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Auszüge/Beispielseiten aus dem Trainingsmaterial der A320-Familie • ATA 22 Autoflight • ATA 79 Oil • ATA 71 Power Plant • ATA 34 Navigation • Cockpit Panel Descriptions • Airbus Abbreviation List Das Trainingsmaterial ist so aufbereitet, dass es auf unterschiedlichen Endgeräten dargestellt und verteilt werden kann. Extracts/sample pages - training material of the A320-family • ATA 22 Autoflight • ATA 79 Oil • ATA 71 Power Plant • ATA 34 Navigation • Cockpit Panel Descriptions • Airbus Abbreviation List The training material is optimized and available for different mobile end devices.
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Page 402|--00|AFS Philosophy|L1
AUTO FLIGHTGENERAL
A318/A319/A320/A321
22--00
FRA US/T-5 PoL Dec 28, 2010
COMMAND
MONITOR
2
FLIGHTMANAGEMENT
FLIGHTGUIDANCE
FLIGHT CONTROL UNIT (FCU)
AUTOFLIGHT SYSTEM
ANALOGUE,DISCRETE& DIGITALA/C DATAINPUTS
(e.G. ADIRS)
MULTIPURPOSE CONTROL ANDDISPLAY UNIT (MCDU)
FADEC
FLIGHT CONTROLSYSTEM
FLIGHT AUGMENTATIONCOMPUTER (FAC)
COMMAND
MONITOR
1
2
FLIGHT MANAGEMENT &GUIDANCE COMPUTER (FMGC)
COMMAND
MONITOR
1
FLIGHTMANAGEMENT
FLIGHTGUIDANCE 1
2
SIDESTICK
F/O
CAPT
THRUST LEVERS
CAPT & F/O PFD/ND
DMC
FIDS
COMMAND
MONITOR
FIDSCFDIU
NOTACTIVE
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Figure 2 Auto Flight System Design Philosophy
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Page 215|--10|AP/FD|L2
AUTOFLIGHTAUTOPILOT/FLIGHT DIRECTOR (AP/FD)
A318/A319/A320/A321
22--10
FRA US/O-7 KnB Nov 07, 2012
10
12
34
56
78
9
TO FCU
MDCU 1,
MDCU 2
FCU
MDCU 2
MDCU 1
1 - ELEVATOR AILERON COMPUTER 12 - SPOILER AND ELEVATOR COMPUTER 13 - FLIGHT MANAGEMENT AND GUIDANCE COMPUTER 14 -- FLIGHT AUGMENTATION COMPUTER 15 -- FLIGHT AUGMENTATION COMPUTER 26 - FLIGHT MANAGEMENT AND GUIDANCE COMPUTER 27 - SPOILER AND ELEVATOR COMPUTER 28 - ELEVATOR AILERON COMPUTER 29 - SPOILER AND ELEVATOR COMPUTER 310 - BRAKE STEERING CONTROL UNIT
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Figure 1 AP/FD Layout & FLT CTRL Components
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Page 202|79--00|Sys|5A|L2/B1/B2
OILGENERAL
A319/A320/A321CFM56--5A
79--00
FRA US/T-5 KoA Mar 4, 2011
LufthansaTechnicalTraining
Figure 1 Oil System General
FORTRAININGPURPOSESONLY!
Page 204|71--00|CTRLS|5A|L1/B1/B2
POWER PLANTGENERAL
A319/A320/A321CFM56--5A
71--00
FRA US/T-5 KoA Mar 4, 2011
FAULT
ON
FAULT
ON
DISCH DISCH
DISCH
DISCH DISCH
LufthansaTechnicalTraining
Figure 1 Engine Controls Overview
FORTRAININGPURPOSESONLY!
Page 1616|--48|Modes|L2
NAVIGATIONGROUND PROXIMITY WARNING SYSTEM
A318/A319/A320/A321
34--48
FRA US/O-7 KnB Nov 20, 2012
PULL UPPULL UP
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MODETCF
Figure 8 Terrain Clearance Floor Mode
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Page 4 LufthansaTechnical Training
Cente
r P
edesta
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INTRODUCTION
COCKPIT PANEL DESCRIPTION A318/A319/A320/A321
FRA US/O-7 KnB Feb 16, 2012
CENTER PEDESTAL PANEL
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Page 11LufthansaTechnical Training
ATA
22
22
AUTOFLIGHT
COCKPIT PANEL DESCRIPTION A318/A319/A320/A321
FRA US/O-7 KnB Feb 16, 2012
ATA 22 AUTO FLIGHT
FLIGHT CONTROL UNIT (FCU) 13VU
SPEED/MACH CONTROL AREA
SPEED/MACH WINDOW
� Shows selected SPD or MACH in “selectedguidance“.
� Shows after PWR UP: SPD 100 −“−−−“ in„managed guidance“.
� Display range: between 100 and 399 KT for speed,between 0.10 and 0.99 for MACH number.
SPD/MACH SELECTOR KNOB
� Knob pushed:
Engaged SPD/MACH for „managed guidance“.
� Knob pulled:
Engaged SPD/MACH for „selected guidance“.
SPD/MACH P/B
Depressing this PB changes SPD target to thecorresponding MACH target and vice versa (automaticon FL 305).
MANAGED SPD/MACH DOT
LATERAL CONTROL AREA
HDG/TRK WINDOW
� shows selected HDG or TRK in „selectedguidance“.
� shows after PWR UP: −−− , −“−−−“ in „managedguidance“.
� Display range: between 0 −359 deg.
HDG TRK SELECTOR KNOB
� Knob pushed:
Arms/engages NAV for „managed guidance“.
� knob pulled:
Engages HDG or TRK in „selected guidance“.
LOC MODE ENGAGEMENT P/B
Arms, engages or disengages the LOC mode.
MANAGED LATERAL DOT
13VU
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Page 68 LufthansaTechnical Training
ATA
33
33
LIGHTS
COCKPIT PANEL DESCRIPTION A318/A319/A320/A321
FRA US/O-7 KnB Feb 16, 2012
ATA 33 LIGHTS
INT LIGHTS, EMER LIGHTS ON 25 VU
OVHD INTEG LT KNOB
This knob turns the integral lighting for the overheadpanel on and off and adjusts its brightness.
STBY COMPASS SWITCH
This switch turns the integral lighting for the standbycompass on and off.
DOME SWITCH
This switch controls both dome lights.
� BRT
Both dome lights on bright.
� DIM
Both dome lights on dim.
� OFF
Both dome lights off.
ANN LT SWITCH
This switch sets the brightness of all the cockpitannunciator lights at either “bright“ or “dim“, and alsotests them.
� TEST
Illuminates all flight deck annunciator lights. Puts8‘s up in all LCDs (Liquid Crystal Displays).
� DIM
Reduces voltage to all annunciator lights.
� BRT
Allows annunciators to function normally.
EMER EXIT LT SWITCH
The selector has three detent positions.
� ON
Overhead emergency lights, EXIT signs andproximity marking system come on.
� OFF
Above lights are off.
� ARM
The proximity emergency escape path markingsystem comes on when the normal aircraftelectrical power or DC SHED ESS BUS is lost.
The overhead emergency lights come on if:
− Normal aircraft electrical power system fails or
− DC SHED ESS BUS fails or
− AC BUS 1 fails.
Exit signs come on if:
− Normal aircraft electrical power system fails or
− DC SHED ESS BUS fails or
NOTE: The LIGHT EMER pushbutton on thepurser‘s panel can turn on theemergency lighting independently of thepositions of this selector switch.
EMER EXIT LT “OFF“ LT
This light comes on amber when the EMER EXIT LTselector is selected OFF.
OFF
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Page 93LufthansaTechnical Training
ATA
71−8
0
71−80
ENGINE
COCKPIT PANEL DESCRIPTION A318/A319/A320/A321
FRA US/T-2 KnB Sep 01, 2010
ATA 71 POWER PLANT (e.g. CFM-56)
ENG MASTER SWITCH 1 (2)
� ON
LP fuel valve opens (if the ENG FIRE pushbutton isin).
− During an automatic start, the HP fuel valveopens if:
� The ENG MODE selector is at IGN/START.
� The engine accelerates to the appropriatethreshold, which is function of T2 and thealtitude.
− During a manual start, the HP FUEL valveopens if:
� The ENG MODE selector is at IGN/START.
� The MAN START pushbutton switch is ON.
� OFF
Close signals go directly to the HP fuel valve andthe LP fuel valve. These signals cause bothchannels of the FADEC to be reset.
NOTE: Releasing the ENG FIRE pushbuttonallows flight crew to shut down theengine by closing the LP fuel valve.There is a time delay of about 60seconds at ground idle as the engineburns the fuel left between the LPvalve and the nozzles.
ENG MODE SELECTOR
� CRANK
The start valve opens, if the MAN STARTpushbutton switch is ON. Ignition is not active.
� NORM
This turns on continuous ignition (A and B) whenthe engine is running and:
− The engine anti−ice pushbutton switch is ON, or
− a flame−out is detected, or
− the approach idle is selected.
− The master lever has been cycled from ON toOFF, then back to the ON position, or
− a surge is detected, or
− in case of severe rain or hail.
� IGN START
If the MASTER switch is ON and N2 . idle, thisposition selects continuous ignition (A and B).
− During an automatic start:
� On the ground, when N2 passes 16 %,ignition switches to A or B. However, if thereis an ignition delay during the start sequence,ignition is continuous (A and B).
� In flight, continuous ignition (A and B) beginswhen the start sequence begins.
− During a manual start, ignition commenceswhen the MASTER switch is turned ON.
NOTE: On the ground, the ignition isswitched off automatically at the endof the start sequence.
(N2 between 47 % and 53 %).
FIRE
FAULT
FIRE
FAULT
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ACR Avionics Communication Router ACRIF ACR Instrumentation Function ACRT Additional Cross Reference Table ACS Access ACS Air Conditioning System ACS Alternating Current Supply ACSC Air Conditioning System Controller ACT Active ACT Activity ACT Additional Center Tank ACTD Actuated ACTG Actuating ACTIV Active ACTN Action ACTR Actuator ACTVN Activation ACTVT Activate ACU Air Cooling Unit ACU Antenna Control Unit ACU Antenna Coupler Unit ACUTE AIRBUS Cockpit Universal Thrust Emulator ACVR Alternating Current Voltage Ratio AD Aerodrome AD Airplane Datum AD Airworthiness Directive A-D Airbus Deutschland ADAM Airbus Spares Distribution and
Materials System ADAU Auxiliary Data Acquisition Unit ADB Aeronautical Data Base ADB Airport Data Base ADB Area Distribution Box ADC Additional Control Device ADC Air Data Computer ADC Airbus Delivery Centre ADCL Airworthiness Directives Compliance List ADCN Avionics Data Communication Network
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P
P Purple P Roll Rate P Pressure
P(±OFF) Polarity (plus, minus, off) P.ALT Profile Altitude P.CLB Profile Climb P.DES Profile Descent P.EPR Profile EPR P.MACH Profile Mach P.N1 Profile N1 P.SPD Profile Speed P/B Pushbutton P/BSW Pushbutton Switch P/C Printed Circuit P/L Payload P/N Part Number P/P ROM Preprocessor ROM Pa Pascal PA Passenger Address PA Public Address PA AMP Passenger Address Amplifier PAD Partner Agreement Document PADS Pneumatic Air Distribution System PAL Programmable Array Logic PAMB Ambient Pressure PAR Precision Approach Radar PARAM Parameter PARK Parking PAS Pitch Attitude Sensor PATCC Production Aircraft Test Completion
Certificate PATM Production Aircraft Test Manual PATS Passenger Air-to-Ground Telephone System PAX PAX Announcement Entertainment and
Service Multiplex System