# A310 AIRWORTHINESS LIMITATIONS SECTION

REVISION: 01 

# ALS Part 1

-

Safe Life

Airworthiness Limitation Items

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.

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

intellectual property rights are gr anted 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 hereun der and provided that any recipient of such

document shall comply with the condition herei n) 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 LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

LIST OF EFFECTIVE PAGES

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

ISSUE: SEP 05/13 ALS PART 1 PAGE: 1-LEP

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# 1 R 1-LEP SEP 05/13

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# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

TABLE OF CONTENTS

SUBJECT PART

ISSUE: SEP 05/13 ALS PART 1 PAGE: 1-TOC

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# N RECORD OF REVISIONS ROR

INTRODUCTION 1-0

ILLUSTRATIONS 1-1

LIFE LIMITS 1-2

DEMONSTRATED FATIGUE LIVES 1-3

# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

RECORD OF REVISIONS

ISSUE: SEP 05/13 ALS PART 1 PAGE: 1-ROR

EASA APPROVED

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

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N The European Aviation Safety Agency (EAS A) Certification Directorate approves the

ALS Part 1. Variations must also be approved.

REVISION

NUMBER SUB-PARTS APPROVED BY

EASA EASA AD INSERTION IN

MAINT. PROG.

R 00 1-2

1-3 DEC 21/06 2007-0293

N 01 ROR

1-2

1-3 SEP 05/13

Note: The ALS Part 1 is covered by the Certification Document 00X0500M091/M41.

Revision 01 is approved by EASA under reference EASA.10046280, REV.1.

REVISION 01 COMPLIANCE TIME:

1. From 05-Sep-2014, it is mandatory to comp ly with the instructions and airworthiness

limitations defined in the A310 ALS Part 1 revision 01.

2. From 05-Sep-2013 to 04-Sep-2014, it is m andatory to comply with the instructions and

airworthiness limitations defined, either:

- In the A310 ALS Part 1 at revision 00,

or,

- In the A310 ALS Part 1 at revision 01.

3. Special compliance times for components whose Part NumbeRs (PNR) are listed in the

table of this ROR:

Replace the affected components no later than the associated special compliance times,

when the compliance with the ALS Part 1 airworthiness limitation(s) cannot be

demonstrated (with or withou t the help of SIL 32-118).

The special compliance times indicated in the following table must be counted from the date

specified in the ‘Start date’ column. Each component must be replaced at or prior to

whichever of the special compliance times occurs first.

# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

RECORD OF REVISIONS

ISSUE: SEP 05/13 ALS PART 1 PAGE: 2-ROR

EASA APPROVED

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. N Designation PNR Start date Compliance time

N LDG CAL

N Main Landing Gear

N Aft pintle pin A32140108200xx 05-Sep-2013 18000 9 years

N A32140108202xx 05-Sep-2013 18000 9 years

N A32140128000xx 05-Sep-2013 18000 9 years

N A32140128002xx 05-Sep-2013 18000 9 years

N Half ball housing (Fwd pintle bearing) A32140101200xx 05-Sep-2013 18000 9 years

N A32140101201xx 05-Sep-2013 18000 9 years

N A32140130002xx 05-Sep-2013 18000 9 years

N A32140130003xx 05-Sep-2013 18000 9 years

N A32140132006xx 05-Sep-2013 18000 9 years

N A32140132007xx 05-Sep-2013 18000 9 years

N Ball (Fwd pintle bearing) A32140100200xx 05-Sep-2013 18000 9 years

N A32140131200xx 05-Sep-2013 18000 9 years

N Reaction bar pin A32140117200xx 05-Sep-2013 18000 9 years

N Pin (Drop link/Frame 50) A53811122200xx 25-Apr-2007 18000 9 years

N MLG Barrel assembly

N Pin (Connecting rod/Upper rod) D52751 25-Apr-2007 18000 9 years

N MLG Shock absorber assembly

N Bogie beam pivot pin nut SL40413P 25-Apr-2007 (2) 9 years

N Nose Landing Gear

N Pintle pin A32210079200xx 25-Apr-2007 13500 9 years

N NLG Telescopic strut assembly

N Nut (Cylinder/Locking cylinder) C61375 25-Apr-2007 13500 9 years

N D55955 25-Apr-2007 13500 9 years

N Locking sleeve C61389 13-Dec-2007 13200 9 years

N C61389-1 25-Apr-2007 13500 9 years

N NLG Barrel assembly

N Pin (Clevis/Telescopic strut) C62231-20 25-Apr-2007 13500 9 years

N D56530 25-Apr-2007 13500 9 years

N Lower pin (Link/Clevis) C62268-20 25-Apr-2007 13500 9 years

N Link (Clevis/Barrel) C62230-1 25-Apr-2007 13500 9 years

N D56526 25-Apr-2007 13500 9 years

N Upper pin (Link/Barrel) C62267-20 25-Apr-2007 13500 9 years

N End fitting pin nut D68062 13-Dec-2007 (1) 9 years

N MS17825-6 13-Dec-2007 (1) 9 years

N End fitting pin AN6-17 13-Dec-2007 (1) 9 years

N D61183 13-Dec-2007 (1) 9 years

N D68063 13-Dec-2007 (1) 9 years

N NAS1306-22D 13-Dec-2007 (1) 9 years

N End fitting C62032 25-Apr-2007 13500 9 years

N C62032-1 25-Apr-2007 13500 9 years

# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

RECORD OF REVISIONS

ISSUE: SEP 05/13 ALS PART 1 PAGE: 3-ROR

EASA APPROVED

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

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N N Designation PNR Start date Compliance time

N LDG CAL

N Rack C61453-1 25-Apr-2007 13500 9 years

N C61453-20 25-Apr-2007 13500 9 years

N C61453-40 25-Apr-2007 13500 9 years

N C61453-41 25-Apr-2007 13500 9 years

N Torque link pin (Upper & Lower) C62223-20 25-Apr-2007 13500 9 years

N NLG Shock absorber assembly

N Upper cam dowel C62270 13-Dec-2007 (1) 9 years

N Upper cam C62034-1 25-Apr-2007 13500 9 years

N Lower cam C62035 25-Apr-2007 13500 9 years

N Restrictor C67863-1 25-Apr-2007 13500 9 years

N C67863-2 25-Apr-2007 13500 9 years

N C67863-4 25-Apr-2007 13500 9 years

N Lower cam dowel C62866 13-Dec-2007 (1) 9 years

N Nut (S/A/Bottom) C64040 -1 13-Dec-2007 (2) 9 years



# (1) Replace by a new one at first part removal/installation following the date specified in the

‘Start date’ column.

(2) Replace by a new one at first nut removal/i nstallation following the date specified in the

‘Start date’ column.

When the nut is temporarily removed and reinstalled for the purpose of performing

maintenance outside a workshop, no replacemen t is required provided the nut's removal

and reinstallation are performed on the same assembly and neither the assembly nor the

nut accumulates time in service during the period between the removal and reinstallation.

# A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 1

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

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D Sub-part 1-0 INTRODUCTION

1. GENERAL

From revision 01 and on, the content of the

A310 Maintenance Planning Document

Section 9-1

Life Limit/Monitored parts

that provided life limitations applicable to A310 models, has been transferred to the

A310 Airworthiness Limitations Section

Part 1

Safe Life Airworthiness Limitation Items

This change is part of a process to provide Operators and Maintenance, Repair and

Overhaul Organizations (MRO) with a ser ies of stand-alone documents in a location

dedicated to the mandatory limitations.

The data provided under Part 1 has been established with the following rules:

Compliance with the requirements contai ned in this document is mandatory. No

person may operate an aircraft to which an ALS applies except in accordance with

the requirements of that ALS, unless otherwis e agreed with the Authority of the State

of the aircraft registry.

Consultation with the State of design should be made by the State of aircraft registry,

in consideration of any deviation from the ALS requirements. This is indicated in the

international Civil Aviation Organisation (ICAO) Airworthiness manual (Doc. 9760),

Volume II, Part A, Chapter 3.

A. Sub-part 1-2: Life limits

Parts listed under this sub-part are those having a life limit due to failure during fatigue

tests and whose failure could result in a catastrophic failure of the aircraft.

B. Sub-part 1-3: Demonstrated fatigue lives

Parts listed under this sub-part are those having a demonstrated fatigue life without

failure but whose failure could result in a catastrophic failure of the aircraft.

For these parts, the life limitation provided (i n flight hours and/or in flight cycles and/or

in landings, as applicable) may evolve depending on fatigue tests results. If the part

fails, its Part NumbeR (PNR) together with t he life limit(s) will be tr ansferred to sub-part

1-2.

# A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 2

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R R C. Traceability and repl acement requirements

In order to maintain aircraft airworthiness, it is mandatory to replace parts listed

under sub-parts 1-2 and 1-3 at or prior to whichever of the life limitations occurs

first, after any necessary adjustment of th e stated life limitations in accordance

with the instructions of paragraph 5 of this sub-part.

Therefore, it is necessary to assure tr aceability and monitoring of these parts.

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

Certificate of Airworthiness.

For a given item of the ALS Part 1, new P NR are introduced as a result of modifications

and Service Bulletins (SB) Airbus publishes . These new PNR may not be listed in the

sub-part 1-3, when the related modificatio ns and/or SB have been released between

two scheduled revisions of the ALS Part 1.

However, it is required to assure traceability and monito ring of such items whatever

their detail PNR.

The next scheduled ALS Part 1 revision will confirm the applicable life limitation(s).

Note: A variation to the ALS Part 1 may be rele ased at the time of the MOD approval to

provide Operators with airworthiness limit ation(s) associated to the new PNR.

For further guidance, Operators ar e requested to contact Airbus.

Note: In the context of the ALS Part 1, traceability means records that clearly

demonstrate the history of each part back to initial entry into service of the part,

so that life limitations are accurately applied. Traceability records may comprise

of, but are not limited to, the following:

- Application history (aircraft type, model, weight variant, MSN i.e.

Manufacturer Serial Number, etc...),

- Maintenance actions carried out (Airwo rthiness Directives, modifications,

repairs, inspections, etc...).

- Life accumulation (accounting for any indi vidual aircraft to which a part may

have been fitted).

Where the complete life history of a part is not known, Operators are requested to refer

to the Service Information Letter (SIL) 32- 118 or SIL 71-039 for guidance. They provide

the means to manage such parts. They have been issued in agreement with the

European Aviation Safety Agency (EASA).

Note: Traceability and monitoring of parts list ed in sub-parts 1-2 and 1-3 is not required

for consumable components, (for whic h replacement is controlled at

assembly/aircraft level).

D. Disposal/quarantine action

When the parts reach the life limitations , disposal/quarantine action must be taken

depending on the following categories:

# A310 AIRWORTHINESS LIMITATIONS SECTION

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R - For parts listed in the ALS sub-part 1- 2: They must be mutilated beyond repair

limits to prevent rework to appear to be airworthy.

Note: Some means may exist to extend thei r life potential provided they are applied

prior to reaching the life limit (e.g. Service Bulletin: POST SB PNR in the ALS

sub-part 1-3).

- For parts listed in the ALS sub-part 1- 3: Appropriate means must be implemented

to deter their installation on aircraft pending possible extension of their life

limitations. Examples of means are:

- Record keeping system,

- Non-permanent markings,

- Segregation (parts stored separately from those currently eligible for

installation).

The ultimate solution is the mutilation beyond repair limits to prevent rework to

appear to be airworthy.

Note: When consumable components are removed, they must be mutilated beyond

repair limits to prevent rework to appear to be airworthy.

E. ALS Part 1 applicability

Sub-parts 1-2 and 1-3 are approved by the EASA.

The applicability of this ALS Part 1 revision is restricted to the ai rcraft series, models

and Weight Variants (WV) listed in the table below:

N Aircraft series Aircraft models WV

N

A310-200 A310-203 00, 01, 03, 04, 06, 08

N A310-204 101, 104, 107

N A310-221 00, 01, 03, 04, 07

N A310-222 00, 01, 04, 11, 101, 104

N A310-200C A310-203C 00, 04

N

A310-300 A310-304 00, 01, 03, 04, 05, 06, 07

N A310-308 05, 08, 09, 13

N A310-322 00, 01, 03

N A310-324 00, 01, 03, 05, 12

N A310-325 08

Note: The engine Time Limits and Maintenance Checks are not included in this manual:

refer to the relevant Engine Manufacturer Chapter 05 manual.

2. DEFINITIONS

The initial entry into service of the part is the date at which the part accomplishes the

first flight for which it will undertake its intended function.

Note: Unless otherwise stated, this means for parts delivered on new aircraft (i.e. from

Airbus Final Assembly Line) that the life accumulated before the aircraft delivery

date/transfer of title date (e.g. as a result of test flights) must be taken into account. R

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# A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 4

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# Calendar times (Cal.): Airworthi ness limitations in Years (Ye), in Months (Mo), etc... must

be counted from the date of initial entry into service of the part,

unless otherwise stated. Storage, maintenance, etc... do not freeze

calendar time accumulation.

Engine Cycles: Each of the following is considered one engine cycle:

- A typical flight consisting of start, landing and shutdown.

- A touch-and-go landing used for pilot training.

Flight Cycle (FC): A complete take-off and landing sequence.

Flight Hour (FH): The accumulated time intervals between ‘wheels-off’ and ‘wheelson’.

Landing (LDG): An operation of an aircraft touching the runway and coming to a full

stop or performing a ‘touch and go’.

Touch and go: A landing in which an aircraft touches the runway and does not

come to a full stop prior to commencing an additional flight.

3. APPLICABILITY SYSTEM

A. General

ALS sub-part 1-2 and 1-3 tables provide th e applicable life limitations only when PNR

installations have been authorized. These tables do not ensure that a PNR has been

validated for a specific individual aircraft MSN.

PNR are authorized for installation on indi vidual aircraft MSN by SB (and the

associated modifications), which are published by Airbus.

B. Aircraft model applicability

ALS sub-part 1-2 and 1-3 table headers indicate aircraft models. When ‘x’ is entered in

the model number, it stands for any number within the limits of the list of models given

in paragraph 1.E. of this sub-part, e.g.:

A310-20x stands for: A310-203, A310-203C and A310-204.

Life limitation applicability is allocated accor ding to the aircraft model affected, e.g.:

X stands for: All A310 m odels defined by the appli cability of the column.

-204 stands for: A310-204 model only , defined by the applicability of the

column.

-203/3C stands for: A310-203 and A310-2 03C models only, defined by the

applicability of the column.

-203/-204 stands for: A310-203 and A310-204 models only, defined by the

applicability of the column.

excl. -204 stands for: All A310 models defined by the applicability of the column,

except the model A310-204. R

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# A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 5

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# Note: The same keys also apply to sub part 1-0 (§7) tables.

C. Weight variant applicability

ALS sub-part 1-2 and 1-3 table headers indicate aircraft WV. When ‘x’ is entered in the

WV number, it stands for any number within the limits of the list of WV given in

paragraph 1.E. of this sub-part.

It is Operators’ r esponsibility to refer to the applicable WV.

The list of the approved WV is provided in the Type Certificate Data Sheet (TCDS)

N°145 issued by the DGAC-F, together with the associated modification

configuration(s).

To determine the applicable WV at the time of aircraft delivery, refer to the list of

modifications embodied during production, provided to the initial Operator of the

aircraft, in the delivery documentation (Air craft Inspection Report ‘Conformity to the

Design Standard Requirements’).

A WV status may evolve as a result of the embodiment of Airbus’ SB.

The list of these SB is also provided in the TCDS.

Note: The paragraph 7 the present sub- part reminds the modifications and SB

associated to the approved WV.

D. Aircraft Manufacturer Serial Number effectivity:

Life limitation applicability may be allocat ed according to the aircraft MSN affected,

e.g.:

XXX – YYY stands for: From aircraft MSN XX X to aircraft MSN YYY (for all aircraft

defined by the applicability of the column).

XYX, XXZ stands for: For aircraft MSN XYX and aircraft MSN XXZ.

XZX stands for: For aircraft MSN XZX only.

excl. XXX stands for: All ai rcraft MSN defined by the ap plicability of the column,

excluding aircraft MSN XXX.

4. LIMITATION/REPLACEMENT TIME INDICATION

A. General

In computing part’s accumulated life, calculations must in clude flight hours

and/or flight cycles and/ or landings and/or calendar time (as applicable) since

the initial entry into service of the part (unless otherwise stated).

The life limitation indicated against PNR originally fitted is counted from the

part’s initial entry into service.

The life limitation indicated against PNR evo lutions is also to be counted from

the part’s initial entry into service (unless otherwise stated). R

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# A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 6

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D B. ALS Part 

# 1 life limitations

Life limitations quoted in sub-parts 1-2 and 1-3 are applicable to the undamaged detail

parts as listed, not to the assembly or the aircraft on which they are installed. The

limitation/replacement time indication is qu oted on the same line/block of lines as the

PNR.

C. Production/Repair concessions, ALS Variat ion and Alternative Method Of Compliance

Limitations of the ALS Part 1 may be negated by instructions given in either a

Production concession, a Repair design Appr oval Sheet (RAS), an ALS Variation (AV)

or an Alternative Method Of Compliance (AMOC).

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

When limitations change in a revision of the ALS Part 1 subsequent to the issuance

date of a Production concession/RAS/AV/AMO C, Operators are requested to contact

Airbus for guidance.

The restrictions on limitation(s) indicated in the RAS/AV/AMOC (or absence thereof)

depend on the part's accumulated life considered during the original evaluation of the

repair solution/AV/AMOC. Oc casionally, repair solutions/AV/AMOC are evaluated on

the basis of a part's accumulated life that includes a conservative life calculation (refer

to SIL 32-118 and/or SIL 71-039). Such repair solutions/AV/AMOC must be reevaluated by Airbus before Operators c an take credit of the history partially or

completely rebuilt after applicati on for the repair solution/AV/AMOC.

Production concessions are provided to the initia l Operator of the aircraft in the delivery

documentation (Aircraft Inspection Report ‘Recordable concessions’).

Note: For spare parts, restricti on of life limitation(s), if any, are indicated in EASA Form

1 ‘Remarks’ block (directly or by reference to another document).

D. Modifications/repairs not developed under Airbus DOA Certificate EASA.21J.031

If an aircraft/a part has a modification or repair embodied that has not been developed

under the Airbus Design Organisation Appr oval (DOA) Certificate EASA.21J.031 and

which affects the content of the ALS Part 1, the Operator is responsible for obtaining

approval by the relevant Airworthiness Auth ority for any necessary adaptations of the

airworthiness limitations. For example, Su pplemental Type Certificates (STC), which

have been designed by Airbus Corporate Jet Centre (ACJC) or which have been

transferred from former Airbus Deutschland , or other entity, under DOA Certificate

EASA.21J.031 are not considered in this ALS Part 1.

When such an aircraft/a part is transferred from an Owner/Operator to another, the

associated approvals and documents indicating the necessary adaptations of

limitations have to be transferred as well.

# A310 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 7

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

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R 5. TRANSFER OF PART BETWEEN AIRCRAFT APPLICATIONS

The airworthiness limitation(s) for a part fitted to an application (aircraft type, aircraft model,

weight variant, etc...) may be different when t he part is transferred to another application. In

this case, the part’s remaining operational life must be calculated using the following

formula:

with:

Tr i = part’s remaining life for operation on current application i.

Ca j = part’s accumulated life on previous application j.

Cp j = part’s airworthiness limitation in previous application j.

Cp i = part’s airworthiness limitati on in current application i.

Note 1: When using the above formula, Tr i, Ca j, Cp j, Cp i are expressed in the same usage

parameter (FH or FC or LDG): Usage parameters cannot be mixed in the same

calculation.

Note 2: The remaining life calculation mu st be reassessed every time the part’s

airworthiness limitation(s) change(s) for current and/or previous aircraft

application(s) to which the part is/was fitted.

6. ASSOCIATED TECHNICAL DOCUMENTATION

PNR provided by sub-parts 1-2 and 1-3 relate to detail parts. They may not all be listed in

Illustrated Parts Catalogue (IPC) issued by Airbus.

For wing structure and landing gear parts m anufactured by Airbus, detail PNR are listed in

the relevant Airbus engineering drawings/C omponent Maintenance Manual manufacturer

(CMMm) issued by Airbus.

For landing gear and engine mount parts manufactured by vendors, detail PNR are listed in

the relevant Illustrated Parts List (IPL)/ Component Maintenance Manual (CMM) issued by

vendors.

Messier-Dowty SB 470-32-797 provides information on procurable repl acement PNR, detail

PNR and applicable SB. i

j j

i 

# Cp Cp Ca

1Tr   

 

 

 

 

 

 

 

 

# 

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R

RA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 8© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RR7. LANDING GEAR LRUs APPLICABILITYA. A310-200/-200C series installationsA310-203 X X X X X XA310-203C X XA310-204 X X XA310-221 X X X X XR A310-222 X X X X X XRWEIGHT VARIANT 00 01 03 04 06 07 08 11 101 104 107MTOW132 138.6 125 142 135 132 138.6 144 138.6 142 134MLW118.5 121.5 118.5 121.5 118.5 119.5 122 121.5 122 122 122MZFW108.5 111.5 108.5 111.5111.5 111.5 112 111.5 112 112 112R Top assembly PNRMain Landing Gear LegD22121/2000-xx X X X XD22121/2001-xx X -203D22121/2005-1xx -203 -203/3C -203 -203 X XD22121/2005-xx X X XD22121/2010-xxXX-221XXXXXXD22121/2011-xx X -221 -203 -203/-222D22121/2015-xx X X X X X X X X X XD22121/2020-xx X X X X X X X X X X XD22121/2021-xx X -221 -203 -203/-222D22121/2025-xx X X X X X X X X X XD22121/2030-xx X X X X X X X X X X XD22121/2035-xx X X X X X X X X X X XD22121/2300-xx X X X X X X X X X X XD22121/2305-xx X X X X X X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 9© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A310-203 X X X X X XA310-203C X XA310-204 X X XA310-221 X X X X XR A310-222 X X X X X XRWEIGHT VARIANT 00 01 03 04 06 07 08 11 101 104 107MTOW132 138.6 125 142 135 132 138.6 144 138.6 142 134MLW118.5 121.5 118.5 121.5 118.5 119.5 122 121.5 122 122 122MZFW108.5 111.5 108.5 111.5111.5 111.5 112 111.5 112 112 112R Top assembly PNRR D22121/2350-xxNOT AUTHORIZEDD22121/2400-x X X X X X X X X X X XD22121/2405-x X X X X X X X X X X XR D22121/2450-xNOT AUTHORIZEDD22121/2500-1x X X X X X X X X X X XD22121/2505-1x X X X X X X X X X X XMain Landing Gear Brace AssemblyD22129/30000-x X -203/3C X -203/3C X X XD22129/30010-x X X -221 X X X X X XD22129/30300-x X X X X X X X X X X XD22129/30400 X X X X X X X X X X XMain Landing Gear Structural LinkageD22139/40000-x X X XD22139/40010-x X X -221 X X X X X XD22139/40020-10x -203 203/3C -203 -203/3C X XD22139/40020-x X XD22139/40030-x X X X X X X X X X XD22139/40300-x X X X X X X X X X X XD22139/40305-x X X X X X X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 10© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A310-203 X X X X X XA310-203C X XA310-204 X X XA310-221 X X X X XR A310-222 X X X X X XRWEIGHT VARIANT 00 01 03 04 06 07 08 11 101 104 107MTOW132 138.6 125 142 135 132 138.6 144 138.6 142 134MLW118.5 121.5 118.5 121.5 118.5 119.5 122 121.5 122 122 122MZFW108.5 111.5 108.5 111.5111.5 111.5 112 111.5 112 112 112R Top assembly PNRD22139/40400 X X X X X X X X X X XD22139/40405-x X X X X X X X X X X XNose Landing Gear LegR C23137002-xNOT AUTHORIZEDR C23137003-xNOT AUTHORIZEDC23137010-x X X X X X X X X X X XC23137020-x X X X X X X X X X XC23137030-x X -221 -203 -203/-222C23137310-x X X X X X X X X X X XC23137320-x X X X X X X X X X X XR C23137350-xNOT AUTHORIZEDC23137610-x X X X X X X X X X X XC23137620-x X X X X X X X X X XC23137630-x X -221 -203 -203/-222R C23137650-xNOT AUTHORIZEDC23137710-x X X X X X X X X X X XC23137720-x X X X X X X X X X X XR C23137750-xNOT AUTHORIZEDC23137810-x X X X X X X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 11© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RRA310-203 X X X X X XA310-203C X XA310-204 X X XA310-221 X X X X XR A310-222 X X X X X XRWEIGHT VARIANT 00 01 03 04 06 07 08 11 101 104 107MTOW132 138.6 125 142 135 132 138.6 144 138.6 142 134MLW118.5 121.5 118.5 121.5 118.5 119.5 122 121.5 122 122 122MZFW108.5 111.5 108.5 111.5111.5 111.5 112 111.5 112 112 112R Top assembly PNRC23137820-x X X X X X X X X X X XC23137910-x X X X X X X X X X X XR C23137915-xNOT AUTHORIZEDC23137920-x X X X X X X X X X X XR C23137950-xNOT AUTHORIZEDNose Landing Gear Telescopic StrutC23037-xxxx (*) X X X X X X X X X X XC23109-xxxx (**) X X X X X X X X X X XC23109x10-xxxx X X X X X X X X X X XR C23109915-xNOT AUTHORIZEDNotes: Telescopic strut PRE VSB 470-32-055/FAM 51 ‘Replacement of visual indicator by a mechanical indicator’:(*) Except PNR C23037-2, PNR C23037-2-1, PNR C23037-2-2 and PNR C23037-3.(**) Except PNR C23109 and PNR C23109-0-x.Weight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet N°145):WV00: Basic aircraft or POST SB A310-00-2025.WV01: Aircraft POST MOD 03703or POST SB A310-00-2003.WV03: Aircraft POST MOD 04008.WV04: Aircraft POST MOD 05124 or POST SB A310-00-2002 or POST MOD 11992 or POST SB A310-00-2044.WV06: Aircraft POST MOD 06395.A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 12© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RWV07: Aircraft POST MOD 06764or POST SB A310-00-2006.WV08: Aircraft POST MOD 07415.WV11: Aircraft POST MOD 10685or POST SB A310-00-2024.WV101: Aircraft POST MOD 06527or POST SB A310-00-2008.WV104: Aircraft POST MOD 06528or POST SB A310-00-2015.WV107: Aircraft POST MOD 07290.THE ABOVE TABLE INDICATES THE LANDING GEAR LRUs THAT HAVE BEEN CERTIFIED FOREACH AIRCRAFT MODEL WEIGHT VARIANT BUTIT DOES NOT:- ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL AIRCRAFT MSN,- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES.Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service Bulletins, ComponentMaintenance Manuals, etc...) for the applicability of LRUs compared with individualaircraft MSN and forthe interchangeabilities/mixabilities of LRUs.A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 13© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RB. A310-300 series installationsA310-304X X X X X X XR A310-308X X X XA310-322 X X XA310-324X X X X XA310-325XRWEIGHT VARIANT 00 01 03 04 05 06 07 08 09 12 13R MTOW150 153 153 142 157 138.6 134 164 161 160 164R MLW123 123 124 123 124 123 124 124 124 124 124R MZFW113 113 114 113 114 113 114 114 114 114 116.5R Top assembly PNRMain Landing Gear LegR D22121/2000-xxNOT AUTHORIZEDR D22121/2001-xxNOT AUTHORIZEDR D22121/2005-1xxNOT AUTHORIZEDR D22121/2005-xxNOT AUTHORIZEDR D22121/2010-xxNOT AUTHORIZEDR D22121/2011-xxNOT AUTHORIZEDR D22121/2015-xxNOT AUTHORIZEDR D22121/2020-xxNOT AUTHORIZEDR D22121/2021-xxNOT AUTHORIZEDR D22121/2025-xxNOT AUTHORIZEDR D22121/2030-xxNOT AUTHORIZEDR D22121/2035-xxNOT AUTHORIZEDD22121/2300-xxXXXXXXXD22121/2305-xx X X X X X X XD22121/2350-xx-304-304Xexcl. -324XR D22121/2400-x X X X X X X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 14© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A310-304X X X X X X XR A310-308X X X XA310-322 X X XA310-324X X X X XA310-325XRWEIGHT VARIANT 00 01 03 04 05 06 07 08 09 12 13R MTOW150 153 153 142 157 138.6 134 164 161 160 164R MLW123 123 124 123 124 123 124 124 124 124 124R MZFW113 113 114 113 114 113 114 114 114 114 116.5R Top assembly PNRR D22121/2405-x X X X X X X X X X X XR D22121/2450-x -304 -304 -304 X excl.-324 X X -308 X XD22121/2500-1x X X X X X X X XD22121/2505-1x X X X X X X X XMain Landing Gear Brace AssemblyR D22129/30000-xNOT AUTHORIZEDR D22129/30010-xNOT AUTHORIZEDD22129/30300-x X X X X X X X XR D22129/30400 X X X X X X X X X X XMain Landing Gear Structural LinkageR D22139/40000-xNOT AUTHORIZEDR D22139/40010-xNOT AUTHORIZEDR D22139/40020-10xNOT AUTHORIZEDR D22139/40020-xNOT AUTHORIZEDR D22139/40030-xNOT AUTHORIZEDD22139/40300-x X X X X X X X XD22139/40305-x X X X X X X X XR D22139/40400 X X X X X X X X X X XR D22139/40405-x X X X X X X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 15© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A310-304X X X X X X XR A310-308X X X XA310-322 X X XA310-324X X X X XA310-325XRWEIGHT VARIANT 00 01 03 04 05 06 07 08 09 12 13R MTOW150 153 153 142 157 138.6 134 164 161 160 164R MLW123 123 124 123 124 123 124 124 124 124 124R MZFW113 113 114 113 114 113 114 114 114 114 116.5R Top assembly PNRNose Landing Gear LegR C23137002-xNOT AUTHORIZEDR C23137003-xNOT AUTHORIZEDR C23137010-x (!) X X X X X X X X X X XR C23137020-x (!) X X X X X X X X X X XR C23137030-xNOT AUTHORIZEDR C23137310-x (!) X X X X X X X X X X XR C23137320-x (!) X X X X X X X X X X XR C23137350-x(!) -304 -304 -304 X excl.-324 X X -308 X XR C23137610-x X X X X X X X X X X XR C23137620-x X X X X X X X X X X XR C23137630-xNOT AUTHORIZEDR C23137650-x -304 -304 -304 X excl.-324 X X -308 X XR C23137710-x X X X X X X X X X X XR C23137720-x X X X X X X X X X X XR C23137750-x -304 -304 -304 X excl.-324 X X -308 X XR C23137810-x X X X X X X X X X X XR C23137820-x X X X X X X X X X X XR C23137910-x X X X X X X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 16© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RA310-304X X X X X X XR A310-308X X X XA310-322 X X XA310-324X X X X XA310-325XRWEIGHT VARIANT 00 01 03 04 05 06 07 08 09 12 13R MTOW150 153 153 142 157 138.6 134 164 161 160 164R MLW123 123 124 123 124 123 124 124 124 124 124R MZFW113 113 114 113 114 113 114 114 114 114 116.5R Top assembly PNRR C23137915-xNOT AUTHORIZEDR C23137920-x X X X X X X X X X X XR C23137950-x -304 -304 -304 X excl.-324 X X -308 X XNose Landing Gear Telescopic StrutR C23037-xxxxNOT AUTHORIZEDR C23109-xxxx (**) (!) X X X X X X X X X X XR C23109x10-xxxx X X X X X X X X X X XR C23109915-xNOT AUTHORIZEDNotes: Telescopic strut PRE VSB 470-32-055/FAM 51 ‘Replacement of visual indicator by a mechanical indicator’:(**) Except PNR C23109, PNR C23109-0-x.(!) assembly can be installed provided the towing bar is fitted with a 150 ton capacity shear pin.Weight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet N°145):WV00: Basic aircraft.WV01: Aircraft POST MOD 05616 or POST SB A310-00-2007.WV03: Aircraft POST MOD 08144.WV04: Aircraft POST MOD 06707.WV05: Aircraft POST MOD 07088 or POST SBA310-00-2012 or POST MOD 13082 or POSTSB A310-00-2051 or POST MOD 13157 orSB A310-00-2052.WV06: Aircraft POST MOD 07614.WV07: Aircraft POST MOD 07659.A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 17© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.WV08: Aircraft POST MOD 08130 or POST SB A310-00-2037.WV09: Aircraft POST MOD 08469 or POST SB A310-00-2018 or POST MOD 11640 or POST SB A310-00-2040.WV12: Aircraft POST MOD 11103 or POST SB A310-00-2029.WV13: Aircraft POST MOD 13302 or POST SB A310-00-2053.THE ABOVE TABLE INDICATES THE LANDING GEAR LRUs THAT HAVE BEEN CERTIFIED FOREACH AIRCRAFT MODEL WEIGHT VARIANT BUTIT DOES NOT:- ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL AIRCRAFT MSN.- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES.Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service Bulletins, ComponentMaintenance Manuals, etc...) for the applicability of LRUs compared with individualaircraft MSN and forthe interchangeabilities/mixabilities of LRUs.NREND OF SUB-PART 1-0A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 PART 1-0 PAGE: 17© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.WV08: Aircraft POST MOD 08130 or POST SB A310-00-2037.WV09: Aircraft POST MOD 08469 or POST SB A310-00-2018 or POST MOD 11640 or POST SB A310-00-2040.WV12: Aircraft POST MOD 11103 or POST SB A310-00-2029.WV13: Aircraft POST MOD 13302 or POST SB A310-00-2053.THE ABOVE TABLE INDICATES THE LANDING GEAR LRUs THAT HAVE BEEN CERTIFIED FOREACH AIRCRAFT MODEL WEIGHT VARIANT BUTIT DOES NOT:- ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL AIRCRAFT MSN.- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES.Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service Bulletins, ComponentMaintenance Manuals, etc...) for the applicability of LRUs compared with individualaircraft MSN and forthe interchangeabilities/mixabilities of LRUs.NREND OF SUB-PART 1-0

# A310 AIRWORTHINESS LIMITATIONS SECTION

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# Sub-part 1-1 ILLUSTRATIONS

Upper torque link pin and nut

Torque link medium pin and nut

Lower torque link pin and nut Reaction bar Drop link

Pin (Drag link/Barrel/Brace strut) Barrel

Drag link Pin (Drag link/Barrel)

Forward pintle pin

Torque link

(Upper & Lower)

Brake torque arm pin (x2)

Bogie beam pivot pin and nut

Bogie beam Wheel axle (x2) Brace strut upper side stay

Brace strut middle pin Lower lock link Upper lock link

Lock link pin

Sleeve (Barrel/Drag link)

Brake torque arm (x4) Lock link

upper pin

Brace strut upper pin

Brace strut lower side stay Lock link middle pin



# MAIN LANDING GEAR - FIG. 01

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# MAIN LANDING GEAR - FIG. 02 Ball (Fwd pintle bearing) Fwd pick up

Half ball housing

(Fwd pintle bearing)

Gear support rib

Reaction bar pin Gear support rib Aft pintle pin

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# MAIN LANDING GEAR - FIG. 03 Cage

Upper torque

link pin

Sleeve

(Barrel/Drag link)

Pin (Drag link/Barrel/

Brace strut) Drag link Barrel Pin (Drop link/Frame 50)

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© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. (*) Location, item not illustrated.



# MAIN LANDING GEAR - FIG. 04 Brake torque arm (x4)

Bogie beam pivot

pin and nut (*) Lower torque link pin S/A sliding rod

Brake torque arm pin (x2) Barrel

S/A upper rod Pin (Connecting

rod/ Upper rod) S/A connecting rod

End fitting

# A310 AIRWORTHINESS LIMITATIONS SECTION

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Torque link

(Upper & Lower)

Torque link pin

(Lower) Torque link

medium pin

Torque link

medium pin nut Pin (Barrel/

Airframe) (x2)

Pin (Clevis/

Telescopic strut) (*)

Pin (Clevis/Barrel) Clevis Lower pin

(Link/Clevis)

Rack (x2) Turning tube Barrel

Torque link pin

(Upper) Upper pin

(Link/Barrel) Link

(Clevis/Barrel)



# NOSE LANDING GEAR - FIG. 05

# A310 AIRWORTHINESS LIMITATIONS SECTION

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# NOSE LANDING GEAR - FIG. 06 Upper rod

Bottom End fitting End fitting pin and nut

(x6) PRE MOD 1257/S7730 and PRE SB A310-32-2037

(x4) POST MOD 1257/S7730 or POST SB A310-32-2037

Sliding rod

Wheel axle Wheel axle nut (x2) Nut (S/A/Barrel)

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Upper cam dowel (x12)

Upper cam Lower cam

Restrictor

Lower cam dowel (x8) Upper rod



# NOSE LANDING GEAR - FIG. 07

# A310 AIRWORTHINESS LIMITATIONS SECTION

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Locking cylinder End fitting pin

Locking piston Lock claw

Cylinder Locking sleeve

Pintle pin End fitting

Rod Nut (Cylinder/Locking cylinder)



# NOSE LANDING GEAR - FIG. 08

# A310 AIRWORTHINESS LIMITATIONS SECTION

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# WING STRUCTURE - FIG. 09 Retraction actuator fitting Rear spar

Fwd pick up Link (Retraction actuator

fitting/Fwd pick up) (x2) Top skin panel n°2 (*)

Gear support rib Reaction bar fitting

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# WING STRUCTURE - FIG. 10 Track 4 rib (outer)

Track 4 rib (inner)

Track 5 rib (outer)

Track 5 rib (inner)

Track 6 rib (outer)

Track 6 rib (inner)

Track 7 rib (outer)

Track 7 rib (inner)

Track 8 rib (outer)

Track 8 rib (inner)

Track 11 rib (outer)

Track 11 rib (inner) Track 9 rib (outer)

Track 9 rib (inner)

Track 10 rib (outer)

Track 10 rib (inner)

# A310 AIRWORTHINESS LIMITATIONS SECTION

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# GENERAL ELECTRIC AFT ENGINE MOUNT CF6-80C2 - FIG. 11 Shear bolt

(Link/Engine) Shear bolt (Outer,

Link/Lower beam)

Shear bolt (Inner, RH

link/Lower beam)

Link (LH) Link (RH)

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# PRATT & WHITNEY FORWARD ENGINE MOUNT - FIG. 12

Bolt (Link/Fan

case) (x2)

Thrust link (x2) Cross beam Bolt (Cross beam/

Main beam)

Main beam Shear pin

Outer support

(PW JT9D-7R4)

Inner support

(PW JT9D-7R4) Support

(PW 4000) Bolt (Link/Cross

beam) (x2) Pylon pyramid

# A310 AIRWORTHINESS LIMITATIONS SECTION

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# PRATT & WHITNEY AFT ENGINE MOUNT - FIG. 13

END OF SUB-PART 1-1 Bolt (Mid link/Engine)

Bolt (Side link/Engine) (x2) Link (x3) Pin (Link/Main beam) (x3) Main beam

PylonA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 1EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 1-2 LIFE LIMITSNote: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325RATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 04)RBARREL ASSEMBLY (FIG. 01, 03 & 04)(1) Limitation applicable only toA310-203 WV04 and A310-203C WV04.(2) Limitation applicable only to A310-203 WV01 & WV08 and A310-203C WV01.(3) Limitation applicable only to A310-203 WV00, WV03 & WV06 and A310-221 WV00, WV03 & WV07.Barrel (LH)D52697-1N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)Barrel (RH)D52698-1N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)Upper torque link pin(LH)D52725N/A 48300 N/A -203/3C (1)N/A53300N/A-203/3C(2)N/A 63300 N/A -203 (3) -221 (3)Upper torque link pin(RH)D52726N/A 48300 N/A -203/3C (1)N/A53300N/A-203/3C(2)N/A 63300 N/A -203 (3) -221 (3)Torque link (Upper &Lower)D52703-1N/A 48300 N/A -203/3C (1)N/A53300N/A-203/3C(2)N/A 63300 N/A -203 (3) -221 (3)Drag link (LH)D52701N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 2EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325Drag link (RH)D52702N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)Forward pintle pinD53230-1N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)S/A connecting rodD53209N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)RSHOCK ABSORBER ASSEMBLY (FIG. 01 & 04)(1) Limitation applicable only toA310-203 WV04, A310-203C WV04, A310-221 WV04 and A310-222 WV04, WV11 & WV104.(2) Limitation applicable only to A310-203 WV01 & WV08, A310-203C WV01, A310-221 WV01 and A310-222 WV01 & WV101.(3) Limitation applicable only to A310-203 WV00, WV03 & WV06 and A310-221 WV00, WV03 & WV07.(4) Limitation applicable only to A310-203 WV01 & WV08 and A310-203C WV01.(5) Limitation applicableonly to A310-203/3C WV04.S/A upper rodD52747N/A 48300 N/A -203/3C (1) X (1)N/A 53300 N/A -203/3C (2)X (2)N/A 63300 N/A -203 (3) -221 (3)S/A sliding rod (LH)D52699-1N/A 48300 N/A -203/3C (5)N/A 53300 N/A -203/3C (4)N/A 63300 N/A -203 (3) -221 (3)S/A sliding rod (RH)D52700-1N/A 48300 N/A -203/3C (5)N/A 53300 N/A -203/3C (4)N/A 63300 N/A -203 (3) -221 (3)A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 3EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325Bogie beam pivot pinD52705N/A 48300 N/A -203/3C (5)N/A 53300 N/A -203/3C (4)N/A 63300 N/A -203 (3) -221 (3)D52705-1N/A 48300 N/A -203/3C (5)N/A 53300 N/A -203/3C (4)N/A 63300 N/A -203 (3) -221 (3)RLINKAGE ASSEMBLY (FIG. 01)(1) Limitation applicable only to A310-308 WV08 & WV09 and A310-324 WV12.(2) Limitation applicable only toA310-304, to A310-308 WV05 and toA310-324 WV00, WV01,.WV03 & WV05.Drop linkD62523N/A 48300 N/A -308 (1) X (1) XN/A 63300 N/A X X (2) X X X (2)RBRACE ASSEMBLY (FIG. 01)BRACE STRUT (FIG. 01)(1) Limitation applicable only toA310-203 WV04 and A310-203C WV04.(2) Limitation applicable only to A310-203 WV01 & WV08 and A310-203C WV01.(3) Limitation applicable only to A310-203 WV00, WV03 & WV06 and A310-221 WV00, WV03 & WV07.Brace strut upper sidestayD52919N/A 48300 N/A -203/3C (1)N/A53300N/A-203/3C(2)N/A 63300 N/A -203 (3) -221 (3)D53034N/A 48300 N/A -203/3C (1)N/A 53300 N/A -203/3C (2)N/A 63300 N/A -203 (3) -221 (3)Brace strut lower sidestayD52817N/A 48300 N/A -203/3C (1)N/A53300N/A-203/3C(2).../...N/A 63300 N/A -203 (3) -221 (3)A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 4EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325Brace strut lower sidestayD52817-1N/A 48300 N/A -203/3C (1)N/A53300N/A-203/3C(2)N/A 63300 N/A -203 (3) -221 (3)A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 5EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325RATA 32-20-00 NOSE LANDING GEAR (FIG. 05 to 08)R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.(2) - 12000 LDG from initial entry into service: For parts having an initial entry into service date after 30-Apr-1986.- 12000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated 9000 LDG or less on 30-Apr-1986.- 3000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated between 9000 and 14000 LDG on 30-Apr-1986.- Either 17000 LDG from initial entry intoservice or 2000 LDG from 30-Apr-1986, whichever occurs first: For parts installed on aircraft having accumulated morethan 14000 LDG on 30-Apr-1986.Pintle pin (1)A32210001205xx N/A (2) N/A 203/3CXRBARREL ASSEMBLY (FIG. 05 & 06)(1) Limitation applicable only to A310-308 WV08 & WV09 and to A310-324 WV12.(2) Limitation applicable only to A310-304, to A310-308 WV05 and to A310-324 WV00, WV01, WV03 & WV05.BarrelC59049-2N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XC59049-4N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XC59049-20N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XC59049-25N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XC59049-26N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2).../...N/A 65700 N/A X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 6EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325N BarrelC59049-27N/A 50000 N/A X (1) X (1) XNN/A 57800 N/A X (2)X X (2)NN/A 65700 N/A X XC59049-40N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XC59049-41N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XNC59049-42N/A 50000 N/A X (1) X (1) XNN/A 57800 N/A X (2)X X (2)NN/A 65700 N/A X XC59049-45N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XC59049-46N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XNC59049-47N/A 50000 N/A X (1) X (1) XNN/A 57800 N/A X (2)X X (2)NN/A 65700 N/A X XD56525N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2).../...N/A 65700 N/A X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 7EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325BarrelD56525-1N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XD56525-10N/A 50000 N/A X (1) X (1) XN/A 57800 N/A X (2) X X (2)N/A 65700 N/A X XND56525-11N/A 50000 N/A X (1) X (1) XNN/A 57800 N/A X (2)X X (2)NN/A 65700 N/A X XTurning tubeC59050-4 N/A 24000 N/A X X X X X XC59050-20 N/A 24000 N/A X X X X X XRSHOCK ABSORBER ASSEMBLY (FIG. 06 & 07)(1) - For the first accomplishment, replace the bottom before accumulation of 24000 LDG since the initial entry into service, or within 12000 LDG after 10-Apr-1993,whichever occurs later, but without exceeding a total of 36000LDG since the initial entry into service. The stated limits apply to the NLG itself, and not to theassociated aircraft.- For the subsequent accomplishments, replace the bottom beforeaccumulation of 24000 LDG since initial entry into service. The stated limit applies to the detailpart and not to the associated NLG.BottomC62037-1 N/A (1) N/A X X X X X XND68531 N/A (1) N/A X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 8EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH FC Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325RATA 71-20-00 ENGINE MOUNTS (FIG. 11 to 13)RDRGENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY (FIG. 11)(1) Replacement with improved links at next engine shop visit after 01-May-2001, or before accumulation of 29000 Engine Cyclessince the initial entry into service,whichever occurs first. Refer to FAA AD 2000-06-09.R(2) Replacement with improved links at next engine shop visit after 28-Aug-2000, or before accumulation of 29000 Engine Cyclessince the initial entry into service,whichever occurs first. Refer to FAA AD 2000-12-08.RShear bolt (Outer,Link/Lower beam)77458-16-70 N/A N/A 31-Dec-09 -203/3CR RA22021-16-70N/AN/A31-Dec-09 -203/3CR9380M75P01 N/A N/A 31-Dec-09 -204 XRShear bolt (Inner, RHLink/Lower beam)77458-12-60 N/A N/A 31-Dec-09 -203/3CR RA22021-12-60N/AN/A31-Dec-09 -203/3CR9380M80P01 N/A N/A 31-Dec-09 -204 XR Link (LH)224-1608-1 N/A (1) (1) -203/3CR224-1608-3 N/A (1) (1) -203/3CR224-1608-5 N/A (1) (1) -203/3CR9348M79P01 N/A (2) (2) -204 XR Link (RH)224-1615-505 N/A (1) (1) -203/3CR224-1615-507 N/A (1) (1) -203/3CR224-1615-509 N/A (1) (1) -203/3CR9348M84P01 N/A (2) (2) -204 XRShear bolt(Link/Engine)81841-8 N/A N/A 31-Dec-09 -203/3CR 9380M73P01N/AN/A31-Dec-09 -204XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE: 9EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclature Part Number FH FC Cal. A310-20x A310-30x A310-22x A310-322 A310-324 A310-325RPRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 12)(1) Part to be removed no later than 31-Dec-2005. The replacement of this part can be delayed until the next engine removal after 31-Dec-2005, provided 58000 FCare not exceeded. The life the part accumulated before the lastengine installation date must be calculated in accordance withthe methodology described in theSIL 71-039. It must be added to the actual life accumulated since the last engine installation date. The total must not exceed58000 FC at any time.Bolt (Link/Fan case) 221-0251-503 N/A (1) (1)X X X XBolt (Cross beam/Mainbeam)221-0251-501 N/A (1) (1)X X X XBolt (Link/Cross beam) 221-0251-503 N/A (1) (1)X X X221-0251-505 N/A (1) (1)X X X X221-0251-507 N/A (1) (1)X X X XMain beam221-0241-9 N/A 20000 N/AX X X X221-4005-1N/A 20000 N/AXN/A 40000 N/AX X XShear pin221-0252-501 N/A (1) (1)X X X X221-0252-503 N/A (1) (1)X X X XRPRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 13)(1) Part to be removed no later than 31-Dec-2005. The replacement of this part can be delayed until the next engine removal after 31-Dec-2005, provided 52500 FCare not exceeded. The life the part accumulated before the lastengine installation date must be calculated in accordance withthe methodology described in theSIL 71-039. It must be added to the actual life accumulated since the last engine installation date. The total must not exceed52500 FC at any time.Pin (Link/Main beam) 221-0264-501 N/A (1) (1)X X X XBolt (Mid link/Engine) 80876-20-4 N/A (1) (1)X X X XBolt (Side link/Engine) 80876-20-3 N/A (1) (1)X X X XEND OF SUB-PART 1-2A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 1EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 1-3 DEMONSTRATED FATIGUE LIVESNote: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325RATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 04)R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.N Aft pintle pin (1)A32140108200xx N/A 63300 XXXXXXNA32140108202xx N/A 63300 X X X X X XNA32140128000xx N/A 63300 X X X X X XNA32140128002xx N/A 63300 X X X X X XNHalf ball housing (Fwd pintlebearing) (1)A32140101200xx N/A 63300 X X X X X XNA32140101201xx N/A 63300 X X X X X XNA32140130002xx N/A 63300 X X X X X XNA32140130003xx N/A 63300 X X X X X XNA32140132006xx N/A 63300 X X X X X XNA32140132007xx N/A 63300 X X X X X XN Ball (Fwd pintle bearing) (1) A32140100200xx N/A 63300 XXXXXXNA32140131200xx N/A 63300 X X X X X XN Reaction bar pin (1)A32140117200xx N/A 63300 XXXXXXPin (Drop link/Frame 50) (1) A53811122200xx N/A 63300 XXXXXXNA53811122202xx N/A 63300 X X X X X XRBARREL ASSEMBLY (FIG. 01, 03 & 04)(1) Limitation applicable only to A310-304 and to A310-308 WV05.(2) Limitation applicable only to A310-324 WV00, WV01, WV03 and WV05.RRR(3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performingmaintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same pin and neither the pin northe nut accumulates time in service during the period between the removal and reinstallation..../...A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 2EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325(4) Limitation applicable only A310-203 WV00,WV01, WV04 and to A310-203C and to A310-204.CageD53212 N/A 63300 X X X X X XBarrel(LH) D52697-11 N/A 63300 X XD58061-1 N/A 63300 X X (1) X X XD62507 N/A 63300 X X X X X XBarrel(RH) D52698-11 N/A 63300 X XD58062-1 N/A 63300 X X (1) X X XD62508 N/A 63300 X X X X X XUpper torque link pin (LH) D52725-10 N/A 63300 XXD52725-20 N/A 63300 X XD58067 N/A 63300 X X (1) X X X (2)D58067-20 N/A 63300 X X (1) X X X (2)D58067-25 N/A 63300 X X X X X XUpper torque link pin (RH) D52726-10 N/A 63300 XXD52726-20 N/A 63300 X XD58068 N/A 63300 X X (1) X X X (2)D58068-20 N/A 63300 X X (1) X X X (2)D58068-25 N/A 63300 X X X X X XUpper torque link pin nut SL40123P N/A (3)XXXXXXTorque link (upper & lower) D52703-11 N/A 63300 XXD58066-1 N/A 63300 X X X X X XTorque link medium pin C65542-20 N/A 63300 XXXXXXTorque link medium pin nut SL40114P N/A (3)XXXXXXSleeve (Barrel/Drag link)D52727N/A 63300 XXXXXXD66167 N/A 63300 X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 3EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325Draglink(LH) D52701-10 N/A 63300 X XD58063 N/A 63300 X X (1) X X XD62509 N/A 63300 X X X X X XDraglink(RH) D52702-10 N/A 63300 X XD58064 N/A 63300 X X (1) X X XD62510 N/A 63300 X X X X X XPin (Drag link/Barrel/Bracestrut)D53237 N/A 63300 X X X X X XPin (Drag link/Barrel)D53225N/A 63300 XXD58878 N/A 63300 X X (1) X X XD62511 N/A 63300 X X X X X XForward pintle pinD53230-11 N/A 63300 XXD58060-1 N/A 63300 X X (1) X X XD62506 N/A 63300 X X X X X XPin (Connecting rod/Upperrod)D52751 N/A 63300 X X X X X XD52751-1 N/A 63300 X X X X X XND52751-2 N/A 63300 X X X X X XND52751-10 N/A 63300 X X X X X XND68547 N/A 63300 X X X X X XS/A connecting rodD53209-10 N/A 63300 X (4)XD58065 N/A 63300 X X (1) X X X (2)D58065-1 N/A 63300 X X X X X XRSHOCK ABSORBER ASSEMBLY (FIG. 01 & 04)(1) Limitation applicable only to A310-304 and to A310-308 WV05..../...A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 4EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325(2) Limitation applicable only to A310-324 WV00, WV01, WV03 and WV05.RRR(3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performingmaintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same pin and neither the pin northe nut accumulates time in service during the period between the removal and reinstallation.(4) Limitation applicable only to A310-203 WV00, WV03 & WV06.(5) Limitation applicable only to A310-221 WV00, WV03 & WV07.R (6) PNR CRA50548 applies to nuts used for repaired bogie beam pivot pins.S/A upper rodD52747-10 N/A 63300 X X (1) XXXD62515 N/A 63300 X X X X X XS/A sliding rod (LH)D52699-21 N/A 63300 XXD52699-31 N/A 63300 X XD58069-1 N/A 63300 X X (1) X X XD61671-1 N/A 63300 X X (1) X X XD62513 N/A 63300 X X X X X XS/A sliding rod (RH)D52700-21 N/A 63300 XXD52700-31 N/A 63300 X XD58070-1 N/A 63300 X X (1) X X XD61672-1 N/A 63300 X X (1) X X XD62514 N/A 63300 X X X X X XEndfittingD54174 N/A 63300 X XD54174-1 N/A 63300 X X (1) X X XD62512 N/A 63300 X X X X X XLower torque link pinD52721N/A 63300 XXD52721-20 N/A 63300 X XD58073 N/A 63300 X X (1) X X X (2)D58073-20 N/A 63300 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 5EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325Lower torque link pin nut SL40123P N/A (3)XXXXXXBrake torque arm pinD52712N/A 63300 XXND52712-1 N/A 63300 X XD58075 N/A 63300 X X (1) X X XD62516 N/A 63300 X X X X X XBrake torque armC66434-10 N/A 63300 -203 (4) -221 (5)C66434-20 N/A 63300 X X (1) X X X (2)D52710N/A 63300 -203 (4) -221 (5)D62518 N/A 63300 X X X X X XBogie beam pivot pinD52705-10 N/A 63300 XXD52705-20 N/A 63300 X XD58071 N/A 63300 X X (1) X X X (2)D58071-20 N/A 63300 X X X X X XBogie beam pivot pin nut CRA50548 (6) N/A 63300 XXXXXXSL40413P N/A (3) X X X X X XBOGIE BEAM ASSEMBLY (FIG. 01)(1) Limitation applicable only to A310-203 WV00, WV03 & WV06.(2) Limitation applicable only to A310-221 WV00, WV03 & WV07.(3) Limitation applicable only to A310-304 and to A310-308 WV05.(4) Limitation applicable only to A310-324 WV00, WV01, WV03 and WV05.Bogie beamD52809-1 N/A 63300 -203 (1) -221 (2)D52809-3 N/A 63300 -203 (1) -221 (2)D52809-21 N/A 63300 -203 (1) -221 (2)D58000-1 N/A 63300 X X (3) X X X (4).../...D58000-3 N/A 63300 X X (3) X X X (4)A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 6EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325Bogiebeam D62519-1 N/A 63300 X X X X X XWheel AxleD52833-1 N/A 63300 -203 (1) -221 (2)D52833-21 N/A 63300 X XD58001-1 N/A 63300 X X (3) X X X (4)D62520-1 N/A 63300 X X X X X XLINKAGE ASSEMBLY (FIG. 01)(1) Limitation applicable only to A310-203 WV00, WV03 & WV06.(2) Limitation applicable only to A310-221 WV00 & WV03.(3) Limitation applicable only to A310-203 WV00, WV01, WV03, WV04 & WV06, and to A310-203C.(4) Limitation applicable only to A310-221 WV00,WV01, WV03 & WV04, and to A310-222 WV01 & WV04.(5) Limitation applicable only to A310-304 and to A310-308 WV05.Reaction barD52807N/A 63300 -203 (1) -221 (2)D52807-1 N/A 63300 -203/3C (3)X (4)D52807-2 N/A 63300 -203 (1) -221 (2)D52807-3 N/A 63300 -203 (1) -221 (2)D52807-10 N/A 63300 X XD58002 N/A 63300 X X (5) X X XD62522 N/A 63300 X X X X X XDrop linkD52915N/A 63300 -203 (1) -221 (2)D52915-1 N/A 63300 X XD58003 N/A 63300 X X (5) X X XRBRACE ASSEMBLY (FIG. 01)BRACE STRUT (FIG. 01)(1) Limitation applicable only to A310-304 and to A310-308 WV05.(2) Limitation applicable only to A310-203 WV00, WV01 & WV04.A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 7EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325Brace strut upper pinD53016N/A 63300 XXD53016-10 N/A 63300 X XD58008 N/A 63300 X X X X X XBrace strut upper side stay D53034-10 N/A 63300 X X (1) XXXD62521 N/A 63300 X X X X X XBrace strut middle pinD53013N/A 63300 XXD58007 N/A 63300 X X X X X XBrace strut lower side stay D52817-10 N/A 63300 X (2)XD58004 N/A 63300 X X X X X XLock link pinD53027N/A 63300 XXD53027-2 N/A 63300 X X X X X XLOCK LINK (FIG. 01)R (1) Limitation applicable only to A310-221 WV00, WV03 & WV07.Lower lock linkD52917N/A 63300 XXXXXXLock link middle pinD53044N/A 63300 -203/3C -221 (1)D53044-1 N/A 63300 X X X X X XD53044-2 N/A 63300 X X X X X XUpper lock linkD52913N/A 63300 -203/3C -221 (1)D52913-1 N/A 63300 X X X X X XD53033 N/A 63300 -203/3C -221 (1)D53033-1 N/A 63300 X X X X X XD53033-10 N/A 63300 X X X X X XLock link upper pinD53047N/A 63300 XXXXXXD53047-2 N/A 63300 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 8EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325RATA 32-20-00 NOSE LANDING GEAR (FIG. 05 to 08)R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.Pintle pin (1)A32210079200xx105000 65700 X X116000 65700 X X X XA32210080200xx105000 65700 X X116000 65700 X X X XNA32210082200xx105000 65700 X XN116000 65700 X X X XRTELESCOPIC STRUT ASSEMBLY (FIG. 08)End fitting pinC62911-1 N/A 65700 XXC62911-2 N/A 65700 X X X X X XC62911-15 N/A 65700 X XNC62911-18 N/A 65700 X XC62911-20 N/A 65700 X X X X X XNC62911-25 N/A 65700 X X X X X XD55951 N/A 65700 X X X X X XEndfittingC61390-1 N/A 65700 X XC61390-2 N/A 65700 X X X X X XD55962 N/A 65700 X X X X X XCylinderC61371 N/A 65700 X X X X X XD55954 N/A 65700 X X X X X XRNut (Cylinder/Lockingcylinder)C61375 N/A 65700 X X X X X XNC61375-1 N/A 65700 X X X X X X.../...D55955 N/A 65700 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 9EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325NNut (Cylinder/Lockingcylinder)D55955-1 N/A 65700 X X X X X XND68538 N/A 65700 X X X X X XLockingcylinder C61373-1 N/A 65700 X XC61373-3 N/A 65700 X X X X X XC61373-4 N/A 65700 X X X X X XC61373-6 N/A 65700 X X X X X XC61373-7 N/A 65700 X X X X X XNC61373-10 N/A 65700 X XC61373-40 N/A 65700 X X X X X XD63091 N/A 65700 X X X X X XD63091-1 N/A 65700 X X X X X XLockingsleeve C61389 N/A 65700 X X X X X XC61389-1 N/A 65700 X X X X X XLockclawC61391 N/A 65700 X X X X X XD55952 N/A 65700 X X X X X XLockingpiston C61378-1 N/A 65700 X XC61378-3 N/A 65700 X XNC61378-10 N/A 65700 X XC68483 N/A 65700 X XC68483-1 N/A 65700 X X X X X XC68483-2 N/A 65700 X X X X X XC68483-3 N/A 65700 X X X X X XC68483-4 N/A 65700 X X X X X XD63282 N/A 65700 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 10EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325RodC61372-1 N/A 65700 X XC61372-2 N/A 65700 X X X X X XC61372-4 N/A 65700 X XD55953-1 N/A 65700 X X X X X XD55953-2 N/A 65700 X X X X X XD57050 N/A 65700 X X X X X XD57050-1 N/A 65700 X X X X X XBARREL ASSEMBLY (FIG. 05 & 06)R (1) Part must be replaced by a new one every time it is removed from the barrel.RRR(2) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performingmaintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same pin and neither the pin northe nut accumulates time in service during the period between the removal and reinstallation.Pin (Clevis/Telescopic strut) C62231-20 N/A 65700 XXXXXXD56530 N/A 65700 X X X X X XClevisC62002-2 N/A 65700 X X X X X XD56527 N/A 65700 X X X X X XLower pin (Link/Clevis)C62268-20 N/A 65700 XXXXXXNC62268-200 N/A 65700 X X X X X XND68541 N/A 65700 X X X X X XLink(Clevis/Barrel) C62230-1 N/A 65700 X X X X X XNC62230-10 N/A 65700 X X X X X XD56526 N/A 65700 X X X X X XND56526-1 N/A 65700 X X X X X XND68539 N/A 65700 X X X X X XND68540 N/A 65700 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 11EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325Upperpin(Link/Barrel) C62267-20 N/A 65700 X X X X X XNC62267-200 N/A 65700 X X X X X XND68544 N/A 65700 X X X X X XPin(Clevis/Barrel) C62229-20 N/A 65700 X X X X X XD56528 N/A 65700 X X X X X XBarrelD59448 N/A 65700 X X X X X XD59448-1 N/A 65700 X X X X X XD59448-10 N/A 65700 X X X X X XD59633 N/A 65700 X X X X X XD59633-1 N/A 65700 X X X X X XD59633-10 N/A 65700 X X X X X XD61185 N/A 65700 X X X X X XD61185-10 N/A 65700 X X X X X XD61553 N/A 65700 X X X X X XD61661 N/A 65700 X X X X X XPin(Barrel/Airframe) C62228-20 N/A 65700 X X X X X XN End fitting pin nutD68062N/A (1)XXXXXXRMS17825-6 N/A (1) X X X X X XR End fitting pinAN6-17N/A (1)XXXXXXRD61183 N/A (1) X X X X X XND68063 N/A (1) X X X X X XRNAS1306-22D N/A (1) X X X X X XEndfittingC62032 N/A 65700 X X X X X XC62032-1 N/A 65700 X X X X X XN .../...C62032-2 N/A 65700 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 12EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325N EndfittingC62032-10 N/A 65700 X X X X X XD61184 N/A 65700 X X X X X XND61184-1 N/A 65700 X X X X X XND68076 N/A 65700 X X X X X XND68695 N/A 65700 X X X X X XRackC61453-1 N/A 65700 X X X X X XNC61453-15 N/A 65700 X X X X X XC61453-20 N/A 65700 X X X X X XC61453-40 N/A 65700 X X X X X XC61453-41 N/A 65700 X X X X X XNC61453-205 N/A 65700 X X X X X XTurningtube C59050-30 N/A 65700 X X X X X XC59050-40 N/A 65700 X X X X X XC59050-50 N/A 65700 X X X X X XC59050-60 N/A 65700 X X X X X XTorque link pin (Upper &Lower)C62223-20 N/A 65700 X X X X X XTorque link (Upper & Lower) C59562-2 N/A 65700 XXXXXXC59562-3 N/A 65700 X X X X X XC59562-4 N/A 65700 X X X X X XNC59562-20 N/A 65700 X X X X X XTorque link medium pin C62041-20 N/A 65700 XXXXXXNC62041-200 N/A 65700 X X X X X XD53431-20 N/A 65700 X X X X X XR Torque link medium pin nut SL40110P N/A (2)XXXXXXA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 13EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325RSHOCK ABSORBER ASSEMBLY (FIG. 06 & 07)RRR(1) The nut must be replaced by a new one every time it is removed from the assembly. When the nut is temporarily removed and reinstalled for the purpose ofperforming maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same assembly andneither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation.R (2) Part must be replaced by a new one everytime it is removed from the sliding rod.R (3) Part must be replaced by a new one every time it is removed from the upper rod.WheelaxleC59053-4 N/A 65700 X X X X X XC59053-21 N/A 65700 X X X X X XR Wheelaxlenut C62879 N/A (1) X X X X X XNC62879-1 N/A (1) X X X X X XND68537 N/A (1) X X X X X XSlidingRodC59051-3 N/A 65700 X X X X X XC59051-21 N/A 65700 X X X X X XR Uppercamdowel C62270 N/A (2) X X X X X XUppercamC62034-1 N/A 65700 X X X X X XNC62034-10 N/A 65700 X X X X X XND68534 N/A 65700 X X X X X XLowercamC62035 N/A 65700 X X X X X XNC62035-1 N/A 65700 X X X X X XND68532 N/A 65700 X X X X X XR Lower cam dowelC62866N/A (3)XXXXXXRestrictorC67863-1 N/A 65700 X X X X X XC67863-2 N/A 65700 X X X X X XC67863-4 N/A 65700 X X X X X XNC67863-10 N/A 65700 X X X X X XN .../...C67863-20 N/A 65700 X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 14EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325N RestrictorC67863-40 N/A 65700 X X X X X XND68536 N/A 65700 X X X X X XUpperRodC59052-2 N/A 65700 X X X X X XR Nut(S/A/Barrel) C64040-1 N/A (1) X X X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 15EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310s PW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325NATA 57-00-00 WING STRUCTURE (FIG. 09 & 10)NMAIN LANDING GEAR SUPPORT RIB ASSEMBLY AND ASSOCIATED FITTINGS (FIG. 09)N (1) This item is not transferable from an aircraft toanother: traceability at aircraft level is authorised.N (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.N (3) Only the area of the top skin panel aft of the rear spar at gear support rib/retraction actuator fitting attachment is considered as safe life.N Gear support rib (LH) (1) (2) A57242444002xx N/A 45000 XXNA57242444006xxN/A 40000 X X X XNN/A 45000 X XNA57242444018xx N/A 40000 X X X XN Gear support rib (RH) (1) (2) A57242444003xx N/A 45000 XXNA57242444007xxN/A 40000 X X X XNN/A 45000 X XNA57242444019xx N/A 40000 X X X XNReaction bar fitting (LH)(1) (2)A57242436002xx N/A45000 X XN A57242436006xxN/A40000 X X X XNA57242436010xx N/A40000 X X X XNReaction bar fitting (RH)(1) (2)A57242436003xx N/A45000 X XN A57242436007xxN/A40000 X X X XNA57242436011xx N/A40000 X X X XNRetraction actuator fitting(LH) (1) (2)A57242452002xxN/A 40000 X X X XNN/A 45000 X XNRetraction actuator fitting(RH) (1) (2)A57242452003xxN/A 40000 X X X XNN/A 45000 X XNLink (Retraction actuatorfitting/Fwd pick up) (1) (2)A57242453200xxN/A 40000 X XNN/A 45000 X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 16EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310s PW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325N Fwd pick up (LH) (1) (2)A57242439000xxN/A 40000 X X X XNN/A 45000 X XNA57242439002xx N/A 40000 X X X XNA57242439004xx N/A 40000 X X X XN Fwd pick up (RH) (1) (2)A57242439001xxN/A 40000 X X X XNN/A 45000 X XNA57242439003xx N/A 40000 X X X XNA57242439005xx N/A 40000 X X X XNTop skin panel n°2 (LH)(1) (2) (3)A57350001200xx N/A 45000 X XNA57350101200xx N/A 45000 X XNA57350101202xx N/A 45000 X XNA57350101204xx N/A 45000 X XNA57350141200xx N/A 40000 X X X XNA57350141202xx N/A 40000 X X X XNTop skin panel n°2 (RH)(1) (2) (3)A57350001201xx N/A 45000 X XNA57350101201xx N/A 45000 X XNA57350101203xx N/A 45000 X XNA57350101205xx N/A 45000 X XNA57350141201xx N/A 40000 X X X XNA57350141203xx N/A 40000 X X X XNFIXED LEADING EDGE STRUCTURE AND SLATS ATTACHEMENTS (FIG. 10)N (1) This item is not transferable from an aircraft toanother: Traceability at aircraft level is authorised.N (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.N (3) Limitation in FC.A310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 17EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310s PW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325NTrack 4 rib (outer) (LH)(1) (2)A57243014200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 4 rib (inner) (LH)(1) (2)A57243014202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 4 rib (outer) (RH)(1) (2)A57243014201xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 4 rib (inner) (RH)(1) (2)A57243014203xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 5 rib (outer) (LH)(1) (2)A57243015200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 5 rib (inner) (LH)(1) (2)A57243015202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 5 rib (outer) (RH)(1) (2)A57243015201xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 5 rib (inner) (RH)(1) (2)A57243015203xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 6 rib (outer) (LH)(1) (2)A57243016200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 6 rib (inner) (LH)(1) (2)A57243016202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 6 rib (outer) (RH)(1) (2)A57243016201xxN/A 40000 (3) X X X XNN/A 45000(3) X XN Track 6 rib (inner) (RH)(1) (2)A57243016203xxN/A 40000 (3) X X X XNN/A 45000(3) X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 18EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310s PW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325NTrack 7 rib (outer) (LH)(1) (2)A57243017200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 7 rib (inner) (LH)(1) (2)A57243017202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 7 rib (outer) (RH)(1) (2)A57243017201xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 7 rib (inner) (RH)(1) (2)A57243017203xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 8 rib (outer) (LH)(1) (2)A57243018200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 8 rib (inner) (LH)(1) (2)A57243018202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 8 rib (outer) (RH)(1) (2)A57243018201xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 8 rib (inner (RH)(1) (2)A57243018203xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 9 rib (outer) (LH)(1) (2)A57243019200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 9 rib (inner (LH)(1) (2)A57243019202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 9 rib (outer) (RH)(1) (2)A57243019201xxN/A 40000 (3) X X X XNN/A 45000(3) X XN Track 9 rib (inner) (RH)(1) (2)A57243019203xxN/A 40000 (3) X X X XNN/A 45000(3) X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 19EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability system are provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A310s PW POWERED A310sNomenclaturePart Number FH LDG A310-20xA310-30x A310-22x A310-322 A310-324 A310-325NTrack 10 rib (outer) (LH)(1) (2)A57243020200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 10 rib (inner) (LH)(1) (2)A57243020202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 10 rib (outer) (RH)(1) (2)A57243020201xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 10 rib (inner) (RH)(1) (2)A57243020203xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 11 rib (outer) (LH)(1) (2)A57243021200xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 11 rib (inner) (LH)(1) (2)A57243021202xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 11 rib (outer) (RH)(1) (2)A57243021201xxN/A 40000 (3) X X X XNN/A 45000(3) X XNTrack 11 rib (inner) (RH)(1) (2)A57243021203xxN/A 40000 (3) X X X XNN/A 45000(3) X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 20EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability systemare provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH FC A310-20X A310-30x A310-22x A310-322 A310-324 A310-325RATA 71-20-00 ENGINE MOUNTS (FIG. 11 to 13)RGENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY (FIG. 11)Shear bolt (Outer Link/Lowerbeam)96739-16-70 N/A 64000 -203/3C9380M75P02N/A64000-204XShear bolt (Inner, RH Link/Lower beam)96739-12-60 N/A 64000 -203/3C9380M80P02N/A64000-204XLink (LH)224-1608-7 N/A 80000 -203/3C224-1608-9 N/A 80000 -203/3C1846M23P01 N/A 50000 -204 XLink (RH)224-1615-511 N/A 80000 -203/3C224-1615-513 N/A 80000 -203/3C9348M84P02 N/A 80000 -204 XShear bolt (Link/Engine)96738-8N/A 64000 -203/3C9380M73P02 N/A 64000 -204 XRPRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 12)R Bolt (Link/Fan case) 221-0251-511 N/A 40000X X X XThrust link221-0245-5 N/A 40000X X X X221-0245-9 N/A 40000X X X X221-0245-13 N/A 40000X X X XBolt (Link/Cross beam) 221-0251-515 N/A 40000X X X XCross beam221-0242-5 N/A 40000X X X221-4004-1 N/A 40000X X X X221-4004-5 N/A 40000X X X XBolt (Cross beam/Mainbeam)221-0251-509 N/A 40000X X X XA310 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE: 21EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: explanations on the applicability systemare provided in the sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)APPLICABILITYNotes are located under the assy title.GE POWERED A310sPW POWERED A310sNomenclaturePart Number FH FC A310-20X A310-30x A310-22x A310-322 A310-324 A310-325Main beam221-0241-5 N/A 40000X X221-4006-3 N/A 40000X X X X221-4006-5 N/A 40000X X X XShear pin221-0252-507 N/A 40000X X X XOuter support221-0243-501 N/A 40000X XInner support221-0244-501 N/A 40000X X221-0244-503 N/A 40000X XSupport221-4047-503 N/A 40000X221-4047-505 N/A 40000X X221-4047-507 N/A 40000X XRPRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 13)Main beam221-261-9 N/A 40000X X X X221-0261-11 N/A 40000X X X X221-0261-15 N/A 40000X X X XPin (Link/Main beam)221-0264-503 N/A 40000X X X XLink221-0262-5 N/A 40000X X221-0262-7 N/A 40000X X X XBolt (Mid link/Engine)80876-20-6 N/A 40000X X X XBolt (Side link/Engine)80876-20-5 N/A 40000X X X XEND OF SUB-PART 1-3

# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

HISTORY FILE

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 1/6

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# 1- GENERAL

- A310 ALS Part 1 revision 00:

The airworthiness limitations previously listed in the A310 MPD section 9-1 were transferred into

the initial version of the ALS Part 1, (excluding the system-related airworthiness limitations that

were transferred to the A310 ALS Part 4).

- A310 ALS Part 1 revision 01:

This revision is dedicated to introduce new Safe Life Airworthiness Limitation Items (wing and

landing gear/wing interface components). The Weight Variant 13 is introduced for the A310-308

model. This revision includes the variation 0BVLG120007/C0S.

2- SUMMARY OF CHANGES:

The following summarizes the changes with respect to the previous issue of the A310 ALS Part

1 (revision 00).

New items:

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY:

* A310-300 series:

Introduction of the WV13 (MOD 13302) for A310-308 model.

SUB-PART 1-2:

None.

SUB-PART 1-3:

* Main landing gear:

Aft pintle pin PNR A32140108200xx, PNR A32140108202xx, PNR A32140128000xx

and PNR A32140128002xx: PNR added.

Half ball housing (Fwd pintle bearing) PNR A32140101200xx, PNR A32140101201xx,

PNR A32140130002xx, PNR A32140130003xx, PNR A32140132006xx and PNR

A32140132007xx: PNR added.

Ball (Fwd pintle bearing) PNR A32140100200xx and PNR A32140131200xx: PNR

added.

Reaction bar pin PNR A32140117200xx: PNR added.

* Wing structure, Main landing gear support rib assembly and associated fittings:

Notes (1), (2) and (3) added.

Gear support rib (LH) PNR A57242444002xx, PNR A57242444006xx and PNR

A57242444018xx: PNR added.

Gear support rib (RH) PNR A57242444003xx, PNR A57242444007xx and PNR

A57242444019xx: PNR added.

# A310 AIRWORTHINESS LIMITATIONS SECTION

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HISTORY FILE

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© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# Reaction bar fitting (LH) PNR A57242436002xx, PNR A57242436006xx and PNR

A57242436010xx: PNR added.

Reaction bar fitting (RH) PNR A57242436003xx, PNR A57242436007xx and PNR

A57242436011xx: PNR added.

Retraction actuator fitting (LH) PNR A57242452002xx: PNR added.

Retraction actuator fitting (RH) PNR A57242452003xx: PNR added.

Link (Retraction actuator fitting/Fwd pick up) PNR A57242453200xx: PNR added.

Fwd pick up (LH) PNR A57242439000xx, PNR A57242439002xx and PNR

A57242439004xx: PNR added.

Fwd pick up (RH) PNR A57242439001xx, PNR A57242439003xx and PNR

A57242439005xx: PNR added.

Top skin panel n°2 (LH) PNR A57350001200xx, PNR A57350101200xx, PNR

A57350101202xx, PNR A57350101204xx, PNR A57350141200xx and PNR

A57350141202xx: PNR added.

Top skin panel n°2 (RH) PNR A57350001201xx, PNR A57350101201xx, PNR

A57350101203xx, PNR A57350101205xx, PNR A57350141201xx and PNR

A57350141203xx: PNR added.

* Wing structure, Fixed leading edge structure and slat attachments:

Notes (1), (2) and (3) added.

Track 4 rib (outer) (LH) PNR A57243014200xx: PNR added.

Track 4 rib (inner) (LH) PNR A57243014202xx: PNR added.

Track 4 rib (outer) (RH) PNR A57243014201xx: PNR added.

Track 4 rib (inner) (RH) PNR A57243014203xx: PNR added.

Track 5 rib (outer) (LH) PNR A57243015200xx: PNR added.

Track 5 rib (inner) (LH) PNR A57243015202xx: PNR added.

Track 5 rib (outer) (RH) PNR A57243015201xx: PNR added.

Track 5 rib (inner) (RH) PNR A57243015203xx: PNR added.

Track 6 rib (outer) (LH) PNR A57243016200xx: PNR added.

Track 6 rib (inner) (LH) PNR A57243016202xx: PNR added.

Track 6 rib (outer) (RH) PNR A57243016201xx: PNR added.

Track 6 rib (inner) (RH) PNR A57243016203xx: PNR added.

Track 7 rib (outer) (LH) PNR A57243017200xx: PNR added.

Track 7 rib (inner) (LH) PNR A57243017202xx: PNR added.

Track 7 rib (outer) (RH) PNR A57243017201xx: PNR added.

Track 7 rib (inner) (RH) PNR A57243017203xx: PNR added.

Track 8 rib (outer) (LH) PNR A57243018200xx: PNR added.

Track 8 rib (inner) (LH) PNR A57243018202xx: PNR added.

Track 8 rib (outer) (RH) PNR A57243018201xx: PNR added.

Track 8 rib (inner) (RH) PNR A57243018203xx: PNR added.

Track 9 rib (outer) (LH) PNR A57243019200xx: PNR added.

Track 9 rib (inner) (LH) PNR A57243019202xx: PNR added.

Track 9 rib (outer) (RH) PNR A57243019201xx: PNR added.

# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

HISTORY FILE

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 3/6

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# Track 9 rib (inner) (RH) PNR A57243019203xx: PNR added.

Track 10 rib (outer) (LH) PNR A57243020200xx: PNR added.

Track 10 rib (inner) (LH) PNR A57243020202xx: PNR added.

Track 10 rib (outer) (RH) PNR A57243020201xx: PNR added.

Track 10 rib (inner) (RH) PNR A57243020203xx: PNR added.

Track 11 rib (outer) (LH) PNR A57243021200xx: PNR added.

Track 11 rib (inner) (LH) PNR A57243021202xx: PNR added.

Track 11 rib (outer) (RH) PNR A57243021201xx: PNR added.

Track 11 rib (inner) (RH) PNR A57243021203xx: PNR added.

Amendments:

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY:

* A310-200 series:

Extension of WV00 (Basic aircraft) to A310-222 model.

SUB-PART 1-2:

* Main landing gear:

Figures number added.

* Main landing gear, Barrel assembly:

Figure number amended.

* Main landing gear, Shock absorber assembly:

Figure number amended.

* Main landing gear, Linkage assembly:

Figures number deleted.

* Main landing gear, Brace assembly:

Figure number added.

* Nose landing gear:

Figures number added.

Note (1) amended.

* Nose landing gear, Barrel assembly:

Figures number amended.

Barrel PNR C59049-27; PNR C59049-42; PNR C59049-47 and PNR D56525-11: PNR

added (MOD 13212).

# A310 AIRWORTHINESS LIMITATIONS SECTION

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SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

HISTORY FILE

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 4/6

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# * Main landing gear, Shock absorber assembly:

Figures number amended.

Bottom PNR D68531: PNR added (MOD 13457).

* Engine mounts:

Figures number added.

Note (1) transferred in ‘Cal.’ column.

Notes (2) and (3) renumbered.

* Engine mounts, General electric aft engine mount assembly:

Figure number amended.

* Engine mounts, Pratt & Whitney forward engine mount assembly:

Figure number amended.

* Engine mounts, Pratt & Whitney aft engine mount assembly:

Figure number amended.

SUB-PART 1-3:

* Main landing gear:

Figures number added.

Note (1) amended.

Pin (Drop link/Frame 50) PNR A53811122202xx: PNR added (MOD 13384).

* Main landing gear, Barrel assembly:

Figure number amended.

Note (3) amended.

Pin (Connecting rod/Upper rod) PNR D52751-2, PNR D52751-10 and PNR D68547:

PNR added (MOD 13450).

* Main landing gear, Shock absorber assembly:

Figure number amended.

Notes (3) and (6) amended.

Brake torque arm pin PNR D52712-1: PNR added (MOD 13450).

* Main landing gear, Brace assembly:

Figure number added.

* Main landing gear, Brace assembly, Lock link:

Note (1) amended.

# A310 AIRWORTHINESS LIMITATIONS SECTION

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SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

HISTORY FILE

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 5/6

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# * Nose landing gear:

Figures number added.

Note (1) amended.

Pintle pin PNR A32210082200xx: PNR added (MOD 13380).

* Nose landing gear, Telescopic strut assembly:

Figure number amended.

End fitting pin PNR C62911-18 and PNR C62911-25: PNR added (MOD 13455).

Nut (Cylinder/Locking cylinder) PNR C61375- 1, PNR D55955-1 and PNR D68538: PNR

added (MOD 13455), nomenclature amended.

Locking cylinder PNR C61373-10: PNR added (MOD 13455).

Locking piston PNR C61378-10: PNR added (MOD 13455).

* Nose landing gear, Barrel assembly:

Figures number amended.

Notes (1) and (2) amended.

Lower pin (Link/Clevis) PNR C62268-200 and PNR D68541: PNR added (MOD 13456).

Link (Clevis/Barrel) PNR C62230-10, P NR D56526-1, PNR D68539 and PNR D68540:

PNR added (MOD 13456).

Upper pin (Link/Barrel) PNR C62267-200 and PNR D68544: PNR added (MOD 13456).

End fitting pin nut:

- PNR D68062: PNR added (MOD 13212),

- PNR MS17825-6: Note (1) assigned.

End fitting pin:

- PNR AN6-17, PNR D61183 and PNR NAS1306-22D: Note (1) assigned.

- PNR D68063: PNR added (MOD 13212).

End fitting:

- PNR D68076: PNR added (MOD 13212).

- PNR C62032-2, PNR C62032-10, PNR D61184-1 and PNR D68695: PNR added

(MOD 13456).

Rack PNR C61453-15 and PNR C61453-205: PNR added (MOD 13456).

Torque link (Upper & Lower) PNR C59562-20: PNR added (MOD 13456).

Torque link medium pin PNR C62041-200: PNR added (MOD 13456).

Torque link medium nut PNR SL40110P: Note (2) assigned.

* Main landing gear, Shock absorber assembly:

Figures number amended.

Notes (1), (2) and (3) amended.

Wheel axle nut:

- PNR C62879: Note (1) assigned.

- PNR C62879-1 and PNR D68537: PNR added (MOD 13457).

Upper cam dowel PNR C62270: Note (2) assigned.

Upper cam PNR C62034-10 and PNR D68534: PNR added (MOD 13457).

Lower cam PNR C62035-1 and PNR D68532: PNR added (MOD 13457).

# A310 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

HISTORY FILE

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 6/6

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. 

# Lower cam dowel PNR C62866: Note (3) assigned.

Restrictor PNR C67863-10, PNR C67863- 20, PNR C67863-40 and PNR D68536: PNR

added (MOD 13457).

Nut (S/A/Barrel) PNR C64040-1: Limitation amended, note (1) assigned.

* Engine mounts:

Figures number added.

* Engine mounts, General electric aft engine mount assembly:

Figure number amended.

* Engine mounts, Pratt & Whitney forward engine mount assembly:

Figure number amended.

Bolt (Link/Fan case) PNR 221-0251-511: PNR corrected.

* Engine mounts, Pratt & Whitney aft engine mount assembly:

Figure number amended.

Deletions:

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY:

None.

SUB-PART 1-2:

None.

SUB-PART 1-3:

None.