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 herein is the sole property of AIRBUS SAS. No 

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

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

purposes of performing the tasks described hereunder and provided that any recipient of such 

document shall comply with the condition herein) without the express written consent of 

AIRBUS SAS. This document and its content shall not be used for any purpose other than that 

for which it is supplied. 
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. 

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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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The European Aviation Safety Agency (EASA) 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 

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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 comply 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 mandatory 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 whose Part NumbeRs (PNR) are listed in the 

table of this ROR: 

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

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

demonstrated (with or without 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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(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/installation 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 replacement 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 

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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 series 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 otherwise 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 those having a demonstrated fatigue life without 

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

For these parts, the life limitation provided (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 the life limit(s) will be transferred to sub-part 

1-2. 
A300 AIRWORTHINESS LIMITATIONS SECTION 

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

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C. Traceability and replacement 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 the stated life limitations in accordance 

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

Therefore, it is necessary to assure traceability 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 modifications and/or SB have been released between 

two scheduled revisions of the ALS Part 1. 

However, it is required to assure traceability and monitoring 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 released at the time of the MOD approval to 

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

For further guidance, Operators are requested to contact Airbus. 

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

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

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

of, but are not limited to, the following: 

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

Manufacturer Serial Number, etc...), 

- Maintenance actions carried out (Airworthiness Directives, modifications, 

repairs, inspections, etc...). 

- Life accumulation (accounting 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 and 1-3 is not required 

for consumable components, (for which 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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- 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. Service Bulletin: POST SB PNR in the ALS 

sub-part 1-3). 

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

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

limitations. Examples of means are: 

- Record keeping system, 

- Non-permanent markings, 

- Segregation (parts stored separately from those currently eligible for 

installation). 

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

appear to be airworthy. 

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

repair limits to prevent rework to appear to be airworthy. 

E. ALS Part 1 applicability 

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

The applicability of this ALS Part 1 revision is restricted to the 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 and 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. 

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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.): Airworthiness 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 aircraft touches the runway and does not 

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

3. APPLICABILITY SYSTEM 

A. General 

ALS sub-part 1-2 and 1-3 tables provide the 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 according to the aircraft model affected, e.g.: 

X stands for: All A300 models defined by the applicability of the column. 

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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’ responsibility 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 modification configuration(s). 

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

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

aircraft, in the delivery documentation (Aircraft 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 allocated 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 applicability of the column). 

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

XZX stands for: For aircraft MSN XZX only. 

excl. XXX stands for: All aircraft MSN defined by the applicability of the column, 

excluding aircraft MSN XXX. 

4. LIMITATION/REPLACEMENT TIME INDICATION 

A. General 

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In computing part’s accumulated life, calculations 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 evolutions is also to be counted from 

the 

part’s initial entry into service (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 quoted on the same line/block of lines as the 

PNR. 

C. Production/Repair concessions, ALS Variation 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 Approval 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/AMOC, 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. Occasionally, 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 can take credit of the history partially or 

completely rebuilt after application for the repair solution/AV/AMOC. 

Production concessions are provided to the initial Operator of the aircraft in the delivery 

documentation (Aircraft Inspection Report ‘Recordable concessions’). 

Note: For spare parts, restriction 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 Authority for any necessary adaptations of the 

airworthiness limitations. For example, Supplemental Type Certificates (STC), which 
A300 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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

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

associated approvals and documents indicating the necessary adaptations of 

limitations have to be transferred as well. 

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 the part is transferred to another application. In 

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

formula: 

with: 

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

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

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

Cpi = part’s airworthiness limitation in current application i. 

Note 1: When using the above formula, Tri, Caj, Cpj, Cpi 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 manufactured by Airbus, detail PNR are listed in 

the relevant Airbus engineering drawings/Component Maintenance Manual manufacturer 

(CMMm) issued by Airbus. 

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

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

vendors. 

Messier-Dowty SB will be issued to provide information on procurable 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 

R 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

R R 

7. LANDING GEAR LRUs APPLICABILITY 

A. A300 B1 model, A300 B2-100/-200/-300 series installations 

A300 B1 X A300 B2-1A X X X A300 B2-1C X X X A300 B2K-3C X X A300 B2-202 X X A300 B2-203 X X A300 B2-320 

WEIGHT VARIANT 00 00 00 01 02 

MTOW 137 137 142 137 142 MLW 122 127.5 130 130 130 MZFW 116.5 116.5 120.5 120.5 120.5 

R Top assembly PNR 

Main Landing Gear Leg 

C22997/8-1 X X X C22997/8-2 X X X C22997/8-3 X X X X X C22997/8-4 X X X X X C22997/8-5 X X X X X C22997/8-6 X X X X C22997/8-7 X X X C22997/8-8 X X X C22997/8-18 X X X X X 

 C23093/4-0 NOT AUTHORIZED  C23093/4-1 NOT AUTHORIZED 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

A300 B1 X A300 B2-1A X X X A300 B2-1C X X X A300 B2K-3C X X A300 B2-202 X X A300 B2-203 X X A300 B2-320 

WEIGHT VARIANT 00 00 00 01 02 

MTOW 137 137 142 137 142 MLW 122 127.5 130 130 130 MZFW 116.5 116.5 120.5 120.5 120.5 

R Top assembly PNR 

 C23093/4-2 NOT AUTHORIZED  C23093/4-3 NOT AUTHORIZED 

C23093/4-4 C23093/4-5 C23093/4-8 C23093/4-9 C23093/4-10 C23093/4-11 

 C23093/4-12 NOT AUTHORIZED 

C23093/4-15 C23093/4-19 C23093/4-25 C23093/4-35 

Main Landing Gear Brace Strut 

C23021/2-0 X C23021/2-1 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

A300 B1 X A300 B2-1A X X X A300 B2-1C X X X A300 B2K-3C X X A300 B2-202 X X A300 B2-203 X X A300 B2-320 

WEIGHT VARIANT 00 00 00 01 02 

MTOW 137 137 142 137 142 MLW 122 127.5 130 130 130 MZFW 116.5 116.5 120.5 120.5 120.5 

R Top assembly PNR 

C23021/2-2 X X X X C23021/2-3 X X X X C23021/2-4 X X X X X 

 C23111/2-1 NOT AUTHORIZED 

C23111/2-2 C23111/2-3 C23111/2-23 

Main Landing Gear Structural Linkage 

C23023/4-0 X X X X C23023/4-1 X X X X C23121/2-0 C23121/2-1 

D 

C23121/2-21 

Nose Landing Gear Leg 

C23042-0 X C23042-2 X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

A300 B1 X A300 B2-1A X X X A300 B2-1C X X X A300 B2K-3C X X A300 B2-202 X X A300 B2-203 X X A300 B2-320 

WEIGHT VARIANT 00 00 00 01 02 

MTOW 137 137 142 137 142 MLW 122 127.5 130 130 130 MZFW 116.5 116.5 120.5 120.5 120.5 

R Top assembly PNR 

C23042-3 X X X 

 C23137-0 NOT AUTHORIZED 

C23137-1 X X X C23137002 X X X X 

 C23137003 NOT AUTHORIZED 

C23137006 

Nose Landing Gear Telescopic Strut 

C23037-1 X X X C23037-2 X X X C23037-3 X X X X C23037-4 X X X X C23037-12 X X X C23037-13 X X X X C23037-14 X X X X C23109-0 X X X C23109-1 X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

A300 B1 X A300 B2-1A X X X A300 B2-1C X X X A300 B2K-3C X X A300 B2-202 X X A300 B2-203 X X A300 B2-320 

WEIGHT VARIANT 00 00 00 01 02 

MTOW 137 137 142 137 142 MLW 122 127.5 130 130 130 MZFW 116.5 116.5 120.5 120.5 120.5 

R Top assembly PNR 

C23109-2 C23109-11 C23109-12 C23109610 C23109710 

Weight 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 SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

© 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 GEAR LRUs THAT CAN BE INSTALL

AIRCRAFT MODEL WEIGHT VARIANT BUT IT DOES NOT: - ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL A- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES. Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service BulletMaintenance Manuals, etc...) for the applicability of LRUs compared with individual aircrathe interchangeabilities/mixabilities of LRUs. 

R 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

R B. A300 B4-100 series installations 

 A300 B4-2C X X X X X X X X X  A300 B4-102 X X X X X X X X X 

R A300 B4-103 X X X X X X X X X 

 A300 B4-120 X X X X X X X X X 

R WEIGHT VARIANT 00 01 02 03 04 05 12 13 14 R MTOW 150 153 157.5 157.5 150 153 160 150 157.5 R MLW 133 133 133 134 133 134 136 (1) 134 134 

134 (2) 

R MZFW 122 122 122 124 122 124 123 126 126 R Top assembly PNR 

Main Landing Gear Leg 

 C22997/8 series NOT AUTHORIZED 

R C23093/4-0 X X X X X X X X X R C23093/4-1 X X X X X X X X X R C23093/4-2 X X X X X X X X X R C23093/4-3 X X X X X X X X X R C23093/4-4 X X X X X X X X X R C23093/4-5 X X X X X X X X X R C23093/4-8 X X X X X X X X X R C23093/4-9 X X X X X X X X X R C23093/4-10 X X X X X X X X X R C23093/4-11 X X X X X X X X X 

 C23093/4-12 NOT AUTHORIZED 

R C23093/4-15 X X X X X X X X X R C23093/4-19 X X X X X X X X X R C23093/4-25 X X X X X X X X X R C23093/4-35 X X X X X X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

 A300 B4-2C X X X X X X X X X  A300 B4-102 X X X X X X X X X 

R A300 B4-103 X X X X X X X X X 

 A300 B4-120 X X X X X X X X X 

R WEIGHT VARIANT 00 01 02 03 04 05 12 13 14 R MTOW 150 153 157.5 157.5 150 153 160 150 157.5 R MLW 133 133 133 134 133 134 136 (1) 134 134 

134 (2) 

R MZFW 122 122 122 124 122 124 123 126 126 R Top assembly PNR 

Main Landing Gear Brace Strut 

 C23021/2 series NOT AUTHORIZED 

R C23111/2-1 X X X X X X X X X R C23111/2-2 X X X X X X X X X R C23111/2-3 X X X X X X X X X R C23111/2-23 X X X X X X X X X 

Main Landing Gear Structural Linkage 

 C23023/4 series NOT AUTHORIZED 

R C23121/2-0 X X X X X X X X X R C23121/2-1 X X X X X X X X X R D 

C23121/2-21 X X X X X X X X X 

Nose Landing Gear Leg 

 C23042 series NOT AUTHORIZED 

R C23137-0 X X X X X X X X X R C23137-1 X X X X X X X X X R C23137002 X X X X X X X X X 

 C23137003 NOT AUTHORIZED 

R C23137006 X X X X X X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

 A300 B4-2C X X X X X X X X X  A300 B4-102 X X X X X X X X X 

R A300 B4-103 X X X X X X X X X 

 A300 B4-120 X X X X X X X X X 

R WEIGHT VARIANT 00 01 02 03 04 05 12 13 14 R MTOW 150 153 157.5 157.5 150 153 160 150 157.5 R MLW 133 133 133 134 133 134 136 (1) 134 134 

134 (2) 

R MZFW 122 122 122 124 122 124 123 126 126 R Top assembly PNR 

Nose Landing Gear Telescopic Strut 

 C23037 series NOT AUTHORIZED  C23109-0 X X X X X X X X 

R C23109-1 X X X X X X X X X R C23109-2 X X X X X X X X X R C23109-11 X X X X X X X X X R C23109-12 X X X X X X X X X R C23109610 X X X X X X X X X R C23109710 X X X X X X X X X 

Weight 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 POST SB A300-34-0024 or SB A300-34-0127. 

WV03: Aircraft POST MOD 01652 and MOD 02032 or POST SB A300-34-0024 and SB A300-34-00WV04: Aircraft POST MOD 03752 or POST A300-00-0018. WV05: Aircraft POST MOD 01614 and MOD 02032 or POST SB A300-34-0020 and SB A300-34-00WV11: This WV is listed in the TCDS N°145 however the LRU table above does not list WV11, a

Aircraft. 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

© 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 GEAR LRUs THAT CAN BE INSTALLAIRCRAFT MODEL WEIGHT VARIANT BUT IT DOES NOT: - ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL A- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES. Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service BulletMaintenance Manuals, etc...) for the applicability of LRUs compared with individual aircra

the interchangeabilities/mixabilities of LRUs. 

R 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

R C. A300 B4/C4/F4-200 series installations 

R A300 B4-203 X X X X X X X X 

 A300 B4-220 X X  A300 C4-203 X X  A300 F4-203 X 

R WEIGHT VARIANT 06 07 08 10 14 16 17 18 R MTOW 165 165 157.5 157.5 157.5 147.5 147.5 165 R MLW 134 136 (1) 134 136 (1) 134 134 136 (1) 134 

134 (2) 134 (2) 134 (2) 

R MZFW 124 126 124 126 126 124 126 126 R Top assembly PNR 

Main Landing Gear Leg 

 C22997/8 series NOT AUTHORIZED  C23093/4-0 NOT AUTHORIZED  C23093/4-1 NOT AUTHORIZED  C23093/4-2 NOT AUTHORIZED  C23093/4-3 NOT AUTHORIZED  C23093/4-4 NOT AUTHORIZED 

R C23093/4-5 X X X X X X X X R C23093/4-8 B4-203 B4-220 B4-203 X X X X X X R C23093/4-9 X X X X X X X X R C23093/4-10 B4-203 B4-220 B4-203 X X X X X X 

 C23093/4-11 NOT AUTHORIZED 

R C23093/4-12 B4-203 B4-220 B4-203 X X X X X X R C23093/4-15 X X X X X X X X R C23093/4-19 B4-203 B4-220 B4-203 X X X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

R A300 B4-203 X X X X X X X X 

 A300 B4-220 X X  A300 C4-203 X X  A300 F4-203 X 

R WEIGHT VARIANT 06 07 08 10 14 16 17 18 R MTOW 165 165 157.5 157.5 157.5 147.5 147.5 165 R MLW 134 136 (1) 134 136 (1) 134 134 136 (1) 134 

134 (2) 134 (2) 134 (2) 

R MZFW 124 126 124 126 126 124 126 126 R Top assembly PNR R C23093/4-25 X X X X X X X X R C23093/4-35 X X X X X X X X 

Main Landing Gear Brace Strut 

 C23021/2 series NOT AUTHORIZED  C23111/2-1 B4-203 B4-220  C23111/2-2 B4-203 B4-220 

R C23111/2-3 X X X X X X X X R C23111/2-23 X X X X X X X X 

Main Landing Gear Structural Linkage 

 C23023/4 series NOT AUTHORIZED  C23121/2-0 NOT AUTHORIZED 

R C23121/2-1 X X X X X X X X R D 

C23121/2-21 X X X X X X X X 

Nose Landing Gear Leg 

 C23042 series NOT AUTHORIZED 

R C23137-0 X X X X X X X X R C23137-1 X X X X X X X X R C23137002 X X X X X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

N 

R A300 B4-203 X X X X X X X X 

 A300 B4-220 X X  A300 C4-203 X X  A300 F4-203 X 

R WEIGHT VARIANT 06 07 08 10 14 16 17 18 R MTOW 165 165 157.5 157.5 157.5 147.5 147.5 165 R MLW 134 136 (1) 134 136 (1) 134 134 136 (1) 134 

134 (2) 134 (2) 134 (2) 

R MZFW 124 126 124 126 126 124 126 126 R Top assembly PNR R C23137003 B4-203 B4-220 B4-203 X X X X X X R C23137006 X X X X X X X X 

Nose Landing Gear Telescopic Strut 

 C23037 series NOT AUTHORIZED  C23109-0 NOT AUTHORIZED 

R C23109-1 X X X X X X X X R C23109-2 X X X X X X X X R C23109-11 X X X X X X X X R C23109-12 X X X X X X X X R C23109610 X X X X X X X X R C23109710 X X X X X X X X 

Weight 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 A300-00-0037 and MOD 03424 or POST MOD 619 WV14: Aircraft POST MOD 06193 or POST SB A300-00-0007. 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

N N N 

 WV16: 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 GEAR LRUs THAT CAN BE INSTALLAIRCRAFT MODEL WEIGHT VARIANT BUT IT DOES NOT: - ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL A- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES. Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service BulletMaintenance Manuals, etc...) for the applicability of LRUs compared with individual aircra

the interchangeabilities/mixabilities of LRUs. 

END OF SUB-PART 1-0 

R 
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 

Multiple link Cross bars 

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 

Gear support rib Aft pintle pin 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 

Aft cross bar fitting fitting/Gear support rib) 

Fwd pick up 

Fwd cross bar fitting 

Gear support rib 

WING STRUCTURE - FIG. 10 

END OF SUB-PART 1-1 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-2 

EASA APPROVED 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. Sub-part 1-2 LIFE LIMITS 

Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. LIFE LIMITS (*) LIFE LIMITS APPL

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG Cal. B1 B2-1A B2-1C B2K-3C B2-20x B2-320 R ATA 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. Barrel C58954-3 N/A 63300 N/A X X 

C58954-5 N/A 63300 N/A X X X C58954-9 N/A 63300 N/A X X X 

C58954-11 N/A 63300 N/A X X X C58954-13 N/A 63300 N/A X X X C58954-17 N/A 63300 N/A X X X C58954-19 N/A 63300 N/A X X X C58954-21 N/A 63300 N/A X X X 

C65380-1 N/A 63300 N/A C65380-3 N/A 63300 N/A X C65380-5 N/A 63300 N/A X C65380-7 N/A 63300 N/A X C65380-9 N/A 63300 N/A X 

C65380-11 N/A 63300 N/A X C65380-13 N/A 63300 N/A X C65380-15 N/A 63300 N/A X C65380-17 N/A 63300 N/A X 

 Upper torque link pin C65546 (1) N/A 16000 N/A X X X N C65546-5 (1) N/A 16000 N/A X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-2 

EASA 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 APPL

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG Cal. B1 B2-1A B2-1C B2K-3C B2-20x B2-320 

Torque link medium pin C66192 N/A 50000 N/A X 

 Drag link C58957-3 N/A 20000 N/A X X X X D 

 C58957-5 N/A 20000 N/A X X X X 

S/A connecting rod C65389 N/A 12000 N/A 

C65389-1 N/A 58300 N/A X C65389-2 N/A 58300 N/A X C65389-3 N/A 58300 N/A X 

C65825 N/A 12000 N/A X X X 

C65825-1 N/A 12000 N/A X X X C65825-3 N/A 58300 N/A X X X X C65825-4 N/A 12000 N/A X X X C65825-5 N/A 12000 N/A X X X 

 SHOCK 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 rod C65388 N/A 58300 N/A X 

C65826 N/A 58300 N/A X X X X D60500 N/A 58300 N/A X 

 S/A Sliding rod C58958-3 N/A 35500 N/A X X X 

C65384-5 

N/A 53300 N/A 

N/A 76600 N/A X 

C65384-7 

N/A 53300 N/A 

N/A 76600 N/A X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-2 

EASA 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 APPL

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG Cal. B1 B2-1A B2-1C B2K-3C B2-20x B2-320  End fitting C61643-2 N/A 6600 N/A X X X 

C61643-4 N/A 13000 N/A X X X X C61643-5 N/A 13000 N/A X X X X 

 Lower torque link pin C65546 (1) N/A 16000 N/A X X X N D 

 C65546-5 (1) N/A 16000 N/A X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-2 

EASA 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 APPL

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG Cal. B1 B2-1A B2-1C B2K-3C B2-20x B2-320 R ATA 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 parts having an initial entry into service date after 30-Apr-1986. 

- 12000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated 9000 LDG or less on 30-Apr-1986. - 3000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated between 9000 and 14000 LDG on 30-Apr-

 - Either 17000 LDG from initial entry into service or 2000 LDG from 30-Apr-1986, whichever occurs first: For parts installed 

than 14000 LDG on 30-Apr-1986. 

 Pintle Pin (1) A32210001205xx N/A (2) N/A X X X X R BARREL ASSEMBLY (FIG. 06)  (1) Limitation applicable to WV01 & WV03 only.  Barrel C59049-1 N/A 64400 N/A X X X (1) 

C59049-2 

N/A 50000 N/A X 

N/A 64400 N/A X X 

C59049-3 N/A 64400 N/A X X (1) 

C59049-4 

N/A 50000 N/A X 

N/A 64400 N/A X X 

C59049-15 N/A 64400 N/A X X (1) C59049-16 N/A 64400 N/A X X (1) 

C59049-20 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-25 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-26 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-27 

N/A 50000 N/A X 

 .../... N/A 64400 N/A X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-2 

EASA 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 APPL

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG Cal. B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Barrel C59049-30 N/A 64400 N/A X X (1) 

C59049-31 N/A 64400 N/A X X (1) 

C59049-40 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-41 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-42 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-45 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-46 

N/A 50000 N/A X N/A 64400 N/A X X 

C59049-47 

N/A 50000 N/A X N/A 64400 N/A X X 

D56525 

N/A 50000 N/A X N/A 64400 N/A X X 

D56525-1 

N/A 50000 N/A X 

N/A 64400 N/A X X 

D56525-10 

N/A 50000 N/A X N/A 64400 N/A X X 

D56525-11 

N/A 50000 N/A X N/A 64400 N/A X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-2 

EASA 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 APPL

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG Cal. B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Turning tube C59050 N/A 24000 N/A X X X (1) 

C59050-2 N/A 24000 N/A X X (1) X C59050-3 N/A 24000 N/A X X (1) C59050-4 N/A 24000 N/A X X X 

C59050-20 N/A 24000 N/A X X X 

N C59050-28 N/A 24000 N/A X X (1) X R SHOCK ABSORBER ASSEMBLY (FIG. 07 & 08) 

(1) - For the first accomplishment, replace the bottom before accumulation of 24000 LDG since the initial entry into service, o

whichever occurs later, but without exceeding a total of 36000 LDG since the initial entry into service. The stated limits 

associated aircraft. 

 - For the subsequent accomplishments, replace the bottom before accumulation of 24000 LDG since initial entry into servic

part and not to the associated NLG. 

 Bottom C62037-1 N/A (1) N/A X X X N D68531 N/A (1) N/A X X X 

END OF SUB-PART 1-2 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA APPROVED 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. Sub-part 1-3 DEMONSTRATED FATIGUE LIVES 

Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 R ATA 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 76600 X X X 

A32140056200xx N/A 76600 X X X A32140056202xx N/A 76600 X X X A32140056204xx N/A 76600 X X X A32140057200xx N/A 76600 A32140057202xx N/A 76600 A32140057204xx N/A 76600 A32140062000xx N/A 76600 X X X A32140062002xx N/A 76600 X X X A32140063000xx N/A 76600 A32140063002xx N/A 76600 

Half ball housing (Fwd pintle bearing) (1) 

A32140036200xx N/A 76600 X X X 

 A32140036202xx N/A 76600 X X X 

A32140036204xx N/A 76600 X X X A32140036206xx N/A 76600 X X X A32140042200xx N/A 76600 A32140042202xx N/A 76600 A32140068002xx N/A 76600 X X X A32140068004xx N/A 76600 X X X A32140069002xx N/A 76600 

 .../... A32140069004xx N/A 76600 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 

Half ball housing (Fwd pintle bearing) (1) 

A32140076002xx N/A 76600 X X X 

 A32140076004xx N/A 76600 X X X 

A32140077002xx N/A 76600 A32140077004xx N/A 76600 

Ball (Fwd pintle bearing) (1) 

A32140012202xx N/A 76600 X X X 

A32140043202xx N/A 76600 

A32140074200xx N/A 76600 A32140075200xx N/A 76600 X X X 

Pin (Multiple link/Frame 50) (1) 

A53833451200xx N/A 76600 X X X 

N A53833451204xx N/A 76600 X X X 

A53833451206xx N/A 76600 X X X 

N A53833451208xx N/A 76600 X X X N A53833480200xx N/A 76600 X X X N A53833480202xx N/A 76600 X X X N A53833490200xx N/A 76600 

A53834451200xx N/A 76600 A53834451202xx N/A 76600 

 BARREL ASSEMBLY (FIG. 01 & 03)

R R R 

(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 re

maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed o

the 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. Lower torque link pin is included in the Shock Absorber assembly.R D 

(4) This PNR is common to upper and lower torque link pin nuts. Lower torque link pin nut is included in the Shock Absorber ass

Cage C66208 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Eye fitting C58956-3 N/A 76600 X X X X 

C58956-5 N/A 76600 X X X X C58956-7 N/A 76600 X X X X 

C58956-13 N/A 76600 X X X X 

C65382-1 N/A 76600 X C65382-3 N/A 76600 X C65382-5 N/A 76600 X 

D64926 N/A 76600 X 

 Pin (Hinge arm/Barrel) C65543-1 N/A 76600 X X X X 

C65543-3 N/A 76600 X X X X 

C65543-21 N/A 76600 X X X X 

C66441-1 N/A 76600 X C66441-3 N/A 76600 X 

C66441-21 N/A 76600 X 

 Barrel D56520-1 N/A 76600 X 

D56520-4 N/A 76600 X 

D64927 N/A 76600 X 

D64927-10 N/A 76600 X 

 Upper torque link pin C65546-1 (3) N/A 76600 X X X X 

C65546-2 (3) N/A 76600 X X X X 

N C65546-10 (3) N/A 76600 X X X X 

C65546-20 (3) N/A 76600 X X X X 

N C65546-25 (3) N/A 76600 X X X X 

C66191-1 (3) N/A 76600 X 

 .../... C66191-2 (3) N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 N Upper torque link pin C66191-10 (3) N/A 76600 X 

C66191-20 (3) N/A 76600 X 

N C66191-25 (3) N/A 76600 X 

D56729 (3) N/A 76600 X 

 Upper torque link pin nut 00-200-402 (4) N/A (1) X X 

SL40089 (4) N/A (1) X X X X 

SL40089P (4) N/A (1) X X X X 

SL40123 (4) N/A (1) X 

SL40123P (4) N/A (1) X 

Torque link (Upper & Lower) 

C58960-3 N/A 76600 X X X X 

 C58960-5 N/A 76600 X X X X 

C65386-1 N/A 76600 C65386-3 N/A 76600 X C65386-5 N/A 76600 X C65386-7 N/A 76600 X D56521-1 N/A 76600 X 

 Torque link medium pin C65542 N/A 76600 X X X X N C65542-5 N/A 76600 X X X X 

C65542-1 N/A 76600 X X X X 

C65542-20 N/A 76600 X X X X 

C66192-1 N/A 76600 X 

C66192-20 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 

Torque link medium pin nut 

00-200-358 N/A (1) X X X X 

 SL40114P N/A (1) X X X X 

SL40132 N/A (1) X 

SL40132P N/A (1) X 

 Pin (Drag link/Barrel) C62017-1 N/A 76600 X X X X 

C62017-2 N/A 76600 X X X X C62017-3 N/A 76600 X X X X 

C62017-20 N/A 76600 X X X X 

N C62017-25 N/A 76600 X X X X N C62017-30 N/A 76600 X X X X 

C66444 N/A 76600 X 

C66444-1 N/A 76600 X 

N C66444-5 N/A 76600 X N C66444-10 N/A 76600 X 

C66444-20 N/A 76600 X 

 Drag link C58957-9 N/A 76600 X X X 

C58957-11 N/A 76600 X X X X C58957-13 N/A 76600 X X X X 

C65383-3 N/A 76600 X C65383-5 N/A 76600 X 

C65383-13 N/A 76600 X 

Pin (Drag link/ Barrel/Brace strut) 

C65549 N/A 76600 X X X X 

 C65549-1 N/A 76600 X X X X N C65549-10 N/A 76600 X X X X  .../... C65549-20 N/A 76600 X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 

Pin (Drag link/ Barrel/Brace strut) 

C66443-1 N/A 76600 X 

N C66443-10 N/A 76600 X 

C66443-20 N/A 76600 X 

Pin (Hinge arm/Drag link) 

C65548 N/A 76600 X X X X 

N C65548-1 N/A 76600 X X X X 

C66442 N/A 76600 X X X X 

C66442-1 N/A 76600 X 

N C66442-5 N/A 76600 X X X X N C66442-10 N/A 76600 X 

C66442-20 N/A 76600 X X X X 

D60499 N/A 76600 X 

 Hinge Arm C58955-1 N/A 76600 X 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 X C58955-15 N/A 76600 X X X X C58955-17 N/A 76600 X X X X C58955-19 N/A 76600 X X X X 

C65381-1 N/A 76600 X C65381-3 N/A 76600 X C65381-5 N/A 76600 X C65381-7 N/A 76600 X D57195-1 N/A 76600 X D57196-1 N/A 76600 X 

D D57739-1 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Attaching fitting pin C62311-1 N/A 76600 X X X X N C62311-10 N/A 76600 X X X X 

C62311-20 N/A 76600 X X X X 

N C62311-200 N/A 76600 X X X X N D68529 N/A 76600 X X X X  Attaching fitting (LH) C61639 N/A 76600 X X X 

C66197 N/A 76600 X X (2) C69205 N/A 76600 X X X X 

C69205-1 N/A 76600 X X X X 

D48885 N/A 76600 X 

D48885-1 N/A 76600 X 

D51421 N/A 76600 X 

D51421-1 N/A 76600 X 

 Attaching fitting (RH) C61640 N/A 76600 X X X 

C66198 N/A 76600 X X (2) C69206 N/A 76600 X X X X 

C69206-1 N/A 76600 X X X X 

D48886 N/A 76600 X 

D48886-1 N/A 76600 X 

D51422 N/A 76600 X 

D51422-1 N/A 76600 X 

Pin (Connecting rod/ Upper rod) 

C65815 N/A 76600 X X X X 

 C65815-1 N/A 76600 X X X X N C65815-5 N/A 76600 X X X X N .../... C65815-10 N/A 76600 X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 

Pin (Connecting rod/ Upper rod) 

C65815-20 N/A 76600 X X X X 

N C65815-200 N/A 76600 X X X X 

C66472 N/A 76600 X 

C66472-1 N/A 76600 X 

N C66472-5 N/A 76600 X N C66472-10 N/A 76600 X 

C66472-20 N/A 76600 X 

N C66472-200 N/A 76600 X N D68528 N/A 76600 X N D68676 N/A 76600 X X X X  S/A connecting rod C58963-1 N/A 76600 X X X 

 SHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04)

 (1) Limitation applicable to WV 01 & WV03 only. R R R 

(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 re

maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed o

the 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 rod C58962-1 N/A 76600 X X (1) 

C65497 N/A 76600 X X X (1) 

 S/A Sliding rod C58958-5 N/A 76600 X X X 

C58958-11 N/A 76600 X X X C58958-13 N/A 76600 X X X X 

 .../... C65384-11 N/A 76600 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  S/A Sliding rod C65384-13 N/A 76600 X 

C65384-21 N/A 76600 X 

D64922 N/A 76600 X 

 End fitting C61643-10 N/A 76600 X X X X 

C61643-11 N/A 76600 X X X X 

 Lower torque link pin C65546-1 (5) N/A 76600 X X X X 

C65546-2 (5) N/A 76600 X X X X 

N C65546-10 (5) N/A 76600 X X X X 

C65546-20 (5) N/A 76600 X X X X 

N C65546-25 (5) N/A 76600 X X X X 

C66191-1 (5) N/A 76600 X C66191-2 (5) N/A 76600 X 

N C66191-10 (5) N/A 76600 X 

C66191-20 (5) N/A 76600 X 

N C66191-25 (5) N/A 76600 X 

D56729 (5) N/A 76600 X 

 Lower torque link pin nut 00-200-402 (6) N/A (2) X X 

SL40089 (6) N/A (2) X X X X 

SL40089P (6) N/A (2) X X X X 

SL40123 (6) N/A (2) X 

SL40123P (6) N/A (2) X 

 Brake torque arm pin C65544 N/A 76600 X X X N C65544-1 N/A 76600 X X X 

C65544-20 N/A 76600 X X X 

 .../... C66196 N/A 76600 X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Brake torque arm pin C66196-20 N/A 76600 X X X X 

D55709 N/A 76600 X 

N D55709-1 N/A 76600 X 

D60501 N/A 76600 X 

 Brake torque arm C61648-1 N/A 76600 X X X 

C61648-2 N/A 76600 X X X 

C66434 N/A 76600 X X X X 

C66434-1 N/A 76600 X 

C66434-30 N/A 76600 X 

D51989 N/A 76600 X D60502 N/A 76600 X 

 Bogie beam pivot pin C65545 N/A 76600 X X X 

C65545-1 N/A 76600 X X X C65545-2 N/A 76600 X (3) X X C65545-3 N/A 76600 X X X C65545-4 N/A 76600 X X X C65545-5 N/A 76600 X X X X C65545-6 N/A 76600 X X X 

C65545-20 N/A 76600 X X X X 

C66194 N/A 76600 X 

C66194-1 N/A 76600 X C66194-2 N/A 76600 X C66194-3 N/A 76600 X C66194-4 N/A 76600 X 

 .../... C66194-5 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Bogie beam pivot pin C66194-20 N/A 76600 X 

D60503 N/A 76600 X D64921 N/A 76600 X 

 Bogie beam pivot pin nut CRA50551 (4) N/A 76600 X X X X 

SL40054 N/A (2) X X X X 

SL40054P N/A (2) X X X X 

 BOGIE BEAM ASSEMBLY (FIG. 01)

 Bogie beam C58959-3 N/A 76600 X X X 

C65385-1 N/A 76600 X C65385-3 N/A 76600 X X X C65385-5 N/A 76600 X X X X C65385-7 N/A 76600 X C65385-9 N/A 76600 X 

C65385-13 N/A 76600 X X X X C65385-15 N/A 76600 X 

D51991-1 N/A 76600 X D51991-3 N/A 76600 X D56731-1 N/A 76600 X D60504-1 N/A 76600 X D60504-3 N/A 76600 X 

D64920 N/A 76600 X 

 Wheel axle C58961-3 N/A 76600 X X X 

C58961-5 N/A 76600 X X X 

C58961-11 N/A 76600 X X 

 .../... C65387-1 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Wheel axle C65387-3 N/A 76600 X 

C65387-5 N/A 76600 X C65387-7 N/A 76600 X 

C65387-11 N/A 76600 X C65387-31 N/A 76600 X X X X 

D48520-1 N/A 76600 X X X X D48520-3 N/A 76600 X X X X D48520-5 N/A 76600 X X X X 

D48520-11 N/A 76600 X X X X 

D51992-1 N/A 76600 X 

D51992-11 N/A 76600 X 

D56625-1 N/A 76600 X D60505-1 N/A 76600 X 

 LINKAGE ASSEMBLY (FIG. 01 & 05)

 Cross bar pin C62319-1 N/A 76600 X X 

C62319-2 N/A 76600 X X 

C62319-20 N/A 76600 X X 

N C62319-25 N/A 76600 X X 

C67676 N/A 76600 X 

N C67676-1 N/A 76600 X 

C67676-20 N/A 76600 X 

 Cross bar C61160-1 N/A 76600 X X 

C66792 N/A 76600 X 

C66792-1 N/A 76600 X 

D60522 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Multiple link pin C62318-1 N/A 76600 X X N C62318-10 N/A 76600 X X 

C62318-20 N/A 76600 X X 

C67131 N/A 76600 X 

N C67131-1 N/A 76600 X 

C67131-20 N/A 76600 X 

 Multiple link C61942-1 N/A 76600 X X 

C66503 N/A 76600 X 

C66503-1 N/A 76600 X C66503-2 N/A 76600 X 

N D 

 C66503-5 N/A 76600 X 

 BRACE ASSEMBLY (FIG. 01) 

 BRACE STRUT (FIG. 01) 

 (1) Limitation applicable to WV06 only.  Brace strut upper arm C59061-1 N/A 76600 X X X 

C66504 N/A 76600 X 

C66504-1 N/A 76600 X C66504-2 N/A 76600 X 

 Brace strut middle pin C62313-1 N/A 76600 X X X 

C68376 N/A 76600 X X X 

C68376-1 N/A 76600 X X X 

N C68376-2 N/A 76600 X X X 

C68376-20 N/A 76600 X X X 

C68400 N/A 76600 X 

 .../... C68400-1 N/A 76600 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 N Brace strut middle pin C68400-2 N/A 76600 X 

C68400-20 N/A 76600 X 

N D68670 N/A 76600 X  Brace strut lower arm C59062-1 N/A 76600 X X X 

C65606 N/A 76600 X 

C65606-1 N/A 76600 X C65606-2 N/A 76600 X C65606-3 N/A 76600 X C65606-6 N/A 76600 X 

N C65606-10 N/A 76600 X  Lock link pin C62314 N/A 76600 X X X X 

C62314-20 N/A 76600 X X X X C62314-30 N/A 76600 X X X X 

R LOCK LINK (FIG. 01) (1) Limitation applicable to WV06 only. N N N 

(2) The lock link middle pin must be replaced by a new one every time it is removed from the lock link lower arm. When the pin 

for the purpose of performing maintenance outside a workshop, no replacement is required provided the pin’s removal a

same lock link lower arm and neither the lower arm nor the pin accumulates time in service during the period between the re

 Lock link lower arm C61483-1 N/A 76600 X X X 

C65607 N/A 76600 C69426 N/A 76600 X C69443 N/A 76600 X X X 

C69443-1 N/A 76600 X X X 

R Lock link middle pin C61485-1 N/A (2) X X X X R C61485-20 N/A (2) X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Lock link upper arm C61484-2 N/A 76600 X X X 

C65608 N/A 76600 X 

 Lock link upper pin C62315-10 N/A 76600 X X X X 

C62315-20 N/A 76600 X X X X C62315-30 N/A 76600 X X X X 

R ATA 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 N A32210082200xx N/A 65700 X X X X R TELESCOPIC STRUT ASSEMBLY (FIG. 09) (1) Limitation applicable to WV01 & WV03 only.  End fitting pin C62911-1 N/A 65700 X X X 

C62911-2 N/A 65700 X X X 

C62911-15 N/A 65700 X X X 

N C62911-18 N/A 65700 X X X 

C62911-20 N/A 65700 X X X 

N C62911-25 N/A 65700 X X X 

D55951 N/A 65700 X 

 End fitting C61390-1 N/A 65700 X X X 

C61390-2 N/A 65700 X X X 

D55962 N/A 65700 X 

 Cylinder C61371 N/A 65700 X X X X 

D55954 N/A 65700 X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 

Nut (Cylinder/Locking cylinder) 

C61375 N/A 65700 X X X X 

N C61375-1 N/A 65700 X X X X 

D55955 N/A 65700 X 

N D55955-1 N/A 65700 X N D68538 N/A 65700 X  Locking cylinder C61373-1 N/A 65700 X X X 

C61373-3 N/A 65700 X X X C61373-4 N/A 65700 X X X C61373-6 N/A 65700 X X X C61373-7 N/A 65700 X X X 

N C61373-10 N/A 65700 X X X 

C61373-40 N/A 65700 X X X 

 Locking sleeve C61389 N/A 65700 X X X X 

C61389-1 N/A 65700 X 

 Lock claw C61391 N/A 65700 X X X X 

D55952 N/A 65700 X 

 Locking piston C61378-1 N/A 65700 X X X 

C61378-3 N/A 65700 X X (1) C61378-5 N/A 65700 X X (1) 

N C61378-10 N/A 65700 X X X 

C68483 N/A 65700 X X X 

C68483-1 N/A 65700 X X X C68483-2 N/A 65700 X X X C68483-3 N/A 65700 X X X C68483-4 N/A 65700 X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Rod C61372-1 N/A 65700 X X X 

C61372-2 N/A 65700 X X X C61372-3 N/A 65700 X X X C61372-4 N/A 65700 X D55953-1 N/A 65700 X D55953-2 N/A 65700 X 

D57050 N/A 65700 X X X 

D57050-1 N/A 65700 X 

R BARREL 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. R R R 

(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 re

maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed o

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

Pin (Clevis/Telescopic strut) 

C62231-1 N/A 65700 X X X (1) C62231-2 N/A 65700 X X X 

N C62231-10 N/A 65700 X X X (1) 

C62231-20 N/A 65700 X X X 

N C62231-25 N/A 65700 X X X 

D56530 N/A 65700 X X 

 Clevis C62002-1 N/A 65700 X X X (1) 

C62002-2 N/A 65700 X X X X 

D56527 N/A 65700 X 

 Lower pin (Link/Clevis) C62268-1 N/A 65700 X X X (1) 

C62268-2 N/A 65700 X X X 

N .../... C62268-15 N/A 65700 X X X (1) 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Lower pin (Link/Clevis) C62268-20 N/A 65700 X X X N C62268-25 N/A 65700 X X X N C62268-200 N/A 65700 X X X N D68541 N/A 65700 X X X  Link (Clevis/Barrel) C62230-1 N/A 65700 X X X X N C62230-10 N/A 65700 X X X X 

D56526 N/A 65700 X 

N D56526-1 N/A 65700 X N D68539 N/A 65700 X X X X N D68540 N/A 65700 X  Upper pin (Link/Barrel) C62267-1 N/A 65700 X X X (1) 

C62267-2 N/A 65700 X X X 

N C62267-10 N/A 65700 X X X (1) 

C62267-20 N/A 65700 X X X 

N C62267-25 N/A 65700 X X X N C62267-200 N/A 65700 X X X N D68544 N/A 65700 X X X  Pin (Clevis/Barrel) C62229-1 N/A 65700 X X X X N C62229-10 N/A 65700 X X X X 

C62229-20 N/A 65700 X X X 

D56528 N/A 65700 X 

 Barrel D59448 N/A 65700 X X X 

D59448-1 N/A 65700 X X X 

D59448-10 N/A 65700 X X X 

 .../... D59633 N/A 65700 X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Barrel D59633-1 N/A 65700 X X X 

D59633-10 N/A 65700 X X X 

D61185 N/A 65700 X X X 

D61185-10 N/A 65700 X X X 

D61553 N/A 65700 X X X D61661 N/A 65700 X X X 

 Pin (Barrel/Airframe) C62228-1 N/A 65700 X X X X 

C62228-20 N/A 65700 X X X 

 End fitting pin nut D68062 N/A (2) X X X X 

MS17825-6 N/A (2) X X X X 

 End fitting pin AN6-17 N/A (2) X X X 

D61183 N/A (2) X X X D68063 N/A (2) X X X 

NAS1306-22D N/A (2) X X X X 

 End fitting C62032 N/A 65700 X X X X 

C62032-1 N/A 65700 X X X 

N C62032-2 N/A 65700 X X X X N C62032-10 N/A 65700 X X X R D61184 N/A 65700 X X X N D61184-1 N/A 65700 X X X R D68076 N/A 65700 X X X N D68695 N/A 65700 X X X  Rack C61453 N/A 65700 X X X (1) 

C61453-1 N/A 65700 X X X 

N .../... C61453-15 N/A 65700 X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Rack C61453-20 N/A 65700 X X X 

C61453-40 N/A 65700 X X X C61453-41 N/A 65700 X X X 

N C61453-205 N/A 65700 X X X  Turning tube C59050-30 N/A 65700 X X X 

C59050-40 N/A 65700 X X X C59050-50 N/A 65700 X X X C59050-60 N/A 65700 X X X 

Torque link pin (Upper & Lower) 

C62223-1 N/A 65700 X X X X 

N C62223-15 N/A 65700 X X X X 

C62223-20 N/A 65700 X X X 

Torque link (Upper & Lower) 

C59562-2 N/A 65700 X X X X 

 C59562-3 N/A 65700 X 

C59562-4 N/A 65700 X X X 

N C59562-20 N/A 65700 X X X X  Torque link medium pin C62041-1 N/A 65700 X X X X N C62041-15 N/A 65700 X X X X 

C62041-20 N/A 65700 X X X 

N C62041-200 N/A 65700 X X X 

D53431 N/A 65700 X X X 

D53431-20 N/A 65700 X X X 

Torque link medium pin nut SL40110P N/A (3) X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 R SHOCK ABSORBER ASSEMBLY (FIG. 07 & 08) (1) Limitation applicable to WV01 & WV03 only. R R R 

(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 temp

purpose of performing maintenance outside a workshop, no replacement is required provided the nut’s removal and reinwheel axle and neither the wheel axle nor the nut accumulates time in service during the period between the removal and re

 (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 axle C59053-2 N/A 65700 X X (1) 

C59053-4 N/A 65700 X X X 

C59053-21 N/A 65700 X X X 

 Wheel axle nut C62879 N/A (2) X X X X N C62879-1 N/A (2) X X X X N D68537 N/A (2) X X X X  Sliding rod C59051-1 N/A 65700 X X X (1) 

C59051-3 N/A 65700 X X X C59051-5 N/A 65700 X X (1) 

C59051-21 N/A 65700 X X X 

 Upper cam dowel C62270 N/A (4) X X X X  Upper cam C62034-1 N/A 65700 X X X X N C62034-10 N/A 65700 X X X X N D68534 N/A 65700 X X X X  Lower cam C62035 N/A 65700 X X X X N C62035-1 N/A 65700 X X X X N D68532 N/A 65700 X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320  Restrictor C62036 N/A 65700 X 

C62036-1 N/A 65700 X X (1) C62036-2 N/A 65700 X X (5) 

N C62036-10 N/A 65700 X X (1) 

C67863 N/A 65700 X X (1) 

C67863-1 N/A 65700 X X (1) X C67863-2 N/A 65700 X X X C67863-3 N/A 65700 X X (1) C67863-4 N/A 65700 X X X 

N C67863-5 N/A 65700 X X (1) N C67863-10 N/A 65700 X X (1) X N C67863-20 N/A 65700 X X X N C67863-30 N/A 65700 X X (1) N C67863-40 N/A 65700 X X X N D68536 N/A 65700 X X X  Lower cam dowel C62866 N/A (6) X X X X  Upper rod C59052-1 N/A 65700 X X (1) 

C59052-2 N/A 65700 X X X 

 Nut (S/A/Barrel) C64040 N/A (6) X 

C64040-1 N/A (6) X X X X 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 R ATA 57-00-00 WING STRUCTURE (FIG. 10 & 11) (1) This item is not transferable from an aircraft to an 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 003 

A57240810214xx N/A 57000 

A57241955216xx N/A 60000 X X X A57241955218xx N/A 60000 244 

Gear support rib (RH) (1) (2) 

A57240035221xx N/A 60000 003 

A57240810215xx 

N/A 57000 

N/A 60000 244 

A57241955217xx N/A 60000 X X X 

 Fwd pick up (LH) (1) (2) A57240044002xx N/A 60000 003 

A57241947002xx N/A 60000 X X X A57241959002xx N/A 57000 

A57242390000xx 

N/A 57000 

N/A 60000 X X X 

A57242391000xx N/A 57000 

 Fwd pick up (RH) (1) (2) A57240044003xx N/A 60000 003 

A57241947003xx N/A 60000 X X X A57241959003xx N/A 57000 

A57242390001xx 

N/A 57000 

N/A 60000 X X X 

A57242391001xx N/A 57000 
A300 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-3 

EASA 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. DEMONSTRATED 

FATIGUE LIVES (*) DEMONSTRATED FATIGUE LIVE

Notes are located under the assy title. 

 Nomenclature Part Number FH LDG B1 B2-1A B2-1C B2K-3C B2-20x B2-320 R Aft cross bar fitting 

(LH) (1) (2) 

A57240042206xx N/A 60000 003 

A57240806200xx N/A 57000 

A57241946200xx N/A 60000 X X X 

R Aft cross bar fitting 

(RH) (1) (2) 

A57240042207xx N/A 60000 003 

A57240806201xx N/A 57000 

A57241946201xx N/A 60000 X X X 

R Fwd cross bar fitting 

(LH) (1) (2) 

A57240040206xx N/A 60000 003 

A57240808200xx N/A 57000 

A57241948200xx N/A 60000 X X X 

R Fwd cross bar fitting 

(RH) (1) (2) 

A57240040207xx N/A 60000 003 

A57240808201xx N/A 57000 

A57241948201xx N/A 60000 X X X 

R Link (Fwd cross bar 

fitting/Gear support rib) (1) (2) 

A57240406202xx N/A 60000 X X X 

A57240813200xx N/A 57000 A57242386200xx N/A 57000 

END 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 limitations 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 C62231-10 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, PNR 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 C62229-10: 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 attachment 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 C61637-11 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.