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 

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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 existing operators to follow the revised FAL document will normally be 

mandated by Airworthiness Directive (Consigne 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 issued against an existing Fuel Airworthiness Limitation, 

supersede the specific requirement given in this document. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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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 concerning A340 aircraft as defined in paragraph 1-B (Applicability 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 replacement requirements 

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 monitoring 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 records 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...), 
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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 practices or an approved reliability 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 reliability program make adjustments 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 exceptional 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. 
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It is the operator's responsibility 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 feature of the flammability reduction system. 

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

prevention or critical flammability reduction system design feature during configuration 

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

It is the operator’s responsibility to ensure that their internal documentation 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 

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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 component/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 Check: A qualitative check to determine that 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 

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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 responsibility to refer 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 Applicability 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 identifies the system/sub-system or component on 

which the task is to be accomplished. 

YYYYY: Stands 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 developments of a task, 

introduced by modifications or specific requirement. 

F: Stands for discriminating task related to ALS Part 5. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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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 related illustration identified 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 embodied. 

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 fitted, the Flammability Reduction System (FRS) 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 flammability reduction features during configuration 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 compromise 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 documentation. The applicability column gives the combination 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 limitation applicability means that all aircraft operated under 

FAA registration or aircraft registered under an Airworthiness Authority which follow 

FAA rules, have to comply with 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
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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 

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VAPOUR HEATSHIELDS - FIG. 02
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

DUAL FLAPPER CHECK VALVE - FIG. 03 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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© 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 

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

FLOW SHUT OFF VALVE - FIG. 05 

END OF SUB-PART 5-1
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA 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 thprevious revision is acceptable. Where a particular revision is stated, the revision or any later approved revision must be used. 

ATA 21-00 AIR CONDITIONING SYSTEM

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 49520 A340-21-4107 

R01 

2006-0191 2006-21-08 Air conditioning - Center fuselage – Install 

heatshields in belly fairing to segregate air system. 

N/A N/A 31

 58551 A340-21-4147 2009-0150 2010-04-09 Air conditioning - Air cooling - Modify heatshields N/A N/A 23

 (1) On which Airbus modification 49520 has been embodied in production or on which Airbus Service Bulletin (SB) A340-21-4

embodied in service. 

Note: The embodiment limits given in the table above are for EASA compliance. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA 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, bacceptable. Where a particular revision is stated, the revision or any later approved revision must be used. 

ATA 28-00 FUEL SYSTEM 

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 N/A A340-28-4107 

R01 

2007-0278 2008-25-02 Fuel - General - Inspection of p-clips in the 

wings and center fuel tanks. 

N/A N/A 31

 42969 A340-28-4054 

R01 

1998-103-082 

(B) 

N/A Fuel - FQI - Fit modified densitometer electrically 

bonded to aircraft structure. 

N/A N/A W

s

i

tan

b

7

si

I

 45580 A340-28-4069 1998-103-082 

(B) 

N/A Fuel − Quantity indication − Improve electrical 

bonding of densitometer to aircraft structure. 

N/A N/A W

s

i

tan

b

7

si

I

 49135 

51825 50104 

A340-28-4097 

R03 

2007-0278 2008-25-02 Fuel - General - Revise the electrical bonding of 

the equipment in the fuel tanks. 

N/A N/A 31

 55118 A340-28-4118 

R02 

2007-0278 2008-25-02 Fuel - general - bonding of fuel diffuser support 

bracket to wing Structure. 

N/A N/A 31

 N/A A340-28-4097 

R05 

2010-0232 2008-25-02 Fuel - General - Revise the electrical bonding of 

the equipment in the fuel tanks. 

N/A N/A 26
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA APPROVED © AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 200242 A340-28-4129 

R00 

2011-0196 N/A Fuel – Main transfer system – Intro ground fault 

interrupters to center tank fuel pump control circuit. 

N/A N/A 21

 200242 A340-28-5051 

R00 

2011-0196 N/A Fuel – Main transfer system – Intro ground fault 

interrupters to center and rear center tank fuel 

pump control circuit. 

N/A N/A 21

 47215 A340-28-4078 2007-0278 2008-25-02 Fuel - Tanks - Revise electrical bonding in act N/A N/A 31 46142 A340-28-4073 2007-0278 2008-25-02 Fuel - Jettison system - Install additional 

bonding lead 

N/A N/A 31

(1) Except on which AIRBUS modification No. 47634 has been embodied in production (2) Except for aircraft on which the four AIRBUS modifications No. 49135 and 49630 and 51825 and 55118 have been embod

modified 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 accordance with SB A340-28-4097 at any previous issue preceding Revision 

December 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 been embodied in production and which have embodied Airbus SB A3issue or a later revision up to Revision 03 inclusive has been embodied in service, except aeroplanes on which Airbus modificaembodied in production. (5) For aircraft which have the AIRBUS modification 42612/SB A340-28-4047 or 44002/SB A340-28-4066 or 44005/SB A340-2

production/in-service (installation of ACT) 

Note: The embodiment limits given in the table above are for EASA compliance. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA 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, bacceptable. Where a particular revision is stated, the revision or any later approved revision must be used. 

ATA 31-00 INDICATING & RECORDING SYSTEMS 

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 51791 A340-31-4125 2010-0089 2011-01-02 Indicating/recording systems - FWC - Install new 

FWC standard L11-0 on A340. 

N/A N/A 24

Note: The embodiment limits given in the table above are for EASA compliance. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA 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, bacceptable. Where a particular revision is stated, the revision or any later approved revision must be used. 

ATA 55-00 HORIZONTAL STABILIZER 

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 44848 A340-55-4017 

R01 

2007-0278 2008-25-02 Stabilizer - Horizontal stabilizer - Rework of 

some metallic parts for improvement of lightning strike protection. 

N/A N/A 31

 (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 

55-03 dated 22 August 1996 (“solution A”), mandated by DGAC AD F-1996-178-049(B) R1 and DGAC with a compliance time of November,15th 1996, it is allowed to increase the distance between metallic par

in accordance with the instructions of SB A340-55-4017 after 31st December 2009, whenever the THS rput on ground on support Tool (Lifting and Resting points Fittings must be installed) for any reason repair...) is performed for the first time after such date, or at the first aircraft maintenance task requiring thResting points Fittings performed after such date. 

- The embodiment limits given in the table above are EASA compliance. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA 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, bacceptable. Where a particular revision is stated, the revision or any later approved revision must be used. 

ATA 57-00 WINGS 

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 52649 

53507 

A340-57-5007 2006-0187 N/A Wings - Main structure - Introduce new 

fastener positions in wing box ribs for improved electrical bonding 

N/A N/A 31

Note: The embodiment limits given in the table above are for EASA compliance. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-2  EASA 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, bacceptable. Where a particular revision is stated, the revision or any later approved revision must be used. 

ATA 92-00 ELECTRIC AND ELECTRONIC COMMON INSTALLATION 

MOD SB EASA AD FAA AD DESCRIPTION 

EMBODIMENT LIMIT

(Whichever occurs fir

FH FC 

 52251 A340-92-5010 CN 

F-2005-030 

N/A Electric/electronic common installation - Improve 

APU feeder route installation. 

N/A N/A 31

Note: The embodiment limits given in the table above are for EASA compliance. 

END OF SUB-PART 5-2 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-3  EASA APPROVED © AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. Sub-part 5-3 LIFE LIMITATIONS

ATA 47-10-00 INERT GAS SYSTEM – GENERATION/STORAGE

Nomenclature Part Number(1) LIFE LIMITS (whichever occurs the first) LIFE L

FH FC Cal. 

 Air Separation Module (ASM) 2060032-1XX 27000 N/A N/A 

A340-200 APOST MOD A340-500 APOST MOD 

(1) XX at the end of the Part Number stands for any number between 01 and 99

END OF SUB-PART 5-3 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-4  EASA APPROVED 

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Sub-Part 5-4 REPETITIVE MAINTENANCE/INSPECTION TASKS

 ALS PART 5 REPETITIVE MAINTENANCE/INSPECTION TASKS 

REFERENCE INTERVAL 

 Description FAL reference number

GROUND FAULT INTERRUPTERS – FIG. 01 Operational check of centre tank fuel pump Ground Fault Interrupter (GFI). 

281800-00001-1-F AMM 

28-18-00-710 

4000 FH 

VAPOUR HEATSHIELDS – FIG. 02 Detailed inspection of the heatshields below the centre tank. 

281800-00002-1-F AMM 

28-18-52-210 

6 Ye (2) 

NEA and DFCV – FIG. 03 IGGS A340-200/300, and DFSOV – FIG. 04 IGGS A340-500/600, and DFSOV – FIG. 05 Operational check of Dual Flow Shut Off Valve (DFSOV), Dual Flapper Check Valve (DFCV) and Nitrogen Enriched Air (NEA) pipeline for leaks. 

470000-00001-1-F AMM 

47-21-43-710 

12000FH 

NEA and DFCV – FIG. 03 Operational check of both Dual Flapper Check Valves (DFCV) for leaks. 

470000-00002-1-F AMM 

47-20-43-710 

60000FH (3) 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-4  EASA APPROVED 

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

 ALS PART 5 REPETITIVE MAINTENANCE/INSPECTION TASKS 

REFERENCE INTERVAL 

 Description FAL reference number

NEA and DFCV – FIG. 03 Operational check of Dual Flapper Check Valves (DFCV) for reverse flow. 

470000-00003-1-F AMM 

47-20-43-710 

12000FH 

(1) “FAA only” term in the limitation applicability means that all aircraft operated under FAA registration or airc

Airworthiness Authority which follow FAA rules, have to comply with this limitation. It is the operator’s responsibilapplicability 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 mentionebe adjusted in accordance with an operator's approved escalation practices or an approved reliability program, b

not 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 cheCheck Valves for leaks shall also be performed at time of embodiment of MOD 58020 or MOD 58022. 

END OF SUB-PART 5-4 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-5  EASA APPROVED 

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.Sub-part 5-5: CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

REF. CDCCL REQUIREMENTS REFERENCE LIMITATI

 1 Air Gap between Fuel 

Quantity Indicator (FQI) probe and tank structure. 

Critical to prevent spark generation during lightning strike conditions and must not be compromised. The gaps stated in the relevant maintenance procedure in the AMM must be achieved during installation of a fuel quantity probe. 

AMM 28-42-15-400 28-42-16-400 28-42-17-400 28-42-19-400 28-42-21-400 28-42-26-400 

A340 – AA340 – AA340 – AA340-200 A340 – AA340-500 

 2 Separation of fuel quantity 

and level indicating system wiring from other wiring. 

To prevent cross coupling of high voltage transients and thereby keep unsafe ignition energies from inside the tank. It is required 

that operators obey the wire routing and separation standards given in the Electrical Standard Practices Manual (ESPM). 

ESPM 20-10-00 20-33-20 20-33-21 20-33-22 

A340 – AA340 – AA340 – AA340 – A

 3 

3 

Direct bonding on items of equipment inside a fuel tank. 

Direct bonding is critical to prevent spark generation during component failure and lightning strike conditions and must not be compromised. Direct Bonding in fuel tanks must be carried out during component installation to the appropriate bonding method and standard stated within the installation procedure in the AMM. 

AMM 28-11-33-400 28-11-41-400 28-11-44-400 28-12-41-400 28-12-45-400 28-12-48-400 28-12-51-400 28-12-52-400 28-13-43-400 28-17-51-400 28-17-52-400 28-17-54-400 

A340 – AA340 – AA340 – AA340 – AA340 – AA340 – AA340 – AA340 – AA340 – AA340-200 A340-200 A340-500 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-5  EASA APPROVED 

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

CDCCL 

REF. CDCCL REQUIREMENTS REFERENCE LIMITATI

(continuing) 

3 

(continuing)

28-17-55-400 28-21-51-400 28-21-52-400 28-22-41-400 28-22-42-400 28-22-51-400 28-22-52-400 28-25-33-400 28-25-42-400 28-25-43-400 28-25-44-400 28-26-21-400 28-26-42-400 28-26-49-400 28-26-51-400 28-26-56-400 28-27-22-400 28-27-24-400 28-27-48-400 28-27-56-400 28-27-58-400 27-27-59-400 28-28-44-400 28-42-18-400 28-42-23-400 28-42-33-400 28-42-34-400 28-42-36-400 

A340-500 A340 – AA340 – AA340 – AA340-200 A340 – AA340-200 A340-500 A340 – AA340 – AA340 – AA340-500 A340 – AA340 – AA340 – AA340-500 A340 200 A340-500 A340 – AA340-200 A340-500 A340-500 A340-200 A340 – AA340-500 A340-500 A340-500 A340-500 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-5  EASA APPROVED 

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

CDCCL 

REF. CDCCL REQUIREMENTS REFERENCE LIMITATI

28-43-51-400 28-43-53-400 57-27-11-400 

A340 – AA340 – AA340 – A

 4 Safety critical features of 

fuel pumps. 

These features must be maintained throughout the full life of the fuel pump to avoid the possibility of generation of an ignition source by overheating or sparks caused by arcing, friction etc. Repair and overhaul of fuel pumps must be carried out in accordance with the equipment manufacturer’s maintenance instructions or other maintenance instructions acceptable to the certifying authority. 

CMM 28-20-40 28-20-51 28-21-50 28-21-55 28-21-59 28-22-11 28-22-12 

A340-200 A340-500 A340-200 A340 – AA340-500 A340 – AA340-200 

 5 Centre fuel tank volume, 

ventilation and flow rate. 

The volume of the Centre fuel tank and the flow rate of the ventilation system must be maintained at values which, when used in the determination of the fuel tank flammability exposure, comply 

with the Flammability Reduction System (FRS) requirements. 

N/A A340-200 

POST MOA340-500 POST MO

 6 Protective coating on fuel 

tank at the connection of 

A protective coating (Finch paint) is necessary at the connection between the centre fuel tank and the Dual Flapper Check Valves 

AMM A340-200 

POST MO
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-5  EASA APPROVED 

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

CDCCL 

REF. CDCCL REQUIREMENTS REFERENCE LIMITATI

fuel tank inerting system. (DFCV) housing of the Inert Gas Generating System (IGGS) to 

prevent fuel or fuel vapour leaks into an area containing ignition sources. After maintenance of the DFCV the protective coating must be restored to the appropriate standard using the method stated within the maintenance procedure in the AMM. 

47-20-43-710 47-21-43-710 

A340-500 POST MO

 7 Warning Placards for 

areas that may contain oxygen depleted atmospheres. 

When a Flammability Reduction System is installed, the access doors and panels to the fuel tank(s) and any other enclosed areas that could contain hazardous atmosphere under either normal conditions or failure conditions must be permanently stencilled, marked, or placarded to warn of hazards. Warning placards must be installed in the appropriate positions to ensure maintenance personnel are aware of areas that may be 

hazardous because of possible oxygen depleted atmosphere. 

AMM 25-52-00-000 25-52-00-400 28-12-52-000 57-17-11-000 57-17-00-400 

A340-200 POST MOA340-500 POST MO

 8 Flammability Reduction 

System (FRS) design performance 

Flammability reduction system performance is dependent on airplane descent times. Industry efforts to reduce descent time may result in Flammability Reduction System performance that does not 

N/A FAA only 

A340-200 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 16/11 ALS PART 5-5  EASA APPROVED 

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

CDCCL 

REF. CDCCL REQUIREMENTS REFERENCE LIMITATI

meet FAA requirements. Fleet average flammability exposure for the fuel tanks with flammability reduction system of this airplane type must be maintained in accordance with 14 CFR Part 25, appendix M. Airbus will monitor descent statistics (including US descents) and, if necessary to maintain compliance, will publish service information. If Airbus publishes such service information, this CDCCL requires that Operators implement these FAA approved design changes to maintain compliance with 14 CFR Part 25, appendix M. 

POST MOA340-500 POST MO

(1) “FAA only” term in the limitation applicability means that all aircraft operated under FAA registration or airc

Airworthiness Authority which follow FAA rules, have to comply with this limitation. It is the operator’s responsibilapplicability with the authority of the state of aircraft registration. Note: The CDCCL Ref. 8 does not require individual Operators to monitor descent rates of their fleets. Airbus will m

and provide any needed service instructions to Operators. To prevent increasing flammability exposure abovCDCCL requires Operators to incorporate future Airbus published service instructions denoted to maintaCDCCL, or other approved actions, within the compliance times stated in the service instructions. 

END OF SUB-PART 5-5 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

HISTORY FILE

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

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

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. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

HISTORY FILE

ISSUE: NOV 16/11 ALS PART 5 HISTORY FILE PAGE: 2/4 

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

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). 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

HISTORY FILE

ISSUE: NOV 16/11 ALS PART 5 HISTORY FILE PAGE: 3/4 

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

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. 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

HISTORY FILE

ISSUE: NOV 16/11 ALS PART 5 HISTORY FILE PAGE: 4/4 

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

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.