A300 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 1 

Printed in France 

AIRBUS 

CUSTOMER SERVICES DIRECTORATE 

1 Rond Point Maurice BELLONTE 

31707 BLAGNAC CEDEX FRANCE 

Tel: (33) 5 61-93-33-33 

Telex: AIRBU 530526 F 

MODIFICATION No. : NONE ATA SYSTEM : 57 

TITLE : WINGS – FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS 

 This page transmits revision No. 07 of Service Bulletin A300-57-0116. 

 ADDITIONAL WORK 

 No additional work is required by this revision for aircraft inspected by any 

 previous revision. 

 REASON

 This Service Bulletin is issued at revision 07 to inform Operators that the 

 inspection is reinstated. Also a new Extended Service Goal (ESG), and 

 inspection thresholds and intervals with Flight Hours (FH) conversion figures 

 have been added to the Accomplishment Timescale. 

 CHANGES

SUMMARY: 

 . AIRBUS address has been amended. 

 . New Summary added. 

SERVICE BULLETIN: 

. AIRBUS address has been amended. 

- PLANNING INFORMATION 

- EFFECTIVITY 

. Para. (1) Effectivity has been updated. 

 . Para. (2)(a) Effectivity has been updated. 
A300 

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 2 

Printed in France 

 . Para. (2)(b) Effectivity has been updated. 

 . Para. (2)(c) Effectivity by MSN and Kit/Configuration has been added. 

 - DESCRIPTION 

. Text has been amended to show the ESG and inspection thresholds and 

 intervals with Flight Hours (FH) conversion figures. 

 - APPROVAL 

 . Approval statement has been amended. 

 - FIGURE 5 

 . Flowchart added for clarity. 

 ACCEPTANCE/REJECTION LETTER: 

 . AIRBUS address has been amended. 

FILING INSTRUCTIONS

1. Remove and destroy pages 1, 2, 3, 4, 5, 6 and 11 of the Service Bulletin and the 

Acceptance/Rejection Letter. 

2. Insert pages 1, 2, 3, 4 and 5 of the Summary, pages 1, 2, 3, 4, 5, 6, 7, 7a, 11 

and 12 of the Service Bulletin and the Acceptance/Rejection Letter. 

Put this Revision Transmittal Sheet in front of the Service Bulletin. 

HISTORY OF PREVIOUS REVISIONS

This is only applicable for Revision 07 and subsequent. If information is required 

for revisions issued previous to this, please check your copies of Revision 

Transmittal Sheet or contact AIRBUS. 

REVISION SEQUENCE 

ORIGINAL : Feb 25/83 

REVISION No. : 01 – Aug 27/83 

REVISION No. : 02 – Apr 24/84 

REVISION No. : 03 – Jul 20/84 

REVISION No. : 04 – Aug 13/86 

REVISION No. : 05 – Jul 10/89 

REVISION No. : 06 – Jul 16/93 

REVISION No. : 07 – Sep 19/11
A300 

SERVICE BULLETIN 

SUMMARY 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 1 

Printed in France 

 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 : 57 

TITLE : WINGS – FLAP BEAM 2 INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS 

MODIFICATION No. : NONE. 

REASON/DESCRIPTION/OPERATIONALCONSEQUENCES

Calculations, confirmed by fatigue and fail safe testing, show that transverse 

cracking may occur at the bolt holes of the flap beam members and light alloy side 

members. 

During fatigue testing the flap beam under test developed cracks at the steel base 

member and light alloy side members lower flanges at approx. 43,000 simulated 

flights and failure occurred at approx. 48,000 simulated flights. 

Modification 04740H0842 (Service Bulletin A300-57-0128) introduces a life extension 

of the flap beam by the removal of any incipient damage and the fitting of larger 

diameter bolts. If no cracks are found during the first inspection at 15,000 Flight 

Cycles (FC), this modification may be embodied as long as 16,700 Flight Cycles (FC) 

have not been exceeded. 

Modification 05815H0968 (Service Bulletin A300-57-0141) introduces oversized 

transition fit bolts in cold expanded holes in order to increase the fatigue life 

of the flap beam base and side members. 

If no cracks are found, this modification may be embodied at any time after the 

first inspection at 15,000 Flight Cycles(FC). 

This Service Bulletin is mandatory as per a Consigne de Navigabilite No. 86-187-

076(B) issued by DGAC. 
A300 

SERVICE BULLETIN 

SUMMARY 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 2 

Printed in France 

Early detection of cracks is beneficial as significant cracking in this area would 

necessitate very extensive and costly repairs. The inspections must be done no 

later than the thresholds which follow: 

A flap beam 2, inspection for transverse cracking using NDT 

techniques is required upon completion: 

 - 15,000 FC, 16,900 FH (for A300B2 aircraft) 

- 15,000 FC, 20,500 FH (for A300B4-100 aircraft) 

- 15,000 FC, 34,000 FH (for A300B4-200 aircraft) 

- 16,200 FC, 22,200 FH (for A300B4-200 aircraft) with an 

 Average Flight Time (AFT) of less than 1.5 hrs. 

With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an AFT of 

 less than 1.5 hrs. 

These intervals apply provided that no cracks are found. 

When Modification 04740H0842 (Service Bulletin A300-57-0128) is embodied the next 

 inspection is required not later than a further: 

 - 12,000 FC, 13,500 FH (for A300B2 aircraft) 

- 12,000 FC, 16,400 FH (for A300B4-100 aircraft) 

- 12,000 FC, 27,200 FH (for A300B4-200 aircraft) 

- 12,900 FC, 17,700 FH (for A300B4-200 aircraft) with an 

 AFT of less than 1.5 hrs. 

With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an AFT of 

 less than 1.5 hrs. 

These intervals apply provided that no cracks are found. 

When Modification 05815H0968 (Service Bulletin A300-57-0141) is embodied (and no 

 bolts larger than 7/16 inch dia. are fitted) the next inspection is required not 

 later than a further: 

 - 33,000 FC, 37,200 FH (for A300B2 aircraft) 

- 33,000 FC, 45,200 FH (for A300B4-100 aircraft) 

- 33,000 FC, 74,900 FH (for A300B4-200 aircraft) 

- 35,600 FC, 48,800 FH (for A300B4-200 aircraft) with an 

 average flight time (AFT) of less than 1.5 hrs. 
A300 

SERVICE BULLETIN 

SUMMARY 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 3 

Printed in France 

With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an average 

 flight time (AFT) of less than 1.5 hrs. 

 These intervals apply provided no cracks are found and that no bolt larger than 

 7/16 inch diameter is fitted. 

 When Modification 05815H0968 (Service Bulletin A300-57-0141) is embodied (and some 

 15/32 inch diameter bolts are fitted) the next inspection is required not later 

 than a further: 

 - 22,000 FC, 24,800 FH (for A300B2 aircraft) 

- 22,000 FC, 30,100 FH (for A300B4-100 aircraft) 

- 22,000 FC, 49,900 FH (for A300B4-200 aircraft) 

- 23,700 FC, 32,500 FH (for A300B4-200 aircraft) with an 

 average flight time (AFT) of less than 1.5 hrs. 

With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an average 

 flight time (AFT) of less than 1.5 hrs. 

These intervals apply provided no cracks are found. 

 

Where cracks are found during the initial or repetitive inspections, the limits as 

defined in Figs. 4 and 5 of this Service Bulletin are to be applied and all 

inspection results transmitted to the AI/ST1, whether cracks are within limits or 

not, on copies of Figs. 1 to 4 of this Service Bulletin using these as reporting 

forms. 

Revision 07 of this Service Bulletin has been issued to reinstate the inspection 

requirement which was previously cancelled by the embodiment of Modification 

05815H0968 (Service Bulletin A300-57-0141). Changes to the inspection schedule were 

also included to account for aircraft operations to the applicable Extended Service 

Goal (ESG), and inspection thresholds and intervals with Flight Hours (FH) 

conversion figures. 
A300 

SERVICE BULLETIN 

SUMMARY 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 4 

Printed in France 

EFFECTIVITY

This Service Bulletin is applicable to these operators: 

50W, 69X, A2S, AFG, BCS, DHL, F2I, FLM, IAW, IRA, IRB, IRM, KZU, MIX, MNB, MSR, 

NTR, OHY, RUN, SOP, TDX, TNO, TSY 

SERVICE BULLETINS TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY

None 

REFERENCES/REPERCUSSIONS

TFU : 572000007 

OEB : None 

AOT : None 

SIL : None 

LIFE LIMIT : None 

LINE MAINTENANCE AFFECTED : None 

NATURE OF THE WORK

AIRCRAFT : Yes 

EQUIPMENT : No 

 HARD : No 

 SOFT : No 

 OBRM : No 

COMPLIANCE

Mandatory 
A300 

SERVICE BULLETIN 

SUMMARY 

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 5 

Printed in France 

MANPOWER

 Aircraft 

Total Manhours : 6.0 

Elapsed Time (Hours) : 5.0 

MATERIAL INFORMATION

None 

APPENDICES

None
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 1 

Printed in France 

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 : 57 

TITLE : WINGS – FLAP BEAM 2 – INSPECTION OF FLAP BEAM BASE AND SIDE MEMBERS. 

MODIFICATION NO. : None 

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain 

the property of AIRBUS; no intellectual property right or license 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 

B2-1C, B2-203, B2K-3C, B4-103, B4-120, B4-203, B4-2C, C4-203, F4-203 

(2) Aircraft 

(a) Effectivity by MSN 

The Service Bulletin is applicable to aircraft MSN: 

0003 0019 0041 0044 0045 0047 0053 0055 0063 0073 0074 0075 0078 

0079 0080 0082 0083 0084 0085 0090 0093 0094 0095 0100 0101 0105 

0107 0116 0117 0121 0123 0124 0125 0126 0128 0129 0133 0134 0135 
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 2 

Printed in France 

0136 0137 0138 0139 0141 0147 0148 0149 0150 0151 0152 0154 0155 

0156 0157 0160 0170 0173 0175 0176 0180 0183 0184 0185 0187 0189 

0190 0192 0196 0199 0200 0203 0204 0208 0210 0211 0212 0216 0218 

0219 0220 0226 0227 0234 0235 0236 0239 0243 0244 0247 0249 0250 

0255 0256 0259 0261 0265 0271 0274 0277 0289 0292 0299 0302 0304 

(b) 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 further 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 

 

 50W 0003 

 69X 0073 

 A2S 0063 

 AFG 0180 0190 

 BCS 0095 0116 0148 0150 0152 0184 0189 

 0199 0208 0219 0220 0234 0235 0236 

 0250 0259 0274 0289 

 DHL 0084 0085 0141 0149 0249 0265 

 F2I 0079 0083 0093 0094 0128 0133 0135 

 0136 0137 0156 0170 0243 

 FLM 0082 0151 0176 0256 

 IAW 0239 

 IRA 0080 0139 0173 0185 0187 0226 

 IRB 0299 0302 

 IRM 0055 0090 0160 0175 0204 0244 

 KZU 0041 0044 0101 0117 

 MIX 0125 0134 0157 0196 0203 0218 
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 3 

Printed in France 

 OPERATOR MSN 

 MNB 0019 0047 0123 0212 0277 0292 0304 

 MSR 0200 0255 

 NTR 0124 0155 0210 0227 0247 0261 

 OHY 0138 0192 

 RUN 0075 0105 0107 0121 0147 0154 0183 

 SOP 0126 

 TDX 0053 0100 0211 0216 0271 

 TNO 0045 0074 0078 

 TSY 0129 

(c) Effectivity by MSN and Kit/Configuration 

 None 

(3) SPARES 

 None 

B. REASON

(1) Calculations, confirmed by fatigue and fail safe testing, show that

 transverse cracking may occur at the bolt holes of the flap beam 

 members and light alloy side members. 

(2) During fatigue testing the flap beam under test developed cracks at 

 the steel base member and light alloy side members lower flanges at 

 approx. 43,000 simulated flights and failure occurred at approx. 

 48,000 simulated flights. 

(3) Modification 04740H0842 (Service Bulletin A300-57-0128) introduces 

 a life extension of the flap beam by the removal of any incipient 

 damage and the fitting of larger diameter bolts. If no cracks are 

 found during the first inspection at 15,000 Flight Cycles (FC), 
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 4 

Printed in France 

 this modification may be embodied as long as 16,700 Flight Cycles 

 (FC) have not been exceeded. 

(4) Modification 05815H0968 (Service Bulletin A300-57-0141) introduces 

 oversized transition fit bolts in cold expanded holes in order to 

 increase the fatigue life of the flap beam base and side members. 

 If no cracks are found, this modification may be embodied at any 

 time after the first inspection at 15,000 Flight Cycles (FC). 

(5) This Service Bulletin is mandatory as per a Consigne de 

 Navigabilite No. 86-187-076(B) issued by DGAC. 

C. DESCRIPTION

 Early detection of cracks is beneficial as significant cracking in this 

 area would necessitate very extensive and costly repairs. The inspections 

 must be done no later than the thresholds which follow: 

(1) A flap beam 2, inspection for transverse cracking using NDT 

techniques is required upon completion: 

- 15,000 FC, 16,900 FH (for A300B2 aircraft) 

- 15,000 FC, 20,500 FH (for A300B4-100 aircraft) 

- 15,000 FC, 34,000 FH (for A300B4-200 aircraft) 

- 16,200 FC, 22,200 FH (for A300B4-200 aircraft) with an 

 Average Flight Time (AFT) of less than 1.5 hrs. 

 With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an AFT of 

 less than 1.5 hrs. 

These intervals apply provided that no cracks are found. 

(2) When Modification 04740H0842 (Service Bulletin A300-57-0128) is 

 embodied the next inspection is required not later than a further: 

 - 12,000 FC, 13,500 FH (for A300B2 aircraft) 

- 12,000 FC, 16,400 FH (for A300B4-100 aircraft) 

- 12,000 FC, 27,200 FH (for A300B4-200 aircraft) 

- 12,900 FC, 17,700 FH (for A300B4-200 aircraft) with an 

 AFT of less than 1.5 hrs. 
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 5 

Printed in France 

 With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an AFT of 

 less than 1.5 hrs. 

 These intervals apply provided that no cracks are found. 

(3) When Modification 05815H0968 (Service Bulletin A300-57-0141) is 

 embodied (and no bolts larger than 7/16 inch dia. are fitted) the 

 next inspection is required not later than a further: 

 - 33,000 FC, 37,200 FH (for A300B2 aircraft) 

- 33,000 FC, 45,200 FH (for A300B4-100 aircraft) 

- 33,000 FC, 74,900 FH (for A300B4-200 aircraft) 

- 35,600 FC, 48,800 FH (for A300B4-200 aircraft) with an 

 average flight time (AFT) of less than 1.5 hrs. 

 With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an average 

 flight time (AFT) of less than 1.5 hrs. 

 These intervals apply provided no cracks are found and that no bolt 

 larger than 7/16 inch diameter is fitted. 

(4) When Modification 05815H0968 (Service Bulletin A300-57-0141) is 

 embodied (and some 15/32 inch diameter bolts are fitted) the 

 next inspection is required not later than a further: 

 - 22,000 FC, 24,800 FH (for A300B2 aircraft) 

- 22,000 FC, 30,100 FH (for A300B4-100 aircraft) 

- 22,000 FC, 49,900 FH (for A300B4-200 aircraft) 

- 23,700 FC, 32,500 FH (for A300B4-200 aircraft) with an 

 average flight time (AFT) of less than 1.5 hrs. 

 With repeat inspections at intervals not exceeding: 

 - 1,500 FC, 1,600 FH (for A300B2 aircraft) 

- 1,500 FC, 2,000 FH (for A300B4-100 aircraft) 

- 1,500 FC, 3,400 FH (for A300B4-200 aircraft) 

- 1,600 FC, 2,200 FH (for A300B4-200 aircraft) with an average 

 flight time (AFT) of less than 1.5 hrs. 

 These intervals apply provided no cracks are found. 
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 6 

Printed in France 

(5) Where cracks are found during the initial or repetitive 

 inspections, the limits as defined in Figs. 4 and 5 of this Service 

 Bulletin are to be applied and all inspection results transmitted 

 to the AI/ST1, whether cracks are within limits or not, on copies 

 of Figs. 1 to 4 of this Service Bulletin using these as reporting 

 forms. 

(6) Revision 07 of this Service Bulletin has been issued to reinstate 

 the inspection requirement which was previously cancelled by the 

 embodiment of Modification 05815H0968 (Service Bulletin A300-57-

 0141). Changes to the inspection schedule were also included to 

 account for aircraft operations to the applicable Extended Service

 Goal (ESG), and inspection thresholds and intervals with Flight 

 Hours (FH) conversion figures. 

D. APPROVAL

 Approved under EASA Design Organisation Approval No. EASA.21J.031. 

 If an aircraft listed in the effectivity has a modification or repair 

 that is not of AIRBUS origin, and which effects 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. 

E. MANPOWER

 Manhours (each flap beam) 

 Gain Access 2 

 Ultrasonic inspections 2 

 Close-up 2

 TOTAL MANHOURS 6 

 ELAPSED TIME (hours) 5 

 NOTE: This Service Bulletin is written for an aircraft in a maintenance 

 condition. The Manhours/Elapsed Time estimates do not include the 

 time to prepare for the inspection, non-productive elapsed time or 

 administration. 

F. MATERIAL – COST AND AVAILABILITY

 None 

G. TOOLING – PRICE AND AVAILABILITY

 None 
A300 

SERVICE BULLETIN 

DATE Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

 

REVISION No. : 07 Sep 19/11 PAGE : 7 

Printed in France 

H. WEIGHT AND BALANCE

 Not changed 

I. REFERENCES

 Aircraft Maintenance Manual (AMM 27-51-65 Page Block 401 

 Non-Destructive Testing Manual (NTM) Part 4, 57-25-11 

 57-25-12 

 Service Bulletin (SB) A300-57-0128, A300-57-0141 

J. PUBLICATIONS AFFECTED

 None 
. . 

2. 

%)A300 

SERVICE BULLETIN 

ACCOMPLISHHENT INSTRUCTIONS 

A. INSPECT FLAP BEANS 2 FOR CRACKING 

(1) Gain access to flap beams 2 LH and RH. Refer to AM 

27-51-65 Page Block 401 for removal of fairings. 

(21 Refer to NTII, Part 4, Ultrasonic Techniques 57-25-11 

and 57-25-12 and carry out work detailed therein. 

(3) Yhere cracks are found refer to Fig. 4 of this bulletin for 

limitations and repeat inspection frequencies. 

B. CLOSE UP 

Cl) Hake certain that the work areas are clean and clear of 

tools and miscellaneous items of equipment. 

(2) Refer to AM 27-51-65, Page Block 401 and replace fairings. 

(31 Enter details of this inspection in the technical records 

of the aircraft. 

(4) Notify all findings including nil results to AI/ST1 on 

the forms provided in this bulletin. 

I 

7 DATE: FEB 25183 SERVICE BULLETIN NO.: A300057-116 

REVISION NO.: 6-JUL 16/93 PAGE: 7 

hinlad h FIJ~C~ 
fDA300 

SERVICE BULLETIN 

Record crack positions and lengths 

in Base Members on this form and Fig.2 

a 

u I- 

-a cl 

Figure 1 - Flap Track Base Member, Tracks 2 

7 DATE: FEB 25183 SERVICE BULLETIN NO.: A300-57-116 

I REVISION NO.: 6- JUL 16/93 PAGE: 8 

printed h Fr- 
DA300 

SERVICE BULLETIN 

0 0 0 

1 

0 

Q 

I 0 

0 

4 

.o 

0 

4 

0 

0 

c 

0 

0 

t 

0 

0 

cr 

C 

1 

I 

9 

, 

Q 

4 

h 

4 

4 

b 

4 Cl A 

Figure 2 - Flap Track Base Herbers, Tracks 2 

7 DATE: FEB 25183 SERVICE BULLETIN NO.: A300-57-116 

I REVISION NO.: 6- JUL 16/93 PAGE: 9 

PhnbdhFra- 
SERVICE BULLETIN 

Record crack positions and lengths in Side Members on this fora 

figure 3 - Flap Track 2, Light Alloy Side Nesrbers 

7 DATE: FEB 25183 SERVICE BULLETIN NO.: A300-57-116 

I 

REVISION NO.: 6- JUL 16/93 PAGE: 10 

Prided h Fru# 
GA300 

SERVICE BULLETIN 

LIGHT ALLOY 

SIDE r(t.rreER 

SlfEL - 

SlRAPS I 

=I’ 

-, 

! 

I STELL 

SIRAPS 

SIX WCBER 

I 

STEEL BASE MMLR / 

F16.4, Section thru’ Flap Beam 2 Assembly 

The lover half of the flap bear structure constitutes a Tension Boor assembly 

made froa the following elements: Tuo Light Alloy Side Hembers, a Steel Base 

Herber and four Steel Straps, two each side as illustrated above. 

Yhen cracks are found the following limitations apply:- 

DESCRIPTION ReDeat inspections 

1. A crack in either side 250 flights 

aember or base rerber to edge 

or up to 4 II beyond bolt hole. 

2. Crack in either side member Replace irrediately 

or base member greater than 

4 IA beyond bolt hole. 

7 DATE: FEB 25f83 SERVICE BULLETIN NO.: A300-57-116 

I REVISION NO.:6- JUL 16/93 PAGE: 11 

printed in FfaM 
 A300 

SERVICE BULLETIN

DATE: Feb 25/83 SERVICE BULLETIN No. : A300-57-0116 

REVISION No. : 07 Sep 19/11 PAGE : 12 

Printed in France

START 

Figure 5 

Flowchart 

DO AN INSPECTION AT THE 

THRESHOLDS AND 

INTERVALS LISTED IN 

PARAGRAPH 1.C. (1)

PRE MODS 

04740 AND 

05815? 

POST MODS 

04740 AND 

05815? 

POST MOD 

05815 (some 

with 7/16 

in. Bolt 

max)?

DO AN INSPECTION AT 

THE THRESHOLDS AND 

INTERVALS LISTED IN 

PARAGRAPH 1.C. (2)

DO AN INSPECTION AT THE 

THRESHOLDS AND 

INTERVALS LISTED IN 

PARAGRAPH 1.C. (3) 

DO AN INSPECTION 

AT 250 FC 

INTERVALS 

WAS A 

CRACK 

FOUND?

HAS THE 

AIRCRAFT 

ACCUMULATED 

LESS THAN 

15,000 FC?

IS THE 

CRACK 

OVER 4MM?

CONTACT AIRBUS 

HAS MOD 05815 BEEN 

EMBODIED?

DO MOD 05815 

YES 

NO 

NO NO 

NO 

NO 

YES 

YES 

YES 

YES 

YES 

YES 

NO 

POST MOD 

05815 (some 

with 15/32 

in. Bolt 

max)? 

DO AN INSPECTION AT THE 

THRESHOLDS AND 

INTERVALS LISTED IN 

PARAGRAPH 1.C. (4) 

NO 

YES 
AIRBUS m 

t/l/ 

INDUSTRIE APPENDIX A TO 

SE /‘,300-57-l 16 

A300 NONDESTRUCTIVE TESTING MANUAL 

PART 4 - ULTRASONIC 

SSI No.57-11-04, 57-11-06, 57-11-08, 57-11-10, 57-11-12 

1. COMPONENT OR AREA TO BE INSPECTED 

A. Steel base member on flap track beams No.2 thru 6, LH and RH. 

2. DESCRIPTION OF POSSIBLE DAMAGE 

A. Cracks in base member, propogating inboard or outboard from bolt holes. 

3. RELATED DOCUMENTS 

A. Aircraft Maintenance Manual Chapter 27-51-65, Page Block 401, for removal/ 

installation of fairings. 

B. NTM Chapter 51-20-00, Ultrasonic Testing. 

4. EQUIPMENT AND MATERIALS 

A. This technique was devised using a Krautkramer USL38 ultrasonic instrument, 

but any suitable ultrasonic instrument may be used provided it satisfies 

the requirements of this technique. 

(I> Probe : Miniature 70 degree, 5 mHz. 

(2) Connecting cable. 

(3) Couplant oil or grease. 

5. PREPARATION FOR INSPECTION 

A. Remove flap track fairings No.2 thru 6. 

NOTE : Leave flaps in extended position. 

B. Clean area to be inspected. 

C. Remove any flaking or damaged paint to ensure a smooth surface. 

6. INSTRUMENT CALIBRATION 

A. Connect 700 angle probe to the instrument. 

B. Select IOOmm (3.937 in.> test range and switch instrument on. 

C. Select a suitable bolt hole in the base member to act as a calibration 

datum and apply couplant. The hate selected must provide a strong 

reflection. 

PART 4 

57m25 41 

Page 1 
AIRBUS &-’ 

ks 

NMJSTRIE 

A300 NONDESTRUCTIVE TESTING MANUAL 

D. Using the datum hole adjust the position of the probe until a maximum 

reflection is achieved from the hole, this may necessitate the probe 

overlapping the countersunk bolt head (Ref. Fig.1, Detail C and 9) and 

adjust the instrument gain control to bring the reflection to fuLL 

screen height. Note the position of the reflection on the instrument 

time base and the position of the probe in relation to the hole 

(Ref. Fig.2, Detail Dl). 

7. INSPECTION PROCEDURE 

A. On completion of the calibration procedure perform the following :- 

(11 SeLect an appropriate bolt hole and apply couptant. 

(2) Couple probe to base member adjacent to the bolt hole as in 6.D. 

(3) Slide the probe to the Left and right of the hole in turn at each 

position scanning the suspect area at the transverse axis of.the 

hole. (Ref. Fig.2, Detail D2). 

(4) Repeat (11, (2) and (31 for all. affected bolt holes. 

(5) Record all cracks and where possible their Lengths before proceeding 

to the next bolt hole. 

PART 4 

57 m2541 

Page 2 
AIRBUS s INDUSTRIE 

A300 NONDESTRUCTIVE TESTING MANUAL 

NOTE I- REFER TO PART7 57-25-11 PAGES 1 TO 3 

FOR VISUAL INSPECTION 

\ 

--PROBE 

FLap Track Beam No.2 thru 6 

Figure 1 

PART 4 

57m2541 

Page 3 

Printed III France 
AiRBUS m 

v 

NDUSTFE 

A300 NONDUSTRUCTIVE TESTING MANUAL 

0 D 

02 

‘1 , 

PROBE DIRECTION OF SCANNING DIRECTKIN DIRECTION OF SCANNING 

OF CRACK 

INDICATION FROM POSlTlON Dl 

0 1 2 3 4 5 6 7 0 9 10 0 1 2 3 I 5 6 7 6 9 10 

DEFECT INDICATION FROM PDSITION D2 

0 I1 I2 I3 I4 I5 

PART 4 

FLap Track Beam No.2 thru 6 - Details 

Figure 2 57m2541 

Page 4 

PA...,4 .- E.---a 
AIRBUS s WWUSTRIE 

A300 NoNbESTRUCTIVE TESTING MANUAL 

APPENDIX B TO 

SB A300-57-116 

PART 4 - ULTRASONIC 

SSI No. 57-11-04, 57-11-06, 57-11-08, 57-11-10, 57-11-12 

1. COMPONENT OR AREA TO BE INSPECTED 

Aluminium alloy side member on flap track beams No.2 thru 6, LH and RH. 

2. DESCRIPTION AND POSSIBLE DAMAGE 

Cracks i'n the s@e member , propogating inboard or outboard from bolt holes. 

3. RELATED DOCUMENTS 

A. Aircraft Maintenance Manual, Chapter 27-51-65, Page Block 401, for 

removal/installation of fairings. 

B. NTM Chapter 51-20-00, Ultrasonic Testing. 

4. EQUIPMENT AND MATERIALS 

A. This technique was devised using a Krautkramer USL38 ultrasonic instrument, 

but any suitable ultrasonic instrument may be used provided it satisfies 

the requirements of this technique. 

(I) Probe : Miniature top entry 45 degree, 5 mHz. 

(2) Connecting cable. 

(3) Couplant oil or grease. 

5. PREPARATION FOR INSPECTION 

A. 

B. 

C. 

Remove flap track fairings No.2 thru 6. 

NOTE : Leave flaps in extended position. 

Clean area to be inspected. 

Remove any flaking or damaged paint to ensure a smooth surface. 

6. INSTRUMENT CALIBRATION 

A. Connect 45O angle probe to the instrument. 

B. Select IOOmm (3.937 in.) test range and switch instrument on. 

C. Select a suitable bolt hole in the side member to act as a calibration 

datum and apply couplant. The hole selected must provide a strong 

reflection from the bottom of the hole at the side member/strap interface. 

(Ref. Fig.1, Detail C). 

PART 4 

57m2542 

Page 1 

Printed m Frsnce 
A300 NONDESTRUCTIVE TESTING MANUAL 

D. Using the datum hole adjust the position of the.probe until a maximum 

reflection is achieved from the bottom of the hole and adjust the 

instrument gain control to bring the reflection to full screen height. 

Note the position of the reflection on the instrument time base, and 

the position of the probe in relation to the hole (Ref. Fig.2, Detail Dl). 

7. INSPECTION PROCEDURE 

A. On completion of the calibration procedure, perform the following :- 

(1) Select an appropriate bolt hole and apply couplant. 

(2) Couple probe to side member adjacent to the bolt hole as in 6.D. 

(3) Slide the probe to the left and right of the hole in turn at each 

position scanning the suspect area at the transverse axis of the hole. 

(Ref. Fig.2, Detail 02). 

(4) Repeat (I), (2) and (3) for all affected bolt holes. 

(5) Record all cracks and where possible their lengths before proceeding 

to the next bolt hole. 

PART 4 

574512 

Page 2 
AIRBUS m INWSTRIE 

v 

A300 NONDESTRUCTIVE TESTING MANUAL 

NOTE:- REFER TO PART 7 57-X-11 F%GES 1 TO 3 

FOR VISUAL INSPECTION 

Flap Track Beam No.2 thru 6 

Figure 1 

PART 4 

57@25=12 

Page 3 
AIRBUS f$lNDL!STRlE 

A300 NONDESTRUCTIVE TESTING MANUAL 

02 

Dl I I 

DIRECTION OF 

CRACK 

PROBE 

. 

DlRECTlON OF SCANNING PROBE DIRECTION OF SCANNING 

INDICATION OF HOLE FROM POSITION 01 DEFECT INDICATION FROM POSITION D2 

0123456 7 8 9 10 0 1 2 3 4 5 6 7 8 9 10 

PART 4 

FLap Track Beam No.2 thru 6 - Details 

Figure 2 57m2542 

Page 4 
SERVICE BULLETIN 

AIRBUS INDUSTRIE 

SUPPORT DIVISION DIRECTORATE 

1 ROND POINT RAURICE BELLONTE 

31707 BLAGNAC CEDEX FRANCE 

Tel.: (33) 61-93-33-33 

Telex: AIRBU 530526 F 

MODIFICATION NO.: 0000 (INSPECTION1 ATA SYSTEA: 57 

T I T L E: YINGS - FLAP BEAM 2 - INSPECTION OF FLAP BEAM BASE 

BEBBERS. 

AND SIDE 

IS BEING HEREYITH SUBMITTED TO YOU FOR REVIEY 

Please fill: . ..REJECTED 

. ..YILL BE EHBODIED 

. ..EFFECTIVITY 

This SB can only be incorporated in your "custoaized" docurentation uithin 

he agreed time schedule in so far as this sheet is returned to us on 

purchase date and signed by a duly authorized and erpouered officer or 

representative. 

FROM : 

AIRLINE : 

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

w: 

.I........................ 

OAfE: 

. . . . . . . . . . . . . . . . ...*. 19.. 

Please return to : 

AIRBUS INDUSTRIE 

PRODUCT SUPPORT DIRECTORATE 

1 ROND POINT HAURICE BELLONTE 

31707 BLAGNAC CEDEX FRANCE 

Att.: AI/SP - Technical Publications 

Department 

DATE: FEB 25183 SERVICE BULLETIN NO.: A300-57-116 

I REVISION NO.:6- JIJL 16/93 PAGE: 1 of 1 

Pmhzd k France