# 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 her ein is the sole property of AIRBUS SAS. No

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

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

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

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

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

for which it is supplied.

# 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

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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

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

ALS Part 1. Variations must also be approved.

REVISION

NUMBER SUB-PARTS APPROVED BY

EASA EASA AD INSERTION IN

MAINT. PROG.

R 00 1-2

1-3 DEC 21/06 2007-0293

N 01 ROR

1-2

1-3 SEP 05/13

Note: The ALS Part 1 is covered by the Certification 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 comp ly 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 m andatory 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 withou t the help of SIL 32-118).

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

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

whichever of the special compliance times occurs first.

# A300-600 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 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/i nstallation following the date specified in the

‘Start date’ column.

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

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

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

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

# A300-600 AIRWORTHINESS LIMITATIONS SECTION

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

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

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D Sub-part 1-0 INTRODUCTION

1. GENERAL

From revision 01 and on, the content of the

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 serie s of stand-alone documents in a location

dedicated to the mandatory limitations.

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

Compliance with the requirements contained in this document is mandatory. No

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

the requirements of that ALS, unless otherwi se agreed with the Authority of the State

of aircraft registry.

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

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

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

Volume II, Part A, Chapter 3.

A. Sub-part 1-2: Life limits

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

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

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

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

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

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

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

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

1-2. R

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# A300-600 AIRWORTHINESS LIMITATIONS SECTION

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

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R R C. Traceability and repl acement requirements

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

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

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

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

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

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

Certificate of Airworthiness.

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

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

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

two scheduled revisions of the ALS Part 1.

However, it is requi red to assure traceability and moni toring of such items whatever

their detail PNR.

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

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

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

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

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

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

so that life limitations are accurately ap plied. Traceability re cords may comprise

of, but are not limited to, the following:

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

Manufacturer Serial Number, etc...),

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

repairs, inspections, etc...).

- Life accumulation (account ing for any individual aircraft to which a part may

have been fitted).

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

to the Service Information Letter (SIL) 32- 118 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 a nd 1-3 is not required

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

assembly/aircraft level).

D. Disposal/quarantine action

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

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

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

# R

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

limits to prevent rework to appear to be airworthy.

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

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

sub-part 1-3).

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

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

limitations. Examples of means are:

- Record keeping system,

- Non-permanent markings,

- Segregation (parts stored separately from those currently eligible for

installation).

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

appear to be airworthy.

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

repair limits to prevent rework to appear to be airworthy.

E. ALS Part 1 applicability

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

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

and Weight Variants (WV) or MSN listed in the tables below:

A300-600

N Aircraft series Aircraft models WV

N

A300 B4-600 A300 B4-601

00 N A300 B4-603

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. R

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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 lif e accumulated before the aircraft delivery

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

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

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

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

calendar time accumulation.

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

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

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

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

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

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

stop or performing a ‘touch and go’.

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

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

3. APPLICABILITY SYSTEM

A. General

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

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

validated for a specific individual aircraft MSN.

PNR are authorized for installation on 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 num ber within the limits of the list of aircraft

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

x4-605R stands for: A300 B4-605R, A 300 C4-605R Variant F and A300 F4-605R. R

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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 accor ding to the aircraft model affected, e.g.:

X stands for: All A300-600 models defi ned 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 on ly, defined by the applicability of the

column.

excl. B4-204 stands for: All A300-600 model s 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’ r esponsibility to refer to the applicable WV.

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

- N°145 issued by DGAC-F 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, pr ovided to the initial Operator of the

aircraft, in the delivery documentation (Aircr aft Inspection Report ‘Conformity to the

Design Standard Requirements’).

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

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

Note 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 R

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

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R 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 ai rcraft MSN defined by the ap plicability of the column,

excluding aircraft MSN XXX.

4. LIMITATION/REPLACEMENT TIME INDICATION

A. General

In computing part’s accumulated life, ca lculations must include flight hours

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

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

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

part’s initial entry into service.

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

the part’s initial entry into 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 qu oted on the same line/block of lines as the

PNR.

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

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

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

or an Alternative Method Of Compliance (AMOC).

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

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

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

Airbus for guidance.

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

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

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

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

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

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

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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 initia l Operator of the aircraft in the delivery

documentation (Aircraft Inspection Report ‘Recordable concessions’).

Note: For spare parts, restriction of life limit ation(s), if any, are indicated in EASA Form

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

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

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

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

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

approval by the relevant Airworthiness Aut hority for any necessary adaptations of the

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

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

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

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

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

associated approvals and documents indicating the necessary adaptations of

limitations have to be transferred as well.

5. TRANSFER OF PART BETWEEN AIRCRAFT APPLICATIONS

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

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

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

formula:

with:

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

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

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

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

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

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

calculation.

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

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

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

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j j

i 

# Cp Cp Ca

1Tr   

 

 

 

 

 

 

 

 

# 

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N 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 manuf actured by Airbus, detail PNR are listed in

the relevant Airbus engineering drawings/Com ponent Maintenance Manual manufacturer

(CMMm) issued by Airbus.

For landing gear and engine mount parts 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 informat ion on procurable replacement PNR, detail

PNR and applicable SB.A300-600 AIRWORTHINESSLIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 9© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.R7. LANDING GEAR LRUs APPLICABILITYA300 B4-601 XA300 B4-603 XA300 B4-620 XA300 B4-622 X XA300 C4-620 XA300 B4-605R X X X X X XA300 B4-622R X X X X XA300 C4-605R Variant F XA300 F4-605R X X XA300 F4-622R X XA300 F4-608ST X XWEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 09 10 (2) (3)MTOW165 153 170.5 171.7 171.7 167.8171.7 144 165.1 153 150 168 140 153 155MLW138 138 140 140 138 140 140 140 140.6 140 140 143.3 140 140 140MZFW130 130 130 123 123 131 130 130 133.8 130 130 136.5 130 132 133R Top assembly PNRMain Landing Gear LegD22497/8000-x X XD22497/8010-x X XD22497/8011-x XD22497/8015-x XD22497/8020-x X X X X X X X X X X X X X X XD22497/8025-x X X X X X X X X X X X XD22497/8030-x X X X X X X X X X X X X X X XD22497/8040-x X X X X X X X X X X X X X X XD22497/8145-x X XD22497/8150-x X XA300-600 AIRWORTHINESSLIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 10© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300 B4-601 XA300 B4-603 XA300 B4-620 XA300 B4-622 X XA300 C4-620 XA300 B4-605R X X X X X XA300 B4-622R X X X X XA300 C4-605R Variant F XA300 F4-605R X X XA300 F4-622R X XA300 F4-608ST X XWEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 09 10 (2) (3)MTOW165 153 170.5 171.7 171.7 167.8171.7 144 165.1 153 150 168 140 153 155MLW138 138 140 140 138 140 140 140 140.6 140 140 143.3 140 140 140MZFW130 130 130 123 123 131 130 130 133.8 130 130 136.5 130 132 133R Top assembly PNRD22497/8250-x X XD23243/4000-x X X X X X X X X X X X X X X XMain Landing Gear Brace AssemblyC23111/2010-x X X X X X X X X X X X X X X XC23111/2020-x X X X X X X X X X X X X X X XC23111/2030-x X X X X X X X X X X X X X X XMain Landing Gear Structural LinkageD22537/8000-x X XD22537/8010-x X XD22537/8015-x X X XD22537/8020-x X X X X X X X X X X X X X X XD22537/8025-x X X X X X X X X X X X X XD22537/8030-x X X X X X X X X X X X X X X XA300-600 AIRWORTHINESSLIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 11© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300 B4-601 XA300 B4-603 XA300 B4-620 XA300 B4-622 X XA300 C4-620 XA300 B4-605R X X X X X XA300 B4-622R X X X X XA300 C4-605R Variant F XA300 F4-605R X X XA300 F4-622R X XA300 F4-608ST X XWEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 09 10 (2) (3)MTOW165 153 170.5 171.7 171.7 167.8171.7 144 165.1 153 150 168 140 153 155MLW138 138 140 140 138 140 140 140 140.6 140 140 143.3 140 140 140MZFW130 130 130 123 123 131 130 130 133.8 130 130 136.5 130 132 133R Top assembly PNRNose landing Gear LegC23137010-x X XC23137020-x X X X X X X X X X X XC23137610-x X X X X X X X X X X X X XC23137620-x X X X X X X X X X X XC23137630-x X XC23137650-x X XC23137710-x X X X X X X X X X X X X XC23137720-x X X X X X X X X X X XC23137750-x X XC23137810-x X X X X X X X X X X X X XC23137820-x X X X X X X X X X X XC23137910-x X X X X X X X X X X X X XA300-600 AIRWORTHINESSLIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 12© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.A300 B4-601 XA300 B4-603 XA300 B4-620 XA300 B4-622 X XA300 C4-620 XA300 B4-605R X X X X X XA300 B4-622R X X X X XA300 C4-605R Variant F XA300 F4-605R X X XA300 F4-622R X XA300 F4-608ST X XWEIGHT VARIANT 00 08 00 01 (1) 02 (1) 03 04 05 06 07 08 09 10 (2) (3)MTOW165 153 170.5 171.7 171.7 167.8171.7 144 165.1 153 150 168 140 153 155MLW138 138 140 140 138 140 140 140 140.6 140 140 143.3 140 140 140MZFW130 130 130 123 123 131 130 130 133.8 130 130 136.5 130 132 133R Top assembly PNRC23137915-x X XC23137920-x X X X X X X X X X X XC23137950-x X XNose landing Gear Telescopic StrutC23109610-x X X X X X X X X X X X X XC23109710-x X X X X X X X X X X X X XC23109810-x X X X X X X X X X X X X XC23109915-x X XWeight variant number allocation (refer to the TypeCertificate Data Sheet DGAC-F N°145, EASA N°A.014):A300 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 AIRWORTHINESSLIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-0 PAGE: 13© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.RA300 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 A300-00-6018.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 together with WV04).Note 1: Linear variation of MZFW from 123tto 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 tank used).THE ABOVE TABLE INDICATES THE LANDING GEARLRUs THAT CAN BE INSTALLED FOR EACHAIRCRAFT MODEL WEIGHT VARIANT BUTIT DOES NOT:- ENSURE THAT A LRU PNR HAS BEEN VALIDATED FOR A SPECIFIC INDIVIDUAL AIRCRAFT MSN,- PROVIDE ANY INTERCHANGEABILITY OR MIX POSSIBILITIES.Refer to Airbus and Messier-Dowty publications (Illustrated Parts Catalogue, Service Bulletins, ComponentMaintenance Manuals, etc...) for the applicability of LRUs compared with individualaircraft MSN and forthe interchangeabilities/mixabilities of LRUs.END OF SUB-PART 1-0

# A300-600 AIRWORTHINESS LI MITATIONS SECTION

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

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

# Sub-part 1-1 ILLUSTRATIONS

Pin (Hinge arm/Barrel)

Upper torque link pin and nut

Torque link medium pin and nut

Lower torque link pin and nut Cross bars Multiple link

Pin (Drag link/Barrel/

Brace strut) Barrel

Drag link Pin (Hinge arm/

Drag link) Hinge arm

Torque links

(Upper & Lower)

Brake torque arm pin (x2)

Bogie beam pivot

pin and nut

Bogie beam Wheel axle (x2) Brace strut upper arm

Brace strut middle pin Lock link

lower arm Lock link upper

pin

Lock link

upper arm

Pin (Drag link/

Barrel) Brace strut

lower arm Lock link pin Lock link

middle pin Multiple link pin Cross bar pin (x2)

Brake torque arm (x4)



# MAIN LANDING GEAR - FIG. 01

# A300-600 AIRWORTHINESS LI MITATIONS SECTION

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

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. Gear support rib Aft pintle pin Gear support rib Fwd pick up

Ball (Fwd pintle bearing)

Half ball housing

(Fwd pintle bearing)



# MAIN LANDING GEAR - FIG. 02

# A300-600 AIRWORTHINESS LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS SECTION

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

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

Link (Fwd cross bar

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

Fwd cross bar fitting

Gear support rib



# WING STRUCTURE - FIG. 10

# A300-600 AIRWORTHINESS LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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

PylonA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE 1EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 1-2 LIFE LIMITSNote: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A300-600sPW POWERED A300-600sNomenclature Part Number FH LDG Cal.B4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 05)RBARREL ASSEMBLY (FIG. 01 & 03)Pin (Hinge arm/Barrel)C66441-21N/A 36000 N/A XN/A 55600 N/A X X X X X XUpper torque link pin C66191-20 N/A 45000 N/A XX XD56729N/A 36000 N/A XN/A 50600 N/A X X X X X XTorque link medium pinC66192-20N/A 45000 N/A XN/A 75000 N/A X X X X X XS/A connecting rodC65389-3N/A 36000 N/A XN/A 58000 N/A X X X X X XRSHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04)S/A Upper rodC65388 N/A 55800 N/A XX XD60500N/A 40000 N/A XN/A 66600 N/A X X X X XLower torque link pin C66191-20 N/A 45000 N/A XX XD56729N/A 36000 N/A XN/A 50600 N/A X X X X X XRLINKAGE ASSEMBLY (FIG. 01 & 05)Cross bar C66792 N/A 71600 N/A X X XC66792-1 N/A 74000 N/A X X XD60522N/A 41000 N/A XN/A 68300 N/A X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE 2EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A300-600sPW POWERED A300-600sNomenclature Part Number FH LDG Cal.B4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RMultiple link pinC67131-20N/A 36000 N/A XN/A 52000 N/A X X X X X XMultiple linkC66503-1N/A 42600 N/A XN/A 71000 N/A X X X X X XC66503-2N/A 42600 N/A XN/A 71000 N/A X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE 3EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A300-600sPW POWERED A300-600sNomenclature Part Number FH LDG Cal.B4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRATA 32-20-00 NOSE LANDING GEAR (FIG. 06 to 09)R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.(2) - 12000 LDG from initial entry into service: For partshaving an initial entry into service date after 30-Apr-1986.- 12000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated 9000 LDG or less on 30-Apr-1986.- 3000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated between 9000 and 14000 LDG on 30-Apr-1986.- Either 17000 LDG from initial entry into service or 2000 LDGfrom 30-Apr-1986, whichever occurs first: For parts installed on aircraft having accumulated morethan 14000 LDG on 30-Apr-1986.Pintle Pin (1) A32210001205xx N/A (2) N/A X X XRBARREL ASSEMBLY (FIG. 06)(1) Limit not applicable to A300 B4-605R WV08 and A300 F4-605R WV06.BarrelC59049-2 N/A 38100 N/A X X (1) X X X XC59049-4 N/A 38100 N/A X X (1) X X X XC59049-20 N/A 38100 N/A X X (1) X X X XC59049-25 N/A 38100 N/A X X (1) X X X XC59049-26 N/A 38100 N/A X X (1) X X X XNC59049-27 N/A 38100 N/A X X (1) X X X XC59049-40 N/A 38100 N/A X X (1) X X X XC59049-41 N/A 38100 N/A X X (1) X X X XNC59049-42 N/A 38100 N/A X X (1) X X X XC59049-45 N/A 38100 N/A X X (1) X X X XC59049-46 N/A 38100 N/A X X (1) X X X XNC59049-47 N/A 38100 N/A X X (1) X X X XD56525 N/A 38100 N/A X X X X X XD56525-1 N/A 38100 N/A X X X X X XD56525-10 N/A 38100 N/A X X X X X XND56525-11 N/A 38100 N/A X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE 4EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A300-600sPW POWERED A300-600sNomenclature Part Number FH LDG Cal.B4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RTurning tube C59050-4 N/A 17000 N/A X X XC59050-20 N/A 17000 N/A X X XRSHOCK ABSORBER ASSEMBLY (FIG. 07 & 08)(1) - For the first accomplishment, replace the bottom before accumulation of 24000 LDG since the initial entry into service, or within 12000 LDG after 10-Apr-1993,whichever occurs later, but without exceeding a total of 36000LDG since the initial entry intoservice. The stated limits apply to the NLG itself, and not to theassociated aircraft.- For the subsequent accomplishments, replace the bottom beforeaccumulation of 24000 LDG since initial entry into service. The stated limit applies to the detailpart and not to the associated NLG.BottomC62037-1 N/A (1) N/A X X X X X X XND68531 N/A (1) N/A X X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE 5EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A300-600sPW POWERED A300-600sNomenclature Part Number FH FC Cal.B4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRATA 71-20-00 ENGINE MOUNTS (FIG. 12 to 14)RGENERAL 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 visitafter 28-Aug-2000, or before accumulation of 29000 Engine Cyclessince the initial entry into service,whichever occurs first. Refer to FAA AD 2000-12-08.Shear bolt (Outer,Link/Lower beam)9380M75P01 N/A N/A (1) X X XShear bolt (Inner, RHlink/Lower beam)9380M80P01 N/A N/A (1) X X XLink (LH)9348M79P01 N/A (2) (2) X X XLink (RH)9348M84P01 N/A (2) (2) X X XShear bolt(Link/Engine)9380M73P01 N/A N/A (1) X X XRPRATT & 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 after 31-Dec-2005, provided 58000 FCare not exceeded. The life the part accumulated before the lastengine installation date must be calculated in accordance withthe methodology described in theSIL 71-039. It must be added to the actual life accumulated since the last engine installation date. The total must not exceed58000 FC at any time.Bolt (Link/Fan case) 221-0251-503 N/A (1) (1)X X X XBolt (Link/Cross beam) 221-0251-503 N/A (1) (1)X221-0251-505 N/A (1) (1)X X X X221-0251-507 N/A (1) (1)X X X XCross beam221-0242-5 N/A 20000 N/AXBolt (Cross beam/Mainbeam)221-0251-501 N/A (1) (1)X X X XMain beam221-0241-5 N/A 20000 N/AX221-0241-9 N/A 20000 N/AX X X X221-4005-1 N/A 20000 N/AX X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-2 PAGE 6EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.LIFE LIMITS (*)LIFE LIMITS APPLICABILITYNotes are located under the assy title.GE POWERED A300-600sPW POWERED A300-600sNomenclature Part Number FH FC Cal.B4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RShear pin221-0252-501 N/A (1) (1)X X X X221-0252-503 N/A (1) (1)X X X XRPRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 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 after 31-Dec-2005, provided 52500 FCare not exceeded. The life the part accumulated before the lastengine installation date must be calculated in accordance withthe methodology described in theSIL 71-039. It must be added to the actual life accumulated since the last engine installation date. The total must not exceed52500 FC at any time.Pin (Link/Main beam) 221-0264-501 N/A (1) (1)X X X XBolt (Mid link/Engine) 80876-20-4 N/A (1) (1)X X X XBolt (Side link/Engine)80876-20-3 N/A (1) (1)X X X XEND OF SUB-PART 1-2A300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 1EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Sub-part 1-3 DEMONSTRATED FATIGUE LIVESNote: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 05)R (1) ‘xx’ at the end of the PNR stands for anynumber between 00 and 99, including unused digits.N Aft pintle pin (1)A32140057202xxN/A 46000 XNN/A 76600 X X X X X XNA32140057204xxN/A 46000 XNN/A 76600 X X X X X XNA32140063000xxN/A 46000 XNN/A 76600 X X X X X XNA32140063002xxN/A 46000 XNN/A 76600 X X X X X XNHalf ball housing (Fwdpintle bearing) (1)A32140042200xxN/A 46000 XNN/A 76600 X X X X X XNA32140042202xxN/A 46000 XNN/A 76600 X X X X X XNA32140069002xxN/A 46000 XNN/A 76600 X X X X X XNA32140069004xxN/A 46000 XNN/A 76600 X X X X X XNA32140077002xxN/A 46000 XNN/A 76600 X X X X X XNA32140077004xxN/A 46000 XN .../...N/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 2EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RNHalf ball housing (Fwdpintle bearing) (1)A32140077008xxN/A 46000 XNN/A 76600 X X X X X XNA32140077010xxN/A 46000 XNN/A 76600 X X X X X XNBall (Fwd pintle bearing)(1)A32140043202xxN/A 46000 XNN/A 76600 X X X X X XNA32140074200xxN/A 46000 XNN/A 76600 X X X X X XNPin (Multiple link/Frame50) (1)A53833490200xxN/A 46000 XNN/A 76600 X X X X X XNA53834451200xxN/A 46000 XNN/A 76600 X X X X X XA53834451202xxN/A 46000 XN/A 76600 X X X X X XRBARREL ASSEMBLY (FIG. 01 & 03)RRR(1) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performingmaintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same pin and neither the pin northe nut accumulates time in service during theperiod between the removal and reinstallation.CageC66208N/A 46000 XN/A 76600 X X X X X XEye fittingC65382-5N/A 46000 XN/A 76600 X X X X X XD64926N/A 46000 XN/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 3EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RBarrelC65380-19 N/A 76600 X X XC65380-21 N/A 76600 X X XD56520-1N/A 46000 XN/A 76600 X X X X X XD56520-3N/A 46000 XN/A 76600 X X X X X XD64927N/A 46000 XN/A 76600 X X X X X XD64927-10N/A 46000 XN/A 76600 X X X X X XUpper torque link pin nut SL40123P N/A (1) X X X X X X XTorque links (Upper &Lower)C65386-7 N/A 76600 X X XD56521-1N/A 46000 XN/A 76600 X X X X X XTorque link medium pin nutSL40132P N/A (1) X X X X X X XPin (Drag link/Barrel)C66444-20N/A 46000 XN/A 76600 X X X X X XDrag linkC65383-5N/A 46000 XN/A 76600 X X X X X XC65383-13N/A 46000 XN/A 76600 X X X X X XPin (Drag link/Barrel/Bracestrut)C66443-20N/A 46000 XN/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 4EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RPin (Hinge arm/Drag link) C66442-20 N/A 76600 XX XD60499N/A 46000 XN/A 76600 X X X X X XHingearm C65381-7 N/A 76600 X X XD57739-1N/A 46000 XN/A 76600 X X X X X XAttaching fitting pinC62311-20N/A 46000 XN/A 76600 X X X X X XNC62311-200N/A 46000 XNN/A 76600 X X X X X XND68529N/A 46000 XNN/A 76600 X X X X X XAttaching fitting (LH)D51421N/A 46000 XN/A 76600 X X X X X XD51421-1N/A 46000 XN/A 76600 X X X X X XAttaching fitting (RH)D51422N/A 46000 XN/A 76600 X X X X X XD51422-1N/A 46000 XN/A 76600 X X X X X XPin (Connecting rod/Upperrod)C66472-20N/A 46000 XN/A 76600 X X X X X XNC66472-200N/A 46000 XN .../...N/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 5EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RNPin (Connecting rod/Upperrod)D68528N/A 46000 XNN/A 76600 X X X X X XRSHOCK ABSORBER ASSEMBLY (FIG. 01, 03 & 04)R (1) PNR CRA50551 applies to nuts used for repaired bogie beam pivot pins.RRR(2) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performingmaintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same pin and neither the pin northe nut accumulates time in service during theperiod between the removal and reinstallation.S/ASlidingrod C65384-13 N/A 76600 X X XC65384-21N/A 46000 XN/A 76600 X X X X X XD64922N/A 46000 XN/A 76600 X X X X X XEnd fittingC61643-10N/A 46000 XN/A 76600 X X X X X XC61643-11N/A 46000 XN/A 76600 X X X X X XLower torque link pin nut SL40123P N/A (2) X X X X X X XBrake torque arm pinD55709 N/A 76600 XX XND55709-1 N/A 76600 X X XD60501N/A 46000 XN/A 76600 X X X X X XBraketorquearm C66434-30 N/A 76600 X X XD60502N/A 46000 XN/A 76600 X X X X X XD61200N/A 46000 XN/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 6EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RBogie beam pivot pin C66194-20 N/A 76600 XX XD60503N/A 46000 XN/A 76600 X X X X X XD61201N/A 46000 XN/A 76600 X X X X X XD64921N/A 46000 XN/A 76600 X X X X X XBogie beam pivot pin nutCRA50551 (1)N/A 46000 XN/A 76600 X X X X X XSL40054P N/A (2) X X X X X X XBOGIE BEAM ASSEMBLY (FIG. 01)Bogiebeam C65385-15 N/A 76600 X X XD56731-1 N/A 76600 X X XD60504-1N/A 46000 XN/A 76600 X X X X X XD60504-3N/A 46000 XN/A 76600 X X X X X XD61198-1N/A 46000 XN/A 76600 X X X X X XD64920N/A 46000 XN/A 76600 X X X X X XWheelaxle D56625-1 N/A 76600 X X XD60505-1N/A 46000 X.../...N/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 7EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RWheel axleD61199-1N/A 46000 XN/A 76600 X X X X X XRLINKAGE ASSEMBLY (FIG. 01 & 05)Cross bar pinC67676-20N/A 46000 XN/A 76600 X X X X X XRBRACE ASSEMBLY (FIG. 01)BRACE STRUT (FIG. 01)Brace strut upper armC66504-2N/A 46000 XN/A 76600 X X X X X XBrace strut middle pinC68400-20N/A 46000 XN/A 76600 X X X X X XBrace strut lower armC65606-3N/A 46000 XN/A 76600 X X X X X XLock link pinC62314-30N/A 46000 XN/A 76600 X X X X X XLOCK LINK (FIG. 01)RRR(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 pinis temporarily removed and reinstalledfor the purpose of performing maintenance outside a workshop,no replacement is required provided the pin’s removal and reinstallation are performed on thesame lock link lower arm and neither the lower arm nor the pinaccumulates time in service during the period between the removal and reinstallation.Lock link lower armC69426N/A 46000 XN/A 76600 X X X X X XLock link middle pinC61485-20 N/A (1) X X X X X X XLock link upper armC65608N/A 46000 XN/A 76600 X X X X X XLock link upper pinC62315-30N/A 46000 XN/A 76600 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 8EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRATA 32-20-00 NOSE LANDING GEAR (FIG. 06 to 09)R (1) ‘xx’ at the end of the PNR stands for anynumber between 00 and 99, including unused digits.N Pintle pin (1)A32210079200xxN/A 50000 XRN/A 61150 X B4 X X XRA32210080200xx N/A 61150 X X X X X XNA32210082200xxN/A 50000 XNN/A 61150 X X X X X XRTELESCOPIC STRUT ASSEMBLY (FIG. 09)End fitting pinD55951N/A 50000 XN/A 65700 X X X X X XEnd fittingD55962N/A 50000 XN/A 65700 X X X X X XCylinderD55954N/A 50000 XN/A 65700 X X X X X XRNut (Cylinder/Lockingcylinder)D55955N/A 50000 XN/A 65700 X X X X X XND55955-1N/A 50000 XNN/A 65700 X X X X X XND68538N/A 50000 XNN/A 65700 X X X X X XLocking cylinderC61373-3N/A 65700 X X X X X XC61373-4N/A 50000 XN/A 65700 X X X X X XC61373-6N/A 50000 X.../...N/A 65700 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 9EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RLocking cylinderC61373-7N/A 50000 XN/A 65700 X X X X X XC61373-40 N/A 65700 X X X X X XD63091N/A 50000 XN/A 65700 X X X X X XD63091-1N/A 50000 XN/A 65700 X X X X X XLocking sleeveC61389-1N/A 50000 XN/A 65700 X X X X X XLock clawD55952N/A 50000 XN/A 65700 X X X X X XLocking pistonC68483-1N/A 50000 XN/A 65700 X X X X X XC68483-2N/A 50000 XN/A 65700 X X X X X XC68483-3N/A 50000 XN/A 65700 X X X X X XC68483-4N/A 50000 XN/A 65700 X X X X X XD63282N/A 50000 XN/A 65700 X X X X X XRodD55953-1 N/A 65700 X X X X X XD55953-2 N/A 65700 X X X X X X.../...D57050 N/A 65700 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 10EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRodD57050-1N/A 50000 XN/A 65700 X X X X X XRBARREL 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 oneevery time it is removed from the barrel.RRR(3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performingmaintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same pin and neither the pin northe nut accumulates time in service during theperiod between the removal and reinstallation.Pin (Clevis/Telescopicstrut)C62231-20 N/A 65700 X X (1) X X X XD56530N/A 50000 XN/A 65700 X X X X X XClevisC62002-2 N/A 65700 X X (1) X X X XD56527N/A 50000 XN/A 65700 X X X X X XLower pin (Link/Clevis)C62268-20N/A 50000 XN/A 65700 X X X X X XNC62268-200N/A 50000 XNN/A 65700 X X X X X XND68541N/A 50000 XNN/A 65700 X X X X X XLink (Clevis/Barrel)C62230-1 N/A 65700 X X (1)X X X XNC62230-10 N/A 65700 X X (1) X X X XD56526N/A 50000 X.../...N/A 65700 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 11EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RN Link (Clevis/Barrel)D56526-1N/A 50000 XNN/A 65700 X X X X X XND68539 N/A 65700 X X (1) X X X XND68540N/A 50000 XNN/A 65700 X X X X X XUpper pin (Link/Barrel)C62267-20N/A 50000 XN/A 65700 X X X X X XNC62267-200N/A 50000 XNN/A 65700 X X X X X XND68544N/A 50000 XNN/A 65700 X X X X X XPin (Clevis/Barrel)C62229-20 N/A 65700 X X (1)X X X XD56528N/A 50000 XN/A 65700 X X X X X XBarrelD59448 N/A 65700 X X X X X XD59448-1 N/A 65700 X X X X X XD59448-10 N/A 65700 X X X X X XD61185 N/A 65700 X X X X X XD61185-10 N/A 65700 X X X X X XD61553N/A 50000 XN/A 65700 X X X X X XD61661 N/A 65700 X X X X X XPin (Barrel/Airframe)C62228-20N/A 50000 XN/A 65700 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 12EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RN End fitting pin nutD68062 N/A (2) X X X X X X XMS17825-6 N/A (2) X X X X X X XEnd fitting pinAN6-17 N/A (2) X X X X X X XD61183 N/A (2) X X X X X XND68063 N/A (2) X X X X X X XNAS1306-22D N/A (2) X X X X X XEnd fittingC62032 N/A 65700 X X X X X XC62032-1 N/A 65700 X X X X X XNC62032-2 N/A 65700 X X X X X XNC62032-10 N/A 65700 X X X X X XD61184N/A 50000 XN/A 65700 X X X X X XND61184-1N/A 50000 XNN/A 65700 X X X X X XND68076N/A 50000 XNN/A 65700 X X X X X XND68695N/A 50000 XNN/A 65700 X X X X X XRackC61453-1 N/A 65700 X X XNC61453-15 N/A 65700 X X XC61453-20 N/A 65700 X X XC61453-40N/A 50000 XN/A 65700 X X X X X XC61453-41N/A 50000 X.../...N/A 65700 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 13EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RN RackC61453-205 N/A 65700 X X XTurning tubeC59050-30 N/A 65700 X X (1)X X X XC59050-40 N/A 65700 X X (1) X X X XC59050-50N/A 50000 XN/A 65700 X X X X X XC59050-60N/A 50000 XN/A 65700 X X X X X XTorque link pin (Upper &Lower)C62223-20N/A 50000 XN/A 65700 X X X X X XTorque link (Upper &Lower)C59562-2N/A 50000 XN/A 65700 X X X X X XC59562-3N/A 50000 XN/A 65700 X X X X X XC59562-4N/A 50000 XN/A 65700 X X X X X XNC59562-20N/A 50000 XNN/A 65700 X X X X X XTorque link medium pinC62041-20N/A 50000 XN/A 65700 X X X X X XNC62041-200N/A 50000 XNN/A 65700 X X X X X XD53431-20N/A 50000 XN/A 65700 X X X X X XTorque link medium pin nut SL40110P N/A (3) X X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 14EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRSHOCK ABSORBER ASSEMBLY (FIG. 07 & 08)RRR(1) The nut must be replaced by a new one every time it is removed from the assembly. When the nut is temporarily removed andreinstalled for the purpose ofperforming maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same assembly andneither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation.R (2) Part must be replaced by a new one 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.Wheelaxle C59053-4 N/A 65700 X X XC59053-21N/A 50000 XN/A 65700 X X X X X XR Wheel axle nut C62879 N/A (1) X X X X X X XNC62879-1 N/A (1) X X X X X X XND68537 N/A (1) X X X X X X XSliding RodC59051-3N/A 50000 XN/A 65700 X X X X X XC59051-21N/A 50000 XN/A 65700 X X X X X XR Upper cam dowelC62270 N/A (2) X X X X X X XUpper camC62034-1N/A 50000 XN/A 65700 X X X X X XNC62034-10N/A 50000 XNN/A 65700 X X X X X XND68534N/A 50000 XNN/A 65700 X X X X X XLower camC62035N/A 50000 X.../...N/A 65700 X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 15EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RN Lower camC62035-1N/A 50000 XNN/A 65700 X X X X X XND68532N/A 50000 XNN/A 65700 X X X X X XRestrictorC67863-1 N/A 65700 X X X X X XC67863-2N/A 50000 XN/A 65700 X X X X X XC67863-4N/A 50000 XN/A 65700 X X X X X XNC67863-10 N/A 65700 X X X X X XNC67863-20N/A 50000 XNN/A 65700 X X X X X XNC67863-40N/A 50000 XNN/A 65700 X X X X X XND68536N/A 50000 XNN/A 65700 X X X X X XR Lower cam dowelC62866 N/A (3) X X X X X X XUpper RodC59052-2N/A 50000 XN/A 65700 X X X X X XR Nut (S/A/Barrel) C64040-1 N/A (1) X X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 16EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RNATA 57-00-00 WING STRUCTURE (FIG. 10 & 11)NMAIN LANDING GEAR SUPPORT RIB ASSEMBLY AND ASSOCIATED FITTINGS (FIG. 10)N (1) This item is not transferable from an aircraft toanother: Traceability at aircraft level is authorized.N (2) ‘xx’ at the end of the PNR stands for anynumber 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.NGear support rib (LH)(1) (2)A57240810214xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNA57240810216xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XNA57240810218xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XNGear support rib (RH)(1) (2)A57240810215xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNA57240810217xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XNA57240810219xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 17EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RN Fwd pick up (LH) (1) (2)A57242391000xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XN Fwd pick up (RH) (1) (2)A57242391001xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XNAft cross bar fitting (LH)(1) (2)A57240806004xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNAft cross bar fitting (RH)(1) (2)A57240806005xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNFwd cross bar fitting (LH)(1) (2)A57240808004xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNFwd cross bar fitting (RH)(1) (2)A57240808005xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNLink (Fwd cross bar fitting/Gear support rib) (1) (2)A57242386204xxN/A 30000 F4 (3) X XN N/A42500C4/F4(4)C4NN/A 51000 X B4 B4 X XNA57242386206xxN/A 30000 F4 (3) X XNN/A 42500 C4/F4 (4) C4NN/A 51000 X B4 B4 X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 18EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH LDGB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RNFLAPS 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 anynumber between 00 and 99, including unused digits.N Special bolt (2)A57940357200xx N/A (1) X X X X X X XNA57940357202xx N/A (1) X X X X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 19EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH FCB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622RRATA 71-20-00 ENGINE MOUNTS (FIG. 12 to 14)RGENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY CF6-80C2 (FIG. 12)Shear bolt (Outer,Link/Lower beam)9380M75P02N/A 36800 XN/A64000XXShear bolt (Inner, RHlink/Lower beam)9380M80P02N/A 36800 XN/A64000XXLink (LH)1846M23P01N/A 36800 XN/A 50000 X XLink (RH)9348M84P02N/A 36800 XN/A 80000 X XShear bolt (Link/Engine)9380M73P02N/A 36800 XN/A 64000 X XRPRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 13)Bolt (Link/Fan case) 221-0251-511 N/A 40000X X X XTrust link221-0245-5 N/A 40000X X X X221-0245-9 N/A 40000X X X X221-0245-13 N/A 40000X X X XBolt (Link/Cross beam) 221-0251-515 N/A 40000X X X XCross beam221-4004-1 N/A 40000X X X X221-4004-5 N/A 40000X X X XBolt (Cross beam/Mainbeam)221-0251-509 N/A 40000X X X XMain beam221-4006-3 N/A 40000X X X X221-4006-5 N/A 40000X X X XShear pin221-0252-507 N/A 40000X X X XA300-600 AIRWORTHINESS LIMITATIONS SECTIONISSUE: SEP 05/13 ALS PART 1-3 PAGE 20EASA APPROVED© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document.Note: Explanations on the applicability system are provided in sub-part 1-0 paragraph 3.(*) Whichever occurs first.DEMONSTRATEDFATIGUE LIVES (*)DEMONSTRATED FATIGUE LIVES APPLICABILITYNotes are located under the assy title.GE POWERED A300-600s PW POWERED A300-600sNomenclaturePart Number FH FCB4-601B4-603x4-605R F4-608STB4-620C4-620B4-622 B4-622R F4-622ROuter support221-0243-501 N/A 40000XInner support221-0244-501 N/A 40000X221-0244-503 N/A 40000XSupport221-4047-505 N/A 40000X X X221-4047-507 N/A 40000X X XRPRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 14)Main beam221-0261-9 N/A 40000X X X X221-0261-11 N/A 40000X X X X221-0261-15 N/A 40000X X X XPin (Link/Main beam) 221-0264-503 N/A 40000X X X XLink221-0262-5 N/A 40000X221-0262-7 N/A 40000X X X XBolt (Mid link/Engine) 80876-20-6 N/A 40000X X X XBolt (Side link/Engine) 80876-20-5 N/A 40000X X X XEND OF SUB-PART 1-3

# A300-600 AIRWORTHINESS LI MITATIONS 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 limit ations 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). Th is 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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 LI MITATIONS 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.