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ALS Part 4 

- Ageing Systems Maintenance 

© AIRBUS SAS 2008. All rights reserved. Confidential and propnetary 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 

supphed. 

REVISION: 00 
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ALS PART 4 

AGEING SYSTEMS MAINTENANCE 

LIST OF EFFECTIVE PAGES 

PART MVT PAGE ISSUE PART MVT PAGE ISSUE 

4 N 1-LEP JAN 08/08 

4 N 1-TOC JAN 08/08 

4 N 1-ROR JAN 08/08 

4-0 N 1 JAN 08/08 

4-0 N 2 JAN 08/08 

4-0 N 3 JAN 08/08 

4-0 N 4 JAN 08/08 

4-0 N 5 JAN 08/08 4~0 N 6 JAN 08/08 

4-0 N 7 JAN 08/08 

4-0 N 8 JAN 08/08 

4-0 N 9 JAN 08/08 

4-0 N 10 JAN 08/08 

4-0 N 11 JAN 08/08 

4-0 N 12 JAN 08/08 

4-1 N 1 JAN 08/08 

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4-1 N 4 JAN 08/08 

4-1 N 5 JAN 08/08 

4-1 N 6 JAN 08/08 

4-2 N 1 JAN 08/08 

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4-2 N 3 JAN 08/08 

4-3 N 1 JAN 08/08 

4-3 N 2 JAN 08/08 

ISSUE: JAN 08/08 ALS PART 4 PAGE· 1-LEP 

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ALS PART 4 

AGEING SYSTEMS MAINTENANCE 

TABLE OF CONTENTS 

SUBJECT 

RECORD OF REVISIONS 

INTRODUCTION 

ILLUSTRATIONS 

SYSTEMS LIFE-LIMITED COMPONENTS 

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 

ISSUE· JAN 08/08 ALS PART 4 

@AIRBUS SAS 2008. All rights reserved. 

PART 

ROR 

4-0 

4-1 

4-2 

4-3 

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ALS PART4 

AGEING SYSTEMS MAINTENANCE 

RECORD OF REVISIONS 

The European Aviation Safety Agency (EASA) approves the ALS Part 4. Variations must 

also be approved (unless justified in accordance with a procedure stated herein). 

REVISION SUB-PARTS APPROVED BY EASAAD INSERTION IN 

NUMBER EASA MAINT. PROG. 

ROR 

00 4-2 JAN 08/08 

4-3 

Note: The ALS Part 4 is covered by the certification document OOD050AM094/C01 

Revision 00 is approved by EASA under reference N° EASA.A.C.07695 Rev 1. 

REVISION 00 COMPLIANCE TIME: 

1. Except as provided in paragraph 2. of this Record Of Revisions (ROR), it is mandatory to 

adhere to the airworthiness limitations as defined in the sub-parts 4-2 and 4-3 of the 

A318/A319/A320/A321 ALS Part 4 revision 00 from January 08, 2009. 

2. It is mandatory to comply with the following airworthiness limitations defined in the sub-part 

4-2 or 4-3 of the A318/A319/A320/A321 ALS Part 4 revision 00: 

From January 08, 2008 for: 

All the limitations listed in the sub-part 4-2, 

ASM task ref. 324400-0001-1-E for brake accumulator 

ALS PART 4 

------------------------EASAAPPROVEn------------------------

ISSUE: JAN 08/08 PAGE: 1-ROR 

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Sub-part 4-0 INTRODUCTION 

1. GENERAL 

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

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

person may operate an aircraft to which an ALS applies except in accordance with 

the requirements of that ALS, unless otherwise agreed with the Authority of the State 

of aircraft registry. 

C{)nsultation 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. Ageing Systems Maintenance (ASM). 

Airbus' definition of Ageing Systems Maintenance (ASM) refers to limitations applicable 

to aircraft systems that operate beyond their original qualification. Beyond this point, 

ageing effects may affect the characteristics leading to an increased potential for 

failure. The maintenance associated with failure conditions shown to be sensitive to the 

ageing effects on system components are subject to limitations. 

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

the maintenance actions together with their limitations to help to qualify the systems 

installations for continued operation up to the Limit Of Validity shown hereafter. 

Limitations quoted in the ALS Part 4 are applicable to the undamaged and unrepaired 

aircraft systems installations. They may need to be adjusted in case of damage/repair. 

This document was defined by a process agreed between Airbus and the European 

Aviation Safety Agency (EASA). This document replaces the need for individual 

Airworthiness Directives (AD) that would otherwise be needed for such limitations. 

8 Limit Of Validity (LOV). 

Operation of aircraft systems up to the stated Limit Of Validity (In FH or FC, 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. 

Aircraft series LOV (whichever occurs first) 

FH FC 

A318-100 I 60000 48000 

A319-100 excluding Corporate Jet operations I 60000 48000 

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Aircraft series LOV (whichever occurs first} 

FH FC 

A319-1 00 Corporate Jet operations 77400 18000 

A320-100 48000 48000 

A320-200 60000 48000 or 80000 (*) 37500 (*) 

A321-100 60000 48000 

A321-200 60000 48000 

(*)Applies only to aircraft POST MOD 37734/SB A320-00-1198. 

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

combination of values extracted from different sets is allowed. 

C. ALS Part 3 and ALS Part 4 correlation 

At time of 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. 

Compliance with the requirements of the ALS Part 3 must be maintained throughout 

the LOV stated in the ALS Part 4, except where any CMR is superseded by AD or a 

requirement of the ALS Part 4. 

D. Origin of ALS Part 4 items. 

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 a previous section 9 of the Maintenance Planning Document. 

Items previously listed in the ALS Part 1. 

Life extension study (Change in LOV). 

Continued Airworthiness (operational safety) issues (in-service experience). 

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

Components listed under this sub-part are those having a life limitation, due to the 

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

contribute to an unsafe condition of the airplane. 

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

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

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

airplane. These limitations are determined in consideration of the probability of an 

aircraft system level failure condition or conditions. 

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Note: Credit may be taken for the Maintenance Review Board Report (MRBR) Systems 

and Powerplant section maintenance tasks, providing that they are performed 

with the same inspection level, as frequently, or more frequently, than the 

inspection threshold and interval quoted in this document. 

Sub-parts 4-3-1 and 4-3-2 give maintenance requirements 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 i_tem, not the aircraft, reaching the 

limitation. 

When items given in sub-part 4-3-1 reach the stated 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 accumulated the stated 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 limitation. 

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

stated threshold/interval. 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 items listed 

uncJer sub-part 4-2 at or prior to whichever of the life limitations occurs first, after 

any necessary adjustment of the stated life limitation In accordance with the 

instructions of sub-part 4·0 paragraph 3.C. 

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. 

Therefore, It Is necessary to assure traceabi lity and monitoring of the 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. 

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For a given item of the sub-parts 4-2 and 4-3-1, new part numbers may be introduced 

in the future. These new part numbers may not be listed in the sub-parts 4-2 and 4-3-1 

of the current revision of the ALS Part 4. 

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

whatever their detail part number in case of future introduction in the ALS Part 4. 

For further guidance, Operators are requested to contact Airbus. 

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

demonstrate the history of items back to initial entry into service, so that 

limitations are accurately applied. Traceability records may comprise, but are not 

limited to, the following: 

Application history (aircraft type, model, 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 an item may 

have been fitted). 

H. Disposal/quarantine action. 

When the items listed in the sub-part 4-2 reach the life limitations, disposal/quarantine 

action must be taken: appropriate means must be implemented to deter their 

installation on aircraft pending possible extension of their life limitations. Examples of 

means are: 

Record keeping system, 

Non-permanent markings, 

Segregation (ftems 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. 

I. Reporting. 

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

The concept of Continuing Airworthiness includes the reporting of defects and 

other significant maintenance and operational information by the Operator to the 

organisation responsible for the Type Design in accordance with the 

requirements of the State of aircraft registry. 

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 Manufacturer Serial Number (MSN) affected. 

Identification of the affected item. 

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Life since new (in FH and/or FC and/or LOG and/or calendar time, as applicable) 

accumulated by the affected system/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. 

J Production/Repair concessions and Alternative Means Of Compliance. 

Limitations of the ALS sub-part 4-2 and 4-3 may be negated by instructions given in 

either a Production or Repair concession, or an Alternative Means 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 limitations evolve in a revision of the ALS Part 4 subsequent to the issuance 

date of the Produc1ion or Repair concession/AMOC, Operators are requested to 

contact Airbus for guidance. 

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

depend on the 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 SIL 05-009). 

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, restriction of limitation(s), if any, are indicated in EASA Form 1 block 

13 (directly or by reference to another document) 

K. Modifications/Repairs not originating from Airbus 

If an aircraft/a sub-assembly/an item has a modification or repair embodied that is not 

of Airbus origin (e.g. 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 limitations. 

When such an aircraft/a sub-assembly/an item ts transferred from one Owner/Operator 

to another, the associated approvals and documents indicating the necessary 

adaptations of limitations must be transferred as well. 

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L. ALS Part 4 applicability. 

Sub-parts 4-2 and 4-3 are approved by the EASA. ALS Part 4 covers the following 

models: 

A318-111 A319-111 A320-111 A321-111 

A318-112 A319-112 A320-211 A321-112 

A318-121 A319-113 A320-212 A321-131 

A318-122 A319-114 A320-214 A321-211 

A319-115 A320-215 A321-212 

A319-131 A320-216 A321-213 

A319-132 A320-231 A321-231 

A319-133 A320-232 A321-232 

A320-233 

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 limitations in Calendar times. 

unless otherwise stated In any delivery documentation to the first Operator. 

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

landings. 

The initial entry into service for the transferable systems items is defined as the date at 

which the item accomplishes the first flight for which it will undertake its intended function 

Note: Unless otherwise stated, this means for transferable items delivered on new aircraft 

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

delivery date/transfer of title date (e.g. as a result of test flights) must be taken Into 

account. 

Calendar times (Cal.): 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 items). 

Exceptional Short Term Extension· An extension in an ASM limitation that may be needed 

to cover an uncontrollable or exceptional unexpected 

situation. 

Flight Cycle (FC) 

Flight Hour (FH)· 

Functional Check 

A complete take-off and landing sequence. 

The accumulated time intervals between ''wheels-off' 

and "wheels-on". 

A quantitative check to determine if an item performs 

one or more of its functions within spec1fied hmits 

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Interval: 

Landing (LOG): 

Limit of Validity (LOV): 

Operational Check: 

Threshold: 

Touch and go· 

The period expressed in usage parameters like FH 

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

between successive accomplishments of a specific 

task. 

An operation of an aircraft touching the runway and 

coming to a complete stop or performing a "touch and 

go". 

The LOV is the time at which the aircraft maintenance 

programme ceases to be valid: The maintenance 

requirements and their limitations contained in the ALS 

Part 4 cease to be valid beyond the LOV indicated in 

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

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. 

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 LOG and/or Calendar time. 

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/LOG, up to threshold 

inspection or between two consecutive inspections. 

3. RULES SPECIFIC TO SUB-PART 4-2 

A. Part Number applicability 

ALS part 4-2 tables provide the applicable limitations only for systems installations that 

have been authorized. These tables do not ensure that a part number has been 

validated for a specific individual aircraft MSN. 

Part numbers are authorized for installation on individual aircraft MSN by Serv1ce 

Bulletins (and the associated modifications) that are published by Airbus. 

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B. Limitation/Replacement time indication. 

(1) General 

In computing 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 item (unless otherwise stated). 

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

Life limitations quoted in sub-part 4-2 are applicable to the undamaged items as 

listed, not to the aircraft on which they are installed. The limitation/replacement 

time indication is quoted on the same line/block of lines as the Part Number. 

C. Transfers of items between applications having different life limitations. 

In case of item transfers between applications (aircraft types, aircraft models, etc ... ) 

with different life limitations. the remaining life for operation must be defined by the use 

of the following formula: 

with: 

Tq = 

Caj = 

Cpj = 

Cpi= 

remaining life for operation on model i (present application) 

accumulated life on previous application j. 

life limitation in previous application j. 

life limitation in present application i. 

Note: when using the above formula Tfj. Caj. Cpj. Cpi are expressed in the same usage 

parameters (FH or FC or LOG): usage parameters can not be mixed in the same 

calculation. 

Where the complete life history of an item is not known, Operators are requested to 

refer to Service Information Letter (SIL 05-009) for guidance. It provides the means to 

manage such items. It has been issued in agreement with the EASA. 

D Limitation applicability. 

limitation applicability may be allocated according to the aircraft MSN affected (for all 

aircraft of the column for sub-part 4-2), e g. 

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

X stands for all aircraft of the column. 

-212 stands for all-212 models of the column 

excl. -113 stands for all a1rcraft of the column excluding the -113 model. 

(2) Aircraft Manufacturer Serial Number, e.g. 

XXX-YYY stands for aircraft MSN XXX to aircraft MSN YYY. 

XYX, XXZ stands for atrcraft MSN XYX and aircraft MSN XXZ 

XZX stands for aircraft MSN XZX only. 

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excl. XXX stands for all aircraft, excluding MSN XXX. 

4 . RULES SPECIFIC TO SUB-PART 4-3 

A. General. 

In computing the life accumulated by the aircraft systems installations/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). 

The limitations must be applied from: 

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

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

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

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

associated with the inspection method used at last inspection. 

B. Sub-part 4-3 layout 

The maintenance requirements 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 Plannmg 

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 organized as follows: 

XXXXXX-MEFYY-Z-E 

XXX XXX 

M 

E 

F 

yy 

z 

E 

ISSUE· JAN 08/08 

is AT A 1 00 task reference. 

is the selection methodologies used. It will always be "0". 

is engine/APU/ ... manufacturer identification (where applicable, "0'' 

is default value) 

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

the same manufacturer is applicable to the program (where 

applicable, "0" is default value). 

is sequential number. 

is for technical solution applicable to the same task requirement 

Is "E" and stands for ASM (i.e. task related to an ageing systems 

function or Enhanced maintenance requirement). 

ALS PART 4-0 PAGE 9 

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(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 concise description of the maintenance task to be performed 

(b) Note. 

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

(4) Threshold/Interval columns. 

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

The interval and threshold 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 technical documentation where maintenance 

practices/procedures necessary for the task accomplishment are provided, e.g. the 

AMM. 

(6) Applicability column 

These columns give the combination of component part number and alrcraft that 

requires the accomplishment of the task. 

{a) Part Number 

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

installations that have been authorised. These tables do not ensure that a part 

number has been validated for a specific individual aircraft MSN. 

Part numbers are authorised for installation on individual aircraft MSN by 

Service Bulletins (and the associated modifications) that are published by 

Airbus. 

(b) Aircraft 

Applicability Task applicable to 

ALL All A318, A319, A320 and A321 aircraft 

A320-xxx A320-xxx series aircraft. 

PRE nnnnn All a1rcraft PRE MOD nnnnn. 

1.e A318/A319/A320/A321 that do not have MOD nnnnn 

embodied. 

POST nnnnn All aircraft POST MOD nnnnn 

i.e. A318/A319/A320/A321 that do have MOD nnnnn 

embodied. 

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Applicability Task applicable to 

POST nnnnn All aircraft POST MOD nnnnn (at least with mod proposal 

Sxxxxx no. Sxxxxx embodied). 

POST nnnnn All aircraft POST MOD nnnnn and POST MOD mmmmm. 

POSTmmmmm i.e. A318/A319/A320/A321 that do have MOD nnnnn and 

MOD mmmmm embodied. 

POST nnnnn All aircraft that do have MOD nnnnn or aircraft that do not 

OR have MOD mmmmm. 

PREmmmmm 

A320-200 All A320-200, or 

OR All A321-100 that do not have MOD nnnnn embodied. 

A321-100 

PRE nnnnn 

A320-200 All A320-200 that do have MOD nnnnn embodied, or 

POST nnnnn All A321-100 that do have MOD nnnnn embodied and do 

OR not have MOD mmmmm embodied. 

A321-100 

POST nnnnn 

PRE mmmmm 

POST nnnnn All aircraft that do have MOD nnnnn embodied. 

(xx-yyyy) (xx-yyyy) is the Service Bulletin reference associated to 

the modification. 

CFM All aircraft equipped with CFM engines. 

IAE All aircraft equipped with IAE engines. 

C. Exceptional short-term extensions for items listed in sub-part 4-3. 

Since sub-part 4-3 intervals are based on statistical averages ancl reliability rates; an 

exceptional short-term extension for a specific 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 limitation, for all limitations identified in the sub-part 4-3, it 

has been accepted by the Primary Certification Office (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 limitations quoted in terms of Flight Hours. 

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

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

be granted on ASM 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 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 

program. 

END OF SUB-PART 4-0 

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Sub-part 4-1 ILLUSTRATIONS 

ISSUE: JAN 08/08 

ATA 29-22 - RAM AIR TURBINE (RAT) 

(Hamilton Sundstrand) - FIG 01 

ALS PART 4-1 

•DAIRBUS SAS 2008. All rights reserved 

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-IIAT EJECTION 

JACK 

ATA 29-22 - RAM AIR TURBINE (RAT) 

(Dowty)- FIG. 02 

ALS PART 4-1 

©AIRBUS SAS 2008. All rights reserved. 

RATOIIOUNO 

CHECI( MODULE 

PAGE· 2 
~ A31 8/A31 9/A320/A32'f 

AIRWORTHINESS LIMITATIONS SECTION 

ATA 29-23- POWER TRANSFER UNIT- FIG. 03 

ISSUE. JAN 08/08 ALS PART 4-1 PAGE- 3 

®AIRBUS SAS 2008. All nghts reserved. 
ISSUE: JAN 08/08 

~ A318/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Ret. actuato1 pin 

(rear spar side) 

Ret. actuator pin 

(malh fitting side) 

I 

L------ --' 

r---- ---, . . I 

I 

. 

I 

I 

. 

I 

I 

ATA 32-10- MLG RETRACTION ACTUATOR- FIG. 04 

ALS PART 4-1 

©AIRBUS SAS 2008. All rights reserved. 

Pislon rod 

PAGE. 4 
~ A3f 8/A3f 9/A320/A32f 

AIRWORTHINESS LIMITATIONS SECTION 

ATA 32-20- NLG DOOR UPLOCK- FIG 05 

ISSUE· JAN 08/08 ALS PART 4-1 PAGE· 5 

@AIRBUS SAS 2008. All rights reserved. 
~ A318/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Air Data Modules are remotely 

mounted near and above the level of 

the pitot and static probes 

B 

ATA 34-12- AIR DATA MODULE - FIG. 06 

END OF SUB-PART 4-1 

ISSUE: JAN 08/08 ALS PART 4-1 

©AIRBUS SAS 2008. All rights reserved. 

PAGE: 6 
~ A318/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Sub-part 4-2 SYSTEMS LIFE LIMITED COMPONENTS 

Explanatory notes are located under each LIFE LIMITATION LIFE LIMITATION APPLICABILITY assembly title. (Wlichever occurs first) 

Nomenclature Part Number FH LDG Cal. A318-100 A319-100 A320-100 A320-200 A320-200 

Twin Bogie 

ATA 29-23-00 HYDRAULIC POWER TRANSFER (FIG 03) 

(1) Thts limit can be extended to 2000 FH if the inspection described in SB A320-29-1027 is applied from 1000 FH on a daily basis without fi

Power Transfer Unit -211 

(PTU) 1000 -212 4101002-3 N/A N/A X -214 X (1) -231 

-232 

-211 

1000 -212 4101002-4 (1) N/A N/A X -214 X -231 

-232 

-211 

-212 

4101002-5 3000 NJA N/A X -214 X 

-231 

-232 

-211 

-212 

4101002-6 3000 N/A N/A X -214 X 

I -231 

-232 

-211 

-212 

4101002-91 2000 N/A N/A X -214 X 

-231 

-232 

ALS PART 4-~ -----------------------------------EASAAPPROVEO-----------------------

ISSUE: JAN 08/08 

©AIRBUS SAS 2008. All nghts reserved. 
A31B/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Explanatory notes are located under each LIFE LIMITATION LIFE LIMITATION APPLICABILITY assembly title. (Whichever occurs first) 

Nomenclature Part Number FH LOG Cal. A318-100 A319-100 A320-100 A320-200 A320-200 

TWin Bogie 

ATA 32-10-00 MAIN LANDING GEAR RETRACTION ACTUATOR (FIG 04) 

{1) Retaining ring P/N 114094611 and P/N 114193606 must be replaced by a new one every time it is removed from the piston head. 

(2) Retaining ring PIN 114193643 must be replaced by a new one every time it is removed from the gland. 

Rel actuator pin {main 114094617 N/A 20000 N/A X 

fitting side) 114094661 N/A 60000 N/A X 

114193631 N/A 20000 N/A X X X X 114193637 N/A 60000 N/A X X X X 

201590900 N/A 60000 N/A X X X X 201590903 N/A 60000 N/A X 

Piston rod 114094303 N/A 60000 N/A X 

114094308 N/A 60000 N/A X 114193601 N/A 60000 N/A X X X X 

201590907 N/A 60000 N/A X 

201590908 N/A 60000 N/A X X X X 

Retaining ring (piston 114094611 N/A (1) N/A X 

rod) 114193606 N/A {1) N/A X X X X 

Piston head 114094608 N/A 60000 N/A X 

114193603 N/A 60000 N/A X X X X 

I 

201590909 N/A 60000 N/A X X X X 201590912 N/A 60000 N/A X 

Piston head nut 114094605 N/A 60000 N/A X 

114193604 N/A 60000 N/A X X X X 

201590910 N/A 60000 N/A X X X X 

201590911 N/A 60000 N/A X 

ALS PART 4-2 

-----------------------------------EASAAPPROVEO-----------------------

ISSUE: JAN 08/08 

©AIRBUS SAS 2008. All rights reseNed. 
~ A31B/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Explanatory notes are located under each LIFE LIMITATION LIFE LIMITATION APPLICABILITY assembly title. (Whichever occurs first) 

Nomenclature Part Number FH LOG Cal. A318-100 A319-100 A320-100 A320-200 A320-200 

Twin Bogie 

Gland 114094604 N/A 60000 N/A X 

114193602 N/A 60000 N/A X X X X 

114193642 N/A 60000 N/A X X X X 

201590913 N/A 60000 N/A X X X X 

201590914 N/A 60000 N/A X 

201590915 N/A 60000 N/A X X X X 

Retaining ring (gland) 114193643 N/A (2) N/A X X X X 

Cylinder 114094600 N/A 60000 N/A X 

114193600 N/A 60000 N/A X X X X 

114193641 N/A 60000 N/A X X X X 

201590904 N/A 60000 N/A X 

201590905 N/A 60000 N/A X X X X 

201590906 N/A 60000 N/A X X X X 

Retraction actuator p1n 114094615 N/A 60000 N/A X 

(rear spar side) 114094635 N/A 60000 N/A X 

114193610 N/A 60000 N/A X X X X 

201590901 N/A 60000 N/A X X X X 

201590902 N/A 60000 N/A X 

ATA 32-20-00 NOSE GEAR AND DOORS (FIG 05) 

Door uplock -211 C24730000-3 N/A 1000 N/A X -212 

·231 

ATA 34-12-00 NAVIGATION (FIG 06) 

1 Air Data Module (ADM) -211 

PG1 152AC02 N/A N/A 3Ye X -212 -231 

-232 

END OF SUB-PART 4-2 

ALS PART 4-2 

---------------------------------------------------------------------------------EASAAPPROVEO----------------------------------------------------

ISSUE: JAN 08/08 

©AIRBUS SAS 2008. All nghts reserved. 
A318/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Sub-part 4-3 SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 

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

ALS PART 4 MAINTENANCE TASKS LIMITATIONS LIMITA

(whichever occurs first) REFERENCE 

Task. Number Zone Description Threshold Interval PI

292200-0000 1-1-E Z195 Ram Air Turbine (RAT) including actuator - 20 Yrs 20 Yrs AMM 292251/401 RAT 

(Hamilton Sundstrand)- FIG. 01 AMM 292253/401 7599

Remove RAT and actuator for overhaul and 7616

replace with new or reconditioned units. CMM 7623

CMM 29-21-42 7623

CMM 29-21-44 7623

7663

7663

Actuator 

7647

7647

292200-00002-1 -E Z195 Ram Air Turbine (RAT) including Ejection Jack 20 Yrs 20 Yrs AMM 292251/401 RAT 

and AGCM - (Dowty) FIG. 02 AMM 292252/401 68020

Remove RAT, Jack and AGCM for overhaul and AMM 292253/401 68020

replace with new or reconditloned units. 680203

CMM 29-21-21 Ejection 

CMM 29-21·24 11416

CMM 29-21-27 114160

I CMM 29-21-28 11416

I AGCM 

76910

7691

ISSUE· JAN 08/08 ALS PART 4-3 

EASAAPPROVEo-----------------------------------

®AIRBUS SAS 2008. All rights reserved. 
$ A318/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4 

AGEING SYSTEMS MAINTENANCE 

HISTORY FILE 

1- GENERAL 

The ALS Part 4 revision 00 has been created at the opportunity of the life extension study for the 

A320-200 aircraft (MOD 37734). Systems-related limitations included in the ALS Part 1 revision 00 

have been transferred to ALS Part 4-2. 

2- SUMMARY OF CHANGES 

The following summarizes the changes with respect to the previous issues of 

A318/A319/A320/A321 ALS Part 4. 

N/A 

ISSUE; JAN 08/08 ALS PART 4 HISTORY FILE PAGE. 1/1 

©AIRBUS SA$ 2008. All rights reserved 
~ A318/A319/A320/A321 

AIRWORTHINESS LIMITATIONS SECTION 

Sub-part 4-3-2 Controlled at atrcraft system level 

ALS PART 4 MAINTENANCE TASKS LIMITATIONS LIMITA

(Whichever occurs first) REFERENCE 

Task Number Zone Description Threshold Interval P/N 

324400-0001-1-E Z190 Parking/Ultimate emergency braking system 60000 FH 60000 FH AMM 324400/501 N/A 

Functional check of the Brake Accumulator 324400-720-002 

system with the Parking Brake not applied 

END OF SUB-PART 4-3 

ALS PART 4-3 

-----------------------------------EASAAPPROVEo-----------------------

ISSUE JAN 08/08 

©AIRBUS SAS 2008. All rights reseNed.