A319 - AWM - Introduction

Customer : 95W Type : A318/A319/A320/A321 Rev. Date : November 1, 2011

Manual: AWM Selected effectivity: ALL Introduction

INTRODUCTION - DESCRIPTION AND OPERATION ** ON A/C ALL 1. General A. Contents The Wiring Diagram Manual (WDM) is subdivided into three manuals: - AIRCRAFT SCHEMATIC MANUAL (ASM) - AIRCRAFT WIRING MANUAL (AWM) - AIRCRAFT WIRING LIST (AWL) These manuals have been prepared in accordance with ATA Specification No. 100. B. Purpose of the Manual The purpose of the AIRCRAFT WIRING MANUAL (AWM) and the AIRCRAFT SCHEMATIC MANUAL (ASM) is to permit a full understanding of the electrical, electronic and electromechanical system physical connection, operation. It shall also assist in troubleshooting and maintenance. NOTE TO USERS OF THIS MANUAL If you cannot find the data you need to ensure the continued airworthiness of the aircraft, or if you think that the information given is not complete, contact Airbus. C. Coverage of Manual The manuals making up the WDM are made up as follows: ---------------------------------------------------------------------------| ASM | AWM | AWL | |--------------------------------------------------------------------------| | - Introduction | - Introduction | - Introduction | | * Standard Practices | * Standard Practices | * Standard Practices | | | | - Equipment List | | - Diagrams | - Diagrams | - Extended Wire List | | * The contents of this part are transferred to: | | - The ESPM manual for airframe part, | | - The AMM 70-71-XX for the WDM engine part. | ---------------------------------------------------------------------------D. Customization The Wiring Diagram Manual contains only the diagrams applicable to the particular customer or group of customers. The customer code and the revision date will appear in header of each page. E. Effectivity The effectivity of the diagram is given in Fleet Serial Number. Statement in Table of Contents and the footer of the diagram. When the diagram is valid for all the aircraft in the customer fleet, the effectivity statement on the diagram is EFF: ALL. When the diagram is not valid for the whole fleet but for certain aircraft only, the effectivity statement gives the aircraft for which it is valid in FSN (Fleet Serial Number). In this case, the effectivity statement gives the block(s) of aircraft for which the diagram is valid. Each block has 6 digits (e.g. On A/C 010–021): The first 3 digits give the FSN of the first aircraft for which the diagram is valid, the last 3 digits give the FSN of the last aircraft of the block for which the diagram is valid. The effectivity statement can have one or more blocks. A ''-” means that the diagrams is applicable from the first FSN to the last FSN in the same block. 2. Diagram Make-up The schematics contained in these manuals have been prepared to meet ATA specification No. 100 requirements and include four types, as follows: - Block Diagrams: Have broad scope but little depth. Simplified Schematics: Have schematic symbols but do not show sufficient detail to permit fault isolation. In some cases, simplified schematics, logic diagrams or block diagrams have been incorporated in schematics whenever it has been deemed necessary, for full understanding of system operation. - Schematics: Show all line replaceable items, all logical wires within a sub-sub system and give sufficient depth for A/C fault isolation. - Wiring Diagrams: Show all components and wires. - Combined Diagrams: Show circuit breaker panels (same schematics are in ASM and AWM). A. Routing, Antenna Locations, Harnesses and Panels Diagrams. In AWM ATA 93 and 94, a list of main wire routing, antenna locations, harnesses and panels (rear face) is provided. 3. Aircraft Configuration The diagram shall represent the aircraft in the following configurations: - Aircraft on the ground resting on landing gear,

Print Date: February 14, 2012 Local Time

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- Engines shut down, thrust reversers locked and closed, - Flaps, slats and speed brakes retracted, - Doors and gear doors closed, - Parking brake applied, - Aircraft electrical network de-energized, - All controls in normal, AUTO or OFF position. If, for clarity, it is necessary to depict the equipment in any other configuration, a NOTE must state this specific configuration. 4. Electrical and Electronic System and Circuit Identification General The marking of systems and circuits is in accordance with the following coding system. A. System identification LETTERS - The letters A and B are reserved for special request by an airline for system references where the system is considered likely to be unique to that airline and not covered by the system letters shown in the table. C - Flight controls system D - De-icing E - Engine monitoring F - Flight instrumentation G - Landing gear H - Air conditioning J - Ignition K - Engine control and starting L - Lighting M - Interior arrangement P - DC power supply distribution Q - Fuel R - Radio (navigation communications) S - Radar navigation T - Special electronics V - Fictitious circuits W - Fire protection warning system X - AC Generation distribution B. Circuit identification The identification number of a circuit consists of 2 letters: the letter of the system followed by a letter identifying the circuit within this system. Example: CA - C : System Identification - A : Circuit Identification C. Identification of circuits (1) C - Flight controls system CA - Autothrust engagement CA - Electrical power supply (FMGS) CA - Discretes/analog interfaces (FMGS) CA - ARINC bus interfaces (FMGS) CC - Engagement internal monitoring CC - Electrical hydraulic power supply (FAC) CC - Discretes/analog interfaces (FAC) CC - ARINC bus interfaces (FAC) CE - Control inputs interface power supply CE - ELAC system (elevator aileron computer) CE - SEC system (spoiler elevator computer) CE - FCDC system (flight control DATA concentrator) CN - Flaps position indicating CN - Slats position indicating CV - Flaps electrical control monitoring CV - Slats electrical control monitoring (2) D - De-icing DA - Probe ice protection DB - Windshield rain protection DD - Ice detection DG - Windshield anti-icing defogging DH - Escape slide locking mechanism ice protection DL - Wing ice protection DN - Engine air intake ice protection


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DR - Flight crew foot warmers DS - Ancillary equipment (including door area heating panels) DU - Drain mast ice protection DV - Water servicing panels heating DW - Potable water ice protection (3) E - Engine monitoring EL - Fuel filter clogging warning system EG - Thrust reverser opening mechanism EN - Oil indicating power supply EV - Engine vibration indicating system (4) F - Flight instrumentation FH - Head up display (HUD) FN - Angle of attack indicating FN - Standby data: altitude and airspeed FN - Standby data: attitude and heading FN - Radio magnetic information - switching and indicating FP - Sensor power supply switching FR - Flight number reminder FS - Electrical clock FW - Paravisual indicating (PVI) FX - On board airport navigation system (5) G - Landing gear hydraulics GA - Normal extension retraction GB - Indicating warning GB - Landing gear-position information GC - Steering GD - Yellow main hydraulic power GE - Blue auxiliary hydraulic power (ram air turbine) GG - Normal braking GG - Alternate braking with anti skid GG - Alternate braking without anti skid GG - Parking/ultimate emergency braking GH - Reservoir pressurization indicating GJ - Blue main hydraulic power GK - Green main hydraulic power GL - Power transfer GN - Hydraulic fluid pressure indicating GP - Ground internal leak test system GQ - Hydraulic fluid quantity indicating GR - Hydraulic fluid temperature indicating GS - Brake cooling GT - Weight and balance system (WBS) GV - Tire pressure indicating system (TPIS) GW - Brake system temperature GX - Yellow auxiliary hydraulic power (electrical/hand pumps) (6) H - Air conditioning HA - Engine bleed air supply system HB - Flow control indicating HD - Avionics equipment ground cooling HC - Cargo compartment heating HF - Leak detection HG - Air distribution recirculation HH - Pack temperature control HJ - Door area heating HK - Cockpit cabin temperature control HL - Pressure control monitoring HN - Cargo compartment ventilation HP - Passenger compartment seats HQ - Avionics equipment ventilation HT - Control indicating HU - Lavatory/galley ventilation HV - APU bleed air supply and crossbleed systems HZ - Emergency ram air inlet (7) J - Ignition


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JH - Ignition starting and continuous relight (8) K - Engine control starting KA - Starting KB - Air intake system KC - Engine master control KD - Control monitoring KL - Emergency shutdown KS - Functional interfaces KT - APU oil heating (9) L - Lighting LA - Navigation lights LB - Landing lights LC - Runway turnoff lights LE - General illumination LF - Instrument panel integral lighting LG - General illumination LJ - Service area lighting LK - Air conditioning duct accessory compt lighting LL - Wheel well lighting LN - Main deck cargo compartment lighting LP - Annunciator light test dimming LQ - Lavatory lighting LR - Taxi take off lights LS - Equipment compartment lighting LU - FWD-AFT cargo compartment lighting LV - Anti-collision/strobe lighting LW - Passenger reading lights LX - Wing engine scan lighting LY - Logo lights LZ - Cabin work, cabin attendant (10) M - Interior arrangement MA - Quantity indicating MB - Distribution MC - Galley supply MD - Air supply boost system ME - Electrical service supply MF - Supplementary medical equipment MG - Toilet system MH - Passenger information system MH - Passenger entertainment (video) MJ - Cargo compt door electrical control system MK - Passenger entertainment (music) ML - Forward galley ML - Mid galley unit ML - Aft galley MP - Water draining (dump) MQ - Passenger compartment fixed interior doors MS - Cockpit seats MT - Razor supply MV - Waste level indicating MW - Entrance stairs system MX - Miscellaneous emergency equipment MY - Semi automatic cargo loading (11) P - DC power supply distribution PB - DC generation - batteries PC - DC essential normal generation switching PE - DC emergency generation (TR) PH - DC essential distribution PN - DC main distribution PP - DC ancillary equipment PR - Refuelling on battery PU - DC main generation (TR) PV - DC generation monitoring indicating PX - DC ground service bus control


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(12) Q - Fuel QA - Main fuel pump system QC - APU fuel pump system QE - Crossfeed system QF - APU LP fuel shut off QG - Engine LP fuel shut off QH - Additional center tank transfer system QJ - Tank level sensing QL - Main transfer system QN - Fuel control and monitoring system (FCMS) QP - Intercell transfer system QS - Fuel recirculation - cooling QT - Quantity indicating QU - Refuel/defuel system (13) R - Radio (navigation communications) RB - Aircraft communication addressing reporting system (ACARS) RC - VHF system RD - Pax facilities - air to ground telephone RE - HF/calsel aerocall system RF - Cabin management system RF - Cabin information network system (CINS) RG - Radio management RH - Cabin intercommunication DATA system (CIDS) RJ - Service interphone RK - Cockpit voice recorder RN - Audio management (integrating/flight interphone/selcal/call) RP - ADF RR - Pax facilities - AM/FM radio system RS - VOR/MARKER RT - ILS RU - MLS (microwave landing system) RV - Satellite communication RX - Announcement-music tape reproducer system RZ - Voice privacy system (14) S - Radar navigation SA - Radio altimeter SD - DME SG - TCAS (traffic collision avoidance system) SH - ATC/Mode S (select) SN - Satellite navigation SQ - Weather radar system (15) T - Special electronics TA - On board peripherals and flight operational peripherals TD - Up and down data loading system acquisition/interface and equipment TL - Aircraft information network system TT - Gate link TU - Digital flight data recording sys. intercon. (FDIU, DFDR, LA, QAR) TU - DFRS input interface TV - AIDS interconnection (DMU, DAR.) TV - AIDS input interface TW - Centralized fault display interface (CFDIU) TW - Multifunction printing (printer) TX - Air trafic and information management system (ATIMS) (16) V - Fictitious circuits VB - Main wire routing (harnesses) VC - A/C electrical connectors VD - Diode module VG - Ground terminal block VN - Ground points VP - Pressure seal feedthrough VS - Splices VT - Terminal blocks VU - Panels VZ - Spare wires (ATA 2499 only)


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(17) W - Fire protection warning system WA - Avionics compartment smoke detection WC - Cockpit to ground crew call system WD - Engine fire overheat detection WE - Engine fire extinguishing WF - APU fire extinguishing WG - APU fire overheat detection WH - Cargo compartment smoke detection WJ - Passenger lighted signs WL - Cabin emergency lighting WN - Emergency escape slide release warning and overpressure warning systems WP - Evacuation signaling equipment WQ - Lavatory smoke detection WR - Control indicating WT - EIS - control WT - DMC - acquisition/interface WT - EIS - switching WV - SDAC - acquisition/interface WW - FWS - acquisition/interface WX - Cargo compartment fire extinguishing WZ - Ground proximity warning system (GPWS) (18) X - AC generation XA - Galley supply control XB - Static inverter (generation) XC - AC essential generation switching XE - AC emergency generation (CSM/G, GCU) XG - AC external power control (GPCU) XH - AC essential distribution XN - AC main distribution XP - AC equipment ancillary XS - AC auxiliary generation (APU generator GCU) XT - Integrated drive generator system (IDG, GCU) XU - AC main generation XX - AC ground service bus control (19) Y - Inert gas system YA - Inert gas generation system 5. Equipment Identification/Functional Item Number (FIN) A. Equipment Equipment on the A/C is generally allocated a unique identifier known as a Functional Item Number (FIN). The basic element of the FIN is a two letter code indicating to which system and circuit the equipment belongs. To this code are added prefixes and/or suffixes which provide the unique identification for individual equipment. NOTE: Several identical components which perform same function in the same circuit can be differentiated by the suffix number. General rule is that even suffix (2, 4, 6...) is identifying any component on right hand side and odd suffix (1, 3, 5...) is identifying component on left hand side. For mechanical equipment the FIN is similar to the electrical FIN except that the second letter of the system/circuit identifier becomes an M (for example GM). For electrical equipment (any component with an electrical connection) the FIN could be for example 14CA1 which is broken down as follows: - 14 Fourteenth component in circuit CA - CA System/circuit two letter code (Autothrust Engagement) - 1 - Suffix - First of several similar systems (Autothrust Engagement 1). B. Connectors Connections to components shall be identified by a suffix letter (or two for multiple connection parts) following the circuit identification. Example: 14CA-A - 14 : Component number - CA : Circuit code - A : Plug identification This will identify plug A on the 14th component in the circuit CA. If there are several connections, the other plugs shall be identified A, B, C, D, etc... Example 1: 11CA-B


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- 11CA : Component identification - B : Plug identification letter Example 2: 14CA-AA - 14 : Component number - CA : Circuit code - AA : Multiple connection identification NOTE: Connectors on equipment fitted on mountings are identified with reference to the equipment but not with reference to the mounting.. As a general rule, the connector PNs given are for connector without contacts. For computers, plug identifications comply with ARINC 600. (Ref. Fig. 001) C. Fictitious Components All components not specifically related to a circuit are identified by fictitious circuit letter V. The second letter defines the type of component. (1) VC A/C electrical connectors The electrical connector is identified in a fictitious circuit VC by a numerical designator. This identification shall be preceded by a group of numbers. Example: 19VC-A - 19 : Component prefix - VC : Fictitious circuit code - A : Plug identification letter - 19VC associated receptacle. (2) VN ground points The ground point is identified in fictitious circuit VN by a numerical designator taken from the complete aircraft. (3) VG ground terminal block The ground terminal block is identified in fictitious circuit VG by a numerical designator taken from the complete aircraft. (4) VP pressure seal/feedthrough The pressure seal/feedthrough is identified in fictitious circuit VP by a numerical designator. Terminal identifications are indicated to define a precise feedthrough identifier for each wire (in the case of wire to wire feedthrough). (5) VS splices Splices are identified like equipment, being grouped by route and by type. Such grouping shall not be systematic, but only accomplished where a priority is required. Identification shall consist of a numeric designator, identifying the group in fictitious circuit VS, and an alpha designator giving connection identification per unit. Example: 24VS A - 24 : Component group number - VS : Fictitious circuit code - A : Identification per unit (6) VT terminal blocks (a) The terminal block is identified in fictitious circuit VT by a numerical designator. Example: 494VT1224 - 494 : Component number - VT : Fictitious circuit code - 12 : The two digits following the circuit code will be reserved for identification of repetitive item numbers. - 24 : The two digits following the repetitive item number will be reserved for identification of the module number within the repetitive circuit concerned. (b) Shunt connections for modular type terminals are identified in the shunt the letter M followed by a sequence number is given in the AWL ''Extended Wire List”. Interconnected pins of a terminal block module have the same sequence number. On Wiring diagrams these pins are shown together in one square. (7) VD diode module The diode module is identified in fictitious circuit VD by a numerical designator. Example: 138VD - 138 : Component prefix - VD : Fictitious circuit code (8) VU panels racks The panels racks are identified in fictitious circuit VU by a numerical designator. Example: 123VU - 123 : Component prefix - VU : Fictitious circuit code


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There are several panels and racks (circuit VU) with the same function, but different configuration in the A/C. The FIN of these components have one or two additional letters between the circuit letter and the suffix. Example: - 2010VUA4 - 2010VUB010 - 2010VUAB22 component identification: 2010VU configuration letter: - A first configuration - B second configuration - AB third configuration suffix (position number on the A/C): 010 That means:there are several Passenger Service Unit (PSU) in the aircraft with 1, 2 or 3 reading lights. These PSUs all have the same basic layout and function but different features. Example:PSUs in the same column have one PN and they are interchangeable.PSUs in different columns have different PN and they are not interchangeable. --------------------------------------------------------| PSU with | PSU with | PSU with | | 1 reading light | 2 reading lights | 3 reading lights | |-------------------------------------------------------| | 2010VUA4 | 2010VUB4 | 2010VUAB5 | | 2010VUA10 | 2010VUB10 | 2010VUAB20 | | 2010VUA23 | 2010VUB23 | 2010VUAB30 | --------------------------------------------------------Any component and wire which performs the same function in different PSU's have the same identification. D. Busbar Busbars are identified with: (1) A sequence number (2) Letters XP for AC busbars and PP for DC busbars (3) A phase letter as applicable Example: - 12XP-A: AC busbar, phase A - 2PP: 28VDC busbar NOTE: If a terminal strip fulfills the function of a busbar identified within the fictitious circuit VT : reference is made to the busbar supplying the terminal strip. E. Identification of Equipment Added in the Aircraft by the Customer. The equipment added in the aircraft by the customer shall be numbered from 9000 to 9999. Example: Repair of the wires - The splice shall be identified by a FIN in 9XXXVS serie (E.G 9001VS for the first splice installed on A/C by the customer). - A sleeve shall be installed on each side of the splice and shall be print numbered in the 9XXXVS serie, in accordance with splice FIN. - A Customer Originated Change (COC) shall be raised by the customer to incorporate the VS identified into the WDM (AWM/ASM/AWL). F. Equipment Location Equipment are located in reference to zones and stations. Stations numbers are in CENTIMETERS. When an equipment is fitted on a VU panel, the FIN of this one is referred.All Panels are depicted in ATA 93 (PANELS) of the AWM. 6. Wire Identification A. Identification by Number Codes (1) Wire identification Wire identification is numerical plus a color identification when used, dependent on its circuit and independent of its location on the aircraft. Each wire is identified by an 8 digit number composed as follows: Example: 2322-0121R - 2322: Circuit identification prefix corresponding to ATA 100 numbering (chapter, section). - 0121: Wire number in circuit (different for each segment) - R: Color (if used). NOTE: In most of wiring diagrams, the wire number shall only be shown. The ATA 100 correspondence for total identification shall be given in a standard note.


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(2) Ground wire identification Ground wires shall be numbered from 0001 to 8999. These wires shall be shown on circuit VN wiring diagram (ATA 24–91). i.e. Their identification will include the ATA 100 designator for circuit VN: 2491. Example: 2491-1610 NOTE: All direct ground wires are identified by the ATA number of the circuit to which they belong. NOTE: All direct ground wires are identified by the ATA number of the circuit to which they belong. (3) Spare wire identification Spare wires shall be numbered from 0001 to 8999 with ATA 100 prefix 2499. Example: 2499-1611 (4) Wires added or modified in the aircraft by the customer The wires added or modified in the aircraft by the customer shall be numbered from 9000 to 9999 and 9AAA to 9YZZ with the ATA 100 prefix of the corresponding system. Example: 2411-9010 ; 2411–9AAA (5) Wires added or modified in the aircraft by product support The wires added or modified in the aircraft by product support shall be numbered from 8000 to 8999 and 8AAA to 8YZZ with the ATA 100 prefix of the corresponding system. Example: 2212-8021 ; 2212–8AAC (6) Identification of shielding or shielded wires/cables (a) Shielding or shielded wires/cables shall be numbered from 7000 to 7999 with ATA 100 prefix of the corresponding systems. Examples: 3411-7500; 7832-7800 (b) Shielding or shielded wires/cables added or modified in the aircraft by the customer. The shielding or shielded wires/cables added or modified in the aircraft by the customer shall be numbered from 9900 to 9999 with the ATA 100 prefix of the corresponding system. Example: 3443-9905 (7) Bundles supplied by a vendor (a) Bundles Some bundles are supplied by a vendor. They are identified by a FIN, the corresponding PN can be found in the IPC/CMM. Wire data is replaced by the real vendor reference. The Aircraft Wiring Manual represents these bundles through special symbols described as follow: - for bundles without vendor wire identification (Ref. Fig. 002) - for bundles with vendor wire identification (Ref. Fig. 003) (b) Wires Vendor bundle wires connected on an A/C manufacturer plug are identified as follows : - identification number of wire - YY type. YY is the A/C manufacturer code used to identify vendor wires that require identification. B. Identification by Color Codes A Amber B Blue BK Black BR Brown C Clear G Green GY Grey O Orange P Purple PK Pink R Red V Violet W White Y Yellow C. Types and Gauges Ref. Electrical Standard Practices Manual. (ESPM) for ELEC systems, except engines.Ref. AMM 70–71 – POWER PLANT WIRING for engines. Each wire is identified by an alphanumerical code comprising 2 alpha digits followed by 2 numerical digits. Example CF24


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where CF = Type and 24 = Gauge. D. Sensitive Wires The sensitive wires are identified either by pink sleeves with black printing at their ends or directly on the wire with the S letter indicated after each wire identification (e.g.:2231 0015S) on all wire length. In the WDM, these wires are identified by letter S. NOTE: The presence of this marking indicates to the maintenance personnel that these wires must not be modified . In the event of an action on these wires, a test of the concerned system is required. E. Wire Connection An upper-case letter preceded by "<" means a lower-case letter. Example:

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-

4T DME 1 and DME 2 5T Radio altimeter 1 6T Radio altimeter 2 7T HF 1 8T HF 2 9T VHF 3 1U VOR 1 2U VOR 2 3U Glide GP 1 - GP 2 4U Localizer GP 1 - GP 2 5U Marker 7U ADF 1 8U ADF 2

D. Route Segments (1) In general, identification of the route is sufficient to specify without risk of confusion, the routing of an electrical cable between two points provided that both ends are designated (e.g. the case illustrated below: for routing from A to B). (Ref. Fig. 005) (Item A) (2) Where a number of possibilities exist, the wire segments must be called up. (Ref. Fig. 005) (Item B) Called up are the route segments described below: - 1M-C: Rear of LH side rack routing to flight compartment ceiling - 1M-B: Junction in turbine containment zone - 2M-C: Same as 1M-C - 2M-B: Same as 1M-B - 3M-C: Same as 1M-C 9. Symbols A. General Symbols (Ref. Fig. 006) (Ref. Fig. 007) B. Wiring and Connections (Ref. Fig. 008) (Ref. Fig. 009) (Ref. Fig. 010) (Ref. Fig. 011) (Ref. Fig. 012) (Ref. Fig. 013) C. Resistors (Ref. Fig. 014) D. Capacitors, Induction Coils (Ref. Fig. 015) E. Transformers (Ref. Fig. 016) (Ref. Fig. 017) F. Switches (Ref. Fig. 018) (Ref. Fig. 019) (Ref. Fig. 020) (Ref. Fig. 021) (Ref. Fig. 022) (Ref. Fig. 023) (Ref. Fig. 024) G. Relays (Ref. Fig. 025) (Ref. Fig. 026) (Ref. Fig. 027) (Ref. Fig. 028) H. Solid State Devices (Ref. Fig. 029) (Ref. Fig. 030)


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(Ref. Fig. 031) J. Lamps, Indicator Lights and Miscellaneous Warnings (Ref. Fig. 032) (Ref. Fig. 033) (Ref. Fig. 034) K. Logic Symbols (Ref. Fig. 035) (Ref. Fig. 036) (Ref. Fig. 037) (Ref. Fig. 038) (Ref. Fig. 039) (Ref. Fig. 040) L. Circuit Breaker (Ref. Fig. 041) (Ref. Fig. 042) (Ref. Fig. 043) M. Motor (Ref. Fig. 044) N. Mechanical Symbols (Ref. Fig. 045) (Ref. Fig. 046) (Ref. Fig. 047) (Ref. Fig. 048) (Ref. Fig. 049) (Ref. Fig. 050) (Ref. Fig. 051) (Ref. Fig. 052) (Ref. Fig. 053) (Ref. Fig. 054) 10. Panel Make-up The term panel covers: - Instrument panels - Circuit breaker panels - Electrical racks - Shelves - Boxes containing items of equipment with electrical identification numbers. Panels are shown in AWM as seen by the mechanic. (Ref. Fig. 055) On such panels, the components appear at their exact locations, identified by their electrical identification numbers. The panels are shown, rear view like in removed position. 11. How to Use the WDM A. General The following pages contain a layout chart of the Manual and show the relationship between the schematics and the hook-up list, the method to be used for locating an equipment on a panel using a schematic and the method used for locating instrument integral lighting connections. All station numbers and length of wires are in CENTIMETERS. Aircraft equipment identifiers are listed in the alphanumerical order in the Equipment list. Equipment linked to a Next Higher Assembly (NHA), such as the power plant, do not have the same type of identifier and are therefore listed in the AWL engine data part. B. Access to the manuals The manuals can be accessed as follows: - ASM or AWM: by ATA, by wire number, by FIN - AWL: by FIN, by wire number, by location, by shielded wire, etc. C. Intra-and inter-manual links The links are described below: ----------------------------------------------------------------------------I FROM I TO I LINK I I---------------------------------------------------------------------------I I ASM diagram I AWM diagram I AWM ATA ref. I I ASM diagram I FIN menu I navigation on the FIN I I AWM diagram I FIN menu I navigation on the FIN I I SB list I ASM/AWM I I I Search by SB or COC I ASM/AWM I I


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I Word search menu I ASM/AWM/AWL/ESPM I I ----------------------------------------------------------------------------12. Aircraft Manufacturer's Service Bulletins and Customer Originated Changes. A. SB information in the Schematics and Wiring Diagrams (1) SB identification SB indications in schematics and wiring diagrams are placed outside the drawing area, in the footer of the diagram. The location of modifications to an ASM/AWM sheet because of incorporation of an SB is indicated by alphanumeric guide references, providing the sheet is not modified by more than 10 % (e.g. SB 22-1010 E1, F2, C9). If the modification exceeds 10 %, the SB is followed by an asterisk with no alphanumeric coordinates (e.g. SB 22-2010*). If the modification does not have a technical impact on a sheet, the SB is followed with the value NE or N0 (No Effect). In this case the SB is only used to extend the effectivity of a dedicated sheet, which is not affected by the SB in case of multi-sheet page composition for which the SB has been integrated. B. COC Information in the Schematics and Wiring Diagrams (1) COC identification Customer Originated Changes (COCs), incorporated into the ASM/AWM at Customer request to reflect data or procedures originated by and peculiar to that customer, will be permanently identified by the COC reference number and by alphanumeric coordinates. The location of modifications to an ASM/AWM sheet because of incorporation of a COC is indicated by alphanumeric guide references, providing the sheet is not modified by more than 10 % (e.g. IAW03-18-30 E1, F2, C9). If the modification exceeds 10 %, the COC is followed by an asterisk with no alphanumeric coordinates (e.g. IAW03-1830*). If the modification does not have a technical impact on a sheet the COC is followed with value NE or N0 (No Effect). In this case the COC is only used to extend the effectivity of a dedicated sheet, which is not affected by the COC in case of multi-sheet page composition for which the COC has been integrated. The COC data incorporated into the Technical Data is shown like that ''EMB COC EO05–18–14 for A/C 004–009”. (2) Responsibility Where the Customer requests Airbus to incorporate the Customer's originated data or that of any other party into the technical data issued by Airbus (Technical Data) relating to the operation, maintenance, overhaul, repair or modification of the aircraft, Airbus shall do so on the condition that the use of the COC data shall be entirely at the Customer's risk, Airbus being under no liability whatsoever in respect of either the contents of any COC data, or the effect which the incorporation of such COC data may have on the Technical Data issued by Airbus. (3) Disclaimer clause AIRBUS HEREBY EXPRESSLY DISCLAIMS ANY AND ALL WARRANTIES, EXPRESSED OR IMPLIED, ORAL OR WRITTEN, ARISING BY LAW, COURSE OF DEALING, OR OTHERWISE, AND WITHOUT LIMITATION ALL WARRANTIES AS TO QUALITY, OPERATION, MERCHANTABILITY, FITNESS FOR ANY INTENDED PURPOSE, AND ALL OTHER CHARACTERISTICS WHATSOEVER, OF CUSTOMER ORIGINATED CHANGES INCORPORATED INTO THE TECHNICAL DATA ISSUED BY AIRBUS. THE FOREGOING DISCLAIMER SHALL ALSO APPLY TO ANY OTHER PORTION OF AIRBUS TECHNICAL DATA WHICH MAY BE AFFECTED BY SUCH CUSTOMER ORIGINATED CHANGES. 13. ASM Representation A component is shown complete at least once on the schematic, illustrating the basic function or the most important part of the component A. Component home diagram The component home diagram is the diagram where the component is shown in full. There are three cases : (1) The component is shown in full with all terminals including the unused terminals to be identified UNUSED (Ref. Fig. 056) (Item A). (2) The component is considered homed in the diagram by the addition of all cross-referenced to the ATA scheme where the component function is represented. The component is completed (terminals A and B plus terminals represented in SCH 2) (Ref. Fig. 056) (Item B). (3) In SCH2, the same component is partly shown with ATA break symbol and cross-reference to SCH 1, where the component is homed (Ref. Fig. 056) (Item C). B. Component contours (1) General: see symbols.


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(2) For reference components The for reference components (represented by a patterned contour) are components which do not belong to the ATA CH/SE where they are represented. The functions represented inside a component given for information can be processed in three ways : 1st case : The functions represented are covered in several schematics different from the schematic where the component is homed (Ref. Fig. 057) (Item A). Terminals AB/6 and AB/7 are cross-referenced to the SCH which covers their functions i.e. SCH 2 and 3. 2nd case : The functions represented are covered in a single schematic different from the schematic where the component is homed (Ref. Fig. 057) (Item B). Terminals AB/10D and AE/12G are cross-referenced to SCH 3 which covers their functions. Component 1 CA1 is homed in SCH 1 of 22-84. 3rd Case: The functions represented are covered in the schematic where the component is homed (Ref. Fig. 057) (Item C): The functions of terminals AA/13 and AA/14 is covered in the home diagram. Consequently the component cross-reference, i.e. SCH 1 (34-36) applies to terminals AA/13 and AA/14. NOTE 1: When one function is used several times, cross-reference to ATA CH/SE where the function is generated shall be indicated. NOTE 2 : There must be no contour break symbols on items shown for reference purposes and on diode modules (except for transit items such as stages of pushbutton switches). C. Representation of conductors Liaison between units covered on the same home diagrams shown by an unbroken line if one of the units is the informer. If one of the units covered on the same home diagram is an informer (information is received from another system), the liaison will be shown by a dotted line. (1) General conductors (a) Example N 1 (Ref. Fig. 058) (Item A) Component 1AA and 2AA are homed in the schematic. Component 3AA is functional in the diagram at terminal 4. This component is however homed in schematic 2. Component 1BB does not belong to the ATA CH/SE but is depicted by a patterned contour. Special case : If the component cannot be illustrated , its presence is supported by a cross-reference. In such cases the cross-reference is accompanied by the nature of the signal carried, its source and the schematic where this function is to be taken into account (schematic not necessarily where the component is homed). In the example quoted, the conductor is represented by a solid line because it is functional and in this diagram ALL THE INFORMED COMPONENTS are depicted if there is space. (b) Example N 2 (Ref. Fig. 058) (Item B) When depicting component 1BB on its home diagram, the connection is shown by a dash line , since the conductor is not functional in this ATA (CH-SE) . Rule : All termination points of a function is shown at least once on the schematic illustrating that function (Example N 1). All other schematics show the wire carrying this function by a dash line (Example N 2). (2) Special conductors (DATA BUS) This is a twin wire used for the transmission of digital data signals. It is represented by two lines with a half-arrow on each wire depicting the direction of signal-flow. The ends of the DATA BUS are identified by the annotations HI and LO or A and B placed within the wire (Ref. Fig. 059) (Item A). In the case of branch points on a data bus, it is possible to use . (a) A dash line between the informer and informed items connecting the two ends of the data bus (Ref. Fig. 059) (Item B). (b) A line between all the ends of the data bus (Ref. Fig. 059) (Item C). 14. AWM representation With the exception of fictitious circuits, connectors and terminal blocks are shown at least once with all connections.


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A list of cross-reference, without terminal identification, to the various diagrams where the connector/terminal block is shown with wiring, is given to find all terminals for a connector/terminal block. A connector/terminal block is always cross-referenced to its Home wiring diagram (complete connector/terminal). Figure 1 - ARINC 600 Plug Figure 1 - Bundle without vendor wire identification Figure 1 - Bundle with vendor wire identification Figure 1 - Grounds Figure 1 - Route Segments Figure 1 - General Symbols Figure 1 - General Symbols Continued Figure 1 - Wiring and Connections Figure 1 - Wiring and Connections Continued Figure 1 - Wiring and Connections Continued Figure 1 - Wiring and Connections Continued Figure 1 - Wiring and Connections Continued Figure 1 - Wiring and Connections Continued Figure 1 - Resistors Figure 1 - Capacitors, Induction Coils Figure 1 - Transformers Figure 1 - Transformers Continued Figure 1 - Switches Figure 1 - Switches Continued Figure 1 - Switches Continued Figure 1 - Switches Continued Figure 1 - Switches Continued Figure 1 - Switches Continued Figure 1 - Switches Continued Figure 1 - Relays


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Figure 1 - Relays Continued Figure 1 - Relays Continued Figure 1 - Relays Continued Figure 1 - Solid State Devices Figure 1 - Solid State Devices Continued Figure 1 - Lamps - Solid State Devices Continued Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings Continued Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings Continued Figure 1 - Logic Symbols Figure 1 - Logic Symbols Continued Figure 1 - Logic Symbols Continued Figure 1 - Logic Symbols Continued Figure 1 - Logic Symbols Continued Figure 1 - Logic Symbols Continued Figure 1 - Circuit Breaker Figure 1 - Circuit Breaker Continued Figure 1 - Circuit Breaker Continued Figure 1 - Motors Figure 1 - Mechanical Symbols Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued


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Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued Figure 1 - Mechanical Symbols Continued Figure 1 - Method of Layout of Panel Figure 1 - Component Home Diagram Figure 1 - For reference component contour Figure 1 - Representation of conductors Figure 1 - Representation of special conductors (DATA BUS)


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Figure 1 - ARINC 600 Plug ** ON A/C ALL


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SYMBOLS USED ON WIRING MANUAL

OF BUNDLES

A/C TO BE CONNECTED

A/C MANUFACTURER WIRE IDENTIFICATION NUMBER OF CABLE

WITHOUT VENDOR WIRE

GAUGE

CONNECTION AT ONE END ONLY . BUNDLE SUPPLIED WITH SINGLE CONNECTOR . ENDS TO BE CONNECTED

CONNECTION AT BOTH BUNDLE SUPPLIED WITHOUT CONNECTOR.

NO CONNECTION. BUNDLE SUPPLIED WITH 2 CONNECTORS . WIRE WITHOUT ANY

NO

NO

Figure 1 - Bundle without vendor wire identification ** ON A/C ALL


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SYMBOLS USED ON WIRING MANUAL

OF BUNDLES

A/C MANUFACTURER WIRE IDENTIFICATION

A/C TO BE CONNECTED

VENDOR WIRE

NUMBER OF CABLE

VENDOR WIRE

GAUGE

CONNECTION AT ONE END ONLY . BUNDLE SUPPLIED WITH SINGLE CONNECTOR . ENDS TO BE CONNECTED

CONNECTION AT BOTH BUNDLE SUPPLIED WITHOUT CONNECTOR.

NO CONNECTION. BUNDLE SUPPLIED WITH 2 CONNECTORS .

NO

NO

Figure 1 - Bundle with vendor wire identification ** ON A/C ALL


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(DC GROUND

(DC GROUND

(DC GROUND

(AC GROUND

(AC GROUND

(AC GROUND

(AC GROUND

(AC GROUND

(AC GROUND

(GROUND FOR ALL SCREEN

(GROUND FOR ALL SCREEN AND BOX BONDING SYS2)

(SINGLE POINT AUDIO SYS EQPT FOR AUDIO COM)

Figure 1 - Grounds ** ON A/C ALL


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Figure 1 - Route Segments ** ON A/C ALL


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BROUGHT OUT

DELTA OR MESH

INCOMPLETE COMPONENT INCOMPLETE ON THE SAME

OR BASE BUT COMPLETELY SHOWN ON SAME DIAGRAM

ARROW HEAD TO IDENTIFY THE SUBJECT GROUND CONNECTION GROUND CONNECTION CHASSIS OR FRAME CONNECTION MECHANICAL CONNECTION SINGLE TEST POINT

Figure 1 - General Symbols ** ON A/C ALL


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SINGLE TEST POINT

POINT TO ANOTHER ON THE SAME DIAGRAM OR FROM ONE SHEET TO ANOTHER POINT TO ANOTHER ON THE SAME DIAGRAM OR FROM ONE SHEET TO ANOTHER CONDUCTOR FURNISHED BY THE THE EQUIPMENT AND BEARING

AT LEAST ONE END TO BE

Figure 1 - General Symbols Continued ** ON A/C ALL


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CONDUCTOR CABLE

SCREW OR STUD

POKE HOME CONNECTION

FASTON CONNECTION

CROSSING OF PATHS OR CONDUCTORS NOT

JUNCTION OF CONDUCTORS OR

Figure 1 - Wiring and Connections ** ON A/C ALL


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GROUPING OF LEADS

CONDUCTOR WITH END CAP

SHIELDED 3 WIRE CABLE HOOK-UP FLAG TO INDICATE CONNECTED TO SAME LUG

TWISTED DOUBLE CABLE

Figure 1 - Wiring and Connections Continued ** ON A/C ALL


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SHORTING LINK

WITH SHORTING LINK 28 AND 29 AND 31 AND 35

DOUBLE COAXIAL CABLE WITHOUT LINK (ROTATION OF BAR B32A

DOUBLE COAXIAL CABLE WITH LINK



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B) INCOMPLETE C) INCOMPLETE BUT FULLY SHOWN ON

SINGLE CONNECTOR

AA INSTALLED ON THE



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SINGLE COAXIAL CONNECTOR DOUBLE COAXIAL CONNECTOR

OUTSIDE CONDUCTOR NOT

PHONE PLUG (JACK) TWO CONDUCTORS PHONE PLUG (JACK)

PHONE PLUG (JACK)

TWO CONDUCTORS

JACK 2 CONDUCTORS



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TERMINAL JUNCTION MODULES

2 CONNECTIONS

8 CONNECTIONS

2 CONNECTIONS 6 CONNECTIONS


K




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ADJUSTABLE OR CONTINUOUSLY

CONTACT AND OFF

NON LINEAR

Figure 1 - Resistors ** ON A/C ALL


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MAGNETIC CORE INDUCTOR MAGNETIC CORE INDUCTOR

TAPPED INDUCTION COIL SHUNT WINDING COMPENSATING OR COMMUTATING

WINDING OR COIL

Figure 1 - Capacitors, Induction Coils ** ON A/C ALL


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DOTS INDICATE NO

Figure 1 - Transformers ** ON A/C ALL


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3 WINDING

Figure 1 - Transformers Continued ** ON A/C ALL


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DOUBLE THROW

DOUBLE THROW

DOUBLE THROW

DOUBLE THROW SWITCH WITH ONE

DOUBLE THROW SWITCH WITH ONE MAKE, CENTER OFF

DOUBLE THROW SWITCH WITH BOTH MAKE, CENTER OFF

Figure 1 - Switches ** ON A/C ALL


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WITH 2 MOMENTARY CONTACTS,

DOUBLE POLE,MECHANICALLY

(SHOWN IN OPEN POSITION) (SHOWN IN CLOSED POSITION)

Figure 1 - Switches Continued ** ON A/C ALL


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NORMALLY OPEN PUSH

SINGLE POLE DOUBLE



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ONLY : THE "L" WIRE IS COMMON. INDICATED BY A BLACK BLOCK IN POSITION 4, WIRES L AND D

THE "L" WIRE IS COMMON. CONTINUITY IS INDICATED BY A BLACK BLOCK ARE INDICATED BY THE NUMBERS IN THE BOTTOM ROW.



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3 POLES



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DOUBLE THROW PUSH BUTTON SWITCH AND MONITORING INDICATORS WITH INSCRIPTION AND

AS ABOVE BUT SHOWN INCOMPLETE

PUSH BUTTON SWITCH AND MONITORING INDICATORS WITH INSCRIPTION AND




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ECONOMY COIL,

SINGLE POLE LATCHING RELAY AND TRIP COIL

SINGLE POLE DOUBLE

WITH MAGNETIC HOLD

Figure 1 - Relays ** ON A/C ALL


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Figure 1 - Relays Continued ** ON A/C ALL


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THE BASE MAY NOT BE SHOWN IN FULL IN THE FUNCTIONAL MUST BE USED



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(BRIDGE) SINGLE PHASE

TUNNEL DIODE

DIODE MODULE

Figure 1 - Solid State Devices ** ON A/C ALL


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N-CHANNEL FET

N-CHANNEL MOSFET

DIODE AND

Figure 1 - Solid State Devices Continued ** ON A/C ALL


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OR BALLAST LAMP

NON LINEAR VOLTAGE

Figure 1 - Lamps - Solid State Devices Continued ** ON A/C ALL


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LIGHT WITH 3 TERMINALS

COLD CATHODE LAMP, NEON LAMP,DC TYPE

COLD CATHODE LAMP, NEON LAMP,AC TYPE

WITH BALLAST UNIT

WITH PUSH TO TEST

ABCDEFG

ABCDEFG

ABCDEFG

ABCDEFG

Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings ** ON A/C ALL


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INDICATION SEGMENT

BELL OR GONG

LOOP ANTENNA

DOUBLE ANTENNA

Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings Continued ** ON A/C ALL


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Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings Continued ** ON A/C ALL


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AND FUNCTION AND FUNCTION

LOGIC LOW NEGATION INDICATOR SYMBOL DIRECTLY LOCATED ON CONDUCTOR AT INPUT AND OUTPUT OF SYMBOL DENOTES INVERSION OF LOGIC

DELAY FUNCTION (TIME DELAY SHALL BE SHOWN WHEN DELAY IS QUOTED FOR

Figure 1 - Logic Symbols ** ON A/C ALL


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Figure 1 - Logic Symbols Continued ** ON A/C ALL


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ONE CELL BATTERY

CONTINUOUS LOOP

WITH FOUR OHMIC



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WITH CONNECTOR

UNIT OR QUARTZ



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CX : CONTROL TRANSMITTER CT : CONTROL TRANSFORMER



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BLOW OUT COIL

Figure 1 - Circuit Breaker ** ON A/C ALL


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THREE POLES PUSH PULL TYPE


SHOWN INCOMPLETE

Figure 1 - Circuit Breaker Continued ** ON A/C ALL


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K


K

K

K

Figure 1 - Circuit Breaker Continued ** ON A/C ALL


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MOTOR (M) OR GENERATOR (G)

MOTOR (M) OR GENERATOR (G) DC WITH SHUNT EXCITATION

MOTOR (M) OR GENERATOR (G)

MOTOR (M) OR GENERATOR (G) DC WITH COMPOUND EXCITATION

ASYNCHRONOUS SINGLE PHASE

BOTH ENDS OF EACH PHASE BROUGHT OUT

DOUBLE WOUND MOTOR

CLUTH ENGAGED

CLUTH DISENGAGED

Figure 1 - Motors ** ON A/C ALL


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LUBE PUMP INLET

Figure 1 - Mechanical Symbols ** ON A/C ALL


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Figure 1 - Mechanical Symbols Continued ** ON A/C ALL


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ENGINE PUMP



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HAND PUMP

HP GEAR PUMP



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GROUND CONNECTOR



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Figure 1 - Method of Layout of Panel ** ON A/C ALL


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Figure 1 - Component Home Diagram ** ON A/C ALL


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LOC DEV 2 LOC DEV COMP

AP OWN ENG D COM OWN

LOC DEV LOC DEV COMP

Figure 1 - For reference component contour ** ON A/C ALL


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TO SIGNAL EQT XX

Figure 1 - Representation of conductors ** ON A/C ALL


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Figure 1 - Representation of special conductors (DATA BUS) ** ON A/C ALL


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A319 - AWM - Introduction

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