# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION



# ALS Part 4



# - Ageing Systems Maintenance

© AIRBUS SAS 2008. All rights reserved. Confiden tial and propnetary document. This document and all information contained herein is the sole property of AIRBUS SAS. No intellectual property rights are granted 

### by the delivery of this document or the disclosure of its content. This document shall not be reprodu ced or disclosed to a third party (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein) without the express written consent of AIRBUS SAS

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

. REVISION : 00

# ~ 

# 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 4 N 1 -L EP JAN 08/08 4 N 1-TOC JAN 08/08 4 N 1 - ROR JAN 08/08 4-0 N 1 JAN 08/08 4-0 N 2 JAN 08/08 4-0 N 

### 3 JAN 08/08 4-0 N 4 JAN 08/08 4-0 N 

### 5 JAN 08/08**4~0** N 

### 6 JAN 08/08 4-0 N 

### 7 JAN 08/08 4-0 N 8 JAN 08/08 4-0 N 9 JAN 08/08 4-0 N 10 JAN 08/08 4-0 N 11 JAN 08/08 4 - 0 

### N 12 JAN 08/08 4-1 N 1 JAN 08/08 4 - 1 N 2 JAN 08/08 4-1 N 

### 3 JAN 08/08 4-1 N 4 JAN 08/08 4-1 N 

### 5 JAN 08/08 4-1 N 

### 6 JAN 08/08 4-2 N 

### 1 JAN 08/08 4 -2 

### N 2 JAN 08/08 4-2 N 3 JAN 08/08 4-3 

### N 1 JAN 08/08 

### 4-3 N 

### 2 JAN 08/08

ISSUE: JAN 08/08 ALS PART 4 PAGE · 1-LEP € AIRBUS SAS 2008

_ AU rights reserved

.

# ~ 

# A31 BIA319/A320/A321 A I RWORTHINESS LIMITATIONS SECTION ALS PART 4 AGE IN G SYSTEMS MAINTENANCE TABLE OF CONTENTS
SUBJECT RECORD OF REVISIONS INTRODUCTION IL LUSTRATIONS SYSTEMS LIFE -LI MITED COMPONENTS SYSTEMS INSTALLATIONS MAINTENANCE REQUIREMENTS

ISSUE· JAN 08/08 ALS PART 4 @A IRBUS SAS 2008. All rights reserved

. PART ROR 4-0 

### 4-1 

### 4-2 4-3

PAGE : 1-TOC

# ~ 

# A318/A319/A320/A321 A I RWORTHINESS LIMITAT I ONS SECTION ALS PART4 AGEING SYSTEMS MAINTENANCE RECORD OF REVISIONS

The European Aviation Safety Agency (EASA) approv es the ALS Part 4

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

.

REVISION SUB-PARTS APPROVED BY EASAAD INSERTION IN NUMBER EASA MAINT

. PROG. ROR 00 4 - 2 JAN 08/08 4-3 Note: The ALS Part 4 is cove red by the certifi ca tion document OOD050AM094/C01 Revision 00 is approved by EASA under reference 

### N° EASA.A

. C

. 07695 Rev 

### 1
. REVISION 00 COMPLIANCE TIME : 

### 1
. Except as provided in paragraph 2

. of this Reco rd Of Revisions (ROR) , it is mandatory to adhere to the airworth in ess limitations as defin ed in the sub-part s 4 - 2 and 4-3 of the A318/A319/A320/A321 ALS Part 4 revision 00 from January 08 , 2009

. 2. It i s mandatory to comply with the following airworthiness limitations defin e d in the sub
- part 4 - 2 or 4-3 of the A318/A319/A320/A321 ALS Part 4 revi s ion 00 : F rom January 08 , 2008 for : All the limit ations listed in t h e sub-part 4 - 2 , ASM task ref

. 324400-0001
- 1 - E for brake accumulato r

A L S PART 4 ------------------------EASAAP PRO VEn------------------------ IS S U E: JAN 08/ 08 PAG E: 1- R OR ©A IR BUS SAS 2008. All righ ts 

### reserved

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION Sub- p art 4-0 INTRODUCTION 1

. GE N ERAL The data provided under Part 4 has been estab li shed with the following rules : 

### Compliance with the requirements contained in this document is mandatory

. No person may operate an aircraft to which an ALS applies exce pt in accordance with the requirements of that ALS , unless otherwise agreed with the Authority of the State of aircraft registry. C{)nsultation with the State of design should be made by the State of aircraft registry, in consideration of any deviation from the ALS requirements. This is indicated in the International Civil Aviation Organization (ICAO) Airworthiness manual (Doc

. 9760) , Volume II , Part A , Chapter 3

. The procedures contained therein (ALS) must be taken into account when conside ring any variation requests
. 

### A. Ageing Systems Maintenance (ASM)

. Airbus' definition of Ageing Syste m s Maintenance (ASM) refers to li mi tatio ns appli cable to aircraft systems that operate beyond th ei r orig ina l qualification

. Beyo nd this point , ageing effects may affect the characteristics leading to an increased potential for failure

. The maintenance associated with failure conditions shown to be sensitive to the ageing effects on system components are subject to limitations

. The Part 4 of the Airworthiness Limitations Section (ALS) has been created to contain the maintenance actions together with their limitations to help to qua l ify the systems installations for continued operation up to the Limit Of Validity shown hereafter

. Limi tations quoted in the ALS Part 4 are app li cable to th e undamaged and unrepaired aircraft systems installations

. They may nee d to be adj us ted i n case of damage/repair. This document was defined by a process agreed between Airbus a n d the European Aviation Safety Agency (EASA)

. This document rep l aces the need for individual Airworthiness Directives (AD) that would otherwise be needed for such limitations

. 

### 8 Limit Of Validity (LOV). Operation of aircraft systems up to the stated Limit Of Validity (In FH or FC , whichever occurs fi rst) is cove red by this document. The relevant LOV values are stated below

. The aircraft systems must not be operated beyond these values unless the Type Certificate Holder (i.e

. Airbus) has updated this document to include a clearly defined LOV extension. Aircraft series LOV (whichever occurs first) FH FC A318-100 

## I 60000 48000 A319-100 excluding Corporate Jet operations 

## I 60000 48000 I SSUE: JAN 08/08 ALS PART 4 - 0 PAGE 1 ©AIRBUS SAS 2008 All r igh t s reserved

.

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECT ION Aircraft series LOV (whichever occurs first} FH FC A319-1 00 Corporate Jet operations 77400 18000 A320-100 48000 48000 A320-200 60000 48000 or 80000 (*) 37500 (*) A321-100 60000 48000 A321-200 60000 48000 (*)Applies only to aircraft POST MOD 37734/SB A320-00-1198

. Note: When different sets of LOV are indicated for a given aircraft series

. no combination of values extracted from different se ts is allowed

. C. ALS Part 3 and ALS Part 4 correlation At time of Type Certification , an appraisal of aircraft systems is carried out within the frame of the Systems Safety Assessments. This may identify a need to schedule repetitive maintenance tasks within a defined interval so as to maintain the required safety objectives for individual failure conditions. A subset of these tasks , the majority of which detect latent failures, are identified as Certification Maintenance Requirements (CMR). These constit ute operational limitations and are mandated through their location in the ALS Part 3

. Compliance with the requirements of the ALS Part 3 must be maintained throughout the LOV stated in the ALS Part 4, except where any CMR is superseded by AD or a requirement of the ALS Part 

### 4
. D

. Origin of ALS Part 4 items

. Items listed in this ALS Part 4 may originate from : Aircraft Maintenance Manual (AMM) chapter 05 Service Life Lim i ts and Maintenance Checks (SLMC) section 05 - 11-00 Service Life Limits, subsequently transferred into a previous section 9 of the Maintenance Planning Document. Items previously listed in the ALS Part 1

. Life extension study (Change in LOV)

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

### E. Sub-part 

### 4-2 : SYSTEMS LIFE LIMITED COMPONENTS. Componen ts li sted under this sub-part are those having a life limitation , due to the difficulty to define a continued/enhanced inspection program, and whose failure could contribute to an unsafe condition of the airplane. F

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

. The continued/enhanced inspection program given in this sub-part includes limitations to prevent aircraft systems failures, which could contribute to an unsafe condition of the airplane. These limitations are determined in consideration of the probability of an aircraft system level failure condition or conditions. ISSUE : JAN 08/08 ALS PART 4-0 PAGE

. 

### 2 ©

AIRBUS SAS 2008

. All nghts reserved

.

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION Note : Credit may be taken for the Maintenance Review Board Report (MRBR) Systems and Powerplant section maintenance tasks , providing that they are performed with the sa me inspection level , as frequently, or more frequently , than the inspection threshold and interval quoted in this document. Sub-parts 4 -3- 1 and 4-3-2 give maintenance requirements at component level and aircraft (system) level respectively

. Sub-part 4-3-1: Controlled at component/sub-assembly level This sub
- part identifies tasks controlled at item level. The recurrent maintenance requirements are applicable no l ater than the i_tem, not the aircraft, reaching the limitation

. When items given in sub-part 4-3-1 reach the stated limitations. the given task must be carried out. Any item removed from the aircraft for any reason , (such as failure of functiona l check, degradation of condition, etc) must be replaced by a serviceable item , which has not accumulated the stated limitations. Sub-part 4 -3- 2 : Controlled at aircraft system level This sub-part identifies tasks at aircraft level. The recurrent maintenance requirements are applicable no later than the aircraft , not the item , reaching the limitation

. The tasks listed in sub-part 4 -3-2 must be carried out when the aircraft reaches the stated threshold/interval. Should a failu r e to reach the task requirements be detected, the appropriate trouble-shooting must be carried out and the relevant suspected items replaced in accordance with the Aircraft Maintenance Manual (AMM) procedures. Following any replacements, the listed tasks must be repeated until a successful task recording can be entered

. G

. Traceability and replacement/maintenance requirements. In 

### order to maintain aircraft airworthiness, it is mandatory to replace items listed uncJer sub-part 4-2 at or prior to whichever of the life limitations occurs first, after any necessary adjustment of the stated life limitation In accordanc e with the instructions of sub-part 4·0 paragraph 3.C. It is also mandatory to perform/repeat the maintenance requirements listed in sub-part 4-3 

### at or prior to whichever of the limitations threshold/interval occurs first. Therefore, It Is necessary to assure traceabi lity and monitoring of th e items list ed in the sub-parts 4 -2 and 4-3-1

. Non-compliance with these requirements could suspend the validity of the Certificate of Airworthiness

.

ISSUE: JAN 08/08 ALS PART 4 - 0 PAGE : 3 ©AIRBUS SAS 2008

. All rights reserved

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS L1 MITATIONS SEC TI O N For a given item of the sub-parts 

### 4 -2 and 4 -3-1, new part numbers may be introduced in the fu ture. These new part numbers may not be listed in the sub-parts 

### 4-2 and 

### 4-3-1 of the current revision of the ALS Part 4. However , it is recommended to maintain tracea bility and monitoring of such items whatever their det ail part numb er in case of future introduction in the ALS Part 

### 4
. For further guidance , Operators are requested to contact Airbus

. Note : In the context of the ALS Part 

### 4 , traceability means records that clearly demon strate the history of it ems back to initial entry into service, so that limitation s are accurately app l ied. Traceability records may comprise , but are not limited to, the following : Application history (aircraft type , model , MSN i.e

. Manufacturer Serial Numb e r , etc
... ) , Maintenance actions carried out (Airworthiness Directives , modifications , repairs , inspections , etc
... ), Life accumulation (accoun ting for any individual a i rcraft to whic h an item may have been fitted)

. H

. Disposal/quarantine action. Whe n the items listed in the sub- p art 

### 4-2 reach the life limitations, disposal/quarantine action must be taken: appropriate means must be implemen t ed to deter their installation on aircraft pending possible extension of their l ife limitations

. Examples of means are : Record keeping system , Non-perman ent markings , Se greg ation (ft ems stored separately from those currently eligible for installation) The ultima te solu ti on is the mutilation beyond repair limits to prevent rework to appear to be airworthy. 

### I. R epo rt ing. The ICAO Airworthiness manual (Doc

. 9760), Vo lu me II, Part B , Chapter 2 indicates : The concept of Continuing Airworthiness includes the reporting of def ects and other significant maintenance and operational information by the Operator to the organisation res ponsibl e for the Type Des ign in accordance with the requirements of the State of aircraft registry

. Any damage (e.g fatigue cracks , wear , corrosion, etc
...) on systems affected by the ALS Part 4 must be reported to Airbus

. The finding report should include at least the Information stated below : ASM maintenance requirement reference. Aircraft Manufacturer Serial Number (MSN) affected

. Identification of the affected item.
I SSUE: JAN 08/08 ALS PART 4 -0 © AIRBUS SAS 2008 All nghts reserved PAGE. 4

# ~ 

# A31 BIA319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION Life since new (in FH and/or FC and/or LOG and/or calendar time , as applicable) accumulated by the affected system/item at the time of the finding , Location and description of the finding, with indication of the size and orientation, Circumstance of detection and inspection method used

. 

### J Production/Repair concessions and Alternative Means Of Compliance

. Limitations of the ALS sub-part 4-2 and 4-3 may be negated by instructions given in either a Production or Repair concession , or an Alternative Means Of Compliance (AMOC)

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

. Production concessions are provided to the initial Operator of the aircraft in the delivery documentation (Aircraft Inspection Report: ' Recordable concessions ' ). When limitations evolve in a revision of the ALS Part 4 subsequent to the issuance date of the Produc1ion or Repair concession/AMOC , Operators are requested to contact Airbus for guidance

. The restrictions of limitation(s) indicated in the repair file/AMOC (or absence thereof) depend on the item's accumulated life considered during the original evaluation of the repair solution/AMOC. Occasionally, repair solutions/AMOC are evaluated on the basis of an accumulated life that includes a conservative life calculation (refer to SIL 05-009)

. Such AMOC/repair solutions MUST be re-evaluated by Airbus before Operators can take credit of the history partially or completely rebuilt after application for the repair solution/AMOC

. Note : For spares, restriction of limitation(s), if any, are indicated in EASA Form 1 block 13 (directly or by reference to another document) K

. Modifications/Repairs not originating from Airbus If an aircraft/a sub-assembly/an item has a modification or repair embodied that is not of Airbus origin (e

. g . Supplemental Type Certificate) and which affects the content of the ALS Part 4 , the Operator is responsible for obtaining approval by the relevant Airworthiness Authority for any necessary adaptations of the limitations

. When such an aircraft/a sub-assembly/an item ts transferred from one Owner/Operator to another , the assoc iated approvals and documents indicating the necessary adaptations of limitations must be transferred as well.

ISSUE· JAN 08/08 ALS PART 4 - 0 PAGE : 5 @

AIRBUS SAS 2008 All nght s reserved2. 

# ~ 

# A318/A319/A320/A321 A I RWORTHINESS LIMITATIONS SECTION L. ALS Part 4 applicability

. Sub-parts 4-2 and 4-3 are approved by the EASA. ALS Part 4 covers the following models: A318
- 111 A319-111 A320-111 A321-111 A318-112 A319-112 A320-211 A321-112 A318-121 A319-113 A320-212 A321-131 A318-122 A319-114 A320-214 A321-211 A319-115 A320-215 A321-212 A319-131 A320-216 A321-213 A319-132 A320-231 A321-231 A319-133 A320-232 A321-232 A320-233 DEFINITIONS The initial entry into service is defined for the aircraft (systems installations) as : The date of Transfer of Title to the first Operator for limitations in Calen d ar 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 f li ght cycles and/or landings. The initial entry into service for the transferable systems items is defined as the date at which the item accomplishes the first flight for which it will undertake its intended function Note: Unless otherwise stated, this means for transferable items delivered on new aircraft (i.e

. from Airbus Final Assembly Line) that the life accumulated before the aircraft delivery date/transfer of title date (e.g. as a result of test flights) must be taken In to account. Ca l endar 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 en try into service , it should be noted that Calendar time usage parameter cannot be frozen (unless stated for Individual items). Exceptional Short Term Extension· An extension in an ASM limitation that may be needed to cover an uncontrollable or exceptional unexpected situation. Flight Cycle (FC) Flight Hour (FH)·
Functional Check A complete take-off and landing sequence. The accumulated time intervals between ''w heels
- off' and "whee l s-on"

. A quantitative check to determine if an item performs one or more of its functions within spec1fied hmits
I SSUE JAN 08/08 ALS PART 4 - 0 PAGE : 6 •JA IRBU S SAS 2008 All nghts reserved

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION Interval :

Landing (LOG):

Limit of Validity (LOV) :

Operational Check:

Threshold :

Touch a nd go · The period expressed in usage parameters like FH and/or FC and/or LanDinGs and/or Calendar time between successive accomplishments of a specific task. An operation of an aircraft touching the runway and coming to a complete stop or performing a "touch and go ". The LOV is the time at which the aircraft maintenance programme ceases to be valid: The maintenance requirements and their limitations contained in the ALS Part 4 cease to be valid beyond the LOV indicated in the sub-part 4-0 , paragraph 1

. B. A qualitative check to determine that an item is fulfilling its intended purpose . It is a failure finding task and does not require quantitative tolerances. The initial accomplishment of a specific maintenance task from the initial entry into service

. It may be expressed in usage parameters l ike FH and/or FC and/or LOG and/or Calendar time

. A landing in which an aircraft touches the runway and does not come to a full stop prior to commencing an additional flight. In the sub-part 4-3 , touch and go cyc les can be neglected if they are less than 5% of the total number of FC up to threshold inspection or between two consecutive inspections

. Each "Touch and go" above 

### 5% is to be counted as one FC/LOG, up to threshold inspection or between two consecutive inspections

. 

### 3. RULES SPECIFIC TO SUB-PART 

### 4-2 A

. Part Number applicability ALS part 4 - 2 tables provide the applicable limitations only for systems installations that have been authorized. These tables do not ensure that a part number has been validated for a specific individual aircraft MSN

. Part numbers a r e authorized for installation on individual aircraft MSN by Serv1ce Bulletins (and the associated modifications) that are published by Airbus

.

ISSUE · JAN 08/08 ALS PART 4-0 PAGE : 7 @

AIRBUS SAS 2008 All nghts re served

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION B

. Limitation/Replacement time indication

. (1) General In computing items' life

. calcu l ations must include flight hours and/or flight cycles and/or landings and/or Calendar tim e (as applicable) since the initial entry into service of the item (unless otherwise s t ated). (2) ALS sub-part 4-2 life limitations Life limitations quoted in sub-part 4-2 are applicable to the undamaged items as listed, not to the aircraft on which they are installed. The limitation/replacement time indication is quoted on the same line/block of lines as the Part Number

. C

. Transfers of items between applications having different life limitations

. In case of item transfers between applications (aircraft types , aircraft models , etc
... ) with different l ife limitations. the remaining life for operation must be defined by the use of the following formula:

with: 

### Tq 

# = Caj 

# = Cpj 

### = Cpi= remaining life for operation on model i (present application) accumulated life on previous application j. life limitation in previous application 

### j
. life limitation in present application 

### i. Note: when using the above formula Tfj

. Caj. Cpj. Cpi are expressed in the same usage parameters (FH or FC or LOG) : usage parameters can not be mixed in the same calculation

. Where the comp l ete life history of an item is not known, Operators are requested to refer to Service Information Letter (SIL 05-009) for guidance. It provides the means to manage such items

. It has been issued in agreement with the EASA. 

### D Limitation applicability

. limitation applicability may be allocated according to the aircraft MSN affected (for a ll aircraft of the co lumn for sub-part 4-2) , e g . ( 1) Aircraft type, series and model , e.g. 

### X stands for all aircraft of the column. -212 stands for all-212 models of the column excl.



### - 113 s tands for all a1rcraft of the column excluding the 

### -113 model

. (2) Aircraft Manufacturer Serial Number , e . g . XXX-YYY stands for aircraft MSN XXX to aircraft MSN YYY

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

### XXZ XZX stands for aircraft MSN XZX only. ISSUE , JAN 08/08 ALS PART 4-0 PAGE

. 8 @

AIRBUS SAS 2008 All nghts reserved

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECT ION excl. XXX stands for all aircraft, excluding MSN XXX

. 4
. RULES SPECIFIC TO SUB-PART 4 -3 A. Gene ral. In computing the life accumulated by the aircraft systems installations/items , calculations must include flight hours and/or flight cycles and/or landings and/or calendar time (as applicable) since the initial entry into service (unless otherwise stated). The limitations must be applied from: The initial entry into service, for the threshold and the LOV, and The original due date of the last accomplishment of the task , excluding any exceptio nal short-term extensions from calculations, for the i nterval. When alternative inspection methods are provided, the next interval applicable is the one associated with the inspection method used at last inspection. B

. Sub-part 4 -3 layout The maintenance requirements are presented in the ALS sub-part 4-3 in accordance with the following method : (1) Task Number The task numbering system follows a similar format to the Maintenance Plannmg Document (MPD) s ystem , as follows: Each task is identified by a specific task number

. When a task applies to two specific main zones located symmetrically to either side of the aircraft centreline , the task is assigned a single task number , but both LH and RH zones are indicated in "ZONE" column

. The task number comprises 13 digits organized as follows : XXXXXX-MEFYY-Z-E XXX XXX 

### M 

### E F 

### yy 

## z E

ISSUE · JAN 08/08 is AT A 100 task reference

. is the selection methodologies used

. It will always be " 0 ". is engine/APU/

... manufacturer identification (where applicable , " 0' ' is default value) is engine/APU type i nformation when more than one engme from the same manufacturer is applicable to the program (where applicable , " 0 " is default value). is sequential number

. is for technical solution applicable to the same task requirement Is "E" and stands for ASM (i

.e . task related to an ageing systems function or Enhanced maint ena nc e requirement)

.

ALS PART 4 - 0 PAGE 9 ©A IRBUS SAS 2008 All rights reserved

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION (2) Zone column The zone column defines where the maJor part of the maintenance task requirement is to be carried out on the aircraft. (3) Description column This column provides the following information : (a) Task Description. Contains concise description of the maintenance task to be performed (b) Note. Where given , it states further requirements and/or provides useful information. (4) Threshold/Interval columns

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

. The interval and threshold may be expressed in terms of usage parameters or notes. Usage parameters are defined in the paragraph 2 of this sub-part

. (5) Reference column This column provides reference to technical documentation where maintenance practices/procedures necessary for the task accomplishment are provided , e.g . the AMM

. (6) Applicability column These columns give the combination of component part number and alrcraft that requires the accomplishment of the task

. {a) Part Number ALS sub-part 4-3 tables provide the applicable limitations only for systems installations that have been authorised

. These tables do not ensure that a part number has been validated for a specific individual aircraft MSN

. Part numbers are authorised for installation on individual aircraft MSN by Service Bulletins (and the associated modifications) that are published by Airbus. (b) Aircraft Applicability Task app l icable 

### to ALL All A318, A319, A320 and A321 aircraft A320-xxx A320-xxx series aircraft

. PRE nnnnn All a1rcraft PRE MOD nnnnn . 1.e A318/A319/A320/A321 that do not have MOD nnnnn embodied

. POST nnnnn All aircraft POST MOD nnnnn i.e. A318/A319/A320/A321 that do have MOD nnnnn embodied

.
ISSU E: JAN 08/08 ALS PART

**~0** PAGE : 10 ©AIRBUS SAS 2008 All nghts reserved

# ~ 

# A318/A31 9/A320/A321 AIRWORTHINESS LIMITATIONS SECTION Applicability Task applicable to POST nnnnn All aircraft POST MOD nnnnn (at least with mod proposal Sxxxxx no. Sxxxxx embodied). POST nnnnn All aircraft POST MOD nnnnn and POST MOD mmmmm. POSTmmmmm i.e. A318/A319/A320/A321 that do have MOD nnnnn and MOD mmmmm embodied. POST nnnnn All aircraft that do have MOD nnnnn or aircraft that do not OR have MOD mmmmm . PREmmmmm A320-200 All A320-200, or OR All A321-100 that do not have MOD nnnnn embodied

. A321-100 PRE nnnnn A320-200 All A320-200 that do have MOD nnnnn embodied , or POST nnnnn All A321-100 that do have MOD nnnnn embodied and do OR not have MOD mmmmm embodied. A321-100 POST nnnnn PRE mmmmm POST nnnnn All aircraft that do have MOD nnnnn embodied.

(xx-yyyy) (xx-yyyy) is the Service Bulletin reference associated to the modification. CFM All aircraft equipped with CFM engines. IAE All aircraft equipped with IAE engines

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

. Since sub-part 4-3 intervals are based on statistical averages ancl reliability rates ; an exceptional short-term extension for a specific sub-part 4-3 interval may be made on one aircraft for a limited period of time without compromising the safety objectives declared at Type Certification. Repeated use of such extensions, either on the same aircraft or on similar aircraft in the Operator's fleet, should not be used as a substitute for good management practices

. Short-term extensions must not be used for fleet ASM escalation. Unless noted adjacent to the limitation , for all limitations identifi ed in the sub-part 4-3 , it has been accepted by the Primary Cert ification Office (EASA) that short
-term extensions up to the following maximum values may be granted without consultation with that office

. (1) Controlled by Flight Hours (FH) Extensions up to 10% or 500 FH (whichever is the lesser ) may exceptionally be granted on ASM limitations quoted in terms of Flight Hours

. ISSUE : JAN 08/08 ALS PART 4 - 0 PAGE : 11 ®AIRBUS SAS 2 008

. All nghts reserved

.

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION (2) Controlled by Flight Cycles or LanDinGs (FC or LOG) Extensions up to 5% or 250 FC/LDG (whichever is the lesser) may exceptionally be granted on ASM limitations quoted in terms of Flight Cycles or LanDinGs

. ( 3) Controlled by Calendar Time (Ye , Mo , etc .. .) Where the repeat interval is 12 Months or less , extensions up to 10% or 1 month (whichever is the lesser) may exceptionally be granted on ASM limitations quote d 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 .

E N D OF SUB-PART 4-0 I SS UE : JA N 08/08 ALS PART 4-0 PAGE: 12

**RBUS** SAS 2008

. All nghts reserved

# ~ 

# A318/A319/A320/A321 A I RWORTHINE S S LIMITATI O N S S ECT I ON Sub
- p a rt 4 - 1 I L LU STRATION S

ISS U E : JAN 08/08 ATA 

### 29-22

- RAM AIR TURB I NE (RAT) (Hamilton Sundstrand)
- FIG 01
ALS PART 4 - 1 •DAIRBUS SAS 2008

. All rights reserved PAGE: 119SC8

ISSUE JAN 08/08 

# ~ 

# A318/A319/A320/A321 AIRWORTH IN ESS LIMI TATIONS SECT ION

-IIAT EJECTION JACK

ATA 29-22
- RAM AIR TURBINE (RAT) (Dowty)- FIG. 02

ALS PART 4-1 © AIRBUS SAS 2008

. All ri ghts reserved

. RATOIIOUNO C H

EC I( MODU LE

PAGE · 2

# ~ 

# A31 8/A31

# 9/A320/A32'f AIRWORTHINESS LIMITATIONS SECTION

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

I SSUE

. JAN 08/08 A L S PART 

### 4 - 1 PAGE
- 

### 3 ®

AIRBUS SAS 2008
. All nghts reserved

.ISSUE: JAN 08/08

# ~ 

# A318/A319/A320/A32 1 AIRWORTHINESS LIM ITAT I ONS SECTI O N

Ret. actuato1 pin (rear spar side) Ret. actuator pin (malh fitting side)

I 

# L

---- - - - -' r--- - ---, 

# . . I I 

# . I I 

# . I I

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

ALS PART 4-1 © AIRBUS SAS 2008

. All rights reserved

. Pislon rod

PAGE. 4

# ~ 

# A3f 8/A3f9/A320/A32f AIRWORTHINESS LIMITATIONS SECTION

ATA 32-20- NLG DOOR UPLOCK- FIG 05

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

AIRBUS SAS 2008

. 

### All rights reserved

.

# ~ 

# A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTIO N

Air Data Modules are remotely mounted near and above the level of the pitot and static probes

B

ATA 34-12- AIR DATA MODULE
- FIG

. 06 END OF SUB-PART 4-1 ISSUE : JAN 08/08 ALS PART 4-1 ©AIRBUS SAS 2008

. All rights reserved

. PAGE: 6**~** A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECT I ON

Sub-part 4-2 SYSTEMS LIFE LIMITED COMPONENTS
Explanatory notes are located under each LIFE LIMITATION LIFE LIMITATION APPLICABILITY

assembly title. (Wlichever occurs first) Nomenclature Part Number FH LDG Cal. A318-100 A319-100 A320-100 A320-200 A320-200 A321-100 A321-200

Twin Bogie

ATA 29-23-00 HYDRAULIC PO W ER T R A NS F ER (F I G 0 3)

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

Power Transfer Uni t -211

(PTU) 1000 -2 1 2

4101002-3 N/A N/A X -214 X

(1) -231 '

-232 -211

1000 -212

4101002-4 (1) N/A N/A X - 214 X

-231

-232 -211

-212

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

-231 -232 -211 -212

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

I -231 -232 -211

-212

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

-231

-232

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

ISSUE : JAN 08/08 PAGE: 1

© AIRBUS SAS 2008. All nghts reserved .A31B/A319/A320/A321AIRWORTHINESSLIMITATIONSSECTIONExplanatorynotesarelocatedundereachLIFELIMITATIONLIFELIMITATIONAPPLICABILITYassemblytitle.(Whicheveroccursfirst)NomenclaturePartNumberFHLOGCal.A318-100A319-100A320-100A320-200A320-200A321-100A321-200TWinBogieATA32-10-00MAINLANDINGGEARRETRACTIONACTUATOR(FIG04){1)RetainingringP/N114094611andP/N114193606mustbereplacedbyanewoneeverytimeitisremovedfromthepistonhead.(2)RetainingringPIN114193643mustbereplacedbyanewoneeverytimeitisremovedfromthegland.Relactuatorpin{main114094617N/A20000N/AXfittingside)114094661N/A60000N/AX114193631N/A20000N/AXXXXX X114193637N/A60000N/AXXXXXX201590900N/A60000N/AXXXXXX201590903N/A60000N/AXPistonrod114094303N/A60000N/AX114094308N/A60000N/AX114193601N/A60000N/AXXXXXX201590907N/A60000N/AX201590908N/A60000N/AX XX X XXRetainingring(piston114094611N/A(1)N/AXrod)114193606N/A{1)N/AXXX X XXPistonhead114094608N/A60000N/AX114193603N/A60000N/AXXXXXXI201590909N/A60000N/AXXXXXX201590912N/A60000N/AXPistonheadnut114094605N/A60000N/AX114193604N/A60000N/AXXXXXX201590910N/A60000N/AXXXXX X201590911N/A60000N/AXALSPART4-2-----------------------------------EASAAPPROVEO-----------------------------------ISSUE:JAN08/08PAGE:2©AIRBUSSAS2008.AllrightsreseNed.**~** A31B/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION

Explanatory notes are located under each LIFE LIMITATIO N LIFE LIMITATION APPLICABILITY

assembly title. (Whichever occurs first) Nomenclature Part Number FH LOG Cal. A318-100 A319-100 A320-100 A320-200 A320-2 00 A321-100 A321-200 I

Twin Bog ie

Gland 114094604 N / A 60000 N / A X

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

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

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

201590914 N /A 60000 N / A X

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

Retaining ring (gland) 114 19 3643 N /A (2) N / A X X X X X X

Cylinder 11409 4600 N /A 60000 N /A X

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

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

201590904 N/A 60000 N/A X

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

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

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

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

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

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

201590902 N/A 60000 N /A X

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

Door uplock -211

C24730000-3 N /A 1000 N/A X -212

·231

ATA 34-12-00 NAVIGATION (FIG 06)

1 Air Data Module (ADM) -211

PG1 1 52AC02 N /A N/A 3Ye X -212 -231

-232

END OF SUB-PART 4-2 ALS PART 4-2 -------------------------------------------------------------- -- -----------------EASAAPPROVEO------------------------------------- ------- --------------------------------------

ISSUE: JAN 08/08 PAGE : 3

© AIRBUS SAS 2008. All nghts reserved .A318/A319/A320/A321AIRWORTHINESSLIMITATIONSSECTIONSub-part4-3SYSTEMSINSTALLATIONSMAINTENANCEREQUIREMENTSSub-part4-3-1Controlledatcomponent/sub-assemblylevelALSPART4MAINTENANCETASKSLIMITATIONSLIMITATIONAPPLICABILITY(whicheveroccursfirst)REFERENCETask.NumberZoneDescriptionThresholdIntervalPINAIRCRAFT292200-00001-1-EZ195RamAirTurbine(RAT)includingactuator-20Yrs20YrsAMM292251/401RATA318(HamiltonSundstrand)-FIG.01AMM292253/401759998ORRemoveRATandactuatorforoverhauland761618replacewithneworreconditionedunits.CMM762308A319CMM29-21-42762308ACMM29-21-447623088OR766352A320766352APOST27189ActuatorPRE28413764711A7647118ORA321292200-00002-1-EZ195RamAirTurbine(RAT)includingEjectionJack20Yrs20YrsAMM292251/401RATA320andAGCM-(Dowty)FIG.02AMM292252/40168020320PRE27189RemoveRAT,JackandAGCMforoverhaulandAMM292253/401680203037ORreplacewithneworreconditlonedunits.680203037ACMM29-21-21EjectionJackA320CMM29-21·24114160004POST28413CMM29-21-27114160004AICMM29-21-28114160005IAGCM769105A769106AISSUE·JAN08/08ALSPART4-3PAGE:1EASAAPPROVEo-----------------------------------------------------®AIRBUSSAS2008.Allrightsreserved.

# $ A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION ALS PART 4 AGEING SYSTEMS MAINTENANCE HISTORY FILE
1 - GENERAL The ALS Part 4 revision 00 has been created at the opportunity of the life extension study for the A320-200 aircraft (MOD 37734 ). Systems
- related limitations included 

### in the ALS Part 1 revision 00 have been transferred to ALS Part 4 - 2

. 2 - SUMMARY OF CHANGES The following summarizes the c hanges with respect to the previous issues of A318/A319/A320/A321 ALS Part 

### 4
. N/A

I SSUE ; JAN 08/0 8 ALS PAR T 4 HIS T ORY F IL E PAGE. 1/1 ©AIRBUS SA$ 2008

. All rights reserved**~** A318/A319/A320/A321 AIRWORTHINESS LIMITATIONS SECTION

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

ALS PART 4 MAINTENANCE TASKS LIMITATIONS LIMITATION APPLICABILITY

(Whichever occurs first) REFERENCE

Task Number Zone Description Threshold Interval P/N AIRCRAFT

324400-0001-1-E Z190 Parki n g/U lt i m ate e me rgenc y bra k in g s ys t em 60000 FH 60000 FH AMM 324400/501 N/A A320-200

Functional check of the Brake Accumulator 324400-720-002 PRE26925

system with the Parking Brake not applied PRE 20139 OR A320-200

PRE 26925

POST 20139

POST 22129

- ---

END OF SUB-PART 4 - 3 ALS PART 4-3 -----------------------------------EASAAPPROVEo---------------- ---- ---------------

ISSUE JAN 08/08 PAGE: 2

© AIRBUS SAS 2008. All rights reseNed.