A300-600 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. 
A300-600 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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A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

TABLE OF CONTENTS 

SUBJECT PART 

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

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

N RECORD OF REVISIONS ROR 

INTRODUCTION 1-0 

ILLUSTRATIONS 1-1 

LIFE LIMITS 1-2 

DEMONSTRATED FATIGUE LIVES 1-3 
A300-600 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 DEC 21/06 2007-0293 

N 01 

ROR 

1-2 

1-3 

SEP 05/13 

Note: The ALS Part 1 is covered by the Certification Documents 00X0500M091/M31 and 

00K0500M091/M31. 

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 A300-600 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 A300-600 ALS Part 1 at revision 00, 

or, 

- In the A300-600 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. 
A300-600 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 A32140057202xx 13-Dec-2007 13500 9 years 

N A32140057204xx 05-Sep-2013 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) A32140042200xx 13-Dec-2007 13500 9 years 

N A32140042202xx 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) A32140043202xx 13-Dec-2007 13500 9 years 

N Pin (Multiple link/Frame 50) A53834451202xx 25-Apr-2007 13500 9 years 

N MLG Barrel assembly

N Attaching fitting pin C62311-20 25-Apr-2007 13500 9 years 

N Pin (Connecting rod/Upper rod) C66472-20 25-Apr-2007 13500 9 years 

N MLG Shock absorber assembly

N Bogie beam pivot pin nut 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) D55955 25-Apr-2007 13500 9 years 

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

N NLG Barrel assembly

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

N D56530 25-Apr-2007 13500 9 years 

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

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

N D56526 25-Apr-2007 13500 9 years 

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

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

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

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

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

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

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

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

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

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

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

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

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

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

N NLG Shock absorber assembly

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

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

N Lower cam C62035 25-Apr-2007 13500 9 years 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

RECORD OF REVISIONS 

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

EASA APPROVED 

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

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N Designation PNR Start date Compliance time 

N LDG CAL 

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

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

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

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

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

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

‘Start date’ column. 

(2) Replace by a new one at first nut removal/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. 
A300-600 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 01 and on, the content of the 

A300-600 Maintenance Planning Document 

Section 9-1 

Life Limits/Monitored parts 

From revision 02 and on, the content of the 

A300-600ST Aircraft Maintenance Manual 

Service Life Limits 

and 

Maintenance Checks 

that provided life limitations applicable to A300-600/A300-600ST models, has been 

transferred to the 

A300-600 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. 

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A300-600 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 or SIL 71-039 for guidance. They provide 

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

European Aviation Safety Agency (EASA). 

Note: Traceability and monitoring of parts 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: 

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ISSUE: SEP 05/13 ALS PART 1-0 PAGE: 3 

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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) or MSN listed in the tables below: 

A300-600 

N Aircraft series Aircraft models WV 

N 

A300 B4-600 

A300 B4-601 

N A300 B4-603 00 

N A300 B4-620 

N A300 B4-622 00, 08 

N A300 C4-600 A300 C4-620 00 

N A300 B4-600R A300 B4-605R 00, 01, 02, 03, 04, 08 

N A300 B4-622R 00, 04, 05, 07, 10 

N A300 C4-600R A300 C4-605R 

Variant F 00 

N A300 F4-600R A300 F4-605R 00, 06, 09 

N A300 F4-622R 00, 09 

A300-600ST 

N Aircraft model MSN 

N A300 F4-608ST (MSN 655), (MSN 751, 765, 776, 796) 

Note: 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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A300-600 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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. 

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

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

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

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

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

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

stop or performing a ‘touch and go’. 

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

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

3. APPLICABILITY SYSTEM 

A. General 

ALS sub-part 1-2 and 1-3 tables provide 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 aircraft model number, it stands for any number within the limits of the list of aircraft 

models defined in the tables of the paragraph 1.E. of this sub-part, e.g.: 

x4-605R stands for: A300 B4-605R, A300 C4-605R Variant F and A300 F4-605R. 

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A300-600 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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

X stands for: All A300-600 models defined by the applicability of the 

column. 

B4 stands for: All A300 B4-600 models, defined by the applicability of the 

column. 

B4/C4 stands for: All A300 B4-600 and A300 C4-600 models, defined by the 

applicability of the column. 

B4-620 stands for: A300 B4-620 model only, defined by the applicability of the 

column. 

excl. B4-204 stands for: All A300-600 models defined by the applicability of the 

column, except the model A300 B4-204. 

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 for A300-600, and 

- N°A.014 issued by the EASA for A300-600ST. 

A modification configuration is associated to each WV and is declared in the TCDS. 

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

associated to the approved WV. 

Note 2: For aircraft with Flexible Operational Weight (FOW): 

- Life limitations applicable to A300 B4-622R WV04 also apply to aircraft: 

- POST MOD 12311 or POST SB A300-00-6016 

- POST MOD 12922 or POST SB A300-00-6023 

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A300-600 AIRWORTHINESS LIMITATIONS SECTION 

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

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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 

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. 

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A300-600 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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 

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. 

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Ca

1Tr 

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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 470-32-796 provides information on procurable replacement PNR, detail 

PNR and applicable SB. 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

R 7. LANDING GEAR LRUs APPLICABILITY 

 A300 B4-601 X  A300 B4-603 X  A300 B4-620 X  A300 B4-622 X X  A300 C4-620 X  A300 B4-605R X X X X X X  A300 B4-622R X X X X  A300 C4-605R Variant F X  A300 F4-605R X X  A300 F4-622R X  A300 F4-608ST 

WEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 

 MTOW 165 153 170.5 171.7 171.7 167.8 171.7 144 165.1 153 150  MLW 138 138 140 140 138 140 140 140 140.6 140 140  MZFW 130 130 130 123 123 131 130 130 133.8 130 130 

R Top assembly PNR 

Main Landing Gear Leg 

 D22497/8000-x X X  D22497/8010-x X X  D22497/8011-x X  D22497/8015-x X  D22497/8020-x X X X X X X X X X X X  D22497/8025-x X X X X X X X X X X  D22497/8030-x X X X X X X X X X X X  D22497/8040-x X X X X X X X X X X X  D22497/8145-x X X  D22497/8150-x X X 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

 A300 B4-601 X  A300 B4-603 X  A300 B4-620 X  A300 B4-622 X X  A300 C4-620 X  A300 B4-605R X X X X X X  A300 B4-622R X X X X  A300 C4-605R Variant F X  A300 F4-605R X X  A300 F4-622R X  A300 F4-608ST 

WEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 

 MTOW 165 153 170.5 171.7 171.7 167.8 171.7 144 165.1 153 150  MLW 138 138 140 140 138 140 140 140 140.6 140 140  MZFW 130 130 130 123 123 131 130 130 133.8 130 130 

R Top assembly PNR 

 D22497/8250-x X X  D23243/4000-x X X X X X X X X X X X 

Main Landing Gear Brace Assembly 

 C23111/2010-x X X X X X X X X X X X  C23111/2020-x X X X X X X X X X X X  C23111/2030-x X X X X X X X X X X X 

Main Landing Gear Structural Linkage 

 D22537/8000-x X X  D22537/8010-x X X  D22537/8015-x X X X  D22537/8020-x X X X X X X X X X X X  D22537/8025-x X X X X X X X X X X X  D22537/8030-x X X X X X X X X X X X 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

 A300 B4-601 X  A300 B4-603 X  A300 B4-620 X  A300 B4-622 X X  A300 C4-620 X  A300 B4-605R X X X X X X  A300 B4-622R X X X X  A300 C4-605R Variant F X  A300 F4-605R X X  A300 F4-622R X  A300 F4-608ST 

WEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 

 MTOW 165 153 170.5 171.7 171.7 167.8 171.7 144 165.1 153 150  MLW 138 138 140 140 138 140 140 140 140.6 140 140  MZFW 130 130 130 123 123 131 130 130 133.8 130 130 

R Top assembly PNR 

Nose landing Gear Leg 

 C23137010-x X X  C23137020-x X X X X X X X X X  C23137610-x X X X X X X X X X X X  C23137620-x X X X X X X X X X X  C23137630-x X X  C23137650-x X X  C23137710-x X X X X X X X X X X X  C23137720-x X X X X X X X X X X  C23137750-x X X  C23137810-x X X X X X X X X X X X  C23137820-x X X X X X X X X X X  C23137910-x X X X X X X X X X X X 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

 A300 B4-601 X  A300 B4-603 X  A300 B4-620 X  A300 B4-622 X X  A300 C4-620 X  A300 B4-605R X X X X X X  A300 B4-622R X X X X  A300 C4-605R Variant F X  A300 F4-605R X X  A300 F4-622R X  A300 F4-608ST 

WEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 

 MTOW 165 153 170.5 171.7 171.7 167.8 171.7 144 165.1 153 150  MLW 138 138 140 140 138 140 140 140 140.6 140 140  MZFW 130 130 130 123 123 131 130 130 133.8 130 130 

R Top assembly PNR 

 C23137915-x  C23137920-x X X X X X X X X X X  C23137950-x X X 

Nose landing Gear Telescopic Strut 

 C23109610-x X X X X X X X X X X X  C23109710-x X X X X X X X X X X X  C23109810-x X X X X X X X X X X X  C23109915-x 

Weight variant number allocation (refer to the Type Certificate Data Sheet DGAC-F N°145, EASA N°A.014A300 B4/C4-600 series:  WV00: Basic aircraft or, aircraft POST MOD 12619 or POST SB A300-00-6020.  WV08: Aircraft POST MOD 10955 or POST SB A300-00-6009. 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-0 

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

R 

A300 B4/C4-600R series:  WV00: Basic aircraft.  WV01: Aircraft POST MOD 07047.  WV02: Aircraft POST MOD 07486 or POST SB A300-00-6005.  WV03: Aircraft POST MOD 07619 or POST SB A300-00-6001.  WV04: Aircraft POST MOD 08152 or POST SB A300-00-6003 or, POST MOD 12376 or POST SB 

 WV05: Aircraft POST MOD 08153 or POST SB A300-00-6004.  WV07: Aircraft POST MOD 10956 or POST SB A300-00-6011.  WV08: Aircraft POST MOD 12375 or POST SB A300-00-6017.  WV10: Aircraft POST MOD 12949 or POST SB A300-00-6026 (only when operated with dual WV to

Note 1: Linear variation of MZFW from 123t to 130t and of MTOW from 171,7t to 170,5t. 

A300 F4-600R series:  WV00: Basic aircraft.  WV06: Aircraft POST MOD 10395.  WV09: Aircraft POST MOD 12199 or POST MOD 12852. A300 F4-608ST: 

Note 2: Applicable to MSN 655. MZFW 132t (centre tank empty), 130t (centre tank used). Note 3: Applicable to MSN 751, 765, 776 and 796. MZFW 133t (centre tank empty), 130t (centre ta

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. 

END OF SUB-PART 1-0 
A300-600 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 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

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

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

Gear support rib 

Gear support rib Aft pintle pin Fwd pick up 

Ball (Fwd pintle bearing)

Half ball housing 

(Fwd pintle bearing) 

MAIN LANDING GEAR - FIG. 02 
A300-600 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 
A300-600 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 
A300-600 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 
A300-600 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 
A300-600 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 A300-32-6020 

 (x4) POST MOD 1257/S7730 or POST SB A300-32-6020 

Sliding rod 

Wheel axle 

Wheel axle nut (x2) 

Nut (S/A/Barrel) 

NOSE LANDING GEAR - FIG. 07 
A300-600 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 
A300-600 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) 
A300-600 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 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-1 PAGE: 11 

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

Special bolt 

Rear carriage assy 

Track 3 to 6 

WING STRUCTURE - FIG. 11 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-1 PAGE: 12 

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

GENERAL ELECTRIC AFT ENGINE MOUNT CF6-80C2 - FIG. 12 

Shear bolt 

(Link/Engine) 

Shear bolt (Outer, 

Link/Lower beam) 

Shear bolt (Inner, RH 

link/Lower beam) 

Link (LH) 

Link (RH) 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

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

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

PRATT & WHITNEY FORWARD ENGINE MOUNT - FIG. 13 

Bolt (Link/Fan 

case) (x2) 

Thrust link (x2) 

Cross beam 

Bolt (Cross beam/ 

Main beam) 

Main beam 

Shear pin 

Outer support 

(PW JT9D-7R4) 

Inner support 

(PW JT9D-7R4) 

Support 

(PW 4000) 

Bolt (Link/Cross 

beam) (x2) 

Pylon pyramid
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 ALS PART 1-1 PAGE: 14 

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

PRATT & WHITNEY AFT ENGINE MOUNT - FIG. 14 

END OF SUB-PART 1-1

Bolt (Mid link/Engine) 

Bolt (Side link/Engine) (x2) 

Link (x3) 

Pin (Link/Main beam) (x3) 

Main beam 

Pylon 
A300-600 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. GE POWERED A300-600s 

 Nomenclature Part Number FH LDG Cal. B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 R ATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 05)R BARREL ASSEMBLY (FIG. 01 & 03) Pin (Hinge arm/Barrel) C66441-21 N/A 36000 N/A X 

N/A 55600 N/A X X X 

 Upper torque link pin C66191-20 N/A 45000 N/A X X 

D56729 

N/A 36000 N/A X N/A 50600 N/A X X X 

 Torque link medium pin C66192-20 N/A 45000 N/A X 

N/A 75000 N/A X X X 

 S/A connecting rod C65389-3 N/A 36000 N/A X 

N/A 58000 N/A X X X 

R SHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04) S/A Upper rod C65388 N/A 55800 N/A X X 

D60500 

N/A 40000 N/A X N/A 66600 N/A X X 

 Lower torque link pin C66191-20 N/A 45000 N/A X X 

D56729 

N/A 36000 N/A X N/A 50600 N/A X X X 

R LINKAGE ASSEMBLY (FIG. 01 & 05) Cross bar C66792 N/A 71600 N/A X X 

C66792-1 N/A 74000 N/A X X 

D60522 

N/A 41000 N/A X N/A 68300 N/A X X X 
A300-600 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. GE POWERED A300-600s 

 Nomenclature Part Number FH LDG Cal. B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Multiple link pin C67131-20 N/A 36000 N/A X 

N/A 52000 N/A X X X 

 Multiple link C66503-1 N/A 42600 N/A X 

N/A 71000 N/A X X X 

C66503-2 

N/A 42600 N/A X 

N/A 71000 N/A X X X 
A300-600 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. GE POWERED A300-600s 

 Nomenclature Part Number FH LDG Cal. B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 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 R BARREL ASSEMBLY (FIG. 06) (1) Limit not applicable to A300 B4-605R WV08 and A300 F4-605R WV06.  Barrel C59049-2 N/A 38100 N/A X X (1) X 

C59049-4 N/A 38100 N/A X X (1) X 

C59049-20 N/A 38100 N/A X X (1) X C59049-25 N/A 38100 N/A X X (1) X C59049-26 N/A 38100 N/A X X (1) X 

N C59049-27 N/A 38100 N/A X X (1) X 

C59049-40 N/A 38100 N/A X X (1) X C59049-41 N/A 38100 N/A X X (1) X 

N C59049-42 N/A 38100 N/A X X (1) X 

C59049-45 N/A 38100 N/A X X (1) X C59049-46 N/A 38100 N/A X X (1) X 

N C59049-47 N/A 38100 N/A X X (1) X 

D56525 N/A 38100 N/A X X X 

D56525-1 N/A 38100 N/A X X X 

D56525-10 N/A 38100 N/A X X X 

N D56525-11 N/A 38100 N/A X X X 
A300-600 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. GE POWERED A300-600s 

 Nomenclature Part Number FH LDG Cal. B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Turning tube C59050-4 N/A 17000 N/A X X 

C59050-20 N/A 17000 N/A X 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 X N D68531 N/A (1) N/A X X X X 
A300-600 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. GE POWERED A300-600s 

 Nomenclature Part Number FH FC Cal. B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 R ATA 71-20-00 ENGINE MOUNTS (FIG. 12 to 14)R GENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY CF6-80C2 (FIG. 12) (1) Part to be removed no later than 31-Dec-2009. 

(2) Replacement with improved links at next engine shop visit after 28-Aug-2000, or before accumulation of 29000 Engine Cy

whichever occurs first. Refer to FAA AD 2000-12-08. 

Shear bolt (Outer, Link/Lower beam) 9380M75P01 N/A N/A (1) X X X Shear bolt (Inner, RH link/Lower beam) 9380M80P01 N/A N/A (1) X X X 

 Link (LH) 9348M79P01 N/A (2) (2) X X X  Link (RH) 9348M84P01 N/A (2) (2) X X X 

Shear bolt (Link/Engine) 9380M73P01 N/A N/A (1) X X X 

R PRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 13)

(1) Part to be removed no later than 31-Dec-2005. The replacement of this part can be delayed until the next engine removal a

are not exceeded. The life the part accumulated before the last engine installation date must be calculated in accordance SIL 71-039. It must be added to the actual life accumulated since the last engine installation date. The total must not exceed 

 Bolt (Link/Fan case) 221-0251-503 N/A (1) (1) X  Bolt (Link/Cross beam) 221-0251-503 N/A (1) (1) X 

221-0251-505 N/A (1) (1) X 221-0251-507 N/A (1) (1) X 

 Cross beam 221-0242-5 N/A 20000 N/A X 

Bolt (Cross beam/Main beam) 221-0251-501 N/A (1) (1) X 

 Main beam 221-0241-5 N/A 20000 N/A X 

221-0241-9 N/A 20000 N/A X 221-4005-1 N/A 20000 N/A X 
A300-600 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. GE POWERED A300-600s 

 Nomenclature Part Number FH FC Cal. B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Shear pin 221-0252-501 N/A (1) (1) X 

221-0252-503 N/A (1) (1) X 

R PRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 14)

(1) Part to be removed no later than 31-Dec-2005. The replacement of this part can be delayed until the next engine removal a

are not exceeded. The life the part accumulated before the last engine installation date must be calculated in accordance SIL 71-039. It must be added to the actual life accumulated since the last engine installation date. The total must not exceed 

 Pin (Link/Main beam) 221-0264-501 N/A (1) (1) X  Bolt (Mid link/Engine) 80876-20-4 N/A (1) (1) X  Bolt (Side link/Engine) 80876-20-3 N/A (1) (1) X 

END OF SUB-PART 1-2 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 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. N Aft pintle pin (1) A32140057202xx N/A 46000 X N N/A 76600 X X X N 

A32140057204xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140063000xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140063002xx 

N/A 46000 X 

N N/A 76600 X X X N Half ball housing (Fwd 

pintle bearing) (1) A32140042200xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140042202xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140069002xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140069004xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140077002xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140077004xx 

N/A 46000 X 

N .../... N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N Half ball housing (Fwd 

pintle bearing) (1) A32140077008xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140077010xx 

N/A 46000 X 

N N/A 76600 X X X N Ball (Fwd pintle bearing) 

(1) A32140043202xx 

N/A 46000 X 

N N/A 76600 X X X N 

A32140074200xx 

N/A 46000 X 

N N/A 76600 X X X N Pin (Multiple link/Frame 

50) (1) A53833490200xx 

N/A 46000 X 

N N/A 76600 X X X N 

A53834451200xx 

N/A 46000 X 

N N/A 76600 X X X 

A53834451202xx 

N/A 46000 X N/A 76600 X X X 

R 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. 

 Cage C66208 N/A 46000 X 

N/A 76600 X X X 

 Eye fitting C65382-5 N/A 46000 X 

N/A 76600 X X X 

D64926 

N/A 46000 X N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Barrel C65380-19 N/A 76600 X X 

C65380-21 N/A 76600 X X 

D56520-1 

N/A 46000 X 

N/A 76600 X X X 

D56520-3 

N/A 46000 X 

N/A 76600 X X X 

D64927 

N/A 46000 X N/A 76600 X X X 

D64927-10 

N/A 46000 X N/A 76600 X X X 

 Upper torque link pin nut SL40123P N/A (1) X X X X 

Torque links (Upper & Lower) 

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

N/A 46000 X 

N/A 76600 X X X 

Torque link medium pin nut SL40132P N/A (1) X X X X 

 Pin (Drag link/Barrel) C66444-20 N/A 46000 X 

N/A 76600 X X X 

 Drag link C65383-5 N/A 46000 X 

N/A 76600 X X X 

C65383-13 

N/A 46000 X N/A 76600 X X X 

Pin (Drag link/Barrel/Brace strut) C66443-20 

N/A 46000 X N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Pin (Hinge arm/Drag link) C66442-20 N/A 76600 X X 

D60499 

N/A 46000 X N/A 76600 X X X 

 Hinge arm C65381-7 N/A 76600 X X 

D57739-1 

N/A 46000 X 

N/A 76600 X X X 

 Attaching fitting pin C62311-20 N/A 46000 X 

N/A 76600 X X X 

N 

C62311-200 

N/A 46000 X 

N N/A 76600 X X X N 

D68529 

N/A 46000 X 

N N/A 76600 X X X  Attaching fitting (LH) D51421 N/A 46000 X 

N/A 76600 X X X 

D51421-1 

N/A 46000 X 

N/A 76600 X X X 

 Attaching fitting (RH) D51422 N/A 46000 X 

N/A 76600 X X X 

D51422-1 

N/A 46000 X 

N/A 76600 X X X 

Pin (Connecting rod/Upper rod) C66472-20 

N/A 46000 X N/A 76600 X X X 

N 

C66472-200 

N/A 46000 X 

N .../... N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N Pin (Connecting rod/Upper 

rod) D68528 

N/A 46000 X 

N N/A 76600 X X X R SHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04)R (1) PNR CRA50551 applies to nuts used for repaired bogie beam pivot pins. 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. 

 S/A Sliding rod C65384-13 N/A 76600 X X 

C65384-21 

N/A 46000 X N/A 76600 X X X 

D64922 

N/A 46000 X N/A 76600 X X X 

 End fitting C61643-10 N/A 46000 X 

N/A 76600 X X X 

C61643-11 

N/A 46000 X N/A 76600 X X X 

 Lower torque link pin nut SL40123P N/A (2) X X X X  Brake torque arm pin D55709 N/A 76600 X X N D55709-1 N/A 76600 X X 

D60501 

N/A 46000 X N/A 76600 X X X 

 Brake torque arm C66434-30 N/A 76600 X X 

D60502 

N/A 46000 X N/A 76600 X X X 

D61200 

N/A 46000 X N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Bogie beam pivot pin C66194-20 N/A 76600 X X 

D60503 

N/A 46000 X N/A 76600 X X X 

D61201 

N/A 46000 X N/A 76600 X X X 

D64921 

N/A 46000 X N/A 76600 X X X 

 Bogie beam pivot pin nut CRA50551 (1) N/A 46000 X N/A 76600 X X X 

SL40054P N/A (2) X X X X 

 BOGIE BEAM ASSEMBLY (FIG. 01)

 Bogie beam C65385-15 N/A 76600 X X 

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

N/A 46000 X 

N/A 76600 X X X 

D60504-3 

N/A 46000 X 

N/A 76600 X X X 

D61198-1 

N/A 46000 X 

N/A 76600 X X X 

D64920 

N/A 46000 X N/A 76600 X X X 

 Wheel axle D56625-1 N/A 76600 X X 

D60505-1 

N/A 46000 X 

 .../... N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Wheel axle 

D61199-1 

N/A 46000 X 

N/A 76600 X X X 

R LINKAGE ASSEMBLY (FIG. 01 & 05) Cross bar pin C67676-20 N/A 46000 X 

N/A 76600 X X X 

R BRACE ASSEMBLY (FIG. 01)

 BRACE STRUT (FIG. 01)

 Brace strut upper arm C66504-2 N/A 46000 X 

N/A 76600 X X X 

 Brace strut middle pin C68400-20 N/A 46000 X 

N/A 76600 X X X 

 Brace strut lower arm 

C65606-3 

N/A 46000 X 

N/A 76600 X X X 

 Lock link pin C62314-30 N/A 46000 X 

N/A 76600 X X X 

 LOCK LINK (FIG. 01)

R R R 

(1) 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 asame 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 

C69426 

N/A 46000 X N/A 76600 X X X 

 Lock link middle pin C61485-20 N/A (1) X X X X  Lock link upper arm C65608 N/A 46000 X 

N/A 76600 X X X 

 Lock link upper pin C62315-30 N/A 46000 X 

N/A 76600 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 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. N Pintle pin (1) A32210079200xx N/A 50000 X R N/A 61150 X B4 X R A32210080200xx N/A 61150 X X X N 

A32210082200xx 

N/A 50000 X 

N N/A 61150 X X X R TELESCOPIC STRUT ASSEMBLY (FIG. 09) End fitting pin D55951 N/A 50000 X 

N/A 65700 X X X 

 End fitting D55962 N/A 50000 X 

N/A 65700 X X X 

 Cylinder D55954 N/A 50000 X 

N/A 65700 X X X 

R Nut (Cylinder/Locking 

cylinder) D55955 

N/A 50000 X N/A 65700 X X X 

N 

D55955-1 

N/A 50000 X 

N N/A 65700 X X X N 

D68538 

N/A 50000 X 

N N/A 65700 X X X  Locking cylinder C61373-3 N/A 65700 X X X 

C61373-4 

N/A 50000 X 

N/A 65700 X X X 

C61373-6 

N/A 50000 X 

 .../... N/A 65700 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Locking cylinder C61373-7 N/A 50000 X 

N/A 65700 X X X 

C61373-40 N/A 65700 X X X 

D63091 

N/A 50000 X N/A 65700 X X X 

D63091-1 

N/A 50000 X 

N/A 65700 X X X 

 Locking sleeve C61389-1 N/A 50000 X 

N/A 65700 X X X 

 Lock claw 

D55952 

N/A 50000 X N/A 65700 X X X 

 Locking piston C68483-1 N/A 50000 X 

N/A 65700 X X X 

C68483-2 

N/A 50000 X 

N/A 65700 X X X 

C68483-3 

N/A 50000 X 

N/A 65700 X X X 

C68483-4 

N/A 50000 X 

N/A 65700 X X X 

D63282 

N/A 50000 X N/A 65700 X X X 

 Rod D55953-1 N/A 65700 X X X 

D55953-2 N/A 65700 X X X 

 .../... D57050 N/A 65700 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Rod 

D57050-1 

N/A 50000 X 

N/A 65700 X X X 

R BARREL ASSEMBLY (FIG. 06)

(1) For A300 B4-605R, limitation applicable only to WV00, WV01, WV02, WV03 & WV04.  For A300 F4-605R, limitation applicable only to WV00 & WV09. 

 (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) 

C62231-20 N/A 65700 X X (1) X 

D56530 

N/A 50000 X N/A 65700 X X X 

 Clevis C62002-2 N/A 65700 X X (1) X 

D56527 

N/A 50000 X N/A 65700 X X X 

 Lower pin (Link/Clevis) C62268-20 N/A 50000 X 

N/A 65700 X X X 

N 

C62268-200 

N/A 50000 X 

N N/A 65700 X X X N 

D68541 

N/A 50000 X 

N N/A 65700 X X X  Link (Clevis/Barrel) C62230-1 N/A 65700 X X (1) X N C62230-10 N/A 65700 X X (1) X 

D56526 

N/A 50000 X 

 .../... N/A 65700 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N Link (Clevis/Barrel) D56526-1 N/A 50000 X N N/A 65700 X X X N D68539 N/A 65700 X X (1) X N 

D68540 

N/A 50000 X 

N N/A 65700 X X X  Upper pin (Link/Barrel) C62267-20 N/A 50000 X 

N/A 65700 X X X 

N 

C62267-200 

N/A 50000 X 

N N/A 65700 X X X N 

D68544 

N/A 50000 X 

N N/A 65700 X X X  Pin (Clevis/Barrel) C62229-20 N/A 65700 X X (1) X 

D56528 

N/A 50000 X N/A 65700 X X 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 

D61185 N/A 65700 X X X 

D61185-10 N/A 65700 X X X 

D61553 

N/A 50000 X N/A 65700 X X X 

D61661 N/A 65700 X X X 

 Pin (Barrel/Airframe) C62228-20 N/A 50000 X 

N/A 65700 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N 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 X 

D61183 N/A (2) X X X 

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

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

 End fitting C62032 N/A 65700 X X X 

C62032-1 N/A 65700 X X X 

N C62032-2 N/A 65700 X X X N C62032-10 N/A 65700 X X X 

D61184 

N/A 50000 X N/A 65700 X X X 

N 

D61184-1 

N/A 50000 X 

N N/A 65700 X X X N 

D68076 

N/A 50000 X 

N N/A 65700 X X X N 

D68695 

N/A 50000 X 

N N/A 65700 X X X  Rack C61453-1 N/A 65700 X X N C61453-15 N/A 65700 X X 

C61453-20 N/A 65700 X X C61453-40 

N/A 50000 X N/A 65700 X X X 

C61453-41 

N/A 50000 X 

 .../... N/A 65700 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N Rack C61453-205 N/A 65700 X X  Turning tube C59050-30 N/A 65700 X X (1) X 

C59050-40 N/A 65700 X X (1) X C59050-50 

N/A 50000 X N/A 65700 X X X 

C59050-60 

N/A 50000 X N/A 65700 X X X 

Torque link pin (Upper & Lower) C62223-20 

N/A 50000 X N/A 65700 X X X 

Torque link (Upper & Lower) C59562-2 

N/A 50000 X 

N/A 65700 X X X 

C59562-3 

N/A 50000 X 

N/A 65700 X X X 

C59562-4 

N/A 50000 X 

N/A 65700 X X X 

N 

C59562-20 

N/A 50000 X 

N N/A 65700 X X X  Torque link medium pin C62041-20 N/A 50000 X 

N/A 65700 X X X 

N 

C62041-200 

N/A 50000 X 

N N/A 65700 X X X 

D53431-20 

N/A 50000 X N/A 65700 X X X 

 Torque link medium pin nut SL40110P N/A (3) X X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 R SHOCK ABSORBER ASSEMBLY (FIG. 07 & 08)R R R 

(1) The nut must be replaced by a new one every time it is removed from the assembly. When the nut is temporarily remo

performing maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are neither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation. 

R (2) Part must be replaced by a new one every time it is removed from the sliding rod. R (3) Part must be replaced by a new one every time it is removed from the upper rod.  Wheel axle C59053-4 N/A 65700 X X 

C59053-21 

N/A 50000 X N/A 65700 X X X 

R Wheel axle nut C62879 N/A (1) X X X X N C62879-1 N/A (1) X X X X N D68537 N/A (1) X X X X  Sliding Rod C59051-3 N/A 50000 X 

N/A 65700 X X X 

C59051-21 

N/A 50000 X N/A 65700 X X X 

R Upper cam dowel C62270 N/A (2) X X X X  Upper cam C62034-1 N/A 50000 X 

N/A 65700 X X X 

N 

C62034-10 

N/A 50000 X 

N N/A 65700 X X X N 

D68534 

N/A 50000 X 

N N/A 65700 X X X  Lower cam 

C62035 

N/A 50000 X 

 .../... N/A 65700 X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N Lower cam 

C62035-1 

N/A 50000 X 

N N/A 65700 X X X N 

D68532 

N/A 50000 X 

N N/A 65700 X X X  Restrictor C67863-1 N/A 65700 X X X 

C67863-2 

N/A 50000 X 

N/A 65700 X X X 

C67863-4 

N/A 50000 X 

N/A 65700 X X X 

N C67863-10 N/A 65700 X X X N 

C67863-20 

N/A 50000 X 

N N/A 65700 X X X N 

C67863-40 

N/A 50000 X 

N N/A 65700 X X X N 

D68536 

N/A 50000 X 

N N/A 65700 X X X R Lower cam dowel C62866 N/A (3) X X X X  Upper Rod C59052-2 N/A 50000 X 

N/A 65700 X X X 

R Nut (S/A/Barrel) C64040-1 N/A (1) X X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N ATA 57-00-00 WING STRUCTURE (FIG. 10 & 11)N MAIN LANDING GEAR SUPPORT RIB ASSEMBLY AND ASSOCIATED FITTINGS (FIG. 10) N (1) This item is not transferable from an aircraft to another: Traceability at aircraft level is authorized. N (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits. N (3) This limitation applies to parts fitted to aircraft POST MOD 12699. N (4) For A300 F4-605R, this limitation applies to parts fitted to aircraft PRE MOD 12699. N Gear support rib (LH) 

(1) (2) A57240810214xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N 

A57240810216xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N 

A57240810218xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Gear support rib (RH) 

(1) (2) A57240810215xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N 

A57240810217xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N 

A57240810219xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N Fwd pick up (LH) (1) (2) 

A57242391000xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Fwd pick up (RH) (1) (2) 

A57242391001xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Aft cross bar fitting (LH) 

(1) (2) A57240806004xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Aft cross bar fitting (RH) 

(1) (2) A57240806005xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Fwd cross bar fitting (LH) 

(1) (2) A57240808004xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Fwd cross bar fitting (RH) 

(1) (2) A57240808005xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N Link (Fwd cross bar fitting/ 

Gear support rib) (1) (2) A57242386204xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 N 

A57242386206xx 

N/A 30000 F4 (3) X 

N N/A 42500 C4/F4 (4) C4 N N/A 51000 X B4 B4 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH LDG B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 N FLAPS REAR CARRIAGE ASSEMBLY (FIG. 11) N (1) Part to be removed no later than 31-Dec-2050. N (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits. N Special bolt (2) A57940357200xx N/A (1) X X X X N A57940357202xx N/A (1) X X X X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH FC B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620 R ATA 71-20-00 ENGINE MOUNTS (FIG. 12 to 14)R GENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY CF6-80C2 (FIG. 12)

Shear bolt (Outer, Link/Lower beam) 9380M75P02 

N/A 36800 X 

 N/A 64000 X X 

Shear bolt (Inner, RH link/Lower beam) 9380M80P02 

N/A 36800 X 

 N/A 64000 X X  Link (LH) 1846M23P01 N/A 36800 X 

N/A 50000 X X 

 Link (RH) 9348M84P02 N/A 36800 X 

N/A 80000 X X 

 Shear bolt (Link/Engine) 9380M73P02 N/A 36800 X 

N/A 64000 X X 

R PRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 13) Bolt (Link/Fan case) 221-0251-511 N/A 40000 X  Trust link 221-0245-5 N/A 40000 X 

221-0245-9 N/A 40000 X 

221-0245-13 N/A 40000 X 

 Bolt (Link/Cross beam) 221-0251-515 N/A 40000 X  Cross beam 221-4004-1 N/A 40000 X 

221-4004-5 N/A 40000 X 

Bolt (Cross beam/Main beam) 221-0251-509 N/A 40000 X 

 Main beam 221-4006-3 N/A 40000 X 

221-4006-5 N/A 40000 X 

 Shear pin 221-0252-507 N/A 40000 X 
A300-600 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 LIV

 Notes are located under the assy title. GE POWERED A300-600s P Nomenclature Part Number FH FC B4-601 B4-603 x4-605R F4-608ST B4-620 C4-620  Outer support 221-0243-501 N/A 40000 X  Inner support 221-0244-501 N/A 40000 X 

221-0244-503 N/A 40000 X 

 Support 221-4047-505 N/A 40000 

221-4047-507 N/A 40000 

R PRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 14) Main beam 221-0261-9 N/A 40000 X 

221-0261-11 N/A 40000 X 221-0261-15 N/A 40000 X 

 Pin (Link/Main beam) 221-0264-503 N/A 40000 X  Link 221-0262-5 N/A 40000 X 

221-0262-7 N/A 40000 X 

 Bolt (Mid link/Engine) 80876-20-6 N/A 40000 X  Bolt (Side link/Engine) 80876-20-5 N/A 40000 X 

END OF SUB-PART 1-3 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

1- GENERAL 

- A300-600 ALS Part 1 revision 00: 

The airworthiness limitations previously listed in the A300-600 MPD section 9-1 and in the 

A300-600ST AMM Chapter 05 were transferred into the initial version of the ALS Part 1, 

(excluding the system-related airworthiness limitations that were transferred to the A300-600 

ALS Part 4). 

- A300-600 ALS Part 1 revision 01: 

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

landing gear/wing interface components). This revision includes the variation 

0CVLG120008/C0S. 

2- SUMMARY OF CHANGES: 

The following summarizes the changes with respect to the previous issue of the A300-600 ALS 

Part 1 (revision 00). 

New items: 

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY: 

None. 

SUB-PART 1-2: 

None. 

SUB-PART 1-3: 

* Main landing gear: 

Aft pintle pin PNR A32140057202xx, PNR A32140057204xx, PNR A32140063000xx 

and PNR A32140063002xx: PNR added. 

Half ball housing (Fwd pintle bearing) PNR A32140042200xx, PNR A32140042202xx, 

PNR A32140069002xx, PNR A32140069004xx, PNR A32140077002xx, PNR 

A32140077004xx, PNR A32140077008xx and PNR A32140077010xx: PNR added. 

Ball (Fwd pintle bearing) PNR A32140043202xx and PNR A32140074200xx: PNR 

added. 

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

Notes (1), (2), (3) and (4) added. 

Gear support rib (LH) PNR A57240810214xx, PNR A57240810216xx and PNR 

A57240810218xx: PNR added. 

Gear support rib (RH) PNR A57240810215xx, PNR A57240810217xx and PNR 

A57240810219xx: PNR added. 

Fwd pick up (LH) PNR A57242391000xx: PNR added. 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 2/5 

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

Fwd pick up (RH) PNR A57242391001xx: PNR added. 

Aft cross bar fitting (LH) PNR A57240806004xx: PNR added. 

Aft cross bar fitting (RH) PNR A57240806005xx: PNR added. 

Fwd cross bar fitting (LH) PNR A57240808004xx: PNR added. 

Fwd cross bar fitting (RH) PNR A57240808005xx: PNR added. 

Link (Fwd cross bar fitting/Gear support rib) PNR A57242386204xx and PNR 

A57242386206xx: PNR added. 

* Wing structure, Flaps rear carriage assembly: 

Note (1) added. 

Special bolt PNR A57940357200xx and PNR A57940357202xx: PNR added. 

Amendments: 

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY: 

None. 

SUB-PART 1-2: 

* Main landing gear: 

Figures number added. 

* Main landing gear, Barrel assembly: 

Figure number amended. 

* Main landing gear, Shock absorber assembly: 

Figures number amended. 

* Main landing gear, Linkage assembly: 

Figure number amended. 

* Nose landing gear: 

Figures number added. 

Note (1) amended. 

* Nose landing gear, Barrel assembly: 

Figure number amended. 

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

added (MOD 13212). 

* Main landing gear, Shock absorber assembly: 

Figures number amended. 

Bottom PNR D68531: PNR added (MOD 13457). 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 3/5 

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

* Engine mounts: 

Figures number added. 

* Engine mounts, General electric aft engine mount assembly CF6-80C2: 

Figure number amended. 

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

Figure number amended. 

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

Figure number amended. 

SUB-PART 1-3: 

* Main landing gear: 

Figures number added. 

Note (1) amended. 

Pin (Multiple link/Frame 50): 

- PNR A53833490200xx: PNR added (MOD 13384 and MOD 19639). 

- PNR A53834451200xx: PNR added. 

* Main landing gear, Barrel assembly: 

Figure number amended. 

Note (1) amended. 

Attaching fitting pin PNR C62311-200 and PNR D68529: PNR added (MOD 13453). 

Pin (Connecting rod/Upper rod) PNR C66472-200 and PNR D68528: PNR added (MOD 

13453). 

* Main landing gear, Shock absorber assembly: 

Figures number amended. 

Notes (1) and (2) amended. 

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

* Main landing gear, Linkage assembly: 

Figure number amended. 

* Main landing gear, Brace assembly: 

Figure number added. 

* Main landing gear, Brace assembly, Lock link: 

Note (1) amended. 

Lock link middle pin PNR C61485-20: Limitation amended, note (1) assigned. 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

ISSUE: SEP 05/13 ALS PART 1 HISTORY FILE PAGE: 4/5 

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

* Nose landing gear: 

Figures number added. 

Note (1) amended. 

Pintle pin: 

- PNR A32210079200xx: Limitation amended. 

- PNR A32210080200xx: Limitation applicability amended. 

- PNR A32210082200xx: PNR added (MOD 13380 and MOD 19634). 

* Nose landing gear, Telescopic strut assembly: 

Figure number amended. 

Nut (Cylinder/Locking cylinder) PNR D55955-1 and PNR D68538: PNR added (MOD 

13455), nomenclature amended. 

* Nose landing gear, Barrel assembly: 

Figure number amended. 

Note (3) amended. 

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

End fitting pin nut PNR D68062: PNR added (MOD 13212). 

End fitting pin PNR D68063: PNR added (MOD 13212). 

End fitting: 

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

(MOD 13456). 

- PNR D68076: PNR added (MOD 13212). 

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

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

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

* Main landing gear, Shock absorber assembly: 

Figures number amended. 

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

Wheel axle nut: 

- PNR C62879: Note (1) assigned. 

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

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

Upper cam PNR C62034-1 and PNR D68534: PNR added (MOD 13457). 

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

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

added (MOD 13457). 

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

Nut (S/A/Barrel) PNR C64040-1: Limitation amended, note (1) assigned. 
A300-600 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

* Engine mounts: 

Figures number added. 

* Engine mounts, General electric aft engine mount assembly CF6-80C2: 

Figure number amended. 

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

Figure number amended. 

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

Figure number amended. 

Deletions: 

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY: 

None. 

SUB-PART 1-2: 

None. 

SUB-PART 1-3: 

None.