a319 - awm - introduction

INTRODUCTION - DESCRIPTION AND OPERATION

The Wiring Diagram Manual (WDM) is subdivided into three manuals:

These manuals have been prepared in accordance with ATA Specification No. 100.

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.

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. | ----------------------------------------------------------------------------

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.

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.

The schematics contained in these manuals have been prepared to meet ATA specification No. 100 requirements and include four types, as follows:

In AWM ATA 93 and 94, a list of main wire routing, antenna locations, harnesses and panels (rear face) is provided.

The diagram shall represent the aircraft in the following configurations:

1. General A. Contents

- AIRCRAFT SCHEMATIC MANUAL (ASM)- AIRCRAFT WIRING MANUAL (AWM) - AIRCRAFT WIRING LIST (AWL)

B. Purpose of the Manual

C. Coverage of Manual

D. Customization

E. Effectivity

2. Diagram Make-up

- 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.

3. Aircraft Configuration

- Aircraft on the ground resting on landing gear,

** ON A/C ALL

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

Manual: AWM Selected effectivity: ALL

Introduction

Print Date: February 14, 2012 Local Time of 76

If, for clarity, it is necessary to depict the equipment in any other configuration, a NOTE must state this specific configuration.

The marking of systems and circuits is in accordance with the following coding system.

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

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

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

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

- 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.

4. Electrical and Electronic System and Circuit Identification General

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.

B. Circuit identification

C. Identification of circuits (1) C - Flight controls system

(2) D - De-icing



Introduction


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

EL - Fuel filter clogging warning system EG - Thrust reverser opening mechanism EN - Oil indicating power supply EV - Engine vibration indicating system

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

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)

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

(3) E - Engine monitoring

(4) F - Flight instrumentation

(5) G - Landing gear hydraulics

(6) H - Air conditioning

(7) J - Ignition



Introduction


JH - Ignition starting and continuous relight

KA - Starting KB - Air intake system KC - Engine master control KD - Control monitoring KL - Emergency shutdown KS - Functional interfaces KT - APU oil heating

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

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

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

(8) K - Engine control starting

(9) L - Lighting

(10) M - Interior arrangement

(11) P - DC power supply distribution



Introduction


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

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

SA - Radio altimeter SD - DME SG - TCAS (traffic collision avoidance system) SH - ATC/Mode S (select) SN - Satellite navigation SQ - Weather radar system

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)

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)

(12) Q - Fuel

(13) R - Radio (navigation communications)

(14) S - Radar navigation

(15) T - Special electronics

(16) V - Fictitious circuits



Introduction


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)

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

YA - Inert gas generation system

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.

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:

Connections to components shall be identified by a suffix letter (or two for multiple connection parts) following the circuit identification. Example: 14CA-A

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

(17) W - Fire protection warning system

(18) X - AC generation

(19) Y - Inert gas system

5. Equipment Identification/Functional Item Number (FIN)A. 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.

- 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

- 14 : Component number- CA : Circuit code - A : Plug identification



Introduction


Example 2: 14CA-AA

For computers, plug identifications comply with ARINC 600. (Ref. Fig. 001)

All components not specifically related to a circuit are identified by fictitious circuit letter V. The second letter defines the type of component.

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

The ground point is identified in fictitious circuit VN by a numerical designator taken from the complete aircraft.

The ground terminal block is identified in fictitious circuit VG by a numerical designator taken from the complete aircraft.

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).

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

Example: 494VT1224

Interconnected pins of a terminal block module have the same sequence number. On Wiring diagrams these pins are shown together in one square.

The diode module is identified in fictitious circuit VD by a numerical designator. Example: 138VD

The panels racks are identified in fictitious circuit VU by a numerical designator. Example: 123VU

- 11CA : Component identification - B : Plug identification letter

- 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.

C. Fictitious Components

(1) VC A/C electrical connectors

- 19 : Component prefix- VC : Fictitious circuit code- A : Plug identification letter- 19VC associated receptacle.

(2) VN ground points

(3) VG ground terminal block

(4) VP pressure seal/feedthrough

(5) VS splices

- 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.

- 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”.

(7) VD diode module

- 138 : Component prefix - VD : Fictitious circuit code

(8) VU panels racks

- 123 : Component prefix- VU : Fictitious circuit code



Introduction


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:

component identification: 2010VU configuration letter:

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.

Busbars are identified with:

Example:

The equipment added in the aircraft by the customer shall be numbered from 9000 to 9999. Example: Repair of the wires

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.

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

- 2010VUA4 - 2010VUB010 - 2010VUAB22

- A first configuration - B second configuration- AB third configuration

D. Busbar

(1) A sequence number (2) Letters XP for AC busbars and PP for DC busbars(3) A phase letter as applicable

- 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 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

6. Wire Identification A. Identification by Number Codes

(1) Wire identification

- 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.



Introduction


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

Spare wires shall be numbered from 0001 to 8999 with ATA 100 prefix 2499. Example: 2499-1611

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

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

Examples: 3411-7500; 7832-7800

Example: 3443-9905

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:

Vendor bundle wires connected on an A/C manufacturer plug are identified as follows :

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

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

(2) Ground wire identification

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

(4) Wires added or modified in the aircraft by the customer

(5) Wires added or modified in the aircraft by product support

(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.

(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.

(7) Bundles supplied by a vendor(a) Bundles

- for bundles without vendor wire identification (Ref. Fig. 002) - for bundles with vendor wire identification (Ref. Fig. 003)

(b) Wires

- 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

C. Types and Gauges



Introduction


where CF = Type and 24 = Gauge.

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.

An upper-case letter preceded by "<" means a lower-case letter. Example: <R (lower-case letter)

Grounding is achieved in two ways:

In the case of ground loop circuits, grounding can be accomplished through several circuits. These circuits are filled under chap. 24. DC as well as AC grounds are identified in the same way as DC and AC circuit:

Example: (Ref. Fig. 004)

Route identification consists of an alphabetical character, which denotes the type of route, prefixed by a sequence number.

Five main route functions are provided for in electrical wiring: G, P, M, S, E ROUTES FUNCTION

Three main route functions are provided in electronic wiring: R, T, U ROUTES FUNCTION

D. Sensitive Wires

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

7. Ground Point Identification

- direct - ground loop circuit(s).

- DC1 power supply distribution (SYS1). - DC2 power supply distribution (SYS2). - AC1 power supply (system 1 in normal operation).- AC2 power supply (system 2 in normal operation).- B1 for screen and box bonding (SYS1) (except audio communication).- B2 for screen and box bonding (SYS2) (except audio communication).- S for the intercommunication system Single Point Audio System Equipment (SPASE).

8. Routing Identification A. General

B. Electrical Wiring

- 1G Generator 1 feeders - 2G Generator 2 feeders - 3G APU generator feeders- 4G Battery feeders - 5G External power feeders- 1P Power supply from AC and DC bus 1- 2P Power supply from AC bus 2- 3P APU start supply - 1M System 1 not sensitive - 2M System 2 not sensitive - 6M Power supply for secondary emergency circuit- 7M Fly by wire (not sensitive) generator 1 emergency- 8M Fly by wire (not sensitive) generator 2 - 1S Sensitive system 1 - 2S Sensitive system 2 - 7S Fly by wire (sensitive) - 8S Fly by wire (sensitive) - 1E Generator 1 energization- 2E Generator 2 energization- 3E APU generator energization- 6E Emergency excitation

C. Electronic Wiring

- 1R System 1 radio communication and radio navigation- 1T VHF 1 - 2T VHF 2 - 3T ATC 1 and ATC 2



Introduction


(Ref. Fig. 005) (Item A)

(Ref. Fig. 005) (Item B) Called up are the route segments described below:

(Ref. Fig. 006) (Ref. Fig. 007)

(Ref. Fig. 008) (Ref. Fig. 009) (Ref. Fig. 010) (Ref. Fig. 011) (Ref. Fig. 012) (Ref. Fig. 013)

(Ref. Fig. 014)

(Ref. Fig. 015)

(Ref. Fig. 016) (Ref. Fig. 017)

(Ref. Fig. 018) (Ref. Fig. 019) (Ref. Fig. 020) (Ref. Fig. 021) (Ref. Fig. 022) (Ref. Fig. 023) (Ref. Fig. 024)

(Ref. Fig. 025) (Ref. Fig. 026) (Ref. Fig. 027) (Ref. Fig. 028)

(Ref. Fig. 029) (Ref. Fig. 030)

- 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).

(2) Where a number of possibilities exist, the wire segments must be called up.

- 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. SymbolsA. General Symbols

B. Wiring and Connections

C. Resistors

D. Capacitors, Induction Coils

E. Transformers

F. Switches

G. Relays

H. Solid State Devices



Introduction


(Ref. Fig. 031)

(Ref. Fig. 032) (Ref. Fig. 033) (Ref. Fig. 034)

(Ref. Fig. 035) (Ref. Fig. 036) (Ref. Fig. 037) (Ref. Fig. 038) (Ref. Fig. 039) (Ref. Fig. 040)

(Ref. Fig. 041) (Ref. Fig. 042) (Ref. Fig. 043)

(Ref. Fig. 044)

(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)

The term panel covers:

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.

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.

The manuals can be accessed as follows:

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

J. Lamps, Indicator Lights and Miscellaneous Warnings

K. Logic Symbols

L. Circuit Breaker

M. Motor

N. Mechanical Symbols

10. Panel Make-up

- Instrument panels - Circuit breaker panels - Electrical racks - Shelves - Boxes containing items of equipment with electrical identification numbers.

11. How to Use the WDMA. General

B. Access to the manuals

- 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



Introduction


I Word search menu I ASM/AWM/AWL/ESPM I I -----------------------------------------------------------------------------

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.

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. IAW03-18-30*). 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”.

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 ofthe 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.

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.

A component is shown complete at least once on the schematic, illustrating the basic function or the most important part of the component

The component home diagram is the diagram where the component is shown in full. There are three cases :

(Ref. Fig. 056) (Item A).

The component is completed (terminals A and B plus terminals represented in SCH 2) (Ref. Fig. 056) (Item B).

(Ref. Fig. 056) (Item C).

12. Aircraft Manufacturer's Service Bulletins and Customer Originated Changes.A. SB information in the Schematics and Wiring Diagrams

(1) SB identification

B. COC Information in the Schematics and Wiring Diagrams(1) COC identification

(2) Responsibility

(3) Disclaimer clause

13. ASM Representation

A. Component home diagram

(1) The component is shown in full with all terminals including the unused terminals to be identified UNUSED

(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.

(3) In SCH2, the same component is partly shown with ATA break symbol and cross-reference to SCH 1, where the component is homed

B. Component contours (1) General: see symbols.



Introduction


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).

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.

(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.

(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 N1). All other schematics show the wire carrying this function by a dash line (Example N 2).

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 .

(Ref. Fig. 059) (Item B).

(Ref. Fig. 059) (Item C).

With the exception of fictitious circuits, connectors and terminal blocks are shown at least once with all connections.

(2) For reference components

C. Representation of conductors

(1) General conductors (a) Example N 1

(b) 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.

(a) A dash line between the informer and informed items connecting the two ends of the data bus

(b) A line between all the ends of the data bus

14. AWM representation



Introduction


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 - Resistors

Figure 1 - Capacitors, Induction Coils

Figure 1 - Transformers

Figure 1 - Transformers Continued

Figure 1 - Switches

Figure 1 - Switches Continued






Figure 1 - Relays



Introduction


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 - Logic Symbols

Figure 1 - Logic Symbols Continued





Figure 1 - Circuit Breaker

Figure 1 - Circuit Breaker Continued


Figure 1 - Motors

Figure 1 - Mechanical Symbols

Figure 1 - Mechanical Symbols Continued








Introduction





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)



Introduction


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



Introduction


Figure 1 - Bundle without vendor wire identification

** ON A/C ALL

A/C MANUFACTURERWIRE IDENTIFICATION

CONNECTION AT ONE ENDONLY .BUNDLE SUPPLIED WITHSINGLE CONNECTOR .

CONNECTION AT BOTH

BUNDLE SUPPLIEDWITHOUT CONNECTOR.

GAUGENUMBER OF CABLE

NO CONNECTION.BUNDLE SUPPLIED WITH2 CONNECTORS .WIRE WITHOUT ANY

WITHOUTVENDOR WIRE

ENDS TO BECONNECTED

SYMBOLS USED ON WIRING MANUAL

TO BECONNECTED

A/C

NO NO

OF BUNDLES



Introduction


Figure 1 - Bundle with vendor wire identification

** ON A/C ALL

SYMBOLS USED ON WIRING MANUAL

TO BECONNECTED

A/CA/C MANUFACTURERWIRE IDENTIFICATION

OF BUNDLES

CONNECTION AT ONE ENDONLY .BUNDLE SUPPLIED WITHSINGLE CONNECTOR .

NO NONO CONNECTION.BUNDLE SUPPLIED WITH2 CONNECTORS .

CONNECTION AT BOTH

BUNDLE SUPPLIEDWITHOUT CONNECTOR.

ENDS TO BECONNECTED

GAUGENUMBER OF CABLEVENDOR WIRE VENDOR WIRE



Introduction


Figure 1 - Grounds

** ON A/C ALL

(DC GROUND

(AC GROUND (AC GROUND (AC GROUND

(AC GROUND(AC GROUND (AC GROUND

(DC GROUND (DC GROUND

(GROUND FOR ALL SCREENAND BOX BONDING SYS2)

(GROUND FOR ALL SCREEN (SINGLE POINT AUDIO SYSEQPT FOR AUDIO COM)



Introduction


Figure 1 - Route Segments

** ON A/C ALL



Introduction


Figure 1 - General Symbols

** ON A/C ALL

BROUGHT OUT

DELTA OR MESH

INCOMPLETE COMPONENT

INCOMPLETE ON THE SAME

ARROW HEAD TO IDENTIFYTHE SUBJECT

OR BASE BUT COMPLETELYSHOWN ON SAME DIAGRAM

GROUND CONNECTION

GROUND CONNECTION

CHASSIS OR FRAME CONNECTION

MECHANICAL CONNECTION

SINGLE TEST POINT



Introduction


Figure 1 - General Symbols Continued

** ON A/C ALL

SINGLE TEST POINT

AT LEAST ONE END TO BE

POINT TO ANOTHER ON THESAME DIAGRAM OR FROMONE SHEET TO ANOTHER

POINT TO ANOTHER ON THESAME DIAGRAM OR FROMONE SHEET TO ANOTHER

CONDUCTOR FURNISHED BY THE

THE EQUIPMENT AND BEARING



Introduction


Figure 1 - Wiring and Connections

** ON A/C ALL

CONDUCTOR CABLE

SCREW OR STUD

FASTON CONNECTION

CROSSING OF PATHSOR CONDUCTORS NOT

JUNCTION OF

CONDUCTORS OR

POKE HOME CONNECTION



Introduction



** ON A/C ALL

GROUPING OF LEADS

SHIELDED 3 WIRE CABLE

HOOK-UP FLAG TO INDICATE

CONNECTED TO SAME LUG

TWISTED DOUBLE CABLE

CONDUCTOR WITH END CAP



Introduction



** ON A/C ALL

SHORTING LINK

WITH SHORTING LINK

28 AND 29 AND 31 AND 35

DOUBLE COAXIALCABLE WITHOUTLINK (ROTATION OF BAR

DOUBLE COAXIALCABLE WITH LINK

B32A



Introduction



** ON A/C ALL

SINGLE CONNECTOR

A A

B) INCOMPLETEC) INCOMPLETE BUT FULLY SHOWN ON

INSTALLED ON THE



Introduction



** ON A/C ALL

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



Introduction



** ON A/C ALL

TERMINAL JUNCTION MODULES


K


2 CONNECTIONS

8 CONNECTIONS

2 CONNECTIONS

6 CONNECTIONS



Introduction


Figure 1 - Resistors

** ON A/C ALL

ADJUSTABLE OR CONTINUOUSLY

CONTACT AND OFF

NON LINEAR



Introduction


Figure 1 - Capacitors, Induction Coils

** ON A/C ALL

MAGNETIC CORE INDUCTOR

MAGNETIC CORE INDUCTOR

TAPPED INDUCTION COIL

COMPENSATING OR COMMUTATING

SHUNT WINDING

WINDING OR COIL



Introduction


Figure 1 - Transformers

** ON A/C ALL

DOTS INDICATE NO



Introduction


Figure 1 - Transformers Continued

** ON A/C ALL

3 WINDING



Introduction


Figure 1 - Switches

** ON A/C ALL

DOUBLE THROW

DOUBLE THROW

DOUBLE THROW

DOUBLE THROWSWITCH WITH ONE

MAKE, CENTER OFF

DOUBLE THROWSWITCH WITH BOTH

MAKE, CENTER OFF

DOUBLE THROWSWITCH WITH ONE



Introduction



** ON A/C ALL

(SHOWN IN OPEN POSITION)

(SHOWN IN CLOSED POSITION)

WITH 2 MOMENTARY CONTACTS,

DOUBLE POLE,MECHANICALLY



Introduction



** ON A/C ALL

NORMALLY OPEN PUSH

SINGLE POLE DOUBLE



Introduction



** ON A/C ALL



Introduction



** ON A/C ALL

ONLY : THE "L"WIRE IS COMMON.

INDICATED BY ABLACK BLOCK

IN POSITION 4,WIRES L AND D

THE "L" WIRE ISCOMMON. CONTINUITYIS INDICATED BY ABLACK BLOCK

ARE INDICATED BYTHE NUMBERS INTHE BOTTOM ROW.



Introduction



** ON A/C ALL

3 POLES



Introduction



** ON A/C ALL

DOUBLE THROWPUSH BUTTON SWITCHAND MONITORING INDICATORSWITH INSCRIPTION AND

PUSH BUTTON SWITCHAND MONITORING INDICATORSWITH INSCRIPTION AND

AS ABOVE BUTSHOWN INCOMPLETE




Introduction


Figure 1 - Relays

** ON A/C ALL

SINGLE POLE LATCHING RELAY

AND TRIP COIL

SINGLE POLE DOUBLE

WITH MAGNETIC HOLD

ECONOMY COIL,



Introduction



** ON A/C ALL



Introduction



** ON A/C ALL

THE BASE MAY NOT BE SHOWNIN FULL IN THE FUNCTIONAL

MUST BE USED



Introduction



** ON A/C ALL



Introduction


Figure 1 - Solid State Devices

** ON A/C ALL

(BRIDGE) SINGLE PHASE

TUNNEL DIODE

DIODE MODULE



Introduction


Figure 1 - Solid State Devices Continued

** ON A/C ALL

N-CHANNEL FET

N-CHANNEL MOSFET

DIODE AND



Introduction


Figure 1 - Lamps - Solid State Devices Continued

** ON A/C ALL

OR BALLAST LAMP

NON LINEAR VOLTAGE



Introduction


Figure 1 - Lamps, Indicator Lights and Miscellaneous Warnings

** ON A/C ALL

LIGHT WITH 3 TERMINALS

COLD CATHODE LAMP,NEON LAMP,DC TYPE

COLD CATHODE LAMP,NEON LAMP,AC TYPE

WITH BALLAST UNIT

ABCDEFG

ABCDEFG

ABCDEFG

ABCDEFG

WITH PUSH TO TEST



Introduction



** ON A/C ALL

INDICATION SEGMENT

BELL OR GONG

LOOP ANTENNA

DOUBLE ANTENNA



Introduction



** ON A/C ALL



Introduction


Figure 1 - Logic Symbols

** ON A/C ALL

AND FUNCTION

AND FUNCTION

NEGATION INDICATOR SYMBOLDIRECTLY LOCATED ON CONDUCTORAT INPUT AND OUTPUT OF SYMBOLDENOTES INVERSION OF LOGIC

LOGIC LOW

DELAY FUNCTION (TIMEDELAY SHALL BE SHOWN WHENDELAY IS QUOTED FOR



Introduction



** ON A/C ALL



Introduction



** ON A/C ALL

ONE CELL BATTERY

CONTINUOUS LOOP

WITH FOUR OHMIC



Introduction



** ON A/C ALL

WITH CONNECTOR

UNIT OR QUARTZ



Introduction



** ON A/C ALL

CX : CONTROL TRANSMITTER

CT : CONTROL TRANSFORMER



Introduction


Figure 1 - Circuit Breaker

** ON A/C ALL

BLOW OUT COIL



Introduction



** ON A/C ALL

THREE POLES PUSH PULL TYPE

SHOWN INCOMPLETE





Introduction



** ON A/C ALL

K

K

K

KAS ABOVE BUTSHOWN INCOMPLETE



Introduction


Figure 1 - Motors

** ON A/C ALL

ASYNCHRONOUS SINGLE PHASE

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

BOTH ENDS OF EACH PHASEBROUGHT OUT

DOUBLE WOUND MOTOR

CLUTH ENGAGED

CLUTH DISENGAGED



Introduction


Figure 1 - Mechanical Symbols

** ON A/C ALL

LUBE PUMP INLET



Introduction



** ON A/C ALL



Introduction



** ON A/C ALL

ENGINE PUMP



Introduction



** ON A/C ALL

HAND PUMP

HP GEAR PUMP



Introduction



** ON A/C ALL

GROUND CONNECTOR



Introduction



** ON A/C ALL



Introduction


Figure 1 - Method of Layout of Panel

** ON A/C ALL



Introduction


Figure 1 - Component Home Diagram

** ON A/C ALL



Introduction


Figure 1 - For reference component contour

** ON A/C ALL

LOC DEV 2

LOC DEV COMP

AP OWN ENG DCOM OWN

LOC DEV

LOC DEV COMP



Introduction


Figure 1 - Representation of conductors

** ON A/C ALL

TO SIGNAL EQT XX



Introduction


Figure 1 - Representation of special conductors (DATA BUS)

** ON A/C ALL



Introduction


a319 - awm - introduction

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