7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - 

CRACKS AT BOLT HOLES

MODIFICATION No. : None

This page transmits Revision No. 03 of Service Bulletin No. A310-

ADDITIONAL WORK

No additional work is required by this revision for aircraft m

previous issue.

REASON

This revision is issued to make the main changes that follow:

— Accomplishment timescale to include inspection threshold, in

grace periods to Extended Service Goal (ESG) requirements.

— Aircraft configurations added.

— Effectivity revised.

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Inspection thresholds and intervals revised. Evaluation 

— EFFECTIVITY

. Effectivity revised. Models revised. Operators CYP, DAH, 

MPH, NGA, SAB and SWR deleted. Operators F2I, FDX, and S8G 

— MANPOWER

. Configuration layout applied.

PLANNING INFORMATION :
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

. 1.C.(1) Inspection thresholds and intervals revised.

— Objective/Action

. 1.C.(2) Inspection thresholds and intervals revised.

— DESCRIPTION

. 1.D. Configuration layout applied. Revised description in 

— COMPLIANCE

— Accomplishment Timescale

. 1.E.(2)(a) Mandatory sentence updated.

. 1.E.(2)(b) Inspection thresholds and intervals revised.

. 1.E.(2)(c) Inspection thresholds revised.

— APPROVAL

. 1.F. Approval sentence updated. Effectivity/Modification 

— MANPOWER

. 1.G. Configuration layout applied. Manpower para added.

ACCOMPLISHMENT INSTRUCTIONS :

— Preparation

. 3.A.(1) Configuration Layout applied. Ref to figure 6 add

. 3.A.(1)(a)1 Para revised.

— INSPECTION

. 3.B. Configuration layout applied. Ref to figure 6 added.

. 3.B.(1)(a) Inspection intervals revised.

— REPAIR

. 3.C. Configuration layout applied. Ref to figure 6 added.

. 3.C.(1)(a) Inspection intervals revised.

2
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

. Configuration layout applied.

— Figure 2

. Configuration layout applied.

— Figure 3

. Configuration layout applied.

— Figure 4

. Configuration layout applied.

— Figure 5

. Configuration layout applied.

— Figure 6

. Configuration layout applied.

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and is 

complete document. Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

If information is required for Revisions issued previous to t

check your copies of Revision Transmittal Sheets or contact A

REVISION SEQUENCE

ORIGINAL : Dec 31/88

REVISION No. : 01 — Jul 02/92

REVISION No. : 02 — Jan 04/96

REVISION No. : 03 — Nov 28/06

3
7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - 

CRACKS AT BOLT HOLES

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

On the full scale wing fatigue test, cracking of the skin occurred 

covered by this inspection. The cracks originated from the leadin

strap attachment holes. These attachments, initially rivets, were 

changed to interference fit bolts, both on the fatigue specimen a

aircraft before delivery.

Detail panel tests have shown that with these improved attachments

still occur on some aircraft within the economic repair life.

Modification 05101 has been introduced to improve the fatigue lif

fatigue critical areas, thereby reducing the possibility of expen

being required later in the life of the aircraft. Service Bulleti

covers retrofit embodiment of Mod. 05101. Where Mod. 05101 has no

embodied, special Mandatory inspections, detailed in this inspect

Bulletin, will be required, starting at 9,400 flight cycles (FC) 

flight hours (FH) which ever comes first.

Embodiment of modification 05101 (Service Bulletin A310-57-2003) 

before the inspection threshold to avoid possible repair situatio

introduction of this special Mandatory inspection procedure.

A Mandatory detailed visual inspection of the external surface of 

skin area around each of the bolt positions is required.

Where modification 03028 has not been embodied, this Service Bull

the mandatory inspection of 975 bolt positions. Where modificatio

been embodied, this Service Bulletin calls for the mandatory insp

bolt positions.

Where cracks are found extending in a forward direction, they are 

continue until they reach the skin edge. When this has occurred, 

be carried out within 390 FC or 780 FH, which ever comes first.
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

F2I FDX S8G

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

EQUIPMENT : No

HARD : No

SOFT : No

OBRM : No

MANPOWER

Config. 01 thru Config. 02

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION S

POTENTIAL AD Yes A/C OPERATION AFFECT

RELIABILITY AFFECTED No PAX COMFORT AFFECTED 

COST SAVING No ETOPS AFFECTED 

STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED 

KIT PRICE (USD) No AIRBUS Kit

2
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

None

APPENDICES

None

3
7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - LEADING EDGE ACCESS PANELS LANDING - LOWER SKIN - 

CRACKS AT BOLT HOLES

MODIFICATION No. : None

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS' prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

310-203 A310-222

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0162 0191 0201 0217 0224 0230 0233 0237 0241 024

0254 0257 0260 0264 0267 0273 0278 0281 0283 029

0309

(b) Effectivity by Operator

The Operator/MSN relationship is provided for in

and is correct at the time of issue in accordan

information available to AIRBUS. Any future cha

from transfer of an aircraft from one operator t
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(c) Effectivity by MSN and Kit/Configuration

The kits and configurations applicable to these 

at the end of this list:

0300 0309

The kits and configurations applicable to these 

at the end of this list:

0162 0191 0201 0217 0224 0230 0233 0237 0241 024

0254 0257 0260 0264 0267 0273 0278 0281 0283 029

NOTE : Config. 01 are pre-Modification 05101 ai

Config. 02 are pre-Modification 05101 ai

have had Modification 03028 embodied.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

On the full scale wing fatigue test, cracking of the 

in the region covered by this inspection. The cracks 

from the leading edge landing strap attachment holes

0248 0251 0254 0257 0260 0264 0267 0

0283 0297 0303

S8G 0300

KIT No. QTY PER A/C CONFIGURATION

01

KIT No. QTY PER A/C CONFIGURATION

02

2
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Modification 05101 has been introduced to improve th

in the fatigue critical areas, thereby reducing the 

expensive repairs being required later in the life of 

Service Bulletin A310-57-2003 covers retrofit embodim

05101. Where Mod. 05101 has not been embodied, speci

inspections, detailed in this inspection Service Bul

required, starting at 9,400 flight cycles (FC) or 18

hours (FH) which ever comes first.

Embodiment of modification 05101 (Service Bulletin A3

recommended before the inspection threshold to avoid 

repair situation and the introduction of this specia

inspection procedure.

(2) Objective/Action

A Mandatory detailed visual inspection of the extern

the wing lower skin area around each of the bolt pos

required.

Where cracks are found extending in a forward direct

allowed to continue until they reach the skin edge. W

occurred, a repair must be carried out within 390 FC 

which ever comes first.

Where modification 03028 has not been embodied, this 

Bulletin calls for the mandatory inspection of 975 bo

Where modification 03028 has been embodied, this Serv

calls for the mandatory inspection of 972 bolt posit

Where cracks are extending rearwards, a High Frequenc

(HFEC) inspection is required to determine crack leng

direction. A repair must then be carried out within 

FH, which ever comes first.

(3) Advantages

Accomplishment of this Service Bulletin reduces the 

expensive and time consuming repairs being required.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

3
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(d) Close up.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

(a) Accomplishment of this Service Bulletin is expe

rendered mandatory by the issue of an Airworthi

(AD) published by the European Aviation Safety A

It is anticipated that the AD will confirm the 

and/or intervals and/or date) given above but re

be made to the AD for confirmation of the mandat

accomplishment timescale.

(b) Inspection thresholds and intervals are given be

NOTE : The tables that follow list all the inspe

in flight cycles and flight hours. Inspec

be carried out either at FC or FH limit w

first.

(c) Where aircraft have exceeded the inspection thre

paragraph 1.E.(2) (b), then this inspection must 

out within 1,500 FC or 3,000 FH, whichever come

the issue date of Revision 03 of this Service Bu

exceeding the already planned inspections in ac

Service Bulletin 57-2002 revision 02.

(d) Where Modification 03028 has not been embodied, 

Bulletin calls for the mandatory inspection of 9

positions. Where Modification 03028 has been em

Service Bulletin calls for the mandatory inspect

bolt positions.

Threshold Interval

FC FH FC FH

9,400 18,800 2,300 4,70

4
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

A touch and go is a landing in which the aircraf

come to a compleat standstill before commencing 

flight.

NOTE : The inspection requirements described in 

Bulletin are cancelled by the embodiment 

Bulletin 57-2003.

F. APPROVAL

Approved under the EASA Design Organisation Approval No. 

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying times for paints, 

and general administration work are also not included.

Config. 01 thru Config. 02

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

Not changed

Gain Access 

Inspection 

Close up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

5
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

None

L. INTERCHANGEABILITY/MIXABILITY

None

6
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

AIRBUS will not provide industry support for accomplishme

Service Bulletin.

C. LIST OF COMPONENTS

None

D. LIST OF MATERIALS — OPERATOR SUPPLIED

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None

7
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

8
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(a) Config. 01 thru Config. 02

Refer to figure 1 thru figure 6

1 Gain access to the bottom wing skin on the un

leading edge.

(2) Standard Practices

None

B. INSPECTION

(1) Config. 01 thru Config. 02

Refer to figure 1 thru figure 6

(a) Carry out a detailed visual inspection (DVI) of 

surface of the wing bottom skin around the bolts 

panel positions. Where no cracks are found, repe

inspection at intervals not exceeding 2,300 FC o

which ever comes first.

C. REPAIR

(1) Config. 01 thru Config. 02

Refer to figure 1 thru figure 6

(a) Where a crack is found to be extending from a bo

towards the skin edge, it can be allowed to cont

repeat DVIs every 390 FC or 780 FH, which ever 

monitor the cracks progress until it reaches the 

When this has occurred contact SER1 and report 

details of the crack (Refer to SRM 51-10-13 Page 

A repair must be carried out within 390 FC or 7

ever comes first, after the crack has reached t

(b) Where a crack is found extending in an rearward 

(Refer to NTM 51-10-08 part 6 Page block 601) a

HFEC inspection around the bolt position affecte

Contact AI.SE-E1 with complete details of the c

SRM 51-10-13 Page block 001) for an approved re

repair must be carried out within 390 FC or 780 

comes first, after crack detection.

9
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

E. CLOSE UP

(1) Config. 01 thru Config. 02

(a) Make certain that the work area is clean and cle

and miscellaneous items of equipment.

F. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

10
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Access Panel General Location (Config 01 and 02)

11
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1

LH Wing, Root Rib 1 to Slat Track 3 Bolting Arrangement (Confi

12
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 1

LH Wing, Slat Track 3 to Slat Track 5 Bolting Arrangement (Conf

13
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 1

LH Wing, Slat Track 5 to Slat Track 7 Bolting Arrangement (Conf

14
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 5 Sheet 1

LH Wing, Slat Track 7 to Slat Track 9 Bolting Arrangement (Conf

15
DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 6 Sheet 1

RH Wing, Refuel Panel, After Mod.AM 3028 Only, Bolting Arrangeme

16
7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

A - SB WILL BE embodied............. YES/NO (if NO p

If YES, aircraft concerned (as per SB effectivity by default) and 

(month/year) of embodiment:...................

.................................

.................................

B - SB HAS BEEN embodied on aircraft:..............

.................................

.................................

Operator comments:.......................

................................

................................

From Airline:..........................

Name/Title:...........................

Signature:.............. Date:......

If operational documentation is affected (see Paragraph 1.K of th

information is needed prior to next normal revision or prior to S

please indicate required service:

Either: Modification Operational Impact (MOI), if available. . YE

Or : Intermediate revision. ................ YE

Important Information: This SB will only be incorporated in your m

operational documentation if this sheet is returned to Airbus and 

duly authorised representative. With the next feasible revision, 

result in

- updating of maintenance documentation to show pre and post S

- updating of maintenance and operational documentation to show 

after embodiment.

If this SB requires previous or simultaneous accomplishment of ot

Airbus shall automatically include them in the manual revisions. 

00-037 for detailed information.

Please return this completed sheet to:

 AIRBUS

 CUSTOMER SERVICES DIRECTORATE

 1 Rond Point Maurice Bellonte

 31707 BLAGNAC CEDEX FRANCE

 Attn: SDC32 Technical Data and Documentation Services

 FAX: (+33) 5 61 93 28 06

 e-mail: sb.reporting@airbus.com

 or via your Resident Customer Support Office.

 Alternatively, SB lists via letters or fax are also accepted.
7 DATE : Dec 31/88 SERVICE BULLETIN No. : A310

REVISION No. : 03 — Nov 28/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(Please rate on a scale of 1 to 4, with 4 being the 

- Quality rating of this SB 

- Quality rating of the Accomplishment Instructions 

- Quality rating of the Illustrations 

- Is this SB easy to understand ? 

If you have had difficulties in the accomplishment of this SB plea

the area(s) and give a short description of the issue.

Planning Material Instruct

X Effectivity X Kit content X Preparat

X Reason X List of Materials X Mod/Insp

X Manpower Operator Supplied X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustra

Comments :

Operator : Date:

Name/Title :

Please return this form to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.