### 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. 

### 4 R 1-LEP AUG 27/13

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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. R

R

R

R

R

R

R

### 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 th e next accomplishment must be determined from

previous accomplishment date. R

### 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,

WV050 series R

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. R

### 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 (i ncluding 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 sa fety) 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 0 60000 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 0 60000 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

R

D

R

D

R

R

R

R

R

D

### A330 AIRWORTHINESS LIMITATIONS SECTION

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

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

### 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 ins pection 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. R

R

R

### A330 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 5

 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

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 6

 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:

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

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

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

Cp i = 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  

 

###  

 

 

 

 

 

 

 

R

R

R

### A330 AIRWORTHINESS LIMITATIONS SECTION

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 flui d 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

ISSUE: AUG 27/13 ALS PART 4-0 PAGE: 8

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

### 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 r epair 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 airworthine ss 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. R

R

### A330 AIRWORTHINESS LIMITATIONS SECTION

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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 trans ferable 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 limit ations 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 extens ion 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 excepti onal 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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 AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

### 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 procur able 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

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### 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 indica tion 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

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### (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

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### 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

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 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



### A LL All A330 aircraft.

A 330-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

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 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 fo r 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

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

Extensions up to 5% or 250 FC/LDG (whic hever 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 except ionally 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. 

### ATA 27-23-00 – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION – FIG. 03 R

### A330 AIRWORTHINESS LIMITATIONS SECTION

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

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

### ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 04 R

### A330 AIRWORTHINESS LIMITATIONS SECTION

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

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

### ATA 27-44-00 – THS HYDRAULIC ACTUATION – FIG. 05 R

### 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. 

### ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 08 R

### 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. 

### ATA 29-24-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 10 R

### 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



### ATA 32-11-00 – MAIN GEAR – FIG. 12 R

### 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



### ATA 32-31-00 – NORMAL EXTENSION AND RETRACTION – FIG. 16 R

### 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 RA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 1EASA APPROVEDAIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 4-2 SYSTEMS LIFE-LIMITED COMPONENTSSub-part 4-2-1 LIFE LIMITSNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xATA 26-23-00 FIRE PROTECTION – LOWER DECK CARGO COMPARTMENT FIRE EXTINGUISHING (FIG. 01)R Pressure reducer D41428 N/AN/A 20 Ye X X X X X X X XATA 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 FIN 9CS1, 10CS1, 9CS2 and10CS2 for outboard servo-controls (active and damping).(2) Embodiment of MOD 45512/SB A330-27-3054 introduces different PNR. MOD 45512factory embodied on MSN 229 and subsequent.Inboard aileron servocontrol (1) (2)3337457-22 6000 N/A N/A X X3337457-23 6000 N/A N/A X X3337457-26 18000 N/A N/A X X3337457-27 18000 N/A N/A X X3337457-30 32000 21600 N/A X X X3337457-31 32000 21600 N/A X X X3337457-35 32000 21600 N/A X X X3337457-36 32000 21600 N/A X X X3337457-37 32000 21600 N/A X X X3337457-38 32000 21600 N/A X X XOutboard aileronservo-control (1) (2)3337458-30 32000 21600 N/A X X X3337458-31 32000 21600 N/A X X X3337458-35 32000 21600 N/A X X X3337458-36 32000 21600 N/A X X X3337458-37 32000 21600 N/A X X X3337458-38 32000 21600 N/A X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 2EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xNATA 27-23 FLIGHT CONTROL – RUDDER AND PEDALTRAVEL LIMITING ACTUATION (FIG. 03)N (1) FIN 24CS.N (2) FIN 36CS.NRudder TravelLimitation Unit (RTLU)341400M02 (1) 100000 33000 N/A X X X XNPedal TravelLimitation Unit (PTLU)341400M02 (2) 100000 33000 N/A X X X XRATA 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 X XSC4800-3N/AN/A31-Aug-04 X X X XSC4800-4 N/A N/A31-Aug-04 X X X XSC4800-6 N/A N/A31-Aug-04 X X X XSC4800-7 N/A N/A 31-Aug-04 X X X XSC4800-7A N/A N/A 30-Jun-08 X X X X X X XSC4800-8 N/A N/A 31-Aug-04 X X X XSC4800-9 N/A N/A30-Jun-08 X X X X X X XSC4800-10 N/A N/A30-Jun-08 X X X X X X XSC4800-11 N/A N/A30-Jun-08 X X X X X X XSC4800-72 N/A N/A30-Jun-08 X X X X X X XSC4800-73 N/A N/A30-Jun-08 X X X X X X XSC4800-92 N/A N/A30-Jun-08 X X X X X X XSC4800-93 N/A N/A30-Jun-08 X X X X X X XSC4800-103 N/A N/A30-Jun-08 X X X X X X XSC4800-113 N/A N/A30-Jun-08 X X X X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 3EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 05)(1) Embodiment of MOD 45906/SBA330-27-3052 and MOD 49591/SB A330-27-3093 introduces different PNR. MOD 45906 factory embodiedon MSN 233 andsubsequent.(2) Embodiment of MOD 49590/SB A330-27-3085 introduces different PNR. MOD 49590factory embodied on MSN 437 and subsequent.NNNN(3) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906)and retrofitted into PNR 47147-500 bySB 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 retrofittedinto PNR 47147-500 (MOD49591/SB A330-27-3093). The sum of the accumulated lives PRE and POST SB A330-27-3052must not exceed 60000 FH/40000 FC, whichever occurs first.NNNNN(4) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906)and retrofitted into PNR 47147-500 bySB 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 retrofittedinto PNR 47147-500 (MOD49591/SB A330-27-3093) then retrofitted to PNR 47147-700 by SB A330-27-3143 (MOD 54881). The sum of the accumulated lives PRE and POST SB A330-27-3052 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 (1)47147-210 N/A N/A 31-Jul-04 X (1) X (1)47147-213 N/A N/A 31-Jul-04 X (1) X (1)47147-300 N/A N/A 31-Jul-04 X (1) X (1)47147-303 N/A N/A 31-Jul-04 X (1) X (1)47147-350 N/A N/A 31-Jul-04 X (1) X (1)47147-400 N/A N/A 31-Jul-04 X (1) X (1)N47147-500 36000 24000N/AX (3) X (3) X (3) X (3) X (3)N47147-700 36000 24000 N/A X (4) X (4) X (4) X (4) X (4)R47172 N/A N/A31-Dec-03X (2) X (2) X (2) X (2)RATA 27-54-00 FLIGHT CONTROL – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 06 & 07)(1) Embodiment of MOD 50044 and/orMOD 52591 (both associated to SB A330-27-3106)introduces different PNR. MOD 50044 and MOD 52591 factory embodiedon MSN 506, MSN 509 thru 521, MSN 524 and subsequent.Flap Rotary Actuator– Type A697510004 (1) N/A 18000 12 Ye X X X X697510005 (1) N/A 18000 12 Ye X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 4EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xFlap Rotary Actuator– Type B697511004 (1) N/A 18000 12 Ye X X X X697511005 (1) N/A 18000 12 Ye X X X X697511006 (1) N/A 18000 12 Ye X X X X697511007 (1) N/A 18000 12 Ye X X X XNFlap Power ControlUnit (PCU)953A0000-04 N/A N/A 31-Oct-14 X X X XN 953A0000-05N/AN/A31-Oct-14 X X X XN 953B0000-01N/AN/A31-Oct-14 X X X XRATA 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 A330-27-3113introduces different PNR.(2) FIN 13CS1 and 13CS2.(3) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1and 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 addition of the life accumulated bythe 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 equalto 8500 FC since aircraft initial entry into service, modify all servo-control actuators inaccordance 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-control actuators inaccordance 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. MOD48956 factory embodied on MSN 422, MSN 443 and subsequent.A330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 5EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRSpoiler servo-controlin position 1 (2)MZ4339390-01X(1)N/A 11000 (5) N/A X XR N/AN/A05-Mar-10(6)X X X X XRMZ4339390-02X(1)N/A 11000 (5) N/A X XRN/A N/A05-Mar-10(6)X X X X XRMZ4339390-10X(1)N/A 11000 (5) N/A X XRN/A N/A05-Mar-10(6)X X X X XRDMZ4339390-12(1)N/A 11000 (5) N/A X XS4-3000470(1) (5)N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000470-01(1) (5)N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000470-02(1) (5)N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000470-03(1) (5)N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)1387A0000-01 (7) N/A N/A 31-Dec-03 X X X X X X X1387B0000-01 (7) N/A N/A 31-Dec-03 X X X X X X XRSpoiler servo-controlin position 2 to 6 (3)MZ4306000-01X(1)N/A 6000 (5) N/A X XR N/AN/A05-Mar-10(6)X X X X XRMZ4306000-02X(1)N/A 6000 (5) N/A X XR.../...N/A N/A05-Mar-10(6)X X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 6EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRSpoiler servo-controlin position 2 to 6 (3)MZ4306000-10X(1)N/A 6000 (5) N/A X XR N/AN/A05-Mar-10(6)X X X X XRDMZ4306000-12(1)N/A 6000 (5) N/A X XS4-3000460(1)(5)N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000460-01(1)(5)N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000460-02(1)(5)N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000460-03(1)(5)N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)1386A0000-01 (7) N/A N/A 31-Dec-03 X X X X X X X1386B0000-01 (7) N/A N/A 31-Dec-03 X X X X X X XNATA 27-84 LIFT AUGMENTING - SLATS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 09)N (1) Comply with these requirements no later than 31-Oct-2014.NT-Gearbox (TGBx)921A0000-01 N/A N/A 31-Oct-14 X X X X X X X XN921B0000-01 (1) N/A 32000 N/A X X X X X X X XN921C0000-01 (1) N/A 24000 N/A X X X X X X X XN921D0000-01 (1) N/A 24000 N/A X X X X X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 7EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 11 to 13 & 16 to 17)RMAIN STRUT AND DRESSINGS (FIG. 11 & 13)Notes (1) to (6): Refer to CN97-007-042(B) latest approved revision.(1) 3250 LDG with an unserviceable retraction line Delay Valve.4300 LDG with a serviceable retraction line Delay Valve. Embodiment of MOD 43863 or MOD45031/SB A330-32-3066 introduces a differentPNR. MOD 43863 factory embodied on original landing gear of MSN 116 and subsequent.(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 applicableto SNR 003WHM (only this SNR exists).(5) For this PNR, note (1) is applicableto 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 introduces a different PNR.MOD 43863 factory embodied on originallanding gear of MSN 116 and subsequent.(7) Embodiment of MOD 46903/SBA330-32-3096 introduces a different PNR. MOD46903 factory embodied on original landing gear ofMSN 271 and subsequent.(8) Embodiment of MOD 46904/SBA330-32-3095 introduces a different PNR. MOD46904 factory embodied on original landing gear ofMSN 271 and subsequent.(9) Embodiment of MOD 48066/SBA330-32-3123 introduces a different PNR. MOD48066 factory embodied on original landing gear ofMSN 366 and subsequent.(10) Life limit is the later of 900 aircraft FH counted from08-Jul-2009 or the accumulation of 11150 total LDG since initialentry into service of Pin W1 on any aeroplane.(11) Life limit is the earlier ofthe 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 W201275796 (7) N/A 20000 10 Ye X X X X X X X201478613 N/A 42800 N/A X X X X X X X201489770 N/A 42800 N/A X X X X X X X XRetraction link (LH) 201275317 (9) N/A 35200 36 Mo X X X X X X X201489311 (12) N/A 8400 N/A X X X X X X XRetraction link (RH) 201275318 (9) N/A 35200 36 Mo X X X X X X X201489312 (12) N/A 8400 N/A X X X X X X XPin W1201275673 (7) (11) N/A (10) 10 Ye X X X X X X X201478614 N/A (10) N/A X X X X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 8EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction bracket(LH)201428305 N/A (1) N/A X X201428307 N/A (1) N/A X X201428318 N/A (1) N/A X X201428323 N/A (1) N/A X X201428331 (2) N/A (1) N/A X X201428331 (6) N/A 9000 N/A X X201428333 N/A (1) N/A X X201428335 N/A (1) N/A X X201428338 (4) N/A (1) N/A X X201428351 N/A 19800 N/A X X X X X X X201428378 N/A 19800 N/A X X X X X X X201428380 N/A 19800 N/A X X201428382 N/A 19800 N/A X X201428384 N/A 19800 N/A X X201478303 N/A 19800 N/A X X201478305 N/A 19800 N/A X X201478307 N/A 19800 N/A X XRetraction bracket(RH)201428306 N/A (1) N/A X X201428308 N/A (1) N/A X X201428319 N/A (1) N/A X X201428324 N/A (1) N/A X X201428332 (3) N/A (1) N/A X X201428332 (6) N/A 9000 N/A X X201428334 N/A (1) N/A X X.../...201428336 N/A (1) N/A X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 9EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction bracket(RH)201428339 (5) N/A (1) N/A X X201428352 N/A 19800 N/A X X X X X X X201428379 N/A 19800 N/A X X X X X X X201428381 N/A 19800 N/A X X201428383 N/A 19800 N/A X X201428385 N/A 19800 N/A X X201478304 N/A 19800 N/A X X201478306 N/A 19800 N/A X X201478308 N/A 19800 N/A X XPin W2201275667 (8)N/A 4500 5 Ye X XN/A 9400 5 Ye X X X X X201478615 N/A 42800 N/A X X X X X X X201478637 N/A 42800 N/A X X X X X X XPin P201275602 (7) N/A 20000 10 Ye X X X X X X X201478612 N/A 42800 N/A X X X X X X XRRETRACTION ACTUATOR (FIG. 11 & 16)(1) Rework in accordance with SB A330-32-3216 (MOD 56557) may introduce a different PNR.(2) Embodiment of MOD200837/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 gearof MSN 1092 and subsequent for A330-200F series.Retraction actuatorpiston rod114256309 N/A 8080 31-Dec-07 X X X X X X X114256321 (1) N/A 8080 31-Dec-07 X X X X X X X114256323 N/A 5500 N/A X X X X X X XR114256326 N/A 18000 N/A X X X X X X XR114256328 N/A 18000 N/A X X X X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 10EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction actuatorgland50-2113004-00(2)N/A 27790 N/A X X X X X XRetraction actuatorcylinder114256310 N/A 22900 N/A X X X X X X X114256320 N/A 22900 N/A X X X X X X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 14 & 15)RRETRACTION ACTUATOR (FIG. 15)Retraction actuatorbodyD61954 N/A 30000 N/A X X X X X X XD61954-10 N/A 30000 N/A X X X X X X XD67876 N/A 30000 N/A X X X X X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-1 PAGE: 11EASA 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.RExplanation notes are located under theassy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xDRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xATA 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 X X XRATA 35-23-00 OXYGEN – PASSENGER OXYGEN (GASEOUS) – CONTROL ANDINDICATING (FIG. 19)Quantity CalculationControl UnitE69027 80000 N/A 20 Ye X X XEND OF SUB-PART 4-2-1A330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-2 PAGE: 12EASA APPROVEDAIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 4-2-2 CURRENT DEMONSTRATED LIVESNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.Explanation notes are located under theassy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xATA 27-14-00 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 02)(1) Applicable to servo-control installedin positions FIN 7CS1, 8CS1, 7CS2 and 8CS2for inboard servo-controls, and FIN 9CS1,10CS1, 9CS2 and 10CS2 foroutboard servo-controls(active and damping).RDRDRInboard aileron servocontrol (1)3337457-59 110000 N/A N/A X X X X X X X XOutboard aileronservo-control (1)3337458-59 110000 N/A N/A X X X X X X X XATA 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.RDR(3) Embodiment of MOD 58916/SB A330-27-3172 introduces different PNR. MOD58916 factory embodied on MSN 1095 and subsequent.THS Actuator47172-300 (1)60000 4000025 YeX X X X X X XN65000 2000025 YeX X X X X X XR47172-500 (2)60000 40000 25 Ye X X X X X X X XN65000 20000 25 Ye X X X X X X X XR47172-510 (3)60000 40000 25 Ye X X X X X X X XN65000 20000 25 Ye X X X X X X X X47172-52060000 40000 N/A X X X X X X X XN65000 20000 N/A X X X X X X X X47172-53060000 40000 N/A X X X X X X X XN65000 20000 N/A X X X X X X X XDA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-2 PAGE: 13EASA 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 theassy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 11 to 13 & 16 to 17)RMAIN 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 X XRetraction link (LH) 50-2105026-00N/A 46480 N/A X X X X X X50-2105224-00 N/A 46480 N/A X X X X X X201489315 N/A 10700 N/A X X X X X X XRetraction link (RH) 50-2106026-00N/A 46480 N/A X X X X X X50-2106224-00 N/A 46480 N/A X X X X X X201489316 N/A 10700 N/A X X X X X X XPin W1 55-2105060-00 N/A 46480 N/A X X X X X XN201478652 N/A 25179 N/A X X X X X X XRetraction bracket(LH)50-2105027-00 N/A 46480 N/A X X X X X XRetraction bracket(RH)50-2106027-00 N/A 46480 N/A X X X X X XPin W2 55-2105059-00 (1) N/A 46480 N/A X X X X X XPin P 55-2105059-00 (1) N/A 46480 N/A X X X X X XRCOMPLETE SIDE STAY (FIG. 13)Lock stay actuator pin 201440611N/A 50000 N/A X X201457606 N/A 50000 N/A X XRLOCK STAY ACTUATOR (FIG. 17)Lock stay actuatorcylinder114354600 N/A 50000 N/A X X201686600 N/A 50000 N/A X XLock stay actuatorpiston rod114354605 N/A 50000 N/A X X201686602 N/A 50000 N/A X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-2 PAGE: 14EASA 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 theassy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xLock stay actuatorgland114354606 N/A 50000 N/A X X201481611 N/A 50000 N/A X X201481614 N/A 50000 N/A X XLock stay actuator rodend114354602 N/A 50000 N/A X X201686601 N/A 50000 N/A X XRRETRACTION ACTUATOR (FIG. 11 & 16)(1) Must be replaced by a new one every time the piston head is removedfrom the piston rod.Retraction actuatorpiston rod50-2113002-00 N/A 50000 N/A X X X X X XRetraction actuatorgland114256312 N/A 50000 N/A X X X X X X X114256322 N/A 50000 N/A X X X X X X X50-2113004-01 N/A 27790 N/A X X X X X XRetraction actuatorpiston head114256308 N/A 50000 N/A X X X X X X X114256639 N/A 50000 N/A X X X X X X X50-2113003-00 N/A 50000 N/A X X X X X XRetraction actuatorinsert114256629 N/A (1) N/A X X X X X X X XRetraction actuatorcylinder50-2113001-00 N/A 50000 N/A X X X X X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 14 & 15)(1) ‘xx’ at the end of the PNRs stands forany number between 00 and 99, including unused digits.Retraction actuatorpin (airframe side) (1)F53112357200xx N/A 50000 N/A X X X XF53112357204xxN/A 50000 N/A X XN/A 41250 N/A X X XF53114022200xxN/A 50000 N/A X XN/A 41250 N/A X X XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-2 PAGE: 15EASA 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 theassy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction actuatorpin (airframe side) (1)F53114023200xx N/A 50000 N/A X X X XF53120422200xxN/A 50000 N/A X XN/A 41250 N/A X X X XRNOSE LANDING GEAR LEG (FIG. 14)RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 14)RRetraction actuatorpin (Main fitting side)D61686N/A 50000 N/A X X X X X X XN/A 18000 N/A XRRETRACTION ACTUATOR (FIG. 15)Retraction actuatoreye endD62588N/A 50000 N/A X X X X X X XN/A 18000 N/A XD62588-1N/A 50000 N/A X X X X X X XN/A 18000 N/A XD67840N/A 50000 N/A X X X X X X XN/A 18000 N/A XRetraction actuatorbearingD61950-1N/A 50000 N/A X X X X X X XN/A 18000 N/A XD61950-10N/A 50000 N/A X X X X X X XN/A 18000 N/A XD67839N/A 50000 N/A X X X X X X XN/A 18000 N/A XND68397N/A 50000 N/A X X X X X X XNN/A 18000 N/A XA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-2-2 PAGE: 16EASA 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 theassy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxF A330-2xx A330-30x A330-32x/A330-34xNomenclature Part NumberFH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction actuatorsliding rodD62328N/A 50000 N/A X X X X X X XN/A 18000 N/A XD62328-1N/A 50000 N/A X X X X X X XN/A 18000 N/A XD67837N/A 50000 N/A X X X X X X XN/A 18000 N/A XRetraction actuatorplugD61952N/A 50000 N/A X X X X X X XN/A 18000 N/A XD61952-1N/A 50000 N/A X X X X X X XN/A 18000 N/A XD67838N/A 50000 N/A X X X X X X XN/A 18000 N/A XRetraction actuatorcylinderD62587N/A 50000 N/A X X X X X X XN/A 18000 N/A XD62587-1N/A 50000 N/A X X X X X X XN/A 18000 N/A XD67836N/A 50000 N/A X X X X X X XN/A 18000 N/A XNRetraction actuatorbodyD61954 N/A 18000 N/A XND61954-10 N/A 18000 N/A XND67876 N/A 18000 N/A XDEND OF SUB-PART 4-2-2A330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-3-1 PAGE: 1EASA APPROVEDAIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTSSub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRN274400-00001-1-E311312THSA – FIG. 05Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the gap atthe secondary nuttrunnion.This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.Note 2: In computing the life accumulated bythe THSA for compliance with thethreshold, calculations must includeflight hours since theinitial entry intoservice or since 17-Aug-2002,whichever occurs later.700 FHNotes 1 & 2700 FHNote 1SB A330-27-3102 R08AMM 27-44-5147147-50047172-300PRE 27-3143PRE 27-3137PRE 27-3181PRE 55780RR274400-00001-2-E311312THSA – FIG. 05Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note: No short-term extension is allowed.700 FHNote700 FHNoteSB A330-27-3102 R08AMM 27-44-5147172-50047172-520POST 27-3137PRE 56056PRE 92-3046R05A330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-3-1 PAGE: 2EASA 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 TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRRNNNNN274400-00001-3-E 311312THSA – FIG. 05Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note: No short-term extension is allowed.700 FHNote700 FHNoteSB A330-27-3102 R08AMM 27-44-5147172-51047172-530POST 55780PRE 56056PRE 92-3046R05ORPOST 27-3181PRE 56056PRE 92-3046R05RR274400-00001-4-E 311312THSA – FIG. 05Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note: No short-term extension is allowed.700 FHNote700 FHNoteSB A330-27-3102 R08AMM 27-44-5147147-700 A330-300POST 27-3143PRE 92-3046R05PRE 56056RRRNNNNN274400-00002-1-E311312THSA – FIG. 05Lubrication of the THSA ball-nut.Note 1: No short-term extension is allowed.Note 2: This task must be carried out at theopportunity of ASM tasks 274400-00001-1-E, 274400-00001-2-E,274400-00001-3-E and 274400-00001-4-E once applicable.1000 FHNote 11000 FHNote 1AMM 12-22-27/30147147-50047147-70047172-30047172-50047172-51047172-52047172-530ALLA330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-3-1 PAGE: 3EASA 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 TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRRRRRRRRRR292400-00001-1-E 633Ram Air Turbine (RAT) – FIG. 10Remove RAT (including actuator, manifold,hydraulic pump, turbine-lower gearboxassembly and strut-lug assembly), for overhauland replace with serviceable units.20 Ye.20 Ye.AMM 292452-960-801RAT (includingactuator,manifold,hydraulic pump,turbine-lowergearboxassembly andstrut-lugassembly)ALLALLEND OF SUB-PART 4-3-1A330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-3-2 PAGE: 4EASA APPROVEDAIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFT275000-00001-1-E570670FlapsPerform a simultaneous detailed visualinspection of the InputGear Boxes (IPGB) andof the Down Drive Shafts (DDS) on flap tracks 2and 4 on both wings.Note 1: No short-term extension is allowed.Note 2: Report inspection results, whateverthey are, to AIRBUS.16-Dec-2007Notes 1 & 2N/ASB A330-27-3151AMM 27-54-56AMM 27-54-57N/AUp to MSN 0183inclusive275000-00001-2-E570670FlapsPerform a simultaneous detailed visualinspection of the InputGear Boxes (IPGB) andof the Down Drive Shafts (DDS) on all flaptracks on both wings.Note 1: No short-term extension is allowed.Note 2: First inspection is performed inaccordance with SB A330-27-3151.Report inspection results, whateverthey are, to AIRBUS.Subsequent repetitive inspections areperformed in accordance with SBA330-27-3152.16-Aug-2009Notes 1 & 26 YeNotes 1 & 2SB A330-27-3151SB A330-27-3152AMM 27-54-56AMM 27-54-57N/AUp to MSN 0420inclusivePRE 200492PRE 201194(27-3173)A330 AIRWORTHINESS LIMITATIONS SECTIONISSUE: AUG 27/13 ALS PART 4-3-2 PAGE: 5EASA 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 TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFT275000-00001-3-E570670FlapsPerform a simultaneous detailed visualinspection of the InputGear Boxes (IPGB) andof the Down Drive Shafts (DDS) on all flaptracks on both wings.Note: No short-term extension is allowed.26-Oct-2009or6 years fromthe date oforiginaldelivery ofthe aircraft,whicheveroccurs later.Note6 YeNoteSB A330 27-3152AMM 27-54-56AMM 27-54-57N/AMSN 0421(inclusive)onwardsPRE 200492PRE 201194(27-3173)NNR275000-00001-4-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS) for all flap tracks on both wings.24 Mo 24 Mo AMM 12-22-27 N/A POST 200492PRE 201194(27-3173)R275000-00001-5-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS) for all flap tracks on both wings.One-time inspection for corrosion inaccordance with SB A330-27-3173 at the timeof SB A330-27-3173 embodiment.24 Mo SB A330-27-3173AMM 12-22-27N/A POST 201194(27-3173)END OF SUB-PART 4-3-2

### A330 AIRWORTHINESS LIMITATIONS SECTION

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### 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

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###  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

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###  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 foll owing 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

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###  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

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© 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.