A320 Review Book

A319, AA320, AA321Oral SSystem RReview©

trs-digital-presentation™www.digital-presentation.net

(480) 497-4114(602) 534-8676 (cell)

320 E. Barbarita Ave.Gilbert, AZ 85234

legal statement . . . . . . . . . . . . . . .p 2review book . . . . . . . . . . . .p’s 3 - 128index . . . . . . . . . . . . . . . p’s 129 - 132other products . . . . . . . . . . .133 - 134

trs-digital-presentationA319, A320, A321 System Review©

TM

Aug 2004page 2

COPYRIGHT NOTICECopyright 2004 Tom Sceurman d/b/a trs-digital-presentation™. All rights reserved.Permission to use, duplicate or copy and distribute this document and/or any includ-ed text or graphics or Compact Disc content contained in this publication is forbid-den without the express written permission of the author.

TRADEMARKStrs-digital-presentation and digitial-presentation.net are trademarks owned by TomSceurman. All rights reserved.

DISCLAIMERThis guide is for familiarization purposes ONLY. This guide is not approvedby the aircraft manufacturer or the FAA/CAA/JAA or Transport Canada and doesnot supercede, replace, or overrule the aircraft manufacturer's AOM or FCOM.Tom Sceurman d/b/a trs-digital-presentation™ makes NO WARRANTY or REPRE-SENTATIONS about the suitability of the information contained in the documents orattached Compact Discs and related graphics/text published in this guide.

All such documents and related graphics are provided "AS IS" without warranty ofany kind. Tom Sceurman d/b/a trs-digital-presentation™ hereby disclaims all war-ranties and conditions with regard to this information including all implied warrantiesand conditions of merchantability, fitness for a particular purpose and non- infringe-ment. In no event shall Tom Sceurman d/b/a trs-digital-presentation™ be liable forany special, indirect or consequential damages or any damages what so ever result-ing from loss of use, data or profits, whether in an action of contract, negligence orother tortious action, arising out of or in connection with the use or performance orinformation available from this Documents contents.

The documents and related graphics published in this guide could include technicalinaccuracies or typographical errors. Changes are periodically added to the informa-tion herein. Tom Sceurman d/b/a trs-digital-presentation™ may make improvementsand/or changes in the document(s) and/or the CD program(s) described herein atany time.

Overhead CB, Reading Lt. & Door Control Panel

FIRST OFFICER’S RESPONSIBILITIESFIRST OFFICER’S RESPONSIBILITIES


TM

Aug 2004 page 3

TOILETOCCPD (green)- forward lav occupied.

READING LT- for each pilot with OFF to BRT selection.

OVHD DOOR CONTROL PANELSTRIKES’ status lightsOFF: upper, mid or lower locking latch is operative.ON: upper, mid or lower locking latch is faulty.Pressure sensor status lightsOFF: corresponding (1 or 2) press sensor is operative.ON: corresponding (1 or 2) press sensor is faulty.Pressure sensors- two redundant differential pressure sensors enable

rapid pressure variation in the cockpit to be detected,in order to command simultaneous opening of alllatches when a defined pressure drop is detected.

NOTE: these indications allow crew to identify faultwhen Ctr Ped FAULT indicator is illuminated.

OCCPD

Audio Switching & OVHD Panel

AUDIO SWITCHING SELECTORNORMAL- each crewmember uses its dedicated communication

equipment.CAPT 3- Capt uses its acoustic equipment and the 3rd occupant

ACP.F/O 3- F/O uses its acoustic equipment and the 3rd occupant

ACP.

CVR HEADSET JACK

OXYGEN TMR RESET PB SWITCHON- PASSENGER SYS ON light goes off and tape

announcement stops,- TMR RESET ON light comes on.FAULT- Illuminates when the door latch solenoids are ene-

gized for more than 30 seconds.

SVCE INT OVRD PB SWITCHAUTO- communication via service interphone jacks is pos-sible when on the ground,10 seconds after landing,

- inoperative when the landing gear is not com-pressed.

ON- communication is possible with the landing gear

not compressed.

AVIONICS COMPT LT PB SWITCHAUTO- avionics compartment lighting is automatically con-

trolled by door opening.ON- avionics compartment lighting is on.

LEAK MEASUREMENT VALVESBLUE & YELLOW OFF- respective electohydraulic valve closes and

hydraulic supply to pri-flight controls is shut off.GREEN VALVE- PB not active,- valve always open.

FADEC GND PWR PB SWITCHON- FADEC is electrically supplied on the ground.

RESET PBPUSH- test circuit is reset.TEST PB SWITCH(pb sw must be held - MASTER sw mustbeON)- APU FIRE warning auto extinguishing and

shutdown circuits are tested (ten sec dura-tion).

- OK light on to indicates test successful.BLUE PUMP OVRD PB SWITCHON- blue electric pump is energized provided

the ELEC PUMP pb switch on HYD panelis at AUTO position.


TM

Aug 2004page 4


TM

Aug 2004 page 5

Pilot’s Overhead Panel

CAPTCAPTAIN’S RESPONSIBILITIESAIN’S RESPONSIBILITIES



TM

page 6 Aug 2004

ADIRS

DISPLAY WINDOWS- display the data selected by the DATA

selector,- keyboard entry will override the selected

display.

DATA SELECTORWIND- true wind direction and wind speed are

displayed.P POS- present latitude and longitude are

displayed.HDG- true heading and the minutes remaininguntil alignment is completed are displayed

STS- action code is displayed.TK/GS- true track & ground speed are displayedTEST- lights (ENT and CLR) and all 8’s are

displayed in the windows.

ON BAT LIGHTILLUMINATED- a few seconds during initial alignment

(but) not during a fast alignment,- when one or more ADIRUs is supplied by

aircraft battery power only.

IR 1 (2) (3)FAULT LIGHT- steady: fault affects respective IR,- flashing if: Heading and Attitude are

usable.ALIGN LIGHT- steady: IR in align mode,- flashing if: IR alignment fault, or no pres-

ent position entry after 10 min, or differ-ence between position at shutdown andentered position exceeds 1° of latitudeor longitude.

- extinguished if:alignment is complete.

IR MODE ROTARY SELECTOROFF- ADR and IR data not available.NAV- provides full inertial data to aircraft sys.ATT- IR providing only attitude and heading

information.

ADR 1 (2) (3) SWITCHOFF- air data output disconnected.FAULT- accompanied by ECAM activation if a

fault is detected in the air data reference.

SYS SELOFF- CDU display is not energized,- ADIRS are still energized provided asso-

ciated IR mode selectors are not at OFF.1,2,3- system selected for data display.

KEYBOARD- allows present position, or HDG in ATT mode, to

be entered in the selected system.ALPHA KEYS- N, S, E & W for position entry,- H for heading entry (ATT mode).NUMERIC KEYS- permits manual entry of present position (or pres-

ent magnet heading in ATT mode).CLR KEY- the integral cue light illuminates following an entry

operation if the dat is of an unreasonable value,- when depressed the data display of data keyed-in

(but not yet entered) is cleared.ENT KEY- the integral cue light illuminates when N, S, W & E

or H entry has been keyed,- when depressed the data keyed is entered into the

ADIRS.


TM

page 7Aug 2004

FLT CTL (left side) & EVAC Panel

(as installed)COMMAND PB SWITCHEVAC LIGHT ILLUMINATED- flashes RED when alert is activated.ON: on the flight deck- EVAC light flashes RED,- specific horn is triggered.

in the cabin- EVAC lights flash at fwd & aft attendant

panels,- specific EVAC tone sounds,- PINK light comes on and «EVAC ALERT»

message is displayed on AIPs,- PINK lights flash at all attendant panels.OFF- alert stops.

CAPT & PURS/CAPT SWITCHCAPT & PURS- alert may be activated from either flight deck or

cabin.CAPT- alert may be activated from flight deck only.

HORN SHUT OFF PB SWITCHPUSH

- flight deck horn is silenced.

SEC PB SWITCH- Control of the spoiler & elevator computer.- Three SECs are identical, but are used differ-

ently depending on their positions 1, 2 or 3.ON (following functions provided to both)- roll normal (spoilers control)- speed brakes/Grnd spoilers (SEC 1 & 3 only)- pitch alternate (SEC 1 & 2 only),- roll direct (SEC 1 and 2 only)- roll direct,- LAF alternate- abnormal attitudeOFF- computer not active,- selecting OFF then ON resets computers.FAULT (with ECAM Caution)- fault detected,- FAULT light out when selected OFF

ELAC 1 (2) PB SWITCH- Control of the elevator & aileron computers.ON (following functions provided to both)- pitch, roll,- pitch,- pitch & roll direct,- abnormal attitude,- aileron droop,- A/P orders acquisition.OFF- corresponding computer is not active,- selecting OFF then ON resets computer.FAULT (with ECAM Caution)- failure detected,- during ELAC power up test (8 sec. duration),- light off when OFF selected, or at the end of

ELAC power up test provided test is satisfac-tory.

FAC PB SWITCH- Control of Flight Augmentation ComputersON- roll normal (Turn coordination & dutch roll damping)- rudder trim,- rudder travel unit,- yaw alternate.OFF- computer not active,- selecting OFF then ON resets computers.FAULT (with ECAM Caution)- fault detected,- FAULT light out when selected OFF


TM

Aug 2004page 8

EMER ELEC PWR Panel

EMER GEN TEST PG (guarded)PUSH AND HELD• if AC NORMAL BUSSES are supplied:- CSM/G is hydraulically powered, provided

blue electric pump is running.- AC ESS BUS and the DC ESS BUS are con-

nected to the emergency generator (the DCSHED ESS and AC ESS SHED busses arenot powered),

- ELEC page is automatically displayed onECAM (only on ground)

• if BAT only supplies the airplane:-AC ESS BUS is powered by the static inverter.

SMOKE LIGHTILLUMINATED- associated with ECAM warning when smoke

is detected in the anionic ventilation duct.

MAN 0N PB (guarded)AUTO when all the following

conditions are met:- AC BUS 1 not electrically supplied- AC BUS 2 not electrically supplied- airplane speed above 100 kts.

- RAT extends,- with gear up, CSM/G is hydrauli-cally powered by the blue system,

- when emergency generator withintolerances, emergency generatoris connected to the airplane net-work.

PUSH- RAT manually extended,- emergency generator coupling occurs if the

gear is up.

GEN 1 LINE PB SWITCHPUSH- GEN 1 line contactor opens- AC BUS 1 channel is supplied from GEN 2 through

bus tie contractors.

FAULT LIGHTILLUMINATED - if the emergency generator is notsupplying power when:- AC BUS 1 and AC BUS 2 are not powered, and- nose landing gear is up.


TM

Aug 2004 page 9

LDG FLAP 3ON- warning mode 4 is inhibited for flaps at

position 3,- NOTE: LDG MEMO displays

FLAPS ... 3 instead of “CONF... FULL”

FLAP MODE PB SWITCHOFF- Mode 4 warning (TOO LOW FLAPS) is

inhibited. (To avoid nuisance warning in caseof landing with reduced flaps setting.)

G/S MODE PB SWITCHOFF- Glide Slope Mode (Mode 5) Warning is

inhibited.

TERR PB SWITCHOFF- inhibits the Terrain Awareness Display (TAD)

and Terrain Clearance Floor (TCF) modes,and does not affect the basic GPWSmode 1 to 5.

FAULT- illuminated along with ECAM caution, if the

TAD or TCF mode fails,- basic GPWS mode 1 to mode 5 are still

operative if the SYS pb switch lights OFF orFAULT are not illuminated.

SYS PB SWITCHOFF- all basic warning are inhibited.FAULT- indicates a malfunction of the GPWS is

detected,- ECAM activated.

GPWS Panel


TM

Aug 2004page 10

GND CTL SWITCHON- the CVR and DRDR are energized.AUTO- the CVR and DFDR are energized according

to the logic.

CVR ERASE PBPUSH (two seconds)- complete erasure of the tape if:

• on ground,• parking brake is ON.

CVR TEST PBPUSH (and hold)- test is activated provided CVR is energized

(by pressing the GND CTL pb switch orduring the first five minutes following energiz-tion of AC electrical network) and parkingbrake is ON.

- low frequency signal is heard on the flightdeck loudspeakers,

- after test activation the CVR is de-energizedby pressing again the GND CTL pb switch.

MASK MAN ON PB (guarded in AUTO)AUTO- oxygen generator/mask PSU doors open

automatically when cabin altitude exceeds14,000 ft. (+0, –500).

DEPRESSED- oxygen generator/mask PSU doors open.

SYS ON- indicates when system is activated.

CREW SUPPLY PB SWITCHON- supply valve is open, low pressure oxygen is

supplied to the masks.OFF- the valve is closed.

CVR, OXYGEN Panel


TM

Aug 2004 page 11

ECAM DOOR/OXY Display

OXY Indication- normally green - becomes amber when:

• pressure goes below 400 psi,• low oxygen pressure is detected,• the OXYGEN CREW SUPPLY pb switch on overhead panel is OFF.

OXY High Pressure IndicationGREEN

- when pressure is ≥ 400 psi.AMBER

- when pressure is < 400 psi.- an amber half frame appears when oxygen pressure is < 1500 psi. In this case the

flight crew must check that the remaining quantity is not below the minimum (referto Operating Limitations).

REGUL LO PR Indication- appears amber if oxygen pressure on the low-pressure circuit is low (50 psi).

DOOR Symbol (includes avionics, cargo, pax doors & overwing exits)GREEN

- door is closed and locked.AMBER

- door is not locked.

DOOR Indication- appears amber when a door is not locked.

SLIDE Indication- appears white when slide is armed.

1

2

3

4

5

6

1

2

3

4

5

6


TM

Aug 2004page 12

Intentionally left blank


TM

Aug 2004 page 13

EMER PB SWITCHON- all PINK lights at all attendant stations flash,- «EMERGENCY CALL» msg appears at the

Attendant Indication Panels,- 3 HI/LO chime at all loudspeakers

CALL LIGHT- flashes with buzzer when an emergency call

is performed from cabin to flight deck.

FWD/AFT PBPRESSED- a RED and a GREEN light illuminate at the

fwd/aft attendant panel- «CAPTAIN CALL» msg appears at Attendant

Indication Panels,- HI/LO chime sounds at fwd/aft attendant

loudspeaker.

MECH PBPRESSED (and held)- COCKPIT CALL light on the nose L/G panel

illuminates BLUE,- external mechanical call horn sounds.

RELEASED- COCKPIT CALL light remains illuminated

until pressing RESET on interphone panel,- external horn stops.

WIPER ROTARY SELECTOR- controls Capt’s wiper to either low or high

speed- when selected off the wiper (parks) out of

view.

RAIN REPELLENT- DEACTIVATED

Max Speed for wiper operations: 230 kts

CALLS & WIPER Panel


TM

Aug 2004page 14

AGENT 1 (2) (active when correspondingENG FIRE pb is pushed)PUSH- bottle is discharged.SQUIB LIGHTs- illuminate when corresponding ENG FIRE pbis pushed to facilitate identification of the agentpb to be activated.

DISCH LIGHTs- illuminate when the related fire extinguisher

bottle is depressurized.

ENG 1 (2) FIRE PBNORMAL POSITION- in and guarded.RELEASED (out)- aural warning cancelled,- squib armed,- fuel LP valve closed,- ENG fuel return valve closed,- hydraulic fire valve closed,- bleed valve closed,- pack flow control valve closed,- elec IDG deactivated.ENG 1 (2) FIRE LIGHT- illuminates independently of pb position as

long as fire warning active..

APU FIRE PBNORMAL POSITION- in and guarded.RELEASED (out)- APU automatic shutdown,- aural warning cancelled,- squib armed,- APU fuel LP valve closed,- APU fuel pump off,- APU bleed & x bleed valves closed,- APU GEN deactivated.

APU TEST PB (tests detection & protectionsys)- continuous repetitive chime,- MASTER WARN light flashes,- ECAM APU FIRE warning active,- APU FIRE pb illuminates,- SQUIB lights illuminate,- DISCH lights illuminate,

NOTE: Automatic shutdown on ground does notoccur during test.

ENG 1 or 2 & APU FIRE Panel

TEST PB (tests detection & protection sys)PRESSED- continuous repetitive chime,- MASTER WARN light flashes,- ECAM ENG FIRE warning active,- ENG FIRE pb illuminates,- SQUIB lights illuminate,- DISCH lights illuminate,- ENG FIRE lights on pedestal ON.

AGENT 1 (2) (active when corresponding ENGFIRE pb is pushed)PUSH- bottle is discharged.SQUIB LIGHTs- illuminate when corresponding ENG FIRE pb is

pushed to facilitate identification of the agent pbto be activated.

DISCH LIGHTs- illuminate when the related fire extinguisher

bottle is depressurized.

ENG 2 same as ENG 1


TM

Aug 2004 page 15

Engine Fire Schematic & APU EXT FIRE Panel

APU FIRE LT- illuminates with warning horn

when fire detected.- APU extinguisher auto discharges within

three seconds of fire detection.- light out when fire extinguished.

APU (FIRE) SHUTOFF pb- if selected, shuts down APU and

silences horn.


TM

Aug 2004page 16

ENG 1 (2) PUMP PB SWITCHESON- pump pressurizes system when engine running.

OFF- pump depressurized.FAULT LIGHT- reservoir low level,- reservoir overheat, (light on as long as overheat

is present),- reservoir low air pressure,- pump low press (inhibited on ground when

engine stopped).

RAT MAN ON PB (guarded)PRESS- RAT extended.

NOTE: RAT automatically extended in case of totalelectrical failure.

BLUE ELEC PUMP PB SWITCHAUTO- electric pump is energized provided AC power

available:• in flight,• on ground provided one

engine is running or theBLUE PUMP OVRD pb hasbeen pressed.

FAULT (with ECAM Caution)- reservoir low level,- reservoir low air press,- reservoir overheat (light remains on

as long as overheat is present),- pump low pressure,- pump overheat

PTU PB SWITCHAUTO- bidirectional PTU unit armed,- both yellow & green electro-

hydraulic valves are open,- runs automatically when the

differential pressure betweengreen & yellow sys is more than 500 psi,

- PTU inhibited during first eng.start, & auto tested during thesecond eng. start.

OFF- both green & yellow PTU electro-

hydraulic valves close,- transfer stops.FAULT LIGHT (with ECAM caution)- green or yellow reservoir overheat,

(light on as long as overheat ispresent),

- green or yellow reservoir low airpressure,

- green or yellow reservoir low level.

YELLOW ELEC PUMP PB SWITCHON- electric pump is energized. (If theelectric power supply is removed thepump will remain de-energized at thenext electrical power application.)OFF- pump is de-energized. (It is automati-cally energized when the lever of thecargo door manual selector valve is setto the OPEN or CLOSED position.FAULT (with ECAM Caution)- reservoir low level,- reservoir low air press,- reservoir overheat (light remains on

as long as overheat is present),- pump low pressure,- pump overheat.

HYDRAULIC Panel


TM

Aug 2004 page 17

Hydraulic Schematic


TM

Aug 2004page 18

HYD ECAM Display

RESERVOIR Quantity- indicates green with normal fluid level.- indicates amber when fluid level is below warning level.

Reservoir LO AIR PRESS- appears amber if air pressure drops below normal, and a caution appears on ECAM.

Reservoir OVHT- appears amber if temperature of return fluid is above normal, and a caution appears on

ECAM.FIRE VALVE

- Cross Line Amber: valve fully closed- In Line Green: valve fully open.

OVHT (amber)- electric pump for r blue or yellow system reaches an overheat condition.

RAT- WHITE: RAT stowed.- GREEN: RAT extended.- AMBER: pressure for stowing RAT has been applied, or RAT pump is not available.

ELEC- normally indicates white.- indicates amber if associated power supply fails.

YELLOW ELEC PUMP Control- WHITE: Electric Pump OFF- GREEN: Electric Pump ON- AMBER: Electric Pump ON and yellow system pressure is low.

1

1

2

2

3

3

4

4

5

5

6

7

7

8

8

6

LO AIRPRESS

OVHT

PTU Control

GREEN: PTU pb in AUTO and PTU not transferring pressure.AMBER: PTU pb is OFF

GREEN: PTU is supplying the green hydraulic system.

GREEN: PTU is supplying the yellow hydraulic system.

ENG PUMP Control & Low Pressure Indication- In line (Green): the pb for designated PUMP is ON - Press normal- Cross line (Amber): the pb for designated PUMP is OFF- “LO” (Amber): the pb for designated PUMP is ON - Press low

System Label

System Pressure- normally green- becomes amber when pressure is below 1450 psi.

PUMP- normally white.- becomes amber when N2 below idle.

1

2

3


TM

Aug 2004 page 19

HYD ECAM Display (cont)

9

9

10

11

11

12

13

13

12

10

1

23

pressure > 1450 psi pressure < 1450 psi

YELLOW white amber

white amber

LO


TM

Oct 2004page 20

L & R TK PUMPS PB SWITCHESON- pump is energized, but fuel feeds only

when CTR TK PUMPS delivery pressuredrops below threshold.

OFF- pump deactivated.FAULT LIGHT (with ECAM Caution)- low pressure,- inhibited when OFF selected.

CTR TK PUMPS 1 (2) PB SWITCHESON- pump runs if MAN mode is selected on MODE

SEL pb switch,- pump is automatically controlled when

AUTO mode is selected.OFF- pump is deactivated.FAULT (with ECAM Caution)- pump is on with pressure low.

MODE SEL PB SWITCHAUTO- center tank pumps control is automatic,- on with engine start (for 2 min.),- before or after engine start sequence pumps run

provided slats are up.- automatically switched off 5 min. after center tank

low level is reached.MAN- center tank pumps are manually controlled with

CTR TK pb sws.FAULT (with ECAM Caution)- pump is on with pressure low.

X FEED PB SWITCHOFF- valve closed,- no light.ON- valve open,- ON light illuminated.OPEN LIGHT- illuminated when valve is fully open.

ACT PB SWITCH (A321 only) *Control of ACT transfer is automatic:- the automatic forward transfer occurs if:

• aircraft is in flight• slat are retracted• at least one ACT low level sensor is wet, and• center tank high level sensor has been dry for

at least 10 minutes- automatic forward transfer stops as soon as one

of the above conditions is not met.FWD LIGHT- manual tansfer to the center tank is initiated by

opening• ACT transfer valve, and• ACT 1 or 2 inlet valve

- the ACT transfer is then commanded on.FAULT LIGHT (with ECAM Caution)• center tank has less than 6614 lbs and one ACT

has more than 550 lbs, and• the ACT pb is in AUTO

FUEL LIMITATIONS:Minimum fuel quantity for takeoff: 7000lbs.Max imbalance inner tanks: 3300 lbs.Max imbalance outer tanks: 1100 lbs.

FUEL Panel* A321 Fuel Panel


TM

Aug 2004 page 21

Fu

el S

chem

atic


TM

Aug 2004page 22

Fuel Tanks, Quantities & ECAM Display

USABLE FUEL

VOLUME

WEIGHT *

OUTER TANKS INNER TANKS CENTER TANK TOTAL

(liters) 880 x 2 6924 x 2 8250 23858

(US Gallons) 232 x2 1829 x 2 2180 6302

(KG) 691 x 2 5435 x 2 6476 18728

(LB) 1520 x 2 11982 x 2 14282 41285

* Fuel density: 0.785 kg/1 or 6.5551 lb/US Gal.

MEMO indications (green)- examples shown

TOTAL Fuel Indication

Fuel Temperature Indication- normally green- temp above high limit or below low limitdisplays an ECAM caution

Fuel Used indication- eng id # amber when eng below idle- eng id # white when eng at or above idle- ind green flt phase 2 until elec pwr cut off

CTR TK FEEDFUEL X FEEDOUTER TK FUEL XFRD

REFUEL


TM

Aug 2004 page 23

FUEL ECAM Display (cont)

Wing Pump IndicationsIn Line - GREEN: pump pressure is normal (pump contactor on).“LO” - AMBER: pump pressure is low (pump contactor on).Cross LIne - AMBER: pump contactor is off.CTR Tank Pumps indicationsIn LIne - GREEN: pump pressure is normal (pump contactor on)“LO” - AMBER: pump pressure is low (pump contactor on).Cross Line - GREEN: pump contactor is off and auto shut off is required.Cross LIne - AMBER: pump contactor is off and auto shut off is not required.LP valve (eng-apu) indicationsIn LIne - GREEN: valve is openIn Line - AMBER: valve is open with ENG (APU) MASTER sw OFF or FIRE pb out.Cross LIne - GREEN: APU valve is closed.Cross Line - AMBER: ENG valve is closed or APU valve is closed with master sw. on.Transit - AMBER: valve is in transit.X Feed indicationsIn LIne - GREEN: valve is openIn Line - AMBER: valve is open with pb sw off.Cross LIne - GREEN: valve is closed with pb sw onCross Line - AMBER: valve is closed with pb sw. on.Transit - AMBER: valve is in transit.Transfer valves indications

closed transit open low level openFuel Quantity indication

- GREEN normal indication- AMBER line across last two digits when FQI is inaccurate.- outer indication is boxed AMBER if both ctr tank pumps fail to open when inner low- ctr tank is boxed AMBER if both ctr tank pumps fail or ares selected OFF.- advisory in flt phases 2 & 6, when difference in two wings is > 1500kg (3300lb)- indications of the wing inner and outer tanks with the highest fuel level pulses.

Fuel on board (FOB) indication (green - normal)- amber line across last two digits when FQI inaccurate- boxed AMBER ctr tank pumps failed or switched OFF/xfr valves failed to open when inner cell low.

1

1

2

2

3

3

4

4

5

5

6

6

7

7


TM

Aug 2004page 24

BAT 1 (2) INDICATOR- shows battery voltage.GALLEY PB SWITCHAUTO- main & secondary galleys are

powered,- main galley shed:

• in flight if only one gen operating• on grd if only one gen operating

(all galleys are avail. when APUGEN or EXT PWR is on).

OFF- main & secondary galleys are off.FAULT (with ECAM activation)- load of any GEN above 100% of

rated output.

COMMERCIAL pb sw as installedON- all aircraft commercial electrical

loads are supplied:• cabin & cargo lights• water & toilet system• drainb mast ice protection• galley• passengers entertainment• semi-auto cargo loading (if

Installed)OFF- switches off all aircraft

commercial electrical loads

ELECTRICAL Panel

BAT 1 (2) PB SWITCH (controls Batt Charge Limit.)AUTO- battery charge limiter auto.controls the connection/ disconnection of corresponding battery to the DC BATBUS (3 PP) by closing/opening of the battery line con-tactor.

- battery is connected to the DC BAT BUS in the follow-ing cases:• APU starting (Master Sw at ON and N< 95%) The

connection is limited to 3min when the Emer-Gen isrunning.

• batt voltage below 26.5. On the grd - immediatelyin flight, after a time delay of 30 min.

• loss of AC BUS 1 * 2 when below 100 kt (EMERGEN not operating). The batteries are connected tothe DC ESS BUS provided

- airplane speed lower than 50 kt, and- AC BUS 1 & 2 are not supplied.

NOTE 1: In normal config. the batteries are discon-nected most of the time.NOTE 2: A battery’s auto cut off logic prevents batter-ies from complete discharge when on grd (parking)Auto battery contactors opening occurs when:

• airplane is on ground,• BAT pb sw are at auto,• main power supply (EXT PWR + GEN) is

cut off,• batt voltage is lower than 23V for >16 sec.

NOTE 3: Reset is achieved by switching BAT pb sw atOFF then AutoOFF- battery line contactor is open,- battery charge limiter is not operating.OFF LIGHT- illuminates provided the DC bat bus is supplied,- hot busses remain powered.FAULT LIGHT (with ECAM Caution)- illuminated if battery is being charged at an abnormal

rate. (Battery contactor opens).


TM

Aug 2004 page 25

AC ESS FEED PB SWITCHNORMAL- AC ESS BUS is powered from AC BUS 1.ALTN- AC ESS BUS is powered from AC BUS 2.FAULT LIGHT (with ECAM activation)- illuminated when the AC ESS BUS is not powered.NOTE: with total loss of main GENS, the AC ESS BUS is auto-matically powered by the emergency generator or by the staticinverter if the emergency generator is not available.

ELECTRICAL Panel (cont)

IDG 1 (2) PB SWITCH (guarded)CAUTION: 1) if pb is held longerthan 3 sec, damagemay occur to disconnect mecha-nism.

2) do not disconnect the IDG wheneng. not running.

PRESS- IDG is disconnected,- can only be reconnected by maint.FAULT LIGHT (with ECAM Caution)- IDG oil outlet temp above 185°C,- IDG oil press is low. (Inhibited with N2

below 14%).

GEN 1 (2) PB SWITCHON- GEN field energized,- line contactor closed (provided elec. parameters

are normal).OFF- GEN field open,- line contactor open,- fault circuit reset.FAULT LIGHT (with ECAM Caution)- indicates protection trip initiated by associated

GCU.NOTE: if the protection trip is initiated by a differ-ential fault the reset action has no affect after twoattempts.- line contactor open (except if GEN pb s

selected OFF).

EXT PWR PB (momentary action)AVAIL LIGHT- external power plugged in,- external power parameters are normal.PRESS- ext pwr contactor closes,- AVAIL light goes out,- ON light illuminates,

If the ON light was illuminated:- ext pwr contactor opens,- ON light extinguishes,- AVAIL light illuminates

NOTE: external power has priority overthe APU GEN. ENG GENs have priorityover EXT PWR and the APU GEN. ONlight remains on even when the ENGGENs supply the airplane.

BUS TIE PB SWITCHAUTO- BTCs open or closes automatically in order to main-tain power supply to both AC BUS 1 and 2.

• one contactor is closed when:- one ENG GEN supplies the assoc. AC BUS bar

and,- APU GEN or EXT PWR supplies the other side.

• both contactors are closed in case of one engine,or APU GEN, or EXT PWR supply.

OFF- both bus tie contactors open.

Electrical Schematic


TM

Aug 2004page 26


TM

Aug 2004 page 27

ECAM ELEC Display

1

BATTERY Indications- BAT pushbutton switch at OFF, legend is in white (OFF replaces volts & amps),- BAT pushbutton switch at AUTO, legend is white “BAT 1 or 2” but becomes amber

when:• voltage and current indications changes to amber or,• in case of a BAT FAULT warning.

- BAT voltage is normally green - but becomes amber if V > 31 V or V < 25 V.- BAT amps normally green - but become amber if discharge current > 5 A.

BATTERY Charge/Discharge Indication- battery contactor closed. Battery charging current > 1A (green)- battery contactor closed. Battery discharge current > 1A (amber)- battery contactor closed. Current < 1A- (as shown) battery contactor open.

DC BAT Indication- legend normally green - becomes amber if DC BAT voltage ≤ 25 V.

BUS Indication- label normally green - becomes amber when corresponding bus is off,- SHED appears in amber when AC or DC SHED ESS BUS is off.

TR 1 (2) Indication- legend “TR 1 or 2” normally white - becomes amber when volts & amps become amber.- TR volts normally green - become amber if V > 31 V or V < 25 V.- TR amps normally green - becomes amber when TR current ≤ 5 A.

EMER GEN Indication- legend “EMERG GEN” normally white - becomes amber when either the volts or freq

become amber,- volts legend normally green - becomes amber if V > 120 V or V< 110,- frequency legend normally green - becomes amber if F > 410 Hz or F < 390 Hz,- Volts and freq indications are not displayed (as shown) when the EMER GEN line

contactor is open.

2 3

4

5

64

1

2

3

4

5


TM

Aug 2004page 28

ECAM ELEC Display (cont)

GEN (1) 2 Indications- GEN pushbutton switch is OFF (no load, volts or frequency indicated),

• GEN legend is amber,• “OFF” indication is white - replaces load, volts and frequency,• 1 or 2 indication is white if associated engine running, amber if not.

- GEN pushbutton switch is ON:• GEN 1 or GEN 2 normally white - becomes amber if any of the following

legends become amber,• load % legend normally green - amber if load > 100%,• volts normally green - becomes amber if V > 120 V or V < 110 V,• freq normally green - becomes amber if F > 410 Hz or F < 390 Hz.

IDG Indications (example: 115°C IDG 2)115°C

- oil outlet temperature,- legend normally green - appears amber if T > 185°C,- flashes if 147°C < T < 185°C (advisory).

IDG (1) or 2- normally white - amber if

• oil outlet temp > 185°C• oil pressure gets too low• IDG becomes disconnected

- the 1 or 2 is white if the corresponding engine is running, or the FADEC is not powered,amber if the engine is not running and the FADEC is powered.

DISC/LO PR (not displayed in example - would occupy second line of info)*- legend in amber when IDG disconnected,- LO PR appears in amber when IDG low pressure is detected.

RISE (not displayed in example - would occupy third line of info)*- normally green,- difference between temp at IDG inlet and that at the outlet.

ESS TR Indication- legend follows the logic of TR 1 (2),- the volts and amps are not displayed (as shown) when the essential TR contactor is

open.* see next page

1

2

1

2

3

3


TM

Aug 2004 page 29

ECAM ELEC Display (cont)

EXT PWR Indications- not displayed if external power is not available (see previous examples).- EXT PWR normally white - becomes amber if either of the following legends turn amber.- volts normally green - becomes amber if V > 120 V or if V < 110 V.- freq normally green - becomes amber if F > 410 Hz or if F < 390 Hz.

NOTE: EXT PWR replaced by STAT INV during static inverter test. It is normally green - but becomesamber if:

- V < 110 V or V > 120 V.- F < 390 Hz or F > 410 Hz

APU GEN Indications- when APU MASTER switch is OFF legend is white regardless of the position of the

APU GEN pushbutton switch.- when APU MASTER switch is ON, and the APU GEN pushbutton switch is OFF:

•APU GEN legend is amber,•OFF legend is white.

- when APU MASTER switch is ON and the APU GEN pushbutton is ON:• indications are the same as for GEN 1 (2).

GALLEY SHED Indication- legend appears in white when:

• GALLEY pushbutton switch is OFF, or,• main galleys are shed meaning:

- in flight, only one generator operating,- on ground, the aircraft is being supplied by one generator only.

- legend not displayed when aircraft is in its normal configuration.

123

1

2

3


TM

Oct 2004page 30

HOT AIR PB SWITCHON- valve regulates hot air pressure.OFF- valve closes,- trim air valves close,- FAULT circuit is reset.FAULT LIGHT (with ECAM Caution)- duct overheat (88° C)- light out when temp drops below 70° C and OFF

is selected.

AIR CONDITIONING Panel

ZONE TEMPERATURE SELECTORS- 12 o’clock position: 24° C (76°F)- COLD position: = 18° C (64° F)- HOT position: = 30° C (86° F)

PACK FLOW SELECTORPermits selection of pack flow according to num-ber of passengers & ambient conditions (smokeremoval, hot or wet conditions).LO - 80%

If low is selected, pack flow can beautomatically selected up to 100%when cooling demand cannot besatisfied.

NORM - 100%HI - 120%

The manual selection is irrelevant in single pack operation or with APU bleed supply. In these cases, HI is automatically selected.

PACK PB SWITCHON- pack flow control valve is automatically con-

trolled.- valve opens except in the following cases:

• upstream pressure below minimum,• compressor outlet overheat,• engine start sequence:

Both valves close when the MODE Sel. isset to IGN (or CRK) and when either ENG:- MASTER sw is set to ON (or MAN STARTps sw is set to ON), and

- the start valve is open, and- N2 < 50%On ground, the valves reopening is delayed30 sec to avoid a supplementary packclosure cycle during second engine start.

- onside engine fire pb depressed,- ditching is selected.FAULT LIGHT (with ECAM Caution)

• valve disagrees with selected position• compressor outlet overheat, or• pack outlet overheat.

OFF• pack flow control valve closes.

ENG 1 (2) BLEED PB SWITCHON- bleed valve opens provided:

• upstream pressure is above 8 psi.,• APU BLEED pb sw is OFF, or APU bleed

valve is closed,• there is no onside wing or pylon leak, and

no OVER PRESS or OVER TEMP detect-ed.

• ENG FIRE pb not released out,• ENG start valve closed.

FAULT LIGHT (with ECAM Caution)- overpressure downstream of the bleed val.- bleed overheat,- wing or ENG leak on the related side,- bleed valve not closed during engine start,- bleed valve not closed with APU bleed ON.It extinguishes when the ENG BLEED pb sw isat OFF provided the failure has disappeared.OFF- bleed valve & HP valve close,- OFF light illuminates.


TM

Aug 2004 page 31

AIR CONDITIONING Panel (cont)

RAM AIR PB SWITCH (guarded)ON- provided the DITCHING pb sw on the CABIN

PRESS panel is in normal position:• RAM air inlet opens,• if ∆P ≥ 1 psi: the outflow valve control

remains normal.• if ∆P < 1 psi: the outflow valve opens to

about 50% when not under manual control.OFF- RAM air inlet closes.

APU BLEED PB SWITCHON- APU valve opens provided N > 95% and

there is no leak on APU or left side bleed.(Should a leak occur on the right side, theX-bleed would close).

- ON light illuminates.OFF- APU valve closes.FAULT LIGHT (with ECAM Caution)- APU leak is detected.

X BLEED SELAUTO- X bleed valve is open if APU bleed valve is

open,- X bleed valve is closed if APU bleed valve is

closed or in case of wing, pylon or APU leak(except during engine start).

OPEN- X bleed valve is open.SHUT- X bleed is closed.


TM

Aug 2004page 32

Air Conditioning Schematic


TM

Oct 2004 page 33

ECAM (Air) COND Display

TEMP- unit of measure (°C or °F) is indicated in cyan

HOT AIR Pressure Regulating Valve- fully closed & PB at AUTO - closed & PB at OFF or valve disagree closed

-open - not closed, disagree with control position

ZONE TRIM Air Valve Position- indication is normally green - becomes amber if valve fails.- C = Cold Valve fully closed,- H = Hot Valve fully open.

ZONE DUCT Temperature- normally green, becomes amber at 80°C (176°F).

ZONE Temperature- indication is green.

CABIN FAN Fault Indication- appears amber if fault detected.

ZONE CONTROLLER Fault IndicationALTN MODE

- primary zone controller fault (green).PACK REG

- zone controller fault (basic regulation by packs only) (green).No Indication

- zone controller normal operation.

1

1

7

6

5

42

3

2

3

4

5

6

7


TM

Aug 2004page 34

Pneumatic Schematic


TM

Aug 2004 page 35

ECAM BLEED Display

PACK Outlet Temperature- indication is green - becomes amber if temperature above 90°C.

RAM AIR Inlet- fully open in flight - fully open on ground

-fully closed - amber in transit

PACK Bypass Valve Position- indication is green,- C = Cold - valve closed- H = Hot - valve open.

ENGINE Bleed Valves- BLEED valve normally opened - BLEED valve not in commanded (open) position

- BLEED valve normally closed - BLEED valve not in commanded (closed) position

HP Valves

- HP valve normally fully closed - HP valve not in commanded (closed) position

- HP valve not fully closed

PACK Flow Control Valve- valve open - not closed, disagree with control position

-fully closed - fully closed, disagree with control position.

PACK Flow- indication is green - becomes amber if pack flow control valve is closed.NOTE: the pack flow indication can be up to 30% below the actual flow rate.

PACK Compressor Outlet Temperature- indication is green - becomes amber if temperature above 230°C.

1

2

3

4

6

5

1

2

3

6

8

7

4

5

8

7


TM

Aug 2004page 36

ECAM BLEED Display (cont)

7

6

5

CROSS BLEED Valve- crossbleed valve normally closed - crossbleed valve not in commanded (closed) position.

- crossbleed valve normally open - crossbleed valve not in commanded (open) position.

- crossbleed valve in transitAPU Bleed Valve

- APU valve not fully open and APU master switch ON,

- APU valve fully open and APU master switch ONENGINE Bleed IndicationsPrecooler inlet pressure (example 30 PSI)

- normally green,- becomes amber if under 4 psi or if overpressure detected by the BMC (threshold

between 57 and 60 psi).Precooler outlet temperature (example 160°C)

- normally green, - becomes amber if BMC detects overheat or low temperature.‘ - overheat: temperature exceeds

• 290°C for more than 5 seconds, or• 270°C for more than 15 seconds, or• 257°C for more than 55 seconds.

- low temperature is detected if the temperature is lower than 150°CNOTE: on the ground with engines at idle, depending on ambient temperature, the pre-

cooler outlet temperature may be below 150°C.ENGINE IDENTIFICATION (1 or 2)

- normally white - becomes amber when engine N2 below idle.GND HP Ground Connection Indication

- displayed in green on ground.ANTI-ICE Indication

- displayed in white when the WING PB switch on ANTI-Ice panel is ON.ARROW

- normally not displayed when the corresponding valve is closed,- normally green when corresponding valve is open- amber when valve is open and air pressure is low or high, or valve is open on ground

for more than 10 seconds.

4

3

2

1

1 2

1

4

3

2

5

6

7


TM

Aug 2004 page 37

ANTI-ICE Panel

WING ANTI-ICE PB SWITCHON- «ON» light illuminates,- WING ANTI ICE indications appears on ECAM

MEMO page,- wing anti-ice control valve opens if pneumatic

air is available. On ground wing control valvesopen for 30 seconds (test sequence).

OFF- «ON» light extinguishes,- wing anti-ice control valves close.FAULT LIGHT (with ECAM activation)- anti-ice control valve disagree,- valve intransit,- low pressure detected.

ENG 1 (2) PB SWITCHON- «ON» light illuminates,- ENG ANTI ICE indications appears on ECAM

MEMO page,- eng anti-ice control valve opens if pneumatic

air is available. - continuous ignition is selected when valve is

open and Anti-ice Eng pb is ON.OFF- «ON» light extinguishes,- eng anti-ice control valves close.FAULT LIGHT (with ECAM activation)- anti-ice control valve disagree,- valve intransit.

PROBES/WINDOW HEAT PBAUTO- probes/windows auto heated in flight,- on ground with one engine operating (except

TAT probes).ON- «ON» illuminated,- probes/windows heated.


TM

Aug 2004page 38

Wing & Engine Anti-Ice Schematics

Aug 2004 page 39

trs-digital-presentationA319, A320, A321 System Review

TM

Window & Probe Anti-Ice Schematics

Aug 2004page 40


TM

CABIN PRESS Panel

MODE SEL PB SWITCHAUTO- auto mode operating (one system at a time),

NOTE: if pressurization degraded performance issuspected, a selection of the pressurization sys-tem which is not active could be attempted byswitching the MODE SEL pb to MAN for at least10 sec - then to AUTO.

MAN- «MAN» illuminates,- «FAULT» extinguishes,- manual control is then operative by the MAN V/S

CTL switch.FAULT LIGHT (with ECAM Caution)- both automatic systems indicate faults.

MAN V/S CTL TOGGLE SWITCH (spring loadedto neutral)- controls outflow valve position by the MAN motor

when MODE SEL P/B switch is at MAN position.UP- valve moves towards open position.DN- valve moves toward closed position.

LDG ELEV ROTARY SELECTORAUTO- pressurization system uses FMGS data to elab-

orate an optimized pressure schedule.OTHER POSITIONS- landing elevation from FMGS is not used by the

pressurization system,- landing elevation selected (from –2,000 to

14,000 ft) is taken as reference.

DITCHING PB SWITCH (guarded)NORMAL (de-selected)- normal system operation.ON- a closed signal is sent to the outflow valve,

emergency ram air inlet, avionics ventilationextract valve and pack flow control valves.

NOTE: if the MODE SEL pb sw is at MAN, the out-flow valve remains controlled by the MAN V/SCTL switch.

PRESSURIZATION LIMITATIONSMax cabin differential pressure 8.6 psiNeg cabin differential pressure - 1.0 psi


TM

Aug 2004 page 41

ECAM CAB PRESS Display

9

LDG ELEV AUTO/MAN- LDG ELEV AUTO appears in green when the LDG ELEV selector is in AUTO,- LDG ELEV MAN appears in green when the LDG ELEV selector is not in AUTO,- neither appears when the MODE SEL pushbutton switch is in MAN

Landing Elevation- the landing elevation selected either automatically by the FMGS or manually by the pilot

appears in green (but not when the MODE SEL pushbutton is in MAN).∆P PSI (Cabin Differential Pressure)

- analog and digital presentations appear in green when ∆P is in the normal range.- they appear amber when ∆P ≤ 0.4 psi or ≥ 8.5 psi,- digital presentation pulses if ∆P > 1.5 psi (resets at 1 psi) during flight phase 7.

V/S FT/MIN (Cabin Vertical Speed)- analog and digital presentations appear in green when V/S is in the normal range,- they appear amber when V/S ≥ 2000 feet/minute,- digital presentation pulses when V/S > 1800 feet/minute (resets at 1600 fpm).

CAB ALT FT (Cabin Altitude)- analog and digital presentations appear in green, in normal range,- they appear in red if the cabin altitude goes above 9550 feet,- digital presentation pulses if the cabin altitude is at or above 8800 feet (resets at 8600 ft.)

Active System Indication (SYS 1 or SYS 2 or MAN)- SYS 1 or SYS 2 appears in green when active and in amber when fault,- when either system is inactive, its title does not appear,- MAN appears in green when the MODE SEL switch is in MAN.

SAFETY VALVE Position- SAFETY appears in white & diagram in green when both safety valves are fully closed,- SAFETY & the diagram appear in amber when either valve is not closed.

NOTE: Safety valve opens when the cabin differential pressure is between 8.2 and 8.9 psi.The rangeis due to the reduced accuracy of ∆P measurements (in MAN mode),combined with the decrease incabin differential pressure that occurs immediately after the safety valve opens.OUTFLOW VALVE Position

- indicates green with valve operating normally - amber when valve opens more than 95%during flight.

PACK Indication- triangle normally green, PACK 1 (2) indication normally white. Both become amber when

pack flow control valve is closed with associated engine running.

1

1

2

3

4

5

6

7

8

2

3

4

5

6

7

8

9


TM

Aug 2004page 42

CRUISE ECAM Display (cont)

LDG ELEV AUTO/MANIdentical to CAB PRESS page.CAB V/S FT/MIN (cabin vertical speed)

- GREEN normal range- AMBER out of normal range: V/S > 2000 feet/min- pulses when V/S > 1800 feet/min (resets at 1600 fpm)

CAB ALT FT (cabin altitude)- GREEN normal range.- RED: excessive cabin altitude > 9550 feet- pulses when cabin altitude at or above 8800 feet (resets at 8,600 feet)

P indication- GREEN normal indication- AMBER when out of normal range P < - 0.4 psi or > 8.5 psi

ZONE indication and temperature- temperature scale in use (C or F)

1

1

2

2

3

3

4

4

5

5

P 6.4 PSI


TM

Aug 2004 page 43

NAV & LOGO SWITCHNAV & LOGO- navigation & logo lights activation,

• Navigation lights are located at each wingtip and the APU tail cone.

• Logo lights are installed in the upper surfaceof each horizontal stabilizer to illuminate the the vertical stabilizer provided the main gearstruts are compressed or the slats are out.

WING SWITCHON- illuminates two single beam lights on each

side of the fuselage to illuminate the wingleading edge & engine air intake.

BEACON SWITCHON- illuminated the two flashing red (anti-colli-

sion) lights on the top and bottom of thefuselage.

STROBE SWITCHON- stobe lights on each wing tip flash.AUTO- stobe lights are automatically switched onwhen the shock absorber is not compressed.

OFF- all strobe lights are off.

RWY TURN OFF SWITCHON- illuminates runway turnoff light on the nose

gear strut.- lights auto off when gear retracted.

L & R LAND SELECTORSON- related landing light is extended & comes on

when fully extended.OFF- related light is extended but off.RETRACT- retracts the LDG lights & shuts them off.

NOSE SWITCHTO- both taxi & take-off lights are illuminated.TAXI- only taxi light is illuminated.OFF- taxi & take-off lights are off,

NOTE: lights also automatically off with gearretraction.

EXT LT Panel


TM

Aug 2004page 44

MASTER PB SWITCH (controls power supply for APUoperation and protections)ON- «ON» illuminates- APU system is active, ECB completes power up test,- APU air intake flap opens,- APU fuel isolation valve opens,- if not tank fuel pump is running, APU fuel pump operates,- if grd pwr or main gen pwr is used, APU page appears on

ECAM system display.OFF- manual shutdown sequence starts.- ON and/or AVAIL lights extinguish,- if bleed air used, APU runs for a cooling period of 60 to 120

seconds at 75% speed (rpm),- at 7% speed (rpm), air inlet flap closes.FAULT (with ECAM activation - when auto shutdownoccurs)Auto shutdown when:- Fire (on ground),- air inlet flap closed,- overspeed,- no acceleration,- slow start,- overtemp,- no flame (no light-off)- reverse flow

START PB SWITCHON- «ON» illuminates, starter is energized,- 7% speed (rpm) ignition,- 50% speed (rpm) starter cut-out, ignition turned off,- 95% speed (rpm) «ON» on START pb extinguishes and

«AVAIL» light illuminates.- APU now available for bleed air and/or electrical power,- 15 seconds later, APU page is removed from ECAM display.AVAIL LIGHT- on at 95% speed (rpm).

APU Panel

- low oil pressure,- high oil temp,- DC power lost,- over-current,- sensor failure,- IGV failure,- ECB failure.

APU LIMITATIONS:Max start temp: 1038° CMax continuous: 725 ° CMax RPM: 107%3 Start attemptsGenerator operation to FL 390Bleed operation to FL 200Batt Start altitude FL250Full 90 KVA altitude FL250


TM

Aug 2004 page 45

AVAIL- displayed in green when APU N is above 95%.

APU Bleed Valve Position- valve open

- valve fully closed - valve fully closed if APU bleed ONAPU Bleed Air Pressure

- box displays the relative bleed air pressure in green,- XXXX in amber is displayed when ADIRS2 is not available or selected OFF.

APU GEN Line Contactor Indication- displayed in green when the APU GEN line contactor is closed.

APU GEN Parameters- identical to the APU GEN parameters on the ELEC page.

FUEL LO PR- displayed in amber if APU fuel pressure gets low.

FLAP OPEN- displayed in green when APU air intake flap is fully open (MASTER SW ON).

APU N-displays APU speed in green,- becomes amber when N ≥ 102%,- becomes red when N ≥ 107%

APU EGT- displays APU EGT in green,- becomes amber when EGT ≥ EGT max* – 33°C (stead during APU start, pulsing

when APU is running). [Amber line]- becomes red when EGT ≥ EGT max* (automatic shutdown begins). [Red line]

* ECB calculates EGT max and transmits it to ECAM. It is a function of N during startand a function of ambient temperature when the APU is running.Maximum EGT during start: 1038°CMaximum EGT with APU running: 690 - 725°C depending on ambient temperature.

LOW OIL LEVEL- ADVISORY: displayed if the ECB detects a low APU oil level when on the ground and

APU not running.

ECAM APU Display

1

2

3

6

7

10

4

5

8

9

1

2

3

4

6

7

8

9

10

5


TM

Aug 2004page 46

ANN LIGHT SELTEST- all flight deck annunciator lights illuminate,- all LCDs indicate “eight”.DIM- annunciator lights dim,BRT- normal position.

DOME SELECTORBRT- both dome lights on.DIM- dome lights dim.OFF- lights off.

ICE IND & STBY COMPASS SWITCHON- turns on integral lighting for standby com-pass and visual ice indicator on and off.

OVHD INTEG LIGHT KNOBROTATE- overhead integral lighting intensity adjust-ment.

SEAT BELTS SWITCHON- «FASTEN SEAT BELT» signs (in cabin) and

«RETURN TO YOUR SEAT» signs (in lav)illuminate with low chime.

OFF- signs off,- low chime sounds

NO SMOKING SWITCHON- «NO SMOKING & EXIT» signs (in cabin)

illuminate with low chime.AUTO- «NO SMOKING & EXIT» signs (in cabin)

illuminate when gear is down and go out when retracted.

- low chime sounds each event.OFF- signs off,- low chime sounds.

NOTE: FASTEN SEAT BELT, NO SMOKING& EXIT signs (in cabin & lavs) illuminate auto-matically regardless of switch position if cabinalt. exceeds 11,300 feet ± 350 feet.

INT LT & SIGNS Panels

EMER EXIT LT OFF LIGHT PBOFF- «OFF» illuminated- if EMER PB switch at Purser’s panel is pressed

to activate emergency lighting, light is off.

EMER EXIT LT SWITCHON- overhead emergency lights, exit signs and floor proxim-

ity marking system illuminate.OFF- all lights off.ARM- floor prox. emerg. escape path system and ovhd emer.

lighting auto on if:• DC SHED ESS BUS failure, or• AC BUS 1 failure

- exit signs auto on if:• DC SHED ESS BUS failure, or,• excessive cabin alt, or• NO SMOKING sing illumination.

NOTE: Purser panel can over-ride emergency lights.


TM

Aug 2004 page 47

TRANSMISSION KEYSDEPRESSED- associated channel is selected for transmis-

sion,- three green lines illuminate,- channel is deselected by pushing sw again

or selecting another channel.CALL LIGHT- flashes with buzzer for call from SELCAL

system.MECH LIGHT- flashes with buzzer for call from nose gear

bay,- light out if not reset within 60 seconds.ATT LIGHT- flashes with buzzer for call from cabin atten-

dant,- light out if not reset within 60 seconds.

RECEPTION KNOBS (alternate action)PRESSED - KNOB OUT- associated knob illuminates,- associated audio reception channel is select-

ed- rotate knob for volume adjustment.PRESSED - KNOB IN- audio reception channel is disconnected.

PA KEYPRESSED (and held)- green bars illuminate and boom set, oxygen

mask or hand mic may be used for PA

RESET KEYPRESS- CALL, MECH and ATT lights extinguish.

NOTE: MECH & ATT lights out after 60 sec. ifcall not cancelled by RESET key.

ON VOICE KEYDEPRESSED- «ON» light illuminates,- ident signals (Morse code nav signals [VOR

& ADF] are filtered.

AUDIO SELECTOR Panel

INT/RAD SWITCH (PTT)INT- flight interphone transmission mode is selected when using

boomset or mask mic’s regardless of the transmission keyselection,

- for reception, INT knob must be selected.NEUTRAL (position)- reception normal,- boomset & mask mic’s disconnected.RAD (switch must be held - PTT)- used to talk by boomset or mask mic’s through facility

selected on the ACP.


TM

Aug 2004page 48

OVHD RADIO MANAGEMENT Panel (RMP)

ACTIVE WINDOW- shows active freq of selected radio which is

identified by a green bar on selection key.

RADIO COMM SEL KEYSPRESSED (green dot or bars illuminated)- ACTIVE and STBY/CRS windows display

frequencies previously selected.- example of bars display.

NAV KEY (with transparent switch-guard)PRESSED- green monitor light illuminates,- Radio Nav Back-up mode is engaged,- VOR, ILS, MLS & ADF receivers controlled

by RMP (no longer from FMGS),- pressing again returns control to FMGS.NOTE 1: back up tuning mode must be select-ed on RMP 1 and 2 in case of both FMGCs orMCDU failure. In case of emergency electricalconfig RMP 1 only is powered.NOTE 2: pressing NAV key on RMP3 (ifinstalled) has no effect.NOTE 3: in NAV back-up mode, radio comm.systems can be selected as in normal mode.NOTE 4: setting one RMP to NAV back-upmode removes NAV AIDS tuning capabilityfrom both FMGCs.NOTE 5: when an ILS/DME is tuned using theRMPs, the DME distance is not displayed inthe PFDs.ON LIGHT- illuminates when RMP has control.NAV LIGHT- light always on.

STBY/CRS WINDOW- displays a stby freq which can be made active by de-

pressing the Transfer Key or changed by rotating theTuning Knob,

- if course is displayed associated freq isin ACTIVE window.

NOTE: if a course is displayed, depressing the transferkey will show active freq on both windows.

TRANSFER KEYPRESSED- ACTIVE and STY freq are interchanged,- selected receiver is now turned to new

ACTIVE freq.

STBY NAV KEYSPRESSED (with NAV KEY on)- when appropriate key pressed, the ACTIVE

window displays the present freq.,- the green dot or bars illuminate on the selected

key (and previous STBY NAV or COM key lightsextinguish.

ROTATING (Frequency) KNOBS- Two concentric knobs allow preselection of freqfor radio comm systems, standby nav systemsand selection of the required course for VOR orILS. A rate multiplier speeds up tuning if knob isrotated rapidly.- preselected frequency (STBY) becomes activeby pressing Transfer Key.OUTER KNOB- controls the most significant digits of the freq.INNER KNOB- controls the least significant digits of the freq.

ON/OFF SWITCH- controls the power to each RMPNOTE: when RMP 1 or 2 are off, RMP 3 is stillable to control UHF/VHF transceivers.


TM

Aug 2004 page 49

FLT CTL (right side) & CARGO SMOKE Panel

DISCH PB SWITCHPRESS- ignites squib to discharge agent in corre-

sponding compartment (FWD or AFT).

DISCH LIGHTON- bottle discharged.

SMOKE LIGHT (with ECAM Warning)ON- both channels detect smoke, or- one channel detects smoke and the SDCU

detects a fault in the other channel.

TEST PBPRESS- tests smoke detector lights in sequence,- «SMOKE» light flashes twice, and- displays the ECAM Warning,- closes the isolation valves of the ventilation

system,- «DISCH»light illuminates.

SAME AS Pg. 7 (left side)


TM

Aug 2004page 50

FWD AFT

Cargo Compt Fire Detection Schematic

ECAM ECAM

CARGOVENTILATION

AND AND AND

OR

CARGOVENTILATION

SDCU

SMOKEDETECTORS


TM

Aug 2004 page 51

Cargo Compt Fire Protection Schematic

DISCHARGEHEADS

PRESSURESWITCH

BOTTLE

FORWARD

NOTE: ETOPS aircraft have two bottles.

AFT


TM

Aug 2004page 52

VENTILATION Panel

CAB FANS PB SWITCHON- two cabin fans run.OFF- two cabin fans stop

NOTE: a double fan failure an ECAM Cautionis activated.

BLOWER PB SW & EXTRACT PB SWAUTO (both switches are in AUTO)On ground before power application:- ventilation system is in open circuit configu-

ration (closed configuration when skin temp below the ground threshold).

On ground after TO power application, or in flt:- ventilation system is in closed circuit config.OVRD (either switch is at OVRD)- system goes to closed circuit configuration.- air from air conditioning system is added toventilation air (the blower fan stops if BLOW-ER pb sw at OVRD position).

OVRD (both switches are at OVRD)- air is provided from the air conditioning sys-

tem and then extracted overboard,- extract fan remains energized.FAULT LIGHT (with ECAM activation)Blower Fault Light- blowing pressure low*- duct overheat*- computer power supply failure- smoke warning.Extract Fault Light- extract pressure low*- computer power supply failure,- smoke warning*

* if the warning occurs on the ground, enginesstopped, the external horn is triggered.


TM

Aug 2004 page 53

Ventilation Schematic

AVIONIC BAY

SKIN EXCHOUTLETBYPASS

VALVESKIN EXCHISOL VALVE

SMOKEDETECTOR

AIR CONDFROM COCKPIT

SKINHEATEXCH

SKIN EXCHINLETBYPASSVALVE

SKIN AIRINLET

VALVE

SKIN AIREXTRACTVALVE

BLOWERFAN

EXTRACTFAN

VALVES & FANSCONTROLS

FILTER

AIR CONDINLET VALVE

AIR CONDDUCT

CONTROLLER


TM

Aug 2004page 54

ENG Panel

N1 MODE PB SWITCHON- «ON» light illuminates.- thrust control reverts from EPR mode to rated N1 mode,- following an automatic reversion to N1, rated or unrated

mode, pressing the pb sw confirms the mode.OFF- if available, EPR mode is selected.

MAN START PB SWITCHON- «ON» light illuminates.- start valve opens provided MODE sel is on the IGN/START

position and N2 < 15%.- on ground both pack valves close provided MODE sel is on

the IGN/START position and N2 is < idle. They reopenwhen IGN is deselected.

OFF- start valve closed unless a start cycle is in progress.


TM

Aug 2004 page 55

F/O WIPER PANELSame as Capt’s controls

WIPER LIMITATION:Wiper operation - 230 kts.

WIPER (right side) Panel


TM

Aug 2004page 56

WET COMPASS.

Wet Compass & Glareshield




TM

Aug 2004 page 57

Glareshield Panel

MASTER CAUTION LIGHTILLUMINATES- for level 2 cautions,- accompanied by a single chime,EXTINGUISHED when- pressed,- warning/caution no longer exists,- pressing CLR pb on the ECAM control panel,- pressing the EMERG CANCEL pb on ECAM

control panel (for Master Caution only).

SIDE STICK PRIORITY ARROW LIGHTILLUMINATES- on side losing authority,- remains on as long as authority is no recovered:

• because the other TAKE OVER pb is releasedin less than 40 sec, or

• because TAKE OVER pb used to cancel alatched priority situation (> 30 sec).

CAPT F/O LIGHTILLUMINATES- on side who has taken priority by depressing

the takeover pb if the opposite stick is not atneutral.

EXTINGUISHES when- opposite stick is returned to the neutral position.

CHRONO SWITCHPUSH- used to stop/start ECAM chronometer.

MASTER WARNING LIGHTSFLASH- for level 3 warning,- accompanied by an aural warning (continuous

repetitive chime, specific sounds or syntheticvoice.

AUTO LAND LIGHTILLUMINATED if- excessive deviation,- loss of second autopilot,- long flare,- greater than 10 ft. difference

between radio altimeters.


TM

Aug 2004page 58

Glareshield Panel (cont)

OPTIONAL DATA DISPLAY PB SWITCHESPUSH- enables display of optional data in addition to

the data permanently displayed in PLAN, ARCor ROSE modes,

- green stripes illuminate,- only one activated at at time.BARO REFERENCE DISPLAY WINDOW

FD PB SWITCHPUSH (on)- allows FD bars (or FPD Symbol) to be

displayed,- green stripes illuminate.PUSH (off)- removes FD bars from associated PFD

(or FPD Symbol, if the TRK FPA isselected.

ILS PB SWITCHPUSH- LOC and GS scales and deviation

symbols displayed on PFD,- green stripes illuminate.

ADF - VOR BEARING SWITCHESSELECT- enables selection of ADF and/or VOR

bearing pointers and DME distance ononside ND as well as the correspondingnavigation station characteristics in anymode except PLAN mode.

RANGE SELECTOR SWITCH- enables selection of required scale on

onside ND.

MODE SELECTOR SWITCH- enables selection of required navigation

display on onside ND.


TM

Aug 2004 page 59


DISPLAY ALT WINDOW- displays altitude selected by the

pilot on the FCU,- ALT is never dashed.

SPEED/MACHSWITCHING

SPEED/MACHREF CONT KNOB

LOCALIZERENGAGEMENT

HDG/TRKREF CONT KNOB

AUTOPILOTENGAGEMENT

AUTOTHRUSTENGAGEMENT

HDG - V/S/TRK - FPASELECTION

ALTITUDEREF CONT KNOB

ALTITUDESETTING METERS

EXPEDITEENGAGEMENT

APPROACHENGAGEMENT

V/SPEED - FPAREF CONT KNOB

FLIGHT CONTROL UNIT- two types of guidance and their associated modes are available. Those managed by the FMGS

are associated with dashed windows and their illuminated lights. Those selected by the crew aredisplayed on the windows with the corresponding lights extinguished.

- in order to engage MANAGED guidance, the pilot must push the associated selector.

- in order to engage a SELECTED guidance mode, the pilot must TURN (to select the requiredparameter value) and PULL the selector.

GLARESHIELD LIGHTING KNOBSTURN- to adjust integral and flood lighting.

INTEGRAL FLOOD


TM

Aug 2004page 60


same as opposite side

same as opposite side


TM

Aug 2004 page 61

Instrument Panel Flow




TM

Aug 2004page 62

Captain’s Tiller, Side Stick & Arm Rest

PUSH-TO-TALK SW

A/P DISCONNECT/SIDESTICK PRIORI-TY PB- controls general brightness

of ND symbology.- extreme left position switches

off ND.

ARM RESTPitch AdjustmentHeight Adjustment (similar wheel onarm edge - not shown on this photo)Protection Wheel

HANDWHEEL (interconnected)- steer nosewheel up to 75 degrees ineither direction.

Rudder PEDAL DISC PB- removes control of nose wheel steeringfrom the rudder pedals until the button isreleased.

POSITION display- arm rest memory display in pitch and

height

GPWS - G/S PBGPWS LIGHT- illuminates when any mode 1 to 4 is activated,- accompanied by specific voice warning,- ECAM activation.G/S LIGHT- illuminates when mode 5 is activated,- «GLIDESLOPE» voice warning,- ECAM activation.

PFD/ND XFRPUSH (each push)- PFD and ND images will be interchanged.NOTE: in case of PFDU failure, PFD display auto-matically transferred on the NDU.

ND BRIGHTNESS CONTROLKNOBOUTER KNOB- controls brightness of weather

radar image only,INNER KNOB- controls general brightness

of ND symbology.- extreme left position switches

off ND.

LOUD SPEAKER VOLUME CONTROL

PDF BRIGHTNESS CONTROL KNOBOFF- PFD off,- PDF image automatically displayed on the ND- pilot may recover the ND by means of the

PFD-ND XFR pb switch.

CONSOLE/FLOOR SWITCH (Capt and for)BRT & DIM control- permits illumination of side consoles,- brief cases,- floor around each pilot seat.

Captains Instrument Panel


TM

Aug 2004 page 63


TM

Aug 2004page 64

PFD INDICATIONS

Captains Instrument Panel (cont)

FMA

Airspeed

Attitude

Guidance

Radio Height

Altitude

and

Vertical

Speed

AltitudeBaroSet

Mach ILSdata Heading / Track


TM

Aug 2004 page 65

PRIMARY FLIGHT DISPLAY (PFD)

APPROACHCAPABILITIES

ANDDA/MDA

AP, FD, A/THRENGAGEMENT

STATUSLATERALGUIDANCE

MODE

VERTICALGUIDANCE

MODE

A/THRMODE

SELECTEDHEADING

(IF OFF TAPE)

LOCALIZERCOURSE HEADING

SELECTEDHEADING

ACTIVE MODEGREEN 1ST LINE

ARMED MODEBLUE 2ND LINE

CPIP 3

CPIP 1


TM

Aug 2004page 66

PFD ALTITUDE DATA

SELECTED SELECTED ALALTT

VERTICALVERTICAL SPDSPD

CURRENT CURRENT ALALTT

ALALT SETTINGT SETTING

CONSTRAINT CONSTRAINT ALALTT

DESCENT PDESCENT PAATHTHINDICAINDICATTOROR(MAGENT(MAGENTAA DONUT)DONUT)

RADIO RADIO ALALT ELEVT ELEV

LANDING ELEVLANDING ELEVFROM DAFROM DATTABASEABASE

29.88QNH

29.88QNH


TM

Aug 2004 page 67

PFD SPEED DATA

VMAXVMAX

VLSVLSALPHAALPHA PROT SPEEDPROT SPEED

ALPHAALPHA MAX SPEEDMAX SPEED

VFE NEXTVFE NEXT - VFE corresponding to next flaplever position when aircraft below FL150 orFL200.

NOTE: see next page for Symbology & Definitions.

ECON SPEED RANGEECON SPEED RANGE

ENG OUT OPERAENG OUT OPERATING SPEED INTING SPEED INCLEAN CONFIGURACLEAN CONFIGURATIONTIONAIRSPEED REF AIRSPEED REF AND SCALEAND SCALE

MIN SLAMIN SLAT RETRACT SPEEDT RETRACT SPEEDMIN FLAPMIN FLAP RETRACT SPEEDRETRACT SPEED

TTARGET ARGET AIRSPEEDAIRSPEEDDECISION SPEED (V1)DECISION SPEED (V1)

MACH NUMBERMACH NUMBER


TM

Aug 2004page 68

SYMBOLOGY & DEFINITIONS:Vs - reference stalling speed (Equal to Vs1g).

VMCG - minimum control speed on ground from which a sudden failure ofthe critical engine can be controlled by use of primary flight con-trols only, the other engine remaining at TO power.

V1 - represented by “1” on airspeed scale (or (V1 value when out ofrange). Manually inserted by the crew through the MCDU.

Vr - manually inserted by the crew through theMCDU.

V2 - represented by the SPEED SELECT symbol on airspeed scale. - minimum value for V2 is equal to 1.13 Vs of the corresponding

configuration.- manually inserted by the crew through the MCDU.

VMCA - minimum controls speed in flight at which aircraft can be control-led with 5° max bank, in case of failure of one engine, the otherengine remaining at TO power (TO flaps setting, gear retracted).

F - is the minimum speed at which the flaps may be retracted toCONF 1. Represented by “F” on airspeed scale. It is equal to about 1.23 Vs of CONFIGURATION 1+F.

S - is the minimum speed at which the slats may be retracted toCONF 0. Representated by “S” on airspeed scale. It is equal to about 1.29 Vs of CLEAN CONFIGURATION.

O - ENGINE OUT OPERATING (Green Dot) speed (Best lift to dragration speed or DRIFT DOWN SPEED) in clean configuration. Itcorresponds also the the FINAL TAKEOFF SPEED. It is calcul-ated by FACs and represents:• below 20,000 ft:

Green dot = 2 x weight (t) +80• above 20,000 ft. add 1 kt per 1,000 ft.

VFE - max speed for each flaps and/or slats configuration.

VREF - reference speed used for a normal final approach, it is equal to1.23 Vs of configuration “FULL”

- represented on the MCDU APP page.


TM

Aug 2004 page 69

SYMBOLOGY & DEFINITIONS: (cont)VLS - Lowest Selectable Speed.

- it is represented by the top of an amber strip along the airspeedscale. It corresponds to 1.13 Vs during the takeoff or following atouch-and-go. As soon as the flap/slat selection is made VLS

becomes:• 1.23 Vs for CONF other than CLEAN CONF• !.28 Vs for CONF 0NOTE: if in CONF 0 VLS was 1.23 Vs (instead of 1.28 Vs) theVLS strip on PFD would be hidden by the alpha prot. strip.

- above 20,000 ft. VLS is corrected for Mach effect to maintain0.2g buffet margin.

VAPP - FINAL APPROACH SPEED- displayed on MCDU APPR page. It is calculated by the FMGC

and represents: VAPP = VLS + Wind correction + 5 kts.NOTE: 5 kts increment is required for autoland only. Never the less,

this increment is always added by FMGC. WIND correctionis 1/3 of headwind component based upon wind directionand speed entered on the MCDU APPR page.

- VAPP may be modified and manually entered through MCDU. Forfailure cases VAPP should be entered as follows:

VAPP = VREF + CONF CORR + WIND CORRECTION** WIND CORRECTION:

• if configuration correction > 20 kts:WIND CORRECTION = 0

• if configuration correction < 20 kts:WIND CORRECTION = 1/3 of headwind component limited suchthat the configuration correction plus the wind correction do notexceed 20 kts.

VAPP - it is represented by a magenta triangle. It is calculated by FMGCTARGET and provides an efficient speed guidance in approach in various

windy conditions. It represents:VAPP TARGET = GS mini + actual headwind (measured by ADRIS)with GS mini = VAPP - TOWER WIND (headwind component on runway axis calculated by FMGC from tower wind entered on the MCDU APPR page).

VSW - Stall Warning Speed. It is represented by a red and black stripalong the speed scale when the flight controls normal law isinoperative. It is equal to 1.05 Vs of the present configuration.


TM

Aug 2004page 70

PFD Flags

1

2

3

4

5

6

7

8

9

10

11

12

1 SI Flag (red) appears if the sideslip information is lost or any reverse is deployed in flight, theindex disappears.

2 SPD SEL Flag (red) indicates failure of selected speed information.

4 FD Flag (red) appears when both FMGC’s fail, or if both FD’s are disengaged and the FD pb isON and the attitude is valid.

5 CHECK ATT Flag (amber) appears when there is a disagreement (of at least 5°) in the attitudeinformation displayed by the two PFD’s. CHECK ATT appears on both PFD’s and a cautionappears on the ECAM.

6 SPD Flag (red) replaces the speed scale when the speed information fails.

7 WINDSHEAR Flag (red) flashes for nine seconds, then steady if appropriate navigation receiversfails.

8 FPV Flag (red) appears in the TRK FPA mode, when the drift angle or flight path angle is notvalid.

10 MACH Flag (red) appears when Mach data fails.

11 ILS 1 Flag (red) appears with ILS frequency failure, or if either the LOC or G/S signals fail, anILS 1 (on PDF1) or ILS 2 (on PDF2) fail.

12 DME 1 Flag (red) appears when DME distanceis not valid, a DME 1 (on PFD1) or DME 2 (onPFD2 replaces the DME distance indication.

9 SPD LIM Flag (red) appears when both FAC’s are inoperative, or in the case of SFCC dual flap/slat channel failure. the PFD information is lost: VLS, S, F, Green Dot, Vtrend, Vmax, VFE nextand VSW.

3 V1 INOP Flag (red) flag replaces digital value when V1 signal is not valid.


TM

Aug 2004 page 71

PFD Flags (cont)

23

22

15

21

20

19

18

17

16

15

14

13

13 CHECK HDG Flag (amber) appears with a 5° discrepancy between the Captain’s and FirstOfficer’s heading indications.

14 HDG Flag (red) replaces the heading indicator with failure of heading information..

16 RA Flag (red) replaces RA height information when both radio altimeters fail.

17 ILS Flag (red) appears when APPR mode is armed & ILS display not selected.

18 DH Flag (amber) appears when the aircraft reaches the selected DH.

19 V/DEV Flag (red) flashes when FINAL mode is armed or engaged, and the ILS pb is selected.

20 V/S Flag (red) replaces VS scale if vertical speed information fails.

22 CHECK ALT Flag (amber) appears along with an ECAM caution if the difference between thetwo PDF altitude indications is greater than 250 feet when QNH is selected, or 500 feet whenSTD is selected. .

23 ALT SEL Flag (red) appears when selected altitude information fails.

24 V/DEV Flag (amber) flashes when in approach phase and, when either the FINAL mode isarmed/engaged or a non-ILS aproach has been selected and the ILS pb is selected.

25 ATT Flag (red) if PFD loses all attitude data, its entire sphere is cleared to display the ATT flag.

21 ALT Flag (red) replaces altitude scale with failure of altitude information.

15 LOC & G/S Flag (red) appears with failure of the localizer or glideslope receiver.

24

25


TM

Aug 2004page 72

Navigation Display (ND) Rose NAV Mode

GROUND SPEED/TRUE AIRSPEEDWIND ORIGIN/FORCEDIRECTION ARROW

A/C HEADINGACTUAL TRK

SEL HDG or TRK

NAVAID

“TRU” appears at the top of the rose when it is displaying true headinginstead of magnetic heading (latitude above 73°N and 60°S)

A/C SYMBOL

BEARINGPOINTER

CHRONOMETER

NAVAID


TM

Aug 2004 page 73

Navigation Display (ND) Rose ARC Mode

TO WAYPOINT

ACTIVEFLIGHT

PLAN

RANGEMARKS

Range Marks & ValuesThe range scale value selected on the EFIS control panel (10 to 320 NM) governsthe scale on the ND.The values displayed on the ND are:In ROSE NAV mode - 1/4 of the selected range for the inner circle

- 1/2 of the selected range for the heading scale circleIn ROSE ARC mode - 1/4 of the selected range for the first inner circle

- !/2 of the selected range for the second inner arc- 3/4 of the selected range for the third inner arc.


TM

Aug 2004page 74

ROSE VORROSE ILS

ROSE NAV

PLANARC

Navigation Display Modes


TM

Aug 2004 page 75

WEATHER RADAR

TCAS

Navigation Display Modes (cont)


TM

Aug 2004page 76

ND Flags

4

GPS APP

PRED W/S

MODE CHANGE

OFST R 12

36

7

8

5

7

2

1

1 HDG Flag (red) flashes for nine seconds, then steady if heading data fails, rose, arc and associ-ated symbols disappear.

2 CHECK HDG Flag (amber) when flight warning computer detects a discrepancy (5°) betweensides 1 and 2, this flag appears on both ND’s, along with a caution on the ECAM.

4 LOC Flag (red) flashes for nine seconds, then steady if LOC data fails.

5 G/S Flag (red) flashes for nine seconds, then steady if G/S data fails.

6 VOR Flag (red) flashes for nine seconds, then steady if ROSE VOR bearing data is not valid.

7 VOR1(2) or ADF1(2) or DME1(2) Flag (red) flashes for nine seconds, then steady if appropriatenavigation receivers fails.

8 VOR Course Flag if VOR course fails, a red CRSXXX flag appears. If there is non-computeddata (NCD), a blue CRS_ _ _ appears.

3 MODE CHANGE (green) when there is a discrepancy between the selected mode on the EFIScontrol panel and the mode sent from the outside FMGC, or while the DMC is preparing a newpage for display. [MODE CHANGE has priority over RANGE CHANGE]RANGE CHANGE (green) when there is a discrepancy between the the EFIS range and the out-side FMGC range.MAP NOT AVAIL (red)

- MODE CHANGE and RANGE CHANGE displayed for more than six seconds.- FMGC has failed.- FMGC has delivered an invalid aircraft position.

W/S SET RING 10 NM (red for warning, amber for caution) is displayed if a predictive winds-hear alert is triggered and the range is above 10 NM.W/S CHANGE MODE (red for warning, amber for caution) is displayed if a predictive wind-shear alert is triggered and the ND is not in ARC or ROSE mode.


TM

Aug 2004 page 77ND Flags (cont)

12 GPS APP

PRED W/S

MODE CHANGE

OFST R 12

1011

9

9 Other messagesMAP PARTLY DISPLAYED (amber) incomplete data transmission between FMGC (priority crite-ria) and the DMC, or if the DMC cannot draw the complete MAP. This messages is also displayedwhen a very long leg [when the starting point (or endpoint) is located more than 45° from aircraftlocation (45° of longitude or latitude)] exists in the flight plan.NAV ACCUR UPGRADE (white) or NAV ACCUR DOWNGRAD (amber) signals a change innavigation accuracy.SPECIFIC VOR/D UNAVAIL (amber) navaid that is tuned for selected approach or departure isnot available.SET OFFSIDE RING/MODE (amber) displayed on ND1(2) in case of an FMGC1(2) failure whenthe two ND ranges or modes selected on the EFIS control panels are different.GPS PRIMARY (white, boxed white) GPS PRIMARY mode is availalble, or has been recovered.Pilot can clear this message by pressing the CLR key on the MCDU.GPS PRIMARY LOST (amber, boxed white) GPS PRIMARY is not available and not clearable.

NOTE: a green (down) arrow is displayed when more than one of these messages are present atthe same time.

10 OFST R(L) XX Flag (yellow) when temporary or an offset flight plan is entered in NM.

12 GPS Flag (green) is displayed when a GPS approach is selected.

11 PRED W/S Flag (amber) when the WINDSHEAR switch on the weather radar is set to AUTO,and a Predictive Windshear System fault is detected appears on the ground or when flaps andslats are extended. A single chime sounds, and the radar image remains available, provided thefault does not affect the radar mode.


TM

Aug 2004page 78

Intentinally left blank


TM

Aug 2004 page 79

EFIS Symbology

NAVAIDS are displayed in:BLUE when tuned and selected for displayMAGENTA when presented on the ND as an option (not

part of the F-PLN)GREEN when the current waypoint of the F-PLNWHITE when the navaid is the TO waypoint

SYMBOL TYPE SYMBOL DEFINITION

Position wherethe A/C willreach

Top of DES

Start of CLIMB

Interceptpoint

Speed change

Deceleratepoint

FCU selected altitude (Blue)

Constrained altitude (Magenta)

DES not armed (White)

DES armed (Blue)

CLB not armed (White)

CLB armed (Blue)

Indicates the point where theA/C meets the FMGC comput-ed vertical profileSelected (White)

Managed (Blue)

Indicates the point where the A/C willinitiate an automatic ACCEL orDECEL from current speed to newcomputed speed in case of SPD,LIM, SPD CSTR or HOLDING SPD(Magenta)

Indicates where the A/C will initiatean automatic DECEL to reach Vapp(When APPR phase starts)(Magenta)

D

Aug 2004page 80


TM

EFIS Symbology (cont)

SYMBOL TYPE SYMBOL DEFINITION

SYMBOL DEFINITION SYMBOL COLOR

Active Flight Plan Route

Secondary Flight Plan Route

Temporary Flight Plan Route

Alternate Flight Plan Route

Missed Approach FlightPlan Route

Engine Out Flight PlanRoute

Pre-Nav Engage PathVector

Airports

Runway Symbol

Tuned ILS

Collocated VORTAC andVOR/DME NAVAID

Collocated Tuned VORTACor VOR/DME NAVAID

VOR NAVAID

Tuned VOR NAVAID

Green(NAV Engaged)(NAV Not Engaged)

White

Yellow

Blue in PlanGreen in ARC or Rose

Blue in PlanGreen in ARC or Rose

Blue (F-PLN Not Active)Green (F-PLN Active)

Green

Magenta

White

Blue

Magenta

Blue

Magenta

Blue

ALT CNST CSTR is predicted to be met (Magenta)

CSTR is predicted to be missed (Amber)

CSTR is not being considered (White)


TM

Aug 2004 page 81

EFIS Symbology (cont)

SYMBOL DEFINITION SYMBOL COLOR

DME NAVAID, i.e. TACAN(no azimuth)

Tuned DME NAVAID (noazimuth)

NDB NAVAID

Tuned VOR NAVAID

Waypoint (option to ND)

Active Waypoint

Left Holding Pattern orProcedure Turn (Not activeor Next Leg)

Right Holding Pattern orProcedure Turn (Not activeor Next Leg)

Left Holding Pattern(Active or Next Leg)

Right Holding Pattern(Active or Next Leg)

Cross Track Error information

Magenta

Blue

Magenta

Blue

Magenta

White

White

White

Green

Green

Yellow/Green2R


TM

Aug 2004page 82



TM

Aug 2004 page 83

Pitot-Static Schematic


TM

Aug 2004page 84

Standby Instruments & TERR ON ND Panel

STANDBY AIRSPEED INDICATOR

AIRSPEED POINTER

AIRSPEED BUGS (4)- provided for marking airspeed reference.

STANDBY ALTIMETER

ALTITUDE COUNTER

ALTITUDE POINTER

BARO-SET COUNTER- display pressure setting in “INHg”.

BARO-SET KNOB- adjusts number in lower window.

TERR ON ND pb (Capt)ON- terrain is displayed on the ND, if TERR sw ON

and FAULT light is not on.OFF- terrain data is not displayed on ND

STANDBY HORIZONROLL SCALE- measures bank angle up to 60°.FLAG- appears if instrument or power supply fails.PITCH SCALE- measures pitch angle.A/C REFERENCE- fixed symbol.CAGING KNOBPull- gyro is erected,- horizon is leveled and centered (airplane

should be level during this procedure).


TM

Aug 2004 page 85

DME 1 (2) WINDOWS

- DME 1 and 2 distances are indicated in NM.

COMPASS CARD

- normally supplied from ADIRU 1,- can be selected to ADIRU 3 by the ATT HD

G SWITCHING Selector.

BEARING POINTERS

- indicate magnetic bearing to the station received byVOR 1 or ADF 1 (narrow or single needle),

- indicate magnetic bearing to the station received byVOR 2 or ADF 2.

VOR/ADF FLAGS

- VOR or ADF receiver failure,- internal failure of RMI,- heading signal from ADIRS invalid,- power supply failure.

VOR/ADF SELECTOR

- selects VOR or ADF on dashed or double pointer.

Digital Distance & Radio Magnetic Indicators

Captain’s Panel

TERR ON ND pbON- terrain is displayed on the ND, if TERR sw ON



TM

Aug 2004page 86

ECAM

Engine Limitations:Max engine start EGT 635°CStart Attempts 3

1st attempt 2 min.2nd attempt 2 min.3rd attempt 1 min(15 sec between attempts- then 30 minute cool)

Max re-engage 10% N2Max oil temp for start; neg 40°Min oil quantity : 13 qtsMin oil press: 60 psiMin oil temp above idel - 10° CMin oil temp for Takeoff 50° C

Max cont oil temp: 155° CMax transient oil temp 165° CMax time in TOGA: 5 min (single eng - 10 min)Max assumed temp for flex TO

ISA + 65° (A319)ISA + 55° (A320 A5)ISA + 46° (A320 A1)

Max EGT for MCT: 610° CMax EPR with parking brake: 1.18Max N1: 100%Max N2: 100%Min speed for full reverse: 60 kts

Engine Control ParametersEPREGTN1N2

TOGA

FUEL QUANTITY INDICATORFUEL FLOWTANK QUANTITYFUEL ON BOARD

FLAPS/SLATS POSITION

MEMO INFORAMTION

FLIGHT PHASE RELATEDSYSTEMS PAGECrusie page in this example.

PERMANENT DATA


TM

Aug 2004 page 87

ECAM (cont)

Primary & Secondary Failures

ACTION LINE SECONDARY(BLUE) FAILURES

(AMBER)(AMBER)

ACTION LINE OVERFLOW(BLUE) SYMBOL

(GREEN)(GREEN)

Primary Failures are identified by a boxed title.Secondary Failures are identified by a star preceding name of affected system.NOTE: overflow symbol will be displayed in case of overflow of sec. failures.

Scrolling of the messages is controlled by depressing the CLR key on the ECAMControl Panel.

Name of anotherindependent failure.

Displayed here in case of overflow.

Independent Failures

Checklists

PRIMARYFAILURE(AMBER(AMBER or RED)

INDEPENDENTFAILURE(AMBER(AMBER or or RED)RED)

ECAMChecklists


TM

Aug 2004page 88

ECAM (cont)

Memo’s

Memo’s are listed on the ECAM as a reminder of temporary components currentlyin use: i.e. LDG LTS, SEAT BELTS, NO SMOKING

Memo’s are normally green, but can be amber in case of an abnormal situation.

Begins when 1st engine is set to TO power and ends crossing 1500 ft. RA or 2 minutes after takeoff.Most critical failures are inhibited durning this phase of flight.

T - O Memo

T - O INHIBIT Memo

TO MEMO appears2 mins after 2ndengine start, orwhen TO CONFIGkey is pressed (atleast 1 engine run-ning)


TM

Aug 2004 page 89

ECAM (cont)

LANDING Memo’s

LANDING INHIBIT Memo

STATUS PAGE

LDG MEMO appearsbelow 2000 ft.if L/G isdown, orbelow 800 ft. if L/G isnot down.Memo disappears aftertouchdown

LDG INHIBIT MEMObegins descendingthrough 800 ft andends when decelerat-ing through 80 kts.Most critical failureswill be inhibited duringthis phase of flight.

Limitations

ApproachProcedures

GeneralInformation

CancelledCautions

InoperativeSystems

MaintenanceStatus

Permanent Data(on all SDpages)


TM

Aug 2004page 90

Landing Gear Panel

LANDING GEAR INDICATOR PANELNOTE: LDG GEAR indicator panel does not illuminatewhen LGCIU is not electrically powered.UNLK lt.- illuminates RED if the gear is not locked in selected

position.- GREEN down indicator when gear is locked downBRK FAN pb swON- brake fans run if the left-hand main gear is down and

locked.OFF- brake fans stopHOT- AMBER light on when brakes get too hot (A caution

ECAM also appears).A/SKID and N/W STRG swON- if green hydraulic pressure available

• Anti-skid is available• Nose wheel steering is available

- if green hydraulic press lost• Yellow hyd press take over automatically• Anti-skid remains available• Nose wheel steering is lost• Brake yellow press is displayed on triple

indicatorOFF- yellow hydraulic pressure supplies the brakes.

• Anti-skid deactivated. Brake pressure hasto be limited by the pilot by referring to thetriple indicator to avoid wheel locking.

• Nose wheel steering lost• Differential braking remains available by

pedals• Yellow brake pressure is displayed on the

triple indicator.AUTO BRAKE pb sw (spring loaded)MAX- normally selected for TO; aborted TO max pressure is

sent to the brakes as soon as ground spoiler deployMED or LO- normally selected for landing.- LO: progressive pressure sent to brakes four sec. after

the ground spoiler deploy (5.6ft/sec sq) deceleration.- MED: increases deceleration to 9.8 ft/sec sq.

• ON illuminates blue for positive arming• DECEL (green) when deceleration at 80%

of selected rate.• OFF: mode deactivated.

TRIPLE INDICATORACCU PRESS indicator- indicates pressure in yellow brakes accumulator.BRAKE PRESSURE indicator- indicates yellow pressure delivered to LH and RH

brakes measured upstream of alternate servo-valves.


TM

Aug 2004 page 91

Clock, TERR ON ND & Landing Gear Panel (cont)

CLOCKCHR pb- FIRST PUSH: starts CHR counter- SEC PUSH: stops CHR counter, keeps display at last

indicationCHRONO (CHR) counter- registers elapsed time from “0” to “99” hrs 59 min.RST pb- counter restarts from “0” if chrono is running.GPS (UTC) selector-time (or date, if selected) is displayed, and date is sync’don GPS information.

NOTE: Signal lost dashes displayed.Signal detected, GPS invalid - clock runs oninternal time.Clock auto sync on GPS info when available.INT: internal time (or date) displayed.- sysn’d with valid GPS- no GPS, 00:00:00 until initialized or valid

GPS information is present.SET: internal time and date initialized

DATE/SET button- FIRST PUSH: sets clock to date mode- SEC PUSH: sets clock to time modeNOTE: to select date, UTC selector must be in GPS

or INT positionUTC (GMT) counter- displays time in 24hr - from “0” to 23hrs, 59min, 59 sec.ET counter- registers flight time from 0 to 99 hrs. 59 mins.RUN/STP/RST selector- RUN: ET counter starts counting- STP: ET counter stops counting- RST (spring loaded): ET counter blanked.NOTE: cumulative elapsed time can be realized by alter-nately setting switch in RUN and STP position.

LANDING GEAR LEVER (green hyd supply)UP- retraction selected- airspeed at 260 knots, pressure is shut off

• interlock prevents unsafe retract by notallowing raising gear lever when eithernose or any main gear strut is not extendedor nose wheel is not centered.

• main gear braked with gear door opening• nose gear braked by brake band.

DOWN- airspeed below 260 kts, green pressure applied to sys.- landing gear extension is selected, the sys remains

pressurized (if green pressure available)RED ARROW- illuminates RED if gear not down and locked in

approach configuration at 750’ RA

TERR ON ND pbON- terrain is displayed on the ND, if TERR sw ON



TM

Aug 2004page 92



TM

Aug 2004 page 93

First Officers Instrument Panel

First Officers Instrument Panel same as the Capatin’s panels


TM

Aug 2004page 94

Center Console Responsibilities


TM

Aug 2004 page 95

MCDU Panel

LINE SELECT KEYS (each side)PUSH-selects or enters data on adjacent line,- selects page, procedure, data or function identified on adjacent line,- if scratch pad blank, copies adjacent data in scratch pad,- if scratch pad contains data, transfers scratch pad data to adjacent line,

replacing previous data on selected line. This is normal method forentering data,

- scratch pad data cannot be moved to blank line,- some data cannot be moved or changed,- scratch pad displays message if inappropriate line selection made.

CDU DISPLAY

PAGE TITLE

PAGE NUMBER

ANNUNCIATORS- FAIL/FMGC

BOXES - require entrypoints

DASHES - data requested

SCRATCH PAD- displays system generated messages forcrew, keyboard entries and data beingmoved from one line to another,- may be blanked by pushing CLR Key

Brightness Knob

FUNCTION KEYS- Direct Key- Progress Key- Performance Key- Initialization Key- Data Key- Flight Plan Key- Radio Navigation Key- Fuel Prediction Key- Secondary Flight Plan Key- MCDU Menu Key- Airport Key- Slew Up Key- Next Page Key- Slew Down Key

ANNUNCIATOR- MCDU MENU

ALPHA NUMERIC KEYS

CLEAR KEY

OVERFLY KEY

INITCO RTE FROM / TO

ALTN RTE ALTN_ _ _ _ _ _ _ _ _ _FLT NBR

LAT LONG_ _ _ _ . _ _ _ _ _ _ . _ _COST INDEX_ _ _ WIND > CRZ FL / TEMP T R O P O_ _ _ _ _ / _ _ _ o 3 6 0 9 0

KMSP/KLGA


TM

Aug 2004page 96

ATT HDG and AIR DATA selectorsNORM- ADIRU 1 supplies data to PFD 1, ND 1 and RMI/VOR, DME

ADIRU 2 supplies data to PFD 2 and ND2.

CAPT 3- DR 3 or IR 3 replaces ADR 1 or IR 1.

F/O 3- ADR 3 or IR 3 replaces ADR 2 or IR 2

OFF/BRT knobs- controls on/off and brightness for each ECAM DU- automatic adjustment of the display intensity with changing lightconditions is combined with manual brightness control.NOTE: When the UPPER DISPLAY knob is turned OFF theengine/warning image is displayed on the lower display. (autotransfer).

ALL pb sw- When pressed all system pagesare displayed successively at 1sec. intervals.- In case of ECAM cont panel fail-ure, the ALL pb allows a succes-sive presentation of a ll pagesand the ability to stop on thedesired page.

ECAM/ND XFR selectorAllows transfer of lower ECAM page to either CAPT or F/O NDU

EIS DMC selectorNORM- DMC 1 supplies data to PFD 1, ND 1 and upper ECAM DU- DMC 2 supplies data to PFD 2 and ND2 and lower ECAM DU

CAPT 3- DMC 3 replaces DMC 1

F/O 3- DMC 3 replaces DMC 2

NOTE: In case of DMC failure, the associated DU’s display a diagonalline.

SWITCHING Panel


TM

Aug 2004 page 97

System pages pb sw- When pressed the lower ECAM DU displays the corresponding system page.- Illuminates after manual selection or when an advisory is detected.- By pressing the illuminated system page pb a second time, the A/C system pagecorresponding to the present flight phase or the current warning come in view.

In mono ECAM display, system pages may be displayed by pressing and holdingthe system page pb sw.

- in case of an advisory condition the concerned system page is not automatically displayed, the system page pb sw only pulses.

- there is no automatic system page display, nor system page pb sw illumination, in the event of an ECAM warning triggered.

STS pb sw- Illuminates when pressed as long as the STS page is displayed on the lowerECAM DU. If there is no status message present, “NORMAL” is displayed for 5 sec.The STATUS page may be cleared by the CLR pb or by depressing the STS pb asecond time. - the STATUS page is only displayed when the STATUS pb is pressed and held. thenext page, if any, is displayed by pressing it again.- holding the STS pb displays the STATUS page for a 30 sec max, then the EngineWarning page is automatically displayed.RCL pb sw- recalls messages which have been previously cancelled. If not warning/cautionmessages present, NORMAL is displayed for 5 sec. When held for more than 3 sec.the caution messages suppressed by the EMER CANC pb are recalled.CLR pb sw- is illuminated as long as a warning/caution message or status message is pres-ent on the ECAM DU - pressing it will change the ECAM display

TO CONFIG pb sw- When depressed a TO power application is simulated. This test will trigger a warningif the aircraft is not in TO configuration. If the configuration is correct, the message “TOCONFIG NORMAL” is displayed on the upper ECAM DU.NOTE: In case of ECAM control panel failure, the CLR, RCL, STS, EMER CANC andALL pb sw remain operative since the contacts are directly wired to the FWCs/DMCs.

EMER CANC pb swPRESSED- Any present aural warning is cancelled as long as the failure condition is present. TheMASTER WARNING lights extinguish and the ECAM message display is not affectedby the EMER CANC pb sw.- Any present caution (single chime, Master Caution lights, ECAM message) is can-celled for the rest of the flight. The STATUS page is automatically displayed and thefollowing messages is presented:“CANCELLED CAUTION” & “ TITLE OF THE FAILURE WHICH IS INHIBITED”The inhibition is automatically suppressed when flight phase 1 is initiated. It may bemanually restored by pressing the RECALL pb for more than 3 sec.

ECAM Control Panel


TM

Aug 2004page 98

Radio Management & Audio Control Panel

Both panels - Capt’s and F/Os areidentical to those on the pilot’s overhead panel

shown on page


TM

Aug 2004 page 99



TM

Aug 2004page 100

Thrust Control System

IDLE

REVERSE

A/THR OPERATING

A/THR OPERATING

RO AROUND (GA)

MAX CONT. (MCT)

MAX CLIMB (CL)

IDLE

RE

V I

DLE

MAZ

REVER

SE

THRUST LEVERS- the thrust levers can only be moved manually.- they move over a sector that is divided into four operating segments.- the sector has five positions defined by detents or stops.- thrust lever position is transmitted to the FADEC, which computes and

displays the thrust rating limit and the N1 for that Thrust Lever Angle (TLA).

NOTE: there is no reverse ident. When the pilot moves the lever out of theidle stop by pulling up the reverse lever on the front of the thrustlever, he selects reverse idle.

The FADEC computes the thrust rating limit for each thrust lever position. Ifthe thrust lever is set in a detent, the FADEC selects the rating limit corre-sponding to this detent.If the thrust lever is set between two detents, the FADEC selects the ratinglimit corresponding to the higher detent.


TM

Aug 2004 page 101

Thrust Lever & Trim Quadrant

PITCH TRIM WHEELS- (BOTH WHEELS) provide mechanical control of the THS and have priority over electricalcontrol.NOTE: Crew action on pitch trim wheel does not disconnect the ELAC’s (Microswitchesactuated by the override mechanism ensure that the computers remain synchronized withthe manually selected position).

Trim position is indicated in degrees on a scale adjacent to each trim wheel. the THSmechanical control must be used when pitch direct law is in use.

After landing, pitch trim is automatically reset to “0” as the pitch attitude becomes less than2.5 degrees (confirmed 2.4 sec).

THRUST LEVERSThe Thrust Levers are used as a thrust limit selector and as a classical thrust setting lever.The respective positions are:- Takeoff/Go-Around (TOGA)- Max continuous/flexible takeoff (FLEX/MCT)- Climb- Forward Idle- Reverse Idle- Full Reverse Thrust

NOTE: the thrust levers don’t move when autothrust function is selected.


TM

Aug 2004page 102

FROM FUEL TANK

LP FUELSHUTOFF

VALVE

LPPUMP

IDG COOLING

OIL IN

OIL OUT

TO TANK

20 FUELINJECTORS

Engine Fuel Schematic


TM

Aug 2004 page 103

Engine Oil Schematic

OIL PRESS

OIL LOWPRESS

(set at 60 psi)

FUEL OUTFUEL IN

FUEL / OILHEATEXCHANGER

TO BEARINGS ANDGEARBOX

SCAVENGE PUMPS

MAIN SCAVENGEFILTER

(20 psi)

BYPASSOILQTY

OILCLOG

ENG OILTEMP

AIR / OILHEAT

EXCHANGER

OIL FILTER

OIL SUPPLYPUMP


TM

Aug 2004page 104

FLOOD LT MAIN PNL KNOB- Brightness adjustment of main panel flood lighting.

INTEG LT MAIN PNL & PED KNOB- Brightness adjustment of main panel and pedestal integral lighting.

FLOOD LT PED KNOBBrightness adjustment of pedestal flood lighting.

AIDS PRINT PB

DFDR EVENT PB- Pressed (momentarily) sends an event mark to the DFDR.

1

2

2

3

3

4

4

5

5

1

INTERNAL LIGHT Panel


TM

Aug 2004 page 105

MODE sel- WX: weather mode: colors indicate the intensity of precipitation (black for

lowest intensity, green, amber and red indicating progressively higherintensities.

- WX+T: the screen shows turbulence areas (in precipitation area) in magenta(within 40 NM).

- TURB: the screen shows only turbulence areas.- MAP: radar operates in ground mapping mode: black indicates water, green

indicates ground, and amber indicates cities and mountains.

SYS switch- turns radar on or off.

GND CLTR SPRS sw- ON: suppresses the ground echo on the screen.- OFF: normal use of the radar.

GAIN knob- sdjusts sensitivity of transceiver in all modes- CAL is normal position; adjusts gain to calibrated setting

PWS switch (operative only if predictive windshear function is embodied)- OFF: no predictive windshear function- AUTO: predictive windshear function is activated:

windshear areas are detected by antenna scanning below 2300 feet RA,even if the SYS switch is set to OFF, and displayed on the ND is below1500 feet.

TILT knob- controls antenna tilt.- “0” represents horizon as seen by ADIR

WEATHER RADAR Panel


TM

Aug 2004page 106

MASTER sw 1 or 2ON:- in automatic start, the LP fuel valve opens provided: MODE set at

IGN/START- in manual start, the HP fuel valve opens provided:

MODE switch selected to IGN START andMAN START pb sw selected to ON

OFF:- closed signal sent directly to HP and LP fuel valves.- controls the reset of both channels of the FADEC.

FIRE/FAULT light 1 or 2FIRE: - illuminates RED when a fire warning is activatedFAULT: - illuminates AMBER with ECAM caution during:

- automatic start abort- disagreement with HP fuel valves commanded position- start valve fault

MODE selectorCRANK: - start valve opens provided MAN START pb is

ON and N2 < 10%.- no ignition is provided

NORM: - continuous ignition of both A + B igniters auto-matically activated when ENG ANTI-ICE isselected ON

- or when the EIU fails- or if flame out is detected.

IGN/START:- continuous ignition is activated provided

- MASTER sw is ON and- N2 < 16% for Autostart, or- MAN START pb sw at ON for

manual start, or- N2 > idle (continuous ignition)

- both pack valves automatically close provided:1. A/C is on ground2. Either MASTER sw is ON (or manual

start selected)3. Corresponding engine N2 is below idle

ENGINE CONTROL Panel

INITIAL CONFIG OFTHE CONTROLS(engine not running)

- START IDENT:ECAM displays ENGpage.

- PACK VALVEcloses.

- LP fuel valve opens.- START VALVE

opens.- After the auto dry

crank sequence(approx 30 - 50 sec*)

•Ignition starts.•HP fuel valve opens

- When N2 > 43%• START VALVE

closes.• Ignition stops.• PACK VALVE reopen

after 30 seconds.

-ECAM ENG pagedisappears.

- After engine start, moving the MODE SELsw. to NORM and backto IGN/STARTactivates cont. relighton running engine.

Further Start RequiresPanel Reconfiguration

ENG MAN STARTpb OFF

• LP & HP Fuel ValveVavle Closes.

• Ignition Stops.• Start Vavle Closes.


TM

Aug 2004 page 107

IGNITION - Automatic Starting Sequence

* depending of aircraft tail number


TM

Aug 2004page 108

IGNITION - Manual Start Sequence

INITIAL CONFIG OF THECONTROLS(engine not running)

- START IDENT:ECAM displays ENGpage.• PACK VALVE

closes.

• START VALVEopens.

• APU speed (if APUused) increases

• Both igniters come on• LP & HP fuel valves

open.• When N2 > 43% start

valve closes and, (if onground) ignition stops.

• APU speed returns to normal (if APU used).

• PACK VALVES reopenafter 30 seconds.

• ECAM ENG pagedisappears.

30 - 50 sec* after ENGMAN START is set ot

the ON position,switch ENG master

sw ON

Select MAN START OFFand MODE NORM

when N2 > 43%

SELECTED OFF

SELECTED OFF

SELECTED OFF

SELECTED OFF

SELECTED OFF

STARTING INTERRUPTION

NOTE: if the ENG MAN START pushbutton is not switched ONafter 30 seconds, then the pack valves will open.

STARTING INTERRUPTION

FU

RT

HE

R S

TAR

T R

EQ

UIR

ES

PAN

EL

RE

CO

NF

IGU

RA

TIO

N

ENG MANSTART

ENG MANSTART

ENG MANSTART

ENG MANSTART

ENG MANSTART

ENG MANSTART

ENG MANSTART

* depending of aircraft tail number


TM

Aug 2004 page 109

ATC panelALT RPTG sw- ON: barometric standard altitude date is sent- OFF: no altitude data sent. With TCAS installed, upper ECAM

displays TCAS STBY in green.ATC sel- selects transponder 1 or 2Mode sel- STBY: both transponders are in standby mode.- ON: selected transponder operates- AUTO (in flight): selected transponder operates- AUTO (on ground): selected transponder operates only in mode SCode display- displays selected code.ATC FAIL- illuminates when selected transponder fails.

Keyboard- used to set codeCLR pb- used to clear displayNOTE: as long as the four digits of the new code are notentirely written, previous code remains.TRAFFIC selTHRT: proximate and other intruders are displayed only if a TA or RA is present and theyare withing 2700 feet above ore below the aircraft.ALL: proximate and other intruders are displayed enven if no TA or RA is present (full timefunction). Altitude range is - 2700 feet to + 2700 feet.ABV: identical to ALL, except that other intruders are displayed if within 9900 feet abovethe aircraft and 2700 feet below.BLW: identical to ALL, except that other intruders are displayed if within 9900 feet belowthe aircraft and 2700 feet above.IDENT sw- selected to send aircraft identification signal.Mode selTA/RA: normal positionTA: TCAS will not generate any vertical orders. All RAs are donverted to TAs. TAs proxi-mate and other intruders are displayed, if the ALT RPT switch is ON and the transponderis not on STBY. TA ONLY (white) memo is displayed on the NDsSTBY: TCAS is in the standyb mode.

ATC Panel


TM

Aug 2004page 110

SPEEDBRAKE leverLever- controls position of speedbrake surfaces- manual preselection of ground spoilers.* push down to selected position

- hard point at 1/2 position* to arm lever pulled up when in RET position

- when lever armed, or reverse thrust selected, all spoilers on theupper wing will automaticallyextend on landing or in case ofa rejected takeoff.

RUDDER TRIMPOSITION indicator- displays trim direction (L or R) and value

(0 to 20 degrees).Selector- controls trim actuator moving neutral point of

artificial feel by 1 degree per second ofrudder travel.

RESET pb- PUSH: resets trim actuator to zero trim.

FLAPS lever- selects simultaneous operation of slats & flaps.Takeoff in conf 1- 1 + F (10/18). If conf. 0 is not selected after TO,

the flaps automatically retract at 210 kts.Takeoff in conf 2 or 3- at conf 1 selection: 1 + F (18/10) if speed <210

kts. If conf 0 is not selected after TO, flapsautomatically retract at 210 kts.

0 to 1 in flight- 1 (18/0)NOTE: Position 1 + F (18/10) is only avail-

able at takeoff.When speed > 210 kts, only position1 (18/0) will be available during theflight.(The reset of position 1 + F occursat 100 kts.)

Speedbrake, Rudder Trim & Flap Lever


TM

Aug 2004 page 111

Normal Computer Control


TM

Aug 2004page 112

Elevator / THS Architecture


TM

Aug 2004 page 113

Speedbrake & Roll Schematic


TM

Aug 2004page 114

Rudder Schematic


TM

Aug 2004 page 115

Flaps & Slats Schematic

Flaps / Slats max altitude: FL200


TM

Aug 2004page 116

ECAM F/CTL Display

HYDRAULIC SYSTEM Pressure Indication- normally green - changes to amber if pressure in the system low.

SPOILER/SPEED BRAKES Indication- spoiler deflection more than 2.5°- spoiler retracted (as shown)- spoiler fault deflected- 1 spoiler fault retracted

AILERON POSITION Indication- white scale & green index - changes to amber when neither (green nor blue) servo jack

is available.- top tick = neutral position in clean configuration,- bottom tick neutral position when flaps are extended (5° aileron droop).

AILERON and ELEVATOR ACTUATOR Indication- “G” and “B” are normally green - changes to amber when:

• corresponding actuator is not available (low hyd press, jamming, computerfailure, etc.)

• the partial box also changes to amber if the associated computer fails.

ELAC/SEC Indication- normally green - changes to amber if:

• there is a failure in the ELAC or the SEC,• if ELAC or SEC pushbutton is OFF,• if both flight control data concentrators (FCDCs) fail.

- surrounding box is normally grey - changes to amber if ELAC or SEC change to amber.

1

2

5

1

3

4

2

3

4

5


TM

Aug 2004 page 117

ECAM F/CTL Display

1

2

3

4

5


PITCH TRIM Position Indication- PITCH TRIM is white - changes to amber if there is a pitch trim jam,- numbers are green - change to amber if the hyd press gets low in the G and Y Systems.

AILERON and ELEVATOR ACTUATOR Indication- “G” and “B” are normally green - changes to amber when:

• corresponding actuator is not available (low hyd press, jamming, computerfailure, etc.)

• the partial box also changes to amber if the associated computer fails.

ELEVATOR Position Indication- white scale and green index - index changes to amber when both associated actuators

are not available.


YAW CONTROL IndicationsRUDDER Position Indication

- normally green,- symbol and scale become amber if all (GBY) hydraulic system pressure is low .

RUDDER Travel Limiter (white tick either side of rudder trim position)- indication of high-speed position.

RUDDER Trim Position- normally blue - changes to amber if rudder trim reset fails.

6

1

2

3

4

5

6


TM

Aug 2004page 118

COCKPIT DOOR toggle switchUNLOCK position:- this position used to enable the cabin crewmember to open the door.

The switch must be pulled and maintained in the unlock position untilthe door is pushed open.

NORM position:- all latches are locked, and EMERGENCY access is possible for the cabin

crew.LOCK position:- once button has been moved to this position, the door is locked;

emergency access, the buzzer and the keypad are inhibited for a preselected time (5 to 20 Minutes).

NOTE: 1. if the LOCK position has not been used by the pilot, for atleast 5 to 20 minutes, the cabin crew is able to requestemergency access to open the cockpit door.2. the UNLOCK position overrides and resets any previousselection.3. in case of an electrical supply failure, the cockpit door isautomatically unlocked, but remains closed.

COCKPIT DOOR Fault Open indicatorOPEN light ON:- the door is not closed or not locked.OPEN light flashes:- the cabin crew has started an emergency access procedure. If there is no

reaction from the flight crew, the door will unlock at the end of the adjustable time delay (15 to 120 seconds).

FAULT:- this light comes on when a system failure has been identified (Example:

Latch, pressure sensors, control unit). - the inoperative item can be identified by checking the strike and pressure

sensor status lights on the CKPT DOOR CONT panel.

COCKPIT DOOR Panel

FAULT


TM

Aug 2004 page 119

PARKING BRAKEON - clockwise (top picture OFF)- activation parking brake deactivates all of the

braking modes.- <<PARKING BRAKE ON>> displayed on

ECAM memo page.

NOTE: it is not necessary to step on the rudder pedals to set the brakes.

Max brake temp for TO: 300° CMax tire speed : 195 kts.

GRAVITY GEAR EXTNPULL & TURN- pull and turn three times CW

* cut off valve is closed* gear door uplocks released* gear uplocks are released

PRINTERDOOR LATCH- locks printer front door used for paper loading.SLEW switch- used to feed paper after loading a new roll

NOTE: all reports printing selected throughthe MCDU’s.

PARK BRK, GEAR EXTN & Printer


TM

Aug 2004page 120

First Officer & Observers MasksCaptain’s (single Mask identical)

CREW OXYGEN MASKSBlinker- flashes yellow when oxygen is flowing

RESET/TEST control slidePULL in direction of arrow- tests:

* operation of blinker* regulator supply and sealing* system sealing downstream of

the valve, * system operation

- RESET: after masks has been used, cuts offoxygen mask microphone.

N/100% selector100%:- mask delivers 100% O2- system is locked in this positionN- mask delivers diluted O2.- this config reached by simultaneously

activating the UNLOCK lever and theN/100% selector

RED clips- squeezing clips unlocks the two-flap door and

initiates harness inflation.


TM

Aug 2004 page 121

ENHANCED GROUND PROXIMITYWARNING SYSTEM

The Ground Proximity Warning System (EGPWS) generates aural and visual warnings when one of the fol-lowing conditions occurs between radio altitudes 30 feet and 2450 feet.

EGPWS Modes• Mode 1 - Excessive Descent Rate• Mode 2 - Excessive Terrain Closure Rate• Mode 3 - Altitude Loss After Takeoff or Go-Around• Mode 4 - Unsafe Terrain Clearance when not in landing configuration.• Mode 5 - Too Far Below Glide Slope

Terrain Awareness Alerting and Display (TAAD) - provides a graphic display of the surrounding terrain onthe weather radar indicator or EHSI. With the radar ON, the terrain display may be manually selected or “Pop-Up” automatically during an alert event.

“Peaks” - is a TAAD supplemental feature providing additional terrain display features for enhanced situationalawareness, independent of the aircraft’s altitude, such as in cruise. This includes digital elevations for the high-est and lowest displayed terrain.

“Obstacles” is a feature utilizing an obstacle data base for obstacle conflict alerting and display. EGPWS cau-tion and warning visual and audio alerts are provided when a conflict is detected. Additional, when TAAD is on,obstacles are graphically displayed similar to terrain.

Terrain Clearance Floor (TCF) is a feature that adds an additional element of protection by alerting the pilotof possible premature descent.

The flight deck loudspeakers broadcast, even if turned off, the aural warning or caution messages associatedwith each mode. The uadio volume of these messages is not controlled by the loudspeaker volume knobs.(These knobs allow adjustment for radio communications only).

GPWS lights come on to give a visual warning for modes 1 - 4. For mode 5 the glideslope (G/S) lights illumi-nate on the Captain’s and First Officer’s instrument panels.

NOTE: A number of airporst throughout the world have approaches or departures that are not entirely com-patable with standard GPWS operation. These airports are identified in the data base in such a way that whenthe GPWS recognizes such an airport, it modifies the profile to avoid nuisance warnings.

EGPWS

The following illustrates the Peaks displayat a low relative altitude.

The following illustrates the Peaks displayat a high relative altitude.


TM

Aug 2004page 122

GPWS - Mode 1

MODE 1 - EXCESSIVE DESCENT RATE

Mode 1 has two boundaries and is independent of airplane configuration. Penetrationof the first boundary generates a repeated aural alert of “SINK RATE”. Penetrating thesecond boundary causes the repeated aural warning “ PULL UP”.

MODE 1 - EXCESSIVE DESCENT RATE

FLIGHT PATH PROFILE - - - - - - - - - - - EXCESSIVE DESCENT RATE ENVELOPE

Aural warning - “Whoop whoop pull up”

Aural alert - “Sink rate, sink rate”

Visual -


TM

Aug 2004 page 123

GPWS - MODE 2

MODE 2A - EXCESSIVE TERRAIN CLOSURE RATE WITH FLAPS NOT IN LANDING POSITION

FLIGHT PATH PROFILE- - - - - - - - - - - - - - - - - - - - - EXCESSIVE TERRAIN CLOSURE RATE ENVELOPE

Aural warning - “ Pull up”

Aural alert - “Terrain, terrain”

Visual -

MODE 2B - EXCESSIVE TERRAIN CLOSURE RATE WITH FLAPS IN LANDING POSITION

FLIGHT PATH PROFILE- - - - - - - - - - - - - - - - - - - - - EXCESSIVE TERRAIN CLOSURE RATE ENVELOPE

Aural alert - “Terrain, terrain” followed by “PULL UP” if aircraft remains in the envelope.

Visual -


TM

Aug 2004page 124

MODE 3 - ALTITUDE LOSS AFTER TAKEOFF OR GO-AROUND

FLIGHT PATH PROFILE- - - - - - - - - - EXCESSIVE ALTITUDE LOSS AFTER TAKEOFF OR GO-AROUNDENVELOPE

Aural warning - “Don’t sink”

Visual - - -

GPWS - Mode 3


TM

Aug 2004 page 125

GPWS - Mode 4

MODE 4A - UNSAFE TERRAIN CLEARANCE WITH LANDING GEAR NOT DOWN AND FLAPS NOT INLANDING POSITION

FLIGHT PATH PROFILE- - - - - - - - - - - - - - - - - - - - - - - - - - UNSAFE TERRAIN CLEARANCE ENVELOPE

Aural warning - “Too low gear” or “Too low terrain”

Visual - -

MODE 4B - UNSAFE TERRAIN CLEARANCE WITH LANDING GEAR OR FLAPS NOT IN LANDINGPOSITION

FLIGHT PATH PROFILE- - - - - - - - - - - - - - - - - - - - - - - - - - UNSAFE TERRAIN CLEARANCE ENVELOPE

Aural warning - “Too low flap”, “Too low gear”, or “Too low terrain”

Visual - -


TM

Aug 2004page 126

GPWS - Mode 4 (continued)

MODE 4C - TO CLOSE TO TERRAIN

FLIGHT PATH PROFILE- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - TO CLOSE TO TERRAIN ENVELOPE

Aural warning - - - - - “Too low - Terrain”

Visual - -


TM

Aug 2004 page 127

GPWS - Mode 5

MODE 5 - BELOW GLIDE SLOPE DEVIATION CAUTION

FLIGHT PATH PROFILE- - - - - - - - - - - - - - - - - - - - - - - - - BELOW GLIDE SLOPE DEVIATION ENVELOPE(armed when ILS 1 receives a valid signal)

Aural warning - - - - - “Glide slope”

Visual - - both lights illuminate


TM

Aug 2004page 128



TM

Aug 2004 page 129

IndexACARS Printer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p 119ADF Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p.107ADIRS Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 06Aileron Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 111

Aileron Trim Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p.112Airconditioning Panell . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 30

Airconditioning Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 32Anti-Ice Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 37

Wing & Eng Anti-Ice Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 38Window & Probe Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 39

Arm Rest . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 63ATC Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 109Audio Selector Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 47Audio Switching Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04APU EXT FIRE Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 15APU Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 44

APU Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 44APU Test pb & Reset pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04AVIONICS COMPT LT pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04BLUE PUMP OVRD pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04CABIN PRESS Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 40CALLS Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 13CARGO SMOKE Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 49

Cargo Compt Fire Detection Schematic . . . . . . . . . . . . . . . . . . . . . .p. 50Cargo Compt Fire Protection Schematic . . . . . . . . . . . . . . . . . . . . . .p. 51

Center Console . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 94Circuit Breakers (Ovhd) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 03Clock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 91Cockpit Door Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 03Cockpit Door Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 118CVR Headset Jack . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04CVR Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 10Digital Distance Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 85ECAM Display

(Air) COND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 33APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .P. 45BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 35CAB PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 41Checklists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 87CRUISE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 42Door/Oxy . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 11


TM

Aug 2004page 130

IndexECAM (continued)

Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 27Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 86F/CTL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 116Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 22Independent Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 87Memo’s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 88Primary & Secondary Failures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 87Status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 89

ECAM Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 97ELEC Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 24

Electrical Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 26EXT LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 43Hydraulic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 18EFIS Symbology . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 79Elevator Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 112EMER ELEC PWR Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 08Engine Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 106

Automaic Start Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 107Manual Start Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 108

Engine FADEC GND PWR pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04Engine Fuel Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 102Engine Oil Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 103ENG Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 54

MAN START . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 54N1 Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 54

EVAC Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 07FIRE Panels (Engine & APU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 14

Fire Schematic (Engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 15Flap Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 110

Flap & Slats Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 115FLT CTL (left) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 07FLT CTL (right) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 49

Normal Computer Control (ELAC) . . . . . . . . . . . . . . . . . . . . . . . . . .p. 111FUEL Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 20

Fuel Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 21Fuel Tanks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 22 Fuel Quantities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 22

GPWS Panel (EGPWS) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 09EGPWS Modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 121

Glareshield . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 56


TM

Aug 2004 page 131

IndexGEAR EXTN (Gravity) Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 119HYD Leak Measurement Valves . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04HYD Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 16

Hydraulic Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 17INT KT & SIGNS Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 46Internal Light Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 104Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 61

Captains . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 63Landing Gear Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 90MCDU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 95Navigation Display (ND) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 72

Rose ILS, Rose VOR, Rose Nav, Arc & Plan . . . . . . . . . . . . . . . . . .p. 74Weather Radar and TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 75ND Flags . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 76

Oxygen Mask Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 120Oxygen Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 05Oxygen TMR Reset pbl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 05lPARK BRK Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 119Primary Flight Display (PFD) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 64

PFD Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 66PFD Flags . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 70PFD Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 67

Pilots Overhead Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 05Pitot-Static Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 83Pneumatic Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 34Radio Magnetic Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 85Radio Management Panel (Ovhd) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 48Reading Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 03Rudder Trim Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 110

Rudder Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 114Side Stick . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 62Speed Brake Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 110

Speedbranke & Roll Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 113Standby Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 84SVCE INT OVRD pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 04SWITCHING Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 96Symbology & Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 68TERR ON ND Panel (Capt) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 84TERR ON ND Panel (F/O) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 91Thrust Contol System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 100Thrust Lever & Trim Quadrant . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 101


TM

Aug 2004page 132

IndexTiller . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 62VENTILATION Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 52

Ventilation Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 53Weather Radar Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 105Wet Compass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .P. 56WIPER Panel (left) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 13WIPER Panel (right) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .p. 55


TM

Aug 2004 page 133


TM

Aug 2004page 134