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REVISION: 03 

# A330



# ALS Part 4

- Ageing Systems Maintenance

© AIRBUS SAS 2011. 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.

### AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

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

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4 R 1-LEP SEP 09/11

4 1-TOC NOV 04/08

4 R 1-ROR SEP 09/11

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

TABLE OF CONTENTS

SUBJECT PART

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

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# A330

RECORD OF REVISIONS ROR

INTRODUCTION 4-0

ILLUSTRATIONS 4-1

SYSTEMS LIFE LIMITED COMPONENTS 4-2

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 4-3

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

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

EASA APPROVED

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# A330

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

R

R

R 02 ROR

4-2

4-3 DEC 16/09 N/A

N

N

N 03 ROR

4-2

4-3 SEP 09/11

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

Revision 03 is approved by EASA under reference 10036453.

REVISION 03 COMPLIANCE TIME:

1. Except as stated in paragraph 3. of this Record Of Revisions (ROR), 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 03 from 09-Sep-2012.

2. From 09-Sep-2011 to 08-Sep-2012, 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 02, except as stated in

paragraph 3. of this ROR,

or,

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

3. From 09-Sep-2011, it is mandatory to comply with the maintenance requirements and

associated airworthiness limitations defined in the A330 ALS Part 4 revision 03 for: R

R

R

R

R

R

R

R

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

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

EASA APPROVED

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# A330

− THSA PNR 47172-520,

− The spoiler servo-control in position 1 PNR 1387A0000-01, and PNR 1387B0000-01,

− The spoiler servo-control in positions 2 to 6 PNR 1386A0000-01, and PNR 1386B0000-

01,

− The retraction bracket (LH) PNR 201428351, PNR 201428378, PNR 201428380, PNR

201428382, PNR 201428384, PNR 201478303, PNR 201478305, PNR 201478307,

− The retraction bracket (RH) PNR 201428352, PNR 201428379, PNR 201428381, PNR

201428383, PNR 201428385, PNR 201478304, PNR 201478306, PNR 201478308,

− The pitot probe PNR C16195BA,

− The AOA sensor PNR C16291AB.

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

previous accomplishment date. N

N

N

N

N

N

N

N

N

N

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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) listed in the table below:

Aircraft series Aircraft models W V

R

R

A330-200 A330-201 020, 023, 024, 050, 052, 054, 055, 056, 057,

058, 059, 060, 061

R A330-202 020, 021, 022, 023, 050, 052, 053, 054, 055,

056, 057, 058, 059, 060, 061

A330-203 020, 022, 023, 026, 050, 051, 052, 054, 055,

056, 057, 058, 059, 060, 061 R

R A330-223 020, 021, 022, 023, 050, 052, 054, 055, 056,

057, 058, 059, 060, 061

R A330-243 020, 021, 022, 023, 024, 025, 026, 027, 050,

052, 054, 055, 056, 057, 058, 059, 060, 061

N A330-200F A330-223F 000, 001, 002

N A330-243F 000, 001, 002

A330-300 A330-301 000, 001, 002, 003, 004, 010, 051

A330-302 050, 052, 053

A330-303 050, 052

A330-321 000, 002, 003, 004, 010, 011, 012, 013

A330-322 000, 002, 003, 004, 010, 011, 012, 013

A330-323 020, 022, 025, 050, 052

A330-341 000, 002, 003, 004, 010, 011, 012, 013, 014

A330-342 000, 002, 003, 004, 010, 011, 012, 013, 014,

022, 052

A330-343 020, 022, 024, 050, 052

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# A330

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

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

B. Ageing Systems Maintenance (ASM)

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

preventative maintenance requirements (including replacements) and associated

airworthiness limitations within the relevant aircraft systems operational life, 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 within the relevant aircraft systems operational life will also be included to

complement the mandatory preventative maintenance requirements (refer also to ALS

sub-part 4-0, paragraph 1.D.).

This Part 4 of the ALS has been created to contain the maintenance requirements and

their associated airworthiness limitations to help to qualify the systems installations for

continued operation up to the Limit Of Validity (LOV) shown hereafter.

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 (Change in LOV).

− 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. Limit Of Validity (LOV)

Operation of aircraft systems up to the stated Limit Of Validity (in Flight Hours or Flight

Cycles, whichever occurs first) is covered by this document. The relevant LOV values

are stated below. The aircraft systems must not be operated beyond these values

unless the Type Certificate Holder (i.e. Airbus) has updated this document to include a

clearly defined LOV extension. R

R

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# A330

(1) General LOV applicable to A330 systems installations

Aircraft series LOV

Flight Hours

(FH) Flight Cycles

(FC)

A330-200 series WV020’s OR 0 60000 40000

100000 (*) 33000 (*)

A330-200 series WV050’s & WV060’s 100000 33000

A330-200F series WV000’s 100000 33000

A330-300 series WV000’s, WV010’s &

WV020’s OR 0 60000 40000

100000 (*) 33000 (*)

A330-300 series WV050’s 100000 33000

(*) Applies only to aircraft POST MODification (MOD) 200103 or POST Service

Bulletin (SB) A330-00-3068 R01.

Note: When different sets of LOV are indicated for a given aircraft series, no

combination of values extracted from different sets is permitted.

The life limitations for some Part NumbeR (PNR) may exceed the stated LOV as a

result of analyses/tests carried out for another aircraft application having a greater

LOV.

(2) Specific LOV applicable to A330 landing gear retraction actuator chain

Main Landing Gear (MLG) LOV

Flight Hours Landings

A330-300 series WV000’s & WV010’s

PNR 201252 series (basic) 0 75000 50000

A330-200/-300 series WV020’s & WV050’s

PNR 201490 series (growth) 0 75000 50000

PNR 10-210 series (enhanced) 125000 50000

A330-200 series WV060’s

PNR 10-210 series (enhanced) 125000 50000

A330-200F series WV000’s

PNR 10-210 series (enhanced) 125000 50000

Nose Landing Gear (NLG) LOV

Flight Hours Landings

A330-300 series, WV000’s & WV010’s

PNR D23285 series (basic) 0 75000 50000

PNR D23581 series (reinforced) 0 75000 50000

A330-200/-300 series, WV020’s & WV050’s

PNR D23581 series (reinforced) 0 75000 50000

A330-200 series WV060’s

PNR D23581 series (reinforced) 75000 50000

A330-200F series WV000’s

PNR D23581 series (reinforced) 125000 50000 N

N

N

N

D

R

R

N

N

N

R

N

N

R

R

R

N

N

N

N

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# A330

The list of the approved weight variants is provided in the Type Certification Data Sheet

(TCDS) N°A.004 issued by the EASA, together with the associated modification

configuration(s).

To determine the applicable WV at the time of aircraft delivery, refer to the list of

modifications embodied during production, provided to the initial Operator of the

aircraft, in the delivery documentation (Aircraft Inspection Report ‘Conformity to Design

Standard Requirements’).

A WV status may evolve as a result of the embodiment of Airbus SB.

It is the Operators’ responsibility to identify the applicable aircraft WV and to refer to the

appropriate airworthiness limitation(s) given in this ALS Part 4.

Note 1: The modifications and SB associated to the approved WV are summarised

below:

− A330-200 series WV020’s applications:

WV020: Basic aircraft.

WV021: Aircraft POST MOD 46892 or POST SB A330-00-3019.

WV022: Aircraft POST MOD 47784 or POST SB A330-00-3026.

WV023: Aircraft POST MOD 47888.

WV024: Aircraft POST MOD 49819.

WV025: Aircraft POST MOD 50864 or POST SB A330-00-3028.

WV026: Aircraft POST MOD 51712.

WV027: Aircraft POST MOD 54519.

− A330-200 series WV050’s and WV060’s applications:

WV050: Aircraft POST MOD 51802.

WV051: Aircraft POST MOD 51803.

WV052: Aircraft POST MOD 51804.

WV053: Aircraft POST MOD 53109.

WV054: Aircraft POST MOD 54106.

WV055: Aircraft POST MOD 54107.

WV056: Aircraft POST MOD 55813.

WV057: Aircraft POST MOD 58859 or POST201436.

WV058: Aircraft POST MOD 58860 or POST 201437.

WV059: Aircraft POST MOD 57439.

WV060: Aircraft POST MOD 57440.

WV061: Aircraft POST MOD 200561.

− A330-200F series WV000’s applications:

WV000: Aircraft POST MOD 200589.

WV001: Aircraft POST MOD 58981.

WV002: Aircraft POST MOD 200989. D

R

N

N

N

N

N

N

N

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# A330

− A330-300 series WV000’s and WV010’s applications:

WV000: Basic aircraft.

WV001: Aircraft POST MOD 42200.

WV002: Aircraft POST MOD 42600 or POST SB A330-00-3003 or, POST

MOD 44700 or POST SB A330-00-3006.

WV003: Aircraft POST MOD 44270 or POST SB A330-00-3004.

WV004: Aircraft POST MOD 44849.

WV010: Aircraft POST MOD 43308 or POST SB A330-00-3014.

WV011: Aircraft POST MOD 44803.

WV012: Aircraft POST MOD 45086 or POST SB A330-00-3020.

WV013: Aircraft POST MOD 46688 or POST SB A330-00-3015.

WV014: Aircraft POST MOD 48377 or POST SB A330-00-3024.

− A330-300 series WV020’s and WV050’s applications:

WV020: Aircraft POST MOD 46028.

WV022: Aircraft POST MOD 47785 or POST SB A330-00-3023 or, POST

MOD 50943 or POST SB A330-00-3039.

WV024: Aircraft POST MOD 48350.

WV025: Aircraft POST MOD 49651.

WV050: Aircraft POST MOD 51805 or, POST MOD 53107 or SB A330-

00-3036.

WV051: Aircraft POST MOD 51806.

WV052: Aircraft POST MOD 51807 or POST SB A330-00-3035.

WV053: Aircraft POST MOD 52924.

Note 2: Multiple operation weight configurations are summarised below:

− Airworthiness limitations applicable to A330-243 WV020 also apply to

aircraft POST MOD 50302 (A330-200 series with dual MTOW 230/192

tons).

− Airworthiness limitations applicable to A330-243 WV022 also apply to

aircraft POST MOD 50830 or POST SB A330-00-3027 (A330-200 series

with triple MTOW 233/230/220 tons).

− Airworthiness limitations applicable to A330-302 WV050 also apply to

aircraft POST MOD 52910 (A330-300 series with dual MTOW 230/205

tons).

− Airworthiness limitations applicable to A330-202 WV050 also apply to

aircraft POST MOD 53108 (A330-200 series with dual MTOW 230/210

tons).

− Airworthiness limitations applicable to A330-203 WV052 also apply to

aircraft POST MOD 54105 (A330-200 series with triple MTOW

233/230/192 tons).

− Airworthiness limitations applicable to A330-243 WV020 also apply to

aircraft POST MOD 54518 or POST SB A330-00-3044 (A330-200 series

with quadruple MTOW 230/220/202/192 tons).

− Airworthiness limitations applicable to A330-202 WV052 also apply to

aircraft POST MOD 57441 (A330-200 series with quadruple MTOW

233/220/202/192 tons).

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− Airworthiness limitations applicable to A330-202 WV054 also apply to

aircraft POST MOD 58324 (A330-200 series with quadruple MTOW

230/220/202/192 tons).

− Airworthiness limitations applicable to A330-202 WV052 also apply to

aircraft POST MOD 200099 (A330-200 series with dual MTOW 233/202

tons).

D. ALS Part 3 and ALS Part 4 correlation

At time of original Type Certification, 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.

Should additional repetitive maintenance tasks of this nature be necessary within the

applicable LOV, they will be included in the ALS Part 4.

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 less than or equal to the applicable LOV, due

to the difficulty to define a continued/enhanced inspection program, 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 less than the

LOV 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 without failure but whose failure could result in an unsafe condition of the

aircraft.

Where the values are less than the LOV, tests are still on-going. For these

components/items, the life limitation provided is temporary, waiting for completion of

the tests. If the demonstrated life reaches the LOV, it will remain in sub-part 4-2-2. If

the component/item fails before the LOV, its part number together with the life limit(s)

will be transferred to sub-part 4-2-1. N

N

N

N

N

N

R

R

R

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# A330

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

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

The continued/enhanced inspection program given in this sub-part includes

airworthiness limitations less than or equal to the applicable LOV to prevent aircraft

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

airworthiness limitations are determined in consideration of the probability of an aircraft

system level failure condition or conditions.

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 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.

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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.

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).

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 R

R

R

R

R

R

R

R R

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# A330

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 LOV 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 and/or the LOV, 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.

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 and/or LOV. Examples of these means are:

− Record keeping system, i Cp

j Cp j Ca

1 i Tr × ∑

− = 

### ⎥ ⎥

⎦ ⎤

⎢ ⎢

⎣ ⎡

⎟ ⎟

⎠ ⎞

⎜ ⎜

⎝ ⎛ R

R

R

R

R

R

N

N

N

R

R

R

R

R

N

N

N

N

N

N

N

N

N

N

N

N

N

R

### AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-0 PAGE: 10

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# A330

− Non-permanent markings,

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

The ultimate solution is the mutilation beyond repair limits to prevent rework to appear

to be airworthy.

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), Vo lume 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) N

N

N

R

D

N

N

N

N

N

N

N

N

N

N

N

R

R

N

N

N

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

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 changes 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 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. For example, Supplemental

Type Certificates (STC), which have been designed by Airbus Corporate Jet Centre

(ACJC) or which have been transferred from former Airbus Deutschland, or other entity,

under DOA Certificate EASA.21J.031 are not considered in this ALS Part 4.

When such an aircraft/a sub-assembly/a co mponent/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

R

R

R

R

R

R

R

N

N

R

R

N

N

N

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

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”. R

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

Limit of Validity (LOV): The LOV, as stated in the ALS Part 4, is the time at

which the maintenance programme defined in that Part

ceases to be valid. The applicable LOV are indicated in

the sub-part 4-0, paragraph 1.C.

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 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’), R

R R

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

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

− Messier-Dowty SA Service Bulletin number:

− D23285-32-040 (nose landing gear).

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. R

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

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

column, excluding the A330-341 model.

(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

(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 LOV, 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:

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

(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,

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.

Usage parameters are defined in the paragraph 2 of this sub-part. R

R

R

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

(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 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.

A330-223

OR

A330-341

PRE nnnnn All A330-223, or

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

### AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-0 PAGE: 18

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# A330

Applicability Task applicable to

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.

(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. R N

N

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

(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 R

RAIRWORTHINESS LIMITATIONS SECTION

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

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# A33 0

Sub-part 4-1 ILLUSTRATIONS

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

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

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# A33 0

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

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 3

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# A33 0

ATA 27-22-00 – RUDDER TRIM ACTUATION AND ARTIFICIAL FEEL – FIG. 03AIRWORTHINESS LIMITATIONS SECTION

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

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# A33 0

ATA 27-23-00 – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION – FIG. 04AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 5

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# A33 0

ATA 27-24-00 – RUDDER HYDRAULIC ACTUATION – FIG. 05AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 6

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# A33 0

ATA 27-26-00 – YAW DAMPER ACTUATION – FIG. 06 Yaw Damper ActuatorAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 7

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# A33 0

ATA 27-26-00 – BACK-UP YAW DAMPER ACTUATION – FIG. 07 Back-up Yaw Damper UnitAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 8

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# A33 0

ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 08AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 9

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# A33 0

ATA 27-44-00 – THS HYDRAULIC ACTUATION – FIG. 09AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 10

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# A33 0

ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 10AIRWORTHINESS LIMITATIONS SECTION

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

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# A33 0

ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 11AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 12

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# A33 0

ATA 29-24-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 12AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 13

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# A33 0

(*) Location, item not illustrated

FORWARD

ATA 32-11-00 – MAIN GEAR – FIG. 13 Pin P (*) Retraction

actuator

Lock stay

actuator

Side Stay

AssemblyAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 14

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# A33 0

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. 14AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 15

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# A33 0

Lock link

(subassembly) Lock stay actuator

pin (x2)

ATA 32-11-00 – MAIN GEAR – FIG. 15 Side Stay AssemblyAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 16

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# A33 0

ATA 32-21-00 – NOSE GEAR – FIG. 16 Retraction actuator pin

(main fitting side) Main FittingAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 17

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# A33 0

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

cylinderAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 18

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# A33 0

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. 18AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 19

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# A33 0

ATA 32-31-00 – NORMAL EXTENSION AND RETRACTION – FIG. 19 Lock stay actuator

piston rod Lock stay actuator

cylinder Lock stay actuator

rod end

Lock stay actuator

glandAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 20

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# A33 0

ATA 34-11-00 – NAVIGATION – PITOT PROBE – FIG. 20AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 21

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# A33 0

ATA 34-11-00 – NAVIGATION – ANGLE OF ATTACK SENSOR – FIG. 21AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 22

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# A33 0

ATA 34-21-00 – ALTITUDE AND AIRSPEED STANDBY DATA – FIG. 22AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 23

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# A33 0

ATA 34-22-00 – ATTITUDE AND HEADING STANDBY DATA – FIG. 23AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 24

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# A33 0

ATA 35-13-00 – CREW OXYGEN – CONTROL AND INDICATING – FIG. 24 Pressure SwitchAIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 09/11 ALS PART 4-1 PAGE: 25

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# A33 0

ATA 35-23-00 – PAX OXYGEN (GASEOUS) – CONTROL AND INDICATING – FIG. 25

END OF SUB-PART 4-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 1EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330Sub-part 4-2 SYSTEMS LIFE LIMITED COMPONENTSSub-part 4-2-1 LIFE LIMITSRNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xATA 26-23-00 FIRE PROTECTION – LOWER DECK CARGO COMPARTMENT FIRE EXTINGUISHING (FIG. 01)DPressure reducer D41428 N/A N/A 20 Ye X X X X X X XATA 27-14-00 FLIGHT CONTROL – AILERONAND HYDRAULIC ACTUATION (FIG. 02)RR(1) Applicable to servo-controls in positions Functional Item Number (FIN) 7CS1, 8CS1, 7CS2 and 8CS2 for inboard servo-controls, and FIN 9CS1, 10CS1, 9CS2and 10CS2 for outboard servo-controls (active and damping).D(2) Embodiment of MOD 45512/SB A330-27-3054introduces different PNR. MOD 45512 factory embodied on MSN 229 and subsequent.Inboard aileron servocontrol (1) (2)3337457-22 6000 N/A N/A X XD3337457-23 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 XD3337457-31 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 XD3337458-31 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 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 2EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 27-34-00 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC CONTROL (FIG. 08)(1) Applicable to elevator servo-controls installed inpositions 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 XSC4800-3 N/A N/A 31-Aug-04 X X X XSC4800-4 N/A N/A 31-Aug-04 X X X XSC4800-6 N/A N/A 31-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/A 30-Jun-08 X X X X X X XSC4800-10 N/A N/A 30-Jun-08 X X X X X X XSC4800-11 N/A N/A 30-Jun-08 X X X X X X XSC4800-72 N/A N/A 30-Jun-08 X X X X X X XSC4800-73 N/A N/A 30-Jun-08 X X X X X X XSC4800-92 N/A N/A 30-Jun-08 X X X X X X XSC4800-93 N/A N/A 30-Jun-08 X X X X X X XSC4800-103 N/A N/A 30-Jun-08 X X X X X X XSC4800-113 N/A N/A 30-Jun-08 X X X X X X XRATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 09)(1) Embodiment of MOD 45906/SB A330-27-3052 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 49590 factory embodied on MSN 437 and subsequent.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)AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 3EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xTHS Actuator 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)47172 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. 10)RR(1) Embodiment of MOD 50044 and/or MOD 52591 (both associated toSB 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 XFlap 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 XRATA 27-64-00 FLIGHT CONTROL – SPOILERHYDRAULIC ACTUATION (FIG. 11)(1) Not applicable to aircraft POST MOD 44670 and delivered from13-Jan-2006 onwards. Embodimentof MOD 51413/SB A330-27-3113introduces different PNR.(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 addition of the life accumulatedby 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.AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 4EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05x(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 FCsince 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.N(7) Embodiment of MOD 48956/SB A340-27-3094 introduces different PNR. MOD 48956 factory embodied on MSN 422, MSN 443 and subsequent.Spoiler servo-controlin position 1 (2)MZ4339390-01X(1) (5) (6)N/A 11000 N/A X XN/A N/A 05-Mar-10X X X X XMZ4339390-02X(1) (5) (6)N/A 11000 N/A X XR N/A N/A 05-Mar-10X X X X XMZ4339390-10X(1) (5) (6)N/A 11000 N/A X XR N/A N/A 05-Mar-10X X X X XMZ4339390-12(1) (5)N/A 11000 N/A X XR N/A N/A N/A X X X X XS4-3000470(1) (5)N/A 11000 N/A X XR N/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 XR N/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 XR .../... N/A 15000 N/A X (4) X (4) X (4) X (4) X (4)AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 5EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xSpoiler servo-controlin position 1 (2)S4-3000470-03(1) (5)N/A 11000 N/A X XR N/A 15000 N/A X (4) X (4) X (4) X (4) X (4)N1387A0000-01 (7) N/A N/A 31-Dec-03 X X X X X X XN1387B0000-01 (7) N/A N/A 31-Dec-03 X X X X X X XSpoiler servo-controlin position 2 to 6 (3)MZ4306000-01X(1)(5)(6)N/A 6000 N/A X XR N/A N/A 05-Mar-10X X X X XMZ4306000-02X(1)(5)(6)N/A 6000 N/A X XR N/A N/A 05-Mar-10X X X X XMZ4306000-10X(1)(5)(6)N/A 6000 N/A X XR N/A N/A 05-Mar-10X X X X XRMZ4306000-12(1)(5)N/A 6000 N/A X XR N/A N/A N/A X X X X XS4-3000460(1)(5)N/A 6000 N/A X XR N/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 XR N/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 XR N/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 XR N/A 14000 N/A X (4) X (4) X (4) X (4) X (4)N 1386A0000-01 (7) N/A N/A 31-Dec-03 X X X X X X XN 1386B0000-01 (7) N/A N/A 31-Dec-03 X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 6EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 13 to 15 & 18 to 19)RMAIN STRUT AND DRESSINGS (FIG. 13 & 15)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. Embodiment of MOD 43863 or MOD45031/SB A330-32-3066 introduces a different PNR. 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 original landing gear of MSN 116 and subsequent.(7) Embodiment of MOD 46903/SB A330-32-3096introduces a different PNR. MOD 46903 factory embodied on original landing gear ofMSN 271 and subsequent.(8) Embodiment of MOD 46904/SB A330-32-3095introduces a different PNR. MOD 46904 factory embodied on original landing gear ofMSN 271 and subsequent.(9) Embodiment of MOD 48066/SB A330-32-3123introduces a different PNR. MOD 48066 factory embodied on original landing gear ofMSN 366 and subsequent.(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 of Pin W1 on anyaeroplane.(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 X X X201478613 N/A 42800 N/A X X X X X X XR 201489770 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 W1 201275673 (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 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 7EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH 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 XR 201428351 N/A 19800 N/A X X X X X X XR 201428378 N/A 19800 N/A X X X X X X XN201428380 N/A 19800 N/A X XN 201428382 N/A 19800 N/A X XN 201428384 N/A 19800 N/A X XN 201478303 N/A 19800 N/A X XN 201478305 N/A 19800 N/A X XN 201478307 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 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 8EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction bracket(RH)201428339 (5) N/A (1) N/A X XR 201428352 N/A 19800 N/A X X X X X X XR 201428379 N/A 19800 N/A X X X X X X XN201428381 N/A 19800 N/A X XN 201428383 N/A 19800 N/A X XN 201428385 N/A 19800 N/A X XN 201478304 N/A 19800 N/A X XN 201478306 N/A 19800 N/A X XN 201478308 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 P 201275602 (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. 13 & 18)(1) Rework in accordance with SB A330-32-3216(MOD 56557) may introduce a different PNR.NNN(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 gearof MSN 1092 and subsequent for A330-200F series.RRetraction actuatorpiston rod114256309 N/A 8080 31-Dec-07 X X X X X X XR 114256321 (1) N/A 8080 31-Dec-07 X X X X X X XN114256323 N/A 5500 N/A X X X X X X X114256326 N/A 20950 N/A X X X X X X X114256328 N/A 20950 N/A X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 9EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xNNRetraction 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. 16 & 17)RRETRACTION ACTUATOR (FIG. 17)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 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-1 PAGE: 10EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 20)R Pitot Probe C16195AA N/A N/A 07-Jan-10 X X X X X X XATA 35-13-00 OXYGEN – CREW OXYGEN –CONTROL AND INDICATING (FIG. 24)N Pressure Switch CMK80-01 80000 N/A 20 Ye X X X X X X XNATA 35-23-00 OXYGEN – PASSENGEROXYGEN (GASEOUS) – CONTROL AND INDICATING (FIG. 25)NQuantity CalculationControl UnitE69027 80000 N/A 20 Ye X X XEND OF SUB-PART 4-2-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 11EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330Sub-part 4-2-2 CURRENT DEMONSTRATED LIVESRNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xATA 27-14-00 FLIGHT CONTROL – AILERONAND HYDRAULIC ACTUATION (FIG. 02)RR(1) Applicable to servo-control installed in positions FIN 7CS1, 8CS1, 7CS2 and 8CS2 for inboard servo-controls, and FIN 9CS1,10CS1, 9CS2 and 10CS2 foroutboard servo-controls (active and damping).RInboard aileron servocontrol (1)3337457-59 N/A N/A N/A X X X X X X X XR 3337457-60 N/A N/A N/A X X X X X X X XRC38661-00260000 40000 N/A X X X X X X X XR 80000 20000 N/A X X X X X X X XROutboard aileronservo-control (1)3337458-59 N/A N/A N/A X X X X X X X XR 3337458-60 N/A N/A N/A X X X X X X X XRC38657-00260000 40000 N/A X X X X X X X XR 80000 20000 N/A X X X X X X X XNATA 27-22-00 FLIGHT CONTROL – RUDDER TRIM ACTUATION AND ARTIFICIAL FEEL (FIG. 03)NRudder Trim Actuator(RTA)6197-1 90000 N/A N/A X X X XN 6197-2 90000 N/A N/A X X X XNATA 27-23 FLIGHT CONTROL – RUDDER AND PEDALTRAVEL LIMITING ACTUATION (FIG. 04)NRudder TravelLimitation Unit (RTLU)341400M01 90000 N/A N/A X X X XN 341400M02 90000 N/A N/A X X X XN 343500M00 90000 N/A N/A X X X XNPedal TravelLimitation Unit (PTLU)341400M01 90000 N/A N/A X X X XN 341400M02 90000 N/A N/A X X X XN 343500M00 90000 N/A N/A X X X XRAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 12EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 27-24-00 FLIGHT CONTROL – RUDDERHYDRAULIC ACTUATION (FIG. 05)N (1) Installation not authorised onA330-200, A330-200Fand on A330-300 WV05x.N Rudder servo-control 31110-080 N/A N/A N/A XR SC5300 N/A N/A N/A N/A (1) X N/A (1) X X N/A (1)RSC5300-1 N/A N/A N/A N/A (1) X N/A (1) X X N/A (1)RSC5300-2 N/A N/A N/A N/A (1) X N/A (1) X X N/A (1)RSC5300-3 N/A N/A N/A N/A (1) X N/A (1) X X N/A (1)R SC5300-4 N/A N/A N/A N/A (1) X N/A (1) X X N/A (1)NATA 27-26-00 FLIGHT CONTROL – YAW DAMPER ACTUATION (FIG. 06 & 07)NYaw damper servocontrolSC4710 N/A N/A N/A X X X XN SC4710-1 N/A N/A N/A X X X XNBack-up Yaw DamperUnit (BYDU)41800831001 N/A N/A N/A X X X XN 41800831002 N/A N/A N/A X X X XN41800831100 N/A N/A N/A X X X XRATA 27-34-00 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC CONTROL (FIG. 08)(1) Applicable to elevator servo-controls installed inpositions FIN 2CS1, 2CS2, 3CS1, and 3CS2 (active and damping).RElevator servo-control(1)SC4800-74 N/A N/A N/A X X X X X X X XR SC4800-94 N/A N/A N/A X X X X X X X XR SC4800-104 N/A N/A N/A X X X X X X X XR SC4800-114 N/A N/A N/A X X X X X X X XRATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 09)(1) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906)and retrofitted into PNR 47147-500by SB A330-27-3093 (MOD 49591).Life limitation to be applied from the time of retrofitinto 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 A330-27-3052 must not exceed 60000 FH/40000 FC, whichever occurs first.AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 13EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05x(2) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906)and retrofitted into PNR 47147-500by 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) forTHSA 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.N (3) Embodiment of MOD 200698/SB A330-27-3172 introduces different PNR.N (4) Embodiment of MOD 58916//SB A330-27-3172introduces different PNR. MOD 58916 factory embodied on MSN 1095 and subsequent.THS Actuator 47147-500 36000 24000N/AX (1) X (1) X (1) X (1) X (1)47147-700 36000 24000 N/A X (2) X (2) X (2) X (2) X (2)47172-300 60000 40000N/AX X X X X X XR 47172-500 60000 40000 25 Ye X (3) X (3) X (3) X (3) X (3) X (3) X (3) X (3)R 47172-510 60000 40000 25 Ye X (4) X (4) X (4) X (4) X (4) X (4) X (4) X (4)N 47172-520 60000 40000 N/A X X X X X X X XN 47172-530 60000 40000 N/A X X X X X X X XRATA 27-64-00 FLIGHT CONTROL – SPOILERHYDRAULIC ACTUATION (FIG. 11)(1) FIN 13CS1 and 13CS2.DRDR(2) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1 and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2.Spoiler servo-controlin positions 1 (1)1387A0000-02 N/A N/A N/A X X X X X X X X1387B0000-02 N/A N/A N/A X X X X X X X XR1387C0000-01 N/A N/A N/A X X X X X X X XDRDRSpoiler servo-controlin positions 2 to 6 (2)1386A0000-02 N/A N/A N/A X X X X X X X X1386B0000-02 N/A N/A N/A X X X X X X X XR1386C0000-01 N/A N/A N/A X X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 14EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRDRATA 29-24-00 AUXILARY HYDRAULIC POWER – RAM Air Turbine (FIG. 12)RAM Air Turbine 766351 N/A N/A N/A X X X X X X X XR 768084 N/A N/A N/A X X X X X X X XR 770379 N/A N/A N/A X X X X X X X XR 770952 N/A N/A N/A X X X X X X X XR 770952A N/A N/A N/A X X X X X X X XR 770952B N/A N/A N/A X X X X X X X XR 1702934 N/A N/A N/A X X X X X X X XR 1702934A N/A N/A N/A X X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 15EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 13 to 15 & 18 to 19)RMAIN STRUT AND DRESSINGS (FIG. 13 & 15)(1) This PNR is common to pin W2 and pin P.R Pin W 55-2105061-00 N/A 46480 N/A X X X X X XR Retraction link (LH) 50-2105026-00 N/A 46480 N/A X X X X X XR 50-2105224-00 N/A 46480 N/A X X X X X X201489315 N/A 10700 N/A X X X X X X XR Retraction link (RH) 50-2106026-00 N/A 46480 N/A X X X X X XR 50-2106224-00 N/A 46480 N/A X X X X X X201489316 N/A 10700 N/A X X X X X X XR Pin W1 55-2105060-00 N/A 46480 N/A X X X X X XDRRetraction bracket(LH)50-2105027-00 N/A 46480 N/A X X X X X XDRRetraction bracket(RH)50-2106027-00 N/A 46480 N/A X X X X X XR Pin W2 55-2105059-00 (1) N/A 46480 N/A X X X X X XR Pin P 55-2105059-00 (1) N/A 46480 N/A X X X X X XRCOMPLETE SIDE STAY (FIG. 15)Lock stay actuator pin 201440611 N/A 50000 N/A X X201457606 N/A 50000 N/A X XRLOCK STAY ACTUATOR (FIG. 19)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 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 16EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH 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. 13 & 18)DR(1) Must be replaced by a new one every time the piston head is removed from 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 XDN114256322 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 XR 50-2113003-00 N/A 50000 N/A X X X X X XRRetraction actuatorinsert114256629 N/A (1) N/A X X X X X X X XRRetraction actuatorcylinder50-2113001-00 N/A 50000 N/A X X X X X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 16 & 17)(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 XR N/A 41250 N/A X X XF53114022200xxN/A 50000 N/A X X.../... N/A 41250 N/A X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 17EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRRetraction actuatorpin (airframe side) (1)F53114023200xx N/A 50000 N/A X X X XRF53120422200xxN/A 50000 N/A X XR N/A 41250 N/A X X X XRNOSE LANDING GEAR LEG (FIG. 16)RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 16)Retraction actuatorpin (Main fitting side)D6168675000 50000 N/A X X X X X X XN N/A 18000 N/A XRRETRACTION ACTUATOR (FIG. 17)Retraction actuatoreye endD62588N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD62588-1N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD67840N/A 50000 N/A X X X X X X XNN/A 18000 N/A XRetraction actuatorbearingD61950-1N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD61950-10N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD67839N/A 50000 N/A X X X X X X XN N/A 18000 N/A XRetraction actuatorsliding rodD62328N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD62328-1N/A 50000 N/A X X X X X X XN .../... N/A 18000 N/A XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 18EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH LDG Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRRetraction actuatorsliding rodD67837N/A 50000 N/A X X X X X X XN N/A 18000 N/A XRetraction actuatorplugD61952N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD61952-1N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD67838N/A 50000 N/A X X X X X X XNN/A 18000 N/A XRetraction actuatorcylinderD62587N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD62587-1N/A 50000 N/A X X X X X X XN N/A 18000 N/A XD67836N/A 50000 N/A X X X X X X XN N/A 18000 N/A XAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-2-2 PAGE: 19EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 APPLICABILITYRA330-2xxF A330-2xx A330-30x A330-32x/A330-34xRRNomenclature Part Number FH FC Cal. WV00x WV02xWV05xWV06xWV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 20 to 21)N (1) Not authorised at the position 01 and 03 on aircraft after 07-Jan-2010.R Pitot Probe C16195BA (1) 90000 48000 N/A X X X X X X X XRSensor – Angle OfAttack45150320 90000 48000 N/A X X X X X X X XR C16291AA 90000 48000 N/A X X X X X X X XN C16291AB 90000 48000 N/A X X X X X X X XRATA 34-21-00 NAVIGATION - ALTITUDE AND AIRSPEED STANDBY DATA (FIG. 22)R Altimeter Standby 64141-582-1 N/A N/A N/A X X X X X X XR 64141-590-1 N/A N/A N/A X X X X X X XRIndicator StandbyAirspeed64050-868-1 N/A N/A N/A X X X X X X XRATA 34-22-00 NAVIGATION – ATTITUDE AND HEADING STANDBY DATA (FIG. 23)R Compass Standby KCA0105W N/A N/A N/A X X X X X X XRIndicator StandbyHorizon501-1568-34 N/A N/A N/A X X X X X X XR H321BHM1 N/A N/A N/A X X X X X X XRH341BVM N/A N/A N/A X X X X X X XEND OF SUB-PART 4-2-2AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-3-1 PAGE: 1EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTSSub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELRNote: 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 NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRRR274400-00001-1-E311312THSA – FIG. 09Detailed inspection of the ball screw assemblyfor integrity of the primary and secondary loadpath and check the gap at the 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 the initial 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 55780RNNN274400-00001-2-E311312THSA – FIG. 09Detailed inspection of the ball screw assemblyfor integrity of the primary 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 92-3046R04AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-3-1 PAGE: 2EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRNN274400-00001-3-E 311312THSA – FIG. 09Detailed inspection of the ball screw assemblyfor integrity of the primary 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 92-3046R04RNN274400-00001-4-E 311312THSA – FIG. 09Detailed inspection of the ball screw assemblyfor integrity of the primary 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 92-3046R04PRE 56056RNN274400-00002-1-E311312THSA – FIG. 09Lubrication of the THSA ball-nut.Note: No short-term extension is allowed.1000 FHNote1000 FHNoteAMM 12-22-27/30147147-50047147-70047172-30047172-50047172-51047172-52047172-530ALLAIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-3-1 PAGE: 3EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRRNN.292400-00001-1-E 633Auxiliary Hydraulic Power – FIG. 12Remove Ram Air Turbine (RAT) for overhaul.Fit a RAT that has not accumulated 20 Yesince last overhaul.20 Ye.20 Ye.AMM 29-24-52/401CMM 29-21-31766351768084770379770952770952A770952B17029341702934AALLEND OF SUB-PART 4-3-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-3-2 PAGE: 4EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELRNote: 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 NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTR275000-00001-1-E570670FlapsPerform a simultaneous detailed visualinspection of the Input Gear Boxes (IPGB) andof the Down Drive Shafts (DDS) on flap tracks2 and 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 MSN0183inclusiveRNNNRRR275000-00001-2-E570670FlapsPerform a simultaneous detailed visualinspection of the Input Gear 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 MSN0420inclusivePRE 200492PRE 201194(27-3173)AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 09/11 ALS PART 4-3-2 PAGE: 5EASA APPROVED©AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A330RNote: 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 NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTNNN275000-00001-3-E570670FlapsPerform a simultaneous detailed visualinspection of the Input Gear 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)NNNNN275000-00001-4-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS). Lubricate all flap tracks on both wings.24 Mo 24 Mo AMM 12-22-27 N/A POST200492NNNNNNNN275000-00001-5-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS). Lubricate 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 POST201194(27-3173)END OF SUB-PART 4-3-2

### AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: SEP 09/11 ALS PART 4 HISTORY FILE PAGE: 1/5

© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document. 

# A330

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 task applicabilities 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

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

− EASA AD 2010-0205, and

− AMOC Reference 10033009 dated 14-Dec-2010.

2- SUMMARY OF CHANGES:

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

4 (revision 02).

New items:

RECORD OF REVISIONS:

None.

SUB-PART 4-0:

− A330 Limit Of Validity:

− New limitations in 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. The LOV is escalated up to 100000 FH/33000 FC in accordance

with the associated rules detailed in paragraph 1C.

− A330-200 series WV057, WV058, WV061 are added.

− Transfer of components/items between aircraft applications.

− Instructions for calculating the remaining life when components/items are installed on

an application where the ALS Part 4 does not impose an airworthiness limitation. This

is added to paragraph 1H.

− The LOV applicable to the A330-200F series main and nose landing gear retraction

chain are added.

SUB-PART 4-1:

− New illustrations added to reflect changes introduced in sub-parts 4-2 and 4-3-1.

SUB-PART 4-2:

− Introduction of new items:

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

− Rudder Travel Limitation Unit (RTLU) PNR 341400M01, PNR 341400M02 and PNR

343500M00,

− Pedal Travel Limitation Unit (PTLU) PNR 341400M01, PNR 341400M02 and PNR

343500M00,

− Yaw damper servo-control PNR SC4710 and PNR SC4710-1,

− The back-up yaw damper unit (BYDU) PNR 41800831001, PNR 41800831002 and

PNR 41800831100,

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

− Pressure switch PNR CMK80-01,

− Quantity calculation control unit PNR E69027.

− Introduction of new PNR of:

− The rudder servo-control PNR 31110-080,

− THSA PNR 47172-520, PNR 47172-530,

− Angle Of Attack sensor PNR C16291AB,

− Retraction actuator gland PNR 50-2113004-01.

SUB-PART 4-3:

− Introduction of new maintenance tasks:

− Task 275000-00001-4-E, 275000-00001-5-E.

Amendments:

RECORD OF REVISIONS:

Introduction of transition phases between previous revisions and A330 ALS Part 4 revision 03.

SUB-PART 4-2:

− Cancellation of the limitation of the following items:

− Inboard aileron servo-controls PNR 3337457-59 and PNR 3337457-60,

− Outboard aileron servo-controls PNR 3337458-59 and PNR 3337458-60,

− Rudder servo-controls PNR SC5300, PNR SC5300-1, PNR SC5300-2, PNR SC5300-3

and PNR SC5300-4. Applicability restricted to A330-300 WV000, WV010 and WV020

series,

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

SC4800-114,

− Spoiler servo-controls in position 1 PNR 1387A0000-02, PNR 1387B0000-02 and PNR

1387C0000-01,

− Spoiler servo-controls in positions 2 to 6 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,

− Altimeter Standby PNR 64141-582-1 and PNR 64141-590-1,

− Indicator Standby Airspeed PNR 64050-868-1,

− Compass Standby PNR KCA0105W,

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

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− Changes in the limitations of the following items:

− THSA: 25 Ye calendar life limit added for PNR 47172-500 and PNR 47172-510,

− Spoiler servo-controls in position 1: Life limits amended for PNR 1387A0000-01,

1387B0000-01 in accordance with CN 2002-552(B),

− Spoiler servo-controls in positions 2 to 6: Life limits amended for PNR 1386A0000-01,

PNR 1386B0000-01 in accordance with CN 2002-552(B),

− Retraction bracket (LH): Life limits amended for PNR 201428351, PNR 201428378,

PNR 201428380, PNR 201428382, PNR 201428384, PNR 201478303, PNR

201478305, PNR 201478307 in accordance with EASA AD 2010-0205,

− Retraction bracket (RH): Life limits amended for PNR 201428352, PNR 201428379,

PNR 201428381, PNR 201428383, PNR 201428385, PNR 201478304, PNR

201478306 and PNR 201478308 in accordance with EASA AD 2010-0205,

− Retraction bracket (RH): Life limitation amended for PNR 50-2106027-00,

− Retraction bracket (LH): Life limitation amended for PNR 50-2105027-00,

− Pin W: Life limitation amended for PNR 55-2105061-00,

− Retraction link (LH): Life limitation amended for PNR 50-2105026-00, PNR 50-

2105224-00,

− Retraction link (RH): Life limitation amended for PNR 50-2106026-00, PNR 50-

2106224-00,

− Pin W1: Life limitation amended for PNR 55-2105060-00,

− Pin W2: Life limitation amended for PNR 55-2105059-00,

− Pin P: Life limitation amended for PNR 55-2105059-00,

− Retraction actuator piston rod: Life limits amended for PNR 114256309, PNR

114256321, and PNR 50-2113002-00,

− Retraction actuator gland: Life limitation amended for PNR 50-2113004-00,

− Retraction actuator piston head: Life limitation amended for PNR 50-2113003-00,

− Retraction actuator cylinder: Life limitation amended for PNR 50-2113001-00,

− Retraction actuator pin (Main fitting side) PNR D61686: 18000 FC limitation when fitted

to A330-200F,

− Retraction actuator eye end PNR D62588, PNR D62588-1 and PNR D67840: new

limitation when fitted to A330-200F,

− Retraction actuator bearing PNR D61950-1, PNR D61950-10 and PNR D67839: new

limitation when fitted to A330-200F,

− Retraction actuator sliding rod PNR D62328, PNR D62328-1 and PNR D67837: new

limitation when fitted to A330-200F,

− Retraction actuator plug PNR D61952, PNR D61952-1 and PNR D67838: new

limitation when fitted to A330-200F,

− Retraction actuator piston rod PNR D62587, PNR D62587-1 and PNR D67836: new

limitation when fitted to A330-200F,

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− Pitot probes: Life limitations amended for PNR C16195BA,

− AoA sensors: Life limitations amended for PNR 45150320 and PNR C16291AA.

− Changes in the applicability of the following items:

− Rudder servo-controls PNR SC5300, PNR SC5300-1, PNR SC5300-2, PNR SC5300-3

and PNR SC5300-4: Applicability restricted to A330-300 WV000, WV010 and WV020

series.

SUB-PART 4-3:

− Task 274400-00001-1-E: Revision 08 of SB A330-27-3102 added,

− Task 274400-00001-2-E: Aircraft applicability amended and new PNR added,

− Task 274400-00001-3-E: Aircraft applicability amended and new PNR added,

− Task 274400-00001-4-E: Aircraft applicability amended,

− Task 274400-00002-1-E: Aircraft applicability and interval amended,

− Task 275000-00001-2-E: Aircraft applicability amended,

− Task 275000-00001-3-E: Aircraft applicability amended,

− Task 292400-00001-1-E: Limitations and aircraft applicability amended.

Deletions:

SUB-PART 4-0:

None.

SUB-PART 4-1:

None.

SUB-PART 4-2:

− Inboard aileron servo-control PNR 3337457-21, PNR 3337457-25, PNR 3337457-34,

− Outboard aileron servo-control PNR 3337458-21, PNR 3337458-25, PNR 3337458-34,

− RAM Air Turbine PNR 758546, PNR 759123, PNR 762956, PNR 762973, and PNR

764239. Their limitations are mandated by CN 94-281-005(B)R2 and CN 1999-144-

094(B)R2.

SUB-PART 4-3:

None.