# GA300 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS INDUSTRIE CUSTOMERSERVICES DIRECTORATE 1Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEXFRANCE Tel : 

### (33) 561-93-33-33 Telex : AIRBU 530526 F TITLE : WINGS- CENTERWINGBOX- INSPECT CENTERWINGBOTTOMSKIN FOR

CORROSIONAT RIB 1. MODIFICATION No. NONE(INSPECTION) ATASYSTEM : 57 This page transmits Revision No. 01 of Service Bulletin No. A300-57-0204.
ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous revision. HISTORY OFPREVIOUS REVISIONS No previous revisions.
REASON Revision No. 1 issued to inform the operators that the compliance has changed into mandatory, clarify the permissible limits of rework and update the effectivity.

SERVICE BULLETIN SUMMARY Page 1 of 4 - Para. REASON, Airworthiness Directive No. 97-006-210(B)

added. Page 

### 2 - Para. EFFECTIVITY, customers updated.

Para. COMPLIANCE, Recommended becomes Mandatory.
SERVICE BULLETIN Pages 1of 101 to 3- Para. l.A.(2), effectivity updated. PROPRIETARY RIGHTS statement added. Page 6 :., Para. l.B.(5), Airworthiness Directive No. 97-006~21&B) added.
5 DATE : Dee O4/95 SERVIC;BULLETIN No. : 

### A300-57-0204 REVISION.No. : 01 - Apr 

### 02/99 PAGE: 1 of 2
Printed inFrancePage 8

Page 9 Page 40 Page 11 Page 17 Page 19 Page 20 Pages 21 thru 23 Page 31-32 Page 101 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

- Para l.C.(3)(a)(b), permissible rework limits clarified and NOTEadded. Para. l-D., sentence updated and sentence concerning the approval for a possible adaptation added.

- Para. l.G.(2), reference modified. Para. l-I., SRMreference'added. Para. 1-J., MPDreference modified.

- Para. Z.A., WARNINGadded.

- Para. 2.B.(l)(a), application of Mat. No. 13-002 cancelled.

- Para. 2-B.(2)(a), application of Mat. No. 13-002 cancelled.

- Para. 2.8.(2)(b), application of Mat. No. 13-002 cancelled.

- Para. 2.B.C3), text and references modified, application of Mat. No. 13-002 cancelled.

- Figure 5, Views Aand'B minimum thicknesses clarified. NOTE2 updated.

- Para. 3-C., Mat. No. 13-002 deleted.
FILING INSTRUCTIONS Replace pages SUMMARY1of 4 and 2

SERVICE BULLETIN 1of 101, 2, 3, 6, 8, 9, IO, 11, 17, 19, 20, 21, 22, 23, 31-32 and 101. Put this Revision Transmittal Sheet in front of the Service Bulletin.
REVISION SEQUENCES ORIGINAL : Dee 04195 REVISION NO. : 01 - Apr 02199

DATE : Dee 04195 REVISION No. : 01 - Apr 02/99 SERVICE BULLETIN No. : A300-57-0204 PAGE: 2
Printed inFrance, AIRBUS INDUSTRIE

CUSTOMERSERVICES DIRECTORATE 

# GA300 1 Rand Point Maurice BELLONTE 31707 BLAGNACCEDEXFRANCE SERVICE BULLETIN 

### Tel : (33) 561-93-33-33 

### Telex : AIRBU 530526 F SUMMARY

This summary is for information only and is not approved for

modification on the aircraft. TITLE 

### :WINGS

- CENTERWINGBOX- INSPECT CENTER

### WINGBOTTOM

### SKINFOR 

### CORROSION

AT

### RIB.I. MODIFICATIONNo. NONE

### (INSPECTION) ATASYSTEM : 57
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES Eight operators of A300 aircraft have reported 20 cases of corrosion on the 

### lower wing root joint during scheduled maintenance. The aircraft have been in-service between 4 and 10 years. The corrosion was 

### located in the wing bottom skin inboard and outboard of the 

### external lower surface splice. Most of the corrosion was found in the area aft of FR43, 

### although some corrosion has 

### also been found forward of this area, and around the fasteners starting from the edges of the countersinks. This Service Bulletin recommends adetailed visual inspection of the wing bottom skin, inboard and outboard of the rib 

### 1external lower surface splice, between FR40 and FR47. Repair of the corrosion damage is by 

### local blend-out and spotfacing. Once the corrosion has been removed, if the corrosion damage exceeds a certain limit, there would be a reduction in strength margins which 

### could lead to cracking from the fastener holes. Non Destructive Testing or 

### detailed visual inspections are then necessary to detect the presence of cracks around the fastener holes. Afatigue program inspection has been developed in this Service 

### Bulletin to cover this possibility. Accomplishment of this Service Bulletin permits detection of corrosion in 

### the lower wing root 

### at an

### early stage. This will avoid extensive corrosion damage, resulting in extensive rework and/or repairs and possible fatigue cracks in the future. The'corrosion inspection is recommended on aircraft which have been in-service for 5years or more from the date of delivery. The inspection is to be repeated every 5years. After corrosion 

### removal, a repetitive inspection for 

### possible fatigue damage is recommended. The thresholds and 

### intervals given for the fatigue inspection depend on the results of the corrosion inspection. This Service Bulletin is rendered mandatory by Airworthiness Directive (Consigne de Navigabilite) No. 97-006-210(B).

5 DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 

### REVISIONNo. : 01 - Apr 02/99 PAGE: 1of 4
PrintedinFrance

# GA300 SERVICEBULLETIN SUMMARY EFFECTIVITY This Service 

### Bullet in is 

### applicable to the 

### following operators : AFR, AIC, AJM, AUS, IRA, ITF, JAS, KAL, TAR, THA, VIA, VSP. AZA, CAL, COA, DLH, EAL, FIN, GIA, HLF, 

### IAC, IBE, LGL, MAS, MSR, OAL, OYC, PAA, PAL, 

### PIA, RKA, SAA,

SERVICE BULLETIN TOBEACCOMPLISHED PREVIOUSLY ORSIMULTANEOUSLY None.
REFERENCES/REPERCUSSIONS TFU OEB AOT SIL. LIFE LIMIT : 

### 53-15-00-021
: None
: None
:

### 38-013
: None 

### LINEMAINTENANCE AFFECTED : NO OTHER : None
NATUREOFTHEWORK AIRCRAFT : YES EQUIPMENT : NO
COMPLIANCE

I Mandatory.

DATE : Dee 04/95 SERVICE BULLETIN No. : 

### A300-57-0204 REVISION No. : 01 - Apr 

### 02/99 PAGE: 

### 2
PrintedinFranceSERVICE BULLETIN SUMMARY MANPOWER Inspection TOTAL MANHOURS ELAPSED TIME (HOURS) 7.5 3.5
MATERIAL INFORMATION AIRCRAFT DATA None. EQUIPMENT DATA None.
APPENDICES None.

DATE : Dee O4/95 REVISION No. : SERVICE BULLETIN No. : A300-57-0204 PAGE: 3
Printed inFranceSERVICE BULLETIN SUMMARY

u ARES TOINSPECT

DATE : Dee 04195 REVISION No’. : SERVICE BULLETIN No. : 

### ASOO-57-0204 PAGE: 4AIRBUS INDUSTRIE

CUSTOMERSERVICES DIRECTORATE 

# GA300 1 Rond Point Maurice BELLONTE 31707 BLAGNACCEDEXFRANCE SERVICE BULLETIN Tel : 

### (33) 561-93-33-33 Telex : AIRBU 530526 F

TITLE : WINGS- CENTERWINGBOX- INSPECT CENTERWINGBOTTOMSKIN FOR

CORROSIONAT RIB 1. MODIFICATION No. NONE(INSPECTION) ATASYSTEM: 57

1. PLANNING INFORMATION A. EFFECTIVITY (1) Aircraft models : B2-1C, B2-203, B2K-3C, B4-2C, 84-103, B4-120, 84-203, 84-220, C4-203, F4-203. (2) Aircraft Customer and Fleet No. AFR051-054 

### 056-060 062 064 MSN

019,023,045,047 074,078,100,129,145 175 183 Kit No. Qty None of Kits

AICIOI-103 AJMOOl-004 AUSOOl 

### 003-005 177,180,190



### 127,131,109,143 134 157,196,218

.Ai!A101,102 

### 151-162 049,051

101,106,107,123,139,140 142,173,067,118,120,068 CALOOI-006 193,197,221,232,179,171 COA966-968 117,121,126 970-972 250,262,289 DLHOOI-007 

### 071,084,085,141,149,249

265 ' EAL201,202 

### 041,042 204-206 044,065,066 209,210 086,087 212 091 220,221 124,152
5 DATE : Dee 04195 SERVICE BULLETIN No. : A300-57-0204 REVISION No. : 

### 01 - Apr 

### 02/99 PAGE: 1of 101
Printed inFranceCustomer and Fleet No. EAL223-235
FIN001,002 299,302 GIAOOI-007 cm9 HLF307 083 IAC002-009 051,052 IBE251-256 130,133,135,136,156,170 281,282 076,077 IRAOOI-003 061,080,185 005,006 187,226 

## ITF034-037 027,062,097,112 042,043 050,132 092-094 057,020,017 096 012 JASOOI-009 101-108
KAL007 101,102 LGLOOI MASOOl-004

.MSR002-005 007,008 OALOOI-008 OYC201,202 204

DATE : pet 04/95 

## SERVICE BULLETIN

No.: A300-57-0204 

## SERVICE BULLETIN MSN Kit No. Qty None of Kits 154,155,158,161,204,207 211,216,220,259,261,271 274
159,164,165,166,167,168 213 215
036,038,059,060,088,111 113,026 181,182

082,089,090,160,163,176 209,244,253 256,151,169,174,110,194 239,178 031 277,292 269 073,093,095,147 116,150,199,200 240,255 046,056,058,103,105,148 184,189 079,094 128



## REVISION

No. : 01 - Apr 02/99 

## PAGE : 2
PrintedinFrance

### Customer and 

### Fleet No. PAAOOI-012 PALOOI-005 PIAOOI-004 

### 010-012 014 RKASSI-553 SAAOOl-004 051-053 101 TAR001 THAOOI-004 VIA001,002 VSPOOI-003

.Unassigned SERVICE BULLETIN MSN Kit No. Qty None of Kits 195,227,198,247,234,236 304,305,238,235,208,210 063,069,125,203,219 096,098,099,114 064,144,268 146 137,243,282 032,037,039,040 138,192,222 212 188 033,035,054,055 053,075 202,205,225
003 This Service Bulletin is applicable to A/C listed above. This document contains Airbus Industrie PROPRIETARY INFORMATION and 

### shall at all times remain the property of Airbus Industrie; no 

### intellectual property right 

### orlicence is granted by Airbus Industrie 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 notbedisclosed in 

### wholeor 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 complywith the conditions herein), without Airbus Industrie's prior written consent. (3) Spares None.

DATE : Dee04/95 SERVICE BULLETIN No. : A300-57-0204 REVISION No. :01 - Apr 02/99 PAGE: 3
PrintedinFrance

# GA300 SERVICE BULLETIN B. REASON (I) History Eight operators of A300 aircraft have reported 20 cases of corrosion in the area of the 

### lower wing root joint during scheduled maintenance. The corrosion was located 

### mainly in the wing bottom skin inboard and outboard of the 

### external lower surface splice. Most of the corrosion was found in the area aft of FR43, although corrosion has 

### also been found forward of this area. One operator of an A310 aircraft has also reported severe corrosion in the same area. 

### At one 

### location, the remaining 

### material thickness after 

### removal of the corrosion was

### only 20percent of 

### thenominal thickness. However, Airbus Industrie has reported that this aircraft had a history of 

### fluid leaks coming from the forward 

### toilet service-panel, that were not repaired. This aircraft had 

### also been stored without the correct weather protection. The operator report 

### also suggests that previous storm damage may have 

### also contributed to corrosion, as 

### large areas of missing and flaking paint were found. The corrosion was discovered on aircraft which have been in-service between 4 and 10 years. The A310 has been in-service for just over 9

### years. The corrosion initiated at the edge of the countersinks of the fasteners. The heads, or part of the heads, of some fasteners are recessed into the countersinks. This exposes the top edges of the countersinks. If the paint is damaged, the area 

### will not have the correct protection from 

### pollutants such 

### asleaking toilet 

### fluids. In 

### all the cases reported, with the exception of the A310, the corrosion was repaired 

### bylocal rework 

### (blend-out). The A310 required extensive 

### external doubler repairs. Corrosion in this area, if it is not detected and treated at an 

### early stage, can 

### leadtocostly and time-consuming repairs. (2) Objective/Action This Service 

### Bulletin recommends adetailed 

### visual inspection of the wing bottom skin, inboard and outboard of the rib 1 lower surface 

### splice, between FR40 

### andFR47.It also recommendscheckof the condition of the protective finish and renewing of protection if necessary. After the inspections and/or repairs, it is 

### recommendedto apply sealant beadsalongthejoints to prevent 

### fluids going into this area.

DATE : Dee 04/95 

### REVISIONNo. : SERVICEBULLETIN No. : A300-57-0204 

### PAGE:4
PrintedinFrance

### SERVICEBULLETIN



### (3)

(41
(5) Repair of the corrosion damage is by 

### local blend-out and spot-facing. 

### If the corrosion damage found is more than the permissible limits given in this Service Bulletin, then special 

### doubler repairs are necessary and the operators are requested to 

### contact Airbus Industrie for advice. Once the corrosion is removed, if the corrosion damage exceeds the permissible limits, there would be areduction in the strength margins which 

### would lead to cracking from the fastener 

### holes. Non Destructive Testing or detailed visual inspections are then necessary to detect the presence of cracks around the fastener 

### holes. Afatigue program inspection has been developed in this Service 

### Bulletin to cover this possibility. Advantages Accomplishment of this Service 

### Bulletin permits detection of the corrosion at an

### early stage in the area of the wing bottom skin. This 

### will avoid extensive corrosion damage, 

### resulting inextensive rework and/or repairs and 

### possible fatigue cracks inthefuture. Operational/Maintenance Consequences This Service 

### Bulletin modifies the corrosion inspection task in the A300 MPD, Section 06-07-57, Task No. 578021-0607-I. Accomplishment 

### Timescale CORROSION

INSPECTION The corrosion inspection is recommended on aircraft which' have been in-service for 5years of more from the date of 

### delivery. The inspection is to be repeated every 5years. Aircraft that have been in-service more than 5 years should be inspected within the timescaies given 

### below:

- Aircraft with more than 5years but 

### less than 15 years service 

### should beinspected not later than18months from receipt of this 

### Service Bulletin, oratthenext C-check,whichever occurs last.

- Aircraft with more than 15 years but 

### less than 20 years service 

### should be inspected not 

### later than 12 months from receipt of this Service 

### Bulletin.

- Aircraft with more than 20

### years service 

### since delivery should be 

### inspected within 6 months from receipt of this Service 

### Bulletin.

DATE : Dee 04/95 

### REVISIONNo.: SERVICEBULLETIN No. : A300-57-0204 

### PAGE:5
Printed inFrance

# 32A300 SERVICEBULLETIN FATIGUEINSPECTION The fatigue inspections, if corrosion is found to be outside the limits given in this Service 

### Bulletin, depend on the 

### results of the corrosion inspection. An

### outline is included in this Service Bulletin (Table B, Figure 4). The thresholds and intervals given for the fatigue inspection in this Service 

### Bulletin, areestablished andvalid for aircraft operating with the 

### following average airborne flight time : A300 Bl and 82 

### models 65 minutes (1.08 FH) A300 B4-100 modeLs 80 minutes (1.33 FH) A300 84-200, C4, F4 models 125 minutes (2.08 FH) Therefore, when aircraft are operating with different 

### flight times,

. inspection 

### thresholds andintervals are to be adjusted in accordance with the instructions given in the A300 SSID Section 4, Para. 4.4. For the fatigue inspection given in this Service 

### Bulletin, the Fatigue Rating (FR) to be applied is FR=0.28. 

### Additional flights flexibility for aircraft close tooroverthe threshold is notapplicable to the fatigue inspection in this Service Bulletin.



### .This Service Bulletin is rendered mandatory by Airworthiness Directive (Consigne 

### deNavigabilite) No.97-006-210(B). (6) Special Information Airbus Industrie has issued 

### several modifications to improve the resistance of the structure to corrosion. For the area of the wing 

### lower root joint, operators are 

### strongly advised tofollow the recommendations listed 

### below: If 

### replacement offasteners is needed, 

### IVD-coated fasteners are preferred to anodised MOS2coatings. After inspection and repair (if repair is necessary) 

### fill all countersinks in the area with PR1422B (Hat. No. 09-002). 

### Install all fasteners wet with PR1422B (Mat. No. 09-002). Any damage to the surface protection should be repaired at the 

### earliest opportunity.

DATE : Dee O4/95 

### SERVICEBULLETINNo. :A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE: 6
PrintedinFranceSERVICE BULLETIN Operator's attention is drawn to the recommendations of Service Information Letter (SIL) No. 38-013, for prevention of leaks from the toilet service panels.
C. DESCRIPTION To accomplish this Service Bulletin, it is necessary to : (1) Corrosion Inspection Onthe center wing bottom skin, inboard and outboard areas of rib 1 between frames 40 and 47, do adetailed visual inspection for corrosion around the fasteners and on the surface of panels without stripping off paint. (a) If no corrosion is detected : Check condition of paint finish, touch up if protection is missing or damaged. (b1 If corrosion is detected : Rework corroded areas (if necessary remove the fasteners). Check the reworked depth and compare with the permissible limits. (2) Fatigue Inspection Check the reworked depth with respect to the initial thickness of the panel and the permissible limit of the reworked depth per area previously defined. (a) Check if the reworked depth is higher than 5 %of the initial thickness of the panel and less or equal to the permissible limit of the reworked depth per area. (b) Check if the reworked depth is less or equal to 5%of the initial thickness of the panel. Cc) Check if the reworked depth is higher than the permissible limit of the reworked depth per area.

DATE : Dee 04/95 REVISION No. : SERVICE BULLETIN No. : A300-57-0204 PAGE: 7
Printed inFrance

### SERVICEBULLETIN



### (3) Replace the fasteners. Check if the remaining panel thickness is in the permissible 

### limits given for the forward and aft 

### lower surface panels. (a) If the remaining minimum panel thickness is in the permissible Limits :

- Install an oversize countersunk head fastener. (b) If the remaining minimum 

### panel thickness is not in the permissible limits 

### to install an oversize countersunk head fastener :



### -Install an oversize protruding head fastener. NOTE: The remaining minimum thickness (X1 is the 

### panel thickness

below the head of the fastener (Refer to Figure 5, Views A and B). (4) Sealing 

### (a)Apply sealant along the 

### external lower surface 

### splice and fuselage pick-up 

### angle.
D. APPROVAL The technical content of this Service Bulletin has been approved under the authority of the DGACDesign Organisation Approval No. F.JA.02. 

### If an aircraft listed in the effectivity has amodification 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 : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE: 8
PrintedinFranceSERVICE BULLETIN E. MANPOWER 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 modification, non-productive elapsed time or. administration. Inspection Gain access 

### 0.5 Inspection 

### 6.0 Close-up TOTALMANHOURS .ELAPSEDTIME (HOURS) 

### 1.0 7.5 3.5
F. MATERIAL - COSTANDAVAILABILITY None.
G. TOOLING - PRICE ANDAVAILABILITY Accomplishment of this Service Bulletin entails use of the following tools and equipment. (1) Equipment and materials for inspection ; refer to NTM51-20-13, 51-31-05 and 51-40-13. 

# I (2) Equipment and tools for repair ; refer to SRM51-30-30, 51-30-40,

51-30-45 and 51-31-00. H, WEIGHTANDBALANCE None.

DATE : Dee O4/95 SERVICE BULLETIN No. : 

### A300-57-0204 REVISION No. : 01 - Apr 

### 02/99 PAGE: 9
Printed inFrance

# SA300 SERVICE BULLETIN I. REFERENCES Aircraft Maintenance Manual (AMM) : 

### 12-11-28, 20-31-00, 24-00-00, 24-41-00, 28-00-00, 28-10-00, 28-11-14, 28-22-00 Structural I Repair Manual (SRM) : 

### 51-30-29, 51-30-30, 51-30-40, 51-30-45, 51-40-11, 51-31-00,

51-40-12, 51-40-10,

51-40-20, 51-40-21 Service Information Letter (SIL) : 

### 38-013 Non Destructive Testing Manual (NDTM) : 

### 51-20-13, Part 1 51-31-05, Part 1 51-40-13, Part 1
J. PUBLICATIONS AFFECTED I Maintenance Planning Document (MPD) : 

### 57-80-21 Task No. 

### 578021-0602-1, C57500-01-02

DATE : Dee 04/95 SERVICE BULLETIN No. : A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE: IO
PrintedinFranceSERVICEBULLETIN 2. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL 

# I WARNING : MAKESURETHATYOUOBEYALL THEWARNINGSANDALL THE CAUTIONS INCLUDED IN THEREFERENCEDPROCEDURES. Cl) Preparation (a) De-energite the aircraft electrical network and connect the aircraft to ground (Refer to AWM24-41-00 and AM\ 24-00-00, P. Block 3011. (b) Put the access platforms in position. (2) Job set-up NOTE1 : Draining of fuel tanks is not necessary to do the

corrosion inspection. However, if bolt removal is necessary, the inner and center fuel tanks must be defuelled and drained. NOTE

### 2 : The operations below are necessary only if the fasteners

are removed (Refer to Para. 2.B.C3)). WARNING : BEFOREUNDERTAKINGMAINTENANCE WORKONTHEFUEL SYSTEM,

PERSONNELMUSTRIGOROUSLYOBSERVETHEFOLLOWINGSAFETY PRECAUTIONS. THEDESCRIPTION OFTHESESAFETYPRECAUTIONS SHOULDBEREADATTHESAMETIME ASTHESPECIAL INSTRUCTIONS ANDSAFETYMEASURESCONCERNINGSPECIFIC MAINTENANCE PROCEDURESAND, IN PARTICULAR, THEFOLLOWING OPERATIONS : (a) Job set-up 1 General servicing precaution (Refer to AMM28-00-00, P. Block 

### 301). 2 Tank defueling (Refer to ARM

### 28-22-00, P. Block 

### 301). 3 Access to fuel tanks (Refer to AMM28-10-00, P. Block 

### 301). 5 Manhole cover removal (Refer to AMH28-11-14, P. Block 

### 401).

------------------------------------------------------------------------------ MANHOLECOVERREFERENCE LOCATION BETWEEN LOCATION BETWEEN L WING RWING RIBS STRINGERS -------------------------------- ---------------------------------------------- 541AB 641AB STA71 (rib 2) and STAl42 (rib 3) 8 and 11 542CB 642C5 STAfl (rib 2) and STA142 (rib 3) 13 and 16
DATE : Dee 04/95 SERVICE BULLETIN No. : 

### A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE: 11
PrintedinFrance

# GA300 SERVICE BULLETIN 1. FueL tank working area (Refer to AMM28-10-00, P. Block 301). 6 Use of fLammabLe gas detection devices (Refer to AMM28-10-00, P. BLock 301). 1 Fuel tank ventilation (Refer to AMM28-10-00, P. Block 301). (3) Standard procedures (a) If paint stripping is required (Refer to SRM51-41-50). (b) To drill and deburr the holes (Refer to SRM31-30-40). (c) Countersinking (Refer to SRM51-30-45). Cd) Data for installation and removal fasteners (Refer to SRM51-30-29 and 51-30-30). (e) To torque the standard threaded fasteners (Refer to AMM51-31-00). (f) If paint coating is required (Refer to SRM51-40-10 and 51-40-12).

DATE : Dee 04/95 

## REVISION

No.: SERVICE BULLETIN No. : A300-57-0204 PAGE: 12
hinted inFrance

# GA300 SERVICE BULLETIN 8. INSPECTION An inspection program for fatigue inspection has been established in case of corrosion finding for which avisual check or an NDTinspection is recommended at different thresholds and flight cycles intervals. NOTE: Inspection results must be reported to Airbus Industrie

(AI/SE-El) after completion, on the recording forms attached.

- In case of findings, this reporting has to be made in accordance with Service Bulletin instructions, that is to say :

. immediately (maximum within 48 hours) in case of damage which exceeds allowable or rework Limits for further action(s) before next flight.

. after completion of the corrective action when damage is either within aLLowabLe or rework Limits, or repaired in accordance with Service Bulletin instructions.

- In case of no findings, inspection record has to be sent as soon as maintenance check or visit report which involves subject Service BuLLetin has been established. (9) CORROSION

## INSPECTION Onthe center wing bottom skin, inboard and outboard areas of rib 1 between frames 40 and 47, do adetailed visual inspection for corrosion around the fasteners and on the surface of panels without stripping off paint.

. (a) If no corrosion is detected : Check condition of paint finish, touch up if necessary. 1 

## If protection is missing or damaged : 2 Apply wash primer, Mat. No. 16-020 and primer, Mat. No. 16-001. b Apply new protective coating (Refer to SRH51-40-10 and 

### 51-40-12). Next visual inspection for corrosion in 5years. 2 If protection is not missing or not damaged : Next visual inspection for corrosion in 5years.

DATE : Dee 04/95 

## SERVICE BULLETIN

No. 

## :A300-57-0204 

## REVISION

No. : 01 - Apr 02/99 PAGE: 17
Printed inFrance

# GA300 SERVICEBULLETIN (b) 

### If corrosion is detected : For the correspondence of the different reference 

### values used in this part of the inspection (W, L, Al, 

### A2, D), refer to the evaluation principle of corrosion Fig. 2. These 

### values enable to determine the rework conditions and 

### also to check the permissible limits. 

## w : Rework 

### length inflight direction L : Rework 

### length in outboard direction 

### Al : Distance between two adjacent rework areas in flight direction 

### A2: Distance between two adjacent rework areas in outboard direction 1 Remove the corrosion (Refer to SRH51-40-11). Obey the rework conditions specified 

### below. 

# I REWORK

### CONDITIONS I L/2 >41, ) and 1 Refer to Fig. 2 W/2 >40 1 I

NOTE: 

### If you find corrosion around the fasteners, remove 

### thefasteners (Refer toSRR51-30-29 

### and51-30-30). 2 Measure the reworked depth (D), do a Non-Destructive Test (NDT) (Refer to NTM51-20-13, Part 1or 51-40-13, Part I). 2 Make sure that the rework is in the permissible limits specified 

### below. 

# I REWORK

### PERMISSIBLELIMITS I W < 50 mm(1.968 in.) L < 100 mm(3.937 in.) Refer to Fig, 2 

### Al > 50mm(1.968 in.) A2 >not limited

2 If the rework is not in the permissible limits :

- Contact 

### AIB before the next flight. b If the rework is in the permissible limits :

- Continue the inspection. Refer to Para. 2.B.(2)(a).
DATE : Dee 04/95 

### REVISIONNo. 

### : SERVICE BULLETIN No. : A300-57-0204 PAGE: 18
PrintedinFrance

# GA300 SERVICE BULLETIN

.(2). FATIGUE INSPECTION In this part of the inspection, the reference value is the reuorked depth (D) (result of corrosion inspection Para. 2.8.(l)). The permissible limits (5 X, d) are reference values with respect to the initial thickness of the panel (El. Permissible limit of reworked depth CD), 5%of the initial thickness of the panels (E) (Refer to Table A, Fig. 3). Permissible Limit of reworked depth per area Cd) (Refer to Table A, Fig. 3). NOTE: According to A/C models and damaged areas, permissible

Limits of the reworked depth are specified Table A, Fig. 3. Check the reworked depth CD1with respect to the initial thickness of the panel (El, and the permissible limit of the reworked depth per area Cd) previously defined. (a) If the reworked depth CD) is higher than 5%of the initial thickness of the panel (E) and Less or equal to the permissible Limit of the reworked depth per area Cd> (Refer to Table A, Fig. 31, i.e. :

# I S%<D=d I Detect presence of crack around the fasteners and on the surface of forward and aft lower surface panels. Doa Non-Destructive Test (NDT) for fatigue damage (Refer to NTM51-31-05, Part I). 1 If crack is detected : Contact AIB before the next flight. 1. If no crack is detected : 2 Apply wash primer, Mat. No. 16-020 and primer, Mat. No. 16-001 on countersunk heads and reworked areas. h Apply new protective coating (Refer to SRM51-40-10 and 51-40-12). NOTE: Replace the fasteners if they have been removed for

the corrosion inspection (Refer to Para. 2.B.C3)).

DATE : Dee O4/95 SERVICE BULLETIN No. : A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE: 19
PrintedinFranceSERVICE BULLETIN 2 Inspection program

- Next visual inspection for corrosion in 5.years.

- Next inspection for fatigue damage (Refer 

### toTable B, Fig. 4). NOTE: According 

### toA/Cmodelsanddamaged area, the fatigue

inspection program gives the thresholds and inter'vals (FC) 

### applicable to the visual check or the Non-Destructive Test (NDT) (Refer to Table 8,

. Fig. 4). 

### (b) If the reworked depth CD) is 

### less or 

### equal to 5%of the initial thickness of the panel (E) (Refer to Table A, Fig. 31, i.e. : 

# I I
Apply wash primer, Mat. No. 16-020 and primer, Mat. No. 16-001. Apply new protective coating (Refer to SRM51-40-10 and 51-40-12). NOTE

### :Replace the fasteners if they have been removed for

the corrosion inspection (Refer to Para. 2.8.(3)). Next visual inspection for corrosion in 5years. Cc> If the reworked depth CD) is higher than the permissible limit of the reworked depth per area Cd) (Refer to Table A, Fig. 31, i.e. : 

# I D>d
Contact AIB before next 

### flight.

DATE : Dee 04195 SERVICE BULLETIN No. : A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE: 20
PrintedinFrance

# GA300 SERVICE BULLETIN (3) Replace the fasteners. Replace fasteners of damaged holes when sitting is not correct or/and the fasteners have been removed for rework. The reference 

### value is the remaining thickness of the panel (X1. The permissible remaining thickness varies depending on the fastener 

### replacement area. Permissible remaining minimum thickness (X1 for the forward 

### lower surface 

### panel :3mm(0.118 in.).

.Permissible remaining minimum thickness (X1 for the aft 

### lower surface 

### panel :5mm(0.196 in.). NOTE: The remaining minimum thickness (X1 is the panel'thickness 

### below the head of the fastener (Refer to Figure 5, Views A and 6). 

### CAUTION: BEFOREYOUDOTHENEWCOUNTERSINK ORTHESPOTFACING FOR

THENEWFASTENER (REFERTOFIG. 51, DOACHECKOFTHE REMAINING THICKNESS (X) REFERTONONDESTRUCTIVE TEST (NDT) (REFER TONTM51-20-13, PART 1OR51-40-13, PART1). (a) 

### If the remaining minimum 

### panelthickness is inthepermissible limits : - Install an oversize countersunk head fastener. (Refer to Fig. 5, View A1
1FWDLOWERSURFACEPANEL1

Dothe subsequent steps to fastener. and /I


### install anoversize 

### countersunk head
1 Drill and deburr the 

### holes (Refer to SRN51-30-40). 1 Dothe new countersink for an oversize countersunk head fastener (Refer to SRM51-30-45). 

### 3 Do

### wetassembly of 

### all parts and fasteners to be installed with Mat. No. 09-025 (Refer to SRN51-40-20 and 51-40-21). 5 Torque standard threaded fasteners (Refer to SRH51-31-00).

DATE : Dee O4/95 SERVICE BULLETIN No. :

### A300-57-0204 REVISION No. : 01 - Apr 02/99 PAGE:

### 21
Printed inFrance

# GA300 SERVICE BULLETIN 2 Apply wash primer, Mat. No. 16-020 and primer, Mat. No. 16-001 on countersunk heads and reworked areas. NOTE: According to A/C 

### models and damaged area, for each

type of existing fastener to be replaced, refer to Figures 6, 7, 8 and 9and associated tables which give the alternative fastener identification (1st oversize or 2nd oversize). 

### fi Apply sealant Mat. No. 09-002 on the head of the fasteners. Make sure that the 

### sealant does not come out of the skin (Refer to Fig. 5, View A).
z Apply new protective coating (Refer to SRN51-40-10 and 51-40-121. (b> 

### If the remaining minimum panel thickness is not in the permissible limits to 

### install an oversize countersunk head fastener : - Install an oversize protruding head fastener. (Refer to Fig. 5, View B)

Dothe subsequent steps 

### to install an oversize protruding head fastener. 1 Drill and deburr the holes (Refer to SRN51-30-40). 2 Doa spotfacing to insure a good seating for an oversize protruding head fastener. 

### 2 Do

### wetassembly of 

### all parts and fasteners 

### to be 

### installed with Mat. No. 09-025 (Refer to SRN51-40-20 and 51-40-21). 4 Torque standard threaded fasteners (Refer to SRN51-31-00). 2 Apply wash primer, Mat. No. 16-020 and primer, Mat. No. 16-001 on countersunk heads and reworked areas. NOTE: According to A/C models and damaged area, for each

type of existing fastener to be replaced, refer to Figures 6, 7, 8 and 9 and associated 

### tables which give the alternative fastener identification (1st oversize or 2nd oversize).

DATE : Dee 04/95 

### SERVICEBULLETINNo.: A300-57-0204 

### REVISIONNo. : 01 - Apr 02/99 PAGE: 22
Printed inFrance

# GA300 SERVICE BULLETIN 6 Apply sealant Mat. No. 

### 09-002 on the head of the fasteners. Make sure that the sealant does not come out of the skin (Refer to Fig. 5, View B). 1 Apply new protective coating (Refer to SRM51-40-10 and 

### 51-40-12). (c) Close-up 1 Make sure that the work areas are 

### clean and clear of 

### tools and other items of equipment. 

### 2 Install the manhole covers (Refer to AMM28-11-14, P. 

### Block 401). 

### 3 Fill the fuel tank (Refer to AMM12-11-28, P.

### Block 1). 3 Make an inspection for 

### leaks of the manhole covers. (4). Sealing 

### (a)Apply alayer of 

### sealant Mat. No. 

### 09-002 

### alongtheexternal lower surface splice and 

### fuselage pick-up 

### angle.
C. TESTS None.
DI_CLOSE-UP (I) Make sure that the work areas 

### areclean and 

### clear of 

### tools and other items of equipment. (2) Remove the access platforms. (3) De-energize the aircraft 

### electrical circuits and disconnect the aircraft 

### electrical ground-connection (Refer to AMW24-41-00 and AMM

### 24-00-00, P. Block 

### 301). (4). Write in 

### theapplicable aircraft records that you have done 

### all the work given in this Service Bulletin.

DATE : 'oec 

### 04/95 REVISION No. : 01 - Apr 02199 PrintedinFranceSERVICE BULLETIN No. : 

### A300-57-0204 PAGE: 

### 23SERVICE BULLETIN


# 0 A

MANHOLE COVER 

# /

FWO LhWER

SURFACE PANEL MANHOLE COVER 541~S/641~~

AREASTO INSPECT 

# -A

EXTERNAL LOWER SURFACE SPLICE

Center Wing Bottom Skin Inboard and Outboard

Areas to Be Inspected

Figure 1
DATE : Dee 04195 

## SERVICE BULLETIN

No.:A300-57-0204 REVISION

Ntq.: PAGE: 24 PrintedinFranceSERVICE BULLETIN

INBOARD AREA

i 

# I

_--_I 

# =/p-%7+++ 1 -I- + t I\+++p,+ + I + + + + +

LATTICE FLANGE 45 ----

STIFFENER 45.1
_

LATTICE FLANG

STIFFENER 46.1 ---- I,
!IEXTERNAL LOWER SURFACE SPLICE

SECTION 

### AA

DATE : Dee 

### 04195 REVISION No. : AFT LOWER supK


# IREWORK PERMISSIBLE LIMITS I

LEGEND : W: REWORK LENGTH INFLIGHT DIRECTION L: REWORK LENGTH INOUTBOARD DIRECTION Al: DISTANCE BETWEEN TWOADJACENT REWORK AREAS INFLIGHT DIRECTION A2: DISTANCE BETWEENTWO ADJACENT REWORK AREASINOUTBOARD DIRECTION 0: REWORKED DEPTH E: INITIAL THICKNESS OFTHE PANEL 

### Evaluation Principle of Corrosion

Figure 2
SERVICE BULLETIN No. : A300-57-0204

PAGE: 25-26
Printed inFra~yc