# A340 AIRWORTHINESS LIMITATIONS SECTION

REVISION: 03 

# ALS Part 4

- Ageing Systems Maintenance

© AIRBUS SAS 2012. 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.

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

ISSUE: NOV 15/12 ALS PART 4 PAGE: 1-LEP

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

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# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

TABLE OF CONTENTS

SUBJECT PART

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

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# RECORD OF REVISIONS ROR

INTRODUCTION 4-0

ILLUSTRATIONS 4-1

SYSTEMS LIFE-LIMITED COMPONENTS 4-2

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 4-3

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: NOV 15/12 ALS PART 4 PAGE: 1-ROR

EASA APPROVED

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

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

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

procedure stated herein).

REVISION

NUMBER SUB-PARTS APPROVED BY

EASA EASA AD INSERTION IN

MAINT. PROG.

00 ROR

4-2

4-3 MAY 29/09 N/A

01 ROR

4-2

4-3 DEC 15/09 N/A

R 02 ROR

4-2

4-3 OCT 12/11 2012-0021

N

N

N 03 ROR

4-2

4-3 NOV 15/12

Note: The ALS Part 4 is covered by the Certification Document 00F050AM094/C01.

Revision 03 is approved by EASA under reference 10042208.

REVISION 03 COMPLIANCE TIME:

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

limitations defined in the sub-part 4-2 and 4-3 of the A340 ALS Part 4 revision 03 from 15-

Nov-2013.

2. From 15-Nov-2012 to 14-Nov-2013, 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 A340 ALS Part 4 at revision 02,

or,

− The sub-part 4-2 and 4-3 of the A340 ALS Part 4 at revision 03.

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

previous accomplishment date. R

R

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R

R

N

N

N

N

N

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 1

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# Sub-part 4-0 INTRODUCTION

1. GENERAL

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

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

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

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

agreed with the Authority of the State of aircraft registry.

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

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

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

Volume II, Part A, Chapter 3.

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

considering any variation requests.

A. ALS Part 4 applicability

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

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

Aircraft series Aircraft models WV

R A340-200 A340-211 WV000 series A340-212

R A340-213 WV000 series, WV020 series

R

A340-300 A340-311 WV000 series

R A340-312 WV000 series, WV020 series

R A340-313 WV000 series, WV020 series , WV050 series

R A340-500 A340-541 WV000 series, WV100 series

R A340-542 WV100 series

R A340-600 A340-642 WV000 series, WV100 series

R A340-643 WV100 series

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 (i ncluding 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. R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 2

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# 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 main tenance requirements (refer also to ALS

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

The Part 4 of the Airworthiness Limitations Section (ALS) has been created to contain

such maintenance requirements and associated airworthiness limitations to help to

qualify the systems installations for continued operation up to the operational life 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 A340 ALS Part 1.

− Life extension study.

− Continued Airworthiness (operational sa fety) issues (in-service experience).

All the maintenance requirements and associated airworthiness limitations indicated in

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

Aviation Safety Agency (EASA).

The publication of this document precludes the necessity to publish individual

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

C. Operational life applicable to A340 systems installations

Operation of aircraft systems up to the stated operational life (in Flight Hours or Flight

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

life 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 operational life extension.

R

Aircraft series Operational life

Flight Hours

(FH) Flight Cycles

(FC)

A340-200 series OR 0 80000 20000

100000 (3) 20000

N 134000 (4) 25000 (4)

A340-300 series PRE 49144 (2) (excluding A340-

300 POST 46650 and POST 46651) OR 0 80000 20000

100000 (3) 20000

N 156000 (4) 31000 (4)

A340-300 POST 46650 and POST 46651 (1) 0 60000 30000

A340-300 series POST 49144 (2) 100000 20000

A340-500 series 100000 16600

A340-600 series 100000 16600

(1) A340-300 POST MODification (MOD) 46650 and POST MOD 46651 is A340-313

model WV027 series (Short Range mission). R

R

R

R

R

R

R

R

R

R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 3

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# (2) Within the context of ALS Part 4, MOD 49144 is used to identify WV050 series

aircraft (Enhanced aircraft) since this modification cannot be retrofitted on WV000,

WV010 and WV020 series aircraft.

(3) Applies only to aircraft POST MOD 200103/Service Bulletin (SB) A340-00-4050

PRE MOD 202206.

(4) Applies on only to aircraft POST MOD 202206.

Note: When different sets of operational life 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 operational life

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

operational life.

D. ALS Part 3 and ALS Part 4 correlation

At time of original Type Certification and major design change during aircraft

operational life, an appraisal of aircraft systems is carried out within the frame of the

Systems Safety Assessments. This may identify a need to schedule repetitive

maintenance tasks within a defined interval so as to maintain the required safety

objectives for individual failure conditions. A subset of these tasks, the majority of which

detect latent failures, are identified as Certification Maintenance Requirements (CMR).

These constitute operational limitations and are mandated through their location in the

ALS Part 3.

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

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

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

requirement associated to a life limitation less than or equal to the applicable

operational life, 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 utilization. Combining the limitations from

different sets is not permitted.

Sub-part 4-2-1: Life Limits

Components/items listed under this sub-part ar e those having a life limit less than the

operational life due to failure during tests and whose failure could result in an unsafe

condition of the aircraft.

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

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

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

R

R

D D N

N

N

R

N

R

R

R

D

R

R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 4

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

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

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

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

than or equal to the applicable operational life to prevent aircraft systems failures,

which could contribute to an unsafe condition of the aircraft.

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

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

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

the inspection threshold and interval quoted in this document.

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

at component/item level and aircraft (system) level respectively.

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

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

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

reaching the airworthiness limitation.

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

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

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

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

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

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

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

limitation.

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

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

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

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

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

successful task recording can be entered.

G. Traceability and replacement/maintenance requirements

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

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

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

limitations.

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

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

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

R

R

R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# Airworthiness limitations (including life limitations) must be adjusted as

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

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

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

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

Certificate of Airworthiness.

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

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

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

current revision of the ALS Part 4.

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

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

Part 4.

For further guidance, Operators are requested to contact Airbus.

Note 1: In the context of the ALS Part 4, traceability means records that clearly

demonstrate the history of components/items back to initial entry into service,

so that airworthiness limitations are accurately applied. Traceability records

may comprise, but are not limited to, the following:

− Application history (aircraft type, model, WV, MSN i.e. Manufacturer Serial

Number, etc...),

− Maintenance actions carried out (Airworthiness Directives, modifications,

repairs, inspections, etc...),

− Life accumulation (accounting for any individual aircraft to which a

component/an item may have been fitted).

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

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

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

issued in agreement with the EASA.

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

required for consumable component (for which replacement is controlled at

assembly/aircraft level).

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

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

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

H. Transfers of items between aircraft applications

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

types, aircraft models, etc...) may be different when this component/item is transferred N

N

N

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 6

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# to 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 present application i.

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

does not impose an airworthiness limitation, the operational life of the relevant ALS

Part 4 for that application must be used.

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

same usage parameters (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 operational life, 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 exit 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 organization 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 operational life. Examples of these means are:

− Record keeping system, 

# i Cp

j Cp j Ca

1 i Tr × ∑

−= 

# ⎥ ⎥

⎦ ⎤

⎢ ⎢

⎣ ⎡

⎟ ⎟

⎠ ⎞

⎜ ⎜

⎝ ⎛

R

R R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 7

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# − 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), Volume II, Part B, Chapter 2 indicates:

The concept of Continuing Airworthiness includes the reporting of defects and

other significant maintenance and operational information by the Operator to the

organization 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,

significant hydraulic fluid or fuel leak age and any emergency system or total system

failure.

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

− Organization 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 organization identifying the condition to which the report relates (Refer to

EASA Part M.A.202 and Part 145.A.60). R R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 8

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# K. ALS Part 4 airworthiness limitations

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

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

case of damage/repair.

L. Production/Repair concessions and Alternative Methods Of Compliance

Airworthiness limitations of the ALS sub-parts 4-2 and 4-3 may be negated by

instructions given in either a Production concession, a Repair design Approval Sheet

(RAS), an ALS Variation (AV) or an Alternative Method Of Compliance (AMOC).

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

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

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

requested to contact Airbus for guidance.

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

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

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

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

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

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

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

solution/AV/AMOC.

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

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

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

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

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

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

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

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

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

by the relevant Airworthiness Authority for any necessary adaptations of the

airworthiness limitations.

When such an aircraft/a sub-assembly/a component/an item is transferred from one

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

necessary adaptations of airworthiness limitations must be transferred as well. R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 9

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# 2. DEFINITIONS

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

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

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

Operator.

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

cycles and/or landings.

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

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

its intended function.

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

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

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

test flights) must be taken into account.

Calendar times (Cal.): Airworthiness limit ations in Years (Ye), Months (Mo),

etc... must be counted from the date of initial entry into

service (unless otherwise stated). In considering the

accumulated time since the initial entry into service, it

should be noted that Calendar time usage parameter

cannot be frozen (unless stated for individual

components/items).

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

may be needed to cover an uncontrollable or

exceptional unexpected situation.

Flight Cycle (FC): A complete take-off and landing sequence.

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

and “wheels-on”.

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

item performs one or more of its functions within

specified limits.

Interval: The period expressed in usage parameters like FH

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

between consecutive accomplishments of a specific

task, excluding any excepti onal short-term extensions

from calculations.

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

coming to a complete stop or performing a “touch and

go”.

# A340 AIRWORTHINESS LIMITATIONS SECTION

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

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

tolerances.

Threshold: The initial accomplishment of a specific maintenance

task from the initial entry into service. It may be

expressed in usage parameters like FH and/or FC

and/or LDG and/or Calendar time.

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

does not come to a full stop prior to commencing an

additional flight.

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

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

of FC up to threshold inspection or between two

consecutive inspections. Each “Touch and go” above

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

inspection or between two consecutive inspections.

3. RULES SPECIFIC TO SUB-PART 4-2

A. Authorised systems components/items

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

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

has been validated for a specific individual aircraft MSN.

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

associated modifications, which are published by Airbus.

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

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

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

assembly.

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

replacement PNR, detail PNR and applicable SB:

− Messier-Dowty Ltd Service Bulletin number:

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

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

47487 – ‘growth scallop’),

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

− Messier-Dowty SA Service Bulletin number:

− D23285-32-040 (nose landing gear).

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

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

R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 11

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# B. Life limitation/Replacement time indication

(1) General

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

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

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

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

stated).



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

paragraph 1.G.

In computing components’/items’ life, calculations must include flight hours

and/or flight cycles and/or landings and/or Calendar time (as applicable)

since the initial entry into service of the component/item (unless otherwise

stated).



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

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

lines as the PNR.

C. Life limitation applicability

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

sub-part 4-2), according to:

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

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

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

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

A340-21x stands for: A340-211, A340-212 and A340-213

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

X stands for: All A340 models defined by the applicability of the

column.

-313 stands for: A340-313 model only, defined by the applicability

of the column.

excl. -311 stands for: All A340 models defined by the applicability of the

column, excluding the A340-311 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.

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 12

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# (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 (for all aircraft defined by the

applicability of the column), excluding MSN XXX.

4. RULES SPECIFIC TO SUB-PART 4-3

A. Airworthiness limitations

(1) General

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

calculations must include flight hours and/or flight cycles and/or landings

and/or calendar time (as applicable) since the initial entry into service of the

component/item (unless otherwise stated).



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

The limitations must be applied from:

− The initial entry into service, for the threshold and

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

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

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

one associated with the inspection method used at last inspection.

B. ALS sub-part 4-3 layout.

The maintenance requirements and associated airworthiness limitations are presented

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

(1) Task Number

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

Document (MPD) system and is described as follows:

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

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

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. R

R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 13

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# 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.

(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.

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 14

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# (a) PNR

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

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

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

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

the associated modifications, which are published by Airbus.

(b) Aircraft

Applicability Task applicable to



# A LL All A340 aircraft.

A 340-xxx A340-xxx series aircraft.

PRE nnnnn All aircraft PRE MOD nnnnn.

i.e. A340 that do not have MOD nnnnn embodied.

POST nnnnn All aircraft POST MOD nnnnn.

i.e. A340 that do have MOD nnnnn embodied.

POST nnnnn

Sxxxxx A ll 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. A340 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.

A340-211

OR

A340-311

PRE nnnnn All A340-211, or

All A340-311 that do not have MOD nnnnn embodied.

A340-211

POST nnnnn

OR

A340-311

POST nnnnn

PRE mmmmm All A340-211 that do have MOD nnnnn embodied, or

All A340-311 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 A340-xx-yyyy embodied

(applicable only to retrofit solution).

CFM All aircraft equipped with CFM56-5C engines.

RR All aircraft equipped with RR Trent 500 engines. R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-0 PAGE: 15

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

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

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

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

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

objectives declared at Type Certification.

Repeated use of such extensions, either on the same aircraft or on similar

aircraft in the Operator's fleet, should not be used as a substitute for good

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

escalation.



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

identified in the ALS sub-part 4-3, it has been accepted by the Primary Certification

Authority (EASA) that short-term extensions up to the following maximum values may

be granted without consultation with that office.

(1) Controlled by Flight Hours (FH)

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

granted on ASM airworthiness limitations quoted in terms of Flight Hours.

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

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

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

LanDinGs.

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

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

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

limitations quoted in terms of Months.

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

may exceptionally be granted.

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

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

Programme.

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

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

column.

END OF SUB-PART 4-0

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 1

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 26-23-00 – LWR DECK CARGO COMPART. FIRE EXTING. FWD, AFT & BULK – FIG. 01 Sub-part 4-1 ILLUSTRATIONS

Pressure Reducer

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/2012 ALS PART 4-1 PAGE: 2

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 26-28-00 – AUXILIARY AREA FIRE EXTING. BCRC – FIG. 02 Pressure Reducer 

# D

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 3

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 27-14-00 – AILERON AND HYDRAULIC ACTUATION – FIG. 03 Aileron

Servo-control

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 4

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 27-23-00 – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION – FIG. 04 Rudder/Pedal

Limitation Unit



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 05 Elevator Servo-control



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 6

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 27-44-00 – THS HYDRAULIC ACTUATION – FIG. 06 THSA



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 7

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.



# ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 07 Flap Rotary Actuator



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 8

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.



# ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 08 Flap Power Control Unit (PCU) 

# A

N

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 9

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 09 R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 10

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.



# ATA 27-84-00 – SLATS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 10 T-Gearbox 

# B

N

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 11

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 29-24-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 11 R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 12

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-11-00 – MAIN LANDING GEAR – FIG. 12 (*) Location, item not illustrated

FORWARD Pin P (*) Retraction

actuator

Lock stay

actuator

Side Stay

Assembly



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 13

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-11-00 – MAIN LANDING GEAR – FIG. 13 Retraction link

Retraction

bracket Pin W2

Retraction actuator

piston rod Retraction

jack fitting

Pin W

Pin W1

Main fitting



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 14

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-11-00 – MAIN LANDING GEAR – FIG. 14 Side Stay Assembly Lock link

(subassembly) Lock stay actuator

pin (x2)



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 15

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-31-00 – MAIN LANDING GEAR – FIG. 15 Lock stay actuator

piston rod Lock stay actuator

cylinder Lock stay actuator

rod end

Lock stay actuator

gland



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 16

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-31-00 – MAIN LANDING GEAR – FIG. 16 Retraction actuator

piston rod

Retraction actuator

insert

Retraction actuator

gland

Retraction actuator

cylinder Retraction actuator

piston head



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 17

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-15-00 – CENTER LANDING GEAR – FIG. 17 (A340-500/-600 SERIES) FORWARD Main fitting

Retraction actuator pin

(main fitting side) Unlock actuator pin

(drag stay)

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 18

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-15-00 – CENTER LANDING GEAR – FIG. 18 (A340-500/-600 SERIES) Unlock actuator

rod end

Unlock actuator

piston rod Unlock actuator

gland Unlock actuator

cylinder Unlock actuator pin

(lock link) Unlock actuator pin

(drag stay)

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 19

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-31-00 – CENTER LANDING GEAR – FIG. 19 (A340-500/-600 SERIES) Retraction actuator

piston rod

Retraction actuator

bearing Retraction actuator

cylinder

Retraction actuator

piston head

Retraction actuator

piston rod nut Retraction actuator pin

(airframe side)



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 20

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-21-00 – NOSE LANDING GEAR – FIG. 20 (A340-200/-300 SERIES) Main fitting

Retraction actuator pin

(main fitting side)



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 21

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. Airframe

Retraction actuator pin

(main fitting side) Retraction actuator pin

(airframe side)

Retraction actuator

bearing

Retraction actuator

eye end Retraction actuator

body

Retraction actuator

plug

Retraction actuator

sliding rod Retraction actuator

cylinder



# ATA 32-31-00 – NOSE LANDING GEAR – FIG. 21 (A340-200/-300 SERIES) R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 22

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. Retraction actuator pin

(main fitting side) Main fitting



# ATA 32-21-00 – NOSE LANDING GEAR – FIG. 22 (A340-500/-600 SERIES) R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 23

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 32-31-00 – NOSE LANDING GEAR – FIG. 23 (A340-500/-600 SERIES) Retraction actuator pin

(airframe side) FORWARD

Retraction actuator pin

(main fitting side) Retraction actuator

piston rod

Retraction actuator

piston rod nut Retraction actuator

bearing Retraction actuator

cylinder

Retraction actuator

piston head Main fitting

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 24

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 35-13-00 – CREW OXYGEN – CONTROL AND INDICATING – FIG. 24 Pressure Switch



# R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 25

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

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

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 26

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 53-40-00 – REAR FUSELAGE – FIG. 26 R

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 27

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 78-31-00 – THRUST REVERSER CONTROL AND INDICATING – FIG. 27 

# B

N

# A340 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 15/12 ALS PART 4-1 PAGE: 28

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# ATA 78-31-00 – THRUST REVERSER CONTROL AND INDICATING – FIG. 28

END OF SUB-PART 4-1 NA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 1EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-2 SYSTEMS LIFE-LIMITED COMPONENTS1. Sub-part 4-2-1 LIFE LIMITSA. A340-200/-300 SERIESNote: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xATA 26-23 FIRE PROTECTION – LOWER DECK CARGO COMPARTMENT FIRE EXTINGUISHING (FIG. 01)Pressure reducerD41428N/A N/A 20Ye X X X X XATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02)Pressure reducerE62691-00 N/A N/A 20 YeXATA 27-14 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 03)(1) Applicable to servo-controls installed in positions Functional Item Number (FIN) 7CS1, 8CS1, 7CS2 and 8CS2 for inboard servo-controls, and FIN 9CS1, 10CS1,9CS2, 10CS2 for outboard servo-controls (active and damping).(2) Embodiment of MOD 45512/SB A340-27-4062 introduces different PNR. MOD 45512factory embodied on MSN 228 and subsequent.Inboard aileron servo-control(1) (2)3337457-22 9000 N/A N/A X X X3337457-23 9000 N/A N/A X X X3337457-26 27000 N/A N/A X X X3337457-27 27000 N/A N/A X X X3337457-30 65600 16400 N/A X X X3337457-31 65600 16400 N/A X X X3337457-35 65600 16400 N/A X X X3337457-36 65600 16400 N/A X X X3337457-37 65600 16400 N/A X X X3337457-38 65600 16400 N/A X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 2EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xOutboard aileron servo-control(1) (2)3337458-30 65600 16400 N/A X X X3337458-31 65600 16400 N/A X X X3337458-35 65600 16400 N/A X X X3337458-36 65600 16400 N/A X X X3337458-37 65600 16400 N/A X X X3337458-38 65600 16400 N/A X X XNATA 27-23 FLIGHT CONTROL – RUDDER AND PEDALTRAVEL LIMITING ACTUATION (FIG. 04)N (1) FIN 24CS.N (2) FIN 36CS.NRudder Travel Limitation Unit(RTLU) (1)341400M02 100000 33000 N/A X X X XNPedal Travel Limitation Unit(PTLU) (2)341400M02 100000 33000 N/A X X X XRATA 27-34 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC ACTUATION (FIG. 05)(1) Applicable to servo-controls installed in positions FIN 2CS1, 2CS2, 3CS1 and 3CS2 (active and damping).Elevator servo-control (1)SC4800-2 N/A N/A 31-Aug-04 XXXXSC4800-3 N/A N/A31-Aug-04 X XXXSC4800-4 N/A N/A31-Aug-04 X XXXSC4800-6 N/A N/A31-Aug-04 X XXXSC4800-7 N/A N/A31-Aug-04 X XXXSC4800-7A N/A N/A30-Jun-08 X X X X XSC4800-8 N/A N/A31-Aug-04 X XXXSC4800-9 N/A N/A30-Jun-08 X X X X X.../...SC4800-10 N/A N/A30-Jun-08 X X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 3EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xElevator servo-control (1)SC4800-11 N/A N/A 30-Jun-08 X X X X XSC4800-72 N/A N/A30-Jun-08 X X X X XSC4800-73 N/A N/A30-Jun-08 X X X X XSC4800-92 N/A N/A30-Jun-08 X X X X XSC4800-93 N/A N/A30-Jun-08 X X X X XSC4800-103 N/A N/A30-Jun-08 X X X X XSC4800-113 N/A N/A30-Jun-08 X X X X XRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06)(1) Embodiment of MOD 45906/SBA340-27-4059 and MOD 49591/SB A340-27-4099 introduces different PNR. MOD 45906 is factory embodied on MSN 233 andsubsequent.(2) Embodiment of MOD 49590/SBA340-27-4089 introduces differentPNR. MOD 49590 is factoryembodied on MSN 429, 433, 435 and subsequent.THS Actuator47147-200 N/A N/A 31-Jul-04X (1)47147-210 N/A N/A 31-Jul-04X (1)47147-213 N/A N/A 31-Jul-04X (1)47147-300 N/A N/A 31-Jul-04X (1)47147-303 N/A N/A 31-Jul-04X (1)47147-350 N/A N/A 31-Jul-04 204 X (1)X (1)47147-400 N/A N/A 31-Jul-04 X (1) X (1)X (1)N47147-500 80000 20000 N/A X X X X XN47147-700 80000 20000 N/A X X X X X47172 N/A N/A 31-Dec-03X (2) X (2) X (2)RATA 27-54 FLIGHT CONTROL – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 07 & 08)(1) Embodiment of MOD 50044 (associatedto SB A340-27-4111) introduces new PNR.Flap Rotary Actuator – Type A 697510004 (1) N/A 18000 12 Ye XXXX697510005 (1) N/A 18000 12 Ye XXXXA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 4EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xFlap Rotary Actuator – Type B 697511004 (1) N/A 18000 12 Ye XXXX697511005 (1) N/A 18000 12 Ye XXXX697511006 (1) N/A 18000 12 Ye XXXX697511007 (1) N/A 18000 12 Ye XXXXN Flap Power Control Unit (PCU)953A0000-04 N/A N/A 31-Oct-14 X X X XN953A0000-05 N/A N/A31-Oct-14 X X X XN953B0000-01 N/A N/A31-Oct-14 X X X XRATA 27-64 FLIGHT CONTROL – SPOILER HYDRAULIC ACTUATION (FIG. 09)(1) Not applicable to aircraft POST MOD 44670 and deliveredafter 13-Jan-2006. Embodimentof MOD 51413/SB A340-27-4139 introduces different PNR.(2) FIN 13CS1 and 13CS2.(3) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2.(4) For spoiler servo-controls with unknown history of life accumulation on 31-Aug-2006,their total accumulated life is calculated by addition of the life accumulated bythe aircraft they are fitted to on 31-Aug-2006,to their actual life accumulated since.(5) When removed from aircraft, these servo-controls must be scrapped.(6) Applicable to aircraft up to and including MSN 598.−For aircraft, which have accumulated on 05-Sep-08 less than or equalto 8500 FC since aircraft initial entry into service, modify all servo-controls inaccordance with SB A340-27-4115 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-controls, in accordance withSB A340-27-4115:−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 sinceaircraft 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.(7) Embodiment of MOD 48956/SBA340-27-4100 introduces differentPNR. MOD 48956 is factoryembodied on MSN 385, MSN 446 and subsequent.A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 5EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xSpoiler servo-controlposition 1 (2)MZ4339390-01X(6) N/A N/A 05-Mar-10 X X X X XMZ4339390-02X(6) N/A N/A 05-Mar-10 X X X X XMZ4339390-10X (6) N/A N/A 05-Mar-10 X X X X XS4-3000470(1)(4)(5)N/A 15000 N/A X X X X XS4-3000470-01(1)(4)(5)N/A 15000 N/A X X X X XS4-3000470-02(1)(4)(5)N/A 15000 N/A X X X X XS4-3000470-03(1)(4)(5)N/A 15000 N/A X X X X X1387A0000-01 (7) N/A N/A 31-Dec-03 X X X X X1387B0000-01 (7) N/A N/A 31-Dec-03 X X X X XSpoiler servo-controlpositions 2-6 (3)MZ4306000-01X(6) N/A N/A 05-Mar-10 X X X X XMZ4306000-02X(6) N/A N/A 05-Mar-10 X X X X XMZ4306000-10X(6) N/A N/A 05-Mar-10 X X X X XS4-3000460(1)(4)(5)N/A 14000 N/A X X X X XS4-3000460-01(1)(4)(5)N/A 14000 N/A X X X X XS4-3000460-02(1)(4)(5)N/A 14000 N/A X X X X XS4-3000460-03(1)(4)(5)N/A 14000 N/A X X X X X1386A0000-01 (7) N/A N/A31-Dec-03 X X X X X1386B0000-01 (7) N/A N/A 31-Dec-03 X X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 6EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xNATA 27-84 SLATS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 10)N (1) Comply with these requirements no later than 31-Oct-2014.N T-Gearbox (TGBx)921A0000-01N/A N/A 31-Oct-14 X X X X XN921B0000-01 (1) N/A 32000 N/A X X X X XN921C0000-01 (1) N/A 24000 N/A X X X X XN921D0000-01 (1) N/A 24000 N/A X X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 7EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16)RMAIN STRUT AND DRESSINGS (FIG. 12 & 13)Notes (1) to (6): Refer to DGAC CN 97-008-058(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 A340-32-4092 introduces a differentPNR. MOD 43863 factory embodied on original landing gear of A340-200 MSN 151 and subsequent, excludingMSN 204. MOD 43863 factory embodied on original landing gear of A340-300 MSN 115,125, 133, 134, 145 and 146.(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 A340-32-4092 introduces a different PNR. MOD43863 factory embodied on original landinggear of A340-200 MSN 151 and subsequent, excluding MSN 204. MOD 43863 factory embodied on original landinggear of A340-300 MSN 115,125, 133, 134, 145 and 146.(7) Embodiment of MOD 46903/SBA340-32-4135 introduces a different PNR. MOD46903 factory embodied on original landing gear ofMSN 273 and subsequent.(8) Embodiment of MOD 46904/SBA340-32-4134 introduces a different PNR. MOD46904 factory embodied on original landing gear ofMSN 273 and subsequent.(9) Embodiment of MOD 48066/SBA340-32-4164 introduces a different PNR. MOD48066 factory embodied on original landing gear ofMSN 367 and subsequent.(10) Life limit is the later of 900 aircraft FH counted from08-Jul-2009 or the accumulation of 11150 total LDG since initialentry into service of Pin W1 on any aircraft.(11) Life limit is the earlier of the 10-year calendar limit orthe limitation deducedfrom note (10).(12) Embodiment of MOD 58527/SB A340-32-4273 introduces a different PNR.Pin W201275796 (7) N/A 20000 10 Ye XX-313 -312/-313 -313Retraction link (LH)201275317 (9) N/A 35200 36 Mo X X -313 -312/-313 -313201489311 (12) N/A 8400 N/AX X -313 -312/-313 -313Retraction link (RH)201275318 (9) N/A 35200 36 Mo X X -313 -312/-313 -313201489312 (12) N/A 8400 N/AX X -313 -312/-313 -313Pin W1201275673 (7)(11) N/A (10)10 Ye X X -313 -312/-313 -313201478614 N/A (10) N/AX X -313 -312/-313 -313A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 8EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction bracket (LH)201428305 N/A (1) N/A excl. 204 X201428307 N/A (1) N/A excl. 204 X201428318 N/A (1) N/A excl. 204 X201428323 N/A (1) N/A excl. 204 X201428331 (2) N/A (1) N/A excl. 204 X201428331 (6) N/A 9000 N/A excl. 204 X201428333 N/A (1) N/A excl. 204 X201428335 N/A (1) N/A excl. 204 X201428338 (4) N/A (1) N/A excl. 204 X201428351 N/A 19800 N/A XX -313 -312/-313 -313201428378 N/A 19800 N/A XX -313 -312/-313 -313201428380 N/A 19800 N/A excl. 204 X201428382 N/A 19800 N/A excl. 204 X201428384 N/A 19800 N/A excl. 204 X201478303 N/A 19800 N/A excl. 204 X201478305 N/A 19800 N/A excl. 204 X201478307 N/A 19800 N/A excl. 204 XRetraction bracket (RH)201428306 N/A (1) N/A excl. 204 X201428308 N/A (1) N/A excl. 204 X201428319 N/A (1) N/A excl. 204 X201428324 N/A (1) N/A excl. 204 X201428332 (3) N/A (1) N/A excl. 204 X201428332 (6) N/A 9000 N/A excl. 204 X.../...201428334 N/A (1) N/A excl. 204 XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 9EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction bracket (RH)201428336 N/A (1) N/A excl. 204 X201428339 (5) N/A (1) N/A excl. 204 X201428352 N/A 19800 N/A XX -313 -312/-313 -313201428379 N/A 19800 N/A XX -313 -312/-313 -313201428381 N/A 19800 N/A excl. 204 X201428383 N/A 19800 N/A excl. 204 X201428385 N/A 19800 N/A excl. 204 X201478304 N/A 19800 N/A excl. 204 X201478306 N/A 19800 N/A excl. 204 X201478308 N/A 19800 N/A excl. 204 XPin W2201275667 (8)N/A 4500 5 Ye excl. 204 XN/A94005Ye204-313-312/-313-313Pin P201275602 (7) N/A 20000 10 Ye XX-313 -312/-313 -313RRETRACTION ACTUATOR (FIG. 16)(1) Embodiment of MOD 200837/SB A340-32-4284 introduces a different PNR.Retraction actuator piston rod 114256309 N/A 8080 31-Dec-07 X X -313 -312/-313 -313114256321 N/A 8080 31-Dec-07X X -313 -312/-313 -313114256323 N/A 5500 N/A XX -313 -312/-313 -313R114256326 N/A 18000 N/A XX -313 -312/-313 -313R114256328 N/A 18000 N/A XX -313 -312/-313 -313Retraction actuator gland 50-2113004-00(1) N/A 27790 N/A -312/-313 -313Retraction actuator cylinder 114256310N/A 22900 N/A X X -313 -312/-313 -313114256320 N/A 22900 N/A XX -313 -312/-313 -313A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 10EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xDRWV00x WV027 Other WV02x WV05xATA 35-13-00 OXYGEN – CREW OXYGEN– CONTROL AND INDICATING (FIG. 24)Pressure switchCMK80-01 80000 N/A 20 Ye XXXXXRATA 35-23-00 OXYGEN – PASSENGER OXYGEN (GAZEOUS) – CONTROL ANDINDICATING (FIG. 25)Quantity calculation control unit E69027 80000 N/A 20 Ye X X X X XNATA 78-31-00 THRUST REVERSER CONTROL AND INDICATING (FIG. 27 & 28)NN(1) Not authorised in position FIN 5003EG1 for engine 1 and engine 2 and FIN 5003EG4 for engine 3 and engine 4 on aircraft after 28-Feb-2011. Refer to EASA AD2010-0044 [Correction: 25 March 2010].NN(2) Not authorised in position FIN 5003EG2, 5003EG3, 5003EG4 for engine 1 and FIN 5003EG1, 5003EG2, 5003EG3 for engine 4 on aircraft after 31-Dec-2012.Refer to EASA AD 2010-0044 [Correction: 25 March 2010].NN(3) Not authorised in position FIN 5002EG1 for engine 1 and engine 2 and FIN 5002EG4 for engine 3 and engine 4 on aircraft after 28-Feb-2011. Refer to EASA AD2010-0044 [Correction: 25 March 2010].NN(4) Not authorised in position FIN 5002EG2, 5002EG3, 5002EG4 for engine 1 and FIN 5002EG1, 5002EG2, 5002EG3 for engine 4 on aircraft after 31-Dec-2012.Refer to EASA AD 2010-0044 [Correction: 25 March 2010].N Thrust reverser primary lock2885000-9 (1) (2) N/A 20000 N/A X X X X XN618700-1003 N/A 20000 N/A X X X X XN Thrust reverser actuator 1608000-4 (3) (4) N/A 20000 N/A X X X X XN1608000-5 (3) (4) N/A 20000 N/A XXXXXN1608000-6 (3) (4) N/A 20000 N/A XXXXXN1608000-7 (3) (4) N/A 20000 N/A XXXXXN618800-1003 N/A 20000 N/A X X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 11EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.B. A340-500/-600 SERIESNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02)Pressure reducerE62691-00 N/A N/A 20Ye X X X XRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06)(1) Embodiment of SB A340-27-5030introduces different PNR.THS Actuator47175-200 (1) N/A 4730 N/A X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-1PAGE: 12EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16)RRETRACTION ACTUATOR (FIG. 16)Retraction actuator pistonrod 50-1231002-01 N/A 6090 N/A X X X XRATA 32-15-00 CENTER LANDING GEAR (FIG. 17 to 19)RRETRACTION ACTUATOR (FIG. 19)(1) The calendar life limit is to be counted from the Date Of Manufacture (DOM) of the part. DOMsare provided in Messier-Dowty Service Letter A34/56-32-055.Retraction actuator cylinder50-1104001-00 N/A 7800 N/A X XRetraction actuator piston rod55-1104003-00 (1) N/A 3000 42 Mo XXRATA 32-21-00 NOSE LANDING GEAR (FIG. 22 & 23)RETRACTION ACTUATOR (FIG. 23)(1) The calendar life limit is to be counted from the Date Of Manufacture (DOM) of the part. DOMsare provided in Messier-Dowty Service Letter A34/56-32-055.Retraction actuator piston rod55-1026003-00 (1) N/A 3000 42 Mo XXRetraction actuator cylinder50-1026001-00 N/A 10300 N/A X XDEND OF SUB-PART 4-2-1A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 13EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.2. Sub-part 4-2-2 CURRENT DEMONSTRATED LIVESA. A340-200/-300 SERIESNote: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xATA 27-14 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 03)(1) Applicable to servo-controls installed in positions FIN 7CS1, 8CS1, 7CS2, 8CS2 for inboard servo-controls, and FIN 9CS1, 10CS1, 9CS2, 10CS2 for outboardservo-controls (active and damping).RDRDRInboard aileron servo-control(1)3337457-59 110000 N/A N/A X X X X XOutboard aileron servo-control(1)3337458-59 110000 N/A N/A X X X X XATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06)(1) Embodiment of MOD 200698/SB A340-27-4170 introduces different PNR.DR(2) Embodiment of MOD 58916/SB A340-27-4170 introduces different PNR.THS Actuator47172-300 8000020000 25 Ye X X X X X47172-500 (1) 80000 20000 25 Ye XXXXX47172-510 (2) 80000 20000 25 Ye XXXXX47172-520 80000 20000 N/A X X X X X47172-530 80000 20000 N/A X X X X XDA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 14EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16)RMAIN STRUT AND DRESSINGS (FIG. 12 & 13)(1) This PNR is common to pin W2 and pin P.Pin W201478613 N/A 42800 N/AX X -313 -312/-313 -313201489770 N/A 42800 N/A XX -313 -312/-313 -31355-2105061-00 N/A 46480 N/A-312/-313 -313Retraction link (LH)201489315 N/A10700 N/A X X -313-312/-313 -31350-2105026-00 N/A 46480 N/A-312/-313 -31350-2105224-00 N/A 46480 N/A-312/-313 -313Retraction link (RH)201489316 N/A10700 N/A X X -313-312/-313 -31350-2106026-00 N/A 46480 N/A-312/-313 -31350-2106224-00 N/A 46480 N/A-312/-313 -313N Pin W1201478652 N/A 25179 N/AX X -313 -312/-313 -31355-2105060-00 N/A 46480 N/A-312/-313 -313Retraction bracket (LH)50-2105027-00 N/A 46480 N/A -312/-313 -313Retraction bracket (RH) 50-2106027-00 N/A 46480 N/A -312/-313 -313Pin W2201478615 N/A 42800 N/AX X -313 -312/-313 -313201478637 N/A 42800 N/A XX -313 -312/-313 -31355-2105059-00 (1) N/A 46480 N/A -312/-313 -313Pin P201478612 N/A 42800 N/AX X -313 -312/-313 -31355-2105059-00 (1) N/A 46480 N/A -312/-313 -313RCOMPLETE SIDE STAY (FIG. 12, 14 & 15)Lock stay actuator pin201440611N/A 25000 N/A excl. 204 X201457606 N/A 25000 N/A excl. 204 XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 15EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRLOCK STAY ACTUATOR (FIG. 15)Lock stay actuator cylinder114354600 N/A 25000 N/A excl. 204 X201686600 N/A 25000 N/A excl. 204 XLock stay actuator piston rod 114354605 N/A 25000 N/A excl. 204 X201686602 N/A 25000 N/A excl. 204 XLock stay actuator gland114354606N/A 25000 N/A excl. 204 X201481611 N/A 25000 N/A excl. 204 X201481614 N/A 25000 N/A excl. 204 XLock stay actuator rod end114354602 N/A 25000 N/A excl. 204 X201686601 N/A 25000 N/A excl. 204 XRRETRACTION ACTUATOR (FIG. 16)(1) Must be replaced by a new one every timethe piston head is removedfrom the piston rod.Retraction actuator piston rod 50-2113002-00 N/A 50000 N/A-312/-313 -313Retraction actuator gland114256312 N/A 50000 N/A X X -313 -312/-313 -313114256322 N/A 50000 N/A X X-313 -312/-313 -31350-2113004-01 N/A 27790 N/A-312/-313 -313Retraction actuator piston head 114256308N/A 50000 N/A X X -313 -312/-313 -313114256639 N/A 50000 N/A XX -313 -312/-313 -31350-2113003-00 N/A 50000 N/A-312/-313 -313Retraction actuator insert114256629N/A (1) N/A X X-313 -312/-313 -313Retraction actuator cylinder 50-2113001-00 N/A 50000 N/A-312/-313 -313A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 16EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-21-00 NOSE LANDING GEAR (FIG. 20 & 21)DR(1) “xx” at the end of the PNR stands for any number between 00 and 99.Retraction actuator pin(Airframe side) (1)F53112357200xx N/A 37500 N/A XX -313 -312/-313RF53112357204xxN/A 25000 N/A -313NN/A 37500 N/A -312/-313RF53114022200xxN/A 25000 N/A -313NDRN/A 37500 N/A -312/-313F53114023200xx N/A 37500 N/AX X -313 -312/-313RF53120422200xxN/A 25000 N/A -313NN/A 37500 N/A -312/-313RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 20 & 21)RRetraction actuator pin(Main fitting side)D61686N/A 25000 N/A X X-312/-313 -313RN/A 37500 N/A -313RRETRACTION ACTUATOR (FIG. 21)Retraction actuator eye endD62588N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D62588-1N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D67840N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313Retraction actuator bearingD61950-1N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D61950-10N/A 25000 N/A X X-312/-313 -313.../...N/A 37500 N/A-313A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 17EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator bearingD67839N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313ND68397N/A 25000 N/A X X-312/-313 -313NN/A 37500 N/A -313Retraction actuator sliding rodD62328N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D62328-1N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D67837N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313Retraction actuator plugD61952N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D61952-1N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D67838N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313Retraction actuator cylinderD62587N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D62587-1N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D67836N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 18EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator bodyD61954N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D61954-10N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313D67876N/A 25000 N/A X X-312/-313 -313N/A 37500 N/A -313DA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 19EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.B. A340-500/-600 SERIESNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06)(1) Embodiment of MOD 200491/SB A340-27-5054 introduces different PNR. MOD 200491factory embodied on MSN 1102, MSN 1122 and subsequent.R THS Actuator47175-300 70000 10000 25 Ye XXXXR47175-500 (1) 70000 10000 25 Ye XXXXR47175-520 70000 10000 N/A XXXXA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 20EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16)RMAIN STRUT AND DRESSINGS (FIG. 12 & 13)(1) This PNR is common to pin W2 and pin P.Pin W55-1205156-03 N/A 20600 N/A XXXXRetraction link (LH)50-1205288-01 N/A 20600 N/A X X X XRetraction link (RH)50-1206288-01 N/A 20600 N/A X X X XPin W155-1205154-00 N/A 20600 N/A XXXXRetraction bracket (LH)50-1205007-00 N/A 20600 N/A X X X XRetraction bracket (RH)50-1206007-00 N/A 20600 N/A X X X XPin W255-1205151-00 (1) N/A 20600 N/AXXXXPin P55-1205151-00 (1) N/A 20600 N/AXXXXRRETRACTION ACTUATOR (FIG. 16)(1) Must be replaced by a new one every timethe piston head is removedfrom the piston rod.R Retraction actuator pistonrod 50-1231002-02 N/A 20600 N/A X X X XR Retraction actuator gland50-1231004-02 N/A 20600 N/A X X X XR Retraction actuator pistonhead 50-1231003-00 N/A 20600 N/A X X X XRetraction actuator insert 114256629 N/A (1) N/A X X X XR Retraction actuator cylinder50-1231001-00 N/A 20600 N/A X X X XRATA 32-15-00 CENTER LANDING GEAR (FIG. 17 to 19)(1) “xx” at the end of the PNR stands for any number between 00 and 99.Retraction actuator pin(Airframe side) (1)G53323620200xx N/A 16600 N/A X XG53323625200xx N/A 16600 N/A X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 21EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xLEG EQUIPPED (FIG. 17)RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 17 & 19)Retraction actuator pin(Main fitting side)55-1105016-00 N/A 13100 N/A X X55-1105315-00N/A 13100 N/A X XN/A 10300 N/A X XCOMPLETE DRAG STAY (FIG. 18)Unlock actuator pin (drag stay)55-1110052-00N/A 13100 N/A X XN/A 10300 N/A X XLOCK LINK (FIG. 18)Unlock actuator pin (lock link)55-1110052-00N/A 13100 N/A X XN/A 10300 N/A X XUNLOCK ACTUATOR (FIG. 18)Unlock actuator rod end55-1113006-00 N/A 20600 N/A X X55-1113006-01 N/A 20600 N/A X X X XUnlock actuator piston rod55-1113003-00 N/A 20600 N/A X X55-1113003-01 N/A 20600 N/A X X X XUnlock actuator gland55-1113016-00 N/A 20600 N/A X X55-1113016-01 N/A 20600 N/A X X X XUnlock actuator cylinder55-1113001-00 N/A 20600 N/A X X55-1113001-01 N/A 20600 N/A X X X XRRETRACTION ACTUATOR (FIG. 19)Retraction actuator cylinder50-1104001-01 N/A 20600 N/A X X X XRetraction actuator piston rod55-1104003-01 N/A 20600 N/A X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 22EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRetraction actuator piston head50-1104005-01 N/A 1400 N/A X X55-1104036-00 N/A 20600 N/A X X X XRetraction actuatorpiston rod nut55-1104008-00 N/A 20600 N/A X X55-1104008-01 N/A 20600 N/A X X X XRetraction actuator bearing50-1104010-01 N/A 20600 N/A X X50-1104010-02 N/A 20600 N/A X X X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 22 & 23)(1) “xx” at the end of the PNR stands for any number between 00 and 99.Retraction actuator pin(Airframe side) (1)F53115740000xx N/A 16600 N/A X X XF53115982000xx N/A 16600 N/A X X X XRNOSE LANDING GEAR LEG (FIG. 22 & 23)Retraction actuator pin(Main fitting side)55-1003014-00 N/A 20600 N/A X XR 55-1003283-00N/A16982N/AXXRETRACTION ACTUATOR (FIG. 23)Retraction actuator piston rod55-1026003-01 N/A 20600 N/A X X X XRetraction actuator bearing55-1026010-01 N/A 20600 N/A X X55-1026010-02 N/A 20600 N/A X X X XRetraction actuator piston head55-1026005-01 N/A 1400 N/A X X55-1026033-00 N/A 20600 N/A X X X XRetraction actuatorpiston rod nut55-1026008-00 N/A 20600 N/A X X55-1026008-01 N/A 20600 N/A X X X XRetraction actuator cylinder50-1026001-01 N/A 20600 N/A X X X XA340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-2-2PAGE: 23EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xDNWV00x WV10x WV00x WV10xATA 53-40-00 REAR FUSELAGE (FIG. 26)N (1) Apply to aircraft POST MOD 50990 or POST MOD 51344.N (2) This item is not transferable from an aircraftto another. Traceability at aircraft level is authorized.NRear Center Tank (RCT) liner (1)(2)F0003076900000 N/A N/A 12 Ye X XN F0003077000000N/AN/A12YeXXNF0003077100000 N/A N/A 12 Ye XXNF0003077200000 N/A N/A 12 Ye XXNF0003077300000 N/A N/A 12 Ye XXNF0003077400000 N/A N/A 12 Ye XXNF0003077500000 N/A N/A 12 Ye XXNF0003077600000 N/A N/A 12 Ye XXEND OF SUB-PART 4-2-2A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-3-1PAGE: 1EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTSSub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTR 274400-00001-1-E 311312THSA – FIG. 06Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the gap atthe secondary nuttrunnion.This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.Note 2: In computing the life accumulated bythe THSA for compliance with thethreshold, calculations must includeflight hours since the initial entry intoservice or since 17-Aug-2002,whichever occurs later.700 FHNotes 1 & 2700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147147-50047172-300PRE 55780PRE 27-4136PRE 27-4143R 274400-00001-2-E 311312THSA – FIG. 06Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.Note 2: At the time of SB A340-27-4136accomplishment.Note 2 700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147172-50047172-520POST 27-4136PRE 56056PRE 92-4056R03A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-3-1PAGE: 2EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTR 274400-00001-3-E 311312THSA – FIG. 06Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.700 FHNote 1700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147172-51047172-530POST 55780PRE 56056PRE 92-4056R03R 274400-00001-4-E 311312THSA – FIG. 06Detailed inspection of the ball screw assemblyfor integrity of theprimary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.700 FHNote 1700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147147-700 POST 27-4143PRE 56056PRE 92-4056R03R 274400-00002-1-E 311312THSA – FIG. 06Lubrication of the THSA ball-nut.Note: No short-term extension is allowed.1000 FHNote1000 FHNoteAMM 12-22-27/301 47147-50047147-70047172-30047172-50047172-51047172-52047172-530A340-200ORA340-300A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-3-1PAGE: 3EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTRRRRRRRRRRR292400-00001-1-E 633Ram Air Turbine (RAT) – FIG. 11Removal of Ram Air Turbine (RAT) (includingactuator, manifold, hydraulic pump, turbinelower gearbox assembly and strut-legassembly) for overhaul and replace with newor reconditioned units.20 Ye20 YeAMM 292452-960-801RAT (includingactuator,manifold,hydraulicpump,turbine-lowergearboxassemblyand strut-legassembly)ALLA340-200ORA340-300NNNN292400-00001-2-E 633Ram Air Turbine (RAT) – FIG. 11Remove RAT (including actuator) for overhauland replace with new or reconditioned units20 Ye 20 Ye AMM 292452-960-801 RAT (includingactuator)ALLA340-500ORA340-600END OF SUB-PART 4-3-1A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-3-2PAGE: 4EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFT275000-00001-1-E 570670FlapsPerform a simultaneous detailed visualinspection of the InputGear 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/A SB A340-27-4151AMM 27-54-56AMM 27-54-57N/A Up to MSN 0185inclusive275000-00001-2-E 570670FlapsPerform a simultaneous detailed visualinspection of the InputGear Boxes (IPGB) andof the Down Drive Shafts (DDS) on all flaptracks on both wings.Note 1: No short-term extension is allowed.Note 2: First inspection is performed inaccordance with SB A340-27-4151.Report inspections results, whateverthey are, to AIRBUS.Subsequent repetitive inspections areperformed in accordance with SBA340-27-4152.16-Aug-2009Notes 1 & 26 YeNotes 1 & 2SB A340-27-4151SB A340-27-4152AMM 27-54-56AMM 27-54-57N/A Up to MSN 0415inclusivePRE 200492PRE 201194(27-4171 and 27-5055), exceptMSN 0385 and0395A340 AIRWORTHINESS LIMITATIONS SECTIONISSUE: NOV 15/12ALS PART 4-3-2PAGE: 5EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTNNNNNN275000-00001-3-E 570670FlapsPerform a simultaneous detailed visualinspection of the InputGear Boxes (IPGB) andof the Down Drive Shafts (DDS) on all flaptracks on both wings.Note: No short-term extension is allowed.26-Oct-2009or6 years fromthe date oforiginaldelivery ofthe aircraft,whicheveroccurs later.Note6 YeNoteSB A340-27-4152SB A340-27-5040AMM 27-54-56AMM 27-54-57N/A MSN 0371, andMSN 0376, andMSN 0383, andMSN 0385, andMSN 0391, andMSN 0394, andMSN 0395, andMSN 0410, andMSN 0416(inclusive)onwardsPRE 200492PRE 201194(27-4171 and27-5055)275000-00001-4-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS). Lubricate all flap tracks on both wings24 Mo 24 Mo AMM 12-22-27 N/A POST 200492275000-00001-5-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 A340-27-4171 or SBA340-27-5055 at the time of SB A340-27-4171or SB A340-27-5055 embodiment.24 Mo SB A340-27-4171SB A340-27-5055AMM 12-22-27N/A POST 201194(27-4171 or27-5055)END OF SUB-PART 4-3-2

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: NOV 15/12 ALS PART 4 HISTORY FILE PAGE: 1/5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# 1- GENERAL

A340 ALS Part 4 revision 00:

The A340 ALS Part 4 revision 00 is primarily dedicated to transfer the retraction actuator chain

components from the A340 ALS Part 1 into this document. It is also the opportunity to include

the requirements of the following Airworthiness Directives (AD):

− French DGAC Consigne de Navigabilité (CN) 2001-519(B), and

− French DGAC CN 2001-529(B)R1, and

− French DGAC CN 2001-549(B)R1, and

− French DGAC CN F-2002-415(B)R2, and

− French DGAC CN F-2003-141(B), and

− European Aviation Safety Agency (EASA) AD 2006-0158, and

− EASA AD 2007-0308, and

− EASA AD 2008-0026.

A340 ALS Part 4 revision 01:

The A340 ALS Part 4 Revision 01 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

200103). It was also the opportunity to include the requirements of the following French DGAC

Consigne de Navigabilité (CN)/Airworthiness Directives (AD):

− CN F-2003-141(B)R1, and

− AD 2007-0008, and

− AD 2007-0011, and

− AD 2007-0308 (correction for A340-500 WV000’s), and

− AD 2008-0160, and

− AD 2009-0138, and

− AD 2009-0195 (partially for Pitot probe PNR C16195AA).

A340 ALS Part 4 revision 02:

The A340 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 3 activities (Mod

200103 issue 02) and the Variations approved since the revision 01. It was also the opportunity

to include the requirements of the following French DGAC Consigne de Navigabilité

(CN)/Airworthiness Directives (AD):

− CN 2002-553(B), and

− EASA AD 2010-0081 (partially), and

− EASA AD 2010-0193 (paragraph 1.1, 1.2, 2.1, 2.2, 3, 4, 5, 6, 7) and

− EASA AD 2010-0205.

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: NOV 15/12 ALS PART 4 HISTORY FILE PAGE: 2/5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# A340 ALS Part 4 revision 03:

The A340 ALS Part 4 Revision 03 has been primarily produced to introduce new limitations into

ALS Parts 4-2 and 4-3 resulting from the Extended Service Goal (ESG) activities (Mod 202206

issue 01) and the Variations approved since the revision 02.

2- SUMMARY OF CHANGES:

The following summarizes the changes with respect to the previous issue of the A340 ALS Part

4 (revision 03).

New items:

RECORD OF REVISIONS:

None.

SUB-PART 4-0:

− A340 Operational Life:

− Extension of the Operational Life in a ccordance with the Extended Service Goal (ESG)

exercise. The Operational Life is escalated from 100000 FH/20000 FC up to 134000

FH/25000 FC for A340-200 and up to 156000 FH/31000 FC for A340-300, excluding

A340-300 WV027 and A340-200/300, WV050s).

SUB-PART 4-1:

− New illustrations added to reflect the new items introduced in sub-parts 4-2.

SUB-PART 4-2:

− Introduction of new items/part numbers for A340-200/-300

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

953B0000-01,

− T-Gearbox PNR 921A0000-01, PNR 921B0000-01, PNR 921C0000-01, PNR

921D0000-01,

− Pin W1 PNR 201478652,

− Retraction actuator bearing PNR D68397,

− Thrust Reverser Primary Lock PNR 2885000-9, PNR 618700-1003,

− Thrust Reverser Actuator PNR 1608000-4, PNR 1608000-5, PNR 1608000-6, PNR

1608000-7, PNR 618800-1003.

SUB-PART 4-3:

− Introduction of new maintenance tasks:

− 292400- 00001-2-E.

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: NOV 15/12 ALS PART 4 HISTORY FILE PAGE: 3/5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# Amendments:

SUB-PART 4-0:

− The term “Limit Of Validity” is replaced by “Operational Life”.

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

SUB-PART 4-1:

− Figures numbers amended.

SUB-PART 4-2:

− Changes in the limitations of the follow ing items/part numbers fitted to A340-200/-300:

− THSA PNR 47147-500 and PNR 47147-700 have the life limit of 80000 FH/20000 FC

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

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

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

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

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

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

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

− Retraction actuator piston rod: life limit reduced from 20950 LDG to 18000 LDG for

PNR 114256326 and PNR 114256328,

− Retraction actuator pin (Main fitting side) : Life limitation amended for PNR D61686,

− Retraction actuator pin (Airframe Side): Life limitation amended for PNR

F53112357200xx and PNR F53114023200xx fitted to A340-21x series, A340-300

WV00x and WV02x series (excluding WV027).

− Retraction actuator pin (Airframe Side): Life limitation amended for PNR

F53112357204xx, PNR F53114022200xx, and PNR F53120422200xx fitted to A340-

300 WV02x series (excluding WV027).

− Changes in the limitations of the follow ing items/part numbers fitted to A340-500/-600:

− THS Actuator: Life limitation 25 Ye added for PNR 47175-300,

− THS Actuator: Life limitation amended for PNR 47175-300, PNR 47175-500 and PNR

47175-520,

− Retraction actuator piston rod: Life limitation amended for PNR 50-1231002-02,

− Retraction actuator gland: Life limitation amended for PNR 50-1231004-02,

− Retraction actuator piston head: Life limitation amended for PNR 50-1231003-02,

− Retraction actuator cylinder: Life limitation amended for PNR 50-1231001-00,

− Retraction actuator pin (Main fitting side): Life limitation amended for PNR 55-1003283-

00,

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: NOV 15/12 ALS PART 4 HISTORY FILE PAGE: 4/5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# − Rear Center Tank (RCT) liner part numbers have been moved from sub-part 4-2-1 to

sub-part 4-2-2. The part numbers have been amended, i.e.“00” added.

SUB-PART 4-3:

− Task 292400-00001-1-E: Applicability amended.

− Task 275000-00001-3-E: Applicability amended.

Deletions:

SUB-PART 4-0:

− Deletion of paragraph 1.C (2) Specific LOV applicable to A340 landing gear retraction

actuator chain.

SUB-PART 4-1:

− Figures deleted

SUB-PART 4-2:

− The removal of the following items/part numbers fitted to A340-200/-300 (refer to SIL 05-

014 for the Recommended Tracking of components/items):

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

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

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

− Rudder Travel Limitation Unit (RTLU) PNR 343500M00,

− Pedal Travel Limitation Unit (PTLU) PNR 343500M00,

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

PNR SC5300-4,

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

− Back-up yaw damper servo-control PNR 41800831001, PNR 41800831002, PNR

41800831100,

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

SC4800-114,

− Spoiler servo-control in position 1 PNR MZ4339390-12, PNR 1387A0000-02, PNR

1387B0000-02 and PNR 1387C0000-01,

− Spoiler servo-control in positions 2 to 6 PNR MZ4306000-12, PNR 1386A0000-02,

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

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

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

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

“Navigation – Airspeed Pitot Probes – Replacement”),

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

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

# A340 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: NOV 15/12 ALS PART 4 HISTORY FILE PAGE: 5/5

© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. 

# − Indicator Standby Airspeed PNR 64050-868-1,

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

− The removal of the following items/part numbers fitted to A340-500/600:

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

“Navigation – Airspeed Pitot Probes – Replacement”),

− Sensor – Angle Of Attack PNR C16291AA, PNR C19291AB.

SUB-PART 4-3:

− None.