ATR 72-600 Systems [PDF]
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PRODUCT SUPPORT & SERVICES
SYSTEMS Contact
For ordering manuals, please contact us at: Phone: +33 (0)5 6221 6207
SCAN YOUR AIRCRAFT
42 PEC 72 PEC Glass cockpit - 600
e-mail: [email protected] ATR Product Support & Services Portal: https://www.atractive.com
© ATR Product Support & Services - May 2014 Avions de Transport Régional. 1, allée Pierre-Nadot 31712 Blagnac Cedex - France Phone: +33 (0)5 62 21 62 07 - Fax: +33 (0)5 62 21 63 67 - https://www.atractive.com
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Dear Readers, Every effort has been made to ensure document quality. However please do not hesitate to share your comments and information with us by using the following address: [email protected] Yours faithfully,
Printed on 100% recycled paper using vegetable inks
Your ATR Training and Flight Operations support team.
© ATC May 2014 All reasonable care has been taken by ATC to ensure the accuracy of the present document. However this document does not constitute any contractual commitment from the part of ATC which will offer, on request, any further information on the content of this brochure. Information in this brochure is the property of ATC and will be treated as confidential. No use or reproduction or release to a third part may be made there of other than as expressely authorised by ATC.
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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.
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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
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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
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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
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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
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A. Aircraft general FCOM 1.00
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S y s t e m s 4 2/72 - 6 0 0
1. Doors location
Cargo door
Pilot communication hatch
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
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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)
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4. External lights
ABCDE F GH-
ATA 33
Navigation lights Taxi and T/O lights Landing lights Wing lights Beacon lights Strobe lights Logo lights Emergency light
Cabin panel
Memo panel display
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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 20V on STBY bus and at least 1 GEN operating
DISARM system deactivated
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8. Internal lighting
ATA 33
MIP/PED
OVHD
The STORM switch overrides the MIP/PED rotary selector to put in the maximum intensity setting
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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)
MIP/PED
OVHD
OVHD rotary selector selects activation and intensity of overhead panels integral lighting
FLOOD knob selects activation and intensity panel flood lighting. (OFF TO BRT)
10. ANN LT panel
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
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B. Integrated systems FCOM 1.01
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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)
DU 1
DU2 FMA 1 RMA 1
DU 3
DU 4 FMA 2 RMA 2
DU 5
AFDX A429 CPM 1
IOM /S 1
IOM /AP 11
IOM /DC 12
IOM SWM /DC 1 13
CPM 2
IOM /S 2
AFCA 1 FWA 1 DCA 1 CMA 1
CAC 1
IOM /AP 21
IOM /DC 22
IOM SWM /DC 2 23
AFCA 2 FWA 2 DCA 2 DISCRETE ANALOG
A429
CAC 2
SYSTEMS
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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 Inter-card dialogue (ARINC 429)
MFC1A Hardwired logic Aircraft system outputs
Electrical power
28VDC Alternate supply
MFC1B
MFC2A
MFC2B
Aural
Hardwired logic
Aural
Computation (soft) Computation (soft)
Aircraft system inputs
28VDC Normal supply
Inter-card dialogue (ARINC 429)
DC ESS BUS or GND HDLG BUS HOT EMER BAT BUS
Aircraft system outputs
Aircraft system outputs
Aircraft system inputs
Aircraft system inputs
Electrical power
Electrical power
DC EMER BUS
MAIN BUS 1
28VDC Alternate supply
28VDC Normal supply
28VDC Normal supply
28VDC Alternate supply
Aircraft system outputs
Computation (soft) Computation (soft)
DC ESS BUS or GND HDLG BUS HOT EMER BAT BUS
Aircraft system inputs
Electrical power
DC EMER BUS
MAIN BUS 1
28VDC Alternate supply 28VDC Normal supply
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.
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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) → FDM purpose – Management of reports (take-off, cruise... ) → FDM purpose – Dialogue with the following aircraft equipments: MCDU, Printer, ACARS (optional) – Other maintenance functions.
PRINTER ACARS (Optional)
MCDU
DU 1
MPC DMU
DU 2
CAC 1
Accelerometer Signals From Aircraft Systems
DU 3
FDAU DU 4
CAC 2 DU 5
SSFDR
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B. Integrated systems
4. Schematic
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C. Flight warning system FCOM 1.02
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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)
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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.
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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)
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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 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 140°C
ENG 1 OIL PRESS / ENG 2 OIL PRESS
Oil press 50°C
FUEL 1 TEMP LO / FUEL 2 TEMP LO
Fuel temperature 25 PSI. Filter blocked and by-passed when ∆PSI >45 PSI
FUEL FEED LO PR
Engine feed low press 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
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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 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.
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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 ∆P
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 ALPHA / A-ICING ALPHAS
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
YAW AUTO 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
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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
AVNX SGL SWITCH
gateway and SWitching Module (SWM) card loss on one CAC
AVNX CPM 1 / CPM 2
Core Processing Module (CPM) card loss on one CAC
AVNX IOM 12 / IOM 13 / IOM 22 / IOM 23
Input/Output Module (IOM) card loss
AVNX CPM x + IOM xx
Core Processing Module (CPM) card loss on one CAC and Input/ Output Module (IOM) card loss on the other CAC
AVNX 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
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
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C. Flight warning system
5. Aural alarms
ATA 31
CLACKER VMO VLO VFE
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)
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D. Air FCOM 1.03
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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 PACK 1
X VALVE OPEN
PACK 2
OVHT
OVHT
T LOOP
T LOOP
T° >153°C
T° >153°C
ENG.1 BLEED
ENG.2 BLEED
LEAK
ENG 1 FIRE PROP BRK SELECTOR OFF
FAULT
T >274°C
FAULT
T >274°C
OFF
BLEED VALVE OVER PRESSURE SWITCH (80 PSI)
BLEED VALVE
HP VALVE
HP VALVE
T >270°C HP
ENG 2 FIRE
OFF
ON
ENG/WING DE ICING
LEAK
ENG 1
T >270°C LP
LP
ENG 2
HP
ENG/WING DE ICING
LEFT LEAK DETECTION LOOP RIGHT LEAK DETECTION LOOP
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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
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2
4
3 1
5
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D. Air Item
Display
Description
BLEED VALVE ON , OPENED AND ENGINE RUNNING
Item
Display
Description
BLEED OFF
BLEED VALVE OFF
BLEED FAULT
BLEED VALVE FAULT
3
LEAK
BLEED LEAK
4
OVHT
BLEED OVERHEAT
2
BLEED VALVE OFF
1
BLEED VALVE ON BUT CLOSED
X FEED NORMAL OPERATION X FEED OPEN & AIR FLOW BLEED VALVE OFF BUT NOT CLOSED AND ENGINE RUNNING
X FEED X FEED
BLEED VALVE OFF BUT NOT CLOSED AND ENGINE NOT RUNNING
NORMAL OPERATION XFEED CLOSED NOTHING DISPLAYED
X FEED X FEED NORMALLY CLOSED BUT OPENED & AIR FLOW
5
X FEED
X FEED NORMALLY CLOSED BUT OPENED & NO AIR FLOW
X FEED X FEED NORMALLY OPENED BUT CLOSED
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AIR CONDITIONING IN HOTEL MODE On ground, when engine 2 is started in hotel mode: – The right HP bleed valve is opened (air supplied by HP compressor at low engine power) – The right Eng bleed valve opened (at NH 45% + 30s) – The cross feed valve is opened – Both packs are supplied with air at 38 psi
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D. Air
AIR CONDITIONING IN NORMAL FLIGHT – Both HP bleed valves are closed (air supplied by LP compressor at high engine power) – The cross feed valve is closed – Each pack is supplied by its dedicated engine with air at 25 psi
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AIR CONDITIONING IN FLIGHT WITH A BLEED FAULT In case of: • Overtemperature (T>274°C) • Leak (T>153°C outside the duct) • Overpressure (P>80 psi) The eng bleed valve is closed and the FAULT is triggered on the bleed P/B and on the pack P/B. The other engine supplies the cockpit and cabin ducts throught the mixing chamber – HP bleed valves is closed (air supplied by LP compressor at high engine power) – The cross feed valve is closed – One pack is supplied by its dedicated engine with air at 25 psi
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D. Air
2. Air conditionning
ATA 21
The air conditionning system is provided to keep the flight compartments at the required temperature, pressure, humidity and cleanliness for the comfort of the passengers and crew.
2.1. Schematic
Cooling of air: – by ground turbo fans: • IAS ≤ 150 kt and ldg gear is retracted for less than 10 min • IAS ≤ 150 kt and ldg gear is extended. – by ram air when IAS >150 kt
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2.2. COMPT TEMP panel
RECIRC FAN Assists pack air flow RECIRC FAN FAULT: fan low speed or motor overheat + FWS. No auto disconnect
COMPT INDICATOR Duct temperature limited to 88°C. (191°F) by pneumatic temp.limiter
TEMP SEL OVHT: duct overheat >92 °C + FWS. Pack valve will not auto close
MAN compt temp knob controls directly temp control valve
TEMP SEL AUTO: the temperature is regulated 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)
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D. Air
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4
5
3 6
1 8
7 2
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D. Air Item
Display
PACK
1
Description
Item
Display
PACK VALVE ON
PACK OFF
PACK VALVE OFF
PACK FAULT
PACK FAULT
PACK STBY
PACK VALVE STANDBY P/B DEPRESSED AND BLEED VALVE P/B RELEASED OUT
EXTRACT FAN ON
4
EXHAUST OVBD EXHAUST FAULT
FULL OPEN
FULL CLOSE
RECIRCULATION FAN ON
RECIRCULATION FAN FAULT
RECIRC
RECIRCULATION FAN 1 OR 2 OFF
RECIRC
RECIRCULATION FAN 1 OR 2 FAULT
MANUEL MODE OVBD VLV FULL OPEN MANUEL MODE OVBD VLV FULL CLOSED
AUTOMATIC MODE OVBD VLV PARTIALLY OPEN OVBD VALVE
OVBD VLV FAULT DISPLAY OVBD VLV OPEN
OVBD VALVE
OVBD VLV FAULT DISPLAY OVBD VLV CLOSED
AUTO
6
3
EXTRACTION FAN FAULT DISPLAY
AUTOMATIC MODE OVBD VLV FULL CLOSED
5
BOTH PACK VALVES ON OR BOTH RECIRC FANS ON
LEFT PACK VALVE AND RECIRC FAN 2 OFF OR FAULT
EXHAUST MODE P/B RELEASED
AUTOMATIC MODE OVBD VLV FULL OPEN
RECIRCULATION FAN OFF
2
Description
AUTOMATIC TEMPERATURE CONTROL
MAN
MANUAL TEMPERATURE CONTROL
OVHT
DUCT OVERHEAT ALERT
21 °C
VALID SENSOR MEASUREMENT
-- °C
INVALID MEASUREMENT
AIR HIGH FLOW
HIGHT FLOW SELECTED
7
8 RIGHT PACK VALVE AND RECIRC FAN 1 OFF OR FAULT
PACK VALVES AND RECIRC FANS OFF OR FAULT ON BOTH SIDES
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3. Avionics ventilation
ATA 21
The ventilation system provides cooling through ambient air extraction to limit the internal operating temperature of the electronic equipment
3.1. Schematic
ELEC SMK
3.2. AVIONICS VENT panel FAULT fan failure/overheat (fan inhibited for 120 s. after eng start or after a GPU power on. FWS)
EXHAUST MODE NORM – On ground, ENG 1 off: extract fan on. OVBD valve full open, U/F valve closed – Air/ground, ENG 1 on: extract fan operates. OVBD valve closed. U/F valve opened
OVBD extract fan off OVBD valve partially opened (in flight only). U/F valve closed
FAULT OVBD valve in disagreement with ovbd valve SW position
OVBD VALVE – AUTO except in emergency – direct control of OVBD valve. The full open position is possible only if the delta P is 6.35 PSI or < –0.5
Cabin pressure
Manual controller knob MANUAL MODE
Pneumatic outflow valve
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S y s t e m s 4 2/72 - 6 0 0 4.2. Cabin pressure indicators Pressure control mode AUTO or MAN DIFF Differential pressure: max +6.35/–0.5
ALT Cabin alt: based on 29.92 in.hg (1013,2 Hpa)
RATE Cabin rate of climb
4.3. AUTO PRESS panel
AUTO PRESS (DC BUS ) Memorize departure field elevation up to 3500 ft
DUMP FUNCTION ON (guarded pusbutton) Both outflow valves fully open in auto mode only.
ELV SET 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
4.4. MAN RATE KNOB and CABIN PRESS panel
NORM AUTO MODE position. When used in MAN mode, cabin rate selection +2500/–1500 fpm
FAULT digital controller failure. FWS
DITCH pb ON both outflows are fully closed
MAN digital controller out of operation. (no more digits on landing elevation display)
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D. Air
1
Item
Display
6 8 3.00
0
3
Description
2 Item
Display
Description
AUTOMATIC PRESSURE CONTROL AUTO PRESS CAB ALT 5020 FT NOMINAL DISPLAY
ΔP NOMINAL DISPLAY
AUTOMATIC PRESSURE CONTROL AUTO PRESS CAB ALT 1300 FT FAULT
0
6 8 0.25
0
6 8 7.00
ΔP ALERTING DISPLAY
6 8
INVALID ΔP
ΔP PRE-ALERTING DISPLAY
MAN PRESS CAB ALT 5020 FT TARGET 5020 FT
MANUAL PRESSURE CONTROL NOMINAL DISPLAY
1
0
3
2000 0
700 UP
MAN PRESS MANUAL PRESSURE CONTROL CAB ALT 2050 FT TARGET ____ FT INVALID TARGET
RATE OF CLIMB
MAN PRESS CAB ALT ____ FT INVALID CAB ALT TARGET 2050 FT MAN PRESS CAB ALT 8900 FT CAB ALT PRE-ALERTING DISPLAY TARGET 5020 FT MAN PRESS CAB ALT 10100 FT CAB ALT ALERTING DISPLAY TARGET 5020 FT
2000
MAN PRESS NO DESTINATION IN CAB ALT 5200 FT TARGET LDG ELEV FMS AND BACK COURSE OF THE LOC (UPPER MODE)
BC * LNAV ‘’LO‘’ or ’‘ ‘’
NAV MODE ASSOCIATED WITH A FMS (UPPER MODE)
LNAV BC
LNAV BC *
10
3
Mode change
1
8
AP FD DUAL SPD HLD TCS FD SINGLE CH
13 1
7
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4
5
ARM
Mode change
+7s
PITCH HOLD
PITCH HOLD
VOR
IAS
IAS
IAS MODE (UPPER MODE)
VOR
VS
VS
VS MODE (UPPER MODE)
4
5 Mode change + CAPTURE
+7s
HOLD
ALT SEL
ALT 9
ALT 9
ALT
ALT MODE (UPPER MODE)
GS
GS 9
GS9
GS
APP MODE ASSOCIATED WITH AN ILS (COMMON UPPER MODE)
1
2 Mode change
4 +7s
HDG HOLD LOC
PITCH HOLD MODE (BASIC MODE)
VOR
ARM
ARM
Description
LOC✶
HOLD
HDG HOLD LOC✶ Item
LOC Display
Description
5
ARM
Mode change
0
GA
GS
GS✶
+7s
HOLD
GA MODE COMMON MODE
GA GS✶
Description
GS
APP MODE COMMON MODE
Description
AP
ENGAGEMENT OF THE AP/YD ON THE FGCP (⊳ AP u AND ⊳ YD u)
YD
ENGAGEMENT OF THE YD ON THE FGCP (⊳ YD u)
FD
FLIGHT DIRECTOR COMMAND BARS DISPLAYED ON THE PFD
6
7
COUPLING ON CAPT SIDE WITH THE CPL P/B ON THE FGCP (⊳ CPL) COUPLING ON F/O SIDE WITH THE CPL P/B ON THE FGCP (CPL u)
8 DUAL
DUAL COUPLING IN CAT 2 APPROACH (⊳ CPL u)
9
SPD HLD
SPEED HOLD IN PROVISION FOR CAT 3
10
TCS
ACTIVATION OF THE TCS PUSH BUTTON
CAT 1
ILS CAT 1 APPROACH
CAT 2
ILS CAT 2 APPROACH
13
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E. Automatic flight control system
16
15
ROLL HOLD LO ICING DGD PERF VOR RETRIM ROLL R WING DN CAT1 14
PITCH HOLD ALT SEL CHECK NAV SRC 12
AP FD DUAL SPD HLD TCS FD SINGLE CH 11
11 AP/YD disengagement, approach category retrogression, AFCS internal failure. Message AP DISENG
Message + 7s
Aural alert
AP DISENG
Cavalry Charge AP/YD DISENG
AP/YD DISENG
YD DISENG AP/YD DISENG
YD DISENG AP/YD DISENG
AP/YD INVALID
YD DISENG
AP INVALID
AP/YD DISENG
AP INHIBIT
YD DISENG
YD INHIBIT
Display logic
Comments
Red message, reverse The AP/YD can be disengaged either video flashing. Reset by the automatically or manually Quick Disconnect P/B Amber message, reverse The AP/YD can be disengaged either video flashing. Reset by the automatically or manually Quick Disconnect P/B Amber message, reverse video flashing.
When an AFCS Internal failure inhibits AP/YD or YD engagement
AP/YD DISENG
Yellow message, steady for 7 seconds
When AP or YD engagement are attempted and an AFCS External failure or condition inhibits AP engagement
SPD HLD INHIBIT YD INHIBIT
YD DISENG AP/YD DISENG
Yellow message, steady for 7 seconds
When speed hold engagement are attempted and an AFCS External failure or condition inhibits speed hold engagement
CHECK SPD HLD YD INHIBIT
CHECK SPD HLD AP/YD DISENG
Amber message, reverse video flashing
When speed hold is unable to maintain target speed
FD SINGLE CH YD INHIBIT
FD SINGLE CH AP/YD DISENG
Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared
When one FD channel is lost
Amber permanent steady message
When “single AHRS” and /or “single ADC” configuration is active. After an AHRS or ADC failure, the “single AHRS” and/or “single ADC” configuration is selected on the switching control panel
FD SINGLE SRC YD INHIBIT
FD SINGLE SRC AP/YD DISENG
CAT 2 INVALID YD INHIBIT
FD SINGLE SRC AP/YD DISENG
Triple clicks
Amber message, reverse video flashing for 7 seconds, then disappears
Loss of CAT2 valid requirements during a CAT2 approach
CAT 3 INVALID YD INHIBIT
FD SINGLE SRC AP/YD DISENG
Triple clicks
Amber message, reverse video flashing for 7 seconds, then disappears
Loss of CAT3 valid requirements during a CAT3 approach
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S y s t e m s 4 2/72 - 6 0 0 12 Unexpected mode change, or problem in navigation parameters Message flashing CHECK NAV SRC
CHECK NAV SRC
CHECK T/O SPEED
Message + 7s PITCH MISTRIM
CHECK NAV SRC
CHECK T/O SPEED
ADC INVALID
CHECK T/O SPEED
ATT INVALID
CHECK T/O SPEED
HDG INVALID
CHECK T/O SPEED
NAV INVALID
CHECK T/O SPEED
SPD AUTO INOP
SPD AUTO INOP
EXCESS DEV
ALT OFF
FD MODE CHG
CHECK T/O SPEED
CHECK T/O SPEED
EXCESS DEV
EXCESS DEV
FD MODE CHG
Aural alert
Display logic Yellow message flashing for 7 seconds then disappears Amber message, reverse video flashing for 7 seconds, then steady until failure is cleared by trying to engage another FD mode, or by pressing STBY pb Amber message, reverse video flashing for 7 seconds, then steady
Comments If the crew try to engage a NAV mode where as the wrong nav source is selected, or if the navigation source is lost – If an armed or engaged NAV mod dropped off following a nav source change – If a VOR/LOC nav frequency change induces the current mode loss – In case of coupling change If VCP lcing selection disagrees with the actual icing conditions (HORNS ON/OFF)
– In case of ADC data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on CAS and TAS). After clearing the AP/YD DISENG warning, the FMA displays ADC Yellow message, flashing for INVALID, associated with CHECK ALT or CHECK IAS on the PFD 7 seconds, then disappears – Or in case of loss of ADC redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the AP/YD DISENG warning, the FMA displays ADC INVALID – In case of AHRS data miscomparison, the AP/YD is disengaged (disengagement only for discrepancy on attitude parameter). After clearing the AP/YD DISENG warning, the FMA displays Yellow message, flashing for ATT INVALID, associated with CHECK ATT on PFD if Roll or Pitch 7 seconds, then disappears angles are not coherent – Or in case of loss of AHRS redundant sensor indicated by a flag, the AP/YD is disengaged. After clearing the AP/YD DISENG warning, the FMA displays ATT INVALID – In case of AHRS data miscomparison, the FMA displays HDG Yellow message, flashing for INVALID, associated with CHECK HDG on the PFD & ND, if 7 seconds, then disappears magnetic headings are not coherent (No AP/YD disengagement) – Or in case of loss of AHRS redundant sensor indicated by a flag Yellow message, flashing for In case of loss of NAV redundant sensor indicated by a flag 7 seconds, then disappears If AUTO is selected with the ”AUTO/MAN” SEL P/B and the speed Amber message, reverse target from both FMS is not valid. The AUTO speed mode is video flashing for not available and the speed is automatically switched to MAN 7 seconds, then disappears (Cyan Speed Target Bug). The Speed Target Bug is automatically synchronized to the current value of A/C speed – When the ICP AUTO/MAN push-button is pressed while man is selected and IAS target from the selected FMS is invalid – The aircraft is not in the good configuration before selecting Yellow message, flashing for SPD AUTO 7 seconds, then disappears good configuration: - Flaps 15° - PWR MGT TO - Alt sel > Alt A/C - IAS mode engaged Red message, reverse video Excessive deviation on the GS or the LOC. The message on the flashing for 7 seconds, then FMA is associated with the GS or the LOC deviation scale flashing steady amber amber to indicate a flight path excusion Amber message, reverse During Altitude Capture video flashing for – When the selected altitude is changed (transition to basic pitch) 7 seconds, then disappears – When baro correction is changed (transition to basic pitch) Amber message, reverse video flashing for 7 seconds, then steady until failure is When an AHRS failure (ATT INVALID cleared by changing AHRS or HDG INVALID) leads to the FD mode cancellation source selection, or by selecting another FD mode, or by pressing STBY P/B
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E. Automatic flight control system
nav
nav
mode
STEEP APP
EXCESS DEV
Green message steady
When steep approach is selected
AFCS TEST
EXCESS DEV
Amber flashing
During the AFCS test (maintenance opération)
14 Trim status Message
Message + 7s
AP PITCH TRIM FAIL
AP PITCH TRIM FAIL
PITCH MISTRIM
PITCH MISTRIM
Aural alert
Display logic
Displayed when the AFCS is not able to command the pitch trim and the AP is engaged
ons
ged r
ENG
When the pitch servo motor reaches a torque value threshold
RETRIM ROLL R WING DN RETRIM ROLL R WING DN RETRIM ROLL L WING DN RETRIM ROLL L WING DN
FD
Comments
NIL
Amber message, reverse video flashing 7 seconds, then steady
When the aileron servo motor reaches a first torque value threshold
AILERON MISTRIM
AILERON MISTRIM
When the aileron servo motor reaches a second torque value threshold
YAW AUTO TRIM FAIL
YAW AUTO TRIM FAIL
Displayed when the AFCS is not able to command the yaw autotrim
RUDDER MISTRIM
RUDDER MISTRIM
aged ).
itch
a ENG
When the rudder servo motor reaches a second torque value threshold
DG
ment) a flag
15 Icing message (refer to chapter ice and rain protection) 16 APM message (refer to chapter ice and rain protection)
speed
AN cally
When both FD channel are lost. The FMA is black. The AFCS FAIL is the only message displayed
an is
AFCS FAIL
ng
the ashing
pitch) h)
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S y s t e m s 4 2/72 - 6 0 0
3. FGCP (Flight Guidance and Control Panel) NAV SOURCE Selector CAPT side Select the NAV source for CAPT EHSI and/or ND (FMS1, VOR/ILS1, VOR/ ILS2, FMS2)
VS mode to use FD with a desired vertical speed
IAS mode to use FD with a target indicated airspeed. (Cyan speed bug: MAN on ICP) (Magenta speed bug: AUTO on ICP) NAV mode to use FD with VOR and LNAV course
HDG mode to use FD with HDG SEL
ATA 22
AP pb engages autopilot and yaw damper and disengages only autopilot Engagement inhibited for 5 sec after T/O
NAV SOURCE Selector F/O side Select the NAV source for F/O EHSI and/or ND (FMS1, VOR/ ILS1, VOR/ILS2, FMS2)
CRS 1 knob selects course on CAPT EHSI and/or ND
FD bars P/B to set ON/OFF
CRS 2 knob selects course on F/O EHSI and/or ND
HDG knob selects HDG bug on both EHSI and/or ND. Pushing on the knob, synchronize the heading to the actual one.
APP mode to use FD with ILS information course (lateral and vertical): – lateral (LOC) – vertical (GS)
BC mode to use FD with localizer in back course
Pitch wheel to adjust VS or pitch attitude in basic mode
ALT mode to use FD with a desired altitude
FD bars P/B to set ON/OFF
YD pb engages yaw damper and disengages yaw damper and autopilot if engaged
CPL pb permit to couple AP/FD on CAPT or F/O side. Dual coupling for CAT 2
STBY pb cancels all FD upper modes (armed and captured and active modes) and returns in basic modes.
4. ICP (Index Control Panel)
Speed target selection Selection of the speed bug between: – AUTO: Speed bug managed by the FMS (Magenta) – MAN: Speed bug set manually by the speed knob (Cyan)
ALT knob controls the preselected altitude on PFD
ATA 22,31
Speed knob Used to set the speed bug In MAN mode
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F. Communications FCOM 1.05
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S y s t e m s 4 2/72 - 6 0 0
1. Schematic
ATA 23
The communication system provides communication between: – aircraft and ground stations – cockpit crew stations – cabin attendant station – ground crew stations
CAPT SIDE – oxy mask mike – hand mike – boom set – head set – PTT switch – nose wheel steering control PTT – loudspeaker – loudspeaker audio level – audio control panel
COM SYSTEM
NAVIGATION SYSTEM
COCKPIT VOICE RECORDER
CABIN ATTENDANT OBSERVER SIDE – oxy mask – boom set – head set – PTT switch
REMOTE CONTROL AUDIO UNIT
GROUND CREW
PASSENGER F/O SIDE – oxy mask mike – hand mike – boom set – head set – PTT switch – loudspeaker – loudspeaker audio level – audio control panel
PUBLIC ADDRESS SYSTEM
2. PTT selector and NOSE WHEEL STEERING CONTROL SW
PTT selector interphone: forward position neutral: center position radio: backward position
GPWS
TCAS
ATA23
NOSE WHEEL STEERING CONTROL switch When depressed, BOOM SET or OXY mike is connected for transmission
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F. Communications
3. Audio control panel
Transmission keys Only one key can be engaged at a time. It illuminates white when selected
VOICE ONLY key When depressed, it inhibits NAV receivers station identification. Light illuminates amber when selected.
Volume control knob to set volume from associated communication or navigation facilities
ATA 23 INT/RAD selector Provides selection of transmission mode when using OXY MASK or BOOM SET mike INT: hot mike position. Interphone is always operative between crew stations. Other transmissions require to select a transmission key and use a PTT pb NEUTRAL: Interphone is inoperative. Other transmissions require selecting a transmission key and using a PTT pushbutton. RAD: This position is required to automatically connect for transmissions BOOM SET and OXY MASK mikes without using a PTT pb, when released the selector is springloaded to NEUTRAL.
4. VHF control
ATA 23 VCP
MCDU MCP
MCP and MCDU allow to tune VHF frequencies MCDU allows to: – set the squelch (SQL - ON/OFF) – set directly the EMER frequency (121.5 Mhz)
VHF 1 Frequency Display
Selection Push Button To change the selection cursor To VHF
Rotary selector To tune the VHF frequency
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5. AUDIO SEL pb FAULT illuminates amber and the FWS is activated when an associated RCAU processing board failure or power loss is detected
ATA 23 AUDIO SEL Controls functioning of associated RCAU processing board. NORM: RCAU functions normally 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
6. Loudspeaker volume knobs
ATA 23 LOUDSPEAKER Communication reception. In case of aural alert: – normal volume is always available regardless of knobs position. – during any transmission the volume of both loudspeakers is muted
7. TCAS control box
ATA 34 VCP
MCDU
MCP
MCP and MCDU allow to set between AUTO, TA ONLY and STBY MCDU allows to set between ABV, NORM, BLW on the displays.
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F. Communications
8. EMER LOC XMTR panel AUTO TEST RST is used in case of undue alert or to test the emergency beacon. two cases are possible for the test – network X MIT ALERT illuminates amber during 2’’ – failure XMIT ALERT lt flashes during 15 seconds
9. Cabin attendant handset
ATA 23 Switch AUTO transmission is made automatically on 121.5 MHz, 243 MHz and 406 MHz when deceleration exceeds 5 g MAN allows commanded operation or test
ATA 23 Cabin attendant handset PA: public adress to make an annoncement to passengers INT: internal communications with crew EMER: emergency call
10. Handmike and handset
ATA 23
11. CALLS panel
ATA 23
EMER illuminates in case of emergency call from cabin
12. Head set / boom set / hand mike panels
CALLS ATTND to call cabin from cockpit. One time for a normal call three times for an emergency call MECH to call the ground crew from cockpit A horn is generated In case of cabin crew or ground crew call, depress RESET to cancel both associated visual and aural alerts
ATA 23
Head set / boom set panel / hand mike panels allows connection of a boom set, a head set and a hand mike
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13. ATC control
ATA 23 VCP
MCDU
MCP and MCDU allow: – to set the transponder code – to set the mode (ON/ STBY) – to set the ALT mode (ON/OFF) – to set XPDR 1 or 2
MCP
MCDU allows to: – set the flight identification (FLT ID) – set directly the EMER code (7700)
14. CVR panel
ATA 23 TEST pb when depressed and held, the test circuit is activated – the pointer moves to a location between graduations 8 and 10 – if a headset is plugged into the jack, the 600 HZ signal is heard
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 recordings when the landing gear shock absorbers are compressed and parking brake is set (depress for 2 sec. to completly erase) During erasure, a 400Hz audio signal can be heard in the headset
HEADSET jack when headset is plugged into the jack: – cockpit sounds picked up by the microphone are audible – erase tone is audible when ERASE pb is depressed
MICROPHONE picks up cockpit conversations and alert sounds
15. Crew oxygen mask
ATA 23
A micro phone is incorporated inside the crew oxygen mask
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G. Electrical systems FCOM 1.06
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S y s t e m s 4 2/72 - 6 0 0
1. Sources of power
ATA 24
Three type of currents are available: Direct current (DC) Alternating current with constant frequency (AC) Alternating current with variable frequency (ACW)
Two DC starter/generators 61,5% NH generator mode
Two batteries
DC power 28 VDC
Two inverters
AC power VAC 26 V VAC 115 V
ACW power 115V/200V
TRU (Emergency supply)
DC power 28 VDC
DC GPU
Two AC wild frequency alternators minimum NP 66%
AC GPU
The TRU provides power to the emergency loads in case of dual DC generators loss. It is supplied by the ACW bus 2.
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G. Electrical systems The DC Starter Generator is driven by the HP spool throught the Accessorry Gear Box (AGB) – From 0 to 45% NH as a Starter – Above 61.5% as a Generator The ACW Generator is driven by the Reduction Gear Box, and is available when NP > 66%
DC Starter Generator
Accessory gear box
ACW Generator
Reduction gear box
In Hotel Mode or with the propeller feathered, there is no ACW. When the propeller is unfeathered (CL in AUTO /100% OVRD), The NP is maintained at a minimum of 70,8%, in order to have ACW (minimum 66%)
DC Starter Generator
Accessory gear box
ACW Generator
Reduction gear box
HOTEL MODE OR PROPELLER FEATHERED
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2. DC-AC schematic
ATA 24
2.1. Normal supply: On ground with battery only AC BUS 1
AC BUS 2
AC STBY BUS BAT INV 1
INV 2 ON
TRU
DC STBY BUS
DC EMER BUS
EMER BAT CHG
DC ESS BUS
HOT EMER BAT BUS
HOT MAIN BAT BUS
MAIN BAT CHG
DC/AC overhead panel
UTLY BUS 1
DC BUS 1
UTLY BUS 2
DC BUS 2
BTC DC SVCE BUS DC GEN 1
EXT. PWR
FAULT
AVAIL
GND HDLG BUS
DC GEN 2 FAULT
The GOUND HANDLING BUS is supplied only on ground, by 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 from the EXT PWR via the DC SVCE BUS – BAT ON with EXT PWR ON or with one GEN on line, the GND HDLG BUS is supplied by the from the DC BUS 1 via DC SVCE BUS.
NOTE: The GND HDLG BUS is disconnected when airborne.
ELEC SD page: on battery only
ELEC SD page: on battery + GPU available
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G. Electrical systems 2.2. Normal Supply: On ground with external power AC BUS 1
AC BUS 2
AC STBY BUS BAT INV 1
INV 2 ON
TRU
DC STBY BUS
DC EMER BUS
EMER BAT CHG
DC ESS BUS
HOT EMER BAT BUS
HOT MAIN BAT BUS
UTLY BUS 1
DC BUS 1
UTLY BUS 2
MAIN BAT CHG
DC BUS 2
DC/AC overhead panel BTC DC SVCE BUS DC GEN 1 FAULT
GND HDLG BUS
EXT. PWR
DC GEN 2
AVAIL
FAULT
ON
The BTC is closed and the GPU supplies all the DC and AC busses. Even if the GEN are available, the GPU has always priority.
ELEC SD page
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S y s t e m s 4 2/72 - 6 0 0 2.3. Hotel mode or DC GEN 1 FAULT AC BUS 1
AC BUS 2
AC STBY BUS BAT INV 1
INV 2 ON
TRU
DC STBY BUS
DC EMER BUS
EMER BAT CHG
DC ESS BUS
HOT EMER BAT BUS
HOT MAIN BAT BUS
UTLY BUS 1
DC BUS 1
UTLY BUS 2
MAIN BAT CHG
DC BUS 2
DC/AC overhead panel BTC DC SVCE BUS DC GEN 1
EXT. PWR
DC GEN 2
FAULT
GND HDLG BUS
The BTC is closed and the GEN 2 supplies 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.
ELEC SD page
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G. Electrical systems 2.4. Normal supply: with two generators on line AC BUS 1
AC BUS 2
AC STBY BUS BAT INV 1
INV 2 ON
TRU
DC STBY BUS
DC EMER BUS
EMER BAT CHG
DC ESS BUS
HOT EMER BAT BUS
HOT MAIN BAT BUS
UTLY BUS 1
DC BUS 1
UTLY BUS 2
MAIN BAT CHG
DC BUS 2
DC/AC overhead panel BTC DC SVCE BUS DC GEN 1
EXT. PWR
DC GEN 2
GND HDLG BUS
The BTC is opened and each GEN supply its respective busses. On ground the GND HDLG BUS is supplied by the DC BUS 1 through the DC SVCE BUS, and disconnected when airborne.
ELEC SD page
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S y s t e m s 4 2/72 - 6 0 0 2.5. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD AC BUS 1
AC BUS 2
AC STBY BUS BAT INV 1
INV 2 OVRD
The BAT toggle switch has to be selected to OVRD. The OVRD position ensures that busses are supplied by their respective battery by overriding all protections. This position is protected by a switch guard.
TRU
DC STBY BUS
DC EMER BUS
EMER BAT CHG
DC ESS BUS
HOT EMER BAT BUS
HOT MAIN BAT BUS
UTLY BUS 1
DC BUS 1
UTLY BUS 2
MAIN BAT CHG
DC BUS 2
BTC DC SVCE BUS DC GEN 1
EXT. PWR
FAULT
DC GEN 2 FAULT
DC/AC overhead panel
GND HDLG BUS
ELEC SD page
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G. Electrical systems 2.6. Emergency supply: In dual DC GEN LOSS with the battery toggle switch on OVRD and second OVRD selected AC BUS 1
AC BUS 2
AC STBY BUS
BAT INV 1
INV 2 OVRD
After a Dual DC GEN loss, the UNDV is triggered when the DC STBY BUS 18V WITH OVRD UND/V PB IN OVRD POS.
DC BUS ON
OVRD UNDV DC STBY BUS
DC STBY BUS VOLTAGE 18V WITH BAT TOGGLE P/B SW IN OVRD POSITION
Item
Display HOT BUS EMER BAT 28 V
HOT BUS
16
EMER BAT 28 V
DC MAIN BUS INVALID VOLTAGE OR 18V DC EMER BUS VALID VOLTAGE AND >18V WITH BAT TOGGLE P/B SW IN OVRD POSITION DC EMER BAT INVALID VOLTAGE OR 18V
XX V
DC EMER BAT VALID VOLTAGE AND >18V
EMER BAT
13
XX V
DC MAIN BAT VALID VOLTAGE AND 42 – 3 PBE ––> 72
ATA 26
PBE stowage box
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I. Fire protection FCOM 1.08
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S y s t e m s 4 2/72 - 6 0 0 The fire protection system provides detection, warning and extinguishing for each engine, cabin and lavatory.
1. Schematic
ATA 26
FIRE DETECTION
FIRE EXTINGUISHING SYSTEM
AND
LOOP 1A Bottle N°1
Bottle N°2
ENG 1 FIRE ENG 1 ENG 2
2. Avionics FWD and AFT smoke detection
ATA 26
FORWARD CARGO SMOKE DETECTION
AFT CARGO OR LAVATORY SMOKE DETECTION
AVIONICS COMPARTMENT SMOKE DETECTION
AIR CAUTION / FAN FAILURE
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I. Fire protection
3. Fire handle SQUIB TEST Electrical test of the squibs
ATA 26 LOOP FAULT: change in resistance, inhibits fire signal until turned off. LOOP 1A (1B, 2A, 2B) on FWS (DC emer)
AGENT 1 DISCH: Bottle depressurized. Opposite agent DISCH light will also illuminate on other fire panel. Bottle located in the wing fairing of the associated side
ENGINE FIRE HANDLE Pulled on the respective engine: – PROP: feather – FUEL: LP valve closed – AIR: BLEED and HP valve closed – DEICING: deice and shutoff valve closed – ELEC : DC and ACW gen. disconnected – SQUIBS armed lts illumination + Hydraulic to prop brake closed on engine 2 Agent 2 bottle located on the opposite side FIRE TEST MW + CRC + ENG 1 FIRE on FWS + fire handle illuminated + FUEL S/O light on CL (if out of FUEL S/O position)
AGENT SQUIB armed when T handle pulled. Discharges bottle. (DC EMER/HOT MAIN BAT)
FAULT TEST MC + SC + LOOP on FWS Fault lights in A/B loop pb
OFF takes respective loop out of parallel circuit. Allows other loop to activate fire signal alone.
4. EWD (Engine and Warning Display) Engine Fire detected by two loops. (Not detected if one loop fault. Detection recovered when the faulty loop is selected OFF) LOOP Engine fire loop FAULT. When a loop FAULT. No detection of Engine Fire (Detection recovered when the faulty loop is selected OFF) NAC OVHT RH Nacelle Overheat >170°C Alert on FWS
5. Condition levers fuel light
ATA 26
FUEL SO Illuminates red in case of fire signal from associated engine. Extinguishes after CL is set at fuel shut off position or if fire detection signal stops
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6. Compartment smoke panel
ATA 26 NORM one fan runs FAULT: the fan is out of order and illuminates amber + FWS is activated ALTN: The alternate fan runs, ALTN light illuminates cyan
SMK TEST Tests the smoke detectors operation
Normal operation Fan Fault associated with AIR AFT DET FAN on FWS
DET FANS ALTN DET FANS
Aft Fan Fault, selection of the alternate FAN
On SD CABIN
7. SD cabin Avionics smoke
Forward cargo smoke
Aft cargo compartment smoke Lavatory smoke
Aft compartment & lavatory Detection fans
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J. Flight control FCOM 1.09
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S y s t e m s 4 2/72 - 6 0 0
The elevators, ailerons and rudder are mechanically actuated The spoilers and flaps are hydraulically actuated.
1. Roll schematic
ATA 27
2. Pitch schematic
ATA 27
In case of jamming, pitch control will be recovered by disengaging the pitch coupling system (by applying a differential force of 52 daN).
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J. Flight control
3. Yaw schematic
ATA 27
4. Gust lock
ATA 27 GUST LOCK lever permits to lock mechanically the roll and pitch axes against wind gusts. The PL travel is limited to slightly above FI. 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 actuators is in disagreement with the gust lock position (lock or unlock position)
5. Stick Shaker/Stick Pusher push button and display
ATA 27
STICK SHAKER/PUSHER PB – FAULT light indicates a stick pusher or stick shaker failure – OFF position: enables to switch OFF the stick pusher and the stick shaker system STICK PUSHER illuminates to indicate that the stick pusher is operating
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6. Spoilers position indicator
ATA 27 SPOILERS position indicator When illuminated, each green light indicates that the associated spoiler is not in the fully retracted position (more than 2.5° aileron travel)
7. Pitch trim asym light
ATA 27 PITCH TRIM ASYM Amber labels are displayed to indicate a pitch tabs desynchronization greater than 0.7°
8. Trim position indicator
ATA 27 Pitch trim position indicates the right trim actuator controlled tab travel. A green sector identifies the take off range. If take off (or take off config test) is performed with pitch trim out of this range, CONFIG warning will be generated by the FWS.
Roll trim position indicates the LH aileron trim controlled tab travel
Yaw trim position indicates units of trim motor displacement
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J. Flight control
AP engaged
Manual mode Associated to: PITCH TRIM ASYM on FWS Or PITCH MISTRIM or AP PITCH TRIM FAIL with AP engaged, on FMA and FWS Or Pointer outside of green band in pre take off condition (Take off CONFIG)
AP engaged Yaw Damper engaged (Yaw Auto Trim active)
Manual mode Associated to: RETRIM ROLL L(R) WING DN In case of roll retrim with AP engaged The cyan arrow indicates the side to retrim The trim is inhibited on the other side. Associated to: AILERON MISTRIM On FMA The cyan arrow indicates the side to retrim The trim is inhibited on the other side
9. Trim controls
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. The Yaw TRIM manual control is inhibited when the autopilot is engaged (Yaw autotrim) When the autopilot is engaged, the “RUDDER MISTRIM” message can be triggered on FMA.
Manual mode Yaw Damper off (no Yaw Auto Trim) Associated to: RUDDER MISTRIM on FMA Or YAW AUTOTRIM FAIL on FWS The cyan arrow indicates the side to retrim
ATA 27 Roll TRIM control SW controls the roll trim actuator. For operation, both sws must be moved and held in the same direction (L WING DN or R WING DN) to energize the system (safety reasons). The roll trim is inhibited during autopilot operation. When the autopilot is engaged, the “RETRIM ROLL R(L) WING DOWN” or “AILERON MISTRIM” messages can be triggered on the FMA. These messages authorize to retrim on the dedicated side. The other side is still inhibited STBY PITCH control SW is a guarded sw which controls the electrical motors of each trim actuator. Action on this switch will disengage the autopilot.
Pitch trim rocker two switches installed on each control wheel. It is necessary to operate both rocker switches to activate the normal electrical motor of each trim actuator and to control nose up or down. The switches are spring loaded to neutral position. An aural whooler is generated by the FWS if trim is used for more than 1 second. Action on this switch will disengage the autopilot.
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10. Flaps schematic
11. Flaps position indicator F L A P
F L A P
ATA 27
Flaps retracted SEL
0°
ATA 27
Flaps retracted SEL
0° Flaps extension toward 15°
SEL 15° Flaps extended at 15° SEL 15°
SEL 15°
Flaps jam or asym, associated to or on FWS Flaps unlock, associated to
SEL 15°
on FWS
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J. Flight control
12. Flaps control lever
ATA 27
FLAPS control lever controls the flaps operation. Distinct positions correspond to flaps 0°, 15°, 30° (72-600) or 25°, 35° (42-600)
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K. Flight instruments FCOM 1.10
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1. Schematic
ATA 31
The Avionics Full DupleX switched ethernet (AFDX) allows transmission of data in all directions between the CAC 1&2 and the DUs. The AFDX is controlled by the SWM’s (Module of the CAC). The SWM (Gateway and Switch module) is connecting together CPM (Core Processing Module) and other Avionics Data Network subscribers. SWM external interface mainly consists of: AFDX with the 5 Display Units, AFDX with the CPM, AFDX interconnection between the 2 SWM, Ethernet with dataloading Port. AFCS (Auto Flight Control System) is managed by the two Auto Flight Control Application (AFCA) of the CACs. The AFCAs receives data from the two ADC, two AHRS and aircraft equipments as navigation and some sensors.The AFCAs receives data from the two FMS (Flight Management Application: DU 2 & 4). The AFCS generates commands to flight control actuators and to the FD bars. AHRS (Attitude and Heading Reference System) comprises: (1) An AHRU (Attitude and Heading Reference Unit) which integrates inertial components, to compute the gyro-heading, the attitude, acceleration and the vertical speed. (2) A Removable Memory Module to store compensation parameters (3) A flux valve which detects the direction of the earth’s magnetic field line. The AHRS gyro-magnetic heading computation automatically updates the heading value with the magnetic heading of the flux valve. ADC (Air Data Computers) is supplied with static air pressure (static ports), total air pressure (pitot ports), total air temperature (TAT probe). With these inputs, the ADC computes pressure altitude, IAS, TAS, TAT, SAT. DU (Display Unit): – Collects all the data, coming from the AFDX (CAC 1 & 2), from Arinc 429 (control panels, CACs, aircraft equipments), from discrete lines – Converts the data in video format, through the FDA (Flight Display Application). NOTES: The FMA (Flight Management Application) and RMA (Radio Management Apllication) are part of the DU 2 & 4 Each DU can display three different formats: the Primary Flight Display (PFD), the Multi Function Display (MFD), the Engine and Warning Display (EWD)
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K. Flight instruments
2. PFD (Primary Flight Display) ROLL ATTITUDE scale 0 , 10, 20, 30, 45 and 60° Lateral ARM, CAPTURE✶ and HOLD mode
Bank angle limit: two green ticks
Flight Mode Annunciator (FMA)
ATA 31 Vertical ARM, CAPTURE✶ and HOLD mode
SLIP indicator
Horizon and pitch scale is white and has reference marks every 2.5° up to 20° up or down, then marks at 25, 30, 50, 80°.
FLIGHT DIRECTOR command bars (green)
Vertical deviation indication
RADIO ALTITUDE indication
VSI (Vertical Speed Indicator)
Altimeter: altitude tape
Lateral deviation indication
TCAS and Transponder annunciator
DH indication
Indication of True Air Speed, Ground Speed, and wind
Airspeed indicator: Speed tape
EHSI (Electronic Horizontal Situation Indicator). The EHSI can be replaced by a mini ND (Navigation Display) when the the ND is replaced by an other format on the MFD.
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3. MFD (Multi Function Display)
ATA 31
MFD upper window
Memo panel display VCP (Virtual Control Panel Window)
MFD upper window selection
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K. Flight instruments
4. EWD (Engine and Warning Display) ATA 31
Trim indicator
Primary engine display
Brake messages Test status
Permanent Data
Flap indicator
Alert window
Procedure window
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5. ND - ARC MODE with terrain or weather radar information
TERRAIN
6. Source failure alert
DU total loss
AHRS failure
ATA 31
WEATHER RADAR
ATA 31
FAIL A fatal failure has been detected by DU software or by the hardware
ADC failure
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K. Flight instruments
7. Switching panel
ATA 34
ATT/HDG pb enables to use AHRS 2 information. When captain pb is depressed SYS 2 illuminates white on CAPT pb, CAPT 2 illuminates green on F/O pb
DISPLAY pb In normal conditions, enables to cycle the three formats on DU 2 (capt switching), on DU 4 (F/O switching). In case of failure of any DU (DU 1 or 2 on capt side or DU 4 or 5 on F/O side) enables to cycle the three formats on the remaining DU
ADC pb enables to use ADC 2 information. When captain pb is depressed SYS 2 illuminates white on CAPT pb, CAPT 2 illuminates green on F/O pb
8. EFCP (control panel) MFD PERF page: The performance page can be displayed, by pressing on the PERF push button.
MFD ND page: Three different ND format can be displayed on the MFD, by pressing on the ND push button, and then by selecting the format on the FORMAT rotary knob.
MFD SYS page: Four different system pages can be displayed on the MFD, by pressing the SYS push button consecutively.
BRG1(2)push button: By pressing it, VOR1(2) or ADF1(2) or no indication is displayed.
RANGE “+/–” push button: By pressing it, the range of the Navigation Display page is increased /decreased.
ATA 31
MFD VID page: In provision for video display
FORMAT rotary knob: By turning it, the format of the ND is changed. RCL PB A first push enables to display in the Alert Window the alert messages previously cleared but still detected. A second push scrolls down the alert messages list in case of overflow in the alert window.
MAN DEL By pressing on it, procedures inserted manually are deleted
MFD MISC page: Engine run up page
MFD MAP page: Airport map page (option)
Procedure control pb: Allows to move on upward/downward line in the procedure window and to validate actions
CLR PB By pressing on it, a clearable alert displayed on the Alert Window is cleared. PROC MENU By pressing on it, procedure menu is displayed in the procedure window.
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9. MCP (Multipurpose Control Panel)
ATA 31
Multi directionnal pad To move the cursor for choosing a selection area COM P/B Selection on VCP – VHF – HF 1 (if installed) – HF 2 (if installed)
Enter P/B To validate the selection area
NAV P/B Selection on VCP – VOR – ADF – ND OVLY (ND Overlay)
SURV P/B (surveillance) Selection on VCP – XPDR – TCAS
ESC P/B (Escape) Before validation, the escape P/B allows to recover the previous value
Numeric Key Board Allows setting the frequency or transponder code.
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K. Flight instruments
10. Weather radar control
ATA 34
Primus 660
GAIN setting to set receiving amplification
MODE selector OFF radar is off STBY radar is on but no pulse is sent by the antenna TEST range at 100 NM, 3 arcs green, yellow and red WX normal operating position, intensity of weather obstacles is displayed by different colors (black: no cloud; green: normal cloud; yellow: dense; red: severe storm) G MAP enables to display ground obstacles (black, pale blue, yellow, magenta)
RCT pb activates Rain Echo Attenuation Compensation technique function and permits display with more accurracy the weather situation behind storms
TGT pb activates target alert
SECT pb Used to select either the normal 12 looks/minute 120° sector scan or the faster update 24 looks/ minute 60° sector scan
TILT control to adjust radar antenna in pitch axis from 15° down to 15° up
Turns the pitch and roll stability on and off. When selected off, an amber legend illuminates above the pushbutton
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11. TAT/SAT indicator
ATA 34 TAT indicator indicates total air temperature SAT indicator indicates static air temperature
TAS indicator indicates true air speed
12. CLOCK
MODE P/B By pressing the MODE pushbutton, six annunciators (DT, GPS, INT, LT, ET and CHR) indicate which mode is selected (the functions INT, LOC and DT are available in succession, ET and CHR functions are controlled by the ET and CHR buttons respectively, the GPS is automatically selected when GPS is valid). Chronometer (CHR) P/B – START: Display is active and the chronometer starts incrementing – STOP: The value displayed at the instant the push-button was depressed is held as long as no action occurs on this push button. – RESET: the LCD display is zeroed and blanked.
ATA 31
Elapsed time (ET) P/B – When selecting the ET push button, the ET display comes on. – When the elapsed time counter is stopped, by pressing the ET push button for more than two seconds the display is blanked and value is zeroed. For the time set, the ET P/B is used to decrease the digits (-)
TEST P/B For the time set, the TEST P/B is used to increase the digits (+)
Six digits display of either: – Universal Time Coordinated (from GPS or internal time) – Date: MONTH / DAY / YEAR – Local Time
Four digits display of either: – ELAPSED TIME (ET) – CHRONOMETER TIME (CHR)
ELAPSED TIME When depressed ON the flight time starts automatically when airborne
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K. Flight instruments
13. RCDR panel
ATA 31
RCDR pb when depressed, both cockpit voice recorder and digital flight data recorder are energized (manual mode). ON lt illuminates cyan RESET pb when depressed, inhibits recording in the manual mode
14. STBY instruments
ATA 34
STANBY COMPASS STANDBY COMPASS Hidden in up position. Compass control should be placed on DN for use. The compass rose is graduated in 10 degrees increments
IESI: Integrated Electronic Standby Instrument Menu P/B Enable sub function selection menu
STD P/B Reset at 1013.25Hpa, when pushed more than 0.2 sec.
LATERAL ACCELERATION INDEX indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index.
STANDBY AIRSPEED INDICATOR The actual airspeed is given in a T shaped window positioned in the center of the white moving speed tape on the left of the IESI.
Brightness
STANDBY HORIZON – The pitch scale has markers every 2.5 degrees up to ±20°. If pitch exceeds ±25° degrees large red chevron will indicate excessive attitude and direction to follow to resume normal attitude. – The roll scale has markers are set at 10, 20, 30, 45, 60 degrees of bank.
SEL P/B – Change cursor selection between VHF COM, VHF NAV, BARO SETTING and COURSE when VOR mode. – Used to validate manual entry.
SET ROTARY SWITCH – Sub fonction menu scroller – Baro setting – VHF com tuning – VHF nav tuning – Course setting in VOR mode
STANDBY ALTIMETER The altitude indication is given in a rectangular window positioned in the center of the white moving altitude tape on the right of the IESI. Altitude in meters can also be displayed on the IESI underneath the altitude tape. The barometric reference is displayed in cyan. It corresponds to either the selected barometric pressure or the standard pressure.
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15. Airspeed indicator
ATA 34
VmLB0 (icing condition)
Speed bug read out Speed trend Predicted airspeed in 10s
VmLB0 (normal condition) Maximum speed Vmo/Mmo or Vfe or Vle or Vtlu
Flaps retraction speed
Speed bug –Automatic speed bug (Magenta) managed by the FMS. –Manual speed bug (Cyan) selected on the ICP.
VminOPS Upper amber limit VPROT Upper red limit Activation of the stick shaker
V1, VR and V2 (Cyan) Actual IAS
Before rotation
Initial climb
Cruise
Flaps extension speed (VFE NEXT) VmHB15 normal (white line) VmHB15 icing (amber line) Flaps retraction speed Vref VmHB30 or Vmcl whichever is higher
Approach Flaps 15°
Approach Flaps 30°
The speed bug is controlled by the ICP (Index Control Panel)
Speed target selection Selection of the speed bug between: – AUTO: Speed bug managed by the FMS
Speed knob Used to set the speed bug In MAN mode
– MAN: Speed bug set manually by the speed knob
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K. Flight instruments
16. Altimeter
ATA 34
Selected Altitude ALT SEL
Current altitude or FL
ALTITUDE ALERT An amber frame is flashing (± 1000ft) then a yellow frame is steady (± 250ft)
DA / MDA
Landing Elevation Barometric setting in Hpa and InHG
Barometric setting knob The knob is used to set the barometric reference. Pushing the knob sets standard barometric reference (29.92 INHG / 1013.25 Hpa)
DH / MDA knob Outer knob permits to select between DH (Decision Height) or MDA (Minimum Descent Altitude). Inner knob is used to set DH or MDA values, depending of the outer knob position.
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17. Vertical speed indicator and TCAS ATA 34 VS target readout Set by the FGCP Pitch Wheel (PW)
VS digital readout
VS scale
VERTICAL SPEED INDICATOR based on both inertial (AHRS) and barometric data (ADC).
VS pointer
VS target Set by the FGCP Pitch Wheel (PW)
Above (+) or Below (–) separation height descending or climbing Open diamond Other traffic
Solid diamond Proximate traffic (PA) traffic within ± 1200 ft and 6 NM Solid circle Traffic Advisory (TA) Traffic in caution area 20 to 48s before collision area Solid cube Resolution Advisory (RA) Traffic in warning area 15 to 35s before collision area
TCAS Status
Resolution Advisory (RA) vertical rates to be avoided.
RANGE RING 2.5NM around the A/C
AIRCRAFT own aircraft symbol
TCAS no bearing advisory: In case the bearing of the TA or RA intruder is not available, a message provides an indication on the two most dangerous RA or TA intruders
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L. Fuel system FCOM 1.11
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1. Schematic
ATA 28
The fuel is stored in two tanks, one in each wing. Each tank is fitted with: – a vent surge tank to ensure positive pressure and allows a thermal expansion without spillage – a main wing tank – a feeder tank, always full to protect the engine feed system against negative or lateral load factors Total quantity 4500 kg
ATR 42
Refueling panel Refueling point
Gravity filling cap Access door
Main wing tank
Vent surge tank (100 l)
Main wing tank
Feeder tank (200 l / 160 kg)
Vent surge tank
Total quantity 5000 kg
ATR 72
Refueling panel Gravity filling cap Access door
Main wing tank
Refueling point Vent surge tank (100 l)
Main wing tank
Feeder tank (200 l / 160 kg)
Vent surge tank
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L. Fuel system
2. Electrical fuel pump OFF
ATA 28
ENGINE 1 HMU FWS
FCOC FEED LO PR MOTIVE FLOW VALVE
LP VALVE
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP
MEMO PANEL DISPLAY L TANK
FEEDER COMPARTMENT
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3. Starting procedure
ATA 28
ENGINE 1 HMU FWS
FCOC FEED LO PR MOTIVE FLOW VALVE
LP VALVE
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP MEMO PANEL DISPLAY
L TANK
FEEDER COMPARTMENT
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 in the pipe. At the same time, the feeder jet pump is activated by the electrical pump output pressure, to supply and maintain the feeder tank full.
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L. Fuel system
4. Normal procedure
ATA 28
ENGINE 1 HMU FWS
FCOC FEED LO PR MOTIVE FLOW VALVE
LP VALVE
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP
P >8.5 PSI + 30s MEMO PANEL DISPLAY L TANK
FEEDER COMPARTMENT
ENGINE RUNNING / NORMAL OPERATION OF THE FUEL SYSTEM After engine start, the flow, from return line of the HMU, opens the Motive Flow 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 the electrical pump is de-energized. Conditions to energize the electrical pump (See details on pages hereafter) – Cross feed operation – Engine Feed Jet Pump outlet pressure drops below 5 psi – Low Level
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5. Cross feed procedure
ATA 28
ENGINE 1 HMU FWS
FCOC FEED LO PR MOTIVE FLOW VALVE
LP VALVE
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP
MEMO PANEL DISPLAY L TANK
FEEDER COMPARTMENT
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.
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L. Fuel system CROSS FEED PROCEDURE CONT’D ENGINE 1 HMU FWS
FCOC FEED LO PR MOTIVE FLOW VALVE
LP VALVE
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP
MEMO PANEL DISPLAY L TANK
FEEDER COMPARTMENT
By selecting OFF the corresponding PUMP push button, the electrical pump is de-energized and the motive flow valve is supplied to close. The engine is fed from the opposite tank.
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6. Engine feed jet pump low pressure ATA 28 ENGINE 1 HMU FWS
FCOC FEED LO PR MOTIVE FLOW VALVE
LP VALVE
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP
P < 5 PSI MEMO PANEL DISPLAY L TANK
FEEDER COMPARTMENT
In the event of engine feed jet pump failure, the pressure switch ( 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 feeder tank through the flappers.
LO LVL with FQI 160kg (feeder tank not full)
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8. Engine fire procedure
ATA 28
ENGINE 1 HMU FWS
FCOC
P < 4 PSI MOTIVE FLOW VALVE
LP VALVE
FEED LO PR
ENGINE 1 FIRE PULL
R TANK CROSSFEED VALVE PUMP RUN OFF FEEDER JET PUMP
ELECTRO PUMP
ENGINE FEED JET PUMP
P > 600 mbar MEMO PANEL DISPLAY L TANK
FEEDER COMPARTMENT
In case of engine fire, when corresponding engine fire handle is pulled, it closes associated LP shut off valve.
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L. Fuel system
9. Fuel panel
ATA 28 XFEED valve Activates both elect fuel pumps.
FEED LO PR Delivery pressure < 4 PSI. Pump failure or fuel starvation. FWS.
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 pump failure) – during fuel quantity test
FLOW BAR Shows position of valve. No bar: valve fault or moving.
RUN illuminates green when elec fuel pump is running.
10. SD Engine
ATA 31
FUEL TEMPERATURE in °C
Fuel Xfeed valve Fuel Xfeed valve open
Fuel LP valve
OFF
Electrical pump OFF
Fuel LP valve open
XFEED
XFEED
Fuel Xfeed valve closing or opening
Fuel Xfeed valve closed
RUN
Electrical pump ON and the pump is running
Fuel LP valve closing or opening
Electrical pump ON and the pump is not running
Fuel LP valve closed
XFEED Fuel Xfeed valve not closed or not open after XFEED 3s
Electrical pump OFF and the pump is running
Fuel LP valve not closed or not open after 3s
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11. Fuel QTY indication
Fuel used
ATA 28
Fuel On Board (FMS computed)
Fuel quantity indication If >160 kg If 50 kg If OVERHEAT – If not ––> UNDERPRESSURE
In case of overheat, the ENG P/B is deselected, the AFR AIR BLEED is selected again to isolate the affected engine.
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N. Ice and rain protection
8. Anti-icing & de-icing panel PROP ACW supply. Inhibited below NP 63%
HORNS ACW supply. Inhibited on ground. Either horn activates AOA Lt
FAULT power loss on at least 1 blade. A-ICING PROP 1 (2) on FWS
DE ICING air is always available regardless of bleed pb. NORM: 60’’ / cycle SLOW: 240’’ / cycle
MODE SEL AUTO Automatic selection of cycle depending on ADC1/2 to MFC1B/2B FAULT when ADC or MFC fail: Fast mode is automatically selected for ENG and AIRFRAME DEICING and High Power for PROP ANTI-ICE. A-ICING AUTO on FWS. MAN: manual selection of cycles depending on SAT
FAULT both MFC modules have failed to control boots cycles. The monitoring is preformed by the stby controller. A-ICING SEL on FWS AFR AIR BLEED OVRD: no MFC. Boots inflated by separate stantby controller (cycle 60’’)
ENG FAULT: distribution valve opened but no air pressure. OR valve closed and pressure detected OR AFR AIR BLEED off and air temp above deice valve >230°C for more than 6’’. A-ICING ENG 1 ( 2) on FWS
MODE SEL ENG AND AIRFRAME SLOW: 240’’/cycle FAST: 60’’/cycle
HORNS FAULT Power loss. A-ICING HORNS 1 (2) on FWS SIDE WINDOWS Defog only. FAULT for power loss. A-ICING WINDOWS on FWS. (DC BUS)
MODE SEL PROP NORM: 10’’ on per 3 blades; then 10’’ off between cycles. ON (HIGH POWER): 20’’ on per 3 blades. No stop between cycles.
ENG ON: signal sent to MFC to start deice cycle on the engine air intake, deice valve opened even if AFR AIR BLEED off
ATA 30
AIR FRAME FAULT: valve opened but no downstream pressure. Or valve closed and downstream pressure detected. A-ICING FRAME on FWS
AIR FRAME ON: signal sent to MFC to start deice cycle on the airframe AFR AIR BLEED FAULT: air dowstream deice valve < 14 psi more than 10’’ OR Air upstream of the deice valve > 230°C. A-ICING BLEED on FWS
9. De-icing/anti-icing indication (memo panel display)
OFF : isol valves closed. Deice valves closed unless ENG 1 / 2 deice on.
ATA 30
CYAN When selected ON AMBER When FAULT
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O. Landing gear FCOM 1.14
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1. Landing gear description
ATA 32
The landing gear is hydraulically operated. In case of hydraulic failure, it may be extended by gravity.
LANDING GEAR CONTROL
STEERING HANDWHEEL
2. Brakes schematic
EMERGENCY / PARKING BRAKE HANDLE
ATA 32
PILOT BRAKE PEDALS
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O. Landing gear
3. LDG GEAR position indicators
ATA 32
System 2 UNLK gear not locked in selected position or (on GND) uplock box not opened. Green Lt down lock engaged
System 1 UNLK gear not locked in selected position or (on GND) uplock box not opened. Green Lt down lock engaged.
4. Landing gear handles
GEAR HANDLE RED LIGHT any gear not sensed down and locked with some conditions. FWS.
LDG GEAR EMERGENCY EXTENSION HANDLE permits to unlock the landing gear
5. Brakes temperature and antiskid BRK TEMP WHEELS BRK HOT on FWS for any brake T° >160°C (42) T° >150°C (72)
ATA 32
ANTISKID Operative if speed > 10 kts. Activates when speed > 23 kts + 50% diff between wheels (locked wheel protection). Braking action inhibited at touchdown as long as wheel spin up speed < 35 kts or 5 sec. (touchdown protection). CAUTION: THE TEST INHIBITS BRAKES
OFF Pb released, system deactivated
TEST pb (inhibited if speed > 17 kts) = MC + SC+ FWS.
ATA 32
Test duration Test duration in flight on ground 3 sec. +
6 sec. +
17 sec.
14 sec.
F (FAULT) wheel channel failure + WHEELS A-SKID on FWS
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6. Emergency parking brake handle EMERGENCY BRAKE HANDLE permits to apply a metered pressure. The brake accumulator allows at least six braking applications without any antiskid operation if the blue hydraulic system is not available (Springloaded to the off position)
7. Steering handwheel N/W STEERING SW activates or deactivates the nose wheel steering system (guarded type in the ON position) OFF: unpressurizes the steering system (91° of deflection)
ATA 32 PARKING BRAKE permits a full pressure on the brakes. When brake handle is not in the fully released position, amber PRKG BRK caution light is displayed on FWS and is taken into account by the T/O CONFIG. (Springloaded to the off position)
ATA 32 THE STEERING HAND WHEEL controls the nose wheel angle up to 60° in either direction: – clockwise: steering to the right – counter clockwise: steering to the left
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P. Navigation system FCOM 1.15
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1. Nav control
ATA 34 VCP
MCDU
MCP
MCP and MCDU allow: – to tune VOR/ILS/DME frequencies – to set tune mode (AUTO/ MAN) – to do DME HOLD In AUTO tuning, the NAV source has to be on FMS (Inhibited on V/ILS)
2. Marker sensibility setting
ATA 34 MCDU
MCDU allows to set MKR sensibility (LO/HI position)
3. ADF control
ATA 34 VCP
MCDU
MCP
MCP and MCDU allow: – to tune ADF frequencies – to set mode (ADF/ANT) – to set tone (OFF/ON)
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P. Navigation system
4. TAWS alert modes
ATA 34
The Terrain Awareness Warning System provides visual and aural alerts in case of dangerous flight path conditions which would result inadvertent ground contact if maintained. The TAWS performs the following alert modes: – Reactive warning modes * Mode 1: excessive descent rate * Mode 2: excessive terrain closure rate * Mode 3: altitude loss after take-off * Mode 4: unsafe terrain clearance * Mode 5: below glideslope * Mode 6: altitude callouts – Predictive warning modes: * Terrain Caution and Warning * Obstacle Caution and Warning
MODE 1 excessive descent rate
MODE 2 excessive terrain closure rate
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MODE 3 altitude loss after take-off
MODE 4 unsafe terrain clearance
MODE 5 below glideslope
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P. Navigation system
MODE 6 altitude callouts
TERRAIN CLEARANCE FLOOR (TCF)
The Terrain Clearance Floor (TCF) mode creates an increasing terrain clearance envelope around the airport runway directly related to the distance from the runway.
Runway Field Clearance Floor (RFCF)
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TERRAIN AND OBSTACLE AWARENESS
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.
The terrain advisory line is drawn along the points where a terrain caution alert will occur if the aircraft continues along its current trajectory.
“TERRAIN AHEAD” or “OBSTACLE AHEAD”
When a terrain caution or warning occurs, the terrain advisory line is removed from the display and the terrain display is changed to identify the terrain that caused the alert.
“TERRAIN AHEAD, PULL UP” Or “OBSTACLE AHEAD PULL UP”
The Pull-Up Warning is generated as long as the current aircraft trajectory will not safely clear the terrain, and the aircraft performances are able to clear the terrain in climb
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P. Navigation system
“AVOID TERRAIN”
The Pull-Up maneuver will not allow for a safe clearance with terrain, and the crew has to immediately initiate an appropriate vertical and turning escape maneuver in order to avoid terrain
5. TAWS pb
ATA 34
6. TAWS panel
ATA 34 TAWS selector is guarded in the norm position. FLAP OVRD mode 4 alert caused by flap extension is inhibited to avoid nuisance in case of reduced flaps landing
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7. ND OVERLAY
ATA 31
The MCP allows to set ND OVLY – Traffic – Weather radar – Terrain – Navaid – Airport
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P. Navigation system
8. FMS
ATA 34
The dual THALES Flight Management System (FMS) installed on ATR 72/42-600 aircraft is composed of two identical sets of software applications, called FMS1 and FMS2. Each FMS is hosted within the DU2 and DU4, normally used with the MFD format.This dual FMS is built on dual cockpit system architecture. It is used to be normally handled with both FMS, synchronized by the cross talk function.
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Q. Power plant FCOM 1.16
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1. Engine schematic
ATA 61/72
Aircraft fitted with – two Pratt &Whitney, PW 127 M (72-600/42-600) – 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 drives the accessory gear box (AGB) – The shaft of the LP spool composed of the LP turbine and the LP compressor (rotation speed of the LP spool: NL) – The Power shaft composed of 2 power turbines (Free turbines). This 2 power turbines drive the propeller through the reduction gear box (RGB) (rotation speed of the propeller NP)
REDUCTION GEAR BOX These equipments are fitted on the RGB – the ACW generator – the Propeller Valve Module (PVM) – the propeller pump (HP) and overspeed governor – the auxiliary feathering pump – the propeller brake (on RH engine only)
HIGH PRESSURE COMPRESSOR centrifugal type
LOW PRESSURE COMPRESSOR centrifugal type
HIGH PRESSURE TURBINE
POWER TURBINE
ACCESSORY GEAR BOX driven by the HP spool. Drives – the DC starter/generator – the HP fuel pump – the engine oil pumps
DIFFUSER PIPES
ANNULAR COMBUSTION CHAMBER
LOW PRESSURE TURBINE
6 blades propeller
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Q. Power plant
2. Power and propeller controls
ATA 61/72
The different powers ratings for the engine are: (SHP: Shaft Horse Power) – RTO (Reserve Take Off) (maximum power) Used in case of an engine flame out during take off (up trim) or in case of go around (ramp) – MCT (Maximum continuous) – TO (Take Off 0,9 RTO) – Climb – Cruise
72-600 2750 SHP
42-600 2400 SHP
2500 SHP 2475 SHP 2192 SHP 2132 SHP
2400 SHP 2160 SHP 2160 SHP 2132 SHP
Power (PWR) = Torque (TQ) x NP For the same power: If TQ increases, NP decreases If TQ decreases, NP increases Power setting is characterized by constant power lever (PL) 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 position: PWR MGT in – TO: – MCT – CLB – CRZ
→ NP 100% and 0,9 RTO → TQ up to 90% → NP 100% and TQ up to 90,9% (72-600) → NP 100% and TQ up to 100% (42-600) → NP 82% and TQ up to 97% (72-600) → NP 82% and TQ up to 109,7% (42-600) → NP 82% and TQ up to 94,5% (72-600) → NP 82% and TQ up to 108,3% (42-600)
Reversion in manual mode when EEC FAULT (green band 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
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Q. Power plant – The PWR MGT has four positions: TO, MCT, CLB, CRZ – Considering that CLs are in AUTO and the PLs are in the notch, the control system delivers max rated power corresponding to the mode selected (the max rated power is delivered only when the engine is not thermodynamically limited)
ATR 72-600 NORMAL OPERATION, EEC ON, ISA CONDITIONS SHP
115% TQ
A
102% TQ 100% TQ
RTO (UP TRIM)
2750 2500 2475 2192 2132
MCT OR TO
B
TO 90% TQ
C
D
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.
100% Np 100% Np
MCT 90.9% TQ
RAMP
100% Np
WALL
NOTCH
0
50
67
81
100
POWER LEVER ANGLE
– TO – MCT – CLB – CRZ
PWR = 2475 SHP PWR = 2500 SHP PWR = 2192 SHP PWR = 2132 SHP
NP=100% NP=100% NP=82% NP=82%
TQ = 90% TQ = 90,9% TQ = 97% TQ = 94,5%
The RTO (Reserve Take-Off) is obtained in case of up trim (one engine out during take off) or with the PL to the ramp – RTO
PWR = 2750 SHP
ATR 42-600
NP=100%
TQ = 100%
NORMAL OPERATION, EEC ON, ISA CONDITIONS SHP
115% TQ
A 2400
MCT OR TO
2160
102% TQ 100% TQ
RTO (UP TRIM)
B
90% TQ
100% Np 100% Np
C
2132
LINE A: One engine out operation LINE B: Normal TO or MCT LINE C: CRZ NOTE: Sensible sector designed to allow for fix throttle engine control.
RAMP
WALL
NOTCH
0
– TO – MCT – CLB – CRZ
PWR = 2160 SHP PWR = 2400 SHP PWR = 2160 SHP PWR = 2132 SHP
50
NP=100% NP=100% NP=82% NP=82%
67
TQ = 90% TQ = 100% TQ = 109,7% TQ = 108,3%
81
100
POWER LEVER ANGLE
The RTO (Reserve Take-Off) is obtained in case of up trim (one engine out during take off) or with the PL to the ramp – RTO
PWR = 2400 SHP
NP=100%
TQ = 100%
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3. Engine indication
ATA 31
Power Management selection Analogic indication
RTO Torque at TO Objective TQ in MCT CLB CRZ
UPTRIM
ATPCS uptrim activation
GO Around Torque
91.1 102 .5 125 .6 --- . HBV L AB
Normal
LO PITCH LO PITCH NO REV
Lo Pitch Normal operation on ground
Abnormal Over-limit Invalid numeric torque HBV failure Discrepancy between EEC and aircraft configuration
Lo Pitch Abnormal operation in flight No Lo Pitch on ground with PL below FI
Lost of propeller control by one PEC channel
AUTO FTR
Auto Feather activation
Propeller brake is applied
Red line for “S”: limit during engine start
Red line for “H”: limit during Hotel Mode
---.-
NP %
---.-
NP information
90 . 0 110 .0 122 . 0 --- . -
Normal operation Abnormal operation Red limit NP invalid signal
500
800 --- . -
999
ITT numeric counter ITT invalid signal
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Q. Power plant
60
Normal
19.5
Normal transient range
81.0
Normal operating range
0
90
60 0
137
Amber exceedance
60 104.0
Amber exceedance range
110.0
Red limit
---.-
Invalid data
0 60
–35 0
60
Red limit 190 0
100.0 105 164 .0 --- . -
---.-
Normal 31
63
Normal operating range Amber exceedance range Red limit Invalid data
NL %
---.-
NL information Amber exceedance
Red limit
KG/H or LBS/H
100
LAB FUEL Invalid data –– –
1+2
394 --- L AB
START
Start in progress
START
Fault occurs during a start sequence
START
Start invalid signal
X START FAIL Cross start failed flag X START FAIL Cross start failed invalid signal
FLOW KG/H 12.0
KG/MN
The fuel quantity consumed by two engines/minute Fuel flow unit is set to KG/MN or LBS/MN
90 .0 110. 0 122. 0 --- . -
Normal operation Abnormal operation Red limit NL invalid signal
Fuel CLOG when ∆PSI>25 PSI. Filter blocked and by-passed when ∆PSI>45 PSI
Normal indication Invalid data Unit or type discrepancy
500
800 --- . -
999
ITT numeric counter ITT invalid signal
IGN ITT is displayed only during start sequence
Red line for “S”: limit during engine start
Red line for “H”: limit during Hotel Mode
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4. ENG START panel CRANK dry motoring (no ignition)
ON starter engaged. At 45% NH, light goes off and the starter is disconnected
START A OR B on ground, only exciter A or B is supllied (except for the position A&B) In flight regardless of start selection (A, B or A+B) both exciters are energized
UNLOCK PROP BRAKE not fully locked or not fully released. After 15 sec: FWS alarm. Also used to check lock/unlock time: – 5 sec. to unlock – 10 sec. to lock
ATA 61/72 FAULT Illuminates when: – remains ON with NH >45% or – GCU failure during start or – starter failure or – ENG 2 only: ENG START selector on start position + PROP BRK ON + GUST lock not engaged ON Continuous ignition (both A & B). Memo panel light.
42/72 PEC
READY engagement or disengag. conditions are met: – A/C on ground – gust 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
5. ENG control panel ARMING CONDITIONS PWR MGT sel on TO +ATPCS pb in +both PL > 49° +both TQ > 46% (72) and > 53% (42) = (arm green LT illuminated)
ATPCS – ARM on ground = uptrim + auto FTR (2.15’’ delay) – ARM in flight (In case of go around) = auto FTR only
ATA 61/72 TRIGGER one TQ below 18% Cancel: PWR MGT out of TO or ATPCS pb OFF or at least one PL retarded below 49° or both TQ 2.5° aileron travel. Lt ON=Spoiler not fully retracted (BLUE HYD PWR). Light on when SW TEST depressed and all door microsws opened. (Passengers and service doors opened) At least 1 microsw is opened. (DC BUS 2) Tests continuity of microsw. System (on ground, doors opened). Fuel delivery pressure below 4 PSI. Pump failure or fuel starvation. FWS.
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 EWD and FWS +Fire handle illuminated +FUEL S/O Lt on CL (if out of Fuel S/O position) Fault test MC+SC+ loop on FWS FAULT Lts on A/B Loop pb. OFF Takes respective loop out of parallel circuit. Allows other loop to activate fire signal.
The opening of the cargo door control panel cover. Self Test of MFC 1A/2A. FAULT Malfunction or electrical supply fault: AUTO disengagement – FWS
Gear position secondary system as sensed by MFC 2. UNLK gear not in selected position or uplock not opened (on Gnd) Green Lt down lock engaged
Controls XFEED valve. Activates both elect fuel pumps. Controls elect pump power supply and jet pump motive flow valve. Runs automatically if: Jet pump press 92°C. FWS. Pack valve will not auto close. MAN Compt temp knob controls directly temp control valve. Selects the zone where T° check is desired. PACK VALVE Spring loaded closed. Must have air pressure and select power to open (6 sec delay on RH pack for pax comfort). FAULT pack valve disagreement with PB or Ovht downstream of pack comp (>204°C). FWS. Valve auto closed. LEAK activates when temperature detected by bleed loop exceeds 156°C. FWS. Auto closure after 1 sec of following valves: Bleed, HP, PACK and GND XFeed. DO NOT RESET BLEED.
Tests all lights. Ldg Elev indicators show all 8 segments.
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Annexes
Menu P/B Enable sub function selection menu
Brightness
SEL P/B Change cursor selection between VHF COM, VHF NAV, BARO SETTING and COURSE when VOR mode.
BOOST (if installed) ON The boost can be selected on ground with the PL below FI, or in flight after an engine failure. When the torque is thermodynamically limited, the boost increase the torque: – With PWR MGT in TO by: – 4.5% up to 4000ft – 4% above 4000ft – With PWR MGT in MCT by 4% The selection of the boost is latched when the PLs are advanced above FI, and can not be changed during flight (except in case of engine failure). FAULT For any disagreement between the position of the push button and the rating of both EEC (MC+SC+FAULT+ENG BOOST on FWS).
FAULT stick shaker or pusher failure. OFF turns off both shaker and pusher
STD P/B Reset at 1013.25Hpa, when pushed more than 0.2 sec.
IESI (Integrated Electronic Stantby Instrument) displays the following information: – Attitude – Airspeed – Altitude – Baro pressure setting – VHF 1 – VOR/ILS 1
SET ROTARY SWITCH – Sub fonction menu scroller – Baro setting – VHF com tuning – VHF nav tuning – Course setting in VOR mode
PWR MGT 2 co-axial sw, (LH: Bottom/RH: Top) providing FDAU (MPC), PEC, PIU and EEC with basic power requirements.
FAULT: illuminates when both PEC channels are lost FWS. OFF: PEC is deactivated and Np is limited at 102.5% by the overspeed governor if power is sufficient.
APM FAULT Failure in the APM function computation APM Test PTT performed daily
PTT pb press for 3 sec. – icing will flash on the display if system works correctly (steady if ice detector failure is detected). – FAULT LT illuminate. A-ICING DETECT is displayed steady on the FWS. ICING AOA Lt illuminates green as soon as 1 horn anti-icing ON. Stall alarm (stick shaker threshold lowered). It can be extinguished manually only by releasing ICING AOA Pb (DC EMER) provided both Horns anti-icing selected OFF.
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S y s t e m s 4 2/72 - 6 0 0 Panel with EWD format.
Arming conditions: PWR MGT sel on TO +ATPCS pb in + both PL >49° + both TQ > 53%(42) both TQ > 46% (72) ARM green LT on.
ATPCS – ARM on ground = uptrim + auto FTR (2.15” delay) – ARM in flight (In case of go around) = auto FTR only.
ATPCS Trigger one TQ 23 kts + 50% diff between wheels (locked wheel protection). Braking action inhibited at touchdown as long as wheel spin up speed 17 kts) = MC + SC EWD 4 amber F on EWD. Test duration: 3 sec. in flight and 6 sec. on ground
Gear handle red Lt any gear not sensed down and locked with the further conditions: a) Any gear not down and locked + flaps normal landing configuration + Zra -1500 ft/mn
NORM AUTO mode selection MAN digital controller out of operation. No more digits in landing elevation display
TEST displays alternatively 18800 and –8800, FAULT appears on MAN pb (Test inhibited in FLT)
FAULT digital controller failure. FWS
DUMP ON (guarded) both outflow valves fully open in AUTO mode only
ON both outflow valves forced to fully closed
CABIN RATE KNOB NORM AUTO MODE position. When used in MAN mode, cabin rate selection +2500/–1500 ft/mn
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S y s t e m s 4 2/72 - 6 0 0 MCDUs (Multifunction Control Display Unit) Access to the FMS, MPC, and ACARS (Data Link) when the ACARS is installed.
WEATHER RADAR CONTROL PANEL
COCKPIT DOOR CONTROL PANEL Allows to control CDLS (Cockpit Door Locking System)
MULTIPURPOSE CONTROL PANEL (MCP) Allows cockpit crew to control the virtual control panel format (VCP) on MFD
POWER LEVER ( PL )
EMER & PARKING BRAKE CONDITION LEVER (CL) GA push button when depressed the GA FD mode is selected with: – HDG HOLD lateral mode with the wings level – GA vertical mode
EMER AUDIO CANCEL This SW cancels an undue aural alert. Cancelled aural warning will be reactivated: – at next A/C energization – after MFC 1B/2B reset – after pressing RCL pb – following TO config test The alerts here after are rearmed as soon as the triggering condition disappears – landing gear – VMO, VFE, VLE – Stall warning – Pitch trim whooler – AP disconnect
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 activated when the gate does not engage automatically in flight or does not extend automatically on ground In this case the idle gate lever enables manual override in case of failure of the automatic logic – In flight: push – On ground pull (an amber band appears)
F/O AUDIO CONTROL PANEL
Manual recording on DFDR or CVR (when supplied by GPU) Manual recording stopped with the reset P/B
EFis Control Panel (EFCP) Allows to control: -Display of the MFD pages (ND, SYST, PERF, MISC, VID and MAP) -Navigation Display (ND) functionalities -Warning Display (WD)
CAPT AUDIO CONTROL PANEL
FLAPS
TO CONFIG TEST pb: Check if the TO configuration is correct for take off: – PWR MGT TO – Flaps 15° – Pitch trim in the green band – TLU LO SPD – no AIL LOCK light The same test is performed when advancing the PL with this additional requirement: – Parking Brake released
ACARS & MPC PRINTER
Panel & flood light control
Aileron, rudder & stby pitch trims
ATPCS test (static or dynamic)
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Annexes
FD lateral mode
FD vertical mode
NAV SOURCE Selector CAPT side Selects the NAV SOURCE for CAPT EHSI and/or ND depending on display configuration
ALT knob controls the preselected altitude on the PFD
NAV SOURCE Selector F/O side Selects the NAV SOURCE for F/O EHSI and/or ND depending on display configuration
FD bars ON/OFF switch
Chrono P/B Start/Stop/Zero
Chrono P/B Start/Stop/Zero
CRS 1 knob selects Course on CAPT EHSI
STBY COMPASS Hidden in up position. Compass Control should be place on DN For use. The compass rose is graduated in 10 degrees increments
Pitch wheel to adjust – VS or – Pitch attitude in basic mode
CRS 2 knob selects Course on F/O EHSI and ND
– AP pb engages autopilot and yaw damper and disengages only autopilot
HDG knob selects HDG bug on both EHSI and ND
– YD pb engages 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
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TAWS
TAWS visual alert GPWS If any TAWS mode is activated PULL UP Alert triggered after the GPWS alert in mode 1, 2 and terrain and obstacle awareness modes
GPWS switch and associated lights: ON: All basic GPWS modes are operative FLAP OVRD: In reduced flaps landing, to inhib the mode 4 alert OFF: All basic GPWS modes inhibited. OFF: light come on FAULT: GPWS FAULT —— > some or all GPWS basic modes are lost FAULT: TERR FAULT —— > some or all enhanced modes are lost OFF: All enhanced (TCF&TAD) modes inhibited
AHRS switching P/B To select the opposite side AHRS source. When depressed, SYS 2 is illuminated on CAPT side, while CAPT / 2 is illuminated green on F/O side The CAPT P/B has priority
ACARS message ATC DLK (ATC Data LinK) is illuminated when a message is received through the ACARS. The message can be read on the MCDU
MASTER WARNING MASTER CAUTION
Display P/B The P/B allows to switch formats (PFD/EWD/MFD) on the DU2, or on DU1 if DU2 is OFF.
ADC switching P/B To select the opposite side ADC source. When depressed, SYS 2 is illuminated on CAPT side, while CAPT / 2 is illuminated green on F/O side The CAPT P/B has priority
MFD upper window Displays the different pages selected on the EFCP: – ND page (Navigation Display: shown here) – SYST page (System) – PERF page (Performance) – MAP page (airport mapping) – MISC page (in provision) – VD page (Video in provision)
ND page (Navigation Display) Different mode selected on the EFCP: – ARC mode – ROSE mode – PLAN mode
STEEP APP P/B (optional) When selected ON, moves the mode 1 threshold, to avoid TAWS triggering in steep slope approach
AUDIO 1 SEL FAULT: When the associated RCAU part is failed. ALTN: Affected crew station is connected directly to VHF1 if CAPT station is affected.
Index Control Panel (ICP) Baro setting control
Index Control Panel (ICP) Speed target control
DISPLAY UNIT 1 (DU1) In the normal configuration, with CAPT as PF, the PFD format is displayed
Memo Panel Display Displays the following system information when selected FUEL XFEED PROP HORN SIDE WINDOW ENG AIFRAME NO DEVICE SEAT BELT
VCP window (Vitual Control Panel) Displays the informations about: The COM selection The NAV selection (shown here) The SURV (surveillance) selection DISPLAY UNIT 2 (DU2) In the normal configuration, with CAPT as PF, the MFD format is displayed with the ND page. The FMA 1 (Flight Management Application 1) and the RMA 1 (Radio Management Application 1) are included in the DU2 functions
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Annexes MFD upper window Displays the different pages selected on the EFCP: – ND page (Navigation Display) – SYST page (System: shown here) – PERF page (Performance) – MAP page (airport mapping) – MISC page (in provision) – VD page (Video in provision)
Display P/B The P/B allows to switch formats (PFD/EWD/MFD) on the DU4, or on DU5 if DU4 is OFF.
Airspeed Indicator (ASI)
Flight Mode Annuciator (FMA)
MASTER WARNING MASTER CAUTION
ELAPSED TIME P/B When the ELAPS TM P/B is depressed ON the flight time starts automatically, on the EWD, when airborne
Attitude Display Indicator (ADI)
Altimeter
ADC switching P/B To select the opposite side ADC source. When depressed, SYS 1 is illuminated on F/O side, while F/O /1 is illuminated green on CAPT side The CAPT P/B has priority
Vertical Speed Indicator (VSI)
SYST page (System page) Different mode selected on the EFCP: – ACW-HYDRAULIC – ENGINE (secondary engine display) – CABIN (shown here) – AC-DC ELECTRIC
CLOCK
AHRS switching P/B To select the opposite side AHRS source. When depressed, SYS 1 is illuminated on F/O side, while F/O /1 is illuminated green on CAPT side The CAPT P/B has priority
LOUDSPEAKERS VOLUME KNOBS Individual knob for each loudspeaker
VCP window (Vitual Control Panel) Displays the informations about: The COM selection (shown here) The NAV selection The SURV (surveillance) selection
DISPLAY UNIT 4 (DU4) In the normal configuration, with F/O as PM, the MFD format is displayed with the SYST page. The FMA 2 (Flight Management Application 2) and the RMA 2 (Radio Management Application 2) are included in the DU4 functions
DISPLAY UNIT 5 (DU5) In the normal configuration, with F/O as PM, the PFD format is displayed.
Navigation Area With the ND on the MFD, the EHSI is displayed on the PFD. With an other page on the MFD, a mini ND is displayed on the PFD. The mini ND can be in ARC mode or ROSE mode, selected on the EFCP.
Index Control Panel (ICP) Speed target control: – Speed target selection Selection of the speed bug between: – AUTO: Speed bug managed by the FMS (Magenta) – MAN: Speed bug set manually by the speed knob (Cyan) – Speed knob Used to set the speed bug In MAN mode (Cyan)
Index Control Panel (ICP) Baro setting control: – Barometric setting knob The knob is used to set the barometric reference. Pushing the knob sets standard barometric reference (29.92 INHG / 1013.25 Hpa) – DH / MDA knob Outer knob permits to select between DH (Decision Height) or MDA (Minimum Descent Altitude). Inner knob is used to set DH or MDA values, depending of the outer knob position.
READING LT knob Control the respective spot light
CONSOLE LT knob Control the lights of the associated lateral console
AUDIO 2 SEL FAULT: When the associated RCAU part is failed. ALTN: Affected crew station is connected directly to VHF2 if F/O station is affected.
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S y s t e m s 4 2/72 - 6 0 0
Parking/emergency braking accumulator pressure indicator This indicator is used when the MFDs are not energized, to check brake accumulator pressure. When the switch is activated, the indicator is energized for two minutes When the accumulator pressure is 3100 psi, the indicator displays blinks.
N/W STEERING ON: The steering solenoid valve is electrically armed. The steering is available with an angle up to 60° in either direction OFF: The steering system is unpressurized. Should be OFF for towing and push back The steering is disconnected with an angle up to 91° in either direction
Nose wheel steering Push To Talk When depressed, BOOM SET or OXY mike is connected for transmission over the selected communication facility
Test & Reset slider Blinker indicator Normal/100% selector RH red grips (inflate harness) Emergency rotaty knob
Position of the selector: EXT PWR DC panel indicates the DC GPU voltage & current AC panel indicates the AC GPU voltage, load & current GEN 1/ 2 DC panel indicates the DC Generator voltage & current AC panel indicates the ACW Generator voltage, load & current INV 1/ 2 No indication on DC panel AC panel indicates the AC Inverter voltage, load & current MAIN and EMER BAT DC panel indicates the DC Main & Emer Battery voltage & current No indication on AC panel
PRELIMINARY COCKPIT PREPARATION: OXYGEN MASK TEST INT/RAD SELECTOR (On AUDIO CONTROL PANEL) .................................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 leak PRESS TO TEST AND RESET PB ...................................................................... HOLD RED GRIPS ON EACH SIDE OF THE HOSE ......................................................PRESS
NOTE: Oxygen pressure inflates the harness. Observe blinker momentarily turns yellow and must turn dark PRESS TO TEST AND RESET PB ...................................................................... HOLD EMERGENCY KNOB ....................................................................................... SELECT
NOTE: Emergency flow is tested. Observe blinker momentarily turns yellow during oxygen flow and must turn dark when the knob is released. NOTE: In this 3 cases, check that oxygen flow sounds though loudspeakers OXY LO PR LIGHT ................................................................. CHECK EXTINGUISHED N/100% Selector ..................................................................................... SET to 100%
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Annexes
FLIGHT DECK VENTILATION ISOLATION EXTRACT AIR FLOW CAUTION: Close only in case of FWD COMPT smoke Enables, in case of smoke in the forward cargo compartment, to isolate the flight deck ventilation preventing smoke to enter the flight compartment
MAIN PNL Before the flight, check that all the switch and selector are in the normal position. If not, the MAIN PANEL is displayed on the FWS
BITE LOADED magnetic indicator Indicates that a failure has been recorded by the maintenance system. Report to maintenance
BRK TEMP TEST When depressed, MC, SC, WHEELS BRK HOT on FWS
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Annexes
Annex 2. Abbreviations A AAS AC A/C ACARS AC BTC AC BTR ACW ADC ADF ADI ADN ADS AFCS AFDX A/FEATH AFCA AFT AFU AGB AHRS AHRU AIL ALT ALTM ALTN AMP AOA AP APP APU APAU ARINC A 429 ARM ASI ASYM ATC ATPCS ATT ATTND AUTO AUX AVAIL
Anti-icing Advisory System Alternating Current Aircraft ARINC Communication Addressing and Reporting System AC Bus Tie Contactor AC Bus Tie Relay Alternating Current Wild Frequency Air Data Computer Automatic Direction Finder Attitude Director Indicator Avionic Data Network Air Data System Automatic Flight Control System Avionic Full DupleX Auto Feathering Auto Flight Control Application Rear Part Auto Feather Unit Accessory Gear Box Attitude and Heading Reference System Attitude and Heading Reference Unit Aileron Altitude Altimeter Alternate Ampere Angle of Attack Auto-Pilot Approach Auxiliary Power Unit AutoPilot Actuator Unit Aeronautical Radio INCorporated ARINC 429 Armed Air Speed indicator Asymmetry Air Traffic Control Automatic Take off Power Control System Attitude Attendant Automatic Auxiliary Available
B BARO BAT BC BITE BPCU BPU
Barometric Battery Back Course Built in Test Equipment Bus Power Control Unit Battery Protection Unit
BRG BRK B-RNAV BRT BTC BTR
Bearing Brake Basic Area Navigation Bright Bus Tie Contactor Bus Tie Relay
C CAB CAC CAPT CAT C/B CDI CDLS CHAN CHC CL CLA CLB CLR CMA CMS CMPTR CMU COM COMPT CONFIG CPL CPM CRC CRS CRZ CTL CVR
Cabin Core Avionic Cabinet Captain Category Circuit Breaker Course Deviation Indicator Cockpit Door Locking System Channel Charge Contactor Condition Lever Condition Lever Angle Climb Clear Centralized Maintenance Application Cabin Management System Computer Communication Management Unit (ACARS) Communication Compartment Configuration Auto Pilot Coupling Core Processing Module Continuous Repetitive Chime Course Cruise Control Cockpit Voice Recorder
D DC DCA DELTA P DEV DFDR DGR DH DIFF DISCH DIM DIST DLK DME DMU DN DSPL DU
Direct Current Data Concentration Application Differential Pressure Deviation Digital Flight Data Recorder Degraded Decision Height Differential Discharge Light Dimmer Distance Data LinK Distance Measuring Equipment Data Management Unit Down Display Display Unit
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S y s t e m s 4 2/72 - 6 0 0 E EEC EFCP EFIS EHSI EHV ELEC ELV EMER ENG EQPT ESS ETOPS EWD EXT
H Engine Electronic Control EFis Control Panel Electronic Flight Instrument System Electronic Horizontal Situation Indicator Electro Hydraulic Valve Electrical Elevation Emergency Engine Equipment Essential Extended Twin Operations Engine & Warning Display Exterior, External
F F FAIL FAP FCOC FCU FD FDA FDAU FEATH, FTR FF FGC FGCP FGS Fl FLT FMA FMA FMS F/O FOS FQI FT FU FWD FWS
Farenheit Failed, Failure Flight Attendant Panel Fuel Cooled Oil Cooler Fuel Control Unit Flight Director Flight Data Application Flight Data Acquisition Unit Feathered, Feathering Fuel Flow Flight Guidance Computer Flight Guidance and Control Panel Flight Guidance System Flight Idle Flight Flight Management Application Flight Modes Annunciators Flight Management System First Officer Flight Operations Software Fuel Quantity Indication Foot, Feet Fuel Used Forward Flight Warning System
G GA GCU GEN GI GND GPS GPU GRD G/S GSPD
Go Around Generator Control Unit Generator Ground Idle Ground Global Positioning System Ground Power Unit Ground Glide Slope Ground Speed
HBV HDG HF HI HLD HMU HP HSI HTG HYD
Handling Bleed Valve Heading High Frequency High Hold Hydromechanical Unit High Pressure Horizontal Situation Indicator Heating Hydraulic
I IAS ICP IDT IESI IGN ILS IMA IND IN/HG INHI INOP INST INT INV IOM ISOL ITT
Indicated Air Speed Index Control Panel Ident Integrated Electronic Standby Instrument Ignition Instrument Landing System Integrated Modular Avionics Indicator Inches of Mercury Inhibit Inoperative Instrument Interphone Inverter Input Output Module Isolation Inter Turbine Temperature
JK KHZ KT
Kilo-Hertz Knot
L LAT LAV LB LDG L/G LH LMU LNAV LO LOC LO-PR LP LT LVL
Lateral Lavatory Pound Landing Landing Gear Left Hand Light Management Unit Lateral Navigation Low Localizer Low Pressure Low Pressure Light Level
M MAX MAP MB MC MCDU MCP
Maximum Mapping Millibar Master Caution Multifunction Control Display Unit Multifunction Control Panel
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Annexes MCT MECH MFC MFCU MFD MGT MHZ MIC MLG MIN MIP MISC MKR MLW MM MMO MOD MPC MPU MSG MSN MTOW MW MZFW
Maximum Continous Mechanic Multi Function Computer Mechanical Fuel Control Unit Multi Function Display Management Megahertz Microphone Main Landing Gear Minimum Main Instrument Panel Miscellaneous Marker Maximum Landing Weight Millimeter Maximum Operating Mach Modification Multi Purpose Computer Micro Processor Unit Messages Manufacturer Serial Number Maximum lake off Weight Master Warning Maximum Zero Fuel Weight
N NAC NAV ND NDB NEG NH NIL NL NM NORM NP N/W NWS
Nacelle Navigation Navigation Display Non Directional Beacon Negative High Pressure Spool Rotation Speed Nothing, No Object Low Pressure Spool Rotation Speed Nautical Mile Normal Propeller Rotation Speed Nose Wheel Nose Wheel Steering
O OAT OVBD OVERTEMP OVHT OVRD OXY
Outside Air Temperature Overboard Overtemperature Overheat Override Oxygen
P PA PB PEC PED PERF PFD PIU PL PLA PNL
Passenger Address Push Button Propeller Electronic Control Pedestal Performance Primary Flight Display Propeller Interface Unit Power Lever Power Lever Angle Panel
POS P-RNAV PRESS PRIM PRKG PROP PSI PSU PT PT (TCAS) PTB PTT PTW PVM PWR PW
Position Precision Area Navigation Pressurization, Pressure Primary Parking Propeller Pound per Square Inch Pax Service Unit Point Proximity traffic Pitch Trim Box Push To Talk, Push To Test Pitch Thumb Wheel (same as PW) Propeller Valve Module Power Pitch Wheel (same as PTW)
Q QAR QT QTY
Quick Access Recorder Quart Quantity
R RA (TCAS) RA RAD/ALT RAD/INT RCAU RCDR RCL RCU RECIRC REV RGA RGB RH RLY RMA RMI RMS RNP RPM RTO RUD
Resolution Advisory Radio Altitude Radio Altitude Radio/Interphone Remote Control Audio Unit Recorder Recall Releasable Centering Unit Recirculation Reverse Reserve Go-Around Reduction Gear Box Right Hand Relay Radio Management Application Radio Magnetic Indicator Radio Management System Required Navigation Performance Revolution Per Minute Reserve Take-Off Rudder
S SAT SBY SC SEL SGL SGU SMK SMKG S/O (SO) SOV SPD SPLR SPLY
Static Air Temperature Stand By Single Chime, Starter Contactor Selector Single Symbol Generator Unit Smoke Smoking Shut Off Shut Off Valve Speed Spoiler Supply
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S y s t e m s 4 2/72 - 6 0 0 STBY STRG SSFDR SURV SVCE SW SWM SYS
Stand By Steering Solid State Flight Data Recorder Surveillance Service Switch gateway and SWitch Module System
T TA (TCAS) TAD TAS TAT TAWS TCF TCS TEMP TGT TK TLU T/O (TO) TOW TQ TRU TTG
TRAFFIC Advisory Terrain Awareness Display True Air Speed Total Air Temperature Terrain Awareness Warning System Terrain Clearance Floor Touch Control Steering Temperature Target Tank Travel Limiting Unit Take off Take off weight Torque Transformer Rectifier Unit Time To Go
U U/F UHF UNCPL UNDV
Underfloor Ultra High Frequency Uncouple Undervoltage
UNLK UTLY
Unlock Utility
V VC VCP VENT VERT VHF VID VMO VNAV VOR VSI
Calibrated Airspeed Virtual Control Panel Ventilation Vertical Very High Frequency Video Maximum Operating Speed Vertical Navigation VHF OMNI Directional Range Vertical Speed Indicator
W WARN WOW XFEED XFR
Warning Weight On Wheel Cross feed Transfer
XY YD YDAU
Yaw Damper Yaw Damper Actuator Unit
Z ZA ZCTH ZFW ZP ZRA
Aircraft Altitude Theoretical Cabin Altitude Zero Fuel Weight Pressure Altitude Radio Altimeter Altitude
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Dear Readers, Every effort has been made to ensure document quality. However please do not hesitate to share your comments and information with us by using the following address: [email protected] Yours faithfully,
Printed on 100% recycled paper using vegetable inks
Your ATR Training and Flight Operations support team.
© ATC May 2014 All reasonable care has been taken by ATC to ensure the accuracy of the present document. However this document does not constitute any contractual commitment from the part of ATC which will offer, on request, any further information on the content of this brochure. Information in this brochure is the property of ATC and will be treated as confidential. No use or reproduction or release to a third part may be made there of other than as expressely authorised by ATC.
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