systems 42 72pec 1.0 copy

8/16/2019 Systems 42 72PEC 1.0 Copy

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42-500 72-212A


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IntroductionThis Systems guide is an essential tool for all ATR flight crew and engineer to learn or review ATR systems operation. To make learning process easier, systems areintroduced in a user-friendly and efficient training method, including diagram and

schematic display as appropriate.

This guide is a comprehensive document that efficiently complements FC ! " st part # Systems description . Systems are organi$ed as per FC ! chapter, including their ATAclassification along with cockpit location. Cockpit panels familiarisation is presented witheach relevant system description in a separate anne%.

This new guide release is intended for training on ATR &'-()) and *'-'"'A. +t presentsa generic aircraft not customi$ed to your own aircraft systems. Should you find anydiscrepancy etween Systems guide and your customi$ed ATR operationaldocumentation AF!, FC ! /R01, the latter takes precedence.

234 This Systems guide is also availa le for ATR &'-5)) and *'-')) not 67C. This document willalso e developed for the ATR-8)).

The Training and Flight perations support team.


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p. 1


4/171Content p. 2

Chapter A. Aircraft general". Doors location ..................................................................................................................... *'. Cargo door panel ................................................................................................................. 95. Doors panel ......................................................................................................................... 9&.External lights ..................................................................................................................... :(. EXT T panel ..................................................................................................................... ")!. "emo panel ....................................................................................................................... ")#. $igns panel ....................................................................................................................... ")9. Internal lighting ................................................................................................................. ""%. T panel ............................................................................................................................. "'"). A&& T panel ................................................................................................................... "'11. $ide panel ....................................................................................................................... "'"'. ' T C(")T T panel ............ .............. .............. .............. .............. .............. ........... ..... ..... . "'

Chapter *. "ulti 'unction Computer .............. .............. ......... ..... ..... ..... ...... ..... "5

Chapter C. Centrali+ed Cre, Alerting $ystem". Coc-pit philosophy ............. .............. ............. .............. .............. ........... ..... ..... ...... ..... ...... . "8'. CCA$ description ............. .............. .............. .............. .............. .............. .............. ..... ..... ... "*5. Cre, alerting panel .............. .............. .............. .............. .............. .............. .............. ......... . "9&.E"ER audio cancel T( Config test ............. .............. .............. .............. ..... ...... ..... ...... .... ":(. Aural alarms ...................................................................................................................... ')

Chapter D. Air ". )neumatic system ............................................................................................................. ''

1.1. $chematic ................................................................................................................... ''

".'. AIR * EED panel .............. .............. .............. .............. .............. ........... ..... ..... ..... ...... .. '5'. Air conditioning ................................................................................................................. '&

2.1. $chematic ................................................................................................................... '&'.'. C(")T TE") panel ............ .............. .............. .............. .............. ........... ...... ...... ..... .... '(

5. A/ionics /entilation ........................................................................................................... '80.1. $chematic ................................................................................................................... '85.'. A I(&IC$ E&T panel .............. .............. .............. .............. .............. .............. ....... ...... '8

&.)ressuri+ation ................................................................................................................... '*.1. $chematic ................................................................................................................... '*

&.'. Ca3in pressure indicators ............ .............. .............. .............. .............. ...... ..... ..... ..... .. '9&.5. Auto4press panel ............. .............. .............. .............. .............. .............. .............. ....... . '9&.&."A& RATE 5no3 Ca3in press panel .............. .............. .............. ....... ...... ..... ...... ...... . '9

Chapter E. Automatic 'light Control $ystem1. $chematic ......................................................................................................................... 5)2. AD6 .................................................................................................................................. 5"5. A'C$ control panel ............. .............. .............. .............. .............. ........... ..... ..... ..... ..... ...... . 5"

Chapter '. Communications1. $chematic ......................................................................................................................... 55'. )TT selector &($E 78EE $TEERI&9 C(&TR( s,itch .............. .............. ...... ..... ...... .. 55

5. Audio control panel ............ .............. .............. .............. .............. .............. .......... ..... ..... ..... 5&. 8' ................................................................................................................................... 5&

(. A6DI( $E p3 ................................................................................................................... 5&8. oudspea-er /olume -no3s ............ .............. .............. .............. .............. .............. ......... .... 5&

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*. TCA$ control 3ox ............. .............. .............. .............. .............. .............. ....... ..... ..... . 5(9. E"ER (C X"TR panel ............. .............. .............. .............. .............. ............. ..... ..... 5(:. Ca3in attendant handset ............ .............. .............. .............. .............. .............. ......... 5(").................................................................................................... 8andmi-e handset 5(""................................................................................................................ CA $ panel 5(

"'.................................................................... 8ead set : *oom set : 8and mi-e panels 58"5....................................................................................................................... ATC 3ox 58"&.................................................................................................................... C R panel 58"(....................................................................................................... Cre, oxygen mas- 58

Chapter 9. Electrical $ystems". $ources of po,er ............ .............. .............. .............. .............. .............. ....... ..... ..... ..... ..... . 59'. DC4AC schematic ............ .............. .............. .............. .............. .............. ....... ..... ..... ..... ..... . &)

'.". &ormal supply; (n ground ,ith 3attery only ............. .............. .............. .............. ........ . &)'.'. &ormal $upply; (n ground ,ith external po,er .............. .............. .............. .......... ..... .. &"'.5. 8otel mode or DC 9E& 1 'A6 T ............ .............. .............. .............. .............. ............ ... &''.&. &ormal supply; ,ith t,o generator on line .............. ............. .............. .............. ......... ... &5'.(. Emergency supply; In dual DC 9E& ($$ ,ith the 3attery toggle s,itch on ( RD ...... &&2.!. Emergency supply; In dual DC 9E& ($$ ,ith the 3attery toggle s,itch on ( RD

and second ( RD selected ............. .............. .............. .............. .............. ...... ..... ..... .... &('.*. Emergency supply; In dual DC 9E& ($$ ,ith TR6 .............. .............. .......... ..... ...... ... &8

5. DC4AC panel ............. .............. .............. .............. .............. .............. ............. .............. ....... . &*&.AC7 schematic ............ .............. .............. .............. .............. .............. .............. ...... ..... ..... . &9(. AC7 panel ........................................................................................................................ &:8. *rea-ers panels ............. .............. ............. .............. .............. .............. ...... ..... ...... ...... ..... .. ()

8.". (/erhead panel ............. .............. .............. .............. .............. .............. .............. ..... ..... ()

8.'. Electric rac- 3ehind ':( .............. .............. .............. .............. .............. ......... ...... ..... .... ()

Chapter 8. Emergency e


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5. 'ire handle ........................................................................................................................ (9

&.Compartment smo-e panel .............. .............. .............. .............. .............. .............. ...... ..... ..... ..... (9(. Condition le/ers fuel light ........................................................................................................... (9

Chapter >. 'light control

". Roll schematic ................................................................................................................... 8)'. )itch schematic ................................................................................................................. 8)5. ?a, schematic ................................................................................................................... 8"&.9ust loc- ........................................................................................................................... 8"(. $tic- $ha-er:$tic- )usher push 3utton and light ............. .............. .............. .............. ...... ... 8"8. $poilers position indicator ............ .............. .............. .............. .............. .............. ........... .... 8'*. )itch trim asym light .............. .............. .............. .............. .............. .............. .............. ....... . 8'9. Trim position indicator .............. .............. .............. .............. .............. .............. .......... ...... ... 8':. Trim controls ..................................................................................................................... 8'"). 'laps schematic .............................................................................................................. 85"". 'laps position indicator ............. .............. .............. .............. .............. .......... ...... ..... ...... ... 85

"'. 'laps control le/er ............. .............. .............. .............. .............. .............. ............. ..... ..... . 85

Chapter 5. 'light instruments". $chematic ......................................................................................................................... 8('. EADI .................................................................................................................................. 885. E8$I .................................................................................................................................. 88&.E8$I ,ith composite mode ............. .............. .............. .............. .............. ............. ..... ..... .... 8*(. E8$I 4 ARC "(DE ,ith terrain or ,eather radar information .............. ......... ..... ..... ..... ...... .. 8*8. $ource failure alert ............................................................................................................ 8**. $ources s,itching panel ............. .............. .............. .............. .............. .............. .............. ... 899. E'I$ control panel ............................................................................................................. 89:. 7eather radar control .............. .............. .............. .............. .............. .............. ......... ..... ..... . 8:

:.". )rimus @ .................................................................................................................. 8::.'. )rimus !! .................................................................................................................. 8:

"). A8R$ erect )* ................................................................................................................ 8:"". TAT:$AT indicator ............................................................................................................. *)"'. Cloc- ............................................................................................................................... *)"5. RCDR panel ..................................................................................................................... *)"&. $T*? instruments ............. .............. .............. .............. .............. .............. ............. ........... . *)"(. Airspeed indicator ........................................................................................................... *""8. Altimeter .......................................................................................................................... *"

"*. R"I .................................................................................................................................. *""9. 'light data entry panel .............. .............. .............. ............. .............. ............. ...... ..... ...... .. *'":. TCA$ /ertical speed indicator ............. .............. .............. .............. .............. ............ ..... .... *'

Chapter . 'uel system". $chematic ......................................................................................................................... *&'. $tarting procedure ............. .............. .............. .............. ............. .............. .............. ............. *(5. &ormal procedure .............................................................................................................. *8&.Crossfeed procedure ............ .............. .............. .............. .............. .............. ........... ..... ..... .. **(. Engine feed =et pump lo, pressure .............. .............. .............. ............. .............. ...... ...... ... *98. o, le/el ........................................................................................................................... *:*. Engine fire procedure ............ .............. .............. .............. .............. .............. ......... ..... ..... ... 9)9. 'uel panel ......................................................................................................................... 9":. 'uel BT? panel .................................................................................................................. 9"

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"). X'EED ad/isory light ............ .............. .............. .............. .............. .............. .......... ..... ..... . 9"


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Chapter !. 0ydraulic". Schematic ........................... ............................ ......................... ........................... ........... 95'. 0;< 6=R panel ............. .............. .............. .............. .............. .............. ....... ..... ..... ...... ..... .. 9&5. 6ressure indicator ....................... .......................... ............................ ...... ....... ....... ....... .. 9&&. A>? pump pedestal switch ........................................................................... ........... 9&

Chapter 2. +ce and rain protection". Schematic ........................... ............................ ......................... ........................... ........... 98'. 6ro,es and windshield 0T@ .......................... ......................... ......................... ....... ....... .. 9*5. Rain protection ................................................................................................ ....... 9*&.+ce detector icing A A .......................................................................................... 9*(.


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A. Aircraft general'C(" 1.


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A - Aircraft general p. !


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1. Doors location ATA 2

Cargo door 7mergency e%ittype +++

Service door Bemergency e%it type

+

6ilot emergency hatch

6ilot communicationhatch

Rear entry door Bemergency e%it type+

Aft avionicscompartment door

Forward avionicsaccess hatch


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A - Aircraft general p. #


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MED light

tor armed green light is ON, when actuator selection switch working conditions are met: panel openedunlocked by operating handle: all hooks are disengaged and FWD latchlock is unfastened

LCHD lightblue light is ON when all door hooks and latch locks are fully engaged

GND HDL lightround handling bus ON !"# red light is On when ground handling bus is directly supplied by $O# main bat bus: m

#his red light is ON when: #he refueling panel is open #he cargo door control panel is open #he passenger door is openand alert, that the battery is discharging before leaving the aircraft

Actuator selection switchis used to operate the door & OPEN or CLOSE ' when the (") O DOO) ")*+D green light is on

cover switchects the ground handling bus on line when the panel cover is opened and allows operation of cargo door During the opening, a self test of the

CARGO LIGHT switch allows act

! Doors "anel

DOORS lightsCA#IN and CARGO aural alarms are inhibited when the (ondition /ever - is on F#) or F0+/ SOS$CE and %&D COMPT aural alarms are inhibited when the (ondition /ever . is on F#) or F0+/ SO

O' and S$CE O' on when SW #+S# depressed and check microswitches operation

(NL'

"t least - micro switch is opened

& TESTts continuity of microswitch system &on ground, doors opened'

- Aircraft p. @

2. Cargo door panel ATA 2

ATA 00

A . A

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f t g e


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(abin panel

. External lights ATA 00

A - 2avigation lights

3 - Ta%i and TBlights C - andinglights< - =ing lights7 - 3eacon lightsF - Stro e lights@ - ogo lights0 - 7mergency light

!emo panel


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&INGSupplied by D( !0S .

#EACON and NA$supplied by S1(+ !0S and !0S -LOGOsupplied by S1(+ !0S

STRO#E , LANDsupplied by "(W !0S - &/eft $and', "(W !0S . &)ight $and'

TA)I * T!OSupplied by "(W !0S .

NO SM'Gilluminates blue when associated switch is selected ON

SEAT #ELTSilluminates blue when associated switch is selected ON

Mgency lights illuminate when 2-3 1 on S#!4 bus or if both D( +N o5 line +mergency lights e6tinguish when 7.81 on S#!4 bus and at least -

NO SM'G and SEAT #ELTS!lues /ts on *+*O panel when ON &D( !0S .'

ONemergency e6it lights illuminates Supply: D( S#!4 or 9 1 !"# packs

DISARMsystem deactivated

. EXT T panel ATA 00

!. "E"( panel ATA 00

#. $igns panel ATA 00

A . A

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@. Internal lighting ATA 00


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ts activation and intensity of main panel instrument integral lighting

DSPL +no,selects activation and intensity of all digit lighting

PNL rotar- selectorselects activation and intensity of glareshield, pedestal and overhead panels instrument integral lighting

PT CONSOLE LT +no,cts activation and intensity of the respective lateral console

./! %LT COMPT LT "anelME switch

dome lights are supplied with ma6imum intensity: dome lights are dimmed

%: both dome are o5 ME light : the F O dome light becomes !)# when the switch in !)# or D;* if:

D( +N lossground, with !"# supply only

STORM switchOn position,


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*. "ulti 'unctionComputer

'C(" 1. 1


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B - Multi Function Computer p. 10


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O%%

#he module stops operating

2umerous logic funtions are performed y two independant computers !FC" and!FC'1. 7ach computer includes two independant modules A and 31

The purpose of these computers is to4 # monitor, control, authorise operation of the aircraft systems # manage system failures and flight enveloppe anomalies and command triggering of associated warning

The !FC functions can e treated4 # in one module only # in several modules redundancy1

'A6 Tilluminates and the CCAS is activatedwhen a malfunction or electricalsupply fault is detected. The moduleautomatically ecomes inoperative.This light also flashes during self-testof the module. T lightsflashing self-test of these modules1!FC "3 and !FC '3 FA> T lightse%tinguish

&(TE; 0ere, if the cargo doorcontrolpanel is opened, the selftest of !FC "A and 'A are alreadydone, and only the !FC "3 and '3are tested. See chapter A.'1

# partially in ' modules

Example;

S;ST7! F>2CT+ 2! 7

"A "3 'A '3

F +@0T

C 2TR S

ST+CD 6>S07R

STA =AR2+2@

K K

●

c c

●

# The stick pusher function is integrated in modules "A, "3, 'A and '3.

# The stall warning function is integrated in modules "3 and '3.

# The stick pusher function is availa le if modules "A A2< 'A1 R "A A2<'31 R "3 A2< 'A1 R "3 A2< '31 operate. This function is therefore notavaila le if modules "A A2< "31 R 'A A2< '31 are lost.

# The stall warning is availa le if modules "3 R '3 operate.This function is therefore not availa le if modules "3 A2< '3 are lost.

* . "

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c t i o n


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B - Multi Function Computer p. 1


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C. Centrali+edcre, alerting

system'C(" 1. 2


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C - Centralized crew alerting s stemp. 1


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1. Coc-pit philosophy ATA 01

+n normal operation, all the lights are e%tinguished


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CON%IG # O con>g test or =/?s at # O with:=W) * # not at # O


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ENG . 2 / %IRE+ngine >re

ELEC"ny D( or "( power failure

E&9 2 (I il pressure G &) 6S+ inhi ited 5)

EXCE$$ CA* A T sec during engine

start1 Ca in altitude H ")))) ft &AC ( 8T

R0 2AC I0T H"*)JC

E$$ CA* ) Ca in press diff H 8.5( 6si

E&9 1 (Iil press G &) 6siinhi ited 5) sec during

"AI&T )&!aint panel rotary sel oneither panel not in normalposition

' T CT # T press FA> T #3oth >TF = valves in


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ER A(DIO CANCELded switch, cancel the aural speci>c of an undue continuous aural e6cept for landing gear, 1*O, 1F+, 1/+, stall warning, pitch

TO CON%IG TEST #o check # O con>guration &=H pitch trim in green sectorH<

#o perform an automatic )+("

config test ATA 01


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CRIC'ETStall warning associated S#;(B S$"B+) =0S$+)"O" &"ngle Of "ttack'

&HOOLER=itch trim in motion &more than -s'

CA$ALR1 CHARGE"= Disconnects

DOOR #ELL$ostess or ground calls

C CHORD"ltitude alerts

. Aural alarms ATA 01

I - ( ktF7

I !

C . C

e n t r a

l i + e

d c r e , a l

C AC5ER

I - ( kt


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D. Air 'C(" 1. 0


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! - Air p. 21


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%A(LT

O%%

PAC' . PAC' /

O$HT O$HT

LEA' T LOOPT3 4.5 3C

T LOOPT3 4.5 3C

LEA'

ENG !. #LEED

ENG . %IRE T 4/673C T 4/673CPROP #R' SELECTORO%%

ENG !/ #LEED%A(LT O%%

ENG / %IRE

ON#LEED $AL$EO$ER PRESS(RE S&ITCH 89: PSI;

#LEED $AL$E

HP $AL$ET 4/6:3C

HP $AL$ET 4/6:3C

ENG 2 &ING DE ICINGHP

ENG .LP LP

ENG /

ENG 2 &INGHP DE ICING

) $AL$E OPEN

- p. 22

1. )neumatic system ATA 21:0!The pneumatic system supplies aircraft systems which use pressuri$edair4 These systems are4 # Air conditioning

#Ientilation

#6ressuri$ation #


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Tr duct temp switch above .E A( ("= "uto closure bleed valves &/= and $=' *ay be reset after cooling

PAC' $AL$E %A(LTpack valve disagreement with pb or O1$# downstre am pack comp &7.8 A(' ("= 1alve auto closed round cooling turbo fan failure

ates when #A detected by bleed loop e6ceeds -@C I3A( ("= "uto closure after -?? of following valves: !leed, $=, pack and ND Jfeed if left bl

NO# )+S+# !/++D

#LEED %A(LTvalve disagreement with selected po sition &or in case of O$HT or LEA' ' ("= "ssociated valves auto closed

GRD ) %EEDSpring loaded closed round only inhibited in


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O$HT MAN!

HIGH

ELECTRONIC TEMPERAT(RE CONT!

%A(LT O%%

-8 .8

8(O*=# C8

TEMP SEL

-88COLD HOT 8

A( T O

D0(#@8

%LO& COMPT! TEMPN O R M

MAN! A(TO!#LEED AIR

T 4 993C

RECIRC!%AN

PAC' $AL$EMI)INGCHAM#ER

%A(LTO%%

PAC' $AL$E

DISAGREECONDENSER

T 4 /:73C

&ATERE)TRACTOR

TEMP!CONTROL $AL$E

GRO(ND INLETGRO(NDT(R#O %ANCOOLINGSH(T O%%

T(R#INE

%AN$AL$E HOT #1


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RECIRC %AN"ssists pack air


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O1!D6tract fan o5

O1!D valve partially opened &in


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Digital controller "0#O *OD+

# O elevation up to C@88 ft

!aro setting by ("=# "ltimeter &"D( -' or -8-C&"D( .' if failure "D( -

/anding elevation

(abin pressure

+lectropneumatic out


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%LAGOFF eld elevation up to C@88 ft

EL$ SET #rigger switch to set landing elevation

DESCENT RATENORM 88 ft min%AST @88 ft minFast is used when 1s 7 -@88 ft min

TESTDisplays alternately -3388 and

3388, F"0/# appears on *"N pb #est is inhibited in


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E. Automatic Gightcontrol system

'C(" 1.


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" - Automatic #ig$t control s stemp. 2%


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#ouch (ontrol Steeringpb allows to control temporary the aircraft "= arrows e6tinguish;n basic mode, attitude limits 2 I -@A and bank angle limits 2 I C@A

"D0

CRS . +no,selects course on ("=# +$S;

%D ,arsSW to set ON OFF

ALT +no,controls the preselected altitude on "D0

CRS / +no,selects course on F O +$S;

HDG +no,selects $D bug on both +$S;

%D ,ars&horiMontal bar fo r vertical modes and vertical bar for lateral modes'

uick disconnect pbonnect "= when depressed onceessed again, clears "= OFF alert &aural and visual'

"F(S(ON#)O/ ="N+/

When depressed actives, $D$O/D and " mode

"F(S(O*=0#+)

P0;(B D;S( #(S

P0;(B D;S( #(S

- Automatic #ig$t control p. 0

1. $chematic ATA 22

E . A

u t o m a

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"D1;SO);+S S+/+(# /#

*+SS" +S

")*+D *OD+

("=#0)+D *OD+

AD$ISORIES #(S +N ("# -("# .

SELECT ALT"/# S+/ %%%%%%%%%F# "/# S+/ C888 F#

#RT"dQus

RESET("N(+/ " ("0#;ON *+SS" +

MESSAGESD;S+N " +D "NN0N D"#" F"0/#+N " + ;N$;!;# (=/ D"#" ;N1"/;D "$)S D"#" ;N1"/;D D"D( D"#" ;N1"/;D "F(S D"#" ;N1"/;D "= ;N1"/;D

ARMED an= CAPT(REDMODELATERAL MODE$D S+/ /O $D S+/ $;

1O)/N"1 /O(

1O)R/N"1 /O(R

1O)

/O($D $O/D

!( !(R !(

MESSAGES"= 4D D;S+N " +D "= D;S+N " + D

4D D;S+N " +D ";/+)ON *;S#);* =;#($ #);* F";/=;#($ *;S#);* NOS+ DN =;#($ *;S#);* NOS+ 0= )+#);* )O// ) W;N DN )+#);* )O// ) W;N 0=

L2R SELS+/ pb is used in "= ground maintenance test

IAS >o=eto use FD with a desired indicated airspeed

AP ",engages autopilot and yaw damper and disengages only auto

HDG >o=eto use FD with $D S+/

NA$ >o=eto use FD with 1O) and /N"1 course

1D ",engages yaw damper and disengages yaw damper and autopilot if eng

Pitch wheelAPP >o=e to adQust 1S or ;"S or pitch attitudeto use FD with ;/S informationin basic mode

course &lateral and vertical'

#C >o=eto use FD with localiMer in back course

$S >o=eto use FD with a desired vertical speed

",els all FD modes &both armed and captured' and return in basic modes with "= engagedALT >o=e

to use FD with a desired altitude

CPL ",permit to couple "= FD on ("=# or F O sideDouble coupling below -.88 ft )"

#AN' ",selects /OW bank angle &-@A' or $; $ bank &.EA'

2. AD6 ATA 22

AR"ED and CA)T6RED"(DE

ERTICA "(DE A T A TN A T

+AS --- DTS+AS "8) DTSIS ---- F6!IS - 8))F6!

"E$$A9E$2AI !+S!ATC0 S7 2AI !+S!ATC0 RS7 7?C7SS


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'. Communications'C(" 1.


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F - Communications p. 02


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)+*O#+ (ON#)O/ "0D;O 0N;#

- p. 00

1. $chematic ATA 20The communication system provides communication etween4

# aircraft and ground stations # cockpit crew stations

# ca in attendant station # ground crew stations

2. )TT selector and &($E 78EE$TEERI&9 C(&TR( $7 ATA20

C CD6+T I +C7R7C R3 +C A


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PTT selectorinterphone: forward position neutral: center position radio: backward position

NOSE &HEEL STEERING

CONTROL switchWhen depressed, !OO* S+# or OJ4 mike is connected for transmission

- p. 0


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>ission +e-s

one key can be engaged at a time ;t illuminates white when selected

>e control +no,eive volume from associated communication or navigation facilities

! Au=io control "anel$OICE ONL1 +e-When depressed, it inhibits N"1 receivers station identi>cation /ight illuminates amber when selected

ATA /INT2RAD selector=rovides selection of transmission mode when using OJ4 *"SB or;N#: hot mike position ;nterphone is always operative between creN+0#)"/: only handmike is usable as long as one transmission ke)"D: #his position is re uired to automatically connect for transmi

7! $H%ON2O%% switchenergiMes the control bo6 and the associated 1$F When pulled, allows override of the automatic s uelch

)%R2MEM switch #his is a three positions springN+0#)"/JF): e6changes preset and act*+*: successive actions cycle

ACT ,uttonWhen depressed, second line displays dash

,uttonws entering si6 fre uencies in the memory When depressed, the upper window displays the channel number of available memory &($- to ($9'

TEST ,uttonis used to initiate the radio self% test diagnostic routine

Tinates amber and the (("S is activated when an associated )("0 processing board failure or power loss is detected

LO(DSPEA'ER(ommunication reception ;n case of aural alert:normal volume is always available regardless of knobs positionduring any transmission the volume of both loudspeakers is muted

. A6DI( $E p3 ATA 20

A6DI( $EControls functioning of associated RCA> processing

oard.2 R!4 RCA> functions normally

A T2affected crew station isconnected directly to I0F " for CA6T station or I0F ' for FBstation.Iolume is adOusted y affectedloudspeaker volume control

!. oudspea-er /olume -no3s ATA 20

' . C

o m m u n

i c a


48/171

6! TCAS control ,o?TCAS rotar- selectorST#1 : #("S system is under power but intruder visualisation, tra c advisory mode or resolution advisory are not operativeA(TO : normal operating mode of #("STA ONL1 : disables the )" mode of operation

TEST #("S test function operates the test during co

O TEST RSTd in case of undue alert or to test the emergency beacon two cases are possible for the testork J *;# "/+)# illuminates amber during .??e J*;# "/+)# lt


49/171

Hea= set2 ,oo> set2 han= >i+e "anels

ea= set 2 ,oo> set "anel 2 han= >i+e "anels

lows connection of a boom set, a head set and a hand mike

. ! ATC ,o?

.7! C$R "anel

IDENT ,uttonwhen depressed, causes the trans% ponder to transmit ;D+N# signal

r an= >o=e switch%: control bo6 and receiver are deenergiMed

: system is under power but does not transmit repliestransponder replies to both mode " and mode ( interrogations but without


50/171

9. Electrical systems'C(" 1. !


51/171

% - "lectrical s stemsp. 0#


52/171

D( power .3 1D( #wo inverters

"(W power --@1 .881

% - "lectrical p. 0@

1. $ources of po,er ATA 2Three kind of current are availa le4 7mergencysupply1


53/171

D( Starter enerator

"(Wenerator

"ccessorygear bo6

)eductiongear bo6

D( Starter enerator

"(Wenerator

"ccessorygear bo6

)eductiongear bo6

The


54/171

AC #(S .

IN$ .

AC #(S /

(TL1 #(S .(TL1 #(S /

%A(LT %A(LTA$AIL

AC ST#1 #(S

#AT IN$ /

ON

TR(

DC ST#1 #(S

DC ESS #(S

EMER #AT CHG

HOT EMER #AT #(S HOT MAIN #AT #(S

MAIN #AT CHG

DC #(S . DC #(S /

#TC

DC S$CE #(S

DC GEN . E)T! P&R DC GEN /

GND HDLG #(S

DC EMER #(S

GO(ND HANLING #(S is supplied only on ground, in three di5erent ways:FF or !"# ON with the +J# =W) not available, the ND $D/ !0S is supplied by the $O# *";N !"# !0S for ground servicing only when:efueling panel is openargo door control panel is open

passenger door is openFF or !"# ON with the +J# =W) available but not ON, the ND $D/ !0S is supplied directly from the +J# =W)N with +J# =W) ON or with one +N on line, the ND $D/ !0S is supplied by the D( S1(+ !0S

TE0 #he ND $D/ !0S is disconnected when airborne

2. DC4AC schematic ATA 22.1. &ormal supply; (n ground ,ith 3attery only

9 . E

l e c t r

i c a

l s y


55/171

%A(LT A$AIL

ON

%A(LT

IN$ .

AC #(S /

AC ST#1 #(S

#AT IN$ /

ON

TR(

DC ST#1 #(S

DC ESS #(S

EMER #AT CHG


MAIN #AT CHG

DC #(S . (TL1 #(S .(TL1 #(S / DC #(S /

#TC

DC S$CE #(S


DC EMER #(S

AC #(S .

2.2. &ormal $upply; (n ground ,ith external po,er

9&D 8D 9*6$

The 3TC is closed and the @6> supplied all the has always the

priority


56/171

%A(LT

AC #(S . AC #(S /

AC ST#1 #(S

#ATIN$ . IN$ /

ON

TR(

DC ST#1 #(S

DC ESS #(S

EMER #AT CHG


MAIN #AT CHG

DC #(S . (TL1 #(S .(TL1 #(S / DC #(S /

#TC

DC S$CE #(S


GND HDLG #(S

DC EMER #(S

2.0. 8otel mode or DC 9E& 1 'A6 T

The 3TC is closed and the @72 ' supplied all the S is supplied y the S "through the S.

9

. E l e c t r

i c a

l s y


57/171

IN$ .

AC #(S /

AC ST#1 #(S

#AT IN$ /

ON

TR(

DC ST#1 #(S

DC ESS #(S

EMER #AT CHG


MAIN #AT CHG

DC #(S . (TL1 #(S .(TL1 #(S / DC #(S /

#TC

DC S$CE #(S


GND HDLG #(S

DC EMER #(S

AC #(S .

2. . &ormal supply; ,ith t,o generators on line

The 3TC is opened and each @72 supply its own usses.n ground the @2< 0< @ 3>S is supplied y the S "

through the S, and disconnected when air orne.


58/171

2. . Emergency supply; In dual DC 9E& ($$ ,ith

3attery toggle s,itch on ( RD

I& 1

AC *6$ 1 AC *6$2

AC $T*? *6$

*AT

( RD

I& 2

The 3AT toggle switch has to e selected toIR


59/171

2.!. Emergency supply; In dual DC 9E& ($$ ,ith3attery toggle s,itch on ( RD and second ( RD selected

AC *6$ 1 AC *6$ 2

AC $T*? *6$

I& 1

TR6

DC $T*? *6$

*AT

( RD

I& 2

After a


60/171

AC #(S /

(TL1 #(S .(TL1 #(S /

%A(LT %A(LTGND HDLG #(S

AC #(S .

AC ST#1 #(S

#ATIN$ . IN$ /

O$RD

TR(

ONDC ST#1 #(S

DC ESS #(S

EMER #AT CHG

HOT EMER #AT #(S

MAIN #AT CHG

DC #(S . DC #(S /

#TC

DC S$CE #(S


DC EMER #(S

HOT MAIN #AT #(S

2.#. Emergency supply; In dual DC 9E& ($$ ,ith TR6

The TR> connected to the AC= 3>S ' supplies S, S, SS7S

9

. E l e c t r

i c a

l s y


61/171

R #AT CHGLT : Overheat detected by *F( or failure of contactor ELEC on ("=ctor auto opens if: thermal runaway bus voltage 2.@ 1 Start se uence: !at sw on O1)D

#TC"llows !=(0 to control !#( operation +6t power, hotel mode or single gen operation, !#( is closed &green S

(''7SS 3>S, S +2I "areisolated from 0 T !A+2 3AT 3>SS is isolated from

DC *6$ (''Respective us not supplied.E EC on CA6

DC $ CE:6T ? *6$+n automatic shedding

ne of the T ; "and ' usses is shed " us$8ED 3C6>1. E EC on CA6.+n FFall T ; " and' usses are shedT ; 3>SS7S suplly non-essential loads

DC 9E& 2

FA> T4 protection trip y @C>P Auto reset if underspeed4 in other cases manual. 3TC auto closes

A AI@6> has een checked y 36C>for overBunder voltage, overcurrent and polarity

DC 9E& 1@enerator 'A6 T t.7%tinguishes a ove 8".(L 20 if @72 is operating normally

X $TART 'AIpposite generator has not come

on line to assist start at ") L 20

*6$ ('' Associated us deenergi$ed.E EC on CA6

I& 'A6 T>nderBover voltage at +2Ioutput. +2I failure or supplyloss1. Auto- ?fer of all AC

usses to remaining inverter.E EC on CA6

( RD?ferBst y usses from 0 T !A+2to 0 T 7!7R 3AT 3>S


62/171

"(W =0

"(W !0S - "(W !0S . #)0

"(W +N - "(W +N .

!0S ."(W #)0

"(W +N .

"(W !0S -

"(W =0

S1(+ !0S

"(W +N -

"(W =0

"(W !0S - "(W !0S . #)0

S1(+ !0S

"(W +N - "(W +N .

. AC7 schematic ATA 2

NP=0 NP=0

AC7 supplied 3y the External )o,er #=hen the AC= @6> is availa le A AI 1 ut not 2, the @6> supplies only the AC=

Service 3us, if the @2< Service 3us switch, on the Qight attendant panel, is 2.

#=hen the AC= @6> is (& , the @6> supplies through the 3TC, the AC= 3>S ", the AC= 3>S ' and the AC= SIC7 3>S. #7ven if one AC= generator is availa le, the @6> has always the priority.

0 NP=0 in hotel modeNPS " through the 3TC, ut the SIC73>S is shed one generator is not a le to supply all the usses1CA>T+ 24 on ground in case of an 77C or 67C fault, the fuel governing mode is lost and the

AC= generator is not availa le 26G88L1

9 . E

l e c t r

i c a

l s y

SVCE BUS


63/171

GEN . 2/T : "uto reset in case of under over speed: manual reset otherwiseS1(+ !0S auto shed if - +N is out

"(W !0S -

"(W =0

"(W !0S . #)0

S1(+ !0S

"(W +N - "(W +N .

"(W =0

"(W !0S - "(W !0S . #)0

S1(+ !0S

"(W +N - "(W +N .

E)T P&RA$AIL H ON =0 has priority on both +N

#TC &green S " and the AC= SIC7 3>S # The AC= @72 ' supplied the AC= 3>S '. # The TR> is connected to the AC= 3>S '

=100% NP=100%

(ne 9enerator 'ault=hen one generator is fault, the other one supplies the AC= 3>S" and the AC= 3>S 'through the 3TC.The SIC7 3>S is automatically shed one generator is not a le to supply all the usses1

. AC7 panel ATA 2


64/171

!. *rea-er panels ATA 2!.1. (/erhead panel

!.2. Electric rac- 3ehind ':(

9 . E

l e c t r

i c a

l s y


65/171

8. Emergencye


66/171

& - "mergenc e'uipment p. 1


67/171

halone6tinguishercrash a6e life Qackets

emergencye6it type ;;;

type ; servicedoor

o6ygen bottleo6ygen masklife Qacket


68/171

ins bandages, burn dressings, small adhesive dressings, antiseptic wound cleaner, adhesive wound closures, disposable resuscitation aid, woumall, adhesive tape, safety pins and scissors, simple analgesic, antiemetic, nasal decongestant, >rst%aid handbook, splints, suitable for uppera

(rash a6e with pick and edge $andle insulated up to .8881 to open of a door or a compartment

megaphone E. only

With batteries, morse code switch

With oral in


69/171

used to evacuate the cockpit

@. Escape rope ATA 2


70/171

#o protect against >re

Water e6tinguisher. liters of water with an anti%ice additivedischarge time: C8 to 8 TT

$alon e6tinguisher- . kg of halon gas discharge time: 3 to -8 TT

Mo=ules or 7/,ers

O?-gen ,ottle

%. 9lo/es ATA 2

1 . 7ater extinguisher ATA 2!

11. 8alon extinguisher ATA 2!

12. (xygen schematic ATA 0

8 . E

m e r g e n c y e


71/171

MAIN S(PPL1

pb in: crew supply only

ONPA) S(PPL1 .@U for .%@88 E.%.-."

HP INDICATORo6ygen bottle pressure )ed arc 8 to 3@ psi

reen arc 3@ to .8.@ psi;f below - 88 psi, use table LO PR

supply below @8 psi

PRESS TO TEST AND RESETpermits a test of o6ygen


72/171

-. O6ygen masks for .%@88-L O6ygen masks for E.%.-." e uipped with valves, bag and elastic strap

Protective ,reathing e ui">ent 8P#E;to supply -@ min pure o6ygen with hood, visor, speaking diaphragm and oronasal mask

. =!+ 7 .%@88 C =!+ 7 E.%.-."

P#Estowage bo6

1#. )rotecti/e3reathing e


73/171

I. 'ire protection'C(" 1. @


74/171

( - Fire protection p. !


75/171

!ottle NA- !ottle NA.

+N -

"ND

FO)W")D (") O S*OB+ D+#+(#;ON

"1;ON;(S (O*=")#*+N# S*OB+ D+#+(#;ON

"F# (") O O) /"1"#O)4 S*OB+ D+#+(#;ON

";) ("0#;ON F"N F";/0)+

- Fire p. #

The fire protection system provides detection, warning and e%tinguishing for each engine, ca in and lavatory.

1. $chematic ATA 0

F+R7 +S0+2@ S;ST7!

72@ '

2. A/ionics '7D and A'T smo-edetection ATA 0


76/171

ENGINE %IRE HANDLE=ulled on the respective engine:=)O=: feather

F0+/: /= valve closed";): !/++D and $= valve closedD+;(;N : deice and shuto5 valve closed+/+( : D( and "(W gen disconnectedSP0;!S armed lts illuminationH $ydraulic to prop brake closed on engine .

! %ire han=le

LOOP%A(LT : change in resistance, inhibits >re signal until t

AGENT .DISCH : !ottle depressuriMed Opposite agent D;S($ light wil l also illuminate on other >re panel !ottle located in the wing fairin

%A(LT TEST*( H S( H /OO= on ("=Fault lights in " ! loop pb

S (I# TEST+lectrical test of the s uibs

%IRE*WH >r

AGENTSP0;!armed when # handle pulled Discharges bottle&D( +*+) $O# *";N !"#'

OFFtakes respective loop out of parallel circuit "llows other loop to activate >re signal alone

SM' TEST #ests the smoke detectors working

L SOinates red in case of >re signal from associated engine +6tinguishes after (/ is set at fuel shut o5 position or if >re detection signal stops

. Compartment smo-e panel ATA 0

. Condition le/ers fuel light ATA 0

I

.

' i r e p r o

t e c t

&(R"one fan runsFA> T4 the fan is out of orderand illuminates am er CCASis activated

A T24 The alternate fanruns, A T2 light illuminates


77/171

>. 'light control'C(" 1. %


78/171

) - Flig$t control p. %


79/171 ) - Flig$tControl p. !

The elevators, ailerons and rudder are me-chanically actuated

The spoilers and flaps are hydraulicallyactuated.

1. Roll schematic ATA 2#

2. )itch schematic ATA 2#

> . '

l i g h t c o n t


80/171 ) - Flig$tControl p. !1

+n case of Oamming, pitch control will e re-covered y disengaging the pitch couplingsystem y applying a differential force of (' da21.


81/171

0. ?a, schematic ATA 2#

. 9ust loc- ATA 2#

For aircraft e uipped with a spring ta on the aileron, theroll locking system is composed of two electro-mechanical locking devices.The A+ CD is triggered whenever one of the lockingactuators is in disagreement with the gust lock position

lock or unlock position1

. $tic- $ha-er:$tic- )usher push 3utton and light ATA 2#

96$T (C5 le/er permits to lock mechanicallythe roll and pitch a%es againstthe wing gusts. The 6 travel

is limited to slightly a ove F+.


82/171

$TIC5 $8A5ER:)6$8ER )* # 'A6 T light indicates a stick

pusher or stick shaker failure # FF position4 ena les to switch

FF the stick pusher and thestick shaker system

)ITC8 )6$8ERilluminates to indicate that thestick pusher is operating


83/171

LERS "osition in=icator When illuminated, each blue light indicates that the associated spoiler is not in the fully retracted position &more th

Tri> "osition in=icator ATA /6

E.=+( .=+(

Pitch tri> "ositionindicates the right trim actuator controlled tab travel" green sector identi>es the take o5 range ;f take o5 &or take o5 con>g test' is performed with pitch trim out of this range, (ON

Roll tri> "ositionndicates the /$ aileron trim controlled tab travel

1aw tri> "ositionindicates units of trim motor displacement

1aw TRIM control switches controls the yaw trim actuator "s a safety device both levers must be moved and held in the sam

!. $poilers position indicator ATA 2#

#. )itch trim asym light ATA 2#)ITC8 TRI" A$?"light illuminates to indicate a pitch ta sdesynchroni$ation greater than ).*J

%. Trim controls ATA 2#

> . '

l i g h t c o n

)itch trim roc-er two switches installed on each control wheel. +t isnecessary to operate oth rocker switches to activate thenormal electrical motor of each trim actuator and to control

nose up or down. The switches are spring loaded toneutral position. An aural whooler is generated y theCCAS if trim is used for more than " second. Action on this switch will disengage the autopilot.


84/171

1 . 'laps schematic ATA 2#

11. 'laps position indicator ATA 2#

ATR *' 67C

' A)$ position indicator shows the flaps position

ATR &' 67C

12. 'laps control le/er ATA 2#

EXT flagappears to indicate that the flapsvalve is hydraulicallycommanding flap e%tension. +f7?T flag appears when flaps aree%tended, it means that there is aleak in the flaps hydraulic circuit

' A)$ control le/er controls the flaps operation.


85/171

ATR *' 67C ATR &' 67C


86/171

5. 'light instruments'C(" 1.1


87/171

* - Flig$t instruments p. !


88/171 - Flig$t p. !

1. $chematic ATA 0 H 22

The Avionics Standard Communication 3us ASC31 system allows transmission of data in all directionsetween computers of the aircraft. The ASC3 is controlled y the AFCS computer

6rivate line4 =hen the ASC3 is failed, the private line is used as a ack up, to transmit data from the A0R> to theS@>.

Iideo 3us

AFCS Auto Flight Control System1 receives data from the two A, the radio altimeter, the @2SSand from some sensors. +t generates commands to the flight control actuators and to the F< ars. The AFCS is the

ASC3 controller too.

A0R> Attitude and 0eading Reference >nit1 includes an +nertial measurement unit +2>1 composed of three gyrometers and three accelerometers. The A0R> receives inputs from its associated flu% valve and the TAS,fed y oth A


89/171

GRO(ND SPEED2TIME TO GOannunciator

NTER 8 ;cates the bearing to a station by NA. system &1O) . or "DF .'

ROLL ATTIT(DEscale 8 , -8, .8, C8, @ and 98A

1ertical ARM and CAPT(REmode

Fon an= "itch scaleite and has reference marks at @, -8, -@, .8, C8, 8 and 98Aup and @, -8, -@, .8, C8,nd 98A nose down "bove 8A nose up and below C8A nose down, red arrows come into view

/ateral ARM and CAPT(REmode

%LIGHT DIRECTORcommand bars &magenta'

LOCALI ER indication

GLIDESLOPE indication

T2SLO& indicators the di5erence between speed bug and actual speed &I-8 Bts'

NA$ SO(RCE annunciator

CRS pointer and deviation

HDG #(Gselected by the remote $D knob

DISTANCE =is"la-to the selected 1O) D*+ or ;/S D*+ station

NTER 8 ;ates the bearing to a station by NA- system &1O) - or "DF -'

DH indication

SLIP indicator

RADIO ALTIT(DE indication

Runwa- s->,olappears lower than .88 ft

2. EADI ATA 0

0. E8$I ATA 0

5 . '

l i g h t

i n s

t r u


90/171

Selected HDG #(GHDG select display

HDG SCALESelected CO(RSE POINTER

:77 Digital heading display

#+))";N W+"#$+) )"D")

SELECTED RANGESCALE

(ADRANTAL HEADING SCALE")( with uadrantal heading scale *OD+ on an arc showing @A either side of actual headi

%AIL(RE alertd ! part failure and all information disappears from +"D; and +$S;

SG( %AIL(RE alert( part failure and a red cross appears on +"D; and +$S;

S %AIL(REssociated information immediatly disappear from both ()#s "## F";/ message is displayed

AHRS %AIL(REthe associated information immediatly disappear from both ()#s $D F";/ message is displayed

. E8$I ,ith composite mode ATA 0

. E8$I 4 ARC "(DE ,ith terrainor ,eather radar information ATA 0

!. $ource failure alert ATA 0


91/171

9! E%IS control "anelGSPD2TTG ",permits to select ground speed or time to go

ATA

%(LL2ARC ",permits to select F0// or ")( mode on +$S;

RG 8 ;tor to select blue bearing pointer to 1O) - or to "DF - or to =S active waypoints &)! N"1 -'

$2L ",to select the 1O) /O( m

MAP ",permits to select *"= selection with waypoints of the


92/171

GAIN

setting to set receiving ampli>cation

DE selector% radar is o5

radar is ON but no pulse is sent by antennaT range at -88 N*, C arcs green, yellow and rednormal operating position, intensity of weather obstacles is displayed by di5erent colors &black: no cloudV green: normal c loudV yellow: denseV r

RCT ",activates )ai

RANGE selectoto select the dist

RCT ",activates )ain +cho "ttenuation (ompensation tec

#urns the pitchamber legend il

#he range pusbutton are used to select the operating range o

GAINsetting to set receiving ampli>cation

DE selector O%% radar is o5 radar ins on but no pulse is sent by antenna

T range at -88 N*, C arcs green, yellow and rednormal operating position, intensity of weather obstacles is displayed by di5erent colors &black: no cloudV green: normal c loudV yellow: denseV r

AHRS erect ",illuminates amber when the associated "$)S loses the #"S signal from the "D(;f the aircraft is stabiliMed &unaccelareted level


93/171

..! TAT 2SAT in=icator ATAT in=icatorindicates total air temperature

TAS in=icatorindicates true air spe

SAT in=icator "ush ,utton indicates static air temperature, when pushed

CHRONOdepress once to start, once to stop, once to reset

ATA 7CLOC' $ours and minutes pointer

RE$OL$ING #E EL

;ndicates elapsed time from start markTIME 'NO#=ull then rotate knob to set time

R ",depressed, both cockpit voice recorder and digital


94/171

AIRSPEED INDICATORdisplays the airspeed Scale from 98 Bt to 88 Bt

POINTERd and white strips indicates the ma6 airspeed computede associated "D( which represents 1*O **O "n aural warning &clacker' willnerated by the (("S if overshoot

MO$A#LE INDICES&bugs' in four colors

O%%2RED %LAGindicates a failure a5ecting the 1*O channel or the airspeed indicator

ALTIMETERWith baro set knob in $pa and ;N $

ALTIT(DE ALERTlt illuminates amber when altitude alert is triggered &%H -888 ft or H% .@8 ft'

ALTIMETERWith baro set knob in *! and ;N $

SPEED SELECTORto set a desired speed during a given phase of


95/171

NTS ",n momentarily depressed, the tape records are marked to identify a special event

EN ARCmmandes vertical speed to resolve corrective resolution advisory

NTERite' indicates present vertical speed =ointer displayed when vertical speed is valid

LID CIRCLEuder #" generated )ange and bearing relative to own aircraft

RANGE RING&white' . miles radius range about own aircraft

.9! %light =ata entr- "anelDATA DISPLA1 Date and time may be displayed and selecte

%LIGHT N(M#ER AND DATA ENTR1 PANELpanel enables through thumwheels to insert di5erent data: hour, minutes, month, day, year

(PDATE ",>rst left thumbwheel of data entry panel must be on>rst se uence: hours and minutes0=D"#+ pb depressed, the display


96/171

. 'uel system'C(" 1.11


97/171

+ - Fuel s stem p. #0


98/171

$ent surge tan+ %ee=er tan+ 8/:: l 2 . : +g;

Re ueling "oint

Access =oor

Main wing tan+

Main wing tan+

Re ueling "anel

Gravit- lling ca"

$ent surge tan+ 8.:: l;

%ee=er tan+ 8/:: l 2 . : +g;

Total uantit- 75:: +g

Total uantit- 5::: +g

$ent surge tan+

Access =oor

Main wing tan+

Main wing tan+

Re ueling "anel

Gravit- lling ca"

Re ueling "oint$ent surge tan+ 8.:: l;

- Fuel p. #

1. $chematic ATA 2@The fuel is stored in two tanks, one in each wing. 7ach tank is fitted with4

# a vent surge tank to ensure positive pressure and allows a thermal e%pansion without spillage # a main wing tank

# a feeder tank, always full to protect the engine feed system against negative or lateral load factors

ATR 2

ATR #2

. ' u

e l s y s t


99/171

R(N

O%%

ENGINE .

MOTI$E %LO& $AL$E

LP $AL$E ENGINE . %IRE P(LL

R TAN

CROSS%EED $AL$E

P(MP

%EEDER JET P(MP ELECTRO P(MPENGINE %EED JETP(MP

L TAN' %EEDER COMPARTMENT

HM(

CCAS

%COC

%EED LO PR

2. $tarting procedure ATA 2@

72@+27 S0>T < =2 =+T0 7 7CTR+CA 6>!6 R>22+2@3oth fuel engine electrical pumps push uttons are pressed +2 and green R>2 lightsilluminate. The electrical pumps are energi$ed and egin to supply fuel to engines.The F77< 6R am er light e%tinguishes when the pressure is H & psi on the line.

At the same time, the feeder Oet pump is activated y the electrical pump output pressure, to supply and maintain thefeeder tank full.


100/171

R(N

O%%

ENGINE .

MOTI$E %LO& $AL$E


R

CROSS%EED $AL$E

P(MP

%EEDER JET P(MPENGINE

ELECTRO%EED JETP(MPP(MP

P 49!5 PSIK :s


HM(

CCAS

%COC

%EED LO

0. &ormal procedure ATA 2@

72@+27 R>22+2@ B 2 R!A 67RAT+ 2 F T07 F>7 S;ST7! After engine starting, the flow, from return line of the 0!>, opens the !otive Flow Ialve, in order to supply the7ngine Feed et 6ump.The 7ngine Feed et 6ump egins to operate y driving fuel from the feedertank. At the same time, it supplies the Feeder et 6ump.=hen the 7ngine Feed et 6ump outlet pressure reaches 9.( 6S+, the electrical pump is de-energi$ed after 5)s time

delay.+n normal operation of the fuel system, the engine is only supplied y the 7ngine Feed et 6ump and the electricalpump is de-energi$ed.

Conditions to energi$e the electrical pump See details on pages hereafter1 # Cross feed operation # 7ngine Feed et 6ump oulet pressure drops elow ( psi # ow evel

. ' u

e l s y s t


101/171

R(N

O%%

%(EL ) %EED

ENGINE .

MOTI$E %LO& $AL$E


R TAN'

CROSS%EED $AL$E

P(MP

%EEDER JET P(MP ELECTRO P(MPENGINE %EED JET P(MP


HM(

CCAS

%COC

%EED LO PR

R(N

O%%

%(EL ) %EED

ENGINE .

MOTI$E %LO& $AL$E


R TAN'

CROSS%EED $AL$E

P(MP

%EEDER JET P(MP ELECTRO P(MPENGINE %EED JET P(MP


HM(

CCAS

%COC

%EED LO PR

. Cross feed procedure ATA 2@

Cross feed valve could e used to supply an engine from the oppositetank. The cross feed is not used to tranfer fuel from one tank to the othertank.=ith the ?feed valve push utton pressed +2, the valve opens, green flow ar is hori$ontal. 3oth electrical pump areenergi$ed.


102/171

3y selecting FF the corresponding 6>!6 push utton, the electrical pump is de-energi$ed and the motive flow

valve is supplied to close. The engine is fed through the opposite tank.


103/171


104/171

R(N

O%%

ENGINE .

MOTI$E %LO& $AL$E


R TAN

CROSS%EED $AL$E

%LAPPERS P(MP

%EEDER JET P(MPELECTRO P(MP

ENGINE %EED JETP(MP


HM(

CCAS

%COC

%EED LO PR

!. o, le/el ATA 2@

=hen the low level is triggered on one tank, its electrical pump is automaticallyactivated. Two cases of low level4

# I with fuel uantity indicator G "8) kg ow level of the remaining fuel in the tank. # I with fuel uantity indicator H "8) kg Feeder tank not full due to a failure of the feeder Oet pump.

+n this condition, the fuel is transfered from the main tank to the feeder tank through the flappers.


105/171


106/171

F0+/ #+*=+)"#0)+ in A(

)%EED valve"ctivates both elect fuel pumps

P(MP(ontrol electrical pump power and Qet pump motive


107/171

". 8ydraulic system'C(" 1.12


108/171

M - & draulic s stem p. @2


109/171

LO L$L O$HTO$HT LO L$L

LO PR

O%% LO PR

O%%

ONLO PR

ON

NOSE &HEEL STEERING

LANDING GEAR

%LAPS

SPOILERS

PROPELLER #RA'E

#RA'INGEMERG AND PAR'INGNORMAL

RET(RN

M M

#L(E P(MP

GREEN P(MP

M) %EED

A() P(MP

#otal lling: minimum >lling: alert level:

L 9 lL C@ l3 @ l. @ l

O$HT

- & draulic p. @0

1. $chematic ATA 2%

The aircraft has two hydraulic systems, designated lue and green. 7ach system is pressuri$ed y an electric pump,supplied y AC= power. The lue system is also provided with and au%illiary pump, supplied y


110/171


111/171

&. Ice and rainprotection

'C(" 1.10


112/171

, - (ce and rain protection p. @


113/171 , - (ce and rain p. @!

=)O=+//+)&+/+(#);("/'

W;NS$;+/D&+/+(#);("/'

Aircraft ice protection is provided y a pneumatic and an electrical system adapted for the critical areas. +ce detectormonitors ice accretion. +t is connected to the CCAS.

1. $chematic ATA 0 A+ 7R 2 0 R2S

7 7CTR+CA 1

S+!AT+C1

+C+2@ 7I+!AT+C1

6R 37S7 7CTR+CA 1

0 R+ 2TA TA+ 6 A27 3 TS627>!AT+C1 B R>


114/171

T ",ss for C??:

ng will


115/171

. De4icing schematic ATA 0ATR 2

1 E&9 2

"(DE$E AIR'RA"E

"(DE $EA6T(

'A6 T

A (&

'A6 T

(&

'A6 T

(& ( RD

'A6 T

(&

'A6 T

(& *

*ENGINE 1 FIRE

F !!

"'C A

ENGINE 2 FIREF !!

1 2 0 ! #

T( T8E)AC5$

DI$TRI*6TI(&A E

1

DE ICEA E

DE ICEA E

DI$TRI*6TI(&A E

2

I$( ATI(&A E

* EEDA E

T 20 FC

AIR'RA"EAIR

* EED

'A6 T

(''

* EEDA E I$( ATI(&A E

E&9 1 CCA$ E&9 2

I&TER&A I&TER&A

* *A A

* *

A A

D6ADI$TRI*6TI(&

A E$

0

D6ADI$TRI*6TI(&

A E$

* *

A A

!

DI$TRI*6TI(&A E

& . I c e a n d r a

i n p r

CCA$


116/171

%A(LT

ON

%A(LT

ON ON

%A(LT

O$RD

%A(LT

ON

%A(LT

O%%

A

# MODE. ENG /SEL AIR%RAME

M%C

ENGINE . %IRE %(LL ENGINE / %IRE %(LL

. / 7 5 6DISTRI#(TION

$AL$E

DE ICE$AL$E

DE ICE$AL$E

.DISTRI#(TION

$AL$E/

TO THEPAC'S

ISOLATION$AL$E

#LEED$AL$E

AIR%RAMEAIR #LEED

#LEED$AL$E ISOLATION

$AL$E

T 4/ :3C

ENG . ENG /

P .7PSI

INTERNAL INTERNAL

##

A A

# #

A#

A#

A

# #D(ALDISTRI#(TION $AL$ES

A A

D(ALDISTRI#(TION

7 6 5

CCAS

ATR #2A *

DI$TRI*6TI(&A E

CCA$


117/171

%A(LTboth *F( modules have failed to control boots cycles #he monitoring is preformed by the stby controller

DE ICINGair is always available regardless of bleed pb NO)*: 98?? cycle SLO& : . 8?? cycle

AIR %RAME%A(LT : valve opened but no downstream press Orvalve closed and downstream press Detected ("=

AIR %RAMEON : signal sent to *F( to start deice cycle on the airframe

A%R AIR #LEED O$RD : no *F( !oots in


118/171

CING LIGHTinates when airframe deicing syst is ONes when airframe deicing syst still selected ON @ min after last ice accretion detection


119/171

(. anding gear 'C(" 1.1


120/171

- +anding gear p. %1


121/171

/"ND;N +")(ON#)O/

S#++);N$"NDW$++/

+*+) +N(4 =")B;N !)"B+ $"ND/+

=;/O# !)"B+=+D"/S

- +anding p. %2

1. anding gear description ATA 02

The landing gear is hydraulically operated. +n case of hydraulic failure, it may e e%tended y gravity.

2. *ra-es schematic ATA 02

( .

a n

d i n g g


122/171

#R' TEMPHOT "ny brake #A 7 -98A(

> /gear not locked in selected position or &on ND' uplock bo6 not opened

n /t down lock engaged

> .gear not locked i n selected position or &on ND' uplock bo6 not opened

n /t down lock engaged

LDG GE AR EMERGENC1 E)TENSION HANDLEpermits to unlock the landing gear

#ra+es te>"erature an= antis+i= ATA /ANTIS'IDOperative if speed 7 -8 kts"ctivates when speed 7 .C kts H @8U di5 between wheels &locked wheel protect!raking action inhibited at touchdown as long as wheel spin up speed 2 C@ kts o("0#;ON: #$+ #+S# ;N$;!;#S !)"B+S

% 8%A(LT;wheel channel failure ("= #+S# pb

&inhibited if speed 7 -E kts' *( H S( ("= F amber lt #est duration: C sec in


123/171

). &a/igation system'C(" 1.1


124/171

. - ,a/igation s stem p. %


125/171

ER SELECTOR toiMe the control bo6 and associated 1O) ;/S D*+ receivers: holding the D*+ on the current active fre uency

M'R S&is used to set marker sensibility

)%R2MEM switchJF) e6changes active and preMEM to activate fre uencies s

%%: "DF deenergiMed

: #he antenna loop is disabled and the receiver is used as a conventional receiver the )*; pointer will park horiMontally%: #he system operates in "DF mode and provides the bearing

E : " -888 $M sound indicates that "DF is correctly tune to the station

ACTDirect active tuning mode to change

- ,a/igation p. %

1. &a/ control 3ox ATA 0

2. "ar-er s,itch ATA 0

0. AD' control 3ox ATA 0

. E9)7$ alert modes ATA 0The 7nhanced @ound 6ro%imity =arning System provides visual and aural alerts in case of dangerous flight pathconditions which would result inadvertent ground contact if maintained.

The 7@6=S performs the following alert modes4 # 3asic @6=S modes

N !ode "4 e%cessive descent rateN !ode '4 e%cessive terrain closure rateN !ode 54 altitude loss after take-off N !ode &4 unsafe terrain clearanceN !ode (4 elow glideslopeN !ode 84 altitude callouts

# 7nhanced modes4

X'R:"E" s,itch?FR e%changes activeand preset fre uency

"E" to activate fre uenciesstored in the memory

ACT


126/171 - ,a/igation p. %!

NTerrain Clearance Floor TCF1NTerrain Awareness


127/171

MODE /e6cessive terrain closure rate

MODE .e6cessive descent rate

MODE altitude loss after take%o5

) . &

a / i g a

t i o n s


128/171


129/171

MODE altitude callouts

The Terrain Clearance Floor TCF1 modecreates an increasing terrain clearance

envelope around the airport runway directlyrelated to the distance from the runway.

TERRAI& C EARA&CE' ((R

ystem

) . &

a /

i g a

t i o s n


130/171

TERRAIN A&ARENESS * DISPLA1

GP&Silluminates red as long as any mode -%.%C% alert is activated,accompanied by the voice alert for the particular mode

EGP&S selectoris guarded in the norm position %LAP O$RD mode alert caused by


131/171

O

Lateral navigation trac+ing

$ertical =eviation scale

- ,a/igation p. 1

#. 9lo3al na/igation satellite system9&$$J ATA 0

The @lo al 2avigation!anagement System @2SS1receives and processes@lo al 6ositioning System

@6S1 Signals.

The @2SS provides enroute and terminal areaguidance, autopilotcoupling, roll steering andvertical deviation non-coupled1, along definedflight plan, selected on the!C

)

)

) Selection of a flight plan and vertical navigation profile

) . &

a / i g a

t i o n s


132/171

ht "lan wa-"oints Ne6t waypoint &magenta' Other waypoint &white'

- ,a/igation p. 1

) Selection on !A6 and R2I 6B3 on the 7F+S control panelSelection of the 2AI mode on autopilot control panel


133/171

B. )o,er plant'C(" 1.1!


134/171

0 - .ower plant p. 1 1


135/171

DI%%(SER PIPES LO& PRESS(RE T(R#INE

HIGH PRESS(RE T(R#INE

HIGH PRESS(RE COMPRESSORcentrifugal type

PO&ER T(R#INE

ANN(LAR COM#(STIONCHAM#ER

RED (CTION GEAR #O) #hese e uipments are >tted on the ) !the "(W generatorthe =ropeller 1alve *odule &=1*'the propeller pump &$=' and overspeed governor

the au6iliary feathering pumpthe propeller brake &on )$ engine only' LO& PRESS(RE COMPRESSORcentrifugal type

ACCESSOR1 GEAR #O)driven by the $= spool Drivesthe D( starter generatorthe $= fuel pump

the engine oil pumps

0 - .ower p. 1 2

1. Engine schematic ATA !1:#2 Aircraft fitted with # two 6ratt =hitney, 6= "'* F *'-'"'A1, 7 &'-())1 or ! &'-())B*'-'"'A1

# two, si% lades propellers 0amilton1

+t is a free tur ines engine, composed of 5 concentric shafts of spools4 # The shaft of the 06 spool composed of the 06 tur ine and the 06 compressor rotation speed of the 06 spool4 201.

The 06 spool drives the accessory gear o% A@31 # The shaft of the 6 spool composed of the 6 tur ine and the 6 compressor # The 6ower shaft composed of ' power tur ines Free tur ines1. This ' power tur ines drive the propeller through the

reduction gear o% R@31 rotation speed of the propeller 261 B . ) o

, e r p l


136/1710 - .ower p. 1 0

8 lades propeller


137/171

*"J =W) &Full stop': *a6imum =ower #P up to--@U &On emergency only' O around position &!eginning of the ramp': )#O #P up to-88U

NO#($ position:=W) * # in #O: N= -88U and 8,L )#O #P up to L8U *(# N= -88U and #P up to L8,LU &E.%.-."' N= -88U and #P up to -88U & .%@88' (/! N= 3.U and #P up to LEU &E.%.-."' N= 3.U and #P up to -8L,EU & .%@88' ()G N= 3.U and #P up to L ,@U &E.%.-."' N= 3.U and #P up to -83,CU & .%@88'

)eversion in manual mode when ++( F"0/# &green band [email protected]' Flight ;dle positionround ;dle position

)everse position

2. )o,er and propeller controls ATA !1:#2The different powers of the engine are4 S064 Shaft 0orse 6ower1

#24212A 24 # RT Reserve Take ff1 ma%imum power1 '*() S06 '&))

S06 >sed in case of an engine flame out during take off up trim1 or in case of go around ramp1

# !CT !a%imum continuous1 '()) S06 '&)) S06 # T Take ff ),: RT 1 '&*( S06 '"8) S06 # Clim '":' S06 '"8) S06 # Cruise '"5' S06 '"5' S06

6ower 6=R1 M Tor ue T/1 % 26For the same power4 +f T/ increases, 26 decreases

+f T/ decreases, 26 increases

6ower setting is characteri$ed y constant power lever 6 1 and condition lever C 1 positions. The power adapted to

the flight phase is selected y the pilot through a power management selector 6=R !@T1.

# =ith input coming from the 6=R !@T and the position of the 6 , the 77C 7ngine 7lectronic Control1 control the fuelflow to the engine.


138/171

CONDITION LE$ER

)egardless of the =W) * # position, N= is at -88U

"0#O position: !lade angle governing mode #he N= is regulated by the =+( &!lade angle change' =W) * # in: #O N= -88U *(# N= -88U

(/! N= 3.U()G N= 3.U

Fuel governing mode #he N= is regulated by the ++( &Fuel Flow change' ground operation in low power #he N= is maintained at E8 3U to have the "(W available he "(W generator is on line when N= 7 99U'

F#) &Feather position' #he fuel governing mode is cancelled &No "(W generator'

Fuel Shut O5 position: (lose the shut o5 valve on the $*0

# =ith the input coming from the 6=R !@T and the position of the C , the 67C 6ropeller 7ngine Control1 control the 26 propellerspeed1 y changing the lades angle.

B . ) o

, e r p l


139/171

C

/;N+ ": One engine out operation /;N+ !: Normal #O or *(#/;N+ (: (/! /;N+ D: ()GNOTE0 Sensible sector designed toallow for >6 throttle engine control

NO

A -8.U #P

)#O &0= #);*' -88U #P -88U Np

*(# O) #O # #O L8U #P -88U NpD *(# L8 LU #P -88U Np

W"//)"*=

#($

C

/;N+ ": One engine out operation /;N+ !: Normal #O or *(#/;N+ (: ()GNOTE0 Sensible sector designed toallow for >6 throttle engine control

NO

A -8.U #P

)#O &0= #);*' -88U #P -88U Np

*(# O) #O # L8U #P -88U Np

W"//)"*=

#($

# The 6=R !@T has four positions4 T , !CT, C 3, CR # Considering that C s are in A>T and the 6 s are at this

position marked y the notch, the control system delivers ma%rated power corresponding to the mode selected the ma% ratedpower is delivered only when the engine is notthermodynamically limited1

ATR #24212A

S06

2750

2500247521922132

NORMAL OPERATION, EEC ON, ISA CONDITIONS

115% T

0 50 !7 "1 100

6 =7R 7I7R A2@ 7

# T # !CT # C 3 # CR

6=R M '&*(S06 6=R M'()) S06 6=RM '":' S06

26M"))L26M"))L26M9'L26M9'L

T/ M :)LT/ M :),:LT/ M :*LT/ M :&,(L

The RT Reserve Take- ff1 is o tained in case of up trim one engine out during take off1 or with the 6 to the ramp

# RT 6=R M '*() S06 26M"))L T/ M "))L

ATR 24S06

NORMAL OPERATION, EEC ON, ISA CONDITIONS

115% T

2400

21!0

2132

0 50 !7 "1 100

R 7I7R A2@ 7 # T 6=R M '"8) S06 26M"))L T/ M :)L # !CT 6=R M '&)) S06 26M"))L T/ M "))L # C 3 6=R M '"8) S06 26M9'L T/ M "):,*L # CR 6=R M '"5' S06 26M9'L T/ M ")9,5L


140/171

The RT Reserve Take- ff1 is o tained in case of up trim one engine out during take off1 or with the 6 to the ramp

# RT 6=R M '&)) S06 26M"))L T/ M "))L


141/171

! Engine in=icator

TOR (E in=! &D( +*+)'. probes located on the reduction gear bo6 shafts sends signal to the "F0 &"uto Feathering 0nit' and to the ++( &+ngine +lectro

#he "F0 controls the pointer and the ++( controls the digital display

ITT in=!&D( +SS' from 8 to -.88A( )ed point: .8?? ma6)ed point H S: @??ma6 on start $: limite for hotel mode operation

OIL PRESS in=!&*ain D( !0S' from 8 to L8 =S;

OIL LO& PRESS Lt2 8 =S; " separate press sw activates (("S below 8 =S;

OIL TEMP&*ain D( !0S' from 8 to -C8

INTERNAL #(Gcomputed by FD"0V shows )#O * # on # O, otherwise ma6 #P depending on =W) * # s

B . ) o

, e r p l


142/171

EECacts on stepper motor to regulate Fuel Flow

LT Bashingailure #he fuel


143/171

%A(LTilluminates when both =+( channels are lost ("=

FF( is deactivated and N= is limited at -8.,@U if power is su cient

MGT

a6ial sw &/$: bottom )$: #O=' providing FD"0, =+( and ++( with basic power re uirements

SGL CH

illuminates when one channel is lost &.?? for self test when advancing (/ from F#) to "0#O'

9! I=le gate

GATE %AILilluminates amber and the (("S is activated when the gate does not engage automatically in


144/171

Annexes


145/171

Anne1es p. 1 %


146/171

%ire test*WH()(H +N - F;)+ on ("=HFire handle illuminatedHF0+/ S O /t on (/ &if out of Fuel S O position'%ault test*(HS(H loop on ("= F"0/# /ts on " ! /oop pbO%%

#akes respective loop out of parallel circuit "llows other loop to activate >re signal

ear position secondary system as sensed by *F( .(NL' gear not in selected position or uplock not opened &on nd'Green Ltdown lock engaged

Anne1es p. 11

Annex 1. Coc-pit panelsE&9I&E 'IRE 8A&D E6ulled4 on the respectiveengine 6rop Feather Fuel 6 valve closed

Air 3leed valve closed

7 0;< 6=R1.


147/171

#o call cabin from cockpit &S(' #o be called by cabin attendant: blue /t and door bell(ancelled when pressing )+S+# pb

#o call mechanic $O)N is activated #o be called by mechanic: !lue /# and Door !ell(ancelled when depressing )+S+# =b

Do not use above -98 kts +SS !0S

Anne1es p. 111

Fuel delivery pressure elow& 6S+. 6ump failure or fuelstarvation. CA6.

Shows position of valve.2o ar M valve fault or moving.

R6&+lluminates green whenelec fuel pump is running.

(''disconnect the elect pumpand force to close the motiveflow valve

Feeder Tk Fuel Temp +nd

0 only S "1Range #8)JCB)JC1

3oth domes S "1FB only in asic mode se in asic mode to limit tsin ca in.

ight on the R0 side only.

Two fluorescent lights under glareshield.


148/171

n e%ternal power, pedestal 63must e on to power CIR test

Supplied y AC=.

6&DS1and SS from TR>is effective.'A6 T

3attery charger failure detectedy !FC. CA6.

Contactor Auto opens !FC1 if4thermal runawayB3us voltageG'(I B start se uenceB3at swon IR.

Auto reset if underspeed4 inother cases manual reset.3TC auto closes.

'A6 Tilluminates when4

starter remains 2 with20H&(L

or @C> failure during startor starter failureor 72@' only 6R 6 3RD

2 @ust lock not engagedStarting not inhi ited1.

(&Continuous ignition oth A

31. !emo panel light.

(&started engaged. At &(L 20,light out, starter disengagesautomatically.CRA&5dry monitoring no ignition1.

$TARTselects a start se uence.

+n flight regardless of startselection A, 3, A 31 othe%citers are energi$ed.

READ?engagement ordisengagement cond. Are met4

# ABC on ground # gust lock engaged # C on FT0 of F>7 SB # lue hyd press H '")) 6S+ # fire handle not pulled

)R() *R56rop rake fully locked.!emo panel light.

6rop 3rake not fully locked ornot fully released. After "( secMCA) .


149/171

Supplied y S3ack up S "1.

Supplied y S '.


150/171

ALPHA"(W supply"mber /# illuminates in case of Failure or =wr loss CAPTATno heated CAP &"(W supply' $eating inhibited on groundPITOTtube not heated CAP &"(W !0S for (=# X F O'PITOT ST#1 not heated &("='"(W bus - or --@ "( S#!4 !0S as back up

supply &inhibited when N= 29CU'Tr loss on at least - !lade

Mc on per C bladesV then -8 sec o5 between cycles

H PO&ERon per C blades No pause between cycles &ON /# illuminates !/0+'

$TATStatic source not heated orfailed. CA) on ground only

S1. no alarm inflight1

(&

S1( 8TTemp H"'"JC '()JF1. CA) no auto off1

"ain 9REE& )6")Supplied y AC=, controlled

y S.

X'EED63 released. ?feed closed63 pressed4 2 Tilluminated =0+T7, ?feedvalve selected 672. 7%ceptin case of I where the

?feed is locked closed1( )R

pump delivery pressure lessthan "()) psi. CA6. 2o autooff.

( E Eassociated compartmentG',( lt CA) . ?feed openinginhi ited.

A n

n e x e s

Associated us not supplied

A AI@6> has een checked y 36C>A AI (&@6> supplied AC= system. @6>has always the priority on oth @72

A>T reset in case of underBoverspeed4 manual reset otherwise. AC=SIC7 3>S auto shed if one @72 is

*TC Allows 36C> to control 3TCoperation.7%t 6wr or simple @72operation4 3TC is closed

@reen Flow 3AR1. Auto closure when either AC= @72 drops off line.I$(3TC opened 6 released

out1. !in 2p for AC=M 88L.

'A6 T6ower loss or failureP CA) .

(& AC= supplied. 0orns heati

systems 42 72pec 1.0 copy

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