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© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

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

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

A310 

Airworthiness Limitation Items 

Document 

Airbus 

Customer Services 

1, Rond Point Maurice Bellonte 

31707 Blagnac Cedex AI/SE-M2/95A.1309/07 

France October 2010 

 Issue 8
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TABLE OF CONTENTS

TABLE OF CONTENTS .......................................................................................................................... 1-TOC

RECORD OF REVISIONS ...................................................................................................................... 1-ROR

SECTION A: INTRODUCTION ............................................................................................................... 1-A

1. GENERAL ..................................................................................................................................................... 1-A

a) Modification requirements ............................................................................................................ 1-A

b) Inspection requirements ............................................................................................................... 2-A

c) Alternative Special Range Utilization requirements ..................................................................... 2-A

2. LIMIT OF VALIDITY (LOV) ........................................................................................................................... 2-A

3. APPLICABILITY ........................................................................................................................................... 2-A

a) General ......................................................................................................................................... 2-A

b) Applicability system ...................................................................................................................... 2-A

SECTION B: RULES FOR COMPLIANCE DEMONSTRATION ............................................................ 1-B

1. General ......................................................................................................................................................... 1-B

2. Conditions for ALI inspection .................................................................................................................... 1-B

3. Reporting ...................................................................................................................................................... 2-B

4. Production/Repair concessions and Alternative Means Of Compliance ............................................... 2-B

5. Modifications/repairs not originating from Type Certificate Holder (i.e. Airbus) .................................. 2-B

6. Interchangeable parts policy ...................................................................................................................... 2-B

SECTION C: MODIFICATION REQUIREMENTS .................................................................................. 1-C

SECTION D: INSPECTION REQUIREMENTS ...................................................................................... 1-D

SECTION E: ALTERNATIVE SPECIAL RANGE UTILIZATION REQUIREMENTS ............................. 1-E

APPENDIX A : SUMMARY OF CHANGES ........................................................................................... APXA -1

APPENDIX B : ABBREVIATIONS ......................................................................................................... APXB-1

APPENDIX C : TERMS AND DEFINITIONS .......................................................................................... APXC-1

APPENDIX D : ALI ILLUSTRATIONS ................................................................................................... APXD-1
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APPENDIX E : INSPECTION REPORTING ...........................................................................................APXE- 1

APPENDIX F : DT ALI REQUIREMENT DELETED ..............................................................................APXF- 1
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RECORD OF REVISIONS

 Issue Date Reason for revision Approved 

by EASA

 1 

 2 

3 

4 

5 

Sep 98 

Jul 99 

Feb 03 

MAY 04 

Sep 05 

Section 2 of CMR documents originally 

identified “Structural Inspections”. These are 

not CMRs. New document created. 

Reference to A310 MRB Document dated 

Feb 1992 changed to A310 MRB Report 

dated April 1998. 

Reference to “FLP-1 limits” replaced by 

“100% limits”. 

Reference to “FLP-1 concept” replaced by 

“concept S”. 

To reflect reduced inspection interval values 

for specified SSIs on PW4000 powered 

aircraft following re-appraisal of powerplant 

Weight used in original calculations. Table 1 

added. 

To highlight the need to reduce, in defined 

circumstances, certain FC figures using the 

“Adjustment for Range” formulae. 

“Airbus Industrie” logo replaced by “Airbus” 

logo on all pages. Page Issue / Date not 

modified by this change. 

To introduce the ALIs, which must be 

performed to permit operation between the 

Design Service Goal and the Intermediate 

Extended Service Goal, the Table 2 has 

been added. 

- Format of document completely revised 

Limit Of Validity (LOV) extension 

Application Tolerance amended 

Contact amended 

Equation for Adjustment For Range revised 

Introduction of new / revised / deleted 

requirements 
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 Issue Date Reason for revision Approved 

by EASA

6 April 06 Limit Of Validity (LOV) extension 

Section B : Application Tolerance paragraph 

amended and alternative special range 

added. 

Section D: New and revised requirement 

Section E: New Special range section 

Section F: Illustration amended 

EASA.A.C.03893 

Approved 31-May-06

T.R. 

6.1 

Nov 06 Revised requirements in Section D and E to 

cover A310-300 WV 013 certification 

EASA.A.C.05096 

Approved 12-Dec-06

7 JUN 08 ALI Document layout has been reworked 

New / updated DT ALI requirements due to 

modifications/In-service experience 

EASA.A.C.10907 

Approved 2-Dec-08 

8 October 

2010 

New / updated DT ALI requirements due to 

modifications/ In service experience 

EASA 10036763 

Approved 05-Oct-11 
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COMPLIANCE TIME:

1. It is mandatory to strictly adhere to the airworthiness limitations as defined in the A310 

ALI Issue 8 from 5 October 2012. 

2. From 5 October 2011 to 4 October 2012, it is mandatory to comply with the 

airworthiness limitations defined in, either: 

− The A310 ALI Document at issue 7, except as provided in paragraph 3. of this 

ROR, 

or, 

− The A310 ALI Document at issue 8. 

3. Special Compliance Times:

For aircraft that have already exceeded or are close to exceeding the new or revised 

airworthiness limitations in ALI Issue 8, the next due accomplishment of each such task 

may be deferred by up to 1500 FC or 50% of the new interval, whichever is the lesser, 

without exceeding the limitations quoted in ALI Issue 7. 

This is not applicable to the following ALIs for which the inspection must be carried out 

within the time frame specified below: 

• ALI 572104 

o For A310-200 due for their first inspection, 400FC or 900FH from date 

approval of the ALI document Issue 8 are allowed, whichever comes first. 

o For A310-300 flying below 4 FH/FC on average and due for their first 

inspection, 400FC or 1300FH from date approval of the ALI document 

Issue 8 are allowed, whichever comes first 

o For A310-300 flying above 4 FH/FC on average and due for their first 

inspection, 300FC or 1500FH from date approval of the ALI document 

Issue 8 are allowed, whichever comes first 

• ALI 572545 

For aircraft that have already exceeded or are close to exceed the new or 

revised published airworthiness limitations, a special compliance time of 800FC 

or 1600FH from date of approval of ALI Document Issue 8 is applicable date as 

long as this value does not exceed: 

o The previous threshold and/or interval as defined in the referenced 

A310 ALI document issue 7, 

o 50% of the intervals quoted in section D and E 

• ALI 712102 

o For aircraft equipped with CF6-80C2 that have already exceeded or are 

close to exceed the new or revised published airworthiness limitations and 

that have accumulated less or equal than 5000FC since the last inspection 

or new, the next inspection must be carried no latter than 7500FC. 

o For aircraft equipped with CF6-80C2 that have already exceeded or are 

close to exceed the new or revised published airworthiness limitations and 

that have accumulated more than 5000FC since the last inspection or 

new, the next inspection must be carried at the next engine removal 

opportunity. 

o For aircraft equipped with CF6-80A3 that have already exceeded or are 

close to exceed the new or revised published airworthiness limitations, the 
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next inspection must be carried out at the next engine opportunity or no 

latter than previous Threshold or Interval as quoted in Section D or E 
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SECTION A: INTRODUCTION

1. GENERAL

The data provided in this docment has been established with the following rules: 

Compliance with the requirements contained in this document is mandatory. ALL 

aircraft shall be operated in accordance with the requirements of ALI Document, 

unless otherwise agreed with the Authority of the State of aircraft registry. 

Note: The ALI Document is covered by the Certification Document 00X0500M092M41. 

The ALI contains airworthiness limitations arising from fatigue and damage tolerance 

evaluation on structural element that could contribute to catastrophic failure of the aircraft. It 

also contains the fatigue related structural inspections arising from the Widespread Fatigue 

Damage (WFD) evaluation. 

The ALI requires also to control corrosion to Level 1 or better on all metallic structure details, 

elements or assemblies which contribute significantly to carrying flight, ground, or 

pressurization loads, and whose failure could result in catastrophic failure of the airplane 

Corrosion Level 1 is defined as follows: 

− Corrosion damage that does not require structural reinforcement or replacement. 

or 

− Corrosion occurring between successive inspections that exceeds allowable limit but is 

local and can be attributed to an event not typical of Operator usage of other aircraft in the 

same fleet (e.g. mercury spill). 

The Corrosion Prevention and Control Program (CPCP) defined in the Structure Program of 

the A310 MRB Report is an acceptable means of compliance. 

Credit may be taken for the Maintenance Review Board Report (MRBR) Structures Section 

maintenance tasks, providing that they are performed with the same inspection level, as 

frequently, or more frequently, than the inspection threshold and interval quoted in this 

document. Additional information concerning DT ALI requirements can be found in the 

following Airbus supporting publications: 

− Maintenance Planning Document (MPD), 

− Aircraft Maintenance Manual (AMM), 

− Non-Destructive Testing Manual (NTM) 

− Structural Repair Manual (SRM). 

a) Modification requirements

This section provides the list of ALIs for which modifications must be embodied at the 

stated embodiment times. 
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b) Inspection requirements

This section D provides the list of ALIs arising from fatigue and damage tolerance 

evaluation on structural element that could contribute to catastrophic failure of the aircraft. 

It also contains the fatigue related structural inspections arising from the Widespread 

Fatigue Damage (WFD) evaluation. 

c) Alternative Special Range Utilization requirements

Inspection requirements of section D are applicable to all aircraft, whatever the average 

flight time (AFT). 

However, operators may benefit from the alternative “Special Range utilization” 

requirements, which are reflected in section E, where aircraft are operated with an AFT 

above 4 FH/FC on average. 

NOTE: The “Note” column in section D contains an “S” where an alternative “Special 

Range Utilization” requirement exist in section E. 

2. LIMIT OF VALIDITY (LOV)

The requirements developed and published in this document allow operation up to the Limit 

Of Validity (LOV) in Flight Cycles (FC) or Flight Hours (FH), whichever occurs first. The 

relevant LOV values are stated below for each aircraft model. The aircraft or structure items 

must not be operated beyond these values unless the manufacturer has updated this 

document to include a clearly defined life extension. 

The relevant LOV values for each A/C type are as follows: 

- A310-200: 45000FC / 105000FH 

- A310-300: 40000FC / 116000FH 

3. APPLICABILITY

a) General

The ALI document covers the following aircraft models: 

A310-203 A310-204 A310-222 A310-308 A310-324 

A310-203C A310-221 A310-304 A310-322 A310-325 

b) Applicability system

The applicability column of ALI indicates the aircraft type/series/model/weight variant 

group and modification status for which the task is applicable. Examples are given below: 
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APPLICABILITY A/C MODEL 

ALL : The requirement is applicable to -200 and -300 series A/C. 

-200 : This requirement is applicable to -200 series A/C only. 

-200C : This requirement is applicable to -200C series A/C only. 

-300 : This requirement is applicable to -300 series A/C only. 

PRE 10685 : This requirement applies to all A310 series without MOD 10685, i.e. aircraft which 

do not have the modification 10685 embodied 

-300 

POST 7601 

: This requirement applies to all A310-300 aircraft type POST MOD 7601, i.e. A310-

300 which do have the modification 7601 embodied 

-200 

PRE 4799 

: This requirement applies to A310 series without MOD 4799, i.e. aircraft which do 

not have the modification 4799 embodied 

PRE 8130 

PRE 11103 

: This requirement applies to all A310 aircraft type without MOD 8130 and without 

MOD 11103, i.e. aircraft which do not have modification 8130 embodied and do not 

have modification 11103 embodied 

 POST 8130 

OR 

POST 11103 

: This requirement applies to all A310 aircraft type POST MOD 8130 or POST MOD 

11103, i.e. aircraft which do have either modification 8130 embodied or modification 

11103 embodied 

POST 8130 

PRE 11103 

: This requirement applies to all A310 aircraft type POST MOD 8130 and PRE MOD 

11103, i.e. aircraft which do have modification 8130 embodied and do not have 

11103 embodied 

-300PW : This requirement is applicable to -300 series A/C with Pratt&Whitney Engines. 

CF6-80C2 : This requirement is applicable to all A310 A/C with CF6-80C2 Engines. 
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SECTION B: RULES FOR COMPLIANCE DEMONSTRATION

1. GENERAL

The airworthiness limitation items contained herein allow operation up to the Limit Of Validity 

(LOV) in FC or FH whichever occurs first. (Refer to paragraph 3 for definition of the LOV). 

No aircraft or structure item shall be operated beyond this LOV, unless the Type Certificate 

Holder (i.e. Airbus) has updated this document to reflect an approved LOV extension. 

The Threshold is the time at which the maintenance requirement is first due. 

- For FC or FH tasks without MOD applicability, thresholds are counted from first 

flight. 

- For FC or FH tasks with MOD applicability, thresholds are counted from point of 

embodiment, unless otherwise stated. 

- For tasks in Calendar Time, thresholds are counted from date of initial delivery 

from manufacturer, unless otherwise stated. 

For repeat maintenance tasks, the interval starts at the time of the last maintenance task 

performed. 

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

associated with the inspection method used at last inspection. 

In cases when the first maintenance task is accomplished very early, the next inspection can 

be performed at the threshold if the period (years, FC or FH) between initial task 

accomplishment and the threshold is greater than the interval. 

“Touch and Go" cycles can be neglected if they are less than 5% of the total number of 

Flight Cycles up to threshold inspection or between two consecutive inspections. 

Each "Touch and Go" cycle above 5% is to be counted as one Flight Cycle, up to threshold 

inspection or between two consecutive inspections. 

2. CONDITIONS FOR ALI INSPECTION

It is assumed that the ALI to be inspected is in a state of cleanliness, which allows a 

satisfactory inspection to be carried out at the required inspection level. 

Where existing Temporary Protection System (TPS) permits unobscured assessment of the 

condition of the ALI, then that TPS may remain in place for the inspection. 

Limitations quoted in section C and D are applicable to the undamaged and unrepaired ALI. 

Damage has to be evaluated and repaired in accordance with the AIRBUS Structural Repair 

Manual SRM or other documentation acceptable to the relevant Airworthiness Authority. 

If damage is found or suspected (such as bulging skin, paint discoloration) then the full 

extent of any damage must be clearly identified using appropriate inspection techniques 

and/or disassembly when necessary. This may require additional access to that stated for 

the ALI maintenance requirement. 
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In cases of damage or repairs, the ALI maintenance requirements may have to be adapted, 

or additional requirements may be required. In these cases the requirements that are given 

in the relevant documents (SRM or specific Repair design Approval Sheet) must be applied. 

3. REPORTING

Any damage, e.g. fatigue cracks or corrosion greater than Level 1 (regardless where and 

when the corrosion is detected), shall be reported to Airbus. 

Mailto: Maint.sched@airbus.com 

The finding report should include at least the information stated below (refer also to 

appendix E: 

− ALI maintenance requirement reference, 

− Aircraft Manufacturer Serial Number (MSN) affected, 

− Life (in FH and/or FC and/or calendar time, as applicable) accumulated at the time of 

the finding, 

− Identification of the affected structure, 

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

− Circumstance of detection and inspection method used. 

4. PRODUCTION/REPAIR CONCESSIONS AND ALTERNATIVE MEANS OF

COMPLIANCE

Limitations of the ALI may be superseded by instructions given in either a Production 

concession, a Repair design Approval Sheet (RAS) or an Alternative Means Of Compliance 

(AMOC). 

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

5. MODIFICATIONS/REPAIRS NOT ORIGINATING FROM TYPE CERTIFICATE HOLDER 

(I.E. AIRBUS)

If an aircraft/ALI has a modification or repair embodied that has not been developed by the 

Type Certificate Holder (i.e. Airbus) and which affects the content of the ALI, the Operator is 

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

adaptations of the limitations. 

6. INTERCHANGEABLE PARTS POLICY

Where a part is removed from one aircraft and fitted to another aircraft, then, the life of this 

part must be tracked if it is covered by an DT ALI requirement. 
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SECTION C: MODIFICATION REQUIREMENTS

For A310 aircraft models no modification is required to be embodied before LoV to 

satisfy CS/FAR 25 by this section. 
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SECTION D: INSPECTION REQUIREMENTS

Detailed information is given below concerning the format of the section D table: 

“Revision Code”: 

This column indicates the revision code “status ” of the ALI task requirement 

compared to previous issue of the document. 

<Blank> = No amendment. 

<R> = The ALI task requirement has been revised. 

<N> = The ALI task requirement is new. 

<D> = The ALI task requirement is deleted. 

“Task reference”: 

This column indicates the number (XXXXXX-YY-ZA) selected for each ALI. 

3⁄4 The first four digits are in accordance with the A310 ATA100 breakdown, 

showing where the ALI is located. 

3⁄4 The fifth and sixth digits are sequential numbers within the section. 

3⁄4 The seventh and eighth digits are for sequential number 

3⁄4 The ninth digit is for technical solution applicable to same task requirement 

3⁄4 The tenth digit is “A” and stands for ALI. 

 “Zones”: 

This column indicates the zone(s) where the ALI is located. 

“Access “: 

This column indicates the access requirements to adequately perform the 

maintenance task. All items listed must be removed or opened unless otherwise 

stated. 

 “Task description”: 

This column describes the task to be performed. It includes the inspection level, the 

description and the boundaries of the ALI to be inspected. All items within this 

boundary are to be inspected e.g. fasteners, cutouts, attachments, unless otherwise 

stated. Additional information may be added to clarify the inspection area. 

For Special Detailed Inspections the NDT method is to be stated between brackets. 

Where applicable, Notes providing details of alternative tasks, and tasks to be 

performed at the same time, will be included. 
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 “Th./ Int.”: 

This column indicates the Threshold (i.e. the time when maintenance task is first 

due) and Interval (which starts at the time of the last maintenance task performed). 

The stated values must not be exceeded. 

“NTM Ref.”: 

This column provides reference to supporting documentation, such as SBs or NTM, 

where the procedure necessary for task accomplishment is provided (alternative 

procedures must be approved by Airbus). 

“Applicability”: 

This column indicates the aircraft types/series/model/Mod status/MSN to which the 

requirement is applicable. 

NOTE: The MSN’s 419, 427, 430, 454, 468, 486 and 487 were certificated as 

A310-200, variant 100 aircraft. The fuselage, center wing and outer wing 

structure is basically identical to the A310-300. However, due to the 

loading, the aircraft are covered by the A310-200 structural requirements, 

with the exception of the outer wing. 

Thus, for all ALIs in ATA chapters 57.21, 57.25, 57.41, 57.43, 57.44 and 

57.51, where different requirements exist for the –200 and –300 aircraft, 

the above listed aircraft are to be covered by the –300 requirements. 

“Note”: 

Note “1”: For those tasks with General Visual Inspection level, the first inspection 

interval starts counting from the A/C status on 25 November 2004. 

Note “S”: For those tasks, an alternate “Special Range Utilization” requirement exists 

in section E. However, section D requirements are applicable whatever the 

A/C utilization but they are optimized for A/C operated below 4FH/FC. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

521101-01-1A 831/841 831/841 General visual inspection of door stop assemblies on FWD

passenger/crew doors, LH/RH.

T: 12000FC 

I: 12000FC

ALL 

521103-01-1A 800 N/A General visual inspection of FWD passenger/crew door skin,

external surface, LH/RH.

T: 3000FC

I: 3000FC

ALL 

521301-01-1A 833/843 N/A General visual inspection of AFT passenger/crew door skin, external 

surface, LH/RH.

T: 3000FC

I: 3000FC

ALL 

521303-01-1A 833/843 833/843 General visual inspection of door stop assemblies on AFT 

passenger/crew doors, LH/RH.

T: 18000FC

I: 12000FC

ALL 

522201-01-1A 834/844 N/A General visual inspection of emergency exit skin, external surface, 

LH/RH.

T: 18000FC

I: 5000FC

ALL 

522203-01-1A 834/844 833/844 General visual inspection of door stop assemblies on emergency 

exits, LH/RH.

T: 18000FC

I: 12000FC

ALL 

523101-01-1A 811 N/A General visual inspection of FWD cargo compartment door skin, 

external surface.

T: 8100FC

I: 8100FC

ALL 

523103-01-1A 811 811 Special detailed inspection (HFEC) of actuator attach fitting of FWD 

cargo compartment door at FR 22A.

T: 6000FC

I: 6000FC

523103 ALL

523105-01-2A 811 811

132 AR t LR

Detailed inspection of hinge arms of FWD cargo compartment door 

t FR 20A t 25A (10 l ) i fl dii dj t t t ki

T: 30000FC

I 6000FC

ALL

A310

Airworthiness Limitation Items

132 AR to LR at FR 20A to 25A (10 places) in flange radii adjacent to outer skin. I: 6000FC

523109-02-1A 811 811 General visual inspection of locking hooks of FWD cargo 

compartment door (10 places).

T: 18000FC

I: 6000FC

ALL 

523201-01-1A 812 N/A General visual inspection of AFT cargo compartment door skin, 

external surface.

T: 8100FC 

I: 8100FC

ALL 

523203-01-1A 812 812

152 AR to HR

Detailed inspection of hinge arms of AFT cargo compartment door from FR 60 to 63 (7 places) in flange radii adjacent to outer skin.

T: 18000FC

I: 3000FC

ALL

523204-01-1A 812 812 Special detailed inspection (HFEC) of actuator attach fitting of AFT 

cargo compartment door at FR 61 A.

T: 6000FC

I: 6000FC

523204 ALL

523205-02-1A 812 812 General visual inspection of locking hooks of AFT cargo 

compartment door (7 places).

T: 18000FC

I: 6000FC

ALL 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

523207-01-1A 812 812 Detailed inspection of hinge end aft cargo compartment door at FR 

60 to FR 63 ( 7 places ) especially in flange radius adjacent to outer skin.

T: 40000FC

I: 1500FC

-200

523207-01-2A 812 812 Detailed inspection of hinge end aft cargo compartment door at FR 

60 to FR 63 ( 7 places ) especially in flange radius adjacent to outer skin.

T: 35000FC

I: 1500FC

-300

523401-01-1A 813 N/A General visual inspection of bulk cargo compartment door skin, 

external surface.

T: 550FC

I: 550FC

ALL 

523403-01-2A 813 813 Detailed inspection of door stop assemblies at bulk cargo 

compartment door.

T: 18000FC

I: 6000FC

ALL

523403-01-3A 813 813 Detailed inspection of door stop assemblies at bulk cargo 

compartment door.

T: 40000FC

I: 1000FC

-200

523403-01-4A 813 813 Detailed inspection of door stop assemblies at bulk cargo 

compartment door.

T: 35000FC

I: 1000FC

-300

523601-01-1A 835 N/A Detailed inspection of main deck cargo door skin, external surface.

Note: this task is an alternative to 523601-02-1A

T: 8500FC

I: 8500FC

-200C

523601 02 1A 523601-02-1A 835 N/A G l i l i ti f i d k d ki t l General visual inspection of main deck cargo door skin, external T 1960FC 200C 

surface.Note: this task is an alternative to 523601-01-1A

T: 1960FC

I: 1960FC

-200C 

523603-01-1A 835 835

lining, Insulation displaced as required

Detailed inspection of main deck cargo door actuator attach fittings including riveting.

T: 6000FC

I: 6000FC

-200Cin cargconfigu

523608-01-1A 835 835

835 AL, BL, CL

Detailed inspection of locking mechanism, attach fittings and support structure of main deck cargo door at all frames from longerons 8 to 9 (8 places).

T: 12000FC

I: 12000FC

-200C

523609-01-1A 835 835

835 AL, BL, CL

Detailed inspection of locking hooks and bolts of main deck cargo door.Note: Refer to AMM 523600 P605 2B for torque check.

T: 12000FC

I: 12000FC

-200C

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

523611-01-2A 835 835,

lining

Detailed inspection of mechanical linkage of main deck cargo door actuator unit.

T: 6000FC

I: 6000FC

-200C in cargconfigu

524103-01-1A 121/122 121BL, floor 

panel on door

Detailed inspection of avionics compartment access door, internal structure between FR7 and FR10

T: 40000FC

I: 24000FC

-200

531101-01-3A 211/212 419VU & 

420VU displaced (if fitted). linings, glareshield lateral covers.

Detailed inspection of fuselage internal structure from FR2 to FR4, windshield frame lower section and closing panel, LH/RH.Note: this task could be done at the same time as task 531101-02-3A or 531101-02-4A

T: 33000FC

I: 4700FC

PRE 36

531101-01-4A 211/212 419VU & 

420VU displaced (if fitted). linings, glareshield lateral covers.

Detailed inspection of fuselage internal structure from FR2 to FR4, windshield frame lower section and closing panel, LH/RH.Note: this task could be done at the same time as task 531101-02-5A or 531101-02-6A

T: 25000FC

I: 5300FC

POST 

531101-02-3A 211/212 419VU & 

420VU displaced (if fitted). linings, 

glareshield

Special detailed inspection (HFEC) of fuselage internal structure from FR2 to FR4, windshield frame lower section and closing panel, LH/RH.Note: this task could be done at the same time as task 531101-01-3A

T: 33000FC

I: 8600FC

531101 PRE 36

glareshield

lateral covers.

3ANote: this task is an alternative to 531101-02-4A

531101-02-4A 211/212 419VU & 

420VU displaced (if fitted). linings, glareshield lateral covers, bolts.

Special detailed inspection (rototest) of fuselage internal structure from FR2 to FR4, windshield frame lower section and closing panel, LH/RH.Note: this task could be done at the same time as task 531101-01-3ANote: this task is an alternative to 531101-02-3A

T: 33000FC

I: 13600FC

531101 PRE 36

531101-02-5A 211/212 419VU & 

420VU displaced (if fitted). linings, glareshield lateral covers.

Special detailed inspection (HFEC) of fuselage internal structure from FR2 to FR4, windshield frame lower section and closing panel, LH/RH.Note: this task could be done at the same time as task 531101-01-4ANote: this task is an alternative to 531101-02-6A

T: 25000FC 

I: 7500FC

531101 POST 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531101-02-6A 211/212 419VU & 

420VU displaced (if fitted). linings, glareshield lateral covers, bolts.

Special detailed inspection (rototest) of fuselage internal structure from FR2 to FR4, windshield frame lower section and closing panel, LH/RH. Note: this task could be done at the same time as task 531101-01-4ANote: this task is an alternative to 531101-02-5A

T: 25000FC

I: 12200FC

531101 POST 

531108-01-2A 200 N/A Detailed inspection of side window rear post at FR10, external 

surface, LH/RH.

T: 26000FC

I: 5000FC

ALL

531109-01-1A 211/212 lining, 

insulation displaced as requiredsliding window opened.

Detailed inspection of cockpit internal structure, splice at the intersection between FR4 and windshield front frame and tee pick-up at junction of FR8 and FR9 with aft window upper frame, LH/RH

T: 32000FC

I: 7000FC

PRE 36

531110-01-1A 211/212 lining, 

insulation displaced as requiredsliding window opened.

Detailed inspection of cockpit internal structure, lower surface of upper closing panel and splice between FR7 and front windshield side post and tee pick-up at junction of FR8 and FR9 with aft window upper frame, LH/RH.Note : Grace period of 500FC or 6 Months whichever occurs first.

T: 18000FC

I: 7000FC

POST 

531114-01-1A 200 N/A General visual inspection of fuselage skin above windshield from 

FR4 to FR10, external surface, LH/RH.

T: 9000FC

I: 9000FC

ALL 

531115-01-1A 100 N/A General visual inspection of fuselage lower side panels from FR1 to 

FR10, external surface, LH/RH.

T: 12000FC

I: 12000FC

ALL 

531117-01-1A 100 N/A General visual inspection of fuselage bottom skin panels from FR1 to 

FR10, external surface, LH/RH.

T: 5600FC

I: 5600FC

ALL 

531118-01-1A 100/200 N/A General visual inspection of fuselage upper side skin panels below 

cockpit windows, from FR1 to FR10 external surface, LH/RH.

T: 10500FC

I: 10500FC

ALL 

531144-01-1A 122 121BL Detailed inspection of angle fittings between FR10 crossbeam and 

Y=-953mm, Y=-1456mm long beams, RH side.

T: 30000FC

I: 18000FC

ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531149-01-1A 211/212 831/841, lining, 

Insulation displaced as required

Detailed inspection of fuselage internal structure, angle gusset above front windshield panels, including 3 nuts on centre post

T: 40000FC

I: 9500FC

-200

531165-01-1A 211/212 3VU, 5VU 

displaced, front windshield removed

Detailed inspection of fixation bolt of FR2, lower surface of closing panel and lower post of front windshield, LH/RH.Note: This task is an alternative to 531165-02-1A

T: 40000FC

I: 40000FC

-200

531165-02-1A 211/213 3VU, 5VU 

displaced

Special detailed inspection (torque check) of fixation bolt of FR2, lower surface of closing panel and lower post of front windshield, LH/RH.Note: This task is an alternative to 531165-01-1A

T: 40000FC

I: 40000FC

-200

531201-01-1A 200 831/841 Detailed inspection of fuselage skin and fail safe ring around fwd 

passenger/crew door cutout from FR13A to FR17 and STR9 to main deck floor level, except scuff plate area, external surface, LH/RH.

T: 6700FC

I: 6700FC

ALL

531203-01-2A 200 831/841 Detailed inspection of fuselage skin and fail safe ring around fwd 

passenger/crew door cutout from FR14 to FR16A, from stiffener 7 to 

10 t l f LH/RH

T: 27000FC

I: 3400FC

ALL

10, external surface LH/RH.

531204-01-1A 121/122 831/841

lining, floor panel, insulation displaced as required

Detailed inspection of fuselage internal structure, junction area at FR14 floor beam and cruciform fitting, LH/RH

T: 22200FC

I: 5200FC

PRE 36

531204-01-2A 121/122 831/841

lining, floor panel, insulation displaced as required

Detailed inspection of fuselage internal structure, junction area at FR14 floor beam and cruciform fitting, LH/RH 

T: 26300FC

I: 6600FC

POST 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531204-02-1A 121/122 831/841

lining, floor panel, insulation displaced as required

Special detailed inspection (ultrasonic) of fuselage internal structure, junction area at FR14 floor beam and cruciform fitting, LH/RH

T: 22200FC

I: 9300FC

531204 PRE 36

531204-02-2A 121/122 831/841

lining, floor panel, insulation displaced as required

Special detailed inspection (ultrasonic) of fuselage internal structure, junction area at FR14 floor beam and cruciform fitting, LH/RH

T: 26300FC

I: 11900FC

531204 POST 

531205-01-1A 211/212 831/841

lining, insulation displaced as required

Detailed inspection of FR10, inner flange from side window lower section to main deck floor, LH/RH.

T: 36000FC

I: 9000FC

ALL

531206-01-2A 200 N/A Detailed inspection of fuselage skin panel from FR10 to FR11 and 

from upper corner of side window, 120 cm downwards, external surface, LH/RH.

T: 25000FC

I: 5000FC

ALL

531207-01-2A 123/124 715, 716 to be 

d

Special detailed inspection (X-Ray) of NLG bay, fuselage internal 

ki d bl d fl t FR17 LH/RH

T: 28200FC

I 4000FC

531207 ALL

removed skin, doublers and corner flange at FR17, LH/RH. I: 4000FC

531208-01-1A 221/222 831/841

floor panels, insulation, and if installed: cabin attendant seat, lavatory, galley

Special detailed inspection (HFEC) of FR12A stiffeners at upper horizontal flange LH/RH

T: 20400FC

I: 13300FC

511008 POST 

531209-01-1A 100 N/A General visual inspection of fuselage skin from FR10 to FR19, below 

main deck floor level, external surface, LH/RH.

T: 3500FC

I: 3500FC

ALL 

531216-01-1A 221/222 831/841 General visual inspection of door stop fittings on FR14 and FR16A, 

LH/RH

T: 20000FC

I: 4500FC

POST OR POST 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531225-01-2A 221/222 N/A Special detailed inspection (LFEC) of skin at FR13 circumferential 

joint from STR 9 rear to STR 25, external surface, LH/RH.

T: 40000FC

I: 6200FC

531225 -200

531226-01-1A 221/222 linings, 

insulation, lavatory (if installed) and bolts

Special detailed inspection (rototest) of fuselage circumferential joint forward of frame 13 datum at stringer 9 fwd and aft level and above stringer 25 at crossbeam 2 level, external surface, LH/RH.

T: 40000FC

I: 14000FC

531226 -200

531228-01-1A 211/212 linings, 

insulation, lavatory (if installed) 

Detailed inspection of attachment web between FR10 and STR9, LH/RH.

T: 34000FC

I: 19500FC

ALL

531229-01-1A 221/222 linings, 

insulation, lavatory (if installed) 

Detailed inspection of FR11 LH side at partition wall lateral web attachment and FR12 at upper web.

T: 36200FC

I: 6700FC

-200PRE 48

531232-01-2A 223/224 linings, 

insulation displaced as required, galleys and 

lavatory

Detailed inspection of FR12 and FR13 upper part from STR1 LH to STR2 LH and from STR3 RH to STR5 RH.

T: 32000FC

I: 10000FC

ALL

lavatory

531233-01-1A 100 121DL Detailed inspection of fuselage skin external surface in area of waste 

water connection box, including door cutout edges and 25 cm (10 in.) around cutout, from FR12 to FR12A, LH

T: 4000FC

I: 4000FC

PRE 60

531239-01-1A 231/232 lining, 

insulation

Detailed inspection of STR12 between FR17 and FR19, LH/RH T: 29000FC

I: 24900FC

ALL

531270-01-1A 221/222 831/841

lining, insulation

Detailed inspection of fuselage FR14 and FR16A, forward and rear faces in areas of cross beams 1 and 8, LH/RH.Note: this task is an alternative to 531270-02-1A

T: 30000FC

I: 2800FC

ALL

531270-02-1A 221/222 831/841

lining, insulation, bolts

Special detailed inspection (rototest) of fuselage FR14 and FR16A, forward and rear faces in areas of cross beams 1 and 8, LH/RH.Note: this task is an alternative to 531270-01-1A

T: 30000FC

I: 9700FC

531270 ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531271-01-1A 211/212,

212/222

lining, insulation, 15VU, 50VU, lh lavatory, galley if installed

Detailed inspection of FR10A to FR12 at each intersection of stringer, from cabin floor to STR9, LH/RH.

T: 36000FC

I: 8700FC

ALL

531273-01-1A 121/122 121/122 LF,

121/122 MF,121/122 NF,121/122 PF

Detailed inspection of nose gear bay arches attachments to frames at stringer 44 and struts attachments lugs, from FR11A to FR16A inclusive, LH/RH

T: 30500FC

60900FH

I: 5300FC

10800FH

-200

531273-01-2A 121/122 121/122 LF,

121/122 MF,121/122 NF,121/122 PF

Detailed inspection of nose gear bay arches attachments to frames at stringer 44 and struts attachments lugs, from FR11A to FR16A inclusive, LH/RH

T: 29400FC

82400FH

I: 5200FC

14600FH

-300 

531276-01-1A 123/124 713, 714 Detailed inspection of nose gear telescopic drag strut attach fitting. T: 34000FC

67900FH

I: 6200FC

12500FH

-200

531276-01-2A 123/124 713, 714 Detailed inspection of nose gear telescopic drag strut attach fitting. T: 32500FC

91000FH

I: 6200FC

17400FH

-300 

531293-01-1A 231, 232, 

233, 234 

Ceiling and sidewall panels, insulation displaced as required

Special detailed Inspection (LFEC) splice plate at circumferential skin splice at FR 18 from STR 9 LH to STR 13 LH, STR 1 RH to STR 3 RH, STR 5 RH to STR 8 RH and STR 9 RH to STR 11 RH, i.e. excluding lap joints area.

T: 36500FC

 73000FH

I: 6000FC

 12000FH

531293 -200C 

R 531294-01-1A 231/232

233/234

Galleys, lavatories, overhead stowage compartments, ceiling and sidewall panels, insulation displaced as required, bolt removal

Special Detailed Inspection (Roto Test) splice plate at circumferential skin at FR 18 from STR 1 LH to STR 9 LH, from STR 3 RH to STR 5 RH, from STR 8 RH to STR 9 RH and from STR 11 RH to STR 13 RH, i.e. where lap joints intersect with circumferential skin splice.

T: 34500FC

 69000FH

I: 20500FC

 41000FH

531294 -200C 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531297-01-1A 121/122 linings, 

insulation displaced as required

Detailed inspection of fuselage internal structure, FR16A joint between STR28 and STR30, LH/RH

T: 18500FC

I: 13000FC

PRE 36

531297-01-2A 121/122 linings, 

insulation displaced as required

Detailed inspection of fuselage internal structure, FR16A joint between STR28 and STR30, LH/RH

T: 21500FC

I: 16500FC

POST 

531297-02-1A 121/122 linings, 

insulation displaced as required

Special detailed inspection (HFEC) of fuselage internal structure, FR16A joint between STR28 and STR30, LH/RH

T: 18500FC

I: 13000FC

531297 PRE 36

531297-02-2A 121/122 linings, 

insulation displaced as required

Special detailed inspection (HFEC) of fuselage internal structure, FR16A joint between STR28 and STR30, LH/RH

T: 21500FC

I: 16500FC

531297 POST 

531298-01-1A 221/222 linings, 

insulation displaced as required

Special detailed inspection (ultrasonic) of fuselage internal structure, FR16A at cabin floor level.

T: 22000FC

I: 3300FC

531298 PRE 36

531298 01 2A 531298-01-2A 221/222 221/222 linings, li i S i l d t il d i ti ( lt i ) f f l i t l t t T 25000FC 531298 POST 

insulation displaced as required

Special detailed inspection (ultrasonic) of fuselage internal structure, FR16A at cabin floor level.

T: 25000FC

I: 4200FC

531298 POST 

R 531305-01-1A 131 811 Eccentric 

bolts

Detailed inspection of FWD cargo compartment door eccentric bolts from FR 20B to FR 25.

T: 20000FC

I: 10000FC

ALL

R 531305-02-1A 131 811 General visual inspection of FWD cargo compartment door lock 

fittings, lugs, bushes, eccentric bolts and surround structure from FR 20B to FR 25.

T: 8000FC

I: 8000FC

ALL 

531307-01-1A 100/200 N/A General visual inspection of fuselage skin panel around FWD cargo 

compartment door cutout from FR 19 to FR 26/32 and from STRs 22 RH to 46 RH, external surface.

T: 5800FC

I: 5800FC

ALL 

531309-01-1A 100 N/A General visual inspection of fuselage skin from FR 20 to FR 26/32 

and from STRs 40 LH to 42 LH, external surface.

T: 24000FC

I: 2600FC

ALL 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531316-01-2A 132

134

Lining, Insulation displaced as required

Detailed inspection of FRs 20, 20A and 25A from STRs 38 RH to 46 RH, internal structure.

T: 30000FC

I: 5300FC

ALL

R 531318-01-2A 132

232

132 AC to CC, DW, KW,232 AW to HW,Insulation displaced as required

Detailed inspection of FRs 20, 20A and 25A from STRs 22 RH to 29 RH, internal structure.

T: 30000FC

I: 5200FC

ALL

531331-01-1A 100 N/A Detailed inspection of fuselage skin of FWD cargo compartment 

door cutout at upper and lower corners.

T: 18000FC

I: 2250FC

ALL

531339-01-1A 200 N/A Detailed inspection of lower skin of longitudinal lap joint in crack 

stopper areas at STR 5, 13, 22 LH/RH from FR 18 to FR 26/32, external surface.Note: this task is an alternative to 531339-02-1A

T: 33000FC

I: 4300FC

ALL

531339-02-1A 200 N/A Special detailed inspection (HFEC) of lower skin of longitudinal lap 

joint STR5 LH/RH in rivet row between FR18 and FR26

N t thi t k i lt ti t 531339 01 1A

T: 33000FC

I: 16000FC

531339 ALL

Note: this task is an alternative to 531339-01-1A 

531343-01-1A 100 N/A General visual inspection of lower skin of longitudinal lap joint in 

crack stopper areas at STRs 31, 43 LH and 28, 39 RH from FR 18 to FR 26/32 and at STRs 46 RH and 51 LH from FR 19 to FR 26/32, external surface.

T: 33000FC

I: 2800FC

ALL 

531354-01-1A 200 835 Detailed inspection of fuselage skin of MDC door cutout at upper and 

lower corners, external surface.

T: 12000FC

I: 9000FC

-200C

531355-01-1A 233

835

835,bolt,Lining, Insulation displaced as required

Detailed and Special detailed inspection (HFEC + Rotating probe) of piano hinges of MDC door, on fuselage and door, including surround structure.

T: 18000FC

I: 12000FC

531355 -200C

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531357-01-1A 233 Ceiling panels,

lining, Insulation displaced as required

Detailed inspection of support structure of piano hinge for MDC door from STRs 4 to 5 LH, longeron from FR 20 to FR 33 and attach fitting for door struts.

T: 12000FC

I: 9200FC

-200C

R 531359-01-1A 231 835

Eccentric bolts

Detailed inspection of MDC door eccentric bolts from FR 20B to FR 26/32.

T: 12000FC

I: 12000FC

-200C

531361-01-1A 131 Lining, 

Insulation displaced as required

Detailed inspection of attachment areas of lock fittings and MDC door lower longeron from FR 19 to FR 34 and from STRs 26 LH to 34 LH.

T: 12000FC

I: 12000FC

-200C

531363-01-1A 131/132

133/134231/232233/234

Ceiling andsidewall panels,cargo floor panels,Insulation displaced as required

Detailed inspection of fuselage FRs 20 and 33 from crown to bottom center line.

T: 12000FC

I: 12000FC

-200C

531365-01-1A 232/234 Ceiling panels,

I l ti

Detailed inspection of attachment area of truss frames with normal f f FR 21 t FR 26/32 d f STR 5 t 10 RH (6

T: 12000FC

I 8800FC

-200C

Insulation displaced as required

frames from FR 21 to FR 26/32 and from STRs 5 to 10, RH (6 places).

I: 8800FC

531366-01-1A 100

200

N/A General visual inspection of fuselage skin around MDC door cutout 

from FR 19 to FR 34 and from STR 3 to STR 31, LH, external surface.

T: 4950FC

I: 4950FC

-200C

531370-01-1A 100 N/A Special detailed inspection (HFEC + Rotating probe) of longitudinal 

butt joint rivet rows, above and below the skin gap at STR 35 LH, between FR18 to FR 35, external surface .

T: 33000FC

I: 11000FC

531370 -200C

R 531371-01-1A 100 N/A General visual inspection of fuselage skin external surface from FR 

19 to FR 54 and from STRs 26 RH/LH to bottom center line, excluding the areas under fairings.NOTE: This task is an alternative to task 531371-02-1A.

T: 2200FC

I: 2200FC

ALL 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. 

A310

Airworthiness Limitation Items

N 531371-02-1A 100 N/A Detailed inspection of fuselage skin external surface from FR 19 to 

FR 54 and from STRs 26 RH/LH to bottom center line, excluding the areas under fairings.NOTE: This task is an alternative to task 531371-01-1A.

T: 6900FC

I: 6900FC

N 531372-01-1A 100 N/A General visual inspection of fuselage skin external surface, from FR 

19 to FR 40/41, and from STR 6 to STR 26, LH/RH.NOTE: This task is an alternative to task 531372-02-1A.

T: 20000FC

I: 2200FC

N 531372-02-1A 100 N/A Detailed inspection of fuselage skin external surface, from FR 19 to 

FR 40/41, and from STR 6 to STR 26, LH/RH.NOTE: This task is an alternative to task 531372-01-1A.

T: 20000FC

I: 6900FC

N 531373-01-1A 100 N/A General visual inspection of fuselage skin external surface, from FR 

19 to FR 40/41, and from STR 6 to Crown Center Line LH/RH.NOTE: This task is an alternative to task 531373-02-1A.

T: 4500FC

I: 4500FC

N 531373-02-1A 100 N/A Detailed inspection of fuselage skin external surface, from FR 19 to 

FR 40/41 and from STR 6 to Crown Center Line LH/RH

T: 6900FC

I: 6900FC

FR 40/41, and from STR 6 to Crown Center Line, LH/RHNOTE: This task is an alternative to task 531373-01-1A.

I: 6900FC

531378-01-2A 132 811 General visual inspection of FWD cargo compartment door cutout, 

visible part of lateral frames (FR 20A and 25A) and sill beam, as far as visible.

T: 6500FC

I: 6500FC

531393-01-1A 134 132BF,CF,KF,

MF,ballmat insulation Cargo roller tracks to be removed

Special detailed inspection (HFEC) of Attachment Areas of Lock Fittings from FR 20 to FR 26/32 from Cargo Door Floor Level to STR 45 RH 

T: 40000FC

I: 4000FC

531393-01-2A 134 132BF,CF,KF,

MF,ballmat insulation Cargo roller tracks to be removed

Special detailed inspection (HFEC) of Attachment Areas of Lock Fittings from FR 20 to FR 26/32 from Cargo Door Floor Level to STR 45 RH 

T: 35000FC

I: 4000FC

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531410-01-2A 513/613 Krueger flap 

extended513 AL, 613 AR

Detailed inspection of fuselage skin from FR 36 and FR 37 and from STRs 30 to 32 LH/RH, external surface.

T: 30000FC

I: 7600FC

ALL

531411-01-2A 513/613 513 AL, GL

613 AR, GR

Detailed inspection of fuselage skin around wing fairing attachment fittings at FR 38, FR 38.1 and FR 38.2 LH/RH, external surface.

T: 30000FC

I: 5400FC

ALL

531412-01-2A 131/132 131/132 QW,

Insulation displaced as required

Detailed inspection of FRs 38, 38.1 and 38.2 from STRs 27 to 34, LH/RH.

T: 30000FC

I: 5400FC

-200

531412-01-3A 131/132 131/132 QW,

Insulation displaced as required

Detailed inspection of FRs 38, 38.1 and 38.2 from STRs 27 to 34, LH/RH.

T: 30000FC

I: 7900FC

-300

531417-01-2A 200 N/A Detailed inspection of fuselage skin at FR 36 from STRs 2 LH to 2 

RH, external surface.

T: 30000FC

I: 10200FC

-200

531418-01-2A 200 N/A Detailed inspection of fuselage skin at FR 35 from STRs 2 LH to 2 

RH, external surface.

T: 30000FC

I: 12300FC

-300

531421 01 1A 531421-01-1A 100 N/A G l i l i ti f f l ki f FR 26/32 t FR 38 2 General visual inspection of fuselage skin from FR 26/32 to FR 38.2 T 18000FC ALL 

and from STRs 40 to 42 LH/RH, external surface.

T: 18000FC

I: 2600FC

ALL 

531429-01-1A 200 N/A Detailed inspection of lower skin of longitudinal lap joint in crack 

stopper areas at STRs 5, 13, 22 LH/RH from FR 26/32 to FR 40, external surface.Note: this task is an alternative to 531429-02-1A

T: 33000FC

I: 4300FC

ALL

531429-02-1A 200 N/A Special detailed inspection (HFEC) of lower skin of longitudinal lap 

joint STR 5 in rivet row between FR 26/32 and FR 40/41 LH/RH.Note: this task is an alternative to 531429-01-1A 

T: 33000FC

I: 16000FC

531429 ALL

531433-01-1A 100 N/A General visual inspection of lower skin external surface of 

longitudinal lapjoint in following crack stopper areas:- STRs 31 LH/RH from FR 26/32 to 35.- STRs 43, 47 LH and STRS 43, 49 RH from FR 26/32 to FR 39.

T: 33000FC

I: 2800FC

ALL 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531434-01-2A 513/613 Krueger flap 

extended513/613 AL, GL, RL

Special Detailed Inspection (HFEC) of fuselage external surface underneath wing fillet fairing from FR 37 to FR 40/41, including lower skin of longitudinal lap joint in crack stopper areas at STR 31 LH/RH.Note: this task is an alternative to 531434-03-1A

T: 33000FC

I: 16000FC

531434 ALL

531434-03-1A 513/613 Krueger flap 

extended513/613 AL, GL, RL

Detailed inspection of fuselage external surface underneath wing fillet fairing from FR 37 to FR 40/41, including lower skin of longitudinal lap joint in crack stopper areas at STR 31 LH/RH.Note: this task is an alternative to 531434-01-2A

T: 33000FC

I: 4300FC

ALL

531435-01-1A 231, 232, 

233, 234 

Ceiling and sidewall panels, insulation displaced as required

Special detailed inspection (LFEC) of Splice plate at circumferential skin splice at FR 26/32 from STR 4 LH/RH to crown centre line and from STR 5 to 12, LH/RH. Note: A310-300 Short Range Requirement beyond Extended Service Goal.

T: 43500FC

 123000FH

I: 7000FC

 20500FH

531435 -300 

531436-01-1A 231/232 

233/234 

Galleys, toilets, overhead stowage compartments, ceiling and 

sidewall

Special detailed inspection (LFEC) of Splice plate at circumferential skin splice at FR 35 from STR 9 to STR 13 LH, and from STR 6 to 12, RH.

T: 40000FC

 80000FH

I: 6500FC

 13000FH

531436 -200C 

sidewall

panels, insulation displaced as required

531501-01-2A 200 N/A Detailed inspection of skin in circumferential splice and stringer 

coupling areas at FR 40/41, from STR 13 LH/RH to crown center line, external surface.

T: 41200FC

 82400FH

I: 12800FC

 25600FH

-200

531501-01-4A 200 N/A Detailed inspection of skin in circumferential splice and stringer 

coupling areas at FR 40/41, from STR 13 LH/RH to crown center line, external surface.

T: 37400FC

 104600FH

I: 9800FC

 27700FH

-300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531502-01-1A 200 N/A Detailed inspection of lower skin external surface of longitudinal lap 

joints in following crack stopper areas:- at STR 5 and STR 13, LH/RH, from FR 40/41 to FR 54- at STR 22, LH/RH, from FR 45 to FR 54.Note: This task is an alternative to 531502-02-1A

T: 32000FC

I: 3600FC

ALL

531502-02-1A 200 N/A Special detailed inspection (HFEC) of lower skin external surface of 

longitudinal lap joint in rivet row at STR 5 and STR 13, LH/RH from FR 40/41 to FR 54 and at STR 22, LH/RH from FR 45 to FR 54.Note: This task is an alternative to 531502-01-1A

T: 32000FC

I: 16000FC

531502 ALL

531505-01-1A 200 N/A Detailed inspection of fuselage skin and visible part of window 

forgings from FR 45 to FR 54, and from STR 18 to STR 22 LH/RH, external surface.

T: 40000FC

I: 6500FC

-200

531505-01-2A 200 N/A Detailed inspection of fuselage skin and visible part of window 

forgings from FR 45 to FR 54, and from STR 18 to STR 22 LH/RH, external surface.

T: 35000 FC

I: 6500 FC

-300PRE 13

531505-01-3A 200 N/A Detailed inspection of fuselage skin and visible part of window 

forgings from FR 45 to FR 54, and from STR 18 to STR 22 LH/RH, external surface.

T: 35000 FC

I: 6400 FC

-300POST 

531506 01 1A 531506-01-1A 200 Antenna A t D t il d i ti f ki d VHF t t t f T 40000FC 200

removal

Detailed inspection of skin around VHF antenna cutout from FR 47/48 to FR 49 and between STR 1 LH and STR 1 RH, external surface.

T: 40000FC

 80000FH

 I: 6200FC

 12400FH

-200

531506-01-2A 200 Antenna 

removal

Detailed inspection of skin around VHF antenna cutout from FR 47/48 to FR 49 and between STR 1 LH and STR 1 RH, external surface.

 T: 35000 FC

 98000 FH

 I: 5300 FC

 14900 FH

-300PRE 13

531506-01-3A 200 Antenna 

removal

Detailed inspection of skin around VHF antenna cutout from FR 47/48 to FR 49 and between STR 1 LH and STR 1 RH, external surface.

 T: 35000 FC

 98000 FH

 I: 5100 FC

 14400 FH

-300POST 

531507-01-3A 241/242

243/244

Sidewall and ceiling panels,Insulation displaced as required

Detailed inspection of FR 40 and FR 47 from STR 22 LH/RH to crown center line.

T: 30000FC

I: 6650FC

-300

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531508-01-1A 200 N/A Detailed inspection of fuselage skin in frame coupling area at FR 42 

to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH, external surface.

T: 36500FC

 73000FH

I: 12200FC

 24500FH

-200

531508-01-2A 200 N/A Detailed inspection of fuselage skin in frame coupling area at FR 42 

to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH, external surface.

T: 29000 FC

 81000 FH

I: 6200 FC

 17600 FH

-300PRE 13

531508-01-3A 200 N/A Detailed inspection of fuselage skin in frame coupling area at FR 42 

to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH, external surface.

T: 29000 FC

 81000 FH

I: 6000 FC

 16900 FH

-300POST 

531509-01-1A 100/200

834/844

834/844 Detailed inspection of fuselage skin external surface, from FR 40/41 

to FR 45 and from STR 14 to STR 28 LH/RH, including visible portion of emergency exit frames and window forgings.

T: 40000FC

I: 6000FC

-200

531509-01-2A 100/200

834/844

834/844 Detailed inspection of fuselage skin external surface, from FR 40/41 

to FR 45 and from STR 14 to STR 28 LH/RH, including visible portion of emergency exit frames and window forgings.

T: 35000 FC

I: 6000 FC

-300PRE 13

531509-01-3A 100/200

834/844

834/844 Detailed inspection of fuselage skin external surface, from FR 40/41 

t FR 45 d f STR 14 t STR 28 LH/RH i l di i ibl

T: 35000 FC

I 5500 FC

-300

834/844 to FR 45 and from STR 14 to STR 28 LH/RH, including visible POST 

portion of emergency exit frames and window forgings.

I: 5500 FC POST 

531511-01-1A 241/242

834/844

834/844 General visual inspection of door stop fittings on 

FR 42A and FR 43A, LH/RH.

T: 18000FC

I: 12000FC

ALL 

531512-01-1A 100/200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 45, from STR 13 to STR 27, LH/RH, external surface.

T: 18000FC

 36000FH

I: 13500FC

 27000FH

-200 

531512-01-2A 100/200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 45, from STR 13 to STR 27, LH/RH, external surface.

T: 14400 FC

 40500 FH

I: 7400 FC

 20000 FH

-300PRE 13

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531512-01-3A 100/200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 45, from STR 13 to STR 27, LH/RH, external surface.

T: 14400 FC

 40500 FH

I: 7200 FC

 20000 FH

-300POST 

531513-01-1A 100/200 N/A General visual inspection of fuselage skin at FR 47/48 from wing to 

fuselage fairing to STR 13 LH/RH, external surface.

T: 18000FC 

I: 5900FC

ALL 

531515-01-1A 241/242 Sidewall 

panels,insulation displaced as required 

Detailed inspection of FR 46 between STR 22 and STR 26, LH/RH.

T: 40000FC

I: 16500FC

-200

531515-01-2A 241/242 Sidewall 

panels,insulation displaced as required 

Detailed inspection of FR 46 between STR 22 and STR 26, LH/RH.

T: 35000FC

I: 16500FC

-300

531518-01-1A 145/146 Main deck floor 

panels

Detailed inspection of longitudinal floor beams from FR 45 to FR 54, above pressure deck including shear plates, cross beams and attachment of cross beams. 

T: 24000FC

I: 12000FC

ALL

531519-01-1A 145/146 Main deck floor 

l

General visual inspection of membranes of pressure deck between FR 47 d FR 54 f

T: 24000FC

I 12500FC

ALL 

panels FR 47and FR 54, upper surface. I: 12500FC

R 531524-01-1A 200 Anticollision 

light

Detailed inspection of fuselage skin around anti-collision light cutout from FR 42 to FR 43, and from STR 1 LH to STR 1 RH, external surface.

T: 40000FC

 80000FH

I: 18000FC

 36000FH

-200

R 531524-01-2A 200 Anticollision 

light

Detailed inspection of fuselage skin around anti-collision light cutout from FR 42 to FR 43, and from STR 1 LH to STR 1 RH, external surface.

T: 35000FC

 98000FH

I: 14400FC

 50500FH

-300 

N 531529-01-1A 200 N/A General visual inspection of fuselage skin external surface, from FR 

40/41 to FR 80/82, and from STR 6 to crown center line, LH/RH.Note: This task is an alternative to task 531529-02-1A.

T: 4500FC

I: 4500FC

ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

N 531529-02-1A 200 N/A Detailed inspection of fuselage skin external surface, from FR 40/41 

to FR 80/82, and from STR 6 to crown center line, LH/RH.Note: This task is analternative to task 531529-01-1A.

T: 6900FC

I: 6900FC

ALL

N 531530-01-1A 200 N/A General visual inspection of fuselage skin external surface, from FR 

40/41 to FR 80/82, and from STR 6 to STR 26, LH/RH.Note: This task is an alternative to task 531530-02-1A.

T: 20000FC

I: 2200FC

ALL

N 531530-02-1A 200 N/A Detailed inspection of fuselage skin external surface, from FR 40/41 

to FR 80/82, and from STR 6 to STR 26, LH/RH.Note: This task is an alternative to task 531530-01-1A.

T: 20000FC

I: 6900FC

ALL

531541-01-1A 241/242 Main deck floor 

panelSealant Removal

Special detailed inspection (HFEC) of longitudinal beams 1 to 5 lower flange at FR47-1, 49-1, 50-1, 51, 51-1, 52-1 and 53-1, LH/RH.

T: 33000FC

I: 9200FC

531541 -200

531542-01-1A 141/142 734, 744

147/148AZSealant Removal

Special detailed inspection (Ultrasonic) of stiffener at wing to fuselage lower skin splice at rib 1 (center wing box side) from FR42 to FR47.

T: 21800FC

 43600FH

I: 2800FC

 5700FH

531542 -200

531542-01-3A 141/142 734, 744

147/148AZSealant 

Removal

Special detailed inspection (Ultrasonic) of stiffener at wing to fuselage lower skin splice at rib 1 (center wing box side) from FR42 to FR47.

T: 23900FC

 67200FH

I: 6000FC

16900FH

531542 -300 

Removal

531551-01-1A 143/144 144 FR

143 FL

Detailed inspection of fuselage skin and doubler around air conditioning compartment access cutouts, LH/RH.

T: 22700FC

 45400FH

I: 22700FC

 45400FH

-200

531551-01-2A 143/144 144 FR

143 FL

Detailed inspection of fuselage skin and doubler around air conditioning compartment access cutouts, LH/RH.Note: Internal and external side to be inspected

T: 16500FC

 46300FH

I: 16500FC

 46300FH

-300 

531552-01-1A 145/146

241/242

Main deck floor panels, insulation, bolts to be removed

Special detailed inspection (Rotating Probe) of FR49, 50, 51, 52 and 53 between STR 25 and 29 at frame foot, LH/RH.

T: 35000FC

 70100FH

I: 8600FC

 17300FH

531552 -200 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531552-01-2A 145/146

241/242

Main deck floor panels, insulation, bolts to be removed 

Special detailed inspection (Rotating Probe) of FR49, 50, 51, 52 and 53 between STR 25 and 29 at frame foot, LH/RH.

T: 30700FC

 85900FH

I: 8600FC

 24200FH

531552 -300 

531555-01-1A 147/148 734/744 General visual inspection of slanted frames from FR 47 to FR 54, 

LH/RH.

T: 6600FC

 13300FH

I: 6600FC 

 13300FH

-200 

531555-01-2A 147/148 734/744 General visual inspection of slanted frames from FR 47 to FR 54, 

LH/RH.

T: 6700FC

 19000FH

I: 6700FC 

 19000FH

-300 

531556-01-1A 147/148 734/744

147/148 CZ

Detailed inspection of fuselage internal structure at FR 47/48 from STRs 42 to 43, LH/RH.

T: 11200FC

 22400FH

I: 3300FC

 6600FH

-200

531556-01-2A 147/148 734/744

147/148 CZ

Detailed inspection of fuselage internal structure at FR 47/48 from STRs 42 to 43, LH/RH.

T: 12400FC

 34700FH

I: 2800FC

 8000FH

-300 

531561 01 1A 531561-01-1A 145/146 145/146 M i d k fl D t il d i ti f FR47A 49A 50A 51A d 52A t f f t T 28900FC 200

241/242

Main deck floor panels, insulation. 

Detailed inspection of FR47A, 49A, 50A, 51A and 52A at frame foot runout, LH/RH. 

T: 28900FC

 57900FH

I: 15200FC

 30500FH

-200

531561-01-2A 145/146 

241/242

Main deck floor panels, insulation. 

Detailed inspection of FR47A, 49A, 50A, 51A and 52A at frame foot runout, LH/RH. 

T: 30800FC

 86200FH

I: 15200FC

 42600FH

-300 

531567-01-1A 147/148 734/744 Detailed inspection of keel beam side panels, adjacent fuselage 

structure up to STR 40 and MLG hinge assemblies and door actuator fitting from FR 47 to FR 54, LH/RH.

T: 15300FC

 30700FH

I: 4000FC

 8000FH

-200

531567-01-2A 147/148 734/744 Detailed inspection of keel beam side panels, adjacent fuselage 

structure up to STR 40 and MLG hinge assemblies and door actuator fitting from FR 47 to FR 54, LH/RH.

T: 16100FC

 45300FH

I: 3600FC

 10300FH

-300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531571-01-2A 143/144

147/148

734/744143DF147AF,BF,BZ148BF

Detailed inspection of keel beam box from FR44 to FR54, internal structure.

T: 19000FC

 38000FH

I: 11600FC

 23300FH

-200

531571-01-3A 143/144

147/148

734/744143DF147AF,BF,BZ148BF

Detailed inspection of keel beam box from FR44 to FR54, internal structure.

T: 18300FC

 51200FH

I: 15000FC

 42100FH

-300 

R 531574-01-1A 145/146 734/744, angle 

web to be removed

Special detailed inspection (Ultrasonic) of STR36 fillet radius at FR54, internal structure, LH/RH.

T: 24900FC

I: 5600FC

 531574 

Proc A 

and Proc 

B

-200 PO53-2014980)

531579-01-1A 135/136

137/138

Cargo compartment floor and sidewall panelsInsulation displaced as required

Detailed inspection of FWD face of pressure bulkhead at FR 39, including stringer end fittings from STR35 LH / STR35 RH to bottom center line

T: 15800FC

 31600FH

I: 7700FC

 15400FH

-200PRE 55

531579-01-2A 135/136

137/138

Cargo 

t t

Detailed inspection of FWD face of pressure bulkhead at FR 39, i l di t i d fitti f STR35 LH / STR35 RH t b tt

T: 26500FC

53100FH

-200

137/138 compartment POST 

floor and sidewall panelsInsulation displaced as required

including stringer end fittings from STR35 LH / STR35 RH to bottom center line

 53100FH

I: 17500FC

 35000FH

POST or -200 PO

531579-01-3A 135/136

137/138

Cargo compartment floor and sidewall panelsInsulation displaced as required

Detailed inspection of FWD face of pressure bulkhead at FR 39, including stringer end fittings from STR35 LH / STR35 RH to bottom center line

T: 33400FC

 93500FH

I: 23500FC

 66000FH

-300 

531580-01-1A 143/144 734/744

147BZ

Detailed inspection of stringer end fittings and horizontal cross members at AFT face of pressure bulkhead at FR39, from STR35 to bottom center line, LH/RH

T: 14500FC

 29100FH

I: 7700FC

 15400FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531580-01-2A 143/144 734/744

147BZ

Detailed inspection of stringer end fittings and horizontal cross members at AFT face of pressure bulkhead at FR39, from STR35 to bottom center line, LH/RH

T: 20200FC

 56500FH

I: 8700FC

 24300FH

-300 

R 531582-01-1A 143/144 571 / 671 AB Special detailed inspection (Ultrasonic) of fuselage skin from 

FR47/48 to FR49 and from STR 35 to STR 36, LH/RH.

T: 30100FC

 60300FH

I: 18300FC

 36600FH

531582 -200

R 531582-01-2A 143/144 571 / 671 AB Special detailed inspection (Ultrasonic) of fuselage skin from 

FR47/48 to FR49 and from STR 35 to STR 36, LH/RH.

T: 27700FC

 77600FH

I: 16700FC

 46700FH

531582 -300 

531584-01-1A 143/144 Chafing plate 

removal as per SB 53-2069Sealant Removal

Special detailed inspection (LFEC and Ultrasonic) of fuselage skin underneath pick-up angle from FR 39 to FR 42, LH/RH.

T: 15600FC

 31300FH

I: 9100FC 

 18300FH

531584 -200

PRE 12

531584-01-2A 143/144 Chafing plate 

removal as per SB 53-2069

Slt

Special detailed inspection (LFEC and Ultrasonic) of fuselage skin underneath pick-up angle from FR 39 to FR 42, LH/RH.

T: 17000FC

 34000FH

I: 4500FC 

9100FH

531584 -200

POST 

Sealant Removal

 9100FH

531584-01-3A 143/144 Chafing plate 

removal as per SB 53-2069Sealant Removal

Special detailed inspection (LFEC and Ultrasonic) of fuselage skin underneath pick-up angle from FR 39 to FR 42, LH/RH.

T: 15400FC

 43100FH

I: 9100FC 

 25400FH

531584 -300

PRE 12

531584-01-4A 143/144 Chafing plate 

removal as per SB 53-2069Sealant Removal

Special detailed inspection (LFEC and Ultrasonic) of fuselage skin underneath pick-up angle from FR 39 to FR 42, LH/RH.

T: 20000FC

 56100FH

I: 4500FC 

 12700FH

531584 -300

POST 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531586-01-1A 241/242 241BW 

242BW

Special detailed inspection (X-RAY) of fuselage skin doubler at FR40/41, between STRs 20 and 23, LH/RH

T: 29600FC

 59300FH

I: 4500FC

 9000FH

 531586 -200

531586-01-2A 241/242 241BW 

242BW

Special detailed inspection (X-RAY) of fuselage skin doubler at FR40/41, between STRs 20 and 23, LH/RH

T: 29400FC

 82300FH

I: 2200FC

 6100FH

 531586 -300 

531587-01-1A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 21300FC

 42700FH

I: 13500FC

 27100FH

-200PRE 54

531587-01-2A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 35100FC

 70200FH

I: 13500FC

 27100FH

-200POST 

531587-01-3A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 21100FC

 59100FH

I: 13400FC

 37600FH

-300PRE 54

531587 01 4A 531587-01-4A 147/148 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 734/744 D t il d i ti f M i L di G t t tt h t fitti T 27200FC 300 

lower part, LH/RH.

T: 27200FC

 76100FH

I: 13400FC

 37600FH

-300PARTIA5411

531587-01-5A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 34700FC

 97300FH

I: 13400FC

 37600FH

-300POST 

531588-01-3A 147/148

151/152153/154

734/744Floor and sidewall panels, bolts, Insulation displaced as required

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 43 to STR 46,13 holes RH and 16 holes LH.

T: 28300FC

I: 10000FC 

531588 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531588-01-5A 147/148

151/152153/154

734/744Floor and sidewall panels, bolts, Insulation displaced as required

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 43 to STR 46,13 holes RH and 16 holes LH.

T: 31200FC

I: 12000FC 

531588 -300

531589-01-3A 147

151153

734/744Sidewall panels, bolts, Insulation displaced as required

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 39 to STR 40, 5 holes LH.Note: this task is an alternative to 531589-01-4A

T: 28300FC

I: 10000FC

531589 -200

531589-01-4A 147

151153

734/744Sidewall panels, Insulation displaced as required

Special detailed inspection (X-RAY) of circumferential skin joint and frame at FR 54 from STR 39 to STR 40, 5 holes LH.Note: this task is an alternative to 531589-01-3A

T: 28300FC

I: 6000FC

531589 -200

531589-01-5A 147,151

153

734/744Sidewall panels, bolts, 

I l ti

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 39 to STR 40, 5 holes LH.N t thi t k i lt ti t 531589 01 6A

T: 31000FC

I: 12000FC

531589 -300

Insulation displaced as required.

Note: this task is an alternative to 531589-01-6A

531589-01-6A 147,151

153

734/744Sidewall panels, Insulation displaced as required.

Special detailed inspection (X-RAY) of circumferential skin joint and frame at FR 54 from STR 39 to STR 40, 5 holes LH.Note: this task is an alternative to 531589-01-5A

T: 31000FC

I: 6000FC

531589 -300

531590-01-2A 147,151

153

734/744572 AB,bolts,Sidewall panels,Insulation displaced as required.

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 35 to STR 37, 13 holes LH.

T: 24000FC

I: 12000FC

531590 ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531591-01-3A 148,152

154

734/744672 AB, bolts, Sidewall panels, Insulation displaced as required.

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 36 to STR 37, 7 holes, RH.

T: 25000FC

I: 10000FC 

531591 -200

531591-01-5A 148,152

154

734/744672 AB, bolts, Sidewall panels, Insulation displaced as required.

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 36 to STR 37, 7 holes, RH.

T: 28000FC

I: 12000FC 

531591 -300

531594-01-1A 147/148

151/152153/154

734/744Sidewall and floor panels, Insulation displaced as required, bolts removal.

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR54 from STR 43 to STR 46, 15 holes RH and 24 holes LH

T: 28800FC

I: 5000FC

531594 -200

531594-01-2A 147/148

151/152

734/744Sid ll d

Special detailed inspection (Rotating Probe) of circumferential skin j i t d f t FR54 f STR 43 t STR 46 15 h l RH d

T: 28800FC

I 6000FC

531594 -300

151/152153/154

Sidewall and floor panels, Insulation displaced as required, bolts removal.

joint and frame at FR54 from STR 43 to STR 46, 15 holes RH and 24 holes LH

I: 6000FC

531595-01-3A 147,151

153

744/734Sidewall panels, bolts, Insulation displaced as required.

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-4A

T: 33500FC

I: 8000FC 

531595 -200

531595-01-4A 147,151

153

734/744Sidewall panels, Insulation displaced as required.

Special detailed inspection (X-RAY) of circumferential skin joint and frame at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-3A

T: 33500FC

I: 5000FC

531595 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531595-01-5A 147,151

153

734/744Sidewall panels, bolts, Insulation displaced as required

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-6A

T: 36000FC

I: 9000FC 

531595 -300

531595-01-6A 147,151

153

734/744Sidewall panels, Insulation displaced as required.

Special detailed inspection (X-RAY) of circumferential skin joint and frame at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-5A

T: 36000FC

I: 5500FC 

531595 -300

531596-01-2A 147,151

153

734/744572 AB, bolts, Sidewall panels, Insulation displaced as required

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54, from STR 36 to STR 38, 13 holes LH.

T: 38300FC

I: 6000FC

531596 ALL

531597-01-1A 148

152

734/744672AB, sidewal panels, 

I l ti

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 36 to STR 40, 7 holes RH

T: 27000FC

I: 5000FC

531597 -200

Insulation displaced as required, bolts removal

531597-01-2A 148

152

734/744, 672AB, sidewal panels, Insulation displaced as required, bolts removal

Special detailed inspection (Rotating Probe) of circumferential skin joint and frame at FR 54 from STR 36 to STR 40, 7 holes RH

T: 27000FC

I: 6000FC

531597 -300

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531602-01-1A 243

244253254

Ceiling panels, insulation, overhead stowage compartments (if fitted), bolts. 

Special detailed inspection (Rotating Probe) of splice plate at the circumferential skin splice at FR54 at STR5, LH/RH

T: 38000FC

 76000FHI: 8700FC 17500FH

531602 -200

531602-01-2A 243

244

Ceiling panels, insulation, overhead stowage compartments (if fitted), bolts. 

Special detailed inspection (Rotating Probe) of splice plate at the circumferential skin splice at FR54 at STR5, LH/RH

T: 34600FC

 97200FHI: 7100FC 20000FH

531602 -300 

531605-01-2A 200 N/A Detailed inspection of skin in circumferential splice and stringer 

coupling areas at FR 55/58 from STR 13, LH/RH, to crown center line, external surface.Note: This task is an alternative to 531605-02-1A

T: 22000FC 

 44500FH 

I: 10000FC 

 20000FH 

-200

531605-01-3A 200 N/A Detailed inspection of skin in circumferential splice and stringer 

li t FR 55/58 f STR 13 LH/RH t t

T: 15500FC 

43500FH

-300 

coupling areas at FR 55/58 from STR 13, LH/RH, to crown center line, external surface.Note: This task is an alternative to 531605-02-4A

 43500FH 

I: 7300FC 

 20000FH 

531605-02-1A 200 N/A Special detailed inspection (HFEC) of skin in circumferential splice 

and stringer coupling areas at FR 55/58 from STR 13, LH/RH, to crown center line, external surface.Note: This task is an alternative to 531605-01-2A

T: 22000FC 

 44500FH 

I: 14500FC 

 29500FH 

531605 -200

531605-02-4A 200 N/A Special detailed inspection (HFEC) of skin in circumferential splice 

and stringer coupling areas at FR 55/58 from STR 13, LH/RH, to crown center line, external surface.Note: This task is an alternative to 531605-01-3A

T: 15500FC 

 43500FH 

I: 10600FC 

 29500FH 

531605 -300 

531606-01-3A 200 N/A Special Detailed Inspection (LFEC) of Splice plate at circumferential 

skin splice at FR 55/58 from STR 4 LH/RH to crown centre line and from STR 5 to 12, LH/RH

T: 20500FC

41000FH

I: 3000FC

6000FH

531606 -200

PRE 1353-212

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531606-01-4A 200 N/A Special Detailed Inspection (LFEC) of Splice plate at circumferential 

skin splice at FR 55/58 from STR 4 LH/RH to crown centre line and from STR 5 to 12, LH/RH 

T: 16000FC

46000FH

I: 2400FC

6700FH

531606 -300

PRE 1353-212

531608-01-1A 100 N/A General visual inspection of lower skin of longitudinal lap joint in 

crack stopper areas at STR 44 LH/RH, from FR 54 to FR 55/58, external surface.

T: 32000FC

I: 2250FC

ALL

531610-01-1A 100 N/A Special detailed inspection (LFEC + US) of lower skin of longitudinal 

lap joint at STR 52, LH/RH, from FR 54 to FR 55/58, external surface.

T: 32000FC

I: 16000FC

531610 ALL

531611-01-1A 200 N/A Detailed inspection of skin at shear tie attachments at FR 54.1, 54.2 

and 54.3 from STR 22 LH/RH, to crown center line, external surface.

T: 28000FC

 56000FH

I: 3800FC

 7700FH

-200

531611-01-2A 200 N/A Detailed inspection of skin at shear tie attachments at FR 54.1, 54.2 

and 54.3 from STR 22 LH/RH, to crown center line, external surface.

T: 27000FC

 76500FH

I: 3700FC

 10600FH

-300 

R 531612-01-1A 100 N/A General visual inspection of fuselage skin external surface, from FR 

54 to FR 80/82, and from STR 26 LH/RH, to bottom center line, excluding area covered by the AFT wing root fairings.Note: This is an alternative to task 531612-02-1A.

T: 2200FC

I: 2200FC

ALL 

N 531612-02-1A 100 N/A Detailed inspection of fuselage skin external surface, from FR 54 to 

FR 80/82, and from STR 26 LH/RH, to bottom center line, excluding area covered by the AFT wing root fairings.Note: This is an alternative to task 531612-01-1A.

T: 6900FC

I: 6900FC

ALL

531616-01-1A 200

577/677

577 AL677 AR

Detailed inspection of lower skin external surface of longitudinal lap joint in crack stopper areas at STRs 5, 13, 22 and 31, LH/RH, from FR 54 to FR 55/58.Note : This task is an alternative to 531616-02-1A

T: 32000FC

I: 3600FC

ALL

531616-02-1A 200

577/677

577 AL677 AR

Special Detailed Inspection (HFEC) of Iower skin external surface of longitudinal lap joints in rivet row at STRs 5, 13, 22 and 31, LH/RH, from FR 54 to FR 55/58.Note : This task is an alternative to 531616-01-1A 

T: 32000FC

I: 16000FC

531616 ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531621-01-1A 253/254 Ceiling planels, 

Insulation displaced as required, air conditioning duct, overhead stowage compartments, bolts

Special Detailed Inspection ( HFEC + Rotating probe ) of splice plate at circumferential skin splice at FR 55/58, from STR 4 to STR 6, LH/RH, and from STR 12 to STR 13, LH/RH, i.e. where lap joints intersect with circumferential skin splice. 

T: 30000FC

 60000FH

I: 19000FC

 38000FH

531621 -200

PRE 1353-212

531621-01-2A 253/254 Ceiling planels, 

Insulation displaced as required, air conditioning duct, overhead stowage compartments, bolts

Special Detailed Inspection ( HFEC + Rotating probe ) of splice plate at circumferential skin splice at FR 55/58, from STR 4 to STR 6, LH/RH, and from STR 12 to STR 13, LH/RH, i.e. where lap joints intersect with circumferential skin splice.

T: 26500FC

 75000FH

I: 16000FC

 44500FH

531621 -300

PRE 1353-212

531633-01-1A 251/252 N/A Detailed inspection of fuselage skin and visible portion of window 

forgings between FR 54 and FR 77 from

STR 18 t STR 22

T: 40000FC

I: 6500FC

-200

STR 18 to STR 22. 

531633-01-2A 251/252 N/A Detailed inspection of fuselage skin and visible portion of window 

forgings between FR 54 and FR 77 from STR 18 to STR 22. 

T: 35000FC

I: 6500FC

-300

531701-01-3A 200 N/A Detailed inspection of fuselage skin in circumferential splice and 

stringer coupling areas at FR 72, from STR 13 LH/RH, to crown center line, external surface. 

T: 30000FC

 60000FH

I: 14400FC

 28500FH

-200

531701-01-4A 200 N/A Detailed inspection of fuselage skin in circumferential splice and 

stringer coupling areas at FR 72, from STR 13 LH/RH, to crown center line, external surface. 

T: 26500FC

 75000FH

I: 10500FC

 29500FH

-300 

531702-01-3A 200 N/A Special detailed inspection (LFEC) of splice plate at circumferential 

skin splice at FR 72, from STR 4, LH/RH, to crown center line and from STR 6 to STR 11, LH/RH.

T: 33000FC

 66000FH

I: 9000FC

 18000FH

531702 -200 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531702-01-4A 200 N/A Special detailed inspection (LFEC) of splice plate at circumferential 

skin splice at FR 72, from STR 4, LH/RH, to crown center line and from STR 6 to STR 11, LH/RH.

T: 29000FC

 82000FH

I: 7500FC

 21000FH

531702 -300 

R 531704-01-1A 200

577

577 BL , 577 EL

Detailed inspection of lower skin external surface of longitudinal lap joints in following crack stopper areas:- at STRs 5,13 and 22, LH/RH from FR 55/58 to FR 72- at STR 31, LH, from FR 55/58 to FR 62.Note : This task is an alternative to 531704-02-1A 

T: 32000FC

I: 3600FC

ALL

R 531704-02-1A 200

577

577 BL , 577 EL

Special detailed inspection (HFEC) of lower skin external surface of longitudinal lap joints in rivet row: At STR 5 LH/RH from FR 55/58 to FR 72 At STR 31 LH from FR55/58 to 62.Note : This task is an alternative to 531704-01-1A 

T: 32000FC

I: 16000FC

531704 ALL

531708-01-1A 200 N/A General visual inspection of skin at shear tie attachments from FR 

55/58 to FR 72, and from STR 13, LH/RH, to crown center line, external surface.

T: 18000FC

I: 8800FC

ALL 

531712-01-1A 100 N/A General visual inspection of skin of AFT cargo compartment door 

cutout at upper and lower corners, external surface.

T: 18000FC

I: 4200FC

ALL 

531713-01-1A 152

154

812 General visual inspection of AFT cargo compartment door cutout, 

visible parts of FR 59A and FR 63A and sill beam.

T: 6500FC

I: 6500FC

ALL 

R 531716-01-1A 154 812

Eccentric bolts

Detailed inspection of AFT cargo compartment door eccentric bolts and bushes from FR 60 to FR 63 and from STR 44 RH to STR 46 RH.

T: 20000FC

I: 10000FC

ALL

R 531716-02-1A 154 812 General visual inspection of AFT cargo compartment door lock 

fittings and surrounding structure from FR 60 to FR 63and from STR 44 RH to STR 46 RH.

T: 8000FC

I: 8000FC

ALL 

531719-01-1A 162 813 General visual inspection of bulk cargo compartment door cutout, 

visible parts of FR 67 and FR 69.

T: 6500FC

I: 6500FC

ALL 

531720-01-1A 100 N/A General visual inspection of skin of bulk cargo compartment door 

cutout at upper corners, external surface.

T: 18000FC

I: 3500FC

ALL 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531721-01-3A 162

164

Scuff plate removal

Detailed inspection of skin of bulk cargo compartment door cutout at lower corners, underneath scuff plate.

T: 30000FC

I: 12000FC

-200

531721-02-4A 162

164

Scuff plate removal

Detailed inspection of skin of bulk cargo compartment door cutout at lower corners, underneath scuff plate.

T: 30000FC

I: 8000FC

-300

531722-01-2A 162

164

813Lining, floor panels, Insulation displaced as required.

Detailed inspection of fuselage internal structure around bulk cargo compartment door cutout from FR 66 toFR 70 from STR 31 RH to STR 48 RH.

T: 30000FC

I: 9000FC

ALL

531723-01-1A 162 813 Detailed inspection of bulk cargo door stop fittings at FR 67 and FR 

69.

T: 40000FC

I: 8000FC

-200

531723-01-2A 162 813 Detailed inspection of bulk cargo door stop fittings at FR 67 and FR 

69.

T: 35000FC

I: 8000FC

-300

531726-01-1A 100 N/A General visual inspection of lower skin external surface of 

longitudinal lap joint in following crack stopper areas:- at STR 31 RH, from FR 65 to FR 72,- at STR 31 LH, from FR 62 to FR 72,

t STR 44 LH 47 RH d 48 RH f FR 55/58 t FR 72

T: 32000FC

I: 2250FC

ALL

- at STRs 44 LH, 47 RH and 48 RH from FR 55/58 to FR 72,

- at STR 52 LH/RH from FR 55/58 to FR 65,- at STR 57 LH/RH from FR 65 to FR 72.

531731-01-1A 253/254 Ceiling panels,

Insulation displaced as required, air conditioning duct,overhead stowage compartments,bolts

Special detailed inspection (HFEC + rotating probe) of splice plate at circumferential skin splice at FR 72, from STRs 3 to 7, LH/RH, and from STRs 11 to 13, LH/RH, (at intersection of lap joints with circumferential skin splice).

T: 33000FC

 66000FH

I: 21000FC

 42000FH

531731 -200 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531731-02-1A 253/254 Ceiling panels,

Insulation displaced as required, air conditioning duct,overhead stowage compartments,bolts

Special detailed inspection (HFEC + rotating probe) of splice plate at circumferential skin splice at FR 72, from STRs 3 to 7, LH/RH, and from STRs 11 to 13, LH/RH, (at intersection of lap joints with circumferential skin splice).

T: 29000FC

 82000FH

I: 17000FC

 47500FH

531731 -300 

531732-01-1A 251/252 Sidewall 

panels,Insulation displaced as required

Detailed inspection of fuselage internal structure from FR 59 to FR 64, and from STR 19 to STR 23, LH/RH, in frame coupling areas.

T: 18000FC

I: 6000FC

ALL

531737-01-1A 240 Antenna to be 

removed

Detailed inspection of skin around ADF1 and ADF2 antenna cutouts between FR 59 and FR 60 and between FR 62 and FR 63, on crown center line, external surface. 

T: 40000FC

 80000FH

I: 9000FC

 18000FH

-200

531737-01-2A 240 Antenna to be 

removed

Detailed inspection of skin around ADF1 and ADF2 antenna cutouts between FR 59 and FR 60 and between FR 62 and FR 63, on crown center line, external surface. 

T: 35000FC

 98000FH

I: 7200FC

 20000FH

-300 

531801-01-1A 200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 76, from STR 13 LH/RH, to crown center line, external surface. 

T: 18000FC

 36000FH

I: 11800FC

 23600FH

-200 

531801-01-2A 200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 76, from STR 13, LH/RH, to crown center line, external surface.

T: 16000FC

 45000FH

I: 10500FC

 29500FH

-300 

531803-01-1A 200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 80/82, from STR 6 to STR 13, LH/RH, external surface. 

T: 18000FC

 36000FH

I: 16000FC

 32000FH

-200 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531803-01-2A 200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 80/82, from STR 6 to STR 13, LH/RH, external surface.

T: 12500FC

 36000FH

I: 11400FC

 32000FH

-300 

531806-01-1A 200 N/A Detailed inspection of lower skin external surface of longitudinal lap 

joints in following crack stopper areas:- at STR 6, LH/RH, from FR 72 to FR 80/82- at STRs 17 and 24, LH/RH, from FR 76 to FR 80/82.Note : This task is an alternative to 531806-02-1A 

T: 32000FC

I: 3600FC

ALL

531806-02-1A 200 N/A Special detailed inspection (HFEC) of Iower skin external surface of 

longitudinal lap joints in rivet row: - at STR6, LH/RH from FR72 to FR76 and from FR76 to FR80 Note : This task is an alternative to 531806-01-1A. 

T: 32000FC

I: 16000FC

531806 ALL

531807-01-1A 100/200 N/A General visual inspection of fuselage skin and fail safe ring around 

AFT passenger/crew door cutouts from FR 73 to FR 76, and from STR 9 to STR 28, external surface (without scuff plate removal).

T: 5000FC

 10000FH

I: 5000FC

 10000FH

-200 

531807-01-2A 100/200 N/A General visual inspection of fuselage skin and fail safe ring around 

AFT passenger/crew door cutouts from FR 73 to FR 76, and from 

STR 9 t STR 28 t l f ( ith t ff l t l)

T: 4000FC

 11200FH

I 4000FC

-300 

STR 9 to STR 28, external surface (without scuff plate removal). I: 4000FC

 11200FH

531808-01-3A 261/262 833/843 Special detailed inspection (HFEC) of AFT passenger/crew door 

cutouts, upper corners including skin and fail safe ring.

T: 30000FC

 60000FH

I: 10200FC

 20400FH

531808 -200

531808-01-4A 261/262 833/843 Special detailed inspection (HFEC) of AFT passenger/crew door 

cutouts, upper corners including skin and fail safe ring.

T: 26500FC

 75000FH

I: 6000FC

 17000FH

531808 -300 

531809-01-3A 171/172

261/262

Scuff plate removal

Special detailed inspection (US+ HFEC + VISUAL) of fail safe ring and skin of AFT passenger/crew door cutouts at lower corners, underneath the scuff plates.

T: 30000FC

 60000FH

I: 12000FC

 24000FH

531809 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531809-01-4A 171/172

261/262

Scuff plate removal

Special detailed inspection (US+ HFEC + VISUAL) of fail safe ring and skin of AFT passenger/crew door cutouts at lower corners, underneath the scuff plates.

T: 24000FC

 67500FH

I: 6300FC

 17500FH

531809 -300 

531810-01-1A 261/262 Linings, 

insulation833/843

Detailed inspection of internal structure around AFT passenger/crew door cutouts above main deck floor level, from FR 72 to FR 77 and from STR 9 to STR 26 LH/RH.

T: 25000FC

I: 10000FC

ALL

531813-01-1A 261/262 833/843 General visual inspection of door stop fittings on FR 73A and FR 

75A, LH/RH.

T: 18000FC

I: 12000FC

ALL 

531820-01-1A 100 N/A General visual inspection of lower skin external surface of 

longitudinal lap joints in following crack stopper areas:- at STR 29, LH/RH, from FR 72 to FR 76- at STRs 35 and 51, LH/RH, from FR 72 to FR 80/82.

T: 32000FC

I: 2250FC

ALL

531902-01-2A 261/262

263/264

Galleys/lavatories,lining, Insulation displaced as required

Detailed inspection of rear pressure bulkhead FWD face above main deck floor level including FR 80/82, rim angle attachments and attachments to skin.

T: 30000FC

I: 14800FC

ALL

531904 01 2A 531904-01-2A 311/312 311/312 312 AR Detailed inspection of rear pressure bulkhead AFT face including 312 AR D t il d i ti f b lkh d AFT f i l di T 18000FC ALL

attachment to skin from STR 26 LH/RH to crown center line.

T: 18000FC

I: 14800FC

ALL

531906-01-1A 311/312 312 AR Detailed inspection of rear pressure bulkhead web AFT face in outer 

circumferential splice area, at inner rivet row.

T: 18000FC

I: 9500FC

ALL

531910-01-1A 323 323 AL, BL

323 AR, BR

Detailed inspection of fuselage skin, external surface in area of fin to fuselage FWD, MID and AFT attach fitting fasteners and visible part of the fittings.

T: 40000FC

 80000FH

I: 12300FC

 24500FH

-200

531910-01-2A 323 323 AL, BL

323 AR, BR

Detailed inspection of fuselage skin, external surface in area of fin to fuselage FWD, MID and AFT attach fitting fasteners and visible part of the fittings.

T: 35000FC

 98000FH

I: 8100FC

 22500FH

-300 

531913-01-1A 311/312 313 AL Special detailed inspection (US) of horizontal stabilizer hinge support 

members and upper and lower attachment lugs of FR 91 LH/RH.

T: 18000FC

 36000FH

I: 15000FC

 30000FH

531913 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

531913-01-2A 311/312 313 AL Special detailed inspection (US) of horizontal stabilizer hinge support 

members and upper and lower attachment lugs of FR 91 LH/RH.

T: 14400FC

 40500FH

I: 12000FC

 33500FH

531913 -300 

R 531919-01-1A 300 323 AL, AR Special detailed inspection (LFEC) of rear pressure bulkhead rim 

angle in the area of frame profile radius.

T: 24000FC

I: 9000FC

531919 POST

5526

531921-01-1A 311/312 312 AR Special detailed inspection (LHEC) of rear pressure bulkhead AFT 

face around cutouts for APU fuel line (and trim tank line from MSN 378 and on).

T: 24000FC

I: 6000FC

531921 ALL

531922-01-1A 311/312 312 AR Detailed inspection of rear pressure bulkhead web AFT face around 

cutouts, except cutout for bleed air duct, APU fuel line (and trim tank line from MSN 378 and on).

T: 24000FC

I: 6000FC

ALL

531924-01-1A 300 N/A Special detailed inspection (LFEC) of fuselage skin at circumferential 

splice at FR 86 from STR 22 to STR 27 LH/RH.

T: 28000FC

 56000FH

I: 12000FC

 24000FH

531924 -200

531924-01-2A 300 N/A Special detailed inspection (LFEC) of fuselage skin at circumferential 

splice at FR 86 from STR 22 to STR 27 LH/RH.

T: 22400FC

 63000FH

I: 9600FC

 27000FH

531924 -300 

531926-01-4A 311/312 313 AL Special detailed inspection (HFEC) of horizontal stabilizer cutout, 

lower longeron, corner fitting, skin strap and skin, LH/RH.

T: 30000FC

 60000FH

I: 3900FC

 7800FH

531926 -200

POST6146

531926-01-5A 311/312 313 AL Special detailed inspection (HFEC) of horizontal stabilizer cutout, 

lower longeron, corner fitting, skin strap and skin, LH/RH.

T: 24000FC

 67500FH

I: 3100FC

 8700FH

531926 -300

POST6146

531927-01-1A 171

311

813162 AZ, 312 AR,Insulation displaced as required, bleed air duct

Special detailed inspection (HFEC + Rotating probe) of rear pressure bulkhead web FWD and AFT faces around cutout for bleed air duct.

T: 24000FC

I: 6000FC

531927 ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

545002-P1-1A 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 40000FC

80000FH

I: 8100FC

16200FH

545002 -200 PW

545002-G1-1A 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 40000FC

80000FH

I: 6800FC

13600FH

545002 -200 G

80A3

545002-G1-3A 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 40000FC

80000FH

I: 5900FC

11800FH

545002 -200 G

80C2

545002-P1-3A 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 35000FC

97900FH

I: 10500FC

29500FH

545002 -300 PW 

545002-P1-5A 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 35000FC

97900FH

I: 9100FC

25500FH

545002 -300 PW 

545002 G1 5A 545002-G1-5A 415/416 415/416 451/461 AL S i l d t il d i ti (Ult i ) f l id tt h t T 35000FC 545002 300 G

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 35000FC

98000FH

I: 3100FC

8800FH

545002 -300 G

545003-P1-1A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 4600FC

9200FH

I: 4600FC

9200FH

-200 PW

545003-G1-1A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 2600FC

5200FH

I: 2600FC

5200FH

-200 G80A3

545003-G1-2A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 2200FC

4500FH

I: 2200FC

4500FH

-200 G80C2 P

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

545003-G1-3A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 3000FC

6000FH

I: 3000FC

6000FH

-200 G80C2 P

545003-P1-2A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 9800FC

27500FH

I: 9800FC

27500FH

-300 PW 

545003-P1-4A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 8400FC

23800FH

I: 8400FC

23800FH

-300 PW PRE 60

545003-P1-5A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 11300FC

31600FH

I: 11300FC

31600FH

-300 PW POST 

545003-G1-4A 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 2000FC

5600FH

I: 2000FC

5600FH

-300 G6080

545003 G1 5A 545003-G1-5A 415/416 415/416 451/461 AL D t il d i ti f l t i FWD tt h fitti ( id) T 2700FC 300 G

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 2700FC

7500FH

I: 2700FC

7500FH

-300 G6080

545008-G1-1A 453/454 

463/464

Engine removed, engine AFT mount upper beam removed

Special detailed inspection (Liquid Penetrant) of pylon-to engine AFT attachment beam assembly, including mating face with engine AFT mount.

T: 20000FC

I: 20000FC

GE CMM 

71.20.05

GE CF

545008-G1-2A 453/454 

463/464

Engine removed, engine AFT mount upper beam removed 

Special detailed inspection (Liquid Penetrant) of pylon-to engine AFT attachment beam assembly, including mating face with engine AFT mount.

T: 10000FC

I: 10000FC

GE CMM 

71.20.05

GE CF

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

545028-01-2A 435/436

445/446451/452461/462

435/445 AL451/461 AL436/446 AR452/462 AR

Detailed inspection of engine cowl hinge fittings, LH/RH (including bolts and nacelle hinge side).

T: 700FC

1450FH

I: 700FC

1450FH

-200

545028-01-3A 435/436

445/446451/452461/462

435/445 AL451/461 AL436/446 AR452/462 AR

Detailed inspection of engine cowl hinge fittings, LH/RH (including bolts and nacelle hinge side).

T: 700FC

1950FH

I: 700FC

1950FH

-300 

545030-01-2A 473/474 

483/484

473/483 AL, 474/484 AR

Detailed inspection of pylon lateral panels at the edge of access door cutouts between ribs 13 and 14, LH/RH.

T: 10400FC

20800FH

I: 10400FC

20800FH

-200

545030-01-3A 473/474 

483/484

473/483 AL, 474/484 AR

Detailed inspection of pylon lateral panels at the edge of access door cutouts between ribs 13 and 14, LH/RH.

T: 10400FC

29100FH

I: 10400FC

29100FH

-300 

545043-G1-3A 415/416

425/426

N/A Detailed inspection of pylon side panels at rib 8, LH/RH T: 28300FC

79400FH

I: 10000FC

28000FH

-300 G10432

545043-P1-3A 415/416

425/426

N/A Detailed inspection of pylon side panels at rib 8, LH/RH T: 23600FC

59100FH

-300 PW 10432

425/426

I: 9300FC

23200FH

10432

551015-01-2A 333/343 333/343 AB, 

AT334/344 AB, ATTHS Bell Crank and Push RodAutopilot Pitch Actuator (LH only)

Special detailed inspection (HFEC) of horizontal stabilizer rear sparjoining part outboard of rib 3 upper end, LH/RH.Note: For A/C POST 4933 the threshold is due at 19500FC afterembodiment of SB A310-55-2002 (mandatory by CN 1992-106-132(B)). Modification 4933 is embodied prior to delivery on A/C MSN172, 311 and subsequents until 400 included.

T: 19500FC

 38400FH

I: 8200FC

 16500FH 

551015 -200

551018-01-2A 319

333/343

312 AR313 AL331/341 BB

Detailed inspection of horizontal stablizer spar box internal structure in area of hinge fitting attachments, both sides of rib 3 and top skin rear spar upper cap between rib 2 and rib 3, LH/RH

T: 33000FC

 66000FH

I: 5100FC

 10300FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

551020-01-1A 333/343 333/343 AT Detailed inspection of horizontal stabilizer outer box top skin upper

surface chordwise splice between rib 3 and rib 4 from rear spar toSTR 9, LH/RH.Note: This task has to be done at the same time as task 551020-02-1A.

T: 14700FC

 29400FH

I: 6200FC

 12500FH

-200POST 

551020-01-3A 333/343 333/343 AT

rearmost apron fitting

Detailed of horizontal stabilizer outer box top skin upper surfacechordwise splice between rib 3 and rib 4 from rear spar to STR 9,LH/RH.Note: This task has to be done at the same time as task 551020-02-3A.

T: 27400FC

 76700FH

I: 6300FC

 17600FH

-300 

551020-02-1A 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre box

top skin upper surface chordwise splice between rib 3 and rib 4 fromrear spar to STR 9, LH/RH.Note: This task has to be done at the same time as task 551020-01-1A.

T: 14700FC

 29400FH

I: 6200FC

 12500FH

551020 -200

POST 

551020-02-3A 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre box

top skin upper surface chordwise splice between rib 3 and rib 4 fromrear spar to STR 9, LH/RH.

N t Thi t k h t b d t th ti t k 551020 01

T: 27400FC

 76700FH

I: 6300FC

 17600FH

551020 -300 

Note: This task has to be done at the same time as task 551020-01-

3A.

551021-01-1A 333/343 333/343 AT Detailed inspection of horizontal stabilizer outer box top skin upper 

surface chordwise splice between rib 3 and rib 4 from rear spar to STR 9, excluding the attachment to the reinforcement plate, LH/RH.Note: This task has to be done at the same time as task 551021-02-1A.

T: 34200FC

 68400FH

I: 6200FC

 12500FH

-200PRE 60

551021-02-1A 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre box 

top skin upper surface chordwise splice between rib 3 and rib 4 from rear spar to STR 9, excluding the attachment to the reinforcement plate, LH/RH.Note: This task has to be done at the same time as task 551021-01-1A.

T: 34200FC

 68400FH

I: 6200FC

 12500FH

551021 -200

PRE 60

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

551022-01-2A 333/343 333/343 AT Detailed inspection of horizontal stabilizer outer box top skin upper 

surface chordwise splice between rib 3 and rib 4 from STR 9 to front spar, LH/RH.Note: This task has to be done at the same time as task 551022-02-2A.

T: 38300FC

 76600FH

I: 4800FC

 9600FH

-200 

551022-02-2A 333/343 333/343 AT Special detailed inspection (Ultrasonic) of horizontal stabilizer centre 

box top skin upper surface chordwise splice between rib 3 and rib 4 from STR 9 to front spar, LH/RH.Note: This task has to be done at the same time as task 551022-01-2A.

T: 38300FC

 76600FH

I: 4800FC

 9600FH

551022 -200 

551025-01-1A 311/312 313 AL Detailed inspection of horizontal stabilizer rear spar joining part

inboard side at rib 3, LHRH.

T: 33000FC

 66000FH

I: 5100FC

 10300FH

-200

551026-01-1A 331/341 331/341 AB, 

BB, CB

Detailed inspetion of horizontal stabilizer front spar web atattachment of upper T profile from rib 3 to rib 12, LH/RH.

T: 32500FC

 65000FH

I: 14400FC

 28900FH

-200

551027-01-1A 334/344 334/344 BB, 

CB

Detailed inspetion of horizontal stabilizer rear spar web at

tt h t f T fil f ib 3 t ib 9 LH/RH

T: N/A

99400FH

-200

CB attachment of upper T profile from rib 3 to rib 9, LH/RH. 99400FH

I: 3600FC

 7200FH

551028-01-1A 300 N/A Detailed inspection of horizontal stabilizer top skin from fuselage

fairing to rib 5, LH/RH.

T: 32000FC

 64100FH

I: 4100FC

 8200FH

-200 

551029-01-1A 300 N/A Detailed inspection of horizontal stabilizer top skin at attachment to

the front spar T profile from rib 3 to rib 12, LH/RH.

T: 32500FC

 65000FH

I: 7300FC

 14600FH

-200

551030-01-1A 300 N/A Detailed inspection of horizontal stabilizer top skin at attachment to

the rear spar T profile from rib 3 to rib 9, LH/RH.

T: N/A

 99400FH

I: 7300FC

 14600FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

551075-01-1A 311/312 313 AL Detailed inspection of horizontal stabilizer rear spar joining part

inboard side at rib 3, LHRH.

T: 28300FC

 79200FH

I: 6900FC

 19400FH

-300 

553002-01-1A 300 N/A General visual inspection of vertical stabilizer skin panels LH/RH, 

from front to rear spar and from fin/fuselage fairing to tip, external surface.

T: 18000FC

 36000FH

I: 13600FC

 27000FH

-200PRE 48

553003-01-1A 323 311 AZ, BZ

312 AR323 AL, AR, BL, BR

Detailed inspection of FWD, center and AFT vertical stabilizer to fuselage attach and side load fittings.

T: 40000FC

 80000FH

I: 6000FC

 12000FH

-200PRE 48

553011-01-1A 323 311 AZ, BZ

312 AR

General visual inspection of vertical stabilizer center box internal structure from rib 1 to 12.

T: 30000FC

 60000FH

I: 9900FC

 19500FH

-200PRE 48

553017-01-1A 323 N/A Detailed inspection of vertical stabilizer skin panels LH/RH from front 

to rear spar and from fin/fuselage fairing to tip rib 12, external surface.

T: 40000FC

 80000FH

I: 6000FC

 12000FH

-200PRE 48

R 553019-01-1 553019 01 1A 323 N/A D t il d i ti f ti l t bili ki t j i t ib 16 t l Detailed inspection of vertical stabilizer skin at joint rib 16, external T 40000FC 200

surface.

T: 40000FC

80000FH

I: 8900FC

17500FH

-200PRE 48

571002-01-1A 141/142 734, 744

147/148AZSealant Removal

Detailed inspection of center wing box front spar upper cap from Rib 1 LH to Rib 1 RH, inside fuel tank, excluding angle fittings

T: 36800FC

I: 10700FC

-200PRE 49

571006-01-1A 141/142 N/A Special detailed inspection (Ultrasonic) of lower panel at wing to 

fuselage lower attachment, inboard side, between FR42.1 and FR44, LH/RH.

T: 35900FC

 71900FH

I: 4100FC

 8200FH

571006 -200

571008-01-1A 540/640 540/640 AB Special detailed inspection (X-RAY) of outboard horizontal flange of 

lower T section, inboard row of fasteners from front spar to rear spar, LH/RH.

T: 40650FC

 81300FH

I: 9950FC

 19900FH

571008 -200 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571008-01-2A 540/640 540/640 AB Special detailed inspection (X-RAY) of outboard horizontal flange of 

lower T section, inboard row of fasteners from front spar to rear spar, LH/RH.

T: 32500FC

 91150FH

I: 7950FC

 22250FH

571008 -300 

571009-01-1A 141/142 734/744

147/148 AZ

Detailed inspection of center wing box rear spar around access door cutouts.

T: 15400FC

 30800FH

I: 8600FC 

 17200FH

-200

571009-01-2A 141/142 734/744

147/148 AZ

Detailed inspection of center wing box rear spar around access door cutouts.

T: 14200FC

 39800FH

I: 11200FC 

 31500FH

-300 

571013-01-2A 241/242 Sidewall 

panels,Insulation displaced as required,241 LW, MW,242 LW, MW

Special detailed inspection (Ultrasonic) of FR 47/48, FWD and AFT faces from STRs 22 to 24, LH/RH.

T: 28000FC

 56000FH

I: 4700FC

 9500FH

571013 -200

571013-01-4A 241/242 Sidewall 

panels,

I l ti

Special detailed inspection (Ultrasonic) of FR 47/48, FWD and AFT faces from STRs 22 to 24, LH/RH.

T: 27100FC

 75800FH

I 4600FC

571013 -300 

Insulation displaced as required,241 LW, MW,242 LW, MW

I: 4600FC

 13100FH

571022-01-1A 541/542

641/642

540/640ABSealant Removal

Special detailed inspection (Ultrasonic) of stiffener at wing to fuselage lower attachment, outboard side between FR43 and FR45, at stiffeners 7, 8 and 9, LH/RH.

T: 17100FC

 34200FH

I: 2900FC

 5900FH

571022 -200

571022-01-3A 541/542

641/642

540/640ABSealant Removal

Special detailed inspection (Ultrasonic) of stiffener at wing to fuselage lower attachment, outboard side between FR43 and FR45, at stiffeners 7, 8 and 9, LH/RH.

T: 15900FC

 44400FH

I: 2200FC

 6200FH

571022 -300 

571023-01-1A 141

142

734/744147/148AZ, bolts

Special detailed inspection (Rotating Probe) of center wing box lower skin at pump holes reinforcing plates upper side, from FR 46 to 47 and from beams 3 to 5, LH/RH .

T: 30500FC

 61100FH

I: 15000FC

 30000FH

571023 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571023-01-2A 141

142

734/744147/148AZ, bolts

Special detailed inspection (Rotating Probe) of center wing box lower skin at pump holes reinforcing plates upper side, from FR 46 to 47 and from beams 3 to 5, LH/RH.

T: 31300FC

 87500FH

I: 13300FC

 37100FH

571023 -300 

571024-01-3A 141/142 734/744,

147/ 148 AZ, Sealant removal

Special detailed inspection (Ultrasonic) of center wing box front spar lower cap corner fitting and adjacent front spar structure, LH/RH.

T: 21500FC

 43100FH

I: 15800FC

 31600FH

571024 -200

571024-01-4A 141/142 734/744,

147/ 148 AZ, Sealant removal

Special detailed inspection (Ultrasonic) of center wing box front spar lower cap corner fitting and adjacent front spar structure, LH/RH.

T: 20100FC

 56300FH

I: 12300FC

 34400FH

571024 -300 

571026-01-1A 141/142 Main deck floor 

panels, galleys and toilets (if installed)Sealant Removal

Special detailed inspection (Ultrasonic) of inboard side of cruciform fitting at junction with stiffeners between FR40-1 and FR44-2, LH/RH

T: 39950FC

 79900FH

I: 5550FC

 11050FH

571026 -200

571026-01-2A 141/142 Main deck floor 

panels, galleys 

d t il t (if

Special detailed inspection (Ultrasonic) of inboard side of cruciform fitting at junction with stiffeners between FR40-1 and FR44-2, LH/RH

T: 24200FC

 67800FH

I 3750FC

571026 -300 

and toilets (if installed)Sealant Removal

I: 3750FC

 10550FH

571028-01-1A 141/142 Main deck floor 

panels, galleys and toilets (if installed)Sealant Removal

Special detailed inspection (Ultrasonic) of center wing box upper panel between stiffeners 43.2 and 44.1 at cruciform fitting junction, LH/RH

T: 40000FC

 80000FH

I: 11200FC

 22500FH

571028 -200

571028-01-2A 141/142 Main deck floor 

panels, galleys and toilets (if installed)Sealant Removal

Special detailed inspection (Ultrasonic) of center wing box upper panel between stiffeners 43.2 and 44.1 at cruciform fitting junction, LH/RH

T: 22400FC

 62900FH

I: 7000FC

 19700FH

571028 -300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571040-01-1A 540/640 577/677AT

577/677BTSealant Removal

Special detailed inspection (HFEC) of cruciform at upper wing skin to fuselage joint from FR 40/41 to 47/48, upper outboard radius, LH/RH 

T: 23100FC

 46200FH

I: 12500FC

 25000FH

571040 -200

571040-01-3A 540/640 577/677AT

577/677BTSealant Removal

Special detailed inspection (HFEC) of cruciform at upper wing skin to fuselage joint from FR 40/41 to 47/48, upper outboard radius, LH/RH 

T: 21900FC

 61400FH

I: 12100FC

 33900FH

571040 -300 

R 571041-01-2A 540/640 577/677 AT

577/677 BT

Detailed inspection of cruciform at upper wing skin to fuselage joint from FR 40/41 to FR 47/48, outboard flange upper surface, LH/RH.

T: 23000FC

 46000FH

I: 4000FC

 8000FH

-200

R 571041-01-3A 540/640 577/677 AT

577/677 BT

Detailed inspection of cruciform at upper wing skin to fuselage joint from FR 40/41 to FR 47/48, outboard flange upper surface, LH/RH.

T: 22100FC

 62000FH

I: 4300FC

 12000FH

-300 

571042-01-2A 540/640 540/640AB

Sealant Removal

Detailed inspection of outer wing upper skin stringer end fittings and adjacent part of stringers at Rib 1, from front to rear spar, LH/RH. Note: This task is an alternative to 571042-02-1A 

T: 32150FC

 100800FH

I: 7250FC

 14500FH

-200 

571042-01-3A 540/640 540/640AB

Sealant Removal

Detailed inspection of outer wing upper skin stringer end fittings and adjacent part of stringers at rib 1, from front to rear spar, LH/RH. Note: This task is an alternative to 571042-02-2A 

T: 32300FC

 90650FH

I: 7150FC

 20000FH

-300 

571042-02-1A 540/640 540/640AB

Sealant Removal

Special detailed inspection (Ultrasonic) of outer wing upper skin stringer end fittings and adjacent part of stringers at Rib 1, from front to rear spar, LH/RH. Note: This task is an alternative to 571042-01-2A 

T: 32150FC

 100800FH

I: 11650FC

 23300FH

571042 -200 

571042-02-2A 540/640 540/640AB

Sealant Removal

Special detailed inspection (Ultrasonic) of outer wing upper skin stringer end fittings and adjacent part of stringers at rib 1, from front to rear spar, LH/RH. Note: This task is an alternative to 571042-01-3A 

T: 32300FC

 90650FH

I: 11500FC

 32200FH

571042 -300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571043-01-1A 540/640 540/640AB Special detailed inspection (Ultrasonic) of outer wing rear spar to rib 

1 junction, vertical tee splice fitting outboard flange, LH/RH

T: 32900FC

 65800FH

I: 8900FC

 17800FH

571043 -200

571043-01-3A 540/640 540/640AB Special detailed inspection (Ultrasonic) of outer wing rear spar to rib 

1 junction, vertical tee splice fitting outboard flange, LH/RH

T: 32300FC

 90600FH

I: 8800FC

 24600FH

571043 -300 

571045-01-2A 143/144 147BZ

734/744vapour seal displaced

Detailed inspection of center wing box bottom skin lower surface in air conditioning bay.

T: 20400FC

 40900FH

I: 11200FC

 22500FH

-200

571045-01-3A 143/144 147BZ

734/744vapour seal displaced

Detailed inspection of center wing box bottom skin lower surface in air conditioning bay.

T: 19800FC

 55700FH

I: 10800FC

 30200FH

-300 

571047-01-1A 143/144 147BZ

734/744vapour seal displacedSealant 

Removal

Special detailed inspection (Ultrasonic and Rototest) of center wing box bottom skin lower surface in beam attachment areas from front to rear spars and from Rib 1 LH to Rib 1 RH. 

T: 20400FC

 40900FH

I: 17300FC

 34500FH

571047 -200

PRE 50

Removal

571047-01-2A 143/144 147BZ

734/744vapour seal displacedSealant Removal

Special detailed inspection (Ultrasonic and Rototest) of center wing box bottom skin lower surface in beam attachment areas from front to rear spars and from Rib 1 LH to Rib 1 RH. 

T: 25800FC

 51700FH

I: 20500FC

 41100FH

571047 -200

POST 

571047-01-3A 143/144 147BZ

734/744vapour seal displacedSealant Removal

Special detailed inspection (Ultrasonic and Rototest) of center wing box bottom skin lower surface in beam attachment areas from front to rear spars and from Rib 1 LH to Rib 1 RH. 

T: 19800FC

 55700FH

I: 15800FC

 44300FH

571047 -300 

571051-01-1A 141

142

734/744147/148 AZ, boltsSealant Removal

Special detailed inspection (Rotating Probe) of center wing box rear spar to Rib 1 junction vertical T splice fitting and angle fitting, LH/RH

T: 31900FC

 63850FH

I: 7800FC

 15650FH

571051 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571051-01-2A 141

142

734/744147/148 AZ, boltsSealant Removal

Special detailed inspection (Rotating Probe) of center wing box rear spar to Rib 1 junction vertical T splice fitting and angle fitting, LH/RH

T: 26600FC

 74500FH

I: 8800FC

 24650FH

571051 -300 

571052-01-1A 540

640

540AB640AB, boltsSealant Removal

Special detailed inspection (Rotating Probe) of outer wing rear spar to Rib 1 junction angle fitting, LH/RH

T: 43850FC

 87700FH

I: 11200FC

 22400FH

571052 -200

571052-01-2A 540

640

540AB640AB, boltsSealant Removal

Special detailed inspection (Rotating Probe) of outer wing rear spar to Rib 1 junction angle fitting, LH/RH

T: 35750FC

 100250FH

I: 12250FC

 34450FH

571052 -300 

571053-01-1A 540

640

540AB640ABSealant Removal

Detailed inspection of outer wing upper skin fittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-02-1A

T: 32500FC

 65050FH

I: 3950FC

 7950FH

-200

571053-01-2A 540

640

540AB640ABSealant Removal

Detailed inspection of outer wing upper skin fittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-02-2A

T: 32250FC

 90450FH

I: 3800FC

 10600FH

-300 

571053 02 1A 571053-02-1A 540 540AB S i l d t il d i ti (R t ti P b ) f t i ki T 32500FC 571053 200

640

540AB640AB, boltsSealant Removal

Special detailed inspection (Rotating Probe) of outer wing upper skin fittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-01-1A

T: 32500FC

 65050FH

I: 23600FC

 47200FH

571053 -200

571053-02-2A 540

640

540AB640AB, boltsSealant Removal

Special detailed inspection (Rotating Probe) of outer wing upper skin fittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-01-2A

T: 32250FC

 90450FH

I: 22450FC

 62950FH

571053 -300 

571054-01-1A 145/146 Main deck floor 

panels, bolts removal

Special detailed inspection (Rotating Probe) of upper cruciform fitting junction with fuselage panel at FR43A, LH/RH

T: 26000FC

 52100FH

I: 7200FC

 14400FH

571054 -200

571054-01-2A 145/146 Main deck floor 

panels, bolts removal

Special detailed inspection (Rotating Probe) of upper cruciform fitting junction with fuselage panel at FR43A, LH/RH

T: 39300FC

 N/A FH

I: 9500FC

 26700FH

571054 -300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571056-01-1A 540/640 540/640AB Special detailed inspection (Ultrasonic) of wing upper surface panel 

between stiffener 5 and 6 at cruciform fitting end, LH/RH

T: N/A FC

100000FH

I: 1650FC

 3350FH

571056 -200

571056-01-2A 540/640 540/640AB Special detailed inspection (Ultrasonic) of wing upper surface panel 

between stiffener 2 and 7 at cruciform fitting end, LH/RH

T: 37550FC

N/A FH

I: 1500FC

 4250FH

571056 -300 

571061-01-1A 540/640 540/640 AB

Sealant Removal

Special detailed inspection (Ultrasonic) of outboard horizontal flange of lower T section, inboard row of fasteners at stiffener 7 and stiffener 9, LH/RHNote : Grace period of 1100FC.

T: 23350FC

 46650FH

I: 7700FC

 15400FH

571061 -200

571061-01-2A 540/640 540/640 AB

Sealant Removal

Special detailed inspection (Ultrasonic) of outboard horizontal flange of lower T section, inboard row of fasteners at stiffener 7 and stiffener 9, LH/RHNote : Grace period of 1100FC.

T: 20250FC

 56750FH

I: 6150FC

 17250FH

571061 -300 

571062-01-1A 540/640 N/A Special detailed inspection (Ultrasonic) of lower splice between 

FR40/41 and FR47/48 at the first row of fasteners from Rib 1 datum (wing side), LH/RH.

T: 29000FC

 58050FH

I: 4600FC

9200FH

571062 -200

Note : Grace period of 1100FC.

 9200FH

571062-01-2A 540/640 N/A Special detailed inspection (Ultrasonic) of lower splice between 

FR40/41 and FR47/48 at the first row of fasteners from Rib 1 datum (wing side), LH/RH.Note : Grace period of 1100FC.

T: 21850FC

 61300FH

I: 3450FC

 9700FH

571062 -300 

571067-01-1A 141/142 N/A Special detailed inspection (Ultrasonic) of center wing box lower 

splice at Rib 1, first fasteners row from Rib 1 datum between stiffener 42.2 and 44.1, LH/RH

T: 27600FC

 55200FH

I: 10650FC

 21300FH

571067 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

571067-01-2A 141/142 N/A Special detailed inspection (Ultrasonic) of center wing box lower 

splice at Rib 1, first fasteners row from Rib 1 datum between stiffener 42.2 and 44.1, LH/RH

T: 29750FC

 83500FH

I: 7950FC

 22350FH

571067 -300 

571068-01-1A 141/142 N/A Special detailed inspection (Ultrasonic) of center wing box lower 

splice at Rib 1, first fasteners row from Rib 1 datum between stiffener 44.2 and 46.2, LH/RH

T: 40400FC

 80850FH

I: 11700FC

 23400FH

571068 -200

571068-01-2A 141/142 N/A Special detailed inspection (Ultrasonic) of center wing box lower 

splice at Rib 1, first fasteners row from Rib 1 datum between stiffener 44.2 and 46.2, LH/RH

T: 34600FC

 97100FH

I: 8700FC

 24350FH

571068 -300 

571069-01-1A 141/142 734/744

147/148AZbolts to be removedSealant Removal

Special detailed inspection (Rotating Probe) of center wing box bottom skin stiffener at FR44 level, LH/RH.

T: 42650FC

 85300FH

I: 4000FC

 8000FH

571069 -200

571069-01-2A 141/142 734/744

147/148AZbolts to be removedSealant Removal

Special detailed inspection (Rotating Probe) of center wing box bottom skin stiffener at FR44 level, LH/RH.

T: 38250FC

 107350FH

I: 3400FC

 9600FH

571069 -300

PRE 81

572006-01-2A 532/632

533/633534/634535/635

532/533/534/535/632/633/634/635AB, BB, CB

Detailed inspection of flap track beams No. 2, 3, 4 and 5 lower flange titanium and steel straps.

T: 30000FC

I: 11400FC

ALL

572008-01-2A 534/634 534/634 AB, 

BB

Detailed inspection of flap track beam No. 4 FWD attachment fork bracket lugs.

T: 30000FC

I: 9600FC

ALL

572011-01-2A 577/677 Flaps extended Detailed inspection of flap track beam No. 1 to fuselage attachment

members including track attachments and roller support assembly.

T: 30000FC

I: 11200FC

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572016-01-2A 532/533/

534/535632/633/634/635

532/533/534/ 535/632/633/ 634/635AB, BB

Detailed inspection of flap track beams No. 2, 3, 4 and 5 frontattachment shear bolts.

T: 30000FC

I: 9400FC

R 572104-01-3A 512/612 512/612 CB, 

EB, HB

Detailed inspection of outer wing front spar FWD face from ribs 1 to7 at slat track cutouts (3 places).

T: 17600FC

35300FH

I: 2400FC

4800FH

-200

R 572104-01-4A 512/612 512/612 CB, 

EB, HB

Detailed inspection of outer wing front spar FWD face from ribs 1 to7 at slat track cutouts (3 places).

T: 17500FC

49100FH

I: 2300FC

6600FH

-300 

572105-01-3A 523/623 523/623 BB, 

CB

Detailed inspection of outer wing front spar forward face splice plate at rib 10. 

T: 37800FC

 75700FH

I: 8600FC

 17300FH

-200

572105-01-4A 523/623 523/623 BB, 

CB

Detailed inspection of outer wing front spar forward face splice plate at rib 10. 

T: 36200FC

 101100FH

I: 8200FC

 23100FH

-300 

572107-01-1A 540/640 540/640 AB, 

BB

Detailed inspection of outer wing front spar AFT face from ribs 1 to7

T: 13200FC

26400FH

-200

BB 7.

Note : This task is an alternative to 572107-02-1A

I: 6400FC

12900FH

R 572107-01-2A 540/640 540/640 AB, 

BB

Detailed inspection of outer wing front spar AFT face from ribs 1 to7.Note : This task is an alternative to 572107-02-2A

T: 13200FC

37100FH

I: 9600FC

26900FH

-300 

572107-02-1A 540/640 N/A Special detailed inspection (Ultrasonic) of outer wing front spar AFT

face from ribs 1 to 7.Note : This task is an alternative to 572107-01-1A

T: 13200FC

26400FH

I: 9900FC

19800FH

572107 -200

N 572107-02-2A 540/640 N/A Special detailed inspection (Ultrasonic) of outer wing front spar AFT

face from ribs 1 to 7.Note : This task is an alternative to 572107-01-2A

T: 13200FC

37100FH

I: 9900FC

27800FH

572107 -300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572108-01-3A 540/640 540/640 CB, 

DB

Detailed inspection of outer wing front spar AFT face from ribs 7 to9.

T: 24300FC

48700FH

I: 6000FC

12100FH

-200

572108-01-4A 540/640 540/640 CB, 

DB

Detailed inspection of outer wing front spar AFT face from ribs 7 to9.

T: 24000FC

67100FH

I: 8900FC

24900FH

-300 

572109-01-1A 540/640

550/650

540/640 EB, FB, GB, HB550/650 AB, BB, CB

Detailed inspection of outer wing front spar AFT face from ribs 9 to17.

T: 15000FC

30100FH

I: 3850FC

7700FH

-200 P

572109-01-2A 540/640

550/650

540/640 EB, FB, GB, HB550/650 AB, BB, CB

Detailed inspection of outer wing front spar AFT face from ribs 9 to17.

T: 15000FC

30100FH

I: 7900FC

15900FH

-200 PO

572109-01-3A 540/640

550/650

540/640 EB, FB, GB, HB550/650 AB, BB, CB

Detailed inspection of outer wing front spar AFT face from ribs 9 to17.

T: 13500FC

37800FH

I: 7100FC

20000FH

-300 P(SB 00

572109 01 4A 572109-01-4A 540/640 540/640 540/640 EB D t il d i ti f t i f t AFT f f ib 9 t T 13500FC 300 PO

550/650

540/640 EB, FB, GB, HB550/650 AB, BB, CB

Detailed inspection of outer wing front spar AFT face from ribs 9 to17.

T: 13500FC

37800FH

I: 6000FC

17000FH

-300 PO(SB 00

572111-01-4A 571/671 N/A Detailed inspection of outer wing rear spar AFT face and attachment

angle from rib 1 to 3.

T: 36200FC

72400FH

I: 2700FC

5400FH

-200

572111-01-5A 571/671 N/A Detailed inspection of outer wing rear spar AFT face and attachment

angle from rib 1 to 3.

T: 36100FC

101200FH

I: 2700FC

7600FH

-300 

572115-01-3A 575/675 575/675 DB Detailed inspection of outer wing rear spar aft face splice plate at rib 

10. 

T: 31200FC

 62500FH

I: 6900FC

 13900FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572115-01-4A 575/675 575/675 DB Detailed inspection of outer wing rear spar aft face splice plate at rib 

10. 

T: 31600FC

 88600FH

I: 7000FC

 19800FH

-300 

572116-01-1A 571/671

540/640

540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar at

selected bolt locations, for attachment of MLG FWD pick up fittingand MLG rib 5 AFT of rear spar, 31 holes, LH/RH.

T: 16100FC

 45100FH

I: 7100FC

 19800FH

572116 -300

POST 

572117-01-5A 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 

to 3. 

T: 24300FC

 48700FH

I: 8500FC

 17000FH

-200

572117-01-6A 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 

to 3. 

T: 24300FC

 48700FH

I: 8100FC

 16300FH

-200C

572117-01-7A 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 

to 3. 

T: 24600FC

 69000FH

I: 8500FC

 24000FH

-300 P(SB 00SB 00-PRE 11(SB 00

572117 01 8A 572117-01-8A 540/640 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 540/640 AB D t il d i ti f t i f d f f ib 1 T 24600FC 300 PO

to 3. 

T: 24600FC

 69000FH

I: 7000FC

 19600FH

-300 PO(SB 00SB 00-or POS(SB 00

572118-01-4A 540/640 540/640 AB, 

BB

Detailed inspection of outer wing rear spar forward face from ribs 3 to 6. 

T: 24400FC

 48900FH

I: 8900FC

 17900FH

-200 

572118-01-5A 540/640 540/640 AB, 

BB

Detailed inspection of outer wing rear spar forward face from ribs 3 to 6. 

T: 24000FC

 67400FH

I: 8800FC

 24700FH

-300 P(SB 00SB 00-PRE 11(SB 00

572118-01-6A 540/640 540/640 AB, 

BB

Detailed inspection of outer wing rear spar forward face from ribs 3 to 6. 

T: 24000FC

 67400FH

I: 7200FC

 20200FH

-300 PO(SB 00SB 00-or POS(SB 00

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572119-01-5A 540/640 540/640 BB, 

CB, DB

Detailed inspection of outer wing rear spar FWD face from ribs 6 to10.

T: 24700FC

49400FH

I: 12500FC

25000FH

-200

572119-01-6A 540/640 540/640 BB, 

CB, DB

Detailed inspection of outer wing rear spar FWD face from ribs 6 to10.

T: 24700FC

49400FH

I: 12000FC

24000FH

-200C

572119-01-7A 540/640 540/640 BB, 

CB, DB

Detailed inspection of outer wing rear spar FWD face from ribs 6 to10.

T: 24600FC

69000FH

I: 12500FC

35000FH

-300 P(SB 00SB 00-PRE 11(SB 00

572119-01-8A 540/640 540/640 BB, 

CB, DB

Detailed inspection of outer wing rear spar FWD face from ribs 6 to10.

T: 24600FC

69000FH

I: 10200FC

28500FH

-300 PO(SB 00SB 00-or POS(SB 00

572120-01-3A 540/640 540/640 EB to 

HB

Detailed inspection of outer wing rear spar FWD face from ribs 10 to14.

T: 23500FC

47000FH

I: 11400FC

22800FH

-200

572120-01-4A 540/640 540/640 EB to 

HB

Detailed inspection of outer wing rear spar FWD face from ribs 10 to14.

T: 23500FC

65800FH

I: 11400FC

31900FH

-300 

572122-01-1A 540/640

571/671

540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar at

selected bolt locations for attachment of MLG FWD pick-up fittingand MLG rib 5 AFT of rear spar, 26 holes, LH/RH.

T: 17700FC

 35500FH

I: 9800FC

 19600FH

572122 -200

572122-01-2A 540/640

571/671

540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar at

selected bolt locations for attachment of MLG FWD pick-up fittingand MLG rib 5 AFT of rear spar, 26 holes, LH/RH.

T: 17300FC

 48500FH

I: 7100FC

 19800FH

572122 -300

PRE 76

572137-01-3A 540/640 540/640 AB, 

BB,CB

Detailed inspection of outer wing bottom skin butt strap at STR 8from ribs 1 to 9.

T: 18000FC

 38300FH

I: 6300FC

 12600FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572137-01-4A 540/640 540/640 AB, 

BB,CB

Detailed inspection of outer wing bottom skin butt strap at STR 8from ribs 1 to 9.

T: 18000FC

 51800FH

I: 6100FC

 17000FH

-300 

572138-01-3A 540/640 540/640 DB to 

HB

Detailed inspection of outer wing bottom skin butt strap at STR 8from ribs 9 to 14.

T: 25400FC

 50800FH

I: 6300FC

 12700FH

-200

572138-01-4A 540/640 540/640 DB to 

HB

Detailed inspection of outer wing bottom skin butt strap at STR 8from ribs 9 to 14.

T: 24900FC

 69900FH

I: 6200FC

 17400FH

-300 

572141-02-1A 540/640 540/640 AB to 

HB

Special detailed inspection (HFEC) of outer wing bottom skin aroundmanhole surrounds between ribs 2 and 14, LH and RH wings.

T: 13600FC

 27300FH

I: 10700FC

 21500FH

572141 -200

572141-02-2A 540/640 540/640 AB to 

HB

Special detailed inspection (HFEC) of outer wing bottom skin aroundmanhole surrounds between ribs 2 and 14, LH and RH wings.

T: 13400FC

 37600FH

I: 10600FC

 29600FH

572141 -300 

R 572142-01-3 572142 01 3A 500/600 500/600 540/640 GB S i l d t il d i ti (Ult i ) f t i b tt ki T 27800FC 572142 200

530/630

540/640 GB, HBFlap Track 3 fairing brackets removed.

Special detailed inspection (Ultrasonic) of outer wing bottom skin lower surface at attachment to stringers 9 and 12 adjacent to access door cutouts from ribs 1 to 14.

T: 27800FC

 55600FH

I: 9300FC

 18700FH

572142 -200

R 572142-01-4A 500/600

530/630

540/640 GB, HBFlap Track 3 fairing brackets removed.

Special detailed inspection (Ultrasonic) of outer wing bottom skin lower surface at attachment to stringers 9 and 12 adjacent to access door cutouts from ribs 1 to 14.

T: 26900FC

 75600FH

I: 9100FC

 25500FH

572142 -300 

572143-01-2A 500/600 N/A General visual inspection of outer wing top skin upper surface at

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to14.Note : This task is an alternative to task 572143-02-1A.

T: 16500FC

 33000FH

I: 4350FC

 8700FH

-200 P(SB 00

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572143-01-3A 500/600 N/A General visual inspection of outer wing top skin upper surface at

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to14.Note : This task is an alternative to task 572143-02-2A.

T: 16500FC

 33000FH

I: 3700FC

 7400FH

-200 PO10685(SB 00

572143-01-4A 500/600 N/A General visual inspection of outer wing top skin upper surface at

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to14.Note : This task is an alternative to task 572143-02-3A.

T: 18000FC

 52200FH

I: 4250FC

 11900FH

-300 

572143-02-1A 500/600 N/A Detailed inspection of outer wing top skin upper surface at

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to14.Note : This task is an alternative to task 572143-01-2A.

T: 16500FC

 33000FH

I: 11500FC

 23000FH

-200 P(SB 00

572143-02-2A 500/600 N/A Detailed inspection of outer wing top skin upper surface at

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to14.Note : This task is an alternative to task 572143-01-3A.

T: 16500FC

 33000FH

I: 9900FC

 19800FH

-200 PO10685(SB 00

572143-02-3A 500/600 N/A Detailed inspection of outer wing top skin upper surface at

tt h t t f t f ib 1 t 14 d f ib 7 t

T: 18000FC

52200FH

-300 

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to14.Note : This task is an alternative to task 572143-01-4A.

 52200FH

I: 11200FC

 31300FH

572144-01-1A 500/600 N/A Detailed inspection of outer wing top skin upper surface at

attachment to rear spar from ribs 1 to 7.

T: 16000FC

 32000FH

I: 3800FC

 7600FH

-200 P(SB 00

572144-01-2A 500/600 N/A Detailed inspection of outer wing top skin upper surface at

attachment to rear spar from ribs 1 to 7.

T: 16000FC

 32000FH

I: 3200FC

 6400FH

-200 PO10685(SB 00

572144-01-4A 500/600 N/A Detailed inspection of outer wing top skin upper surface at

attachment to rear spar from ribs 1 to 7.

T: 18300FC

 51200FH

I: 3800FC

 10600FH

-300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572145-01-2A 500/600 N/A General visual inspection of outer wing top skin upper surface at

attachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).

T: 15200FC

 30400FH

I: 5550FC

 11100FH

-200 P(SB 00

572145-01-3A 500/600 N/A General visual inspection of outer wing top skin upper surface at

attachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).

T: 15200FC

 30400FH

I: 4100FC

 8200FH

-200 PO10685(SB 00

572145-01-4A 500/600 N/A General visual inspection of outer wing top skin upper surface at

attachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).

T: 18000FC

 52200FH

I: 5550FC

 15500FH

-300 

572147-01-4A 540/640 540/640 CB, 

DB

Special detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.

T: 36900FC

 73800FH

I: 9400FC

 18900FH

572147 -200 P

(SB 00

572147-01-5A 540/640 540/640 CB, 

DB

Special detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.

T: 36900FC

 73800FH

I: 8200FC

 16400FH

572147 -200 PO

10685(SB 00

572147 01 6A 572147-01-6A 540/640 540/640 540/640 CB, 540/640 CB S il d t il d i ti (X R ) f t i t ki d T 36900FC 572147 300 

DB

Special detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.

T: 36900FC

 103300FH

I: 8500FC

 23900FH

572147 -300 

572151-01-4A 540/640 540/640 AB to 

HB

Detailed inspection of outer wing top skin stringers from ribs 1 to 14. T: 14600FC

 29200FH 

I: 12000FC

 24000FH

-200 P(SB 00

572151-01-5A 540/640 540/640 AB to 

HB

Detailed inspection of outer wing top skin stringers from ribs 1 to 14. T: 14600FC

 29200FH 

I: 11500FC

 23000FH

-200 PO10685(SB 00

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

R 572153-01-1A 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR540/640 CB, DB

Special detailed inspection (X-Ray) of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-02-1A.

T: 15200FC

 30500FH

I: 9700FC

 19400FH

572153 -200

R 572153-01-2A 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR540/640 CB, DB

Special detailed inspection (X-Ray) of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-02-2A.

T: 15000FC

 42000FH

I: 9500FC

 26700FH

572153 -300 P

(SB 00SB 00-PRE 11(SB 00

R 572153-01-3A 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR540/640 CB, 

DB

Special detailed inspection (X-Ray) of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-02-3A.

T: 15000FC

 42000FH

I: 8900FC

 25000FH

572153 -300 PO

(SB 00SB 00-or POS(SB 00

DB

R 572153-02-1A 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR

Detailed inspection of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-01-1A.

T: 15200FC

 30500FH

I: 9700FC

 19400FH

-200 

R 572153-02-2A 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR

Detailed inspection of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-01-2A.

T: 15000FC

 42000FH

I: 9500FC

 26700FH

-300 P(SB 00SB 00-PRE 11(SB 00

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

R 572153-02-3A 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR

Detailed inspection of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-01-3A.

T: 15000FC

 42000FH

I: 8900FC

 25000FH

-300 PO(SB 00SB 00-or POS(SB 00

572157-01-1A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to front spar from ribs 1 to 10 and rear spar from ribs 3 to10 excluding area covered by pylon fairing and MLG reinforcing.

T: 16500FC

 33000FH

I: 3900FC

 7900FH

-200

572157-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to front spar from ribs 1 to 10 and rear spar from ribs 3 to10 excluding area covered by pylon fairing and MLG reinforcing.

T: 16000FC

 44800FH

I: 4300FC

 12200FH

-300 

572159-01-3A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to rear spar from ribs 1 to 3.

T: 32700FC

 65400FH

I: 5300FC

 10700FH

-200

572159-01-4A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to rear spar from ribs 1 to 3.

T: 31300FC

 87600FH

I 5100FC

-300 

I: 5100FC

 14300FH

572161-01-1A 500/600 N/A General visual inspection of outer wing bottom skin lower surface at

attachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.

T: 18000FC

 42000FH

I: 3100FC

 6200FH

-200 

R 572161-01-2A 500/600 N/A General visual inspection of outer wing bottom skin lower surface at

attachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.

T: 23400FC

 65800FH

I: 5000FC

 14000FH

-300 P(SB 00SB 00-PRE 11(SB 00

R 572161-01-3A 500/600 N/A General visual inspection of outer wing bottom skin lower surface at

attachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.

T: 23400FC

 65800FH

I: 4500FC

 12600FH

-300 PO(SB 00SB 00-or POS(SB 00

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572162-01-1A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

spanwise skin joint at STR 8, from ribs 1 to 20, excluding areascovered by pylon and flap track fairings.

T: 14100FC

 28200FH

I: 2400FC

 4800FH

-200

572162-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

spanwise skin joint at STR 8, from ribs 1 to 20, excluding areascovered by pylon and flap track fairings.

T: 13600FC

 38200FH

I: 2300FC

 6500FH

-300 

572163-01-4A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front and rear spars from ribs 10 to 14 excluding area covered by flap track fairing.

T: 18000FC

 41500FH

I: 3000FC

 6100FH

-200 PPRE 47

572163-01-5A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front and rear spars from ribs 10 to 14 excluding area covered by flap track fairing.

T: 18000FC

 41500FH

I: 5700FC

 11400FH

-200 POor POS

572163-01-6A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front and rear spars from ribs 10 to 14 excluding area covered by flap track fairing.

T: 20300FC

 57000FH

I: 5600FC

 15700FH

-300 

572164-01-1A 500/600 N/A Detailed inspection of outer wing bottom skin at MLI from ribs 1 to 2

and water drain valves from ribs 1 to 28.

T: 18000FC

 37300FH

I 5400FC

-200

I: 5400FC

 10800FH

572164-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin at MLI from ribs 1 to 2

and water drain valves from ribs 1 to 28.

T: 17600FC

 49400FH

I: 5100FC

 14400FH

-300 

572167-01-4A 540/640 540/640 AB to 

HB

Detailed inspection of outer wing bottom skin stringers from rib 1 to rib 14.

T: 48100FC

 96200FH

I: 7000FC

 14000FH

-200 

572169-01-1A 500/600

530/630540/640

532/632 AB, BB540/640 AB, BB

Special detailed inspection (X-Ray) of outer wing bottom skin covered by MLG reinforcing doubler and adjacent skin.

T: 15700FC

 31500FH

I: 9400FC

 18800FH

572169 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572169-01-2A 500/600

530/630540/640

532/632 AB, BB540/640 AB, BB

Special detailed inspection (X-Ray) of outer wing bottom skin covered by MLG reinforcing doubler and adjacent skin.

T: 15100FC

 42500FH

I: 9000FC

 25400FH

572169 -300 

572171-01-2A 532/632 532/632 BB Detailed inspection of outer wing forward attachment fitting for flap 

track beam No. 2.

T: 28400FC

I: 9000FC

ALL

572183-01-4A 470/480 473/483 BL, 

474/484 BR,Engine and attach link removal.

Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.

T: 13000FC

 26100FH

I: 11400FC

 22800FH

572183 -200

572183-01-5A 470/480 473/483 BL, 

474/484 BR,Engine and attach link removal.

Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.

T: 12800FC

 35800FH

I: 11200FC

 31400FH

572183 -300 P

(SB 00SB 00-PRE 11(SB 00

572183-01-6A 470/480 473/483 BL, 

474/484 BR,Engine and attach link removal.

Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.

T: 12800FC

 35800FH

I: 5500FC

 15600FH

572183 -300 PO

(SB 00SB 00-or POS(SB 00

572185-01-1A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface around fuel pump apertures from ribs 1 to 2.

T: 13000FC

 26000FH

I: 8700FC

 17500FH

572185 -200

572185-01-2A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface around fuel pump apertures from ribs 1 to 2.

T: 12200FC

 34200FH

I: 8200FC

 23000FH

572185 -300 

572187-01-1A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface at stringer runouts of stringers 1, 2, 3, 4, 5 (at ribs 2, 5, 7, 11 and 13 respectively) and of stringer 14 (at rib 8).

T: 14300FC

 28700FH

I: 8900FC

 17800FH

572187 -200

572187-01-2A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface at stringer runouts of stringers 1, 2, 3, 4, 5 (at ribs 2, 5, 7, 11 and 13 respectively) and of stringer 14 (at rib 8).

T: 14100FC

 39600FH

I: 8700FC

 24500FH

572187 -300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572502-01-2A 550/650 550/650 FB to 

JBNut removal at selected locations

Special detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.

T: 18800FC

 37600FH

I: 4400FC

 8900FH

572502 -200

PRE 35PRE 47

572502-01-3A 550/650 550/650 FB to 

JBNut removal at selected locations

Special detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.

T: 18800FC

 37600FH

I: 5600FC

 11200FH

572502 -200

POST orPOST 

572502-01-4A 550/650 550/650 FB to 

JBNut removal at selected locations

Special detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.

T: 18800FC

 37600FH

I: 4500FC

 9000FH

572502 -200C

572502-01-5A 550/650 550/650 FB to 

JBNut removal at selected locations

Special detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.

T: 17700FC

 49600FH

I: 5200FC

 14800FH

572502 -300 

572505-01-2A 550/650 550/650 DB, 

EB KB LB

Detailed inspection of outer wing front spar aft face from ribs 17 to 19 d ib 23 t 28

T: 15000FC

30000FH

-200 

EB, KB, LB, MB, NB, PB. 

19 and ribs 23 to 28. 30000FH

I: 8200FC

 16400FH

572505-01-3A 550/650 550/650 DB, 

EB, KB, LB, MB, NB, PB. 

Detailed inspection of outer wing front spar aft face from ribs 17 to 19 and ribs 23 to 28.

T: 15000FC

 30000FH

I: 8200FC

 16400FH

-200C

572505-01-4A 550/650 550/650 DB, 

EB, KB, LB, MB, NB, PB. 

Detailed inspection of outer wing front spar aft face from ribs 17 to 19 and ribs 23 to 28.

T: 13900FC

 39000FH

I: 7600FC

 21300FH

-300 

572512-01-3A 550/650 550/650 AB to 

PB

Detailed inspection of outer wing rear spar FWD face from ribs 14 to28.

T: 33000FC

 66000FH

I: 10200FC

 20500FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572512-01-4A 550/650 550/650 AB to 

PB

Detailed inspection of outer wing rear spar FWD face from ribs 14 to28.

T: 33000FC

 92400FH

I: 9800FC

 27600FH

-300 

572526-01-2A 550/650 550/650 FB Special detailed inspection (X-Ray and LFEC and HFEC) of outer

wing top skin stringer joints from STRs 9 to 15, between ribs 19 and20.

T: 33000FC

92400FH

I: 5400FC

15300FH

572526 -300 

572528-01-2A 550/650 550/650 FB, 

GB

Special detailed inspection (X-Ray and LFEC and HFEC) of outerwing top skin stringer joints, from STR 9 to 15, from ribs 19 to 21.

T: 16700FC

33500FH

I: 5700FC

11400FH

572528 -200

572529-01-3A 550/650 N/A Detailed inspection of outer wing top skin upper surface from ribs 19

to 21.

T: 32600FC

 65200FH

I: 11000FC

 22000FH

-200PRE 51(SB 00PRE 10(SB 00

572529-01-4A 550/650 N/A Detailed inspection of outer wing top skin upper surface from ribs 19

to 21.

T: 32600FC

 65200FH

I: 8200FC

 16500FH

-200POST (SB 00orPOST 

(SB 00 (SB 00

572535-01-4A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to front spar from ribs 14 to 17 and ribs 21 to 23.

T: 25100FC

 50300FH

I: 3100FC

 6200FH

-200 PPRE 47

572535-01-5A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to front spar from ribs 14 to 17 and ribs 21 to 23.

T: 25100FC

 50300FH

I: 5300FC

 10700FH

-200 POorPOST 

572535-01-6A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to front spar from ribs 14 to 17 and ribs 21 to 23.

T: 25200FC

 70700FH

I: 5400FC

 15100FH

-300 

572536-01-1A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front spar from ribs 17 to 21 and 23 to 28

T: 12800FC

 25600FH

I: 4600FC

 9300FH

-200 PPRE 47

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572536-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front spar from ribs 17 to 21 and 23 to 28

T: 12800FC

 25600FH

I: 5800FC

 11600FH

-200 POor POS

572536-01-3A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front spar from ribs 17 to 21 and 23 to 28

T: 12500FC

 35200FH

I: 5600FC

 15900FH

-300 

572538-01-3A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to rear spar from ribs 14 to 28.

T: 26400FC

 52800FH

I: 9400FC

 18800FH

-200

572538-01-4A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to rear spar from ribs 14 to 28.

T: 25900FC

 72600FH

I: 9200FC

 25900FH

-300 

572539-01-3A 530/630 534/634 AB, 

BB 535/635 AB, BB

Detailed inspection of outer wing bottom skin lower surface at attachment to ribs and stringers in area covered by flap track fairings No. 4 and 5.

T: 29400FC

 58900FH

I: 7500FC

 15100FH

-200

572539 01 4A 572539-01-4A 530/630 530/630 534/634 AB, 534/634 AB D t il d i ti f t i b tt ki l f t T 28800FC 300 

BB 535/635 AB, BB

Detailed inspection of outer wing bottom skin lower surface at attachment to ribs and stringers in area covered by flap track fairings No. 4 and 5.

T: 28800FC

 80600FH

I: 7400FC

 20700FH

-300 

572541-01-1A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to ribs and stringers from ribs 14 to 28, from front to rearspar.

T: 18000FC

42000FH

I: 2600FC

5200FH 

-200

R 572541-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at

attachment to ribs and stringers from ribs 14 to 28, from front to rearspar.

T: 23400FC

 65400FH

I: 2600FC

 7200FH

-300 

572542-01-3A 500/600 N/A Detailed inspection of outer wing bottom skin at MLI, slat track and

jack drain holes from ribs 2 to 28.

T: 18000FC

 40300FH

I: 6600FC

 13200FH

-200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

R 572542-01-4A 500/600 N/A Detailed inspection of outer wing bottom skin at MLI, slat track and

jack drain holes from ribs 2 to 28.

T: 19600FC

 55200FH

I: 6400FC

 18000FH

-300 P(SB 57

572542-01-5A 500/600 N/A Detailed inspection of outer wing bottom skin at MLI, slat track and

jack drain holes from ribs 2 to 28.

T: 39300FC

 110300FH

I: 6400FC

 18000FH

-300 PO(SB 57

572543-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface in area of

joint at rib 20

T: 17900FC

 35900FH

I: 9300FC

 18600FH

-200

572544-01-2A 550/650 550/650 EB, 

FB

Special detailed inspection (X-Ray and LFEC and HFEC) of outerwing bottom skin stringer joints inboard of rib 19 and from rib 19 torib 20.

T: 19700FC

 55300FH

I: 6500FC

 18200FH

572544 -300 

R 572545-01-2A 500/600 N/A Special detailed inspection (LFEC) of outer wing bottom skin joint

strap at rib 20.

T: 17900FC

 35900FH

I: 4300FC 

 8700FH 

572545 -200

R 572546-01-2A 550/650 550/650 FB, 

GB

Special detailed inspection (X-Ray and LFEC and HFEC) of outerwing bottom skin stringers at STR joints from ribs 19 to 21.

T: 20200FC 

 40500FH

I: 5500FC 

 11000FH 

572546 -200

572547-01-3A 550/650 550/650 AB to 

HB, JB to NB, PB

Detailed inspection of outer wing bottom skin stringers from ribs 14 to 28.

T: 48800FC

 97700FH

I: 4500FC

 9000FH

-200

572548-01-4A 550/650 550/650 AB to 

FB

Detailed inspection of outer wing bottom skin butt strap at stringer 8 from ribs 14 to 20.

T: 21100FC

 42300FH

I: 11900FC

 23900FH

-200 PPRE 47

572548-01-5A 550/650 550/650 AB to 

FB

Detailed inspection of outer wing bottom skin butt strap at stringer 8 from ribs 14 to 20.

T: 21100FC

 42300FH

I: 12800FC

 25700FH

-200 POor POS

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572548-01-6A 550/650 550/650 AB to 

FB

Detailed inspection of outer wing bottom skin butt strap at stringer 8 from ribs 14 to 20.

T: 20600FC

 57800FH

I: 12500FC

 35200FH

-300 

572549-01-3A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface at stringer runouts of stringers 6, 7 and 8b at ribs 16, 19 and 22.

T: 18000FC

 41000FH

I: 4600FC

 9200FH

572549 -200

572549-01-4A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface at stringer runouts of stringers 6, 7 and 8b at ribs 16, 19 and 22.

T: 20200FC

 56800FH

I: 4500FC

 12800FH

572549 -300 

572553-01-4A 550/650 550/650 AB, 

AT,Rubber ring removal

Special detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.

T: 18000FC

 40400FH

I: 14900FC

 29800FH

572553 -200 P

PRE 47

572553-01-5A 550/650 550/650 AB, 

AT,Rubber ring removal

Special detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.

T: 18000FC

 40400FH

I: 17000FC

 34000FH

572553 -200 PO

orPOST 

572553-01-6A 550/650 550/650 AB, 

AT,

R bb i

Special detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.

T: 20500FC

 57600FH

I 17000FC

572553 -300 

Rubber ring removal

I: 17000FC

 47600FH

572554-01-3A 550/650 550/650 KB Special detailed inspection (HFEC) of outer wing bottom skin upper 

surface at stringer runout of stringer 13b at rib 23.

T: 27700FC

 55400FH

I: 7900FC

 15900FH

572554 -200

572554-01-4A 550/650 550/650 KB Special detailed inspection (HFEC) of outer wing bottom skin upper 

surface at stringer runout of stringer 13b at rib 23.

T: 27500FC

 77000FH

I: 5600FC

 15800FH

572554 -300 

572557-02-1A 550/650 550/650 BB to 

FB

Special detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts from ribs 15 to 20.

T: 17200FC

 34400FH

I: 13500FC

 27000FH

572557 -200

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

572557-02-2A 550/650 550/650 BB to 

FB

Special detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts from ribs 15 to 20.

T: 17300FC

 48500FH

I: 13500FC

 37800FH

572557 -300 

R 572558-01-3A 500/600

530/630

550/650 JB, KBFlap track 5 fairing brackets removed.

Special detailed inspection (Ultrasonic) of outer wing bottom skin at attachment to stringers adjacent to access door cutouts from ribs 14 to 28.

T: 49700FC

 99500FH

I: 10200FC

 20400FH

572558 -200

572561-01-1A 550/650 550/650 GB to 

PB

Special detailed inspection (HFEC) of outer wing bottom skin access doors and skin around access door cutouts from ribs 20 to 28.

T: 18600FC

 37200FH

I: 11200FC

 22400FH

572561 -200

572561-01-2A 550/650 550/650 GB to 

PB

Special detailed inspection (HFEC) of outer wing bottom skin access doors and skin around access door cutouts from ribs 20 to 28.

T: 18600FC

 52000FH

I: 11300FC

 31900FH

572561 -300 

572563-01-2A 533/633

534/634535/635

533/633 BB534/634 BB535/635 BB

Detailed inspection of outer wing forward attachment fittings for flap track beams No. 3, 4 and 5.

T: 42000FC

I: 15000FC

-200

572565 01 1A 572565-01-1A 550/650 550/650 N/A S i l d t il d i ti (X R d Ult i ) f t i Special detailed inspection (X-Ray and Ultrasonic) of outer wing T 16300FC 572565 300 

bottom skin joint strap in area of rib 20.

T: 16300FC

 45800FH

I: 4600FC

 12900FH

572565 -300 

R 574105-01-1A 512/612 Slats extended Detailed inspection of outer wing inboard fixed leading edge "D"

nose skin including jack and track cutouts.

T: 18000FC

42000FH

I: 15000FC 

30000FH

-200 

R 574105-01-2A 512/612 Slats extended Detailed inspection of outer wing inboard fixed leading edge "D"

nose skin including jack and track cutouts.

T: 20100FC

56500FH

I: 15000FC 

42000FH

-300 

R 574113-01-1A 523/623 Slats extended Detailed inspection of outer wing center fixed leading edge "D" nose

skin including jack and track cutouts.

T: 21000FC

42000FH

I: 15000FC 

30000FH

-200 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

R 574113-01-2A 523/623 Slats extended Detailed inspection of outer wing center fixed leading edge "D" nose

skin including jack and track cutouts.

T: 20100FC

56500FH

I: 15000FC 

42000FH

-300 

R 574121-01-1A 524/624 Slats extended Detailed inspection of outer wing outboard fixed leading edge "D"

nose skin including jack, track and antiicing telescopic duct cutouts.

T: 18000FC

42000FH

I: 15000FC 

30000FH

-200 

R 574121-01-2A 524/624 Slats extended Detailed inspection of outer wing outboard fixed leading edge "D"

nose skin including jack, track and antiicing telescopic duct cutouts.

T: 20100FC

56500FH

I: 15000FC 

42000FH

-300 

574129-01-2A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface FWD of

front spar from root to tip.

T: 15200FC

 30400FH

I: 3600FC

 7200FH

-200

574129-01-3A 500/600 N/A Detailed inspection of outer wing bottom skin lower surface FWD of

front spar from root to tip.

T: 14900FC

 41700FH

I: 2400FC

 6900FH

-300 

574129 01 4A 574129-01-4A 500/600 500/600 N/A D t il d Detailed inspection of outer wing bottom skin lower surface FWD of i ti f t i b tt ki l f FWD f T 15200FC 200C

front spar from root to tip.

T: 15200FC

 30400FH

I: 3600FC

 7200FH

-200C

574130-01-2A 500/600 N/A Detailed inspection of outer wing top skin upper surface FWD of

front spar from rib 7 to rib 28.

T: 15800FC

 31600FH

I: 3900FC

 7900FH

-200 PO(SB 57

575129-01-1A 500/600 N/A Detailed inspection of outer wing bottom wing skin lower surface at

attachments to the trailing edge between ribs 5 and 11.

T: 18000FC

 42000FH

I: 2200FC

 4500FH

-200

575129-01-2A 500/600 N/A Detailed inspection of outer wing bottom wing skin lower surface at

attachments to the trailing edge between ribs 5 and 11.

T: 18000FC

 52200FH

I: 2200FC

 6200FH

-300 

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

575131-01-5A 575/675 575/675 CB, 

DBRemoval of anti rotation locking device (only for Post Mod 13297)

Detailed inspection of outer wing bottom skin upper surface aft of rear spar in area of pylon fairing.

T: 26800FC

 53600FH

I: 10800FC

 21600FH

-200

575131-01-6A 575/675 575/675 CB, 

DBRemoval of anti rotation locking device (only for Post Mod 13297)

Detailed inspection of outer wing bottom skin upper surface aft of rear spar in area of pylon fairing.

T: 26200FC

 73500FH

I: 10500FC

 29600FH

-300 P(SB 00SB 00-PRE 11(SB 00

575131-01-7A 575/675 575/675 CB, 

DBRemoval of anti rotation locking device (only for Post Mod 13297)

Detailed inspection of outer wing bottom skin upper surface aft of rear spar in area of pylon fairing.

T: 26200FC

 73500FH

I: 9300FC

 26200FH

-300 PO(SB 00SB 00-or POS(SB 00

575141-01-4A 581/681

591/691

Flap extended, 581/681 AB t

Detailed inspection of outer wing bottom skin upper and lower 

f ft f b t ib 11 d 28 i l di

T: 18000FC

41900FH

-200

591/691 581/681 AB to 

JB, 591/691 AB, BB, cable steady bracket removal at track 5.

surfaces aft of rear spar between ribs 11 and 28 including areas covered by flap track fairings.

 41900FH

I: 9100FC

 18300FH

575141-01-5A 581/681

591/691

Flap extended, 581/681 AB to JB, 591/691 AB, BB, cable steady bracket removal at track 5.

Detailed inspection of outer wing bottom skin upper and lower surfaces aft of rear spar between ribs 11 and 28 including areas covered by flap track fairings.

T: 20400FC

 57200FH

I: 8900FC

 25000FH

-300 

575147-01-4A 572/672 572/672 AB Detailed inspection of outer wing shroud box for spoiler 1, inboard rib 

and attachment bracket (inboard face).

T: 32200FC

I: 15500FC

ALL

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

575201-01-1A 574/674 Flaps extended General visual inspection of inboard flap, vane and vane tracks,

external surface.

T: 5400FC

I: 5400FC

ALL 

575211-01-2A 574/674

577/677

Flaps extended Detailed inspection of inboard flap carriage 1 including hinge. T: 30000FC

I: 8700FC

ALL

575214-01-2A 532/632

574/674

Flaps extended,532/632 CB,574/674 AT

Detailed and Special detailed inspection (ENDOSCOPE) of inboardflap carriage 2, rear link, and fixed link with attachments to flap andcarriage 2.

T: 30000FC

I: 11900FC

575214 ALL

575224-01-2A 574/674 Vane tracks 

andfork fittings removal

Detailed inspection of lugs and fittings in vane attachment area attrack 1 to 5.

T: 30000FC

I: 7900FC

575301-01-1A 500/600 Flaps extended General visual inspection of outboard flap upper and lower skin

including leading edge, external surface.

T: 5800FC

I: 5800FC

ALL 

576102-01-1A 500/600 N/A General visual inspection of all speed aileron upper and lower skin,

external surface.

T: 10000FC

I: 10000FC

ALL 

712101-01-1A 453/463 

454/464

435/445/451/461 AL436/446/452/4

62 AR

Detailed inspection of forward engine mount excluding the platform T: 3200FC

I: 3200FC

CF6-80

62 AR

712101-01-2A 453/463 

454/464

435/445/451/461 AL436/446/452/462 AR

Detailed inspection of forward engine mount excluding the platform T: 3000FC

I: 3000FC

CF6-80

R 712102-01-1A 453/463 

454/464

Engine removed435/445/451/461 AL436/446/452/462 AR

Special detailed inspection (Fluorescent Penetrant Inspection) offorward engine mount platform

T: 7500 FC

I: 7500 FC

GE CMM 

71.21.01

CF6-80

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. A

A310

Airworthiness Limitation Items

R 712102-01-2A 453/463 

454/464

Engine removed435/445/451/461 AL436/446/452/462 AR

Special detailed inspection (Fluorescent Penetrant Inspection) offorward engine mount platform

T: 5170 FC

I: 5170 FC

GE CMM 

71.21.01

CF6-80

712202-01-1A 453/463 

454/464

Engine removed435/445/451/461 AL436/446/452/462 AR

Special detailed inspection (Fluorescent Penetrant Inspection) of aftengine mount beam

T: 20000 FC

I: 20000 FC

GE CMM 

71.20.05

CF6-80

712202-01-2A 453/463 

454/464

Engine removed435/445/451/461 AL436/446/452/462 AR

Special detailed inspection (Fluorescent Penetrant Inspection) of aftengine mount beam

T: 14400 FC

I: 14400 FC

GE CMM 

71.20.05

CF6-80

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section D

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 PAGE: 1-E 

EASA APPROVED 

Ref: 95A.1309/07 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

SECTION E: ALTERNATIVE SPECIAL RANGE UTILIZATION REQUIREMENTS

This section provides alternative requirement for those tasks of section D, which are 

identified with note “S”. 

It has been recognized that the aircraft operated long range Average Flight Time (AFT) 

>= 4 FH/FC were penalized by the standard program. 

Therefore, aircraft operated with an AFT >= 4 FH/FC have the following specific figures 

to get an optimized maintenance program. 

The concerned ALI tasks are provided in the section E of this document and replace for 

long-range operations, the similar ALI tasks of the section D. 

For the task format, refer to the description provided in the previous paragraph section 

D. The only difference is for the task reference number. The last digit is “S” and stands 

for Special Range 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

531273-01-2A-S 121/122 121/122 LF,

121/122 MF,121/122 NF,121/122 PF

Detailed inspection of nose gear bay arches attachments to frames atstringer 44 and struts attachments lugs, from FR11A to FR16Ainclusive, LH/RH.

T: 23600FC

118000FH

I: 3900FC

19500FH

-

531276-01-2A-S 123/124 713, 714 Detailed inspection of nose gear telescopic drag strut attach fitting. T. 29000FC

145000FH

I. 5500FC

27800FH

-

531435-01-1A-S 231, 232, 

233, 234 

Ceiling and sidewall panels, insulation displaced as required

Special detailed inspection (LFEC) of Splice plate at circumferential skin splice at FR 26/32 from STR 4 LH/RH to crown centre line and from STR 5 to 12, LH/RH. 

T: 27000FC

 135000FH

I: 4500FC

 22500FH

531435 -

531501-01-4A-S 200 N/A Detailed inspection of skin in circumferential splice and stringer 

coupling areas at FR 40/41, from STR 13 LH/RH to crown center line, external surface.

T: 36600FC

 183300FH

I: 9100FC

 45800FH

-

A310

Airworthiness Limitation Items

531506-01-2A-S 200 Antenna 

removal

Detailed inspection of skin around VHF antenna cutout from FR 47/48 to FR 49 and between STR 1 LH and STR 1 RH, external surface.

 T: 24000FC

116000FH

 I: 3600 FC

18200 FH

-P

531506-01-3A-S 200 Antenna 

removal

Detailed inspection of skin around VHF antenna cutout from FR 47/48 to FR 49 and between STR 1 LH and STR 1 RH, external surface.

 T: 24000FC

116000FH

 I: 3500FC

17600FH

-P

531508-01-2A-S 200 N/A Detailed inspection of fuselage skin in frame coupling area at FR 42 

to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH, external surface.

T: 18000 FC

90000 FH

I: 3900 FC

19600 FH

-P

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531508-01-3A-S 200 N/A Detailed inspection of fuselage skin in frame coupling area at FR 42 

to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH, external surface.

T: 18000 FC

90000 FH

I: 3750 FC

18700 FH

-P

531512-01-2A-S 100/200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 45, from STR 13 to STR 27, LH/RH, external surface.

T: 9000 FC

45000 FH

I: 4500 FC

23000 FH

-P

531512-01-3A-S 100/200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 45, from STR 13 to STR 27, LH/RH, external surface.

T: 9000 FC

45000 FH

I: 4500 FC

22500 FH

-P

R 531524-01-2A-S 200 Anticollision 

Light

Detailed inspection of fuselage skin around anti-collision light cutout from FR 42 to FR 43, and from STR 1 LH to STR 1 RH, external surface.

T: 21500FC

 109000FH

I: 9000FC

 56000FH

-

531542-01-3A-S 141/142 734, 744

147/148AZ

Special detailed inspection (Ultrasonic) of stiffener at wing to fuselage lower skin splice at rib 1 (center wing box side) from FR42 to FR47.

T: 18700FC

93700FH

531542 -

147/148AZSealant Removal

lower skin splice at rib 1 (center wing box side) from FR42 to FR47. 93700FH

I: 4700FC

 23800FH

531551-01-2A-S 143/144 144 FR

143 FL

Detailed inspection of fuselage skin and doubler around air conditioning compartment access cutouts, LH/RH.Note: Internal and external side to be inspected

T: 13200FC

 66200FH

I: 13200FC

 66200FH

-

531552-01-2A-S 145/146

241/242

Main deck floor panels, insulation, bolts to be removed 

Special detailed inspection (Rotating Probe) of FR49, 50, 51, 52 and 53 between STR 25 and 29 at frame foot, LH/RH.

T: 28000FC

 140400FH

I: 8200FC

 41000FH

531552 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531555-01-2A-S 147/148 734/744 General visual inspection of slanted frames from FR 47 to FR 54, 

LH/RH.

T: 6500FC

 32900FH

I: 6500FC 

 32900FH

-

531556-01-2A-S 147/148 734/744

147/148 CZ

Detailed inspection of fuselage internal structure at FR 47/48 from STRs 42 to 43, LH/RH.

T: 9800FC

 49000FH

I: 2200FC

 11200FH

-

531561-01-2A-S 145/146 

241/242

Main deck floor panels, insulation. 

Detailed inspection of FR47A, 49A, 50A, 51A and 52A at frame foot runout, LH/RH. 

T: 28200FC

 141000FH

I: 14400FC

 72000FH

-

531567-01-2A-S 147/148 734/744 Detailed inspection of keel beam side panels, adjacent fuselage 

structure up to STR 40 and MLG hinge assemblies and door actuator fitting from FR 47 to FR 54, LH/RH.

T: 12700FC

 63900FH

I: 2900FC

 14500FH

-

531571-01-3A-S 143/144

147/148

734/744143DF

Detailed inspection of keel beam box from FR44 to FR54, internal structure.

T: 13700FC

 68600FH

-

147/148 143DF

147AF,BF,BZ148BF

structure. 68600FH

I: 11300FC

 56500FH

531579-01-3A-S 135/136

137/138

Cargo compartment floor and sidewall panelsInsulation displaced as required

Detailed inspection of FWD face of pressure bulkhead at FR 39, including stringer end fittings from STR35 LH / STR35 RH to bottom center line

T: 29800FC

 149400FH

I: 21300FC

 106800FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531580-01-2A-S 143/144 734/744

147BZ

Detailed inspection of stringer end fittings and horizontal cross members at AFT face of pressure bulkhead at FR39, from STR35 to bottom center line, LH/RH

T: 14900FC

 74700FH

I: 6400FC

 32100FH

-

531582-01-2A-S 143/144 572 / 672 AB Special detailed inspection (Ultrasonic) of fuselage skin from 

FR47/48 to FR49 and from STR 35 to STR 36, LH/RH.

T: 23000FC

 115400FH

I: 13900FC

 69400FH

531582 -

531584-01-3A-S 143/144 Chafing plate 

removal as per SB 53-2069Sealant Removal

Special detailed inspection (LFEC and Ultrasonic) of fuselage skin underneath pick-up angle from FR 39 to FR 42, LH/RH.

T: 13400FC

 66900FH

I: 8000FC 

 40200FH

531584 -

P

531584-01-4A-S 143/144 Chafing plate 

removal as per SB 53-2069Sealant 

Special detailed inspection (LFEC and Ultrasonic) of fuselage skin underneath pick-up angle from FR 39 to FR 42, LH/RH.

T: 17400FC

 87000FH

I: 4000FC 

 20100FH

531584 -

P

Removal

531586-01-2A-S 241/242 241BW 

242BW

Special detailed inspection (X-RAY) of fuselage skin doubler at FR40/41, between STRs 20 and 23, LH/RH

T: 27200FC

 136100FH

I: 1900FC

 9900FH

531586 -

531587-01-3A-S 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 17700FC

 87800FH

I: 11100FC

 55800FH

-P

531587-01-4A-S 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 22900FC

 113100FH

I: 11100FC

 55800FH

-P5

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531587-01-5A-S 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fitting 

lower part, LH/RH.

T: 29200FC

 144600FH

I: 11100FC

 55800FH

-P

531602-01-2A-S 243

244

Ceiling panels, insulation, overhead stowage compartments (if fitted), bolts. 

Special detailed inspection (Rotating Probe) of splice plate at the circumferential skin splice at FR54 at STR5, LH/RH

T: 27000FC

135100FH

I: 5900FC

 29700FH

531602 -

531605-01-3A-S 200 N/A Detailed inspection of skin in circumferential splice and stringer 

coupling areas at FR 55/58 from STR 13, LH/RH, to crown center line, external surface.Note: This task is an alternative to 531605-02-4A-S

T: 9800FC 

 49000FH 

I: 4600FC 

 23000FH 

-

531605-02-4A-S 200 N/A Special detailed inspection (HFEC) of skin in circumferential splice 

and stringer coupling areas at FR 55/58 from STR 13, LH/RH, to crown center line, external surface.

T: 9800FC 

 49000FH 

I: 6700FC 

531605 -

c o ce te e, e te a su aceNote: This task is an alternative to 531605-01-3A-S

6 00 C

 33500FH 

531606-01-4A-S 200 N/A Special detailed inspection (LFEC) of Splice plate at circumferential 

skin splice at FR 55/58 from STR 4 LH/RH to crown centre line and from STR 5 to 12, LH/RH 

T: 10000FC

50000FH

I: 1400FC

7400FH

531606 -

P5

531611-01-2A-S 200 N/A Detailed inspection of skin at shear tie attachments at FR 54.1, 54.2 

and 54.3 from STR 22 LH/RH, to crown center line, external surface.

T: 23500FC

 116000FH

I: 3300FC

 16400FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531621-01-2A-S 253/254 Ceiling 

planels, Insulation displaced as required, air conditioning duct, overhead stowage compartments, bolts

Special detailed inspection (HFEC + rotating probe) of splice plate at circumferential skin splice at FR 55/58, from STR 4 to STR 6, LH/RH, and from STR 12 to STR 13, LH/RH, i.e. where lap joints intersect with circumferential skin splice. 

T: 16500FC

 82500FH

I: 9500FC

 49000FH

531621 -

P5

531701-01-4A-S 200 N/A Detailed inspection of fuselage skin in circumferential splice and 

stringer coupling areas at FR 72, from STR 13 LH/RH, to crown center line, external surface. 

T: 18500FC

 82500FH

I: 6500FC

 32500FH

-

531702-01-4A-S 200 N/A Special detailed inspection (LFEC) of splice plate at circumferential 

skin splice at FR 72 from STR 4 LH/RH to crown centre line and from STR 6 to 11, LH/RH. 

T: 18000FC

 90000FH

I: 4500FC

 23000FH

531702 -

531731-02-1A-S 253/254 Ceiling 

panels, insulation displaced as required, air conditioning duct, overhead stowage compartments, bolts

Special detailed inspection (HFEC + rotating probe) of Splice plate at circumferential skin splice at FR 72, from STR 3 to STR 7, LH/RH, and from STR 11 to STR 13, LH/RH, i.e. where lap joints intersect with circumferential skin splice. 

T: 18000FC

 90000FH

I: 10500FC

 52500FH

531731 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531737-01-2A-S 240 Antenna to be 

removed

Detailed inspection of skin around ADF1 and ADF2 antenna cutouts between FR 59 and FR 60 and between FR 62 and FR 63, on crown center line, external surface. 

T: 21500FC

 109000FH

I: 4500FC

 22500FH

-

531801-01-2A-S 200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 76, from STR 13 LH/RH, to crown center line, external surface. 

T: 9900FC

 49500FH

I: 6400FC

 32000FH

-

531803-01-2A-S 200 N/A General visual inspection of fuselage skin in circumferential splice 

and stringer coupling areas at FR 80/82, from STR 6 to STR 13, LH/RH, external surface. 

T: 8100FC

 40500FH

I: 7200FC

 36000FH

-

531807-01-2A-S 100/200 N/A General visual inspection of fuselage skin and fail safe ring around 

AFT passenger/crew door cutouts from FR 73 to FR 76, and from STR 9 to STR 28, external surface (without scuff plate removal).

T: 2700FC

 13700FH

I: 2700FC

 13700FH

-

531808-01-4A-S 261/262 833/843 S 531808 01 4A S 261/262 833/843 Special detailed ins detailed inspection pection (HFEC) of AFTpassenger/crew assenger/crew door T: 16500FC 531808 -

door

cutouts, upper corners including skin and fail safe ring.

T: 16500FC

 82500FH

I: 3700FC

 18500FH

531808 

531809-01-4A-S 171/172

261/262

Scuff plate removal

Special detailed inspection (US + HFEC + VISUAL) of fail safe ring and skin of AFT passenger/crew door cutouts at lower corners, underneath the scuff plates.

T: 16500FC

 82500FH

I: 4300FC

 21500FH

531809 -

531910-01-2A-S 323 323 AL, BL

323 AR, BR

Detailed inspection of fuselage skin, external surface in area of fin to fuselage FWD, MID and AFT attach fitting fasteners and visible part of the fittings.

T: 21500FC

 109000FH

I: 5100FC

 25500FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

531913-01-2A-S 311/312 313 AL Special detailed inspection (US) of horizontal stabilizer hinge support 

members and upper and lower attachment lugs of FR 91 LH/RH.

T: 9000FC

 45000FH

I: 7500FC

 37500FH

531913 -

531924-01-2A-S 300 N/A Special detailed inspection (LFEC) of fuselage skin at circumferential 

splice at FR 86 from STR 22 to STR 27 LH/RH.

T: 14000FC

 70000FH

I: 6000FC

 30000FH

531924 -

531926-01-5A-S 311/312 313 AL Special detailed inspection (HFEC) of horizontal stabilizer cutout, 

lower longeron, corner fitting, skin strap and skin, LH/RH.

T: 15000FC

 75000FH

I: 1900FC

 9700FH

531926 -

P6

545002-P1-3A-S 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 35000FC

175000FH

I: 9900FC

49900FH

545002 -

545002-P1-5A-S 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 35000FC

175000FH

545002 -

425/426 452/462 AR areas at AFT end of lower arms, from rib 1 to rib 2. 175000FH

I: 8600FC

43200FH

545002-G1-5A-S 415/416

425/426

451/461 AL, 452/462 AR

Special detailed inspection (Ultrasonic) of pylon pyramid, attachment areas at AFT end of lower arms, from rib 1 to rib 2.

T: 30200FC

151300FH

I: 3000FC

15000FH

545002 -

545003-P1-2A-S 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 9300FC

46500FH

I: 9300FC

46500FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

545003-P1-4A-S 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 8000FC

40200FH

I: 8000FC

40200FH

-P

545003-P1-5A-S 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 10700FC

53500FH

I: 10700FC

53500FH

-P

545003-G1-4A-S 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 1900FC

9800FH

I: 1900FC

9800FH

-6

545003-G1-5A-S 415/416

425/426

451/461 AL, 452/462 AR

Detailed inspection of pylon-to-engine FWD attach fitting, (pyramid) arms.

T: 2600FC

13000FH

I: 2600FC

13000FH

-6

545028-01-3A-S 435/436

445/446

435/445 AL451/461 AL

Detailed inspection of engine cowl hinge fittings, LH/RH (including bolts and nacelle hinge side).

T: 600FC

3150FH

-

445/446451/452461/462

451/461 AL436/446 AR452/462 AR

bolts and nacelle hinge side). 3150FH

I: 600FC

3150FH

545030-01-3A-S 473/474 

483/484

473/483 AL, 474/484 AR

Detailed inspection of pylon lateral panels at the edge of access door cutouts between ribs 13 and 14, LH/RH.

T: 8300FC

41700FH

I: 8300FC

41700FH

-

545043-G1-3A-S 415/416

425/426

N/A Detailed inspection of pylon side panels at rib 8, LH/RH T: 25600FC

128300FH

I: 8900FC

44700FH

-1

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

545043-P1-3A-S 415/416

425/426

N/A Detailed inspection of pylon side panels at rib 8, LH/RH T: 22300FC

111600FH

I: 8700FC

43600FH

-1

551020-01-3A-S 333/343 333/343 AT

rearmost apron fitting

Detailed of horizontal stabilizer outer box top skin upper surface chordwise splice between rib 3 and rib 4 from rear spar to STR 9, LH/RH.Note: This task has to be done at the same time as task 551020-02-3A-S.

T: 20900FC

 104800FH

I: 4900FC

 24800FH

-

551020-02-3A-S 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre box 

top skin upper surface chordwise splice between rib 3 and rib 4 from rear spar to STR 9, LH/RH.Note: This task has to be done at the same time as task 551020-01-3A-S.

T: 20900FC

 104800FH

I: 4900FC

 24800FH

551020 -

551075-01-1A-S 311/312 313 AL Detailed inspection of horizontal stabilizer rear spar joining part 

inboard side at rib 3, LHRH.

T: 22800FC

 114400FH

I: 5400FC

-

5 00 C

 27300FH

571008-01-2A-S 540/640 540/640 AB Special detailed inspection (X-RAY) of outboard horizontal flange of 

lower T section, inboard row of fasteners from front spar to rear spar, LH/RH.

T: 26900FC

 134500FH

I: 6250FC

 31300FH

571008 -

571009-01-2A-S 141/142 734/744

147/148 AZ

Detailed inspection of center wing box rear spar around access door cutouts.

T: 10800FC

 54400FH

I: 8600FC 

 43200FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

571013-01-4A-S 241/242 Sidewall 

panels,Insulation displaced as required,241 LW, MW,242 LW, MW

Special detailed inspection (Ultrasonic) of FR 47/48, FWD and AFT faces from STRs 22 to 24, LH/RH.

T: 24800FC

 124000FH

I: 4200FC

 21400FH

571013 -

571022-01-3A-S 541/542

641/642

540/640ABSealant removal

Special detailed inspection (Ultrasonic) of stiffener at wing to fuselage lower attachment, outboard side between FR43 and FR45, at stiffeners 7, 8 and 9, LH/RH.

T: 12500FC

 62500FH

I: 1800FC

 9000FH

571022 -

571023-01-2A-S 141

142

734/744147/148AZ, bolts

Special detailed inspection (Rotating Probe) of center wing box lower skin at pump holes reinforcing plates upper side, from FR 46 to 47 and from beams 3 to 5, LH/RH.

T: 23100FC

 115500FH

I: 9800FC

 49000FH

571023 -

571024-01-4A-S 141/142 734/744,

147/ 148 AZ, Sealant 

Special detailed inspection (Ultrasonic) of center wing box front spar lower cap corner fitting and adjacent front spar structure, LH/RH.

T: 16100FC

 80500FH

I: 9800FC

571024 -

Sea a tremoval

9800 C

 49200FH

571026-01-2A-S 141/142 Main deck 

floor panels, galleys and toilets (if installed)Sealant Removal

Special detailed inspection (Ultrasonic) of inboard side of cruciform fitting at junction with stiffeners between FR40-1 and FR44-2, LH/RH

T: 21500FC

 107550FH

I: 3350FC

 16800FH

571026 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

571028-01-2A-S 141/142 Main deck 

floor panels, galleys and toilets (if installed)Sealant Removal

Special detailed inspection (Ultrasonic) of center wing box upper panel between stiffeners 43.2 and 44.1 at cruciform fitting junction, LH/RH

T: 19950FC

 99700FH

I: 6250FC

 31250FH

571028 -

571040-01-3A-S 540/640 577/677AT

577/677BTSealant Removal

Special detailed inspection (HFEC) of cruciform at upper wing skin to fuselage joint from FR 40/41 to 47/48, upper outboard radius, LH/RH 

T: 17200FC

 86400FH

I: 10200FC

 51000FH

571040 -

R 571041-01-3A-S 540/640 577/677 AT

577/677 BT

Detailed inspection of cruciform at upper wing skin to fuselage joint from FR 40/41 to FR 47/48, outboard flange upper surface, LH/RH.

T: 17400FC

 87200FH

I: 2600FC

 13100FH

-

571042-01-3A-S 540/640 540/640AB

Sealant Removal

Detailed inspection of outer wing upper skin stringer end fittings and adjacent part of stringers at rib 1, from front to rear spar, LH/RH. 

T: 30300FC

 151650FH

I: 7150FC

-

e oa

Note: This task is an alternative to 571042-02-2A-S

50 C

 35750FH

571042-02-2A-S 540/640 540/640AB

Sealant Removal

Special detailed inspection (Ultrasonic) of outer wing upper skin stringer end fittings and adjacent part of stringers at rib 1, from front to rear spar, LH/RH. Note: This task is an alternative to 571042-01-3A-S

T: 30300FC

 151650FH

I: 11500FC

 57550FH

571042 -

571043-01-3A-S 540/640 540/640AB Special detailed inspection (Ultrasonic) of outer wing rear spar to rib 1 

junction, vertical tee splice fitting outboard flange, LH/RH

T: 30300FC

 151600FH

I: 8800FC

 44100FH

571043 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

571045-01-3A-S 143/144 147BZ

734/744vapour seal displaced

Detailed inspection of center wing box bottom skin lower surface in air conditioning bay.

T: 15500FC

 77400FH

I: 8400FC

 42100FH

-

571047-01-3A-S 143/144 147BZ

734/744vapour seal displacedSealant Removal

Special detailed inspection (Ultrasonic and Rototest) of center wing box bottom skin lower surface in beam attachment areas from front to rear spars and from Rib 1 LH to Rib 1 RH. 

T: 15500FC

 77400FH

I: 12300FC

 61600FH

571047 -

571051-01-2A-S 141

142

734/744147/148 AZ, boltsSealant Removal

Special detailed inspection (Rotating Probe) of center wing box rear spar to Rib 1 junction vertical T splice fitting and angle fitting, LH/RH

T: 23600FC

 118150FH

I: 7800FC

 39100FH

571051 -

571052-01-2A-S 540

640

540AB640AB, boltsSealant Removal

Special detailed inspection (Rotating Probe) of outer wing rear spar to Rib 1 junction angle fitting, LH/RH

T: 33550FC

 167750FH

I: 12000FC

60150FH

571052 -

571053-01-2A-S 540

640

540AB640ABSealant Removal

Detailed inspection of outer wing upper skin fittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-02-2A-S

T: 27750FC

 138850FH

I: 3250FC

 16250FH

-

571053-02-2A-S 540

640

540AB640AB, boltsSealant Removal

Special detailed inspection (Rotating Probe) of outer wing upper skin fittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-01-2A-S

T: 27750FC

 138850FH

I: 19300FC

 96650FH

571053 -

571054-01-2A-S 145/146 Main deck 

floor panels, bolts removal

Special detailed inspection (Rotating Probe) of upper cruciform fitting junction with fuselage panel at FR43A, LH/RH

T: 34700FC

 173600FH

I: 8400FC

 42200FH

571054 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

571056-01-2A-S 540/640 540/640AB Special detailed inspection (Ultrasonic) of wing upper surface panel 

between stiffener 2 and 7 at cruciform fitting end, LH/RH

T: 29600FC

 148050FH

I: 1250FC

 6400FH

571056 -

571061-01-2A-S 540/640 540/640 AB

Sealant Removal

Special detailed inspection (Ultrasonic) of outboard horizontal flange of lower T section, inboard row of fasteners at stiffener 7 and stiffener 9, LH/RH

T: 15800FC

 79100FH

I: 4850FC

 24250FH

571061 -

571062-01-2A-S 540/640 N/A Special detailed inspection (Ultrasonic) of lower splice between 

FR40/41 and FR47/48 at the first row of fasteners from Rib 1 datum (wing side), LH/RH.

T: 17100FC

 85450FH

I: 2700FC

 13600FH

571062 -

571067-01-2A-S 141/142 N/A Special detailed inspection (Ultrasonic) of center wing box lower 

splice at Rib 1, first fasteners row from Rib 1 datum between stiffener 42.2 and 44.1, LH/RH

T: 23250FC

 116350FH

I: 6250FC

 31400FH

571067 -

571068-01-2A-S 141/142 N/A Special detailed inspection (Ultrasonic) of center wing box lower 

splice at Rib 1, first fasteners row from Rib 1 datum between stiffener 44.2 and 46.2, LH/RH

T: 27050FC

 135300FH

I: 6850FC

 34250FH

571068 -

571069-01-2A-S 141/142 734/744

147/148AZbolts to be removedSealant Removal

Special detailed inspection (Rotating Probe) of center wing box bottom skin stiffener at FR44 level, LH/RH.

T: 29900FC

 149600FH

I: 2700FC

 13500FH

571069 -

P

R 572104-01-4A-S 512/612 512/612 CB, 

EB, HB

Detailed inspection of outer wing front spar FWD face from ribs 1 to 7 at slat track cutouts (3 places).

T: 11500FC

57700FH

I: 1500FC

7800FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572105-01-4A-S 523/623 523/623 BB, 

CB

Detailed inspection of outer wing front spar forward face splice plate at rib 10. 

T: 26600FC

 133000FH

I: 6000FC

 30400FH

-

R 572107-01-2A-S 540/640 540/640 AB, 

BB

Detailed inspection of outer wing front spar AFT face from ribs 1 to 7.Note : This task is an alternative to 572107-02-2A-S

T: 9900FC

 49500FH

I: 7100FC

 35900FH

-

N 572107-02-2A-S 540/640 N/A Special detailed inspection (Ultrasonic) of outer wing front spar AFT

face from ribs 1 to 7.Note : This task is an alternative to 572107-01-2A-S

T: 9900FC

49500FH

I: 7400FC

37000FH

572107 -

572108-01-4A-S 540/640 540/640 CB, 

DB

Detailed inspection of outer wing front spar AFT face from ribs 7 to 9. T: 19100FC

95500FH

I: 7000FC

35400FH

-

572109-01-3A-S 540/640

550/650

540/640 EB, FB, GB, HB

Detailed inspection of outer wing front spar AFT face from ribs 9 to17.

T: 8500FC

 42800FH

-

550/650 FB, GB, HB (

550/650 AB, BB, CB

17. 42800FH

I: 4500FC

 22600FH

(

572109-01-4A-S 540/640

550/650

540/640 EB, FB, GB, HB550/650 AB, BB, CB

Detailed inspection of outer wing front spar AFT face from ribs 9 to17.

T: 8500FC

 42800FH

I: 3800FC

 19200FH

-(

572111-01-5A-S 571/671 N/A Detailed inspection of outer wing rear spar AFT face and attachment 

angle from rib 1 to 3.

T: 23000FC

115200FH

I: 1700FC

8600FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572115-01-4A-S 575/675 575/675 DB Detailed inspection of outer wing rear spar aft face splice plate at rib 

10. 

T: 27000FC

 135000FH

I: 6000FC

 30100FH

-

572116-01-1A-S 571/671

540/640

540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar at 

selected bolt locations, for attachment of MLG FWD pick up fitting and MLG rib 5 AFT of rear spar, 31 holes, LH/RH.

T: 12800FC

 52200FH

I: 5600FC

 28300FH

572116 -

P

572117-01-7A-S 540640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 to 

3. 

T: 20000FC

 100400FH

I: 7000FC

 35000FH

-(SP(

572117-01-8A-S 540640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 to 

3. 

T: 20000FC

 100400FH

I: 5700FC

 28600FH

-(So(

572118-01-5A-S 540640 540/640 AB 572118 01 5A S 540640 540/640 AB, Detailed inspection of outer wing rear spar forward face from ribs 3 to T: 19800FC -

BB

Detailed inspection of outer wing rear spar forward face from ribs 3 to

6. 

T: 19800FC

 99500FH

I: 7300FC

 36500FH

(SP(

572118-01-6A-S 540640 540/640 AB, 

BB

Detailed inspection of outer wing rear spar forward face from ribs 3 to 6. 

T: 19800FC

 99500FH

I: 5900FC

 29700FH

-(So(

572119-01-7A-S 540640 540/640 BB, 

CB, DB

Detailed inspection of outer wing rear spar FWD face from ribs 6 to 10.

T: 22200FC

111400FH

I: 11400FC

52200FH

-(SP(

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572119-01-8A-S 540640 540/640 BB, 

CB, DB

Detailed inspection of outer wing rear spar FWD face from ribs 6 to 10.

T: 22200FC

111400FH

I: 9200FC

46100FH

-(So(

572120-01-4A-S 540640 540/640 EB to 

HB

Detailed inspection of outer wing rear spar FWD face from ribs 10 to 14.

T: 22100FC

110500FH

I: 9900FC

49500FH

-

572122-01-2A-S 540/640

571/671

540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar at 

selected bolt locations for attachment of MLG FWD pick-up fitting and MLG rib 5 AFT of rear spar, 26 holes, LH/RH.

T: 13800FC

52200FH

I: 5600FC

28300FH

572122 -

P

572137-01-4A-S 540/640 540/640 AB, 

BB,CB

Detailed inspection of outer wing bottom skin butt strap at STR 8 from ribs 1 to 9.

T: 13600FC

52200FH

I: 4500FC

22500FH

-

572138-01-4A-S 540/640 540/640 DB to Detailed ins 572138 01 4A S 540/640 540/640 DB to pection of outer wing bottom skin butt strap at STR 8 from T: 18500FC -

HB

Detailed inspection of outer wing bottom skin butt strap at STR 8 from

ribs 9 to 14.

T: 18500FC

92800FH

I: 4600FC

23200FH

572141-02-2A-S 540/640 540/640 AB to 

HB

Special detailed inspection (HFEC) of outer wing bottom skin around manhole surrounds between ribs 2 and 14, LH and RH wings.

T: 10400FC

52000FH

I: 8100FC

40900FH

572141 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

R 572142-01-4A-S 500/600

530/630

540/640 GB, HBFlap Track 3 fairing brackets removed.

Special detailed inspection (Ultrasonic) of outer wing bottom skin lower surface at attachment to stringers 9 and 12 adjacent to access door cutouts from ribs 1 to 14.

T: 20700FC

 103500FH

I: 6900FC

 34900FH

 572142 -

R 572143-01-4A-S 500/600 N/A General visual inspection of outer wing top skin upper surface at 

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to 14.Note : This task is an alternative to task 572143-02-3A-S.

T: 14500FC

 72800FH

I: 3440FC

 17200FH

-

572143-02-3A-S 500/600 N/A Detailed inspection of outer wing top skin upper surface at 

attachment to front spar from ribs 1 to 14 and rear spar from ribs 7 to 14.Note : This task is an alternative to task 572143-01-4A-S.

T: 14500FC

 52200FH

I: 9100FC

 45500FH

-

572144-01-4A-S 500/600 N/A Detailed inspection of outer wing top skin upper surface at 

attachment to rear spar from ribs 1 to 7.

T: 17300FC

 86500FH

I: 3050FC

 15400FH

-

R 572145-01-4A-S 500/600 N/A General visual inspection of outer wing top skin upper surface at 

attachment to ribs and STRs from ribs 1 to 14, front spar to rear spar (excluding skin reinforcing at pylon).

T: 13300FC

 66900 FH

I: 4130FC

 20600FH

-

572147-01-6A-S 540/640 540/640 CB, 

DB

Special detailed inspection (X-Ray) of outer wing top skin and external and internal reinforcings in areas of ribs 8 and 9, LH and RH wings.

T: 24900FC

 124500FH

I: 5700FC

 28800FH

572147 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

R 572153-01-2A-S 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR540/640 CB, DB

Special detailed inspection (X-Ray) of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-02-2A-S

T: 11100FC

 52200FH

I: 7000FC

 35400FH

 572153 -

(SP(

R 572153-01-3A-S 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR540/640 CB, DB

Special detailed inspection (X-Ray) of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-02-3A-S.

T: 11100FC

 52200FH

I: 6600FC

 33200FH

 572153 -

(So(

R 572153-02-2A-S 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 

473/483 BL

Detailed inspection of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task

T: 11100FC

 52200FH

I: 7000FC

 35400FH

-(SP

473/483 BL (474/484 BR

Note : This task has to be performed at the same time as task

572153-01-2A-S.

(

R 572153-02-3A-S 500/600

471/481473/483

471/481 AL, BL472/482 AR, BR 473/483 BL474/484 BR

Detailed inspection of outer wing bottom skin lower surface reinforcing at ribs 8 and 9 and adjacent skin, including skin covered by pylon fairings.Note : This task has to be performed at the same time as task 572153-01-3A-S.

T: 11100FC

 52200FH

I: 6600FC

 33200FH

-(So(

572157-01-2A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front spar from ribs 1 to 10 and rear spar from ribs 3 to 10 excluding area covered by pylon fairing and MLG reinforcing.

T: 11600FC

 52200FH

I: 3100FC

 15800FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572159-01-4A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to rear spar from ribs 1 to 3.

T: 23200FC

 116000FH

I: 3800FC

 19000FH

-

R 572161-01-2A-S 500/600 N/A General visual inspection of outer wing bottom skin lower surface at 

attachment to ribs and stringers from ribs 1 to 10, excluding area covered by pylon fairing and MLG reinforcing.

T: 18000FC

 90400FH

I: 3800FC

 19200FH

-(SP(

R 572161-01-3A-S 500/600 N/A General visual inspection of outer wing bottom skin lower surface at 

attachment to ribs and stringers from ribs 1 to 10, excluding area covered by pylon fairing and MLG reinforcing.

T: 18000FC

 90400FH

I: 3400FC

 17400FH

-(So(

572162-01-2A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

spanwise skin joint at STR 8, from ribs 1 to 20, excluding areas covered by pylon and flap track fairings.

T: 9900FC

 49600FH

I: 1700FC

 8500FH

-

R 572163-01-6A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front and rear spars from ribs 10 to 14 excluding area covered by flap track fairing.

T: 14900FC

 74500FH

I: 4100FC

 20500FH

-

572164-01-2A-S 500/600 N/A Detailed inspection of outer wing bottom skin at MLI from ribs 1 to 2 

and water drain valves from ribs 1 to 28.

T: 11100FC

 52200FH

I: 3200FC

 16200FH

-

572169-01-2A-S 500/600

530/630540/640

532/632 AB, BB540/640 AB, BB

Special detailed inspection (X-Ray) of outer wing bottom skin covered by MLG reinforcing doubler and adjacent skin.

T: 11200FC

 52200FH

I: 6700FC

 33500FH

572169 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572183-01-5A-S 470/480 473/483 BL, 

474/484 BR,Engine and attach link removal.

Special detailed inspection (HFEC) of wing to pylon AFT attachment fitting.

T: 10900FC

 54800FH

I: 9500FC

 47900FH

572183 -

(SP(

572183-01-6A-S 470/480 473/483 BL, 

474/484 BR,Engine and attach link removal.

Special detailed inspection (HFEC) of wing to pylon AFT attachment fitting.

T: 10900FC

 54800FH

I: 4700FC

 23800FH

572183 -

(So(

572185-01-2A-S 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface around fuel pump apertures from ribs 1 to 2.

T: 8100FC

 40800FH

I: 5400FC

 27400FH

572185 -

572187-01-2A-S 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface at stringer runouts of stringers 1, 2, 3, 4, 5 (at ribs 2, 5, 7, 11 and 13 respectively) and of stringer 14 (at rib 8).

T: 10300FC

 51700FH

I: 6400FC

 32000FH

572187 -

572502-01-5A-S 550/650 550/650 FB to 

JBNut removal at selected locations

Special detailed inspection (HFEC and Ultrasonic) of outer wing front spar AFT face from ribs 19 to 23.

T: 11100FC

 52200FH

I: 3300FC

 16700FH

572502 -

572505-01-4A-S 550/650 550/650 DB, 

EB, KB, LB, MB, NB, PB. 

Detailed inspection of outer wing front spar aft face from ribs 17 to 19 and ribs 23 to 28.

T: 8800FC

 44100FH

I: 4800FC

 24100FH

-

572512-01-4A-S 550/650 550/650 AB to 

PB

Detailed inspection of outer wing rear spar FWD face from ribs 14 to 28.

T: 26600FC

 133400FH

I: 8000FC

 40000FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572526-01-2A-S 550/650 550/650 FB Special detailed inspection (X-Ray) of outer wing top skin stringer 

joints from STRs 9 to 15, between ribs 19 and 20.

T: 27000FC

 135300FH

I: 4400FC

 22400FH

572526 -

572535-01-6A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front spar from ribs 14 to 17 and ribs 21 to 23.

T: 19600FC

 98400FH

I: 4200FC

 21000FH

-

572536-01-3A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to front spar from ribs 17 to 21 and 23 to 28

T: 9200FC

 46000FH

I: 4100FC

 20800FH

-

572538-01-4A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to rear spar from ribs 14 to 28.

T: 19700FC

 98800FH

I: 7000FC

 35300FH

-

572539-01-4A-S 530/630 534/634 AB, 

BB 

Detailed inspection of outer wing bottom skin lower surface at attachment to ribs and stringers in area covered by flap track fairings 

T: 22300FC

 111500FH

-

BB

535/635 AB, BB

attachment to ribs and stringers in area covered by flap track fairings

No. 4 and 5.

111500FH

I: 5700FC

 28600FH

R 572541-01-2A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface at 

attachment to ribs and stringers from ribs 14 to 28, from front to rear spar.

T: 18000FC

 90400FH

I: 2000FC

10000FH

-

R 572542-01-4A-S 500/600 N/A Detailed inspection of outer wing bottom skin at MLI, slat track and 

jack drain holes from ribs 2 to 28.

T:14600FC

73300FH

I:4800FC

24000FH 

-(

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

572542-01-5A-S 500/600 N/A Detailed inspection of outer wing bottom skin at MLI, slat track and 

jack drain holes from ribs 2 to 28.

T:29300FC

146600FH

I:4800FC

24000FH 

-(

R 572544-01-2A-S 550/650 550/650 EB, 

FB

Special detailed inspection (X-Ray) of outer wing bottom skin stringer joints inboard of rib 19 and from rib 19 to rib 20.

T: 14700FC

73500FH

 I: 4800FC

 24200FH

572544 -

R 572548-01-6A-S 550/650 550/650 AB to 

FB

Detailed inspection of outer wing bottom skin butt strap at stringer 8 from ribs 14 to 20.

T: 15100FC

75600FH

 I: 9200FC

 46100FH

-

R 572549-01-4A-S 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skin 

lower surface at stringer runouts of stringers 6, 7 and 8b at ribs 16, 19 and 22.

T: 14800FC

74200FH

 I: 3300FC

 16700FH

572549 -

R 572553-01-6A-S 550/650 550/650 AB, 

AT,

Special detailed inspection (HFEC) of outer wing bottom skin around access door cutouts, from ribs 14 to 15.

T: 17500FC

87800FH

572553 -

AT,Rubber ring removal

access door cutouts, from ribs 14 to 15. 87800FH

I: 15100FC

75500FH

572554-01-4A-S 550/650 550/650 KB Special detailed inspection (HFEC) of outer wing bottom skin upper 

surface at stringer runout of stringer 13b at rib 23.

T: 22300FC

 111800FH

I: 4600FC

 23000FH

572554 -

572557-02-2A-S 550/650 550/650 BB to 

FB

Special detailed inspection (HFEC) of outer wing bottom skin around access door cutouts from ribs 15 to 20.

T: 14500FC

 52200FH

I: 12100FC

 52200FH

572557 -

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

R 572561-01-2A-S 550/650 550/650 GB to 

PB

Special detailed inspection (HFEC) of outer wing bottom skin access doors and skin around access door cutouts from ribs 20 to 28.

T: 15100FC

75600FH

 I: 9200FC

 46300FH

572561 -

572565-01-1A-S 550/650 N/A Special detailed inspection (X-Ray and Ultrasonic) of outer wing 

bottom skin joint strap in area of rib 20.

T: 12100FC

 52200FH

I: 3400FC

 17100FH

 572565 -

R 574105-01-2A-S 512/612 Slats 

extended

Detailed inspection of outer wing inboard fixed leading edge "D" noseskin including jack and track cutouts.

T: 12700FC

 63900FH

I: 9500FC

 47500FH

-

R 574113-01-2A-S 523/623 Slats 

extended

Detailed inspection of outer wing center fixed leading edge "D" noseskin including jack and track cutouts.

T: 12700FC

 63900FH

I: 9500FC

 47500FH

-

R 574121-01-2A-S 524/624 Slats 

extended

Detailed inspection of outer wing outboard fixed leading edge "D"nose skin including jack, track and antiicing telescopic duct cutouts.

T: 12700FC

 63900FH

-

extended nose skin including jack, track and antiicing telescopic duct cutouts. 63900FH

I: 9500FC

 47500FH

574129-01-3A-S 500/600 N/A Detailed inspection of outer wing bottom skin lower surface FWD of 

front spar from root to tip.

T: 11500FC

 57500FH

I: 1900FC

 9500FH

-

R 575129-01-2A-S 500/600 N/A Detailed inspection of outer wing bottom wing skin lower surface at 

attachments to the trailing edge between ribs 5 and 11.

T: 13800FC 

 69200FH 

I: 1600FC

 8200FH

-

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
Rev 

Code Task reference Zone Access Task description Th. Int. NTM Ref. 

A310

Airworthiness Limitation Items

575131-01-6A-S 575/675 575/675 CB, 

DBRemoval of anti rotation locking device (only for Post Mod 13297)

Detailed inspection of outer wing bottom skin upper surface aft of rear spar in area of pylon fairing.

T: 19500FC

 97700FH

I: 7800FC

 39300FH

-(SP(

575131-01-7A-S 575/675 575/675 CB, 

DBRemoval of anti rotation locking device (only for Post Mod 13297)

Detailed inspection of outer wing bottom skin upper surface aft of rear spar in area of pylon fairing.

T: 19500FC

 97700FH

I: 6900FC

 34900FH

-(So(

R 575141-01-5A-S 581/681

591/691

Flap extended, 581/681 AB to JB, 591/691 

Detailed inspection of outer wing bottom skin upper and lower surfaces aft of rear spar between ribs 11 and 28 including areas covered by flap track fairings.

T: 15200FC

76000FH

 I: 6600FC

 33200FH

-

,

AB, BB, cable steady bracket removal at track 5.

Issue: 8 - OCTOBER 2010Ref: 95A.1309/07

ALI Section E

© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 ALI SUMMARY OF CHANGES PAGE: APXA- 1 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

APPENDIX A : SUMMARY OF CHANGES

1- GENERAL

Compared to A310 ALI Document issue 7, the ALI issue 8 has the following changes: 

• Introduction has been revised 

• The Inspections requirements section introduces updated DT ALI requirements due 

to modifications/In-service experience 

• The illustrations are revised 

2- SUMMARY OF CHANGES – AIRWORTHINESS LIMITATION ITEMS:

Rev 

Code Task reference SoC 

Section D

R 531294-01-1A Access revised 

R 531305-01-1A Access revised 

R 531305-02-1A Access revised 

R 531318-01-2A Acces revised 

R 531359-01-1A Access revised 

R 531371-01-1A Description note added 

Threshold revised 

Interval revised 

N 531371-02-1A New Task 

N 531372-01-1A New Task 

N 531372-02-1A New Task 

N 531373-01-1A New Task 

N 531373-02-1A New Task 

N 531529-01-1A New task 

N 531529-02-1A New task 

N 531530-01-1A New task 

N 531530-02-1A New task 

R 531574-01-1A Note in Task description 

deleted 

R 531582-01-1A Access updated 

R 531582-01-2A Access updated 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 ALI SUMMARY OF CHANGES PAGE: APXA- 2 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

R 531612-01-1A Description note added 

Threshold revised 

Interval revised 

N 531612-02-1A New task 

R 531704-01-A Access revised 

R 531704-02-1A Access revised 

R 531716-01-1A Description revised 

R 531716-02-1A Description revised 

R 531919-01-1A Description revised 

R 553019-01-1A Threshold revised 

R 571041-01-2A Access are revised 

R 571041-01-3A Access are revised 

R 572104-01-3A Threshold and Interval 

revised 

R 572104-01-4A Threshold and Interval 

revised 

R 572107-01-2A Note added in the task 

description 

N 572107-02-2A New task 

R 572142-01-3A Zone revised 

Access revised 

R 572142-01-4A Zone revised 

Access revised 

R 572153-01-1A Zone revised 

R 572153-01-2A Zone revised 

R 572153-01-3A Zone revised 

R 572153-02-1A Zone revisedAccess 

revised 

R 572153-02-2A Zone revised 

Access revised 

R 572153-02-3A Zone revised 

Access revised 

R 572161-01-2A Threshold figure revised 

R 572161-01-3A Threshold figure revised 

R 572541-01-2A Threshold figure revised 

R 572542-01-4A Threshold figure revised 

R 572545-01-2A Interval figures revised 

R 572546-01-2A Threshold and Interval 

figures revised 

R 572558-01-3A Access revised 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 ALI SUMMARY OF CHANGES PAGE: APXA- 3 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

R 574105-01-1A Inspection level revised 

R 574105-01-2A Inspection level and 

Threshold figures revised 

R 574113-01-1A Inspection level and 

Threshold figures revised 

R 574113-01-2A Inspection level and 

Threshold figures revised 

R 574121-01-1A Inspection level revised 

R 574121-01-2A Inspection level and 

Threshold figures revised 

R 712102-01-1A Threshold and interval 

revised 

R 712102-01-2A Threshold and interval 

revised 

Section E

R 571041-01-3A-S Access are revised 

R 572104-01-4A-S Threshold and Interval 

figures revised 

R 572107-01-2A-S Addition of Note in Task 

description column 

N 572107-02-2A-S New task 

R 572142-01-4A-S Zone revisedAccess 

revised 

R 572143-01-4A-S Threshold figure revised 

R 572145-01-4A-S Threshold figure revised 

R 572153-01-2A-S Zone revised 

R 572153-01-3A-S Zone revised 

R 572153-02-2A-S Zone revised

Access revised 

R 572153-02-3A-S Zone revised

Access revised 

R 572161-01-2A-S Threshold and Interval 

figures revised 

R 572161-01-3A-S Threshold and Interval 

figures revised 

R 572163-01-6A-S Threshold figure revised 

R 572541-01-2A-S Threshold figure revised 

R 572542-01-4A-S Threshold figure revised 

R 572544-01-2A-S Threshold figure revised 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 ALI SUMMARY OF CHANGES PAGE: APXA- 4 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

R 572548-01-6A-S Threshold figure revised 

R 572549-01-4A-S Threshold figure revised 

R 572553-01-6A-S Threshold and Interval 

figures revised 

R 572561-01-2A-S Threshold figure revised 

R 574105-01-2A-S Inspection level and 

Threshold figures revised 

R 574113-01-2A-S Inspection level and 

Threshold figures revised 

R 574121-01-2A-S Inspection level and 

Threshold figures revised 

R 575129-01-2A-S Threshold figure revised 

R 575141-01-5A-S Threshold figure revised 

Appendix D

N 531372 New illustration 

N 531373 New illustration 

N 531529 New illustration 

N 531530 New illustration 

R 531612 Illustration revised 

R 531633 Illustration revised 

R 531716 Illustration revised 

R 572144 Illustration revised 

R 575141 Illustration revised 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 ABBREVIATIONS PAGE: APXB - 1 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

APPENDIX B : ABBREVIATIONS

ABBREVIATION MEANING 

AD Airworthiness Directive 

ALI Airworthiness Limitation Item 

ALS Airworthiness Limitations Section 

AMM Aircraft Maintenance Manual 

ATA Air Transport Association 

CPCP Corrosion Prevention and Control Program 

D Deleted 

EASA European Aviation Safety Agency 

FAR Federal Aviation Regulations 

FC Flight Cycle 

FH Flight Hour 

FR Frame 

HFEC High Frequency Eddy Current (NDT inspection method) 

HTP Horizontal Tail Plane 

JAR Joint Aviation Requirements 

LOV Limit Of Validity 

MOD Modification 

MPD Maintenance Planning Document 

MRBR Maintenance Review Board Report 

MSN Manufacturer Serial Number 

N New 

N/A Not Applicable 

NDT Non Destructive Test 

NTM Non Destructive Test Manual 

R Revised 

RAS Repair Design Approval Sheet 

ROR Record Of Revisions 

SB Service Bulletins 

SRM Structural Repair Manual 

SSI Structural Significant Item 

STC Supplemental Type Certificate 

STR Stringer 

THS Trimmable Horizontal Stabilizer 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 ABBREVIATIONS PAGE: APXB - 2 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

ABBREVIATION MEANING 

TPS Temporary Protection System 

TOC Table Of Contents 

US UltraSonic (NDT inspection method) 

WV Weight Variant 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 TERMS AND DEFINITIONS PAGE: APXC - 1 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

APPENDIX C : TERMS AND DEFINITIONS

TERM DEFINITION 

AIRCRAFT 

STRUCTURE 

Consists of all load-carrying members including wings, fuselage, empennage, 

engine mountings, landing gear, flight control surfaces, and related points of 

attachment. The actuating portions of items such as landing gear, flight controls, 

doors, etc. are treated as systems components. Attachments of the actuators to 

the airframe are treated as structure. 

AIRWORTHINESS 

LIMITATION ITEMS 

(ALI) 

They are all those parts of the structure whose failure could result in catastrophic 

failure of the airplane and that are designed to fatigue and damage-tolerance 

concept. 

CALENDAR TIME 

(Cal) 

In Years (Ye), in Months (Mo), etc... must be counted from the date of initial entry 

into service, unless otherwise stated. Storage, maintenance, etc... do not freeze 

calendar time accumulation. 

CONTINUED 

AIRWORTHINESS 

Is the process of ensuring that the level of airworthiness guaranteed by TC is 

maintained for each individual aircraft at the time of its entry into service and 

during all its service life. 

DAMAGE 

TOLERANCE 

CONCEPT 

The damage-tolerance evaluation of structure is intended to ensure that should 

serious fatigue, corrosion, or accidental damage occur within the operational life 

of the aeroplane, the remaining structure can withstand reasonable loads without 

failure or excessive structural deformation until the damage is detected. 

Damage-tolerance design is required, unless it entails such complications that an 

effective damage-tolerant structure cannot be achieved within the limitations of 

geometry, inspectability, or good design practice. Under these circumstances, a 

design that complies with the fatigue evaluation (safe life) requirements is used. 

DESIGN SERVICE 

GOAL Is a reference figure selected for the design and certification of the aircraft. 

EXTENDED 

SERVICE GOAL Is an extension of the DSG. 

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

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

INTERVAL The maximum period expressed in usage parameters between the completion of 

a task and its next due accomplishment. 

LANDING (LDG) Is an operation of an aircraft touching the runaway and coming to a full stop or 

performing a "touch and go". 

LIMIT OF VALIDITY 

(LOV) 

Is the period of time, expressed in appropriate units (e.g. flight cycles) for which it 

has been shown that the established inspections and replacement times will be 

sufficient to allow safe operation and in particular to preclude development of 

widespread fatigue damage 

THRESHOLD 

The maximum period of time expressed in usage parameters between the first 

flight of the aircraft, and the first due completion of the task. 

Subsequent accomplishment deadlines are obtained by adding the repeat interval 

and its multiples to the threshold. 

TOUCH AND GO A ‘Touch and go’ is a landing in which an aircraft touches the runway and does 

not come to a full stop prior to commencing an additional flight. 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 INSPECTION REPORTING PAGE: APXE - 1 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

APPENDIX E : INSPECTION REPORTING

SUMMARY REPORT OF COMPLETED INSPECTIONS 

 Operator : Inspection agency : 

 Date of inspection : A/C flight hours : 

 A/C series : A/C flight cycles : 

 A/C MSN : A/C registration : 

ALI N° Inspection method Finding Defect Report 

reference 

Visual NDT 

method 

Nil Yes 

 

 Date : 

Issue : Approved : Page : 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 INSPECTION REPORTING PAGE: APXE - 2 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

 AIRBUS Ref :

 Structural Inspection Report 

A300 [ ] A310 [ ] A300-600 [ ] A319 [ ] A320 [ ] A321 [ ] A330 [ ] A340 [ ] 

Date of inspection : 

Operator Code : 

Station : 

MSN : 

Registration : 

A/C FC : 

A/C FH : 

Inspection: Task reference : ...............................................................................(if available) 

Inspection method used : General Visual [ ] 

Detailed Visual [ ] 

Ultrasonic [ ] 

Magnetic Particle [ ] 

X-Ray [ ] 

Eddy Current [ ] 

Ultrasonic [ ] 

Other [ ] 

Reason for reporting/recording :

Corrosion [ ] 

Crack [ ] 

Nil finding [ ] 

 Level 

1 [ ] 2 [ ] 3 [ ] Disbonding [ ] 

Composite damage [ ] 

Other [ ] 

 Temporary 

Protection 

System (TPS) 

Visible : 

YES [ ] NO [ ] 

Location of Damage :

Zone number : 

ATA 100 code : 

Between stringer : 

Between frame : 

Between rib : 

and : 

and : 

LH [ ] / RH [ ] 

LH [ ] / RH [ ] 

Part Concerned : 

Spar / Stringer [ ] 

Bracket / Shear tie [ ] 

Frame [ ] 

Other [ ] .................. 

Chord [ ] 

Web [ ] 

Skin [ ] 

Doubler [ ] 

Rib [ ] 

Bulkhead [ ] 

Fitting [ ] 

Time since last maintenance task for concerned part : ......... months ..................FC ..............FH 

Repair Approval Sheet (RAS) number (if available) : 

Extend of damage : (ref. to SRM 51.10.13/51.11.13 for criteria) 

Length : 

Width : 

Depth : 

mm [ ] inches [ ] 

Description of damage / cause of damage / corrective action : 

(Additional photograph / Details of findings to be provided if available) 
CUSTOMER SERVICES

A310 AIRWORTHINESS LIMITATION ITEMS

ISSUE: OCTOBER 2010 DT ALI REQUIREMENT DELETED PAGE: APXF - 1 

©AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. 

APPENDIX F : DT ALI REQUIREMENT DELETED

In the following table all deleted requirement of the ALI are listed. Those tasks will not longer 

be listed in the modification, standard, or alternative sections of this document (Section C, D 

and E). 

NOTE: 

All tasks which were deleted during this ALI revision are marked in the 'Revision Code' column 

by a 'N'. 

Rev 

Code

Task 

Reference Remark

Section D

 531298-02-1A Task deleted

 531298-02-2A Task deleted

 531542-01-2A Task deleted

 531553-01-3A Task deleted

 531588-01-4A Task deleted

 531588-01-6A Task deleted

 551004-01-1A Task deleted

 551004-01-2A Task deleted

 551010-01-1A Task deleted

 551010-01-2A Task deleted

 551016-02-1A Task deleted

 551024-01-2A Task deleted

 551024-02-1A Task deleted

 551038-01-1A Task deleted

 551088-01-1A Task deleted

 571006-01-2A Task deleted

 571022-01-2A Task deleted

Section E

N 572179-01-4A-S Task deleted