Integrated Systems¶
Integrated Systems: 1 DESCRIPTION¶
Integrated Systems: 1.1 GENERAL¶
Integrated Systems: 1.1.1 General¶
The MPC unit is including two parts: - Flight Data Acquisition Unit (FDAU) - Data Management Unit (DMU)
Integrated Systems: 1.2 FDAU¶
Integrated Systems: 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).
Integrated Systems: 1.3 DMU (DATA MANAGEMENT UNIT)¶
Integrated Systems: 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.
Integrated Systems: 2 ELECTRICAL SUPPLY¶
Integrated Systems: 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
Integrated Systems: 3 SCHEMATIC¶
Integrated Systems: 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
Integrated Systems: 4 LOST EQUIPMENT LIST¶
Integrated Systems: 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
Integrated Systems: 1 DESCRIPTION¶
Integrated Systems: 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.
Integrated Systems: 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.
Integrated Systems: 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).
Integrated Systems: 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
Integrated Systems: 2 CONTROLS¶
Integrated Systems: 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.
Integrated Systems: 3 OPERATION¶
Integrated Systems: 3.1 Introduction¶
Charts on the following pages list the implementation and availability of the functions ensured by each module.
Integrated Systems: 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.
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 3.6 Light¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B LIGHT LIGHT TEST
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 3.10 Idle Gate¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B IDLE GATE IDLE GATE CTL IDLE GATE AMBER ALERT
Integrated Systems: 3.11 Engine Start¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B ENGINE START START indicator LIGHTS
Integrated Systems: 3.12 Engine¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B ENGINE HIGH FLIGHT IDLE
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 3.16 Hydraulic¶
SYSTEM FUNCTION MODULE 1A 1B 2A 2B HYDRAULIC BLUE HYDRAULIC PUMP (CTL) GREEN PUMP LO PR INDICATION
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 4 ELECTRICAL SUPPLY¶
Integrated Systems: 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
Integrated Systems: 5 SYSTEM MONITORING¶
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 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
Integrated Systems: 6 LATERAL MAINTENANCE PANEL¶
Integrated Systems: 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.
Integrated Systems: 7 SCHEMATIC¶
Integrated Systems: 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.