7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION FOR 

MODIFICATION No. : None

This page transmits Revision No. 04 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.

— Operators revised.

— Models revised.

CHANGES

SUMMARY :

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. Inspection thresholds and intervals revised. Evaluation 

— EFFECTIVITY

. Operators F2I, FDX and S8G have been added. Operators CY

KAC, KLM, MPH, NGA, SAB and SWR have been deleted. Effect

— MANPOWER

. Configuration layout applied.
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Objective/Action

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

— DESCRIPTION

. 1.D. Configuration layout applied.

. 1.D.(1)(b) Step rewitten.

— 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 and intervals revised.

— APPROVAL

. 1.F. Approval sentence updated. Approval paras added.

— MANPOWER

. 1.G. Configuration layout applied.

ACCOMPLISHMENT INSTRUCTIONS :

— Preparation

. 3.A.(1) Configuration layout applied.

. 3.A.(1)(a)1 Step rewitten.

— INSPECTION

. 3.B. Configuration layout applied.

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

— REPAIR

. 3.C. Configuration layout applied.

2
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

— Figure 1

. Configuration layout applied.

— Figure 2

. 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 : Apr 30/89

REVISION No. : 01 — Jan 06/93

REVISION No. : 02 — Apr 23/93

REVISION No. : 03 — Jan 04/96

REVISION No. : 04 — Dec 01/06

3
7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 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 - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION FOR 

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Cracks have been found during full scale fatigue tests at various 

the wing top skin between rib 7 and rib 14, where there are disco

the leading edge to the top skin joint strap. These cracks were f

from bolt holes running forward to the skin edge and rearwards tow

spar at 41,000 simulated flight cycles (FC).

If the cracks are allowed to extend beyond the limits of normal r

extensive and time consuming repair actions will be required.

Modification 05026H0878 (Service Bulletin A310-57-2005) was intro

prevent the cracks and is recommended to be embodied before the i

threshold.

When modification 05026H0878 has been embodied, no further inspec

required in accordance with this Service Bulletin.

The following mandatory inspection is required not later than 10,

cycles (FC) or 21,000 flight hours (FH) whichever comes first, on 

are Pre modification 05026H0878. Repeat inspections are required 

not exceeding 3,900 FC or 7,900 FH, whichever comes first.

A Detailed Visual inspection of the wing top skin upper surface f

front spar is required between rib 7 and rib 28. Where a crack is 

high frequency Eddy current (HFEC) inspection is required.

Where cracks are verified by a HFEC inspection, all details found 

reported to Airbus (AI/SE-E1) as soon as possible. Where a crack 

forwards, a repair must be carried out within 220 FC or 440 FH, w

first, after the crack has reached the skin edge. Where a crack i

rearward, a repair must be carried out within 220 FC or 440 FH, w

first or before further flights depending on the crack length.
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 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

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

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

2
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

None

3
7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 57

TITLE : WINGS - UPPER SKIN FORWARD OF FRONT SPAR - INSPECTION FOR 

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

A310-203 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

NOTE : Modification 05026H0878 is embodied prio

on aircraft MSN 0172, 0288, 0291, 0293, 0

subsequent.

(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
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 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:

0162 0191 0201 0217 0224 0230 0233 0237 0241 024

0254 0257 0260 0264 0267 0273 0278 0281 0283 029

0309

(3) Spares

None

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Cracks have been found during full scale fatigue test

positions in the wing top skin between rib 7 and rib 

there are discontinuities in the leading edge to the 

strap. These cracks were found emanating from bolt ho

forward to the skin edge and rearwards towards the f

41,000 simulated flight cycles (FC).

If the cracks are allowed to extend beyond the limit

repairs, extensive and time consuming repair actions 

required.

Modification 05026H0878 (Service Bulletin A310-57-200

introduced to prevent the cracks and is recommended t

before the inspection threshold.

FDX 0162 0191 0201 0217 0224 0230 0233 0

0248 0251 0254 0257 0260 0264 0267 0

0283 0297 0303

S8G 0300

KIT No. QTY PER A/C CONFIGURATION

01

2
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Repeat inspections are required at intervals not exce

or 7,900 FH whichever comes first.

A Detailed Visual inspection of the wing top skin up

forward of the front spar is required between rib 7 

Where a crack is suspected a high frequency Eddy cur

inspection is required.

Where cracks are verified by a HFEC inspection, all d

must be reported to Airbus (AI/SE-E1) as soon as pos

crack is running forwards, a repair must be carried o

FC or 440 FH, whichever comes first, after the crack 

the skin edge. Where a crack is running rearward, a 

carried out within 220 FC or 440 FH, whichever comes 

before further flights depending on the crack length

(3) Advantages

Timely detection of cracks may reduce the necessity o

extensive and time consuming repairs.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Gain access to wing top skin, forward.

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

forward of the front spar for cracks.

(c) Carry out repair as necessary.

(d) Close up.

E. COMPLIANCE

(1) Classification

Mandatory

3
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

accomplishment timescale.

(b) Inspections are to be carried out at or before t

of 10,500 FC or 21,000 FH, whichever comes first

inspections are required at intervals not exceed

or 7,900 FH, whichever comes first.

(c) For aircraft that have already exceeded the ins

threshold, the first inspection is to be carried 

than 850 FC or 1,700 FH, whichever comes first, 

receipt of this Service Bulletin and without ex

existing planned next inspection according to re

this Service Bulletin.

(d) The number of touch and go flights can be negle

are less than five percent of the total number o

between two consecutive inspections.

When the percentage of touch and go flights is m

percent of the total number of flights between t

inspections, each touch and go flight beyond fiv

to be counted as a flight cycle.

A touch and go is a landing in which the aircraf

come to a compleat standstill before commencing 

flight.

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.

4
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

H. WEIGHT AND BALANCE

None

I. ELECTRICAL LOAD DATA

Not changed

J. REFERENCES

K. PUBLICATIONS AFFECTED

None

L. INTERCHANGEABILITY/MIXABILITY

None

ELAPSED TIME (HOURS) 

Non destructive Testing Manual (NTM) : Part 6, 51-10-08

Structural Repair Manual (SRM) : 51-10-13

Service Bulletin (SB) : A310-57-2005

5
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

6
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

None

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 : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

This Page Intentionally Left Blank

8
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(a) Config. 01

Refer to figure 1 and figure 2

1 Gain access to the upper wing skin forward of 

spar.

(2) Standard Practices

None

B. INSPECTION

(1) Config. 01

Refer to figure 1 and figure 2

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

skin upper surface, at all areas detailed, arou

denoted 'X'. Where no cracks are found, repeat t

at intervals not exceeding 3,900 FC or 7,900 FH

comes first.

C. REPAIR

(1) Config. 01

Refer to figure 1 and figure 2

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

towards the skin edge, it can be allowed to cont

repeat detailed visual inspections every 220 FC 

whichever comes first, to monitor the cracks pro

reaches the skin edge.

When this has occurred, contact SER1 and report 

details of the crack for a repair solution (Refe

51-10-13 Page block 001).

A repair must be carried out within 220 FC or 44

whichever comes first, after the crack has reac

edge.

(b) Where a crack is found to be extending in an rea

direction, carry out a HFEC inspection around t

position affected (Refer to NTM 51-10-08, part 

601).

9
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

comes first, intervals are required from the in

detection up to the maximum of 220 FC or 440 FH

comes first, to monitor the crack length.

Where the crack exceeds 10.0mm in length, a repa

carried out before the next flight.

D. TEST

None

E. CLOSE UP

(1) Config. 01

(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 : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1 (Goto A3 section)

Wing Leading Edge (Config 01)

11
DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1 (Goto A3 section)

Bolt Positions at Skin Strap (Config 01)

13
7 DATE : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 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 : Apr 30/89 SERVICE BULLETIN No. : A310

REVISION No. : 04 — Dec 01/06 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.
@ A310

SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032REVISION No. : 04 — Dec 01/06 Page : 11/12

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

Wing Leading Edge (Config 01)
@ A310

SERVICE BULLETIN

DATE : Apr 30/89 SERVICE BULLETIN No. : A310—57—2032REVISION No. : 04 — Dec 01/06 Page : 13/14

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1

Bolt Positions at Skin Strap (Config 01)