SB_27_1199_02 service buletin

@A318/A319/A320/A321SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORYATA SYSTEM: 27

TITLE: FLIGHT CONTROLS - ELAC SYSTEM - RESTORE ELAC2 AND THSMOTOR 1 POWER SUPPLY (SB ONLY)

MODIFICATION No.: 39998P11410 39999P11411

This page transmits Revision No.02 of Service Bulletin No.A320-27-1199

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

This Service Bulletin has been accomplished at Revision No. 01 on aircraft MSN 3480 to validate itscontent.

Compliance becomes Mandatory

CHANGES

SUMMARYREASON/DESCRIPTION/OPERATIONALCONSEQUENCES

REASON UPDATED R

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED RMATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATEDR

EFFECTIVITY OPERATOR LIST UPDATED RMANPOWER MANPOWER UPDATED RAPPENDICES APPENDICES UPDATED RPLANNING INFORMATIONEFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATEDR

Material Effectivity MATERIAL EFFECTIVITY UPDATEDMATERIAL SET UPDATED

R

REASONHistory HISTORY UPDATED R

DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199

REVISION No.: 02 - Sep 20/10 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.



Operational/MaintenanceConsequences

OPERATIONAL/MAINTENANCE CONSEQUENCESUPDATED

R

COMPLIANCEClassification CLASSIFICATION UPDATED RAccomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER UPDATED RWEIGHT AND BALANCE WEIGHT UPDATED

BALANCE UPDATEDR

REFERENCES REFERENCED DOCUMENTATION UPDATED RPUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED RMATERIAL INFORMATIONMATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATEDMATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATEDMATERIAL PRICE UPDATEDMATERIAL SET UPDATED

R

LIST OF COMPONENTSKit 271199A01R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATEDQUANTITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONSTASK 271199- 831-801-001-Modification

Task associated data - 001 ZONE UPDATEDMAN HOURS UPDATEDELAPSED TIME UPDATED

R

Subtask 271199-941-001-001 SUBTASK SOLUTION UPDATEDREFERENCED DOCUMENTATION UPDATEDCONFIGURATION UPDATEDFIGURE REFERENCE UPDATEDNOTE UPDATEDPANEL UPDATEDFIN UPDATEDREFERENCES UPDATED

R

Subtask 271199-010-001-001 SUBTASK SOLUTION ADDED NSubtask 271199-831-001-001 SUBTASK SOLUTION UPDATED

PANEL UPDATEDQUANTITY UPDATEDNOTE UPDATEDLOCATION UPDATEDMANPOWER RESSOURCE UPDATEDMATERIAL LIST UPDATED

R

Subtask 271199-831-002-001 SUBTASK SOLUTION UPDATEDNOTE UPDATEDMANPOWER RESSOURCE UPDATEDMATERIAL LIST UPDATED

R



5




Subtask 271199-831-003-001 SUBTASK SOLUTION UPDATEDFIN UPDATEDREFERENCED DOCUMENTATION UPDATEDNOTE UPDATEDMANPOWER RESSOURCE UPDATEDMATERIAL LIST UPDATED

R

Subtask 271199-831-004-001 SUBTASK SOLUTION UPDATEDPANEL UPDATEDCONFIGURATION UPDATEDFIGURE REFERENCE UPDATEDNOTE UPDATEDLOCATION UPDATEDMANPOWER RESSOURCE UPDATEDMATERIAL LIST UPDATEDREFERENCES UPDATED

R

Subtask 271199-710-002-001 SUBTASK SOLUTION UPDATEDREFERENCED DOCUMENTATION UPDATEDFIN UPDATEDREFERENCES UPDATED

R

Subtask 271199-740-001-001 SUBTASK SOLUTION UPDATEDREFERENCED DOCUMENTATION UPDATEDREFERENCES UPDATED

R

Subtask 271199-865-001-001 SUBTASK SOLUTION UPDATEDREFERENCES UPDATEDREFERENCED DOCUMENTATION UPDATEDNOTE UPDATED

R

Subtask 271199-710-003-001 SUBTASK SOLUTION UPDATEDREFERENCES UPDATEDNOTE UPDATEDREFERENCED DOCUMENTATION UPDATED

R

Subtask 271199-710-004-001 SUBTASK SOLUTION UPDATEDREFERENCES UPDATEDNOTE UPDATEDREFERENCED DOCUMENTATION UPDATED

R

Subtask 271199-710-005-001 SUBTASK SOLUTION UPDATEDREFERENCED DOCUMENTATION UPDATEDNOTE UPDATEDREFERENCES UPDATED

R

Subtask 271199-865-003-001 SUBTASK SOLUTION UPDATEDREFERENCES UPDATEDNOTE UPDATEDREFERENCED DOCUMENTATION UPDATEDCIRCUIT BREAKER UPDATEDPANEL UPDATED

R

Subtask 271199-410-002-001 SUBTASK SOLUTION ADDED NSubtask 271199-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATEDPANEL UPDATEDREFERENCES UPDATED

R

Fig. A-FBGAA FIGURE SOLUTION ADDED N

Fig. A-FBGAA Sheet 01 SHEET ADDED N



5




Fig. A-FBEAA FIGURE SOLUTION UPDATED R

Fig. A-FBEAA Sheet 01 SHEET UPDATED R



Fig. A-FBEAA Sheet 04 SHEET ADDED N

Fig. A-FBHAA FIGURE SOLUTION ADDED N

Fig. A-FBHAA Sheet 01 SHEET ADDED N

Fig. A-FBFAA FIGURE SOLUTION ADDED N

Fig. A-FBFAA Sheet 01 SHEET ADDED N

Fig. A-FBFAA Sheet 02 SHEET ADDED N

Fig. A-FBDAA FIGURE SOLUTION UPDATED R

Fig. A-FBDAA Sheet 02 SHEET UPDATED R

Fig. A-FCDAA FIGURE SOLUTION UPDATED R

Fig. A-FCDAA Sheet 01 SHEET UPDATED R

Appendix 01

Fig. A-FAAAA FIGURE SOLUTION ADDED N

Fig. A-FAAAA Sheet 01 SHEET ADDED N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

Revision No.01 of this Service Bulletin is issued to correct the following paragraphs:

SUBTASK 271199-710-003 001 Operational test of the Logics that activate the ELAC 1 and 2 and SEC1 STBY PWR SPLY

SUBTASK 271199-710-005 001 Operational Test of the Ability of the ELAC 1 and SEC1 and 2 toachieve Pitch Control

REVISION SEQUENCE

ORIGINAL: Nov 09/09

REVISION No. : 01 - Mar 04/10

REVISION No. : 02 - Sep 20/10



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SUMMARY


This summary is for information only and is not approved for modification of the aircraft.



**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATIONMAJOR NoneMINOR 39998P11410 39999P11411

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on themass, balance, structural strength, reliability, operational characteristics affecting theairworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

This Service Bulletin is published for all operators of A320 aircraft.

Under emergency electrical configuration (electrical power achieved by emergency electrical generatorCSMG (Constant Speed Motor Generator) driven by the RAT (Ram Air Turbine)), only ELAC1 andSEC1 are operative among the Flight Control computer.

In the original design of the Single Aisle (SA) A/C family, the RAT was not efficient enough with NLGextended to provide Blue hydraulic pressure and to energize the emergency electrical generator CSMG.

In order to provide better aircraft controllability and redundancy, a set of wiring and relays was installedto energize the ELAC2 and THS Motor 1 through the battery under emergency electrical configurationas soon the NLG is extended. Taking benefit of the enhanced RAT installed later on SA aircraft,the ELAC2 and THS Motor 1 supply logic has been simplified. Logic has been simplified and isno more activated when NLG is extended. This has been introduced by Mod. No. 38310P10576(FLIGHT CONTROLS -ELAC SYSTEM - IMPROVE ELECTRICAL INSTALLATION OF ELAC2 ANDTHS MOTOR 1 POWER SUPPLY) in 2007. This modification aimed at removing temporized relays44CE, 46CE and 64CE (which embed electronic devices that make them more fragile), thus improvingthe ELAC2 and THS Motor 1 supply logic robustness.



5



SUMMARY

However, it has been identified that this modification affects the roll controllability in case of emergencyelectrical configuration combined with a dual G +Y hydraulic loss. In this extremely remote situation, onA320 aircraft, the roll control would be only provided by the left aileron with landing gear extended.

This Service Bulletin recommends to restore the aircraft configuration before the application of the Mod.No. 38310P10576.

This modification will permit, in case of an emergency electrical configuration combined with a dual G+Y hydraulic loss arises on the A320 aircraft, to restore the availability of the right aileron upon landinggear extension.

Accomplishment of this Service Bulletin implies some changes in the procedure given in AMM Task27-96-00-710-018 that is called as per MPD 27-90-00 (400FH or 80DY). Until the AMM is accordinglyupdated (after the SB Reporting Sheet receipt and AMM update processing), Airbus ask operatorsto use the testing procedure embedded in this Service Bulletin at SUBTASK 271199-710-003 001Operational test of the Logics that activate the ELAC 1 and 2 and SEC 1 STBY PWR SPLY .

GENERAL EVALUATION

EVALUATION TABLECOMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NORELIABILITY AFFECTED NO PAX COMFORT AFFECTED NOCOST SAVING NO ETOPS AFFECTED NOSTRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLEMATERIAL SET QTY PER

A/CPRICE PERA/C (USD)

MAIN PARTS

Kit 271199A01R01 1 3,370.00 Bundle, relays

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

62X AAR ABY ADH AEE AFL AFR AIJ AVA AXM AZA BAW BHPCCA CEB CES CSC CSZ DKH EIN FFT IGO JBU JST KNE KZRLAN LBT LTU MDL PAL RNV SBI TAI TAM VLG VRD WAU WZZ

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU NoneOEB NoneAOT NoneSIL None



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SUMMARY

LINE MAINTENANCE AFFECTED NoLIFE LIMIT NoneOTHER None

NATURE OF THE WORK

AIRCRAFT YESEQUIPMENT NO

HARD NOSOFT NOOBRM NO

MANPOWER

Task 271199-831-801-001: ModificationTOTAL MANHOURS 56.00ELAPSED TIME (HOURS) 37.00

APPENDICES

Appendix 01



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SUMMARY

**CONF ALL

FR1

FR9

FR16

FR20

FR24A

80VU

90VU

106VU

188VU

N_SB_271199_5_SAAA_01_00

Figure A-FSAAA - Sheet 01



5







This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain theproperty of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection withany information contained in it. It is delivered on the express condition that said document and theinformation contained in it shall be treated as confidential, shall not be used for any purpose other thanthat for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shallnot be duplicated in any manner (except for the purposes of performing the tasks described hereunderand provided that any recipient of such document shall comply with the conditions herein), withoutAIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This modification is applicable by Service Bulletin only.

NOTE: This Service Bulletin has been validated on A320 aircraft MSN3480.

NOTE: This Service Bulletin is only applicable on Aircraft on which Mod.No. 38310P10576 (FLIGHT CONTROLS - ELAC SYSTEM IMPROVEELECTRICAL INSTALLATION OF ELAC2 AND THS MOTOR 1 POWERSUPPLY) is embodied.

(1) Models

320-214 320-216 320-232 320-233

(2) Effectivity by MSN

3391-3392 3394 3396 3398 3400 3402 3404 3408-3410 3412 3414 3416 3418 34203422-3423 3425 3427 3430-3431 3433 3435 3437 3439-3440 3444 3446 3448-34493451 3453 3455-3457 3460-3461 3464-3465 3468 3470 3472-3490 3492 3494-34973499 3501-3503 3505-3506 3508 3510-3511 3514-3517 3519 3521 3524 35263528-3529 3531-3532 3535-3536 3538 3540-3541 3543 3545 3547 3549-35503553-3554



5



(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the timeof issue in accordance with the information available to AIRBUS. Any future changesresulting from transfer of an aircraft from one operator to another will not be reflected inthis list unless the Service Bulletin is revised for another reason.

OPERATOR MSN62X 3402AAR 3437 3483 3496ABY 3444 3476ADH 3502 3515 3532AEE 3392 3423 3439 3478 3526AFL 3410 3511 3545AFR 3420 3470AIJ 3508 3514AVA 3408AXM 3394 3404 3427 3448 3477 3486 3489 3505 3521 3536 3549AZA 3412 3464 3482BAW 3468 3499 3550BHP 3422CCA 3461 3506CEB 3433 3472 3487CES 3481CSC 3449CSZ 3435 3440 3456 3528DKH 3485EIN 3501FFT 3431IGO 3414 3453 3457 3497 3541JBU 3416 3451 3479 3488 3517 3554JST 3474 3495 3547KNE 3396 3425 3475KZR 3484 3519LAN 3535LBT 3480LTU 3516MDL 3524 3543PAL 3455 3553RNV 3492SBI 3446 3473 3490 3494TAI 3418 3510 3538TAM 3391 3540VLG 3400 3529VRD 3398 3460 3465 3503WAU 3531WZZ 3409 3430



5



(4) Configuration by MSN

MSN CONFIGURATION3391 3392 3394 3396 3398 3400 3402 3404 3408 3409 34103412 3414 3416 3418 3420 3422 3423 3425 3427 3430 34313433 3435 3437 3439 3440 3444 3446 3448 3449 3451 34533455 3456 3457 3460 3461 3464 3465 3468 3470 3472 34733474 3475 3476 3477 3478 3479 3480 3481 3482 3483 34843485 3486 3487 3488 3489 3490 3492 3494 3495 3496 34973499 3501 3502 3503 3505 3506 3508 3510 3511 3514 35153516 3517 3519 3521 3524 3526 3528 3529 3531 3532 35353536 3538 3540 3541 3543 3545 3547 3549 3550 3553 3554

001

(5) Configuration definition

**CONF 001Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as astandard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTESKit 271199A01R01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

This Service Bulletin is published for all operators of A320 aircraft.

Under emergency electrical configuration (electrical power achieved by emergencyelectrical generator CSMG (Constant Speed Motor Generator) driven by the RAT (RamAir Turbine)), only ELAC1 and SEC1 are operative among the Flight Control computer.

In the original design of the Single Aisle (SA) A/C family, the RAT was not efficientenough with NLG extended to provide Blue hydraulic pressure and to energize theemergency electrical generator CSMG.

In order to provide better aircraft controllability and redundancy, a set of wiring andrelays was installed to energize the ELAC2 and THS Motor 1 through the batteryunder emergency electrical configuration as soon the NLG is extended. Taking benefitof the enhanced RAT installed later on SA aircraft, the ELAC2 and THS Motor 1supply logic has been simplified. Logic has been simplified and is no more activatedwhen NLG is extended. This has been introduced by Mod. No. 38310P10576 (FLIGHTCONTROLS -ELAC SYSTEM - IMPROVE ELECTRICAL INSTALLATION OF ELAC2AND THS MOTOR 1 POWER SUPPLY) in 2007. This modification aimed at removingtemporized relays 44CE, 46CE and 64CE (which embed electronic devices that makethem more fragile), thus improving the ELAC2 and THS Motor 1 supply logic robustness.



5



However, it has been identified that this modification affects the roll controllability in caseof emergency electrical configuration combined with a dual G +Y hydraulic loss. In thisextremely remote situation, on A320 aircraft, the roll control would be only provided bythe left aileron with landing gear extended.

(2) Objective/Action

This Service Bulletin recommends to restore the aircraft configuration before theapplication of the Mod. No. 38310P10576.

(3) Advantages

This modification will permit, in case of an emergency electrical configuration combinedwith a dual G +Y hydraulic loss arises on the A320 aircraft, to restore the availability ofthe right aileron upon landing gear extension.

(4) Operational/Maintenance Consequences

Accomplishment of this Service Bulletin implies some changes in the procedure given inAMM Task 27-96-00-710-018 that is called as per MPD 27-90-00 (400FH or 80DY). Untilthe AMM is accordingly updated (after the SB Reporting Sheet receipt and AMM updateprocessing), Airbus ask operators to use the testing procedure embedded in this ServiceBulletin at SUBTASK 271199-710-003 001 Operational test of the Logics that activatethe ELAC 1 and 2 and SEC 1 STBY PWR SPLY .

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 271199-831-801-001: Modification

(1) Modify the wiring in Electronics Racks 80VU and 188VU

(2) Modify the Wiring in Electronics Racks 83VU and 84VU

(3) Modify the wiring in Electronics Rack 93VU

(4) Modify the wiring in zone 120

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin has been rendered mandatory by the issue of anAirworthiness Directive (AD) published by the European Aviation Safety Agency (EASA).The AD must be used as the reference document for the mandatory accomplishmenttimescale.



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F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA 21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not ofAIRBUS origin, and which affects the content of this Service Bulletin, the operator isresponsible for obtaining approval by its airworthiness authority for any adaptation necessarybefore incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost todo the work. These estimates assume that the work will be done by experienced personnel,and may need to be revised upwards to suit operator’s circumstances. The estimates do notinclude the time to prepare, plan or inspect the work. Manufacture and procurement of partsand tools, drying times for paints, sealants, etc., and general administration work are also notincluded.

Task 271199-831-801-001: ModificationGet Access 2.00On Aircraft

Modify the wiring in Electronics Racks 80VU and188VU

24.00

Modify the Wiring in Electronics Racks 83VU and84VU

7.00

Modify the wiring in Electronics Rack 93VU 5.00

Modify the wiring in zone 120 12.00

Tests 4.00Close-Up 2.00

TOTAL MANHOURS 56.00ELAPSED TIME (HOURS) 37.00

NOTE: For details of elapsed time assumptions, Refer to Appendix 01

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on theManufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition ofMEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.308 KG (+0.6790 LB)Effect on Balance +2.883 KGM (+20.852 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed



5



J. REFERENCES

Aircraft Maintenance Manual (AMM) 11-00-00 12-34-24 20-28-0021-26-00 21-41-00 21-63-0021-63-34 22-96-00 22-97-0024-22-34 24-24-00 24-38-5124-41-00 24-50-00 25-54-1125-54-12 27-93-00 27-93-3427-94-00 27-94-34 27-96-0029-10-00 29-23-00 29-24-0031-50-00 31-60-00 32-31-7132-69-00 33-13-00 33-14-0035-11-41 35-12-00 52-10-0052-30-00 52-41-00

Elec. Std. Practices Manual (ESPM) 20-25-51 20-30-00 20-33-4420-46-50 20-52-10 20-52-2120-55-00

Maintenance Planning Document (MPD) 27-90-00Standards Manual (SM)Weight and Balance Manual (WBM) 1-00-07

K. PUBLICATION AFFECTED

Aircraft Maintenance Manual (AMM) 27-90-00 27-93-00 27-96-00Aircraft Schematic Manual (ASM) 24-24-00 27-92-00Aircraft Wiring List (AWL)Aircraft Wiring Manual (AWM) 24-24-05 24-24-06 27-92-02

27-92-10Illustrated Parts Catalog (IPC) 24-24-08 24-62-08 27-92-08Maintenance Planning Document (MPD) 27-90-00Trouble Shooting Manual (TSM) 27-96-00

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None



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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 271199A01R01 Customers with aircraft shown in theeffectivity of this Service Bulletin should senda purchase order to AIRBUS. Quote thenumber of this Service Bulletin. The addressis:AIRBUS Material, Logistics and SuppliersWeg beim Jaeger 150 D22335 HamburgGermanyFor ordering by internet:http://spares.airbus.comFor ordering modification kits by fax: +49 4050 76 25 90For ordering of single spares by fax: +49 4050 76 40 13

(2) Price and Availability

Kit 271199A01R01Cost 3,370.00 USD

Availability 90 calendar days from receipt of order

The Kit availability given above is the standard lead time from the date of your purchaseorder. If you require Kits before this time, please include a retrofit planning schedule withyour order so that we can try to comply with your requirements.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will provide the material at no charge for orders placed before Dec. 31st 2011.AIRBUS will also credit the manhours indicated in this Service Bulletin at the operator’sagreed in-house warranty labor rate for claims received not later than 90 days aftercompletion of the last affected aircraft of your fleet.

C. LIST OF COMPONENTS

Kit 271199A01R01

ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEENOTES

1 MS21042L04 9 NUT2 E0219ASXXV 3 BASE (1) (2)

3 E0217XXV0250A 3 RELAY (2)

D9000095024895 1 BundleD9100095008795 1 Placard



5



ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEENOTES

NSA935401-03 150 TIENSA935401-10 125 TIE

NOTE: If you find part numbers of hardware components in the related kit(s) whichyou cannot identify in the LIST OF COMPONENTS of this Service Bulletin,refer to Standards Manual (SM). The SM will give you the correct part numberto part number relationship.

NOTE (1): PN E0219ASXXV will be supplied through PN E0219AS.

NOTE (2): For the polarization, refer to ESPM 20-46-50.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None



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3. ACCOMPLISHMENT INSTRUCTIONS

Task 271199-831-801-001 - Modification

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONSINCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEPELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLYAND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCEWORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DOTHIS:

PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; ASNECESSARY ON WIRING AND COMPONENTS.

REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHERCONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATIONAND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

Zone120 121 125 127 128From 128 to 127From 131 to 132

Modified FIN44CE 44CEA 46CE 46CEA 64CE 64CEA 13VC 35VC 80VC 219VC 281VC 1227VC1249VC 1833VT 1837VT 1846VT 1892VT

AccessDoor 811 812 822 824 825

Panel 131DW 131HC 131KC 131LC 132BW 132EWManpower

TOTAL MANHOURS 56.00ELAPSED TIME (HOURS) 37.00

A. GENERAL

(1) Subtask 271199-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in thisService Bulletin.



5



(2) Subtask 271199-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

ReferencesAircraft Maintenance Manual (AMM) 11-00-00, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-25-5120-30-0020-33-4420-52-21

(a) Put blanking caps on the disconnected electrical connectors.

(b) Obey the instructions for the general wiring installation (Refer to ESPM 20-30-00).

(c) Route the new wires with the wires that are in the aircraft.

(d) Use existing spare conduits to route wires in location difficult to get access to.

(e) To install the new wires, cut them to the necessary length, crimp the terminals andconnect them.

(f) For the cable tie application and tooling refer to ESPM 20-25-51 and ESPM20-33-44.

(g) Do a continuity test of the modified and new wires (Refer to ESPM 20-52-21).

(h) When you will install new or modified electrical connectors do a visual check ofeach connector which was disconnected to make sure that :

- all the electrical connectors are serviceable before you connect them,

- the label of the connector is the same as the label on the receptacle,

- where locking facilities exist, the connector is correctly locked with appropriatedlockwire.

(i) Bond the placards (Refer to AMM 11-00-00, Page Block 001).

B. PREPARATION

(1) Subtask 271199-941-001-001 - Job Set-up

Manpower Resources

Skills ELECTRICAL

ReferencesAircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 24-38-51-000-001Task 52-10-00-010-00152-30-00, Page Block 201Task 52-41-00-010-002



5



ReferencesFig. A-FBGAAAccess to Work area

Sheet 01

(a) Make sure that the aircraft is electrically grounded (Refer to AMM Task12-34-24-869-002).

(b) Put the access platform in position.

(c)

NOTE:For access description, refer to Fig. A-FBGAA.

(d) Open the FWD avionics compartment lateral doors 812, 822 and 824 (Refer toAMM Task 52-41-00-010-002).

(e) Open the FWD avionics compartment door 811 (Refer to AMM Task52-41-00-010-002).

(f) Open the FWD cargo compartment door 825 (Refer to AMM 52-30-00, Page Block201).

(g) Make sure that the external connector(s) is(are) not connected to the aircraftreceptacle(s) EXT PW.

(h) Make sure that there is(are) warning notice(s) on external power receptacle to tellperson not to connect an external power source.

(i) Make sure that the EMER EXIT LT pushbutton switch on 25VU is on OFF position.

(j) In the cockpit, on the overhead panel 35VU release BAT pushbutton switches.

(k) Put a warning notice on panel 35VU to tell persons not to operate the batteries.

(l) Put a warning notice on refuel/defuel panel 800VU to tell persons not to operate theNORMAL BATTERY switch.

(m) Put a warning notice in the cockpit to tell persons not to start the APU.

(n) Put a warning notice in the cockpit to tell persons not to start the ENG1, 2.

(o) Batteries disconnection:

- for Job Set-up, refer to Removal/Installation of the Batteries (Refer to AMMTask 24-38-51-000-001),

- turn the knurled nut a quarter turn,

- disconnect the connectors,

- put blanking caps on the disconnected electrical connectors.



5



(2) Subtask 271199-010-001-001 - Removal of items for Access

Work Zones and Access PanelsZone Access/Work location

125 Access Door 812Work location Frame 13

From 131 Access Door 825Work location Frame 24

To 132 Access Door 825Work location Frame 24


Manpower Resources

Skills AIRFRAME


Task 25-54-11-000-001Task 25-54-12-000-002Task 27-93-34-000-001Task 35-11-41-000-001

Fig. A-FBHAADrain panel above 90VU Left side

Sheet 01

(a) Remove and retain the partition panels 131DW, 131CW and 132EW for access(Refer to AMM Task 25-54-11-000-001).

(b) Remove and retain the Ceiling panels 131LC, 131KC and 131HC for access (Referto AMM Task 25-54-12-000-002).

(c) Remove and retain the Crew Oxygen-Storage Cylinder (5750HM) as per AMM Task35-11-41-000-001.

(d) Remove and retain the Drain panel above the Electronics Rack 91VU (Refer to Fig.A-FBHAA).

1 Remove the bracket for electrical routing

1 Screw NAS1096-3-8 Item (3) Retain

1 Washer ASNA2397-10L Item (4) Retain

1 Nut NSA5067-3-1 Item (5) Retain

2 Turn the 3 latches a quarter turn

3 Latch ASNA2584-1201 Item (2) Retain



5



3 Remove the Drain panel

1 Cover assy Left D92412461 Item (1) Retain

(e) Remove and retain the ELAC2 (2CE2) for access (Refer to AMM Task27-93-34-000-001).

(f) Remove and retain the Generator Control Units (1XU1, 1XU2) as per AMM Task24-22-34-000-001.

C. PROCEDURE

(1) Subtask 271199-831-001-001 - Modify the wiring in Electronics Racks 80VU and188VU


128 Access Door 824, Door 825Panel 131DW, Panel 132BW, Panel 132EW,Panel 131LC, Panel 131KC, Panel 131HC

Work location Electrical panel 80VUElectrical panel 188VU

Manpower Resources

Manhours 24.00Minimum number of person 1

Subtask elapsed time 24.00

Skills ELECTRICAL

Material necessary to do the job

Kit 271199A01R01ITEM NEW PART N˚ QTY (UM) KEYWORD SEE

NOTES1 MS21042L04 9 NUT2 E0219ASXXV 3 BASE (1) (2)

3 E0217XXV0250A 3 RELAY (2)

D9000095024895 1 BundleD9100095008795 1 PlacardNSA935401-03 50 TIENSA935401-10 50 TIE

NOTE (1): PN E0219ASXXV will be supplied through PN E0219AS.

NOTE (2): For the polarization, refer to ESPM 20-46-50.

ReferencesElec. Std. Practices Manual (ESPM) 20-46-50

Fig. A-FBAAAWiring diagram 188VU

Sheet 01Sheet 02



5



ReferencesFig. A-FCAAAHook-up Chart 188VU

Sheet 01Sheet 02

Fig. A-FBEAAWork area location

Sheet 01Sheet 02Sheet 03Sheet 04

(a) Installation of the Relays 44CE, 46CE and 64CE (refer to Fig. A-FBEAA):

1 Install in position D02 :

FIN 44CEA1 Base E0219ASXXV Item 2

FIN 44CE1 Relay E0217XXV0250A Item 3

3 Nut MS21042L04 Item 1

2 Install in position C08:




3 Install in position A08:




4 Near new relays, affix placards supplied in :

1 Placard Set D9100095008795

(b) Modify the wiring:

1 Remove the wire as shown on the wiring diagram Fig. A-FBAAA Sheet 01 andas given in the Hook-up Chart lines:

- 1 thru 8 (refer to Fig. A-FCAAA Sheet 01).



5



2 Install the wires as shown on the wiring diagram Fig. A-FBAAA Sheet 02 andas given in the Hook-up Chart lines:

- 12 thru 25 (refer to Fig. A-FCAAA Sheet 01)

- 1 thru 15 (refer to Fig. A-FCAAA Sheet 02)

supplied in

1 Bundle D9000095024895

NOTE: Routes 7M and 8M are not identified on the aircraft:

- route 7M is a branch from route 1M,

- route 8M is a branch from route 2M.

3 Attach the wires with:

50 Tie-Cable NSA935401-03


(2) Subtask 271199-831-002-001 - Modify the Wiring in Electronics Racks 83VU and84VU


127 Access Door 824Work location Electrical panel 83VU

Electrical panel 84VU

Manpower Resources



Skills ELECTRICAL



NOTESD9000095024895 1 BundleNSA935401-03 25 TIENSA935401-10 25 TIE

ReferencesFig. A-FBBAAWiring diagram 83VU/84VU

Sheet 01Sheet 02



5



ReferencesFig. A-FCBAAHook-up Chart 83VU/84VU

Sheet 01

(a) Remove the wires as shown on the wiring diagram Fig. A-FBBAA Sheet 01 and asgiven in the Hook-up Chart lines:

- 1 thru 3 (refer to Fig. A-FCBAA Sheet 01).

(b) Install the wires as shown on the wiring diagram Fig. A-FBBAA Sheet 02 and asgiven in the Hook-up Chart lines:

- 7 thru 11 (refer to Fig. A-FCBAA Sheet 01)

supplied in

1 Bundle D9000095024895

NOTE: Routes 7M and 8M are not identified on the aircraft:

- route 7M is a branch from route 1M,


(c) Attach the wires with:



(3) Subtask 271199-831-003-001 - Modify the wiring in Electronics Rack 93VU



Manpower Resources



Skills ELECTRICAL



NOTESD9000095024895 1 BundleNSA935401-03 25 TIE



5




Task 21-63-34-000-001Task 21-63-34-400-001Task 27-94-34-000-001Task 27-94-34-400-001Task 32-31-71-000-001Task 32-31-71-400-001

Fig. A-FBCAAWiring diagram 93VU

Sheet 01

Fig. A-FCCAAHook-up Chart 93VU

Sheet 01

(a) On aircraft, remove and retain:

- the Spoiler and Elevator Computer (SEC3), FIN 1CE3 (Refer to AMM Task27-94-34-000-001)

- the Landing Gear Control and Interface Unit 1 (LGCIU1), FIN 5GA1 (Refer toAMM Task 32-31-71-000-001)

(b) On aircraft, if installed, remove the Zone Controller (ZC):

- FIN 8HK (Refer to AMM Task 21-63-34-000-001)

(c) Put blanking caps on the disconnected connectors.

(d) Disconnect the bonding braid.

(e) Remove the attachment hardware from the shelf.

NOTE: Retain the hardware.

(f) Remove the shelf 93VU and install it on the work bench.

(g) Remove the wire as shown on the wiring diagram Fig. A-FBCAA Sheet 01 and asgiven in the Hook-up Chart line:

- 1 (refer to Fig. A-FCCAA Sheet 01)

(h) Install the wire as shown in the wiring diagram Fig. A-FBCAA Sheet 01 and asshown in the Hook-up Chart line’s:

- 2 (refer to Fig. A-FCCAA Sheet 01)

supplied in

1 Bundle D9000095024895

NOTE: Routes 7M is not identified on the aircraft:




5



(i) Attach the wires with:


(j) Install the shelf 93VU on aircraft.

(k) Do the electrical bonding on the shelf attachment (Refer to AMM Task20-28-00-912-004).

(l) Attach the shelf 93VU and connect the bonding braid with the hardware retained atremoval.

(m) Connect the related connectors.

(n) On the shelf 93VU, if removed, install:

- FIN 1CE3 (Refer to AMM Task 27-94-34-400-001)

- FIN 8HK (Refer to AMM Task 21-63-34-400-001)

- FIN 5GA1 (Refer to AMM Task 32-31-71-400-001)

(4) Subtask 271199-831-004-001 - Modify the wiring in zone 120




From 128 Access Door 822, Door 824Work location Electrical panel 188VU

To 127 Access Door 825Panel 131HC, Panel 131KC, Panel 131LC

Work location Electrical panel 83VU

Manpower Resources



Skills ELECTRICAL



NOTESD9000095024895 1 BundleNSA935401-03 50 TIENSA935401-10 50 TIE



5



ReferencesFig. A-FBDAAModify the wiring in Zone 120

Sheet 01Sheet 02

Fig. A-FCDAAHook-up Chart wiring in Zone 120

Sheet 01

Fig. A-FBFAARouting of the wires in Zone 120

Sheet 01Sheet 02

NOTE:Overview of the routing in Zone 120 is given by Fig. A-FBFAA.

(a) Remove the wires as shown on the wiring diagram Fig. A-FBDAA Sheet 01 and asgiven in the Hook-up Chart lines:

- 1 thru 2 (refer to Fig. A-FCDAA Sheet 01)

(b) Install the wires as shown on the wiring diagram Fig. A-FBDAA Sheet 02 and asgiven in the Hook-up Chart lines:

- 6 thru 11 (refer to Fig. A-FCDAA Sheet 01)

supplied in

1 Bundle D9000095024895

NOTE: Routes 6M, 7M and 8M are not identified on the aircraft:

- routes 6M and 7M is a branch from the route 1M,

- route 8M is a branch from the route 8M.

(c) Attach the wires with:



D. TEST

(1) Subtask 271199-941-002-001 - Job Set-up


120 Access Door 812, Door 822

Manpower Resources

Skills NON SPECIFIC




5



(a) Battery re-connection:

1 For Job Set-up, refer to Removal/Installation of the Batteries (Refer to AMMTask 24-38-51-400-001),

2 Remove the blanking caps from the electrical connectors,

3 Make sure that the electrical connectors are clean and in correct condition,

4 Connect the connector on the battery,

5 Turn the knurled nut a quarter turn.

(b) Remove all warning notices.

(c) Restore the systems and the aircraft to normal operating condition.

(2) Subtask 271199-710-001-001 - Preliminary test

Manpower Resources

Skills NON SPECIFIC


Task 22-96-00-710-001Task 22-97-00-710-001Task 31-50-00-710-001Task 31-50-00-710-004Task 31-60-00-710-001Task 33-13-00-710-001Task 33-14-00-710-001

Elec. Std. Practices Manual (ESPM) 20-52-10

NOTE: If the aircraft is operated in CAT 3 conditions, you must also do the LandCAT 3 Capability Test (Refer to AMM Task 22-97-00-710-001).

(a) On each connectors which was disconnected do the checks as defined by ESPM20-52-10.

NOTE: The Functional test and/or operational test requested by this ESPMprocedure is given hereafter.

(b) Do the Operational Test of the Instrument and Panel Integral Lighting (Refer toAMM Task 33-13-00-710-001).

(c) Do the Operational Test of the Light (Refer to AMM Task 33-14-00-710-001).

(d) Do the Operational Test of the System via MCDU (Refer to AMM Task21-26-00-710-001).

(e) Do the Operational Test of the AFS (Refer to AMM Task 22-96-00-710-001).

(f) Do the Operational Test of the EIS (Refer to AMM Task 31-60-00-710-001).



5



(g) Do the Operational Test of the ECAM Control Panel (Refer to AMM Task31-50-00-710-004).

(h) Ground Scanning of the Central Warning System (Refer to AMM Task31-50-00-710-001).

(3) Subtask 271199-710-002-001 - Test after Removal/Installation of the equipments

Manpower Resources

Skills NON SPECIFIC


Task 24-22-34-400-001Task 24-41-00-740-002Task 27-93-00-710-001Task 27-93-34-400-001Task 27-94-00-710-001Task 32-69-00-740-001Task 35-12-00-710-001

(a) Install the ELAC2 (2CE2) for access (Refer to AMM Task 27-93-34-400-001).

(b) Install the Generator Control Units (1XU1, 1XU2) as per AMM Task24-22-34-400-001

(c) Do the operational test of the ELAC (Refer to AMM Task 27-93-00-710-001).

(d) Do the BITE test of the landing gear, (Refer to AMM Task 32-69-00-740-001).

(e) Do an operational test of the cockpit and cabin temperature control (Refer to AMMTask 21-63-00-710-004).

(f) Do the Operational Test of the SEC (1CE3), (Refer to AMM Task27-94-00-710-001).

(g) Do the Operational Test of the GAPCU with the CFDS, (Refer to AMM Task24-41-00-740-002).

(h) Do the Operational Test of the crew oxygen distribution, (Refer to AMM Task35-12-00-710-001).

(4) Subtask 271199-740-001-001 - Test after disconnection/re-connection of theconnectors

Manpower Resources

Skills NON SPECIFIC




5



(a) Test of the connectors 35VC, 80VC, 219VC, 1837VT, 1846VT and 1892VT:

1 None (Covered by the specific test).

(b) Test after disconnection/re-connection of connectors 13VC, 1227VC, 1249VC and1833VT:

- Do the Operational test of the Emergency Generation System (Refer to AMMTask 24-24-00-710-001).

(c) Test after disconnection/re-connection of connectors 281VC:

1 None (Covered by the test of equipment).

(5) Subtask 271199-760-001-001 - Specific Test of Logics Activating ELAC 1, ELAC 2and SEC1 STBY PWR SPLY

Manpower Resources

Skills NON SPECIFIC


Task 29-10-00-863-003Task 29-23-00-864-001Task 29-24-00-864-001Task 31-60-00-860-001

(a) Job Set-up

1 Aircraft Maintenance Configuration

a Energize the aircraft electrical circuits (Refer to AMM Task24-41-00-861-002).

b On the overhead panel 23VU:

- make sure that the ELAC 1 and SEC 1 pushbutton switches arepushed (the OFF and FAULT legends are off).

c On the overhead panel 24VU:

- make sure that the ELAC 2, SEC 2 and SEC 3 pushbutton switchesare pushed (the OFF and FAULT legends are off).

d On the overhead panel 20VU, on the ADIRS CDU:

- set the 3 OFF/NAV/ATT selector switches to NAV.

e Do the EIS start procedure (Refer to AMM Task 31-60-00-860-001).

f On the center pedestal, on the ECAM control panel push:

- the CLEAR key until all the warnings (if any) stop,



5



- the F/CTL key (on the lower ECAM display unit, the F/CTL pagecomes into view).

g Make sure that the Green and Yellow hydraulic systems aredepressurized (Refer to AMM Task 29-23-00-864-001 and AMM Task29-24-00-864-001).

h Pressurize the Blue hydraulic system (Refer to AMM Task29-10-00-863-003).

2 Get Access

a On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

(6) Subtask 271199-865-001-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC


(a) Make sure that these circuit breakers are closed:

NOTE: For the Circuit Breakers location, refer to the Circuit Breaker DataTable (Refer to AMM 24-50-00, Page Block 001).

PANEL DESIGNATION FIN LOCATION SEENOTES

49VU FLIGHT CONTROLS/ELAC1/NORM/SPLY

15CE1 10 B


15CE1 11 B

49VU FLIGHTCONTROLS/THS/ACTR/MOT2

19CE2 08 B

49VU FLIGHTCONTROLS/THS/ACTR/MOT2

19CE2 09 B

49VU FLIGHT CONTROLS/SEC1/NORM/SPLY

21CE1 07 B

49VU FLIGHT CONTROLS/SEC1/NORM/SPLY

21CE1 08 B

49VU L/G/LGCIU/SYS1/NORM 1GA 11 C49VU L/G/LGCIU/SYS1/NORM 1GA 09 C105VU FLIGHT

CONTROLS/ELAC2/STBYSPLY

16CE2 02 A

105VU FLT CTL/ELAC1/STBY SPLY 16CE1 01 A105VU FLT CTL/SEC1/STBY SPLY 22CE 01 B121VU HYD/LGCIU/SYS1/GRND

SPLY52GA 34 Q



5




121VU HYD/LGCIU/SYS1/GRNDSPLY

52GA 23 Q

121VU FLIGHTCONTROLS/SEC3/SPLY

21CE3 19 Q

121VU FLIGHTCONTROLS/SEC2/SPLY

21CE2 18 Q

121VU FLIGHT CONTROLS/THSACTR/MOT3

19CE3 17 Q

121VU FLIGHT CONTROLS/THSACTR/MOT1

19CE1 16 Q


15CE2 20 R

(b) Open, safety and tag these circuit breakers:

NOTE: For the Circuit Breakers location, refer to the Circuit Breaker DataTable (Refer to AMM 24-50-00, Page Block 001).


49VU ANTI ICE/PROBES/AOA/1 4DA1 04 D49VU ANTI ICE/PROBES/PHC/1 2DA1 03 D49VU ANTI ICE/PROBES/PITOT/1 3DA1 02 D122VU ANTI ICE/WINDOWS/R 4DG2 14 W122VU ANTI ICE/WHC/2 5DG2 13 W122VU ANTI ICE/WINDOWS/L 4DG1 14 X122VU ANTI ICE/WHC/1 5DG1 13 X122VU ANTI ICE/PROBES/PHC/3 2DA3 16 Y122VU ANTI ICE/PROBES/2/TAT 1DA2 15 Y122VU ANTI ICE/PROBES/2/PITOT 3DA2 14 Y122VU ANTI ICE/PROBES/2/AOA 4DA2 13 Y122VU ANTI ICE/PROBES/2/PHC 2DA2 12 Y122VU ANTI ICE/PROBES/2/STATIC 5DA2 11 Y122VU ANTI ICE/PROBES/3/PITOT 3DA3 16 Z122VU ANTI ICE/PROBES/3/AOA 4DA3 15 Z122VU ANTI ICE/PROBES/3/STATIC 5DA3 14 Z122VU ANTI ICE/PROBES/1/STATIC 5DA1 13 Z122VU ANTI ICE/PROBES/1/TAT 1DA1 12 Z

(7) Subtask 271199-710-003-001 - Operational test of the Logics that activate theELAC 1 and 2 and SEC 1 STBY PWR SPLY

Manpower Resources

Skills NON SPECIFIC


NOTE: For the Circuit Breaker location, refer to the Circuit Breaker Data Table(Refer to AMM 24-50-00, Page Block 001).



5



(a) Procedure

1 Operational Test of the Logics that activate the ELAC 1 and 2 and the SEC 1STBY PWR SPLY:

NOTE: During the test, ignore the MASTER CAUTION light and singlechime.

ACTION RESULT1. Open the Circuit Breakers (CB)15CE1 and 21CE1.

On the FLT CTL section of the overhead panel 23VU:

- the FAULT legend of the ELAC 1 and SEC 1 pushbuttonswitches are off.

2. On the overhead panel 50VU:

- release the BLUE PUMP OVRDpushbutton switch.


- the ON legend of the BLUE PUMP OVRD pushbutton switchgoes off.

On the overhead panel 23VU:

- the FAULT legends of the ELAC 1 and SEC 1 pushbuttonswitches are off.

After approximately 30 seconds:

- on the overhead panel 23VU, the FAULT legends of the ELAC1 and SEC 1 come on,

- on the upper ECAM display unit, the ELAC 1 FAULT and SEC1 FAULT warnings comes into view,

- on the lower ECAM display unit, the ELAC 1 and SEC 1legends change to amber.


- push the BLUE PUMP OVRDpushbutton switch.


- the ON legend of the BLUE PUMP OVRD pushbutton switchcomes on.

The above warnings are still shown.

4. Close the CB 15CE1 and21CE1.

On the FLT CTL section of the overhead panel 23VU:

- the FAULT legends of the ELAC 1 and SEC 1 pusbuttonswitches go off.

On the upper ECAM display unit:

- the ELAC 1 FAULT and SEC 1 FAULT warnings go out ofview.

On the lower ECAM display unit:

- the ELAC 1 and SEC 1 legends change to green.



5



ACTION RESULT5. Open the CB 52GA, 1GA and15CE2.

NOTE: Ignore the warningsrelated to the othersystems.


- the FAULT legend of the ELAC 2 pushbutton switch comes on.On the upper ECAM display unit:

- the ELAC 2 FAULT warning comes into view.On the lower ECAM display unit:

- the ELAC 2 legend changes to amber.

6. Open the CB 19CE1. On the overhead panel 24VU:

- the FAULT legend of the ELAC 2 pushbutton switch goes off.On the upper ECAM display unit:

- the ELAC 2 FAULT warning goes out of view.On the lower ECAM display unit:

- the ELAC 2 legend changes to green.After approximately 30 seconds:

- on the lower ECAM display unit, the ELAC 2 legend changes toamber again,

- on the upper ECAM display unit, the ELAC 2 FAULT warningcomes into view,

- on the overhead panel 24VU, the FAULT legend of the ELAC 2pushbutton switch is off.


- push the YELLOW/ELEC PUMPpushbutton switch.


- the ON legend of the YELLOW/ELEC PUMP pushbutton switchcomes on.


- release the BLUE PUMP OVRDpushbutton switch.


- the ON legend of the BLUE PUMP OVRD pushbutton switchgoes off.


- the FAULT legend of the ELAC 2 pushbutton switch is off.On the upper ECAM display unit:

- the ELAC 2 FAULT warning goes out of view.On the lower ECAM display unit:

- the ELAC 2 legend changes to green.



5



ACTION RESULT9. On the overhead panel 50VU:

- push the BLUE PUMP OVRDpushbutton switch.


- the ON legend of the BLUE PUMP OVRD pushbutton switchcomes on.


- the ELAC 2 FAULT warning comes into view.On the lower ECAM display unit:

- the ELAC 2 legend changes to amber.On the overhead panel 24VU:

- the FAULT legend of the ELAC 2 pushbutton switch is off.


- release the YELLOW/ELECPUMP pushbutton switch.


- the ON legend of the YELLOW/ELEC PUMP pushbutton switchgoes off.

11. Close the CB 1GA, 52GA. On the lower ECAM display unit:

- the ELAC 2 legend changes to green,On the upper ECAM display unit:

- the ELAC 2 FAULT warning goes out of view.

12. Open the CB 1GA and 52GA. On the lower ECAM display unit:

- the ELAC 2 legend is green.On the upper ECAM display unit:

- there is no ELAC 2 FAULT warning.On the overhead panel 24VU:

- the FAULT legend on the ELAC 2 pushbutton switch is off.

13. Close the circuit breakers 1GAand 52GA.


- the ELAC 2 legend is green.On the upper ECAM display unit:

- there is no ELAC 2 FAULT warning.On the overhead panel 24VU:

- the FAULT legend on the ELAC 2 pushbutton switch is off.

14. Go to next paragraph.

(8) Subtask 271199-710-004-001 - Operational Test of the Sidestick Priority Function

Manpower Resources

Skills NON SPECIFIC




5




NOTE: During the test, ignore the MASTER CAUT light and single chime.


- release the ELAC 1 pushbuttonswitch.


- the OFF legend of the ELAC 1 pushbutton switch comes on.On the lower ECAM display unit:

- the ELAC 1 legend changes to amber

- the ELAC 2 legend stays green.


- release the SEC 1 pushbuttonswitch.


- the OFF legend of the SEC 1 pushbutton switch comes on.On the overhead panel 24VU:

- the FAULT legend of the ELAC 2 pushbutton switch comes on.On the lower ECAM display unit:

- the SEC 1 legend changes to amber

- the ELAC 2 legend changes to amber.On the upper ECAM display unit:

- the ELAC 2 FAULT warning comes into view.


- push the ELAC 1 pushbuttonswitch.


- the OFF legend of the ELAC 1 pushbutton switch goes off.On the overhead panel 24VU:

- the FAULT legend of the ELAC 2 pushbutton switch goes off.On the lower ECAM display unit:

- the ELAC 1 legend changes to green

- the ELAC 2 legend changes to greenOn the upper ECAM display unit:

- the ELAC 2 FAULT warning goes out of view.


- push the SEC 1 pushbuttonswitch.


- the OFF legend of the SEC 1 pushbutton switch goes offOn the lower ECAM display unit:

- the SEC 1 legend changes to green.



5



ACTION RESULT5. On the CAPT and F/O side, onthe side sticks:

- move at the same time the twosticks around their axis.

You can heard an aural announcement: DUAL INPUTOn the glareshield panels 130VU and 131VU, on the SIDESTICK PRIORITY CAPT and the SIDE STICK PRIORITY F/Oannunciators:

- the green CAPT and F/O legends flash at the same time.

6. At the same time:

- on the CAPT side, push and holdfor less than 30 seconds thetakeover and priority pushbuttonswitch

- on the F/O side, move the sidestick to the left, then release it tothe neutral position.

You can heard an aural warning.On the F/O side, on the glareshield panel 130VU:

- the red arrow of the SIDE STICK PRIORITY F/O annunciatorcomes on.

On the CAPT side, on the glareshield panel 131VU:

- the green CAPT legend comes on.

7. On the CAPT side:

- release the takeover and prioritypushbutton switch.

8. At the same time:

- on the F/O side, push and holdfor less than 30 seconds thetakeover and priority pushbuttonswitch

- on the CAPT side, move the sidestick to the left, then release it tothe neutral position.

You can heard an aural warning.On the CAPT side, on the glareshield panel 131VU:

- the red arrow of the SIDE STICK PRIORITY CAPT annunciatorcomes on.

On the F/O side, on the glareshield panel 130VU:

- the green F/O legend comes on.

9. On the F/O side:

- release the takeover and prioritypushbutton switch.


- move the side stick to the leftuntil it touches the stop.


- the L/AIL index moves to the upper stop,

- the R/AIL index moves to the lower stop,

- the spoiler surfaces are retracted.



5



ACTION RESULT11. On the CAPT side:

- move quickly the side stick fromthe left to the right in less than 2seconds,

- move the side stick to the neutralposition.


- the L/AIL index moves to the lower stop (the total travel time isapproximately 5 seconds),

- the R/AIL index moves to the upper stop (the total travel time isapproximately 5 seconds),


- the R/AIL and L/AIL indexes go back to the neutral position.

12. Close the CB 15CE2 and19CE1


- the FAULT legend of the ELAC 2 pushbutton switch is off.On the lower ECAM display unit:

- the ELAC 2 legend is green.

13. Go to next paragraph"Operational Test of the Ability ofthe ELAC 1 and SEC 1 and 2 toachieve Pitch Control".

(9) Subtask 271199-710-005-001 - Operational Test of the Ability of the ELAC 1 andSEC1 and 2 to achieve Pitch Control

Manpower Resources

Skills NON SPECIFIC


Task 29-10-00-863-003Task 29-10-00-864-003Task 29-23-00-863-001Task 29-23-00-864-001Task 29-24-00-863-001Task 29-24-00-864-001


NOTE: During the test, ignore the MASTER CAUTION light and single chime.

ACTION RESULT1. Pressurize the Green and Yellowhydraulic systems (Refer to AMMTask 29-23-00-863-001 and AMMTask 29-24-00-863-001)

On the lower ECAM display unit, the G and Y indicationsbecome green.

2. Depressurize the Blue hydraulicsystem (Refer to AMM Task29-10-00-864-003).

On the lower ECAM display unit, the B indication becomesamber.

3. Wait for 5 seconds.



5



ACTION RESULT4. Pressurize the Blue hydraulicsystem (Refer to AMM Task29-10-00-863-003).

On the lower ECAM display unit, the B indication becomesgreen.




- the OFF legend of the SEC 1 pushbutton switch comes on.


- release the ELAC 2 and SEC 2pushbutton switches.


- the OFF legends of the ELAC 2 and SEC 2 pushbuttonswitches come on.

7. On the CAPT or F/O side:

- pull the side stick rearward untilit touches the stop, and move itback to the neutral position.


- the indexes of the L/ELEV and R/ELEV indicators move upand go back to the neutral position.




- the OFF legend of the SEC 1 pushbutton switch goes off.


- push the ELAC 2 and SEC 2pushbutton switches.


- the OFF legends of the ELAC 2 and SEC 2 pushbuttonswitches go off.

10. Depressurize the Green andYellow hydraulic systems (Refer toAMM Task 29-23-00-864-001 andAMM Task 29-24-00-864-001).

On the lower ECAM display unit, the G and Y indicationsbecome amber.

11. Wait for 5 seconds.12. Pressurize the Green andYellow hydraulic systems (Refer toAMM Task 29-23-00-863-001 andAMM Task 29-24-00-863-001)

On the lower ECAM display unit, the G and Y indicationsbecome green.








- the OFF legend of the ELAC 2 pushbutton switch comes on.



5



ACTION RESULT15. On the CAPT side:

- give the orders below one afterthe other and keep the side stickin each position for 3 seconds:

. full nose up

. full nose down

. full right turn

. full left turn

- move the side stick back to theneutral position.

On the lower ECAM display unit, on the F/CTL page:

- the indexes of the elevators and spoilers 2 and 5 move inrelation to the side stick orders.

16. On the F/O side:


. full nose up

. full nose down

. full right turn

. full left turn




17. Set the pitch-trim control wheelto the 10 UP position.


- release and push again the SEC2 pushbutton switch.

After approximately five seconds, the pitch-trim control wheelgoes back automatically to the 0 position.On the lower ECAM display unit, on the F/CTL page:

- the PITCH TRIM indicator shows 0 DEG plus or minus 0.3.

19. Set the pitch-trim control wheelto the 3 DN position.






- push the ELAC 1 and SEC 1pushbutton switches.


- the OFF legends of the ELAC 1 and SEC 1 pushbuttonswitches go off.



5




- push the ELAC 2 pushbuttonswitch.


- the OFF legend of the ELAC 2 pushbutton switch goes off.

23. Depressurize the Blue hydraulicsystem (Refer to AMM Task29-10-00-864-003).

On the lower ECAM display unit, the B indication becomesamber.

24. Wait for 5 seconds.25. Pressurize the Blue hydraulicsystem (Refer to AMM Task29-10-00-863-003).

On the lower ECAM display unit, the B indication becomesgreen.




- the OFF legend of the ELAC 1 pushbutton switch comes on.







. full nose up

. full nose down

. full right turn

. full left turn



- the indexes of the elevators and spoilers 2, 3 and 4 move inrelation to the side stick orders.



5



ACTION RESULT29. On the F/O side:


. full nose up

. full nose down

. full right turn

. full left turn




30. Set the pitch-trim control wheelto the 10 UP position.





32. Set the pitch-trim control wheelto the 3 DN position.





34. Open the CB 15CE1 and15CE2.


- the F/CTL ELAC 1 FAULT and F/CTL ELAC 2 FAULTmessages come into view.


- give the orders below one afterthe other:

. full nose up

. full nose down

. full right turn

. full left turn






5






- the OFF legend of the SEC 1 pushbutton switch comes on.




- the OFF legend of the SEC 2 pushbutton switch goes off.


- give the orders below one afterthe other:

. full nose up

. full nose down

. full right turn

. full left turn




39. Close the CB 15CE1 and15CE2.


- the F/CTL ELAC 1 FAULT and F/CTL ELAC 2 FAULTmessages go out of view.

(10) Subtask 271199-865-003-001 - C/B Opening/Closing

Manpower Resources

Skills NON SPECIFIC



(a) Remove the safety clips and tags and close these circuit breakers:


122VU ANTI ICE/PROBES/1/TAT 1DA1 12 Z122VU ANTI ICE/PROBES/2/TAT 1DA2 15 Y49VU ANTI ICE/PROBES/PHC/1 2DA1 03 D122VU ANTI ICE/PROBES/2/PHC 2DA2 12 Y122VU ANTI ICE/PROBES/PHC/3 2DA3 16 Y49VU ANTI ICE/PROBES/PITOT/1 3DA1 02 D122VU ANTI ICE/PROBES/2/PITOT 3DA2 14 Y122VU ANTI ICE/PROBES/3/PITOT 3DA3 16 Z



5




122VU ANTI ICE/PROBES/2/AOA 4DA2 13 Y122VU ANTI ICE/PROBES/3/AOA 4DA3 15 Z122VU ANTI ICE/WINDOWS/L 4DG1 14 X122VU ANTI ICE/WINDOWS/R 4DG2 14 W122VU ANTI ICE/PROBES/2/STATIC 5DA2 11 Y122VU ANTI ICE/PROBES/3/STATIC 5DA3 14 Z122VU ANTI ICE/WHC/1 5DG1 13 X122VU ANTI ICE/WHC/2 5DG2 13 W49VU ANTI ICE/PROBES/AOA/1 4DA1 04 D122VU ANTI ICE/PROBES/1/STATIC 5DA1 13 Z

(11) Subtask 271199-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC


Task 24-41-00-862-002Task 29-10-00-864-003Task 29-23-00-864-001Task 29-24-00-864-001Task 31-60-00-860-002

(a) Put the aircraft back to the initial configuration.

1 Depressurize the aircraft hydraulic systems (Refer to AMM Task29-23-00-864-001, AMM Task 29-24-00-864-001 and AMM Task29-10-00-864-003).

2 On the overhead panel 23VU:

- push the ELAC 1 and SEC 1 pushbutton switches (the OFF legends gooff).

3 On the overhead panel 24VU:

- push the ELAC 2 pushbutton switch (the OFF legend goes off).

4 On the overhead panel 20VU, on the ADIRS CDU:

- set the 3 OFF/NAV/ATT selector switches to OFF.

5 Do the EIS stop procedure (Refer to AMM Task 31-60-00-860-002).

6 De-energize the aircraft electrical circuits (Refer to AMM Task24-41-00-862-002).

7 Remove the warning notices.



5



E. CLOSE-UP

(1) Subtask 271199-410-002-001 - Install Items removed for access.


121 Access Door 811Work location from Frame 8 to Frame 9


Manpower Resources

Skills AIRFRAME


Task 25-54-11-400-001Task 25-54-12-400-002Task 35-11-41-400-001

Fig. A-FBHAADrain panel above 90VU Left side

Sheet 01

(a) Install the computers GCU1 and GCU2 (1XU1, 1XU2) as per (Refer to AMM Task24-22-34-400-001)

(b) Install the Drain panel retained at removal above the 91VU:

1 Install

1 Cover assy Left D92412461 Item (1)

3 Latch ASNA2584-1201 Item (2)

1 Screw NAS1096-3-8 Item (3)

1 Washer ASNA2397-10L Item (4)

1 Nut NSA5067-3-1 Item (5)

(c) Install the Crew Oxygen-Storage Cylinder (5750HM) as per AMM Task35-11-41-400-001.

(d) Install the partition panel 131DW, 131CW and 132EW retained at removal (Refer toAMM Task 25-54-11-400-001).

(e) Install the ceiling panels 131LC, 131KC and 131HC retained at removal (Refer toAMM Task 25-54-12-400-002).



5



(2) Subtask 271199-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC


52-30-00, Page Block 201Task 52-41-00-410-002

(a) Make sure that the work areas are clean and clear of tools and other items ofequipment.

(b) On the battery power center 105VU, install the protective cover and tighten the twoscrews.

(c) Close the FWD cargo compartment door 825 (Refer to AMM 52-30-00, Page Block201).

(d) Close the FWD avionics compartment lateral doors 812, 822 and 824 (Refer toAMM Task 52-41-00-410-002).

(e) Close the FWD avionics compartment door 811 (Refer to AMM Task52-41-00-410-002).

(f) Close the passenger/crew doors (Refer to AMM Task 52-10-00-410-001).

(g) Remove the access platform.



5



**CONF ALL

N_SB_271199_5_BGAA_01_00

FR23FR21

FR3FR5

FR15

FR13

FR14FR12

824ACCESS TO 188 VU

ACCESS TO AVIONICS COMPARTMENT

ACCESS TO 106VU, 1227VC,1249VC AND OXYGEN CREWBOTTLE 5070HM

825 ACCESS TO 80VU, 1833VT, 1836VT,1846VT, 13VC, 35VC AND 80VC

811ACCESS TO 90VU,219VC AND 281VC

822

812

Figure A-FBGAA - Sheet 01Access to Work area



5



**CONF ALL

80VU

90VU

80VC

35VC

219VC

188VU

B

C D

A

N_SB_271199_5_BEAA_01_01

188VU

80VU

106VU

90VU

FR1

FR20

FR16

FR9

FR24A

A

BF

G

13VC

281VC

Figure A-FBEAA - Sheet 01Work area location



5



**CONF ALL

PLATE RELAY188VU

LOCATION:

A08

C08

D02

188VU

64CE

46CE

44CE

188VU

188VU

C

D

E

188VU CLOSED

OPENED188VU

N_SB_271199_5_BEAA_02_01

E

1804VD

1892VT




5



**CONF ALL

N_SB_271199_5_BEAA_03_01

80VU

106VU

1249VC

1833VT

1837VT

1846VT

G

F




5



**CONF ALL

RELAY INSTALLATION PRINCIPLE44CE 46CE 64CEFOR , ,

LOCATION OF RELAYS

N_SB_271199_5_BEAA_04_00VIEW OF THE 188VU OPENED

DC

A

1

1

1

LOCATION A08

LOCATION C08

LOCATION D02

1

2

1

3

H

H




5



**CONF ALL

FR9

FR1

N_SB_271199_5_BHAA_01_00

A

FR24A

90VU

B

A(3)(4)(5)

(1)

(2)

(2)B

C

(2)

C

Figure A-FBHAA - Sheet 01Drain panel above 90VU Left side



5



**CONF ALL

N_SB_271199_5_BFAA_01_00

93VU

1XU1

1XU21XS 4T

2M2S

1M

1E1P

1M2M

1031VCA1033VCA1R

3E

1M1S

Z120

A

FR8

FR9

219VC

A

B

TO 80VU

Figure A-FBFAA - Sheet 01Routing of the wires in Zone 120



5



**CONF ALL

6P−6G6M

2M2P

1M1P

4G

1S1C

1M−7M

1S 2S2M

1R

1G1P

1R

1S1M1231VN

6P−6G6M

1XE

2M

22LS5XH1R

1S

1M

1R4T

6G−6P−6E6S7S

1R

1249VC

N_SB_271199_5_BFAA_02_00

FR15

FR14

FR12

FR13

FR11

FR10

FR9

FR8

FR7FR6

FR5

1M−7M

B

C

106VU

C

FROM 93VU

TO 80VU

TO 1227VC

1227VC

Figure A-FBFAA - Sheet 02Routing of the wires in Zone 120



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**CONF ALL

Figure A-FBAAA - Sheet 01Wiring diagram 188VU



5



**CONF ALL

Figure A-FBAAA - Sheet 02Wiring diagram 188VU



5



**CONF ALL

Figure A-FBBAA - Sheet 01Wiring diagram 83VU/84VU



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**CONF ALL

Figure A-FBBAA - Sheet 02Wiring diagram 83VU/84VU



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**CONF ALL

Figure A-FBCAA - Sheet 01Wiring diagram 93VU



5



**CONF ALL

Figure A-FBDAA - Sheet 01Modify the wiring in Zone 120



5



**CONF ALL

Figure A-FBDAA - Sheet 02Modify the wiring in Zone 120



5



**CONF ALL

END1 LEAD END2

InstructionsZone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or


L

i

n

e

1 188VU 50CE−A A2 2792S1565 8M CF22 188VU 1892VT 1M D

2 188VU 50CE−A A3 2792S1566 8M CF22 188VU 982VG GND D

3 188VU 50CE−A X1 2792S1567 8M CF22 188VU 1892VT 3V D

4 188VU 50CE−A X2 2792S1576 8M CF22 188VU 982VG GND D

5 188VU 982VG / 2792−1582 8M CF24 188VU 40CE2−A A3 D

6 188VU 1892VT 1P 2792S1765 8M CF22 188VU 53CE X2 D

7 188VU 53CE X1 2792S1766 8M CF22 188VU 48CE−A A3 D

8 83VU 1837VT 20M 2792S1510 8M CF22 188VU 1892VT 3X D

9

10

11

12 188VU 1892VT 1B EN3155−016M2222 2792S1345 8M CF22 2100 84 188VU 44CE−A X1 EN3155−017F1620 (a) A

13 188VU 1892VT 1D EN3155−016M2222 2792S1346 8M CF22 1470 58 188VU 1804VD−A 1 EN3155−003F2222 (a) A

14 188VU 1892VT 3V EN3155−016M2222 2792S1373 8M CF22 2100 84 188VU 46CE−A X1 EN3155−017F1620 (a) A

15 188VU 1892VT 1A EN3155−016M2222 2792S1510 8M CF22 1200 48 188VU 1892VT 3X EN3155−016M2222 (a) A

16 188VU 1892VT 1J EN3155−016M2222 2792S1564 8M CF24 2100 84 188VU 44CE−A X2 EN3155−017F1620 (a) A

17 188VU 1892VT 1M EN3155−016M2222 2792S1565 8M CF24 2100 84 188VU 50CE−A A2 EN3155−017F1620 (a) A

18 188VU 1892VT 1K EN3155−016M2222 2792S1570 8M CF24 2100 84 188VU 46CE−A X2 EN3155−017F1620 (a) A

19 188VU 1892VT 3M EN3155−016M2222 2792S1576 8M CF22 2100 84 188VU 50CE−A X1 EN3155−017F1620 (a) A

20 188VU 1892VT 1H EN3155−016M2222 2792S1766 8M CF24 3000 120 188VU 53CE−A X2 EN3155−017F1620 (a) A

21 188VU 1892VT 1E EN3155−016M2222 2792S1767 8M CF22 2100 84 188VU 44CE−A A2 EN3155−017F1620 (a) A

22 188VU 1892VT 2S EN3155−016M2222 2792S1797 7M CF22 2520 100 188VU 64CE−A A1 EN3155−017F1620 (a) A

23 188VU 1892VT 2J EN3155−016M2222 2792S1798 7M CF22 2520 100 188VU 64CE−A X1 EN3155−017F1620 (a) A

24 188VU 1892VT 1N EN3155−016M2222 2792S1805 8M CF24 2520 100 188VU 64CE−A B1 EN3155−017F1620 (a) A

25 188VU 1892VT 2B EN3155−016M2222 2792S1806 7M CF22 1470 58 188VU 1804VD−A 39 EN3155−003F2222 (a) A

(a) = BUNDLE D9000095024895 S = SENSITIVE WIRE

A = ADDED WIRE

D = DELETED WIRE

Figure A-FCAAA - Sheet 01Hook-up Chart 188VU



5



**CONF ALL

END1 LEAD END2

InstructionsZone or


Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or


L

i

n

e

1 188VU 50CE−A B2 EN3155−017F1620 2792−1581 8M CF24 1200 48 188VU 46CE−A A3 EN3155−017F1620 (a) A

2 188VU 50CE−A A3 EN3155−017F1620 2792S1566 8M CF24 1470 58 188VU 982VG GND EN3155−015F2018 (a) A

3 188VU 50CE−A X2 EN3155−017F1620 2792S1567 8M CF24 1470 58 188VU 982VG GND EN3155−015F2018 (a) A

4 188VU 50CE−A B3 EN3155−017F1620 2792S1580 8M CF24 1470 58 188VU 980VG GND EN3155−015F2018 (a) A

5 188VU 64CE−A B2 EN3155−017F1620 2792−1794 8M CF24 1200 48 188VU 986VG GND EN3155−015F2018 (a) A

6 188VU 64CE−A X2 EN3155−017F1620 2792S1795 7M CF22 1820 72 188VU 976VG GND EN3155−015F2018 (a) A

7 188VU 64CE−A A2 EN3155−017F1620 2792S1803 7M CF22 2100 84 188VU 1804VD−A 4 EN3155−003F2222 (a) A

8 188VU 46CE−A A2 EN3155−017F1620 2792−1582 8M CF24 2000 80 188VU 40CE2−A A3 EN3155−017F1620 (a) A

9 188VU 46CE−A A1 EN3155−017F1620 2792S0188 8M CF24 1470 58 188VU 980VG GND EN3155−015F2018 (a) A

10 188VU 1804VD−A 16 EN3155−003F2222 2792S1341 8M CF22 1820 72 188VU 982VG GND EN3155−015F2018 (a) A

11 188VU 1804VD−A 19 EN3155−003F2222 2792S1801 7M CF22 2100 84 188VU 48CE−A A3 EN3155−017F1620 (a) A

12 188VU 44CE−A A1 EN3155−017F1620 2792−1765 8M CF22 2000 80 188VU 53CE−A X1 EN3155−017F1620 (a) A

13 84VU 1846VT 18P EN3155−016M2222 2792S1568 8M CF22 2940 117 188VU 1892VT 3F EN3155−016M2222 (a) A

14 84VU 1846VT 18V EN3155−016M2222 2792S1573 8M CF22 2940 117 188VU 1892VT 1C EN3155−016M2222 (a) A

15 84VU 1846VT 8B EN3155−016M2222 2792S1799 7M CF22 2940 117 188VU 1804VD−A 40 EN3155−003F2222 (a) A

16

17

18

19

20

21

22

23

24

25

(a) = BUNDLE D9000095024895

A = ADDED WIRE

S = SENSITIVE WIRE

Figure A-FCAAA - Sheet 02Hook-up Chart 188VU



5



**CONF ALL

END1 LEAD END2

InstructionsZone or


Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or


L

i

n

e

1 84VU 1846VT 18N 2792S1574 8M CF22 84VU 2CE2−AB 7H D

2 84VU 1846VT 18M 2792S1575 8M CF22 84VU 2CE2−AD 14D D

3 83VU 1837VT 20X 2792S1573 8M CF22 84VU 1846VT 18V D

4

5

6

7 84VU 1846VT 18N EN3155−016M2222 2792−1574 8M CF22 1200 48 84VU 2CE2−AB 7H E0170FA2200 (a) A

8 84VU 1846VT 18M EN3155−016M2222 2792−1575 8M CF22 1200 48 84VU 2CE2−AD 14D E0170FA2200 (a) A

9 83VU 1833VT 3R EN3155−016M2222 2792−1910 7M CF24 950 38 83VU 1837VT 10S EN3155−016M2222 (a) A

10 83VU 1837VT 20M EN3155−016M2222 2792−1569 8M CF22 4200 168 84VU 1846VT 18G EN3155−016M2222 (a) A

11 83VU 1837VT 10J EN3155−016M2222 2792−1796 7M CF22 4200 168 84VU 1846VT 8A EN3155−016M2222 (a) A

12

13

14

15

16

17

18

19

20

21

22

23

24

25


A = ADDED WIRE

D = DELETED WIRE

Figure A-FCBAA - Sheet 01Hook-up Chart 83VU/84VU



5



**CONF ALL

END1 LEAD END2

InstructionsZone or


Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or


L

i

n

e

1 93VU 5GA1−AB 11D 2424−0487 1M CF22 93VU 281VC 43 D

2 93VU 5GA1−AB 11D E0170FA2200 2792S1800 7M CF22 2500 100 93VU 219VC 78 EN3155−008M2222 (a) A

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25


A = ADDED WIRE

D = DELETED WIRE

Figure A-FCCAA - Sheet 01Hook-up Chart 93VU



5



**CONF ALL

END1 LEAD END2

InstructionsZone or


Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or


L

i

n

e

1 93VU 281VC−A 43 2424−0481 6M CF22 106VU 1249VC−A <F D

2 188VU 1892VT 1L 2792S1572 8M CF22 128 80VC 8 D

3

4

5

6 83VU 1833VT 3S EN3155−016M2222 2424−0475 8M CF24 3000 120 127 13VC 77 EN3155−008M2222 (a) A

7 83VU 1837VT 10B EN3155−016M2222 2792−1804 7M CF22 2100 84 127 35VC 75 EN3155−008M2222 (a) A

8 93VU 219VC−A 78 EN3155−003F2222 2792−1802 7M CF22 12300 492 127 35VC−A 75 EN3155−003F2222 (a) A

9 106VU 1249VC−A <F EN3155−019F2018 2424−0481 6M CF22 3000 120 125 1227VC 46 EN3155−015F2018 (a) A

10 188VU 1892VT 1L EN3155−016M2222 2792S1572 8M CF24 4200 168 128 80VC 8 EN3155−014M2018 (a) A

11 125 1227VC−A 46 EN3155−014M2018 2424−0478 1M CF24 6000 240 127 13VC−A 77 EN3155−003F2222 (a) A

12

13

14

15

16

17

18

19

20

21

22

23

24

25


A = ADDED WIRE

D = DELETED WIRE

Figure A-FCDAA - Sheet 01Hook-up Chart wiring in Zone 120



5



Appendix 01

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A320−27−1199

SB ELAPSED TIME(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURSSB ELAPSED TIME

56.037.0

STEPS

2.00 1.00

5 10 15 20 25 30 35 400

MODIFICATION WIRING 24.00 24.00



TEST 4.00 4.00

CLOSE−UP 2.00 1.00

MH

ET/S:PER

MANHOURS

ELAPSED TIME PER STEPNUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.OPERATORS MAY DETERMINE THAT ANOTHER WAYTO DO THE WORK IS MORE SUITABLE FOR THEM.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINSARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

PER

2

1

1

1

1

2

MODIFICATION ZONE 120 12.00 12.001

::

N_SB_271199_5_AAAA_01_00

80VU AND 188VU

83VU AND 84VU

93VU

Figure A-FAAAA - Sheet 01Gantt Chart



5


@A318/A319/A320/A321SERVICE BULLETINREPORTING SHEET



Please complete the appropriate item (A or B):A - SB WILL BE embodied YES/NO (if NO please comment)If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) ofembodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:Name/Title:Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior tonext normal revision or prior to SB embodiment, please indicate required service(s):Either: Modification Operational Impact (MOI), if available YES/NOOr : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operationaldocumentation if this sheet is returned to Airbus and signed by a duly authorised representative. Withthe next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automaticallyinclude them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation ServicesFAX: (+33) 5 61 93 28 06e-mail: [email protected] via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.



5



QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported datathat you provide us will be used to analyse areas of difficulties and to take corrective action to furtherimprove the quality of our Service Bulletins.We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give ashort description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins ManagementFAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.



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SB_27_1199_02 service buletin

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Transcript of SB_27_1199_02 service buletin