0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 55

TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION 

REINFORCEMENT AS PER MOD.4933 EMBODIMENT

MODIFICATION No. : None

This page transmits Revision No. 05 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 update the Threshold and Inspectio

following ESG analysis, and also to include Flight Hour Limit

CHANGES

SUMMARY

— REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

. EVALUATION TABLE added

— EFFECTIVITY

. Effectivity updated

SERVICE BULLETIN

— 1.A. EFFECTIVITY

. Effectivity updated

— 1.E. COMPLIANCE

. Accomplishment Timescale updated and modified and Grace P

— 1.K. PUBLICATIONS AFFECTED

. Maintenance Planning Document added
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

. Figure 2, sheet 2 changed

NOTE : Lay-out changes due to computerization of this revisio

identified.

NOTE : Changes due to new lay-out per configurations are not 

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

The Revision 04 was issued to provide alternative hi-lok fast

repair.

The revision 03 was issued to remove the inspection procedure 

Service Bulletin after its inclusion in the NTM.

REVISION SEQUENCE

ORIGINAL : Sep 06/88

REVISION No. : 01 — Nov 06/90

REVISION No. : 02 — Feb 07/91

REVISION No. : 03 — Apr 16/97

REVISION No. : 04 — Apr 17/01

REVISION No. : 05 — Oct 13/06

2
0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 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 : 55

TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION 

REINFORCEMENT AS PER MOD.4933 EMBODIMENT

MODIFICATION No. : None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

SB A310-55-2004 is introduced to examine the THS structure to mak

further cracking occurs after the embodiment of SB A310-55-2002 o

Mod.4933C0029.

Accomplishment of this Service Bulletin consists of gaining acces

examining specified fastener holes using the HFEC Rototest inspec

skin chordwise splice is to be examined along the contour of the 

between ribs 3 and 4 on the LH and RH center and side boxes.

Accomplishment of this Service Bulletin will detect any crack aft

embodiment of SB A310-55-2002 or production Mod. 4933C0029.

EFFECTIVITY

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

BAF CES DAH F2I FDX IRA JAV KYV S8G THY

EVALUATION TABLE

COMPLIANCE Mandatory CANCELS INSPECTION S

 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 kit
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

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. 03 . Inspection every 9700 FC or 19500 FH

Config. 02 thru Config. 03 . Inspection every 4800 FC or 9700 FH.

MATERIAL INFORMATION

AIRCRAFT DATA

None

APPENDICES

Appendix 1 - CRACK EVALUATION SHEET

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

2
0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

MANDATORY MANDATORY MAND

ATA SYSTEM : 55

TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION 

REINFORCEMENT AS PER MOD.4933 EMBODIMENT

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

310-203 310-222

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

0162 0172 0191 0201 0217 0224 0230 0233 0237 024

0251 0254 0257 0260 0264 0267 0273 0278 0281 02

0293 0297 0300 0303 0309 0311 0313 0316 0318 03

0333 0335 0338 0339 0342 0343 0345 0346 0349 03

0355-0357 0359 0360 0362 0364 0367 0369 0370 03

0386 0389 0390 0394 0397 0400

(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 Industrie. Any f
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 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:

0172 0311 0313 0316 0318 0320 0326 0331 0333 03

0342-0343 0345-0346 0349 0352-0353 0355-0357 03

0364 0367 0369-0370 0372 0375 0379 0386 0389-039

0400

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 02

0297 0300 0303 0309

CES 0311 0320

DAH 0291 0293

F2I 0309 0352

FDX 0162 0191 0201 0217 0224 0230 0233 0

0248 0251 0254 0257 0260 0264 0267 0

0283 0288 0297 0303 0313 0316 0318 0

0335 0339 0342 0343 0345 0346 0349 0

0359 0360 0362 0364 0369 0394 0397 0

IRA 0338 0370 0375 0379 0389 0390

JAV 0357

KYV 0172

S8G 0300

THY 0386

KIT No. QTY PER A/C CONFIGURATION

01

KIT No. QTY PER A/C CONFIGURATION

02

03

2
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

aircraft MSN 378, 392, 399, 404 and subse

NOTE : Config. 01 is applicable to aircraft that 

production Mod. 4933C0029 embodied.

NOTE : Config. 02 is applicable to aircraft that 

Bulletin A310-55-2002 accomplished before 

NOTE : Config. 03 is applicable to aircraft that 

Bulletin A310-55-2002 accomplished betwee

and 12000 F.C.

(3) Spares

None

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prio

accomplishment of the following Service Bulletin(s) or th

production modification(s):

Service Bulletin No. A310-55-2002 Mod. No. 4933C0029

C. REASON

(1) History

SB A310-55-2004 is introduced to examine the THS str

sure that no further cracking occurs after the embod

A310-55-2002 or production Mod.4933C0029.

(2) Objective/Action

Accomplishment of this Service Bulletin consists of g

to and examining specified fastener holes using the 

inspection. The top skin chordwise splice is to be ex

the contour of the steel doubler between ribs 3 and 4 

RH center and side boxes.

(3) Advantages

Accomplishment of this Service Bulletin will detect a

the embodiment of SB A310-55-2002 or production Mod. 

3
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(1) Config. 01

(a) Removal of the fasteners of the area to be inspe

(b) Inspection of the fastener holes

(c) Inspection of the top skin adjacent to the Steel 

edges.

(d) Inspection of the top Rear Spar area

(e) If no cracks are found install new fasteners of 

diameter.

(f) Application of the surface treatment.

(2) Config. 02 thru Config. 03

(a) Removal of the fasteners of the area to be inspe

(b) Inspection of the fastener holes

(c) Inspection of the top skin adjacent to the Steel 

edges.

(d) Inspection of the top Rear Spar area

(e) If no cracks are found install new fasteners of 

diameter.

(f) Application of the surface treatment.

E. COMPLIANCE

(1) Classification

Mandatory

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is expected t

mandatory by the issue of an Airworthiness Directive 

by the European Aviation Safety Agency (EASA). It is 

that the AD will confirm the (thresholds and/or inte

date) given above but reference should be made to th

confirmation of the mandated accomplishment timescal

4
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

28500 FH and every 9700 FC or 19500 FH thereafter.

— For aircraft modified by A310-55-2002 between 6.000 

inspection is to be carried out every 9700 FC or 1

modification embodied point.

— If cracks were found when SB A310-55-2002 was carr

repair insert was installed at fastener position A 

figure 2). Do not remove this fastener and repair 

these aircraft a repeat HFEC inspection of area B 

figure 3) is to be made every 4800 FC or 9700 FH fr

A31-55-2002 was accomplished, in addition to the 14

28500 FH and 9700 FC or 19500 FH inspections.

For A/C which are close to or beyond the new thresho

inspection interval values, an application tolerance 

applicable, without exceeding previous requirements 

or 18 month, from current SB revision date.

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. 03 . Inspection every 9700 FC or 

Gain access 

Inspection 

Close-up 

5
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

H. WEIGHT AND BALANCE

Not changed

I. ELECTRICAL LOAD DATA

None

J. REFERENCES

Service Bulletin No. A310-55-2002

Appendix 1

K. PUBLICATIONS AFFECTED

L. INTERCHANGEABILITY/MIXABILITY

None

Inspection 

Close-up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Aircraft Maintenance Manual (AMM) : 55-00-00 55-13-11 

55-15-11

Elec. Std. Practices Manual (ESPM) : 20-55-00

Non destructive Testing Manual (NTM) : 55-10-01

Structural Repair Manual (SRM) : 51-24-00 51-40-40

Maintenance Planning Document (MPD) : 55-10-69

6
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

of this Service Bulletin. The address is :

AIRBUS

SPARES SUPPORT AND SERVICES

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet: http://spa

For ordering by fax: +49 40 50 76 25 

(2) Price and Availability

No AIRBUS kit will be provided. Parts required to ac

Service Bulletin are to be purchased by a Spares Pur

B. INDUSTRY SUPPORT INFORMATION

Airbus will not provide industry support for accomplishme

Service Bulletin.

C. LIST OF COMPONENTS

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

NAS1080C8 18 Collar

NAS1080C10 24 Collar

NAS1080C12 6 Collar

NAS1448-11 8 Fastener

NAS1448-11A 4 Fastener

NAS1448-12 2 Fastener

NAS1448-12A 2 Fastener

NAS1448-13 6 Fastener

NAS1448-13A 6 Fastener

NAS1450-11 4 Fastener

NAS1450-12 2 Fastener

NAS1450-13 12 Fastener

NAS1450-13A 6 Fastener

NAS1452-13 6 Fastener

7
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

(2) Components

None

E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR

None

F. TOOLING — PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None

g q

cleaning agent 11-026 As required

chemical conversion coating 13-002 As required

polyurethane primer 16-001C As required

top coats 16-002 As required

polyurethane finish paint 16-018C As required

8
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTICES ARE IN POSITION. MOVEMENT OF COMPONENTS 

INJURE PERSONS.

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS, AND OTH

MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH T

THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND 

IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. 

PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOU

SMOKE. DO NOT BREATHE THE GAS. GET MEDICAL HELP 

OR EYES BECOME IRRITATED.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP 

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY 

MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENAN

REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICA

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIB

— PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOT

NECESSARY ON WIRING AND COMPONENTS.

— REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CON

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. I

CONTAMINATION, REFER TO CHAPTER ESPM 20-55-00, C

(1) Preparation

(a) Config. 01 thru Config. 03

1 Make THS safe. (Refer to AMM 55-00-00 Page b

2 Remove THS apron panels 333AL, 333AT, 333AB a

343AT, 343AB. (Refer to AMM 55-15-11 Page blo

3 Remove THS trailing edge access panels 334AT 

(Refer to AMM 55-13-11 Page block 401 55-13-

55-13-13 Page block 401)

(2) Standard Practices

(a) For specification of the consumable material lis

Service Bulletin, refer to the Consumable Mater

(b) For information on sealing (Refer to SRM 51-24-0

9
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

See the inspection flowchart to follow through the v

inspection/repair phases described in this Service B

Refer to figure 1

B. INSPECTION

(1) Config. 01

(a) Removal of the fasteners of the area to be inspe

Refer to figure 2

CAUTION : IF A REPAIR INSERT WAS INSTALLED DURIN

A310-55-2002 (REFER TO FIG. 2) DO NOT 

FASTENER INDICATED

1 Break the collars fitted on outside of top s

2 Using a mallet push out the bolts inside the 

3 Recover the bolts from the lateral box, thro

hole of the front spar.

 Refer to figure 4

(b) Inspection of the fastener holes

Refer to figure 3 , Area C.

1 Using cleaning agent (Mat No. 11-026) remove 

examination area and particularly from the bo

the removed fasteners.

2 With the aid of a magnifying glass examine t

holes for any scratches, corrosion, cracks, o

which may affect the inspection.

3 If any of the above defects are found, carefu

hole to try and remove the damage before ream

next oversize diameter.

9 Collars

9 Bolts

10
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

or 19500 FH (Refer to NTM 55-10-01, Part 6).

7 If cracks are found inform AIRBUS who will i

repair definition. Record the results of the 

the crack evaluation sheet.

Refer to Appendix 01

(c) Inspection of the top skin adjacent to the Steel 

edges.

Refer to figure 3

1 Using cleaning agent (Mat No. 11-026) make 

edge and surrounding area of the doubler plat

area "A", is free from grease.

2 Using the HFEC method, inspect the top skin 

adjacent to the doubler plate contoured edge

NTM 55-10-01, Part 6, Area A.)

3 If no cracks are found repeat the inspection 

or 19500 FH (Refer to NTM 55-10-01, Part 6).

4 If cracks are found inform AIRBUS who will i

repair definition and record the results of t

on the crack evaluation sheet.

Refer to Appendix 01

(d) Inspection of the top Rear Spar area

Refer to figure 3

1 Using cleaning agent (Mat No. 11-026) make 

edge and surrounding area of the doubler plat

area "B", is free from grease.

2 Using the HFEC method, inspect the rear spar 

to NTM 55-10-01, Part 6, Area B.)

3 If no cracks are found repeat the inspection 

or 19500 FH (Refer to NTM 55-10-01, Part 6).

4 If cracks are found inform AIRBUS who will i

repair definition and record the results of t

on the crack evaluation sheet.

11
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

NOTE : The maximum diameter allowed for that hi

specified in the table as second oversize

diameter is required, contact AIRBUS, ind

many and where are they located, for spec

instructions.

Follow the procedure given below for installatio

— Install a mirror at the end of a rod and attac

bolt in a vertical position to insert it in t

hole.

— Introduce the "equipped stick" inside the late

through the lightning hole of the inboard F/S 

with the aid of the mirror position the faste

correspondent hole. Refer to figure 4

— With the aid of a mallet also attached on a ro

lightning hole, tap the bolt head till the tre

outside the top skin and then install the col

(f) Application of the surface treatment.

1 Make certain that edges of paint have been fe

that no paint residues remain.

2 Remove dirt and grease from surface with clea

(Mat No. 11-026)

3 Apply chemical conversion coating (Mat No. 1

6 Collar NAS1080C12

4 Fastener NAS1448-11

4 Fastener NAS1448-11

18 Collar NAS1080C8

4 Fastener NAS1448-11A

2 Fastener NAS1448-12

2 Fastener NAS1448-12A

6 Fastener NAS1448-13

6 Fastener NAS1448-13A

4 Fastener NAS1450-11

2 Fastener NAS1450-12

12 Fastener NAS1450-13

6 Fastener NAS1450-13A

6 Fastener NAS1452-13

12
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

6 Apply moisture-removing oil (Mat No. 05-005) 

(2) Config. 02 thru Config. 03

(a) Removal of the fasteners of the area to be inspe

Refer to figure 2

CAUTION : IF A REPAIR INSERT WAS INSTALLED DURIN

A310-55-2002 (REFER TO FIG. 2) DO NOT 

FASTENER INDICATED

1 Break the collars fitted on outside of top s

2 Using a mallet push out the bolts inside the 

3 Recover the bolts from the lateral box, thro

hole of the front spar.

 Refer to figure 4

(b) Inspection of the fastener holes

Refer to figure 3 , Area C.

1 Using cleaning agent (Mat No. 11-026) remove 

examination area and particularly from the bo

the removed fasteners.

2 With the aid of a magnifying glass examine t

holes for any scratches, corrosion, cracks, o

which may affect the inspection.

3 If any of the above defects are found, carefu

hole to try and remove the damage before ream

next oversize diameter.

4 Ream to the next oversize diameter any damage

hole. (Refer to SRM 51-40-40 Page block 1)

9 Collars

9 Bolts

13
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

repair definition. Record the results of the 

the crack evaluation sheet.

Refer to Appendix 01

(c) Inspection of the top skin adjacent to the Steel 

edges.

Refer to figure 3

1 Using cleaning agent (Mat No. 11-026) make 

edge and surrounding area of the doubler plat

area "A", is free from grease.

2 Using the HFEC method, inspect the top skin 

adjacent to the doubler plate contoured edge

NTM 55-10-01, Part 6, Area A.)

3 If no cracks are found repeat the inspection 

or 19500 FH (Refer to NTM 55-10-01, Part 6).

4 If cracks are found inform AIRBUS who will i

repair definition and record the results of t

on the crack evaluation sheet.

Refer to Appendix 01

(d) Inspection of the top Rear Spar area

Refer to figure 3

1 Using cleaning agent (Mat No. 11-026) make 

edge and surrounding area of the doubler plat

area "B", is free from grease.

2 Using the HFEC method, inspect the rear spar 

to NTM 55-10-01, Part 6, Area B.)

3 If no cracks are found, and if no repair inse

installed during SB A310-55-2002 embodiment 

figure 2 ), repeat the inspection every 9700 

FH.

4 If no cracks are found, but a repair insert w

during SB A310-55-2002 embodiment (refer to f

repeat the inspection every 4800 FC or 9700 

14
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Refer to figure 2

NOTE : The maximum diameter allowed for that hi

specified in the table as second oversize

diameter is required, contact AIRBUS, ind

many and where are they located, for spec

instructions.

Follow the procedure given below for installatio

— Install a mirror at the end of a rod and attac

bolt in a vertical position to insert it in t

hole.

— Introduce the "equipped stick" inside the late

through the lightning hole of the inboard F/S 

with the aid of the mirror position the faste

correspondent hole. Refer to figure 4

— With the aid of a mallet also attached on a ro

lightning hole, tap the bolt head till the tre

outside the top skin and then install the col

(f) Application of the surface treatment.

1 Make certain that edges of paint have been fe

that no paint residues remain.

24 Collar NAS1080C10

6 Collar NAS1080C12

4 Fastener NAS1448-11

4 Fastener NAS1448-11

18 Collar NAS1080C8

4 Fastener NAS1448-11A

2 Fastener NAS1448-12

2 Fastener NAS1448-12A

6 Fastener NAS1448-13

6 Fastener NAS1448-13A

4 Fastener NAS1450-11

2 Fastener NAS1450-12

12 Fastener NAS1450-13

6 Fastener NAS1450-13A

6 Fastener NAS1452-13

15
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

external surfaces and top coats (Mat No. 16-0

internal surfaces.

NOTE : Where necessary apply top coats to mat

paint scheme.

6 Apply moisture-removing oil (Mat No. 05-005) 

C. TEST

None

D. CLOSE UP

(1) Config. 01 thru Config. 03

(a) Make certain the working area is clean and clea

equipment and loose objects.

(b) Install THS trailing edge access panels 334AT a

(Refer to AMM 55-13-11 Page block 401 and to AMM 

block 401)

(c) Install THS apron panels 333AL, 333AT, 333AB and 

343AB. (Refer to AMM 55-15-11 Page block 401)

E. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

16
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

All Config: Inspection flow-chart

17
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 1

All Config: Inspection of fastener holes

18
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 2 Sheet 2

All Config: Inspection of fastener holes

19
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 3 Sheet 1

All Config: Area to be inspected

20
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 4 Sheet 1

All Config: Access though Front Spar

21
0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page : 1 of 

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Structure Engineering SEE8

Fax number: 33(0)561933614

AIRBUS

CUSTOMER SERVICE DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE
DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 Page :

Printed in FRANCE © AIRBUS, 2006 All rights reserved

Figure 1 Sheet 1

All Config: CRACK EVALUATION SHEET

2
0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 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.
0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310

REVISION No. : 05 — Oct 13/06 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.