# AIRWORTHINESS LIMITATIONS SECTION

REVISION: 01 

# A340



# ALS Part 4

- Ageing Systems Maintenance

© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.

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

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

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

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

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

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

supplied.

# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

ISSUE: DEC 15/09 ALS PART 4 PAGE: 1-LEP

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4 R 1-LEP DEC 15/09

4 1-TOC MAY 29/09

4 R 1-ROR DEC 15/09

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# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

TABLE OF CONTENTS

SUBJECT PART

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

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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

# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: DEC 15/09 ALS PART 4 PAGE: 1-ROR

EASA APPROVED

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# A340

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

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

procedure stated herein).

REVISION

NUMBER SUB-PARTS APPROVED BY

EASA EASA AD INSERTION IN

MAINT. PROG.

R 00 ROR

4-2

4-3 MAY 29/09 N/A

N

N

N 01 ROR

4-2

4-3 DEC 15/09

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

Revision 01 is approved by EASA under reference EASA 10028283.

REVISION 01 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 01 from 15-Dec-2010.

2. From 15-Dec-2009 to 14-Dec-2010, it is mandatory to comply with the maintenance

requirements and associated airworthiness limitations defined in, either:

− The sub-part 4-2 and 4-3 of the A340 ALS Part 4 at revision 00, 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 01.

3. From 15-Dec-2009, it is mandatory to comply with the maintenance requirements and

associated airworthiness limitations defined in the A340 ALS Part 4 revision 01, for:

− The Inboard aileron servo-control PNR C38661-002,

− The Outboard aileron servo-control PNR C38657-002,

− The Rudder Trim Actuator (RTA) PNR 6197-1 and PNR 6197-2,

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

− The Pedal Travel Limitation Unit (PTLU) PNR 341400M02 and PNR 343500M00, R

R

R

R

N

N

N

N

N

N

N

N

N

N

N

N

N

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ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: DEC 15/09 ALS PART 4 PAGE: 2-ROR

EASA APPROVED

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# A340

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

SC5300-3 and PNR SC5300-4,

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

− The Back-up Yaw Damper Unit (BYDU) PNR 41800831001, PNR 41800831002 and

PNR 41800831100,

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

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

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

SC4800-113 and PNR SC4800-114,

− The Trimmable Horizontal Stabilizer Actuator (THSA) PNR 47175-200,

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

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

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

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

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

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

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

− The Pitot probes PNR C16195AA and PNR C16195BA,

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

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

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

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

H341BVM,

− The Pressure swit ch PNR CMK80-01,

− The Quantity control unit PNR E69027,

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

4-E, 274400-00002-1-E and 275000-00001-3-E.

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

previous accomplishment date. N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

N

# AIRWORTHINESS LIMITATIONS SECTION

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

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# A340

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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# A340

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

Flight Hours Flight Cycles

A340-200 series OR 0 80000 20000

N 100000 (3) 20000 (3)

A340-200 WV021 series 0 60000 30000

A340-300 series WV000’s and WV020’s (1) OR 0 80000 20000

N 100000 (3) 20000 (3)

A340-300 WV027 series (2) 0 60000 30000

R 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. R

N

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# A340

(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 (e.g. the A330): e.g. the parts included in the retraction actuator chains, the

Ram Air Turbine, etc...

(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. N

N

N

N

N

N

N

N

D

# AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 15/09 ALS PART 4-0 PAGE: 4

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# A340

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

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

configuration(s).

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

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

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

Standard Requirements’).

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

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

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

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

below:

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

WV000: Basic aircraft.

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

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

WV021: Aircraft POST MOD 44281.

− A340-300 series WV000’s applications:

WV000: Basic aircraft.

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

WV002: Aircraft POST MOD 44228.

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

MOD 47434 or POST SB A340-00-4027.

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

− A340-300 series WV020’s and WV030 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

D

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# A340

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

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

A340-00-5005.

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

WV002: Aircraft POST MOD 50791.

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

WV004: Aircraft POST MOD 56719.

WV101: Aircraft POST MOD 53039.

WV102: Aircraft POST MOD 54806.

WV103: Aircraft POST MOD 55642.

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

WV000: Basic aircraft.

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

WV101: Aircraft POST MOD 53043.

WV102: Aircraft POST MOD 54805.

WV103: Aircraft POST MOD 57713.

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

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

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

the column ‘Other WV02x’.

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

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

275/260/218 tons).

D. ALS Part 3 and ALS Part 4 correlation

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

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

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

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

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

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

through their location in the ALS Part 3.

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

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

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

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

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

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

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

could contribute to an unsafe condition of the aircraft.

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# A340

Sub-part 4-2-1: Life Limits

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

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

the aircraft.

Sub-part 4-2-2: Demonstrated Life Limitations

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

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

aircraft.

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

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

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

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

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

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

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

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

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

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

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

system level failure condition or conditions.

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

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

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

the inspection threshold and interval quoted in this document.

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

at component level and aircraft (system) level respectively.

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

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

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

airworthiness limitation.

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

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

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

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

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

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

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

limitation. R

R

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# A340

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

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

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

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

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

successful task recording can be entered.

G. Traceability and replacement/maintenance requirements

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

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

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

limitations.

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

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

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

Airworthiness limitations (including life limitations) must be adjusted as

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

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

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

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

Certificate of Airworthiness.

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

introduced in the future. These new PNRs may not be listed in the sub-parts 4-2 and/or

4-3-1 of the current revision of the ALS Part 4.

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

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

Part 4.

For further guidance, Operators are requested to contact Airbus.

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

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

so that airworthiness limitations are accurately applied. Traceability records

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

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

Number, etc...),

− Maintenance actions carried out (Airworthiness Directives, modifications,

repairs, inspections, etc...),

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

component/an item may have been fitted).

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# A340

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

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

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

issued in agreement with the EASA.

H. Transfers of items between applications having different airworthiness limitations

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

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

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

with:

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

Ca j = accumulated life on previous application j.

Cp j = airworthiness limitation in previous application j.

Cp i = airworthiness limitation in present application i.

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

usage parameters (FH or FC or LDG): Usage parameters cannot be mixed in

the same calculation.

Note 2: The remaining life calculation must be reassessed every time the

component’s/item’s airworthiness limitations evolve for current and/or previous

aircraft application(s) to which the component/item is/was fitted.

I. Disposal/quarantine action

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

limitations and/or the LOV, disposal/quarantine action must be taken: Appropriate

means must be implemented to deter their installation on aircraft pending possible

extension of the life limitations and/or LOV. Examples of these means are:

− Record keeping system,

− Non-permanent markings,

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

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

to be airworthy.

J. Reporting

The ICAO Airworthiness manual (Doc. 9760), Vo lume II, Part B, Chapter 2 indicates: i Cp

j Cp j Ca

1 i Tr × ∑

−= 

# ⎥ ⎥

⎦ ⎤

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# AIRWORTHINESS LIMITATIONS SECTION

ISSUE: DEC 15/09 ALS PART 4-0 PAGE: 9

© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document. 

# A340

The concept of Continuing Airworthiness includes the reporting of defects and

other significant maintenance and operational information by the Operator to the

organisation responsible for the Type Design in accordance with the

requirements of the State of aircraft registry.

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

ALS Part 4 must be reported to Airbus.

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

− ASM maintenance requirement reference,

− Aircraft MSN affected,

− Identification of the affected component/item,

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

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

at the time of the finding,

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

− Circumstance of detection and inspection method used.

K. ALS Part 4 airworthiness limitations

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

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

case of damage/repair.

L. Production/Repair concessions and Alternative Methods Of Compliance

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

instructions given in either a Production or Repair concession, or an Alternative Method

Of Compliance (AMOC).

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

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

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

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

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

to contact Airbus for guidance.

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

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

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

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

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

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

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

solution/AMOC.

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

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

# AIRWORTHINESS LIMITATIONS SECTION

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

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

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

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

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

by the relevant Airworthiness Authority for any necessary adaptations of the

airworthiness limitations.

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

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

necessary adaptations of airworthiness limitations must be transferred as well.

2. DEFINITIONS

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

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

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

Operator.

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

cycles and/or landings.

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

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

its intended function.

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

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

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

test flights) must be taken into account.

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

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

service (unless otherwise stated). In considering the

accumulated time since the initial entry into service, it

should be noted that Calendar time usage parameter

cannot be frozen (unless stated for individual

components/items).

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

may be needed to cover an uncontrollable or

exceptional unexpected situation.

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

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

and “wheels-on”.

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Functional Check: A quantitative check to determine if an item performs

one or more of its functions within specified limits.

Interval: The period expressed in usage parameters like FH

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

between consecutive accomplishments of a specific

task, excluding any exceptional short-term extensions

from calculations.

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

coming to a complete stop or performing a “touch and

go”.

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

which the maintenance programme defined in that Part

ceases to be valid. The applicable LOV are indicated in

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

Operational Check: A qualitative check to determine that an item is fulfilling

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

does not require quantitative tolerances.

Threshold: The initial accomplishment of a specific maintenance

task from the initial entry into service. It may be

expressed in usage parameters like FH and/or FC

and/or LDG and/or Calendar time.

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

does not come to a full stop prior to commencing an

additional flight.

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

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

of FC up to threshold inspection or between two

consecutive inspections. Each “Touch and go” above

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

inspection or between two consecutive inspections.

3. RULES SPECIFIC TO SUB-PART 4-2

A. Authorised systems components/items

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

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

has been validated for a specific individual aircraft MSN.

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

associated modifications), which are published by Airbus.

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

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

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

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

replacement PNR, detail PNR and applicable SB:

− Messier-Dowty Ltd Service Bulletin number:

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

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

47487 – ‘growth scallop’),

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

− Messier-Dowty SA Service Bulletin number:

− D23285-32-040 (nose landing gear).

Detail parts are listed in the relevant Component Maintenance Manuals. The MessierDowty SB listed above provides the procurable replacement Part Numbers.

B. Life limitation/Replacement time indication

(1) General

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

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

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

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

stated).

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

paragraph 1.G.

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

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

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

stated).

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

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

lines as the PNR.

C. Life limitation applicability

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

sub-part 4-2), according to: N

N

N

N

N

N

N

N

N

N

N

N

N

N

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

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

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

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

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

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

# AIRWORTHINESS LIMITATIONS SECTION

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# A340

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

one associated with the inspection method used at last inspection.

B. ALS sub-part 4-3 layout.

The maintenance requirements and associated airworthiness limitations are presented

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

(1) Task Number

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

Document (MPD) system, as follows:

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

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

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

in "Zone" column.

The task number comprises 13 digits organised as follows:

XXXXXX-MEFYY-Z-E

XXXXXX is ATA 100 task reference.

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

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

is default value).

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

the same manufacturer is applicable to the program (where

applicable, “0” is default value).

YY is sequential number.

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

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

function or Enhanced maintenance requirement).

(2) Zone column

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

requirement is to be carried out on the aircraft.

(3) Description column

This column provides the following information:

(a) Task Description.

Contains basic description of the maintenance task to be performed.

(b) Note.

Where given, it states further requirements and/or provides useful information.

# AIRWORTHINESS LIMITATIONS SECTION

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(4) Threshold/Interval columns

These columns are used to record the selected threshold and interval for the task.

The threshold and interval may be expressed in terms of usage parameters or

notes.

Usage parameters are defined in the paragraph 2 of this sub-part.

(5) Reference column

This column provides reference to Instructions for Continued Airworthiness where

maintenance practices/procedures necessary for the task accomplishment are

provided, e.g. the AMM.

Where reference is made to an Airbus SB, it must be assumed that the latest

approved revision of the SB is applicable, but any previous revision is acceptable.

Where a particular revision is stated, the revision or any later approved revision

must be used.

(6) Limitations applicability columns

These columns give the combination of component(s)/item(s) PNR and aircraft that

requires the accomplishment of the task.

(a) PNR

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

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

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

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

associated modifications), which are published by Airbus.

(b) Aircraft

Applicability Task applicable to

ALL All 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.

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# A340

Applicability Task applicable to

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.

N

N POST SB

A340-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 items listed in sub-part 4-3.

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

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

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

objectives declared at Type Certification.

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

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

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

escalation.

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

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

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

be granted without consultation with that office.

(1) Controlled by Flight Hours (FH)

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

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

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# A340

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

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

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

LanDinGs.

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

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

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

limitations quoted in terms of Months.

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

may exceptionally be granted.

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

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

programme.

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

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

column.

END OF SUB-PART 4-0

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

Pressure Reducer

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ATA 27-14-00 – AILERON AND HYDRAULIC ACTUATION – FIG. 02 Aileron

Servo-control

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ATA 27-22-00 – RUDDER TRIM ACTUATION AND ARTIFICIAL FEEL – FIG. 03

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

Limitation Unit

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ATA 27-24-00 – RUDDER HYDRAULIC ACTUATION – FIG. 05 Rudder Servo-control

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ATA 27-26-00 – YAW DAMPER ACTUATION – FIG. 06 Yaw Damper Actuator

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ATA 27-26-00 – YAW DAMPER ACTUATION – FIG. 07 Back-up Yaw Damper Unit

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ATA 27-34-00 – ELEVATOR AND HYDRAULIC ACTUATION – FIG. 08 Elevator Servo-control

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ATA 27-44-00 – THS HYDRAULIC ACTUATION – FIG. 09 THSA

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ATA 27-54-00 – FLAPS HYDRAULIC ACTUATION AND POWER TRANSMISSION – FIG. 10 Example

Flap Rotary Actuator

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ATA 27-64-00 – SPOILER HYDRAULIC ACTUATION – FIG. 11

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ATA 27-64-00 – GREEN AUXILIARY HYDRAULIC POWER – FIG. 12

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ATA 32-11-00 – MAIN LANDING GEAR – FIG. 13 (*) Location, item not illustrated

FORWARD Pin P (*) Retraction

actuator

Lock stay

actuator

Side Stay

Assembly

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

Retraction

bracket Pin W2

Retraction actuator

piston rod Retraction

jack fitting

Pin W

Pin W1

Main fitting

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ATA 32-11-00 – MAIN LANDING GEAR – FIG. 15 Side Stay Assembly Lock link

(subassembly) Lock stay actuator

pin (x2)

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ATA 32-15-00 – CENTER LANDING GEAR – FIG. 16 (A340-500/-600 SERIES) FORWARD Main fitting

Retraction actuator pin

(main fitting side) Unlock actuator pin

(drag stay)

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ATA 32-15-00 – CENTER LANDING GEAR – FIG. 17 (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)

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ATA 32-21-00 – NOSE LANDING GEAR – FIG. 18 (A340-200/-300 SERIES) Main fitting

Retraction actuator pin

(main fitting side)

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Retraction actuator pin

(main fitting side) Main fitting



# ATA 32-21-00 – NOSE LANDING GEAR – FIG. 19 (A340-500/-600 SERIES)

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ATA 32-31-00 – CENTER LANDING GEAR – FIG. 20 (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)

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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. 21 (A340-200/-300 SERIES)

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ATA 32-31-00 – NOSE LANDING GEAR – FIG. 22 (A340-500/-600 SERIES) Retraction actuator pin

(airframe side) FORWARD

Retraction actuator pin

(main fitting side) Retraction actuator

piston rod

Retraction actuator

piston rod nut Retraction actuator

bearing Retraction actuator

cylinder

Retraction actuator

piston head Main fitting

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ATA 32-31-00 – MAIN LANDING GEAR – FIG. 23 Lock stay actuator

piston rod Lock stay actuator

cylinder Lock stay actuator

rod end

Lock stay actuator

gland

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

piston rod

Retraction actuator

insert

Retraction actuator

gland

Retraction actuator

cylinder Retraction actuator

piston head

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ATA 34-11-00 – NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING – FIG. 25 Pitot Probe

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

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ATA 34-21-00 – NAVIGATION – ALTITUDE AND AIRSPEED STANDBY DATA – FIG. 27

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ATA 34-22-00 – NAVIGATION – ATTITUDE AND HEADING STANDBY DATA – FIG. 28 Standby Horizon

Indicator

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ATA 35-13-00 – CREW OXYGEN – CONTROL AND INDICATING – FIG. 29 Pressure Switch

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ATA 35-23-00 – PAX OXYGEN (GASEOUS) – CONTROL AND INDICATING – FIG. 30

END OF SUB-PART 4-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 1EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xNATA 26-23 FIRE PROTECTION – LOWER DECK CARGOCOMPARTMENT FIRE EXTINGUISHING (FIG. 01)NPressurereducer D41428 N/A N/A 20Ye X X X X XNE62691-00 N/A N/A 20Ye X X X X XRATA 27-14 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 02)RR(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).(2) Embodiment of MOD 45512/SB A340-27-4062introduces different PNR. MOD 45512 factory embodied on MSN 228 and subsequent.Inboard aileron servo-control(1) (2)3337457-21 9000 N/A N/A X X X3337457-22 9000 N/A N/A X X X3337457-23 9000 N/A N/A X X X3337457-25 27000 N/A N/A X X X3337457-26 27000 N/A N/A X X X3337457-27 27000 N/A N/A X X X3337457-30 65600 16400 N/A X X X3337457-31 65600 16400 N/A X X X3337457-34 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: DEC 15/09ALS PART 4-2-1PAGE: 2EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xOutboard aileron servo-control(1) (2)3337458-30 65600 16400 N/A X X X3337458-31 65600 16400 N/A X X X3337458-34 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. 08)N (1) Applicable to servo-controls installed in positions FIN 2CS1, 2CS2, 3CS1 and 3CS2 (active and damping).R Elevator servo-control (1)SC4800-2 N/A N/A 31-Aug-04 XXXXSC4800-3 N/A N/A 31-Aug-04 XXXXSC4800-4 N/A N/A 31-Aug-04 XXXXSC4800-6 N/A N/A 31-Aug-04 XXXXSC4800-7 N/A N/A 31-Aug-04 XXXXNSC4800-7A N/A N/A 30-Jun-08 X X X X XSC4800-8 N/A N/A 31-Aug-04 XXXXNSC4800-9 N/A N/A 30-Jun-08 X X X X XNSC4800-10 N/A N/A 30-Jun-08 X X X X XNSC4800-11 N/A N/A 30-Jun-08 X X X X XNSC4800-72 N/A N/A 30-Jun-08 X X X X XNSC4800-73 N/A N/A 30-Jun-08 X X X X XNSC4800-92 N/A N/A 30-Jun-08 X X X X XNSC4800-93 N/A N/A 30-Jun-08 X X X X XNSC4800-103 N/A N/A 30-Jun-08 X X X X XNSC4800-113 N/A N/A 30-Jun-08 X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 3EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS)HYDRAULIC ACTUATION (FIG. 09)(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 Actuator47147-200 N/A N/A 31-Jul-04X (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. 10)(1) Embodiment of MOD 50044 (associatedto SB A340-27-4111) introduces new PNR.Flap Rotary Actuator – Type A 697510004 (1) N/A 18000 12 Ye XXXX697510005 (1) N/A 18000 12 Ye XXXXFlap Rotary Actuator – Type B 697511004 (1) N/A 18000 12 Ye XXXX697511005 (1) N/A 18000 12 Ye XXXX697511006 (1) N/A 18000 12 Ye XXXX697511007 (1) N/A 18000 12 Ye XXXXRATA 27-64 FLIGHT CONTROL – SPOILERHYDRAULIC ACTUATION (FIG. 11)(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: DEC 15/09ALS PART 4-2-1PAGE: 4EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.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.NNNNNNNNNNNNN(6) Applicable to aircraft up to and including MSN 588.−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 A330-27-3110 no later than 05-Mar-2010.−For aircraft, which have accumulated on 05-Sep-08 more than 8500 FC since aircraft initial entry into service, modify the servo-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.NSpoiler servo-controlposition 1 (2)MZ4339390-01X (6) N/A N/A 05-Mar-10 X X X X XNMZ4339390-02X(6) N/A N/A 05-Mar-10 X X X X XNMZ4339390-10X(6) N/A N/A 05-Mar-10 X X X X XRS4-3000470(1)(4)(5)N/A 15000 N/A X X X X XRS4-3000470-01(1)(4)(5)N/A 15000 N/A X X X X XRS4-3000470-02(1)(4)(5)N/A 15000 N/A X X X X XRS4-3000470-03(1)(4)(5)N/A 15000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 5EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xNSpoiler servo-controlpositions 2-6 (3)MZ4306000-01X (6) N/A N/A 05-Mar-10 X X X X XNMZ4306000-02X(6) N/A N/A 05-Mar-10 X X X X XNMZ4306000-10X (6) N/A N/A 05-Mar-10 X X X X XRS4-3000460(1)(4)(5)N/A 14000 N/A X X X X XRS4-3000460-01(1)(4)(5)N/A 14000 N/A X X X X XRS4-3000460-02(1)(4)(5)N/A 14000 N/A X X X X XRS4-3000460-03(1)(4)(5)N/A 14000 N/A X X X X XNATA 29-24 HYDRAULIC POWER – GREEN AUXILIARY HYDRAULIC POWER (FIG. 12)N Ram Air Turbine (RAT)758546 N/A 40000 N/A XXXXXN759123 N/A 40000 N/A X X X X XN762956 N/A 40000 N/A X X X X XN762973 N/A 40000 N/A X X X X XN764239 N/A 40000 N/A X X X X XN766351 N/A 40000 N/A X X X X XN768084 N/A 40000 N/A X X X X XN770379 N/A 40000 N/A X X X X XN770952 N/A 40000 N/A X X X X XN770952A N/A 40000 N/A X X X X XN770952B N/A 40000 N/A X X X X XN1702934 N/A 40000 N/A X X X X XN1702934A N/A 40000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 6EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 13 to 15 & 23 to 24)RMAIN STRUT AND DRESSINGS (FIG. 13 & 15)Notes (1) to (6): Refer to DGAC-F 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 (onlythis 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 A340-200 MSN 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 differentPNR. MOD 46904 factory embodied on original landing gear of MSN 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.N (10) Life limit is the later of 900 aircraft FH counted from 08-Jul-2009 or the accumulation of 11150 total LDG since initial entry into service of Pin W1 on any aircraft.N (11) Life limit is the earlier of the 10-year calendar limit or the limitation deduced from note (10).N (12) Embodiment of MOD 58527/SB A340-32-4273 introduces a different PNR.Pin W201275796 (7) N/A 20000 10 Ye XX-313 -312/-313 -313Retraction link (LH)201275317 (9) N/A 35200 36 Mo XX-313 -312/-313 -313R201489311 (12) N/A 8400 N/A X X -313 -312/-313 -313Retraction link (RH)201275318 (9) N/A 35200 36 Mo XX-313 -312/-313 -313R201489312 (12) N/A 8400 N/A X X -313 -312/-313 -313R Pin W1201275673 (7)(11) N/A (10) 10 Ye XX-313 -312/-313 -313N201478614 N/A (10) N/A X X -313 -312/-313 -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 7EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction bracket (LH)201428305 N/A (1) N/A excl. 204 X201428307 N/A (1) N/A excl.204 X201428318 N/A (1) N/A excl.204 X201428323 N/A (1) N/A excl.204 X201428331 (2) N/A (1) N/A excl. 204 X201428331 (6) N/A 9000 N/A excl. 204 X201428333 N/A (1) N/A excl.204 X201428335 N/A (1) N/A excl.204 X201428338 (4) N/A (1) N/A excl. 204 X201428351 N/A 30500 N/A X X -313 -312/-313 -313201428378 N/A 30500 N/A X X -313 -312/-313 -313Retraction 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 X201428336 N/A (1) N/A excl.204 X201428339 (5) N/A (1) N/A excl. 204 X201428352 N/A 30500 N/A X X -313 -312/-313 -313201428379 N/A 30500 N/A X X -313 -312/-313 -313Pin W2201275667 (8)N/A 4500 5 Ye excl. 204 XN/A 9400 5 Ye 204 -313 -312/-313 -313Pin P201275602 (7) N/A 20000 10 Ye XX-313 -312/-313 -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 8EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRRETRACTION ACTUATOR (FIG. 24)Retraction actuator piston rod 114256309 N/A 8080 N/A XX-313 -312/-313 -313114256321 N/A 8080 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 -313Retraction actuator cylinder 114256310 N/A 22900 N/A XX-313 -312/-313 -313114256320 N/A 22900 N/A X X -313 -312/-313 -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 9EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xNATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 25)NPitotProbeC16195AA 90000 2000007-Jan-10 X X X X XNATA 35-13-00 OXYGEN – CREW OXYGEN –CONTROL AND INDICATING (FIG. 29)NPressureswitch CMK80-01 80000 N/A 20Ye X X X X XNATA 35-23-00 OXYGEN – PASSENGEROXYGEN (GAZEOUS) – CONTROL AND INDICATING (FIG. 30)N Quantity calculation control unit E69027 80000 N/A 20 Ye XXXXXAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 10EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS)HYDRAULIC ACTUATION (FIG. 09)(1) Equipment installed new in production as per MOD 50487.R THS Actuator (1)47175-200 N/A 4730 N/AXXAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 11EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHLDGCal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 32-11-00 MAIN LANDING GEAR (FIG. 13 to 15 & 23 to 24)RRETRACTION ACTUATOR (FIG. 24)Retraction actuator piston rod 50-1231002-01 N/A 6090 N/AXXXXRATA 32-15-00 CENTER LANDING GEAR (FIG. 16, 17 & 20)RRETRACTION ACTUATOR (FIG. 20)(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 cylinder50-1104001-00 N/A 7800 N/AXXRetraction actuator piston rod 55-1104003-00 (1) N/A 3000 42 Mo XXRATA 32-21-00 NOSE LANDING GEAR (FIG. 19 & 22)RRETRACTION ACTUATOR (FIG. 22)(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 XXRetraction actuator cylinder50-1026001-00 N/A 10300 N/AXXAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-1PAGE: 12EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340NNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.NN(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNNomenclature PartNumberFHFCCal.A340-54x A340-64xNWV00x WV10x WV00x WV10xNATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 25)NPitotProbeC16195AA 90000 2000007-Jan-10 X X X XEND OF SUB-PART 4-2-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 13EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A3402. Sub-part 4-2-2 DEMONSTRATED LIFE LIMITATIONSA. A340-200/-300 SERIESNote: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 27-14 FLIGHT CONTROL – AILERON AND HYDRAULIC ACTUATION (FIG. 02)RN(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 80000 20000 N/A X X X X XR3337457-60 80000 20000 N/A X X X X XNC38661-002 80000 20000 N/A X X X X XROutboard aileron servo-control(1)3337458-59 80000 20000 N/A X X X X XR3337458-60 80000 20000 N/A X X X X XNC38657-002 80000 20000 N/A X X X X XNATA 27-22 FLIGHT CONTROL – RUDDER TRIM ACTUATION AND ARTIFICIAL FEEL (FIG. 03)N Rudder Trim Actuator (RTA) 6197-1 90000 20000 N/A XXXXXN6197-2 90000 20000 N/A X X X X XNATA 27-23 FLIGHT CONTROL – RUDDER AND PEDALTRAVEL LIMITING ACTUATION (FIG. 04)NRudder Travel Limitation Unit(RTLU)341400M02 90000 20000 N/A X X X X XN343500M00 90000 20000 N/A X X X X XNPedal Travel Limitation Unit(PTLU)341400M02 90000 20000 N/A X X X X XN343500M00 90000 20000 N/A X X X X XNATA 27-24 FLIGHT CONTROL – RUDDERHYDRAULIC ACTUATION (FIG. 05)NRudderservo-control SC5300 80000 20000 N/A X X X X XNSC5300-1 80000 20000 N/A X X X X XNSC5300-2 80000 20000 N/A X X X X XN.../...SC5300-3 80000 20000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 14EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xNRudderservo-control SC5300-4 80000 20000 N/A X X X X XNATA 27-26 FLIGHT CONTROL – YAW DAMPER ACTUATION (FIG. 06 & 07)NYawdamperservo-control SC4710 80000 20000 N/A X X X X XNSC4710-1 80000 20000 N/A X X X X XNBack-up Yaw Damper Unit(BYDU)41800831001 90000 20000 N/A X X X X XN41800831002 90000 20000 N/A X X X X XN41800831100 90000 20000 N/A X X X X XRATA 27-34 FLIGHT CONTROL – ELEVATORAND HYDRAULIC ACTUATION (FIG. 08)R (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 80000 20000 N/A X X X X XRSC4800-94 80000 20000 N/A X X X X XNSC4800-104 80000 20000 N/A X X X X XNSC4800-114 80000 20000 N/A X X X X XRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS)HYDRAULIC ACTUATION (FIG. 09)RN(1) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906)and retrofitted into PNR 47147-500by SB A340-27-4099 (MOD 49591).Life limitation to be applied from the time of retrofitinto PNR 47147-400 (SB A340-27-4059) for THSA subsequently retrofittedinto PNR 47147-500 (MOD49591/SB A340-27-4099). Nevertheless, the sum of the accumulated lives PRE and POST SB A340-27-4059 must not exceed 80000 FH/20000 FC, whicheveroccurs first.NNNNN(2) Life limitation to be applied from initial entry into service for THSA originally manufactured as PNR 47147-400 (MOD 45906)and retrofitted into PNR 47147-500by SB A340-27-4099 (MOD 49591) and subsequently retrofitted to PNR 47147-700 by SB A340-27-4143 (MOD 54881).Life limitation to be applied from the time of retrofitinto PNR 47147-400 (SB A340-27-4059) for THSA subsequently retrofittedinto PNR 47147-500 (MOD49591/SB A340-27-4099) then retrofitted to PNR 47147-700 by SB A340-27-4143 (MOD 54881). Nevertheless, the sum of the accumulated lives PRE and POSTSB A340-27-4059 must not exceed 80000 FH/20000 FC, whichever occurs first.THS Actuator47147-500 80000 20000 N/A X (1) X (1) X (1) X (1) X (1)N47147-700 80000 20000 N/A X (2) X (2) X (2) X (2) X (2).../...47172-300 80000 20000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 15EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHFCCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xTHSActuator 47172-500 80000 20000 N/A X X X X X47172-510 80000 20000 N/A X X X X XNATA 27-64 FLIGHT CONTROL – SPOILERHYDRAULIC ACTUATION (FIG. 11)NSpoiler servo-controlposition 11387A0000-01 80000 20000 N/A X X X X XN1387A0000-02 80000 20000 N/A X X X X XN1387B0000-01 80000 20000 N/A X X X X XN1387B0000-02 80000 20000 N/A X X X X XN1387C0000-01 80000 20000 N/A X X X X XNMZ4339390-12 80000 20000 N/A X X X X XNSpoiler servo-controlpositions 2 to 61386A0000-01 80000 20000 N/A X X X X XN1386A0000-02 80000 20000 N/A X X X X XN1386B0000-01 80000 20000 N/A X X X X XN1386B0000-02 80000 20000 N/A X X X X XN1386C0000-01 80000 20000 N/A X X X X XNMZ4306000-12 80000 20000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 16EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRATA 32-11-00 MAIN LANDING GEAR (FIG. 13 to 15 & 23 to 24)RMAIN STRUT AND DRESSINGS (FIG. 13 & 15)(1) This PNR is common to pin W2 and pin P.Pin W201478613 N/A 42800 N/A X X -313 -312/-313 -313201489770 N/A 42800 N/A X X -313 -312/-313 -31355-2105061-00 N/A 30000 N/A -313N Retraction link (LH)201489315 N/A 10700 N/A XX-313 -312/-313 -31350-2105026-00 N/A 30000 N/A -31350-2105224-00 N/A 30000 N/A-312/-313 -313N Retraction link (RH)201489316 N/A 10700 N/A XX-313 -312/-313 -31350-2106026-00 N/A 30000 N/A -313D50-2106224-00N/A30000N/A-312/-313-313Pin W155-2105060-00 N/A 30000 N/A-312/-313 -313Retraction bracket (LH)201428380 N/A 30500 N/A excl. 204 X201428382 N/A 30500 N/A excl.204 X201428384 N/A 30500 N/A excl.204 X201478303 N/A 30500 N/A excl.204 X201478305 N/A 30500 N/A excl.204 X201478307 N/A 30500 N/A excl.204 X50-2105027-00 N/A 30000 N/A-312/-313 -313Retraction bracket (RH)201428381 N/A 30500 N/A excl. 204 X201428383 N/A 30500 N/A excl.204 X201428385 N/A 30500 N/A excl.204 X201478304 N/A 30500 N/A excl.204 X.../...201478306 N/A 30500 N/A excl.204 XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 17EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction bracket (RH)201478308 N/A 30500 N/A excl. 204 X50-2106027-00 N/A 30000 N/A-312/-313 -313Pin W2201478615 N/A 42800 N/A X X -313 -312/-313 -313201478637 N/A 42800 N/A X X -313 -312/-313 -31355-2105059-00 (1) N/A 30000 N/A-312/-313 -313Pin P201478612 N/A 42800 N/A X X -313 -312/-313 -31355-2105059-00 (1) N/A 30000 N/A-312/-313 -313RCOMPLETE SIDE STAY (FIG. 13, 15, 23 & 24)Lock stay actuator pin201440611 N/A 25000 N/A excl. 204 X201457606 N/A 25000 N/A excl.204 XRLOCK STAY ACTUATOR (FIG. 23)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. 24)(1) Must be replaced by a new one every timethe piston head is removed from the piston rod.Retraction actuator piston rod 114256323 N/A 5500 N/A XX-313 -312/-313 -31350-2113002-00 N/A 20000 N/A-312/-313 -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 18EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator gland114256312 N/A 50000 N/A XX-313 -312/-313 -313114256322 N/A 50000 N/A X X -313 -312/-313 -31350-2113004-00 N/A 20000 N/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 -31350-2113003-00 N/A 20000 N/A-312/-313 -313Retraction actuator insert114256629 N/A (1) N/A XX-313 -312/-313 -313Retraction actuator cylinder 50-2113001-00 N/A 20000 N/A-312/-313 -313RATA 32-21-00 NOSE LANDING GEAR (FIG. 18 & 21)(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-313F53112357204xx 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 -313NF53120422200xx N/A 25000 N/A-312/-313 -313RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 21)Retraction actuator pin(Main fitting side)D61686100000 25000 N/A X X-312/-313 -3137500037500N/A-313RRETRACTION ACTUATOR (FIG. 21)Retraction actuator eye endD62588N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D62588-1N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 19EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator eye endD67840N/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 -313N/A 37500 N/A -313D67837N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator plugD61952N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D61952-1N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D67838N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313Retraction actuator cylinderD62587N/A 25000 N/A X X -312/-313 -313N/A 37500 N/A -313D62587-1N/A 25000 N/A X X -312/-313 -313.../...N/A 37500 N/A -313AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 20EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system areprovided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*) LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-21xA340-31xWV00x WV027 Other WV02x WV05xRetraction actuator cylinderD67836N/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: DEC 15/09ALS PART 4-2-2PAGE: 21EASAAPPROVED© AIRBUS SAS 2009. 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 PartNumberFHFCCal.A340-21xA340-31xNWV00x WV027 Other WV02x WV05xNATA 34-11-00 NAVIGATION – SENSORS, POWER SUPPLY AND SWITCHING (FIG. 25 & 26)NPitotProbeC16195BA 90000 20000 N/A X X X X XN Sensor – Angle Of Attack45150320 90000 20000 N/A XXXXXNC16291AA 90000 20000 N/A X X X X XNATA 34-21-00 NAVIGATION – ALTITUDE AND AIRSPEED STANDBY DATA (FIG. 27)NAltimeterStandby 64141-582-1 90000 20000 N/A X X X X XN64141-590-1 90000 20000 N/A X X X X XNIndicatorStandbyAirspeed 64050-868-1 90000 20000 N/A X X X X XNATA 34-22-00 NAVIGATION – ATTITUDE AND HEADING STANDBY DATA (FIG. 28)NIndicatorStandbyHorizon 501-1568-34 90000 20000 N/A X X X X XNH321BHM1 90000 20000 N/A X X X X XNH341BVM 90000 20000 N/A X X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 22EASAAPPROVED© AIRBUS SAS 2009. 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.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHFCCal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 27-44 FLIGHT CONTROL – TRIMMABLE HORIZONTAL STABILIZER (THS)HYDRAULIC ACTUATION (FIG. 09)(1) Equipment installed new in production as per MOD 52274.(2) Equipment installed new in production as per MOD 54882.THS Actuator47175-300 (1) 50000 10000 N/AXXXX47175-500(2) 50000 10000 N/A X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 23EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-54x A340-64xWV00x WV10x WV00x WV10xRATA 32-11-00 MAIN LANDING GEAR (FIG. 13 to 15 & 23 to 24)RMAIN STRUT AND DRESSINGS (FIG. 13 & 15)(1) This PNR is common to pin W2 and pin P.PinW55-1205156-03 N/A 20600 N/A X X X XRetraction link (LH)50-1205288-01 N/A 20600 N/AXXXXRetraction link (RH)50-1206288-01 N/A 20600 N/AXXXXPinW155-1205154-00 N/A 20600 N/A X X X XRetraction bracket (LH)50-1205007-00 N/A 20600 N/AXXXXRetraction bracket (RH)50-1206007-00 N/A 20600 N/AXXXXPin W255-1205151-00 (1) N/A 20600 N/AXXXXPin P55-1205151-00 (1) N/A 20600 N/AXXXXRRETRACTION ACTUATOR (FIG. 24)(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/AXXXXRetraction actuator gland50-1231004-02 N/A 10000 N/AXXXXRetraction actuator piston head 50-1231003-00 N/A 10000 N/AXXXXRetraction actuator insert114256629 N/A (1) N/AXXXXRetraction actuator cylinder50-1231001-00 N/A 10000 N/AXXXXRATA 32-15-00 CENTER LANDING GEAR (FIG. 16, 17 & 20)(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: DEC 15/09ALS PART 4-2-2PAGE: 24EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-54x A340-64xWV00x WV10x WV00x WV10xRLEG EQUIPPED (FIG. 16)RMAIN FITTING-SHOCK ABSORBER STRUCTURE (FIG. 16 & 20)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. 17 & 20)Unlock actuator pin (drag stay)55-1110052-00N/A 13100 N/A X XN/A 10300 N/A X XRLOCK LINK (FIG. 17)Unlock actuator pin (lock link)55-1110052-00N/A 13100 N/A X XN/A 10300 N/A X XRUNLOCK ACTUATOR (FIG. 17)Unlock actuator rod end55-1113006-00 N/A 20600 N/AXX55-1113006-01 N/A 20600 N/A X X X XUnlock actuator piston rod55-1113003-00 N/A 20600 N/AXX55-1113003-01 N/A 20600 N/A X X X XUnlock actuator gland55-1113016-00 N/A 20600 N/AXX55-1113016-01 N/A 20600 N/A X X X XUnlock actuator cylinder55-1113001-00 N/A 20600 N/AXX55-1113001-01 N/A 20600 N/A X X X XRRETRACTION ACTUATOR (FIG. 20)Retraction actuator cylinder50-1104001-01 N/A 20600 N/AXXXXRetraction actuator piston rod 55-1104003-01 N/A 20600 N/AXXXXRetraction actuator piston head 50-1104005-01 N/A 1400 N/AXX55-1104036-00 N/A 20600 N/A X X X XAIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-2-2PAGE: 25EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Note: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.R(*) Whichever occurs first.Explanation notes are located under the assy title.LIFE LIMITATIONS (*)LIFE LIMITATIONS APPLICABILITYNomenclature PartNumberFHLDGCal.A340-54x A340-64xWV00x WV10x WV00x WV10xRetraction actuator piston rod nut 55-1104008-00 N/A 20600 N/AXX55-1104008-01 N/A 20600 N/A X X X XRetraction actuator bearing50-1104010-01 N/A 20600 N/AXX50-1104010-02 N/A 20600 N/A X X X XRATA 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)F53115740000xx N/A 16600 N/A X X XF53115982000xx N/A 16600 N/A X X X XRNOSE LANDING GEAR LEG (FIG. 19 & 22)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. 22)Retraction actuator piston rod 55-1026003-01 N/A 20600 N/AXXXXRetraction actuator bearing55-1026010-01 N/A 20600 N/AXX55-1026010-02 N/A 20600 N/A X X X XRetraction actuator piston head 55-1026005-01 N/A 1400 N/AXX55-1026033-00 N/A 20600 N/A X X X XRetraction actuator piston rod nut 55-1026008-00 N/A 20600 N/AXX55-1026008-01 N/A 20600 N/A X X X XRetraction actuator cylinder50-1026001-01 N/A 20600 N/AXXXXEND OF SUB-PART 4-2-2AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-3-1PAGE: 1EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340Sub-part 4-3 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS1. Sub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTRRRRR274400-00001-1-E 311312THSA– FIG. 09Detailed 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 R02AMM 27-44-5147147-50047172-300PRE MOD55780PRE SBA340-27-4136PRE SBA340-27-4143RRRRRRRRR274400-00001-2-E 311312THSA– FIG. 09Detailed 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 27-44-5147172-500 POST SBA340-27-4136PRE MOD52269ORPOST SBA340-27-4136PRE SBA340-92-4056AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-3-1PAGE: 2EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTRRRRRRRRRRRRRR274400-00001-3-E 311312THSA– FIG. 09Detailed 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 27-44-5147172-510 POST MOD55780PRE MOD52269ORPOST MOD55780PRE MOD56056ORPOST MOD55780PRE SBA340-92-4056NNNNNNNNNNN274400-00001-4-E 311312THSA– FIG. 09Detailed 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 SBA340-27-4143PRE MOD52269ORPOST SBA340-27-4143PRE SBA340-92-4056RR274400-00002-1-E 311312THSA– FIG. 09Lubrication of the THSA ball-nut.Note: No short-term extension is allowed.700 FHNote700 FHNoteAMM 12-22-27/301 47147-50047147-70047172-30047172-50047172-510A340-200ORA340-300AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-3-1PAGE: 3EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A340ALS PART 4 MAINTENANCE TASKSLIMITATIONS(Whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFTNNNNNNNNNNNNN2924000-00001-1-E 633 Auxiliary Hydraulic Power – FIG. 12Removal of Ram Air Turbine (RAT) foroverhaul.20 Ye100000 FH20 Ye100000 FHAMM 292452/401CMM 29-21-31758546759123762956762973764239766351768084770379770952770952A770952B17029341702934AA340-200ORA340-300END OF SUB-PART 4-3-1AIRWORTHINESS LIMITATIONS SECTIONISSUE: DEC 15/09ALS PART 4-3-2PAGE: 4EASAAPPROVED© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document.A3402. Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONS APPLICABILITYTask Number Zone DescriptionThreshold IntervalPNR AIRCRAFT275000-00001-1-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-2007Note 1N/A SB A340-27-4151AMM 27-54-56AMM 27-54-57N/A Up to MSN0185 inclusive275000-00001-2-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 in accordance withSB A340-27-4151. Report inspectionsresults, whatever they are, toAIRBUS. Repetitive inspections inaccordance with SB A340-27-4152.16-Aug-2009Note 16 YeNote 1SB A340-27-4151SB A340-27-4152AMM 27-54-56AMM 27-54-57N/A Up to MSN0415 inclusiveexcept MSN0385 and 0395RRR275000-00001-3-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)onwardsEND OF SUB-PART 4-3-2

# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: DEC 15/09 ALS PART 4 HISTORY FILE PAGE: 1/4

© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document. 

# A340

1- GENERAL

A340 ALS Part 4 revision 00:

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

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

the requirements of the following Airworthiness Directives (AD):

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

− French DGAC CN 2001-529(B)R1, and

− French DGAC CN 2001-549(B)R1, and

− French DGAC CN F-2002-415(B)R2, and

− French DGAC CN F-2003-141(B), and

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

− EASA AD 2007-0308, and

− EASA AD 2008-0026.

A340 ALS Part 4 revision 01:

The A340 ALS Part 4 Revision 01 has been primarily produced to introduce new limitations into

ALS Parts 4-2 and 4-3 resulting from the Intermediate Service Goal (ISG) activities (Mod

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

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

− CN F-2003-141(B)R1, and

− AD 2007-0008, and

− AD 2007-0011, and

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

− AD 2008-0160, and

− AD 2009-0138, and

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

2- SUMMARY OF CHANGES:

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

4 (revision 00).

New items:

RECORD OF REVISIONS:

Introduction of transition phases between A340 ALS Part 4 revisions 00 and 01 for airworthiness

limitations not subject to exceptions. Exceptions listed.

Indication of the origin to apply for modified intervals.

# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: DEC 15/09 ALS PART 4 HISTORY FILE PAGE: 2/4

© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document. 

# A340

SUB-PART 4-0:

− 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 A340-200 WV021, A340-300 WV027 and A340-300

WV050 series. Associated rules included.

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

detail part numbers added to paragraph 3A.

SUB-PART 4-1:

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

SUB-PART 4-2:

− Introduction of new items:

− Pressure reducers PNR D41428 and PNR E62691-00,

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

− Pedal Travel Limitation Units (PTLU) PNR 341400M02 and PNR 343500M00,

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

and PNR SC5300-4,

− Yaw damper servo-controls PNR SC4710 and PNR SC4710-1,

− Back-up Yaw Damper Unit (DYDU) PNR 41800831001, PNR 41800831002 and PNR

41800831100,

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

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

770952B, PNR 1702934 and PNR 1702934A,

− Pitot probes: PNR C16195AA and PNR C16195BA,

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

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

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

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

− Pressure switch PNR CMK80-01.

− Quantity control unit PNR E69027.

# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: DEC 15/09 ALS PART 4 HISTORY FILE PAGE: 3/4

© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document. 

# A340

− Introduction of new PNR of:

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

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

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

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

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

− THS Actuator: PNR 47147-700,

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

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

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

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

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

01X, PNR MZ4306000-02X, PNR MZ4306000-10X and PNR MZ4306000-12.

− MLG retraction links: PNR 201489315 and PNR 201489316,

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

SUB-PART 4-3:

− Task 274400-00001-4-E.

− Task 292400-00001-1-E.

Amendments:

SUB-PART 4-2:

− Figures numbers amended for each components/items.

− Aileron servo-controls: Limits applicability extended to all positions (active and damping).

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

3337457-60.

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

3337458-60.

− Elevator servo-controls: Clarification of limits applicability (all positions, active and

damping). Life limits amended for PNR SC4800-7A and PNR SC4800-9.

− THSA PNR 47175-200: Life limit applicability corrected (extended to A340-500 WV000’s).

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

# AIRWORTHINESS LIMITATIONS SECTION

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: DEC 15/09 ALS PART 4 HISTORY FILE PAGE: 4/4

© AIRBUS SAS 2009. All rights reserved. Confidential and proprietary document. 

# A340

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

− Task 275000-00001-3-E: Reference to SB A340-27-5040 added.

Deletions:

SUB-PART 4-0:

None.

SUB-PART 4-1:

None.

SUB-PART 4-2:

None.

SUB-PART 4-3:

None.