Airbus ESLD ECAM System Logic Data

ECAM SYSTEM LOGIC DATA

RECORD OF REVISIONSATA How to use 31 Revision n Date Revision 00 00 May 01/03 May 01/03 ATA Revision n Date Revision

Effectivity :

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R.O.R. 1

Date : May 01/03


Revision n : 00

Date :

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ATA 31

P Effectivity

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ReasonsFWC H2E4 Software (Mod 30660P6801)

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ATA HIGHLIGHTS Page : Date : 1 May 01/03

Printed in France

ESLD (ECAM SYSTEM LOGIC DATA)AIRBUS A319/A320/A321:

HOW TO USE

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ECAM System Logic Data( CAUTION: ( THE DESCRIPTION OF THE SYSTEM LOGIC GIVEN IN THIS PRODUCT ISNOT EXHAUSTIVE AND DOES NOT COVER THE TOTAL SYSTEM LOGIC. IT IS PROVIDED ONLY AS AN AID TO HELP YOU UNDERSTAND THE SYSTEM AND TROUBLESHOOT THE AIRCRAFT.

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ECAM System Logic Data( The ESLD can be used to find the following information:( ( ( ( ( ( ( ( ( (Required computer inputs Applicable computer logic Type of computer input (digital, ARINC, etc.) Messages (text code) Procedure and status messages Color of messages Flight phase inhibition ARINC label data Aural warning generation data Overhead panel annunciator light data

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ECAM System Logic Data( The ESLD Covers :( Chapter 31-51: ( ESLD FWS Description/Operation ( Warning index ( Contains each warning criteriom (warning-page presentation (corresponds to ATA31-51-00 to 31-51-77)) ( FWC Display Logic

( Chapter 31-52: ( FWC Description/Operation ( Describes and details the FWC input/output signals ( Describes the FWC connector pin assignment ( Chapter 31-54: ( SDAC Description/Operation ( Describes and details the SDAC input/output signals ( Describes the SDAC connector pin assignment4

ECAM System Logic Data( I ) ESLD Bookmark

ESLD FWS Description /Operation Access to Warning Criteria page and FWC Display Logic through the alarm index Access to Warning Criteria pages Access to FWC Display Logic ESLD FWC Description /Operation FWC Pin Assignment FWC input/output signals ESLD SDAC Description /Operation SDAC Pin Assignment SDAC input/output signals

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ECAM System Logic Data( II ) FIND Command Key

1. The Find command key is used for quick access to specific data. 2. You can select the Match Whole Word Only box if you want that the information you enter matches exactly the writing format of the source data.

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ECAM System Logic Data( III) Copy of data :A. T function ( ):

1. Use the T function

2. Drag the pointing device and highlight the data you want to copy 3. Press Ctrl-C 4. Get access to the file that may contain the data 5. Press Ctrl-V in the find funtion ( 6. Search Result is hightlighted in blue )

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ECAM System Logic Data( IV ) Warning Index menu:A. Search function ( ): Example: Warning AVNCS SYS FAULT

1. Use the Find Function

2. Type AVNCS SYS FAULT 3. Click on Find

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ECAM System Logic Data( IV ) Warning Index menu (Contd):A. Search function : Example: Warning AVNCS SYS FAULT

4. Search Result is Highlighted in Blue

5. Drag the pointing device in corresponding area (blue box) and click

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ECAM System Logic Data( IV ) Warning Index menu (Contd):A. Search function : Example: Warning AVNCS SYS FAULT

6. Associated Warning Criteria page is displayed

7 Read the Warning Criteria page effectivity ST1 = applies to all A320 aircraft ST2 = applies to all A321 aircraft ST3 = applies to all A319 aircraft ST4 = applies to all A318 aircraft

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ECAM System Logic DataA. Search function (Contd): In case of a restricted effectivity, do the following steps:

7 (a) . Read the Warning Criteria page effectivity (

)

7 (b). Drag the pointing device in corresponding area and click

7 (c). Next Warning Criteria page with effectivity change is displayed (

) if any ...

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ECAM System Logic DataA. Search function (Contd): In case of a restricted engine effectivity, do the following steps: 7 (d) . Read the Warning Criteria page effectivity ( )

7 (e). Drag the pointing device in corresponding area and click (next page)

7 (f). Next Warning Criteria page with engine effectivity change is displayed (

) if any ...

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ECAM System Logic Data( IV ) Warning Index menu (Contd):A. Search function : Example: Warning AVNCS SYS FAULT 8. Drag the pointing device in corresponding area (blue box) and click

9. Associated Logic diagram is displayed.

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ECAM System Logic Data( IV ) Warning Index menu (Contd):A. Search function : Example: Warning AVNCS SYS FAULT 10. Drag the pointing device in corresponding area and click

11. Associated alarm text is displayed

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ECAM System Logic Data( IV ) Warning Index menu (Contd):B. Part description: Each Logic Page is divided into two parts: Example: Warning AVNCS SYS FAULT

B.1. System Logic Part (logic diagram) corresponds to the logic number correspond to: (a) the title of the alarm (b) or the A/C warning wording

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ECAM System Logic Data( IV ) Warning Index menu (Contd):B. Part Description: Each Logic Page is divided into two parts: Example: Warning AVNCS SYS FAULT B.2. Typical System Logic Page (second part): Displayed Message

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ECAM System Logic Data( IV ) Warning Index menu (Contd)C. Meaning of data logics: Example: Warning AVNCS SYS FAULT

Message Generation Logic

Inputs

Operational data

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ECAM System Logic Data( IV ) Warning Index menu (Contd)C. 1. Detailed information: Example: Warning AVNCS SYS FAULT

Inputs:SDAC/003-00/23#I = Input source/ARINC Label-SDI/BIT#Logic 1 or 0 AVIONICS VENT FAULT = Signal name VAVF = Signal code or = Type of inputs

Message Generation Logic

Operational dataAural warning Visual warning Text code (text code transmitted in ARINC 429 format via labels 112 ( ) and 357 ( )) DU system page Flight phase inhibition 18

ECAM System Logic Data( IV ) Warning Index menu (Contd)C.2. Meaning of main typical signals symbols of a FWC Display Logic page

Input signals:= Boolean value: FWC input bus = Analog Input = Incoming discrete from FWC connector = Numerical value taken from SDAC or another BUS

Internal signals= Incoming signal logic sheet = Incoming numerical value from another sheet

Output external signals= Out boolean value available for processing = Outgoing numerical value available for processing 19

ECAM System Logic Data( IV ) Warning Index menu (Contd):D. Displayed text: Example: Warning AVNCS SYS FAULT

Displayed text

VENT = Heading AVCNS SYS FAULT = Title of the ECAM warning

Text Color

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ECAM System Logic Data( V ) Warning Criteria menu:A. Search function ( ): Example: Warning AVNCS SYS FAULT

1. Use the Find Function

2. Type AVNCS SYS FAULT 3. Click on Find

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ECAM System Logic Data( V ) Warning Criteria menu (Contd): :A. Search function : Example: Warning AVNCS SYS FAULT 4. Search Result is Highlighted in Blue

5. The requested Warning Criteria page is displayed (with AVNCS SYS FAULT highlighted in blue).

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ECAM System Logic Data( VI ) FWC Display Logic menu:A. Search function: Example: Signal Name VAVF 1. Use the Find Function

2. Type the Signal Name VAVF 3. Click on Find

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ECAM System Logic Data( VI ) FWC Display Logic menu (Cont d):A. Search function: Example: Signal Name VAVF 4. Search Result is Highlighted in Blue

5. The requested VAVF signal is displayed on its associated FWC Display Logic page

VAVF

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ECAM System Logic Data( VI ) FWC Display Logic menu (Cont d):B. Search function: Example: find all logics with signal VAVF as an entry in the FWC Display Logic menu 1. Click on the FWC Display Logic menu of the bookmark to return to the first page of this index:

2. Click on the Hand Tool section ( in blue in the FWC Display Logic menu)

) (do steps 2. and 3. only if your previous data is always highlighted

3. Then click on the file of the FWC Display Logic page: now the first page of the FWC Display Logic file is active

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ECAM System Logic Data( VI ) FWC Display Logic menu (Cont d):B. Search function: Example: find all logics with signal VAVF as an entry in the FWC Display Logic menu 4. Do steps 1., 2. and 3. in para. (VI), A. with VAVF 5. Search Result is Highlighted in Blue 6. The requested logic of VAVF signal is displayed on associated FWC Display Logic page

VAVF signal

7. Click on Find Again in the Find Function as many times as necessary to have all logics linked VAVF signal 8. As soon as the end of the FWC Display Logic menu is reached, it means that you are on the next menu (see para. ( VI ), C.: tip to know when you have reached the end of the FWC Display Logic menu) 9. Stop the find function (click on Cancel)

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ECAM System Logic Data( VI ) FWC Display Logic menu (Cont d):C. Tip to avoid searching a data in a menu other than the one selected Example: search signal VAVF in the FWC Display Logic menu 1. Click on the menu just below FWC Display Logic

2. Record the page number of the index page, e.g. 4109: It means that the last page of the FWC Display Logic menu is 4108 3. Click on the FWC Display Logic menu

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ECAM System Logic Data( VI ) FWC Display Logic menu (Cont d):C. Tip to avoid searching a data in a menu other than the one selected Example: search signal VAVF in the FWC Display Logic menu 4. Do all steps in para. (VI), B. 5. When the last existing VAVF signal is found in the FWC Display Logic menu, the index page number continues to increment

6. As soon as page 4109 appears, it means that you are on the next menu (next menu is FWC Acquisition/Interface) and that no other VAVF signal has been found 7. Stop the find function (click on Cancel)

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ECAM System Logic Data( VII ) FWC Signals menu:A. FWC Signals menu (Search function) : Example: Signal Name VAVF

1. Use the Find Function 2. Type the Signal Name VAVF 3. Click on Find

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ECAM System Logic Data( VII ) FWC Signals menu (Cont d):A. FWC Signals menu (Search function) : Example: Signal Name VAVF 4. Result is Highlighted in Blue

5. : Signal identification : Label-SDI/Bit input : Signal Type : Signal Kind I/O = Input/Output : Source name : ATA chapter : Wiring Code : FWC Input Connector/Pin 30

ECAM System Logic Data( VIII ) FWC Connector menu:A. FWC Connector menu: Example: Signal Name VAVF : allocation from FWC Signal Index:

FWC connector pin assignment for VAVF signal: is on Left Medium (Middle) Plug (LMP) 04,JK and Right Medium (Middle) Plug (RMP) 04,AB (not shown) 31

ECAM System Logic Data( IX ) SDAC Signals Index :A. SDAC Signals menu (Search function) : Example: Signal Name VAVF 1. Result is Highlighted in Blue

2. : Signal identification : Label-SDI/Bit input : Signal Type : Signal Kind I/O = Input/Output 32 : Source name : ATA chapter : SDAC Input Connector/Pin

ECAM System Logic Data( X ) SDAC Connector menu:A. SDAC Connector menu: Example: Signal Name VAVF : allocation from SDAC Signal Index:

SDAC connector pin assignment for VAVF signal: is on Right Top Plug (RTP) 12C 33

ECAM System Logic Data( Summary( (example for AVNCS SYS FAULT ECAM warning) (Refer to Warning Index menu ( Refer to Warning Criteria menu (Refer to FWC Display Logic menu (Refer to FWC Signals menu (Refer to FWC Connector menu (Refer to SDAC Signals menu (Refer to SDAC Connector menu

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1. General A. Objectives This section defines the warning function of the ECAM system. The WARNING function: - informs the crew of a failure, dangerous configuration and its degree of seriousness - clearly identifies the failed system or dangerous configuration - indicates the appropriate corrective action without the risk of confusion. These objectives are achieved by generating visual, aural, etc. signals transmitted by specific peripherals: annunciator lights, display units, loud speakers, etc. In addition, the warning system provides other functions such as automatic call out of altitude, decision height, computing reference speeds and indicating when is necessary to refer to the QRH by "LDG DIST PROC...APPLY", etc. This section does not define the aspects which are mentioned elsewhere: e.g. internal software architecture is defined by the Vendor (refer to Vendor documentation). e.g. ARINC 429 arrangement is defined by ARINC Specification. e.g. the link and protocol to the CFDS is mentioned in ABD0018.

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B. Basic Principles (1) Cockpit "Lights out" philosophy Under normal operating conditions, annunciator lights are off. The use of annunciator lights to indicate correct operation is limited to a few examples of temporary but normal operation of a system. (2) Detection principle Comprises three phases: - Warning : Aural (chime) and visual (MASTER CAUT or MASTER WARN lights) - Identification: Aural (specific sound), visual (display unit) - Location : Detailed, ordered display (display unit). C. ECAM Data Interpretation (1) Annunciator lights The color code used complies with SAE recommendations. (a) Warnings 1 Red: Configuration or failure requiring immediate action. 2 Amber: Configuration or failure not requiring immediate action, the decision is made by the crew.

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(b) Indications 1 2 3 Green: Normal long term configuration. Blue: Normal short term configuration. White: Indication of a controlled function. Flashing: draws the attention of the crew for rapid fault finding in the event of a failure or monitoring an action to be carried out.

(2) Display units The color code used on display units for the warning function is as follows: - Red: Configuration or failure requiring immediate action. - Amber: Configuration or failure not requiring immediate action. - Cyan: Action to be carried out. - White: Action already carried out. - Green: Indications. (3) Aural indications (a) General sounds: single chime or repetitive chime for awareness. (b) Specific sounds for "instinctive" reactions. (c) Synthetic voice: identification or altitude call out. D. Definition of Warning Levels Warnings are classified in levels according to the importance and urgency of the corrective action required.

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(1) LEVEL 3 Corresponds to an emergency configuration. Corrective action must be taken by the crew immediately. The following warnings fall into this category: - aircraft in dangerous configuration or in limit flight condition - system failure modifying flight conditions - major system failure. Visual warning: red Aural warning: repetitive chime or specific sound. (2) LEVEL 2 Corresponds to an abnormal aircraft configuration. Immediate corrective action is not necessary but the crew must decide when to take the action. This level mainly comprises system failures which do not have direct effect on flight safety. Visual warning: amber Aural warning: single chime. (3) LEVEL 1 Corresponds to a caution configuration requiring monitoring of the system concerned by the crew. This level mainly concerns failures leading to system degradation. Visual warning: amber No aural warning. (4) LEVEL 0 Corresponds to an information configuration not requiring action. Display: blue, green or white. No sound. E. Classification of Warnings in Order of Priority Warnings are classified in levels as follows: - Level 3 has priority over levels 2, 1 and 0 - Level 2 has priority over levels 1 and 0 - Level 1 has priority over level 0. Within each level, an order of priority has been defined. The list of warnings given below (Ref. para. 3.C) defines the priority of warnings displayed on the display unit. The associated aural warnings have the same priority.

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ECAM SYSTEM LOGIC DATACertain level 3 warnings are not displayed on the display unit; their aural warnings are broadcast in accordance with the list of priority below for all level 3 warnings. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Stall Over speed Engine dual failure Engine fire APU fire Takeoff configuration Sidestick fault Excessive cabin altitude Engine oil lo pressure L + R Elevator fault Landing gear Autopilot disconnection Auto land Smoke Emergency configuration Dual hydraulic failure

F. Types of Failures and Warnings - Status - Memo (1) Independent failures and warnings A system failure which does not lead to the malfunction of other systems is said to be independent; it only causes a single independent warning. e.g.: failure of the radio altimeter. (2) Primary and secondary failures and warnings A system failure which leads to the malfunction of other systems is said to be primary. e.g.: engine failure. The consequences of this failure on other systems are called secondary failures. e.g.: failure of the IDG. The associated warnings are said to be primary and secondary respectively. (3) STATUS Status indicates the operational status of the aircraft on the display unit. (4) MEMO Memo indicates the configuration of certain auxiliary systems such as: parking brake, anti ice system. EFF : ALL

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2. Characteristics A. System Organization (Ref. Fig. 001) The system comprises the following: - a Navigation Display (ND) and a Primary Flight Display (PFD) on the Captain main instrument panel - a Navigation Display (ND) and a Primary Flight Display (PFD) on the First Officer main instrument panel. - two ECAM (ENGINE/WARNING and SYSTEM/STATUS) display units on the center instrument panel - three Display Management Computers (DMC) common to the EFIS/ECAM in the avionics compartment - two Flight Warning Computers (FWC) (this specification) in the avionics compartment - two System Data Acquisition Concentrators (SDAC) in the avionics compartment - a Flight Control Unit (FCU) on the glareshield - an ECAM control panel on the center pedestal - transfer pushbutton switches - display unit brightness controls (potentiometers) - a MASTER CAUT light and a MASTER WARN light on the Captain glareshield panel - a MASTER CAUT light and a MASTER WARN light on the First Officer glareshield panel - two loud speakers. B. Interfaces The FWCs perform numerical and boolean computations. Boolean and numericals are transmitted by interfaces which receive various electrical signals (discrete, ARINC 429, synchro...) from the aircraft systems. These interfaces comprise connections, electrical protection systems, filters, wave-shaping and digitizing systems. The acquisition cycle is less than 120 ms. The results of these computations are managed by a MONITOR which, automatically or on request, sends the computer output variables such as loud speaker activation, warning display to the crew, to the interfaces. The output interfaces comprise electrical signal shaping, protection and connection systems. The output signals are of the discrete, ARINC 429, RS 422, low frequency type. Some inputs and outputs are protected against lightning strikes.

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EFIS/ECAM Architecture Figure 001 EFF : ALL

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(1) Connector Inputs and outputs are made on a single ARINC 600 size 3 connector (600 contacts for signals plus contacts for power supply) (Ref. Fig. 002). (2) Power supply The FWC1 power supply is via the AC ESS BUS busbar. The FWC2 power supply is via the AC BUS2 busbar. (For connection, refer to 31-50-00). (3) Input interfaces The computer is fitted with all protection systems. All parameters or groups of parameters acquired are allocated validity which is the result of the test of receivers and of the type of signal and its contents, if necessary. (a) Discrete inputs In accordance with ARINC specifications, discrete signals from the aircraft systems connected to an input interface are DC voltages between 0 and 36 volts. There are two valid zones. 36 18 3.5 0 V V V V -------------------------Voltage applied or disappearance of ground --------------------------------------------------Application of ground or disappearance of voltage -------------------------high level zone not used low level

NOTE : When reading logic charts, use positive logic, i.e., logic 1 must correspond to each name, term or expression defining a discrete signal. NOTE : For acquisition (in accordance with ARINC specifications), negative logic can be used i.e., logic 0 corresponds to a name, term or expression defining a discrete signal. In this case, an (IP-), (IP-0), (IP+) or (IP+0) indication is given and switching to positive logic is performed by software or hardware inversion of the signal. After inversion, the indicating label is the same as before but without the indication (IP-), EFF : ALL

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Rear Connector of FWC Figure 002 EFF : ALL

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(IP-0), (IP+) or (IP+0). NOTE : Similarly, the (I) indication can apply to booleans if necessary (discrete signals on ARINC words). Each discrete input comprises a first order low pass filter whose time constant is between 7 and 20 ms. Acquisition of discrete signals is in groups of eight. The result of the test of each receiver circuit validates each group. (b) ARINC 429 inputs The computer acquires ARINC 429 digital buses. For each label, the discrete or digital values and the sign/status matrix (SSM) are stored and validity is allocated to it. The computer is capable of detecting a refresh or parity failure. An internal test enables the malfunction of the source or a failure on the receiver circuit to be detected. Validity is allocated to each label. (c) Analog inputs (Synchro) There are 6 analog inputs of the synchro type. Synchro signals encode angle values from 0 to 360 degrees and acquisition accuracy is to 1 degree. Other signals have a range of 60 degrees and acquisition accuracy is to 0.18 degree. (4) Output interfaces All output interfaces are protected against short circuits on the ground or a positive voltage up to 10 volts for discrete outputs and 36 volts for other types of outputs. (a) Discrete outputs The computer has 16 discrete outputs of the ground/open type. - in the open state, each output has a maximum leak current of 10 microamperes for an applied voltage of less than 36 volts. - in the closed state (ground), the current capacity is 300 milliamperes. These outputs are steady or flashing according to software programming. EFF : ALL

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They flash at a frequency of two hertz and are synchronized in frequency and in phase with the opposite FWC. One output indicates computer status: - ground: correct operation - open: incorrect operation. (b) Audio outputs Each computer has two identical low frequency outputs. Available nominal power is 40 mW per output for a load of 600 ohms. The audio output level can be programmed in the software for each type of audio output. There is an automatic reduction in level of 6 dB when the engines are shut down. A priority system is provided so that the two loud speakers supplied by the two FWCs broadcast coherent sounds. (c) ARINC 429 outputs The computer has three identical ARINC 429 high speed DATA BUS outputs. This bus carries all acquisition signals and their validity with the exception of most of those from other EFIS/ECAM systems (DMC, SDAC, FWC,...). It also carries computed parameters. (d) RS 422 outputs The computer has four identical RS 422 MESSAGE BUS outputs. This one-way bus transmits warning texts in the form of ISO 5 character strings to the DMCs. RS 422 standard uses USASCII characters comprising 7 data bits plus 1 parity bit plus 1 stop bit. The bits are sent at a rate of 19,200 bauds. The data flow transmitted on the message bus is an endless succession of frames. Each frame consists of two blocks: E/W display block and S display block. There are 150 ms between the end of the transmission of one block and the start of the same block in the next frame. Each block is made up of commands mixed with printable characters. The command characters define the blocks, the various sections of the block, the lines, color and size of the text.

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1 Esc N Esc 1N Esc 2N Esc 3N Esc 4N Esc 9H Esc 9f Esc 8H Esc 28H Esc 1H Esc H Esc K Esc 1F Esc 2F Esc 3F Esc 4F Esc 5F Esc 6F Esc 7F Esc 8F Esc E Esc m Esc 4m Esca)m Esca'm Esc

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Airbus ESLD ECAM System Logic Data