### A340 AIRWORTHINESS LIMITATIONS SECTION

REVISION: 00 

# ALS Part 5

-

Fuel

Airworthiness Limitations

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.

This document and all information contained herein is the sole property of AIRBUS SAS. No

intellectual property rights are granted by the delivery of this document or the disclosure of its

content. This document shall not be reproduced or disclosed to a third party (except for the

purposes of performing the tasks described hereunder and provided that any recipient of such

document shall comply with the conditions herein) without the express written consent of

AIRBUS SAS. This document and its content shall not be used for any purpose other than that

for which it is supplied.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

ISSUE: NOV 16/11 ALS PART 5 PAGE: 1-LEP

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

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### A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

TABLE OF CONTENTS

SUBJECT PART

ISSUE: NOV 16/11 ALS PART 5 PAGE: 1-TOC

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### RECORDS OF REVISIONS ROR

INTRODUCTION 5-0

ILLUSTRATIONS 5-1

CHANGES TO TYPE DESIGN 5-2

LIFE LIMITATIONS 5-3

REPETITIVE MAINTENANCE/INSPECTION TASKS 5-4

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS 5-5

### A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

RECORD OF REVISIONS

ISSUE: NOV 16/11 ALS PART 5 PAGE: 1-ROR

EASA APPROVED

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### The European Aviation Safety Agency (EASA) Certification Directorate approves the ALS

Part 5. Variations must also be approved.

REVISION

NUMBER SUB-PARTS APPROVED BY

EASA EASA AD INSERTION IN

MAINT. PROG.

00 ROR

5-2

5-3

5-4

5-5 NOV 16/11

Note: The A340 ALS Part 5 R00 is covered by the Certification Document 00F050AM095/C01

issue 01.

Revision 00 is approved by EASA under reference 10037273.

REVISION 00 COMPLIANCE TIME:

1. Except as stated in paragraph 3 of this Record Of Revisions (ROR), it is mandatory to

comply with instructions and airworthiness limitations defined in the A340 ALS Part 5

revision 00 from 16 NOV 2012

2. From 16 NOV 2011 to 15 NOV 2012 except as stated in paragraph 3 of this Record Of

Revisions (ROR) it is mandatory to comply with the instructions and airworthiness limitations

defined, either:

- In the A340 Fuel Airworthiness Limitations Document ref. 95A.1933/05 at issue 3 and in

the A340 ALS Variation to FAL doc issue 03 ref.0FVLG110019/C0S issue 01

Or

- In the A340 ALS Part 5 at Revision 00.

3. It is mandatory to comply with the AD listed in the sub-part 5.2. When AD have been

cancelled or superseded, it is mandatory to comply with instructions provided by the subpart 5.2.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-0 PAGE: 1

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### Sub-part 5-0 INTRODUCTION

1. GENERAL

Compliance with the requirements contained in this document is mandatory. No person may

operate an aircraft to which an Airworthiness Limitations Section (ALS) applies except in

accordance with the requirements of that ALS, unless otherwise agreed with the Authority of

the State of aircraft registry.

A. ALS Part 5 Scope

This document contains the Fuel Airworthiness Limitations that arise from compliance

with JAA’s Interim Policy on Fuel Tank Safety (INT/POL/25/12), FAA’s Special Federal

Aviation Regulation (SFAR) 88 and FAA’s 14 CFR 26.33. They have been derived in

accordance with JAA’s draft Temporary Guidance Leaflet (TGL) 47 and FAA’s Advisory

Circular (AC) 25.981-1B. The nomenclature and means of promulgation follow the

FAA’s memorandum ref PS-ANM100-2004-10029 ‘Policy Statement on Process for

Developing SFAR 88-related Instructions for Maintenance and Inspection of Fuel Tank

Systems’. This latter document has been jointly developed between FAA and JAA to

ensure a unified approach.

These requirements, together with the Life Limits / Monitored Parts, structural

Airworthiness Limitation Items (ALI) and systems Certification Maintenance

Requirements (CMR) comprise the Airworthiness Limitation Section which satisfies the

requirements of JAR 25.1529 Appendix H paragraph 25.4.

IMPORTANT: At first delivery of an aircraft configuration into an operator’s fleet, the

requirements given in this document are mandatory, except in so far that interval

escalations can be justified in accordance with the procedure stated herein. If a more

restrictive Fuel ALI is issued on an aircraft configuration already in service, the

requirement for exis ting operators to follo w the revised FAL document will normally be

mandated by Airworthi ness Directive (Consi gne de Navigabilité).

Non-compliance suspends the validity of the Airworthiness Certificate. The identification

of Fuel Airworthiness Limitations in no way diminishes the importance of other tasks

and practices associated with the fuel system. Changes to these are subject to normal

practices and procedures between the operator and his national authorities.

This document does not take into account Airworthiness Directives (Consignes de

Navigabilité) which, if i ssued against an existing Fuel Airworthiness Limitation,

supersede the specific requirement given in this document.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-0 PAGE: 2

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### B. ALS Part 5 Applicability

The applicability of this ALS Part 5 revision is restricted to the aircraft series and models

listed in the table below:

Aircraft

series Aircraft

models

A340-200 -211

-212

-213

A340-300 -311

-312

-313

A340-500 -541

-542

A340-600 -642

-643



### C. Reporting

Accountable persons or organizations should report to Airbus, any identified condition

affecting components listed in this ALS Part 5 which could endanger flight safety.

“Endanger flight safety” for this ALS means any condition that could contribute to the

occurrence of an ignition source in or adjacent to the fuel tanks.

The finding report should include at least the information stated below:

− Aircraft MSN affected,

− FAL maintenance requirement reference,

− Identification of the affected component/item,

− Life since new (in Flight Hours and/or Flight Cycles and/or landings and/or calendar

time, as applicable) accumulated by the affected system/component/item at the

time of the finding,

− Location and description of the finding, with indication of the size and orientation,

− Circumstance of detection and inspection method used.

D. Sub-part 5-1: Illustrations

ALS Sub-part 5-1 provides illustrations of aircraft zone where the repetitive

maintenance/inspection tasks listed in the sub-part 5-4 are performed.

Illustrations included in this sub-part are for information only. Refer to the AMM

for illustrations applicable to an actual aircraft configuration.

### A340 AIRWORTHINESS LIMITATIONS SECTION

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### E. Sub-part 5-2: Design changes

The Sub-part 5-2 is approved by the EASA.

This section provides mandatory changes to type design related to SFAR 88 and

INT/POL/25/12 in accordance with the EASA policy statement on the process for

developing instructions for maintenance and inspection of fuel tank system ignition

source prevention.

Each modification and associated instructions arise from Airworthiness Directives

previously issued by EASA or French DGAC. Airbus has introduced only the

requirements conc erning A340 aircraft as defined in par agraph 1-B (Applic ability of the

document).

F. Sub-part 5-3: Life limitations

The Sub part 5-3 is approved by the EASA.

Components listed under this sub-part are those affected by a replacement requirement

associated to a life limitation less than the applicable aircraft life limit due. Failure of

these components in combination with other failure conditions can contribute to an

unsafe condition.

a. Traceability and repl acement r equirements

In order to maintain aircraft airworthiness, it is mandatory to replace

components listed under sub-part 5-3 at or prior to whichever of the life

limitations (if applicable) occurs first.

Therefore, it is necessary to assure traceability and monitoring of the

components listed in the sub-parts 5-3. Non-compliance with these

requirements could suspend the validity of the Certificate of Airworthiness.

New PNRs are introduced as a result of modifications and Service Bulletins Airbus

publishes. These new PNRs may not be listed in the current ALS Part 5, when the

related modifications and/or Service Bulletins have been released after the

approval of this revision.

However, it is recommended to assure traceability and monitori ng of such items

whatever their PNR in case of future introduction in the ALS Part 5. For further

guidance, Operators are requested to contact Airbus.

Note : In the context of this revision, traceability means reco rds that clearly

demonstrate the history of each component back to initial entry into

service of the component, so that life limitations are accurately applied.

Traceability records may comprise, but are not limited to, the following:

− Application history (aircraft type, model, weight variant, MSN i.e.

Manufacturer Serial Number, etc...),

### A340 AIRWORTHINESS LIMITATIONS SECTION

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### − Maintenance actions carried out (Airworthiness Directives,

modifications, repairs, inspections, etc...),

− Life accumulation (accounting for any individual aircraft to which a

component may have been fitted).

b. Disposal/quarantine action

When a component listed under sub-part 5-3 reaches the life limitation,

disposal/quarantine action must be taken. Appropriate means must be

implemented to deter their installation on aircraft pending possible extension of

their life limitations.

Examples of means are:

− Record keeping system,

− Non-permanent markings,

− Segregation (items stored separately from those currently eligible for

installation).

The ultimate solution is the mutilation beyond repair limits to prevent rework to

appear to be airworthy.

G. Sub-part 5-4: Repetitive maintenance/inspection tasks

The Sub-part 5-4 is approved by the EASA.

It is mandatory to perform/repeat the maintenance requirements listed in Sub-part

5-4 at or prior to whichever of the limitations threshold/interval (if applicable)

occurs first.

The sub-part 5-4 identifies repetitive maintenance/inspection tasks at aircraft level. The

maintenance requirements are applicable no later than the aircraft reaching the

airworthiness limitation.

These tasks must be included in an Operator’s Approved Maintenance Program. The

task interval may be quoted in any usage parameter (Flight Hour, Flight Cycle or

Calendar time) depending on the cause of potential degradation that, if not detected

and addressed, could lead to a catastrophic failure of the airplane.

Unless otherwise stated, the tasks and intervals specified in sub-part 5-4 of the ALS

Part 5 are mandatory and cannot be changed, escalated or deleted without the

concurrence of the Primary Certification Authority (EASA).

Where explicitly stated, task intervals may be adjusted in accordance with an operator's

approved escalation prac tices or an approved re liability program, but the task content

may not be changed or deleted without prior Primary Certification Authority (EASA)

approval. This statement has been agreed on the basis that operators with approved

escalation practices or an approved reliabilit y program make adj ustments to their

maintenance programs based on data collection and analytical techniques. It has been

demonstrated that the use of such methods to manage a maintenance program does

not give rise to undue escalation.

### A340 AIRWORTHINESS LIMITATIONS SECTION

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© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### With respect to tasks requiring tank entry, the interval quoted in this document is

intended to allow Operators to perform the task during an extended hangar visit during

which tank entry is already likely to be required for accomplishment of structural and

Zonal inspections.

a. Exceptional Short-Term Extensions

Since Fuel ALI Maintenance / Inspection intervals are based on statistical averages

and reliability rates, an except ional short-term extension for a specific Fuel ALI

interval may be made on one aircraft for a limited period of time without

jeopardising safety.

The term 'exceptional short-term extension' is defined as an increase in a Fuel ALI

interval that may be needed to cover an uncontrollable or unexpected situation.

Repeated use of such extensions, either on the same aircraft or on similar aircraft

in the operator's fleet, should not be used as a substitute for good management

practices.

Unless noted adjacent to the task, for all Fuel ALIs identified in this document, it

has been accepted by the Primary Certification Office (EASA) that short-term

extensions up to the following maximum values may be granted without

consultation with that office. Requests for extensions in excess of these values

must be submitted with full justification to the Primary Certification Office (EASA)

such that approval, if granted, can be given prior to their use.

(1) Fuel ALIs controlled by Flight Hours (FH)

Extensions up to 10% or 500FH (whichever is the lesser) may exceptionally be

granted on Fuel ALI intervals quoted in terms of flight hours.

(2) Fuel ALIs controlled by Flight Cycles (FC or LDGS)

Extensions up to 5% or 250FC (whichever is the lesser) may exceptionally be

granted on Fuel ALI intervals quoted in terms of flight cycles or landings.

(3) Fuel ALIs controlled by Calendar Time (MTHS or MO)

− Where the repeat interval is 12 months or less, extensions up to 10% or 1

month (whichever is the lesser) may exceptionally be granted on Fuel ALI

intervals quoted in terms of months.

− Where the repeat interval is greater than 12 months but less than 3 years,

extensions up to 2 months may exceptionally be granted.

− Where the repeat interval is 3 years or greater, extensions up to 3 months

may exceptionally be granted.

### A340 AIRWORTHINESS LIMITATIONS SECTION

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© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### It is the operator's responsib ility to identify appropriate procedures with his local

regulatory authority for the control and development of his maintenance program.

This paragraph in the Fuel Airworthiness Limitation document is written to confirm to the

local regulatory authority that exceptional short-term extensions of Fuel ALI intervals are

permissible. Approval of such extensions rests with the local authority in the same way

as it does for any other scheduled maintenance task interval extension.

H. Sub-part 5-5: Critical Design Configuration Control Limitations

The Sub part 5-5 is approved by the EASA.

A CDCCL is a limitation requirement to preserve either a critical ignition source

prevention feature of the fuel system design that is necessary to prevent the occurrence

of an unsafe condition or a critical design f eature of the flammab ility reduction system.

The purpose of the CDCCL is to provide instructions to retain the critical ignition source

prevention or critical flammability r eduction system design feat ure during c onfiguration

change that may be caused by alterations, repairs, or maintenance actions.

It is the operator’s responsib ility to ensure that their in ternal document ation is amended

to reflect the limitations and associated instructions contained within this sub-part and

provide appropriate text to highlight the existence of each CDCCL. Such identification is

necessary in the instructions used by the person performing an installation, alteration,

repair or modification so as to minimize the risk that the work performed compromises

the original design criteria.

Regulatory oversight of the operator’s compliance with this mandatory requirement is

based on the appropriate identification of the CDCCL in the accomplishment

instructions associated with the installation, alteration, repair or modification.

I. Modifications/repairs not developed under Airbus DOA Certificate EASA.21J.031

If an aircraft/a component/an item has a modification or repair embodied that has not

been developed under the Design Organization Approval (DOA) Certificate

EASA.21J.031 (e.g. under a Supplemental Type Certificate) and which affects the

content of the ALS Part 5, the Operator is responsible for obtaining approval by the

relevant Airworthiness Authority for any necessary adaptations of the airworthiness

limitations.

When such an aircraft/a component/an item is transferred from one Owner/Operator to

another, the associated approvals and documents indicating the necessary adaptations

of airworthiness limitations must be transferred as well.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-0 PAGE: 7

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### 2. DEFINITIONS

The initial entry into service is defined for the aircraft (systems installations) as:

− The date of Transfer of Title (ToT) to the first Operator for airworthiness limitations in

Calendar times and/or flight hours, unless otherwise stated in any delivery

documentation to the first Operator. Considering the very low number of Flight Hours

performed between first flight and delivery, and the methodology used to define task

intervals, EASA agree to consider the date of delivery of the aircraft as the starting time

for Fuel ALI tasks whose intervals are given in Flight Hours.

− The date of aircraft first flight for airworthiness limitations in Flight Cycles and/or

Landings.

The initial entry into service for the transferable systems components/items is defined as the

date at which the componen t/item accomplishes the first flight for which it will undertake its

intended function.

Note: Unless otherwise stated, this means for transferable components/items delivered

on new aircraft (i.e. from Airbus Final Assembly Line) that the life accumulated

between aircraft first flight and the aircraft delivery date/transfer of title date (e.g.

as a result of test flights) must be taken into account.

Calendar times (Cal.): Thresholds/intervals in Years (Ye), Months (Mo) etc... must be

counted from the date of initial entry into service (unless

otherwise stated). In considering the accumulated time since the

initial entry into service, it should be noted that Calendar time

usage parameter cannot be frozen (unless otherwise stated).

Flight Cycle (FC): A complete take-Off and landing sequence.

Flight Hour (FH): The accumulated time intervals between ‘wheels-off’ and ‘wheelson’.

Interval: The period expressed in usage parameters like FH and/or FC

and/or LDG and/or Calendar time between successive

accomplishments of a specific task.

Operational Che ck: A qualitative check to determine t hat an item is fulfilling its

intended purpose. It is a failure finding task and does not require

quantitative tolerances.

Threshold: The initial accomplishment of a specific maintenance task from

the initial Entry Into Service (EIS). It may be expressed in usage

parameters like FH and/or FC and/or LDG and/or Calendar time.

Detailed Inspection: An intensive examination of a specific item, installation or

assembly, to detect damage, failure or irregularity. Available

lighting is normally supplemented with a direct source of good

lighting at an intensity deemed appropriate. Inspection aids such

as mirrors, magnifying lenses, etc. may be necessary. Surface

cleaning and elaborate access procedures may be required.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-0 PAGE: 8

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### 3. LIMITATION/REPLACEMENT TIME INDICATION

A. General

In computing the part’s accumulated life, calculations must include flight hours

and/or flight cycles and/or landings and/or calendar time (as applicable) since the

initial entry into service of the part (unless otherwise stated).

The life limitation indicated against PNR originally fitted is counted from the

part’s initial entry into service.

The life limitation indicated against PNR evolutions is also to be counted from the

part’s initial entry into service (unless otherwise stated).

B. ALS Part 5 Life Limitation

Life limitations quoted in Sub-part 5-3 are applicable to the undamaged detail parts as

listed, not to the assembly or the aircraft on which they are installed. The

limitation/replacement time indication is quoted on the same line/block of lines as the

PNR.

C. Production/Repair concessions, ALS Variation and Alternative Method Of Compliance

The life limitation of the ALS Part 5 may be negated by instructions given in either a

Production concession, a Repair design Approval Sheet (RAS), an ALS Variation (AV)

or an Alternative Method Of Compliance (AMOC).

It is the operator’s res ponsibility to refe r to the applicable limitations.

When limitations change in a revision of the ALS Part 5 subsequent to the issuance

date of the Production concession/RAS/AV/AMOC, Operators are requested to contact

Airbus for guidance.

The restrictions of limitation(s) indicated in the RAS/AV/AMOC (or absence thereof)

depend on the part's accumulated life considered during the original evaluation of the

repair solution/AV/AMOC.

Production concessions are provided to the initial Operator of the aircraft in the delivery

documentation (Aircraft Inspection Report ‘Recordable concessions’).

4. RULES SPECIFIC TO ALS PART 5

A. Sub-part 5-2: Design changes

The modifications and associated Service Bulletins are presented in the sub-part 5-2

and are classified by ATA chapters by ascending numbers.

The requirements arising from airworthiness directives introduced in this revision

concern only the A340 series aircraft as defined in paragraph 1-B of this sub-part.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-0 PAGE: 9

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### Unless otherwise stated, where no revision number is made for an Airbus SB, it must

be assumed that the latest approved revision of the SB is applicable but any previous

revision is acceptable.

Where a revision number is stated, Operators must use this revision number. The use

of any further approved revision is an acceptable mean of compliance for modification

requirements.

B. Sub-part 5-3: Life limitations

The life limitation and associated instructions must be applied from:

− The initial Entry Into Service of the part (Refer to paragraph 2 of this sub-part for

Definitions).

Life limitation applicability is allocated to all affected aircraft (refer to Sub-part 5-0

paragraph 1-B Applic ability system).

C. Sub-part 5-4: Repetitive maintenance/inspection tasks

The limitations and associated instructions must be applied from:

− The Entry Into Service of the aircraft for the first accomplishment and then the date

of last accomplishment of the task.

The repetitive maintenance/inspection tasks are presented in the sub-part 5-4 in

accordance with the following method:

a. FAL reference number

The FAL reference numbering system follows a similar format to the Maintenance

Planning Document (MPD) system, as follows:

The FAL reference number comprises 12 digits and 1 letter organised as follows:

XXXXXX- YYYYY-I-F

XXXXXX: The ATA reference i dentifies the system/sub-system or component on

which the task is to be accomplished.

YYYYY: St ands for the Sequence Number, apart from a few cases, the

sequence number is used to discriminate between different tasks

relating to the same hardware.

I: The Applicability Index identifies successive developm ents of a task,

introduced by modifications or specific requirement.

F: Stands for discriminating task related to ALS Part 5.

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-0 PAGE: 10

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### b. Description column

The description column provides the following information:

− A task description: Gives a concise description of the work to be performed.

− A reference to the rela ted illustration i dentified in the sub-part 5-1.

c. Threshold/Interval column

These columns are used to record the selected threshold and interval for the task.

The threshold and interval may be expressed in terms of usage parameters or

notes. Usage parameters are defined in the paragraph 2 of this sub-part.

d. Reference column

The reference column provides reference(s) to Instruction for Continued

Airworthiness where maintenance practices/procedures necessary for the task

accomplishment are provided. E.g.: Reference to Aircraft Maintenance Manual

(AMM).

The reference column is for guidance only as its content is not approved by EASA.

Should a reference change between two successive revisions of the ALS Part 5,

the Operator should consider the updated reference.

e. Limitations applicability column

Applicability Task applicable to

A340- xxx

POST nnnnn All A340- xxx that do have MOD nnnnn embodied

A340- xxx

POST nnnnn

OR

POST SB A340-yy- yyyy All A340- xxx that do have MOD nnnnn embodied OR All A340- xxx that do

have SB A340-yy- yyyy em bodied.

A340- xxx

POST nnnnn

PRE mmmmm All A340- xxx that do have MOD nnnnn embodied but that do not have MOD

mmmmm embodied.

A340- xxx

POST nnnnn

PRE mmmmm

A340- yyy

POST aaaaa

PRE bbbbb All A340- xxx that do have MOD nnnnn embodied but do not have MOD

mmmmm OR A340- yyy that do have MOD aaaaa but do not have MOD

bbbbb embodied.



### D. Sub-part 5-5: CDCCL

The CDCCL items related to fuel tank system are presented in the ALS part 5 sub-part

5-5.

a. CDCCL column

The CDCCL column identifies the critical component/part or design features of the

fuel tanks and, if fi tted, the Flammabilit y Reduction System (F RS) which provides

an inerting function.

### A340 AIRWORTHINESS LIMITATIONS SECTION

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### b. Requirements column

The requirements column explains why critical component/ part or design features

of the fuel tanks or of the FRS are considered critical with regards to ignition risk.

This column provides instructions to retain the critical ignition source prevention or

critical flammabilit y reduction feat ures during c onfigurati on change that may be

caused by alterations, repairs, or maintenance actions that Operators are required

to comply with.

c. Reference column

This column provides a reference to Instruction for Continued Airworthiness where

a CDCCL is contained.

E.g: Reference to Aircraft Maintenance Manual (AMM), or Component Maintenance

Manual (CMM).

Operators must ensure that the person performing an installation, a repair or a

modification will not compro mise the original design criteria and must reflect

CDCCL in their internal documentation.

d. Applicability column

Due to their general nature, CDCCL n°5 and n°8 are considered impracticable to

identify in aircraft document ation. The applicability column gives the co mbination of

critical design features with aircraft that requires the identification of CDCCL items.

Note: CDCCL n°8 applies only to FAA registered aircraft.

“FAA only” term in the limit ation applicability means that all aircraft operated under

FAA registration or aircraft registered under an Airworthiness Authority which follow

FAA rules, have to comply wi th this limitation. It is the operator’s responsibility to

check the limitation applicability with the authority of the state of aircraft registration.

END OF SUB-PART 5-0

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-1 PAGE: 1

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### Sub-part 5-1 ILLUSTRATIONS

GROUND FAULT INTERRUPTERS - FIG. 01

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-1 PAGE: 2

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### VAPOUR HEATSHIELDS - FIG. 02

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-1 PAGE: 3

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### DUAL FLAPPER CHECK VALVE - FIG. 03

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-1 PAGE: 4

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### INERT GAS GENERATOR SYSTEM PALLET ON A340-200/300, INCLUDING THE DUAL

FLOW SHUT OFF VALVE - FIG. 04

### A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 16/11 ALS PART 5-1 PAGE: 5

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

### INERT GAS GENERATOR SYSTEM PALLET ON A340-500/600, INCLUDING THE DUAL

FLOW SHUT OFF VALVE - FIG. 05

END OF SUB-PART 5-1A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 1EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Sub-part 5-2 CHANGES TO TYPE DESIGNNote: Where reference is made to an Airbus Service Bulletin (SB), it must be assumed that the latest approved revision of the SB is applicable, but anyprevious revision is acceptable. Where a particular revision is stated, the revision or any later approved revision must be used.ATA 21-00 AIR CONDITIONING SYSTEMMOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.49520A340-21-4107R012006-0191 2006-21-08 Air conditioning - Center fuselage – Installheatshields in belly fairing to segregate airsystem.N/A N/A 31-Oct-2008A340-200A340-30058551 A340-21-4147 2009-0150 2010-04-09 Air conditioning - Air cooling - Modify heatshields N/A N/A 23-Jul-2011A340-200(1)A340-300(1)(1) On which Airbus modification 49520 has been embodied in production or on which Airbus Service Bulletin (SB) A340-21-4107 Revision 01 has beenembodied in service.Note: The embodiment limits given in the table above are for EASA compliance.A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 2EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Note: Where reference is made to an Airbus SB, it must be assumed that the latest approved revision of the SB is applicable, but any previous revision isacceptable. Where a particular revision is stated, the revision or any later approved revision must be used.ATA 28-00 FUEL SYSTEMMOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.N/A A340-28-4107R012007-0278 2008-25-02 Fuel - General - Inspection of p-clips in thewings and center fuel tanks.N/A N/A 31-Dec-2009A340-200(1)A340-300(1)42969 A340-28-4054R011998-103-082(B)N/A Fuel - FQI - Fit modified densitometer electricallybonded to aircraft structure.N/A N/A Within thefirstscheduledinner fueltank openingbut no laterthan72 Monthssince EntryIn ServiceA340-200A340-30045580 A340-28-4069 1998-103-082(B)N/A Fuel−Quantity indication−Improve electricalbonding of densitometer to aircraft structure.N/A N/A Within thefirstscheduledinner fueltank openingbut no laterthan72 Monthssince EntryIn ServiceA340-200A340-300491355182550104A340-28-4097R032007-0278 2008-25-02 Fuel - General - Revise the electrical bonding ofthe equipment in the fuel tanks.N/A N/A 31-Dec-2009A340-200(2)(3)A340-300(2)(3)55118 A340-28-4118R022007-0278 2008-25-02 Fuel - general - bonding of fuel diffuser supportbracket to wing Structure.N/A N/A 31-Dec-2009A340-200(2)A340-300(2)N/A A340-28-4097R052010-0232 2008-25-02 Fuel - General - Revise the electrical bonding ofthe equipment in the fuel tanks.N/A N/A 26-Nov-2012A340-200(4)A340-300(4)A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 3EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.MOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.200242 A340-28-4129R002011-0196 N/A Fuel – Main transfer system – Intro ground faultinterrupters to center tank fuel pump controlcircuit.N/A N/A 21-Oct-2015A340-200A340-300200242 A340-28-5051R002011-0196 N/A Fuel – Main transfer system – Intro ground faultinterrupters to center andrear center tank fuelpump control circuit.N/A N/A 21-Oct-2015A340-500A340-60047215 A340-28-4078 2007-0278 2008-25-02 Fuel -Tanks - Revise electrical bonding in act N/A N/A 31-Dec-2009A340-200(5)A340-300(5)46142 A340-28-4073 2007-0278 2008-25-02 Fuel - Jettison system - Install additionalbonding leadN/A N/A 31-Dec-2009A340-200A340-300(1) Except on which AIRBUS modification No. 47634 has been embodied in production(2) Except for aircraft on which the four AIRBUSmodifications No. 49135 and 49630 and 51825 and 55118 have been embodied in production ormodified in-service in accordance with both SB A340-28-4097 Revision 03 and SB A340-28-4118 Revision 02(3) For aircraft that have already been modified in accordancewith SB A340-28-4097 at any previous issue preceding Revision 03: Not later thanDecember 31st, 2011, perform the additional work in accordance with the instructions of or SB A340-28-4097 Revision 03.(4) For aircraft on which Airbus modification 41600 has beenembodied in production and which have embodied Airbus SB A340-28-4097 at originalissue or a later revision up to Revision 03 inclusive has been embodied in service, except aeroplanes on which Airbus modification 49135 has beenembodied in production.(5) For aircraft which have the AIRBUS modification 42612/SB A340-28-4047 or 44002/SB A340-28-4066 or 44005/SB A340-28-4067 embodied inproduction/in-service (installation of ACT)Note: The embodiment limits given in the table above are for EASA compliance.A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 4EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Note: Where reference is made to an Airbus SB, it must be assumed that the latest approved revision of the SB is applicable, but any previous revision isacceptable. Where a particular revision is stated, the revision or any later approved revision must be used.ATA 31-00 INDICATING & RECORDING SYSTEMSMOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.51791A340-31-41252010-0089 2011-01-02 Indicating/recording systems - FWC - Install newFWC standard L11-0 on A340.N/A N/A 24-Nov-2010A340-200A340-300Note: The embodiment limits given in the table above are for EASA compliance.A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 5EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Note: Where reference is made to an Airbus SB, it must be assumed that the latest approved revision of the SB is applicable, but any previous revision isacceptable. Where a particular revision is stated, the revision or any later approved revision must be used.ATA 55-00 HORIZONTAL STABILIZERMOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.44848 A340-55-4017R012007-0278 2008-25-02 Stabilizer - Horizontal stabilizer - Rework ofsome metallic parts for improvement of lightningstrike protection.N/A N/A 31-Dec-2009A340-200(1)A340-300(1)(1)Except for aircraft on which AIRBUS modification No. 44252 has been embodied in production.Notes:- For all aircraft where the improvement of the THS lighting strike protection has already been performed in accordance with AOT55-03 dated 22 August 1996 (“solution A”), mandated by DGAC AD F-1996-178-049(B) R1 and DGAC AD F-1996-177-038(B)with a compliance time of November,15th1996, it is allowed to increase the distancebetween metallic parts on the THS Trim Tankin accordance with the instructions of SB A340-55-4017 after 31st December 2009, whenever the THS removal from aircraft andput on ground on support Tool (Lifting and Resting points Fittings must be installed) for any reason (fuselage stress jacking,repair...) is performed forthe first time after such date,or at the first aircraft maintenance task requiringthe use of THSLifting andResting points Fittings performed after such date.- The embodiment limits given in the table above are EASA compliance.A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 6EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Note: Where reference is made to an Airbus SB, it must be assumed that the latest approved revision of the SB is applicable, but any previous revision isacceptable. Where a particular revision is stated, the revision or any later approved revision must be used.ATA 57-00 WINGSMOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.5264953507A340-57-50072006-0187N/A Wings - Main structure - Introduce newfastener positions in wing box ribs forimproved electrical bondingN/A N/A 31-Dec-2009A340-541A340-642Note: The embodiment limits given in the table above are for EASA compliance.A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-2 PAGE: 7EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Note: Where reference is made to an Airbus SB, it must be assumed that the latest approved revision of the SB is applicable, but any previous revision isacceptable. Where a particular revision is stated, the revision or any later approved revision must be used.ATA 92-00 ELECTRIC AND ELECTRONIC COMMON INSTALLATIONMOD SB EASA AD FAA AD DESCRIPTIONEMBODIMENT LIMITS(Whichever occurs first)LIMITATIONSAPPLICABILITYFH FC Cal.52251 A340-92-5010CNF-2005-030N/A Electric/electronic common installation - ImproveAPU feeder route installation.N/A N/A 31-Dec-2009A340-541A340-642Note: The embodiment limits given in the table above are for EASA compliance.END OF SUB-PART 5-2A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-3 PAGE: 1EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Sub-part 5-3 LIFE LIMITATIONSATA 47-10-00 INERT GAS SYSTEM – GENERATION/STORAGENomenclature Part Number(1)LIFE LIMITS (whichever occurs the first)LIFE LIMITS APPLICABILITYFH FC Cal.Air Separation Module (ASM) 2060032-1XX 27000 N/A N/AA340-200 AND A340-300POST MOD 58723A340-500 AND A340-600POST MOD 58724(1) XX at the end of the Part Number stands for any number between 01 and 99END OF SUB-PART 5-3A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-4 PAGE: 1EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Sub-Part 5-4 REPETITIVE MAINTENANCE/INSPECTION TASKSALS PART 5 REPETITIVE MAINTENANCE/INSPECTION TASKSREFERENCE INTERVAL APPLICABILITYDescription FAL reference numberGROUND FAULT INTERRUPTERS – FIG. 01Operational check of centre tank fuel pump Ground Fault Interrupter(GFI).281800-00001-1-F AMM28-18-00-7104000 FHFAA only (1)A340-200 and A340-300POST MOD 200242A340-500 and A340-600POST MOD 200242VAPOUR HEATSHIELDS – FIG. 02Detailed inspection of the heatshields below the centre tank.281800-00002-1-F AMM28-18-52-2106 Ye (2)A340-200 and A340-300POST MOD 49520A340-500A340-600NEA and DFCV – FIG. 03IGGS A340-200/300, and DFSOV – FIG. 04IGGS A340-500/600, and DFSOV – FIG. 05Operational check of Dual Flow Shut Off Valve (DFSOV), Dual FlapperCheck Valve (DFCV) and Nitrogen Enriched Air (NEA) pipeline for leaks.470000-00001-1-F AMM47-21-43-71012000FHA340-200 and A340-300POST MOD 58020A340-500 and A340-600POST MOD 58022NEA and DFCV – FIG. 03Operational check of both Dual Flapper Check Valves (DFCV) for leaks.470000-00002-1-F AMM47-20-43-71060000FH (3)A340-200 and A340-300POST MOD 58020A340-500 and A340-600POST MOD 58022A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-4 PAGE: 2EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.ALS PART 5 REPETITIVE MAINTENANCE/INSPECTION TASKSREFERENCE INTERVAL APPLICABILITYDescription FAL reference numberNEA and DFCV – FIG. 03Operational check of Dual Flapper Check Valves (DFCV) for reverse flow.470000-00003-1-F AMM47-20-43-71012000FHA340-200 and A340-300PRE MOD 58020POST MOD 58019A340-500 and A340-600PRE MOD 58022POST MOD 58021(1) “FAA only” term in the limitation applicability means that all aircraft operated under FAA registration or aircraft registered under anAirworthiness Authority which follow FAA rules, have to comply with this limitation. It is theoperator’s responsibility to check the limitationapplicability with the authority of the state of aircraft registration.(2) In accordance with sub-part 5-0, paragraph 1-G, it is herewith confirmed that the interval of the task mentioned in the above table maybe adjusted in accordance withan operator's approved escalation practicesor an approved reliability program, but the task content maynot be changed or deleted without prior Primary Certification Authority (EASA) approval.(3) For aircraft that have operated with MOD 58019 or MOD 58021 embodied in isolation, the operational check of both Dual FlapperCheck Valves for leaks shall also be performed at time of embodiment of MOD 58020 or MOD 58022.END OF SUB-PART 5-4A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-5 PAGE: 1EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Sub-part 5-5: CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONSCDCCLREF.CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITY1 Air Gap between FuelQuantity Indicator (FQI)probe and tank structure.Critical to prevent spark generation during lightning strikeconditions and must not be compromised.The gaps stated in the relevant maintenance procedure in the AMMmust be achieved during installation of a fuel quantity probe.AMM28-42-15-40028-42-16-40028-42-17-40028-42-19-40028-42-21-40028-42-26-400A340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340-200 AND A340-300A340 – ALL seriesA340-5002 Separation of fuel quantityand level indicatingsystem wiring from otherwiring.To prevent cross coupling ofhigh voltage transients and therebykeep unsafe ignition energies frominside the tank. It is requiredthat operators obey the wire routing and separation standards givenin the Electrical Standard Practices Manual (ESPM).ESPM20-10-0020-33-2020-33-2120-33-22A340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL series33Direct bonding on items ofequipment inside a fueltank.Direct bonding is critical toprevent spark generation duringcomponent failure and lightning strike conditions and must not becompromised.Direct Bonding in fuel tanks must be carried out during componentinstallation to the appropriate bonding method and standard statedwithin the installation procedure in the AMM.AMM28-11-33-40028-11-41-40028-11-44-40028-12-41-40028-12-45-40028-12-48-40028-12-51-40028-12-52-40028-13-43-40028-17-51-40028-17-52-40028-17-54-400A340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340-200 AND A340-300A340-200 AND A340-300A340-500A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-5 PAGE: 2EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.CDCCLREF.CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITY(continuing)3(continuing)28-17-55-40028-21-51-40028-21-52-40028-22-41-40028-22-42-40028-22-51-40028-22-52-40028-25-33-40028-25-42-40028-25-43-40028-25-44-40028-26-21-40028-26-42-40028-26-49-40028-26-51-40028-26-56-40028-27-22-40028-27-24-40028-27-48-40028-27-56-40028-27-58-40027-27-59-40028-28-44-40028-42-18-40028-42-23-40028-42-33-40028-42-34-40028-42-36-400A340-500 AND A340-600A340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340-200 AND A340-300A340 – ALL seriesA340-200 AND A340-300A340-500A340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340-500A340 – ALL seriesA340 – ALL seriesA340 – ALL seriesA340-500A340 200 AND A340-300A340-500 AND A340-600A340 – ALL seriesA340-200 AND A340-300A340-500 AND A340-600A340-500 AND A340-600A340-200 AND A340-300A340 – ALL seriesA340-500 AND A340-600A340-500 AND A340-600A340-500 AND A340-600A340-500 AND A340-600A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-5 PAGE: 3EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.CDCCLREF.CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITY28-43-51-40028-43-53-40057-27-11-400A340 – ALL seriesA340 – ALL seriesA340 – ALL series4 Safety critical features offuel pumps.These features must be maintained throughout the full life of thefuel pump to avoid the possibility of generation of an ignition sourceby overheating or sparks caused by arcing, friction etc.Repair and overhaul of fuel pumps must be carried out inaccordance with the equipment manufacturer’s maintenanceinstructions or other maintenance instructions acceptable to thecertifying authority.CMM28-20-4028-20-5128-21-5028-21-5528-21-5928-22-1128-22-12A340-200 AND A340-300A340-500 AND A340-600A340-200 AND A340-300A340 – ALL seriesA340-500A340 – ALL seriesA340-200 AND A340-3005Centre fuel tank volume,ventilation and flow rate.The volume of the Centre fuel tank and the flow rate of theventilation system must be maintained at values which, when usedin the determination of the fuel tank flammability exposure, complywith the Flammability Reduction System (FRS) requirements.N/AA340-200 AND A340-300POST MOD 58723A340-500 AND A340-600POST MOD 587246 Protective coating on fueltank at the connection ofA protective coating (Finch paint) is necessary at the connectionbetween the centre fuel tank and the Dual Flapper Check ValvesAMMA340-200 AND A340-300POST MOD 59019A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-5 PAGE: 4EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.CDCCLREF.CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITYfuel tank inerting system. (DFCV) housing ofthe Inert Gas Generating System (IGGS) toprevent fuel or fuel vapour leaks into an area containing ignitionsources.After maintenance of the DFCV the protective coating must berestored to the appropriate standardusing the method stated withinthe maintenance procedure in the AMM.47-20-43-71047-21-43-710A340-500 AND A340-600POST MOD 580217 Warning Placards forareas that may containoxygen depletedatmospheres.When a Flammability Reduction System is installed, the accessdoors and panels to the fuel tank(s) and any other enclosed areasthat could contain hazardousatmosphere under either normalconditions or failure conditions must be permanently stencilled,marked, or placarded to warn of hazards.Warning placards must be installed in the appropriate positions toensure maintenance personnel areaware of areas that may behazardous because of possible oxygen depleted atmosphere.AMM25-52-00-00025-52-00-40028-12-52-00057-17-11-00057-17-00-400A340-200 AND A340-300POST MOD 58723A340-500 AND A340-600POST MOD 587248 Flammability ReductionSystem (FRS) designperformanceFlammability reduction system performance is dependent onairplane descent times. Industry efforts to reduce descent time mayresult in Flammability Reduction System performance that does notN/A FAA only (1)A340-200 AND A340-300A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 16/11 ALS PART 5-5 PAGE: 5EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.CDCCLREF.CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITYmeet FAA requirements. Fleet average flammability exposure forthe fuel tanks with flammability reduction system of this airplanetype must be maintained in accordance with 14 CFR Part 25,appendix M.Airbus will monitor descent statistics (including US descents) and, ifnecessary to maintain compliance, will publish service information.If Airbus publishes such serviceinformation, this CDCCL requiresthat Operators implement these FAA approved design changes tomaintain compliance with 14 CFR Part 25, appendix M.POST MOD 58723A340-500 AND A340-600POST MOD 58724(1) “FAA only” term in the limitation applicability means that all aircraft operated under FAA registration or aircraft registered under anAirworthiness Authority which follow FAA rules, have to comply with this limitation. It is theoperator’s responsibility to check the limitationapplicability with the authority of the state of aircraft registration.Note: The CDCCL Ref. 8 does not require individual Operators to monitordescent rates of their fleets.Airbus will monitor descent statisticsand provide any needed service instructions to Operators. To preventincreasing flammability exposure above permissible levels,thisCDCCL requires Operators to incorporate future Airbus published service instructions denoted to maintain compliance with thisCDCCL, or other approved actions, within the compliance times stated in the service instructions.END OF SUB-PART 5-5

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### 1- GENERAL

A340 Fuel Airworthiness Limitations (FAL) Document issue 1

First issue of the A340 FAL document referenced in the ALS part 5.

A340 Fuel Airworthiness Limitations (FAL) Document issue 2

The A340 FAL document issue 2 was dedicated to:

− Reword the task 1 title to read: ““Detailed inspection of the Heat shields below the Centre

tank.”

− Clarify the applicability of CDCCLs by identifying ESPM, AMM and CMM references.

− Delete ref. to AMM 28-42-18-400 of CDCCL 1, ref. to ESPM 20-33-11 for CDCCL 2, Ref to

AMM 28-31-43 for CDCCL 3, Ref. to CMM 28-27-48 for CDCCL 4

− Add ref to AMM 28-42-26-400 for A340-500 for CDCCL 1 and ref. “-400” for AMM

references for CDCCL 3, ref. to AMM 28-20-51, 28-21-55 and 28-21-59 for CDCCL 4.

− Correct the applicability of AMM 28-11-48 and 28-17-52 from ALL to A340-200/300 for

CDCCL 3 and AMM 28-20-40 from ALL to A340-200/-300 for CDCCL 4.

A340 Fuel Airworthiness Limitations (FAL) Document issue 3

The A340 FAL issue 03 has been produced to update the document applicability to include the

A340-542 model.

A340 ALS Part 5 Revision 00

A340 ALS Part 5 revision 00 was dedicated to transfer the content of the A340 FAL Document

issue 3 into the subject document.

It was also produced to introduce new limitations resulting from the installation modifications

(Fuel Tank Inerting System (FTIS) and Ground Fault Interrupters (GFI)).

This revision 00 is the opportunity to introduce the requirements of the following Airworthiness

Directives coming from EASA and French DGAC:

− CN F-2005-030

o SB A340-92-5010 at initial issue or later approved revision.

− CN F-1998-103-082(B)

o SB A340-28-4054 Revision 1 or later approved revision.

o SB A340-28-4069 at initial issue or later approved revision.

− AD 2006-0187

o Service Bulletin A340-57-5007 at initial issue or later approved revision.

− AD 2006-0191

o Service Bulletin A340-21-4107 Revision 1 or later approved revision.

− AD 2007-0278

o SB A340-28-4107 Revision 1 or later approved revision.

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### o SB A340-28-4097 Revision 1 or later approved revision.

o SB A340-28-4118 Revision 2 or later approved revision.

o SB A340-28-4078 at initial issue or later approved revision.

o SB A340-28-4073 Revision 1 or later approved revision.

o SB A340-55-4017 Revision 1 or later approved revision.

− AD 2009-0150

o SB A340-21-4147 Revision 1 or later approved revision.

− AD 2010-0232

o SB A340-28-4097 Revision 5.

− AD 2010-0089

o SB A340-31-4125 at initial issue or later approved revision.

− AD 2011-0196

o SB A340-28-4129 R00 or SB A340-28-5051 R00



### 2- SUMMARY OF CHANGES:

The following summarizes the changes between the previous issue A340 FAL Document (issue

3) and the A340 ALS Part 5 Revision 00.

New items:

SUB-PART 5-1 ILLUSTRATIONS

Illustrations added to reflect ALS part 5 Sub-Part 5-4.

SUB-PART 5-2 DESIGN CHANGES:

Introduction of the requirements of the following Airworthiness Directives (EASA/French DGAC)

− CN F-2005-030

− CN F-1998-103-082(B)

− AD 2006-0187

− AD 2006-0191

− AD 2007-0278

− AD 2009-0150

− AD 2010-0232

− AD 2010-0089

− AD 2011-0196

SUB-PART 5-3 LIFE LIMITS

Introduction of a new item:

− Air Separation Module (ASM) PNR 2060032-1XX (XX stands for any number between 01

and 99).

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### SUB-PART 5-4 REPETITIVE MAINTENANCE/ INSPECTION TASKS

Introduction of new maintenance tasks:

− Task 281800-00001-1-F (POST MOD 200242)

− Task 470000-00001-1-F (POST MOD 58020 or POST MOD 58022)

− Task 470000-00002-1-F (POST MOD 58020 or POST MOD 58022)

− Task 470000-00003-1-F (POST MOD 58019 and PRE MOD 58020 or POST MOD 58021

and PRE MOD 58022)

SUB-PART 5-5 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

Introduction of new CDCCL items:

− CDCCL 5 (POST MOD 58723 or POST MOD 58724)

− CDCCL 6 (POST MOD 58019 or POST MOD 58021)

− CDCCL 7 (POST MOD 58723 or POST MOD 58724)

− CDCCL 8 (FAA registered aircraft or other operators under an Airworthiness Authority

which follows FAA rules, POST MOD 58723 or POST MOD 58724)

Amendments:

SUB-PART 5-1 ILLUSTRATIONS:

None.

SUB-PART 5-2 DESIGN CHANGES:

None.

SUB-PART 5-3 LIFE LIMITS

None.

SUB-PART 5-4 REPETITIVE MAINTENANCE/ INSPECTION TASKS

− Task 28-18-00-02-1-F: AMM reference added.

SUB-PART 5-5 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

− CDCCL No. 3: AMM task references added.

− CDCCL No. 4: CMM 28-22-11 and CMM 28-22-12 references added.

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### Deletions:

SUB-PART 5-1 ILLUSTRATIONS

None.

SUB-PART 5-2 DESIGN CHANGES

None.

SUB-PART 5-3 LIFE LIMITS

None.

SUB-PART 5-4 REPETITIVE MAINTENANCE/ INSPECTION TASKS

None.

SUB-PART 5-5 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

− CDCCL 3: AMM task ref 28-11-45-400, 28-11-48-400, 28-23-43-400, 28-31-41-400, 28-26-

42-400 deleted.