A310 AIRWORTHINESS LIMITATIONS SECTION 

REVISION: 01 

ALS Part 1 

- 

Safe Life 

Airworthiness Limitation Items 

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

This document and all information contained 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. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

LIST OF EFFECTIVE PAGES 

PART MVT PAGE ISSUE PART MVT PAGE ISSUE

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

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

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A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

TABLE OF CONTENTS 

SUBJECT PART 

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

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

N RECORD OF REVISIONS ROR 

INTRODUCTION 1-0 

ILLUSTRATIONS 1-1 

LIFE LIMITS 1-2 

DEMONSTRATED FATIGUE LIVES 1-3 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

RECORD OF REVISIONS 

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

EASA APPROVED 

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

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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 Document 00X0500M091/M41. 

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

REVISION 01 COMPLIANCE TIME: 

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

limitations defined in the A310 ALS Part 1 revision 01. 

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

airworthiness limitations defined, either: 

- In the A310 ALS Part 1 at revision 00, 

or, 

- In the A310 ALS Part 1 at revision 01. 

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

table of this ROR: 

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

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

demonstrated (with or 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. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

RECORD OF REVISIONS 

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

EASA APPROVED 

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

N Designation PNR Start date Compliance time 

N LDG CAL 

N Main Landing Gear

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

N A32140108202xx 05-Sep-2013 18000 9 years 

N A32140128000xx 05-Sep-2013 18000 9 years 

N A32140128002xx 05-Sep-2013 18000 9 years 

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

N A32140101201xx 05-Sep-2013 18000 9 years 

N A32140130002xx 05-Sep-2013 18000 9 years 

N A32140130003xx 05-Sep-2013 18000 9 years 

N A32140132006xx 05-Sep-2013 18000 9 years 

N A32140132007xx 05-Sep-2013 18000 9 years 

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

N A32140131200xx 05-Sep-2013 18000 9 years 

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

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

N MLG Barrel assembly

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

N MLG Shock absorber assembly

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

N Nose Landing Gear

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

N NLG Telescopic strut assembly

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

N D55955 25-Apr-2007 13500 9 years 

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

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

N NLG Barrel assembly

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

N D56530 25-Apr-2007 13500 9 years 

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

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

N D56526 25-Apr-2007 13500 9 years 

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

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

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

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

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

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

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

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

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

 

 

 

 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

RECORD OF REVISIONS 

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

EASA APPROVED 

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

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N Designation PNR Start date Compliance time 

N LDG CAL 

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

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

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

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

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

N NLG Shock absorber assembly

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

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

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

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

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

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

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

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

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

‘Start date’ column. 

(2) Replace by a new one at first nut removal/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. 
A310 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 

A310 Maintenance Planning Document 

Section 9-1 

Life Limit/Monitored parts 

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

A310 Airworthiness Limitations Section 

Part 1 

Safe Life Airworthiness Limitation Items 

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

Overhaul Organizations (MRO) with a 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 the aircraft registry. 

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

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

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

Volume II, Part A, Chapter 3. 

A. Sub-part 1-2: Life limits 

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

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

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

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

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

For these parts, the life limitation provided (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. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

limits to prevent rework to appear to be airworthy. 

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

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

sub-part 1-3). 

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

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

limitations. Examples of means are: 

- Record keeping system, 

- Non-permanent markings, 

- Segregation (parts stored separately from those currently eligible for 

installation). 

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

appear to be airworthy. 

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

repair limits to prevent rework to appear to be airworthy. 

E. ALS Part 1 applicability 

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

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

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

N Aircraft series Aircraft models WV 

N 

A310-200 

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

N A310-204 101, 104, 107 

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

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

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

N 

A310-300 

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

N A310-308 05, 08, 09, 13 

N A310-322 00, 01, 03 

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

N A310-325 08 

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

refer to the relevant Engine Manufacturer Chapter 05 manual. 

2. DEFINITIONS 

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

first flight for which it will undertake its intended function. 

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

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

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

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A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

Calendar times (Cal.): 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 model number, it stands for any number within the limits of the list of models given 

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

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

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

X stands for: All A310 models defined by the applicability of the column. 

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

column. 

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

applicability of the column. 

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

applicability of the column. 

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

except the model A310-204. 

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A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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

C. Weight variant applicability 

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

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

paragraph 1.E. of this sub-part. 

It is Operators’ 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 the DGAC-F, together with the associated modification 

configuration(s). 

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

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

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

Design Standard Requirements’). 

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

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

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

associated to the approved WV. 

D. Aircraft Manufacturer Serial Number effectivity: 

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). 

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A310 AIRWORTHINESS LIMITATIONS SECTION 

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B. ALS Part 1 life limitations 

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

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

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

PNR. 

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

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

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

or an Alternative Method Of Compliance (AMOC). 

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

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

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

Airbus for guidance. 

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

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

repair solution/AV/AMOC. Occasionally, repair solutions/AV/AMOC are evaluated on 

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

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

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

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

documentation (Aircraft Inspection Report ‘Recordable concessions’). 

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

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

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

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

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

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

approval by the relevant Airworthiness Authority for any necessary adaptations of the 

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

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

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

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

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

associated approvals and documents indicating the necessary adaptations of 

limitations have to be transferred as well. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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5. TRANSFER OF PART BETWEEN AIRCRAFT APPLICATIONS 

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

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

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

formula: 

with: 

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

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

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

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

Note 1: When using the above formula, Tri, Caj, Cpj, Cpi are expressed in the same usage 

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

calculation. 

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

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

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

6. ASSOCIATED TECHNICAL DOCUMENTATION 

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

Illustrated Parts Catalogue (IPC) issued by Airbus. 

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

the relevant Airbus engineering drawings/Component Maintenance Manual manufacturer 

(CMMm) issued by Airbus. 

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

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

vendors. 

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

PNR and applicable SB. 

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A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

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7. LANDING GEAR LRUs APPLICABILITY 

A. A310-200/-200C series installations 

 A310-203 X X X X X X  A310-203C X X  A310-204  A310-221 X X X X X 

R A310-222 X X X X R WEIGHT VARIANT 00 01 03 04 06 07 08 11 

 MTOW 132 138.6 125 142 135 132 138.6 144  MLW 118.5 121.5 118.5 121.5 118.5 119.5 122 121.5  MZFW 108.5 111.5 108.5 111.5 111.5 111.5 112 111.5 

R Top assembly PNR 

Main Landing Gear Leg 

 D22121/2000-xx X X X X  D22121/2001-xx X -203  D22121/2005-1xx -203 -203/3C -203 -203 X X  D22121/2005-xx X X X  D22121/2010-xx X X -221 X X X  D22121/2011-xx X -221 -203 -203/-222  D22121/2015-xx X X X X X X X  D22121/2020-xx X X X X X X X X  D22121/2021-xx X -221 -203 -203/-222  D22121/2025-xx X X X X X X X  D22121/2030-xx X X X X X X X X  D22121/2035-xx X X X X X X X X  D22121/2300-xx X X X X X X X X  D22121/2305-xx X X X X X X X X 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

 A310-203 X X X X X X  A310-203C X X  A310-204  A310-221 X X X X X 

R A310-222 X X X X R WEIGHT VARIANT 00 01 03 04 06 07 08 11 

 MTOW 132 138.6 125 142 135 132 138.6 144  MLW 118.5 121.5 118.5 121.5 118.5 119.5 122 121.5  MZFW 108.5 111.5 108.5 111.5 111.5 111.5 112 111.5 

R Top assembly PNR R D22121/2350-xx NOT AUTHORIZED 

 D22121/2400-x X X X X X X X X  D22121/2405-x X X X X X X X X 

R D22121/2450-x NOT AUTHORIZED 

 D22121/2500-1x X X X X X X X X  D22121/2505-1x X X X X X X X X 

Main Landing Gear Brace Assembly 

 D22129/30000-x X -203/3C X -203/3C X X X  D22129/30010-x X X -221 X X X  D22129/30300-x X X X X X X X X  D22129/30400 X X X X X X X X 

Main Landing Gear Structural Linkage 

 D22139/40000-x X X X  D22139/40010-x X X -221 X X X  D22139/40020-10x -203 203/3C -203 -203/3C X X  D22139/40020-x X X  D22139/40030-x X X X X X X X  D22139/40300-x X X X X X X X X  D22139/40305-x X X X X X X X X 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

 A310-203 X X X X X X  A310-203C X X  A310-204  A310-221 X X X X X 

R A310-222 X X X X R WEIGHT VARIANT 00 01 03 04 06 07 08 11 

 MTOW 132 138.6 125 142 135 132 138.6 144  MLW 118.5 121.5 118.5 121.5 118.5 119.5 122 121.5  MZFW 108.5 111.5 108.5 111.5 111.5 111.5 112 111.5 

R Top assembly PNR 

 D22139/40400 X X X X X X X X  D22139/40405-x X X X X X X X X 

Nose Landing Gear Leg 

R C23137002-x NOT AUTHORIZED R C23137003-x NOT AUTHORIZED 

 C23137010-x X X X X X X X X  C23137020-x X X X X X X X  C23137030-x X -221 -203 -203/-222  C23137310-x X X X X X X X X  C23137320-x X X X X X X X X 

R C23137350-x NOT AUTHORIZED 

 C23137610-x X X X X X X X X  C23137620-x X X X X X X X  C23137630-x X -221 -203 -203/-222 

R C23137650-x NOT AUTHORIZED 

 C23137710-x X X X X X X X X  C23137720-x X X X X X X X X 

R C23137750-x NOT AUTHORIZED 

 C23137810-x X X X X X X X X 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

R R 

 A310-203 X X X X X X  A310-203C X X  A310-204  A310-221 X X X X X 

R A310-222 X X X X R WEIGHT VARIANT 00 01 03 04 06 07 08 11 

 MTOW 132 138.6 125 142 135 132 138.6 144  MLW 118.5 121.5 118.5 121.5 118.5 119.5 122 121.5  MZFW 108.5 111.5 108.5 111.5 111.5 111.5 112 111.5 

R Top assembly PNR 

 C23137820-x X X X X X X X X  C23137910-x X X X X X X X X 

R C23137915-x NOT AUTHORIZED 

 C23137920-x X X X X X X X X 

R C23137950-x NOT AUTHORIZED 

Nose Landing Gear Telescopic Strut 

 C23037-xxxx (*) X X X X X X X X  C23109-xxxx (**) X X X X X X X X  C23109x10-xxxx X X X X X X X X 

R C23109915-x NOT AUTHORIZED 

Notes: Telescopic strut PRE VSB 470-32-055/FAM 51 ‘Replacement of visual indicator by a mechanical in

(*) Except PNR C23037-2, PNR C23037-2-1, PNR C23037-2-2 and PNR C23037-3. (**) Except PNR C23109 and PNR C23109-0-x. 

Weight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet N°145): 

WV00: Basic aircraft or POST SB A310-00-2025. WV01: Aircraft POST MOD 03703 or POST SB A310-00-2003. WV03: Aircraft POST MOD 04008. WV04: Aircraft POST MOD 05124 or POST SB A310-00-2002 or POST MOD 11992 or POST SB A310-0WV06: Aircraft POST MOD 06395. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

R 

WV07: Aircraft POST MOD 06764 or POST SB A310-00-2006. 

WV08: Aircraft POST MOD 07415. WV11: Aircraft POST MOD 10685 or POST SB A310-00-2024. WV101: Aircraft POST MOD 06527 or POST SB A310-00-2008. WV104: Aircraft POST MOD 06528 or POST SB A310-00-2015. WV107: Aircraft POST MOD 07290. 

THE ABOVE TABLE INDICATES THE LANDING GEAR LRUs THAT HAVE BEEN C

EACH 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 aircra

the interchangeabilities/mixabilities of LRUs. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

R B. A310-300 series installations 

 A310-304 X X X X X X X 

R A310-308 X X 

 A310-322 X X X  A310-324 X X X X  A310-325 X 

R WEIGHT VARIANT 00 01 03 04 05 06 07 08 R MTOW 150 153 153 142 157 138.6 134 164 R MLW 123 123 124 123 124 123 124 124 R MZFW 113 113 114 113 114 113 114 114 R Top assembly PNR 

Main Landing Gear Leg 

R D22121/2000-xx NOT AUTHORIZED R D22121/2001-xx NOT AUTHORIZED R D22121/2005-1xx NOT AUTHORIZED R D22121/2005-xx NOT AUTHORIZED R D22121/2010-xx NOT AUTHORIZED R D22121/2011-xx NOT AUTHORIZED R D22121/2015-xx NOT AUTHORIZED R D22121/2020-xx NOT AUTHORIZED R D22121/2021-xx NOT AUTHORIZED R D22121/2025-xx NOT AUTHORIZED R D22121/2030-xx NOT AUTHORIZED R D22121/2035-xx NOT AUTHORIZED 

 D22121/2300-xx X X X X X X X  D22121/2305-xx X X X X X X X  D22121/2350-xx -304 -304 X excl. -324 X 

R D22121/2400-x X X X X X X X X 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

 A310-304 X X X X X X X 

R A310-308 X X 

 A310-322 X X X  A310-324 X X X X  A310-325 X 

R WEIGHT VARIANT 00 01 03 04 05 06 07 08 R MTOW 150 153 153 142 157 138.6 134 164 R MLW 123 123 124 123 124 123 124 124 R MZFW 113 113 114 113 114 113 114 114 R Top assembly PNR R D22121/2405-x X X X X X X X X R D22121/2450-x -304 -304 -304 X excl. -324 X X -308 

 D22121/2500-1x X X X X X X X  D22121/2505-1x X X X X X X X 

Main Landing Gear Brace Assembly 

R D22129/30000-x NOT AUTHORIZED R D22129/30010-x NOT AUTHORIZED 

 D22129/30300-x X X X X X X X 

R D22129/30400 X X X X X X X X 

Main Landing Gear Structural Linkage 

R D22139/40000-x NOT AUTHORIZED R D22139/40010-x NOT AUTHORIZED R D22139/40020-10x NOT AUTHORIZED R D22139/40020-x NOT AUTHORIZED R D22139/40030-x NOT AUTHORIZED 

 D22139/40300-x X X X X X X X  D22139/40305-x X X X X X X X 

R D22139/40400 X X X X X X X X R D22139/40405-x X X X X X X X X 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

 A310-304 X X X X X X X 

R A310-308 X X 

 A310-322 X X X  A310-324 X X X X  A310-325 X 

R WEIGHT VARIANT 00 01 03 04 05 06 07 08 R MTOW 150 153 153 142 157 138.6 134 164 R MLW 123 123 124 123 124 123 124 124 R MZFW 113 113 114 113 114 113 114 114 R Top assembly PNR 

Nose Landing Gear Leg 

R C23137002-x NOT AUTHORIZED R C23137003-x NOT AUTHORIZED R C23137010-x (!) X X X X X X X X R C23137020-x (!) X X X X X X X X R C23137030-x NOT AUTHORIZED R C23137310-x (!) X X X X X X X X R C23137320-x (!) X X X X X X X X R C23137350-x (!) -304 -304 -304 X excl. -324 X X -308 R C23137610-x X X X X X X X X R C23137620-x X X X X X X X X R C23137630-x NOT AUTHORIZED R C23137650-x -304 -304 -304 X excl. -324 X X -308 R C23137710-x X X X X X X X X R C23137720-x X X X X X X X X R C23137750-x -304 -304 -304 X excl. -324 X X -308 R C23137810-x X X X X X X X X R C23137820-x X X X X X X X X R C23137910-x X X X X X X X X 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

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

R 

 A310-304 X X X X X X X 

R A310-308 X X 

 A310-322 X X X  A310-324 X X X X  A310-325 X 

R WEIGHT VARIANT 00 01 03 04 05 06 07 08 R MTOW 150 153 153 142 157 138.6 134 164 R MLW 123 123 124 123 124 123 124 124 R MZFW 113 113 114 113 114 113 114 114 R Top assembly PNR R C23137915-x NOT AUTHORIZED R C23137920-x X X X X X X X X R C23137950-x -304 -304 -304 X excl. -324 X X -308 

Nose Landing Gear Telescopic Strut 

R C23037-xxxx NOT AUTHORIZED R C23109-xxxx (**) (!) X X X X X X X X R C23109x10-xxxx X X X X X X X X R C23109915-x NOT AUTHORIZED 

Notes: Telescopic strut PRE VSB 470-32-055/FAM 51 ‘Replacement of visual indicator by a mechanical in

(**) Except PNR C23109, PNR C23109-0-x. (!) assembly can be installed provided the towing bar is fitted with a 150 ton capacity shear pin. 

Weight variant number allocation (refer to the DGAC-F Type Certificate Data Sheet N°145): 

WV00: Basic aircraft. WV01: Aircraft POST MOD 05616 or POST SB A310-00-2007. WV03: Aircraft POST MOD 08144. WV04: Aircraft POST MOD 06707. WV05: Aircraft POST MOD 07088 or POST SB A310-00-2012 or POST MOD 13082 or POST SB A310-0

SB A310-00-2052. 

WV06: Aircraft POST MOD 07614. WV07: Aircraft POST MOD 07659. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. WV08: Aircraft POST MOD 08130 or POST SB A310-00-2037. WV09: Aircraft POST MOD 08469 or POST SB A310-00-2018 or POST MOD 11640 or POST SB A310-00WV12: Aircraft POST MOD 11103 or POST SB A310-00-2029. WV13: Aircraft POST MOD 13302 or POST SB A310-00-2053. 

THE ABOVE TABLE INDICATES THE LANDING GEAR LRUs THAT HAVE BEEN CEACH 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 aircra

the interchangeabilities/mixabilities of LRUs. 

N R 

END OF SUB-PART 1-0 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ISSUE: SEP 05/13 PART 1-0 

© AIRBUS SAS 2013. All rights reserved. Confidential and proprietary document. WV08: Aircraft POST MOD 08130 or POST SB A310-00-2037. WV09: Aircraft POST MOD 08469 or POST SB A310-00-2018 or POST MOD 11640 or POST SB A310-00WV12: Aircraft POST MOD 11103 or POST SB A310-00-2029. WV13: Aircraft POST MOD 13302 or POST SB A310-00-2053. 

THE ABOVE TABLE INDICATES THE LANDING GEAR LRUs THAT HAVE BEEN CEACH 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 aircra

the interchangeabilities/mixabilities of LRUs. 

N R 

END OF SUB-PART 1-0 
A310 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 

Upper torque link pin and nut 

Torque link medium pin and nut

Lower torque link pin and nut 

Drop link Reaction bar 

Pin (Drag link/Barrel/Brace strut)

Barrel 

Drag link 

Pin (Drag link/Barrel) 

Forward pintle pin 

Torque link 

(Upper & Lower)

Brake torque arm pin (x2) 

Bogie beam pivot pin and nut 

Bogie beam 

Wheel axle (x2)

Brace strut upper side stay 

Brace strut middle pin

Lower lock link

Upper lock link

Lock link pin

Sleeve (Barrel/Drag link) 

Brake torque arm (x4) 

Lock link 

upper pin 

Brace strut upper pin 

Brace strut lower side stay 

Lock link middle pin 

MAIN LANDING GEAR - FIG. 01 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

MAIN LANDING GEAR - FIG. 02 

Ball (Fwd pintle bearing)

Fwd pick up 

Half ball housing 

(Fwd pintle bearing) 

Gear support rib 

Reaction bar pin 

Gear support rib Aft pintle pin 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

MAIN LANDING GEAR - FIG. 03 

Cage 

Upper torque 

link pin 

Sleeve 

(Barrel/Drag link) 

Pin (Drag link/Barrel/ 

Brace strut) 

Drag link Barrel 

Pin (Drop link/Frame 50)
A310 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. 

MAIN LANDING GEAR - FIG. 04 

Brake torque arm (x4) 

Bogie beam pivot 

pin and nut (*) 

Lower torque link pin 

S/A sliding rod 

Brake torque arm pin (x2)

Barrel 

S/A upper rod 

Pin (Connecting 

rod/ Upper rod) 

S/A connecting rod 

End fitting 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

© 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. 05 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

NOSE LANDING GEAR - FIG. 06 

Upper rod 

Bottom 

End fitting 

End fitting pin and nut 

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

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

Sliding rod 

Wheel axle 

Wheel axle nut (x2) 

Nut (S/A/Barrel) 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

© 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. 07 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

Locking cylinder 

End fitting pin 

Locking piston 

Lock claw 

Cylinder 

Locking sleeve 

Pintle pin 

End fitting 

Rod 

Nut (Cylinder/Locking cylinder) 

NOSE LANDING GEAR - FIG. 08 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

(*) Location, item not illustrated. 

WING STRUCTURE - FIG. 09 

Retraction actuator fitting 

Rear spar 

Fwd pick up

Link (Retraction actuator 

fitting/Fwd pick up) (x2) 

Top skin panel n°2 (*) 

Gear support rib Reaction bar fitting
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

WING STRUCTURE - FIG. 10 

Track 4 rib (outer) 

Track 4 rib (inner) 

Track 5 rib (outer) 

Track 5 rib (inner) 

Track 6 rib (outer) 

Track 6 rib (inner) 

Track 7 rib (outer) 

Track 7 rib (inner) 

Track 8 rib (outer) 

Track 8 rib (inner) 

Track 11 rib (outer) 

Track 11 rib (inner) 

Track 9 rib (outer) 

Track 9 rib (inner) 

Track 10 rib (outer) 

Track 10 rib (inner) 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

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

Shear bolt 

(Link/Engine) 

Shear bolt (Outer, 

Link/Lower beam) 

Shear bolt (Inner, RH 

link/Lower beam) 

Link (LH) 

Link (RH) 
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

PRATT & WHITNEY FORWARD ENGINE MOUNT - FIG. 12 

Bolt (Link/Fan 

case) (x2) 

Thrust link (x2) 

Cross beam 

Bolt (Cross beam/ 

Main beam) 

Main beam 

Shear pin 

Outer support 

(PW JT9D-7R4) 

Inner support 

(PW JT9D-7R4) 

Support 

(PW 4000) 

Bolt (Link/Cross 

beam) (x2) 

Pylon pyramid
A310 AIRWORTHINESS LIMITATIONS SECTION 

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

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

PRATT & WHITNEY AFT ENGINE MOUNT - FIG. 13 

END OF SUB-PART 1-1

Bolt (Mid link/Engine) 

Bolt (Side link/Engine) (x2) 

Link (x3) 

Pin (Link/Main beam) (x3) 

Main beam 

Pylon 
A310 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31R ATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 04) R BARREL ASSEMBLY (FIG. 01, 03 & 04)  (1) Limitation applicable only to A310-203 WV04 and A310-203C WV04. (2) Limitation applicable only to A310-203 WV01 & WV08 and A310-203C WV01.  (3) Limitation applicable only to A310-203 WV00, WV03 & WV06 and A310-221 WV00, WV03 & WV07.  Barrel (LH) 

D52697-1 

N/A 48300 N/A -203/3C (1) N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 

 Barrel (RH) 

D52698-1 

N/A 48300 N/A -203/3C (1) N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 

Upper torque link pin (LH) D52725 

N/A 48300 N/A -203/3C (1) 

 N/A 53300 N/A -203/3C (2) 

N/A 63300 N/A -203 (3) -221 (3) 

Upper torque link pin (RH) D52726 

N/A 48300 N/A -203/3C (1) 

 N/A 53300 N/A -203/3C (2) 

N/A 63300 N/A -203 (3) -221 (3) 

Torque link (Upper & Lower) D52703-1 

N/A 48300 N/A -203/3C (1) 

 N/A 53300 N/A -203/3C (2) 

N/A 63300 N/A -203 (3) -221 (3) 

 Drag link (LH) 

D52701 

N/A 48300 N/A -203/3C (1) 

N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 
A310 AIRWORTHINESS LIMITATIONS 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31 Drag link (RH) 

D52702 

N/A 48300 N/A -203/3C (1) 

N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 

 Forward pintle pin 

D53230-1 

N/A 48300 N/A -203/3C (1) N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 

 S/A connecting rod 

D53209 

N/A 48300 N/A -203/3C (1) 

N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 

R SHOCK ABSORBER ASSEMBLY (FIG. 01 & 04) (1) Limitation applicable only to A310-203 WV04, A310-203C WV04, A310-221 WV04 and A310-222 WV04, WV11 & WV104. (2) Limitation applicable only to A310-203 WV01 & WV08, A310-203C WV01, A310-221 WV01 and A310-222 WV01 & WV101.  (3) Limitation applicable only to A310-203 WV00, WV03 & WV06 and A310-221 WV00, WV03 & WV07.  (4) Limitation applicable only to A310-203 WV01 & WV08 and A310-203C WV01.  (5) Limitation applicable only to A310-203/3C WV04.  S/A upper rod 

D52747 

N/A 48300 N/A -203/3C (1) X (1) 

N/A 53300 N/A -203/3C (2) X (2) N/A 63300 N/A -203 (3) -221 (3) 

 S/A sliding rod (LH) 

D52699-1 

N/A 48300 N/A -203/3C (5) N/A 53300 N/A -203/3C (4) N/A 63300 N/A -203 (3) -221 (3) 

 S/A sliding rod (RH) 

D52700-1 

N/A 48300 N/A -203/3C (5) N/A 53300 N/A -203/3C (4) N/A 63300 N/A -203 (3) -221 (3) 
A310 AIRWORTHINESS LIMITATIONS 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31 Bogie beam pivot pin 

D52705 

N/A 48300 N/A -203/3C (5) 

N/A 53300 N/A -203/3C (4) N/A 63300 N/A -203 (3) -221 (3) 

D52705-1 

N/A 48300 N/A -203/3C (5) N/A 53300 N/A -203/3C (4) N/A 63300 N/A -203 (3) -221 (3) 

R LINKAGE ASSEMBLY (FIG. 01) (1) Limitation applicable only to A310-308 WV08 & WV09 and A310-324 WV12.  (2) Limitation applicable only to A310-304, to A310-308 WV05 and to A310-324 WV00, WV01,.WV03 & WV05.  Drop link D62523 N/A 48300 N/A -308 (1) 

N/A 63300 N/A X X (2) X 

R BRACE ASSEMBLY (FIG. 01) 

 BRACE STRUT (FIG. 01) 

 (1) Limitation applicable only to A310-203 WV04 and A310-203C WV04. (2) Limitation applicable only to A310-203 WV01 & WV08 and A310-203C WV01.  (3) Limitation applicable only to A310-203 WV00, WV03 & WV06 and A310-221 WV00, WV03 & WV07. 

Brace strut upper side stay D52919 

N/A 48300 N/A -203/3C (1) 

 N/A 53300 N/A -203/3C (2) 

N/A 63300 N/A -203 (3) -221 (3) 

D53034 

N/A 48300 N/A -203/3C (1) 

N/A 53300 N/A -203/3C (2) N/A 63300 N/A -203 (3) -221 (3) 

Brace strut lower side stay D52817 

N/A 48300 N/A -203/3C (1) 

 N/A 53300 N/A -203/3C (2)  .../... N/A 63300 N/A -203 (3) -221 (3) 
A310 AIRWORTHINESS LIMITATIONS 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31

Brace strut lower side stay D52817-1 

N/A 48300 N/A -203/3C (1) 

 N/A 53300 N/A -203/3C (2) 

N/A 63300 N/A -203 (3) -221 (3) 
A310 AIRWORTHINESS LIMITATIONS 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31R ATA 32-20-00 NOSE LANDING GEAR (FIG. 05 to 08) R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits. 

(2) - 12000 LDG from initial entry into service: For parts having an initial entry into service date after 30-Apr-1986. 

 - 12000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated 9000 LDG or less on 30-Apr-1986.  - 3000 LDG from 30-Apr-1986: For parts installed on aircraft having accumulated between 9000 and 14000 LDG on 30-Apr-1 - 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 203/3C X R BARREL ASSEMBLY (FIG. 05 & 06)  (1) Limitation applicable only to A310-308 WV08 & WV09 and to A310-324 WV12.  (2) Limitation applicable only to A310-304, to A310-308 WV05 and to A310-324 WV00, WV01, WV03 & WV05.  Barrel 

C59049-2 

N/A 50000 N/A X (1) N/A 57800 N/A X (2) N/A 65700 N/A X X 

C59049-4 

N/A 50000 N/A X (1) N/A 57800 N/A X (2) N/A 65700 N/A X X 

C59049-20 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

C59049-25 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

C59049-26 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) 

 .../... N/A 65700 N/A X X 
A310 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31N Barrel 

C59049-27 

N/A 50000 N/A X (1) 

N N/A 57800 N/A X (2) N N/A 65700 N/A X X 

C59049-40 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

C59049-41 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

N 

C59049-42 

N/A 50000 N/A X (1) 

N N/A 57800 N/A X (2) N N/A 65700 N/A X X 

C59049-45 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

C59049-46 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

N 

C59049-47 

N/A 50000 N/A X (1) 

N N/A 57800 N/A X (2) N N/A 65700 N/A X X 

D56525 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) 

 .../... N/A 65700 N/A X X 
A310 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH LDG Cal. A310-20x A310-30x A310-22x A31 Barrel 

D56525-1 

N/A 50000 N/A X (1) N/A 57800 N/A X (2) N/A 65700 N/A X X 

D56525-10 

N/A 50000 N/A X (1) 

N/A 57800 N/A X (2) N/A 65700 N/A X X 

N 

D56525-11 

N/A 50000 N/A X (1) 

N N/A 57800 N/A X (2) N N/A 65700 N/A X X  Turning tube C59050-4 N/A 24000 N/A X X X 

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

R SHOCK ABSORBER ASSEMBLY (FIG. 06 & 07)

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

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

associated aircraft. 

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

part and not to the associated NLG. 

 Bottom C62037-1 N/A (1) N/A X X X N D68531 N/A (1) N/A X X X 
A310 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH FC Cal. A310-20x A310-30x A310-22x A31R ATA 71-20-00 ENGINE MOUNTS (FIG. 11 to 13) R D R 

 GENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY (FIG. 11) 

(1) Replacement with improved links at next engine shop visit after 01-May-2001, or before accumulation of 29000 Engine Cy

whichever occurs first. Refer to FAA AD 2000-06-09. 

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

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

R Shear bolt (Outer, 

Link/Lower beam) 

77458-16-70 N/A N/A 31-Dec-09 -203/3C 

R RA22021-16-70 N/A N/A 31-Dec-09 -203/3C R 9380M75P01 N/A N/A 31-Dec-09 -204 X R Shear bolt (Inner, RH 

Link/Lower beam) 

77458-12-60 N/A N/A 31-Dec-09 -203/3C 

R RA22021-12-60 N/A N/A 31-Dec-09 -203/3C R 9380M80P01 N/A N/A 31-Dec-09 -204 X R Link (LH) 224-1608-1 N/A (1) (1) -203/3C R 224-1608-3 N/A (1) (1) -203/3C R 224-1608-5 N/A (1) (1) -203/3C R 9348M79P01 N/A (2) (2) -204 X R Link (RH) 224-1615-505 N/A (1) (1) -203/3C R 224-1615-507 N/A (1) (1) -203/3C R 224-1615-509 N/A (1) (1) -203/3C R 9348M84P01 N/A (2) (2) -204 X R Shear bolt 

(Link/Engine) 

81841-8 N/A N/A 31-Dec-09 -203/3C 

R 9380M73P01 N/A N/A 31-Dec-09 -204 X 
A310 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 the sub-part 1-0 paragraph 3.

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

Notes are located under the assy title. GE POWERED A310s PW 

 Nomenclature Part Number FH FC Cal. A310-20x A310-30x A310-22x A31R PRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 12)

(1) Part to be removed no later than 31-Dec-2005. The replacement of this part can be delayed until the next engine removal 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 (Cross beam/Main beam) 221-0251-501 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 

 Main beam 221-0241-9 N/A 20000 N/A X 

221-4005-1 

N/A 20000 N/A 

N/A 40000 N/A X 

 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. 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 

 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 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AR ATA 32-10-00 MAIN LANDING GEAR (FIG. 01 to 04) R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits. N Aft pintle pin (1) A32140108200xx N/A 63300 X X X N A32140108202xx N/A 63300 X X X N A32140128000xx N/A 63300 X X X N A32140128002xx N/A 63300 X X X N Half ball housing (Fwd pintle 

bearing) (1) 

A32140101200xx N/A 63300 X X X 

N A32140101201xx N/A 63300 X X X N A32140130002xx N/A 63300 X X X N A32140130003xx N/A 63300 X X X N A32140132006xx N/A 63300 X X X N A32140132007xx N/A 63300 X X X N Ball (Fwd pintle bearing) (1) A32140100200xx N/A 63300 X X X N A32140131200xx N/A 63300 X X X N Reaction bar pin (1) A32140117200xx N/A 63300 X X X  Pin (Drop link/Frame 50) (1) A53811122200xx N/A 63300 X X X N A53811122202xx N/A 63300 X X X R BARREL ASSEMBLY (FIG. 01, 03 & 04) (1) Limitation applicable only to A310-304 and to A310-308 WV05.  (2) Limitation applicable only to A310-324 WV00, WV01, WV03 and WV05. 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. 

.../... 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A (4) Limitation applicable only A310-203 WV00, WV01, WV04 and to A310-203C and to A310-204.  Cage D53212 N/A 63300 X X X  Barrel (LH) D52697-11 N/A 63300 X X 

D58061-1 N/A 63300 X X (1) X 

D62507 N/A 63300 X X X 

 Barrel (RH) D52698-11 N/A 63300 X X 

D58062-1 N/A 63300 X X (1) X 

D62508 N/A 63300 X X X 

 Upper torque link pin (LH) D52725-10 N/A 63300 X X 

D52725-20 N/A 63300 X X 

D58067 N/A 63300 X X (1) X 

D58067-20 N/A 63300 X X (1) X D58067-25 N/A 63300 X X X 

 Upper torque link pin (RH) D52726-10 N/A 63300 X X 

D52726-20 N/A 63300 X X 

D58068 N/A 63300 X X (1) X 

D58068-20 N/A 63300 X X (1) X D58068-25 N/A 63300 X X X 

 Upper torque link pin nut SL40123P N/A (3) X X X  Torque link (upper & lower) D52703-11 N/A 63300 X X 

D58066-1 N/A 63300 X X X 

 Torque link medium pin C65542-20 N/A 63300 X X X  Torque link medium pin nut SL40114P N/A (3) X X X  Sleeve (Barrel/Drag link) D52727 N/A 63300 X X X 

D66167 N/A 63300 X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A Drag link (LH) D52701-10 N/A 63300 X X 

D58063 N/A 63300 X X (1) X D62509 N/A 63300 X X X 

 Drag link (RH) D52702-10 N/A 63300 X X 

D58064 N/A 63300 X X (1) X D62510 N/A 63300 X X X 

Pin (Drag link/Barrel/Brace strut) D53237 N/A 63300 X X X 

 Pin (Drag link/Barrel) D53225 N/A 63300 X X 

D58878 N/A 63300 X X (1) X D62511 N/A 63300 X X X 

 Forward pintle pin D53230-11 N/A 63300 X X 

D58060-1 N/A 63300 X X (1) X 

D62506 N/A 63300 X X X 

Pin (Connecting rod/Upper rod) 

D52751 N/A 63300 X X X 

D52751-1 N/A 63300 X X X 

N D52751-2 N/A 63300 X X X N D52751-10 N/A 63300 X X X N D68547 N/A 63300 X X X  S/A connecting rod D53209-10 N/A 63300 X (4) X 

D58065 N/A 63300 X X (1) X 

D58065-1 N/A 63300 X X X 

R SHOCK ABSORBER ASSEMBLY (FIG. 01 & 04) (1) Limitation applicable only to A310-304 and to A310-308 WV05.  .../... 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A (2) Limitation applicable only to A310-324 WV00, WV01, WV03 and WV05. 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. 

 (4) Limitation applicable only to A310-203 WV00, WV03 & WV06.  (5) Limitation applicable only to A310-221 WV00, WV03 & WV07. R (6) PNR CRA50548 applies to nuts used for repaired bogie beam pivot pins.  S/A upper rod D52747-10 N/A 63300 X X (1) X 

D62515 N/A 63300 X X X 

 S/A sliding rod (LH) D52699-21 N/A 63300 X X 

D52699-31 N/A 63300 X X 

D58069-1 N/A 63300 X X (1) X D61671-1 N/A 63300 X X (1) X 

D62513 N/A 63300 X X X 

 S/A sliding rod (RH) D52700-21 N/A 63300 X X 

D52700-31 N/A 63300 X X 

D58070-1 N/A 63300 X X (1) X D61672-1 N/A 63300 X X (1) X 

D62514 N/A 63300 X X X 

 End fitting D54174 N/A 63300 X X 

D54174-1 N/A 63300 X X (1) X 

D62512 N/A 63300 X X X 

 Lower torque link pin D52721 N/A 63300 X X 

D52721-20 N/A 63300 X X 

D58073 N/A 63300 X X (1) X 

D58073-20 N/A 63300 X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A Lower torque link pin nut SL40123P N/A (3) X X X  Brake torque arm pin D52712 N/A 63300 X X N D52712-1 N/A 63300 X X 

D58075 N/A 63300 X X (1) X D62516 N/A 63300 X X X 

 Brake torque arm C66434-10 N/A 63300 -203 (4) -221 (5) 

C66434-20 N/A 63300 X X (1) X 

D52710 N/A 63300 -203 (4) -221 (5) D62518 N/A 63300 X X X 

 Bogie beam pivot pin D52705-10 N/A 63300 X X 

D52705-20 N/A 63300 X X 

D58071 N/A 63300 X X (1) X 

D58071-20 N/A 63300 X X X 

 Bogie beam pivot pin nut CRA50548 (6) N/A 63300 X X X 

SL40413P N/A (3) X X X 

 BOGIE BEAM ASSEMBLY (FIG. 01)

 (1) Limitation applicable only to A310-203 WV00, WV03 & WV06.  (2) Limitation applicable only to A310-221 WV00, WV03 & WV07.  (3) Limitation applicable only to A310-304 and to A310-308 WV05.  (4) Limitation applicable only to A310-324 WV00, WV01, WV03 and WV05.  Bogie beam D52809-1 N/A 63300 -203 (1) -221 (2) 

D52809-3 N/A 63300 -203 (1) -221 (2) 

D52809-21 N/A 63300 -203 (1) -221 (2) 

D58000-1 N/A 63300 X X (3) X 

 .../... D58000-3 N/A 63300 X X (3) X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A Bogie beam D62519-1 N/A 63300 X X X  Wheel Axle D52833-1 N/A 63300 -203 (1) -221 (2) 

D52833-21 N/A 63300 X X 

D58001-1 N/A 63300 X X (3) X D62520-1 N/A 63300 X X X 

 LINKAGE ASSEMBLY (FIG. 01)

 (1) Limitation applicable only to A310-203 WV00, WV03 & WV06.  (2) Limitation applicable only to A310-221 WV00 & WV03.  (3) Limitation applicable only to A310-203 WV00, WV01, WV03, WV04 & WV06, and to A310-203C.  (4) Limitation applicable only to A310-221 WV00, WV01, WV03 & WV04, and to A310-222 WV01 & WV04.  (5) Limitation applicable only to A310-304 and to A310-308 WV05.  Reaction bar D52807 N/A 63300 -203 (1) -221 (2) 

D52807-1 N/A 63300 -203/3C (3) X (4) D52807-2 N/A 63300 -203 (1) -221 (2) D52807-3 N/A 63300 -203 (1) -221 (2) 

D52807-10 N/A 63300 X X 

D58002 N/A 63300 X X (5) X D62522 N/A 63300 X X X 

 Drop link D52915 N/A 63300 -203 (1) -221 (2) 

D52915-1 N/A 63300 X X 

D58003 N/A 63300 X X (5) X 

R BRACE ASSEMBLY (FIG. 01) 

 BRACE STRUT (FIG. 01)

 (1) Limitation applicable only to A310-304 and to A310-308 WV05.  (2) Limitation applicable only to A310-203 WV00, WV01 & WV04. 
A310 AIRWORTHINESS LIMITATIONS 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A Brace strut upper pin D53016 N/A 63300 X X 

D53016-10 N/A 63300 X X 

D58008 N/A 63300 X X X 

 Brace strut upper side stay D53034-10 N/A 63300 X X (1) X 

D62521 N/A 63300 X X X 

 Brace strut middle pin D53013 N/A 63300 X X 

D58007 N/A 63300 X X X 

 Brace strut lower side stay D52817-10 N/A 63300 X (2) X 

D58004 N/A 63300 X X X 

 Lock link pin D53027 N/A 63300 X X 

D53027-2 N/A 63300 X X X 

 LOCK LINK (FIG. 01)

R (1) Limitation applicable only to A310-221 WV00, WV03 & WV07.  Lower lock link D52917 N/A 63300 X X X  Lock link middle pin D53044 N/A 63300 -203/3C -221 (1) 

D53044-1 N/A 63300 X X X D53044-2 N/A 63300 X X X 

 Upper lock link D52913 N/A 63300 -203/3C -221 (1) 

D52913-1 N/A 63300 X X X 

D53033 N/A 63300 -203/3C -221 (1) 

D53033-1 N/A 63300 X X X 

D53033-10 N/A 63300 X X X 

 Lock link upper pin D53047 N/A 63300 X X X 

D53047-2 N/A 63300 X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AR ATA 32-20-00 NOSE LANDING GEAR (FIG. 05 to 08) R (1) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits.  Pintle pin (1) A32210079200xx 105000 65700 X X 

116000 65700 X 

A32210080200xx 

105000 65700 X X 

116000 65700 X 

N 

A32210082200xx 

105000 65700 X X 

N 116000 65700 X R TELESCOPIC STRUT ASSEMBLY (FIG. 08) End fitting pin C62911-1 N/A 65700 X X 

C62911-2 N/A 65700 X X X 

C62911-15 N/A 65700 X X 

N C62911-18 N/A 65700 X X 

C62911-20 N/A 65700 X X X 

N C62911-25 N/A 65700 X X X 

D55951 N/A 65700 X X X 

 End fitting C61390-1 N/A 65700 X X 

C61390-2 N/A 65700 X X X 

D55962 N/A 65700 X X X 

 Cylinder C61371 N/A 65700 X X X 

D55954 N/A 65700 X X X 

R Nut (Cylinder/Locking 

cylinder) 

C61375 N/A 65700 X X X 

N C61375-1 N/A 65700 X X X  .../... D55955 N/A 65700 X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN Nut (Cylinder/Locking 

cylinder) 

D55955-1 N/A 65700 X X X 

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

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

N C61373-10 N/A 65700 X X 

C61373-40 N/A 65700 X X X 

D63091 N/A 65700 X X X 

D63091-1 N/A 65700 X X X 

 Locking sleeve C61389 N/A 65700 X X X 

C61389-1 N/A 65700 X X X 

 Lock claw C61391 N/A 65700 X X X 

D55952 N/A 65700 X X X 

 Locking piston C61378-1 N/A 65700 X X 

C61378-3 N/A 65700 X X 

N C61378-10 N/A 65700 X X 

C68483 N/A 65700 X X 

C68483-1 N/A 65700 X X X C68483-2 N/A 65700 X X X C68483-3 N/A 65700 X X X C68483-4 N/A 65700 X X X 

D63282 N/A 65700 X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A Rod C61372-1 N/A 65700 X X 

C61372-2 N/A 65700 X X X 

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

D57050 N/A 65700 X X X 

D57050-1 N/A 65700 X X X 

 BARREL ASSEMBLY (FIG. 05 & 06)

R (1) Part must be replaced by a new one every time it is removed from the barrel. 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. 

 Pin (Clevis/Telescopic strut) C62231-20 N/A 65700 X X X 

D56530 N/A 65700 X X X 

 Clevis C62002-2 N/A 65700 X X X 

D56527 N/A 65700 X X X 

 Lower pin (Link/Clevis) C62268-20 N/A 65700 X X X N C62268-200 N/A 65700 X X X N D68541 N/A 65700 X X X  Link (Clevis/Barrel) C62230-1 N/A 65700 X X X N C62230-10 N/A 65700 X X X 

D56526 N/A 65700 X X X 

N D56526-1 N/A 65700 X X X N D68539 N/A 65700 X X X N D68540 N/A 65700 X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x A Upper pin (Link/Barrel) C62267-20 N/A 65700 X X X N C62267-200 N/A 65700 X X X N D68544 N/A 65700 X X X  Pin (Clevis/Barrel) C62229-20 N/A 65700 X X X 

D56528 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 

D59633 N/A 65700 X X X 

D59633-1 N/A 65700 X X X 

D59633-10 N/A 65700 X X X 

D61185 N/A 65700 X X X 

D61185-10 N/A 65700 X X X 

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

 Pin (Barrel/Airframe) C62228-20 N/A 65700 X X X N End fitting pin nut D68062 N/A (1) X X X R MS17825-6 N/A (1) X X X R End fitting pin AN6-17 N/A (1) X X X R D61183 N/A (1) X X X N D68063 N/A (1) X X X R NAS1306-22D N/A (1) 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 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN End fitting C62032-10 N/A 65700 X X X 

D61184 N/A 65700 X X X 

N D61184-1 N/A 65700 X X X N D68076 N/A 65700 X X X N D68695 N/A 65700 X X X  Rack C61453-1 N/A 65700 X X X N C61453-15 N/A 65700 X X X 

C61453-20 N/A 65700 X X X C61453-40 N/A 65700 X X X C61453-41 N/A 65700 X X X 

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

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

Torque link pin (Upper & Lower) C62223-20 N/A 65700 X X X 

 Torque link (Upper & Lower) C59562-2 N/A 65700 X X X 

C59562-3 N/A 65700 X X X C59562-4 N/A 65700 X X X 

N C59562-20 N/A 65700 X X X  Torque link medium pin C62041-20 N/A 65700 X X X N C62041-200 N/A 65700 X X X 

D53431-20 N/A 65700 X X X 

R Torque link medium pin nut SL40110P N/A (2) X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AR SHOCK ABSORBER ASSEMBLY (FIG. 06 & 07)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 X 

C59053-21 N/A 65700 X X X 

R Wheel axle nut C62879 N/A (1) X X X N C62879-1 N/A (1) X X X N D68537 N/A (1) X X X  Sliding Rod C59051-3 N/A 65700 X X X 

C59051-21 N/A 65700 X X X 

R Upper cam dowel C62270 N/A (2) X X X  Upper cam C62034-1 N/A 65700 X X X N C62034-10 N/A 65700 X X X N D68534 N/A 65700 X X X  Lower cam C62035 N/A 65700 X X X N C62035-1 N/A 65700 X X X N D68532 N/A 65700 X X X R Lower cam dowel C62866 N/A (3) X X X  Restrictor C67863-1 N/A 65700 X X X 

C67863-2 N/A 65700 X X X C67863-4 N/A 65700 X X X 

N C67863-10 N/A 65700 X X X N .../... C67863-20 N/A 65700 X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN Restrictor C67863-40 N/A 65700 X X X N D68536 N/A 65700 X X X  Upper Rod C59052-2 N/A 65700 X X X R Nut (S/A/Barrel) C64040-1 N/A (1) X X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN ATA 57-00-00 WING STRUCTURE (FIG. 09 & 10) N MAIN LANDING GEAR SUPPORT RIB ASSEMBLY AND ASSOCIATED FITTINGS (FIG. 09) N (1) This item is not transferable from an aircraft to another: traceability at aircraft level is authorised.N (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits. N (3) Only the area of the top skin panel aft of the rear spar at gear support rib/retraction actuator fitting attachment is considered N Gear support rib (LH) (1) (2) A57242444002xx N/A 45000 X X N 

A57242444006xx 

N/A 40000 X 

N N/A 45000 X X N A57242444018xx N/A 40000 X N Gear support rib (RH) (1) (2) A57242444003xx N/A 45000 X X N 

A57242444007xx 

N/A 40000 X 

N N/A 45000 X X N A57242444019xx N/A 40000 X N Reaction bar fitting (LH) 

(1) (2) 

A57242436002xx N/A 45000 X X 

N A57242436006xx N/A 40000 X N A57242436010xx N/A 40000 X N Reaction bar fitting (RH) 

(1) (2) 

A57242436003xx N/A 45000 X X 

N A57242436007xx N/A 40000 X N A57242436011xx N/A 40000 X N Retraction actuator fitting 

(LH) (1) (2) A57242452002xx 

N/A 40000 X 

N N/A 45000 X X N Retraction actuator fitting 

(RH) (1) (2) A57242452003xx 

N/A 40000 X 

N N/A 45000 X X N Link (Retraction actuator 

fitting/Fwd pick up) (1) (2) A57242453200xx 

N/A 40000 X X 

N N/A 45000 X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN Fwd pick up (LH) (1) (2) A57242439000xx N/A 40000 X N N/A 45000 X X N A57242439002xx N/A 40000 X N A57242439004xx N/A 40000 X N Fwd pick up (RH) (1) (2) A57242439001xx N/A 40000 X N N/A 45000 X X N A57242439003xx N/A 40000 X N A57242439005xx N/A 40000 X N Top skin panel n°2 (LH) 

(1) (2) (3) 

A57350001200xx N/A 45000 X X 

N A57350101200xx N/A 45000 X X N A57350101202xx N/A 45000 X X N A57350101204xx N/A 45000 X X N A57350141200xx N/A 40000 X N A57350141202xx N/A 40000 X N Top skin panel n°2 (RH) 

(1) (2) (3) 

A57350001201xx N/A 45000 X X 

N A57350101201xx N/A 45000 X X N A57350101203xx N/A 45000 X X N A57350101205xx N/A 45000 X X N A57350141201xx N/A 40000 X N A57350141203xx N/A 40000 X N FIXED LEADING EDGE STRUCTURE AND SLATS ATTACHEMENTS (FIG. 10) N (1) This item is not transferable from an aircraft to another: Traceability at aircraft level is authorised.N (2) ‘xx’ at the end of the PNR stands for any number between 00 and 99, including unused digits. N (3) Limitation in FC. 
A310 AIRWORTHINESS LIMITATIONS 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN Track 4 rib (outer) (LH) 

(1) (2) A57243014200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 4 rib (inner) (LH) 

(1) (2) A57243014202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 4 rib (outer) (RH) 

(1) (2) A57243014201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 4 rib (inner) (RH) 

(1) (2) A57243014203xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 5 rib (outer) (LH) 

(1) (2) A57243015200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 5 rib (inner) (LH) 

(1) (2) A57243015202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 5 rib (outer) (RH) 

(1) (2) A57243015201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 5 rib (inner) (RH) 

(1) (2) A57243015203xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 6 rib (outer) (LH) 

(1) (2) A57243016200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 6 rib (inner) (LH) 

(1) (2) A57243016202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 6 rib (outer) (RH) 

(1) (2) A57243016201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 6 rib (inner) (RH) 

(1) (2) A57243016203xx N/A 40000 (3) X 

N N/A 45000 (3) X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN Track 7 rib (outer) (LH) 

(1) (2) A57243017200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 7 rib (inner) (LH) 

(1) (2) A57243017202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 7 rib (outer) (RH) 

(1) (2) A57243017201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 7 rib (inner) (RH) 

(1) (2) A57243017203xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 8 rib (outer) (LH) 

(1) (2) A57243018200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 8 rib (inner) (LH) 

(1) (2) A57243018202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 8 rib (outer) (RH) 

(1) (2) A57243018201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 8 rib (inner (RH) 

(1) (2) A57243018203xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 9 rib (outer) (LH) 

(1) (2) A57243019200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 9 rib (inner (LH) 

(1) (2) A57243019202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 9 rib (outer) (RH) 

(1) (2) A57243019201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 9 rib (inner) (RH) 

(1) (2) A57243019203xx N/A 40000 (3) X 

N N/A 45000 (3) X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

DEMONSTRATED FATIGUE L

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH LDG A310-20x A310-30x A310-22x AN Track 10 rib (outer) (LH) 

(1) (2) A57243020200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 10 rib (inner) (LH) 

(1) (2) A57243020202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 10 rib (outer) (RH) 

(1) (2) A57243020201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 10 rib (inner) (RH) 

(1) (2) A57243020203xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 11 rib (outer) (LH) 

(1) (2) A57243021200xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 11 rib (inner) (LH) 

(1) (2) A57243021202xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 11 rib (outer) (RH) 

(1) (2) A57243021201xx N/A 40000 (3) X 

N N/A 45000 (3) X X N Track 11 rib (inner) (RH) 

(1) (2) A57243021203xx N/A 40000 (3) X 

N N/A 45000 (3) X X 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

APPLICABIL

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH FC A310-20X A310-30x A310-22x AR ATA 71-20-00 ENGINE MOUNTS (FIG. 11 to 13) R GENERAL ELECTRIC AFT ENGINE MOUNT ASSEMBLY (FIG. 11)

Shear bolt (Outer Link/Lower beam) 

96739-16-70 N/A 64000 -203/3C 

 9380M75P02 N/A 64000 -204 X 

Shear bolt (Inner, RH Link/ Lower beam) 

96739-12-60 N/A 64000 -203/3C 

 9380M80P02 N/A 64000 -204 X  Link (LH) 224-1608-7 N/A 80000 -203/3C 

224-1608-9 N/A 80000 -203/3C 

1846M23P01 N/A 50000 -204 X 

 Link (RH) 224-1615-511 N/A 80000 -203/3C 

224-1615-513 N/A 80000 -203/3C 

9348M84P02 N/A 80000 -204 X 

 Shear bolt (Link/Engine) 96738-8 N/A 64000 -203/3C 

9380M73P02 N/A 64000 -204 X 

R PRATT & WHITNEY FORWARD ENGINE MOUNT ASSEMBLY (FIG. 12)R Bolt (Link/Fan case) 221-0251-511 N/A 40000 X  Thrust 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 221-0242-5 N/A 40000 X 

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 
A310 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 the sub-part 1-0 paragraph 3.

 (*) Whichever occurs first. DEMONSTRATED 

FATIGUE LIVES (*) 

APPLICABIL

 Notes are located under the assy title. GE POWERED A310s P Nomenclature Part Number FH FC A310-20X A310-30x A310-22x A Main beam 221-0241-5 N/A 40000 X 

221-4006-3 N/A 40000 X 221-4006-5 N/A 40000 X 

 Shear pin 221-0252-507 N/A 40000 X  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 221-4047-503 N/A 40000 

221-4047-505 N/A 40000 221-4047-507 N/A 40000 

R PRATT & WHITNEY AFT ENGINE MOUNT ASSEMBLY (FIG. 13) Main beam 221-261-9 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 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

1- GENERAL 

- A310 ALS Part 1 revision 00: 

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

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

were transferred to the A310 ALS Part 4). 

- A310 ALS Part 1 revision 01: 

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

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

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

2- SUMMARY OF CHANGES: 

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

1 (revision 00). 

New items: 

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY: 

* A310-300 series: 

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

SUB-PART 1-2: 

None. 

SUB-PART 1-3: 

* Main landing gear: 

Aft pintle pin PNR A32140108200xx, PNR A32140108202xx, PNR A32140128000xx 

and PNR A32140128002xx: PNR added. 

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

PNR A32140130002xx, PNR A32140130003xx, PNR A32140132006xx and PNR 

A32140132007xx: PNR added. 

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

added. 

Reaction bar pin PNR A32140117200xx: PNR added. 

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

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

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

A57242444018xx: PNR added. 

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

A57242444019xx: PNR added. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

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

A57242436010xx: PNR added. 

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

A57242436011xx: PNR added. 

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

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

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

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

A57242439004xx: PNR added. 

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

A57242439005xx: PNR added. 

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

A57350101202xx, PNR A57350101204xx, PNR A57350141200xx and PNR 

A57350141202xx: PNR added. 

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

A57350101203xx, PNR A57350101205xx, PNR A57350141201xx and PNR 

A57350141203xx: PNR added. 

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Track 9 rib (outer) (RH) PNR A57243019201xx: PNR added. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

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

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

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

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

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

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

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

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

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

Amendments: 

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY: 

* A310-200 series: 

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

SUB-PART 1-2: 

* Main landing gear: 

Figures number added. 

* Main landing gear, Barrel assembly: 

Figure number amended. 

* Main landing gear, Shock absorber assembly: 

Figure number amended. 

* Main landing gear, Linkage assembly: 

Figures number deleted. 

* Main landing gear, Brace assembly: 

Figure number added. 

* Nose landing gear: 

Figures number added. 

Note (1) amended. 

* Nose landing gear, Barrel assembly: 

Figures number amended. 

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

added (MOD 13212). 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

* Main landing gear, Shock absorber assembly: 

Figures number amended. 

Bottom PNR D68531: PNR added (MOD 13457). 

* Engine mounts: 

Figures number added. 

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

Notes (2) and (3) renumbered. 

* Engine mounts, General electric aft engine mount assembly: 

Figure number amended. 

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

Figure number amended. 

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

Figure number amended. 

SUB-PART 1-3: 

* Main landing gear: 

Figures number added. 

Note (1) amended. 

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

* Main landing gear, Barrel assembly: 

Figure number amended. 

Note (3) amended. 

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

PNR added (MOD 13450). 

* Main landing gear, Shock absorber assembly: 

Figure number amended. 

Notes (3) and (6) amended. 

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

* Main landing gear, Brace assembly: 

Figure number added. 

* Main landing gear, Brace assembly, Lock link: 

Note (1) amended. 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

* Nose landing gear: 

Figures number added. 

Note (1) amended. 

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

* Nose landing gear, Telescopic strut assembly: 

Figure number amended. 

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

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

added (MOD 13455), nomenclature amended. 

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

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

* Nose landing gear, Barrel assembly: 

Figures number amended. 

Notes (1) and (2) amended. 

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

Link (Clevis/Barrel) PNR C62230-10, 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), 

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

End fitting pin: 

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

- PNR D68063: PNR added (MOD 13212). 

End fitting: 

- PNR D68076: PNR added (MOD 13212). 

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

(MOD 13456). 

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

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

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

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

* Main landing gear, Shock absorber assembly: 

Figures number amended. 

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

Wheel axle nut: 

- PNR C62879: Note (1) assigned. 

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

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

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

Lower cam PNR C62035-1 and PNR D68532: PNR added (MOD 13457). 
A310 AIRWORTHINESS LIMITATIONS SECTION 

ALS PART 1 

SAFE LIFE AIRWORTHINESS LIMITATION ITEMS 

HISTORY FILE 

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

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

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

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

added (MOD 13457). 

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

* Engine mounts: 

Figures number added. 

* Engine mounts, General electric aft engine mount assembly: 

Figure number amended. 

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

Figure number amended. 

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

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

Figure number amended. 

Deletions: 

SUB-PART 1-0 LANDING GEAR LRUs APPLICABILITY: 

None. 

SUB-PART 1-2: 

None. 

SUB-PART 1-3: 

None.