A310 AIRWORTHINESS LIMITATIONS SECTION

REVISION: 00 

# ALS Part 5

- Fuel Airworthiness Limitation s

© 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 prope rty 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 recipie nt of such document shall comply with the condition s 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 supplie d.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 27/1 4 5-3 R 1 MAY 27/14 5-4 R 1 MAY 27/14 5-4 R 2 MAY 27/14A310 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 LIMIT ATION S 5-2

REPETITIVE MAINTENANCE/INSPECTION TASKS 5-3

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

ISSUE: May 2 7 /14 ALS PART 5 PAGE: 1- ROR

© AIRBUS SA S 2014 . All rights reserved. Confidential and proprietary document. The Europe an Aviation Safety Agency (EASA) Certification Dir ectorate 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 AL S Part 5 R evision 00 is covered by the Certification Document 00 X0500M095/M41 issue 03

Revision 0 0 is a pproved by EASA under referenc e 10049247

. REVISION 00 COMPLIANCE TIME:

1. I t is mandatory to comply with instructio ns and airworthiness limitations defined in the A310 ALS Part 5 R evision 00 from May 2 7 /15.

2. From MAY 27/14 t o May 2 6 /15 , it is mandatory to comply with the instructions and airworthiness limitations defined, either:

- In the A310 Fuel Airworthiness Limitations Docu ment ref. 95A.1930 /05 at iss ue 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 2 7 /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
o perate 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 th e 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 draf t 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 M aintenance 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 oper ator’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 i n 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 do cument 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 2 7 /14 ALS PART 5 -0 PAGE: 2

© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. B. ALS P art 5 Applicability The ap plicability 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 116000 FH 45000 FC A31 0

- 221 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 indi vidual 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 op erator 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. “E ndanger 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 a ffected 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 co nfiguration.A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /14 ALS PART 5 -0 PAGE: 3

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

- part 5 -2 : Life limit ation s **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

- par t 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 va lidity 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 conta ct 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 eligibl e 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 2 7 /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 r equirements 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 require ments 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 (F light H our , F light C ycle or Calenda r 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. Exception al 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 tim e 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 (E ASA) such that approval, if granted, can be given prior to their use.A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /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) Fu el 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)

- Wher e 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 regulato ry 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 p ermissible. 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 o perator ’ 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, alteratio n, 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 theA310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /14 ALS PART 5 -0 PAGE: 6

© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. rele vant 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 adapta tions 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 C alendar 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 fu n ction. Note: Unless otherwise stated, this means for transferable com ponents/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. Cale ndar 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 interval s between ‘wheels

- off’ and ‘wheels

on’. 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. Detai led 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 suchA310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /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 L ife L imitation s 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 o perator’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 restriction s 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 2 7 /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 li m it ations 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 d efined 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 2 7 /14 ALS PART 5 -0 PAGE: 9

© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. e. Limitati ons 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. S ub

- 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 iden ti fies 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 limi tation. 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 tan ks a re considered critical with regards to ignition risk. This column provides instructions to retain the critical ignition source prevention design feature s 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). N ote: 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 t he original design criteria and must reflect CDCCL in their internal documentation.A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /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 ai rcraft to which the CDCCL reference applies.

END OF SUB

- PART 5

- 0A31 0 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /14 ALS PART 5 -1 PAGE: 1

© AIRBUS SAS 201 4 . All rights reserved. Confidential and proprietary document. Sub

- part 5- 1 ILLUSTRATIONS

CENTER TANK VAP O UR SEAL

- FIG. 01A31 0 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /14 ALS PART 5 -1 PAGE: 2

© AIRBUS SAS 201 4 . All rights reserved. Confidential and proprietary document. GROUND FAULT INTERRUPTERS

- FIG. 02

END OF SUB

- PART 5

- 1

### A31 0 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: May 2 7 /14 ALS PART 5-2 PAGE: 1 EASA APPROVED © AIRBUS SAS 201 4 . All rights re served. Confidential and proprietary document. 

### END OF SUB

- PART 5

- 2 Sub

- part 5-2 LIFE LIMIT ATION S

No Life Limited Components have been identifiedA31 0 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 se al

. 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

- 6 01 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 4 000 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 a pplicability 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. C ritical to prevent spark generation durin g 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 AL L 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 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 t ank. 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 met hod 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
- 30 0 (1) A310
- 300 ALL ALLA310 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 069 19 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 ig nition 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 certi fying authority. CMM 28

- 09

- 01 28

- 24

- 11 28

- 20

- 40 ALL

ALL A310
- 300 POST 069 19

(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 2 7 /14 ALS PAR T 5 HISTORY FILE PAGE: 1 / 2

© AIRBUS SAS 201 4 . 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:

- Sect ion 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 f uel 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 40 1, 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 i s dedicated to transfer the content of the A310 FAL Do cument 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 2 7 /14 ALS PAR T 5 HISTORY FILE PAGE: 2 / 2

© AIRBUS SAS 201 4 . 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; 2 8

- 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

- 3 5

- 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.