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ATR 42-500, Manual, Page: 28 / 129

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ATR 42-500 Manual Download Page 28

D - Air

p. 27

T/O elevation up to 3500 ft

Baro setting by CAPT

Altimeter (ADC 1) or 1013

(ADC 2) if failure ADC 1

Landing elevation

Cabin pressure

Digital controller

AUTO MODE

Electropneumatic

outflow valve

Pneumatic

outflow valve

Manual controller knob

MANUAL MODE

Safety device

if DIFF > 6.35 PSI

or < –0.5

4. Pressurization  

ATA 21

Compressed air is delivered by the packs. Pressure is controlled by the amount of cabin air discharged outboard.

4.1. Schematic

FL 250 = DIFF 6 PSI

Cabin altitude 6740 ft

Normal rate = 30% aircraft 

VS, max +550 ft/min

FL 100 = DIFF 4 PSI

3500 ft

Cabin altitude = aircraft altitude

 – 300 ft before LDG

  0 ft  after LDG

normal rate – 400 ft/min

fast rate – 500 ft/min

Normal rate = 50% aircraft 

VS, max +600 ft/min

FL 200 = DIFF 5 PSI

Summary of Contents for 42-500

Page 1: ...72 212A 42 500 ...

Page 2: ...er including their ATA classification along with cockpit location Cockpit panels familiarisation is presented with each relevant system description in a separate annex This new guide release is intended for training on ATR 42 500 and 72 212A It presents a generic aircraft not customized to your own aircraft systems Should you find any discrepancy between Systems guide and your customized ATR opera...

Page 3: ...l TO Config test 19 5 Aural alarms 20 Chapter D Air 1 Pneumatic system 22 1 1 Schematic 22 1 2 AIR BLEED panel 23 2 Air conditioning 24 2 1 Schematic 24 2 2 COMPT TEMP panel 25 3 Avionics ventilation 26 3 1 Schematic 26 3 2 AVIONICS VENT panel 26 4 Pressurization 27 4 1 Schematic 27 4 2 Cabin pressure indicators 28 4 3 Auto press panel 28 4 4 MAN RATE Knob Cabin press panel 28 Chapter E Automatic ...

Page 4: ... In dual DC GEN LOSS with the battery toggle switch on OVRD and second OVRD selected 45 2 7 Emergency supply In dual DC GEN LOSS with TRU 46 3 DC AC panel 47 4 ACW schematic 48 5 ACW panel 49 6 Breakers panels 50 6 1 Overhead panel 50 6 2 Electric rack behind F O 50 Chapter H Emergency equipment 1 Emergency equipment situation 52 2 Emergency lighting system 52 3 First aid kit 53 4 Crash axe 53 5 M...

Page 5: ...SI with composite mode 67 5 EHSI ARC MODE with terrain or weather radar information 67 6 Source failure alert 67 7 Sources switching panel 68 8 EFIS control panel 68 9 Weather radar control 69 9 1 Primus 800 69 9 2 Primus 660 69 10 AHRS erect PB 69 11 TAT SAT indicator 70 12 Clock 70 13 RCDR panel 70 14 STBY instruments 70 15 Airspeed indicator 71 16 Altimeter 71 17 RMI 71 18 Flight data entry pan...

Page 6: ...GEAR position indicators 93 4 Landing gear handles 93 5 Brakes temperature and antiskid 93 6 Emergency parking brake handle 93 7 Steering handwheel 93 Chapter P Navigation system 1 Nav control box 95 2 Marker switch 95 3 ADF control box 95 4 EGPWS alert modes 95 5 EGPWS pb 99 6 EGPWS selector 99 7 Global navigation satellite system GNSS 100 Chapter Q Power plant 1 Engine schematic 102 2 Power and ...

Page 7: ...A Aircraft general p 6 A Aircraft general p 6 A Aircraft general FCOM 1 00 ...

Page 8: ...tion ATA 52 Pilot communication hatch Rear entry door emergency exit type I Cargo door Aft avionics compartment door Emergency exit type III Service door emergency exit type I Pilot emergency hatch Forward avionics access hatch ...

Page 9: ...s ON when all door hooks and latch locks are fully engaged CARGO LIGHT switch allows activation of the cargo bay light from outside Panel cover switch connects 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 MFC 1A and 2A is performed to initiate the control system of the cargo door Actuator selection switch is...

Page 10: ...ircraft general p 9 A Navigation lights B Taxi and T O lights C Landing lights D Wing lights E Beacon lights F Strobe lights G Logo lights H Emergency light 4 External lights ATA 33 Memo panel Cabin panel ...

Page 11: ... at least 1 GEN operating NO SMKG and SEAT BELTS Blues Lts on MEMO panel when ON DC BUS 2 DISARM system deactivated STROBE LAND supplied by ACW BUS 1 Left Hand ACW BUS 2 Right Hand ON emergency exit lights illuminates Supply DC STBY or 6 V BAT packs SEAT BELTS illuminates blue when associated switch is selected ON NO SMKG illuminates blue when associated switch is selected ON 5 EXT LT panel ATA 33...

Page 12: ...A Aircraft general p 11 8 Internal lighting ATA 33 ...

Page 13: ...re ON with maximum intensity and fluorescent tubes are ON STBY COMPASS switch to illuminate the STBY COMPASS ON and OFF position CAPT READING LT knob selectsactivationandintensity of the respective spot light To check and control the intensity of the annunciator lights on the overhead and pedestal panels the overhead panel flow bars TEST All the associated lights come on bright BRT associated ligh...

Page 14: ...B Multi Function Computer p 13 B Multi Function Computer FCOM 1 01 ...

Page 15: ...c funtions are performed by two independant computers MFC1 and MFC2 Each computer includes two independant modules A and B The purpose of these computers is to monitor control authorise operation of the aircraft systems manage system failures and flight enveloppe anomalies and command triggering of associated warning The MFC functions can be treated in one module only in several modules redundancy...

Page 16: ...C Centralized crew alerting system p 15 C Centralized crew alerting system FCOM 1 02 ...

Page 17: ...on all the lights are extinguished Dark cockpit philosophy With few exceptions the lights illuminate to indicate a failure or an abnormal condition Normal operation Warning indication Caution indication Other than normal basic operation Temporarily required system in normal operation Back up or alternate system selected ...

Page 18: ... affected by the failure Three types of visual devices are used MASTER WARNING and MASTER CAUTION lights CREW ALERTING PANEL CAP lights LOCAL ALERT lights Detection sequence INFORMATION IDENTIFICATION ISOLATION Example ACW Generator 1 failure MASTER CAUTION light flashing Single Chime ELEC light on the CAP Local alert fault light on the ACW gen 1 push button ...

Page 19: ...stem failure PRKG BRK Parking brake not fully released RCL When pressed all inhibited or cancelled caution lights will illuminate recall if the respective system is still degraded or manual cancellation of T O INHI CLR When pressed all amber lights are cleared except PRK BRK GPWS and MAINT PNL PITCH DISCONNECT Elevator uncoupling PROP BRK Prop brake not locked in full locked or in full released po...

Page 20: ...Any DC or AC power failure FLT CTL During T O or T O config test pitch trim out of green sector or flaps not at 15 AIL LOCK actuators not fully retracted disagreement between Ail lock acts and Gust lock lever Flaps asymmetry 6 7 TLU fault Stick pusher or stick shaker fault or pitch trim asym AIL LOCK EFIS COMP AHRS or LOC GS disagreement FUEL Engine feed low press 4 psi or tank low levels AFT SMK ...

Page 21: ...ing system CLACKER VMO VLO 5 kt VFE 5 kt DOOR BELL Hostess or ground calls WHOOLER Pitch trim in motion more than 1s CAVALRY CHARGE AP Disconnects C CHORD Altitude alerts CRICKET Stall warning associated STICK SHAKER PUSHER AOA Angle Of Attack 5 Aural alarms ATA 31 ...

Page 22: ...D Air p 21 D Air FCOM 1 03 ...

Page 23: ... 1 Schematic LEAK OVHT LEAK OVHT HP VALVE HP VALVE BLEED VALVE BLEED VALVE OVER PRESSURE SWITCH 80 PSI ENG WING DE ICING ENG WING DE ICING ENG 2 BLEED ENG 1 BLEED PROP BRK SELECTOR T LOOP T LOOP T 153 C T 153 C T 274 C T 274 C T 270 C T 270 C PACK 1 PACK 2 ENG 2 FIRE HP LP LP HP ENG 2 ENG 1 LEFT LEAK DETECTION LOOP RIGHT LEAK DETECTION LOOP X VALVE OPEN OFF FAULT ENG 1 FIRE OFF FAULT OFF ON ...

Page 24: ...e fire T pulled when UPTRIM is triggered or prop break on left one only Inhibited during eng start GRD X FEED Spring loaded closed Ground only inhibited in flight Auto opens when only one bleed valve is opened LEAK activates when T detected by bleed loop exceeds 153 8 C CAP Auto closure after 1 of following valves Bleed HP pack and GND Xfeed if left bleed leak affected DO NOT RESET BLEED ENG BLEED...

Page 25: ...ure humidity and cleanliness for the comfort of the passengers and crew 2 1 Schematic MAN OVHT HIGH ELECTRONIC TEMPERATURE CONT OFF FAULT FLOW BLEED AIR N O R M MAN PACK VALVE DISAGREE PACK VALVE GROUND INLET GROUND COOLING FAN RAM AIR INLET TURBO FAN SHUT OFF VALVE HEAT EXCHANGERS EXHAUST TURBINE COMPRESSOR HOT BY PASS VALVE TEMP CONTROL VALVE TIC VALVE WATER EXTRACTOR CONDENSER MIXING CHAMBER RE...

Page 26: ... FAULT fan low speed or motor overheat AIR on CAP No auto disconnect TEMP SEL AUTO the temperature is closed by the electronic temperature controller taking into account duct temperature zone temperature demand selector associated compartment temperature aircraft skin temperature FLOW NORM 22 psi pack valves HIGH 30 psi pack valves MAN compt temp knob controls directly temp control valve 2 2 COMPT...

Page 27: ...BD VALVE AUTO except for emergency direct control of OVBD valve The full open position is possible only if the delta P is 1 psi FAULT OVBD valve in disagreement with ovbd valve SW position OVBD extract fan off OVBD valve partially opened in flight only U F valve closed 3 2 AVIONICS VENT panel 3 Avionics ventilation ATA 21 The ventilation system provides cooling through ambient air extraction to li...

Page 28: ...fety device if DIFF 6 35 PSI or 0 5 4 Pressurization ATA 21 Compressed air is delivered by the packs Pressure is controlled by the amount of cabin air discharged outboard 4 1 Schematic FL 250 DIFF 6 PSI Cabin altitude 6740 ft Normal rate 30 aircraft VS max 550 ft min FL 100 DIFF 4 PSI 3500 ft Cabin altitude aircraft altitude 300 ft before LDG 0 ft after LDG normal rate 400 ft min fast rate 500 ft ...

Page 29: ...ET Trigger switch to set landing elevation DESCENT RATE NORM 400 ft min FAST 500 ft min Fast is used when Vs 1500 ft min TEST Displays alternately 18800 and 8800 FAULT appears on MAN pb Test is inhibited in flight 4 3 AUTO PRESS panel DITCH pb ON both outflows are fully closed FAULT digital controller failure CAP AIR on CAP NORM AUTO MODE position When used in MAN mode cabin rate selection 2500 15...

Page 30: ...E Automatic flight control system p 29 E Automatic flight control system FCOM 1 04 ...

Page 31: ...s the preselected altitude on ADU CRS 2 knob selects course on F O EHSI CRS 1 knob selects course on CAPT EHSI FD bars horizontal bar for vertical modes and vertical bar for lateral modes When depressed actives HDG HOLD and GA mode Touch Control Steering pb allows to control temporary the aircraft AP arrows extinguish In basic mode attitude limits 15 and bank angle limits 35 1 Schematic ATA 22 ADU...

Page 32: ...P engaged ALT mode to use FD with a desired altitude 2 ADU ATA 22 3 AFCS control panel ATA 22 MESSAGES DISENGAGED ANNUN DATA FAULT ENGAGE INHIBIT CPL DATA INVALID AHRS DATA INVALID DADC DATA INVALID AFCS DATA INVALID AP INVALID SELECT ALT ALT SEL FT ALT SEL 3000 FT ARMED and CAPTURED MODE VERTICAL MODE ALT ALT ALT IAS KTS IAS 160 KTS VS FPM VS 600 FPM GS GS GS GA ARMED and CAPTURED MODE LATERAL MO...

Page 33: ...F Communications FCOM 1 05 p 32 F Communications ...

Page 34: ...nt station ground crew stations 2 PTT selector and NOSE WHEEL STEERING CONTROL SW ATA23 COM SYSTEMS NAVIGATION SYSTEM COCKPIT VOICE RECORDER CABIN ATTENDANT GROUND CREW PASSENGER PUBLIC ADDRESS SYSTEM GPWS TCAS REMOTE CONTROL AUDIO UNIT CAPT SIDE oxy mask mike hand mike boom set head set PTT switch nose wheel steering control loudspeaker loudspeaker audio level audio control panel F O SIDE oxy mas...

Page 35: ...ning of associated RCAU processing board NORM RCAU functions normally FAULT illuminates amber and the CCAS is activated when an associated RCAU processing board failure or power loss is detected ALTN affected crew station is connected directly to VHF 1 for CAPT station or VHF 2 for F O station Volume is adjusted by affected loudspeaker volume control 5 AUDIO SEL pb ATA 23 Transmission keys Only on...

Page 36: ... is used in case of undue alert or to test the emergency beacon two cases are possible for the test net work X MIT ALERT illuminates amber during 2 failure XMIT ALERT lt flashes during 15 seconds 8 EMER LOC XMTR panel ATA 23 Cabin attendant handset PA public adress to make an annoncement to passengers INT internal communications with crew EMER emergency call 9 Cabin attendant handset ATA 23 10 Han...

Page 37: ...ecalled by momentarily pressing the PRE button again TEST button initiates the radio self test routine 13 ATC box ATA 23 COCKPIT VOICE RECORDER Monitor indicator for test only Movement of pointer in white band indicates all channels are operative ERASE pb provides fast erasure of tape recordings when the landing gear shock absorbers are compressed and parking brake is set depress for 2 sec to comp...

Page 38: ...G Electrical systems p 37 G Electrical systems FCOM 1 06 ...

Page 39: ...h variable frequency ACW Two DC starter generators 45 NH starter mode 61 5 NH generator mode Two batteries DC GPU DC power 28 VDC Two inverters AC power VAC 26 V VAC 115 V Two AC wild frequency alternators minimum NP 66 ACW power 115V 200V ACW GPU DC power 28 VDC TRU Emergency supply The TRU provides power to the emer gency loads in case of dual DC generators loss It is supplied by the ACW bus 2 ...

Page 40: ...eduction Gear Box and is available with NP 66 DC Starter Generator ACW Generator Accessory gear box Reduction gear box In Hotel Mode or with the propeller feathered there is no ACW When the propeller is unfeathered CL in AUTO The NP is maintained at a minimum of 70 8 in order to have ACW minimum 66 DC Starter Generator ACW Generator Accessory gear box Reduction gear box HOTEL MODE OR PROPELLER FEA...

Page 41: ... DC SVCE BUS The GOUND HANLING BUS is supplied only on ground in three different ways BAT OFF or BAT ON with the EXT PWR not available the GND HDLG BUS is supplied by the HOT MAIN BAT BUS for ground servicing only when The refueling panel is open The cargo door control panel is open The passenger door is open BAT OFF or BAT ON with the EXT PWR available but not ON the GND HDLG BUS is supplied dire...

Page 42: ... BUS INV 1 DC STBY BUS DC ESS BUS DC EMER BUS HOT EMER BAT BUS HOT MAIN BAT BUS EMER BAT CHG DC BUS 2 MAIN BAT CHG UTLY BUS 1 UTLY BUS 2 BTC DC GEN 1 EXT PWR DC GEN 2 INV 2 DC BUS 1 DC SVCE BUS GND HDLG BUS The BTC is closed and the GPU supplied all the DC and AC busses Even if the GEN are available the GPU has always the priority ...

Page 43: ...BUS DC ESS BUS DC EMER BUS HOT EMER BAT BUS HOT MAIN BAT BUS EMER BAT CHG DC BUS 2 MAIN BAT CHG UTLY BUS 1 UTLY BUS 2 BTC DC GEN 1 EXT PWR DC GEN 2 INV 2 DC BUS 1 DC SVCE BUS GND HDLG BUS ON The BTC is closed and the GEN 2 supplied all the DC and AC busses In hotel mode the GND HDLG BUS is supplied by the DC BUS 1 through the DC SVCE BUS ...

Page 44: ...BUS DC EMER BUS HOT EMER BAT BUS HOT MAIN BAT BUS EMER BAT CHG DC BUS 2 MAIN BAT CHG UTLY BUS 1 UTLY BUS 2 BTC DC GEN 1 EXT PWR DC GEN 2 INV 2 DC BUS 1 DC SVCE BUS GND HDLG BUS The BTC is opened and each GEN supply its own busses On ground the GND HDLG BUS is supplied by the DC BUS 1 through the DC SVCE BUS and disconnected when airborne ...

Page 45: ...Y BUS DC ESS BUS DC EMER BUS HOT EMER BAT BUS HOT MAIN BAT BUS EMER BAT CHG DC BUS 2 MAIN BAT CHG UTLY BUS 1 UTLY BUS 2 BTC DC GEN 1 EXT PWR DC GEN 2 INV 2 DC BUS 1 DC SVCE BUS GND HDLG BUS The BAT toggle switch has to be selected to OVRD The OVRD position allows to be sure that busses are supplied by their respective battery by overriding all protections This position is protected by a guard ...

Page 46: ...V 1 DC STBY BUS DC ESS BUS DC EMER BUS HOT EMER BAT BUS HOT MAIN BAT BUS EMER BAT CHG DC BUS 2 MAIN BAT CHG UTLY BUS 1 UTLY BUS 2 BTC DC GEN 1 EXT PWR DC GEN 2 INV 2 DC BUS 1 DC SVCE BUS GND HDLG BUS After a Dual DC GEN loss the UNDV is triggered when the DC STBY BUS 19 5 V Then by pushing on the OVRD the DC and AC STBY BUS are transfered from the HOT MAIN BAT BUS to the HOT EMER BAT BUS ...

Page 47: ...U ON AC BUS 1 AC BUS 2 AC STBY BUS INV 1 DC STBY BUS DC ESS BUS DC EMER BUS HOT EMER BAT BUS HOT MAIN BAT BUS EMER BAT CHG DC BUS 2 MAIN BAT CHG UTLY BUS 1 UTLY BUS 2 BTC DC GEN 1 EXT PWR DC GEN 2 INV 2 DC BUS 1 DC SVCE BUS GND HDLG BUS The TRU connected to the ACW BUS 2 supplies DC EMER BUS DC ESS BUS DC AC STBY BUSSES ...

Page 48: ...S OFF Associated bus deenergized ELEC on CAP INV FAULT Under over voltage at INV output INV failure or supply loss Auto Xfer of all AC busses to remaining inverter ELEC on CAP OVRD Insures basic mode operation by overriding all other protections ON Basic mode STBY busses supplied by HOT MAIN BAT BUS Ext or gen power DC STBY bus transferred to HOT EMER BAT BUS AC STBY BUS to DC BUS 1 AVAIL GPU has ...

Page 49: ... NP is above 66 When the right engine is running in hotel mode the NP 0 When the engines are running but the propeller is feathered the NP is bellow 20 In both cases the ACW Busses are not supplied ACW GEN 1 ACW BUS 1 ACW BUS 2 TRU ACW GEN 2 SVCE BUS ACW GPU NP 0 NP 70 8 The propeller unfeathered and one ACW GEN on line On ground when the propeller is unfeathered the engine is running on fuel gove...

Page 50: ...e 66 The fuel governing mode is cancelled with the propeller feathered No ACW 5 ACW panel ATA 24 NP 100 NP 100 Normal condition in flight The ACW GEN 1 supplies the ACW BUS 1 and the ACW SVCE BUS The ACW GEN 2 supplied the ACW BUS 2 The TRU is connected to the ACW BUS 2 ACW GEN 1 ACW BUS 1 ACW BUS 2 TRU ACW GEN 2 SVCE BUS ACW GPU NP 100 NP 100 One Generator Fault When one generator is fault the oth...

Page 51: ...G Electrical systems p 50 G Electrical systems 6 Breaker panels ATA 24 6 1 Overhead panel 6 2 Electric rack behind F O ...

Page 52: ...H Emergency equipment p 51 H Emergency equipment FCOM 1 07 ...

Page 53: ...gency lighting system ATA 33 flash light goggles oxygen masks life jackets halon extinguisher crash axe emergency exit type III fire resistant gloves hood goggles oxygen mask water extinguisher flash light smoke hood first aid kit bag containing oxygen masks oxygen bottle oxygen mask life jacket flash light halon extinguisher type I entry door type I service door smoke hood emergency exit type III...

Page 54: ... splints suitable for upperand lower limbs gastro intestinal antacid anti diarrhoel medication disposable gloves Crash axe with pick and edge Handle insulated up to 2000V to open of a door or a compartment megaphone 72 only With batteries morse code switch used to evacuate the cockpit With oral inflation tube CO2 sparklets inflation red toggle whistle straps battery light 3 First aid kit ATA 25 4 ...

Page 55: ...To flight crew members To protect against fire 9 Gloves ATA 25 Water extinguisher 2 liters of water with an anti ice additive discharge time 30 to 40 10 Water extinguisher ATA 26 Halon extinguisher 1 2 kg of halon gas discharge time 8 to 10 11 Halon extinguisher ATA 26 12 Oxygen schematic ATA 35 ...

Page 56: ...SS TO TEST AND RESET permits a test of oxygen flow without removing the mask from the container It is springloaded to the reset position EMERGENCY selector activates pressurization of mask delivery flow when N 100 rocker is at 100 14 Cockpit crew oxygen mask ATA 35 Portable oxygen bottle green with pressure gauge and re charge valve 120 liters under pressure 1800 psi duration 30 min at 4 ltr mn 1 ...

Page 57: ...I Fire protection p 56 I Fire protection FCOM 1 08 I Fire protection p 56 ...

Page 58: ...UTION FAN FAILURE 2 Avionics FWD and AFT smoke detection ATA 35 AFT CARGO OR LAVATORY SMOKE DETECTION Bottle N 2 ENG 2 ENG 1 Bottle N 1 FIRE DETECTION FIRE EXTINGUISHING SYSTEM The fire protection system provides detection warning and extinguishing for each engine cabin and lavatory 1 Schematic ATA 35 ...

Page 59: ...pective loop out of parallel circuit Allows other loop to activate fire signal alone FAULT TEST MC SC LOOP on CAP Fault lights in A B loop pb AGENT SQUIB armed when T handle pulled Discharges bottle DC EMER HOT MAIN BAT NORM one fan runs FAULT the fan is out of order and illuminates amber CCAS is activated ALTN The alternate fan runs ALTN light illuminates white SMK TEST Tests the smoke detectors ...

Page 60: ...J Flight control p 59 J Flight control FCOM 1 09 ...

Page 61: ...tch schematic ATA 27 The elevators ailerons and rudder are me chanically actuated The spoilers and flaps are hydraulically actuated In case of jamming pitch control will be re covered by disengaging the pitch coupling system by applying a differential force of 52 daN ...

Page 62: ...5 Stick Shaker Stick Pusher push button and light ATA 27 GUST LOCK lever permits to lock mechanically the roll and pitch axes against the wing gusts The PL travel is limited to slightly above FI 4 Gust lock ATA 27 For aircraft equipped with a spring tab on the aileron the roll locking system is composed of two electro mechanical locking devices The AIL LOCK is triggered whenever one of the locking...

Page 63: ... ADU This message authorizes to retrim on the dedicated side the other side is still inhibited Yaw TRIM control switches controls the yaw trim actuator As a safety device both levers must be moved and held in the same direction nose LH or nose RH to energize the system and trim the aircraft When used the RCU is declutched 9 Trim controls ATA 27 PITCH TRIM ASYM light illuminates to indicate a pitch...

Page 64: ...0 15 30 72PEC or 25 35 42PEC EXT flag appears to indicate that the flaps valve is hydraulically commanding flap extension If EXT flag appears when flaps are extended it means that there is a leak in the flaps hydraulic circuit 11 Flaps position indicator ATA 27 12 Flaps control lever ATA 27 ATR 72 PEC ATR 72 PEC ATR 42 PEC ATR 42 PEC 10 Flaps schematic ATA 27 ...

Page 65: ...K Flight instruments p 64 K Flight instruments FCOM 1 10 K Flight instruments p 64 ...

Page 66: ...controller too AHRU Attitude and Heading Reference Unit includes an Inertial measurement unit INU composed of three gyrometers and three accelerometers The AHRU receives inputs from its associated flux valve and the TAS fed by both ADC is used to compute gyro erection ADC Air Data Computers is supplied with static air pressure static ports total air pressure pitot ports total air temperature TAT p...

Page 67: ...EHSI ATA 34 ROLL ATTITUDE scale 0 10 20 30 45 and 60 Vertical ARM and CAPTURE mode Horizon and pitch scale is white and has reference marks at 5 10 15 20 30 40 and 60 nose up and 5 10 15 20 30 45 and 60 nose down Above 40 nose up and below 30 nose down red arrows come into view DH indication Lateral ARM and CAPTURE mode FLIGHT DIRECTOR command bars magenta SLIP indicator LOCALIZER indication GLIDE...

Page 68: ...owing 45 either side of actual heading 044 Digital heading display SGU FAILURE alert A and B part failure and all information disappears from EADI and EHSI SGU FAILURE alert C part failure and a red cross appears on EADI and EHSI AHRS FAILURE the associated information immediatly disappear from both CRTs ATT FAIL message is displayed AHRS FAILURE the associated information immediatly disappear fro...

Page 69: ...ness inner knob WX DIM to set ON OFF weather radar traces N 2 BRG selector to select green bearing pointer to VOR 2 or to ADF 2 or to GPS active waypoints RB NAV 2 RNV pb to select the GPS mode MAP pb permits to select MAP selection with waypoints of the flight plan 8 EFIS control panel ATA 34 ATT HDG pb enables to use AHRS 2 information When captain pb is depressed SYS 2 illuminates white on CAPT...

Page 70: ...us 800 10 AHRS erect PB ATA 34 AHRS erect pb illuminates amber when the associated AHRS loses the TAS signal from the ADC If the aircraft is stabilized unaccelareted level flight a gyro fast erection may be performed by depressing the associated pb for 15 s MODE selector OFF radar is off STBY radar ins on but no pulse is sent by antenna TEST range at 100 NM 3 arcs green yellow and red WX normal op...

Page 71: ...le is given by a scale marked at 10 20 30 60 and 90 degrees Setting knob when pulled causes a rapid erection if the instrument is powered STANDBY ALTIMETER With baro set knob altitude pointer and Hpa counter 14 STBY instruments ATA 34 RCDR pb when depressed both cockpit voice recorder and digital flight data recorder are energized manual mode ON lt illuminates blue RESET pb when depressed inhibits...

Page 72: ...ED FLAG indicates a failure affecting the VMO channel or the airspeed indicator 15 Airspeed indicator ATA 34 ALTIMETER With baro set knob in MB and IN HG ALTIMETER With baro set knob in Hpa and IN HG ALTITUDE ALERT lt illuminates amber when altitude alert is triggered 1000 ft or 250 ft 16 Altimeter ATA 34 RADIO MAGNETIC INDICATOR RMI is coupled to the opposite AHRS with a compass rose showing magn...

Page 73: ...INTER white indicates present vertical speed Pointer displayed when vertical speed is valid OPEN DIAMOND shows other traffic Range and bearing of other aircraft within surveillance range and selected range and altitude for display SOLID CIRCLE intruder TA generated Range and bearing relative to own aircraft RANGE RING white 2 miles radius range about own aircraft A B Mode button select display of ...

Page 74: ...L Fuel system p 73 L Fuel system FCOM 1 11 ...

Page 75: ...ys full to protect the engine feed system against negative or lateral load factors Gravity filling cap Refueling panel Main wing tank Vent surge tank Access door Vent surge tank 100 l Main wing tank Feeder tank 200 l 160 kg Total quantity 5000 kg ATR 72 Refueling point Gravity filling cap Refueling panel Refueling point Main wing tank Vent surge tank Access door Vent surge tank 100 l Main wing tan...

Page 76: ...JET PUMP ENGINE SHUT DOWN WITH ELECTRICAL PUMP RUNNING Both fuel engine electrical pumps push buttons are pressed IN and green RUN lights illuminate The electrical pumps are energized and begin to supply fuel to engines The FEED LO PR amber light extinguishes when the pressure is 4 psi on the line At the same time the feeder jet pump is activated by the electrical pump output pressure to supply an...

Page 77: ...low Valve in order to supply the Engine Feed Jet Pump The Engine Feed Jet Pump begins to operate by driving fuel from the feeder tank At the same time it supplies the Feeder Jet Pump When the Engine Feed Jet Pump outlet pressure reaches 8 5 PSI the electrical pump is de energized after 30s time delay In normal operation of the fuel system the engine is only supplied by the Engine Feed Jet Pump and...

Page 78: ...DER COMPARTMENT ENGINE 1 HMU CCAS FCOC LP VALVE R TANK FUEL X FEED FEEDER JET PUMP ENGINE FEED JET PUMP Cross feed valve could be used to supply an engine from the opposite tank The cross feed is not used to tranfer fuel from one tank to the other tank With the Xfeed valve push button pressed IN the valve opens green flow bar is horizontal Both electrical pump are energized By selecting OFF the co...

Page 79: ... HMU CCAS FCOC LP VALVE R TANK FUEL X FEED P 5 PSI FEEDER JET PUMP ENGINE FEED JET PUMP 5 Engine feed jet pump low pressure ATA 28 In the event of engine feed jet pump failure the pressure switch 5 psi provides electrical pump running control which ensures fuel supply to the engine The electrical pump delivers the necessary flow rate for engine consumption ...

Page 80: ...PUMP 6 Low level ATA 28 When the low level is triggered on one tank its electrical pump is automatically activated Two cases of low level LO LVL with fuel quantity indicator 160 kg Low level of the remaining fuel in the tank LO LVL with fuel quantity indicator 160 kg Feeder tank not full due to a failure of the feeder jet pump In this condition the fuel is transfered from the main tank to the feed...

Page 81: ...PULL CROSSFEED VALVE ELECTRO PUMP MOTIVE FLOW VALVE PUMP L TANK FEEDER COMPARTMENT ENGINE 1 HMU CCAS FCOC LP VALVE R TANK FUEL X FEED P 600 mbar P 4 PSI FEEDER JET PUMP ENGINE FEED JET PUMP In case of engine fire when corresponding engine fire handle is pulled it closes associated LP shut off valve ...

Page 82: ...Lt When the quantity is 160 kg or When the quantity is 160 kg but the feeder tank is not full Feeder jet pump failure PUMP Control electrical pump power and jet pump motive flow valve Runs automatically if jet pump press 5 PSI or till reaching 8 5 PSI during engine start XFEED in line fuel LO LVL When the quantity is 160 kg or When the quantity is 160 kg but the feeder tank is not full Feeder jet ...

Page 83: ...M Hydraulic system p 82 M Hydraulic system FCOM 1 12 M Hydraulic system p 82 ...

Page 84: ... ON LO PR ON AUX PUMP LO LVL PROPELLER BRAKE Total fluid volume 9 6 l normal filling 9 35 l minimum filling 8 5 l alert level 2 5 l 1 Schematic ATA 29 The aircraft has two hydraulic systems designated blue and green Each system is pressurized by an electric pump supplied by ACW power The blue system is also provided with and auxilliary pump supplied by DC power automatic or manual mode ...

Page 85: ...running conditions simultaneoustly AUX Pump pb depressed at least one engine running blue system press 1500 psi prop brake off gear lever down supply DC BUS 2 or Hot main bat bus 2 HYD PWR panel ATA 29 BRAKE ACCU by blue system for emer brakes max 6 applications DC STBY Green HYD SYST Green system hydraulic pressure indicator Blue HYD SYST Blue system hydraulic pressure indicator 3 Pressure indica...

Page 86: ...N Ice and rain protection p 85 N Ice and rain protection FCOM 1 13 ...

Page 87: ...reas Ice detector monitors ice accretion It is connected to the CCAS 1 Schematic ATA 30 AILERON HORNS ELECTRICAL WINGS BOOTS PNEUMATIC ICING EVIDENCE PROBE PROBES ELECTRICAL ICE DETECTOR ENGINE AIR INTAKE BOOTS PNEUMATIC HORIZONTAL TAILPLANE BOOTS PNEUMATIC RUDDER AND ELEVATOR HORNS ELECTRICAL WINSHIELD ELECTRICAL SIDE WINDOWS ELECTRICAL PROPELLER ELECTRICAL ...

Page 88: ...Outer surface 2 C Inner 21 C CAPT STBY and F O Normal operation ON depressed and OFF released PITOT STBY not heated ACW BUS 1 or 115 AC STBY BUS as back up FAULT detector failure or supply loss ACW BUS 2 CAP PTT pb press for 3 icing will flash if system works correctly FAULT LT illuminates steady if ice detector failure is detected ICING AOA Lt DC emer BUS Illuminates green as soon as 1 horn anti ...

Page 89: ... ICE VALVE BLEED VALVE T 230 C ENG 1 A A B B INTERNAL DUAL DISTRIBUTION VALVES DUAL DISTRIBUTION VALVES DISTRIBUTION VALVE B B B B A A A 4 A EXTERNAL 1 EXTERNAL 2 EXTERNAL 2 EXTERNAL 1 INTERNAL ENG 2 CCAS BLEED VALVE AIRFRAME AIR BLEED ISOLATION VALVE ISOLATION VALVE DISTRIBUTION VALVE DISTRIBUTION VALVE A A B B MODE SEL AUTO AIRFRAME 1 ENG 2 3 5 6 2 1 1 2 3 4 5 6 7 5 De icing schematic ATA 30 ATR...

Page 90: ... VALVE BLEED VALVE T 230 C P 14PSI ENG 1 A A B B INTERNAL DUAL DISTRIBUTION VALVES DUAL DISTRIBUTION VALVES DISTRIBUTION VALVE B B B B A A A A A EXTERNAL 1 EXTERNAL 2 EXTERNAL 2 MEDIAN EXTERNAL 1 INTERNAL ENG 2 CCAS BLEED VALVE AIRFRAME AIR BLEED ISOLATION VALVE ISOLATION VALVE DISTRIBUTION VALVE DISTRIBUTION VALVE A A B B AIRFRAME 1 ENG 2 3 4 5 6 7 2 1 1 2 3 4 5 6 7 B A MEDIAN ...

Page 91: ...ice cycle on the engine air intake deice valve opened even if AFR AIR BLEED off AIR FRAME FAULT valve opened but no downstream press Or valve closed and downstream press Detected CAP AIR FRAME ON signal sent to MFC to start deice cycle on the airframe MODE SEL ENG AND AIRFRAME SLOW 240 cycle FAST 60 cycle AFR AIR BLEED FAULT air dowstream deice valve 14 psi more than 10 OR Air upstream of the deic...

Page 92: ...O Landing gear p 91 O Landing gear FCOM 1 14 ...

Page 93: ...G HANDWHEEL LANDING GEAR CONTROL 1 Landing gear description ATA 32 The landing gear is hydraulically operated In case of hydraulic failure it may be extended by gravity EMERGENCY PARKING BRAKE HANDLE PILOT BRAKE PEDALS 2 Brakes schematic ATA 32 ...

Page 94: ...pin up speed 35 kts or 5 sec touchdown protection CAUTION THE TEST INHIBITS BRAKES PARKING BRAKE permits a full pressure on the brakes When brake handle is not in the fully released position amber PRKG BRK caution light illuminates on CAP and is taken into account by the T O CONFIG Springloaded to the off position System 2 UNLK gear not locked in selected position or on GND uplock box not opened G...

Page 95: ...P Navigation system p 94 P Navigation system FCOM 1 15 P Navigation system p 94 ...

Page 96: ...activate frequencies stored in the memory NAV POWER SELECTOR to energize the control box and associated VOR ILS DME receivers HLD holding the DME on the current active frequency ACT Direct active tuning mode to change directly the active frequency 1 Nav control box ATA 34 MKR SW is used to set marker sensibility 2 Marker switch ATA 34 XFR MEM switch XFR exchanges active and preset frequency MEM to...

Page 97: ...P Navigation system p 96 P Navigation system MODE 3 altitude loss after take off MODE 2 excessive terrain closure rate MODE 1 excessive descent rate ...

Page 98: ...P Navigation system p 97 MODE 4 unsafe terrain clearance MODE 5 below glideslope ...

Page 99: ... Navigation system MODE 6 altitude callouts TERRAIN CLEARANCE FLOOR The Terrain Clearance Floor TCF mode creates an increasing terrain clearance envelope around the airport runway directly related to the distance from the runway ...

Page 100: ...OVRD mode 4 alert caused by flap extension is inhibited to avoid nuisance in case of flapless landing 6 EGPWS selector ATA 34 This function use the aircraft geographic position from the GPS aircraft altitude and a worldwide terrain database to predict potential conflict between the aircraft flight path and the terrain and to provide aural alert and graphic displays of the conflicting terrain TERRA...

Page 101: ...e and terminal area guidance autopilot coupling roll steering and vertical deviation non coupled along defined flight plan selected on the MCDU Lateral navigation tracking Vertical deviation scale Flight plan waypoints Next waypoint magenta Other waypoint white Selection of a flight plan and vertical navigation profile Selection on MAP and RNV P B on the EFIS control panel Selection of the NAV mod...

Page 102: ...Q Power plant p 101 Q Power plant FCOM 1 16 ...

Page 103: ...tarter generator the HP fuel pump the engine oil pumps 1 Engine schematic ATA 61 72 Aircraft fitted with two Pratt Whitney PW 127 F 72 212A E 42 500 or M 42 500 72 212A two six blades propellers Hamilton It is a free turbines engine composed of 3 concentric shafts of spools The shaft of the HP spool composed of the HP turbine and the HP compressor rotation speed of the HP spool NH The HP spool dri...

Page 104: ...L and condition lever CL positions The power adapted to the flight phase is selected by the pilot through a power management selector PWR MGT With input coming from the PWR MGT and the position of the PL the EEC Engine Electronic Control control the fuel flow to the engine MAX PWR Full stop Maximum Power TQ up to115 On emergency only GO around position Beginning of the ramp RTO TQ up to100 NOTCH p...

Page 105: ...nge ground operation in low power The NP is maintained at 70 8 to have the ACW available The ACW generator is on line when NP 66 FTR Feather position The fuel governing mode is cancelled No ACW generator Fuel Shut Off position Close the shut off valve on the HMU With the input coming from the PWR MGT and the position of the CL the PEC Propeller Engine Control control the NP propeller speed by chan...

Page 106: ...00 RTO UP TRIM NORMAL OPERATION EEC ON ISA CONDITIONS A B C D MCT OR TO TO 90 TQ 100 Np MCT 90 9 TQ 100 Np 100 TQ 100 Np 102 TQ 115 TQ LINE A One engine out operation LINE B Normal TO or MCT LINE C CLB LINE D CRZ NOTE Sensible sector designed to allow for fix throttle engine control WALL POWER LEVER ANGLE RAMP NOTCH TO PWR 2475 SHP NP 100 TQ 90 MCT PWR 2500 SHP NP 100 TQ 90 9 CLB PWR 2192 SHP NP 8...

Page 107: ...ORQUE ind white TQ bug manually selected NP ind NP actual display TEST 115 blue dot ITT ind ITT actual display ALERT When ITT 800 C or 715 C in hotel mode Lt CAP TEST 1150 C blue dot TEST 115 blue dot NH NL ind DC ESS NH actual display from 0 to 120 FUEL FLOW Ind Main DC BUS FU reset knob FU reset to 0 when pulled FUEL USED readout Main DC BUS OIL TEMP Main DC BUS from 0 to 130 C OIL PRESS ind Mai...

Page 108: ...lock engaged CL on FTH or FUEL S O blue hyd press available on the prop brake input 2100psi Fire handle not pulled PROP BRK Brake fully locked same indication on the memo panel 42 72 PEC 5 ENG control panel ATA 61 72 ARMING CONDITIONS PWR MGT sel on TO ATPCS pb in both PL 49 both TQ 46 arm green LT illuminated TRIGGER one TQ below 18 Cancel PWR MGT out of TO or ATPCS pb OFF or at least one PL reta...

Page 109: ...8 Idle gate ATA 61 72 ATPCS selector allows to check the correct functionning of the ATPCS This rotary selector is spring loaded to neutral position 7 ATPCS test panel ATA 61 72 SGL CH illuminates when one channel is lost 2 for self test when advancing CL from FTR to AUTO PWR MGT 2 co axial sw LH bottom RH TOP providing FDAU PEC and EEC with basic power requirements FAULT illuminates when both PEC...

Page 110: ...Annexes p 109 Annexes ...

Page 111: ...only Two fluorescent lights under glareshield ENGINE FIRE HANDLE Pulled on the respective engine Prop Feather Fuel LP valve closed Air Bleed valve closed Deice Deice shutoff valve closed Elect DC ACW gen disconnected Squibs Armed Lts illuminated Hydraulic Hyd prop brake eng 2 only Fire test MW CRC ENG 1 FIRE on CAP Fire handle illuminated FUEL S O Lt on CL if out of Fuel S O position Fault test MC...

Page 112: ...S to DC BUS 1 OFF ESS BUS DC STBY BUS INV 1 are isolated from HOT MAIN BAT BUS DC EMER BUS is isolated from HOT EMER BAT BUS Allows BPCU to control BTC operation Bus Tie Contactor Ext power Hotel mode or single gen operation BTC is closed green flow bar ISOL BTC opened released out BTR Bus Tie Relay locked open Tie between AC Busses AVAIL GPU has been checked by BPCU for over under voltage over cu...

Page 113: ... unless ENG 1 2 deice on STAT Static source not heated or failed CAP on ground only DC BUS no alarm in flight FAULT Power loss or failure CAP ON emergency exit lights illuminated Supply 6V Bat packs ARM lights on if DC STBY BUS 18V lights off if DC STBY 20V or in case of dual DC GEN loss DISARM system desactivated Associated bus not supplied AVAIL GPU has been checked by BPCU AVAIL ON GPU supplied...

Page 114: ...TRIM is triggered or prop brk on left one only Inhibited during eng start FAULT Bleed valve disagreement with selected position case of Ovht Overpressure or Leak CAP Associated valves auto closed OVHT either bleed duct temp thermal switch above 274 C CAP Associated valves auto closed May be reset after cooling Do not use above 160 knots DC BUS 2 FAULT fan inop CAP ALTN activates altn fan LO PR sup...

Page 115: ... from selected ADC indicates TAS from 68 to 600 kts if ADC not valid it displays TAT Ind from selected ADC Indicates TAT If ADC not valid it displays SAT pb shows SAT when depressed and held TEST pb when pushed in displays all 8 s LO LVL LTs CAP elect Pumps energized Refuel panel disabled during test and refuel valves auto close LO LVL Lt When the quantity is 160kg or When the quantity is 160kg bu...

Page 116: ...L retarded 49 or both TQ 53 EEC acts on stepper motor to regulate Fuel Flow FAULT flashing EEC Failure The fuel flow is frozen to maintain the power Do not deselect EEC when flashing The PL has to be retarded to the green sector before deselection of the EEC FAULT steady EEC Failure HMU base law reversion Fault become steady when the PL is retarded in the green band OFF HMU base law reversion OIL ...

Page 117: ...ON 190 kts 42 180 kts 72 maximum Xwind 15 kts EXT BLUE flap hyd valve commanding flap extension is opened If EXT appears when flaps are extended hyd circuit leak FLAP ASYM 6 7 CAP Flaps frozen in actual position PITCH TRIM ASYM pitch tab desynchronization CAP AUTO PRESS DC BUS 1 550 up to FL 200 620 above FL 200 Memorizes departure field elev up to 3500 ft ELV SET Select switch to set landing elev...

Page 118: ... triggering condition disappears landing gear VMO VFE VLE Stall warning Pitch trim whooler AP disconnect GA push button when depressed the GA FD mode is selected with HDG HOLD lateral mode with the wings level GA vertical mode HYD AUX PUMP CONTROL HOT MAIN BAT BUS Aux pump stopped 30 after p b released MFC supplied Aux pump stopped after p b released MFC not supplied IDLE GATE IDLE GATE FAIL activ...

Page 119: ...tude mode Aircraft stabilized gyro fast erection when pushing on the P B for 15s AUDIO 1 2 SEL FAULT When the associated RCAU part is failed ALTN Affected crew station is connected directly to VHF1 if CAPT station is affected VHF2 if F O station is affected DSP SEL P B RDR Weather Radar display on EFIS TERR Terrain display on EFIS Even if RDR is selected in case of terrain warning an automatic pop...

Page 120: ...nduces a speed decrease or a loss of rate of climb INCREASE SPEED After degraded perf Drag abnormally high and IAS lower than RED BUG 10 kt APM Weight rotary selector Before take off Both engines running it should be set to minimum weight then to take off nearest weight Only taken into account if the selector has been changed No effect for any change in flight If no selection an internal calculati...

Page 121: ... yaw damper and disengages yaw damper and autopilot if engaged CPL pb permit to couple AP FD On CAPT or F O side In CAT 2 ILS selected on NAV 1 2 1200 ft RA Dual coupling 800 ft RA CAT 2 invalid if still in single coupling 500 ft RA ILS excess dev activated 100 ft RA GS excess dev deactivated ALT knob controls the preselected altitude on ADU HDG knob selects HDG bug on both EHSI NAV 1 CRS 2 knob s...

Page 122: ...lk When depressed BOOM SET or OXY mike is connected for transmission over the selected communication facility Blinker indicator Test Reset slider PRELIMINARY COCKPIT PREPARATION OXYGEN MASK TEST INT RAD SELECTOR On AUDIO CONTROL PA SET TO INT PRESS TO TEST AND RESET PB DEPRESS AND HOLD NOTE Hose and mask charged with oxygen Observe blinker momentarily turns yellow and must turn dark if there is no...

Page 123: ...k ventilation preventing smoke to enter the flight compartment BITE LOADED magnetic indicator Indicates that a failure has been recorded by the maintenance system Report to maintenance MAIN PNL Before the flight check that all the switch and selector are in the normal position If not the MAINT PNL is illuminated on the CAP BRK TEMP TEST When depressed MC SC WHEEL on CAP and HOT amber light illumin...

Page 124: ...BAT Battery BC Back Course BITE Built in Test Equipment BPCU Bus Power Control Unit BPU Battery Protection Unit BRG Bearing BRK Brake B RNAV Basic Area Navigation BRT Bright BTC Bus Tie Contactor BTR Bus Tie Relay C CAB Cabin CAP Crew Alerting Panel CAPT Captain CAT Category C B Circuit Breaker CCAS Centralized Crew Alerting System CDI Course Deviation Indicator CHAN Channel CHC Charge Contactor C...

Page 125: ...gh Frequency HI High HLD Hold HMU Hydromechanical Unit HP High Pressure HSI Horizontal Situation Indicator HTG Heating HYD Hydraulic I IAS Indicated Air Speed IDT Ident IGN Ignition ILS Instrument Landing System IND Indicator IN HG Inches of Mercury INHI Inhibit INOP Inoperative INST Instrument INT Interphone INV Inverter ISOL Isolation ITT Inter Turbine Temperature JK KHZ Kilo Hertz KT Knot L LAT...

Page 126: ...ALT Radio Altitude RAD INT Radio Interphone RCAU Remote Control Audio Unit RCDR Recorder RCL Recall RCU Releasable Centering Unit RECIRC Recirculation REV Reverse RGA Reserve Go Around RGB Reduction Gear Box RH Right Hand RLY Relay RMI Radio Magnetic Indicator RNP Required Navigation Performance RPM Revolution Per Minute RTO Reserve Take Off RUD Rudder S SAT Static Air Temperature SBY Stand By SC ...

Page 127: ...NAV Vertical Navigation VOR VHF OMNI Directional Range VSI Vertical Speed Indicator W WARN Warning WOW Weight On Wheel XFEED Cross feed XFR Transfer XY YD Yaw Damper Z ZA Aircraft Altitude ZCTH Theoretical Cabin Altitude ZFW Zero Fuel Weight ZP Pressure Altitude ZRA Radio Altimeter Altitude ...

Page 128: ...p 127 ...

Page 129: ...t quality However please do not hesitate to share your comments and information with us by using the following address flight ops support atr fr Yours faithfully Your ATR Training and Flight Operations support team Printed on 100 recycled paper using vegetable inks ...

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