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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.

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

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

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4 R 1-LEP OCT 12/11

4 1-TOC MAY 29/09

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

TABLE OF CONTENTS

SUBJECT PART

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

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# A340

RECORD OF REVISIONS ROR

INTRODUCTION 4-0

ILLUSTRATIONS 4-1

SYSTEMS LIFE-LIMITED COMPONENTS 4-2

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 4-3

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

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

EASA APPROVED

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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

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# 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 W V

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 sa fety) issues (in-service experience).

All the maintenance requirements and associated airworthiness limitations indicated in this document were defined by a process agreed between AIRBUS and the European Aviation Safety Agency (EASA).

The publication of this document precludes the necessity to publish individual Airworthiness Directives (AD) for each listed item and its requirements.

C. Limit Of Validity (LOV)

Operation of aircraft systems up to the stated Limit Of Validity (in Flight Hours or Flight Cycles, whichever occurs first) is covered by this document. The relevant LOV values are stated below. The aircraft systems must not be operated beyond these values unless the Type Certificate Holder (i.e. Airbus) has updated this document to include a clearly defined LOV extension.

(1) General LOV applicable to A340 systems installations

Aircraft series LOV

R Flight Hours (FH) Flight Cycles (FC)

A340-200 series OR 0 80000 20000

D 100000 (3) 20000

A340-300 series WV000’s and WV020’s (1) OR 0 80000 20000 100000 (3) 20000 A340-300 WV027 series (2) 0 60000 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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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)

0 75000 (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)

0 75000 (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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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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− A340-500 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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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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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 asnecessary 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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− 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:

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

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

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

Cp i = component/item’s airworthiness limitation in present application i.

When a component/item has been installed on an application where the ALS Part 4 does not impose an airworthiness limitation, the LOV of the relevant ALS Part 4 for that application must be used.

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

same usage parameters (FH or FC or landings): Usage parameters cannot be

mixed in the same calculation.

Note 2: The remaining life calculation must be reassessed every time the component’s/item’s airworthiness limitation(s) change(s) for current and/or previous aircraft application(s) to which the component/item is/was fitted. i 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 appliedprior 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), Vo lume II, Part B, Chapter 2 indicates:

The concept of Continuing Airworthiness includes the reporting of defects and other significant maintenance and operational information by the Operator to the organisation responsible for the Type Design in accordance with the requirements of the State of aircraft registry.

Accountable persons or organizations shall report to the competent authority and Airbus, any identified condition of an aircraft or component that has resulted or may result in an unsafe condition that hazards seriously the flight safety (Refer to EASA Part M.A.202 and Part 145.A.60). This will enable Airbus to issue appropriate service instructions to all owners or Operators. R

N

N

N

N

N

N

N

N

N

N

N

R

N

N

N

R

N

N

N

N

N

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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

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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 co mponent/an item is transferred from one Owner/Operator to another, the associated approvals and documents indicating the necessary adaptations of airworthiness limitations must be transferred as well.

2. DEFINITIONS

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

− The date of Transfer of Title to the first Operator for airworthiness limitations in Calendar times, unless otherwise stated in any delivery documentation to the first Operator.

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

The initial entry into service for the transferable systems components/items is defined as the date at which the component/item accomplishes the first flight for which it will undertake

its intended function.

Note: Unless otherwise stated, this means for transferable components/items delivered on new aircraft (i.e. from Airbus Final Assembly Line) that the life accumulated between aircraft first flight and the aircraft delivery date/transfer of title date (e.g. as a result of test flights) must be taken into account.

Calendar times (Cal.): Airworthiness limitations in Years (Ye), Months (Mo), etc... must be counted from the date of initial entry into service (unless otherwise stated). In considering the accumulated time since the initial entry into service, it should be noted that Calendar time usage parameter cannot be frozen (unless stated for individual components/items). N

N

R

R

N

N

N

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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/anitem 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

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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

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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

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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

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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.

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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

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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

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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 ReducerAIRWORTHINESS LIMITATIONS SECTION

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ATA 26-28-00 – AUXILIARY AREA FIRE EXTING. BCRC – FIG. 02 Sub-part 4-1 ILLUSTRATIONS

Pressure ReducerAIRWORTHINESS LIMITATIONS SECTION

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

Servo-controlAIRWORTHINESS LIMITATIONS SECTION

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

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

Limitation UnitAIRWORTHINESS LIMITATIONS SECTION

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ATA 27-24-00 – RUDDER HYDRAULIC ACTUATION – FIG. 06 Rudder Servo-controlAIRWORTHINESS LIMITATIONS SECTION

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ATA 27-26-00 – YAW DAMPER ACTUATION – FIG. 07 Yaw Damper ActuatorAIRWORTHINESS LIMITATIONS SECTION

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ATA 27-26-00 – BACK-UP YAW DAMPER ACTUATION – FIG. 08 Back-up Yaw Damper UnitAIRWORTHINESS LIMITATIONS SECTION

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ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 09 Elevator Servo-controlAIRWORTHINESS LIMITATIONS SECTION

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

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ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 11 Example Flap Rotary ActuatorAIRWORTHINESS LIMITATIONS SECTION

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

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

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ATA 32-11-00 – MAIN LANDING GEAR – FIG. 14 (*) Location, item not illustrated

FORWARD Pin P (*) Retraction

actuator

Lock stay

actuator

Side Stay AssemblyAIRWORTHINESS LIMITATIONS SECTION

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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 fittingAIRWORTHINESS LIMITATIONS SECTION

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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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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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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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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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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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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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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 fittingAIRWORTHINESS LIMITATIONS SECTION

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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 glandAIRWORTHINESS LIMITATIONS SECTION

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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 headAIRWORTHINESS LIMITATIONS SECTION

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

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ATA 34-11-00 – NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING – FIG. 27 Angle of Attack SensorAIRWORTHINESS LIMITATIONS SECTION

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

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

IndicatorAIRWORTHINESS LIMITATIONS SECTION

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ATA 35-13-00 – CREW OXYGEN – CONTROL AND INDICATING – FIG. 30 Pressure SwitchAIRWORTHINESS LIMITATIONS SECTION

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

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

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

END OF SUB-PART 4-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 1EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Sub-part 4-2 SYSTEMS LIFE LIMITED COMPONENTS1. Sub-part 4-2-1 LIFE LIMITSA. A340-200/-300 SERIESNote: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xATA 26-23 FIRE PROTECTION – LOWER DECK CARGOCOMPARTMENT FIRE EXTINGUISHING (FIG. 01)DNPressure reducer D41428 N/A N/A 20 Ye X X X X XATA 26-28 FIRE PROTECTION – AUXILIARY AREAS FIRE EXTINGUISHING (FIG. 02)N Pressure reducer E62691-00 N/A N/A 20 Ye XRATA 27-14 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 03)(1) Applicable to servo-controls installedin positions Functional Item Number (FIN)7CS1, 8CS1, 7CS2 and 8CS2 for inboard servo-controls, and FIN 9CS1, 10CS1,9CS2, 10CS2 for outboard servo-controls (active and damping).D(2) Embodiment of MOD 45512/SB A340-27-4062 introduces different PNR. MOD 45512 factory embodied on MSN 228 and subsequent.Inboard aileron servo-control(1) (2)3337457-22 9000 N/A N/A X X XD3337457-23 9000 N/A N/A X X X3337457-26 27000 N/A N/A X X X3337457-27 27000 N/A N/A X X X3337457-30 65600 16400 N/A X X XD3337457-31 65600 16400 N/A X X X3337457-35 65600 16400 N/A X X X3337457-36 65600 16400 N/A X X X3337457-37 65600 16400 N/A X X X3337457-38 65600 16400 N/A X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 2EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xOutboard aileron servo-control(1) (2)3337458-30 65600 16400 N/A X X XD3337458-31 65600 16400 N/A X X X3337458-35 65600 16400 N/A X X X3337458-36 65600 16400 N/A X X X3337458-37 65600 16400 N/A X X X3337458-38 65600 16400 N/A X X XRATA 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 XSC4800-3 N/A N/A 31-Aug-04 X X X XSC4800-4 N/A N/A 31-Aug-04 X X X XSC4800-6 N/A N/A 31-Aug-04 X X X XSC4800-7 N/A N/A 31-Aug-04 X X X XSC4800-7A N/A N/A 30-Jun-08 X X X X XSC4800-8 N/A N/A 31-Aug-04 X X X XSC4800-9 N/A N/A 30-Jun-08 X X X X XSC4800-10 N/A N/A 30-Jun-08 X X X X XSC4800-11 N/A N/A 30-Jun-08 X X X X XSC4800-72 N/A N/A 30-Jun-08 X X X X XSC4800-73 N/A N/A 30-Jun-08 X X X X XSC4800-92 N/A N/A 30-Jun-08 X X X X XSC4800-93 N/A N/A 30-Jun-08 X X X X XSC4800-103 N/A N/A 30-Jun-08 X X X X XSC4800-113 N/A N/A 30-Jun-08 X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 3EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 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 A340-27-4099introduces different PNR. MOD 45906 is factory embodied on MSN 233 andsubsequent.(2) Embodiment of MOD 49590/SB A340-27-4089 introduces different PNR. MOD 49590 is factory embodied on MSN 429, 433, 435 and subsequent.THS Actuator 47147-200 N/A N/A 31-Jul-04 X (1)47147-210 N/A N/A 31-Jul-04 X (1)47147-213 N/A N/A 31-Jul-04 X (1)47147-300 N/A N/A 31-Jul-04 X (1)47147-303 N/A N/A 31-Jul-04 X (1)47147-350 N/A N/A 31-Jul-04 204 X (1) X (1)47147-400 N/A N/A 31-Jul-04 X (1) X (1) X (1)47172 N/A N/A31-Dec-03X (2) X (2) X (2)RATA 27-54 FLIGHT CONTROL – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION (FIG. 11)(1) Embodiment of MOD 50044 (associatedto SB A340-27-4111) introduces new PNR.Flap Rotary Actuator – Type A 697510004 (1) N/A 18000 12 Ye X X X X697510005 (1) N/A 18000 12 Ye X X X XFlap Rotary Actuator – Type B 697511004 (1) N/A 18000 12 Ye X X X X697511005 (1) N/A 18000 12 Ye X X X X697511006 (1) N/A 18000 12 Ye X X X X697511007 (1) N/A 18000 12 Ye X X X XRATA 27-64 FLIGHT CONTROL – SPOILERHYDRAULIC 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 introduces different PNR.(2) FIN 13CS1 and 13CS2.(3) FIN 14CS1, 15CS1, 16CS1, 17CS1, 18CS1 and 14CS2, 15CS2, 16CS2, 17CS2 and 18CS2..../...AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 4EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05x(4) For spoiler servo-controls with unknown history of life accumulation on 31-Aug-2006, their total accumulated life is calculated by addition of the life accumulatedby the aircraft they are fitted to on 31-Aug-2006,to their actual life accumulated since.(5) When removed from aircraft, these servo-controls must be scrapped.RR(6) Applicable to aircraft up to and including MSN 598.−For aircraft, which have accumulated on 05-Sep-08 less than or equalto 8500 FC since aircraft initial entry into service, modify all servo-controls inaccordance with SB A340-27-4115 no later than 05-Mar-2010.−For aircraft, which have accumulated on 05-Sep-08 more than 8500 FC since aircraft initial entry into service, modify the servo-controls, in accordance withSB A340-27-4115:−If 3 hydraulic circuits are affected:(a) On first circuit within 10400 FC since aircraft initial entry into service.(b) On second circuit within 10800 sinceaircraft initial entry into service.(c) On third circuit no later than 05-Mar-2010.−If 2 hydraulic circuits are affected:(a) On first circuit within 10800 FC since aircraft initial entry into service.(b) On second circuit or no later than 05-Mar-2010.−If 1 hydraulic circuit is affected: no later than 05-Mar-2010.N (7) Embodiment of MOD 48956/SB A340-27-4100 introduces different PNR. MOD 48956 is factory embodied on MSN 385, MSN 446 and subsequent.Spoiler servo-controlposition 1 (2)MZ4339390-01X (6) N/A N/A 05-Mar-10 X X X X XMZ4339390-02X (6) N/A N/A 05-Mar-10 X X X X XMZ4339390-10X (6) N/A N/A 05-Mar-10 X X X X XS4-3000470(1)(4)(5)N/A 15000 N/A X X X X XS4-3000470-01(1)(4)(5)N/A 15000 N/A X X X X XS4-3000470-02(1)(4)(5)N/A 15000 N/A X X X X X.../...S4-3000470-03(1)(4)(5)N/A 15000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 5EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xNSpoiler servo-controlposition 1 (2)1387A0000-01 (7) N/A N/A 31-Dec-03 X X X X XN 1387B0000-01 (7) N/A N/A 31-Dec-03 X X X X XSpoiler servo-controlpositions 2-6 (3)MZ4306000-01X (6) N/A N/A 05-Mar-10 X X X X XMZ4306000-02X (6) N/A N/A 05-Mar-10 X X X X XMZ4306000-10X (6) N/A N/A 05-Mar-10 X X X X XS4-3000460(1)(4)(5)N/A 14000 N/A X X X X XS4-3000460-01(1)(4)(5)N/A 14000 N/A X X X X XS4-3000460-02(1)(4)(5)N/A 14000 N/A X X X X XS4-3000460-03(1)(4)(5)N/A 14000 N/A X X X X XN1386A0000-01 (7) N/A N/A 31-Dec-03 X X X X XN 1386B0000-01 (7) N/A N/A 31-Dec-03 X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 6EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH LDG Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25)RMAIN 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. Embodiment of MOD 43863 or MOD45031/SB A340-32-4092 introduces a different PNR. MOD 43863 factory embodied on original landing gear of A340-200 MSN 151 and subsequent, excludingMSN 204. MOD 43863 factory embodied on original landinggear of A340-300 MSN 115, 125, 133, 134, 145 and 146.(2) For this PNR, note (1) is applicable to SNR 0018WHM and SNR 0022WHM.(3) For this PNR, note (1) is applicable to SNR 0034WHM and SNR 0041WHM.(4) For this PNR, note (1) is applicableto SNR 003WHM (only this SNR exists).(5) For this PNR, note (1) is applicableto SNR 0031WHM (only this SNR exists).(6) For this PNR, applicable to the other SNRs. See notes (2) and (3). Embodiment of MOD 43863 or MOD 45031/SB A340-32-4092 introduces a different PNR.MOD 43863 factory embodied on original landing gear of A340-200MSN 151 and subsequent, excluding MSN 204. MOD 43863 factory embodied on originallanding 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 ofMSN 273 and subsequent.(8) Embodiment of MOD 46904/SB A340-32-4134 introduces a different PNR. MOD 46904 factory embodied on original landing gear ofMSN 273 and subsequent.(9) Embodiment of MOD 48066/SB A340-32-4164 introduces a different PNR. MOD 48066 factory embodied on original landing gear ofMSN 367 and subsequent.(10) Life limit is the later of 900 aircraft FH counted from08-Jul-2009 or the accumulation of 11150 total LDG since initialentry into service of Pin W1 on any aircraft.(11) Life limit is the earlier of the 10-year calendar limit 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 -312/-313 -313Retraction link (LH) 201275317 (9) N/A 35200 36 Mo X X -313 -312/-313 -313201489311 (12) N/A 8400 N/A X X -313 -312/-313 -313Retraction link (RH) 201275318 (9) N/A 35200 36 Mo X X -313 -312/-313 -313201489312 (12) N/A 8400 N/A X X -313 -312/-313 -313Pin W1 201275673 (7)(11) N/A (10) 10 Ye X X -313 -312/-313 -313201478614 N/A (10) N/A X X -313 -312/-313 -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 7EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH LDG Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction bracket (LH) 201428305 N/A (1) N/A excl. 204 X201428307 N/A (1) N/A excl. 204 X201428318 N/A (1) N/A excl. 204 X201428323 N/A (1) N/A excl. 204 X201428331 (2) N/A (1) N/A excl. 204 X201428331 (6) N/A 9000 N/A excl. 204 X201428333 N/A (1) N/A excl. 204 X201428335 N/A (1) N/A excl. 204 X201428338 (4) N/A (1) N/A excl. 204 XR 201428351 N/A 19800 N/A X X -313 -312/-313 -313R 201428378 N/A 19800 N/A X X -313 -312/-313 -313N 201428380 N/A 19800 N/A excl. 204 XN 201428382 N/A 19800 N/A excl. 204 XN 201428384 N/A 19800 N/A excl. 204 XN 201478303 N/A 19800 N/A excl. 204 XN 201478305 N/A 19800 N/A excl. 204 XN 201478307 N/A 19800 N/A excl. 204 XRetraction bracket (RH) 201428306 N/A (1) N/A excl. 204 X201428308 N/A (1) N/A excl. 204 X201428319 N/A (1) N/A excl. 204 X201428324 N/A (1) N/A excl. 204 X201428332 (3) N/A (1) N/A excl. 204 X201428332 (6) N/A 9000 N/A excl. 204 X201428334 N/A (1) N/A excl. 204 X.../... 201428336 N/A (1) N/A excl. 204 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 8EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH LDG Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction bracket (RH) 201428339 (5) N/A (1) N/A excl. 204 XR 201428352 N/A 19800 N/A X X -313 -312/-313 -313R 201428379 N/A 19800 N/A X X -313 -312/-313 -313N 201428381 N/A 19800 N/A excl. 204 XN 201428383 N/A 19800 N/A excl. 204 XN 201428385 N/A 19800 N/A excl. 204 XN 201478304 N/A 19800 N/A excl. 204 XN 201478306 N/A 19800 N/A excl. 204 XN 201478308 N/A 19800 N/A excl. 204 XPin W2201275667 (8)N/A 4500 5 Ye excl. 204 XN/A 9400 5 Ye 204 -313 -312/-313 -313Pin P 201275602 (7) N/A 20000 10 Ye X X -313 -312/-313 -313RRETRACTION ACTUATOR (FIG. 25)N (1) Embodiment of MOD 200837/SB A340-32-4284 introduces a different PNR.R Retraction actuator piston rod 114256309 N/A8080 31-Dec-07 X X -313 -312/-313 -313R 114256321 N/A 8080 31-Dec-07 X X -313 -312/-313 -313N 114256323 N/A 5500 N/A X X -313 -312/-313 -313114256326 N/A 20950 N/A X X -313 -312/-313 -313114256328 N/A 20950 N/A X X -313 -312/-313 -313N Retraction actuator gland 50-2113004-00 (1) N/A 27790 N/A -312/-313 -313Retraction actuator cylinder 114256310 N/A 22900 N/A X X -313 -312/-313 -313114256320 N/A 22900 N/A X X -313 -312/-313 -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 9EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 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 X XRATA 35-13-00 OXYGEN – CREW OXYGEN –CONTROL AND INDICATING (FIG. 30)Pressure switch CMK80-01 80000 N/A 20 Ye X X X X XRATA 35-23-00 OXYGEN – PASSENGEROXYGEN (GAZEOUS) – CONTROL AND INDICATING (FIG. 31)Quantity calculation control unit E69027 80000 N/A 20 Ye X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 10EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340B. A340-500/-600 SERIESNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xNATA 26-28 FIRE PROTECTION – AUXILIARYAREAS FIRE EXTINGUISHING (FIG. 02)N Pressure reducer E62691-00 N/A N/A 20 Ye X X X XRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS)HYDRAULIC ACTUATION (FIG. 10)N(1) Embodiment of SB A340-27-5030introduces different PNR.R THS Actuator 47175-200 (1) N/A 4730 N/A X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 11EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25)RRETRACTION ACTUATOR (FIG. 25)Retraction actuator piston rod 50-1231002-01 N/A 6090 N/A X X X XRATA 32-15-00 CENTER LANDING GEAR (FIG. 17, 18 & 21)RRETRACTION ACTUATOR (FIG. 21)(1) The calendar life limit is to be counted from the Date OfManufacture (DOM) of the part. DOMs are provided in Messier-Dowty Service Letter A34/56-32-055.Retraction actuator cylinder 50-1104001-00 N/A 7800 N/A X XRetraction actuator piston rod 55-1104003-00 (1) N/A 3000 42 Mo X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 20 & 23)RRETRACTION ACTUATOR (FIG. 23)(1) The calendar life limit is to be counted from the Date OfManufacture (DOM) of the part. DOMs are provided in Messier-Dowty Service Letter A34/56-32-055.Retraction actuator piston rod 55-1026003-00 (1) N/A 3000 42 Mo X XRetraction actuator cylinder 50-1026001-00 N/A 10300 N/A X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-1 PAGE: 12EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 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 XNATA 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.NRear Center Tank (RCT) liner (1)(2)F00030769000 N/A N/A 12 Ye X XN F00030770000 N/A N/A 12 Ye X XN F00030771000 N/A N/A 12 Ye X XN F00030772000 N/A N/A 12 Ye X XN F00030773000 N/A N/A 12 Ye X XN F00030774000 N/A N/A 12 Ye X XN F00030775000 N/A N/A 12 Ye X XN F00030776000 N/A N/A 12 Ye X XEND OF SUB-PART 4-2-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 13EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A3402. Sub-part 4-2-2 CURRENT DEMONSTRATED LIVESA. A340-200/-300 SERIESNote: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 27-14 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 03)(1) Applicable to servo-controls installed in positions FIN 7CS1, 8CS1, 7CS2, 8CS2 for inboard servo-controls, and FIN 9CS1, 10CS1, 9CS2, 10CS2 for outboardservo-controls (active and damping).RInboard aileron servo-control(1)3337457-59 N/A N/A N/A X X X X XR 3337457-60 N/A N/A N/A X X X X XC38661-002 80000 20000 N/A X X X X XROutboard aileron servo-control(1)3337458-59 N/A N/A N/A X X X X XR 3337458-60 N/A N/A N/A X X X X XC38657-002 80000 20000 N/A X X X X XRATA 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 X N/A (1)R 6197-2 90000 N/A N/A X X X X N/A (1)ATA 27-23 FLIGHT CONTROL – RUDDER AND PEDALTRAVEL LIMITING ACTUATION (FIG. 05)N (1) Installation not authorised on A340-31x WV05x.RRudder Travel Limitation Unit(RTLU)341400M02 90000 N/A N/A X X X X N/A (1)R 343500M00 90000 N/A N/A X X X X N/A (1)RPedal Travel Limitation Unit(PTLU)341400M02 90000 N/A N/A X X X X N/A (1)R 343500M00 90000 N/A N/A X X X X N/A (1)RAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 14EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 27-24 FLIGHT CONTROL – RUDDERHYDRAULIC 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 X N/A (1)R SC5300-1 N/A N/A N/A X X X X N/A (1)R SC5300-2 N/A N/A N/A X X X X N/A (1)R SC5300-3 N/A N/A N/A X X X X N/A (1)R SC5300-4 N/A N/A N/A X X X X N/A (1)RATA 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 X N/A (1)R SC4710-1 N/A N/A N/A X X X X N/A (1)RBack-up Yaw Damper Unit(BYDU)41800831001 N/A N/A N/A XX X X N/A (1)R 41800831002 N/A N/A N/AX X X X N/A (1)R 41800831100 N/A N/A N/AX X X X N/A (1)RATA 27-34 FLIGHT CONTROL – ELEVATORAND HYDRAULIC ACTUATION (FIG. 09)(1) Applicable to elevator servo-controls installed in positions FIN 2CS1, 2CS2, 3CS1, and 3CS2 (in active and damping modes).RElevator servo-controls (1)SC4800-74 N/A N/A N/A X X X X XR SC4800-94 N/A N/A N/A X X X X XR SC4800-104 N/A N/A N/A X X X X XR SC4800-114 N/A N/A N/A X X X X XRDNATA 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 X XR .../... 47147-700 80000 20000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 15EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xTHS Actuator 47172-300 80000 20000 N/A X X X X XR 47172-500 (1) 80000 20000 25 Ye X X X X XR 47172-510 (2) 80000 20000 25 Ye X X X X XN 47172-520 80000 20000 N/A X X X X XN 47172-530 80000 20000 N/A X X X X XRDRDRATA 27-64 FLIGHT CONTROL – SPOILERHYDRAULIC ACTUATION (FIG. 12)Spoiler servo-controlpositions 11387A0000-02 N/A N/A N/A X X X X X1387B0000-02 N/A N/A N/A X X X X XR 1387C0000-01 N/A N/A N/A X X X X XRDRRMZ4339390-12 N/A N/A N/A X X X X XSpoiler servo-controlpositions 2 to 61386A0000-02 N/A N/A N/A X X X X X1386B0000-02 N/A N/A N/A X X X X XR 1386C0000-01 N/A N/A N/A X X X X XR MZ4306000-12 N/A N/A N/A X X X X XNATA 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 X XN 768084 N/A N/A N/A X X X X XN 770379 N/A N/A N/A X X X X XN 770952 N/A N/A N/A X X X X XN 770952A N/A N/A N/A X X X X XN 770952B N/A N/A N/A X X X X XN 1702934 N/A N/A N/A X X X X XN 1702934A N/A N/A N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 16EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25)RMAIN 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 -312/-313 -313201489770 N/A 42800 N/A X X -313 -312/-313 -313R 55-2105061-00 N/A 46480 N/A -312/-313 -313Retraction link (LH) 201489315 N/A 10700 N/A X X -313 -312/-313 -313R 50-2105026-00 N/A 46480 N/A -312/-313 -313R 50-2105224-00 N/A 46480 N/A -312/-313 -313Retraction link (RH) 201489316 N/A 10700 N/A X X -313 -312/-313 -31350-2106026-00 N/A 46480 N/A -312/-313 -313R 50-2106224-00 N/A 46480 N/A -312/-313 -313RDRDRPin W1 55-2105060-00 N/A 46480 N/A -312/-313 -313Retraction bracket (LH) 50-2105027-00 N/A 46480 N/A -312/-313 -313Retraction bracket (RH) 50-2106027-00 N/A 46480 N/A -312/-313 -313Pin W2 201478615 N/A 42800 N/A X X -313 -312/-313 -313201478637 N/A 42800 N/A X X -313 -312/-313 -313R 55-2105059-00 (1) N/A 46480 N/A -312/-313 -313Pin P 201478612 N/A 42800 N/A X X -313 -312/-313 -313R 55-2105059-00 (1) N/A 46480 N/A -312/-313 -313RCOMPLETE SIDE STAY (FIG. 14, 16 & 24)Lock stay actuator pin 201440611 N/A 25000 N/A excl. 204 X201457606 N/A 25000 N/A excl. 204 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11ALS PART 4-2-2PAGE: 17EASAAPPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRLOCK STAY ACTUATOR (FIG. 24)Lock stay actuator cylinder 114354600 N/A 25000 N/A excl. 204 X201686600 N/A 25000 N/A excl.204 XLock stay actuator piston rod 114354605 N/A 25000 N/A excl. 204 X201686602 N/A 25000 N/A excl.204 XLock stay actuator gland114354606 N/A 25000 N/A excl. 204 X201481611 N/A 25000 N/A excl.204 X201481614 N/A 25000 N/A excl.204 XLock stay actuator rod end 114354602 N/A 25000 N/A excl. 204 X201686601 N/A 25000 N/A excl.204 XRRETRACTION ACTUATOR (FIG. 25)(1) Must be replaced by a new one every timethe piston head is removed from the piston rod.R Retraction actuator piston rod 50-2113002-00 N/A 50000 N/A-312/-313 -313Retraction actuator gland114256312 N/A 50000 N/A XX-313 -312/-313 -313DN114256322 N/A 50000 N/A X X -313 -312/-313 -31350-2113004-01N/A27790N/A-312/-313-313Retraction actuator piston head 114256308 N/A 50000 N/A XX-313 -312/-313 -313114256639 N/A 50000 N/A X X -313 -312/-313 -313R50-2113003-00 N/A 50000 N/A-312/-313 -313Retraction actuator insert114256629 N/A (1) N/A XX-313 -312/-313 -313R Retraction actuator cylinder 50-2113001-00 N/A 50000 N/A-312/-313 -313RATA 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)F53112357200xxN/A 25000 N/A X X -312/-313N/A37500N/A-313AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 18EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator pin(Airframe side) (1)F53112357204xx N/A 25000 N/A -312/-313 -313F53114022200xx N/A 25000 N/A -312/-313 -313F53114023200xxN/A 25000 N/A X X -312/-313N/A 37500 N/A -313F53120422200xx N/A 25000 N/A -312/-313 -313RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 22)Retraction actuator pin(Main fitting side)D61686100000 25000 N/A X X -312/-313 -31375000 37500 N/A -313RRETRACTION ACTUATOR (FIG. 22)Retraction actuator eye endD62588N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D62588-1N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D67840N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator bearingD61950-1N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D61950-10N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D67839N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator sliding rodD62328N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D62328-1N/A 25000 N/A X X -312/-313 -313.../... N/A 37500 N/A -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 19EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator sliding rodD67837N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator plugD61952N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D61952-1N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D67838N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator cylinderD62587N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D62587-1N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D67836N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator bodyD61954N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D61954-10N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D67876N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 20EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal. A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 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 X XR Sensor – Angle Of Attack 45150320 90000 48000 N/A X X X X XR C16291AA 90000 48000 N/A X X X X XN C16291AB 90000 48000 N/A X X X X XRATA 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 X XR 64141-590-1 N/A N/A N/A X X X X XR Indicator Standby Airspeed 64050-868-1 N/A N/A N/A X X X X XRATA 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 X XR H321BHM1 N/A N/A N/A X X X X XR H341BVM N/A N/A N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 21EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340B. A340-500/-600 SERIESNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH FC Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRDNATA 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 and subsequent.R THS Actuator 47175-300 50000 10000 N/A X X X XR 47175-500 (1) 50000 10000 25 Ye X X X XN 47175-520 50000 10000 N/A X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 22EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 32-11-00 MAIN LANDING GEAR (FIG. 14 to 16 & 24 to 25)RMAIN 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 X XRetraction link (LH) 50-1205288-01 N/A 20600 N/A X X X XRetraction link (RH) 50-1206288-01 N/A 20600 N/A X X X XPin W1 55-1205154-00 N/A 20600 N/A X X X XRetraction bracket (LH) 50-1205007-00 N/A 20600 N/A X X X XRetraction bracket (RH) 50-1206007-00 N/A 20600 N/A X X X XPin W2 55-1205151-00 (1) N/A 20600 N/A X X X XPin P 55-1205151-00 (1) N/A 20600 N/A X X X XRRETRACTION 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 X XRetraction actuator gland 50-1231004-02 N/A 10000 N/A X X X XRetraction actuator piston head 50-1231003-00 N/A 10000 N/A X X X XRetraction actuator insert 114256629 N/A (1) N/A X X X XRetraction actuator cylinder 50-1231001-00 N/A 10000 N/A X X X XRATA 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 X XG53323625200xx N/A 16600 N/A X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 23EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRLEG EQUIPPED (FIG. 17)RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 17 & 21)Retraction actuator pin(Main fitting side)55-1105016-00 N/A 13100 N/A X X55-1105315-00N/A 13100 N/A X XN/A 10300 N/A X XRCOMPLETE DRAG STAY (FIG. 18 & 21)Unlock actuator pin (drag stay)55-1110052-00N/A 13100 N/A X XN/A 10300 N/A X XRLOCK LINK (FIG. 18)Unlock actuator pin (lock link)55-1110052-00N/A 13100 N/A X XN/A 10300 N/A X XRUNLOCK ACTUATOR (FIG. 18)Unlock actuator rod end 55-1113006-00 N/A 20600 N/A X X55-1113006-01 N/A 20600 N/A X X X XUnlock actuator piston rod 55-1113003-00 N/A 20600 N/A X X55-1113003-01 N/A 20600 N/A X X X XUnlock actuator gland 55-1113016-00 N/A 20600 N/A X X55-1113016-01 N/A 20600 N/A X X X XUnlock actuator cylinder 55-1113001-00 N/A 20600 N/A X X55-1113001-01 N/A 20600 N/A X X X XRRETRACTION ACTUATOR (FIG. 21)Retraction actuator cylinder 50-1104001-01 N/A 20600 N/A X X X XRetraction actuator piston rod 55-1104003-01 N/A 20600 N/A X X X XRetraction actuator piston head 50-1104005-01 N/A 1400 N/A X X55-1104036-00 N/A 20600 N/A X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 24EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature Part Number FH LDG Cal.A340-54x A340-64xWV00x WV10x WV00x WV10xRetraction actuator piston rod nut 55-1104008-00 N/A 20600 N/A X X55-1104008-01 N/A 20600 N/A X X X XRetraction actuator bearing 50-1104010-01 N/A 20600 N/A X X50-1104010-02 N/A 20600 N/A X X X XRATA 32-21-00 NOSE LANDING GEAR (FIG. 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 X XF53115982000xx N/A 16600 N/A X X X XRNOSE LANDING GEAR LEG (FIG. 20 & 23)Retraction actuator pin(Main fitting side)55-1003014-00 N/A 20600 N/A X X55-1003283-00 N/A 6000 N/A X XRRETRACTION ACTUATOR (FIG. 23)Retraction actuator piston rod 55-1026003-01 N/A 20600 N/A X X X XRetraction actuator bearing 55-1026010-01 N/A 20600 N/A X X55-1026010-02 N/A 20600 N/A X X X XRetraction actuator piston head 55-1026005-01 N/A 1400 N/A X X55-1026033-00 N/A 20600 N/A X X X XRetraction actuator piston rod nut 55-1026008-00 N/A 20600 N/A X X55-1026008-01 N/A 20600 N/A X X X XRetraction actuator cylinder 50-1026001-01 N/A 20600 N/A X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-2-2 PAGE: 25EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340NNote: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.NN(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNNomenclature Part Number FH FC Cal.A340-54x A340-64xNWV00x WV10x WV00x WV10xNATA 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 X XN Sensor – Angle Of Attack C16291AA 90000 48000 N/A X X X XN C16291AB 90000 48000 N/A X X X XEND OF SUB-PART 4-2-2AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-3-1 PAGE: 1EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTSSub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone Description Threshold Interval PNR AIRCRAFTR 274400-00001-1-E 311312THSA – FIG. 10Detailed inspection of the ball screw assemblyfor integrity of the primary and secondary loadpath and check the gap at the secondary nuttrunnion.This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.Note 2: In computing the life accumulated bythe THSA for compliance with thethreshold, calculations must includeflight hours since the initial entry intoservice or since 17-Aug-2002,whichever occurs later.700 FHNotes 1 & 2700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147147-50047172-300PRE 55780PRE 27-4136PRE 27-4143RNN274400-00001-2-E 311312THSA – FIG. 10Detailed inspection of the ball screw assemblyfor integrity of the primary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.Note 2: At the time of SB A340-27-4136accomplishment.Note 2 700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147172-50047172-520POST 27-4136PRE 56056PRE 92-4056R03AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-3-1 PAGE: 2EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone Description Threshold Interval PNR AIRCRAFTRNN274400-00001-3-E 311312THSA – FIG. 10Detailed inspection of the ball screw assemblyfor integrity of the primary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.700 FHNote 1700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147172-51047172-530POST 55780PRE 56056PRE 92-4056R03RNN274400-00001-4-E 311312THSA – FIG. 10Detailed inspection of the ball screw assemblyfor integrity of the primary and secondary loadpath and check the Checkable Shear Pins(CSP).This task must be carried out before task274400-00002-1-E.Note 1: No short-term extension is allowed.700 FHNote 1700 FHNote 1SB A340-27-4107 R08AMM 27-44-5147147-700 POST 27-4143PRE 56056PRE 92-4056R03RNN274400-00002-1-E 311312THSA – FIG. 10Lubrication of the THSA ball-nut.Note: No short-term extension is allowed.1000 FHNote1000 FHNoteAMM 12-22-27/301 47147-50047147-70047172-30047172-50047172-51047172-52047172-530A340-200ORA340-300AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-3-1 PAGE: 3EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone Description Threshold Interval PNR AIRCRAFTRRRR2924000-00001-1-E 633Auxiliary Hydraulic Power – FIG. 13Removal of Ram Air Turbine (RAT) foroverhaul.Fit a RAT that has not accumulated 20 Yesince last overhaul.20 Ye20 YeAMM 292452/401CMM 29-21-31766351768084770379770952770952A770952B17029341702934AA340-200ORA340-300END OF SUB-PART 4-3-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-3-2 PAGE: 4EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone Description Threshold Interval PNR AIRCRAFTR275000-00001-1-E 570670FlapsPerform a simultaneous detailed visualinspection of the Input Gear Boxes (IPGB) andof the Down Drive Shafts (DDS) on flap tracks2 and 4 on both wings.Note 1: No short-term extension is allowed.Note 2: Report inspection results, whateverthey are, to AIRBUS.16-Dec-2007Notes 1 & 2N/A SB A340-27-4151AMM 27-54-56AMM 27-54-57N/A Up to MSN0185 inclusiveNNNNRRR275000-00001-2-E 570670FlapsPerform a simultaneous detailed visualinspection of the Input Gear Boxes (IPGB) andof the Down Drive Shafts (DDS) on all flaptracks on both wings.Note 1: No short-term extension is allowed.Note 2: First inspection is performed inaccordance with SB A340-27-4151.Report inspections results, whateverthey are, to AIRBUS.Subsequent repetitive inspections areperformed in accordance with SBA340-27-4152.16-Aug-2009Notes 1 & 26 YeNotes 1 & 2SB A340-27-4151SB A340-27-4152AMM 27-54-56AMM 27-54-57N/A Up to MSN0415 inclusivePRE 200492PRE 201194(27-4171 and27-5055),except MSN0385 and 0395AIRWORTHINESS LIMITATIONS SECTIONISSUE: OCT 12/11 ALS PART 4-3-2 PAGE: 5EASA APPROVED© AIRBUS SAS 2011. All rights reserved. Confidential and proprietary document.A340NNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone Description Threshold Interval PNR AIRCRAFTNNNN275000-00001-3-E 570670FlapsPerform a simultaneous detailed visualinspection of the Input Gear Boxes (IPGB) andof the Down Drive Shafts (DDS) on all flaptracks on both wings.Note: No short-term extension is allowed.26-Oct-2009or6 years fromthe date oforiginaldelivery ofthe aircraft,whicheveroccurs later.Note6 YeNoteSB A340-27-4152SB A340-27-5040AMM 27-54-56AMM 27-54-57N/A MSN 0385 and,MSN 0395 and,MSN 0416(inclusive)onwardsPRE 200492PRE 201194(27-4171 and27-5055)NNNNN275000-00001-4-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS). Lubricate all flap tracks on both wings24 MoNote24 MoNoteAMM 12-22-27 N/A POST 200492NNNNNNNNN275000-00001-5-E 570670FlapsLubricate the spline joint between the InputGear Boxes (IPGB) and the Down Drive Shafts(DDS). Lubricate all flap tracks on both wings.One-time inspection for corrosion inaccordance with SB A340-27-4171 or SBA340-27-5055 at the time of SB A340-27-4171or SB A340-27-5055 embodiment.24 Mo SB A340-27-4171SB A340-27-5055AMM 12-22-27N/A POST 201194(27-4171 or27-5055)END OF SUB-PART 4-3-2

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# 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.

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# 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.

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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

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− 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

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# 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.