# A300 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 granted by the delivery of this document or the disclosure of its

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

purposes of performing the tasks described 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.

# A300 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

1 1-TOC SEP 06/07

1 R 1-ROR SEP 05/13

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# A300 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

TABLE OF CONTENTS

SUBJECT PART

ISSUE: SEP 06/07 ALS PART 1 PAGE: 1-TOC

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

# RECORDS OF REVISIONS ROR

INTRODUCTION 1-0

ILLUSTRATIONS 1-1

LIFE LIMITS 1-2

DEMONSTRATED FATIGUE LIVES 1-3

# A300 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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R 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 SEP 06/07 2007-0293

N 01 ROR

1-2

1-3 SEP 05/13

Note: The ALS Part 1 is covered by the Certification Document 00X0500M091/M01.

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 A300 ALS Part 1 revision 01.

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

airworthiness limitations defined, either:

- In the A300 ALS Part 1 at revision 00,

or,

- In the A300 ALS Part 1 at revision 01.

3. Special compliance times for components w hose 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.

# A300 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 A32140032200xx 13-Dec-2007 13500 9 years

N A32140056200xx 13-Dec-2007 13500 9 years

N A32140056202xx 13-Dec-2007 13500 9 years

N A32140057200xx 13-Dec-2007 13500 9 years

N A32140057202xx 13-Dec-2007 13500 9 years

N A32140057204xx 05-Sep-2013 13500 9 years

N A32140062000xx 13-Dec-2007 13500 9 years

N A32140063000xx 13-Dec-2007 13500 9 years

N A32140063002xx 05-Sep-2013 13500 9 years

N Half ball housing (Fwd pintle bearing) A32140036200xx 13-Dec-2007 13500 9 years

N A32140036202xx 13-Dec-2007 13500 9 years

N A32140036204xx 13-Dec-2007 13500 9 years

N A32140036206xx 13-Dec-2007 13500 9 years

N A32140042200xx 13-Dec-2007 13500 9 years

N A32140042202xx 13-Dec-2007 13500 9 years

N A32140068002xx 13-Dec-2007 13500 9 years

N A32140068004xx 13-Dec-2007 13500 9 years

N A32140069002xx 13-Dec-2007 13500 9 years

N A32140069004xx 13-Dec-2007 13500 9 years

N Ball (Fwd pintle bearing) A32140012202xx 13-Dec-2007 13500 9 years

N A32140043202xx 13-Dec-2007 13500 9 years

N Pin (Multiple link/Frame 50) A53833451200xx 13-Dec-2007 13500 9 years

N A53833451204xx 13-Dec-2007 13500 9 years

N A53833451206xx 13-Dec-2007 13500 9 years

N A53833451208xx 13-Dec-2007 13500 9 years

N A53834451200xx 13-Dec-2007 13500 9 years

N A53834451202xx 25-Apr-2007 13500 9 years

N MLG Barrel assembly

N Attaching fitting pin C62311-1 13-Dec-2007 13500 9 years

N C62311-20 25-Apr-2007 13500 9 years

N Pin (Connecting rod/Upper rod) C65815 13-Dec-2007 13500 9 years

N C65815-1 13-Dec-2007 13500 9 years

N C65815-20 13-Dec-2007 13500 9 years

N C66472 13-Dec-2007 13500 9 years

N C66472-1 13-Dec-2007 13500 9 years

N C66472-20 25-Apr-2007 13500 9 years

N MLG Shock absorber assembly

N Bogie beam pivot pin nut SL40054 13-Dec-2007 (2) 9 years

N SL40054P 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

# A300 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. N Designation PNR Start date Compliance time

N LDG CAL

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) C62231-1 13-Dec-2007 13200 9 years

N C62231-2 13-Dec-2007 13200 9 years

N C62231-20 25-Apr-2007 13500 9 years

N D56530 25-Apr-2007 13500 9 years

N Lower pin (Link/Clevis) C62268-1 13-Dec-2007 13200 9 years

N C62268-2 13-Dec-2007 13200 9 years

N 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) C62267-1 13-Dec-2007 13200 9 years

N C62267-2 13-Dec-2007 13200 9 years

N 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

N Rack C61453 13-Dec-2007 13200 9 years

N 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) C62223-1 13-Dec-2007 13200 9 years

N 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 C62036 13-Dec-2007 13200 9 years

N C62036-1 13-Dec-2007 13200 9 years

N C62036-2 13-Dec-2007 13200 9 years

N C67863 13-Dec-2007 13200 9 years

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

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

N C67863-3 13-Dec-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 13-Dec-2007 (2) 9 years

N C64040-1 13-Dec-2007 (2) 9 years

# A300 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

RECORD OF REVISIONS

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

EASA APPROVED

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

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N (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.

# A300 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 29 and on, the content of the

A300 Aircraft Maintenance Manual Chapter 05

Service Life Limits and Maintenance Checks

that provided life limitations applicable to A300 models, has been transferred to the

A300 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 serie s 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 contained 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 otherwi se agreed with the Authority of the State

of 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 thos e having a demonstrated fatigue life without

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

For these parts, the life limitat ion provided (in 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.

# A300 AIRWORTHINESS LIMITATIONS SECTION

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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 PNR 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 requi red to assure traceability and moni toring 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 re leased 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 ap plied. Traceability re cords may comprise

of, but are not limited to, the following:

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

Manufacturer Serial Number, etc...),

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

repairs, inspections, etc...).

- Life accumulation (account ing for any individual 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 for guidance. It provides the means to

manage such parts. It has been issued in agreement with the European Aviation Safety

Agency (EASA).

Note: Traceability and monitoring of parts listed in sub-parts 1-2 a nd 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:

# A300 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 their life potential provided they are applied

prior to reaching the life limit (e.g. Serv ice 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 aircraft series, models

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

R Aircraft series Aircraft models WV

R A300 B2-100 A300 B2-1C 00, 01, 02, 03

R A300 B2-200 A300 B2K-3C 00, 01, 03 R A300 B2-203

R

A300 B4-100 A300 B4-2C 00, 01, 02, 03, 04, 05, 11, 12, 13, 14, 15, 19

R A300 B4-103 00, 01, 02, 03, 04, 05, 11, 12, 13, 14, 15, 19,

20

R A300 B4-200 A300 B4-203 06, 07, 08, 10, 14, 16, 17, 18, 20, 21, 22

R A300 C4-200 A300 C4-203 06, 07

R A300 F4-200 A300 F4-203 07

Note 1: The models A300 B1, A300 B2-1A, A300 B2-202, A300 B2-320, A300 B4-102,

A300 B4-120 and A300 B4-220 are no longer in service. LRUs and

airworthiness limitations for detail parts applicable to these models are listed in

the tables of sub-parts 1-0 (§ 7), 1-2 an d 1-3 of this document, only when they

are common to other A300 models listed in the table above.

Note 2: The engine Time Limits and Maintenance Checks are not included in this

manual: Refer to the relevant Engine Manufacturer Chapter 05 manual. R

R

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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R 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.

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.

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 airc raft 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 individual 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 the paragraph 1.E. of this sub-part, e.g.:

B4-2xx stands for: A300 B4-203 and A300 B4-220.

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

X stands for: All A300 m odels defined by the appli cability of the column. N

N

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D

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# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

# B4-120 stands for: A300 B4 -120 model only, defined by the applicability of the

column.

B4-203/-220 stands for: A300 B4-203 and A300 B4-220 models only, defined by the

applicability of the column.

C4/F4-203 stands for: A300 C4-203 and A300 F4-203 models only, defined by the

applicability of the column.

excl. B2-202 stands for: All A300 models defined by the applicability of the column,

except the model A300 B2-202.

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 DGAC-F, together with the associated modificati on configuration(s).

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

modifications embodied during production, pr ovided to the initial Operator of the

aircraft, in the delivery documentation (Aircr aft 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 applicability

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

e.g.:

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

defined by the applicabilit y 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 R

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R In computing part’s accumulated life, ca lculations must include 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 servi ce (unless otherwise stated).

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 Approval (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 Aut hority for any necessary adaptations of the

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

# A300 AIRWORTHINESS LIMITATIONS SECTION

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R 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 transferre d from an Owner/Operator to another, the

associated approvals and documents indicating the necessary adaptations of

limitations have to be transferred as well.

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 must 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/Com ponent Maintenance Manual manufacturer

(CMMm) issued by Airbus.

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

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

vendors.

Messier-Dowty SB will be issued to provide in formation on procurabl e replacement PNR,

detail PNR and applicable SB. i

j j

i 

# Cp Cp Ca

1Tr   

 

 

 

 

 

 

 

 

# 

R

R

N D

R

R

R

R

R

R

R

R

RA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 8© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RR7. LANDING GEAR LRUs APPLICABILITYA. A300 B1 model, A300 B2-100/-200/-300 series installationsA300B1 XA300B2-1A X X X XA300B2-1C X X X XA300B2K-3C X X XA300B2-202 X X XA300B2-203 X X XA300B2-320 XWEIGHTVARIANT 00 00 00 01 02 03 00MTOW 137 137 142 137 142 134 142MLW 122 127.5 130 130 130 130136 (1)134 (2)MZFW 116.5 116.5 120.5 120.5 120.5 120.5 126R Top assembly PNRMain Landing Gear LegC22997/8-1 X X X XC22997/8-2 X X X XC22997/8-3 X X X X X XC22997/8-4 X X X X X XC22997/8-5 X X X X X XC22997/8-6 X X X X XC22997/8-7 X X X X XC22997/8-8 X X X X XC22997/8-18 X X X X X X XC23093/4-0NOT AUTHORIZEDC23093/4-1NOT AUTHORIZEDA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 9© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300B1 XA300B2-1A X X X XA300B2-1C X X X XA300B2K-3C X X XA300B2-202 X X XA300B2-203 X X XA300B2-320 XWEIGHTVARIANT 00 00 00 01 02 03 00MTOW 137 137 142 137 142 134 142MLW 122 127.5 130 130 130 130136 (1)134 (2)MZFW 116.5 116.5 120.5 120.5 120.5 120.5 126R Top assembly PNRC23093/4-2NOT AUTHORIZEDC23093/4-3NOT AUTHORIZEDC23093/4-4 XC23093/4-5 XC23093/4-8 XC23093/4-9 XC23093/4-10 XC23093/4-11 XC23093/4-12NOT AUTHORIZEDC23093/4-15 XC23093/4-19 XC23093/4-25 XC23093/4-35 XMain Landing Gear Brace StrutC23021/2-0 XC23021/2-1 XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 10© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300B1 XA300B2-1A X X X XA300B2-1C X X X XA300B2K-3C X X XA300B2-202 X X XA300B2-203 X X XA300B2-320 XWEIGHTVARIANT 00 00 00 01 02 03 00MTOW 137 137 142 137 142 134 142MLW 122 127.5 130 130 130 130136 (1)134 (2)MZFW 116.5 116.5 120.5 120.5 120.5 120.5 126R Top assembly PNRC23021/2-2 X X X X XC23021/2-3 X X X X XC23021/2-4 X X X X X XC23111/2-1NOT AUTHORIZEDC23111/2-2 XC23111/2-3 XC23111/2-23 XMain Landing Gear Structural LinkageC23023/4-0 X X X X XC23023/4-1 X X X X XC23121/2-0 XC23121/2-1 XDC23121/2-21 XNose Landing Gear LegC23042-0 XC23042-2 X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 11© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300B1 XA300B2-1A X X X XA300B2-1C X X X XA300B2K-3C X X XA300B2-202 X X XA300B2-203 X X XA300B2-320 XWEIGHTVARIANT 00 00 00 01 02 03 00MTOW 137 137 142 137 142 134 142MLW 122 127.5 130 130 130 130136 (1)134 (2)MZFW 116.5 116.5 120.5 120.5 120.5 120.5 126R Top assembly PNRC23042-3 X X X XC23137-0NOT AUTHORIZEDC23137-1 X X X X XC23137002 X X X X X XC23137003NOT AUTHORIZEDC23137006 XNose Landing Gear Telescopic StrutC23037-1 X X X XC23037-2 X X X XC23037-3 X X X X X XC23037-4 X X X X X XC23037-12 X X X XC23037-13 X X X X X XC23037-14 X X X X X XC23109-0 X X X X XC23109-1 X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 12© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300B1 XA300B2-1A X X X XA300B2-1C X X X XA300B2K-3C X X XA300B2-202 X X XA300B2-203 X X XA300B2-320 XWEIGHTVARIANT 00 00 00 01 02 03 00MTOW 137 137 142 137 142 134 142MLW 122 127.5 130 130 130 130136 (1)134 (2)MZFW 116.5 116.5 120.5 120.5 120.5 120.5 126R Top assembly PNRC23109-2 XC23109-11 XC23109-12 XC23109610 XC23109710 XWeight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet - TCDS N°145):A300 B1 series:WV00: Basic aircraft.A300 B2-100/200 series (refer to § 1E):WV00: Basic aircraft.WV01: Aircraft POST MOD 01569 or POST SB A300-34-0025.WV02: Aircraft POST MOD 01357 or POST SB A300-34-0008.WV03: Aircraft POST MOD 06696.A300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 13© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300 B2-300 series (refer to § 1E):WV00: Basic aircraft.Note (1): Slat 16° Flaps 15°.Note (2): Slat 25° Flaps 25°.THE ABOVE TABLE INDICATES THE LANDING GEARLRUs THAT CAN BE INSTALLED FOR EACHAIRCRAFT 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.RA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 14© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RB. A300 B4-100 series installationsA300 B4-2C X X X X X X X X X X XA300 B4-102 X X X X X X X X X X XR A300 B4-103 X X X X X X X X X X X XA300 B4-120 X X X X X X X X X X XRWEIGHT VARIANT 00 01 02 03 04 05 12 13 14 15 19 20R MTOW150 153 157.5 157.5 150 153 160 150 157.5 150 135 154R MLW133 133 133 134 133 134136 (1)134 134 134 134 134134 (2)R MZFW122 122 122 124 122 124 123 126 126 126 126 126R Top assembly PNRMain Landing Gear LegC22997/8 seriesNOT AUTHORIZEDR C23093/4-0 X X X X X X X X X X X XR C23093/4-1 X X X X X X X X X X X XR C23093/4-2 X X X X X X X X X X X XR C23093/4-3 X X X X X X X X X X X XR C23093/4-4 X X X X X X X X X X X XR C23093/4-5 X X X X X X X X X X X XR C23093/4-8 X X X X X X X X X X X XR C23093/4-9 X X X X X X X X X X X XR C23093/4-10 X X X X X X X X X X X XR C23093/4-11 X X X X X X X X X X X XC23093/4-12NOT AUTHORIZEDR C23093/4-15 X X X X X X X X X X X XR C23093/4-19 X X X X X X X X X X X XR C23093/4-25 X X X X X X X X X X X XR C23093/4-35 X X X X X X X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 15© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300 B4-2C X X X X X X X X X X XA300 B4-102 X X X X X X X X X X XR A300 B4-103 X X X X X X X X X X X XA300 B4-120 X X X X X X X X X X XRWEIGHT VARIANT 00 01 02 03 04 05 12 13 14 15 19 20R MTOW150 153 157.5 157.5 150 153 160 150 157.5 150 135 154R MLW133 133 133 134 133 134136 (1)134 134 134 134 134134 (2)R MZFW122 122 122 124 122 124 123 126 126 126 126 126R Top assembly PNRMain Landing Gear Brace StrutC23021/2 seriesNOT AUTHORIZEDR C23111/2-1 X X X X X X X X X X X XR C23111/2-2 X X X X X X X X X X X XR C23111/2-3 X X X X X X X X X X X XR C23111/2-23 X X X X X X X X X X X XMain Landing Gear Structural LinkageC23023/4 seriesNOT AUTHORIZEDR C23121/2-0 X X X X X X X X X X X XR C23121/2-1 X X X X X X X X X X X XRDC23121/2-21 X X X X X X X X X X X XNose Landing Gear LegC23042 seriesNOT AUTHORIZEDR C23137-0X X X X X X X X X X X XR C23137-1X X X X X X X X X X X XR C23137002 X X X X X X X X X X X XC23137003NOT AUTHORIZEDR C23137006 X X X X X X X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 16© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300 B4-2C X X X X X X X X X X XA300 B4-102 X X X X X X X X X X XR A300 B4-103 X X X X X X X X X X X XA300 B4-120 X X X X X X X X X X XRWEIGHT VARIANT 00 01 02 03 04 05 12 13 14 15 19 20R MTOW150 153 157.5 157.5 150 153 160 150 157.5 150 135 154R MLW133 133 133 134 133 134136 (1)134 134 134 134 134134 (2)R MZFW122 122 122 124 122 124 123 126 126 126 126 126R Top assembly PNRNose Landing Gear Telescopic StrutC23037 seriesNOT AUTHORIZEDC23109-0X X X X X X X XR C23109-1X X X X X X X X X X X XR C23109-2X X X X X X X X X X X XR C23109-11 X X X X X X X X X X X XR C23109-12 X X X X X X X X X X X XR C23109610 X X X X X X X X X X X XR C23109710 X X X X X X X X X X X XWeight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet - TCDS N°145):A300 B4-100 series (refer to § 1E):WV00: Basic aircraft.WV01: Aircraft POST MOD 01614 or POST SB A300-34-0020.WV02: Aircraft POST MOD 01652 or POSTSB A300-34-0024 or SB A300-34-0127.WV03: Aircraft POST MOD 01652 and MOD 02032 or POST SB A300-34-0024 and SB A300-34-0048.WV04: Aircraft POST MOD03752 or POST A300-00-0018.WV05: Aircraft POST MOD 01614 and MOD 02032 or POST SB A300-34-0020 and SB A300-34-0048.WV11: This WV is listed in the TCDS N°145 however the LRU table above does not list WV11, as never embodied on any A300Aircraft.A300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 17© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.WV12: Aircraft POST MOD 05511 or POST SB A300-00-0004.WV13: Aircraft POST MOD 06207 and MOD 06208.WV14: Aircraft POST MOD 06193 or POST SB A300-00-0007.WV15: Aircraft POST MOD 07163.WV19: Aircraft POST MOD 12875.or POST SB A300-00-0038.WV20: Aircraft POST MOD 13468 or POST SB A300-00-0041.Note (1): Slat 16° Flaps 15°.Note (2): Slat 25° Flaps 25°.THE ABOVE TABLE INDICATES THE LANDING GEARLRUs THAT CAN BE INSTALLED FOR EACHAIRCRAFT 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.RA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 18© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RC. A300 B4/C4/F4-200 series installationsR A300 B4-203 X X X X X X X X X X XA300B4-220 X XA300C4-203 X XA300F4-203 XRWEIGHT VARIANT 06 07 08 10 14 16 17 18 20 21 22R MTOW165 165 157.5 157.5 157.5 147.5 147.5 165 157.5 154 154R MLW134136 (1)134136 (1)134 134136 (1)134 134 136 134134 (2)134 (2)134 (2)R MZFW124 126 124 126 126 124 126 126 126 126 126R Top assembly PNRMain Landing Gear LegC22997/8 seriesNOT AUTHORIZEDC23093/4-0NOT AUTHORIZEDC23093/4-1NOT AUTHORIZEDC23093/4-2NOT AUTHORIZEDC23093/4-3NOT AUTHORIZEDC23093/4-4NOT AUTHORIZEDR C23093/4-5 X X X X X X X X X X XR C23093/4-8B4-203B4-220B4-203 X X X X X X X X XR C23093/4-9 X X X X X X X X X X XR C23093/4-10B4-203B4-220B4-203 X X X X X X X X XC23093/4-11NOT AUTHORIZEDR C23093/4-12B4-203B4-220B4-203 X X X X X X X X XR C23093/4-15 X X X X X X X X X X XR C23093/4-19B4-203B4-220B4-203 X X X X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 19© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.R A300 B4-203 X X X X X X X X X X XA300B4-220 X XA300C4-203 X XA300F4-203 XRWEIGHT VARIANT 06 07 08 10 14 16 17 18 20 21 22R MTOW165 165 157.5 157.5 157.5 147.5 147.5 165 157.5 154 154R MLW134136 (1)134136 (1)134 134136 (1)134 134 136 134134 (2)134 (2)134 (2)R MZFW124 126 124 126 126 124 126 126 126 126 126R Top assembly PNRR C23093/4-25 X X X X X X X X X X XR C23093/4-35 X X X X X X X X X X XMain Landing Gear Brace StrutC23021/2 seriesNOT AUTHORIZEDC23111/2-1B4-203B4-220C23111/2-2B4-203B4-220R C23111/2-3 X X X X X X X X X X XR C23111/2-23 X X X X X X X X X X XMain Landing Gear Structural LinkageC23023/4 seriesNOT AUTHORIZEDC23121/2-0NOT AUTHORIZEDR C23121/2-1 X X X X X X X X X X XRDC23121/2-21 X X X X X X X X X X XNose Landing Gear LegC23042 seriesNOT AUTHORIZEDR C23137-0 X X X X X X X X X X XR C23137-1 X X X X X X X X X X XR C23137002 X X X X X X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 20© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.NR A300 B4-203 X X X X X X X X X X XA300B4-220 X XA300C4-203 X XA300F4-203 XRWEIGHT VARIANT 06 07 08 10 14 16 17 18 20 21 22R MTOW165 165 157.5 157.5 157.5 147.5 147.5 165 157.5 154 154R MLW134136 (1)134136 (1)134 134136 (1)134 134 136 134134 (2)134 (2)134 (2)R MZFW124 126 124 126 126 124 126 126 126 126 126R Top assembly PNRR C23137003B4-203B4-220B4-203 X X X X X X X X XR C23137006 X X X X X X X X X X XNose Landing Gear Telescopic StrutC23037 seriesNOT AUTHORIZEDC23109-0NOT AUTHORIZEDR C23109-1 X X X X X X X X X X XR C23109-2 X X X X X X X X X X XR C23109-11 X X X X X X X X X X XR C23109-12 X X X X X X X X X X XR C23109610 X X X X X X X X X X XR C23109710 X X X X X X X X X X XWeight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet - TCDS N°145):A300 B4-200 series (refer to § 1E):WV06: Basic aircraft.WV07: Aircraft POST MOD 03195. or POST SB A300-00-0037.WV08: Aircraft POST MOD 03424.WV10: Aircraft POST MOD 03195 or POST SB A300-00-0037and MOD 03424 or POST MOD 6193 or POST SB A300-00-0007.WV14: Aircraft POST MOD 06193 or POST SB A300-00-0007.A300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 21© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.NNNWV16: Aircraft POST MOD 11685 or POST SB A300-00-0028.WV17: Aircraft POST MOD 11686 or POST SB A300-00-0027.WV18: Aircraft POST MOD 11877 or POST SB A300-00-0032.WV20: Aircraft POST MOD 13362 or POST SB A300-00-0040.WV21: Aircraft POST MOD 13469 or POST SB A300-00-0042.WV22: Aircraft POST MOD 13470 or POST SB A300-00-0043.A300 C4-200 series (refer to § 1E):WV06: Basic aircraft.WV07: Aircraft POST MOD 03195 and MOD 03319.A300 F4-200 series (refer to § 1E):WV07: Basic aircraft.Note (1): Slat 16° Flaps 15°.Note (2): Slat 25° Flaps 25°.THE ABOVE TABLE INDICATES THE LANDING GEARLRUs THAT CAN BE INSTALLED FOR EACHAIRCRAFT 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 withindividual aircraft MSN and forthe interchangeabilities/mixabilities of LRUs.END OF SUB-PART 1-0R

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

# Sub-part 1-1 ILLUSTRATIONS

Pin (Hinge arm/Barrel)

Upper torque link pin and nut

Torque link medium pin and nut

Lower torque link pin and nut Cross bars Multiple link

Pin (Drag link/Barrel/

Brace strut) Barrel

Drag link Pin (Hinge arm/

Drag link) Hinge arm

Torque links

(Upper & Lower)

Brake torque arm pin (x2)

Bogie beam pivot

pin and nut

Bogie beam Wheel axle (x2) Brace strut upper arm

Brace strut middle pin Lock link

lower arm Lock link upper

pin

Lock link

upper arm

Pin (Drag link/

Barrel) Brace strut

lower arm Lock link pin Lock link

middle pin Multiple link pin Cross bar pin (x2)

Brake torque arm (x4)



# MAIN LANDING GEAR - FIG. 01

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

# MAIN LANDING GEAR - FIG. 02 Gear support rib Aft pintle pin Gear support rib Fwd pick up

Ball (Fwd pintle bearing)

Half ball housing

(Fwd pintle bearing)

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

Barrel Attaching fitting Attaching fitting pin (x2)

S/A

Connecting rod S/A

connecting rod Pin (Connecting

rod/Upper rod)

S/A

upper rod Barrel



# MAIN LANDING GEAR - FIG. 03

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

S/A Upper rod

S/A Sliding rod

End fitting

Brake torque arms

Bogie beam pivot pin and nut (*) Lower torque link pin and nut

Brake torque arms Brake torque arm pin (x2)



# MAIN LANDING GEAR - FIG. 04

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

Multiple link Pin (Multiple link/

Frame 50)

Multiple link pin Pin (Multiple link/

Frame 50) (*)

Multiple link



# MAIN LANDING GEAR - FIG. 05

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

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. 06

# A300 AIRWORTHINESS LIMITATIONS SECTION

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

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

Bottom End fitting End fitting pin and nut

(x6) PRE MOD 1257/S7730 and PRE SB A300-32-383

(x4) POST MOD 1257/S7730 or POST SB A300-32-383

Sliding rod

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



# NOSE LANDING GEAR - FIG. 07

# A300 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-1 PAGE: 8

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

Upper cam dowel (x12)

Upper cam Lower cam

Restrictor

Lower cam dowel (x8) Upper rod



# NOSE LANDING GEAR - FIG. 08

# A300 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-1 PAGE: 9

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

# NOSE LANDING GEAR - FIG. 09 Locking cylinder End fitting pin

Locking piston Lock claw

Cylinder Locking sleeve

Pintle pin End fitting

Rod Nut (Cylinder/Locking cylinder)

# A300 AIRWORTHINESS LIMITATIONS SECTION

ISSUE: SEP 05/13 ALS PART 1-1 PAGE: 10

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

Link (Fwd cross bar

fitting/Gear support rib) Aft cross bar fitting Fwd pick up

Fwd cross bar fitting

Gear support rib



# WING STRUCTURE - FIG. 10

END OF SUB-PART 1-1A300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*) LIFE LIMITS APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG Cal. B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 05)BARREL ASSEMBLY (FIG. 01 & 03)R (1) This PNR is common to upper and lower torque link pins.Lower torque link pin is included in the Shock Absorber assembly.BarrelC58954-3 N/A 63300 N/A X XC58954-5 N/A 63300 N/A X X XC58954-9 N/A 63300 N/A X X XC58954-11 N/A 63300 N/A X X XC58954-13 N/A 63300 N/A X X XC58954-17 N/A 63300 N/A X X XC58954-19 N/A 63300 N/A X X XC58954-21 N/A 63300 N/A X X XC65380-1 N/A 63300 N/A X XC65380-3 N/A 63300 N/A X X XC65380-5 N/A 63300 N/A X X X XC65380-7 N/A 63300 N/A X X X XC65380-9 N/A 63300 N/A X X X XC65380-11 N/A 63300 N/A X X X XC65380-13 N/A 63300 N/A X X X XC65380-15 N/A 63300 N/A X X X XC65380-17 N/A 63300 N/A X X X XUpper torque link pin C65546 (1) N/A 16000 N/A X X XNC65546-5 (1) N/A 16000 N/A X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG Cal. B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Torque link mediumpinC66192 N/A 50000 N/A X X X XDrag link C58957-3 N/A 20000 N/A X X X XDC58957-5 N/A 20000 N/A X X X XS/A connecting rod C65389 N/A 12000 N/AXC65389-1 N/A 58300 N/A X X XC65389-2 N/A 58300 N/A X X X XC65389-3 N/A 58300 N/A X X X XC65825 N/A 12000 N/A X X XC65825-1 N/A 12000 N/A X X XC65825-3 N/A 58300 N/A X X X XC65825-4 N/A 12000 N/A X X XC65825-5 N/A 12000 N/A X X XSHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04)R (1) This PNR is common to upper and lower torque link pins.Upper torque link pin is included in the Barrel assembly.S/A Upper rodC65388 N/A 58300 N/AX X X XC65826 N/A 58300 N/A X X X XD60500 N/A 58300 N/A X X X XS/A Sliding rodC58958-3 N/A 35500 N/A X X XC65384-5N/A 53300 N/A X XN/A 76600 N/A X XC65384-7N/A 53300 N/A X XN/A 76600 N/A X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG Cal. B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203End fittingC61643-2 N/A 6600 N/A X X X XC61643-4 N/A 13000 N/A X X X X XC61643-5 N/A 13000 N/A X X X X XLower torque link pin C65546 (1) N/A 16000 N/A X X XNDC65546-5 (1) N/A 16000 N/A X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG Cal. B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RATA 32-20-00 NOSE LANDING GEAR (FIG. 06 to 09)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 partshaving 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 into service 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 X X X X X X XRBARREL ASSEMBLY (FIG. 06)(1) Limitation applicable to WV01 & WV03 only.BarrelC59049-1 N/A 64400 N/A X X X (1)C59049-2N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-3 N/A 64400 N/A X X (1)C59049-4N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-15 N/A 64400 N/A X X (1)C59049-16 N/A 64400 N/A X X (1)C59049-20N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-25N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-26N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-27N/A 50000 N/A X X X X.../...N/A 64400 N/A X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG Cal. B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203BarrelC59049-30 N/A 64400 N/A X X (1)C59049-31 N/A 64400 N/A X X (1)C59049-40N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-41N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-42N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-45N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-46N/A 50000 N/A X X X XN/A 64400 N/A X XC59049-47N/A 50000 N/A X X X XN/A 64400 N/A X XD56525N/A 50000 N/A X X X XN/A 64400 N/A X XD56525-1N/A 50000 N/A X X X XN/A 64400 N/A X XD56525-10N/A 50000 N/A X X X XN/A 64400 N/A X XD56525-11N/A 50000 N/A X X X XN/A 64400 N/A X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG Cal. B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Turning tube C59050 N/A 24000 N/A X X X (1)C59050-2 N/A 24000 N/A X X (1) X X X XC59050-3 N/A 24000 N/A X X (1)C59050-4 N/A 24000 N/A X X X X X XC59050-20 N/A 24000 N/A X X X X X XNC59050-28 N/A 24000 N/A X X (1) X X X XRSHOCK ABSORBER ASSEMBLY (FIG. 07 & 08)(1) - For the first accomplishment, replacethe 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 XEND OF SUB-PART 1-2A300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 05)R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.Aft pintle pin (1)A32140032200xx N/A 76600X X XA32140056200xx N/A 76600 X X XA32140056202xx N/A 76600 X X XA32140056204xx N/A 76600 X X XA32140057200xx N/A 76600 X X XA32140057202xx N/A 76600 X X XA32140057204xx N/A 76600 X X XA32140062000xx N/A 76600 X X XA32140062002xx N/A 76600 X X XA32140063000xx N/A 76600 X X XA32140063002xx N/A 76600 X X XHalf ball housing (Fwdpintle bearing) (1)A32140036200xx N/A 76600 X X XA32140036202xxN/A76600XXXA32140036204xx N/A 76600 X X XA32140036206xx N/A 76600 X X XA32140042200xx N/A 76600 X X XA32140042202xx N/A 76600 X X XA32140068002xx N/A 76600 X X XA32140068004xx N/A 76600 X X XA32140069002xx N/A 76600 X X X.../... A32140069004xx N/A 76600 X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Half ball housing (Fwdpintle bearing) (1)A32140076002xx N/A 76600 X X XA32140076004xxN/A76600XXXA32140077002xx N/A 76600 X X XA32140077004xx N/A 76600 X X XBall (Fwd pintle bearing)(1)A32140012202xx N/A 76600 X X XA32140043202xx N/A 76600 X X XA32140074200xx N/A 76600 X X XA32140075200xx N/A 76600 X X XPin (Multiple link/Frame50) (1)A53833451200xx N/A 76600 X X XN A53833451204xxN/A76600XXXA53833451206xx N/A 76600 X X XNA53833451208xx N/A 76600 X X XNA53833480200xx N/A 76600 X X XNA53833480202xx N/A 76600 X X XNA53833490200xx N/A 76600 X X XA53834451200xx N/A 76600 X X XA53834451202xx N/A 76600 X X XBARREL ASSEMBLY (FIG. 01 & 03)RRR(1) 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 providedthe 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.(2) Limitation applicable to WV01 & WV03 only.R (3) This PNR is common to upper and lower torque link pins. Lowertorque link pin is included in the Shock Absorber assembly.RD(4) This PNR is common to upper and lower torque link pin nuts. Lower torque link pin nut is included in the Shock Absorber assembly.Cage C66208N/A76600XXXXA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Eye fittingC58956-3 N/A 76600X X X XC58956-5 N/A 76600 X X X XC58956-7 N/A 76600 X X X XC58956-13 N/A 76600X X X XC65382-1 N/A 76600 X X XC65382-3 N/A 76600 X X X XC65382-5 N/A 76600 X X X XD64926 N/A 76600 X X X XPin (Hinge arm/Barrel) C65543-1 N/A 76600 X X X XC65543-3 N/A 76600 X X X XC65543-21 N/A 76600 X X X XC66441-1 N/A 76600 X X X XC66441-3 N/A 76600 X X X XC66441-21 N/A 76600 X X X XBarrelD56520-1 N/A 76600 XX X XD56520-4 N/A 76600 XX X XD64927 N/A 76600 XX X XD64927-10 N/A 76600 XX X XUpper torque link pin C65546-1 (3) N/A 76600 X X X XC65546-2 (3) N/A 76600 X X X XNC65546-10 (3) N/A 76600 X X X XC65546-20 (3) N/A 76600 X X X XNC65546-25 (3) N/A 76600 X X X XC66191-1 (3) N/A 76600 X X X X.../...C66191-2 (3) N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203N Upper torque link pin C66191-10 (3) N/A 76600X X XXC66191-20 (3) N/A 76600 X X X XNC66191-25 (3) N/A 76600 X X X XD56729 (3) N/A 76600 X X X XUpper torque link pin nut 00-200-402 (4) N/A (1)X XSL40089 (4) N/A (1) X X X XSL40089P (4) N/A (1) X X X XSL40123 (4) N/A (1) X X X XSL40123P (4) N/A (1) X X X XTorque link (Upper &Lower)C58960-3 N/A 76600 X X X XC58960-5N/A76600XXXXC65386-1 N/A 76600 XC65386-3 N/A 76600 X X X XC65386-5 N/A 76600 X X X XC65386-7 N/A 76600 X X X XD56521-1 N/A 76600 X X X XTorque link medium pin C65542 N/A 76600 X X X XNC65542-5 N/A 76600 X X X XC65542-1 N/A 76600 X X X XC65542-20 N/A 76600 X X X XC66192-1 N/A 76600 X X X XC66192-20 N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Torque link medium pinnut00-200-358 N/A (1) X X X XSL40114PN/A(1)XXXXSL40132 N/A (1) X X X XSL40132P N/A (1) X X X XPin (Drag link/Barrel) C62017-1 N/A 76600 X X X XC62017-2 N/A 76600 X X X XC62017-3 N/A 76600 X X X XC62017-20 N/A 76600 X X X XNC62017-25 N/A 76600 X X X XNC62017-30 N/A 76600 X X X XC66444 N/A 76600 X XC66444-1 N/A 76600 X X X XNC66444-5 N/A 76600 X XNC66444-10 N/A 76600 X X X XC66444-20 N/A 76600 X X X XDrag linkC58957-9 N/A 76600 X X XC58957-11 N/A 76600 X X X XC58957-13 N/A 76600 X X X XC65383-3 N/A 76600 X X X XC65383-5 N/A 76600 X X X XC65383-13 N/A 76600 X X X XPin (Drag link/Barrel/Brace strut)C65549 N/A 76600 X X X XC65549-1N/A76600XXXXNC65549-10 N/A 76600 X X X X.../...C65549-20 N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Pin (Drag link/Barrel/Brace strut)C66443-1 N/A 76600 X X X XN C66443-10N/A76600XXXXC66443-20 N/A 76600 X X X XPin (Hinge arm/Draglink)C65548 N/A 76600 X X X XN C65548-1N/A76600XXXXC66442 N/A 76600 X X X X X XC66442-1 N/A 76600 X X X XNC66442-5 N/A 76600 X X X X X XNC66442-10 N/A 76600 X X X XC66442-20 N/A 76600 X X X X X X XD60499 N/A 76600 X X X XHinge ArmC58955-1 N/A 76600X X (2)C58955-3 N/A 76600 X X (2)C58955-11 N/A 76600 X X (2)C58955-13 N/A 76600 X X X XC58955-15 N/A 76600 X X X XC58955-17 N/A 76600 X X X XC58955-19 N/A 76600 X X X XC65381-1 N/A 76600 X X X XC65381-3 N/A 76600 X X X XC65381-5 N/A 76600 X X X XC65381-7 N/A 76600 X X X XD57195-1 N/A 76600 X X X XD57196-1 N/A 76600 X X X XDD57739-1 N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Attaching fitting pinC62311-1 N/A 76600 X X X X X XXNC62311-10 N/A 76600 X X X X X X XC62311-20 N/A 76600 X X X X X X XNC62311-200 N/A 76600 X X X X X X XND68529 N/A 76600 X X X X X X XAttaching fitting (LH)C61639 N/A 76600 X X XC66197 N/A 76600 X X(2) XC69205 N/A 76600 X X X X X XC69205-1 N/A 76600 X X X X X XD48885 N/A 76600 X X X XD48885-1 N/A 76600 X X X XD51421 N/A 76600 X X X XD51421-1 N/A 76600 X X X XAttaching fitting (RH)C61640 N/A 76600 X X XC66198 N/A 76600 X X(2) XC69206 N/A 76600 X X X X X XC69206-1 N/A 76600 X X X X X XD48886 N/A 76600 X X X XD48886-1 N/A 76600 X X X XD51422 N/A 76600 X X X XD51422-1 N/A 76600 X X X XPin (Connecting rod/Upper rod)C65815 N/A 76600 X X X XC65815-1N/A76600XXXXNC65815-5 N/A 76600 X X X XN .../...C65815-10 N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Pin (Connecting rod/Upper rod)C65815-20 N/A 76600 X X X XN C65815-200N/A76600XXXXC66472 N/A 76600 X X X XC66472-1 N/A 76600 X X X XNC66472-5 N/A 76600 X X X XNC66472-10 N/A 76600 X X X XC66472-20 N/A 76600 X X X XNC66472-200 N/A 76600 X X X XND68528 N/A 76600 X X X XND68676 N/A 76600 X X X XS/A connecting rodC58963-1 N/A 76600X X XSHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04)(1) Limitation applicable to WV 01 & WV03 only.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 providedthe 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.(3) Limitation applicable to WV01, WV02 & WV03 only.R (4) PNR CRA50551 applies to nuts used for repaired bogie beam pivot pins.R (5) This PNR is common to upper and lower torque link pins. Upper torque link pin is included in the Barrel assembly.R (6) This PNR is common to upper and lower torque link pin nuts. Upper torque link pin nut is included in the Barrel assembly.S/A Upper rodC58962-1 N/A 76600X X (1)C65497 N/A 76600 X X X (1)S/A Sliding rodC58958-5 N/A 76600 X X XC58958-11 N/A 76600 X X XC58958-13 N/A 76600 X X X X.../...C65384-11 N/A 76600 XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203S/A Sliding rodC65384-13 N/A 76600X XX XC65384-21 N/A 76600 X XX XD64922 N/A 76600 X XX XEnd fitting C61643-10 N/A 76600 X X X X X X XC61643-11 N/A 76600 X X X X X X XLower torque link pin C65546-1 (5) N/A 76600 X X X XC65546-2 (5) N/A 76600 X X X XNC65546-10 (5) N/A 76600 X X X XC65546-20 (5) N/A 76600 X X X XNC65546-25 (5) N/A 76600 X X X XC66191-1 (5) N/A 76600 X X X XC66191-2 (5) N/A 76600 X X X XNC66191-10 (5) N/A 76600 X X X XC66191-20 (5) N/A 76600 X X X XNC66191-25 (5) N/A 76600 X X X XD56729 (5) N/A 76600 X X X XLower torque link pin nut 00-200-402 (6) N/A (2)X XSL40089 (6) N/A (2) XX XXSL40089P (6) N/A (2) XX XXSL40123 (6) N/A (2)X X X XSL40123P (6) N/A (2)X X X XBrake torque arm pin C65544 N/A 76600 X X XNC65544-1 N/A 76600 X X XC65544-20 N/A 76600 X X X.../...C66196 N/A 76600 X X X X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Brake torque arm pin C66196-20 N/A 76600 X X X X X XXD55709 N/A 76600 X X X XND55709-1 N/A 76600 X X X XD60501 N/A 76600 X X X XBrake torque armC61648-1 N/A 76600 X X XC61648-2 N/A 76600 X X XC66434 N/A 76600 X X X XX XC66434-1 N/A 76600 XX XXC66434-30 N/A 76600 XX XXD51989 N/A 76600 XX XXD60502 N/A 76600 XX XXBogie beam pivot pin C65545 N/A 76600 X X XC65545-1 N/A 76600 X X XC65545-2 N/A 76600 X (3) X XC65545-3 N/A 76600 X X XC65545-4 N/A 76600 X X XC65545-5 N/A 76600 X X X XC65545-6 N/A 76600 X X XC65545-20 N/A 76600 X X X XC66194 N/A 76600 XXC66194-1 N/A 76600 XXC66194-2 N/A 76600 XXX XC66194-3 N/A 76600 XXXC66194-4 N/A 76600 XXX.../...C66194-5 N/A 76600 XXX XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Bogie beam pivot pin C66194-20 N/A 76600XXX XD60503 N/A 76600 XXX XD64921 N/A 76600 XXX XBogie beam pivot pin nut CRA50551 (4) N/A 76600 X X X X X XXSL40054 N/A (2) X X X X X X XSL40054P N/A (2) X X X X X X XBOGIE BEAM ASSEMBLY (FIG. 01)Bogie beamC58959-3 N/A 76600 X X XC65385-1 N/A 76600 X X XC65385-3 N/A 76600 X X XC65385-5 N/A 76600 X X X XC65385-7 N/A 76600 X X X XC65385-9 N/A 76600 X X X XC65385-13 N/A 76600 X X X XC65385-15 N/A 76600 X X X XD51991-1 N/A 76600 X X X XD51991-3 N/A 76600 X X X XD56731-1 N/A 76600 X X X XD60504-1 N/A 76600 X X X XD60504-3 N/A 76600 X X X XD64920 N/A 76600 X X X XWheel axleC58961-3 N/A 76600 X X XC58961-5 N/A 76600 X X XC58961-11 N/A 76600 X X.../...C65387-1 N/A 76600 X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Wheel axleC65387-3 N/A 76600 X X X XC65387-5 N/A 76600 X X X XC65387-7 N/A 76600 X X X XC65387-11 N/A 76600 X X X XC65387-31 N/A 76600 X X X XD48520-1 N/A 76600 X X X XD48520-3 N/A 76600 X X X XD48520-5 N/A 76600 X X X XD48520-11 N/A 76600 X X X XD51992-1 N/A 76600 X X X XD51992-11 N/A 76600 X X X XD56625-1 N/A 76600 X X X XD60505-1 N/A 76600 X X X XLINKAGE ASSEMBLY (FIG. 01 & 05)Cross bar pinC62319-1 N/A 76600 X XC62319-2 N/A 76600 X XC62319-20 N/A 76600 X XNC62319-25 N/A 76600 X XC67676 N/A 76600 X X X XNC67676-1 N/A 76600 X X X XC67676-20 N/A 76600 X X X XCross barC61160-1 N/A 76600 X XC66792 N/A 76600 X X X XC66792-1 N/A 76600 X X X XD60522 N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Multiple link pinC62318-1 N/A 76600X XNC62318-10 N/A 76600 X XC62318-20 N/A 76600 X XC67131 N/A 76600 X X X XNC67131-1 N/A 76600 X X X XC67131-20 N/A 76600 X X X XMultiple linkC61942-1 N/A 76600 X XC66503 N/A 76600 X XC66503-1 N/A 76600 X X X XC66503-2 N/A 76600 X X X XNDC66503-5 N/A 76600 X XBRACE ASSEMBLY (FIG. 01)BRACE STRUT (FIG. 01)(1) Limitation applicable to WV06 only.Brace strut upper arm C59061-1 N/A 76600 X X XC66504 N/A 76600 X X X (1)C66504-1 N/A 76600 X X X (1)C66504-2 N/A 76600 X X X XBrace strut middle pin C62313-1 N/A 76600 X X XC68376 N/A 76600 X X XC68376-1 N/A 76600 X X XNC68376-2 N/A 76600 X X XC68376-20 N/A 76600 X X XC68400 N/A 76600 X X X X.../...C68400-1 N/A 76600 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203N Brace strut middle pin C68400-2 N/A 76600X X XXC68400-20 N/A 76600 X X X XND68670 N/A 76600 X X X XBrace strut lower arm C59062-1 N/A 76600 X X XC65606 N/A 76600 X X X (1)C65606-1 N/A 76600 X X X (1)C65606-2 N/A 76600 X X X XC65606-3 N/A 76600 X X X XC65606-6 N/A 76600 X X X XNC65606-10 N/A 76600 X X X XLock link pinC62314 N/A 76600 X X X X X XXC62314-20 N/A 76600X X X X X X XC62314-30 N/A 76600X X X X X X XRLOCK LINK (FIG. 01)(1) Limitation applicable to WV06 only.NNN(2) The lock link middle pin must be replacedby a new one every time it is removed from the lock link lower arm. When the pinis temporarily removed and reinstalledfor the purpose of performing maintenance outside a workshop, noreplacement is required provided the pin’s removal and reinstallation are performed on thesame lock link lower arm and neither the lower arm nor the pin accumulates time in service during the period between the removal and reinstallation.Lock link lower armC61483-1 N/A 76600X X XC65607 N/A 76600X X(1)C69426 N/A 76600X X X XC69443 N/A 76600X X XC69443-1 N/A 76600X X XR Lock link middle pinC61485-1 N/A (2) X X X X X XXRC61485-20 N/A (2) X X X X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Lock link upper armC61484-2 N/A 76600 X X XC65608 N/A 76600 X X X XLock link upper pinC62315-10 N/A 76600 X X X X X XXC62315-20 N/A 76600 X X X X X X XC62315-30 N/A 76600 X X X X X X XRATA 32-20-00 NOSE LANDING GEAR (FIG. 06 to 09)R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.Pintle pin (1) A32210079200xx N/A 65700 X X X X X X XNA32210082200xx N/A 65700 X X X X X X XRTELESCOPIC STRUT ASSEMBLY (FIG. 09)(1) Limitation applicable to WV01 & WV03 only.End fitting pinC62911-1 N/A 65700X X XC62911-2 N/A 65700 X X X X X XC62911-15 N/A 65700 X X XNC62911-18 N/A 65700 X 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 XEnd fittingC61390-1 N/A 65700 X X XC61390-2 N/A 65700 X X X X X XD55962 N/A 65700 X X X XCylinderC61371 N/A 65700 X X X X X X XD55954 N/A 65700 X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Nut (Cylinder/Lockingcylinder)C61375 N/A 65700 X X X X X X XNC61375-1 N/A 65700 X X X X X X XD55955 N/A 65700 X X X XND55955-1 N/A 65700 X X X XND68538 N/A 65700 X X X XLocking cylinder C61373-1 N/A 65700 X X X X 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 X X X X XC61373-40 N/A 65700 X X X X X XLocking sleeve C61389 N/A 65700 X X X X X X XC61389-1 N/A 65700 X X X XLock claw C61391 N/A 65700 X X X X X X XD55952 N/A 65700 X X X XLocking piston C61378-1 N/A 65700 X X X X X XC61378-3 N/A 65700 X X (1)C61378-5 N/A 65700 X X (1)NC61378-10 N/A 65700 X X X X X XC68483 N/A 65700 X X X X 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 XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RodC61372-1 N/A 65700 X X XC61372-2 N/A 65700 X X X X X XC61372-3 N/A 65700 X X XC61372-4 N/A 65700 X X X XD55953-1 N/A 65700 X X X XD55953-2 N/A 65700 X X X XD57050 N/A 65700 X X X X X XD57050-1 N/A 65700 X X X XRBARREL ASSEMBLY (FIG. 06)(1) Limitation applicable to WV01 & WV03 only.(2) Part must be replaced by a new one every time it is removed from the barrel.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 providedthe 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/Telescopicstrut)C62231-1 N/A 65700 X X X (1)C62231-2 N/A 65700 X X X X X XNC62231-10 N/A 65700 X X X (1)C62231-20 N/A 65700 X X X X X XNC62231-25 N/A 65700 X X X X X XD56530 N/A 65700XX X XXClevisC62002-1 N/A 65700 X X X (1)C62002-2 N/A 65700 X X X X X X XD56527 N/A 65700 X X X XLower pin (Link/Clevis) C62268-1 N/A 65700 X X X (1)C62268-2 N/A 65700 X X X X X XN .../...C62268-15 N/A 65700 X X X (1)A300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Lower pin (Link/Clevis) C62268-20 N/A 65700 X X X X X XNC62268-25 N/A 65700 X X X X X XNC62268-200 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 X XNC62230-10 N/A 65700 X X X X X X XD56526 N/A 65700 X X X XND56526-1 N/A 65700 X X X XND68539 N/A 65700 X X X X X X XND68540 N/A 65700 X X X XUpper pin (Link/Barrel) C62267-1 N/A 65700 X X X (1)C62267-2 N/A 65700 X X X X X XNC62267-10 N/A 65700 X X X (1)C62267-20 N/A 65700 X X X X X XNC62267-25 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) C62229-1 N/A 65700 X X X X X X XNC62229-10 N/A 65700 X X X X X X XC62229-20 N/A 65700 X X X X X XD56528 N/A 65700 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 X.../...D59633 N/A 65700 X X X X X XA300 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 sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203BarrelD59633-1 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) C62228-1 N/A 65700 X X X X X X XC62228-20 N/A 65700 X X X X X XEnd fitting pin nutD68062 N/A (2) X X X X X XXMS17825-6 N/A (2) X X X X X X XEnd fitting pinAN6-17N/A (2)X X X X X XD61183 N/A (2)X X X X X XD68063 N/A (2)X X X X X XNAS1306-22D N/A (2)X X X X X X XEnd fitting C62032 N/A 65700 X X X X X X XC62032-1 N/A 65700 X X X X X XNC62032-2 N/A 65700 X X X X X X XNC62032-10 N/A 65700 X X X X X XRD61184 N/A 65700 X X X X X XND61184-1 N/A 65700 X X X X X XRD68076 N/A 65700 X X X X X XND68695 N/A 65700 X X X X X XRackC61453 N/A 65700 X X X (1)C61453-1 N/A 65700 X X X X X XN .../...C61453-15 N/A 65700 X X X X X XA300 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 system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RackC61453-20 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 XTurning tube 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)C62223-1 N/A 65700 X X X X X X XNC62223-15 N/A 65700 X X X X X X XC62223-20 N/A 65700 X X X X X XTorque link (Upper &Lower)C59562-2 N/A 65700 X X X X X X XC59562-3N/A65700XXXXC59562-4 N/A 65700 X X X X X XNC59562-20 N/A 65700 X X X X X X XTorque link medium pin C62041-1 N/A 65700 X X X X X XXNC62041-15 N/A 65700 X X X X X X XC62041-20 N/A 65700 X X X X X XNC62041-200 N/A 65700 X X X X X XD53431 N/A 65700 X X X X X XD53431-20 N/A 65700 X X X X X XTorque link medium pinnutSL40110P N/A (3) X X X X X X XA300 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 system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RSHOCK ABSORBER ASSEMBLY (FIG. 07 & 08)(1) Limitation applicable to WV01 & WV03 only.RRR(2) The wheel axle nut must be replaced by a new one every time it is removed from the wheel axle. When the nut is temporarilyremoved and reinstalled for thepurpose of performing maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallationare performed on the samewheel axle and neither the wheel axle northe nut accumulates time in service during the period between the removal and reinstallation.(3) Limitation applicable to WV 06 only.(4) Part must be replaced by a new one every time it is removed from the sliding rod.(5) Limitation applicable to WV 00 only.(6) Part must be replaced by a new one every time it is removed from the upper rod.Wheel axleC59053-2 N/A 65700X X (1)C59053-4 N/A 65700 X X X X X XC59053-21 N/A 65700 X X X X X XWheel axle nutC62879 N/A (2) X X X X X XXNC62879-1 N/A (2) X X X X X X XND68537 N/A (2) X X X X X X XSliding rodC59051-1 N/A 65700 X X X (1)X (3) X (3)C59051-3 N/A 65700 X X X X X XC59051-5 N/A 65700 X X (1)C59051-21 N/A 65700 X X X X X XUpper cam dowelC62270 N/A (4) X X X X X XXUpper cam C62034-1 N/A 65700 X X X X X X XNC62034-10 N/A 65700 X X X X X X XND68534 N/A 65700 X X X X X X XLower cam C62035 N/A 65700 X X X X X X XNC62035-1 N/A 65700 X X X X X X XND68532 N/A 65700 X X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 22EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203Restrictor C62036 N/A 65700 X X(3) X(3)C62036-1 N/A 65700 X X (1)C62036-2 N/A 65700 X X (5)NC62036-10 N/A 65700 X X (1)C67863 N/A 65700 X X (1)C67863-1 N/A 65700 X X (1) X X X XC67863-2 N/A 65700 X X X X X XC67863-3 N/A 65700 X X (1)C67863-4 N/A 65700 X X X X X XNC67863-5 N/A 65700 X X (1)NC67863-10 N/A 65700 X X (1) X X X XNC67863-20 N/A 65700 X X X X X XNC67863-30 N/A 65700 X X (1)NC67863-40 N/A 65700 X X X X X XND68536 N/A 65700 X X X X X XLower cam dowelC62866 N/A (6) X X X X X XXUpper rodC59052-1 N/A 65700X X (1)C59052-2 N/A 65700 X X X X X XNut (S/A/Barrel)C64040 N/A (6) XX (3) X (3)C64040-1 N/A (6) X X X X X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 23EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RATA 57-00-00 WING STRUCTURE (FIG. 10 & 11)(1) This item is not transferable from an aircraft toan another: Traceability at aircraft level is authorized.R (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.Gear support rib (LH)(1) (2)A57240035220xx N/A 60000 003A57240810214xx N/A 57000 X X XA57241955216xx N/A 60000 X X XA57241955218xx N/A 60000 244Gear support rib (RH)(1) (2)A57240035221xx N/A 60000 003A57240810215xxN/A 57000 X X XN/A 60000 244A57241955217xx N/A 60000 X X XFwd pick up (LH) (1) (2) A57240044002xx N/A 60000 003A57241947002xx N/A 60000 X X XA57241959002xx N/A 57000 X X XA57242390000xxN/A 57000 X X XN/A 60000 X X XA57242391000xx N/A 57000 X X XFwd pick up (RH) (1) (2) A57240044003xx N/A 60000 003A57241947003xx N/A 60000 X X XA57241959003xx N/A 57000X X XA57242390001xxN/A 57000X X XN/A 60000X X XA57242391001xx N/A 57000X X XA300 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 24EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.Nomenclature Part Number FH LDG B1B2-1AB2-1CB2K-3CB2-20xB2-320B4-2CB4-1xxB4-2xxC4-203F4-203RAft cross bar fitting(LH) (1) (2)A57240042206xx N/A 60000 003A57240806200xx N/A 57000 X X XA57241946200xx N/A 60000 X X XRAft cross bar fitting(RH) (1) (2)A57240042207xx N/A 60000 003A57240806201xx N/A 57000 X X XA57241946201xx N/A 60000 X X XRFwd cross bar fitting(LH) (1) (2)A57240040206xx N/A 60000 003A57240808200xx N/A 57000 X X XA57241948200xx N/A 60000 X X XRFwd cross bar fitting(RH) (1) (2)A57240040207xx N/A 60000 003A57240808201xx N/A 57000 X X XA57241948201xx N/A 60000 X X XRLink (Fwd cross barfitting/Gear support rib)(1) (2)A57240406202xx N/A 60000 X X XA57240813200xx N/A 57000 X X XA57242386200xx N/A 57000 X X XEND OF SUB-PART 1-3

# A300 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

- A300 ALS Part 1 revision 00:

The airworthiness limitations previously listed in the A300 AMM Chapter 05 were transferred

into the initial version of the ALS Part 1. New Safe Life Airworthiness Limitation Items were

introduced (wing and landing gear/wing interface components).

- A300 ALS Part 1 revision 01:

This revision is dedicated to delete the system-related airworthiness li mitations from the ALS

Part 1. The Weight Variant 20 is introduced for the A300 B4-103 model. The WV 14, 20, 21 and

22 are introduced for the A300 B4-203 model. This revision includes the variations

0AVLG120005/C0S and 0AVLG120006/C0S.

2- SUMMARY OF CHANGES:

The following summarizes the changes with respect to the previous issue of the A300 ALS Part

1 (revision 00).

New items:

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY:

* A300 B4-100 series:

Introduction of the WV20 (MOD 13468) for A300 B4-103 model.

* A300 B4-200 series:

Introduction of the WV14 (MOD 6193) for A300 B4-203 model.

Introduction of the WV20 (MOD 13362) for A300 B4-203 model.

Introduction of the WV21 (MOD 13469) for A300 B4-203 model.

Introduction of the WV22 (MOD 13470) for A300 B4-203 model.

SUB-PART 1-2:

None.

SUB-PART 1-3:

None.

Amendments:

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY:

None.

# A300 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS

HISTORY FILE

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 2/6

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

# SUB-PART 1-2:

* Main landing gear:

Figure number amended.

* Main landing gear, Barrel assembly:

Note (1) amended.

Upper torque link pin PNR C65546-5: PNR added (MOD 13453).

* Main landing gear, Shock absorber assembly:

Note (1) amended.

Lower torque link pin PNR C65546-5: PNR added (MOD 13452).

* Nose landing gear:

Figures number amended.

Note (1) amended.

* Nose landing gear, Barrel assembly:

Figure number amended.

Turning tube PNR C59050-28: PNR added (MOD 13456).

* Nose landing gear, Shock absorber assembly:

Figure number amended.

Bottom PNR D68531: PNR added (MOD 13457).

* Wing structure:

Figures number amended.

Note (1) amended.

SUB-PART 1-3:

* Main landing gear:

Figure number amended.

Note (1) amended.

Pin (Multiple link/Frame 50):

- PNR A53833451204xx and PNR A53833451208xx: PNR added.

- PNR A53833480200xx, PNR A53833480202xx and PNR A53833490200xx: PNR

added (MOD 13384).

* Main landing gear, Barrel assembly:

Notes (1), (3) and (4) amended.

Upper torque link pin PNR C65546-10, PNR C65546-25, PNR C66191-10 and PNR

C66191-25: PNR added (MOD 13453).

Torque link medium pin PNR C65542-5: PNR added (MOD 13453).

Pin (Drag link/Barrel) PNR C62017-25, PNR C62017-30, PNR C66444-5 and PNR

C66444-10: PNR added (MOD 13453).

# A300 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. 

# Pin (Drag link/Barrel/Brace strut) PNR C65549-10 and PNR C66443-10: PNR added

(MOD 13453).

Pin (Hinge arm/Drag link) PNR C65548-1, PNR C66442-5 and PNR C66442-10: PNR

added (MOD 13453).

Attaching fitting pin PNR C62311-10, PNR C62311-200 and PNR D68529: PNR added

(MOD 13453).

Pin (Connecting rod/Upper rod) PNR C65815-5, PNR C65815-10, PNR C65815-200,

PNR C66472-5, PNR C66472-10, PNR C66472-200, PNR D68528 and PNR D68676:

PNR added (MOD 13453).

* Main landing gear, Shock absorber assembly:

Notes (2), (4), (5) and (6) amended.

Lower torque link pin PNR C65546-10, PNR C65546-25, PNR C66191-10 and PNR

C66191-25: PNR added (MOD 13452).

Brake torque arm pin PNR C65544-1 and PNR D55709-1: PNR added (MOD 13452).

* Main landing gear, Linkage assembly:

Cross bar pin PNR C62319-25 and PNR C67676-1: PNR added (MOD 13454).

Multiple link pin PNR C62318-10 and PNR C67131-1: PNR added (MOD 13454).

Multiple link PNR C66503-5: PNR added (MOD 13454).

* Main landing gear, Brace assembly, Brace strut:

Brace strut middle pin PNR C68376-2, PNR C68400-2 and PNR D68670: PNR added

(MOD 13451).

Brace strut lower arm PNR C65606-10: PNR added (MOD 13451).

* Main landing gear, Brace assembly, Lock link:

LRU title amended.

Note (2) added.

Lock link middle pin: nomenclature amended.

Lock link middle pin PNR C61485-1 and PNR C61485-20: Limitation amended, note (2)

assigned.

* Nose landing gear:

Figures number amended.

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).

# A300 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

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. 

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

Locking piston PNR 61378-10: PNR added (MOD 13455).

* Nose landing gear, Barrel assembly:

Figure number amended.

Note (3) amended.

Pin (Clevis/Telescopic strut) PNR C622 31-10 and PNR C62231-25: PNR added (MOD

13456).

Lower pin (Link/Clevis) PNR C62268-15, PNR C62268-25, 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 C62267-10, PNR C62267-25, PNR C62267-200 and PNR

D68544: PNR added (MOD 13456).

Pin (Clevis/Barrel) PNR C622 29-10: PNR added (MOD 13456).

End fitting:

- PNR D61184 and PNR D68076: PNR sequence corrected.

- 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 pin (Upper & Lower) PNR C62223-15: PNR added (MOD 13456).

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

Torque link medium pin PNR C62041-15 and PNR C62041-200: PNR added (MOD

13456).

* Nose landing gear, Shock absorber assembly:

Figures number amended.

Note (2) amended.

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

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

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

Restrictor PNR C62036-10, PNR C67863-5, PNR C67863-10, PNR C67863-20, PNR

C67863-30, PNR C67863-40 and PNR D68536: PNR added (MOD 13457).

* Wing structure:

Figures number amended.

Note (2) amended.

Items sequence amended.

Aft cross bar fitting: Nomenclature amended.

Fwd cross bar fitting: Nomenclature amended.

Link (Fwd cross bar fitting/Gear support rib): Nomenclature amended.

# A300 AIRWORTHINESS LIMITATIONS SECTION

ALS PART 1

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. 

# Deletions:

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY:

* Main landing gear, Retraction actuator assembly:

Titles deleted.

Top assembly PNR C22551 series, PNR C23035 series, PNR C23129 series, PNR

C23042 series, PNR C23137 series: PNR deleted.

SUB-PART 1-2:

* Main landing gear, Barrel assembly:

Stirrup PNR C66277-10: Item and PNR deleted.

Plate (Rear head end) PNR C61638-10 and PNR C61638-11: Item and PNR deleted.

* Main landing gear, Retraction actuator assembly:

Title and figure deleted.

Sliding rod PNR C69028-1, PNR C69028-4, PNR C69029-1, PNR C69029-2, PNR

C69029-3 and PNR C69029-4: Item PNR deleted.

Piston PNR C67078 and PNR C67078-1: Item and PNR deleted.

End fitting PNR C61342-4 and PNR C66510-4: Item and PNR deleted.

* Pneumatic:

Title and figure deleted.

Duct flanged PNR A21274063000xx: Item and PNR deleted.

* Wing structure:

Title and figure deleted.

Flap track beam n°2, rear attachme nt bolts PNR A57940384216xx and PNR

A57940384218xx: item and PNR deleted.

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

Title and figure deleted.

Cross beam PNR 196-0328-1, PNR 196-0328-501 and PNR 196-1300-501: Item and

PNR deleted.

SUB-PART 1-3:

* Main landing gear, Barrel assembly:

Cage PNR C62018-1, PNR C62018-2, PNR C62018-6, PNR C62018-7, PNR C62018-8

and PNR C62018-10: Item and PNR deleted.

Stirrup PNR C66277-12, PNR C66277-14 and PNR D58303-1: Item and PNR deleted.

Stirrup pin PNR C66457, PNR D48939, PNR D48939-1 and PNR D58314-1: Item and

PNR deleted.

Universal joint PNR C66279, PNR C66279-2, PNR C66279-6 and PNR D58313-1: Item

and PNR deleted.

# A300 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. 

# Plate (Upper end) PNR C61637-10, PNR C6 1637-11 and PNR C61637-12: Item and

PNR deleted.

Plate (Rear head end) PNR C61638-20: Item and PNR deleted.

Tie rod PNR C68523-3: Item and PNR deleted.

* Main landing gear, Linkage assembly:

Upper multiple link pin (Multiple link/Upper link) PNR C61505 and PNR C61505-20: Item

and PNR deleted.