# A 300 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.

# A 300 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

# A 300 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.

# A 300 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.

# A 300 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.

# A 300 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

# A 300 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

# A 300 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

# A 300 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

# A 300 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),

# A 300 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.

# A 300 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.

# A 300 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

# A 300 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 Prin ted in France START



### Figure 5 Flowchart DO AN INSPECTION AT THE THRESHOLDS AND INTERVALS LISTED IN PARAG RAPH 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 PARAG RAPH 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 

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Printed m FrsnceA300 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 

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### 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



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### 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 4SERVICE 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