A330 AIRWORTHINESS LIMITATIONS SECTION 

REVISION: 04 

ALS Part 4 

- 

Ageing Systems Maintenance 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

This document and all information contained herein is the sole property of AIRBUS SAS. No 

intellectual property rights are granted by the delivery of this document or the disclosure of its 

content. This document shall not be reproduced or disclosed to a third party (except for the 

purposes of performing the tasks described hereunder and provided that any recipient of such 

document shall comply with the conditions herein) without the express written consent of AIRBUS 

SAS. This document and its content shall not be used for any purpose other than that for which it is 

supplied. 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

ISSUE: AUG 27/13 ALS PART 4 PAGE: 1-LEP 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

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A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

TABLE OF CONTENTS 

SUBJECT PART

ISSUE: NOV 04/08 ALS PART 4 PAGE: 1-TOC 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

RECORD OF REVISIONS ROR 

INTRODUCTION 4-0 

ILLUSTRATIONS 4-1 

SYSTEMS LIFE-LIMITED COMPONENTS 4-2 

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 4-3 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: AUG 27/13 ALS PART 4 PAGE: 1-ROR 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

The European Aviation Safety Agency (EASA) Certification Directorate approves the 

ALS Part 4. Variations must also be approved (unless justified in accordance with a 

procedure stated herein). 

 

REVISION 

NUMBER SUB-PARTS APPROVED BY EASA EASA AD INSERTION IN MAINT. PROG. 

 00 

ROR 

4-2 

4-3 

NOV 04/08 N/A 

01 

ROR 

4-2 

4-3 

MAY 29/09 N/A 

 02 

ROR 

4-2 

4-3 

DEC 16/09 N/A 

R 03 

ROR 

4-2 

4-3 

SEP 09/11 2012-0020 

N 

N 

N 

04 

ROR 

4-2 

4-3 

AUG 27/13 

Note: The ALS Part 4 is covered by the Certification Document 00G050AM094/C01. 

Revision 04 is approved by EASA under reference 10046192. 

REVISION 04 COMPLIANCE TIME:

1. It is mandatory to comply with the maintenance requirements and associated airworthiness 

limitations defined in the sub-part 4-2 and 4-3 of the A330 ALS Part 4 revision 04 from 27-

Aug-2014. 

2. From 27-Aug-2013 to 26-Aug-2014, it is mandatory to comply with the maintenance 

requirements and associated airworthiness limitations defined in, either: 

 The sub-part 4-2 and 4-3 of the A330 ALS Part 4 at revision 03 

or, 

 The sub-part 4-2 and 4-3 of the A330 ALS Part 4 at revision 04. 

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R 

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R 

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A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: AUG 27/13 ALS PART 4 PAGE: 2-ROR 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

3. For tasks where the interval is changed the next accomplishment must be determined from 

previous accomplishment date. 

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A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 1 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Sub-part 4-0 INTRODUCTION

1. GENERAL

The data provided under Part 4 has been established with the following rules: 

Compliance with the requirements contained in this document is mandatory. No 

person may operate an aircraft to which an Airworthiness Limitations Section (ALS) 

applies except in accordance with the requirements of that ALS, unless otherwise 

agreed with the Authority of the State of aircraft registry. 

Consultation with the State of design should be made by the State of aircraft registry, 

in consideration of any deviation from the ALS requirements. This is indicated in the 

International Civil Aviation Organization (ICAO) Airworthiness manual (Doc. 9760), 

Volume II, Part A, Chapter 3. 

The procedures contained therein (ALS) must be taken into account when 

considering any variation requests. 

A. ALS Part 4 applicability 

The applicability of this ALS Part 4 revision is restricted to the aircraft series, models 

and Weight Variants (WV) series listed in the table below: 

 Aircraft series Aircraft models WV 

R 

A330-200 

A330-201 WV020 series, WV050 series, WV060 series 

R A330-202 WV020 series, WV050 series, WV060 series 

R A330-203 WV020 series, WV050 series, WV060 series 

R A330-223 WV020 series, WV050 series, WV060 series 

R A330-243 WV020 series, WV050 series, WV060 series 

R A330-200F A330-223F WV000 series 

R A330-243F WV000 series 

R 

A330-300 

A330-301 WV000 series, WV010 series, WV050 series 

R A330-302 WV050 series 

R A330-303 WV050 series 

R A330-321 WV000 series, WV010 series 

R A330-322 WV000 series, WV010 series 

R A330-323 WV020 series, WV050 series 

R A330-341 WV000 series, WV010 series 

R A330-342 WV000 series, WV010 series, WV020 series, 

R WV050 series 

R A330-343 WV020 series, WV050 series 

Note: The engine Time Limits and Maintenance Checks are not included in this 

manual: Refer to the relevant Engine Manufacturer Chapter 05 manual. 

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A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 2 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

B. Ageing Systems Maintenance (ASM) 

Airbus’ definition of Ageing Systems Maintenance (ASM) primarily refers to 

preventative maintenance requirements (including replacements) and associated 

airworthiness limitations applicable to aircraft systems susceptible to ageing effects. 

Such ageing effects could change the characteristics leading to an increased potential 

for failure, which in isolation or in combination with one or more other specific failures 

or events, could result in an unsafe condition of the aircraft. 

Failure-finding checks (addressing similar unsafe conditions) with airworthiness 

limitations will also be included to complement the mandatory preventative 

maintenance requirements (refer also to ALS sub-part 4-0, paragraph 1.D). 

Note: Items listed in this ALS Part 4 may originate from: 

 Aircraft Maintenance Manual (AMM) chapter 05 Service Life Limits and 

Maintenance Checks (SLMC) section 05-11-00 Service Life Limits, 

subsequently transferred into the A330 ALS Part 1. 

 Life extension study. 

 Continued Airworthiness (operational safety) issues (in-service experience). 

All the maintenance requirements and associated airworthiness limitations indicated in 

this document were defined by a process agreed between AIRBUS and the European 

Aviation Safety Agency (EASA). 

The publication of this document precludes the necessity to publish individual 

Airworthiness Directives (AD) for each listed item and its requirements. 

C. A330 aircraft systems utilisation 

The limitations published in this document have been identified in consideration of a 

maximum number of Flight Hours (FH)/Flight Cycles (FC) that may be accrued by an 

individual aircraft, as follows: 

R Aircraft series Flight Hours Flight Cycles 

 A330-200 series PRE 49144 (3) OR 060000 40000 

R 100000 (2) 33000 (2) 

R A330-200 series POST 49144 (3) 100000 33000 

 A330-200F series 100000 33000 

 

A330-300 series PRE 49144 (3) OR

060000 40000 

N 80000 (1) 20000 (1) 

R 100000 (2) 33000 (2) 

R A330-300 series POST 49144 (3) 100000 33000 

Depending on fleet leader operation, the impact of a greater aircraft accumulated 

FH/FC value may subsequently be investigated and might demonstrate a need for new 

or revised limitations. As a consequence, should any operator envisage future aircraft 

operations beyond the quoted values, they must first contact Airbus for advice. 

R 

R 

D 

R 

D 

N

N 

N 

N

N

N

N 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 3 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

(1) Applies only to aircraft POST MODification (MOD) 58269/Service Bulletin (SB) 

A330-00-3068 R00. 

(2) Applies only to aircraft POST MOD 200103/Service Bulletin (SB) A330-00-3068 

R01. 

(3) Within the context of ALS Part 4, MOD 49144 is used to identify WV050 and 

WV060 series aircraft (Enhanced aircraft) since this modification cannot be 

retrofitted on WV000, WV010 and WV020 series aircraft. 

Note: When different sets of aircraft systems utilisation values are indicated for a given 

aircraft series, no combination of values extracted from different sets is permitted. 

D. ALS Part 3 and ALS Part 4 correlation 

At time of original Type Certification (TC) and Post TC design changes, an appraisal of 

aircraft systems is carried out within the frame of the Systems Safety Assessments. 

This may identify a need to schedule repetitive maintenance tasks within a defined 

interval so as to maintain the required safety objectives for individual failure conditions. 

A subset of these tasks, the majority of which detect latent failures, are identified as 

Certification Maintenance Requirements (CMR). These constitute operational 

limitations and are mandated through their location in the ALS Part 3. 

E. Sub-part 4-2: SYSTEMS LIFE-LIMITED COMPONENTS 

Sub-part 4-2 is approved by the EASA. 

Components/items listed under this sub-part are those affected by a replacement 

requirement associated to a life limitation and whose failure could contribute to an 

unsafe condition of the aircraft. 

For a given PNR, when more than one set of limitations (FH/FC/Calendar time) is 

published for the same application, it is the Operator/MRO’s responsibility to select the 

appropriate set depending on the aircraft utilisation. Combining the limitations from 

different sets is not permitted. 

Sub-part 4-2-1: Life Limits

Components/items listed under this sub-part are those having a life limit due to failure 

during tests and whose failure could result in an unsafe condition of the aircraft. 

Sub-part 4-2-2: Current Demonstrated Lives

Components/items listed under this sub-part are those having a demonstrated life 

limitation, which is temporary waiting for completion of the tests. 

N

N 

R 

N

N

N 

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D 

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D 

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A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 4 

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F. Sub-part 4-3: SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 

Sub-part 4-3 is approved by the EASA. 

The maintenance tasks given in this sub-part includes airworthiness limitations set to 

prevent the aircraft systems failures, which could contribute to an unsafe condition of 

the aircraft. 

Note: Credit may be taken for accomplishment of the Maintenance Review Board 

Report (MRBR) Systems and Powerplant section maintenance tasks, providing 

that they are performed with the same inspection level, at least as frequently as 

the inspection threshold and interval quoted in this document. 

Sub-parts 4-3-1 and 4-3-2 give maintenance requirements and airworthiness limitations 

at component level and aircraft (system) level respectively. 

Sub-part 4-3-1: Controlled at component/sub-assembly level

This sub-part identifies tasks controlled at component/item level. The recurrent 

maintenance requirements are applicable no later than the item, not the aircraft, 

reaching the airworthiness limitation. 

When items given in sub-part 4-3-1 reach the stated airworthiness limitations, the given 

task must be carried out. Any item removed from the aircraft for any reason, (such as 

failure of functional check, degradation of condition, etc) must be replaced by a 

serviceable item, which has not reached the stated airworthiness limitations. 

Sub-part 4-3-2: Controlled at aircraft system level

This sub-part identifies tasks at aircraft level. The recurrent maintenance requirements 

are applicable no later than the aircraft, not the item, reaching the airworthiness 

limitation. 

The tasks listed in sub-part 4-3-2 must be carried out when the aircraft reaches the 

stated airworthiness limitation. Should a failure to reach the task requirements be 

detected, the appropriate trouble-shooting must be carried out and the relevant 

suspected items replaced in accordance with the Aircraft Maintenance Manual (AMM) 

procedures. Following any replacements, the listed tasks must be repeated until a 

successful task recording can be entered. 

G. Traceability and replacement/maintenance requirements 

In order to maintain aircraft airworthiness, it is mandatory to replace 

components/items listed under sub-part 4-2 at or prior to whichever of the life 

limitations occurs first, after any necessary adjustment of the stated life 

limitations. 

It is also mandatory to perform/repeat the maintenance requirements listed in 

sub-part 4-3 at or prior to whichever of the limitations threshold/interval occurs 

first, after any necessary adjustment of the stated airworthiness limitations. 

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 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Airworthiness limitations (including life limitations) must be adjusted as 

necessary in accordance with the instructions of paragraph 1.H. of this ALS subpart 4-0.

Therefore, it is necessary to assure traceability and monitoring of the 

components/items listed in the sub-parts 4-2 and 4-3-1. 

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

Certificate of Airworthiness. 

For a given component/item of the sub-parts 4-2 and 4-3-1, new PNRs may be 

introduced in the future as a result of modifications and/or Airbus Service Bulletin (SB) 

publishes. These new PNRs may not be listed in the sub-parts 4-2 and/or 4-3-1 of the 

current revision of the ALS Part 4. 

However, it is recommended to maintain traceability and monitoring of such 

components/items whatever their PNR in case of future introduction in the ALS 

Part 4. 

For further guidance, Operators are requested to contact Airbus. 

Note 1: In the context of the ALS Part 4, 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 (accounting for any individual aircraft to which a 

component/an item may have been fitted). 

Note 2: Where the partial/complete life history of a component/an item is not known, 

Operators are requested to refer to the applicable SIL for guidance. Such SIL 

provide the means to manage such components/items. They have been 

issued in agreement with the EASA. 

Note 3: Traceability and monitoring of component/item listed in sub-part 4-2 is not 

required for consumable component (for which replacement is controlled at 

assembly/aircraft level). 

In addition to the mandatory traceability and monitoring of the components/items listed 

in the sub-parts 4-2 and 4-3-1, refer to SIL 05-014 for the Recommended Tracking of 

components/items, which could be subject to future Airworthiness Limitation. 

H. Transfers of components/items between aircraft applications 

The airworthiness limitation(s) for a component/item fitted to an application (aircraft 

type, aircraft model, etc...) may be different when this component/item is transferred to 

N

N

N 
A330 AIRWORTHINESS LIMITATIONS SECTION 

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 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

another application. In this case, the component’s/item’s remaining operational life 

must be calculated using the following formula: 

with: 

Tri = component/item’s remaining life for operation on current application i. 

Caj = component/item’s accumulated life on previous application j. 

Cpj = component/item’s airworthiness limitation in previous application j. 

Cpi = component/item’s airworthiness limitation in current application i. 

When a component/item has been installed on an application where the ALS Part 4 

does not impose an airworthiness limitation, the aircraft systems utilisation values (refer 

to ALS sub-part 4-0, paragraph 1.C) of the relevant ALS Part 4 for that application must 

be used. 

Note 1: When using the above formula, Tri, Caj, Cpj, and Cpi are expressed in the 

same usage parameter (FH or FC or landings): Usage parameters cannot be 

mixed in the same calculation. 

Note 2: The remaining life calculation must be reassessed every time the 

component’s/item’s airworthiness limitation(s) change(s) for current and/or 

previous aircraft application(s) to which the component/item is/was fitted. 

I. Disposal/quarantine action 

When the components/items listed in the sub-parts 4-2 and/or 4-3-1 reach the life 

limitations, disposal/quarantine action must be taken depending on the following 

categories: 

For component/item listed in sub-part 4-2-1: They must be mutilated beyond repair 

limits to prevent rework to appear to be airworthy. 

Note 1: Some means may exist to extend their potential life provided they are applied 

prior to reaching the life limit (e.g. Service Bulletin: POST SB PNR in the subpart 4-2-1). 

Note 2: It’s recommended that the organisation that mutilates a component/item 

should provide the original manufacturer with the data plate and/or serial 

number and final disposition of the component to maintain the records of serial 

numbers for “retired” certified life-limited components/items or other critical 

components/items. 

 i Cp

j Cp

j Ca

1 i Tr   

































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ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 7 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

For component listed in sub-part 4-2-2 and/or 4-3-1: Appropriate means must be 

implemented to deter their installation on aircraft pending possible extension of the life 

limitations. Examples of these means are: 

 Record keeping system, 

 Non-permanent markings, 

 Segregation (items stored separately from those currently eligible for installation). 

Note: When components/items are removed by way of a systematic replacement, 

they must be mutilated beyond repair limits to prevent rework to appear to be 

airworthy. 

J. Occurrence reporting 

The ICAO Airworthiness manual (Doc. 9760), Volume II, Part B, Chapter 2 indicates: 

The concept of Continuing Airworthiness includes the reporting of defects and 

other significant maintenance and operational information by the Operator to the 

organisation responsible for the Type Design in accordance with the 

requirements of the State of aircraft registry. 

Accountable persons or organizations shall report to the competent authority and 

Airbus, any identified condition of an aircraft or component that has resulted or may 

result in an unsafe condition that hazards seriously the flight safety (Refer to EASA 

Part M.A.202 and Part 145.A.60). This will enable Airbus to issue appropriate service 

instructions to all owners or Operators. 

“Hazard seriously the flight safety” means any instances where safe operation could 

not be assured or which could lead to an unsafe condition. It typically includes, but is 

not limited to, significant cracking, deformation, corrosion, any evidence of burning, 

electrical arcing, significant hydraulic fluid or fuel leakage and any emergency system 

or total system failure. 

The finding report should include at least the information stated below: 

 Organisation name, 

 Approval reference if relevant, 

 ASM maintenance requirement reference, 

 Aircraft MSN affected, 

 Identification of the affected component/item, 

 Overhaul, life since new (in FH and/or FC and/or landings and/or Calendar time, as 

applicable) accumulated by the affected system/component/item at the time of the 

finding, 

 Location and detailed description of the finding, with indication of the size and 

orientation, 

 Circumstance of detection and inspection method used. 

Note: Report shall be made as soon as practical, but in any case within 72 hours of 

the organisation identifying the condition to which the report relates. (Refer to 

EASA Part M.A.202 and Part 145.A.60). 
A330 AIRWORTHINESS LIMITATIONS SECTION 

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K. ALS Part 4 airworthiness limitations 

Airworthiness limitations quoted in the ALS Part 4 are applicable to the undamaged 

and unrepaired aircraft systems and components/items. They may need to be adapted 

in case of damage/repair. 

L. Production/Repair concessions and Alternative Methods Of Compliance 

Airworthiness limitations of the ALS sub-parts 4-2 and 4-3 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 Operator’s responsibility to refer to the applicable limitations. 

When airworthiness limitations change in a revision of the ALS Part 4 subsequent to 

the issuance date of the Production concession/RAS/AV/AMOC, Operators are 

requested to contact Airbus for guidance. 

The restrictions of airworthiness limitation(s) indicated in the RAS/AV/AMOC (or 

absence thereof) depend on the component’s/item’s accumulated life considered 

during the original evaluation of the repair solution/AV/AMOC. Occasionally, repair 

solutions/AV/AMOC are evaluated on the basis of an accumulated life that includes a 

conservative life calculation (refer to the applicable Service Information Letter). Such 

AV/AMOC/repair solutions MUST be re-evaluated by Airbus before Operators can take 

credit of the history partially or completely rebuilt after application for 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”). 

Note: For spares, restrictions of airworthiness limitation(s), if any, are indicated in EASA 

Form 1 block “Remark” (directly or by reference to another document). 

M. Modifications/Repairs not developed under Airbus DOA Certificate EASA.21J.031 

If an aircraft/a sub-assembly/a component/an item has a modification or repair 

embodied that has not been developed under the Design Organisation Approval (DOA) 

Certificate EASA.21J.031 (e.g. under a Supplemental Type Certificate) and which 

affects the content of the ALS Part 4, 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 sub-assembly/a component/an item is transferred from one 

Owner/Operator to another, the associated approvals and documents indicating the 

necessary adaptations of airworthiness limitations must be transferred as well. 

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2. DEFINITIONS

The initial entry into service is defined for the aircraft (systems installations) as: 

 The date of Transfer of Title to the first Operator for airworthiness limitations in 

Calendar times, unless otherwise stated in any delivery documentation to the first 

Operator. 

 The date of aircraft first flight for airworthiness limitations in flight hours and/or flight 

cycles and/or landings. 

The initial entry into service for the transferable systems components/items is defined as 

the date at which the component/item accomplishes the first flight for which it will undertake 

its intended function. 

Note: Unless otherwise stated, this means for transferable components/items delivered on 

new aircraft (i.e. from Airbus Final Assembly Line) that the life accumulated between 

aircraft first flight and the aircraft delivery date/transfer of title date (e.g. as a result of 

test flights) must be taken into account. 

Calendar times (Cal.): Airworthiness limitations 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 stated for individual 

components/items). 

Exceptional Short Term Extension: An extension in an ASM airworthiness limitation that 

may be needed to cover an uncontrollable or 

exceptional unexpected situation. 

Flight Cycle (FC): A complete takeoff and landing sequence. 

Flight Hour (FH): The accumulated time intervals between “wheels-off” 

and “wheels-on”. 

Functional Check: A quantitative check to determine if a component/an 

item performs one or more of its functions within 

specified limits. 

Interval: The period expressed in usage parameters like FH 

and/or FC and/or LanDinGs and/or Calendar time 

between consecutive accomplishments of a specific 

task, excluding any exceptional short-term extensions 

from calculations. 

Landing (LDG): An operation of an aircraft touching the runway and 

coming to a complete stop or performing a “touch and 

go”. 
A330 AIRWORTHINESS LIMITATIONS SECTION 

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Operational Check: A qualitative check to determine that a component/an 

item is fulfilling its intended purpose. It is a failurefinding task and does not require quantitative 

tolerances. 

Threshold: The initial accomplishment of a specific maintenance 

task from the initial entry into service. It may be 

expressed in usage parameters like FH and/or FC 

and/or LDG and/or Calendar time. 

Touch and go: A landing in which an aircraft touches the runway and 

does not come to a full stop prior to commencing an 

additional flight. 

In the sub-part 4-3, touch and go cycles can be 

neglected if they are less than 5% of the total number 

of FC up to threshold inspection or between two 

consecutive inspections. Each “Touch and go” above 

5% is to be counted as one FC/LDG, up to threshold 

inspection or between two consecutive inspections. 

3. RULES SPECIFIC TO SUB-PART 4-2

A. Authorised systems components/items 

ALS sub-part 4-2 tables provide the applicable life limitations only for systems 

components/items that have been authorised. These tables do not ensure that a PNR 

has been validated for a specific individual aircraft MSN. 

PNR are authorised for installation on individual aircraft MSN by SB and/or the 

associated modifications, which are published by Airbus. 

PNR provided by sub-parts 4-2-1 and 4-2-2 for ATA 32 items relate to detail parts. 

They may not all be listed in Illustrated Parts Catalogue (IPC) issued by Airbus. This is 

the case, for example, when the procurable replacement part is delivered as an 

assembly. 

Messier-Dowty SBs have been/will be issued to provide information on procurable 

replacement PNR, detail PNR and applicable SB: 

 Messier-Dowty Ltd Service Bulletin number: 

 A33/34-32-85 (main landing gear PRE MOD 43029 – ‘basic’), 

 A33/34-32-88 (main landing gear POST MOD 43029 – ‘growth’ or POST 

MOD 47487 – ‘growth scallop’), 

 A33/34-32-258 (main landing gear POST MOD 54500 – ‘enhanced’). 

 Messier-Dowty SA Service Bulletin number: 

 D23285-32-040 (nose landing gear). 

D 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 11 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Detail parts are listed in the relevant Component Maintenance Manuals (CMM). The 

Messier-Dowty SB listed above provides the procurable replacement Part Numbers. 

B. Life limitation/Replacement time indication 

(1) General 

The life limitation indicated against PNR originally fitted is counted from the 

component’s/item’s initial entry into service. 

The life limitation indicated against PNR evolutions is also to be counted 

from the component’s/item’s initial entry into service (unless otherwise 

stated). 

Note: Where component/item history is unknown/partially unknown, refer to Note 2 

paragraph 1.G. 

In computing components’/items’ 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 component/item (unless otherwise 

stated). 

(2) ALS sub-part 4-2 life limitations 

The life limitation/replacement time indication is quoted on the same line/block of 

lines as the PNR. 

C. Life limitation applicability 

Life limitation applicability is allocated to aircraft affected (for all aircraft of the column in 

sub-part 4-2), according to: 

(1) Aircraft type, series and model, e.g. 

ALS sub-part 4-2 table headers indicate aircraft models. When ‘x’ is entered in the 

model number, it stands for any number within the limits of the list of models given 

in the paragraph 1.A. of this sub-part, e.g.: 

A330-30x stands for: A330-301, A330-302 and A330-303. 

Life limitation applicability is allocated according to the aircraft model affected, e.g.: 

X stands for: All A330 models defined by the applicability of the 

column. 

-223 stands for: A330-223 model only, defined by the applicability 

of the column. 

excl. -341 stands for: All A330 models defined by the applicability of the 

column, excluding the A330-341 model. 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 12 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

(2) Aircraft weight variant, e.g. 

ALS sub-part 4-2 table headers indicate aircraft WV. When ‘x’ is entered in the WV 

number, it stands for any number within the limits of the list of WV’s defined in the 

tables of the paragraph 1.A. above. 

(3) Aircraft Manufacturer Serial Number, e.g. 

XXX–YYY stands for: From aircraft MSN XXX to aircraft MSN YYY (for 

all aircraft defined by the applicability of the 

column). 

XYX, XXZ stands for: For aircraft MSN XYX and aircraft MSN XXZ. 

XZX stands for: For aircraft MSN XZX only. 

excl. XXX stands for: For all aircraft (defined by the applicability of the 

column), excluding MSN XXX. 

4. RULES SPECIFIC TO SUB-PART 4-3

A. Airworthiness limitations 

(1) General 

In computing the life accumulated by the aircraft systems/components/items, 

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 

component/item (unless otherwise stated). 

(2) ALS sub-part 4-3 airworthiness limitations 

The limitations must be applied from: 

 The initial entry into service for the threshold and 

 The original due date of the last accomplishment of the task, excluding any 

exceptional short-term extensions from calculations, for the interval. When 

alternative inspection methods are provided, the next interval applicable is the 

one associated with the inspection method used at last inspection. 

B. ALS sub-part 4-3 layout. 

The maintenance requirements and associated airworthiness limitations are presented 

in the ALS sub-part 4-3 in accordance with the following method: 

(1) Task Number 

The task numbering system follows a similar format to the Maintenance Planning 

Document (MPD) system and is described as follows: 

Each task is identified by a specific task number. When a task applies to two 

specific main zones located symmetrically to either side of the aircraft centerline, 

R 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 13 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

the task is assigned a single task number, but both LH and RH zones are indicated 

in "Zone" column. 

The task number comprises 13 digits organised as follows: 

XXXXXX-MEFYY-Z-E 

XXXXXX is ATA 100 task reference. 

M is the selection methodologies used. It will always be “0”. 

E is engine/APU/... manufacturer identification (where applicable, “0” 

is default value). 

F is engine/APU type information when more than one engine from 

the same manufacturer is applicable to the program (where 

applicable, “0” is default value). 

YY is sequential number. 

Z is for technical solution applicable to the same task requirement. 

E is “E” and stands for ASM (i.e. task related to an ageing systems 

function or Enhanced maintenance requirement). 

(2) Zone column 

The zone column defines where the major part of the maintenance task 

requirement is to be carried out on the aircraft. 

(3) Description column 

This column provides the following information: 

(a) Task Description 

Contains basic description of the maintenance task to be performed. 

(b) Note 

Where given, it states further requirements and/or provides useful information. 

(4) Threshold/Interval columns 

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. 

The repeat interval starts at the original due date of the last accomplishment of the 

task, excluding any exceptional short-term extensions from calculations. 

Usage parameters are defined in the sub-part 4-0 paragraph 2. 

R 

R

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 14 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

(5) Reference column 

This column provides reference to Instructions for Continued Airworthiness where 

maintenance practices/procedures necessary for the task accomplishment are 

provided, e.g. the AMM. 

Where reference is made to an Airbus SB, it must be assumed that the latest 

approved revision of the SB is applicable, but any previous revision is acceptable. 

Where a particular revision is stated, the revision or any later approved revision 

must be used. 

(6) Limitations applicability columns 

These columns give the combination of component(s)/item(s) PNR and aircraft that 

requires the accomplishment of the task. 

(a) PNR 

ALS sub-part 4-3 tables provide the applicable airworthiness limitations only 

for systems installations that have been authorised. These tables do not 

ensure that a PNR has been validated for a specific individual aircraft MSN. 

PNR are authorised for installation on individual aircraft MSN by SBs and/or 

the associated modifications, which are published by Airbus. 

(b) Aircraft 

Applicability Task applicable to 

ALL All A330 aircraft. 

A330-xxx A330-xxx series aircraft. 

PRE nnnnn All aircraft PRE MOD nnnnn. 

i.e. A330 that do not have MOD nnnnn embodied. 

POST nnnnn All aircraft POST MOD nnnnn. 

i.e. A330 that do have MOD nnnnn embodied. 

POST nnnnn 

Sxxxxx 

All aircraft POST MOD nnnnn (at least with mod proposal 

no. Sxxxxx embodied). 

POST nnnnn 

POST mmmmm 

All aircraft POST MOD nnnnn and POST MOD mmmmm. 

i.e. A330 that do have MOD nnnnn and MOD mmmmm 

embodied. 

POST nnnnn 

OR 

PRE mmmmm 

All aircraft that do have MOD nnnnn or aircraft that do not

have MOD mmmmm. 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 15 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Applicability Task applicable to 

A330-223 

OR 

A330-341 

PRE nnnnn 

All A330-223, or 

All A330-341 that do not have MOD nnnnn embodied. 

A330-223 

POST nnnnn 

OR 

A330-341 

POST nnnnn 

PRE mmmmm 

All A330-223 that do have MOD nnnnn embodied, or 

All A330-341 that do have MOD nnnnn embodied and do 

not have MOD mmmmm embodied. 

POST nnnnn 

(xx-yyyy) 

All aircraft that do have MOD nnnnn embodied. 

(xx-yyyy) is the SB reference associated to the 

modification. 

POST xx-yyyy All aircraft that do have SB A330-xx-yyyy embodied 

(applicable only to retrofit solution). 

GE All aircraft equipped with GE CF6-80E engines. 

PW All aircraft equipped with PW4100 series engines. 

RR All aircraft equipped with RR Trent 700 engines. 

 

C. Exceptional short-term extensions for components/items listed in sub-part 4-3. 

Since ALS sub-part 4-3 intervals are based on statistical averages and reliability rates, 

an exceptional short-term extension for a specific ALS sub-part 4-3 interval may be 

made on one aircraft for a limited period of time without compromising the safety 

objectives declared at Type Certification. 

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. Short-term extensions must not be used for fleet ASM 

escalation.

Unless noted adjacent to the airworthiness limitation, for all airworthiness limitations 

identified in the ALS sub-part 4-3, 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. 

(1) Controlled by Flight Hours (FH) 

Extensions up to 10% or 500 FH (whichever is the lesser) may exceptionally be 

granted on ASM airworthiness limitations quoted in terms of Flight Hours. 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 16 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

(2) Controlled by Flight Cycles or LanDinGs (FC or LDG) 

Extensions up to 5% or 250 FC/LDG (whichever is the lesser) may exceptionally 

be granted on ASM airworthiness limitations quoted in terms of Flight Cycles or 

LanDinGs. 

(3) Controlled by Calendar Time (Ye, Mo, etc...) 

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 ASM airworthiness 

limitations quoted in terms of Months. 

Where the repeat interval is greater than 12 Months, extensions up to 2 Months 

may exceptionally be granted. 

It is the Operator’s responsibility to identify appropriate procedures with the Authority of 

the State of aircraft registry for the control and development of his Aircraft Maintenance 

Programme. 

Note: No short-term extensions are permissible for tasks previously required by 

individual ADs. These items will highlighted by a note in the task description 

column. 

END OF SUB-PART 4-0 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 1 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Sub-part 4-1 ILLUSTRATIONS

ATA 26-23-00 – LWR DECK CARGO COMPART. FIRE EXTING. FWD, AFT & BULK – FIG. 01

Pressure reducer 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 2 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 27-14-00 – AILERON AND HYDRAULIC ACTUATION – FIG. 02
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 3 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

R ATA 27-23-00 – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION – FIG. 03
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 4 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

R ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 04
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 5 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

R ATA 27-44-00 – THS HYDRAULIC ACTUATION – FIG. 05
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 6 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

 

ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 06

Example 

Flap Rotary Actuator 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 7 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 07

Flap Power Control Unit (PCU) 

N 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 8 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

R ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 08
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 9 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 27-84-00 – SLATS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG.09

T-Gearbox 

N 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 10 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

R ATA 29-24-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 10 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 11 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

(*) Location, item not illustrated 

FORWARD

ATA 32-11-00 – MAIN GEAR – FIG. 11 

Pin P (*) 

Retraction 

actuator 

Lock stay 

actuator 

Side Stay 

Assembly 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 12 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Retraction link

Retraction 

bracket 

Pin W2 

Retraction actuator 

piston rod 

Retraction 

jack fitting 

Pin W 

Pin W1 

Main fitting 

R ATA 32-11-00 – MAIN GEAR – FIG. 12 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 13 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Lock link 

(subassembly) 

Lock stay actuator 

pin (x2) 

ATA 32-11-00 – MAIN GEAR – FIG. 13 

Side Stay Assembly 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 14 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 32-21-00 – NOSE GEAR – FIG. 14 

Retraction actuator pin 

(main fitting side) 

Main Fitting 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 15 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 32-31-00 – NORMAL EXTENSION AND RETRACTION – FIG. 15 

Airframe 

Retraction actuator pin 

(main fitting side) 

Retraction actuator pin 

(airframe side) 

Retraction actuator 

bearing 

Retraction actuator 

eye end 

Retraction actuator 

body 

Retraction actuator 

plug 

Retraction actuator 

sliding rod 

Retraction actuator 

cylinder 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 16 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Retraction actuator 

piston rod 

Retraction actuator 

insert 

Retraction actuator 

gland 

Retraction actuator 

cylinder 

Retraction actuator 

piston head 

R ATA 32-31-00 – NORMAL EXTENSION AND RETRACTION – FIG. 16 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 17 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 32-31-00 – NORMAL EXTENSION AND RETRACTION – FIG. 17 

Lock stay actuator 

piston rod 

Lock stay actuator 

cylinder 

Lock stay actuator 

rod end 

Lock stay actuator 

gland 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 18 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 35-13-00 – CREW OXYGEN – CONTROL AND INDICATING – FIG. 18

Pressure Switch 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-1 PAGE: 19 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

ATA 35-23-00 – PAX OXYGEN (GASEOUS) – CONTROL AND INDICATING – FIG. 19 

END OF SUB-PART 4-1 

R 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. Sub-part 4-2 SYSTEMS LIFE-LIMITED COMPONENTS

Sub-part 4-2-1 LIFE LIMITS

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

ATA 26-23-00 FIRE PROTECTION – LOWER DECK CARGO COMPARTMENT FIRE EXTINGUISHING (FIG. 01)

R Pressure reducer D41428 N/A N/A 20 Ye X X X X X 

ATA 27-14-00 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 02)(1) Applicable to servo-controls in positions Functional Item Number (FIN) 7CS1, 8CS1, 7CS2 and 8CS2 for inboard servo-controls, and F

10CS2 for outboard servo-controls (active and damping). 

 (2) Embodiment of MOD 45512/SB A330-27-3054 introduces different PNR. MOD 45512 factory embodied on MSN 229 and subsequent. 

Inboard aileron servocontrol (1) (2) 3337457-22 6000 N/A N/A X 

3337457-23 6000 N/A N/A X 

 3337457-26 18000 N/A N/A X  3337457-27 18000 N/A N/A X  3337457-30 32000 21600 N/A X X  3337457-31 32000 21600 N/A X X 

3337457-35 32000 21600 N/A X X 3337457-36 32000 21600 N/A X X 

 3337457-37 32000 21600 N/A X X  3337457-38 32000 21600 N/A X X 

Outboard aileron servo-control (1) (2) 

3337458-30 32000 21600 N/A X X 

3337458-31 32000 21600 N/A X X 

 3337458-35 32000 21600 N/A X X  3337458-36 32000 21600 N/A X X  3337458-37 32000 21600 N/A X X  3337458-38 32000 21600 N/A X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

N ATA 27-23 FLIGHT CONTROL – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION (FIG. 03)N (1) FIN 24CS.N (2) FIN 36CS.N Rudder Travel Limitation Unit (RTLU) 341400M02 (1) 100000 33000 N/A X X N Pedal Travel Limitation Unit (PTLU) 341400M02 (2) 100000 33000 N/A X X R ATA 27-34-00 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC CONTROL (FIG. 04) (1) Applicable to elevator servo-controls installed in positions FIN 2CS1, 2CS2, 3CS1 and 3CS2 (active and damping). 

Elevator servo-control (1) 

SC4800-2 N/A N/A 31-Aug-04 X X 

 SC4800-3 N/A N/A 31-Aug-04 X X  SC4800-4 N/A N/A 31-Aug-04 X X  SC4800-6 N/A N/A 31-Aug-04 X X 

SC4800-7 N/A N/A 31-Aug-04 X X 

SC4800-7A N/A N/A 30-Jun-08 X X X X 

SC4800-8 N/A N/A 31-Aug-04 X X 

 SC4800-9 N/A N/A 30-Jun-08 X X X X  SC4800-10 N/A N/A 30-Jun-08 X X X X  SC4800-11 N/A N/A 30-Jun-08 X X X X  SC4800-72 N/A N/A 30-Jun-08 X X X X  SC4800-73 N/A N/A 30-Jun-08 X X X X  SC4800-92 N/A N/A 30-Jun-08 X X X X  SC4800-93 N/A N/A 30-Jun-08 X X X X  SC4800-103 N/A N/A 30-Jun-08 X X X X  SC4800-113 N/A N/A 30-Jun-08 X X X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

R ATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 05)

(1) Embodiment of MOD 45906/SB A330-27-3052 and MOD 49591/SB A330-27-3093 introduces different PNR. MOD 45906 factory 

subsequent. 

 (2) Embodiment of MOD 49590/SB A330-27-3085 introduces different PNR. MOD 49590 factory embodied on MSN 437 and subsequent. N N N N 

(3) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906) and retrof

SB A330-27-3093 (MOD 49591). Life limitation to be applied from the time of retrofit into PNR 47147-400 (SB A330-27-3052) for THSA subsequently retrofitted into PNR 

49591/SB A330-27-3093). The sum of the accumulated lives PRE and POST SB A330-27-3052 must not exceed 60000 FH/40000 FC

N N N N N 

(4) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906) and retrof

SB A330-27-3093 (MOD 49591) and subsequently retrofitted to PNR 47147-700 by SB A330-27-3143 (MOD 54881). Life limitation to be applied from the time of retrofit into PNR 47147-400 (SB A330-27-3052) for THSA subsequently retrofitted into PNR 

49591/SB A330-27-3093) then retrofitted to PNR 47147-700 by SB A330-27-3143 (MOD 54881). The sum of the accumulated lives PR3052 plus PRE and POST SB A330-27-3143 must not exceed 60000 FH/40000 FC, whichever occurs first. 

 THS Actuator 47147-200 N/A N/A 31-Jul-04 X (1) X 

47147-210 N/A N/A 31-Jul-04 X (1) X 47147-213 N/A N/A 31-Jul-04 X (1) X 47147-300 N/A N/A 31-Jul-04 X (1) X 47147-303 N/A N/A 31-Jul-04 X (1) X 

47147-350 N/A N/A 31-Jul-04 X (1) X 

47147-400 N/A N/A 31-Jul-04 X (1) X 

N 47147-500 36000 24000 N/A X (3) X (3) X N 47147-700 36000 24000 N/A X (4) X (4) X R 47172 N/A N/A 31-Dec-03 X (2) X (2) X R ATA 27-54-00 FLIGHT CONTROL – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 06 & 07)

(1) Embodiment of MOD 50044 and/or MOD 52591 (both associated to SB A330-27-3106) introduces different PNR. MOD 50044 and MO

on MSN 506, MSN 509 thru 521, MSN 524 and subsequent. 

Flap Rotary Actuator – Type A 

697510004 (1) N/A 18000 12 Ye X X 697510005 (1) N/A 18000 12 Ye X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Flap Rotary Actuator – Type B 

697511004 (1) N/A 18000 12 Ye X X 697511005 (1) N/A 18000 12 Ye X X 697511006 (1) N/A 18000 12 Ye X X 697511007 (1) N/A 18000 12 Ye X X 

N Flap Power Control 

Unit (PCU) 

953A0000-04 N/A N/A 31-Oct-14 X X 

N 953A0000-05 N/A N/A 31-Oct-14 X X N 953B0000-01 N/A N/A 31-Oct-14 X X R ATA 27-64-00 FLIGHT CONTROL – SPOILER HYDRAULIC ACTUATION (FIG. 08) (1) Not applicable to aircraft POST MOD 44670 and delivered from 13-Jan-2006 onwards. Embodiment of MOD 51413/SB A330-27-3113  (2) FIN 13CS1 and 13CS2.  (3) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1 and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2. 

(4) For spoiler servo-controls with unknown history of life accumulation on 31-Aug-2006, their total accumulated life is calculated by additi

the aircraft they are fitted to on 31-Aug-2006, to their actual life accumulated since. 

 (5) When removed from aircraft, these servo-controls must be scrapped. 

(6) Applicable to aircraft up to and including MSN 588. 

 For aircraft, which have accumulated on 05-Sep-08 less than or equal to 8500 FC since aircraft initial entry into service, modify a

accordance with SB A330-27-3110 no later than 05-Mar-2010. 

 For aircraft, which have accumulated on 05-Sep-08 more than 8500 FC since aircraft initial entry into service, modify the servo-co

accordance with SB A330-27-3110: 

 If 3 hydraulic circuits are affected: 

(a) On first circuit within 10400 FC since aircraft initial entry into service. (b) On second circuit within 10800 FC since aircraft initial entry into service. (c) On third circuit no later than 05-Mar-2010. 

 If 2 hydraulic circuits are affected: 

(a) On first circuit within 10800 FC since aircraft initial entry into service. 

(b) On second circuit or no later than 05-Mar-2010. 

 If 1 hydraulic circuit is affected: no later than 05-Mar-2010. 

R (7) Embodiment of MOD 48956/SB A330-27-3094 introduces different PNR. MOD 48956 factory embodied on MSN 422, MSN 443 and su
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

R Spoiler servo-control 

in position 1 (2) MZ4339390-01X (1) N/A 11000 (5) N/A X X R N/A N/A 05-Mar-10 (6) X X 

R MZ4339390-02X 

(1) 

N/A 11000 (5) N/A X X 

R N/A N/A 05-Mar-10 (6) X X R MZ4339390-10X 

(1) 

N/A 11000 (5) N/A X X 

R N/A N/A 05-Mar-10 (6) X X R D 

MZ4339390-12 

(1) N/A 11000 (5) N/A X X 

S4-3000470 

(1) (5) 

N/A 11000 N/A X X 

N/A 15000 N/A X (4) X (4) X 

S4-3000470-01 

(1) (5) 

N/A 11000 N/A X X 

N/A 15000 N/A X (4) X (4) X 

S4-3000470-02 

(1) (5) 

N/A 11000 N/A X X N/A 15000 N/A X (4) X (4) X 

S4-3000470-03 

(1) (5) 

N/A 11000 N/A X X N/A 15000 N/A X (4) X (4) X 

1387A0000-01 (7) N/A N/A 31-Dec-03 X X X X 1387B0000-01 (7) N/A N/A 31-Dec-03 X X X X 

R Spoiler servo-control 

in position 2 to 6 (3) MZ4306000-01X (1) N/A 6000 (5) N/A X X R N/A N/A 05-Mar-10 (6) X X 

R MZ4306000-02X 

(1) 

N/A 6000 (5) N/A X X 

R .../... N/A N/A 05-Mar-10 (6) X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

R Spoiler servo-control 

in position 2 to 6 (3) MZ4306000-10X (1) N/A 6000 (5) N/A X X R N/A N/A 05-Mar-10 (6) X X 

R D 

 MZ4306000-12 

(1) N/A 6000 (5) N/A X X 

S4-3000460 

(1)(5) 

N/A 6000 N/A X X 

N/A 14000 N/A X (4) X (4) X 

S4-3000460-01 

(1)(5) 

N/A 6000 N/A X X 

N/A 14000 N/A X (4) X (4) X 

S4-3000460-02 

(1)(5) 

N/A 6000 N/A X X 

N/A 14000 N/A X (4) X (4) X 

S4-3000460-03 

(1)(5) 

N/A 6000 N/A X X N/A 14000 N/A X (4) X (4) X 

1386A0000-01 (7) N/A N/A 31-Dec-03 X X X X 1386B0000-01 (7) N/A N/A 31-Dec-03 X X X X 

N ATA 27-84 LIFT AUGMENTING - SLATS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 09)N (1) Comply with these requirements no later than 31-Oct-2014. N T-Gearbox (TGBx) 921A0000-01 N/A N/A 31-Oct-14 X X X X X N 921B0000-01 (1) N/A 32000 N/A X X X X X N 921C0000-01 (1) N/A 24000 N/A X X X X X N 921D0000-01 (1) N/A 24000 N/A X X X X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 11 to 13 & 16 to 17)R MAIN STRUT AND DRESSINGS (FIG. 11 & 13) Notes (1) to (6): Refer to CN 97-007-042(B) latest approved revision. 

(1) 3250 LDG with an unserviceable retraction line Delay Valve. 4300 LDG with a serviceable retraction line Delay Valve. Embodim

45031/SB A330-32-3066 introduces a different PNR. MOD 43863 factory embodied on original landing gear of MSN 116 and subsequ

 (2) For this PNR, note (1) is applicable to SNR 0018WHM and SNR 0022WHM.  (3) For this PNR, note (1) is applicable to SNR 0034WHM and SNR 0041WHM.  (4) For this PNR, note (1) is applicable to SNR 003WHM (only this SNR exists).  (5) For this PNR, note (1) is applicable to SNR 0031WHM (only this SNR exists). 

(6) For this PNR, applicable to the other SNRs. See notes (2) and (3). Embodiment of MOD 43863 or MOD 45031/SB A330-32-3066 

MOD 43863 factory embodied on original landing gear of MSN 116 and subsequent. 

 (7) Embodiment of MOD 46903/SB A330-32-3096 introduces a different PNR. MOD 46903 factory embodied on original landing gear of M (8) Embodiment of MOD 46904/SB A330-32-3095 introduces a different PNR. MOD 46904 factory embodied on original landing gear of M (9) Embodiment of MOD 48066/SB A330-32-3123 introduces a different PNR. MOD 48066 factory embodied on original landing gear of M (10) Life limit is the later of 900 aircraft FH counted from 08-Jul-2009 or the accumulation of 11150 total LDG since initial entry into service  (11) Life limit is the earlier of the 10 year calendar limit or the limitation deduced from Note (10).  (12) Embodiment of MOD 58527/SB A330-32-3229 introduces a different PNR.  Pin W 201275796 (7) N/A 20000 10 Ye X X X X 

201478613 N/A 42800 N/A X X X X 201489770 N/A 42800 N/A X X X X X 

 Retraction link (LH) 201275317 (9) N/A 35200 36 Mo X X X X 

201489311 (12) N/A 8400 N/A X X X X 

 Retraction link (RH) 201275318 (9) N/A 35200 36 Mo X X X X 

201489312 (12) N/A 8400 N/A X X X X 

 Pin W1 201275673 (7) (11) N/A (10) 10 Ye X X X X 

201478614 N/A (10) N/A X X X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Retraction bracket (LH) 

201428305 N/A (1) N/A X 201428307 N/A (1) N/A X 201428318 N/A (1) N/A X 201428323 N/A (1) N/A X 

201428331 (2) N/A (1) N/A X 201428331 (6) N/A 9000 N/A X 

201428333 N/A (1) N/A X 201428335 N/A (1) N/A X 

201428338 (4) N/A (1) N/A X 

201428351 N/A 19800 N/A X X X X 201428378 N/A 19800 N/A X X X X 201428380 N/A 19800 N/A X 201428382 N/A 19800 N/A X 201428384 N/A 19800 N/A X 201478303 N/A 19800 N/A X 201478305 N/A 19800 N/A X 201478307 N/A 19800 N/A X 

Retraction bracket (RH) 

201428306 N/A (1) N/A X 201428308 N/A (1) N/A X 201428319 N/A (1) N/A X 201428324 N/A (1) N/A X 

201428332 (3) N/A (1) N/A X 201428332 (6) N/A 9000 N/A X 

201428334 N/A (1) N/A X 

.../... 201428336 N/A (1) N/A X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Retraction bracket (RH) 

201428339 (5) N/A (1) N/A X 

201428352 N/A 19800 N/A X X X X 201428379 N/A 19800 N/A X X X X 201428381 N/A 19800 N/A X 201428383 N/A 19800 N/A X 201428385 N/A 19800 N/A X 201478304 N/A 19800 N/A X 201478306 N/A 19800 N/A X 201478308 N/A 19800 N/A X 

 Pin W2 

201275667 (8) 

N/A 4500 5 Ye X N/A 9400 5 Ye X X X 

201478615 N/A 42800 N/A X X X X 

 201478637 N/A 42800 N/A X X X X 

 Pin P 201275602 (7) N/A 20000 10 Ye X X X X 

201478612 N/A 42800 N/A X X X X 

R RETRACTION ACTUATOR (FIG. 11 & 16) (1) Rework in accordance with SB A330-32-3216 (MOD 56557) may introduce a different PNR. 

(2) Embodiment of MOD 200837/SB A330-32-3243 may introduce a different PNR. 

 MOD 200837 factory embodied on original landing gear of MSN 1195 and subsequent for A330 series excluded A330-200F.  MOD 200837 factory embodied on original landing gear of MSN 1092 and subsequent for A330-200F series. 

Retraction actuator piston rod 

114256309 N/A 8080 31-Dec-07 X X X X 

114256321 (1) N/A 8080 31-Dec-07 X X X X 

114256323 N/A 5500 N/A X X X X 

R 114256326 N/A 18000 N/A X X X X R 114256328 N/A 18000 N/A X X X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Retraction actuator gland 

50-2113004-00 

(2) N/A 27790 N/A X X X X 

Retraction actuator cylinder 

114256310 N/A 22900 N/A X X X X 114256320 N/A 22900 N/A X X X X 

R ATA 32-21-00 NOSE LANDING GEAR (FIG. 14 & 15)R RETRACTION ACTUATOR (FIG. 15)

Retraction actuator body 

D61954 N/A 30000 N/A X X X X 

D61954-10 N/A 30000 N/A X X X X 

D67876 N/A 30000 N/A X X X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

R Explanation notes are located under the 

assy title. 

LIFE LIMITS 

(Whichever occurs first) 

LIFE LIMITS APPLICABILITY 

A330-2xxF A330-2xx A330-30x 

D R 

Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

ATA 35-13-00 OXYGEN – CREW OXYGEN – CONTROL AND INDICATING (FIG. 18)

R Pressure Switch CMK80-01 N/A N/A 20 Ye X X X X R ATA 35-23-00 OXYGEN – PASSENGER OXYGEN (GASEOUS) – CONTROL AND INDICATING (FIG. 19)

Quantity Calculation Control Unit E69027 80000 N/A 20 Ye X X 

END OF SUB-PART 4-2-1 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. Sub-part 4-2-2 CURRENT DEMONSTRATED LIVES

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

Explanation notes are located under the 

assy title. 

LIFE LIMITATIONS 

(Whichever occurs first) 

LIFE LIMITATIONS APPLICABILIT

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH FC Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

ATA 27-14-00 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 02)

(1) Applicable to servo-control installed in positions FIN 7CS1, 8CS1, 7CS2 and 8CS2 for inboard servo-controls, and FIN 9CS1, 10CS1, 

outboard servo-controls (active and damping). 

R D R D R 

Inboard aileron servocontrol (1) 3337457-59 110000 N/A N/A X X X X X 

Outboard aileron servo-control (1) 3337458-59 110000 N/A N/A X X X X X ATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 05)

N (1) Embodiment of MOD 54880/SB A330-27-3137 introduces different PNR. R (2) Embodiment of MOD 200698/SB A330-27-3172 introduces different PNR. R D R 

(3) Embodiment of MOD 58916/SB A330-27-3172 introduces different PNR. MOD 58916 factory embodied on MSN 1095 and subsequen

THS Actuator 

47172-300 (1) 

60000 40000 25 Ye X X X X 

N 65000 20000 25 Ye X X X X R 

47172-500 (2) 

60000 40000 25 Ye X X X X X 

N 65000 20000 25 Ye X X X X X R 

47172-510 (3) 

60000 40000 25 Ye X X X X X 

N 65000 20000 25 Ye X X X X X 

47172-520 

60000 40000 N/A X X X X X 

N 65000 20000 N/A X X X X X 

47172-530 

60000 40000 N/A X X X X X 

N 65000 20000 N/A X X X X X D 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

Explanation notes are located under the 

assy title. 

LIFE LIMITATIONS 

(Whichever occurs first) 

LIFE LIMITATIONS APPLICABILIT

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 11 to 13 & 16 to 17)R MAIN STRUT AND DRESSINGS (FIG. 11 & 13) (1) This PNR is common to pin W2 and pin P.  Pin W 55-2105061-00 N/A 46480 N/A X X X X  Retraction link (LH) 50-2105026-00 N/A 46480 N/A X X X X 

50-2105224-00 N/A 46480 N/A X X X X 

201489315 N/A 10700 N/A X X X X 

 Retraction link (RH) 50-2106026-00 N/A 46480 N/A X X X X 

50-2106224-00 N/A 46480 N/A X X X X 

201489316 N/A 10700 N/A X X X X 

 Pin W1 55-2105060-00 N/A 46480 N/A X X X X N 201478652 N/A 25179 N/A X X X X 

Retraction bracket (LH) 50-2105027-00 N/A 46480 N/A X X X X Retraction bracket (RH) 50-2106027-00 N/A 46480 N/A X X X X 

 Pin W2 55-2105059-00 (1) N/A 46480 N/A X X X X  Pin P 55-2105059-00 (1) N/A 46480 N/A X X X X R COMPLETE SIDE STAY (FIG. 13) Lock stay actuator pin 201440611 N/A 50000 N/A X 

201457606 N/A 50000 N/A X 

R LOCK STAY ACTUATOR (FIG. 17)

Lock stay actuator cylinder 

114354600 N/A 50000 N/A X 201686600 N/A 50000 N/A X 

Lock stay actuator piston rod 

114354605 N/A 50000 N/A X 201686602 N/A 50000 N/A X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

Explanation notes are located under the 

assy title. 

LIFE LIMITATIONS 

(Whichever occurs first) 

LIFE LIMITATIONS APPLICABILIT

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Lock stay actuator gland 

114354606 N/A 50000 N/A X 201481611 N/A 50000 N/A X 201481614 N/A 50000 N/A X 

Lock stay actuator rod end 

114354602 N/A 50000 N/A X 201686601 N/A 50000 N/A X 

R RETRACTION ACTUATOR (FIG. 11 & 16)

(1) Must be replaced by a new one every time the piston head is removed from the piston rod. 

Retraction actuator piston rod 50-2113002-00 N/A 50000 N/A X X X X 

Retraction actuator gland 

114256312 N/A 50000 N/A X X X X 114256322 N/A 50000 N/A X X X X 

50-2113004-01 N/A 27790 N/A X X X X 

Retraction actuator piston head 

114256308 N/A 50000 N/A X X X X 114256639 N/A 50000 N/A X X X X 

50-2113003-00 N/A 50000 N/A X X X X 

Retraction actuator insert 114256629 N/A (1) N/A X X X X X Retraction actuator cylinder 50-2113001-00 N/A 50000 N/A X X X X 

R ATA 32-21-00 NOSE LANDING GEAR (FIG. 14 & 15) (1) ‘xx’ at the end of the PNRs stands for any number between 00 and 99, including unused digits. 

Retraction actuator pin (airframe side) (1) 

F53112357200xx N/A 50000 N/A X X 

F53112357204xx 

N/A 50000 N/A X 

N/A 41250 N/A X X 

F53114022200xx 

N/A 50000 N/A X N/A 41250 N/A X X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

Explanation notes are located under the 

assy title. 

LIFE LIMITATIONS 

(Whichever occurs first) 

LIFE LIMITATIONS APPLICABILIT

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Retraction actuator pin (airframe side) (1) 

F53114023200xx N/A 50000 N/A X X 

F53120422200xx 

N/A 50000 N/A X 

N/A 41250 N/A X X X 

R NOSE LANDING GEAR LEG (FIG. 14)R MAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 14)R Retraction actuator 

pin (Main fitting side) D61686 

N/A 50000 N/A X X X X N/A 18000 N/A X 

R RETRACTION ACTUATOR (FIG. 15)

Retraction actuator eye end D62588 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D62588-1 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D67840 

N/A 50000 N/A X X X X N/A 18000 N/A X 

Retraction actuator bearing D61950-1 

N/A 50000 N/A X X X X 

N/A 18000 N/A X 

D61950-10 

N/A 50000 N/A X X X X 

N/A 18000 N/A X 

D67839 

N/A 50000 N/A X X X X N/A 18000 N/A X 

N 

D68397 

N/A 50000 N/A X X X X 

N N/A 18000 N/A X 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-2-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. 

Explanation notes are located under the 

assy title. 

LIFE LIMITATIONS 

(Whichever occurs first) 

LIFE LIMITATIONS APPLICABILIT

A330-2xxF A330-2xx A330-30x 

 Nomenclature Part Number FH LDG Cal. WV00x WV02x WV05x WV06x WV00x WV01x WV05x WV

WV

Retraction actuator sliding rod D62328 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D62328-1 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D67837 

N/A 50000 N/A X X X X N/A 18000 N/A X 

Retraction actuator plug D61952 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D61952-1 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D67838 

N/A 50000 N/A X X X X N/A 18000 N/A X 

Retraction actuator cylinder D62587 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D62587-1 

N/A 50000 N/A X X X X N/A 18000 N/A X 

D67836 

N/A 50000 N/A X X X X N/A 18000 N/A X 

N Retraction actuator 

body 

D61954 N/A 18000 N/A X 

N D61954-10 N/A 18000 N/A X N D67876 N/A 18000 N/A X D 

END OF SUB-PART 4-2-2 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-3-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS

Sub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVEL

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4. 

ALS PART 4 MAINTENANCE TASKS LIMITATIONS (Whichever occurs first) REFERENCE LIM

Task Number Zone Description Threshold Interval 

R N 

274400-00001-1-E 311 

312

THSA – FIG. 05 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the gap at the secondary nut trunnion. This task must be carried out before task 274400-00002-1-E. Note 1: No short-term extension is allowed. Note 2: In computing the life accumulated by 

the THSA for compliance with the threshold, calculations must include flight hours since the initial entry into 

service or since 17-Aug-2002, whichever occurs later.

700 FH 

Notes 1 & 2

700 FH 

Note 1

SB A330-27-3102 R08 

AMM 27-44-51

44

R R 

274400-00001-2-E 311 

312

THSA – FIG. 05 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the Checkable Shear Pins (CSP). This task must be carried out before task 274400-00002-1-E. Note: No short-term extension is allowed.

700 FH 

Note 

700 FH 

Note 

SB A330-27-3102 R08 

AMM 27-44-51

44
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-3-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4. 

ALS PART 4 MAINTENANCE TASKS LIMITATIONS (Whichever occurs first) REFERENCE LIM

Task Number Zone Description Threshold Interval 

R R N N N N N 

274400-00001-3-E 311 

312

THSA – FIG. 05 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the Checkable Shear Pins (CSP). This task must be carried out before task 274400-00002-1-E. Note: No short-term extension is allowed.

700 FH 

Note 

700 FH 

Note

SB A330-27-3102 R08 

AMM 27-44-51

44

R R 

274400-00001-4-E 311 

312 

THSA – FIG. 05 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load 

path and check the Checkable Shear Pins (CSP). This task must be carried out before task 274400-00002-1-E. Note: No short-term extension is allowed. 

700 FH 

Note 

700 FH 

Note 

SB A330-27-3102 R08 

AMM 27-44-51 

4

R R R N N N N N 

274400-00002-1-E 311 

312

THSA – FIG. 05 Lubrication of the THSA ball-nut. Note 1: No short-term extension is allowed. Note 2: This task must be carried out at the 

opportunity of ASM tasks 274400-00001-1-E, 274400-00001-2-E, 274400-00001-3-E and 274400-00001-4-E once applicable.

1000 FH 

Note 1 

1000 FH 

Note 1 

AMM 12-22-27/301 4

444444
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-3-1 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4. 

ALS PART 4 MAINTENANCE TASKS LIMITATIONS (Whichever occurs first) REFERENCE LIM

Task Number Zone Description Threshold Interval 

R R R R R R R R R R 

292400-00001-1-E 633 Ram Air Turbine (RAT) – FIG. 10 

Remove RAT (including actuator, manifold, hydraulic pump, turbine-lower gearbox assembly and strut-lug assembly), for overhaul and replace with serviceable units.

20 Ye 

. 

20 Ye 

. 

AMM 292452-960-801 RA

hyd

tu

as

a

END OF SUB-PART 4-3-1 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-3-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

 Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVEL

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4. 

ALS PART 4 MAINTENANCE TASKS LIMITATIONS (whichever occurs first) REFERENCE LIM

 Task Number Zone Description Threshold Interval  275000-00001-1-E 570 

670

Flaps Perform a simultaneous detailed visual inspection of the Input Gear Boxes (IPGB) and of the Down Drive Shafts (DDS) on flap tracks 2 and 4 on both wings. Note 1: No short-term extension is allowed. Note 2: Report inspection results, whatever 

they are, to AIRBUS.

16-Dec-2007

Notes 1 & 2 

N/A SB A330-27-3151 

AMM 27-54-56 AMM 27-54-57

 275000-00001-2-E 570 

670

Flaps Perform a simultaneous detailed visual inspection of the Input Gear Boxes (IPGB) and of the Down Drive Shafts (DDS) on all flap tracks on both wings. Note 1: No short-term extension is allowed. Note 2: First inspection is performed in 

accordance with SB A330-27-3151. Report inspection results, whatever they are, to AIRBUS. 

 Subsequent repetitive inspections are 

performed in accordance with SB A330-27-3152.

16-Aug-2009

Notes 1 & 2

6 Ye 

Notes 1 & 2

SB A330-27-3151 SB A330-27-3152 

AMM 27-54-56 AMM 27-54-57
A330 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: AUG 27/13 ALS PART 4-3-2 

EASA APPROVED 

 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4. 

ALS PART 4 MAINTENANCE TASKS LIMITATIONS (whichever occurs first) REFERENCE LIM

 Task Number Zone Description Threshold Interval  275000-00001-3-E 570 

670

Flaps Perform a simultaneous detailed visual inspection of the Input Gear Boxes (IPGB) and of the Down Drive Shafts (DDS) on all flap tracks on both wings. Note: No short-term extension is allowed.

26-Oct-2009 

or 

6 years from 

the date of 

original 

delivery of 

the aircraft, 

whichever 

occurs later. 

Note

6 Ye 

Note

SB A330 27-3152 

AMM 27-54-56 AMM 27-54-57

N N R 

275000-00001-4-E 570 

670 

Flaps Lubricate the spline joint between the Input Gear Boxes (IPGB) and the Down Drive Shafts (DDS) for all flap tracks on both wings. 

24 Mo 24 Mo AMM 12-22-27 

R 

275000-00001-5-E 570 

670 

Flaps Lubricate the spline joint between the Input Gear Boxes (IPGB) and the Down Drive Shafts (DDS) for all flap tracks on both wings. One-time inspection for corrosion in accordance with SB A330-27-3173 at the time of SB A330-27-3173 embodiment. 

 24 Mo SB A330-27-3173 

AMM 12-22-27 

END OF SUB-PART 4-3-2 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: AUG 27/13 ALS PART 4 HISTORY FILE PAGE: 1/5 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

1- GENERAL

 A330 ALS Part 4 revision 00: 

The A330 ALS Part 4 revision 00 was primarily dedicated to transfer the retraction actuator 

chain components from the A330 ALS Part 1 into this document. It was also the opportunity 

to include the requirements of the following Airworthiness Directives (AD): 

 French DGAC Consigne de Navigabilité (CN) 2001-530(B), and 

 French DGAC CN 2001-545(B)R1, and 

 French DGAC CN F-2002-414(B)R3, and 

 French DGAC CN F-2003-140(B)R1, and 

 European Aviation Safety Agency (EASA) AD 2006-0159, and 

 EASA AD 2007-0309, and 

 EASA AD 2008-0026. 

 A330 ALS Part 4 revision 01: 

The revision 01 of the A330 ALS Part 4 has been issued to extend the WV054 applicability 

to all A330-200 series aircraft. The requirements of the EASA AD 2001-518(B) have been 

included and some applicability tasks have been corrected in the A330 ALS Part 4 revision 

01. 

 A330 ALS Part 4 revision 02: 

The A330 ALS Part 4 Revision 02 has been primarily produced to introduce new limitations 

into ALS Parts 4-2 and 4-3 resulting from the Intermediate Service Goal (ISG) Step 1 

activities (Mod 58269) which is applicable only to A330-301 Weight Variants 000 and 010. It 

was also the opportunity to include the requirements of the EASA AD 2009-0138. 

 A330 ALS Part 4 revision 03: 

The A330 ALS Part 4 Revision 03 has been primarily produced to introduce new limitations 

into ALS Parts 4-2 and 4-3 resulting from the Intermediate Service Goal (ISG) Step 2 and 3 

activities (Mod 200103) which are applicable to all A330, including the A330-200F series. It 

was also the opportunity to include the requirements of the following AD: 

 CN 2002-552(B), and 

 EASA AD 2007-0008, and 

 EASA AD 2007-0011 (paragraph 2, 3, 5), and 

 EASA AD 2007-0309, and 

 EASA AD 2008-0160, and 

 EASA AD 2009-0195 (paragraph 1.1, 3, 4), and 

 EASA AD 2010-0081 (paragraph 1, 2, 4, 5, 6, 7, 10), and 

 EASA AD 2010-0192 (paragraph 1.1, 1.2, 2.1, 2.2, 3, 4, 5, 6, 7), and 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: AUG 27/13 ALS PART 4 HISTORY FILE PAGE: 2/5 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

 EASA AD 2010-0205, and 

 AMOC Reference 10033009 dated 14-Dec-2010. 

 A330 ALS Part 4 revision 04: 

The A330 ALS Part 4 Revision 04 has been primarily produced to introduce new limitations 

into ALS Parts 4-2 and 4-3 resulting from: 

 ALS Variation - 0GVLG100009/C0S issue 01 

 ALS Variation - 0GVLG110013/C0S issue 02 

 ALS Variation - 0GVLG110020/C0S issue 01 

 ALS Variation - 0GVLG110029/C0S issue 01 

 ALS Variation - 0GVLG110031/C0S issue 01 

 ALS Variation - 0GVLG120001/C0S issue 01 

 ALS Variation - 0GVLG120004/C0S issue 01 

 ALS Variation - 0GVLG120005/C0S issue 01 

 ALS Variation - 0GVLG120008/C0S issue 01 

 ALS Variation - 0GVLG120011/C0S issue 01 

 ALS Variation - 0GVLG120016/C0S issue 01

2- SUMMARY OF CHANGES:

The following summarizes the changes with respect to the previous issue of the A330 ALS Part 

4 (revision 04). 

New items: 

RECORD OF REVISIONS:

None. 

SUB-PART 4-0:

None. 

SUB-PART 4-1:

 New illustrations added for the new items introduced in ALS sub-part 4-2. 

SUB-PART 4-2:

 Introduction of new items/part numbers 

 Flap Power Control Unit (PCU) PNR 953A0000-04, PNR 953A0000-05, and PNR 

953B0000-01, 

 T-Gearbox PNR 921A0000-01, PNR 921B0000-01, PNR 921C0000-01, and PNR 

921D0000-01, 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: AUG 27/13 ALS PART 4 HISTORY FILE PAGE: 3/5 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

 Pin W1 PNR 201478652, 

 Retraction actuator bearing PNR D68397, 

 Retraction actuator body fitted to A330-200F PNR D61954, D61954-10, and D67876 

(ALS Variation 0GVLG100009/C0S issue 01 applicable to A330-200F). 

SUB-PART 4-3:

None 

Amendments: 

SUB-PART 4-0:

 The term “Limit Of Validity” is removed. 

 The paragraph 1.A “ALS Part 4 applicability” updated. 

 Minor wording changes. 

SUB-PART 4-1:

 Figures numbers amended due to removal/addition of items. 

SUB-PART 4-2:

 Changes in the limitations of the following items/part numbers fitted to A330: 

 Inboard aileron servo-control: Life limitation amended for PNR 3337457-59, 

 Outboard aileron servo-control: Life limitation amended for PNR 3337458-59, 

 Rudder Travel Limitation Unit (RTLU): Life limitation amended for PNR 341400M02 and 

this part number is transferred from sub-part 4-2-2 to sub-part 4-2-1, 

 Pedal Travel Limitation Unit (PTLU): Life limitation amended for PNR 341400M02 and 

this part number is transferred from sub-part 4-2-2 to sub-part 4-2-1, 

 THSA PNR 47147-500 and PNR 47147-700 with the life limit of 36000 FH/24000 FC 

are transferred from sub-part 4-2-2 to sub-part 4-2-1, 

 THSA PNR 47172-300, 47172-500, 47172-510, 47172-520, 47172-530: an alternative 

set of life limitations is added, i.e. 65000 FH/20000 FC, 

 THSA PNR 47172-300: Life limitation of 25 Ye added, 

 Pressure switch PNR CMK80-01: Life limit in FH, i.e. 80000 FH, is removed, 

 Retraction actuator piston rod PNR 114256326 and PNR 114256328: Life limit reduced 

from 20950 LDG to 18000 LDG, 

 Retraction actuator pin (Main fitting side) PNR D61686: Life limitation in FH, i.e. 75000 

FH, is removed. 

SUB-PART 4-3:

 Task 274400-00001-1-E: Applicability amended. 

 Task 274400-00001-2-E: Applicability amended. 

 Task 274400-00001-3-E: Applicability amended. 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: AUG 27/13 ALS PART 4 HISTORY FILE PAGE: 4/5 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

 Task 274400-00001-4-E: Applicability amended. 

 Task 274400-00002-1-E: Description amended. 

 Task 292400-00001-1-E: Description, reference and applicability amended. 

 Task 275000-00001-4-E: Description and applicability amended. 

 Task 275000-00001-5-E: Description amended. 

Deletions: 

SUB-PART 4-0:

 Deletion of paragraph 1.C (2) Specific LOV applicable to A330 landing gear retraction 

actuator chain. 

SUB-PART 4-1:

 Figures deleted because of some items removed from sub-part 4-2. 

SUB-PART 4-2:

 The removal of the following items/part numbers fitted to A330 (refer to SIL 05-014 for the 

Recommended Tracking of components/items): 

 Inboard aileron servo-control PNR 3337457-60 and PNR C38661-002, 

 Outboard aileron servo-control PNR 3337458-60, and PNR C38657-002, 

 Rudder Trim Actuator (RTA) PNR 6197-1 and PNR 6197-2, 

 Rudder Travel Limitation Unit (RTLU) PNR 341400M01, PNR 343500M00, 

 Pedal Travel Limitation Unit (PTLU) PNR 341400M01, PNR 343500M00, 

 Rudder servo-control PNR 31110-080, PNR SC5300, PNR SC5300-1, PNR SC5300-

2, PNR SC5300-3, PNR SC5300-4, 

 Yaw damper servo-control PNR SC4710, PNR SC4710-1, 

 Back-up yaw damper Unit (BYDU) PNR 41800831001, PNR 41800831002, PNR 

41800831100, 

 Elevator servo-control PNR SC4800-74, PNR SC4800-94, PNR SC4800-104 and PNR 

SC4800-114, 

 Spoiler servo-control in position 1 PNR MZ4339390-12 (fitted to A330-300), PNR 

1387A0000-02, PNR 1387B0000-02 and PNR 1387C0000-01, 

 Spoiler servo-control in positions 2 to 6 PNR MZ4306000-12 (fitted to A330-300), PNR 

1386A0000-02, PNR 1386B0000-02 and PNR 1386C0000-01, 

 RAM Air Turbine PNR 766351, PNR 768084, PNR 770379, PNR 770952, PNR 

770952A, PNR 770952B, PNR 1702934 and PNR 1702934A, 

 Pitot Probe PNR C16195AA, PNR C16195BA (Refer to EASA AD 2009-0195 – 

“Navigation – Airspeed Pitot Probes – Replacement”), 

 Sensor – Angle Of Attack PNR 45150320, PNR C16291AA, PNR C19291AB, 

 Altimeter Standby PNR 64141-582-1 and PNR 64141-590-1, 
A330 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: AUG 27/13 ALS PART 4 HISTORY FILE PAGE: 5/5 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

 Indicator Standby Airspeed PNR 64050-868-1, 

 Compass Standby PNR KCA0105W, 

 Indicator Standby Horizon PNR 501-1568-34, PNR H321BHM1 and PNR H341BVM. 

SUB-PART 4-3:

None.