAKE-OFF VIA
THE APM WEIGHT ROTARY SELECTOR
THE FDAU ACQUIRES DATA FROM WHICH OF THE BELOW SYSTEMS:
FLIGHT DATA RECORDING
AIRCRAFT PERFORMANCE MONITORING
DATA BROADCAST TO CAC (TO AVIONICS SYSTEM)
THE INDICATION “INCREASED SPEED” AMBER MESSAGE INDICATES:
THE AIRCRAFT SPEED IS LOWER THAN THE MINIMUM ICING SPEED +1OKTS
THE INDICATION “DEGRADED PERF” ON THE ALERT WINDOW IN LEVEL FLIGHT MEANS:
DRAG ABNORMALLY HIGH & IAS SIGNIFICANT DECREASE COMPARED TO MAXIMUM
CRUISE SPEED
THE MFC SYSTEM CONSISTS OF:
2 COMPUTERS, EACH WITH 2 MODULES
THE SELF TEST SEQUENCE OBSERVED DURING POWER UP IS:
MFC 1A & MFC 2A FLASH, THEN MFC1B & MFC 2B FLASH
THE INDICATION “MFC 2A” ON THE ALERT WINDOW MEANS:
A SINGLE MFC CHANNEL FAILURE
THE INDICATION “MFC 1A + MFC 2B” AMBER MESSAGE ON THE EWD MEANS:
A SINGLE CHANNEL FAILURE OF EACH MFC MODULE
THE INDICATION “MFC 1A + MFC 1B” AMBER MESSAGE ON THE EWD MEANS:
MULTIPLE MFC CHANNEL FAILURES
THE INTEGRATED MODULAR AVIONIC (IMA) PROVIDES:
COMPUTATION AND MEMORY
THE INTEGRATED MODULAR AVIONIC (IMA) IS MAINLY COMPOSED OF
A DUAL CORE AVIONICS CABINET
THE CORE AVIONICS CABINET (CAC) EQUIPMENT COMPRISES OF:
A RACK AND SET OF CARDS
IN BASIC CONFIGURATION EACH CAC INCLUDES:
1 CORE PROCESSING MODULE (CPM)
IN BASIC CONFIGURATION EACH CAC INCLUDES:
1 IOM-S (INPUT OUTPUT MODULE)
IN BASIC CONFIGURATION EACH CAC INCLUDES:
2 x IOM-DC
THE CORE PROCESSING MODULE PROVIDES:
SHARED MEMORY COMPUTATION RESOURCES TO EXECUTE HOSTED AVIONICS
APPLICATIONS
THE SWM (GATEWAY AND SWITCH MODULE) PROVIDES:
CONNECTION BETWEEN THE CPM AND OTHER AVIONICS DATA NETWORK SUBSCRIBERS
THE MAIN APPLICATIONS HOSTED BY THE CORE AVIONICS CABINET INCLUDE:
FLIGHT WARNING (FWA) AND AUTOFLIGHT (AFCA)
THE CAC 1 AND 2 COMMUNICATE WITH:
5 DISPLAY UNITS – DU1, DU2, DU3, DU4, DU5
THE CAC 1 AND 2 COMMUNICATE WITH FIVE DISPLAY UNITS AND SYSTEMS THROUGH
DIFFERENT DATA BUS FORMATS INCLUDING:
AFDX: AVIONICS FULL DUPLEX SWITCHED ETHERNET AND A429: ARINC 429
TWO OF THE FIVE DISPLAY UNITS (DUs) ARE DEDICATED TO TWO ADDITIONAL
APPLICATIONS – FMA AND RMA. THESE DUs ARE:
DU2 AND DU4
. IF THE CARGO DOOR CONTROL PANEL HAS BEEN OPENED WHICH SELF TEST WILL
COMMENCE:
MFC 1A + MFC 2A
ACMS FUNCTIONS ARE:
QAR/DAR REPORTING ON A PCMIA DISK
MANAGEMENT OF REPORTS
THE FLIGHT INSTRUMENTS SYSTEM INCLUDES:
5 x DUs, 2 x EFCPs, 2 x ICPs, 2 x MCDUs, 2 x MCPs AND 2 x SWITCHING PANELS
THE AUTOFLIGHT CONTROL SYSTEM (AFCS) IS MANAGED BY:
TWO AUTOFLIGHT CONTROL APPLICATIONS (AFCA) OF THE CACs
THE AFCAs RECEIVE DATA FROM:
A) 2 x ADC
B) 2 x AHRS
C) AIRCRAFT EQUIPMENT SUCH AS NAVIGATION EQUIPMENT AND SENSORS
EACH DU CAN DISPLAY DIFFERENT FORMATS:
A) PRIMARY FLIGHT DISPLAY (PFD)
B) MULTI FUNCTION DISPLAY (MFD)
C) THE ENGINE AND WARNING DISPLAY (EWD)
THE MFD SHOWS:
NAVIGATION DISPLAY, MEMO DISPLAY, VCP AND SYSTEM DISPLAY (SD)
THE NAVIGATION DISPLAY (ND) CAN BE SET UP IN:
ARC MODE, ROSE MODE + PLAN MODE
THE SYSTEM DISPLAY (SD) PAGE CAN SHOW:
CABIN PAGE, ELECTRICS PAGE, HYDRAULICS PAGE, ENGINE SECONDARY PAGE
THE EWD INCLUDES:
ENGINE PARAMETERS AND ALERT WINDOW
THE EWD INCLUDES:
FLIGHT CONTROLS, TRIMS, BRAKES, TEST STATUS AND PRIMARY ENGINE WINDOW
THE MULTI PURPOSE CONTROL (MCP) PANEL ALLOWS ACCESS TO:
A) COMM, NAV AND SURVEILLANCE PAGES
B) MULTI DIRECTIONAL PAD AND NUMERIC KEYBOARD
THE STANDBY INSTRUMENTS INCLUDE:
AN INTEGRATED ELECTRONIC STANDBY INSTRUMENT
THE WEATHER RADAR IS ACCESSED USING:
THE SURV PB
THE IESI ARCHITECTURE INCLUDES:
VOR ILS, VHF, AIRSPEED SCALE AND BAROMETRIC REFERENCE
THE SET SWITCH ON THE IESI ALLOWS:
A) COURSE ADJUSTMENT WHEN IN VOR MODE
B) VHF NAV TUNING
C) VHF COMM TUNING
THE CONTROL AND DISPLAY SYSTEM (CDS) ENABLES THE FLIGHT CREW TO ACCESS:
A) FLIGHT INFORMATION
B) AIRCRAFT ENVIRONMENT & AIRCRAFT SYSTEM STATUS
C) AIRCRAFT ALERTS, PROCEDURES, CHECKLISTS
CDS MANUAL REVERSION IS CONTROLLED BY:
TWO REVERSION PBS
ON THE GROUND AIRCRAFT POWERED BY BATTERIES WHICH DUs ARE RESPECTIVELY
CONFIGURED AS EWD AND SD ENGINE PAGE:
DU 2 & DU4
HOW MANY DUs ARE POWERED ON BATTERIES ONLY:
2
MANUAL FORMAT RECONFIGURATION IS CONTROLLED BY:
A) PFD/EWD/MFD PB ON THE CAPT SIDE
B) PFD/EWD/MFD PB ON THE F/O SIDE
ELAPSED TIME ON THE CLOCK CONTROLS THE FOLLOWING FUNCTION:
A) WHEN SELECTING THE ET PB THE ET DISPLAY COMES ON
B) WHEN THE ELAPSED TIME COUNTER IS STOPPED, BY STOPPING THE ET PB FOR MORE
THAN 2 SECONDS, THE DISPLAY IS BLANKED AND VALUE IS ZEROED
THE CHRONO PB CAN BE USED FOR THE FOLLOWING:
A) TO START THE CHRONOMETER
B) TO STOP THE CHRONOMETER
C) TO RESET THE LCD DISPLAY
THE AIRCRAFT IS EQUIPPED WITH WHICH OF THE FOLLOWING SOLID STATE RECORDERS:
A) COCKPIT VOICE RECORDER
B) FLIGHT DATA RECORDER
THE SOLID STATE VOICE RECORDER STARTS AUTOMATICALLY WHEN:
WHEN ONE ENGINE IS STARTED
THE EFIS CONTROL PANEL LOCATED ON THE CENTRAL PEDESTAL ENABLES CONTROL OF;
A) MFD
B) NAV
C) WARNING DISPLAY
HOW CAN THE PERFORMANCE PAGE BE DISPLAYED ON THE ND?
BY SELECTING “PERF” PB ON THE MFD
THE MULTI PURPOSE CONTROL PANEL (MCP) ENABLES:
A) COCKPIT CREW TO CONTROL THE VIRTUAL CONTROL PANEL FORMAT ON MFD
B) SELECTION OF THE TCAS
WHEN AUTO SPEED IS SELECTED ON THE ICP WHAT COLOUR DOES IT DISPLAY IN:
MAGENTA
THE FOLLOWING PUSH BUTTONS/SWITCHES ARE CIRCLED IN AMBER TO HELP THE FLIGHT
CREW FIND THEM IN CASE OF SMOKE (FLUORESCENT PAINTING)?
A) BTC, DC SVCE/UTLY BUS, ACW GEN 1/2
B) EXHAUST MODE, OVBD VALVE SELECTOR
C) RECIRC FAN ½
AN AMBER COLOUR IS USED FOR:
A) ICING CONDITION DATA
B) DETECTED MALFUNCTIONS
C) ABNORMAL RANGE DATA
A CYAN COLOUR IS ASSOCIATED WITH:
MANUAL OPERATION
A GREEN COLOUR IS DEDICATED TO:
AUTOMATIC NORMAL FUNCTIONING AND COMPUTED DATA IN THE NORMAL RANGE
FOR EACH INTERFACE E.G. CONTROL PANEL DISPLAY UNIT AND MCDU
A MAGENTA COLOUR IS USED TO DISPLAY:
B) ACTIVE SPEED CONSTRAINTS
C) ALTITUDE CONSTRAINTS
HOW ARE INVALID SIGNALS DISPLAYED?
AMBER CROSSES OR DASHES
What colour is the active or selected emergency procedure title
Red
A FAILURE DETECTION SEQUENCE FOLLOWS WHICH OF THE BELOW:
INFORMATION, IDENTIFICATION, ISOLATION
THE CLACKER SOUNDS AT:
VMO
THE WHOOLER SOUNDS WHEN THE PITCH TRIM IS IN MOTION FOR MORE THAN:
1 SECOND
WHAT AURAL ALERT IS USED FOR ALTITUDE?
C CHORD
THE ROLL ATTITUDE ON THE ALTITUDE DISPLAY INDICATOR (ADI) HAS THE FOLLOWING FIX
SCALE REFERENCE MARKS:
10, 20, 30, 45 & 60 DEGREES
THE HORIZON AND PITCH SCALE ON THE ALTITUDE DISPLAY INDICATOR (ADI) HAS THE
FOLLOWING REFERENCE MARKS:
2.5° UP OR DOWN TO 20°, THEN MARKS AT 25°, 30°, 50° & 80°
What colour are the flight director command bars
Green
WHAT IS THE TCAS RANGE WHEN SELECTED ABOVE:
-2700FT TO +9900FT
WHICH OF THE FOLLOWING DOES THE MEMO PANEL DISPLAY?
A) FUEL CROSS FEED CONTROL
B) ANTI-ICING CONTROL
C) DE-ICING CONTROL
WHAT IS THE COLOUR CODING FOR A SYSTEM THAT IS SELECTED OFF?
WHITE
WHEN THE TAKE-OFF INHIBIT IS SELECTED FOR TAKE-OFF WHAT ALERTS ARE INHIBITED:
ALL OIL AND SMOKE WARNINGS
WHAT IS THE ASSOCIATED AURAL ALERT FOR STALL?
CRICKET
WHAT IS THE ASSOCIATED AURAL ALERT FOR ENGINE FIRE?
CONTINUOUS REPETITIVE CHIME
WHAT DOES THE TAKE-OFF CONFIG NOT TEST?
BOTH ENGINES ARE RUNNING
ON THE ECL WHAT COLOUR CORRESPONDS TO ACTIONS TO BE PERFORMED OR CHOICES TO
BE MADE BY THE FLIGHT CREW:
CYAN
HOW LONG DOES THE “MAN DEL” PB BE PRESSED FOR IT TO FUNCTION?
3 seconds
HOW CAN THE TAKE-OFF INHIBIT BE CANCELLED?
MANUALLY DEACTIVATED BY PRESSING THE RCL PB
HOW LONG IS THE STICK PUSHER ACTIVATION INHIBITED AFTER TAKE-OFF?
10 SECONDS AFTER LIFT OFF
HOW ARE THE TWO ANGLE OF ATTACK CHANNELS TESTED?
MANUALLY TESTED ON THE LATERAL MAINTENANCE PANEL
THE MFD MEMO PANEL DISPLAYS THE FOLLOWING INFORMATION:
A) FUEL CROSS-FEED AND ANTI-ICING
B) DE-ICING CONTROL, CABIN SEATBELT, NO DEVICE MESSAGE STATUS
THE VCP PRESENTS THE FOLLOWING INFORMATION WHICH CAN BE MANAGED THROUGH
THE MCP:
VCP NAV, VCP COMM AND SURVEILLANCE PAGES
THE FWS IS COMPOSED OF THE FOLLOWING:
A) AN ALERTING WINDOW ON THE LEFT PART
B) A PROCEDURE WINDOW ON THE RIGHT PART AND A STATUS AREA DEDICATED TO THE
FWS INFORMATION ON THE BOTTOM PART OF THE PROCEDURAL WINDOW
WHAT COLOUR IS THE TAKE-OFF INHIBIT MESSAGE ON THE EWD?
GREEN
WHAT CAUTIONS ARE NOT INHIBITED FOR TAKE-OFF?
ENGINE OIL LO PRESS
WHAT COLOUR IS DISPLAYED FOR A TAKE-OFF CONFIG TEST “OK”?
CYAN
WHERE IS THE TAKE-OFF CONFIG TEST OK DISPLAYED ON THE EWD?
ON THE FLIGHT CONTROLS, TRIMS, BRAKE MESSAGE AND TEST STATUS
WHICH OF THE FOLLOWING IS CORRECT FOR A STICK PUSHER SHAKER YES TEST?
A) STALL CRICKET AND BOTH STICK SHAKERS ARE ACTIVATED
B) AFTER 5 SECONDS GPWS AMBER ALERT MESSAGE IS DISPLAYED ON THE EWD
C) AFTER 10 SECONDS CHANNEL 1, CHANNEL 2 ARE ILLUMINATED, STICK PUSHER IS
ACTIVATED AND STICK PUSHER INDICATION S ILLUMINATE GREEN
FOR THE FLIGHT WARNING MANAGEMENT IN ECL WHICH OF THE FOLLOWING IS NOT
CORRECT:
PRIORITY CHECKLIST IS BOXED
ON THE FLIGHT MANAGEMENT AND ECL NORMAL CHECKLISTS WHEN IS THE AFTER TAKE-
OFF CHECKLIST DISPLAYED?
AFTER TAKE-OFF ONCE AIRCRAFT IS AIRBORNE
