A310 AIRWORTHINESS LIMITATIONS SECTION

REVISION: 00 

ALS Part 5

- 

Fuel 

Airworthiness Limitations 

© AIRBUS SAS 2014. 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. 
A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE 

ISSUE: MAY 27/14 ALS PART 5 PAGE: 1-LEP

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

5 R 1-LEP MAY 27/14

5 R 1-TOC MAY 27/14

5 R 1-ROR MAY 27/14

5-0 N 1 MAY 27/14

5-0 N 2 MAY 27/14

5-0 N 3 MAY 27/14

5-0 N 4 MAY 27/14

5-0 N 5 MAY 27/14

5-0 N 6 MAY 27/14

5-0 N 7 MAY 27/14

5-0 N 8 MAY 27/14

5-0 N 9 MAY 27/14

5-0 N 10 MAY 27/14

5-1 N 1 MAY 27/14

5-1 N 2 MAY 27/14

5-2 R 1 MAY 27/14 

5-3 R 1 MAY 27/14

5-4 R 1 MAY 27/14

5-4 R 2 MAY 27/14
A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

TABLE OF CONTENTS

SUBJECT PART

ISSUE: MAY 27/14 ALS PART 5 PAGE: 1-TOC

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

RECORDS OF REVISIONS ROR

INTRODUCTION 5-0 

ILLUSTRATIONS 5-1 

LIFE LIMITATIONS 5-2 

REPETITIVE MAINTENANCE/INSPECTION TASKS 5-3 

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS 5-4 
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5 PAGE: 1-ROR

© AIRBUS SAS 2014. 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 

MAY 27/14

Note: The A310 ALS Part 5 Revision 00 is covered by the Certification Document 

00X0500M095/M41 issue 03 

Revision 00 is approved by EASA under reference 10049247. 

REVISION 00 COMPLIANCE TIME:

1. It is mandatory to comply with instructions and airworthiness limitations defined in the A310

ALS Part 5 Revision 00 from May 27/15.

2. From MAY 27/14 to May 26/15, it is mandatory to comply with the instructions and 

airworthiness limitations defined, either: 

- In the A310 Fuel Airworthiness Limitations Document ref. 95A.1930/05 at issue 02 and 

in the A310 ALS Variation to FAL Doc issue 02 ref. 0BVLG110006/C0S issue 01 

Or

- In the A310 ALS Part 5 at Revision 00.
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 1 

© AIRBUS SAS 2014. 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 Part 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 FAR 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.
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 2 

© AIRBUS SAS 2014. 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 Flight Hours (FH) Flight Cycles (FC)

A310-200

A310-203 85000 FH 40000 FC

A310-204

A310-221 116000 FH 45000 FC

A310-222

A310-200C A310-203C 85000 FH 40000 FC

A310-300

A310-304

116000 FH 45000 FC

A310-308

A310-322

A310-324

A310-325

Note: The limitations published in this document have been identified in 

consideration of a maximum individual aircraft utilization as detailed 

above. Depending on fleet leader operation, the impact of a greater 

aircraft utilization may subsequently be investigated which might 

demonstrate a need for new or revised limitations. As a consequence, 

should any operator envisage future aircraft operations beyond the quote 

utilization values, they must first contact Airbus for advice.

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 5-3 are performed.

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

for illustrations applicable to an actual aircraft configuration. 
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 3 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

E. Sub-part 5-2: Life limitations 

The Sub-part 5-2 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 5-2 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 5-2. 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...),

− 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 5-2 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.
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 4 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

F. Sub-part 5-3: Repetitive maintenance/inspection tasks

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

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

5-3 at or prior to whichever of the limitations threshold/interval (if applicable) 

occurs first.

The sub-part 5-3 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 5-3 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.

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 Authority (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 Authority (EASA) 

such that approval, if granted, can be given prior to their use.
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 5 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

(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.

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.

G. Sub-part 5-4: Critical Design Configuration Control Limitations

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

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

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

unsafe condition. The purpose of the CDCCL is to provide instructions to retain the 

critical ignition source prevention 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.

H. 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 
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 6 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

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.

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 
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 7 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

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

cleaning and elaborate access procedures may be required.

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 Limitations 

Life limitations quoted in Sub-part 5-2 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: 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).
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 8 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

B. Sub-part 5-3: 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 5-3 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.

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.

Note: “FAA ONLY” term in the description column 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.

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 sub-part 5-0. 

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.
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 9 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

e. Limitations applicability column

Applicability Task applicable to

A310 -xxx

POST nnnnn All A310 -xxx that do have MOD nnnnn embodied

A310 -xxx

POST nnnnn

OR

POST SB A310-yy-yyyy

All A310-xxx that do have MOD nnnnn embodied OR All A310-xxx that do

have SB A310-yy-yyyy embodied.

A310-xxx

POST nnnnn

PRE mmmmm

All A310-xxx that do have MOD nnnnn embodied but that do not have MOD 

mmmmm embodied.

A310-xxx

POST nnnnn

PRE mmmmm

A310-yyy

POST aaaaa

PRE bbbbb

All A310-xxx that do have MOD nnnnn embodied but do not have MOD 

mmmmm OR A310-yyy that do have MOD aaaaa but do not have MOD 

bbbbb embodied.

C. Sub-part 5-4: CDCCL

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

5-4. 

a. CDCCL column

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

fuel tanks. 

Note: “FAA ONLY” term in the CDCCL column 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.

b. Requirements column

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

of the fuel tanks are considered critical with regards to ignition risk. This column 

provides instructions to retain the critical ignition source prevention design 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).

Note: This reference is for guidance only. Operators are required to be compliant 

with the instruction provided in the column “Requirements”.

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.
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-0 PAGE: 10

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

d. Applicability column

The applicability column gives the specific aircraft series/model and possible 

additional identifier (MOD etc) to allow the identification of those aircraft to which 

the CDCCL reference applies.

END OF SUB-PART 5-0
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-1 PAGE: 1 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

Sub-part 5-1 ILLUSTRATIONS

CENTER TANK VAPOUR SEAL - FIG. 01
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-1 PAGE: 2 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

GROUND FAULT INTERRUPTERS - FIG. 02

END OF SUB-PART 5-1
A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 27/14 ALS PART 5-2 PAGE: 1 

EASA APPROVED

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

END OF SUB-PART 5-2

Sub-part 5-2 LIFE LIMITATIONS 

No Life Limited Components have been identified
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: May 27/14 ALS PART 5-3 PAGE: 1 

EASA APPROVED 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document. 

END OF SUB-PART 5-3

Sub-part 5-3 REPETITIVE MAINTENANCE/INSPECTION TASKS 

ALS PART 5 REPETITIVE MAINTENANCE/INSPECTION TASKS

REFERENCE INTERVAL APPLICABILITY

Description FAL reference number

CENTER TANK VAPOUR SEAL – FIG. 01

Functional check of center tank vapour seal.

281800-00001-1-F AMM

28-18-00-501

6 YE ALL

CENTER TANK VAPOUR SEAL – FIG. 01

Detailed inspection of center tank vapour seal.

281800-00002-1-F AMM

28-18-00-601

6 YE ALL

FUEL QUANTITY INDICATING AND LEVEL SENSING 

Operational check of fuel quantity indicating and level sensing for electrical 

continuity.

281800-00003-1-F AMM

28-18-00-501

40000 FH ALL

FAA ONLY

GROUND FAULT INTERRUPTERS – FIG. 02

Operational Check of the Fuel Pump Ground Fault Interrupters (GFIs).

281800-00004-1-F AMM

28-18-00-501

4000 FH ALL (1)

POST 13382

(1) Only 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.
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: May 27/14 ALS PART 5-4 PAGE: 1 

EASA APPROVED 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document. 

Sub-part 5-4: CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS 

CDCCL

REF. CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITY

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

28-42-31-401

28-42-32-401

28-42-33-401

28-42-61-401

ALL

ALL

ALL

A310-300

POST 06920

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

ALL

ALL

ALL

ALL

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

28-00-00-401

28-11-21-401

28-11-22-401

28-11-24-401

28-11-28-401

28-11-31-401

28-11-32-401

28-11-33-401

28-11-37-401

28-11-41-401

28-12-21-401

28-12-33-401

28-12-35-401

28-21-12-401

28-21-13-401

ALL

ALL

ALL

ALL

ALL

ALL

A310-300

A310-300

A310-300

POST 06920

A310-300

POST 08679

OR

POST 08681

ALL

A310-300 (1)

A310-300

ALL

ALL
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: May 27/14 ALS PART 5-4 PAGE: 2 

EASA APPROVED 

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document. 

END OF SUB-PART 5-4

CDCCL

REF. CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITY

3

(Continued)

28-21-19-401

28-21-21-401

28-21-36-401

28-21-37-401

28-24-31-401

28-25-15-401

28-27-11-401

28-27-12-401

28-28-14-401

28-43-21-401

ALL

ALL

ALL

ALL

ALL

ALL

A310-300

A310-300

A310-300

POST 06919

ALL

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

28-09-01

28-24-11

28-20-40

ALL

ALL

A310-300

POST 06919

(1) This task is also applicable to the following A310-200 aircraft: MSN's 419, 427, 454. Although certificated as A310-200, the fuselage, centre wing 

and outer wing structure is basically identical to the A310-300. 
A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

HISTORY FILE

ISSUE: May 27/14 ALS PART 5 HISTORY FILE PAGE: 1/2

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

1- GENERAL

- A310 Fuel Airworthiness Limitations (FAL) Document issue 1:

First issue of the A310 Fuel Airworthiness Limitations Document.

- A310 Fuel Airworthiness Limitations (FAL) Document issue 2:

The A310 FAL Document issue 2 to update contents:

- Section 1

 Task 2 title reworded from “Detailed inspection of vapour seal / drip shield” to 

“Detailed inspection of center tank vapour seal”.

 Task 3 title reworded from “Operational check of lo-level / underfull / calibration 

sensors” to “Operational check of fuel quantity indicating and level sensing for 

electrical continuity”.

- Section 2: Applicability of CDCCLs clarified by identifying applicability of individual ESPM, 

AMM and CMM references.

 CDCCL1: pb401 added to AMM references in place of –400.

 CDCCL2: Ref to ESPM 20-33-11 deleted.

 CDCCL3: -pb401 added to AMM references in place of p4. Ref to AMM 28-13-12 

deleted, ref. to AMM 28-11-21 pb 401, 28-11-32 pb 401, 28-12-33 pb 401, 28-12-

34 pb 401, 28- 21-13 pb 401, 28-21-21 pb 401, 28-24-31 pb 401, 28-27-12 pb 401, 

28-43-21 pb 401 & 28-46-21 pb 401 added.

 CDCCL4: Ref. to CMM 28-20-40, 28-21-50 & 28-27-48 deleted. Ref to CMM 28-

09-11 & 28-24-11 added.

- A310 ALS Part 5 Revision 00:

 A310 ALS Part 5 revision 00 is dedicated to transfer the content of the A310 FAL Document 

issue 2 into the subject document.

 A new limitation resulting from the installation of Ground Fault Interrupters (GFI) has been 

added.

2- SUMMARY OF CHANGES:

The following summarizes the changes between the previous issue A310 FAL Document issue 

2 and the A310 ALS Part 5 Revision 00.

New items:

SUB-PART 5-1 ILLUSTRATIONS

Illustrations added to reflect ALS part 5 Sub-Part 5-3.

SUB-PART 5-2 LIFE LIMITS

No new item introduced.
A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 5

FUEL AIRWORTHINESS LIMITATIONS

HISTORY FILE

ISSUE: May 27/14 ALS PART 5 HISTORY FILE PAGE: 2/2

© AIRBUS SAS 2014. All rights reserved. Confidential and proprietary document.

SUB-PART 5-3 REPETITIVE MAINTENANCE/ INSPECTION TASKS

Introduction of a new maintenance task:

− Task 281800-00004-1-F (POST 13382)

SUB-PART 5-4 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS 

No new CDCCL introduced.

Amendments:

SUB-PART 5-1 ILLUSTRATIONS:

None.

SUB-PART 5-2 LIFE LIMITS

None.

SUB-PART 5-3 REPETITIVE MAINTENANCE/ INSPECTION TASKS

AMM references for all tasks have been added.

SUB-PART 5-4 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

 CDCCL No. 1:

- AMM task ref. added: 28-42-61-401.

 CDCCL No. 3:

- AMM task ref. deleted: 28-12-34 pb 401; 28-46-21 pb 401.

- AMM task ref. added: 28-11-28-401; 28-11-31-401; 28-11-33-401; 

28-11-37-401; 28-11-41-401; 28-12-35-401; 28-21-12-401; 28-21-

19-401; 28-21-36-401; 28-21-37-401; 28-27-11-401; 28-28-14-401.

 CDCCL No. 4:

- CMM ref. added: 28-20-40.

Deletions:

SUB-PART 5-1 ILLUSTRATIONS

None.

SUB-PART 5-2 LIFE LIMITS

None.

SUB-PART 5-3 REPETITIVE MAINTENANCE/ INSPECTION TASKS

None.

SUB-PART 5-4 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

None.