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. 

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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 (including replacements) and associated 

airworthiness limitations within the relevant aircraft systems operational life, applicable 

to aircraft systems susceptible to ageing effects. Such ageing effects could change the 

characteristics leading to an increased potential for failure, which in isolation or in 

combination with one or more other specific failures or events, could result in an unsafe 

condition of the aircraft. 

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© 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 maintenance 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 safety) issues (in-service experience). 

All the maintenance requirements and associated airworthiness limitations indicated in 

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

Aviation Safety Agency (EASA). 

The publication of this document precludes the necessity to publish individual 

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

C. 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

080000 20000 

100000 (3) 20000 

N 134000 (4) 25000 (4) 

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

300 POST 46650 and POST 46651) OR

080000 20000 

100000 (3) 20000 

N 156000 (4) 31000 (4) 

A340-300 POST 46650 and POST 46651 (1) 060000 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). 

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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 are 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. 

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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 inspection level, at least as frequently as 

the inspection threshold and interval quoted in this document. 

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

at component/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. 

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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 

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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: 

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

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

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

Cpi = component/item’s airworthiness limitation in 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 Tri, Caj, Cpj, and Cpi 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 −= ∑ ×

⎥

⎥

⎦

⎤

⎢

⎢

⎣

⎡

⎟

⎟

⎠

⎞

⎜

⎜

⎝

⎛

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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 leakage 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). 

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K. ALS Part 4 airworthiness limitations 

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

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

case of damage/repair. 

L. Production/Repair concessions and Alternative Methods Of Compliance 

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

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

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

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

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

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

requested to contact Airbus for guidance. 

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

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

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

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

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

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

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

solution/AV/AMOC. 

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

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

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

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

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

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

embodied that has not been developed under the Design 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. 

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2. DEFINITIONS

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

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

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

Operator. 

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

cycles and/or landings. 

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

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

its intended function. 

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

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

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

test flights) must be taken into account. 

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

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

service (unless otherwise stated). In considering the 

accumulated time since the initial entry into service, it 

should be noted that Calendar time usage parameter 

cannot be frozen (unless stated for individual 

components/items). 

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

may be needed to cover an uncontrollable or 

exceptional unexpected situation. 

Flight Cycle (FC): A complete 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 exceptional short-term extensions 

from calculations. 

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

coming to a complete stop or performing a “touch and 

go”. 
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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 procurable replacement part is delivered as an 

assembly. 

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

replacement PNR, detail PNR and applicable SB: 

− Messier-Dowty Ltd Service Bulletin number: 

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

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

47487 – ‘growth scallop’), 

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

− Messier-Dowty SA Service Bulletin number: 

− D23285-32-040 (nose landing gear). 

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 indication is quoted on the same line/block of 

lines as the PNR. 

C. Life limitation applicability 

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

sub-part 4-2), according to: 

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

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

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

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

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 

 ALL All A340 aircraft. 

 A340-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 

All aircraft POST MOD nnnnn (at least with mod proposal 

no. Sxxxxx embodied). 

 POST nnnnn 

POST mmmmm 

All aircraft POST MOD nnnnn and POST MOD mmmmm. 

i.e. 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 for components/items listed in sub-part 4-3. 

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

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

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

objectives declared at Type Certification. 

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

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

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

escalation.

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

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

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

be granted without consultation with that office. 

(1) Controlled by Flight Hours (FH) 

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

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

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

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

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

LanDinGs. 

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

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

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

limitations quoted in terms of Months. 

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

may exceptionally be granted. 

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

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

Programme. 

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

individual ADs. These items will 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. 

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

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

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

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

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

N 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-2 SYSTEMS LIFE-LIMITED COMPONENTS

1. Sub-part 4-2-1 LIFE LIMITS

A. A340-200/-300 SERIES 

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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

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

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

ATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02)

 Pressure reducer E62691-00 N/A N/A 20 Ye 

ATA 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-cont

9CS2, 10CS2 for outboard servo-controls (active and damping). 

 (2) Embodiment of MOD 45512/SB A340-27-4062 introduces different PNR. MOD 45512 factory embodied on MSN 228 and subsequent. 

Inboard aileron servo-control (1) (2) 

3337457-22 9000 N/A N/A X X 

3337457-23 9000 N/A N/A X X 

3337457-26 27000 N/A N/A X X 3337457-27 27000 N/A N/A X X 3337457-30 65600 16400 N/A X X 

 3337457-31 65600 16400 N/A X X 

3337457-35 65600 16400 N/A X X 

3337457-36 65600 16400 N/A X X 3337457-37 65600 16400 N/A X X 3337457-38 65600 16400 N/A X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

Outboard aileron servo-control (1) (2) 

3337458-30 65600 16400 N/A X X 

3337458-31 65600 16400 N/A X X 

3337458-35 65600 16400 N/A X X 3337458-36 65600 16400 N/A X X 3337458-37 65600 16400 N/A X X 3337458-38 65600 16400 N/A X X 

N ATA 27-23 FLIGHT CONTROL – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION (FIG. 04)N (1) FIN 24CS. N (2) FIN 36CS. N Rudder Travel Limitation Unit (RTLU) (1) 341400M02 100000 33000 N/A X X X N Pedal Travel Limitation Unit (PTLU) (2) 341400M02 100000 33000 N/A X X X R ATA 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 X X X 

SC4800-3 N/A N/A 31-Aug-04 X X X SC4800-4 N/A N/A 31-Aug-04 X X X SC4800-6 N/A N/A 31-Aug-04 X X X SC4800-7 N/A N/A 31-Aug-04 X X X 

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

SC4800-8 N/A N/A 31-Aug-04 X X X SC4800-9 N/A N/A 30-Jun-08 X X X 

 .../... SC4800-10 N/A N/A 30-Jun-08 X X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

 Elevator servo-control (1) SC4800-11 N/A N/A 30-Jun-08 X X X 

SC4800-72 N/A N/A 30-Jun-08 X X X SC4800-73 N/A N/A 30-Jun-08 X X X SC4800-92 N/A N/A 30-Jun-08 X X X SC4800-93 N/A N/A 30-Jun-08 X X X 

SC4800-103 N/A N/A 30-Jun-08 X X X SC4800-113 N/A N/A 30-Jun-08 X X X 

R ATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06) 

(1) Embodiment of MOD 45906/SB A340-27-4059 and MOD 49591/SB A340-27-4099 introduces different PNR. MOD 45906 is factory 

subsequent. 

 (2) Embodiment of MOD 49590/SB A340-27-4089 introduces different PNR. MOD 49590 is factory embodied on MSN 429, 433, 435 and  THS Actuator 47147-200 N/A N/A 31-Jul-04 

47147-210 N/A N/A 31-Jul-04 47147-213 N/A N/A 31-Jul-04 47147-300 N/A N/A 31-Jul-04 47147-303 N/A N/A 31-Jul-04 47147-350 N/A N/A 31-Jul-04 204 X (1) 47147-400 N/A N/A 31-Jul-04 X (1) X (1) 

N 47147-500 80000 20000 N/A X X X N 47147-700 80000 20000 N/A X X X 

47172 N/A N/A 31-Dec-03 X (2) X (2) 

R ATA 27-54 FLIGHT CONTROL – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 07 & 08)  (1) Embodiment of MOD 50044 (associated to SB A340-27-4111) introduces new PNR.  Flap Rotary Actuator – Type A 697510004 (1) N/A 18000 12 Ye X X X 

697510005 (1) N/A 18000 12 Ye X X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

 Flap Rotary Actuator – Type B 697511004 (1) N/A 18000 12 Ye X X X 

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

N Flap Power Control Unit (PCU) 953A0000-04 N/A N/A 31-Oct-14 X X X N 953A0000-05 N/A N/A 31-Oct-14 X X X N 953B0000-01 N/A N/A 31-Oct-14 X X X R ATA 27-64 FLIGHT CONTROL – SPOILER HYDRAULIC ACTUATION (FIG. 09)  (1) Not applicable to aircraft POST MOD 44670 and delivered after 13-Jan-2006. Embodiment of MOD 51413/SB A340-27-4139 introduce (2) FIN 13CS1 and 13CS2.  (3) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1 and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2. 

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

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

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

(6) Applicable to aircraft up to and including MSN 598. 

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

accordance 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

SB 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 since aircraft initial entry into service. (c) On third circuit no later than 05-Mar-2010. 

− If 2 hydraulic circuits are affected: 

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

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

 (7) Embodiment of MOD 48956/SB A340-27-4100 introduces different PNR. MOD 48956 is factory embodied on MSN 385, MSN 446 and 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

Spoiler servo-control position 1 (2) 

MZ4339390-01X (6) N/A N/A 05-Mar-10 X X X MZ4339390-02X (6) N/A N/A 05-Mar-10 X X X 

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

S4-3000470 

(1)(4)(5) N/A 15000 N/A X X X 

S4-3000470-01 

(1)(4)(5) N/A 15000 N/A X X X 

S4-3000470-02 

(1)(4)(5) N/A 15000 N/A X X X 

S4-3000470-03 

(1)(4)(5) N/A 15000 N/A X X X 

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

Spoiler servo-control positions 2-6 (3) 

MZ4306000-01X (6) N/A N/A 05-Mar-10 X X X MZ4306000-02X (6) N/A N/A 05-Mar-10 X X X MZ4306000-10X (6) N/A N/A 05-Mar-10 X X X 

 S4-3000460 

(1)(4)(5) N/A 14000 N/A X X X 

S4-3000460-01 

(1)(4)(5) N/A 14000 N/A X X X 

S4-3000460-02 

(1)(4)(5) N/A 14000 N/A X X X 

S4-3000460-03 

(1)(4)(5) N/A 14000 N/A X X X 

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

1386B0000-01 (7) N/A N/A 31-Dec-03 X X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

N ATA 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) 921A0000-01 N/A N/A 31-Oct-14 X X X N 921B0000-01 (1) N/A 32000 N/A X X X N 921C0000-01 (1) N/A 24000 N/A X X X N 921D0000-01 (1) N/A 24000 N/A X X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16) R MAIN 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. Embodim

45031/SB A340-32-4092 introduces a different PNR. MOD 43863 factory embodied on original landing gear of A340-200 MSN 151 

MSN 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 applicable to SNR 003WHM (only this SNR exists).  (5) For this PNR, note (1) is applicable to SNR 0031WHM (only this SNR exists). 

(6) For this PNR, applicable to the other SNRs. See notes (2) and (3). Embodiment of MOD 43863 or MOD 45031/SB A340-32-4092 intro

43863 factory embodied on original landing gear of A340-200 MSN 151 and subsequent, excluding MSN 204. MOD 43863 factory e

gear of A340-300 MSN 115, 125, 133, 134, 145 and 146. 

 (7) Embodiment of MOD 46903/SB A340-32-4135 introduces a different PNR. MOD 46903 factory embodied on original landing gear of M (8) Embodiment of MOD 46904/SB A340-32-4134 introduces a different PNR. MOD 46904 factory embodied on original landing gear of M (9) Embodiment of MOD 48066/SB A340-32-4164 introduces a different PNR. MOD 48066 factory embodied on original landing gear of M (10) Life limit is the later of 900 aircraft FH counted from 08-Jul-2009 or the accumulation of 11150 total LDG since initial entry into service  (11) Life limit is the earlier of the 10-year calendar limit or the limitation deduced from note (10).  (12) Embodiment of MOD 58527/SB A340-32-4273 introduces a different PNR.  Pin W 201275796 (7) N/A 20000 10 Ye X X -313  Retraction link (LH) 201275317 (9) N/A 35200 36 Mo X X -313 

201489311 (12) N/A 8400 N/A X X -313 

 Retraction link (RH) 201275318 (9) N/A 35200 36 Mo X X -313 

201489312 (12) N/A 8400 N/A X X -313 

 Pin W1 201275673 (7)(11) N/A (10) 10 Ye X X -313 

201478614 N/A (10) N/A X X -313 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

 Retraction bracket (LH) 201428305 N/A (1) N/A excl. 204 X 

201428307 N/A (1) N/A excl. 204 X 201428318 N/A (1) N/A excl. 204 X 

201428323 N/A (1) N/A excl. 204 X 

201428331 (2) N/A (1) N/A excl. 204 X 201428331 (6) N/A 9000 N/A excl. 204 X 

201428333 N/A (1) N/A excl. 204 X 201428335 N/A (1) N/A excl. 204 X 

201428338 (4) N/A (1) N/A excl. 204 X 

201428351 N/A 19800 N/A X X -313 201428378 N/A 19800 N/A X X -313 201428380 N/A 19800 N/A excl. 204 X 201428382 N/A 19800 N/A excl. 204 X 201428384 N/A 19800 N/A excl. 204 X 201478303 N/A 19800 N/A excl. 204 X 201478305 N/A 19800 N/A excl. 204 X 201478307 N/A 19800 N/A excl. 204 X 

 Retraction bracket (RH) 201428306 N/A (1) N/A excl. 204 X 

201428308 N/A (1) N/A excl. 204 X 201428319 N/A (1) N/A excl. 204 X 201428324 N/A (1) N/A excl. 204 X 

201428332 (3) N/A (1) N/A excl. 204 X 201428332 (6) N/A 9000 N/A excl. 204 X 

 .../... 201428334 N/A (1) N/A excl. 204 X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

 Retraction bracket (RH) 201428336 N/A (1) N/A excl. 204 X 

201428339 (5) N/A (1) N/A excl. 204 X 

201428352 N/A 19800 N/A X X -313 201428379 N/A 19800 N/A X X -313 

201428381 N/A 19800 N/A excl. 204 X 201428383 N/A 19800 N/A excl. 204 X 201428385 N/A 19800 N/A excl. 204 X 201478304 N/A 19800 N/A excl. 204 X 201478306 N/A 19800 N/A excl. 204 X 201478308 N/A 19800 N/A excl. 204 X 

Pin W2 

201275667 (8) 

N/A 4500 5 Ye excl. 204 X 

 N/A 9400 5 Ye 204 -313 

 Pin P 201275602 (7) N/A 20000 10 Ye X X -313 R RETRACTION 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 

114256321 N/A 8080 31-Dec-07 X X -313 

114256323 N/A 5500 N/A X X -313 

R 114256326 N/A 18000 N/A X X -313 R 114256328 N/A 18000 N/A X X -313  Retraction actuator gland 50-2113004-00 (1) N/A 27790 N/A  Retraction actuator cylinder 114256310 N/A 22900 N/A X X -313 

114256320 N/A 22900 N/A X X -313 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLICABILNomenclature Part Number FH FC Cal. A340-21x 

A340-31

D R 

WV00x WV027 Ot

ATA 35-13-00 OXYGEN – CREW OXYGEN – CONTROL AND INDICATING (FIG. 24)

 Pressure switch CMK80-01 80000 N/A 20 Ye X X X R ATA 35-23-00 OXYGEN – PASSENGER OXYGEN (GAZEOUS) – CONTROL AND INDICATING (FIG. 25) Quantity calculation control unit E69027 80000 N/A 20 Ye X X X N ATA 78-31-00 THRUST REVERSER CONTROL AND INDICATING (FIG. 27 & 28) N N 

(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-F

2010-0044 [Correction: 25 March 2010]. 

N N 

(2) Not authorised in position FIN 5003EG2, 5003EG3, 5003EG4 for engine 1 and FIN 5003EG1, 5003EG2, 5003EG3 for engine 4 o

Refer to EASA AD 2010-0044 [Correction: 25 March 2010]. 

N N 

(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-F

2010-0044 [Correction: 25 March 2010]. 

N N 

(4) Not authorised in position FIN 5002EG2, 5002EG3, 5002EG4 for engine 1 and FIN 5002EG1, 5002EG2, 5002EG3 for engine 4 o

Refer to EASA AD 2010-0044 [Correction: 25 March 2010]. 

N Thrust reverser primary lock 2885000-9 (1) (2) N/A 20000 N/A X X X N 618700-1003 N/A 20000 N/A X X X N Thrust reverser actuator 1608000-4 (3) (4) N/A 20000 N/A X X X N 1608000-5 (3) (4) N/A 20000 N/A X X X N 1608000-6 (3) (4) N/A 20000 N/A X X X N 1608000-7 (3) (4) N/A 20000 N/A X X X N 618800-1003 N/A 20000 N/A X X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

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

B. A340-500/-600 SERIES 

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 APPLIC

Nomenclature Part Number FH FC Cal. 

A340-54x 

WV00x WV10x W

ATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02) 

 Pressure reducer E62691-00 N/A N/A 20 Ye X X R ATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06) 

(1) Embodiment of SB A340-27-5030 introduces different PNR. 

 THS Actuator 47175-200 (1) N/A 4730 N/A X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-2-1 

 EASA APPROVED 

©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 APPLIC

Nomenclature Part Number FH FC Cal. 

A340-54x 

WV00x WV10x W

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16) R RETRACTION ACTUATOR (FIG. 16) Retraction actuator piston rod 50-1231002-01 N/A 6090 N/A X X R ATA 32-15-00 CENTER LANDING GEAR (FIG. 17 to 19) R RETRACTION ACTUATOR (FIG. 19) (1) The calendar life limit is to be counted from the Date Of Manufacture (DOM) of the part. DOMs are provided in Messier-Dowty Service  Retraction actuator cylinder 50-1104001-00 N/A 7800 N/A X  Retraction actuator piston rod 55-1104003-00 (1) N/A 3000 42 Mo X R ATA 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. DOMs are provided in Messier-Dowty Service  Retraction actuator piston rod 55-1026003-00 (1) N/A 3000 42 Mo X  Retraction actuator cylinder 50-1026001-00 N/A 10300 N/A X D 

END OF SUB-PART 4-2-1 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.2. Sub-part 4-2-2 CURRENT DEMONSTRATED LIVES

A. A340-200/-300 SERIES 

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 APPLICA

Nomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 Ot

ATA 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

servo-controls (active and damping). 

R D R D R 

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

Outboard aileron servo-control (1) 

3337458-59 110000 N/A N/A X X X 

ATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 06)

 (1) Embodiment of MOD 200698/SB A340-27-4170 introduces different PNR. D R 

(2) Embodiment of MOD 58916/SB A340-27-4170 introduces different PNR.

THS Actuator 47172-300 80000 20000 25 Ye X X X 

47172-500 (1) 80000 20000 25 Ye X X X 47172-510 (2) 80000 20000 25 Ye X X X 

47172-520 80000 20000 N/A X X X 47172-530 80000 20000 N/A X X X 

D 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPLICA

Nomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16) R MAIN STRUT AND DRESSINGS (FIG. 12 & 13)  (1) This PNR is common to pin W2 and pin P.  Pin W 201478613 N/A 42800 N/A X X -313 

201489770 N/A 42800 N/A X X -313 

55-2105061-00 N/A 46480 N/A 

 Retraction link (LH) 201489315 N/A 10700 N/A X X -313 

50-2105026-00 N/A 46480 N/A 50-2105224-00 N/A 46480 N/A 

 Retraction link (RH) 201489316 N/A 10700 N/A X X -313 

50-2106026-00 N/A 46480 N/A 50-2106224-00 N/A 46480 N/A 

N Pin W1 201478652 N/A 25179 N/A X X -313 

55-2105060-00 N/A 46480 N/A 

 Retraction bracket (LH) 50-2105027-00 N/A 46480 N/A  Retraction bracket (RH) 50-2106027-00 N/A 46480 N/A  Pin W2 201478615 N/A 42800 N/A X X -313 

201478637 N/A 42800 N/A X X -313 

55-2105059-00 (1) N/A 46480 N/A 

 Pin P 201478612 N/A 42800 N/A X X -313 

55-2105059-00 (1) N/A 46480 N/A 

R COMPLETE SIDE STAY (FIG. 12, 14 & 15) Lock stay actuator pin 201440611 N/A 25000 N/A excl. 204 X 

201457606 N/A 25000 N/A excl. 204 X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPLICA

Nomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

R LOCK STAY ACTUATOR (FIG. 15) Lock stay actuator cylinder 114354600 N/A 25000 N/A excl. 204 X 

201686600 N/A 25000 N/A excl. 204 X 

 Lock stay actuator piston rod 114354605 N/A 25000 N/A excl. 204 X 

201686602 N/A 25000 N/A excl. 204 X 

 Lock stay actuator gland 114354606 N/A 25000 N/A excl. 204 X 

201481611 N/A 25000 N/A excl. 204 X 201481614 N/A 25000 N/A excl. 204 X 

 Lock stay actuator rod end 114354602 N/A 25000 N/A excl. 204 X 

201686601 N/A 25000 N/A excl. 204 X 

R RETRACTION ACTUATOR (FIG. 16) (1) Must be replaced by a new one every time the piston head is removed from the piston rod.  Retraction actuator piston rod 50-2113002-00 N/A 50000 N/A  Retraction actuator gland 114256312 N/A 50000 N/A X X -313 

 114256322 N/A 50000 N/A X X -313 

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

 Retraction actuator piston head 114256308 N/A 50000 N/A X X -313 

114256639 N/A 50000 N/A X X -313 

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

 Retraction actuator insert 114256629 N/A (1) N/A X X -313  Retraction actuator cylinder 50-2113001-00 N/A 50000 N/A 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPLICA

Nomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

R ATA 32-21-00 NOSE LANDING GEAR (FIG. 20 & 21)D R 

(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 X X -313 

R 

F53112357204xx 

N/A 25000 N/A 

N N/A 37500 N/A R 

F53114022200xx 

N/A 25000 N/A 

N D R 

 N/A 37500 N/A 

F53114023200xx N/A 37500 N/A X X -313 

R 

F53120422200xx 

N/A 25000 N/A 

N N/A 37500 N/A R MAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 20 & 21)R Retraction actuator pin 

(Main fitting side) D61686 

N/A 25000 N/A X X 

R N/A 37500 N/A -313 R RETRACTION ACTUATOR (FIG. 21) Retraction actuator eye end D62588 N/A 25000 N/A X X 

N/A 37500 N/A -313 

D62588-1 

N/A 25000 N/A X X N/A 37500 N/A -313 

D67840 

N/A 25000 N/A X X 

N/A 37500 N/A -313 

 Retraction actuator bearing D61950-1 N/A 25000 N/A X X 

N/A 37500 N/A -313 

D61950-10 

N/A 25000 N/A X X 

 .../... N/A 37500 N/A -313 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPLICA

Nomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

 Retraction actuator bearing D67839 N/A 25000 N/A X X 

N/A 37500 N/A -313 

N 

D68397 

N/A 25000 N/A X X 

N N/A 37500 N/A -313  Retraction actuator sliding rod D62328 N/A 25000 N/A X X 

N/A 37500 N/A -313 

D62328-1 

N/A 25000 N/A X X N/A 37500 N/A -313 

D67837 

N/A 25000 N/A X X 

N/A 37500 N/A -313 

 Retraction actuator plug D61952 N/A 25000 N/A X X 

N/A 37500 N/A -313 

D61952-1 

N/A 25000 N/A X X N/A 37500 N/A -313 

D67838 

N/A 25000 N/A X X 

N/A 37500 N/A -313 

 Retraction actuator cylinder D62587 N/A 25000 N/A X X 

N/A 37500 N/A -313 

D62587-1 

N/A 25000 N/A X X N/A 37500 N/A -313 

D67836 

N/A 25000 N/A X X 

N/A 37500 N/A -313 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPLICA

Nomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 Ot

 Retraction actuator body D61954 N/A 25000 N/A X X 

N/A 37500 N/A -313 

D61954-10 

N/A 25000 N/A X X 

N/A 37500 N/A -313 

D67876 

N/A 25000 N/A X X 

N/A 37500 N/A -313 

D 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

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

B. A340-500/-600 SERIES 

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 APPL

Nomenclature Part Number FH FC Cal. 

A340-54x 

WV00x WV10x W

R ATA 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 200491 factory embodied on MSN 1102, MSN 1122 aR THS Actuator 47175-300 70000 10000 25 Ye X X R 47175-500 (1) 70000 10000 25 Ye X X R 47175-520 70000 10000 N/A X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPL

Nomenclature Part Number FH LDG Cal. 

A340-54x 

WV00x WV10x W

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 12 to 16) R MAIN STRUT AND DRESSINGS (FIG. 12 & 13) (1) This PNR is common to pin W2 and pin P.  Pin W 55-1205156-03 N/A 20600 N/A X X  Retraction link (LH) 50-1205288-01 N/A 20600 N/A X X  Retraction link (RH) 50-1206288-01 N/A 20600 N/A X X  Pin W1 55-1205154-00 N/A 20600 N/A X X  Retraction bracket (LH) 50-1205007-00 N/A 20600 N/A X X  Retraction bracket (RH) 50-1206007-00 N/A 20600 N/A X X  Pin W2 55-1205151-00 (1) N/A 20600 N/A X X  Pin P 55-1205151-00 (1) N/A 20600 N/A X X R RETRACTION ACTUATOR (FIG. 16) (1) Must be replaced by a new one every time the piston head is removed from the piston rod. R Retraction actuator piston rod 50-1231002-02 N/A 20600 N/A X X R Retraction actuator gland 50-1231004-02 N/A 20600 N/A X X R Retraction actuator piston head 50-1231003-00 N/A 20600 N/A X X  Retraction actuator insert 114256629 N/A (1) N/A X X R Retraction actuator cylinder 50-1231001-00 N/A 20600 N/A X X R ATA 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 

G53323625200xx N/A 16600 N/A X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPL

Nomenclature Part Number FH LDG Cal. 

A340-54x 

WV00x WV10x W

 LEG EQUIPPED (FIG. 17)

R MAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 17 & 19)

Retraction actuator pin (Main fitting side)

55-1105016-00 N/A 13100 N/A X 

55-1105315-00 

N/A 13100 N/A X 

N/A 10300 N/A X 

 COMPLETE DRAG STAY (FIG. 18)Unlock actuator pin (drag stay) 55-1110052-00 N/A 13100 N/A X 

N/A 10300 N/A X 

 LOCK LINK (FIG. 18)Unlock actuator pin (lock link) 55-1110052-00 N/A 13100 N/A X 

N/A 10300 N/A X 

 UNLOCK ACTUATOR (FIG. 18)Unlock actuator rod end 55-1113006-00 N/A 20600 N/A X 

55-1113006-01 N/A 20600 N/A X X 

Unlock actuator piston rod 55-1113003-00 N/A 20600 N/A X 

55-1113003-01 N/A 20600 N/A X X 

Unlock actuator gland 55-1113016-00 N/A 20600 N/A X 

55-1113016-01 N/A 20600 N/A X X 

Unlock actuator cylinder 55-1113001-00 N/A 20600 N/A X 

55-1113001-01 N/A 20600 N/A X X 

R RETRACTION ACTUATOR (FIG. 19)

Retraction actuator cylinder 50-1104001-01 N/A 20600 N/A X X Retraction actuator piston rod 55-1104003-01 N/A 20600 N/A X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPL

Nomenclature Part Number FH LDG Cal. 

A340-54x 

WV00x WV10x W

Retraction actuator piston head 50-1104005-01 N/A 1400 N/A X 

55-1104036-00 N/A 20600 N/A X X 

Retraction actuator piston rod nut 55-1104008-00 N/A 20600 N/A X 

55-1104008-01 N/A 20600 N/A X X 

Retraction actuator bearing 50-1104010-01 N/A 20600 N/A X 

50-1104010-02 N/A 20600 N/A X X 

R ATA 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 F53115982000xx N/A 16600 N/A X X 

R NOSE LANDING GEAR LEG (FIG. 22 & 23)

Retraction actuator pin (Main fitting side)

55-1003014-00 N/A 20600 N/A X 

R 55-1003283-00 N/A 16982 N/A X 

 RETRACTION ACTUATOR (FIG. 23)Retraction actuator piston rod 55-1026003-01 N/A 20600 N/A X X Retraction actuator bearing 55-1026010-01 N/A 20600 N/A X 

55-1026010-02 N/A 20600 N/A X X 

Retraction actuator piston head 55-1026005-01 N/A 1400 N/A X 

55-1026033-00 N/A 20600 N/A X X 

Retraction actuator piston rod nut 55-1026008-00 N/A 20600 N/A X 

55-1026008-01 N/A 20600 N/A X X 

Retraction actuator cylinder 50-1026001-01 N/A 20600 N/A X X 
A340 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©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 APPL

Nomenclature Part Number FH FC Cal. 

A340-54x 

D N 

WV00x WV10x W

ATA 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 aircraft to another. Traceability at aircraft level is authorized. N Rear Center Tank (RCT) liner (1) 

(2) 

F0003076900000 N/A N/A 12 Ye X X 

N F0003077000000 N/A N/A 12 Ye X X N F0003077100000 N/A N/A 12 Ye X X N F0003077200000 N/A N/A 12 Ye X X N F0003077300000 N/A N/A 12 Ye X X N F0003077400000 N/A N/A 12 Ye X X N F0003077500000 N/A N/A 12 Ye X X N F0003077600000 N/A N/A 12 Ye X X 

END OF SUB-PART 4-2-2 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-3-1 

 EASA APPROVED 

©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS

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

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

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

 Task Number Zone Description Threshold Interval R 274400-00001-1-E 311 

312 

THSA – FIG. 06 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the gap at the secondary nut trunnion. This task must be carried out before task 274400-00002-1-E. Note 1: No short-term extension is allowed. Note 2: In computing the life accumulated by 

the THSA for compliance with the threshold, calculations must include flight hours since the initial entry into service or since 17-Aug-2002, whichever occurs later. 

700 FH 

Notes 1 & 2 

700 FH 

Note 1 

SB A340-27-4107 R08

AMM 27-44-51 

44

R 274400-00001-2-E 311 

312 

THSA – FIG. 06 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the Checkable Shear Pins (CSP). This task must be carried out before task 274400-00002-1-E. Note 1: No short-term extension is allowed. Note 2: At the time of SB A340-27-4136 

accomplishment. 

Note 2 700 FH 

Note 1 

SB A340-27-4107 R08

AMM 27-44-51 

44
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-3-1 

 EASA APPROVED 

©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 TASKS LIMITATIONS (Whichever occurs first) REFERENCE LIM

 Task Number Zone Description Threshold Interval R 274400-00001-3-E 311 

312 

THSA – FIG. 06 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the Checkable Shear Pins (CSP). This task must be carried out before task 274400-00002-1-E. Note 1: No short-term extension is allowed. 

700 FH 

Note 1 

700 FH 

Note 1 

SB A340-27-4107 R08

AMM 27-44-51 

44

R 274400-00001-4-E 311 

312 

THSA – FIG. 06 Detailed inspection of the ball screw assembly for integrity of the primary and secondary load path and check the Checkable Shear Pins (CSP). This task must be carried out before task 274400-00002-1-E. Note 1: No short-term extension is allowed. 

700 FH 

Note 1 

700 FH 

Note 1 

SB A340-27-4107 R08

AMM 27-44-51 

4

R 274400-00002-1-E 311 

312 

THSA – FIG. 06 Lubrication of the THSA ball-nut. Note: No short-term extension is allowed. 

1000 FH 

Note 

1000 FH 

Note 

AMM 12-22-27/301 4

444444
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-3-1 

 EASA APPROVED 

©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 TASKS LIMITATIONS (Whichever occurs first) REFERENCE LIM

 Task Number Zone Description Threshold Interval R R R R R R R R R R R 

292400-00001-1-E 633 Ram Air Turbine (RAT) – FIG. 11 

Removal of Ram Air Turbine (RAT) (including actuator, manifold, hydraulic pump, turbinelower gearbox assembly and strut-leg assembly) for overhaul and replace with new or reconditioned units. 

20 Ye 20 Ye AMM 292452-960-801 RAT 

a

m

h

tur

a

an

a

N N N N 

292400-00001-2-E 633 Ram Air Turbine (RAT) – FIG. 11 

Remove RAT (including actuator) for overhaul and replace with new or reconditioned units

20 Ye 20 Ye AMM 292452-960-801 RA

a

END OF SUB-PART 4-3-1 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-3-2 

 EASA APPROVED 

©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 TASKS LIMITATIONS (whichever occurs first) REFERENCE LIM

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

670 

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

they are, to AIRBUS. 

16-Dec-2007

Notes 1 & 2 

N/A SB A340-27-4151 

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

 275000-00001-2-E 570 

670 

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

accordance with SB A340-27-4151. Report inspections results, whatever they are, to AIRBUS. 

 Subsequent repetitive inspections are 

performed in accordance with SB A340-27-4152. 

16-Aug-2009

Notes 1 & 2 

6 Ye 

Notes 1 & 2 

SB A340-27-4151 SB A340-27-4152 

AMM 27-54-56 AMM 27-54-57 
A340 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: NOV 15/12 ALS PART 4-3-2 

 EASA APPROVED 

©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 TASKS LIMITATIONS (whichever occurs first) REFERENCE LIM

 Task Number Zone Description Threshold Interval N N N N N N 

275000-00001-3-E 570 

670 

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

26-Oct-2009 

or 

6 years from 

the date of 

original 

delivery of 

the aircraft, 

whichever 

occurs later. 

Note 

6 Ye 

Note 

SB A340-27-4152 SB A340-27-5040 

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

 275000-00001-4-E 570 

670 

Flaps Lubricate the spline joint between the Input Gear Boxes (IPGB) and the Down Drive Shafts 

(DDS). Lubricate all flap tracks on both wings

24 Mo 24 Mo AMM 12-22-27 

 275000-00001-5-E 570 

670 

Flaps Lubricate the spline joint between the Input Gear Boxes (IPGB) and the Down Drive Shafts 

(DDS). Lubricate all flap tracks on both wings. One-time inspection for corrosion in accordance with SB A340-27-4171 or SB A340-27-5055 at the time of SB A340-27-4171 or SB A340-27-5055 embodiment.

 24 Mo SB A340-27-4171 

SB A340-27-5055 

AMM 12-22-27 

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 accordance 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 following 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 following 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.