A300
- 600 AIRWORTHINESS LIMITATIONS SECTION

REVISION: 0 0 

# 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 th an that for which it is supplie d

.A300
- 600 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
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- 600 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
- 4A300
- 600 AIRWORTHINESS LIMITATIONS SECTI ON ALS PART 5 FUEL AIRWORTHINESS LIMITATIONS RECORD OF REVISIONS

ISSUE: MAY 27/14 ALS PART 5 PAGE: 1
- ROR EASA APPROVED © AIRBUS SAS 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 A300
- 60 0 ALS Part 5 R evision 00 is covered by the Certification Document s 00K05 00 M095/M31 issue 0 3 and 00X0500M095/M31 issue 0 3

. Revision 0 0 is a pproved by EASA under reference 10049247

. REVISION 00 COMPLIANCE TIME: 1. I t is mandatory to comply with instructions and airworthiness l imitations defined in the A300
- 600 ALS Part 5 R evision 00 from MA Y 2 7 /15

. 2. From MAY 27/14 t o MAY 2 6 /1 5 , it is mandatory to comply with the instructions and airworthiness limitations defined, either:

- In the A300
- 600 Fuel Airworthiness Limitations Docu ment ref. 95A.1929 /05 at issue 0 2 and in the A300
- 600 ALS Variation to FAL Doc issue 02 ref. 0CVLG110007/C0S issue 01

. Or

- In the A300
- 600 ALS Part 5 at Revision 00.A300
- 600 AIRWORTHINESS LIMITATIO NS 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 cont ained 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 r egistry

.
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 Proce ss 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 / Monit ored Parts, structural Airworthiness Limitation Items (ALI) and systems Certification Maintenance Requirements (CMR) comprise the Airworthiness Limitation Section which satisfies the requirements of F AR 25.1529 Appendix H paragraph 25.4. IMPORTANT: At firs t 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.A300
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ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 2
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. B. ALS P art 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)

A300B4 - 600 A300B4
- 601
89000 FH 51000 FC A300B4
- 603 A300B4
- 605R A300B4
- 620 A300B4
- 622 A300B4
- 622R A300C4 - 600 A300C4

- 60 5R Variant F 89000 FH 51000 FC A300C4

- 620 A300F4 - 600 A300F4
- 605R 89000 FH 51000 FC A300F4
- 622R A300F4 - 600ST A300F4
- 608ST 6300 0 FH 36000 FC
Note 1 : 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 s ubsequently 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. Note 2: I n some cases, the applicability section of a limitation may be abbreviated to A300
- 600 or A300
- 600R. A300
- 600 in the limitation applicability means that the applicability is valid for all aircraft models defined in the table above. A300
- 600R in the limitat ion applicability means that the applicability is valid only for A300

- 600 with a trim tank (aircraft models which include suffix R).
C. Reporting Accountable persons or organizations should report to Airbus, any identified condition affecting components list ed 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) accumulate d 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 detec tion and inspection method used.A300
- 600 AIRWORTHINESS LIMITATIO NS SECTION

ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 3
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. D. Sub

- part 5
- 1: Illustrations ALS Sub

- part 5
- 1 pro vides 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 ai rcraft configuration.

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 lim it 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 unde r 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 suspe nd 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 Bull etins 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, inspectio ns, 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. Ap propriate means must be implemented to deter their installation on aircraft pending possible extension of their life limitations.A300
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- 0 PAGE: 4
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. Examples of means are:

− Record keeping system,

− Non
- permanent markings,

− Segregation (items stored separately from those current ly eligible for installation). The ultimate solution is the mutilation beyond repair limits to prevent rework to appear to be airworthy.

F. Sub

- part 5
- 3 : Repetitive maintenance/inspection tasks **The Sub -**  **part 5 -**  **3 is approved by the EASA.**  It is mandatory to per form/repeat the maintenance r equirements listed in Sub - part 5 - 3 at or prior to whichever of the limitations t hreshold/interval (if applicable) occurs first. The sub
- part 5
- 3 identifies repetitive maintenance/inspection tasks at aircraft level. The maintena nce 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 (F light H our , F light C ycle 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 m andatory 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 approv ed 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 reliabili ty 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 task s 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 pe riod 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 sam e aircraft or on similar aircraftA300
- 600 AIRWORTHINESS LIMITATIO NS SECTION

ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 5
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. 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 A uthority (EASA) such that approval, if granted, can be given prior to their use. (1) Fuel ALIs controlled by Flight Hours (FH) Extensions up to 10% or 500FH (whichever is the lesser) may exceptionally be granted on Fuel ALI intervals quoted in terms of flight hours. (2) Fuel ALIs controlled by Flight Cycles (FC or LDGS) Extensions up to 5% or 250FC (whichever is the lesser) may exceptionally be granted on Fuel ALI intervals quoted in terms of flight cycles or landings. (3) Fuel ALIs controlled by Calendar Time (MTHS or MO)

- Where the repeat interval is 12 months or less, extensions up to 10% or 1 month (whichever is the lesser) may exceptionally be granted on Fuel ALI intervals quoted in terms of months.

- Where the repeat interval is greater than 12 months but less than 3 years, extensions up to 2 months may exceptionally be granted.

- Where the repeat interval is 3 years or greater, extensions up to 3 months may exceptionally be granted. 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 interv als 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 app roved 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 instructio ns 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 t o 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.A300
- 600 AIRWORTHINESS LIMITATIO NS SECTION

ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 6
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. 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 repai r embodied that has not been developed under the Design Organization Approval (DOA) Certificate EASA.21J.031 (e.g. under a Supplemental Type Certificate) and which affects the content of the ALS Part 5, the Operator is responsible for obtaining approval by the relevant Airworthiness Authority for any necessary adaptations of the airworthiness limitations. When such an aircraft/a component/an item is transferred from one Owner/Operator to another, the associated approvals and documents indicating the necessa ry 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 limitat ions 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 in tervals, 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 in itial 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 transfe rable 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 acco unt. 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 n oted 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

o n’. Interval: The per iod expressed in usage parameters like FH and/or FC and/or LDG and/or Calendar time between successive accomplishments of a specific task.A300
- 600 AIRWORTHINESS LIMITATIO NS SECTION

ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 7
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. 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 Calend ar 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 appro priate. Inspection aids such 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 Life limitations quoted in Sub

- part 5
- 2 are applicab le 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 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’).A300
- 600 AIRWORTHINESS LIMITATIO NS SECTION

ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 8
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. 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).

B. Sub

- part 5
- 3 : Repetitive maintenance/inspection ta sks The limitations and associated instructions must be applied from:

− The Entry I nto S ervice 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 th e 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 lette r 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 discrim inate 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 w ith 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 p arameters are defined in the paragraph 2 of sub

- part 5
- 0

.A300
- 600 AIRWORTHINESS LIMITAT IONS SECTION

ISSUE: MAY 27/14 ALS PART 5

- 0 PAGE: 9
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. 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 re ference. e. Limitations applicability column Applicability Task applicable to A300
- 600
- xxx POST nnnnn All A300
- 600
- xxx that do have MOD nnnnn embodied A300
- 600
- xxx POST nnnnn OR POST SB A300
- 600
- yy yyyy All A300
- 600
- xxx that do have MOD nnnnn embodied OR All A300
- 600
- xxx that do have SB A300
- 600
- yy - yyyy embodied.
A300
- 600
- xxx POST nnnnn PRE mmmmm All A300
- 600
- xxx that do have MOD nnnnn embodied but that do not have MOD mmmmm embodied. A300
- 600
- xxx POST nnnnn PRE mmmmm A300
- 600
- yyy POST aaaaa PRE b bbbb All A300
- 600
- xxx that do have MOD nnnnn embodied but do not have MOD mmmmm OR A300
- 600
- 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 Airworth iness 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 exp lains 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 t hat may be caused by alterations, repairs, or maintenance actions that Operators are required to comply with.A300
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© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. c. Reference column This column provides a reference to Instruction for Continued Airworthiness where a CDCCL is contained. E.g: Reference to Airc raft 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 perfo rming an installation, a repair or a modification will not compromise the original design criteria and must reflect CDCCL in their internal documentation. d. Applicability column The applicability column gives the specific aircraft series/model and possible a dditional identifier (MOD etc) to allow the identification of those aircraft to which the CDCCL reference applies.

END OF SUB

- PART 5
- 0A300
- 600 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 2 7 /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. 01A300
- 600 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 2 7 /14 ALS PART 5

- 1 PAGE: 2
© AIRBUS SAS 2014 . All rights reserved. Confidential and proprietary document. END OF SU B
- PART 5
- 1 GROUND FAULT INTERRUPTERS

- FIG. 02

### A300
- 600 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 2 7 /14 ALS PART 5

- 2 PAGE: 1 EASA APPROVED © AIRBUS SAS 201 4 . All rights reserved. Confid ential and proprietary document. 

### END OF SUB

- PART 5
- 2 Sub

- part 5
- 2 LIFE LIMIT ATION S

No Life Limited Components have been identifiedA300
- 600 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 2 7/ 14 ALS PART 5

- 3 PAGE: 1 EASA APPROVED © AIRB US SAS 201 4 . All rights reserved. Confidential and proprietary document. END OF SUB

- PART 5
- 3 Sub

- p art 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 sea l

. 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 ind icating 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 F ault Interrupters (GFI s)

. 281800
- 00004
- 1
- F AMM 28
- 18
- 00
- 501 4000 F H A300B4 - 600 (1) POST 13382 A300C4 - 600 (1) POST 13382 A300F4 - 600 (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.A300
- 600 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 27 /14 ALS PART 5

- 4 PAGE: 1 EASA APPROVED © AIRBUS SAS 201 4 . 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. Air Gap between Fuel Quantity Indicator (F QI) probe and tank structure are 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
- 3 1
- 401 28
- 42
- 32
- 401 28
- 42
- 33
- 401 ALL

ALL 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 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 bondi ng 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 ins tallation 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
- 32
- 401 28
- 11
- 33
- 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 28
- 21
- 19
- 401 28
- 21
- 21
- 401 28
- 21
- 36
- 401 28
- 21
- 37
- 401 28
- 24
- 31
- 4 01 ALL

ALL ALL A300 - 600R A300 - 600R A300 - 600 POST 08679 OR POST 08680 ALL A300 - 600R A300 - 600R ALL ALL ALL ALL ALL ALL ALLA300
- 600 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 27 /14 ALS PART 5

- 4 PAGE: 2 EASA APPROVED © AIRBUS SAS 201 4 . All rights reserved. Confidential and proprietary document. END OF SUB

- PART 5
- 4 CDCCL REF. CDCCL REQUIREMENTS REFERENCE LIMITATION APPLICABILITY

3 (continued) 28
- 25
- 15
- 401 28
- 27
- 11
- 401 28
- 27
- 12
- 401 28
- 43
- 21
- 401 ALL

A300 - 600R A300 - 600R 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. Rep air 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 ALL

ALLA300
- 600 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 201 4. All rights reserved. Confidential and proprietary document. 1
- GENERAL

- A300 - 600 Fuel Airworthiness Limitations (FAL) Document issue 1:

First issue of the A300
- 600 Fuel Airworthiness Limitations Document.

- A300 - 600 Fuel Airworthiness Limitations (FAL) Document issue 2: The A300
- 600 FAL Document issue 2 to updat e contents:

- Section 1

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

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

 Task 3 title reworded from “Operational check of low

- level / underfull / calibration sensors” to “Operational check of fuel quantity indicating and level sensing for electrical continuity”.

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

AMM and CMM references.

 CDCCL1:

- 400 changed to pb401 in all AMM references.

 CDCCL2: Ref. to ESPM 20

- 33
- 11 deleted.

 CDCCL3: p4 changed to pb401 in all AMM references. Ref. to AMM 28

- 11
- 21, 28
- 11
- 3 2, 28
- 12
- 34, 28
- 21
- 13, 28
- 21
- 21, 28
- 25
- 15, 28
- 27
- 12 and 28
- 43
- 21 added. Ref to AMM 28

- 27
- 11 deleted.

 CDCCL4: Ref. to CMM 28

- 20
- 40, 28
- 21
- 50 & 28
- 27
- 48 deleted. Ref. To CMM 28

- 09
- 01 and 28
- 24
- 11 added. Note added to define applicability ‘A300

- 600R’

- A30 0 - 600 ALS Part 5 Revision 00:

− A300
- 600 ALS Part 5 R evision 00 i s dedicated to transfer the content of the A300

- 600 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 A300

- 600 FAL Document (issue 2) and the A300

- 600 ALS Part 5 Revision 00. New items: SUB

- PART 5
- 1 ILLUSTRATIONS Illustrations added to reflect ALS part 5 Sub

- Part 5
- 4.A300
- 600 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 201 4. All rights reserved. Confidential and proprietary document. SUB

- PART 5
- 2 LIFE LIMITS No new item introduced. SUB

- PART 5
- 3 REPETITIVE MAINTENANCE/ INSPECTION TASKS Introduction of a new maintenance task and title updated : − Task 281800
- 00004
- 1
- F (POST MOD 13382) SUB

- PART 5
- 5 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/ INSPECT ION TASKS

− AMM references for all tasks have been added. SUB

- PART 5
- 4 CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

− CDCCL No. 3 :

- Ref. AMM task deleted: 28
- 12
- 34 pb401; 28
- 46
- 21pb401

.

- Ref. AMM task Added: 28

- 11
- 41
- 401; 28
- 12
- 35
- 401; 28
- 21
- 12
- 401; 2 8
- 21
- 19
- 401; 28
- 21
- 36
- 401; 28
- 21
- 37
- 401; 28
- 27
- 11
- 401. 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.