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# A318 / A319 / A320 / A321

Fuel Airworthiness Limitations

95A.1931/05 26 Aug 2010

Issue 4

AIRBUS OPERATIONS SAS 2010

. All rights reserved. Confidential and proprie tary document. This document and all information contained herein is the sole property of AIRBUS OPERATIONS SAS. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be repr oduced or disclosed to a third party without the express written consent of AIRBUS OPERATIONS SAS. This document and its content shall not be used for any purpose other than that for which it is supplied

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95A.1931/05 I ssue 4

26

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- 2010 Section ROR Page 1

- ROR

AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT RECORD OF REVISIONS

Issue Date Reason for revision Approved by EASA

1

2

3 19 Dec 05

08 Jul 08

01 Mar 10 First Issue

Section 0: Document applicability updated to include

A320

- 215 a nd A320

- 216

Section 1:

Correction of Fuel ALI 281800

- 01

- 1 task title to be in line with AMM task title (deletion of the words ‘centre box’) Applicability of both tasks clarified (it previously stated ‘ALL’). The words ‘(aircraft fitted with a centre wing tank)’ deleted from both task descriptions.

Section 2: Applicability of CDCCLs clarified by identifying applicability of individual ESPM, AMM and CMM

references.

CDCCL 2: Ref to ESPM 20

- 33

- 11 deleted.

CDCCL 3: Ref to 28

- 42

- 15 deleted. Ref to 28

- 21

- 51, 2 8

- 22

- 51 and 28

- 42

- 47 added.

‘

- 400’ added to all AMM references. CDCCL 4: Applicability ‘ALL’ added.

Section 0

The document introduction is extended to include the latest compliance requirement references for Ignition Prevention and for Flammability Red uction Systems. References to Flammability Reduction requirements included.

Section 1: Maintenance/Inspection Tasks 47

- 00

- 00

- 01

- 1,

47

- 00

- 00

- 02

- 1, 47

- 00

- 00

- 03

- 1, 47

- 00

- 00

- 04

- 1

and 47

- 00

- 00

- 05

- 1 added.

Section 2:

CDCCL 3: Ref to 28

- 12

- 47, 28

- 21

- 43 and 28

- 43

- 22 added

CDCCL 4: Ref to 28

- 20

- 40 and 28

- 24

- 11 added

CDCCL 5: New CDCCL added

CDCCL 6: New CDCCL added

CDCCL 7: New CDCCL added Approved by EASA

under reference

EASA.A.C.02456

on 14 Mar 2006

A pproved by EASA

under reference

EASA.A.C.10876

on 19

- Dec

- 2008.

Approved by EASA

under reference

10029203 REV. 1

on 22

- Mar

- 2010

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- ROR

AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Issue Date Reason for revision Approved by EASA

4 26 Aug 1 0 Section 0:

Categories of Maintenance / Inspection tasks extended to include components having a life

limitatio n. Section 1:

Table 1 added . Valve names in tasks 470000

- 01/02/03/04

- 1 amended from Dual Flow Check Valves to Dual Flapper Check Valves. Applicability of tasks 470000

- 01/02/03/04/05

- 1

amended.

Table 2 added. ASM included in Table 2.

Section 2:

CDCCL 6. Va lve name amended from Dual Check Valve to Dual Flapper Check Valves. A pproved by EASA

under reference

EASA.A.C10031572

on 26

- Aug

- 2010.

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## A318/A319/A320/A321 Fuel Airworthiness Limitations

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- 2010 Section LEP Page 1

- LEP

AIRBUS OPERATIONS SAS 2010

. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT LIST OF EFFECTIVE PAGES

SECTION PAGE DATE

ROR 1 ROR 26

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2 ROR 26

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LEP 1 LEP 26

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95A.1931/05 Issue 4

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AIRBUS OPERATIONS SAS 2010. ALL R IGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT TABLE OF CONTENTS

SUBJECT SECTION N

Introduction 0 Scope Applicability

Criteria for identification Handling of Fuel ALIs Exceptional Short

- Term Extensio ns

Maintenance / Inspection Tasks 1

Critical Design Configuration Control Limitations 2

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95A.1931/05 Issue 4

26

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT SECTION 0

- INTRODUCTION

1. 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, FAA’s Advisory Circular (AC) 25.981

- 1 C and FAA’s Advisory Circular (AC) 25.981

- 2A . The nomenclature and means of promulgation

follow the FAA’s memorandum ref PS

- ANM100

- 2004

- 10029 ‘Policy Statement on Process fo r 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.

This document is referenced in the ALS Part 5

– Fuel Airworth iness Limitations, which, together with other ALS Parts, contributes to the demonstration of compliance with JAR 25, Appendix

H25.

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

requirements given in this docume nt 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 t o 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 w ay 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 Airwor thiness Directives (Consigne de Navigabilité) which, if issued against an existing Fuel Airworthiness Limitation, supersede the specific requirement given in this document.

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 2. APPLICABILITY

The document covers the following A318/A319/A320/A32 1 models:

- A318

- 111

- A319

- 111

- A320

- 111

- A321

- 111

- A318

- 112

- A319

- 112

- A320

- 211

- A321

- 112

- A318

- 121

- A319

- 113

- A320

- 212

- A321

- 131

- A318

- 122

- A319

- 114

- A320

- 214

- A321

- 211

- A319

- 115

- A320

- 215

- A321

- 212

- A319

- 131

- A320

- 216

- A321

- 213

- A319

- 132

- A320

- 231

- A321

- 231

- A319

- 133

- A320

- 232

- A321

- 232

- A320

- 233

3. CRITERIA FOR IDENTIFICATION

Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition’ as defined in FAA’s memo

2003

- 112

- 15 ‘SFAR 88

– Mandatory Action Decision Criteria’. These are identified in Failure Conditions for which an unacceptable probability of ignition risk or an unacceptable increase in fuel tank flammability exposure could exist if specific tasks and/o r practices are not performed in

accordance with this document.

Having identified the need for the task through detailed systems analysis (including th at required for JAR 25.1309 compliance), the repeat interval for any task required on a regular basis was determined through engineering judgment. This judgment was largely based on existing experience of the condition of the component and its installation combined with a desire to avoid tank entry specifically for the purpose of performing a Fuel ALI.

Fuel ALIs fall into two categories:

3.1 Maintenance / Inspection Tasks The repetitive tasks are similar to Certification Maintenance Requirements but since they have been identified after initial certification of the design, in accordance with EASA’s AMC 25

- 19 and

FAA’s AC 25

- 19, they cannot be identified as CMRs. Th ese tasks are listed in Table 1.

Fuel ALIs may include life limitations. These are associated with components that exhibit functional degradation characteristics at an identifiable age and whose failure could contribute to an unsafe condition of the aircraft or lead to an inability to maintain system performance to

certification levels. These task s are listed in Table 2, thus ensuring a common approach with

those items with life limitations identified in ALS Parts 1 & 4.

These tasks must be included in an operator’s approved maintenance program/ schedule. The

ta sk interval may be quoted in a usage parameter (FH, FC or Calendar time) depending on the cause of potential degradation that, if not detected and addressed, could lead to an unacceptable risk.

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 3.2 Critical Design Configuration Control Limitations (CDCCL)

A CDCCL is a limitation requirement to preserve either a critical ignition source prevention feature of the fuel system design or a critical design feature of the flammability reduction 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 or critical flammability reduction feature during configuration change that may be caused by alterations, repairs, or maintenance actions.

A critical ignition source prevention featur e may exist in the fuel system and related installation or in systems that, if a failure condition were to develop, could interact with the fuel system in such a way that an unsafe condition would develop in the fuel system without this

limitation.

A crit ical feature that contributes to the integrity of the flammability reduction system may exist in the fuel tank inerting system and related installation that, if not maintained, could compromise the design and lead to an unsafe condition in the fuel system.

4. HANDLING OF FUEL ALIs

4.1. Maintenance / Inspection Tasks

4.1.1 Table 1

- Repetitive Tasks

Unless otherwise stated, the tasks and intervals specified in Table 1 of the Fuel Airworthiness

Limitation document are mandatory and cannot be changed, escalat ed or deleted without the concurrence of the Primary Certification Authority (EASA).

Where explicitly stated, t ask intervals may be adjusted in accordance with an operator's approved escalation practices or an approved reliability program, but the task c ontent 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.

Furthermore, 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. Tank entry specifical ly to accomplish a Fuel ALI should be avoided in view of the fact that degradation could be caused by the human intervention in a restricted zone. Such tank entries need to be kept to a minimum.

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 4.1.2 Table 2

- Life Limits

For those Fuel ALIs associated wi th a component with a life limitation, listed in Table 2, the recurrent maintenance requirements are applicable no later than the component, not the aircraft, reaching the airworthiness limitation.

In order to maintain aircraft airworthiness, it is mandat ory to replace components/items listed in Table 2 at, or prior to, whichever of the life limitations occurs first (if applicable), after any necessary adjustment of the stated life limitations.

It is necessary therefore, to assure traceability and monitor ing of the components/items listed

in the Table 2.

Non

- compliance with these requirements could suspend the validity of the Certificate

of Airworthiness.

For a given component/item of the Table 2, new Part Numbers (PNRs) may be introduced in

the future. These new PNRs may not be listed in the Table 2 of the current revision of the

ALS Part 5. However, it is recommended to maintain traceability and monitoring of such components/items whatever their Part Number in case of future introduction in the ALS Part

5.

Note: In the context of the ALS Part 5, traceability means records that clearly

demonstrate the history of components/items back to initial entry into service, so that airworthiness limitations are accurately applied. Traceability records may comprise , but are not limited to, the following: Application history (aircraft type, model, WV, MSN i.e. Manufacturer Serial Number, etc), Maintenance actions carried out (Airworthiness Directives, modifications, repairs, inspections, etc) Life accumulation (accou nting for any individual aircraft to which a component/an item may have been fitted).

4.2.1 CDCCLs

Operators are responsible for ensuring that their internal documentation is amended to reflect the data contained within this section and provides appropriate t ext 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 modifica tion.

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 5. EXCEPTIONAL SHORT

- TERM EXTENSIONS

This paragraph addresses repetitive Maintenance/Inspection tasks identified in Table 1. It does not apply to component life limitations identified in Table 2.

Since Fuel ALI Maintenance / Inspection interva ls listed in Table 1, are generally not determined from calculations in which failure rate data is known with a high level of confidence, 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 ai rcraft 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 Of fice (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.

5.1 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 hou rs.

5.2 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.

5.3 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 les s 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 h is 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

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 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.

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### 1

AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 

### SECTION 1

MAINTENANCE / INSPECTION TASKS

TABLE 1

– Repetitive Tasks

TASK REF TASK TITLE INTERVAL APPLICABILITY

1 281800

- 01

- 1 Functional check of tank vapour seal and vent

drain system. 6 Years A318 ALL

A319 ALL

A320 Post 20024

A321 ALL

2 281800

- 02

- 1 Detailed inspection of vapour seal. 6 Years A318 ALL

A319 ALL

A320 Post 20024

A321 ALL

3 470000

- 01

- 1 Operational Check of DFSOV, Dual Flapper

Check Valves and NEA line for leaks. 12,000 FH Post 38062

Or

Post SB 47

- 1002

Or

Post SB 47

- 1004

4 470000

- 02

- 1 Operational Check of both Dual Flapper Check

Valves for leak s. 60,000 FH Post 38062

Or

Post SB 47

- 1002

Or

Post SB 47

- 1004

5 470000

- 03

- 1 Operational Check of Dual Flapper Check Valves

for reverse flow and NEA line for leaks. 12,000 FH Post SB 47

- 1001

Pre SB 47

- 1002

Or

Post SB 47

- 1003

Pre SB 47

- 1004

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### 2

AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 

### MAINTENANCE / INSPECTION TASKS

TABLE 1

– Repetitive Tasks (continued)

In accordance with Section 0, para 4.1, it is herewith confirmed that the intervals of the tasks mentioned in the above table 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 with out prior Primary Certification Authority (EASA) approval.

TABLE 2

– Life Limits TASK REF TASK TITLE INTERVAL APPLICABILITY

6 470000

- 04

- 1 Operational Check of Dual Flapper Check Valves

for reverse flow 12,000 FH Post 38195

Pre SB 47

- 1002

Or

Post 38195

P re SB 47

- 1004

7 470000

- 05

- 1 Remove ASM and return to Vendor for workshop

check 4,000 FH Post 38062

Pre 151529 (SB 47

- 1005)

Or

Post SB 47

- 1002

Pre 151529 (SB 47

- 1005)

Or

Post SB 47

- 1004

Pre 151529 ( SB 47

- 1005)

COMPONENT PART NUMBER (P/N) LIFE LIMITATION APPLICABILITY

Note: ‘XX’ at the end of the P/N stands for any number between 00 and 99 Air Separation Module (ASM) 206 0017

- 1XX 27000 FH (component flying hours) Post 38062

Post SB 47

- 1002

Post SB 47

- 1004

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT SECTION 2

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL Requirement Reference Applicability

1 Air gap between a fuel quantity indicating probe and

the aircraft structure. Critical to prevent spark generation during lightning strike conditions and must not be compromised

The gap stated in the relevant maintenance procedure in the AMM must be achieved during installation of a fuel quantity probe. AM M

28

- 42

- 15

- 400 ALL

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 o bey 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 t o 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 th e installation procedure in the AMM. AMM

28

- 11

- 37

- 400

28

- 11

- 41

- 400

28

- 12

- 41

- 400

28

- 12

- 45

- 400

28

- 12

- 46

- 400

28

- 12

- 47

- 400

28

- 13

- 43

- 400

28

- 15

- 41

- 400

28

- 21

- 42

- 400

28

- 21

- 43

- 400

28

- 21

- 51

- 400

28

- 21

- 52

- 400

28

- 22

- 51

- 400

28

- 25

- 41

- 400

28

- 25

- 42

- 400

28

- 25

- 46

- 400

28

- 25

- 52

- 400

28

- 42

- 16

- 400

28

- 42

- 46

- 400

28

- 42

- 47

- 400

28

- 42

- 48

- 400

28

- 43

- 21

- 400

28

- 43

- 22

- 400

57

- 27

- 11

- 400 A321 Post 25453

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL

ALL
A318, 19, 20

A321

A321

A321

ALL

ALL

ALL

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AIRBUS OPERATIONS SAS 2010. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT CDCCL Requirement Reference Applicability

4 Safety critical

features of f uel

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

- 21

- 51

28

- 22

- 19

28

- 24

- 11 A319, 20, 21

(with ACT)

ALL

ALL

ALL

5 Centre fuel tank

vo lume and

ventilation 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 fuel tank inerting syst em requirements. N/A Post 38062

Or

Post SB 47

- 1002

Or

Post SB 47

- 1004

6 Protective coating

on fuel tank at the

connection of fuel tank inerting system A protective coating (Finch paint) is necessary at

the connection between the centre fuel tank and the

dual flapper check valve s ’ 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 dual flapper check valve s the protective coating must be restored to the appropriate standard using the method stated within the maintenance procedure in the AMM. AMM

47

- 20

- 43

- 400

47

- 20

- 43

- 700 Post 38062

Or

Post 38195

Post 38196

Or

Post 150499

Post 150500

Or

Post SB 47

- 1001

Post SB 47

- 1002

Or

Post SB 47

- 1003

Post SB 47

- 1004

7 Warning Placards for areas that may contain oxygen depleted atmospheres. Warning placards installed to ensure maintenance personnel are aware of areas that may be hazardous because of possible oxygen depleted atmosphere, must be ensured to be present in t he designated positions AMM

57

- 17

- 11

- 000

57

- 17

- 11

- 400

28

- 12

- 47

- 000

28

- 12

- 47

- 400 Post 150837