# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : 1 of 2 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 55 TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION PROGRAM AFTER REINFORCEMENT AS PER MOD.4933 EMBODIMENT MODIFICATION No. : None This page transmits Revision No. 05 of Service Bulletin No. A310-55-2004 ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous issue. REASON This revision is issued to update the Threshold and Inspection Interval following ESG analysis, and also to include Flight Hour Limitations. 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 Period added — 1.K. PUBLICATIONS AFFECTED . Maintenance Planning Document added

# @ A310 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved — 3.B. INSPECTION . Threshold and Inspection Interval changed — ILLUSTRATION . Figure 1 changed . Figure 2, sheet 2 changed NOTE : Lay-out changes due to computerization of this revision are not identified. NOTE : Changes due to new lay-out per configurations are not identified. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS The Revision 04 was issued to provide alternative hi-lok fasteners to repair. The revision 03 was issued to remove the inspection procedure from the 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

# @ A310 SERVICE BULLETIN SUMMARY

0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : 1 of 2 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 This summary is for information only and is not approved for modification of the aircraft 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 55 TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION PROGRAM AFTER 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 make sure that no further cracking occurs after the embodiment of SB A310-55-2002 or production Mod.4933C0029. Accomplishment of this Service Bulletin consists of gaining access to and examining specified fastener holes using the HFEC Rototest inspection. The top skin chordwise splice is to be examined along the contour of the steel doubler between ribs 3 and 4 on the LH and RH center and side boxes. Accomplishment of this Service Bulletin will detect any crack after the 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 SB No AD Yes A/C OPERATION AFFECTED No RELIABILITY AFFECTED No PAX COMFORT AFFECTED No COST SAVING No ETOPS AFFECTED No STRUCTURAL LIFE EXTN No VENDOR SB INVOLVED No KIT PRICE (USD) No kit

# @ A310 SERVICE BULLETIN SUMMARY

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved CONCURRENT REQUIREMENTS Accomplishment of this Service Bulletin requires the prior accomplishment of the following Service Bulletin(s) or the equivalent production modification(s): Service Bulletin No. A310-55-2002 Mod. No. 4933C0029 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. 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 15.50 ELAPSED TIME (HOURS) 15.50

TOTAL MANHOURS 2.50 ELAPSED TIME (HOURS) 3.00

2

# @ A310 SERVICE BULLETIN

0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : 1 of 21 Printed in FRANCE © AIRBUS, 2006 All rights reserved AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51 

# MANDATORY MANDATORY MANDATORY

ATA SYSTEM : 55 TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION PROGRAM AFTER REINFORCEMENT AS PER MOD.4933 EMBODIMENT MODIFICATION No. : None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the 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 MSN : 0162 0172 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0300 0303 0309 0311 0313 0316 0318 0320 0326 0331 0333 0335 0338 0339 0342 0343 0345 0346 0349 0352 0353 0355-0357 0359 0360 0362 0364 0367 0369 0370 0372 0375 0379 0386 0389 0390 0394 0397 0400 (b) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS Industrie. Any future changes

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason.

(c) Effectivity by MSN and Kit/Configuration The kits and configurations applicable to these MSNs are given at the end of this list: 0172 0311 0313 0316 0318 0320 0326 0331 0333 0335 0338-0339 0342-0343 0345-0346 0349 0352-0353 0355-0357 0359-0360 0362 0364 0367 0369-0370 0372 0375 0379 0386 0389-0390 0394 0397 0400

The kits and configurations applicable to these MSNs are given at the end of this list: 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0291 0293 0297 0300 0303 0309 OPERATOR MSN BAF 0367 0372 CES 0311 0320 DAH 0291 0293 F2I 0309 0352 FDX 0162 0191 0201 0217 0224 0230 0233 0237 0241 0245 0248 0251 0254 0257 0260 0264 0267 0273 0278 0281 0283 0288 0297 0303 0313 0316 0318 0326 0331 0333 0335 0339 0342 0343 0345 0346 0349 0353 0355 0356 0359 0360 0362 0364 0369 0394 0397 0400 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved NOTE : This Service Bulletin is applicable to those aircraft listed above which have had SB A310-55-2002 embodied or had mod. 4933C0029 embodied in production. Mod. 4933C0029 was embodied in production from MSN 311 to MSN 400. NOTE : This Service Bulletin is not applicable to aircraft that have had mod. 6070C0075 embodied in production; aircraft MSN 378, 392, 399, 404 and subsequent. NOTE : Config. 01 is applicable to aircraft that have the production Mod. 4933C0029 embodied. NOTE : Config. 02 is applicable to aircraft that have Service Bulletin A310-55-2002 accomplished before 6000 F.C. NOTE : Config. 03 is applicable to aircraft that have Service Bulletin A310-55-2002 accomplished between 6000 F.C. and 12000 F.C. (3) Spares None B. CONCURRENT REQUIREMENTS Accomplishment of this Service Bulletin requires the prior accomplishment of the following Service Bulletin(s) or the equivalent 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 structure to make sure that no further cracking occurs after the embodiment of SB A310-55-2002 or production Mod.4933C0029. (2) Objective/Action Accomplishment of this Service Bulletin consists of gaining access to and examining specified fastener holes using the HFEC Rototest inspection. The top skin chordwise splice is to be examined along the contour of the steel doubler between ribs 3 and 4 on the LH and RH center and side boxes. (3) Advantages Accomplishment of this Service Bulletin will detect any crack after the embodiment of SB A310-55-2002 or production Mod. 4933C0029.

3

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Config. 01 (a) Removal of the fasteners of the area to be inspected. (b) Inspection of the fastener holes (c) Inspection of the top skin adjacent to the Steel Doubler Plate edges. (d) Inspection of the top Rear Spar area (e) If no cracks are found install new fasteners of the required diameter. (f) Application of the surface treatment. (2) Config. 02 thru Config. 03 (a) Removal of the fasteners of the area to be inspected. (b) Inspection of the fastener holes (c) Inspection of the top skin adjacent to the Steel Doubler Plate edges. (d) Inspection of the top Rear Spar area (e) If no cracks are found install new fasteners of the required diameter. (f) Application of the surface treatment. E. COMPLIANCE (1) Classification Mandatory (2) Accomplishment Timescale Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale.

4

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved The inspection program is to be carried out as follow: — For aircraft MSN 311-400 that have modification 4933 embodied in production the first inspection is to be carried out at 14400 FC or 28500 FH and every 9700 FC or 19500 FH thereafter. — For aircraft modified by A310-55-2002 before 6.000 flight cycles (FC) the first inspection is to be carried out at 14400 FC or 28500 FH and every 9700 FC or 19500 FH thereafter. — For aircraft modified by A310-55-2002 between 6.000 and 12.000 FC inspection is to be carried out every 9700 FC or 19500 FH from modification embodied point. — If cracks were found when SB A310-55-2002 was carried out, a repair insert was installed at fastener position A (Refer to figure 2). Do not remove this fastener and repair insert. For these aircraft a repeat HFEC inspection of area B (Refer to figure 3) is to be made every 4800 FC or 9700 FH from the time SB A31-55-2002 was accomplished, in addition to the 14400 FC or 28500 FH and 9700 FC or 19500 FH inspections. For A/C which are close to or beyond the new threshold or inspection interval values, an application tolerance of 1500 FC is applicable, without exceeding previous requirements (if existing) or 18 month, from current SB revision date. F. APPROVAL Approved under the EASA Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin. G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator's circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration work are also not included. Config. 01 thru Config. 03 . Inspection every 9700 FC or 19500 FH Gain access 3.00 Inspection 2.50 Close-up 10.00

5

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Config. 02 thru Config. 03 . Inspection every 4800 FC or 9700 FH.

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 TOTAL MANHOURS 15.50 ELAPSED TIME (HOURS) 15.50

Gain access 0.50 Inspection 2.00 Close-up 0.50 TOTAL MANHOURS 2.50 ELAPSED TIME (HOURS) 3.00

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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2. MATERIAL INFORMATION A. MATERIAL — PRICE AND AVAILABILITY (1) Material Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number 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://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 (2) Price and Availability No AIRBUS kit will be provided. Parts required to accomplish this Service Bulletin are to be purchased by a Spares Purchase Order. B. INDUSTRY SUPPORT INFORMATION Airbus will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. INT INST DISP 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved D. LIST OF MATERIALS — OPERATOR SUPPLIED (1) Consumable Materials

(2) Components None E. PARTS TO BE RE—IDENTIFIED BY THE OPERATOR None F. TOOLING — PRICE AND AVAILABILITY None G. SPECIAL TOOLS None DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C INST DISP moisture-removing oil 05-005 As required 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION. MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS. WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS, AND OTHER SPECIAL MATERIALS ONLY WITH A GOOD FLOW OF AIR THROUGH THE WORK AREA. THESE MATERIALS ARE POISONOUS AND FLAMMABLE AND SKIN IRRITANTS. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: — PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC. AS NECESSARY ON WIRING AND COMPONENTS. — REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO CHAPTER ESPM 20-55-00, CLEANING. (1) Preparation (a) Config. 01 thru Config. 03 1 Make THS safe. (Refer to AMM 55-00-00 Page block 301) 2 Remove THS apron panels 333AL, 333AT, 333AB and 343AR, 343AT, 343AB. (Refer to AMM 55-15-11 Page block 401) 3 Remove THS trailing edge access panels 334AT and 344AT. (Refer to AMM 55-13-11 Page block 401 55-13-13 and to AMM 55-13-13 Page block 401) (2) Standard Practices (a) For specification of the consumable material list used in this Service Bulletin, refer to the Consumable Material List (CML) (b) For information on sealing (Refer to SRM 51-24-00)

9

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved (c) Clean the area and surfaces to be sealed or painted with cleaning agent (Mat No. 11-026) . (d) Deburr and protect with alodine 1200 (Mat No. 13-002) all the drilled holes. (3) Work Breakdown See the inspection flowchart to follow through the various inspection/repair phases described in this Service Bulletin. Refer to figure 1 B. INSPECTION (1) Config. 01 (a) Removal of the fasteners of the area to be inspected. Refer to figure 2 CAUTION : IF A REPAIR INSERT WAS INSTALLED DURING SB A310-55-2002 (REFER TO FIG. 2) DO NOT REMOVE THE FASTENER INDICATED 1 Break the collars fitted on outside of top skin.
2 Using a mallet push out the bolts inside the lateral box. 3 Recover the bolts from the lateral box, through the access 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 grease from examination area and particularly from the bore holes of the removed fasteners. 2 With the aid of a magnifying glass examine the fastener holes for any scratches, corrosion, cracks, or ovality which may affect the inspection. 3 If any of the above defects are found, carefully polish the hole to try and remove the damage before reaming to the next oversize diameter. 9 Collars

9 Bolts

10

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 4 Ream to the next oversize diameter any damaged or irregular hole. (Refer to SRM 51-40-40 Page block 1) 5 Inspect the fastener holes shown in figure 2 and 3 using High Frequency Eddy Current (HFEC), as described in NTM 55-10-01, Part 6, Area C. 6 If no cracks are found repeat the inspection every 9700 FC or 19500 FH (Refer to NTM 55-10-01, Part 6). 7 If cracks are found inform AIRBUS who will issue a special repair definition. Record the results of the inspection on the crack evaluation sheet. Refer to Appendix 01 (c) Inspection of the top skin adjacent to the Steel Doubler Plate edges. Refer to figure 3 1 Using cleaning agent (Mat No. 11-026) make sure that the edge and surrounding area of the doubler plate, inspection area "A", is free from grease. 2 Using the HFEC method, inspect the top skin surface adjacent to the doubler plate contoured edges. (Refer to NTM 55-10-01, Part 6, Area A.) 3 If no cracks are found repeat the inspection every 9700 FC or 19500 FH (Refer to NTM 55-10-01, Part 6). 4 If cracks are found inform AIRBUS who will issue a special repair definition and record the results of the inspection 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 sure that the edge and surrounding area of the doubler plate, inspection area "B", is free from grease. 2 Using the HFEC method, inspect the rear spar area. (Refer to NTM 55-10-01, Part 6, Area B.) 3 If no cracks are found repeat the inspection every 9700 FC or 19500 FH (Refer to NTM 55-10-01, Part 6). 4 If cracks are found inform AIRBUS who will issue a special repair definition and record the results of the inspection on the crack evaluation sheet.

11

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved Refer to Appendix 01 (e) If no cracks are found install new fasteners of the required diameter. Refer to figure 2

NOTE : The maximum diameter allowed for that hi-loks are the specified in the table as second oversize. If a higher diameter is required, contact AIRBUS, indicating how many and where are they located, for specific instructions. Follow the procedure given below for installation: — Install a mirror at the end of a rod and attach also the bolt in a vertical position to insert it in the top skin hole. — Introduce the "equipped stick" inside the lateral box through the lightning hole of the inboard F/S web plate, and with the aid of the mirror position the fastener in the correspondent hole. Refer to figure 4 — With the aid of a mallet also attached on a rod, through the lightning hole, tap the bolt head till the tread comes outside the top skin and then install the collar on it. (f) Application of the surface treatment. 1 Make certain that edges of paint have been feathered and that no paint residues remain. 2 Remove dirt and grease from surface with cleaning agent (Mat No. 11-026) 3 Apply chemical conversion coating (Mat No. 13-002) 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

12

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 4 Apply polyurethane primer (Mat No. 16-001C) 5 Apply polyurethane finish paint (Mat No. 16-018C) to external surfaces and top coats (Mat No. 16-002) to internal surfaces. NOTE : Where necessary apply top coats to match original paint scheme. 6 Apply moisture-removing oil (Mat No. 05-005) if required. (2) Config. 02 thru Config. 03 (a) Removal of the fasteners of the area to be inspected. Refer to figure 2 CAUTION : IF A REPAIR INSERT WAS INSTALLED DURING SB A310-55-2002 (REFER TO FIG. 2) DO NOT REMOVE THE FASTENER INDICATED 1 Break the collars fitted on outside of top skin.
2 Using a mallet push out the bolts inside the lateral box. 3 Recover the bolts from the lateral box, through the access 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 grease from examination area and particularly from the bore holes of the removed fasteners. 2 With the aid of a magnifying glass examine the fastener holes for any scratches, corrosion, cracks, or ovality which may affect the inspection. 3 If any of the above defects are found, carefully polish the hole to try and remove the damage before reaming to the next oversize diameter. 4 Ream to the next oversize diameter any damaged or irregular hole. (Refer to SRM 51-40-40 Page block 1) 9 Collars

9 Bolts

13

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 5 Inspect the fastener holes shown in figure 2 and 3 using High Frequency Eddy Current (HFEC), as described in NTM 55-10-01, Part 6, Area C. 6 If no cracks are found repeat the inspection every 9700 FC or 19500 FH (Refer to NTM 55-10-01, Part 6). 7 If cracks are found inform AIRBUS who will issue a special repair definition. Record the results of the inspection on the crack evaluation sheet. Refer to Appendix 01 (c) Inspection of the top skin adjacent to the Steel Doubler Plate edges. Refer to figure 3 1 Using cleaning agent (Mat No. 11-026) make sure that the edge and surrounding area of the doubler plate, inspection area "A", is free from grease. 2 Using the HFEC method, inspect the top skin surface adjacent to the doubler plate contoured edges. (Refer to NTM 55-10-01, Part 6, Area A.) 3 If no cracks are found repeat the inspection every 9700 FC or 19500 FH (Refer to NTM 55-10-01, Part 6). 4 If cracks are found inform AIRBUS who will issue a special repair definition and record the results of the inspection 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 sure that the edge and surrounding area of the doubler plate, inspection area "B", is free from grease. 2 Using the HFEC method, inspect the rear spar area. (Refer to NTM 55-10-01, Part 6, Area B.) 3 If no cracks are found, and if no repair insert was installed during SB A310-55-2002 embodiment (refer to figure 2 ), repeat the inspection every 9700 FC or 19500 FH. 4 If no cracks are found, but a repair insert was installed during SB A310-55-2002 embodiment (refer to figure 2 ), repeat the inspection every 4800 FC or 9700 FH.

14

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 5 If cracks are found inform AIRBUS who will issue a special repair definition and record the results of the inspection on the crack evaluation sheet. Refer to Appendix 01 (e) If no cracks are found install new fasteners of the required diameter. Refer to figure 2

NOTE : The maximum diameter allowed for that hi-loks are the specified in the table as second oversize. If a higher diameter is required, contact AIRBUS, indicating how many and where are they located, for specific instructions. Follow the procedure given below for installation: — Install a mirror at the end of a rod and attach also the bolt in a vertical position to insert it in the top skin hole. — Introduce the "equipped stick" inside the lateral box through the lightning hole of the inboard F/S web plate, and with the aid of the mirror position the fastener in the correspondent hole. Refer to figure 4 — With the aid of a mallet also attached on a rod, through the lightning hole, tap the bolt head till the tread comes outside the top skin and then install the collar on it. (f) Application of the surface treatment. 1 Make certain that edges of paint have been feathered and 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : Printed in FRANCE © AIRBUS, 2006 All rights reserved 2 Remove dirt and grease from surface with cleaning agent (Mat No. 11-026) 3 Apply chemical conversion coating (Mat No. 13-002) 4 Apply polyurethane primer (Mat No. 16-001C) 5 Apply polyurethane finish paint (Mat No. 16-018C) to external surfaces and top coats (Mat No. 16-002) to internal surfaces. NOTE : Where necessary apply top coats to match original paint scheme. 6 Apply moisture-removing oil (Mat No. 05-005) if required. C. TEST None D. CLOSE UP (1) Config. 01 thru Config. 03 (a) Make certain the working area is clean and clear of tools, equipment and loose objects. (b) Install THS trailing edge access panels 334AT and 344AT. (Refer to AMM 55-13-11 Page block 401 and to AMM 55-13-13 Page block 401) (c) Install THS apron panels 333AL, 333AT, 333AB and 343AR, 343AT, 343AB. (Refer to AMM 55-15-11 Page block 401) E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in the Service Bulletin.

16

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 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

# @ A310 SERVICE BULLETIN

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 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

# @ A310 SERVICE BULLETIN APPENDIX 01

0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : 1 of 2 Printed in FRANCE © AIRBUS, 2006 All rights reserved CRACK EVALUATION SHEET In order to evaluate the appearance of cracks in the whole A310 fleet, when you carry out the crack inspection, please fill out and return the attached CRACK EVALUATION SHEET to: Customer Services Engineering and Technical Support Structure Engineering SEE8 Fax number: 33(0)561933614 AIRBUS CUSTOMER SERVICE DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE

# @ A310 SERVICE BULLETIN APPENDIX 01

DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 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

# @ A310 SERVICE BULLETIN REPORTING SHEET

0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved TITLE : STABILIZER - HORIZONTAL TAILPLANE STRUCTURE - INSPECTION PROGRAM AFTER REINFORCEMENT AS PER MOD.4933 EMBODIMENT MODIFICATION No. : None
Please complete the appropriate item (A or B): A - SB WILL BE embodied............. YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (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 this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service: Either: Modification Operational Impact (MOI), if available. . YES/NO Or : Intermediate revision.
................ YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - updating of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 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.

# @ A310 SERVICE BULLETIN QUALITY PERCEPTION FORM

0 DATE : Sep 06/88 SERVICE BULLETIN No. : A310—55—2004 REVISION No. : 05 — Oct 13/06 Page : 1 of 1 Printed in FRANCE © AIRBUS, 2006 All rights reserved Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 4 3 2 1 - Quality rating of the Accomplishment Instructions 4 3 2 1 - Quality rating of the Illustrations 4 3 2 1 - Is this SB easy to understand ? Y / N If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a short description of the issue. Planning Material Instructions X Effectivity X Kit content X Preparation X Reason X List of Materials X Mod/Inspection X Manpower Operator Supplied X Test X References X Re-identification X Close-Up X Publication X Tooling X Illustrations 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.