FCTM Sistemas ATR-600.pdf

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(1)PRODUCT SUPPORT & SERVICES. SYSTEMS SCAN YOUR AIRCRAFT. 42 PEC 72 PEC Glass cockpit - 600.

(2) Introduction. Introduction This Systems guide is an essential tool for all ATR flight crews and engineers to learn or review ATR systems operation. To make learning process easier, systems are introduced in a user-friendly and efficient training method, including diagrams and schematics and displays as appropriate. This guide is a comprehensive document that efficiently complements FCOM 1st part – Systems description. Systems are organized as per FCOM chapters, 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 New Avionics Suite (42-600 and 72-600). It presents a generic aircraft not customized to your own aircraft systems. Should you find any discrepancy between Systems guide and your customized ATR operational documentation (AFM, FCOM & QRH), the latter takes precedence. NB: This Systems guide is also available for ATR 42-300, 72-200 not PEC, 42-500 and 72-212A.. The Training and Flight Operations support team..

(3) S y s t e m s 4 2/72 - 6 0 0 Chapter A. Aircraft general 1. Doors location .....................................................................................................................................................................................................................................................8 2. Cargo door panel ...........................................................................................................................................................................................................................................9 3. Doors panel ...........................................................................................................................................................................................................................................................9 4. External lights ................................................................................................................................................................................................................................................10 5. EXT LT panel .....................................................................................................................................................................................................................................................11 6. Memo panel display .................................................................................................................................................................................................................................11 7. Signs panel .........................................................................................................................................................................................................................................................11 8. Internal lighting ............................................................................................................................................................................................................................................12 9. LT panel ...................................................................................................................................................................................................................................................................13 10. ANN LT panel ...............................................................................................................................................................................................................................................13 11. Side panel .........................................................................................................................................................................................................................................................13 12. FLT COMPT LT panel .........................................................................................................................................................................................................................13. Chapter B. Integrated systems 1. Integrated Modular Avionics (IMA)......................................................................................................................................................................................16 2. Multi Function Computer (MFC)..............................................................................................................................................................................................17 3. Multi Purpose Computer (MPC) ..............................................................................................................................................................................................18 4. Schematic..............................................................................................................................................................................................................................................................19. Chapter C. Flight warning system 1. Cockpit colors philosophy ............................................................................................................................................................................................................22 2. FWS description ..........................................................................................................................................................................................................................................24 3. Alert window ....................................................................................................................................................................................................................................................25 4. EMER audio cancel & TO config test .............................................................................................................................................................................28 5. Aural alarms ......................................................................................................................................................................................................................................................29. Chapter D. Air 1. Pneumatic system......................................................................................................................................................................................................................................32 1.1. Schematic .................................................................................................................................................................................................................................................32 1.2. AIR BLEED panel.............................................................................................................................................................................................................................33 2. Air conditionning ........................................................................................................................................................................................................................................39 2.1. Schematic .................................................................................................................................................................................................................................................39 2.2. COMPT TEMP panel ...................................................................................................................................................................................................................40 3. Avionics ventilation .................................................................................................................................................................................................................................44 3.1. Schematic .................................................................................................................................................................................................................................................44 3.2. AVIONICS VENT panel .............................................................................................................................................................................................................44 4. Pressurization ................................................................................................................................................................................................................................................45 4.1. Schematic .................................................................................................................................................................................................................................................45 4.2. Cabin pressure indicators ..................................................................................................................................................................................................46 4.3. AUTO PRESS panel .....................................................................................................................................................................................................................46 4.4. MAN RATE KNOB and CABIN PRESS panel..............................................................................................................................................46. Chapter E. Automatic flight control system 1. Schematic ............................................................................................................................................................................................................................................................50 2. FMA ..............................................................................................................................................................................................................................................................................51 3. FGCP (Flight Guidance and Control Panel) ............................................................................................................................................................56 4. ICP (Index Control Panel) .................................................................................................................................................................................................................56. Chapter F. Communications 1. Schematic............................................................................................................................................................................................................................................................. 58 2. PTT selector and NOSE WHEEL STEERING CONTROL SW.............................................................................................................58 3. Audio control panel ..................................................................................................................................................................................................................................59 4. VHF control ..........................................................................................................................................................................................................................................................59 5. AUDIO SEL pb..................................................................................................................................................................................................................................................60 6. Loudspeaker volume knobs .........................................................................................................................................................................................................60. 2.

(4) Contents 7. TCAS control box ........................................................................................................................................................................................................................................60 8. EMER LOC XMTR panel .....................................................................................................................................................................................................................61 9. Cabin attendant handset...................................................................................................................................................................................................................61 10. Handmike and handset....................................................................................................................................................................................................................61 11. CALLS panel ...................................................................................................................................................................................................................................................61 12. Head set / boom set / hand mike panels ...................................................................................................................................................................61 13. ATC control.......................................................................................................................................................................................................................................................62 14. CVR panel...........................................................................................................................................................................................................................................................62 15. Crew oxygen mask ................................................................................................................................................................................................................................62. Chapter G. Electrical systems 1. Sources of power ........................................................................................................................................................................................................................................64 2. DC-AC schematic .......................................................................................................................................................................................................................................66 2.1. Normal supply: On ground with battery only ............................................................................................................................................66 2.2. Normal Supply: On ground with external power .........................................................................................................................................67 2.3. Hotel mode or DC GEN 1 FAULT ................................................................................................................................................................................68 2.4. Normal supply: with two generators on line..............................................................................................................................................69 2.5. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD .......................70 2.6. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD and second OVRD selected ..........................................................................................................................................................................................................71 2.7. Emergency supply: In dual DC GEN LOSS with TRU ....................................................................................................................72 3. DC-AC panel ......................................................................................................................................................................................................................................................73 4. Elec SD ......................................................................................................................................................................................................................................................................74 5. ACW schematic .............................................................................................................................................................................................................................................78 6. ACW panel ............................................................................................................................................................................................................................................................80 7. SD page ....................................................................................................................................................................................................................................................................81 8. Breaker panels ................................................................................................................................................................................................................................................82 8.1. Overhead panel .................................................................................................................................................................................................................................82 8.2. Electric rack behind F/O .......................................................................................................................................................................................................83. Chapter H. Emergency equipment 1. Emergency equipment situation.............................................................................................................................................................................................86 2. Emergency lighting system ...........................................................................................................................................................................................................86 3. First aid kit ............................................................................................................................................................................................................................................................87 4. Crash axe ...............................................................................................................................................................................................................................................................87 5. Megaphone ..........................................................................................................................................................................................................................................................87 6. Flashing light .....................................................................................................................................................................................................................................................87 7. Life jacket ..............................................................................................................................................................................................................................................................87 8. Escape rope ........................................................................................................................................................................................................................................................87 9. Gloves .........................................................................................................................................................................................................................................................................88 10. Water extinguisher .................................................................................................................................................................................................................................88 11. Halon extinguisher .................................................................................................................................................................................................................................88 12. Oxygen schematic..................................................................................................................................................................................................................................88 13. Oxygen panel and display ............................................................................................................................................................................................................89 14. Cockpit crew oxygen mask .......................................................................................................................................................................................................89 15. Portable oxygen bottle......................................................................................................................................................................................................................90 16. Passenger oxygen mask ................................................................................................................................................................................................................90 17. Protective breathing equipment ..........................................................................................................................................................................................90. Chapter I. Fire protection 1. Schematic..............................................................................................................................................................................................................................................................92 2. Avionics FWD and AFT smoke detection ...................................................................................................................................................................92 3. Fire handle ............................................................................................................................................................................................................................................................93 4. EWD (Engine and Warning Display)....................................................................................................................................................................................93 5. Condition levers fuel light ................................................................................................................................................................................................................93 6. Compartment smoke panel...........................................................................................................................................................................................................94 7. SD cabin...................................................................................................................................................................................................................................................................94 3.

(5) S y s t e m s 4 2/72 - 6 0 0 Chapter J. Flight control 1. Roll schematic.................................................................................................................................................................................................................................................96 2. Pitch schematic .............................................................................................................................................................................................................................................96 3. Yaw schematic ................................................................................................................................................................................................................................................97 4. Gust lock .................................................................................................................................................................................................................................................................97 5. Stick Shaker/Stick Pusher push button and display ..................................................................................................................................97 6. Spoilers position indicator..............................................................................................................................................................................................................98 7. Pitch trim asym light ...............................................................................................................................................................................................................................98 8. Trim position indicator .........................................................................................................................................................................................................................98 9. Trim controls ......................................................................................................................................................................................................................................................99 10. Flaps schematic .................................................................................................................................................................................................................................... 100 11. Flaps position indicator............................................................................................................................................................................................................... 100 12. Flaps control lever .............................................................................................................................................................................................................................. 101. Chapter K. Flight instruments 1. Schematic.......................................................................................................................................................................................................................................................... 104 2. PFD (Primary Fight Display) ...................................................................................................................................................................................................... 105 3. MFD (Multi Function Display) .................................................................................................................................................................................................. 106 4. EWD (Engine and Warning Display)................................................................................................................................................................................ 107 5. ND - ARC MODE with terrain or weather radar information ...................................................................................................... 108 6. Source failure alert ................................................................................................................................................................................................................................ 108 7. Switching panel ......................................................................................................................................................................................................................................... 109 8. EFCP (control panel) ........................................................................................................................................................................................................................... 109 9. MCP (Multipurpose Control Panel) ................................................................................................................................................................................. 110 10. Weather radar control ................................................................................................................................................................................................................... 111 Primus 660 ........................................................................................................................................................................................................................................................ 111 11. TAT/SAT indicator ............................................................................................................................................................................................................................... 112 12. CLOCK................................................................................................................................................................................................................................................................ 112 13. RCDR panel ................................................................................................................................................................................................................................................. 113 14. STBY instruments ............................................................................................................................................................................................................................... 113 15. Airspeed indicator .............................................................................................................................................................................................................................. 114 16. Altimeter........................................................................................................................................................................................................................................................... 115 17. Vertical speed indicator and TCAS .............................................................................................................................................................................. 116. Chapter L. Fuel system 1. Schematic.......................................................................................................................................................................................................................................................... 118 2. Electrical fuel pump OFF............................................................................................................................................................................................................... 119 3. Starting procedure................................................................................................................................................................................................................................. 120 4. Normal procedure................................................................................................................................................................................................................................... 121 5. Cross feed procedure........................................................................................................................................................................................................................ 122 6. Engine feed jet pump low pressure................................................................................................................................................................................ 124 7. Low level ............................................................................................................................................................................................................................................................. 125 8. Engine fire procedure ........................................................................................................................................................................................................................ 126 9. Fuel panel........................................................................................................................................................................................................................................................... 127 10. SD Engine ....................................................................................................................................................................................................................................................... 127 11. Fuel QTY indication ........................................................................................................................................................................................................................... 128 12. XFEED advisory on memo panel display ............................................................................................................................................................. 128. Chapter M. Hydraulic system 1. Schematic.......................................................................................................................................................................................................................................................... 130 3. SD ACW and hydraulic ..................................................................................................................................................................................................................... 131 2. HYD PWR panel ......................................................................................................................................................................................................................................... 131 4. Pressure indication ............................................................................................................................................................................................................................... 132 5. AUX pump pedestal switch ....................................................................................................................................................................................................... 132 6. Hydraulic on Ramp (only on battery) ............................................................................................................................................................................ 133 7. Hydraulic on Ramp (aux pump P/B selected on the pedestal) ................................................................................................. 133 8. Hydraulic system normal operation............................................................................................................................................................................... 134. 4.

(6) Contents 9. Hydraulic system failures ............................................................................................................................................................................................................. 135 10. Hydraulic system crossfeed operation .................................................................................................................................................................. 135 11. Both main hydraulic pumps loss .................................................................................................................................................................................... 136 12. Both hydraulic systems loss ................................................................................................................................................................................................ 137. N. Ice and rain protection 1. Schematic.......................................................................................................................................................................................................................................................... 140 2. Probes and windshield HTG ..................................................................................................................................................................................................... 141 3. Rain protection ........................................................................................................................................................................................................................................... 141 4. Ice detector panel and icing AOA ..................................................................................................................................................................................... 141 5. Aircraft Performance Monitoring (APM) .................................................................................................................................................................. 142 6. De-icing schematic............................................................................................................................................................................................................................... 143 7. Airframe air bleed FAULT .............................................................................................................................................................................................................. 144 8. Anti-icing & de-icing panel ......................................................................................................................................................................................................... 145 9. De-icing/anti-icing indication (memo panel display) .............................................................................................................................. 145. O. Landing gear 1. Landing gear description ............................................................................................................................................................................................................. 148 2. Brakes schematic ................................................................................................................................................................................................................................... 148 3. LDG GEAR position indicators .............................................................................................................................................................................................. 149 4. Landing gear handles ........................................................................................................................................................................................................................ 149 5. Brakes temperatureand antiskid ....................................................................................................................................................................................... 149 6. Emergency parking brake handle..................................................................................................................................................................................... 150 7. Steering handwheel ............................................................................................................................................................................................................................. 150. P. Navigation system 1. Nav control ....................................................................................................................................................................................................................................................... 152 2. Marker sensibility setting ............................................................................................................................................................................................................. 152 3. ADF control ...................................................................................................................................................................................................................................................... 152 4. TAWS alert modes .................................................................................................................................................................................................................................. 153 5. TAWS pb............................................................................................................................................................................................................................................................... 157 6. TAWS panel...................................................................................................................................................................................................................................................... 157 7. ND OVERLAY ................................................................................................................................................................................................................................................. 158 8. FMS ............................................................................................................................................................................................................................................................................ 159. Q. Power plant 1. Engine schematic/72 .......................................................................................................................................................................................................................... 162 2. Power and propeller controls/72 ....................................................................................................................................................................................... 163 3. Engine indication ..................................................................................................................................................................................................................................... 166 4. ENG START panel/72 .......................................................................................................................................................................................................................... 168 5. ENG control panel/72......................................................................................................................................................................................................................... 168 6. PWR MGT panel/72............................................................................................................................................................................................................................... 169 7. ATPCS test panel/72 ........................................................................................................................................................................................................................... 169 8. Idle gate/72 ...................................................................................................................................................................................................................................................... 169. Annexes Annex 1. Cockpit panels ....................................................................................................................................................................................................................... 173 Annex 2. Abbreviations ........................................................................................................................................................................................................................... 187. 5.

(7) A. Aircraft general FCOM 1.00. 7.

(8) S y s t e m s 4 2/72 - 6 0 0. 1. Doors location. Cargo door. Pilot communication hatch. 8. Emergency exit type III. Rear entry door / emergency exit type I. ATA 52. Service door / emergency exit type I. Pilot emergency hatch. Aft avionics compartment door. Forward avionics access hatch.

(9) A. Aircraft general. 2. Cargo door panel. ATA 52. ARMED light – Selector armed green light is ON, when actuator selection switch working conditions are met: – cover panel opened – door unlocked by operating handle: all hooks are disengaged and FWD latchlock is unfastened. LCHD light blue light is ON when all door hooks and latch locks are fully engaged. GND HDL light Ground handling bus ON BAT red light is ON when ground handling bus is directly supplied by HOT main bat bus: means that the battery is discharging even if the BAT toggle switch is in OFF position (visible even when the cover panel is closed) This red light is ON when: – The refueling panel is open – The cargo door control panel is open – The passenger door is open and alert, that the battery is discharging before leaving the aircraft. Actuator selection switch is used to operate the door (OPEN or CLOSE) when the CARGO DOOR ARMED green light is on. 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.. CARGO LIGHT switch allows activation of the cargo bay light from outside. 3. Doors panel. ATA 52. CAB OK and SVCE OK Light on when SW TEST depressed and check microswitches operation. UNLK At least 1 micro switch is opened SW TEST Tests continuity of microswitch system (on ground, doors opened). 9.

(10) S y s t e m s 4 2/72 - 6 0 0. 4. External lights. ATA 33. ABCDE F GH-. Navigation lights Taxi and T/O lights Landing lights Wing lights Beacon lights Strobe lights Logo lights Emergency light. Cabin panel. Memo panel display. 10.

(11) A. Aircraft general. 5. EXT LT panel. ATA 33. BEACON and NAV supplied by SVCE BUS and BUS 1 LOGO supplied by SVCE BUS. STROBE, LAND supplied by ACW BUS 1 (Left Hand), ACW BUS 2 (Right Hand) TAXI & T.O Supplied by ACW BUS 2 WING Supplied by DC BUS 2. 6. Memo panel display. ATA 33. SEAT BELT displayed in cyan when associated switch is selected ON. NO DEVICE displayed in cyan when associated switch is selected ON. SEAT BELT displayed in amber crossed when the signal is invalid.. NO DEVICE displayed in amber crossed when the signal is invalid.. 7. Signs panel. ATA 33 ON emergency exit lights illuminates. Supply: DC STBY or 6 V BAT packs. NO DEVICE and SEAT BELTS Cyan message on memo panel display when ON. (DC BUS 2). ARM Emergency lights illuminate when <18 V on STBY bus or if both DC GEN off line. Emergency lights extinguish when >20V on STBY bus and at least 1 GEN operating. DISARM system deactivated. 11.

(12) S y s t e m s 4 2/72 - 6 0 0. 8. Internal lighting. ATA 33. 0,33('. 29+'. The STORM switch overrides the MIP/PED rotary selector to put in the maximum intensity setting. 12.

(13) A. Aircraft general. 9. LT panel. ATA 33. MIP / PED Selects activation and intensity of integral lighting of the main instrument panels (MIP) and pedestal (PED). 0,33('. 29+'. OVHD rotary selector selects activation and intensity of overhead panels integral lighting. 10. ANN LT panel. FLOOD knob selects activation and intensity panel flood lighting. (OFF TO BRT). ATA 33 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 light illuminate bright DIM: associated light are dimmed. 11. Side panel. ATA 33 CAPT READING LT knob selects activation and intensity of the respective spot light. CAPT CONSOLE LT knob selects activation and intensity of the respective lateral console. 12. FLT COMPT LT panel DOME switch BRT: dome lights are supplied with maximum intensity DIM: dome lights are dimmed OFF: both dome are off DOME light: the F/O dome light becomes BRT when the switch in BRT or DIM if: – dual DC GEN loss – or on ground, with BAT supply only. ATA 33. STORM switch On position, it overrides the MIP/ PED rotary selector to put in the maximum intensity setting. STBY COMPASS switch to illuminate the STBY COMPASS ON and OFF position. 13.

(14) B. Integrated systems FCOM 1.01. 15.

(15) S y s t e m s 4 2/72 - 6 0 0. 1. Integrated Modular Avionics (IMA). ATA 42. The Integrated Modular Avionic (IMA) provides computation, memory and Input/Output data processing resources, shared between several avionics applications. The Integrated Modular Avionic is mainly composed of the dual Core Avionic Cabinets (CAC 1&2). The term CAC (Core Avionic Cabinet) designs the whole equipment composed of the rack and the set of cards. In the basic configuration, each CAC is composed of: – 1 CPM (Core Processing Module) The CPMs provide shared memory and computation resources to execute hosted avionics applications. – 1 IOM-S (Input/Output Module) This IO Module is dedicated to provide ARINC and discrete I/O for all functions – 1 IOM-AP (Input/Output Module) This IO Module is dedicated to provide discrete and analog I/O for the Auto-Flight application. – 2 IOM-DC (Input/Output Module) The IOM-DC provide discrete and analog I/O for Data Concentration Application (DCA) . – 1 SWM (gateway and SWitch Module) This module is dedicated to connect together CPM and other Avionics Data Network subscribers. The communication means is based on AFDX network, linking network subscribers through SWM. The main applications hosted by the Core Avionic Cabinets are : – Flight Warning (FWA) – Auto-Flight (AFCA) – Centralized Maintenance (CMA) (only on CAC 1) – Data Concentration (DCA) The CAC 1 & 2, communicate with five display units and systems through different data bus formats: – AFDX: Avionics Full DupleX switched ethernet – A429: ARINC 429 – Analogic – Discretes Two of the five displays units (DU2 and DU4) are dedicated to two other functions: – Flight Management Application (FMA) – Radio Management Application (RMA). '8. '8 )0$ 50$. '8. '8 )0$ 50$. '8. $)'; $ &30 ,20 ,20 ,20 ,20 6:0 6 $3 '& '& . &30 ,20 ,20 ,20 ,20 6:0 6 $3 '& '& . $)&$ ):$ '&$ &0$. $)&$ ):$ '&$. &$&. ',6&5(7(. 6<67(06. 16. $1$/2*. $. &$&.

(16) B. Integrated systems. 2. Multi Function Computer (MFC). ATA 31. Numerous logic 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 ,QWHUFDUGGLDORJXH $5,1&

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(22) (OHFWULFDO SRZHU. '&(66%86 RU*1'+'/*%86 +27(0(5%$7%86. $LUFUDIWV\VWHP LQSXWV. (OHFWULFDO SRZHU. '&(0(5%86. 0$,1%86. 9'&$OWHUQDWH VXSSO\ 9'&1RUPDO VXSSO\. FAULT illuminates and the FWS is activated when a malfunction or electrical supply fault is detected. The module automatically becomes inoperative. This light also flashes during self-test of the module. During powering, since all 4 modules are selected ON, the following sequence is executed: MFC 1A and MFC 2A FAULT lights flashing (selftest of these modules) MFC 1A and MFC 2A FAULT lights extinguish. MFC 1B and MFC 2B FAULT lights flashing (selftest of these modules) MFC 1B and MFC 2B FAULT lights extinguish. OFF The module stops operating. The MFC functions can be processed: – in one module only – in several modules (redundancy) – partially in 2 modules. NOTE: If the cargo door control panel is opened, the self test of MFC 1A and 2A are already done, and only the MFC 1B and 2B are tested. (See chapter A.2). Example: MODULE SYSTEM. FUNCTION 1A. FLIGHT. STICK PUSHER. CONTROLS. STALL WARNING. 1B. 2A. 2B. – The stick pusher function is integrated in modules 1A, 1B, 2A and 2B. – The stall warning function is integrated in modules 1B and 2B. – The stick pusher function is available if modules (1A AND 2A) OR (1A AND 2B) OR (1B AND 2A) OR (1B AND 2B) operate. This function is therefore not available if modules (1A AND 1B) OR (2A AND 2B) are lost. – The stall warning is available if modules 1B OR 2B operate. This function is therefore not available if modules 1B AND 2B are lost.. 17.

(23) S y s t e m s 4 2/72 - 6 0 0. 3. Multi Purpose Computer (MPC). ATA 31. The MPC unit is including two parts: – Flight Data Acquisition unit (FDAU) – Data Management unit (DMU) A) FDAU Part The MPC acquires data in digital, analog or discrete format from aircraft systems for various FDAU functions: – Flight Data Recording (SSFDR) (refer to chapter Flight Instruments). – Aircraft Performance Monitoring (APM) (Refer to chapter Ice and Rain Protection). – Data broadcast to CAC (to avionics system). – Time management. – Flight time management. – Flight number management. – Configuration management (A/C type, A/C ident, APM version). B) DMU Part The MPC has the capability to manage ACMS functions (Aircraft Condition Monitoring System) in order to: – facilitate the maintenance of the aircraft. – record data for the Flight Data Monitoring purpose (FDM) The main possible ACMS functions are: – QAR/DAR recording on a PCMCIA disk (QAR when the data frame is the FDR one’s/DAR when it is reprogrammed by a ground support equipment) A FDM purpose – Management of reports (take-off, cruise... ) A FDM purpose – Dialogue with the following aircraft equipments: MCDU, Printer, ACARS (optional) – Other maintenance functions.. 35,17(5 $&$56 2SWLRQDO

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(25) B. Integrated systems. 4. Schematic. 19.

(26) C. Flight warning system FCOM 1.02. 21.

(27) S y s t e m s 4 2/72 - 6 0 0. 1. Cockpit colors philosophy. ATA 31. In normal operation, all lights are extinguished (Dark cockpit philosophy). With some exceptions, the lights illuminate to indicate a failure or an abnormal condition.. HIGH LEVEL COLOR CODE RULES FOR ATR 600 COLOR USED for DISPLAY PICTURES – PRINTING – PUSH BUTTONS – CONTROL PANELS. WHITE. WHITE means an inert information – Unit data and external world reference: graduations on IAS strip, Baro-Alt strip, VS strip & Heading rose. Engine & system parameter indicators graduations – Consulted data (MCDU) – Normal (non icing) speed references (VMLBO, Flaps retraction speed) – System selected OFF (displayed on Display Unit), Push Button OFF light on control panels, inert shape on Display Unit – Title, comments & action menu list – Advisory messages on MCDU (no crew action required) – Segregation area with horizontal or vertical lines. LIGHT GREY. LIGHT GREY is used for typing, for system picture inoperative functions & for virtual control buttons (VCP) – Light grey typing on Display Unit means associated virtual control is inhibited – Pipe shapes (fuel or air or hydraulics) are displayed light grey when no flow or pressure is detected – Virtual control button light grey means button is not auto maintained pushed Specific for ANF (Airport Navigation Virtual Control Panel): opened menu on a light grey background summarizes MCP (Manual Control Panel) current active PB functions. DARK GREY. DARK GREY is used for virtual control button (on Virtual Control Panel) – Dark grey virtual push button means associated virtual control is auto maintained pushed for a given time (i.e. IDENT for ATC transponder). YELLOW. YELLOW is used for A/C references, for temporary information, for reversion configuration – On PFD & ND: IAS strip, Baro-Alt strip, VS strip & Heading rose A/C references are yellow in relationship with A/C mock up displayed yellow (same philosophy as Airbus) – Temporary data on Display Units & MCDU: manual insertion in progress (active flight plan update in progress, COM or NAV or SURV radio tuning in progress, Take Off performances data not yet confirmed) – Temporary FMA message (7 seconds) following an “unable” AP-FD manual selection (associated to triple “clic”) – Temporary System TEST phase launched by crew – Manual ADC, AHRS or NAV Source reversion: new active source is typed yellow to advise crew that a single source is used by both sides (amber is inappropriate as long as current source in not malfunctioning). 22.

(28) C. Flight warning system AMBER. AMBER is used for Icing condition data, for detected malfunction, for abnormal range data, for aircraft parameter or computation result out of normal range – In icing conditions flight, aircraft may have downgraded performances and handling qualities. Crew shall not disregard it. An amber CAUTION level is associated (for ATR) to this flight condition change. Speed references are adjusted, icing speed references (VMLBO, Flaps retraction speed) are displayed amber to point out icing conditions effects (icing color reference is amber) – CAUTION alerts & messages (requiring crew action) are typed amber to point out icing or malfunction detected – Active or selected Abnormal Procedure title are typed amber (and displayed according to a defined priority level) – Active Status title associated to a previous system malfunction is typed amber – If a data resulting of a system calculation is out of range, this data is typed amber to point out the crew needs to adjust some flight parameters in order to recover normal target range (for instance, if unable to match an altitude constraint, constraint data will be typed amber, crew must react to fulfill the constraint) – If data (flight or system) are out of normal range, data parameter are displayed amber (Push Button Fault, dedicated amber light on a panel, system picture displayed amber, parameter value typed amber) – Invalid signals are displayed by amber crosses or dashes. RED. RED is associated to a warning & requests an immediate crew action – WARNING alerts & messages are typed red – Active or selected Emergency Procedure title are typed red (and displayed according to a defined priority level) – If a system is detected out of limits, data parameter are displayed red (dedicated red light, system picture displayed red, parameter value typed red). MAGENTA. MAGENTA is associated to current constraint. – FMS Managed Speed and FMS current leg guidance are considered as current constraints. – Current FMS active leg data & lateral deviations are considered as current constraints information and displayed magenta to point out FMS source. – Active Speed and Altitude constraints are displayed magenta – Some specific constraints (Take Off pitch trim, GO-AROUND Torque) are displayed magenta – ANF (Airport Navigation) selections are magenta (according to Airbus rules applied).. CYAN. CYAN is dedicated to manual operations – Manual insertion are typed cyan – Manual target selections are cyan bugs (IAS, HDG, Baro-Alt, VS) or cyan dots (selected flaps or man selected TO TQ) – Active VCP selection in a menu (except ANF) – Alternate system selection is indicated cyan (XFEED valve) on system page and on control panel light – Override system selection is indicated cyan on system page and on control panel light – Armed AP-FD modes. LIGHT BLUE. LIGHT BLUE is dedicated to VCP area of Display Unit to make evident that VHF manual management page is active and discriminate it from the other ones.. GREEN. GREEN is dedicated to automatic normal functioning & to computed data in normal range for each interface: CONTROL PANEL, DISPLAY UNIT format & MCDU.. 23.

(29) S y s t e m s 4 2/72 - 6 0 0. 2. FWS description. ATA 31. The FWS draws crew’s attention when a failure is detected and guides the crew to the system affected by the failure Three types of visual devices are used: – MASTER WARNING and MASTER CAUTION lights – FWS alert and procedure windows – LOCAL ALERT lights. Detection sequence INFORMATION. IDENTIFICATION. ISOLATION. Example: ACW Generator 1 failure. Local alert: fault light on the ACW gen 1 push-button. MASTER CAUTION light flashing + Single Chime. ELEC ACW GEN 1 on alert window and ACW GEN 1 on procedure window. Local alert: ACW GEN 1 FAULT on ACW/HYD Schematic Display (SD). 24.

(30) C. Flight warning system. 3. Alert window. ATA 31. ENGINE ENG 1 FIRE / ENG 2 FIRE. Engine fire detected. ENG 1 OUT / ENG 2 OUT. Engine 1 or 2 sensed out, in takeoff / go-around configuration. ENG 1+2 OUT. Both engine sensed out with aircraft in flight configuration. SINGLE ENGINE. Aircraft in flight configuration and one engine sensed out. ENG START. Start light ON past 45% NH or GCU failure during start. ELEC X START. Cross start failure. Opposite generator has not come on line to assist start at 10% NH (on ground only).. ENG EXCESS ITT. ITT more than 800°C (715°C in hotel mode). ENG START NO NH. NH <20%, 10s after starter push button ON. ENG NO ITT. ITT <400°C, 10s after opening the fuel. NAC OVHT. RH NAC OVHT >170°C. LOOP 1A / LOOP 1B / LOOP 2A / LOOP 2B. engine fire loop fault. PROP BRK. Prop brake not in full, locked or in full, released position. ENG EEC / ENG EEC 1+2. EEC or both EECs Failure. ENG BOOST. Disagreement between the EEC rating and the push button position. ENG 1 OUT / ENG 2 OUT. Engine 1 or 2 sensed out in flight configuration. IDLE GATE. Automatic idle gate system failure. ENG 1 LO PITCH / ENG 2 LO PITCH. propeller blande angle <8° in flight. ENG PROP NP1 / ENG PROP NP2. Unexpected 100% NP (triggered >86%). ENG 1 PROP LIM / ENG 2 PROP LIM. NP >106%. ENG 1 PEC SG CH / ENG 2 PEC SG CH. Lost of one PEC channel ----> operation on single channel. ENG 1 PEC / ENG 2 PEC. PEC Failure. ENG 1 OVER LIM / ENG 2 OVER LIM. TQ >120%, NH >106.4%, NL >106.8% and start rotary selector OFF. ENG1 OIL TEMP L / ENG2 OIL TEMP L. Oil temp low on ground <0°C / Oil temp low <45°C with engine running and PL>30°. ENG1 OIL TEMP H / ENG2 OIL TEMP H. Oil temp between 125°C and 140°C. ENG 1 OIL OVHT / ENG 2 OIL OVHT. Oil temp >140°C. ENG 1 OIL PRESS / ENG 2 OIL PRESS. Oil press <40 Psi (inhibited 30 sec during engine start). FUEL FUEL 1 TEMP HI / FUEL 2 TEMP HI. Fuel temperature >50°C. FUEL 1 TEMP LO / FUEL 2 TEMP LO. Fuel temperature <0°C. ENG FUEL CLOG. Fuel press loss in corresponding HP pump fuel filter ΔPSI >25 PSI. Filter blocked and by-passed when ΔPSI >45 PSI. FUEL FEED LO PR. Engine feed low press <4 psi. FUEL LO LVL. Fuel tank <160 kg or Fuel tank >160 kg and feeder tank not full. FUEL MISMATCH. Difference between fuel FMS and fuel quantity indicator: on ground >200 kg during 10s, in flight >200 kg during 60s. FUEL UNBALANCED. Difference between both tanks >200 kg. ELEC ELEC DC GEN 1+2. Dual DC GEN Loss. ELEC DC 1 / ELEC DC 2. DC BUS 1 or 2 not supplied. ELEC AC 1 / ELEC AC 2. AC BUS 1 or 2 not supplied. ELEC ACW 1 / ELEC ACW 2 / ELEC ACW 1+2 ACW BUS 1 or/and 2 not supplied ELEC DC ESS. DC essential bus not supplied. 25.

(31) S y s t e m s 4 2/72 - 6 0 0. ELEC DC EMER. DC emergency bus not supplied. ELEC DC GEN. One DC GEN Loss. ELEC INV 1 / ELEC INV 2. Inverter failure or supply loss. ELEC ACW GEN 1 / ELEC ACW GEN 2. One ACW GEN Loss. ELEC DC SHED. One of the DC SVCE / UTLY 1 and 2 busses is shed. ELEC BAT CHG. Thermal runaway / Bus voltage <25V / start sequence/Bat sw on OVRD.. ELEC CHG LOSS. Both batteries chargers fault. ELEC BAT DISCH. Main or Emergency battery discharge. ELEC STBY UNDV. DC STBY <19.5V. HYDRAULIC HYD BLUE LO LVL / HYD GREEN LO LVL. Associated compartment <2,5 liters. HYD PUMPS LOSS. Both main pump loss. Blue pressure can be recovered with the aux pump in approach (Landing gear lever in down position). HYD SYS LOSS. Both system loss.. HYD BLUE (GREEN) LO PR / HYD AUX LO PR. Pump delivery pressure <1500 psi. HYD BLUE (GREEN) OVHT / HYD AUX OVHT. Temperature >121°C (250°F). FLIGHT CONTROL FLAPS UNLK. Spurious Flaps retraction more than 3° (42-600), 4° (72-600). FLAPS ASYM. >6.7° between the left and right flaps. Flaps frozen in current position. FLAPS JAM. Triggerred when the difference between the average flaps position and the selected position is >1°. PITCH TRIM ASYM. pitch tabs desynchronization greater than 0.7°. FLT CTL RUD RCU. RCU supplied by DC current for more than 60s. PITCH DISC. Elevator uncoupling. PITCH RECONNCT. Appears during the procedure of pitch reconnection on ground. FLT CTL PUSHER. Stick pusher failure. FLT CTL TLU. System disagree / two ADC failures / ADC datas incoherence / TLU position synchro failure. T/O or T/O Config Test and TLU not LO SPD. AIL LOCK LIT. Triggered whenever one of the locking actuators is in disagreement with the gust lock lever position (lock or unlock position). LANDING GEAR LDG GEAR NOT DN. Any gear not seen down and locked and: 1. flaps 25° or flaps 30°, ZRA <500 ft and PL at low power. 2. at least one PL at FI and ZRA <500 ft. LDG GEAR. Landing lever down, but at least one landing gear is not sensed in lock down position. WHEELS A-SKID. Anti-skid failure. WHEELS BRK HOT. Brake temp >160° (42-600) and >150° (72-600). AIR FWD SMK. Forward cargo smoke. AFT SMK. Aft cargo or lavatory smoke. ELEC SMK. Avionics smoke. AUX AFT SMK. Smoke in auxiliary aft compartment (optional). AIR BLEED 1 / AIR BLEED 2. Bleed valve disagreement with P/B selected position. AIR BLEED1 OVHT / AIR BLEED2 OVHT. Bleed DUCT temp >274°c. AIR LEAK 1 / AIR LEAK 2. Leak detected with a loop when the temperature >153°C. AIR X VALVE. Air cross feed valve open in flight. AIR PACK / AIR PACK 1+2. Pack valve disagreement with PB selected position or Ovht downstream pack comp (>204°C).. AIR RECIR FAN 1 / AIR RECIR FAN 2. Fan low speed or motor overheat.. AIR DUCT OVHT. Duct overheat >92°C.. 26.

(32) C. Flight warning system EXCESS CAB ALT. Cabin altitude over threshold (10.000 ft or 11.000 ft if mod High Alt Rwy). AIR AUTO PRESS. Auto press digital controller failure.. AIR VENT EXH. Avionic extraction fan failure or overheat. AIR OVBD. Ovbd Valve in disagreement with Ovbd Valve SW position.. EXCESS CAB ΔP. Cabin/ Outside pressure difference in excess of 6.6 psi. AIR FWD DET FAN. Forward fan sensed inop. AIR AFT DET FAN. Lavatory fan sensed inop. AIR DITCH. Ditch P/B selected on. OXY. Oxygen supply off or oxygen lo pressure sensed. ANTI ICE A-ICING BLEED. Airframe bleed fault alert covering low pressure, overheat and AFR airbleed P/B off. A-ICING FRAME. Airframe deicing fault confirmed by MFC. A-ICING AUTO. Auto mode fault detected or MAN mode selected. A-ICING SEL. Mode selector fault. A-ICING DETECT. Ice detector fault. A-ICING ENG 1 / A-ICING ENG 2. Deicing boots fault detected on engine 1 or 2. A-ICING PROP 1 / A-ICING PROP 2. Blade deicing fault detected on at least one blade on enigne 1 or 2. A-ICING HORNS 1 / A-ICING HORNS 2. Horn deicing fault detected on Horns 1 (rudder & left elevator) or Horns 2 (aileron & right elevator). A-ICING L WSHLD / A-ICING R WSHLD. Windshield deicing fault detected on left (L) or right (R) side. A-ICING WINDOWS. Either Left or Right side windows deicing fault detected. A-ICING PROBE. Either Left or Right or both alpha probe deicing fault detected. A-ICING PIT CPT / --- PIT F/O / --- PIT SBY. Pitot heating fault (captain, first officer or stand by). A-ICING TAT CPT / A-ICING TAT F/O. TAT probe heating fault (captain or first officer). ICING. Ice accretion detected by ice detector. AUTO PILOT AP PITCH TRIM. Pitch trim failed. PITCH MISTRIM. Pitch mistrim. AILERON MISTRIM. Aileron mistrim. RUDDER MISTRIM. Rudder mistrim. AP YAW TRIM. Yaw auto trim fail. MPC APM FAULT. A fault has been detected in the APM system. DEGRADED PERF. Abnormal drag increase. INCREASE SPEED. Aircraft speed lower than Minimum Severe Icing Speed + 2kt. AVIONICS AUDIO SEL CAPT / AUDIO SEL F/O. RCAU on CAPT or F/O side is sensed fault or has a power loss. SGL DME / DME LOSS. One DME lost (2 DME config)/ Both DME lost (2 DME config) or DME lost (single DME config). RMS / RMS 1+2. One RMS lost / RMS 1+2 lost. TCAS. TCAS sensed fault. XPDR. At least one XPDR detected fault. AHRS / AHRS 1+2. One AHRS fault / Both AHRS fault. AHRS NOT ALIGN. AHRS sensed not aligned. ADC / ADC 1+2. One ADC fault / Both ADC fault. ATT DISAGREE. 3° pitch and 3° roll discrepancy. HDG DISAGREE. 8° discrepancy. ALT DISAGREE. 60ft + (Zp1 + Zp2)/460. IAS DISAGREE. 10kt discrepancy. 27.

(33) S y s t e m s 4 2/72 - 6 0 0. VHF / VHF 1+2 / HF / HF 1+2. VHF or HF set(s) sensed failed. VHF EMITTING / HF EMITTING. Transmitting / Emitting for more than 29s. DU 1(2)(3)(4)(5) DISCRPNCY. Discrepancy on one DU (internal and external with other DU). DU DISCREPANCY. Discrepancy on not identified DU (at least 2 DU discrepancy). DU TEMP HI. Temperature >70°C after brightness reduction. MULTI DUs T HI. Temperature >70°C after brightness reduction for at least 2 DUs. FWS SGL CH. Flight Warning Application (FWA) loss on one CAC. SWITCH SGL CH. gateway and SWitching Module (SWM) card loss on one CAC. CPM 1 / CPM 2. Core Processing Module (CPM) card loss on one CAC. IOM 12 / IOM 13 / IOM 22 / IOM 23. Input/Output Module (IOM) card loss. CPM x + IOM xx. Core Processing Module (CPM) card loss on one CAC and Input/ Output Module (IOM) card loss on the other CAC. IOM xx + xx. 2 Input/Output Module (IOM) cards loss. MISCELLANEOUS CONFIG. Configuration warning refer to chapter C.4 here below. RAD-ALT. Single RA loss on 2 RA installed configuration. RAD-ALT LOSS. RA loss on single RA configuration or dual RA loss on 2 RA configuration. GPWS. GPWS fault sensed. TERRAIN. Terrain mode fault sensed. DOORS. Any door sensed open on ground. DOOR EMER / DOOR FWD COMPT. Emergency hatch or Forward compartment door sensed unlocked in flight. DOOR LH (RH) FWD / DOOR LH (RH) AFT. Respective door sensed unlocked in flight. DATALINK. CMU fault or loss of link for more than 120s. MAINT PANEL. Maintenance panel sensed open. DATA RECORDER. Loss of power supply to Data recorder detected. VOICE RECORDER. Loss of power supply to Voice recorder detected. FDAU. FDAU sensed failed. BAD CONF / CONF UPDATED. At least one DU software discrepancy at A/C power up. MFC MFC 1A / MFC 1B / MFC 2A / MFC 2B. Single MFC channel failure. MFC 1A(1B)(2A)(2B) + 1B (1A)(2A)(2B). Multiple MFC channels failures (combinations). 4. EMER audio cancel & TO config test EMER AUDIO CANCEL Guarded switch, cancel the aural specific of an undue continuous aural except for landing gear, VMO, VFE, VLE, stall warning, pitch trim whooler, landing gear, AP disconnection. 28. ATA 31 TO CONFIG TEST – To check T/O configuration (PWR MGT in T/O+ TLU LO SPD illuminated + pitch trim in green sector+flaps 15° + no AIL LOCK LIT on FWS) by simulating power levers at T/O position, except PARK BRAKE – To perform an automatic RECALL.

(34) C. Flight warning system. 5. Aural alarms. ATA 31. CLACKER VMO VLO - 5 kt VFE - 5 kt. DOOR BELL Attendant 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). 29.

(35) D. Air FCOM 1.03. 31.

(36) S y s t e m s 4 2/72 - 6 0 0. 1. Pneumatic system. ATA 21/36. The pneumatic system supplies aircraft systems which use pressurized air: These systems are: – Air conditioning – Ventilation – Pressurization – De-icing. 1.1. Schematic 3$&.. ;9$/9( 23(1. 3$&.. 29+7. 29+7 /($.. 3523%5. 6(/(&725 2)). 7/223. 7/223. 7!&. 7!&. (1* %/(('. (1* %/(('. (1*),5(. )$8/7. 7!&. 2)). %/((' 9$/9( 29(535(6685( 6:,7&+ 36,

(37). 21. )$8/7. 7!&. %/((' 9$/9(. +3 9$/9(. 7!& +3. (1*. 7!& /3. /3 /()7/($.'(7(&7,21/223 5,*+7/($.'(7(&7,21/223. 32. (1*),5(. 2)). +3 9$/9( (1* :,1* '(,&,1*. /($.. (1*. +3. (1*:,1* '(,&,1*.

(38) D. Air 1.2. AIR BLEED panel ENG BLEED Controls both bleed and HP valves. Spring loaded closed. Must have air and electricity to open Auto closure when OVHT, leak, overpressure, fire handle pulled, UPTRIM triggered or prop brake on (left one only). Inhibited during eng start. GRD X FEED Spring loaded closed. Inhibited in flight. Auto opens on ground when only one bleed valve is opened. PACK VALVE FAULT pack valve disagreement with pb / or OVHT downstream pack comp. (>204°C). FWS. Valve auto closed. Ground cooling turbo fan failure. OVHT either duct temp switch above 274°C. FWS. Auto closure bleed valves (LP and HP). May be reset after cooling. OVERHEAD PANEL ENG BLEED FAULT Bleed valve disagreement with selected position (or in case of OVHT or LEAK). FWS. Associated valves auto closed. PACK VALVE Spring loaded closed. Must have air and elec power to open. 6’’ delay on RH valve for pax comfort. LEAK activates when T° detected by bleed loop exceeds 153 ±8°C. EWD. Auto closure after 1’’ of following valves: Bleed, HP, pack and GND Xfeed if left bleed leak affected DO NOT RESET BLEED. 33.

(39) S y s t e m s 4 2/72 - 6 0 0. 2. 4. 3 1. 5. 34.

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