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Flashcards in ATR SYSTEMS Deck (19)
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1

MFC

MULTI FUNCTION COMPUTER
Two independent computers each include two independent modules.
Purpose= Monitor,control,authorise operation of the aircraft systems.
Manage system failures and flight envelope anomalies and command triggering of associated warnings.

2

CCAS

CENTRALIZED CREW ALERTING SYSTEM
Purpose= To draw crews attention when a failure is detected and guides the crew to the system affected by the failure.
THREE TYPES OF VISUAL DIVICES USED
-Master warning and master caution lights
-Crew alerting panel CAP
-Local alert lights

3

AFCS

AUTOMATIC FLIGHT CONTROL SYSTEM
Receives data from the two ADC,AHRS,SGU, the radio altimeter,the GNSS and some sensors. It generates commands to the flight control actuators/servos and to the FD bars.

4

ADU

ADVISORY DISPLAY UNIT
Displays; Advisories, selected modes, messages, armed modes and captured modes.

5

EFIS

ELECTRONIC FLIGHT INSTUMENT SYSTEM
Control panel to set nav, brg arc and map on the EHSI

6

EGPWS

ENHANCED GROUND PROXIMITY WARNING SYSTEM
Provides visual and aural alerts in case of dangerous flight path conditions which would result in inadvertent ground contact if maintained.
Alert modes;
1 EXCESSIVE DECENT RATE
2 EXCESSIVE TERRAIN CLOSURE RATE
3 ALTITUDE LOSS AFTER TAKE OFF
4 UNSAFE TERAIN CLEARENCE
5 BELOW GLIDESLOPE
6 ALTITUDE CALLOUTS
Enhanced modes:
TERRAIN CLEARANCE FLOOR TCF
TERRAIN AWARENESS & DISPLAY TAD

7

MCDU

MULTIFUNCTION CONTROL DISPLAY UNIT
Is the interface between pilot and HT1000.
It is used to enter, monitor and revise routes

8

NPU

NAVIGATION PROCESSOR UNIT
Receives and processes the GNS/FMS signal data from the GPS antenna and other aircraft systems i.e Air Data Computer to compute position and course info. It transmits data to the MCDU for display and to other aircraft systems such as autopilot, HSI and CDI.

9

AHRU

ATTITUDE AND HEADING REFERENCE UNIT
Includes an internal measurement unit composed of three gyro meters and three accelerometers. The AHRU receives inputs from its associated flux valve and the TAS, fed by both ADC, is used to compute gyro erection

10

ADC

AIR DATA COMPUTERS
Is supplied with static air pressure, total pressure (Pitot ports) total air temp (TAT probes). with these inputs the ADC computes pressure altitude,VS,IAS,TAS,TAT,SAT.

11

SGU

SYMBOLS GENERATOR UNIT
Collects data from AFCS,AHRU,ADC,VOR,ILS,DME,ADF, GNSS,CRS and HDG. Converts the data into video format for EADI,EHSI

12

TLU

TRAVEL LIMITING UNIT
Limits rudder travel is done through ADC 1/2 when reaching speed 185 kts when accelerating and disengaged when reaching 180 knots when decelerating.

13

TRU

TRANSFORMER RECTIFIER UNIT

14

HMU

HYDROMECHANICAL UNIT

15

BTC

BUS TIE CONTACTOR

16

ATPCS

AUTOMATIC TAKE OFF POWER CONTROL SYSTEM
It provides in case of an engine failure during take off the untrimmed take off power on the remaining engine combined with an automatic feathering on the failed engine.
Arming conditions:
PWR MGT SELECTOR TO
ATPCS PB ON
BOTH PL 49'
BOTH TORQUE ABOVE 46%
AIRCRAFT ON THE GROUND
= uptrim and auto feather
same conditions for in flight however there is no uptrim

17

ETOPS

EXTENDED TWIN OPERATIONS

18

PEC

PROPELLER ELECTRONIC CONTROL
Is a dual channel electronic box which provides closed loop control over the propeller pitch change system.The PEC detects, isolates and accommodates system faults.

19

TAWS

TERRAIN AWARENESS WARNING SYSTEM