# @A310 SERVICE BULLETIN SUMMARY 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. 

# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - AFT SECTION - INSPECT PAX DOOR FRAME HOLES AT FR73A **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During the preparation phase for conversion of an A300-600 aircraft from PAX to Freighter, a crack was detected in Door Frame(FR) 73A, between STGR24 to STGR25, LH/RH. The crack initiation was found on the seal retainer run out rivet hole, near the frame web of door stops No.8. Because the A310 and A300-600 aircraft have the same structural door frame design, AIRBUS has decided to do a special detailed inspection of FR73A on A310 aircraft. This Service Bulletin requires the operator to introduce a High Frequency Eddy Current (HFEC) inspection of the seal retainer run out rivet hole at FR73A. Accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible crack propagation and will contribute to ensure the structural integrity of the door frame FR73A. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL 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 NOTE (1): Service Bulletin must be accomplished. MATERIAL PRICE INFORMATION No Material DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A310 SERVICE BULLETIN SUMMARY EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

82Z 85Z 98W 99Y AFG BBC C9L F2I FDX GAF HFY IRA IRM IYE K1P KAC KZU MGL PIA QAF R1T RJA ROT RZO SGX TSC UBD UZB WHT CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 532138-832-848-001: Inspection TOTAL MANHOURS 3.75 ELAPSED TIME (HOURS) 2.75 APPENDICES Appendix 01 - Elapsed Time Assumption

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 2 6

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# @A310 SERVICE BULLETIN SUMMARY

**CONF ALL

STGR18

STGR22X STGR22A STGR23 STGR24 STGR25 STGR26
STGR27 STGR28 STGR29 FR73 FR73A FR74 FR75 FR75A FR76 

### A Z260



## A INSPECTION OF DOOR FRAME HOLES

LH SHOWN RH SYMMETRICAL

B_SB_532138_6_SAAA_01_00

Figure A-GSAAA - Sheet 01
DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 3 6

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# @A310 SERVICE BULLETIN SUMMARY

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# @A310 SERVICE BULLETIN
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



# MANDATORYMANDATORYMANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - AFT SECTION - INSPECT PAX DOOR FRAME HOLES AT FR73A 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 **CONF ALL A. EFFECTIVITY (1) Models 310-304 310-308 310-324 310-325 (2) Effectivity by MSN 0489-0492 0494-0500 0503 0519-0520 0522-0524 0526-0527 0537 0539 0545 0547 0549-0552 0562 0564-0565 0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624 0636 0644 0646-0649 0651-0653 0656 0658 0660-0661 0663 0667 0671-0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 (3) 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. Any future changes 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. OPERATOR MSN 82Z 0550 0551 DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A310 SERVICE BULLETIN
OPERATOR MSN 85Z 0527 98W 0495 99Y 0489 AFG 0496 0497 BBC 0594 0700 C9L 0652 F2I 0520 FDX 0492 0500 0539 0549 0552 0593 GAF 0498 0503 0522 0523 HFY 0565 IRA 0671 IRM 0499 0524 0537 0547 0564 0567 0586 0595 0620 IYE 0568 0702 0704 K1P 0648 KAC 0647 0649 0663 KZU 0592 0622 0646 MGL 0526 PIA 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691 QAF 0667 R1T 0591 RJA 0490 0491 ROT 0636 0644 RZO 0571 0624 0651 0661 SGX 0519 0562 TSC 0545 0588 0597 0599 0600 0658 UBD 0672 0674 UZB 0574 0576 0706 WHT 0494 (4) Configuration by MSN MSN CONFIGURATION 0489 0490 0491 0492 0494 0495 0496 0497 0498 0499 0500 0503 0519 0520 0522 0523 0524 0526 0527 0537 0539 0545 0547 0549 0550 0551 0552 0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587 0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620 0622 0624 0636 0644 0646 0647 0648 0649 0651 0652 0653 0656 0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682 0687 0689 0691 0700 0702 0704 0706 001

(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 2 6

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# @A310 SERVICE BULLETIN (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History During the preparation phase for conversion of an A300-600 aircraft from PAX to Freighter, a crack was detected in Door Frame(FR) 73A, between STGR24 to STGR25, LH/RH. The crack initiation was found on the seal retainer run out rivet hole, near the frame web of door stops No.8. Because the A310 and A300-600 aircraft have the same structural door frame design, AIRBUS has decided to do a special detailed inspection of FR73A on A310 aircraft. (2) Objective/Action This Service Bulletin requires the operator to introduce a High Frequency Eddy Current (HFEC) inspection of the seal retainer run out rivet hole at FR73A. (3) Advantages Accomplishment of this Service Bulletin will allow early detection of cracks in order to avoid possible crack propagation and will contribute to ensure the structural integrity of the door frame FR73A. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 532138-832-848-001: Inspection (1) Do a HFEC inspection for cracks at FR73A LH (2) Do a HFEC inspection for cracks at FR73A RH E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 3 6

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# @A310 SERVICE BULLETIN (2) Accomplishment Timescale This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued to confirm this classification. It is anticipated that the AD will confirm the (thresholds and/or intervals and/or date) given below but reference should be made to the AD for confirmation of the mandated accomplishment timescale. Table 01: Config 001- Inspection of seal retainer run out rivet hole at frame 73A Compliance Time Whichever occurs later Condition Action Threshold: Grace Period: Repetitive interval
All aircraft Do a HFEC inspection of the seal retainer run out rivet hole at frame 73A 32000 FC from aircraft first flight Whichever occurs first between a) and b) a)Before 36000 FC from aircraft first flight or b) within 36 months after the Service Bulletin issue date 7500 FC

Contact AIRBUS Repair support Before the next flight none none Crack findings Report inspection result to AIRBUS Within 10 days none none Report inspection result to AIRBUS Within 1 month none none No crack findings Next HFEC inspection of the seal retainer run out rivet hole at frame 73A none none 7500FC

F. APPROVAL The technical content of this document is approved under the authority of 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.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 4 6

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# @A310 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. Task 532138-832-848-001: Inspection Get Access 1.00 On Aircraft Do a HFEC inspection for cracks at FR73A LH 0.50 Do a HFEC inspection for cracks at FR73A RH 0.50 Tests 1.50 Close-Up 0.25 TOTAL MANHOURS 3.75 ELAPSED TIME (HOURS) 2.75 NOTE: For a breakdown of the manhours and elapsed time, refer to the Gantt Chart Fig. A-GAAAA as given in Appendix 01 H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-21-00 06-31-53 06-41-00 20-21-12 24-00-00 24-41-00 25-00-00 25-12-11 25-22-11 25-23-41 52-10-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-52-10 20-55-00 Non Destructive Test Manual (NTM) 51-10-08 Structural Repair Manual (SRM) 51-24-00 51-40-20 K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 531814-02-1 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 5 6

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# @A310 SERVICE BULLETIN

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# @A310 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY No Material Set B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS No Kit D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Non Aqueous Cleaner-General - - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools To accomplish this Service Bulletin it is necessary to use the tools listed in NTM 51-10-08, Page Block 601. (3) Special Tools None DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 7 6

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# @A310 SERVICE BULLETIN

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# @A310 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 532138-832-848-001 - Inspection WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: INSTALL A SAFETY BARRIER OR MAKE SURE THAT THE ACCESS PLATFORM IS IN POSITION BEFORE YOU OPEN A DOOR. A FALL FROM THE DOOR OPENING CAN BE DANGEROUS. 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. IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words ’refer to’ are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words ’in accordance with’ are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. NOTE: The purpose of flow charts is to supplement the information given in the Procedure

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 9 6

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# @A310 SERVICE BULLETIN and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. Task Associated Data Zone 260 Manpower TOTAL MANHOURS 3.75 ELAPSED TIME (HOURS) 2.75 A. GENERAL (1) Subtask 532138-910-201-001 - Standard Practices Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) 06-21-00, Page Block 001 06-31-53, Page Block 001 06-41-00, Page Block 001 20-21-12, Page Block 001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-52-10 Structural Repair Manual (SRM) 51-24-00 51-40-20 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Material List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-21-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-00, Page Block 001. (e) Do a check of the electrical connectors before you connect them, refer to ESPM 20-52-10. (f) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page Block 001. (g) Remove and install fasteners in accordance with SRM 51-40-20. (h) Use a non-metallic spatula to remove the sealant and clean the surface. (i) Apply sealant in accordance with SRM 51-24-00.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 10 6

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# @A310 SERVICE BULLETIN (2) Subtask 532138-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 532138-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A LH/RH Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 24-00-00, Page Block 301 24-41-00, Page Block 301 25-00-00, Page Block 801 25-22-11, Page Block 401 25-23-41, Page Block 401 52-10-00, Page Block 001 (a) The following items shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked. - Aircraft in clean configuration. - Parking brake applied. - Aircraft electrical network de-energized. - Hydraulic systems depressurized. - Access to the cockpit and cabin is available. - All circuit breakers are in closed position. - All controls in NORM, AUTO or OFF position. (b) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page Block 301. (c) Energize the ground service network, refer to AMM 24-41-00, Page Block 301. DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 11 6

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# @A310 SERVICE BULLETIN (d) Put an access platform in position at the AFT passenger/crew doors 833 and 843. (e) Open the AFT passenger/crew doors 833 and 843, refer to AMM 52-10-00, Page Block 001. (f) Open, safety/lock and tag the applicable circuit breakers as specified in the removal of door frame linings, refer to AMM 25-23-41, Page Block 401. (g) At Frame 73A, remove the door frame linings for access, refer to AMM 25-23-41, Page Block 401. (h) Put blanking caps on the disconnected electrical connectors. (i) Between Frame 73 and Frame 73A, remove the heat and sound insulation blankets for access, refer to AMM 25-22-11, Page Block 401. (j) If necessary for repair of insulation blankets, refer to AMM 25-00-00, Page Block 801. C. PROCEDURE (1) Subtask 532138-250-201-001 - Do a HFEC inspection for cracks at FR73A LH Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A LH from Stringer 24 to Stringer 25 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GBAAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 12 6

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# @A310 SERVICE BULLETIN

References Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 (a) At Frame 73A LH, between STGR 24 and STGR 25 as shown on Fig. A-GBAAA Sheet 01 , Detail A and Fig. A-GBAAA Sheet 02, Detail B, clean the inspection surface with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of the seal retainer run out hole at Frame 73A LH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBAAA Sheet 01 , View A, Fig. A-GBAAA Sheet 02, View B and the on flow chart Fig. A-GFAAA Sheet 01 , at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet 01 , View A and Fig. A-GBAAA Sheet 02, View B. 2 If there are no cracks:
a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). 3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. (2) Subtask 532138-250-202-001 - Do a HFEC inspection for cracks at FR73A RH Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A RH from Stringer 24 to Stringer 25

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 13 6

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# @A310 SERVICE BULLETIN
Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral - 08BAA9 As required Textile-Lint Free Cotton - 14SBA1 As required References Non Destructive Test Manual (NTM) 51-10-08, Page Block 601 Fig. A-GBAAA HFEC Inspection from the seal retainer run out rivet hole Sheet 01 Sheet 02 Fig. A-GFAAA HFEC Inspection Flow Chart Sheet 01 Fig. A-GRAAA HFEC inspection Reporting Sheet Sheet 01 (a) At Frame 73A RH, between STGR 24 and STGR 25 as shown on Fig. A-GBAAA Sheet 01 , Detail A and Fig. A-GBAAA Sheet 02, Detail B, clean the inspection surface with: Textile-Lint Free Cotton - 14SBA1 As required Non Aqueous Cleaner-General - 08BAA9 As required (b) Do a High-Frequency Eddy-Current (HFEC) inspection for cracks around the rivet head of the seal retainer run out hole at Frame 73A RH, refer to NTM 51-10-08, Page Block 601, Fig. A-GBAAA Sheet 01 , View A, Fig. A-GBAAA Sheet 02, View B and the flow chart Fig. A-GFAAA Sheet 01 at the threshold given in Para 1.E.(2). 1 Scanning probe to be circled around the rivet head of seal retainer run out hole within an area of 10.0 mm (0.39 in.) as shown on Fig. A-GBAAA Sheet 01 , View A and Fig. A-GBAAA Sheet 02, View B. 2 If there are no cracks:
a Report the inspection results within 1 month to AIRBUS, refer to Fig. AGRAAA Sheet 01

. b Repeat the HFEC inspection at intervals given in Para 1.E.(2). DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 14 6

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# @A310 SERVICE BULLETIN
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next flight. b Report the inspection results within 10 days to AIRBUS, refer to Fig. AGRAAA Sheet 01

. D. TEST (1) Subtask 532138-720-201-001 - Functional Work Zones and Access Panels Zone Access/Work location 260 Work location Frame 73A LH/RH Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 25-12-11, Page Block 401 25-23-41, Page Block 401 (a) Between Frame 73A and Frame 73 LH/RH, install the heat and insulation blankets, refer to AMM 25-12-11, Page Block 401. (b) Remove the blanking caps from the disconnected electrical connectors. (c) Install the door frame linings, refer to AMM 25-23-41, Page Block 401. (d) Remove the safety clips and/or the tags and close/unlock the applicable circuit breakers as specified after installation of the door frame linings, refer to AMM 25-23-41, Page Block 401. (e) Do a functional test of exit lights as specified after installation on the door frame linings, refer to AMM 25-23-41, Page Block 401. E. CLOSE-UP (1) Subtask 532138-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 260 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 52-10-00, Page Block 001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 15 6

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# @A310 SERVICE BULLETIN (b) Close the AFT passenger/crew doors 833 and 843, refer to AMM 52-10-00, Page Block 001. (c) Remove the access platform(s).

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 16 6

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# @A310 SERVICE BULLETIN

**CONF ALL

STGR18

STGR22X STGR22A STGR23 STGR24 STGR25 STGR26
STGR27 STGR28 STGR29 FR73 FR73A FR74 FR75 FR75A FR76 

### B



## A LH SHOWN RH SYMMETRICAL SEAL REATAINER 

### A Z260

B_SB_532138_6_BAAA_01_00 Figure A-GBAAA - Sheet 01 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 17 6

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# @A310 SERVICE BULLETIN

**CONF ALL

STGR22A

STGR23

STGR24

STGR25 FR73A

AREA TO BE INSPECTED. MINIMUM 10.0mm (0.39 in) AROUND RIVET HEAD. DOOR STOP 8

10.0 mm (0.39 in)

LH SHOWN RH SYMMETRICAL VIEW LOOKING AFT SEAL RETAINER



## B

B_SB_532138_6_BAAA_02_01 Figure A-GBAAA - Sheet 02 HFEC Inspection from the seal retainer run out rivet hole DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 18 6

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# @A310 SERVICE BULLETIN

**CONF ALL

NO CRACKS FOUND

CONTACT AIRBUS REPAIR SUPPORT BEFORE NEXT FLIGHT

REPORT INSPECTION RESULT WITHIN 10 DAYS TO AIRBUS 1 MONTH TO AIRBUS REPORT INSPECTION RESULT WITHIN

AT INTERVAL DO A REPETITIVE INSPECTION DO A SPECIAL DETAILED INSPECTION OF THE HOLES AT THRESHOLD DETAILED IN PARA. 1.E.(2)

YES

DETAILED IN PARA. 1.E.(2) FOR THE CRACKED FRAME(S)

ON NON−REPAIRED FRAME(S)

**NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE
B_SB_532138_6_FAAA_01_03 Figure A-GFAAA - Sheet 01 HFEC Inspection Flow Chart DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 19 6

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# @A310 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A310−53−2138

DATE OF INSPECTION : INSPECTION METHOD : GENERAL INSPECTION DETAILED INSPECTION DETAILED INSPECTION VISUAL SPECIAL x RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES1 FUSELAGE (WB/LR) − VERTICAL TAIL PLANE 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE Structure.sbinspectionresult@airbus.com FAX +33 (0)5 61 93 36 14 E−mail: CENTER WING BOX (WB/LR)

YES NO RESULT OF INSPECTION CRACK ON

FRAME LEFT SIDE RIGHT SIDE

73A YES NO

DISCRIPTION OF FINDINGS

B_SB_532138_6_RAAA_01_01 Figure A-GRAAA - Sheet 01 HFEC inspection Reporting Sheet DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 20 6

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# @A310 SERVICE BULLETIN Appendix 01 - Elapsed Time Assumption

**CONF ALL

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A310−53−2138**

ON DOOR 833 MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 3.75 2.75 STEPS

0.50 0.50

10 0 INSPECTION DOOR 843 0.50 0.50

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 **NOTE:** PER

1

1

: : SB ELAPSED TIME (HOURS) 2 4 6 8 12

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. REMOVE FRAME LININGS

ON DOOR 843 0.50 0.50 1 REMOVE FRAME LININGS INSPECTION DOOR 833 0.50 0.50 1

ON DOOR 833 0.75 0.75 1 INSTALL FRAME LININGS INSTALL FRAME LININGS 0.75 0.75 1 ON DOOR 843 CLOSE UP 0.25 0.25 1

B_SB_532138_6_AAAA_01_02

Figure A-GAAAA - Sheet 01 Gantt chart DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A310 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - AFT SECTION - INSPECT PAX DOOR FRAME HOLES AT FR73A 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(s): 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.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 1 6

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# @A310 SERVICE BULLETIN QUALITY PERCEPTION FORM 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 4321 - Quality rating of the Accomplishment Instructions 4321 - Quality rating of the Illustrations 4321 - 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 Operator Supplied X Mod/Inspection X Manpower X Industry support 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 CEDEX FRANCE Attn : SEM4 Service Bulletins Management FAX : (33) 5 61 93 42 51 Or via your Resident Customer Support Office.

DATE: May 28/14 SERVICE BULLETIN No.: A310-53-2138 REVISION No.: 00 - May 28/14 Page: 1 6

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