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REVISION: 02 

# A330



# ALS Part 4

- Ageing Systems Maintenance

© AIRBUS SAS 2009. 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: DEC 16/09 ALS PART 4 PAGE: 1-LEP

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4 R 1-LEP DEC 16/09

4 1-TOC NOV 04/08

4 R 1-ROR DEC 16/09

4 N 2-ROR DEC 16/09

4-0 1 MAY 29/09

4-0 R 2 DEC 16/09

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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: DEC 16/09 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

R 01 ROR

4-2

4-3 MAY 29/09 N/A

N

N

N 02 ROR

4-2

4-3 DEC 16/09

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

Revision 02 is approved by EASA under reference 10028295.

REVISION 02 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 02 from 16-Dec-2010.

2. From 16-Dec-2009 to 15-Dec-2010, 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 01, 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 02.

3. From 16-Dec-2009, it is mandatory to comply with the maintenance requirements and

associated airworthiness limitations defined in the A330 ALS Part 4 revision 02, for: R

R

R

R

R

N

N

N

N

N

N

N

N

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: DEC 16/09 ALS PART 4 PAGE: 2-ROR

EASA APPROVED

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# A330

− The Inboard aileron servo-control PNR 3337457-59, PNR 3337457-60 and PNR

C38661-002,

− The Outboard aileron servo-control PNR 3337458-59, PNR 3337458-60 and PNR

C38657-002,

− The Rudder servo-control PNR SC5300, PNR SC5300-1, PNR SC5300-2, PNR

SC5300-3 and PNR SC5300-4,

− The Elevator servo-control PNR SC4800-7A, PNR SC4800-9, PNR SC4800-10, PNR

SC4800-11, PNR SC4800-72, PNR SC4800-73, PNR SC4800-74, PNR SC4800-92,

PNR SC4800-93, PNR SC4800-94, PNR SC4800-103, PNR SC4800-104, PNR

SC4800-113 and PNR SC4800-114,

− The Spoiler servo-control in position 1 PNR 1387A0000-01, PNR 1387A0000-02, PNR

1387B0000-01, PNR 1387B0000-02, PNR 1387C0000-01, PNR MZ4339390-01X, PNR

MZ4339390-02X, PNR MZ4339390-10X and PNR MZ4339390-12,

− The Spoiler servo-control in positions 2 to 6 PNR 1386A0000-01, PNR 1386A0000-02,

PNR 1386B0000-01, PNR 1386B0000-02, PNR 1386C0000-01, PNR MZ4306000-01X,

PNR MZ4306000-02X, PNR MZ4306000-10X and PNR MZ4306000-12,

− The Main Landing Gear Pin W1 PNR 201275673 and PNR 201478614,

− The Pitot probes PNR C16195AA and PNR C16195BA,

− The Sensor – Angle Of Attack PNR 45150320 and PNR C16291AA,

− The Altimeter standby PNR 64141-582-1 and PNR 64141-590-1,

− The Indicator standby airspeed PNR 64050-868-1,

− The Compass standby PNR KCA0105W,

− The Indicator standby horizon PNR 501-1568-34, PNR H321BHM1 and PNR

H341BVM,

− The tasks 274400-00001-1-E, 274400-00001-2-E, 274400-00001-3-E, 274400-00001-

4-E and 274400-00002-1-E.

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

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

### AIRWORTHINESS LIMITATIONS SECTION

ISSUE: MAY 29/09 ALS PART 4-0 PAGE: 1

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# A330

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

A330-200 A330-201 020, 023, 024, 050, 052, 054, 055, 056, 059,

060

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

056, 059, 060

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

056, 059, 060

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

059, 060

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

052, 054, 055, 056, 059, 060

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

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

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

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

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ISSUE: DEC 16/09 ALS PART 4-0 PAGE: 2

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# A330

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 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.

(1) General LOV applicable to A330 systems installations

Aircraft series LO V

Flight Hours Flight Cycles

A330-200 series, WV020’s 0 60000 40000

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

A330-300 series excl. A300-301,

WV000’s, WV010’s & WV020’s 0 60000 40000

A330-301 series, WV000’s & WV010’s OR 0 60000 40000

80000 (*) 20000 (*) R

R

N

N

### AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-0 PAGE: 3

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# A330

Aircraft series LO V

Flight Hours Flight Cycles

A330-300 series, WV050’s 100000 33000

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

A330-00-3068.

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

combination of values extracted from different sets is permitted.

(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

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 (re-inforced) 0 75000 50000

A330-200/-300 series, WV020’s, WV050’s & WV060

PNR D23581 series (re-inforced) 0 75000 50000

Note: The parts included in the retraction actuator chains are not subject to the

ground loads. Therefore, the life limitations for the related Part NumbeR

(PNR) may exceed the stated LOV as a result of a fatigue test carried out for

another aircraft application having a greater LOV.

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. N

N

N

N

R

D

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ISSUE: DEC 16/09 ALS PART 4-0 PAGE: 4

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# A330

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 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.

WV059: Aircraft POST MOD 57439.

WV060: Aircraft POST MOD 57440.

− 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.

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ISSUE: DEC 16/09 ALS PART 4-0 PAGE: 5

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# A330

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).

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 limitation (FH/FC/Cal) 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. N

N

N

N

### AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-0 PAGE: 6

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# A330

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: Demonstrated life limitations

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 finalization 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.

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. R

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ISSUE: DEC 16/09 ALS PART 4-0 PAGE: 7

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# A330

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

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

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

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

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

successful task recording can be entered.

G. Traceability and replacement/maintenance requirements

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

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

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

limitations.

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

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

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

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. 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).

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

Note 2: Where the 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.

H. Transfers of components/items between applications having different airworthiness

limitations

In case of component/item transfers between applications (aircraft types, aircraft

models, etc...) with different airworthiness limitations (including LOV), the remaining life

for operation must be defined by the use of the following formula:

with:

Tr i = remaining life for operation on current application i.

Ca j = accumulated life on previous application j.

Cp j = airworthiness limitation in previous application j.

Cp i = airworthiness limitation in present application i.

Note 1: When using the above formula Tr i , Ca j , Cp j , Cp i are expressed in the same

usage parameters (FH or FC or LDG): 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 limitations evolve 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: 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,

− 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. i Cp

j Cp j Ca

1 i Tr × ∑

−= 

### ⎥ ⎥

⎦ ⎤

⎢ ⎢

⎣ ⎡

⎟ ⎟

⎠ ⎞

⎜ ⎜

⎝ ⎛

R

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

J. 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.

Any damage (e.g. fatigue cracks, wear, corrosion, etc...) on systems affected by the

ALS Part 4 must be reported to Airbus.

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

− ASM maintenance requirement reference,

− Aircraft MSN affected,

− Identification of the affected component/item,

− Life since new (in Flight Hours and/o r Flight Cycles and/or landings and/or

calendar time, as applicable) accumulated by the affected system/component/item

at the time of the finding,

− Location and description of the finding, with indication of the size and orientation,

− Circumstance of detection and inspection method used.

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 or Repair concession, or an Alternative Method

Of Compliance (AMOC).

It is Operator’s responsibility to refer to the applicable limitations.

Production concessions are provided to the initial Operator of the aircraft in the delivery

documentation (Aircraft Inspection Report: ‘Recordable concessions’).

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

issuance date of the Production or Repair concession/AMOC, Operators are requested

to contact Airbus for guidance.

The restrictions of airworthiness limitation(s) indicated in the repair file/AMOC (or

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

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

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

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

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

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

credit of the history partially or completely rebuilt after application for the repair

solution/AMOC.

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

Form 1 block 13 (directly or by reference to another document).

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

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

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

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

affects the content of the ALS Part 4, the Operator is responsible for obtaining approval

by the relevant Airworthiness Authority for any necessary adaptations of the

airworthiness limitations.

When such an aircraft/a sub-assembly/a 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.

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.

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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 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”.

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 an item is fulfilling

its intended purpose. It is a failure-finding task and

does not require quantitative tolerances.

Threshold: The initial accomplishment of a specific maintenance

task from the initial entry into service. 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.

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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 issued by Airbus. This is the

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

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

replacement PNR, detail PNR and applicable SB:

− Messier-Dowty Ltd Service Bulletin number:

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

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

47487 – ‘growth scallop’),

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

− Messier-Dowty SA Service Bulletin number:

− D23285-32-040 (nose landing gear).

Detail parts are listed in the relevant Component Maintenance Manuals. The MessierDowty 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: N

N

N

N

N

N

N

N

N

N

N

N

N

N

### AIRWORTHINESS LIMITATIONS SECTION

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

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

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

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

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

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

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

column.

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

of the column.

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

column, excluding the A330-341 model.

(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

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

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

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

one associated with the inspection method used at last inspection.

B. ALS sub-part 4-3 layout.

The maintenance requirements and associated airworthiness limitations are presented

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

(1) Task Number

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

Document (MPD) system, 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 centreline,

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.

### AIRWORTHINESS LIMITATIONS SECTION

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(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.

(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.

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

Applicability Task applicable to

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.

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.

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 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.

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

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

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

LanDinGs.

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

Where the repeat interval is 12 Months or less, extensions up to 10% or 1 month

(whichever is the lesser) may exceptionally be granted on ASM airworthiness

limitations quoted in terms of Months.

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

may exceptionally be granted.

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

the State of aircraft registry for the control and development of his maintenance

programme.

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

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

column.

END OF SUB-PART 4-0AIRWORTHINESS LIMITATIONS SECTION

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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: DEC 16/09 ALS PART 4-1 PAGE: 2

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

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 3

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ATA 27-24 00 – RUDDER HYDRAULIC ACTUATION – FIG. 03AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 4

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

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 5

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

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 6

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

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 7

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ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 07AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 8

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ATA 29-24-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 08AIRWORTHINESS LIMITATIONS SECTION

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(*) Location, item not illustrated

FORWARD

ATA 32-11-00 – MAIN GEAR – FIG. 09 Pin P (*) Retraction

actuator

Lock stay

actuator

Side Stay

AssemblyAIRWORTHINESS LIMITATIONS SECTION

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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. 10AIRWORTHINESS LIMITATIONS SECTION

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Lock link

(subassembly) Lock stay actuator

pin (x2)

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

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 12

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ATA 32-21-00 – NOSE GEAR – FIG. 12 Retraction actuator pin

(main fitting side) Main FittingAIRWORTHINESS LIMITATIONS SECTION

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ATA 32-31-00 – NORMAL EXTENSION AND RETRACTION – FIG. 13 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

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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. 14AIRWORTHINESS LIMITATIONS SECTION

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

piston rod Lock stay actuator

cylinder Lock stay actuator

rod end

Lock stay actuator

glandAIRWORTHINESS LIMITATIONS SECTION

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ATA 34-11-00 – NAVIGATION – PITOT PROBE – FIG. 16AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 17

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ATA 34-11-00 – NAVIGATION – ANGLE OF ATTACK SENSOR – FIG. 17AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 18

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ATA 34-21-00 – ALTITUDE AND AIRSPEED STANDBY DATA – FIG. 18AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 16/09 ALS PART 4-1 PAGE: 19

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ATA 34-22-00 – ATTITUDE AND HEADING STANDBY DATA – FIG. 19

END OF SUB-PART 4-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 1EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330Sub-part 4-2 SYSTEMS LIFE LIMITED COMPONENTSSub-part 4-2-1 LIFE LIMITSNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xNATA 26-23-00 FIRE PROTECTION – LOWER DECK CARGO COMPARTMENT FIRE EXTINGUISHING (FIG. 01)N Pressure reducerD41428N/A N/A 20 Ye X X X X X X XNE62691-00 N/A N/A 20 Ye X X X X X X XRATA 27-14-00 FLIGHT CONTROL – AILERONAND HYDRAULIC ACTUATION (FIG. 02)(1) Applicable to servo-control in active position: i.e. Functional Item Number (FIN) 8CS1 and 8CS2 for inboard servo-controls, and FIN 10CS1 and 10CS2 foroutboard servo-controls.(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)3337457-21 6000 N/A N/A X X X3337457-226000N/AN/AXXX3337457-23 6000 N/A N/A X X X3337457-25 18000 N/A N/A X X X3337457-26 18000 N/A N/A X X X3337457-27 18000 N/A N/A X X X3337457-30 32000 21600 N/A X X X3337457-31 32000 21600 N/A X X X3337457-34 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 XRAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 2EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xOutboard aileron servocontrol (1) (2)3337458-30 32000 21600 N/A X X X3337458-313200021600N/AXXX3337458-34 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 XRATA 27-34-00 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC CONTROL (FIG. 04)R (1) Applicable to elevator servo-controls installed inpositions FIN 2CS1, 2CS2, 3CS1 and 3CS2 (active and damping).R 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 XNSC4800-7A 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 XNSC4800-9 N/A N/A 30-Jun-08 X X X X X X XNSC4800-10 N/A N/A 30-Jun-08 X X X X X X XNSC4800-11 N/A N/A 30-Jun-08 X X X X X X XNSC4800-72 N/A N/A 30-Jun-08 X X X X X X XNSC4800-73 N/A N/A 30-Jun-08 X X X X X X XNSC4800-92 N/A N/A 30-Jun-08 X X X X X X XNSC4800-93 N/A N/A 30-Jun-08 X X X X X X XNSC4800-103 N/A N/A 30-Jun-08 X X X X X X XNSC4800-113 N/A N/A 30-Jun-08 X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 3EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 05)(1) Embodiment of MOD 45906/SB A330-27-3052 and MOD 49591/SB A330-27-3093introduces different PNR. MOD 45906 is factory embodied on MSN 233 andsubsequent.(2) Embodiment of MOD 49590/SB A330-27-3085introduces different PNR. MOD 49590 is factory embodied on MSN 437 and subsequent.THS Actuator47147-200 N/A N/A 31-Jul-04 X (1) X (1)47147-210 N/A N/A 31-Jul-04 X (1) X (1)47147-213 N/A N/A 31-Jul-04 X (1) X (1)47147-300 N/A N/A 31-Jul-04 X (1) X (1)47147-303 N/A N/A 31-Jul-04 X (1) X (1)47147-350 N/A N/A 31-Jul-04 X (1) X (1)47147-400 N/A N/A 31-Jul-04 X (1) X (1)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. 06)(1) Embodiment of MOD 50044 and/or MOD 52591 (both associated to SB A330-27-3106) introduces different PNR.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. 07)(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..../...AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 4EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05x(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.NNNNNNNNNNNNN(6) Applicable to aircraft up to and including MSN 588.−For aircraft, which have accumulated on 05-Sep-08 less than or equal to 8500 FC since aircraft initial entry into service, modify all servo-control actuators inaccordance with SB A330-27-3110 no later than 05-Mar-2010.−For aircraft, which have accumulated on 05-Sep-08 more than 8500 FC since aircraft initial entry into service, modify the servo-control actuators inaccordance with SB A330-27-3110:−If 3 hydraulic circuits are affected:(a) On first circuit within 10400 FC since aircraft initial entry into service.(b) On second circuit within 10800 FC since aircraft initial entry into service.(c) On third circuit no later than 05-Mar-2010.−If 2 hydraulic circuits are affected:(a) On first circuit within 10800 FC since aircraft initial entry into service.(b) On second circuit or no later than 05-Mar-2010.−If 1 hydraulic circuit is affected: no later than 05-Mar-2010.Spoiler servo-control inposition 1(1) (2) (5)MZ4339390-01XN/A 11000 N/A X XN N/AN/A05-Mar-10(6)X X X X XMZ4339390-02XN/A 11000 N/A X XNN/A N/A05-Mar-10(6)X X X X XMZ4339390-10XN/A 11000 N/A X XNN/A N/A05-Mar-10(6)X X X X XMZ4339390-12N/A 11000 N/A X XN60000 40000 N/A X X X X XN .../...80000 20000 N/A XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 5EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xSpoiler servo-control inposition 1(1) (2) (5)S4-3000470N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000470-01N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000470-02N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000470-03N/A 11000 N/A X XN/A 15000 N/A X (4) X (4) X (4) X (4) X (4)Spoiler servo-control inpositions 2 to 6(1) (3) (5)MZ4306000-01XN/A 6000 N/A X XN N/AN/A05-Mar-10(6)X X X X XMZ4306000-02XN/A 6000 N/A X XNN/A N/A05-Mar-10(6)X X X X XMZ4306000-10XN/A 6000 N/A X XNN/A N/A05-Mar-10(6)X X X X XMZ4306000-12N/A 11000 N/A X XN60000 40000 N/A X X X X XN80000 20000 N/A XS4-3000460N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000460-01N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)S4-3000460-02N/A 6000 N/A X X.../...N/A 14000 N/A X (4) X (4) X (4) X (4) X (4)AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 6EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xSpoiler servo-control inpositions 2 to 6(1) (3) (5)S4-3000460-03N/A 6000 N/A X XN/A 14000 N/A X (4) X (4) X (4) X (4) X (4)AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 7EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 09 to 11 & 14 to 15)RMAIN STRUT AND DRESSINGS (FIG. 09 & 10)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 A330-32-3096 introduces a differentPNR. MOD 46903 factory embodied on original landing gear of MSN 271 and subsequent.(8) Embodiment of MOD 46904/SB A330-32-3095 introduces a differentPNR. MOD 46904 factory embodied on original landing gear ofMSN 271 and subsequent.(9) Embodiment of MOD 48066/SB A330-32-3123 introduces a differentPNR. MOD 48066 factory embodied on original landing gear ofMSN 366 and subsequent.NN(10) Life limit is the later of 900 aircraft FH counted from 08 July 2009 or the accumulation of 11150 total LDG since initialentry into service of Pin W1 on anyaeroplane.N (11) Life limit is the earlier of the 10 year calendar limit or the limitation deduced from Note (10).N (12) Embodiment of MOD 58527/SB A330-32-3229 introduces a different PNR.Pin W201275796 (7) N/A 20000 10 Ye X X X X X X X201478613 N/A 42800 N/A X X X X X X X201489770 N/A 42800 N/A X X X X X X 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 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 8EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xR Pin W1201275673 (7) (11) N/A (10) 10 Ye X X X X X X XR201478614 N/A (10) N/A X X X X X X XRetraction bracket (LH) 201428305 N/A (1) N/A X X201428307 N/A (1) N/A X X201428318 N/A (1) N/A X X201428323 N/A (1) N/A X X201428331 (2) N/A (1) N/A X X201428331 (6) N/A 9000 N/A X X201428333 N/A (1) N/A X X201428335 N/A (1) N/A X X201428338 (4) N/A (1) N/A X X201428351 N/A 30500 N/A X X X X X X X201428378 N/A 30500 N/A X X X X X 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 X201428336 N/A (1) N/A X X201428339 (5) N/A (1) N/A X X201428352 N/A 30500 N/A X X X X X X X201428379 N/A 30500 N/A X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-1PAGE: 9EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYA330-2xxA330-30xA330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xPin W2201275667 (8)N/A 4500 5 Ye X XN/A 9400 5 Ye X X X X X201478615 N/A 42800 N/A X X X X X X X201478637 N/A 42800 N/A X X X X X X XPin P201275602 (7) N/A 20000 10 Ye X X X X X X X201478612 N/A 42800 N/A X X X X X X XRRETRACTION ACTUATOR (FIG. 09)(1) Rework in accordance with SB A330-32-3216 (MOD 56557) may introduce a different PNR.Retraction actuator pistonrod114256309 N/A 8080 N/A X X X X X X X114256321 (1) N/A 8080 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 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. 12 & 13)RRETRACTION ACTUATOR (FIG. 13)Retraction actuator body D61954N/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: DEC 16/09ALS PART 4-2-1PAGE: 10EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.N Explanation notes are located under the assy title.LIFE LIMITS(Whichever occurs first)LIFE LIMITS APPLICABILITYNA330-2xxA330-30xA330-32x/A330-34xNNNomenclature Part Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xNATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 16)N Pitot ProbeC16195AA60000 40000 07-Jan-10 X X X X X X XN80000 20000 07-Jan-10 XEND OF SUB-PART 4-2-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 11EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330Sub-part 4-2-2 DEMONSTRATED LIFE LIMITATIONSNNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 27-14-00 FLIGHT CONTROL – AILERONAND HYDRAULIC ACTUATION (FIG. 02)(1) Applicable to servo-control in activeposition: i.e. FIN 8CS1 and 8CS2 for inboard servo-controls, and FIN 10CS1 and 10CS2for outboard servo-controls.RInboard aileron servocontrol3337457-59 (1)60000 40000 N/A X X X X X X XN 8000020000N/AXR3337457-60 (1)60000 40000 N/A X X X X X X XN80000 20000 N/A XNC38661-00260000 40000 N/A X X X X X X XN80000 20000 N/A XROutboard aileron servocontrol3337458-59 (1)60000 40000 N/A X X X X X X XN 8000020000N/AXR3337458-60 (1)60000 40000 N/A X X X X X X XN80000 20000 N/A XNC38657-00260000 40000 N/A X X X X X X XN80000 20000 N/A XNATA 27-24-00 FLIGHT CONTROL – RUDDERHYDRAULIC ACTUATION (FIG. 03)N Rudder servo-controlSC530060000 40000 N/A X X X X X X XN80000 20000 N/A XNSC5300-160000 40000 N/A X X X X X X XN80000 20000 N/A XNSC5300-260000 40000 N/A X X X X X X XN80000 20000 N/A XNSC5300-360000 40000 N/A X X X X X X XN .../...80000 20000 N/A XRAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 12EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xN Rudder servo-controlSC5300-460000 40000 N/A X X X X X X XN80000 20000 N/A XRDNATA 27-34-00 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC CONTROL (FIG. 04)Elevator servo-controlSC4800-7460000 40000 N/A X X X X X X XN80000 20000 N/A XNSC4800-9460000 40000 N/A X X X X X X XN80000 20000 N/A XNSC4800-10460000 40000 N/A X X X X X X XN80000 20000 N/A XNSC4800-11460000 40000 N/A X X X X X X XN80000 20000 N/A XRATA 27-44-00 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 05)(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 retrofit into PNR 47147-400 (SB A330-27-3052) forTHSA subsequently retrofittedinto PNR 47147-500 (MOD49591/SB A330-27-3093). The sum of the accumulated lives PRE andPOST SB A330-27-3052 must not exceed 60000 FH/40000 FC, whichever occurs first.NNNNN(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.THS Actuator47147-50036000 24000 N/A X (1) X (1) X (1) X (1) X (1)N47147-70036000 24000 N/A X (2) X (2) X (2) X (2) X (2)47172-300 60000 40000 N/A X X X X X X X47172-500 60000 40000 N/A X X X X X X X47172-510 60000 40000 N/A X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 13EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xNATA 27-64-00 FLIGHT CONTROL – SPOILERHYDRAULIC ACTUATION (FIG. 07)N (1) FIN 13CS1 and 13CS2.N (2) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1 and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2.NSpoiler servo-control inposition 1 (1)1387A0000-0160000 40000 N/A X X X X X X XN 8000020000N/AXN1387A0000-0260000 40000 N/A X X X X X X XN80000 20000 N/A XN1387B0000-0160000 40000 N/A X X X X X X XN80000 20000 N/A XN1387B0000-0260000 40000 N/A X X X X X X XN80000 20000 N/A XN1387C0000-0160000 40000 N/A X X X X X X XN80000 20000 N/A XNSpoiler servo-control inpositions 2 to 6 (2)1386A0000-0160000 40000 N/A X X X X X X XN 8000020000N/AXN1386A0000-0260000 40000 N/A X X X X X X XN80000 20000 N/A XN1386B0000-0160000 40000 N/A X X X X X X XN80000 20000 N/A XN1386B0000-0260000 40000 N/A X X X X X X XN80000 20000 N/A XN1386C0000-0160000 40000 N/A X X X X X X XN80000 20000 N/A XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 14EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH FC Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xNATA 29-24-00 AUXILARY HYDRAULIC POWER – RAM Air Turbine (FIG. 08)N RAM Air Turbine758546N/A 40000 N/A X X X X X X XN759123 N/A 40000 N/A X X X X X X XN762956 N/A 40000 N/A X X X X X X XN762973 N/A 40000 N/A X X X X X X XN764239 N/A 40000 N/A X X X X X X XN766351 N/A 40000 N/A X X X X X X XN768084 N/A 40000 N/A X X X X X X XN770379 N/A 40000 N/A X X X X X X XN770952 N/A 40000 N/A X X X X X X XN770952A N/A 40000 N/A X X X X X X XN770952B N/A 40000 N/A X X X X X X XN1702934 N/A 40000 N/A X X X X X X XN1702934A N/A 40000 N/A X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 15EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 09 to 11 & 14 to 15)RMAIN STRUT AND DRESSINGS (FIG. 09 & 10)(1) This PNR is common to pin W2 and pin P.Pin W55-2105061-00 N/A 30000 N/A X X XRetraction link (LH)50-2105026-00 N/A 30000 N/A X X X50-2105224-00 N/A 30000 N/A X X X X XN201489315 N/A 10700 N/A X X X X X X XRetraction link (RH)50-2106026-00 N/A 30000 N/A X X X50-2106224-00 N/A 30000 N/A X X X X XN201489316 N/A 10700 N/A X X X X X X XPin W155-2105060-00 N/A 30000 N/A X X X X XRetraction bracket (LH) 201428380N/A 30500 N/A X X201428382 N/A 30500 N/A X X201428384 N/A 30500 N/A X X201478303 N/A 30500 N/A X X201478305 N/A 30500 N/A X X201478307 N/A 30500 N/A X X50-2105027-00 N/A 30000 N/A X X X X XRetraction bracket (RH) 201428381N/A 30500 N/A X X201428383 N/A 30500 N/A X X201428385 N/A 30500 N/A X X201478304 N/A 30500 N/A X X201478306 N/A 30500 N/A X X201478308 N/A 30500 N/A X X50-2106027-00 N/A 30000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 16EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xPin W255-2105059-00 (1) N/A 30000 N/A X X X X XPin P55-2105059-00 (1) N/A 30000 N/A X X X X XRCOMPLETE SIDE STAY (FIG. 11)Lock stay actuator pin201440611N/A 50000 N/A X X201457606 N/A 50000 N/A X XRLOCK STAY ACTUATOR (FIG. 15)Lock stay actuatorcylinder114354600 N/A 50000 N/A X X201686600N/A50000N/AXXLock stay actuator pistonrod114354605 N/A 50000 N/A X X201686602N/A50000N/AXXLock stay actuator gland 114354606N/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 X201686601N/A50000N/AXXRRETRACTION ACTUATOR (FIG. 09)(1) Must be replaced by a new one every timethe piston head is removed from the piston rod.Retraction actuatorpiston rod114256323 N/A 5500 N/A X X X X X X X50-2113002-00N/A20000N/AXXXXXRetraction actuator gland 114256312N/A 50000 N/A X X X X X X X114256322 N/A 50000 N/A X X X X X X X50-2113004-00 N/A 20000 N/A X X X X XRetraction actuatorpiston head114256308 N/A 50000 N/A X X X X X X X114256639 N/A 50000 N/A X X X X X X X50-2113003-00 N/A 20000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 17EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction actuator insert 114256629N/A (1) N/A X X X X X X XRetraction actuatorcylinder50-2113001-00 N/A 20000 N/A X X X X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 12 & 13)R (1) ‘xx’ at the end of the PNRs stands forany number between 00 and 99, including unused digits.Retraction actuator pin(airframe side) (1)F53112357200xx N/A 50000 N/A X X X XF53112357204xxN/A50000N/AXXF53112357204xx N/A 41250 N/A X X XF53114022200xxN/A 50000 N/A X XN/A 41250 N/A X X XF53114023200xx N/A 50000 N/A X X X XNF53120422200xxN/A 50000 N/A X XNN/A 41250 N/A X X XRNOSE LANDING GEAR LEG (FIG. 12)RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 11)Retraction actuator pin(Main fitting side)D61686 75000 50000 N/A X X X X X X XRRETRACTION ACTUATOR (FIG. 12)Retraction actuator eyeendD62588 N/A 50000 N/A X X X X X X XD62588-1 N/A 50000 N/A X X X X X X XD67840 N/A 50000 N/A X X X X X X XRetraction actuatorbearingD61950-1 N/A 50000 N/A X X X X X X XD61950-10 N/A 50000 N/A X X X X X X XD67839 N/A 50000 N/A X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 18EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYA330-2xxA330-30x A330-32x/A330-34xNomenclaturePart Number FH LDG Cal. WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xRetraction actuatorsliding rodD62328 N/A 50000 N/A X X X X X X XD62328-1 N/A 50000 N/A X X X X X X XD67837 N/A 50000 N/A X X X X X X XRetraction actuator plugD61952N/A 50000 N/A X X X X X X XD61952-1 N/A 50000 N/A X X X X X X XD67838 N/A 50000 N/A X X X X X X XRetraction actuatorcylinderD62587 N/A 50000 N/A X X X X X X XD62587-1 N/A 50000 N/A X X X X X X XD67836 N/A 50000 N/A X X X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-2-2PAGE: 19EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system areprovided in the sub-part 4-0 paragraph 1.N Explanation notes are located under the assy title.LIFE LIMITATIONS(Whichever occurs first)LIFE LIMITATIONS APPLICABILITYNA330-2xxA330-30x A330-32x/A330-34xNNNomenclature PartNumber FH FCCal.WV02xWV05xWV060WV00xWV01xWV05xWV00xWV01xWV02x WV05xNATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 16 to 17)N Pitot ProbeC16195BA60000 40000 N/A X X X X X X XN80000 20000 N/A XN Sensor – Angle Of Attack4515032060000 40000 N/A X X X X X X XN80000 20000 N/A XNC16291AA60000 40000 N/A X X X X X X XN80000 20000 N/A XNATA 34-21-00 NAVIGATION - ALTITUDE AND AIRSPEED STANDBY DATA (FIG. 18)N Altimeter Standby64141-582-160000 40000 N/A X X X X X X XN80000 20000 N/A XN64141-590-160000 40000 N/A X X X X X X XN80000 20000 N/A XNIndicator StandbyAirspeed64050-868-160000 40000 N/A X X X X X X XN 8000020000N/AXNATA 34-22-00 NAVIGATION – ATTITUDE AND HEADING STANDBY DATA (FIG. 19)N Compass StandbyKCA0105W60000 40000 N/A X X X X X X XN80000 20000 N/A XNIndicator StandbyHorizon501-1568-3460000 40000 N/A X X X X X X XN 8000020000N/AXNH321BHM160000 40000 N/A X X X X X X XN80000 20000 N/A XNH341BVM60000 40000 N/A X X X X X X XN 8000020000N/AXEND OF SUB-PART 4-2-2AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-3-1PAGE: 1EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTSSub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRRRRRR274400-00001-1-E311312THSA– FIG. 05Detailed inspection of the ball screwassembly for integrity of the primary andsecondary load path and check the gap at thesecondary nut trunnion.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 R02AMM 27-44-5147147-50047172-300PRE MOD55780ORPRE MOD54880(27-3137)ORPRE MOD54881(27-3143)RRR274400-00001-2-E311312THSA– FIG. 05Detailed inspection of the ball screwassembly for integrity of the primary andsecondary load path and check theCheckable 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 27-44-5147172-500POST SBA330-27-3137PRE SBA330-92-3046DRAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-3-1PAGE: 2EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTRRRRRRRRRRRR274400-00001-3-E 311312THSA– FIG. 05Detailed inspection of the ball screwassembly for integrity of the primary andsecondary load path and check theCheckable 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 27-44-5147172-510POST MOD55780PRE MOD52269ORPOST MOD55780PRE MOD56056ORPOST MOD55780PRE SBA330-92-3046NNNNNNNNNNN274400-00001-4-E 311312THSA– FIG. 05Detailed inspection of the ball screwassembly for integrity of the primary andsecondary load path and check theCheckable 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 POST MOD54881(27-3143)PRE SBA330-92-3046RN274400-00002-1-E311312THSA– FIG. 05Lubrication of the THSA ball-nut.Note: No short-term extension is allowed.700 FHNote700 FHNoteAMM 12-22-27/30147147-50047147-70047172-30047172-50047172-510ALLAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-3-1PAGE: 3EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFTNNNNNNNNNNNNN292400-00001-1-E 633Auxiliary Hydraulic Power– FIG. 08Remove Ram Air Turbine (RAT) for overhaul.Fit a RAT that has not accumulated 20 Yesince last overhaul.20 Ye80000 FH20 Ye80000 FHAMM 292452/401CMM 29-21-31758546759123762956762973764239766351768084770379770952770952A770952B17029341702934AALLEND OF SUB-PART 4-3-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-3-2PAGE: 4EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330R Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFT275000-00001-1-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-2007Note 1N/ASB A330-27-3151AMM 27-54-56AMM 27-54-57N/AUp to MSN0183inclusive275000-00001-2-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 in accordance withSB A330-27-3151. Report inspectionresults, whatever they are, toAIRBUS.Repetitive inspections in accordancewith SB A330-27-3152.16-Aug-2009Note 16 YeNote 1SB A330-27-3151SB A330-27-3152AMM 27-54-56AMM 27-54-57N/AUp to MSN0420inclusiveAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 16/09ALS PART 4-3-2PAGE: 5EASA APPROVED©AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A330NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 1.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask NumberZoneDescriptionThresholdIntervalPNRAIRCRAFT275000-00001-3-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)onwardsEND OF SUB-PART 4-3-2

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1- GENERAL

− A330 ALS Part 4 revision 00:

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

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

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

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

− French DGAC CN 2001-545(B)R1, and

− French DGAC CN F-2002-414(B)R3, and

− French DGAC CN F-2003-140(B)R1, and

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

− EASA AD 2007-0309, and

− EASA AD 2008-0026.

− A330 ALS Part 4 revision 01:

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

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

included and some 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) activities

(Mod 58269) which are 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.

2- SUMMARY OF CHANGES:

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

4 (revision 01).

New items:

RECORD OF REVISIONS:

Introduction of transition phases between A330 ALS Part 4 revision 01 and 02 for airworthiness

limitations not subject to exceptions.

Indication of the origin to apply for modified intervals.

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SUB-PART 4-0:

− A330-301 Limit Of Validity:

− Extension of the LOV in accordance with the Intermediate Service Goal (ISG) exercise.

The ISG step 1 allows the LOV to be escalated from 60000 FH/40000 FC up to 80000

FH/20000 FC for A330-301. Associated rules included.

− References of Messier Dowty SB providing the relationships between assemblies and

detail part numbers added to paragraph 3A.

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:

− Pressure reducers PNR D41428 and PNR E62691-00

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

and PNR SC5300-4,

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

764239, PNR 766351, PNR 768084, PNR 770379, PNR 770952, PNR 770952A, PNR

770952B, PNR 1702934 and PNR 1702934A,

− Pitot probes: PNR C16195AA and PNR C16195BA,

− Sensors – Angle of Attack: PNR 45150320 and PNR C16291AA,

− Altimeters standby: PNR 64141-582-1 and PNR 64141-590-1,

− Indicators standby airspeed: PNR 64050-868-1,

− Compass standby: PNR KCA0105W,

− Indicators standby horizon: PNR 501-1568-34, PNR H321BHM1 and PNR H341BVM.

− Introduction of new PNR of:

− Elevator servo-controls: PNR SC4800-10, PNR SC4800-11, PNR SC4800-72, PNR

SC4800-73, PNR SC4800-74, PNR SC4800-92, PNR SC4800-93, PNR SC4800-94,

PNR SC4800-103, PNR SC4800-104, PNR SC4800-113 and PNR SC4800-114.

− Inboard aileron servo-control: PNR C38661-002.

− Outboard aileron servo-control: PNR C38657-002.

− THS Actuator: PNR 47147-700,

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− Spoiler servo-controls in position 1: PNR 1387A0000-01, PNR 1387A0000-02, PNR

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

− Spoiler servo-controls in positions 2 to 6: PNR 1386A0000-01, PNR 1386A0000-02,

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

− MLG retraction links: PNR 201489315 and PNR 201489316,

− NLG retraction actuator pin (airframe side): PNR F53120422200xx.

SUB-PART 4-3:

− Task 274400-00001-4-E.

− Task 292400-00001-1-E.

Amendments:

SUB-PART 4-2:

− Figures numbers amended for each components/items.

− Spoiler servo-controls in position 1: Life limits amended for PNR MZ4339390-01X, PNR

MZ4339390-02X, PNR MZ4339390-10X and PNR MZ4339390-12.

− Spoiler servo-controls in positions 2 to 6: Life limits amended for PNR MZ4306000-01X,

PNR MZ4306000-02X, PNR MZ4306000-10X and PNR MZ4306000-12.

− Main Gear Pin W1: Life limit amended for PNR 201275673 and 201478614.

− Inboard aileron servo-controls: Life limitation amended for PNR 3337457-59 and PNR

3337457-60.

− Outboard aileron servo-controls: Life limitation amended for PNR 3337458-59 and PNR

3337458-60.

SUB-PART 4-3:

− Task 274400-00001-1-E: Aircraft limitation applicability amended.

− Task 274400-00001-2-E: Threshold amended. Aircraft limitations applicability amended.

− Task 274400-00001-3-E: Aircraft limitation applicability amended.

− Task 274400-00002-1-E: PNR limitation applicability amended.

### AIRWORTHINESS LIMITATIONS SECTION

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# A330

Deletions:

SUB-PART 4-0:

None.

SUB-PART 4-1:

None.

SUB-PART 4-2:

None.

SUB-PART 4-3:

None.