A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

REVISION: 01 

ALS Part 4 

- 

Ageing Systems Maintenance 

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

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

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

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

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

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

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

supplied. 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

ISSUE: JUN 15/12 ALS PART 4 PAGE: 1-LEP 

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

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A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

TABLE OF CONTENTS 

SUBJECT PART

ISSUE: JAN 08/08 ALS PART 4 PAGE: 1-TOC 

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

RECORD OF REVISIONS ROR 

INTRODUCTION 4-0 

ILLUSTRATIONS 4-1 

SYSTEMS LIFE LIMITED COMPONENTS 4-2 

SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS 4-3 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

RECORD OF REVISIONS

ISSUE: JUN 15/12 ALS PART 4 PAGE: 1-ROR 

EASA APPROVED 

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

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

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

procedure stated herein). 

 

REVISION 

NUMBER SUB-PARTS APPROVED BY EASA EASA AD INSERTION IN MAINT. PROG. 

 00 

ROR 

4-2 

4-3 

JAN 08/08 

N 

N 

N 

01 

ROR 

4-2 

4-3 

 JUN 15/12 

Note: The ALS Part 4 is covered by the certification document 00D050AM094/C01 

Revision 01 is approved by EASA under reference 10040191. 

REVISION 01 COMPLIANCE TIME:

1. It is mandatory to comply with the maintenance requirements and airworthiness limitations 

defined in the sub-parts 4-2 and 4-3 of the A318/A319/A320/A321 ALS Part 4 revision 01 

from 15-Jun-2013. 

2. From 15-Jun-2012 to 14-Jun-2013, it is mandatory to comply with the maintenance 

requirements and airworthiness limitations defined in, either: 

− The sub-part 4-2 and 4-3 of the A318/A319/A320/A321 ALS Part 4 at revision 00, 

or 

− The sub-part 4-2 and 4-3 of the A318/A319/A320/A321 ALS Part 4 at revision 01. 

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

previous accomplishment date. 

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A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 1 

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

Sub-part 4-0 INTRODUCTION

1. GENERAL

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

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

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

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

agreed with the Authority of the State of aircraft registry. 

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

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

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

Volume II, Part A, Chapter 3. 

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

considering any variation requests. 

A. ALS Part 4 applicability 

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

listed in the table below: 

 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 

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 replacement) 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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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 2 

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

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

such maintenance requirements and airworthiness limitations to help to qualify the 

systems installations for continued operation up to the operational life applicable to 

A318/A319/A320/A321 systems installations 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 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). 

All the mandatory instructions and airworthiness limitations indicated in this document 

was defined by a process agreed between Airbus and the European Aviation Safety 

Agency (EASA). 

The publication of this document precludes the necessity to publish individual 

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

C. Operational life applicable to A318/A319/A320/A321 systems installations 

Operation of aircraft systems up to the stated operational life (in FH or FC, whichever 

occurs first) is covered by this document. The relevant operational life values are stated 

below. The aircraft systems must not be operated beyond these values unless the 

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

defined operational life extension. 

R 

Aircraft series 

Operational life 

 (whichever occurs first) 

R Flight Hours (FH) Flight Cycles (FC)

 A318-100 60000 48000 

 A319-100 excluding Corporate Jet operations 60000 48000 

 A319-100 Corporate Jet operations 77400 18000 

 A320-100 48000 48000 

 

A320-200 or

60000 48000 

 80000 (*) 37500 (*) 

N 120000 (**) 60000 (**) 

 A321-100 60000 48000 

 A321-200 60000 48000 

(*) Applies only to aircraft POST MOD 37734 (SB A320-00-1198) PRE MOD 39020 

(Intermediate Service Goal, ISG) 

(**) Applies only to aircraft POST MOD 39020 (Extended Service Goal 1, ESG1) 

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 

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 3 

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

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

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

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

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

through their location in the ALS Part 3. 

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

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

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

requirements associated to a life limitation less than or equal to the operational life 

applicable to systems installations, due to the difficulty to define a continued/enhanced 

inspection program, and whose failure could contribute to an unsafe condition of the 

aircraft. 

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

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

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

different sets is not permitted. 

Sub-part 4-2-1: Life Limits

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

operational life applicable to systems installations due to failure during tests and whose 

failure could result in an unsafe condition of the aircraft. 

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

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

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

aircraft. 

Where the values are less than the operational life applicable to systems installations, 

tests are still on-going. For these components/items, the life limitation provided is 

temporary, waiting for completion of the tests. If the demonstrated life reaches the 

applicable operational life, it will remain in sub-part 4-2-2. If the component/item fails 

before the applicable operational life, 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 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 

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 4 

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

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 component 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

Not applicable (The maintenance requirements in this sub-part have been transferred 

to A318/A319/A320/A321 ALS Part 3 since revision 01). 

G. Traceability and replacement/maintenance requirements 

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

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

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

limitations. 

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

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

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

Airworthiness limitations (including life limitations) must be adjusted as 

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

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

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

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

Certificate of Airworthiness. 

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

introduced in the future as a result of modifications and/or Airbus Service Bulletin (SB) 

publishes. These new PNRs may not be listed in the sub-parts 4-2 and/or 4-3-1 of the 

current revision of the ALS Part 4. 

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

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

Part 4. 

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 5 

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

For further guidance, Operators are requested to contact Airbus. 

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

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

so that airworthiness limitations are accurately applied. Traceability records 

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

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

Number, etc...), 

− Maintenance actions carried out (Airworthiness Directives, modifications, 

repairs, inspections, etc...), 

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

component/an item may have been fitted). 

Note 2: Where the partial/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. 

Note 3: Traceability and monitoring of component/item listed in sub-part 4-2 is not 

required for consumable component (for which replacement is controlled at 

assembly/aircraft level). 

H. Transfers of components/items between aircraft applications 

The airworthiness limitation(s) for a component/item fitted to an application (aircraft 

type, aircraft model, etc...) may be different when this component/item is transferred to 

another application. In this case, the component’s/item’s remaining operational life 

must be calculated using the following formula: 

with: 

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

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

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

Cpi = component/item’s airworthiness limitation in current application i. 

When a component/item has been installed on an application where the ALS Part 4 

does not impose an airworthiness limitation, the operational life applicable to systems 

installations of the relevant ALS Part 4 for that application must be used. 

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

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

mixed in the same calculation. 

i Cp

j Cp

j Ca

1 i Tr = − ∑ ×

⎥

⎥

⎦

⎤

⎢

⎢

⎣

⎡

⎟

⎟

⎠

⎞

⎜

⎜

⎝

⎛

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 6 

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

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

component’s/item’s airworthiness limitation(s) change(s) for current and/or 

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

I. Disposal/quarantine action 

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

limitations, disposal/quarantine action must be taken depending on the following 

categories: 

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

limits to prevent rework to appear to be airworthy. 

Note 1: Some means may exist to extend their potential life provided they are applied 

prior to reaching the life limit (e.g. Service Bulletin: POST SB PNR in the subpart 4-2-1). 

Note 2: It’s recommended that the organization that mutilates a component/item 

should provide the original manufacturer with the data plate and/or serial 

number and final disposition of the component to maintain the records of serial 

numbers for “retired” certified life-limited components/items or other critical 

components/items. 

For component listed in sub-part 4-2-2 and/or 4-3-1: Appropriate means must be 

implemented to deter their installation on aircraft pending possible extension of the life 

limitations and/or Operational life. Examples of these means are: 

− Record keeping system, 

− Non-permanent markings, 

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

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

to be airworthy. 

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

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

airworthy. 

J. Occurrence Reporting 

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

The concept of Continuing Airworthiness includes the reporting of defects and 

other significant maintenance and operational information by the Operator to the 

organization responsible for the Type Design in accordance with the 

requirements of the State of aircraft registry. 

Accountable persons or organizations shall report to the competent authority and 

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

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

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 7 

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

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

instructions to all owners or Operators. 

“Hazard seriously the flight safety” means any instances where safe operation could 

not be assured or which could lead to an unsafe condition. It typically includes, but is 

not limited to, significant cracking, deformation, corrosion, any evidence of burning, 

electrical arcing, significant hydraulic fluid or fuel leakage and any emergency system 

or total system failure. 

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

− Organization name, 

− Approval reference if relevant, 

− ASM maintenance requirement reference, 

− Aircraft MSN affected, 

− Identification of the affected component/item, 

− Overhaul, life since new (in FH and/or FC and/or landings and/or Calendar time, as 

applicable) accumulated by the affected system/component/item at the time of the 

finding, 

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

orientation, 

− Circumstance of detection and inspection method used. 

Note: Report shall be made as soon as practical, but in any case within 72 hours of 

the organization identifying the condition to which the report relates. (Refer to 

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

K. ALS Part 4 airworthiness limitations 

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

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

in case of damage/repair. 

L. Production/Repair concessions and Alternative Means Of Compliance 

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

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

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

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

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

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

requested to contact Airbus for guidance. 

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

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

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

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

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

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 8 

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

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

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

solution/AV/AMOC. 

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

documentation (Aircraft Inspection Report: “Recordable concessions”). 

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

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

M. Modifications/Repairs not originating from Airbus 

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

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

Certificate EASA.21J.031 and which affects the content of the ALS Part 4, the Operator 

is responsible for obtaining approval by the relevant Airworthiness Authority for any 

necessary adaptations of the airworthiness limitations. For example, Supplemental 

Type Certificates (STC), which have been designed by Airbus Corporate Jet Centre 

(ACJC) or which have been transferred from former Airbus Deutschland, or other entity, 

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

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

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

necessary adaptations of airworthiness limitations must be transferred as well. 

2. DEFINITIONS

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

− The date of Transfer of Title to the first Operator for 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 components/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 components/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 

components/items). 

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 9 

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

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): A complete takeoff and landing sequence. 

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

and “wheels-on”. 

Functional Check: A quantitative check to determine if a component/an 

item performs one or more of its functions within 

specified limits. 

Interval: The period expressed in usage parameters like FH 

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

between successive 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”. 

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

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ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 10 

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

Part numbers are authorized for installation on individual aircraft MSN by SBs (and the 

associated modifications), which are published by Airbus. 

PNR provided by sub-parts 4-2 for ATA 32 items relate to detail parts. They may not all 

be listed in Illustrated Parts Catalogue (IPC) issued by Airbus. This is the case, for 

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

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

replacement PNR, detail PNR and applicable SB: 

Messier-Dowty Ltd Service Bulletin number: 

- 200-32-230 (main landing gear for A318-100, A319-100, A320-100 and A320-

 200 including bogie main landing gear), 

- 201-32-08 (main landing gear for A321-100 and A321-200). 

Detail parts are listed in the relevant Component Maintenance Manuals (CMM). The 

Messier-Dowty SB listed above provides the procurable replacement Part Numbers. 

B. 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 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. Life limitation applicability. 

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

sub-part 4-2), according to: 

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

X stands for all aircraft of the column. 

-212 stands for all -212 models of the column. 

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

R 

R 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

N 

R 

R 

R 

R 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 11 

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

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

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

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

XZX stands for aircraft MSN XZX only. 

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

4. RULES SPECIFIC TO SUB-PART 4-3

A. Airworthiness limitations 

(1) General 

In computing the life accumulated by the aircraft systems components/items, 

calculations must include flight hours and/or flight cycles and/or landings 

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

component/item (unless otherwise stated). 

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

The limitations must be applied from: 

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

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

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

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

one associated with the inspection method used at last inspection. 

B. ALS Sub-part 4-3 layout. 

The maintenance requirements and associated airworthiness limitations are presented 

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

(1) Task Number 

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

Document (MPD) system and is described as follows: 

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

specific main zones located symmetrically to either side of the aircraft 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 

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). 

N 

R 

R 

R 

N 

R 

R 

R 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 12 

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

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 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) 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) that are published by Airbus. 

R 

R 

R 

R 

R 

R 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 13 

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

(b) Aircraft 

Applicability Task applicable to 

ALL All A318, A319, A320 and A321 aircraft. 

A320-xxx A320-xxx series aircraft. 

PRE nnnnn All aircraft PRE MOD nnnnn. 

i.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. 

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

MOD mmmmm embodied. 

POST nnnnn 

OR 

PRE mmmmm 

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

have MOD mmmmm. 

A320-200 

OR 

A321-100 

PRE nnnnn 

All A320-200, or 

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

A320-200 

POST nnnnn 

OR 

A321-100 

POST nnnnn 

PRE mmmmm 

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

All A321-100 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 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 components/items listed in sub-part 4-3. 

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

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

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

objectives declared at Type Certification. 

R 

R 

R 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JUN 15/12 ALS PART 4-0 PAGE: 14 

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

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

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

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

escalation.

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

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

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

be granted without consultation with that office. 

(1) Controlled by Flight Hours (FH) 

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

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

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

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

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

LanDinGs. 

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

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

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

limitations quoted in terms of Months. 

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

may exceptionally be granted. 

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

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

program. 

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

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

description column. 

END OF SUB-PART 4-0 

R 

R 

R 

R 

R 

R 

N 

N 

N 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

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

Sub-part 4-1 ILLUSTRATIONS

ATA 29-22 - RAM AIR TURBINE (RAT) 

(Hamilton Sundstrand) - FIG. 01 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JAN 08/08 ALS PART 4-1 PAGE: 2 

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

ATA 29-22 - RAM AIR TURBINE (RAT) 

(Dowty) - FIG. 02 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

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

ATA 29-23 - POWER TRANSFER UNIT - FIG. 03 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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

Gland 

Ret. actuator pin 

(rear spar side) 

Ret. actuator pin 

(main fitting side)

Piston rod

Nut 

Retaining 

ring (Gland)

Retaining ring 

(Piston rod) 

Cylinder

Piston 

head 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

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

ATA 32-20 - NLG DOOR UPLOCK - FIG. 05 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: JAN 08/08 ALS PART 4-1 PAGE: 6 

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

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

Air Data Modules are remotely 

mounted near and above the level of 

the pitot and static probes 

AIR DATA MODULE

(Typical Installation) 

STATIC PROBE 

(Typical)

PITOT PROBE 

(Typical)

END OF SUB-PART 4-1 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

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

Sub-part 4-2-1 LIFE LIMITS

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

Explanatory notes are located under each assembly title. 

LIFE LIMITATION 

(Whichever occurs first) LIFE LIMITATION APPLICABILIT

 Nomenclature Part Number FH LDG Cal. A318-100 A319-100 A320-100 A320-200 Twin A320-20

Bogie 

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

 (1) This 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 withou

Power Transfer Unit (PTU) 4101002-3 1000 (1) N/A N/A X 

-211 -212 -214 -231 -232 

X 

4101002-4 1000 (1) N/A N/A X 

-211 -212 -214 -231 -232 

X 

4101002-5 3000 N/A N/A X 

-211 -212 -214 -231 -232 

X 

4101002-6 3000 N/A N/A X 

-211 -212 -214 -231 -232 

X 

4101002-91 2000 N/A N/A X 

-211 -212 -214 -231 -232 

X 

N R 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

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

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

Explanatory notes are located under each assembly title. 

LIFE LIMITATION 

(Whichever occurs first) LIFE LIMITATION APPLICABILIT

 Nomenclature Part Number FH LDG Cal. A318-100 A319-100 A320-100 A320-200 Twin A320-20

Bogie 

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

R Retraction actuator pin 

(main fitting side) 

114094617 N/A 20000 N/A X 

114193631 N/A 20000 N/A X X X X 

ATA 32-20-00 NOSE GEAR AND DOORS (FIG 05) Door uplock C24730000-3 N/A 1000 N/A X -211 -212 

-231 

ATA 34-12-00 NAVIGATION (FIG 06) Air Data Module (ADM) 

PG1152AC02 N/A N/A 3 Ye X 

-211 -212 -231 -232 

END OF SUB-PART 4-2-1 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

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

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

Explanatory notes are located under each assembly title. 

LIFE LIMITATION 

(Whichever occurs first) LIFE LIMITATION APPLICABILIT

 Nomenclature Part Number FH LDG Cal. A318-100 A319-100 A320-100 A320-200 Twin A320-20

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 P/N 114193643 must be replaced by a new one every time it is removed from the gland. R Retraction actuator pin 

(main fitting side) 

114094661 N/A 60000 N/A 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 

R Retraction actuator 

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 (retraction actuator piston rod) 

114094611 N/A (1) N/A X 

114193606 N/A (1) N/A X X X X 

R Retraction actuator 

piston head 

114094608 N/A 60000 N/A X 

114193603 N/A 60000 N/A X X X X 201590909 N/A 60000 N/A X X X X 201590912 N/A 60000 N/A X 

R Retraction actuator 

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 

N 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

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

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

Explanatory notes are located under each assembly title. 

LIFE LIMITATION 

(Whichever occurs first) LIFE LIMITATION APPLICABILIT

 Nomenclature Part Number FH LDG Cal. A318-100 A319-100 A320-100 A320-200 Twin A320-20

Bogie 

R Retraction actuator 

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 

R Retaining ring (retraction 

actuator gland) 114193643 N/A (2) N/A X X X X 

R Retraction actuator 

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 

N 201697600 N/A 60000 N/A X X X X N 201697601 N/A 60000 N/A X X X X N 201697602 N/A 60000 N/A X X X X N 201697603 N/A 60000 N/A X X X X 

Retraction actuator pin (rear spar side) 

114094615 N/A 60000 N/A X 

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 

END OF SUB-PART 4-2-2 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

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

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

N Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.R ALS PART 4 MAINTENANCE TASKS LIMITATIONS (whichever occurs first) REFERENCE R Task Number Zone Description Threshold Interval R R R 

292200-00001-1-E Z195 Ram Air Turbine (RAT) and actuator – 

(Hamilton Sundstrand) – FIG. 01 Remove RAT and actuator for overhaul and replace with new or reconditioned units. 

20 Yrs 20 Yrs AMM 292200-960-001

CMM 29-21-03 CMM 29-21-42 CMM 29-21-44 

RA

R R R R R R R R 

292200-00002-1-E Z195 Ram Air Turbine (RAT), Ejection Jack and 

AGCM – (Dowty) FIG. 02 Remove RAT (including turbine, leg and pump), Ejection Jack and AGCM for overhaul and replace with new or reconditioned units. 

20 Yrs 20 Yrs AMM 292200-960-002

CMM 29-21-05 CMM 29-21-27 CMM 29-21-28 CMM 29-21-80 

Rtua

E

A

END OF SUB-PART 4-3-1 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

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

 EASA APPROVED 

©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVEL

N Note: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.R ALS PART 4 MAINTENANCE TASKS LIMITATIONS (whichever occurs first) REFERENCE R Task Number Zone Description Threshold Interval D 324400-0001-1-E Z190 Parking/Ultimate emergency braking system

Functional check of the Brake Accumulator 

system with the Parking Brake not applied

60000 FH 60000 FH AMM 324400/501

324400-720-002

END OF SUB-PART 4-3-2 
A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 4

AGEING SYSTEMS MAINTENANCE

HISTORY FILE

ISSUE: JUN 15/12 ALS PART 4 HISTORY FILE PAGE: 1/1 

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

1- GENERAL

- A318/A319/A320/A321 ALS Part 4 revision 00 

The A318/A319/A320/A321 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. 

- A318/A319/A320/A321 ALS Part 4 revision 01 

The A318/A319/A320/A321 ALS Part 4 revision 01 is mainly dedicated to introduce the 

Extended Service Goal 1 (ESG1) exercise, which allows continued operation of the A320-200 

systems POST MOD 39020 up to 120000 FH or 60000 FC (whichever occurs first). 

2- SUMMARY OF CHANGES

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

A318/A319/A320/A321 ALS Part 4 (revision 00). 

New items: 

None 

Amendments: 

Sub-part 4-0.

Wording changes in harmonization with other programmes. 

New operational life applicable to systems installations for A320-200 POST MOD 39020. 

Sub-part 4-2.

Separation of sub-part 4-2 into sub-part 4-2-1 and sub-part 4-2-2 and nomenclature wording 

changed for some ATA 32 items. 

Retraction actuator cylinder new PNRs added: PNR 201697600, PNR 201697601, PNR 

201697602 and PNR 201697603. 

Sub-part 4-3.

ASM task reference 292200-00001-1-E: wording revised, applicability changed to ALL for RAT 

and Actuator and AMM references changed. 

ASM task reference 292200-00002-1-E: wording revised, applicability changed to ALL for RAT, 

Ejection Jack and AGCM and AMM and CMM references changed. 

Deletion: 

Sub-part 4-3.

ASM task reference 324400-0001-1-E is transferred to A318/A319/A320/A321 ALS Part 3 

revision 01 as CMR One Star 324000-00002-1-C.