# AIRBUS

Customer Services

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

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

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

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

performing the tasks described hereunder and prov ided that any recipient of such document shall

comply with the conditions herein) without the express written consent of AIRBUS SAS. This

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

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

# 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 requiremen ts ..............

.............................................. ......... 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 CO MPLIANCE DEMONSTRATION ............................................................ 1 -B

1. General ....................................................................................................................... .................................. 1 

# -B

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

3. Reporting

............................................................................................................................... ....................... 2 -B

4. Production/Repair concessions and Alternative Mean s Of Compliance ............................................... 2 

# -B

5. Modifications/repairs not originati ng 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 UTILIZ ATION REQUIREMENTS

................. ............ 1 -E

APPENDIX A : SUMMARY OF CHANGES

................. ............... .................................................. ......... APXA 

# -1

APPENDIX B : ABBREVIATIONS ......

.................................... ............... ............................ ............... ..... APXB-1

APPENDIX C : TERMS AND DEFINITION S .................

................................................................ ......... APXC- 1

APPENDIX D : ALI ILLUSTRATIONS ................................................................................................

... APXD- 1

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

# 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 ar e 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 In terval as quoted in Section D or E

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

# SECTION A: INTRODUCTION

1. GENERAL

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

Compliance with the requirem ents 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 airworthi ness limitations arising fr om fatigue and damage tolerance

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

also contains the fatigue related structural inspections arising fr om the Widespread Fatigue

Damage (WFD) evaluation.

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

elements or assemblies which contribute signi ficantly to carrying flight, ground, or

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

Corrosion Level 1 is defined as follows:

− Corrosion damage that does not require st ructural reinforcement or replacement.

or

− Corrosion occurring between successive inspec tions 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 (C PCP) 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 per formed with the same inspection level, as

frequently, or more frequently, than the inspec tion 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 fo r which modifications must be embodied at the

stated embodiment times.

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# b) Inspection requirements

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

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

It also contains the fatigue related structur al inspections arisi ng from the Widespread

Fatigue Damage (WFD) evaluation.

c) Alternative Special R ange Utilization requirements

Inspection requirements of section D are applic able 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 Cy cles (FC) or Flight Hours (F H), 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 t he aircraft type/series/model/weight variant

group and modification status for which the task is applicable. Examples are given below:

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© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document. APPLICABILITY A/C MODEL

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

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

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

-300 : This requirement is app licable 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 no t 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 whic h 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 applicabl e 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 herei n allow operation up to the Limit Of Validity

(LOV) in FC or FH whichever occurs first. (R efer 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 applicabi lity, thresholds are counted from first

flight.

- For FC or FH tasks with MOD applicabili ty, 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 prov ided, 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 peri od (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 c ounted 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 (T PS) 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 ar e applicable to the undamaged and unrepaired ALI.

Damage has to be evaluated and repaired in acco rdance 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 identif ied 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 corrosi on 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 ORIGINAT ING 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 a ffects the content of the ALI, the Operator is

responsible for obtaining approval by the relev ant Airworthiness Authority for any necessary

adaptations of the limitations.

6. INTERCHANGEABLE PARTS POLICY

Where a part is removed from one aircraft and fitte d 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 concer ning 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 acco rdance 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 solu tion 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 perfo rmed. 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 suppor ting documentation, such as SBs or NTM,

where the procedure necessary for task ac complishment is provided (alternative

procedures must be approved by Airbus).

“Applicability”:

This column indicates the aircraft types/s eries/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 Vi sual 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” r equirement exists

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

A/C utilization but they are optim ized for A/C operated below 4FH/FC.RevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. Note521101-01-1A 831/841 831/841 General visual inspection of door stop assemblies on FWDpassenger/crew doors, LH/RH.T: 12000FCI: 12000FCALL1521103-01-1A 800 N/AGeneral visual inspection of FWD passenger/crew door skin,external surface, LH/RH.T: 3000FCI: 3000FCALL1521301-01-1A 833/843 N/AGeneral visual inspection of AFT passenger/crew door skin, externalsurface, LH/RH.T: 3000FCI: 3000FCALL1521303-01-1A 833/843 833/843 General visual inspection of door stop assemblies on AFTpassenger/crew doors, LH/RH.T: 18000FCI: 12000FCALL1522201-01-1A 834/844 N/AGeneral visual inspection of emergency exit skin, external surface,LH/RH.T: 18000FCI: 5000FCALL1522203-01-1A 834/844 833/844 General visual inspection of door stop assemblies on emergencyexits, LH/RH.T: 18000FCI: 12000FCALL1523101-01-1A 811 N/AGeneral visual inspection of FWD cargo compartment door skin,external surface.T: 8100FCI: 8100FCALL1523103-01-1A 811 811Special detailed inspection (HFEC) of actuator attach fitting of FWDcargo compartment door at FR 22A.T: 6000FCI: 6000FC523103 ALL523105-01-2A 811 811132 AR t LRDetailed inspection of hinge arms of FWD cargo compartment doort FR 20A t 25A (10 l ) i fl dii dj t t t kiT: 30000FCI 6000FCALLA310Airworthiness Limitation Items132 AR to LR at FR 20A to 25A (10 places) in flange radii adjacent to outer skin. I: 6000FC523109-02-1A 811 811General visual inspection of locking hooks of FWD cargocompartment door (10 places).T: 18000FCI: 6000FCALL1523201-01-1A 812 N/AGeneral visual inspection of AFT cargo compartment door skin,external surface.T: 8100FCI: 8100FCALL1523203-01-1A 812 812152 AR to HRDetailed inspection of hinge arms of AFT cargo compartment doorfrom FR 60 to 63 (7 places) in flange radii adjacent to outer skin.T: 18000FCI: 3000FCALL523204-01-1A 812 812Special detailed inspection (HFEC) of actuator attach fitting of AFTcargo compartment door at FR 61 A.T: 6000FCI: 6000FC523204 ALL523205-02-1A 812 812General visual inspection of locking hooks of AFT cargocompartment door (7 places).T: 18000FCI: 6000FCALL1Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 3 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items523207-01-1A 812 812Detailed inspection of hinge end aft cargo compartment door at FR60 to FR 63 ( 7 places ) especially in flange radius adjacent to outerskin.T: 40000FCI: 1500FC-200523207-01-2A 812 812Detailed inspection of hinge end aft cargo compartment door at FR60 to FR 63 ( 7 places ) especially in flange radius adjacent to outerskin.T: 35000FCI: 1500FC-300523401-01-1A 813 N/AGeneral visual inspection of bulk cargo compartment door skin,external surface.T: 550FCI: 550FCALL1523403-01-2A 813 813Detailed inspection of door stop assemblies at bulk cargocompartment door.T: 18000FCI: 6000FCALL523403-01-3A 813 813Detailed inspection of door stop assemblies at bulk cargocompartment door.T: 40000FCI: 1000FC-200523403-01-4A 813 813Detailed inspection of door stop assemblies at bulk cargocompartment door.T: 35000FCI: 1000FC-300523601-01-1A 835 N/ADetailed inspection of main deck cargo door skin, external surface.Note: this task is an alternative to 523601-02-1AT: 8500FCI: 8500FC-200C523601 02 1A835AG l i l i ti f i d k d ki t lT 1960FC200C1523601-02-1AN/General visual inspection of main deck cargo door skin, externalsurface.Note: this task is an alternative to 523601-01-1AT: 1960FCI: 1960FC-200C1523603-01-1A 835 835lining,Insulationdisplaced asrequiredDetailed inspection of main deck cargo door actuator attach fittingsincluding riveting.T: 6000FCI: 6000FC-200Cin cargoconfiguration523608-01-1A 835 835835 AL, BL, CLDetailed inspection of locking mechanism, attach fittings and supportstructure of main deck cargo door at all frames from longerons 8 to 9(8 places).T: 12000FCI: 12000FC-200C523609-01-1A 835 835835 AL, BL, CLDetailed inspection of locking hooks and bolts of main deck cargodoor.Note: Refer to AMM 523600 P605 2B for torque check.T: 12000FCI: 12000FC-200CIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 4 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items523611-01-2A 835 835,liningDetailed inspection of mechanical linkage of main deck cargo dooractuator unit.T: 6000FCI: 6000FC-200Cin cargoconfiguration524103-01-1A 121/122 121BL, floorpanel on doorDetailed inspection of avionics compartment access door, internalstructure between FR7 and FR10T: 40000FCI: 24000FC-200531101-01-3A 211/212 419VU &420VUdisplaced (iffitted).linings,glareshieldlateral 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 531101-02-4AT: 33000FCI: 4700FCPRE 3632531101-01-4A 211/212 419VU &420VUdisplaced (iffitted).linings,glareshieldlateral 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 531101-02-6AT: 25000FCI: 5300FCPOST 3632531101-02-3A 211/212 419VU &420VUdisplaced (iffitted).linings,glareshieldSpecial detailed inspection (HFEC) of fuselage internal structurefrom FR2 to FR4, windshield frame lower section and closing panel,LH/RH.Note: this task could be done at the same time as task 531101-01-3AT: 33000FCI: 8600FC531101 PRE 3632glareshieldlateral covers.3ANote: this task is an alternative to 531101-02-4A531101-02-4A 211/212 419VU &420VUdisplaced (iffitted).linings,glareshieldlateral covers,bolts.Special detailed inspection (rototest) of fuselage internal structurefrom 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 531101-02-3AT: 33000FCI: 13600FC531101 PRE 3632531101-02-5A 211/212 419VU &420VUdisplaced (iffitted).linings,glareshieldlateral covers.Special detailed inspection (HFEC) of fuselage internal structurefrom 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 531101-02-6AT: 25000FCI: 7500FC531101 POST 3632Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 5 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531101-02-6A 211/212 419VU &420VUdisplaced (iffitted).linings,glareshieldlateral covers,bolts.Special detailed inspection (rototest) of fuselage internal structurefrom 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 531101-02-5AT: 25000FCI: 12200FC531101 POST 3632531108-01-2A 200 N/ADetailed inspection of side window rear post at FR10, externalsurface, LH/RH.T: 26000FCI: 5000FCALL531109-01-1A 211/212 lining,insulationdisplaced asrequiredsliding windowopened.Detailed inspection of cockpit internal structure, splice at theintersection between FR4 and windshield front frame and tee pick-upat junction of FR8 and FR9 with aft window upper frame, LH/RHT: 32000FCI: 7000FCPRE 3632531110-01-1A 211/212 lining,insulationdisplaced asrequiredsliding windowopened.Detailed inspection of cockpit internal structure, lower surface ofupper closing panel and splice between FR7 and front windshieldside post and tee pick-up at junction of FR8 and FR9 with aft windowupper frame, LH/RH.Note : Grace period of 500FC or 6 Months whichever occurs first.T: 18000FCI: 7000FCPOST 3632531114-01-1A 200 N/AGeneral visual inspection of fuselage skin above windshield fromFR4 to FR10, external surface, LH/RH.T: 9000FCI: 9000FCALL1531115-01-1A 100 N/AGeneral visual inspection of fuselage lower side panels from FR1 toFR10, external surface, LH/RH.T: 12000FCI: 12000FCALL1531117-01-1A 100 N/AGeneral visual inspection of fuselage bottom skin panels from FR1 toFR10, external surface, LH/RH.T: 5600FCI: 5600FCALL1531118-01-1A 100/200 N/AGeneral visual inspection of fuselage upper side skin panels belowcockpit windows, from FR1 to FR10 external surface, LH/RH.T: 10500FCI: 10500FCALL1531144-01-1A 122 121BL Detailed inspection of angle fittings between FR10 crossbeam andY=-953mm, Y=-1456mm long beams, RH side.T: 30000FCI: 18000FCALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 6 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531149-01-1A 211/212 831/841, lining,Insulationdisplaced asrequiredDetailed inspection of fuselage internal structure, angle gussetabove front windshield panels, including 3 nuts on centre postT: 40000FCI: 9500FC-200531165-01-1A 211/212 3VU, 5VUdisplaced,frontwindshieldremovedDetailed inspection of fixation bolt of FR2, lower surface of closingpanel and lower post of front windshield, LH/RH.Note: This task is an alternative to 531165-02-1AT: 40000FCI: 40000FC-200531165-02-1A 211/213 3VU, 5VUdisplacedSpecial 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 531165-01-1AT: 40000FCI: 40000FC-200531201-01-1A 200 831/841 Detailed inspection of fuselage skin and fail safe ring around fwdpassenger/crew door cutout from FR13A to FR17 and STR9 to maindeck floor level, except scuff plate area, external surface, LH/RH.T: 6700FCI: 6700FCALL531203-01-2A 200 831/841 Detailed inspection of fuselage skin and fail safe ring around fwdpassenger/crew door cutout from FR14 to FR16A, from stiffener 7 to10 t l f LH/RHT: 27000FCI: 3400FCALL10, external surface LH/RH.531204-01-1A 121/122 831/841lining, floorpanel,insulationdisplaced asrequiredDetailed inspection of fuselage internal structure, junction area atFR14 floor beam and cruciform fitting, LH/RHT: 22200FCI: 5200FCPRE 3632531204-01-2A 121/122 831/841lining, floorpanel,insulationdisplaced asrequiredDetailed inspection of fuselage internal structure, junction area atFR14 floor beam and cruciform fitting, LH/RHT: 26300FCI: 6600FCPOST 3632Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 7 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531204-02-1A 121/122 831/841lining, floorpanel,insulationdisplaced asrequiredSpecial detailed inspection (ultrasonic) of fuselage internal structure,junction area at FR14 floor beam and cruciform fitting, LH/RHT: 22200FCI: 9300FC531204 PRE 3632531204-02-2A 121/122 831/841lining, floorpanel,insulationdisplaced asrequiredSpecial detailed inspection (ultrasonic) of fuselage internal structure,junction area at FR14 floor beam and cruciform fitting, LH/RHT: 26300FCI: 11900FC531204 POST 3632531205-01-1A 211/212 831/841lining,insulationdisplaced asrequiredDetailed inspection of FR10, inner flange from side window lowersection to main deck floor, LH/RH.T: 36000FCI: 9000FCALL531206-01-2A 200 N/ADetailed inspection of fuselage skin panel from FR10 to FR11 andfrom upper corner of side window, 120 cm downwards, externalsurface, LH/RH.T: 25000FCI: 5000FCALL531207-01-2A 123/124 715, 716 to bedSpecial detailed inspection (X-Ray) of NLG bay, fuselage internalki d bl d fl t FR17 LH/RHT: 28200FCI 4000FC531207 ALLremoved skin, doublers and corner flange at FR17, LH/RH.I: 4000FC531208-01-1A 221/222 831/841floor panels,insulation, andif installed:cabin attendantseat, lavatory,galleySpecial detailed inspection (HFEC) of FR12A stiffeners at upperhorizontal flange LH/RHT: 20400FCI: 13300FC511008 POST 12662531209-01-1A 100 N/AGeneral visual inspection of fuselage skin from FR10 to FR19, belowmain deck floor level, external surface, LH/RH.T: 3500FCI: 3500FCALL1531216-01-1A 221/222 831/841 General visual inspection of door stop fittings on FR14 and FR16A,LH/RHT: 20000FCI: 4500FCPOST 11286ORPOST 112451Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 8 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531225-01-2A 221/222 N/ASpecial detailed inspection (LFEC) of skin at FR13 circumferentialjoint from STR 9 rear to STR 25, external surface, LH/RH.T: 40000FCI: 6200FC531225 -200531226-01-1A 221/222 linings,insulation,lavatory (ifinstalled) andboltsSpecial detailed inspection (rototest) of fuselage circumferential jointforward of frame 13 datum at stringer 9 fwd and aft level and abovestringer 25 at crossbeam 2 level, external surface, LH/RH.T: 40000FCI: 14000FC531226 -200531228-01-1A 211/212 linings,insulation,lavatory (ifinstalled)Detailed inspection of attachment web between FR10 and STR9,LH/RH.T: 34000FCI: 19500FCALL531229-01-1A 221/222 linings,insulation,lavatory (ifinstalled)Detailed inspection of FR11 LH side at partition wall lateral webattachment and FR12 at upper web.T: 36200FCI: 6700FC-200PRE 4803531232-01-2A 223/224 linings,insulationdisplaced asrequired,galleys andlavatoryDetailed inspection of FR12 and FR13 upper part from STR1 LH toSTR2 LH and from STR3 RH to STR5 RH.T: 32000FCI: 10000FCALLlavatory531233-01-1A 100 121DL Detailed inspection of fuselage skin external surface in area of wastewater connection box, including door cutout edges and 25 cm (10 in.)around cutout, from FR12 to FR12A, LHT: 4000FCI: 4000FCPRE 6016531239-01-1A 231/232 lining,insulationDetailed inspection of STR12 between FR17 and FR19, LH/RH T: 29000FCI: 24900FCALL531270-01-1A 221/222 831/841lining,insulationDetailed inspection of fuselage FR14 and FR16A, forward and rearfaces in areas of cross beams 1 and 8, LH/RH.Note: this task is an alternative to 531270-02-1AT: 30000FCI: 2800FCALL531270-02-1A 221/222 831/841lining,insulation, boltsSpecial 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 531270-01-1AT: 30000FCI: 9700FC531270 ALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 9 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531271-01-1A 211/212,212/222lining,insulation,15VU, 50VU,lh lavatory,galley ifinstalledDetailed inspection of FR10A to FR12 at each intersection ofstringer, from cabin floor to STR9, LH/RH.T: 36000FCI: 8700FCALL531273-01-1A 121/122 121/122 LF,121/122 MF,121/122 NF,121/122 PFDetailed inspection of nose gear bay arches attachments to framesat stringer 44 and struts attachments lugs, from FR11A to FR16Ainclusive, LH/RHT: 30500FC60900FHI: 5300FC10800FH-200531273-01-2A 121/122 121/122 LF,121/122 MF,121/122 NF,121/122 PFDetailed inspection of nose gear bay arches attachments to framesat stringer 44 and struts attachments lugs, from FR11A to FR16Ainclusive, LH/RHT: 29400FC82400FHI: 5200FC14600FH-300S531276-01-1A 123/124 713, 714 Detailed inspection of nose gear telescopic drag strut attach fitting. T: 34000FC67900FHI: 6200FC12500FH-200531276-01-2A 123/124 713, 714 Detailed inspection of nose gear telescopic drag strut attach fitting. T: 32500FC91000FHI: 6200FC17400FH-300S531293-01-1A 231, 232,233, 234Ceiling andsidewallpanels,insulationdisplaced asrequiredSpecial detailed Inspection (LFEC) splice plate at circumferentialskin splice at FR 18 from STR 9 LH to STR 13 LH, STR 1 RH toSTR 3 RH, STR 5 RH to STR 8 RH and STR 9 RH to STR 11 RH,i.e. excluding lap joints area.T: 36500FC73000FHI: 6000FC12000FH531293 -200CWFDR 531294-01-1A 231/232233/234Galleys,lavatories,overheadstowagecompartments,ceiling andsidewallpanels,insulationdisplaced asrequired, boltremovalSpecial Detailed Inspection (Roto Test) splice plate at circumferentialskin at FR 18 from STR 1 LH to STR 9 LH, from STR 3 RH to STR 5RH, from STR 8 RH to STR 9 RH and from STR 11 RH to STR 13RH, i.e. where lap joints intersect with circumferential skin splice.T: 34500FC69000FHI: 20500FC41000FH531294 -200CWFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 10 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531297-01-1A 121/122 linings,insulationdisplaced asrequiredDetailed inspection of fuselage internal structure, FR16A jointbetween STR28 and STR30, LH/RHT: 18500FCI: 13000FCPRE 3632531297-01-2A 121/122 linings,insulationdisplaced asrequiredDetailed inspection of fuselage internal structure, FR16A jointbetween STR28 and STR30, LH/RHT: 21500FCI: 16500FCPOST 3632531297-02-1A 121/122 linings,insulationdisplaced asrequiredSpecial detailed inspection (HFEC) of fuselage internal structure,FR16A joint between STR28 and STR30, LH/RHT: 18500FCI: 13000FC531297 PRE 3632531297-02-2A 121/122 linings,insulationdisplaced asrequiredSpecial detailed inspection (HFEC) of fuselage internal structure,FR16A joint between STR28 and STR30, LH/RHT: 21500FCI: 16500FC531297 POST 3632531298-01-1A 221/222 linings,insulationdisplaced asrequiredSpecial detailed inspection (ultrasonic) of fuselage internal structure,FR16A at cabin floor level.T: 22000FCI: 3300FC531298 PRE 3632531298 01 2A221/222li iS i l d t il d i ti ( lt i ) f f l i t l t tT 25000FC531298POST 3632531298-01-2A221/222 linings,insulationdisplaced asrequiredSpecial detailed inspection (ultrasonic) of fuselage internal structure,FR16A at cabin floor level.T: 25000FCI: 4200FC531298 POST 3632R 531305-01-1A 131 811 EccentricboltsDetailed inspection of FWD cargo compartment door eccentric boltsfrom FR 20B to FR 25.T: 20000FCI: 10000FCALLR 531305-02-1A 131 811General visual inspection of FWD cargo compartment door lockfittings, lugs, bushes, eccentric bolts and surround structure from FR20B to FR 25.T: 8000FCI: 8000FCALL1531307-01-1A 100/200 N/AGeneral visual inspection of fuselage skin panel around FWD cargocompartment door cutout from FR 19 to FR 26/32 and from STRs 22RH to 46 RH, external surface.T: 5800FCI: 5800FCALL1531309-01-1A 100 N/AGeneral visual inspection of fuselage skin from FR 20 to FR 26/32and from STRs 40 LH to 42 LH, external surface.T: 24000FCI: 2600FCALL1Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 11 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531316-01-2A 132134Lining,Insulationdisplaced asrequiredDetailed inspection of FRs 20, 20A and 25A from STRs 38 RH to 46RH, internal structure.T: 30000FCI: 5300FCALLR 531318-01-2A 132232132 AC to CC,DW, KW,232 AW toHW,Insulationdisplaced asrequiredDetailed inspection of FRs 20, 20A and 25A from STRs 22 RH to 29RH, internal structure.T: 30000FCI: 5200FCALL531331-01-1A 100 N/ADetailed inspection of fuselage skin of FWD cargo compartmentdoor cutout at upper and lower corners.T: 18000FCI: 2250FCALL531339-01-1A 200 N/ADetailed inspection of lower skin of longitudinal lap joint in crackstopper areas at STR 5, 13, 22 LH/RH from FR 18 to FR 26/32,external surface.Note: this task is an alternative to 531339-02-1AT: 33000FCI: 4300FCALL531339-02-1A 200 N/ASpecial detailed inspection (HFEC) of lower skin of longitudinal lapjoint STR5 LH/RH in rivet row between FR18 and FR26N t thi t k i lt ti t 531339 01 1AT: 33000FCI: 16000FC531339 ALLNote: this task is an alternative to 531339-01-1A531343-01-1A 100 N/A General visual inspection of lower skin of longitudinal lap joint incrack stopper areas at STRs 31, 43 LH and 28, 39 RH from FR 18 toFR 26/32 and at STRs 46 RH and 51 LH from FR 19 to FR 26/32,external surface.T: 33000FCI: 2800FCALL1531354-01-1A 200 835Detailed inspection of fuselage skin of MDC door cutout at upper andlower corners, external surface.T: 12000FCI: 9000FC-200C531355-01-1A 233835835,bolt,Lining,Insulationdisplaced asrequiredDetailed and Special detailed inspection (HFEC + Rotating probe) ofpiano hinges of MDC door, on fuselage and door, including surroundstructure.T: 18000FCI: 12000FC531355 -200CIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 12 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531357-01-1A 233 Ceiling panels,lining,Insulationdisplaced asrequiredDetailed inspection of support structure of piano hinge for MDC doorfrom STRs 4 to 5 LH, longeron from FR 20 to FR 33 and attachfitting for door struts.T: 12000FCI: 9200FC-200CR 531359-01-1A 231 835Eccentric boltsDetailed inspection of MDC door eccentric bolts from FR 20B to FR26/32.T: 12000FCI: 12000FC-200C531361-01-1A 131 Lining,Insulationdisplaced asrequiredDetailed inspection of attachment areas of lock fittings and MDCdoor lower longeron from FR 19 to FR 34 and from STRs 26 LH to34 LH.T: 12000FCI: 12000FC-200C531363-01-1A 131/132133/134231/232233/234Ceiling andsidewallpanels,cargo floorpanels,Insulationdisplaced asrequiredDetailed inspection of fuselage FRs 20 and 33 from crown to bottomcenter line.T: 12000FCI: 12000FC-200C531365-01-1A 232/234 Ceiling panels,I l tiDetailed inspection of attachment area of truss frames with normalf f FR 21 t FR 26/32 d f STR 5 t 10 RH (6T: 12000FCI 8800FC-200CInsulationdisplaced asrequiredframes from FR 21 to FR 26/32 and from STRs 5 to 10, RH (6places).I: 8800FC531366-01-1A 100200N/AGeneral visual inspection of fuselage skin around MDC door cutoutfrom FR 19 to FR 34 and from STR 3 to STR 31, LH, externalsurface.T: 4950FCI: 4950FC-200C531370-01-1A 100 N/ASpecial detailed inspection (HFEC + Rotating probe) of longitudinalbutt joint rivet rows, above and below the skin gap at STR 35 LH,between FR18 to FR 35, external surface .T: 33000FCI: 11000FC531370 -200CR 531371-01-1A 100 N/AGeneral visual inspection of fuselage skin external surface from FR19 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: 2200FCI: 2200FCALL1Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 13 - DRevCodeTask reference Zone Access Task descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsN 531371-02-1A 100 N/A Detailed inspection of fuselage skin external surface from FR 19 toFR 54 and from STRs 26 RH/LH to bottom center line, excluding theareas under fairings.NOTE: This task is an alternative to task 531371-01-1A.T: 6900FCI: 6900FCALLN 531372-01-1A 100 N/A General visual inspection of fuselage skin external surface, from FR19 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: 20000FCI: 2200FCALLN 531372-02-1A 100 N/A Detailed inspection of fuselage skin external surface, from FR 19 toFR 40/41, and from STR 6 to STR 26, LH/RH.NOTE: This task is an alternative to task 531372-01-1A.T: 20000FCI: 6900FCALLN 531373-01-1A 100 N/A General visual inspection of fuselage skin external surface, from FR19 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: 4500FCI: 4500FCALLN 531373-02-1A 100 N/A Detailed inspection of fuselage skin external surface, from FR 19 toFR 40/41 and from STR 6 to Crown Center Line LH/RHT: 6900FCI: 6900FCALLFR40/41,andfromSTR6toCrownCenterLine,LH/RHNOTE: This task is an alternative to task 531373-01-1A.I:6900FC531378-01-2A 132 811 General visual inspection of FWD cargo compartment door cutout,visible part of lateral frames (FR 20A and 25A) and sill beam, as faras visible.T: 6500FCI: 6500FCALL 1531393-01-1A 134 132BF,CF,KF,MF,ballmatinsulationCargo rollertracks to beremovedSpecial detailed inspection (HFEC) of Attachment Areas of LockFittings from FR 20 to FR 26/32 from Cargo Door Floor Level to STR45 RHT: 40000FCI: 4000FC511008 -200531393-01-2A 134 132BF,CF,KF,MF,ballmatinsulationCargo rollertracks to beremovedSpecial detailed inspection (HFEC) of Attachment Areas of LockFittings from FR 20 to FR 26/32 from Cargo Door Floor Level to STR45 RHT: 35000FCI: 4000FC511008 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS2010. All rights reserved. Confidential and proprietary document.Page 14 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531410-01-2A 513/613 Krueger flapextended513 AL, 613ARDetailed inspection of fuselage skin from FR 36 and FR 37 and fromSTRs 30 to 32 LH/RH, external surface.T: 30000FCI: 7600FCALL531411-01-2A 513/613 513 AL, GL613 AR, GRDetailed inspection of fuselage skin around wing fairing attachmentfittings at FR 38, FR 38.1 and FR 38.2 LH/RH, external surface.T: 30000FCI: 5400FCALL531412-01-2A 131/132 131/132 QW,Insulationdisplaced asrequiredDetailed inspection of FRs 38, 38.1 and 38.2 from STRs 27 to 34,LH/RH.T: 30000FCI: 5400FC-200531412-01-3A 131/132 131/132 QW,Insulationdisplaced asrequiredDetailed inspection of FRs 38, 38.1 and 38.2 from STRs 27 to 34,LH/RH.T: 30000FCI: 7900FC-300531417-01-2A 200 N/ADetailed inspection of fuselage skin at FR 36 from STRs 2 LH to 2RH, external surface.T: 30000FCI: 10200FC-200531418-01-2A 200 N/ADetailed inspection of fuselage skin at FR 35 from STRs 2 LH to 2RH, external surface.T: 30000FCI: 12300FC-300531421 01 1A100AG l i l i ti f f l ki f FR 26/32 t FR 38 2T 18000FCALL1531421-01-1AN/General visual inspection of fuselage skin from FR 26/32 to FR 38.2and from STRs 40 to 42 LH/RH, external surface.T: 18000FCI: 2600FCALL1531429-01-1A 200 N/ADetailed inspection of lower skin of longitudinal lap joint in crackstopper areas at STRs 5, 13, 22 LH/RH from FR 26/32 to FR 40,external surface.Note: this task is an alternative to 531429-02-1AT: 33000FCI: 4300FCALL531429-02-1A 200 N/ASpecial detailed inspection (HFEC) of lower skin of longitudinal lapjoint STR 5 in rivet row between FR 26/32 and FR 40/41 LH/RH.Note: this task is an alternative to 531429-01-1AT: 33000FCI: 16000FC531429 ALL531433-01-1A 100 N/AGeneral visual inspection of lower skin external surface oflongitudinal 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: 33000FCI: 2800FCALL1Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 15 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531434-01-2A 513/613 Krueger flapextended513/613 AL,GL, RLSpecial Detailed Inspection (HFEC) of fuselage external surfaceunderneath wing fillet fairing from FR 37 to FR 40/41, including lowerskin of longitudinal lap joint in crack stopper areas at STR 31 LH/RH.Note: this task is an alternative to 531434-03-1AT: 33000FCI: 16000FC531434 ALL531434-03-1A 513/613 Krueger flapextended513/613 AL,GL, RLDetailed inspection of fuselage external surface underneath wingfillet fairing from FR 37 to FR 40/41, including lower skin oflongitudinal lap joint in crack stopper areas at STR 31 LH/RH.Note: this task is an alternative to 531434-01-2AT: 33000FCI: 4300FCALL531435-01-1A 231, 232,233, 234Ceiling andsidewallpanels,insulationdisplaced asrequiredSpecial detailed inspection (LFEC) of Splice plate at circumferentialskin splice at FR 26/32 from STR 4 LH/RH to crown centre line andfrom STR 5 to 12, LH/RH.Note: A310-300 Short Range Requirement beyond Extended ServiceGoal.T: 43500FC123000FHI: 7000FC20500FH531435 -300WFDS531436-01-1A 231/232233/234Galleys, toilets,overheadstowagecompartments,ceiling andsidewallSpecial detailed inspection (LFEC) of Splice plate at circumferentialskin splice at FR 35 from STR 9 to STR 13 LH, and from STR 6 to12, RH.T: 40000FC80000FHI: 6500FC13000FH531436 -200CWFDsidewallpanels,insulationdisplaced asrequired531501-01-2A 200 N/ADetailed inspection of skin in circumferential splice and stringercoupling areas at FR 40/41, from STR 13 LH/RH to crown centerline, external surface.T: 41200FC82400FHI: 12800FC25600FH-200531501-01-4A 200 N/ADetailed inspection of skin in circumferential splice and stringercoupling areas at FR 40/41, from STR 13 LH/RH to crown centerline, external surface.T: 37400FC104600FHI: 9800FC27700FH-300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 16 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531502-01-1A 200 N/ADetailed inspection of lower skin external surface of longitudinal lapjoints 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 531502-02-1AT: 32000FCI: 3600FCALL531502-02-1A 200 N/ASpecial detailed inspection (HFEC) of lower skin external surface oflongitudinal lap joint in rivet row at STR 5 and STR 13, LH/RH fromFR 40/41 to FR 54 and at STR 22, LH/RH from FR 45 to FR 54.Note: This task is an alternative to 531502-01-1AT: 32000FCI: 16000FC531502 ALL531505-01-1A 200 N/ADetailed inspection of fuselage skin and visible part of windowforgings from FR 45 to FR 54, and from STR 18 to STR 22 LH/RH,external surface.T: 40000FCI: 6500FC-200531505-01-2A 200 N/ADetailed inspection of fuselage skin and visible part of windowforgings from FR 45 to FR 54, and from STR 18 to STR 22 LH/RH,external surface.T: 35000 FCI: 6500 FC-300PRE 13302531505-01-3A 200 N/ADetailed inspection of fuselage skin and visible part of windowforgings from FR 45 to FR 54, and from STR 18 to STR 22 LH/RH,external surface.T: 35000 FCI: 6400 FC-300POST 13302531506 01 1A200A tD t il d i ti f ki d VHF t t t fT 40000FC200531506-01-1AAntennaremovalDetailed inspection of skin around VHF antenna cutout fromFR 47/48 to FR 49 and between STR 1 LH andSTR 1 RH, external surface.T: 40000FC80000FHI: 6200FC12400FH-200531506-01-2A 200 AntennaremovalDetailed inspection of skin around VHF antenna cutout fromFR 47/48 to FR 49 and between STR 1 LH and STR 1 RH, externalsurface.T: 35000 FC98000 FHI: 5300 FC14900 FH-300PRE 13302S531506-01-3A 200 AntennaremovalDetailed inspection of skin around VHF antenna cutout fromFR 47/48 to FR 49 and between STR 1 LH andSTR 1 RH, external surface.T: 35000 FC98000 FHI: 5100 FC14400 FH-300POST 13302S531507-01-3A 241/242243/244Sidewall andceiling panels,Insulationdisplaced asrequiredDetailed inspection of FR 40 and FR 47 from STR 22 LH/RH tocrown center line.T: 30000FCI: 6650FC-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 17 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531508-01-1A 200 N/ADetailed inspection of fuselage skin in frame coupling area at FR 42to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH,external surface.T: 36500FC73000FHI: 12200FC24500FH-200531508-01-2A 200 N/ADetailed inspection of fuselage skin in frame coupling area at FR 42to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH,external surface.T: 29000 FC81000 FHI: 6200 FC17600 FH-300PRE 13302S531508-01-3A 200 N/ADetailed inspection of fuselage skin in frame coupling area at FR 42to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH,external surface.T: 29000 FC81000 FHI: 6000 FC16900 FH-300POST 13302S531509-01-1A 100/200834/844834/844 Detailed inspection of fuselage skin external surface, from FR 40/41to FR 45 and from STR 14 to STR 28 LH/RH, including visibleportion of emergency exit frames and window forgings.T: 40000FCI: 6000FC-200531509-01-2A 100/200834/844834/844 Detailed inspection of fuselage skin external surface, from FR 40/41to FR 45 and from STR 14 to STR 28 LH/RH, including visibleportion of emergency exit frames and window forgings.T: 35000 FCI: 6000 FC-300PRE 13302531509-01-3A 100/200834/844834/844 Detailed inspection of fuselage skin external surface, from FR 40/41t FR 45 d f STR 14 t STR 28 LH/RH i l di i iblT: 35000 FCI 5500 FC-300POST 13302834/844to FR 45 and from STR 14 to STR 28 LH/RH, including visibleportion of emergency exit frames and window forgings.I: 5500 FCPOST 13302531511-01-1A 241/242834/844834/844 General visual inspection of door stop fittings onFR 42A and FR 43A, LH/RH.T: 18000FCI: 12000FCALL1531512-01-1A 100/200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 45, from STR 13 to STR 27,LH/RH, external surface.T: 18000FC36000FHI: 13500FC27000FH-2001531512-01-2A 100/200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 45, from STR 13 to STR 27,LH/RH, external surface.T: 14400 FC40500 FHI: 7400 FC20000 FH-300PRE 133021SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 18 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531512-01-3A 100/200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 45, from STR 13 to STR 27,LH/RH, external surface.T: 14400 FC40500 FHI: 7200 FC20000 FH-300POST 133021S531513-01-1A 100/200 N/AGeneral visual inspection of fuselage skin at FR 47/48 from wing tofuselage fairing to STR 13 LH/RH, external surface.T: 18000FCI: 5900FCALL1531515-01-1A 241/242 Sidewallpanels,insulationdisplaced asrequiredDetailed inspection of FR 46 between STR 22 and STR 26,LH/RH.T: 40000FCI: 16500FC-200531515-01-2A 241/242 Sidewallpanels,insulationdisplaced asrequiredDetailed inspection of FR 46 between STR 22 and STR 26,LH/RH.T: 35000FCI: 16500FC-300531518-01-1A 145/146 Main deck floorpanelsDetailed inspection of longitudinal floor beams from FR 45 to FR54, above pressure deck including shear plates, cross beams andattachment of cross beams.T: 24000FCI: 12000FCALL531519-01-1A 145/146 Main deck floorlGeneral visual inspection of membranes of pressure deck betweenFR 47 d FR 54 fT: 24000FCI 12500FCALL1panels FR 47and FR 54, upper surface.I: 12500FCR 531524-01-1A 200 AnticollisionlightDetailed inspection of fuselage skin around anti-collision light cutoutfrom FR 42 to FR 43, and from STR 1 LH to STR 1 RH, externalsurface.T: 40000FC80000FHI: 18000FC36000FH-200R 531524-01-2A 200 AnticollisionlightDetailed inspection of fuselage skin around anti-collision light cutoutfrom FR 42 to FR 43, and from STR 1 LH to STR 1 RH, externalsurface.T: 35000FC98000FHI: 14400FC50500FH-300SN 531529-01-1A 200 N/AGeneral visual inspection of fuselage skin external surface, from FR40/41 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: 4500FCI: 4500FCALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 19 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsN 531529-02-1A 200 N/ADetailed inspection of fuselage skin external surface, from FR 40/41to FR 80/82, and from STR 6 to crown center line, LH/RH.Note: This task is analternative to task 531529-01-1A.T: 6900FCI: 6900FCALLN 531530-01-1A 200 N/AGeneral visual inspection of fuselage skin external surface, from FR40/41 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: 20000FCI: 2200FCALLN 531530-02-1A 200 N/ADetailed inspection of fuselage skin external surface, from FR 40/41to FR 80/82, and from STR 6 to STR 26, LH/RH.Note: This task is an alternative to task 531530-01-1A.T: 20000FCI: 6900FCALL531541-01-1A 241/242 Main deck floorpanelSealantRemovalSpecial detailed inspection (HFEC) of longitudinal beams 1 to 5lower flange at FR47-1, 49-1, 50-1, 51, 51-1, 52-1 and 53-1, LH/RH.T: 33000FCI: 9200FC531541 -200531542-01-1A 141/142 734, 744147/148AZSealantRemovalSpecial detailed inspection (Ultrasonic) of stiffener at wing tofuselage lower skin splice at rib 1 (center wing box side) from FR42to FR47.T: 21800FC43600FHI: 2800FC5700FH531542 -200531542-01-3A 141/142 734, 744147/148AZSealantRemovalSpecial detailed inspection (Ultrasonic) of stiffener at wing tofuselage lower skin splice at rib 1 (center wing box side) from FR42to FR47.T: 23900FC67200FHI: 6000FC16900FH531542 -300SRemoval531551-01-1A 143/144 144 FR143 FLDetailed inspection of fuselage skin and doubler around airconditioning compartment access cutouts, LH/RH.T: 22700FC45400FHI: 22700FC45400FH-200531551-01-2A 143/144 144 FR143 FLDetailed inspection of fuselage skin and doubler around airconditioning compartment access cutouts, LH/RH.Note: Internal and external side to be inspectedT: 16500FC46300FHI: 16500FC46300FH-300S531552-01-1A 145/146241/242Main deck floorpanels,insulation, boltsto be removedSpecial detailed inspection (Rotating Probe) of FR49, 50, 51, 52 and53 between STR 25 and 29 at frame foot, LH/RH.T: 35000FC70100FHI: 8600FC17300FH531552 -200WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 20 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531552-01-2A 145/146241/242Main deck floorpanels,insulation, boltsto be removedSpecial detailed inspection (Rotating Probe) of FR49, 50, 51, 52 and53 between STR 25 and 29 at frame foot, LH/RH.T: 30700FC85900FHI: 8600FC24200FH531552 -300WFDS531555-01-1A 147/148 734/744 General visual inspection of slanted frames from FR 47 to FR 54,LH/RH.T: 6600FC13300FHI: 6600FC13300FH-2001531555-01-2A 147/148 734/744 General visual inspection of slanted frames from FR 47 to FR 54,LH/RH.T: 6700FC19000FHI: 6700FC19000FH-3001S531556-01-1A 147/148 734/744147/148 CZDetailed inspection of fuselage internal structure at FR 47/48 fromSTRs 42 to 43, LH/RH.T: 11200FC22400FHI: 3300FC6600FH-200531556-01-2A 147/148 734/744147/148 CZDetailed inspection of fuselage internal structure at FR 47/48 fromSTRs 42 to 43, LH/RH.T: 12400FC34700FHI: 2800FC8000FH-300S531561 01 1A145/146M i d k flD t il d i ti f FR47A 49A 50A 51A d 52A t f f tT 28900FC200531561-01-1A145/146241/242Main deck floorpanels,insulation.Detailed inspection of FR47A, 49A, 50A, 51A and 52A at frame footrunout, LH/RH.T: 28900FC57900FHI: 15200FC30500FH-200531561-01-2A 145/146241/242Main deck floorpanels,insulation.Detailed inspection of FR47A, 49A, 50A, 51A and 52A at frame footrunout, LH/RH.T: 30800FC86200FHI: 15200FC42600FH-300S531567-01-1A 147/148 734/744 Detailed inspection of keel beam side panels, adjacent fuselagestructure up to STR 40 and MLG hinge assemblies and dooractuator fitting from FR 47 to FR 54, LH/RH.T: 15300FC30700FHI: 4000FC8000FH-200531567-01-2A 147/148 734/744 Detailed inspection of keel beam side panels, adjacent fuselagestructure up to STR 40 and MLG hinge assemblies and dooractuator fitting from FR 47 to FR 54, LH/RH.T: 16100FC45300FHI: 3600FC10300FH-300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 21 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531571-01-2A 143/144147/148734/744143DF147AF,BF,BZ148BFDetailed inspection of keel beam box from FR44 to FR54, internalstructure.T: 19000FC38000FHI: 11600FC23300FH-200531571-01-3A 143/144147/148734/744143DF147AF,BF,BZ148BFDetailed inspection of keel beam box from FR44 to FR54, internalstructure.T: 18300FC51200FHI: 15000FC42100FH-300SR 531574-01-1A 145/146 734/744, angleweb to beremovedSpecial detailed inspection (Ultrasonic) of STR36 fillet radius atFR54, internal structure, LH/RH.T: 24900FCI: 5600FC531574Proc Aand ProcB-200 POST SB53-2016 (Mod.4980)531579-01-1A 135/136137/138Cargocompartmentfloor andsidewall panelsInsulationdisplaced asrequiredDetailed inspection of FWD face of pressure bulkhead at FR 39,including stringer end fittings from STR35 LH / STR35 RH to bottomcenter lineT: 15800FC31600FHI: 7700FC15400FH-200PRE 5566531579-01-2A 135/136137/138Cargot tDetailed inspection of FWD face of pressure bulkhead at FR 39,i l di t i d fitti f STR35 LH / STR35 RH t b ttT: 26500FC53100FH-200POST 5566137/138 compartmentfloor andsidewall panelsInsulationdisplaced asrequiredincluding stringer end fittings from STR35 LH / STR35 RH to bottomcenter line53100FHI: 17500FC35000FHPOST 5566or-200 POST 6527531579-01-3A 135/136137/138Cargocompartmentfloor andsidewall panelsInsulationdisplaced asrequiredDetailed inspection of FWD face of pressure bulkhead at FR 39,including stringer end fittings from STR35 LH / STR35 RH to bottomcenter lineT: 33400FC93500FHI: 23500FC66000FH-300S531580-01-1A 143/144 734/744147BZDetailed inspection of stringer end fittings and horizontal crossmembers at AFT face of pressure bulkhead at FR39, from STR35 tobottom center line, LH/RHT: 14500FC29100FHI: 7700FC15400FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 22 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531580-01-2A 143/144 734/744147BZDetailed inspection of stringer end fittings and horizontal crossmembers at AFT face of pressure bulkhead at FR39, from STR35 tobottom center line, LH/RHT: 20200FC56500FHI: 8700FC24300FH-300SR531582-01-1A 143/144 571 / 671 AB Special detailed inspection (Ultrasonic) of fuselage skin fromFR47/48 to FR49 and from STR 35 to STR 36, LH/RH.T: 30100FC60300FHI: 18300FC36600FH531582 -200R531582-01-2A 143/144 571 / 671 AB Special detailed inspection (Ultrasonic) of fuselage skin fromFR47/48 to FR49 and from STR 35 to STR 36, LH/RH.T: 27700FC77600FHI: 16700FC46700FH531582 -300S531584-01-1A 143/144 Chafing plateremoval as perSB 53-2069SealantRemovalSpecial detailed inspection (LFEC and Ultrasonic) of fuselage skinunderneath pick-up angle from FR 39 to FR 42, LH/RH.T: 15600FC31300FHI: 9100FC18300FH531584 -200PRE 12776531584-01-2A 143/144 Chafing plateremoval as perSB 53-2069SltSpecial detailed inspection (LFEC and Ultrasonic) of fuselage skinunderneath pick-up angle from FR 39 to FR 42, LH/RH.T: 17000FC34000FHI: 4500FC9100FH531584 -200POST 12776SealantRemoval9100FH531584-01-3A 143/144 Chafing plateremoval as perSB 53-2069SealantRemovalSpecial detailed inspection (LFEC and Ultrasonic) of fuselage skinunderneath pick-up angle from FR 39 to FR 42, LH/RH.T: 15400FC43100FHI: 9100FC25400FH531584 -300PRE 12776S531584-01-4A 143/144 Chafing plateremoval as perSB 53-2069SealantRemovalSpecial detailed inspection (LFEC and Ultrasonic) of fuselage skinunderneath pick-up angle from FR 39 to FR 42, LH/RH.T: 20000FC56100FHI: 4500FC12700FH531584 -300POST 12776SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 23 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531586-01-1A 241/242 241BW242BWSpecial detailed inspection (X-RAY) of fuselage skin doubler atFR40/41, between STRs 20 and 23, LH/RHT: 29600FC59300FHI: 4500FC9000FH531586 -200531586-01-2A 241/242 241BW242BWSpecial detailed inspection (X-RAY) of fuselage skin doubler atFR40/41, between STRs 20 and 23, LH/RHT: 29400FC82300FHI: 2200FC6100FH531586 -300S531587-01-1A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 21300FC42700FHI: 13500FC27100FH-200PRE 5411531587-01-2A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 35100FC70200FHI: 13500FC27100FH-200POST 5411531587-01-3A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 21100FC59100FHI: 13400FC37600FH-300PRE 5411S531587 01 4A147/148734/744D t il d i ti f M i L di G t t tt h t fittiT 27200FC300S531587-01-4A147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 27200FC76100FHI: 13400FC37600FH-300PARTIAL MOD5411S531587-01-5A 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 34700FC97300FHI: 13400FC37600FH-300POST 5411S531588-01-3A 147/148151/152153/154734/744Floor andsidewallpanels, bolts,Insulationdisplaced asrequiredSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 43 to STR 46,13 holes RH and16 holes LH.T: 28300FCI: 10000FC531588 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 24 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531588-01-5A 147/148151/152153/154734/744Floor andsidewallpanels, bolts,Insulationdisplaced asrequiredSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 43 to STR 46,13 holes RH and16 holes LH.T: 31200FCI: 12000FC531588 -300531589-01-3A 147151153734/744Sidewallpanels, bolts,Insulationdisplaced asrequiredSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 39 to STR 40, 5 holes LH.Note: this task is an alternative to 531589-01-4AT: 28300FCI: 10000FC531589 -200531589-01-4A 147151153734/744Sidewallpanels,Insulationdisplaced asrequiredSpecial detailed inspection (X-RAY) of circumferential skin joint andframe at FR 54 from STR 39 to STR 40, 5 holes LH.Note: this task is an alternative to 531589-01-3AT: 28300FCI: 6000FC531589 -200531589-01-5A 147,151153734/744Sidewallpanels, bolts,I l tiSpecial detailed inspection (Rotating Probe) of circumferential skinjoint 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 6AT: 31000FCI: 12000FC531589 -300Insulationdisplaced asrequired.Note: this task is an alternative to 531589-01-6A531589-01-6A 147,151153734/744Sidewallpanels,Insulationdisplaced asrequired.Special detailed inspection (X-RAY) of circumferential skin joint andframe at FR 54 from STR 39 to STR 40, 5 holes LH.Note: this task is an alternative to 531589-01-5AT: 31000FCI: 6000FC531589 -300531590-01-2A 147,151153734/744572 AB,bolts,Sidewallpanels,Insulationdisplaced asrequired.Special detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 35 to STR 37, 13 holes LH.T: 24000FCI: 12000FC531590 ALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 25 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531591-01-3A 148,152154734/744672 AB, bolts,Sidewallpanels,Insulationdisplaced asrequired.Special detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 36 to STR 37, 7 holes, RH.T: 25000FCI: 10000FC531591 -200531591-01-5A 148,152154734/744672 AB, bolts,Sidewallpanels,Insulationdisplaced asrequired.Special detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 36 to STR 37, 7 holes, RH.T: 28000FCI: 12000FC531591 -300531594-01-1A 147/148151/152153/154734/744Sidewall andfloor panels,Insulationdisplaced asrequired, boltsremoval.Special detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR54 from STR 43 to STR 46, 15 holes RH and24 holes LHT: 28800FCI: 5000FC531594 -200531594-01-2A 147/148151/152734/744Sid ll dSpecial detailed inspection (Rotating Probe) of circumferential skinj i t d f t FR54 f STR 43 t STR 46 15 h l RH dT: 28800FCI 6000FC531594 -300151/152153/154Sidewall andfloor panels,Insulationdisplaced asrequired, boltsremoval.joint and frame at FR54 from STR 43 to STR 46, 15 holes RH and24 holes LHI: 6000FC531595-01-3A 147,151153744/734Sidewallpanels, bolts,Insulationdisplaced asrequired.Special detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-4AT: 33500FCI: 8000FC531595 -200531595-01-4A 147,151153734/744Sidewallpanels,Insulationdisplaced asrequired.Special detailed inspection (X-RAY) of circumferential skin joint andframe at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-3AT: 33500FCI: 5000FC531595 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 26 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531595-01-5A 147,151153734/744Sidewallpanels, bolts,Insulationdisplaced asrequiredSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-6AT: 36000FCI: 9000FC531595 -300531595-01-6A 147,151153734/744Sidewallpanels,Insulationdisplaced asrequired.Special detailed inspection (X-RAY) of circumferential skin joint andframe at FR 54, from STR 39 to STR 41, 10 holes LH.Note: this task is an alternative to 531595-01-5AT: 36000FCI: 5500FC531595 -300531596-01-2A 147,151153734/744572 AB, bolts,Sidewallpanels,Insulationdisplaced asrequiredSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54, from STR 36 to STR 38, 13 holes LH.T: 38300FCI: 6000FC531596 ALL531597-01-1A 148152734/744672AB, sidewalpanels,I l tiSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 36 to STR 40, 7 holes RHT: 27000FCI: 5000FC531597 -200Insulationdisplaced asrequired, boltsremoval531597-01-2A 148152734/744,672AB, sidewalpanels,Insulationdisplaced asrequired, boltsremovalSpecial detailed inspection (Rotating Probe) of circumferential skinjoint and frame at FR 54 from STR 36 to STR 40, 7 holes RHT: 27000FCI: 6000FC531597 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 27 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531602-01-1A 243244253254Ceiling panels,insulation,overheadstowagecompartments(if fitted), bolts.Special detailed inspection (Rotating Probe) of splice plate at thecircumferential skin splice at FR54 at STR5, LH/RHT: 38000FC76000FHI: 8700FC17500FH531602 -200531602-01-2A 243244Ceiling panels,insulation,overheadstowagecompartments(if fitted), bolts.Special detailed inspection (Rotating Probe) of splice plate at thecircumferential skin splice at FR54 at STR5, LH/RHT: 34600FC97200FHI: 7100FC20000FH531602 -300S531605-01-2A 200 N/ADetailed inspection of skin in circumferential splice and stringercoupling areas at FR 55/58 from STR 13, LH/RH, to crown centerline, external surface.Note: This task is an alternative to 531605-02-1AT: 22000FC44500FHI: 10000FC20000FH-200531605-01-3A 200 N/ADetailed inspection of skin in circumferential splice and stringerli t FR 55/58 f STR 13 LH/RH ttT: 15500FC43500FH-300Scoupling areas at FR 55/58 from STR 13, LH/RH, to crown centerline, external surface.Note: This task is an alternative to 531605-02-4A43500FHI: 7300FC20000FH531605-02-1A 200 N/ASpecial detailed inspection (HFEC) of skin in circumferential spliceand stringer coupling areas at FR 55/58 from STR 13, LH/RH, tocrown center line, external surface.Note: This task is an alternative to 531605-01-2AT: 22000FC44500FHI: 14500FC29500FH531605 -200531605-02-4A 200 N/ASpecial detailed inspection (HFEC) of skin in circumferential spliceand stringer coupling areas at FR 55/58 from STR 13, LH/RH, tocrown center line, external surface.Note: This task is an alternative to 531605-01-3AT: 15500FC43500FHI: 10600FC29500FH531605 -300S531606-01-3A 200 N/ASpecial Detailed Inspection (LFEC) of Splice plate at circumferentialskin splice at FR 55/58 from STR 4 LH/RH to crown centre line andfrom STR 5 to 12, LH/RHT: 20500FC41000FHI: 3000FC6000FH531606 -200PRE 13211 (SB53-2125)WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 28 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531606-01-4A 200 N/ASpecial Detailed Inspection (LFEC) of Splice plate at circumferentialskin splice at FR 55/58 from STR 4 LH/RH to crown centre line andfrom STR 5 to 12, LH/RHT: 16000FC46000FHI: 2400FC6700FH531606 -300PRE 13211 (SB53-2125)WFDS531608-01-1A 100 N/AGeneral visual inspection of lower skin of longitudinal lap joint incrack stopper areas at STR 44 LH/RH, from FR 54 to FR 55/58,external surface.T: 32000FCI: 2250FCALL531610-01-1A 100 N/ASpecial detailed inspection (LFEC + US) of lower skin of longitudinallap joint at STR 52, LH/RH, from FR 54 to FR 55/58, externalsurface.T: 32000FCI: 16000FC531610 ALL531611-01-1A 200 N/ADetailed inspection of skin at shear tie attachments at FR 54.1, 54.2and 54.3 from STR 22 LH/RH, to crown center line, external surface.T: 28000FC56000FHI: 3800FC7700FH-200531611-01-2A 200 N/ADetailed inspection of skin at shear tie attachments at FR 54.1, 54.2and 54.3 from STR 22 LH/RH, to crown center line, external surface.T: 27000FC76500FHI: 3700FC10600FH-300SR 531612-01-1A 100 N/AGeneral visual inspection of fuselage skin external surface, from FR54 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: 2200FCI: 2200FCALL1N 531612-02-1A 100 N/ADetailed inspection of fuselage skin external surface, from FR 54 toFR 80/82, and from STR 26 LH/RH, to bottom center line, excludingarea covered by the AFT wing root fairings.Note: This is an alternative to task 531612-01-1A.T: 6900FCI: 6900FCALL531616-01-1A 200577/677577 AL677 ARDetailed inspection of lower skin external surface of longitudinal lapjoint in crack stopper areas at STRs 5, 13, 22 and 31, LH/RH, fromFR 54 to FR 55/58.Note : This task is an alternative to 531616-02-1AT: 32000FCI: 3600FCALL531616-02-1A 200577/677577 AL677 ARSpecial Detailed Inspection (HFEC) of Iower skin external surface oflongitudinal 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 531616-01-1AT: 32000FCI: 16000FC531616 ALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 29 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531621-01-1A 253/254 Ceiling planels,Insulationdisplaced asrequired, airconditioningduct, overheadstowagecompartments,boltsSpecial Detailed Inspection ( HFEC + Rotating probe ) of splice plateat 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 jointsintersect with circumferential skin splice.T: 30000FC60000FHI: 19000FC38000FH531621 -200PRE 13211 (SB53-2125)WFD531621-01-2A 253/254 Ceiling planels,Insulationdisplaced asrequired, airconditioningduct, overheadstowagecompartments,boltsSpecial Detailed Inspection ( HFEC + Rotating probe ) of splice plateat 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 jointsintersect with circumferential skin splice.T: 26500FC75000FHI: 16000FC44500FH531621 -300PRE 13211 (SB53-2125)WFDS531633-01-1A 251/252 N/ADetailed inspection of fuselage skin and visible portion of windowforgings between FR 54 and FR 77 fromSTR 18 t STR 22T: 40000FCI: 6500FC-200STR 18 to STR 22.531633-01-2A 251/252 N/A Detailed inspection of fuselage skin and visible portion of windowforgings between FR 54 and FR 77 fromSTR 18 to STR 22.T: 35000FCI: 6500FC-300531701-01-3A 200 N/ADetailed inspection of fuselage skin in circumferential splice andstringer coupling areas at FR 72, fromSTR 13 LH/RH, to crown center line, external surface.T: 30000FC60000FHI: 14400FC28500FH-200531701-01-4A 200 N/ADetailed inspection of fuselage skin in circumferential splice andstringer coupling areas at FR 72, fromSTR 13 LH/RH, to crown center line, external surface.T: 26500FC75000FHI: 10500FC29500FH-300S531702-01-3A 200 N/ASpecial detailed inspection (LFEC) of splice plate at circumferentialskin splice at FR 72, from STR 4, LH/RH, to crown center line andfrom STR 6 to STR 11, LH/RH.T: 33000FC66000FHI: 9000FC18000FH531702 -200WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 30 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531702-01-4A 200 N/ASpecial detailed inspection (LFEC) of splice plate at circumferentialskin splice at FR 72, from STR 4, LH/RH, to crown center line andfrom STR 6 to STR 11, LH/RH.T: 29000FC82000FHI: 7500FC21000FH531702 -300WFDSR 531704-01-1A 200577577 BL , 577ELDetailed inspection of lower skin external surface of longitudinal lapjoints 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 531704-02-1AT: 32000FCI: 3600FCALLR 531704-02-1A 200577577 BL , 577ELSpecial detailed inspection (HFEC) of lower skin external surface oflongitudinal lap joints in rivet row:At STR 5 LH/RH from FR 55/58 to FR 72At STR 31 LH from FR55/58 to 62.Note : This task is an alternative to 531704-01-1AT: 32000FCI: 16000FC531704 ALL531708-01-1A 200 N/AGeneral visual inspection of skin at shear tie attachments from FR55/58 to FR 72, and from STR 13, LH/RH, to crown center line,external surface.T: 18000FCI: 8800FCALL1531712-01-1A 100 N/AGeneral visual inspection of skin of AFT cargo compartment doorcutout at upper and lower corners, external surface.T: 18000FCI: 4200FCALL1531713-01-1A 152154812General visual inspection of AFT cargo compartment door cutout,visible parts of FR 59A and FR 63A and sill beam.T: 6500FCI: 6500FCALL1R 531716-01-1A 154 812Eccentric boltsDetailed inspection of AFT cargo compartment door eccentric boltsand bushes from FR 60 to FR 63 and from STR 44 RH to STR 46RH.T: 20000FCI: 10000FCALLR 531716-02-1A 154 812General visual inspection of AFT cargo compartment door lockfittings and surrounding structure from FR 60 to FR 63and fromSTR 44 RH to STR 46 RH.T: 8000FCI: 8000FCALL1531719-01-1A 162 813General visual inspection of bulk cargo compartment door cutout,visible parts of FR 67 and FR 69.T: 6500FCI: 6500FCALL1531720-01-1A 100 N/AGeneral visual inspection of skin of bulk cargo compartment doorcutout at upper corners, external surface.T: 18000FCI: 3500FCALL1Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 31 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531721-01-3A 162164Scuff plateremovalDetailed inspection of skin of bulk cargo compartment door cutout atlower corners, underneath scuff plate.T: 30000FCI: 12000FC-200531721-02-4A 162164Scuff plateremovalDetailed inspection of skin of bulk cargo compartment door cutout atlower corners, underneath scuff plate.T: 30000FCI: 8000FC-300531722-01-2A 162164813Lining,floor panels,Insulationdisplaced asrequired.Detailed inspection of fuselage internal structure around bulk cargocompartment door cutout from FR 66 toFR 70 from STR 31 RH to STR 48 RH.T: 30000FCI: 9000FCALL531723-01-1A 162 813Detailed inspection of bulk cargo door stop fittings at FR 67 and FR69.T: 40000FCI: 8000FC-200531723-01-2A 162 813Detailed inspection of bulk cargo door stop fittings at FR 67 and FR69.T: 35000FCI: 8000FC-300531726-01-1A 100 N/AGeneral visual inspection of lower skin external surface oflongitudinal 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 72T: 32000FCI: 2250FCALL- atSTRs 44 LH, 47 RH and 48RHfrom FR 55/58to 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,Insulationdisplaced asrequired,air conditioningduct,overheadstowagecompartments,boltsSpecial detailed inspection (HFEC + rotating probe) of splice plate atcircumferential skin splice at FR 72, from STRs 3 to 7, LH/RH, andfrom STRs 11 to 13, LH/RH, (at intersection of lap joints withcircumferential skin splice).T: 33000FC66000FHI: 21000FC42000FH531731 -200WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 32 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531731-02-1A 253/254 Ceiling panels,Insulationdisplaced asrequired,air conditioningduct,overheadstowagecompartments,boltsSpecial detailed inspection (HFEC + rotating probe) of splice plate atcircumferential skin splice at FR 72, from STRs 3 to 7, LH/RH, andfrom STRs 11 to 13, LH/RH, (at intersection of lap joints withcircumferential skin splice).T: 29000FC82000FHI: 17000FC47500FH531731 -300WFDS531732-01-1A 251/252 Sidewallpanels,Insulationdisplaced asrequiredDetailed inspection of fuselage internal structure from FR 59 to FR64, and from STR 19 to STR 23, LH/RH, in frame coupling areas.T: 18000FCI: 6000FCALL531737-01-1A 240 Antenna to beremovedDetailed inspection of skin around ADF1 and ADF2 antenna cutoutsbetween FR 59 and FR 60 and between FR 62 and FR 63, on crowncenter line, external surface.T: 40000FC80000FHI: 9000FC18000FH-200531737-01-2A 240 Antenna to beremovedDetailed inspection of skin around ADF1 and ADF2 antenna cutoutsbetween FR 59 and FR 60 and between FR 62 and FR 63, on crowncenter line, external surface.T: 35000FC98000FHI: 7200FC20000FH-300S531801-01-1A 200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 76, from STR 13 LH/RH, tocrown center line, external surface.T: 18000FC36000FHI: 11800FC23600FH-2001531801-01-2A 200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 76, from STR 13, LH/RH, tocrown center line, external surface.T: 16000FC45000FHI: 10500FC29500FH-3001S531803-01-1A 200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 80/82, from STR 6 to STR 13,LH/RH, external surface.T: 18000FC36000FHI: 16000FC32000FH-2001Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 33 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531803-01-2A 200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 80/82, from STR 6 to STR 13,LH/RH, external surface.T: 12500FC36000FHI: 11400FC32000FH-3001S531806-01-1A 200 N/ADetailed inspection of lower skin external surface of longitudinal lapjoints 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 531806-02-1AT: 32000FCI: 3600FCALL531806-02-1A 200 N/ASpecial detailed inspection (HFEC) of Iower skin external surface oflongitudinal lap joints in rivet row:- at STR6, LH/RH from FR72 to FR76 and from FR76 to FR80Note : This task is an alternative to 531806-01-1A.T: 32000FCI: 16000FC531806 ALL531807-01-1A 100/200 N/AGeneral visual inspection of fuselage skin and fail safe ring aroundAFT passenger/crew door cutouts from FR 73 to FR 76, and fromSTR 9 to STR 28, external surface (without scuff plate removal).T: 5000FC10000FHI: 5000FC10000FH-2001531807-01-2A 100/200 N/AGeneral visual inspection of fuselage skin and fail safe ring aroundAFT passenger/crew door cutouts from FR 73 to FR 76, and fromSTR 9 t STR 28 t l f ( ith t ff l t l)T: 4000FC11200FHI 4000FC-3001SSTR 9 to STR 28, external surface (without scuff plate removal). I: 4000FC11200FH531808-01-3A 261/262 833/843 Special detailed inspection (HFEC) of AFT passenger/crew doorcutouts, upper corners including skin and fail safe ring.T: 30000FC60000FHI: 10200FC20400FH531808 -200531808-01-4A 261/262 833/843 Special detailed inspection (HFEC) of AFT passenger/crew doorcutouts, upper corners including skin and fail safe ring.T: 26500FC75000FHI: 6000FC17000FH531808 -300S531809-01-3A 171/172261/262Scuff plateremovalSpecial detailed inspection (US+ HFEC + VISUAL) of fail safe ringand skin of AFT passenger/crew door cutouts at lower corners,underneath the scuff plates.T: 30000FC60000FHI: 12000FC24000FH531809 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 34 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531809-01-4A 171/172261/262Scuff plateremovalSpecial detailed inspection (US+ HFEC + VISUAL) of fail safe ringand skin of AFT passenger/crew door cutouts at lower corners,underneath the scuff plates.T: 24000FC67500FHI: 6300FC17500FH531809 -300S531810-01-1A 261/262 Linings,insulation833/843Detailed inspection of internal structure around AFT passenger/crewdoor cutouts above main deck floor level, from FR 72 to FR 77 andfrom STR 9 to STR 26 LH/RH.T: 25000FCI: 10000FCALL531813-01-1A 261/262 833/843 General visual inspection of door stop fittings on FR 73A and FR75A, LH/RH.T: 18000FCI: 12000FCALL1531820-01-1A 100 N/AGeneral visual inspection of lower skin external surface oflongitudinal 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: 32000FCI: 2250FCALL531902-01-2A 261/262263/264Galleys/lavatories,lining,Insulationdisplaced asrequiredDetailed inspection of rear pressure bulkhead FWD face above maindeck floor level including FR 80/82, rim angle attachments andattachments to skin.T: 30000FCI: 14800FCALL531904 01 2A311/312312 ARD t il d i ti fb lkh d AFT f i l diT 18000FCALL531904-01-2A311/312 312 AR Detailed inspection of rear pressure bulkhead AFT face includingattachment to skin from STR 26 LH/RH to crown center line.T: 18000FCI: 14800FCALL531906-01-1A 311/312 312 AR Detailed inspection of rear pressure bulkhead web AFT face in outercircumferential splice area, at inner rivet row.T: 18000FCI: 9500FCALL531910-01-1A 323 323 AL, BL323 AR, BRDetailed inspection of fuselage skin, external surface in area of fin tofuselage FWD, MID and AFT attach fitting fasteners and visible partof the fittings.T: 40000FC80000FHI: 12300FC24500FH-200531910-01-2A 323 323 AL, BL323 AR, BRDetailed inspection of fuselage skin, external surface in area of fin tofuselage FWD, MID and AFT attach fitting fasteners and visible partof the fittings.T: 35000FC98000FHI: 8100FC22500FH-300S531913-01-1A 311/312 313 AL Special detailed inspection (US) of horizontal stabilizer hinge supportmembers and upper and lower attachment lugs of FR 91 LH/RH.T: 18000FC36000FHI: 15000FC30000FH531913 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 35 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531913-01-2A 311/312 313 AL Special detailed inspection (US) of horizontal stabilizer hinge supportmembers and upper and lower attachment lugs of FR 91 LH/RH.T: 14400FC40500FHI: 12000FC33500FH531913 -300SR 531919-01-1A 300 323 AL, AR Special detailed inspection (LFEC) of rear pressure bulkhead rimangle in the area of frame profile radius.T: 24000FCI: 9000FC531919 POST5526531921-01-1A 311/312 312 AR Special detailed inspection (LHEC) of rear pressure bulkhead AFTface around cutouts for APU fuel line (and trim tank line from MSN378 and on).T: 24000FCI: 6000FC531921 ALL531922-01-1A 311/312 312 AR Detailed inspection of rear pressure bulkhead web AFT face aroundcutouts, except cutout for bleed air duct, APU fuel line (and trim tankline from MSN 378 and on).T: 24000FCI: 6000FCALL531924-01-1A 300 N/ASpecial detailed inspection (LFEC) of fuselage skin at circumferentialsplice at FR 86 from STR 22 to STR 27 LH/RH.T: 28000FC56000FHI: 12000FC24000FH531924 -200531924-01-2A 300 N/ASpecial detailed inspection (LFEC) of fuselage skin at circumferentialsplice at FR 86 from STR 22 to STR 27 LH/RH.T: 22400FC63000FHI: 9600FC27000FH531924 -300S531926-01-4A 311/312 313 AL Special detailed inspection (HFEC) of horizontal stabilizer cutout,lower longeron, corner fitting, skin strap and skin, LH/RH.T: 30000FC60000FHI: 3900FC7800FH531926 -200POST6146531926-01-5A 311/312 313 AL Special detailed inspection (HFEC) of horizontal stabilizer cutout,lower longeron, corner fitting, skin strap and skin, LH/RH.T: 24000FC67500FHI: 3100FC8700FH531926 -300POST6146S531927-01-1A 171311813162 AZ, 312AR,Insulationdisplaced asrequired,bleed air ductSpecial detailed inspection (HFEC + Rotating probe) of rear pressurebulkhead web FWD and AFT faces around cutout for bleed air duct.T: 24000FCI: 6000FC531927 ALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 36 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items545002-P1-1A 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 40000FC80000FHI: 8100FC16200FH545002 -200 PW545002-G1-1A 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 40000FC80000FHI: 6800FC13600FH545002 -200 GE CF6-80A3545002-G1-3A 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 40000FC80000FHI: 5900FC11800FH545002 -200 GE CF6-80C2545002-P1-3A 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 35000FC97900FHI: 10500FC29500FH545002 -300 PW JT9D S545002-P1-5A 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 35000FC97900FHI: 9100FC25500FH545002 -300 PW 4000 S545002 G1 5A415/416451/461 ALS i l d t il d i ti (Ult i ) f l id tt h tT 35000FC545002300 GES545002-G1-5A415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 35000FC98000FHI: 3100FC8800FH545002 -300 GES545003-P1-1A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 4600FC9200FHI: 4600FC9200FH-200 PW545003-G1-1A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 2600FC5200FHI: 2600FC5200FH-200 GE CF6-80A3545003-G1-2A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 2200FC4500FHI: 2200FC4500FH-200 GE CF6-80C2 PRE 6080Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 37 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items545003-G1-3A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 3000FC6000FHI: 3000FC6000FH-200 GE CF6-80C2 POST 6080545003-P1-2A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 9800FC27500FHI: 9800FC27500FH-300 PW JT9D S545003-P1-4A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 8400FC23800FHI: 8400FC23800FH-300 PW 4000PRE 6080S545003-P1-5A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 11300FC31600FHI: 11300FC31600FH-300 PW 4000POST 6080S545003-G1-4A 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 2000FC5600FHI: 2000FC5600FH-300 GE PRE6080S545003 G1 5A415/416451/461 ALD t il d i ti f l t i FWD tt h fitti ( id)T 2700FC300 GE POSTS545003-G1-5A415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 2700FC7500FHI: 2700FC7500FH-300 GE POST6080S545008-G1-1A 453/454463/464Engineremoved,engine AFTmount upperbeam removedSpecial detailed inspection (Liquid Penetrant) of pylon-to engine AFTattachment beam assembly, including mating face with engine AFTmount.T: 20000FCI: 20000FCGE CMM71.20.05GE CF6-80C2545008-G1-2A 453/454463/464Engineremoved,engine AFTmount upperbeam removedSpecial detailed inspection (Liquid Penetrant) of pylon-to engine AFTattachment beam assembly, including mating face with engine AFTmount.T: 10000FCI: 10000FCGE CMM71.20.05GE CF6-80A3Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 38 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items545028-01-2A 435/436445/446451/452461/462435/445 AL451/461 AL436/446 AR452/462 ARDetailed inspection of engine cowl hinge fittings, LH/RH (includingbolts and nacelle hinge side).T: 700FC1450FHI: 700FC1450FH-200545028-01-3A 435/436445/446451/452461/462435/445 AL451/461 AL436/446 AR452/462 ARDetailed inspection of engine cowl hinge fittings, LH/RH (includingbolts and nacelle hinge side).T: 700FC1950FHI: 700FC1950FH-300S545030-01-2A 473/474483/484473/483 AL,474/484 ARDetailed inspection of pylon lateral panels at the edge of access doorcutouts between ribs 13 and 14, LH/RH.T: 10400FC20800FHI: 10400FC20800FH-200545030-01-3A 473/474483/484473/483 AL,474/484 ARDetailed inspection of pylon lateral panels at the edge of access doorcutouts between ribs 13 and 14, LH/RH.T: 10400FC29100FHI: 10400FC29100FH-300S545043-G1-3A 415/416425/426N/ADetailed inspection of pylon side panels at rib 8, LH/RHT: 28300FC79400FHI: 10000FC28000FH-300 GE POST10432S545043-P1-3A 415/416425/426N/ADetailed inspection of pylon side panels at rib 8, LH/RHT: 23600FC59100FH-300 PW POST10432S425/426I: 9300FC23200FH10432551015-01-2A 333/343 333/343 AB,AT334/344 AB,ATTHS BellCrank andPush RodAutopilot PitchActuator (LHonly)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: 19500FC38400FHI: 8200FC16500FH551015 -200551018-01-2A 319333/343312 AR313 AL331/341 BBDetailed inspection of horizontal stablizer spar box internal structurein area of hinge fitting attachments, both sides of rib 3 and top skinrear spar upper cap between rib 2 and rib 3, LH/RHT: 33000FC66000FHI: 5100FC10300FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 39 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items551020-01-1A 333/343 333/343 AT Detailed inspection of horizontal stabilizer outer box top skin uppersurface 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: 14700FC29400FHI: 6200FC12500FH-200POST 6070551020-01-3A 333/343 333/343 ATrearmost apronfittingDetailed 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: 27400FC76700FHI: 6300FC17600FH-300S551020-02-1A 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre boxtop 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: 14700FC29400FHI: 6200FC12500FH551020 -200POST 6070551020-02-3A 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre boxtop skin upper surface chordwise splice between rib 3 and rib 4 fromrear spar to STR 9, LH/RH.N tThit khtbdtthtit k551020 01T: 27400FC76700FHI: 6300FC17600FH551020 -300SNote: 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 uppersurface chordwise splice between rib 3 and rib 4 from rear spar toSTR 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: 34200FC68400FHI: 6200FC12500FH-200PRE 6070551021-02-1A 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre boxtop skin upper surface chordwise splice between rib 3 and rib 4 fromrear spar to STR 9, excluding the attachment to the reinforcementplate, LH/RH.Note: This task has to be done at the same time as task 551021-01-1A.T: 34200FC68400FHI: 6200FC12500FH551021 -200PRE 6070Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 40 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items551022-01-2A 333/343 333/343 AT Detailed inspection of horizontal stabilizer outer box top skin uppersurface chordwise splice between rib 3 and rib 4 from STR 9 to frontspar, LH/RH.Note: This task has to be done at the same time as task 551022-02-2A.T: 38300FC76600FHI: 4800FC9600FH-200WFD551022-02-2A 333/343 333/343 AT Special detailed inspection (Ultrasonic) of horizontal stabilizer centrebox top skin upper surface chordwise splice between rib 3 and rib 4from STR 9 to front spar, LH/RH.Note: This task has to be done at the same time as task 551022-01-2A.T: 38300FC76600FHI: 4800FC9600FH551022 -200WFD551025-01-1A 311/312 313 AL Detailed inspection of horizontal stabilizer rear spar joining partinboard side at rib 3, LHRH.T: 33000FC66000FHI: 5100FC10300FH-200551026-01-1A 331/341 331/341 AB,BB, CBDetailed inspetion of horizontal stabilizer front spar web atattachment of upper T profile from rib 3 to rib 12, LH/RH.T: 32500FC65000FHI: 14400FC28900FH-200551027-01-1A 334/344 334/344 BB,CBDetailed inspetion of horizontal stabilizer rear spar web attt h t f T fil f ib 3 t ib 9 LH/RHT: N/A99400FH-200CBattachment of upper T profile from rib 3 to rib 9, LH/RH.99400FHI: 3600FC7200FH551028-01-1A 300 N/ADetailed inspection of horizontal stabilizer top skin from fuselagefairing to rib 5, LH/RH.T: 32000FC64100FHI: 4100FC8200FH-200WFD551029-01-1A 300 N/ADetailed inspection of horizontal stabilizer top skin at attachment tothe front spar T profile from rib 3 to rib 12, LH/RH.T: 32500FC65000FHI: 7300FC14600FH-200551030-01-1A 300 N/ADetailed inspection of horizontal stabilizer top skin at attachment tothe rear spar T profile from rib 3 to rib 9, LH/RH.T: N/A99400FHI: 7300FC14600FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 41 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items551075-01-1A 311/312 313 AL Detailed inspection of horizontal stabilizer rear spar joining partinboard side at rib 3, LHRH.T: 28300FC79200FHI: 6900FC19400FH-300S553002-01-1A 300 N/AGeneral visual inspection of vertical stabilizer skin panels LH/RH,from front to rear spar and from fin/fuselage fairing to tip, externalsurface.T: 18000FC36000FHI: 13600FC27000FH-200PRE 48861553003-01-1A 323 311 AZ, BZ312 AR323 AL, AR,BL, BRDetailed inspection of FWD, center and AFT vertical stabilizer tofuselage attach and side load fittings.T: 40000FC80000FHI: 6000FC12000FH-200PRE 4886553011-01-1A 323 311 AZ, BZ312 ARGeneral visual inspection of vertical stabilizer center box internalstructure from rib 1 to 12.T: 30000FC60000FHI: 9900FC19500FH-200PRE 4886553017-01-1A 323 N/ADetailed inspection of vertical stabilizer skin panels LH/RH from frontto rear spar and from fin/fuselage fairing to tip rib 12, externalsurface.T: 40000FC80000FHI: 6000FC12000FH-200PRE 4886R553019 01 1A323AD t il d i ti f ti l t bili ki t j i t ib 16 t lT 40000FC200553019-01-1N/Detailed inspection of vertical stabilizer skin at joint rib 16, externalsurface.T: 40000FC80000FHI: 8900FC17500FH-200PRE 4886571002-01-1A 141/142 734, 744147/148AZSealantRemovalDetailed inspection of center wing box front spar upper cap from Rib1 LH to Rib 1 RH, inside fuel tank, excluding angle fittingsT: 36800FCI: 10700FC-200PRE 4977571006-01-1A 141/142 N/ASpecial detailed inspection (Ultrasonic) of lower panel at wing tofuselage lower attachment, inboard side, between FR42.1 and FR44,LH/RH.T: 35900FC71900FHI: 4100FC8200FH571006 -200571008-01-1A 540/640 540/640 AB Special detailed inspection (X-RAY) of outboard horizontal flange oflower T section, inboard row of fasteners from front spar to rear spar,LH/RH.T: 40650FC81300FHI: 9950FC19900FH571008 -200WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 42 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571008-01-2A 540/640 540/640 AB Special detailed inspection (X-RAY) of outboard horizontal flange oflower T section, inboard row of fasteners from front spar to rear spar,LH/RH.T: 32500FC91150FHI: 7950FC22250FH571008 -300WFDS571009-01-1A 141/142 734/744147/148 AZDetailed inspection of center wing box rear spar around access doorcutouts.T: 15400FC30800FHI: 8600FC17200FH-200571009-01-2A 141/142 734/744147/148 AZDetailed inspection of center wing box rear spar around access doorcutouts.T: 14200FC39800FHI: 11200FC31500FH-300S571013-01-2A 241/242 Sidewallpanels,Insulationdisplaced asrequired,241 LW, MW,242 LW, MWSpecial detailed inspection (Ultrasonic) of FR 47/48, FWD and AFTfaces from STRs 22 to 24, LH/RH.T: 28000FC56000FHI: 4700FC9500FH571013 -200571013-01-4A 241/242 Sidewallpanels,I l tiSpecial detailed inspection (Ultrasonic) of FR 47/48, FWD and AFTfaces from STRs 22 to 24, LH/RH.T: 27100FC75800FHI 4600FC571013 -300SInsulationdisplaced asrequired,241 LW, MW,242 LW, MWI: 4600FC13100FH571022-01-1A 541/542641/642540/640ABSealantRemovalSpecial detailed inspection (Ultrasonic) of stiffener at wing tofuselage lower attachment, outboard side between FR43 and FR45,at stiffeners 7, 8 and 9, LH/RH.T: 17100FC34200FHI: 2900FC5900FH571022 -200571022-01-3A 541/542641/642540/640ABSealantRemovalSpecial detailed inspection (Ultrasonic) of stiffener at wing tofuselage lower attachment, outboard side between FR43 and FR45,at stiffeners 7, 8 and 9, LH/RH.T: 15900FC44400FHI: 2200FC6200FH571022 -300S571023-01-1A 141142734/744147/148AZ,boltsSpecial detailed inspection (Rotating Probe) of center wing box lowerskin at pump holes reinforcing plates upper side, from FR 46 to 47and from beams 3 to 5, LH/RH .T: 30500FC61100FHI: 15000FC30000FH571023 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 43 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571023-01-2A 141142734/744147/148AZ,boltsSpecial detailed inspection (Rotating Probe) of center wing box lowerskin at pump holes reinforcing plates upper side, from FR 46 to 47and from beams 3 to 5, LH/RH.T: 31300FC87500FHI: 13300FC37100FH571023 -300S571024-01-3A 141/142 734/744,147/ 148 AZ,SealantremovalSpecial detailed inspection (Ultrasonic) of center wing box front sparlower cap corner fitting and adjacent front spar structure, LH/RH.T: 21500FC43100FHI: 15800FC31600FH571024 -200571024-01-4A 141/142 734/744,147/ 148 AZ,SealantremovalSpecial detailed inspection (Ultrasonic) of center wing box front sparlower cap corner fitting and adjacent front spar structure, LH/RH.T: 20100FC56300FHI: 12300FC34400FH571024 -300S571026-01-1A 141/142 Main deck floorpanels, galleysand toilets (ifinstalled)SealantRemovalSpecial detailed inspection (Ultrasonic) of inboard side of cruciformfitting at junction with stiffeners between FR40-1 and FR44-2, LH/RHT: 39950FC79900FHI: 5550FC11050FH571026 -200571026-01-2A 141/142 Main deck floorpanels, galleysd t il t (ifSpecial detailed inspection (Ultrasonic) of inboard side of cruciformfitting at junction with stiffeners between FR40-1 and FR44-2, LH/RHT: 24200FC67800FHI 3750FC571026 -300Sand toilets (ifinstalled)SealantRemovalI: 3750FC10550FH571028-01-1A 141/142 Main deck floorpanels, galleysand toilets (ifinstalled)SealantRemovalSpecial detailed inspection (Ultrasonic) of center wing box upperpanel between stiffeners 43.2 and 44.1 at cruciform fitting junction,LH/RHT: 40000FC80000FHI: 11200FC22500FH571028 -200571028-01-2A 141/142 Main deck floorpanels, galleysand toilets (ifinstalled)SealantRemovalSpecial detailed inspection (Ultrasonic) of center wing box upperpanel between stiffeners 43.2 and 44.1 at cruciform fitting junction,LH/RHT: 22400FC62900FHI: 7000FC19700FH571028 -300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 44 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571040-01-1A 540/640 577/677AT577/677BTSealantRemovalSpecial detailed inspection (HFEC) of cruciform at upper wing skin tofuselage joint from FR 40/41 to 47/48, upper outboard radius, LH/RHT: 23100FC46200FHI: 12500FC25000FH571040 -200571040-01-3A 540/640 577/677AT577/677BTSealantRemovalSpecial detailed inspection (HFEC) of cruciform at upper wing skin tofuselage joint from FR 40/41 to 47/48, upper outboard radius, LH/RHT: 21900FC61400FHI: 12100FC33900FH571040 -300SR 571041-01-2A 540/640 577/677 AT577/677 BTDetailed inspection of cruciform at upper wing skin to fuselage jointfrom FR 40/41 to FR 47/48, outboard flange upper surface, LH/RH.T: 23000FC46000FHI: 4000FC8000FH-200R 571041-01-3A 540/640 577/677 AT577/677 BTDetailed inspection of cruciform at upper wing skin to fuselage jointfrom FR 40/41 to FR 47/48, outboard flange upper surface, LH/RH.T: 22100FC62000FHI: 4300FC12000FH-300S571042-01-2A 540/640 540/640ABSealantRemovalDetailed inspection of outer wing upper skin stringer end fittings andadjacent part of stringers at Rib 1, from front to rear spar, LH/RH.Note: This task is an alternative to 571042-02-1AT: 32150FC100800FHI: 7250FC14500FH-200WFD571042-01-3A 540/640 540/640ABSealantRemovalDetailed inspection of outer wing upper skin stringer end fittings andadjacent part of stringers at rib 1, from front to rear spar, LH/RH.Note: This task is an alternative to 571042-02-2AT: 32300FC90650FHI: 7150FC20000FH-300WFDS571042-02-1A 540/640 540/640ABSealantRemovalSpecial detailed inspection (Ultrasonic) of outer wing upper skinstringer end fittings and adjacent part of stringers at Rib 1, from frontto rear spar, LH/RH.Note: This task is an alternative to 571042-01-2AT: 32150FC100800FHI: 11650FC23300FH571042 -200WFD571042-02-2A 540/640 540/640ABSealantRemovalSpecial detailed inspection (Ultrasonic) of outer wing upper skinstringer end fittings and adjacent part of stringers at rib 1, from frontto rear spar, LH/RH.Note: This task is an alternative to 571042-01-3AT: 32300FC90650FHI: 11500FC32200FH571042 -300WFDSIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 45 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571043-01-1A 540/640 540/640AB Special detailed inspection (Ultrasonic) of outer wing rear spar to rib1 junction, vertical tee splice fitting outboard flange, LH/RHT: 32900FC65800FHI: 8900FC17800FH571043 -200571043-01-3A 540/640 540/640AB Special detailed inspection (Ultrasonic) of outer wing rear spar to rib1 junction, vertical tee splice fitting outboard flange, LH/RHT: 32300FC90600FHI: 8800FC24600FH571043 -300S571045-01-2A 143/144 147BZ734/744vapour sealdisplacedDetailed inspection of center wing box bottom skin lower surface inair conditioning bay.T: 20400FC40900FHI: 11200FC22500FH-200571045-01-3A 143/144 147BZ734/744vapour sealdisplacedDetailed inspection of center wing box bottom skin lower surface inair conditioning bay.T: 19800FC55700FHI: 10800FC30200FH-300S571047-01-1A 143/144 147BZ734/744vapour sealdisplacedSealantRemovalSpecial detailed inspection (Ultrasonic and Rototest) of center wingbox bottom skin lower surface in beam attachment areas from frontto rear spars and from Rib 1 LH to Rib 1 RH.T: 20400FC40900FHI: 17300FC34500FH571047 -200PRE 5028Removal571047-01-2A 143/144 147BZ734/744vapour sealdisplacedSealantRemovalSpecial detailed inspection (Ultrasonic and Rototest) of center wingbox bottom skin lower surface in beam attachment areas from frontto rear spars and from Rib 1 LH to Rib 1 RH.T: 25800FC51700FHI: 20500FC41100FH571047 -200POST 5028571047-01-3A 143/144 147BZ734/744vapour sealdisplacedSealantRemovalSpecial detailed inspection (Ultrasonic and Rototest) of center wingbox bottom skin lower surface in beam attachment areas from frontto rear spars and from Rib 1 LH to Rib 1 RH.T: 19800FC55700FHI: 15800FC44300FH571047 -300S571051-01-1A 141142734/744147/148 AZ,boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of center wing box rearspar to Rib 1 junction vertical T splice fitting and angle fitting, LH/RHT: 31900FC63850FHI: 7800FC15650FH571051 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 46 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571051-01-2A 141142734/744147/148 AZ,boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of center wing box rearspar to Rib 1 junction vertical T splice fitting and angle fitting, LH/RHT: 26600FC74500FHI: 8800FC24650FH571051 -300S571052-01-1A 540640540AB640AB, boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of outer wing rear sparto Rib 1 junction angle fitting, LH/RHT: 43850FC87700FHI: 11200FC22400FH571052 -200571052-01-2A 540640540AB640AB, boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of outer wing rear sparto Rib 1 junction angle fitting, LH/RHT: 35750FC100250FHI: 12250FC34450FH571052 -300S571053-01-1A 540640540AB640ABSealantRemovalDetailed inspection of outer wing upper skin fittings at junction withRib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-02-1AT: 32500FC65050FHI: 3950FC7950FH-200571053-01-2A 540640540AB640ABSealantRemovalDetailed inspection of outer wing upper skin fittings at junction withRib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-02-2AT: 32250FC90450FHI: 3800FC10600FH-300S571053 02 1A540540ABS i l d t il d i ti (R t ti P b ) f t i kiT 32500FC571053200571053-02-1A640540AB640AB, boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of outer wing upper skinfittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-01-1AT: 32500FC65050FHI: 23600FC47200FH571053 -200571053-02-2A 540640540AB640AB, boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of outer wing upper skinfittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-01-2AT: 32250FC90450FHI: 22450FC62950FH571053 -300S571054-01-1A 145/146 Main deck floorpanels, boltsremovalSpecial detailed inspection (Rotating Probe) of upper cruciform fittingjunction with fuselage panel at FR43A, LH/RHT: 26000FC52100FHI: 7200FC14400FH571054 -200571054-01-2A 145/146 Main deck floorpanels, boltsremovalSpecial detailed inspection (Rotating Probe) of upper cruciform fittingjunction with fuselage panel at FR43A, LH/RHT: 39300FCN/A FHI: 9500FC26700FH571054 -300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 47 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571056-01-1A 540/640 540/640AB Special detailed inspection (Ultrasonic) of wing upper surface panelbetween stiffener 5 and 6 at cruciform fitting end, LH/RHT: N/A FC100000FHI: 1650FC3350FH571056 -200571056-01-2A 540/640 540/640AB Special detailed inspection (Ultrasonic) of wing upper surface panelbetween stiffener 2 and 7 at cruciform fitting end, LH/RHT: 37550FCN/A FHI: 1500FC4250FH571056 -300S571061-01-1A 540/640 540/640 ABSealantRemovalSpecial detailed inspection (Ultrasonic) of outboard horizontal flangeof lower T section, inboard row of fasteners at stiffener 7 andstiffener 9, LH/RHNote : Grace period of 1100FC.T: 23350FC46650FHI: 7700FC15400FH571061 -200571061-01-2A 540/640 540/640 ABSealantRemovalSpecial detailed inspection (Ultrasonic) of outboard horizontal flangeof lower T section, inboard row of fasteners at stiffener 7 andstiffener 9, LH/RHNote : Grace period of 1100FC.T: 20250FC56750FHI: 6150FC17250FH571061 -300S571062-01-1A 540/640 N/ASpecial detailed inspection (Ultrasonic) of lower splice betweenFR40/41 and FR47/48 at the first row of fasteners from Rib 1 datum(wing side), LH/RH.T: 29000FC58050FHI: 4600FC9200FH571062 -200Note : Grace period of 1100FC.9200FH571062-01-2A 540/640 N/ASpecial detailed inspection (Ultrasonic) of lower splice betweenFR40/41 and FR47/48 at the first row of fasteners from Rib 1 datum(wing side), LH/RH.Note : Grace period of 1100FC.T: 21850FC61300FHI: 3450FC9700FH571062 -300S571067-01-1A 141/142 N/ASpecial detailed inspection (Ultrasonic) of center wing box lowersplice at Rib 1, first fasteners row from Rib 1 datum betweenstiffener 42.2 and 44.1, LH/RHT: 27600FC55200FHI: 10650FC21300FH571067 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 48 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571067-01-2A 141/142 N/ASpecial detailed inspection (Ultrasonic) of center wing box lowersplice at Rib 1, first fasteners row from Rib 1 datum betweenstiffener 42.2 and 44.1, LH/RHT: 29750FC83500FHI: 7950FC22350FH571067 -300S571068-01-1A 141/142 N/ASpecial detailed inspection (Ultrasonic) of center wing box lowersplice at Rib 1, first fasteners row from Rib 1 datum betweenstiffener 44.2 and 46.2, LH/RHT: 40400FC80850FHI: 11700FC23400FH571068 -200571068-01-2A 141/142 N/ASpecial detailed inspection (Ultrasonic) of center wing box lowersplice at Rib 1, first fasteners row from Rib 1 datum betweenstiffener 44.2 and 46.2, LH/RHT: 34600FC97100FHI: 8700FC24350FH571068 -300S571069-01-1A 141/142 734/744147/148AZbolts to beremovedSealantRemovalSpecial detailed inspection (Rotating Probe) of center wing boxbottom skin stiffener at FR44 level, LH/RH.T: 42650FC85300FHI: 4000FC8000FH571069 -200571069-01-2A 141/142 734/744147/148AZbolts to beremovedSealantRemovalSpecial detailed inspection (Rotating Probe) of center wing boxbottom skin stiffener at FR44 level, LH/RH.T: 38250FC107350FHI: 3400FC9600FH571069 -300PRE 8133S572006-01-2A 532/632533/633534/634535/635532/533/534/535/632/633/634/635AB, BB, CBDetailed inspection of flap track beams No. 2, 3, 4 and 5 lower flangetitanium and steel straps.T: 30000FCI: 11400FCALL572008-01-2A 534/634 534/634 AB,BBDetailed inspection of flap track beam No. 4 FWD attachment forkbracket lugs.T: 30000FCI: 9600FCALL572011-01-2A 577/677 Flaps extended Detailed inspection of flap track beam No. 1 to fuselage attachmentmembers including track attachments and roller support assembly.T: 30000FCI: 11200FCALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 49 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572016-01-2A 532/533/534/535632/633/634/635532/533/534/535/632/633/634/635AB, BBDetailed inspection of flap track beams No. 2, 3, 4 and 5 frontattachment shear bolts.T: 30000FCI: 9400FCALLR 572104-01-3A 512/612 512/612 CB,EB, HBDetailed inspection of outer wing front spar FWD face from ribs 1 to7 at slat track cutouts (3 places).T: 17600FC35300FHI: 2400FC4800FH-200R 572104-01-4A 512/612 512/612 CB,EB, HBDetailed inspection of outer wing front spar FWD face from ribs 1 to7 at slat track cutouts (3 places).T: 17500FC49100FHI: 2300FC6600FH-300S572105-01-3A 523/623 523/623 BB,CBDetailed inspection of outer wing front spar forward face splice plateat rib 10.T: 37800FC75700FHI: 8600FC17300FH-200572105-01-4A 523/623 523/623 BB,CBDetailed inspection of outer wing front spar forward face splice plateat rib 10.T: 36200FC101100FHI: 8200FC23100FH-300S572107-01-1A 540/640 540/640 AB,BBDetailed inspection of outer wing front spar AFT face from ribs 1 to7T: 13200FC26400FH-200BB7.Note : This task is an alternative to 572107-02-1AI: 6400FC12900FHR 572107-01-2A 540/640 540/640 AB,BBDetailed inspection of outer wing front spar AFT face from ribs 1 to7.Note : This task is an alternative to 572107-02-2AT: 13200FC37100FHI: 9600FC26900FH-300S572107-02-1A 540/640 N/ASpecial detailed inspection (Ultrasonic) of outer wing front spar AFTface from ribs 1 to 7.Note : This task is an alternative to 572107-01-1AT: 13200FC26400FHI: 9900FC19800FH572107 -200N 572107-02-2A 540/640 N/ASpecial detailed inspection (Ultrasonic) of outer wing front spar AFTface from ribs 1 to 7.Note : This task is an alternative to 572107-01-2AT: 13200FC37100FHI: 9900FC27800FH572107 -300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 50 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572108-01-3A 540/640 540/640 CB,DBDetailed inspection of outer wing front spar AFT face from ribs 7 to9.T: 24300FC48700FHI: 6000FC12100FH-200572108-01-4A 540/640 540/640 CB,DBDetailed inspection of outer wing front spar AFT face from ribs 7 to9.T: 24000FC67100FHI: 8900FC24900FH-300S572109-01-1A 540/640550/650540/640 EB,FB, GB, HB550/650 AB,BB, CBDetailed inspection of outer wing front spar AFT face from ribs 9 to17.T: 15000FC30100FHI: 3850FC7700FH-200 PRE 3510572109-01-2A 540/640550/650540/640 EB,FB, GB, HB550/650 AB,BB, CBDetailed inspection of outer wing front spar AFT face from ribs 9 to17.T: 15000FC30100FHI: 7900FC15900FH-200 POST 3510572109-01-3A 540/640550/650540/640 EB,FB, GB, HB550/650 AB,BB, CBDetailed inspection of outer wing front spar AFT face from ribs 9 to17.T: 13500FC37800FHI: 7100FC20000FH-300 PRE 7088(SB 00-2012)S572109 01 4A540/640540/640 EBD t il di tiftif tAFTffib9tT 13500FC300 POST 7088S572109-01-4A540/640550/650540/640 EB,FB, GB, HB550/650 AB,BB, CBDetailed inspection of outer wing front spar AFT face from ribs 9 to17.T: 13500FC37800FHI: 6000FC17000FH-300 POST 7088(SB 00-2012)S572111-01-4A 571/671 N/ADetailed inspection of outer wing rear spar AFT face and attachmentangle from rib 1 to 3.T: 36200FC72400FHI: 2700FC5400FH-200572111-01-5A 571/671 N/ADetailed inspection of outer wing rear spar AFT face and attachmentangle from rib 1 to 3.T: 36100FC101200FHI: 2700FC7600FH-300S572115-01-3A 575/675 575/675 DB Detailed inspection of outer wing rear spar aft face splice plate at rib10.T: 31200FC62500FHI: 6900FC13900FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 51 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572115-01-4A 575/675 575/675 DB Detailed inspection of outer wing rear spar aft face splice plate at rib10.T: 31600FC88600FHI: 7000FC19800FH-300S572116-01-1A 571/671540/640540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar atselected bolt locations, for attachment of MLG FWD pick up fittingand MLG rib 5 AFT of rear spar, 31 holes, LH/RH.T: 16100FC45100FHI: 7100FC19800FH572116 -300POST 7601S572117-01-5A 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1to 3.T: 24300FC48700FHI: 8500FC17000FH-200572117-01-6A 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1to 3.T: 24300FC48700FHI: 8100FC16300FH-200C572117-01-7A 540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1to 3.T: 24600FC69000FHI: 8500FC24000FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)S572117 01 8A540/640540/640 ABD t il d i ti f t if d f f ib 1T 24600FC300 POST 8130S572117-01-8A540/640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1to 3.T: 24600FC69000FHI: 7000FC19600FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)S572118-01-4A 540/640 540/640 AB,BBDetailed inspection of outer wing rear spar forward face from ribs 3to 6.T: 24400FC48900FHI: 8900FC17900FH-200572118-01-5A 540/640 540/640 AB,BBDetailed inspection of outer wing rear spar forward face from ribs 3to 6.T: 24000FC67400FHI: 8800FC24700FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)S572118-01-6A 540/640 540/640 AB,BBDetailed inspection of outer wing rear spar forward face from ribs 3to 6.T: 24000FC67400FHI: 7200FC20200FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 52 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572119-01-5A 540/640 540/640 BB,CB, DBDetailed inspection of outer wing rear spar FWD face from ribs 6 to10.T: 24700FC49400FHI: 12500FC25000FH-200572119-01-6A 540/640 540/640 BB,CB, DBDetailed inspection of outer wing rear spar FWD face from ribs 6 to10.T: 24700FC49400FHI: 12000FC24000FH-200C572119-01-7A 540/640 540/640 BB,CB, DBDetailed inspection of outer wing rear spar FWD face from ribs 6 to10.T: 24600FC69000FHI: 12500FC35000FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)S572119-01-8A 540/640 540/640 BB,CB, DBDetailed inspection of outer wing rear spar FWD face from ribs 6 to10.T: 24600FC69000FHI: 10200FC28500FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)S572120-01-3A 540/640 540/640 EB toHBDetailed inspection of outer wing rear spar FWD face from ribs 10 to14.T: 23500FC47000FHI: 11400FC22800FH-200572120-01-4A 540/640 540/640 EB toHBDetailed inspection of outer wing rear spar FWD face from ribs 10 to14.T: 23500FC65800FHI: 11400FC31900FH-300S572122-01-1A 540/640571/671540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar atselected bolt locations for attachment of MLG FWD pick-up fittingand MLG rib 5 AFT of rear spar, 26 holes, LH/RH.T: 17700FC35500FHI: 9800FC19600FH572122 -200572122-01-2A 540/640571/671540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar atselected bolt locations for attachment of MLG FWD pick-up fittingand MLG rib 5 AFT of rear spar, 26 holes, LH/RH.T: 17300FC48500FHI: 7100FC19800FH572122 -300PRE 7601S572137-01-3A 540/640 540/640 AB,BB,CBDetailed inspection of outer wing bottom skin butt strap at STR 8from ribs 1 to 9.T: 18000FC38300FHI: 6300FC12600FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 53 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572137-01-4A 540/640 540/640 AB,BB,CBDetailed inspection of outer wing bottom skin butt strap at STR 8from ribs 1 to 9.T: 18000FC51800FHI: 6100FC17000FH-300S572138-01-3A 540/640 540/640 DB toHBDetailed inspection of outer wing bottom skin butt strap at STR 8from ribs 9 to 14.T: 25400FC50800FHI: 6300FC12700FH-200572138-01-4A 540/640 540/640 DB toHBDetailed inspection of outer wing bottom skin butt strap at STR 8from ribs 9 to 14.T: 24900FC69900FHI: 6200FC17400FH-300S572141-02-1A 540/640 540/640 AB toHBSpecial detailed inspection (HFEC) of outer wing bottom skin aroundmanhole surrounds between ribs 2 and 14, LH and RH wings.T: 13600FC27300FHI: 10700FC21500FH572141 -200572141-02-2A 540/640 540/640 AB toHBSpecial detailed inspection (HFEC) of outer wing bottom skin aroundmanhole surrounds between ribs 2 and 14, LH and RH wings.T: 13400FC37600FHI: 10600FC29600FH572141 -300SR572142 01 3A500/600540/640 GBS i l d t il d i ti (Ult i ) f t i b tt kiT 27800FC572142200572142-01-3500/600530/630540/640 GB,HBFlap Track 3fairing bracketsremoved.Special detailed inspection (Ultrasonic) of outer wing bottom skinlower surface at attachment to stringers 9 and 12 adjacent to accessdoor cutouts from ribs 1 to 14.T: 27800FC55600FHI: 9300FC18700FH572142 -200R 572142-01-4A 500/600530/630540/640 GB,HBFlap Track 3fairing bracketsremoved.Special detailed inspection (Ultrasonic) of outer wing bottom skinlower surface at attachment to stringers 9 and 12 adjacent to accessdoor cutouts from ribs 1 to 14.T: 26900FC75600FHI: 9100FC25500FH572142 -300S572143-01-2A 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment 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: 16500FC33000FHI: 4350FC8700FH-200 PRE 10685(SB 00-2024)1Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 54 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572143-01-3A 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment 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: 16500FC33000FHI: 3700FC7400FH-200 POST10685(SB 00-2024)1572143-01-4A 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment 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: 18000FC52200FHI: 4250FC11900FH-300 1S572143-02-1A 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment 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: 16500FC33000FHI: 11500FC23000FH-200 PRE 10685(SB 00-2024)572143-02-2A 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment 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: 16500FC33000FHI: 9900FC19800FH-200 POST10685(SB 00-2024)572143-02-3A 500/600 N/ADetailed inspection of outer wing top skin upper surface attt h ttf tfib1t14dfib7tT: 18000FC52200FH-300 Sattachment 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.52200FHI: 11200FC31300FH572144-01-1A 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment to rear spar from ribs 1 to 7.T: 16000FC32000FHI: 3800FC7600FH-200 PRE 10685(SB 00-2024)572144-01-2A 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment to rear spar from ribs 1 to 7.T: 16000FC32000FHI: 3200FC6400FH-200 POST10685(SB 00-2024)572144-01-4A 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment to rear spar from ribs 1 to 7.T: 18300FC51200FHI: 3800FC10600FH-300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 55 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572145-01-2A 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).T: 15200FC30400FHI: 5550FC11100FH-200 PRE 10685(SB 00-2024)1572145-01-3A 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).T: 15200FC30400FHI: 4100FC8200FH-200 POST10685(SB 00-2024)1572145-01-4A 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).T: 18000FC52200FHI: 5550FC15500FH-3001S572147-01-4A 540/640 540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.T: 36900FC73800FHI: 9400FC18900FH572147 -200 PRE 10685(SB 00-2024)572147-01-5A 540/640 540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.T: 36900FC73800FHI: 8200FC16400FH572147 -200 POST10685(SB 00-2024)572147 01 6A540/640540/640 CBS ild t il di ti(X R )ftitkidT 36900FC572147300S572147-01-6A540/640 540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.T: 36900FC103300FHI: 8500FC23900FH572147 -300S572151-01-4A 540/640 540/640 AB toHBDetailed inspection of outer wing top skin stringers from ribs 1 to 14. T: 14600FC29200FHI: 12000FC24000FH-200 PRE 10685(SB 00-2024)572151-01-5A 540/640 540/640 AB toHBDetailed inspection of outer wing top skin stringers from ribs 1 to 14. T: 14600FC29200FHI: 11500FC23000FH-200 POST10685(SB 00-2024)Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 56 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 572153-01-1A 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BR540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing bottom skin lowersurface reinforcing at ribs 8 and 9 and adjacent skin, including skincovered by pylon fairings.Note : This task has to be performed at the same time as task572153-02-1A.T: 15200FC30500FHI: 9700FC19400FH572153 -200R 572153-01-2A 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BR540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing bottom skin lowersurface reinforcing at ribs 8 and 9 and adjacent skin, including skincovered by pylon fairings.Note : This task has to be performed at the same time as task572153-02-2A.T: 15000FC42000FHI: 9500FC26700FH572153 -300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)SR 572153-01-3A 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BR540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing bottom skin lowersurface reinforcing at ribs 8 and 9 and adjacent skin, including skincovered by pylon fairings.Note : This task has to be performed at the same time as task572153-02-3A.T: 15000FC42000FHI: 8900FC25000FH572153 -300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)SDBR 572153-02-1A 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BRDetailed inspection of outer wing bottom skin lower surfacereinforcing at ribs 8 and 9 and adjacent skin, including skin coveredby pylon fairings.Note : This task has to be performed at the same time as task572153-01-1A.T: 15200FC30500FHI: 9700FC19400FH-200R 572153-02-2A 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BRDetailed inspection of outer wing bottom skin lower surfacereinforcing at ribs 8 and 9 and adjacent skin, including skin coveredby pylon fairings.Note : This task has to be performed at the same time as task572153-01-2A.T: 15000FC42000FHI: 9500FC26700FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 57 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 572153-02-3A 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BRDetailed inspection of outer wing bottom skin lower surfacereinforcing at ribs 8 and 9 and adjacent skin, including skin coveredby pylon fairings.Note : This task has to be performed at the same time as task572153-01-3A.T: 15000FC42000FHI: 8900FC25000FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)S572157-01-1A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment 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: 16500FC33000FHI: 3900FC7900FH-200572157-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment 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: 16000FC44800FHI: 4300FC12200FH-300S572159-01-3A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to rear spar from ribs 1 to 3.T: 32700FC65400FHI: 5300FC10700FH-200572159-01-4A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to rear spar from ribs 1 to 3.T: 31300FC87600FHI 5100FC-300SI: 5100FC14300FH572161-01-1A 500/600 N/AGeneral visual inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.T: 18000FC42000FHI: 3100FC6200FH-2001R 572161-01-2A 500/600 N/AGeneral visual inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.T: 23400FC65800FHI: 5000FC14000FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)1SR 572161-01-3A 500/600 N/AGeneral visual inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.T: 23400FC65800FHI: 4500FC12600FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)1SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 58 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572162-01-1A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atspanwise skin joint at STR 8, from ribs 1 to 20, excluding areascovered by pylon and flap track fairings.T: 14100FC28200FHI: 2400FC4800FH-200572162-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atspanwise skin joint at STR 8, from ribs 1 to 20, excluding areascovered by pylon and flap track fairings.T: 13600FC38200FHI: 2300FC6500FH-300S572163-01-4A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front and rear spars from ribs 10 to 14 excluding areacovered by flap track fairing.T: 18000FC41500FHI: 3000FC6100FH-200 PRE 3510PRE 4799572163-01-5A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front and rear spars from ribs 10 to 14 excluding areacovered by flap track fairing.T: 18000FC41500FHI: 5700FC11400FH-200 POST 3510or POST 4799572163-01-6A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front and rear spars from ribs 10 to 14 excluding areacovered by flap track fairing.T: 20300FC57000FHI: 5600FC15700FH-300 S572164-01-1A 500/600 N/ADetailed inspection of outer wing bottom skin at MLI from ribs 1 to 2and water drain valves from ribs 1 to 28.T: 18000FC37300FHI 5400FC-200I: 5400FC10800FH572164-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin at MLI from ribs 1 to 2and water drain valves from ribs 1 to 28.T: 17600FC49400FHI: 5100FC14400FH-300S572167-01-4A 540/640 540/640 AB toHBDetailed inspection of outer wing bottom skin stringers from rib 1 torib 14.T: 48100FC96200FHI: 7000FC14000FH-200572169-01-1A 500/600530/630540/640532/632 AB,BB540/640 AB,BBSpecial detailed inspection (X-Ray) of outer wing bottom skincovered by MLG reinforcing doubler and adjacent skin.T: 15700FC31500FHI: 9400FC18800FH572169 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 59 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572169-01-2A 500/600530/630540/640532/632 AB,BB540/640 AB,BBSpecial detailed inspection (X-Ray) of outer wing bottom skincovered by MLG reinforcing doubler and adjacent skin.T: 15100FC42500FHI: 9000FC25400FH572169 -300S572171-01-2A 532/632 532/632 BB Detailed inspection of outer wing forward attachment fitting for flaptrack beam No. 2.T: 28400FCI: 9000FCALL572183-01-4A 470/480 473/483 BL,474/484 BR,Engine andattach linkremoval.Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.T: 13000FC26100FHI: 11400FC22800FH572183 -200572183-01-5A 470/480 473/483 BL,474/484 BR,Engine andattach linkremoval.Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.T: 12800FC35800FHI: 11200FC31400FH572183 -300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)S572183-01-6A 470/480 473/483 BL,474/484 BR,Engine andattach linkremoval.Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.T: 12800FC35800FHI: 5500FC15600FH572183 -300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)S572185-01-1A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skinlower surface around fuel pump apertures from ribs 1 to 2.T: 13000FC26000FHI: 8700FC17500FH572185 -200572185-01-2A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skinlower surface around fuel pump apertures from ribs 1 to 2.T: 12200FC34200FHI: 8200FC23000FH572185 -300S572187-01-1A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skinlower 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: 14300FC28700FHI: 8900FC17800FH572187 -200572187-01-2A 500/600 N/A Special detailed inspection (Ultrasonic) of outer wing bottom skinlower 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: 14100FC39600FHI: 8700FC24500FH572187 -300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 60 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572502-01-2A 550/650 550/650 FB toJBNut removal atselectedlocationsSpecial detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.T: 18800FC37600FHI: 4400FC8900FH572502 -200PRE 3510PRE 4799572502-01-3A 550/650 550/650 FB toJBNut removal atselectedlocationsSpecial detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.T: 18800FC37600FHI: 5600FC11200FH572502 -200POST 3510orPOST 4799572502-01-4A 550/650 550/650 FB toJBNut removal atselectedlocationsSpecial detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.T: 18800FC37600FHI: 4500FC9000FH572502 -200C572502-01-5A 550/650 550/650 FB toJBNut removal atselectedlocationsSpecial detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.T: 17700FC49600FHI: 5200FC14800FH572502 -300S572505-01-2A 550/650 550/650 DB,EB KB LBDetailed inspection of outer wing front spar aft face from ribs 17 to19 d ib 23 t 28T: 15000FC30000FH-200EB, KB, LB,MB, NB, PB.19 and ribs 23 to 28.30000FHI: 8200FC16400FH572505-01-3A 550/650 550/650 DB,EB, KB, LB,MB, NB, PB.Detailed inspection of outer wing front spar aft face from ribs 17 to19 and ribs 23 to 28.T: 15000FC30000FHI: 8200FC16400FH-200C572505-01-4A 550/650 550/650 DB,EB, KB, LB,MB, NB, PB.Detailed inspection of outer wing front spar aft face from ribs 17 to19 and ribs 23 to 28.T: 13900FC39000FHI: 7600FC21300FH-300S572512-01-3A 550/650 550/650 AB toPBDetailed inspection of outer wing rear spar FWD face from ribs 14 to28.T: 33000FC66000FHI: 10200FC20500FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 61 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572512-01-4A 550/650 550/650 AB toPBDetailed inspection of outer wing rear spar FWD face from ribs 14 to28.T: 33000FC92400FHI: 9800FC27600FH-300S572526-01-2A 550/650 550/650 FB Special detailed inspection (X-Ray and LFEC and HFEC) of outerwing top skin stringer joints from STRs 9 to 15, between ribs 19 and20.T: 33000FC92400FHI: 5400FC15300FH572526 -300S572528-01-2A 550/650 550/650 FB,GBSpecial 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: 16700FC33500FHI: 5700FC11400FH572528 -200572529-01-3A 550/650 N/ADetailed inspection of outer wing top skin upper surface from ribs 19to 21.T: 32600FC65200FHI: 11000FC22000FH-200PRE 5124(SB 00-2002)PRE 10685(SB 00-2024)572529-01-4A 550/650 N/ADetailed inspection of outer wing top skin upper surface from ribs 19to 21.T: 32600FC65200FHI: 8200FC16500FH-200POST 5124(SB 00-2002)orPOST 10685(SB 00 2024)(SB00-2024)572535-01-4A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 14 to 17 and ribs 21 to 23.T: 25100FC50300FHI: 3100FC6200FH-200 PRE 3510PRE 4799572535-01-5A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 14 to 17 and ribs 21 to 23.T: 25100FC50300FHI: 5300FC10700FH-200 POST 3510orPOST 4799572535-01-6A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 14 to 17 and ribs 21 to 23.T: 25200FC70700FHI: 5400FC15100FH-300 S572536-01-1A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 17 to 21 and 23 to 28T: 12800FC25600FHI: 4600FC9300FH-200 PRE 3510PRE 4799Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 62 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572536-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 17 to 21 and 23 to 28T: 12800FC25600FHI: 5800FC11600FH-200 POST 3510or POST 4799572536-01-3A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 17 to 21 and 23 to 28T: 12500FC35200FHI: 5600FC15900FH-300 S572538-01-3A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to rear spar from ribs 14 to 28.T: 26400FC52800FHI: 9400FC18800FH-200572538-01-4A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to rear spar from ribs 14 to 28.T: 25900FC72600FHI: 9200FC25900FH-300S572539-01-3A 530/630 534/634 AB,BB535/635 AB,BBDetailed inspection of outer wing bottom skin lower surface atattachment to ribs and stringers in area covered by flap track fairingsNo. 4 and 5.T: 29400FC58900FHI: 7500FC15100FH-200572539 01 4A530/630534/634 ABD t il d i ti f t i b tt ki l f tT 28800FC300S572539-01-4A530/630 534/634 AB,BB535/635 AB,BBDetailed inspection of outer wing bottom skin lower surface atattachment to ribs and stringers in area covered by flap track fairingsNo. 4 and 5.T: 28800FC80600FHI: 7400FC20700FH-300S572541-01-1A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 14 to 28, from front to rearspar.T: 18000FC42000FHI: 2600FC5200FH-200R 572541-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 14 to 28, from front to rearspar.T: 23400FC65400FHI: 2600FC7200FH-300S572542-01-3A 500/600 N/ADetailed inspection of outer wing bottom skin at MLI, slat track andjack drain holes from ribs 2 to 28.T: 18000FC40300FHI: 6600FC13200FH-200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 63 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 572542-01-4A 500/600 N/ADetailed inspection of outer wing bottom skin at MLI, slat track andjack drain holes from ribs 2 to 28.T: 19600FC55200FHI: 6400FC18000FH-300 PRE 8253(SB 57-2053)S572542-01-5A 500/600 N/ADetailed inspection of outer wing bottom skin at MLI, slat track andjack drain holes from ribs 2 to 28.T: 39300FC110300FHI: 6400FC18000FH-300 POST 8253(SB 57-2053)S572543-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface in area ofjoint at rib 20T: 17900FC35900FHI: 9300FC18600FH-200572544-01-2A 550/650 550/650 EB,FBSpecial 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: 19700FC55300FHI: 6500FC18200FH572544 -300SR 572545-01-2A 500/600 N/ASpecial detailed inspection (LFEC) of outer wing bottom skin jointstrap at rib 20.T: 17900FC35900FHI: 4300FC8700FH572545 -200R 572546-01-2A 550/650 550/650 FB,GBSpecial detailed inspection (X-Ray and LFEC and HFEC) of outerwing bottom skin stringers at STR joints from ribs 19 to 21.T: 20200FC40500FHI: 5500FC11000FH572546 -200572547-01-3A 550/650 550/650 AB toHB, JB to NB,PBDetailed inspection of outer wing bottom skin stringers from ribs 14to 28.T: 48800FC97700FHI: 4500FC9000FH-200572548-01-4A 550/650 550/650 AB toFBDetailed inspection of outer wing bottom skin butt strap at stringer 8from ribs 14 to 20.T: 21100FC42300FHI: 11900FC23900FH-200 PRE 3510PRE 4799572548-01-5A 550/650 550/650 AB toFBDetailed inspection of outer wing bottom skin butt strap at stringer 8from ribs 14 to 20.T: 21100FC42300FHI: 12800FC25700FH-200 POST 3510or POST 4799Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 64 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572548-01-6A 550/650 550/650 AB toFBDetailed inspection of outer wing bottom skin butt strap at stringer 8from ribs 14 to 20.T: 20600FC57800FHI: 12500FC35200FH-300 S572549-01-3A 500/600 N/ASpecial detailed inspection (Ultrasonic) of outer wing bottom skinlower surface at stringer runouts of stringers 6, 7 and 8b at ribs 16,19 and 22.T: 18000FC41000FHI: 4600FC9200FH572549 -200572549-01-4A 500/600 N/ASpecial detailed inspection (Ultrasonic) of outer wing bottom skinlower surface at stringer runouts of stringers 6, 7 and 8b at ribs 16,19 and 22.T: 20200FC56800FHI: 4500FC12800FH572549 -300S572553-01-4A 550/650 550/650 AB,AT,Rubber ringremovalSpecial detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.T: 18000FC40400FHI: 14900FC29800FH572553 -200 PRE 3510PRE 4799572553-01-5A 550/650 550/650 AB,AT,Rubber ringremovalSpecial detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.T: 18000FC40400FHI: 17000FC34000FH572553 -200 POST 3510orPOST 4799572553-01-6A 550/650 550/650 AB,AT,R bb iSpecial detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.T: 20500FC57600FHI 17000FC572553 -300 SRubber ringremovalI: 17000FC47600FH572554-01-3A 550/650 550/650 KB Special detailed inspection (HFEC) of outer wing bottom skin uppersurface at stringer runout of stringer 13b at rib 23.T: 27700FC55400FHI: 7900FC15900FH572554 -200572554-01-4A 550/650 550/650 KB Special detailed inspection (HFEC) of outer wing bottom skin uppersurface at stringer runout of stringer 13b at rib 23.T: 27500FC77000FHI: 5600FC15800FH572554 -300S572557-02-1A 550/650 550/650 BB toFBSpecial detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts from ribs 15 to 20.T: 17200FC34400FHI: 13500FC27000FH572557 -200Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 65 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572557-02-2A 550/650 550/650 BB toFBSpecial detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts from ribs 15 to 20.T: 17300FC48500FHI: 13500FC37800FH572557 -300SR 572558-01-3A 500/600530/630550/650 JB,KBFlap track 5fairing bracketsremoved.Special detailed inspection (Ultrasonic) of outer wing bottom skin atattachment to stringers adjacent to access door cutouts from ribs 14to 28.T: 49700FC99500FHI: 10200FC20400FH572558 -200572561-01-1A 550/650 550/650 GB toPBSpecial detailed inspection (HFEC) of outer wing bottom skin accessdoors and skin around access door cutouts from ribs 20 to 28.T: 18600FC37200FHI: 11200FC22400FH572561 -200572561-01-2A 550/650 550/650 GB toPBSpecial detailed inspection (HFEC) of outer wing bottom skin accessdoors and skin around access door cutouts from ribs 20 to 28.T: 18600FC52000FHI: 11300FC31900FH572561 -300S572563-01-2A 533/633534/634535/635533/633 BB534/634 BB535/635 BBDetailed inspection of outer wing forward attachment fittings for flaptrack beams No. 3, 4 and 5.T: 42000FCI: 15000FC-200572565 01 1A550/650AS i l d t il d i ti (X R d Ult i ) f t iT 16300FC572565300S572565-01-1A550/650 N/Special detailed inspection (X-Ray and Ultrasonic) of outer wingbottom skin joint strap in area of rib 20.T: 16300FC45800FHI: 4600FC12900FH572565 -300SR 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: 18000FC42000FHI: 15000FC30000FH-2001R 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: 20100FC56500FHI: 15000FC42000FH-3001SR 574113-01-1A 523/623 Slats extended Detailed inspection of outer wing center fixed leading edge "D" noseskin including jack and track cutouts.T: 21000FC42000FHI: 15000FC30000FH-2001Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. 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NoteA310Airworthiness Limitation ItemsR 574113-01-2A 523/623 Slats extended Detailed inspection of outer wing center fixed leading edge "D" noseskin including jack and track cutouts.T: 20100FC56500FHI: 15000FC42000FH-3001SR 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: 18000FC42000FHI: 15000FC30000FH-2001R 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: 20100FC56500FHI: 15000FC42000FH-3001S574129-01-2A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface FWD offront spar from root to tip.T: 15200FC30400FHI: 3600FC7200FH-200574129-01-3A 500/600 N/ADetailed inspection of outer wing bottom skin lower surface FWD offront spar from root to tip.T: 14900FC41700FHI: 2400FC6900FH-300S574129 01 4A500/600AD t il di tiftib ttkilfFWDfT 15200FC200C574129-01-4A500/600 N/Detailed inspection of outer wing bottom skin lower surface FWD offront spar from root to tip.T: 15200FC30400FHI: 3600FC7200FH-200C574130-01-2A 500/600 N/ADetailed inspection of outer wing top skin upper surface FWD offront spar from rib 7 to rib 28.T: 15800FC31600FHI: 3900FC7900FH-200 POST 5026(SB 57-2005)575129-01-1A 500/600 N/ADetailed inspection of outer wing bottom wing skin lower surface atattachments to the trailing edge between ribs 5 and 11.T: 18000FC42000FHI: 2200FC4500FH-200575129-01-2A 500/600 N/ADetailed inspection of outer wing bottom wing skin lower surface atattachments to the trailing edge between ribs 5 and 11.T: 18000FC52200FHI: 2200FC6200FH-300SIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. 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NoteA310Airworthiness Limitation Items575131-01-5A 575/675 575/675 CB,DBRemoval ofanti rotationlocking device(only for PostMod 13297)Detailed inspection of outer wing bottom skin upper surface aft ofrear spar in area of pylon fairing.T: 26800FC53600FHI: 10800FC21600FH-200575131-01-6A 575/675 575/675 CB,DBRemoval ofanti rotationlocking device(only for PostMod 13297)Detailed inspection of outer wing bottom skin upper surface aft ofrear spar in area of pylon fairing.T: 26200FC73500FHI: 10500FC29600FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)S575131-01-7A 575/675 575/675 CB,DBRemoval ofanti rotationlocking device(only for PostMod 13297)Detailed inspection of outer wing bottom skin upper surface aft ofrear spar in area of pylon fairing.T: 26200FC73500FHI: 9300FC26200FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)S575141-01-4A 581/681591/691Flap extended,581/681 AB tDetailed inspection of outer wing bottom skin upper and lowerf ft f b t ib 11 d 28 i l diT: 18000FC41900FH-200591/691 581/681 AB toJB, 591/691AB, BB, cablesteady bracketremoval attrack 5.surfaces aft of rear spar between ribs 11 and 28 including areascovered by flap track fairings.41900FHI: 9100FC18300FH575141-01-5A 581/681591/691Flap extended,581/681 AB toJB, 591/691AB, BB, cablesteady bracketremoval attrack 5.Detailed inspection of outer wing bottom skin upper and lowersurfaces aft of rear spar between ribs 11 and 28 including areascovered by flap track fairings.T: 20400FC57200FHI: 8900FC25000FH-300S575147-01-4A 572/672 572/672 AB Detailed inspection of outer wing shroud box for spoiler 1, inboard riband attachment bracket (inboard face).T: 32200FCI: 15500FCALLIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 68 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items575201-01-1A 574/674 Flaps extended General visual inspection of inboard flap, vane and vane tracks,external surface.T: 5400FCI: 5400FCALL 1575211-01-2A 574/674577/677Flaps extended Detailed inspection of inboard flap carriage 1 including hinge.T: 30000FCI: 8700FCALL575214-01-2A 532/632574/674Flapsextended,532/632 CB,574/674 ATDetailed and Special detailed inspection (ENDOSCOPE) of inboardflap carriage 2, rear link, and fixed link with attachments to flap andcarriage 2.T: 30000FCI: 11900FC575214 ALL575224-01-2A 574/674 Vane tracksandfork fittingsremovalDetailed inspection of lugs and fittings in vane attachment area attrack 1 to 5.T: 30000FCI: 7900FCALL575301-01-1A 500/600 Flaps extended General visual inspection of outboard flap upper and lower skinincluding leading edge, external surface.T: 5800FCI: 5800FCALL1576102-01-1A 500/600 N/AGeneral visual inspection of all speed aileron upper and lower skin,external surface.T: 10000FCI: 10000FCALL1712101-01-1A 453/463454/464435/445/451/461 AL436/446/452/462 ARDetailed inspection of forward engine mount excluding the platform T: 3200FCI: 3200FCCF6-80C262 AR712101-01-2A 453/463454/464435/445/451/461 AL436/446/452/462 ARDetailed inspection of forward engine mount excluding the platform T: 3000FCI: 3000FCCF6-80A3R 712102-01-1A 453/463454/464Engineremoved435/445/451/461 AL436/446/452/462 ARSpecial detailed inspection (Fluorescent Penetrant Inspection) offorward engine mount platformT: 7500 FCI: 7500 FCGE CMM71.21.01CF6-80C2Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 69 - DRevCodeTask referenceZone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 712102-01-2A 453/463454/464Engineremoved435/445/451/461 AL436/446/452/462 ARSpecial detailed inspection (Fluorescent Penetrant Inspection) offorward engine mount platformT: 5170 FCI: 5170 FCGE CMM71.21.01CF6-80A3712202-01-1A 453/463454/464Engineremoved435/445/451/461 AL436/446/452/462 ARSpecial detailed inspection (Fluorescent Penetrant Inspection) of aftengine mount beamT: 20000 FCI: 20000 FCGE CMM71.20.05CF6-80C2712202-01-2A 453/463454/464Engineremoved435/445/451/461 AL436/446/452/462 ARSpecial detailed inspection (Fluorescent Penetrant Inspection) of aftengine mount beamT: 14400 FCI: 14400 FCGE CMM71.20.05CF6-80A3Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section D© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 70 - D

# 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 oper ated 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 descripti on provided in the previous paragraph section

D. The only difference is for the task refe rence number. The last digit is “S” and stands

for Special RangeRevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. Note531273-01-2A-S 121/122 121/122 LF,121/122 MF,121/122 NF,121/122 PFDetailed inspection of nose gear bay arches attachments to frames atstringer 44 and struts attachments lugs, from FR11A to FR16Ainclusive, LH/RH.T: 23600FC118000FHI: 3900FC19500FH-300531276-01-2A-S 123/124 713, 714 Detailed inspection of nose gear telescopic drag strut attach fitting. T. 29000FC145000FHI. 5500FC27800FH-300531435-01-1A-S 231, 232,233, 234Ceiling andsidewallpanels,insulationdisplaced asrequiredSpecial detailed inspection (LFEC) of Splice plate at circumferentialskin splice at FR 26/32 from STR 4 LH/RH to crown centre line andfrom STR 5 to 12, LH/RH.T: 27000FC135000FHI: 4500FC22500FH531435 -300WFD531501-01-4A-S 200 N/ADetailed inspection of skin in circumferential splice and stringercoupling areas at FR 40/41, from STR 13 LH/RH to crown center line,external surface.T: 36600FC183300FHI: 9100FC45800FH-300A310Airworthiness Limitation Items531506-01-2A-S 200 AntennaremovalDetailed inspection of skin around VHF antenna cutout fromFR 47/48 to FR 49 and between STR 1 LH andSTR 1 RH, external surface.T: 24000FC116000FHI: 3600 FC18200 FH-300PRE 13302531506-01-3A-S 200 AntennaremovalDetailed inspection of skin around VHF antenna cutout fromFR 47/48 to FR 49 and between STR 1 LH andSTR 1 RH, external surface.T: 24000FC116000FHI: 3500FC17600FH-300POST 13302531508-01-2A-S 200 N/ADetailed inspection of fuselage skin in frame coupling area at FR 42to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH,external surface.T: 18000 FC90000 FHI: 3900 FC19600 FH-300PRE 13302Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 2 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531508-01-3A-S 200 N/ADetailed inspection of fuselage skin in frame coupling area at FR 42to FR 46 and FR 49 to FR 53, and from STR 3 to STR 16, LH/RH,external surface.T: 18000 FC90000 FHI: 3750 FC18700 FH-300POST 13302531512-01-2A-S 100/200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 45, from STR 13 to STR 27,LH/RH, external surface.T: 9000 FC45000 FHI: 4500 FC23000 FH-300PRE 133021531512-01-3A-S 100/200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 45, from STR 13 to STR 27,LH/RH, external surface.T: 9000 FC45000 FHI: 4500 FC22500 FH-300POST 133021R 531524-01-2A-S 200 AnticollisionLightDetailed inspection of fuselage skin around anti-collision light cutoutfrom FR 42 to FR 43, and from STR 1 LH to STR 1 RH, externalsurface.T: 21500FC109000FHI: 9000FC56000FH-300531542-01-3A-S 141/142 734, 744147/148AZSpecial detailed inspection (Ultrasonic) of stiffener at wing to fuselagelower skin splice at rib 1(center wingbox side)from FR42 to FR47.T: 18700FC93700FH531542 -300147/148AZSealantRemovallowerskinspliceatrib1(centerwingboxside)fromFR42toFR47.93700FHI: 4700FC23800FH531551-01-2A-S 143/144 144 FR143 FLDetailed inspection of fuselage skin and doubler around airconditioning compartment access cutouts, LH/RH.Note: Internal and external side to be inspectedT: 13200FC66200FHI: 13200FC66200FH-300531552-01-2A-S 145/146241/242Main deckfloor panels,insulation,bolts to beremovedSpecial detailed inspection (Rotating Probe) of FR49, 50, 51, 52 and53 between STR 25 and 29 at frame foot, LH/RH.T: 28000FC140400FHI: 8200FC41000FH531552 -300WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 3 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531555-01-2A-S 147/148 734/744 General visual inspection of slanted frames from FR 47 to FR 54,LH/RH.T: 6500FC32900FHI: 6500FC32900FH-3001531556-01-2A-S 147/148 734/744147/148 CZDetailed inspection of fuselage internal structure at FR 47/48 fromSTRs 42 to 43, LH/RH.T: 9800FC49000FHI: 2200FC11200FH-300531561-01-2A-S 145/146241/242Main deckfloor panels,insulation.Detailed inspection of FR47A, 49A, 50A, 51A and 52A at frame footrunout, LH/RH.T: 28200FC141000FHI: 14400FC72000FH-300531567-01-2A-S 147/148 734/744 Detailed inspection of keel beam side panels, adjacent fuselagestructure up to STR 40 and MLG hinge assemblies and door actuatorfitting from FR 47 to FR 54, LH/RH.T: 12700FC63900FHI: 2900FC14500FH-300531571-01-3A-S 143/144147/148734/744143DFDetailed inspection of keel beam box from FR44 to FR54, internalstructure.T: 13700FC68600FH-300147/148143DF147AF,BF,BZ148BFstructure.68600FHI: 11300FC56500FH531579-01-3A-S 135/136137/138Cargocompartmentfloor andsidewallpanelsInsulationdisplaced asrequiredDetailed inspection of FWD face of pressure bulkhead at FR 39,including stringer end fittings from STR35 LH / STR35 RH to bottomcenter lineT: 29800FC149400FHI: 21300FC106800FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 4 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531580-01-2A-S 143/144 734/744147BZDetailed inspection of stringer end fittings and horizontal crossmembers at AFT face of pressure bulkhead at FR39, from STR35 tobottom center line, LH/RHT: 14900FC74700FHI: 6400FC32100FH-300531582-01-2A-S 143/144 572 / 672 AB Special detailed inspection (Ultrasonic) of fuselage skin fromFR47/48 to FR49 and from STR 35 to STR 36, LH/RH.T: 23000FC115400FHI: 13900FC69400FH531582 -300531584-01-3A-S 143/144 Chafing plateremoval asper SB 53-2069SealantRemovalSpecial detailed inspection (LFEC and Ultrasonic) of fuselage skinunderneath pick-up angle from FR 39 to FR 42, LH/RH.T: 13400FC66900FHI: 8000FC40200FH531584 -300PRE 12776531584-01-4A-S 143/144 Chafing plateremoval asper SB 53-2069SealantSpecial detailed inspection (LFEC and Ultrasonic) of fuselage skinunderneath pick-up angle from FR 39 to FR 42, LH/RH.T: 17400FC87000FHI: 4000FC20100FH531584 -300POST 12776Removal531586-01-2A-S 241/242 241BW242BWSpecial detailed inspection (X-RAY) of fuselage skin doubler atFR40/41, between STRs 20 and 23, LH/RHT: 27200FC136100FHI: 1900FC9900FH531586 -300531587-01-3A-S 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 17700FC87800FHI: 11100FC55800FH-300PRE 5411531587-01-4A-S 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 22900FC113100FHI: 11100FC55800FH-300PARTIAL MOD5411Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 5 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531587-01-5A-S 147/148 734/744 Detailed inspection of Main Landing Gear strut attachment fittinglower part, LH/RH.T: 29200FC144600FHI: 11100FC55800FH-300POST 5411531602-01-2A-S 243244Ceilingpanels,insulation,overheadstowagecompartments(if fitted),bolts.Special detailed inspection (Rotating Probe) of splice plate at thecircumferential skin splice at FR54 at STR5, LH/RHT: 27000FC135100FHI: 5900FC29700FH531602 -300531605-01-3A-S 200 N/ADetailed inspection of skin in circumferential splice and stringercoupling areas at FR 55/58 from STR 13, LH/RH, to crown centerline, external surface.Note: This task is an alternative to 531605-02-4A-ST: 9800FC49000FHI: 4600FC23000FH-300531605-02-4A-S 200 N/ASpecial detailed inspection (HFEC) of skin in circumferential spliceand stringer coupling areas at FR 55/58 from STR 13, LH/RH, tocrown center line, external surface.T: 9800FC49000FHI: 6700FC531605 -300c o ce te e, e te a su aceNote: This task is an alternative to 531605-01-3A-S6 00 C33500FH531606-01-4A-S 200 N/A Special detailed inspection (LFEC) of Splice plate at circumferentialskin splice at FR 55/58 from STR 4 LH/RH to crown centre line andfrom STR 5 to 12, LH/RHT: 10000FC50000FHI: 1400FC7400FH531606 -300PRE 13211 (SB53-2125)WFD531611-01-2A-S 200 N/ADetailed inspection of skin at shear tie attachments at FR 54.1, 54.2and 54.3 from STR 22 LH/RH, to crown center line, external surface.T: 23500FC116000FHI: 3300FC16400FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 6 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531621-01-2A-S 253/254 Ceilingplanels,Insulationdisplaced asrequired, airconditioningduct,overheadstowagecompartments, boltsSpecial detailed inspection (HFEC + rotating probe) of splice plate atcircumferential 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 intersectwith circumferential skin splice.T: 16500FC82500FHI: 9500FC49000FH531621 -300PRE 13211 (SB53-2125)WFD531701-01-4A-S 200 N/ADetailed inspection of fuselage skin in circumferential splice andstringer coupling areas at FR 72, from STR 13 LH/RH, to crowncenter line, external surface.T: 18500FC82500FHI: 6500FC32500FH-300531702-01-4A-S 200 N/ASpecial detailed inspection (LFEC) of splice plate at circumferentialskin splice at FR 72 from STR 4 LH/RH to crown centre line and fromSTR 6 to 11, LH/RH.T: 18000FC90000FHI: 4500FC23000FH531702 -300WFD531731-02-1A-S 253/254 Ceilingpanels,insulationdisplaced asrequired, airconditioningduct,overheadstowagecompartments, boltsSpecial detailed inspection (HFEC + rotating probe) of Splice plate atcircumferential 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 intersectwith circumferential skin splice.T: 18000FC90000FHI: 10500FC52500FH531731 -300WFDIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 7 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531737-01-2A-S 240 Antenna to beremovedDetailed inspection of skin around ADF1 and ADF2 antenna cutoutsbetween FR 59 and FR 60 and between FR 62 and FR 63, on crowncenter line, external surface.T: 21500FC109000FHI: 4500FC22500FH-300531801-01-2A-S 200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 76, from STR 13 LH/RH, to crowncenter line, external surface.T: 9900FC49500FHI: 6400FC32000FH-3001531803-01-2A-S 200 N/AGeneral visual inspection of fuselage skin in circumferential spliceand stringer coupling areas at FR 80/82, from STR 6 to STR 13,LH/RH, external surface.T: 8100FC40500FHI: 7200FC36000FH-3001531807-01-2A-S 100/200 N/AGeneral visual inspection of fuselage skin and fail safe ring aroundAFT passenger/crew door cutouts from FR 73 to FR 76, and fromSTR 9 to STR 28, external surface (without scuff plate removal).T: 2700FC13700FHI: 2700FC13700FH-3001531808-01-4A-S 261/262 833/843 Sdetailed inspection(of AFTpassenger/crew door T: 16500FC 531808 -300531808 01 4A S261/262833/843SpecialdetailedinspectionHFEC)assenger/crewdoorcutouts, upper corners including skin and fail safe ring.T:16500FC82500FHI: 3700FC18500FH531808300531809-01-4A-S 171/172261/262Scuff plateremovalSpecial detailed inspection (US + HFEC + VISUAL) of fail safe ringand skin of AFT passenger/crew door cutouts at lower corners,underneath the scuff plates.T: 16500FC82500FHI: 4300FC21500FH531809 -300531910-01-2A-S 323 323 AL, BL323 AR, BRDetailed inspection of fuselage skin, external surface in area of fin tofuselage FWD, MID and AFT attach fitting fasteners and visible partof the fittings.T: 21500FC109000FHI: 5100FC25500FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 8 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items531913-01-2A-S 311/312 313 AL Special detailed inspection (US) of horizontal stabilizer hinge supportmembers and upper and lower attachment lugs of FR 91 LH/RH.T: 9000FC45000FHI: 7500FC37500FH531913 -300531924-01-2A-S 300 N/ASpecial detailed inspection (LFEC) of fuselage skin at circumferentialsplice at FR 86 from STR 22 to STR 27 LH/RH.T: 14000FC70000FHI: 6000FC30000FH531924 -300531926-01-5A-S 311/312 313 AL Special detailed inspection (HFEC) of horizontal stabilizer cutout,lower longeron, corner fitting, skin strap and skin, LH/RH.T: 15000FC75000FHI: 1900FC9700FH531926 -300POST6146545002-P1-3A-S 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 35000FC175000FHI: 9900FC49900FH545002 -300 PW JT9D545002-P1-5A-S 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 35000FC175000FH545002 -300 PW 4000425/426452/462ARareasatAFTendoflowerarms,fromrib1torib2.175000FHI: 8600FC43200FH545002-G1-5A-S 415/416425/426451/461 AL,452/462 ARSpecial detailed inspection (Ultrasonic) of pylon pyramid, attachmentareas at AFT end of lower arms, from rib 1 to rib 2.T: 30200FC151300FHI: 3000FC15000FH545002 -300 GE545003-P1-2A-S 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 9300FC46500FHI: 9300FC46500FH-300 PW JT9DIssue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 9 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items545003-P1-4A-S 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 8000FC40200FHI: 8000FC40200FH-300 PW 4000PRE 6080545003-P1-5A-S 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 10700FC53500FHI: 10700FC53500FH-300 PW 4000POST 6080545003-G1-4A-S 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 1900FC9800FHI: 1900FC9800FH-300 GE PRE6080545003-G1-5A-S 415/416425/426451/461 AL,452/462 ARDetailed inspection of pylon-to-engine FWD attach fitting, (pyramid)arms.T: 2600FC13000FHI: 2600FC13000FH-300 GE POST6080545028-01-3A-S 435/436445/446435/445 AL451/461 ALDetailed inspection of engine cowl hinge fittings, LH/RH (includingbolts and nacelle hinge side).T: 600FC3150FH-300445/446451/452461/462451/461AL436/446 AR452/462 ARboltsandnacellehingeside).3150FHI: 600FC3150FH545030-01-3A-S 473/474483/484473/483 AL,474/484 ARDetailed inspection of pylon lateral panels at the edge of access doorcutouts between ribs 13 and 14, LH/RH.T: 8300FC41700FHI: 8300FC41700FH-300545043-G1-3A-S 415/416425/426N/ADetailed inspection of pylon side panels at rib 8, LH/RHT: 25600FC128300FHI: 8900FC44700FH-300 GE POST10432Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 10 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items545043-P1-3A-S 415/416425/426N/ADetailed inspection of pylon side panels at rib 8, LH/RHT: 22300FC111600FHI: 8700FC43600FH-300 PW POST10432551020-01-3A-S 333/343 333/343 ATrearmostapron fittingDetailed 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-S.T: 20900FC104800FHI: 4900FC24800FH-300551020-02-3A-S 333/343 333/343 AT Special detailed inspection (X-Ray) of horizontal stabilizer centre boxtop 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 551020-01-3A-S.T: 20900FC104800FHI: 4900FC24800FH551020 -300551075-01-1A-S 311/312 313 AL Detailed inspection of horizontal stabilizer rear spar joining partinboard side at rib 3, LHRH.T: 22800FC114400FHI: 5400FC-3005 00 C27300FH571008-01-2A-S 540/640 540/640 AB Special detailed inspection (X-RAY) of outboard horizontal flange oflower T section, inboard row of fasteners from front spar to rear spar,LH/RH.T: 26900FC134500FHI: 6250FC31300FH571008 -300WFD571009-01-2A-S 141/142 734/744147/148 AZDetailed inspection of center wing box rear spar around access doorcutouts.T: 10800FC54400FHI: 8600FC43200FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 11 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571013-01-4A-S 241/242 Sidewallpanels,Insulationdisplaced asrequired,241 LW, MW,242 LW, MWSpecial detailed inspection (Ultrasonic) of FR 47/48, FWD and AFTfaces from STRs 22 to 24, LH/RH.T: 24800FC124000FHI: 4200FC21400FH571013 -300571022-01-3A-S 541/542641/642540/640ABSealantremovalSpecial detailed inspection (Ultrasonic) of stiffener at wing to fuselagelower attachment, outboard side between FR43 and FR45, atstiffeners 7, 8 and 9, LH/RH.T: 12500FC62500FHI: 1800FC9000FH571022 -300571023-01-2A-S 141142734/744147/148AZ,boltsSpecial detailed inspection (Rotating Probe) of center wing box lowerskin at pump holes reinforcing plates upper side, from FR 46 to 47and from beams 3 to 5, LH/RH.T: 23100FC115500FHI: 9800FC49000FH571023 -300571024-01-4A-S 141/142 734/744,147/ 148 AZ,SealantSpecial detailed inspection (Ultrasonic) of center wing box front sparlower cap corner fitting and adjacent front spar structure, LH/RH.T: 16100FC80500FHI: 9800FC571024 -300Sea a tremoval9800 C49200FH571026-01-2A-S 141/142 Main deckfloor panels,galleys andtoilets (ifinstalled)SealantRemovalSpecial detailed inspection (Ultrasonic) of inboard side of cruciformfitting at junction with stiffeners between FR40-1 and FR44-2, LH/RHT: 21500FC107550FHI: 3350FC16800FH571026 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 12 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571028-01-2A-S 141/142 Main deckfloor panels,galleys andtoilets (ifinstalled)SealantRemovalSpecial detailed inspection (Ultrasonic) of center wing box upperpanel between stiffeners 43.2 and 44.1 at cruciform fitting junction,LH/RHT: 19950FC99700FHI: 6250FC31250FH571028 -300571040-01-3A-S 540/640 577/677AT577/677BTSealantRemovalSpecial detailed inspection (HFEC) of cruciform at upper wing skin tofuselage joint from FR 40/41 to 47/48, upper outboard radius, LH/RHT: 17200FC86400FHI: 10200FC51000FH571040 -300R 571041-01-3A-S 540/640 577/677 AT577/677 BTDetailed inspection of cruciform at upper wing skin to fuselage jointfrom FR 40/41 to FR 47/48, outboard flange upper surface, LH/RH.T: 17400FC87200FHI: 2600FC13100FH-300571042-01-3A-S 540/640 540/640ABSealantRemovalDetailed inspection of outer wing upper skin stringer end fittings andadjacent part of stringers at rib 1, from front to rear spar, LH/RH.T: 30300FC151650FHI: 7150FC-300WFDe oaNote: This task is an alternative to 571042-02-2A-S50 C35750FH571042-02-2A-S 540/640 540/640ABSealantRemovalSpecial detailed inspection (Ultrasonic) of outer wing upper skinstringer end fittings and adjacent part of stringers at rib 1, from frontto rear spar, LH/RH.Note: This task is an alternative to 571042-01-3A-ST: 30300FC151650FHI: 11500FC57550FH571042 -300WFD571043-01-3A-S 540/640 540/640AB Special detailed inspection (Ultrasonic) of outer wing rear spar to rib 1junction, vertical tee splice fitting outboard flange, LH/RHT: 30300FC151600FHI: 8800FC44100FH571043 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 13 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571045-01-3A-S 143/144 147BZ734/744vapour sealdisplacedDetailed inspection of center wing box bottom skin lower surface inair conditioning bay.T: 15500FC77400FHI: 8400FC42100FH-300571047-01-3A-S 143/144 147BZ734/744vapour sealdisplacedSealantRemovalSpecial detailed inspection (Ultrasonic and Rototest) of center wingbox bottom skin lower surface in beam attachment areas from front torear spars and from Rib 1 LH to Rib 1 RH.T: 15500FC77400FHI: 12300FC61600FH571047 -300571051-01-2A-S 141142734/744147/148 AZ,boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of center wing box rearspar to Rib 1 junction vertical T splice fitting and angle fitting, LH/RHT: 23600FC118150FHI: 7800FC39100FH571051 -300571052-01-2A-S 540640540AB640AB, boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of outer wing rear spar toRib 1 junction angle fitting, LH/RHT: 33550FC167750FHI: 12000FC60150FH571052 -300571053-01-2A-S 540640540AB640ABSealantRemovalDetailed inspection of outer wing upper skin fittings at junction withRib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-02-2A-ST: 27750FC138850FHI: 3250FC16250FH-300571053-02-2A-S 540640540AB640AB, boltsSealantRemovalSpecial detailed inspection (Rotating Probe) of outer wing upper skinfittings at junction with Rib 1 from front to rear spar, LH/RHThis task is an alternative to 571053-01-2A-ST: 27750FC138850FHI: 19300FC96650FH571053 -300571054-01-2A-S 145/146 Main deckfloor panels,bolts removalSpecial detailed inspection (Rotating Probe) of upper cruciform fittingjunction with fuselage panel at FR43A, LH/RHT: 34700FC173600FHI: 8400FC42200FH571054 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 14 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items571056-01-2A-S 540/640 540/640AB Special detailed inspection (Ultrasonic) of wing upper surface panelbetween stiffener 2 and 7 at cruciform fitting end, LH/RHT: 29600FC148050FHI: 1250FC6400FH571056 -300571061-01-2A-S 540/640 540/640 ABSealantRemovalSpecial detailed inspection (Ultrasonic) of outboard horizontal flangeof lower T section, inboard row of fasteners at stiffener 7 and stiffener9, LH/RHT: 15800FC79100FHI: 4850FC24250FH571061 -300571062-01-2A-S 540/640 N/ASpecial detailed inspection (Ultrasonic) of lower splice betweenFR40/41 and FR47/48 at the first row of fasteners from Rib 1 datum(wing side), LH/RH.T: 17100FC85450FHI: 2700FC13600FH571062 -300571067-01-2A-S 141/142 N/ASpecial detailed inspection (Ultrasonic) of center wing box lowersplice at Rib 1, first fasteners row from Rib 1 datum betweenstiffener 42.2 and 44.1, LH/RHT: 23250FC116350FHI: 6250FC31400FH571067 -300571068-01-2A-S 141/142 N/ASpecial detailed inspection (Ultrasonic) of center wing box lowersplice at Rib 1, first fasteners row from Rib 1 datum betweenstiffener 44.2 and 46.2, LH/RHT: 27050FC135300FHI: 6850FC34250FH571068 -300571069-01-2A-S 141/142 734/744147/148AZbolts to beremovedSealantRemovalSpecial detailed inspection (Rotating Probe) of center wing boxbottom skin stiffener at FR44 level, LH/RH.T: 29900FC149600FHI: 2700FC13500FH571069 -300PRE 8133R 572104-01-4A-S 512/612 512/612 CB,EB, HBDetailed inspection of outer wing front spar FWD face from ribs 1 to 7at slat track cutouts (3 places).T: 11500FC57700FHI: 1500FC7800FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 15 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572105-01-4A-S 523/623 523/623 BB,CBDetailed inspection of outer wing front spar forward face splice plateat rib 10.T: 26600FC133000FHI: 6000FC30400FH-300R 572107-01-2A-S 540/640 540/640 AB,BBDetailed inspection of outer wing front spar AFT face from ribs 1 to 7.Note : This task is an alternative to 572107-02-2A-ST: 9900FC49500FHI: 7100FC35900FH-300N 572107-02-2A-S 540/640 N/ASpecial detailed inspection (Ultrasonic) of outer wing front spar AFTface from ribs 1 to 7.Note : This task is an alternative to 572107-01-2A-ST: 9900FC49500FHI: 7400FC37000FH572107 -300572108-01-4A-S 540/640 540/640 CB,DBDetailed inspection of outer wing front spar AFT face from ribs 7 to 9. T: 19100FC95500FHI: 7000FC35400FH-300572109-01-3A-S 540/640550/650540/640 EB,FB, GB, HBDetailed inspection of outer wing front spar AFT face from ribs 9 to17.T: 8500FC42800FH-300 PRE 7088(SB 00-2012)550/650FB,GB,HB550/650 AB,BB, CB17.42800FHI: 4500FC22600FH(SB00 2012)572109-01-4A-S 540/640550/650540/640 EB,FB, GB, HB550/650 AB,BB, CBDetailed inspection of outer wing front spar AFT face from ribs 9 to17.T: 8500FC42800FHI: 3800FC19200FH-300 POST 7088(SB 00-2012)572111-01-5A-S 571/671 N/ADetailed inspection of outer wing rear spar AFT face and attachmentangle from rib 1 to 3.T: 23000FC115200FHI: 1700FC8600FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 16 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572115-01-4A-S 575/675 575/675 DB Detailed inspection of outer wing rear spar aft face splice plate at rib10.T: 27000FC135000FHI: 6000FC30100FH-300572116-01-1A-S 571/671540/640540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar atselected bolt locations, for attachment of MLG FWD pick up fittingand MLG rib 5 AFT of rear spar, 31 holes, LH/RH.T: 12800FC52200FHI: 5600FC28300FH572116 -300POST 7601572117-01-7A-S 540640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 to3.T: 20000FC100400FHI: 7000FC35000FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)572117-01-8A-S 540640 540/640 AB Detailed inspection of outer wing rear spar forward face from ribs 1 to3.T: 20000FC100400FHI: 5700FC28600FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)572118-01-5A-S 540640 540/640 ABDetailed inspection of outer wingrear spar forward face from ribs 3 to T: 19800FC-300 PRE 8130572118 01 5A S540640540/640AB,BBDetailedinspectionofouterwingrearsparforwardfacefromribs3to6.T:19800FC99500FHI: 7300FC36500FH300PRE8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)572118-01-6A-S 540640 540/640 AB,BBDetailed inspection of outer wing rear spar forward face from ribs 3 to6.T: 19800FC99500FHI: 5900FC29700FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)572119-01-7A-S 540640 540/640 BB,CB, DBDetailed inspection of outer wing rear spar FWD face from ribs 6 to10.T: 22200FC111400FHI: 11400FC52200FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 17 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572119-01-8A-S 540640 540/640 BB,CB, DBDetailed inspection of outer wing rear spar FWD face from ribs 6 to10.T: 22200FC111400FHI: 9200FC46100FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)572120-01-4A-S 540640 540/640 EB toHBDetailed inspection of outer wing rear spar FWD face from ribs 10 to14.T: 22100FC110500FHI: 9900FC49500FH-300572122-01-2A-S 540/640571/671540/640 AB Special detailed inspection (Ultrasonic) of outer wing rear spar atselected bolt locations for attachment of MLG FWD pick-up fitting andMLG rib 5 AFT of rear spar, 26 holes, LH/RH.T: 13800FC52200FHI: 5600FC28300FH572122 -300PRE 7601572137-01-4A-S 540/640 540/640 AB,BB,CBDetailed inspection of outer wing bottom skin butt strap at STR 8 fromribs 1 to 9.T: 13600FC52200FHI: 4500FC22500FH-300572138-01-4A-S 540/640 540/640 DB to Detailed inspection of outer wingbottom skin butt strapat STR 8 from T: 18500FC-300572138 01 4A S540/640540/640DBtoHBDetailedinspectionofouterwingbottomskinbuttstrapatSTR8fromribs 9 to 14.T:18500FC92800FHI: 4600FC23200FH300572141-02-2A-S 540/640 540/640 AB toHBSpecial detailed inspection (HFEC) of outer wing bottom skin aroundmanhole surrounds between ribs 2 and 14, LH and RH wings.T: 10400FC52000FHI: 8100FC40900FH572141 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 18 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 572142-01-4A-S 500/600530/630540/640 GB,HBFlap Track 3fairingbracketsremoved.Special detailed inspection (Ultrasonic) of outer wing bottom skinlower surface at attachment to stringers 9 and 12 adjacent to accessdoor cutouts from ribs 1 to 14.T: 20700FC103500FHI: 6900FC34900FH572142 -300R 572143-01-4A-S 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment 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-S.T: 14500FC72800FHI: 3440FC17200FH-3001572143-02-3A-S 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment 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-S.T: 14500FC52200FHI: 9100FC45500FH-300572144-01-4A-S 500/600 N/ADetailed inspection of outer wing top skin upper surface atattachment to rear spar from ribs 1 to 7.T: 17300FC86500FHI: 3050FC15400FH-300R 572145-01-4A-S 500/600 N/AGeneral visual inspection of outer wing top skin upper surface atattachment to ribs and STRs from ribs 1 to 14, front spar to rear spar(excluding skin reinforcing at pylon).T: 13300FC66900 FHI: 4130FC20600FH-3001572147-01-6A-S 540/640 540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing top skin andexternal and internal reinforcings in areas of ribs 8 and 9, LH and RHwings.T: 24900FC124500FHI: 5700FC28800FH572147 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 19 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 572153-01-2A-S 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BR540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing bottom skin lowersurface reinforcing at ribs 8 and 9 and adjacent skin, including skincovered by pylon fairings.Note : This task has to be performed at the same time as task572153-02-2A-ST: 11100FC52200FHI: 7000FC35400FH572153 -300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)R 572153-01-3A-S 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BR540/640 CB,DBSpecial detailed inspection (X-Ray) of outer wing bottom skin lowersurface reinforcing at ribs 8 and 9 and adjacent skin, including skincovered by pylon fairings.Note : This task has to be performed at the same time as task572153-02-3A-S.T: 11100FC52200FHI: 6600FC33200FH572153 -300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)R 572153-02-2A-S 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BLDetailed inspection of outer wing bottom skin lower surfacereinforcing at ribs 8 and 9 and adjacent skin, including skin coveredby pylon fairings.Note : This task has to be performed at the same time as taskT: 11100FC52200FHI: 7000FC35400FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)473/483BL474/484 BRNote:Thistaskhastobeperformedatthesametimeastask572153-01-2A-S.(SB00-2029)R 572153-02-3A-S 500/600471/481473/483471/481 AL,BL472/482 AR,BR473/483 BL474/484 BRDetailed inspection of outer wing bottom skin lower surfacereinforcing at ribs 8 and 9 and adjacent skin, including skin coveredby pylon fairings.Note : This task has to be performed at the same time as task572153-01-3A-S.T: 11100FC52200FHI: 6600FC33200FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)572157-01-2A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment 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: 11600FC52200FHI: 3100FC15800FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 20 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572159-01-4A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to rear spar from ribs 1 to 3.T: 23200FC116000FHI: 3800FC19000FH-300R572161-01-2A-S 500/600 N/AGeneral visual inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.T: 18000FC90400FHI: 3800FC19200FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)1R572161-01-3A-S 500/600 N/AGeneral visual inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 1 to 10, excluding areacovered by pylon fairing and MLG reinforcing.T: 18000FC90400FHI: 3400FC17400FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)1572162-01-2A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atspanwise skin joint at STR 8, from ribs 1 to 20, excluding areascovered by pylon and flap track fairings.T: 9900FC49600FHI: 1700FC8500FH-300R 572163-01-6A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front and rear spars from ribs 10 to 14 excluding areacovered by flap track fairing.T: 14900FC74500FHI: 4100FC20500FH-300572164-01-2A-S 500/600 N/ADetailed inspection of outer wing bottom skin at MLI from ribs 1 to 2and water drain valves from ribs 1 to 28.T: 11100FC52200FHI: 3200FC16200FH-300572169-01-2A-S 500/600530/630540/640532/632 AB,BB540/640 AB,BBSpecial detailed inspection (X-Ray) of outer wing bottom skin coveredby MLG reinforcing doubler and adjacent skin.T: 11200FC52200FHI: 6700FC33500FH572169 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 21 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572183-01-5A-S 470/480 473/483 BL,474/484 BR,Engine andattach linkremoval.Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.T: 10900FC54800FHI: 9500FC47900FH572183 -300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)572183-01-6A-S 470/480 473/483 BL,474/484 BR,Engine andattach linkremoval.Special detailed inspection (HFEC) of wing to pylon AFT attachmentfitting.T: 10900FC54800FHI: 4700FC23800FH572183 -300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)572185-01-2A-S 500/600 N/ASpecial detailed inspection (Ultrasonic) of outer wing bottom skinlower surface around fuel pump apertures from ribs 1 to 2.T: 8100FC40800FHI: 5400FC27400FH572185 -300572187-01-2A-S 500/600 N/ASpecial detailed inspection (Ultrasonic) of outer wing bottom skinlower 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: 10300FC51700FHI: 6400FC32000FH572187 -300572502-01-5A-S 550/650 550/650 FB toJBNut removalat selectedlocationsSpecial detailed inspection (HFEC and Ultrasonic) of outer wing frontspar AFT face from ribs 19 to 23.T: 11100FC52200FHI: 3300FC16700FH572502 -300572505-01-4A-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 19and ribs 23 to 28.T: 8800FC44100FHI: 4800FC24100FH-300572512-01-4A-S 550/650 550/650 AB toPBDetailed inspection of outer wing rear spar FWD face from ribs 14 to28.T: 26600FC133400FHI: 8000FC40000FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 22 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572526-01-2A-S 550/650 550/650 FB Special detailed inspection (X-Ray) of outer wing top skin stringerjoints from STRs 9 to 15, between ribs 19 and 20.T: 27000FC135300FHI: 4400FC22400FH572526 -300572535-01-6A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 14 to 17 and ribs 21 to 23.T: 19600FC98400FHI: 4200FC21000FH-300572536-01-3A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to front spar from ribs 17 to 21 and 23 to 28T: 9200FC46000FHI: 4100FC20800FH-300572538-01-4A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to rear spar from ribs 14 to 28.T: 19700FC98800FHI: 7000FC35300FH-300572539-01-4A-S 530/630 534/634 AB,BBDetailed inspection of outer wing bottom skin lower surface atattachment to ribs and stringers in area covered byflaptrack fairingsT: 22300FC111500FH-300BB535/635 AB,BBattachmenttoribsandstringersinareacoveredbyflaptrackfairingsNo. 4 and 5.111500FHI: 5700FC28600FHR 572541-01-2A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface atattachment to ribs and stringers from ribs 14 to 28, from front to rearspar.T: 18000FC90400FHI: 2000FC10000FH-300R 572542-01-4A-S 500/600 N/ADetailed inspection of outer wing bottom skin at MLI, slat track andjack drain holes from ribs 2 to 28.T:14600FC73300FHI:4800FC24000FH-300 PRE 8253(SB 57-2053)Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 23 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items572542-01-5A-S 500/600 N/ADetailed inspection of outer wing bottom skin at MLI, slat track andjack drain holes from ribs 2 to 28.T:29300FC146600FHI:4800FC24000FH-300 POST 8253(SB 57-2053)R 572544-01-2A-S 550/650 550/650 EB,FBSpecial detailed inspection (X-Ray) of outer wing bottom skin stringerjoints inboard of rib 19 and from rib 19 to rib 20.T: 14700FC73500FHI: 4800FC24200FH572544 -300R 572548-01-6A-S 550/650 550/650 AB toFBDetailed inspection of outer wing bottom skin butt strap at stringer 8from ribs 14 to 20.T: 15100FC75600FHI: 9200FC46100FH-300R 572549-01-4A-S 500/600 N/ASpecial detailed inspection (Ultrasonic) of outer wing bottom skinlower surface at stringer runouts of stringers 6, 7 and 8b at ribs 16, 19and 22.T: 14800FC74200FHI: 3300FC16700FH572549 -300R 572553-01-6A-S 550/650 550/650 AB,AT,Special detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts, from ribs 14 to 15.T: 17500FC87800FH572553 -300AT,Rubber ringremovalaccessdoorcutouts,fromribs14to15.87800FHI: 15100FC75500FH572554-01-4A-S 550/650 550/650 KB Special detailed inspection (HFEC) of outer wing bottom skin uppersurface at stringer runout of stringer 13b at rib 23.T: 22300FC111800FHI: 4600FC23000FH572554 -300572557-02-2A-S 550/650 550/650 BB toFBSpecial detailed inspection (HFEC) of outer wing bottom skin aroundaccess door cutouts from ribs 15 to 20.T: 14500FC52200FHI: 12100FC52200FH572557 -300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 24 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation ItemsR 572561-01-2A-S 550/650 550/650 GB toPBSpecial detailed inspection (HFEC) of outer wing bottom skin accessdoors and skin around access door cutouts from ribs 20 to 28.T: 15100FC75600FHI: 9200FC46300FH572561 -300572565-01-1A-S 550/650 N/ASpecial detailed inspection (X-Ray and Ultrasonic) of outer wingbottom skin joint strap in area of rib 20.T: 12100FC52200FHI: 3400FC17100FH572565 -300R 574105-01-2A-S 512/612 SlatsextendedDetailed inspection of outer wing inboard fixed leading edge "D" noseskin including jack and track cutouts.T: 12700FC63900FHI: 9500FC47500FH-3001R 574113-01-2A-S 523/623 SlatsextendedDetailed inspection of outer wing center fixed leading edge "D" noseskin including jack and track cutouts.T: 12700FC63900FHI: 9500FC47500FH-3001R 574121-01-2A-S 524/624 SlatsextendedDetailed inspection of outer wing outboard fixed leading edge "D"nose skin includingjack, track and antiicingtelescopic duct cutouts.T: 12700FC63900FH-3001extendednoseskinincludingjack,trackandantiicingtelescopicductcutouts.63900FHI: 9500FC47500FH574129-01-3A-S 500/600 N/ADetailed inspection of outer wing bottom skin lower surface FWD offront spar from root to tip.T: 11500FC57500FHI: 1900FC9500FH-300R 575129-01-2A-S 500/600 N/ADetailed inspection of outer wing bottom wing skin lower surface atattachments to the trailing edge between ribs 5 and 11.T: 13800FC69200FHI: 1600FC8200FH-300Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 25 - ERevCodeTask reference Zone AccessTask descriptionTh.Int.NTMRef.Appli. NoteA310Airworthiness Limitation Items575131-01-6A-S 575/675 575/675 CB,DBRemoval ofanti rotationlocking device(only for PostMod 13297)Detailed inspection of outer wing bottom skin upper surface aft of rearspar in area of pylon fairing.T: 19500FC97700FHI: 7800FC39300FH-300 PRE 8130(SB 00-2037SB 00-2054)PRE 11103(SB 00-2029)575131-01-7A-S 575/675 575/675 CB,DBRemoval ofanti rotationlocking device(only for PostMod 13297)Detailed inspection of outer wing bottom skin upper surface aft of rearspar in area of pylon fairing.T: 19500FC97700FHI: 6900FC34900FH-300 POST 8130(SB 00-2037SB 00-2054)or POST 11103(SB 00-2029)R 575141-01-5A-S 581/681591/691Flapextended,581/681 AB toJB, 591/691Detailed inspection of outer wing bottom skin upper and lowersurfaces aft of rear spar between ribs 11 and 28 including areascovered by flap track fairings.T: 15200FC76000FHI: 6600FC33200FH-300,AB, BB, cablesteadybracketremoval attrack 5.Issue: 8 - OCTOBER 2010Ref: 95A.1309/07ALI Section E© AIRBUS SAS 2010. All rights reserved. Confidential and proprietary document.Page 26 - E

# 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-s ervice 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 Li mitation 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 ite ms such as landing gear, flight controls,

doors, etc. are treated as systems compon ents. 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, unle ss it entails such co mplications 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 fi rst 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 Dama g e :

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 alter native sections of this document (Section C, D

and E).

NOTE:

All tasks which were deleted during this ALI revi sion 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