AIRWORTHINESS LIMITATIONS SECTION 

REVISION: 02 

A340

ALS Part 4 

- 

Ageing Systems Maintenance 

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

This document and all information contained herein is the sole property of AIRBUS SAS. No 

intellectual property rights are granted by the delivery of this document or the disclosure of its 

content. This document shall not be reproduced or disclosed to a third party (except for the 

purposes of performing the tasks described hereunder and provided that any recipient of such 

document shall comply with the conditions herein) without the express written consent of AIRBUS 

SAS. This document and its content shall not be used for any purpose other than that for which it is 

supplied. 
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

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

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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 2011. All rights reserved. Confidential and proprietary document. 

A340

RECORD OF REVISIONS ROR 

INTRODUCTION 4-0 

ILLUSTRATIONS 4-1 

SYSTEMS LIFE-LIMITED COMPONENTS 4-2 

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 4-3 
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

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

EASA APPROVED 

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

A340

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 

R 

R 

R 

01 

ROR 

4-2 

4-3 

DEC 15/09 N/A 

N 

N 

N 

02 

ROR 

4-2 

4-3 

OCT 12/11 

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

Revision 02 is approved by EASA under reference 10036856. 

REVISION 02 COMPLIANCE TIME:

1. Except as stated in paragraph 3. of this Record Of Revisions (ROR), it is mandatory to 

comply with the maintenance requirements and associated airworthiness limitations defined 

in the sub-part 4-2 and 4-3 of the A340 ALS Part 4 revision 02 from 12-Oct-2012. 

2. From 12-Oct-2011 to 11-Oct-2012, it is mandatory to comply with the maintenance 

requirements and associated airworthiness limitations defined in, either: 

− The sub-part 4-2 and 4-3 of the A340 ALS Part 4 at revision 01, except as stated in 

paragraph 3. of this ROR, 

or, 

− The sub-part 4-2 and 4-3 of the A340 ALS Part 4 at revision 02. 

3. From 12-Oct-2011, it is mandatory to comply with the maintenance requirements and 

associated airworthiness limitations defined in the A340 ALS Part 4 revision 02, for: 

− THSA PNR 47172-520, THSA 47175-520, 

R 

R 

R 

R 

R 

R 

R 

R 

R 
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ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: OCT 12/11 ALS PART 4 PAGE: 2-ROR 

EASA APPROVED 

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

A340

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

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

01, 

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

201428382, PNR 201428384, PNR 201478303, PNR 201478305, and PNR 

201478307, 

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

201428383, PNR 201428385, PNR 201478304, PNR 201478306, and PNR 

201478308, 

− The pitot probe PNR C16195BA, 

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

previous accomplishment date. 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 
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Sub-part 4-0 INTRODUCTION

1. GENERAL

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

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

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

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

agreed with the Authority of the State of aircraft registry. 

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

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

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

Volume II, Part A, Chapter 3. 

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

considering any variation requests. 

A. ALS Part 4 applicability 

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

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

 Aircraft series Aircraft models WV

 

A340-200 

A340-211 000, 001, 002 A340-212 

 A340-213 000, 001, 002, 021 

 

A340-300 

A340-311 000, 001, 002, 003, 004 

 A340-312 000, 001, 002, 003, 004, 029 

 A340-313 000, 001, 002, 003, 004, 020, 021, 023, 024, 

025, 026, 027, 028, 050, 051, 052, 053, 054 

A340-500 A340-541 000, 001, 002, 003, 004, 101, 102, 103 

 A340-542 101, 102, 103 

A340-600 A340-642 000, 001, 101, 102, 103 

 A340-643 101, 102, 103 

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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Failure-finding checks (addressing similar unsafe conditions) with airworthiness 

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

complement the mandatory preventative maintenance requirements (refer also to ALS 

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

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

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

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

Note: Items listed in this ALS Part 4 may originate from: 

− Aircraft Maintenance Manual (AMM) chapter 05 Service Life Limits and 

Maintenance Checks (SLMC) section 05-11-00 Service Life Limits, 

subsequently transferred into the A340 ALS Part 1. 

− Life extension study (Change in LOV). 

− 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. Limit Of Validity (LOV) 

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

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

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

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

clearly defined LOV extension. 

(1) General LOV applicable to A340 systems installations 

Aircraft series 

LOV 

R 

Flight Hours 

(FH) 

Flight Cycles 

(FC) 

A340-200 series OR 080000 20000 

D 100000 (3) 20000 

A340-300 series WV000’s and WV020’s (1) OR 080000 20000 

100000 (3) 20000 

A340-300 WV027 series (2) 060000 30000 

A340-300 series WV050’s 100000 20000 

A340-500 series 100000 16600 

A340-600 series 100000 16600 

(1) Excluding A340-313 model POST MODification (MOD) 46650 and POST 

MOD 46651. 

(2) A340-313 model POST MOD 46650 and POST MOD 46651 only. 
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A340

R 

D 

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

4050. 

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

combination of values extracted from different sets is permitted. 

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

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

LOV. 

(2) Specific LOV applicable to A340 landing gear retraction actuator chain 

Main Landing Gear (MLG) LOV 

Flight Hours Landings 

A340-200/-300 series WV000’s 

 PNR 201252 series (basic) 100000 25000 

A340-200 series WV020’s 

 PNR 201490 series (growth) 100000 25000 

A340-300 series WV020’s & WV050’s 

 PNR 201490 series (growth) 100000 (1) 25000 (1) 

075000 (2) 37500 (2) 

 PNR 10-210 series (enhanced) 125000 25000 

A340-500/-600 series WV000’s & WV100’s 

 PNR 10-120 series 125000 20600 

Center Landing Gear (CLG) LOV 

Flight Hours Landings 

A340-500/-600 series WV000’s 

 PNR 10-110101 & PNR 10-110102 series

 PNR 10-110103 & PNR 10-110104 series 125000 20600 

A340-500/-600 series WV100’s 

 PNR 10-110105 series 125000 20600 

Nose Landing Gear (NLG) LOV 

Flight Hours Landings 

A340-200/-300 series WV000’s 

 PNR D23285 series (basic) 100000 25000 

 PNR D23581 series (reinforced) 100000 25000 

A340-200/-300 series WV020’s & WV050’s 

 PNR D23581 series (reinforced) 100000 (1) 25000 (1) 

075000 (2) 37500 (2) 

A340-500/-600 series WV000’s 

 PNR 10-100101 series 125000 20600 

A340-500/-600 series WV100’s 

 PNR 10-100102 series 125000 20600 

(1) Excluding A340-313 model POST MOD 46650 and POST MOD 46651. 

(2) Model POST MOD 46650 and POST MOD 46651 only. 
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A340

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

(TCDS) N°A.015 issued by the EASA, together with the associated modification 

configuration(s). 

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

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

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

Standard Requirements’). 

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

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

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

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

below: 

− A340-200 series WV000’s and WV021 applications: 

WV000: Basic aircraft. 

WV001: Aircraft POST MOD 41302 or POST SB A340-00-4002. 

WV002: Aircraft POST MOD 44229 or POST SB A340-00-4024. 

WV021: Aircraft POST MOD 44281. 

− A340-300 series WV000’s applications: 

WV000: Basic aircraft. 

WV001: Aircraft POST MOD 41302 or POST SB A340-00-4002. 

WV002: Aircraft POST MOD 44228. 

WV003: Aircraft POST MOD 44102 or POST SB A340-00-4021 or, POST 

MOD 47434 or POST SB A340-00-4027. 

WV004: Aircraft POST MOD 44230 or POST SB A340-00-4007. 

− A340-300 series WV020’s applications: 

WV020: Aircraft POST MOD 43500 or, POST MOD 52693 or POST SB 

A340-00-4033 or, POST MOD 53628 or POST SB A340-00-

4040. 

WV021: Aircraft POST MOD 44135 or POST SB A340-00-4010. 

WV023: Aircraft POST MOD 44625 or POST SB A340-00-4023. 

WV024: Aircraft POST MOD 45738 or POST SB A340-00-4022. 

WV025: Aircraft POST MOD 44791 or POST SB A340-00-4034. 

WV026: Aircraft POST MOD 46613 or POST SB A340-00-4025. 

WV027: Aircraft POST MOD 46650. 

WV028: Aircraft POST MOD 49529. 

WV029: Aircraft POST MOD 53243 or POST SB A340-00-4041. 

− A340-300 series WV050’s applications: 

WV050: Aircraft POST MOD 51808. 

WV051: Aircraft POST MOD 51809. 

WV052: Aircraft POST MOD 51810. 

WV053: Aircraft POST MOD 55566. 

WV054: Aircraft POST MOD 55677. 

R 
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A340

− A340-500 series WV000’s and W100’s applications: 

WV000: Aircraft POST MOD 51000 or, POST MOD 52925 or POST SB 

A340-00-5005. 

WV001: Aircraft POST MOD 51080 or POST SB A340-00-5003. 

WV002: Aircraft POST MOD 50791. 

WV003: Aircraft POST MOD 54237 or POST SB A340-00-5007. 

WV004: Aircraft POST MOD 56719. 

WV101: Aircraft POST MOD 53039. 

WV102: Aircraft POST MOD 54806. 

WV103: Aircraft POST MOD 55642. 

− A340-600 series WV000’s and W100’s applications: 

WV000: Basic aircraft. 

WV001: Aircraft POST MOD 50312 or POST SB A340-00-5001. 

WV101: Aircraft POST MOD 53043. 

WV102: Aircraft POST MOD 54805. 

WV103: Aircraft POST MOD 57713. 

Note 2: - In the ALS Part 4 sub-part 4-2 tables, the column ‘WV027’ applies only to 

aircraft POST MOD 46650 (WV027) and POST MOD 46651 (Short Range 

mission). For aircraft POST MOD 46650 and PRE MOD 46651, refer to 

the column ‘Other WV02x’. 

- Life limitations applicable to A340-313 WV021 also apply to aircraft POST 

MOD 48668 or POST SB A340-00-4037 (A340-313 with triple MTOW 

275/260/218 tons). 

D. ALS Part 3 and ALS Part 4 correlation 

At time of original Type Certification, an appraisal of aircraft systems is carried out 

within the frame of the Systems Safety Assessments. This may identify a need to 

schedule repetitive maintenance tasks within a defined interval so as to maintain the 

required safety objectives for individual failure conditions. A subset of these tasks, the 

majority of which detect latent failures, are identified as Certification Maintenance 

Requirements (CMR). These constitute operational limitations and are mandated 

through their location in the ALS Part 3. 

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

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

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

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

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

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

to the difficulty to define a continued/enhanced inspection program, and whose failure 

could contribute to an unsafe condition of the aircraft. 
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A340

For a given PNR, when more than one set of limitations (FH/FC/Calendar time) is 

published for the same application, it is the Operator/MRO’s responsibility to select the 

appropriate set depending on the aircraft utilisation. Combining the limitations from 

different sets is not permitted. 

Sub-part 4-2-1: Life Limits

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

LOV due to failure during tests and whose failure could result in an unsafe condition of 

the aircraft. 

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

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

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

aircraft. 

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

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

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

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

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

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

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

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

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

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

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

system level failure condition or conditions. 

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

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

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

the inspection threshold and interval quoted in this document. 

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

at component level and aircraft (system) level respectively. 

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

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

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

airworthiness limitation. 

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

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

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

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

N 

N 

N 

N 

R 

R 

R 
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A340

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. 

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: 

R 

R 
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A340

− 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). 

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 

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 LOV of the relevant ALS Part 4 for that 

application must be used. 

Note 1: When using the above formula Tri, Caj, Cpj, and Cpi are expressed in the 

same usage 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 Cp

j Cp

j Ca

1 i Tr = − ∑ ×

⎥

⎥

⎦

⎤

⎢

⎢

⎣

⎡

⎟

⎟

⎠

⎞

⎜

⎜

⎝

⎛

R 

N

N

N 

R 

R

R

R

R 

R 

R 

R 

R 

N

N

N 

R 

R 

R 
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I. Disposal/quarantine action 

When the components/items listed in the sub-parts 4-2 and/or 4-3-1 reach the life 

limitations and/or the LOV, disposal/quarantine action must be taken depending on the 

following categories: 

For component/item listed in sub-part 4-2-1: They must be mutilated beyond repair 

limits to prevent rework to appear to be airworthy. 

Note 1: Some means may 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 LOV. Examples of these means are: 

− Record keeping system, 

− Non-permanent markings, 

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

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

to be airworthy. 

Note: When components/items are removed by way of a systematic replacement, 

they must be mutilated beyond repair limits to prevent rework to appear to be 

airworthy. 

J. Occurrence reporting 

The ICAO Airworthiness manual (Doc. 9760), Volume II, Part B, Chapter 2 indicates: 

The concept of Continuing Airworthiness includes the reporting of defects and 

other significant maintenance and operational information by the Operator to the 

organisation responsible for the Type Design in accordance with the 

requirements of the State of aircraft registry. 

Accountable persons or organizations shall report to the competent authority and 

Airbus, any identified condition of an aircraft or component that has resulted or may 

result in an unsafe condition that hazards seriously the flight safety (Refer to EASA 

Part M.A.202 and Part 145.A.60). This will enable Airbus to issue appropriate service 

instructions to all owners or Operators. 

R 

N 

N 

N 

N

N 

N 

N

N

N

N 

N 

R 

N 

N

N 

R 

N

N

N

N 

N 
AIRWORTHINESS LIMITATIONS SECTION 

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“Hazards 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 organisation identifying the condition to which the report relate (refer to 

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

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. 

N 

N 

N 

N 

N 

N 

N 

R 

R 

N

N 

N 

R

R 

D 

R

R 

R 

R 

R 

R 

R 
AIRWORTHINESS LIMITATIONS SECTION 

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

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

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

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

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

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

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

Certificate EASA.21J.031 (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. For example, Supplemental Type Certificates (STC), which 

have been designed by Airbus Corporate Jet Centre (ACJC) or which have been 

transferred from former Airbus Deutschland, or other entity, under DOA Certificate 

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

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

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). 

N 

N 

R 

R

N

N

N 
AIRWORTHINESS LIMITATIONS SECTION 

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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”. 

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

which the maintenance programme defined in that Part 

ceases to be valid. The applicable LOV are indicated in 

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

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

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

tolerances. 

Threshold: The initial accomplishment of a specific maintenance 

task from the initial entry into service. It may be 

expressed in usage parameters like FH and/or FC 

and/or LDG and/or Calendar time. 

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

does not come to a full stop prior to commencing an 

additional flight. 

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

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

of FC up to threshold inspection or between two 

consecutive inspections. Each “Touch and go” above 

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

inspection or between two consecutive inspections. 

R 

R 
AIRWORTHINESS LIMITATIONS SECTION 

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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 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. 

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). 

R 

R 

R 
AIRWORTHINESS LIMITATIONS SECTION 

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(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. 

(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 
AIRWORTHINESS LIMITATIONS SECTION 

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

(unless otherwise stated). 

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

The limitations must be applied from: 

− The initial entry into service, for the threshold and the LOV, and 

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

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

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

one associated with the inspection method used at last inspection. 

B. ALS sub-part 4-3 layout. 

The maintenance requirements and associated airworthiness limitations are presented 

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

(1) Task Number 

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

Document (MPD) system and is described as follows: 

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

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

the task is assigned a single task number, but both LH and RH zones are indicated 

in "Zone" column. 

The task number comprises 13 digits organised as follows: 

XXXXXX-MEFYY-Z-E 

XXXXXX is ATA 100 task reference. 

M is the selection methodologies used. It will always be “0”. 

E is engine/APU/... manufacturer identification (where applicable, “0” 

is default value). 

F is engine/APU type information when more than one engine from 

the same manufacturer is applicable to the program (where 

applicable, “0” is default value). 

YY is sequential number. 

Z is for technical solution applicable to the same task requirement. 

E is “E” and stands for ASM (i.e. task related to an ageing systems 

function or Enhanced maintenance requirement). 

(2) Zone column 

The zone column defines where the major part of the maintenance task 

requirement is to be carried out on the aircraft. 

R 

R 
AIRWORTHINESS LIMITATIONS SECTION 

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(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. 

(a) PNR 

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

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

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

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

associated modifications), which are published by Airbus. 
AIRWORTHINESS LIMITATIONS SECTION 

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(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.

R 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. 

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. 

R 
AIRWORTHINESS LIMITATIONS SECTION 

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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 

R

R 
AIRWORTHINESS LIMITATIONS SECTION 

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

Sub-part 4-1 ILLUSTRATIONS

Pressure Reducer 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

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

Sub-part 4-1 ILLUSTRATIONS

Pressure Reducer 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

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

Aileron 

Servo-control 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-22-00 – RUDDER TRIM ACTUATION AND ARTIFICIAL FEEL – FIG. 04 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-23-00 – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION – FIG. 05 

Rudder/Pedal 

Limitation Unit 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-24-00 – RUDDER HYDRAULIC ACTUATION – FIG. 06 

Rudder Servo-control 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-26-00 – YAW DAMPER ACTUATION – FIG. 07 

Yaw Damper Actuator 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-26-00 – BACK-UP YAW DAMPER ACTUATION – FIG. 08 

Back-up Yaw Damper Unit 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 09 

Elevator Servo-control 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-44-00 – THS HYDRAULIC ACTUATION – FIG. 10 

THSA 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 11 

Example 

Flap Rotary Actuator 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 12 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 29-24-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 13 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 32-11-00 – MAIN LANDING GEAR – FIG. 14 

(*) Location, item not illustrated 

FORWARD

Pin P (*) 

Retraction 

actuator 

Lock stay 

actuator 

Side Stay 

Assembly 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 32-11-00 – MAIN LANDING GEAR – FIG. 15 

Retraction link

Retraction 

bracket 

Pin W2 

Retraction actuator 

piston rod 

Retraction 

jack fitting 

Pin W 

Pin W1 

Main fitting 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 16 

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A340

ATA 32-11-00 – MAIN LANDING GEAR – FIG. 16 

Side Stay Assembly 

Lock link 

(subassembly) 

Lock stay actuator 

pin (x2) 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

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) 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

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) 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 32-21-00 – NOSE LANDING GEAR – FIG. 19 (A340-200/-300 SERIES) 

Main fitting 

Retraction actuator pin 

(main fitting side) 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

Retraction actuator pin 

(main fitting side) 

Main fitting 

ATA 32-21-00 – NOSE LANDING GEAR – FIG. 20 (A340-500/-600 SERIES) 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 32-31-00 – CENTER LANDING GEAR – FIG. 21 (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) 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

Airframe 

Retraction actuator pin 

(main fitting side) 

Retraction actuator pin 

(airframe side) 

Retraction actuator 

bearing 

Retraction actuator 

eye end 

Retraction actuator 

body 

Retraction actuator 

plug 

Retraction actuator 

sliding rod 

Retraction actuator 

cylinder 

ATA 32-31-00 – NOSE LANDING GEAR – FIG. 22 (A340-200/-300 SERIES) 
AIRWORTHINESS LIMITATIONS SECTION 

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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 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 32-31-00 – MAIN LANDING GEAR – FIG. 24 

Lock stay actuator 

piston rod 

Lock stay actuator 

cylinder 

Lock stay actuator 

rod end 

Lock stay actuator 

gland 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 32-31-00 – MAIN LANDING GEAR – FIG. 25 

Retraction actuator 

piston rod 

Retraction actuator 

insert 

Retraction actuator 

gland 

Retraction actuator 

cylinder 

Retraction actuator 

piston head 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 34-11-00 – NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING – FIG. 26 

Pitot Probe 
AIRWORTHINESS LIMITATIONS SECTION 

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A340

ATA 34-11-00 – NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING – FIG. 27 

Angle of Attack Sensor 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 28 

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

A340

ATA 34-21-00 – NAVIGATION – ALTITUDE AND AIRSPEED STANDBY DATA – FIG. 28 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 29 

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

A340

ATA 34-22-00 – NAVIGATION – ATTITUDE AND HEADING STANDBY DATA – FIG. 29 

Standby Horizon 

Indicator 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 30 

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

A340

ATA 35-13-00 – CREW OXYGEN – CONTROL AND INDICATING – FIG. 30 

Pressure Switch 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 31 

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

A340

ATA 35-23-00 – PAX OXYGEN (GASEOUS) – CONTROL AND INDICATING – FIG. 31 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-1 PAGE: 32 

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

A340

ATA 53-40-00 – REAR FUSELAGE – FIG. 32 

END OF SUB-PART 4-1 

 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

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

D N 

Pressure reducer D41428 N/A N/A 20 Ye X X X ATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02)

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

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

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

Inboard aileron servo-control (1) (2) 

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

D 

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 D 

 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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

Outboard aileron servo-control (1) (2) 

3337458-30 65600 16400 N/A X X 

D 

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 R ATA 27-34 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC ACTUATION (FIG. 09)  (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  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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

R ATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 10) 

(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)  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. 11)  (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  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 R ATA 27-64 FLIGHT CONTROL – SPOILER HYDRAULIC ACTUATION (FIG. 12)  (1) Not applicable to aircraft POST MOD 44670 and delivered after 13-Jan-2006. Embodiment of MOD 51413/SB A340-27-4139 introdu (2) FIN 13CS1 and 13CS2.  (3) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1 and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2.  .../... 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

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

by 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. R R 

(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. 

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

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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

N Spoiler servo-control 

position 1 (2) 

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

N 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 

N 1386A0000-01 (7) N/A N/A 31-Dec-03 X X X N 1386B0000-01 (7) N/A N/A 31-Dec-03 X X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25) R MAIN STRUT AND DRESSINGS (FIG. 14 & 15)  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 15

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 

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

landing 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  (8) Embodiment of MOD 46904/SB A340-32-4134 introduces a different PNR. MOD 46904 factory embodied on original landing gear of  (9) Embodiment of MOD 48066/SB A340-32-4164 introduces a different PNR. MOD 48066 factory embodied on original landing gear of  (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 servic (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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

 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 R 201428351 N/A 19800 N/A X X -313 R 201428378 N/A 19800 N/A X X -313 N 201428380 N/A 19800 N/A excl. 204 X N 201428382 N/A 19800 N/A excl. 204 X N 201428384 N/A 19800 N/A excl. 204 X N 201478303 N/A 19800 N/A excl. 204 X N 201478305 N/A 19800 N/A excl. 204 X N 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  .../... 201428336 N/A (1) N/A excl. 204 X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

 Retraction bracket (RH) 201428339 (5) N/A (1) N/A excl. 204 X R 201428352 N/A 19800 N/A X X -313 R 201428379 N/A 19800 N/A X X -313 N 201428381 N/A 19800 N/A excl. 204 X N 201428383 N/A 19800 N/A excl. 204 X N 201428385 N/A 19800 N/A excl. 204 X N 201478304 N/A 19800 N/A excl. 204 X N 201478306 N/A 19800 N/A excl. 204 X N 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. 25)N (1) Embodiment of MOD 200837/SB A340-32-4284 introduces a different PNR. R Retraction actuator piston rod 114256309 N/A 8080 31-Dec-07 X X -313 R 114256321 N/A 8080 31-Dec-07 X X -313 N 114256323 N/A 5500 N/A X X -313  114256326 N/A 20950 N/A X X -313  114256328 N/A 20950 N/A X X -313 N 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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 APPLICABINomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

R ATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 26) R Pitot Probe C16195AA N/A N/A 07-Jan-10 X X X R ATA 35-13-00 OXYGEN – CREW OXYGEN – CONTROL AND INDICATING (FIG. 30) 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. 31) Quantity calculation control unit E69027 80000 N/A 20 Ye X X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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

N ATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02) N 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. 10) N (1) Embodiment of SB A340-27-5030 introduces different PNR. R THS Actuator 47175-200 (1) N/A 4730 N/A X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 LDG Cal. 

A340-54x 

WV00x WV10x W

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25) R RETRACTION ACTUATOR (FIG. 25) Retraction actuator piston rod 50-1231002-01 N/A 6090 N/A X X R ATA 32-15-00 CENTER LANDING GEAR (FIG. 17, 18 & 21) R RETRACTION ACTUATOR (FIG. 21) (1) The calendar life limit is to be counted from the Date Of Manufacture (DOM) of the part. DOMs are provided in Messier-Dowty Servic 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. 20 & 23) R 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 Servic 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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-1  EASA APPROVED 

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

A340

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 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 26) R Pitot Probe C16195AA N/A N/A 07-Jan-10 X X N ATA 53-40-00 REAR FUSELAGE (FIG. 32) 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) 

F00030769000 N/A N/A 12 Ye X X 

N F00030770000 N/A N/A 12 Ye X X N F00030771000 N/A N/A 12 Ye X X N F00030772000 N/A N/A 12 Ye X X N F00030773000 N/A N/A 12 Ye X X N F00030774000 N/A N/A 12 Ye X X N F00030775000 N/A N/A 12 Ye X X N F00030776000 N/A N/A 12 Ye X X 

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

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

R 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 Inboard aileron servo-control 

(1) 

3337457-59 N/A N/A N/A X X X 

R 3337457-60 N/A N/A N/A X X X  C38661-002 80000 20000 N/A X X X R Outboard aileron servo-control 

(1) 

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

R 3337458-60 N/A N/A N/A X X X  C38657-002 80000 20000 N/A X X X R ATA 27-22 FLIGHT CONTROL – RUDDER TRIM ACTUATION AND ARTIFICIAL FEEL (FIG. 04)N (1) Installation not authorised on A340-31x WV05x.R Rudder Trim Actuator (RTA) 6197-1 90000 N/A N/A X X X R 6197-2 90000 N/A N/A X X X 

ATA 27-23 FLIGHT CONTROL – RUDDER AND PEDAL TRAVEL LIMITING ACTUATION (FIG. 05)

N (1) Installation not authorised on A340-31x WV05x.R Rudder Travel Limitation Unit 

(RTLU) 

341400M02 90000 N/A N/A X X X 

R 343500M00 90000 N/A N/A X X X R Pedal Travel Limitation Unit 

(PTLU) 

341400M02 90000 N/A N/A X X X 

R 343500M00 90000 N/A N/A X X X 

R 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

R ATA 27-24 FLIGHT CONTROL – RUDDER HYDRAULIC ACTUATION (FIG. 06)N (1) Installation not authorised on A340-31x WV05x.R Rudder servo-control SC5300 N/A N/A N/A X X X R SC5300-1 N/A N/A N/A X X X R SC5300-2 N/A N/A N/A X X X R SC5300-3 N/A N/A N/A X X X R SC5300-4 N/A N/A N/A X X X R ATA 27-26 FLIGHT CONTROL – YAW DAMPER ACTUATION (FIG. 07 & 08)N (1) Installation not authorised on A340-31x WV05x.R Yaw damper servo-control SC4710 N/A N/A N/A X X X R SC4710-1 N/A N/A N/A X X X R Back-up Yaw Damper Unit 

(BYDU) 

41800831001 N/A N/A N/A X X X 

R 41800831002 N/A N/A N/A X X X R 41800831100 N/A N/A N/A X X X R ATA 27-34 FLIGHT CONTROL – ELEVATOR AND HYDRAULIC ACTUATION (FIG. 09) (1) Applicable to elevator servo-controls installed in positions FIN 2CS1, 2CS2, 3CS1, and 3CS2 (in active and damping modes).R Elevator servo-controls (1) SC4800-74 N/A N/A N/A X X X R SC4800-94 N/A N/A N/A X X X R SC4800-104 N/A N/A N/A X X X R SC4800-114 N/A N/A N/A X X X R D N 

ATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 10)(1) Embodiment of MOD 200698/SB A340-27-4170 introduces different PNR. 

N (2) Embodiment of MOD 58916/SB A340-27-4170 introduces different PNR. R THS Actuator 47147-500 80000 20000 N/A X X X R .../... 47147-700 80000 20000 N/A X X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

 THS Actuator 47172-300 80000 20000 N/A X X X R 47172-500 (1) 80000 20000 25 Ye X X X R 47172-510 (2) 80000 20000 25 Ye X X X N 47172-520 80000 20000 N/A X X X N 47172-530 80000 20000 N/A X X X R D R D R 

ATA 27-64 FLIGHT CONTROL – SPOILER HYDRAULIC ACTUATION (FIG. 12)Spoiler servo-control positions 1 

1387A0000-02 N/A N/A N/A X X X 

1387B0000-02 N/A N/A N/A X X X 

R 1387C0000-01 N/A N/A N/A X X X R D R R 

 MZ4339390-12 N/A N/A N/A X X X Spoiler servo-control positions 2 to 6 

1386A0000-02 N/A N/A N/A X X X 

1386B0000-02 N/A N/A N/A X X X 

R 1386C0000-01 N/A N/A N/A X X X R MZ4306000-12 N/A N/A N/A X X X N ATA 29-24 HYDRAULIC POWER – GREEN AUXILIARY HYDRAULIC POWER (FIG. 13)N Ram Air Turbine (RAT) 766351 N/A N/A N/A X X X N 768084 N/A N/A N/A X X X N 770379 N/A N/A N/A X X X N 770952 N/A N/A N/A X X X N 770952A N/A N/A N/A X X X N 770952B N/A N/A N/A X X X N 1702934 N/A N/A N/A X X X N 1702934A N/A N/A N/A X X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25)R MAIN STRUT AND DRESSINGS (FIG. 14 & 15) (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 R 55-2105061-00 N/A 46480 N/A  Retraction link (LH) 201489315 N/A 10700 N/A X X -313 R 50-2105026-00 N/A 46480 N/A R 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 R 50-2106224-00 N/A 46480 N/A R D R D R 

Pin W1 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 R 55-2105059-00 (1) N/A 46480 N/A  Pin P 201478612 N/A 42800 N/A X X -313 R 55-2105059-00 (1) N/A 46480 N/A R COMPLETE SIDE STAY (FIG. 14, 16 & 24) Lock stay actuator pin 201440611 N/A 25000 N/A excl. 204 X  201457606 N/A 25000 N/A excl. 204 X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2 

 EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

R LOCK STAY ACTUATOR (FIG. 24) 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. 25) (1) Must be replaced by a new one every time the piston head is removed from the piston rod. R Retraction actuator piston rod 50-2113002-00 N/A 50000 N/A  Retraction actuator gland 114256312 N/A 50000 N/A X X -313 D N 

 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 

R 50-2113003-00 N/A 50000 N/A  Retraction actuator insert 114256629 N/A (1) N/A X X -313 R Retraction actuator cylinder 50-2113001-00 N/A 50000 N/A R ATA 32-21-00 NOSE LANDING GEAR (FIG. 19 & 22) (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 25000 N/A X X 

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

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

Retraction actuator pin (Airframe side) (1) 

F53112357204xx N/A 25000 N/A 

 F53114022200xx N/A 25000 N/A 

F53114023200xx 

N/A 25000 N/A X X 

 N/A 37500 N/A -313  F53120422200xx N/A 25000 N/A R MAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 22)

Retraction actuator pin (Main fitting side) D61686 

100000 25000 N/A X X 

 75000 37500 N/A -313 R RETRACTION ACTUATOR (FIG. 22) 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 

D67839 

N/A 25000 N/A X X 

 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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH LDG Cal. A340-21x 

A340-31

WV00x WV027 O

 Retraction actuator sliding rod 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  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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APPLICANomenclature Part Number FH FC Cal. A340-21x 

A340-31

WV00x WV027 O

R ATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 26 & 27) N (1) Not authorised at the position 01 and 03 on aircraft after 07-Jan-2010. R Pitot Probe C16195BA (1) 90000 48000 N/A X X X R Sensor – Angle Of Attack 45150320 90000 48000 N/A X X X R C16291AA 90000 48000 N/A X X X N C16291AB 90000 48000 N/A X X X R ATA 34-21-00 NAVIGATION – ALTITUDE AND AIRSPEED STANDBY DATA (FIG. 28) R Altimeter Standby 64141-582-1 N/A N/A N/A X X X R 64141-590-1 N/A N/A N/A X X X R Indicator Standby Airspeed 64050-868-1 N/A N/A N/A X X X R ATA 34-22-00 NAVIGATION – ATTITUDE AND HEADING STANDBY DATA (FIG. 29) R Indicator Standby Horizon 501-1568-34 N/A N/A N/A X X X R H321BHM1 N/A N/A N/A X X X R H341BVM N/A N/A N/A X X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APP

Nomenclature Part Number FH FC Cal. 

A340-54x 

WV00x WV10x W

R D N 

ATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS) HYDRAULIC ACTUATION (FIG. 10) 

(1) Embodiment of MOD 200491/SB A340-27-5054 introduces different PNR. MOD 200491 factory embodied on MSN 1102, MSN 1122 

R THS Actuator 47175-300 50000 10000 N/A X X R 47175-500 (1) 50000 10000 25 Ye X X N 47175-520 50000 10000 N/A X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APP

Nomenclature Part Number FH LDG Cal. 

A340-54x 

WV00x WV10x W

R ATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25) R MAIN STRUT AND DRESSINGS (FIG. 14 & 15) (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. 25) (1) Must be replaced by a new one every time the piston head is removed from the piston rod.  Retraction actuator piston rod 50-1231002-02 N/A 10000 N/A X X  Retraction actuator gland 50-1231004-02 N/A 10000 N/A X X  Retraction actuator piston head 50-1231003-00 N/A 10000 N/A X X  Retraction actuator insert 114256629 N/A (1) N/A X X  Retraction actuator cylinder 50-1231001-00 N/A 10000 N/A X X R ATA 32-15-00 CENTER LANDING GEAR (FIG. 17, 18 & 21) (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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APP

Nomenclature Part Number FH LDG Cal. 

A340-54x 

WV00x WV10x W

R LEG EQUIPPED (FIG. 17)R MAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 17 & 21)

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 R COMPLETE DRAG STAY (FIG. 18 & 21) Unlock actuator pin (drag stay) 55-1110052-00 N/A 13100 N/A X  N/A 10300 N/A X R LOCK LINK (FIG. 18) Unlock actuator pin (lock link) 55-1110052-00 N/A 13100 N/A X  N/A 10300 N/A X R 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. 21) 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  Retraction actuator piston head 50-1104005-01 N/A 1400 N/A X  55-1104036-00 N/A 20600 N/A X X 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

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 APP

Nomenclature Part Number FH LDG Cal. 

A340-54x 

WV00x WV10x W

 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. 20 & 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. 20 & 23)

Retraction actuator pin (Main fitting side) 

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

 55-1003283-00 N/A 6000 N/A X R 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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-2-2  EASA APPROVED 

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

A340

N Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3. N N 

(*) Whichever occurs first. Explanation notes are located under the assy title. LIFE LIMITATIONS (*) LIFE LIMITATIONS APP

N 

Nomenclature Part Number FH FC Cal. 

A340-54x 

N WV00x WV10x WN ATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 26 & 27) N (1) Not authorised at the position 01 and 03 on aircraft after 07-Jan-2010. N Pitot probe C16195BA (1) 90000 48000 N/A X X N Sensor – Angle Of Attack C16291AA 90000 48000 N/A X X N C16291AB 90000 48000 N/A X X 

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

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

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

A340

Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS

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

N 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. 10 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 

4747

R N N 

274400-00001-2-E 311 

312 

THSA – FIG. 10 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 

4747
AIRWORTHINESS LIMITATIONS SECTION 

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

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

A340

N 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 N N 

274400-00001-3-E 311 

312 

THSA – FIG. 10 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 

4747

R N N 

274400-00001-4-E 311 

312 

THSA – FIG. 10 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 

47

R N N 

274400-00002-1-E 311 

312 

THSA – FIG. 10 Lubrication of the THSA ball-nut. Note: No short-term extension is allowed. 

1000 FH 

Note 

1000 FH 

Note 

AMM 12-22-27/301 47

474747474747
AIRWORTHINESS LIMITATIONS SECTION 

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

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

A340

N 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 

2924000-00001-1-E 633 Auxiliary Hydraulic Power – FIG. 13 

Removal of Ram Air Turbine (RAT) for overhaul. Fit a RAT that has not accumulated 20 Ye since last overhaul. 

20 Ye 20 Ye AMM 292452/401 

CMM 29-21-31 

77

1

1

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

ISSUE: OCT 12/11 ALS PART 4-3-2  EASA APPROVED 

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

A340

Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVEL

N 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 

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 

N N N N R R R 

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 
AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: OCT 12/11 ALS PART 4-3-2  EASA APPROVED 

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

A340

N 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 

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 

N N N N N 

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 

Note 

24 Mo 

Note 

AMM 12-22-27 

N N N N N N N N N 

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 
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: OCT 12/11 ALS PART 4 HISTORY FILE PAGE: 1/5 

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

A340

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.
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: OCT 12/11 ALS PART 4 HISTORY FILE PAGE: 2/5 

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

A340

2- SUMMARY OF CHANGES:

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

4 (revision 01). 

New items: 

RECORD OF REVISIONS:

None. 

SUB-PART 4-0:

− A340 Limit Of Validity: 

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

The LOV is escalated from 80000 FH/20000 FC up to 100000 FH/20000 FC for A340-

200 and A340-300, excluding A340-300 WV027. Associated rules included. 

− Transfer of components/items between aircraft applications. 

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

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

is added to paragraph 1H. 

SUB-PART 4-1:

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

SUB-PART 4-2:

− Introduction of new items for A340-500/-600 

− Pressure reducer PNR E62691-00, 

− Pitot probe PNR C16195BA, 

− Angle Of Attack sensor PNR C16291AA, PNR C16291AB, 

− Rear Center Tank (RCT) liner PNR F00030769000, PNR F00030770000, PNR 

F00030771000, PNR F00030772000, PNR F00030773000, PNR F00030774000, PNR 

F00030775000, PNR F00030776000, 

− Introduction of new PNR of: 

− THSA PNR 47172-520, PNR 47172-530 fitted to A340-200/-300, 

− THSA PNR 47175-520 fitted to A340-500/-600, 

− Angle Of Attack sensor PNR C16291AB fitted to A340-200/-300, 

− Retraction actuator gland PNR 50-2113004-01. 
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: OCT 12/11 ALS PART 4 HISTORY FILE PAGE: 3/5 

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A340

SUB-PART 4-3:

− Introduction of new maintenance tasks: 

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

Amendments: 

SUB-PART 4-2:

− Figures numbers amended for each components/items. 

− Cancellation of the limitation of the following items: 

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

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

− Rudder Trim Actuator (RTA) PNR 6197-1, PNR 6197-2 (Cancellation of the limitation in 

FC), 

− Rudder Travel Limitation Unit (RTLU) PNR 341400M02, PNR 343500M00 

(Cancellation of the limitation in FC), 

− Pedal Travel Limitation Unit (PTLU) PNR 341400M02, PNR 343500M00 (Cancellation 

of the limitation in FC), 

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

and 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, 

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

− Indicator Standby Airspeed PNR 64050-868-1, 

− Compass Standby PNR KCA0105W, 

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

− Changes in the limitations of the following items: 

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

A340-200/-300, 

− THSA: 25 Ye calendar life limit added for PNR 47175-500 A340-500/-600 
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: OCT 12/11 ALS PART 4 HISTORY FILE PAGE: 4/5 

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

A340

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

1387B0000-01 in accordance with CN 2002-553(B), 

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

PNR 1386B0000-01 in accordance with CN 2002-553(B), 

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

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

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

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

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

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

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

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

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

− Retraction link (LH): Life limits amended for PNR 50-2105026-00, PNR 50-2105224-00, 

− Retraction link (RH): Life limits amended for PNR 50-2106026-00, PNR 50-2106224-

00, 

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

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

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

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

114256321, and PNR 50-2113002-00, 

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

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

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

− Pitot probes: Life limitations amended for PNR C16195BA, 

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

− Changes in the applicability of the following items: 

− Rudder Trim Actuator (RTA) PNR 6197-1, PNR 6197-2: Applicability restricted to A340-

200, A340-300 WV00x and WV02x series, 

− Rudder Travel Limitation Unit (RTLU) PNR 341400M02, PNR 343500M00: Applicability 

restricted to A340-200, A340-300 WV00x and WV02x series, 

− Pedal Travel Limitation Unit (PTLU) PNR 341400M02, PNR 343500M00: Applicability 

restricted to A340-200, A340-300 WV00x and WV02x series, 

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

and PNR SC5300-4: Applicability restricted to A340-200, A340-300 WV00x and WV02x 

series, 

− Yaw damper servo-control PNR SC4710, PNR SC4710-1: Applicability restricted to 

A340-200, A340-300 WV00x and WV02x series, 
AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: OCT 12/11 ALS PART 4 HISTORY FILE PAGE: 5/5 

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

A340

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

41800831100: Applicability restricted to A340-200, A340-300 WV00x and WV02x 

series, 

− Pin W PNR 55-2105061-00, 

− Retraction link (LH) PNR 50-2105026-00, 

− Retraction link (RH) PNR 50-2106026-00. 

SUB-PART 4-3:

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

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

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

− Task 274400-00001-4-E: Aircraft limitation applicability amended. 

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

− Task 294000-00001-1-E: PNR limitation applicability amended. 

Deletions: 

SUB-PART 4-0:

None. 

SUB-PART 4-1:

None. 

SUB-PART 4-2:

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

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

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

764239. Their limitations are mandated by CN 94-282-013(B)R3 and CN 1999-145-

115(B)R1. 

SUB-PART 4-3:

None.