Indicating & Recording¶
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 GENERAL¶
Indicating & Recording: 1.1.1 General¶
The MPC unit is including two parts: - Flight Data Acquisition Unit (FDAU) - Data Management Unit (DMU)
Indicating & Recording: 1.2 FDAU¶
Indicating & Recording: 1.2.1 FDAU¶
1) 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 DESCRIPTION) - Aircraft Performance Monitoring (APM) (Refer to AIRCRAFT PERFORMANCE MONITORING (APM)) - Data broadcast to CAC (to avionics system) - Time management - Flight time management - Flight number management - Configuration management (Aircraft type, Aircraft ident, APM version).
Indicating & Recording: 1.3 DMU (DATA MANAGEMENT UNIT)¶
Indicating & Recording: 1.3.1 DMU (Data Management Unit)¶
1) 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/ DAR when it is reprogrammed by a ground support equipment) --> FDM purpose - Management of reports (takeoff, cruise, ...) --> FDM purpose - Dialogue with the following aircraft equipment: MCDU, Printer, ACARS (optional) - Other maintenance functions.
Indicating & Recording: 2 ELECTRICAL SUPPLY¶
Indicating & Recording: 2.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) MPC (in flight) DC ESS BUS (SECT 1) (on lateral panel C/B FLT DATA RCDR/FDAU DFDR/FLT SPLY) NIL MPC (on ground) DC EMER BUS (on lateral panel C/B FLT DATA RCDR/FDAU DFDR/GND SPLY) NIL
Indicating & Recording: 3 SCHEMATIC¶
Indicating & Recording: 3.1 Schematic¶
DU 2 CPM 1 IOM /S1 IOM /AP1 IOM /DC 12 IOM /DC 13 SWM 1 AFCA 1 FWA 1 DCA 1 CMA 1 CPM 2 IOM /S2 IOM /AP2 IOM /DC 22 IOM /DC 23 SWM 2 CAC 1 CAC 2 AFCA 2 FWA 2 DCA 2 11 21 APAU PITCH APAU ROLL YDAU GPS 1 DME 1 ADF 1 VHF 1 NAV 1 MCDU HDG NAV APP BC STBY ALT VS AP YD SPD HLD CPL HDG PUSH SYNC FD NAV SOURCE ALT SEL COURSE V/ILS 1 V/ILS 2 FM 1 FM 2 NAV SOURCE COURSE V/ILS 1 FM 2 FM 1 NOSE UP NOSE DN FD DU 4 FGCP AFDX IAS DU 1 SSFDR EEC 1 ATC 1 RA 1 HF 1 CMU VHF 3 ACARS AHRS 1 ADC 1 AIRCRAFT SYSTEMS AFDAU DMU TO OPEN TURN SLIDE DOWN TO CLOSE TURN SLIDE UP PPR ADV SELF ADV PWR ON ALERT RESET PTR BUSY 1A MODULE 1B MODULE TAT 1 STATIC 1 PITOT 1 FLUX VALVES MPC MFC 1 2B MODULE 2A MODULE MFC 2 PITCH TRIM BOX AFDX ARINC, DISCRETES AFCS CONTROL OPTIONAL IESI STBY PITOT STBY STATIC DU 3 DU 5 M F D PERF ND MISC SYS BRG1 BRG2 N A V - + RANGE FORMAT P R O C RCL CLR PROC MENU VID MAP M F D PERF ND MISC SYS BRG1 BRG2 N A V - + RANGE FORMAT P R O C MAN DEL 1 2 3 4 5 6 7 8 9 0 COM NAV SURV ENT ESC AUTO/MAN SPD TGT BARO SET PUSH STD DH MDA SEL ET - / + TST CHR MODE H/MO MN/DY S/YR GPS CHR CLOCK 1 GPS 1 DME 2 ADF 2 VHF 2 NAV 2 EEC 2 ATC 2 RA 2 HF 2 VHF1 ILS1 108.50 118.100 ILS M 47 MENU SET 130 10 10 1019 125 160 220 18 1 2 20 127 00 200 STD SEL + - ICP MCDU CLOCK 2 GPS 2 AHRS 2 ADC 2 TAT 2 STATIC 2 PITOT 2 FLUX VALVES DISPLAY PFD /EWD /MFD ATT/HDG ADC F/O SWITCHING CAPT/2 SYS 1 CAPT/2 SYS 1 PFD /EWD /MFD ATT/HDG ADC F/O/1 SYS 2 CAPT SWITCHING F/O/1 SYS 2 MCP 1 2 3 4 5 6 7 8 9 0 COM NAV SURV ENT ESC MCP EFCP EFCP ICP AUTO/MAN SPD TGT BARO SET PUSH STD DH MDA SEL
FUNCTIONAL ABSTRACTION - MPC/CAC aircraft-data architecture
DU1 DU2 DU3 DU4 DU5
| | | | |
+----+----+----+----+---- AFDX / display network ----+
|
+---------------------+---------------------+
v v
[CAC 1] [CAC 2]
A429 / analog / discrete A429 / analog / discrete
^ ^
ADC, AHRS, DME, GPS, NAV, ACARS, CMU, MPC/MFC, aircraft systems and trim racks
Indicating & Recording: 4 LOST EQUIPMENT LIST¶
Indicating & Recording: 4.1 Lost Equipment List¶
Lost Equipment List Integrated Systems - Maintenance Access (Via MCDU) - FDAU Function - DFDR Electrical Systems - AC STBY BUS indication lost on electrical system page - EMER BUS indication lost on electrical system page - ESS BUS indication lost on electrical system page Flight Instruments - Flight time on EWD Ice and Rain Protection - APM fault indication Power Plant - NL indication
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 General¶
Numerous logic functions are performed by the MFC system provides by, two independent computers (MFC 1 and MFC 2) Each computer includes two independent modules (A and B). Each module includes: - A 28 VDC dual power supply - An input/output circuit - A computation unit - For module 1A and 2A only, a hard-wired logic independent of the computation unit.
Indicating & Recording: 1.2 Signal Processing¶
Each module receives signals from the various systems and system controls. Each signal received by a module is then converted, if necessary, to a digital signal by the input circuit. Then: - For most of the functions, the signal is sent to the computation unit which processes the data according to the logic programmes - For some specific functions (stick pusher, flaps), signal processing is performed in a conventional way by the hard-wired card (to avoid computation errors or common failures). An intercard dialogue is established between all modules to enable each module to use signals processed by other modules. Signals from each system are taken into account by one or more modules depending on the degree of reliability/safety required for the system. Each module is equipped with a self test system which monitors correct operation of that module.
Indicating & Recording: 1.3 Functions¶
After processing, computation unit transmits orders from the output circuit to the various systems in order to: - Monitor, control and authorize operation of the aircraft systems - Manage system failures and flight envelope anomalies and command triggering of associated warning in the Flight Warning System (FWS).
Indicating & Recording: 1.4 MCDU¶
During a maintenance operation on the ground, MFC fault codes can be displayed by means of MPC menu on MCDU. In the MPC menu, select MAINTENANCE sub-menu then MFC: - The BASIC MEMORY gives access to the content of the fault codes stored since the last erase (no chronological information) - The FLIGHT FAULT memory gives access to the fault codes which occurred during the 9 previous flights. Note To erase the maintenance memory, select MAINT MEMORY ERASING menu via MFC menu to erase basic memory and/or the flight memory. To erase the maintenance magnetic indicator, press ERS pb on the lateral maintenance panel.
MCDU V BASIC MEMORY FLT FAULT MEMORY MAINT MEMORY ERASING COPY TO PCMCIA RETURN V V V V V V MFC V V V V V PRINT WOW & LG DOORS BOOTS NAV BRK RETURN BASIC MEMORY FLT CTL MISC1 MISC2 MISC3 MFC/MISC4 PRINT* V V V V V V V V V V V V
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 Control Panel¶
25VU MFC 1A 1B 2A 2B FAULT OFF FAULT OFF FAULT OFF FAULT OFF MFC Pbs Controls operation of associated module: ON (pb pressed in) the module operates OFF (pb released) the module stops operating. The OFF white indicator light comes on. FAULT The amber light comes on 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 four modules are selected ON, the following sequence is executed: - MFC 1A and MFC 2A FAULT lights (self-test of these modules) flashing - MFC 1A and MFC 2A FAULT lights turn off, MFC 1B and MFC 2B FAULT lights (self-test of these modules) flashing - MFC 1B and MFC 2B FAULT lights turn off. 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.
Indicating & Recording: 3 OPERATION¶
Indicating & Recording: 3.1 Introduction¶
Charts on the following pages list the implementation and availability of the functions ensured by each module.
Indicating & Recording: 3.2 Reading of Tables¶
The table uses the following symbols : , , to indicate: - Location of the functions o A function is integrated in each module denoted by one of these symbols. - Availability can be treated: o In one module only o In several modules (redundancy) o Partially in two modules, i.e. both modules considered are to be operative to process this function. Example: SYSTEM FUNCTION MODULE 1A 1B 2A 2B FLIGHT STICK PUSHER CONTROLS STALL WARNING - 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.
Indicating & Recording: 3.3 AFCS¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B AFCS GUIDANCE (AURAL) AP DISENGAGEMENT IN CASE OF - STALL WARNING - PITCH TRIM ASYMMETRY - STBY TRIM CONTROL - PITCH EFFORT
Indicating & Recording: 3.4 COM¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B COM MECHANICAL CALL indicator ATTENDANT CALL indicator CREW CALL indicator CVR ERASE RECORDERS (START/STOP) PUBLIC ADDRESS VOLUME MUTING HP GALLEY
Indicating & Recording: 3.5 Electrical System¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B E L E C DC EMER BAT CHG CTL MAIN BAT CHG CTL BAT DISCHARGE IN FLIGHT DC BUS 1 OFF WARNING DC BUS 2 OFF WARNING DC STBY BUS UNDV DETECTION SUPPLY OF DC EMER BUS FROM HOT EMER BAT BUS OR FROM MAIN BUSSES SUPPLY OF DC ESS BUS FROM HOT MAIN BAT BUS OR FROM MAIN BUSSES EMER BAT PROTECTION MAIN BAT PROTECTION LEFT PFTS RIGHT PFTS AC SUPPLY OF INV 1 FROM DC BUS 1 OR FROM HOT MAIN BAT BUS AC BUS 1/INV 1 RELAY AC BUS 2/INV 2 RELAY AC BUS TIE RELAY (BTR) INV 1 FAULT LIGHT INV 2 FAULT LIGHT
Indicating & Recording: 3.6 Light¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B LIGHT LIGHT TEST
Indicating & Recording: 3.7 Engine Bleeds¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B ENGINE BLEEDS BLEED 1 SHUT-OFF VALVE BLEED 1 HP VALVE BLEED 1 FAULT indicator BLEED 2 SHUT-OFF VALVE BLEED 2 HP VALVE BLEED 2 FAULT indicator XFEED VALVE
Indicating & Recording: 3.8 ATPCS¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B ATPCS ATPCS ARM LIGHT ENGINE 1 UPTRIM PROP 1 A/FEATH INHIBITION ON GROUND OF ENG 1 ELECTRICAL FEATH PUMP ACTIVATION BY CL 1 ENGINE 2 UPTRIM PROP 2 A/FEATH INHIBITION ON GROUND OF ENG 2 ELECTRICAL FEATH PUMP ACTIVATION BY CL 2
Indicating & Recording: 3.9 PROP Brake¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B PROP BRAKE BRAKING RELEASING PROP BRAKE UNLK indicator AUTOMATIC DC AUX PUMP CUT OFF AFTER PROP BRAKE LOCKING FAULT START 2 ILLUMINATION WHEN PROP BRAKE ENGAGED AND GUST LOCK NOT ENGAGED PROP BRK ILLUMINATION ON FWS WHEN GUST LOCK IS RELEASED, ENG IS RUNNING AND PROP BRAKE STILL ENGAGED DC AUX PUMP
Indicating & Recording: 3.10 Idle Gate¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B IDLE GATE IDLE GATE CTL IDLE GATE AMBER ALERT
Indicating & Recording: 3.11 Engine Start¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B ENGINE START START indicator LIGHTS
Indicating & Recording: 3.12 Engine¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B ENGINE HIGH FLIGHT IDLE
Indicating & Recording: 3.13 Ice and Rain Protection¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B I C E - A N D - R A I N - P R O T E C T I O N ENGINES ENGINE 1 DE (OR ANTI-) ICING ENGINE 2 DE (OR ANTI-) ICING ENGINE 1 DE (OR ANTI-) ICING FAULT ENGINE 2 DE (OR ANTI-) ICING FAULT AIRFRAME DEICING (BOOTS A) AIRFRAME AIRFRAME DEICING (BOOTS B) AIRFRAME DEICING FAULT MODES AUTO SEL PROP 1 ANTI-ICING PROPELLERS PROP 2 ANTI-ICING PROP 1 ANTI-ICING FAULT PROP 2 ANTI-ICING FAULT WINDOWS LEFT SIDE WINDOW ANTI-ICING PWR SPLY RIGHT SIDE WINDOW ANTI-ICING PWR SPLY LEFT SIDE WINDOW ANTI-ICING FAULT DETECTION RIGHT SIDE WINDOW ANTI-ICING FAULT DETECTION AAS AAS indicator
Indicating & Recording: 3.14 Landing Gear¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B LANDING GEAR LANDING GEAR CONTROL CENTRAL PANEL PRIMARY RED UNLK indicator PRIMARY DOWNLOCK indicator OVERHEAD PANEL SECONDARY RED UNLK indicator SECONDARY DOWNLOCK indicator LDG GEAR NOT DOWN WARNING BRAKE OVERTEMP ALERT (L/H) BRAKE OVERTEMP ALERT (R/H) BRAKE OVERTEMP TEST WEIGHT ON WHEELS (SYSTEM 1) WEIGHT ON WHEELS (SYSTEM 2) NOSE WHEELS STEERING
Indicating & Recording: 3.15 Flight Control¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B F L I G H T C O N T R O L FLAPS EXTENSION AND ASYM PROTECTION RETRACTION AND ASYM PROTECTION RED FLAPS UNLK WARNING AMBER FLAP ASYM ALERT IN FLIGHT INHIBITION OF FLAPS UNLK TEST (MAINTENANCE) ASYM TEST MAINTENANCE STALL WARNING STICK PUSHER STICK PUSHER INHIBITION STICK PUSHER/SHAKER FAULT indicator STALL WARNING STICK SHAKER STICK PUSHER TEST PITCH TRIM WHOOLER PITCH TRIM ASYM WARNING RUDDER TRIM RELEASE CENTERING UNIT AUTO DISCONNECT DURING YAW TRIM ACTION OR YAW DAMPER ENGAGEMENT TLU TRAVEL LIMITATION UNIT AUTOMATIC CONTROL INDICATION
Indicating & Recording: 3.16 Hydraulic¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B HYDRAULIC BLUE HYDRAULIC PUMP (CTL) GREEN PUMP LO PR INDICATION
Indicating & Recording: 3.17 FWS¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B FWS AURAL ALERTS MASTER WARNING AND MASTER CAUTION AMBER ALERTS ON EWD RED CONFIG ENG OIL PROP BRK ALERTS ON EWD RED FLAPS UNLK ALERT ON EWD
Indicating & Recording: 3.18 Air¶
SYSTEM MODEL FUNCTION MODULE 1A 1B 2A 2B AIR ALL PACK 1 PACK 1 FAULT indicator PACK 2 PACK 2 FAULT indicator GND TURBO FAN 1 GND TURBO FAN 2 OUTFLOW VALVE AUTO OPENING AFTER LANDING OVBD VALVE PWR RLY CTL OVBD VALVE FAULT indicator X VALVE UNDER FLOOR VALVE PWR RLY CTL EXTRACT FAN EXTRACT FAN SHUT DOWN RLY COMMAND
Indicating & Recording: 3.19 Doors¶
SYSTEM MODEL FUNCTION MODULE 1A 1B 2A 2B DOORS 102 or 202 or 212 CARGO DOOR UNLK indicator CARGO DOOR CTL EMER HATCH UNLK indicator FWD COMPT DOOR UNLK indicator CARGO DOOR CTL panel
Indicating & Recording: 4 ELECTRICAL SUPPLY¶
Indicating & Recording: 4.1 Electrical Supply¶
Each module is supplied by two separate electrical sources (primary and alternate). Power supply switching is automatic: - From primary to alternate if primary V < 19 V and if alternate V > 22 V - From alternate to primary if primary V > 22 V.
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) MFC 1A Primary Supply DC ESS BUS (Overhead panel 1A NORM SPLY ) NIL Alternate Supply HOT EMER BAT BUS (Overhead panel 1A AUX / ADC 1 SPLY ) NIL MFC 1B Primary Supply DC BUS 1 (Overhead panel 1B NORM SPLY ) NIL Alternate Supply DC EMER BUS (Overhead panel 1B AUX SPLY ) NIL MFC 2A Primary Supply DC EMER BUS (Overhead panel 2A NORM SPLY ) NIL Alternate Supply HOT MAIN BAT BUS (Overhead panel 2A AUX SPLY ) NIL MFC 2B Primary Supply DC BUS 2 (Overhead panel 2B NORM SPLY ) NIL Alternate Supply DC EMER BUS (Overhead panel 2B AUX SPLY ) NIL
Indicating & Recording: 5 SYSTEM MONITORING¶
Indicating & Recording: 5.1 MFC 1A FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1A FAULT - MC light flashing amber - MFC 1A amber message on EWD - MFC 1A FAULT amber light on overhead panel SC
Indicating & Recording: 5.2 MFC 1B FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1B FAULT - MC light flashing amber - MFC 1B amber message on EWD - MFC 1B FAULT amber light on overhead panel SC
Indicating & Recording: 5.3 MFC 2A FAULT-Alert¶
CONDITION VISUAL AURAL MFC 2A FAULT - MC light flashing amber - MFC 2A amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.4 MFC 2B FAULT-Alert¶
CONDITION VISUAL AURAL MFC 2B FAULT - MC light flashing amber - MFC 2B amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.5 MFC 1A+1B FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1A + 1B FAULT - MC light flashing amber - MFC 1A + 1B amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.6 MFC 1A+2A FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1A + 2A FAULT - MC light flashing amber - MFC 1A + 2A amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.7 MFC 1A+2B FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1A + 2B FAULT - MC light flashing amber - MFC 1A + 2B amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.8 MFC 1B+2A FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1B + 2A FAULT - MC light flashing amber - MFC 1B + 2A amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.9 MFC 2A+2B FAULT-Alert¶
CONDITION VISUAL AURAL MFC 2A + 2B FAULT - MC light flashing amber - MFC 2A + 2B amber message on EWD - Associated MFC FAULT amber light on overhead panel SC
Indicating & Recording: 5.10 MFC 1B+2B FAULT-Alert¶
CONDITION VISUAL AURAL MFC 1B + 2B FAULT - MFC 1B + 2B amber message on EWD - Associated MFC FAULT amber light on overhead panel NIL
Indicating & Recording: 6 LATERAL MAINTENANCE PANEL¶
Indicating & Recording: 6.1 RH Maintenance Panel¶
Recording of the failures is performed by the MFC 1A module.
PTA/ERS TEST IND MAG LOADED BITE BUS DATAMFC 1 2 3 4
1 “BITE LOADED" Magnetic Indicator Indicates that a failure has been recorded by the maintenance system. 2 TEST pb Used to check operation of the BITE LOADED magnetic indicator. When pressed for more than 3 s the magnetic indicator is activated. 3 PTA/ERS pb When depressed for at least 5 s the maintenance magnetic indicator is erased. This procedure also erases the MFC maintenance memory thus it has to be performed at the end of the maintenance task. 4 CONNECTOR OUTLET Enables the optional MTS (Maintenance Test Set) system to be connected.
Indicating & Recording: 7 SCHEMATIC¶
Indicating & Recording: 7.1 Schematic¶
HARD WIRED LOGIC OUTPUTS INPUTS OUTPUTS INPUTS COMPUTATION (SOFT) COMPUTATION (SOFT) AURAL ELECTRICAL POWER PRIMARY SUPPLY DC ESS BUS HOT EMER BAT BUS DC EMER BUS PRIMARY SUPPLY MAIN BUS ELECTRICAL POWER MFC1A MFC1B INTER-CARD DIALOGUE (ARINC 429) HARD WIRED LOGIC COMPUTATION (SOFT) COMPUTATION (SOFT) AURAL ELECTRICAL POWER PRIMARY SUPPLY DC EMER BUS HOT MAIN BAT BUS DC EMER BUS PRIMARY SUPPLY MAIN BUS ELECTRICAL POWER MFC2A MFC2B INTER-CARD DIALOGUE (ARINC 429) OUTPUTS INPUTS OUTPUTS INPUTS
INTER-CARD A429 --> [MPC1: hard-wired I/O | computation | A429 | power]
INTER-CARD A429 --> [MPC2: hard-wired I/O | computation | A429 | power]
Each MPC has independent primary and hot-emergency/DC-emergency supply paths.
Inputs and outputs are duplicated across the two cards for monitoring and
computation availability.
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 Description¶
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 IO for all functions - 1 IOM-AP (Input/Output Module) This IO Module is dedicated to provide discrete and analog IO for the Auto-Flight application - 2 IOM-DC (Input/Output Module) The IOM-DC provide discrete and analog IO 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.
CPM 1 IOM /S1 IOM /AP IOM /DC 12 IOM /DC 13 SWM 1 CPM 2 IOM /S2 IOM /AP IOM /DC 22 IOM /DC 23 SWM 2 CAC 1 CAC 2 11 21
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 by means of different data bus formats: - AFDX: Avionics Full DupleX switched ethernet - A429: ARINC 429 - Analogic - Discrete. Two of the five displays units (DU 2 and DU 4) are dedicated to two other functions: - Flight Management Application (FMA) - Radio Management Application (RMA). Refer to AVNX CPM and Refer to AVNX IOM to see the lost equipment lists in case of CPM and/or IOM failure.
Indicating & Recording: 2 ELECTRICAL SUPPLY¶
Indicating & Recording: 2.1 Electrical Supply¶
The CPM, IOM-AP&-DC, IOM-S and SWM cards are connected to the 28VDC aircraft electrical network. The power supply details are shown in the table below:
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) CAC 1 CPM 1 & IOM-S 1 DC EMER BUS (Upper panel CAC / CPM 1 / IOM-S 1) NIL IOM – AP 11 DC EMER BUS (Upper panel AFCS / FGCP CHAN 1 / IOM-AP 1) NIL IOM – DC 12 DC STBY BUS (Upper panel CAC / IOM-DC 12) NIL IOM – DC 13 DC STBY BUS (Upper panel CAC / IOM-DC 13) NIL SWM 1 DC EMER BUS (Upper panel CAC / SWM 1) NIL CAC 2 CPM 2 & IOM-S 2 DC ESS BUS (NORM SPLY) (Upper panel CAC / CPM 2 / IOM-S 2) DC STBY BUS (AUX SPLY- ENG START) (Upper panel CAC /CPM 2 / IOM-S 2) NIL IOM – AP 21 DC ESS BUS (Upper panel AFCS / FGCP CHAN 2 / IOM-AP 2) NIL IOM – DC 22 DC ESS BUS (Upper panel CAC / IOM-DC 22) NIL IOM – DC 23 DC ESS BUS (Upper panel CAC / IOM-DC 23) NIL SWM 2 DC ESS BUS (Upper panel CAC / SWM 2) NIL
Indicating & Recording: 3 SYSTEM MONITORING¶
Indicating & Recording: 3.1 AVNX CPM 1 LOSS-Alert¶
CONDITION VISUAL AURAL CPM 1 fail. - MC light flashing amber - AVNX CPM 1 amber message on EWD SC
Indicating & Recording: 3.2 AVNX CPM 2 LOSS-Alert¶
CONDITION VISUAL AURAL AVNX CPM 2 fail. - MC light flashing amber - AVNX CPM 2 amber message on EWD SC
Indicating & Recording: 3.3 AVNX CPM 1+2 LOSS-Alert¶
CONDITION VISUAL AURAL CPM 1 + 2 fail. - FWS NOT AVAIL amber message on Procedure Window - REFER TO QRH on Procedure Window SC
Indicating & Recording: 3.4 AVNX CPM 1 + IOM 22 LOSS-Alert¶
CONDITION VISUAL AURAL CPM 1 + IOM 22 fail. - MC light flashing amber - AVNX CPM 1 + IOM 22 amber message on EWD SC
Indicating & Recording: 3.5 AVNX CPM 1 + IOM 23 LOSS-Alert¶
CONDITION VISUAL AURAL CPM 1 + IOM 23 fail. - MC light flashing amber - AVNX CPM 1 + IOM 23 amber message on EWD SC
Indicating & Recording: 3.6 AVNX CPM 2 + IOM 12 LOSS-Alert¶
CONDITION VISUAL AURAL CPM 2 + IOM 12 fail. - MC light flashing amber - AVNX CPM 2 + IOM 12 amber message on EWD SC
Indicating & Recording: 3.7 AVNX CPM 2 + IOM 13 LOSS-Alert¶
CONDITION VISUAL AURAL CPM 2 + IOM 13 fail. - MC light flashing amber - AVNX CPM 2 + IOM 13 amber message on EWD SC
Indicating & Recording: 3.8 AVNX IOM 12 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 12 fail. - MC light flashing amber - AVNX IOM 12 amber message on EWD SC
Indicating & Recording: 3.9 AVNX IOM 13 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 13 fail. - MC light flashing amber - AVNX IOM 13 amber message on EWD SC
Indicating & Recording: 3.10 AVNX IOM 22 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 22 fail. - MC light flashing amber - AVNX IOM 22 amber message on EWD SC
Indicating & Recording: 3.11 AVNX IOM 23 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 23 fail. - MC light flashing amber - AVNX IOM 23 amber message on EWD SC
Indicating & Recording: 3.12 AVNX IOM 12 + IOM 13 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 12 + IOM 13 fail. - MC light flashing amber - AVNX IOM 12+13 amber message on EWD SC
Indicating & Recording: 3.13 AVNX IOM 12 + IOM 22 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 12 + IOM 22 fail. - MC light flashing amber - AVNX IOM 12+22 amber message on EWD SC
Indicating & Recording: 3.14 AVNX IOM 12 + IOM 23 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 12 + IOM 23 fail. - MC light flashing amber - AVNX IOM 12+23 amber message on EWD SC
Indicating & Recording: 3.15 AVNX IOM 13 + IOM 22 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 13 + IOM 22 fail. - MC light flashing amber - AVNX IOM 13+22 amber message on EWD SC
Indicating & Recording: 3.16 AVNX IOM 13 + IOM 23 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 13 + IOM 23 fail. - MC light flashing amber - AVNX IOM 13+23 amber message on EWD SC
Indicating & Recording: 3.17 AVNX IOM 22 + IOM 23 LOSS-Alert¶
CONDITION VISUAL AURAL IOM 22 + IOM 23 fail. - MC light flashing amber - AVNX IOM 22+23 amber message on EWD SC
Indicating & Recording: 3.18 AVNX FWS SGL CH-Alert¶
CONDITION VISUAL AURAL One of FWA detected faulty - MC light flashing amber - FWS SGL CH amber message on EWD SC
Indicating & Recording: 3.19 AVNX SGL SWITCH-Alert¶
CONDITION VISUAL AURAL Only one switch available. - MC light flashing amber - AVNX SGL SWITCH amber message on EWD SC
Indicating & Recording: 3.20 AVNX SWITCH 1+2 LOSS-Alert¶
CONDITION VISUAL AURAL AVNX switch lost - REFER TO QRH on Procedure Window SC
Indicating & Recording: 4 SCHEMATICS¶
Indicating & Recording: 4.1 Schematics¶
CPM 1 IOM /S1 IOM /AP1 IOM /DC 12 IOM /DC 13 SWM 1 AFCA 1 FWA 1 DCA 1 CMA 1 CPM 2 IOM /S2 IOM /AP2 IOM /DC 22 IOM /DC 23 SWM 2 SYSTEMS ANALOG DISCRETE A429 AFDX CAC 1 CAC 2 AFCA 2 FWA 2 DCA 2 A429 11 21 DU 1 FMA 2 RMA 2 DU 2 FMA 1 RMA 1 DU 3 DU 4
DU1 DU2 DU3 DU4 DU5
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+----+----+----+----+-- AFDX --> [CAC 1] <----> [CAC 2]
^ ^
+-- A429 buses --+
+-- ARINC inputs-+
+-- analog ------+
+-- discrete ----+
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AIRCRAFT SYSTEMS
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 General¶
The Control and Display System (CDS) is the main interface between cockpit flight crew and avionic systems. The CDS enables the flight crew to access to : - Flight information - Aircraft environment - Aircraft system status - Aircraft alerts, procedures, check lists. The CDS is composed of 5 display units, 6 control panels, 2 MCDUs and 2 switching panel. The CDS is managed by two Core Avionics Cabinet (CAC 1&2). Data to be displayed by the CDS are organized in “format” so as to provide a coherent set of information. There are three main formats: - The Primary Flight Display (PFD) format that groups data related to the flight and auto flight - The Multi-Function Display (MFD) format that groups data mainly related to navigation, communication and aircraft system status - The Engine and Warning Display (EWD) that groups data related to flight control, engine primary parameters and crew alerting. Each format is divided in several windows. The upper window of MFD can display several pages.
Indicating & Recording: 1.2 Nominal Format Configuration¶
UP 5 0 DN UP 3.0 L R L I A R U D TO CONF TEST OK SEL LAB LAB ELEC SMOKE SEL ON ON PACK VALVE 2 PACK VALVE 1 PREVIOUS CHOICE SMOKE PERSISTS CAUTION 2 CAUTION 3 CAUTION 4 CAUTION 5 CAUTION 6 CAUTION 7 CAUTION 8 CAUTION 9 CAUTION 10 CAUTION 11 CAUTION 12 WARNING 2 WARNING 1 CAUTION 1 EVACUATION OF AIR CONDITIONING SMOKE MAY TRIGGER ELECTRICAL SMOKE WARNING. DISREGARD IT ENG 1 + 2 PARAMETERS 123456789012345678901234567890123456 IF NORMAL CONDITIONS IF ANY ANOMALY OCCURS MONITOR CAREFULLY TAT SAT LAB LABLBS LBS FOB GW °C °C FT13 H 52 12 52 H 13 : LO PITCH SGL CH 500 ITT °C ISN 500 0 AUTO FTR PROP BRK NP% 2 N N 2 SGL CH TQ% LOOP 360.0 CLB FIRE 1 50 100 0 UPTRIM LOOP FIRE 2 XXX 50 100 0 UPTRIM 100 PWR B + C + 40.0 500 500 LO PITCH FUEL USED LBS P I T C H F L A P LAB CAUTION 13 CAUTION 14 CAUTION 15 CAUTION 16 TO INHIB STATUSWAIT 10 SEC 999.0 NAC OVHT 0 PWR B + C + 025 BRG ° 50 10 : 3.0 NM 10 +03 RNG WX WAIT 025 TOWPT 200 GS 250 TAS T + VOR2 250.30 40.5 NM H ADF1 1250.5 AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 HDG HDG 040° NM 5 A +03 +05 A OFST L 18.3 ANTI ICING FUEL XFEED DE ICING NO DEVICE SEAT BELT ENG AIRFRAME HORN SIDE WINDOWS PROP 1 1 2 2 1 2 TERR NAV DR AUTO TAT 1 TAT 2 TO DATA ENG OAT TAT 1 + TAT SEL T/O TQ GND SAT +21 °C PWR B + C + PWR B + C + PWR B + C +
PFD1 MFD EWD MFD PFD2 PFD1 MFD EWD MFD PFD2 N MDH 160 155 M 99A ICING ICING AOA HLD SPD ALT 2 1 3 200 220 240 180 3 2 1 205 900 MSG TERM 40 . 5 012 ID_FMS FMS1 29 . 20 QNH NM TA ONLY ° ADF2 1250.5 M VOR1 250.30 40.5 NM CHECK HDG 0 M 25 15315 FL 20 157 60 40 80M 20 G 30000 FL R V2 F 20 10 10 DH 19999 0 10 10 F 1 N MDH 160 155 M 99A ICING ICING AOA HLD SPD ALT 2 1 3 200 220 240 180 3 2 1 205 900 MSG TERM 40 . 5 012 ID_FMS FMS1 29 . 20 QNH NM TA ONLY ° ADF2 1250.5 M VOR1 250.30 40.5 NM CHECK HDG 0 M 25 15315 FL 20 157 60 40 80M 20 G 30000 FL R V2 F 20 10 10 DH 19999 0 F 1 2750 2750 G-VAR -07 -07 20 20 10 10 20 20 025 BRG ° 50 10 : 3.0 NM 10 +03 RNG WX WAIT 025 TOWPT 200 GS 250 TAS T VOR2 250.30 40.5 NM H ADF1 1250.5 AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 HDG HDG 040° NM 5 A +03 +05 A OFST L 18.3 ANTI ICING FUEL XFEED DE ICING NO DEVICE SEAT BELT ENG AIRFRAME HORN SIDE WINDOWS PROP 1 1 2 2 1 2 TERR NAV DR AUTO TAT 1 TAT 2 TO DATA ENG OAT TAT 1 + TAT SEL T/O TQ GND SAT +21 °C G-VAR -07 -07
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 Display Units¶
The Display Units DU1, DU2, DU3, DU4 and DU5 show the display images necessary for the control, monitoring and safe navigation of the aircraft. They have interfaces with most of the aircraft systems.
B + - C + - 1 1 2 3 5 4 6 PWR 1 Luminance Sensors For integrated automatic dimming (illumination data is provided to the core processing function in order to adjust the brightness command for the display backlighting function).
2 Contrast Setting 3 Brightness Setting 4 Power Switch 5 ON/OFF Light White when ON, dark when OFF 6 Compact Flash Card slot The slots are used to insert the data cards containing performance, navigation, and company specific databases. All the DU, are equipped with the same slot, but only the DU 2 and 4, dedicated for the FMA and RMA, have data card. COLOR CODING : Refer to Cockpit Philosophy
Indicating & Recording: 2.2 EFIS Control Panel¶
MF D PERF ND MISC SYS BRG1 BRG2 N A V - + RANGE FORMAT P R O C RCL CLR PROC MENU VID MAP MF D PERF ND MISC SYS BRG1 BRG2 N A V - + RANGE FORMAT P R O C VID MAP EFCP-R EFCP-L MFD CONTROL NAV CONTROL WD CONTROL
MAN DEL The EFIS Control panel enables to control the display of MFD pages, to control some Navigation Display (ND) functionalities and to control the Warning Display (WD) format (through the Flight Warning Application). The two EFCPs are on the center pedestal. EFCP-L and EFCP-R are divided in three groups of dedicated controls: - MFD control - NAV control - Warning Display (WD) control
Indicating & Recording: 2.3 MFD Page¶
This part of the EFCPs enables the selection of the different MFD pages:
PWR B + - C + - VIRTUAL CONTROL PANEL WINDOW MFD UPPER WINDOW MFD MF D PERF ND MISC SYS VID MAP MEMO PANEL DISPLAY
Indicating & Recording: 2.4 SYST Page¶
Four different system pages can be displayed on the MFD, by pressing the SYS pb consecutively.
MF D PERF ND MISC VID MAP 21 °C PACK BLEED AUTO HIGH FLOW AIR RECIRC PACK BLEED AUTO OXY SUPPLY PAX CREW P PSI 0 6 0 8 8.00 VS FT/MIN 0 2000 0 2000 MAN ALT TARGET CAB ALT FT FT 5200 5200 ELEC SMK FWD SMK LAV SMK AFT COMPT SMK BTC TRU CHG OFF SVCE BUS OFF UTLY BUS 1 SHED UTLY BUS 2 SHED EMER BAT V 28 DC STBY BUS EMER BUS ESS BUS MAIN BAT V 28 CHG OFF INV 1 INV 2 FAULT AC STBY BUS AC BUS 1 AC BUS 2 OFF OFF ACW-HYDRAULIC ENGINE CABIN AC-DC ELECTRIC DC BUS 1 OFF HOT BUS HOT BUS DC BUS 2 OFF DC GEN 2 OFF DC GEN 1 OFF X FEED AVAIL EXT AC ON BTC GREEN HYD TRU ACW BUS 2 3000 PSI NORM BRK LDG GEAR EMER BRK ACCU FLAPS SPOILERS PSI 3000 STRG N/W PROP BRK 3000 PSI ACW BUS 1 DC STBY FAULT ACW GEN1 AUX HYD MAIN BAT FAULT ACW GEN2 BLUE HYD 12, 5, 0, 17 V2.2.1 0 260 FEED LO PR XFR FUEL TANK RUN 250 KG 1170 TEMP °C 31 LO PR FEED FUEL FLOW KG/H 90.4 1+2 KG/MN ITT °C ITT °C X START FAIL ENGINE LO PR OIL PRESS PSI TEMP °C 0 NH % NL % 60 0 64.0 60 0 NAC OVHT LO PR 0 OIL 0 PRESS PSI TEMP °C START
---¶
--- . - °C -54 RUN KG 1170 TEMP °C 29 CLOG
SYS
Indicating & Recording: 2.5 ND Page¶
Three different ND formats can be displayed on the MFD, by depressing the ND pb on the EFCP and then selecting the format using the FORMAT rotary knob on the EFCP.
F D PERF MISC SYS VID MAP 025° 50 10 : 3.0 3 33 10 AUTO LFBE LFBA 355 80 ° / AGN NEXTWPT +05 025 TOWPT 200 GS TAS NM M ND +05 +05 +03 RNG WAIT G-VAR T +10 3 . VOR2 250.30 40.5 NM H VOR1 250.30 40.5 NM H AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 HDG HDG 040° NM L 1.20 5
250
Indicating & Recording: 2.6 PERF Page¶
The performance page can be displayed, by pressing on the PERF pb.
ZFW 17000 KG FOB 2998 KG GW 19998 KG RESERVE 500 KG T/O CG 25.0 % FF FACTOR 0.0 % T/O TRIM 1.3 UP V1 106 VR 110 V2 NORMAL VMLB0 ICING NORMAL 133 158 VMHB FLAPS FULL V APP FLAPS FULL WIND 0 / ° 360 106 A/C DATA TAKE OFF T/O TQ BLEED_OFF 90.0% BLEED_ON 90.0% APPROACH ICING NORMAL 104 113 ICING NORMAL 104 113 ANTI ICING DE ICING B + C + PWR TO DATA ENG OAT RESET FUEL USED ICING CONDITIONS CONFIRM T/O DATA F D PERF ND MISC SYS VID MAP M
Indicating & Recording: 2.7 NAV Control¶
This part of the EFCPs enables to control navigation information display on PFD and ND format :
N MDH 160 155 M 99A ICING ICING AOA HLD SPD ALT 2 1 3 200 220 240 180 3 2 1 205 900 MSG TERM 40 . 5 012 ID_FMS FMS1 29 . 20 QNH NM TA ONLY ° ADF2 1250.5 M VOR1 250.30 40.5 NM CHECK HDG 0 M 25 15315 FL 20 157 60 40 80M 20 G 30000 FL R V2 F 20 10 10 DH 19999 0 10 10 F 1 2750 025 BRG ° 50 10 : 3.0 NM 10 +03 RNG WX WAIT 025 TOWPT 200 GS 250 TAS T VOR2 250.30 40.5 NM H ADF1 1250.5 AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 HDG HDG 040° NM 5 A +03 +05 A OFST L 18.3 ANTI ICING FUEL XFEED DE ICING NO DEVICE SEAT BELT ENG AIRFRAME HORN SIDE WINDOWS PROP 1 1 2 2 1 2 TERR NAV DR AUTO TAT 1 TAT 2 TO DATA ENG OAT TAT 1 + TAT SEL T/O TQ GND SAT +21 °C -07 -07 G-VAR
BRG1 BRG2 N A V - + RANGE FORMAT (EFCP NAV) This area is composed of four pb and one rotary knob: - BRG1(2) pb By pressing it, VOR1(2) or ADF1(2) or no indication is displayed. - RANGE “+” (“-”) pb By pressing it, the range of the Navigation Display page is increased (decreased). - FORMAT rotary knob By rotating it, the format of the ND is changed: ROSE, ARC, PLAN. On the flight guidance coupled side, the ND is displayed by default on the MFD. A mini ND page (ROSE or ARC) is displayed on the PFD, in place of the HSI when the flight crew changes the ND to another page (system for example). In this case the format of the mini ND can the changed by the rotary knob. ND format display is automatic for the following scenarios: - ARC is automatically selected on ND / mini ND if a TERRAIN alert is activated - ROSE is automatically selected on ND / mini ND if a TRAFFIC alert is activated - ROSE is automatically selected on mini ND when ND in PLAN format is transferred on mini ND. Mini ND accepts only ARC and ROSE formats.
250.30 VOR2 1250.5 ADF 1 A A 40.5 ° ° 06.12 015 85 200 TAS GS 5 GPS1 30 33 N W 24 21 S 15 12 E 6 ° AUTO 250 80 / 025 03 NM 30.45 10 355 E N HDG 040° T +10.3° H G-VAR WAIT RNG TA 25.3NM / +03 RA 25.3NM / +03 MF D PERF ND MISC SYS BRG1 BRG2 N A V RANGE FORMAT VID MAP - + 10 +05 RNG WX WAIT 025 T +10 3 . VOR2 250.30 40.5 NM H ADF1 1250.5 AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 NM L 1.20 5 A +03 ND ARC MODE ND ROSE MODE 3 33 A ° 205 80 ° / 200 250 GS TAS +03 025 50 10 : 3.0 TOWPT NM BRG ° G-VAR HDG NAV 355 80 ° / 200 250 GS TAS AIRPORT NAVAID N S W E 10 5 025 50 10 : 3.0 TOWPT NM ° DR AGN NEXTWPT L 1.20 NM ND PLAN MODE BRG AUTO 040° LFBE LFBA
Indicating & Recording: 2.8 WD Control¶
This part of the EFCP enables the cockpit crew to manage alerts and procedures displayed on EWD format and generated by the Flight Warning System:
PWR B + - C + - ALERT ENGINE DISPLAY PROCEDURE EWD PERMANENT DATA FLAP BRAKE MSG TRIM TEST STATUS P R O C C AS RCL MAN DEL CLR PROC MENU The WD control right part of the EFCP-L is unique and thus used by both cockpit crew. Note CLR pb and RCL pb also manage the procedure window. Refer to FWS Description chapter.
EFCP LEFT MF D PERF ND MISC SYS BRG2 P R O C VID MAP EFCP RIGHT MF D PERF ND MISC SYS BRG2 P R O C C AS VID MAP - + RANGE FORMAT N A V BRG1 BRG1 N A V - + RANGE FORMAT MAN DEL PROC MENU RCL CLR 1 2 3 5 6 4 1 First Officer Procedure Control pb Enables to move on upward/downward line in the procedure window and to validate actions. 2 MAN DEL By pressing on it, procedures inserted manually are deleted. 3 PROC MENU By pressing on it, procedure menu is displayed in the procedure window. 4 Captain Procedure Control pb Enables to move on upward/downward line in the procedure window and to validate actions. 5 CLR pb By pressing on it, a clearable alert displayed on the Alert Window is cleared.
6 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.
Indicating & Recording: 2.9 MCP¶
The Multipurpose Control panel enables cockpit crew to control the virtual control panel format on MFD. 2 MCPs, one on each side (pilot/copilot) enables an independent setting on each VCP (on MFD 1 and MFD 2 respectively). The VCP is functionally interfaced with the Radio Management System and the Flight Management. ENT COM NAV SURV ESC 1 2 3 4 5 6 7 8 9 0 MCP PWR B + - C + - MFD UPPER WINDOW VIRTUAL CONTROL PANEL WINDOW MFD MEMO PANEL DISPLAY
4 3 2 1 7 5 1 2 3 4 5 6 7 8 9 0 6 COM NAV SURV ENT 14, 0, 4, 3 V13.2 L_CB_00000000_0000000_000_00_00
ESC
1 COM pb Enables the selection of the COM pages on the VCP. Two pages: - VHF - HF 1 2 NAV pb Enables the selection of the NAV pages on the VCP. Three pages: - VOR - ADF - ND OVLY (ND Overlay) 3 SURV pb Enables the selection of the surveillance pages on the VCP. Two pages: - XPDR - TCAS 4 Enter pb Enables validating the selection area. 5 Multi Directional Pad Enables choosing the selection area. 6 ESCape Key Enables to exit current VCP function. 7 Numeric Key Board Enables setting manually the frequency.
Indicating & Recording: 2.10 ICP¶
The ICP is linked to the PFD format, it controls managed speed selection and setting (through the Auto Flight Control Application), baro setting and DH/MDA setting. Each ICP is connected to one DU (1 or 5) and enables an independent setting and display on PFD 1 and PFD 2. The ICP is split in 2 zones: SPEED TARGET control and BARO SETTING and DH control. PWR B + - C + - FLIGHT MODE ANNUNCIATOR A I R S P E E D A L T I T U D E ATTITUDE DISPLAY INDICATOR NAVIGATION AREA PFD AUTO/MAN SPD TGT BARO SET PUSH STD DH MDA SPEED TARGET CONTROL BARO SETTING CONTROL ICP V E R T I C A L S P E E D SEL
Speed Target Area The SPEED TARGET area is composed by 1 AUTO/MAN pb and 1 rotary knob. The rotary knob enables setting indicated air speed target. The AUTO/MAN pb enables setting Auto/man mode : - Auto (automatic): the speed target is calculated by the FMS (Magenta). - Man (manual) : the speed target is set by the CAPT / F/O (Cyan). The speed target is displayed on each PFD. Baro Setting The BARO SET internal rotary knob enables barometric pressure setting. By pushing the rotactor button, the barometric setting is set to STD setting. The BARO SET is displayed on each PFD.
DH/MDA Rotary knob Outer knob enables to select between DH or MDA. Inner knob enables to set: - Decision Height from 0 ft to 990 ft. (radio-altitude) - Minimum Descent Altitude from 0 ft to 19 990 ft. (baro-altitude) Note There is no display of negative MDA.
Indicating & Recording: 2.11 MCDU¶
There are two Multi-purpose Control and Display Units (MCDUs), one on captain side, and one on first officer side. The MCDU enables to interface with the following systems: - FMS (Flight Management function) - ACARS (if installed) (Aircraft Communication Addressing and Reporting System) - RMS (Radio Management System) - ACMS (Aircraft Condition Monitoring System) - CMS (Central Maintenance System/function) The front face consists of a pb keyboard and a multi-function alphanumeric display
4 V V V V V V V V V V V V RETURN NAV1 A C T I V E 114.05 DME HOLD / OFF STBY PRESET TUNE MODE / MAN AUTO 114.05 ON TEST NEAREST
It includes: - An alphanumeric keyboard - Function and line keys - Select keys - Annunciators - A display brightness control - A 5.5” screen (14 lines with 24 characters per line). The MCDUs are located on the center pedestal.
Indicating & Recording: 2.12 Switching Control¶
The system switching enables to switch displays on the different DUs.
DISPLAY PFD /EWD /MFD ATT/HDG ADC F/O SWITCHING CAPT/2 SYS 1 CAPT/2 SYS 1 PFD /EWD /MFD 2 1 ATT/HDG ADC F/O/1 SYS 2 CAPT SWITCHING F/O/1 SYS 2
DISPLAY
1 CAPT switching control panel (display successively PFD/EWD/MFD when pb pressed in 2 F/O switching control panel (display successively PFD/EWD/MFD when pb pressed in. Note Switching occurs primarily on DU 2/4, it there are inoperative switching occurs on DU 1/5
Indicating & Recording: 3 ELECTRICAL SUPPLY¶
Indicating & Recording: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) DU 1 DC BUS 1 (on overhead panel DU 1 PFD) NIL DU 2 DC EMER BUS (on overhead panel DU 2 MFD) BACK UP SUPPLY HOT MAIN BAT BUS (on overhead panel DU 2 MFD AUX) NIL DU 3 DC BUS 1 (on overhead panel DU 3 EWD) NIL DU 4 DC ESS BUS SECT 1 (on overhead panel DU 4 MFD) BACK UP SUPPLY HOT EMER BAT BUS (on overhead panel DU 4 MFD AUX) NIL DU 5 DC BUS 2 (on overhead panel DU 5 PFD) NIL EFCP-L DC EMER BUS (on overhead panel EFCP / CAPT) NIL EFCP-R DC ESS BUS SECT 2 (on overhead panel EFCP / F/O) NIL MCP 1 DC EMER BUS (on overhead panel NAV / COM / SURV / CAPT / MCP) NIL MCP 2 DC ESS BUS SECT 1 (on overhead panel NAV / COM / SURV / F/O / MCP) NIL ICP 1 DC EMER BUS (on overhead panel ADC 1 / EMER SPLY / ICP CAPT) NIL
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) ICP 2 DC BUS 2 (flight) (on overhead panel ADC 2 / ICP F/O / FLT SPLY) DC EMER BUS (Ground) (On overhead panel ADC 2 / ICP F/O / GND SPLY) NIL MCDU 1 DC STBY BUS (on overhead panel NAV / COM / SURV / CAPT / MCDU) NIL MCDU 2 DC BUS 2 (on overhead panel NAV / COM / SURV / F/O / MCDU) NIL
Indicating & Recording: 4 SYSTEM MONITORING¶
Indicating & Recording: 4.1 DU DISCREPANCY-Alert¶
CONDITION VISUAL AURAL DU with corrupted parameters - MC light flashing amber - DUs DISCREPANCY amber message on EWD SC
Indicating & Recording: 4.2 DU TEMP HI-Alert¶
CONDITION VISUAL AURAL One DU TEMP high - MC light flashing amber - DU TEMP HI amber message on EWD SC
Indicating & Recording: 4.3 SEVERAL DUs TEMP HI-Alert¶
CONDITION VISUAL AURAL More than one DU TEMP HI - MC light flashing amber - DUs TEMP HI amber message on EWD SC
Indicating & Recording: 5 SCHEMATIC¶
Indicating & Recording: 5.1 Schematic¶
switching panel / EFCP / MCP / ICP command paths
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v
DU1 DU2 DU3 DU4 DU5
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AFDX network
/ \
[CAC 1] [CAC 2]
^ ^
ADC1 AHRS1 AHRS2 ADC2
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aircraft equipment
IESI and both MCDUs connect to the associated display/control side.
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 GENERAL¶
Indicating & Recording: 1.1.1 General¶
The PFD is divided into 6 areas: - Flight Mode Annunciator Area (FMA Area) - Airspeed area - Attitude Display Indicator (ADI Area) - Altitude area - Vertical speed area - Navigation area (HSI or ND). The PFD is located on: - In normal condition, the PFD 1 (CAPT side) and PFD 2 (F/O side) are respectively on the DU 1 and DU 5 - In abnormal condition (manual or automatic switching), PFD can be displayed on DU 2 (CAPT side) and/or DU 4 (F/O side). It is controlled by : - FGCP (Flight Guidance Control Panel) - ICP (Index Control Panel) - EFCP (EFIS Control Panel) Note For AHRS system description Refer to DESCRIPTION
PFD PWR B + - C + - FLIGHT MODE ANNUNCIATOR A I R S P E E D A L T I T U D E V E R T I C A L S P E E D ATTITUDE DISPLAY INDICATOR NAVIGATION AREA LO ICING PROT LEVEL AP FD DUAL ICING AOA HLD SPD TCS V-FP VOR YAW AUTOTRIM FAIL RNPAR REDUCE SPD FD DISAGREE 2 1 6 6 2 1 -10 -9 20 15760 40 80M 2750 010 M 999 15315 FL M 15315 1500 C L NEG C E C K A L T H AHRS1 DGD AHRS1 ADC1 20 20 10 10 10 10 I RA 20 20 MDA 10500 DH 900 CHECK ATT 200 220 180 IAS SEL 195 C H E C K I A S FR V2 F TCAS FAIL XPDR2 ALT OFF 24.5 000 CRS FMS1 NM ° CCCCCC H 00 CHR :00 STD TAS 250 GS 200 000° HDG °/ 80 355 RNP 1.0 N ADF2 1250.5 A ILS1 VOR1_ID 40.5 NM A H RNG WX WAIT TERR G-VAR -07 -07 MSG TERM OFST LPV 5 10 141 PWR B + C + PFD 000 240
Indicating & Recording: 1.1.2 Displays¶
Displays are: In the FMA Area Auto Flight data Icing status In the ADI, Airspeed, Altitude and Vertical Speed Areas Air Data Inertial Data FMS Data Radio Altimeter data ILS and Marker data T2CAS and Transponder status
In the Navigation Area Horizontal Situation Indicator (HSI): - FMS data - Radio NAV (VOR, ILS, ADF, DME) data - Auto Flight Target - Inertial data Mini-Navigation Display (ND): - FMS data - Radio NAV (VOR, ILS, ADF, DME) data - Auto flight target - T2CAS data - Weather Radar data and status
PWR B + - C + - FLIGHT MODE ANNUNCIATOR A I R S P E E D A L T I T U D E V E R T I C A L S P E E D ATTITUDE DISPLAY INDICATOR NAVIGATION AREA PFD
Indicating & Recording: 1.2 FLIGHT MODE ANNUNCIATOR¶
Indicating & Recording: 1.2.1 Flight Mode Annunciator (FMA)¶
For more information about Flight Mode Annunciator, Refer to DSC.22.1.2.1 General.
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 ATTITUDE DISPLAY INDICATOR¶
Indicating & Recording: 2.1.1 ADI Normal Display¶
(Applies: 1054;1237-1283)
99 MDA 10 20 10 20 10 20 20 V I 900 DH 900 DH 2 1 3 4 5 6 7 8 9 10 11 10 PFD 6 - SELECTED HEADING INDEX: ON THE HORIZON WHEN FD BARS ARE NOT DISPLAYED 12 1 Aircraft Symbol The fixed aircraft symbol is black outlined in yellow. Aircraft pitch and roll attitudes are displayed in relationship between this symbol and the movable horizon. 2 Roll Attitude Displays current roll attitude through a movable index and fixed scale reference marks at 10, 20, 30, 45 and 60 degrees. Roll indexes are displayed as yellow triangles. 3 Slip/Skid Indicator Lateral acceleration index indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index.
4 Horizon and Pitch Scale Both move with respect to the aircraft symbol to display current pitch and roll attitude. Sky zone is colored blue and earth zone brown. In case of high pitch value a horizon or earth reference always remains in sight. If pitch exceeds +/ - 25 ° large red chevron indicates excessive attitude and direction to follow to resume normal attitude. Pitch scale is white and has reference marks every 2.5 ° up to 20 ° up or down, then marks at 25, 30, 50, 80 °.
50 30 20 10 50 30 20 10 50 30 20 10 50 30 20 10 PFD 5 Flight Director Command Bars (Green) Display computed commands to capture and maintain a desired flight path. The horizontal bar is related to vertical modes and the vertical to lateral ones. The commands are satisfied by flying the aircraft symbol to the command bars. 6 Selected Heading index The selected heading is indicated by a perpendicular cyan line when flight director commands bar are not displayed.
7 Vertical Deviation Indication Vertical deviation is from ILS source or FMS source, it is displayed on the right side of the ADI: - ILS source When navigation source is V/ILS, deviation pointer is displayed as a cyan diamond. Cyan letter “G” is displayed in the right upper corner of the ADI. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - GPS source (LPV) When LPV approach is performed, Vertical deviation from GPS source is displayed as a cyan diamond. Cyan letter “L” is displayed in the right upper corner of the ADI. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - FMS source When navigation source is FM, deviation pointer is displayed as a magenta open rectangle. Magenta letter “V” is displayed in the right upper corner of the ADI. The scale of the Vertical deviation (or VDEV) is two white lines each side from yellow reference line. The full deflection represents +/ - 500 ft. When the deflection value exceeds the scale, only a partial view of the open rectangle is displayed. In case of failure the deviation scale is crossed in red (Refer to ADI Warning Displays).
8 Lateral Deviation Indication Lateral deviation can be either from ILS source or FMS source: - V/ILS source When navigation source is V/ILS, deviation pointer is cyan diamond with deviation scale dedicated to approach operations. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - GPS source (LPV) When LPV approach is performed, Vertical deviation from GPS source is displayed as a cyan diamond with deviation scale dedicated to approach operations. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - FMS source When navigation source is FM, deviation pointer is displayed as a magenta open rectangle. The scale is two white dots each side from a yellow reference line. The deviation value associated with the scale varies according to the flight phase and corresponding RNP value. The full deflection is equals present RNP considered by FMS with a maximum of 5 Nm. Deviation between each dot is equal to half of RNP value. For example : o In Terminal area, the value of the full deflection is 1 Nm (i.e. 0.5 Nm between each dot) o In Approach area, the value of the full deflection is 0.3 Nm (i.e. 0.15 Nm between each dot). When the lateral deviation value exceeds the scale, only a partial view of the open rectangle is in view. In case of failure the deviation scale is crossed in red (Refer to ADI Warning Displays). 9 DH Indication and Annunciation The selected DH is displayed in cyan in the bottom left corner. The central rectangle displays RA (amber) readout at decision height. Maximum selectable DH is 999 ft. 10 Minimum Decision Altitude Displayed in cyan, the range being from 0 ft to 19 999 ft with 1 ft increments. If baro altitude is equal or less than selected MDA, the altitude numeric readout is displayed in amber. 11 Radio Altitude Numeric value displayed from 0 to 2 500 ft (762 m) in green digits. 12 MKR Indication Displays marker symbols. (Refer to 34.5.1.4 MARKER)
(Applies: 1096-1160)
99 MDA 10 20 10 20 10 20 20 V I 900 DH 900 DH 2 1 3 4 5 6 7 8 9 10 11 10 PFD 6 - SELECTED HEADING INDEX: ON THE HORIZON WHEN FD BARS ARE NOT DISPLAYED 12 1 Aircraft Symbol The fixed aircraft symbol is black outlined in yellow. Aircraft pitch and roll attitudes are displayed in relationship between this symbol and the movable horizon. 2 Roll Attitude Displays current roll attitude through a movable index and fixed scale reference marks at 10, 20, 30, 45 and 60 degrees. Roll indexes are displayed as yellow triangles. 3 Slip/Skid Indicator Lateral acceleration index indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index. 4 Horizon and Pitch Scale Both move with respect to the aircraft symbol to display current pitch and roll attitude. Sky zone is colored blue and earth zone brown. In case of high pitch value a horizon or earth reference always remains in sight. If pitch exceeds +/ - 25 ° large red chevron indicates excessive attitude and direction to follow to resume normal attitude. Pitch scale is white and has reference marks every 2.5 ° up to 20 ° up or down, then marks at 25, 30, 50, 80 °.
50 30 20 10 50 30 20 10 50 30 20 10 50 30 20 10 PFD 5 Flight Director Command Bars (Green) Display computed commands to capture and maintain a desired flight path. The horizontal bar is related to vertical modes and the vertical to lateral ones. The commands are satisfied by flying the aircraft symbol to the command bars. 6 Selected Heading index The selected heading is indicated by a perpendicular cyan line when flight director commands bar are not displayed.
7 Vertical Deviation Indication Vertical deviation is from ILS or FMS source, it is displayed on the right side of the ADI. - ILS source When navigation source is V/ILS, deviation pointer is displayed as a cyan diamond. Cyan letter “G” is displayed in the right upper corner of the ADI. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - GPS source (LPV) When LPV approach is performed, Vertical deviation from GPS source is displayed as a cyan diamond. Cyan letter “L” is displayed in the right upper corner of the ADI. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - FMS source When navigation source is FM, deviation pointer is displayed as a magenta open rectangle. Magenta letter “V” is displayed in the right upper corner of the ADI. The scale of the Vertical deviation (or VDEV) is two white line each side from yellow reference line and varies according to the flight phase: o In the FMS approach phase (background in black), the full deflection represents +/ - 150 ft o In other flight phase (transparent background), the full deflection represents +/– 500 ft. When the deflection value exceeds the scale, only a partial view of the open rectangle is displayed. In case of failure the deviation scale is crossed in red (Refer to ADI Warning Displays).
8 Lateral Deviation Indication Lateral deviation can be either from ILS source or FMS source. - V/ILS source When navigation source is V/ILS, deviation pointer is cyan diamond with deviation scale dedicated to approach operations. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - GPS source (LPV) When LPV approach is performed, Vertical deviation from GPS source is displayed as a cyan diamond with deviation scale dedicated to approach operations. The scale is two white dots each side from a yellow reference line. When the deflection value exceeds the scale, only a partial view of the diamond is displayed. - FMS source When navigation source is FM, deviation pointer is displayed as a magenta open rectangle. The scale is two white dots each side from a yellow reference line. The deviation value associated with the scale varies according to the flight phase and corresponding RNP value. The full deflection is equals present RNP considered by FMS with a maximum of 5 Nm. Deviation between each dot is equal to half of RNP value. For example : o In Terminal area, the value of the full deflection is 1 Nm (i.e. 0.5 Nm between each dot) o In Approach area, the value of the full deflection is 0.3 Nm (i.e. 0.15 Nm between each dot). When the lateral deviation value exceeds the scale, only a partial view of the open rectangle is in view. In case of failure the deviation scale is crossed in red (Refer to ADI Warning Displays). 9 DH Indication and Annunciation The selected DH is displayed in cyan in the bottom left corner. The central rectangle displays RA (amber) readout at decision height. Maximum selectable DH is 999 ft. 10 Minimum Decision Altitude Displayed in cyan, the range being from 0 ft to 19 999 ft with 1 ft increments. If baro altitude is equal or less than selected MDA, the altitude numeric readout is displayed in amber. 11 Radio Altitude Numeric value displayed from 0 to 2 500 ft (762 m) in green digits. 12 MKR Indication Displays marker symbols. (Refer to 34.5.1.4 MARKER)
Indicating & Recording: 2.1.2 ADI Warning Display¶
ATT FAIL CHECK ATT --- DH ----- MDA AHRS1 ADC1 4 PFD 2 1 3
1 AHRS Reversion Flag Yellow AHRS 1(2) in the left upper corner of the ADI indicates in case of one AHRS failure which is remaining and is used for computation of reference data. 2 ADC Reversion Flag Yellow ADC 1(2) in the upper left corner of the ADI indicates in case of one ADC failure which is remaining and is used for computation of air data. 3 CHECK ATT Flag Flashes for 9 s, then steady amber message. Will be displayed on PFD when a discrepancy for pitch or roll data between AHRS 1 & 2 is detected. 4 ATT FAIL Flag ADI part of PFD will turn black with a white ADI outline, ATT FAIL in red will be displayed. ATT FAIL will be displayed in case of dual AHRS failure.
Indicating & Recording: 2.2 AIR SPEED DATA¶
Indicating & Recording: 2.2.1 Air Speed Data¶
5 14 1 232 CRUISE 200 240 260 220 140 180 200 120 140 APPROACH F 15° 160 F 1 2 120 160 180 100 F 115 APPROACH F 30° 140 1 11 10 9 13 12 80 120 140 60 F 119 BEFORE ROTATION 3 4 8 7 6 R V2 100 140 160 80 F 119 INITIAL CLIMB 3 5 V2 PFD 1 120 100 141 162 231 15
1 Maximum Speed - Speed Limit Band Limit band indicates the maximum speed to not exceed according to aircraft configuration. Speed Limit band is represented along the IAS tape, on the right side border, by a red band, with white oblical dashes, extended from the VMAX value to the top of the speed scale. Width is larger than selected speed bug. As example: Cruise approach FLAPS 15 approach FLAPS 30 VMO VFE FLAPS 15 VFE FLAPS 30 2 Flaps Extension Speed (VFE NEXT) Indicates the maximum speed to command the flaps extension to the next flap lever position and avoid damaging the flaps. The bug is represented by two amber horizontal lines. 3 Flaps Retraction Speed Bug VmLB0 bug : - Indicates the value of the minimum speed in Low Bank conditions (FLAPS LEVER = 0°). - Normal condition VmLB0 normal: The indication is composed of a white triangle. - Icing conditions VmLB0 Icing: The indication is composed of an amber triangle. 4 Target Speed Bug Gives the target airspeed in cyan when it is manually selected. Cyan “M-shape” pointer displayed along the speed scale for manual selection. Magenta “M-shape" pointer displayed along the speed scale for an AUTO selection (speed computed by FMS). 5 Shaker Speed Speed below which the Flight Controls equipment activates the stick shaker. VMIN is represented along the speed tape, on the right side border, by a red band extended from the VMIN value to the bottom of the speed scale. Width is larger than selected speed bug. 6 V1 Indication V1 Bug: - Indicates the value of the decision speed on the speed scale. - The indication is composed of a horizontal cyan line followed by a cyan “1" label. V1 readout: - Indicates the value of the decision speed when value is out of the speed scale. - Cyan readout displayed on the top or bottom right of the speed scale. 7 VR Indication Indicates the value of the rotation speed (VR) on the speed scale. The VR bug is a horizontal cyan line followed by a space and a cyan “R“ label.
8 V2 Indication Indicates the value of the initial climb speed on the speed scale. The indication is composed of a cyan triangle followed by a cyan “V2" label. 9 Flaps Retraction Speed Bug (FLAPS 30) ; FLAPS Position > 15° Normal conditions : White line (VmHB15 normal), with white “F" on the right side. Icing conditions : Amber line (VmHB15 icing), with amber “F" on the right side. 10 Airspeed Scale A vertical tape included in a grey rectangle with graduations every 10 kt, with associated numbers every 20 kt, from 30 kt to 450 kt. The displayed part of the tape shall cover +/- 42 kt around the current aircraft computed airspeed. A yellow line represents the airspeed reference on the centre of the tape. 11 Airspeed Trend Provides the predicted airspeed in 10 s if acceleration remains constant. The trend is a yellow arrow extending from the airspeed reference line to the predicted airspeed value on the speed scale, with a filled up end of arrow. 12 VmHB in Landing Configuration The bug indicates the VmHB in landing configuration. The indication is composed of a green triangle. 13 Minimum Operational Speed Mini VOPS is represented along the IAS tape, on the right side border, by an empty amber band extending from the Mini VOPS value to the bottom of the speed scale or to Vmin band. Width is larger than selected speed bug. 14 Numeric Airspeed Read Out Display is in knots on the speed scale. Numeric airspeed read out is displayed when IAS is above 30 kt. 15 IAS target value Indicates the IAS target value, which can be either computed by FMS or manually selected: - Displayed in cyan when IAS target is manually selected on ICP. - Displayed in magenta when AUTO SPD TGT is activated on ICP (computed by FMS).
Indicating & Recording: 2.3 AIRSPEED MISMATCH FLAG¶
Indicating & Recording: 2.3.1 Airspeed Mismatch Flag¶
CHECK IAS The message appears when a discrepancy is detected for airspeed data between the ADC sources. IAS FAIL This message appears in case of loss of the validity of the signal.
PFD 180 160 200 220 240 I A S I A F L C H E C K I A S
Indicating & Recording: 2.4 ALTITUDE INDICATOR¶
Indicating & Recording: 2.4.1 Altitude Indicator¶
This indicator displays the aircraft baro-altitude of the selected AHRS source. This altitude is the altitude computed by the ADC, corrected with the barosetting (if any), and then corrected by the AHRS. The altitude is referenced to hectoPascal and to inches of mercury.
IMPERIAL 1 2 4 5 7 6 PFD 100 20 80 3048M 00 7 20 00 80 1000 STD 1013 / METRIC 29.92 3 005 010 M 196 5880 FL
2 FL 160 160 FL 160 1 6 1 Selected Altitude Indication Displayed above the tape: - In cyan If the altitude was selected by the crew on the FGCP. - In magenta The next altitude constraint defined by the FMS (if capability VNAV available). When Imperial system is used : - When altitude indication is in feet, only digits are displayed - When altitude indication is in flight level, “FL" label followed by 3 cyan digits are displayed. Maximum operational display will be 25000 or FL250. When Metric system is used : - Cyan digits and a white “M" label are displayed. Maximum operational display will be 7 500 m. The units system are set via the MCDU. 2 Landing elevation brown band Top limit indicates FMS landing elevation. It refers to departure airport (when defined in FPLN) at departure or to destination airport or landing runway (when defined in FPLN) at arrival.
3 Baro-setting Digital Readout Reference pressure altitude is displayed in millibars and in inches of Hg based on baro settings selected by the flight crew on the ICP. White "/" separates values in Hpa to value in inches of Hg. Value in Hpa is displayed in cyan on the right side, from 745 hPa to 1 050 hPa with 1 hPa of resolution. Value in inches of Hg is displayed in cyan on the left side, from 22 to 31 inches with 0.01 of resolution. In case of invalidity, amber “-- -- -- --/-- --. -- --" label is displayed. Cyan STD label is displayed in a white box if barosetting selection is set to STD. The indication is flashing in following cases: - The QNH value is still displayed above the TRANS ALT value in climb - The STD label is still displayed below the TRANS FL value in descent or below 2 500 ft RA - Long (>5 s) selection discrepancy between the Captain side and the First Officer side. TRANS ALT and TRANS FL values are defined based on departure and destination airports information in databases. The flight crew flight crew can check and modify these values on the TAKEOFF and APPROACH MCDU pages. 4 Altitude Scale A vertical tape included in a grey rectangle with graduation from -1 000 ft to above 25 000 ft, every 100 ft with longer marks and associated numbers every 500 ft. A yellow line represents the altitude reference on the centre of the tape. 5 Minimum Decision Altitude Indication Two amber horizontal lines indicates the selected minimum decision altitude. 6 Altitude Bug - FMS Altitude Bug Represented by a magenta filled triangle bug, it indicates the next flight plan altitude constraint. (If capability VNAV available) - Selected Altitude Bug Represented by a cyan filled “M-shaped" bug, it indicates the selected target altitude (If capability VNAV available). 7 Altitude Numeric Readout Display is in feet on the altitude scale, the readout being a digital drum counter with 20 ft increments. When operating in feet the altitude is displayed as “T-shape", it reverts to a rectangle in case that metric readout is selected. Readout in meters will be displayed above the rectangular altimeter. NEG label is added in place of thousands digits for negative values. It is displayed in white on the left of the first digit. Readout range is from NEG 980 ft to above 25 000 ft. The units are set via the MCDU (Meter or Feet)
Note On ground, permitted deviation between altimeter indications and aerodrome elevation is: Elevation of the aerodrome (ft) Permitted deviation (ft) 0 60 3 000 70 4 000 75 5 000 80 6 000 85 7 000 95 8 000 105 9 000 115 10 000 125 11 000 135 12 000 145 13 000 155 14 000 165 15 000 175
Indicating & Recording: 2.5 ALTITUDE MISMATCH FLAGS¶
Indicating & Recording: 2.5.1 Altitude Mismatch Flags¶
CHECK ALT The message appears when a discrepancy is detected for altitude data between the ADC sources. ALT FAIL Three white lines surrounding the tape and a red ALT FAIL vertical message are displayed when the baro altitude is invalid.
015 025 00 20 80 20 A L F A I L T PFD
Indicating & Recording: 2.6 VERTICAL SPEED INDICATOR¶
Indicating & Recording: 2.6.1 Vertical Speed Indicator¶
(Applies: 1054;1237-1283) This indicator displays the vertical speed information, based on both inertial (AHRS) and barometric data (ADC). -10 -06 TA ONLY BELOW XPDR1 ON PFD 1 2 3 4 5 7 9 8 6 6 2 1 6 2 1
1 VS Target Readout Indicates the active vertical speed target value in hundreds of feet. It is composed of two digits from 0 hundreds of fpm to +/ - 99 hundreds of fpm with 100 fpm resolution. Minus signs are displayed when the value is negative. It is located above the current vertical speed value. The VS target readout is associated with the cyan target bug. 2 VS Pointer This is a green line (in normal operation) extended from a fixed point outside the display to a point along the scale indicating the current vertical speed. The line has a fine black outline. Only the part of the pointer which is inside the VS scale is displayed. During TCAS resolution advisory, if the pointer points on a red band, the vertical speed pointer color is red. 3 TCAS Corrective Advisory It is green Fly-To band. It displays the vertical speed range to maintain in case of TCAS corrective advisory 4 TCAS Vertical Resolution Advisory (RA) In case of TCAS resolution advisory, one or two red bands are displayed on the vertical speed scale in order to show the vertical rates to be avoided. 5 Transponder Status Indication Indicates the selected transponder status. The displayed indications (spread on two lines) are: First line Second line Color (First line/Second line) XPDR STATUS XPDR1 FAIL Amber/Amber Failed XPDR2 FAIL Amber/Amber Failed XPDR1 STBY White/White Set to Standby XPDR2 STBY White/White Set to Standby XPDR1 ALT OFF Green/White Alt report set to OFF XPDR2 ALT OFF Green/White Alt report set to OFF XPDR1 ALT Green/Green Alt report set to ON XPDR2 ALT Green/Green Alt report set to ON
6 TCAS Status Indication Indicates the current TCAS status. The displayed indications (spread on two lines) are: First line Second line Color TCAS STATUS TCAS display mode TCAS FAIL Amber Failed - TCAS STBY White Set to STBY - TCAS TEST Yellow Test is in progress - TA ONLY THREAT Green TA only mode None NORM Green Normal BELOW Green Below ABOVE Green Above TCAS THREAT Green TCAS operative None NORM Green Normal BELOW Green Below ABOVE Green Above 7 VS Digital Readout Indicates in green the current vertical speed value in hundreds of feet in normal operation. If TCAS vertical resolution advisory exists the readout is red. Minus signs are displayed when the value is negative. The VS readout is associated to the VS pointer. 8 VS Target This is a filled M-shape bug located on the vertical tape between numeric indications and graduations of the scale. The VS target is associated to the VS target readout. The VS target bug is Cyan when VS target is defined by the flight crew. 9 VS Scale The altitude scale is the reference for vertical speed information. The 1, 2 and 6 numeric white indications are displayed respectively for +/- 1000 fpm, +/- 2000 fpm and +/- 6000 fpm. A yellow line represents the vertical reference on the center of the tape. The scale is outlined in white. In case of invalidity, three white lines surrounding a red VS FAIL vertical message are displayed.
(Applies: 1096-1160) This indicator displays the vertical speed information, based on both inertial (AHRS) and barometric data (ADC).
-10 -06 TA ONLY BELOW XPDR1 ON PFD 1 2 3 4 5 7 9 8 6 6 2 1 6 2 1
1 VS Target Readout Indicates the active vertical speed target value in hundreds of feet. It is composed of two digits from 0 hundreds of fpm to +/ - 99 hundreds of fpm with 100 fpm resolution. Minus signs are displayed when the value is negative. The VS target readout is associated with the cyan target bug if defined by the flight crew. In descent phase with VNAV mode, the VS target is computed by the FMS. The VS target readout and VS target are in magenta. 2 VS Pointer This is a green line (in normal operation) extended from a fixed point outside the display to a point along the scale indicating the current vertical speed. The line has a fine black outline. Only the part of the pointer which is inside the VS scale is displayed. During TCAS resolution advisory, if the pointer points on a red band, the vertical speed pointer color is red. 3 TCAS Corrective Advisory It is green Fly-To band. It displays the vertical speed range to maintain in case of TCAS corrective advisory. 4 TCAS Vertical Resolution Advisory (RA) In case of TCAS resolution advisory, one or two red bands are displayed on the vertical speed scale in order to show the vertical rates to be avoided.
5 Transponder Status Indication Indicates the selected transponder status. The displayed indications (spread on two lines) are: First line Second line Color (First line/Second line) XPDR STATUS XPDR1 FAIL Amber/Amber Failed XPDR2 FAIL Amber/Amber Failed XPDR1 STBY White/White Set to Standby XPDR2 STBY White/White Set to Standby XPDR1 ALT OFF Green/White Alt report set to OFF XPDR2 ALT OFF Green/White Alt report set to OFF XPDR1 ALT Green/Green Alt report set to ON XPDR2 ALT Green/Green Alt report set to ON 6 TCAS Status Indication Indicates the current TCAS status. The displayed indications (spread on two lines) are: First line Second line Color TCAS STATUS TCAS display mode TCAS FAIL Amber Failed - TCAS STBY White Set to STBY - TCAS TEST Yellow Test is in progress - TA ONLY THREAT Green TA only mode None NORM Green Normal BELOW Green Below ABOVE Green Above TCAS THREAT Green TCAS operative None NORM Green Normal BELOW Green Below ABOVE Green Above 7 VS Digital Readout Indicates in green the current vertical speed value in hundreds of feet in normal operation. If TCAS vertical resolution advisory exists the readout is red. Minus signs are displayed when the value is negative. The VS readout is associated to the VS pointer.
8 VS Target This is a filled M-shape bug located on the vertical tape between numeric indications and graduations of the scale. The VS target is associated to the VS target readout. The VS target bug is : - Cyan when VS target is defined by the flight crew - Magenta when VS target is computed by the FMS in descent with VNAV mode. 9 VS Scale The altitude scale is the reference for vertical speed information. The 1, 2 and 6 numeric white indications are displayed respectively for +/- 1000 fpm, +/- 2000 fpm and +/- 6000 fpm. A yellow line represents the vertical reference on the center of the tape. The scale is outlined in white. In case of invalidity, three white lines surrounding a red VS FAIL vertical message are displayed.
Indicating & Recording: 2.7 NAVIGATION INDICATORS¶
Indicating & Recording: 2.7.1 Navigation Indicators¶
The PFD provides on its Navigation Area the medium term flight information. The navigation area can be displayed in 2 formats: - HSI (Horizontal Situation Indicator) - Mini-ND (Mini-Navigation Display)
N MDH 160 155 M 99A ICING ICING AOA HLD SPD ALT 2 1 6 200 220 240 180 6 2 1 205 900 MSG TERM 40 . 5 012 ID_FMS FMS1 29 . 20 QNH NM TA ONLY ° ADF2 1250.5 M VOR1 250.30 40.5 NM CHECK HDG 0 M 25 15315 FL 20 157 60 40 80M 20 G 30000 FL R V2 F 20 10 10 DH 19999 0 10 10 F 1 ADF1 1250.5 OFST +10.3 G - A U T O T RNG STAB 1250.5 ADF2 WAIT 157 60 40 160 155 HOLD VOR ICING DGD PERF CAT1 RETRIM ROLL R WING DN HLD TCS SPD 0 9 2 1 6 FL 25 200 220 240 180 TA ONLY BELOW XPDR1 VOR1 110.30 M 012 40.5 H NM 29.20 1013 / 6 2 1 FD SINGLE CH 195 ° ° 80 20 PITCH HOLD A M MSG TERM HDG HDG 000 ° C H E C K I A S N 10 AUTO 5 CHECK HDG ON 200 250 GS TAS ADF1 1250.5 OFST +10.3 G - A U T O T RNG STAB 1250.5 ADF2 WAIT 157 60 40 160 155 HOLD VOR ICING DGD PERF CAT1 RETRIM ROLL R WING DN HLD TCS SPD 0 9 2 1 6 FL 25 200 220 240 180 TA ONLY BELOW XPDR1 ON VOR1 110.30 M 012 40.5 H NM 29.20 1013 / 200 250 GS TAS 6 2 1 FD SINGLE CH 195 ° ° 80 20 PITCH HOLD A CHECK HDG 10 AUTO M MSG TERM HDG HDG 000 ° C H E C K I A S
MINI-ND MODE ROSE MINI-ND MODE ARC HSI MDH M 99A 900 20 G 30000 FL 20 10 10 DH 19999 0 10 10 V2 F MDH M 99A 900 20 G 30000 FL 20 10 10 DH 19999 0 10 10 V2 F 2750
Indicating & Recording: 2.8 NAVIGATION AREA DISPLAY LOGIC¶
Indicating & Recording: 2.8.1 Navigation Area Display Logic¶
When a ND page on MFD is replaced by another page (e.g. ND is replaced by one of the System pages), the navigation part of the PFD auto-reverts : HSI format is replaced by Mini-ND format. ND ARC format on the MFD reverts to MINI ND ARC format on the PFD. ND ROSE and PLAN format on the MFD reverts to MINI ND ROSE format on the PFD . When on MFD, the ND format is displayed again, the navigation part of the PFD automatically switches back into the HSI format and the ND keeps the Mini-ND format selected. When a Traffic Alert is triggered by TCAS, the Mini-ND page automatically reverts to ROSE mode in 10 Nm range. When a Terrain Alert is triggered by TAWS, the Mini-ND page automatically reverts to: - ARC mode in a 10 Nm range and DU contrast automatically reverts to 80 %. - TERRAIN display mode (terrain selection becomes active on VCP)
Indicating & Recording: 2.9 HORIZONTAL SITUATION INDICATOR¶
Indicating & Recording: 2.9.1 Horizontal Situation Indicator¶
Refer to NAVIGATION DISPLAY
Indicating & Recording: 3 ELECTRICAL SUPPLY¶
Indicating & Recording: 3.1 Electrical Supply¶
It is associated with the DU electrical supply where the PFD is displayed.
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 Description¶
The Multi Functional Display, presented on the inner Display Units (DUs) in normal configuration, indicates the medium term flight information for the navigation, gives synoptics of system information, displays the radio navigation and radio communication selections. The MFDs provide this information based on the formats, pages and modes selectable. The MFD is divided into three areas : - MFD upper window - Memo panel display - Virtual Control panel window. PWR B + C + 025 BRG ° 50 10 : 3.0 NM 10 +03 RNG WX WAIT 025 TOWPT 200 GS 250 TAS T + VOR2 250.30 40.5 NM H ADF1 1250.5 AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 HDG HDG 040° NM 5 A +03 +05 A OFST L 18.3 ANTI ICING FUEL XFEED DE ICING NO DEVICE SEAT BELT ENG AIRFRAME HORN SIDE WINDOWS PROP 1 1 2 2 1 2 TERR NAV DR AUTO TAT 1 TAT 2 TO DATA ENG OAT TAT 1 + TAT SEL T/O TQ GND SAT +21 °C G-VAR -07 -07 PWR B + - C + - VIRTUAL CONTROL PANEL WINDOW MFD UPPER WINDOW MFD MEMO PANEL DISPLAY
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 MFD Upper Window¶
The MFD upper window displays several formats: - Navigation Display (ND) - System Display (SYS) displays the system pages: ENGINE/FUEL, CABIN, ACW/HYD, ELEC - Performance init (PERF) - MISC (provision) - Airport MAP (provision) - Video (provision)
Indicating & Recording: 2.2 Navigation Display (ND)¶
ND is displayed in several modes : ARC MODE, ROSE MODE or PLAN MODE.
2 10 +05 RNG WX WAIT 025 T +10 3 . VOR2 250.30 40.5 NM H ADF1 1250.5 AIRPORT NAVAID TA 25.3NM / +03 RA 25.3NM / +03 NM L 1.20 5 A +03 ND ARC MODE ND ROSE MODE 3 33 A 355 80 ° / RNG WX WAIT G-VAR 025 200 250 GS TAS T +10 3 . VOR2 250.30 40.5 NM H ADF1 1250.5 TA 25.3NM / +03 TA 25.3NM / +03 HDG HDG 040 ° A A OFST L 18.3 ° ° NAVAID AIRPORT 025 50 10 : 3.0 TOWPT NM BRG ° NAV DR L18.3 OFST TERR ON S W E 33 15 24 3 30 12 21 10 5 6 L 1.20 NM 355 80 ° / 200 250 GS TAS HDG HDG 040 ° +03 025 50 10 : 3.0 TOWPT NM BRG ° NAV DR G-VAR TERR ON NAV 355 80 ° / 200 250 GS TAS AIRPORT NAVAID N S W E 10 5 025 50 10 : 3.0 TOWPT NM ° DR AGN NEXTWPT L 1.20 NM ND PLAN MODE BRG MFD PAMELA AMPOUL 20W
Indicating & Recording: 2.3 System Display¶
The MFD can display the following system pages (for description see related FCOM chapters) : - ENGINE (secondary engine parameters) - CABIN - ACW/HYD - ELEC BTC TRU CHG OFF SVCE BUS OFF UTLY BUS 1 SHED UTLY BUS 2 SHED EMER BAT V 28 DC STBY BUS EMER BUS ESS BUS MAIN BAT V 28 CHG OFF INV 1 INV 2 FAULT AC STBY BUS AC BUS 1 AC BUS 2 OFF OFF DC BUS 1 OFF HOT BUS HOT BUS DC BUS 2 OFF DC GEN 2 OFF DC GEN 1 OFF 21 °C PACK BLEED AUTO HIGH FLOW AIR RECIRC PACK BLEED AUTO OXY SUPPLY PAX CREW P PSI 0 6 0 8 8.00 VS FT/MIN 0 2000 0 2000 MAN ALT TARGET CAB ALT FT FT 5200 5200 ELEC SMK FWD SMK LAV SMK AFT COMPT SMK X FEED BTC GREEN HYD TRU ACW BUS 2 0 PSI NORM BRK LDG GEAR EMER BRK ACCU FLAPS SPOILERS PSI 3000 STRG N/W PROP BRK 0 PSI ACW BUS 1 OFF OFF ACW GEN1 AUX HYD DC BUS 2 OFF ACW GEN2 BLUE HYD OFF OFF OFF OFF ACW/HYD CABIN 12, 5, 0, 17 V2.2.1 0 260 FEED LO PR XFR FUEL TANK RUN 250 KG 1170 TEMP °C 31 LO PR FEED FUEL FLOW KG/H 90.4 1+2 KG/MN ITT °C ITT °C X START FAIL ENGINE LO PR OIL PRESS PSI TEMP °C 0 NH % NL % 60 0 64.0 60 0 NAC OVHT LO PR 0 OIL 0 PRESS PSI TEMP °C START
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--- . - °C -54 RUN KG 1170 TEMP °C 29 CLOG ENGINE (SECONDARY ENGINE PARAMETERS) ELEC
Indicating & Recording: 2.4 PERF INIT¶
MFD PERF INIT page enables the flight crew to displayed FMS perf data. Pressing PERF key on EFCP displays the MFD PERF INIT and VCP PERF INIT pages.
Note The flight crew cannot modify one of these values directly through the MFD PERF page.
2 ZFW ----- FOB GW RESERVE T/O CG % FF % T/O UP V1 VR V2 NORMAL VMLB0 ICING NORMAL VMHB FLAPS V WIND / ° A/C OFF T/O % % APPROACH ICING NORMAL ICING NORMAL
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--.- -.- -.- FACTOR TRIM
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TQ¶
--.- --.- APP FLAPS ° -- ° --
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A/C DATA AREA TAKEOFF AREA APPROACH AREA DEST RWY AREA DATA TAKE PWR B + - C + - MFD format - Fig. 1 : MFD PERF INIT page (empty page) - For information only, not representative of an operational situation The MFD PERF INIT contain 4 AREA : - A / C DATA AREA - TAKEOFF AREA - APPROACH AREA - DEST RWY AREA AREA DESCRIPTION: A/C DATA AREA
3 ZFW FOB GW RESERVE T/O CG % FF % T/O UP A/C FACTOR TRIM DATA 15000 KG 4988 KG 19988 KG 500 KG 25.0 0.0 1.3 PWR B + - C + - MFD PERF PAGE - A/C WEIGHTS: ZFW, FOB, GW These data are set in the WEIGHT page on MCDU. FOB and GW values are also displayed in permanent data field on EWD. - FUEL: FOB, RESERVE, FF FACTOR RESERVE : this parameter is set in the WEIGHT page on MCDU. FF FACTOR : this parameter is set in the PERF INIT page on MCDU. - T/O CG is the aircraft center of gravity assessed at takeoff. This parameter is set in the WEIGHT page on MCDU and in TRIM area on EWD. TAKEOFF AREA
V1 VR V2 ICING VMLB0 ICING NORMAL OFF T/O % % TQ TAKE 114 114 118 133 158 BLEED_OFF BLEED_ON 90.0 90.0 PWR B + - C + - MFD PERF PAGE
- TAKEOFF SPEEDS o V1: Decision speed o VR: Rotation speed o V2: Initial Climb speed Note Takeoff speeds bugs are displayed on IAS speed scale in PFD when T / O data are confirmed.
- Takeoff speeds condition is displayed on the right side: o NORMAL (green): T/O speeds computed by the FMS in non-icing situation. o ICING (amber): T / O speeds computed by the FMS in icing situation. ICING condition at takeoff is set if the Icing conditions is selected on VCP TO DATA page or if icing accretion is automatically detected at lift off. o MANUAL (white): T / O speeds entered by the flight crew into the PERF / TAKEOFF page on MCDU.
- VmLB0 are displayed in NORMAL and ICING conditions. VmLB0 bugs (respectively white and amber triangles) are displayed in IAS speed scale on PFD.
- T / O TQ, takeoff objective torques of engines; T / O TQ are provided for BLEED OFF and BLEED ON configurations. T / O TQ bug (cyan circle) is displayed on torque scales of both engines in the Primary Engine window on EWD. APPROACH AREA
VMHB FLAPS FULL ICING NORMAL 104 113 APPROACH V APP FLAPS FULL PWR B + - C + - ICING NORMAL 104 113 MFD PERF PAGE - VmHB FLAPS FULL, is provided in NORMAL and ICING conditions. VmHB bug (green triangle) is displayed on PFD speed scale - VAPP FLAPS FULL, is provided in NORMAL and ICING conditions. VAPP bug (magenta M-shape) is displayed on PFD speed scale when SPD AUTO is activated. DEST RWY AREA
APPROACH WIND 0 / ° 360 PWR B + - C + - VMHB FLAPS FULL ICING NORMAL 104 113 V APP FLAPS FULL ICING NORMAL 104 113 MFD PERF PAGE WIND field indicates the ground wind direction (magnetic) and speed on landing runway at destination airport. The flight crew set wind information in the PERF / APPROACH page on MCDU.
Indicating & Recording: 2.5 Memo Panel Display¶
MFD Memo Panel Display provides the following information: - Fuel crossfeed control/failure device status - Anti-icing control/failure devices status - Deicing control/failure devices status - Cabin seat belt/No smoking message status. PWR B + - C + - MFD ANTI ICING FUEL XFEED DE ICING NO DVCE SEAT BELT ENG AIRFRAME HORN SIDE WINDOWS PROP 1 1 2 2 1 2 MFD UPPER WINDOW VIRTUAL CONTROL PANEL WINDOW
If systems are selected and are operating normally they will be displayed in cyan.
They will be displayed in amber in case of failure.
Indicating & Recording: 2.6 Virtual Control Panel¶
PWR B + - C + - MFD UPPER WINDOW MEMO PANEL DISPLAY ACTIVE STBY ACTIVE 115.10 V/ILS2 DME HOLD V/ILS1
< VOR/ILS STBY
< DME HOLD AUTO AUTO 113.15 117.10 112.30 112.30 ADF ND OVLY
The VCP format presents the information which can be managed through the MCP, in the lower part of the MFD. Three different types of pages are displayed to manage the information: - VCP NAV pages - VCP COM page - SURV page. Also, pages are displayed when the performance data are entered in the FMS.
Indicating & Recording: 2.7 VCP NAV Pages¶
VOR/ILS Selection of the VOR and ILS frequency, and activation of the DME HOLD function.
ACTIVE STBY ACTIVE 115.10 V/ILS2 DME HOLD V/ILS1
< VOR/ILS ADF ND OVLY STBY
< DME HOLD AUTO AUTO 113.15 117.10 112.30 112.30 DME HOLD DME HOLD ADF Selection of the ADF frequency
ACTIVE STBY ACTIVE 1415.0 ADF2 ADF1
< VOR/ILS ADF ND OVLY STBY
< ADF 1423.0 1423.0 1603.0 TONE TONE ND OVLY Selection of the required overlay information on the ND: - Traffic - Weather radar - Terrain - Navaid - Airport.
VOR/ILS ADF NAVAID AIRPORT TRAFFIC WX WX/TERR NORM ABOVE BELOW NONE TERR NONE ND OVLY
Indicating & Recording: 2.8 VCP COM Pages¶
VHF Selection of the VHF frequency.
ACTIVE VHF1
< VHF HF 1 HF 2 STBY 122.100 118.600 ACTIVE VHF2
< STBY 122.100 123.500 ACTIVE VHF1
< VHF HF 1 HF 2 STBY 122.100 118.600 ACTIVE VHF2
< STBY 122.100 123.500 HF Selection of the HF frequency
ACTIVE HF1
< VHF HF 1 HF 2 STBY 11.345 11.200 SQUELCH USB PWR MED OFF 1 2 3
Indicating & Recording: 2.9 VCP SURV Pages¶
XPDR
ON 4304 IDENT STBY ALT OFF FLT ID F1046 XPDR XPDR 1 XPDR 2 TCAS TCAS
XPDR AUTO TA ONLY TCAS STBY
Indicating & Recording: 2.10 VCP PERF Page¶
The VPC performance pages can be displayed, by pressing on the PERF pb on the EFCP. Pressing PERF pb display also the MFD Perf page.
Two pages are available on VCP page: - TO DATA
RESET FUEL USED TO DATA ENG OAT ICING CONDITIONS CONFIRM T/O DATA 1 2 3 TO DATA page used to: o 1 Reset the fuel used o 2 Select the icing condition: box activates ICING condition for computation of T/O performance predictions o 3 Confirm the T/O performance data inserted and computed by the FMS. When dual FMS cross-talk is running normally: o Modification of T / O data on one side automatically affects both sides o Any action on VCP/TO DATA page affects both sides. After T/O DATA confirmation, button label changes to “T/O DATA CONFIRMED” and T/O speeds and torque bugs appear on DUs. CAUTION Flight crew must confirm performance before takeoff. A new confirmation is required after any change among performance data entries. - ENG OAT
TAT SEL AUTO TAT 1 TAT 2 T/O TQ + GND SAT - + 21 °C TO DATA ENG OAT ENG OAT page used to: o Select the source of the TAT (Total Air Temperature) Note On Auto TAT sel, the source is: - ADC2 on even days. - ADC1 on odd days.
o Enter GND SAT (Static Air Temperature) for T/O TQ BUG computation, if there is a difference between weather message and TAT.
Indicating & Recording: 1 Indication on EWD¶
The EWD page is divided into 5 areas: - Flight controls, trims, brake message and test status - Primary engine window - Permanent Data Window : TAT (°C), SAT (°C), FT (Flight Time), Hour, FOB (Fuel On Board - kg or lb), GW (Gross Weight - kg or lb) - Alert Window - Procedure Window. EWD PWR B + - C + - ALERT ENGINE DISPLAY PROCEDURE PERMANENT DATA FLAP BRAKE MSG TEST STATUS TRIM UP 5 0 DN UP 3.0 L R L I A R U D TO CONF TEST OK SEL 1500 FLAPS UNLK DURING TAKEOFF BEFORE V1
FLAPS UNLK TAT SAT 44100 LBS FOB GW °C °C FT H 52 12 52 H 13 : LO PITCH SGL CH 500 ITT °C ISN 500 0 AUTO FTR PROP BRK NP% 2 N N 2 SGL CH TQ% LOOP 80.0 CLB FIRE 1 50 100 0 UPTRIM LOOP FIRE 2 50 100 0 UPTRIM 100 PWR B + C + 40.0 500 500 LO PITCH FUEL USED LBS P I T C H F L A P TO INHIB STATUSWAIT 10 SEC 999.0 NAC OVHT 0
100 80.0 CLB 1600 00 6600 LBS TAKEOFF. . . . . . . . . . . . . . . . . . . . . . . .ABORT AFTER V1 VR & V2 SPEED BUGS AUTOMATICALLY INCREASED
WHEN POSSIBLE FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .0° FOR APPROACH REDUCED FLAPS LANDING PROC . . .APPLY PROCEDURE COMPLETED For information only, not representative of an operational situation. Flight Crew controls EWD through EFCP.
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 General¶
The IESI displays the following information: - Attitude - Airspeed - Altitude - Barometric pressure - VHF 1 radio communication - VOR/ILS 1 radio navigation The IESI has to be complemented with the standby compass (Refer to CONTROLS) for standby navigation purpose.
Indicating & Recording: 1.2 Architecture¶
DC ESS BUS --------+
HOT EMER BUS ------+--> [IESI]
VOR/ILS 1 ---------+ |
VHF 1 -------------+ +--> standby attitude / airspeed / altitude / nav display
STBY PITOT --------+
STBY STATIC PORTS -+
Indicating & Recording: 1.3 Standby Navigation System Indication¶
ILS M 47
MENU STD SEL SET + - 130 VHF1 10 10 ILS1 108.55 125 180 240 118.100 20 127 00 220 3 2 4 1 7 8 9 10 5 6 1013 181 2 1 Fixed Aircraft Symbol The fixed aircraft symbol is black outlined in yellow 2 Roll Scale The roll scale is in white, markers are set at 10,20,30,45,60 ° of bank. 3 Roll Index The roll index indicates the bank angle. It is in black, and outlined in yellow. 4 Lateral Acceleration Index Lateral acceleration index indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index. 5 Pitch Scale The pitch scale indicates aircraft attitude and is displayed in white. The scale has markers every 2.5 ° up to +/ - 20 °. If pitch exceeds +/ - 25 ° large red chevron will indicate excessive attitude and direction to follow to resume normal attitude. 6 Airspeed Scale 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. 7 Altitude Indication 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.
8 Barometric Reference The barometric reference is displayed in cyan. It corresponds to either the selected barometric pressure or the standard pressure. 9 Glideslope & Localizer Scales and Indexes The deviation scales appear when the ILS MODE is selected. The indexes appear when the glideslope and localizer signals are valid and deviation scales displayed. 10 VOR Scale and Index The deviation scale appears when the VOR MODE is selected. In the bottom left corner TO ▲ and FROM▼ are indicated in cyan followed by the selected course.
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 IESI¶
The IESI has 5 pushbuttons and a knob: - A brightness (-) pb (4) - A brightness (+) pb (4) - A MENU pb (5) - A STD pb (1) - A SEL pb (3) - A SET knob (2) VHF1 ILS1 108.50 118.100 ILS M 47
MENU SET 1 STD 5 4 3 SEL + - 2 1 STD pb When pressed for more than 0.2s, resets barometric setting at 1 013.25 hPa.
2 SET knob Sub function menu scroller Baro setting tunning VHF COM tunning VHF NAV tunning Course adjustment when in VOR mode 3 SEL pb - Validates the selection, or - When VOR mode is selected, changes cursor selection between VHF COM, VHF NAV, BARO setting and course. 4 +/- pb Adjust IESI screen brightness 5 MENU pb Enable sub function selection menu.
Indicating & Recording: 2.2 ILS Tuning¶
When MENU pb is pushed and VHF NAV 1 is tuned on ILS:
SEL SET BARO UNIT [INHG] SEL SET SEL SET TUNING MODE [OFF] SEL SET MAINTENANCE [OFF] SET TURN SET SET TURN SET SET TURN SET EXIT MENU PRESS MENU ENTER MENU PRESS MENU ILS MODE IESI MENU WITH ILS TUNING MENU STD SEL SET + - 130 10 10 1013 125 180 240 201 2 20 127 00 220
Indicating & Recording: 2.3 VOR Tuning¶
When MENU pb is pushed and VHF NAV 1 is tuned on VOR:
SEL SET BARO UNIT [INHG] SEL SET SEL SET TUNING MODE [OFF] SEL SET MAINTENANCE [OFF] SET TURN SET SET TURN SET SET TURN SET EXIT MENU PRESS MENU ENTER MENU PRESS MENU VOR MODE IESI MENU WITH VOR TUNING MENU STD SEL SET + - 130 10 10 1013 125 180 240 201 2 20 127 00 220
Indicating & Recording: 2.4 Flags¶
3 2 4 1 5 6 MENU SEL SET + - ATT:RST ATT STD IAS ILS FAIL
ALT 1 ATT Label (Red Reverse Video) Means that attitude data are lost. 2 IAS Label (Red Reverse Video) Means that airspeed data is lost. 3 ALT Label (Red Reverse Video) Means that altitude data is lost. 4 VOR, ILS, LOC or G/S Label (Red Reverse Video) Appropriate MODE is selected but invalid, no signal is detected from selected source. 5 ATT:RST Label (Cyan) This message appears if the aircraft has moved during initialization of IESI. 6 FAIL Label (Amber) FAIL amber boxed label is displayed in case of invalid signal or tuning mode off. 7 OUT OF ORDER (White) (not Depicted) A fatal error has occurred and the IESI is unserviceable. 8 Black Screen with White Frame (not Depicted) The processor of the IESI is unserviceable.
Indicating & Recording: 3 ELECTRICAL SUPPLY¶
Indicating & Recording: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) IESI (normal operation) DC ESS BUS (on overhead panel C/B PRIM REF / IESI NORM SPLY) NIL IESI (abnormal operation e.g DC ESS BUS voltage < 19 V) HOT EMER BAT BUS (on lateral panel 130 VU C/B STBY HOT EMER PWR SPLY) NIL
Indicating & Recording: 1 GENERAL¶
Indicating & Recording: 1.1 General¶
The Control and Display System (CDS) provides manual and automatic format configuration of DU. Main formats manual reversion is controlled with two reversion pushbuttons. These pushbuttons enable a circular reversion between PFD, EWD and MFD formats. Automatic reversion occurs following DU failures or FWS request. On ground, powering aircraft with batteries, DU 2 and DU 4 are respectively configured as EWD and SD Engine page (power supply is not available on DU 1, 3 and 5) OFF EWD OFF OFF MFD (SD ENG) AFTER GPU/ENGINE POWERING, CDS CONFIGURATION IS AS FOLLOWING: PFD MFD (ND) EWD PFD MFD (SD ENG)
Indicating & Recording: 2 CDS CONFIGURATION¶
Indicating & Recording: 2.1 Automatic Configurations¶
The CDS reversion system provides automatic DU reconfiguration in case of DU failure(s). The leading rule of the automatic reconfiguration is: following PFD or EWD failure, MFD is reconfigured in PFD or EWD. The automatic reconfiguration takes into account the following parameters : - Flight/Ground Status - Pilot Flying Side: Right or Left Automatic reconfiguration can also occur on FWS request.
If EWD is no more displayed because it was manually reversed in PFD or MFD (in the case of DU 3 failure for instance), EWD can be automatically recalled by FWS. When one System Display page is displayed on MFD format, another System Display page can be automatically displayed on FWS request.
Indicating & Recording: 2.2 Manual Reconfiguration¶
Manual reconfiguration is controlled by two associated means: - The DISPLAY PFD/EWD/MFD pushbuttons on CAPT and F/O SWITCHING panels: The system enables to switch displays on the different DUs. If DU 2(4) is available, the DISPLAY pb enables a circular reversion of PFD/EWD/MFD format on DU 2(4). If DU 2(4) is inoperative, DU 1(5) takes into account the reversion command. Manual reversion overrides a DU automatic reconfiguration but if a new automatic reconfiguration occurs, current manual reversion is superseded by this new configuration. - The EFCP (EFIS Control Panel): Refer to DSC.31.4.2.2 EFIS Control Panel Note The EFIS Control panel enables to directly call the associated EWD/MFD display and can be used as a shortcut (to avoid the display cycling through the DISPLAY pb).
Indicating & Recording: 2.3 Degraded Configuration¶
In case of AFDX loss, last DU configuration is unchanged and manual reversion is effective on DU 2 and DU 4. In flight, in case of DC electrical generation loss, DU 2 and DU 4 are respectively powered by EMER and ESS bus. DU 2 and DU 4 are configured depending on “Pilot flying side”. When a fatal DU failure is detected a big “F” label is displayed on the corresponding DU.
F
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 Description¶
An electronic clock provides: - On selection, a six digits display of either: o Universal Time Coordinated (UTC) o Date : DAY/MONTH and YEAR o Local Time (LT) o GPS Time - On selection, a four digits display of either: o ELAPSED TIME (ET) o CHRONOMETER TIME (CHR) - A serialized UTC, DATE and Elapse time Output - A remote controls: CHR and ET - An automatic synchronization on external data word from GPS receiver - A display function test (TST) on front face and on a remote test. The operating modes are controlled by: - A pb mode selector : DATE (DT) , GPS , INT , LOCAL TIME (LT) - A pb : ET - A pb : CHR - A pb : TST The clock is supplied with two 28 VDC power supplies, one of which is a direct connection to the aircraft battery hot bus.
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 Controls¶
ET - / + TST CHR MODE H/MO MN/DY S/YR GPS CHR Time Display - UTC from GPS or internal computed (INT) is indicated from 0 to 23 h 59 min and 59 s. The clock automatically switches to GPS mode if the GPS data is valid and the clock is in “INT” mode. In the same way, the clock automatically switches to INT mode if the GPS becomes invalid and the clock is in GPS mode (except on power up where the Time Setting mode is active if the GPS is invalid). - LOCAL TIME (LT) is indicated from 0 to 23 h 59 min and 59 s. At first power up of the battery bus, if the local time setting is displayed, the local time is initiated with the INT value and it can be modified by setting the desired time differences. At each next LOCAL TIME setting, the proposed value is synchronized with GPS or INT time, then it can be modified by setting the desired time differences. Date Display Months, days and years are displayed when the DATE mode is selected. MODE pb By pressing the MODE pb, 6 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 pb and CHR pb respectively, the GPS is automatically selected when GPS is valid). ELAPSED TIME (ET) pb ET counter displays the aircraft flight from 0 to 23 h 59 min. The ET pb controls the following functions: - When selecting the ET pb, the ET display comes on - When the elapsed time counter is stopped, by pressing the ET pb for more than two seconds the display is blanked and value is zeroed.
CHRONOMETER (CHR) pb The CHR displays time from 0 to 99 min 59 s. The CHR pb controls the following functions: - START : Display is active and the chronometer starts incrementing - STOP : The value displayed at the instant the pb was pressed in is held as long as no action occurs on this pb - RESET : the LCD display is zeroed and blanked. TEST (TST) pb The TST pb function starts rotating displays of the digits from 0 to 9, twice time. The function could be reset by pressing the TST pb before the end of the sequence. Time Setting At the first application of power, the clock is in UTC minutes adjustment if GPS is invalid. If the GPS data is valid, the clock data are automatically updated and switched in GPS mode. The setting is obtained by pressing the ET pb to decrease the data and pressing the TST pb to increase the data.
Indicating & Recording: 3 ELECTRICAL SUPPLY¶
Indicating & Recording: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) CAPT clock DC EMER BUS (on lateral panel CLOCK/CAPT/ NORM SPLY) HOT EMER BAT BUS (on lateral panel CLOCK/ CAPT/AUX SPLY) NIL F/O clock DC BUS 2 (on lateral panel CLOCK/F/O/ NORM SPLY) HOT MAIN BAT BUS (on lateral panel CLOCK/F/O/AUX SPLY) NIL
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 General¶
The aircraft is equipped with: - A Solid State Cockpit Voice Recorder (SSCVR) - A Solid State Flight Data Recorder (SSFDR). The recorders are automatically energized as soon as the aircraft is on its own electrical supply and are switched OFF automatically 10 min after engines shutdown . When the aircraft is on external power, recorders are OFF until one engine is started. They can be energized by selecting ON the RCDR pb, and deenergized by pressing the RESET pb. Each recorder is equipped with an underwater acoustic beacon which is used to locate the recorder in the event of an aircraft accident over the sea. The beacons actuate immediately after immersion. They transmit a signal on 37.5 kHz for 30 days. The detection range is 3.5 km (12 000 ft).
Indicating & Recording: 1.2 SSCVR¶
All crew communications transmitted through the RCAU are recorded. In addition, a CVR microphone, below the overhead panel, acquires cockpit conversation and aural alerts for recording. Cabin crew announcements are also recorded. Recording is made in the memory with a recording capacity of 120 min. All recording may be erased by pressing ERASE pb provided the aircraft is on ground and the parking brake is set.
Indicating & Recording: 1.3 SSFDR¶
The Solid State Flight Data Recorder (SSFDR) records the main aircraft parameters in digital format (concentrated by the Flight Data Acquisition Unit hosted in the MPC). At least the last 25 hours are kept in SSFDR memory.
112VM 112VM EVENT RESET RCDR ON GND CTL MCDU SSFDR SIGNALS FROM AIRCRAFT SYSTEMS DMU FDAU MPC ACCELEROMETER
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 MCDU Time and Flight Page¶
The MCDU TIME & FLIGHT page enables the flight crew to set hours, months, years and flight number before departure. This data is used for the recording on the SSFDR.
RETURN V V V V V V V TIME & FLIGHT V V V V V HOUR : MINUTE 11 : 55 MONTH : DAY 06 : 30 YEAR 2010 FLIGHT NUMBER 4526
Indicating & Recording: 2.2 Cockpit Voice Recorder Panel¶
(Applies: 1054-1160)
B A
5 B 1 COCKPIT VOICE RECORDER 600 OHMS TEST ERASE HEADSET 0 2 4 8 6 10 2 3 4 A
1 Monitor Indicator For test only. Movement of pointer in the white band indicates all channels are operative. 2 Test pb When pressed in 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 will be heard. 3 Erase pb Provides fast erasure of tape recordings when the landing gear shock absorbers are compressed and parking brake is set (press in for 2 s to completely erase). During erasure, a 400 Hz audio signal can be heard in the headset. 4 Headset Jack When headset is plugged into the jack: - Cockpit sounds picked up by the microphone are audible - Test tone is audible when TEST pb is pressed in - Erase tone is audible when ERASE pb is pressed in 5 Microphone Picks up cockpit conversations and alert sounds.
(Applies: 1237-1283)
B A 5 B A COCKPIT VOICE RECORDER TEST HOLD 5 SEC HEADSET ERASE 1 2 3 4
2 1 Test pb Press and maintain the pb to initiate the CVR self-test. During test, a 600 Hz audio signal can be heard in the headset. 2 Test light Successful completion of the CVR TEST is indicated by the illumination of the green light.
3 Erase pb Press for 2 seconds and release the pb to initiate recordings erasure when the landing gear shock absorbers are compressed and parking brake is set. During erasure, a 400 Hz audio signal can be heard in the headset. 4 Headset Jack When headset is plugged into the jack: - Cockpit sounds picked up by the microphone are audible - Test tone is audible during CVR self-test - Erase tone is audible during recordings erasure 5 Microphone Picks up cockpit conversations and alert sounds.
Indicating & Recording: 2.3 RCDR Panel¶
112VM EVENT RESET RCDR ON GND CTL
RCDR pb When pressed in, both Cockpit Voice Recorder and Solid State Flight Data Recorder are energized (manual mode). ON light comes on blue. Reset pb When pressed in, inhibits recording in the manual mode. Event pb When momentarily pressed in, the Solid Sate Memory records are marked to identify a special event.
Indicating & Recording: 3 ELECTRICAL SUPPLY¶
Indicating & Recording: 3.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) SSFDR power supply NIL 115 VAC STBY BUS (on lateral panel C/B RCDR/DFDR) SSFDR synchronizer NIL 26 VAC STBY BUS (on lateral panel C/B DFDR/SYNC) SSFDR control DC ESS BUS (on lateral panel C/B CVR/CVR) NIL FDAU MPC DC EMER BUS (on ground) (on overhead panel C/B MPC/FDAU GND SUPPLY) DC ESS BUS (in flight) (on overhead panel C/B MPC/FDAU FLT SUPPLY) NIL SSCVR power supply DC ESS BUS (on lateral panel C/B CVR) NIL
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 General¶
The Flight Warning System (FWS) provides the flight crew an operational support for the management of normal and abnormal configurations of the aircraft systems. The FWS performs the following functions: - In case of detected alert, it draws flight crew attention through visual and aural attention getters - In case of detected alert, it guides the flight crew to the system or subsystem concerned by activating an alert message - It helps the flight crew to set the aircraft in T.O configuration - It inhibits some alerts at T.O - It enables the flight crew to carry out normal procedures (checklist) - It enables the flight crew to carry out abnormal and emergency procedures - It enables the flight crew to know limitations and/or remaining actions - It helps the flight crew identifying system action status required during procedure processing by displaying the relevant system page on the SD. The display area dedicated to the FWS is on the lower part of the EWD. EWD PWR B + - C + - ALERT ENGINE DISPLAY PROCEDURE PERMANENT DATA FLAP BRAKE MSG TEST STATUS TRIM UP 5 0 SEL AFTER TAKEOFF FUEL ENG 1 FIRE ELEC 500 ITT °C S TQ% PWR B + C + T R I M S 0
LDG GEAR..........................................UP AT WHITE BUG FLAPS..................................................REMAIN 15° PWR MGT / NP..................................MCT / CHECK BLEED VALVES ON LIVED ENGINE..................ON TAXI & TO LIGHTS............................................OFF AIR ALTIMETERS....................................SET & CHECH ENGINE FIRE OR SEVERE DAMAGE PENDING 9 -4 2.5 15° R L 100 90.2 58.3 50 0 100 90.2 58.3 50 0 458 500 S 0 458 S H F USED KG 1 1 2 F USED KG 1 1 2 TAT SAT ISA GW 1 7 .6 T F O B 2 1 4 0 KG 13 5 2 12 H : N P% 8 2 . 0 8 1 . 9 -1 0 °C -2 1 °C -0 2 ° FIRE 1 2 3 1 It is composed of three parts: 1 An Alerting Window on the left part 2 A Procedure Window on the right part 3 A status area dedicated to FWS information on the bottom part of the procedure window.
Indicating & Recording: 1.2 Architecture¶
The FWS is composed of : - Two modules, on each Multi Function Computer (MFC) 1B and 2B - Two Core Processing Module (CPM), one on each Core Avionic Cabinet (CAC) - Two Input/Output Module (IOM-S), one on each CAC - Four Input/Output Module (IOM-DC), two on each CAC - Two SWitch Module (SWM), one on each CAC - One display format dedicated to the FWS: EWD is displayed on normal configuration on the center Display Unit (DU 3) - Two EFIS Control Panels (EFCP) - Two Master Warning pushbuttons (MW), one for each crew member - Two Master Caution pushbuttons (MC), one for each crew member - One TO CONFIG TEST pb - One EMER AUDIO CANCEL guarded toggle switch - One maintenance panel to test some warnings (red) that can not be tested at system level. The FWS is managed by the FWA (Flight Warning Application) function of the CAC
Indicating & Recording: 1.3 Basic Principles¶
The following two principles have been adopted: - “All flight deck lights out” concept In normal operation all the lights are turned off (except sometimes green or cyan light for transient phases) - Detection sequence The detection sequence comprises three different phases. PHASE FUNCTION MEANS OF DETECTION 1 DETECTION AURAL ALERT + MW or MC 2 IDENTIFICATION ALERT MESSAGE IN THE ALERTING WINDOW 3 ISOLATION SYSTEM CONTROL AND INDICATING PANEL
Indicating & Recording: 1.4 Alert Levels¶
The alerts are classified in 4 levels based on their importance and to the urgency of the corrective actions required. 1) Level 3: Warnings This corresponds to an emergency situation requiring crew prompt corrective actions.
The following alerts fall into this category: - Aircraft in hazardous configuration or limiting flight conditions (e.g. stall warning) - Serious system failure (e.g. engine fire). These warnings are identified by: - The MW light flashing red associated with a continuous repetitive chime (CRC) and a red warning message displayed in the alerting window - A specific aural warning. 2) Level 2: Cautions This corresponds to an abnormal situation of the aircraft requiring timely crew corrective actions. Time for taking action will be left to the discretion of the flight crew. This level mainly includes system failures having no immediate impact on safety (e.g. engine overheat). The cautions are identified by the MC light flashing amber associated with a single chime (SC) and an amber message displayed in the alerting window. 3) Level 1: Advisories This corresponds to a situation requiring flight crew monitoring. This level mainly includes failures leading to a loss of redundancy or degradation of a system. These advisories are identified by an amber caution message displayed in the alerting window without aural alert. 4) Level 0: Information This corresponds to an information situation action (e.g. DME hold). This information is provided by cyan, green or white display on the control display. This level is not taken into account by the FWS. Therefore, there is no associated display in the alerting window nor on the procedure window.
Indicating & Recording: 1.5 Color Coding¶
INDICATION COLOR INTERPRETATION WARNING RED Configuration or failure requiring immediate action CAUTION AMBER Configuration not requiring immediate action Left to discretion of the flight crew INFORMATION GREEN Normal operation CYAN Normal transient configuration WHITE System selected off
Indicating & Recording: 1.6 Takeoff Alert Inhibition¶
An Alert Inhibition function prevents the occurrence of some alerts during the critical takeoff phase (display, attention getters and aural are inhibited). The green TO INHIB message on EWD indicates that Alert Inhibition is active.
PWR B + C + TO INHIB Alert Inhibition activates automatically at takeoff when power levers are at or above the notch. While Alert Inhibition is active, all OIL and SMOKE warnings are inhibited.
All cautions are also inhibited, except: - SINGLE ENG OPERATION - UNEXPECTED 100% NP - ENG OVER LIMIT - PROP X OVER LIMIT - ENG X OIL TEMP BELOW 45°C - FLAPS JAM / UNCPL / ASYM - PITCH TRIM ASYM - TLU FAULT - AIL LOCK LIT - DE-ICING MODE SEL FAULT - AP PITCH TRIM FAIL - PITCH MISTRIM - AILERON MISTRIM - RUDDER MISTRIM - YAW AUTOTRIM FAIL - AHRS NOT ALIGN - ATTITUDE DISAGREE - IAS DISAGREE - ALTITUDE DISAGREE - HEADING DISAGREE - MFC 1B + 2B FAULT - MAINTENANCE PANEL. Alert Inhibition deactivates: - Automatically when the main landing gear retracts, or - Manually when the flight crew presses the RCL pb. As soon as the Alert Inhibition deactivates, any alert previously triggered and inhibited appears on the EWD. Note MAINTENANCE PANEL is an ADVISORY (Refer to Alert Levels).
Indicating & Recording: 1.7 Aurals¶
(Applies: 1124-1160) Two types of aural alerts are used to alert the flight crew: - Non specific alert always associated with an alert message displayed in the alerting window: o A continuous repetitive chime (CRC) associated with Master Warning (MW) lights and red warning message displayed in the alerting window o A single chime (SC) associated with Master Caution (MC) and amber caution message displayed in the alerting window. - Specific aurals for alerts not associated with the lighting of the Master Warning (MW)lights, or the Master Caution (MC) lights nor with an alert message displayed in the alerting window: Warnings: o Stall (cricket) o Overspeed: VMO, VFE, VLE (clacker) o AP disconnect (cavalry charge) o Trim in motion (whooler) Cautions: o Altitude alert ("c chord") o Calls (door bell) o AP capability downgrading, low speed protection and high speed protection(triple click).
Note A priority order has been defined for aurals in case of simultaneous occurrence of warnings and cautions: o Cricket (Stall) o Clacker (overspeed) o Continuous repetitive chime for following warnings: - Engine Fire - Engine Out - Dual DC Loss - Config - Nac OVHT - Propeller brake failure - Flaps unlock - Pitch disconnect - Excess cabin altitude, Excess cabin Δ P and Negative cabin Δ P - RNP LNAV guidance. o Whooler (Trim in motion) o continuous repetitive chime for following warnings: - Smoke detection - Oil low Press - Landing gear not down. o Cavalry charge (AP disconnection) o Triple click (AP capability downgrading, low speed protection and high speed protection) o C-chord (altitude alert) o Single chime (caution alerts) o Door bell (calls).
(Applies: 1054-1096;1237-1283) Two types of aural alerts are used to alert the flight crew: - Non specific alert always associated with an alert message displayed in the alerting window: o A continuous repetitive chime (CRC) associated with Master Warning (MW) lights and red warning message displayed in the alerting window o A single chime (SC) associated with Master Caution (MC) and amber caution message displayed in the alerting window. - Specific aurals for alerts not associated with the lighting of the Master Warning (MW) lights, or the Master Caution (MC) lights nor with an alert message displayed in the alerting window: Warnings: o Stall (cricket) o Overspeed: VMO, VFE, VLE (clacker) o AP disconnect (cavalry charge) o Trim in motion (whooler) Cautions: o Altitude alert (“c chord”) o Calls (door bell) o AP capability downgrading, low speed protection and high speed protection(triple click).
Note A priority order has been defined for aurals in case of simultaneous occurrence of warnings and cautions: o Cricket (Stall) o Clacker (overspeed) o Continuous repetitive chime for following warnings: - Engine Fire - Engine Out - Dual DC Loss - Config - Nac OVHT - Propeller brake failure - Flaps unlock - Pitch disconnect - Excess cabin altitude, Excess cabin Δ P and Negative cabin Δ P. o Whooler (Trim in motion) o continuous repetitive chime for following warnings: - Smoke detection - Oil low Press - Landing gear not down. o Cavalry charge (AP disconnection) o Triple click (AP capability downgrading, low speed protection and high speed protection) o C-chord (altitude alert) o Single chime (caution alerts) o Door bell (calls).
Indicating & Recording: 1.8 Local Alerts¶
All the local alerts on the control and indicating panel, on the overhead panel, on the central panel, or on display units, are activated by the systems. The local alerts are then independent from the FWS that only takes these local alerts into account to draw attention of the flight crew and has no possible action on them.
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 EFIS Control Panel¶
The control panel for FWS management is composed of two EFCPs (e.g Captain EFCP)
P R O C C AS 1 2 3 4 5 6 7 RCL MAN DEL PROC MENU CLR
1 PROC MENU Pb Enables the display of the "Procedure Menu" in the procedure window. 2 MAN DEL Pb Enables the flight crew to manually delete inserted procedure. 3 CLR Pb Enables to clear the clearable alert messages and procedures displayed in the alerting window and in the procedure window.
4 RCL Pb - A first press on Recall pb (RCL pb) enables to display (in the alerting window) the alert messages previously cleared but still detected - A second press on Recall pb (RCL pb) scrolls down the alert messages list in case of overflow in the alerting window. 5 ▲ Pb Enables the selection of upward line boxing in the procedure window. 6 ▼ Pb Enables the selection of downward line boxing in the procedure window. 7 V Pb Enables the validation (boxed item) of an action or to activate a boxed procedure or status.
Indicating & Recording: 2.2 MW-MC Lights¶
134VM MASTER CAUT MASTER WARN 133VM MASTER CAUT MASTER WARN 1 2 1 MASTER WARNING Light Flashes red when a warning is generated with associated red label and procedures displayed on the EWD. When pressed in, light will turn off and associated aural warning will be cancelled. 2 MASTER CAUTION Light Flashes amber when a caution is generated with associated amber label and procedures displayed on EWD. When pressed in, light will turn off.
Indicating & Recording: 2.3 Control Panel¶
902VU TO CONFIG TEST 1 EMER AUDIO CANCEL 2 1 TO CONFIG TEST pb Used before takeoff to: - Check if aircraft configuration is correct for takeoff by simulating power levers at TO position (except PRK BRK ON) - Perform an automatic RECALL (thus reactivating all aural warnings previously cancelled by EMER Audio/Cancel). When the flight crew presses the TO CONFIG Test pb, the EWD displays the status messages described in the below table.
EWD TO CONFIG TEST DISPLAY DESCRIPTION CONFIG FLT CTL - TLU is not in low speed - Disagreement on aileron lock (AIL LOCK) - Pitch trim outside green range - Flaps are not in takeoff configuration CONFIG PWR MGT PWR MGT selector is not in the TO (takeoff) position TO CONFIG TEST OK Display in the flight control window if aircraft is in configuration for takeoff The same test is performed when advancing the PL to T.O position, with parking brake released.
2 EMER AUDIO CANCEL Switch Is safety wired. In the case of false alert generated and undue continuous alert, EMER AUDIO CANCEL sw will enable cancelation of this unwanted aural alert. Example: If the switch is used to cancel a system X failure CRC, CRC is not cancelled for the systems other than system X. Cancelled aural warning will be reactivated: - At next aircraft energization (MFC reset) - After MFC 1B/2B reset - After pressing RCL pb - Following T.O CONFIG test Except for aural warning associated with: - Landing gear (landing configuration) - VMO, VFE, VLE - Stall warning - Pitch trim whooler - AP Disconnect Which will be rearmed as soon as the triggering condition disappears.
Indicating & Recording: 3 OPERATION¶
Indicating & Recording: 3.1 PROCEDURE PRINCIPLES¶
Indicating & Recording: 3.1.1 Without Aircraft System Failure¶
- On the right side of the alerting window, the procedure window enables the flight crew to manage procedures
- Procedure window is blank when no checklist is detected by the FWS
- When activating the PROCEDURE MENU through EFCP, NO ACTIVE PROCEDURE is displayed in the PROCEDURE MENU. The LIST menu is displayed below
- Any procedure can be called from the LIST menu
- During takeoff, some alert messages are not displayed and attention getters are not activated. When the power levers are in the takeoff position, the CONFIG warning is activated if parking brake is applied and the amber PRKG BRK ON message is displayed on EWD. On landing gear retraction, TO INHIB indication goes off and all alert messages detected but inhibited during T.O are displayed. The inhibition at T.O can also be manually deactivated by pressing the RCL pb
- Before approach when RCL pb is pressed, no alert message is displayed in the alerting window if no failure occurred in flight.
EWD (OTHER TEXTS CYAN) (WHITE) ABNORMAL PROCEDURES NORMAL CHECK LISTS PROCEDURE MENU EMERGENCY PROCEDURES LIST NO ACTIVE PROCEDURE
Indicating & Recording: 3.1.2 With Aircraft System Failure¶
1) Single Failure Detection When a failure is detected, the associated alert message is displayed in the alert window. If a procedure is associated with the detected failure, it is simultaneously displayed in the procedure window instead of the PROCEDURE MENU. The alert message remains displayed as long as the failure is detected. If the failure is a level 2 (caution message), the flight crew can press the CLR pb to clear the alert message and procedure.
VALIDATED ACTIONS: WHITE) (NON VALIDATED ACTIONS: CYAN EWD ELEC SMK ELECTRICAL SMOKE IF SMOKE/FUMES IN THE COCKPIT PWR B + C +
---------------------------------1/2¶
CREW OXY MASKS................DON CREW OXY MASK MODE............... ................100% OR EMERGENCY GOGGLES.......................DON CREW COMMUNICATIONS.....ESTABLISH RECIRC FANS 1+2..................OFF CABIN CREW COMMUNICATIONS..ESTABLISH NEXT PAGE AP................................ON LAND ASAP a) Color Coding - Cyan indicates actions that the flight crew must perform or decide - Amber items correspond to abnormal procedure titles, recommendations and statuses titles (even statuses derived from emergency procedures) - Red color corresponds to emergency procedures titles and strong recommendations - White color is used for subtitles items without associated action to be performed like notes, normal procedures titles and items associated with validated actions. b) Pending List Displayed in the PROCEDURE MENU above the LIST menu. It makes a list of the titles of all the active procedures and statuses. Pressing RCL pb enables to display the PROCEDURE MENU and to access the active procedures and statuses through the PENDING list. The entire procedure then starts over, as item previously validated items are not memorized. c) Status Some procedures can result in a status. In this case, when the procedure is performed and validated, the FWS changes the procedure by the associated status. Status titles are displayed in the PENDING list between brackets. d) Manually Inserted Procedure Any normal, abnormal and emergency procedures available in the LIST sub- menu can be called. Manually called procedures are displayed in the PENDING list with the MAN message at the right end of the line. This only occurs if at least one item is acknowledged.
2) Multiple Failures Detection All procedures associated with alert message have the same priority level as the alert message. Level 3 alerts (Master Warning) have priority over any Level 2 (Master Caution) or normal procedures.
Indicating & Recording: 3.2 FWS OPERATION¶
Indicating & Recording: 3.2.1 Without Aircraft System Failure¶
1) After Engines Start No alert light turned on in the cockpit except PRKG BRK ON amber message displayed on EWD if the parking brake is set. 2) Before Takeoff Press TO CONFIG TEST pb - If aircraft is in correct configuration, no light will come on - If aircraft is not in correct configuration: o MW light will flash red o CRC aural will be generated o CONFIG red message on EWD associated with: - FLT CTL when: o Flaps are not in the TO configuration and/or o Pitch trim is not in the TO configuration (out of the green sector) and/or o TLU Fault if the Travel Limiting Unit (TLU) is not in LO SPD configuration and /or o Aileron lock disagreement (AIL LOCK light turned on) - PWR MGT when power management not in TO position 3) Before Starting Descent Press RCL pb on EFCP. No messages displayed on EWD provided no failure occurred in flight.
Indicating & Recording: 3.2.2 Overspeed Alert¶
If the aircraft is in overspeed conditions (VMO, VFE, VLE), a specific aural alert is generated. The alert persists until return into the following flight envelope:
ALERTS VFE - 5 kt VLE - 5 kt VMO FLAPS 0 180 kt 250 kt FLAPS 15 180 kt FLAPS 30 145 kt
Indicating & Recording: 3.2.3 Stall Alert¶
To generate this alert (cricket and stick shaker), aircraft is fitted with two angle of attack probes, one on each side of the forward fuselage.
CAPT AOA PROBE F/O AOA PROBE Angle of attack probe information is directly processed by the FWS. Critical angle of attack detected by angle of attack probes results in aural alert (cricket), stick shaker activation, and then stick pusher activation. In normal conditions, stick shaker and stick pusher triggering thresholds are elaborated by adding a ∆α value to angles of attack corresponding to the basic protections. ∆α depends on engine 1 & 2 torques and flaps configuration. Engine 1 torque signal is processed by MFC 1A and engine 2 torque signal is processed by MFC 2A. So, two ∆α are computed, but only the larger one is considered. The monitoring system uses: - One microswitch signal on PL handles - Both EECs - Four MFC modules. The failure of one of these elements invalids the associated ∆α. If a ∆α is invalidated, the system takes into account the other one. If both ∆α are invalidated, system chooses ∆α = 0. Note System operation goes unnoticed for the flight crew.
AIRCRAFT CRITICAL ANGLE OF ATTACK ALERT and STICK SHAKER ACTIVATION STICK PUSHER ACTIVATION FLAPS 0 15 30 0 15 30 HIGH POWER 10.9 ° 10.9 ° 9.9 ° 13.4 ° 14.1 ° 12.8 ° LOW POWER 10.9 ° 10.9 ° 10.4 ° 13.4 ° 14.1 ° 14.3 ° Whenever ICING AOA comes on, the aircraft is protected by an earlier stall threshold as follows: AIRCRAFT CRITICAL ANGLE OF ATTACK ALERT and STICK SHAKER ACTIVATION STICK PUSHER ACTIVATION FLAPS 0 15 30 0 15 30 TAKEOFF 8.4 ° 10.9 ° EN ROUTE 8 ° 8.4 ° 7.7 ° 10.6 ° 10.9 ° 10.8 °
Note - EN ROUTE values occurs, when 10 min have elapsed if takeoff was performed FLAPS 15 or immediately if takeoff not performed FLAPS 15 (ferry flight for instance) - Stall alarm alert and shaker are inhibited when aircraft is on the ground - Stick pusher activation is inhibited: o On ground o During 10 s after liftoff o In flight, provided radio altimeter is operative, when the aircraft descends below 500 ft.
STICK PUSHER NOT INHIBITED STICK PUSHER INHIBITED 10 SECONDS AFTER LIFT OFF 500 ft GROUND 0 ft - If radio altimeter gives an erroneous < 500 ft signal meanwhile IAS > 185 kt for more than 120 s (cruise), STICK PUSHER FAULT amber light will come on to notify the flight crew that stick pusher is inhibited.
Indicating & Recording: 3.2.4 With Aircraft System Failure¶
LEVEL 3 LEVEL 2 Failure detection - Aural alert: CRC - MW light flashing red - Red warning message on EWD identifying the failure - For all cases, a red light on the affected system control panel and/or on SD system page. - Aural alert: SC - MC light flashing amber - Amber caution message on EWD identifying the failure - Local alert light on the affected system control panel and/or SD system page. Acknowledgement of the failure by the flight crew Press MW light - MW light turns off - Aural alert is canceled. Press MC light - MC light turns off. Corrective action - lf the failure disappears, associated local alert light turns off, EWD message disappears - If the failure does not disappear, associated local alert light remains turned on, EWD message remains displayed. Press CLR pb on EFCP (after Procedure application) EWD message does not disappear Before starting descent, press RCL pb on EFCP. EWD messages, associated with systems where a failure persists, or, with a white light turned on, on the associated control panel will be displayed. EWD message disappears Take into account the failure consequences for the landing. Press CLR pb on EFCP (after Procedure application). Caution alert messages will disappear. Note The local alert lights always reflect directly the system status: They are never inhibited or cleared by any other mean than restoring normal functioning. When a local alert light disappears, the other alert sequence elements (MW/MC Iight, EWD messages, aurals) also disappear.
Indicating & Recording: 3.2.5 Operation with MFC Failure¶
In case of MFC 1B and 2B failure: - MC lights on without flashing - MFC amber message displayed on EWD - MFC 1B and 2B amber FAULT lights come on, on overhead panel. In these conditions, processing of alerts is as follows: - All level 2 alerts and CONFIG + ENG OIL + PROP BRK level 3 alerts are not processed. The flight crew has to monitor the overhead panel where the local alerts are still active - All other level 3 alerts are processed on EWD (without MW and CRC). If both FWA are detected failed, the FWS NOT AVAIL message is displayed on a blank black page on the procedure window. No alert message is displayed anymore and the flight crew has to monitor the instrument panels where the local alerts are still active. For failures detected by MFC, attention getters MC and SC or MW, and CRC are still activated.
Indicating & Recording: 4 ELECTRICAL SUPPLY¶
Indicating & Recording: 4.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) MFC 1B Primary supply DC BUS 1 (Overhead panel C/B 1B NORM SPLY) NIL Alternate supply DC EMER BUS (Overhead panel C/B 1B AUX SPLY) NIL MFC 2B Primary supply DC BUS 2 (Overhead panel C/B 2B NORM SPLY) NIL Alternate supply DC EMER BUS (Overhead panel C/B 2B AUX SPLY) NIL
Indicating & Recording: 5 SYSTEM MONITORING¶
Indicating & Recording: 5.1 FWS NOT AVAIL¶
This message is displayed amber on the EWD when: - Both AFDX switches are reported faulty (SWM 1 and 2 fault). The message is displayed on a blank black page on the lower part of the EWD. Alerts are no more displayed and the crew has to monitor the overhead panel. Attention getters MC and SC or MW and CRC are still activated. - Both CPMs are reported faulty (CPM 1 and 2 fault). The message is displayed on a blank black page on the lower part of the EWD. Alerts are no more computed and the crew has to monitor the overhead panel. For failures detected by MFC, attention getters MC and SC or MW and CRC are still activated. - Both FWA are detected failed (FWA 1 and 2 fault). The message is displayed on a blank black page on the lower part of the EWD. Alerts are no more computed and the crew has to monitor the overhead panel. For failures detected by MFC, attention getters MC and SC or MW and CRC are still activated. Note The flight crew is then headed toward the corresponding procedure to apply (See Procedure page)
EWD AFDX / FWS NOT AVAIL IF FPLN NOT AVAILABLE ON DISPLAY AVNX SWITCH 1+2 PROCEDURE ...........APPLY IF FPLN AVAILABLE ON DISPLAY IF TRIM IND NOT AVAILABLE AVNX CPM 1+2 LOSS PROCEDURE ....APPLY IF TRIM IND AVAILABLE AVNX FWS 1+2 LOSS PROCEDURE ....APPLY
Indicating & Recording: 5.2 AVNX FWS SGL CH-Alert¶
CONDITION VISUAL AURAL One of FWA detected faulty - MC light flashing amber - FWS SGL CH amber message on EWD SC
Indicating & Recording: 5.3 FWS 1+2 LOSS-Alert¶
CONDITION VISUAL AURAL FWS not available - REFER TO QRH on Procedure Window NIL
Indicating & Recording: 6 LATERAL MAINTENANCE PANEL¶
Indicating & Recording: 6.1 LH Maintenance Panel¶
On LH maintenance panel, a WARN section enables testing, on ground, of several warnings which cannot be tested on their own system. This section includes: - A selector to set the system to be tested - A PTT pb (Push To Test) to activate the selected test.
Note The selector must be replaced in NORM FLT position before flight.
CHAN 1 CHAN 2 PTT PITCH DISC EXCESS CAB ALT LDG GEAR NOT DOWN EXCESS CAB P TEST 3 TEST 2 TEST 1 YES VMO SMK NORM FLT STICK PUSHER/ SHAKER WARN 1 2 3
1 CHAN Lights Comes on green to check the two angle of attack channels for correct operation.
2 Selector System which can be tested: SMK MW, CRC, FWD SMK, AFT SMK, and ELEC SMK red message on EWD. EXCESS CAB ALT MW, CRC, EXCESS CAB ALT red message on EWD. PITCH DISCONNECT MW, CRC, PITCH DISCONNECT red message on EWD. LDG GEAR NOT DOWN MW, CRC, LDG GEAR NOT DOWN red message on EWD, red light in landing gear lever. EXCESS CAB ΔP MW, CRC, EXCESS CAB ΔP red message on EWD. VMO Clacker. STICK PUSHER SHAKER - YES - Stall cricket and both stick shakers are activated - After 10 s: o CHAN 1, CHAN 2 come on o Stick pusher is activated o Stick pusher indicators come on green. - Select WARN selector to NORM FLT - Monitor: o STICK PUSHER lights OFF o C/B 14 FU FLT CTL / C/B STICK PUSHER / C/B PWR SUPPLY in. STICK PUSHER SHAKER - TEST 1 - Stall cricket and left stick shaker are activated - After 5 s: o MC o FLT CTL amber message appears on EWD o Stick pusher FAULT pb comes on amber. STICK PUSHER SHAKER - TEST 2 - Stall cricket and right stick shaker are activated - After 5 s: o MC o FLT CTL amber message appears on EWD o Stick pusher FAULT pb comes on amber. STICK PUSHER SHAKER - TEST 3 - CHAN 1, CHAN 2 come on - Stall cricket and both stick shakers are activated. Note If ICING AOA is turned on: - YES procedure is the same - TEST 1 procedure is the same except that CHAN 1, CHAN 2 come on - TEST 2 procedure is the same except that CHAN 1, CHAN 2 come on - TEST 3 procedure is the same except that stick pusher is activated in the same time as shakers. 3 PTT Pushbutton After having selected a system with the selector, the PTT pb enables to activate the test. As soon as a test is initiated, MAINT PNL amber message will be displayed on EWD.
Indicating & Recording: 7 SCHEMATIC¶
Indicating & Recording: 7.1 Schematic¶
+--> [MFC 1] --+
AIRCRAFT SYSTEMS --+ +--> MW/MC + AUDIO
A429/discretes +--> [MFC 2] --+--> EMER AUDIO CANCEL
| |
+--> [CAC 1] --> [FWA 1] --+
+--> [CAC 2] --> [FWA 2] --+--> AFDX --> EWD / DU3
|
EFCPs -------------------------------------------------> inhibit/control inputs
Indicating & Recording: 8 FWS MANAGEMENT AND ECL¶
Indicating & Recording: 8.1 FWS Management and ECL¶
Note For human factor recommendations, Refer to Foreword, Refer to AFM - Engine Parameters and Refer to AFM - Automatic Flight Control System. FWS automatically generates alerts (Warnings and Cautions) when an abnormal system condition is detected. FWS automatically triggers procedures (when correctly documented) associated to abnormal system operation and/or icing conditions. FWS automatically displays related associated C/L. Easy access to C/L and procedures is enabled within FWS display area. The dedicated FWS area lies on the bottom of the EWD and is split between CAS window (left column), procedures and C/L window (right hand side area). 1) Alerts Alerts consists of WARNINGS and CAUTIONS. WARNING labels are specific, intuitive and self-explanatory. CAUTION labels are initially prefixed with QRH abnormal procedures titles. Pop-up CAS window alerts will trigger: - MW flasher is associated with CRC - MC flasher is associated with SC. Depressing corresponding flashers will turn these off and silence their associated chimes. - New following pop-up alerts will though trigger similar sequence of events. A new CAUTION pop-up alert, bearing similar class label as before uncleared alert, will not trigger any corresponding chime. - WARNING alerts cannot be cleared using CLR pb, while CAUTION alerts maybe. - CAUTION alerts maybe recalled using RCL pb provided condition is still pending. CAS display sorting sequence: - Warnings are displayed on top and sorted based on a specifically designed hierarchy. - Cautions are displayed below warnings if any, they are also sorted based on a specifically designed hierarchy. - CAS list may exceed CAS window capability. Therefore, a second (third etc.) list remain hidden and is indicated by an amber arrowhead lying to the bottom. Flight crew may display it, hitting RCL pb. Alerts (WARNING or CAUTION) may be associated with: - Neither procedure at all - One specifically dedicated procedure - Several activated procedures in accordance with operational context.
2) EWD Window EWD Window may be: - Empty if neither procedure nor C/L is activated - Displayed as a “PENDING PROCEDURE" if any active procedure was cleared before being correctly completed - One given PROCEDURE (or C/L) displayed on a single or several pages. 3) Check Lists FWS is designed to detect either current ground and flight phases. CHECK LISTS will be purposely triggered on a timely manner: - FINAL COCKPIT PREPARATION with PRKG BRK on and ACFT either powered using GPU or HOTEL Mode. - BEFORE PROPELLER ROTATION will be pending until FINAL COCKPIT PREPARATION is completed - BEFORE TAXI once one engine is running and associated Condition Lever is set to AUTO or OVRD - TAXI once PRKG BRK is released - BEFORE TAKEOFF once TO CONFIG TEST pb is pressed - AFTER TAKEOFF once ACFT is set airborne - DESCENT upon final descent phase detection - APPROACH is pending following DESCENT completion - BEFORE LANDING upon final approach phase detection - AFTER LANDING upon touchdown once airspeed gets below 40 kt - PARKING follows AFTER LANDING once PRKG BRK is set ON - LEAVING AIRCRAFT is pending once PARKING is completed. Note The checklists automatic trigger may be impacted by an inoperative function (e.g. with parking brake signal inoperative, the TAXI checklist will not automatically be displayed ). In that situation, the associated checklist must be manually selected from NORMAL CHECK LISTS in the PROC MENU. 4) Normal Procedures NORMAL PROCEDURES may be associated to icing conditions: - With ICING being detected and/or DE ICING AIRFRAME pb being selected ON, ICE ACCRETION procedure will be activated (FAA requires ENTERING ICING CONDITIONS procedure to be activated upon ENGINE DEICING selection). - If ICING AOA condition is active, deselecting ANTI ICING HORNS pb will trigger LEAVING ICING CONDITIONS procedure. 5) Emergency and Abnormal Procedures EMERGENCY PROCEDURES are associated with a red WARNING label. ABNORMAL PROCEDURES are associated with a red WARNING or to an amber CAUTION label.
EMERGENCY or ABNORMAL procedure is cancelled if: - None item of procedure is acknowledged and/or associated WARNING or CAUTION condition is not anymore valid. - Items of procedure are acknowledged all with “PROCEDURE COMPLETED" prompt down to the bottom of the procedure page. All procedures and C/L may be manually browsed, using EFCP PROC MENU pb. Manually activated procedure title is “MAN" suffixed on RH side of the line. 6) Procedure and Status Pages Layouts A PROCEDURE body starts with title (line 1) and an optional subtitle (line 2) when a sub-procedure is engaged. PROCEDURE embodies 3 main parts: - Itemized list of actions that needs be completed following displayed steps to immediately resolve failure consequences - deferred items to be later applied for specific flight phases, taking into account failure’s future operational consequences. Those flight phases might be “icing conditions", “before approach", “before landing", “after touchdown" etc. - Failure’s resulting limitations. Three pushbuttons are designed to scroll and browse within procedures: - Two arrowheads pushbutton (for up and down scrolling) move a blue outlined highlighted frame all along item list - One dedicated pushbutton enables for boxed item acknowledgement. Once all items are completed & acknowledged, procedure and/or C/L is now completed and a “PROCEDURE COMPLETED" caption pops out. Once complete, “PROCEDURE COMPLETED" caption needs be acknowledged itself with: - No pending procedure, C/L or status, procedure window turns blank - One pending procedure, C/L or status, a “PROC MENU" page is activated. Flight crew is kept aware of yet to apply procedure list and related status for flight remainder. “PROC MENU" displays pending list and associated menu - Only one pending C/L along with a currently open procedure (C/L), the first one will be recalled after corresponding “PROCEDURE COMPLETED" acknowledgement.
PROCEDURE TITLE SUB TITLE ACTIONS TO PERFORM NOW ACTIONS DELAYED TO A FURTHER PHASE LIMITATIONS PROCEDURE COMPLETED STATUS TITLE SUB TITLE ACTIONS DELAYED TO A FURTHER PHASE LIMITATIONS INOP FUNCTIONS
Within a given procedure, mandatory items (those displayed in first part of the procedure) are labeled in cyan. They turn white once acknowledged. Other items are shown in white, excepting caution items (amber) and/or warning items (red). Further flight phase postponed actions and limitations are automatically embodied in pending stored status of the list. “STATUS" begins with a title (and subtitle if triggered by sub-procedure). “STATUS" is made of 3 parts: - DEFERRED ACTIONS to be later applied in specified flight phase, in order to consider deferred failure operational consequences. Flight phase may be “icing conditions", “approach", “before landing", “after touchdown" etc. - LIMITATIONS related to failure and applied actions - Failure associated INOP EQUIPMENT list (not exceeding 3 pages).
To help PROCEDURE or STATUS items browsing, a blue highlighted box helps focusing each item. When PROCEDURES or STATUSES are displayed on more than 2 pages, white PROCEDURES and amber STATUSES page numbers are displayed. 7) Algorithms of the Procedure FWS is not able to detect all related operational scenarii. Flight crew must choose most appropriate scenario as applicable. These options are highlighted with sub-title of the procedure. Selecting an option needs all preceding items be acknowledged Option list is identified by flight crew using colored fonts: Activating an option also activates associated sub-menu. Once option is activated, “PREVIOUS CHOICE" prompt on line 3, enables returning to option list to change previous selection. a) Conditional Action of the Procedure Conditional action is identified by flight crew using colored fonts: b) Conditional Phase of the Procedure Conditional Phase is identified using colored fonts: c) Clearing/Deleting C/L - Procedures or Statuses 1) EWD window displayed PROCEDURES, C/L or STATUSES: - Hitting CLR pb deletes PROCEDURES, C/L and STATUSES from being displayed on EWD window A “PENDING PROCEDURE" caption will remind a pending C/L or PROCEDURE on EWD. - Pressing MAN DEL pb more than 3 s will clear displayed PROCEDURE or C/L from EWD window until pilot hits RCL pb again, though recalling related PROCEDURE or C/L if triggering conditions are still valid. 2) EWD window active PROC MENU page - Pressing MAN DEL pb more than 3 s will delete boxed PROCEDURE or C/L until Pilot hits RCL pb again, though recalling related PROCEDURE or C/L if triggering conditions are still valid - Pressing MAN DEL pb more than 3 s will clear boxed STATUS MAN (bad label, MAN STATUS is a lot better). Automatic STATUSES cannot be cleared.
d) Procedures and C/L Automatic Management - Blank EWD window will automatically display newly triggered procedure or C/L - Displayed “PROCEDURE PENDING” on a blank EWD window will be bypassed to display a newly triggered procedure or C/L - Displayed procedures or C/L will get their newly triggered similar or sub-leveled counterparts stored in the PENDING LIST with a related CAS window caption to get flight crew correctly reminded - No items acknowledged and displayed lower level procedure or C/L will automatically be bypassed by any highly leveled newly triggered ones o Then, previously displayed procedure is stored, based on its rank, in the PENDING LIST (alert CAS window caption is kept displayed if related procedure is still active o Previously displayed procedure is automatically cleared of EWD WINDOW if triggering conditions are no longer valid o Manually open procedures or C/L are not stored in the PENDING LIST (therefore no CAS window caption is displayed). - All activated “WARNING" PROCEDURES automatically bypass lower rank procedures or C/L o Previously displayed procedure is then stored in the PENDING LIST based on its rank (CAS window corresponding caption is still displayed). o If triggering conditions are no longer valid, associated procedure is cleared (so is the associated CAS window caption). o Manually open procedures or C/L are not stored in the PENDING LIST (nor was CAS window caption displayed). - With an active PROC MENU page, once a new CAUTION procedure or C/L is triggered, associated PROC MENU page is kept displayed while procedure pending list is automatically refreshed with this newly triggered CAUTION procedure, appropriately listed based on its rank. Highest ranks are sorted with focus to the top of associated pending list. - Newly triggered WARNING procedure is automatically sorted and displayed on associated active PROC MENU page. - Active and browsed PROC MENU will: o Automatically display newly triggered WARNING procedure o Open any of 3 EMERGENCY/NORMAL/ABNORMAL sub-menus, all along with newly triggered CAUTION procedure or C/L, appropriately stored in the pending list with unaltered sub-menu page.
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 Description¶
(Applies: 1126) The Electronic Flight Bag (EFB) installed on ATR aircraft is a Class II system. The aim of this system is to provide documents viewer and performance calculation in electronic format in order to reduce: - Flight crew workload - Paper quantity in cockpit. Main components of the EFB installation are: - Two EDUs (Captain and First Officer) - Two EMUs (Captain and First Officer) - Two Mounting devices (Captain and First Officer). The Electronic Display Unit (EDU) contains the processor, memory, display and back-up batteries for stand alone operation (30 min autonomy). The Expansion Module Unit (EMU) is the interface that provides normal power supply (DC BUS) to the EDU and connectivity to the aircraft. EMUs EDUs
Main Enter Esc Apps PgUp PgDn Video Main Enter Esc Apps PgUp PgDn Video The EFB has two independent sides to ensure no possibility of induced failure from one side to the other: - The power supplies are segregated - GPS inputs are common but the cable’s routes are separated.
The Cross Talk optional function permits sending the screen visualization from one EDU to the other one. GPS EMU CAPT EMU F/O DISCRETE DC BUS#1 DC BUS#2 CAPT F/O EDU EDU CROSS TALK
(Applies: 1054;1124;1142-1283) The Electronic Flight Bag (EFB) installation is aimed at hosting a portable EFB. Each EFB installation consists in an individual mounting arm and associated power supply. Users are able to operate the EFB either on hands or mounted. The aim of the EFB is to provide documents viewer, performance calculation, navigation chart and any other applications in electronic format in order to reduce: - Flight crew workload - Paper quantity in cockpit.
The main components of the EFB installation are: - Two mounting arms (Captain & First Officer) - Two USB power supply (Captain & First Officer). The flight crewmembers can reach each of their reserved EFB on the mounting arms while strapped in normal seating position. The portable EFB can be detached from the mounting arm easily by unlocking the latch handle. Cradle position may be adjusted and is locked/unlocked by the lever located on the mounting arm Note Cradle position should only be adjusted when the EFB is installed.
EFBs
Cradle USB Power Supply Cap Arm 196.6mm 251.4mm 18.4mm Latch Handle
Indicating & Recording: 2 CONTROLS¶
Indicating & Recording: 2.1 EFB Screen¶
(Applies: 1126) 1 2 3 4 5 6 7 8 9 10 11 12 13 14 B 5 4 A
Main Enter Esc Apps PgUp PgDn Video 1 POWER pb Switch on the EFB when pressed for more than 1 s. Switch off the EFB when depressed for more than 2 s then validated (to avoid unwanted shutdowns in critical phases). 2 MENU SELECT KEYS Direct access to the MAIN, TOOLS and COMMS sub menus of the EFB. 3 BRIGHTNESS ADJUSTEMENT Moon key permits dimming the screen and the sun key increasing its brightness. 4 LINE SELECT KEYS To select applications / functions. 5 ZOOM IN/ ZOOM OUT KEYS To zoom in / zoom out. 6 VIDEO KEY Not used.
7 MAIN KEY To go directly to the main menu page. Pressed twice, show the list of all the applications running. 8 ESC KEY To escape the current application. 9 ENTER KEY To validate a selection. 10 APPS KEY To show the list of all the applications running. 11 ARROWS KEYS Permits navigating within a displayed document, chart or application. When left and right arrows are pressed simultaneously the screen will be displayed in landscape mode. When up and down arrows are pressed simultaneously the screen will be displayed in portrait mode. 12 PgUp and PgDn KEYS Permits navigating within documents. 13 HOT KEY To access directly a specified application if defined in the EFB setup. 14 CLOSE KEY To leave the current page. A AMBIENT LIGHT SENSOR Automatically adjust the screen brightness in accordance to cockpit luminosity. B TOUCH SCREEN “Film-on-glass” touch sensitive screen. Most of the function can be directly accessed by finger tipping the on screen application icon.
Indicating & Recording: 2.2 Physical Keyboard¶
(Applies: 1126) 1 2 3 4
1 NUMERICAL KEYBOARD 2 ALPHABETIC KEYBOARD 3 FUNCTION KEYS Bottom part of the physical keyboard. 4 KEYBOARD LATCH When lifted permits the screen to slide upward and access to the physical keyboard.
Indicating & Recording: 3 ELECTRICAL SUPPLY¶
Indicating & Recording: 3.1 Electrical Supply¶
(Applies: 1126) EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) EMU-EDU 1 (CAPT) DC BUS 1 INTERNAL BATTERY (EDU only) NIL EMU-EDU 2 (F/O) DC BUS 2 INTERNAL BATTERY (EDU only) NIL
(Applies: 1054;1124;1142-1283) The USB ports provide 5VDC / 2 A. EFB power connector for Captain is connected to DC Bus 1, and EFB power connector for First Officer is connected to DC Bus 2. A removable cap is fixed on each connector. This cap must be installed on the connector when the Portable EFB is not connected.
Indicating & Recording: 4 SYSTEM MONITORING¶
Indicating & Recording: 4.1 System Monitoring¶
(Applies: 1126) The system is monitored through the power pushbutton. The incorporated diode can indicate six EFB states: System State Power Source Power Diode Indicator System Off No power No light DC BUS powered Flashing Green Start Up Temperature out of range Flashing Amber System On DC BUS powered Steady Green (Charging) Internal battery Flashing Green Internal battery (low) Flashing Amber
Indicating & Recording: 1 DESCRIPTION¶
Indicating & Recording: 1.1 Description¶
The printer is used to print MCDU data (ACARS messages, VMS data, ...)
TURN PPR ADV SELF TEST PWR ON ALERT RESET PTR BUSY TURN OPEN TO TO CLOSE SLIDE UP SLIDE DOWN 1 2 3 4 5 1 PPR ADV pb Advances paper as long as pushbutton is pressed. 2 SELF TEST pb Produces a test pattern as long as the pushbutton is pressed. 3 PWR ON Light Comes on green whenever AC power is applied. 4 ALERT RESET pb Enables to reset the aural/visual alert function. 5 PTR BUSY Light - Comes on amber upon receipt of first text character and remains on until paper has advanced three lines beyond tear off edge. - Flashes continuously after using PPR ADV pb until the RESET pb is pressed.
Indicating & Recording: 2 ELECTRICAL SUPPLY¶
Indicating & Recording: 2.1 Electrical Supply¶
EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Printer Power Supply AC BUS 2 (Overhead panel - position A11 - C/B MPC / PTR)