A320 Chapter 01 General

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  • A319/A320/A321TECHNICAL TRAINING MANUAL

    MECHANICS / ELECTRICS & AVIONICS COURSE

    01 GENERAL

  • This document must be used for training purpose only

    Under no circumstances should this document be used as a reference.

    It will not be updated.

    All rights reserved.No part of this manual may be reproduced in any form,

    by photostat, microfilm, retrieval system, or any other means,without the prior written permission of Airbus Industrie.

  • GENERAL** Aircraft Dimensions (1) (A320) 1................** Aircraft Dimensions (1) (A319) 7................** Aircraft Dimensions (1) (A321) 13...............** Structure General (1) 19........................** Structural Breakdown and Zoning (3) 29.........** Ground Handling (1) 51..........................** Cockpit Presentation (1) 57.....................** Avionics Compartment (1) 63.....................** Cockpit Philosophy (1) 67.......................Electrostatic Discharge (3) 77.....................Computer R/I (3) 89.................................** Maintenance External Visit (3) 91...............

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    01-00-00 AIRCRAFT GENERAL

    CONTENTS :Lateral ViewTop ViewFront ViewDoor Heights

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    CONTENTS :Lateral ViewTop ViewFront ViewDoor Heights

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  • 51 - STRUCTURE

    51-00-00 - A320 STRUCTURE GENERAL

    CONTENTS:Metallic MaterialsComposite MaterialsAircraft DrainageSurface PretreatmentPaint SystemNo Step AreasJacking Points

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  • A320 STRUCTURE GENERAL

    METALLIC MATERIALS

    The basic aircraft structure is made of aluminiumalloys with stainless steel and titanium alloys inspecific areas.

    COMPOSITE MATERIALS

    Composite materials are used for primary and secondarystructure.Composite materials represents about 15% of theaircraft structural weight. CFRP is mainly used forprimary structures, whilst AFRP and GFRP are only usedfor secondary structures.

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    AIRCRAFT DRAINAGE

    Wings and fuselage are equipped with different typesof drains.Holes and gaps are provided to ensure natural drainageof the fluid collection points. Drain holes are drilledbefore application of pretreatments. Remote drains areused when natural drainage is not possible.

    SURFACE PRETREATMENT

    The protection of the structure against corrosion isachieved by means of appropriate surface pretreatmentof the metallic parts.

    Aluminium Alloys :The primary protection is generally a pure aluminiumcladding. The main pretreatment used is the unsealedchromic acid anodizing (CAA).

    Titanium Alloys :Surface interfaying with aluminium alloy parts arezinc sprayed. The other titanium alloy surfaces areleft bare.Titanium fasteners are either sulphuric acid anodizedor aluminium coated.Composite materials are left bare.

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    PAINT SYSTEM

    Before the final paint system, all aluminium parts areprimed.The paint system used includes polyurethane primersand paint on the external surfaces, and epoxy primersand polyurethane paint on the internal surfaces.Anti-slip paint is the overwing escape zones.

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    NO STEP AREAS

    Wing and tailplane no step areas.Protective mats are required on the horizontalstabilizer as it is a carbon fiber structure.

    JACKING POINTS

    There are three jacking points provided.Three jacking points are provided, one below each wingoutboard of the pylon and one in front of the noselanding gear bay.

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    51-00-00 A320 STRUCTURAL BREAKDOWN ANDZONING

    CONTENTS:Reference AxesATA ChaptersSection NumbersStation NumbersZone Numbers

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    REFERENCE AXES

    The structure elements are localized according to thefollowing reference axis.

    Note : The reference (station 0) for all structuralmeasurements in the X axis is located 100 in.(254 cm) forward of the aircraft nose.

    Here is a typical fuselage contour in the Y and Zplanes. Section A-A at frame 55.These are the major aircraft reference axis.

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    ATA CHAPTERS

    The aircraft structure is divided according to the ATA100 specifications.

    SECTION NUMBERS

    Each major part of the aircraft, corresponding toproduction receives a section number. The fuselagesection base number is 10.The fuselage is divided into various sections formanufacturing reasons.

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    SECTION NUMBERS

    The general wing section base number is 20.The general tail plane section base number is 30.

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    SECTION NUMBERS

    The engine sectionbase number is 40.The landing gear section base number is 50.The general belly fairing section base number is 60.

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    STATION NUMBERS

    The station number is the distance in centimeters ofa cross section from a reference point.The station/frame numbers shown correspond to thesection boundaries.Here are the engine station numbers.

    Note : For the vertical stabilizer the referencestation is z=0 at the VTZ axis.

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    STATION NUMBERS

    Horizontal stabilizer station numbers.

    Note : For the horizontal stabilizer the referencestation is y=0 at the A/C Y axis.

    Wings station numbers.

    Note : For wings the reference station is wingreference axis (WY). WY is located at 1868 mm(73.54 in) from A/C X axis.

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    ZONE NUMBERS

    There are 8 major zones in the aircraft.Each major zone is identified by the first digit of athree digit number.Fuselage and vertical stabilizer zones.

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    ZONE NUMBERS

    Belly fairing zones.

    Landing gear zones.

    Wings and horizontal stabilizer zones.

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  • A320 STRUCTURAL BREAKDOWN AND ZONING

    ZONE NUMBERS

    Nacelles and pylon zones.

    Door zones.

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  • A320 STRUCTURAL BREAKDOWN AND ZONING

    ZONE NUMBERS

    Access doors and panels are identified by the numberof the zone in which the panel is located followed bya two-letter suffix which locates it within the zone.Here is an example of access panel doors on the leftwing lower surface.

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  • 01 - GENERAL

    01-00-00 GROUND HANDLING

    CONTENTS :Servicing pointsA/C Servicing Arrangement 1Turning Radii

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  • AIRCRAFT GENERAL - SERVICING POINTS

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  • AIRCRAFT GENERAL - A/C SERVICING ARRANGEMENT

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  • SIMULATOR COCKPIT SAFETY CHECK LIST

    BEFORE POWER UP

    1. PLACARDS............................... CHECK 2. CIRCUIT BRAKERS ........................ CHECK 3. BAT 1.2 ...................OFF (CHECK VOLTAGE) 4. FIRE HANDLE (ENGINE/APU) ............IN/LATCHED 5. WIPERS .................................. OFF 6. LANDING GEAR LEVER ...................... DOWN 7. THRUST LEVERS ..............IDLE/REVERSE STOWED 8. ENGINE MASTER LEVERS...................... OFF 9. ENGINE START ROTARY SELECTOR ........... NORMAL10. SLAT/FLAPS LEVER ............... CHECK POSITION11. SPEED BRAKE LEVER .............. CHECK POSITION12. PARKING BRAKE ............................. ON13. WEATHER RADAR/ATC TRANSPONDER ............. OFF14. EXTERNAL POWER (IF AVAILABLE) .............. ON15. BAT 1.2 .................................. ON

    AFTER POWER UP

    1. VENT PANEL...................CHECK NO LIGHTS ON2. PROBE HEAT/WINDOW HEAT.............. AS REQUIRED3. EXTERIOR LIGHTS .................... AS REQUIRED4. ANNUNCIATOR LIGHT TEST..................PERFORM5. FUEL PUMPS................................ OFF6. LANDING GEARS INDICATION............ DOWN LOCKED

    BEFORE LEAVING THE SIMULATOR

    1. ADIRS ................................... OFF2. EXTERIOR LIGHTS ........................... OFF3. APU BLEED P/B ............................. OFF4. APU MASTER SW ............................. OFF5. EMERGENCY EXIT LIGHT....................... OFF6. CRTS (ECAM-EFIS) ......................... OFF7. BAT 1.2 .................................. OFF8. EXTERNAL POWER ............................ OFF

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  • 25 - EQUIPMENT/FURNISHING

    25-10-00 COCKPIT PRESENTATION

    CONTENTS:GeneralOverhead PanelGlareshieldMain Instrument PanelCenter PedestalSide Consoles

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    GENERAL

    The cockpit is equipped with adjustable seats for twocrew members, a third occupant seat and depending ofconfiguration a folding seat for a fourth occupant.Various furnishings and equipment are fitted in thecockpit for the comfort, convenience and safety ofthe occupants.

    OVERHEAD PANEL

    The controls of most aircraft systems are located onthe overhead panel.The overhead panel is divided into two main sections:

    - a FWD section including the system panels.- an AFT section mainly comprising the circuitbreaker panel.

    GLARESHIELD

    The Flight Control Unit (FCU), includes the ElectronicFlight Instrument System (EFIS) controls, and is usedfor control and monitoring of the Auto Flight System(AFS).It is located on the glareshield.The "Master Caution" and the "Master Warning" lightsare also located on the glareshield.

    MAIN INSTRUMENT PANEL

    Six interchangeable Cathode Ray Tubes are located onthe main instrument panel.Two of them are dedicated to the ECAM.The others are two Primary Flight Displays and twoNavigation Displays.Stand-by instruments and landing gear controls arealso located on the main instrument panel.

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    CENTER PEDESTAL

    Several control panels are located on the centerpedestal as shown on the screen.The mainly control panels are:

    - thrust levers and thrust reverser levers,- pitch trim wheels,- flaps and slats control, - brakes controls,- MCDUs.

    SIDE CONSOLES

    The side sticks and nose wheel steering handles aremounted on the side consoles.The side consoles provide documentation stowage,oxygen masks and communication devices.

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  • 31 - INDICATING/RECORDING SYSTEMS

    31-16-00 AVIONICS COMPARTMENT

    CONTENTS:Description

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  • AVIONICS COMPARTMENT

    DESCRIPTION

    The electronic avionics compartment is located belowthe cockpit and cabin floors.It includes:

    - the electronic racks (90VU and 80VU),- the weather radar shelf (109VU),- the relay and contactor boxes (103VU and107VU),

    - the annunciator light test unit (70VU),- AC and DC emergency power center (106VU).

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  • 31 - INDICATING/RECORDING SYSTEMS

    31-10-00 COCKPIT PHILOSOPHY

    CONTENTS:PhilosophyPush buttonsIndicationsColor Philosophy

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  • COCKPIT PHILOSOPHY

    PHILOSOPHY

    All the aircraft and system controls are arranged tobe within easy reach of the two crew members. Theconcentration of system controls on the overhead panelis achieved by extensive use of illuminated pushbuttonsdirectly installed on the system synoptic panel.In normal operation, no lights are illuminated in thecockpit. This is called the "lights out philosophy".

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  • COCKPIT PHILOSOPHY - PHILOSOPHYT MU

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  • COCKPIT PHILOSOPHY

    PUSHBUTTONS

    Status and failure indications are integrated wheneverpossible into the relevant illuminated pushbuttonswhich must be operated for corrective action.Most of the illuminated pushbuttons have two stablepositions: pressed in and released out; each positioncorresponding to a control signal sent to a system.Pressed in (Recessed):

    - Normally used system activation (AUTO or ON)- Temporarily used system activation (ON) - System activated for maintenance operation (ON)or override (OVRD).

    Released out (flush with the panel):- System deactivation (OFF)- Manual activation of a system (ON) - Activation of an alternate system (ALTN).

    Some pushbuttons have only one stable position:- released out.

    When pushed they send a control signal to the system.NOTE: When a part of the pushbutton is not used, it

    is identified by two dots.

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  • COCKPIT PHILOSOPHY - PUSH BUTTONSTM

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  • COCKPIT PHILOSOPHY

    INDICATIONS

    The indications lights which appeared on the screenare not push buttons. The lower part is not dedicatedto a control. These lights are not surrounded by alighted border.

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  • COCKPIT PHILOSOPHY - INDICATIONSTM

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  • COCKPIT PHILOSOPHY

    COLOR PHILOSOPHY

    The illuminated pushbutton and annunciator lights areof different colors according to their function.In normal operation, only green lights and sometimesblue lights are illuminated.

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  • THIS PAGE INTENTIONALLY LEFT BLANK

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  • 20 - STANDARD PRACTICES

    20-00-00 ELECTROSTATIC DISCHARGE

    CONTENTS:ESD ProblemsESD ProtectionLRU RemovalLRU TestWork StationSelf Examination

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  • ELECTROSTATIC DISCHARGE

    ESD PROBLEMS

    ESD stands for ELECTROSTATIC DISCHARGE which isgenerated by rubbing materials with each other.By moving over plastic materials (synthetic fibers),wearing synthetic fiber clothing, electrical chargesbuild up on the body.Thus voltages of 12000 to 35000 volts can develop ona person.Touching connector pins of computer units (Fig. 1), adischarge path is formed through wiring and components.Integrated Circuit(IC) chips can be partly damaged ortotally destroyed.Here is the so-called "tribo-electric" series ofmaterials (Fig. 2).Rubbing materials from this series against each otherand then separating them from each other causes abuild-up of electrostatic charges.If the materials are far apart in the series, therewill be a higher electric charge.

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  • ELECTROSTATIC DISCHARGE - ESD PROBLEMS

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  • ELECTROSTATIC DISCHARGE

    ESD PROTECTION

    Here are some precautions to avoid damage of electronicequipment by ELECTROSTATIC DISCHARGE.

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  • ELECTROSTATIC DISCHARGE

    LRU REMOVAL

    Replacing an LRU (LINE-REPLACEABLE UNIT) bearing thislabel, requires these precautions.

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  • ELECTROSTATIC DISCHARGE - LRU REMOVAL

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  • ELECTROSTATIC DISCHARGE

    LRU TEST

    Testing of installed LRUs requires the followingprecautions.

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  • ELECTROSTATIC DISCHARGE - LRU TEST

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  • ELECTROSTATIC DISCHARGE

    WORK STATION

    The removal and testing of PRINTED-CIRCUIT BOARDS froman LRU bearing this label, is carried out as follows.

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  • ELECTROSTATIC DISCHARGE - WORK STATION

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  • SELF EXAMINATION

    How does electrostatic electricity build up ?A - By touching electrical circuits under

    tension.B - By rubbing materials with each other or

    separating plastic sheets or tapes.C - By moving metals over plastic surfaces.

    How is electrostatic discharge sensitive equipmentidentified ?

    A - By a circular red label.B - By an orange triangular label.C - By a black-and-yellow label.

    Which are some basic precautions to be taken inthe case of electrostatic discharge sensitiveequipement ?

    A - Cover the unit with plastic material.B - Do not touch connector pins, place

    protective caps on them.C - Test circuits with dielectric testers if

    necessary.

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  • 31 - INDICATING/RECORDING SYSTEMS

    31-00-00 COMPUTER REMOVAL/INSTALLATION

    CONTENTS:Computer Removal/Installation

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  • COMPUTER REMOVAL/INSTALLATION

    COMPUTER REMOVAL/INSTALLATION

    Before starting a computer removal installationprocedure, the aircraft has to be set in maintenanceconfiguration.The first task is to make sure that the ground servicenetwork is energized and the access door is open andaccessible.Then make sure that the circuit breaker listed in theremoval of the computer procedure of the AMM is open.The first action is to loosen the nut and then to lowerthe nut.When the nut is lowered, pull the computer on its rackto disconnect the electrical connectors and remove thecomputer from its rack.Before starting a computer installation procedure,clean and do a visual inspection of the componentinterface and of the adjacent area.The first task is to remove the blanking caps from theelectrical connectors and make sure that the electricalconnectors are clean and in the correct condition.Then install the computer on its rack and push it onits rack to connect the electrical connectors.

    Now you can engage the nuts on the studs and tightenthem.The installation is finished. You can close the circuitbreaker.The last actions of the computer installation are todo a test through the MCDU and close the access.Make sure that the work area is clean and clear oftools and other items, close the access door and removethe access platform.

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  • 24 - ELECTRICAL POWER

    24-00-00 OUTSIDE SAFETY INSPECTION,COCKPIT CHECK-LIST AND POWERSUPPLY FOR MAINTENANCE PURPOSES

    CONTENTS:1 - Nose Station2 - Right Main Landing Gear Station3 - Right Engine Station4 - Right Wing Station5 - Left Wing Station6 - Left Engine Station7 - Left Main Landing Gear Station8 - Aircraft Area9 - Nose Station-EXT PWR Receptacle10 - Cockpit Station

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  • OUTSIDE SAFETY INSPECTION, COCKPIT CHECK-LIST ANDPOWER SUPPLY FOR MAINTENANCE PURPOSES

    Note: this module presents an A321 but the procedureis also valid for both A319 and A320.

    Note: this module presents an A/C powered by CFMengines but the procedure is also valid for IAEengines.

    1- NOSE STATION

    Nose landing gear chocks................in placeNose landing gear doors.................. closedNose landing gear safety pin ...........installedNose landing gear steering pin ....... as requiredAircraft ..................electrically grounded

    2 - RIGHT MAIN LANDING GEAR STATION

    Main landing gear door................... closedMain landing gear safety sleeve ........installedMain landing gear chocks................in place

    3 - RIGHT ENGINE STATION

    Engine right side access doors ...........securedEngine left side access doors ............securedEngine fan cowls ........................securedEngine thrust reverser cowls .............secured

    4 - RIGHT WING STATION

    Flaps/slats..................... check position Ground spoilers .................. check position

    5 - LEFT WING STATION

    Flaps/slats...................... check positionGround spoilers .................. check position

    6 - LEFT ENGINE STATION

    Engine right side access doors .......... securedEngine left side access doors ........... securedEngine fan cowls ....................... securedEngine thrust reverser cowls ............ secured

    7 - LEFT MAIN LANDING GEAR STATION

    RAT safety device ............... stowed positionMain landing gear door................... closedMain landing gear safety sleeve.........installedMain landing gear chocks............... in place

    8 - AIRCRAFT AREA

    Aircraft area.......................clear/clean

    9 - NOSE STATION-EXT PWR RECEPTACLE

    External power ...............connected/available

    10 - COCKPIT STATION

    Cockpit safety check-listRear and overhead C/B panels .......... checkedEmergency equipment :escape ropes ....................... checkedfire extinguisher................... checkedsmoke hood ......................... checkedfire protective gloves .............. checkedcrash axe.......................... checkedlife vests ......................... checked

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  • oxygen masks ........................checkedflash lights ........................checked

    Wipers .................................. OFFBAT1 and 2 pushbutton switches ............ OFFCheck voltage above 25Volts.

    BAT1 and 2 pushbutton switches ........... AUTOCheck R/H dome light on.

    Speed brake handle ............. RETRACT-DISARMIf speed brake handle disagrees with surfaceposition, maintenance action due.

    Thrust levers ........................... IDLEEngine master switches 1 and 2 ............ OFFEngine ignition mode selector ............ NORMFlap handle... set according to surface positionSet flap handle according to surfaceposition.If engine reverser cowls have to be openedfor maintenance action, the slats must beretracted.

    Radar ................................... OFFATC transponder .......................... OFFGravity gear extension............ RESET/STOWEDLanding gear lever ........... DOWN/THREE GREENControls Safety C/L .................COMPLETED

    Power supplyEXT PWR .................................. ONGEN1 and GEN2 ............................. ONScan and check no amber lights (except GEN 1and 2 fault lights).

    GALLEY ...............................AS RQRDVentilation panel ...................no lights

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  • OUTSIDE SAFETY INSPECTION, COCKPIT CHECK-LIST AND POWER SUPPLY FOR MAINTENANCE PURPOSES

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    Table of contentsGENERAL** Aircraft Dimensions (1) (A320)** Aircraft Dimensions (1) (A319)** Aircraft Dimensions (1) (A321)** Structure General (1)** Structural Breakdown and Zoning (3)** Ground Handling (1)** Cockpit Presentation (1)** Avionics Compartment (1)** Cockpit Philosophy (1)Electrostatic Discharge (3)Computer R/I (3)** Maintenance External Visit (3)

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