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

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4-3 R 2 JUN 15/12A318/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 4-3A318/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. R

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NA318/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

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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 sa fety) 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 R

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© 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 ar e 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 D

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© AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document. that they are performed with the same ins pection 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 asnecessary in accordance with the instructions of paragraph 1.H. of this ALS subpart 4-0.

Therefore, it is necessary to assure traceability and monitoring of the components/items listed in the sub-parts 4-2 and 4-3-1.

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

Certificate of Airworthiness.

For a given component/item of the sub-parts 4-2 and 4-3-1, new PNRs may be introduced in the future as a result of modifications and/or Airbus Service Bulletin (SB) publishes. These new PNRs may not be listed in the sub-parts 4-2 and/or 4-3-1 of the

current revision of the ALS Part 4.

However, it is recommended to maintain traceability and monitoring of such components/items whatever their PNR in case of future introduction in the ALS

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© 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:

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

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

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

Cp i = component/item’s airworthiness limitation in 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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© 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 appliedprior to reaching the life limit (e.g. Service Bulletin: POST SB PNR in the subpart 4-2-1).

Note 2: It’s recommended that the organization that mutilates a component/item should provide the original manufacturer with the data plate and/or serial number and final disposition of the component to maintain the records of serial numbers for “retired” certified life-limited components/items or other critical components/items.

For component listed in sub-part 4-2-2 and/or 4-3-1: Appropriate means must be implemented to deter their installation on aircraft pending possible extension of the life limitations and/or 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 N

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© 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 flui d 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 r epair 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 N

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© 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 airworthine ss 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 transfe rable 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). R

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© 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. R

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© 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 replacem ent 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

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© 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

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R

N

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RA318/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

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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

A LL All A318, A319, A320 and A321 aircraft.

A 320-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 fo r components/items listed in sub-part 4-3.

Since ALS sub-part 4-3 intervals are based on statistical averages and reliability rates, an exceptional short-term extension for a specific ALS sub-part 4-3 interval may be made on one aircraft for a limited period of time without compromising the safety objectives declared at Type Certification. R

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RA318/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 except ionally 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 per missible 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

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NA318/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. 01A318/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. 02A318/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. 03A318/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

headA318/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. 05A318/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 4-1A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIONISSUE: JUN 15/12ALS PART 4-2-1PAGE: 1EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-2 SYSTEMS LIFE LIMITED COMPONENTSSub-part 4-2-1 LIFE LIMITSNNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.Explanatory notes are located under eachassembly title.LIFE LIMITATION(Whichever occurs first)LIFE LIMITATION APPLICABILITYNomenclature Part Number FHLDG Cal. A318-100 A319-100 A320-100A320-200TwinA320-200BogieA321-100 A321-200ATA 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 without finding.Power Transfer Unit(PTU)4101002-31000(1)N/A N/A X-211-212-214-231-232X4101002-41000(1)N/A N/A X-211-212-214-231-232X4101002-5 3000 N/A N/A X-211-212-214-231-232X4101002-6 3000 N/A N/A X-211-212-214-231-232X4101002-91 2000 N/A N/A X-211-212-214-231-232XNRA318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIONISSUE: JUN 15/12ALS PART 4-2-1PAGE: 2EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.NNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.Explanatory notes are located under eachassembly title.LIFE LIMITATION(Whichever occurs first)LIFE LIMITATION APPLICABILITYNomenclature Part Number FHLDG Cal. A318-100 A319-100 A320-100A320-200TwinA320-200BogieA321-100 A321-200ATA 32-10-00 MAIN LANDING GEAR RETRACTION ACTUATOR (FIG 04)RRetraction actuator pin(main fitting side)114094617 N/A 20000 N/A X114193631 N/A 20000 N/A X X X X X XATA 32-20-00 NOSE GEAR AND DOORS (FIG 05)Door uplockC24730000-3 N/A 1000 N/A X-211-212-231ATA 34-12-00 NAVIGATION (FIG 06)Air Data Module (ADM)PG1152AC02 N/A N/A 3 Ye X-211-212-231-232END OF SUB-PART 4-2-1A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIONISSUE: JUN 15/12ALS PART 4-2-2PAGE: 3EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-2-2 CURRENT DEMONSTRATED LIVESNNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.Explanatory notes are located under eachassembly title.LIFE LIMITATION(Whichever occurs first)LIFE LIMITATION APPLICABILITYNomenclature Part Number FHLDG Cal. A318-100 A319-100 A320-100A320-200TwinA320-200BogieA321-100 A321-200ATA 32-10-00 MAIN LANDING GEAR RETRACTION ACTUATOR (FIG 04)(1) Retaining ring P/N 114094611 and P/N 114193606 must be replaced bya new one every time it is removed from the piston head.(2) Retaining ring P/N 114193643 must be replaced by a newone every time it is removed from the gland.RRetraction actuator pin(main fitting side)114094661 N/A 60000 N/A X114193637 N/A 60000 N/A X X X X X X201590900 N/A 60000 N/A X X X X X X201590903 N/A 60000 N/A XR Retraction actuatorpiston rod114094303 N/A 60000 N/A X114094308 N/A 60000 N/A X114193601 N/A 60000 N/A X X X X X X201590907 N/A 60000 N/A X201590908 N/A 60000 N/A X X X X X XRetaining ring (retractionactuator piston rod)114094611 N/A (1) N/A X114193606 N/A (1) N/A X X X X X XR Retraction actuatorpiston head114094608 N/A 60000 N/A X114193603 N/A 60000 N/A X X X X X X201590909 N/A 60000 N/A X X X X X X201590912 N/A 60000 N/A XR Retraction actuatorpiston head nut114094605 N/A 60000 N/A X114193604 N/A 60000 N/A X X X X X X201590910 N/A 60000 N/A X X X X X X201590911 N/A 60000 N/A XNA318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIONISSUE: JUN 15/12ALS PART 4-2-2PAGE: 4EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.NNote: explanations on the applicability system are provided in the sub-part 4-0 paragraph 3.Explanatory notes are located under eachassembly title.LIFE LIMITATION(Whichever occurs first)LIFE LIMITATION APPLICABILITYNomenclature Part Number FHLDG Cal. A318-100 A319-100 A320-100A320-200TwinA320-200BogieA321-100 A321-200R Retraction actuatorgland114094604 N/A 60000 N/A X114193602 N/A 60000 N/A X X X X X X114193642 N/A 60000 N/A X X X X X X201590913 N/A 60000 N/A X X X X X X201590914 N/A 60000 N/A X201590915 N/A 60000 N/A X X X X X XR Retaining ring (retractionactuator gland)114193643 N/A (2) N/A X X X X X XR Retraction actuatorcylinder114094600 N/A 60000 N/A X114193600 N/A 60000 N/A X X X X X X114193641 N/A 60000 N/A X X X X X X201590904 N/A 60000 N/A X201590905 N/A 60000 N/A X X X X X X201590906 N/A 60000 N/A X X X X X XN201697600 N/A 60000 N/A X X X X X XN201697601 N/A 60000 N/A X X X X X XN201697602 N/A 60000 N/A X X X X X XN201697603 N/A 60000 N/A X X X X X XRetraction actuator pin(rear spar side)114094615 N/A 60000 N/A X114094635 N/A 60000 N/A X114193610 N/A 60000 N/A X X X X X X201590901 N/A 60000 N/A X X X X X X201590902 N/A 60000 N/A XEND OF SUB-PART 4-2-2A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIONISSUE: JUN 15/12ALS PART 4-3-1PAGE: 1EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-3 SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTSSub-part 4-3-1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVELNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.R ALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONSAPPLICABILITYR Task Number ZoneDescriptionThreshold IntervalPNR AIRCRAFTRRR292200-00001-1-E Z195Ram Air Turbine (RAT) and actuator –(Hamilton Sundstrand) – FIG. 01Remove RAT and actuator for overhaul andreplace with new or reconditioned units.20 Yrs 20 Yrs AMM 292200-960-001CMM 29-21-03CMM 29-21-42CMM 29-21-44RATALLActuatorALLA318ORA319ORA320POST 27189PRE 28413ORA321RRRRRRRR292200-00002-1-E Z195Ram Air Turbine (RAT), Ejection Jack andAGCM – (Dowty) FIG. 02Remove RAT (including turbine, leg and pump),Ejection Jack and AGCM for overhaul and replacewith new or reconditioned units.20 Yrs 20 Yrs AMM 292200-960-002CMM 29-21-05CMM 29-21-27CMM 29-21-28CMM 29-21-80RAT (includingturbine, legand pump)ALLEjection JackALLAGCMALLA320PRE 27189ORA320POST 28413END OF SUB-PART 4-3-1A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIONISSUE: JUN 15/12ALS PART 4-3-2PAGE: 2EASAAPPROVED©AIRBUS SAS 2012. All rights reserved. Confidential and proprietary document.Sub-part 4-3-2 CONTROLLED AT AIRCRAFT SYSTEM LEVELNNote: Explanations on the applicability system are provided in the sub-part 4-0 paragraph 4.RALS PART 4 MAINTENANCE TASKSLIMITATIONS(whichever occurs first)REFERENCELIMITATIONSAPPLICABILITYR Task Number ZoneDescriptionThreshold IntervalPNR AIRCRAFTD 324400-0001-1-E Z190Parking/Ultimate emergency braking systemFunctional check of the Brake Accumulatorsystem with the Parking Brake not applied60000 FH60000 FHAMM 324400/501324400-720-002N/AA320-200PRE 26925PRE 20139ORA320-200PRE 26925POST 20139POST 22129END OF SUB-PART 4-3-2A318/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 aircra ft (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, wh ich 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 A 318/A319/A320/A321 ALS Part 3

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