A318/A319/A320/A321 Airworthiness Limitations Section (ALS) … · 2021. 3. 16. · A321 NEO ACF...

AIRBUS SAS 2019. 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.

ISSUE: NOV 07/19

C80_ALS Part 4 Scheduled Revision Template_FM1404456_v4.0

A318/A319/A320/A321

Airworthiness Limitations Section (ALS)

Part 4

System Equipment Maintenance Requirements (SEMR)

-

Revision 07 Issue 02

A320 Family

AIRWORTHINESS LIMITATIONS SECTION

ISSUE: NOV 07/19 ALS PART 4 - TOC PAGE: 2/37

© AIRBUS SAS 2019. All rights reserved. Confidential and proprietary document.

TABLE OF CONTENTS

REVISION STATUS ................................................................................................................... 4

COMPLIANCE TIME .................................................................................................................. 6

SECTION 1. INTRODUCTION ............................................................................... 7

1. GENERAL ...........................................................................................................................................7

2. APPLICABILITY .................................................................................................................................7

3. MAINTENANCE PROGRAM PUBLICATION ....................................................................................8

4. DEFINITION OF ALS PART 4 CONTENT....................................................................................... 11

4.1 SYSTEMS LIFE-LIMITED COMPONENTS ............................................................................... 11

4.1.1 LIFE LIMITS ......................................................................................................................... 11

4.1.2 CURRENT DEMONSTRATED LIVES ................................................................................. 11

4.2 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS .............................................. 11

4.2.1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVEL ............................................. 11

4.2.2 CONTROLLED AT AIRCRAFT SYSTEM LEVEL ................................................................ 12

5. BASIC RULES ................................................................................................................................. 12

5.1 CLOCK STARTING POINT FOR SEMR .................................................................................... 12

5.1.1 AT AIRCRAFT LEVEL ......................................................................................................... 12

5.1.2 AT COMPONENT/ITEM LEVEL .......................................................................................... 12

5.2 TRACEABILITY .......................................................................................................................... 13

5.3 INTENTIONALLY LEFT BLANK ................................................................................................ 13

5.4 TRANSFER OF FATIGUE RELATED COMPONENTS/ITEMS BETWEEN AIRCRAFT APPLICATIONS/AIRCRAFT CONFIGURATION CHANGE ...................................................... 13

5.5 DISPOSAL/QUARANTINE ACTION .......................................................................................... 14

5.6 EXCEPTIONAL SHORT-TERM EXTENSIONS FOR SEMR ITEMS LISTED IN SECTION 4 .. 15

6. INTENTIONALLY LEFT BLANK ..................................................................................................... 15

7. PRODUCTION CONCESSIONS, REPAIRS, ALS VARIATIONS, AIRWORTHINESS DIRECTIVES AND ALTERNATIVE METHODS OF COMPLIANCE .............................................. 15

8. MODIFICATIONS/REPAIRS NOT DEVELOPED BY AIRBUS DOA CERTIFICATE EASA.21J.031 .................................................................................................................................. 16

SECTION 2. EXPLANATION OF TABLE FORMAT ............................................. 17

1. SYSTEMS LIFE-LIMITED COMPONENTS (SECTION 3) .............................................................. 17

2. SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS (SECTION 4) ............................ 20

SECTION 3. SYSTEMS LIFE LIMITED COMPONENTS ...................................... 24

SECTION 4. SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS .... 25

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - TOC PAGE: 3/37


1. CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVEL ....................................................... 25

2. CONTROLLED AT AIRCRAFT SYSTEM LEVEL ........................................................................... 25

APPENDIX A. ABBREVIATIONS ........................................................................... 26

APPENDIX B. TERMS AND DEFINITIONS ............................................................ 29

APPENDIX C. LIST OF DELETED TASK ............................................................... 31

APPENDIX D. HISTORY FILE ................................................................................ 32

APPENDIX E. SUMMARY OF CHANGES .............................................................. 36

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - REVISION STATUS PAGE: 4/37


REVISION STATUS

The ALS Part 4 is approved and Variations must also be approved.

The technical content of this Revision is approved under the authority of the DOA ref. EASA.21J.031.

Note: the present Revision includes ALS data already approved either by EASA for major changes or by Airbus under DOA privilege for minor changes.

REVISION NUMBER APPROVAL REFERENCE APPROVAL DATE

07 D050419070 OCT 11/19

07 issue 02 D050419070 issue 02 NOV 07/19

This Revision contains all approved changes to A318/A319/A320/A321 ALS Part 4 since the last Revision

Issue 02 of considered Revision has been issued in order to administratively update description of ALS part 4 SEMR tasks 361101-00003-1-E / -2-E from “Discard seal 32” to “Discard Wing Anti Ice tapping seals” ; this aims to restore consistency of ALS documentation with IPC / AMM documentation.

This includes changes published through the following Variations:

VARIATION NUMBER REASON OF THE VARIATION

6.1 MOD 160766 introduces new A321 NEO ACF A/C models. For those aircrafts, this Variation introduces a new SEMR task (ref. 522101-00001-1-E) related to Over Wing Door (OWD).

6.2

A321 NEO ACF aircraft (A321 POST 160766) were subject to SEMR task 522101-00001-1-E (“Set the OWD handle back to the closed position”) introduced through Variation 6.1 to A318/A319/A320/A321 ALS Part 4 Revision 06. MODs 164456 and 164457 introduce modification of door mechanism of forward (FWD) / afterward (AFT) Over Wing Door (OWD). This Variation supersedes previous Variation 6.1 : Indeed, it revises SEMR task 522101-00001-1-E, and clarifies that OWD handle is no more required to be set back to the closed position, on OWD(s) of aircraft where MOD(s) 164456 and / or 164457 has (have) been embodied.

6.3

This Variation aims at providing the impact on the mandatory instructions and airworthiness limitations published in the A318/A319/A320/A321 ALS Part 4 Revision 06 following applicability extension of MOD 160177 to A321-100 aircraft series.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - REVISION STATUS PAGE: 5/37


6.4

This Variation aims at providing the impact on the mandatory instructions and airworthiness limitations published in the A318/A319/A320/A321 ALS Part 4 Revision 06 issue 2 related to :

new life limitations for ATA 29 rods P/Ns (D00031070004 & D00031070006)

and new SEMR maintenance requirement to "DISCARD WING BELLOW" (tasks 361101-00002-1-E & 361101-00002-2-E).

6.5

MOD 161004 introduces the new A319-151N aircraft model. MOD 165511 introduces the new A319-153N aircraft model. MOD 162338 introduces envelope for design weight of A319 NEO ACJ aircraft. This MOD is used as marker of A319 NEO ACJ configuration. This Variation aims to provide the impact on the mandatory instructions and airworthiness limitations published in the A318/A319/A320/A321 ALS Part 4 Revision 06 issue 02 following embodiment of MOD 161004 and/or MOD 165511 and/or MOD 162338.

This includes also additional changes that were not published through Variations. For detailed traceability in the SOC, group of change has been defined as follow:

GROUP OF CHANGES REASON OF THE CHANGE

A Introduction of SEMR tasks 361101-00003-1-E and 361101-00003-2-E related to ATA 36 WAI Tapping Seal.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - COMPLIANCE TIME PAGE: 6/37


COMPLIANCE TIME

Airbus recommends Operators to consider the implementation of the new or revised instructions and airworthiness limitations introduced by Airbus A318/A319/A320/A321 ALS Part 4 Revision 07 in the Operators approved Maintenance Program (OMP) at the next scheduled opportunity. Maintenance tasks and/or replacement of items in SECTIONS 3 and 4 are to be accomplished prior to the new/revised thresholds and/or intervals provided in this Revision.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - SECTION 1 PAGE: 7/37


SECTION 1. INTRODUCTION

1. GENERAL

The ALS Part 4 provides System Equipment Maintenance Requirements (SEMR) which refer to preventative maintenance requirements (including replacement) found necessary to comply with safety objectives (associated to hazardous or catastrophic failure conditions) by stabilization of equipment failure rate. Those requirements shall be complied with, as per EASA Part M.A.302 – Aircraft Maintenance Program.

2. APPLICABILITY

The A318/A319/A320/A321 ALS Part 4 applies to the following aircraft series and models:

AIRCRAFT SERIES AIRCRAFT MODELS

A318

A318-111

A318-112

A318-121

A318-122

A319

A319-111

A319-112

A319-113

A319-114

A319-115

A319-131

A319-132

A319-133

A319-151N

A319-153N

A320

A320-211

A320-212

A320-214

A320-215

A320-216

A320-231

A320-232

A320-233

A320 Family




AIRCRAFT SERIES AIRCRAFT MODELS

A320

A320-251N

A320-252N

A320-253N

A320-271N

A320-272N

A320-273N

A321

A321-111

A321-112

A321-131

A321-211

A321-212

A321-213

A321-231

A321-232

A321-251N

A321-252N

A321-253N

A321-271N

A321-272N

A321-251NX

A321-252NX

A321-253NX

A321-271NX

A321-272NX

Note: The A320-100 aircraft series has been permanently withdrawn from service.

3. MAINTENANCE PROGRAM PUBLICATION

The published maintenance program content is provided for aircraft operating up to the publication trigger quoted in the table below. Operation beyond these values requires an update of the ALS Part 4 data that are approved by the EASA. Should any operator envisage future operations beyond the quoted values, they must first contact Airbus for advice.

A320 Family




AIRCRAFT CONFIGURATION

PUBLICATION TRIGGER (Whichever occurs first)

FLIGHT HOURS (FH) FLIGHT CYCLES (FC)

A318-1xx 60 000 48 000

A319-1xx CEO PRE 155789 (Excluding Corporate Jet Operations)

60 000 48 000

A319 CJ (Corporate Jet Operations) (A319 CEO POST 28162 POST 28238 POST 28342 OR A319 NEO POST 162338)

77 400 18 000

A319-1xx CEO POST 160080 (Excluding Corporate Jet Operations)

96 000 48 000

A319-1xx CEO POST 155789 (Excluding Corporate Jet Operations)

120 000 60 000

A320-2xx CEO PRE 37734 PRE 39020 60 000 48 000

A320-2xx CEO POST 37734 PRE 39020 80 000 37 500

A320-2xx CEO POST 39020 [excluding A320-2xx CEO POST 20139 PRE 22129 POST 39020]

120 000 60 000

A320-2xx CEO POST 20139 PRE 22129 POST 39020

63 500 45 000

A320-2xx CEO POST 160080 96 000 48 000

A320 CJ (Corporate Jet Operations) (A320 POST 162339)

77 400 18 000

A321-1xx / -2xx CEO PRE 154881 PRE 156130 60 000 48 000

A321-1xx / -2xx CEO POST 154881 PRE 156130 74 000 37 000

A321-1xx / -2xx CEO POST 156130 120 000 60 000

A319 / A320 / A321 NEO aircraft (Excluding Corporate Jet Operations)

96 000 48 000

Note:

- A319 / A320 / A321 CEO (Current Engine Option) aircraft are A319 / A320 / A321 aircraft not fitted with NEO engine.

- A319 CEO used as Corporate Jet Operations (included in A319-VIP) have received MOD 28238, MOD 28162 and MOD 28342 in production.

- A319 NEO used as Corporate Jet Operations (included in A319-VIP) have received MOD 162338 in production.

- A320 NEO used as Corporate Jet Operations (A320-VIP) have received MOD 162339 in production.

- MOD 155789 refers to Design Service Goal (DSG) extension of A319-1xx CEO aircraft up to 120 000 FH or 60 000 FC, whichever occurs first.

A320 Family






For the particular case of A320-2xx CEO POST 20139 PRE 22129, MOD 39020 refers to Design Service Goal (DSG) extension of A320-2xx CEO POST 20139 PRE 22129 up to 63 500 FH or 45 000 FC.

- MOD 154881 refers to Design Service Goal (DSG) extension of A321-131 aircraft (MSN

00385, MSN 00550 and MSN 00591), A321-211 aircraft (MSN 00677, MSN 00781, MSN

00815, MSN 00841, MSN 00852, MSN 01238, MSN 01250 and MSN 01720) and A321-

231 aircraft (MSN 00663, MSN 00668, MSN 00787, MSN 00878, MSN 00915 and MSN

00954) up to 74000 FH or 37000 FC, whichever occurs first.

- MOD 160080 introduces the sharklet devices in the A319-1xx CEO or A320-2xx CEO in-

service aircraft and extends the Design Service Goal (DSG) of the A319-1xx CEO

(excluding Corporate Jets Operations) POST MOD 160080 or A320-2xx CEO POST MOD

160080 up to 96 000 FH or 48 000 FC, whichever occurs first.

- MOD 156130 refers to Design Service Goal (DSG) extension of A321-1xx / -2xx CEO

aircraft up to 120 000 FH or 60 000 FC, whichever occurs first.

- A319 / A320 / A321 NEO aircraft includes:

A319-151N (A319 POST MOD 161004), A319-153N (A319 POST MOD 165511), A320-251N (A320 POST MOD 161003), A320-252N (A320 POST MOD 162680), A320-253N (A320 POST MOD 161860), A320-271N (A320 POST MOD 161000), A320-272N (A320 POST MOD 163955), A320-273N (A320 POST MOD 162512), A321-251N (A321 POST MOD 161005), A321-251NX (A321 POST MOD 161005 POST MOD 160766), A321-252N (A321 POST MOD 162681), A321-252NX (A321 POST MOD 162681 POST MOD 160766), A321-253N (A321 POST MOD 161006), A321-253NX (A321 POST MOD 161006 POST MOD 160766), A321-271N (A321 POST MOD 161002), A321-271NX (A321 POST MOD 161002 POST MOD 160766), A321-272N (A321 POST MOD 162038) and A321-272NX (A321 POST MOD 162038 POST MOD 160766). For all these aircraft (excluding A319 NEO Corporate Jet) a Design Service Goal (DSG) of 96 000 FH or 48 000 FC, whichever occurs first, has been set.

A320 Family




4. DEFINITION OF ALS PART 4 CONTENT

4.1 SYSTEMS LIFE-LIMITED COMPONENTS

Components/items listed under SECTION 3 are those affected by a replacement requirement associated to a life limitation and whose failure could contribute to an unsafe condition of the aircraft.

For a given PNR, when more than one set of limitations is published for the same application, the selection depends on the aircraft utilization. No combination of limitations from different sets is permitted.

Life limitations quoted in SECTION 3 are applicable to the undamaged detail components/items as listed, not to the assembly or the aircraft on which they are installed.

4.1.1 LIFE LIMITS

ALS Part 4 contains, in SECTION 3, components/items having a life limit due to failure during tests and whose failure could result in a catastrophic or hazardous failure condition. Their Part Numbers (PNR) are labelled “LL” in the table.

4.1.2 CURRENT DEMONSTRATED LIVES

ALS Part 4 contains, in SECTION 3, components/items having a demonstrated life limitation, which is temporary waiting for completion of the tests. Their PNRs are labelled “DL” in the table.

4.2 SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS

The maintenance tasks given in SECTION 4 include airworthiness limitations set to prevent the aircraft systems failures, which could contribute to an unsafe condition of the aircraft.

Note: Credit may be taken for accomplishment of the Maintenance Review Board Report (MRBR) Systems and Power plant section maintenance tasks, providing that they are performed with the same inspection level, at least as frequently as the inspection threshold and interval quoted in this document.

SECTION 4, paragraph 1 and paragraph 2 provide maintenance requirements and airworthiness limitations at component level and aircraft (system) level respectively.

4.2.1 CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVEL

SECTION 4, paragraph 1 identifies maintenance tasks controlled at component/item level. The recurrent maintenance requirements are applicable no later than the component/item, not the aircraft, reaching the airworthiness limitation.

When components/items given in SECTION 4, paragraph 1 reach the stated airworthiness limitations, the given maintenance task must be carried out. Any component/item removed from the aircraft for any reason, (such as failure of functional check, degradation of condition, etc.) shall be replaced by a serviceable component/item, which has not reached the stated airworthiness limitations.

A320 Family




4.2.2 CONTROLLED AT AIRCRAFT SYSTEM LEVEL

SECTION 4, paragraph 2 identifies maintenance tasks controlled at aircraft level. The recurrent maintenance requirements are applicable no later than the aircraft, not the component/item, reaching the airworthiness limitation.

The maintenance tasks listed in SECTION 4, paragraph 2 must be carried out when the aircraft reaches the stated airworthiness limitation. Should a failure to reach the task requirements be detected, the appropriate trouble-shooting must be carried out and the relevant suspected components/items replaced in accordance with the Aircraft Maintenance Manual (AMM) procedures. Following any replacements, the listed maintenance tasks must be repeated until a successful maintenance task recording can be entered.

5. BASIC RULES

5.1 CLOCK STARTING POINT FOR SEMR

This paragraph provides general rules related to the starting point for calculation of due dates or times for limitations and maintenance requirements identified in this document according to the different usage parameters.

5.1.1 AT AIRCRAFT LEVEL

For maintenance tasks in SECTION 4 paragraph 2:

- The threshold is applied from the initial Entry-Into-Service of the aircraft (unless otherwise stated).

- The next interval is calculated from the original due date of the last accomplishment of the task, excluding any exceptional short-term extensions from calculation.

When alternative inspection methods are provided, the next interval applicable is the one associated with the inspection method used at last inspection.

For maintenance tasks in SECTION 4 paragraph 2 whose interval is changed, the next accomplishment must be determined from previous accomplishment date unless otherwise stated.

The time to start the clock for maintenance tasks with applicability determined by post-delivery modification is the date of MOD embodiment.

5.1.2 AT COMPONENT/ITEM LEVEL

For the transferable systems components/items, the starting point or initial Entry-Into-Service is defined as the date at which the component/item accomplishes the first flight for which it will undertake its intended function (unless otherwise stated).

For the components/items in SECTION 3:

- The life limitation indicated against PNR originally fitted is counted from the first flight of the component/item (unless otherwise stated).

- The life limitation indicated against PNR evolutions is also to be counted from the first flight of the component/item (unless otherwise stated).

A320 Family




For maintenance tasks in SECTION 4, paragraph 1:

- The threshold is applied from the initial Entry-Into-Service of the component/item (unless otherwise stated).

- The next interval is calculated from the original due date of the last accomplishment of the task limitation, excluding any exceptional short-term extensions from calculation.

When alternative inspection methods are provided, the next interval applicable is the one associated with the inspection method used at last inspection.

For maintenance tasks in SECTION 4 paragraph 1 whose interval is changed, the next accomplishment must be determined from previous accomplishment date unless otherwise stated.

The time to start the clock for maintenance tasks with applicability determined by post-delivery modification is the date of MOD embodiment.

5.2 TRACEABILITY

Components/items listed under SECTION 3 and SECTION 4 paragraph 1 have to be considered as “life-limited” components and therefore it is necessary to assure traceability and monitoring of these parts as per EASA Part M.A.305 - Aircraft continuing airworthiness record system.

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 of the part, so that life limitations are accurately applied. Traceability records may comprise, but are not limited to, the following:

- Application history (aircraft type, model, weight variant, 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/item may have been fitted).

Where the complete life history of a component/item is not known, Operators are requested to refer to In-Service Information ISI 00.05.00002 for guidance. It provides the means to manage such components/items. It has been issued in agreement with the European Aviation Safety Agency (EASA).

Note: Traceability and monitoring of component/item is not required for consumable component for which replacement is controlled at assembly/aircraft level.

5.3 INTENTIONALLY LEFT BLANK

5.4 TRANSFER OF FATIGUE RELATED COMPONENTS/ITEMS BETWEEN AIRCRAFT APPLICATIONS/AIRCRAFT CONFIGURATION CHANGE

The airworthiness limitation(s) for a fatigue-related (i.e. ATA 27 and 32) component/item fitted to an aircraft may be different when:

- The component/item is transferred to another application (aircraft type, aircraft model, weight variant, etc.),

- The aircraft configuration is changed as a result of MOD/SB embodiment (weight variant, landing gear standard, etc.).

A320 Family




In these cases, the component/item’s remaining life must be calculated using the following formula:

i

j

j

i CpCp

Ca1Tr

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 values in SECTION 1, paragraph 3. MAINTENANCE PROGRAM PUBLICATION shall be used.

Note 1: When using the above formula, Tri, Caj, Cpj and Cpi are expressed in the same usage parameter (e.g. FH or FC or LDG): Usage parameters cannot be mixed in the same calculation.

Note 2: The remaining life calculation must be reassessed every time the component/item’s airworthiness limitation(s) change(s) for current and/or previous aircraft application(s) to which the component/item is/was fitted.

5.5 DISPOSAL/QUARANTINE ACTION

When the components/items reach the life limitations, disposal/quarantine action shall be taken, as per EASA Part M.A.504 - Control of unserviceable components, which asks for a status of life limited components and a life limited components log card. Disposal/quarantine action depends on the following categories:

For “life-limited” components/items listed in the SECTION 3 and labelled “LL”: They shall be mutilated beyond repair limits to prevent rework to appear to be airworthy.

Note 1: The ultimate solution is the mutilation beyond repair limits to prevent rework to appear to be airworthy, as per EASA Part M, AMC M.A.504 – Control of unserviceable components.

Note 2: Some means may exist to extend their life potential provided they are applied prior to reaching the life-limit (e.g. Service Bulletin: POST SB PNR).

For components/items whose fatigue lives have been demonstrated, labelled “DL” and listed in the SECTION 3: Appropriate means shall be implemented to deter their installation on aircraft pending possible extension of their life limitations. Examples of means are:

- Record keeping system,

- Non-permanent markings,

- Segregation (components stored separately from those currently eligible for installation).

Note: When consumable components are removed, they must be mutilated beyond repair limits to prevent rework to appear to be airworthy.

A320 Family




5.6 EXCEPTIONAL SHORT-TERM EXTENSIONS FOR SEMR ITEMS LISTED IN SECTION 4

Since SECTION 4 System Installation Maintenance Requirements intervals are based on statistical averages and reliability rates, an exceptional short-term extension for a specific SECTION 4 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 SEMR escalation.

Unless noted adjacent to the airworthiness limitation, for all airworthiness limitations identified in the SECTION 4, 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 SEMR 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 SEMR airworthiness limitations quoted in terms of Flight Cycles or Landings.

(3) Controlled by Calendar Time

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 SEMR 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.

This paragraph in the ALS Part 4 is written to confirm to the Authority of the State of aircraft registry that exceptional short-term extensions are permissible. Approval of such extensions rests with the Authority of the State of aircraft registry in the same way as it does for any other scheduled maintenance task interval extension.

Note: No short-term extensions are permissible for maintenance tasks previously required by individual ADs. These items will be highlighted by a note in the task description column.

6. INTENTIONALLY LEFT BLANK

7. PRODUCTION CONCESSIONS, REPAIRS, ALS VARIATIONS, AIRWORTHINESS DIRECTIVES AND ALTERNATIVE METHODS OF COMPLIANCE

Limitations of the ALS Part 4 may be superseded by instructions given in either a production concession, a repair solution, an ALS Variation, an Alternative Method of Compliance (AMOC), an Airworthiness Directive (AD) or exemptions provided by National Aviation Authorities (e.g. exemption supported by ASAC – Airbus Statement of Airworthiness Compliance).

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

A320 Family




When a limitation affected by a production concession/repair solution/AD/AMOC is amended within the Revision of the ALS Part 4 subsequent to the issuance date of the production concession/repair solution/AD/AMOC, Operators are requested to contact Airbus for guidance to establish impact on the production concession/repair solution/AD/AMOC.

8. MODIFICATIONS/REPAIRS NOT DEVELOPED BY AIRBUS DOA CERTIFICATE EASA.21J.031

If an aircraft/component has a modification or repair embodied, that has not been developed under the authority of Airbus Design Organisation Approval (DOA) No EASA.21J.031, and affects the content of the ALS, the Design Approval Holder (e.g. Supplementary Type Certificate (STC) holder) is responsible to provide any necessary adaptations of the ALS Part 4 airworthiness limitations.

A320 Family




SECTION 2. EXPLANATION OF TABLE FORMAT

The Systems Life-Limited Components are presented in SECTION 3 of ALS Part 4 and Systems Installation Maintenance Requirements are presented in SECTION 4 of ALS Part 4. Detailed information is given below to explain tables provided on subsequent pages.

1. SYSTEMS LIFE-LIMITED COMPONENTS (SECTION 3)

Explanation notes are located under the table.

LL/DL

LIMITATIONS (Whichever occurs first)

LIMITATIONS APPLICABILITY

NOMENCLATURE PART NUMBER FH LDG FC Cal. A318-1xx

A319-1xx CEO

A319-1xxN NEO

A320-2xx CEO Twin

A320-2xx CEO Bogie

A320-2xxN NEO

A321-1xx CEO

A321-2xx CEO

A321-2xxN/NX NEO (including

ACF)

ATA XX-XX-XX ATA NAME

(1) [Note 1]

(2) [Note 2]

…/…

NOTES

Explanation notes are located under the table. When several notes are provided in the same cell the logical “AND” applies between the different configurations/conditions.

(1) NOMENCLATURE

This column provides the nomenclature of the part number given on the right-hand side column.

(2) PART NUMBER

This column provides the part number impacted by the life limits/current demonstrated lives.

A320 Family




SECTION 3 provides the airworthiness limitations for systems components/items that have been certified on the aircraft series/models stated in the SECTION 1 paragraph 2. APPLICABILITY. Refer to Illustrated Part Catalogue (IPC) for PNR identification.

PNR provided by SECTION 3 for ATA 32 items relate to detail parts, which may not all be listed in Illustrated Parts Catalogue (IPC) issued by Airbus are listed in the relevant Component Maintenance Manual (CMM) issued by vendors. This is the case, for example, when the procurable replacement part is delivered as an assembly.

(3) LL/DL

Components/items having a life limit (LL) due to failure during fatigue tests will be labelled “LL”.

Components/items having a current demonstrated life (DL) without failure will be labelled “DL”.

(4) LIMITATIONS

Limitations are provided in usage parameters, e.g.:

- FH: Flight Hours,

- FC: Flight Cycles/LDG: Landings,

- Cal.: Calendar time in year, months, etc.

(5) LIMITATIONS APPLICABILITY

Limitation applicability is allocated to aircraft affected, according to:

- AIRCRAFT TYPE, SERIES AND MODELS

Table headers (second line) indicate aircraft models. When ‘x’ is entered in the model number, it stands for any number within the limits of the list of models given in SECTION 1, paragraph 2 APPLICABILITY, e.g.:

A318-11x stands for: A318-111, A318-112

A320-2xx CEO Twin stands for: A320-200 CEO PRE 20139 OR A320-200 CEO POST 22129 (A320-200 CEO fitted with 2 wheels bogie Main Landing Gears)

A320-2xx CEO Bogie stands for: A320-200 CEO POST 20139 PRE 22129 (A320-200 CEO fitted with 4 wheels bogie Main Landing Gears)

A320 Family




Limitation applicability is allocated according to the aircraft model affected, e.g.:

X stands for: All aircraft defined by the applicability of the column

-212 stands for: -212 model only, defined by the applicability of the column

-27xN stands for: All aircraft models defined by the applicability of the column, where “x” stands for any relevant number between 0 and 9 (models -271N, -272N, …)

-27xNX stands for: All aircraft models defined by the applicability of the column, where “x” stands for any relevant number between 0 and 9 (models -271NX, -272NX, …)

Excl. -113 stands for: All aircraft models defined by the applicability of the column, excluding the -113 model

- AIRCRAFT MANUFACTURER SERIAL NUMBER

XXXXX-YYYYY stands for: From aircraft MSN XXXXX to aircraft MSN YYYYY (for all aircraft defined by the applicability of the column)

XZXZX, YZYZZ stands for: Aircraft MSN XZXZX and aircraft MSN YZYZZ

XZXZX stands for: Aircraft MSN XZXZX only

Excl. XXXXX stands for: All aircraft (defined by the applicability of the column), excluding MSN XXXXX

A320 Family




2. SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS (SECTION 4)

ALS PART 4 MAINTENANCE TASKS LIMITATIONS REFERENCE

LIMITATIONS APPLICABILITY

TASK NUMBER ZONE DESCRIPTION THRESHOLD INTERVAL PNR AIRCRAFT

(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 centerline, 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 - M E F YY - Z - E

E stands for SEMR.

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

YY is sequential number.

F is engine type information when more than one engine from the same manufacturer is applicable to the program. As it is not applicable to A318/A319/A320/A321 maintenance references, it is always set to ‘0’ in this document.

E is engine/APU/… manufacturer identification. ‘0’ is the default value.

A320 Family




XXXXXX - M E F YY - Z - E

M is used to differentiate aircraft series in Airbus numbering system to which maintenance tasks are applicable. As it is not applicable to A318/A319/A320/A321 maintenance references, it is always set to ‘0’ in this document.

XXXXXX is ATA 1000 task reference.

(2) DESCRIPTION

This column provides the following information:

- Task Description, which contains basic description of the maintenance task to be performed.

- Note, where given, it states further requirements and/or provides useful information.

(3) THRESHOLD/INTERVAL

These columns are used to record the selected threshold and interval for the task. The threshold and interval may be expressed in terms of usage parameters or notes.

Usage parameters are defined in APPENDIX B.

(4) REFERENCE

This column provides reference to Instructions for Continued Airworthiness where maintenance practices/procedures necessary for the task accomplishment are provided, e.g. the AMM.

Where reference is made to an Airbus SB, it must be assumed that the latest approved revision of the SB is applicable, but any previous revision is acceptable.

Where a particular revision is stated, the revision or any later approved revision must be used.

A320 Family




(5) LIMITATIONS APPLICABILITY

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

- PNR

SECTION 4 tables provide the airworthiness limitations for systems components/items that have been certified on the aircraft series/models stated in the SECTION 1 paragraph 2. APPLICABILITY. Refer to Illustrated Part Catalogue (IPC) for PNR identification.

PNR provided by SECTION 4 for ATA 32 items relate to detail parts, which may not all be listed in Illustrated Parts Catalogue (IPC) issued by Airbus are listed in the relevant Component Maintenance Manual (CMM) issued by vendors. This is the case, for example, when the procurable replacement part is delivered as an assembly.

- Aircraft

APPLICABILITY TASK APPLICABLE TO

ALL All A318, A319, A320 and A321 aircraft.

A320-xxx A320-xxx series aircraft.

PRE NNNNN All aircraft on which modification NNNNN has not been embodied.

POST NNNNN All aircraft on which modification NNNNN has been embodied.

POST NNNNN POST MMMMM

All aircraft on which modification NNNNN and modification MMMMM have been embodied.

POST NNNNN OR

PRE MMMMM

All aircraft on which modification NNNNN has been embodied or modification MMMMM has not been embodied.

A320-200 OR

A321-100 PRE NNNNN

All A320-200, or All A321-100 on which modification NNNNN has not been embodied.

A320 Family




APPLICABILITY TASK APPLICABLE TO

A320-200 POST NNNNN

OR A321-100

POST NNNNN PRE MMMMM

All A320-200 on which modification NNNNN has been embodied, or All A321-100 on which modification NNNNN has been embodied and modification MMMMM has not been embodied.

POST NNNNN (xx-yyyy)

All aircraft on which modification NNNNN has been embodied. (xx-yyyy) is the Service Bulletin reference associated to the modification NNNNN.

CFM All aircraft equipped with CFM engines.

IAE All aircraft equipped with IAE engines.

PW All aircraft equipped with Pratt and Whitney engines.

LEAP-1A A320 fitted with new CFM engines, also called CFM LEAP-1A engines.

A320 Family




SECTION 3. SYSTEMS LIFE LIMITED COMPONENTS

Systems life-limited components with limitations at component/item level can be found in the embedded Excel file “SA ALS Part 4 Revision 07 Issue 02.xlsx”.

A320 Family




SECTION 4. SYSTEMS INSTALLATION MAINTENANCE REQUIREMENTS

1. CONTROLLED AT COMPONENT/SUB-ASSEMBLY LEVEL

Systems installation maintenance requirements controlled at component/sub-assembly level can be found in the embedded Excel file “SA ALS Part 4 Revision 07 Issue 02.xlsx”.

2. CONTROLLED AT AIRCRAFT SYSTEM LEVEL

Systems installation maintenance requirements controlled at aircraft system level can be found in the embedded Excel file “SA ALS Part 4 Revision 07 Issue 02.xlsx”.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX A PAGE: 26/37


APPENDIX A. ABBREVIATIONS

ABBREVIATION MEANING

A/C Aircraft

ACF Airbus Cabin-Flex

ACJ Airbus Corporate Jet

AD Airworthiness Directive

ADM Air Data Module

AFT Afterward

AGCM Airborne Ground Check Module

ALS Airworthiness Limitations Section

AMC Acceptable Means of Compliance

AMM Aircraft Maintenance Manual

AMOC Alternative Method of Compliance

APU Auxiliary Power Unit

ASAC Airbus Statement of Airworthiness Compliance

ATA Air Transport Association of America

Cal. Calendar Time

CAS Cabin Attendant Seat

CEO Current Engine Option

CFM CFM International

CJ Corporate Jet

CMM Component Maintenance Manual

D Deleted

DL Current Demonstrated Lives

DOA Design Organization Approval

DSG Design Service Goal

DY Day

EASA European Aviation Safety Agency

ESG Extended Service Goal

FAA Federal Aviation Administration

FC Flight Cycle

A320 Family





FH Flight Hour

FWD Forward

IAE International Aero Engines

IPC Illustrated Part Catalogue

ISI In-Service Information

LDG Landing

LH Left Hand

LL Life Limits

MLG Main Landing Gear

MO Month

MOD Modification

MPD Maintenance Planning Document

MRBR Maintenance Review Board Report

MSN Manufacturer Serial Number

N New

N/A Not Applicable

NBB No-Back Brake

NDT Non-Destructive Test

NEO New Engine Option

NTM Non-destructive Testing Manual

OMP Operators approved Maintenance Program

OWD Over Wing Door

PCE Pre Cooler Exchanger

PRDL Pressure Relief Door Latch

PNR Part Number

PTU Power Transfer Unit

PW Pratt and Whitney

R Revised

RAT Ram Air Turbine

RH Right Hand

A320 Family





SB Service Bulletin

SEMR System Equipment Maintenance Requirements

SOC Summary of Changes

STC Supplemental Type Certificate

TC Type Certificate

THS Trimmable Horizontal Stabilizer

THSA Trimmable Horizontal Stabilizer Actuator

TOC Table Of Contents

VSB Vendor Service Bulletin

WAI Wing Anti-Ice

Ye Years

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX B PAGE: 29/37


APPENDIX B. TERMS AND DEFINITIONS

TERM DEFINITION

CALENDAR TIME (CAL.)

Airworthiness limitations in Years (Ye), in Months (Mo), etc… must be counted from the date of initial Entry-Into-Service of the component/part, unless otherwise stated. Storage, maintenance, etc… do not freeze calendar time accumulation but during those cases the life limit is not considered as exceeded since the aircraft is not in airworthy conditions. Nevertheless the component/part must be replaced before the release to service of the aircraft. Month(s): equivalent of 1 calendar month (can be calculated as 1/12 calendar year). Year(s): equivalent of 12 calendar months (can be calculated as 365, 25 days).

COMPLIANCE TIME

Period of time given to Operators to accomplish maintenance tasks and/or replace items (at component or aircraft level) having exceeded or close to exceed the new/reduced airworthiness limitations provided in the Revision/Variation.

DETAILED INSPECTION

An intensive examination of a specific component/item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required.

ENTRY INTO SERVICE

The initial Entry-Into-Service is defined for the aircraft (systems installations) as:

The date of Transfer of Title to the first Operator for airworthiness limitations in Calendar times, unless otherwise stated in any delivery documentation to the first Operator.

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

The initial Entry-Into-Service for the transferable systems components/items is defined as the date at which the component/item accomplishes the first flight for which it will undertake its intended function.

Note: Unless otherwise stated, this means for transferable components/items delivered on new aircraft (i.e. from Airbus Final Assembly Line) that the life accumulated between aircraft first flight and the aircraft delivery date/transfer of title date (e.g. as a result of test flights) must be taken into account.

EXCEPTIONAL SHORT-TERM EXTENSION

An extension in a SEMR airworthiness limitation that may be needed to cover an uncontrollable or exceptional unexpected situation.

FLIGHT CYCLE (FC) A complete take-off and landing sequence.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX B PAGE: 30/37


TERM DEFINITION

FLIGHT HOUR (FH) The accumulated time intervals between ‘wheels-off’ and ‘wheels-on’.

FUNCTIONAL CHECK

A quantitative check to determine if a component/item performs one or more functions of within specified limits.

IMPLEMENTATION PERIOD

The period of time allocated to Operators to update their approved Maintenance Program.

INTERVAL The maximum period expressed in usage parameters between the completion of a task and its next due accomplishment.

LANDING (LDG) An operation of an aircraft touching the runway and coming to a full stop or performing a “touch and go”.

OPERATIONAL CHECK

A qualitative check to determine that a component/item is fulfilling its intended purpose. It is a failure-finding task and does not require quantitative tolerances.

SPECIAL DETAILED INSPECTION

An intensive examination of a specific item, installation, or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. When such inspections are required, detailed NDT procedures are described in the A318/A319/A320/A321 Non-destructive Testing Manual (NTM).

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.

VISUAL CHECK Observation to determine that a component/item is fulfilling its intended purpose. It is a failure finding task and does not require quantitative tolerances.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX C PAGE: 31/37


APPENDIX C. LIST OF DELETED TASK

TASK REFERENCE SUMMARY OF CHANGES

N/A N/A

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX D PAGE: 32/37


APPENDIX D. HISTORY FILE

RECORD OF REVISIONS

REVISION NUMBER

REASONS FOR REVISION REVISION

DATE

00

The A318/A319/A320/A321 ALS Part 4 Revision 00 is 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 were transferred to the ALS Part 4 Sub part 4-2.

JAN 08/08

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.

JUN 15/12

02

The A318/A319/A320/A321 ALS Part 4 Revision 02 is mainly dedicated to introduce the extension of A321-200 systems installations up to 74 000 FH or 37 000 FC by embodiment of MOD 154881, the Extended Service Goal (ESG) 120 000 FH or 60 000 FC, for in-service A319-100 aircraft series by embodiment of MOD 155789, the new MLG retraction actuator detailed PNRs by embodied MOD 155557 or MOD 155558 (and associated SBs), the new evolution MLG retraction actuator detailed PNRs by embodied MOD 161202 and the new Cabin Attendant Seat (CAS) moving adapter PNR by embodied MOD 153793.

NOV 05/14

03 at issue 01

The A318/A319/A320/A321 ALS Part 4 Revision 03 at issue 01 is mainly dedicated to introduce the extension of A321-100/-200 systems installations up to 74 000 FH or 37 000 FC by embodiment of MOD 154881, the extension of A320-231 POST 20139 PRE 22129 (MLG with four wheels bogie) systems installations up to 63 500 FH or 45 000 FC by embodiment of MOD 39020, the new evolution MLG retraction actuator detailed PNRs by embodied MOD 161346, the sharklet devices for in-service A320-200 and A319-100 aircraft (MOD 160080), the new aircraft model A320-271N (A320 fitted with new PW engines) and the new SEMR task 213100-00001-1-E.

DEC 21/15

03 at issue 02

The A318/A319/A320/A321 ALS Part 4 Revision 03 at issue 02 is released to introduce the editorial changes followings the in-service experiences:

Page 5, section “Compliance Time” is amended to clarify that the compliance time is applicable only to the component or aircraft having exceeded or close to exceed the new or reduced airworthiness limitations.

Definition of “Compliance Time” is amended accordingly.

Note (2) is added to the Air Data Module (ADM) PNR PG1152AC02.

“R” is added to Door Uplock C24730000-3.

JAN 22/16

A320 Family




REVISION NUMBER


DATE

04 at issue 01

The A318/A319/A320/A321 ALS Part 4 Revision 04 at issue 01 is dedicated to introduce the new aircraft model A320-251N (A320 fitted with new CFM engines) and extends the operation of the A320-251N (A320 POST MOD 161003) systems installations up to 96 000 FH or 48 000 FC, whichever occurs first.

JUN 20/16

04 at issue 02

The A318/A319/A320/A321 ALS Part 4 Revision 04 at issue 02 is released to introduce following editorial changes : Page 5, section “Compliance Time” is amended to clarify that compliance time of SEMR task 213100-00001-1-E published in ALS Part 4 revision 03 remain applicable.

JUL 06/16

05

The A318/A319/A320/A321 ALS Part 4 Revision 05 at issue 01 aims at introducing the Extended Service Goal (ESG) for A321 aircraft. It introduces also :

the Airworthiness Limitations for the new A321-271N, A321-251N and A321-253N aircraft models

new Airworthiness Limitations for ATA 27 THS Actuator, when fitted on A320 family NEO aircraft.

APR 06/17

06

The A318/A319/A320/A321 ALS Part 4 Revision 06 is mainly issued to include :

Changes already published through Variations : o Variation 5.1 : introduction of new model A321-272N

(SEMR tables not impacted)

Changes introduced directly in the Revision : o Introduction of following new models :

A320-252N (SEMR tables not impacted) A321-252N (SEMR tables not impacted) A321 NEO ACF (new SEMR 256200-00001-1-E

introduced) o Extend current demonstrated lives of MLG uplock P/Ns

H10800003 and H10800004.

JUN 13/18

06 at issue 02

A318/A319/A320/A321 ALS Part 4 Revision 06 Issue 02 has been released to correct applicability of life limit related to ATA 78-32-00 THRUST REVERSER STRUCTURE Pressure Relief Door Latch (PRDL) P/N 636D0023-509 : applicability is corrected :

from “A320-271N OR A321-271N/NX”

to “A320-27xN OR A321-27xN/NX”, where “x”.stands for any relevant number between 0 and 9.

NOV 26/18

A320 Family




REVISION NUMBER


DATE

07 at issue 01

The A318/A319/A320/A321 ALS Part 4 Revision 07 is mainly issued to introduce:

Changes already published through Variations: o Variation 6.1 :

Introduce new SEMR 522101-00001-1-E related to Over Wing Door (OWD) for A321 NEO ACF.

o Variation 6.2 : Supersede previous Variation 6.1. MODs 164456 and 164457 introduce modification of door mechanism of forward (FWD) / afterward (AFT) Over Wing Door (OWD). Revise SEMR 522101-00001-1-E, to clarify that considered requirement do no more apply on OWD(s) of aircraft where MOD(s) 164456 and / or 164457 has (have) been embodied

o Variation 6.3 : Provide impact on ALS Part 4 – SEMR related to extension of applicability of MOD 160177 to A321-100 CEO aircraft series.

o Variation 6.4 : Provide impact on ALS Part 4 – SEMR related to

new life limitations for ATA 29 rods P/Ns (D00031070004 & D00031070006)

and new SEMR maintenance requirement to "DISCARD WING BELLOW" (tasks 361101-00002-1-E & 361101-00002-2-E).

o Variation 6.5 : Provides impact on ALS part 4 – SEMR related to introduction of new A319 NEO models (A319-151N and A319-153N), as well as introduction of A319 NEO ACJ new configuration ; main impact is introduction of specific temporary limitation by 26 000 FH or 13 000 FC (whichever occurs first) for THSA fitted on A319 NEO aircraft

Changes introduced directly in the Revision: o Explicit the reference of SEMR 213100-00001-1-E (from

AMM 213100-600-001, to AMM 213152-000-001 / AMM 213152-400-001 / NORD MICRO VSB 15704-21-002)

o Correct the reference of SEMR 522101-00001-2-E (from AMM 522200-720-804 to AMM 522200-720-805)

o Introduce new SEMR maintenance requirement to " DISCARD SEALS 32" (tasks 361101-00003-1-E & 361101-00003-2-E)

o Introduction of following new models A320-253N, A320-272N and A320-273N (SEMR tables not impacted).

OCT 11/19

A320 Family




REVISION NUMBER


DATE

07 at issue 02

A318/A319/A320/A321 ALS Part 4 Revision 07 Issue 02 has been released in order to administratively update description of ALS part 4 SEMR tasks 361101-00003-1-E / -2-E from “Discard seal 32” to “Discard Wing Anti Ice tapping seals” ; this aims to restore consistency of ALS documentation with IPC / AMM documentation.

NOV 07/19

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX E PAGE: 36/37


APPENDIX E. SUMMARY OF CHANGES

GENERAL

Summary Of Changes (SOC) from previous ALS revisions are not published within this ALS Part 4. SOC for previous revisions could be found within the related revision.

Except in SECTION 3 and SECTION 4, non-administrative changes are highlighted with a revision bar in the left hand margin in front of the line different from previous revision of the ALS Part 4.

In SECTION 3, SEMR changes are highlighted with the following movement codes printed in the left hand margin of the airworthiness limitation when different from previous revision of the ALS Part 4:

<N> = New (new life limited part number introduced)

<R> = Revised (at least one change in one limitation of considered part number)

<D> = Deleted (part number no more life limited).

In this section, administrative changes are not highlighted but are identified in the SOC column.

In SECTION 4, SEMR changes are highlighted with the following movement codes printed in the left hand margin of the airworthiness limitation when different from previous revision of the ALS Part 4:

<N> = maintenance requirement is new,

<R> = maintenance requirement has been revised,

<D> = maintenance requirement has been deleted.

In this section, administrative changes are not highlighted but are identified in the SOC column.

COVER PAGE

The cover page has been revised to amend the Revision number and to update the Airbus logo.

TABLE OF CONTENT

The table of content has been updated accordingly to the changes performed throughout the document.

REVISION STATUS

The first frame has been updated to take into account subjects approved under DOA authority.

This section has also been updated to provide the: - Approval date and reference of the A318/A319/A320/A321 ALS Part 4 Revision 07. - Reasons of the Variations compiled in this Revision.

- The revision status now displays additional changes that were not published through Variations. For detailed traceability in the SOC, group of changes have been defined in a new table.

A320 Family


ISSUE: NOV 07/19 ALS PART 4 - APPENDIX E PAGE: 37/37


COMPLIANCE TIME

This section has been updated to provide the list of instructions and airworthiness limitations which have been revised and introduced in the A318/A319/A320/A321 ALS Part 4 Revision 07 as well as their associated compliance time (when applicable). This information comes from the original Variations which have been introduced in the current Revision.

SECTION 1 – INTRODUCTION

Page 7 - §2: Applicability table has been updated to introduce new A319-151N, A319-153N, A320-253N, A320-272N and A320-273N aircraft models. The aircraft series have been clarified.

Page 8 - §3: Maintenance Program Publication Table has been updated following new A319 NEO ACJ and A319 NEO ACJ. Notes and clarifications have been updated accordingly.

SECTION 2 – EXPLANATION OF TABLE FORMAT

Page 17: Header of the table has been updated.

Page 18: clarification of configuration addressed in columns “A320-2xx CEO Twin” and “A320-2xx CEO Bogie”.

SECTION 3 – SYSTEMS LIFE-LIMITED COMPONENTS

Limitations table with its associated change description has been transferred in the embedded excel file.

SECTION 4 – SYSTEMS INTALLATION MAINTENANCE REQUIREMENTS

Limitations table with its associated change description has been transferred in the embedded excel file.

APPENDIX A – ABBREVIATIONS

The following abbreviations have been added: A/C, ACF, ACJ, AD, AFT, CEO, DY, FWD, OWD, SOC and WAI.

APPENDIX B – TERMS AND DEFINITIONS

No change.

APPENDIX C – LIST OF DELETED TASKS

No change.

APPENDIX D – HISTORY FILE

This section has been updated to add the reason for issuance of the A318/A319/A320/A321 ALS Part 4 Revision 07.

APPENDIX E – SUMMARY OF CHANGES

This section provides the changes introduced in the A318/A319/A320/A321 ALS Part 4 Revision 07.

A318/A319/A320/A321 Airworthiness Limitations Section (ALS) … · 2021. 3. 16. · A321 NEO ACF...

Documents

Transcript of A318/A319/A320/A321 Airworthiness Limitations Section (ALS) … · 2021. 3. 16. · A321 NEO ACF...